c5 c10 c12 c14 c15 c16 c17 c18 c20 c25 c35 c40 c90 c100 c110 c120 c130 c140 c150 c152 c160 c170 c180 c190 c192 c200 c210 c220 c230 c240 c250 c260 c270 c280 c290 c300 c310a c310b c310c c310d c314a c314b c314c c314d c320a c320b c320c c324a c324b c324c c330 c332 c340 c350 c360 c370 c380 c390 c400 c410 c420 c430 c440 c450 c460 c490 c510a c510b c510c c510d c510e c510f c602 c604 c606 c608 c610 c612 c614 c616 c620 c640 c652 c654 c660 eof 2001021300034 20010213 00034 EU 2001 2 13 20001227SH025 1 19960329 G 2731 PC43402A0 WIRE EXTRA EA300 EA300 70218DI EU TRIM CONTR LEVER BENT B UV4R K NONE O OTHER IN INSP/MAINT 1 SO 15 301NL 459 059 ELEVATOR TRIM FORWARD SPRING STEEL WIRE WAS FOUND BENT CLOSE TO THE TRIM CONTROL LEVER. THIS RENDERED THE SYSTEM UNUSAB LE AND UNAIRWORTHY DUE TO THE POSITION IT WAS IN WHEN IT WAS BENT REMAINS. THE PILOT COULD POSSIBLY NOT KNOW IT WAS BEN T AS IT FEELS FREE WHEN OPERATED IN THE COCKPIT. (X) 1 M 7 1 3O NC A67EU 2001021300035 20010213 00035 EU 2001 2 13 20001227SH026 1 19960627 G 2731 PC43402A0 WIRE EXTRA EA300 EA300 70218DI EU TRIM CONTR LEVER BENT B UV4R K NONE O OTHER IN INSP/MAINT 1 SO 15 303NL 400 056 ELEVATOR TRIM FORWARD SPRING STEEL WIRE WAS FOUND BENT CLOSE TO THE TRIM CONTROL LEVER. THIS RENDERED THE SYSTEM UNUSAB LE AND UNAIRWORTHY DUE TO THE POSITION IT WAS IN WHEN IT WAS BENT REMAINS. THE PILOT COULD POSSIBLY NOT KNOW IT WAS BEN T AS IT FEELS FREE WHEN OPERATED IN THE COCKPIT. (X) 1 M 7 1 3O NC A67EU 2001021300036 20010213 00036 EU 2001 2 13 20001227SH027 1 19960627 G 2731 PC43402A0 WIRE EXTRA EA300 EA300S 1130864 EU TRIM CONTR LEVER BENT B UV4R K NONE O OTHER IN INSP/MAINT 1 SO 15 76PK 300 15 ELEVATOR TRIM FORWARD SPRING STEEL WIRE WAS FOUND BENT CLOSE TO THE TRIM CONTROL LEVER. THIS RENDERED THE SYSTEM UNUSABL E AND UNAIRWORTHY DUE TO THE POSITION IT WAS IN WHEN IT WAS BENT REMAINS. THE PILOT COULD POSSIBLY NOT KNOW IT WAS BENT AS IT FEELS FREE WHEN OPERATED IN THE COCKPIT. (X) 1 M 7 1 3O NC A67EU 2001021300037 20010213 00037 EU 2001 2 13 20001227SH028 1 19960220 G 2731 PC43402A0 WIRE EXTRA EA300 EA300 70218DI EU TRIM CONTR LEVER BENT B UV4R K NONE O OTHER IN INSP/MAINT 1 SO 15 302NL 420 062 ELEVATOR TRIM FORWARD SPRING STEEL WIRE WAS FOUND BENT CLOSE TO THE TRIM CONTROL LEVER. THIS RENDERED THE SYSTEM UNUSAB LE AND UNAIRWORTHY DUE TO THE POSITION IT WAS IN WHEN IT WAS BENT REMAINS. THE PILOT COULD POSSIBLY NOT KNOW IT WAS BEN T AS IT FEELS FREE WHEN OPERATED IN THE COCKPIT. (X) 1 M 7 1 3O NC A67EU 1996062700386 19960627 00386 SW 1996 6 27 9667 1 19960307 G 2840 222366621103 SWITCH BELL 206 206L 1181522 SW FUEL SYS FAULTY H K NONE N FALSE WARNING NR NOT REPORTED 1 FS 01 108W 52034 AIRFRAME FUEL FILTER IMPENDING BYPASS SWITCH MALFUNCTIONING. BYPASS LIGHT COMES ON AND OFF WITH NO CONTAMINATION FOUND IN FILTER. REPLACED WITH NEW FILTER. 1 G 7 1 3U H2SW 1996062700387 19960627 00387 SW 1996 6 27 9668 1 19960307 G 6310 289051098 SEAL BELL 206 206B 1181511 SW FREEWHEEL WORN EXCESS H K NONE O OTHER NR NOT REPORTED 1 FS 01 345RR 2107 PART IS WORN EXCESSIVELY. CUSTOMER COMPLAINT IS THAT ALL OF THE "2890" SERIES SEALS WITH THE BLACK MATERIAL SEEM TO WE AR DEEPER GROOVES AT A FASTER RATE THAN THE CHICAGO RAWHIDE SEALS WITH THE RED MATERIAL. 1 G 7 1 3U H2SW 1996062000439 19960620 00439 WP 1996 6 20 96ZZZM1000 1 19960416 G 5340 APB7177 TRAPEZOIDAL FTG DOUG DC10 DC1030 3023501 WP RT MLG WW CORROSION A NWAA K NONE O OTHER IN INSP/MAINT 1 GL 01 229NW 88344 23313 46551 DURING CHECK, RIGHT MLG FIXED SIDE BRACE ATTACH FITTING INBOARD ATTACH BOLT HOLE SHOWS EVIDENCE OF CORROSION IN TRAP FIT TING. REMOVED CORROSION AND REPAIRED INBOARD ATTACH HOLES IAW SRM 57-20-00 FIG 20. 2 L 7 3 4F A22WE 1996062000440 19960620 00440 WP 1996 6 20 96ZZZM1001 1 19960416 G 5340 APB7177 TRAPEZOIDAL FTG DOUG DC10 DC1030 3023501 WP LT MLG WW CORROSION A NWAA K NONE O OTHER IN INSP/MAINT 1 GL 01 229NW 88344 46551 DURING CHECK, LEFT MLG FIXED SIDE BRACE ATTACH FITTING INBOARD ATTCH BOLT HOLE SHOW EVIDENCE OF CORROSION IN TRAP FITTIN G. REPAIRED BOLT HOLE ON LEFT MLG FIXED SIDE BRACE ATTACH FITTING IAW SRM 57-20-00 FIG 20. (M) 2 L 7 3 4F A22WE 1996062000441 19960620 00441 WP 1996 6 20 96ZZZM1002 1 19960416 G 5343 ATTACH FITTING DOUG DC10 DC1030 3023501 WP RT MLG WW CORROSION A NWAA K NONE O OTHER IN INSP/MAINT 1 GL 01 229NW 88344 23313 46551 DURING CHECK, RIGHT MLG SIDE (FIXED) ATTACH FITTING INBOARD BOLT BARREL NUT HOLE IS BLEEDING RUST. REPAIRED MLG SIDE BR ACE ATTACH FITTING BARREL/NUT HOLE INBOARD SIDE IAW SRM 57-20-00 FIG 20. (M) 2 L 7 3 4F A22WE 1996062000442 19960620 00442 WP 1996 6 20 96ZZZM1003 1 19960319 G 5313 LONGERON DOUG DC10 DC1030 3023501 WP FS 1877-1893 CRACKED A NWAA K NONE O OTHER IN INSP/MAINT 1 GL 01 229NW 88344 46551 DURING CHECK, AFT BULK CARGO STRINGER 42R HAS 4 INCH CRACK AND 4 SQUARE INCHES OF INTERGRANULAR CORROSION ON INBOARD SID E OF STRINGER 42R AT SPLICE FS 1877. REMOVED CORRODED SECTION OF LONGERON 42R, FS 1877 TO FS 1893, FABRICATED LONGERON AND LONG. SPLICE AND INSTALLED PER SRM 53-10-00 FIG 2 TYPE I, INSTALLED CLASS I EXTERNAL REPAIR PER SRM 53-20-00 FIG 6 DOUBLERS AND FINGER DOUBLERS. 2 L 7 3 4F A22WE 1996062000443 19960620 00443 WP 1996 6 20 96ZZZM1004 1 19960311 G 5313 ADA7020559 LONGERON DOUG DC10 DC1030 3023501 WP FS 791-824 CORROSION A NWAA K NONE O OTHER IN INSP/MAINT 1 GL 01 229NW 46551 DURING CHECK 53 SQUARE INCHES OF INTERGRANULAR CORROSION ON LONGERON 38 LEFT AFT FS 791-798 AND AT FS 807-824, LONGERON IS IN SKIN AND LONGERON INSTALLATION. REMOVED CORROSION, FABRICATED REPAIR FITTINGS IAW SRM 53-10-00 PG 1-9 AND INSTALL ED REPAIR IAW 53-10-00. (M) 2 L 7 3 4F A22WE 1996062000444 19960620 00444 WP 1996 6 20 96ZZZM1005 1 19960416 G 5343 ATTACH FITTING DOUG DC10 DC1030 3023501 WP LT MLG WW CORROSION A NWAA K NONE O OTHER IN INSP/MAINT 1 GL 01 229NW 88344 23313 46551 DURING CHECK, TRAPEZOIDAL OUTBOARD FITTING SIDE BRACE ATTACH POINT BARREL NUT HOLE CORRODED RIGHT SIDE. REPAIRED OUTBOA RD TRAPEZOIDAL SIDE BRACE ATTACH POINT BARREL NUT HOLE IAW SRM 57-20-00 FIG 20. 2 L 7 3 4F A22WE 1996082200404 19960822 00404 NE 1996 8 22 96ZZZM1243 2 19960717 G 7320 P3 LINE BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE RT ENGINE LOOSE A AMWA A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CL CLIMB 1 CE 07 182YV UE182 FLT 5627 - AFTER TAKEOFF RIGHT ENGINE ROLLED BACK TORQUE AND THEN STABILIZED AT ABOUT 1000 FT/LBS OF TORQUE, AIRCRAFT. R ETURNED TO FIELD AT MCI. MAINTENANCE TIGHTENED P3 LINE C/W FLIGHT TEST RETURNED AIRCRAFT TO SERVICE. (M) 2 L 7 2 4T 4 T RT A24CE E26NE 1996082900638 19960829 00638 NM 1996 8 29 96ZZZM1254 1 19960731 G 3350 079123 LENS BOEING 747 747212B 1384886 NM CABIN MISSING A TWRA K NONE L NO TEST IN INSP/MAINT 1 EA 15 6186 21439 DURING DAILY CHECK, FOUND EMERGENCY LIGHT INOP AT SEAT 45C. REPLACED LAMP AND LENS ASSY. OPS CHECKED GOOD PER MM 33-51 -00 PG 501. REFERENCE TWRA96256. 2 L 7 4 4F A20WE 1996092600389 19960926 00389 EA 1996 9 26 96ZZZM1323 1 19960624 G 2133 722924E OUTFLOW VLV CNDAIR CL600 CL6001A11 1900302 EA CABIN MALFUNCTIONED A WH6A A UNSCHED LANDING O OTHER CR CRUISE 1 NE 03 601WW 158 1076 APPROX TWO HOURS INTO FLIGHT, CABIN PRESSURIZATION BEGAN TO FLUCTUATE 300 FEET IN AUTO MODE. AIR RUSHING NOISE COULD BE HEARD IN BAGAGE AREA. THE ELECTRO/PNEUMATIC OUTFLOW VALVE WAS REPLACED DURING AT 1200 HOUR INSPECTION APPROXIMATELY (8 ) FLIGHT HOURS PRIOR. PRESSURIZATION IS OK IN MANUAL MODE. AIRCRAFT DIVERTED TO BOMBARDIER IN TUCSON, AZ. OUTFLOW VLV WAS REPLACED. THE ORIGINAL INSTALLED WAS PREVIOUSLY REPAIRED FOR INTERMITTENT PRESSURIZATION FLUCTUATION. 2 L 7 2 4F RT A21EA 1996100300460 19961003 00460 NM 1996 10 3 96ZZZM1386 1 19960829 G 3350 ML7715 BULB BOEING 747 747212B 1384886 NM CABIN INOP A TWRA K NONE L NO TEST IN INSP/MAINT 1 EA 15 6186 21439 DURING DAILY CHECK, FOUND SEAT 21C EVAC LIGHT INOP. REPLACED SOCKET AND RELAMPED. OPS CHECKED NORMAL AS PER MM 33-51-0 0. REFERENCE TWRA96304. 2 L 7 4 4F A20WE 1996032200592 19960322 00592 EU 1996 3 22 96ZZZM319 1 19960218 G 2910 137311D1443 HYD LINE BAG JETSTM JETSTM3201 1500217 EU ACFT BELLY CHAFED A NVEA O OTHER J K WARNING INDICATION FLUID LOSS AP APPROACH 1 SO 03 920AE 920 FLT NR 4501 - TRI - PILOT REPORTED, THE LANDING GEAR DID NOT EXTEND AFTER SELECTING DOWN. CREW NOTICED THAT THE HYD PRE SSURE WAS AT 0 PSI AND THAT THE FLAPS WERE ALSO INOP. CREW MANUALLY EXTENDED THE GEAR AND LANDED WITHOUT FURTHER INCIDE NT. MAINTENANCE INSPECTED AND FOUND HYD LINE CHAFED NEXT TO THE RIGHT AC PACK. REPLACED AND RESECURED A NEW HYD LINE S O AS TO PREVENT FUTURE CHAFING. (M) 2 L 7 2 4T RT A56EU 1996041200496 19960412 00496 WP 1996 4 12 96ZZZM638 2 19960128 G 7260 3588941 BEARING SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE33111U 01514 WP LT GEARBOX FAILED A PNSA E ENGINE SHUTDOWN Y ENGINE STOPPAGE CR CRUISE 1 AL 03 640PA 4729 AC759B P44691 DURING CRUISE FLIGHT, LEFT ENGINE FUEL CONTROL DRIVE GEARBOX BEARING FAILED. 2 L 7 2 4T 4 T RT A8SW E4WE 1996041200509 19960412 00509 1996 4 12 96ZZZM651 4 19960218 G 6122 8210212 PROP GOV BEECH 1900 1900C 1154161 CE LT ENG LEAKING A A GPPA E ENGINE SHUTDOWN K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CE 09 34010 UC3 NR 1 ENGINE SHUT DOWN IN FLIGHT DUE TO DROPPING OIL PRESSURE. CREW DECLARED AN EMERGENCY AND LANDED WITHOUT INCIDENT. U PON INSPECTION MECHANIC FOUND PRIMARY PROP GOVERNOR LEAKING AT THE INBOARD AFT CORNER. TIGHTENED NUT CLEANED LEAK CHECK ED AND RETURNED TO SERVICE. 2 L 7 2 4T RT A24CE 1996062000481 19960620 00481 WP 1996 6 20 96ZZZM999 1 19960416 G 5343 ATTACH FITTING DOUG DC10 DC1030 3023501 WP LT MLG WW CORROSION A NWAA K NONE O OTHER IN INSP/MAINT 1 GL 01 229NW 88344 23313 46551 DURING CHECK, LEFT MLG FIXED SIDE BRACE ATTACH BOLT HOLE SHOWS EVIDENCE OF CORROSION IN TRAP FITTING. REPAIRED LEFT MLG FIXED SIDE BRACE ATTACH FITTING INBOARD BARREL NUT HOLE IAW SRM 57-20-00 FIG 20. 2 L 7 3 4F A22WE 1996031500069 19960315 00069 EU 1996 3 15 96ZZZX1017 1 19960122 G 5311 1053025152 FRAME BOLKMS 105 BO105S 5626006 EU T/R PYLON CRACKED E K NONE O OTHER IN INSP/MAINT 1 SW 03 8776 6616 S776 DURING A ROUTINE INSPECTION, THE TAIL PYLON FRAME 11L WAS FOUND CRACKED COMPLETELY THROUGH LEFT SIDE OF FRAME. THE CRAC K WAS THROUGH THE LOWER RIVET LINE AT THE ATTACHMENT OF DOUBLER PLATE, PN 105-30412.01. REPAIRED PER DER APPROVED 8110- 3. 1 G 7 2 3U H3EU 1996031500071 19960315 00071 WP 1996 3 15 96ZZZX1019 1 19960126 G 5330 369H30109 PANEL HUGHES 369 369D 4470706 WP AIRFRAME CRACKED B EOOR K NONE O OTHER IN INSP/MAINT 1 AL 03 5074R 7686 1151D DURING REMOVAL OF ENGINE, A CRACK WAS FOUND STARTING FROM THE RELIEF HOLE ON PANEL FORWARD .50 INCH AND .3750 INCH. REP AIR PANEL WITH A PATCH. IT APPEARS THE CLEARANCE BETWEEN THE RELIEF HOLE AND THE 369D23007-5 ANGLE WERE TOO TIGHT. 1 G 7 1 3U H3WE 1996031500072 19960315 00072 GL 1996 3 15 96ZZZX1020 2 19960216 G 7230 6877410 CASE HALF HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL COMPRESSOR ERODED B EOOR K NONE O OTHER IN INSP/MAINT 1 AL 03 5074R 1673 14914 1151D CAE832750 DURING ANNUAL INSPECTION, THE COMPRESSOR CASE HALVES WERE FOUND ERODED BEYOND LIMITS. CASE HALVES WERE REMOVED AND SENT IN FOR OVERHAUL. 1 G 7 1 3U 3 U H3WE E4CE 1996031500073 19960315 00073 GL 1996 3 15 96ZZZX1021 2 19960220 G 7313 6895021 NOZZLE 6898735 HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL NR 1 BURNED B EOOR K NONE O OTHER IN INSP/MAINT 1 AL 03 5074R 513 C114422 1151D CAE832750 NR 1 NOZZLE WAS REPLACED DUE TO EROSION AND CRACKING BEYOND LIMITS. NOZZLE SENT IN FOR OVERHAUL. 1 G 7 1 3U 3 U H3WE E4CE 1996031500074 19960315 00074 WP 1996 3 15 96ZZZX1022 1 19960126 G 2820 369H81443 SWITCH HUGHES 369 369D 4470706 WP FUEL BYPASS INOPERATIVE B EOOR K NONE O OTHER IN INSP/MAINT 1 AL 03 5074R 1151D DURING ENGINE REMOVAL, THE FUEL BYPASS SWITCH WAS REMOVED AND CHECKED, FOUND INOPERATIVE. 1 G 7 1 3U H3WE 1996031500075 19960315 00075 GL 1996 3 15 96ZZZX1023 2 19960126 G 7230 6871534 CHIP PLUG HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL COMPRESSOR LEAKING B EOOR K NONE K FLUID LOSS IN INSP/MAINT 1 AL 03 5074R 1151D CAE832750 DURING REMOVAL OF COMPRESSOR, CHIP PLUG FOUND LEAKING PAST THE INSULATOR. REPLACED CHIP PLUG. 1 G 7 1 3U 3 U H3WE E4CE 1996031500076 19960315 00076 GL 1996 3 15 96ZZZX1024 2 19960220 G 7250 6890040 SHIELD 6898735 HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL NR 1 TURB NOZZLE WARPED B EOOR K NONE O OTHER IN INSP/MAINT 1 AL 03 5074R 513 1151D CAE832750 DURING REPLACEMENT OF NR 1 TURBINE NOZZLE, THE NOZZLE SHIELD WAS FOUND WARPED OUT OF SHAPE. PART SENT IN FOR OVERHAUL. 1 G 7 1 3U 3 U H3WE E4CE 1996031500164 19960315 00164 SW 1996 3 15 96ZZZX1026 1 19960131 G 6510 206040339009 BEARING BELL 206 206B 1181511 SW T/R DRV SYS ROUGH B PN5R K NONE O OTHER IN INSP/MAINT 1 NM 03 527TK 1500 4198 TAIL ROTOR DRIVE SHAFT BEARINGS ROUGH. REPLACED WTIH NEW PARTS. 1 G 7 1 3U H2SW 1996031500166 19960315 00166 NE 1996 3 15 96ZZZX1028 1 19960215 G 6220 S611223022002 VERTICAL HINGE SKRSKY S61 S61A 814210C NE M/R HEAD CRACKED B JYER K NONE O OTHER IN INSP/MAINT 1 NM 09 1048Y 8116 2640 61161 CRACK FOUND DURING OVERHAUL OF MAIN ROTOR HEAD. VERTICAL HINGE WAS MAGNETIC PARTICAL. INSPECTED PER OVERHAUL MANUAL. C RACK WAS LOCATED ABOUT .75 INCH BELOW THREADED AREA IN 2.6238 BEARING JOURNAL. THE CRACK WAS ABOUT .75 INCH LONG, GOING UP THROUGH THE THREADS, AND WAS A FINE SURFACE-TYPE CRACK. 2 G 7 2 4U H2EA 1996031500167 19960315 00167 NE 1996 3 15 96ZZZX1029 2 19960201 G 7260 430110701 BEARING BELL 222 222 1182122 SW LYC LTS101 LTS101650C3 41560 NE ACCY GEARBOX DEFECTIVE D K NONE O OTHER IN INSP/MAINT 1 EA 25 29KH 2554 79K027 47053 LE41123 ENGINE REMOVED FOR PT WHEEL REPLACEMENT. DURING DISASSEMBLY, SPUR GEAR PLAY FOUND EXCESSIVE. GEARBOX DISASSEMBLED AND SPUR GEAR ASSY REMOVED. THE NR 19 BEARING HAD BEEN SPINNING IN ITS BORE, WEARING AND ELONGATING BORE. SUBMITTER RECOMM ENDS PINNING OR SECURING BEARING OUTER RACE IN CASE. 1 G 7 2 3U 3 U H9SW E5NE 1996031500169 19960315 00169 NE 1996 3 15 96ZZZX1031 1 19960116 G 6320 7635109002048 HOUSING SKRSKY S76 S76 8143010 NE SERVO MOUNT DAMAGED D K NONE O OTHER IN INSP/MAINT 1 NE 03 3856 932 REWORK PERFORMED TO SERVO MOUNT PADS BEYOND LIMITS OF OVERHAUL MANUAL SA4047-76-7-8. REWORK AREAS MEASURE IN LENGTH FRO M .063 INCH LONG TO 2.957 INCH LONG, WIDTHS MEASURE FROM .063 INCH TO .352 INCH. DEPTHS MEASURE FROM .015 INCH TO .028 INCH AND REWORKED AREAS ARE WITHIN 1 INCH OF EACH OTHER. SUBMITTER STATED, DO NOT REWORK SERVO PAD BEYOND THE LIMITS OF THE OVERHAUL MANUAL. COMPONENT WAS LAST OVERHAULED BY CANADIAN COMPONENT SERVICES ON FEBRUARY 2, 1993, AT TT OF 6,379. 5 HOURS. 1 G 7 2 3U H1NE 1996031500171 19960315 00171 SW 1996 3 15 96ZZZX1033 1 19960131 G 6320 214040810003 INDICATOR BELL 206 206L3 1182108 SW M/R XMSN FILTER DEFECTIVE B PN5R K NONE O OTHER IN INSP/MAINT 1 NM 03 617DE 1500 51138 INDICATOR EXTENDS IN COLD WEATHER GIVING FALSE INDICATION OF BYPASS CONDITION IN M/R TRANSMISSION OIL FILTER. REPLACED WITH NEW P/N INDICATOR. 1 G 7 1 3U H2SW 1996031500172 19960315 00172 SW 1996 3 15 96ZZZX1034 1 19960131 G 6510 327211 DISC ASSY BELL 206 206L3 1182108 SW T/R DRIVE CORRODED B PN5R K NONE O OTHER IN INSP/MAINT 1 NM 03 617DE 5984 51138 DISC ASSY TRAPS MOISTURE BETWEEN THE LAMINATIONS AND EVENTUALLY CAUSES CORROSION PITS IN LAMINATIONS. REPLACED WITH NEW ASSYS. 1 G 7 1 3U H2SW 1996031500173 19960315 00173 SW 1996 3 15 96ZZZX1035 1 19960131 G 6330 206033506101 RESTRAINT BELL 206 206L3 1182108 SW TRANSMISSION DEBONDED B PN5R K NONE O OTHER IN INSP/MAINT 1 NM 03 617DE 3000 51138 TRANSMISSION RESTRAINT - RUBBER SHOWING CRACKING AND DEBONDING DUE TO NORMAL WEAR AND AGE. REPLACED WITH OHC UNIT FROM LORD. 1 G 7 1 3U H2SW 1996031500174 19960315 00174 WP 1996 3 15 96ZZZX1036 1 19960122 G 6310 269A55909 CLUTCH CABLE HUGHES 269 269C 4470504 WP M/R BROKEN G A K NONE O OTHER LD LANDING 1 SW 17 363U 2044 S1568 WHILE HERDING CATTLE, PILOT LANDED TO OPEN GATE. PILOT HEARD A LOUD POP. ON INVESTIGATION, HE FOUND THE CLUTCH CABLE B ROKEN. FURTHER INVESTIGATION REVEALED THE CABLE BROKE AT SWAGED BALL END. THIS CABLE ASSY IS NOT INSPECTED UNTIL THE 4 00-HOUR INSPECTION EVENT FOR DAMAGE. RECOMMEND A TIME-LIMIT REPLACEMENT BE SET AT 1,200 HOURS. THE 400-HOUR INSPECTION REQUIRES DISASSEMBLY OF CLUTCH ASSEMBLY FOR THE COMPLETE INSPECTION OF THE CABLE. 1 G 7 1 3O 4H12 1996031500175 19960315 00175 NE 1996 3 15 96ZZZX1037 2 19960113 G 7314 430112810 FUEL PUMP BENDIX BOLKMS 117 BK117A3 5626015 EU LYC LTS101 LTS101650B1 41560 NE ENGINE LEAKAGE B A BAQR A UNSCHED LANDING Y ENGINE STOPPAGE CR CRUISE 1 EA 03 39181 129 3AFP1001B 7003 45060 INTERNAL LEAKAGE OF FUEL PUMP WASHED GREASE FROM BEARING OF FUEL CONTROL CAUSING AN ENGINE TO OVERSPEED. THERE WAS NO I NDICATION PRIOR TO THE FAILURE. THE FUEL CONTOL SEIZED AND THE NYLON COUPLING SPLINES SHEARED. 1 G 7 2 3U 3 U H13EU E5NE 1996031500176 19960315 00176 NE 1996 3 15 96ZZZX1038 2 19960119 G 7314 430112810 PUMP BOLKMS 117 BK117A3 5626015 EU LYC LTS101 LTS101650B1 41560 NE ENG FUEL LEAKAGE B A BAQR O OTHER Y K ENGINE STOPPAGE FLUID LOSS NR NOT REPORTED 1 EA 03 952CJ 500 4AFP738B 7052 45061 INTERNAL LEAKAGE OF FUEL PUMP WASHED GREASE FROM BEARING IN THE FUEL CONTROL UNIT CAUSING IT TO FAIL, CAUSING THE ENGINE TO FAIL GOING INTO AN OVERSPEED CONDITION. SUBMITTER STATED THIS HAS BEEN THE SECOND INCIDENT IN A 6-DAY PERIOD. 1 G 7 2 3U 3 U H13EU E5NE 1996031500177 19960315 00177 GL 1996 3 15 96ZZZX1039 2 19960110 G 7323 SPLINE SHAFT HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL N2 GOVERNOR CAP DETACHED D P A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CR CRUISE 1 WP 13 8625F 1338 13605 470111D CAE830515 WHILE RETURNING TO BASE DURING FLIGHT, N2 RPM DROOPED. PILOT LANDED AIRCRAFT AND REPORTED MALFUNCTION TO THE MECHANIC. UPON INSPECTION OF GOVERNOR AND ATTACHING AIR LINES, THE DRIVE SPLINE RETAINING CAP WAS FOUND DETACHED AND SMALLER SHAF T FOUND PARTIALLY FAILED AND TWISTED. 1 G 7 1 3U 3 U H3WE E4CE 1996031500178 19960315 00178 SW 1996 3 15 96ZZZX1041 1 19960201 G 6420 222012701119 HUB ASSY BELL 230 230 1182149 SW BLADE FEATHER BEARING BIND B A BAQR O OTHER F FLT CONT AFFECTED AP APPROACH 1 EA 03 231UM 843 A327 23012 DURING A FINAL APPROACH TO A ROOF-TOP HELIPAD, THE PILOT LOST ALL CONTROL OF THE TAIL ROTOR. AFTER A SUCCESSFUL LANDING AT THE AIRPORT, HE REGAINED CONTROL OF THE TAIL ROTOR. AFTER A THOROUGH INSPECTION OF THE T/R CONTROL SYSTEM, IT WAS D ETERMINED THE FEATHER BEARINGS IN THE TAIL ROTOR BLADES WERE ON A BIND. 1 G 7 2 3U NC H9SW 1996031500179 19960315 00179 WP 1996 3 15 96ZZZX1042 1 19960112 G 6310 269A55909 CLUTCH CABLE HUGHES 269 269C 4470504 WP M/R FAILED G A A UNSCHED LANDING O OTHER CR CRUISE 1 SW 17 3623T 2269 S1567 WHILE HERDING CATTLE AT 75 FEET, AGL. PILOT HEARD A LOUD BANG AND ROTOR RPM DECREASED AND ENGINE RPM INCREASED. AIRCRA FT IMPACTED GROUND CAUSING SUBSTANTIAL DAMAGE TO THE AIRCRAFT. INVESTIGATION OF THE NOISE REVEALED THE CLUTCH CABLE HAD BROKEN AT CABLE END SWAGED BALL. THIS CABLE ASSEMBLY IS NOT INSPECTED UNTIL THE 400-HOUR EVENT FOR DAMAGE. RECOMMEND A TIME-LIMIT REPLACEMENT OF 1,200 HOURS. THE 400-HOUR INSPECTION CALLS OUT FOR DISMANTLING OF THE CLUTCH ASSY FOR COMPL ETE INSPECTION OF THE CABLE. 1 G 7 1 3O 4H12 1996031500181 19960315 00181 SW 1996 3 15 96ZZZX1044 1 19960130 G 7160 222062211113 DUCT BELL 222 222U 1182140 SW LT ENG INLET DELAMINATED B A QMLR K NONE O OTHER IN INSP/MAINT 1 NM 03 911ED 5906 47 47551 DURING C/W ASB NR 222U93-34, FOUND UPPER AFT CORNER OF INLET DUCT DELAMINATED DUE TO CONTACT WITH THE COWLING DOOR. SUB MITTER SUGGESTS DUCT BE MADE OUT OF A MORE DURABLE MATERIAL LIKE STAINLESS STEEL. 1 G 7 2 3U H9SW 1996031500182 19960315 00182 SW 1996 3 15 96ZZZX1045 1 19960130 G 7160 222062211114 DUCT BELL 222 222U 1182140 SW RT ENG INLET DELAMINATED B A QMLR K NONE O OTHER IN INSP/MAINT 1 NM 03 911ED 5906 33 45771 DURING C/W ASB NR 222U-95-34, FOUND UPPER AFT CORNER OF THE INLET DUCT DELAMINATED DUE TO CONTACT WITH THE COWLING DOOR. SUBMITTER SUGGESTS DUCT BE MADE OUT OF A MORE DURABLE MATERIAL LIKE STAINLESS STEEL. 1 G 7 2 3U H9SW 1996031500365 19960315 00365 SO 1996 3 15 96ZZZX1047 2 19960223 G 8550 S123660550 HOSE CESSNA 210 T210M 2073451 CE CONT O520 TSIO520R 17040 SO WASTEGATE OIL CHAFED H K NONE O OTHER IN INSP/MAINT 1 NE 03 666SW 21062120 572351 WASTEGATE OIL RETURN HOSE CHAFED THROUGH AT FORWARD RIGHT ENGINE MOUNT. SUBMITTER STATES CORRECTIVE ACTION - CLAMP HOSE OFF FOR PROPER CLEARANCE. 1 H 7 1 3O 3 O 3A21 E8CE 1996031500366 19960315 00366 SO 1996 3 15 96ZZZX1048 2 19960227 G 8530 642619F PISTON PIPER PA34 PA34220T 7103420 SO CONT O360 TSIO360KB 17025 SO NR 2 CYLINDER RINGS BROKEN H E A ENGINE SHUTDOWN UNSCHED LANDING K FLUID LOSS NR NOT REPORTED 1 NM 09 83828 1540 348133089 315090 ENGINE LOST OIL PRESSURE DURING FLIGHT. PILOT SHUT DOWN ENGINE AND MADE UNEVENTFUL LANDING. LARGE AMOUNT OF OIL WAS FO UND UNDER THE ENGINE AND UNDER THE WING. COMPRESSION CHECK SHOWED ZERO COMPRESSION ON NR 2 CYLINDER. CYLINDER REMOVED AND DISCOVERED ALL RINGS BROKEN AND THE RING GLANDS SEVERELY BROKEN AND WORN. A SUBSTANTIAL AMOUNT OF ALUMINUM WAS FOUN D IN THE FILTER AND SCREEN. 1 L 7 2 3O 3 O A7SO E9CE 1996031500367 19960315 00367 1996 3 15 96ZZZX1049 4 19960131 G 6122 C299506B0104 CONTROL ASSY MCAULY C290D3 CESSNA 172 R172K 2072431 CE PROP GOV FROZEN D K NONE O OTHER IN INSP/MAINT 1 WP 21 7585X 2 R1723334 INSTALLED NEW CONTROL CABLE ASSY AS SUPPLIED BY CESSNA AIRCRAFT. INSTALLED AND RIGGED PER CESSNA R172K SERVICE MANUAL. ALL OPS CHECK OK ON GROUND PRIOR TO FLIGHT. RUN-UP OPS CHECK OK. FLOWN FOR 2.0 HOURS FOR ENGINE BREAK-IN. ALL OPS NO RMAL. UPON RETURN TO GROUND. OPS CHECK OF ENGINE CONTROLS REVEALED FROZEN SOLID GOVERNOR CONTROL CABLE ASSY. CABLE NR 1 RETURNED TO CESSNA FOR EVALUATION. 1 H 7 1 3O 3A17 1996031500368 19960315 00368 1996 3 15 96ZZZX1050 4 19960131 G 6122 C299506B0104 CONTROL ASSY MCAULY C29003 CESSNA 172 R172K 2072431 CE PROP GOV SEIZED D K NONE O OTHER IN INSP/MAINT 1 WP 21 7585X 2 R1723334 THIRD TIME TO INSTALL NEW CONTROL CABLE ASSY AS SUPPLIED BY CESSNA AIRCRAFT. INSTALLED AND RIGGED PER CESSNA R172K SERV ICE MANUAL. ALL OPS CHECK OK ON GROUND. RUN-UP OPS CHECK OK. FLOWN FOR 2 HOURS, NO ATTEMPT TO MOVE CONTROL WHILE IN-F LIGHT. UPON RETURN TO GROUND, GOVERNOR CONTROL CABLE ASSY FROZEN SOLID. REMOVE AND INSPECT, NO MARKS, CUTS, ABRASIONS, KINKS OR SIGNS OF OVERHEAT. SUSPECT NORMAL HEAT IN AREA CAUSING INTERNAL COMPONENTS IN CABLE TO EITHER MELT OR SWELL C AUSING CABLE CONTROL TO FREEZE UP. CABLE NR 3 RETURNED TO CESSNA FOR EVALUATION. 1 H 7 1 3O 3A17 1996031500369 19960315 00369 SW 1996 3 15 96ZZZX1051 1 19960220 G 6300 412340102101 SEAL BELL 412 412 1182202 SW DRIVE SHAFT DEBONDED B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 2FOR 11 36112 DRIVE SHAFT SEAL DEBONDED. REPLACED WITH NEW FIXTURE. 1 G 7 2 4U H4SW 1996031500370 19960315 00370 SW 1996 3 15 96ZZZX1052 1 19960201 G 6300 412340102101 SEAL BELL 412 412 1182202 SW DRIVE SHAFT SEPARATED B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 2FOR 17 36111 REPLACED WITH NEW FIXTURE. DRIVE SHAFT SEAL BOOT SEPARATION (2 EACH). 1 G 7 2 4U H4SW 1996031500371 19960315 00371 SW 1996 3 15 96ZZZX1053 1 19960220 G 6300 412040657003 COUPLING BELL 412 412 1182202 SW M/R DRIVE PITTED B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 2FOR 11 A668 36112 DRIVE SHAFT COUPLING PITTED. REPLACED WITH NEW FIXTURE. 1 G 7 2 4U H4SW 1996031500372 19960315 00372 SW 1996 3 15 96ZZZX1054 1 19960220 G 6300 214040675003 COUPLING BELL 412 412 1182202 SW M/R DRIVE PITTED B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 2FOR 13 A713 36114 INTER DRIVE COUPLING PITTED. REPLACED WITH NEW FIXTURE. 1 G 7 2 4U H4SW 1996031500373 19960315 00373 SW 1996 3 15 96ZZZX1055 1 19960220 G 6300 214040659003 COUPLING BELL 412 412 1182202 SW M/R DRIVE PITTED B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 2FOR 13 A917 36114 DRIVE SHAFT COUPLING HAS PITTED TEETH. REPLACED WITH NEW FIXTURE. 1 G 7 2 4U H4SW 1996031500374 19960315 00374 SW 1996 3 15 96ZZZX1056 1 19960220 G 6300 412340102101 SEAL BELL 412 412 1182202 SW DRIVE SHAFT DEBONDED B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 2FOR 13 36114 DRIVE SHAFT SEAL DEBONDED (2 EACH). REPLACED WITH NEW FIXTURE. 1 G 7 2 4U H4SW 1996031500375 19960315 00375 SW 1996 3 15 96ZZZX1057 1 19960220 G 6300 214040659005 COUPLING BELL 412 412 1182202 SW M/R DRIVE PITTED B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 2FOR 11 36112 DRIVE COUPLING PITTED. REPLACED WTIH NEW FIXTURE. 1 G 7 2 4U H4SW 1996031500376 19960315 00376 SW 1996 3 15 96ZZZX1058 1 19960220 G 6320 205040230003 SUN GEAR TOOTH BELL 412 412 1182202 SW TRANSMISSION FAILURE B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 900BH 1147 A2733 33195 TRANSMISSION SUN GEAR TOOTH FAILURE. REPLACED WTIH NEW FIXTURE. 1 G 7 2 4U H4SW 1996031500377 19960315 00377 SW 1996 3 15 96ZZZX1059 1 19960220 G 6220 206011105001 TRUNNION BELL 206 206B3 1181506 SW M/R ROUGH B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 221GP 520 RXFS1298 4309 M/R TRUNNION ROUGH AND BINDING. REPLACED WITH NEW FIXTURE. 1 G 7 1 3U H2SW 1996031500378 19960315 00378 1996 3 15 96ZZZX1060 4 19960131 G 3421 1113034 INDICATOR BELL 412 412 1182202 SW COCKPIT ATTITUDE STICKS B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 3292N 16 89869 36109 COCKPIT ATTITUDE INDICATOR STICKS. REPLACED WITH NEW FIXTURE. 1 G 7 2 4U H4SW 1996031500379 19960315 00379 SW 1996 3 15 96ZZZX1061 1 19960220 G 2140 205072277009 MIXING VALVE BELL 412 412 1182202 SW HEATER DEFECTIVE B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 3293G 15 GWD12874 36115 HEATER FAILED DUE TO MIXING VALVE DEFECTIVE. REPLACED WITH NEW FIXTURE. 1 G 7 2 4U H4SW 1996031500380 19960315 00380 SW 1996 3 15 96ZZZX1062 1 19960220 G 6300 214040657003 COUPLING BELL 412 412 1182202 SW M/R DRIVE PITTED B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 3293G 13 A704 36115 M/R DRIVE COUPLING PITTED. REPLACED WITH NEW FIXTURE. 1 G 7 2 4U H4SW 1996031500381 19960315 00381 SW 1996 3 15 96ZZZX1063 1 19960220 G 6300 214040659005 COUPLING BELL 412 412 1182202 SW M/R DRIVE PITTED B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 3293G 13 A977 36115 DRIVE SHAFT COUPLING PITTED. S/N A977 AND A906. REPLACED WITH NEW FIXTURE. 1 G 7 2 4U H4SW 1996031500382 19960315 00382 1996 3 15 96ZZZX1064 4 19960220 G 3460 412375013101 FDAU BELL 412 412 1182202 SW COCKPIT DEFECTIVE B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 145H 19 10015 36116 FDAU DEFECTIVE. REPLACED WITH NEW FIXTURE. 1 G 7 2 4U H4SW 1996031500383 19960315 00383 SW 1996 3 15 96ZZZX1065 1 19960220 G 2422 412075101103 INVERTER BELL 412 412 1182202 SW AC SYSTEM FAILED B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 145H 19 1052 36116 STATIC INVERTER FAILED. REPLACED WTIH NEW FIXTURE. 1 G 7 2 4U H4SW 1996031500384 19960315 00384 SW 1996 3 15 96ZZZX1066 1 19960220 G 6300 214040659005S COUPLING BELL 412 412 1182202 SW M/R DRIVE PITTED B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 145H 16 A984 36116 DRIVE SHAFT COUPLING (2 EACH PITTED). S/N A984 AND A981. REPLACED WITH NEW FIXTURE. 1 G 7 2 4U H4SW 1996031500385 19960315 00385 SW 1996 3 15 96ZZZX1067 1 19960220 G 6300 214040657003 COUPLING BELL 412 412 1182202 SW M/R RIVE PITTED B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 145H 16 A719 36116 DRIVE SHAFT COUPLING (2 EACH) PITTED. S/N A719 AND A714. REPLACED WITH NEW FIXTURE. 1 G 7 2 4U H4SW 1996031500386 19960315 00386 NE 1996 3 15 96ZZZX1068 1 19960212 G 6520 S613566602 HOUSING S61356660011 SKRSKY S61 S61N 8142104 NE T/R GRBOX MT CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 05 612RM 2228 A16926 61744 DURING ROUTINE INSPECTION, A .75 INCH LONG CRACK WAS FOUND IN THE FORWARD RT ATTACHMENT MOUNT. THIS HOUSING IS MANUFACT URED FROM MAGNESIUM WHICH REQUIRES A ROUTINE INSPECTION. C/W SB 61B35-48 REPLACES THIS ITEM WITH AN ALUMINUM HOUSING WI TH MUCH THICKER MOUNT LUGS. 2 G 7 2 4U 1H15 1996031500387 19960315 00387 NE 1996 3 15 96ZZZX1069 1 19960212 G 6330 S61207626113 FITTING S6120762651 SKRSKY S61 S61N 8142104 NE INTERMED G/B MT CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 05 612RM 61744 DURING ROUTINE INSPECTION, A CRACK IN THE WEB ON THE INTERMEDIATE GEARBOX MOUNT WAS FOUND. THE CRACK IS .75 INCH LONG A ND EXTENDS FROM THE WEB RADIUS TO A FASTENER HOLE. THIS WEB HAS BEEN REPLACED PER SB 61B20-31, WHICH CHANGES THE MATERI AL TO 7075-T73. 2 G 7 2 4U 1H15 1996031500388 19960315 00388 SW 1996 3 15 96ZZZX1070 1 19960220 G 6330 222031605105 FLEXTURE ASSY BELL 222 222 1182122 SW XMSN MOUNT DEBONDED B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 51Q 917 BW567 47151 TRANSMISSION MOUNT FLEXTURE DEBONDED. S/N BW567 AND BW570. REPLACED WITH NEW FIXTURE. 1 G 7 2 3U H9SW 1996031500389 19960315 00389 SW 1996 3 15 96ZZZX1071 1 19960220 G 2841 206075740107 INDICATOR BELL 206 206B 1181511 SW FUEL QUANTITY STICKS B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 221GP 185 4309 FUEL INDICATOR STICKS. REPLACED WITH NEW FIXTURE. 1 G 7 1 3U H2SW 1996031500390 19960315 00390 1996 3 15 96ZZZX1072 4 19960220 G 3421 1113034 INDICATOR FRCHLD 42 42 3370702 EA COCKPIT FLAG INOP B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 92130 20 89849 36118 ATTITUDE DIRECTOR FLAG INOPERATIVE. REPLACED WITH NEW FIXTURE. 1 H 7 1 3R ATC242 1996031500391 19960315 00391 SW 1996 3 15 96ZZZX1073 1 19960220 G 6300 214040657003 COUPLING BELL 412 412 1182202 SW M/R DRIVE PITTED B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 92130 20 A732 36118 DRIVE SHAFT COUPLING PITTED (2 EACH). S/N A732 AND A730. REPLACED WITH NEW FIXTURE. 1 G 7 2 4U H4SW 1996031500392 19960315 00392 1996 3 15 96ZZZX1074 4 19960220 G 3416 1003511424 ALTIMETER BELL 412 412 1182202 SW COCKPIT ERRATIC B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 92130 19 152022 36118 ALTIMETER ERRATIC. REPLACED WITH NEW FIXTURE. 1 G 7 2 4U H4SW 1996031500393 19960315 00393 SW 1996 3 15 96ZZZX1075 1 19960220 G 3230 222031206105 BELLCRANK BELL 230 230 1182149 SW MLG BEARING FAULTY B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 230GN 35 23034 MLG BELLCRANK BEARING FAULTY. REPLACED WTIH NEW FIXTURE. 1 G 7 2 3U NC H9SW 1996031500394 19960315 00394 SW 1996 3 15 96ZZZX1076 1 19960220 G 3222 222336001123 STRUT BELL 230 230 1182149 SW NLG LEAKING B GS1R K NONE K FLUID LOSS IN INSP/MAINT 1 EA 03 230GN 38 0021 23034 NLG STRUT LEAKING. REPLACED WTIH NEW FIXTURE. 1 G 7 2 3U NC H9SW 1996031500395 19960315 00395 SW 1996 3 15 96ZZZX1077 1 19960220 G 6410 222016001111 BLADE BELL 230 230 1182149 SW T/R DENTED B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 230GN 81 A554 23034 T/R BLADE DENTED. S/N A554 AND A535. REPLACED WITH NEW FIXTURE. 1 G 7 2 3U NC H9SW 1996031500396 19960315 00396 WP 1996 3 15 96ZZZX1078 1 19960120 G 3610 6876667 TUBE HUGHES 369 369D 4470706 WP AIR DISCHARGE WORN SLEEVE B S EOOR K NONE O OTHER IN INSP/MAINT 1 AL 03 4571V 11214 97697 490487D DURING ANNUAL INSPECTION, THE ENGINE AIR DISCHARGE TUBES (2 EACH) WERE FOUND WORN BEYOND LIMITS AT THE FORWARD SEAL RETA INING SLEEVE. REPLACED AIR TUBES. 1 G 7 1 3U H3WE 1996031500397 19960315 00397 WP 1996 3 15 96ZZZX1079 1 19960120 G 3610 6876667 TUBE HUGHES 369 369D 4470706 WP AIR DISCHARGE WORN SLEEVE B EOOR K NONE O OTHER IN INSP/MAINT 1 AL 03 4571V 11214 97647 490487D DURING ANNUAL INSPECTION, THE ENGINE AIR DISCHARGE TUBES (2 EACH) WERE FOUND WORN BEYOND LIMITS AT THE FORWARD SEAL RETA INING SLEEVE. REPLACED AIR TUBES. 1 G 7 1 3U H3WE 1996031500398 19960315 00398 GL 1996 3 15 96ZZZX1080 2 19960120 G 7323 369A795155 ROD END HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL GOV/THROTTLE STIFF B EOOR K NONE O OTHER IN INSP/MAINT 1 AL 03 4571V 4904870 DURING ANNUAL INSPECTION, THE ROD ENDS FROM THE GOVERNOR THROTTLE SHAFT TO THE BELLCRANK WERE FOUND EXTREMELY STIFF WITH SOME TEFLON RESIDUE COMING FROM THE ROD ENDS. REPLACED PARTS. 1 G 7 1 3U 3 U H3WE E4CE 1996031500399 19960315 00399 NE 1996 3 15 96ZZZX1081 2 19960216 G 7321 0164348230 FUEL CONTROL SKRSKY S76 S76A 8143006 NE TMECA ARRIEL ARRIEL1S 60030 NE ENGINE MALFUNCTION D A K NONE O OTHER IN INSP/MAINT 1 NE 03 900SK 2900 B678B 760304 3078 AFTER ENGINE START, ALL OPS NORMAL IDLE PLUS OR MINUS 2 PERCENT. ADVANCED POWER LEVER TO FLY POSITION, ENGINE RPM STAYE D AT IDLE 50 PLUS OR MINUS 2 PERCENT. STAYED IN FLY POSITION FOR 10 MINUTES, NO CHANGE IN RPM. BROUGHT POWER LEVER BA CK TO IDLE FOR 10 MINUTES, THEN ADVANCED POWER LEVER TO FLY AND ENGINE RESPONDED NORMALLY. NOTE: AIRCRAFT WAS PARKED O UTSIDE IN BELOW ZERO TEMPS FOR OVER 3 HOURS. TEMPS APPROX 10-20 DEGREES FAHRENHEIT. 1 G 7 2 3U 3 U H1NE E19EU 1996031500400 19960315 00400 SW 1996 3 15 96ZZZX1082 1 19960214 G 6220 204011302105 FRAME 212010300001 BELL 212 212 1181420 SW STABILIZER BAR MISMANUFACTURED B L A ALGR K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 EAFS187 DURING INSTALLATION OF STABILIZER BAR, MECHANIC NOTICED THE BOLT THAT ATTACHES DAMPER CONTROL ARM TO THE STABILIZER BAR FRAME WAS TOO SHORT. FURTHER INVESTIGATION REVEALED THE STABILIZER FRAME WAS APPROXIMATELY .125 INCH THICKER AT THE ATT ACHMENT POINT THAN OTHER FRAMES. STABILIZER BAR ASSY HAD JUST BEEN REASSEMBLED AFTER INSTALLING NEW FRAMES. FRAME RETU RNED TO MFG, WHO, IN TURN, SHIPPED A REPLACEMENT FRAME. WHEN RECEIVED, REPLACEMENT FRAME WAS ALSO TOO THICK IN THE SAME AREA. BOTH FRAMES PURCHASED DIRECTLY FROM BELL HELICOPTER. 1 G 7 1 4U H4SW 1996031500632 19960315 00632 SO 1996 3 15 96ZZZX1083 2 19960217 G 8550 PUMP CESSNA 210 T210H 2073438 CE CONT O520 TSIO520R 17040 SO ENGINE OIL MISOVERHAULED D E ENGINE SHUTDOWN J W WARNING INDICATION INADEQUATE Q C IN INSP/MAINT 1 SW 13 65093 21061844 293717R ON THE 6TH RUN FOR GROUND ADJUSTMENTS, OIL PRESSURE DROPPED TO 30 THEN 10 PSI AND ENGINE SECURED. REPEATED ATTEMPTS TO PRIME OIL SYSTEM, COULD NOT GET OIL PRESSURE UP. PUMP WAS REMOVED AND INSPECTED WITH NO OBVIOUS DEFECTS. OIL PAN WAS R EMOVED AND PICK-UP TUBE INSPECTED WITH NO DEFECTS. ONLY DEFECT NOTED WAS THAT OIL PUMP WAS PROBABLY INCORRECTLY SILK TH READED ALLOWING AIR TO BE SUCKED INTO SYSTEM AROUND ORIFICE. AFTER REINSTALLATION OF COMPONENTS, NO FURTHER PROBLEMS EN COUNTERED AND ACFT FLOWN WITH NO PROBLEMS. 1 H 7 1 3O 3 O 3A21 E8CE 1996031500633 19960315 00633 SO 1996 3 15 96ZZZX1084 2 19960101 G 8530 641917 CYLINDER CESSNA 150 150G 2071816 CE CONT O200 O200A 17020 SO NR 4 EXH PORT CRACKED D A UNSCHED LANDING E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 CE 01 3824J 15065124 648346A PILOT REPORTED A ROUGH ENGINE AND A PARTIAL LOSS OF POWER. A PRECAUTIONARY LANDING MADE ON A COUNTY ROAD. NO DAMAGE TO AIRCRAFT, PERSONNEL, OR PROPERTY. FOUND NR 4 CYLINDER CRACKED AFTER CYLINDER REMOVED. CRACK WENT THROUGH VALVE GUIDE BOSS ALLOWING GUIDE TO MOVE IN OPERATION, UNSEATING VALVE. ENGINE TT, 6,193 HOURS. 1 H 7 1 3O 3 O 3A19 E252 1996031500634 19960315 00634 CE 1996 3 15 96ZZZX1085 1 19960227 G 7602 5038901021 CONTROL CABLE BEECH 55 95B55 1152706 CE MIXTURE END PARTED H JT8S K NONE O OTHER IN INSP/MAINT 1 GL 05 255WP 18 TF38 RT MIXTURE CONTROL ASSY SWAGED END PARTED FROM ROD ON ENGINE END OF CABLE. 1 L 7 2 3O 3A16 1996031500636 19960315 00636 1996 3 15 96ZZZX1087 4 19960206 G 2215 2N5632 TRANSISTOR KS271A PIPER PA31 PA31310 7103103 SO PRIMARY SERVO FAILED D K NONE O OTHER IN INSP/MAINT 1 AL 03 27987 31641 317912054 PRIMARY SERVO TRANSISTOR HAS FAILED IN THREE DIFFERENT SERVOS, OVERHAULED BY TWO SEPARATE VENDORS. CONTACT WITH ALLIED SIGNAL DID NOT RECOGNIZE THE USE OF THIS TRANSISTOR. SUBMITTER STATED MOTOROLA REPLACEMENTS BE USED. 1 L 7 1 3O RT A20SO 1996031500637 19960315 00637 CE 1996 3 15 96ZZZX1088 1 19960223 G 7603 C299500401 CONTROL CABLE CESSNA 177 177RG 2073709 CE THROTTLE FAILED B TRKR O OTHER O OTHER AP APPROACH 1 SO 15 2575V 3037 177RG0622 PILOT REDUCED POWER TO LAND WITH NO RESPONSE TO ENGINE. LANDED UNEVENTFULLY. THROTTLE CONTROL CABLE BROKEN. 1 H 7 1 3O A20CE 1996031500638 19960315 00638 EA 1996 3 15 96ZZZX1089 2 19960205 G 8520 SL72877 LIFTER PIPER PA28 PA28180 7102808 SO LYC O360 O360A4A 41514 EA CAM FOLLOWER FAILED D A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CR CRUISE 1 SW 15 711BD 786 287205271 L1664636A ENGINE POWER LOST IN-FLIGHT. AIRCRAFT LANDED WITHOUT INCIDENT. ENGINE REMOVED AND DISASSEMBLED. FIVE OF EIGHT LIFTER BODIES BROKEN AT THE CAM FOLLOWING FACE. SUBMITTER'S OPINION IS THAT ONLY ONE FAILURE OCCURRED. THE OTHER DAMAGE WAS D UE TO FOD FROM THE FIRST FAILURE. 1 L 7 1 3O 3 O 2A13 E286 1996031500639 19960315 00639 SO 1996 3 15 96ZZZX1090 1 19960215 G 3230 3815100 ROD ASSY PIPER PA32 PA32R300 7103213 SO NLG BENT D K NONE O OTHER IN INSP/MAINT 1 NE 01 5910V 32R7780377 ROD DISCOVERED BADLY BENT DURING ANNUAL INSPECTION. PILOT PREVIOUSLY REPORTED AND HAD AIRCRAFT INSPECTED FOR 'HARD LAND ING'. ROD BENT IN FORWARD PORTION. 1 L 7 1 3O A3SO 1996031500642 19960315 00642 SO 1996 3 15 96ZZZX1093 2 19960226 G 7310 LINE CESSNA 421 421C 2076016 CE CONT O520 GTSIO520L 17032 SO NR 3 CYLINDER B-NUT LOOSE D K NONE K FLUID LOSS IN INSP/MAINT 1 NM 11 211TB 421C0903 685024 NR 3 CYLINDER FUEL INJECTOR LINE ATTACH B-NUT, BACKED OFF A DISTRIBUTOR VALVE CAUSING FUEL LEAK. 1 L 7 2 3O 3 O A7CE E7CE 1996031500643 19960315 00643 NM 1996 3 15 96ZZZX1094 1 19960201 G 5102 S272700 GAUGE HP25 RAVEN S55 S55A 7480402 NM BURNER PSI FAILED B RG1R K NONE O OTHER IN INSP/MAINT 1 SW 01 4226F 448 HP25116 S55A1035 FAILURE OF PRESSURE GAUGE DURING FLIGHT AS A RESULT OF EXCESSIVE USE OF THE METERING VALVE. A SERVICE BULLETIN ADDRESSE S THIS ISSUE, BUT WAS NEVER INSTALLED ON THIS PARTICULAR BURNER. 1 B 0 0 A15CE 1996031500645 19960315 00645 NM 1996 3 15 96ZZZX1096 1 19960131 G 3243 4408B4 CYLINDER SCOTT CHRIS HUSKY A1 221020X NM BRAKE OUTLET FAILED D O OTHER K FLUID LOSS LD LANDING 1 NM 11 2898D 1823 1019 AFTER LANDING, PILOT COMPLAINED OF NO LEFT BRAKE. INSPECTION REVEALED LEFT BRAKE MASTER CYLINDER OUTLET THREAD BOSS HAD SEPARATED FROM THE MASTER CYLINDER, DISCONNECTING THE LEFT BRAKE HOSE. 1 H 7 1 3O NC A22NM 1996031500646 19960315 00646 CE 1996 3 15 96ZZZX1097 1 19960218 G 2434 DGR3 CONTROL UNIT CESSNA 172 172RG 2072438 CE ALTERNATOR FAILED B DJFR O OTHER H ELECT. POWER LOSS-50 PC NR NOT REPORTED 1 EA 23 9343D 4310 172RG1128 PILOT REPORTED LOSS OF ELECTRICAL POWER. AFTER LANDING, UNCOWLED ENGINE AND FOUND THE ACU WAS SMOKED. TROUBLESHOT AND FOUND THE ALTERNATOR WINDINGS OPEN. INSTALLED A NEW ACU AND INSTALLED A SERVICEABLE ALTERNATOR, PN C611503-0102. PERFO RMED GROUND RUN, OPERATIONAL CHECK OF THE ALTERNATOR CHARGING SYSTEM FOUND OK. 1 H 7 1 3O 3A17 1996031500647 19960315 00647 SO 1996 3 15 96ZZZX1098 1 19960215 G 2497 BATTERY CABLE PIPER PA28 PA28151 7102805 SO DC GEN SYSTEM WRONG PART D K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 17 32439 287515156 DURING ANNUAL INSPECTION, THE BATTERY TO MASTER SOLENOID, SOLENOID TO STARTER CONTACTOR, BATTERY TO GROUND, AND AIRFRAME TO ENGINE GROUND CABLES WERE FOUND FABRICATED FROM INDUSTRIAL GRADE 600 VOLT COPPER TRANSMISSION CABLE. LOG RECORDS IN DICATED THESE CABLES WERE INSTALLED IN PLACE OF ORIGINAL ALUMINUM CABLES IN 1989. PIPER SB 836A SPECIFIES COPPER CABLE MEETING MIL-W-22759. 1 L 7 1 3O 2A13 1996031500648 19960315 00648 EA 1996 3 15 96ZZZX1099 2 19960128 G 7322 MA3AU CARBURETOR CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA ENGINE DEFECTIVE G K NONE O OTHER IN INSP/MAINT 1 SW 11 757UK 4625 2552 CR0665 15280012 L1307415 INSPECTION FOUND CARBURETOR COMPOSITE FLOATS BLACK AND CARBONED. IN ADDITION, THROTTLE ARM WORN. TWO PIECE VENTURI WAS INSTALLED. 1 H 7 1 3O 3 O NT 3A19 E223 1996031500652 19960315 00652 SO 1996 3 15 96ZZZX1103 1 19960223 G 5522 SKIN PIPER PA23 PA23 7102302 SO ELEVATOR CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 19 3070P 1944607 23988 WHILE INSPECTING LEFT LOWER ELEVATOR SKIN, NOTICED A 2 INCH CRACK. REMOVED SKIN TO INSPECT INTERNAL COMPONENTS. ALL OK . SKIN HAD CHAFED THROUGH BY RIB IN ELEVATOR RIB LOCATION 19676-00. REPLACED SKIN ON LOWER ELEVATOR WITH NEW. 1 L 7 2 3O 1A10 1996031500654 19960315 00654 SO 1996 3 15 96ZZZX1105 2 19960126 G 8520 649134 CRNAKSHAFT CESSNA 185 A185F 2072821 CE CONT O520 IO520D 17032 SO NR 2 MAIN FAILED D A UNSCHED LANDING E VIBRATION/BUFFET CR CRUISE 1 SW 03 4691E 975 325 B089312N 18503842 175052R CRANKSHAFT BROKE AFT OF NR 2 MAIN JOURNAL AT OIL TRANSFER TUBE. PARTS SET TO TCM FOR DETERMINATION OF FAILURE. CAUSE W AS DETERMINED TO BE LOW THROUGH-BOLT TORQUE WHICH, IN TURN, CAUSED BEARING TO SHIFT AND CRANKSHAFT TO VIBRATE. AIRCRAFT HAD DEPARTED NORMALLY, WHEN LEVELLING AND SETTING CRUISE CONDITION VIBRATION WAS NOTICED. WHEN AIRCRAFT TURNED TO RETU RN TO BASE, ENGINE FAILED. AIRCRAFT LANDED WITHOUT INCIDENT. (SEAPLANE). VAR TYPE CRANKSHAFT. CUT .010 INCH UNDER. 1 H 7 1 3O 3 O 3A24 E5CE 1996031500655 19960315 00655 SO 1996 3 15 96ZZZX1106 1 19960223 G 7110 4180400 BRACKET PIPER PA31 PA31 7103102 SO RT COWL FLAP ELONGATED HOLE D K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 19 2FOR 31157 WHILE INSPECTING RIGHT COWL FLAP FOR EXCESSIVE PLAY, FOUND IMPROPER BOLT USED WHICH ELONGATED HOLES ON ATTACH BRACKETS. REPLACED BRACKETS WITH NEW AND REPLACED BOLTS WITH PROPER CLEVIS PINS AND WASHERS PER PARTS BOOK. 1 L 7 2 3O A20SO 1996031500656 19960315 00656 CE 1996 3 15 96ZZZX1107 1 19960201 G 3230 1683800821 SWIVEL ROD BEECH 23 A24R 1151252 CE NLG BROKEN D K NONE O OTHER NR NOT REPORTED 1 SW 99 9710Q MC66 NOSE WHEEL DID NOT EXTEND NORMALLY. FOUND NOSE WHEEL SWIVEL ROD BROKEN WHICH DID NOT ALLOW WHEEL TO STRAIGHTEN OUT AS I T LEFT WHEELWELL. FOUND ONE CLEVIS, PN 169-820037-3, TIGHTENED TO THE POINT WHERE IT WOULD HARDLY MOVE WITH THE ROD HOO KED. THIS TIGHTNESS HAD BEEN LOADING THE BEARING THREAD END TO THE POINT OF BENDING, THEN FINALLY CRACKING. 1 L 7 1 3O A1CE 1996031500658 19960315 00658 CE 1996 3 15 96ZZZX1109 1 19960221 G 5720 0823400109 BULKHEAD CESSNA 402 402B 207590P CE TIP TANK ATTACH CRACKED D A K NONE O OTHER IN INSP/MAINT 1 SW 07 3131K 6800 402B0248 DURING A ROUTINE INSPECTION, THE LT WING TIP FUEL TANK ATTACH BULKHEAD WAS FOUND CRACKED. THE CRACK WAS LOCATED TWO INC HES OUTBOARD OF THE WING ATTACH BOLT. SUBMITTER STATED THIS CONDITION GOING UNREPAIRED, WOULD RESULT IN LOSS OF WING TI P FUEL TANK AND LOSS OF CONTROL OF AIRCRAFT. 1 L 7 2 3O A7CE 1996031500659 19960315 00659 SO 1996 3 15 96ZZZX1110 1 19960123 G 2710 BUSHING STOLAM RC3 RC3 3080202 SO CONTROL YOKE SEIZED B A HI1R O OTHER O OTHER NR NOT REPORTED 1 NE 05 6713K 996 DURING FLIGHT, AILERON TORQUE TUBE BUSHING SEIZED IN CONTROL YOKE TUBE EFFECTIVELY LOCKING AILERONS. BUSHING AND SHAFT ARE BOTH STEEL, RELATIVELY CLOSE FITTING AND HAVE NO MEANS OF LUBRICATION EXCEPT COMPLETE DISASSEMBLY. SUBMITTER RECOMM ENDS OWNERS OF THE AIRCRAFT HAVE THIS AREA CHECKED AT THE EARLIEST POSSIBLE TIME. 1 H 7 1 3O A769 1996031500660 19960315 00660 SO 1996 3 15 96ZZZX1111 1 19960214 G 7810 1961300 COLLECTOR PIPER PA23 PA23160 7102304 SO LT EXHAUST WRAP FAILED B A XA13 K NONE O OTHER IN INSP/MAINT 1 SW 17 4062P 231540 LEFT EXHAUST COLLECTOR INSULATION WRAP DETERIORATED ALLOWING EXHAUST TO MELT EXTERNAL SHROUD AND DAMAGE NACELLE SKIN INT O WHEELWELL AND TIRE. SUBMITTER STATED PROPER INSPECTION OF COLLECTOR WOULD HAVE PREVENTED FAILURE. 1 L 7 2 3O 1A10 1996031500661 19960315 00661 SO 1996 3 15 96ZZZX1112 1 19960130 G 5541 40226T100 RUDDER AYRES S2 S2RR1820 0970215 SO SPAR WEB CRACKED D A K NONE O OTHER IN INSP/MAINT 1 CE 07 61285 844 1091 R1820036 INSPECTION FOUND CRACKED UPPER RUDDER HINGE AT SPAR WEB AND ALL DOUBLERS. RIB ALSO BROKEN. SUBMITTER STATED RUDDER SPA R BEEF-UP NECESSARY TO PREVENT CRACKING. 1 L 7 1 4R A4SW 1996031500662 19960315 00662 EA 1996 3 15 96ZZZX1113 2 19960119 G 7414 1068256011 MAGNETO BENDIX PIPER PA28 PA28236 7102815 SO LYC O540 O540J3A5 41532 EA MAG MOUNT FLANGE FAILED H A A UNSCHED LANDING Y ENGINE STOPPAGE NR NOT REPORTED 1 WP 05 2476Y E109008GR 288511016 RL2277540A BOTH MOUNTING FLANGES OF THE SINGLE DRIVE DUAL MAGNETO WERE BROKEN. MAGNETO BACKED OUT OF ENGINE GEAR DRIVE CAUSING ENG INE TO STOP. AIRCRAFT LANDED IN OCEAN. 1 L 7 1 3O 3 O 2A13 E295 1996031500663 19960315 00663 CE 1996 3 15 96ZZZX1114 1 19960213 G 2820 S14956 HOSE CESSNA 182 182Q 2072732 CE PILOT DR POST DETERIORATED D A K NONE B K SMOKE/FUMES/ODORS/SPARKS FLUID LOSS IN INSP/MAINT 1 SO 09 95853 6805 18266656 PILOT COMPLAINED OF FUEL SMELL. WHILE INVESTIGATING SMELL, FOUND S1495-6 HOSE SEEPING FUEL AT THE AFT DOORPOST PILOT'S SIDE NEXT TO A BUNDLE OF WIRES GOING TO THE OVERHEAD LIGHTS. SUBMITTER SUGGESTS CLOSER ATTENTION BE PAYED TO ALL RUBBER HOSES CARRYING FLAMMABLE FLUIDS. 1 H 7 1 3O NT 3A13 1996031500664 19960315 00664 1996 3 15 96ZZZX1115 1 19960219 G 2421 952B9561 WEDGE SUNDSTRANDEM 915F7181 ARMATURE MISSING B L MG4R K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 19 ARMATURE ROTOR, PN 915F718-1, WAS RECEIVED BY SUNDSTRAND FROM NORTHWEST AIRLINES UNDER WORK ORDER NR 63462300. SAID ROT OR HAS BEEN WOUND BY PERSON UNKNOWN WITHOUT 8 EACH BOTTOM WEDGES AS REQUIRED IN THE SUNDSTRAND DRAINING OF THE ABOVE ROT OR, PN 915F718-1. 1996031500665 19960315 00665 NE 1996 3 15 96ZZZX1116 2 19960207 G 7210 310709001 BEARING PWA 118 PW118A NE RGB NR 19 SPALLED B RA1R K NONE O OTHER IN INSP/MAINT 1 SW 05 8360 73C029 115608 INSPECTION FOUND REMOTE GEARBOX NR 19 BEARING SPALLED. 4 T E20NE 1996031500666 19960315 00666 NE 1996 3 15 96ZZZX1117 2 19960215 G 7210 310924401 BEARING PWA 118 PW118A NE RGB NR 15 SPALLED B RA1R K NONE O OTHER IN INSP/MAINT 1 SW 05 8486 RH475 121119 INSPECTION FOUND RGB NR 15 BEARING SPALLED. 4 T E20NE 1996031500667 19960315 00667 EU 1996 3 15 96ZZZX1118 2 19960215 G 7250 3053556220 BEARING CFMINT CFM56 CFM563B2 13802 EU HPT ROTOR DAMAGED B RA1R K NONE O OTHER IN INSP/MAINT 1 SW 05 RR10056 721339 ENGINE WAS REMOVED FROM SERVICE DUE TO IN-FLIGHT SHUT DOWN. DISASSEMBLY OF THE ENGINE REVEALED THE NR 4 BEARING AREA WI THIN THE HPT ROTOR REAR SHAFT AND LPT NR 4 BEARING ROTATING SEALS HAD HEAVY DAMAGE. FURTHER INVESTIGATION IS IN PROCESS AT AVIALL. 4 F E21EU 1996031500668 19960315 00668 1996 3 15 96ZZZX1119 1 19960219 G 2421 952B9561 WEDGE 915F7181 ARMATURE MISSING B MG4R K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 19 ARMATURE ROTOR PN 915F718-1 RECEIVED BY SUNDSTRAND FROM DELTA AIRLINES UNDER WORK ORDER NR 63462100. SAID ROTOR HAS BEE N WOUND BY PERSON UNKNOWN WITHOUT 8 EACH BOTTOM WEDGES AS REQUIRED IN THE SUNDSTRAND DRAWING OF THE ABOVE PN 915F7181. 1996031500671 19960315 00671 SO 1996 3 15 96ZZZX1122 2 19960221 G 7414 S6LN25 MAGNETO BENDIX PIPER PA34 PA34200T 7103406 SO CONT O360 TSIO360EB 17025 SO MAGNETO COIL CLAMP BROKEN B APCR K NONE O OTHER IN INSP/MAINT 1 NM 01 4490F 1489 B119325DR 747670339 COIL CLAMP FOUND BROKEN AT BEND RADIUS DURING MAGNETO 500-HOUR INSPECTION. NOTE: CLAMP HAD WHITE DYKEM MARK PER TCM MA NUAL PAGE 7-6, PARAGRAPH 7.2.G(D). 1 L 7 2 3O 3 O A7SO E9CE 1996031500672 19960315 00672 EA 1996 3 15 96ZZZX1123 2 19960223 G 7414 D6LN2230 MAGNETO BENDIX PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA RETARD LEAD DEFECTIVE B APCR K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 01 27343 317752163 RL727061A MAGNETO CAME INSTALLED ON FACTORY OVERHAULED ENGINE. WHEN CONNECTING IGNITION HARNESS, NOTED RETARD LEAD COULD BE PUSHE D ALL THE WAY INTO THE MAG WITHOUT TOUCHING CONTACT FINGER SPRING. REAR COVER REMOVED TO ADJUST FINGER AND RIGHT POINT SET FOUND LOOSE, AND FIVE DEGREE SPLIT BETWEEN LEFT AND RIGHT POINTS. INSTALLER MADE NECESSARY ADJUSTMENTS AND SECURED POINT ATTACHING SCREWS. 1 L 7 2 3O 3 O A20SO E14EA 1996031500673 19960315 00673 CE 1996 3 15 96ZZZX1124 1 19960226 G 5711 SPAR BEECH 33 F33A 1151425 CE CARRY-THROUGH CRACKED B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 8240T 5840 CE1542 CRACK IN SPAR CARRY-THROUGH STRUCTURE AD 95-04-03 NOT VALID BY SERIAL NUMBER. 1 L 7 1 3O 3A15 1996031500674 19960315 00674 CE 1996 3 15 96ZZZX1125 1 19960227 G 5711 SPAR BEECH 33 F33A 1151425 CE CARRY-THROUGH CRACKED B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 8112T 5840 CE1539 CRACK IN SPAR CARRY-THROUGH STRUCTURE AD 95-04-03 NOT VALID BY SERIAL NUMBER. 1 L 7 1 3O 3A15 1996031500675 19960315 00675 SO 1996 3 15 96ZZZX1126 1 19960207 G 2913 765457 SWITCH PARKERHANFIN PIPER PA46 PA46350P SO UP PRESSURE DEFECTIVE D O OTHER J WARNING INDICATION CL CLIMB 1 GL 09 8167Q 78 4622031 PILOT COMPLAINED OF LANDING GEAR NOT RETRACTING. FOUND HYDRAULIC 'UP' PRESSURE SWITCH TO HAVE 165 OHMS RESISTANCE WHICH IS PREVENTING A GOOD GROUND FOR THE PUMP. REPLACED SWITCH. OPS CHECK OK. SWITCH WAS REPLACED 78.2 HOURS PREVIOUSLY A S PART OF PIPER SB 964A. 1 L 7 1 3O RT A25SO 1996031500676 19960315 00676 SO 1996 3 15 96ZZZX1127 1 19960220 G 3310 456732 RHEOSTAT PIPER PA28 PA28181 7102807 SO COCKPIT LIGHTS INOPERATIVE D A K NONE O OTHER IN INSP/MAINT 1 GL 19 91075 120 288690021 INSTRUMENT FLOOD LIGHTING SYSTEM'S RHEOSTAT FAILED IN 120 HOURS. PART APPEARS TO HAVE GOTTEN HOT BEFORE FAILURE. 1 L 7 1 3O 2A13 1996032200001 19960322 00001 CE 1996 3 22 96ZZZX1128 1 19960216 G 3242 50820020 DAMPENER BEECH 300 300BEECH 1152930 CE NLG EXCESS PLAY B JGVR K NONE W INADEQUATE Q C IN INSP/MAINT 1 CE 09 NLG SHIMMY DAMPENER PISTON HEAD APPEARS TO HAVE EXCESSIVE SIDE PLAY WHICH COULD CAUSE IT TO COCK TO ONE SIDE IN DAMPENER HOUSING. 2 L 7 2 4T A24CE 1996032200002 19960322 00002 NE 1996 3 22 96ZZZX1129 2 19960222 G 7200 ENGINE CESSNA 650 650 2076802 CE GARRTT TFE731 TFE7313B 01518 NE FWD FAN GRBOX OIL LOSS B MUCR E A ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION NR NOT REPORTED 1 GL 13 275GC 2316 6500162 87437 ENGINE EXHIBITED LOW OIL PRESSURE AND ENGINE WAS SHUT DOWN. AIRCRAFT MADE NORMAL LANDING ON SINGLE ENGINE. FOUND TWO Q UARTS OF OIL IN ENGINE. NORMAL CAPAPCITY (6 QUARTS). COULD NOT DUPLICATE ANY MALFUNCTIONS DURING TROUBLESHOOTING, BUT SUSPECT OIL SYSTEM PRESSURIZED FORCING OIL OUT BREATHER AS THE RESULT OF EITHER BREATHER PRESSURIZING VALVE STICKING OR UNSEATED CARBON SEAL. REPLACED NR 1 AND NR 3 CARBON SEAL AND BREATHER PRESSURIZING VALVE. 2 L 7 2 4F 4 F A9NM E6WE 1996032200003 19960322 00003 CE 1996 3 22 96ZZZX1130 1 19960213 G 5712 57222061 RIB CESSNA 441 441 2076020 CE WING CANTED RIB CRACKED B WTXR K NONE O OTHER IN INSP/MAINT 1 NM 11 441GE 5724 4410116 WHILE DOING A PHASE INSPECTION, FOUND A CRACK IN WING CANTED RIBS. CRACK EXTENDS FROM THE AFT SIDE OF THE FORWARD SPAR, REARWARD ALONG THE BEND RADIUS, 1.0 INCHES. CESSNA'S REPAIR IS TO STOP-DRILL END OF CRACK AND REINSPECT EACH 200 HOURS . 1 L 7 2 3T RT A28CE 1996032200004 19960322 00004 CE 1996 3 22 96ZZZX1131 1 19960213 G 5712 57222062 RIB CESSNA 441 441 2076020 CE WING CANTED RIB CRACKED B WTXR K NONE O OTHER IN INSP/MAINT 1 NM 11 441GE 5724 4410116 WHILE DOING A PHASE INSPECTION, FOUND A CRACK IN WING CANTED RIBS. CRACK EXTENDS FROM THE AFT SIDE OF THE FORWARD SPAR, REARWARD ALONG THE BEND RADIUS, 1.0 INCHES. CESSNA'S REPAIR IS TO STOP-DRILL END OF CRACK AND REINSPECT EACH 200 HOURS ACCORDING TO THE SUBMITTER. 1 L 7 2 3T RT A28CE 1996032200005 19960322 00005 CE 1996 3 22 96ZZZX1132 1 19960215 G 5712 57222061 RIB CESSNA 441 441 2076020 CE WING CANTED RIB CRACKED B WTXR K NONE O OTHER IN INSP/MAINT 1 NM 11 8617K 5541 4410307 WHILE DOING A PHASE INSPECTION, FOUND A CRACK IN WING CANTED RIBS. CRACKS EXTEND FROM THE AFT SIDE OF THE FORWARD SPAR, REARWARD ALONG THE BEND RADIUS, 1.0 INCHES. CESSNA'S REPAIR IS TO STOP-DRILL THE ENDS OF THE CRACKS AND REINSPECT AT 2 00-HOUR INTERVALS. 1 L 7 2 3T RT A28CE 1996032200006 19960322 00006 CE 1996 3 22 96ZZZX1133 1 19960215 G 5712 57222062 RIB CESSNA 441 441 2076020 CE WING CANTED RIB CRACKED B WTXR K NONE O OTHER IN INSP/MAINT 1 NM 11 8617K 5541 4410307 WHILE DOING A PHASE INSPECTION, FOUND A CRACK IN WING CANTED RIBS. CRACKS EXTEND FROM THE AFT SIDE OF THE FORWARD SPAR, REARWARD ALONG THE BEND RADIUS, 1.0 INCHES. CESSNA'S REPAIR IS TO STOP-DRILL THE ENDS OF THE CRACKS AND REINSPECT AT 2 00-HOUR INTERVALS. 1 L 7 2 3T RT A28CE 1996032200007 19960322 00007 CE 1996 3 22 96ZZZX1134 1 19960213 G 5712 57222061 RIB CESSNA 441 441 2076020 CE LT WING CANTED CRACKED B WTXR K NONE O OTHER IN INSP/MAINT 1 NM 11 171SP 2430 4410326 WHILE DOING A PHASE INSPECTION, FOUND A CRACK IN THE LT WING CANTED RIB, PN 5722206-1. CRACK EXTENDS FROM THE AFT SIDE OF THE FORWARD SPAR, REARWARD ALONG THE BEND RADIUS, 1.0 INCH. CESSNAS' REPAIR IS TO STOP-DRILL THE ENDS OF THE CRACK A ND REINSPECT EACH 200 HOURS. 1 L 7 2 3T RT A28CE 1996032200008 19960322 00008 WP 1996 3 22 96ZZZX1135 2 19960207 G 7260 30702192 GEARSHAFT 30700934 BRAERO DH125 BAE125800A 1500285 EU GARRTT TFE731 TFE7315R 01518 WP TRANSFER GRBOX FAILED D A UNSCHED LANDING J Y WARNING INDICATION ENGINE STOPPAGE CR CRUISE 1 CE 05 1910H 5314 P4880 258023 P91118 AIRCRAFT WAS IN CRUISE FLIGHT AT 39,000 FEET WHEN MASTER WARNING FLASHER CAME ON AND WOULD NOT CANCEL. SEVERAL SECONDS LATER, RT N2 INDICATION DROPPED TO ZERO FOLLOWED BY SHUT DOWN OF RT ENGINE. AIRCRAFT LANDED SAFELY WITHOUT INCIDENT. C AUSE OF SHUT DOWN WAS FAILURE OF BEVEL GEAR ON VERTICAL GEARSHAFT, PN 3070219-2, INSIDE TRANSFER GEARBOX, PN 3070093-4. THERE IS NO REQUIREMENT TO DISASSEMBLE AND DETAIL INSPECT THE GEARBOX ON CIVILIAN AIRCRAFT. AN ANALYSIS OF THE FAILED GEAR IS BENG PERFORMED BY ALLIED SIGNAL. 2 L 7 2 4F 4 F RT A3EU E6WE 1996032200010 19960322 00010 CE 1996 3 22 96ZZZX1137 1 19960201 G 5711 SPAR BEECH 90 C90 1152913 CE UNDER FLOOR FASTENER SHEARED B DP2R K NONE O OTHER IN INSP/MAINT 1 SW 05 2FOR LJ519 INSPECTION FOUND SPAR WITH 2 FASTENERS BROKEN (SHEARED) APPROXIMATELY 14 INCHES FROM CENTER LINE UNDER LEFT SEAT IN COCK PIT AREA (FORWARD FLANGE). 1 L 7 2 3T 3A20 1996032200011 19960322 00011 EA 1996 3 22 96ZZZX1138 1 19960222 G 2730 27719852 BEARING PARKERHANFIN 6007510221 CNDAIR CL600 CL6001A11 1900302 EA ELEVATOR PCU LOOSE FIT B SH5R K NONE W INADEQUATE Q C IN INSP/MAINT 1 NE 03 678ML 3695 0124 1011 UPON INSPECTION, FOUND THREE OUT OF FOUR ELEVATOR P.C.U.'S, ACTUATORS, WITH THE FORWARD BEARING LOOSE. UPON REMOVAL OF THE ACTUATORS, ALL OF THE BEARINGS CITED COULD BE REMOVED WITH LIGHT FINGER PRESSURE. CMM 27-30-01, PARAGRAPH E, STOP 6 .D STATES BEARINGS SHOULD WITHSTAND 500-INCH POUND AXIAL LOAD. ALL THREE ACTUATORS WERE REPLACED. LANDINGS, 2,138. 2 L 7 2 4F RT A21EA 1996032200012 19960322 00012 EA 1996 3 22 96ZZZX1139 1 19960222 G 2730 27719852 BEARING CNDAIR CL600 CL6001A11 1900302 EA ELEVATOR PCU LOOSE FIT B SH5R K NONE W INADEQUATE Q C IN INSP/MAINT 1 NE 03 678ML 3695 0131 1011 UPON INSPECTION, FOUND THREE OUT OF FOUR ELEVATOR P.C.U'S, ACTUATORS, WITH FORWARD BEARINGS LOOSE. UPON REMOVAL OF THE ACTUATORS, ALL OF THE SIGHTED BEARINGS WOULD BE REMOVED WITH LIGHT FINGER PRESSURE. CMM 27-30-01, PARAGRPAH E, STEP 6.D STATES BEARING SHOULD WITHSTAND 500-INCH POUND AXIAL LOAD. ALL THREE ACTUATORS WERE REPLACED. LANDINGS, 2,138. 2 L 7 2 4F RT A21EA 1996032200013 19960322 00013 EA 1996 3 22 96ZZZX1140 1 19960222 G 2730 27719852 BEARING CNDAIR CL600 CL6001A11 1900302 EA ELEVATOR PCU LOOSE FIT B SH5R K NONE W INADEQUATE Q C IN INSP/MAINT 1 NE 03 678ML 286 1011 UPON INSPECTION, FOUND THREE OUT OF FOUR ELEVATOR P.C.U.'S, ACTUATORS, WITH FORWARD BEARINGS LOOSE. UPON REMOVAL OF THE ACTUATORS, ALL OF THE SIGHTED BEARINGS COULD BE REMOVED WITH LIGHT FINGER PRESSURE. LANDINGS, 136. 2 L 7 2 4F RT A21EA 1996032200014 19960322 00014 1996 3 22 96ZZZX1141 4 19960116 G 3418 600591997 ACCELEROMETER SYSTRONDONNR CNDAIR CL600 CL6001A11 1900302 EA STALL WARNING FAILED B SH5R O OTHER N FALSE WARNING CL CLIMB 1 NE 03 1045X 1348 1038 FLASHING STALL LIGHTS ON TAKEOFF. FOUND NR 2 LATERAL ACCELEROMETER STICKING AT MINUS 10.8 VDC. THIS IS ABOUT THE TENTH ACCELEROMETER TO BE CHANGED IN THIS AIRCRAFT. THIS ACCELEROMETER WAS A CND UNIT FROM THE VENDOR. REMOVED AND REPLACED ACCELEROMETER. 2 L 7 2 4F RT A21EA 1996032200015 19960322 00015 NE 1996 3 22 96ZZZX1142 2 19960220 G 8520 CAMSHAFT DOUG DC3 DC3C 3021457 WP PWA R1830 R183092 52020 NE RT ENGINE FAILED E E ENGINE SHUTDOWN E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CR CRUISE 1 SW 11 59316 715 18986 BP462185 RIGHT ENGINE STARTED TO BACKFIRE AND RUN ROUGH. ENGINE WAS SHUT DOWN IN-FLIGHT AND PROP FEATHERED. UPON TROUBLESHOOTIN G, FOUND VALVES ON REAR CYLINDERS NOT ACTUATING. SUSPECT BROKEN CAM GEAR. ENGINE WAS REMOVED FOR REPAIR AND A SERVICEA BLE ENGINE WAS INSTALLED. 2 L 7 2 4R 4 R A669 5E4 1996032200016 19960322 00016 EA 1996 3 22 96ZZZX1143 1 19960221 G 2432 117BC1021 CONTROL BOARD CNDAIR CL600 CL600* EA BATTERY CHARGER MISMANUFACTURED B SH5R K NONE W INADEQUATE Q C IN INSP/MAINT 1 NE 03 932 BATTERY CHARGER MFG BY URDC DEFECTIVE. INCORRECTLY INSTALLED TRANSISTORS ON THE CONTROL BOARD. Q1 WAS INSTALLED INCORR ECTLY. SUBMITTER STATED ABOUT A 30 PERCENT FAILURE RATE FROM STOCK ON THESE CONTROL BOARDS. 2 L 7 2 4F RT A21EA 1996032200017 19960322 00017 EA 1996 3 22 96ZZZX1144 1 19960221 G 2432 117BC1021 CONTROL BOARD CNDAIR CL600 CL600* EA BATTERY CHARGER MISMANUFACTURED B SH5R K NONE W INADEQUATE Q C IN INSP/MAINT 1 NE 03 933 BATTERY CHARGER MFG BY URCD DEFECTIVE. INCORRECT INSTALLATION OF TRANSISTORS ON THE CONTROL BOARD. Q5 WAS INSTALLED IN CORRECTLY. THERE IS ABOUT A 30 PERCENT FAILURE RATE FROM STOCK ON THESE CONTROL BOARDS. 2 L 7 2 4F RT A21EA 1996032200018 19960322 00018 NE 1996 3 22 96ZZZX1145 2 19960221 G 7260 GEARBOX BOEING 747 747SP09 1384903 NM PWA JT9 JT9D7A 52054 NE NR 1 ENGINE WORN D E ENGINE SHUTDOWN J WARNING INDICATION CR CRUISE 1 SW 99 4522V 22805 P695756 FEBRUARY 21, 1996, CI-641, HKG/BKK. NR 1 ENGINE SHUT DOWN DUE TO OIL QUANTITY DROP TO ZERO AND OIL PRESSURE 20 PSI, WIN DMILL AT FL 390 7 MINS MINUS 59 DEGREES CELSIUS. GROUND CHECK FOUND MAIN GEAR BOX WORN. NR 1 ENGINE CHANGED. 2 L 7 4 4F 4 F A20WE E20EA 1996032200019 19960322 00019 NM 1996 3 22 96ZZZX1146 1 19960227 G 2915 V25W712077501 VALVE ISRAEL 1125 1125 NM HYD RESERVOIR DEFECTIVE D A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 WP 19 705MA 4320 011 UPON GEAR RETRACTION, BOTH HYDRAULIC PUMP AMBER LIGHTS AND HYDRAULIC LEVEL AMBER LIGHT ILLUMINATED. FLIGHT WAS ABORTED AND AIRCRAFT RETURNED TO BASE AIRPORT. ON GEAR EXTENSION BY NORMAL PROCEDURES, ALL LIGHTS EXTINGUISHED. WHEN GEAR WAS DOWN AND LOCKED, FOUND AIR RELEASE VALVE AT TOP OF MAIN RESERVOIR NOT SEATED ALLOWING FLUID TO VENT OVERBOARD. RECOMMEN D IAI TO LOOK AT AFFECTED PART DESIGN FOR A MORE RELIABLE SEAL. 2 L 7 2 4F RT A16NM 1996032200020 19960322 00020 EU 1996 3 22 96ZZZX1147 1 19960208 G 5751 AK11A501 AILERON BAC 111 111419EP 1480280 EU LT AILERON TOP DELAMINATED B AMCR K NONE O OTHER IN INSP/MAINT 1 GL 09 5751 8543 VH015 BAC120 WHILE C/W AD 67-19-02, FOUND DELAMINATION ON TOP AFT AREA OF LEFT AILERON. TWO AREAS OF APPROXIMATELY 2 INCHES BY 5 INC HES WERE FOUND. AILERON WAS REPAIRED IAW STRUCTURAL REPAIR MANUAL AND RE-BALANCED. 2 L 7 2 4F A5EU 1996032200021 19960322 00021 1996 3 22 96ZZZX1148 4 19960201 G 3410 LMD6004P BUSS MODULE BEECH 1900 1900D 1154162 CE BM 72 PIN DEFECT B PAIR K NONE O OTHER IN INSP/MAINT 1 SO 05 995WS 98 UE175 BOTH TRANSPONDERS AND BOTH ENCODERS WERE INTERMITTENTLY REPORTING INCORRECT ALTITUDE ABOVE 14,700 FEET DUE TO PIN 1 OF B M-72 BEING INTERMITTENTLY OPEN ON BUSS MODULE. BOTH GRAY CODE INFORMATION IS PARALLELED AT BUSS MODULES WHICH, IF ANY O NE PIN WOULD OPEN, IT WOULD HAMPER BOTH TRANSPONDERS MODE 'C' READ-OUT FROM EITHER ENCODER. REPLACED BM-72 BUSS MODULE TO REPAIR PROBLEM. RECOMMEND GRAY CODE LINES BE ISOLATED WITH RELAY SWITCHING TO FURTHER PROVIDE DUAL ISOLATION. 2 L 7 2 4T RT A24CE 1996032200025 19960322 00025 1996 3 22 96ZZZX1152 1 19960207 G 4920 304071 GEAR SUNDSTRANDEM T62T40C8D1 APU GRBOX FAILED D K NONE O OTHER IN INSP/MAINT 1 SW 05 2FOR 399 SPE925285 APU RECEIVED AND AN INVESTIGATION CONDUCTED DUE TO OIL CONTAMINATION AND HARD TO ROTATE. UPON DISASSEMBLY OF THE GEARBO X ASSEMBLY, PN 160192-100, SN 5002-1206, THE INTERNAL GEAR WAS FOUND CRACKED AND SPLIT IN THREE PLACES FROM THE BASE TO THE HOLES. ALL THREE BEARINGS, PN 9524301, WERE SPINNING IN THE CARRIER HOUSING ASSY. THE PINION SHAFT, PN 44647-0, DI D NOT SHEER, BUT THE TEETH WERE GROUND OFF. THE COVER DRAIN, PN 32896-1, WAS BENT/MANGLED AND THE BOTTOM THIRD WAS GROU ND OFF. SUBMITTER STATED CAUSE IS UNKNOWN AT THIS TIME. 1996032200027 19960322 00027 EU 1996 3 22 96ZZZX1154 1 19960226 G 5520 DHS1465200 BOLT BRAERO 1000 BAE1251000 1500287 EU LT ELEV HINGE WRONG LENGTH D L K NONE W INADEQUATE Q C IN INSP/MAINT 1 NE 03 100U NA1001 DURING A RECENT 2,400 HOUR-INSPECTION, THE LT ELEVATOR UPPER MID-ATTACH HINGE SEAL BOLTS WERE REPLACED WITH 5 EACH, DHS 1465-2DD, PER MOD 253410A DRAWING. AT 84 HRS FROM INSP DURING A PILOT PREFLT CHECK, A BINDING, AND SUBSEQUENT INSP REVE ALED AT EXTREME AFT FLT SURFACE MOVEMENT, 5 BOLTS ARE MAKING CONTACT WITH ELEV PLATE SEAL, PN 25-9TP27-5. NOTIFICIATION SENT TO RCJ CUSTOMER SUPPORT, AND REPAIR DESIGN OFFICE WITH DETAILS OF FINDINGS. THEIR DETERMINATION WAS THE SEAL PLAT E IS REPAIRABLE BY BLENDING AND SMOOTHING DAMAGED PROFILE AND REPLACEMENT OF SCREWS WITH 5 EACH, PN DHS 1465-1, 1/2 DD ( SHORTER). 2 L 7 2 4F RT A3EU 1996032200028 19960322 00028 GL 1996 3 22 96ZZZX1155 2 19960124 G 7250 6878426 NOZZLE ALLSN 250C 250C20 03013 GL 2ND STAGE TURB DEFECTIVE B A XZNR A UNSCHED LANDING J W WARNING INDICATION INADEQUATE Q C CR CRUISE 1 WP 07 27 X25103 CAE830145 THE NR 2 TURBINE NOZZLE EXPERIENCED A NR 2 BLADE TIP PATH SEPARATION IN-FLIGHT. THE PILOT REPORTED A 30 DEGREE RISE IN TOT AND RETURNED TO THE MAINTENANCE BASE. VENDOR'S ENGINEERING DEPARTMENT DETERMINED THE METAL SPRAY APPLICATION PROCES S WAS THE PRIMARY CAUSE OF THE FAILURE. MODIFICATION OF THE SPRAY PARAMETERS AND THOROUGH TESTING HAS PRODUCED A MORE R ELIABLE COATING. ALL NOZZLES FROM THE SUSPECT LOT HAVE BEEN RECALLED FOR RE-APPLICATION OF THE METAL SPRAY FOR BLADE TI P PATH RESTORATION. 3 U E4CE 1996032200029 19960322 00029 GL 1996 3 22 96ZZZX1156 2 19960221 G 7323 23054628 TUBE ASSY HUGHES 369 369E 4470707 WP ALLSN 250C 250C20B 03013 GL SCROLL-TO-FILTER MISMANUFACTURED D A K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 09 5238C 0151E CAE835599 IN AN ATTEMPT TO C/W ALLISION CEB-A-1323 INSTALLATION OF NEW SCROLL-TO-PC FILTER TUBE, FOUND NEW TUBE ASSY MISSED FITTIN G THE FLARES BY .350 INCH. DISTORTION OR STRETCHING OF THE PC FILTER-TO-GOVERNOR TUBE ASSY WOULD BE NEEDED TO INSTALL T HE NEW TUBE AS THE FIT OF THE 6848471 TUBE ASSY (ORIGINAL) WAS PERFECT, REINSTALLED IT. ALSO, THE CEB-A-1323 DOES NOT M ENTION WHICH END OF THE TUBE GOES TO THE PC FILTER ALTHOUGH IT IS ETCHED ON ONE B-NUT. 1 G 7 1 3U 3 U H3WE E4CE 1996032200030 19960322 00030 CE 1996 3 22 96ZZZX1157 1 19960217 G 5730 SKIN CESSNA 500 550 2076604 CE RT WS 49 CRACKED D S A K NONE O OTHER IN INSP/MAINT 1 SW 13 26621 5077 5500593 AFTER AIRCRAFT WAS STRIPPED FOR PAINT JOB, SKIN CRACK FOUND ON UPPER RIGHT WING SURFACE AT WS 49.0, CRACK MEASURED 3 INC HES 'DIAGONALLY' PASSING THROUGH RIVETS THAT ATTACH FLAP BELLCRANK SUPPORT. ONE-THIRD OF HEAD OF MIDDLE RIVETS SHEARED. CESSNA ENGINEERING SUGGESTS THAT FAILURE IS RESULT OF LOWERING FLAPS AT TOO GREAT AN AIRSPEED. 1 L 7 2 4F A22CE 1996032200031 19960322 00031 1996 3 22 96ZZZX1158 4 19960222 G 2211 KCP320 COMPUTER BEECH 90 C90A 1152911 CE AUTOPILOT MALFUNCTIONED G L O OTHER F FLT CONT AFFECTED AP APPROACH 1 AL 03 2247R 065001803 LJ1352 GLIDESLOPE TRIES TO COUPLE A SIGNAL BEYOND THE PARAMETERS ESTABLISHED IN THE PILOT'S OPERATING HANDBOOK. WHEN AUTOPILOT IS IN THE APPR CPLD MODE, THE GLIDESLOPE SIGNAL DROPS OUT AND COMES BACK, THE AUTOPILOT COMMANDS THE ACFT PITCH UP OR D OWN TO INTERCEPT THE GLIDESLOPE AT THE CLOSEST POINT. IT WAS STRESSED REPEATEDLY TO ALLIED SIGNAL THAT DURING ONE PARTI CULAR APPROACH, THIS ACFT PITCHED UP AND AIRSPEED DROPPED TO 90 KNOTS BEFORE THE PILOT COULD DISENGAGE THE AUTOPILOT AND REGAIN NORMAL FLIGHT PROFILE OF THE AIRCRAFT. 1 L 7 2 3T RT 3A20 1996032200122 19960322 00122 EU 1996 3 22 96ZZZX1161 1 19960217 G 2612 FIRE WIRE AEROSP AS355 AS355F2 8680812 EU FUEL PUMP BROKEN D O OTHER N FALSE WARNING AP APPROACH 1 EA 03 355DU 5489 DURING APPROACH, NR 1 FIRE LIGHT DIMLY ILLUMINATED THEN EXTINGUISHED. DURING HOVER, NR 1 FIRE LIGHT DIMLY ILLUMINATED O NCE MORE AND ON ENGINE SHUT-DOWN, CAME ON FULL BRIGHT. NO FIRE WITNESSED. FOUND/REPAIRED BROKEN WIRE TO FIRE DETECTOR TO FUEL PUMP STATION. 1 G 7 2 3U H11EU 1996032200123 19960322 00123 WP 1996 3 22 96ZZZX1162 1 19960220 G 7722 6887761 HARNESS HUGHES 369 369D 4470706 WP TURB TOT FAILED B EOOR K NONE O OTHER IN INSP/MAINT 1 AL 03 5074R 513 FF0L08 1151D TURBINE REMOVED FROM AIRCRAFT EARLIER AND REPLACED. DURING INSPECTION, TOT HARNESS FOUND CRACKED AT ONE OF THE PROBES ( 2:30 O'CLOCK POSITION). PART WAS SCRAPPED. 1 G 7 1 3U H3WE 1996032200124 19960322 00124 GL 1996 3 22 96ZZZX1163 2 19960223 G 7323 23057870 GOVERNOR HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL ENGINE ERRATIC B EOOR K NONE O OTHER IN INSP/MAINT 1 AL 03 5074R 457 24622 1151D CAE880976 PILOT COMPLAINED MANUAL BEEPING WAS REQUIRED FOR TAKEOFF, POWER CHANGES, AND LANDING. GOVERNOR UNIT REPLACED AND SENT I N FOR REPAIR. 1 G 7 1 3U 3 U H3WE E4CE 1996032200125 19960322 00125 WP 1996 3 22 96ZZZX1164 1 19960208 G 6320 369D25140 BEARING 369D25100 HUGHES 369 369D 4470706 WP M/R XMSN SPALLED B EOOR K NONE O OTHER IN INSP/MAINT 1 AL 03 5074R 5001 14 0184 1151D MAIN ROTOR TRANSMISSION DISASSEMBLED AFTER CHIPS DISCOVERED ON THE CHIP DETECTOR. BEARING, 369D25140, FOUND HEAVILY SPA LLED. REPLACED BEARING. 1 G 7 1 3U H3WE 1996032200126 19960322 00126 WP 1996 3 22 96ZZZX1165 1 19960220 G 6320 369D25100505 TRANSMISSION HUGHES 369 369D 4470706 WP M/R MAKING METAL B EOOR K NONE J WARNING INDICATION NR NOT REPORTED 1 AL 03 5074R 8534 2433 1260044 1151D PILOT GOT A FLICKER ON M/R TRANSMISSION CHIP LIGHT, THEN IT STAYED OUT. PILOT CHECKED CHIP PLUG ON LANDING WITH THE LIG HT STILL OFF AND FOUND SEVERAL LARGE CHIPS ON BOTH PLUGS. UNIT REMOVED AND RETURNED FOR REPAIR. 1 G 7 1 3U H3WE 1996032200127 19960322 00127 WP 1996 3 22 96ZZZX1166 1 19960126 G 7920 174H1014 HOSE HUGHES 369 369D 4470706 WP SCAVENGE OIL LEAKING B EOOR K NONE K FLUID LOSS IN INSP/MAINT 1 AL 03 5074R 1151D DURING ENGINE REMOVAL, THE SCAVENGE OIL HOSE FOUND SET WITH OIL. SUBSEQUENT INSPECTION FOUND IT WAS LEAKING. REPLACED HOSE. 1 G 7 1 3U H3WE 1996032200128 19960322 00128 GL 1996 3 22 96ZZZX1167 2 19960101 G 7240 23056130 COMBUSTION LINER HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL ENGINE BURNED B EOOR K NONE O OTHER IN INSP/MAINT 1 AL 03 5074R 1151D CAE832750 WHILE REMOVING TURBINE, THE COMBUSTION LINER WAS FOUND BURNED, WARPED, AND CRACKED. PART REPLACED. 1 G 7 1 3U 3 U H3WE E4CE 1996032200129 19960322 00129 WP 1996 3 22 96ZZZX1168 1 19960202 G 6320 369D25100505 TRANSMISSION HUGHES 369 369D 4470706 WP M/R MAKING METAL B EOOR K NONE O OTHER IN INSP/MAINT 1 AL 03 5074R 5001 14 0466 1151D DURING ANNUAL INSPECTION, CHIPS FOUND ON UPPER CHIP PLUG. UNIT REMOVED AND SENT FOR REPAIR. 1 G 7 1 3U H3WE 1996032200130 19960322 00130 GL 1996 3 22 96ZZZX1169 2 19960202 G 7261 6853301 SUMP HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL NR 6-7 BEARING WARPED B EOOR K NONE K FLUID LOSS IN INSP/MAINT 1 AL 03 5074R 1436 1151D CAE832750 DURING ANNUAL INSPECTION, NR 6 AND NR 7 BEARING SUMP ON THE TURBINE FOUND LEAKING AT THE MATING SURFACE. SUBSEQUENT INS PECTION REVEALED FLANGE WAS WARPED. 1 G 7 1 3U 3 U H3WE E4CE 1996032200131 19960322 00131 GL 1996 3 22 96ZZZX1170 2 19960211 G 7323 230574869 GOVERNOR HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL ENGINE ERRATIC B EOOR K NONE O OTHER IN INSP/MAINT 1 AL 03 5074R 591 24657 1151D CAE832750 DURING RUN-UP, PILOT WAS ADJUSTING ENGINE 'BEEP' AND THE GOVERNOR HESITATED, BUT WHEN AN INCREASE WAS NOTED, IT JUMPED U P 3 PERCENT TO 4 PERCENT AND WAS NOT A SMOOTH TRANSITION. PART SENT IN FOR REPAIR. 1 G 7 1 3U 3 U H3WE E4CE 1996032200132 19960322 00132 WP 1996 3 22 96ZZZX1171 1 19960220 G 6320 369D25100505 TRANSMISSION HUGHES 369 369D 4470706 WP M/R SEALS LEAK B EOOR K NONE K FLUID LOSS IN INSP/MAINT 1 AL 03 4571V 5927 1927 U0296 490487D TRANSMISSION REMOVED TO REPLACE ALL OIL SEALS DUE TO LEAKING. 1 G 7 1 3U H3WE 1996032200133 19960322 00133 NE 1996 3 22 96ZZZX1172 1 19960112 G 2910 0711311111 PISTON SKRSKY S76 S76A 8143006 NE BOOT STRAP BOLT BROKEN B L ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 376AL 4372 2872 760002 DURING SHOP INSPECTION (3,000-HOUR) AND REPAIR AND AFTER UPGRADE TO DASH 104 ASSEMBLY DURING BENCH TESTING, FOUND BOOT S TRAP PISTON RESTRAINING BOLT (PN MS24678-9) BROKEN AND RETAINER PLATE (PN 0711311-209) DEFORMED DURING DISASSEMBLY OF MO DULE. THESE DAMAGED PARTS WERE REPLACED DURING UPGRADE OF MODULE ASSY FROM DASH 103 TO DASH 104 CONFIGURATION. 1 G 7 2 3U H1NE 1996032200134 19960322 00134 WP 1996 3 22 96ZZZX1173 1 19960126 G 3610 369H9014981 TUBE HUGHES 369 369D 4470706 WP SCAVENGE AIR CRACKED B A EOOR K NONE O OTHER IN INSP/MAINT 1 AL 03 5074R 1151D DURING INSPECTION OF SCAVENGE AIR SYSTEM, THE AIR TUBE WAS FOUND CRACKED ABOUT 4 INCHES ABOVE THE SOLENOID. IT APPEARS TO HAVE HAD WATER FROZEN AT THAT POINT AS THE TUBE IS EXPANDED ALONG THE CRACKED AREA AND RECENT TEMPERATURES HAVE BEEN SUB-ZERO. 1 G 7 1 3U H3WE 1996032200436 19960322 00436 CE 1996 3 22 96ZZZX1246 1 19960228 G 5551 12326232 BRACKET 1232600201 CESSNA 210 P210N 2073454 CE LT HORIZ STAB CRACKED D L K NONE O OTHER IN INSP/MAINT 1 WP 17 677PC 2789 P21000677 DURING ROUTINE INSPECTION, LT HORIZONTAL STABILIZER ATTACH BRACKET REINFORCEMENT WAS FOUND CRACKED .50 INCH IN THE LOWER LT RADIUS. CESSNA SERVICE INFORMATION LETTER SE84-17R1 CALLS FOR A REPETITIVE 100-HOUR INSPECTION OF THIS AREA, BUT IT DOES NOT LIST THE 'P210' WHICH HAS THE SAME COMPONENT PARTS AND PINS INSTALLED. REPLACED BRACKETS WITH NEW STYLE P/N 1 232624-1 BRACKET. 1 H 7 1 3O 3A21 1996032200437 19960322 00437 SO 1996 3 22 96ZZZX1247 1 19960301 G 2410 7848300 STRUT PIPER PA28 PA28161 7102803 SO ALTERNATOR BRKT CRACKED D A K NONE O OTHER IN INSP/MAINT 1 GL 23 8198Z 288216146 ALTERNATOR TO STARTER STRUT CRACKED. SUSPECT DUE TO ENGINE VIBRATION. SUBMITTER NOTICED THIS ON 4 OTHER AIRCRAFT ON MO RE THAN ONE OCCASION. ALSO, ELONGATED BOLT HOLES THROUGH ALTERNATOR BRACKETS ON THE SAME (PA28-161) TYPE AIRCRAFT. THE SE ELONGATED HOLES CANNOT BE DETECTED WITHOUT REMOVING THE BRACKETS AND ALTERNATOR FROM AIRCRAFT. SUBMITTER RECOMMENDS INSPECTING BY REMOVAL EVERY 100 HOURS. 1 L 7 1 3O 2A13 1996032200439 19960322 00439 CE 1996 3 22 96ZZZX1249 1 19960204 G 2913 98812011 SOLENOID 12808021 CESSNA 210 T210L 2073449 CE POWER PACK DEFECTIVE D S A O OTHER J WARNING INDICATION LD LANDING 1 SW 99 381DS 2924 21060255 ON FEBRUARY 4, 1996, GEAR-UP LANDING WAS MADE. NO INJURIES. ALL LANDING GEAR DOORS OPENED, BUT GEAR FAILED TO EXTEND B Y ELECTRIC HYDRAULIC OR MANUAL HYDRAULIC. FAILURE CAUSED BY SOLENOID RESIDUE BUILD UP ON SHAFT OF SOLENOID PREVENTED OP ERATION OF MANIFOLD ON POWER PACK. RESIDUE PROBABLY DRIED HYDRAULIC FLUID. AFTER SOLENOID SHAFT CLEANED, LANDING GEAR OPERATED BOTH BY ELECTRIC HYDRAULIC PACK AND MANUAL HYDRAULIC PUMP SATISFACTORILY. SUGGEST CLEANING/INSPECTING SOLENOID SHAFT AT 1,000-HOUR INTERVALS. 1 H 7 1 3O 3A21 1996032200440 19960322 00440 SO 1996 3 22 96ZZZX1250 1 19960226 G 2510 440785 LATCH AMERICANSFTY PIPER PA28 PA28151 7102805 SO SEAT BELT DEFECTIVE D A K NONE O OTHER IN INSP/MAINT 1 NE 03 41287 6300 287415159 ON ANNUAL INSPECTION, FOUND LATCH NOT POSITIVELY ENGAGING. ON FURTHER INSPECTION, FOUND ONE SMALL SECONDARY SPRING MISS ING (PILOT'S BELT). OTHER BELT LATCH FOUND SMALL SECONDARY SPRING DAMAGED (COPILOT'S). CHECKED SEAT BELT LATCHES IN RE ST OF FLEET, ALL USED AMERICAN SAFETY LATCHES WITH MANY OF SAME PART NUMBER OR DESIGN. SUBMITTER RECOMMENDS CLOSER INSP ECTION ON LATCHES. 1 L 7 1 3O 2A13 1996032200442 19960322 00442 GL 1996 3 22 96ZZZX1252 1 19960223 G 3222 STRUT AMTR LANCAR LANCAIR 05616TS GL NLG COLLAPSED H O OTHER O OTHER CL CLIMB 1 CE 05 444WH 100 DURING TAKEOFF AND GEAR RETRACTION, THE FREE CASTERING NOSE GEAR TURNED SIDEWAYS, AND, THEREFORE UPON EXTENSION, THE NOS E GEAR STAYED SIDEWAYS AND COLLAPSED ON ROLL-OUT. THE SUSPECT CAUSE IS NO SELF-CENTERNG MECHANISM IN THE STRUT ASSY. A N ADDITIONAL CAUSE FOR COLLAPSED GEAR ARE GEAR SUPPORT LINKS, P/N 6M027-4, FOR NOT HAVING ENOUGH STRENGTH FOR SHARP TURN ING FORCES. 1 L 7 1 3O RT EXPA1L71 1996032200444 19960322 00444 EA 1996 3 22 96ZZZX1254 2 19960227 G 8530 60828 PISTON PIN PLUG CESSNA 172 172P 2072436 CE LYC O320 O320D2J 41508 EA CYLINDER FAILED H K NONE R PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 GL 19 99263 25 17276424 L1141539A PISTON PIN PLUG, PN 60828, IS NOT CORRECT, BUT LOCATION IS CORRECT. ENGINE OVERHAULED 24.8 HRS AGO. COMPLAINT OF LOSS OF POWER. GROUND RUN SEEMED OK, NOTHING OBVIOUS. COMPRESSION TEST FOUND LOW COMPRESSION ON ONE CYLINDER. BORESCOPED A ND COULD SEE METAL FLAKES. UPON DISASSEMBLY OF CYLINDER, FOUND SMALL ALUMINUM BALL IN CHEWED UP PISTON. AREA FROM NR 2 RING DOWN TO TOP OF PISTON PIN, HOLE WORN AWAY. SECTION OF BOTTOM RING BROKE OFF. CYLINDER WALL IN THIS AREA DAMAGED. 1 H 7 1 3O 3 O NT 3A12 E274 1996032200445 19960322 00445 CE 1996 3 22 96ZZZX1255 1 19960131 G 5321 04150211 FLOOR PANEL CESSNA 150 152 2071835 CE COCKPIT CORRODED B VT3R K NONE O OTHER IN INSP/MAINT 1 WP 09 48650 77 15280926 DURING ROUTINE INSPECTION, CARPET WAS REMOVED. FOUND CORROSION ON FLOOR. FURTHER INSPECTION REVEALED CORROSION ON 5 OF 6 FUEL LINES UNDER FLOOR AND ALONG DOOR SILLS AND DOOR POST. SUBMITTER SUSPECTS IMPROPER FLAMEPROOFING ON CARPET CAUSE D CORROSION. 1 H 7 1 3O NT 3A19 1996032200447 19960322 00447 SO 1996 3 22 96ZZZX1257 1 19960222 G 5312 62413000 FITTING PIPER PA32 PA32260 7103206 SO AFT BLKHD CORRODED D K NONE O OTHER IN INSP/MAINT 1 SO 16 3927W 3961 32874 THESE FITTINGS ARE MADE OF STEEL, DISSIMILAR METAL CORROSION HAD STARTED BETWEEN SKIN AND FITTINGS WHERE THEY ATTACH. O N TWO OF FITTINGS, SEVERAL RIVETS HAD POPPED THE HEADS OFF WHERE ATTACHED TO SKIN. THESE FITTINGS ATTACH FORWARD OF THE AFT BULKHEAD WHERE THE STABILATOR ATTACH BRACKETS ARE. 1 L 7 1 3O A3SO 1996032200448 19960322 00448 SO 1996 3 22 96ZZZX1258 1 19960222 G 5312 62413010 FITTING PIPER PA32 PA32260 7103206 SO AFT BLKHD CORRODED D K NONE O OTHER IN INSP/MAINT 1 SO 16 3927W 3961 32874 THESE FITTINGS ARE MADE OF STEEL, DISSIMILAR METAL CORROSION HAD STARTED BETWEEN SKIN AND FITTINGS WHERE THEY ATTACH. O N TWO OF FITTINGS, SEVERAL RIVETS HAD POPPED THE HEADS OFF WHERE ATTACHED TO SKIN. THESE FITTINGS ATTACH FORWARD OF THE AFT BULKHEAD WHERE THE STABILATOR ATTACH BRACKETS ARE. 1 L 7 1 3O A3SO 1996032200449 19960322 00449 SO 1996 3 22 96ZZZX1259 1 19960222 G 5312 62414000 FITTING PIPER PA32 PA32260 7103206 SO AFT BLKHD CORRODED D K NONE O OTHER IN INSP/MAINT 1 SO 16 3927W 3961 32874 THESE FITTINGS ARE MADE OF STEEL, DISSIMILAR METAL CORROSION HAD STARTED BETWEEN SKIN AND FITTINGS WHERE THEY ATTACH. O N TWO OF FITTINGS, SEVERAL RIVETS HAD POPPED THE HEADS OFF WHERE ATTACHED TO SKIN. THESE FITTINGS ATTACH FORWARD OF THE AFT BULKHEAD WHERE THE STABILATOR ATTACH BRACKETS ARE. 1 L 7 1 3O A3SO 1996032200450 19960322 00450 SO 1996 3 22 96ZZZX1260 1 19960222 G 5312 62414010 FITTING PIPER PA32 PA32260 7103206 SO AFT BLKHD CORRODED D K NONE O OTHER IN INSP/MAINT 1 SO 16 3927W 3961 32874 THESE FITTINGS ARE MADE OF STEEL, DISSIMILAR METAL CORROSION HAD STARTED BETWEEN SKIN AND FITTINGS WHERE THEY ATTACH. O N TWO OF FITTINGS, SEVERAL RIVETS HAD POPPED THE HEADS OFF WHERE ATTACHED TO SKIN. THESE FITTINGS ATTACH FORWARD OF THE AFT BULKHEAD WHERE THE STABILATOR ATTACH BRACKETS ARE. 1 L 7 1 3O A3SO 1996032200451 19960322 00451 CE 1996 3 22 96ZZZX1261 1 19960217 G 3260 15410382 DOWNLOCK STOP CESSNA 337 337E 2075721 CE RT MLG RUSTED D K NONE O OTHER IN INSP/MAINT 1 WP 09 1275M 1738 33701275 DURING ANNUAL INSPECTION, BOTH RT AND LT LANDING GEAR DOWNLOCK STOPS FOUND LOOSE ON MLG STRUTS. STOPS ARE ATTACHED WITH ONE BOLT EACH AND, ALSO, BONDED WITH EPOXY TO INBD LOWER L/E OF STEEL STRUT. LOCK PIN, ACTUATED HYDRAULICALLY, PIVOTS UP AGAINST WEDGE ON BOTTOM OF STOP TO LOCK GEAR IN DOWN POSITION. EPOXY BOND SEPARATES STOP FROM STRUT, USUALLY DUE TO RUST BETWEEN PARTS. IF STOP ROTATES FORWARD DUE TO FAILED BOND, IT CAN BE DISTORTED BY GEAR MOVEMENT AND STRUT CANNOT L OCK. 1 H 7 2 3O A6CE 1996032200452 19960322 00452 CE 1996 3 22 96ZZZX1262 1 19960217 G 3260 15410381 DOWNLOCK STOP CESSNA 337 337E 2075721 CE LT MLG RUSTED D K NONE O OTHER IN INSP/MAINT 1 WP 09 1275M 1738 33701275 DURING ANNUAL INSPECTION, BOTH RT AND LT LANDING GEAR DOWNLOCK STOPS FOUND LOOSE ON MLG STRUTS. STOPS ARE ATTACHED WITH ONE BOLT EACH AND, ALSO, BONDED WITH EPOXY TO INBD LOWER L/E OF STEEL STRUT. LOCK PIN, ACTUATED HYDRAULICALLY, PIVOTS UP AGAINST WEDGE ON BOTTOM OF STOP TO LOCK GEAR IN DOWN POSITION. EPOXY BOND SEPARATES STOP FROM STRUT, USUALLY DUE TO RUST BETWEEN PARTS. IF STOP ROTATES FORWARD DUE TO FAILED BOND, IT CAN BE DISTORTED BY GEAR MOVEMENT AND STRUT CANNOT L OCK. 1 H 7 2 3O A6CE 1996032200453 19960322 00453 CE 1996 3 22 96ZZZX1263 1 19960301 G 5347 SEAT RAIL CESSNA 182 182P 2075816 CE COCKPIT MISREPAIRED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 23 9894E 500 18263955 UPON ANNUAL INSPECTION, FOUND SEAT RAILS INSTALLED BY PERSONS UNKNOWN. RAILS WERE INSTALLED WITH MANY MIS-SIZED RIVETS AND SEVERAL WERE NOT BUCKED. TWO FLANGES OR RIBS WERE SMASHED OUT OF PLACE DUE TO PUNCHING OUT THE OLD RIVETS, AND NOT REPAIRED. UPON REMOVAL OF SEAT RAILS, FOUND EXTENSIVE CORROSION UNDERNEATH RAILS. REMOVED CORROSION, APPLIED ZINC CHRO MATE AND INSTALLED RAILS. RIBS WERE STRAIGHTENED OUT. 1 H 7 1 3O NT TA13 1996032200454 19960322 00454 SO 1996 3 22 96ZZZX1264 1 19960228 G 2842 550695 TRANSMITTER PIPER PA31 PA31350 7103110 SO LT INBD FUEL DEFECTIVE B FGQR K NONE O OTHER IN INSP/MAINT 1 SO 01 41049 318252025 WITH FUEL DRAINED OUT OF LT AND RT INBOARD TANKS, HAD ONE-FOURTH TANK INDICATIONS ON FUEL GAUGES (INBOARD TANK). FOUND INBOARD FUEL SENDER TO BE OUT OF TOLERANCES AT EMPTY AND FULL. OUTBOARD FUEL TRANSMITTERS WERE REPLACED DUE TO FLOAT WE AR/DETERIORATION, PN 550-695, MFG PN 6427512. SUBMITTER SUGGESTS PERIODIC INSPECTION OF FUEL TRANSMITTER FOR FLOAT WEAR AND TOLERANCES IS RECOMMENDED. 1 L 7 2 3O A20SO 1996032200455 19960322 00455 SO 1996 3 22 96ZZZX1265 1 19960228 G 2842 550696 TRANSMITTER PIPER PA31 PA31350 7103110 SO RT INBD FUEL DEFECTIVE B FGQR K NONE O OTHER IN INSP/MAINT 1 SO 01 41049 318252025 WITH FUEL DRAINED OUT OF LT AND RT INBOARD TANKS, HAD ONE-FOURTH TANK INDICATIONS ON FUEL GAUGES (INBOARD TANK). FOUND INBOARD FUEL SENDER TO BE OUT OF TOLERANCES AT EMPTY AND FULL. OUTBOARD FUEL TRANSMITTERS WERE REPLACED DUE TO FLOAT WE AR/DETERIORATION, PN 550-695, MFG PN 6427512. SUBMITTER SUGGESTS PERIODIC INSPECTION OF FUEL TRANSMITTER FOR FLOAT WEAR AND TOLERANCES IS RECOMMENDED. 1 L 7 2 3O A20SO 1996032200456 19960322 00456 CE 1996 3 22 96ZZZX1266 1 19960206 G 3220 2316 BRACKET ASSY SCOTT CESSNA 170 170B 2072306 CE TAIL GEAR FAILED D K NONE O OTHER IN INSP/MAINT 1 EA 05 4373B 3759 3200 26717 WHILE REMOVING AIRCRAFT FROM HANGAR, TAIL WHEEL SWIVELED AND ASSY SEPARATED FROM BRACKET AND SPRING ASSY. AFTER INVESTI GATING, FOUND BOLT IN THE BRACKET ASSY WAS PARTLY FRACTURED AND THE SUDDEN JOLT FROM THE SWIVEL BROKE THE TAIL WHEEL ASS Y OFF THE AIRCRAFT. SUBMITTER SUGGESTS ALL TAIL WHEEL BRACKET ASSYS BE REMOVED, INSPECTED, AND DYE-PENETRANT BOLTS FOR CRACKS. 1 H 7 1 3O A799 1996032200457 19960322 00457 SO 1996 3 22 96ZZZX1267 2 19960228 G 8550 CH48109 OIL FILTER CHAMPION 641639 BEECH 58 58 1152740 CE CONT O550 IO550C SO LT/RT ENGINES MISINSTALLED B ERY2 K NONE O OTHER IN INSP/MAINT 1 SO 11 123ZM 22 TH1768 676924 DURING FIRST ROUTINE ENGINE OIL AND FILTER CHANGE, THE OIL FILTER WAS EXTREMELY DIFFICULT TO REMOVE FROM THE ADAPTER ASS Y. SUBMITTER SUSPECTS CAUSE FOR PROBLEM: NO LUBRICATION AT INSTALLATION AS ENGINE WAS READIED FOR SERVICE. SUGGEST FO LLOW RECOMMENDED PROCEDURE PER MFG. SAME PROBLEM ENCOUNTERED WITH RIGHT ENGINE. (RIGHT ENGINE SN 676926, SAME TOTAL TI ME). 1 L 7 2 3O 3 O 3A16 E3SO 1996032200458 19960322 00458 CE 1996 3 22 96ZZZX1268 1 19960212 G 2701 12708441 CABLE ASSY CESSNA 210 T210M 2073451 CE FWD YOKE TUBE BOUND YOKE D K NONE O OTHER IN INSP/MAINT 1 SW 03 6276B 2600 21062730 UPON PREPARATION FOR TAKEOFF, PILOT CHECKED CONTROLS AND YOKE LOCKED UP ON NEAR TO A FULL FORWARD POSITION. ROLL WAS OK . UPON INSPECTION, YOKE ELECTRICAL RIBBON ASSY FOUND BOUND IN 2 OF THE 4 YOKE TUBE ROLLERS. PHYSICAL FORCE COULD NOT D ISLODGE. ROLLERS REMOVED AND REINSTALLED AFTER CLEARING RIBBON ASSY. 1 H 7 1 3O 3A21 1996032200459 19960322 00459 CE 1996 3 22 96ZZZX1269 1 19960201 G 3230 08411011 FITTING 08411004 CESSNA 310 310L 2074230 CE LT MLG FAILED G K NONE O OTHER LD LANDING 1 SO 09 2201F 310L0001 LEFT MLG END FITTING (SIDE BRACE LOCK) FAILED ON LANDING. THE LEFT MLG COLLAPSED ON LANDING DUE TO THE GEAR NOT BEING A BLE TO LOCK PROPERLY. IT APPEARS THE THREADED ROD PORTION OF THE END FITTING FAILED UNDER STRESS LOAD. 1 L 7 2 3O 3A10 1996032200460 19960322 00460 CE 1996 3 22 96ZZZX1270 1 19960226 G 2460 26700045 BUS BAR 261318118 CESSNA 208 208 2073702 CE PANEL ASSY DEFECTIVE B VT3R O OTHER J WARNING INDICATION CR CRUISE 1 WP 09 9617F 20800107 DURING FLIGHT IN IMC ATC NOTED MODE 'C' INOPERATIVE. CONFIRMED PROBLEM, ALSO FOUND RT FUEL QUANTITY FUEL FLOW AND ITT I NOPERATIVE. DURING DESCENT, PROBLEM DISAPPEARED. EXTENSIVE TROUBLESHOOTING REVEALED WIRE WHICH JUMPS TO THE BUS THAT C ONTROLS THE INTERMITTENT SYSTEMS WAS LOOSE AT THE CIRCUIT BREAKER. FOUND THE THREADS IN THE TAB WHICH THE JUMPER ATTACH ES TO WERE DAMAGED. THE SCREW WOULD 'BOTTOM OUT' AND GET TIGHT, BUT THE CONNECTOR WAS FREE TO ROTATE CAUSING INTERMITTE NT CONDITION. 1 H 7 1 3T NT A37CE 1996032200461 19960322 00461 CE 1996 3 22 96ZZZX1271 1 19960207 G 8010 08504691 RELAY CUTLERHAM CESSNA 404 404CESSNA 2075901 CE STARTER FAILED B APCR K NONE M OVER TEMP NR NOT REPORTED 1 NM 01 48SA 11133 4040417 LEFT ENGINE STARTER BURNED UP DUE TO RUNNING CONTINUOUSLY DUE TO RELAY STICKING. POOR DIAGNOSIS CAUSED STARTER TO BE RE PLACED WITHOUT REPLACING SOLENOID. SECOND STARTER FAILED ALSO. SAME CONDITION. RELAY REPLACED WITH SECOND NEW STARTER . SUBMITTER SUGGESTS MANUFACTURERS INSTALL WARNING LIGHT IN STARTER POWER CIRCUIT TO ALERT PILOT WHEN UNIT IS ENERGIZED . PILOT CANNOT TELL IF POWER IS REACHING STARTER MOTOR, OTHERWISE. 1 L 7 2 3O A25CE 1996032200462 19960322 00462 CE 1996 3 22 96ZZZX1272 1 19960229 G 2750 169524071101 ACTUATOR TUBE D151003 BEECH 76 76 1153005 CE FLAP ACTUATOR DISCONNECTED B UC2R O OTHER F FLT CONT AFFECTED NR NOT REPORTED 1 GL 19 6632J 4321 ME337 PILOT REPORTED FLAPS WOULD NOT EXTEND IN-FLIGHT. EXAMINED FLAP SYSTEM AND FOUND TUBE ACTUATOR DISCONNECTED FROM ACTUATO R ASSEMBLY. RECONNECTED TUBE AND FUNCTIONAL CHECK OF FLAPS SATISFACTORY. SUBMITTER SUGGESTS A METHOD BE DEVELOPED BY B EECH TO SAFETY TUBE ACTUATOR TO ACTUATOR ASSEMBLY. 1 L 7 2 3O A29CE 1996032200463 19960322 00463 1996 3 22 96ZZZX1273 4 19960229 G 3432 096107402 CAPACITOR KING KI525 G.S. IND SHORED B PG2R K NONE O OTHER IN INSP/MAINT 1 GL 11 32625 SUBMITTER STATED THEY HAVE OBSERVED MANY KI525 AND KI525A GLIDESLOPE POINTERS' POSITION AFFECTED BY THE AMOUNT OF FLAG C URRENT THAT THE INDICATOR RECEIVES FROM THE GLIDESLOPE RECEIVER. IN ALL CASES, C110 HAS BEEN DETERMINED TO BE THE SUSPE CT CAUSE OF THIS PROBLEM. DUE TO SIZE AND CIRCUITRY CONSTRAINTS, THE ONLY FIX IS TO REPLACE THE CAPACITOR WITH THE ORIG INAL PART. SUBMITTER STATED THERE WERE 5 INCIDENTS IN 1995, 1 SO FAR IN 1996. 1996032200464 19960322 00464 SO 1996 3 22 96ZZZX1274 1 19960220 G 2430 688169 SWITCH PIPER PA28 PA28161 7102803 SO BAT MASTER FAILED D K NONE O OTHER TX TAXI/GRND HDL 1 SO 15 96PF 9951 288116266 BATTERY HALF ROCKER OF MASTER SWITCH BROKE IN HALF ALLOWING ELECTRICAL CONTACT BAR TO DROP OUT OF SWITCH BODY RESULTING IN COMPLETE LOSS OF ELECTRIC POWER. THIS FAILURE OCCURRED DURING GROUND OPERATIONS AT NIGHT. CAUSE OF FAILURE COULD NO T BE DETERMINED AS PILOT MISPLACED BROKEN PIECES. SUBMITTER SUGGESTS A CLOSE VISUAL INSPECTION OF CENTER AREA OF ROCKER FOR FINE CRACKS AT 100-HOUR INTERVALS FOR AIRCRAFT HAVING A HIGH NUMBER OF HOURS. 1 L 7 1 3O 2A13 1996032200466 19960322 00466 1996 3 22 96ZZZX1276 4 19960228 G 2562 BP1045 BATTERY PACK MERL EBC102A ELT DEFECTIVE B SF5R K NONE O OTHER IN INSP/MAINT 1 NE 03 THIS ELT CAME ON BY ITSELF IN THE GARAGE OF CUSTOMER. FAA/CAP WENT TO CUSTOMER'S HOUSE AND FOUND ELT GOING ON. FAA REP REMOVED ONE SCREW FROM BACK COVER OF ELT AND THE ELT SHUT OFF. REP PUT SCREW BACK IN AND ELT WENT OFF AGAIN. ELT AND BATTERY WIRES WERE ATTACHED PROPERLY WITH WIRE NUTS. UPON INVESTIGATION AT EBC PLANT, FOUND MERL BATTERY HAD AN EXPOSED TAB-WELD SPOT AND THE SCREW FROM THE BACK COVER, WHEN INSTALLED, HIT THE SPOT AND SHORTED THE ELT ON. 1996032200467 19960322 00467 CE 1996 3 22 96ZZZX1277 1 19960131 G 6120 C299506B0104 CONTROL ASSY CESSNA 172 R172K 2072431 CE GOVERNOR SEIZED D K NONE O OTHER IN INSP/MAINT 1 WP 21 7585X 2 R1723334 INSTALL NEW CONTROL CABLE ASSY AS SUPPLIED BY CESSNA AIRCRAFT. INSTALLED AND RIGGED PER CESSNA R172K SM AND UNDER THE S UPERVISION OF A CESSNA FIELD SERVICE ENGINEER. ALL OPS CHECK OK ON GROUND. RUN-UPS CHECK OK. FLOWN FOR 2.0 HRS, NO AT TEMPT MADE TO ADJUST OR MOVE CONTROL WHILE IN-FLIGHT. UPON RETURN TO GROUND, GOVERNOR CONTROL CABLE ASSY FOUND FROZEN S OLID. CURRENT CABLE (CABLE NR 4) AWAITING REINSPECTION BY FIELD ENGINEER. 1 H 7 1 3O 3A17 1996032200468 19960322 00468 WP 1996 3 22 96ZZZX1278 1 19960228 G 3210 PC531014 CLAMP RHNFLU EXT300 EXTRA300 05616CV WP MLG LOWER FAILED D K NONE O OTHER LD LANDING 1 WP 05 300EM 044 LOWER LANDING GEAR CLAMP SEPARATED FORM UPPER CLAMP AT REAR ATTACH POINT (BOLT WAS STILL INTACT). SUSPECT CAUSE: FATIG UE CRACKS ALONG THE INSIDE EDGE OF THE BOXED AFT ATTACHING BOLT AREA OF LOWER CLAMPS (BOTH LT AND RT SIDES AFFECTED) WHI CH CAUSED AFT SECTION OF LOWER CLAMP TO TEAR AWAY FROM UPPER CLAMP UPON LANDING. RECOMMEND DISASSEMBLY AND INSPECTION ( N.D.T.) OF LOWER CLAMP BRACKETS AT 500-HOUR INTERVALS OR HARD LANDINGS. (DYE PENETRANT INSPECTION NEEDED). TT ON AIRCR AFT, 629.4 HOURS. 1 M 7 1 3O NC EXPA1M71 1996032200469 19960322 00469 SO 1996 3 22 96ZZZX1279 2 19960215 G 7322 30764 FLOAT 103965121 CESSNA 182 182 2072702 CE CONT O470 O470L 17026 SO CARBURETOR DETACHED B KC2R O OTHER Y ENGINE STOPPAGE CR CRUISE 1 GL 03 4000457 ENGINE QUIT IN-FLIGHT ONCE AND ON THE GROUND ONCE. FOUND ONE PONTOON OF FLOAT ASSEMBLY HAD BROKEN OFF. DATE CODE STAMP ED IN FLOAT BRACKET IS 884. IT IS A FACTORY MANUFACTURED FLOAT; NOT A PMA. 1 H 7 1 3O 3 O NT 3A13 E273 1996032200470 19960322 00470 CE 1996 3 22 96ZZZX1280 1 19960201 G 2730 12604757 CONTROL CABLE CESSNA 210 T210K 2073447 CE ELEVATOR UP WORN D K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 11 8209M 6468 21059209 DURING ANNUAL INSPECTION, FOUND ELEVATOR 'UP' CABLE WORN THROUGH AT PULLEY JUST FORWARD OF GEARBOX. PULLEY WAS NOT TURN ING DUE TO BRACKET THAT HOLDS PULLEY WAS INSTALLED AT AN ANGLE. IT APPEARS BRACKET WAS INSTALLED THAT WAY FROM FACTORY. LOG BOOKS SHOW NO DATA ON CABLE OR BRACKET REPLACEMENT. CABLE WAS WORN FROM PULLEY AND PULLEY WAS NOT WORN AT ALL. C ABLE HAD 2 STRANDS LEFT HOLDING IT. 1 H 7 1 3O 3A21 1996032200471 19960322 00471 CE 1996 3 22 96ZZZX1281 1 19960228 G 2710 05232193 SUPPORT CESSNA 182 182A 2072704 CE AIL BELLCRANK ELONGATED HOLES D K NONE O OTHER IN INSP/MAINT 1 NM 11 6362B 3500 34262 DURING ANNUAL INSPECTION, FOUND RT AILERON BELLCRANK BOLT HOLES ON THE SUPPORT CHANNELS TO BE ELONGATED. ONLY THE PIVOT HOLES WERE BAD, NOT THE STOP-PIN HOLES. SUSPECT CAUSED BY NOT INSTALLING CONTROL LOCK WHEN ACFT ON GROUND. 1 H 7 1 3O NT 3A13 1996032200472 19960322 00472 CE 1996 3 22 96ZZZX1282 1 19960228 G 2710 05232194 SUPPORT CESSNA 182 182A 2072704 CE AIL BELLCRANK ELONGATED HOLES D K NONE O OTHER IN INSP/MAINT 1 NM 11 6362B 3500 34262 DURING ANNUAL INSPECTION, FOUND RT AILERON BELLCRANK BOLT HOLES ON THE SUPPORT CHANNELS TO BE ELONGATED. ONLY THE PIVOT HOLES WERE BAD, NOT THE STOP-PIN HOLES. SUSPECT CAUSED BY NOT INSTALLING CONTROL LOCK WHEN ACFT ON GROUND. 1 H 7 1 3O NT 3A13 1996032200473 19960322 00473 EA 1996 3 22 96ZZZX1283 1 19960119 G 2810 TA12C60W CLAMP DHAV DHC7 DHC7102 2802708 EA MAIN/AUX BAY DETERIORATED B WVER K NONE O OTHER IN INSP/MAINT 1 EA 09 59AG 59 WHILE PERFORMING MAINTENANCE IN THE FUEL BAY, FOREIGN MATERIAL WAS SEEN IN THE RESIDUAL FUEL. INSPECTION OF THE MATERIA L REVEALED IT TO BE RUBBBER IN COMPOSITION. INVESTIGATION REVEALED THE CLAMPS INSTALLED WERE TA12C60W AND THE CUSHION W AS DISTORTED AND DETERIORATED. THE CLAMPS WERE PART OF THE BRANSON FUEL MOD AND WERE IDENTIFIED AS DSC-162-32 AS SUPPLI ED BY BRANSON. CLAMPS WERE REPLACED WITH DSC-162-32-1, AND FUEL BAYS WERE CLEANED OF ALL DEBRIS. REF. STC NR ST00180DE . 2 H 7 4 4T A20EA 1996032200930 19960322 00930 1996 3 22 96ZZZX1328 4 19960114 G 3424 214075244001 GYRO BELL 212 212 1181420 SW TURN RATE FAULTY C K NONE O OTHER IN INSP/MAINT 1 EU 01 705H 101 1992B 35088 TURN NEEDLE STAYS IN THE CENTER ALL THE TIME. IT WILL NOT FUNCTION. 1 G 7 1 4U H4SW 1996032900214 19960329 00214 CE 1996 3 29 96ZZZX1329 1 19960228 G 2844 10138901823 SWITCH BEECH 200 B200 1152922 CE RT ENG FUEL FAILED B FGQR K NONE O OTHER IN INSP/MAINT 1 SO 01 93ME 2194 5410 BB1345 RT ENGINE FUEL PRESSURE SWITCH FAILED IN OPEN POSITION. TT: 2,193.9 HRS. SUBMITTER STATED THIS IS THE 2ND SWITCH TO F AIL IN FLEET. 1 L 7 2 4T A24CE 1996032900215 19960329 00215 CE 1996 3 29 96ZZZX1330 1 19960229 G 5711 SPAR CAP CESSNA 500 500CESSNA 2076602 CE WS 34-61 CORRODED B SI6R K NONE O OTHER IN INSP/MAINT 1 SW 17 500TM 4705 5000112 WHEN PERFORMING SL500-28-08, FOUND THE SPAR CAP TO BE CORRODED REQUIRING REPAIR. THE SUSPECTED CAUSE WAS LOOSE SEALANT AND POOR PRIMER ADHESION. SUBMITTER RECOMMENDS C/W SL500-28-10. 1 L 7 2 4F A22CE 1996032900216 19960329 00216 CE 1996 3 29 96ZZZX1331 1 19960229 G 5711 SPAR CAP CESSNA 500 500CESSNA 2076602 CE WS 34-61 CORRODED B SI6R K NONE O OTHER IN INSP/MAINT 1 SW 17 501KG 6046 5000279 WHEN PERFORMING SL500-28-08, FOUND LOWER SPAR CAP CORRODED REQUIRING REPAIR. THE SUSPECT CAUSE WAS LOOSE SEALANT AND PO OR PRIMER ADHESION. RECOMMEND C/W SL500-28-10. 1 L 7 2 4F A22CE 1996032900217 19960329 00217 CE 1996 3 29 96ZZZX1332 1 19960229 G 5711 SPAR CAP CESSNA 500 500CESSNA 2076602 CE WS 34-61 CORRODED B SI6R K NONE O OTHER IN INSP/MAINT 1 SW 17 700MP 6482 5000198 WHEN PERFORMING SL500-28-08, FOUND SPAR CAP CORRODED REQUIRING REPAIR. THE SUSPECT CAUSE WAS LOOSE SEALANT AND POOR PRI MER ADHESION. RECOMMEND C/W SL500-28-10. 1 L 7 2 4F A22CE 1996032900218 19960329 00218 CE 1996 3 29 96ZZZX1333 1 19960228 G 2844 10138901823 SWITCH BEECH 200 B200 1152922 CE LT ENG FUEL FAILED B FGQR K NONE O OTHER IN INSP/MAINT 1 SO 01 700WP 2132 3050 BB1313 LT ENGINE FUEL PRESSURE SWITCH FAILED IN OPEN POSITION. TT: 2,131.8 HRS. 1 L 7 2 4T A24CE 1996032900219 19960329 00219 1996 3 29 96ZZZX1334 4 19960209 G 3457 1283800781 ANTIICE SYSTEM BEECH MU300 400BEECH CE LT STAB LE FAILED B OG5R K NONE O OTHER IN INSP/MAINT 1 GL 21 3196N 153 BT0035 RK96 LEFT HORIZONTAL STABILIZER ANTI-ICE FAILED DUE TO INOPERATIVE OVERTEMP SENSOR. INSTALLED NEW LEADING EDGE ASSY. BEECH KIT 128-4014-5, INSTALLED AT ACFT TT, 911.2 HOURS. CURRENT ACFT TT, 1,064.6 HRS. 2 H 7 2 4F RT A16SW 1996032900220 19960329 00220 CE 1996 3 29 96ZZZX1335 1 19960201 G 2435 303001380 BRUSH LUCAS 23048016 BEECH 200 200BEECH 1152920 CE NR 1 GENERATOR EXCESS WORN D A UNSCHED LANDING H ELECT. POWER LOSS-50 PC CR CRUISE 1 CE 03 6689D 982 12768 BB623 AIRCRAFT EXPERIENCED NR 1 GENERATOR DROP OFF LINE AT NIGHT WITH HEATS ON. UNABLE TO RESET. APPROXIMATELY 30 MINUTES LA TER, NR 2 GENERATOR DROPPED OFF LINE. UNABLE TO RESET. DIVERTED TO VFR AIRPORT AND LANDED. FOUND NR 2 GENERATOR BRUSH ES WORN PAST LIMITS AND THEY SHOWED SIGNS OF HEAT DAMAGE TO BRUSH LEADS. NR 1 GENERATOR BRUSHES WORN TO LIMITS, BUT WAS ABLE TO RESET ON GROUND AND IT DID WORK. 1 L 7 2 4T A24CE 1996032900221 19960329 00221 CE 1996 3 29 96ZZZX1336 1 19960201 G 2435 303001380 BRUSH LUCAS 23048016 BEECH 200 200BEECH 1152920 CE NR 2 GENERATOR EXCESS WORN D A UNSCHED LANDING H ELECT. POWER LOSS-50 PC CR CRUISE 1 CE 03 6689D 982 15623 BB623 AIRCRAFT EXPERIENCED NR 1 GENERATOR DROP OFF LINE AT NIGHT WITH HEATS ON. UNABLE TO RESET. APPROXIMATELY 30 MINUTES LA TER, NR 2 GENERATOR DROPPED OFF LINE. UNABLE TO RESET. DIVERTED TO VFR AIRPORT AND LANDED. FOUND NR 2 GENERATOR BRUSH ES WORN PAST LIMITS AND THEY SHOWED SIGNS OF HEAT DAMAGE TO BRUSH LEADS. NR 1 GENERATOR BRUSHES WORN TO LIMITS, BUT WAS ABLE TO RESET ON GROUND AND IT DID WORK. 1 L 7 2 4T A24CE 1996032900222 19960329 00222 1996 3 29 96ZZZX1337 4 19960223 G 3457 071015450200 ANTENNA KING KA91 BEECH 200 200BEECH 1152920 CE GPS FAILED B BXSR K NONE O OTHER IN INSP/MAINT 1 EA 09 200BE 830 12187 BB832 GPS ANTENNA FAILED AFTER ONLY 2 YEARS IN USE. UNIT IS USED WITH KING KLN90. 1 L 7 2 4T A24CE 1996032900223 19960329 00223 CE 1996 3 29 96ZZZX1338 1 19960229 G 3260 1EN18 SWITCH LEAR 35 35LEAR 5170600 CE LT MLG DOWNLK FAILED D O OTHER P NO WARNING INDICATION AP APPROACH 1 GL 07 8040A 048 LEFT MAIN GEAR, NO DOWN AND LOCK INDICATION. REMOVED AND REPLACED SWITCH, OPS OK. 2 L 7 2 4F A10CE 1996032900224 19960329 00224 CE 1996 3 29 96ZZZX1339 1 19960220 G 3220 23420117 GEAR ASSY LEAR 35 35A 5170602 CE NLG MALFUNCTION D O OTHER J WARNING INDICATION AP APPROACH 1 GL 07 118DA 14251 2162 081 NOSE GEAR UNSAFE LIGHT ON. REMOVED AND REPLACED NOSE GEAR ASSY. CYCLED GEAR. OPS CHECK GOOD. 2 L 7 2 4F A10CE 1996032900225 19960329 00225 CE 1996 3 29 96ZZZX1340 1 19960223 G 3230 582212716 ANGLE CESSNA 441 441 2076020 CE UPLOCK HOOK CRACKED B S WTXR K NONE O OTHER IN INSP/MAINT 1 NM 07 88GW 7929 4410187 DURING PHASE INSPECTION, FOUND CRACK IN OUTBOARD END OF RT MAIN GEAR UPLOCK HOOK SUPPORT ANGLE THAT ATTACHES TO FORWARD WING SPAR WEB. CRACK ORIGINATES AT OUTBOARD HILOK HOLE AND EXTENDS FOR A TOTAL LENGTH OF 1.5 INCHES. 1 L 7 2 3T RT A28CE 1996032900226 19960329 00226 EA 1996 3 29 96ZZZX1341 2 19960227 G 7414 1051676 CAPACITOR BENDIX S6RN23 HILLER UH12 UH12B 4360110 WP FRNKLN 6AV335 6V335B 27020 EA RT MAG FAILED D K NONE O OTHER IN INSP/MAINT 1 WP 07 4785C 7 430043 312 WHEN RT MAG SELECTED DURING ENGINE RUN-UP CHECK, ENGINE FAILED. OBSERVED EXCESSIVE SPARKING AND POINT WEAR (7 HRS SINCE NEW). ENGINE RAN NORMALLY AFTER REPLACEMENT OF CAPACITOR AND POINT ADJUSTMENT. SUSPECT MANUFACTURING DEFECT OF PMA CA PACITOR. 1 G 7 1 3O 3 O 6H2 E244 1996032900227 19960329 00227 1996 3 29 96ZZZX1342 4 19960304 G 3421 5040045901 GYRO BELL 412 412 1182202 SW COCKPIT ATTITUDE DEFECTIVE B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 32936 18 25017 36115 ATTITUDE GYRO DEFECTIVE. REPLACED WITH NEW FIXTURE. 1 G 7 2 4U H4SW 1996032900228 19960329 00228 GL 1996 3 29 96ZZZX1343 3 19960219 G 6114 HUB ASSY UNIVAR 415 415C 0420302 NM MCAULY 1A90 1A90CF GL PROP FAILED D O OTHER D INFLIGHT SEPARATION NR NOT REPORTED 1 CE 07 99224 1500 1847 HUB CRACKED ALONG KEYWAY AND PROGRESSED UP PROP FLANGE TO WITHIN .50 INCH OF BOLT HOLE. ASSUME THIS ALLOWED THE HUB TO BECOME LOOSE AND LET NUT, PN 21202, LOOSEN AND WEAR ON SAFETY PIN, PN AN 392-11, CAUSING IT TO BREAK AND ALLOW NUT TO UN SCREW AND LET PROP AND HUB ASSY TO DEPART AIRPLANE. 1 L 7 1 3O A718 5 N P842 1996032900229 19960329 00229 CE 1996 3 29 96ZZZX1344 1 19960130 G 5730 3701301213 SKIN RKWELL NA265 NA26580 7630108 CE TOP LT WING CORRODED D K NONE O OTHER IN INSP/MAINT 1 CE 09 221PH 6083 38049 DURING REPAINT OF AIRCRAFT WITH SUPER CRITICAL WING, FOUND EXISTING SEALANT CRACKED AND DETERIORATED. AT CUSTOMER REQUE ST, REMOVED SEALANT AND FOUND ALUMINUM SKIN SURFACE AT EDGE OF OVERLAY CORRODED BEYOND MANUFACTURER'S ALLOWABLE LIMITS. ONE AREA APPEARED TO GO UNDERNEATH ONE OVERLAY. REMOVED OVERLAY AND FOUND PREVIOUS DELAMINATION REPAIR AREA WHICH CONT AINED DRILL MARKS IN TOP EXTERIOR SKIN SURFACE DEEPER THAN .003 INCH (MAXIMUM DEPTH). SUSPECT AGE AND DETERIORATION OF SEALANT ALLOWED CONTAMINATION AND EVENTUAL CORROSION TO EXPOSED SKIN SURFACES. DRILL MARKS RESULT FROM PREVIOUS DELAMI NATION REPAIR OF SKIN OVERLAY. 2 L 7 2 4F A2WE 1996032900230 19960329 00230 CE 1996 3 29 96ZZZX1345 1 19960130 G 5730 3701301214 SKIN RKWELL NA265 NA26580 7630108 CE TOP RT WING CORRODED D K NONE O OTHER IN INSP/MAINT 1 CE 09 221PH 6083 38049 DURING REPAINT OF AIRCRAFT WITH SUPER CRITICAL WING, FOUND EXISTING SEALANT CRACKED AND DETERIORATED. AT CUSTOMER REQUE ST, REMOVED SEALANT AND FOUND ALUMINUM SKIN SURFACE AT EDGE OF OVERLAY CORRODED BEYOND MANUFACTURER'S ALLOWABLE LIMITS. ONE AREA APPEARED TO GO UNDERNEATH ONE OVERLAY. REMOVED OVERLAY AND FOUND PREVIOUS DELAMINATION REPAIR AREA WHICH CONT AINED DRILL MARKS IN TOP EXTERIOR SKIN SURFACE DEEPER THAN .003 INCH (MAXIMUM DEPTH). SUSPECT AGE AND DETERIORATION OF SEALANT ALLOWED CONTAMINATION AND EVENTUAL CORROSION TO EXPOSED SKIN SURFACES. DRILL MARKS RESULT FROM PREVIOUS DELAMI NATION REPAIR OF SKIN OVERLAY. 2 L 7 2 4F A2WE 1996032900231 19960329 00231 WP 1996 3 29 96ZZZX1346 1 19960125 G 2913 938951 PUMP DOUG DC3 DC3C 3021457 WP RT ENG HYD FAILED H BG7P K NONE O OTHER IN INSP/MAINT 1 NM 05 115Z 1608 A029 33567 ENGINE DRIVEN HYDRAULIC PUMP FAILED DURING ENGINE START. THE ROTARY PISTON-TYPE PUMP FAILED DURING ENGINE START. THE R OTARY PISTON-TYPE PUMP SEIZED; THUS, SHEARING ITS DRIVE SHAFT. METAL PARTICLES FROM THE PUMP'S VANE SENT DOWNSTREAM IN THE HYDRAULIC SYSTEM WERE CAUGHT BY THE HYD FILTER. LINES WERE FLUSHED CLEAN AND NEW FILTER INSTALLED. FIRST REPLACEME NT PUMP (YELLOW TAGGED AS OVERHAULED) WOULD NOT BUILD UP PRESSURE DUE TO STICKING HIGH-BYPASS VALVE. THE SECOND UNIT (A LSO TAGGED AS OVERHAULED), OPERATED AT TOO HIGH A PRESSURE. THE THIRD UNIT (FACTORY NEW), FINALLY OPS CHECKED OK. 2 L 7 2 4R A669 1996032900232 19960329 00232 CE 1996 3 29 96ZZZX1347 1 19960201 G 5711 45A10209007 SPAR CAP BEECH MU300 400BEECH CE LT WING CRACKED G K NONE K FLUID LOSS IN INSP/MAINT 1 CE 07 3240J 559 RK92 WHILE TROUBLESHOOTING LT WING FUEL LEAK, FOUND A 40-INCH CRACK IN LT SPAR AT CHANNEL OF UPPER SPAR CAP. FURTHER INVESTI GATION REVEALED THIS AIRCRAFT HAD BEEN SUBJECT TO A HARD LANDING. PHASE 1 HARD LANDING INSPECTION WAS COMPLETED ON THE FUSELAGE AND A PHASE 2 HARD LANDING INSPECTION WAS COMPLETED ON THE WINGS. SUBMITTER RECOMMENDS INSPECTION OF WING SPAR S IN CONJUNCTION WITH HARD LANDING INSPECTION AND IF CRACK IS SUSPECTED, PERFORM NDI. 2 H 7 2 4F RT A16SW 1996032900233 19960329 00233 EU 1996 3 29 96ZZZX1348 1 19960215 G 2130 5511172251 TRANSFORMER 6331166395 AIRBUS 320 A320231 3930325 EU PRESS SYS DEFECTIVE B L SI3R K NONE O OTHER IN INSP/MAINT 1 NE 03 4919 TR1 TRANSFORMER EXHIBITS FRACTURE SOLDER JOINTS. MAXIMUM SOLDER CONNECTS IS 11. THIS CONDITION CAUSES AN INTERMITTENT FAILURE OF THE AIRCRAFT PRESSURIZATION SYSTEM. SPECIFICALLY, THIS CONDITION WILL CAUSE ONE OR BOTH OF THE ELECTRONIC AC TUATOR BOXES WHICH DRIVE THE OUTFLOW GATE TO SHUT DOWN. 2 L 7 2 4F RT A28NM 1996032900234 19960329 00234 EU 1996 3 29 96ZZZX1349 1 19960226 G 2130 TRANSFORMER 6331166395 AIRBUS 320 A320231 3930325 EU PRESS SYS DEFECTIVE B L SI3R K NONE O OTHER IN INSP/MAINT 1 NE 03 8371 4471 TR1 TRANSFORMER EXHIBITS FRACTURE SOLDER JOINTS. MAXIMUM SOLDLER CONNECTIONS IS 11. THIS CONDITION CAUSES AN INTERMITT ENT FAILURE OF THE AIRCRAFT PRESSURIZATION SYSTEM. SPECIFICALLY, THIS CONDITION WILL CAUSE ONE OR BOTH OF THE ELECTRONI C ACTUATOR BOXES WHICH DRIVE THE OUTFLOW GATE TO SHUT DOWN. 2 L 7 2 4F RT A28NM 1996032900235 19960329 00235 CE 1996 3 29 96ZZZX1350 1 19960201 G 5711 45A10209007 SPAR CAP BEECH MU300 400BEECH CE LT WING CRACKED D A K NONE K FLUID LOSS IN INSP/MAINT 1 CE 07 3240J 559 RK92 WHILE TROUBLESHOOTING LT WING FUEL LEAK, FOUND 40-INCH CRACK IN LT SPAR AT CHANNEL OF UPPER SPAR CAP. FURTHER INVESTIGA TION REVEALED AIRCRAFT HAD A HARD LANDING. PERFORMED PHASE 1 HARD LANDING INSPECTION ON FUSELAGE AND PHASE 2 INSPECTION ON WINGS TO THIS POINT. SUBMITTER RECOMMENDS INSPECTING WING SPARS ON HARD LANDING INSPECTION AND IF SUSPECT CRACK, PE RFORM NDI. 2 H 7 2 4F RT A16SW 1996032900236 19960329 00236 EU 1996 3 29 96ZZZX1351 1 19960228 G 5510 BULKHEAD AVIONS R2160 R2160 0960101 EU STAB BRG BRKT CRACKED D A K NONE O OTHER IN INSP/MAINT 1 WP 05 216RN C200 VERTICAL CRACKS FOUND INTERCONNECTING ALL FOUR BOLT HOLES DRILLED IN THE AFT STABILATOR BULKHEAD TO WHICH THE STABILATOR BEARING BRACKET ATTACHES TO ON THE RT SIDE. SUSPECT CAUSE: EXCESSIVE AIR LOADS ON THE STABILATOR DUE TO AEROBATIC MAN EUVERS (HAMMER HEADS AND SNAP ROLLS), AND AFT BULKHEAD BEING OF INADEQUATE STRENGTH TO ABSORB STRESSES. SUBMITTER RECOM MENDS PERIODIC INSPECTIONS OF AFT BULKHEAD EVERY 100 HOURS OR MORE IF AEROBATIC OR REINFORCEMENT OF BULKHEAD (REFER TO F ORM 337). TT ON AIRCRAFT, 3600 HOURS. 1 L 7 1 3O RT A48EU 1996032900237 19960329 00237 1996 3 29 96ZZZX1352 4 19960305 G 2562 BP1026 BATTERY MERL BEECH 58 58 1152740 CE ELT MISMFG D S K NONE W INADEQUATE Q C IN INSP/MAINT 1 EA 05 65FS TH1084 AN ATTEMPT TO REPLACE A BATTERY PACK IN AN ELT TRANSMITTER FAILED. EXAMINATION REVEALED THE PACK WAS TOO WIDE AND WOULD NOT FIT THE HOUSING OF THE ELT. ANOTHER WAS ORDERED AND FIT OK. MANUFACTURER WAS MERL INC., OF CONNECTICUT. 1 L 7 2 3O 3A16 1996032900238 19960329 00238 1996 3 29 96ZZZX1353 4 19960222 G 2211 065001803 COMPUTER KCP320 PIPER PA42 PA42720 7104212 SO GLIDESLOPE FAULTY B L A CE4R O OTHER F FLT CONT AFFECTED AP APPROACH 1 AL 03 2247R 3271 425501005 ON 2-21-96, SUBMITTER MADE A CONFERENCE CALL WHICH INVOLVED ALLIED SIGNAL TO ESTABLISH COHERENT DIALOG CONCERNING GLIDES LOPE COUPLING PROBLEM. RESOLVED 2 PROBLEMS MAY EXIST. NR 1, GLIDESLOPE TRIES TO COUPLE A SIGNAL BEYOND PARAMETERS ESTA BLISHED IN PILOT'S OPERATING HANDBOOK. NR 2, WHEN AUTOPILOT IS IN APPR CPLD MODE AND GLIDESLOPE SIGNAL DROPS OUT AND CO MES BACK, AUTOPILOT COMMANDS ACFT PITCH UP OR DOWN TO INTERCEPT GLIDESLOPE AT CLOSEST POINT. IT WAS STRESSED REPEATEDLY TO ALLIED SIGNAL THAT DURING ONE APPROACH, ACFT PITCHED UP AND AIRSPEED DROPPED TO 90 KNOTS BEFORE PILOT COULD DISENGAG E AUTOPILOT AND REGAIN NORMAL FLIGHT PROFILE OF ACFT. 1 L 7 2 4T A23SO 1996032900239 19960329 00239 GL 1996 3 29 96ZZZX1354 3 19960308 G 6114 D7015C93 HUB MCAULY 3AF32C 3AF32C93 GL NR 1 SOCKET CRACKED B ME4D K NONE O OTHER IN INSP/MAINT 1 SO 15 790274 DURING INSPECTION, HUB FOUND CRACKED UNDER WELCH PLUG ON NR 1 BLADE SOCKET. HUB HAS BEEN SCRAPPED. 5 C P22EA 1996032900241 19960329 00241 CE 1996 3 29 96ZZZX1356 1 19960201 G 5610 WINDOW LEAR 35 35A 5170602 CE COCKPIT LT OUT OF SPEC B DP2R K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 05 2MIL 1008 INSPECTED WINDSHIELD FOR PROPER THICKNESS. THICKNESS RANGE FELL BELOW LEAR NDT MANUAL SPECIFICATIONS. MINIMUM ALLOWED THICKNESS 1.00 INCH. TESTED PART THICKNESS .097 INCH. SUBMITTER STATED RANDOM INSPECTION OF WINDSHIELD IN AREAS REQUES TED. 2 L 7 2 4F A10CE 1996032900244 19960329 00244 NE 1996 3 29 96ZZZX1359 2 19960209 G 7230 BLADE RKWELL NA265 NA26560 7630106 CE PWA JT12 JT12A8 52042 NE COMPRESSOR RUB B JV2R K NONE O OTHER IN INSP/MAINT 1 CE 03 401MS 1210 30617 P673149NB DURING INSPECTION OF ENGINE, SN P673149NB, A CRACKED INLET GUIDE VANE PROMPTED REMOVAL OF INLET CASE FOR REPAIRS. WITH CASE REMOVED, A COMPRESSOR BLADE RUB, WHICH RESULTED IN DETERIORATION TO A STATOR, WAS NOTED AND REPORTED. AUTHORIZATIO N WAS RECEIVED FROM CUSTOMER TO DISASSEMBLE COMPRESSOR FOR FURTHER INVESTIGATION. UPON DISASSEMBLY OF COMPRESSOR, SEVER E CORROSION NOTED ON STEEL COMPONENTS. A CORROSION INSPECTION AND SUBSEQUENT COMPRESSOR OVERHAUL PER P&WA, SB 1508R16, WAS INITIATED. 2 L 7 2 4J 4 J RT A2WE 1E9 1996032900245 19960329 00245 NE 1996 3 29 96ZZZX1360 2 19960209 G 7250 566101 BLADE RKWELL NA265 NA26560 7630106 CE PWA JT12 JT12A8 52042 NE 1ST STG TURBINE OVERLAP B L JV2R K NONE O OTHER IN INSP/MAINT 1 CE 03 401MS 1210 30617 P673152NB DUE TO CORROSION DMG DISCOVERED ON RT ENG, CUSTOMER ELECTED TO DISASSEMBLE LT ENG FOR CORROSION INSP, & SUBSEQUENT COMPR OVERHAUL PER P&WA. UPON DISASSEMBLY OF COMPR, SEVERE CORROSION NOTED ON STEEL COMPONENTS. CORRRODED STEEL DISK REJECT ED. CUSTOMER ELECTED TO REPLACE LIFE LIMITED DISKS IN BOTH ENGS TO ALLOW ENGS TO CONTINUE IN SERV TO 3000 HRS TBO; THUS , PROMPTING TO ACCESS TURB AREA ON ENG, SN P673152NB, TO REPLACE LIFE LIMITED TURB DISKS. TURB BLADES REMOVED DUE TO RE PLACMENT OF LIFE LIMITED TURB DISK. NOTED 76 1ST STG TURB BLADES SHOWED SIGNS OF SHROUD OVERLAP, DISPLACED METAL & META L SEPARATION IN NOTCH SURFACE OF SHROUD. 14 TURB BLADES PREV INSTALLED IN NEW COND (TT: ZERO) & 2 WERE SERVICEABLE. 2 L 7 2 4J 4 J RT A2WE 1E9 1996032900332 19960329 00332 CE 1996 3 29 96ZZZX1361 1 19960118 G 2710 551426049 CABLE GUARD CESSNA 500 560CESSNA 2076750 CE AIL CONT SECTOR CHAFED B A EBVR K NONE O OTHER IN INSP/MAINT 1 GL 09 141AQ 2409 5600141 THE AILERON LOWER SECTOR PLATE, CABLE GUARD, WAS CHAFING INTO THE PULLEY BOLT OF THE EMERGENCY GEAR BRACKET (PN 6514160- 109) FROM INSUFFICIENT CLEARANCE. SHIMMED AILERON SECTOR UPWARD TO PROVIDE CLEARANCE. 2 L 7 2 4F RT A22CE 1996032900335 19960329 00335 CE 1996 3 29 96ZZZX1364 1 19960220 G 7603 C800741 BALL JOINT 1223890413 BEECH 2000 2000 1152000 CE RT ENG PWR LEVER DISCONNECTED D A O OTHER O OTHER CR CRUISE 1 WP 07 214JB 1083 NC14 RIGHT ENGINE POWER LEVER CABLE BALL JOINT ASSEMBLY CAME UNSCREWED AT RT ENGINE DISCONNECTING RT POWER LEVER CONTROL TO R T ENGINE DURING FLIGHT. THE COLLAR OF BALL JOINT ASSEMBLY IS STAKED TO PROVIDE A FRICTION LOCK BETWEEN OUTER COLLAR AND INNER NUT. SUBMITTER STATES THIS METHOD OF FRICTION LOCK DID NOT HOLD. TO HELP PREVENT THIS, APPLY LOKTITE TO THREADS UPON ASSEMBLY AND INSPECT BALL JOINT ASSEMBLY AT INSPECTIONS. 1 L 7 2 4T RT A38ACE 1996032900336 19960329 00336 EA 1996 3 29 96ZZZX1365 1 19960228 G 3310 LH10B POWER SUPPLY CNDAIR CL600 CL6002B16 1900305 EA OVERHEAD PANEL DEFECTIVE B SH5R K NONE B L SMOKE/FUMES/ODORS/SPARKS NO TEST IN INSP/MAINT 1 NE 03 604CC 354 5301 NUMEROUS PUSH BUTTON ANNUNCIATORS (PBA'S) WILL NOT LAMP TEST ON OVERHEAD PANEL. CONFIRMED DISCREPANCY, FOUND TO BE A DE FECTIVE BRIGHT/DIM POWER SUPPLY. REMOVED AND REPLACED DEFECTIVE UNIT. UNIT HAS A BURNING ELECTRICAL SMELL TO IT THAT W AS NOTICEABLE IN THE COCKPIT. 2 L 7 2 4F RT A21EA 1996032900337 19960329 00337 NM 1996 3 29 96ZZZX1366 1 19960226 G 5320 AND101362402 T-CHORD BOEING 737 737247 138448D NM LT FRAME STR 27 CORRODED B S5WR K NONE O OTHER IN INSP/MAINT 1 SW 01 303VA 54742 20125 DURING SS1D INSPECTION OF E AND E DOOR CUT-OUT AREA, FOUND CORROSION IN T-CHORD FRAME AND SKIN IN LT FRAME STR 27. SUSP ECT CAUSE DUE TO LAVATORY DRAIN LEAK AND LACK OF PROPER DRAINAGE. SUBMITTER STATED ATTENTION SHOULD BE PAID TO ANY FLUI D LEADS IN FWD GALLEY AND LAV AREA AND ANY DEBRIS BLOCKING DRAIN HOLES IN LOWER FUSELAGE. 2 L 7 2 4F A16WE 1996032900339 19960329 00339 EA 1996 3 29 96ZZZX1368 1 19960226 G 3250 70263 SERVO VALVE CNDAIR CL601 CL6013A 8070802 EA NLG STEERING SHORTED D K NONE O OTHER IN INSP/MAINT 1 NE 03 611GS 2096 292 5082 NLG STEERING FAILED. FOUND SERVO VALVE SHORTED TO CASE AND SECONDARY WINDING TO HAVE EXTREMELY HIGH RESISTANCE. 2 L 7 2 4F RT A21EA 1996032900340 19960329 00340 EA 1996 3 29 96ZZZX1369 1 19960305 G 7830 32725703 SCREW SHAFT CNDAIR CL600 CL6002B16 1900305 EA BALL SCREW CORRODED B SH5R K NONE O OTHER IN INSP/MAINT 1 NE 03 PTOSA 5075 BALLSCREW ACTUATORS SCREW SHAFTS WERE FOUND CORRODED. NO CORROSION ALLOWED IAW COMPONENT MAINTENANCE. MANUAL CHAPTER 7 8-30-29, PAGE 505, PARAGRAPH 5B, ITEM NR 5. (BRAZIL) 2 L 7 2 4F RT A21EA 1996032900341 19960329 00341 CE 1996 3 29 96ZZZX1370 1 19960219 G 2435 3143503600919 BEARING LUCAS 23085004 CESSNA 500 560CESSNA 2076750 CE START/GEN FAILED D B A EMER. DESCENT UNSCHED LANDING H E ELECT. POWER LOSS-50 PC VIBRATION/BUFFET CR CRUISE 1 GL 03 168CV 1732 705 3210 5600168 LEFT GENERATOR FAILURE OCCURRED AT 37,000 FEET. THE GENERATOR WOULD NOT RESET. DURING DESCENT, A HUM AND VIBRATION OCC URRED FROM LEFT ENGINE. ENGINE WAS IDLED AND LEFT AT IDLE THROUGHOUT DESCENT AND LANDING. UPON INSPECTION, IT APPEARED THE DRIVE END BEARING OF THE START/GENERATOR HAD FAILED TOTALLY DESTROYING THAT END OF THE GENERATOR (UNREPAIRABLE). S UBMITTER RECOMMENDS OPERATORS REPLACE BEARINGS ANYTIME BRUSHES ARE REPLACED, USUALLY AROUND 600-700 HOURS AND NOT WAIT U NTIL 1,000-HOUR OVERHAUL TIME. 2 L 7 2 4F RT A22CE 1996032900342 19960329 00342 SW 1996 3 29 96ZZZX1371 1 19960311 G 5751 2734023008 SPAR 2734000034 SWRNGN SA227 SA227AC 8780603 SW AIL HINGE CRACKED B HAXR K NONE O OTHER IN INSP/MAINT 1 SW 11 361AE 15492 C015 AC676 DURING DISASSEMBLY OF AILERON TO REPLACE CRACKED AILERON SKINS, SPAR FOUND TO HAVE 3 CRACKS. THERE ARE TWO, 1.5 INCH CR ACKS IN AREA OF OUTBOARD HINGE FITTING ATTACH HOLES AND ONE, .5 INCH CRACK IN AREA OF CENTER HINGE FITTING ATTACH HOLE. CRACKS ARE SUSPECTED TO BE FATIGUE CRACKS. 2 L 7 2 4T RT A8SW 1996032900344 19960329 00344 CE 1996 3 29 96ZZZX1373 1 19960124 G 7714 32005 TACH GENERATOR CESSNA 500 550 2076604 CE LT ENG N1 TACH IMPROPER PART B EBVR K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 09 114DS 376 232324 5500397 THE LT ENGINE N1 TACHOMETER GENERATOR DID NOT RESEMBLE THE OTHER TACHOMETER GENERATORS. INVESTIGATION FOUND VENDOR-ADVA NCE POWER, INC., IS NOT AN APPROVED CESSNA/CITATION VENDOR FOR THIS PART. ENGINE LOG BOOK SHOWS A CITATION PART NUMBER WHEN THIS UNIT WAS INSTALLED. THIS UNIT WAS BLACK IN COLOR AND SMALLER IN DIAMETER THAN THE APPROVED UNITS. 1 L 7 2 4F A22CE 1996032900345 19960329 00345 CE 1996 3 29 96ZZZX1374 1 19960304 G 5730 PANEL LEAR 35 35A 5170602 CE LT WING FUEL LOOSE SCREWS D K NONE K FLUID LOSS IN INSP/MAINT 1 EA 21 133EJ 133 OBSERVED FUEL LEAKING FROM LT WING ROOT. TRACED SOURCE OF LEAK TO LT WING LEADING EDGE BEHIND LEADING EDGE DEICE STRIP. FOUND NUMEROUS LOOSE SCREWS. RETORQUED SCREWS ON BOTH RT AND LT WINGS. LEAK SEEMED TO STOP. UPON FURTHER INSPECTION APPROXIMATELY 1 WEEK LATER FOUND EDGE SEEPING AGAIN (FRI 3-1-96). SEEP WAS NOT WITHIN L-35 MINIMUM LIMITS. SUSPECT LA CK OF TORQUE ON SCREWS LEADING TO DETERIORATION OF TANK SEALER. 2 L 7 2 4F A10CE 1996032900346 19960329 00346 CE 1996 3 29 96ZZZX1375 1 19960201 G 3240 2307006113 HOSE LEAR 25 25 5170506 CE RT MLG BRAKE LEAKING H O OTHER K FLUID LOSS LD LANDING 1 CE 05 500DL 027 RIGHT OUTBOARD BRAKE HOSE LEAKING AT UPPER END NEAR HOSE (FLEX) FITTING. OCCURRED IN-FLIGHT, WAS FOUND ON LANDING. HYD RAULIC PRESSURE WENT TO ZERO, AND ACFT PULLED TO LEFT DURING BRAKING. 2 L 7 2 4J A10CE 1996032900347 19960329 00347 CE 1996 3 29 96ZZZX1376 1 19960315 G 5210 1014401041 ANCHOR BEECH 200 200BEECH 1152920 CE DOOR CABLE ARM FAILED D K NONE O OTHER IN INSP/MAINT 1 WP 27 5559X 1450 BB1372 PASSENGER WAS DEBOARDING AIRCRAFT WHEN DOOR CABLE ATTACH ANCHOR FAILED CAUSING DOOR TO DROP. PASSENGER FELL TO GROUND A ND SUSTAINED MINOR INJURY. SUBMITTER STATED INSPECT CLOSELY AT INSPECTIONS TO UNCOVER SMALL DEFECTS WHICH COULD LEAD TO THIS TYPE OF FAILURE. ALSO, CHECK TORQUE OF MOUNTING SCREWS WHICH TEND TO LOOSEN. 1 L 7 2 4T A24CE 1996032900348 19960329 00348 NE 1996 3 29 96ZZZX1377 2 19960210 G 7261 3008127 GEARSHAFT 3024287 PWA PT6 PT6A42 52043 NE OIL CAV PMP SHEARED D E A ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 GL 17 18260 2730 D618 PCE93133 PILOT REPORTED A LOW FUEL PRESSURE LIGHT FOLLOWED BY AN AUTOFEATHER ON LEFT ENGINE. PILOT SHUT DOWN ENGINE AND LANDED W ITHOUT INCIDENCE. UPON INVESTIGATION, NOTED THE OIL LEVEL LOW, THERE WAS OIL IN THE EXHAUST CASE, AND METAL PARTICLES A ND FLAKES PRESENT IN THE OIL FILTER. FURTHER INVESTIGATION SHOWED SCAVENGE PUMP SHAFT HAD SHEARED. ENGINE REMOVED FOR METAL IN OIL. 4 T E4EA 1996032900349 19960329 00349 CE 1996 3 29 96ZZZX1378 1 19960307 G 5730 SKIN BEECH 200 200CBEECH 1152926 CE LT WS 194.829 MISSING D K NONE O OTHER IN INSP/MAINT 1 SO 11 44MR BL27 WHILE PERFORMING THE INCOMING INSPECTION ON THIS AIRCRAFT, A SMALL PORTION OF METAL WAS DISCOVERED MISSING FROM THE LOWE R SURFACE OF THE LEFT WING AT STA 194.829 ALONG THE FWD MAIN SPAR. 1 L 7 2 4T A24CE 1996032900350 19960329 00350 EA 1996 3 29 96ZZZX1379 2 19960131 G 7250 SHROUD RING BEECH 200 B200 1152922 CE PWA PT6 PT6A41 52043 EA PT SECTION LUG MISSING B RX8R K NONE O OTHER IN INSP/MAINT 1 SO 15 203BS BB476 PCE85365 BINDING, WHEN PROPELLER WAS ROTATED, FOUND DURING MORNING PRE-FLIGHT. THE POWER SECTION WAS REMOVED AND SENT TO DALLGO AIRMOTIVE. D.A. FOUND A MISSING LOCATING LUG FROM THE PT SHROUD RING THAT WAS BINDING UP THE ROTATION OF THE POWER SECT ION. 1 L 7 2 4T 4 T A24CE E4EA 1996032900351 19960329 00351 CE 1996 3 29 96ZZZX1380 1 19960314 G 3230 GEAR LEAR 25 25B 5170511 CE MLG FAIL TO EXTEND H K NONE W INADEQUATE Q C IN INSP/MAINT 1 AL 03 235JW 096 LANDING GEAR FAILED TO EXTEND NORMALLY, BUT WAS EXTENDED MANUALLY. INVESTIGATION REVEALED MLG SYSTEM HAD BEEN IMPROPERL Y LUBRICATION SERVICED. 2 L 7 2 4J A10CE 1996032900352 19960329 00352 EA 1996 3 29 96ZZZX1381 2 19960314 G 7200 ENGINE BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA PWR SECTION FAILED D A UNSCHED LANDING O J OTHER WARNING INDICATION CR CRUISE 1 SW 09 89MP 6581 602 BB166 PCE80363 PILOT REPORTED HE WAS IN LEVEL FLIGHT WITH CRUISE POWER AT OVER 20,000 FEET, WHEN HE HEARD A LOUD BANG AND NOTICED THE I .T.T. CLIMBING RAPIDLY. WHEN TURNING THE PROP BY HAND, A GRINDING NOISE COULD BE HEARD IN THE POWER SECTION. AFTER REM OVING THE COWLING, IT WAS NOTICED THE INLET TO THE GAS GENERATOR HAD NUMEROUS CRACKS AROUND IT AND THE GAS GENERATOR AND ACCESSORY GEARBOX WERE SEIZED. 1 L 7 2 4T 4 T A24CE E4EA 1996032900353 19960329 00353 EA 1996 3 29 96ZZZX1382 2 19960315 G 7200 ENGINE BEECH 100 100BEECH 1152916 CE PWA PT6 PT6A28 EA LT ENG PT SECT FAILED D O OTHER J WARNING INDICATION DE DESCENT 1 SW 09 4200A 5978 3101 B64 PCE50129 PILOT REPORTED LOUD NOISE FOLLOWED BY CHIP DETECTOR WARNING WHILE DESCENDING THROUGH 9,000 FEET. WHEN VIEWED THROUGH EX HAUST OPENINGS, ENGINE HAS SEVERE THERMAL AND MECHANICAL DAMAGE. ALL POWER TURBINE BLADES BROKEN. SOME POWER TURBINE G UIDE VANES MISSING AND COMPRESSOR TURBINE BLADES BROKEN. ENGINE WAS NOT DISASSEMBLED AT THIS LOCATION. 1 L 7 2 3T 4 T A14CE E4EA 1996032900354 19960329 00354 EA 1996 3 29 96ZZZX1383 1 19960314 G 7603 2100140003 GEARBOX CNDAIR CL600 CL6002B16 1900305 EA RT ENG THROTTLE FAILED G K NONE O OTHER IN INSP/MAINT 1 SO 01 80BF 148 518 5117 PILOTS WERE REPORTING A STIFFNESS OR RESISTANCE WHEN MOVING THE THROTTLE ABOVE IDLE. THIS RESISTANCE WOULD COME AND GO. LATER, FOUND TO OCCUR AFTER RT THRUST REVERSER ACTUATION. INSPECTION REVEALED THE RT ENGINE THROTTLE CONTROL GEARBOX HAD FAILED. SPECIFICALLY, THE SPRING INSIDE THAT ATTACHES TO THE THRUST REVERSER AUTOMATIC THROTTLE RETARD CABLE HAD BR OKEN. THERE WAS NO TENSION ON CABLE OR THE THROTTLE RETARD BELLCRANK. RESISTANCE APPARENTLY COMING FROM SLACK IN THIS CABLE. 2 L 7 2 4F RT A21EA 1996032900355 19960329 00355 NE 1996 3 29 96ZZZX1384 2 19960201 G 7532 34A39709 COVER A39710K PWA JT9 JT9* 52054 NE PRBC IMPROPER WELD B SF3R K NONE W INADEQUATE Q C IN INSP/MAINT 1 NE 03 1151823 RECEIVED CECO P.R.B.C. FROM TOWER AIR INC., FOR ZERO TIME OVERHAUL 8-30-95. DISASSEMBLY AND INSPECTION OF COVER REVEALE D UNAUTHORIZED REWORK HAD BEEN PERFORMED (WELD). 4 F E20EA 1996032900356 19960329 00356 1996 3 29 96ZZZX1385 4 19960122 G 2562 1104 ELT ARTEX HUGHES 369 OH6A WP ANTENNA WIRE BROKEN B EHHR K NONE O OTHER IN INSP/MAINT 1 EA 17 1874M 42600 691183 WEAK TRANSMISSION BATTERY VOLTAGE GOOD. WIRE BROKEN OFF ANTENNA CONNECTOR INSIDE TRANSMITTER FROM CIRCUIT BOARD. RETUR NED TO MANUFACTURER FOR REPAIR. 1 G 7 1 3U H3WE 1996032900358 19960329 00358 NE 1996 3 29 96ZZZX1387 2 19960227 G 7261 OIL LINE SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1B 6OO30 NE GP INLET BLOCKED D O OTHER J WARNING INDICATION CR CRUISE 1 WP 13 352HH 2714 4453 LOW ENGINE OIL PRESSURE LIGHT ON, LOW OIL PRESSURE INDICATION DURING FLIGHT. COKE BLOCKING OIL LINE AT THE INLET FITTIN G OF THE GAS PRODUCER REAR BEARING CHIP DETECTOR SCREEN. 1 G 7 1 3U 3 U NC H9EU E19EU 1996032900359 19960329 00359 EU 1996 3 29 96ZZZX1388 1 19960226 G 2913 350A35103004 SHAFT 20117224 SNIAS 350 AS350BA 8680817 EU HYD PUMP WORN D K NONE O OTHER IN INSP/MAINT 1 WP 13 353HH 3074 2707 HYDRAULIC FAILURE DUE TO WEAR OF HYDRAULIC PUMP AND SHAFT SPLINES AND SHAFT COUPLING SPLINES. HYDRAULIC PUMP HARD TO RO TATE AFTER REMOVAL. REPLACED PUMP, COUPLING SHAFT, AND BEARING. 1 G 7 1 3U NC H9EU 1996032900360 19960329 00360 1996 3 29 96ZZZX1389 4 19960223 G 3421 111303 INDICATOR ASTRONAUTICS BELL 412 412 1182202 SW PILOT ATTITUDE WIRE CHAFED B A FE6R O OTHER B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 NM 11 412DE 1982 36033 PILOTS ATTITUDE INDICATOR STARTED SPINNING, SMOKE DETECTED IN COCKPIT. FOUND PILOTS ATTITUDE INDICATOR ISOLATION AMP FA ILED AND SOURCE OF SMOKE. FOUND WIRING AT ATTITUDE INDICATOR HAD CHAFED ON DEFOGGER MOUNTING BOLT SHORTING AMP SIGNAL T O GROUND AND CAUSING AMP FAILURE AND ATTITUDE INDICATION TO SPIN LATERALLY. REPAIRED WIRE AND APPLIED CHAFE PROTECTION TO WIRE HARNESS. SUBMITTER STATED THERE IS INSUFFICIENT SPACE BETWEEN BOLT HEAD AND REAR OF CONNECTOR. 1 G 7 2 4U H4SW 1996032900361 19960329 00361 SW 1996 3 29 96ZZZX1390 1 19960220 G 6730 206076062003 SERVO BELL 206 206L 1181522 SW CYCLIC WATER CONTAM B A XJ2R K NONE F FLT CONT AFFECTED NR NOT REPORTED 1 WP 01 700EA 1299 RH3904A 51497 CYCLIC STICK WOULD PULL HARD FORWARD WHEN COLD. CUSTOMER REMOVED SERVO AND SENT IN FOR REPAIR. RECEIVED UNIT AND BOOT WAS TORN AROUND INPUT VALVE. FUNCTIONAL TEST UNIT FOUND, NO PROBLEM. PUT UNIT IN FREEZER AND INPUT WOULD BECOME LOCKED UP. DISASSEMBLED UNIT AND FOUND WATER BEHIND INPUT VALVE. TORN BOOT ALLOWED WATER TO ENTER INPUT VALVE. 1 G 7 1 3U H2SW 1996040500002 19960405 00002 SW 1996 4 5 96ZZZX1391 1 19960201 G 6320 430136201 BEARING BELL 222 222U 1182140 SW GEARBOX NR 2 FAILED B BAQR O OTHER J WARNING INDICATION CR CRUISE 1 EA 03 587MC 776 47566 DURING FLIGHT, BOTH GEARBOX AND REAR BEARING SUPPORT HOUSING CHIP LIGHTS ILLUMINATED. UPON DISASSEMBLY OF THE ENGINE, F OUND THE NR 2 BEARING ROLLER CAGE SPLIT IN TWO. 1 G 7 2 3U H9SW 1996040500029 19960405 00029 SW 1996 4 5 96ZZZX1418 1 19960111 G 6410 206016201127 BLADE BELL 206 206L1 1182107 SW T/R BEARINGS CRACKED B ZV1R K NONE O OTHER IN INSP/MAINT 1 SW 03 577E 1196 CS6376 45577 DURING ROUTINE MAINTENANCE, FOUND TAIL ROTOR BLADE INBOARD BEARINGS CRACKED. TSI: 743.8 HOURS. 1 G 7 1 3U H2SW 1996040500030 19960405 00030 SW 1996 4 5 96ZZZX1419 1 19960111 G 6410 206016201127 BLADE BELL 206 206L1 1182107 SW T/R BEARINGS CRACKED B ZV1R K NONE O OTHER IN INSP/MAINT 1 SW 03 577E 1196 CS6372 45577 DURING ROUTINE MAINTENANCE, FOUND TAIL ROTOR BLADE INBOARD BEARINGS CRACKED. TSI: 743.8 HOURS. 1 G 7 1 3U H2SW 1996040500031 19960405 00031 NM 1996 4 5 96ZZZX1420 1 19960106 G 5320 PO100092 SUPPORT BOEING 727 727259 138408J NM BS 389 CORRODED B S3BR K NONE O OTHER IN INSP/MAINT 1 WP 01 203AV 22474 FLOOR SUPPORT STRUCTURE AT STA 389, RBL 10 INCHES TO RBL 42 INCHES HAS LEVEL 2 CORROSION. REMOVED AND REPLACED FLOOR SU PPORT PER SRM 53-10-2, SRM 51-10-2, AND SRM 51-30-2. 2 L 7 3 4F A3WE 1996040500032 19960405 00032 NM 1996 4 5 96ZZZX1421 1 19960107 G 5320 69403752 SUPPORT BOEING 727 727259 138408J NM BS 360-460 CORRODED B S3BR K NONE O OTHER IN INSP/MAINT 1 WP 01 203AV 22474 STA 360-STA 460 - RBL 10, FLOOR SUPPORT STRUCTURE HAS LEVEL 2 CORROSION, ALSO LEVEL 1 ON STA 360 FLOOR BEAM UPPER SURFAC E AT RBL 10. REPLACED FLOOR SUPPORT STRUCTURE, PN 69-40375-2 (3 EACH) PER 51-10-1, FIG 14, CORROSION REMOVED AND MATERI AL IS IN-LIMITS PER 53-10-1 FLOOR BEAM. 2 L 7 3 4F A3WE 1996040500033 19960405 00033 NM 1996 4 5 96ZZZX1422 1 19960106 G 5347 SEAT TRACK BOEING 727 727259 138408J NM BS 340-460 CORRODED B S3BR K NONE O OTHER IN INSP/MAINT 1 WP 01 203AV 22474 SEAT TRACK RBL 42, STA 340 TO STA 460, SEVERAL AREAS OF LEVEL 2 CORROSION ALONG TOP OF SEAT TRACK; ALSO, UNDERSIDE OF FL ANGE. REMOVED AND REPLACED SEAT TRACK PER SRM 51-10-4 AND SRM 53-10-05. 2 L 7 3 4F A3WE 1996040500034 19960405 00034 NM 1996 4 5 96ZZZX1423 1 19960107 G 5320 ANGLE BOEING 727 727259 138408J NM BS 1040-1060 CORROSION B S3BR K NONE O OTHER IN INSP/MAINT 1 WP 01 203AV 22474 AFT MAIN ENTRY DOOR L2 SUPPORT ANGLE FOR L2 DOOR SCUFF PLATE HAS LIGHT LEVEL 1 AND EXFOLIATION LEVEL 2 CORROSION AROUND FASTENER HOLES, STA 1040.0 - STA 1060.0, LBL 62.0. REMOVED CORROSION AND TREATED AND INSTALLED 'L' ANGLE DOUBLER PER SR M 51-40-2. 2 L 7 3 4F A3WE 1996040500035 19960405 00035 NM 1996 4 5 96ZZZX1424 1 19960106 G 5320 ANGLE BOEING 727 727259 138408J NM BS 440-470 CORRODED B S3BR K NONE O OTHER IN INSP/MAINT 1 WP 01 203AV 22474 FORWARD CABIN 'L' ANGLE AT RBL 60, STA 440 - STA 470, HAS LEVEL 2 CORROSION. CUT OUT CORRODED AREA AND FABRICATED AND S PLICED NEW 'L' ANGLE AND INSTALLED PER SRM 51-10-1. 2 L 7 3 4F A3WE 1996040500036 19960405 00036 NM 1996 4 5 96ZZZX1425 1 19960106 G 5320 SUPPORT BOEING 727 727259 138408J NM BS 1030-1050 CORRODED B S3BR K NONE O OTHER IN INSP/MAINT 1 WP 01 203AV 22474 FLOOR SUPPORT STRUCTURE AT STA 1030 - STA 1050.0, RBL 10 HAS LEVEL 2 CORROSION. FABRICATED AND INSTALLED FLOOR SUPPORT PER SRM 51-10-1 AND SRM 51-40-2. 2 L 7 3 4F A3WE 1996040500040 19960405 00040 NM 1996 4 5 96ZZZX1429 1 19960106 G 5320 ANGLE BOEING 727 727259 138408J NM BS 1060 CORRODED B S3BR K NONE O OTHER IN INSP/MAINT 1 WP 01 203AV 22474 AFT SERVICE DOOR, R2, L-ANGLE FOR R2 DOOR SCUFF PLATE SUPPORT HAS LEVEL 2 CORROSION AT BS 1060. 2 L 7 3 4F A3WE 1996040500041 19960405 00041 NM 1996 4 5 96ZZZX1430 1 19960105 G 5315 FLOOR BEAM BOEING 727 727259 138408J NM BS 970-990 CORRODED B S3BR K NONE O OTHER IN INSP/MAINT 1 WP 01 203AV 22474 AFT CABIN FLOORING FASTENER HOLES ON FLOOR BEAM AT STA 950, LBL 25 - RBL 25, HAS LIGHT SURFACE CORROSION; ALSO, ON INTER COSTAL AT BL ZERO, STA 970 - STA 990, LEVEL 1 CORROSION. REMOVED CORROSION AND TREATED AND PRIMED STOP DRILLED CRACKS A ND FABRICATED L-ANGLE DOUBLER AND INSTALLED PER SRM 51-10-02, SRM 51-10-06, SRM 53-10-01, AND SRM 51-20-02. 2 L 7 3 4F A3WE 1996040500042 19960405 00042 NM 1996 4 5 96ZZZX1431 1 19960104 G 5320 SPLICE BOEING 727 727259 138408J NM CABIN CORRODED B S3BR K NONE O OTHER IN INSP/MAINT 1 WP 01 203AV 22474 BS MS, RBL 52, FLOOR SUPPORT SPLICE HAS LEVEL 2 CORROSION (NEXT TO FRAME). REMOVED AND REPLACED SUPPORT SPLICE PER SRM 51-10-1 AND SRM 51-30-2. REMOVED CORROSION, TREATED AND PRIMED IN AREA SPLICE PER SRM 51-10-6. 2 L 7 3 4F A3WE 1996040500043 19960405 00043 NM 1996 4 5 96ZZZX1432 1 19960105 G 5347 SEAT TRACK BOEING 727 727259 138408J NM BS 1030-1070 CORRODED B S3BR K NONE O OTHER IN INSP/MAINT 1 WP 01 203AV 22474 AFT CABIN FLOOR STA 1030 - STA 1070, RBL 26, LEVEL 2 CORROSION ON FLANGE OF SEAT TRACK. REMOVED TRACK, INSTALLED FABBED SEAT TRACK PER SRM 51-10-1 AND SRM 51-30-2. 2 L 7 3 4F A3WE 1996040500402 19960405 00402 EA 1996 4 5 96ZZZX1467 2 19960301 G 8520 SL75060 ROD BOLT PIPER PA32 PA32300 7103212 SO LYC O540 IO540K1A5 41532 EA NR 4 FAILED G A UNSCHED LANDING E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 SO 16 8951N 3240753 L762248 NR 4 TOP ROD BOLT FAILED IN-FLIGHT. SEE AD NOTE 95-7-1 TW SMITH SENT LETTER TO SATISFY AD, THAT BOLT WAS NOT INSTALLED AT ENGINE OVERHAUL. TIME SINCE O/H WAS ABOUT 120 HRS. 1 L 7 1 3O 3 O A3SO 1E4 1996040500403 19960405 00403 SO 1996 4 5 96ZZZX1468 2 19960314 G 8530 653446A6 CYLINDER BEECH 58 58 1152740 CE CONT O520 IO520CB 17032 SO NR 2 CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 05 6650D 1531 TH1375 282375R FINDING STEEL CYLINDERS ARE CRACKING FROM THE FUEL INJECTOR BOSS ACROSS TO THE SPARK PLUG BOSS ON A REGULAR BASIS. SUBM ITTER REPORTS SOME CYLINDERS WITH AS LITTLE AS 600.0 TT CRACKED. SUBMITTER BELIEVES THERE MUST BE SOME TYPE OF MANUFACT URING PROBLEM. 1 L 7 2 3O 3 O 3A16 E5CE 1996040500404 19960405 00404 1996 4 5 96ZZZX1469 4 19960312 G 2562 006062 BATTERY PACK DORNEMARGLN DMELT1411 ELT WRONG PART B ODMR K NONE W INADEQUATE Q C IN INSP/MAINT 1 EA 11 0451A WHEN UNIT WAS RETURNED TO DORNE AND MARGOLIN FOR REPAIR DUE TO NO OUTPUT, IT WAS FOUND THAT THE ARTEX BATTERY INSTALLED IN THE UNIT WAS ONLY APPROVED TO TSO C91. SUBMITTER STATED THIS BATTERY PACK DOES NOT FIT PROPERLY IN THE D & M ELT 14- 1-1 AND THIS MAY HAVE CAUSED THE FAILURE IN THIS UNIT AS THE WIRE FOR THE BATTERY WAS DAMAGED CAUSING THE FAILURE. 1996040500405 19960405 00405 CE 1996 4 5 96ZZZX1470 1 19960121 G 3297 WIRE BEECH 23 C24R 1151254 CE NLG DOWNLOCK SW BROKEN D O OTHER J WARNING INDICATION AP APPROACH 1 GL 17 18909 2008 MC524 BROKEN WIRE IN NLG DOWNLOCK SWITCH AT SPLICE WHERE NG SWITCH IS SPLICED IN (IN ENG COMP) CAUSED PUMP TO STOP TOO SOON; N OSE GEAR WOULD NOT LOCK DOWN, AIRCRAFT LANDED WITH NG NOT LOCKED, COLLAPSED. SUBMITTER RECOMMENDS VINYL TUBING AROUND S PLICES BE CHANGED PERIODICALLY SO IT DOES NOT GET STIFF. ALSO, SPLICES CAN BE CHECKED FOR CONDITION. 1 L 7 1 3O A1CE 1996040500406 19960405 00406 CE 1996 4 5 96ZZZX1471 1 19960209 G 7603 CONTROL CABLE BEECH 23 C23 1151242 CE THROTTLE BINDING D A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CR CRUISE 1 GL 17 2149W M1532 THROTTLE AUTHORITY BECAME INTERMITTENT, JAMMED, THEN UNRESPONSIVE IN-FLIGHT. CONDITIONS 2,800 MSL, (MINUS) 15 DEGREES F AHRENHEIT, NIGHT CLEAR. OFF-AIRPORT LANDING MADE WITH THROTTLE STUCK AT 1,600 RPM. CHECKED CONTROL, FOUND JAMMED. THA WED CABLE CONTROL AND GOT SOME MOVEMENT, BUT STILL BINDING. REMOVED AND REPLACED CABLE ASSY. DISASSEMBLED, FOUND INTER MOST CABLE BENT, STRETCHED, AND DIRTY. CAUSE LIKELY DUE TO DIRT AND MOISTURE BUILD-UP AND LOW O.A.T. INSTALLED BEECH C ABLE, PN 169-380084-13. 1 L 7 1 3O A1CE 1996040500407 19960405 00407 SO 1996 4 5 96ZZZX1472 2 19960319 G 7310 LINE BEECH 33 35B33 1151406 CE CONT O470 IO470K 17026 SO NR 3-5 BAFFLE CHAFED D K NONE O OTHER IN INSP/MAINT 1 GL 05 97374 4000 CD604 FUEL METERED PR LINE FROM FUEL CONTROL TO DIST BLOCK CHAFED AT CYL BAFFLE BETWEEN NR 3 AND NR 5 CYLINDERS. ADDED LEATHE R TO LINE TO ADD PROTECTION. SUBMITTER STATED PRESENT METHOD ADOPTED BY BEECHCRAFT CORP USING FIRE SLEEVING IS NOT ADEQ UATE ANTI-CHAFE PROTECTION. 1 L 7 1 3O 3 O 3A15 3E1 1996040500408 19960405 00408 CE 1996 4 5 96ZZZX1473 1 19960319 G 5521 SPAR CESSNA 150 150L 2071826 CE ELEV HINGE HOLES ELONGATED D K NONE O OTHER IN INSP/MAINT 1 GL 05 11831 7661 15075658 INSPECTION OF OUTER HINGE FITTING ON ELEVATORS FOUND HOLES ELONGATED. REQUIRED NEW ELEVATOR SPAR. SUSPECT THIS AREA BE CHECKED CLOSELY ON INSPECTION AND THAT BOLT BE CHECKED FOR PROPER TORQUE. BOTH ELEVATOR SPARS BADLY CORRODED, REPLACED . SUBMITTER STATED THIS CESSNA HAD SEVERAL AREAS OF SEVERE CORROSION. 1 H 7 1 3O 3A19 1996040500409 19960405 00409 SO 1996 4 5 96ZZZX1474 1 19960116 G 3230 2106100 SOLENOID PIPER PA30 PA30 7103002 SO MLG MOTOR FAILED D O OTHER O OTHER LD LANDING 1 CE 07 7338Y 30387 DURING INSPECTION AND OPERATIONAL CHECK OF THE LANDING GEAR RETRACTION AND EXTENSION SYSTEMS AFTER A GEAR COLLAPSE ON LA NDING, THE GEAR MOTOR SOLENOID FAILED TO 'CLOSE' SEVERAL TIMES (PREVENTING OPERATION OF THE GEAR ELECTRICALLY). 1 L 7 2 3O A1EA 1996040500410 19960405 00410 CE 1996 4 5 96ZZZX1475 1 19960319 G 5312 BULKHEAD CESSNA 150 150L 2071826 CE FS 95 CRACKED D K NONE O OTHER IN INSP/MAINT 1 GL 05 11831 7661 15075658 INSPECTION FOUND CRACKS IN CORNERS AT BULKHEAD STA 95 UPPER CORNERS. 1 H 7 1 3O 3A19 1996040500411 19960405 00411 SO 1996 4 5 96ZZZX1476 2 19960225 G 7322 46512 VENTURI FACET MA35PA CESSNA 150 150 2071802 CE CONT O200 O200A 17020 SO CARBURETOR CASTING FLAW D K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 05 11831 DE2216306R 15075658 INSPECTION OF A NEW PMA CARBURETOR VENTURI FOUND CASTING FLAWS. SUBMITTER STATES HAS SEEN THIS DEFECT FREQUENTLY. 1 H 7 1 3O 3 O NT 3A19 E252 1996040500412 19960405 00412 CE 1996 4 5 96ZZZX1477 1 19960208 G 3260 1CH16 SWITCH CESSNA 310 310R 2074245 CE NLG FAILED D O OTHER P NO WARNING INDICATION AP APPROACH 1 GL 17 5119J 310R0996 WHILE ATTEMPTING TO LAND, THE NOSE GEAR DOWN AND LOCK LIGHT DID NOT ILLUMINATE WHEN GEAR WAS EXTENDED. SEVERAL CYCLES W ERE ATTEMPTED, BUT STILL NO LIGHT. A SUCCESSFUL LANDING WAS MADE. INVESTIGATION FOUND THAT ALL THREE GEARS WERE DOWN A ND LOCKED. THE NOSE GEAR DOWN AND LOCK SWITCH HAD FAILED INTERNALLY TO THE POINT WHERE NEITHER UNLOCK OR DOWN AND LOCK INDICATION COULD BE ACHIEVED. REPLACEMENT OF THE SWITCH SOLVED THE PROBLEM. 1 L 7 2 3O 3A10 1996040500413 19960405 00413 SO 1996 4 5 96ZZZX1478 1 19960314 G 2460 BREAKERS PIPER PA31T PA31T2 7103127 SO CB PANEL FAILED D K NONE O OTHER NR NOT REPORTED 1 EA 03 2325W 31T8166075 CIRCUIT BREAKERS BURN UP/MELT INTERNALLY BEFORE TRIPPING, THEN REMAIN OPEN WHEN RESET. 1 L 7 2 3T RT A8EA 1996040500414 19960405 00414 SO 1996 4 5 96ZZZX1479 1 19960317 G 2730 7105602 SPRING PIPER PA31 PA31350 7103110 SO ELEV DOWN WORN D K NONE O OTHER IN INSP/MAINT 1 AL 03 3588Z 6098 318052130 FOUND ELEVATOR DOWN SPRING AND SPRING FORWARD ATTACH TAB WORN. TAB WAS WORN WORSE THAN SPRING HOOK. SUBMITTER RECOMMEN DS STAINLESS STEEL ATTACH TABS AND CLOSE INSPECTION OF SPRING AND TABS. 1 L 7 2 3O A20SO 1996040500415 19960405 00415 CE 1996 4 5 96ZZZX1480 1 19960308 G 3240 B302781 TORQUE PLATE MCAULY C1630320207 CESSNA 206 U206F 2073333 CE LT MLG BUSHING PARTED D S K NONE O OTHER IN INSP/MAINT 1 NE 05 1523U 5948 U20602234 DURING AN ANNUAL INSPECTION, GUIDE BUSHING ON BRAKE TORQUE PLATE FOUND SEPARATED. 1 H 7 1 3O A4CE 1996040500416 19960405 00416 SO 1996 4 5 96ZZZX1481 1 19960301 G 5321 37829800 PANEL ASSY PIPER PA32 PA32R301 7103218 SO CENTER SEAT DETERIORATED D S K NONE O OTHER IN INSP/MAINT 1 EA 07 9779J 1243 32R13024 FLOOR PANEL FOR CENTER SEATS IS A FOAM PANEL WITH METAL TOP AND BOTTOM. FOAM FILLER COMING OUT OF MIDDLE. FOAM FILLER SEEMS TO DRY OUT AND FLAKE APART. SUBMITTER STATED FLOORS FORMERLY MADE OF WOOD. A WOOD FLOOR WITH METAL TOP AND BOTTO M WOULD BE MUCH BETTER. 1 L 7 1 3O A3SO 1996040500624 19960405 00624 SO 1996 4 5 96ZZZX1501 2 19960219 G 8500 ENGINE CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO LT ROUGHNESS I K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 NE 05 3249M 760 402C0296 290143R FLIGHT CREW NOTICED ROUGHNESS IN LEFT ENGINE. INSPECTED MAGS, COMPRESSION TESTED CYLINDERS, CHECKED SPARK PLUGS. ENGIN E WAS GROUND RUN. FLIGHT OK'D. NOTED NO PROBLEMS. RETURNED TO SERVICE. NOTED: MINUS 21 DEGREES FAHRENHEIT TEMPERATU RE. 1 L 7 2 3O 3 O A7CE E8CE 1996040500625 19960405 00625 CE 1996 4 5 96ZZZX1502 1 19960308 G 3221 3216 BRACKET ASSY SCOTT 3200 CESSNA 170 170B 2072306 CE TAILWHEEL BOLT SHEARED D O OTHER O OTHER TO TAKEOFF 1 AL 03 4387B 1000 ARLOFOR 26731 BRACKET ASSY BOLT APPEARS AS METAL HAS CRYSTALLIZED THROUGH AGE. BOLT THEN SHEARED ALLOWING TAILWHEEL TO FALL OFF AIRCR AFT ON TAKEOFF. 1 H 7 1 3O A799 1996040500626 19960405 00626 CE 1996 4 5 96ZZZX1503 1 19960229 G 3211 TRUNNION CESSNA 182 R182 2072734 CE NLG CRACKED D K NONE O OTHER LD LANDING 1 NE 01 6465T 2044 R1820233 NOSE GEAR COLLAPSED AFTER LANDING. CRACKED NOSE GEAR TRUNNION. SUSPECT PREVIOUS HARD LANDINGS, EVIDENCE OF OLD CRACK. CLOSE INSPECTION DURING SCHEDULED MAINTENANCE. 1 H 7 1 3O RT 3A13 1996040500627 19960405 00627 SO 1996 4 5 96ZZZX1504 1 19960130 G 5712 7847503 RIB PIPER PA32 PA32R300 7103213 SO WS 49.25 RT CRACKED D K NONE O OTHER IN INSP/MAINT 1 GL 13 1919H 5837 32R7780202 DURING C/W AD 95-20-07, FOUND AFT RIB ASSEMBLIES, LEFT AND RIGHT, CRACKED AFTER REMOVING MAIN GEAR SIDE BRACE STUD BRACK ET, PN 75643-06. SUBMITTER REPORTED SAME PROBLEM WITH SEVERAL OTHER AIRCRAFT. 1 L 7 1 3O A3SO 1996040500628 19960405 00628 SO 1996 4 5 96ZZZX1505 1 19960130 G 5712 7847502 RIB PIPER PA32 PA32R300 7103213 SO WS 49.25 LT CRACKED D K NONE O OTHER IN INSP/MAINT 1 GL 13 1919H 5837 32R7780202 DURING C/W AD 95-20-07, FOUND AFT RIB ASSEMBLIES, LEFT AND RIGHT, CRACKED AFTER REMOVING MAIN GEAR SIDE BRACE STUD BRACK ET, PN 75643-06. SUBMITTER REPORTED SAME PROBLEM WITH SEVERAL OTHER ARICRAFT. 1 L 7 1 3O A3SO 1996040500630 19960405 00630 CE 1996 4 5 96ZZZX1507 1 19960228 G 5711 082260039 SPAR 08220441 CESSNA 310 310Q 2074242 CE LT WS 85-111.5 CORRODED D K NONE O OTHER IN INSP/MAINT 1 CE 01 199JJ 4295 310Q01080 DURING AN ANNUAL INSPECTION OF AIRCRAFT, NOTED THE REAR SPAR UPPER AFT CAP HAD CORROSION THAT APPEARED TO BE INTERGRANUL AR FROM WS 85.0 TO WS 111.5 (APPROX) LEFT WING. AIRCRAFT FERRIED TO ANOTHER FACILITY FOR EVALUATION AND POSSIBLE REPAIR . 1 L 7 2 3O 3A10 1996040500631 19960405 00631 CE 1996 4 5 96ZZZX1508 1 19960220 G 5711 SPAR BEECH 18 E18S 1151006 CE WS 90 LT-RT CORRODED B DP2R K NONE O OTHER IN INSP/MAINT 1 SW 05 125X BA192 INSPECTION FOUND WS 90 RT UPPER - LIGHT CORROSION AND INDICATION OF .750 INCH CRACK FROM WELD INTO SPAR. FOLLOW-UP INSP ECTION WS 90 RT UPPER WITH DYE PENETRANT AND ULTRASONICS WITH NO CRACK INDICATIONS NOTED. 1 L 7 2 3R A765 1996040500632 19960405 00632 CE 1996 4 5 96ZZZX1509 1 19960204 G 5313 STRUT BEECH 23 C23 1151242 CE CABANE CORRODED D K NONE O OTHER IN INSP/MAINT 1 EA 25 2009D 3175 M2053 LOWER END OF CABANE STRUTS CORRODED DUE TO WINDSHIELD LEAKING. THIS PART IS VERY HARD TO SEE UNLESS GLARE SHIELD AND WI NDSHIELD ARE REMOVED. CORROSION FOUND DURING WINDSHIELD REPLACEMENT. RUST WAS NEARLY THROUGH METAL WALL OF STRUT. SUB MITTER STATED SINCE THIS PART IS NOT CLEARLY VISIBLE, AN AD IS PERHAPS IN ORDER AS THIS IS STRUCTURE. 1 L 7 1 3O A1CE 1996040500633 19960405 00633 SO 1996 4 5 96ZZZX1510 1 19960312 G 3230 400218 BOLT 7642603 PIPER PA28 PA28R201 7102816 SO UPPER NLG LINK MISINSTALLED G K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 25 2247M 2470 28R7837073 ATTACHING HARDWARE FOR NLG UPPER DRAG LINK TO ENGINE MOUNT INSTALLED INCORRECTLY, WASHER SKIN BUSHING, ETC. ARRANGEMENT INCORRECT. 1 L 7 1 3O 2A13 1996040500634 19960405 00634 SO 1996 4 5 96ZZZX1511 1 19960312 G 6120 LW162662538 CLAMP PIPER PA28 PA28R201 7102816 SO PROP GOV LINE INCORRECT G K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 25 2247M 28R7837073 CLAMP POSITION FOR REAR MOUNT PROP GOVERNOR EXTERNAL OIL LINE NOT POSITIONED PER AD 90-4-6. 1 L 7 1 3O 2A13 1996040500635 19960405 00635 SO 1996 4 5 96ZZZX1512 1 19960312 G 7820 6751700 MUFFLER PIPER PA28 PA28R201 7102816 SO ENG EXHAUST DEFECTIVE G K NONE O OTHER IN INSP/MAINT 1 GL 25 2247M 2490 28R7837073 FRONT MUFFLER INTERNAL BAFFLE MISSING. AFT MUFFLER INTERNAL BAFFLE DISTORTED, PARTIALLY BLOCKING OUTLET. 1 L 7 1 3O 2A13 1996040500638 19960405 00638 CE 1996 4 5 96ZZZX1515 1 19960308 G 2730 50935001 CONTROL ARM CESSNA 421 421C 2076016 CE ELEVATOR WORN D K NONE O OTHER IN INSP/MAINT 1 GL 15 40ME 5542 421C1241 FOUND HOLES ELONGATED WHERE ELEVATOR CONTROL ARM ATTACHES TO BRACKET ON THE AFT SPAR OF HORIZONTAL STABILIZER. SUSPECT CAUSE, LOOSE AND WORKING BOLTS AND TIME ON PART. 1 L 7 2 3O A7CE 1996040500639 19960405 00639 CE 1996 4 5 96ZZZX1516 1 19960220 G 2752 511523716 ACTUATOR CESSNA 414 414A 2075907 CE FLAP FAILED H K NONE O OTHER NR NOT REPORTED 1 WP 13 4686N 8066 414A0075 FLAPS WERE BEING LOWERED. A POPPING SOUND WAS HEARD. IT WAS DISCOVERED THE FLAP ACTUATOR HAD FAILED INTERNALLY. FLAP ACTUATOR REPLACED. 1 L 7 2 3O A7CE 1996040500640 19960405 00640 1996 4 5 96ZZZX1517 4 19960308 G 3416 3431 CASTING UNITEDINST 5934P PIPER PA32 PA32RT300 7103215 SO ALTIMETER OUT OF SPEC B EI4R K NONE O OTHER IN INSP/MAINT 1 SO 15 457SC M8448 32R7885139 TWO OF THE CRITICAL SHAFTS IN THE MECHANISM WERE UNDER THE MINIMUM END SHAKE CALLED OUT IN THE OVERHAUL MANUAL. THEY ME ASURED .0005 INCH AND .0009 INCH (O/H MANUAL CALLS OUT .0020 INCH MINIMUM). SUBMITTER STATED THIS UNDER ENDSHAKE CONDIT ION COULD CAUSE A POINTER HANG-UP UNDER COLD CONDITIONS. 1 L 7 1 3O A3SO 1996040500641 19960405 00641 CE 1996 4 5 96ZZZX1518 1 19960220 G 2823 99102011 VALVE CESSNA 414 414A 2075907 CE FUEL SELECT FAILED H K NONE O OTHER IN INSP/MAINT 1 WP 13 4686N 8069 414A0075 FUEL SELECTION WAS MOVED FROM LEFT ENGINE TO CROSS-FEED. AFTER FLIGHT, THE FUEL SELECTOR WAS MOVED FROM CROSS-FEED BACK TO LEFT ENGINE. FUEL SELECTION WOULD NOT MOVE. IT WAS DISCOVERED THE FUEL SHUT-OFF VALVE HAD FAILED INTERNALLY AND WA S STUCK IN THIS POSITION. VALVE REPLACED. 1 L 7 2 3O A7CE 1996040500642 19960405 00642 SW 1996 4 5 96ZZZX1519 1 19960216 G 5541 442283 SPAR GULSTM 112 114 7630314 SW RUDDER CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 05 4895W 2000 14225 AIRCRAFT CAME IN FOR AN ANNUAL. AFTER SEEING JANUARY, 1996 ALERTS, DECIDED TO CHECK THIS AREA AND FOUND A 2.50 INCH CRA CK ON LT SIDE OF RUDDER FITTING ATTACH HOLES. 1 L 7 1 3O A12SO 1996040500643 19960405 00643 SO 1996 4 5 96ZZZX1520 1 19960223 G 2720 6342004 PEDAL ATTACH PIPER PA32 PA32300 7103212 SO PILOT LT RUDDER FAILED D K NONE O OTHER NR NOT REPORTED 1 WP 01 4182R 4011 3240513 PILOT'S LT RUDDER PEDAL ATTACH ARM FAILED AROUND CROSS-OVER TUBE ATTACHMENT. SUBMITTER STATED INSPECTING ALL WELDS FOR CONDITION AT 100-HOUR INTERVALS OR ANNUAL, AND LUBING ALL LUBE HOLES ON RUDDER BAR SUPPORT ASSY. 1 L 7 1 3O A3SO 1996040500644 19960405 00644 GL 1996 4 5 96ZZZX1521 3 19960223 G 6111 BCE2020 BEARING UNIVAC GC1 GC1B 9230104 NM HARTZL HCC2Y HCC2YR1 GL PROP BLADE MISSING D K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 07 44S 68 1251 CH10736 PROPELLER SUBMITTED FOR INSPECTION DUE TO COMPLAINTS OF VIBRATION AND ONE LOOSE BLADE. WHEN DISASSEMBLED, DISCOVERED TH E BCE 2020 BEARINGS WERE LEFT OUT DURING THE LAST OVERHAUL 68.0 HRS AGO. INSPECTED SHANKS FOR CRACKS AND DAMAGE. NONE FOUND, ALTHOUGH THE 2222 TORQUE PLATES WERE DAMAGED BEYOND REPAIR DUE TO THE SIGNIFICANT LOADS APPLIED BY THE LOOSE BLAD ES. REPAIRED PROPELLER INSTALLING CORRECT PARTS, SEALS, GASKETS, AND HARDWARE. 1 L 7 1 3O A766 5 C P920 1996040500645 19960405 00645 SO 1996 4 5 96ZZZX1522 1 19960123 G 2720 63451000 SUPPORT PIPER PA28 PA28140 7102802 SO RUDDER PEDAL CRACKED D K NONE O OTHER IN INSP/MAINT 1 GL 13 42161 3058 287425312 DURING ANNUAL INSPECTION, MOVEMENT WAS NOTICED BACK AND FORTH ON RUDDER PEDAL ASSY. FURTHER INSPECTION REVEALED 4 CRACK S IN SUPPORT. SUBMITTER STATED THIS PROBLEM WAS SUBMITTED PREVIOUSLY ON JANUARY, 1996, COPY OF WESTERN FLYER. 1 L 7 1 3O 2A13 1996040500647 19960405 00647 SO 1996 4 5 96ZZZX1524 2 19960301 G 8550 CH48108 OIL FILTER CESSNA 401 401B 207590E CE CONT O520 TSIO520E 17040 SO ENGINE LEAKING D K NONE K FLUID LOSS IN INSP/MAINT 1 SO 13 401GB 50 401B0004 WHILE AIRCRAFT IN-FLIGHT, PILOT REPORTED OIL LEAKING FROM LEFT ENGINE. DURING INSPECTION OF LEFT ENGINE, FOUND OIL FILT ER AND SURROUNDING AREA OIL SOAKED. AFTER CLEANING AND RUNNING ENGINE FOUND OIL LEAKING FROM HEXHEAD OF OIL FILTER (CH4 8108). REMOVED FILTER AND REPLACED WITH CH48108. AFTER RUNNING UP, ENGINE AGAIN, NO OIL LEAKS WERE NOTED. 1 L 7 2 3O 3 O A7CE E8CE 1996040500648 19960405 00648 CE 1996 4 5 96ZZZX1525 1 19960126 G 5730 SKIN CESSNA 310 310R 2074245 CE LT/RT WING BUCKLED H K NONE O OTHER IN INSP/MAINT 1 CE 01 4113A 310R1307 PRE-INSPECTION REVEALED BUCKLED WING SKIN OUTBOARD OF GEAR DOORS, UNDERSIDE LT AND RT WINGS. SUSPECT CAUSE: PILOT STAT ED, ENCOUNTERED SEVERE TURBULENCE. 1 L 7 2 3O 3A10 1996040500649 19960405 00649 CE 1996 4 5 96ZZZX1526 1 19960228 G 3230 08421043 BELLCRANK CESSNA 421 421B 2076014 CE NLG FAILED H O OTHER O OTHER CL CLIMB 1 SW 99 42AG 1275 421B0425 NOSE LANDING GEAR FAILED TO EXTEND DUE TO FAILURE OF NOSE GEAR RETRACTION BELLCRANK. SUSPECT CAUSED BY NOSE STRUT DEFLA TION EITHER PRIOR TO TAKEOFF, DURING TAXI, OR AFTER TAKEOFF WHICH ALLOWED THE STRUT TO STAY COMPRESSED ON RETRACTION AND GEAR CONTACTED PART OF RETRACTION MECHANISM JAMMING IN PLACE BEFORE COMPLETE RETRACTION. THIS CAUSED BELLCRANK TO FAIL BECAUSE MOTOR CONTINUED TO RUN UNTIL HITTING ITS LIMIT SWITCH AND THE BELLCRANK IS OBVIOUSLY THE WEAKEST LINK IN THE NO SE RETRACTION MECHANISM. 1 L 7 2 3O A7CE 1996040500651 19960405 00651 GL 1996 4 5 96ZZZX1528 3 19960109 G 6111 A31505 PIN CESSNA 185 A185F 2072821 CE MCAULY D3A34 D3A34C401 GL NR 2 BLADE MISSING G C D ABORTED TAKEOFF RETURN TO BLOCK E VIBRATION/BUFFET TO TAKEOFF 1 SW 99 4026Y 6 1850226 950360 DURING TAKEOFF, ENGINE STARTED TO RUN ROUGH AND SHAKE. THE TAKEOFF WAS ABORTED AND ACFT RETURNED TO RAMP. ENGINE AND P ROP WERE THEN INSPECTED FOR ABNORMALTIES. WHILE INSPECTING THE PROP, A MECHANIC DISCOVERD THE NR 2 PROP BLADE COULD BE ROTATED INDEPENDENTLY OF THE OTHER BLADE. THE PROPELLER WAS THEN REMOVED AND SENT IN FOR INSPECTION. THE TEAR-DOWN REV EALED A SAFETY PIN (A-3150-5) THAT SECURES THE BLADE ACTUATING LINK PIN (A-4738) IN PLACE WAS NOT INSTALLED DURING PROPE LLER BUILD-UP. 1 H 7 1 3O 3A24 5 C P47GL 1996040500652 19960405 00652 SO 1996 4 5 96ZZZX1529 2 19960301 G 8530 CYLINDER CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO ENGINE HEAD SEPARATED D K NONE O OTHER NR NOT REPORTED 1 EA 23 5009J 1428 310R0730 266054R CYLINDER HEAD SEPARATED FROM BARREL. 1 L 7 2 3O 3 O 3A10 E5CE 1996040500654 19960405 00654 SO 1996 4 5 96ZZZX1531 1 19960117 G 2140 880942 COMBUSTION TUBE JANITROL B3040 PIPER PA34 PA34200T 7103406 SO HEATER CRACKED D A UNSCHED LANDING C F.O.D. CL CLIMB 1 GL 13 501DM 4781452 347870375 AFTER TAKEOFF WITH HEATER SELECTED ON, SPARKS WERE SEEN COMING OUT OF THE HEATER VENTS. THE HEATER WAS SHUT OFF AND AIR CRAFT RETURNED TO BASE WITHOUT FURTHER INCIDENT. HEATER REMOVED AND INSPECTED. DURING INSPECTION, A CRACK ABOUT 3 INCH ES LONG WAS SEEN 6 INCHES FROM EXIT END. TIME SINCE LAST HEATER DECAY TEST WAS 45.7 HEATER HRS. LAST HEATER O/H RECORD ED WAS 10-15-80. NO RECORD OF WHAT HEATER OVERHAUL INVOLVED IS AVAILABLE. 1 L 7 2 3O A7SO 1996040500655 19960405 00655 1996 4 5 96ZZZX1532 4 19960118 G 2215 6024 MOUNT BRACKET STEC CESSNA 182 TR182 2072735 CE ROLL SERVO CRACKED D K NONE O OTHER IN INSP/MAINT 1 GL 13 5276S 3486 R182201531 UPON REPLACEMENT OF ROLL SERVO, FOUND LOWER BRACKET HAD COMPLETELY CRACKED THROUGH. THE SERVO WAS ONLY BEING HELD IN PL ACE BY THE UPPER MOUNTING BRACKET. ORDERED NEW REPLACMENT PART AND FOUND IT HAS BOTTOM ADJUSTMENT SLOTS FOR SERVO POSIT ION ADJUSTMENT. RECOMMEND INSPECTION OF OLDER S-TEC AUTOPILOT ROLL SERVO BRACKET AND REPLACEMENT WITH NEW IMPROVED PART . 1 H 7 1 3O 3A13 1996040500657 19960405 00657 EA 1996 4 5 96ZZZX1534 2 19960322 G 7322 30766 FLOAT FACET MA3PA CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA CARBURETOR CRACKED D A UNSCHED LANDING Y ENGINE STOPPAGE CR CRUISE 1 SW 15 5366B 864 DM0922 15283849 CARBURETOR FLOAT FILLED WITH FUEL AND SANK IN-FLIGHT RESULTING IN ENGINE STOPPAGE AND FORCED LANDING. FLOAT WAS IN C/W AD 93-19-04. FLOAT CRACKED AND FILLED WITH FUEL. RECOMMEND RE-ENGINEERED FLOAT NOT PRONE TO CRACKING. 1 H 7 1 3O 3 O NT 3A19 E223 1996040500658 19960405 00658 SO 1996 4 5 96ZZZX1535 2 19960313 G 8520 643627 CRANKSHAFT MOONEY M20 M20K 5870220 SW CONT O360 TSIO360GB 17025 SO FLANGE CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 13 5764S 1706 A614M2 250831 316047 WHILE CONDUCTING AN ANNUAL INSPECTION, DISCOVERED SEVERAL SUSPICIOUS BROWN STAINS. AREA WAS CLEANED AND A DYE PENTRANT INSPECTION PERFORMED. CRACKS WERE FOUND RADIATING CIRCUMFERENTIALLY AROUND CRANKSHAFT AND FLANGE IN THE AREA OF THE FLA NGE RADIUS. PROP HAD BEEN REMOVED TO DETERMINE CRANKSHAFT SERIAL NUMBER FOR EVALUATION OF OVERHAUL AND SB COMPLIANCE. 1 L 7 1 3O 3 O 2A3 E9CE 1996040500659 19960405 00659 CE 1996 4 5 96ZZZX1536 1 19960208 G 2434 F3FF10300AA ALTERNATOR FORD CESSNA 210 T210N 2073456 CE DC SYSTEM WARNING LIGHT D A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 GL 03 6611c 780 21063930 LOW VOTLAGE LIGHT WITH FULL LOAD. (PROP ICE, PITOT HEAT). AIRCRAFT LANDED. MECHANIC INSPECTED ALTERNATOR ATTACHMENTS, WIRING, AND BELT TENSION. NO DISCREPANCIES WERE NOTED. AIRCRAFT WAS TEST RUN ON THE GROUND AT SEVERAL POWER SETTINGS AND VARIOUS LOADS. MECHANIC COULD NOT DUPLICATE PROBLEM AND RETURNED ACFT TO SERVICE. 1 H 7 1 3O 3A21 1996040500660 19960405 00660 CE 1996 4 5 96ZZZX1537 1 19960208 G 3260 SWITCH CESSNA 210 T210N 2073456 CE NLG SQUAT OUT OF RIG D O OTHER N FALSE WARNING CL CLIMB 1 GL 03 6611C 21063930 GEAR FAILED TO RETRACT. UPON INSPECTION, FOUND SQUAT SWITCH OUT OF RIG. JACKED ACFT, RE-RIGGED PER MM. OPERATIONALLY TESTED GOOD. SUBMITTER RECOMMENDS CLOSE INSPECTION OF SWITCH AT SCHEDULED INSPECTIONS. 1 H 7 1 3O 3A21 1996040500661 19960405 00661 SO 1996 4 5 96ZZZX1538 2 19960124 G 8520 MOUNT STUD CESSNA 340 340A 2076405 CE CONT O520 TSIO520N 17040 SO NR 4 CYLINDER BROKEN B EBVR K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 GL 09 61JK 340A0333 509498 PILOT COMPLAINED RT ENGINE WAS ROUGH RUNNING. FOUND NR 1 CYLINDER HELD ON BY ONLY AFT TWO THROUGH-BOLTS. ALL OTHER MOU NT STUDS WERE BROKEN. REMOVED CYLINDER AND THROUGH-BOLTS. PENETRATE CHECK OF CASE MOUNTING AREA REVEALED TWO CRACKS (1 O'CLOCK AND 7 O'CLOCK) AT MOUNT STUD HOLES AND MAG PARTICLE OF THROUGH-BOLTS REVEALED ONE CRACKED. 1 L 7 2 3O 3 O 3A25 E8CE 1996040500662 19960405 00662 CE 1996 4 5 96ZZZX1539 1 19960301 G 8011 CC150 CLUTCH PRESTOLITE MZ4214 CESSNA 150 150M 2071830 CE STARTER SEIZED D A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CR CRUISE 1 SO 05 63157 7E000015 15077145 CLUTCH ENGAGED IN-FLIGHT. PILOT NOTED REDUCTION IN ENGINE RPM. AFTER LANDING AND POWER WAS REDUCED TO IDLE, ENGINE INS TALLED. INSPECTION OF CLUTCH AND STARTER REVEALED THAT CLUTCH HAD 'FROZEN' TO STARTER GEAR AND HAD DRIVEN STARTER ARMAT URE TO A HIGH SPEED. ARMATURE WINDINGS SEPARATED FROM ARMATURE. OVERHAUL RECORDS STATE THAT ALL APPLICABLE MANUFACTURE RS SB'S ARE C/W (12-20-94). NO DIRECT REFERENCE TO CONTINENTAL SB 79-10 STARTER CLUTCH AND MODIFICATION. SUBMITTER SUS PECTS LACK OF LUBRICATION AND/OR SPECIFIC TIME INTERVALS AND CRITERIA FOR INSPECTION OF CLUTCH. 1 H 7 1 3O 3A19 1996040500663 19960405 00663 CE 1996 4 5 96ZZZX1540 1 19960227 G 2571 07120591 SUPPORT CESSNA 182 182R 2072731 CE BAT HOLD DOWN CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 25 6396E 1167 18268367 BOTH BATTERY HOLD-DOWN SUPPORTS WERE FOUND CRACKED DURING A ROUTINE INSPECTION. CRACKS WERE AT BOTH ENDS OF THE SUPPORT S AND APPROXIMATELY 1 INCH IN LENGTH. SUBMITTER STATED THIS IS THE SECOND AIRCRAFT FOUND WITH THIS DEFECT. IF FAILURE HAD OCCURED, BATTERY COULD HAVE FALLEN INTO CONTROL CABLES. SUGGEST CLOSE INSPECTION WHENEVER REAR BULKHEAD IS REMOVED. 1 L 7 1 3O NT 3A13 1996040500664 19960405 00664 SO 1996 4 5 96ZZZX1541 1 19960307 G 6120 1998700 BALL JOINT PIPER PA24 PA24250 7102404 SO PROP CONTROL SEPARATED B KQ3R O OTHER O OTHER CR CRUISE 1 WP 07 6849P 244983 IN-FLIGHT, PROP WENT TO 2700 RPM FROM 2350 RPM. UNABLE TO DECREASE WITH PROP CONTROL. FOUND BALL JOINT SEPARATED FROM PROPELLER GOVERNOR. PROPELLER CONTROL WAS CHANGED LAST OCTOBER, 1995, USING SAME BALL JOINT AT THE LAST ANNUAL. THE BA LL JOINT WAS VERY RUSTY AND APPEARED TO HAVE NEVER BEEN LUBRICATED. SUBMITTER STATED THE MM REQUIRES THIS BALL JOINT TO BE LUBRICATED EVERY 100 HOURS. RECURRENCE OF THIS DEFECT CAN BE AVERTED BY FOLLOWING THE LUBRICATION REQUIREMENTS IN T HE AIRCRAFT MM. 1 L 7 1 3O 1A15 1996040500665 19960405 00665 EA 1996 4 5 96ZZZX1542 2 19960311 G 8530 CYLINDER GULSTM 500 500B 0141106 SW LYC O540 IO540E1A5 41532 EA NR 2 FAILED E E ENGINE SHUTDOWN E R K VIBRATION/BUFFET PARTIAL RPM/PWR LOSS FLUID LOSS CR CRUISE 1 CE 07 615MT 802 9112 RL505348 NR 2 CYLINDER BROKE AT BASE. CYLINDER CAME LOOSE FROM THE CRANKCASE CAUSING ENGINE VIBRATION. PILOT SHUT DOWN ENGINE IN-FLIGHT. ON DISASSEMBLY, FOUND CRANKCASE AND PISTON DAMAGED. THE ENGINE WAS REMOVED FROM SERVICE. 1 H 7 2 3O 3 O 6A1 1E4 1996040500667 19960405 00667 SO 1996 4 5 96ZZZX1544 1 19960202 G 3222 NOSE GEAR PIPER PA31 PA31350 7103110 SO TRUNNION COLLAPSED D O OTHER O OTHER LD LANDING 1 NM 05 7694L 317305024 NOSE GEAR COLLAPSED ON LANDING. SUSPECT AIRCRAFT TOW LIMITS EXCEEDED. DAMAGED TRUNNION, SHIMMY DAMPENER, AND UPPER RET RACT CENTERLINE TRACK. TOTAL TIME, 16,511.5 HOURS. 1 L 7 2 3O A20SO 1996040500668 19960405 00668 SO 1996 4 5 96ZZZX1545 2 19960305 G 8550 OIL FILTER CESSNA 180 180J 2072622 CE CONT O470 O470S 17026 SO CONNECTION WRONG PART B FE6R K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 11 7824K 18052758 464271 DURING AN ANNUAL INSPECTION, NOTED A CHAMPION CH 48103 (.8125 INCH BY 16 INCH FEMALE THREAD) OIL FILTER WAS INSTALLED. T HE CORRECT OIL FILTER FOR THIS INSTALLATION SHOULD HAVE BEEN A CH-48110 (.75 INCH BY 16 INCH MALE THREAD). IT IS BELIEV ED THAT THE THREADED ADAPTER CAME OUT OF AN OIL FILTER (BRAND UNKNOWN) IN TIMES PAST (RECORDS SHOW CH 48103 FILTER INSTA LLED AT LEAST SINCE MARCH 1993) AND BECAME STUCK IN THE FEMALE THREADS OF THE OIL FILTER ADAPTER. PERSONNEL, AT THAT TI ME, OBTAINED A FILTER THAT FIT, ALBEIT POORLY. MAINTENANCE PERSONNEL, AFTER THAT TIME, REINSTALLED THE SAME PART NUMBER THAT WAS REMOVED. 1 H 7 1 3O 3 O 5A6 E273 1996040500669 19960405 00669 SO 1996 4 5 96ZZZX1546 2 19960305 G 8540 635050A4 ADAPTER CESSNA 182 182P 2075816 CE CONT O470 O470S 17026 SO STARTER FAILED B LX5R K NONE O OTHER IN INSP/MAINT 1 GL 19 841LL 1397 18263908 463648 WHEN STARTER WAS ENGAGED, THE PROPELLER MADE APPROXIMATELY ONE-EIGHTH REVOLUTION AND STOPPED. FURTHER ATTEMPTS WITH STA RTER WOULD NOT TURN PROPELLER. PROP WAS 'STIFF' TURNING IN DIRECTION OF NORMAL ROTATION. PROP COULD NOT BE TURNED AT A LL IN OPPOSITE DIRECTION. REMOVED STARTER ADAPTER FROM ENGINE AND PROP ROTATION FELT NORMAL IN BOTH DIRECTIONS. 1 H 7 1 3O 3 O NT TA13 E273 1996040500671 19960405 00671 GL 1996 4 5 96ZZZX1548 3 19960304 G 6114 D4344 HUB MCAULY 3AF32C 3AF32C93 GL NR 2 BLD SOCKET CRACKED B DJFR K NONE O OTHER IN INSP/MAINT 1 EA 23 777473 DURING C/W AD 95-24-05, FOUND HUB CRACKED IN THREADS, NR 2 BLADE SOCKET. TOTAL TIME SINCE OVERHAUL, 1,226.8 HOURS. 5 C P22EA 1996040500672 19960405 00672 1996 4 5 96ZZZX1549 4 19960301 G 3454 023009800 METER ASSY KING KI208 FLAG WARNING FADED B PG2R K NONE O OTHER IN INSP/MAINT 1 GL 11 2929 HAVE NOTICED IN MANY OLDER KI208 AND KI209 INDICATORS, THE RED WARNING STRIPES ON THE VOR/LOC TO-OFF-FROM METER AND THE GLIDESLOPE FLAG METER FADE OUT TO WHITE. ON THE KI208, IT IS POSSIBLE TO HAVE AN INDICATION OF HALF-'TO' AND HALF-'FROM ' AT THE SAME TIME. ON THE KI209, THE VOR/LOC MAY BE THE SAME AS THE KI208, BUT THE GLIDESLOPE FLAG MAY POSSIBLY BE MIS TAKEN FOR A 'TO' OR 'FROM' INDICATION. 1996040500673 19960405 00673 1996 4 5 96ZZZX1550 4 19960301 G 3454 023012500 METER ASSY KING KI209 FLAG WARNING FADED B PG2R K NONE O OTHER IN INSP/MAINT 1 GL 11 1771 HAVE NOTICED IN MANY OLDER KI208 AND KI209 INDICATORS, THE RED WARNING STRIPES ON THE VOR/LOC TO-OFF-FROM METER AND THE GLIDESLOPE FLAG METER FADE OUT TO WHITE. ON THE KI208, IT IS POSSIBLE TO HAVE AN INDICATION OF HALF-'TO' AND HALF-'FROM ' AT THE SAME TIME. ON THE KI209, THE VOR/LOC MAY BE THE SAME AS THE KI208, BUT THE GLIDESLOPE FLAG MAY POSSIBLY BE MIS TAKEN FOR A 'TO' OR 'FROM' INDICATION. 1996040500674 19960405 00674 1996 4 5 96ZZZX1551 4 19960202 G 2564 RAFT 69FAAV CO2 BOTTLE FAILED D K NONE O OTHER IN INSP/MAINT 1 SW 99 07200 DURING AN EXERCISE, RAFT FAILED TO INFLATE. INSPECTION SHOWED CO2 BOTTLE VALVE DID NOT OPEN TO EXPEL CO2. CERTIFICATIO N DUE DATE WAS 2-15-96. 1996040500675 19960405 00675 1996 4 5 96ZZZX1552 4 19960229 G 2562 DMELT6 ELT DORNEMARGLN G-SWITCH DEFECTIVE B CM2R K NONE O OTHER IN INSP/MAINT 1 SW 15 55221 FOUND DEFECTIVE G-SWITCHES ON SEVERAL UNITS DURING THE LAST 6 MONTHS. THE SWITCHES WILL ACTIVATE THE ELT, BUT THE ELT W ILL STOP WHEN THE UNIT IS TILTED 20 DEGREES TO 30 DEGREES IN THE ROLL AXIS. ON SOME UNITS, THE G-SWITCH WOULD NOT ACTIV ATE THE ELT. UNITS WERE SENT TO THE MANUFACTURER AND REPAIRED. UNITS THEN TESTED CORRECTLY. 1996040500676 19960405 00676 1996 4 5 96ZZZX1553 4 19960229 G 2562 DMELT6 ELT DORNEMARGLN G-SWITCH DEFECTIVE B CM2R K NONE O OTHER IN INSP/MAINT 1 SW 15 39153 FOUND DEFECTIVE G-SWITCHES ON SEVERAL UNITS DURING THE LAST 6 MONTHS. THE SWITCHES WILL ACTIVATE THE ELT, BUT THE ELT W ILL STOP WHEN THE UNIT IS TILTED 20 DEGREES TO 30 DEGREES IN THE ROLL AXIS. ON SOME UNITS, THE G-SWITCH WOULD NOT ACTIV ATE THE ELT. UNITS WERE SENT TO THE MANUFACTURER AND REPAIRED. UNITS THEN TESTED CORRECTLY. 1996040500677 19960405 00677 1996 4 5 96ZZZX1554 4 19960229 G 2562 DMELT6 ELT DORNEMARGLN G-SWITCH DEFECTIVE B CM2R K NONE O OTHER IN INSP/MAINT 1 SW 15 39040 FOUND DEFECTIVE G-SWITCHES ON SEVERAL UNITS DURING THE LAST 6 MONTHS. THE SWITCHES WILL ACTIVATE THE ELT, BUT THE ELT W ILL STOP WHEN THE UNIT IS TILTED 20 DEGREES TO 30 DEGREES IN THE ROLL AXIS. ON SOME UNITS, THE G-SWITCH WOULD NOT ACTIV ATE THE ELT. UNITS WERE SENT TO THE MANUFACTURER AND REPAIRED. UNITS THEN TESTED CORRECTLY. 1996040500679 19960405 00679 1996 4 5 96ZZZX1556 4 19960129 G 3452 AT50 TRANSPONDER NARCO CAVITY BOGUS MOD H K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 09 11HP0 UNIT WAS INSPECTED AND FOUND TO HAVE AN UNAPPROVED MODIFICATION THAT ALLOWED INSTALLATION OF A 250W CAVITY. THIS UNIT W AS DESIGNED FOR 125W ONLY. THE UNIT WAS TAGGED AS SERVICEABLE. 1996040500680 19960405 00680 EU 1996 4 5 96ZZZX1557 1 19960221 G 7160 TB1050002163 TUBE SOCATA TB9 TB9 8680694 EU CARB AIR BOX DETERIORATED D A K NONE O OTHER IN INSP/MAINT 1 SO 15 50 CARBURETOR HEAT TUBE ERODING DUE TO SUPER HEATED AIR FROM MUFFLER SHROUD. TUBE WIRE SUPPORT AND DEBRIS FROM TUBE COULD BE INJECTED DIRECTLY INTO CARB AND ENGINE. DIFFICULT TO INSPECT DUE TO FIRE SLEEVE WRAPPED AROUND TUBE. SUBMITTER SUGG ESTS DIFFERENT TYPE OF TUBE OR MATERIAL. 1 L 7 1 3O NT AS1EU 1996040500681 19960405 00681 CE 1996 4 5 96ZZZX1558 1 19960301 G 2720 0733100 TORQUE TUBE CESSNA 185 185 2072802 CE RUDDER CORRODED B P2MR K NONE O OTHER IN INSP/MAINT 1 AL 03 SUBMITTER REPORTS FINDING NUMEROUS RUDDER TORQUE TUBES SEVERLY CORRODED. DIFFICULT, BUT CAN BE SEEN ON INSPECTION. 1 H 7 1 3O NC 3A24 1996040500682 19960405 00682 SO 1996 4 5 96ZZZX1559 2 19960301 G 8520 115721 CRANKCASE CESSNA 414 414A 2075907 CE CONT O520 TSIO520NB 17040 SO LT ENGINE CRACKED B L VA1R K NONE O OTHER IN INSP/MAINT 1 SW 19 12455 2080 677 1A688P 414A1207 800530 ENGINE CRANKCASE 1157-21 DEFECTIVE DUE TO CRACKS AFT OF NR 2 CYLINDER. ALSO, NR 2 AND NR 3 BEARING SADDLES HAVE CRACKS. CRANKCASE PN 643202 MODIFIED TO 1157-21 PER STC SE 3630SW. 1 L 7 2 3O 3 O A7CE E8CE 1996040500683 19960405 00683 CE 1996 4 5 96ZZZX1560 1 19960204 G 2913 9881201 SOLENOID 12808021 CESSNA 210 T210L 2073449 CE MLG POWER PAC MALFUNCTION D A O OTHER J WARNING INDICATION LD LANDING 1 GL 03 381DS 2924 21060255 GEAR-UP LANDING ON ASPHALT RUNWAY. NO INJURIES. ALL LANDING GEAR DOORS OPENED, BUT GEAR FAILED TO EXTEND EITHER ELECTR ICALLY OR MANUALLY. FAILURE CAUSED BY RESIDUE BUILT-UP ON SHAFT OF SOLENOID PN 9881201-1 PREVENTING OPERATION OF MANIFO LD ON POWER PACK. AFTER SOLENOID SHAFT CLEANED, LANDING GEAR EXTENDED BOTH ELECTRICALLY AND MANUALLY. SUBMITTER SUGGES TS INSPECTING/CLEANING SOLENOID SHAFT AT 1,000-HOUR INTERVALS. 1 H 7 1 3O 3A21 1996040500685 19960405 00685 SO 1996 4 5 96ZZZX1562 1 19960304 G 5730 4065910 SKIN PIPER PA31 PA31310 7103103 SO WS 147-174 CRACKED D S K NONE O OTHER IN INSP/MAINT 1 EA 25 59984 7402 317512042 WING LEADING EDGE SKIN CRACKED AT STATIONS 147.50, 160.50, AND 174.50. CRACKS OF .1250 INCH LENGTH RADIATING FROM COUNT ERSUNK RIVETS FASTENING SKIN TO NOSE RIBS IN EITHER SIDE OF CUT-OUTS (IN NOSE-RIBS' TOP SURFACES). 1 L 7 1 3O RT A20SO 1996041200030 19960412 00030 SW 1996 4 12 96ZZZX1592 1 19960311 G 2550 206072903101 WIRE ROPE BELL 206 206L4 1182110 SW CARGO HOOK BROKEN B S GJQR K NONE O OTHER IN INSP/MAINT 1 NM 01 108W 1421 52034 DURING A FUEL STOP ON A NORMAL WALK-AROUND, PILOT NOTICED SOMETHING HANGING DOWN BELOW THE CARGO HOOK. FURTHER INVESTIG ATION FOUND THE CARGO HOOK EMERGENCY RELEASE CABLE BROKE COMPLETELY THROUGH 2 INCHES FROM CONNECTION ON CARGO HOOK. 1 G 7 1 3U NC H2SW 1996041200083 19960412 00083 CE 1996 4 12 96ZZZX1622 1 19960301 G 7922 07560221 VALVE CESSNA 210 T210L 2073449 CE OIL BYPASS SPRING WORN D K NONE O OTHER IN INSP/MAINT 1 NM 03 59218 2087 750 21060168 THE OIL FILTER BYPASS VALVE SPRING WAS FOUND WORN IN-HALF. THE BYPASS VALVE WAS OPEN ALLOWING OIL TO BYPASS THE FILTER. 1 H 7 1 3O 3A21 1996041200084 19960412 00084 GL 1996 4 12 96ZZZX1623 3 19960308 G 6114 D5347C73 HUB MCAULY 2A34C E2A34C73 GL OIL PLUG MISDRILLED B ME4D K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 15 764095 DURING INSPECTION, OIL PLUG HOLE WAS FOUND DRILLED IN WRONG LOCATION. (SL 1995-14.) HUB HAS BEEN SCRAPPED. 5 C P3EA9 1996041200085 19960412 00085 SO 1996 4 12 96ZZZX1624 1 19960228 G 5711 20207T902 SPAR CAP AYRES S2 S2RNORMAL 7630202 SO RT WING CORRODED B P FE6R K NONE O OTHER IN INSP/MAINT 1 NM 11 A RIGHT WING WAS RECEIVED BY THIS REPAIR STATION FOR MINOR MODIFICATION TO THE SPAR WEB. IT WAS DETERMINED THE LOWER FO RWARD SPAR CAP, AT THE WING ATTACH FITTING, HAD SEVERE RUSTING, PIT CORROSION. A MAJOR EFFORT HAS BEEN MADE TO HIDE THI S DAMAGE BY USE OF AUTO-BODY FILLERS AND PAINT. IT IS UNKNOWN WHAT AIRCRAFT REGISTRATION OR SERIAL NUMBER THIS WING WAS REMOVED FROM AS WING WAS PURCHASED INDIVIDUALLY. STEEL SPAR CAP TO BE REPLACED WITH FACTORY NEW PART. 1 L 7 1 3R NC A3SW 1996041200086 19960412 00086 CE 1996 4 12 96ZZZX1625 1 19960302 G 5210 95380010 HANDLE BEECH 36 A36 1151604 CE AFT DOOR MISINSTALLED D L A K NONE W INADEQUATE Q C IN INSP/MAINT 1 NE 03 3122U E2431 THE AFT DOOR HANDLE INSIDE AFT CABIN ON BEECH A36 BONANZA AND BEECH 58 BARON AIRCRAFT USE A HANDLE WITH A PUSH BUTTON. A PROBLEM WAS FOUND ON THE AIRCRAFT IN QUESTION DURING A PRE-PURCHASE INSPECTION. THE DOOR HANDLE WAS IMPROPERLY INDEXED ON THE SQUARE MOUNTING SHAFT. THE RESULT WAS A DOOR HANDLE WHICH OPERATED IN A MANNER OPPOSITE TO THE INTENDED DESIGN. IT WOULD ONLY LATCH BY DEPRESSING THE RELEASE BUTTON, BUT WOULD UNLATCH WITH A SINGLE MOTION. 1 L 7 1 3O 3A15 1996041200090 19960412 00090 NE 1996 4 12 96ZZZX1629 2 19960301 G 7270 DC6050001 BIDUCT DOUG DC8 DC8* WP PWA JT3D JT3D7 52039 NE ENGINE MISREPAIRED D A K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 19 0153 BI-DUCT COMPONENT ARRIVED WITH TRANSITION SECTION OF BI-DUCT REPAIRED IN A MANNER NOT CONSISTENT WITH DOUGLAS AIRCRAFT C O. SRM OR THE NACELLE CORP. SRM. DELAMINATED INNER BONDED PANEL ASSEMBLIES BEING SECURED WITH 'STRAPS'. SUSPECT CAUSE WAS MOST LIKELY REPAIR STATION ATTEMPTING REPAIR IT WAS NOT FAMILIAR WITH OR AUTHORIZED TO ACCOMPLISH. TO PREVENT RECUR RENCE, COMPONENT SHOULD BE ROUTED TO PROPER REPAIR STATION. 2 L 7 4 4J 4 F F 4A25 1E8 1996041200091 19960412 00091 NE 1996 4 12 96ZZZX1630 2 19960228 G 7321 7280774 SPIDER VALVE PWA JT8 JT8* 52044 NE FUEL CONTROL SEIZED B RD43 K NONE Y ENGINE STOPPAGE IN INSP/MAINT 1 SW 05 21J F9606 ENGINE SHUT DOWN IN TEST CELL DURING POST-RENTAL INSPECTION TEST. THE ENGINE WAS AT FULL POWER AT THE TIME OF SHUT DOWN . REMOVAL OF THE FUEL CONTROL SHOWED A SHEARED DRIVE SHAFT. REMOVAL OF THE HYDRAULIC HOUSING FROM THE LINKAGE HOUSING ON THE CONTROL SHOWED A SEIZED SPEED GOVERNOR PILOT VALVE IN THE SPIDER. THE CONTROL WAS RE-ASSEMBLED AND IS BEING ROUT ED TO AAR FOR INVESTIGATION. 4 F E2EA 1996041200092 19960412 00092 WP 1996 4 12 96ZZZX1631 1 19960315 G 2752 YS181 BEARING 57726913 DOUG DC8 DC862 3021970 WP INB FLAP ACT CYL BROKEN B DM4R K NONE O OTHER IN INSP/MAINT 1 SO 19 19 BEARING ON FLAP ACTUATOR CYLINDER BARREL RECEIVED BROKEN. SUSPECT DUE TO HIGH STRESS IN THIS AREA AS WELL AS POSSIBLE M ETAL FATIGUE. 2 L 7 4 4F 4A25 1996041200093 19960412 00093 WP 1996 4 12 96ZZZX1632 1 19960315 G 2750 37741723 CRANK 57726913 DOUG DC8 DC861 3021952 WP LT INBD FLAP BROKEN B DM4R K NONE O OTHER IN INSP/MAINT 1 SO 19 71881 CRANK RECIEVED WITH BROKEN LINK MOUNT. SUSPECT DUE TO HIGH STRESS IN THIS AREA AS WELL AS POSSIBLE METAL FATIGUE. 2 L 7 4 4F 4A25 1996041200094 19960412 00094 CE 1996 4 12 96ZZZX1633 1 19960311 G 2910 991242322 LOADING VALVE 991242323 CESSNA 525 525 2076601 CE MANIFOLD ASSY FAILED B IW1R O OTHER J WARNING INDICATION AP APPROACH 1 EA 25 94MZ 311 119 5250094 AFTER TAKEOFF, LANDING GEAR FAILED TO RETRACT. PRIOR TO TAKEOFF, PILOT REPORTED FLAPS SEEMED SLUGGISH. AFTER RECYCLING GEAR SEVERAL TIMES, SYSTEM APPEARED TO BE WORKING PROPERLY. AFTER NEXT TAKEOFF, GEAR RETRACTED NORMALLY, BUT WHEN GEAR WAS SELECTED DOWN, GEAR FAILED TO EXTEND. GEAR WAS BLOWN DOWN SUCCESSFULLY. REPLACED VALVE, OPERATIONAL CHECKED OKAY. 1 L 7 2 4F RT A1WI 1996041200095 19960412 00095 EU 1996 4 12 96ZZZX1634 1 19960301 G 2450 21650 SCREW JACK AMD FALC20 FALCON20C5 2730107 EU RT FLAP STRIPPED B A DELR O OTHER F FLT CONT AFFECTED AP APPROACH 1 CE 03 100HG 9206 362 54 DURING APROACH, PILOT MOVED FLAP HANDLE TO FIRST DETENT. THE AIRCRAFT ROLLED RIGHT. PILOT USED OVERCENTER ON CONTROL W HEEL TO LEFT TO MAINTAIN STRAIGHT AND LEVEL FLIGHT. INVESTIGATION FOUND RT FLAP INBD SCREW JACK GEARS STRIPPED AND DAMA GED. 2 L 7 2 4F RT A7EU 1996041200096 19960412 00096 NE 1996 4 12 96ZZZX1635 2 19960209 G 7250 569551 VANE PWA JT12 JT12A8 52042 NE 1ST STG TURB PLATING PEEL B L IV2R K NONE O OTHER IN INSP/MAINT 1 SW 15 P637109NB REPORTED CAUSE FOR REMOVAL OF ENGINE FROM AIRCRAFT WAS TURBINE BLADE FAILURE. INVESTIGATION FINDINGS: ENGINE DISASSEMB LED AS NECESSARY AND REPAIRED DUE TO TURBINE BLADE FAILURE. DISCREPANCY NOTED DURING INSPECTION WAS PLATING PEELING OFF 23 EACH, PN 569551, FIRST STAGE TURBINE VANES WITH A TOTAL TIME OF 396.6 HRS, AND 10 EACH REWORKED (OVERHAULED) PN 5695 51 VANES WITH 396.6 HRS TSO (REF P & WA PN 435108 OVERHAUL MANUAL, PAGES 6-92, PARA 6-229). SUBJECT VANES WERE REPLACED . 4 J 1E9 1996041200097 19960412 00097 EU 1996 4 12 96ZZZX1636 1 19960228 G 5753 258WF2512A FLAP BRAERO DH125 BAE125800A 1500285 EU RT WING DAMAGED D S K NONE O OTHER IN INSP/MAINT 1 SW 11 801CE 67 SDD263 258253 AIRCRAFT ARRIVED FOR FLAP CHANGE. BOTH LT AND RT FLAPS REMOVED AND NEW FLAPS INSTALLED. BOTH FLAPS WERE FOUND CRACKED AND UPPER SKIN TORN FROM THE LEADING EDGE TO THE TRAILING EDGE AT THE INBD ATTACH FITTING AREA. PILOTS REPORTED POSSIBL E CAUSE, OPERATION OF FLAPS ON THE GROUND WITH ICE AND SNOW BUILD-UP OR AIRCRAFT BEING TOWED OVER SNOW BANKS. 2 L 7 2 4F RT A3EU 1996041200098 19960412 00098 EU 1996 4 12 96ZZZX1637 1 19960228 G 5753 258WF2511A FLAP BRAERO DH125 BAE125800A 1500285 EU LT WING DAMAGED D K NONE O OTHER IN INSP/MAINT 1 SW 11 801CE 67 SDD253 258253 AIRCRAFT ARRIVED FOR FLAP CHANGE. BOTH LT AND RT FLAPS REMOVED AND NEW FLAPS INSTALLED. BOTH FLAPS WERE FOUND CRACKED AND UPPER SKIN TORN FROM THE LEADING EDGE TO THE TRAILING EDGE AT THE INBD ATTACH FITTING AREA. PILOTS REPORTED POSSIBL E CAUSE, OPERATION OF FLAPS ON THE GROUND WITH ICE AND SNOW BUILD-UP OR AIRCRAFT BEING TOWED OVER SNOW BANKS. 2 L 7 2 4F RT A3EU 1996041200099 19960412 00099 EU 1996 4 12 96ZZZX1638 1 19960227 G 2742 AM3C103 MOTOR LUCAS 47142203 AIRBUS 310 A310* EU H STAB ACTUATOR MISASSEMBLED D L A K NONE W INADEQUATE Q C IN INSP/MAINT 1 EA 25 180 ON 2-27-96, TWO HORIZ STAB ACTUATOR MOTORS, SN AH-57563 AND SN AH-57871, WERE RECEIVED FROM REPAIR STATION AFTER INSPECT ION AND VERIFICATION IAW REF AD AND AIRBUS AOT REFERENCED THEREIN. THESE MOTORS WERE ASSEMBLED TO AN A310 TAILPLANE ACT UATOR, PN 47142-203, SN 180. THE ACTUATOR WAS RETURNED TO LUCAS ENGLEWOOD FROM CANADIAN AIRLINES FOR ACCOMPLISHMENT OF THE SUBJECT AD 96-01-52. UPON TEST OF ACTUATOR, IT WAS FOUND TO RUN BACKWARDS TO THE COMMANDED INPUT. CLOSER INSP AND COMPARISON TO ANOTHER KNOWN GOOD A310 ACTUATOR DISCLOSED THE BODIES OF 2 MOTORS APPEARED TO BE ASSEMBLED 180 DEGREES OUT OF POSITION (NAMEPLATE AND MOD PLATES ARE 180 DEGREES OUT OF POSITION). 2 L 7 2 4F RT A35EU 1996041200689 19960412 00689 NM 1996 4 12 96ZZZX1696 1 19960313 G 2752 673D10021 FLAP DRIVE ISRAEL 1125 1125 NM FLAP SYSTEM FAILED D O OTHER F FLT CONT AFFECTED CR CRUISE 1 GL 11 550M 26 137 061 LOST USE OF FLAP SYSTEM DUE TO BROKEN SHAFT OR BAD CLUTCH IN POWER DRIVE UNIT. UNIT FAILED DUE TO ACTUATORS BINDING UP BY FREEZING TEMP AT ALTITUDE. UNITS WERE TESTED PER S.I.L. 1125-27-082 PRIOR TO INSTALLING. CHANGED NR 3 RT ACTUATOR, OK FOR 26 HRS, THEN, FAILED AGAIN. TESTED AGAIN UNDER REVISED SIL 1125-27-082. FOUND ACTUATOR PER S.I.L. IN QUESTION. CHANGED 3 EACH ACTUATORS, RETURNED TO SERVICE. 2 L 7 2 4F RT A16NM 1996041200690 19960412 00690 NM 1996 4 12 96ZZZX1697 1 19960313 G 2752 674D10017 ACTUATOR EEMCO ISRAEL 1125 1125 NM NR 3 FLAP FREEZE UP D A K NONE O OTHER IN INSP/MAINT 1 GL 11 550M 1697 288 061 PART WOULD NOT PASS TESTING FOLLOWING SIL 1125-27-082 R2 FREEZE-UP TEST. ACTUATE GREASE IN WORM GEAR DRIVE TO MIX PC-10 . FREEZE TO MINUS 50 DEGREES FAHRENEIT, MINUS 60 DEGREES FAHRENHEIT FOR 1.5 HRS. BRAKE AWAY TORQUE OF 18 INCH/POUNDS O K. RUN TORQUE OF 12 INCH/POUNDS WOULD NOT PASS. 2 L 7 2 4F RT A16NM 1996041200691 19960412 00691 NM 1996 4 12 96ZZZX1698 1 19960313 G 2752 674D10013 ACTUATOR EEMCO ISRAEL 1125 1125 NM NR 1 FLAP FREEZE UP D K NONE O OTHER IN INSP/MAINT 1 GL 11 550M 1697 480 061 PART WOULD NOT PASS TESTING FOLLOWING SIL 125-27-082 R2 FREEZE TEST. ACTUATE GREASE TO MIX THE PC-10 IN WORM GEAR DRIVE FULL TRAVEL. FREEZE TO MINUS 50 DEGREES FAHRENHEIT, 60 DEGREES FAHRENHEIT FOR 1.5 HRS. BREAK AWAY TORQUE OF 18 INCH/P OUNDS OK. RUN TORQUE OF 12 INCH/POUNDS WOULD NOT PASS. 2 L 7 2 4F RT A16NM 1996041200692 19960412 00692 NM 1996 4 12 96ZZZX1699 1 19960313 G 2752 674D10015 ACTUATOR EEMCO ISRAEL 1125 1125 NM FLAP FREEZE UP D A K NONE O OTHER IN INSP/MAINT 1 GL 11 550M 1697 484 061 PART WOULD NOT PASS TESTING FOLLOWING SIL 1125-27-082 R2 FREEZE TEST. ACTUATE GREASE MIXTURE PC-10 IN GEAR WORM DRIVE F ULL TRAVEL, FREEZE TO MINUS 50 DEGREES FAHRENHEIT, MINUS 60 DEGREES FAHRENHEIT FOR 1.5 HRS. BRAKE AWAY TORQUE 18 INCH/P OUNDS OK. RUN TORQUE 12 INCH/POUNDS WOULD NOT PASS. 2 L 7 2 4F RT A16NM 1996041200693 19960412 00693 NM 1996 4 12 96ZZZX1700 1 19960313 G 2752 673D10021 ACTUATOR EEMCO ISRAEL 1125 1125 NM NR 3 FLAP SHEARED SHAFT D A K NONE O OTHER IN INSP/MAINT 1 GL 11 550M 634 175 061 FLAP POWER DRIVE UNIT FAILED. NR 3 ACTUATOR PN 674D100-18 RIGHT SIDE HAD HIGH INPUT TORQUE WHEN COLD-SOAKED FOLLOWING S IL 1125-27-082. CHANGED POWER DRIVE UNIT AND ACTUATOR FAILED SN 137 PDU, 26 HRS LATER. SUBMITTER SUGGESTS TO REVISE TE STING INSTRUCTIONS. 2 L 7 2 4F RT A16NM 1996041200694 19960412 00694 NM 1996 4 12 96ZZZX1701 1 19960313 G 2752 674D10017 ACTUATOR ISRAEL 1125 1125 NM FLAP NR 3 DEFECTIVE D A K NONE O OTHER IN INSP/MAINT 1 GL 11 550M 551 061 ACTUATOR WAS SHIPPED AS A SERVICEABLE UNIT. TEST PER SIL 1125-27-082 R2. ACTUATED WORM GEAR DRIVE TO MIX THE PC-10 GRE ASE, FULL TRAVEL BOTH DIRECTIONS. FROZE TO MINUS 50 DEGREES FAHRENHEIT, MINUS 60 DEGREES FAHRENHEIT FOR 1.5 HRS. BRAKE AWAY TORQUE OF 18 INCH/POUNDS OK. RUN TORQUE 12 INCH/POUNDS WAS VERY CLOSE. EEMCO SAYS THAT ACTUATOR PASSES THEIR TES T TO MINUS 65 DEGREES FAHRENHEIT. ACTUATOR WAS INSTALLED PER ASTRA JET CORP. SUBMITTER RECOMMENDS BETTER FIELD TESTING INSTRUCTIONS. 2 L 7 2 4F RT A16NM 1996041200695 19960412 00695 NM 1996 4 12 96ZZZX1702 1 19960315 G 2721 D25W582050005 ACTUATOR ISRAEL 1125 1125 NM RUDDER TRIM FREEZE UP D A K NONE O OTHER IN INSP/MAINT 1 GL 11 550M 1724 068 061 TRIM ACTUATOR FREEZING UP AT ALT. IN COLD WEATHER CONDITIONS, 10 DEGREES FAHRENHEIT OR SO. 2 L 7 2 4F RT A16NM 1996041200696 19960412 00696 CE 1996 4 12 96ZZZX1703 1 19960313 G 2440 MS353061 POWER RECEPTACLE LEAR 60 60LEAR 5170707 CE EXT POWER CORRODED D K NONE O OTHER IN INSP/MAINT 1 SW 05 65BL 224 054 AIRCRAFT EXTERNAL POWER RECEPTACLE POSITIVE PROBE CORRODED AND LOOSE. EVIDENCE OF HIGH HEAT WAS APPARENT AT THE TERMINA L ATTACHING CABLES INSIDE THE AIRCRAFT. SUBMITTER RECOMMENDS THAT LR60 OPERATORS INSPECT THIS AREA ASAP. REPLACED THE TERMINALS AND POWER RECEPTACLE. 2 L 7 2 4F RT A10CE 1996041200697 19960412 00697 NM 1996 4 12 96ZZZX1704 1 19960313 G 2752 674D10018 ACTUATOR EEMCO ISRAEL 1125 1125 NM NR 3 RT FLAP FREEZE UP D A K NONE O OTHER IN INSP/MAINT 1 GL 11 550M 495 061 ACTUATOR WAS SHIPPED AS A SERVICEABLE UNIT. TEST PER SIL 1125-27-082 R2 ACTUATED WORM GEAR DRIVE TO MIX PC-10. FULL TR AVEL, BOTH DIRECTIONS. FROZE TO MINUS 50 DEGREES FAHRENHEIT, MINUS 60 DEGREES FAHRENHEIT FOR 1.5 HRS. BRAKE AWAY TORQU E OF 18 INCH/POUNDS OK. RUN TEST OF 12 INCH/POUNDS WOULD NOT PASS. UNIT WAS TESTED AND REPAIRED AND SHIPPED H6-96. 2 L 7 2 4F RT A16NM 1996041200698 19960412 00698 EA 1996 4 12 96ZZZX1705 2 19960315 G 8500 ENGINE MOONEY M20 M20E 5870212 SW LYC O360 IO360A1A 41514 EA PWR SECTION SEIZED H A UNSCHED LANDING Y ENGINE STOPPAGE CR CRUISE 1 SW 99 1940Y 247 L60951 AIRCRAFT WAS IN LEVEL FLIGHT AT 13,500 FEET, HAD COMPLETE ENGINE FAILURE AND SEIZED WITH NO PRIOR WARNING. DECLARED EME RGENCY. GLIDED 17.2 NM BACK TO AIRPORT, LANDED WITHOUT FURTHER INCIDENT. NO DAMAGE TO AIRCRAFT AND NO INJURIES. ENGIN E SCHEDULED TO BE REPLACED 3-28-96. 1 L 7 1 3O 3 O 2A3 1E10 1996041200699 19960412 00699 CE 1996 4 12 96ZZZX1706 1 19960315 G 2810 182001 BLADDER CESSNA 206 P206 2073304 CE WING FUEL CELL LEAKS D K NONE K FLUID LOSS IN INSP/MAINT 1 CE 07 2639X P2060139 OLD RUBBER BLADDERS LEAKED GAS OUT AND HAD LARGE WRINKLES ON BOTTOM OF TANKS. SN 0977 AND SN 0978. 1 H 7 1 3O A4CE 1996041200700 19960412 00700 CE 1996 4 12 96ZZZX1707 1 19960320 G 2437 AMMETER CESSNA 172 172M 2072418 CE DC SYSTEM SEIZED D K NONE O OTHER IN INSP/MAINT 1 NE 01 64262 750 17265135 AMMETER NEEDLE FROZEN. WOULD NOT SHOW ANY SIGN OF CHARGE OR DISCHARGE. NO LOW VOLTAGE INDICATOR ON 172M. 1975 MODEL S KYHAWK. 1 H 7 1 3O NT 3A12 1996041200702 19960412 00702 EA 1996 4 12 96ZZZX1709 2 19960303 G 8530 CYLINDER LYC O320 O320E2A 41508 EA SKIRT AREA DAMAGED H K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 01 100 DURING A TEAR DOWN OF AN ENGINE, FOUND CYLINDERS WERE VERY HARD TO MOVE. AFTER THEY WERE TAKEN OFF, NOTICED ENGRAVED ET CHING ON CYLINDER SKIRT WAS RAISED AND VERY MUCH HIGHER THAN THE SURROUNDING AREA. THE VIBRATING PENCIL WAS VERY SHARP AND SET TO CUT MAXIMUM. STONING THE EFFECTED AREA AND SMOOTHING THE CRANKCASE TO RELIEVE STRESS SOLVED THE PROBLEM. 3 O E274 1996041200703 19960412 00703 EA 1996 4 12 96ZZZX1710 2 19960214 G 7414 10382894 GEARTOOTH BENDIX DYRN2021 CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA LT MAGNETO BROKEN D K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 EA 21 1465E 343 5023753R 17271012 L122176T REMOVED MAGNETO DUE TO ROUGH ENGINE. FOUND A TOOTH BROKEN OFF OF LEFT DISTRIBUTOR GEAR. MAGNETO WAS ON A LYCOMING FACT ORY OVERHAUL. MAGNETO WAS OVERHAULED BY ELECTRO SYSTEMS, INC. 1 H 7 1 3O 3 O NT 3A12 E274 1996041200704 19960412 00704 SO 1996 4 12 96ZZZX1711 2 19960314 G 8530 VALVE PIPER PA28 PA28R200 7102811 SO CONT O360 IO360C 17025 SO NR 4 INT FAILED D A UNSCHED LANDING E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CL CLIMB 1 EA 27 32481 1526 28R7535061 L2220251A ON TAKEOFF, ENGINE BEGAN TO VIBRATE (AT FULL POWER SETTINGS). RETURNED TO AIRPORT. UPON INSPECTION, FOUND NR 4 INTAKE VALVE BROKEN IN HALF ON FACE AREA. NR 4 PISTON SEVERELY DAMAGED, COULD NOT LOCATE PARTS OF MISSING VALVE. SUSPECT INJE STED INTO ENGINE THOUGH NO METAL WAS FOUND IN OIL FILTER OR SUMP SCREEN. TT 1,526.0 HOURS ON ENGINE. 1 L 7 1 3O 3 O 2A13 E1CE 1996041200705 19960412 00705 EA 1996 4 12 96ZZZX1712 2 19960316 G 7414 M3525 COIL SLICK 4270 PIPER PA28 PA28140 7102802 SO LYC O320 O320E2A 41508 EA RT MAGNETO OPEN D K NONE R PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 NE 05 217LM 4270 21689 2821972 L2406227AC DURING RUN-UP, PILOT EXPERIENCED RT MAGNETO EXCESSIVE DROP. ON REMOVAL BY MAINTENANCE, ENGINE WOULD NOT RUN ON RT MAGNE TO. FOUND OPEN IN SECONDARY COIL WINDINGS. 1 L 7 1 3O 3 O 2A13 E274 1996041200706 19960412 00706 CE 1996 4 12 96ZZZX1713 1 19960316 G 7603 5038901223 CONTROL CABLE BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO THROTTLE FAILED D O OTHER O OTHER NR NOT REPORTED 1 NE 05 511CF 474 TH833 CONTROL CABLE SOLID SHAFT BROKE NEAR ROD END THREADS ASSY - WHERE THIS ASSY IS SWEDGED TO SOLID SHAFT. 1 L 7 2 3O 3 O 3A16 E5CE 1996041200707 19960412 00707 SO 1996 4 12 96ZZZX1714 2 19960321 G 8520 634505 STUD NUT CESSNA 182 182Q 2072732 CE CONT O470 O470U 17026 SO NR 6 CYLINDER CRACKED D P K NONE O OTHER IN INSP/MAINT 1 NM 01 9579E 993 18268428 286862R TWELVE-POINT NUT ON THROUGH-BOLT, PN 641931-10.75, CRACKED. NUT IS LOWER FORWARD NUT ON NR 6 CYLINDER. SUBMITTER RECOM MENDS USING 6-POINT NUT ONLY. 1 H 7 1 3O 3 O NT 3A13 E273 1996041200708 19960412 00708 CE 1996 4 12 96ZZZX1715 1 19960320 G 2820 PRIMER SYSTEM CESSNA 182 182Q 2072732 CE CONT O470 O470U 17026 SO PRIMER NOZZLE LEAKAGE D A O OTHER A FLAME/FIRE IN INSP/MAINT 1 NM 01 5164N 18267554 286603R ENGINE HAD FIRE DURING START-UP. FUEL FROM PRIMER NOZZLES RAN DOWN FLOW DIVIDER ABOVE CARBURETOR INTO CARBURETOR THROAT AND THEN INTO CARBURETOR HEAT BOX AND OUT CARBURETOR HEAT DRAIN HOLE INTO COWLING. AFTER START, BACKFIRE IGNITED FUEL. NOTE: EARLIER STYLE 182Q WITH PRIMER SYSTEM AND DISTRIBUTION SPIDER INJECT FUEL DIRECTLY INTO CYLINDERS AVOIDING FUEL DRAINING INTO COWL. 1 H 7 1 3O 3 O NT 3A13 E273 1996041200719 19960412 00719 WP 1996 4 12 96ZZZX1726 2 19960103 G 7250 31038393 SEAL 31033155 GARRTT TPE331 TPE33112UHR WP TURB 1ST STAGE FLANGE CRACKED B DSCR K NONE O OTHER IN INSP/MAINT 1 GL 25 7217 1233151952 P70104 DURING INSPECTION FOR METAL CONTAMINATION, FOUND AIR SEAL CRACKED AT SEALING FLANGE. THIS IS A CRITICAL LIFE-LIMITED CO MPONENT. LIFE-LIMIT IS 20,000 CYCLES. SUBMITTER STATES THIS IS THE 24TH MALFUNCTION/DEFECT REPORT SUBMITTED ON THIS PA RT BY THIS REPAIR STATION. PART TOTAL CYCLES, 7,541. 4 T E4WE 1996041200720 19960412 00720 WP 1996 4 12 96ZZZX1727 2 19960212 G 7250 31038393 SEAL 31033155 GARRTT TPE331 TPE33112UHR WP TURB 1ST STAGE FLANGE CRACKED B DSCR K NONE O OTHER IN INSP/MAINT 1 GL 25 7318 1233151936 P70112 DURING SCHEDULED CAM INSPECTION, FOUND AIR SEAL CRACKED AT FLANGE. THIS IS A CRITICAL LIFE-LIMITED COMPONENT. LIFE-LIM IT IS 20,000 CYCLES. SUBMITTER SUGGESTS THIS IS THE 26TH MALFUNCTION/DEFECT REPORT ON THIS PART BY THIS FACILITY. PART TOTAL CYCLES, 7,435. 4 T E4WE 1996041200721 19960412 00721 WP 1996 4 12 96ZZZX1728 2 19960104 G 7250 31038393 SEAL 31033155 GARRTT TPE331 TPE33112UHR WP TURB 1ST STAGE FLANGE CRACKED B DSCR K NONE O OTHER IN INSP/MAINT 1 GL 25 9588 9233151520 P70035 DURING INSPECTION FOR BIRD INGESTION, FOUND AIR SEAL CRACKED AT FLANGE. THIS IS A CRITICAL LIFE-LIMITED COMPONENT. LIM IT - 20,000 CYCLES. SUBMITTER STATES THIS IS THE 27TH MALFUNCTION/DEFECT REPORT ON THIS PART BY THIS FACILITY. PART TO TAL CYCLES, 9,859. 4 T E4WE 1996041200722 19960412 00722 WP 1996 4 12 96ZZZX1729 2 19960314 G 7250 31038393 SEAL 31033155 GARRTT TPE331 TPE33112UHR WP TURB 1ST STAGE FLANGE CRACKED B DSCR K NONE O OTHER IN INSP/MAINT 1 GL 25 7286 1233151992 P70108 DURING SCHEDULED CAM INSPECTION, FOUND AIR SEAL CRACKED AT FLANGE. CRACKING RESULTED IN DEFLECTION OF SEALING SURFACE O F .040 INCH CAUSING LOSS OF COOLING AIR FOR TURBINE SECTION. THIS IS A CRITICAL LIFE-LIMITED COMPONENT. LIFE-LIMIT IS 20,000 CYCLES. SUBMITTER SUGGESTS THIS IS THE 28TH MALFUNCTION/DEFECT REPORT SUBMITTED BY THIS FACILITY ON THIS DISCREP ANCY. PART TOTAL CYCLES, 8,461. 4 T E4WE 1996041200723 19960412 00723 WP 1996 4 12 96ZZZX1730 2 19960314 G 7250 31038393 SEAL 31033155 GARRTT TPE331 TPE33112UHR WP TURB 1ST STAGE FLANGE CRACKED B DSCR K NONE O OTHER IN INSP/MAINT 1 GL 25 7144 1233151935 P70111C DURING SCHEDULED CAM INSPECTION, FOUND ROTATING AIR SEAL CRACKED AT FLANGE. THIS IS A CRITICAL LIFE-LIMITED COMPONENT. LIFE-LIMIT IS 20,000 CYCLES. SUBMITTER STATES THIS IS THE 29TH MALFUNCTION/DEFECT REPORT SUBMITTED BY THIS FACILITY ON THIS DISCREPANCY. PART TOTAL CYCLES, 7,125. 4 T E4WE 1996041800121 19960418 00121 NE 1996 4 18 96ZZZX1753 3 19960210 G 6111 BLADE BEECH 1900 1900D 1154162 CE HARTZL HCE4A HCE4A3A NE PROPELLER SPLIT A AMWA K NONE O OTHER IN INSP/MAINT 1 CE 07 182YV 1054 UE182 HJ425 DURING ROUTINE MAINTENANCE, PROPELLER BLADE, SN 1655, WAS FOUND TO HAVE A 4 INCH SPLIT ON TRAILING EDGE. REPAIRED IAW H ARTZELL MM AND FORM 8110-3 FROM HARTZELL. 2 L 7 2 4T RT A24CE 5 C P10NE 1996041800122 19960418 00122 NE 1996 4 18 96ZZZX1754 3 19960218 G 6111 E10950PK BLADE BEECH 1900 1900D 1154162 CE HARTZL HCE4A HCE4A3A NE RT PROPELLER SPLIT A AMWA K NONE O OTHER IN INSP/MAINT 1 CE 07 182YV 1155 UE182 HJ425 DURING ROUTINE MAINTENANCE, THE TRAILING EDGE WAS FOUND SPLIT APROXIMATELY 1.5 INCHES. REPAIRED IAW HARTZELL MM AND FOR M 8110-3. 2 L 7 2 4T RT A24CE 5 C P10NE 1996041800132 19960418 00132 EU 1996 4 18 96ZZZX1764 1 19960120 G 3340 A402AR LIGHT BOLKMS 105 BO105S 5626006 EU ANTI COLLISON LENS UNGLUED B AC2R K NONE O OTHER IN INSP/MAINT 1 SW 03 5352Y 252 S781 ANTI-COLLISION LIGHT LENS CAME UNGLUED AT SEAM. COULD GO INTO TAIL ROTOR. REPLACED LENS. 1 G 7 2 3U H3EU 1996041800151 19960418 00151 CE 1996 4 18 96ZZZX1770 1 19960227 G 5511 04320016 RIB CESSNA 150 152 2071835 CE LT-RT HORIZ STAB CRACKED D A K NONE O OTHER IN INSP/MAINT 1 CE 09 89812 5550 15282879 LEFT AND RIGHT HORIZONTAL STABILIZER ATTACH RIBS WERE CRACKED IN REAR FLANGE AND NEXT TO PLATE NUT. NEW PARTS ARE MADE DIFFERENT. SUBMITTER SUGGESTS HIGH TIME, PUSHING ON TAIL, EXCESSIVE GAP BETWEEN BULKHEAD AND RIBS MAY BE CAUSING CRACKS . 1 H 7 1 3O NT 3A19 1996041800152 19960418 00152 CE 1996 4 18 96ZZZX1771 1 19960227 G 5511 043200146 RIB CESSNA 150 152 2071835 CE LT-RT HORIZ STAB CRACKED D K NONE O OTHER IN INSP/MAINT 1 CE 09 89812 5550 15282879 LEFT AND RIGHT HORIZONTAL STABILIZER ATTACH RIBS WERE CRACKED IN REAR FLANGE AND NEXT TO PLATE NUT. NEW PARTS ARE MADE DIFFERENT. SUBMITTER SUGGESTS HIGH TIME, PUSHING ON TAIL, EXCESSIVE GAP BETWEEN BULKHEAD AND RIBS MAY BE CAUSING CRACKS . 1 H 7 1 3O NT 3A19 1996041800153 19960418 00153 CE 1996 4 18 96ZZZX1772 1 19960219 G 2820 05560203 VENT LINE CESSNA 172 172N 2072434 CE WING ROOT DETERIORATED D A K NONE O OTHER IN INSP/MAINT 1 GL 25 2165E 17271174 FUEL VENT LINE CONNECTING HOSES DETERIORATED TO THE POINT OF LEAKAGE OF FUEL IN THE WING ROOT AREA. ALL 3 HOSES ON BOTH SIDES NEEDED REPLACING DUE TO AGE. 1 H 7 1 3O NT 3A12 1996041800154 19960418 00154 SO 1996 4 18 96ZZZX1773 1 19960301 G 5751 6237301 DOUBLER 6810500 PIPER PA32 PA32260 7103206 SO RT AIL HINGE CRACKED H P A K NONE O OTHER IN INSP/MAINT 1 SO 03 3855W 321057 OUTBOARD DOUBLER HOLDING AILERON TO WING (REINFORCES MOUNT) HAS CRACKS. FOUND ON THREE CONSECUTIVE AIRCRAFT DURING ANNU AL INSPECTION. THREE RIGHT OUTBOARD AND ONE LEFT OUTBOARD. SUBMITTER SUGGESTS COUNTERWEIGHTS FOR THE AILERON MAY BE CA USING STRESS FRACTURES. SUGGEST AN ADDITIONAL PRE-FLIGHT CARD ITEM SHOULD BE ADDED TO PRE-FLIGHT CHECK LIST. CAN BE RE ADILY SEEN IF LOOKED FOR. 1 L 7 1 3O A3SO 1996041800155 19960418 00155 SO 1996 4 18 96ZZZX1774 1 19960301 G 5751 6237301 DOUBLER 6810500 PIPER PA32 PA32260 7103206 SO RT AIL HINGE CRACKED H P A K NONE O OTHER IN INSP/MAINT 1 SO 03 5517J 32949 OUTBOARD DOUBLER HOLDING AILERON TO WING (REINFORCES MOUNT) HAS CRACKS. FOUND ON THREE CONSECUTIVE AIRCRAFT DURING ANNU AL INSPECTION. THREE RIGHT OUTBOARD AND ONE LEFT OUTBOARD. SUBMITTER SUGGESTS COUNTERWEIGHTS FOR THE AILERON MAY BE CA USING STRESS FRACTURES. SUGGEST AN ADDITIONAL PRE-FLIGHT CARD ITEM SHOULD BE ADDED TO PRE-FLIGHT CHECK LIST. CAN BE RE ADILY SEEN IF LOOKED FOR. 1 L 7 1 3O A3SO 1996041800156 19960418 00156 SO 1996 4 18 96ZZZX1775 1 19960301 G 5751 6237301 DOUBLER 6810500 PIPER PA32 PA32260 7103206 SO RT AIL HINGE CRACKED H P A K NONE O OTHER IN INSP/MAINT 1 SO 03 3258W 3281 OUTBOARD DOUBLER HOLDING AILERON TO WING (REINFORCES MOUNT) HAS CRACKS. FOUND ON THREE CONSECUTIVE AIRCRAFT DURING ANNU AL INSPECTION. THREE RIGHT OUTBOARD AND ONE LEFT OUTBOARD. SUBMITTER SUGGESTS COUNTERWEIGHTS FOR THE AILERON MAY BE CA USING STRESS FRACTURES. SUGGEST AN ADDITIONAL PRE-FLIGHT CARD ITEM SHOULD BE ADDED TO PRE-FLIGHT CHECK LIST. CAN BE RE ADILY SEEN IF LOOKED FOR. 1 L 7 1 3O A3SO 1996041800157 19960418 00157 CE 1996 4 18 96ZZZX1776 1 19960306 G 7603 10052417715 CONDITION LEVER BEECH 90 C90 1152913 CE LT SIDE PEDESTAL WORN D A K NONE O OTHER IN INSP/MAINT 1 GL 15 2050A 8015 LJ813 INSPECTED CONDITION LEVER AFTER OPPOSITE SIDE FAILED. FOUND LEVER WORN MORE THAN 50 PERCENT THROUGH. SUBMITTER RECOMME NDS MORE FREQUENT INSPECTIONS, I.E., EACH 150 HOURS. 1 L 7 2 3T 3A20 1996041800158 19960418 00158 SO 1996 4 18 96ZZZX1777 1 19960216 G 1210 35669163 PLACARD PIPER PA32 PA32301 7103207 SO FUEL PORT WRONG PART B S BDTR K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 09 8442H 328106098 PARTS BOOK SHOWS 2 DIFFERENT FUEL PORT PLACARDS. WHEN ORDERING THE PLACARD REQUIRED BY THE P.O.H., THE PIPER FACTORY SU PERCEDES TO THE PLACARD FOR THE NEWER MODEL. THIS IS IN ERROR AND PIPER IS CREATING AN UNAIRWORTHY ANSWER -- PN 45-682 IS S/S FROM PN 35669-163. 1 L 7 1 3O A3SO 1996041800159 19960418 00159 CE 1996 4 18 96ZZZX1778 1 19960321 G 5312 05121871 BULKHEAD CESSNA 172 172N 2072434 CE CABIN DOORPOST CRACKED G S K NONE O OTHER IN INSP/MAINT 1 GL 03 1600 DURING AN ANNUAL INSPECTION, THE LOWER REAR CABIN DOORPOST BULKHEAD WAS FOUND CRACKED ON THE LEFT AND RIGHT SIDES AT THE POINT WHERE THE CABIN FLOOR AND BULKHEAD MEET. THE CRACK BEGINS AT A RADIUS RELIEF POINT AND PROPAGATES TO THE UPPER M OUNTING HOLE OF THE LANDING GEAR SUPPORT. THE BULKHEAD PART NUMERS ARE 0512187-1 AND 0512187-2. THE AIRCRAFT THIS CONDI TION HAS BEEN FOUND ON ARE CESSNA MODELS 172N, Q, AND P. THE LOWEST TIME AIRCRAFT HAS 1,600 HOURS TOTAL TIME, THE REST OF THE AIRCRAFT INSPECTED HAD IN EXCESS OF 4,100 HOURS. 1 H 7 1 3O NT 3A12 1996041800160 19960418 00160 CE 1996 4 18 96ZZZX1779 1 19960304 G 5230 5213007200 HINGE CESSNA 402 402C 207590R CE BAGG DOOR CRACKED I K NONE O OTHER IN INSP/MAINT 1 NE 05 3249M 9789 402C0296 BAGGAGE DOOR WAS OPERATED AND FLIGHT CREW NOTICED BROKEN HINGE. HINGE IS WHITE METAL AND SUSPECTED TO BE OLD STYLE SLID E LOCKS THAT CAUSED FRACTURE. CURRENTLY, S.K. KIT OF HYD ACTUATOR INSTALLED. SUBMITTER SUGGESTS WHEN LOADING, MAKE SUR E BAGGAGE DOES NOT STRESS DOOR. 1 L 7 2 3O A7CE 1996041800161 19960418 00161 SO 1996 4 18 96ZZZX1780 1 19960207 G 7820 6689400 MUFFLER PIPER PA28 PA28180 7102808 SO FWD POSITION CRACKED H K NONE O OTHER IN INSP/MAINT 1 SO 05 32103 3623 287505026 UPON ANNUAL INSPECTION, REMOVAL OF EXHAUST SHROUD FOUND MUFFLER CRACKED AT POINT WHERE SHROUD CHAFED MUFFLER. YEAR AFTE R YEAR OF REMOVAL AND REINSTALLATION OF SHROUD TO MUFFLERS FINALLY WORE MUFFLER MATERIAL THIN ENOUGH TO CRACK AND LEAK. SUBMITTER SUGGESTS THOROUGH INSPECTION EACH TIME SHROUD REMOVED (ANYTIME) ESPECIALLY AT CLAMP POINTS. 1 L 7 1 3O 2A13 1996041800162 19960418 00162 EU 1996 4 18 96ZZZX1781 1 19960311 G 7730 GEM610 ENGINE MONITOR SOCATA TB20 TB20TRINIDAD 8680695 EU COCKPIT COMM INTERFERENCE B BF1R K NONE O OTHER IN INSP/MAINT 1 EA 05 25SW 50 360 GRAPHIC ENGINE MONITOR (MODEL GEM610) RADIATING RF1 TO BOTH COMM RADIOS ON 132.05 MHZ. 1 L 7 1 3O RT A51EU 1996041800163 19960418 00163 EA 1996 4 18 96ZZZX1782 2 19960307 G 8520 LW19332S CONNECTING ROD PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA NR 1 CYLINDER FAILED G O OTHER E R K VIBRATION/BUFFET PARTIAL RPM/PWR LOSS FLUID LOSS NR NOT REPORTED 1 CE 09 23NP 1903 318352007 L40668A CONNECTING ROD NR 1 CYLINDER FAILED AND CAME THROUGH THE CASE. THE ROD BEARING HAD NOT SPUN, THE ONLY ROD BOLT FOUND AP PEARED TO HAVE FAILED AFTER THE FACT. 1 L 7 2 3O 3 O A20SO E14EA 1996041800164 19960418 00164 CE 1996 4 18 96ZZZX1783 1 19960112 G 7714 D11125025 TACHOMETER MITCH CESSNA 172 172P 2072436 CE ENG TACHOMETER STICKS D K NONE O OTHER IN INSP/MAINT 1 NM 03 97LP 21 5481 17274398 INSTALLED NEW MITCHELL TACHOMETER IN AIRCRAFT. NEXT MORNING, TACHOMETER WAS STICKING UNTIL A SHORT WARM-UP. THREE FLIG HTS LATER, STRIKING RECURRED. AT 21.1 TACHOMETER HOURS, STICKING OCCURRED AGAIN ALONG WITH ERRATIC READINGS. REPLACED MITCHELL TACHOMETER WITH RECONDITIONED AC UNIT, NO FURTHER PROBLEMS. 1 H 7 1 3O NT 3A12 1996041800165 19960418 00165 CE 1996 4 18 96ZZZX1784 1 19960317 G 2822 8110C PUMP WELDON BBAVIA 7 7KCAB 21101P3 CE MAIN SHAFT SEAL LEAK C K NONE K FLUID LOSS IN INSP/MAINT 1 WP 13 1840G 15101 79 SEAL FAILED CAUSING FUEL TO VENT THROUGH ELECTRIC (DC) MOTOR, PAST ARCING BRUSHES. ASSEMBLY INSTALLED ORIGINALLY WITHOU T CASE VENT AND DRAIN TUBE. SUBMITTER RECOMMENDS OWNERS OF OLD 7KCAB CITABRIAS BE ADVISED TO CHECK INSTALLATION FOR LEA KING AND PRESENCE OF CASE VENT AND DRAIN TUBE. -- FIRE HAZARD --. 1 H 7 1 3O A759 1996041800166 19960418 00166 SO 1996 4 18 96ZZZX1785 1 19960223 G 5513 MS2106123K NUTPLATE 65248000 PIPER PA28 PA28140 7102802 SO LT/RT STAB TRIM RUSTED D K NONE O OTHER IN INSP/MAINT 1 EA 05 9791W 4113 2823284 NUT BODY OF ALL 4 NUTPLATES SECURING ARM ASSY STABILIZER TRIM, PN 65248-000, TO LEFT AND RIGHT STABILATOR TRIM TABS EATE N THROUGH WITH RUST AND SPLIT OPEN. SUSPECT MOISTURE. RECOMMENDATION - SPLIT TRIM TABS AND INSPECT NUTPLATES AT EACH A NNUAL INSPECTION. 1 L 7 1 3O 2A13 1996041800167 19960418 00167 SO 1996 4 18 96ZZZX1786 1 19960301 G 5741 ATTACH FITTING PIPER PA25 PA25235 7102504 SO WING FWD CORRODED D K NONE O OTHER IN INSP/MAINT 1 NE 01 7685Z 5000 253838 DURING C/W AD 95-12-01, (FWD SPAR FITTING INSPECTION), HEAVY RUST FOUND INSIDE RT TUBE CLUSTER; MAINLY BEHIND THE CLOSE- OUT PLATE BETWEEN THE ATTACH FITTING LUGS. THIS AREA USUALLY CANNOT BE INSPECTED, BUT IN THIS CASE, THE CLOSE-OUT PLATE WAS EASILY REMOVED DUE TO THE CORROSION. THE CARRY-THROUGH TUBE BEHIND THE PLATE WAS FOUND RUSTED THROUGH, BUT EXTERNA LLY, THE CLUSTER SHOWED NO SIGN OF CORROSION. THE CLOSE-OUT PLATE HAD TWO SMALL RUST HOLES AT ITS UPPER EDGE. THIS PLA TE IS ONLY PARTIALLY WELDED INTO PLACE AND IT APPEARS TO TRAP MOISTURE AGAINST THE LOWER CARRY-THROUGH TUBE. SUBMITTER STATES AD 95-12-01 SHOULD BE REVISED TO ADDRESS THIS AREA REQUIRING REMOVAL OF CLOSE-OUT PLATES. 1 L 7 1 3O 2A10 1996041800168 19960418 00168 CE 1996 4 18 96ZZZX1787 1 19960306 G 5541 04330106 SPAR CESSNA 150 152 2071835 CE RUDDER CRACKED D K NONE O OTHER IN INSP/MAINT 1 WP 17 4686L 5738 15284216 PERFORMING RUDDER SPAR INSPECTION IAW CESSNA SB SEB 94-3, AND FOUND RUDDER SPAR CRACKED. REPLACED RUDDER IAW SEB 94-3. 1 H 7 1 3O NT 3A19 1996041800169 19960418 00169 1996 4 18 96ZZZX1788 2 19960226 G 7314 5006484 DRIVE GEAR LUCAS 5009986 FUEL PUMP FAILED B OL3R K NONE O OTHER IN INSP/MAINT 1 WP 27 1830 SQUAWK NO FUEL FLOW. PUMP SHUT DOWN. FOUND THERE IS NO SPLINE LEFT ON DRIVE SHAFT OR DRIVE GEAR. DRIVE SHAFT EASILY T URNS BY HAND. SUBMITTER STATED C/W SB NO-21087R5 COULD HAVE PREVENTED EXCESSIVE WEAR ON DRIVE SHAFT INTERNAL SPLINE. 1996041800170 19960418 00170 1996 4 18 96ZZZX1789 2 19960226 G 7314 5006485 DRIVE SHAFT LUCAS 5009986 FUEL PUMP FAILED B OL3R K NONE O OTHER IN INSP/MAINT 1 WP 27 1830 SQUAWK NO FUEL FLOW. PUMP SHUT DOWN. FOUND THERE IS NO SPLINE LEFT ON DRIVE SHAFT OR DRIVE GEAR. DRIVE SHAFT EASILY T URNS BY HAND. SUBMITTER STATED C/W SB NO-21087R5 COULD HAVE PREVENTED EXCESSIVE WEAR ON DRIVE SHAFT INTERNAL SPLINE. 1996041800171 19960418 00171 EA 1996 4 18 96ZZZX1790 2 19960306 G 8530 LW11800 SPRING CESSNA 175 175 2072502 CE LYC O360 O360A1A 41514 EA NR 4 CYL EXH VLV BROKEN D K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 WP 27 9462B 400 55262 L1471536A ROUGH ENGINE OPERATION ABOVE 2,500 RPM'S. FOUND NR 4 CYLINDER OUTER EXHAUST VALVE SPRING BROKEN. 1 H 7 1 3O 3 O NT 3A17 E286 1996041800172 19960418 00172 CE 1996 4 18 96ZZZX1791 1 19960321 G 3222 968200183 RETAINER BEECH 58 58 1152740 CE NLG STRUT CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 11 126LF 2371 TH440 UPPER NLG COLLAR FOUND CRACKED. NOSE GEAR REMOVED, UPPER STRUT RETAINER (COLLAR) REPLACED WITH FACTORY NEW. NLG REINST ALLED AND CYLCED SHOWING PROPER OPERATION. 1 L 7 2 3O 3A16 1996041800173 19960418 00173 CE 1996 4 18 96ZZZX1792 1 19960306 G 7603 10052417717 CONDITION LEVER BEECH 90 C90 1152913 CE RT PEDESTAL FAILED D K NONE O OTHER IN INSP/MAINT 1 GL 15 2050A 8015 LJ813 PILOT WAS STARTING RT ENGINE AND WHEN FUEL CONDITION LEVER WAS ADVANCED, THE LEVER BROKE OFF FLUSH WITH THE PEDESTAL. T HE ONLY WAY TO SHUT DOWN ENGINE WAS TO CLOSE FIREWALL SHUT-OFF VALVE. SUBMITTER STATED NEED SET INSPECTION INTERVAL. 1 L 7 2 3T 3A20 1996041800174 19960418 00174 CE 1996 4 18 96ZZZX1793 1 19960306 G 7603 10052417715 CONDITION LEVER BEECH 100 A100 1152915 CE LT SIDE PEDESTAL WORN D K NONE O OTHER IN INSP/MAINT 1 GL 15 41BE 9709 B245 INSPECTED CONDITION LEVER AFTER FAILURE ON OTHER AIRCRAFT. FOUND WORN 50 PERCENT THROUGH. SUBMITTER RECOMMENDS INSPECT IONS AT 150-HOUR INTERVALS. 1 L 7 2 3T A14CE 1996041800175 19960418 00175 CE 1996 4 18 96ZZZX1794 1 19960306 G 7603 10052417717 CONDITION LEVER BEECH 100 A100 1152915 CE RT SIDE PEDESTAL WORN D K NONE O OTHER IN INSP/MAINT 1 GL 15 41BE 9709 B245 INSPECTED CONDITION LEVERS WHERE WEARS ON PEDESTAL. FOUND LEVER WORN APPROXIMATELY 50 PERCENT THROUGH. SUBMITTER RECOM MENDS MORE FREQUENT INSPECTION. 1 L 7 2 3T A14CE 1996041800176 19960418 00176 CE 1996 4 18 96ZZZX1795 1 19960310 G 5312 24130013 BULKHEAD CESSNA 172 172RG 2072438 CE LOWER FUSELAGE CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 15 115HM 4887 172RG0490 DURING 100-HOUR INSPECTION, FOUND RUDDER PEDAL TUBE MOUNTING BLOCKS FLEXING UP AND DOWN WHEN PRESSURE WAS APPLIED TO PED ALS. FURTHER INSPECTION OF THE PROBLEM REVEALED CRACKS IN THE LOWER BULKHEADS (172RG PART CATALOG, FIGURE 19, INDEX 16 AND INDEX 20) BELOW THE INBOARD RUDDER PEDAL TUBE MOUNTING BLOCKS ON BOTH THE PILOT AND CO-PILOT SIDE. SUSPECT CAUSE IS INSUFFICIENT MATERIAL THICKNESS OF BULKHEAD OR BEARING SURFACE UNDER MOUNTING BLOCK BOLT, NUT. RECOMMEND INSPECTION OF BULKHEAD FOR CRACKS. 1 H 7 1 3O 3A17 1996041800177 19960418 00177 CE 1996 4 18 96ZZZX1796 1 19960310 G 5312 24130014 BULKHEAD CESSNA 172 172RG 2072438 CE LOWER FUSELAGE CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 15 115HM 4887 172RG0490 DURING 100-HOUR INSPECTION, FOUND RUDDER PEDAL TUBE MOUNTING BLOCKS FLEXING UP AND DOWN WHEN PRESSURE WAS APPLIED TO PED ALS. FURTHER INSPECTION OF THE PROBLEM REVEALED CRACKS IN THE LOWER BULKHEADS, 172RG PART CATALOG, FIGURE 19, INDEX 16 AND INDEX 20), BELOW THE INBOARD RUDDER PEDAL TUBE MOUNTING BLOCKS ON BOTH THE PILOT AND CO-PILOT SIDE. SUSPECT CAUSE I S INSUFFICIENT MATERIAL THICKNESS OF BULKHEAD OR BEARING SURFACE UNDER MOUNTING BLOCK BOLT, NUT. RECOMMEND INSPECTION O F BULKHEAD FOR CRACKS. 1 H 7 1 3O 3A17 1996041800178 19960418 00178 CE 1996 4 18 96ZZZX1797 1 19960310 G 5312 24130013 BULKHEAD CESSNA 172 172RG 2072438 CE LOWER FUSELAGE CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 15 9303D 3995 172RG1113 DURING 100-HOUR INSPECTION, FOUND RUDDER PEDAL TUBE MOUNTING BLOCKS FLEXING UP AND DOWN WHEN PRESSURE WAS APPLIED TO PED ALS. FURTHER INSPECTION OF THE PROBLEM REVEALED CRACKS IN THE LOWER BULKHEADS (172RG PART CATALOG, FIGURE 19, INDEX 16 AND INDEX 20) BELOW THE INBOARD RUDDER PEDAL TUBE MOUNTING BLOCKS ON BOTH THE PILOT AND COPILOT SIDE. SUSPECT CAUSE IS INSUFFICIENT MATERIAL THICKNESS OF BULKHEAD OR BEARING SURFACE UNDER MOUNTING BLOCK BOLT, NUT. RECOMMEND INSPECTION OF BULKHEAD FOR CRACKS. 1 H 7 1 3O 3A17 1996041800179 19960418 00179 CE 1996 4 18 96ZZZX1798 1 19960310 G 5312 24130014 BULKHEAD CESSNA 172 172RG 2072438 CE LOWER FUSELAGE CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 15 9303D 3995 172RG1113 DURING 100-HOUR INSPECTION, FOUND RUDDER PEDAL TUBE MOUNTING BLOCKS FLEXING UP AND DOWN WHEN PRESSURE WAS APPLIED TO PED ALS. FURTHER INSPECTION OF THE PROBLEM REVEALED CRACKS IN THE LOWER BULKHEADS (172RG PART CATALOG, FIGURE 19, INDEX 16 AND INDEX 20) BELOW THE INBOARD RUDDER PEDAL TUBE MOUNTING BLOCKS ON BOTH THE PILOT AND COPILOT SIDE. SUSPECT CAUSE IS INSUFFICIENT MATERIAL THICKNESS OF BULKHEAD OR BEARING SURFACE UNDER MOUNTING BLOCK BOLT, NUT. RECOMMEND INSPECTION OF BULKHEAD FOR CRACKS. 1 H 7 1 3O 3A17 1996041800180 19960418 00180 CE 1996 4 18 96ZZZX1799 1 19960310 G 5312 24130013 BULKHEAD CESSNA 172 172RG 2072438 CE LOWER FUSELAGE CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 15 9561B 5666 172RG0881 DURING 100-HOUR INSPECTION, FOUND RUDDER PEDAL TUBE MOUNTING BLOCKS FLEXING UP AND DOWN WHEN PRESSURE WAS APPLIED TO PED ALS. FURTHER INSPECTION OF THE PROBLEM REVEALED CRACKS IN THE LOWER BULKHEADS (172RG PART CATALOG, FIGURE 19, INDEX 16 AND INDEX 20) BELOW THE INBOARD RUDDER PEDAL TUBE MOUNTING BLOCKS ON BOTH THE PILOT AND COPILOT SIDE. SUSPECT CAUSE IS INSUFFICIENT MATERIAL THICKNESS OF BULKHEAD OR BEARING SURFACE UNDER MOUNTING BLOCK BOLT, NUT. RECOMMEND INSPECTION OF BULKHEAD FOR CRACKS. 1 H 7 1 3O 3A17 1996041800181 19960418 00181 CE 1996 4 18 96ZZZX1800 1 19960310 G 5312 241300112 BULKHEAD CESSNA 172 172RG 2072438 CE LOWER FUSELAGE CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 15 9561B 5666 172RG0881 DURING 100-HOUR INSPECTION, FOUND RUDDER PEDAL TUBE MOUNTING BLOCKS FLEXING UP AND DOWN WHEN PRESSURE WAS APPLIED TO PED ALS. FURTHER INSPECTION OF THE PROBLEM REVEALED CRACKS IN THE LOWER BULKHEADS (172RG PART CATALOG, FIGURE 19, INDEX 16 AND INDEX 20) BELOW THE INBOARD RUDDER PEDAL TUBE MOUNTING BLOCKS ON BOTH THE PILOT AND COPILOT SIDE. SUSPECT CAUSE IS INSUFFICIENT MATERIAL THICKNESS OF BULKHEAD OR BEARING SURFACE UNDER MOUNTING BLOCK BOLT, NUT. RECOMMEND INSPECTION OF BULKHEAD FOR CRACKS. 1 H 7 1 3O 3A17 1996041800182 19960418 00182 CE 1996 4 18 96ZZZX1801 1 19960205 G 3230 EPG185 BRUSH SET PRESTOLITE 105932B BEECH 23 B24R 1151253 CE GEAR MOTOR WORN D A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 GL 17 93485 2723 MC350 AFTER TAKEOFF, GEAR SELECTOR MOVED TO RETRACT POSTION. GEAR DOWN (GREEN) INDICATORS TURNED OFF, BUT MALFUNCTION (RED) I NDICATOR ILLUMINATED. ACFT RETURNED. GEAR SELECTOR MOVED TO DOWN POSITION. MALFUNCTION (RED) INDICATOR STILL ILLUMINA TED AND GEAR FAILED TO EXTEND. C/B'S CHECKED AND CYCLED, GEAR SELECTOR RECYCLED, STILL GEAR FAILED TO EXTEND. L/G EXTE NDED USING EMERG GEAR EXT PROCEDURES. UPON INSP OF L/G SYS, LANDING GEAR PUMP MOTOR REMOVED. BOTH OF THE MOTOR'S BRUSH ES FND WORN. BRUSHES REPLACED AND COMMUTATOR POLISHED. REINSTALLED IN ACFT AND CYCLED WITH NO FURTHER PROBLEMS. BEECH CRAFT SM, PN 169-590015G, REISSUED: 11-30-79, HAS NO LISTING FOR BRUSH WEAR OR INSP/OH OF GEAR PUMP ASSY. 1 L 7 1 3O A1CE 1996041800183 19960418 00183 GL 1996 4 18 96ZZZX1802 2 19960214 G 7200 ENGINE BELL 206 206L 1181522 SW ALLSN 250C 250C20B 03013 GL CHIP PLUG MAKING METAL B LX5R K NONE J WARNING INDICATION IN INSP/MAINT 1 GL 19 781LL 45079 CAE830497 HEAVY METAL CONTAMINATION ON UPPER AND LOWER CHIP PLUGS. METAL FOUND IN NICAD EXTERNAL OIL FILTER ALSO. ALL CONTAMINAT ION WAS FERROUS METAL. 1 G 7 1 3U 3 U H2SW E4CE 1996041800185 19960418 00185 EU 1996 4 18 96ZZZX1804 1 19960312 G 6220 350A31183107 FLANGE 31190703 SNIAS 350 AS350B2 8680813 EU M/R STARFLEX LOOSE BUSHING D S A K NONE O OTHER IN INSP/MAINT 1 WP 07 6095U 800 M1973 2699 UPON REMOVAL OF RED AND YELLOW STAR-FLEX ASSEMBLY, ONE BUSHING WAS FOUND UNSCREWED FROM THE UPPER ARM. THE CAUSE MAY BE EITHER A POOR BOND OF BUSHING TO STAR-FLEX ARM OR A POOR CLEANING OF BOLT PRIOR TO USE OF NEW MASTONOX AT LAST BEARING CHANGE. SUBMITTER STATED TO ALWAYS CLEAN AND INSPECT PARTS PRIOR TO RE-USE. 1 G 7 1 3U H9EU 1996041800240 19960418 00240 SW 1996 4 18 96ZZZX1805 1 19960327 G 5400 214031202101 BEAM BELL 214 214ST 1182106 SW WL 65 CRACKED B S ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 391AL 28103 THE RT PYLON SUPPORT IS CRACKED 14.50 INCHES FROM THE FORWARD TRANSMISSION ISLAND AFT. THE CRACK WAS DISCOVERED DURING REPLACEMENT OF THE RT CYCLIC SERVO. THE FOLLOWING COMPONENTS OF THE PYLON STRUCTURE WERE CRACKED: BEAM (W.O. 65.00). P YLON SUPPORT ASSY, RT. BULKHEAD (STA 227.10). 2 G 7 2 4U H10SW 1996041800241 19960418 00241 SW 1996 4 18 96ZZZX1806 1 19960327 G 5400 214031810108 PYLON SUPPORT BELL 214 214ST 1182106 SW PYLON RT CRACKED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 391AL 28103 THE RT PYLON SUPPORT IS CRACKED 14.50 INCHES FROM THE FORWARD TRANSMISSION ISLAND AFT. THE CRACK WAS DISCOVERED DURING REPLACEMENT OF THE RT CYCLIC SERVO. THE FOLLOWING COMPONENTS OF THE PYLON STRUCTURE WERE CRACKED: BEAM (W.O. 65.00). P YLON SUPPORT ASSY, RT. BULKHEAD (STA 227.10). 2 G 7 2 4U H10SW 1996041800242 19960418 00242 SW 1996 4 18 96ZZZX1807 1 19960327 G 5412 214031208109 BULKHEAD BELL 214 214ST 1182106 SW FS 227.10 CRACKED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 391AL 28103 THE RT PYLON SUPPORT IS CRACKED 14.50 INCHES FROM THE FORWARD TRANSMISSION ISLAND AFT. THE CRACK WAS DISCOVERED DURING REPLACEMENT OF THE RT CYCLIC SERVO. THE FOLLOWING COMPONENTS OF THE PYLON STRUCTURE WERE CRACKED: BEAM (W.O. 65.00). P YLON SUPPORT ASSY, RT. BULKHEAD (STA 227.10). 2 G 7 2 4U H10SW 1996041800243 19960418 00243 EU 1996 4 18 96ZZZX1808 1 19960408 G 6220 350A37124420 BOLT AEROSP AS355 AS355F1 8680810 EU M/R STARFLEX BROKEN B S A ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 376E 1719 5213 FOUR BOLTS THAT SECURE THE MAIN ROTOR STARFLEX TO THE MAIN ROTOR MAST WERE FOUND BROKEN DURING TROUBLESHOOTING OF AN OUT -OF-BALANCE CONDITION WITH THE MAIN ROTOR SYSTEM. THERE ARE A TOTAL OF 12 BOLTS IN THE SYSTEM. AN ADDITIONAL 3 BOLTS F AILED WHEN THE SYSTEM WAS BEING DISASEMBLED. ALL OF THE BOLTS IN THE MAST WERE FOUND SEVERELY CORRODED. 1 G 7 2 3U H11EU 1996041800244 19960418 00244 EU 1996 4 18 96ZZZX1809 1 19960408 G 6220 350A37124520 BOLT AEROSP AS355 AS355F1 8680810 EU M/R STARFLEX BROKEN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 376E 1719 5213 FOUR BOLTS THAT SECURE THE MAIN ROTOR STARFLEX TO THE MAIN ROTOR MAST WERE FOUND BROKEN DURING TROUBLESHOOTING OF AN OUT -OF-BALANCE CONDITION WITH THE MAIN ROTOR SYSTEM. THERE ARE A TOTAL OF 12 BOLTS IN THE SYSTEM. AN ADDITIONAL 3 BOLTS F AILED WHEN THE SYSTEM WAS BEING DISASEMBLED. ALL OF THE BOLTS IN THE MAST WERE FOUND SEVERELY CORRODED. 1 G 7 2 3U H11EU 1996041800247 19960418 00247 SW 1996 4 18 96ZZZX1812 1 19960226 G 6230 206340101101 SEAL 206040014105 BELL 206 206L1 1182107 SW MAST PLATE LEAK B ALGR K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 1084Y 27 45433 SEAL WAS FOUND LEAKING BY MAINTENANCE. NEW STYLE SEAL, PN 206-340-101-101, WAS LEAKING. 1 G 7 1 3U H2SW 1996041800248 19960418 00248 SW 1996 4 18 96ZZZX1813 1 19960206 G 6230 206040576105 BEARING BELL 206 206L4 1182110 SW MAST PITTED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 171AL 2954 MB207 52064 FOUND AT 3,000-HOUR OVERHAUL, MAST BEARING OUTER RACE THRUST AREA HAS PITTED AREA - SCRAPPED BEARING. 1 G 7 1 3U NC H2SW 1996041800251 19960418 00251 EU 1996 4 18 96ZZZX1816 1 19960209 G 6730 D133768II ACTUATOR 10545023 BOLKMS 105 BO105C 5626005 EU SERVO DRAIN CONTAMINATED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 90761 9254 27 0916 S160 DURING BENCH TEST OF ACTUATOR, SERVO VALVE DRAIN CHAMBER SCREW PLUG, PN EE3-2042, REMOVED TO CHECK FOR OIL LEAKAGE. DRA IN CHAMBER ABOVE SERVO VALVE AND INSIDE OF SCREW PLUG FOUND FULL OF A HEAVY, GREASE-LIKE CONTAMINATION. SUSPSECT FORMED FOR WATER AND OIL COLLECTING IN CHAMBER FOR A LONG PERIOD OF TIME. 1 G 7 2 3U H3EU 1996041800252 19960418 00252 NE 1996 4 18 96ZZZX1817 1 19960219 G 2930 07113111321 PRESSURE SWITCH 0711311104 SKRSKY S76 S76A 8143006 NE SYSTEM 2 STUCK B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 476AL 1605 1514 760003 IN SHOP. BENCH TEST OF MODULE PERFORMED DUE TO REPORTED DROP OF HYDRAULIC PRESSURE TO ZERO P.S.I. IN SYSTEM 2. ALL TES T RESULTS WERE WITHIN LIMITS EXCEPT PRESSURE SWITCH TEST. ONE-HALF OF SWITCH STUCK ON HIGH PRESSURE SIDE. (FAILURE OF SWITCH NOT RELATED TO ZERO P.S.I. REPORT). 1 G 7 2 3U H1NE 1996041800253 19960418 00253 NE 1996 4 18 96ZZZX1818 1 19960226 G 5530 7620120049101 BULKHEAD SKRSKY S76 S76A 8143006 NE VERTICAL PYLON CORRODED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 1547N 11732 760088 MAJOR INSPECTION FOUND FORWARD CANTED BULKHEAD WITH INTERGRANULAR CORROSION. BULKHEAD WAS REPLACED. 1 G 7 2 3U H1NE 1996041800254 19960418 00254 NE 1996 4 18 96ZZZX1819 1 19960226 G 5531 7620205001106 RIB SKRSKY S76 S76A 8143006 NE VERTICAL PYLON CORRODED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 1547N 11732 760088 MAJOR INSPECTION FOUND VERTICAL STABILIZER RIB WITH INTERGRANULAR CORROSION. RIB WAS REPLACED. 1 G 7 2 3U H1NE 1996041800255 19960418 00255 NE 1996 4 18 96ZZZX1820 1 19960226 G 5531 7620105001107 SPAR WEB SKRSKY S76 S76A 8143006 NE VERTICAL STAB CORRODED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 1547N 11732 760088 MAJOR INSPECTION FOUND VERTICAL STABILIZER SPAR WEB DOUBLER WITH INTERGRANULAR CORROSION. DOUBLER WAS REPLACED. 1 G 7 2 3U H1NE 1996041800256 19960418 00256 NE 1996 4 18 96ZZZX1821 1 19960226 G 5530 7620205002109 SUPORT SKRSKY S76 S76A 8143006 NE VERTICAL STAB CORRODED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 1547N 11732 760088 MAJOR INSPECTION FOUND VERTICAL STABILIZER SUPPORT, AFT LOWER, CORRODED. SUPPORT WAS REPLACED. 1 G 7 2 3U H1NE 1996041800257 19960418 00257 NE 1996 4 18 96ZZZX1822 1 19960226 G 2612 473205 DETECTOR SKRSKY S76 S76A 8143006 NE NR 1 ENGINE MALFUNCTION B ALGR O OTHER N FALSE WARNING CR CRUISE 1 SW 03 768AL 0563 760031 DURING LEVEL FLIGHT, NR 1 ENGINE FIRE T-HANDLE ILLUMINATED. PERFORMED TIGHT TURN, LOOKING FOR INDICATION OF SMOKE. NOT ED NO SMOKE, ALL ENGINE INDICATIONS WERE NORMAL. DURING TROUBLESHOOTING, FOUND ENGINE NR 1 FLAME DETECTOR BAD. REPLACE D FLAME DETECTOR. OPS CHECKED GOOD. 1 G 7 2 3U H1NE 1996041800259 19960418 00259 GL 1996 4 18 96ZZZX1824 2 19960302 G 7210 23039793 SCAVENGE BODY 23035179 SKRSKY S76 S76 8143010 NE ALLSN 250C 250C30S 03013 GL SCAVENGE TUBE WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 701AL 1833 760238 890772S UPON DISASSEMBLY OF GEARBOX, REMOVED OIL PUMP ASSY. VISUALLY INSPECTED, SHOWED WEAR AT SCAVENGE BODY SURFACE, AND IN TH E TUBE BONE. SCAVENGE TUBE WORN IN SCAVENGE BODY. SUSPECT CAUSE IS DUE TO IMPROPER FIT OR ALIGNMENT BRACKETS. 1 G 7 2 3U 3 U H1NE E1GL 1996041800260 19960418 00260 SW 1996 4 18 96ZZZX1825 1 19960301 G 5511 222035401101 WEIGHT BELL 230 230 1182149 SW STABILIZER END LOOSE B SL3R K NONE O OTHER NR NOT REPORTED 1 NE 01 230TX 540 23014 SCREW WHICH HOLDS STABILIZER END WEIGHT BROKE. WEIGHT PIVOTED ON REMAINING ATTACH SCREW DURING FLIGHT, THIS MOVEMENT CA USED WEIGHT TO DEFORM. NO DAMAGE TO SURROUNDING STRUCTURE OCCURRED. NEW WEIGHT AND ATTACH SCREW, PN MS27039-1-13, INST ALLED. 1 G 7 2 3U NC H9SW 1996041800261 19960418 00261 SW 1996 4 18 96ZZZX1826 1 19960322 G 2910 MS21910D6 TEE FITTING BELL 230 230 1182149 SW HYDRAULIC SYSTEM CRACKED B SL3R K NONE K FLUID LOSS IN INSP/MAINT 1 NE 01 230TX 559 23014 HYDRAULIC TEE FITTING ON FUSELAGE UPPER DECK SEEPING HYDRAULIC OIL (SYSTEM NR 1). TEE FITTING FOUND CRACKED, INSTALLED NEW TEE FITTING OF HIGHER STRENGTH PER BHT. 1 G 7 2 3U NC H9SW 1996041800267 19960418 00267 GL 1996 4 18 96ZZZX1832 2 19960320 G 7323 23057869 GOVERNOR HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL ENGINE ERRATIC B EOOR K NONE O OTHER IN INSP/MAINT 1 AL 03 5074R 916 28419 1151D CAE832750 THIS IS THE SECOND TIME THIS UNIT HAS BEEN REMOVED FOR ERRATIC CONDITION. PILOT MUST MAKE CONSTANT ADJUSTMENTS TO THE G OVERNOR 'BEEP' WITH EVERY POWER CHANGE. 1 G 7 1 3U 3 U H3WE E4CE 1996042500286 19960425 00286 CE 1996 4 25 96ZZZX1933 1 19960305 G 2720 R365240795 CONTROL CABLE BEECH 36 A36 1151604 CE RT RUDDER BROKE B A FV1R K NONE W INADEQUATE Q C IN INSP/MAINT 1 EA 11 999PL E2577 RIGHT RUDDER CABLE BROKE IN TAIL SECTION AT THE LAST PULLEY. APPARENTLY, THE CABLE HAD BEEN ROUTED INCORRECTLY FROM THE FACTORY. THE ROUTING OF THIS CABLE AT THE PULLEY IS VERY DIFFICULT TO SEE UNDER NORMAL INSPECTION CONDITIONS. THERE W AS NEVER ANY CONTROL PROBLEM OF THE ELEVATOR. THIS WAS FOUND DURING A PRE-FLIGHT. SPECIAL INSPECTION SHOULD BE DEVELOP ED FOR THIS PULLEY. 1 L 7 1 3O 3A15 1996042500287 19960425 00287 SO 1996 4 25 96ZZZX1934 1 19960312 G 6123 A856 MUSHROOM PIPER PA23 PA23160 7102304 SO HARTZL HC82V HC82V* GL PROPELLER CRACKED B P UCXR K NONE O OTHER IN INSP/MAINT 1 SW 15 76HK 11863 5920 231423 334R THE PART THAT IS DEFECTIVE INSIDE OF THE PROPELLER IS CALLED THE MUSHROOM, PN A856. WHILE DISASSEMBLING THE FEATHER SPR ING KIT DURING IRAN (INSPECT, REPAIR AS NECESSARY) INSPECTION, THE MUSHROOM WAS FOUND BROKEN. WHILE PERFORMING A DYE-PE NETRANT INSPECTION ON THE SAME PART OF THE OTHER PROPELLER, FOUND IT, TOO, WAS CRACKED. 1 L 7 2 3O 1A10 5 C P23EA 1996042500288 19960425 00288 SO 1996 4 25 96ZZZX1935 1 19960312 G 6123 A856 MUSHROOM PIPER PA23 PA23160 7102304 SO HARTZL HC82V HC82V* GL PROPELLER CRACKED B P UCXR K NONE O OTHER IN INSP/MAINT 1 SW 15 76HK 11863 5920 231423 K1596 BOTH PROPELLERS HAVE APPROXIMATELY 11,863 TOTAL HOURS SINCE NEW AND 5,920.1 HOURS SINCE OVERHAUL. HOWEVER, BOTH PROPELL ERS HAVE HAD ROUTINE INTERNAL CORROSION INSPECTIONS OR IRAN INSPECTIONS (INSPECT, REPAIR AS NECESSARY) APPROXIMATELY EVE RY 2 YEARS AND/OR 2,000 HOURS. 1 L 7 2 3O 1A10 5 C P23EA 1996042500289 19960425 00289 SO 1996 4 25 96ZZZX1936 1 19960321 G 3250 751501 COLLAR PIPER PA23 PA23250 7102308 SO STEERING LIMIT BROKEN D K NONE O OTHER IN INSP/MAINT 1 GL 15 204RD 273994 WHILE TROUBLESHOOTING COLLAR NLG SHIMMY PROBLEM, MECHANIC NOTICED THE AFT SHIMMY COLLAR TAB, WHICH LIMITS NLG STEERING, WAS BROKEN OFF. SUSPECT CAUSE WAS EXCEEDING LIMITS WHILE TOWING AIRCRAFT. 1 L 7 2 3O 1A10 1996042500291 19960425 00291 CE 1996 4 25 96ZZZX1938 1 19960321 G 3260 S13771 SWITCH CESSNA 210 T210L 2073449 CE RT DOWNLOCK INOPERATIVE B CS3R O OTHER P NO WARNING INDICATION NR NOT REPORTED 1 WP 17 51TP 21060598 PILOT REPORTED NO DOWN AND LOCK INDICATION. TROUBLESHOT SYSTEM, AND FOUND THE RT MLG DOWNLOCK SWITCH INOPERATIVE. REPL ACED SWITCH, OPS CHECKED OK. 1 H 7 1 3O 3A21 1996042500292 19960425 00292 CE 1996 4 25 96ZZZX1939 1 19960226 G 3230 52130285 BRACKET CESSNA 421 421B 2076014 CE LT NLG BRACE BROKEN D K NONE O OTHER IN INSP/MAINT 1 NE 03 5414J 2366 421B0873 DURING REMOVAL OF OXYGEN BOTTLE FOR HYDROSTATIC TEST, MECHANIC FOUND THE NOSE GEAR LT DRAG BRACE SUPPORT BRACKET BROKEN. AFTER FURTHER INSPECTION, NO OTHER DAMAGE FOUND. ALSO, THERE WERE SEVERAL FLAT SPOTS ON NOSE TIRE. SUBMITTER SUSPECT S THIS HAPPENED DURING HARD NOSE LANDING OR TURNING WHEN GOING TOO FAST. INSPECTION REVEALED NO DEFECTS ON THE RIGHT DR AG BRACE SUPPORT BRACKET. 1 L 7 2 3O A7CE 1996042500293 19960425 00293 CE 1996 4 25 96ZZZX1940 1 19960322 G 5712 RIB CESSNA 421 421B 2076014 CE WING CRACKED D K NONE O OTHER IN INSP/MAINT 1 CE 07 53685 5112 421B0918 TWO CRACKS IN WING RIB AT MLG SIDE BRACE ATTACHMENT AREA WHERE UPLOCK PUSH/PULL TUBE GOES THROUGH RIB. CESSNA SB ME76-2 ADDRESSES THIS PROBLEM. 1 L 7 2 3O A7CE 1996042500296 19960425 00296 CE 1996 4 25 96ZZZX1943 1 19960318 G 7714 A6532 TACH GENERATOR CESSNA 421 421C 2076016 CE ENGINE BRUSH WEAR B YXRR K NONE O OTHER IN INSP/MAINT 1 WP 07 781TC H9414 421C0083 TACHOMETER GENERATOR INTERNAL GEARS ARE WEARING PREMATURELY CAUSING BRUSHES TO FAIL. NEW REPLACEMENT PART FROM SHELF AV ERAGED LESS THAN 100 HOURS TIS, BEFORE FAILURE. 1 L 7 2 3O A7CE 1996042500297 19960425 00297 SO 1996 4 25 96ZZZX1944 1 19960321 G 3250 3227406 TORQUE TUBE PIPER PA23 PA23250 7102308 SO NLG STEERING CRACKED D K NONE O OTHER IN INSP/MAINT 1 GL 15 6881Y 274230 WHILE INSPECTING NLG AREA, MECHANIC NOTICED STEERING TORQUE TUBE ASSY WAS CRACKED WHERE TUBE FOR TAXI LIGHT CONNECTION I S MADE. FURTHER INVESTIGATION FOUND EXCESSIVE FORCE WAS APPLIED WHILE STEERING. SUBMITTER SUGGESTS CAUSE OF CRACK COUL D BE FROM EXCEEDING STEERING LIMITS WHILE TOWING AIRCRAFT. 1 L 7 2 3O 1A10 1996042500298 19960425 00298 EU 1996 4 25 96ZZZX1945 1 19960401 G 5280 BRACKET SOCATA TBM TBM700 8682000 EU RT MLG DR HINGE FAILED B S A RL8R A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 GL 15 292RG 750 014 RIGHT MAIN GEAR DOOR LIGHT DID NOT EXTINGUISH AFTER TAKEOFF RETRACTION, GEAR WAS CYCLED DOWN, NO GEAR SAFE-LIGHT ON RT M AIN. FLY-BY INSPECTION VERIFIED GEAR (RT) NOT EXTENDING. GEAR-UP LANDING HAD TO BE MADE. AT RECOVERY OF AIRCRAFT FROM RUNWAY, RT FORWARD GEAR INBOARD DOOR HINGE BRACKET WAS FOUND BROKEN AND DOOR LOCKED IN WELL. PASSENGERS OK. SUBMITTER RECOMMENDED AD TO IMPROVE INBOARD DOORS IAW SB 70-073-32 IMMEDIATELY. 1 L 7 1 3T RT A60EU 1996042500299 19960425 00299 CE 1996 4 25 96ZZZX1946 1 19960214 G 2910 651710552 LINE CESSNA 500 S550 2076607 CE MLG RETRACT CHAFED B A EBVR K NONE O OTHER IN INSP/MAINT 1 GL 09 204A 2477 S5500008 DURING ACCOMPLISHMENT OF A PHASE INSPECTION, THE LANDING GEAR HYDRAULIC RETRACT LINE WAS FOUND CHAFING ON TWO NUT CLIPS LOCATED ON THE COPILOT'S INBOARD SEAT TRACK, FORWARD END. THE DEFECT TO THE LINE WAS SUCH THAT THE LINE HAD TO BE REPLA CED. SUBMITTER STATED THIS IS THE SECOND AIRCRAFT IN RECENT MONTHS FOUND WITH THIS PROBLEM. THE FIRST WAS A MODEL CE-5 60. RECOMMEND THIS LINE BE INSPECTED ON S550 AND 560 AIRCRAFT AT FIRST OPPORTUNITY AND REPOSITION OR PROTECT THE LINE A S NECESSARY. 1 L 7 2 4F RT A22CE 1996042500300 19960425 00300 NE 1996 4 25 96ZZZX1947 2 19960408 G 7200 ENGINE CNDAIR CL600 CL6002B16 1900305 EA GE CF34 CF343A 30015 NE NR 1 FAILED B VU2R E A ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 GL 05 4PG 2734 5052 350341 LOW OIL PRESSURE LIGHT CAME ON IN CRUISE FLIGHT. ENGINE SECURED AND LANDED AT IND. INVESTIGATION DISCLOSED INTERNAL FA ILURE. ENGINE REPLACED. INSPECTION/INVESTIGATION REPORT TO FOLLOW. 2 L 7 2 4F 4 F RT A21EA E15NE 1996042500301 19960425 00301 EU 1996 4 25 96ZZZX1948 1 19960401 G 2450 LDA150A8C CONTACTOR BRAERO DH125 BAE125800A 1500285 EU BUS TIE TRIPS BREAKER H K NONE O OTHER IN INSP/MAINT 1 EA 21 60PM 30 1251 NA0453 AFTER REPLACING BUS TIE CONTACTOR ON 2-26-96 FOR INTERMITTENT POPPING OF CIRCUIT BREAKER REPLACEMENT, UNIT STARTED RANDO MLY OPENING FOR NO REASON. REPLACED AFTER 30 HOURS OF SERVICE. 2 L 7 2 4F RT A3EU 1996042500302 19960425 00302 CE 1996 4 25 96ZZZX1949 1 19960325 G 2760 20544470 FILTER CESSNA 650 650 2076802 CE LT WING SPOILER FAILED B GJQR K NONE O OTHER IN INSP/MAINT 1 NM 01 39WP 5517 6500039 DURING MAINTENANCE INSPECTION OPERATION 10, ITEM CARD 27-20 INSPECTION REVEALED FILTER SEPARATED FROM MOUNTING FLANGE IN THE END OF ELBOW FITTING PERMITTING IT TO SLIDE BACK AND FORTH WITHIN THE FITTING. THIS NEGATES FILTERING. REPLACED E LBOW FILTER FITTING. SUBMITTER STATED IT APPEARS TO BE POOR DESIGN. THIS IS THE 2ND FITTING FOUND FAILED IN A 6-MONTH PERIOD AND 323 FLIGHT HOURS. (LT WING.) 2 L 7 2 4F A9NM 1996042500303 19960425 00303 CE 1996 4 25 96ZZZX1950 1 19960328 G 5610 55112854 WINDOW CESSNA 501 501 2076603 CE COPILOT SIDE CRACKED B KJ4R O OTHER O OTHER CR CRUISE 1 SO 15 99CK 320 5010153 IN FLIGHT, PILOT HEARD A LOUD NOISE, THEN NOTICED THE RT COCKPIT WINDOW CRACKED ACROSS THE TOP FORWARD TO AFT. UPON REM OVAL, FOUND WINDOW HAD COMPLETELY SEPARATED. THIS WINDOW HAD ONLY BEEN INSTALLED LESS THAN 2 YEARS. IT APPEARED ONE RE TAINER BOLT WAS HARD AGAINST THE MOUNTING HOLE IN THE WINDOW. THIS AIRCRAFT HAD JUST RECENTLY HAD A PHASE INSPECTION TH AT INCLUDED AN INSPECTION OF THIS WINDOW. 1 L 7 2 4F A27CE 1996042500304 19960425 00304 SW 1996 4 25 96ZZZX1951 1 19960321 G 2150 5903828 SEAL SUNDSTRANDEM 736778 GULSTM 690TP 690C 7630517 SW ACM FAILED B BOER H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 GL 19 600BM 1076 0113 11734 AT 18,000 FEET, PILOT SMELLED SMOKE. CABIN TEMP WENT FULL HOT. SHUT DOWN ENVIRONMENTAL CONTROL UNIT. WHEN ON GROUND, TROUBLESHOOTING FOUND THE CARBON FACE SEAL OF THE AIR CYCLE MACHINE HAD FAILED ON THE OUTPUT SIDE ALLOWING OIL INTO THE CABIN AIR. 1 H 7 2 3T 2A4 1996042500305 19960425 00305 CE 1996 4 25 96ZZZX1952 1 19960209 G 3260 1003810061 SWITCH BEECH 200 200BEECH 1152920 CE NLG DOWNLOCK DEFECTIVE B LX5R O OTHER N FALSE WARNING AP APPROACH 1 GL 19 971LL BB572 NO NOSE GEAR DOWN AND LOCKED INDICATION AND INTRANSIT LIGHT IN HANDLE REMAINED ON DURING NORMAL EXTENSION. AN EMERGENCY EXTENSION PROVIDED A DOWN AND LOCK LIGHT, BUT INTRANSIT LIGHT STILL REMAINED ON. INSPECTION AFTER LANDING SHOWED NOSE GEAR DOWNLOCK SWITCH DEFECTIVE. REPLACED SWITCH AND PERFORMED FUNCTIONAL CHECK OF SYSTEM AND RETURNED AIRCRAFT TO SERVI CE. 1 L 7 2 4T A24CE 1996042500306 19960425 00306 EU 1996 4 25 96ZZZX1953 2 19960325 G 7310 REGULATOR GULSTM G1159 G1159 3953505 SO RROYCE SPEY SPEY5118 54523 EU ENG FUEL FLOW MALFUNCTIONED B UA9R K NONE O OTHER IN INSP/MAINT 1 EA 17 125JJ 906 B1669R 15 8674 ENGINE WAS INSPECTED FOR SUSPECTED OVERTEMPERATURE PER CREW REPORT. INSPECTION ACCOMPLISHED PER ROLLS ROYCE OVERHAUL MA NUAL. RESULTS SHOWED NO OVERTEMPERATURE EFFECTS. PRIOR TO DISASSEMBLY, NOTED THE P2 TOWER ON THE FUEL FLOW REGULATOR W AS LOOSE. THREE MOUNTING BOLTS HAD PULLED OUT OF THE HOUSING. THE P2 PORT WAS EXPOSED TO ATMOSPHERE, LOSS OF P2 SIGNAL WOULD EFFECT THE ENGINE'S ABILITY TO CORRECTLY METER FUEL. 2 L 7 2 4F 4 F RT A12EA E2EU 1996042500307 19960425 00307 EU 1996 4 25 96ZZZX1954 1 19960216 G 7830 C41B302133 BUCKET ISRAEL 1124 1124 4500102 EU LT ENG T/R CORRODED B EBVR K NONE O OTHER IN INSP/MAINT 1 GL 09 75BC 4498 2015 426 DURING A C-CHECK/4,800 HOUR-INSPECTION, FOUND LEFT ENGINE'S LOWER T/R BUCKET, OUTER SKIN HAD CORRSION HOLES FROM INSIDE OUT IN TWO SEPARATE LOCATIONS. 2 M 7 2 4F A2SW 1996042500308 19960425 00308 SW 1996 4 25 96ZZZX1955 1 19960214 G 7332 99120332 SWITCH WIRE GULSTM 560 560 0141402 SW LYC O540 IGO540B1A 41532 EA LT BOOST PRESS CHAFED B EBVR K NONE J WARNING INDICATION NR NOT REPORTED 1 GL 09 60GL 1152 0187 AIRCRAFT WAS EXPERIENCING PERIODIC UNCOMMANDED LT BOOST PUMP OPERATION WITH LT BOOST PUMP AND LT FUEL LOW PRESSURE ANNUN CIATOR LIGHTS COMING ON. PROBLEM FOUND TO BE CAUSED BY THE LT ENGINE FUEL PRESSURE SWITCH WIRES HAD CHAFED THROUGH AGAI NST THE SHARP EDGE OF THE FUEL FLOW TRANSMITTER. SUBMITTER STATED WIRES SHOULD BE INSPECTED ON THESE AIRCRAFT FOR CHAFE DAMAGE, PROTECT AND REROUTE AS ABLE. 1 H 7 2 3O 3 O 6A1 1E11 1996042500309 19960425 00309 NE 1996 4 25 96ZZZX1956 2 19960216 G 7250 TURBINE CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE ENGINE HPT DAMAGED B EBVR K NONE O OTHER IN INSP/MAINT 1 GL 09 402ST 5814 1362 5500068 PCE70539 AT THE CUSTOMER'S REQUEST, A BORESCOPE INSPECTION OF THE HIGH PRESSURE TURBINE, IMPELLER, AND THE NR 4 BEARING WAS PERFO RMED. THE HIGH PRESSURE TURBINE SHOWED SIGNS OF FOD DAMAGE. REMOVED THE ENGINE'S HOT SECTION AND FOUND THE H.P. TURBIN E DAMAGED. THE DIFFUSER TUBES WORN BEYOND LIMITS. THE DEFLECTOR RING AND SEGMENTS BROKEN WITH MISSING PIECES, ALSO, TH E L.P. TURBINE AND STATOR WERE DAMAGED. SUSPECT MISSING PIECES CAUSED FOD DAMAGE. 1 L 7 2 4F 4 F A22CE E1NE 1996042500310 19960425 00310 SO 1996 4 25 96ZZZX1957 1 19960320 G 4940 103811602 EXCITER GARRTT GTCP366 GULSTM G1159 G1159 3953505 SO APU IGNITION FAILED D K NONE O OTHER IN INSP/MAINT 1 EA 21 57HJ 2738 409247 0194 IGNITION EXCITER WILL NOT PRODUCE OUTPUT VOLTAGE TO PROVIDE APU START. FAILED TO OPERATE. 2 L 7 2 4F RT A12EA 1996042500311 19960425 00311 EA 1996 4 25 96ZZZX1958 1 19960301 G 7920 LINE DHAV DHC3 DHC3 2800202 EA ENG OIL SUPPLY RUPTURED D K NONE O OTHER IN INSP/MAINT 1 NM 01 2634Y 59 AFTER HARD STARTING PROBLEM, ENGINE WAS TURNED BACKWARDS TO CLEAR CYLINDERS. MAIN OIL SUPPLY LINE WAS HYDRAULICED APART AT HOSE AND CLAMP CONNECTION AT CHECK VALVE LOCATED BETWEEN ENGINE AND OIL TANK. SUBMITTER STATES 'DO NOT TURN ENGINE BACKWARDS'. 1 H 7 1 3R A815 1996042500312 19960425 00312 CE 1996 4 25 96ZZZX1959 1 19960313 G 3320 CR511 DIODE CESSNA 441 441 2076020 CE CABIN INFO BURNED D A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS DE DESCENT 1 SO 05 33DE 3640 4410308 PILOT REPORTED DESCENDING THROUGH 12,000 FEET, SMOKE OBSERVED COMING FROM UNDER COPILOT'S INSTRUMENT PANEL. DECLARED AN EMERGENCY, LANDED WITHOUT INCIDENT. FOUND DIODE ACROSS THE 'NO SMOKE' AND 'FASTEN SEAT BELT'. SWITCH WAS OVERHEATED A ND THE CABIN INFO CIRCUIT BREAKER TRIPPED. REPLACED DIODE, RESET BREAKER SYSTEM, OPERATED NORMAL. 1 L 7 2 3T RT A28CE 1996042500313 19960425 00313 SO 1996 4 25 96ZZZX1960 1 19960313 G 2910 1159H201112 GASKET GULSTM G1159 G1159A 3970109 SO HYD PRESS SYS FAILED B RO3R K NONE K FLUID LOSS NR NOT REPORTED 1 CE 03 2MIL 481 DURING NORMAL ENGINE GROUND RUNS PRIOR TO SHUT DOWN, GASKET FAILED. THE GASKET FITS ON THE T-FITTING, PN AN924-12D, WIT H REDUCER, PN AN919-16. THE REDUCER IS CONNECTED TO A LINE WHICH GOES TO THE HYDRAULIC PRESSURE TRANSMITTER FOR THE FLI GHT HYDRAULIC SYSTEM. THE FAILURE OF THE GASKET CAUSED BOTH STATIC CONVERTERS TO BE SATURATED WITH SKYDROL FLUID. BOTH CONVERTERS HAD TO BE REPLACED. CAUSE OF GASKET FAILURE UNKNOWN. SUBMITTER RECOMMENDS A COVER BE PLACED OVER THE CONVE RTERS TO PREVENT SKYDROL FLUID FROM COMING IN CONTACT IF THE GASKET WERE TO FAIL IN-FLIGHT. THIS WOULD PREVENT AN ELECT RICAL FAILURE AND POSSIBLY A FIRE IN-FLIGHT. 2 L 7 2 4F A12EA 1996042500314 19960425 00314 EA 1996 4 25 96ZZZX1961 2 19960301 G 7250 3027301 BLADE 3028821 BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA CT WHEEL ERODED B CWBR K NONE O OTHER IN INSP/MAINT 1 GL 05 6739P 993 2F642 BB628 PCE81899 BORESCOPE INSPECTION FOUND EVIDENCE OF COATING LOSS FROM COMPRESSOR TURBINE BLADES. COATING WAS ERODED FROM LEADING EDG ES OF SOME BLADES. ENGINE WAS SPLIT AT 'C' FLANGE, HOT SECTION INSPECTED FURTHER. CT WHEEL REMOVED AND SHIPPED TO PRAT T AND WHITNEY FOR INSPECTION AND DETERMINATION OF CAUSE FOR COATING LOSS. CT BLADES WERE INSTALLED AT OVERHAUL IN SERVI CEABLE CONDITION. THESE BLADES WILL NOT BE REINSTALLED IN THIS ENGINE. 1 L 7 2 4T 4 T A24CE E4EA 1996042500315 19960425 00315 CE 1996 4 25 96ZZZX1962 1 19960401 G 7711 PG12A9 TRANSDUCERS HONEYWELL RKWELL NA265 NA26540 6402608 CE ENGINE EPR ERRATIC D K NONE O OTHER IN INSP/MAINT 1 SO 16 308NT K0136 282090 TRANSDUCER WAS INSTALLED IN AIRCRAFT, TESTED DURING GROUND RUN, AND REMOVED WITH ZERO HOURS TIME IN SERVICE SINCE OVERHA UL. E.P.R. READINGS WERE ERRATIC IN ALL POWER RANGES. UNIT WAS OVERHAULED BY REPAIR STATION ON 3-17-96. SUBMITTER STA TED RELIABILITY OF OVERHAULED AND REPAIRED TRANSDUCERS HAS BEEN POOR. AIRCRAFT TOTAL TIME: 8,602.8 HRS. 2 L 7 2 4J A2WE 1996042500316 19960425 00316 CE 1996 4 25 96ZZZX1963 1 19960301 G 2150 206SZZC BEARING FAFNIR BEECH 200 B200 1152922 CE AC DRV SHAFT FAILED D K NONE O OTHER IN INSP/MAINT 1 NM 11 8093W 249 BB1396 AIR CONDITIONING DRIVE PULLEY SUPPORT BEARING ON FORWARD END FAILED AND CAUSED THE QUILL SHAFT TO SHEAR. SUBMITTER STAT ED THIS IS THE FOURTH SUCH FAILURE IN 1,390 HOURS OF AIRCRAFT OPERATION. BEECHCRAFT RECOMMENDS THE QUILL SHAFT BE LUBED AT 600 HOURS AND THE BEARINGS BE INSPECTED. 1 L 7 2 4T A24CE 1996042500317 19960425 00317 CE 1996 4 25 96ZZZX1964 1 19960325 G 2822 2017002 PUMP TRW RKWELL NA265 NA26540 6402608 CE FUEL BOOST FAILED D K NONE O OTHER IN INSP/MAINT 1 SO 16 311NT 195 1001263D 282019 PUMP WAS REMOVED AND REPLACED DUE TO AFTER SEVERAL MINUTES OF OPERATION, PUMP BECAME EXTREMELY NOISY AND ROUGH INDICATIN G A POSSIBLE IMPENDING FAILURE. TIME IN SERVICE AT TIME OF REMOVAL (T.S.M.O.N.): 195.4 HOURS. PUMP WAS OVERHAULED 10- 2-95. SUBMITTER STATED THESE PUMPS ARE A 2,000 HOUR TIME-CHANGE ITEM, AND LOW-TIME FAILURES SUCH AS THIS HAVE OCCURRED IN FLEET OF 17 AIRCRAFT. AIRCRAFT TT: 13,406.0 HRS. 2 L 7 2 4J A2WE 1996042500318 19960425 00318 CE 1996 4 25 96ZZZX1965 1 19960318 G 7120 95910005 MOUNT BEECH 95 95 1153402 CE TOP RT ATTACH CRACKED B A14R K NONE O OTHER IN INSP/MAINT 1 GL 13 MAIN DYNA FOCAL ATTACH RING TUBE AT TIME OF INSPECTION WAS FOUND TO HAVE CRACKS AT TOP RT ATTACH POINT AND AFT OF ATTACH PLATE APPROXIMATELY .75 INCH AND .50 INCH LONG. THIS MOUNT WAS TAGGED UNSERVICEABLE, RED TAG. REPLACEMENT OF UNIT WAS SUGGESTED. 1 L 7 2 3O 3A16 1996042500319 19960425 00319 CE 1996 4 25 96ZZZX1966 1 19960328 G 3060 4E30971 BRUSH BLOCK BEECH 1900 1900 1154160 CE PROPELLER ARCING D K NONE O OTHER IN INSP/MAINT 1 GL 13 ARCING BETWEEN PROPELLER DEICE BRUSHES CAUSED DAMAGE BEYOND REPAIR. 2 L 7 2 4T RT A24CE 1996042500320 19960425 00320 EU 1996 4 25 96ZZZX1967 1 19960409 G 3241 40921 TRANSDUCER ISRAEL 1124 1124 4500102 EU ANTISKID CORRODED B JGVR K NONE O OTHER IN INSP/MAINT 1 CE 09 24SR 6072 406 332 TRANSDUCER IS CORRODED (SEVERELY PITTED). THIS CORROSION APPEARS TO START AT THE ETCHING USED TO INSTALL PART NUMBER OR SERIAL NUMBER. THE CORROSION NORMALLY SPREADS ONTO CONNECTOR PLUG AND TENDS TO TRANSFER ONTO AXLE, CORRODING IT. S/N 406 AND S/N 431. 2 M 7 2 4F A2SW 1996042500321 19960425 00321 SW 1996 4 25 96ZZZX1968 1 19960311 G 7120 20606210114 MOUNT BELL 206 206B3 1181506 SW ENGINE BROKEN B A PN5R K NONE O OTHER IN INSP/MAINT 1 NM 03 3186N 5036 3805 PREFLIGHT INSPECTION, MECHANIC FOUND ENGINE LOOSE. FURTHER INVESTIGATION REVEALED FORWARD RT MOUNT SEVERELY CORRODED AN D BROKEN IN HALF. CORROSION AND BREAK WAS CONCEALED BY CLAMSHELL DAMPER. CORRODED MOUNT GIVEN TO BELL TECH REP. MOUNT WAS REPLACED AND CLAMSHELL REMOVED PER TB 206-89-129A. 1 G 7 1 3U H2SW 1996042500322 19960425 00322 EU 1996 4 25 96ZZZX1969 1 19960307 G 6220 350A31190703 STARFLEX SNIAS 350 AS350B1 8680811 EU M/R SPLINTERED B A UE3R K NONE O OTHER IN INSP/MAINT 1 NM 13 216LA 1962 M2851 2251 ACFT TT: 6,360.8 HRS. YELLOW AND BLUE LEGS OF STARFLEX SPLINTERED AT MIDPOINT OF LEADING EDGES AND TOP SIDE. BEYOND L IMITS PER AS350 MWC 62-20-00-601, PAGE 2. STARFLEX IS A 2,200-HOUR RETIRE AND HAD 1,961.5 HRS AT OCCURRENCE. STARFLEX WAS REMOVED AND REPLACED WITH SERVICEABLE ONE. STARFLEX, SN M-2498, TT 1,961.5 HRS WAS SENT TO AMERICAN EUROCOPTER FOR EVALUATION. 1 G 7 1 3U H9EU 1996042500323 19960425 00323 WP 1996 4 25 96ZZZX1970 1 19960330 G 6220 369D21210501 STRAP ASSY HUGHES 369 369F 4470708 WP M/R HUB BROKEN D A K NONE O OTHER IN INSP/MAINT 1 WP 13 530R 2078 0033434519 0005F AT ACFT TT: 4,378.1 RS, MARCH 30, 1996, DURING POST-FLIGHT INSPECTION OF M/R HUB ASSY - TWO BROKEN STRAPS WERE NOTED ON YELLOW BLADE PITCH HOUSING, STRAPS WERE BROKEN AT LEAD-LAG BOLT STACK-UP. NO BROKEN STRAPS ARE ALLOWED IN THIS AREA. M /R HUB WAS REMOVED FROM SERVICE. M/R HUB WAS INSTALLED AUGUST 16, 1993, ACFT TT, 3,120.6 HRS. TIME IN SERVICE THIS INS TALLATION, 1,207.5 HRS. S/N 003343-4519 THROUGH 4523. 1 G 7 1 3U H3WE 1996042500324 19960425 00324 EU 1996 4 25 96ZZZX1971 1 19960219 G 5512 350A13002061 SKIN SNIAS 350 AS350B 8680801 EU HORIZ STAB AFT CRACKED D A K NONE O OTHER IN INSP/MAINT 1 EA 17 37SH 5604 1288 DURING REPLACEMENT OF HORIZONTAL STABILIZER SKINS AFT, FOUND SKINS CRACKED AT THE UPPER, INBOARD ATTACHMENT AREA. REPLA CING THE SKINS DETAILED ABOVE DUE TO OTHER DEFECTS, BUT HAPPENED TO FIND THESE CRACKS. RECOMMEND CLOSER ATTENTION TO TH E AREA ADJACENT THE STABILIZER ATTACHMENT UPPER AND LOWER SURFACES DURING ROUTINE INSPECTIONS. 1 G 7 1 3U H9EU 1996042500325 19960425 00325 EU 1996 4 25 96ZZZX1972 1 19960219 G 5512 350A13002062 SKIN SNIAS 350 AS350B 8680801 EU HORIZ STAB AFT CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 17 37SH 5604 1288 DURING REPLACEMENT OF HORIZONTAL STABILIZER SKINS AFT, FOUND SKINS CRACKED AT THE UPPER, INBOARD ATTACHMENT AREA. REPLA CING THE SKINS DETAILED ABOVE DUE TO OTHER DEFECTS, BUT HAPPENED TO FIND THESE CRACKS. RECOMMEND CLOSER ATTENTION TO TH E AREA ADJACENT THE STABILIZER ATTACHMENT UPPER AND LOWER SURFACES DURING ROUTINE INSPECTIONS. 1 G 7 1 3U H9EU 1996042500326 19960425 00326 WP 1996 4 25 96ZZZX1973 1 19960402 G 6220 369D21334501 PIVOT BEARING HUGHES 369 369D 4470706 WP M/R HUB PLATE WORN B EOOR K NONE O OTHER IN INSP/MAINT 1 AL 03 3115Y 89 500716D DURING ANNUAL INSPECTION, 3 STRIKER PLATES FOUND WORN BEYOND LIMITS AND ALL 5 PIVOT BEARINGS WORN FROM .030 INCH TO .040 INCH BEARING TO PART NUMBER FIT. 1 G 7 1 3U H3WE 1996042500327 19960425 00327 SW 1996 4 25 96ZZZX1974 1 19960325 G 6510 412340102001 BOOT BELL 412 412 1182202 SW T/R DRIVE DEBONDED B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 92115 39 CB1067 36117 INSPECTION FOUND BOOT DEBONDED. REPLACED WITH NEW BOOT. 1 G 7 2 4U H4SW 1996042500328 19960425 00328 SW 1996 4 25 96ZZZX1975 1 19960325 G 6510 214040659005 COUPLING BELL 412 412 1182202 SW T/R PITTED B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 92115 39 A964 36117 INSPECTION FOUND COUPLING TEETH PITTED. REPLACED WITH NEW COUPLING. 1 G 7 2 4U H4SW 1996042500329 19960425 00329 SW 1996 4 25 96ZZZX1976 1 19960325 G 6510 214040657003 COUPLING BELL 412 412 1182202 SW T/R PITTED B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 92115 39 A716 36117 INSPECTION FOUND COUPLING TEETH PITTED. REPLACED WITH NEW COUPLING. 1 G 7 2 4U H4SW 1996042500330 19960425 00330 SW 1996 4 25 96ZZZX1977 1 19960325 G 6510 214040657003 COUPLING BELL 412 412 1182202 SW T/R PITTED B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 92115 39 A710 36117 INSPECTION FOUND COUPLING TEETH PITTED. REPLACED WITH NEW COUPLING. 1 G 7 2 4U H4SW 1996042500331 19960425 00331 SW 1996 4 25 96ZZZX1978 1 19960313 G 6410 206010765001 BEARING 206016201127 BELL 206 206L3 1182108 SW T/R BLADE CRACKED B PN5R K NONE O OTHER IN INSP/MAINT 1 NM 03 617DE CS6338 51138 INNER RACE CRACKED FROM EDGE OF RACE TOWARDS CENTER OF BALL. REPLACED WITH NEW PN 206-310-105-101 BEARINGS WITH REDUCED CROSS-SECTION OF INNER RACE. 1 G 7 1 3U H2SW 1996042500332 19960425 00332 SW 1996 4 25 96ZZZX1979 1 19960313 G 6410 206010765001 BEARING 206016201127 BELL 206 206L3 1182108 SW T/R BLADE CRACKED B PN5R K NONE O OTHER IN INSP/MAINT 1 NM 03 617DE CS6364 51138 INNER RACE CRACKED FROM EDGE OF RACE TOWARDS CENTER OF BALL. REPLACED WITH NEW PN 206-310-105-101 BEARINGS WITH REDUCED CROSS-SECTION OF INNER RACE. 1 G 7 1 3U H2SW 1996042500333 19960425 00333 WP 1996 4 25 96ZZZX1980 1 19960403 G 6420 369D21800501 SWASHPLATE HUGHES 369 369D 4470706 WP T/R DRIVE BEARING ROUGH B EOOR K NONE O OTHER IN INSP/MAINT 1 AL 03 3115Y SH0715 500716D DURING ANNUAL INSPECTION, THE T/R SWASHPLATE BEARING WAS FOUND ROUGH. REPLACED THE T/R SWASHPLATE. 1 G 7 1 3U H3WE 1996042500334 19960425 00334 EU 1996 4 25 96ZZZX1981 1 19960330 G 5520 10902000293 ELEVATOR AGUSTA A109 A109A2 0260120 EU LT SYNC ELEV CRACKED C K NONE O OTHER IN INSP/MAINT 1 NM 01 1VH 3574 7273 LEFT SYNC ELEVATOR SHOWED CRACKS ALONG EDGE AND INTO ATTACH FITTING HOLES. RIB PN 109-0200-04-7 AND PN 109-0200-02-59. FURTHER DISASSEMBLY REVEALED CRACKS IN FORWARD SPAR AND SPAR DOUBLER PN 104-0200-02-49 AND AFT SPAR AND AFT SPAR DOUBLE R PN 109-0200-02-33. CRACKING APPEARS TO DEVELOP FROM LOOSENING OF THE ATTACH ANGLES LOCATED ON THE SPARS AND ATTACHED TO THE INBOARD RIB. 1 G 7 2 3U H7EU 1996042500335 19960425 00335 EU 1996 4 25 96ZZZX1982 1 19960330 G 5520 10902000294 ELEVATOR AGUSTA A109 A109A2 0260120 EU RT SYNC ELEV CRACKED D K NONE O OTHER IN INSP/MAINT 1 NM 01 55NW 3580 7267 RIGHT SYNC ELEVATOR CRACKS SHOWED ALONG EDGE OF INBOARD RIB. RIB PN 109-8200-02-59 AND PN 109-0200-04-7. FURTHER DISAS SEMBLY REVEALED CRACKS IN FORWARD SPAR AND SPAR DOUBLER PN 109-0200-02-49 AND AFT SPAR AND DOUBLER PN 109-0200-02-33. C RACKING APPEARS TO DEVELOP FROM LOOSENING OF THE ATTACH ANGLES LOCATED ON THE SPARS AND ATTACHED TO THE INBOARD RIB. 1 G 7 2 3U H7EU 1996042500336 19960425 00336 EU 1996 4 25 96ZZZX1983 1 19960330 G 6520 1090372401 ATTACH FITTING AGUSTA A109 A109A2 0260120 EU 90 DEG GRBOX CRACKED D S K NONE O OTHER IN INSP/MAINT 1 NM 01 1VH 3574 7273 INSPECTION FOUND A CRACK IN THE 90 DEGREE GEARBOX ATTACH FITTING UPPER LT CORNER RUNNING LATERALLY ACROSS TO THE UPPER V ERTICAL FIN ATTACH PLATE. ADDITIONAL PORTS CRACKED INCLUDE PN 109-0372-41-5 AND PN 109-0372-41-3. 1 G 7 2 3U H7EU 1996042500363 19960425 00363 CE 1996 4 25 96ZZZX1984 1 19960301 G 5741 0411129 BLOCK CESSNA 170 170B 2072306 CE SPAR BEARING CORRODED D S K NONE O OTHER IN INSP/MAINT 1 NM 01 2364C 20352 SPAR BEARING BLOCK (FWD WING SPAR ATTACH POINT) FOUND SEVERELY CORRODED. 1 H 7 1 3O A799 1996042500364 19960425 00364 CE 1996 4 25 96ZZZX1985 1 19960325 G 2510 05112421 SEAT STOP CESSNA 172 172 2072402 CE PILOT AFT STOP BROKEN D A K NONE O OTHER IN INSP/MAINT 1 NM 11 4642J 17273658 FOUND PILOT'S AFT SEAT STOP BROKEN. IF UNNOTICED, REAR SEAT ROLLERS MAY DISCONNECT FROM RAILS MAKING SEAT PINS NON-FUNC TIONAL. WITH SEAT PINS NOT POSITIONED PROPERLY, SEAT MAY SLIDE AFT ON TAKEOFF AND CREATE POSSIBLE DEPARTURE STALL CONFI GURATION. 1 H 7 1 3O NT 3A12 1996042500365 19960425 00365 CE 1996 4 25 96ZZZX1986 1 19960329 G 2720 15371 RUDDER PEDAL BBAVIA 8 8KCAB 2110612 CE LT FORWARD FAILED D A K NONE O OTHER IN INSP/MAINT 1 NE 01 5061K 65 56079 SUBMITTER STATES THIS IS THE THIRD FAILURE OF THE NEW STYLE RUDDER PEDALS FROM AMERICAN CHAMPION AIRCRAFT. IT IS THE TH IRD BROKEN RUDDER PEDAL IN 298.0 HRS. 1 H 7 1 3O A21CE 1996042500367 19960425 00367 GL 1996 4 25 96ZZZX1988 3 19960307 G 6110 A18916 PILOT TUBE PIPER PA31T PA31T 7103124 SO HARTZL HCB3T HCB3TN3 GL PROP TUBE NR 3 CRACKED B S LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 BU3996 INSPECTION FOUND PROPELLER PILOT TUBE NR 3 CRACKED. 1 L 7 2 3T A8EA 6 C P15EA 1996042500368 19960425 00368 CE 1996 4 25 96ZZZX1989 1 19960314 G 2710 051010513 CONTROL CABLE CESSNA 172 172M 2072418 CE LT AILERON FRAYED B P A K NONE O OTHER IN INSP/MAINT 1 NM 11 9197H 2856 17266009 DURING ROUTINE ANNUAL INSPECTION, THE AILERON BALANCE CABLE WAS FOUND FRAYED WITH APPROXIMATELY 50 PERCENT OF THE STRAND S BROKEN. LOCATION OF THIS DEFECT WAS WHERE THE CABLE PASSED BY THE THREE NYLON CABLE PULLEYS IN THE CENTER FUSELAGE AR EA, ACCESSED THROUGH THE CABIN HEADLINER. THERE WERE NO MARKS ON ANY ADJACENT COMPONENTS TO INDICATE CHAFING. THE PULL EY WAS FREE AND ROTATING NORMALLY. NO SPECIFIC CAUSE COULD BE DETERMINED. 1 H 7 1 3O NT 3A12 1996042500369 19960425 00369 1996 4 25 96ZZZX1990 4 19960130 G 6122 B20258 FLYWEIGHT BASE MCAULY DCFS290D2BT6 CESSNA 421 421C 2076016 CE GOVERNOR CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 145CP 770233 421C0329 INSPECTION FOUND GOVERNOR FLYWEIGHT BASE CRACKED. 1 L 7 2 3O A7CE 1996042500370 19960425 00370 1996 4 25 96ZZZX1991 4 19960130 G 6122 B20431 DRIVE DISC MCAULY DCFS290D2BT6 CESSNA 421 421C 2076016 CE GOVERNOR CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 145CP 770233 421C0329 INSPECTION FOUND GOVERNOR DAMPENER DRIVE DISC CRACKED. SUSPECT CAUSE AS POSSIBLE DETONATION OF ENGINE. 1 L 7 2 3O A7CE 1996042500371 19960425 00371 1996 4 25 96ZZZX1992 4 19960130 G 6122 B20431 DRIVE DISC MCAULY DCFS290D2BT6 CESSNA 421 421C 2076016 CE GOVERNOR CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 145CP 770234 421C0329 INSPECTION FOUND GOVERNOR DAMPENER DRIVE DISC CRACKED. SUSPECT CAUSE AS POSSIBLE DETONATION OF ENGINE. 1 L 7 2 3O A7CE 1996042500372 19960425 00372 1996 4 25 96ZZZX1994 4 19960130 G 6122 B20258 FLYWEIGHT BASE MCAULY DCFS290D2BT6 CESSNA 421 421C 2076016 CE GOVERNOR CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 145CP 770234 421C0329 INSPECTION FOUND GOVERNOR FLYWEIGHT BASE CRACKED. 1 L 7 2 3O A7CE 1996042500373 19960425 00373 GL 1996 4 25 96ZZZX1995 3 19960214 G 6114 771226 HUB CESSNA 206 U206F 2073333 CE MCAULY 3A32C 3A32C* GL BLADE RETAIN CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 8498Q 4513 U20603356 771226 INSPECTION FOUND CRACK IN BLADE RETENTION THREAD OF HUB SOCKET. 1 H 7 1 3O A4CE 5 C P21EA 1996042500374 19960425 00374 GL 1996 4 25 96ZZZX1996 3 19960130 G 6114 B3252 FORK GULSTM G1159 GIV 3980115 SO HARTZL HCC3Y HCC3YR GL 90-DEG RADIUS CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 500DJ 2984 1429 1169 CK1256 INSPECTION FOUND ACTUATING FORK IS CRACKED WHERE THE BLADE BLOCKS REST IN FORK AT THE 90-DEGREE RADIUS. 2 L 7 2 4F RT A12EA 5 C P25EA 1996042500375 19960425 00375 GL 1996 4 25 96ZZZX1997 3 19960214 G 6110 C4451 FERRULE CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL BEARING SEAT CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 68239 340A1276 702328 PROPELLER INSPECTION FOUND FERRULE CRACKED AT BEARING SEAT. 1 L 7 2 3O 3A25 5 C P22EA 1996042500376 19960425 00376 GL 1996 4 25 96ZZZX1998 3 19960214 G 6114 D7015C93 HUB CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL BLADE RETAIN CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 2274 924 801427 INSPECTION FOUND CRACK IN BLADE RETENTION THREADS. 1 L 7 2 3O RT A7CE 5 C P22EA 1996042500377 19960425 00377 GL 1996 4 25 96ZZZX1999 3 19960130 G 6110 C4451 FERRULE CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C87 GL BEARING SEAT CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 739572 INSPECTION FOUND PROPELLER FERRULE CRACKED WHERE BEARING SEATS IN FERRULE RADIUS. 1 L 7 2 3O 3A25 5 C P22EA 1996042500378 19960425 00378 GL 1996 4 25 96ZZZX2000 3 19960329 G 6110 A251314 BOLT CESSNA 172 172 2072402 CE MCAULY 1C172 1C172EM GL PROPELLER DEFECTIVE B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 E5566 PROPELLER FORGING FOLD NEAR FULL LENGTH OF BOLTS, QUANTITY, 2 EACH. 1 H 7 1 3O NT 3A12 5 N P910 1996042500379 19960425 00379 GL 1996 4 25 96ZZZX2001 3 19960130 G 6114 676237 HUB CESSNA 310 310L 2074230 CE MCAULY 3AF32C 3AF32C* GL NR 3 SOCKET CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 167JS 1466 393 310L0129 676237 INSPECTION FOUND CRACK IN BLADE RETENTION THREADS OF NR 3 HUB SOCKET. 1 L 7 2 3O 3A10 5 C P22EA 1996042500380 19960425 00380 1996 4 25 96ZZZX2002 4 19960320 G 6122 B3124 CONTROL SHAFT F411B GOVERNOR CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 D2067U INSPECTION FOUND GOVERNOR CONTROL SHAFT WITH FOUR RADIAL CRACKS IN FLANGE. 1996042500381 19960425 00381 1996 4 25 96ZZZX2003 4 19960329 G 6122 42832 FLYWEIGHT BASE HARTZL F23A GOVERNOR CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 11361T INSPECTION FOUND GOVERNOR FLYWEIGHT CRACKED. 1996042500382 19960425 00382 1996 4 25 96ZZZX2004 4 19960329 G 6122 B20591 DRIVE GEAR MCAULY C2920D4T2 GOVERNOR CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 811954 INSPECTION FOUND GOVERNOR DRIVE GEAR CRACKED. 1996042500383 19960425 00383 1996 4 25 96ZZZX2005 4 19960328 G 6122 20155 FLYWEIGHT MCAULY DCFS290D1ATE CESSNA 414 414 2075908 CE GOVERNOR WELD CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 721284 INSPECTION FOUND CRACKED WELD ON FLYWEIGHT IN THE GOVERNOR. 1 L 7 2 3O RT A7CE 1996042500384 19960425 00384 1996 4 25 96ZZZX2006 4 19960329 G 6122 20155 FLYWEIGHT MCAULY DCFS2902BT6 GOVERNOR WELDS CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 750722 INSPECTION FOUND GOVERNOR FLYWEIGHT WELDS CRACKED. 1996042500385 19960425 00385 1996 4 25 96ZZZX2007 4 19960307 G 6122 41832 FLYWEIGHT BASE HARTZL F624Z PIPER PA31 PA31350 7103110 SO GOVERNOR CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 D178T INSPECTION FOUND GOVERNOR FLYWEIGHTS CRACKED. 1 L 7 2 3O A20SO 1996042500386 19960425 00386 1996 4 25 96ZZZX2008 4 19960307 G 6122 42832 FLYWEIGHT BASE HARTZL F411B GOVERNOR CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 B482U INSPECTION FOUND GOVERNOR FLYWEIGHT BASE CRACKED. 1996042500387 19960425 00387 1996 4 25 96ZZZX2009 4 19960307 G 6122 B3124 CONTROL SHAFT HARTZL F411B PIPER PA32 PA32* SO GOVERNOR SPEED CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 B982U INSPECTION FOUND GOVERNOR SPEED CONTROL SHAFT CRACKED. 1 L 7 1 3O A3SO 1996042500388 19960425 00388 1996 4 25 96ZZZX2010 4 19960307 G 6122 41832 FLYWEIGHT BASE HARTZL F411B PIPER PA32 PA32R300 7103213 SO GOVERNOR CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 B123811 INSPECTION FOUND GOVERNOR FLYWEIGHT BASE CRACKED. 1 L 7 1 3O A3SO 1996042500389 19960425 00389 1996 4 25 96ZZZX2011 4 19960307 G 6122 C4191 DRIVE SHAFT HARTZL F411B GOVERNOR GEAR CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 B982U INSPECTION FOUND GOVERNOR DRIVE GEAR CRACKED. 1996042500390 19960425 00390 1996 4 25 96ZZZX2012 4 19960307 G 6122 D4191 IDLER GEAR HARTZL F624Z GOVERNOR TEETH CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 A4913T INSPECTION FOUND GOVERNOR IDLER GEAR TEETH CRACKED. 1996042500391 19960425 00391 1996 4 25 96ZZZX2013 4 19960307 G 6122 D20541 DRIVE SHAFT MCAULY C290D4T4 GOVERNOR CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 784396 INSPECTION FOUND GOVERNOR DRIVE SHAFT CRACKED. 1996042500392 19960425 00392 1996 4 25 96ZZZX2014 4 19960307 G 6122 D20432 DRIVE SHAFT MCAULY DCFS290D2T3 GOVERNOR CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 751481 INSPECTION FOUND GOVERNOR DRIVE SHAFT CRACKED. 1996042500393 19960425 00393 1996 4 25 96ZZZX2015 4 19960307 G 6122 B20431 SPRING DRIVE MCAULY DCFS290D2T3 GOVERNOR CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 761993 INSPECTION FOUND GOVERNOR CRACKED AT SPRING HOLE. 1996042500394 19960425 00394 1996 4 25 96ZZZX2016 4 19960307 G 6122 B20431 SPRING DRIVE MCAULY DCFS290D2T6 CESSNA 421 421C 2076016 CE GOVERNOR CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 770234 INSPECTION FOUND GOVERNOR SPRING DRIVE HOLDING FLYWEIGHTS CRACKED AT SPRING HOLE. 1 L 7 2 3O A7CE 1996042500396 19960425 00396 GL 1996 4 25 96ZZZX2018 3 19960307 G 6110 A18912 PILOT TUBE PIPER PA31T PA31T 7103124 SO HARTZL HCB3T HCB3TN3 GL PROP TUBE NR 3 CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 118WC 4712 31T8020020 BU3995 INSPECTION FOUND PROPELLER PILOT TUBE, NR 3, HAS LONGITUDINAL CRACK. 1 L 7 2 3T A8EA 6 C P15EA 1996042500397 19960425 00397 GL 1996 4 25 96ZZZX2019 3 19960307 G 6110 A18912 PILOT TUBE PIPER PA31T PA31T 7103124 SO HARTZL HCB3T HCB3TN3 GL PROP TUBE NR 1 CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 118WC 4712 31T8020020 BU3995 INSPECTION FOUND PROPELLER PILOT TUBE, NR 1, HAS LONGITUDINAL CRACK. 1 L 7 2 3T A8EA 6 C P15EA 1996042500398 19960425 00398 EA 1996 4 25 96ZZZX2020 2 19960401 G 7414 M3056 DISTRIBUTOR GEAR SLICK 6363 PIPER PA46 PA46350P SO LYC O540 TIO540AE2A 41532 EA MAGNETO DAMAGED B WC7R K NONE O OTHER IN INSP/MAINT 1 GL 25 202SE 4622092 C908761A 'ENGINE WON'T START' - 766.8 HRS HOBBS. FOUND DISTRIBUTOR GEAR M3056 BURNED. FOUND THE MS20822 FITTING TO PRESSURIZE T HE MAGNETO HAD BEEN SCREWED INTO THE OUTER CASE AND BOTTOMED OUT AGAINST THE DISTRIBUTOR HEAD M3820. SUBMITTER SURMISES THE LACK OF PRESSURIZING AIR CAUSED ARCING THAT, IN TURN, BURNED THE NYLON DISTRIBUTOR GEAR M3056. REPLACED MAGNETO, T RIMMED FITTING MS20822 SO IT WOULD NOT COME IN CONTACT WITH DISTRIBUTOR HEAD. REF: 40-2350. 1 L 7 1 3O 3 O RT A25SO E14EA 1996042500399 19960425 00399 SO 1996 4 25 96ZZZX2021 1 19960206 G 3411 STATIC SYSTEM PIPER PA28 PA28151 7102805 SO ENCODER NOT CONNECTED B JA6R K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 01 32367 287515139 BLIND ALTITUDE ENCODER HAD BEEN DISCONNECTED FROM STATIC SYSTEM AND WAS SAMPLING CABIN AIR RATHER THAN THAT WHICH THE AL TIMETER WAS SENSING. RECONNECTED WITH APPROVED HARDWARE, LEAK TESTED STATIC SYSTEM, AND PERFORMED TEST PER FAR 43 APPEN DICES E AND F. CERTIFIED AIRCRAFT TO BE IN C/W FAR 91.411 AND 91.413. 1 L 7 1 3O 2A13 1996042500400 19960425 00400 CE 1996 4 25 96ZZZX2022 1 19960321 G 2810 41534 TANK BBAVIA 8 8KCAB 2110612 CE LT FUEL SYSTEM BAFFLE BROKEN B OG5R K NONE O OTHER IN INSP/MAINT 1 GL 21 67ND 1728 66792 WITH LEFT TANK FULL, FUEL GAUGE READ 'ZERO' GALLONS. REMOVED SENDER AND CHECKED, OPERATION NORMAL. FOUND FUEL TANK BAF FLE BROKEN OFF AND LAYING ON BOTTOM OF TANK. SENDER PROBLEM TRACED TO FLOAT BEING CAUGHT ON LOOSE BAFFLE LAYING IN TANK . (REMOVED TANK FOR REPAIR). 1 H 7 1 3O A21CE 1996042500401 19960425 00401 SO 1996 4 25 96ZZZX2023 1 19960206 G 3411 TUBING PIPER PA28 PA28151 7102805 SO STATIC SYSTEM WRONG PART B JA6R K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 01 32367 287515139 FOUND DEGRADED/LEAKY SURGICAL RUBBER-TYPE TUBING STRETCHED OVER 'AN' THREADED FITTINGS. THE MATERIAL AND METHOD USED IS UNACCEPTABLE FOR THE APPLICATION. REPLACED WITH AN/MS FITTINGS AND MIL-H HOSE. 1 L 7 1 3O 2A13 1996042500402 19960425 00402 SO 1996 4 25 96ZZZX2024 1 19960321 G 5741 644120 ATTACH PIPER PA25 PA25235 7102504 SO RT WING FWD ATT DEFECTIVE D K NONE O OTHER IN INSP/MAINT 1 GL 21 7318Z 2075 253265 INSPECTED AIRCRAFT FOR NDT-UTT PER AD 95-12-01, RIGHT FORWARD WING SPAR ATTACH. PRELIMINARY INSPECTION SHOWED VISIBLE P OCKET INBETWEEN THE STEEL PLATES. WHEN TESTING UTT, A LOW READING WAS DETECTED IN THIS AREA WHICH WAS BELOW THE MINIMUM THICKNESS ALLOWED. THE EAR HAD BEEN WELDED AT ONE TIME TO REPAIR WHAT LOOKED LIKE IT COULD HAVE BEEN A CRACK. 1 L 7 1 3O 2A10 1996042500403 19960425 00403 EA 1996 4 25 96ZZZX2025 2 19960319 G 8530 PISTON ROD STOLAM RC3 RC3 3080202 SO FRNKLN 6A8215 6A8215B9F 27030 EA FWD RT CYLINDER FAILED G A UNSCHED LANDING E R K VIBRATION/BUFFET PARTIAL RPM/PWR LOSS FLUID LOSS CL CLIMB 1 WP 25 6496K 1020 30 762 23714 AIRCRAFT LOST POWER ON TAKEOFF. PILOT LANDED IN FIELD AT END OF RUNWAY. FOUND FORWARD RIGHT PISTON ROD HAD LOST END CA P (BOLTS FAILED) AND WENT THROUGH CRANKCASE BREAKING STARTER. ENGINE HAD ONLY 30.0 HRS SMOH. 1 H 7 1 3O 3 O A769 E242 1996042500405 19960425 00405 SO 1996 4 25 96ZZZX2027 1 19960403 G 3230 95219902 STUD PIPER PA34 PA34200 7103405 SO RT MLG BRACE CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 06 15839 3214 347350100 IAW AD 95-20-07, MLG SIDE BRACE STUD INSPECTION, RT STUD MAGNETIC PARTICLE INSPECTION FOUND STUD CRACKED; THUS, REMOVED FROM SERVICE. RECORDS REVIEWED NOTED RT MLG TRUNNION REPLACED MARCH, 1994, REASON NOT MENTIONED. AFT WING MOD PIPER KI T 760-977 OUTBOARD OF GEAR AND WING RIB INSTALLED OUTBOARD OF TRUNNION. POSSIBLE GEAR-UP ACCIDENT MAY HAVE WEAKENED SID E BRACE STUD. 1 L 7 2 3O A7SO 1996042500406 19960425 00406 SO 1996 4 25 96ZZZX2028 2 19960326 G 8530 CYLINDER CESSNA 206 TU206G 2073357 CE CONT O520 TSIO520M 17040 SO ENGINE MISINSTALLED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 11 9438M 1117 U20604546 248770R WHEN TRYING TO REMOVE CYLINDERS FOR A TOP OVERHAUL, FOUND TORQUES VERY HIGH TO ALMOST FINGER TIGHT ON CYLINDER STUDS AND THROUGH-BOLTS. THIS ENGINE HAS TORQUE PASTE STILL IN PLACE - ONE-HALF INCH DRIVE AIR WRENCH DID NOTHING - HAD TO CHISE L TWO NUTS OFF SO FAR - TWO CYLINDERS TO GO. SUBMITTER SUGGESTS QUALITY CONTROL SEVERELY LACKING ON THIS FACTORY REMANU FACTURED ENGINE. ENGINE WAS INSTALLED JUNE '89. NO PRIOR PROBLEMS. BROKE CYLINDER WRENCH ON NR 2 CYLINDER. 1 H 7 1 3O 3 O A4CE E8CE 1996042500681 19960425 00681 CE 1996 4 25 96ZZZX2029 1 19960325 G 2810 FUEL CAP CESSNA 182 182E 2072712 CE FUEL TANK DEFECTIVE D K NONE O OTHER IN INSP/MAINT 1 WP 17 3308Y 2793 18254308 FUEL CAPS ARE ALLOWING WATER TO BE INTRODUCED INTO THE FUEL TANKS. SUBMITTER STATED THIS CAN CAUSE ENGINE FAILURE. 1 H 7 1 3O NT 3A13 1996042500682 19960425 00682 CE 1996 4 25 96ZZZX2030 1 19960318 G 3230 DOWNLOCK BEECH 55 95B55 1152706 CE LT MLG LOW TENSION B K5SR K NONE O OTHER LD LANDING 1 NM 11 193L TC1055 LEFT MAIN TIRE WAS SKIDDED ON RUNWAY TO THE POINT OF TIRE FAILURE. LEFT MAIN GEAR THEN COLLAPSED. INVESTIGATION REVEAL ED LANDING GEAR DOWNLOCK TENSION WAS 15-20 POUNDS. BEECHCRAFT SM REQUIRES DOWNLOCK TENSION TO BE 45-65 POUNDS. IT IS S UPPOSED THE ADDITIONAL LOADS IMPOSED BY THE TIRE FAILURE CAUSED THE DOWNLOCK TO MOVE OVER CENTER DUE TO THE LOW DOWNLOCK TENSION. 1 L 7 2 3O 3A16 1996042500683 19960425 00683 NE 1996 4 25 96ZZZX2031 1 19960401 G 3233 180029005 ACTUATOR CONAER LA4 LA4200 5110310 NE NLG FAILED D K NONE O OTHER IN INSP/MAINT 1 SO 19 85213 307 1094 NOSE GEAR ACTUATOR PISTON ASSY (ROD AND PISTON) RECEIVES A SIDE LOAD AT THE THREADED END OF ACTUATOR ROD. NOSE GEAR ACT UATES AT A VERY FAST RATE WHICH MAY CAUSE A 'BOUNCE' AT THE TRAVEL LIMIT WHICH BENDS AND CRACKS, AND ULTIMATELY BREAKS T HE END OF THE ACTUATOR. SUBMITTER STATED THIS IS 6TH OCCURRENCE (DIFFERENT AIRCRAFT) THIS YEAR. 1 H 7 1 3O 1A13 1996042500684 19960425 00684 SO 1996 4 25 96ZZZX2032 1 19960301 G 3233 ACTUATOR GARKENYON PIPER PA28 PA28R200 7102811 SO NLG HOUSING CRACKED D K NONE O OTHER IN INSP/MAINT 1 NE 01 HAVE FOUND VARIOUS ACTUATOR HOUSINGS CRACKED AT THE FITTING BOSS. INITIALLY, IT APPEARS THE UNIT HAS A BAD SEAL, BUT TH EN INSPECTION REVEALS A HAIRLINE CRACK. 1 L 7 1 3O 2A13 1996042500685 19960425 00685 1996 4 25 96ZZZX2033 1 19960325 G 2822 2B729 PUMP AIRBORNE FUEL SYSTEM SHORTED D K NONE O OTHER IN INSP/MAINT 1 GL 13 11AJ198 FUEL PUMP ARMATURE SHORTED, BRUSH BLOCK MELTED, OVERHEATED. ARMATURE CAUSES POTTING TO SWELL. SUBMITTER SUGGESTS MAY H AVE BEEN CAUSED BY RUNNING PUMP DRY. 1996042500687 19960425 00687 CE 1996 4 25 96ZZZX2035 1 19960330 G 5350 04310241791 FAIRING CESSNA 150 150L 2071826 CE DORSAL FIN MISMANUFACTURED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 17 18609 1573984 TRAILING END OF FAIRING IS NOT TALL ENOUGH TO FIT OVER DORSAL FIN. 1 H 7 1 3O 3A19 1996042500688 19960425 00688 EA 1996 4 25 96ZZZX2036 2 19960326 G 8530 LW18729 PISTON CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA NR 3 CYL BROKEN D K NONE O OTHER IN INSP/MAINT 1 EA 03 69265 1745 15282590 RL2333815 ENGINE WAS 'REMANUFACTURED' BY LYCOMING, DATED 12-13-90. REMOVAL OF NR 3 CYLINDER TO INVESTIGATE AN OIL FOULING PROBLEM REVEALED A BROKEN PISTON. PISTON SKIRT HAD BROKEN OFF ON THRUST SIDE (TOP) OF PISTON BETWEEN THE PISTON PIN BOSSES AND UP TO OIL CONTROL RING GROOVE. PISTON APPEARS TO HAVE BEEN CRACKED BETWEEN THE 2 OIL CONTROL RING GROOVE OIL DRAIN HOL ES FOR SOME TIME BEFORE BREAKING. ENGINE RAN FINE WITH NO INDICATIONS OF A SERIOUS PROBLEM EXCEPT FOR OIL FOULING OF TH E BOTTOM SPARK PLUG. A COMPRESSION CHECK DONE HOT JUST BEFORE CYLINDER REMOVAL SHOWED 76/80 PSI. 1 H 7 1 3O 3 O NT 3A19 E223 1996042500689 19960425 00689 CE 1996 4 25 96ZZZX2037 1 19960328 G 8011 MHB4016R STARTER ELECTROSYS MHB4016R CESSNA 172 172RG 2072438 CE REAR CASE BOLTS MISSING D K NONE O OTHER IN INSP/MAINT 1 SW 17 9367D 1900 9P000141 172RG1139 DURING A 100-HOUR INSPECTION, THE STARTER REAR CASE WAS FOUND LOOSE. THREE OF THE FOUR SCREWS THAT SECURE FRONT BENDIX HOUSING TO REAR CASE FOUND MISSING. SUBMITTER STATED CAUSED BY VIBRATION OR POOR ASSEMBLY TORQUES OR LOCK WASHERS WHEN STARTER WAS BUILT. RECOMMEND TORQUING SCREWS AT EACH 100-HOUR INSPECTION. 1 H 7 1 3O 3A17 1996042500690 19960425 00690 GL 1996 4 25 96ZZZX2038 1 19960301 G 2510 0200016 SEAT PAN AMTR PITTS PITTSSPECIAL GL PILOT CRACKED D K NONE O OTHER IN INSP/MAINT 1 NE 01 SEATS CONTINUALLY CRACK, APPARENTLY, UNDER THE HIGH 'G' LOAD. 1 Q 7 1 3O EXPA1Q71 1996042500691 19960425 00691 SO 1996 4 25 96ZZZX2039 1 19960325 G 7603 3174700 BALL JOINT PIPER PA24 PA24260 7102406 SO THROTTLE CABLE CRACKED D K NONE O OTHER IN INSP/MAINT 1 NM 11 8967P 8400 244424 COMPLAINTS OF STIFF THROTTLE OPERATON LED TO LUBING THROTTLE CABLE, HOWEVER, AFTER SHORT TIME, CABLE BECAME STIFF AGAIN. WHILE REPLACING CABLE, DISCOVERED THE BALL JOINT WHICH CONNECTS THE CABLE TO THROTTLE METERING ARM BENT AND CRACKED AP PROXIMATELY TWO-THIRDS THROUGH BALL JOINT. IT IS SUSPECTED THE ROUGH OPERATION PERMITTED EXTRA STRESS ON CONNECTION WIT HOUT PILOT'S KNOWLEDGE. SUBMITTER STATES CLOSE INSPECTION OF ALL ENGINE CONTROLS AND OPERATION SHOULD ELIMINATE POSSIBI LITY OF FAILURES. 1 L 7 1 3O 1A15 1996042500692 19960425 00692 CE 1996 4 25 96ZZZX2040 1 19960325 G 3211 0541153 U-BOLT CESSNA 172 172K 2072430 CE MLG BROKEN D K NONE O OTHER IN INSP/MAINT 1 NE 01 7119G 5800 17258819 DURING 100-HOUR INSPECTION, FOUND MAIN GEAR ATTACHMENT U-BOLT BROKEN ON ONE END. UPON REMOVAL OF THE MAIN GEAR LEG, THE REMAINING AN6-15A BOLT ATTACHING THE GEAR WAS FOUND BENT. SUBMITTER STATED HIGH/TIME FATIGUE IS SUSPECT CAUSE AND A TI ME LIMIT ON THIS PART WOULD MORE THAN LIKELY PREVENT RECURRENCE. 1 H 7 1 3O NT 3A12 1996042500693 19960425 00693 SO 1996 4 25 96ZZZX2041 1 19960322 G 2822 2B663 PUMP AIRBORNE PIPER PA31 PA31350 7103110 SO FUEL SYSTEM MISINSTALLED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 13 10 9E698 FUEL PUMP INSPECTION FOUND PIPE SEALER USED ON INLET AND OUTLET. PUMP HAD PIPE SEALER ALL OVER THE INSIDE WHICH CAUSED THE VANES TO STICK. PUMP FITTINGS ARE SEALED WITH AN O-RING AND DO NOT REQUIRE PIPE SEALER. 1 L 7 2 3O A20SO 1996042500694 19960425 00694 CE 1996 4 25 96ZZZX2042 1 19960325 G 3211 05411212 FITTING CESSNA 172 172K 2072430 CE RT INBD MLG LEG CRACKED D K NONE O OTHER IN INSP/MAINT 1 NE 01 7119G 5800 17258819 DURING 100-HOUR INSPECTION, THE RT INBOARD MAIN GEAR LEG SUPPORT FITTING WAS FOUND CRACKED AT U-BOLT ATTACH HOLE. REMOV AL OF GEAR LEG REVEALED THE CRACK STARTED UNDER THE NUT. SUSPECT CAUSE IS HIGH TIME/FATIGUE. SUBMITTER STATED CLOSE AT TENTION TO THIS AREA WILL PREVENT RECURRENCE. 1 H 7 1 3O NT 3A12 1996042500695 19960425 00695 SO 1996 4 25 96ZZZX2043 1 19960319 G 5700 LIFT STRUT MAULE M5 M5210C 5460134 SO WING NR 1 CORRODED B CO4R K NONE O OTHER IN INSP/MAINT 1 AL 03 51569 6025C INSPECTION OF LIFT STRUTS PER AD 93-10-06 FOUND NR 1 STRUT UNAIRWORTHY DUE TO LOWER 8 INCH OF STRUT DEFECTIVE DUE TO COR ROSION. 1 H 7 1 3O 3A23 1996042500696 19960425 00696 1996 4 25 96ZZZX2044 4 19960112 G 2210 30B200 BRIDLE CABLE CENTURY PIPER PA28 PA28180 7102808 SO AUTOPILOT PIN SLIPPAGE B BCBR K NONE O OTHER IN INSP/MAINT 1 EA 03 6589J 5370 285048 C/W CENTURY FLT SYSTEM SB CFS-95-01 DATED 10-11-95. BRIDLE CABLE INSPECTION FOUND PIN SLIPPAGE ON CABLE. REPLACED CABL E. 1 L 7 1 3O 2A13 1996042500697 19960425 00697 1996 4 25 96ZZZX2045 4 19960112 G 2210 30B200 BRIDLE CABLE CENTURY PIPER PA32 PA32260 7103206 SO AUTOPILOT PIN SLIPPAGE B BCBR K NONE O OTHER IN INSP/MAINT 1 EA 03 5598J 2444 321065 C/W CENTURY FLT SYSTEM SB CFS-95-01 DATED 10-11-95. BRIDLE CABLE INSPECTION FOUND PIN SLIPPAGE ON CABLE. REPLACED CABL E. 1 L 7 1 3O A3SO 1996042500698 19960425 00698 CE 1996 4 25 96ZZZX2046 1 19960202 G 3710 IG44 INDICATOR AIRBORNE BEECH 58 58 1152740 CE SOURCE PRESSURE DEFECTIVE D L K NONE O OTHER IN INSP/MAINT 1 SO 01 66432 2904 TH1056 DURING ANNUAL INSPECTION, INSTRUMENT AIR PRESSURE GAUGE READ NORMAL WHEN EITHER ENGINE WAS RUN INDIVIDUALLY, BUT INDICAT ED HIGH WHEN BOTH ENGINES OPERATING. ALSO, NOTICED ACTIVATION OF DEICE SYS CAUSED INSTRUMENT TO 'PEG' FOR DURATION OF C YCLE. T/S SYS DISCLOSED ACTUAL PRESS DELIVERED TO GYROS WAS WELL BELOW NORMAL (APPROX 3.0 INCH HG) AND INSTRUMENT AIR R EGULATOR SET TO MINIMUM, I.E., SCREWED ALL THE WAY IN. WHEN THE INSTRUMENT REGULATOR ADJUSTED TO PROVIDE CORRECT PRESS TO GYROS, ACFT PRESS GAUGE READING WENT 'OFF THE SCALE'. INVEST REVEALED SOURCE INDICATORS OF INSTR AIR PRESS GAUGE LEA KING & PRESSURIZING INSTR CASE INTERNALLY CAUSING ABNORMALLY HIGH INDICATIONS. DEFECTIVE INSTR REPLACED WITH O/H UNIT. 1 L 7 2 3O 3A16 1996042500699 19960425 00699 SO 1996 4 25 96ZZZX2047 1 19960411 G 2810 63913194 HOSE PIPER PA28 PA28R180 7102809 SO FUEL TANK VENT DETERIORATED D L K NONE O OTHER IN INSP/MAINT 1 EA 01 3486R 2801 28R5701 PULLED BOTH FUEL TANKS PRIOR TO HAVING AIRCRAFT PAINTED TO REPAIR VENT HOSE CONNECTIONS AND SENDER GASKETS. FOUND VENT HOSES BADLY DETERIORATED ESPECIALLY OF UPPER CONNECTION. 1970 YEAR AIRCRAFT, FIRST REPLACEMENT OF THESE HOSES. SUBMITT ER STATED NEED AN AD ON THIS. 1 L 7 1 3O 2A13 1996042500700 19960425 00700 SO 1996 4 25 96ZZZX2048 1 19960411 G 2810 63913193 HOSE PIPER PA28 PA28R180 7102809 SO FUEL TANK VENT DETERIORATED D L K NONE O OTHER IN INSP/MAINT 1 EA 01 3486R 2801 28R5701 PULLED BOTH FUEL TANKS PRIOR TO HAVING AIRCRAFT PAINTED TO REPAIR VENT HOSE CONNECTIONS AND SENDER GASKETS. FOUND VENT HOSES BADLY DETERIORATED ESPECIALLY OF UPPER CONNECTION. 1970 YEAR AIRCRAFT, FIRST REPLACEMENT OF THESE HOSES. SUBMITT ER STATED NEED AN AD ON THIS. 1 L 7 1 3O 2A13 1996042500701 19960425 00701 SO 1996 4 25 96ZZZX2049 1 19960411 G 2810 63913193 HOSE PIPER PA28 PA28140 7102802 SO FUEL TANK VENT DETERIORATED D A K NONE O OTHER IN INSP/MAINT 1 EA 01 1690T 4992 287125007 PULLED FUEL TANKS DUE TO FUEL SMELL IN COCKPIT AFTER TANKS ARE TOPPED OFF. FOUND VENT HOSE CONNECTIONS VERY BADLY SPLIT DUE TO AGE OF HOSES. 1971 YEAR AIRCRAFT, FIRST REPLACEMENT. NEED AD ON THIS SUBJECT AS THE USE OF THESE AIRCRAFT IN T HE FIELD INCREASES. 1 L 7 1 3O 2A13 1996042500702 19960425 00702 SO 1996 4 25 96ZZZX2050 1 19960411 G 2810 63913194 HOSE PIPER PA28 PA28140 7102802 SO FUEL TANK VENT DETERIORATED D K NONE O OTHER IN INSP/MAINT 1 EA 01 1690T 4992 287125007 PULLED FUEL TANKS DUE TO FUEL SMELL IN COCKPIT AFTER TANKS ARE TOPPED OFF. FOUND VENT HOSE CONNECTIONS VERY BADLY SPLIT DUE TO AGE OF HOSES. 1971 YEAR AIRCRAFT, FIRST REPLACEMENT. NEED AD ON THIS SUBJECT AS THE USE OF THESE AIRCRAFT IN T HE FIELD INCREASES. 1 L 7 1 3O 2A13 1996042500703 19960425 00703 CE 1996 4 25 96ZZZX2051 1 19960414 G 2731 07125002 ACTUATOR CESSNA 185 A185F 2072821 CE STABILIZER TRIM STUCK D A K NONE F FLT CONT AFFECTED IN INSP/MAINT 1 SO 07 THE OWNER COMPLAINED HE COULD NOT TRIM PLANE FOR NOSE DOWN. UPON INSPECTION, TRIM SYSTEM WOULD BECOME STUCK REQUIRING E XTREME FORCE TO FREE SYSTEM. UPON STABILIZER REMOVAL, FOUND ACTUATOR WOULD BIND IN APPROXIMATELY NEUTRAL POSITION. AFT ER SOAKING PARTS IN PENETRATING FLUID AND APPLYING EXTREME FORCE, PARTS WERE FINALLY SEPARATED. SUBMITTER SUSPECTED CAU SE - NO LUBRICATION TO ASSEMBLY DUE TO DIFFICULTY OF ACCESS. THIS COULD CAUSE A DANGEROUS CONDITIONIN FLIGHT!. 1 H 7 1 3O 3A24 1996042500704 19960425 00704 CE 1996 4 25 96ZZZX2052 1 19960414 G 2731 07125001 ACTUATOR CESSNA 185 A185F 2072821 CE STABILIZER TRIM STUCK D K NONE F FLT CONT AFFECTED IN INSP/MAINT 1 SO 07 THE OWNER COMPLAINED HE COULD NOT TRIM PLANE FOR NOSE DOWN. UPON INSPECTION, TRIM SYSTEM WOULD BECOME STUCK REQUIRING E XTREME FORCE TO FREE SYSTEM. UPON STABILIZER REMOVAL, FOUND ACTUATOR WOULD BIND IN APPROXIMATELY NEUTRAL POSITION. AFT ER SOAKING PARTS IN PENETRATING FLUID AND APPLYING EXTREME FORCE, PARTS WERE FINALLY SEPARATED. SUBMITTER SUSPECTED CAU SE - NO LUBRICATION TO ASSEMBLY DUE TO DIFFICULTY OF ACCESS. THIS COULD CAUSE A DANGEROUS CONDITIONIN FLIGHT!. 1 H 7 1 3O 3A24 1996042500705 19960425 00705 SO 1996 4 25 96ZZZX2053 1 19960405 G 3233 837693E ACTUATOR PARKERHANFIN PIPER PA46 PA46310P 7104605 SO NLG MISSING O-RING B L WC7R K NONE K FLUID LOSS IN INSP/MAINT 1 GL 25 188RW 285 4608133 HOBBS, 1,124.1 HOURS. NOSE GEAR DOORS WOULD NOT RETRACT (CLOSE) AFTER GEAR RETRACTION. NOSE GEAR DOOR ACTUATOR FOUND L EAKING HYDRAULIC FLUID SEVERELY. DISASSEMBLED ACTUATOR, FOUND A BACK-UP RING MISSING ON PISTON ALLOWING O-RING TO ROLL AND SPLIT. UNIT REQUIRES TWO BACK-UP RINGS. INSTALLED PIPER REPAIR KIT PN 765-330 IAW 32-30-00, PAGES 21-22. SWUNG GE AR, OPS CHECK GOOD. 1 L 7 1 3O A25SO 1996042500706 19960425 00706 CE 1996 4 25 96ZZZX2054 1 19960315 G 3221 05430131 CASTING CESSNA 172 172K 2072430 CE NLG BUTTERFLY SHEARED RIVETS D A K NONE O OTHER IN INSP/MAINT 1 CE 05 2000 A 1971 MODEL AND 1980 MODEL 172, FOUND WITH RIVETS SHEARED AND LOOSE WHICH ATTACH NOSE GEAR BUTTERFLY CASTING; THUS, CAU SING CASTING TO WORK AGAINST FIREWALL. THE TOP TWO BOLTS AT TOP WERE ONLY ATTACHING POINTS LEFT. CESSNA SM ALLOWS RIVE T HOLES TO BE DRILLED AND REPLACED WITH AN-3 BOLTS. SUBMITTER RECOMMENDS MORE FREQUENT INSPECTIONS. 1 H 7 1 3O NT 3A12 1996042500707 19960425 00707 EA 1996 4 25 96ZZZX2055 2 19960318 G 8550 SUMP PLUG PIPER PA44 PA44180 7104402 SO LYC O360 LO360E1A6 41514 EA ENGINE OIL MISSING D A E ENGINE SHUTDOWN J K WARNING INDICATION FLUID LOSS CR CRUISE 1 GL 15 2127D 45 447995131 L18572T AIRCRAFT WAS FLYING WHEN RT ENGINE LOST ALL OIL PRESSURE. ENGINE WAS SECURED. MAINTENANCE DISCOVERED MISSING SUMP PLUG ON OIL SUMP. SUBMITTER STATED UNIT WAS NOT SECURED AT FACTORY. CHECKED LT ENGINE, PLUG WAS NOT SAFETIED. SECURED PLU G WITH SAFETY WIRE AND RELEASED AIRCRAFT FOR SERVICE. 1 L 7 2 3O 3 O A19S0 E286 1996042500708 19960425 00708 CE 1996 4 25 96ZZZX2056 1 19960322 G 2720 04115264 RUDDER BAR CESSNA 150 152 2071835 CE PILOT RT RUDDER WELD BROKEN D P K NONE O OTHER IN INSP/MAINT 1 SW 99 6502H 8753 15284171 DURING RUN-UP FOR FLIGHT, PILOT'S RIGHT RUDDER PEDAL WOULD NOT MOVE RUDDER. THE WELD ASSEMBLY OF RUDDER BAR WAS BROKEN AT ARM ASSEMBLY FOR RUDDER PEDAL. METAL FATIGUE AROUND LOWER END OF WELDED AREA. NEW PART WAS MODIFIED TO INCREASE STR ENGTH. 1 H 7 1 3O NT 3A19 1996042500709 19960425 00709 SW 1996 4 25 96ZZZX2057 1 19960319 G 2810 CCA1650 FUEL DRAIN CURTIS AIRTRC AT400 AT402 0390205 SW FUEL SYSTEM FAILED D A K NONE O OTHER IN INSP/MAINT 1 SO 07 6076U 463 4020971 AFTER PERFORMING NUMEROUS ANNUALS ON AIRCRAFT USING THIS TYPE OF FUEL DRAIN, SUBMITTER FOUND CLOSE TO 15 PERCENT OF THE FUEL DRAINS CRACKED AT THE TOP OF THE DRAIN NEAR THE SEALING SURFACE. IF UNDETECTED, THIS COULD LEAD TO THE INNER PARTS OF THE DRAIN FALLING OUT AND DRAINING FUEL. SUBMITTER RECOMMENDS CLOSE INSPECTION OF THE DRAIN WHENEVER IT IS REMOVED FOR ANY REASON. 1 L 7 1 3T NC A17SW 1996042500710 19960425 00710 CE 1996 4 25 96ZZZX2058 1 19960213 G 3221 169810000663 HOUSING ASSY 169810000661 BEECH 23 C23 1151242 CE NLG CRACKED G A O OTHER D INFLIGHT SEPARATION LD LANDING 1 SW 09 66710 4190 2387 NOSE LANDING GEAR DEPARTED AIRCRAFT WHILE DOING TOUCH-AND-GO LANDINGS DUE TO ATTACH HOLES FOR NLG HOUSING ASSEMBLY BEING CRACKED OUT. TWO HOLES HAD BEEN CRACKED PREVIOUSLY. SUBMITTER STATED THIS AREA IS NOT ACCESSIBLE DURING INSPECTIONS. 1 L 7 1 3O A1CE 1996042500711 19960425 00711 CE 1996 4 25 96ZZZX2059 1 19960328 G 2571 07120591 SUPPORT CESSNA 182 182Q 2072732 CE BATTERY CRACKED D A K NONE O OTHER IN INSP/MAINT 1 EA 25 4821N 2389 18267393 THE SUPPORTS THAT HOLD THE BATTERY WERE FOUND CRACKED. SEPARATION OF THESE SUPPORTS WOULD CAUSE THE BATTERY TO MOVE ARO UND BEHIND THE REAR BULKHEAD, POSSIBLY GOING INTO CONTROL CABLES OR SHORTING THE ELECTRICAL SYSTEM. SUBMITTER STATED TH IS IS THE THIRD AIRCRAFT IN A ROW THAT THIS PROBLEM WAS FOUND. 1 H 7 1 3O NT 3A13 1996042500712 19960425 00712 SO 1996 4 25 96ZZZX2060 1 19960320 G 2710 6755001 SUPPORT PIPER PA28 PA28R180 7102809 SO AIL BELLCRANK CRACKED D A K NONE O OTHER IN INSP/MAINT 1 EA 25 7614J 5431 28R31006 DURING A ROUTINE ANNUAL INSPECTION, BOTH LOWER AILERON BELLCRANK BRACKETS WERE FOUND CRACKED BY THE FORWARD BOLT. SUBMI TTER STATED THIS IS MOST LIKELY CAUSED BY EITHER IMPROPERLY ADJUSTED AILERON STOPS OR BY NOT 'TYING' THE CONTROLS WHILE THE AIRCRAFT IS PARKED. THIS WAS FOUND TWO OTHER TIMES ON PA28-180'S. FAILURE OF THIS BRACKET WILL CAUSE LOSS OF AILER ON CONTROL. 1 L 7 1 3O 2A13 1996042500713 19960425 00713 SO 1996 4 25 96ZZZX2061 1 19960319 G 5230 99938002 LATCH ROD PIPER PA34 PA34200T 7103406 SO FWD BAG DOOR WORN B S APCR K NONE O OTHER IN INSP/MAINT 1 NM 01 4490F 347670339 FORWARD BAGGAGE DOOR AFT LATCH ROD IS WORN PARTIALLY THROUGH JUST BEHIND COTTER PIN HOLE. 1 L 7 2 3O A7SO 1996042500714 19960425 00714 CE 1996 4 25 96ZZZX2062 1 19960301 G 2822 FITTING CESSNA 182 TR182 2072735 CE FUEL PUMP WRONG PART D K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 11 150DB 1560 R18201641 WRONG TYPE FITTING IN ELECTRIC FUEL PUMP RESTRICTED FUEL FLOW. 1 H 7 1 3O 3A13 1996042500715 19960425 00715 EA 1996 4 25 96ZZZX2063 2 19960327 G 7414 ES10382585 CONTACT ASSY BENDIX S1227 PIPER PA28 PA28R200 7102811 SO LYC O360 IO360C1C 41514 EA MAGNETO LOOSE D K NONE O OTHER IN INSP/MAINT 1 EA 25 7693C 907002 28R7635113 L657751A DURING 100-HOUR INSPECTION AND C/W AD 78-9-7R3 (BENDIX IMPULSE COUPLING AND PIN INSP), THE MAIN CONTACT ASSY WAS FOUND L OOSE AND SURROUNDING AREA FROSTED. AGAIN, THE MOUNTING SCREWS WERE TIGHT, BUT THE MFG ASSY SCREW AND NUT WERE LOOSE CAU SING CONTACT HALVES TO DRIFT FROM ALIGNMENT. THE CONTACTS TOTAL TIME WAS UNKNOWN, BUT ESTIMATING BY THE LOOKS, THEY HAD NO MORE THAN 500 HOURS ON THEM. DATE FOUND WAS 3-22-96. 1 L 7 1 3O 3 O 2A13 1E10 1996042500716 19960425 00716 EA 1996 4 25 96ZZZX2064 2 19960327 G 7414 ES10382585 CONTACT ASSY BENDIX D2000 CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA MAGNETO LOOSE D K NONE R PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 EA 25 739NT 413 8324738 17270680 RL460276T ENGINE FAILED TO MAKE FULL STATIC RPM ON GROUND. UPON FURTHER INSPECTION, IT WAS DETERMINED TO BE A MAGNETO PROBLEM. U PON OPENING MAG COVER, BOTH SETS OF CONTACTS WERE FOUND TO BE LOOSE. THE CONTACT ASSY SCREW (NOT MOUNTING SCREWS) WERE DETERMINED TO BE LOOSE. CONTACT HALVES WERE MISALIGNED WITH ONE ANOTHER CAUSING EXCESSIVE FROSTING AROUND ENTIRE CONTAC T AREA AND ON DISTRIBUTOR CAP. 1 H 7 1 3O 3 O NT 3A12 E274 1996042500717 19960425 00717 1996 4 25 96ZZZX2065 1 19960406 G 3510 89501077 OXYGEN CYLINDER SCOTT OXYGEN SYSTEM IMPROPER MARK B RU2R K NONE W INADEQUATE Q C IN INSP/MAINT 1 CE 03 281009 OXYGEN CYLINDER ASSY WAS RECEIVED FOR HYDROTEST. UPON RECEIVING, INSPECTION COULD NOT LOCATE DOT NR OR RATING FOR CYLIN DER. SUSPECT THAT THIS CYLINDER WAS A PROTOTYPE NOT INTENDED FOR USE, BUT IT HAS BEEN IN SERVICE SINCE 3-84. 1996042500718 19960425 00718 SO 1996 4 25 96ZZZX2066 2 19960308 G 8520 633620 CRANKSHAFT CESSNA 340 340CESSNA 2076404 CE CONT O520 TSIO520J 17040 SO NR 3 MAIN BRG FAILED G A UNSCHED LANDING Y ENGINE STOPPAGE CR CRUISE 1 EA 23 78S 6209 1140 10991 3400151 20818870J AFTER TAKEOFF WHILE IN LEVEL FLIGHT, THE PILOT EXPERIENCED A SUDDEN ENGINE SEIZURE ON THE RT ENGINE. AN UNEVENTFUL LAND ING WAS MADE. THE CRANK WAS FOUND BROKEN AT THE NR 3 MAIN BEARING SADDLE BETWEEN THE NR 4 AND NR 5 ROD THROW. THERE WA S CATASTROPHIC DAMAGE INSIDE AND OUTSIDE THE ENGINE TO CASES, CYLINDERS, AND COMPONENTS. THE NR 5 ROD WAS TORN LOOSE FR OM ITS THROW. LOGS SHOWED THE CRANK TO BE OF AIRMELT TYPE AND HAD BEEN GROUND .010 INCH UNDER AT LAST OVERHAUL 1,140 HR S AGO. CAUSE OF CRACK COULD NOT BE DETERMINED. ENGINE WAS A R.A.M. CONVERSION. 1 L 7 2 3O 3 O 3A25 E8CE 1996042500719 19960425 00719 SO 1996 4 25 96ZZZX2067 1 19960331 G 3230 UPLOCK HOOK PIPER PA31T PA31T3 7103128 SO NLG ICED OVER D A O UNSCHED LANDING OTHER O OTHER CL CLIMB 1 AL 01 217CS 8915 31T8275014 AFTER TAKEOFF, PILOT REPORTED NOSE GEAR WOULD NOT LOCK UP. LOWERED GEAR AND RETURNED WITHOUT INCIDENT. FOUND ICE ON UP LOCK HOOK AND UPLOCK ROLLER, CLEANED, AND LUBRICATED NOSE GEAR, RETRACT TEST OK. 1 L 7 2 3T A8EA 1996042500720 19960425 00720 SO 1996 4 25 96ZZZX2068 2 19960325 G 8540 SA539800M15 CLUTCH SPRING 641348A8 CONT O360 TSIO360EB 17025 SO STARTER FAILED B QX2R K NONE O OTHER IN INSP/MAINT 1 EA 11 1 311356 CLUTCH SPRING WOUND ITSELF AROUND STARTER SHAFT GEAR AND WOULD NOT ALLOW ENGINE TO START. 3 O E9CE 1996050200102 19960502 00102 CE 1996 5 2 96ZZZX2069 1 19960327 G 2120 1013841733 CHECK VALVE BEECH 300 300BEECH 1152930 CE CABIN AIR BROKEN B SJ7R K NONE O OTHER IN INSP/MAINT 1 SO 01 194LJ 3949 FA89 THE TWO FLAPPER VALVES THAT STOP AIR FROM EXITING TO ENGINE BROKE LOOSE AND LODGED IN DUCT WORK. VALVES MIGRATED TO THE END OF DUCT AND SLOWED THE FLOW OF PRESSURE AIR TO THE AFT CABIN AND ROUTED ALL TO THE COCKPIT CAUSING TEMPERATURE TO B E VERY HOT IN COCKPIT. 2 L 7 2 4T A24CE 1996050200103 19960502 00103 CE 1996 5 2 96ZZZX2070 1 19960403 G 5541 04330106 SPAR CESSNA 150 150M 2071830 CE RUD UPPER HINGE CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 01 8313U 5608 15077918 CRACKS ORIGINATING FROM BOTH SIDES OF 1 INCH HOLE IN SPAR JUST BELOW THE UPPER HINGE BRACKETS. THE NEW SPAR (SAME PART NR) DOES NOT HAVE THIS HOLE. REFER TO ALERTS 180, 192, AND 205, AND SB 94-3A. THE SUBMITTER'S SPECULATION IN ALERT 192 IS PROBABLY CORRECT, WIND GUSTS CAN SLAM THE RUDDER AGAINST ITS STOPS LOCATED ON THE HORN AT THE BOTTOM OF THE RUDDER W HILE THE INERTIA OF THE WEIGHT AT THE TOP OF THE RUDDER APPLIED A TWISTING MOTION THROUGH THE SPAR. THE NEAREST WEAK PO INT IS THIS 1 INCH HOLE. 1 H 7 1 3O 3A19 1996050200104 19960502 00104 CE 1996 5 2 96ZZZX2071 1 19960408 G 5540 04310282 BRACKET CESSNA 150 A152 2071836 CE RUD HINGE ATTACH EXCESS WEAR D K NONE O OTHER IN INSP/MAINT 1 NM 01 761UA 4375 1520986 APRIL 8, 1996 - 4,375.0 TACHOMETER. 4,350.0 TTAF. WHILE INSPECTING RUDDER SPAR PER CESSNA SB SEB-94-3, FOUND RUDDER SP AR IN NEED OF REPLACING PER THE DESCRIPTION OF THE SB. UPON DISASSEMBLY OF RUDDER AND SPAR, FOUND ALL OF THE UPPER RUDD ER HINGE PIVOT ATTACHMENT BRACKETS SEVERELY WORN AT POINT OF CONTACT TO VERTICAL FIN. SUBMITTER RECOMMENDS ALL RUDDER A TTACHMENT BRACKETS BE INSPECTED ON AIRCRAFT WITH MORE THAN 4,000 HRS TIME IN SERVICE AND DURING THE CESSNA SB SEB-94 INS PECTION. 1 H 7 1 3O 3A19 1996050200105 19960502 00105 CE 1996 5 2 96ZZZX2072 1 19960408 G 5540 04310284 BRACKET CESSNA 150 A152 2071836 CE RUD HINGE ATTACH EXCESS WEAR D K NONE O OTHER IN INSP/MAINT 1 NM 01 761UA 4375 1520986 APRIL 8, 1996 - 4,375.0 TACHOMETER. 4,350.0 TTAF. WHILE INSPECTING RUDDER SPAR PER CESSNA SB SEB-94-3, FOUND RUDDER SP AR IN NEED OF REPLACING PER THE DESCRIPTION OF THE SB. UPON DISASSEMBLY OF RUDDER AND SPAR, FOUND ALL OF THE UPPER RUDD ER HINGE PIVOT ATTACHMENT BRACKETS SEVERELY WORN AT POINT OF CONTACT TO VERTICAL FIN. SUBMITTER RECOMMENDS ALL RUDDER A TTACHMENT BRACKETS BE INSPECTED ON AIRCRAFT WITH MORE THAN 4,000 HRS TIME IN SERVICE AND DURING THE CESSNA SB SEB-94 INS PECTION. 1 H 7 1 3O 3A19 1996050200106 19960502 00106 CE 1996 5 2 96ZZZX2073 1 19960408 G 5540 04310286 BRACKET CESSNA 150 A152 2071836 CE RUD HINGE ATTACH EXCESS WEAR D K NONE O OTHER IN INSP/MAINT 1 NM 01 761UA 4375 1520986 APRIL 8, 1996 - 4,375.0 TACHOMETER. 4,350.0 TTAF. WHILE INSPECTING RUDDER SPAR PER CESSNA SB SEB-94-3, FOUND RUDDER SP AR IN NEED OF REPLACING PER THE DESCRIPTION OF THE SB. UPON DISASSEMBLY OF RUDDER AND SPAR, FOUND ALL OF THE UPPER RUDD ER HINGE PIVOT ATTACHMENT BRACKETS SEVERELY WORN AT POINT OF CONTACT TO VERTICAL FIN. SUBMITTER RECOMMENDS ALL RUDDER A TTACHMENT BRACKETS BE INSPECTED ON AIRCRAFT WITH MORE THAN 4,000 HRS TIME IN SERVICE AND DURING THE CESSNA SB SEB-94 INS PECTION. 1 H 7 1 3O 3A19 1996050200107 19960502 00107 EA 1996 5 2 96ZZZX2074 2 19960228 G 8530 LW13561 CYLINDER BEECH 60 B60 1153605 CE LYC O541 TIO541E1C4 41536 EA NR 4 EXH ROCKER FAILED B BKHR K NONE O OTHER IN INSP/MAINT 1 WP 01 294D 829 P451 RL98559 DURING ENGINE RUN-UP FOR TAKEOFF, ENGINE QUIT. INVESTIGATION BY BORESCOPE FOUND NR 4 CYLINDER EXHAUST VALVE NOT WORKING . REMOVED ROCKER BOSS AND FOUND EXHAUST VALVE ROCKER SHAFT INBOARD ROCKER BOSS CASTING AND COVER TAB FAILED. OUTBOARD CASTING OK. ALL OTHER CYLINDERS ROCKER CASTINGS OK. SUSPECT ROCKER RETAIN CLIP FAILED INITIALLY. 1 L 7 2 3O 3 O A12CE E10EA 1996050200108 19960502 00108 CE 1996 5 2 96ZZZX2075 1 19960411 G 5521 RIB BEECH 90 E90 1152914 CE LT ELEVATOR MISINSTALLED B FTKR K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 19 20S LW267 DURING ROUTINE INSPECTION AFTER AIRCRAFT WAS PAINTED, FOUND CRACK IN HINGE. FOUND UPPER RIVETS WORKING ON OUTBOARD RIB FLANGE. REMOVED ELEVATOR TIP CAP AND FOUND OUTBOARD RIB ATTACHMENT HOLES MISSING REAR PART OF RIB. REPLACED RIB AND RI B FLANGE. STOP DRILLED CRACK AND INSTALLED SURFACE PATCH. BALANCED ELEVATOR AND REINSTALLED. SUSPECT CAUSE DUE TO IMP ROPER ASSEMBLY DURING MANUFACTURE AND ELEVATOR OUT OF BALANCE AFTER BEING PAINTED. 1 L 7 2 3T 3A20 1996050200109 19960502 00109 CE 1996 5 2 96ZZZX2076 1 19960411 G 5521 SKIN BEECH 90 E90 1152914 CE LT ELEVATOR CRACKED B FTKR K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 19 20S LW267 DURING ROUTINE INSPECTION AFTER AIRCRAFT WAS PAINTED, FOUND CRACK IN HINGE. FOUND UPPER RIVETS WORKING ON OUTBOARD RIB FLANGE. REMOVED ELEVATOR TIP CAP AND FOUND OUTBOARD RIB ATTACHMENT HOLES MISSING REAR PART OF RIB. REPLACED RIB AND RI B FLANGE. STOP DRILLED CRACK AND INSTALLED SURFACE PATCH. BALANCED ELEVATOR AND REINSTALLED. SUSPECT CAUSE DUE TO IMP ROPER ASSEMBLY DURING MANUFACTURE AND ELEVATOR OUT OF BALANCE AFTER BEING PAINTED. 1 L 7 2 3T 3A20 1996050200110 19960502 00110 GL 1996 5 2 96ZZZX2077 3 19960401 G 6114 MS150011 GREASE FITTING PIPER PA44 PA44180 7104402 SO HARTZL HCC2Y HCC2YR2 GL PROPELLER FAILED D K NONE O OTHER IN INSP/MAINT 1 SO 15 21113 338 447995040 AU8050 WRITE-UP BY PILOT STATED PROPELLER WAS SLINGING GREASE ON BLADES. MAINTENANCE INSPECTION FOUND GREASE ZERK FITTING HAD FAILED INTERNALLY AND THE CHECK BALL AND SPRING WAS PUSHED INTO THE PROPELLER HUB BY GREASE PRESSURE WHEN HUB WAS SERVIC ED AT LAST 100-HOUR INSPECTION. 1 L 7 2 3O A19S0 5 C P920 1996050200111 19960502 00111 CE 1996 5 2 96ZZZX2078 1 19960404 G 3246 C1630060103 WHEEL ASSY CESSNA 206 U206G 2073356 CE RT MLG CRACKED B WWKR K NONE O OTHER IN INSP/MAINT 1 AL 03 732PT 529 61 U20604705 AIRCRAFT WAS MODIFIED BY INSTALLING GAR-AERO WHEEL ADAPTERS AND 8:50X10 TIRES PER STC SA4305WE WITH THE EXCEPTION - INST ALLED ON MCCAULEY WHEELS INSTEAD OF CLEVELAND WHEELS WITH A FIELD APPROVAL, 60.5 HRS AGO. THIS AIRCRAFT HAD A LIGHT DUT Y WHEEL, PN C163006-0103, ON RT SIDE THAT FAILED (INNER WEBBING AND PARTING SURFACES CRACKED). THE LEFT SIDE HAD HEAVY DUTY PN C163006-0102 THAT DID NOT FAIL BUT SHOWED SIGNS ON MATING SURFACE OF FRETTING AND BOLTS LOOSE. 1 H 7 1 3O A4CE 1996050200113 19960502 00113 SO 1996 5 2 96ZZZX2080 1 19960402 G 5712 7847504 RIB ASSY PIPER PA28 PA28R180 7102809 SO WS 49.25 RT CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 25 7614J 5431 28R31006 DURING C/W PIPER AD 95-20-7, THE RIB ASSYS ON BOTH SIDES WERE FOUND CRACKED UNDERNEATH THE DRAG BRACE STUD BRACKETS. CR ACKS WERE APPROXIMATELY 2 TO 3 INCHES LONG. REPLACEMENT OF THE RIB ASSYS ARE REQUIRED. SUBMITTER STATED THE NEW RIBS A RE MADE OF THICKER MATERIAL IN THIS AREA. 1 L 7 1 3O 2A13 1996050200114 19960502 00114 SO 1996 5 2 96ZZZX2081 1 19960402 G 5712 7847505 RIB ASSY PIPER PA28 PA28R180 7102809 SO WS 49.25 LT CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 25 7614J 5431 28R31006 DURING C/W PIPER AD 95-20-7, THE RIB ASSYS ON BOTH SIDES WERE FOUND CRACKED UNDERNEATH THE DRAG BRACE STUD BRACKETS. CR ACKS WERE APPROXIMATELY 2 TO 3 INCHES LONG. REPLACEMENT OF THE RIB ASSYS ARE REQUIRED. SUBMITTER STATED THE NEW RIBS A RE MADE OF THICKER MATERIAL IN THIS AREA. 1 L 7 1 3O 2A13 1996050200115 19960502 00115 SO 1996 5 2 96ZZZX2082 2 19960403 G 8550 640726 TUBE ASSY CESSNA 421 421C 2076016 CE CONT O520 GTSIO520* 17032 SO FUEL MANIFOLD FAILED C A UNSCHED LANDING K FLUID LOSS CR CRUISE 1 SW 99 6867L 890 421C1087 R610188 DURING FLIGHT, OIL WAS NOTICED ON THE RIGHT NACELLE, THE AIRCRAFT LANDED SAFELY AND THE PROPELLER WAS FEATHERED. INVEST IGATION REVEALED TUBE ASSEMBLY FROM THE CRANKCASE TO THE FUEL MANIFOLD HAD BROKEN FROM THE SOLDER JOINT CLOSEST TO THE F UEL MANIFOLD. 1 L 7 2 3O 3 O A7CE E7CE 1996050200116 19960502 00116 SW 1996 5 2 96ZZZX2083 1 19960404 G 3233 321400 ACTUATOR DUKES MOONEY M20 M20F 5870214 SW MLG FAILED B FMOR O OTHER J WARNING INDICATION AP APPROACH 1 SO 15 24KD 2804 700047 LANDING GEAR FAILED TO EXTEND ELECTRICALLY. MANUAL EXTENSION WAS ATTEMPTED WITH NO EXTENSION. AIRCRAFT LANDED WITH WHE ELS UP. INVESTIGATION REVEALED DUKES ACTUATOR (PN 3214-00) PINION GEAR (ADDRESSED IN AD 75-23-04) WORN BEYOND LIMITS CA USING PINION AND DRIVE GEAR TO SLIP UNDER LOAD RESULTING IN TOTAL ELECTRIC AND MANUAL BACKUP FAILURE. RECORDS INDICATE C/W AD 75-23-04, 33 HOURS PRIOR. 1 L 7 1 3O 2A3 1996050200117 19960502 00117 1996 5 2 96ZZZX2084 1 19960326 G 2822 1D212 PUMP AIRBORNE FUEL BOOST FAILED D K NONE O OTHER NR NOT REPORTED 1 GL 13 5K198 FUEL PUMP MOTOR ARMATURE SEGMENT FAILED CAUSING EXCESSIVE BRUSH WEAR. 1996050200118 19960502 00118 SO 1996 5 2 96ZZZX2085 1 19960328 G 7922 75944 VALVE PIPER PA31 PA31325 7103105 SO THERMO BYPASS NUT MISSING D K NONE O OTHER IN INSP/MAINT 1 NM 01 3539C 1714 317912109 LOCKNUT ON VALVE CAME LOOSE. UPON INSPECTION, NUT WAS MISSING. C/W SB 518C. SUBMITTER SUGGESTS BETTER QUALITY CONTROL AT MFG. 1 L 7 2 3O A20SO 1996050200119 19960502 00119 SO 1996 5 2 96ZZZX2086 1 19960304 G 5230 DOOR LATCH PIPER PA34 PA34200T 7103406 SO NOSE BAG CHAFE DOOR B APCR K NONE O OTHER IN INSP/MAINT 1 NM 01 666HL 11839 347770235 NOSE BAGGAGE DOOR, LOWER CENTER LATCH HAS WORN A NOTCH IN FIBERGLASS DOOR, AFT OF LATCH. ALLOWS KEY TO BE REMOVED WHEN DOOR IS OPENED AND UNLOCKED. SITUATION APPLIES TO AD 88-04-05 AND SB 872. 1 L 7 2 3O A7SO 1996050200120 19960502 00120 SO 1996 5 2 96ZZZX2087 1 19960304 G 5230 96937003 LATCH ROD PIPER PA34 PA34200T 7103406 SO NOSE BAG DOOR WORN B APCR K NONE O OTHER IN INSP/MAINT 1 NM 01 666HL 11839 347770235 DURING INSPECTION OF AIRFRAME FOUND EXCESSIVE PLAY IN NOSE BAGGAGE DOOR LOCK PUSHRODS. WHERE RODS ATTACH TO LOCKING MEC HANISM JUST AFT OF COTTER PIN HOLE, WORN THROUGH 50 PERCENT. (AD 88-04-05 AND SB 872 AND SB 633B APPLIES TO THIS AREA.) 1 L 7 2 3O A7SO 1996050200121 19960502 00121 SO 1996 5 2 96ZZZX2088 1 19960304 G 5230 96938002 LATCH ROD PIPER PA34 PA34200T 7103406 SO NOSE BAG DOOR WORN B APCR K NONE O OTHER IN INSP/MAINT 1 NM 01 666HL 11839 347770235 DURING INSPECTION OF AIRFRAME, FOUND EXCESSIVE PLAY IN NOSE BAGGAGE DOOR LOCK PUSHRODS. WHERE RODS ATTACH TO LOCKING ME CHANISM JUST AFT OF COTTER PIN HOLE, WORN THROUGH 50 PERCENT. (AD 88-04-05 AND SB 872 AND SB 633B APPLIES TO THIS AREA. ) 1 L 7 2 3O A7SO 1996050200122 19960502 00122 SO 1996 5 2 96ZZZX2089 1 19960319 G 5230 96938003 LATCH ROD PIPER PA34 PA34200T 7103406 SO FWD BAG DOOR WORN B APCR K NONE O OTHER IN INSP/MAINT 1 NM 01 4490F 347670339 FORWARD BAGGAGE DOOR, FORWARD LATCH ROD IS PARTIALLY WORN THROUGH JUST BEHIND COTTER PIN HOLE. 1 L 7 2 3O A7SO 1996050200123 19960502 00123 NE 1996 5 2 96ZZZX2090 2 19960402 G 7314 105970 NOZZLE MFP45 BAG BAE146 BAE146300A 1500267 EU LYC ALF502 ALF502R5 41580 NE FUEL PUMP FRACTURED H O OTHER Y ENGINE STOPPAGE CR CRUISE 1 WP 05 616AW 6108 E3145 LF05016 ENGINE SHUT DOWN IN-FLIGHT. FOUND NOZZLE FRACTURED AND ENTERED GEARS CAUSING DRIVE SHAFT TO SHEAR. PUMP IS BEING SENT TO C.E.C.O. (MANUFACTURER) FOR INVESTIGATION. 2 H 7 4 4F 4 F RT A49EU E6NE 1996050200124 19960502 00124 CE 1996 5 2 96ZZZX2091 1 19960403 G 3230 2307006166 HOSE LEAR 35 31A 5170531 CE RT MLG ACTUATOR LEAKING D K NONE K FLUID LOSS IN INSP/MAINT 1 AL 01 789SR 225 31083 HOSE LEAKING FROM BOTH SWAGED ENDS WHEN LANDING GEAR IS EXTENDED. 2 L 7 2 4F RT A10CE 1996050200125 19960502 00125 CE 1996 5 2 96ZZZX2092 1 19960403 G 3240 2307006113 HOSE LEAR 35 31A 5170531 CE RT BRAKE LEAKING D K NONE K FLUID LOSS IN INSP/MAINT 1 AL 01 789SR 225 31083 HOSE ASSEMBLY LEAKING HYDRAULIC FLUID THROUGH THE WALLS OF THE NOSE WHEN THE BRAKES ARE APPLIED. 2 L 7 2 4F RT A10CE 1996050200126 19960502 00126 NE 1996 5 2 96ZZZX2093 2 19960409 G 7530 8008311001L7 CONTROL CESSNA 500 560CESSNA 2076750 CE PWA JT15 JT15D5 52112 NE BLEED VALVE MALFUNCTIONED E A UNSCHED LANDING R M PARTIAL RPM/PWR LOSS OVER TEMP CL CLIMB 1 GL 07 312QS 740 5600312 500109 ON TAKEOFF, THE RIGHT ENGINE RPM ROLLED BACK 10 PERCENT AND THE I.T.T. INCREASED TO 700 DEGREES. AIRCRAFT RETURNED AND ENGINE WAS INSPECTED. NO PROBLEM WAS FOUND. AIRCRAFT WAS TEST FLOWN AND NR 2 ENGINE I.T.T. WAS 50 DEGREES HIGHER. FOU ND BLEED VALVE OPERATING ON GROUND WHEN NOT CALLED FOR. BLEED VALVE CONTROL AND BLEED VALVE ACTUATOR WERE REPLACED AND PROBLEM CORRECTED. 2 L 7 2 4F 4 F RT A22CE E25EA 1996050200127 19960502 00127 NE 1996 5 2 96ZZZX2094 2 19960409 G 7532 F008881L1 ACTUATOR CESSNA 500 560CESSNA 2076750 CE PWA JT15 JT15D5 52112 NE BLEED VALVE MALFUNCTIONED E A UNSCHED LANDING R M PARTIAL RPM/PWR LOSS OVER TEMP CL CLIMB 1 GL 07 312QS 740 F22028 5600312 500109 ON TAKEOFF, THE RIGHT ENGINE RPM ROLLED BACK 10 PERCENT AND THE I.T.T. INCREASED TO 700 DEGREES. AIRCRAFT RETURNED AND ENGINE WAS INSPECTED. NO PROBLEM WAS FOUND. AIRCRAFT WAS TEST FLOWN AND NR 2 ENGINE I.T.T. WAS 50 DEGREES HIGHER. FOU ND BLEED VALVE OPERATING ON GROUND WHEN NOT CALLED FOR. BLEED VALVE CONTROL AND BLEED VALVE ACTUATOR WERE REPLACED AND PROBLEM CORRECTED. 2 L 7 2 4F 4 F RT A22CE E25EA 1996050200128 19960502 00128 CE 1996 5 2 96ZZZX2095 1 19960410 G 5280 45A3038110 HINGE BEECH MU300 400BEECH CE LT MLG DOOR CRACKED B AWKR K NONE O OTHER IN INSP/MAINT 1 WP 25 510WS 1459 RJ24 DURING AN 'A' INSPECTION, HAIR LINE CRACKS WERE DETECTED ON THE END CAP BEAM AT THE FORWARD GEAR DOOR HINGE LOCATION (PN 45A30314-005 AND 006). FURTHER INVESTIGATION REVEALED FORWARD GEAR DOOR HINGES TO BE CRACKED ON THE RT AND LT MAIN GEA R DOORS. 2 H 7 2 4F RT A16SW 1996050200129 19960502 00129 CE 1996 5 2 96ZZZX2096 1 19960410 G 5280 45A303819 HINGE BEECH MU300 400BEECH CE RT MLG DOOR CRACKED B AWKR K NONE O OTHER IN INSP/MAINT 1 WP 25 510WS 1459 RJ24 DURING AN 'A' INSPECTION, HAIR LINE CRACKS WERE DETECTED ON THE END CAP BEAM AT THE FORWARD GEAR DOOR HINGE LOCATION (PN 45A30314-005 AND 006). FURTHER INVESTIGATION REVEALED FORWARD GEAR DOOR HINGES TO BE CRACKED ON THE RT AND LT MAIN GEA R DOORS. 2 H 7 2 4F RT A16SW 1996050200130 19960502 00130 CE 1996 5 2 96ZZZX2097 1 19960207 G 3010 45AS66010009 HEATER TIP BEECH MU300 400BEECH CE LT ELEV HORN BURNED B VIB3 K NONE M OVER TEMP IN INSP/MAINT 1 SO 03 445CC 801 RK45 THE WIRE INSIDE THE HEATED ELEVATOR HORN TIP SHORT CIRCUITED AND BURNED. SUBMITTER SUGGESTS THE SHORT MAY HAVE BEEN CAU SED FROM THE HEATED HORN ASSY CHAFING ON THE ELEVATOR. 2 H 7 2 4F RT A16SW 1996050200131 19960502 00131 NE 1996 5 2 96ZZZX2098 2 19960329 G 7261 3030391 OIL PUMP CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE RT ENGINE DEFECTIVE E K NONE O OTHER IN INSP/MAINT 1 EA 07 245CC 2029 5500212 70663 RIGHT ENGINE WOULD SMOKE DURING ENGINE START. TROUBLSHOOTING SHOWED OIL SCAVAGE PUMP WAS WEAK. REMOVED AND REPLACED OI L PUMP ASSY. SB 7185 HAD BEEN C/W. 1 L 7 2 4F 4 F A22CE E1NE 1996050200132 19960502 00132 EA 1996 5 2 96ZZZX2099 1 19960329 G 7110 215M0000501 COWL CNDAIR CL600 CL6001A11 1900302 EA LT NACELLE CRACKED B JO1R K NONE O OTHER IN INSP/MAINT 1 EA 25 91UC 020096041 1051 FOUND 12 INCH CRACK ON NOSE COWL REAR FRAME TO BARREL ATTACH ANGLE AT ABOUT 10 O'CLOCK POSITION LOOKING FORWARD. SUBMIT TER STATED CAUSE UNKNOWN. ENGINE VIBS WELL WITHIN LIMITS. NOSE COWL HAD EXTENSIVE REPAIRS. 2 L 7 2 4F RT A21EA 1996050200133 19960502 00133 EA 1996 5 2 96ZZZX2100 1 19960322 G 5280 MS20253P5100L PIN 600316661 CNDAIR CL600 CL6002A12 1900304 EA LT GEAR DOOR BROKEN D K NONE O OTHER IN INSP/MAINT 1 EA 21 999JR 2852 3061 PIN WAS FOUND BROKEN ON 600-HOUR INSPECTION. THIS IS THE LATEST PART. THE OLDER STYLE PIN AND HINGE WERE BREAKING THE HINGE PORTION. NO HINGE FROM ALERT SB A601-0329. 2 L 7 2 4F RT A21EA 1996050200134 19960502 00134 CE 1996 5 2 96ZZZX2101 1 19960320 G 2913 710501 MOTOR AIRIGHT 10138800515 BEECH 300 300BEECH 1152930 CE POWER PACK FAILED G O OTHER J WARNING INDICATION AP APPROACH 1 GL 03 63LB 933 58 FA18 LANDING GEAR WOULD NOT EXTEND. PUMPED GEAR DOWN MANUALLY WITH NO PROBLEM. FOUND MOTOR ON POWER PACK WAS FROZEN. POSSI BLE SEAL LEAKAGE ON POWER PACK HAD EFFECT ON MOTOR. 2 L 7 2 4T A24CE 1996050200135 19960502 00135 CE 1996 5 2 96ZZZX2102 1 19960320 G 2913 HP50A1 POWER PACK BEECH 300 300BEECH 1152930 CE LANDING GEAR DEFECTIVE G K NONE O OTHER IN INSP/MAINT 1 GL 03 63LB 2 174C FA18 POWER PACK WAS INSTALLED PER 300 MM. AFTER FIRST HOUR, THE GEAR WOULD CYCLE EVERY 15-20 SECONDS. NO EXTERNAL LEAKAGE F OUND. REMOVED AND REPLACED POWER PACK AND NEW POWER PACK FUNCTIONED OK. 2 L 7 2 4T A24CE 1996050200137 19960502 00137 CE 1996 5 2 96ZZZX2104 1 19960404 G 5210 SEAL CESSNA 500 S550 2076607 CE DOOR LEAKAGE D G B A O2 MASK DEPLOYED EMER. DESCENT UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 GL 07 106QS 9367 S5500106 AIRCRAFT FLYING AT 37,000 FEET. LOST PRESSURIZATION. MASK DROPPED AND AIRCRAFT DESCENDED. PASSENGERS WERE ON BOARD. A IRCRAFT INSPECTED BY MAINTENANCE PERSONNEL FROM A CESSNA SERVICE CENTER AND NO PROBLEM COULD BE FOUND. AIRCRAFT WAS FER RIED TO SERVICE CENTER. FOUND SEVERAL SMALL LEAKS AND A SMALL HOLE IN THE DOOR SEAL. SEALED THE LEAKS, REPLACED THE DO OR SEAL, AND BUILT THE DOOR FRAME UP TO GIVE THE SEAL A MORE POSITIVE SEAT. 1 L 7 2 4F RT A22CE 1996050200138 19960502 00138 CE 1996 5 2 96ZZZX2105 1 19960404 G 3222 084200036 AXLE CESSNA 500 560CESSNA 2076750 CE NLG CORRODED D K NONE O OTHER IN INSP/MAINT 1 EA 11 39N 254 5600243 NOSE LANDING GEAR AXLE WAS INSTALLED NEW, 12-27-95, 1716.4 ACFT HRS. REMOVED FROM SERVICE 4-3-96, 1970.4 ACFT HRS. SEV ERE CORROSION ON INNER WALLS OF TUBE. 2 L 7 2 4F RT A22CE 1996050200140 19960502 00140 EU 1996 5 2 96ZZZX2107 1 19960326 G 2844 Z00M7809178074 TRANSDUCER SOCATA TBM TBM700 8682000 EU FUEL PRESSURE FAILED D O OTHER J WARNING INDICATION NR NOT REPORTED 1 GL 15 300AF 203 03940037 97 FUEL PRESSURE WOULD DROP TO ZERO POUNDS IN-FLIGHT AT TIMES. NOTE: THIS IS THE THIRD TRANSDUCER TO GO BAD ON THIS AIRCR AFT. FIRST ONE LASTED 155 HRS. SECOND ONE LASTED 120 HRS, AND THE THIRD ONE LASTED 203 HRS. 1 L 7 1 3T RT A60EU 1996050200141 19960502 00141 GL 1996 5 2 96ZZZX2108 3 19960307 G 6110 COUNTERWEIGHT MTSBSI MU2 MU2B35 5780411 CE HARTZL HCB3T HCB3TN5 GL DOWEL PIN HOLE CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 6569L 645 BU2089 PROPELLER COUNTERWEIGHT DOWEL PIN HOLE IS CRACKED. 1 H 7 2 3T RT A10SW 6 C P15EA 1996050200142 19960502 00142 GL 1996 5 2 96ZZZX2109 3 19960307 G 6110 B30283 BRACKET MTSBSI MU2 MU2B35 5780411 CE HARTZL HCB3T HCB3TN5 GL PROP START LOCK CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 6569L 645 BU2120 PROPELLER INSPECTION FOUND 2 EACH START LOCK BRACKETS CRACKED. 1 H 7 2 3T RT A10SW 6 C P15EA 1996050200143 19960502 00143 GL 1996 5 2 96ZZZX2110 3 19960307 G 6110 1901 LINK ARM MTSBSI MU2 MU2B35 5780411 CE HARTZL HCB3T HCB3TN5 GL PROPELLER CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 6569L 645 BU2089 PROPELLER LINK ARM IS CRACKED BETWEEN HOLES IN LINK ARM. 1 H 7 2 3T RT A10SW 6 C P15EA 1996050200144 19960502 00144 GL 1996 5 2 96ZZZX2111 3 19960307 G 6110 1891 PILOT TUBE MTSBSI MU2 MU2B35 5780411 CE HARTZL HCB3T HCB3TN5 GL NR 2 SPIDER ARM CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 6569L 645 BU2120 LONGITUDINAL CRACKS FOUND IN PILOT TUBE OF NR 2 SPIDER ARM. 1 H 7 2 3T RT A10SW 6 C P15EA 1996050200145 19960502 00145 GL 1996 5 2 96ZZZX2112 3 19960307 G 6110 1891 PILOT TUBE MTSBSI MU2 MU2B35 5780411 CE HARTZL HCB3T HCB3TN5 GL NR 3 SPIDER ARM CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 6569L 645 BU2120 LONGITUDINAL CRACKS FOUND IN PILOT TUBE OF NR 3 SPIDER ARM. 1 H 7 2 3T RT A10SW 6 C P15EA 1996050200146 19960502 00146 1996 5 2 96ZZZX2113 4 19960410 G 3416 2056011 INDICATOR SMITHSIND BOEING 737 737* NM SERVOED ALTITUDE WRONG CONNECTOR D P K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 15 150 THIS UNIT WAS RECEIVED FOR OVERHAUL. WHEN THE UNIT WAS OPENED, FOUND THE CONNECTORS P3 AND J3 WERE NOT THE CORRECT TYPE PER CMM 34-10-16. 2 L 7 2 4F RT A16WE 1996050200147 19960502 00147 SW 1996 5 2 96ZZZX2114 1 19960410 G 5220 2622107001 SEAL 2622105001 SWRNGN SA226 SA226T 8780122 SW EMERGENCY HATCH MISINSTALLED G A K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 25 200SN T354 ATTEMPT TO REMOVE THE EMERGENCY EXIT FOR ACCESS FOR OTHER MAINTENANCE WAS UNSUCCESSFUL BY ONE PERSON. EXIT HAD TO BE PR IED FROM ACFT USING A SCREWDRIVER WHILE 2 PERSONS PULLED ON THE EXIT FROM WITHIN CABIN. INSPECTION OF EXIT REVEALED SOM E FORM OF SEALANT HAD BEEN APPLIED TO THE CORNERS OF THE EXIT SEAL BONDING THE EXIT TO ACFT AND PREVENTING ITS REQUIRED OPERATION. THE ACFT HAD UNDERGONE A LETTER CHECK 'B' INSPECTION WITHIN 5 HOURS PRIOR TO THIS OCCURRENCE WHICH REQUIRES THE EMERGENCY EXIT BE FUNCTIONAL TESTED AND INSPECTED FOR OPERATION. 2 L 7 2 4T RT A5SW 1996050200148 19960502 00148 NE 1996 5 2 96ZZZX2115 2 19960209 G 7313 231001101 NOZZLE 2163620 BAG BAE146 BAE146300A 1500267 EU LYC ALF502 ALF502R5 41580 NE FUEL MANIFOLD FLANGE CRACKED B S PGLR K NONE O OTHER IN INSP/MAINT 1 SO 13 NOZZLE FLANGE CRACKED APPROXIMATELY 75 PERCENT OF DISTANCE AROUND CIRCUMFERENCE. FOUND USING FPI. VISIBLE ON BOTH SIDE S OF FLANGE UNDER BLACK LIGHT. SUSPECT CAUSE, IMPROPER TORQUE. 2 H 7 4 4F 4 F RT A49EU E6NE 1996050200263 19960502 00263 SO 1996 5 2 96ZZZX2141 1 19960301 G 7603 455358 CONTROL CABLE PS501461313 PIPER PA32 PA32300 7103212 SO THROTTLE BROKEN D K NONE O OTHER IN INSP/MAINT 1 SW 99 21183 1981 327840184 BROKEN THROTTLE CABLE. THE THROTTLE CABLE BROKE WHILE IN THE SHOP BEING CHECKED FOR STIFFNESS IN MOVEMENT. 1 L 7 1 3O A3SO 1996050200264 19960502 00264 SO 1996 5 2 96ZZZX2142 1 19960321 G 2434 ALU8421LS ALTERNATOR PRESTOLITE PIPER PA32 PA32R301 7103218 SO DC SYSTEM WRONG PART B G9NR K NONE W INADEQUATE Q C IN INSP/MAINT 1 EA 07 9779J 1243 8Y000133 3213024 DURING THE COURSE OF AN ANNUAL INSPECTION, DISCOVERED A 24-VOLT ALTERNATOR WAS INSTALLED ON A 12-VOLT SYSTEM. PART INST ALLED WAS ALU-8421LS, 24-VOLT, 70-AMP. ACCORDING TO THE PARTS BOOK PER SERIAL NUMBER OF AIRCRAFT, UNIT SHOULD BE A P/N ALY6421, 12-VOLT, 60-AMP ALTERNATOR. 1 L 7 1 3O A3SO 1996050200265 19960502 00265 CE 1996 5 2 96ZZZX2143 1 19960419 G 2497 WIRE BEECH 18 E18S 1151006 CE COPILOT PANEL CHAFED G A B F UNSCHED LANDING EMER. DESCENT ACTIVATE FIRE EXT. A FLAME/FIRE CR CRUISE 1 EA 03 PILOT REPORTED COCKPIT FIRE/SMOKE AND MADE EMERG DESCENT CONTAINING FIRE WITH HAND EXTINGUISHER. SPARKS AND ENG OIL OBS ERVED COMING FROM BEHIND COPILOT'S INSTRUMENT PANEL AND RT ENG WAS SHUT DOWN. ULTIMATELY, PILOT EXECUTED EMERG LANDING WITH NO INJURIES OR DAMAGE. INVESTIGATION REVEALED A WIRE BUNDLE BEHIND CO-PILOT'S INSTRUMENT PANEL HAD CHAFED AGAINST A 'HARD' LINE FOR RT ENG OIL PRESS PLUMBING SHORTING OUT AND CAUSING FIRE (A/C TIME, 15,400 HRS). INVESTIGATING FSDO CO NTACTED A BE-18 OPERATOR AND RELATED INCIDENT ASKING OPER TO CHK AREA ON A/C. OPER RESPONDED THAT A SIMILAR SITUATION W AS OBSERVED, 'BUS' WIRE BUNDLE FND RESTING AGAINST OIL PRESS GAUGE PLUMBING & HAD EVIDENCE OF CHAFING (A/C TIME, 13,777) 1 L 7 2 3R A765 1996050200266 19960502 00266 SO 1996 5 2 96ZZZX2144 1 19960207 G 2430 9937705 SWITCH PIPER PA32 PA32RT300T 7103216 SO MASTER FAILED D S A A UNSCHED LANDING H J ELECT. POWER LOSS-50 PC WARNING INDICATION CL CLIMB 1 SW 99 132RR 1655 32R7987098 AIRCRAFT LOST ALL ELECTRICAL POWER AFTER GEAR WAS RETRACTED ON DEPARTURE. GEAR EXTENDED USING OVERRIDE AND UNEVENTFUL L ANDING MADE. INSPECTION REVEALED THAT BATTERY SIDE OF MASTER SWITCH WAS INOPERATIVE NOT ALLOWING THE MASTER SOLENOID TO FIND GROUND AND KEEP THE ELECTRICAL SYSTEM ON LINE. LANDING LIGHT SWITCH ON THE SAME PANEL WAS REPLACED DUE TO FAILURE 57 HOURS EARLIER. NUMEROUS CORRODED SCREWS AND MOISTURE WERE FOUND IN THE SAME GENERAL AREA. MASTER SWITCH HAD SLIGHT CORROSION. RECOMMEND INSPECTION OF SIDE PANEL AND REPLACEMENT OF CRITICAL SWITCHES IF ANY EVIDENCE OF CORROSION IS FOU ND. 1 L 7 1 3O A3SO 1996050200267 19960502 00267 CE 1996 5 2 96ZZZX2145 1 19960409 G 7810 3595000539 EXHAUST BEECH 36 A36 1151604 CE RT EXHAUST CRACKED B S WC7R K NONE O OTHER IN INSP/MAINT 1 GL 25 7230D E2281 TAT: 1,999.5 HRS. DURING REGULAR ENGINE OIL CHANGE, MECHANIC NOTICED EXHAUST STAINS ON VACUUM PUMP. UPON CLOSER INSPE CTION, FOUND RT EXHAUST STACK CRACKED AND SPLIT. LENGTH ABOUT 4 INCHES BY .50 INCH WIDE. SPLIT WAS DIRECTLY BELOW AREA WHERE ALL 3 CYLINDERS DUMP INTO STACK. STARTED ALONG WELD SEAM. 1 L 7 1 3O 3A15 1996050200268 19960502 00268 SO 1996 5 2 96ZZZX2146 1 19960410 G 3230 452853 ROD END BEARING PIPER PA46 PA46310P 7104605 SO NLG ACTUATOR BROKEN D L K NONE O OTHER TO TAKEOFF 1 SO 15 701TF 4608140 PILOT LANDED AIRCRAFT ON SOD RUNWAY WITH NUMEROUS SOFT SAND PITS CAUSING ACTUATOR SHAFT TO BEND. PLANS WERE MADE FOR TA KEOFF WITH SHORT FIELD EFFORT. UPON RELEASING THE BRAKES, AIRCRAFT MOVED FORWARD 14 FEET BEFORE ROD END FAILED. PILOT COULD HAVE SAVED PROPELLER AND ENGINE IF ACTUATOR SHAFT HAD BEEN VISUALLY CHECKED PRIOR TO TAKEOFF. HAVE NO REASON TO B ELIEVE THE PART WAS DEFECTIVE NOR WAS THE ACTUATOR BENT PRIOR TO LANDING. GEAR RETRACTED AND EXTENDED PROPERLY AT THE L AST POINT OF DEPARTURE. 1 L 7 1 3O A25SO 1996050200271 19960502 00271 CE 1996 5 2 96ZZZX2149 1 19960408 G 2730 07341102AGW TORQUE TUBE CESSNA 188 A188B 2073005 CE RT ELEVATOR LOOSE RIVETS D A K NONE O OTHER IN INSP/MAINT 1 EA 21 731VX 2916 18803200T DURING ANNUAL INSPECTION, FOUND 6 EACH LOOSE ('WORKING') AN470AD5 RIVETS IN RIGHT ELEVATOR TORQUE TUBE ASSY AT TUBE/ATTA CH FLANGE JOINT TO ELEVATOR ARM, PN 1234029-1AGW. FOUND DEFECT BY MOVING TRAILING EDGE OF LT AND RT ELEVATOR IN OPPOSIT E UP AND DOWN MOTION USING LIGHT TO MODERATE FORCE AND FELT AS WELL AS SAW MOTION IN RIVET JOINT. REMOVED RIVETS AND FO UND 'SHEAR' DAMAGE TO RIVET GRIPS. REPLACED RIVETS TO REPAIR. 1 L 7 1 3O A9CE 1996050200272 19960502 00272 SO 1996 5 2 96ZZZX2150 2 19960320 G 8530 652954A1 CYLINDER CESSNA 206 U206A 2073316 CE CONT O520 IO520A 17032 SO CYLS 2,6,1,3,5 CRACKED D K NONE O OTHER IN INSP/MAINT 1 AL 03 4975U 778 U20605179 284679R NR 2, NR 6, NR 1, NR 3, AND NR 5 CYLINDERS WERE FOUND CRACKED AT INTAKE SEAT. 1 H 7 1 3O 3 O A4CE E5CE 1996050200273 19960502 00273 SO 1996 5 2 96ZZZX2151 2 19960301 G 8530 652954A1 CYLINDER CESSNA 206 U206 2073306 CE CONT O520 IO520A 17032 SO CYLS NR 4, 1 CRACKED D K NONE O OTHER IN INSP/MAINT 1 AL 03 4672U 540 U20605046 284695R NR 4 AND NR 1 CYLINDERS WERE FOUND CRACKED AT INTAKE SEAT. 1 H 7 1 3O 3 O A4CE E5CE 1996050200274 19960502 00274 SO 1996 5 2 96ZZZX2152 2 19960320 G 8530 652954A1 CYLINDER CESSNA 206 U206 2073306 CE CONT O520 IO520A 17032 SO CYLS NR 3, 2, 5 CRACKED D K NONE O OTHER IN INSP/MAINT 1 AL 03 244PL 760 4371 28468R NR 3, NR 2, AND NR 5 CYLINDERS WERE FOUND CRACKED AT INTAKE SEAT. 1 H 7 1 3O 3 O A4CE E5CE 1996050200275 19960502 00275 GL 1996 5 2 96ZZZX2153 3 19960409 G 6111 FC8465B6 BLADE BEECH 55 95B55 1152706 CE HARTZL HCC2Y BHCC2YF2 GL SHANK UNDER SIZE D K NONE O OTHER IN INSP/MAINT 1 SW 99 17978 D22145 TC2063 AN252 INSPECTION FOUND BOTH BLADES OF THE PROPELLER ASSEMBLY TO BE UNDER MINIMUM SHANK DIAMETER. SUBMITTER STATED BLADE SHANK S WERE PROBABLY REWORKED UNDER DIMENSION AT LAST PROPELLER SERVICE. 1 L 7 2 3O 3A16 5 C P920 1996050200276 19960502 00276 GL 1996 5 2 96ZZZX2154 3 19960409 G 6111 FC8465B6 BLADE BEECH 55 95B55 1152706 CE HARTZL HCC2Y BHCC2YF2 GL SHANK UNDER SIZE D K NONE O OTHER IN INSP/MAINT 1 SW 99 17978 D22161 TC2063 AN252 INSPECTION FOUND BOTH BLADES OF THE PROPELLER ASSEMBLY TO BE UNDER MINIMUM SHANK DIAMETER. SUBMITTER STATED BLADE SHANK S WERE PROBABLY REWORKED UNDER DIMENSION AT LAST PROPELLER SERVICE. 1 L 7 2 3O 3A16 5 C P920 1996050200277 19960502 00277 GL 1996 5 2 96ZZZX2155 3 19960409 G 6114 D220118 HUB BEECH 55 95B55 1152706 CE HARTZL HCC2Y BHCC2YF2 GL PRELOAD AREA DAMAGED D K NONE O OTHER IN INSP/MAINT 1 SW 99 17978 TC2063 AN252 HUB WAS FOUND TO HAVE DAMAGE TO PRELOAD RETENTION AREA. SUBMITTER STATED DAMAGE POSSIBLY OCCURRED FROM STRIKE DAMAGE TO ONE OR MORE BLADES. 1 L 7 2 3O 3A16 5 C P920 1996050200278 19960502 00278 GL 1996 5 2 96ZZZX2156 3 19960409 G 6111 FC8465B6 BLADE BEECH 55 95B55 1152706 CE HARTZL HCC2Y BHCC2YF2 GL SHANK UNDER SIZE D K NONE O OTHER IN INSP/MAINT 1 SW 99 17978 D22142 TC2063 AN3264 BOTH BLADES OF THE PROPELLER ASSEMBLY WERE FOUND TO BE UNDER MINIMUM SHANK DIAMETER. SUBMITTER STATED BLADE SHANKS WERE PROBABLY REWORKED UNDER DIMENSION AT LAST PROPELLER SERVICE. 1 L 7 2 3O 3A16 5 C P920 1996050200279 19960502 00279 GL 1996 5 2 96ZZZX2157 3 19960409 G 6111 FC8465B6 BLADE BEECH 55 95B55 1152706 CE HARTZL HCC2Y BHCC2YF2 GL SHANK UNDER SIZE D K NONE O OTHER IN INSP/MAINT 1 SW 99 17978 D22444 TC2063 AN3264 BOTH BLADES OF THE PROPELLER ASSEMBLY WERE FOUND TO BE UNDER MINIMUM SHANK DIAMETER. SUBMITTER STATED BLADE SHANKS WERE PROBABLY REWORKED UNDER DIMENSION AT LAST PROPELLER SERVICE. 1 L 7 2 3O 3A16 5 C P920 1996050200281 19960502 00281 EA 1996 5 2 96ZZZX2159 2 19960223 G 8530 LW11634 VALVE CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA NR 1 CYL EXH STUCK D A UNSCHED LANDING E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 WP 09 757CM 2581 15279633 L1480515 AIRCRAFT WAS ON TRAINING FLIGHT AFTER PERFORMING ROUTINE MANEUVERS. ENGINE BEGAN TO RUN ROUGH. A FORCED OFF-FIELD LAND ING WAS MADE WITHOUT DAMAGE TO AIRCRAFT, HOWEVER, INSPECTION ON ENGINE REVEALED STUCK VALVE (EXHAUST) ON NR 1 CYLINDER. 1 H 7 1 3O 3 O NT 3A19 E223 1996050200283 19960502 00283 SO 1996 5 2 96ZZZX2161 2 19960401 G 7414 CONTACT POINTS SLICK 6320 CESSNA 414 414A 2075907 CE CONT O520 TSIO520NB 17040 SO LT ENG LT MAG CORRODED B CRJR K NONE O OTHER IN INSP/MAINT 1 CE 01 135BG 92080002 414A0419 521195 JUST PRIOR TO AIRCRAFT BEING INDUCTED FOR 100-HOUR INSPECTION, PILOT INFORMED MAINTENANCE OF ROUGH RT MAG ON RT ENGINE. INVESTIGATION SHOWED SEVERE CORROSION ON POINTS, GEARS, CAPACITOR, AND BEARINGS. CHECK REMAINING 3 MAGNETOS AND FOUND IDENTICAL CONDITIONS OF SEVERE CORROSION. ALL FOUR MAGNETOS WERE CLEANED AND AFFECTED PARTS WERE REPLACED. PROBLEM BEL IEVED TO BE CAUSED BY PRESSURIZED AIR FROM TURBOS. 1 L 7 2 3O 3 O A7CE E8CE 1996050200284 19960502 00284 SO 1996 5 2 96ZZZX2162 2 19960401 G 7414 CONTACT POINTS SLICK 6320 CESSNA 414 414A 2075907 CE CONT O520 TSIO520NB 17040 SO RT ENG LT MAG CORRODED B CRJR K NONE O OTHER IN INSP/MAINT 1 CE 01 135BG 93020037 414A0419 521195 JUST PRIOR TO AIRCRAFT BEING INDUCTED FOR 100-HOUR INSPECTION, PILOT INFORMED MAINTENANCE OF ROUGH RT MAG ON RT ENGINE. INVESTIGATION SHOWED SEVERE CORROSION ON POINTS, GEARS, CAPACITOR, AND BEARINGS. CHECK REMAINING 3 MAGNETOS AND FOUND IDENTICAL CONDITIONS OF SEVERE CORROSION. ALL FOUR MAGNETOS WERE CLEANED AND AFFECTED PARTS WERE REPLACED. PROBLEM BEL IEVED TO BE CAUSED BY PRESSURIZED AIR FROM TURBOS. 1 L 7 2 3O 3 O A7CE E8CE 1996050200285 19960502 00285 SO 1996 5 2 96ZZZX2163 2 19960401 G 7414 CONTACT POINTS SLICK 6320 CESSNA 414 414A 2075907 CE CONT O520 TSIO520NB 17040 SO LT ENG RT MAG CORRODED B CRJR K NONE O OTHER IN INSP/MAINT 1 CE 01 135BG 92080010 414A0419 521195 JUST PRIOR TO AIRCRAFT BEING INDUCTED FOR 100-HOUR INSPECTION, PILOT INFORMED MAINTENANCE OF ROUGH RT MAG ON RT ENGINE. INVESTIGATION SHOWED SEVERE CORROSION ON POINTS, GEARS, CAPACITOR, AND BEARINGS. CHECK REMAINING 3 MAGNETOS AND FOUND IDENTICAL CONDITIONS OF SEVERE CORROSION. ALL FOUR MAGNETOS WERE CLEANED AND AFFECTED PARTS WERE REPLACED. PROBLEM BEL IEVED TO BE CAUSED BY PRESSURIZED AIR FROM TURBOS. 1 L 7 2 3O 3 O A7CE E8CE 1996050200286 19960502 00286 SO 1996 5 2 96ZZZX2164 2 19960401 G 7414 CONTACT POINTS SLICK 6320 CESSNA 414 414A 2075907 CE CONT O520 TSIO520NB 17040 SO RT ENG RT MAG CORRODED B CRJR K NONE O OTHER IN INSP/MAINT 1 CE 01 135BG 93020044 414A0419 521195 JUST PRIOR TO AIRCRAFT BEING INDUCTED FOR 100-HOUR INSPECTION, PILOT INFORMED MAINTENANCE OF ROUGH RT MAG ON RT ENGINE. INVESTIGATION SHOWED SEVERE CORROSION ON POINTS, GEARS, CAPACITOR, AND BEARINGS. CHECK REMAINING 3 MAGNETOS AND FOUND IDENTICAL CONDITIONS OF SEVERE CORROSION. ALL FOUR MAGNETOS WERE CLEANED AND AFFECTED PARTS WERE REPLACED. PROBLEM BEL IEVED TO BE CAUSED BY PRESSURIZED AIR FROM TURBOS. 1 L 7 2 3O 3 O A7CE E8CE 1996050200287 19960502 00287 CE 1996 5 2 96ZZZX2165 1 19960329 G 2520 521912514 SEAT CESSNA 402 402C 207590R CE PAX NR 4 FAILED E K NONE O OTHER IN INSP/MAINT 1 WP 19 2610Z 244 402C0068 WHEN LOADING PASSENGERS, A PASSENGER WAS LEANING ON THE SEAT BACK OF NR 4 SEAT AND THE SEAT BUCKET SEPARATED FROM THE PE DESTAL. THIS SEAT WAS A REPLACEMENT SEAT INSTALLED APPROXIMATELY 3 MONTHS AGO AFTER THE EXACT SAME PROBLEM OCCURRED. T HE STC'D SEATS WERE ORIGINALLY INSTALLED IN THIS AIRCRAFT ON DECEMBER 18, 1995 AT 9,805 HRS TOTAL TIME. THE STC NR IS S A 2715CE FOR THE SINGLE PASSENGER SEAT. SUBMITTER RECOMMENDS DAILY INSPECTIONS BE MADE TO THE SEATS ESPECIALLY AREA OF THE 'HOURGLASS' SEAT PEDESTAL. ALSO, RECOMMEND CESSNA MULTIENGINE BULLETIN MEB 87-9 BE CONSIDERED A MANDATORY INSTALLAT ION. AIRCRAFT TOTAL TIME FOR THIS REPORT IS 10,048.8 HOURS. 1 L 7 2 3O A7CE 1996050200288 19960502 00288 CE 1996 5 2 96ZZZX2166 1 19960324 G 3250 AN4H4AM BOLT 960000601 BEECH 55 95C55 1152708 CE NLG BROKEN D K NONE O OTHER IN INSP/MAINT 1 SW 07 65AC 8000 TE242 NOSE LANDING GEAR BOLTS, 2 EACH, BROKE CAUSING STEERING PROBLEMS WHICH CAUSED KNEE (SCISSORS) PN 96-820020-1 TO BREAK ON LANDING. SUSPECT CAUSE OF BOLTS TO BREAK WAS TURNING NOSE GEAR TOO MUCH TO THE LEFT OR RIGHT WHEN THE AIRCRAFT WAS TOW ED PRIOR TO FLIGHT. 1 L 7 2 3O 3A16 1996050200289 19960502 00289 CE 1996 5 2 96ZZZX2167 1 19960205 G 5102 CABLE HEAD AX888 AX888HEAD 05637T7 CE BASKET ELONGATED B RG1R K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 01 8307M 82 218 THE MALFUNCTION CONSISTS OF ELONGATION OF THE EYES ON THE BASKET SUSPENSION CABLES. THIS CONDITION WAS FOUND DURING A R OUTINE ANNUAL INSPECTION AND CLEARLY FALLS OUTSIDE THE MANUFACTURER'S CRITERIA FOR AIRWORTHINESS. WHEN THE MANUFACTURER SENT REPLACEMENT PARTS, IT WAS EVIDENT THAT INCORRECT PARTS WERE ORIGINALLY INSTALLED. 1 B 0 0 A29SO2 1996050200290 19960502 00290 SO 1996 5 2 96ZZZX2168 1 19960205 G 2435 8013C GENERATOR PIPER PA31T PA31T 7103124 SO START/GEN RT SHORTED D L K NONE O OTHER NR NOT REPORTED 1 SO 11 515BA 2989 251 161 31T8120044 INVESTIGATION FOR UNCONTROLLED OVERVOLTAGE CONDITION FOUND SHORTED STARTER/GENERATOR ON RT ENGINE. 1 L 7 2 3T A8EA 1996050200291 19960502 00291 SO 1996 5 2 96ZZZX2169 2 19960208 G 7314 50611043 VANE 6462103 CESSNA 404 404CESSNA 2075901 CE CONT O520 GTSIO520M 17032 SO FUEL PUMP WRONG PART D L K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 09 255CS 240 K179403BR 4040019 276435R SUBMITTER STATES NUMEROUS FAILURES WITH FUEL PUMP VANE PN 50611043. CORRECT VANE PN IS 635549. FURTHER STATES PROBLEM REQUIRES URGENT ACTION DUE TO NUMBERS AND TYPE OF FAILURES. 1 L 7 2 3O 3 O A25CE E7CE 1996050200292 19960502 00292 CE 1996 5 2 96ZZZX2170 1 19960205 G 2730 05133711 BRACKET CESSNA 172 172G 2072420 CE ELEV BELLCRANK BROKEN D A K NONE O OTHER IN INSP/MAINT 1 SO 13 4250L 6731 17254319 DURING ANNUAL INSPECTION, NOTED EXCESS MOVEMENT REQUIRED IN ELEVATOR CONTROL TO PRODUCE ANY MOVEMENT IN ELEVATOR. INVES TIGATION SHOWED ELEVATOR BELLCRANK BRACKET BROKEN LOOSE FROM FRONT STRINGER AND ALL BUT ONE RIVET ON THE REAR STRINGER. REPLACED BRACKET WITH NEW ITEM WHICH HAS BEEN SUBSTANTIALLY STRENGTHENED. SUBMITTER STATED THIS BRACKET HAS BEEN SUBJE CT OF NO FEWER THAN 5 PREVIOUS MDR'S. NO CAUSE DETERMINED. RECOMMEND ONE TIME INSPECTION OF ALL AIRCRAFT WITH THIS BRA CKET INSTALLED. 1 H 7 1 3O NT 3A12 1996050200293 19960502 00293 SW 1996 5 2 96ZZZX2171 1 19960404 G 3244 650X8 TIRE MCCREARY RKWELL 700 700 7630520 SW RIM BEAD RUPTURED H A O OTHER O OTHER TX TAXI/GRND HDL 1 SW 11 4EP 32 B3L6335 00032 TIRE BLEW OUT ON TAXI AFTER NORMAL LANDING. FRACTURE AT THE OUTER EDGE OF RIM BEAD. FOUR LANDINGS LATER ON TAXI TO TAK EOFF, OTHER TIRE FAILED IN THE SAME PLACE. BOTH TIRES WERE INSTALLED 11-20-95 AND FAILED 3-19-96 AND 3-26-96. 1 L 7 2 3O A12SW 1996050200294 19960502 00294 CE 1996 5 2 96ZZZX2172 1 19960327 G 2730 05130633 BRACKET CESSNA 172 172F 2072414 CE ELEV BELLCRANK FAILURE D A K NONE O OTHER IN INSP/MAINT 1 SW 99 5682R 5000 17253323 FOUND FATIGUE FAILURE OF THE ELEVATOR FORWARD BELLCRANK BRACKET. SUSPECT CAUSED BY A STRONG TAIL WIND AT THE TIE-DOWN L OCATION, FLEXING THE ELEVATOR AGAINST THE CONTROL COLUMN LOCK. 1 H 7 1 3O NT 3A12 1996050200295 19960502 00295 CE 1996 5 2 96ZZZX2173 1 19960416 G 3230 504501019 TORQUE TUBE CESSNA 340 340A 2076405 CE LT MLG WELL CRACKED D A K NONE O OTHER IN INSP/MAINT 1 NM 11 6311X 3706 340A0482 DURING ROUTINE ANNUAL INSPECTION, LT LANDING GEAR TORQUE TUBE FOUND CRACKED APPROXIMATELY 2 INCHES AROUND WELD AT CLEVIS BOSS FOR OVERCENTER LINK. SUBMITTER REPORTS FINDING THIS CONDITION ON 4 OTHER MODEL 340 AIRCRAFT. 1 L 7 2 3O 3A25 1996050200296 19960502 00296 CE 1996 5 2 96ZZZX2174 1 19960401 G 2720 PEDAL BBAVIA 8 8KCAB 2110612 CE LT FWD RUDDER FAILED H A LP8S K NONE O OTHER IN INSP/MAINT 1 NE 01 5061K 35 56079 INSTALLED THE 4TH RUDDER PEDAL. THIRTY-FIVE HOURS TACH TIME ON THE THIRD RUDDER PEDAL BEFORE FAILURE. 1 H 7 1 3O A21CE 1996050200297 19960502 00297 EA 1996 5 2 96ZZZX2175 1 19960402 G 3020 601970975 VALVE CNDAIR CL601 CL6013A 8070802 EA COWL ANTI-ICE FAILED D K NONE O OTHER IN INSP/MAINT 1 SW 05 417CL 033 5107 RECEIVED AND INSTALLED REPAIRED COWL ANTI-ICE VALVE. VALVE FAILED ON FIRST FLIGHT. SUBMITTER STATED THESE VALVES HAVE A VERY HIGH FAILURE RATE. 2 L 7 2 4F RT A21EA 1996050200298 19960502 00298 EA 1996 5 2 96ZZZX2176 2 19960328 G 8530 65007 RETAINER PIPER PA28 PA28181 7102807 SO LYC O360 O360A4M 41514 EA INTAKE PUSHROD CRACKED D K NONE K FLUID LOSS IN INSP/MAINT 1 WP 17 8172Q 500 288090263 L2803436A PUSHROD TUBE ON NR 2 CYLINDER INTAKE HAS A PERSISTENT OIL LEAK NEAR THE CRANKCASE. WHEN CHANGING THE PUSHROD TUBE SEAL THIS TIME, THE PUSHROD TUBE RETAINER WHICH IS PRESSED INTO THE CRANKCASE WAS FOUND CRACKED ABOUT ONE-FOURTH OF THE WAY A ROUND THE CIRCUMFERENCE. 1 L 7 1 3O 3 O 2A13 E286 1996050200300 19960502 00300 EA 1996 5 2 96ZZZX2178 2 19960412 G 7322 3472 VALVE SEAT MA45 CESSNA 182 182R 2072731 CE LYC O540 O540L3C5 41532 EA PUMP DISCHARGE WORN D K NONE O OTHER IN INSP/MAINT 1 CE 01 58JK 656 75030510 18268286 ENGINE RUNNING EXTREMELY RICH. FOUND PUMP DISCHARGE CHECK VALVE SEAT WORN OFF. 1 L 7 1 3O 3 O NT 3A13 E295 1996050200301 19960502 00301 EA 1996 5 2 96ZZZX2179 2 19960412 G 7322 3472 VALVE SEAT CESSNA 182 182R 2072731 CE LYC O540 O540L3C5 41532 EA PUMP DISCHARGE WORN D K NONE O OTHER IN INSP/MAINT 1 CE 01 2427E 880 18268202 ENGINE RUNNING EXCESSIVELY RICH. FOUND PUMP DISCHARGE CHECK VALVE SEAT WORN OFF. 1 L 7 1 3O 3 O NT 3A13 E295 1996050200302 19960502 00302 SO 1996 5 2 96ZZZX2180 1 19960408 G 7160 HEAT VALVE MAULE MX7 MX7180 5460185 SO CARBURETOR AIR DETERIORATED D K NONE O OTHER IN INSP/MAINT 1 WP 11 5666N 808 11024C DURING HEAT VALVE INSPECTION PER MAULE SB 16 (2-20-96) REFERENCE SL NR 56 (2-27-96) FOUND ON VISUAL INSPECTION, NO DEFEC TS, BUT WHEN SLIGHT PULL PRESSURE APPLIED, THE RED SILICONE RUBBER SEPARATED. 1 H 7 1 3O NC 3A23 1996050200303 19960502 00303 SO 1996 5 2 96ZZZX2181 1 19960404 G 7922 75944 VALVE PIPER PA23 PA23250 7102308 SO THERMO BYPASS CRIMP NUT LOOSE D K NONE O OTHER IN INSP/MAINT 1 EA 05 6256Y 3828 69503 273495 LYCOMING SB 518C APPLIES. NUT LOOSE ON END OF VERNATHERM, PROBABLY DUE TO VIBRATION. REPLACED DEFECTIVE PART WITH A NE W PART NOT CALLED OUT IN THE SERVICE BULLETIN. 1 L 7 2 3O 1A10 1996050200304 19960502 00304 CE 1996 5 2 96ZZZX2182 1 19960404 G 7922 75944 VALVE CESSNA 150 152 2071835 CE THERMO BYPASS CRIMP NUT LOOSE D K NONE O OTHER IN INSP/MAINT 1 EA 05 65464 4021 9255 15281567 LYCOMING SB 518C APPLIES. NUT LOOSE ON END OF VERNATHERM, PROBABLY DUE TO VIBRATION. REPLACED DEFECTIVE PART WITH A NE W PART NOT CALLED OUT IN THE SERVICE BULLETIN. 1 H 7 1 3O NT 3A19 1996050200305 19960502 00305 CE 1996 5 2 96ZZZX2183 1 19960404 G 7922 75944 VALVE CESSNA 172 172P 2072436 CE THERMO BYPASS CRIMP NUT LOOSE D K NONE O OTHER IN INSP/MAINT 1 EA 05 51804 2721 105188 17274351 LYCOMING SB 518C APPLIES, NUT LOOSE ON END OF VERNATHERM. PROBABLY DUE TO VIBRATION. REPLACED DEFECTIVE PART WITH A NE W PART NOT CALLED OUT IN THE SERVICE BULLETIN. 1 H 7 1 3O NT 3A12 1996050200306 19960502 00306 SO 1996 5 2 96ZZZX2184 1 19960404 G 7922 75944 VALVE GULSTM AA5 AA5B 3960105 SO THERMO BYPASS CRIMP NUT LOOSE D K NONE O OTHER IN INSP/MAINT 1 EA 05 28395 2261 94320 AA5B0588 LYCOMING SB 518C APPLIES, NUT LOOSE ON END OF VERNATHERM. PROBABLY DUE TO VIBRATION. REPLACED DEFECTIVE PART WITH A NE W PART NOT CALLED OUT IN THE SERVICE BULLETIN. 1 L 7 1 3O A16EA 1996050200307 19960502 00307 CE 1996 5 2 96ZZZX2185 1 19960404 G 7922 75944 VALVE CESSNA 172 172K 2072430 CE THERMO BYPASS CRIMP NUT LOOSE D K NONE O OTHER IN INSP/MAINT 1 EA 05 7410G 3861 17259110 LYCOMING SB 518C APPLIES, NUT LOOSE ON END OF VERNATHERM, PROBABLY DUE TO VIBRATION. REPLACED DEFECTIVE PART WITH A NEW PART NOT CALLED OUT IN THE SERVICE BULLETIN. 1 H 7 1 3O NT 3A12 1996050200308 19960502 00308 CE 1996 5 2 96ZZZX2186 1 19960405 G 6123 99103233 BALL JOINT CESSNA 441 441 2076020 CE PROP CONTROL FAILED B FEHR O OTHER O OTHER LD LANDING 1 SO 13 910EA 4410070 AFTER LANDING WHEN REVERSE WAS SELECTED, THE LEFT ENGINE DID NOT REVERSE. INVESTIGATION REVEALED BALL SOCKET HAD WORN T O THE POINT THE BALL FELL OUT OF SOCKET AS PROPELLER CONTROL WAS MOVING AFT. THIS IS A SWAGED JOINT WITH NO SAFETY CLIP S TO PREVENT TOTAL SEPARATION. INSPECTION IS ONLY REQUIRED ON PHASE 2 AND A POSITIVE EVALUATION IS NOT POSSIBLE UNLESS INSPECTION EXCEEDS REQUIREMENTS AND ROD END IS DISCONNECTED TO ACCURATELY ASSESS WEAR BY DETERMINING ACTUAL AMOUNT OF LI NEAR MOVEMENT. 1 L 7 2 3T RT A28CE 1996050200309 19960502 00309 CE 1996 5 2 96ZZZX2187 1 19960222 G 2434 6203BRS BEARING PRESTOLITE ALV9510ECH CESSNA 402 402C 207590R CE LT ALTERNATOR FAILED D O OTHER J WARNING INDICATION IN INSP/MAINT 1 SO 13 51SC 289 9050464 402C0106 SHORTLY AFTER START-UP, THE LEFT ALTERNATOR LIGHT ILLUMINATED. ACFT WAS SHUT DOWN AND INSPECTED. OUTBOARD BEARING OF A LTERNATOR FOUND FAILED. UPON ALTERNATOR REMOVAL, DRIVE HUB (PN 640934) WAS ALSO FOUND FAILED. THIS ALTERNATOR DOES NOT REQUIRE THE 100-HOUR LUBE. THE RIGHT ALTERNATOR BEARING WAS INSPECTED ALSO AND FOUND SERVICEABLE, BUT NOT VERY MUCH GR EASE WAS FOUND. BOTH UNITS WERE INSTALLED AT THE SAME TIME. 1 L 7 2 3O A7CE 1996050200310 19960502 00310 CE 1996 5 2 96ZZZX2188 1 19960222 G 2434 640934 HUB PRESTOLITE ALV9510ECH CESSNA 402 402C 207590R CE ALTERNATOR DRIVE FAILED D K NONE J WARNING INDICATION IN INSP/MAINT 1 SO 13 51SC 289 9050464 402C0106 SHORTLY AFTER START-UP, THE LEFT ALTERNATOR LIGHT ILLUMINATED. ACFT WAS SHUT DOWN AND INSPECTED. OUTBOARD BEARING OF A LTERNATOR FOUND FAILED. UPON ALTERNATOR REMOVAL, DRIVE HUB (PN 640934) WAS ALSO FOUND FAILED. THIS ALTERNATOR DOES NOT REQUIRE THE 100-HOUR LUBE. THE RIGHT ALTERNATOR BEARING WAS INSPECTED ALSO AND FOUND SERVICEABLE, BUT NOT VERY MUCH GR EASE WAS FOUND. BOTH UNITS WERE INSTALLED AT THE SAME TIME. 1 L 7 2 3O A7CE 1996050200311 19960502 00311 EA 1996 5 2 96ZZZX2189 2 19960322 G 8520 75060 CONNECT ROD PIPER PA32 PA32300 7103212 SO LYC O540 IO540K1A5 41532 EA NR 6, NR 1 ROD BOLT NOT MARKED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 15 4053R 339 3240355 L794448 ENGINE DISASSEMBLED AND FOUND 3 BOLTS WITH NO HEAD MARKING. ONE EACH LOCATED ON NR 6 ROD. TWO EACH LOCATED ON NR 1 ROD . 1 L 7 1 3O 3 O A3SO 1E4 1996050200312 19960502 00312 SW 1996 5 2 96ZZZX2190 1 19960325 G 8120 LW10098L CONTROLLER MOONEY M20 M20M 5870222 SW LYC O540 TIO540AF1A 41532 EA TURBO DEFECTIVE D O OTHER R PARTIAL RPM/PWR LOSS CR CRUISE 1 NE 05 1086D 1165 SK0121L 270041 L920561A ENGINE SURGES AT FLIGHT LEVELS. SURGES 200 RPM AND 2 INCH MAP. REPLACED DIFFERENTIAL PRESSURE CONTROLLER TO C/W LYC SB WITH PN 48B21935. 1 L 7 1 30 3 O RT 2A3 E14EA 1996050200570 19960502 00570 SW 1996 5 2 96ZZZX2196 1 19960312 G 6230 206010335001 LEVER ASSY 206010350021 BELL 206 206L1 1182107 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 1084Y 445 45433 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH PN 206-010-338-00 1 SPACERS, 4 EACH PN 206-010-337-001 BEARINGS, 2 EACH PN 206-010-338-003 BUSHINGS, 2 EACH PN NAS6605D64 BOLTS, AND 1 EAC H PN 206-010-470-101 BEARING. SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 445.4 HOURS . 1 G 7 1 3U H2SW 1996050200571 19960502 00571 SW 1996 5 2 96ZZZX2197 1 19960312 G 6230 206010336005 LINK IDLER 206010350021 BELL 206 206L1 1182107 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 1084Y 445 45433 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH PN 206-010-338-00 1 SPACERS, 4 EACH PN 206-010-337-001 BEARINGS, 2 EACH PN 206-010-338-003 BUSHINGS, 2 EACH PN NAS6605D64 BOLTS, AND 1 EAC H PN 206-010-470-101 BEARING. SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 445.4 HOURS . 1 G 7 1 3U H2SW 1996050200574 19960502 00574 SW 1996 5 2 96ZZZX2200 1 19960320 G 6230 206010335001 LEVER ASSY 206010350021 BELL 206 206L4 1182110 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 170AL 532 52063 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH PN 206-010-338-00 1 SPACERS, 4 EACH PN 206-010-337-001 BEARINGS, 2 EACH PN 206-010-338-003 BUSHINGS, 2 EACH PN NAS6605D64 BOLTS, AND 1 EAC H PN 206-010-470-101 BEARING. SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 532.0 HOURS . 1 G 7 1 3U NC H2SW 1996050200575 19960502 00575 SW 1996 5 2 96ZZZX2201 1 19960320 G 6230 206010336005 LINK IDLER 206010350021 BELL 206 206L4 1182110 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 170AL 532 52063 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH PN 206-010-338-00 1 SPACERS, 4 EACH PN 206-010-337-001 BEARINGS, 2 EACH PN 206-010-338-003 BUSHINGS, 2 EACH PN NAS6605D64 BOLTS, AND 1 EAC H PN 206-010-470-101 BEARING. SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 532 HOURS. 1 G 7 1 3U NC H2SW 1996050200576 19960502 00576 SW 1996 5 2 96ZZZX2202 1 19960312 G 6230 206010335001 LEVER ASSY 206010350021 BELL 206 206L4 1182110 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 173AL 456 52066 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH PN 206-010-338-00 1 SPACERS, 4 EACH PN 206-010-337-001 BEARINGS, 2 EACH PN 206-010-338-003 BUSHINGS, 2 EACH PN NAS6605D64 BOLTS, AND 1 EAC H PN 206-010-470-101 BEARING. SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 456.0 HOURS . 1 G 7 1 3U NC H2SW 1996050200577 19960502 00577 SW 1996 5 2 96ZZZX2203 1 19960312 G 6230 206010336005 LINK IDLER 206010350021 BELL 206 206L4 1182110 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 173AL 456 52066 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH PN 206-010-338-00 1 SPACERS, 4 EACH PN 206-010-337-001 BEARINGS, 2 EACH PN 206-010-338-003 BUSHINGS, 2 EACH PN NAS6605D64 BOLTS, AND 1 EAC H PN 206-010-470-101 BEARING. SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 456 HOURS. 1 G 7 1 3U NC H2SW 1996050200578 19960502 00578 SW 1996 5 2 96ZZZX2204 1 19960320 G 6230 206010335001 LEVER ASSY 206010350021 BELL 206 206L1 1182107 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 206SL 360 45245 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH PN 206-010-338-00 1 SPACERS, 4 EACH PN 206-010-337-001 BEARINGS, 2 EACH PN 206-010-338-003 BUSHINGS, 2 EACH PN NAS6605D64 BOLTS, AND 1 EAC H PN 206-010-470-101 BEARING. SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 360.0 HOURS . 1 G 7 1 3U H2SW 1996050200579 19960502 00579 SW 1996 5 2 96ZZZX2205 1 19960320 G 6230 206010336005 LINK IDLER 206010350021 BELL 206 206L1 1182107 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 206SL 360 45245 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH PN 206-010-338-00 1 SPACERS, 4 EACH PN 206-010-337-001 BEARINGS, 2 EACH PN 206-010-338-003 BUSHINGS, 2 EACH PN NAS6605D64 BOLTS, AND 1 EAC H PN 206-010-470-101 BEARING. SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 360.0 HOURS . 1 G 7 1 3U H2SW 1996050200582 19960502 00582 SW 1996 5 2 96ZZZX2208 1 19960320 G 6230 206010335001 LEVER ASSY 206010350021 BELL 206 206L3 1182108 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 358AL 610 51460 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH PN 206-010-338-00 1 SPACERS, 4 EACH PN 206-010-337-001 BEARINGS, 2 EACH PN 206-010-338-003 BUSHINGS, 2 EACH PN NAS6605D64 BOLTS, AND 1 EAC H PN 206-010-470-101 BEARING. SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 609.6 HOURS . 1 G 7 1 3U H2SW 1996050200583 19960502 00583 SW 1996 5 2 96ZZZX2209 1 19960320 G 6230 206010336005 LINK IDLER 206010350021 BELL 206 206L3 1182108 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 358AL 610 51460 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH PN 206-010-338-00 1 SPACERS, 4 EACH PN 206-010-337-001 BEARINGS, 2 EACH PN 206-010-338-003 BUSHINGS, 2 EACH PN NAS6605D64 BOLTS, AND 1 EAC H PN 206-010-470-101 BEARING. SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 609.6 HOURS . 1 G 7 1 3U H2SW 1996050200584 19960502 00584 SW 1996 5 2 96ZZZX2210 1 19960312 G 6230 206010335001 LEVER ASSY 206010350021 BELL 206 206L1 1182107 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 3890B 315 45480 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH PN 206-010-338-00 1 SPACERS, 4 EACH PN 206-010-337-001 BEARINGS, 2 EACH PN 206-010-338-003 BUSHINGS, 2 EACH PN NAS6605D64 BOLTS, AND 1 EAC H PN 206-010-470-101 BEARING. SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 314.7 HOURS . 1 G 7 1 3U H2SW 1996050200585 19960502 00585 SW 1996 5 2 96ZZZX2211 1 19960312 G 6230 206101336005 LINK IDLER 206010350021 BELL 206 206L1 1182107 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 3890B 315 45480 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH PN 206-010-338-00 1 SPACERS, 4 EACH PN 206-010-337-001 BEARINGS, 2 EACH PN 206-010-338-003 BUSHINGS, 2 EACH PN NAS6605D64 BOLTS, AND 1 EAC H PN 206-010-470-101 BEARING. SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 314.7 HOURS . 1 G 7 1 3U H2SW 1996050200586 19960502 00586 SW 1996 5 2 96ZZZX2212 1 19960304 G 6310 206040272101 BOOT 206010015015 BELL 206 206L3 1182108 SW DRIVE SHAFT TORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 364AL 792 499 9193B 51434 DAILY AAIP FOUND BOOT TORN. DRIVE SHAFT SLINGING GREASE. 1 G 7 1 3U H2SW 1996050200587 19960502 00587 NE 1996 5 2 96ZZZX2213 1 19960328 G 2910 7665109007060 TUBE ASSY SKRSKY S76 S76A 8143006 NE NR 1 HYD PUMP CHAFED B ALGR K NONE J WARNING INDICATION IN INSP/MAINT 1 SW 03 376AL 760002 DURING GROUND RUN, NR 1 SERVO CAUTION LIGHT ILLUMINATED. AIRCRAFT WAS SHUT DOWN. DURING TROUBLESHOOTING, HYDRAULIC LIN E WAS FOUND CHAFING ON THE FIREWALL. REPLACED LINE ASSY. SERVICED AND GROUND RUN. LEAK CHECK OK. 1 G 7 2 3U H1NE 1996050200588 19960502 00588 SW 1996 5 2 96ZZZX2214 1 19960313 G 5302 214021209127 SUPPORT ANGLE BELL 214 214ST 1182106 SW TAILBOOM AFT LT CRACKED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 390AL 3612 28198 PHASE INSPECTION FOUND ANGLE CRACKED ON FORWARD END APPROXIMATELY 2 INCHES FROM END OF ANGLE. THE SUSPECT CAUSE WAS VIB RATION. 2 G 7 2 4U H10SW 1996050200591 19960502 00591 NE 1996 5 2 96ZZZX2217 1 19960318 G 6210 761500900047A BLADE SKRSKY S76 S76A 8143006 NE M/R CRACKED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 768AL 7122 469 A08600103 760031 DURING 500-HOUR INSPECTION, FOUND BLADE SPAR CRACKED AT ROOT END BUSHING HOLE. SUBMITTER STATED CAUSE UNKNOWN. 1 G 7 2 3U H1NE 1996050200592 19960502 00592 GL 1996 5 2 96ZZZX2218 2 19960307 G 7210 6889326 BEARING SKRSKY S76 S76A 8143006 NE ALLSN 250C 250C30S 03013 GL GEARBOX GALLED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 768AL MP02911 760031 890074S UPON DISASSEMBLY OF GEARBOX, CLEANED AND INSPECTED PARTS AS REQUIRED. FOUND EXCESSIVE GALLING ON PTO AFT, BEARING INNER RACE. EXCESSIVE GALLING, BEARING INNER RACE, POSSIBLY DUE TO BEARING CAGE OUT-OF-ROUND CAUSING TIGHT FIT BETWEEN INNER AND OUTER RACE AND BALLS. 1 G 7 2 3U 3 U H1NE E1GL 1996050900095 19960509 00095 EU 1996 5 9 96ZZZX2220 1 19960325 G 5320 FRAME SAAB SF340 340B 7860101 EU AFT CARGO DOOR DAMAGED B S DP2R K NONE O OTHER IN INSP/MAINT 1 SW 05 312AE 8473 340B312 FUSELAGE AFT CARGO DOOR FRAME DAMAGED ON GROUND. IMPACTED AREA REVEALED DELAMINATION AND SEPARATION OF SKIN LAYER, APPR OXIMATELY 5 INCHES BY 3.50 INCHES AT BS 685 AND WL 781. INSPECTED TRANSMISSION THROUGH ULTRASONIC. 2 L 7 2 4T RT A52EU 1996050900096 19960509 00096 EU 1996 5 9 96ZZZX2221 1 19960409 G 3010 T700A3013002101 DEICE TUBE SOCATA TBM TBM700 8682000 EU RT HORIZ STAB CHAFED B A JAVR K NONE O OTHER IN INSP/MAINT 1 NE 01 57HC 759 90 DURING ANNUAL INSPECTION, RIGHT ELEVATOR HORN DEICE BOOT AIR TUBE FOUND CHAFED AT THE 90 DEGREE BEND WHERE IT ENTERS THE ELEVATOR TIP. THE CHAFED AREA HAD CREATED A SMALL HOLE IN THE TUBE. NEW TUBE INSTALLED AND ELEVATOR OPENING FOR TUBE SLIGHTLY ENLARGED TO PREVENT CONTACT. SYSTEM OPERATIONALLY CHECKED NORMAL. ELEVATORS ARE REMOVED AT ANNUAL AND AREA SH OULD BE CHECKED. THIS LINE IS STANDARD ON S/N 50 AND UP, IT IS REQUIRED BY AD 95-11-16 SOCATA AND SB 70-020-30 FOR SERI AL NUMBERS 1 THROUGH 49. FAILURE OF LINE COULD CAUSE ELEVATOR JAMMING IN ICING CONDITIONS. 1 L 7 1 3T RT A60EU 1996050900097 19960509 00097 SW 1996 5 9 96ZZZX2222 1 19960315 G 2720 500012253 CONTROL CABLE GULSTM 690TP 690B 7630516 SW AFT RUDDER RT FRAYED B A FB2R K NONE O OTHER IN INSP/MAINT 1 SW 15 100AM 2400 11361 DURING C/W TWIN COMMANDER SB 195B, FOUND BOTH AFT RUDDER CABLES TO HAVE NUMEROUS CABLE STRANDS BROKEN. THE INSTRUCTIONS IN THE SB DO NOT ADDRESS THE REMOVAL OR INSPECTION AS OUTLINED IN AC 43.13-1A, CHAPTER 4, PARAGRAPH 198, FIGURE 4.14. T HIS PROCEDURE IS THE ONLY WAY TO PROPERLY INSPECT THESE CABLES. SUBMITTER HAS FOUND MANY AIRCRAFT WITH CABLE STRANDS BR OKEN BEYOND THE LIMITS IN THE SB WHILE INSPECTING THE CABLES IN THIS MANNER. SUBMITTER SUGGESTS OWNERS C/W SI-199 WHICH INSTALLS LARGER PULLEYS AT THIS LOCATION. 1 H 7 2 3T 2A4 1996050900098 19960509 00098 SW 1996 5 9 96ZZZX2223 1 19960315 G 2720 500012251 CONTROL CABLE GULSTM 690TP 690B 7630516 SW AFT RUDDER LT FRAYED B FB2R K NONE O OTHER IN INSP/MAINT 1 SW 15 100AM 2400 11361 DURING C/W TWIN COMMANDER SB 195B, FOUND BOTH AFT RUDDER CABLES TO HAVE NUMEROUS CABLE STRANDS BROKEN. THE INSTRUCTIONS IN THE SB DO NOT ADDRESS THE REMOVAL OR INSPECTION AS OUTLINED IN AC 43.13-1A, CHAPTER 4, PARAGRAPH 198, FIGURE 4.14. T HIS PROCEDURE IS THE ONLY WAY TO PROPERLY INSPECT THESE CABLES. SUBMITTER HAS FOUND MANY AIRCRAFT WITH CABLE STRANDS BR OKEN BEYOND THE LIMITS IN THE SB WHILE INSPECTING THE CABLES IN THIS MANNER. SUBMITTER SUGGESTS OWNERS C/W SI-199 WHICH INSTALLS LARGER PULLEYS AT THIS LOCATION. 1 H 7 2 3T 2A4 1996050900099 19960509 00099 CE 1996 5 9 96ZZZX2224 1 19960319 G 2150 631430534 ACTUATOR CESSNA 525 525 2076601 CE PRECOOLER FAIL TEST B L JGVR K NONE L NO TEST IN INSP/MAINT 1 CE 09 216CJ 551 5250016 PRE-COOLER ACTUATORS FAILED FUNCTIONAL TEST FOLLOWING COMPLETION OF SB 525-36-02. FOUND P/N 6314305-34 FITTING ORIFICE PLUGGED WITH ADHESIVE MATERIAL. ADHESIVE PRESUMED TO HAVE BEEN BLOCKING FITTING ORIFICE SINCE ORIGINAL AIRCRAFT MANUFAC TURE. SUBMITTER RECOMMENDS ONE-TIME FUNCTIONAL TEST OF ALL MODEL 525 AIRCRAFT TO DETERMINE IF OTHER AIRCRAFT ARE SIMILA RLY AFFECTED. CLEANED ADHESIVE FROM ORIFICE SYSTEM, FUNCTIONALLY CHECKED NORMALLY. 1 L 7 2 4F RT A1WI 1996050900100 19960509 00100 CE 1996 5 9 96ZZZX2225 1 19960306 G 2824 10138901133 CHECK VALVE BEECH 200 200BEECH 1152920 CE AUX XSFER PUMP LEAKING H L K NONE K FLUID LOSS IN INSP/MAINT 1 GL 13 26G 8479 BB787 FUEL CHECK VALVE HAD SOME DIRT IN THE SEAT ALLOWING FUEL TO PRESSURIZE THE AUXILIARY FUEL CELL AND LEAK AROUND THE TOP M ANHOLE PANEL. FUEL TRAVELED THROUGH THE WIRING CONDUIT ALLOWING SOME FUEL AND FUMES INTO THE CABIN AREA. 1 L 7 2 4T A24CE 1996050900101 19960509 00101 CE 1996 5 9 96ZZZX2226 1 19960306 G 5620 57190421 CLIP CESSNA 441 441 2076020 CE CABIN WINDOW RUSTED B P A CGFR K NONE O OTHER IN INSP/MAINT 1 GL 03 441ND 4410123 DURING THE REMOVAL OF THE INTERIOR AND HEADLINER IN PREPARATION FOR INSPECTION, NOTED THE SPRING STEEL CLIPS THAT RETAIN THE INNER WINDOWS WERE EXTENSIVELY RUSTED, SEVERAL TO A POINT OF TOTAL DESTRUCTION. IN ADDITION, THE MAIN CABIN STRUCT URE (TO WHICH THE CLIPS ARE RIVETED), WAS SEVERELY CORRODED. THE SPRING CLIPS ARE A STANDARD CESSNA PART, SIX CLIPS ARE USED ON EACH WINDOW. UPPER CLIPS, CESSNA, P/N 571-9042-1. LOWER CLIPS, CESSNA, P/N 571-9042-2. 1 L 7 2 3T RT A28CE 1996050900102 19960509 00102 CE 1996 5 9 96ZZZX2227 1 19960306 G 5620 57190422 CLIP CESSNA 441 441 2076020 CE CABIN WINDOW RUSTED B P CGFR K NONE O OTHER IN INSP/MAINT 1 GL 03 441ND 5994 4410123 DURING THE REMOVAL OF THE INTERIOR AND HEADLINER IN PREPARATION FOR INSPECTION, NOTED THE SPRING STEEL CLIPS THAT RETAIN THE INNER WINDOWS WERE EXTENSIVELY RUSTED, SEVERAL TO A POINT OF TOTAL DESTRUCTION. IN ADDITION, THE MAIN CABIN STRUCT URE (TO WHICH THE CLIPS ARE RIVETED), WAS SEVERELY CORRODED. THE SPRING CLIPS ARE A STANDARD CESSNA PART, SIX CLIPS ARE USED ON EACH WINDOW. UPPER CLIPS, CESSNA, P/N 571-9042-1. LOWER CLIPS, CESSNA, P/N 571-9042-2. 1 L 7 2 3T RT A28CE 1996050900103 19960509 00103 NE 1996 5 9 96ZZZX2228 2 19960403 G 7240 4059T02601 RETAINER CNDAIR CL600 CL6002B16 1900305 EA GE CF34 CF343A 30015 NE NR 5 BEARING FAILED E S A UNSCHED LANDING E VIBRATION/BUFFET CR CRUISE 1 GL 03 826JP 2656 5050 350353 PILOTS NOTICED ABNORMAL VIBRATION ON LT ENGINE OVER THE NORTH ATLANTIC. UNSCHEDULED LANDING. GE WAS CONTACTED AND ENGI NE WAS REPLACED. ON TEAR-DOWN, NR 5 BEARING RETAINER LOCK PIN FOUND TO HAVE BROKEN OFF ALLOWING BEARING TO SPIN IN ITS SEAT, SUBSEQUENTLY, DAMAGING MOST OF THE ROTATING COMPONENTS ATTACHED. THE PTO SHAFT WAS FOUND LOOSE IN THE ENGINE, AND MAY HAVE BEEN A CONTRIBUTING FACTOR DUE TO VIBRATION. THIS PTO CONDITION WAS FOUND ON THE AIRCRAFT'S OTHER ENGINE AT 3 75 TTSN. 2 L 7 2 4F 4 F RT A21EA E15NE 1996050900104 19960509 00104 SW 1996 5 9 96ZZZX2229 1 19960401 G 3210 7300626 TRUSS SUPPORT GULSTM 690TP 695A 7630519 SW RT OUBOARD DAMAGED B VE2R K NONE O OTHER IN INSP/MAINT 1 SW 05 79PH 4682 96029 AFTER RIGHT AFT LOWER NACELLE REMOVED TO FACILITATE MAINTENANCE, DISCOVERED THAT DURING A PREVIOUS LANDING GEAR REMOVAL, THE LEFT AND RIGHT OUTBOARD MLG TRUSS SUPPORTS WERE ACCIDENTLY DRILLED WHEN THE OUTBOARD TRUNNION PIN COVER WAS DRILLED OFF. THE LEFT TRUSS WAS REPAIRED BY BLENDING, BUT THE RIGHT TRUSS WAS FOUND TO BE DRILLED AS MUCH AS 0.299 INCH IN DEP TH. THE RIGHT SUPPORT WAS REPLACED WITH A NEW PART NR 730062-504. THIS DAMAGE WOULD HAVE BEEN AVOIDED BY USING A DRILL STOP OR A PROTECTIVE COVER DURING DRILLING. 1 H 7 2 4T 2A4 1996050900106 19960509 00106 CE 1996 5 9 96ZZZX2231 1 19960417 G 3246 43667 TIE BOLT 314901 CESSNA 500 560CESSNA 2076750 CE MLG WHEEL FAILED D K NONE O OTHER IN INSP/MAINT 1 GL 05 68881 143 1804 560173 INSPECTION FOUND 2 ADJACENT WHEEL TIE BOLTS FAILED AT 4 THREADS FROM SHANK. BOLTS 43.5 HRS OUT OF MAG PARTICLE CHECK AT 42 CYCLES. BOLTS TT SINCE NEW, 1,462.7 HRS. BOLTS HAD BEEN THROUGH 7 NEW TIRE CHANGES. PROPER LUBE USED DURING TORQU E. NO EVIDENCE OF OVERTORQUE. NUTS AND WASHERS MISSING. 2 L 7 2 4F RT A22CE 1996050900107 19960509 00107 CE 1996 5 9 96ZZZX2232 1 19960402 G 2430 6608513 CONTROL UNIT BEECH 60 60 1153602 CE START/GEN FAILED D K NONE O OTHER IN INSP/MAINT 1 SW 05 65BL 239 60054 LEFT STARTER WOULD NOT ROTATE WHEN START WAS SELECTED. REPLACED GENERATOR CONTROL UNIT. SYSTEM WAS RESTORED TO NORMAL. 1 L 7 2 3O A12CE 1996050900108 19960509 00108 1996 5 9 96ZZZX2233 4 19960415 G 3424 9550B INDICATOR BEECH B300 B300 1159232 CE TURN/SLIP FAILED B KI2R K NONE O OTHER IN INSP/MAINT 1 CE 01 65CR 45 887 FL60 THIS MODEL OF TURN AND SLIP INDICATOR HAS A HIGH FAILURE RATE. (BOTH THE PILOT'S AND COPILOT'S USE THE SAME INDICATOR.) SUBMITTER STATES CHANGED 6 UNITS SINCE THE FIRST OF THE YEAR. THE HIGH TIME UNIT HAS 45 HOURS ON IT SINCE OVERHAUL, M OST HAD LESS. 2 L 7 2 4T RT A24CE 1996050900109 19960509 00109 SW 1996 5 9 96ZZZX2234 1 19960405 G 5610 360012501 WINDOW GULSTM 690TP 690 0141720 SW COPILOT SIDE FAILED B GFER O OTHER D INFLIGHT SEPARATION CR CRUISE 1 NM 09 9175N 11071 AT 13,000 FEET, 4.2 PSID CABIN DIFFERENTIAL RPESSURE AND APPROXIMATELY 250 KIAS, THE COPILOT'S SIDE WINDOW FAILED CATAST ROPHICALLY. APPROXIMATELY 50 PERCENT OF THE WINDOW WAS LOST CAUSING SOME SECONDARY DAMAGE TO THE PROPELLER LEADING EDGE AND FUSELAGE. THE CAUSE COULD NOT BE READILY IDENTIFIED BY EXAMINATION OF THE WINDOW OR FRAME. SUBMITTER RECOMMENDS A PRISM/OIL CHECK OF ALL PRESSURE WINDOWS AT NEXT 100-HOUR INSPECTION TO DETERMINE IF CRACKS HAVE DEVELOPED AT THE FASTEN ER HOLES. 1 H 7 2 3T 2A4 1996050900110 19960509 00110 SW 1996 5 9 96ZZZX2235 1 19960401 G 5412 FIREWALL GULSTM 690TP 695A 7630519 SW LT/RT NACELE CRACKED B VE2R K NONE O OTHER IN INSP/MAINT 1 SW 05 79PH 96029 THE LT AND RT ENGINE FIREWALLS FOUND TO HAVE CRACKS IN THE ALUMINUM PORTION OF FIREWALL AT THE AFT ENGINE MOUNT UPPER AT TACH FASTENERS DURING OTHER MAINTENANCE REQUIRING THE LOWER AFT NACELLES TO BE REMOVED. WITH THE NACELLES REMOVED, THE CRACKS ARE VISIBLE. ACCOMPLISHED A DER REPAIR SIMILAR TO REPAIR IN SB 217 REQUIRED ON EARLIER MODEL AND S/N AIRCRAFT. S UBMITTER SUGGESTS CAUSE AS ENGINE/PROP VIBRATION. ACCOMPLISHED REINFORCEMENT REPAIR AT EARLIEST ACCESS. 1 H 7 2 4T 2A4 1996050900111 19960509 00111 SW 1996 5 9 96ZZZX2236 1 19960401 G 5743 73005834 ANGLE GULSTM 690TP 695A 7630519 SW RT NACELLE CRACKED B VE2R K NONE O OTHER IN INSP/MAINT 1 SW 05 79PH 4682 96029 DURING A 100-HOUR INSPECTION, THE RT MLG INBOARD TRUSS ATTACH ANGLE WAS FOUND TO HAVE A 0.9 INCH RADIUS CRACK 1.0 INCH F ROM AFT END. THIS CRACK WAS STOP DRILLED AND A DOUBLER AND RADIUS BLOCK WAS INSTALLED PER DER'S REPAIR SCHEME. CRACKS APPEAR TO BE ASSOCIATED WITH AIRCRAFT HAVING MORE THAN 2,000 FLIGHT HOURS. SUBMITTER RECOMMENDS CLOSE INSPECTION OF ALL 4 ANGLES ON AIRCRAFT AT REGULAR INTERVALS. 1 H 7 2 4T 2A4 1996050900114 19960509 00114 SW 1996 5 9 96ZZZX2239 1 19960410 G 5530 41000885 CHANNEL GULSTM 690TP 690A 0141722 SW VERTICAL STAB CRACKED B W6NR K NONE O OTHER IN INSP/MAINT 1 GL 25 333CA 4132 11136 DURING C/W AD 95-13-02 IAW SB 218 PART 2, VERTICAL STABILIZER CHANNEL WAS FOUND CRACKED AT THE BEND RADIUS. A NEW PART WAS MADE FROM THE SAME MATERIAL AND TO THE SAME DIMENSIONS IAW 43.131A. REASSEMBLY WAS C/W - NO PROBLEMS. THIS CHANNEL WAS NOT IN THE AREA TO BE INSPECTED PER SB 218. NOTE: THIS WAS THE 3RD AIRCRAFT FOUND WITH THE SAME CHANNEL CRACKED. SUGGEST A MUCH FURTHER INSPECTION OF VERTICAL STABILIZER WHILE C/W SB 218. 1 H 7 2 3T 2A4 1996050900115 19960509 00115 CE 1996 5 9 96ZZZX2240 1 19960315 G 2133 13024 CHECK VALVE BEECH 200 200BEECH 1152920 CE PRESSURIZATION MISSING D K NONE O OTHER IN INSP/MAINT 1 SW 03 130PA BB330 AIRCRAFT WOULD NOT PRESSURIZE. FOUND PRESSURIZATION CHECK VALVES MISSING. FOUND MISSING CHECK VALVES JAMMED INSIDE OF PN 50-380053-1 VENTURI. REMOVED CHECK VALVES, INSTALLED SERVICEABLE PRESSURIZATION VALVE ASSY, PN 1302-2. SYSTEM OPS C HECK SATISFACTORY. SUGGEST A POSSIBLE 10-YEAR LIFE LIMIT ON THIS STYLE VALVE ASSEMBLY. 1 L 7 2 4T A24CE 1996050900116 19960509 00116 WP 1996 5 9 96ZZZX2241 2 19960412 G 7200 ENGINE AMD FALC10 FALCON10 2730101 EU GARRTT TFE731 TFE7312 01518 WP NR 2 FAILED B YL1R E ENGINE SHUTDOWN E VIBRATION/BUFFET CR CRUISE 1 SW 11 662D 4962 584 200 P73550 NR 2 ENGINE HAD HIGH VIBRATION AND EGT 1 HOUR INTO THE FLIGHT. AIRCRAFT WAS EN ROUTE AT CRUISE GOING FROM 33,000 FEET T O 35,000 FEET. THE PILOT MADE A MANUAL ENGINE SHUT DOWN AND LANDED. INSPECTION OF NR 2 ENGINE UPON LANDING SHOWS METAL IN THE TAIL PIPE. SUSPECT CAUSE: HP BLADE FAILURE. NOTE: DOW CHEMICAL (OPERATOR). 2 L 7 2 4F 4 F A33EU E6WE 1996050900117 19960509 00117 NE 1996 5 9 96ZZZX2242 2 19960228 G 7321 EEC SMITHSIND LEAR 60 60LEAR 5170707 CE PWA 305 PW305 NE LT ENGINE MALFUNCTION C O OTHER J WARNING INDICATION CR CRUISE 1 SW 09 799SC 54 Y7545 067 PCE305250 AMBER AND WHITE COMPUTER LIGHTS CAME ON AND ITT INDICATION WAS LOST FOR THE LEFT ENGINE; OTHERWISE, OPERATION WAS NORMAL IN-FLIGHT. ENGINE WOULD NOT START ON GROUND. NO ITT INDICATION CAUSED THE FADER TO ABORT START ATTEMPTS. REPLACED E. E.C. OPERATION NORMAL. 2 L 7 2 4F 4 F RT A10CE E35NE 1996050900118 19960509 00118 SO 1996 5 9 96ZZZX2243 1 19960328 G 4980 38460912 EXHAUST PIPE GARRTT GTCP36100G GULSTM G1159 GIV 3980115 SO APU PLENUM WORN D K NONE O OTHER IN INSP/MAINT 1 EA 25 1086 1802 P467 1086 LARGE DISTORTION IN PLENUM EXHAUST PIPE, 12 O'CLOCK POSITION, DID NOT EXCEED MFG LIMIT OF .50 INCH. APU REMOVED FOR REP AIR AND 2,100 HOUR OVERHAUL C/W. SUSPECT CAUSE, HOT AIR LEAK INSIDE OF PLENUM. TEAR DOWN REVEALED CRACK IN TURBINE NOZ ZLE. 2 L 7 2 4F RT A12EA 1996050900119 19960509 00119 CE 1996 5 9 96ZZZX2244 1 19960403 G 3020 45A6619621 DUCT BEECH MU300 400BEECH CE LT ENG NAC CRACKED B S ERY2 K NONE O OTHER IN INSP/MAINT 1 SO 11 425K 862 RK28 WHILE C/W BEECH SB 2654 INSPECTING THE WELD AREAS OF THE ANTI-ICE DUCT ASSY ATTACH BRACKETS, CRACKS WERE FOUND AROUND TH E WELD OF THE FLANGE AREA. THIS AREA SHOULD ALSO BE INSPECTED AT THE TIME OF C/W THIS BULLETIN. 2 H 7 2 4F RT A16SW 1996050900120 19960509 00120 1996 5 9 96ZZZX2245 4 19960410 G 3418 1N1201825 DIODE CESSNA 500 550 2076604 CE AOA HEATER BURNED D A A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 SW 03 777FL 7033 5500070 AIRCRAFT RETURNED TO MAINTENANCE WHEN COCKPIT FILLED WITH SMOKE SHORTLY AFTER TAKEOFF. AOA HEATER CIRCUIT BREAKER TRIPP ED AND WOULD NOT RESET. INVESTIGATION REVEALED TWO DIODES IN AOA HEAT CIRCUIT TOUCHING GROUND THROUGH RIGHT PITOT STATI C HEAT SWITCH. A REPLACEMENT SWITCH WAS INSTALLED AND DIODES WERE REMOVED FROM THE CIRCUIT IAW WIRING DIAGRAM NOTE AT T HE BOTTOM OF THE DIAGRAM. NO OTHER INFORMATION REGARDING REMOVAL OF THESE DIODES COULD BE FOUND. SUBMITTER RECOMMENDS REMOVAL OF THESE DIIODES IF STILL INSTALLED ON OLDER MODEL CITATIONS. 1 L 7 2 4F A22CE 1996050900306 19960509 00306 WP 1996 5 9 96ZZZX2274 1 19960401 G 6220 369H120331 LEAD/LAG LINK 369D21200 HUGHES 369 369F 4470708 WP M/R HUB CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 15 5205G 2387 619 0011F PILOT FOUND BROKEN LINK ON PRE-FLIGHT. REMOVED BROKEN LINK AND INSTALLED NEW. FOUND LINK SHIMS .024 INCH OVER MAXIMUM. REMOVED SHIMS AS REQUIRED TO OBTAIN CORRECT DIMENSION. NO FURTHER OCCURRENCE. 1 G 7 1 3U H3WE 1996050900307 19960509 00307 WP 1996 5 9 96ZZZX2275 1 19960410 G 1100 DATA PLATE HUGHES 369 369D 4470706 WP VERTICAL STAB MISSING B A EOOR K NONE O OTHER IN INSP/MAINT 1 AL 03 4571V 490487D DURING ANNUAL INSPECTION, FOUND THE DATA PLATE FOR THE VERTICAL STABILIZER WAS MISSING. THESE ARE FOIL STRIPS THAT ARE GLUED ON AND ARE ROUTINELY FOUND MISSING AT INSPECTION. 1 G 7 1 3U H3WE 1996050900308 19960509 00308 EU 1996 5 9 96ZZZX2276 1 19960408 G 6310 109041506101 SHAFT ASSY AGUSTA A109 A109K2 0260502 EU XMSN DRIVE DAMAGED D A K NONE O OTHER IN INSP/MAINT 1 NM 08 911RX 1226 0026U 10017 DURING THE ENGINE 100-HOUR INSPECTION, DAMAGE TO THE ENGINE TO TRANSMISSION DRIVE SHAFT WAS OBSERVED. THE DAMAGE WAS FU LL CIRCUMFERENCE AND WAS CAUSED BY CONTACT WITH THE FIREWALL. THE SHAFT PASSES THROUGH TWO HALF FLANGE ASSEMBLIES. THE CLEARANCE BETWEEN THE HALF FLANGE ASSEMBLIES AND THE SHAFT IS NOT SYMMETRICAL AND RANGES FROM APPROXIMATELY .25 INCH TO .50 INCH. 1 G 7 2 3U RT H7EU 1996050900309 19960509 00309 WP 1996 5 9 96ZZZX2277 1 19960325 G 3213 430013 SKID TUBE HILLER UH12 OH23G 4360121 WP SKID SHOE CORRODED B A PN5R K NONE O OTHER IN INSP/MAINT 1 NM 03 603RA 1527 INSPECTION FOUND 2 EACH SKID TUBES CORRODED THROUGH BETWEEN SKID SHOE AND TUBE. SUSPECT DUE TO TRAPPED SPRAY CHEMICALS AND WATER FROM WASHING THE AIRCRAFT. 1 G 7 1 3O 4H11 1996050900310 19960509 00310 1996 5 9 96ZZZX2278 4 19960322 G 3421 RCA26AK4 GYRO RCALLEN DIAMON DA20A1 DA20A1 05626UX GL COCKPIT HORIZ MALFUNCTION D K NONE O OTHER NR NOT REPORTED 1 SW 15 518SS 12 10073 ARTIFICAL HORIZON BANKS TO LEFT IN STRAIGHT AND LEVEL FLIGHT. 1 L 7 1 3O NT TA4CH 1996050900311 19960509 00311 1996 5 9 96ZZZX2279 4 19960322 G 3421 RCA26AK4 GYRO RCALLEN DIAMON DA20A1 DA20A1 05626UX GL COCKPIT GYRO DEFECTIVE D K NONE O OTHER NR NOT REPORTED 1 SW 15 518SS 24 95K1158 10073 GYRO WILL NOT MAINTAIN LEVEL INDICATION IN STRIAGHT AND LEVEL FLIGHT. 1 L 7 1 3O NT TA4CH 1996050900312 19960509 00312 1996 5 9 96ZZZX2280 4 19960322 G 3120 HOURMETER MITCH DIAMON DA20A1 DA20A1 05626UX GL COCKPIT FAILED D K NONE O OTHER IN INSP/MAINT 1 SW 15 520SS 94 1082 10075 HOURMETER ODOMETER STOPPED RECORDING TIME. 1 L 7 1 3O NT TA4CH 1996050900313 19960509 00313 1996 5 9 96ZZZX2281 4 19960322 G 3421 GYRO RCALLEN DIAMON DA20A1 DA20A1 05626UX GL COCKPIT HORIZ MALFUNCTION D K NONE O OTHER NR NOT REPORTED 1 SW 15 526SS 74 10085 GYRO ARTIFICAL HORIZON WILL NOT STAY UPRIGHT. 1 L 7 1 3O NT TA4CH 1996050900314 19960509 00314 GL 1996 5 9 96ZZZX2282 1 19960322 G 7931 956355 SENSOR DIAMON DA20A1 DA20A1 05626UX GL ENG OIL PRESSURE FAILED D K NONE O OTHER IN INSP/MAINT 1 SW 15 526SS 17 10085 OIL PRESSURE SENSOR HAS OPEN RESISTANCE CONDITION INTERNALLY. 1 L 7 1 3O NT TA4CH 1996050900315 19960509 00315 1996 5 9 96ZZZX2283 4 19960322 G 3120 HOURMETER MITCH DIAMON DA20A1 DA20A1 05626UX GL COCKPIT INOPERATIVE D K NONE O OTHER IN INSP/MAINT 1 SW 15 521SS 38 1153 10081 HOURMETER ODOMETER QUIT RECORDING TIME. 1 L 7 1 3O NT TA4CH 1996050900316 19960509 00316 1996 5 9 96ZZZX2284 4 19960322 G 3120 D11125240 HOURMETER MITCH DIAMON DA20A1 DA20A1 05626UX GL COCKPIT FAILED D K NONE O OTHER IN INSP/MAINT 1 SW 15 521SS 127 1108 10081 HOURMETER ODOMETER QUIT RECORDING TIME. 1 L 7 1 3O NT TA4CH 1996050900317 19960509 00317 GL 1996 5 9 96ZZZX2285 1 19960322 G 7931 956355 SENDER DIAMON DA20A1 DA20A1 05626UX GL ENG OIL PRESS FAILED B K NONE O OTHER IN INSP/MAINT 1 SW 15 521SS 47 10081 OIL PRESSURE SENDER HAS OPEN RESISTENCE CONDITION INTERNALLY. 1 L 7 1 3O NT TA4CH 1996050900318 19960509 00318 GL 1996 5 9 96ZZZX2286 1 19960322 G 7931 956355 SENDER DIAMON DA20A1 DA20A1 05626UX GL ENG OIL PRESS FAILED D K NONE O OTHER IN INSP/MAINT 1 SW 15 528SS 9 10092 OIL PRESSURE SENDER HAS OPEN RESISTENCE CONDITION INTERALLY. 1 L 7 1 3O NT TA4CH 1996050900319 19960509 00319 1996 5 9 96ZZZX2287 4 19960322 G 3120 D11125240 HOURMETER MITCH DIAMON DA20A1 DA20A1 05626UX GL COCKPIT FAILED D K NONE O OTHER IN INSP/MAINT 1 SW 15 528SS 8 1154 10092 HOURMETER ODOMETER STOPPED RECORDING TIME. 1 L 7 1 3O NT TA4CH 1996050900320 19960509 00320 GL 1996 5 9 96ZZZX2288 1 19960322 G 7931 956355 SENDER DIAMON DA20A1 DA20A1 05626UX GL ENG OIL PRESS FAILED D K NONE O OTHER IN INSP/MAINT 1 SW 15 528SS 10092 OIL PRESSURE SENDER HAS OPEN RESISTANCE CONDITION INTERNALLY. 1 L 7 1 3O NT TA4CH 1996050900321 19960509 00321 1996 5 9 96ZZZX2289 4 19960322 G 3421 RCA26AK4 GYRO RCALLEN DIAMON DA20A1 DA20A1 05626UX GL COCKPIT HORIZ FAILED D K NONE O OTHER IN INSP/MAINT 1 SW 15 524SS 65 95K1223 10084 ARTIFICAL HORIZON GYRO WILL NOT TURN ON. 1 L 7 1 3O NT TA4CH 1996050900322 19960509 00322 1996 5 9 96ZZZX2290 4 19960322 G 3421 RCA26AK4 GYRO RCALLEN DIAMON DA20A1 DA20A1 05626UX GL COCKPIT HORIZ DEFECTIVE D K NONE O OTHER NR NOT REPORTED 1 SW 15 527SS 16 95K1201 10090 ARTIFICAL HORIZON WILL NOT SAY UPRIGHT. 1 L 7 1 3O NT TA4CH 1996050900323 19960509 00323 GL 1996 5 9 96ZZZX2291 1 19960322 G 7713 710020 GAUGE DIAMON DA20A1 DA20A1 05626UX GL ENG MANIFOLD ERROR D K NONE O OTHER IN INSP/MAINT 1 SW 15 531SS 31 A7504 10105 ENGINE MANIFOLD PRESSURE READING INCORRECT. 1 L 7 1 3O NT TA4CH 1996050900324 19960509 00324 SO 1996 5 9 96ZZZX2292 2 19960329 G 7414 10349271 COIL BENDIX S6RN1225 BEECH 55 95B55 1152706 CE CONT O470 IO470L 17026 SO MAGNETO CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 09 2023Z A224421 TC2171 465369 DURING ANNUAL INSPECTION, FOUND MAGNETO COIL CRACKED IN NUMEROUS PLACES. AD 94-01-03 R2 REQUIRES REPLACEMENT OF THESE C OILS, BUT THIS SERIAL NUMBER MAGENTO IS NOT COVERED BY THE AD (COIL IS AN OPAQUE AMBER COLOR AS REFERENCED IN TELEDYNE C ONTINENTAL IGNITION SYSTEMS SB MSB644). THERE ARE NO MAINTENANCE RECORD ENTRIES OF THESE COILS HAVING BEEN PREVIOUSLY R EPLACED. 1 L 7 2 3O 3 O 3A16 3E1 1996050900325 19960509 00325 SO 1996 5 9 96ZZZX2293 2 19960411 G 7414 104001664 IMPULSE CAM S6RN25 CESSNA 182 182B 2072706 CE CONT O470 O470L 17026 SO LT MAGNETO WORN D K NONE O OTHER IN INSP/MAINT 1 NM 11 7244E 596 K149104DR 52244 069744R UPON INSPECTION OF CAMS IN IMPULSE COUPLINGS FOR WEAR PER AD 78-09-07, FOUND ONE FLYWEIGHT AND RIVET WORN WELL BEYOND LI MITS. THIS IS NEW STYLE CAM WITH SNAP RING ASSEMBLY. FOR A TOTAL TIME OF ONLY 595 HOURS, FEEL THIS TO BE SIGNIFICANT W EAR AND WOULD ALSO QUESTION THE HARDNESS OF METAL. 1 H 7 1 3O 3 O NT 3A13 E273 1996050900326 19960509 00326 EA 1996 5 9 96ZZZX2294 2 19960317 G 8530 VALVE PIPER PA28 PA28181 7102807 SO LYC O360 O360A4M 41514 EA NR 1 CYL INTAKE HEAD SEPARATED D O OTHER E VIBRATION/BUFFET NR NOT REPORTED 1 GL 15 8347C 1734 287690121 L2101336A ENGINE ROUGHNESS DURING FLIGHT FOUND BENT PUSHROD HOUSING AND PUSHROD. REMOVED CYLINDER AND FOUND VALVE HEAD SEPARATED FORM STEM INTAKE SIDE. 1 L 7 1 3O 3 O 2A13 E286 1996050900327 19960509 00327 CE 1996 5 9 96ZZZX2295 1 19960401 G 3411 STATIC PORT CESSNA 210 2105 2073404 CE STATIC SYSTEM LEAKING D K NONE O OTHER IN INSP/MAINT 1 SW 99 5875 2050014 THE SEALANT BETWEEN STATIC PORT AND SKIN OF AIRCRAFT HAD TURNED TO POWDER MAKING A LEAK IN THE STATIC SYTSEM. DRILLED R IVETS OUT OF STATIC PORT, SEALED WITH PR-1422 SEALANT. STARTED STATIC CHECK AGAIN, GOT UP TO 11,000 FEET AND A SEVERE L EAK STARTED AGAIN. FOUND LEAK AT SAME LOCATION ON OTHER STATIC PORT. WITH THIS STYLE STATIC PORT WHICH PROTRUDES FROM SKIN ABOUT .25 INCH, IT COULD POSSIBLY BUILD PRESSURE IN STATIC LINE AND GIVE FALSE READING. 1 H 7 1 3O 3A21 1996050900328 19960509 00328 EA 1996 5 9 96ZZZX2296 2 19960404 G 7414 BEARING S6LN2230 PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA MAG DIST BLK LOOSE B APCR K NONE O OTHER IN INSP/MAINT 1 NM 01 27343 17 5062990R 317752163 RL727061A ROTORSHAFT CAM-END BEARING FIT TOO LOOSE. SHAFT AND CAM MOVE LATERALLY GIVING VARYING POINT GAP AND TIMING. TIMING FOU ND OUT-OF-TOLERANCE DURING CHECK OF TCM SB 643(1). THIS MAGNETO FURNISHED ON LYCOMING FACTORY REMANUFACTURED ENGINE. 1 L 7 2 3O 3 O A20SO E14EA 1996050900329 19960509 00329 SO 1996 5 9 96ZZZX2297 1 19960210 G 7120 J961355 MOUNT PIPER PA46 PA46310P 7104605 SO ENGINE RT AFT DAMAGED D A K NONE O OTHER IN INSP/MAINT 1 NM 11 9220T 468608016 WHILE C/W PIPER SB NR 960, RIGHT REAR ENGINE MOUNT RUBBER ISOLATOR WAS FOUND BADLY DETERIORATED. THE MOUNT IS IN CLOSE PROXIMITY TO THE EXHAUST SYSTEM AND EXCESSIVE HEAT IS SUSPECTED AS THE CAUSE. THE PARTS MANUAL CALLS OUT A HEAT SHIELD FOR THE LEFT REAR MOUNT, BUT NONE FOR THE RIGHT. A CALL TO PIPER CONFIRMED THERE IS NO HEAT SHIELD FOR THE RIGHT REAR M OUNT. SOME TYPE OF HEAT SHIELD SHOULD BE INSTALLED TO PREVENT THIS TYPE OF DETERIORATION. 1 L 7 1 3O A25SO 1996050900330 19960509 00330 SW 1996 5 9 96ZZZX2298 1 19960417 G 2730 M3414 ROD END BEARING 915007005 MOONEY M20 M20E 5870212 SW ELEV CONTRL TUBE FAILED D A K NONE O OTHER IN INSP/MAINT 1 WP 15 5638Q 2329 675 WHILE PERFORMING A FLIGHT CONTROL OPERATIONAL INSPECTION DURING AN ANNUAL, RESTRICTED MOVEMENT OF ELEVATOR CONTROL WAS N OTED. AFTER MOVING THE ELEVATOR CONTROL THROUGH ITS FULL RANGE OF MOTION 4 TO 5 CYCLES, MOVEMENT BECAME UNRESTRICTED. I T WAS DISCOVERED THE THREADED ROD END BEARING BECAME DETACHED FROM THE ELEVATOR CONTROL TUBE LOCATED AFT OF THE ADJUSTAB LE TAIL SECTION JOINT. THE FRACTURE OCCURRED IN THREADED SECTION OF THE BEARING APPROXIMATELY 6 THREADS FROM THE END WI THIN THE JAM NUT. THE BEARING WAS FROZEN DUE TO CORROSION AND LACK OF LUBRICATION. SUBMITTER STATED TO PREVENT RECURRE NCE OF THIS DEFECT, RECOMMEND THE APPROVED SILICON SPRAY LUBRICANT BE APPLIED TO ALL ROD END BEARINGS. 1 L 7 1 3O 2A3 1996050900331 19960509 00331 CE 1996 5 9 96ZZZX2299 1 19960404 G 5720 12200509 V-CHANNEL CESSNA 206 U206 2073306 CE LT OB AIL HINGE CRACKED D S K NONE O OTHER IN INSP/MAINT 1 CE 01 569QL 10655 U2060608 V-CHANNEL CRACKED WHERE AILERON HINGE RIVETED TO IT. DIFFICULT TO SEE CRACK. SUSPECT DEFECTIVE IF MOVEMENT NOTICED WHE N PRESSURE APPLIED UPWARD TO FLAT OF AILERON LOWER SURFACE. 1 H 7 1 3O A4CE 1996050900332 19960509 00332 NE 1996 5 9 96ZZZX2300 2 19960304 G 7210 7757571 BEARING 5074T6LG10 SAAB SF340 340B 7860101 EU GE CT7TP CT79B 30030 NE GC 49 GEARCASE CRACKED B SI3R K NONE O OTHER IN INSP/MAINT 1 NE 03 202KD 1073 9376 340B202 GEAR CASE WAS RETURNED FOR OIL CONTAMINATION. UNIT WAS DISASSEMBLED AND AN EXAMINATION OF INTERNAL HARDWARE REVEALED A CRACKED INNER RACE ON THE PROPELLER SHAFT FORWARD ROLLER BEARING RACE. LEFT - TSI 4,239.5 HRS. CSI, 4,048. 2 L 7 2 4T 4 T RT A52EU E8NE 1996050900333 19960509 00333 SW 1996 5 9 96ZZZX2301 1 19960328 G 6320 476206283 BEARING 4762060029 BELL 47 47G5A 1181034 SW TRANSMISSION MAKING METAL D K NONE O OTHER IN INSP/MAINT 1 GL 13 615BH 303 MB17046 25126 UPON FINDING METAL IN OIL SCREEN, TRANSMISSION WAS REMOVED AND DISASSEMBLED. LOWER SUN GEAR BEARING WAS FOUND TO BE MAK ING METAL. SUBMITTER STATES THIS HAS BEEN THE SIXTH FAILURE IN TRANSMISSION. 1 G 7 1 3O 2H3 1996050900334 19960509 00334 EU 1996 5 9 96ZZZX2302 1 19960422 G 5520 ELEVATOR DORNER DO228 DO228201 2992020 EU ELEV TOP LT FABRIC MISSING D A O OTHER D F E INFLIGHT SEPARATION FLT CONT AFFECTED VIBRATION/BUFFET CR CRUISE 1 SW 05 279MC 2486 8120 THE PILOT REPORTED AT APPROXIMATELY 100 MILES FROM BNA, EN ROUTE FROM CVG, THAT HE EXPERIENCED A HARD NOSE DOWN ELEVATOR CONDITION AND SOME AIRFRAME VIBRATION. THE PILOT ADJUSTED ELEVATOR TRIM TO HELP THE NOSE DOWN CONDITION AND TRIED TO I SOLATE THE VIBRATION WITH ENGINE POWER CHANGES WITH NO SUCCESS. HE CONTINUED TO BNA AT MINIMUM CRUISE SPEED. A BNA PIL OT C/W A VISUAL CHECK OF THE AIRCRAFT AND FOUND APPROXIMATELY 3 FEET OF THE UPPER LEFT ELEVATOR FABRIC MISSING. ELEVATO R, S/N 5577, HAD BEEN RECOVERED 2,485.9 HRS AGO ON 5-9-91, WITH COOPER SUPERFLITE 102 FABRIC IAW WITH STC SA 1326GL. AI RCRAFT HAD ALSO BEEN PRESSURE DEICED BEFORE DEPARTING FROM CVG. 2 H 7 2 4T RT A16EU 1996050900335 19960509 00335 WP 1996 5 9 96ZZZX2303 2 19960329 G 7250 3587502 BEARING LEAR 35 35LEAR 5170600 CE GARRTT TFE731 TFE73122B 01518 WP TURBINE NR 6 SPALLED B IY2R K NONE O OTHER IN INSP/MAINT 1 SW 15 190GC 195 35014 P74124C 195 HOURS AFTER INSTALLING OVERHAULED NR 6 TURBINE BEARING, BEARING WAS REMOVED FORM SERVICE DUE TO SPALLED ROLLERS. TH IS PROBLEM WAS DISCOVERED DURING A ROUTINE 150-HOUR OIL FILTER ANALYSIS. THE ANALYSIS REVEALED M50 TOOL STEEL PLATELETS , WHICH IS MAIN BEARING MATERIAL. THE REMOVED BEARING WAS RETURNED TO THE OVERHAUL FACILITY. 2 L 7 2 4F 4 F A10CE E6WE 1996051600041 19960516 00041 SW 1996 5 16 96ZZZX2340 1 19960206 G 6310 406040532101 BEARING BELL 206 206L4 1182110 SW FREEWHEEL GROOVED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 171AL 2954 MB490 52064 AT 3,000-HOUR OVERHAUL, BEARING ROLLER FOUND TO HAVE DEEP GROOVE ON ONE ROLLER, SCRAPPED BEARING. 1 G 7 1 3U NC H2SW 1996051600042 19960516 00042 SW 1996 5 16 96ZZZX2341 1 19960110 G 6230 206010335001 LEVER ASSY 206010350021 BELL 206 206L4 1182110 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 174AL 283 52067 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, AND 1 EACH 206-010-47 0-101 BEARING. SUSPECT NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT, 283.4 HOURS. 1 G 7 1 3U NC H2SW 1996051600043 19960516 00043 SW 1996 5 16 96ZZZX2342 1 19960110 G 6230 206010336005 LINK IDLER 206010350021 BELL 206 206L4 1182110 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 174AL 283 52067 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, AND 1 EACH 206-010-47 0-101 BEARING. SUSPECT NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT, 283.4 HOURS. 1 G 7 1 3U NC H2SW 1996051600044 19960516 00044 SW 1996 5 16 96ZZZX2343 1 19960129 G 6230 206010335001 LEVER ASSY BELL 206 206L4 1182110 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 175AL 382 52117 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, AND 1 EACH 206-010-47 0-101 BEARING. SUSPECT NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT, 382.3 HOURS. 1 G 7 1 3U NC H2SW 1996051600045 19960516 00045 SW 1996 5 16 96ZZZX2344 1 19960129 G 6230 206010336005 LINK IDLER 206010350021 BELL 206 206L4 1182110 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 175AL 382 52117 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, AND 1 EACH 206-010-47 0-101 BEARING. SUSPECT NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT, 382.3 HOURS. 1 G 7 1 3U NC H2SW 1996051600046 19960516 00046 SW 1996 5 16 96ZZZX2345 1 19960129 G 6230 206010335001 LEVER ASSY 206010350021 BELL 206 206L1 1182107 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 2755N 375 45243 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, AND 1 EACH 206-010-47 0-101 BEARING. SUSPECT NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT, 374.7 HOURS. 1 G 7 1 3U H2SW 1996051600047 19960516 00047 SW 1996 5 16 96ZZZX2346 1 19960129 G 6230 206010336005 LINK IDLER 206010350021 BELL 206 206L1 1182107 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 2755N 375 45243 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, AND 1 EACH 206-010-47 0-101 BEARING. SUSPECT NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT, 374.7 HOURS. 1 G 7 1 3U H2SW 1996051600048 19960516 00048 SW 1996 5 16 96ZZZX2347 1 19960110 G 6230 206010335001 LEVER ASSY 206010350021 BELL 206 206L1 1182107 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 3179S 551 45781 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, AND 1 EACH 206-010-47 0-101 BEARING. SUSPECT NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT, 551.2 HOURS. 1 G 7 1 3U H2SW 1996051600049 19960516 00049 SW 1996 5 16 96ZZZX2348 1 19960110 G 6230 206010336005 LINK IDLER 206010350021 BELL 206 206L1 1182107 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 3179S 551 45781 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, AND 1 EACH 206-010-47 0-101 BEARING. SUSPECT NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT, 551.2 HOURS. 1 G 7 1 3U H2SW 1996051600050 19960516 00050 SW 1996 5 16 96ZZZX2349 1 19960129 G 6230 206010335001 LEVER ASSY 206010335001 BELL 206 206L1 1182107 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 3184P 412 45774 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, AND 1 EACH 206-010-47 0-101 BEARING. SUSPECT NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT, 412.1 HOURS. 1 G 7 1 3U H2SW 1996051600051 19960516 00051 SW 1996 5 16 96ZZZX2350 1 19960129 G 6230 206010336005 LINK IDLER 206010350021 BELL 206 206L1 1182107 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 3184P 412 45774 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, AND 1 EACH 206-010-47 0-101 BEARING. SUSPECT NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT, 412.1 HOURS. 1 G 7 1 3U H2SW 1996051600052 19960516 00052 SW 1996 5 16 96ZZZX2351 1 19960129 G 6230 206010335001 LEVER ASSY 206010335001 BELL 206 206L3 1182108 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 350AL 415 51429 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, AND 1 EACH 206-010-47 0-101 BEARING. SUSPECT NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT, 415.4 HOURS. 1 G 7 1 3U H2SW 1996051600053 19960516 00053 SW 1996 5 16 96ZZZX2352 1 19960129 G 6230 206010336005 LINK IDLER 206010336005 BELL 206 206L3 1182108 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 350AL 415 51429 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, AND 1 EACH 206-010-47 0-101 BEARING. SUSPECT NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT, 415.4 HOURS. 1 G 7 1 3U H2SW 1996051600054 19960516 00054 SW 1996 5 16 96ZZZX2353 1 19960110 G 6230 206010335001 LEVER ASSY 206010350021 BELL 206 206L3 1182108 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 363AL 437 51472 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, AND 1 EACH 206-010-47 0-101 BEARING. SUSPECT NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT, 436.6 HOURS. 1 G 7 1 3U H2SW 1996051600055 19960516 00055 SW 1996 5 16 96ZZZX2354 1 19960110 G 6230 206010336005 LINK IDLER 206010350021 BELL 206 206L3 1182108 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 363AL 437 51472 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, AND 1 EACH 206-010-47 0-101 BEARING. SUSPECT NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT, 436.6 HOURS. 1 G 7 1 3U H2SW 1996051600056 19960516 00056 SW 1996 5 16 96ZZZX2355 1 19960110 G 6230 206010335001 LEVER ASSY 206010350021 BELL 206 206L3 1182108 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 365AL 437 51376 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, AND 1 EACH 206-010-47 0-101 BEARING. SUSPECT NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT, 436.6 HOURS. 1 G 7 1 3U H2SW 1996051600057 19960516 00057 SW 1996 5 16 96ZZZX2356 1 19960110 G 6230 206010336005 LINK IDLER 206010350021 BELL 206 206L3 1182108 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 365AL 437 51376 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, AND 1 EACH 206-010-47 0-101 BEARING. SUSPECT NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT, 436.6 HOURS. 1 G 7 1 3U H2SW 1996051600058 19960516 00058 GL 1996 5 16 96ZZZX2357 2 19960207 G 7210 23030994 SCAVENGE TUBE 23035178 BELL 206 206L3 1182108 SW ALLSN 250C 250C30P 03013 GL GEARBOX BRACKET BROKEN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 366AL 4181 51470 CAE895428 UPON DISASSEMBLY OF GEARBOX, REMOVED OIL PUMP ASSY, AND SCAVENGE TUBE. FOUND ALIGNMENT BRACKET ON SCAVENGE TUBE BROKEN. ALIGNMENT BRACKET AT LOWER END OF SCAVENGE TUBE WAS FOUND BROKEN AT WELD AREA. SUSPECT CAUSE IS DUE TO IMPROPER FIT O N ALIGNMENT BRACKETS. 1 G 7 1 3U 3 U H2SW E1GL 1996051600059 19960516 00059 GL 1996 5 16 96ZZZX2358 2 19960202 G 7250 6851531 4TH STAGE NOZZLE 6898735 AEROSP AS355 AS355F 8680806 EU ALLSN 250C 250C20F 03013 GL PT SECTION DEFECTIVE B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 378E 1303 WX46323 5214 CAE840026 UPON 1,750-HOUR INSPECTION, FOUND DIAPHRAGM CRACKED AND THE PART WAS SENT FOR OVERHAUL. 1 G 7 2 3U 3 U H11EU E4CE 1996051600060 19960516 00060 EU 1996 5 16 96ZZZX2359 1 19960118 G 6520 4619210902 BEVEL GEAR SET BOLKMS 105 BO105S 5626006 EU GEARBOX ASSY MAKING METAL B ALGR O OTHER J WARNING INDICATION LD LANDING 1 SW 03 4572V 4143 1213 S665 ON LANDING AT DESTINATION, THROTTLE AT FLIGHT IDLE. INTERMEDIATE TAIL ROTOR DRIVE GEARBOX CHIP DETECTOR LIGHT ILLUMINAT ED. FOUND LARGE CHIP MISSING FROM BEVEL GEAR. 1 G 7 2 3U H3EU 1996051600061 19960516 00061 SW 1996 5 16 96ZZZX2360 1 19960122 G 6310 206040272101 BOOT 206040015015 BELL 206 206L1 1182107 SW DRIVESHAFT LEAKING B ALGR K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 57334 336 36 45445 SCHEDULED INSPECTION, FOUND THE BOOT WAS LEAKING AND SEAL WAS TORN. 1 G 7 1 3U H2SW 1996051600063 19960516 00063 GL 1996 5 16 96ZZZX2362 2 19960207 G 7261 23039793 SCAVENGE BODY 23035179 SKRSKY S76 S76 8143010 NE ALLSN 250C 250C30S 03013 GL GEARBOX WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 769AL 2570 760048 CAE890253S UPON DISASSEMBLY OF GEARBOX, REMOVED OIL PUMP ASSY. VISUALLY INSPECTED, SHOWED WEAR AT SCAVENGE BODY AND SCAVENGE TUBE MATING SURFACE. SCAVENGE TUBE WORE INTO SCAVENGE BODY. SUSPECT CAUSE IS DUE TO IMPROPER FIT ON ALIGNMENT BRACKETS. 1 G 7 2 3U 3 U H1NE E1GL 1996051600064 19960516 00064 EU 1996 5 16 96ZZZX2363 1 19960206 G 5311 10520501077 FRAME NR 9 10520001 BOLKMS 105 BO105C 5626005 EU SIDE PANEL RT CRACKED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 90761 14557 S160 DURING 1200-HOUR INSPECTION, FOUND RT FRAME NR 9 CRACKED. THE NR 9 FRAME IS STRUCTURAL SUPPORT FOR THE TRANSMISSION MOU NT. 1 G 7 2 3U H3EU 1996052100002 19960521 00002 EA 1996 5 21 96ZZZX2365 2 19960415 G 7322 1044011 CARBURETOR MA6AA HILLER UH12 UH12E 4360122 WP LYC O540 VO540C2A 41532 EA ENGINE FLOAT STICKS B EVGR K NONE O OTHER IN INSP/MAINT 1 SO 33 14634 175 AC31707 1782 INSPECTION FOUND CARBURETOR FLOAT WAS RUBBING ON LOWER HOUSING AND STICKING OPEN. 1 G 7 1 3O 3 O 4H11 E304 1996052100003 19960521 00003 EA 1996 5 21 96ZZZX2366 2 19960415 G 7322 MA6AA CARBURETOR HILLER UH12 UH12E 4360122 WP LYC O540 VO540C2A 41532 EA ENGINE FLOAT STICKS B EVGR K NONE O OTHER IN INSP/MAINT 1 SO 33 14634 175 AC31784 1782 INSPECTION FOUND CARBURETOR FLOAT WAS RUBBING ON LOWER HOUSING AND STICKING OPEN. 1 G 7 1 3O 3 O 4H11 E304 1996052100004 19960521 00004 GL 1996 5 21 96ZZZX2367 2 19960319 G 7260 6859435 BEARING AGUSTA A109 A109A2 0260120 EU ALLSN 250C 250C20B 03013 GL GEARBOX FAILED B KUVR O OTHER J WARNING INDICATION NR NOT REPORTED 1 SO 19 8WH 266 7256 CAE832739 CHIP LIGHT ILLUMINATED IN-FLIGHT. SHORTLY THEREAFTER, ENGINE FAILED. MAINTENANCE FOUND THE BEARINGS ON EITHER END OF T HE FUEL CONTROL AND OIL PUMP SPUR GEARSHAFT FELL APART STOPPING FUEL CONTROL OPERATION. EXACT CAUSE UNKNOWN AT THIS TIM E. UNUSUAL BECAUSE SHAFT IS SUPPORTED ON BOTH ENDS. SUSPECT ONE BEARING FAILED ALLOWING SHAFT TO WOBBLE AND DESTROY SE COND BEARING. 1 G 7 2 3U 3 U H7EU E4CE 1996052100006 19960521 00006 WP 1996 5 21 96ZZZX2369 1 19960411 G 5753 ARC23121 FITTING DOUG DC10 DC10* WP IB FLAP VANE CORRODED D K NONE O OTHER IN INSP/MAINT 1 SW 07 HANGAR MOUNT FITTINGS THAT ARE RIVETED TO TWO RIBS AND THEN THE RIB AND FITTING ASSYS ARE BONDED TO THE CORE AND SKIN. T HIS IS WHAT ATTACHES THE VANE TO THE FLAP. UPON COMPLETION OF DISASSEMBLING THE VANE, THE FITTINGS WERE FOUND TO HAVE E XCESSIVE DISSIMILAR METAL CORROSION IN THE AREA UNDER THE BOLT HEADS. EXCESSIVE CORROSION WAS ALSO FOUND ON THE 3 EACH FITTINGS THROUGH AND AROUND THE HI-LOK ATTACHMENT HOLES THAT ATTACHES THE FITTINGS TO THE RIBS. 2 L 7 3 4F A22WE 1996052100007 19960521 00007 WP 1996 5 21 96ZZZX2370 1 19960411 G 5753 ARC27151 FITTING DOUG DC10 DC10* WP IB FLAP VANE CORRODED D K NONE O OTHER IN INSP/MAINT 1 SW 07 HANGAR MOUNT FITTINGS THAT ARE RIVETED TO TWO RIBS AND THEN THE RIB AND FITTING ASSYS ARE BONDED TO THE CORE AND SKIN. T HIS IS WHAT ATTACHES THE VANE TO THE FLAP. UPON COMPLETION OF DISASSEMBLING THE VANE, THE FITTINGS WERE FOUND TO HAVE E XCESSIVE DISSIMILAR METAL CORROSION IN THE AREA UNDER THE BOLT HEADS. EXCESSIVE CORROSION WAS ALSO FOUND ON THE 3 EACH FITTINGS THROUGH AND AROUND THE HI-LOK ATTACHMENT HOLES THAT ATTACHES THE FITTINGS TO THE RIBS. 2 L 7 3 4F A22WE 1996052100008 19960521 00008 EA 1996 5 21 96ZZZX2371 2 19960415 G 8530 CYLINDER PIPER PA28 PA28181 7102807 SO LYC O360 O360A4M 41514 EA NR 3 FAILED D K NONE O OTHER IN INSP/MAINT 1 GL 15 39609 2800 400 287890542 L2519936A NR 3 CYLINDER BARREL BROKEN. BARREL FAILED 75 PERCENT OF RADIUS ABOUT 2 INCHES DOWN FROM TOP OF CYLINDER BARREL. 1 L 7 1 3O 3 O 2A13 E286 1996052100010 19960521 00010 SO 1996 5 21 96ZZZX2373 1 19960410 G 5700 LIFT STRUT PIPER PA12 PA12 7101202 SO LT REAR DEFECTIVE B CO4R K NONE O OTHER IN INSP/MAINT 1 AL 03 2526M 121017 PARAGRAPH 'A' OF AD NOTE 93-10-06 HAS BEEN ACCOMPLISHED USING AN FAA APPROVED X-RAY METHOD. REMARKS: LT FRONT STRUT AI RWORTHY, LT REAR STRUT UNAIRWORTHY, RT FRONT STRUT AIRWORTHY, RT REAR STRUT AIRWORTHY. X-RAYS ARE ON FILE AT THIS REPAI R STATION. 1 H 7 1 3O A780 1996052100011 19960521 00011 SW 1996 5 21 96ZZZX2374 1 19960412 G 8011 MZ4218R STARTER MOONEY M20 M20J 5870219 SW FRAME SCREWS FAILED D K NONE O OTHER NR NOT REPORTED 1 EA 07 57413 40 5054342 241450 STARTER FRAME TO GEAR HOUSING SCREWS SHEARED ALLOWING REAR OF STARTER TO DROP JAMMING MIXTURE CONTROL AT SERVO. 1 L 7 1 3O 2A3 1996052100012 19960521 00012 WP 1996 5 21 96ZZZX2375 1 19960417 G 3233 3775836501 GLAND ASSY 57740355507 DOUG DC8 DC8* WP MLG ACT CYL CRACKED H K NONE O OTHER IN INSP/MAINT 1 SO 19 MAIN LANDING GEAR ACTUATING CYLINDER GLAND RECEIVED CRACKED IN HALF COMPLETELY. PART HAS EVIDENCE OF PREVIOUS CHROME RE WORK ON OUTSIDE DIAMETER OF SEAL AREA. 2 L 7 4 4J F 4A25 1996052100013 19960521 00013 SO 1996 5 21 96ZZZX2376 2 19960311 G 7414 10357586 DISTRIBUTOR GEAR BENDIX S6RN205 CESSNA 310 310Q 2074242 CE CONT O470 IO470VO 17026 SO ENG RT MAG BROKEN D K NONE O OTHER IN INSP/MAINT 1 SO 09 7742Q 1300 628473 310Q0242 ENGINE WOULD NOT RUN WHEN RIGHT MAGNETO SELECTED. INSPECTION REVEALED TEETH ON DISTRIBUTOR GEAR (PLASTIC) HAD SHEARED O FF. GEAR DID APPEAR TO BE YELLOWED FROM AGE AS IF IT HAD NOT BEEN REPLACED AT LAST OVERHAUL. 1 L 7 2 3O 3 O 3A10 3E1 1996052100014 19960521 00014 SW 1996 5 21 96ZZZX2377 1 19960403 G 3213 AN522A AXLE BOLT BBAVIA 8 8GCBC 1220803 SW MLG FAILED D O OTHER O OTHER LD LANDING 1 SO 09 86928 3274 UPON LANDING, THE AXLE BOLT NUTS STRIPPED OFF OF THE BOLTS CAUSING THE AXLE AND WHEEL TO DEPART THE AIRCRAFT. THIS CAUS ED THE GEAR TO DIG INTO THE GROUND AND FLIP THE AIRCRAFT ON ITS BACK. 1 H 7 1 3O A21CE 1996052100015 19960521 00015 CE 1996 5 21 96ZZZX2378 1 19960426 G 7160 2652000817 SEPARATOR CESSNA 208 208B 2073701 CE ENGINE INLET CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 15 950FE 7000 208B0056 SUBMITTER MAINTAINS 12 CESSNA 208B AIRCRAFT AND ARE FINDING CRACKS IN SEVERAL INERTIAL SEPARATORS. SINCE THIS AIRCRAFT IS NIGHT IFR 135 SINGLE ENGINE, CRACKS IN THE ENGINE INLET ARE OF GREAT CONCERN. SUBMITTER HAS SEEN ONE OF THESE INTAKE S WITH A SCAB PATCH INSIDE WHICH IS UNACCEPTABLE. SUBMITTER BELIEVES THE CRACKS ARE DUE TO VIBRATION OR THE DESIGN OR A COMBINATION. THE ONLY FIX AT THIS TIME IS TO BUY A NEW PART. 1 H 7 1 3T A37CE 1996052100016 19960521 00016 SO 1996 5 21 96ZZZX2379 2 19960409 G 8530 649543 CYLINDER CESSNA 150 150M 2071830 CE CONT O200 O200A 17020 SO NR 1 CRACKED D K NONE E R K VIBRATION/BUFFET PARTIAL RPM/PWR LOSS FLUID LOSS IN INSP/MAINT 1 SO 13 9432U 1274 15078380 254712A48 EXAMINATION TO DETERMINE CAUSE OF ENGINE FAILURE DISCLOSED NR 1 CYLINDER HAD CRACKED APPROXIMATELY THREE-FOURTHS OF THE BARREL CIRCUMFERENCE CAUSING LOSS OF OIL QUANTITY AND PRESSURE. 1 H 7 1 3O 3 O 3A19 E252 1996052100017 19960521 00017 GL 1996 5 21 96ZZZX2380 3 19960321 G 6111 V84334R BLADE BEECH 35 V35 1151538 CE HARTZL HCA3V PHCA3VF4 GL SHANK CRACKED B A WN1R K NONE O OTHER IN INSP/MAINT 1 SW 19 999ER 1092 A79341 D8304 BR408 BLADE DYE CHECKED IAW AD 68-13-02. NO CRACKS INDICATED. CHECKED OK. FOUND ONE INCH LONG CRACK IN BLADE, USING EDDY CU RRENT, APPROXIMATELY .040 INCH DEEP. SUBMITTER SUGGESTED MAKING EDDY CURRENT INSPECTION MANDATORY. 1 L 7 1 3O 3A15 5 C P6EA 1996052100018 19960521 00018 GL 1996 5 21 96ZZZX2381 3 19960325 G 6111 V843311 BLADE PIPER PA23 PA23250 7102308 SO HARTZL HCA2V HCA2VK2 GL SHANK CRACKED B A WN1R K NONE O OTHER IN INSP/MAINT 1 SW 19 5071Y 300 A36438 272085 H1276 BLADE CRACK FOUND DURING OVERHAUL WITH EDDY CURRENT. PART OF CRACK SHOWS UP DURING DYE CHECK. CRACK IS APPROXIMATELY 6 INCHES LONG. SUBMITTER SUGGESTED REVISING AD 68-19-04 AND AD 68-13-02 TO MAKE EDDY CURRENT MANDATORY. THIRD CRACKED B LADE FOUND IN 10 DAYS. 1 L 7 2 3O 1A10 5 C P24EA 1996052100019 19960521 00019 SO 1996 5 21 96ZZZX2382 1 19960222 G 2720 6342004 RUDDER BAR PIPER PA32 PA32300 7103212 SO PILOT LT CRACKED H S K NONE O OTHER IN INSP/MAINT 1 WP 25 4182R 4011 3240513 DURING ANNUAL INSPECTION, THE RUDDER PEDAL FELT SPONGY ON PILOT'S LEFT SIDE. A CLOSER INSPECTION REVEALED A 1.500 INCH CRACK AT THE POINT WHERE THE CROSS-TUBE WELDS TO THE TORQUE TUBE. AGE AND FATIGUE ARE MAJOR FACTORS FOR TUBE CRACKING. 1 L 7 1 3O A3SO 1996052100020 19960521 00020 SO 1996 5 21 96ZZZX2383 1 19960325 G 5510 BALANCE WEIGHT PIPER PA28 PA28140 7102802 SO HORIZ STAB BOLTS WORN D S K NONE O OTHER IN INSP/MAINT 1 SW 99 4475N 3863 2825599 THROUGH-BOLT HOLDING ELEVATOR BALANCE WEIGHT TO TUBE FOUND TO BE BADLY WORN FROM LOOSE FIT TO TUBE. AD 70-26-04 DOES NO T CALL FOR BOLT INSPECTION. 1 L 7 1 3O 2A13 1996052100021 19960521 00021 SO 1996 5 21 96ZZZX2384 1 19960318 G 3411 1J46 FILTER PIPER PA31 PA31325 7103105 SO LYC O540 LTIO540F2BD 41533 EA PITOT STATIC FAILED D A K NONE O OTHER IN INSP/MAINT 1 SW 11 27934 317912042 L161968A SUBJECT FILTER REMOVED FROM AIRCRAFT AFTER 6 MONTHS AND 200 HOURS. FAILURE OF FILTER RESULTED IN FAILURE OF PILOT'S KFC 200 ATTITUDE INDICATOR, COPILOT'S ATTITUDE INDICATOR, AND DIRECTIONAL GYRO. THE CAUSE OF THE PROBLEM WAS A DETERIORATI NG PRESSURE PUMP 442CW-6. HOWEVER, NO FAILURE WAS NOTED IN THE COCKPIT UNTIL GYROS STARTED FAILING. PUMP WAS STILL PU TTING OUT SYSTEM PRESSURE. SUBMITTER RECOMMENDS FILTER BE INSPECTED TO DETERMINE CAUSE OF FAILURE AND CORRECTIONS BE MA DE ACCORDINGLY. 1 L 7 2 3O 3 O A20SO E14EA 1996052100022 19960521 00022 SW 1996 5 21 96ZZZX2385 1 19960328 G 5711 5147 SPAR BBAVIA 7 7AC 2110102 SW LT/RT WING SPAR DAMAGED G A K NONE O OTHER IN INSP/MAINT 1 CE 01 83032 3721 7AC1688 DISMANTLED LEFT AND RIGHT WING FOR THE PURPOSE OF RECOVERING. WITH THE OLD FABRIC REMOVED, FOUND BOTH REAR SPARS HAD BE EN CHEWED BY MICE MIDWAY BETWEEN THE WING ROOT AND THE STRUT ATTACH FITTING. IT APPEARS THIS DAMAGE WAS PRESENT WHEN TH E WINGS WERE LAST RECOVERED IN 1982 BECAUSE THE CHEW MARKS WERE VARNISHED OVER. THE MAXIMUM DAMAGE THAT CAN EXIST BETWE EN THE SPAR ROOT AND STRUT ATTACH POINT IS .0937 INCH IN DEPTH. ALSO, NO SPAR SPLICING IS ALLOWED IN THIS AREA. 1 H 7 1 3O A759 1996052100023 19960521 00023 SW 1996 5 21 96ZZZX2386 1 19960328 G 5711 5146 SPAR BBAVIA 7 7AC 2110102 SW WING LT FRONT CRACKED G S A K NONE O OTHER IN INSP/MAINT 1 CE 01 83032 3721 7AC1688 DISMANTLED BOTH LEFT AND RIGHT WINGS FOR RECOVERING. ALL SPARS WERE REMOVED FOR CLEANING, INSPECTION, AND VARNISHING. W ITH THE WING SPAR FITTINGS REMOVED, FOUND THE SPAR FITTING HOLES HAD CRACKS EMANATING FROM THE TWO INBOARD HOLES THROUGH THE BUTT OF THE SPAR. ALL FOUR SPARS WERE REPLACED WITH NEW. SUBMITTER RECOMMENDS CLOSE INSPECTION OF ALL ATTACHMENT AREAS OF THE SPARS AT EACH TIME THE WINGS ARE RECOVERED OR REBUILT DUE TO WING IMPACT OR ROLL-OVER. 1 H 7 1 3O A759 1996052100024 19960521 00024 SW 1996 5 21 96ZZZX2387 1 19960328 G 5711 2701 FITTING BBAVIA 7 7AC 2110102 SW LT FRONT SPAR CRACKED F P A K NONE O OTHER IN INSP/MAINT 1 CE 01 83032 3721 7AC1688 DISMANTLED LEFT WING FOR THE PURPOSE OF RECOVERING. AS A PRECAUTION, THE WING SPAR ATTACHMENT FITTINGS WERE MAGNAFLUXED . THE LEFT FRONT WING SPAR ATTACHMENT FITTING WAS FOUND TO HAVE SEVERAL IMPERFECTIONS IN THE WELDED AREA OF BOTH THE TO P AND BOTTOM GUSSETS. THE FITTING WAS REPLACED WITH A NEW PART. IT APPEARS SOME OF THE IMPERFECTIONS ARE FROM PITTING (CORROSION) AND SOME ARE VERY SMALL CRACKS. RECOMMEND NDT AT EACH TIME OF RECOVERING OR REBUILDING AFTER WING IMPACT OF ROLL-OVER DAMAGE. 1 H 7 1 3O A759 1996051600256 19960516 00256 GL 1996 5 16 96ZZZX2388 3 19960223 G 6114 C4239C66 HUB CESSNA 182 182K 2072724 CE MCAULY 2A34C 2A34C66 GL PROPELLER CRACKED H K NONE O OTHER IN INSP/MAINT 1 WP 25 3182Q 896 18258182 805135 PROPELLER WAS SENT IN FOR OVERHAUL DUE TO CALENDAR TIME. HUB WAS FOUND CRACKED FROM MOUNTING STUD HOLE. NEW HUB WAS RE INSTALLED. 1 H 7 1 3O NT 3A13 5 C P3EA 1996051600257 19960516 00257 SO 1996 5 16 96ZZZX2389 2 19960319 G 8550 ENGINE CONT O470 O470R 17026 SO OIL SYSTEM FAILED D A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 EA 03 987908RR ENGINE 235.3 SMOH, 7.6 HRS AFTER NR 4 CYLINDER REMOVED FOR REPAIR. PHILLIPS XC OIL BEING USED. AV BLEND PUT IN ENGINE AFTER CYLINDER WAS REPAIRED. IN-FLIGHT, OIL PRESSURE STARTED TO DECREASE. LANDING MADE OK. AT IDLE, OIL PRESSURE DROP PED TO ZERO PSI, TOTAL FLIGHT TIME, 7 MINUTES. OIL DRAINED, FOUND SLUDGE OF UNKNOWN SUBSTANCE, ABOUT 1-2 TABLESPOONS O F MATERIAL, BROWNISH COLOR, DRAINED OUT WITH OIL. OIL SCREEN WAS VERY CLEAN. NONE OF THIS MATERIAL IN SCREEN. 3 O E273 1996051600258 19960516 00258 EA 1996 5 16 96ZZZX2390 2 19960321 G 8530 SL14995 RETAINER LYC O320 O320E2D 41508 EA CYL PUSH ROD CRACKED H K NONE O OTHER IN INSP/MAINT 1 WP 17 AFTER INSTALLATION AND PROPER TORQUE, THE SPRING RETAINER CRACKED INTO 2 PIECES THROUGH THE STUD HOLE. 3 O E274 1996051600259 19960516 00259 GL 1996 5 16 96ZZZX2391 2 19960220 G 7261 ENGINE CESSNA 206 U206G 2073356 CE ALLSN 250C 250C20 03013 GL OIL SYSTEM CHIP LIGHT B LX5R K NONE J WARNING INDICATION NR NOT REPORTED 1 GL 19 891LL 829 U206G06937 CAE290031 RECEIVED OIL CHIP LIGHT INDICATION. PERFORMED REQUIRED MAINTENANCE PER ALLISON 250-C20S AND SOLOY/CESSNA MAINTENANCE AN D OVERHAUL MANUALS. RECEIVED SECOND CHIP LIGHT INDICATION 3.9 HRS TIS LATER. ENGINE REMOVED AND SENT OUT FOR INSPECTIO N/REPAIR PER ALLISON 250-C20S MAINTENANCE AND OVERHAUL MANUALS. 1 H 7 1 3O 3 U A4CE E4CE 1996051600260 19960516 00260 CE 1996 5 16 96ZZZX2392 1 19960308 G 5312 07126161 BULKHEAD CESSNA 182 182M 2072728 CE LT CUTOUT FS 230 CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 01 70802 3327 18259369 DURING ANNUAL INSPECTION, FOUND AFT BULKHEAD AT FS 230.18 CRACKED AT LEFT RUDDER CABLE CUT OUT. THIS BULKHEAD HAD PREVI OUSLY CRACKED AT THE RIGHT RUDDER CABLE CUT OUT AND WAS REPAIRED. AD 72-07-09 AND CESSNA SB SE72-3 BOTH PERTAIN TO THIS AREA AND DO NOT ALLOW ANY REPAIRS TO THE BULKHEAD. REPLACED BULKHEAD WITH FACTORY NEW PART. AIRCRAFT RETURNED TO SERV ICE. 1 H 7 1 3O NT 3A13 1996051600262 19960516 00262 EA 1996 5 16 96ZZZX2394 2 19960319 G 8530 31C12 STUD GULSTM 112 112A 7630302 SW LYC O360 IO360C1D6 41514 EA NR 4 CYLINDER DETACHED B DWSR L O ABORTED APPROACH OTHER J WARNING INDICATION AP APPROACH 1 SO 05 1189J 189 L1252051A PILOT REPORTED IN-FLIGHT: NOSE GEAR WILL NOT EXTEND NORMALLY, FLY-BY, TOWER VERIFIED NOSE GEAR NOT DOWN. EMERGENCY GEA R EXTENDED, ALL GEAR EXTENDED, SAFE LANDING. FINDINGS: EXHAUST STUD FROM NR 4 CYLINDER FELL OUT AND LODGED IN HINGE SL OT FOR NOSE GEAR DOORS PREVENTING GEAR FROM EXTENDING NORMALLY. COWLING AFT MOUNT DAMAGED, BUT REPAIRABLE. LOGS SHOWED NR 4 EXHAUST GASKET PREVIOUSLY REPLACED. NUT STILL ATTACHED TO STUD AND HELICOIL ON THREADS. 1 L 7 1 3O 3 O A12SO 1E10 1996051600263 19960516 00263 CE 1996 5 16 96ZZZX2395 1 19960401 G 2740 NAS56138 ROLL PIN CESSNA 185 A185F 2072821 CE STABILIZER TRIM SHEARED D K NONE O OTHER IN INSP/MAINT 1 SW 99 101AM 2858 18502390 STABILIZER TRIM CONTROL WHEEL/SHAFT HAD EXCESSIVE PLAY. UPON INSPECTION, FOUND ROLL PINS, P/N NAS561-3-8, BOTH SHEARED AND ONLY RETAINED BY THE SAFETY WIRE PASSED THROUGH THE ROLL PIN PER CESSNA MM FOR ROLL PIN RETENTION. TRIM WHEEL SHAFT HAD THE HOLES OR THE ROLL PINS SEVERELY WORN OBLONG. SUSPECT CAUSE: ROLL PINS SHOULD BE OF DIFFERENT DESIGN OR SOLID PINS INSTALLED. 1 H 7 1 3O 3A24 1996051600264 19960516 00264 CE 1996 5 16 96ZZZX2396 1 19960401 G 2740 07612059 SHAFT CESSNA 185 A185F 2072821 CE STABILIZER TRIM WORN D K NONE O OTHER IN INSP/MAINT 1 SW 99 101AM 2858 18502390 STABILIZER TRIM CONTROL WHEEL/SHAFT HAD EXCESSIVE PLAY. UPON INSPECTION, FOUND ROLL PINS, P/N NAS561-3-8, BOTH SHEARED AND ONLY RETAINED BY THE SAFETY WIRE PASSED THROUGH THE ROLL PIN PER CESSNA MM FOR ROLL PIN RETENTION. TRIM WHEEL SHAFT HAD THE HOLES OR THE ROLL PINS SEVERELY WORN OBLONG. SUSPECT CAUSE: ROLL PINS SHOULD BE OF DIFFERENT DESIGN OR SOLID PINS INSTALLED. 1 H 7 1 3O 3A24 1996051600265 19960516 00265 CE 1996 5 16 96ZZZX2397 1 19960125 G 5522 123463315 ELEVATOR EDGE 123463321 CESSNA 210 210M 2073450 CE LT ELEVATOR CORRODED D K NONE O OTHER IN INSP/MAINT 1 GL 09 761AQ 21062105 DURING INSPECTION PRIOR TO PAINTING, FOUND CORROSION ON INBOARD LOWER SURFACE OF ELEVATOR TRAILING EDGE. TWO HOLES APPR OXIMATELY .125 INCH DIAMETER ALONG WITH SMALLER PIN HOLES WERE FOUND. SUSPECT CAUSE, FOAM IN TRAILING EDGE RETAINING WA TER INSIDE TRAILING EDGE ASSY. SUGGEST CLOSE INSPECTION OF FOAM FILLED SURFACES. 1 H 7 1 3O 3A21 1996051600267 19960516 00267 EA 1996 5 16 96ZZZX2399 2 19960225 G 8550 62817 FILTER SCREEN MOONEY M20 M20C 5870208 SW LYC O360 O360A1D 41514 EA ACCESSORY CASE SPLIT D K NONE O OTHER IN INSP/MAINT 1 EA 27 7821V 2805 RL1289236A DURING ANNUAL, OIL PRESSURE SCREEN WAS REMOVED AND CHECKED FOR METAL, ETC. AFTER SCREEN WAS CLEANED IN PARTS WASHER, IT WAS NOTED THE SOLDERED SEAM OF THE INNER FINE MESH SCREEN WAS SPLIT. ON CLOSER INSPECTION, THE OUTER SCREEN SHOWED APP ROXIMATELY FOUR STRANDS SEPARATED FROM THE SOLDER. THE AREA OF SEPARATION IS MIDWAY AND THE SCREEN LOOKS AS IF IT WAS S WOLLEN. SUSPECT AGE, HEAT CHANGES, AND DIFFERENTIAL OF PRESSURES ON THE INNER AND OUTER SIDES OF SCREEN FROM DIRT, GRIT , AND COLD THICK OIL WERE CAUSES. SUBMITTER STATED MORE FREQUENT AND THOROUGH CLEANING OF SCREEN OR REPLACMENT AT INTER VALS (500 HOURS OR 5 YEARS). 1 L 7 1 3O 3 O 2A3 E286 1996051600268 19960516 00268 SO 1996 5 16 96ZZZX2400 1 19960308 G 3510 BRACKET PIPER PA32 PA32R301T 7103220 SO OXYGEN BOTTLE CRACKED D K NONE O OTHER IN INSP/MAINT 1 GL 19 4383M 32R8529002 TOTAL TIME, 2,400 HOURS. ALL 4 BRACKETS USED TO ATTACH THE OXYGEN BOTTLE RACK TO THE SIDES OF THE REAR FUSELAGE WERE FO UND CRACKED DURING ANNUAL INSPECTION. SUSPECT CAUSE: BRACKETS NOT STRONG ENOUGH TO SUPPORT WEIGHT. REMAKE BRACKETS OU T OF THICKER MATERIAL AND BEND A LARGER 'L' SHAPED BRACKET. BRACKETS INSTALLED ON AFT FUSELAGE SIDE SKINS, PN 99470-800 AND PN 99470-01, FS 210.00. 1 L 7 1 3O A3SO 1996051600269 19960516 00269 CE 1996 5 16 96ZZZX2401 1 19960320 G 7714 MS3106A10S CONNECTOR PLUG MS250382 CESSNA 414 414A 2075907 CE TACHOMETER GEN PINS STRIPPED D O OTHER O OTHER TO TAKEOFF 1 WP 13 6604C A12356 414A0030 LEFT ENGINE TACHOMETER FAILED ON TAKEOFF ROLL. PRE-INSPECTION, CONNECTOR PLUG SECURED AND SAFETIED. IT WAS DISCOVERED THE LEFT TACHOMETER GENERATOR ELECTRICAL CONNECTOR PLUG ELECTRICAL PINS HAD STRIPPED. CONNECTOR PLUG REPLACED. AIRCRAF T RETURNED TO SERVICE. 1 L 7 2 3O A7CE 1996051600273 19960516 00273 CE 1996 5 16 96ZZZX2405 1 19960201 G 2810 FUEL CAP CESSNA 180 180J 2072622 CE LT TANK DEFECTIVE C O OTHER O OTHER CR CRUISE 1 CE 07 6WH 18052492 THE ORIGINAL FLUSH FUEL CAPS AND PLATES WERE REPLACED SEVERAL YEARS AGO WITH 'UMBRELLA' CAPS AND PLATES SOLD BY CESSNA. THE CAPS WERE RED PLASTIC. DURING A FLIGHT IN FEBRUARY OF THIS YEAR, APPROXIMATELY 6 GALLONS OF GAS SIPHONED OUT OF LE FT TANK. DURATION OF THE FLIGHT WAS 5.50 HOURS. SENDING THE ASSY FOR EXAMINATION. 1 H 7 1 3O 5A6 1996051600274 19960516 00274 CE 1996 5 16 96ZZZX2406 1 19960322 G 2913 571302 MOTOR BEECH B300 B300 1159232 CE HYD POWER PACK FAILED B AKGR A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CE 05 8116N 1696 929A FL58 GEAR WOULD NOT COME UP. JACKED AIRCRAFT, GROUND OPERATION NORMAL. REPLACED HYDRAULIC POWER PACK MOTOR. TEAR DOWN OF R EMOVED MOTOR FOUND SPLICE USED TO CONNECT THE B-PLUS WIRE COMING FROM THE RF FILTER TO THE SOLID WIRES OF THE MOTORS, WA S NOT THE PROPER TYPE AND ONE OF THE WIRES WAS NOT EVEN IN THE SPLICE CRIMPED AREA. 2 L 7 2 4T RT A24CE 1996051600275 19960516 00275 SO 1996 5 16 96ZZZX2407 2 19960402 G 8530 646303 PISTON CESSNA 421 421C 2076016 CE CONT O520 GTSIO520N 17032 SO LT ENG NR 5 BURNED B ITWR K NONE R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 NM 07 67934 900 421C1026 610051 AIRCRAFT LOST POWER ON NR 1 ENGINE. REMOVAL OF NR 5 CYLINDER REVEALED PISTON DOME EDGE BURNED AWAY FROM 6:00 POSITION T O 12:00 POSITION. AT 9:00 POSITION, PISTON DOME BURNED COMPLETELY THROUGH, APPROXIMATELY 1 INCH OF PISTON MATERIAL MISS ING FROM EDGE TOWARDS CENTER OF DOME. 1 L 7 2 3O 3 O A7CE E7CE 1996051600276 19960516 00276 SO 1996 5 16 96ZZZX2408 2 19960320 G 8530 CYLINDER CESSNA 210 210L 2073448 CE CONT O520 IO520L 17032 SO ROCKER BOSS CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 99 732DZ 1669 21061446 567326 FIVE OF SIX CYLINDERS HAVE CRACKS IN ROCKER BOSS AREA UP TO THE ROCKER SHAFT RETAINING BOLTS. TWO OF THESE FIVE HAVE CR ACKS ON INTAKE AND EXHAUST BOSSES. THIS ENGINE DOES NOT INCORPORATE LONG BOLTS AND SOLID SHAFTS. 1 H 7 1 3O 3 O 3A21 E5CE 1996051600277 19960516 00277 CE 1996 5 16 96ZZZX2409 1 19960307 G 2720 031019613 SPRING CESSNA 150 150K 2071822 CE RUDDER RETURN BROKEN D K NONE O OTHER IN INSP/MAINT 1 GL 09 5738G 6130 15071238 RUDDER RETURN SPRING ON COPILOT'S LEFT PEDAL WAS FOUND BROKEN. NO RECORD OF SPRING EVER BEING REPLACED. SUSPECT CAUSE WAS METAL FATIGUE. 1 H 7 1 3O 3A19 1996051600278 19960516 00278 SO 1996 5 16 96ZZZX2410 2 19960307 G 8540 99101371 SHAFT CESSNA 421 421C 2076016 CE CONT O520 GTSIO520H 17032 SO RT ENG HYD SHEARED D K NONE O OTHER IN INSP/MAINT 1 GL 09 215MP 421C1231 FOUND DRIVE SHAFT ON AIR CONDITIONING, HYDRAULIC PUMP SHEARED. UPON REMOVAL, SYSTEM HYDRAULIC PUMP SHAFT SPLINES WERE F OUND WORN OUT AND RUSTED. SUBMITTER SUGGESTS SPLINES BE LUBED AT 200-HOUR INTERVALS TO PREVENT THIS PROBLEM FROM RECURR ING. 1 L 7 2 3O 3 O A7CE E7CE 1996051600279 19960516 00279 CE 1996 5 16 96ZZZX2411 1 19960311 G 3211 SCREWS CESSNA 310 310R 2074245 CE TRUNNION SUPPORT LOOSE B EBVR K NONE O OTHER IN INSP/MAINT 1 GL 09 200LE 310R1842 DURING AN UNRELATED INSPECTION, THE 4 MAIN GEAR TRUNNION SUPPORT (PN'S LT AFT, 0822724-11, LT FWD, 0822720-19, RT AFT, 0 822724-10, RT FWD, 0822720-18) VERTICAL MOUNTING NAS SCREWS SECURING THE MOUNTS TO THE WING RIBS (PN'S LT, 5022104-51, R T, 5022104-52) WERE FOUND LOOSE AND WORKING. CLOSER INSPECTION FOUND ALL BUT 7 SCREWS OUT OF ABOUT 50, THE NUTS WERE BO TTOMED ON THE THREADS. MINIMAL WORKING DAMAGE, WASHERS WERE ADDED, AND SCREWS TORQUED TO SPECS. 1 L 7 2 3O 3A10 1996051600280 19960516 00280 SO 1996 5 16 96ZZZX2412 2 19960320 G 8530 ENGINE CESSNA 210 T210M 2073451 CE CONT O520 TSIO520R 17040 SO CYLINDER DEFECTIVE B EBVR K NONE O OTHER IN INSP/MAINT 1 GL 09 761TF 1975 21062499 PRE-PURCHASE INSPECTION OF AIRCRAFT REVEALED ENGINE COMPRESSION WELL BELOW ACCEPTABLE LIMITS, SEAT RAILS WERE WORN BEYON D LIMITS. ESTABLISHED BY AIRWORTHINESS DIRECTIVE. ELEVATOR TRIM TAB WITH HOLES CORRODED THROUGH THE TAB SKIN. AIRCRAF T WAS ANNUALLED THE FIRST WEEK OF MARCH, 1996, AND LESS THAN 2 HOURS AGO. 1 H 7 1 3O 3 O 3A21 E8CE 1996051600281 19960516 00281 CE 1996 5 16 96ZZZX2413 1 19960329 G 3520 OXYGEN MASK BEECH 90 F90 1152909 CE HEADLINER FAIL DEPLOY D K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 99 7775 LA117 DURING ROUTINE MAINTENANCE, THE OXYGEN AUTO-DEPLOY SYSTEM WAS ACTIVATED. ALL MASKS FAILED TO DEPLOY. THE CAUSE WAS THE NEW HEADLINER MATERIAL THICKNESS WHICH PREVENTED THE ACTUATOR PLUNGER FROM CONTACTING THE STRIKER PLATE ON THE MASK CON TAINER. THIS IS THE FIRST TIME THIS SYSTEM HAD BEEN ACTIVATED SINCE THE AIRCRAFT HAS BEEN RE-TRIMMED ON 11-11-93. 1 L 7 2 4T A31CE 1996051600282 19960516 00282 SO 1996 5 16 96ZZZX2414 2 19960417 G 7414 10357586 DISTRIBUTOR GEAR BENDIX S6RN201 CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO RT MAGNETO TEETH MISSING I K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 NE 05 3249M 1161 K1411M 402C0296 ENGINE ROUGNESS NOTED. INSPECTION REVEALED RIGHT MAGNETO DISTRIBUTOR GEAR MISSING SOME OF ITS TEETH (NOTED 259.6 HRS SI NCE ITS LAST INSPECTION). CAUSE UNKNOWN. 1 L 7 2 3O 3 O A7CE E8CE 1996051600283 19960516 00283 CE 1996 5 16 96ZZZX2415 1 19960408 G 2820 LINE CESSNA 402 402B 207590P CE FUEL CROSS FEED LEAKING I K NONE K B FLUID LOSS SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 NE 05 87147 7001 402B1003 UPON LANDING, FLIGHT CREW SMELLED FUEL. AFTER PULLING PANEL TO REVEAL CROSS-FEED LINE, FOUND A PIN HOLE, EVER SO SMALL, SPRAYING FUEL. THIS IS AN OPEN ACCESS LINE AND EVEN WITH A GOOD INSPECTION FINDING FUEL STAINS, ARE THE ONLY CLUES OF THIS LINE DETERIORATING. NOTE: MEB 87-7-R1. 1 L 7 2 3O A7CE 1996051600284 19960516 00284 EU 1996 5 16 96ZZZX2416 1 19960413 G 7810 MUFFLER MRCHTI S205 S20522R 8120412 EU BAFFLE DEFECTIVE G K NONE R PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 GL 15 954W 919 4154 DURING AN ACCIDENT INVESTIGATION, FOUND LEFT SIDE EXHAUST MUFFLER HAD AN INTERNAL BAFFLE/END PLUG THAT WAS NOT SECURED A ND, THUS, ALLOWED EXHAUST GAS TO BE VENTED DIRECTLY TO THE EXHAUST PIPE. IT IS SPECULATED THIS CONDITION WOULD ALLOW IM PROPER EXHAUST BACK PRESSURE AND DEGRADE ENGINE PERFORMANCE. DURING THE REQUIRED INSPECTIONS, IT IS RECOMMENDED THAT A CAREFUL INSPECTION BE MADE OF THE BAFFLE AND DIFFUSSERS TO ASSURE INTERNAL SECURITY OF THESE ITEMS. 1 L 7 1 3O A9EU 1996051600287 19960516 00287 1996 5 16 96ZZZX2419 1 19960420 G 2822 3B74 FUEL PUMP AIRBORNE BOOST FAILED D K NONE O OTHER IN INSP/MAINT 1 GL 13 5AC29 FUEL PUMP CAVITY WORN, VANES BROKEN DUE TO UNBALANCED CONDITION OF ARMATURE. 1996051600288 19960516 00288 1996 5 16 96ZZZX2420 1 19960420 G 2822 1C61 FUEL PUMP AIRBORNE BOOST FAILED D K NONE O OTHER IN INSP/MAINT 1 GL 13 2T824 FUEL PUMP IMPELLER CAME APART, POSSIBLE GLUE OR EPOXY FAILURE. EPOXIED BACK TOGETHER. 1996051600289 19960516 00289 1996 5 16 96ZZZX2421 1 19960420 G 2822 1C61 FUEL PUMP AIRBORNE BOOST FAILED D K NONE O OTHER IN INSP/MAINT 1 GL 13 2T863 FUEL PUMP IMPELLER CAME APART, POSSIBLE GLUE OR EPOXY FAILURE. EPOXIED BACK TOGETHER. 1996051600290 19960516 00290 1996 5 16 96ZZZX2422 1 19960420 G 2822 1C61 FUEL PUMP AIRBORNE BOOST FAILED D K NONE O OTHER IN INSP/MAINT 1 GL 13 5P135 FUEL PUMP IMPELLER CAME APART, POSSIBLE GLUE OR EPOXY FAILURE. EPOXIED BACK TOGETHER. 1996051600291 19960516 00291 1996 5 16 96ZZZX2423 1 19960420 G 2822 2B729 FUEL PUMP AIRBORNE BOOST FAILED D K NONE O OTHER IN INSP/MAINT 1 GL 13 3AB77 FUEL PUMP CAVITY WORN, VANES BROKEN DUE TO UNBALANCED CONDITION OF ARMATURE. 1996051600292 19960516 00292 1996 5 16 96ZZZX2424 1 19960420 G 2822 1B56 FUEL PUMP AIRBORNE BOOST FAILED D K NONE O OTHER IN INSP/MAINT 1 GL 13 4T321 FUEL PUMP CAVITY WORN, VANES BROKEN DUE TO UNBALANCED CONDITION OF ARMATURE. 1996051600293 19960516 00293 1996 5 16 96ZZZX2425 1 19960420 G 2822 2B664 FUEL PUMP AIRBORNE BOOST FAILED D K NONE O OTHER IN INSP/MAINT 1 GL 13 8AF110 FUEL PUMP CAVITY WORN, VANES BROKEN DUE TO UNBALANCED CONDITION OF ARMATURE. 1996051600294 19960516 00294 GL 1996 5 16 96ZZZX2426 3 19960419 G 6114 D7019C92 HUB CESSNA 421 421B 2076014 CE MCAULY 3AF32C 3AF32C* GL BLADE SOCKET CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 112SW 1642 805941 421B0350 805841 INSPECTION FOUND BLADE SOCKET THREADS CRACKED. 1 L 7 2 3O A7CE 5 C P22EA 1996051600295 19960516 00295 CE 1996 5 16 96ZZZX2427 1 19960417 G 3230 12436351 TORQUE LINK CESSNA 206 U206G 2073356 CE NLG UPPER CRACKED D P K NONE O OTHER IN INSP/MAINT 1 EA 07 756TE U20604337 CRACKED UPPER TORQUE LINK ON NOSE GEAR. DEFECT FOUND DURING 100-HOUR INSPECTION AND LUBRICATION OF NOSE GEAR. SUSPECT CAUSE MAY BE WORN STOP LUG ON SCISSORS. THE TWO CRACKS LOCATED APPROXIMATELY 2 INCHES FROM END OF SCISSORS BOTTOM SIDE. 1 H 7 1 3O A4CE 1996051600296 19960516 00296 SO 1996 5 16 96ZZZX2428 1 19960225 G 7120 65000000 MOUNT PIPER PA28 PA28235 7102810 SO NLG SUPPORT FAILED G A O OTHER O OTHER LD LANDING 1 EA 27 8831W 3196 2810378 DURING LANDING AT AIRPORT, NOSE GEAR COLLAPSED. PILOT SHUT DOWN THE ENGINE, AIRCRAFT CAME TO REST ABOUT 210 FEET FROM T HE INCIDENT. THE PILOT AND THE OCCUPANTS SUFFERED NO INJURIES. THE AIRCRAFT WAS TAKEN TO THE HANGAR. BLADE TIPS AND T HE BOTTOM ENGINE COWL HAD MINOR DAMAGE. A TEAR-DOWN INSPECTION OF THE NOSE GEAR REVEALED CORROSION UNDER THE SUPPORT BR ACKET. THE ENGINE SENT FOR A HIDDEN DAMAGE INSPECTION. 1 L 7 1 3O 2A13 1996051600297 19960516 00297 SO 1996 5 16 96ZZZX2429 1 19960325 G 3230 6774803 ACTUATOR PIPER PA28 PA28RT201 7102818 SO EMERG EXTENSION ARM DISENGAGED D L A K NONE O OTHER NR NOT REPORTED 1 GL 03 8162S 2191 28R8018042 GEAR ACTUATOR ARM BECAME DISENGAGED FROM PUSH ROD ARM; THUS, DISABLING EMERGENCY EXTENSION FUNCTION OF MAIN LANDING GEAR . 1 L 7 1 3O 2A13 1996051600298 19960516 00298 CE 1996 5 16 96ZZZX2431 1 19960415 G 3230 35815109 UPLOCK CABLE BEECH 36 A36 1151604 CE MLG UPLOCK FRAYED D S K NONE O OTHER IN INSP/MAINT 1 GL 05 1058W 2966 E409 DURING ANNUAL INSPECTION, UPLOCK CABLE, LEFT GEAR, CABLE TENSION LOW. FOUND 3 BROKEN CABLE STRANDS AND FITTING MS20667- 2 BENT IN THREADED AREA. CHECKED RIGHT UPLOCK ALSO. FOUND TERMINAL MS20667-2 BENT. IT APPEARS THAT THE DAMAGE OCCURS WHEN TERMINAL MS20667-2 IS SCREWED IN TOO FAR TO TERMINAL MS201259-2R. SUBMITTER RECOMMENDS CHANGING TO BEECHCRAFT MM G EAR RIGGING PROCEDURES. 1 L 7 1 3O 3A15 1996051600299 19960516 00299 CE 1996 5 16 96ZZZX2432 1 19960415 G 3230 MS206672 FITTING BEECH 36 A36 1151604 CE UPLOCK CABLE BENT D K NONE O OTHER IN INSP/MAINT 1 GL 05 1058W 2966 E409 DURING ANNUAL INSPECTION, UPLOCK CABLE, LEFT GEAR, CABLE TENSION LOW. FOUND 3 BROKEN CABLE STRANDS AND FITTING MS20667- 2 BENT IN THREADED AREA. CHECKED RIGHT UPLOCK ALSO. FOUND TERMINAL MS20667-2 BENT. IT APPEARS THAT THE DAMAGE OCCURS WHEN TERMINAL MS20667-2 IS SCREWED IN TOO FAR TO TERMINAL MS201259-2R. SUBMITTER RECOMMENDS CHANGING TO BEECHCRAFT MM G EAR RIGGING PROCEDURES. 1 L 7 1 3O 3A15 1996051600300 19960516 00300 SO 1996 5 16 96ZZZX2433 1 19960214 G 2140 460755 FUEL STRAINER 481666 PIPER PA23 PA23 7102302 SO HEATER LEAKING B L A RX7R K NONE K FLUID LOSS IN INSP/MAINT 1 SW 15 2018P 23590 HEATER FUEL STRAINER CRACKED/CORRODED. WHEN FUEL VALVE TO HEATER WAS OPENED, FUEL POURED OUT INTO NOSE CONE SECTION. V ERY SEVERE LEAK. PILOT IMMEDIATELY SMELLED FUEL AND SHUT VALVE OFF. HAD HE NOT, THERE COULD HAVE BEEN A FIRE AND/OR EX PLOSION. APPEARED CLAMPING NUT HAD BEEN OVERTORQUED. ALSO, FUEL STRAINER APPEARED NOT TO HAVE BEEN REMOVED AND CLEANED RECENTLY. SEVERE CORROSION. SKINNER PURIFIER FUEL SCREEN. 1 L 7 2 3O 1A10 1996051600301 19960516 00301 SO 1996 5 16 96ZZZX2434 1 19960308 G 5712 6202100 RIB PIPER PA28 PA28R201 7102816 SO RT WING CRACKED B A OG5R K NONE O OTHER IN INSP/MAINT 1 GL 21 805ND 5928 2837008 FOUND BOTH RIBS CRACKED WHERE FLANGE RIVETS AND BOLTS TO MAIN SPAR. CRACK IS APPROXIMATELY 1 INCH LONG AND ORIGINATES B Y EDGE OF WASHER/NUT FOR TOP BOLT OF GEAR FITTING PN 95643-06 AND PN 95643-07. 1 L 7 1 3O 2A13 1996051600302 19960516 00302 SO 1996 5 16 96ZZZX2435 1 19960308 G 5712 6202101 RIB PIPER PA28 PA28R201 7102816 SO LT WING CRACKED B OG5R K NONE O OTHER IN INSP/MAINT 1 GL 21 805ND 5928 2837008 FOUND BOTH RIBS CRACKED WHERE FLANGE RIVETS AND BOLTS TO MAIN SPAR. CRACK IS APPROXIMATELY 1 INCH LONG AND ORIGINATES B Y EDGE OF WASHER/NUT FOR TOP BOLT OF GEAR FITTING PN 95643-06 AND PN 95643-07. 1 L 7 1 3O 2A13 1996051600303 19960516 00303 GL 1996 5 16 96ZZZX2436 3 19960325 G 6111 V84334 BLADE GULSTM 500 500S 0141107 SW HARTZL HCA3V HCA3VK2 GL SHANK CRACKED B A WN1R K NONE O OTHER IN INSP/MAINT 1 SW 19 4860E 3100 B29226 180717 BJ851 BLADE CRACK FOUND WITH EDDY CURRENT. WOULD NOT SHOW UP WITH DYE CHECK. SUBMITTER SUGGESTS REVISING AD 68-19-04 AND AD 68-13-02 TO MAKE EDDY CURRENT MANDATORY. 1 H 7 2 3O 6A1 5 C P6EA 1996051600304 19960516 00304 EU 1996 5 16 96ZZZX2437 2 19960322 G 7314 996590 PUMP DIAMON DA20A1 DA20A1 05626UX GL ROTAX 912 ROTAX912 55555 EU ENGINE OIL LEAK D K NONE K FLUID LOSS IN INSP/MAINT 1 SW 99 526SS 24 10085 FUEL PUMP STARTED LEAKING OIL AT SEAM WHERE DIAPHRAM WAS IN PUMP. 1 L 7 1 3O 3 I NT TA4CH EXPE3I 1996051600305 19960516 00305 NE 1996 5 16 96ZZZX2438 1 19960116 G 3212 7625100702042 EXPLOSIVE LINK SKRSKY S76 S76A 8143006 NE MLG MALFUNCTION B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 5446E 0375 76075 INADVERTENT FLOAT DEPLOYMENT. SQUIBS FIRED, BUT LINK FAILED TO SEPARATE. WHEN FLOATS WERE INADVERTENTLY INFLATED, THE EXPLOSIVE LINK FAILED TO SEPARATE ON ONE GEAR DOOR. UNABLE TO DETERMINE WHY THE LINK FAILED TO SEPARATE. 1 G 7 2 3U H1NE 1996051600365 19960516 00365 SW 1996 5 16 96ZZZX2447 1 19960415 G 3213 206030104123 FITTING BELL 206 206L4 1182110 SW FWD LANDING GEAR CRACKED B S A ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 170AL 2750 52063 DURING SERVICE CHECK, NOTED MLG FITTING WAS CRACKED. FITTING WAS FOUND CRACKED IN THE SAME AREA AS REPORTED ON MDR SUBM ITTED ON 2-7-94. THE FITTING WAS MANUFACTURED IN OCTOBER, 1992, WHICH IS DIFFERENT FROM THE PREVIOUSLY REPORTED CRACKED FITTINGS. 1 G 7 1 3U NC H2SW 1996051600366 19960516 00366 SW 1996 5 16 96ZZZX2448 1 19960320 G 6230 206010335001 LEVER ASSY 206010350021 BELL 206 206L3 1182108 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 362AL 505 51471 DURING DAILY INSPECTION, FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-3 38-001 SPACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-01 0-470-101 BEARING. SUSPECT NORMAL USE CAUSES PART TO WEAR OUT TOO SOON. WORN PARTS TT 505.1 HOURS. 1 G 7 1 3U H2SW 1996051600367 19960516 00367 SW 1996 5 16 96ZZZX2449 1 19960320 G 6230 206010336005 LINK IDLER 206010350021 BELL 206 206L3 1182108 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 362AL 505 51471 DURING DAILY INSPECTION, FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-3 38-001 SPACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-01 0-470-101 BEARING. SUSPECT NORMAL USE CAUSES PART TO WEAR OUT TOO SOON. WORN PARTS TT 505.1 HOURS. 1 G 7 1 3U H2SW 1996051600368 19960516 00368 SW 1996 5 16 96ZZZX2450 1 19960320 G 6230 206010335001 LEVER ASSY 206010350021 BELL 206 206L1 1182107 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 5734M 701 45449 DURING DAILY INSPECTION, FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-3 38-001 SPACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-01 0-470-101 BEARING. SUSPECT NORMAL USE CAUSES PART TO WEAR OUT TOO SOON. WORN PARTS TT 701.2 HOURS. 1 G 7 1 3U H2SW 1996051600369 19960516 00369 SW 1996 5 16 96ZZZX2451 1 19960320 G 6230 206010336005 LINK IDLER 206010350021 BELL 206 206L1 1182107 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 5734M 701 45449 DURING DAILY INSPECTION, FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-3 38-001 SPACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-01 0-470-101 BEARING. SUSPECT NORMAL USE CAUSES PART TO WEAR OUT TOO SOON. WORN PARTS TT 701.2 HOURS. 1 G 7 1 3U H2SW 1996051600370 19960516 00370 SW 1996 5 16 96ZZZX2452 1 19960415 G 3213 206030104123 FITTING BELL 206 206L1 1182107 SW FWD LANDING GEAR CRACKED B S A ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 5734M 2198 45449 DURING SERVICE CHECK, NOTED MLG FITTING WAS CRACKED. FITTING WAS FOUND CRACKED IN THE SAME AREA AS REPORTED ON MDR SUBM ITTED ON 2-7-94. THE FITTING WAS MANUFACTURED IN OCTOBER, 1992, WHICH IS DIFFERENT FROM THE PREVIOUSY REPORTED CRACKED FITTINGS. 1 G 7 1 3U H2SW 1996051600371 19960516 00371 EU 1996 5 16 96ZZZX2453 1 19960410 G 6230 350A37100205 NON ROTATE STAR 355A37000001 AEROSP AS355 AS355F 8680806 EU SWASHPLATE WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 5787E 6624 M433 5058 DAILY INSPECTION FOUND SERVO TO STAR ATTACH POINT WORN BEYOND LIMITS AND SERVO ROD END WEARING INTO STAR. 1 G 7 2 3U H11EU 1996051600506 19960516 00506 1996 5 16 96ZZZX2454 4 19960322 G 2215 0107P5 SERVO STEC CESSNA 206 U206F 2073333 CE PITCH SERVO LEADS SHORTING D K NONE O OTHER IN INSP/MAINT 1 GL 21 2216U 4536A U20602355 SERVO MOTOR LEADS SHORTING TO FRAME OF PITCH SERVO ONLY WHEN TORQUE APPLIED ON MOTOR WHICH CAUSES PITCH OSCILLATION, PLU S OR MINUS 1,500 FEET/MINUTE. SUBMITTER RECOMMENDS ROUTING TO PREVENT TOUCHING FRAME. 1 H 7 1 3O A4CE 1996051600507 19960516 00507 1996 5 16 96ZZZX2455 4 19960415 G 6113 1250030R201 SPINNER CESSNA 207 207A 2073604 CE MCAULY D3A34 D3A34C404 GL PROPELLER DOME FAILED E O OTHER D INFLIGHT SEPARATION CR CRUISE 1 WP 19 73426 13600 20700588 796960 FORWARD THIRD OF SPINNER DEPARTED AIRPLANE IN-FLIGHT. FOUND SPINNER DOME STABILIZER PN 0550340-1 HAD WORN THROUGH THE S PINNER CAUSING A WEAK SPOT WHICH EVENTUALLY CAUSED THE FAILURE. SUBMITTER SUGGESTS THE POSSIBLE CAUSE WAS IMPROPER SHIM MING OF THE STABILIZER OVER THE YEARS. WHENEVER THE SPINNER IS REMOVED AND REINSTALLED IT SHOULD BE DONE PER CESSNA MM. 1 H 7 1 3O A16CE 5 C P47GL 1996051600508 19960516 00508 1996 5 16 96ZZZX2456 4 19960310 G 2562 BP1025 BATTERY MERL BEECH 36 A36 1151604 CE ELT LEAKING D K NONE K FLUID LOSS IN INSP/MAINT 1 SW 15 601SW E904 CONDUCTING A 91.207 INSPECTION OF ELT, FOUND BATTERY LEAKING 12 MONTHS AFTER INSTALLATION. THIS IS THE SECOND MERL BATT ERY FOUND IN THIS CONDITION. 1 L 7 1 3O 3A15 1996051600509 19960516 00509 CE 1996 5 16 96ZZZX2457 1 19960415 G 3250 35825005 BOLT 35825196 BEECH 36 A36 1151604 CE NLG STEERING BENT D K NONE O OTHER IN INSP/MAINT 1 GL 05 1058W 2966 E409 OWNER INDICATED NOSE GEAR HIT AN OBSTRUCTION ON THE RUNWAY. REMOVED NOSE GEAR ASSY PN 35-825196. FOUND BOLT BENT. NO OTHER DAMAGE FOUND. 1 L 7 1 3O 3A15 1996051600510 19960516 00510 SO 1996 5 16 96ZZZX2458 1 19960412 G 3210 AN6H14A SADDLE BOLT PIPER PA38 PA38112 7103812 SO LT/RT MLG BENT D K NONE O OTHER IN INSP/MAINT 1 NE 01 9171A 3882A0119 BOTH LEFT AND RIGHT MAIN GEAR BOLTS (AN7-17A) AND ONE SADDLE BOLT FROM EACH SIDE (AN6H-14A) WERE BENT. 1 L 7 1 3O A18SO 1996051600511 19960516 00511 SO 1996 5 16 96ZZZX2459 1 19960412 G 3210 AN717A BOLT PIPER PA38 PA38112 7103812 SO LT/RT MLG BENT D K NONE O OTHER IN INSP/MAINT 1 NE 01 9171A 3882A0119 BOTH LEFT AND RIGHT MAIN GEAR BOLTS (AN7-17A) AND ONE SADDLE BOLT FROM EACH SIDE (AN6H-14A) WERE BENT. 1 L 7 1 3O A18SO 1996051600512 19960516 00512 CE 1996 5 16 96ZZZX2460 1 19960319 G 3240 BRAKE FLUID CESSNA 182 182Q 2072732 CE BRAKE SYSTEM CONTAMINATED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 EA 07 97523 18267119 PILOT REPORTED NO BRAKING ACTION, SUSPECTED ICE AND SNOW IN BRAKE CYLINDER. NONE FOUND. AIRCRAFT BROUGHT INTO HEATED H ANGAR. BOTH BRAKES WERE BLED DOWN OF ALL FLUID, FOUND TO HAVE MORE WATER THAN BRAKE FLUID. SYSTEM FLUSHED COMPLETE AND SERVICED WITH 5606 HYDRAULIC FLUID. CONDENSATION NOT SUSPECTED DUE TO AMOUNT OF WATER. SUSPECT POSSIBLY DUE TO CONTAM INATED SERVICE EQUIPMENT. 1 H 7 1 3O NT 3A13 1996051600513 19960516 00513 SO 1996 5 16 96ZZZX2461 1 19960415 G 3230 8194702 ROD ASSY PIPER PA31T PA31T3 7103128 SO NLG RETRACT FROZE UP D O OTHER O OTHER CL CLIMB 1 AL 01 218CS 8061 31T8275016 NOSE GEAR WOULD NOT STAY UP AND LOCKED AFTER GEAR SELECTOR RETURNED TO NEUTRAL IN-FLIGHT. ALL OTHER GEAR FUNCTIONS WERE NORMAL. FOUND MOISTURE UNDER DUST BOOTS ON NORMAL AND EMERGENCY UPLOCK HOOK RETRACT RODS. DRIED ROD ASSYS AND BOOTS W ITH COMPRESSSED AIR, LUBED RODS, AND REINSTALLED BOOTS. RETRACT TEST OK. FLIGHT WAS CONDUCTED UNDER FREEZING TEMPS. R OD ASSY FROZE IN RETRACTED POSITION. 1 L 7 2 3T A8EA 1996051600514 19960516 00514 SO 1996 5 16 96ZZZX2462 1 19960415 G 3230 4194900 ROD ASSY PIPER PA31T PA31T3 7103128 SO NLG RETRACT FROZE UP D O OTHER O OTHER CL CLIMB 1 AL 01 218CS 8061 31T8275016 NOSE GEAR WOULD NOT STAY UP AND LOCKED AFTER GEAR SELECTOR RETURNED TO NEUTRAL IN-FLIGHT. ALL OTHER GEAR FUNCTIONS WERE NORMAL. FOUND MOISTURE UNDER DUST BOOTS ON NORMAL AND EMERGENCY UPLOCK HOOK RETRACT RODS. DRIED ROD ASSYS AND BOOTS W ITH COMPRESSSED AIR, LUBED RODS, AND REINSTALLED BOOTS. RETRACT TEST OK. FLIGHT WAS CONDUCTED UNDER FREEZING TEMPS. R OD ASSY FROZE IN RETRACTED POSITION. 1 L 7 2 3T A8EA 1996051600516 19960516 00516 CE 1996 5 16 96ZZZX2464 1 19960502 G 2842 C6680500802 TRANSMITTER CESSNA 172 172P 2072436 CE LT FUEL QTY FLOAT DAMAGED D K NONE K FLUID LOSS IN INSP/MAINT 1 NM 03 6601K 1034 17274218 DURING 100-HOUR INSPECTION, THE LT FUEL QUANTITY TRANSMITTER WAS REMOVED TO REPLACE LEAKING GASKET AND SCREW SEALS. UPO N REMOVAL OF THE ROCHESTER TRANMSITTER, FOUND THE FLOAT WAS CONTACTING THE TOP AND BOTTOM OF THE FUEL TANK CAUSING THE C OMPOSITE FLOAT TO DISINTEGRATE. BLACK FLOAT RESIDUE WAS IN THE BOTTOM OF THE FUEL TANK AND IN THE MAIN FUEL STRAINER. N EW TRANSMITTER KIT SK 172-117 IS INSTALLED WITH 1034.1 HOURS TOTAL TIME. 1 H 7 1 3O NT 3A12 1996051600517 19960516 00517 CE 1996 5 16 96ZZZX2465 1 19960318 G 5541 04330106 SPAR SKIN CESSNA 150 152 2071835 CE RUDDER FWD CRACKED D S K NONE O OTHER IN INSP/MAINT 1 NM 07 4713Q 7687 15285054 RUDDER FORWARD SKIN CRACKED JUST BELOW UPPER HINGE POINT. THIS ACTS AS THE FORWARD RUDDER SPAR. SKIN (SPAR) WAS CRACKE D ON BOTH SIDES, AND CRACKS EXTENDED HORIZONTALLY FROM THE LIGHTENING HOLE TO THE BEND RADIUS. 1 H 7 1 3O NT 3A19 1996051600518 19960516 00518 CE 1996 5 16 96ZZZX2466 1 19960401 G 2710 NAS428310 BOLT CESSNA 177 177RG 2073709 CE RT WING AILERON WEDGED AILERON D L K NONE O OTHER IN INSP/MAINT 1 EA 01 50478 177RG1134 AILERON STOP BOLT NAS428-3-10 SECURED TO A NUTPLATE ON A BRACKET ASSSEMBLY PN 1221088-8 SECURED TO MAIN SPAR ASSEMBLY AN D IS USED AS A STOP FOR UP-AILERON TRAVEL, FAILED TO STOP THE UP-TRAVEL OF THE RIGHT AILERON. BOLT DEFLECTED AND BOLT H EAD BECAME WEDGED ON AILERON BELLCRANK PN 122187-2 WHICH, IN TURN, LOCKED THE AILERON CONTROL SYSYEM IN FULL UPRIGHT AIL ERON. NO AMOUNT OF PRESSURE APPLIED TO CONTROL WHEELS WOULD FREE LOCKED AILERON BELLCRANK. PRESS APPLIED TO AILERON WO ULD ALSO NOT FREE LOCKED BELLCRANK. THIS INCIDENT TOOK PLACE ON THE GROUND. INSP OF AFFECTED AREAS REVEALED STOP BOLT HAD SLIGHT BEND, PROBABLY DUE TO HARD AND VIOLENT MOVEMENT OF AILERONS FROM STOP-TO-STOP OVER A PERIOD OF TIME. 1 H 7 1 3O A20CE 1996051600519 19960516 00519 SW 1996 5 16 96ZZZX2467 1 19960328 G 5711 2703 FITTING BBAVIA 7 7AC 2110102 SW LT AFT SPAR CRACKED G P K NONE O OTHER IN INSP/MAINT 1 CE 01 83032 3721 7AC1688 DISMANTLED LEFT WING FOR THE PURPOSE OF RECOVERING. AS A PRECAUTION, THE WING SPAR ATTACHMENT FITTINGS WERE MAGNAFLUXED . THE LEFT REAR SPAR ATTACHMENT FITTING WAS FOUND TO HAVE SEVERAL IMPERFECTIONS IN THE WELD AREAS OF BOTH THE TOP AND B OTTOM GUSSETS. THE FITTING WAS REPLACED WITH A NEW PART. 1 H 7 1 3O A759 1996051600520 19960516 00520 SO 1996 5 16 96ZZZX2468 1 19960403 G 2913 105476 POWER PACK PIPER PA28 PA28R200 7102811 SO HYDRAULIC SYS DEFECTIVE D L K NONE O OTHER IN INSP/MAINT 1 EA 21 75340 5500 500 AH4295 28R7635292 AFTER OPERATING FOR 500 HOURS, THE HYDRAULIC POWER PACK BEGAN TO CAVITATE EITHER BECAUSE OF AIR OR CONTAMINATION. THE S M INSTRUCTIONS CLEARLY STATE 'OPERATE PUMP TO PURGE AIR FROM SYSTEM' WHENEVER REPLACING THE PUMP, A CYLINDER, OR A LINE. UNFORTUNATELY, THESE STEPS WILL NOT PURGE AIR NOR CONTAMINATION FROM THE ACTUATING CYLINDERS. 1 L 7 1 3O 2A13 1996051600521 19960516 00521 SW 1996 5 16 96ZZZX2469 1 19960328 G 5712 5142 RIB BBAVIA 7 7AC 2110102 SW LT NR 3 INBD CRACKED G P K NONE O OTHER IN INSP/MAINT 1 CE 01 83032 3721 7AC1688 DISMANTLED BOTH LT AND RT WINGS FOR THE PURPOSE OF RECOVERING. IN THE PROCESS OF REMOVING OLD COVER, DETERMINED THAT AL L THE SCREWS THAT SECURE THE FABRIC TO THE RIBS FOR THE NR 2 AND NR 3 INBOARD RIBS OF EACH WING, HAD ELONGATED THE HOLES IN THE RIBS AND WAS NOT SERVING THE INTENDED PURPOSE OF SECURING THE FABRIC. THE SCREW HOLES WERE ELONGATED THE ENTIRE WIDTH OF THE RIB CAP FLANGE AND HAD SEVERAL WITH CRACKS EMITTING FROM THEM. THE NR 3 INBOARD RIB ON LEFT WING WAS CRAC KED COMPLETELY THROUGH THE LIGHTENING HOLE WHICH ORIGINATED FROM THE SCREW HOLE. SUBMITTER RECOMMENDS WHEN RECOVERING, THAT SCREW HOLES ARE OF PROPER SIZE. 1 H 7 1 3O A759 1996051600522 19960516 00522 SW 1996 5 16 96ZZZX2470 1 19960328 G 5712 5142 RIB BBAVIA 7 7AC 2110102 SW LT/RT NR 2-3 INB CRACKED G K NONE O OTHER IN INSP/MAINT 1 CE 01 83032 3721 7AC1688 DISMANTLED BOTH LT AND RT WINGS FOR THE PURPOSE OF RECOVERING. IN THE PROCESS OF REMOVING OLD COVER, DETERMINED THAT AL L THE SCREWS THAT SECURE THE FABRIC TO THE RIBS FOR THE NR 2 AND NR 3 INBOARD RIBS OF EACH WING, HAD ELONGATED THE HOLES IN THE RIBS AND WAS NOT SERVING THE INTENDED PURPOSE OF SECURING THE FABRIC. THE SCREW HOLES WERE ELONGATED THE ENTIRE WIDTH OF THE RIB CAP FLANGE AND HAD SEVERAL WITH CRACKS EMITTING FROM THEM. THE NR 3 INBOARD RIB ON LEFT WING WAS CRAC KED COMPLETELY THROUGH THE LIGHTENING HOLE WHICH ORIGINATED FROM THE SCREW HOLE. SUBMITTER RECOMMENDS WHEN RECOVERING, THAT SCREW HOLES ARE OF PROPER SIZE. 1 H 7 1 3O A759 1996051600523 19960516 00523 CE 1996 5 16 96ZZZX2471 1 19960423 G 5312 551104013 BULKHEAD CESSNA 500 500CESSNA 2076602 CE FWD PRESS BULKHD CRACKED B S A R2JR K NONE O OTHER IN INSP/MAINT 1 EA 21 153JP 5466 5000153 WHILE PERFORMING 900 HOUR/36 MONTH PRESSURE BULKHEAD INSPECTIONS, FOUND SMALL CRACK AT RIVET HOLE ON FORWARD PRESSURE BU LKHEAD. CRACK WAS ON AIR BOX. AIRCRAFT HAD ABOUT 7,500 CYCLES. REPAIR DATA OBTAINED FROM DER TO INSTALL PATCH. SUBMI TTER STATED THIS IS THE THIRD AIRCRAFT FOUND WITH THIS FAILURE AT THIS REPAIR STATION RECENTLY. 1 L 7 2 4F A22CE 1996051600524 19960516 00524 CE 1996 5 16 96ZZZX2472 1 19960422 G 5730 58250171 FITTING 582500514 CESSNA 441 441 2076020 CE RT INBD FLAP CHAFED SKIN B CM2R K NONE O OTHER IN INSP/MAINT 1 SW 15 6860C 3800 4410304 INBOARD FORWARD SIDE OF RIGHT INBOARD FLAP IS CHAFING INTO THE SKIN AT THE WING STUB. FITTING PN 5825017-1 OR PN 582501 7-2, WHICH IS RIVETED TO THE FORWARD INBOARD SIDE OF THE RIGHT INBOARD FLAP, IS CHAFING AGAINST THE WING SKIN. 1 L 7 2 3T RT A28CE 1996051600525 19960516 00525 CE 1996 5 16 96ZZZX2473 1 19960315 G 3010 45AS660105 HEATER MAT BEECH MU300 400BEECH CE LT HORIZ STAB AI BURNED OUT B OG5R K NONE O OTHER IN INSP/MAINT 1 GL 21 3038V 251 9543363 RK93 HEATER MAT BURNED OUT/FAILED (LEFT SIDE). AIRCRAFT HAS IMPROVED ANTI-ICE KIT PREVIOUSLY INSTALLED. 2 H 7 2 4F RT A16SW 1996051600526 19960516 00526 SW 1996 5 16 96ZZZX2474 1 19960418 G 5610 36004311S WINDSHIELD PPG GULSTM 690TP 695 7630518 SW COCKPIT CRACKED D K NONE O OTHER NR NOT REPORTED 1 SW 11 CGMMO 40 96003H1265 96034 WINDSHIELD CRACKED UNDER NORMAL AND PROPER OPERATING CONDITIONS WITH ONLY 40 HOURS OPERATING TIME. 1 H 7 2 3T 2A4 1996051600527 19960516 00527 SW 1996 5 16 96ZZZX2475 1 19960418 G 5610 36004312 WINDSHIELD PPG GULSTM 690TP 690B 7630516 SW COCKPIT CRACKED D K NONE O OTHER NR NOT REPORTED 1 SW 11 177EM 3400 90173H1785 11471 WINDSHIELD CRACKED UNDER NORMAL AND PROPER OPERATING CONDITIONS WITH 3,400 HOURS ON WINDSHIELD. 1 H 7 2 3T 2A4 1996051600528 19960516 00528 SW 1996 5 16 96ZZZX2476 1 19960418 G 5610 36004312 WINDSHIELD PPG GULSTM 690TP 690B 7630516 SW COCKPIT CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 11 690WM 550 91037H5355 11399 WINDSHIELD CRACKED UNDER NORMAL AND PROPER OPERATING CONDITONS WITH ONLY 550 HOURS ON WINDSHIELD. 1 H 7 2 3T 2A4 1996051600529 19960516 00529 SW 1996 5 16 96ZZZX2477 1 19960418 G 5610 36004311S WINDSHIELD PPG GULSTM 690TP 695 7630518 SW COCKPIT CRACKED D O OTHER O OTHER DE DESCENT 1 SW 11 980WM 312 95006H1256 95034 WINDSHIELD CRACKED ON DESCENT UNDER ALL NORMAL AND PROPER OPERATING CONDITIONS WITH ONLY 311.8 HOURS ON WINDSHIELD. 1 H 7 2 3T 2A4 1996051600530 19960516 00530 SO 1996 5 16 96ZZZX2478 1 19960411 G 5320 4564802 DOOR SILL PIPER PA42 PA42720 7104212 SO AIRSTAIR CRACKED B V2AR K NONE O OTHER IN INSP/MAINT 1 AL 03 2247R 4540 425501005 DOOR SILL DOUBLER FOUND CRACKED. CONNECTED CABIN BULKHEADS ALSO FOUND CRACKED. 1 L 7 2 4T A23SO 1996051600531 19960516 00531 SO 1996 5 16 96ZZZX2479 1 19960411 G 5312 BULKHEAD PIPER PA42 PA42720 7104212 SO CABIN CRACKED B V2AR K NONE O OTHER IN INSP/MAINT 1 AL 03 2247R 4540 425501005 DOOR SILL DOUBLER FOUND CRACKED. CONNECTED CABIN BULKHEADS ALSO FOUND CRACKED. 1 L 7 2 4T A23SO 1996051600532 19960516 00532 SO 1996 5 16 96ZZZX2480 1 19960410 G 5320 4686700 CHANNEL PIPER PA42 PA42720 7104212 SO NLG WELL CRACKED B V2AR K NONE O OTHER IN INSP/MAINT 1 AL 03 2247R 4540 425501005 CHANNELS AND WHEELWELL SIDE WALL CRACKED AT NOSE GEAR STEERING TORQUE TUBE BEARING BLOCK FLANGES. 1 L 7 2 4T A23SO 1996051600533 19960516 00533 SO 1996 5 16 96ZZZX2481 1 19960410 G 5620 5667602 WINDOW PIPER PA42 PA42720 7104212 SO CABIN CRACKED B V2AR K NONE O OTHER IN INSP/MAINT 1 AL 03 2247R 4540 425501005 FOUR CABIN EXTERIOR SIDE WINDOWS FOUND CRACKED WHILE PERFORMING THE INSPECTION REQUIRED BY PIPER SB 984. 1 L 7 2 4T A23SO 1996051600534 19960516 00534 GL 1996 5 16 96ZZZX2482 2 19960425 G 7250 6899373 WHEEL ALLSN 250C 250C20B 03013 GL THIRD STAGE SHROUD CRACKED B YKER K NONE O OTHER IN INSP/MAINT 1 EA 17 HX58891 CAE820030 TURBINE WAS DISASSEMBLED AS PART OF ENGINE REPAIR FOR COMPRESSOR STALLS. FOUND THE SHROUD ON THE THIRD STAGE WHEEL CRAC KED ALL THE WAY THROUGH. 3 U E4CE 1996051600535 19960516 00535 EA 1996 5 16 96ZZZX2483 2 19960316 G 7250 3024502CL9 GEAR BEECH 1900 1900C 1154161 CE PWA PT6 PT6A65B 52043 EA 2ND STAGE MAKING METAL B MASR K NONE O OTHER IN INSP/MAINT 1 SW 01 160YV 14761 39A030 UC160 3144PS THE POWER SECTION AND GAS GENERATOR WOULD NOT ROTATE AT TIME OF DISASSEMBLY. THE CHIP DETECTOR AND AGB HAD BRONZE METAL PIECES. WHEN THE MODULES WERE SEPARATED THERE WAS A HEAVY SMELL OF HYDRAULIC FLUID COMING FROM THE OIL THAT WAS DRAINE D FROM THE MODULES. WHEN THE RGB HOUSING WAS SPLIT, IT WAS FULL OF BRONZE METAL PARTICLES THAT CAME FROM THE PLANET GEA R SLEEVE BUSHINGS ON THE NR 2 CARRIER ASSY. THE GAS GENERATOR PROBLEMS WERE FOUND TO BE SECONDARY DAMAGE RELATED. OIL SAMPLES SENT IN FOR ANALYSIS. 2 L 7 2 4T 4 T RT A24CE E4EA 1996051600536 19960516 00536 SO 1996 5 16 96ZZZX2484 1 19960418 G 5270 MS250851 SWITCH EMB 120 EMB120RT SO CARGO DOOR MISRIGGED G C D ABORTED TAKEOFF RETURN TO BLOCK N FALSE WARNING TO TAKEOFF 1 GL 03 267UE 3934 120071 AIRCRAFT ABORTED TAKEOFF DUE TO CARGO DOOR WARNING LIGHT MALFUNCTION. THE FORWARD AND AFT MICROSWITCHES ON THE CARGO DO OR WERE ADJUSTED AND OPS CHECKED GOOD. 2 L 7 2 4T RT A31SO 1996051600537 19960516 00537 CE 1996 5 16 96ZZZX2485 1 19960424 G 7810 1019500193 STACK BEECH 200 200BEECH 1152920 CE RT ENG RT EXH CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 09 1553M BB1328 RIGHT EXHAUST STACK CRACKED APPROXIMATELY 80 PERCENT OF CIRCUMFERENCE OF MOUNTING FLANGE. INSTALL NEW UNIT. 1 L 7 2 4T A24CE 1996051600538 19960516 00538 NE 1996 5 16 96ZZZX2486 2 19960424 G 7314 105970 NOZZLE CHNDLREVANS MFP45 BAG BAE146 BAE146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE FUEL PUMP FRACTURED D K NONE O OTHER IN INSP/MAINT 1 SW 15 1106 AFR0837 5853 INSPECTION FOUND METAL CHIPS IN FILTER. PUMP NOZZLE IS FRACTURED AND HAS ENTERED MAIN GEAR ASSEMBLY. PUMP IS BEING SEN T TO C.E.C.O. (MANUFACTURER) FOR TEAR DOWN AND INVESTIGATION. 2 H 7 4 4F 4 F RT A49EU E6NE 1996051600539 19960516 00539 NM 1996 5 16 96ZZZX2487 1 19960103 G 5320 T-CHORD BOEING 727 72722 1384002 NM BS 294-344 CORRODED B LVTR K NONE O OTHER IN INSP/MAINT 1 WP 01 40482 18330 T-CHORD COMMON TO NOSE LANDING GEAR WHEELWELL IN LEFT SIDE OF NOSE COMPARTMENT AT FLOOR LEVEL (WL 170 APPROXIMATELY) WAS FOUND CORRODED IN 6 DIFFERENT AREAS. ALSO, NOSE GEAR WALL ABOVE T-CHORD WAS FOUND TO HAVE SURFACE CORROSION. CORROSIO N RANGED FROM SURFACE TO EXFOLIATION. MAXIMUM MATERIAL LOSS WAS 22 PERCENT. 2 L 7 3 4F A3WE 1996051600540 19960516 00540 NM 1996 5 16 96ZZZX2488 1 19960108 G 5347 SEAT TRACK BOEING 727 72722 1384002 NM BS 540 CORRODED B LVTR K NONE O OTHER IN INSP/MAINT 1 WP 01 40482 18330 DURING ROUTINE INSPECTION OF AIRCRAFT, THE FORWARD CARGO COMPARTMENT'S LEFT TIE-DOWN TRACK WAS FOUND CORRODED OVER A 20 INCH AREA CENTERED AROUND BS 540. EVALUATION OF PART COST VERSUS REPAIR COST LED TO REPLACEMENT OF PART WITH NEW. 2 L 7 3 4F A3WE 1996051600541 19960516 00541 NM 1996 5 16 96ZZZX2489 1 19960108 G 5313 STRINGER BOEING 727 72722 1384002 NM FS 1030-1090 CORRODED B LVTR K NONE O OTHER IN INSP/MAINT 1 WP 01 40482 18330 DURING ROUTINE INSPECTION OF AIRCRAFT, 5 EACH FASTENER HEADS WERE FOUND PULLING THROUGH THE SKIN ALONG FUSELAGE STR 28R AND BS 1030, BS 1060, AND FUSELAGE SKIN WAS FOUND BULGING DUE TO CORROSION. ONCE THE AREA WAS DISASSEMBLED, DAMAGE WAS FOUND TO EXTEND BACK TO BS 1090 REQUIRING A STRINGER REPAIR. REMAINDER OF CORROSION WAS REMOVED, FOUND TO BE WITHIN NEG LIGIBLE DAMAGE LIMITS PER SRM, AND TREATED FOR CORROSION PREVENTION. 2 L 7 3 4F A3WE 1996051600542 19960516 00542 NM 1996 5 16 96ZZZX2490 1 19960108 G 5330 SKIN BOEING 727 72722 1384002 NM BS 480-500 CORRODED B LVTR K NONE O OTHER IN INSP/MAINT 1 WP 01 40482 18330 DURING INSPECTION OF AIRCRAFT, A FASTENER WITH ITS HEAD POPPED OFF AND 2 EACH FASTENERS AFT OF THE FIRST FASTENER WERE A LMOST PULLED THROUGH THE FUSELAGE SKIN AT BS 480 NEAR STR 29L. INTERNAL INSPECTION REVEALED CORROSION OF THE FUSELAGE S KIN AROUND THE FASTENERS. DAMAGED AREA WAS REMOVED AND REPAIR ACCOMPLISHED PER THE SRM. 2 L 7 3 4F A3WE 1996051600543 19960516 00543 NM 1996 5 16 96ZZZX2491 1 19960108 G 5330 SKIN BOEING 727 72722 1384002 NM BS 420-460 CORRODED B LVTR K NONE O OTHER IN INSP/MAINT 1 WP 01 40482 18330 DURING ROUTINE INSPECTION OF AIRCRAFT, 3 EACH FASTENER HEADS FOUND WITH HEADS POPPED OFF ALONG THE SKIN LAP JOINT AT STR 28R BETWEEN BS 420 - BS 460. ALSO, BULGING OF THE SKIN WAS EVIDENT AROUND THE FASTENERS INDICATING CORROSION. AREA WA S REPAIRED PER BOEING SIB 727-53-0072, FIGURE 4. 2 L 7 3 4F A3WE 1996051600544 19960516 00544 NM 1996 5 16 96ZZZX2492 1 19960108 G 5311 FRAME BOEING 727 72722 1384002 NM BS 540-STR 27L CORRODED B LVTR K NONE O OTHER IN INSP/MAINT 1 WP 01 40482 67961 18330 FUSELAGE FRAME AT BS 540 AT STR 27L HAS EXFOLIATION CORROSION ON VERTICAL PORTION OF FRAME. CORROSION HAS LEFT A 1.50 I NCH HOLE IN FRAME. 2 L 7 3 4F A3WE 1996051600545 19960516 00545 1996 5 16 96ZZZX2493 1 19960410 G 8011 7381436 ROTOR TURBINE HAMSTD PS70046 STARTER DEFECTIVE B SI3R K NONE O OTHER IN INSP/MAINT 1 NE 03 59U ROTOR HAS STOCK REMOVAL BELOW .020 INCH MINIMUM VIOLATING OVERHAUL MANUAL 80-10-01 REQUIREMENT FOR STOCK REMOVAL DURING BALANCING. REF: FIGURE 4, ITEM 5, PAGES 1142, 1144, AND FIGURE 306, PAGE 308B OF OVERHAUL MANUAL. STARTER S/N JL39288 . 1996051600546 19960516 00546 1996 5 16 96ZZZX2494 1 19960410 G 8011 7831431 ROTOR TURBINE HAMSTD PS70046 STARTER DEFECTIVE B SI3R K NONE O OTHER IN INSP/MAINT 1 NE 03 1336R ROTOR HAS STOCK REMOVAL BELOW .020 INCH MINIMUM VIOLATING OVERHAUL MANUAL 80-10-01 REQUIREMENT FOR STOCK REMOVAL DURING BALANCING. REF: FIGURE 4, ITEM 5, PAGES 1142, 1144 AND FIGURE 306, PAGE 308B OF OVERHAUL MANUAL. STARTER S/N FC28301. 1996051600547 19960516 00547 1996 5 16 96ZZZX2496 1 19960410 G 8011 7381436 ROTOR TURBINE HAMSTD PS70046 STARTER DEFECTIVE B L SI3R K NONE O OTHER IN INSP/MAINT 1 NE 03 18 ROTOR HAS STOCK REMOVAL BELOW .020 INCH MINIMUM VIOLATING OVERHAUL MANUAL 80-10-01 REQUIREMENT FOR STOCK REMOVAL DURING BALANCING. REF: FIGURE 4, ITEM 5, PAGES 1142, 1144 AND FIGURE 306, PAGE 308B OF OVERHAUL MANUAL. STARTER S/N 830819. 1996051600548 19960516 00548 CE 1996 5 16 96ZZZX2497 1 19960210 G 2840 595602710 BRACKET CESSNA 425 425 2076018 CE FUEL TANK PROBE BROKEN D L A K NONE O OTHER IN INSP/MAINT 1 WP 27 425DC 3268 4250185 FOUND THE RT WING NACELLE FUEL TANK PROBES MOUNTING BRACKETS BROKEN AND LEFT ONE BENT. THIS CONDITION CAUSES ERRONEOUS FUEL QUANTITY INDICATION. FOUND THE WEIGHT OF THE TOP OF THE FUEL TANK BLADDER TANK BEARS AGAINST THIS BRACKET WHEN THE TANK IS PARTIALLY OR COMPLETELY EMPTY. PATCHED THE BROKEN AREA OF THE RIGHT BRACKET AND THE BENT AREA OF THE LEFT BRAC KET. 1 L 7 2 3T RT A7CE 1996051600549 19960516 00549 CE 1996 5 16 96ZZZX2498 1 19960426 G 5343 354003043 FITTING BEECH 58 58 1152740 CE DRAG LEG KEEL RT CORRODED D S K NONE O OTHER IN INSP/MAINT 1 SO 15 4626A 6000 TH39 FITTING CORRODED SEVERELY AND CRACKED ON BOTTOM, HOLE ELONGATED AND CORRODED. BOTTOM OF FITTING CORRODED ON BOTTOM BOLT ATTACH AREA DUE TO WATER AND/OR BATTERY ACID BEING TRAPPED IN AREA. FITTING IS LOCATED DIRECTLY BELOW BATTERY BOX. HI NGE BOLT WAS FOUND LOOSE AT ANNUAL INSPECTION. 1 L 7 2 3O 3A16 1996051600550 19960516 00550 SO 1996 5 16 96ZZZX2499 1 19960228 G 5730 62061002 SKIN PIPER PA28 PA28161 7102803 SO WING WALK CRACKED D S K NONE O OTHER IN INSP/MAINT 1 SW 09 2545U 288016032 DOUBLER UNDER WING WALK SKIN CRACKED IN SEVERAL PLACES. SUBMITTER STATED TWO AIRCRAFT FOUND WITH THIS CONDITION. 1 L 7 1 3O 2A13 1996051600551 19960516 00551 SO 1996 5 16 96ZZZX2500 1 19960416 G 5720 62086005 STIFFENER PIPER PA28 PA28161 7102803 SO INBD RT WING CRACKED B S Y2BR K NONE O OTHER IN INSP/MAINT 1 EA 27 302FG 2677 288016274 RIGHT WING INBOARD LOWER FORWARD SKIN STIFFENER CRACKED ACROSS STIFFENER. SUBMITTER STATED THIS IS THE THIRD CRACKED ST IFFENER FOUND IN APRIL, 1996. 1 L 7 1 3O 2A13 1996051600552 19960516 00552 CE 1996 5 16 96ZZZX2501 1 19960306 G 2410 530406 HUB CESSNA 337 337H 2075732 CE ALTERNATOR DRIVE BROKEN D K NONE O OTHER IN INSP/MAINT 1 SW 99 26FG 1377 33701921 THIS FAILURE OCCURRED DESPITE C/W TCM SB 95-3. THE BUSHING AND RETAINER WERE SHOWING WEAR, HOWEVER, NOT NEAR FAILURE. S USPECT THIS FAILURE IS A BY-PRODUCT OF THE SLOP IN THE BUSHING. THIS AREA SHOULD GET A CLOSE INSPECTION AT C/W SERVICE B ULLETIN. 1 H 7 2 3O A6CE 1996051600553 19960516 00553 SO 1996 5 16 96ZZZX2502 1 19960417 G 2820 639010107 HOSE ASSY PIPER PA28 PA28R180 7102809 SO STRAINER DETERIORATED D K NONE O OTHER IN INSP/MAINT 1 EA 01 4605J 28R30485 DURING ANNUAL INSPECTION, FOUND FUEL LINE FROM FIREWALL STRAINER TO ELECTRIC PUMP VERY STIFF. ORIGINAL TAG DATED 1Q67, STILL ATTACHED. UPON REMOVAL FOR REPLACEMENT, FOUND OUTER JACKET AND INNER STEEL BRAIDING DETERIORATED AND COMING APART . 1 L 7 1 3O 2A13 1996051600554 19960516 00554 CE 1996 5 16 96ZZZX2503 1 19960419 G 2436 C6110050103 REGULATOR ELECTRODELTA VR515GC CESSNA 172 172P 2072436 CE DC SYSTEM DEFECTIVE H K NONE P NO WARNING INDICATION IN INSP/MAINT 1 NM 01 52139 111 5022911 17274421 LOW VOLTAGE WARNING FAILED AND WOULD NOT ILLUMINATE. LOW VOLTAGE WARNING LIGHT ON INSTRUMENT PANEL. DISSASSEMBLED REGU LATOR TO INSPECT, AS IT IS OUT OF WARRANTY. FOUND COLD SOLDER JOINTS IN SEVERAL LOCATIONS. REGULATOR MANUFACTURED MAY, 1995. 1 H 7 1 3O NT 3A12 1996051600555 19960516 00555 WP 1996 5 16 96ZZZX2504 1 19960426 G 2750 37741721 CRANK ASSY DOUG DC8 DC862 3021970 WP FLAP ACTUATING BROKEN B DM4R K NONE O OTHER IN INSP/MAINT 1 SO 19 FLAP CRANK ASSY IS BROKEN ON LUG AREA WHERE BOLT P/N NAS1105-23 GOES THROUGH. SUSPECT CAUSE, METAL FATIGUE AND CORROSIO N. 2 L 7 4 4F 4A25 1996051600556 19960516 00556 SO 1996 5 16 96ZZZX2505 2 19960425 G 8530 653445A11 CYLINDER BEECH 58 58 1152740 CE CONT O520 IO520CB 17032 SO PLUG BOSS CRACKED I K NONE O OTHER IN INSP/MAINT 1 SW 07 3695V 1216 TH1183 282447R THE CONTINENTAL CYLINDER CRACKED WITH ONLY 1,216.4 HOURS ON IT. THE CRACK ORIGINATED AT THE SPARK PLUG BOSS AND WAS TRA VELLING TO THE FUEL INJECTION NOZZLE. THE COMPRESSION WAS STILL IN THE UPPER 60'S. SUBMITTER STATED THEY HAVE BEEN EXP ERIENCING ALOT OF THIS TYPE OF CRACKING AND BELIEVE IT TO BE A PROBLEM WITH THE MANUFACTURING PROCESS AT CONTINENTAL OR THEIR SUB-CONTRACTORS. 1 L 7 2 3O 3 O 3A16 E5CE 1996051600557 19960516 00557 SO 1996 5 16 96ZZZX2506 2 19960410 G 8530 CYLINDER CESSNA 150 150M 2071830 CE CONT O200 O200A 17020 SO NR 1 CYL EXH RKR BOSS CRACKED D K NONE K FLUID LOSS IN INSP/MAINT 1 EA 27 9264U 1438 15078214 254467 DURING POST 100 HOUR OPERATIONAL RUN AND LEAK CHECK, NOTED A NOISE SIMILAR TO A 'BAFFLE RATTLE' BEING MADE. AFTER SHUT DOWN, NO LOOSE BAFFLES WERE FOUND. THE ROCKER BOX COVERS WERE REMOVED TO REPLACE THE GASKETS FOUND LEAKING. WHEN NR 1 COVER REMOVED, A SMALL 'HALF-MOON' SHAPED PIECE OF CASTING WAS FOUND. THE OUTER EXHAUST ROCKER SHAFT BOSS HAD BROKEN OF F THROUGH ITS DIAMETER PARALLEL WITH THE ROCKER ARM. AD 94-05-05 ADDRESSES THIS PROBLEM AT OVERHAUL. 1 H 7 1 3O 3 O 3A19 E252 1996051600558 19960516 00558 SO 1996 5 16 96ZZZX2507 1 19960423 G 5330 5212700 SKIN PIPER PA31 PA31350 7103110 SO BELLY WRONG PART D K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 25 44AC 70 318052147 DURING REPAIR TO BELLY OF AIRCRAFT AFTER A GEAR UP LANDING, BELLY SKIN FOUND TO BE A FACTORY MADE SKIN THAT WAS MEASURED AT 0.032 INCH THICK. ACCORDING TO PIPER SM, PN 761-448, FIGURE 4-21, THIS SKIN SHOULD BE 0.040 INCH THICK. THE ADJOIN ING SKINS WERE CHECKED AND FOUND SIMILAR DISCREPANCIES. THESE SKINS WERE ALL FACTORY MADE, BUT INSTALLED PREVIOUSLY IN THE FIELD. 1 L 7 2 3O A20SO 1996051600559 19960516 00559 CE 1996 5 16 96ZZZX2508 1 19960423 G 3010 LINE CESSNA 208 208 2073702 CE DEICE SUPPLY MISDRILLED B APCR K NONE W P INADEQUATE Q C NO WARNING INDICATION IN INSP/MAINT 1 NM 01 9536F 7400 20800090 PNEUMATIC SURFACE DE-ICE SYSTEM WOULD NOT BUILD ENOUGH PRESSURE TO ACTIVATE ANNUNCIATOR LIGHTS. FOUND .1250 INCH DRAIN HOLES DRILLED INTO ALUMINUM SUPPLY LINES CAUSING PRESSURE LOSS. SEALING HOLES CURED THIS PROBLEM. 1 H 7 1 3T NT A37CE 1996051600560 19960516 00560 1996 5 16 96ZZZX2509 4 19960425 G 3418 1869 LIFT DETECTOR CESSNA 404 404CESSNA 2075901 CE LT WING SHORTED B APCR O OTHER N FALSE WARNING IN INSP/MAINT 1 NM 01 48SA 168 4040417 AFTER FLIGHT THROUGH RAIN, WATER ENTERS LIFT DETECTOR AND CAUSES STALL WARNING HORN TO SOUND CONTINUOUSLY. UNIT IS NOT EASY TO DRY OUT REQUIRING REPLACEMENT. SUBMITTER STATED THIS IS A RECURRING PROBLEM. RECOMMEND IMPROVED INTERNAL SEALI NG OF LIFT DETECTOR. MANUFACTURED BY 'SAFE-FLIGHT'. PROBLEM OCCURS WITH SEVERAL PART NUMBERED UNITS. 1 L 7 2 3O A25CE 1996051600561 19960516 00561 SO 1996 5 16 96ZZZX2510 2 19960423 G 8520 CRANKCASE PIPER PA34 PA34200T 7103406 SO CONT O360 TSIO360EB 17025 SO RT NR 5 CYL CRACKED B APCR K NONE O OTHER IN INSP/MAINT 1 NM 01 8407C 15133 1266 347670137 265901R SMALL CRACK FOUND IN RIGHT SIDE OF CRANKCASE NEXT TO THROUGH-BOLT JUST FORWARD OF CYLINDER NR 5. CONSIDERED NON-CRITICA L AREA PER SB M90-17. 1 L 7 2 3O 3 O A7SO E9CE 1996051600562 19960516 00562 EA 1996 5 16 96ZZZX2511 2 19960423 G 7414 M2637 POINTS SLICK 6393 LYC O540 IO540C4B5 41532 EA LT MAG DEFORMED D K NONE O OTHER IN INSP/MAINT 1 NE 05 392 94020017 RL1924648A AIRCRAFT WAS BEING RUN BEFORE FLIGHT. WHEN SHUTTING RIGHT MAG OFF ON LEFT ENGINE, ENGINE QUIT. CHECKED P-LEADS FOR GRO UNDING AND PROPER INSTALLATION. REMOVED MAG AND CHECKED COIL, POINT GAP AND REPLACED CONDENSER. UPON CHECKING E-GAP FO UND POINTS NOT CLOSING. REPLACED POINTS WHICH CORRECTED DISCREPANCY. SUSPECT CAUSE: INSPECTING POINTS WRONG. WHEN OP ENING POINTS TO INSPECT, BE CAREFUL NOT TO OPEN TOO FAR. 3 O 1E4 1996051600563 19960516 00563 SO 1996 5 16 96ZZZX2512 2 19960426 G 8520 653877 LIFTER CESSNA 185 A185F 2072821 CE CONT O520 IO520D 17032 SO LIFTER FACE GALLED D K NONE O OTHER IN INSP/MAINT 1 NE 05 61368 433 18504159 282672R WHILE DOING TOP OVERHAUL, FOUND 3 HYDRAULIC LIFTERS PITTED AND GALLED. SUBMITTER RECOMMENDS CLOSER INSPECTION OF LIFTER S AT OVERHAUL. 1 H 7 1 3O 3 O 3A24 E5CE 1996051600564 19960516 00564 CE 1996 5 16 96ZZZX2513 1 19960411 G 7921 8406E COOLER STWARNER CESSNA 177 177RG 2073709 CE ENGINE OIL LEAK D K NONE K FLUID LOSS IN INSP/MAINT 1 NE 01 34161 1627 24756 177RG0976 OIL COOLER WAS REMOVED DUE TO LEAKING. THERE WAS NO APPARENT REASON FOR THE LEAK SUCH AS EXTERNAL DAMAGE. 1 H 7 1 3O A20CE 1996051600565 19960516 00565 1996 5 16 96ZZZX2514 4 19960416 G 2216 6270197 CONTROL CABLE PIPER PA34 PA34200T 7103406 SO TRIM SERVO BROKEN E K NONE O OTHER IN INSP/MAINT 1 NM 09 20BC 347570233 ELECTRIC TRIM CABLE BROKE. FOUND THE SERVO CAPSTAN BEGAN TO SLIP. THE SLIPPING CAUSED THE CABLE TO BREAK DOWN AND FAIL . REPLACED THE CABLE AND THE TRIM SERVO. 1 L 7 2 3O A7SO 1996051600566 19960516 00566 EA 1996 5 16 96ZZZX2515 2 19960413 G 7414 MAGNETO BENDIX 2000 MOONEY M20 M20J 5870219 SW LYC O360 IO360A3B6 41514 EA ENGINE MISINSTALLED H A UNSCHED LANDING Y W ENGINE STOPPAGE INADEQUATE Q C CL CLIMB 1 EA 17 4244H 240679 ENGINE FAILURE OCCURRED UPON REACHING 4,500 FEET. EMERGENCY LANDING AT AIRPORT WAS MADE. INVESTIGATION DETERMINED MAGN ETO HAD FALLEN OFF ENGINE. INSPECTION REVEALED MAGNETO HAD BEEN REMOVED 4 MONTHS EARLIER TO C/W AD 78-09-07RE. UPON RE INSTALLATION OF MAGNETO, A FLANGED TYPE GASKET P/N 62224 HAD BEEN USED INSTEAD OF PROPER ROUND GASKET, P/N CW12681. THI S ALLOWED GASKET MATERIAL TO BE COMPRESSED BETWEEN MAGNETO HOLD-DOWN CLAMPS AND ACCESSORY HOUSING RESULTING IN IMPROPER TORQUING AND SUBSEQUENT FAILURE. 1 L 7 1 3O 3 O 2A3 1E10 1996051600567 19960516 00567 CE 1996 5 16 96ZZZX2516 1 19960311 G 2410 1100715 SHAFT DELCO BEECH 35 V35A 1151544 CE ALT DRIVE SHEARED PIN D K NONE O OTHER NR NOT REPORTED 1 EA 03 8388N A94668 D8772 AIRCRAFT ALTERNATOR WAS REPORTED INOPERATIVE. TROUBLESHOT AND FOUND ALTERNATOR GEAR RETAINING NUT HAD UNSCREWED FROM TH E ARMATURE SHAFT. DISCOVERED INTERNAL CONDITION OF ARMATURE SHAFT TO BE WORN AT BEARING POINT. ALTERNATOR SHAFT SEIZED AND ROTATION OF THE GEAR SHEARED THE COTTER PIN AND ALLOWED THE RETAINER NUT TO COME OFF. THIS ALTERNATOR HAD APPROXIM ATELY 130 HOURS SINCE OVERHAUL. 1 L 7 1 3O 3A15 1996051600568 19960516 00568 SO 1996 5 16 96ZZZX2517 1 19960328 G 2720 9621200 TORQUE TUBE 9631900 PIPER PA34 PA34200T 7103406 SO STAB FITTING BROKEN D K NONE O OTHER IN INSP/MAINT 1 EA 17 18TP 347970431 BY C/W AD 80-09-04 REPLACING THE TORQUE TUBE FITTING, WIND COULD AND DID BREAK TORQUE TUBE FARTHER UP THE TORQUE TUBE WH ERE IT CANNOT BE SEEN ON PRE-FLIGHT INSPECTIONS OR OTHER WITHOUT REMOVING RUDDER. 1 L 7 2 3O A7SO 1996051600569 19960516 00569 CE 1996 5 16 96ZZZX2518 1 19960220 G 3222 16981001123 HOUSING BEECH 23 C23 1151242 CE NLG UPPER FAILED D K NONE O OTHER LD LANDING 1 SW 09 66710 4079 M2387 NOSE GEAR LANDING GEAR HOUSING FAILED ON LANDING. STRUCTURE FAILED AT BOLT HOLES ON UPPER END OF UNIT WHERE STEERING CO LLAR IS FASTENED. 1 L 7 1 3O A1CE 1996051600570 19960516 00570 SO 1996 5 16 96ZZZX2519 2 19960424 G 8520 CRANKSHAFT BBAVIA 7 7BCM 2110106 SW CONT C85 C858 17008 SO PROPELLER ATTACH FAILED G K NONE O OTHER NR NOT REPORTED 1 GL 09 46AC 120 7AC3382 PROPELLER SEPARATED FROM ENGINE DUE TO CRANKSHAFT FAILURE. INDICATION OF PREVIOUS CRACK AT AREA OF FRACTURE. 1 H 7 1 3O 3 O A759 E233 1996051600572 19960516 00572 GL 1996 5 16 96ZZZX2521 2 19960404 G 7250 23055438 2ND STG NOZZLE 23035128 ALLSN 250C 250C30 03013 GL GP SEC DIAPHRAGM LOOSE B ALGR K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 X61641 UPON RECEIVING FROM ALLISON (NEW) 3-8-96, NOZZLE HAD A DIAPHRAGM MOVEMENT OF .004 INCH. ACCORDING TO CEB-3188, THE DIAP HRAGM SHOULD HAVE A MAXIMUM MOVEMENT OF .003 INCH. THIS NOZZLE IS UNACCEPTABLE AND WAS SENT BACK TO ALLISON FOR WARRANT Y. TIGHTENED THE KEY ON THE DIAPHRAGM INNER RING. 3 U E1GL 1996051600573 19960516 00573 GL 1996 5 16 96ZZZX2522 2 19960404 G 7250 23055438 2ND STG NOZZLE ALLSN 250C 250C30 03013 GL GP SEC DIAPHRAGM LOOSE B ALGR K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 X61606 UPON RECEIVING FROM ALLISON (NEW) 3-5-96, NOZZLE HAD A DIAPHRAGM MOVEMENT OF .005 INCH. ACCORDING TO CEB-72-3188, THE D IAPHRAGM SHOULD HAVE A RADIAL MOVEMENT OF .003 INCH MAXIMUM. THE NOZZLE WAS SENT BACK TO ADDISON FOR WARRANTY. TIGHTEN ED THE KEYS ON THE DIAPHRAGM INNER RING. 3 U E1GL 1996051600574 19960516 00574 GL 1996 5 16 96ZZZX2523 2 19960404 G 7250 23055438 2ND STG NOZZLE 23035128 ALLSN 250C 250C30 03013 GL GP SEC DIAPHRAGM LOOSE B ALGR K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 X61647 UPON RECEIVING FROM ALLISON (NEW) 3-5-96, NOZZLE HAD A DIAPHRAGM MOVEMENT OF .005 INCH. ACCORDING TO CEB-72-3188, THE D IAPHRAGM SHOULD HAVE A MAXIMUM MOVEMENT OF .003 INCH. THE NOZZLE WAS SENT BACK TO ALLISON FOR WARRANTY. TIGHTENED THE K EYS ON THE DIAPHRAGM INNER RING. 3 U E1GL 1996051600575 19960516 00575 GL 1996 5 16 96ZZZX2524 2 19960404 G 7250 23055438 2ND STG NOZZLE 2305128 ALLSN 250C 250C30 03013 GL GP SEC DIAPHRAGM LOOSE B ALGR K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 X61626 UPON RECEIVING FROM ALLISON (NEW) 3-8-96, NOZZLE HAD A DIAPHRAGM MOVEMENT OF .004 INCH. ACCORDING TO CEB-72-3188, THE D IAPHRAGM SHOULD HAVE A MAXIMUM MOVEMENT OF .003 INCH. THIS IS UNACCEPTABLE. THE NOZZLE WAS SENT BACK TO ALLISON FOR WA RRANTY. TIGHTENED THE KEYS ON THE DIAPHRAGM INNER RING. 3 U E1GL 1996052300093 19960523 00093 SW 1996 5 23 96ZZZX2533 1 19960129 G 6230 206010335001 LEVER ASSY 206010350021 BELL 206 206L1 1182107 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 5750Y 451 45517 BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 SPACERS, 4 EACH 206-010- 337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-101 BEARING. SUSPECT NOR MAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 451.1. 1 G 7 1 3U H2SW 1996052300094 19960523 00094 SW 1996 5 23 96ZZZX2534 1 19960129 G 6230 206010336005 LINK IDLER 206010350021 BELL 206 206L1 1182107 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 5750Y 451 45517 BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 SPACERS, 4 EACH 206-010- 337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-101 BEARING. SUSPECT NOR MAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 451.1. 1 G 7 1 3U H2SW 1996052300095 19960523 00095 SW 1996 5 23 96ZZZX2535 1 19960325 G 6230 206040576103 BEARING 206040014103 BELL 206 206L3 1182108 SW MAST SPALLED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 367AL 808 ZV1434 51443 FOUND METAL ON UPPER TRANSMISSION CHIP PLUG. FOUND MAST BEARING OUTER RACE SPALLING. 1 G 7 1 3U H2SW 1996061800001 19960618 00001 SW 1996 6 18 96ZZZX2536 1 19960312 G 5400 212030154101 FITTING ASSY 205030845367 BELL 212 212 1181420 SW LIFT BEAM BROKEN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 XASQ 30818 MAJOR INSPECTION FOUND FORWARD LEG OF FITTING BROKEN THROUGH BOLT HOLE. AIRCRAFT TOTAL TIME 7775.6 HOURS. REPORTED AS: N NR NXA-SQH (MEXICO). 1 G 7 1 4U H4SW 1996052300218 19960523 00218 EU 1996 5 23 96ZZZX2551 1 19960219 G 2730 10604319 Q UNIT AMD FALC50 FALCON50MYST 2730106 EU ELEVATOR FEEL LEAKING D K NONE K FLUID LOSS IN INSP/MAINT 1 SW 09 599SC 704 242 DURING PRE-FLIGHT, FOUND ELEVATOR AUTHORIZATION 'Q' UNIT 'ARTIFICIAL FEEL' LEAKING AT SWIVEL FITTING. 2 L 7 3 4F A46EU 1996052300220 19960523 00220 CE 1996 5 23 96ZZZX2553 1 19960301 G 2810 FUEL CAP CESSNA 210 210L 2073448 CE FUEL TANK WATER LEAK D K NONE O OTHER IN INSP/MAINT 1 CE 07 2498S 21061306 FUEL CAPS LEAKING WATER INTO FUEL TANKS WHEN EXPOSED TO INCLEMENT WEATHER. CORRECTED BY INSTALLING CESSNA T210L, (WW OV AL PLATES) FROM MONARCH AIR AND DEVELOPMENT, INC. 1 H 7 1 3O 3A21 1996052300222 19960523 00222 SO 1996 5 23 96ZZZX2555 2 19960228 G 8530 VALVE GUIDE CESSNA 182 182P 2075816 CE CONT O470 O470R 17026 SO NR 1 CYLINDER LOOSE D K NONE R PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 SO 16 52727 390 18262801 462760 VALVE GUIDE LOOSENED IN CYLINDER HEAD ALLOWING CYLINDER TO MISFIRE. NOTE: DIFFICULT TO DIAGNOSE. COMPRESSION WAS 55/8 0 UNTIL SPRING ASSY WAS MOVED. SUBMITTER RECOMMENDS CHECKING SPRING ASSYS FOR SIDE PLAY WHEN VALVE COVERS REMOVED FOR A NY REASON. 1 H 7 1 3O 3 O NT TA13 E273 1996052300223 19960523 00223 SO 1996 5 23 96ZZZX2556 1 19960312 G 7922 77944 VALVE PIPER PA31 PA31325 7103105 SO THERMO BYPASS CRIMP NUT GONE D K NONE O OTHER IN INSP/MAINT 1 GL 13 413TC 560 317912040 ON REMOVAL TO C/W SB 518C, FOUND NUT HAD FALLEN OFF OF VALVE, SPRING AND SEAT WERE SEPARATED FROM VALVE WITH NUT LODGED IN OIL PASSAGE FROM VALVE. THE ONLY CONTAMINANTS IN OIL FILTER WAS SOME BRASS FROM THE SEAT WORKING AGAINST NUT. 1 L 7 2 3O A20SO 1996052300224 19960523 00224 CE 1996 5 23 96ZZZX2557 1 19960302 G 2842 C6680500802 TRANSMITTER CESSNA 172 172P 2072436 CE LT FUEL TANK FLOAT DAMAGE D K NONE O OTHER IN INSP/MAINT 1 NM 03 6601K 1034 17274218 DURING 100-HOUR INSPECTION, THE LT FUEL QUANTITY TRANSMITTER WAS REMOVED TO REPLACE LEAKING GASKET AND SCREW SEALS. UPO N REMOVAL OF THE ROCHESTER TRANSMITTER, FOUND THE FLOAT WAS CONTACTING THE TOP AND BOTTOM OF THE FUEL TANK CAUSING THE C OMPOSITE FLOAT TO DISINTEGRATE. BLACK FLOAT RESIDUE WAS IN THE BOTTOM OF THE FUEL TANK AND IN THE MAIN FUEL STRAINER. N EW TRANSMITTER KIT SK 172-117 IS INSTALLED WITH 1034.1 HRS TOTAL TIME. 1 H 7 1 3O NT 3A12 1996052300225 19960523 00225 EA 1996 5 23 96ZZZX2558 2 19960124 G 8520 SL18840 CAMSHAFT BBAVIA 7 7KCAB 21101P3 CE LYC O320 IO320E2A 41508 EA LOBES DAMAGED D K NONE O OTHER IN INSP/MAINT 1 WP 09 8643 84 35473 L495755A ANNUAL INSPECTION - LARGE AMOUNT OF METAL FRAGMENTS IN OIL PRESSURE AND OIL SUCTION SCREENS. CYLINDERS REMOVED, 7 LIFTE R BODIES NOT TURNING, ENGINE TEAR-DOWN REVEALED VERY LITTLE TAPER ON CAM LOBE TIPS EXCEPT NR 4 EXHAUST LUBE. IT HAD .00 1 INCH TAPER AND WAS TURNING. FURTHER INVESTIGATION REVEALED NR 3 CONNECTING ROD AND NR 3 ROD JOURNAL SCORED BADLY REND ERING CRANKSHAFT AND NR 3 ROD UNREPAIRABLE DUE TO LARGE FRAGMENT FROM NR 2 INTAKE LIFTER BODY PASSING THROUGH OIL SUCTIO N SCREEN AND BACK INTO OIL SYSTEM. 1 H 7 1 3O 3 O A759 1E12 1996052300226 19960523 00226 EA 1996 5 23 96ZZZX2559 2 19960124 G 8520 SL72877 LIFTER BBAVIA 7 7KCAB 21101P3 CE LYC O320 IO320E2A 41508 EA FACE DAMAGED D K NONE O OTHER IN INSP/MAINT 1 WP 09 8643 84 35473 L495755A ANNUAL INSPECTION - LARGE AMOUNT OF METAL FRAGMENTS IN OIL PRESSURE AND OIL SUCTION SCREENS. CYLINDERS REMOVED, 7 LIFTE R BODIES NOT TURNING, ENGINE TEAR-DOWN REVEALED VERY LITTLE TAPER ON CAM LOBE TIPS EXCEPT NR 4 EXHAUST LUBE. IT HAD .00 1 INCH TAPER AND WAS TURNING. FURTHER INVESTIGATION REVEALED NR 3 CONNECTING ROD AND NR 3 ROD JOURNAL SCORED BADLY REND ERING CRANKSHAFT AND NR 3 ROD UNREPAIRABLE DUE TO LARGE FRAGMENT FROM NR 2 INTAKE LIFTER BODY PASSING THROUGH OIL SUCTIO N SCREEN AND BACK INTO OIL SYSTEM. 1 H 7 1 3O 3 O A759 1E12 1996052300228 19960523 00228 CE 1996 5 23 96ZZZX2561 1 19960509 G 3213 22411001 FITTING CESSNA 172 172RG 2072438 CE RT MLG CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 01 9437D 4533 172RG1161 FOUND 2 CRACKS IN FITTING THAT HOLDS AXLE STUB TO LANDING GEAR DURING A 100-HOUR INSPECTION. 1 H 7 1 3O 3A17 1996052300319 19960523 00319 CE 1996 5 23 96ZZZX2563 1 19960306 G 2730 0510105125 CONTROL CABLE CESSNA 185 A185F 2072821 CE ELEV FS 140 FRAYED D A K NONE O OTHER IN INSP/MAINT 1 SW 99 25FG 3188 18502425 ELEVATOR CABLE WORN. SUBMITTER STATED PROBLEM IS TYPICAL OF ALL 185'S. CABLE CHAFES ON RIB AND IS JUST A MATTER OF TIM E UNTIL STRANDS IN CABLE BREAK. SUBMITTER SUGGESTS INSTALLING PULLEY AT THIS LOCATION (FS 140.0). 1 H 7 1 3O 3A24 1996052300320 19960523 00320 1996 5 23 96ZZZX2564 4 19960415 G 2562 910 ELT NARCO CESSNA 177 177RG 2073709 CE CASE CORRODED D K NONE O OTHER IN INSP/MAINT 1 WP 01 34674 34 10725 177RG1012 ELT HAS CORROSION ON MOUNT FOR THE CASE COVER ATTACHMENT AND ON THE CASE COVER. APPEARS TO BE DISSIMILAR METAL CORROSIO N FROM COPPER MOUNTING SURFACE AND ALUMINUM MOUNT BRACKET. SUBMITTER STATED TO CORROSION-PROOF MOUNT BRACKET BY PAINTIN G OR ALODINING. 1 H 7 1 3O A20CE 1996052300321 19960523 00321 GL 1996 5 23 96ZZZX2565 3 19960430 G 6114 STUD CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER OVER TORQUE B BXSR K NONE O OTHER IN INSP/MAINT 1 EA 09 123RA 310R0221 755779 THESE MCCAULEY PROPELLERS COME PLACARDED TO LUBE TORQUE TO 40-45 FEET/POUNDS. THE CESSNA MM SPECIFIES 80-85 FEET/POUNDS DRY TORQUE. THE CESSNA TECH SAID BOTH ARE ACCEPTABLE, BUT DO NOT MIX THE TWO. TECH SAID 80 POUNDS LUBE TORQUE WILL PU LL THE STUD OUT OF THE HUB. THIS COULD BE CONFUSING, AND HAS CAUSED EXPENSIVE PROBLEMS. 1 L 7 2 3O 3A10 5 C P22EA 1996061800002 19960618 00002 SO 1996 6 18 96ZZZX2569 1 19960430 G 2720 36270109 CONTROL CABLE PIPER PA28 PA28140 7102802 SO RUDDER AFT STRETCHED H K NONE O OTHER IN INSP/MAINT 1 WP 13 6072W 3282 2820085 INSPECTION FOUND RT RUDDER CABLE STRETCHED NOT ALLOWING FOR PROPER PEDAL ALIGNMENT OF 8 DEGREES. SUSPECT CAUSE, STRETCH ING OF CABLE DURING TOWING AND/OR OVERTURNING STOPS THAT ARE NOT PROPERLY ADJUSTED. THRASHING OF RUDDER IN CROSS WIND. SUBMITTER STATED PREVENTION BY PLACARDED WARNING ON TURN DEGREE AND MORE APPROPRIATE INSPECTION PROCEDURE. 1 L 7 1 3O 2A13 1996052300325 19960523 00325 1996 5 23 96ZZZX2571 4 19960504 G 2312 742240001 IC DRIVER NARCO MK120 BEECH 55 95C55 1152708 CE NAV COMM FAILED B QA9R K NONE B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 SW 13 2787T 992 75248 TE388 TRANSMITTER MODULATOR TRANSISTOR Q3702 FAILED (SHORTED) CAUSING IC DRIVER U3701 TO FAIL. BOTH OF THESE COMPONENTS WERE BURNED CAUSING AN ELECTRICAL FIRE SMOKE ODOR TO BE PRESENT IN THE AIRCRAFT COCKPIT. SUBMITTER SUGGESTS THIS APPEARS TO BE AN ISOLATED INCIDENT AS HAVE NOT SEEN THIS PARTICULAR FAILURE MODE IN THE MK-12D RADIOS BEFORE. SUSPECT A VOLTAGE SP IKE ON THE AIRCRAFT AVIONICS POWER BUSS COULD HAVE CAUSED THIS RADIO FAILURE. 1 L 7 2 3O 3A16 1996052300326 19960523 00326 1996 5 23 96ZZZX2572 4 19960504 G 2312 756320001 TRANSISTOR NARCO BEECH 55 95C55 1152708 CE NAV COMM FAILED B QA9R K NONE B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 SW 13 2787T 992 TE388 TRANSMITTER MODULATOR TRANSISTOR Q3702 FAILED (SHORTED) CAUSING IC DRIVER U3701 TO FAIL. BOTH OF THESE COMPONENTS WERE BURNED CAUSING AN ELECTRICAL FIRE SMOKE ODOR TO BE PRESENT IN THE AIRCRAFT COCKPIT. SUBMITTER SUGGESTS THIS APPEARS TO BE AN ISOLATED INCIDENT AS HAVE NOT SEEN THIS PARTICULAR FAILURE MODE IN THE MK-12D RADIOS BEFORE. SUSPECT A VOLTAGE SP IKE ON THE AIRCRAFT AVIONICS POWER BUSS COULD HAVE CAUSED THIS RADIO FAILURE. 1 L 7 2 3O 3A16 1996052300327 19960523 00327 EU 1996 5 23 96ZZZX2573 1 19960424 G 3246 AH52206 WHEEL ASSY DUNLOP HWKSLY DH125 BH125400A 4230138 EU RT MLG BROKEN D K NONE O OTHER IN INSP/MAINT 1 NE 05 808CC NA779 FOUND RT MLG OUTBOARD WHEEL BROKEN ON BRAKE SIDE OF ASSY. APPROXIMATELY 8 INCHES OF THE RIM HAD BROKEN OFF DURING LANDI NG. THIS CONDITION WAS FOUND DURING A POST-FLIGHT INSPECTION. LANDING WAS UNEVENTFUL AND NO DAMAGE OCCURRED IN THE ARE A OF WING. 2 L 7 2 4J A3EU 1996052300329 19960523 00329 NM 1996 5 23 96ZZZX2575 1 19960329 G 2701 1083041100 CONTROL COLUMN UNIVAR 108 1081 9230404 NM LOWER END DRAIN PLUGGED D A K NONE O OTHER IN INSP/MAINT 1 SW 05 8525K 2456 1081525 FOUND CONDENSATION DRAIN HOLE PLUGGED RESULTING IN WATER ACCUMULATION IN CONTROL COLUMN (ABOUT ONE-FOURTH CUP OF WATER R ELEASED WHEN DRAIN HOLE UNPLUGGED). THIS PROBLEM HAS CAUSED ONE IN-FLIGHT FAILURE RESULTING IN SEVERELY DAMAGED AIRCRAF T. THE ALUMINUM PLUG IN THE BOTTOM OF CONTROL COLUMN MUST BE REMOVED TO TREAT AND INSPECT THIS AREA. 1 H 7 1 3O A767 1996052300330 19960523 00330 1996 5 23 96ZZZX2576 4 19960314 G 6122 B20258 DRIVE DISC MCAULY CESSNA 402 402C 207590R CE PROP GOVERNOR CRACKED D S K NONE O OTHER IN INSP/MAINT 1 NE 03 771309 INSPECTION OF PROPELLER GOVERNOR FOUND DRIVE DISC CRACKED. 1 L 7 2 3O A7CE 1996052300331 19960523 00331 CE 1996 5 23 96ZZZX2577 1 19960328 G 3230 98820022 SECTOR GEAR 24411001 CESSNA 172 172RG 2072438 CE LT MLG MISINSTALLED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 6461V 3000 172RG0716 DURING C/W SEB 90-1 AND SUBSEQUENT REASSEMBLY OF MAIN LANDING GEAR ACTUATOR AND PIVOT ASSY, NOTICED THE SECTOR GEARS AND THE PIVOT ASSY SHAFT WERE NOT MARKED FOR PROPER ALIGNMENT PER CESSNA SERVICE MANUAL SECTION 5, PARAGRAPH 75, AND FIGURE 5-12. THE RT GEAR WAS MARKED AS INDICATED, BUT THE LT GEAR WAS MARKED ON THE BACK SIDE. ALSO, NEITHER PIVOT ASSY WAS MARKED WITH ANY REFERENCE TO THE CORRESPONDING SECTOR GEAR ALIGNMENT. ASSEMBLIES WERE INSTALLED BY TRIAL AND INSPECTION . PROPER OPERATION WAS VERIFIED. 1 H 7 1 3O 3A17 1996052300332 19960523 00332 CE 1996 5 23 96ZZZX2578 1 19960426 G 5711 SPAR BEECH 23 B19 1151215 CE LT/RT WING CORRODED B AW1R K NONE O OTHER IN INSP/MAINT 1 EA 01 59BW MB508 INSPECTION FOUND WING SPARS WITH HEAVY CORROSION AND EXFOLIATION. SUSPECT CAUSE, SALT INTRUSION. 1 L 7 1 3O A1CE 1996052300333 19960523 00333 EA 1996 5 23 96ZZZX2579 2 19960402 G 7414 103493704 IMPULSE COUPLER PIPER PA32 PA32300 7103212 SO LYC O540 IO540K1B5 41532 EA MAGNETO WORN D K NONE O OTHER IN INSP/MAINT 1 NE 01 3044K 327940025 960402 MAGNETO SQAWKED AS DEAD. REMOVED AND DISASSEMBLED MAGNETO, FOUND COIL TAB BENT UPWARD TO MAKE UP FOR THE ERODED CONDITI ON OF TAB. TAB HAD COME IN CONTACT WITH METAL AREA OF ROTOR. WORN THROUGH, GROUNDING MAG. IMPULSE COUPLING WORN SO BA DLY AS TO NARROWLY MISS CONTACT WITH STOP POSTS DURING ENGINE RUN MODE. IMPULSE COUPLING SPRING BROKEN. THIS MAGNETO H AS 250 HRS SINCE ENGINE OVERHAUL. WHILE SERVICING TIRES TO MOVE AIRCRAFT OUT OF HANGAR, NOTED MISSING SCREWS ON LEFT FU EL TANK. 1 L 7 1 3O 3 O A3SO 1E4 1996052300334 19960523 00334 SO 1996 5 23 96ZZZX2580 2 19960426 G 8530 CYLINDER CESSNA 421 421C 2076016 CE CONT O520 GTSIO520L 17032 SO ROCKER SHAFT BOLTS FAILED B FCPR E ENGINE SHUTDOWN O OTHER NR NOT REPORTED 1 NM 09 421CW 421C0137 292087R ENGINE WAS SHUT DOWN IN-FLIGHT BY PILOT. FOUND ROCKER SHAFT BOLTS BROKEN, AND BENT PUSH ROD. VALVES, GUIDES AND PISTON WERE INSPECTED. ALL PARTS FOUND IN GOOD CONDITION. REINSTALLED CYLINDER AND GROUND RUN. ALL FOUND GOOD. 1 L 7 2 3O 3 O A7CE E7CE 1996052300709 19960523 00709 SW 1996 5 23 96ZZZX2581 1 19960412 G 5321 212030101003 PANEL BELL 212 212 1181420 SW FUSELAGE DAMAGED H A K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 99 PANEL WAS RECEIVED WITH NO MANUFACTURER'S PART NUMBER OR SERIAL NUMBER TAGS, NOR ANY TRACEABILITY TO A REGISTERED TYPE C ERTIFICATED AIRCRAFT. PART APPEARS TO HAVE BEEN REPAIRED OR OVERHAULED, THEN DAMAGED. PANEL IS COVERED WITH DENTS. PA NEL WAS RECEIVED AS AN EXCHANGE CORE FOR HOUSTON HELICOPTERS FROM DODS, INC. 1 G 7 1 4U H4SW 1996052300710 19960523 00710 SW 1996 5 23 96ZZZX2582 1 19960418 G 6300 M832481235 PACKING BELL 206 206L3 1182108 SW M/R DRIVE BOOT WRONG PART D A K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 07 112TV 36 A810 51123 PACKING LABELED AS M83248-1-235 WERE RECEIVED AND INSTALLED. BOOT PACKING WAS CUT ON INSTALLATION. THIS IS CORRECT DIA METER, BUT SOFTER MATERIAL. ALSO, INCORRECT PACKING IS BLUE IN COLOR. SUBMITTER STATED THIS TO BE LIMITED TO HIS P. O. ONLY AND HAS ASKED VENDOR TO VERIFY. 1 G 7 1 3U H2SW 1996052300711 19960523 00711 NE 1996 5 23 96ZZZX2583 1 19960423 G 6420 S6110334061 SPINDLE SKRSKY S61 S61A 814210C NE T/R HEAD CRACKED D S K NONE O OTHER IN INSP/MAINT 1 NM 09 1043T 7313 283 61083 SPINDLE WAS FOUND CRACKED IN AREA OF FIRST THREAD. SPINDLE HAS BEEN SENT TO SIKORSKY AIRCRAFT. 2 G 7 2 4U H2EA 1996052300712 19960523 00712 SW 1996 5 23 96ZZZX2584 1 19960401 G 5302 206031329103 FITTING BELL 206 206L1 1182107 SW TB STA 230 BL 28 BROKEN D A K NONE O OTHER IN INSP/MAINT 1 SW 99 23PJ 4799 45269 DURING 100-HOUR INSPECTION, TAILBOOM ACCESS PANEL REMOVED FOR FITTING INSPECTION. AT THIS TIME, THE UPPER LEFT FUSELAGE SIDE TAILBOOM ATTACH FITTING WAS DISCOVERED BROKEN. PILOT REPORTED ON LAST FLIGHT PRIOR TO INSPECTION, MODERATE TO HEA VY TURBULENCE. 1 G 7 1 3U H2SW 1996052300713 19960523 00713 EU 1996 5 23 96ZZZX2585 1 19960411 G 6720 704A34130058 CONTROL CABLE SNIAS 350 AS350B1 8680811 EU T/R BINDING D A A UNSCHED LANDING F FLT CONT AFFECTED NR NOT REPORTED 1 WP 01 216LA 6584 2251 PILOT EXPERIENCED BINDING IN T/R PEDALS AND MADE A PRECAUTIONARY RUNNING LANDING. INSPECTION FOUND BINDING IN TELEFLEX CONTROL CABLE. CABLE WAS REPLACED. 1 G 7 1 3U H9EU 1996052300714 19960523 00714 GL 1996 5 23 96ZZZX2586 2 19960426 G 7313 6898735 TURBINE BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL NR 1 NOZZLE FAILED H A A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 SW 09 3187D 6260 3284 1326 CAE833935 DURING CRUISE FLIGHT, TORQUE YAW WAS EXPERIENCED ALONG WITH TOT RISES TO 890 DEGREES CELSIUS. TORQUE WAS REDUCED TO 60 PERCENT AND TOT STABILIZED TO 800 DEGREES CELSIUS. PILOT RETURNED TO OIL PLATFORM WHERE HE SAFELY LANDED. INSPECTION O F ENGINE REVEALED NR 1 NOZZLE (ON CONDITION PART) HAD FAILED. 1 G 7 1 3U 3 U H2SW E4CE 1996052300715 19960523 00715 SW 1996 5 23 96ZZZX2587 1 19960327 G 5510 NAS464P1027 BOLT 2040113267 BELL 204 UH1H 1181407 SW STAB BAR DEFECTIVE D A K NONE O OTHER IN INSP/MAINT 1 NM 05 398M 6509984 DURING C/W ARMY BULLETIN 95-ASAM-05 ON STABILIZER BAR PIVOT BOLTS, THE NUTS WERE FOUND BOTTOMED OUT ON THE BOLT SHANK. N EW PARTS IAW ARMY PART MANUAL DID NOT PROPERLY SOLVE THE PROBLEM, HOWEVER, INSTALLATION OF BELL'S COMMERCIAL 205 BOLTS 2 0-057-10S27D AND SPECIAL WASHERS 140-007-41S38C4 WOULD, PROVIDING APPROPRIATE APPROVAL WAS OBTAINED. 1 G 7 1 4U EXPA1G71 1996052300716 19960523 00716 WP 1996 5 23 96ZZZX2588 1 19960323 G 6210 369D26012 ADAPTER SLEEVE HUGHES 369 369E 4470707 WP LT SKID CORRODED D A K NONE O OTHER IN INSP/MAINT 1 SO 16 5247S 3849 0119E DURING INSPECTION, FOUND LEFT SKID SLEEVE LOOSE. UPON REMOVAL, NOTED IT WAS SEVERELY CORRODED TO THE POINT OF PENETRATI ON AND FAILURE OF SLEEVE. SUBMITTER STATED THIS IS THE SECOND SLEEVE THAT HAS BEEN FOUND IN THIS CONDITION, ON 2 HELICO PTERS. 1 G 7 1 3U H3WE 1996052300717 19960523 00717 WP 1996 5 23 96ZZZX2589 1 19960401 G 6210 36921400513 BLADE HUGHES 369 369E 4470707 WP M/R NR 5 DAMAGED D A K NONE O OTHER IN INSP/MAINT 1 SO 16 5247S 0119E DURING A PRE-FLIGHT INSPECTION, A MECHANIC FOUND M/R BLADE LEADING EDGE TORN AND RIPPED ABOUT 2I INCHES FROM THE LEADING EDGE ABRASION STRIP. THE METAL WAS IN THE PROCESS OF PEELING AWAY FROM THE BLADE. IT WAS DETERMINED THAT FOD CAUSED T HE INITIAL DENT. THE FOLLOW BLADE (NR 1) WAS ALSO DENTED. 1 G 7 1 3U H3WE 1996052300718 19960523 00718 SW 1996 5 23 96ZZZX2590 1 19960416 G 6320 206040037001 BEARING BELL 206 206L3 1182108 SW XMSN SUN GEAR SCORED B A LX5R K NONE O OTHER IN INSP/MAINT 1 GL 19 721LL 4669 2887 5269 51164 FOUND LOWER MAST ALIGNMENT BEARING BAD WHEN PERFORMING THE SUN GEAR INSPECTION. TRANSMISSION, S/N BMC 00687. 1 G 7 1 3U H2SW 1996052300719 19960523 00719 SW 1996 5 23 96ZZZX2591 1 19960503 G 6230 206010454109 SLEEVE ASSY BELL 206 206B 1181511 SW SWASHPLATE CRACKED D A K NONE O OTHER IN INSP/MAINT 1 SW 09 82FC 4231 EA45 2216 DURING A WEEKLY INSPECTION, MECHANIC FOUND THE SWASHPLATE SLEEVE UNIBALL CRACKED AT THE COLLECTIVE LEVER BEARING. REMOV ED SWASHPLATE ASSY, PN 206-010-450-113, SN EAJG-111249, TT 4,230.7 HRS TSO. TSN AIRCRAFT TT, 8,304.5 HRS. INSTALLED SE RVICEABLE SWASHPLATE ASSY, PN 206-010-450-113, SN GDJD-90286, TT, 7,701.1 HRS, TSO 2,919.1 HRS AT AIRCRAFT TT, 8,304.5 H RS. ALL WORK DONE IAW 206B MM. 1 G 7 1 3U H2SW 1996052300720 19960523 00720 SW 1996 5 23 96ZZZX2592 1 19960503 G 2550 206072903001 RELEASE CABLE BELL 206 206B 1181511 SW CARGO HOOK KINKED B A GJQR O OTHER O OTHER EX EXTERNAL LOAD 1 NM 01 86W 2633 4142 ENCOUNTERED AN UNEXPECTED CARGO HOOK RELEASE, DROPPING THE LOAD. INVESTIGATION REVEALED CABLE KINKED ABOUT 3 INCHES FRO M HOOK FRAME DISCONNECT RESTRICTING THE HOOK LOAD BEAM FROM LOCKING IN CLOSED POSITION. AS KINKED AREA ENTERS HOUSING, IT RESTRICTS HOOK FROM LATCHING. SUBMITTER RECOMMENDS OPERATORS AND MECHANICS BE AWARE OF NEED FOR SMOOTH OPERATION OF CABLE WITHIN HOUSING WITH NO RESTRICTIVE KINKS IN CABLE. 1 G 7 1 3U H2SW 1996052300721 19960523 00721 NE 1996 5 23 96ZZZX2593 2 19960304 G 7250 0292507640 COVER SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1B 6OO30 NE MODULE 3 CRACKED D A K NONE O OTHER IN INSP/MAINT 1 SO 14 869AC 518 1695 652 ENGINE NOISE DURING START-UP AND SHUT-DOWN. REMOVED AND DISASSEMBLED MO5, 4, AND 3. FOUND COVER AND DEFLECTOR BROKEN A ND RUBBING ON MO4 TURBINE DISC. THIS IS 2ND TIME THIS ENGINE SERIAL NUMBER HAS HAD A COVER AND DEFLECTOR BROKEN. SUBMI TTER SUGGESTS A DIFFERENT STYLE COVER AND DEFLECTOR ABLE TO WITHSTAND ENGINE HEAT AND NORMAL VIBRATION LEVELS. 1 G 7 1 3U 3 U H9EU E19EU 1996052300722 19960523 00722 NE 1996 5 23 96ZZZX2594 2 19960304 G 7250 0292502390 DEFLECTOR SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1B 6OO30 NE MODULE 3 BROKEN D K NONE O OTHER IN INSP/MAINT 1 SO 14 869AC 518 1695 652 ENGINE NOISE DURING START-UP AND SHUT DOWN. REMOVED AND DISASSEMBLED MO5, 4, AND 3. FOUND COVER AND DEFLECTOR BROKEN A ND RUBBING ON MO4 TURBINE DISC. THIS IS 2ND TIME THIS ENGINE SERIAL NUMBER HAS HAD A COVER AND DEFLECTOR BROKEN. SUBMI TTER SUGGESTS A DIFFERENT STYLE COVER AND DEFLECTOR ABLE TO WITHSTAND ENGINE HEAT AND NORMAL VIBRATION LEVELS. 1 G 7 1 3U 3 U H9EU E19EU 1996052300723 19960523 00723 GL 1996 5 23 96ZZZX2595 2 19960424 G 7230 A23034784 GEARSHAFT RACE 6890550 BOLKMS 105 BO105C 5626005 EU ALLSN 250C 250C20B 03013 GL SPUR ADAPTER SPALLED H K NONE O OTHER IN INSP/MAINT 1 CE 03 205LF 489 010 S146 THE RACE OF THIS SPUR ADAPTER GEARSHAFT SUPPORTS THE TWO AND ONE-HALF BEARING. THE TWO AND ONE-HALF BEARING CAGE FAILED SPALLING THE RACE. THIS GEARSHAFT DRIVES THE TURBINE AND COMPRESSOR. THIS IS AN FAA PMA PART MFG BY SUPERIOR PARTS. 1 G 7 2 3U 3 U H3EU E4CE 1996052300724 19960523 00724 WP 1996 5 23 96ZZZX2596 1 19960412 G 6320 369D25100501 TRANSMISSION HUGHES 369 369D 4470706 WP M/R LEAKING B EOOR K NONE K FLUID LOSS IN INSP/MAINT 1 AL 03 5074R 6030 2030 40296 1151D REMOVED MAIN ROTOR TRANSMISSION FOR LEAKY INPUT SEAL. THIS IS THE SECOND TIME IN 102.8 HOURS THIS HAS BEEN DONE. SUBMI TTER STATED THIS IS NOT AN ISOLATED INCIDENT EITHER. 1 G 7 1 3U H3WE 1996052300725 19960523 00725 GL 1996 5 23 96ZZZX2597 2 19960307 G 7323 23007506 GOVERNOR BENDIX BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL INPUT LEVER CRACKED D K NONE O OTHER IN INSP/MAINT 1 WP 01 211WP 509 6740 3225 CAE833581 DURING A DAILY INSPECTION, MECHANIC FOUND GOVERNOR WITH .75 INCH CRACK AT AREA OF INPUT LEVER BUSHING. GOVERNOR WAS REM OVED AND REPLACED. THESE GOVERNORS HAVE A 2,000-HOUR OVERHAUL. ENGINE HAD BEEN OPERATING NORMALLY. 1 G 7 1 3U 3 U H2SW E4CE 1996052300726 19960523 00726 GL 1996 5 23 96ZZZX2598 2 19960410 G 7261 206075659001 TUBE ASSY BELL 206 206L3 1182108 SW ALLSN 250C 250C30P 03013 GL ENGINE OIL CHAFED B PN5R A UNSCHED LANDING K FLUID LOSS NR NOT REPORTED 1 NM 03 617DE 6133 51138 895179 FREEWHEEL RETURN HOSE CHAFED THROUGH ENGINE OIL PRESSURE TUBE CAUSING OIL TO LEAK ONTO DECK. PRECAUTIONARY LANDING MADE , LINE REPLACED AND RETURNED AIRCRAFT TO SERVICE. 1 G 7 1 3U 3 U H2SW E1GL 1996052300727 19960523 00727 SW 1996 5 23 96ZZZX2599 1 19960227 G 2821 222366621101 FILTER BELL 206 206B 1181511 SW FUEL SYSTEM DEFECTIVE D A UNSCHED LANDING J WARNING INDICATION NR NOT REPORTED 1 SO 09 67939 5228 PRECAUTIONARY LANDING DUE TO FUEL FILTER CAUTION/WARNING LIGHT ILLUMINATED. 1 G 7 1 3U H2SW 1996052300728 19960523 00728 SW 1996 5 23 96ZZZX2600 1 19960213 G 2121 JBS2761 FAN ASSY BELL 206 206B 1181511 SW INST PANEL FAILED D A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 SO 09 67606 5177 PRECAUTIONARY LANDING DUE TO SMOKE COMING FROM BEHIND INSTRUMENT PANEL. FOUND FAN ASSY FAILED. 1 G 7 1 3U H2SW 1996052300729 19960523 00729 SW 1996 5 23 96ZZZX2601 1 19960224 G 6322 476205302 GEAR 47620160027 BELL 47 47J2A 1181106 SW FAN DRIVE MAKING METAL D O OTHER J WARNING INDICATION NR NOT REPORTED 1 WP 13 8552F 3102 404 B12298 3705 THE ENGINE CHIP LIGHT CAME ON IN-FLIGHT TWICE. EACH TIME THE OIL SCREEN HAD ALUMINUM AND SOME STEEL. AN INVESIGATION F OUND THE PULLEY ON THE FAN DRIVE QUILL MOVING IN AND OUT .25 INCH. UPON REMOVAL OF QUILL FROM THE TRANSMISSION, 2 BROKE N TEETH FROM THE GEAR AND SHAVED ALUMINUM FROM THE TRANSMISSION WERE NOTED. SUSPECT CAUSE IS AN IMPROPERLY TORQUED NUT 47-620565-1 WHICH ALLOWED GEARSHAFT TO MOVE. RECOMMEND INSTALLER INSURE PROPER TORQUE AND SAFETY. 1 G 7 1 3O 2H1 1996052300730 19960523 00730 EU 1996 5 23 96ZZZX2602 1 19960405 G 2150 JBS30011 MOUNT BOLKMS BK117 BK117C1 5626025 EU AC EVAP COIL FLANGE CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 03 911TG 381 7506 FORWARD AND REAR MOUNT BRACKETS CRACKED DUE TO VIBRATION AND SB 133-1 HAD NOT BEEN ISSUED YET AND HAD NOT BEEN C/W AT TH E TIME. INSTALLED NEW COIL ASSY, PN JBS3001-3, AND C/W SIB 133-1. 1 G 7 2 3U NC H13EU 1996052300731 19960523 00731 NE 1996 5 23 96ZZZX2603 1 19960401 G 6410 7610105101041 TAIL ROTOR ASSY SKRSKY S76 S76 8143010 NE TIP WEIGHT SEPARATION B RW1R K NONE O OTHER IN INSP/MAINT 1 SW 05 CG1MR 5408 A13700212 SEPARATION BETWEEN TIP WEIGHT SUPPORT BLOCK AND BLADE SKIN. RECOMMEND ALL IN SERVICE BLADES BE INSPECTED FOR DEBONDING OF TIP WEIGHT CHAMBER. 1 G 7 2 3U H1NE 1996052300732 19960523 00732 NE 1996 5 23 96ZZZX2604 1 19960401 G 6410 7610105101041 TAIL ROTOR ASSY SKRSKY S76 S76 8143010 NE TIP WEIGHT SEPARATION B RW1R K NONE O OTHER IN INSP/MAINT 1 SW 05 PTHOR 7938 A13700151 SEPARATION BETWEEN TIP WEIGHT SUPPORT BLOCK AND BLADE SKIN. RECOMMEND ALL IN SERVICE BLADES BE INSPECTED FOR DEBONDING OF TIP WEIGHT CHAMBER. 1 G 7 2 3U H1NE 1996052300733 19960523 00733 SW 1996 5 23 96ZZZX2605 1 19960425 G 3340 A469B BULB A470 BELL 206 206L1 1182107 SW STROBE FAILED D K NONE O OTHER IN INSP/MAINT 1 SW 03 2611 45417 ON DAILY AIRWORTHY INSPECTION, FOUND STROBE LIGHT BULB BURNED OUT. HAD REPLACED BULB LAST WEEK. CAUSE OF PROBLEM UNKNO WN AT THIS TIME. 1 G 7 1 3U H2SW 1996052300734 19960523 00734 GL 1996 5 23 96ZZZX2606 2 19960315 G 7261 23057790 SEAL BELL 206 206B 1181511 SW ALLSN 250C 250C20J 03013 GL OIL JET LEAK D O OTHER B SMOKE/FUMES/ODORS/SPARKS LD LANDING 1 SO 09 381 CAC42587 UPON LANDING FOR STUDENT CHANGE, SMOKE WAS SEEN COMING FROM ENGINE COMPARTMENT. REPLACED NR 6 AND NR 7 ENGINE OIL JET S EAL. 1 G 7 1 3U 3 U H2SW E4CE 1996052300735 19960523 00735 GL 1996 5 23 96ZZZX2607 2 19960424 G 7230 A23034787 BEARING 6894171 BOLKMS 105 BO105C 5626005 EU ALLSN 250C 250C20 03013 GL ENGINE GRBX FAILED D K NONE J WARNING INDICATION IN INSP/MAINT 1 CE 03 205LF 489 034 S146 831080 PART IS AN FAA PMA BEARING. BEARING CAGE CAME APART CAUSING 'CHIP' LIGHT. BEARING FAILURE ALSO CAUSED SPALLING OF THE INNER RACE ON SPUR ADAPTER GEARSHAFT. THIS GEARSHAFT COUPLES (DRIVES) TURBINE AND COMPRESSOR. 1 G 7 2 3U 3 U H3EU E4CE 1996052300736 19960523 00736 WP 1996 5 23 96ZZZX2608 1 19960411 G 3213 369H600151 STRUT HUGHES 369 369D 4470706 WP BRACE ATTACH FAILED D S A O OTHER O OTHER LD LANDING 1 WP 13 8625F 470111D AFTER LANDING, PILOT LOWERED COLLECTIVE, AIRCRAFT SETTLED AND SHORTLY AFTER, AFT LEFT LANDING GEAR STRUT FAILED SLOWLY S ETTLING UNTIL STRINGER CONTACTED THE GROUND. UPON FURTHER INVESTIGATION A CRACK WAS FOUND EMANATING FROM THE BRACE TO S TRUT ATTACHING BOLT HOLE. 1 G 7 1 3U H3WE 1996052300741 19960523 00741 CE 1996 5 23 96ZZZX2613 1 19960508 G 7603 C800791 BALL JOINT BEECH 2000 2000 1152000 CE LT ENG THROTTLE DETACHED D A E ENGINE SHUTDOWN O OTHER NR NOT REPORTED 1 WP 19 8244L 1364 NC29 THROTTLE BALL SWIVEL HAD BACKED OFF FROM THREADED ROD END ON CABLE END. SWEDGE STAKES HAD COME LOOSE ALLOWING ROD TO BA CK OFF AND DISENGAGE THROTTLE. PILOT SHUT ENGINE OFF. ALL NORMAL, LANDING, ETC. SUBMITTER SUGGESTS EITHER DRILLING HO LE CLOSE TO SWIVEL END FOR SAFETY WIRE OR POSSIBLY PINNING LOWER ASSY WITH COTTER PIN. 1 L 7 2 4T RT A38ACE 1996052300743 19960523 00743 NE 1996 5 23 96ZZZX2615 2 19960402 G 7321 32448512 FUEL CONTROL CESSNA 500 560CESSNA 2076750 CE PWA JT15 JT15D5 52112 NE NR 1 ENGINE DEFECTIVE H L O OTHER J WARNING INDICATION CR CRUISE 1 GL 03 502T 3281 B29352 5600153 108317 FOLLOWING POWER REDUCTION FOR DESCENT, WHEN THROTTLE ADVANCED, NO ENGINE RESPONSE. SELECTED ANTI-ICE OFF AND ENGINE RES PONSE INCREASED TO NORMAL OPERATION. SERVICE CENTER REPLACED BOTH ENGINE FUEL CONTROLS. TEST FLIGHT, ENGINE OPERATED, NORMAL AT ALL ALTITUDES. 2 L 7 2 4F 4 F RT A22CE E25EA 1996052300744 19960523 00744 NE 1996 5 23 96ZZZX2616 2 19960402 G 7321 32448512 FUEL CONTROL CESSNA 500 560CESSNA 2076750 CE PWA JT15 JT15D5 52112 NE NR 2 ENGINE DEFECTIVE H L O OTHER J WARNING INDICATION CR CRUISE 1 GL 03 502T 3281 B29358 5600153 108316 FOLLOWING POWER REDUCTION FOR DESCENT, WHEN THROTTLE ADVANCED, NO ENGINE RESPONSE. SELECTED ANTI-ICE OFF AND ENGINE RES PONSE INCREASED TO NORMAL OPERATION. SERVICE CENTER REPLACED BOTH ENGINE FUEL CONTROLS. TEST FLIGHT, ENGINE OPERATED, NORMAL AT ALL ALTITUDES. 2 L 7 2 4F 4 F RT A22CE E25EA 1996052300745 19960523 00745 SO 1996 5 23 96ZZZX2617 1 19960515 G 2731 430838182 TORQUE TUBE GULSTM G1159 GIV 3980115 SO ELEVATOR TRIM DEFECTIVE B A JU2R O OTHER W F INADEQUATE Q C FLT CONT AFFECTED CR CRUISE 1 GL 23 300K 215 1266 ELEVATOR TRIM RAN TO FULL NOSE UP INDICATION AT FL 43,000 FEET, WITH NO MANUAL CONTROL OF THE ELEVATOR TRIM. UPON INVES TIGATION, FOUND TWO RIVETS WERE NOT INSTALLED DURING PRODUCTION IN THE ELEVATOR TRIM TORQUE TUBE ASSY LOWER UNIVERSAL TO DRIVE ADAPTER. THIS ALLOWED THE SHAFT TO TURN INSIDE THE SHAFT, BUT NOT THE ELEVATOR CABLE DRUM. 2 L 7 2 4F RT A12EA 1996052300746 19960523 00746 WP 1996 5 23 96ZZZX2618 1 19960426 G 5313 2597242318000 LONGERON DOUG DC8 DC862 3021970 WP FS 208-270 26 RT CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND CORROSION LEVEL 2 AT LONGERON 26 RT BETWEEN FS 208.00 TO FS 270.00. REMOVED AND REPLACED LONGERON . 2 L 7 4 4F 4A25 1996052300747 19960523 00747 WP 1996 5 23 96ZZZX2619 1 19960426 G 5313 2597242318000 LONGERON DOUG DC8 DC862 3021970 WP FS 208-270 25 RT CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND CORROSION LEVEL 2 AT LONGERON 25 RT BETWEEN FS 208.00 AND FS 270.00. REMOVED AND REPLACED LONGERO N IAW SRM 53-2-0, SRM 51-1-21, AND SRM 51-1-20D. 2 L 7 4 4F 4A25 1996052300748 19960523 00748 WP 1996 5 23 96ZZZX2620 1 19960426 G 5330 SKIN DOUG DC8 DC862 3021970 WP CARGO COMP DOOR CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND LEVEL 2 CORROSION AT AFT CARGO COMPARTMENT DOOR. REPAIRED IAW SRM 51-1-8, SRM 53-2-0, AND SRM 52- 2-0. 2 L 7 4 4F 4A25 1996052300749 19960523 00749 WP 1996 5 23 96ZZZX2621 1 19960426 G 5320 FINGER DOUBLER DOUG DC8 DC862 3021970 WP COCKPIT FS 188 CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND CORROSION ON COCKPIT SUB-FLOOR BEAM FS 188.00 TO FS 208.00. REPAIRED IAW DER DRAWING 950087-0083, JOSSIAR, CO. 2 L 7 4 4F 4A25 1996052300750 19960523 00750 WP 1996 5 23 96ZZZX2622 1 19960426 G 5330 SKIN DOUG DC8 DC862 3021970 WP FS 208 L29 CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND FUSELAGE SKIN WITH CORROSION FUSELAGE STA 208.00 BETWEEN L29 AND L31. REMOVED CORROSION, REPAIRED IAW E.O. NR 961ALE.005D-7. 2 L 7 4 4F 4A25 1996052300751 19960523 00751 WP 1996 5 23 96ZZZX2623 1 19960426 G 5730 PANEL DOUG DC8 DC862 3021970 WP LT WING TRAP CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 ITEM NR 1080. LEFT WING TOP TRAPEZOID PANEL CORRODED. FABRICATED AND INSTALLED NEW PANEL PER DER DRAWING A/R/W/ 950051 -0203 AND SRM 51-1-20. 2 L 7 4 4F 4A25 1996052300752 19960523 00752 WP 1996 5 23 96ZZZX2624 1 19960426 G 5320 CIRCUMFERENTIAL DOUG DC8 DC862 3021970 WP FUSELAGE CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND CIRCUMFERENTIAL LEVEL 2 CORROSION. CUT OUT DAMAGED AREA FABRICATED FROM 7075T6. INSTALLED NEW SE CTION IAW 53-2-5 AND 51-1-21, 51-3-0. 2 L 7 4 4F 4A25 1996052300753 19960523 00753 WP 1996 5 23 96ZZZX2625 1 19960426 G 5311 56119433N FRAME DOUG DC8 DC862 3021970 WP FS 270 RT L36 CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND FUSELAGE RT SIDE STRUCTURAL FRAME STA 270 HAS CORROSION FROM L21R TO L36R. INSTALLED NEW SECTION OF FRAME AT FS 270 FROM L21R TO L36R IAW SRM 53-2-5, FIGURE 8C-2, AND SRM 51-1-21, SRM 51-1-20D. 2 L 7 4 4F 4A25 1996052300754 19960523 00754 WP 1996 5 23 96ZZZX2626 1 19960426 G 5320 DOUBLER DOUG DC8 DC862 3021970 WP FS 188-209 L24R CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK FUSELAGE RT SIDE, STRUCTURAL DOUBLER HAS CORROSION AROUND IT, BETWEEN FS 188 TO FS 208 AND BETWEEN L24R A ND L28R. REMOVED DOUBLER WITH CORROSION, FABRICATED NEW DOUBLER FROM 7075-T6 .065 INCH. TREATED AND PRIMED IAW SRM 51- 1-8. INSTALLED DOUBLER IAW SRM 51-1-21. 2 L 7 4 4F 4A25 1996052300755 19960523 00755 WP 1996 5 23 96ZZZX2627 1 19960426 G 5210 DOUBLER DOUG DC8 DC862 3021970 WP DOOR NR 60 CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 47070 DURING C-CHECK, FOUND DOUBLER AROUND DOOR NR 60 IS EXFOLIATED. REMOVED DOUBLER, FABRICATED NEW ONE IAW SRM 53-1-0 AND S RM 53-5-2, FIGURE 1. TREATED AND PRIMED IAW SRM 51-1-8 AND INSTALLED IAW SRM 51-1-21. 2 L 7 4 4F 4A25 1996052300756 19960523 00756 WP 1996 5 23 96ZZZX2628 1 19960426 G 5530 SKIN DOUG DC8 DC862 3021970 WP FREON EXH DOOR CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND FUSELAGE SKIN BELOW FREON EXHAUST DOOR HAS WORKING FASTENERS, LT SIDE. REMOVED INTERCOSTAL, FABRI CATED NEW INTERCOSTAL, CLEANED CORROSION IN AREA, FOUND WITHIN LIMITS. TREATED AND PRIMED AREA AND INTERCOSTAL IAW SRM 51-1-8. INSTALLED REPAIR IAW SRM 51-1-8, SRM 53-3-2, SRM 51-1-21, AND SRM 51-1-20D. REF: OPERATOR CONTROL NR 0248. 2 L 7 4 4F 4A25 1996052300757 19960523 00757 WP 1996 5 23 96ZZZX2629 1 19960426 G 5532 SKIN DOUG DC8 DC862 3021970 WP VERT STAB LE CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969V 46070 DURING C-CHECK, FOUND VERTICAL STABILIZER, L/E CORRODED AT APPROXIMATELY STA 179.750. CUT OUT DAMAGED SECTION AND REPAI RED IAW SRM 55-2-1, TREATED AND PRIMED IAW 51-1-8. SEALED AREA IAW SRM 51-1-16. REF: OPERATOR CONTROL NR 1707. 2 L 7 4 4F 4A25 1996052300758 19960523 00758 WP 1996 5 23 96ZZZX2630 1 19960426 G 5532 SKIN DOUG DC8 DC862 3021970 WP VERTICAL FIN CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND VERTICAL FIN, RT FORWARD EDGE WITH CORROSION ON SKIN AND SCREWS. REMOVED DAMAGED AREA AND FABRICA TED DOUBLER PER SRM 53-2-1. INSTALLED DOUBLER PER SRM 53-2-1. REF: OPERATOR CONTROL NR 0683. 2 L 7 4 4F 4A25 1996052300759 19960523 00759 WP 1996 5 23 96ZZZX2631 1 19960503 G 5730 SKIN DOUG DC8 DC862 3021970 WP XRS 107-189 CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK FOUND RT UPPER WING SURFACE HAS SEVERAL AREAS WITH CORROSION. AREAS ARE BETWEEN STA XRS 107.000 AND XRS 139.000, AT REAR SPAR APPROXIMATELY (DOT-6022). REMOVED CORROSION, FOUND AREA OUT OF LIMITS. REPAIRED AREA IAW DER NR 961ALE.005D-2. REF: OPERATOR CONTROL NR 07068. 2 L 7 4 4F 4A25 1996052300760 19960523 00760 WP 1996 5 23 96ZZZX2632 1 19960426 G 5313 S2641455 LONGERON DOUG DC8 DC862 3021970 WP FS 208-270 27 RT CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND CORROSION LEVEL 2 AT LONGERON 27 RT BETWEEN FS 208.00 TO FS 270.00. REMOVED AND REPLACED LONGERON IAW 53-2-0, SRM 51-1-21, AND SRM 51-1-20D. 2 L 7 4 4F 4A25 1996052300761 19960523 00761 WP 1996 5 23 96ZZZX2633 1 19960426 G 5311 FRAME DOUG DC8 DC862 3021970 WP FS 270 L28R-L29R CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND FORWARD CARGO COMPARTMENT AREA RT SIDE AT FRAME/STA 270 AND BETWEEN L28R AND L29R. FRAME HAS LOCA L CORROSION. FOUND CORROSION BEYOND LIMITS. CUT OUT CORRODED AREA, FABRICATED NEW FRAME SECTION AND EXTERNAL DOUBLER S TRAP IAW SRM 52-2-5, FIGURE 8C-2. 2 L 7 4 4F 4A25 1996052300762 19960523 00762 WP 1996 5 23 96ZZZX2634 1 19960426 G 5311 BULKHEAD DOUG DC8 DC862 3021970 WP LONGERON 10R WEB CRACKED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 WEB IS CRACKED, AFT SIDE OF FLAT AFT PRESSURE BULKHEAD AT LONGERON 10R, INSTALLED DOUBLERS AND FILLER IAW SRM 53-2-5 AND SRM 51-1-20. 2 L 7 4 4F 4A25 1996052300763 19960523 00763 WP 1996 5 23 96ZZZX2635 1 19960426 G 5320 DOUBLER DOUG DC8 DC862 3021970 WP FS 208-270 L31R CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND AIR CONDITIONING COMPARTMENT INTERNAL DOUBLER LOCATED BETWEEN FS 208 AND FS 270 AT L31R WITH A WID E SPREAD. REMOVED INTERNAL DOUBLER, FABRICATED AND INSTALLED NEW DOUBLER IAW DAC DRAWING NR 5613862 AND SRM 51-1-21 AND SRM 51-1-20D. 2 L 7 4 4F 4A25 1996052300764 19960523 00764 WP 1996 5 23 96ZZZX2636 1 19960426 G 5330 SKIN DOUG DC8 DC862 3021970 WP FWD LAV AREA CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND FORWARD LAVATORY WASTE DISPOSAL SERVICE AREA SKIN AROUND SERVICE NIPPLE WITH EXFOLIATION CORROSION . REMOVED INTERNAL PANEL. FABRICATED NEW INTERNAL PANEL PLATE IAW SRM 53-2-0. TREATED AND PRIMED IAW SRM 51-1-8. INS TALLED IAW SRM 51-1-14. 2 L 7 4 4F 4A25 1996052300765 19960523 00765 WP 1996 5 23 96ZZZX2637 1 19960426 G 5312 5772638103 BULKHEAD DOUG DC8 DC862 3021970 WP RBL 7-RBL 15 CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND SKIN HAS CORROSION LEVEL 2 AT AFT BULKHEAD WALL FORWARD SIDE FLOOR LEVEL, RBL 7 INCHES AND RBL 15 INCHES. REPAIRED IAW DACO ACTION NR 291159. 2 L 7 4 4F 4A25 1996053000001 19960530 00001 CE 1996 5 30 96ZZZX2638 1 19960507 G 2913 PF24390615BCE PUMP RKWELL NA265 NA26540 6402608 CE SEAL FAILED D A K NONE K FLUID LOSS IN INSP/MAINT 1 SO 16 303NT X347724 282029 PUMP WAS INSTALLED, TEST RUN FOR 30 SECONDS, AND REMOVED WITH ZERO HOURS TIME IN SERVICE SINCE OVERHAUL. PUMP WAS REMOV ED DUE TO SHAFT SEAL FAILED WHICH PUMPED FLUID OUT THROUGH THE CASE DRAIN AND CONTAMINATED THE DRIVE MOTOR. PUMP WAS OV ERHAULED ON 1-19-96. AIRCRAFT TOTAL TIME: 10,462. HRS. 2 L 7 2 4J A2WE 1996053000002 19960530 00002 CE 1996 5 30 96ZZZX2639 1 19960401 G 2750 556517531 GEARBOX CESSNA 500 500CESSNA 2076602 CE FLAP GEAR STRIPPED E K NONE O OTHER IN INSP/MAINT 1 SO 09 10UH 117 052893 5000304 FLAP GEARBOX, GEARS STRIP OUT AFTER 100 HOURS TO 200 HOURS. SUBMITTER STATES ONGOING PROBLEM. LANDINGS, 209. 1 L 7 2 4F A22CE 1996053000003 19960530 00003 CE 1996 5 30 96ZZZX2640 1 19960401 G 2750 556517531 GEARBOX CESSNA 500 500CESSNA 2076602 CE FLAP GEAR STRIPPED E K NONE O OTHER IN INSP/MAINT 1 SO 09 10UH 117 PAL037 5000304 FLAP GEARBOX, GEARS STRIP OUT AFTER 100 HOURS TO 200 HOURS. SUBMITTER STATES ONGOING PROBLEM. LANDINGS, 2O9. 1 L 7 2 4F A22CE 1996053000004 19960530 00004 CE 1996 5 30 96ZZZX2641 1 19960430 G 2150 206S22C BEARING BEECH 200 200BEECH 1152920 CE AC COMP DRV SEIZED B BXSR K NONE O OTHER IN INSP/MAINT 1 EA 09 200BE 6011 BB832 THE FORWARD SEALED BEARING ON THE AIR CONDITIONER COMPRESSOR DRIVE SEIZED AND CAUSED THE QUILL SHAFT TO SHEAR. 1 L 7 2 4T A24CE 1996053000005 19960530 00005 EU 1996 5 30 96ZZZX2642 1 19960501 G 3213 253505202 STRUT ISRAEL 1124 1124 4500102 EU RT MLG CORRODED H A K NONE O OTHER IN INSP/MAINT 1 SW 09 789TE 5660 241 RT MLG TRUNNION WOULD NOT TAKE GREASE. TRIED UNSUCCESSFULLY TO REMOVE TRUNNION PIN. PIN HAD TO BE CUT TO FACILITATE RE MOVAL. REPLACED UPPER BODY OF MLG, PIN, AND BUSHINGS DUE TO CORROSION. SUBMITTER STATED 2ND AIRCRAFT THIS YEAR WITH SA ME PROBLEM. REF: OPERATOR CONTROL NR 9601. 2 M 7 2 4F A2SW 1996053000006 19960530 00006 EU 1996 5 30 96ZZZX2643 1 19960501 G 3213 139862ED TRUNNION PIN ISRAEL 1124 1124 4500102 EU UPPER MLG CORRODED H K NONE O OTHER IN INSP/MAINT 1 SW 09 789TE 5660 130972ED 241 RT MLG TRUNNION WOULD NOT TAKE GREASE. TRIED UNSUCCESSFULLY TO REMOVE TRUNNION PIN. PIN HAD TO BE CUT TO FACILITATE RE MOVAL. REPLACED UPPER BODY OF MLG, PIN, AND BUSHINGS DUE TO CORROSION. SUBMITTER STATED 2ND AIRCRAFT THIS YEAR WITH SA ME PROBLEM. REF: OPERATOR CONTROL NR 9601. 2 M 7 2 4F A2SW 1996053000007 19960530 00007 CE 1996 5 30 96ZZZX2644 1 19960426 G 3260 MS244201 SWITCH BEECH MU300 400BEECH CE LT MLG DOOR INOPERATIVE B OG5R O OTHER J WARNING INDICATION AP APPROACH 1 GL 21 3038V 377 RK93 LANDING GEAR FAILED TO EXTEND. FOUND LANDING GEAR DOOR OPEN SWITCH (LEFT) DEFECTIVE. PERFORMED GEAR FREEFALL. THIS IS SECOND OCCURRENCE OF LEFT SWITCH ON THIS AIRCRAFT. PREVIOUS FAILURE AT ACFT TT, 1,096.5 HRS. CURRENT ACFT TT, 1,473.3 HRS. VENDOR P/N 41EN106. 2 H 7 2 4F RT A16SW 1996053000008 19960530 00008 CE 1996 5 30 96ZZZX2645 1 19960427 G 3260 MS243311 SWITCH BEECH MU300 400BEECH CE LT MLG FAILED B OG5R O OTHER N FALSE WARNING NR NOT REPORTED 1 GL 21 3196N 866 RK96 AIRCRAFT HAD REPETITIVE GEAR UNSAFE INDICATIONS. FOUND LEFT GEAR DOWN INDICATOR SWITCH FAULTY. INSTALLED NEW SWITCH. T HIS IS SECOND SWITCH TO FAIL. FIRST FAILURE OCCURRED AT AIRCRAFT TT, 535.1 HRS. AIRCRAFT TT, 1,397.4 HRS. 2 H 7 2 4F RT A16SW 1996053000009 19960530 00009 NE 1996 5 30 96ZZZX2646 2 19960422 G 8520 11768 CAM AIRTRC AT300 AT301 0390103 SW PWA R1340 R1340AN1 52016 NE ENGINE CRACKED G A UNSCHED LANDING E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 SO 09 36503 3010258 39831 ENGINE RAN ROUGH AND BACK-FIRED CAUSING THE PILOT TO MAKE AN EMERGENCY LANDING. THE ENGINE (FRONT) WAS DISASSEMBLED FIN DING THE CAM CRACKED. 1 L 7 1 3R 3 R A9SW 5E2 1996053000011 19960530 00011 SO 1996 5 30 96ZZZX2648 2 19960514 G 8530 653445 CYLINDER BEECH 58 58 1152740 CE CONT O520 IO520CB 17032 SO PLUG BOSS CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 07 1847F 1019 TH1291 298505R THE CONTINENTAL STEEL CYLINDER CRACKED FROM THE SPARK PLUG BOSS TO THE AREA BEHIND THE FUEL NOZZLE. THE CYLINDER HAD A TOTAL TIME OF ONLY 1,019.0 HRS. THE CYLINDER STILL HELD GOOD COMPRESSION, BUT WITH A SOAP CHECK, THE AIR LEAK WAS EVIDE NT. SUBMITTER STATES HAVE BEEN HAVING A SERIOUS PROBLEM WITH CYLINDERS CRACKING IN THIS POSITION. BELIEVE THIS IS A SE RIOUS PROBLEM AND SHOULD BE INVESTIGATED FURTHER. 1 L 7 2 3O 3 O 3A16 E5CE 1996053000012 19960530 00012 CE 1996 5 30 96ZZZX2649 1 19960402 G 3040 53032ARX SOLENOID CESSNA 441 441 2076020 CE WIPER/DEICE STUCK D K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 11 90GC 1584 44100889 WIPER/DEICE SOLENOID STUCK. CYCLED UNIT 2 TIMES, UNIT STUCK IN OPEN POSITION. SOLENOID FAILED AFTER 2 TIMES. UNIT WOU LD RESET AFTER PRESSURE WAS OFF. SUBMITTER STATED NEWLY OVERHAULED UNIT. 1 L 7 2 3T RT A28CE 1996053000013 19960530 00013 CE 1996 5 30 96ZZZX2650 1 19960402 G 3040 53032ARX SOLENOID CESSNA 441 441 2076020 CE WIPER/DEICE STUCK D K NONE O OTHER IN INSP/MAINT 1 GL 11 90GC 228 1420 4410089 WIPER/DEICE SOLENOID UNIT FAILED STUCK OPEN. 1 L 7 2 3T RT A28CE 1996053000014 19960530 00014 CE 1996 5 30 96ZZZX2651 1 19960402 G 3040 53032ARX SOLENOID CESSNA 441 441 2076020 CE WIPER/DEICE STUCK D K NONE O OTHER IN INSP/MAINT 1 GL 11 90GC 22 0334 4410089 WIPER/DEICE SOLENOID FAILED STUCK OPEN. 1 L 7 2 3T RT A28CE 1996053000015 19960530 00015 CE 1996 5 30 96ZZZX2652 1 19960402 G 3040 53032ARX SOLENOID CESSNA 441 441 2076020 CE WIPER/DEICE STUCK D K NONE O OTHER IN INSP/MAINT 1 GL 11 90GC 28 0966 4410089 WIPER/DEICE SOLENOID FAILED STUCK OPEN. 1 L 7 2 3T RT A28CE 1996053000016 19960530 00016 SO 1996 5 30 96ZZZX2653 1 19960410 G 3231 3147100 LINKAGE PIPER PA23 PA23250 7102308 SO LT MLG DOOR DISCONNECTED G A O OTHER J WARNING INDICATION LD LANDING 1 SW 99 2337M 8185 277954042 LEFT GEAR DOOR CONNECTOR LINKAGE BECAME DISCONNECTED PREVENTING DOOR FROM OPENING. GEAR-UP LANDING RESULTED. CLEVIS PI N HAD BECOME DISENGAGED FROM LINKAGE. THE PIPER INSPECTION REPORT DOES NOT SPECIFY THIS AREA, AND THE GEAR DOOR LINKAGE PINS ARE DIFFUCLT TO SEE. INSPECTION REPORT SHOULD BE AMMENDED TO SPECIFICALLY INCLUDE THESE CLEVIS PINS FOR SAFETY AN D SECURITY. 1 L 7 2 3O 1A10 1996053000017 19960530 00017 SO 1996 5 30 96ZZZX2654 1 19960406 G 5720 62086005 STIFFENER PIPER PA28 PA28161 7102803 SO INBD RT WING CRACKED D S K NONE O OTHER IN INSP/MAINT 1 EA 21 84400 6697 288216004 LOWER RIGHT INBOARD SKIN STIFFENER AT REAR OF WING FOUND CRACKED. 1 L 7 1 3O 2A13 1996053000018 19960530 00018 1996 5 30 96ZZZX2655 1 19960501 G 2822 1C610 PUMP AIRBORNE FUEL WATER CONTAM H K NONE O OTHER IN INSP/MAINT 1 GL 13 10 12W1828 INSPECTION FOUND FUEL PUMP FULL OF WATER AND RUST. 1996053000019 19960530 00019 SO 1996 5 30 96ZZZX2656 1 19960430 G 8120 CLAMP PIPER PA46 PA46310P 7104605 SO INTERCOOLER FAILED D A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 EA 03 4384T 468508028 HOSE CLAMP SECURING SONIC TUBE SCAT AT INTERCOOLER FAILED CAUSING LOSS OF 5 INCHES OF MANIFOLD PRESSURE ON TAKEOFF. CLA MP NOT FOUND (AREA DIRECTLY OVER COWL OPENING - PRESUMED LOST IN-FLIGHT). 1 L 7 1 3O A25SO 1996053000020 19960530 00020 NE 1996 5 30 96ZZZX2657 2 19960502 G 8500 ENGINE BEECH 18 RC45J 1151021 CE PWA R985 R985* 52008 NE RT WHEELWELL FIRE D O OTHER A FLAME/FIRE LD LANDING 1 SO 19 64819 523762 JP1956 FIRE IN RIGHT WHEELWELL DURING LANDING. WHILE LANDING, TOWER INFORMED THE PILOT THERE WAS FIRE COMING OUT OF WHAT APPEA RED TO BE THE RIGHT ENGINE. AT THIS POINT, THE CAUSE OF THE FIRE HAS NOT BEEN DETERMINED AND IS UNDER IVNESTIGATION BY THE NTSB AND THE FAA. 1 L 7 2 3R 3 R A765 5E1 1996053000021 19960530 00021 EA 1996 5 30 96ZZZX2658 2 19960507 G 8530 SL14995 SPRING LW12427 LYC O360 LO360A1G6 41514 EA NR 4 PUSH ROD BROKEN B ZM3R K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 07 L26771A ENGINE WAS ASSEMBLED AND TEST CELL RUN 1-24-96. ENGINE WAS NOT INSTALLED UNTIL 5-6-96. WHILE INSTALLING ENGINE, PUSH R OD TUBES ON NR 4 CYLINDER WERE FOUND LOOSE. REMOVAL OF VALVE COVER AND CLOSE INSPECTION FOUND SPRING BROKEN IN 2 PLACES . 3 O 1E10 1996053000022 19960530 00022 SO 1996 5 30 96ZZZX2659 1 19960509 G 2821 62305000 LINE 87477002 PIPER PA28 PA28181 7102807 SO FUEL STRAINER LEAK H A K NONE K W FLUID LOSS INADEQUATE Q C IN INSP/MAINT 1 GL 15 4365F 968 288490082 A PERSISTANT FUEL STAIN WAS NOTICED AT THE FIREWALL. UPON REMOVAL OF THE FUEL STRAINER ASSY, DISCOVERED THE FITTING ON THE INSIDE WAS CROSS-THREADED AND WEEPING FUEL. THE REASON IT WAS CROSS-THREADED IS THAT THE FUEL LINE FROM THE FUEL SE LECTOR TO THE FUEL STRAINER WAS INCORRECTLY BENT. UPON RECEIPT OF THE NEW PART, THE STRAINER TOP WAS FOUND TO HAVE THRE ADS OF POOR QUALITY AND NOT ENOUGH THREADS. PIPER CHECKED STOCK AND FOUND ALL THEIR STOCK DEFECTIVE. FINALLY, A PROPER PART ARRIVED. THIS WAS A FACTORY DEFECT. 1 L 7 1 3O 2A13 1996053000023 19960530 00023 1996 5 30 96ZZZX2660 4 19960401 G 2562 BS2190 ELT NARCO SHARC7 ELT MISMANUFACTURED B A CU4R K NONE W INADEQUATE Q C IN INSP/MAINT 1 AL 03 RED WIRE CONNECTING BATTERIES WAS NOT SOLDERED PROPERLY ON 3 SETS OF BATTERIES THAT WERE RECEIVED. MOUNDS OF SOLDER APP EAR TO HAVE BEEN PLACED ON THE TERMINAL CONNECTION OF THE BATTERIES AND THE WIRES INSERTED RESULTING IN COLD SOLDER CONN ECTIONS. WIRES PULLED OUT OF SOLDER CLEAN. 1996053000024 19960530 00024 WP 1996 5 30 96ZZZX2661 1 19960426 G 5320 FRAME DOUG DC8 DC862 3021970 WP NR 25 LT CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND CABIN WINDOW NR 25 LEFT, INNER FRAME SURFACE HAS CORROSION. REMOVED CORROSION AND REPAIRED IAW DR W SR 08530014. TREATED AND PRIMED AREA IAW SRM 51-1-8 AND REPLACED FASTENERS IAW 51-1-20D. 2 L 7 4 4F 4A25 1996053000025 19960530 00025 WP 1996 5 30 96ZZZX2662 1 19960426 G 5320 S2613996 STIFFENER DOUG DC8 DC862 3021970 WP AFT BLKHD LBL 22 CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK FOUND AFT BULKHEAD WALL, FORWARD SIDE VERTICAL STIFFENER AT LBL 22 HAS CORROSION, BOTTOM END. REMOVED AN D REPLACED CORRODED STIFFENER IAW SRM 51-1-21. 2 L 7 4 4F 4A25 1996053000026 19960530 00026 WP 1996 5 30 96ZZZX2663 1 19960426 G 5313 S1415997 LONGERON DOUG DC8 DC862 3021970 WP FS 1530-1670 32L CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND LONGERON 32L BETWEEN STATIONS 1530-1670 HAS LEVEL 2 CORROSION. REMOVED AND REPLACED LONGERON IAW SRM 51-1-21, ARM 51-1-8, AND SRM 51-1-20D. 2 L 7 4 4F 4A25 1996053000027 19960530 00027 WP 1996 5 30 96ZZZX2664 1 19960426 G 5313 S141599712000 LONGERON DOUG DC8 DC862 3021970 WP FS 1530-1066 30R CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND LONGERON 30R BETWEEN STATIONS 1530 TO 1606 HAS LEVEL 2 CORROSION. REMOVED AND REPLACED LONGERON I AW SRM 51-1-2, SRM 51-1-20D, SRM 51-1-8. 2 L 7 4 4F 4A25 1996053000028 19960530 00028 WP 1996 5 30 96ZZZX2665 1 19960426 G 5330 SKIN DOUG DC8 DC862 3021970 WP RUDDER AREA DENTED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 FOUND DURING C-CHECK, FUSELAGE AREA UNDER RUDDER HAS MAJOR DENTS IN SKIN. REMOVED AND REPLACED SKIN SEGMENT IAW DER 950 087-0699. 2 L 7 4 4F 4A25 1996053000029 19960530 00029 WP 1996 5 30 96ZZZX2666 1 19960426 G 5313 S1415997 LONGERON DOUG DC8 DC862 3021970 WP FS 1380 30R CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND LOWER AFT FUSELAGE COMPARTMENT, FS 1380 AND 30R LONGERON HAS CORROSION. CUT OUT DAMAGED SECTION, FABRICATED REPAIR AND SPLICES IAW SRM 53-2-2, TREATED AND PRIMED IAW SRM 51-1-8. INSTALLED NEW LONGERON SECTION WITH FA STENERS IAW SRM 53-4-1 AND SRM 53-2-2. 2 L 7 4 4F 4A25 1996053000030 19960530 00030 WP 1996 5 30 96ZZZX2667 1 19960426 G 5730 SKIN DOUG DC8 DC862 3021970 WP RT WS XRS 74.869 CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND RT WING UPPER SURFACE HAS CORROSION FORWARD OF CENTER SPAR AND XRS 74.869 (APPROXIMATELY). REPAIR ED RT WING UPPER SKIN AT APPROXIMATELY XRS 74.869 IAW DER 961ALE.005D-1. 2 L 7 4 4F 4A25 1996053000031 19960530 00031 WP 1996 5 30 96ZZZX2668 1 19960426 G 5730 SKIN DOUG DC8 DC862 3021970 WP LT WS XRS 311 CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND LT WING UPPER SKIN HAS CORROSION 10 INCHES AFT OF CENTER SPAR BETWEEN XRS 311.656 AND XRS 351.000. REPAIRED DAMAGED SKIN IAW DER NR 961 ALE.005D-3. 2 L 7 4 4F 4A25 1996053000032 19960530 00032 WP 1996 5 30 96ZZZX2669 1 19960426 G 5751 SKIN DOUG DC8 DC862 3021970 WP LT WING AILERON CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND LEFT WING OUTBOARD AILERON, INBOARD LOWER SURFACE SKIN BULGED. REPAIRED AILERON IAW DER DRW 95008 2-4066. 2 L 7 4 4F 4A25 1996053000033 19960530 00033 WP 1996 5 30 96ZZZX2671 1 19960426 G 5730 SKIN DOUG DC8 DC862 3021970 WP WS XRS 172 CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND LEVEL 2 CORROSION UPPER WING AT STA XRS 172.000. REPAIRED IAW DER DRAWING FROM AVITAS NR 961ALE.0 05D-6. 2 L 7 4 4F 4A25 1996053000034 19960530 00034 WP 1996 5 30 96ZZZX2672 1 19960426 G 5313 141599712000 LONGERON DOUG DC8 DC862 3021970 WP FS 1530-1670 34R CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND LONGERON 34R BETWEEN STA 1530 TO STA 1670 WITH CORROSION, LEVEL 2. REMOVED AND REPLACED LONGERON IAW SRM 51-1-21 AND SRM 51-1-8. 2 L 7 4 4F 4A25 1996053000035 19960530 00035 WP 1996 5 30 96ZZZX2673 1 19960426 G 5320 FLOOR WEB DOUG DC8 DC862 3021970 WP FS 1420 CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND AT FS 1420, FLOOR WEB HAS CORROSION LEVEL 1 LOCAL/TYPE. REMOVED CORROSION IAW 51-1-8 AND TREATED AND PRIMED. REPAIRED DAMAGE IAW 53-2-0. INSTALLED DOUBLER IAW SRM 53-2-6. 2 L 7 4 4F 4A25 1996053000036 19960530 00036 WP 1996 5 30 96ZZZX2674 1 19960426 G 5730 SKIN DOUG DC8 DC862 3021970 WP WS 329.000 TE CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 RIGHT WING, UPPER SURFACE LEADING EDGE ASSY - TRAILING EDGE HAS CORROSION AT FS 329.000, APPROXIMATE. REMOVED CORROSION . AREA FOUND BEYOND LIMITS. REMOVED DAMAGED AREA, FABRICATED DOUBLER AND REPAIRS IAW 57-201. REPAIRED DAMAGE IAW SRM 5-1-8, SRM 57-2-0, SRM 57-2-1, FIGURE 38, PAGES 137/138. 2 L 7 4 4F 4A25 1996053000037 19960530 00037 WP 1996 5 30 96ZZZX2677 1 19960426 G 5730 SKIN DOUG DC8 DC862 3021970 WP WS XRS 238-255 CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND LEFT WING UPPER SKIN HAS SEVERAL SPOTS WITH CORROSION BETWEEN FRONT SPAR AND CENTER SPAR BETWEEN X RS 238.000 AND XRS 255.000. REMOVED CORROSION, FOUND BEYOND LIMITS. FABRICATED DOUBLERS AND INSTALLED IAW DER NR 961AL E005 D-5. 2 L 7 4 4F 4A25 1996053000038 19960530 00038 WP 1996 5 30 96ZZZX2678 1 19960426 G 5311 FRAME DOUG DC8 DC862 3021970 WP FS 225 L21R-36R CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND FUSELAGE, RT SIDE FRAME FS 225, HAS CORROSION APPROXIMATELY BETWEEN L21R AND L36R. REMOVED SECTIO N OF FRAME WITH CORROSION FABRICATED NEW FRAME SECTION AND SPLICE IAW SRM 53-2-0, FIGURE 2, PAGE 5. TREATED, PRIMED, AN D INSTALLED IAW SRM 51-1-8 AND SRM 53-2-0, FIGURE 2. 2 L 7 4 4F 4A25 1996053000039 19960530 00039 WP 1996 5 30 96ZZZX2679 1 19960426 G 5320 INTERCOSTAL DOUG DC8 DC862 3021970 WP FS 188 L27R-L28R CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND FORWARD RT LOWER SIDE OF INTERNAL FUSELAGE BETWEN FS 168 TO FS 188, AND BETWEEN L27R AND L28R, SMA LL INTERCOSTAL HAS CORROSION. REMOVED INTERCOSTAL WITH CORROSION, FABRICATED NEW INTERCOSTAL IAW SRM 53-2-0, TREATED, P RIMED, AND INSTALLED IAW SRM 51-1-21, SRM 51-1-18, AND SRM 51-1-20D. 2 L 7 4 4F 4A25 1996053000040 19960530 00040 WP 1996 5 30 96ZZZX2680 1 19960426 G 5240 DOOR DOUG DC8 DC862 3021970 WP RT FUS LAV SERV CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND FORWARD RT FUSELAGE LAVATORY SERVICE DOOR AND DOOR CUT-OUT HAVE CORROSION. REMOVED DOOR, FABRICAT ED NEW DOOR AND INSTALLED IAW SRM 51-1-0 AND SRM 53-4-1. REMOVED CORROSION ON CUT-OUT, TREATED AND PRIMED IAW SRM 51-1- 8. 2 L 7 4 4F 4A25 1996053000041 19960530 00041 WP 1996 5 30 96ZZZX2681 1 19960426 G 5720 STRAP DOUG DC8 DC862 3021970 WP LT WING LE INBD CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND LEFT WING LEADING EDGE, INBOARD SLOT AREA OUTBOARD END HAS TWO AREAS OF EXFOLIATION WITH CORROSION ON STRAP. REMOVED CORROSION, FOUND BEYOND LIMITS IAW SRM 57-3-0. FABRICATED NEW STRAP IAW SRM 57-3-0. TREATED, PRIME D, AND INSTALLED IAW SRM 51-1-21D. 2 L 7 4 4F 4A25 1996053000042 19960530 00042 WP 1996 5 30 96ZZZX2682 1 19960426 G 5730 SKIN DOUG DC8 DC862 3021970 WP LT WS XRS 22.750 RUSTED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND LEFT WING UPPER SKIN HAS BARE METAL AND RUSTED FASTENERS AT CTR SPAR AND XRS 22.750. REPAIRED UPP ER SKIN IAW E.O. NR 961ALE.005D-4. 2 L 7 4 4F 4A25 1996053000043 19960530 00043 WP 1996 5 30 96ZZZX2683 1 19960426 G 5400 57530057W BRACE DOUG DC8 DC862 3021970 WP NR 2 INBD PYLON DAMAGED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND NR 2 INBOARD PYLON SIDE, BRACE DAMAGED AND GOUGED. REMOVED AND REPLACED NEW THRUST LINK BRACE IAW SB 54-90-00 AND SRM 51-1-20D. 2 L 7 4 4F 4A25 1996053000044 19960530 00044 WP 1996 5 30 96ZZZX2684 1 19960426 G 5313 2597242318000 LONGERON DOUG DC8 DC862 3021970 WP FS 208-270 29R CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND LEVEL 2 CORROSION ON LONGERON 29R, FS 208.00 TO FS 270.00. REMOVED AND REPLACED LONGERON IAW SRM 53-2-0, SRM 51-1-21, AND SRM 51-1-20D. 2 L 7 4 4F 4A25 1996053000045 19960530 00045 WP 1996 5 30 96ZZZX2685 1 19960426 G 5751 SKIN DOUG DC8 DC862 3021970 WP RT OTBD AILERON CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND RT OUTBOARD AILERON SKIN BULGING. CUT OUT DAMAGED AREA, REPAIRED IAW DER DRAWING ARW 950082-0289. 2 L 7 4 4F 4A25 1996053000046 19960530 00046 WP 1996 5 30 96ZZZX2686 1 19960426 G 5330 SKIN DOUG DC8 DC862 3021970 WP FS 1420 LON 30L CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND LOWER AFT FUSELAGE SKIN AT STA 1420.00, LONGERON 30L, BULGING. REPAIRED IAW SRM 53-2-1 AND SRM 51 -1-8. 2 L 7 4 4F 4A25 1996053000047 19960530 00047 WP 1996 5 30 96ZZZX2687 1 19960426 G 5313 14159971200 LONGERON DOUG DC8 DC862 3021970 WP FS 1530-1670 32R CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND LONGERON 32R, BETWEEN STA 1530 AN STA 1670, WITH CORROSION, LEVEL 2. REMOVED AND REPLACED IAW 51- 1-21, SRM 51-1-20D, SRM 51-1-8. 2 L 7 4 4F 4A25 1996053000048 19960530 00048 WP 1996 5 30 96ZZZX2688 1 19960426 G 5320 47731461 FITTING DOUG DC8 DC862 3021970 WP FS 1500 LON 21R CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND CORROSION FUSELAGE FITTING STA 1500.00 AT LONGERON 21R. REMOVED AND REPLACED FITTING IAW SRM 51-1 -20D, 51-1-8. 53-2-0, 51-1-21, AND 51-3-0. 2 L 7 4 4F 4A25 1996053000049 19960530 00049 WP 1996 5 30 96ZZZX2689 1 19960426 G 5320 FRAME DOUG DC8 DC862 3021970 WP WINDOW LT FS 610 CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND FS 610 LT WINDOW FRAME HAS A CRACK AT LOWER SIDE FROM CORROSION LEVEL 1 LOCAL TYPE. BLENDED OUT A ND REMOVED CORROSION. FOUND AREA BEYOND LIMITS IAW DAC SR.08530014 DRAWING. FABRICATED EXTERNAL DOUBLER FROM 7075.T6 . 190 INCH. INSTALLED IAW DAC SR.08530014 AND SRM 51-1-20. 2 L 7 4 4F 4A25 1996053000050 19960530 00050 WP 1996 5 30 96ZZZX2690 1 19960426 G 5320 INTERCOSTAL DOUG DC8 DC862 3021970 WP FS 822 L19L CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND FS 822 L19L HAS CORROSION LEVEL 1 LOCAL TYPE. REMOVED INTERCOSTAL, FABRICATED NEW ONE, TREATED, A LODINED, AND PRIMED. INSTALLED NEW INTERCOSTAL IAW SRM 53-2-0 AND SRM 51-1-8. 2 L 7 4 4F 4A25 1996053000051 19960530 00051 WP 1996 5 30 96ZZZX2691 1 19960426 G 5320 ANGLE DOUG DC8 DC862 3021970 WP AFT BLKHD FWD CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND AFT BULKHEAD, FORWARD SIDE, FLOOR PANEL ATTACH ANGLE ON LEFT SIDE OF CENTER IS CORRODED. REMOVED ANGLE AND FABRICATED NEW ONE PER SRM 53-2-0. INSTALLED ANGLE PER SRM 51-1-21. 2 L 7 4 4F 4A25 1996053000052 19960530 00052 WP 1996 5 30 96ZZZX2692 1 19960426 G 5320 FLANGE DOUG DC8 DC862 3021970 WP FS 420 L5R-L6R CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND FS 420 HAS CORROSION AT THE LOWER FLANGE BETWEEN L5R AND L6R. REMOVED CORROSION IAW SRM 51-1-8. F OUND OUT OF LIMITS IAW SRM 53-2-0. CUT OUT DAMAGED AREA, FABRICATED FILLER AND DOUBLER IAW 53-2-1. PARTS HEAT TREATED ATI P.O. 2407. TREATED AND PRIMED IAW SRM 51-1-8. INSTALLED REPAIRED IAW SRM 53-20-10. 2 L 7 4 4F 4A25 1996053000053 19960530 00053 WP 1996 5 30 96ZZZX2693 1 19960426 G 5320 WEB DOUG DC8 DC862 3021970 WP FS 235 L21R CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND FUSELAGE RT SIDE, A/C COMPARTMENT AREA UNDER CABIN FLOOR PANEL AT FS 235 AND L21R INTERCOSTAL (WEB ) HAS CORROSION. REMOVED, FABRICATED NEW WEB, AND INSTALLED IAW SRM 53-20-6 AND SRM 51-1-21. 2 L 7 4 4F 4A25 1996053000054 19960530 00054 WP 1996 5 30 96ZZZX2694 1 19960426 G 5313 S2593956 LONGERON DOUG DC8 DC862 3021970 WP FS 208-270 31R CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND CORROSION LEVEL 2 ON LONGERON 31R BETWEEN FS 208.00 AND FS 270.00. REMOVED AND REPLACED LONGERON IAW SRM 53-2-0, SRM 51-1-21, AND SRM 51-1-20D. 2 L 7 4 4F 4A25 1996053000055 19960530 00055 WP 1996 5 30 96ZZZX2695 1 19960426 G 5720 T-ANGLE DOUG DC8 DC862 3021970 WP LT WS XW 33 CRACKED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND LEFT WING AUXILIARY SPAR AREA INBD LOWER VERTICAL SUPPORT T-ANGLE CRACKED AT STA XW 33.000. INSTA LLED NEW VERTICAL SUPPORT T-ANGLE IAW SRM 51-1-20, SRM 53-1-0, AND SRM 51-1-8. 2 L 7 4 4F 4A25 1996053000056 19960530 00056 WP 1996 5 30 96ZZZX2696 1 19960426 G 5313 2597242318000 LONGERON DOUG DC8 DC862 3021970 WP FS 208-270 L24R CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND CORROSION LEVEL 2 ON LONGERON 24R BETWEEN FS 208.00 AND FS 270.00. REMOVED AND REPLACED LONGERON IAW SRM 53-2-0, SRM 51-1-21, AND SRM 51-1-20D. 2 L 7 4 4F 4A25 1996053000057 19960530 00057 WP 1996 5 30 96ZZZX2697 1 19960426 G 5313 2597424318000 LONGERON DOUG DC8 DC862 3021970 WP FS 270 8L-7L CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND LONGERONS CRACKED AT FS 270.00, LONGERONS 8L AND 7L. REPAIRED IAW SRM 53-2-2. 2 L 7 4 4F 4A25 1996053000231 19960530 00231 NE 1996 5 30 96ZZZX2698 2 19960507 G 7261 2380 OIL BEECH B300 B300 1159232 CE PWA PT6 PT6A60A 52043 NE ENGINE METAL FOD H A K NONE W INADEQUATE Q C IN INSP/MAINT 1 NE 01 207R FL14 PCE95489 WHEN ADDING OIL TO ENGINE (EXXON 2380 LOT NR B652 11-29-95) NOTICED METAL CONTAMINATION IN STRAINER USED TO POUR OIL INT O ENGINE. INVESTIGATED OIL IN CAN, FOUND PARTICLES COULD BE PICKED UP BY A MAGNET. DRAINED AND FLUSHED ENGINE OIL SYST EM. INFORMED EXXON AND FAA. OIL SAMPLE SUPPLIED TO EXXON. 2 L 7 2 4T 4 T RT A24CE E4EA 1996053000232 19960530 00232 SO 1996 5 30 96ZZZX2699 1 19960514 G 2432 MA5 BATTERY GULSTM G1159 G1159A 3970109 SO NR 2 DEFECTIVE D K NONE O OTHER IN INSP/MAINT 1 EA 25 313RG 9103408 321 DURING ROUTINE INSPECTION, THE NR 2 BATTERY FAILED THE CAPACITY CHECK. FIVE OF 19 CELLS NEED REPLACING. THE BATTERY IS LESS THAN ONE YEAR OLD. THIS HAS BEEN AN ONGOING CONDITION FOR THIS TYPE OF BATTERY. 'A NEW AND IMPROVED BATTERY'. A LSO, 3 CELLS SHOWED EVIDENCE OF EXTREME HEAT (MELTING OBSERVED). 2 L 7 2 4F A12EA 1996053000233 19960530 00233 EA 1996 5 30 96ZZZX2700 2 19960430 G 7321 2528973 BEARING BENDIX DPF2 BEECH 90 B90 1152912 CE PWA PT6 PT6A20 52043 EA RT ENG FUEL CONT FAILED D O OTHER Y ENGINE STOPPAGE NR NOT REPORTED 1 WP 23 388MC 322 194208 LJ383 PCE22420 RIGHT ENGINE FLUCTUATIONS 2-3 SECONDS, 3 TIMES. AIRCRAFT YAW. FIFTEEN MINUTES LATER, FLUCTUATINS OCCURRED THEN FUEL FL OW WENT TO ZERO. ENGINE QUIT. RESTARTED ON GROUND, NO RESPONSE TO THROTTLE. DISASSEMBLED FUEL CONTROL, FOUND BUSHING ASSY BEARING FAILED. 1 L 7 2 3T 3 T 3A20 E4EA 1996053000234 19960530 00234 CE 1996 5 30 96ZZZX2701 1 19960314 G 2910 6000100287 TUBE ASSY LEAR 60 60LEAR 5170707 CE HYD SYS CHAFED C K NONE O OTHER IN INSP/MAINT 1 SW 09 799SC 80 067 THE EXTERNAL HYD CART PRESSURE LINE BETWEEN THE QUICK DISCONNECT AND THE HYD SYSTEM WAS FOUND CHAFING ON THE RT HYD ACCU MULATOR. A LEAK HERE WOULD CAUSE TOTAL LOSS OF FLUID. DAMAGE WAS ALSO FOUND AT THE UPPER B-NUT FERRULE AREA. DEPTH (A PPROXIMATE) OF CHAFE - 0.008 INCH. DEPTH (APPROXIMATE) OF B-NUT AREA TOOL DAMAGE - 0.005 INCH. 2 L 7 2 4F RT A10CE 1996053000235 19960530 00235 WP 1996 5 30 96ZZZX2702 1 19960426 G 5320 3610130501 FITTING DOUG DC8 DC862 3021970 WP FS 270 LON 21R CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, LEVEL 2 CORROSION ON FITTING AT FS 270.00, LONGERON 21R. REPAIRED IAW DAC FAX 287337, 288375, AND 25181 9/01, SRM 51-1-20D AND SRM 51-3-0. 2 L 7 4 4F 4A25 1996053000236 19960530 00236 WP 1996 5 30 96ZZZX2703 1 19960426 G 5320 FINGER DOUBLER DOUG DC8 DC862 3021970 WP FS 188-270 RT CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 FUSELAGE RT SIDE, L21R, HAS CORROSION AT INTERNAL FINGER DOUBLER BETWEEN STA 188 TO STA 270. REMOVED, FABRICATED, INSTA LLED NEW FINGER DOUBLER IAW SRM 51-1-21, SRM 53-3-2, SRM 51-1-8. 2 L 7 4 4F 4A25 1996053000237 19960530 00237 WP 1996 5 30 96ZZZX2704 1 19960426 G 5320 FRAME DOUG DC8 DC862 3021970 WP WINDOW NR 30 LT CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 CABIN WINDOW, NR 30 LT, CORRODED. REPAIRED FRAME IAW DAC SRO 8530014. 2 L 7 4 4F 4A25 1996053000238 19960530 00238 WP 1996 5 30 96ZZZX2705 1 19960426 G 5620 FRAME DOUG DC8 DC862 3021970 WP WINDOW NR 28 LT CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 CABIN WINDOW NR 28 LT, FRAME CORRODED. REPLACED WINDOW FRAME IAW SRM 51-1-20D, SRM 51-1-8. 2 L 7 4 4F 4A25 1996053000239 19960530 00239 WP 1996 5 30 96ZZZX2706 1 19960426 G 5400 THRUST LINK DOUG DC8 DC862 3021970 WP NR 4 ENG PYLON CHAFED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 NR 4 ENGINE PYLON THRUST LINK CHAFED. REMOVED AND REPLACED THRUST LINK IAW SB 54-92-00, SRM 51-1-20D. 2 L 7 4 4F 4A25 1996053000240 19960530 00240 CE 1996 5 30 96ZZZX2707 1 19960506 G 3097 WIRE LEAR 60 60LEAR 5170707 CE V STAB TIP CAP CHAFED D A K NONE L NO TEST IN INSP/MAINT 1 SW 05 638LJ 879 038 ACFT HAD FAILURES OF HORIZ STAB ANTI-ICE SYS. EACH FAILURE COULD NOT BE VERIFIED TO WORK AFTER REPLACEMENT OF FL-94 CUR RENT LIMITER WHICH WAS BLOWN FROM OVERCURRENT SITUATION, T/S FND WIRE NR 10 FROM TERM BLK TB-5 JUNC IN AREA OF VERT STAB TIP CAP CHAFED & BURNED DUE TO CONTACT WITH STRUCT, FS-651.455. LOOP FROM HEAT BLANKET TO TERM BLK NOT CORRECT, ALLOWE D WIRE BUNDLE TO CONTACT ACFT STRUCT WHEN STAB TRIM WAS MOVED & RUBBED INSULATION AWAY ALLOWING WIRE TO SHORT OUT WHEN S YS ENERGIZED & STAB POSITION ALLOWED CONTACT OF WIRE. ARCING BURNED FLANGE OFF STIFFENER AN INCH & DAMAGED INSULATION O F WIRES IN BUNDLE. ONE-TIME INSP OF RT & LT STAB HEAT SYS WIRING IS CALLED FOR TO PREVENT DAMAGE TO SURROUNDING STRUCT. 2 L 7 2 4F RT A10CE 1996053000241 19960530 00241 WP 1996 5 30 96ZZZX2708 1 19960426 G 5320 SUPPORT CHANNEL DOUG DC8 DC862 3021970 WP AFT LAV FS 1574 CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 CABIN, AFT LAVATORY AREA, FLOOR SUPPORT CHANNEL CORRODED. FABRICATED AND INSTALLED NEW CHANNEL IAW SRM 53-2-0, SRM 51-1 -8, SRM 51-3-0. 2 L 7 4 4F 4A25 1996053000242 19960530 00242 WP 1996 5 30 96ZZZX2709 1 19960426 G 5620 FRAME DOUG DC8 DC862 3021970 WP WINDOW NR 26 LT CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 CABIN WINDOW FRAME EXFOLIATED AROUND 1 BOLT HOLE. INSTALLED DOUBLER IAW DER NR SRO8530014 AND SRM 51-1-20D. 2 L 7 4 4F 4A25 1996053000243 19960530 00243 WP 1996 5 30 96ZZZX2710 1 19960426 G 5313 LONGERON DOUG DC8 DC862 3021970 WP FS 1530-1670 34L CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND LONGERON 34L BETWEEN STA 1530 - STA 1670 HAS CORROSION, LEVEL 2. REMOVED AND REPLACED LONGERON IA W SRM 51-1-21, SRM 51-1-20D, AND SRM 51-1-8. 2 L 7 4 4F 4A25 1996053000244 19960530 00244 WP 1996 5 30 96ZZZX2711 1 19960426 G 5313 14159971200 LONGERON DOUG DC8 DC862 3021970 WP FS 1530-1670 CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND LONGERON 36 BETWEEN FS 1530 TO FS 1670 WITH LEVEL 2 CORROSION. REMOVED AND REPLACED LONGERON IAW SRM 51-1-21 AND SRM 51-1-20D. 2 L 7 4 4F 4A25 1996053000245 19960530 00245 WP 1996 5 30 96ZZZX2712 1 19960426 G 5313 S2641455 LONGERON DOUG DC8 DC862 3021970 WP FS 208-270 L30R CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND LEVEL 2 CORROSION AT LONGERON L30R, FS 208.00 TO FS 270.00. REMOVED AND REPLACED LONGERON IAW SRM 53-2-0, SRM 51-1-21, AND SRM 51-1-20D. 2 L 7 4 4F 4A25 1996053000246 19960530 00246 WP 1996 5 30 96ZZZX2713 1 19960426 G 5730 SKIN DOUG DC8 DC862 3021970 WP LT WS XRS 45 CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND LT UPPER WING SKIN HAS CORROSION AT CTR SPAR AND XRS 45.000. REPAIRED SKIN IAW E.O. 96IALE.005D-4 . 2 L 7 4 4F 4A25 1996053000247 19960530 00247 WP 1996 5 30 96ZZZX2714 1 19960426 G 5320 ANGLE DOUG DC8 DC862 3021970 WP FS 1606 AFT BLK CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND LOWER AFT FUSELAGE COMPARTMENT AT STA 1606, ANGLE ATTACHED TO THE AFT BULKHEAD AT FLOOR LEVEL HAS CORROSION. FABRICATED NEW ANGLE AND INSTALLED IAW SRM 53-2-0, SRM 51-1-8, SRM 51-1-20D, SRM 51-1-21. 2 L 7 4 4F 4A25 1996053000248 19960530 00248 WP 1996 5 30 96ZZZX2715 1 19960426 G 5730 SKIN DOUG DC8 DC862 3021970 WP LT WS XRS 22.75 CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND LT WING UPPER SKIN HAS CORROSION AT CTR SPAR AND XRS 22.750. REPAIRED SKIN IAW E.O. 961 ALE.005D- 4. 2 L 7 4 4F 4A25 1996053000249 19960530 00249 WP 1996 5 30 96ZZZX2716 1 19960426 G 5320 ANGLE DOUG DC8 DC862 3021970 WP FS 834.5 XCW 0 CRACKED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND LOWER FUSELAGE LT ADF SENSE ANTENNA COMPARTMENT, FORWARD ATTACH ANGLE, CRACKED AT STA 834.500 BETW EEN XCW ZERO AND XCW 23. INSTALLED REPAIR ANGLE IAW SRM 53-2-0, SRM 53-2-0, AND SRM 51-1-20. 2 L 7 4 4F 4A25 1996053000250 19960530 00250 WP 1996 5 30 96ZZZX2717 1 19960426 G 5320 46401621N FITTING DOUG DC8 DC862 3021970 WP FS 1260 CUSP CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND CABIN UPPER SURFACE OF THE RT SIDE CUSP AREA, FS 1260 AT FLOOR LEVEL, FITTING HAS CORROSION. REMOV ED DAMAGED FITTING, REMOVED CORROSION AREA, FOUND WITHIN LIMITS. ALODINED AND PRIMED AREA. INSTALLED NEW FITTING, PN 4 640162-1N, IAW SRM 51-1-20D, SRM 51-3-0, SRM 51-1-8, AND SRM 53-2-0. 2 L 7 4 4F 4A25 1996053000251 19960530 00251 WP 1996 5 30 96ZZZX2718 1 19960426 G 5320 INTERCOSTAL DOUG DC8 DC862 3021970 WP FS 208-225 L28R CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND FUSELAGE RT SIDE, INTERCOSTAL RT L28R BETWEEN FS 209 TO FS 225, HAS CORROSION. REMOVED INTERCOSTA L IAW SRM 53-2-0, SRM 5-1-21, AND SRM 51-1-20D. 2 L 7 4 4F 4A25 1996053000252 19960530 00252 WP 1996 5 30 96ZZZX2719 1 19960426 G 5320 STIFFENER DOUG DC8 DC862 3021970 WP FS 208 RT CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND A/C COMPARTMENT RT SIDE AT FS 208, BULKHEAD STIFFENER HAS EXFOLIATON CORROSION IN DIFFERENT LOCATI ON. REMOVED STIFFENER WITH CORROSION, FABRICATED NEW IAW SRM 53-2-0. TREATED, PRIMED, AND INSTALLED IAW SRM 51-1-8, SR M 51-1-21, AND SRM 51-1-20D. 2 L 7 4 4F 4A25 1996053000253 19960530 00253 WP 1996 5 30 96ZZZX2720 1 19960426 G 5313 1415997 LONGERON DOUG DC8 DC862 3021970 WP FS 1530-1670 L30 CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND LONGERON 30L BETWEEN FS 1530 TO FS 1670, HAS CORROSION, LEVEL 2. REMOVED AND REPLACED DAMAGED LON GERON AND FITTING IAW SRM 51-1-21 AND SRM 51-1-20D. TREATED AND PRIMED IAW SRM 51-1-8 AND SRM 53-10-0. 2 L 7 4 4F 4A25 1996053000254 19960530 00254 WP 1996 5 30 96ZZZX2721 1 19960426 G 5320 4641324N FITTING DOUG DC8 DC862 3021970 WP FS 1530-1670 L30 CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND LONGERON 30L BETWEEN FS 1530 TO FS 1670, HAS CORROSION, LEVEL 2. REMOVED AND REPLACED DAMAGED LON GERON AND FITTING IAW SRM 51-1-21 AND SRM 51-1-20D. TREATED AND PRIMED IAW SRM 51-1-8 AND SRM 53-10-0. 2 L 7 4 4F 4A25 1996053000255 19960530 00255 WP 1996 5 30 96ZZZX2722 1 19960426 G 5320 INTERCOSTAL DOUG DC8 DC862 3021970 WP FS 188-208 CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND FUSELAGE RT SIDE, STRUCTURAL INTERCOSTAL RT L30R AND BETWEEN FS 188 AND FS 208, HAS CORROSION AT L OWER FLANGE. REMOVED INTERCOSTAL, FABRICATED NEW INTERCOSTAL IAW SRM 53-20-0, TREATED, PRIMED, AND INSTALLED IAW SRM 51 -1-8, SRM 51-1-21, AND SRM 51-1-20D. 2 L 7 4 4F 4A25 1996053000256 19960530 00256 WP 1996 5 30 96ZZZX2723 1 19960426 G 5313 2593956 LONGERON DOUG DC8 DC862 3021970 WP FS 208-270 L31R CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND FUSELAGE RT SIDE, L31R, HAS CORROSION BETWEEN FS 208 TO FS 270. REMOVED CORRODED LONGERON AND INS TALLED NEW LONGERON IAW 53-2-0, SRM 51-1-21, AND SRM 51-1-20D. 2 L 7 4 4F 4A25 1996053000257 19960530 00257 WP 1996 5 30 96ZZZX2724 1 19960426 G 5320 47731471 FITTING DOUG DC8 DC862 3021970 WP FS 1500 CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND CABIN UPPER SURFACE OF THE RT CUSP AREA, FS 1500, INSIDE DOOR JAM AFT LOWER CORNER, SMALL FITTING HAS CORROSION. REMOVED DAMAGED FITTING, REMOVED CORROSION FROM AREA, AREA FOUND WITHIN LIMITS. TREATED AND PRIMED AREA . INSTALLED NEW FITTING, PN 4773147-1, AND CLOSED AREA IAW SRM 51-1-8, SRM 51-1-20, SRM 53-2-0, AND SRM 51-1-21. 2 L 7 4 4F 4A25 1996053000258 19960530 00258 WP 1996 5 30 96ZZZX2725 1 19960426 G 5320 S643396501 FRAME DOUG DC8 DC862 3021970 WP FS 1010 LT CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND LEVEL 2 CORROSION AT WINDOW FRAME FS 1010, LT SIDE. REPAIRED IAW DOUGLAS DRAWING SR08530010-7085. 2 L 7 4 4F 4A25 1996053000259 19960530 00259 WP 1996 5 30 96ZZZX2726 1 19960426 G 5315 FLOOR BEAM DOUG DC8 DC862 3021970 WP FS 160-188 CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND LEVEL 2 CORROSION AT COCKPIT FLOOR BEAM AND FINGER DOUBLERS, FS 160 TO FS 188. REPAIRED IAW DER D RAWING ARW 950087-0083. 2 L 7 4 4F 4A25 1996053000260 19960530 00260 WP 1996 5 30 96ZZZX2727 1 19960426 G 5230 SKIN DOUG DC8 DC862 3021970 WP AFT CARGO DOOR CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND CORROSION AT AFT LOWER CARGO DOOR SKIN NEAR HANDLE. REPAIRED IAW SRM'S 52-2-0, 51-1-21, 51-1-0, A ND 51-1-8. 2 L 7 4 4F 4A25 1996053000261 19960530 00261 WP 1996 5 30 96ZZZX2728 1 19960426 G 5313 LONGERON DOUG DC8 DC862 3021970 WP FS 208-270 L28R CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 FUSELAGE RT SIDE L28R HAS CORROSION BETWEEN STA 208-STA 270. REMOVED AND REPLACED LONGERON IAW SRM'S 53-2-0, 51-1-21, A ND 51-1-20D. 2 L 7 4 4F 4A25 1996053000262 19960530 00262 WP 1996 5 30 96ZZZX2729 1 19960426 G 5313 25972423 LONGERON DOUG DC8 DC862 3021970 WP FS 208-270 L23R CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 FUSELAGE, RT SIDE L23R, HAS CORROSION ON THE CTR FLANGE BETWEEN STA 208-STA 270. REMOVED AND INSTALLED NEW SECTION OF L ONGERON IAW SRM'S 53-2-2, 51-1-20D, 51-1-21, AND 51-3-0. 2 L 7 4 4F 4A25 1996053000263 19960530 00263 WP 1996 5 30 96ZZZX2730 1 19960426 G 5313 LONGERON DOUG DC8 DC862 3021970 WP FS 208-270 L22R CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 FUSELAGE, RT SIDE, L22R, HAS CORROSION BETWEEN STA 208-STA 270. REMOVED AND INSTALLED NEW LONGERON IAW SRM'S 51-1-8, 53 -2-0, AND 51-1-20D. 2 L 7 4 4F 4A25 1996053000264 19960530 00264 WP 1996 5 30 96ZZZX2731 1 19960426 G 5320 SUPPORT BRACKET DOUG DC8 DC862 3021970 WP FS 208 L22R CRACKED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 FRAME CAP SUPPORT BRACKET CRACKED, STA 208, L22R. REMOVED, FABRICATED, AND INSTALLED NEW BRACKET IAW DAC CL-P63-ATM-025 AND SRM'S 51-1-20D AND 51-1-21. 2 L 7 4 4F 4A25 1996053000265 19960530 00265 WP 1996 5 30 96ZZZX2732 1 19960426 G 5400 THRUST LINK DOUG DC8 DC862 3021970 WP NR 1 PYLON LOWER DAMAGED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 NR 1 PYLON THRUST LINK, LOWER FORWARD FLANGE, IS GOUGED. REMOVED AND REPLACED THRUST LINK IAW SB 54-92-00 AND SRM 51-1- 20D. 2 L 7 4 4F 4A25 1996053000266 19960530 00266 WP 1996 5 30 96ZZZX2733 1 19960426 G 5730 SKIN DOUG DC8 DC862 3021970 WP WS XRS 50 LT DAMAGED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 LEFT WING UPPER SKIN HAS DEEP BLEND-OUTS 20 INCHES FORWARD OF CTR SPAR AND XRS 50.000, APPROXIMATE. FABRICATED DOUBLER FROM 7075-T6 .125 INCH IAW SRM 57-2-1, PAGES 59, 60, AND FILLER, SRM'S 51-1-20D AND 51-1-12 AND INSTALLED. 2 L 7 4 4F 4A25 1996053000267 19960530 00267 WP 1996 5 30 96ZZZX2734 1 19960426 G 5315 FLOOR BEAM DOUG DC8 DC862 3021970 WP FS 1568 AFT LAV CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 AFT LAVATORY AREA, FLOOR BEAM AT FS 1568, HAS CORROSION ON TOP CAP. REPLACED FLOOR BEAM IAW SRM'S 53-2-0, 51-1-0, 51-1- 8, 51-1-3, 51-1-21. 2 L 7 4 4F 4A25 1996053000268 19960530 00268 WP 1996 5 30 96ZZZX2735 1 19960426 G 5320 CLIP DOUG DC8 DC862 3021970 WP FS 1040 LT CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 FS 1040, LEFT, FRAME TO LONGERON CLIPS HAVE CORROSION, LEVEL 2. REMOVED, FABRICATED NEW LONGERONS, REINSTALLED CLIPS IA W SRM'S 51-1-8, 51-2-0, 51-1-21D. 2 L 7 4 4F 4A25 1996053000269 19960530 00269 WP 1996 5 30 96ZZZX2736 1 19960426 G 5320 BATHTUB FITTING DOUG DC8 DC862 3021970 WP FS 270 L25 CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 BATHTUB FITTING HAS LEVEL 2 CORROSION, FS 270, L25. REMOVED FITTING, REMOVED CORROSION, REINSTALLED FITTING IAW SRM'S 5 1-1-3, 51-1-8, 51-1-20D. 2 L 7 4 4F 4A25 1996053000270 19960530 00270 WP 1996 5 30 96ZZZX2737 1 19960426 G 5320 INTERCOSTAL DOUG DC8 DC862 3021970 WP FS 335 L30 CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 FS 335, L30, INTERCOSTAL HAS LEVEL 2 CORROSION. REMOVED AND REPLACED DAMAGED INTERCOSTAL IAW SRM'S 53-20, 51-1-8, AND 5 1-20-0. 2 L 7 4 4F 4A25 1996053000271 19960530 00271 WP 1996 5 30 96ZZZX2738 1 19960426 G 5320 FRAME DOUG DC8 DC862 3021970 WP WINDOW NR 27L CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 FUSELAGE CUT-OUT FOR WINDOW NR 27L, INTERIOR SKIN CORRODED. REPLACED WINDOW FRAME IAW SRM 51-1-20D. 2 L 7 4 4F 4A25 1996053000272 19960530 00272 WP 1996 5 30 96ZZZX2739 1 19960426 G 5313 LONGERON DOUG DC8 DC862 3021970 WP FS 1380 LON L32L CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 LOWER AFT FUSELAGE COMPARTMENT, FS 1380, LONGERON L32L, HAS CORROSION. INSTALLED NEW SECTION OF LONGERON AND SPLICED IA W SRM 53-2-2. 2 L 7 4 4F 4A25 1996053000273 19960530 00273 WP 1996 5 30 96ZZZX2740 1 19960426 G 5320 FILLER DOUG DC8 DC862 3021970 WP FS 1500 LT DOOR CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK IN CABIN, FOUND UPPER SURFACE OF THE LT CUSP EXTENSION AREA, FS 1500, LT, SERVICE DOOR AFT LOWER CORNER I NSIDE SCUFF PLATE, HAS CORROSION BELOW. FILLER FOUND BEYOND LIMITS, FABRICATED NEW FILLER AND INSTALLED FILLER AND SCUF F PLATE IAW SRM'S 51-3-0, 51-1-8, 53-2-0, 51-1-0. 2 L 7 4 4F 4A25 1996053000274 19960530 00274 WP 1996 5 30 96ZZZX2741 1 19960426 G 5320 ANGLE DOUG DC8 DC862 3021970 WP FS 1568 RBL 16 CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND AFT LAVATORY AREA AT FS 1568, RBL 16 TO RBL 34, HAS CORRODED ANGLE. REMOVED DAMAGED ANGLE. FABRI CATED NEW ONE IAW SRM 53-2-0 PER ORIGINAL. INSTALLED IAW SRM 51-3-0. 2 L 7 4 4F 4A25 1996053000275 19960530 00275 CE 1996 5 30 96ZZZX2742 1 19960507 G 3310 10836401111 DIMMER CONTROL BEECH 23 C23 1151242 CE INST PANEL MISWIRED G A K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 03 3841T M2307 REPLACEMENT BEECH SUNDOWNER INSTRUMENT LIGHT DIMMER CONTROL WAS FOUND MISWIRED AS SHIPPED FROM BEECHCRAFT. BEECHCRAFT F OUND ALL IN STOCK MISWIRED AND CORRECTED PROBLEM. REPAIR FACILITIES WITH PN 108-364011-11 IN STOCK SHOULD COORDINATE WI TH BEECHCRAFT TO DETERMINE WIRING STATUS OF THE PARTS. 1 L 7 1 3O A1CE 1996053000276 19960530 00276 CE 1996 5 30 96ZZZX2743 1 19960228 G 5540 3364000045 ARM ASSY BEECH 33 F33A 1151425 CE UPPER RUD HINGE MISMANUFACTURED B S BKHR K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 01 17RE 1056 CE1128 WHEN INSTALLING UPPER HINGE PER STC, FOUND WHEN NEW HINGE INSTALLED, RUDDER UPPER MOUNT WOULD NOT LINE UP STRAIGHT. VIS UAL INSPECTION OF ARM REVEALED BEARING BOSS IN ARM DRILLED OFF CENTER CAUSING THIS PROBLEM ALONG WITH RUDDER CHAFING ON VERTICAL STABILIZER SKIN WHEN RUDDER AT EXTREME RIGHT TRAVEL. PART CAME FROM FACTORY LIKE THIS. REPLACED ARM WITH NEW WITH NO DISCREPANCIES NOTED. 1 L 7 1 3O 3A15 1996053000277 19960530 00277 CE 1996 5 30 96ZZZX2744 1 19960308 G 2810 1013890113 CHECK VALVE AIRBORNE 1D212 BEECH 200 200BEECH 1152920 CE AUX XFER PUMP LEAKING D A K NONE K FLUID LOSS IN INSP/MAINT 1 GL 13 26G 8417 BB787 AIRCRAFT HAS FUEL ODOR IN CABIN. INSPECTED AND FOUND FUEL SEEPING INTO CABIN THROUGH FUEL PROBE WIRING CONDUIT. FOUND FUEL TANKS FILLED IN VERY COLD CONDITIONS AND THEN PLACED IN WARM HANGAR. FOUND CHECK VALVE WITH SOME DIRT IN IT CAUSIN G THE FUEL EXPANSION TO FORCE ITS WAY OUT FUEL CELL ACCESS PANEL INSTEAD OF OUTBOARD VENT. 1 L 7 2 4T A24CE 1996053000278 19960530 00278 SO 1996 5 30 96ZZZX2745 1 19960426 G 3230 402960 BOLT PIPER PA28 PA28R200 7102811 SO BRACE LINK DEFECTIVE B L AMYR K NONE W INADEQUATE Q C IN INSP/MAINT 1 CE 05 2981R 1343 28R35370 DURING INSPECTION REPLACEMENT OF MLG BRACE LINK ROD END BOLT TO TRUNNION HOUSING, FOUND OLD STYLE CLEVIS HEAD BOLT, PN 4 00-810, INSTALLED. IF REPLACEMENT WITH NEW STYLE HEX HEAD BOLT, PN 3772202, IS DONE, THE GEAR DOOR RETRACT ROD WILL NOT CLEAR BOLT HEAD DURING RETRACTION/EXTENSION. 1 L 7 1 3O 2A13 1996053000279 19960530 00279 SO 1996 5 30 96ZZZX2746 1 19960310 G 5741 9010443 SHOULDER BOLT GULSTM AA5 AA5A 3960106 SO INBD WING ATTACH MISMANUFACTURED B A NZBR K NONE W INADEQUATE Q C IN INSP/MAINT 1 AL 05 26655 3162 AA5A0623 DURING C/W AD 95-19-15, ONE OF THE FOUR INBOARD WING ATTACH BOLTS WAS FOUND TO HAVE BEEN INCORRECTLY MANUFACTURED, WITH AN AREA OF THE THREADED SHANK MISSING, AND AN AREA OF THE HEX HEAD MIS-MACHINED. 1 L 7 1 3O A16EA 1996053000280 19960530 00280 SO 1996 5 30 96ZZZX2747 1 19960429 G 2140 88D934 COMBUSTION TUB JANITROL 90D381 PIPER PA34 PA34200T 7103406 SO HEATER CRACKED B S APCR K NONE O OTHER IN INSP/MAINT 1 NM 01 666HL 8771387 347770235 HEATER FAILED PDT REQUIREMENT OF AD 82-07-3. SUBSEQUENT VISUAL INSPECTION SHOWED LARGE CRACK IN COMBUSTION TUBE 2.50 IN CHES FROM EXHAUST END. 1 L 7 2 3O A7SO 1996053000291 19960530 00291 CE 1996 5 30 96ZZZX2757 1 19960513 G 3211 24411001 PIVOT CESSNA 172 172RG 2072438 CE RT MLG CRACKED D S K NONE O K OTHER FLUID LOSS IN INSP/MAINT 1 NM 01 5252V 4993 172RG0485 PIVOT CRACKED NEARLY THE ENTIRE CIRCUMFERENCE IN THE RADIUS UNDER PN 2241111-2 INNER RACE. IT IS NOT KNOWN IF A HARD LA NDING OCCURRED. PART HAD SOME AREAS OF INTERGRANULAR CORROSION AND IS IN THE EXHAUST STREAM. NO EVIDENCE OF CORROSION IN AREA OF CRACK. CRACK WAS DISCOVERED DUE TO SPONGY RT BRAKE AND 5606 FLUID LEAK INTO RACK AND PINION CHAMBER OF ASSOC IATED HYDRAULIC ACTUATOR. 1 H 7 1 3O 3A17 1996053000292 19960530 00292 CE 1996 5 30 96ZZZX2758 1 19960509 G 2730 53608014 BELLCRANK CESSNA 340 340A 2076405 CE ELEV FS 360.2 BEARING FAILED B A JBER K NONE O OTHER IN INSP/MAINT 1 SW 01 6829K 340A1233 DURING ANNUAL INSPECTION, FOUND EXCESSIVE SIDE-PLAY IN ELEVATOR BELLCRANK ASSY, FURTHER INVESTIGATION FOUND BEARING AT F AULT. REMOVAL OF BELLCRANK REVEALED BENT BOLT WHICH ADDED DIFFICULTY IN REMOVING ASSY. SUSPECT CAUSE COULD BE NOT USIN G ELEVATOR CONTROL LOCK IN WINDY CONDITIONS. 1 L 7 2 3O 3A25 1996053000293 19960530 00293 GL 1996 5 30 96ZZZX2759 3 19960417 G 6110 PROPELLER CESSNA 150 152 2071835 CE MCAULY 1A103 1A103TCM GL HUB AREA CRACKED D S K NONE O OTHER IN INSP/MAINT 1 CE 05 6359M 4994 15284693 776529 WHILE C/W AD 95-21-01 AND SB 219, THE PROPELLER WAS FOUND CRACKED PAST THE ACCEPTABLE LIMITS. THIS PROPELLER HAS NO HIS TORY OF DAMAGE. PROPELLER WAS REMOVED FROM SERVICE. 1 H 7 1 3O NT 3A19 5 N P50GL 1996053000294 19960530 00294 CE 1996 5 30 96ZZZX2760 1 19960419 G 3221 24130023 CASTING CESSNA 172 172RG 2072438 CE NLG STRUT ANCHOR CRACKED D K NONE O OTHER IN INSP/MAINT 1 WP 07 9516B 5150 172RG0847 DURING A 100-HOUR INSPECTION WHILE CHECKING THE BELLY SKIN AFT OF THE NOSE GEAR, NOTICED BLACK STAINING FROM THE 6 SCREW S THAT ARE ON THE LOWER EDGE OF CASTING. REMOVED SCREWS AND FOUND ALL MOUNTING HOLES OF SKIN NR 2413000-5 ELONGATED. I NSPECTED CASTING WITH A MIRROR AND FOUND A CRACK EXTENDING FROM THE LEFT INBOARD SCREW HOLE FORWARD TO EDGE OF CASTING. SUSPECT CRACKING AND ELONGATIONS DUE TO SCREW LOOSENING DUE TO VIBRATIONS. SUBMITTER RECOMMENDS KEEPING CASTING AREA C LEAN, CHECK SCREW TORQUE, VISUAL INSPECTION OF CASTING, POSSIBLE DYE CHECKS AT 500-HOUR INTERVALS. SUBMITTER STATED THI S IS THE 2ND AIRCRAFT FOUND WITH THIS CRACK. 1 H 7 1 3O 3A17 1996053000295 19960530 00295 SO 1996 5 30 96ZZZX2761 1 19960505 G 5610 549015 WINDOW PIPER PA31T PA31T1 7103126 SO COPILOT RT SIDE DEPARTED D A UNSCHED LANDING D INFLIGHT SEPARATION CR CRUISE 1 NM 05 121BE 31T18004036 PILOT REPORTED AT ALTITUDE OF 27,000 FEET, THE RIGHT SIDE COCKPIT SIDE WINDOW BLEW OUT. PILOT FURTHER REPORTED THAT UP TO THIS TIME, ALL SYSTEMS WERE NORMAL WITH NO INDICATION OF TROUBLE. PILOT RETURNED TO AIRFIELD WITHOUT FURTHER INCIDEN T. CAUSE UNKNOWN FOR WINDOW FAILURE. AIRCRAFT TT, 1,916.2 HOURS. 1 L 7 2 3T A8EA 1996053000296 19960530 00296 SO 1996 5 30 96ZZZX2762 2 19960513 G 7414 104001664 IMPULSE COUPLER BENDIX S6RN25 PIPER PA34 PA34200T 7103406 SO CONT O360 TSIO360EB 17025 SO MAGNETO CAM SPLIT B APCR K NONE O OTHER IN INSP/MAINT 1 NM 01 5384F 1751 V149214DR 347770013 MAGNETO IMPULSE COUPLER CAM SPLIT IN HALF DURING RE-INSTALLATION ON MAGNETO DURING MAGNETO 500-HOUR INSPECTION AND IMPUL SE COUPLER AD 78-09-07R3. 1 L 7 2 3O 3 O A7SO E9CE 1996053000297 19960530 00297 SO 1996 5 30 96ZZZX2763 2 19960405 G 7322 T194593 ACCELERATOR PRECISION 048941 CESSNA 150 150L 2071826 CE CONT O200 O200A 17020 SO CARBURETOR WORN D O OTHER Y ENGINE STOPPAGE NR NOT REPORTED 1 NM 01 19396 2878 649 BE2421667 15074391 254532A48 ACCELERATOR PUMP WORN AND CHECK VALVE LEAKING CAUSING CARBURETOR TO BE EXCESSIVELY RICH RESULTING IN ENGINE FAILURE. LA ST OVERHAUL DATE, 5-6-82. 1 H 7 1 3O 3 O 3A19 E252 1996053000298 19960530 00298 SO 1996 5 30 96ZZZX2764 2 19960501 G 7322 194593 ACCELERATOR PUMP FACET MA5PA CESSNA 150 150M 2071830 CE CONT O200 O200A 17020 SO CARBURETOR PLUNGER RUSTED G A UNSCHED LANDING Y ENGINE STOPPAGE NR NOT REPORTED 1 NM 01 3936V 2297 2422161 15076658 251114A48 ENGINE QUIT CAUSING FORCED LANDING. INVESTIGATION REVEALED PLUNGER RUSTED AND CHECK VALVE WITH BROKEN SPRING INTERNALLY . ACCELERATOR PUMP WAS INOPERABLE AND ENGINE RAN EXCESSIVELY RICH. CARBURETOR LAST OVERHAULED, 8-5-76. SUBMITTER RECO MMENDS CARBURETORS BE REQUIRED TO BE OVERHAULED AT TIMES RECOMMENDED BY PRECISION AIRMOTIVE BULLETIN NR MSA-3. SOME TBO RECOMMENDED ON INSTALLED ENGINE OR 10 YEARS SINCE PLACED IN SERVICE OR LAST OVERHAUL. 1 H 7 1 3O 3 O 3A19 E252 1996053000299 19960530 00299 SO 1996 5 30 96ZZZX2765 2 19960504 G 8530 PISTON PIN CESSNA 337 337C 2075712 CE CONT O360 IO360C 17025 SO NR 2 CYLINDER FAILED D O OTHER E R K VIBRATION/BUFFET PARTIAL RPM/PWR LOSS FLUID LOSS CR CRUISE 1 AL 03 2615S 312 3370915 501398C IT APPEARS THE PISTON PIN BROKE AND THE PISTON HIT THE CRANKSHAFT COUNTERWEIGHT WHICH BROKE A LARGE HOLE IN THE TOP OF T HE CRANKCASE. THE AIRCRAFT WAS ON A CROSS-COUNTRY FLIGHT AT NORMAL CRUISE. WHEN THE VIBRATION STARTED, THE PILOT REDUC ED POWER, BUT THE VIBRATION CONTINUED SO THE PROPELLER WAS FEATHERED AND FLIGHT CONTINUED WITH REAR ENGINE OPERATING. 1 H 7 2 3O 3 O A6CE E1CE 1996053000300 19960530 00300 SO 1996 5 30 96ZZZX2766 2 19960507 G 8540 539800 SPRING CLUTCH CESSNA 414 414A 2075907 CE CONT O520 TSIO520NB 17040 SO RT START ADAPTER FAILED D K NONE O OTHER IN INSP/MAINT 1 GL 13 4677N 26 414A0068 290873R TWENTY-SIX HOURS AFTER INSTALLING A TCM OVERHAULED ENGINE, STARTER ADAPTER FAILED. INSPECTION SHOWED THAT SPRING CLUTCH FAILED AND WAS UNCOILING INTO ENGINE ACC CASE. 1 L 7 2 3O 3 O A7CE E8CE 1996053000301 19960530 00301 CE 1996 5 30 96ZZZX2767 1 19960425 G 2434 C6FF10335B ROTOR ASSY CESSNA 182 R182 2072734 CE ALTERNATOR SHAFT SHEARED D K NONE O OTHER IN INSP/MAINT 1 EA 07 5545T 1310 R18201894 C/W REMOVAL OF ALTERNATOR FOR 500-HOUR INSPECTION. UPON DISASSEMBLY, ROTOR SHAFT SHEARED OFF IN AREA OF NUT (PULLEY RET AINING) THREADS. EVIDENCE OF CRACK BEING VERY OLD EXISTS. MATERIAL CORRODED IN AREA OF CRACK (SHEAR AREA). 1 H 7 1 3O RT 3A13 1996053000303 19960530 00303 CE 1996 5 30 96ZZZX2769 1 19960510 G 3242 C306152 BRAKE DISC CESSNA 180 180K 2072624 CE LT MLG FAILED D C D ABORTED TAKEOFF RETURN TO BLOCK O OTHER TO TAKEOFF 1 SW 11 24SL 3758 18053187 UPON STARING TAKEOFF ROLL, LOUD NOISE AND LEFT BRAKE MALFUNCTION OCCURRED. TAKEOFF ABORTED. LEFT MAIN BRAKE DISC HAD B ROKEN LOOSE FROM MAIN WHEEL BOLTS. SUSPECT CAUSE WAS CRACKS IN DISC. SUBMITTER RECOMMENDS INSPECTION OF DISC FOR CRACK S. 1 H 7 1 3O 5A6 1996053000304 19960530 00304 CE 1996 5 30 96ZZZX2770 1 19960401 G 3231 0024100381 SHAFT ASSY BEECH 58 58P 1152744 CE NLG DR ACTUATOR FAILED D O OTHER O OTHER CL CLIMB 1 NE 05 6648K TJ204 PILOT NOTICED ODD NOISE DURING GEAR RETRACTION AND SUBSEQUENT EXTENSION. INSPECTION ON GROUND REVEALED PART OF SHAFT AS SY THAT CLOSES GEAR DOORS BROKEN ALLOWING DOORS TO FLAP IN FLIGHT. SUBMITTER SUSPECTS NOISE HEARD BY PILOT WAS NOSE GEA R FORCING ITS WAY THROUGH DOORS HELD CLOSED BY AIR PRESSURE AS AIRCRAFT WAS FLYING. 1 L 7 2 3O A23CE 1996053000305 19960530 00305 CE 1996 5 30 96ZZZX2771 1 19960401 G 8120 641284 COUPLING BEECH 58 58P 1152744 CE CONT O520 TSIO520L 17040 SO TURBO EXHAUST CRACKED D K NONE O OTHER IN INSP/MAINT 1 NE 05 4269S TJ96 237270R CLAMP WAS FOUND CRACKED WHEN REMOVED FOR OTHER MAINTENANCE ON THE EXHAUST SYSTEM. SUBMITTER SUSPECTS CLAMP WAS OVERTORQ UED AT PRIOR INSTALLATION. FAILURE OF THIS CLAMP COULD ALLOW HOT EXHAUST GASES TO BE RELEASED IN THE ENGINE COMPARTMENT . SUBMITTER RECOMMENDS CLOSE INSPECTION OF ALL V-BAND STYLE CLAMPS DURING SCHEDULED MAINTENANCE INSPECTION. DEFECT WOU LD BE DETECTABLE WITHOUT REMOVAL. 1 L 7 2 3O 3 O A23CE E8CE 1996053000306 19960530 00306 CE 1996 5 30 96ZZZX2772 1 19960228 G 7602 S17771 MIXTURE CONTROL CESSNA 150 150 2071802 CE SHROUD BROKEN H A UNSCHED LANDING R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 CE 07 45166 15076764 PILOT HAD TO MAKE EMERGENCY LANDING AND WAS BARELY ABLE TO MAKE IT DUE TO ENGINE BARELY RUNNING AND INTERMITTENTLY QUITT ING ENTIRELY. INSPECTION FOUND MIXTURE CONTROL WIRE BROKEN WHERE IT EXITS CONTROL SHROUD TO ATTACH TO MIXTURE. CAUSE W AS FROM NORMAL WEAR AND FATIGUE. SUBMITTER SUGGESTS CLOSER INSPECTION OF ACTUAL CONTROL WIRE FOR WEAR AGAINST SHROUD AT REGULAR MAINTENANCE INTERVALS. 1 H 7 1 3O NT 3A19 1996053000307 19960530 00307 CE 1996 5 30 96ZZZX2773 1 19960507 G 7160 AM107635FP AIR FILTER AIRMAZE CESSNA 177 177RG 2073709 CE ENG INDUCTION MOUNT FAILED D K NONE O OTHER IN INSP/MAINT 1 SO 19 52908 196 177RG1306 DURING ROUTINE OIL CHANGE, OBSERVED AIR INDUCTION FILTER 'LAYING' IN ENGINE BAFFLE. UPON FURTHER INVETSIGATION, FOUND B OTH MOUNTING BRACKETS HAD BROKEN/SHEARED FROM THE INDUCTION FILTER BODY. SUSPECT CAUSE, INADEQUATE METHOD OF ATTACHMENT OF BRACKETS TO FILTER BODY/ASSY. SUBMITTER STATED METHOD OF ATTACHMENT APPEARS TO BE 'SPOT WELDS'. PERHAPS RIVETING O F THE BRACKETS TO THE FILTER ASSY MAY BE MORE SUITABLE. 1 H 7 1 3O A20CE 1996060600121 19960606 00121 CE 1996 6 6 96ZZZX2774 1 19960513 G 5551 12121271 DOUBLER CESSNA 210 T210N 2073456 CE H STAB ATTACH RIVETS DEFECTIVE D K NONE O OTHER IN INSP/MAINT 1 WP 07 7353C 1825 21063943 TOP RIVET ABOVE PLATE. NUT POPPED ON RIGHT SIDE AND WORKING ON LEFTSIDE. RECOMMEND PERIODIC INSPECTION. 1 H 7 1 3O 3A21 1996060600122 19960606 00122 CE 1996 6 6 96ZZZX2775 1 19960513 G 5551 12121273 DOUBLER CESSNA 210 T210N 2073456 CE H STAB ATTACH RIVETS DEFECTIVE D K NONE O OTHER IN INSP/MAINT 1 WP 07 7353C 1825 21063943 TOP RIVET ABOVE PLATE. NUT POPPED ON RIGHT SIDE AND WORKING ON LEFTSIDE. RECOMMEND PERIODIC INSPECTION. 1 H 7 1 3O 3A21 1996060600128 19960606 00128 CE 1996 6 6 96ZZZX2781 1 19960501 G 3240 0301890 BRAKE ASSY CESSNA 500 550 2076604 CE MLG RT WRONG DISK D O OTHER O OTHER LD LANDING 1 NM 09 533MA 1154 5500078 INSTALLED STC SA 4954NM, CLEVELAND WHEELS AND BRAKES. AFTER 1 LANDING, THE BRAKES ALMOST LOCKED UP. BOTH BRAKES: AFTE R INSPECTION, FOUND DISKS FROZEN IN WHEELS. THE DISKS WERE FOUND TO BE THE WRONG TYPE TO BE INSTALLED. BOTH BRAKES WER E NEW AND ASSEMBLED AT FACTORY. THE P/N 159-03500 DISK WAS SUPPOSED TO BE INSTALLED. REPLACING BOTH WHEEL AND BRAKE ASS YS WITH REPLACEMENT COMPONENTS. LANDINGS, 1. 1 L 7 2 4F A22CE 1996060600129 19960606 00129 CE 1996 6 6 96ZZZX2782 1 19960501 G 3240 0301890 BRAKE ASSY CESSNA 500 550 2076604 CE MLG RT WRONG DISK D O OTHER O OTHER LD LANDING 1 NM 09 533MA 1155 5500078 INSTALLED STC SA 4954NM, CLEVELAND WHEELS AND BRAKES. AFTER 1 LANDING, THE BRAKES ALMOST LOCKED UP. BOTH BRAKES: AFTE R INSPECTION, FOUND DISKS FROZEN IN WHEELS. THE DISKS WERE FOUND TO BE THE WRONG TYPE TO BE INSTALLED. BOTH BRAKES WER E NEW AND ASSEMBLED AT FACTORY. THE P/N 159-03500 DISK WAS SUPPOSED TO BE INSTALLED. REPLACING BOTH WHEEL AND BRAKE ASS YS WITH REPLACEMENT COMPONENTS. LANDINGS, 1. 1 L 7 2 4F A22CE 1996060600130 19960606 00130 SW 1996 6 6 96ZZZX2784 1 19960501 G 3230 MS17152B ROLL PIN GULSTM 690TP 690A 0141722 SW GEAR HANDLE SHEARED B A R2JR O OTHER J WARNING INDICATION CL CLIMB 1 EA 21 53RF 9980 11153 IN-FLIGHT, AFTER LANDING GEAR FAILED TO RETRACT PROPERLY, LANDING GEAR SELECTED DOWN AND FAILED TO EXTEND. NO LANDING G EAR EXTENSION OCCURRED UNTIL UPHOLSTERY WAS REMOVED AND LANDING GEAR CONTROL VALVE MANUALLY MOVED TO EXTEND LANDING GEAR . SAFE LANDING MADE. MAINTENANCE FOUND ROLL PIN SHEARED IN HANDLE MECHANISM. NO PARTS BREAK DOWN IN IPC. FACTORY PRO VIDED PART NUMBER FOR PIN. SUGGEST TIME CHANGE OF THIS PART AND AFM SUPPLEMENT INSTRUCTING CREW HOW TO GAIN ACCESS AND MANUALLY MOVE LANDING GEAR CONTROL VALVE IN CASE OF HANDLE FAILURE. VERY DANGEROUS SITUATION. 1 H 7 2 3T 2A4 1996060600131 19960606 00131 CE 1996 6 6 96ZZZX2785 1 19960422 G 2810 MS29513338 O-RING CESSNA 206 U206G 2073356 CE FUEL CAP DEFECTIVE B L UKJR K NONE W INADEQUATE Q C IN INSP/MAINT 1 EA 23 9814G 2 U20603831 OWNER COMPLAINT FOR FUEL CAP O-RINGS BEING TOO LARGE. INVESTIGATION REVEALED RINGS .25 INCH IN DIAMETER TOO LARGE. O-R INGS HAD BEEN INSTALLED ABOUT 30 DAYS, 1.5 HOURS TT. INSTALLED NEW O-RINGS. INSPECTED ACFT 3 WEEKS LATER AND FOUND SAM E CONDITION. INSPECTED O-RINGS REMOVED EARLIER, FOUND THEY HAD SHRUNK BACK TO ORIGINAL SIZE. REMOVED ALL O-RINGS FROM STOCK (SAME BATCH NR) AND RETURNED TO VENDOR. 1 H 7 1 3O A4CE 1996060600132 19960606 00132 EA 1996 6 6 96ZZZX2786 2 19960423 G 7414 67542 BEARING PIPER PA31 PA31310 7103103 SO LYC O540 TIO540A2B 41532 EA MAG DRIVE MISINSTALLED D L A UNSCHED LANDING Y W ENGINE STOPPAGE INADEQUATE Q C CR CRUISE 1 SO 16 107FC 31612 L807761 WHILE IN LEVEL FLIGHT, THE RIGHT ENGINE QUIT WITHOUT WARNING. UPON INVESTIGATION, DETERMINED THE DRIVE DOWEL PIN (STD-1 065) HAD BEEN SHEARED, AND THE LEFT IDLER GEAR (71668) HAD LOST A TOOTH AND JAMMED THE MAGNETO DRIVE GEAR (GEAR RETAINER ASSY LW-19102 OR LW 19096). WHEN THE LEFT MAGNETO (S6LN-1208) WAS REMOVED, THE MAGNETO HAD A BURNED APPEARANCE. UPON D ISASSEMBLY, FOUND THE ROTOR HAD CONTACTED THE POLE SHOES IN THE HOUSING. AFTER SENDING THE MAGNETO TO THE BENDIX FACTOR Y, DISCOVERED THE DRIVE GEAR HAD A SIDE LOAD PLACED ON IT CAUSING THIS TO OCCUR. 1 L 7 1 3O 3 O RT A20SO E14EA 1996060600133 19960606 00133 CE 1996 6 6 96ZZZX2787 1 19960105 G 5312 121340711 BULKHEAD CESSNA 206 U206F 2073333 CE LT-RT DOORPOST CRACKED D A K NONE O OTHER IN INSP/MAINT 1 SW 01 1372V 5231 U20602588 DURING ROUTINE ANNUAL INSP, DISCOVERED FWD CABIN DOORPOST BULKHEAD CRACKED ON LT AND RT SIDES AT WING LIFT STRUT ATTACH FITTINGS. INSP WAS DONE IAW CESSNA SEB 93-5 R1. PREVIOUS INSP OF THIS AREA DURING ANNUAL AND WHEN C/W CESSNA SEB 93-5, FAILED TO FIND THIS DAMAGE. DAMAGE WAS ONLY VISIBLE BY REMOVING LT AND RT UPHOLSTERY SIDE PANELS, CARPETING, AND DIRT THAT BLOCKED THE VIEWING AREA FROM DIRECTLY ABOVE CRACKS. FURTHER INSP REVEALED DAMAGE TO SUPPORTING STRUCTURE OF BULKH EAD ON RT SIDE. REPAIRED CRACKS BY MODIFYING LT AND RT AREAS OF BULKHEAD IAW CESSNA SEB 93-5 R1 BY INSTALLING SERVICE K IT SK 206-42C. DAMAGED SUPPORTING STRUCTURE REPLACED (ANGLE PN 1213408-3 AND DOUBLER PN 1213806-2 (RT SIDE). 1 H 7 1 3O A4CE 1996060600134 19960606 00134 CE 1996 6 6 96ZZZX2788 1 19960509 G 3211 0541153 U-BOLT CESSNA 182 182A 2072704 CE RT MAIN GEAR SHEARED D K NONE O OTHER IN INSP/MAINT 1 NE 03 6191B 34191 DURING ROUTINE INSPECTION, RT MAIN LANDING GEAR U-BOLT WAS FOUND SHEARED AT AFT END. THIS MAY BE DUE TO PARACHUTISTS ST ANDING ON RT MAIN GEAR PRIOR TO DEPARTURE FROM AIRCRAFT. 1 H 7 1 3O NT 3A13 1996060600135 19960606 00135 GL 1996 6 6 96ZZZX2789 1 19960401 G 6720 28163511 CONTROL CABLE ENSTRM F28 F28F 3300412 GL T/R FRAYED D K NONE O OTHER IN INSP/MAINT 1 EA 17 8627J 1200 760 INFORMATION APPLICABLE TO MODELS, F28C, F28C-2 F28-F, 280F, 280FX. INSPECTION FOUND TAIL ROTOR CABLES FRAYED WHERE THEY PASS OVER THE AFT ALIGNMENT PULLEYS IN THE TAIL CONE. PULLEYS WERE LUBED, FREE AND TURNING. SUSPECT VIBRATION WAS CAU SING CABLES TO RATTLE IN PULLEY AND GUIDE, FATIGUING THE CABLE. SUBMITTER RECOMMENDS CAREFUL INSPECTION OF CABLES IN TH IS AREA AT 100-HOUR INSPECTION OR ANNUAL. 1 G 7 1 3O H1CE 1996060600163 19960606 00163 GL 1996 6 6 96ZZZX2796 1 19960408 G 8120 28125523 WASTEGATE ENSTRM F28 F28F 3300412 GL BUTTERFLY FAILED C PP0M K NONE O OTHER IN INSP/MAINT 1 WP 01 8624G 1100 745 BUTTERFLY IN WASTEGATE WARPED AND LOSE FROM CRACKED WELDS JAMMING THROTTLE. BUTTERFLY SHAFT WORN AT PIVOT POINTS ALSO C AUSING THROTTLE BINDING. SUBMITTER STATES COMMON TO ALL F28F AND F280FX MODELS. REQUIRES REPLACEMENT OF WASTEGATE. 1 G 7 1 3O H1CE 1996060600166 19960606 00166 NE 1996 6 6 96ZZZX2799 2 19960301 G 7310 9550147560 ELECTROVALVE AEROSP SA365 SA365N1 8680668 EU TMECA ARRIEL ARRIEL1C 60030 NE NR 2 ENG START FAILED B KY1R K NONE O OTHER IN INSP/MAINT 1 EA 07 92MD 2906 3521 6311 5094 NR 2 ENGINE WOULD NOT HAVE T4 CLIMB UNTIL NG SHOWED 30 PERCENT, THEN RAPID RISE ONCE IGNITION OCCURRED. REPLACED START FUEL ELECTROVALVE. 1 G 7 2 3U 3 U H10EU E19EU 1996060600167 19960606 00167 1996 6 6 96ZZZX2800 4 19960302 G 2210 41800562312 DUPLEX ACTUATOR AEROSP SA365 SA365N1 8680668 EU AUTOFLT FAULTY B KY1R K NONE O OTHER IN INSP/MAINT 1 EA 07 92MD 379 6311 PITCH CHANNEL DISENGAGEMENT AND PITCH C5 FAULT. 1 G 7 2 3U H10EU 1996060600168 19960606 00168 1996 6 6 96ZZZX2801 4 19960229 G 2210 41800562312 DUPLEX ACTUATOR AEROSP SA365 SA365N1 8680668 EU AUTOFLIGHT FAILED B KY1R K NONE O OTHER IN INSP/MAINT 1 EA 07 97MD 413 6330 FAILED INSULATION TEST LOW MEG CHECK. 1 G 7 2 3U H10EU 1996060600861 19960606 00861 1996 6 6 96ZZZX2854 1 19960506 G 3520 417T42631 MASK BOEING 417T4202 PULL STREAMER DEFECTIVE B A GUMR K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 19 PULL STREAMERS FOR ACTIVATING PASSENGER OXYGEN SYSTEMS FAILED THE PULL TEST. INSPECTION OF ALL STREAMERS IN STOCK RESUL TED IN IDENTIFYING APPROXIMATELY 20 PERCENT DEFECTIVE, I.E., BAD CRIMPS, CRIMPS SLIPPING AND FRAYED STRINGS. BOEING AIR CRAFT HAS BEEN NOTIFIED AND IS INVESTIGATING THE PROBLEM. NOTE: THE DEFECTIVE STREAMERS WERE FOUND PRIOR TO BEING INST ALLED IN AN AIRCRAFT. 1996060600862 19960606 00862 CE 1996 6 6 96ZZZX2855 1 19960508 G 3252 22430211 EYE BOLT CESSNA 182 R182 2072734 CE SHIMMY DAMPENER FAILED D S O OTHER O OTHER LD LANDING 1 NE 03 6319T R18201977 SHIMMY DAMPENER EYE BOLT FAILED ON ROLL-OUT ON NORMAL LANDING. NO ACCIDENT RESULTED. 1 H 7 1 3O RT 3A13 1996060600863 19960606 00863 EA 1996 6 6 96ZZZX2856 2 19960514 G 8530 SL17236M294Z VALVE CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA CYL INTAKE PITTED D S K NONE O OTHER IN INSP/MAINT 1 WP 19 5120H 287 15284063 L2052015 EDGE OF INTAKE VALVE APPEARS TO BE BREAKING OFF. EDGE IS ALSO CRACKED IN SEVERAL PLACES. VALVE FACE HAS PITTING ON ENT IRE SEALING SURFACE. METAL ON VALVE APPEARS TO HAVE CONTAMINATES UPON INVESTIGATION WITH 30X MAGNIFIER. 1 H 7 1 3O 3 O NT 3A19 E223 1996060600864 19960606 00864 EA 1996 6 6 96ZZZX2857 2 19960514 G 8520 SL72877 TAPPET PIPER PA28 PA28140 7102802 SO LYC O320 O320E2A 41508 EA CAMSHAFT SPALLED D L K NONE O OTHER IN INSP/MAINT 1 SO 09 1630J 113 2824017 L2022427A ENGINE DISASSEMBLED. CAMSHAFT LOBE AND HYDRAULIC BODY TAPPET FURNISHED BY SUPERIOR AIR PARTS WERE REMOVED. THE CAM LOB E WAS WORN BELOW TOLERANCE, THE HYD BODY WAS BADLY PITTED. THE CAMSHAFT AND BODY HAD BEEN INSTALLED ABOUT 30 MONTHS AGO AND HAD A TOTAL OF 113 HRS SINCE NEW. SUBMITTER STATED THE BODY WAS PITTED FROM THE BODY NOT BEING UP TO SPECS. 1 L 7 1 3O 3 O 2A13 E274 1996060600867 19960606 00867 EU 1996 6 6 96ZZZX2860 1 19960501 G 3230 AIR134702 DRAG BRACE LINK SAAB 2000 2000SAAB 7860200 EU LT MLG BEARING SHIFT D K NONE O OTHER IN INSP/MAINT 1 GL 23 5125 2000030 DURING A POST-FLIGHT INSPECTION, THE UPPER BEARING IN THE LINK ASSY HAD SHIFTED APPROXIMTAELY .050 INCH. REPLACED DRAG BRACE LINK AND PERFORMED A GEAR SWING. ACFT TT: 1,647 HRS. LANDINGS, 196. REF: OPERATOR CONTROL NR 96-002. 2 L 7 2 4T RT A47NM 1996060600868 19960606 00868 EU 1996 6 6 96ZZZX2861 1 19960212 G 3230 AIR843683 DRAG BRACE SAAB 2000 2000SAAB 7860200 EU LT MLG BEARING DEFECT B GMCR O OTHER P NO WARNING INDICATION AP APPROACH 1 GL 23 5124 OZ9560042 200027 WHEN THE GEAR WAS SELECTED DOWN, THE CREW DID NOT HAVE A GREEN INDICATION ON THE LEFT GEAR. CYCLED GEAR, NO HELP, THEN PERFORMED AN EMERGENCY EXTENSION. THE AIRCRAFT LANDED SAFELY AND WAS TOWED TO THE HANGAR. THE LOWER DRAG BRACE BEARING HAD SHIFTED IN THE CASTING. REF: OPERATOR CONTROL NR 96-001. 2 L 7 2 4T RT A47NM 1996060600870 19960606 00870 EU 1996 6 6 96ZZZX2864 1 19960229 G 5302 355A2305000507 SKIN AEROSP AS355 AS355N EU TAILBOOM CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 25 54HG 376 5567 FOUND 2 INCH SKIN CRACK FORWARD OF HORIZONTAL STABILIZER. CRACK THROUGH AFT RIVET ATTACHING STRAKE ON RIGHT SIDE OF TAI LBOOM. 1 G 7 2 3U H11GU 1996060600871 19960606 00871 CE 1996 6 6 96ZZZX2865 1 19960514 G 7603 5038901229 CONTROL CABLE BEECH 58 58 1152740 CE ENG THROTTLE BROKEN D K NONE O OTHER IN INSP/MAINT 1 SO 15 329H TH219 THROTTLE CABLE BROKE BETWEEN CLAMP AND THROTTLE ARM. AIRCRAFT TT, 5,931 HOURS. CABLE WAS PREVIOUSLY REPLACED AT AIRCRA FT TT, 5,638.2 HOURS. CABLE TIME IS SERVICE SINCE NEW WAS 293 HOURS. 1 L 7 2 3O 3A16 1996060600872 19960606 00872 SO 1996 6 6 96ZZZX2866 1 19960515 G 2810 493063 DRAIN VALVE PIPER PA24 PA24260 7102406 SO FUEL SYSTEM FAULTY D K NONE O OTHER IN INSP/MAINT 1 NE 01 8632P 244074 THE FUEL DRAIN VALVE WOULD NOT OPERATE, THE PROBLEM WAS THE VALVE ITSELF, BUT WAS NOT EVIDENT UNTIL THE OVERBOARD HOSE B ECAME STIFF FROM AGE AND TEMPERATURE. WHILE INVESTIGATING, FOUND IF THE VALVE WAS OPENED BY A GREAT DEAL OF FORCE, THE VALVE COULD STICK OPEN. FROM INSIDE THE AIRCRAFT THERE IS NO WAY TO SEE THIS OVERBOARD HOSE OR FUEL COMING OUT OF IT. 1 L 7 1 3O 1A15 1996060600873 19960606 00873 CE 1996 6 6 96ZZZX2867 1 19960520 G 5230 DOOR CESSNA 402 402C 207590R CE RT NAC CARGO BRACKET BROKE D O OTHER E VIBRATION/BUFFET NR NOT REPORTED 1 WP 17 161TA 14505 402C0070 RIGHT NACELLE BAGGAGE COMPARTMENT HOLD-DOWN BRACKET BROKEN CAUSING DOOR TO TRIP OPEN CAUSING A VIBRATION IN THE AIRFRAME . PART NOT LISTED IN CESSNA I.P.B. 1 L 7 2 3O A7CE 1996060600874 19960606 00874 EA 1996 6 6 96ZZZX2868 2 19960513 G 8530 VALVE SEAT PIPER PA31 PA31325 7103105 SO LYC O540 TIO540F2BD 41532 EA LT ENG NR 2 CYL DISLODGED D O OTHER E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CR CRUISE 1 GL 25 62992 554 LW12967 317712013 L631961AC ON A SHORT FLIGHT, A ROUGHNESS DEVELOPED IN THE LEFT ENGINE. NO EMERGENCY ACTION WAS REQUIRED. AFTER PERFORMING A COMP RESSION CHECK, FOUND THE EXHAUST VALVE SEAT ON NR 2 CYLINDER HAD BECOME DISLODGED CAUSING THE EXHAUST VALVE TO REMAIN PA RTIALLY OPEN. THE CYLINDER (HEAD) IN THE AREA OF THE EXHAUST SEAT WAS DAMAGED BEYOND REPAIR, AND THE VALVE OR SEAT CAUS ED MINOR DAMAGE TO THE PISTON. NO CAUSE FOR THE SEAT BECOMING DISLODGED HAS BEEN DETERMINED. 1 L 7 2 3O 3 O A20SO E14EA 1996060600875 19960606 00875 CE 1996 6 6 96ZZZX2869 1 19960510 G 7714 332000002 TACHOMETER BFGOODRICH CESSNA 206 TU206B 2073324 CE ENGINE RPM FAILED D K NONE O OTHER IN INSP/MAINT 1 NM 01 4991F 1 332000022505 U2060691 NEW TACHOMETER INSTALLED FROM CESSNA SUPPLIED BY B. F. GOODRICH. TACHOMETER FAILED WITHIN 1.0 HOURS. NEEDLE AT 1,500 R PM WITH ENGINE OFF. REMOVED CABLE AT ENGINE. TACHOMETER READS ZERO. REMOVED TACHOMETER, TURNED BY HAND, AND PUSHED LI GHTLY ON INPUT SHAFT. NEEDLE STOPS INDICATION. RELEASE PRESSURE, TACH GOES TO ZERO. LOCK-WASHER WRONG TYPE FOR NUT AN D NUT LOOSE ALLOWING TACH TO FLOAT INSIDE CASE. THIS IS THE 2ND TACHOMETER INSTALLED AND FAILED WITHIN 10.0 HOURS. 1 H 7 1 3O A4CE 1996060600876 19960606 00876 CE 1996 6 6 96ZZZX2870 1 19960510 G 7714 08503305 TACH/GENERATOR VICKERS CESSNA 340 340A 2076405 CE THRU SCREWS FAILED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 EA 03 4326C 550 1090 340A0075 THIS IS THE SECOND TACHOMETER/GENERATOR OF THIS MODEL THAT HAD LOOSE THROUGH-SCREWS EVEN THOUGH THEY WERE SAFELY WIRED. BOTH UNITS FAILED AND THE SAFETY WIRE WAS DONE AT THE MANUFACTURER. PART TOTAL TIME, 550.2 HRS, 24 MONTHS. 1 L 7 2 3O 3A25 1996060600877 19960606 00877 SO 1996 6 6 96ZZZX2871 1 19960511 G 7120 1607304 SUPPORT ASSY PIPER PA23 PA23250 7102308 SO ENG MOUNT BENT D K NONE O OTHER IN INSP/MAINT 1 SO 15 14217 274775 SUBMITTER SUSPECTS HARD LANDING RT MLG SIDE. FOUND BENT ENGINE MOUNT SUPPORT ASSY AT ACTUATOR BRACKET. REPLACED WITH S ERVICEABLE PART. DAMAGED RT INBOARD GEAR DOOR. REPLACED WITH SERVICEABLE UNIT. NO FURTHER DAMAGE FOUND. 1 L 7 2 3O 1A10 1996060600878 19960606 00878 NM 1996 6 6 96ZZZX2872 1 19960513 G 7160 BA4111 SCREEN BRACKETT BA4106 CHRIS HUSKY A1 221020X NM INDUCT FILTER CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 13 2908U 481 1023 MECHANIC REMOVED THE FILTER ELEMENT FOR NORMAL REPLACMENT DURING AN ANNUAL, HE NOTICED A 3.5 INCH CRACK RUNNING VERTICAL LY IN THE ELEMENT RETAINING SCREEN. IF PIECES BROKE LOOSE, THEY WOULD BE INGESTED INTO THE CARBURETOR. THIS WAS A STEE L MESH SCREEN NOT COVERED BY AD 81-15-03. 1 H 7 1 3O NC A22NM 1996060600879 19960606 00879 1996 6 6 96ZZZX2873 1 19960501 G 2822 1C2710 FUEL PUMP AIRBORNE IMPELLER BEARING MISMANUFACTURED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 13 4AG140 FUEL PUMP IMPELLER BEARING INSTALLED INCORRECTLY. (WRONG SIDE UP.) FROM THE WEAR PATTERN ON IT, IT APPEARS TO HAVE COM E FROM THE FACTORY IN THIS CONDITION. RECOMMEND INSTALL CORRECTLY. 1996060600880 19960606 00880 1996 6 6 96ZZZX2874 4 19960508 G 2562 450014 MOUNT CLAMP AMERIKING AK450 ELT RIVETS FAILED H K NONE O OTHER IN INSP/MAINT 1 EA 05 4502406 RIVETS ATTACHING LATCH TO MOUNTING CLAMP FAILED WHEN ELT CLAMPED TO MOUNTING TRAY. RIVETS IMPROPERLY DRIVEN. SUBMITTER SUGGESTS INSPECTING ALL HARDWARE PRIOR TO INSTALLATION. 1996060600881 19960606 00881 SO 1996 6 6 96ZZZX2875 2 19960324 G 8520 639243 CRANKSHAFT BEECH 35 V35B 1151548 CE CONT O520 IO520BA 17032 SO 1ST MAIN BEARING BROKEN D A UNSCHED LANDING O OTHER CR CRUISE 1 SW 09 9440Q 2301 34 D9319 20085971B SIXTY-FIVE PERCENT POWER IN LEVEL FLIGHT, IFR CONDITIONS. CRANKSHAFT BROKE AT FIRST MAIN BEARING AFT NOSE BEARING THROU GH CHEEK. CRANKSHAFT TOTAL TIME, 2,301 HOURS. INSPECTED, MAGNAFLUXED, AND PERFORMED ULTRASONIC INSPECTION AT 1,485 HOU RS. SUSPECT FATIGUE AND STRESS FAILURE. SUBMITTER STATED CRANKSHAFT DESIGN NOT ADEQUATE FOR 285 HORSEPOWER RATING. RE COMMEND NR IO520BB FOR THIS HORSEPOWER RATING. MAGNAFLUX AND ULTRASONIC PER SB M87-5 ARE NOT SUFFICIENT TO PREVENT NR I O520BA CRANKSHAFTS FROM BREAKING. 1 L 7 1 3O 3 O 3A15 E5CE 1996060600882 19960606 00882 CE 1996 6 6 96ZZZX2876 1 19960510 G 3230 204101744 DOWNLOCK SUPPORT CESSNA 177 177RG 2073709 CE RT MLG PIN BROKEN D K NONE O OTHER IN INSP/MAINT 1 GL 11 8271G 2486 177RB0171 DOWNLOCK SUPPORT LOWER PIN FOUND BROKEN OFF CAUSING POWERPACK MOTOR TO NOT SHUT OFF. BATTERY DRAINED VERY LOW. ELECTRI CAL SYSTEMS OPERATED VERY MARGINAL DURING IFR FLIGHT. FOUND LEFT DOWNLOCK SUPPORT LOWER PIN CRACKED. THIS CRACK NOT VI SIBLE WITH DOWNLOCK ASSEMBLED. SUSPECT CAUSE, AIRCRAFT OPERATED ON ROUGH LANDING STRIP. SUBMITTER RECOMMENDS DISASSEMB LY OF LOCK TO ZYGLOW PINS IF ACFT IS OPERATED ON ROUGH LANDING STRIPS. 1 H 7 1 3O A20CE 1996060600883 19960606 00883 SO 1996 6 6 96ZZZX2877 1 19960417 G 2434 ALX8421LS ALTERNATOR PIPER PA44 PA44180 7104402 SO LT ENGINE FAN FAILED B OG5R K NONE O OTHER NR NOT REPORTED 1 GL 21 854ND 1833 89320049 4495008 LEFT ALTERNATOR COOLING FAN FAILED. FAN APPEARS TO HAVE LOST FIT BETWEEN SHAFT SHOULDER AND PULLEY. FAN BECAME OFF-CEN TER AND BROKE THROUGH/SEPARATED SHAFT. FOUND FAN SEPARATED FROM ALTERNATOR AND LODGED BETWEEN ALTERNATOR BRACKET AND ST ARTER RING GEAR. 1 L 7 2 3O A19S0 1996060600884 19960606 00884 SO 1996 6 6 96ZZZX2878 1 19960429 G 7603 455322 CABLE PIPER PA28 PA28R201 7102816 SO THROTTLE BROKE B OG5R K NONE O OTHER IN INSP/MAINT 1 GL 21 172ND 5702 2837007 THROTTLE CABLE BROKE AT ENGINE END WHERE CONTROL CONNECTS TO FUEL INJECTOR. FOUND STANDS BROKE WHERE CABLE END SWAGES O NTO CABLE CORE STRANDS. CABLE IS ORIGINAL PART. EXTRA ATTENTION IS BEING PLACED ON HIGH TIME CABLES. THIS SAME CABLE IS USED FOR PROPELLER AND MIXTURE CONTROLS. 1 L 7 1 3O 2A13 1996060600885 19960606 00885 SO 1996 6 6 96ZZZX2879 2 19960508 G 8530 CYLINDER CESSNA 421 421C 2076016 CE CONT O520 GTSIO520L 17032 SO NR 1 CYLINDER HEAD SEPARATED B ETER E A ENGINE SHUTDOWN UNSCHED LANDING E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CL CLIMB 1 SO 11 49TD 421C0025 241033R ON TAKEOFF, NR 1 CYLINDER SEPARATED AT THE HEAD CAUSING ENGINE POWER LOSS. PILOT SHUT DOWN LEFT ENGINE AND RETURNED TO AIRPORT. ENGINE AND CYLINDER HAD 757 HOURS SINCE OVERHAUL WITH .010 INCH OVERSIZED BARRELS. CYLINDER TOTAL TIME UNKNOW N. 1 L 7 2 3O 3 O A7CE E7CE 1996060600886 19960606 00886 CE 1996 6 6 96ZZZX2880 1 19960503 G 3710 212CW PUMP AIRBORNE OLAL002303 BEECH 58 58 1152740 CE RT ENG VAC FAILED D K NONE O OTHER NR NOT REPORTED 1 SW 15 666SH 36 TH1083 FIRST PUMP REPLACED APPEARED TO HAVE OVER 800 HRS IN SERVICE. REPLACED WITH NEW AIRBORNE PUMP 10/95. IT LASTED 35.9 HR S. REPLACED AGAIN 12/95 LASTED 31.9 HRS. SYSTEM CHECKED WITH AIRBORNE 343 TEST KIT. PUMP LASTED 16.0 HRS. REPLACED AN D SYSTEM CHECKED, LASTED 23.3 HRS. LAST 3 PUMPS SENT DIRECTLY TO AIRBORNE FOR ANALYSIS. ALL PUMPS WARRANTIED, BUT HAVE BEEN UNABLE TO DETERMINE A CAUSE FOR CONTINUED FAILURES. HAVE DISCUSSED PROBLEM WITH BEECH, CONTINENTAL, AND AIRBORNE. AT THIS POINT, SUSPECT FAULTY PUMPS. 1 L 7 2 3O 3A16 1996060600887 19960606 00887 SO 1996 6 6 96ZZZX2881 1 19960515 G 5610 5490105 WINDOW PIPER PA31T PA31T1 7103126 SO COCKPIT RT SIDE DEPARTED D A UNSCHED LANDING D INFLIGHT SEPARATION CR CRUISE 1 NM 05 121BE 1919 31T8004036 PILOT REPORTS THAT AT 27,000 FEET, RIGHT SIDE COPILOT'S SIDE WINDOW BLEW OUT. PILOT FURTHER REPORTS THAT UNTIL THIS TIM E, ALL SYSTEMS WERE NORMAL. PILOT THEN RETURNED TO BASE WITHOUT FURTHER INCIDENT. CAUSE FOR WINDOW FAILURE UNKNOWN. 1 L 7 2 3T A8EA 1996060600888 19960606 00888 CE 1996 6 6 96ZZZX2882 1 19960422 G 5753 58250171 FITTING 582500514 CESSNA 441 441 2076020 CE RT INBD FLAP CHAFE WING B CM2R K NONE O OTHER IN INSP/MAINT 1 SW 15 434AE 4410097 INBOARD FORWARD SIDE OF RIGHT INBOARD FLAP IS CHAFING INTO THE SKIN AT THE WING STUB. FITTING WHICH IS RIVETED TO THE F ORWARD INBOARD SIDE OF THE RIGHT INBOARD FLAP IS CHAFING AGAINST THE WING SKIN. 1 L 7 2 3T RT A28CE 1996060600889 19960606 00889 CE 1996 6 6 96ZZZX2883 1 19960422 G 5753 58250172 FITTING 582500514 CESSNA 441 441 2076020 CE RT INBD FLAP CHAFE WING B CM2R K NONE O OTHER IN INSP/MAINT 1 SW 15 434AE 4410097 INBOARD FORWARD SIDE OF RIGHT INBOARD FLAP IS CHAFING INTO THE SKIN AT THE WING STUB. FITTING WHICH IS RIVETED TO THE F ORWARD INBOARD SIDE OF THE RIGHT INBOARD FLAP IS CHAFING AGAINST THE WING SKIN. 1 L 7 2 3T RT A28CE 1996060600890 19960606 00890 CE 1996 6 6 96ZZZX2884 1 19960422 G 5753 58250171 FITTING 582500514 CESSNA 441 441 2076020 CE RT FLAP CHAFE WING B CM2R K NONE O OTHER IN INSP/MAINT 1 SW 15 441AR 3480 4410360 INBOARD FORWARD SIDE OF RIGHT INBOARD FLAP IS CHAFING INTO SKIN ON WING STUB. FITTING WHICH IS RIVETED TO THE FORWARD I NBOARD SIDE OF THE RIGHT INBOARD FLAP IS CHAFING AGAINST THE WING SKIN. 1 L 7 2 3T RT A28CE 1996060600891 19960606 00891 CE 1996 6 6 96ZZZX2885 1 19960422 G 5753 58250172 FITTING 582500514 CESSNA 441 441 2076020 CE RT FLAP CHAFE WING B CM2R K NONE O OTHER IN INSP/MAINT 1 SW 15 441AR 3480 4410360 INBOARD FORWARD SIDE OF RIGHT INBOARD FLAP IS CHAFING INTO SKIN ON WING STUB. FITTING WHICH IS RIVETED TO THE FORWARD I NBOARD SIDE OF THE RIGHT INBOARD FLAP IS CHAFING AGAINST THE WING SKIN. 1 L 7 2 3T RT A28CE 1996060600892 19960606 00892 EA 1996 6 6 96ZZZX2886 2 19960410 G 7322 8618 LOCKWIRE FACET MA4SPA PIPER PA28 PA28161 7102803 SO LYC O320 O320D3G 41508 EA CARB MIX CONTROL FAILED D K NONE O OTHER IN INSP/MAINT 1 WP 09 3567P 2200 CK815279 288016202 L1271039A CARBURETOR MIXTURE CONTROL DID NOT FUNCTION PROPERLY. UPON INSPECTION, PN 86-18 LOCKWIRE, FOUND FATIGUED, CRACKED IN HA LF, NOT ALLOWING FOR MIXTURE CONTROL SHAFT TO BE PROPERLY OPERATED. 1 L 7 1 3O 3 O 2A13 E274 1996060600893 19960606 00893 EA 1996 6 6 96ZZZX2887 2 19960501 G 8500 ENGINE SLNSBY T67 T67M260 8323006 EU LYC O540 AEIO540D4A5 41532 EA POWER PLANT FAILED D O OTHER Y ENGINE STOPPAGE AB AEROBATIC 1 SW 17 3193K 100 2233 L2559748A ENGINE STOPPED IN-FLIGHT AFTER POWER REDUCTION IN SPIN DURING POWER ON OF THE SPIN DEMONSTRATION SORTIE. ENGINE RESTART ED WITH START BUTTON. 1 L 7 1 3O 3 O NT A73EU 1E4 1996060600894 19960606 00894 EA 1996 6 6 96ZZZX2888 2 19960508 G 7414 M3525 COIL SLICK 4271 PIPER PA28 PA28181 7102807 SO LYC O360 O360A4M 41514 EA LT MAGNETO FAILED D K NONE O OTHER IN INSP/MAINT 1 CE 01 8089C 220 89100029 28769002 RL3247136A AFTER FLIGHT, ENGINE WOULD NOT START. BOTH MAGNETOS FOUND TO BE INOPERATIVE, NO SPARK. IT HAS BEEN FOUND THAT ONE MAG GOES INOP. ENGINE STARTS ON THE GOOD ONE, UNTIL IT FAILS. AFTER THE ENGINE RPM MEETS OR EXCEEDS 600 RPM, THESE COILS W ILL MAG CHECK OK. INSTALLED FACTORY NEW COILS, PN M3975. OPS SATISFACTORY. 1 L 7 1 3O 3 O 2A13 E286 1996060600895 19960606 00895 EA 1996 6 6 96ZZZX2889 2 19960508 G 7414 M3525 COIL SLICK 4271 PIPER PA28 PA28181 7102807 SO LYC O360 O360A4M 41514 EA RT MAGNETO FAILED D K NONE O OTHER IN INSP/MAINT 1 CE 01 8089C 220 89100015 28769002 RL3247136A AFTER FLIGHT, ENGINE WOULD NOT START. BOTH MAGNETOS FOUND TO BE INOPERATIVE, NO SPARK. IT HAS BEEN FOUND THAT ONE MAG GOES INOP. ENGINE STARTS ON THE GOOD ONE, UNTIL IT FAILS. AFTER THE ENGINE RPM MEETS OR EXCEEDS 600 RPM, THESE COILS W ILL MAG CHECK OK. INSTALLED FACTORY NEW COILS, PN M3975. OPS SATISFACTORY. 1 L 7 1 3O 3 O 2A13 E286 1996060600896 19960606 00896 GL 1996 6 6 96ZZZX2890 3 19960430 G 6114 D24841 HUB BEECH 58 58 1152740 CE HARTZL HCJ2Y BHCJ2YF2 GL PROPELLER CORRODED D K NONE O OTHER IN INSP/MAINT 1 SW 99 D2149 INSPECTION FOUND CORROSION ON EXTERIOR AND INTERIOR OF HUB. SUBMITTER RECOMMENDS REGULAR MAINTENANCE. 1 L 7 2 3O 3A16 5 C P37EA 1996060600897 19960606 00897 GL 1996 6 6 96ZZZX2891 3 19960430 G 6114 D4887 HUB MCAULY 2AF34C D2AF34C81 GL PROPELLER CORRODED D K NONE O OTHER IN INSP/MAINT 1 SW 99 643154 INSPECTION FOUND CORROSION ON EXTERIOR OF HUB WELL OVER .010 INCH DEEP. 5 C P5EA 1996060600898 19960606 00898 GL 1996 6 6 96ZZZX2892 3 19960430 G 6111 S82NC2 BLADE CESSNA 185 185 2072802 CE MCAULY 3A32C D3A32C90 GL THREADS CORRODED D K NONE O OTHER IN INSP/MAINT 1 SW 99 796156 796156 INSPECTION FOUND CORROSION IN BOTTOM OF BLADE THREADS. SUBMITTER RECOMMENDS REGULAR MAINTENANCE. 1 H 7 1 3O NC 3A24 5 C P21EA 1996060600899 19960606 00899 1996 6 6 96ZZZX2893 1 19960506 G 3520 417T42633 MASK BOEING 417T4204 PULL STREAMER DEFECTIVE B GUMR K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 19 PULL STREAMERS FOR ACTIVATING PASSENGER OXYGEN SYSTEMS FAILED THE PULL TEST. INSPECTION OF ALL STREAMERS IN STOCK RESUL TED IN IDENTIFYING APPROXIMATELY 20 PERCENT DEFECTIVE, I.E., BAD CRIMPS, CRIMPS SLIPPING AND FRAYED STRINGS. BOEING AIR CRAFT HAS BEEN NOTIFIED AND IS INVESTIGATING THE PROBLEM. NOTE: THE DEFECTIVE STREAMERS WERE FOUND PRIOR TO BEING INST ALLED IN AN AIRCRAFT. 1996060600900 19960606 00900 NE 1996 6 6 96ZZZX2894 2 19960501 G 7320 P3 LINE LEAR 24 24D 5170311 CE GE CJ610 CJ6106 30006 NE LT ENGINE LOOSE E O OTHER X ENGINE FLAMEOUT CL CLIMB 1 SW 15 453 323 240C208A ON CLIMB-OUT AT 44,000 FEET, THE LT ENGINE FLAMED OUT. RESTARTED ENGINE AND UPON LANDING, MAINTENANCE INSPECTED THE LEF T ENGINE INLET, COMPRESSOR BLADES, TURBINE BLADES, INLET GUIDE VANES, INLET GUIDE VANE RIGGING, T-2 HOSE, AND P-3 LINE. FOUND P-3 LINE LOOSE. TIGHTENED P-3 LINE. 2 L 7 2 4J 4 J A10CE 1E16 1996060600901 19960606 00901 SO 1996 6 6 96ZZZX2895 1 19960508 G 4940 MS27433300 RELAY ALLIEDCONTRL 36100 GULSTM G159 G159 3952202 SO APU FAILED D K NONE O OTHER IN INSP/MAINT 1 SO 09 5NA P110 125 APU WOULD NOT START. FOUND RELAY BURNED. REPLACED RELAY AND SHORT SECTION OF BATTERY LEAD WIRE, APU WORKS. 2 L 7 2 4T 1A17 1996060600902 19960606 00902 EA 1996 6 6 96ZZZX2896 1 19960430 G 2420 WIRE DHAV DHC7 DHC7102 2802708 EA NR 2 AC GEN CHAFED B WVER O OTHER J WARNING INDICATION NR NOT REPORTED 1 EA 09 89068 14957 88 ON TEST FLIGHT, AC NR 2 GENERATOR LIGHT CAME ON. DURING TROUBLESHOOTING OF SYSTEM, FOUND WIRE 2420-20001E12A-1 GROUNDED OUT. CONDUIT PASSES BETWEEN REAR SPAR AND FLAP PRIMARY CONTROL TUBE. AREA WHERE WIRES PASS THROUGH IS PRESSED AND WIR E RUBS CONDUIT. SUBMITTER STATED IF AC GENERATOR LIGHT COMES ON OR GENERATOR WILL NOT COME ON LINE, THIS IS AN AREA TO LOOK AT. 2 H 7 4 4T A20EA 1996060600903 19960606 00903 SO 1996 6 6 96ZZZX2897 1 19960423 G 2910 JPS33513 TUBE ASSY LKHEED 1329 132925 5263125 SO NR 1 ENG T/R CORRODED B VJ1R K NONE K FLUID LOSS IN INSP/MAINT 1 SW 05 901C 7725 5218 DURING POST-MAINTENANCE ENGINE RUNS, HYDRAULIC FLUID WAS NOTICED LEAKING FROM LINE. FURTHER INVESTIGATION REVEALED A SE RIES OF CORRODED PIN HOLES LOCATED UNDER THE LINE IDENTIFIER TAPE PLACARD. THIS SITUATION IS SIMILAR TO THE PROBLEM THA T AFFECTED THE RUDDER BIAS BLEED AIR LINES ON THE RC1125-700 (SB 27-157R2). SUBMITTER RECOMMENDS PLACARDING TAPE BE REM OVED FROM LINES AND SURFACES AND BE VISUALLY INSPECTED FOR CORROSION. OPERATOR CONTROL NR 96-002. 2 L 7 4 4F 2A1SO 1996060600904 19960606 00904 NM 1996 6 6 96ZZZX2898 1 19960130 G 5610 SPSF900272 WINDSHIELD AMD FALC50 FALCON2000 2730170 NM PILOT DELAMINATED B CW1R B A EMER. DESCENT UNSCHED LANDING O OTHER CR CRUISE 1 EA 25 790L 41 15 PILOT'S FRONT WINDSHIELD OUTER PLY DELAMINATED AT FL 450. AN UNEVENTFUL EMERGENCY DESCENT AND LANDING WAS PERFORMED INT O WICHITA, KS. WINDSHIELD WAS SUBSEQUENTLY REPLACED AND AIRCRAFT RETURNED TO SERVICE. 2 K 7 3 4F RT A50NM 1996060600905 19960606 00905 GL 1996 6 6 96ZZZX2899 2 19960513 G 7250 6892828 NOZZLE SHIELD 23031925 ALLSN 250C 250C30 03013 GL 1ST STAGE TURB CRACKED B YKER K NONE O OTHER IN INSP/MAINT 1 EA 17 CAT90284 CAE890278 DURING REPAIR OF THE TURBINE, NOTED THE DEFLECTOR ON THE FIRST STAGE NOZZLE SHIELD WAS BURNED. CLOSER EXAMINATION REVEA LED 2 CRACKS IN THE DOME DETAIL. THE DOME WAS CHECKED FOR PROPER MATERIAL PER DEB A-72-3208 AND WAS FOUND TO CONFORM. S USPECT THE CAUSE COULD BE A STREAKING FUEL NOZZLE. 3 U E1GL 1996060600906 19960606 00906 NE 1996 6 6 96ZZZX2900 2 19960506 G 7200 ENGINE LEAR 25 25 5170506 CE GE CJ610 CJ6106 30006 NE LT/RT ENGINE FLAME OUT E B A EMER. DESCENT UNSCHED LANDING X ENGINE FLAMEOUT CR CRUISE 1 SW 99 28CK 10530 045 251763 LEFT AND RIGHT ENGINES EXPERIENCED TURBINE AIR FLAME-OUTS. AIRCRAFT DESCENDED AND ENGINES RESTARTED, UNEVENTFUL LANDING MADE. ENGINES INSPECTED, AND GROUND PERFORMANCE RUN CARRIED OUT. NO DEFECTS NOTED. OPERATOR CONTROL NR 5-6-96-28CK. 2 L 7 2 4J 4 J A10CE 1E16 1996060600907 19960606 00907 CE 1996 6 6 96ZZZX2901 1 19960214 G 3397 WIRE HARNESS LEAR 60 60LEAR 5170707 CE ELECT PLUG P728 CHAFED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 05 210FX 55 064 PILOT REPORTED INTERMITTENT PROBLEMS WITH EXTERIOR LIGHTS AND FLUCTUATION IN HYDRAULIC PRESSURE INDICATION. TROUBLESHOO TING FOUND SEVERAL CHAFED AND BROKEN WIRES FROM ELECTRICAL CONNECTOR PLUG NR P-728 GOING TO CONNECTOR J2 ON THE COCKPIT CENTER SWITCH PANEL. THE WIRE BUNDLE WAS HITTING A JUCTION BOX BEHIND THE CENTER INSTRUMENT PANEL. REPAIRED BY SPLICIN G IN NEW SECTIONS OF WIRE, AND RE-ROUTING AND SECURING BUNDLE. OPS CHECKS GOOD. SUSPECT CAUSE AS INATTENTION TO DETAIL , LAX QUALITY CONTROL AT THE FACTORY. SUBMITTER RECOMMENDS INSPECTION OF OTHER LEAR 60'S FOR SIMILAR PROBLEMS IN THE AR EA AROUND THE ELECTRICAL J-BOX BEHIND THE PANEL. 2 L 7 2 4F RT A10CE 1996060600908 19960606 00908 CE 1996 6 6 96ZZZX2902 1 19960213 G 2497 WIRE LEAR 60 60LEAR 5170707 CE ELEC CONN P10 BURNED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 05 205FX 005 WHILE TROUBLESHOOTING UNRELATED ELECTRICAL PROBLEM, FOUND 4 INCORRECT PLASTIC WIRE SPLICES TO ELECTRICAL CONNECTOR PLUG NR P-10 AT UPPER RT CORNER OF AFT PRESSURE BULKHEAD. ALL 4 SPLICES WERE BURNED, 2 SEVERED IN HALF. INSTALLED 4 NEW TEF LON TYPE WIRE SPLICES PER LEARJET FIELD SERVICE. SUSPECT CAUSE AS INATTENTION TO DETAIL, OR LAX QUALITY CONTROL EITHER AT THE FACTORY OR ANOTHER MAINTENANCE SHOP. (UNKNOWN WHERE SPLICES INSTALLED.) SUBMITTER RECOMMENDS INSPECTION OF OTHE R LEAR 60'S FOR CORRECT HARDWARE AND CHECK LEAR FACTORY TO MAKE SURE INCORRECT HARDWARE IS NO BEING USED ON ASSY LINE. 2 L 7 2 4F RT A10CE 1996060600909 19960606 00909 CE 1996 6 6 96ZZZX2903 1 19960430 G 2750 NAS464P413 BOLT CESSNA 500 S550 2076607 CE FLAP CONTROL MISINSTALLED D S K NONE W INADEQUATE Q C IN INSP/MAINT 1 CE 09 9GT S5500159 PHASE INSPECTION. INSPECTOR WAS CHECKING FLAP TENSION AND FOUND FLAP CABLE MISALIGNED WHEN FLAPS RETRACTED. FURTHER IN VESTIGATION REVEALED INBD FLAP CONTROL BELLCRANK FWD PUSHROD BOLT INSTALLED WITH HEAD OF BOLT UP. THIS CAUSED INTERFERE NCE WITH THE SHANK, HITTING FLAP CABLE. PARTS AND MM SHOWS PROPER INSTALLATION WITH HEAD OF BOLT DOWN. TO PROVIDE CLEA RANCE - NOTE: ONLY THE INBD BELLCRANK BOLT IS INSTALLED WITH HEAD DOWN. OTBD BELLCRANKS, THE BOLT HEAD IS INSTALLED IN THE 'UP' POSITION. 1 L 7 2 4F RT A22CE 1996060600910 19960606 00910 WP 1996 6 6 96ZZZX2904 2 19960315 G 7250 3587591 BEARING LEAR 35 35LEAR 5170600 CE GARRTT TFE731 TFE73122B 01518 WP ENG NR 4 FAILED B L MJ1R E ENGINE SHUTDOWN E J VIBRATION/BUFFET WARNING INDICATION DE DESCENT 1 EA 11 130F 2399 044 P74225 DURING DESCENT, FLT CREW OBSERVED FLUCTUATING FUEL FLOW ON RT ENG FOLLOWED BY VIBRATION AND NOISE. CREW REDUCED POWER S ETTING TO IDLE AND CONTINUED FLT. DURING FINAL APROACH, OIL PRESSURE BEGAN TO FLUCTUATE AND LOW OIL PRESSURE CAUTION LI GHT ILLUMINATED. PILOT COMMANDED A SHUT-DOWN AND LANDED ACFT WITHOUT FURTHER INCIDENCE. UNABLE TO ROTATE EITHER THE LP OR HP SPOOLS. EXAMINATION OF INLET AREA SHOWED NO EVIDENCE OF FOREIGN OBJECT INGESTION. METAL CONTAMINATION FND IN OI L TANK, XSFER GEARBOX AND OIL FILTER, FILTER BYPASS BUTTON WAS NOT OUT. UNABLE TO DISASSEMBLE OIL PUMP DUE TO INTERNAL DAMAGE. ENG IN-FLT SHUTDOWN CAUSED BY FAILURE OF NR 4 BEARING AND SUBSEQUENT INTERNAL DOMESTIC OBJECT DAMAGE TO ENGINE. 2 L 7 2 4F 4 F A10CE E6WE 1996060600911 19960606 00911 EU 1996 6 6 96ZZZX2905 1 19960321 G 2730 BELLCRANK SUKHOI SU29 SU29 9850103 EU ELEVATOR BOLT MISSNG G L A A UNSCHED LANDING O OTHER AB AEROBATIC 1 SW 03 729SU 7804 ALNOT ISSUED ON A SINGLE ENGINE SUKHOI SU-29 WHEN 3 HRS OVERDUE. ALNOT REPORTED MISSING AIRCRAFT HAD BEEN OVER AN AEROB ATICS PRACTICE AREA. ACFT HAD CRASHED, FATALLY INJURING PILOT AND DESTROYING ACFT. DURING EXAMINATION OF REMNANTS OF E LEVATOR CONTROL SYSTEM, A BELLCRANK WAS FND WITH UPPER ATTACHING HOLES SHOWING NO VISIBLE DEFORMATION AND NO VISIBLE BEN DING OF THE EARS, ATTACH BOLT AND ROD END WERE MISSING. BELLCRANK ONLY ITEM IN ELEVATOR OR AILERON CONTROL SYS THAT DID NOT DISPLAY SOME IMPACT DAMAGE. BELLCRANK REMOVED AND SENT TO NTSB LAB FOR EXAMINATION, PRELIMINARY REPORT INDICATES A LTHOUGH A BOLT HAD BEEN INSTALLED AT ONE TIME, NO INDICATION A BOLT WAS INSTALLED AT TIME OF IMPACT. 1 L 7 1 3R NC USSR 1996061300039 19960613 00039 SO 1996 6 13 96ZZZX2906 1 19960520 G 2432 36H120 CELL MARATHON MA5 GULSTM G1159 G1159 3953505 SO BATTERY DAMAGED B A JZBR K NONE O OTHER IN INSP/MAINT 1 EA 25 2HF 9404268 221 THE BATTERY WAS REMOVED FROM THE AIRCRAFT AND SENT TO A BATTERY FACILITY FOR SCHEDULED MAINTENANCE. DISCOVERED ALL 19 C ELLS HAD TO BE CONDEMNED DUE TO CELL SEPARATOR DAMAGE. ALL 19 CELLS WERE REPLACED AND THE SCHEDULED MAINTENANCE CONTINU ED. THE BATTERY WAS RETURNED TO SERVICE AND REINSTALLED IN THE AIRCRAFT. THE AIRCRAFT WAS RETURNED TO SERVICE. (NOTE: NO PROBLEMS WERE REPORTED BY THE CREW CONCERNING THIS BATTERY WHILE IN SERVICE. THIS IS ONE OF SEVERAL MA5 BATTERIES EXPERIENCING THIS PROBLEM. SUBMITTER RECOMMENDS IMPROVED CELL SEPARATOR QUALITY AND CHECK OF CURRENT SERVICING PROCEDU RES. 200 HOURS SINCE DEEP CYCLE, (CELL S/N 9404268). 2 L 7 2 4F RT A12EA 1996061300040 19960613 00040 SO 1996 6 13 96ZZZX2907 1 19960520 G 2432 36H120 CELL MARATHON MA5 GULSTM G1159 G1159 3953505 SO BATTERY DAMAGED B A JZBR K NONE O OTHER IN INSP/MAINT 1 EA 25 711RL 9404267 025 THE BATTERY WAS REMOVED FROM THE AIRCRAFT AND SENT TO A BATTERY FACILITY FOR SCHEDULED MAINTENANCE. DISCOVERED THAT ALL 19 CELLS HAD TO BE CONDEMNED DUE TO CELL SEPARATOR DAMAGE. ALL 19 CELLS WERE REPLACED AND THE SCHEDULED MAINTENANCE CO NTINUED. THE BATTERY WAS RETURNED TO SERVICE AND REINSTALLED IN THE AIRCRAFT. THE AIRCRAFT WAS RETURNED TO SERVICE. ( NOTE: NO PROBLEMS WERE REPORTED BY THE CREW CONCERNING THIS BATTERY WHILE IN SERVICE. THIS IS ONE OF SEVERAL MA5 BATTE RIES EXPERIENCING THIS PROBLEM. SUBMITTER RECOMMENDS IMPROVED CELL SEPARATOR QUALITY AND CHECK OF CURRENT SERVICING PRO CEDURES. 200 HOURS SINCE DEEP CYCLE, (CELL S/N 9404267). 2 L 7 2 4F RT A12EA 1996061300041 19960613 00041 SO 1996 6 13 96ZZZX2908 1 19960520 G 2432 36H120 CELL MARATHON MA5 GULSTM G1159 G1159 3953505 SO BATTERY DAMAGED B A JZBR K NONE O OTHER IN INSP/MAINT 1 EA 25 2HF 9404271 221 THE BATTERY WAS REMOVED FROM THE AIRCRAFT AND SENT TO A BATTERY FACILITY FOR SCHEDULED MAINTENANCE. DISCOVERED ALL 19 C ELLS HAD TO BE CONDEMNED DUE TO CELL SEPARATOR DAMAGE. ALL 19 CELLS WERE REPLACED AND THE SCHEDULED MAINTENANCE CONTINU ED. THE BATTERY WAS RETURNED TO SERVICE AND REINSTALLED IN THE AIRCRAFT. AIRCRAFT WAS RETURNED TO SERVICE. (NOTE: NO PROBLEMS WERE REPORTED BY THE CREW CONCERNING THIS BATTERY WHILE IN SERVICE. THIS IS ONE OF SEVERAL MA5 BATTERIES EXPE RIENCING THIS PROBLEM. SUBMITTER RECOMMENDS IMPROVED CELL SEPARATOR QUALITY AND CHECK OF CURRENT SERVICING PROCEDURES. 200 HOURS SINCE DEEP CYCLE, (CELL S/N 9404271). 2 L 7 2 4F RT A12EA 1996061300042 19960613 00042 SO 1996 6 13 96ZZZX2909 1 19960520 G 2432 36H120 CELL MARATHON MA5 GULSTM G1159 G1159 3953505 SO BATTERY DAMAGED B A JZBR K NONE O OTHER IN INSP/MAINT 1 EA 25 711RL 9403011 25 THE BATTERY WAS REMOVED FROM THE AIRCRAFT AND SENT TO A BATTERY FACILITY FOR SCHEDULED MAINTENANCE. DISCOVERED ALL 19 C ELLS HAD TO BE CONDEMNED DUE TO CELL SEPARATOR DAMAGE. ALL 19 CELLS WERE REPLACED AND THE SCHEDULED MAINTENANCE CONTINU ED. THE BATTERY WAS RETURNED TO SERVICE AND REINSTALLED IN THE AIRCRAFT. THE AIRCRAFT WAS RETURNED TO SERVICE. (NOTE: NO PROBLEMS WERE REPORTED BY THE CREW CONCERNING THIS BATTERY WHILE IN SERVICE. SUBMITTER RECOMMENDS IMPROVED CELL SE PARATOR QUALITY AND CHECK OF CURRENT SERVICING PROCEDURES. 200 HOURS SINCE DEEP CYCLE, (CELL S/N 9403011). 2 L 7 2 4F RT A12EA 1996061300043 19960613 00043 CE 1996 6 13 96ZZZX2910 1 19960513 G 2160 12958010 LIMITER LEAR 35 35A 5170602 CE DUCT TEMPERATURE FAILED B XNJR O OTHER M OVER TEMP NR NOT REPORTED 1 WP 21 137RS 7663 1213 183 PILOT REPORT CABIN TEMPERATURE UNCONTROLLABLE IN MANUAL MODE, FULL HOT IN AUTO. FOUND DUCT TEMPERATURE LIMITER HAD FAIL ED. UPON LIMITER REMOVAL, FOUND PART HAD COMPLETELY SEPARATED CAUSING THE BELLOWS TO EXPAND AND MELT. 2 L 7 2 4F A10CE 1996061300044 19960613 00044 WP 1996 6 13 96ZZZX2912 1 19960509 G 5320 SHEAR CLIP DOUG DC9 DC931 3022065 WP FS 945 L15R CRACKED B DU4R K NONE O OTHER IN INSP/MAINT 1 SO 15 977ML 47329 DURING A SCHEDULED INSPECTION, SHEAR CLIP LOCATED BETWEEN LONGERONS 15R AND 16R WAS FOUND CRACKED 2 INCHES. REMOVED CRA CKED SHEAR, FABRICATED AND INSTALLED NEW CLIP IAW DC-9 SRM 53-03, FIGURE 28 AND DC-9, MM 55-00. 2 L 7 2 4F A6WE 1996061300045 19960613 00045 WP 1996 6 13 96ZZZX2913 1 19960509 G 5311 FRAME DOUG DC9 DC931 3022065 WP FS 1074 CRACKED B DU4R K NONE O OTHER IN INSP/MAINT 1 SO 15 977ML 47239 DURING A SCHEDULED INSPECTION, CANTED FRAME WAS FOUND CRACKED AT FS 1074 L3 LT. STOP DRILLED CRACK. FABRICATED AND INS TALLED 5 EACH REPAIR PARTS IAW DC-9 SR 09530086. 2 L 7 2 4F A6WE 1996061300046 19960613 00046 CE 1996 6 13 96ZZZX2914 1 19960520 G 3251 4291006 ACTUATOR BEECH 99 99 1154002 CE NLG STEERING FAULTY B APCR K NONE O OTHER IN INSP/MAINT 1 NM 01 2880A 448 1007 U109 NOSE GEAR STEERING ACTUATOR FAILED INTERNALLY - WILL NOT GO FULL TRAVEL EITHER DIRECTION. 1 L 7 2 3T A14CE 1996061300047 19960613 00047 WP 1996 6 13 96ZZZX2915 1 19960514 G 5320 FRAME DOUG DC8 DC862 3021970 WP WINDOW NR 28 LT CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND WINDOW NR 28 LEFT HAS EVIDENCE OF CORROSION AROUND FRAME INNER SURFACE. REMOVED DAMAGED FRAME AND INSTALLED NEW ONE IAW SRM 51-1-20D. TREATED AND PRIMED IAW SRM 51-1-8. 2 L 7 4 4F 4A25 1996061300048 19960613 00048 CE 1996 6 13 96ZZZX2916 1 19960427 G 2133 21034012 REGULATOR BEECH MU300 400BEECH CE CABIN ALTITUDE FAULTY B QMZR O OTHER O OTHER DE DESCENT 1 EA 05 295FA 1013 0564 RK68 CABIN ALTITUDE WOULD NOT DESCEND WITH AIRCRAFT. MAINTENANCE FOUND NO VACUUM ON TEST PORT NR 3. FURTHER TROUBLESHOOTING ISOLATED FAULTY VACUUM REGULATOR. SUSPECT CAUSE: STICKY BELLOWS INSIDE REGULATOR. 'COLD-SOAKING' CAN BE RULED OUT. 2 H 7 2 4F RT A16SW 1996061300050 19960613 00050 WP 1996 6 13 96ZZZX2918 1 19960517 G 7120 39357391 BOLT DOUG DC9 DC983 3022083 WP LT ENG MOUNT CRACKED B A JR2R K NONE O OTHER IN INSP/MAINT 1 SW 15 832RA 53044 ULTRASONIC INSPECTION OF LT FORWARD UPPER NR 1 ENGINE MOUNT (YOKE) BOLT FOUND CRACKED. REF: OPERATOR CONTROL NR 00001. 2 L 7 2 4F RT A6WE 1996061300051 19960613 00051 NE 1996 6 13 96ZZZX2919 2 19960510 G 7210 7757535 IDLER GEAR 7758002 SAAB SF340 SF340A 7850100 EU GE CT7TP CT75A2 30030 NE LT PROP GRBOX FAILED B S A SI3R K NONE O OTHER IN INSP/MAINT 1 NE 03 3863 C6411160 DISASSEMBLY OF THE PROPELLER GEARBOX REVEALED THE LT IDLER GEAR (775753-5 ITEM 40 OF FIG 5 IN MANUAL 72-11-02) WEB FAILE D AND THE GEAR HAD BROKEN THROUGH THE GEARBOX HOUSING. THE FORWARD INPUT ROLLER BEARING (775765-1 ITEM 180 OF FIG 8) HA D BROKEN AND THE ROLLERS FOUND IN THE BOTTOM OF THE GEAR CASE. 2 L 7 2 4T 4 T RT A52EU E8NE6 1996061300052 19960613 00052 EU 1996 6 13 96ZZZX2920 1 19960517 G 5312 BULKHEAD AGUSTA A109 A109A2 0260120 EU AFT CABIN CRACKED D S A K NONE O OTHER IN INSP/MAINT 1 WP 13 109TS 2234 7276 INSPECTION FOUND AFT CABIN BULKHEAD LOCATED AT STA + 3.5 METERS, AT WATERLINE + 1 METER (LEFT SIDE), 3 INCH CRACK FROM I NSPECTION LIGHTENING HOLE TO BOTTOM OF LT MAIN ROTOR TRANSMISSION VERTICAL STRUT ATTACH BRACKET. SUSPECT BULKHEAD FABRI CATED FROM MATERIAL TOO 'THIN' TO ALLOW FOR HIGH GROSS-WEIGHT OPERATION, OR MANUFACTURING FLAW. 1 G 7 2 3U H7EU 1996061300053 19960613 00053 SW 1996 6 13 96ZZZX2921 1 19960514 G 7120 74612171123 MOUNT BELL 47 47G5A 1181034 SW ENGINE CRACKED D A K NONE O OTHER IN INSP/MAINT 1 GL 13 715BH 1736 506 822185 25105 DURING 100-HOUR ANNUAL INSPECTION, CRACK NOTED AT FORWARD TRUNNION CLUSTER. AREA WAS STRIPPED OF PAINT AND DYE CHECKED. CRACK CONFIRMED. A BULLETIN WAS ISSUED BY THE MFG 3-7-96. THIS WAS A PMA'D PART. 1 G 7 1 3O 2H3 1996061300054 19960613 00054 WP 1996 6 13 96ZZZX2922 1 19960425 G 5302 269A232011 ATTACH FITTING HUGHES 269 269C 4470504 WP TAILBOOM CRACKED G A K NONE O OTHER IN INSP/MAINT 1 EA 17 300KY 700 S825 S1433 DURING ROUTINE INSPECTION, FOUND EXCESSIVE PLAY WHEN INSPECTING SECURITY OF VERTICAL STABILIZER. DISCOVERED LOOSE ATTAC HMENT HARDWARE AT FORWARD END OF THE ATTACHMENT OF THE TAILBOOM ASSEMBLY. SUBMITTER RECOMMENDS A RETORQUE OF ATTACHMENT HARDWARE AT A CERTAIN TIME FOLLOWING INITIAL INSTALLATION OF TAILBOOM ASSEMBLY. 1 G 7 1 3O 4H12 1996061300055 19960613 00055 NE 1996 6 13 96ZZZX2923 1 19960420 G 6320 8528613 THERMOSTAT SKRSKY S64 S64F NE MAIN GEARBOX FAULTY B JYDR A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 NM 09 163AC 3893 78 A6111 64093 AIRCRAFT IN FORWARD FERRY FLIGHT ATTITUDE. OIL COOLER SYSTEM FUNCTIONING PROPERLY. OVERTEMP OF MGB INDICATION OBSERVED ON MASTER CAUTION PANEL. FLIGHT CREW SECURED SAFE LANDING LOCATION AND OBTAINED SAFE LANDING WITHOUT INCIDENT IN LESS THAN 1 MINUTE OF INITIAL WARNING LIGHT. 2 G 7 2 4U H6EA 1996061300217 19960613 00217 GL 1996 6 13 96ZZZX2935 2 19960510 G 7230 ROTOR ASSY HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL COMPRESSOR DEFECTIVE D K NONE R PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 WP 07 911FT 3888 1257 811036D CAE836410 POWER CHECK RESULTS - LOW POWER. COMPRESSOR ASSY REPLACED, DISCREPANCY CLEARED. (ALLISON MODEL 250 REPORT NR A 134718) . 1 G 7 1 3U 3 U H3WE E4CE 1996061300218 19960613 00218 GL 1996 6 13 96ZZZX2936 1 19960521 G 6700 KUP14D5524 RELAY ENSTRM F28 F28F 3300412 GL FLT CONTROL FAILED C PP0M O OTHER F FLT CONT AFFECTED NR NOT REPORTED 1 WP 01 8626S 1057 786 POINTS IN RELAY FUSE TOGETHER CAUSING RUNAWAY TRIM ACTION RESULTING IN UNCONTROLLED ATTITUDES OF AIRCRAFT. REQUIRES BOT H PILOTS ON CYCLIC TO OVERRIDE. RELAY MFG HAS INDICATED THIS IS NOT THE CORRECT RELAY FOR THIS APPLICATION. INSTALLED NEW RELAY PER MM. 1 G 7 1 3O H1CE 1996061300219 19960613 00219 GL 1996 6 13 96ZZZX2937 1 19960502 G 6320 28131709R TRANSMISSION ENSTRM F28 F28F 3300412 GL MAIN ROTOR MAKING METAL C PP0M K NONE J WARNING INDICATION NR NOT REPORTED 1 WP 01 8626S 558 9332281C 786 TRANSMISSION GENERATING CHIP LIGHTS EVERY FIVE MINUTES OF OPERATION. TOOTH OF RING GEAR HAD CHUNK MISSING 1.25 INCHES L ONG BY .25 INCH DEEP. INSTALLED ZERO TIME OVERHAUL TRANSMISSION. 1 G 7 1 3O H1CE 1996061300377 19960613 00377 GL 1996 6 13 96ZZZX2943 2 19960507 G 7200 ENGINE AGUSTA A109 A109C 0260118 EU ALLSN 250C 250C20 03013 GL NR 2 MAKING METAL D A K NONE J WARNING INDICATION NR NOT REPORTED 1 GL 03 97CH 337 7657 CAE295546 NR 2 ENGINE REMOVED DUE TO EXCESSIVE CHIP LIGHTS. THIS IS THE 3RD OCCURRENCE WITH THIS ENGINE. ENGINE TT, 336.5 HRS SI NCE NEW. 1 G 7 2 3U 3 U H7EU E4CE 1996061300378 19960613 00378 SW 1996 6 13 96ZZZX2944 1 19960520 G 6230 214040260105 ADAPTER BELL 214 214ST 1182106 SW MAST ASSY CRACKED B HEER K NONE O OTHER IN INSP/MAINT 1 SW 03 5748M 28102 MAST ASSY ADAPTER HAS CRACK AROUND 90 DEGREES OF CIRCUMFERENCE ON LOWER OR BOTTOM SURFACE, CRACK VISIBLE ON TOP SURFACE. NOTE: ACFT DELIVERY DATE IS 12/27/94. 2 G 7 2 4U H10SW 1996061300379 19960613 00379 WP 1996 6 13 96ZZZX2945 1 19960515 G 6220 514397 HUB HILLER UH12 UH12E 4360122 WP M/R CRACKED D K NONE O OTHER IN INSP/MAINT 1 WP 17 48219 2340 800 1153 2166 HUB FOUND CRACKED INSIDE HUB AT CONTROL ROTOR TRUNNION STUD HOLE. CRACK FOUND AT 50-HOUR DYE PENETRANT INSPECTION DURIN G C/W AD 73-20-3. SUBMITTER STATED CRACKS IN THIS AREA OCCUR ON OCCASION. 1 G 7 1 3O 4H11 1996061300380 19960613 00380 CE 1996 6 13 96ZZZX2946 1 19960507 G 3230 08401253 TUBE ASSY CESSNA 310 310L 2074230 CE NLG GEAR DRIVE BENT G L O OTHER J WARNING INDICATION AP APPROACH 1 WP 05 3305X 3911 310L0155 NOSE LANDING GEAR WAS EXTENDED, BUT DID NOT LOCK IN THE DOWN POSITION. SUBSEQUENT INVESTIGATION REVEALED THE NLG INTERM EDIATE GEAR DRIVE TUBE ASSY WAS BENT. THE ANNUAL AND 100-HOUR INSPECTION WERE COMPLETED APRIL 19, 1996. TACHOMETER TIM E 766.3. TOTAL TIME: 3,900.8 HRS. AIRCRAFT WAS PAINTED DECEMBER 22, 1995. THE NLG MAIN DRIVE TUBE ASSY WAS BROKEN. S UBMITTER STATED IMPROPER RIGGING MAY BE THE CAUSE. 1 L 7 2 3O 3A10 1996061300381 19960613 00381 CE 1996 6 13 96ZZZX2947 1 19960522 G 2710 581510324CR CONTROL CABLE CESSNA 404 404CESSNA 2075901 CE AILERONS WORN B S A APCR K NONE O OTHER IN INSP/MAINT 1 NM 01 41SA 547 4040023 ALL FOUR AILERON CABLES CONTINUALLY WEAR RAPIDLY AT PULLEYS IN WING TRAILING EDGE. PULLEYS ACT AS FAIR LEADS, NO CABLE ANGLE CHANGE. SUBMITTER STATES AIRFLOW CAUSES CABLES TO VIBRATE ON PULLEYS AND WEAR THROUGH STRANDS. 1 L 7 2 3O A25CE 1996061300382 19960613 00382 CE 1996 6 13 96ZZZX2948 1 19960522 G 2710 581510320CR CONTROL CABLE CESSNA 404 404CESSNA 2075901 CE AIL WS 92.28 WORN B APCR K NONE O OTHER IN INSP/MAINT 1 NM 01 41SA 547 4040023 ALL FOUR AILERON CABLES CONTINUALLY WEAR RAPIDLY AT PULLEYS IN WING TRAILING EDGE. PULLEYS ACT AS FAIR LEADS, NO CABLE ANGLE CHANGE. SUBMITTER STATES AIRFLOW CAUSES CABLES TO VIBRATE ON PULLEYS AND WEAR THROUGH STRANDS. 1 L 7 2 3O A25CE 1996061300383 19960613 00383 SO 1996 6 13 96ZZZX2949 1 19960405 G 3230 40336000 LINK PIPER PA31T PA31T1 7103126 SO NLG RT DRAG CRACKED D A K NONE O OTHER IN INSP/MAINT 1 NM 04 200FB 4970 31T7904037 CHECKED DRAG LINK FOR CRACKS AFTER READING REPORT IN AIRWORTHINESS ALERTS. PAINT HAD FAINT CRACK IN IT, SO PART WAS STR IPPED AND DYE CHECKED AT WHICH TIME A DEEP CRACK ACROSS THE FRONT END OF THE LEFT EAR WAS FOUND. DRAG LINK WAS REPLACED BY NEW PART AND NOSE GEAR RIGGED. 1 L 7 2 3T A8EA 1996061300384 19960613 00384 SO 1996 6 13 96ZZZX2950 1 19960503 G 2710 62102001 SUPPORT PIPER PA28 PA28140 7102802 SO RT AIL BELLCRANK CRACKED B A NCLR K NONE O OTHER IN INSP/MAINT 1 NE 01 6777W 4400 2820905 BELLCRANK SUPPORT WAS FOUND CRACKED AT THE FORWARD BOLT HOLE. LEFT AND RIGHT BELLCRANKS WERE NOT MAKING CONTACT WITH TH E AFT STOPS. STOPS WERE APPROXIMATELY .50 INCH AWAY FROM THE BELLCRANKS. BOTH BELLCRANKS APPEAR TO BE IMPROPERLY RIGGE D BECAUSE THE STOPS ARE ALMOST ALL THE WAY OUT OF THE NUT BEFORE THEY CONTACT THE BELLCRANK. 1 L 7 1 3O 2A13 1996061300385 19960613 00385 SO 1996 6 13 96ZZZX2951 1 19960429 G 2730 452855 BEARING PIPER PA38 PA38112 7103812 SO ELEV HORZ STAB MISMANUFACTURED D L A K NONE W F INADEQUATE Q C FLT CONT AFFECTED IN INSP/MAINT 1 SW 15 91BA 3878A0240 ORIGINAL BEARING WAS A BALL BEARING TYPE WITH PIPER PN 25704-00. PART NUMBER HAS BEEN SUPERCEDED ON PN 452-855. THE NE W REPLACEMENT BEARINGS ARE A ROD END TYPE OF BEARING. THE OUTSIDE DIAMETER OF THE ORIGINAL TYPE IS .686 INCH. THE NEW TYPE MEASURES .6875 INCH O.D. PRESSING THE NEW BEARING IN CAUSED THE REMOVAL OF MATERIAL IN THE INSIDE DIAMETER OF BEAR ING BOSSES. IT ALSO LOCKED UP THE BEARING AND CAUSED SEVERE STIFFNESS IN THE CONTROL YOKE WHICH, IN TURN, MADE CONTROLL ING THE PITCH OF ACFT DIFFICULT. (4 EACH REPORTS RECEIVED ON THIS P/N AND CONDITION). SUBMITTER STATED PIPER SHOULD RE TURN TO ORIGINAL TYPE BEARING OR PROVIDE FURTHER INSTRUCTIONS FOR SUCCESSFUL INSTALLATION OF NEW TYPE BEARING. 1 L 7 1 3O A18SO 1996061300386 19960613 00386 EA 1996 6 13 96ZZZX2952 2 19960501 G 8520 AL12186 NUT PIPER PA32 PA32301 7103207 SO LYC O540 IO540K1G5 41532 EA CON ROD BOLT MISMANUFACTURED H L K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 99 2586Y 328506007 L2254348A ASSEMBLING THIS ENGINE DURING NORMAL OVERHAUL, THE ROD BOLT NUT WAS TORQUED AND THE BOLT MEASURED FOR STRETCH LENGTH. T HE MICROMETER DID NOT SMOOTHLY SNUG UP. THE BOLT'S OUTBOARD EDGE MEASURED 2.255 INCHES AND INBOARD EDGE MEASURED, 2.259 INCHES. BELIEVING THE BOLT TO BE DEFECTIVE, IT WAS REMOVED. WHEN SPUN, THE NUT HAD A WOBBLE. INSPECTION FOUND THE TH READS OF THE NUT WERE NOT SQUARE WITH THE FACE AND THIS CAUSED THE BOLT TO BE BENT WHEN TORQUED. THE BOLT WAS STRAIGHT WHEN UNTORQUED. REPLACED BOTH THE NUT AND BOLT WITH NEW PARTS. 1 L 7 1 3O 3 O A3SO 1E4 1996061300387 19960613 00387 SO 1996 6 13 96ZZZX2953 1 19960510 G 2710 CONTROL CABLE MAULE M5 M5235C 5460135 SO LEFT AILERON MISROUTED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 NE 01 10SY 528 7487C DURING ANNUAL INSPECTION, LT AILERON CABLE WAS FOUND ROUTED OVER LIFT STRUT BRACKET. THESE CABLES ARE PART OF SB 12, BU T NOT LISTED FOR THIS MODEL AIRCRAFT. CABLE WAS REMOVED AND INSPECTED FOR DAMAGE. NONE WAS FOUND. CABLE HAD 84 HRS TI ME SINCE REASSEMBLY OF WINGS. CABLE REINSTALLED AND CORRECT CABLE TENSION SET. 1 H 7 1 3O 3A23 1996061300388 19960613 00388 CE 1996 6 13 96ZZZX2954 1 19960521 G 5711 35410158 SPAR BEECH 35 A35 1151504 CE AFT CARRY THRU CORRODED D A K NONE O OTHER IN INSP/MAINT 1 NM 08 8426A 4505 D1863 DURING ANNUAL INSPECTION, MECHANIC BEGAN TO REPAIR FLOORBOARD UNDER FUSELAGE AUXILIARY FUEL TANK. UPON REMOVAL OF AUXIL IARY FUEL TANK AND FLOORBOARD, DISCOVERED THE REAR CARRY-THROUGH SPAR WAS CORRODED BEYOND REPAIR. MECHANIC NOTES THAT A CCESS TO THIS AREA FOR ROUTINE INSPECTION IS NOT ACCESSIBLE. MECHANIC SUGGESTS INSTALLATION OF INSPECTION PANELS IN THI S AREA TO ALLOW VISUAL INSPECTION CAPABILITIES OF REAR CARRY-THROUGH SPAR AFT FACE. 1 L 7 1 3O A777 1996061300389 19960613 00389 SO 1996 6 13 96ZZZX2955 1 19960426 G 7160 P151936 AIR FILTER DONALDSON PIPER PA46 PA46310P 7104605 SO INDUCT AIR SEAL SEPARATION D K NONE W INADEQUATE Q C IN INSP/MAINT 1 EA 05 6908P 468508062 FOUND AIR FILTER, PN B13151936, MATING FOAM SEAL ONE-THIRD UNGLUED WHEN REMOVED FROM NEW SHIPPING BOX. SUBMITTER STATES THIS IS THE SAME PROBLEM TYPE AS BRACKETT MFG SEAL (AD 95-03-02). 1 L 7 1 3O A25SO 1996061300390 19960613 00390 SO 1996 6 13 96ZZZX2956 1 19960520 G 2710 62102001 SUPPORT PIPER PA28 PA28140 7102802 SO RT AIL BELLCRANK CRACKED B NCLR K NONE O OTHER IN INSP/MAINT 1 NE 01 38194 2840 287725268 SUPPORT WAS FOUND CRACKED AT THE FORWARD BOLT HOLE. LEFT AND RIGHT BELLCRANKS WERE NOT MAKING CONTACT WITH THE AFT STOP S. STOPS WERE APPROXIMATELY .50 INCH AWAY FROM THE BELLCRANKS. BOTH BELLCRANKS APPEAR TO BE IMPROPERLY RIGGED BECAUSE THE STOPS ARE ALMOST ALL THE WAY OUT OF THE NUT BEFORE THEY CONTACT THE BELLCRANK. 1 L 7 1 3O 2A13 1996061300391 19960613 00391 SO 1996 6 13 96ZZZX2957 1 19960503 G 2710 67550000 SUPPORT PIPER PA28 PA28R180 7102809 SO RT AIL BELLCRANK CRACKED B NCLR K NONE O OTHER IN INSP/MAINT 1 NE 01 4573J 3453 28R30438 BELLCRANK SUPPORT FOUND CRACKED AT THE FORWARD BOLT HOLE. LEFT AND RIGHT BELLCRANKS WERE NOT MAKING CONTACT WITH THE AF T STOPS. STOPS WERE APPROXIMATELY .50 INCH AWAY FROM THE BELLCRANKS. BOTH BELLCRANKS APPEAR TO BE IMPROPERLY RIGGED BE CAUSE THE STOPS ARE ALMOST ALL THE WAY OUT OF THE NUT BEFORE THEY CONTACT THE BELLCRANK. 1 L 7 1 3O 2A13 1996061300392 19960613 00392 SW 1996 6 13 96ZZZX2958 1 19960515 G 2823 506251 VALVE AIRTRC AT500 AT501 SW FUEL SELECT FAILED D A K NONE O OTHER IN INSP/MAINT 1 SW 07 1006T 1355 5010030 DURING OPERATIONS FOR WEIGHT & BAL PURPOSES, FUEL VALVE TURNED TO 'OFF'. AS VALVE WAS BEING TURNED BACK TO 'ON', IT BEC AME STUCK IN INTERMEDIATE POS. LINKAGE BTWN COCKPIT & VALVE CHKD & FND IN PROPER ORDER. AFTER 2 OR 3 ATTEMPTS, VALVE R ETND TO 'ON'. WHILE PERFORMING A COLD FUEL TEST, VALVE AGAIN BECAME STUCK & COULD NOT BE RETND TO OPEN. AFTER SEVERAL ATTEMPTS, VALVE WAS RETND TO OPEN. FUEL BOOST PUMP TURNED ON BUT COULD NOT GET FUEL TO ENG LINE. VALVE REMVD & COVER P LATE REMVD FROM VALVE. CAM THAT POSITIONS INTERNAL PLUNGERS BROKEN & JAMMED IN OUTLET PORT. PLUNGERS BEING SPRING LOAD ED TO CLOSED POS WERE PREVENTING FUEL TO FLOW TO ENG. HAD MALFUNCTION OCCURRED DURING FLIGHT, ENG WOULD HAVE QUIT. 1 L 7 1 3T NC A17SW 1996061300393 19960613 00393 CE 1996 6 13 96ZZZX2959 1 19960516 G 5711 SPAR CESSNA 500 550 2076604 CE LOWER CAP CORRODED B P GQVR K NONE O OTHER IN INSP/MAINT 1 SW 05 45ME 9941 5500080 UPON REMOVING A SKIN PANEL FROM RT WING AFT OF LANDING GEARWELL TO FACILITATE REPAIR OF SMALL CRACKS IN WING SKIN, DISCO VERED CORROSION ON LOWER AFT SPAR CAP FROM WING ROOT TO WS 74.5. REMOVED CORROSION FROM AFFECTED AREAS OF SPAR CAP AFTE R CONTACTING CESSNA ENGINEERING FOR APPROVAL. DEPTH OF CORRODED AREAS WAS UP TO 20 PERCENT OF SPAR CAP THICKNESS FROM W S 31.00 TO WS 34.00 AND 10 PERCENT OF SPAR CAP THICKNESS FROM WS 34.00 TO WS 74.5. THERE WAS NO OBVIOUS REASON FOR CORR OSION IN THIS AREA. THE SAME WING SKIN SECTION WAS REMOVED FROM LT WING AND NO CORROSION NOTED ON LT LOWER AFT SPAR CAP . 1 L 7 2 4F A22CE 1996061300394 19960613 00394 NE 1996 6 13 96ZZZX2960 2 19960514 G 8550 CYLINDER SCWZER G164 G164A 3952704 EA PWA R1340 R1340AN1 52016 NE NR 8 CRACKED H S MWRG A UNSCHED LANDING E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CL CLIMB 1 EA 17 6620Q 1693 10419 PILOT EXPERIENCED POPPING, MISFIRING, AND POWER LOSS DURING TAKEOFF. AN UNSUCCESSFUL OFF AIRPORT LANDING MADE. AIRCRAF T FLIPPED OVER AND WAS SUBSTANTIALLY DAMAGED. INSPECTION REVEALED NR 8 CYLINDER CRACKED BETWEEN SPARK PLUG BOSSES AND D OWN TO BARREL ON BACK SIDE OF CYLINDER. AIRCRAFT HAD BEEN OPERATED SEVERAL TIMES DURING AG OPERATIONS ON THIS DAY. SMO H: 930.0 HRS. 1 Q 7 1 3R 3 R 1A16 5E2 1996061300395 19960613 00395 GL 1996 6 13 96ZZZX2961 3 19960517 G 6111 BLADE BEECH 100 B100 1152919 CE HARTZL HCB4T HCB4TN5 GL PROP BACKSIDE CRACKED D L A K NONE O OTHER IN INSP/MAINT 1 SO 06 86TR 1910 BE22 CD1028 CORPORATE TECHNICIAN NOTICED A FLAW IN BACKSIDE OF A PROPELLER BLADE. UPON FURTHER INSPECTION, FLAW WAS DISCOVERED TO B E A CRACK APPROXIMATELY 3.25 INCHES IN LENGTH, AND 14.3750 INCHES FROM THE TIP OF THE BLADE. CRACK SPAN WIDTHWISE, AND COULD BE SEEN TO OPEN UP WHEN BLADE WAS FLEXED BY HAND. PROPELLER BLADE SPANS ONLY 7 INCHES AT POSITION OF CRACK. CRAC K WAS APPROXIMATELY CENTER OF BLADE, AND HAS NOT PROPAGATED TO THE LEADING AND TRAILING EDGES. ALSO, CRACK CANNOT BE SE EN OR DETECTED WITH EDDY CURRENT MACHINE ON THE FACE SIDE OF THE PROPELLER BLADE. 1 L 7 2 4T A14CE 6 C P40EA 1996061300396 19960613 00396 CE 1996 6 13 96ZZZX2962 1 19960510 G 2435 1013690113 TERMINAL STUD LEARSIEGLER 23048016 BEECH 200 200BEECH 1152920 CE START/GEN THREADS WEAR D K NONE O OTHER IN INSP/MAINT 1 GL 03 971LL 11727 BB572 WHEN INSTALLING PLASTIC TERMINAL COVER, COVER HOLD-DOWN NUTS TEND TO WEAR THREADS ON STUDS CAUSING THE TERMINAL NUT TO S TRIP THE STUD UPON NEXT INSTALLATION. TIMES UNKNOWN, SHOULD NOT BE A FACTOR. 1 L 7 2 4T A24CE 1996061300397 19960613 00397 CE 1996 6 13 96ZZZX2963 1 19960522 G 2931 156739XP500 GAUGE AMETEK BEECH 200 200BEECH 1152920 CE ACCUM IND WORN B LX5R K NONE O OTHER IN INSP/MAINT 1 GL 19 981LL 388 N9837C BB602 GAUGE MOVEMENT VERY LOOSE CAUSING NEEDLE TO SLIP TOWARD HIGHER READING. 1 L 7 2 4T A24CE 1996061300398 19960613 00398 CE 1996 6 13 96ZZZX2964 1 19960501 G 3244 226K083 TIRE CESSNA 650 650 2076802 CE MLG DEFECTIVE B IW1R O OTHER J WARNING INDICATION CL CLIMB 1 EA 25 650SB 231 71260982 6500018 ON TAKEOFF FROM PBI, GEAR UNSAFE LIGHT REMAINED ON WHEN GEAR WAS RETRACTED. OPERATOR FLEW BY TOWER FOR CONDITION CHECK. GEAR WAS REPORTED UP AND LOCKED. AFTER SEVERAL GEAR CYCLES, GEAR UNSAFE LIGHT WENT OUT. AFTER LANDING AT MORRISTOWN, NR 2 TIRE FOUND TO HAVE OUTER BEAD SEPARATION, AND DAMAGED FLAP AND GEAR UPLOCK SWITCH. AIRCRAFT TOTAL TIME, 3,691.2 H RS. LANDINGS, 145. 2 L 7 2 4F A9NM 1996061300399 19960613 00399 SO 1996 6 13 96ZZZX2965 1 19960529 G 2910 SOLENOID VALVE GULSTM G1159 G1159 3953505 SO HYDRAULIC SYSTEM SEAL LEAK B GJQR K NONE K FLUID LOSS IN INSP/MAINT 1 NM 01 26WP 339 1081 024 AIRCRAFT RETURNED FROM A FLIGHT AND WHILE UNLOADING BAGGAGE, A SKYDROL FLUID LEAK WAS NOTED NEAR BATTERY COMPARTMENT. I NVESTIGATION REVEALED SEAL BLOWN OUT WHERE VALVE BODY AND SOLENOID MEET. REPLACED VALVE ASSEMBLY. SUBMITTER SUSPECTS P ROBLEM OCCURRED AS A RESULT OF THREAD BURR RESULTING IN IMPROPER OR INCOMPLETE ASSEMBLY LETTING O-RING SEAL TO BLOW OUTW ARD. 2 L 7 2 4F RT A12EA 1996061300400 19960613 00400 NM 1996 6 13 96ZZZX2966 1 19960501 G 5313 KEEL STRINGER BOEING 727 727243 138408D NM FS 950A S29R CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 34415 22167 DURING C-10 CHECK, NOTED KEEL STRINGER S29R HAS INTERGRANULAR CORROSION EXTENDING FROM STA 950A TO STA 950D. 2 L 7 3 4F RT A3WE 1996061300401 19960613 00401 NM 1996 6 13 96ZZZX2967 1 19960501 G 5313 STRINGER BOEING 727 727243 138408D NM FS 480-500 S28R CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 34415 22167 DURING A C-10 INSPECTION, STRINGER S28R, BETWEEN STA 480 AND STA 500, WAS NOTED TO HAVE HEAVY INTERGRANULAR CORROSION. 2 L 7 3 4F RT A3WE 1996061300404 19960613 00404 SO 1996 6 13 96ZZZX2970 1 19960501 G 3213 583831 GEAR LEG LUSCOM 8 8A 8190104 SO MLG RT CRACKED G S O OTHER O OTHER LD LANDING 1 SW 99 93CK 1476 4036 LOWER GEAR LEG CRACKED AT BOLT HOLE AT ATTACHMENT TO UPPER ARM ASSEMBLY. CRACK CAUSED GEAR LEG TO FAIL ON LANDING. CRA CK WAS NOT DETECTED BECAUSE OF SKI ATTACHMENT BRACKET COVERING GEAR LEG AT THIS AREA. SUBMITTER SUGGESTS FOR MECHANIC T O INSPECT BOLT HOLE AREAS FOR CRACKING. 1 H 7 1 3O A694 1996061300405 19960613 00405 CE 1996 6 13 96ZZZX2971 1 19960515 G 5341 08113508 FITTING CESSNA 402 402C 207590R CE WING ATTACH CORRODED C S K NONE O OTHER IN INSP/MAINT 1 EA 01 121PB 12316 402C0507 DURING ROUTINE INSPECTION, NOTED LOWER FORWARD CARRY-THROUGH SPAR FITITNG EXFOLIATING DUE TO INTERGRANULAR CORROSION. 1 L 7 2 3O A7CE 1996061300406 19960613 00406 SO 1996 6 13 96ZZZX2972 1 19960517 G 5320 18110 BRACKET LUSCOM 8 8A 8190104 SO NR 8 BULKHEAD CRACKED D S K NONE O OTHER IN INSP/MAINT 1 SW 05 25236 1411 FOUND CRACK IN FLANGE OF PART WHERE LOWER RUDDER HINGE ATTACH BOLT PASSES THROUGH PART. SUBMITTER STATED CAUSED BY FLEX ING OF PART IN NORMAL USE. LATER STYLE II SERIES LUSCOMBES USED DIFFERENT DESIGN TO DISTRIBUTE STRESS BETTER. 1 H 7 1 3O A694 1996061300407 19960613 00407 CE 1996 6 13 96ZZZX2973 1 19960517 G 3250 12606311 ROD END CESSNA 206 U206G 2073356 CE NLG STEERING BROKEN D S A O OTHER O OTHER TX TAXI/GRND HDL 1 NE 05 756HK 1068 U20604102 PILOT HEARD A LOUD NOISE WHILE TAXIING AFTER LANDING. HE ALSO NOTICED LOSS OF NOSE WHEEL STEERING AND VERY FREE MOVEMEN T OF RUDDER CONTROL. INVESTIGATION FOUND THE ROD END ON AFT STEERING BUNGEE HAD BROKEN OFF AND TRIM CHAIN WAS OFF OF SP ROCKET. THIS IS THE SECOND INCIDENCE KNOWN OF THIS HAPPENING ON THIS AIRCRAFT. THERE HAVE BEEN 2 OTHER INCIDENCES OF T HIS ON OTHER AIRCRAFT. SUBMITTER STATED THE PROBLEM COULD BE FROM IMPROPER GROUND HANDLING, BUT SUSPECT THE DIAMETER .2 5 INCH IS VERY SMALL FOR THE DEMANDS PUT ON IT. 1 H 7 1 3O A4CE 1996061300408 19960613 00408 CE 1996 6 13 96ZZZX2974 1 19960515 G 5740 951100171 FITTING BEECH 58 58 1152740 CE LT OTBD WING DAMAGED B S EHHR K NONE W INADEQUATE Q C IN INSP/MAINT 1 EA 17 7353R TH486 WHEN PERFORMING 5-YEAR WING BOLT AND FITTING INSPECTION, DISCOVERED THE LOWER AFT RADIUS WASHERS, PN 95-110025-1, WERE N OT INSTALLED. INSTEAD, 2 EACH, PN NAS143-12, WASHERS WERE INSTALLED. WHEN TORQUED, THE WASHERS MADE IMPRESSIONS IN BOT H LOWER AFT OUTBOARD FITTINGS. 1 L 7 2 3O 3A16 1996061300409 19960613 00409 CE 1996 6 13 96ZZZX2975 1 19960515 G 5740 951100172 FITTING BEECH 58 58 1152740 CE RT OTBD WING DAMAGED B EHHR K NONE W INADEQUATE Q C IN INSP/MAINT 1 EA 17 7353R TH486 WHEN PERFORMING 5-YEAR WING BOLT AND FITTING INSPECTION, DISCOVERED THE LOWER AFT RADIUS WASHERS, PN 95-110025-1, WERE N OT INSTALLED. INSTEAD, 2 EACH, PN NAS143-12, WASHERS WERE INSTALLED. WHEN TORQUED, THE WASHERS MADE IMPRESSIONS IN BOT H LOWER AFT OUTBOARD FITTINGS. 1 L 7 2 3O 3A16 1996061300410 19960613 00410 EA 1996 6 13 96ZZZX2976 2 19960423 G 7322 105135 CARBURETOR ARM FACET PIPER PA28 PA28161 7102803 SO LYC O320 O320D3G 41508 EA THROTTLE DETACHED H K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 05 3457Q 250 CK815086 287716157 L732439A CARBURETOR THROTTLE ARM CAME LOOSE FROM THROTTLE SHAFT DUE TO ATTACHMENT NUT LOOSENING OFF OF ARM. THE SUSPECT CAUSE OF THE NUT COMING LOOSE WAS IMPROPER INSTALLATION OF KOTTER KEY INTO NUT. 1 L 7 1 3O 3 O 2A13 E274 1996061300411 19960613 00411 SO 1996 6 13 96ZZZX2977 2 19960514 G 7414 1051324 SPRING 10400307 CESSNA 182 182C 2072708 CE CONT O470 O470R 17026 SO MAG IMPULSE COUP BROKEN D K NONE O OTHER IN INSP/MAINT 1 NM 01 8617T 7 52517 988558RR TWO NEW SNAP-RING COUPLINGS INSTALLED AT ANNUAL INSPECTION. SEVEN HOURS LATER BOTH COUPLING SPRINGS FAILED ON CONSECUTI VE ENGINE STARTS. SPRING FAILURES APPEAR TO BE IDENTICAL. COUPLINGS WERE BOUGHT AND INSTALLED AS ASSEMBLIES PREVENTING INSPECTION OF SPRINGS PRIOR TO INSTALLATION. 1 H 7 1 3O 3 O NT 3A13 E273 1996061300412 19960613 00412 CE 1996 6 13 96ZZZX2978 1 19960521 G 3230 20846007 BUNGEE ARM PIPER PA24 PA24180 7102402 CE MLG CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 01 7114P 242272 FOUND BOTH LANDING GEAR BUNGEE ARMS CRACKED AT PIN SLOTS AND WELDED ATTACHMENT AREA. CRACKS APPEARED TO HAVE EXISTED FO R SOME TIME, JUDGING BY APPEARANCE. REPLACED BOTH BUNGEE ARMS WITH NEW PARTS, LT W20846-006, RT W20846-007. SUSPECT CA USE OF CRACKS APPEARS TO BE AGE-FATIGUE. THE ONLY WAY OF BEING SURE PART IS NOT CRACKED IS TO REMOVE BUNGEE ARMS COMPLE TELY FOR VISUAL INSPECTION. 1 L 7 1 3O NT 1A15 1996061300413 19960613 00413 CE 1996 6 13 96ZZZX2979 1 19960521 G 3230 20846006 BUNGEE ARM PIPER PA24 PA24180 7102402 CE MLG CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 01 7114P 242272 FOUND BOTH LANDING GEAR BUNGEE ARMS CRACKED AT PIN SLOTS AND WELDED ATTACHMENT AREA. CRACKS APPEARED TO HAVE EXISTED FO R SOME TIME, JUDGING BY APPEARANCE. REPLACED BOTH BUNGEE ARMS WITH NEW PARTS, LT W20846-006, RT W20846-007. SUSPECT CA USE OF CRACKS APPEARS TO BE AGE-FATIGUE. THE ONLY WAY OF BEING SURE PART IS NOT CRACKED IS TO REMOVE BUNGEE ARMS COMPLE TELY FOR VISUAL INSPECTION. 1 L 7 1 3O NT 1A15 1996061300414 19960613 00414 SO 1996 6 13 96ZZZX2980 1 19960419 G 2820 11141760124 FUEL LINE PIPER PA28 PA28180 7102808 SO FUEL TANK DETERIORATED D K NONE O OTHER IN INSP/MAINT 1 EA 05 1261T 2670 287205273 PIPER CHEROKEE FUEL TANKS WERE PULLED TO PUT NEW GASKETS ON THE FUEL QUANTITY SENDERS. AT THIS TIME, THE FUEL LINES (ST RATOFLEX FLEXIBLE HOSE) WERE FOUND CHAFED, RUSTED, AND VERY BRITTLE. WHEN THE ONE HOSE WAS FLEXED, IT BROKE IN HALF. B OTH HOSES WERE ORIGINAL EQUIPMENT WITH DATE CODES OF 2/72. SUBMITTER RECOMMENDS THAT ALL TANKS OF THIS TYPE (PA-32-34-4 4) BE PULLED AND CHECKED FOR THIS CONDITION. 1 L 7 1 3O 2A13 1996061300677 19960613 00677 CE 1996 6 13 96ZZZX2981 1 19960424 G 2840 1200106263 LINE CESSNA 210 210M 2073450 CE INST PANEL GAUGE CHAFED D K NONE K FLUID LOSS IN INSP/MAINT 1 SO 09 823AR 21062661 ROUTINE MAINTENANCE, NOTICED FUEL DRIPPING ONTO FLAP HANDLE WIRING BEHIND INSTRUMENT PANEL. INVESTIGATION FOUND LINE CH AFING ON ADF RADIO RACK. THIS LINE RUNS FROM FIRE WALL TO FUEL PRESSURE GAUGE. TOTAL TIME ON AIRFRAME 11,404 HRS. TT ON PART, UNKNOWN. 1 H 7 1 3O 3A21 1996061300678 19960613 00678 SO 1996 6 13 96ZZZX2982 1 19960427 G 6120 CONTROL SHAFT HARTZL F27A PIPER PA28 PA28R200 7102811 SO PROPELLER GOV NUT BACKED OFF G O OTHER K FLUID LOSS CR CRUISE 1 GL 15 33047 1671 4961W 28R7535111 DURING FLIGHT, CONTROL SHAFT NUT BACKED OUT CAUSING LOSS OF ENGINE OIL AND SUBSEQUENT ENGINE DESTRUCTION. IT HAS BEEN D ETERMINED THE CONTROL SHAFT GASKET WAS NOT PROPERLY BENT TO PROVIDE A MEANS TO SAFETY THE CONTROL SHAFT NUT TO PREVENT I T FROM LOOSENING/BACKING OFF. ITEM 18, PN B-4739, IN HARTZELL MANUAL. 1 L 7 1 3O 2A13 1996061300679 19960613 00679 CE 1996 6 13 96ZZZX2983 1 19960430 G 3230 504501019 TORQUE TUBE CESSNA 340 340A 2076405 CE LT MLG WELD BROKEN E A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 NM 05 1920E 5406 340A0669 LEFT MAIN GEAR WOULD NOT RETRACT AFTER TAKEOFF. PILOT EXTENDED GEAR AND RETURNED TO AIRPORT. INSPECTED LT GEAR RETRACT ION LINKAGE, AND FOUND AFT FORK ASSY WELD BROKEN AND TUBE WITH SPIRAL TEAR. SUBMITTER SUGGESTS FATIGUE TO WELDED AREA, WEAKENING SURROUNDED AREA. AREA SHOULD BE INSPECTED AT EACH INSPECTION. 1 L 7 2 3O 3A25 1996061300681 19960613 00681 EU 1996 6 13 96ZZZX2985 1 19960520 G 2150 ES611301 BLOWER MOTOR SLNSBY T67 T67M260 8323006 EU AIR COND FAILED D K NONE O OTHER IN INSP/MAINT 1 SW 17 100 SUBMITTER REPORTS SEVERAL CONDENSER BLOWER MOTORS QUIT. SEVEN INSPECTED MOTORS FOUND BRUSHES COMPLETELY WORN. SUBMITTE R STATES NO RECOMMENDATIONS AT THIS TIME. (ALL HAVE HAD LESS THAN 100 HRS, TT). 1 L 7 1 3O NT A73EU 1996061300682 19960613 00682 CE 1996 6 13 96ZZZX2986 1 19960520 G 7810 991029521 EXHAUST RISER CESSNA 404 404CESSNA 2075901 CE SLIP JOINT MISOVERHAULED B APCR K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 01 48SA 4040417 RECEIVED OVERHAULED EXHAUST RISER FROM OVERHAULER. DURING INSPECTION PRIOR TO INSTALLATION, FOUND MOUTH FOR SLIP JOINT MANUFACTURED TOO SMALL AND NOT ALLOWING SLIP JOINT TUBE TO SLIDE IN. SUSPECT CAUSE IS POOR MANUFACTURING AND QUALITY CO NTROL PRACTICES. SUBMITTER RECOMMENDS COMPANY CHECK THEIR WORK BEFORE IT IS TAGGED OVERHAULED AND SHIPPED. 1 L 7 2 3O A25CE 1996061300683 19960613 00683 CE 1996 6 13 96ZZZX2987 1 19960417 G 2750 086210051 ACTUATE ROD CESSNA 320 320E 2074514 CE RT INBD FLAP BENT D K NONE F FLT CONT AFFECTED IN INSP/MAINT 1 WP 01 3439Q 3568 320E0039 RIGHT INBOARD FLAP ACTUATING RODS FOUND BENT DURING AN ANNUAL INSPECTION. PILOT COMPLAINED OF AIRCRAFT ROLLING LEFT WHE N FLAPS DEPLOYED ZERO DEGREES TO 15 DEGREES. AD SEARCH FOUND AIRCRAFT NOT PLACARDED TO 140 MPH FOR FLAP DEPLOYMENT FROM 15 DEGREES TO 35 DEGREES (MAXIMUM SPEED). AIRCRAFT PLACARDED AND RODS REPLACED. 1 L 7 2 3O 3A25 1996061300684 19960613 00684 CE 1996 6 13 96ZZZX2988 1 19960417 G 2750 086210050 ACTUATE ROD CESSNA 320 320E 2074514 CE RT INBD FLAP BENT D K NONE F FLT CONT AFFECTED IN INSP/MAINT 1 WP 01 3439Q 3568 320E0039 RIGHT INBOARD FLAP ACTUATING RODS FOUND BENT DURING AN ANNUAL INSPECTION. PILOT COMPLAINED OF AIRCRAFT ROLLING LEFT WHE N FLAPS DEPLOYED ZERO DEGREES TO 15 DEGREES. AD SEARCH FOUND AIRCRAFT NOT PLACARDED TO 140 MPH FOR FLAP DEPLOYMENT FROM 15 DEGREES TO 35 DEGREES (MAXIMUM SPEED). AIRCRAFT PLACARDED AND RODS REPLACED. 1 L 7 2 3O 3A25 1996061300685 19960613 00685 CE 1996 6 13 96ZZZX2989 1 19960512 G 2510 S20415016 RESISTOR CESSNA 172 172P 2072436 CE LIGHTER CIRCUIT DAMAGED D K NONE O OTHER NR NOT REPORTED 1 GL 03 53111 8718 17274685 CIGAR LIGHTER WAS WIRED TO THE LANDING LIGHT CIRCUIT BREAKER. THE RESISTOR WAS WIRED TO A GROUND ON ONE END AND TO THE 7.5 AMP FUSE HOLDER, THEN TO THE BUS BAR. THERE WAS NO FUSE IN THE FUSE HOLDER. WHEN THE CONTACTS IN THE FUSE HOLDER T OUCHED, THE CURRENT (UNPROTECTED) CAUSED THE RESISTOR TO FAIL AND BLOW ONE END OUT. THE LOOSE END BURNED 2 WIRES RUNNIN G UNDER THE CIRCUIT BREAKERS, BEHIND THE PANEL. IT WAS DECIDED IT WOULD BE BEST TO REMOVE ALL ASSOCIATED COMPONENTS AND WIRING. 1 H 7 1 3O NT 3A12 1996061300686 19960613 00686 CE 1996 6 13 96ZZZX2990 1 19960524 G 2460 CM358950 SWITCH CESSNA 402 402C 207590R CE AVIONICS MASTER FAILED C O OTHER O OTHER CL CLIMB 1 NE 01 7037E 13100 402C0471 AFTER TAKEOFF, AIRCRAFT EXPERIENCED COMPLETE AVIONICS ELECTRICAL FAILURE DUE TO AVIONICS MASTER SWITCH FAILURE. EMERGEN CY AVIONICS BUS WAS ACTIVATED AND POWER WAS RESTORED. 1 L 7 2 3O A7CE 1996061300687 19960613 00687 CE 1996 6 13 96ZZZX2991 1 19960417 G 5312 08130228 BULKHEAD CESSNA 320 320E 2074514 CE FS 27.25 CRACKED D K NONE O OTHER IN INSP/MAINT 1 WP 01 3439Q 3568 320E0039 DURING ANNUAL INSPECTION, RT BULKHEAD AT FS 27.25 WAS FOUND CRACKED. THIS AND THE OPPOSITE PART ON THE LT SIDE ARE WHER E THE NLG STEERING CABLES ATTACH VIA STEEL PULLEY BRACKETS. SUBMITTER SUGGESTS MFG EITHER PRODUCE REINFORCEMENT KIT OR STRENGTHEN NEW COMPONENTS. PART WAS REPLACED WITH A SERVICEABLE BULKHEAD OF THE SAME PART NUMBER. 1 L 7 2 3O 3A25 1996061300688 19960613 00688 EA 1996 6 13 96ZZZX2992 2 19960419 G 8520 LIFTER BODY CESSNA 172 172P 2072436 CE LYC O320 O320D2J 41508 EA NR 2 CYL EXHAUST COLLAPSED D O OTHER E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CR CRUISE 1 GL 03 89594 46 17276009 L1253439A 45.9 HOURS AFTER OVERHAUL, PILOT FLYING AN X-C EXPERIENCED VERY ROUGH ENGINE. AFTER TROUBLESHOOTING ALL POSSIBLE ASPECT S, FOUND NR 2 CYLINDER EXHAUST HYDRAULIC LIFTER COLLAPSED AND DAMAGED PUSH ROD. A NEW LIFTER AND PUSH ROD WAS INSTALLED . OPS CHECK WAS PERFECT. 20 MINUTES INTO RETURN FLIGHT, SAME ROUGHNESS OCCURRED. FURTHER INVESTIGATION REVEALED .50 I NCH OF LIFTER BODY WAS BROKEN WHICH CAUSED THE TAPPET TO FLOP AROUND AND NOT GET ANY OIL. ALL 8 LIFTER BODIES WERE SENT TO LYCOMING FOR INSPECTION. 1 H 7 1 3O 3 O NT 3A12 E274 1996061300689 19960613 00689 EU 1996 6 13 96ZZZX2993 1 19960514 G 3230 Z00N7733690395 RELAY SOCATA TB20 TB20TRINIDAD 8680695 EU MLG FAILED D O OTHER J WARNING INDICATION AP APPROACH 1 GL 11 20FF 1032 ON APPROACH, OPERATOR ATTEMPTED TO LOWER GEAR. GEAR DID NOT RESPOND. SEVERAL ATTEMPTS WERE MADE TO LOWER GEAR NORMALLY . GEARS WERE THEN LOWERED WITH EMERGENCY GEAR EXTENSION HANDLE. BOTH MAIN GEARS WERE DOWN AND LOCKED, BUT NOSE GEAR WO ULD NOT LOCK DOWN. OPERATOR SUBSEQUENTLY MADE AN EMERGENCY LANDING WHERE NOSE GEAR FAILED. TROUBLESHOOTING REVEALED TH AT CAUSE OF NORMAL GEAR EXTENSION FAILURE WAS THE RESULT OF THE UP RELAY FAILING IN THE CLOSED POSITION. NOSE GEAR EXTE NSION FAILURE IN EMERGENCY CONFIGURATION WAS CAUSED BY ONE OF THE TWO NOSE GEAR EMERGENCY COMPENSATING ACTUATORS HAVING LOST ITS CHARGE. 1 L 7 1 3O RT A51EU 1996061300690 19960613 00690 EU 1996 6 13 96ZZZX2994 1 19960517 G 3232 Z00N7070110709 ACTUATOR SOCATA TB20 TB20TRINIDAD 8680695 EU NLG EXTENSION LOST CHARGE D O OTHER J WARNING INDICATION AP APPROACH 1 GL 11 20FF 1032 ON APPROACH, OPERATOR ATTEMPTED TO LOWER GEAR. GEAR DID NOT RESPOND. SEVERAL ATTEMPTS WERE MADE TO LOWER GEAR NORMALLY . GEARS WERE THEN LOWERED WITH EMERGENCY GEAR EXTENSION HANDLE. BOTH MAIN GEARS WERE DOWN AND LOCKED, BUT NOSE GEAR WO ULD NOT LOCK DOWN. OPERATOR SUBSEQUENTLY MADE AN EMERGENCY LANDING WHERE NOSE GEAR FAILED. TROUBLESHOOTING REVEALED TH AT CAUSE OF NORMAL GEAR EXTENSION FAILURE WAS THE RESULT OF THE UP RELAY FAILING IN THE CLOSED POSITION. NOSE GEAR EXTE NSION FAILURE IN EMERGENCY CONFIGURATION WAS CAUSED BY ONE OF THE TWO NOSE GEAR EMERGENCY COMPENSATING ACTUATORS HAVING LOST ITS CHARGE. 1 L 7 1 3O RT A51EU 1996061300691 19960613 00691 SO 1996 6 13 96ZZZX2995 2 19960426 G 8530 625393 RETAINER PIPER PA46 PA46310P 7104605 SO CONT O520 TSIO520BE 17040 SO NR 6 CYL VALVE FRACTURED D K NONE O OTHER IN INSP/MAINT 1 EA 05 6908P 1350 468508062 528156 ON REMOVAL OF NR 6 CYLINDER DUE TO METAL FOUND IN OIL FILTER, FOUND PIECES IN ROCKER AREA. THIS WAS VERIFIED AS CONTAMI NANTS THROUGH T.C.M. NO SERVICE INFO ISSUED TO DATE ON AN ONGOING PROBLEM OF THIS PART. 1 L 7 1 3O 3 O A25SO E8CE 1996061300692 19960613 00692 CE 1996 6 13 96ZZZX2996 1 19960601 G 7920 HOSE BEECH 95 B95A 1153406 CE LYC O360 IO360B1A 41514 EA OIL COOLER CHAFE H A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 SW 99 10 GROUND PERSONNEL NOTED FUEL TYPE VAPORS TRAILING BEHIND TAXIING BEECH TRAVEL AIR. ACFT RETURNED TO AIRPORT. INVESTIGAT ION REVEALED VAPOR WAS, IN FACT, BURNING OIL FROM CHAFED THROUGH OIL LINES FROM COOLER. LINE WAS CHAFED AND BURNED THRO UGH BY UNSHIELDED EXHAUST. REPLACED OIL LINE WITH LONGER HOSE AND ADDED AN ADEL CLAMP, ROUTING HOSE FURTHER DOWN IN COW L. A NEW OIL HOSE HAD BEEN INSTALLED ONLY 10 HOURS PREVIOUSLY. 1 L 7 2 3O 3 O 3A16 1E10 1996061300693 19960613 00693 NE 1996 6 13 96ZZZX2997 2 19960517 G 8530 PISTON SCWZER G164 G164A 3952704 EA PWA R1340 R1340AN1 52016 NE NR 1 CYLINDER RING BROKE D A UNSCHED LANDING R K PARTIAL RPM/PWR LOSS FLUID LOSS NR NOT REPORTED 1 EA 17 6565 1921 722 38065 FIRST OR SECOND COMPRESSION RING BROKE CAUSING RING LANDS TO WEAR BETWEEN FIRST AND SECOND RING LAND AND THROUGH PISTON HEAD. COMBUSTION HEAT BURNED HOLE LARGER DIRECTING PRESSURE TO ENGINE CASE. THIS PRESSURE BLEW THE ENGINE OIL OVERBOAR D. THIS RESULTED IN AN EMERGENCY LANDING. 1 Q 7 1 3R 3 R 1A16 5E2 1996061300694 19960613 00694 NE 1996 6 13 96ZZZX2998 2 19960528 G 7322 67019 MIXTURE CONTROL BENDIX P012H4 DOUG DC3 DC3A 3021433 WP PWA R1830 R1830* 52020 NE CARB AUTO MIX MALFUNCTION H O OTHER M E R OVER TEMP VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CR CRUISE 1 SW 17 32MS 844 5682114A 4978 CYLINDER HEAD TEMPERATURE RUNNING HIGHER THAN NORMAL AND ENGINE ERRATIC WHEN AUTO LEAN SELECTED AT CRUISE. AMC TIME IN SERVICE, 843.9 HRS. 2 L 7 2 4R 4 R A669 5E4 1996061300695 19960613 00695 GL 1996 6 13 96ZZZX2999 3 19960409 G 6112 CLAMP CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL DE-ICE LEAD FAILED D K NONE O OTHER IN INSP/MAINT 1 GL 03 3UR 310R0061 760064 BOTH PROPS OVERHAULED ON 1-20-96 TO C/W AD 95-24-05, SB 209, SL 1993-11-OIL FILL-AT OVERHAUL. ALL 6 DE-ICER BOOT LEADS REPLACED. THESE LEADS APPEAR TO BE LARGER IN DIAMETER AND HEAVIER THAN LEADS REMOVED AT OVERHAUL. CABLE ENDS SECURED W ITH NR 6 ADEL CLAMP TO PROP HUB PER CESSNA MANUAL. AFTER APPROXIMATELY 20 HRS OPERATION, ALL 6 CLAMPS BROKE AT FLANGE B OLT HOLE AREA. REPLACED ALL 6 CLAMPS WITH LIKE PART AND THEY AGAIN BROKE AT APPROXIMATELY 4 HRS. AFTER REPLACEMENT, AP PEARS NEW CABLE IS HEAVIER THAN ORIGINAL AND CENTRIFUGAL FORCE IS CRACKING ORIGINAL CLAMPS. CURRENTLY REPLACING ORIGINA L ALUMINUM ADEL CLAMPS WITH STAINLESS STEEL ADEL CLAMPS. 1 L 7 2 3O 3A10 5 C P22EA 1996061300696 19960613 00696 1996 6 13 96ZZZX3000 4 19960515 G 3450 KNS80 R NAV SYS KING CESSNA 310 310R 2074245 CE COCKPIT NAV FAULTY D K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 13 6209X 17983 310R1339 PILOT REPORTED INOPERATIVE NAV/LOCALIZER ON 109.50 MHZ AND A LOUD SQUEAL IN AUDIO. PROBLEM WAS PECULIAR TO THAT FREQUEN CY AND DID NOT APPEAR IN OTHER NAV RADIO. DETERMINED PROBLEM TO BE IN THE UNIT AND NOT IN THE AIRCRAFT. TESTED 3 OTHER KNS-80'S AND ALL DISPLAYED SAME PROBLEM, ALTHOUGH IT WAS NOT BAD ENOUGH TO DEGRADE THE NAV PERFORMANCE. CONSULTED THE MANUFACTURER. MFG AWARE OF THE PROBLEM AND HAVE A FIX FOR IT. CONTACT LOCAL BENDIX/KING DEALER OR ALLIED SIGNAL FOR FU RTHER INFORMATION. SUBMITTER RECOMMENDS MFG RELEASE A SB AS SOON AS POSSIBLE. COULD BE A PROBLEM IN IMC. 1 L 7 2 3O 3A10 1996061300697 19960613 00697 EU 1996 6 13 96ZZZX3001 1 19960528 G 7921 96490432 COOLER LORINORDAM SLNSBY T67 T67M260 8323006 EU ENGINE OIL LEAK D K NONE K FLUID LOSS IN INSP/MAINT 1 SW 17 3192F 105 2228 AFTER FIRST FLIGHT OF THE DAY, AIR CREW NOTICED OIL ON WING WALK. COWLING WAS REMOVED AND OIL WAS SEEN DRIPPING FROM OI L COOLER FINS. REMOVED AND REPLACED OIL COOLER. 1 L 7 1 3O NT A73EU 1996061300698 19960613 00698 CE 1996 6 13 96ZZZX3002 1 19960531 G 2810 FUEL CAP CESSNA 182 182K 2072724 CE FUEL TANK FAULTY D K NONE O OTHER IN INSP/MAINT 1 CE 07 2836R 18258436 REMOVED ORIGINAL CESSNA FLUSH FUEL CAPS AND INSTALLED DOME CAPS WITH REDUCED OPENING. STC KIT SA 2376CE FC-1 (B). 1 H 7 1 3O NT 3A13 1996061300699 19960613 00699 CE 1996 6 13 96ZZZX3003 1 19960507 G 3230 12802091 PIN CESSNA 182 R182 2072734 CE NLG ACTUATOR BROKEN D O OTHER P NO WARNING INDICATION AP APPROACH 1 GL 15 1727R 3185 R18200537 WHEN GEAR WAS EXTENDED, NO GREEN LIGHT. EMERGENCY PROCEDURE, STILL NO GREEN LIGHT. NOSE GEAR COLLAPSED ON LANDING. FO UND DOWNLOCK PIN BROKEN AND MIGRATED INBOARD BLOCKING ACTUATOR FROM RETRACTING FULLY AND NOSE GEAR LOCKING. FOUND OTHER PIN ALSO BROKEN, BUT NOT MIGRATED OUT. 1 H 7 1 3O RT 3A13 1996061300700 19960613 00700 EA 1996 6 13 96ZZZX3004 2 19960503 G 8530 S117235TT67 VALVE CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA ENGINE EXHAUST FAILED D A UNSCHED LANDING Y ENGINE STOPPAGE CR CRUISE 1 GL 15 6132H 15284133 L2057015 INSTRUCTOR AND STUDENT WERE FLYING APPROXIMATELY 5 MILES FROM AIRPORT WHEN THE ENGINE FAILED. BY ADJUSTING MIXTURE, THE INSTRUCTOR WAS ABLE TO GET THE ENGINE RUNNING AGAIN (1,600 RPM) WHICH GOT THEM BACK TO THE AIRPORT. THE ENGINE WAS GIV EN A COMPRESSION CHECK AND FOUND TO HAVE A FAILED EXHAUST VALVE WHICH BROKE OFF AT THE BOTTOM OF THE STEM. TSMOH WAS 1, 917.5 HRS. 1 H 7 1 3O 3 O NT 3A19 E223 1996061300701 19960613 00701 1996 6 13 96ZZZX3005 4 19960515 G 3452 001560033 RESISTOR KING KT76A HI VOLT BLEED DEFECTIVE D K NONE O OTHER IN INSP/MAINT 1 GL 13 SUBMITTER NOTED SEVERAL INSTANCES OF DEFECTIVE HIGH VOLTAGE BLEEDER RESISTORS IN THE KT-76A, ESPECIALLY THE HIGHER SERIA L NUMBER UNITS. FOUND THE FIRST ONE THE HARD WAY, ZAPPED WHILE PUTTING UNIT TOGETHER. THIS DOES NOT POSE A FLIGHT HAZA RD, BUT CAN BE DANGEROUS TO AN UNWARY TECHNICIAN. 1996061300702 19960613 00702 CE 1996 6 13 96ZZZX3006 1 19960502 G 3213 12414231 SADDLE CESSNA 210 T210F 2073422 CE MLG CRACKED B CGFR K NONE O OTHER IN INSP/MAINT 1 GL 03 6782R 660 T2100182 DUE TO THE RELATIVELY LOW TOTAL TIME ON THIS AIRCRAFT (1,399 HRS) AND THE FACT THE LANDING GEAR SADDLES HAD BEEN REPLACE D AT 739 HOURS, AD 76-14-07 R2 DID NOT APPLY AT THIS TIME, HOWEVER, THE PART IN QUESTION HAD A CRACK THAT WAS EVIDENT WI THOUT DYE PENETRANT INSPECTION AND WOULD HAVE EVENTUALLY FAILED LEADING TO A GEAR UP LANDING. 1 H 7 1 3O 3A21 1996061300703 19960613 00703 GL 1996 6 13 96ZZZX3007 1 19960509 G 2731 O8610005 SWITCH DIAMON DA20A1 DA20A1 05626UX GL NOSE TRIM FAILED H CB9T K NONE O OTHER NR NOT REPORTED 1 SW 15 529SS 10095 TRIM SWITCH FAILS TO OPERATE WHEN SELECTING NOSE UP SETTING. 1 L 7 1 3O NT TA4CH 1996061300704 19960613 00704 EA 1996 6 13 96ZZZX3008 2 19960525 G 7314 41270175 FUEL PUMP PIPER PA32 PA32260 7103206 SO LYC O540 O540E4B5 41532 EA ENGINE FAILED H A UNSCHED LANDING Y ENGINE STOPPAGE CL CLIMB 1 SW 99 40933 327400025 L48648 PILOT REPORTED LOSS OF ENGINE POWER ON TAKEOFF AND ELECTED TO LAND ON GOLF COURSE. DURING INVESTIGATION, ENGINE WAS OPE RATED AND ENGINE DRIVEN FUEL PUMP FOUND INOPERATIVE. 1 L 7 1 3O 3 O A3SO E295 1996061300705 19960613 00705 1996 6 13 96ZZZX3009 4 19960522 G 2562 79007P ELT MERL PIPER PA28 PA28161 7102803 SO BATTERY PACK BATTERY LEAKED H HW8S K NONE O OTHER IN INSP/MAINT 1 WP 25 8091K 1005 288016076 AIRCRAFT WAS REMOVED FROM SERVICE NOVEMBER, 1995, FOR RESTORATION. ELT EXPIRATION DATE WAS FEBRUARY, 1996. DECIDED TO C/W FAR 91.207(D). DISCOVERED THIS UNIT IS SEALED, AND THERE IS NO WAY TO INSPECT BATTERIES. THE BATTERIES WERE ABOUT 3 MONTHS OVER EXPIRATION DATE, BUT BELIEVE THEY WERE BAD BEFORE THAT DATE. THERE IS NO WAY TO INSPECT THIS TYPE OF BATT ERY. THERE WAS NO OUTSIDE INDICATION OF A LEAK. IF THE UNIT HAD BEEN WITHIN ITS EXPIRATION DATE AND HAD BEEN OPENED AN D FOUND OK, THEN WOULD NOT HAVE BEEN ABLE TO PROPERLY RESEAL IT. 1 L 7 1 3O 2A13 1996061300706 19960613 00706 CE 1996 6 13 96ZZZX3010 1 19960507 G 3230 08421201 TUBE ASSY CESSNA 310 310L 2074230 CE NLG BROKEN G L A O OTHER O OTHER AP APPROACH 1 WP 05 3305X 3911 310L0155 NOSE LANDING GEAR WAS EXTENDED, BUT DID NOT LOCK IN THE DOWN POSITION. SUBSEQUENT INVESTIGATION REVEALED THAT THE NLG M AIN DRIVE ASSY WAS BROKEN. THE ANNUAL AND 100-HOUR INSPECTION WERE COMPLETED APRIL 19, 1996. TACHOMETER 766.3. TOTAL TIME: 3,900.8 HOURS. AIRCRAFT WAS PAINTED DECEMBER 22, 1995. THE INTERMEDIATE GEAR DRIVE TABLE ASSY WAS BENT. SUBMIT TER STATED IMPROPER RIGGING MAY BE THE CAUSE. 1 L 7 2 3O 3A10 1996061300707 19960613 00707 EU 1996 6 13 96ZZZX3011 1 19960527 G 3211 C48710 TRUNNION PIN AMD FALC20 FALCON20C5 2730107 EU GEAR CRACKED D S K NONE O OTHER IN INSP/MAINT 1 SW 05 GEAR IN FOR OVERHAUL. NDT TEST REVEALED TRUNNION PIN CRACK. 2 L 7 2 4F RT A7EU 1996061300709 19960613 00709 CE 1996 6 13 96ZZZX3013 1 19960529 G 5540 23330072 PANEL 263300112 LEAR 25 25D 5170514 CE RUDDER BAL WT CRACKED D K NONE O OTHER IN INSP/MAINT 1 WP 23 1U 5132 1733 371 DURING 12-YEAR INSPECTION, FOUND THE RUDDER INSPECTION PANEL THAT CONTAINS THE RUDDER BALANCE WEIGHT WAS CRACKED AT 4 OU T OF 6 WEIGHT ATTACH HOLES. SOME OF THE CRACKS WERE NOT VISIBLE UNTIL THE BALANCE WEIGHT WAS REMOVED. 2 L 7 2 4J A10CE 1996061300710 19960613 00710 CE 1996 6 13 96ZZZX3014 1 19960528 G 5320 551124920 FRAME CESSNA 500 550 2076604 CE PILOT WINDOW CRACKED B PAZR K NONE O OTHER IN INSP/MAINT 1 CE 03 80AW 6976 5500186 DURING REMOVAL OF PILOT'S WINDSHIELD TO INSTALL A NEW WINDSHIELD, APPROXIMATELY 3 CRACKS WERE FOUND IN THE SIDE WINDOW F RAME, THE LARGEST OF WHICH WAS APPROXIMATELY 2.5 INCHES LONG AND HAD BEEN PREVIOUSLY STOP DRILLED. THERE WERE ALSO NUME ROUS DEEP GOUGES AND SCRATCHES WHICH APPEAR TO HAVE BEEN CAUSED BY TOOLS USED TO REMOVE THE WINDOW RETAINERS PREVIOUSLY. THE CRACKS ALL APPEAR TO HAVE STARTED AT A POINT WHERE THE GOUGES OR SCRATCHES WERE. THE WINDOW FRAME WAS REMOVED AND REPLACED WITH A NEW PART FROM CESSNA. CITATION DOES NOT ALLOW ANY CRACKS IN THE AREA AND NO REPAIRS ARE ALLOWED OTHER THAN REPLACEMENT. 1 L 7 2 4F A22CE 1996061300712 19960613 00712 CE 1996 6 13 96ZZZX3016 1 19960514 G 7711 PG12A9 TRANSDUCER HONEYWELL RKWELL NA265 NA26540 6402608 CE ENGINE EPR FAILED D K NONE O OTHER IN INSP/MAINT 1 SO 16 306NT K1507 282030 TRANSDUCER WAS INSTALLED IN THE AIRCRAFT, TESTED, AND REMOVED WITH ZERO HOURS SINCE OVERHAUL. UNIT WAS REMOVED DUE TO E PR INDICATION WOULD STICK AT 2.0 AND WOULD NOT CHANGE WITH CHANGES IN ENGINE POWER SETTING. UNIT WAS OVERHAULED 3-29-96 . SUBMITTER STATED RELIABILITY OF OVERHAULED AND REPAIRED UNITS HAS BEEN POOR. AIRCRAFT TOTAL TIME: 1,095.0 HRS. 2 L 7 2 4J A2WE 1996061300713 19960613 00713 CE 1996 6 13 96ZZZX3017 1 19960503 G 3340 G99501 BEACON ASSY GRIMES RKWELL NA265 NA26540 6402608 CE EXT LIGHT FAILED D K NONE O OTHER IN INSP/MAINT 1 SO 09 302NT 27 6725 282081 BEACON WAS REMOVED FROM SERVICE WITH 27.0 HRS SINCE OVERHAUL DUE TO WOULD NOT ROTATE. UNIT WAS OVERHAULED BY REPAIR STA TION. SUBMITTER STATED RELIABILITY OF REPAIRED AND OVERHAULED UNITS HAS BEEN POOR. AIRCRAFT TT: 1,683.0 HRS. 2 L 7 2 4J A2WE 1996061300714 19960613 00714 EA 1996 6 13 96ZZZX3018 1 19960509 G 7110 204318004 SUPPORT CNDAIR CL600 CL6001A11 1900302 EA ENGINE COWL CRACKED B QU2R K NONE O OTHER IN INSP/MAINT 1 EA 17 68SD 2162 1062 DURING 300-HOUR ENGINE INSPECTION, A 6.5 INCH HORIZONTAL CRACK WAS FOUND IN THE FAN COWL SUPPORT AT 3 O'CLOCK POSITION. ALSO, VARIOUS BRACKETRY ATTACHED TO COWL ASSY FOUND TO HAVE SMALL CRACKS. 2 L 7 2 4F RT A21EA 1996062000077 19960620 00077 SW 1996 6 20 96ZZZX3019 1 19960430 G 3213 206033108001 FITTING BELL 206 206L4 1182110 SW FWD CROSS TUBE CHAFED B GJQR K NONE O OTHER IN INSP/MAINT 1 NM 01 108W 1122 52034 FORWARD CROSS TUBE STRAP ASSY WORN INTO RIGHT FORWARD CROSS TUBE FITTING. REPLACED FITTING PER PRODUCT SUPPORT WEAR LIM ITS. 1 G 7 1 3U NC H2SW 1996062000422 19960620 00422 CE 1996 6 20 96ZZZX3041 1 19960606 G 7120 2651011 MOUNT BEAM LEAR 35 35A 5170602 CE PYLON CHAFE B A AN3R K NONE O OTHER IN INSP/MAINT 1 WP 23 754GL 673 197 MOUNT BEAM CHAFING ON PYLON SIDE PANEL MOUNT FEED-THROUGH DOUBLER RING UPPER 3 ATTACH RIVETS. SUSPECT CAUSE: PYLON SID E PANEL MOVEMENT. SUBMITTER STATES TO REMOVE OLD RIVETS AND INSTALL NEW RIVETS IN A DOUBLE FLUSH MANNER. 2 L 7 2 4F A10CE 1996062000423 19960620 00423 CE 1996 6 20 96ZZZX3042 1 19960606 G 7120 2651011 MOUNT BEAM LEAR 35 35A 5170602 CE PYLON CHAFE B A AN3R K NONE O OTHER IN INSP/MAINT 1 WP 23 19LH 889 279 MOUNT BEAM CHAFING ON PYLON SIDE PANEL MOUNT FEED THROUGH DOUBLER RING UPPER 3 ATTACH RIVETS. SUSPECT CAUSE: PYLON SID E PANEL MOVEMENT. SUBMITTER STATED TO REMOVE OLD RIVETS AND INSTALL NEW RIVETS IN A DOUBLE FLUSH MANNER. 2 L 7 2 4F A10CE 1996062000424 19960620 00424 CE 1996 6 20 96ZZZX3043 1 19960606 G 7120 2651011 MOUNT BEAM LEAR 35 36A 5170603 CE PYLON CHAFE B A AN3R K NONE O OTHER IN INSP/MAINT 1 WP 23 14TX 033 MOUNT BEAM CHAFING ON PYLON SIDE PANEL MOUNT FEED THROUGH DOUBLER RING UPPER 3 ATTACH RIVETS. SUSPECT CAUSE: PYLON SID E PANEL MOVEMENT. SUBMITTER STATES TO REMOVE OLD RIVETS AND INSTALL NEW RIVETS IN A DOUBLER FLUSH MANNER. 2 L 7 2 4F A10CE 1996062000425 19960620 00425 CE 1996 6 20 96ZZZX3044 1 19960606 G 7120 2651011 MOUNT BEAM LEAR 35 36A 5170603 CE PYLON CHAFE B A AN3R K NONE O OTHER IN INSP/MAINT 1 WP 23 14TX 453 033 MOUNT BEAM CHAFING ON PYLON SIDE PANEL MOUNT FEED-THROUGH DOUBLER RING UPPER 3 ATTACH RIVETS. SUSPECT PYLON SIDE PANEL MOVEMENT. SUBMITTER STATES TO REMOVE OLD RIVETS AND INSTALL NEW RIVETS IN A DOUBLE FLUSH MANNER. 2 L 7 2 4F A10CE 1996062000426 19960620 00426 WP 1996 6 20 96ZZZX3045 2 19960509 G 7260 8968042 GEARSHAFT 31017262 MTSBSI MU2 MU2B60 5780460 CE GARRTT TPE331 TPE33110 01514 WP FUEL PUMP SHEARED B IZ2R O OTHER Y ENGINE STOPPAGE NR NOT REPORTED 1 SW 15 175CA 4942 3P9426 736SA P36014 AIRCRAFT EXPERIENCED AN UNCOMMANDED ENGINE SHUT DOWN. ENGINE DISASSEMBLY REVEALED GEARSHAFT HAD SHEARED CAUSING FUEL PU MP TO STOP TURNING. REFERENCE: 1PC 72-01-16, SECTION 72-10-17, PAGE 2, ITEM 40. 1 H 7 2 3T 4 T RT A10SW E4WE 1996062000427 19960620 00427 WP 1996 6 20 96ZZZX3046 1 19960523 G 3320 BR9661103 POWER SUPPLY BRUCE BC50447907 DOUG DC9 DC931 3022065 WP TAIL CONE FAILED B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 POWER SUPPLY FOR EXIT ID FAILED DUE TO EXPOSURE TO CHEMICAL ACTION FROM HYDRAULIC FLUID. SUBMITTER STATED DEVICE IS NOT DESIGNED FOR THIS TYPE OF EXPOSURE AND NEEDS TO BE REDESIGNED FOR TAIL CONE MOUNTING. 2 L 7 2 4F A6WE 1996062000428 19960620 00428 NE 1996 6 20 96ZZZX3047 2 19960510 G 7200 ENGINE LEAR 25 25 5170506 CE GE CJ610 CJ6106 30006 NE LT ENGINE FLAME OUT H A B O EMER. DESCENT OTHER X ENGINE FLAMEOUT CR CRUISE 1 GL 07 88NJ 008 240091 LEFT ENGINE FLAMED OUT AT FL 44,500 FEET GOING TO STP. DROPPED DOWN TO 25,000 FEET, RELIT ENGINE, CONTINUED TO STP. MA INTENANCE INSPECTED ENGINE PER GE MM. NO DEFECTS NOTED. RETURNED TO SERVICE. 2 L 7 2 4J 4 J A10CE 1E16 1996062000429 19960620 00429 EU 1996 6 20 96ZZZX3048 1 19960501 G 4920 25V13996 DUCT HWKSLY DH125 BH125400A 4230138 EU APU RAM DUCT CRACKED B P RO3R K NONE O OTHER IN INSP/MAINT 1 CE 03 345GL BHB650 NA753 WHILE ACCOMPLISHING 500-HOUR AIRFRAME INSPECTION, ONE OF THE INSPECTION REQUIREMENTS CALLED OUT TO INSPECT THE APU. DUR ING INSPECTION, LARGE PIECES OF METAL WERE FOUND BEHIND THE APU. APU REMOVED WHICH REVEALED THE CRACKED RAM AIR DUCT AS SY. THE RT SIDE OF THE DUCT CONTAINED A CRACK 5 INCHES BY 8 INCHES IN DIAMETER WITH ADDITIONAL CRACKS THROUGHOUT THE DU CT ASSY. THE APU IS NOT NORMALLY REMOVED DURING THIS INSPECTION WHICH COULD GO FOR NUMEROUS INSPECTIONS UNDETECTED. SU BMITTER SUGGESTS THE HIGH VIBTRATION LEVEL ASSOCIATED WITH THE APU CAUSED THE DUCT ASSY TO CRACK. RECOMMEND THE DUCT AS SY BE INSPECTED ON A REGULARLY SCHEDULED INTERVAL. 2 L 7 2 4J A3EU 1996062000430 19960620 00430 CE 1996 6 20 96ZZZX3049 1 19960506 G 3246 9524796 O-RING RKWELL NA265 NA26540 6402608 CE WHEEL PLUG ASSY MISSING D K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 09 303NT 11 AUG752183 28229 WHEEL ASSY OVERHAULED 4-5-96. UNITS FUSIBLE PLUG O-RING NOT REPLACED DURING OVERHAUL. 2 L 7 2 4J A2WE 1996062000431 19960620 00431 CE 1996 6 20 96ZZZX3050 1 19960513 G 2822 2017002 PUMP TRW RKWELL NA265 NA26540 6402608 CE FUEL BOOST FAILED D O OTHER J WARNING INDICATION NR NOT REPORTED 1 SO 09 303NT 15 1001683D 28229 UNIT FAILED IN-FLIGHT WITHOUT INCIDENT, SUSPECT INTERNAL MOTOR BRUSH OR COMMUTATOR FAILURE. UNIT OVERHAULED. 2 L 7 2 4J A2WE 1996062000432 19960620 00432 NE 1996 6 20 96ZZZX3051 2 19960513 G 7250 597622 BLADE RKWELL NA265 NA26540 6402608 CE PWA JT12 JT12A8 52042 NE 2ND STG TURBINE BROKEN D O OTHER O OTHER CR CRUISE 1 SO 09 311NT 331 28219 P673094NB SECOND STAGE TURBINE ROTOR BLADE FAILURE IN-FLIGHT, WITHOUT INCIDENT. ENGINE TT, 11,164.7 HRS, CYCLES, 8,081, TSO, 330. 9 HRS, TTHSI, 330.9 HRS, TOTAL PART TIME 330.9 HRS. UNIT WAS OVERHAULED 4-12-95. 2 L 7 2 4J 4 J A2WE 1E9 1996062000433 19960620 00433 CE 1996 6 20 96ZZZX3052 1 19960506 G 3246 9524796 O-RING LORAL RKWELL NA265 NA26540 6402608 CE WHEEL PLUG ASSY MISSING D K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 09 313NT 5 MAY801162 28294 WHEEL ASSY OVERHAULED 4-11-96. UNITS FUSIBLE PLUG O-RING, PN 9524796, NOT REPLACED DURING OVERHAUL. 2 L 7 2 4J A2WE 1996062000434 19960620 00434 EU 1996 6 20 96ZZZX3053 1 19960530 G 3241 60026143 CONTROL BOX LORAL AMD FALC50 FALCON50MYST 2730106 EU ANTI-SKID PINS CORRODED D a K NONE O OTHER IN INSP/MAINT 1 GL 11 450K 137 186 IMPROPER ANTI-SKID OPERATION AND INVALID TEST. FOUND OXIDIZATION ON CONTROL BOX CONNECTOR J1 AND J2 PINS. BOX, SN 137, ORDERED EXCHANGE BOX AND EXCHANGE BOX SHIPPED. ALSO, HAD OXIDIZED PINS. BOX, SN DASH 064. CLEANED OXIDIZATION FROM P INS, MALE AND FEMALE CONNECTOR, AND INSTALLED BOX AND OPS CHECKED OK. AIRCRAFT HISTORY SHOWS CONTROL BOX 6002614, SN'S DASH 454 AND DASH 458 WERE ALSO REPLACED FOR SAME PROBLEM IN THE LAST 2 YEARS. SUBMITTER RECOMMENDS PINS, BOTH MALE AND FEMALE, BE REPLACED WITH GOLD PLATED PINS DUE TO ENVIRONMENT (HOT-COLD) AND LOCATION OF CONTROL BOX. 2 L 7 3 4F A46EU 1996062000435 19960620 00435 SO 1996 6 20 96ZZZX3054 1 19960507 G 5553 FITTING GULSTM G1159 GIV 3980115 SO V-STAB ATTACH BUSHING GROOVED B RO3R K NONE O OTHER IN INSP/MAINT 1 CE 03 7RP 1743 1064 WHILE C/W THE VERTICAL STABILIZER ATTACH FITTING INSPECTION IAW GULFSTREAM IV MM, CHAPTER 5, SECTION 55, THE BUSHINGS WE RE FOUND TO HAVE DEEP GROOVES ON THE OUTER SURFACE. FURTHER EXAMINATION OF THE ATTACH FITTINGS FOUND THE HOLES OVERSIZE D AND OUT-OF-ROUND, AND FORWARD STRAPS WERE FOUND GOUGED (THIS WAS THE FIRST INSPECTION OF THIS AREA SINCE NEW). SUBMIT TER RECOMMENDS INSPECTING THE ATTACHING BOLTS, BUSHINGS, AND STRAPS FOR GOUGES, AND THE ATTACH FITTING FOR MISALIGNMENT. NEW STAINLESS STEEL FITTINGS WERE INSTALLED. 2 L 7 2 4F RT A12EA 1996062000436 19960620 00436 CE 1996 6 20 96ZZZX3055 1 19960531 G 3260 444EN496 SWITCH BEECH 90 C90 1152913 CE LT DOWNLOCK WIRE BROKEN B L AKGR K NONE P NO WARNING INDICATION AP APPROACH 1 CE 05 115KU LJ1040 CREW REPORTED NOT HAVING LEFT DOWN AND LOCK INDICATION. MADE AN UNEVENTFUL LANDING, AIRCRAFT INSPECTED AND FOUND A BROK EN WIRE IN THE AREA OF THE TOP END OF THE LEFT GEAR DRAG BRACE. WIRING WAS REPAIRED AND GEAR SYSTEM OPERATION FOUND NOR MAL. 1 L 7 2 3T 3A20 1996062000437 19960620 00437 SO 1996 6 20 96ZZZX3056 1 19960424 G 2761 5802402 TORQUE TUBE PIPER PA42 PA42720 7104212 SO CONTROL COLUMN WORN D A K NONE O OTHER IN INSP/MAINT 1 GL 05 777YP 4702 425501008 EXPERIENCED MOVEMENT OF PILOT'S CONTROL COLUMN WITH COPILOT'S CONTROL COLUMN HELD SECURELY IN PLACE. SIDE PLAY AND FORE /AFT MOVEMENT NOTED IN PILOT'S CONTROL COLUMN. MOVEMENT OF PILOT'S CONTROL COLUMN TRACED TO WEAR BETWEEN LEFT CONTROL C OLUMN PIVOT FITTING ASSY, AND STEEL INTERCONNECT TUBE EXHIBITED SIGNS OF LOOSENESS. REF: PIPER ACFT PA 42/42-720 AIRPL ANE PARTS CATALOG, FIG 102, DATED 2-1-91, FOR ILLUSTRATIONS. NEW CONTROL COLUMN INTERCONNECT TORQUE TUBE ASSY INSTALLED ON 2-13-96. ACFT TT: 5,595.3 HRS, 3,984 LANDINGS. PN 58024-02 PREVIOUSLY REPLACED ON 1-17-86, ACFT TT: 893.4 HRS FO R SAME DISCREPANCY. 1 L 7 2 4T A23SO 1996062000438 19960620 00438 SO 1996 6 20 96ZZZX3057 2 19960513 G 8550 643716 FILTER ADAPTER CESSNA 206 TU206G 2073357 CE CONT O520 TSIO520M 17040 SO WASTEGATE OIL WRONG CONN B L EVGR K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 33 2FOR U20606295 EXPERIENCED INCONSISTENT MANIFOLD PRESS & FUEL FLOWS. LOOKED AT SOURCE OF OIL TO WASTEGATE FROM OIL PUMP HSNG P/N 64371 6, & FND PORT USED SUPPLIED UNFILTERED OIL. OIL PUMP HSNG IS NEW P/N WHICH USES FULL FLOW OIL FILTER. NEW HSNG HAS, BE LOW FILTER BASE, A 2ND PORT THAT WILL PROVIDE FILTERED OIL. OLD P/N 632770 OIL PMP HSNG WHICH USES OTHER STYLE OF FILTE R (CESSNA SUPPLIED OIL FILTER ADAPTER P/N 1250922-4) HAS 1 PORT FOR FILTERED OIL SUPPLY TO W/G. PORT IS IN SAME LOCALE AS UNFILTERED PORT ON NEW P/N HSNG. PROBLEM DEVELOPED WHEN REPLACING ENG WITH OLD HSNG WITH ENG HAVING NEW. ASSUMED FI LTERED OIL WOULD COME OUT OF SAME LOCALE, PORT IS DIFFERENT INSIDE. PORT IS PLUGGED WITH ALLEN HEAD PLUG. 1 H 7 1 3O 3 O A4CE E8CE 1996062000742 19960620 00742 NM 1996 6 20 96ZZZX3058 1 19960506 G 5210 DOOR PIPER PA60 PA60600 7106001 NM TOP CABIN DEPARTED D A A UNSCHED LANDING D INFLIGHT SEPARATION CR CRUISE 1 GL 07 222KD 600557181 TOP CABIN DOOR CAME OPEN IN-FLIGHT, SEPARATED FROM AIRCRAFT. LANDED AIRCRAFT IN SYR. INSTALLED NEW DOOR ASSEMBLY AND R ETURNED TO SERVICE. 1 M 7 2 3O RT A17WE 1996062000743 19960620 00743 SW 1996 6 20 96ZZZX3059 1 19960609 G 2460 727422 BREAKER SWRNGN SA226 SA226TC 8780404 SW ENCODE ALTIMETER DEFECTIVE D A K NONE O OTHER IN INSP/MAINT 1 SW 01 240NM T240 CIRCUIT BREAKER WAS INTERMITTENT EVEN THOUGH THE BREAKER HAD NOT TRIPPED. THIS INTERMITTENT POWER CAUSED ENCODING ALTIM ETER TO FLUCTUATE WITH INTERMITTENT FLAGS. ENCODING ALTIMETER SENT OUT ALTITUDE 300 FEET HIGHER THAN INDICATED, THEN FL AGGED AND WENT OFF-LINE. RESETTING BREAKER CAUSED FAULT TO DISAPPEAR THEN PROBLEM CAME BACK. BELIEVED TO BE DUE TO HIG H AMBIENT TEMPERATURE AT TAKEOFF (110). 2 L 7 2 4T RT A8SW 1996062000744 19960620 00744 CE 1996 6 20 96ZZZX3060 1 19960328 G 2820 3592122169 LINE BEECH 35 G35 1151516 CE RT GEAR WELL CHAFED D A K NONE O OTHER IN INSP/MAINT 1 SO 13 4575D 5325 D4727 DURING ANNUAL INSPECTION AND GEAR RETRACTION TEST, DISCOVERED RT AUXILIARY FUEL TANK LINE WHICH PASSES ACROSS THE TOP OF THE LANDING GEAR HAD BEEN CHAFED ABOUT ONE-HALF OF ITS THICKNESS DUE FROM A GREASE FITTING ON THE FORWARD ROLLER WHICH WAS RUBBING EACH TIME THE GEAR WAS RETRACTED. IT WAS APPARENT THERE WAS NOT ENOUGH CLEARANCE BETWEEN GEAR AND LINE. SU BMITTER STATES THIS COULD HAVE CAUSED A SERIOUS ACCIDENT HAD IT GONE UNDETECTED. THIS AREA NEEDS TO BE CHECKED AT EACH ANNUAL/OR PRE-FLIGHT. 1 L 7 1 3O A777 1996062000745 19960620 00745 CE 1996 6 20 96ZZZX3061 1 19960328 G 2820 LINE BEECH 35 G35 1151516 CE FUEL DETERIORATED D K NONE O OTHER IN INSP/MAINT 1 SO 13 4575D 5325 D4727 DURING ANNUAL INSPECTION, ALL FLEXIBLE FUEL AND BRAKE LINES WERE FOUND SEVERELY DETERIORATED. SUBMITTER STATES THIS IS AN ONGOING PROBLEM. A TIME LIMIT SHOULD BE PLACED ON THESE ITEMS. RECOMMEND 10 YEARS OR 1500 HRS. THESE LINES APPEARE D TO BE ORIGINAL. 1 L 7 1 3O A777 1996062000746 19960620 00746 SO 1996 6 20 96ZZZX3062 1 19960521 G 5512 6358600 SKIN PIPER PA28 PA28161 7102803 SO TAIL LT TRIM TAB CRACKED C K NONE O OTHER IN INSP/MAINT 1 GL 11 529PU 2841194 ONGOING CRACKS ON TRIM TAB LOWER SKINS AND INBOARD RIBS AT TRIM TAB CONTROL ARM ATTACH POINT, SKIN AND/OR RIB HAS CRACK ED FROM 2500-4000 HOURS. FIRST REPAIR WAS TO REPLACE SKIN AND RIBS WITH NEW PIPER PARTS AND THESE LASTED 1000-1500 HOUR S BEFORE CRACKING AGAIN IN THE SAME PLACE. CURRENTLY HAVE ADDED .040 INCH ALUMINUM DOUBLER ON SEVERAL AIRCRAFT FOR LONG ER LIFE. AIRCRAFT USED FOR FLIGHT TRAINING 1,000 HOURS PER YEAR. SUBMITTER STATES OLDER AIRCRAFT DO NOT DISPLAY THIS P ROBLEM TOO WELL AFTER 6000 HOURS. 1 L 7 1 3O 2A13 1996062000747 19960620 00747 SO 1996 6 20 96ZZZX3063 1 19960521 G 5512 6358601 SKIN PIPER PA28 PA28161 7102803 SO TAIL RT TRIM TAB CRACKED C K NONE O OTHER IN INSP/MAINT 1 GL 11 529PU 2841194 ONGOING CRACKS ON TRIM TAB LOWER SKINS AND INBOARD RIBS AT TRIM TAB CONTROL ARM ATTACH POINT, SKIN AND/OR RIB HAS CRACK ED FROM 2500-4000 HOURS. FIRST REPAIR WAS TO REPLACE SKIN AND RIBS WITH NEW PIPER PARTS AND THESE LASTED 1000-1500 HOUR S BEFORE CRACKING AGAIN IN THE SAME PLACE. CURRENTLY HAVE ADDED .040 INCH ALUMINUM DOUBLER ON SEVERAL AIRCRAFT FOR LONG ER LIFE. AIRCRAFT USED FOR FLIGHT TRAINING 1,000 HOURS PER YEAR. SUBMITTER STATES OLDER AIRCRAFT DO NOT DISPLAY THIS P ROBLEM TOO WELL AFTER 6000 HOURS. 1 L 7 1 3O 2A13 1996062000748 19960620 00748 SO 1996 6 20 96ZZZX3064 1 19960521 G 5512 6358601 SKIN PIPER PA28 PA28R201 7102816 SO TAIL RT TAB CRACKED C K NONE O OTHER IN INSP/MAINT 1 GL 11 532PU 2837040 ONGOING CRACKS ON TRIM TAB LOWER SKINS AND INBOARD RIBS AT TRIM TAB CONTROL ARM ATTACH POINT. SKIN AND/OR RIB HAS CRACK ED FROM 2500-4000 HOURS. FIRST REPAIR WAS TO REPLACE SKIN AND RIBS WITH NEW PIPER PARTS AND THESE LASTED 1000-1500 HOUR S BEFORE CRACKING AGAIN IN THE SAME PLACE. CURRENTLY, HAVE ADDED .040 INCH ALUMINUM DOUBLER ON ONE AIRCRAFT FOR LONGER LIFE. AIRCRAFT USED FOR FLIGHT TRAINING 750 HOURS PER YEAR. 1 L 7 1 3O 2A13 1996062000749 19960620 00749 SO 1996 6 20 96ZZZX3065 1 19960521 G 5512 6358600 SKIN PIPER PA28 PA28R201 7102816 SO TAIL LT TAB CRACKED C K NONE O OTHER IN INSP/MAINT 1 GL 11 532PU 2837040 ONGOING CRACKS ON TRIM TAB LOWER SKINS AND INBOARD RIBS AT TRIM TAB CONTROL ARM ATTACH POINT. SKIN AND/OR RIB HAS CRACK ED FROM 2500-4000 HOURS. FIRST REPAIR WAS TO REPLACE SKIN AND RIBS WITH NEW PIPER PARTS AND THESE LASTED 1000-1500 HOUR S BEFORE CRACKING AGAIN IN THE SAME PLACE. CURRENTLY, HAVE ADDED .040 INCH ALUMINUM DOUBLER ON ONE AIRCRAFT FOR LONGER LIFE. AIRCRAFT USED FOR FLIGHT TRAINING 750 HOURS PER YEAR. 1 L 7 1 3O 2A13 1996062000750 19960620 00750 CE 1996 6 20 96ZZZX3066 1 19960425 G 2430 C593000101 SENSOR HOPKINSENG 0337 CESSNA 172 172M 2072418 CE OVERVOLTS DEFECTIVE D K NONE O OTHER IN INSP/MAINT 1 GL 11 4649Q 1310 3031006 17261735 OVERVOLTAGE SENSOR DEFECTIVE: NO POWER OUT ON ORANGE WIRE TO ALTERNATOR FIELD SWITCH TO ENERGIZE ALTERNATOR FIELDS - NO CHARGING. 1 H 7 1 3O NT 3A12 1996062000751 19960620 00751 CE 1996 6 20 96ZZZX3067 1 19960514 G 5540 S16751 BEARING BLOCK CESSNA 172 172F 2072414 CE RUDDER CORRODED D K NONE O OTHER IN INSP/MAINT 1 NE 01 8739U 2200 17252643 COMPLAINT AT ANNUAL THAT AIRCRAFT IS HARD TO STEER. FOUND RUDDER BEARING BLOCKS CORRODED RESTRICTING MOVEMENT OF RUDDER PEDALS. LACK OF LUBRICATION ON RUDDER BAR AT BEARING BLOCKS. REPLACEMENT CESSNA UNITS ARE NO LONGER METAL. 1 H 7 1 3O NT 3A12 1996062000753 19960620 00753 SO 1996 6 20 96ZZZX3069 1 19960503 G 5610 41543 WINDSHIELD PPG PIPER PA31 PA31350 7103110 SO COCKPIT CORRODED E K NONE O OTHER IN INSP/MAINT 1 NM 11 84859 2250 90030H4826 317305043 THE CORROSION STARTED ON THE TERMINAL STRIP WHICH IS LAMINATED BETWEEN 2 PLATES OF PPG GLASS. THE CORROSION THEN SPREAD TO THE 50-GAUGE GOLD HEATED WIRES RUNNING HORIZONTALLY THROUGH THE GLASS AT EYE LEVEL. AS THE 50-GAUGE GOLD WIRE CORRO DES,THE DIAMETER OF THE WIRE IS REDUCED CAUSING THE RESISTANCE TO GO UP WHICH, IN TURN, CAUSES THE WIRE TO HEAT AND BURN . THIS THEN RENDERS THE WINDSHIELD UNAIRWORTHY FOR THE CONDITIONS. SUBMITTER STATES THE SOLUTION FOR PPG PIPER WINDSHI ELDS SHOULD BE AN OHM AND VISUAL CHECK TO PPG HEATED WINDSHIELDS EVERY 12 MONTHS BECAUSE THE PPG WORKMANSHIP WARRANTY IS 48 MONTHS. 1 L 7 2 3O A20SO 1996062000754 19960620 00754 SO 1996 6 20 96ZZZX3070 1 19960523 G 3230 4198300 HOOK PIPER PA31 PA31350 7103110 SO LT DOWNLOCK MALFUNCTION B BONR O OTHER P NO WARNING INDICATION AP APPROACH 1 GL 19 88AJ 3250 318252048 ON TRAINING FLIGHT, PILOT WAS UNABLE TO GET GREEN DOWN LIGHTS ON BOTH MLG. CYCLED GEAR - NO CHANGE. TOWER SAID INBOARD GEAR DOORS OPEN ON FLYBY. HAND PUMP OPERATION WAS VERY HARD AS IF ACTING AGAINST SYSTEM. LANDING WAS MADE WITHOUT INC IDENT. PUT AIRCRAFT ON JACKS, FOUND BOTH LT AND RT DOWNLOCK HOOKS NOT ENGAGED. FOUND PIVOT BOLTS VERY DIRTY AND STICKY . CLEANED AND OPS CHECKS GOOD. 1 L 7 2 3O A20SO 1996062000755 19960620 00755 SO 1996 6 20 96ZZZX3071 1 19960523 G 3230 4198301 HOOK PIPER PA31 PA31350 7103110 SO RT DOWNLOCK MALFUNCTION B BONR O OTHER P NO WARNING INDICATION AP APPROACH 1 GL 19 88AJ 3250 318252048 ON TRAINING FLIGHT, PILOT WAS UNABLE TO GET GREEN DOWN LIGHTS ON BOTH MLG. CYCLED GEAR - NO CHANGE. TOWER SAID INBOARD GEAR DOORS OPEN ON FLYBY. HAND PUMP OPERATION WAS VERY HARD AS IF ACTING AGAINST SYSTEM. LANDING WAS MADE WITHOUT INC IDENT. PUT AIRCRAFT ON JACKS, FOUND BOTH LT AND RT DOWNLOCK HOOKS NOT ENGAGED. FOUND PIVOT BOLTS VERY DIRTY AND STICKY . CLEANED AND OPS CHECKS GOOD. 1 L 7 2 3O A20SO 1996062000756 19960620 00756 SO 1996 6 20 96ZZZX3072 2 19960528 G 7414 10357281H COIL PIPER PA28 PA28RT201T 7102817 SO CONT O360 TSIO360FB 17025 SO ENGINE RT MAG WIRE BROKEN D K NONE W INADEQUATE Q C IN INSP/MAINT 1 CE 05 42946 28R8331025 299532R INSTALLED NEW MAGNETO, WAS INOPERATIVE. TROUBLESHOOTING REVEALED THE COIL WIRE WAS BROKEN AT THE TERMINAL END. (INSULA TION WAS STILL INTACT). SUBMITTER STATED CAUSE WAS DUE TO THE TERMINAL END BEING CRIMPED TOO HARD RESULTING IN BROKEN W IRE. RECOMMEND MANUFACTURER BE INFORMED. 1 L 7 1 3O 3 O 2A13 E9CE 1996062000757 19960620 00757 SO 1996 6 20 96ZZZX3073 2 19960526 G 7414 107902018R MAGNETO PIPER PA28 PA28RT201T 7102817 SO CONT O360 TSIO360FB 17025 SO ENG RT MAG FAILED D K NONE O OTHER NR NOT REPORTED 1 CE 05 42946 59 28R8331025 299532R MAGNETO FAILED. DID NOT TROUBLESHOOT MAG DUE TO IT BEING UNDER WARRANTY. 1 L 7 1 3O 3 O 2A13 E9CE 1996062000758 19960620 00758 SO 1996 6 20 96ZZZX3074 2 19960528 G 7414 CONDENSER 107902018R PIPER PA28 PA28RT201T 7102817 SO CONT O360 TSIO360FB 17025 SO ENG LT MAG FAILED D K NONE O OTHER IN INSP/MAINT 1 CE 05 42946 90 28R8331025 299532R INVESTIGATION FOR MAG PROBLEM FOUND CONDENSER HAD NO CONTINUITY. 1 L 7 1 3O 3 O 2A13 E9CE 1996062000759 19960620 00759 SO 1996 6 20 96ZZZX3075 2 19960528 G 7414 10357281H CONDENSER 107902018R PIPER PA28 PA28RT201T 7102817 SO CONT O360 TSIO360FB 17025 SO ENG RT MAG WIRE BROKEN D L K NONE W INADEQUATE Q C IN INSP/MAINT 1 CE 05 42946 59 28R8331025 299532R RT MAG INOPERATIVE. INSTALLED NEW MAG, SN 1069532DR. THIS NEW MAG WAS INOPERATIVE. TROUBLESHOOTING BOTH MAGS REVEALED ORIGINAL MAG HAD BAD CONSENSER AND THE NEW MAGNETO HAD A BAD COIL. BOTH NEW MAGNETOS HAD A BAD COIL. BOTH THE CONDENS ER AND COIL PROBLEMS RESULTED FROM THE TERMINAL ENDS BEING CRIMPED TOO HARD CAUSING THE WIRE TO FAIL. SUBMITTER RECOMME NDS THE MANUFACTURER BE INFORMED ON THIS PROBLEM. 1 L 7 1 3O 3 O 2A13 E9CE 1996062000760 19960620 00760 WP 1996 6 20 96ZZZX3076 1 19960501 G 3710 33E02 AIR PUMP 2 GRUMAN C1A C1A 3951014 WP ENGINE FAILED H O OTHER K FLUID LOSS NR NOT REPORTED 1 SW 99 26GH 1 1509M 136791 PUMP INSTALLED AND TESTED. APPROXIMATELY 15 MINUTES INTO FLIGHT, PUMP SHAFT SHEARED AFTER SPLITTING PUMP BODY RESULTING IN COMPLETE OIL LOSS IN ENGINE. SUBMITTER UNABLE TO DETERMINE EXACT CAUSE OF FAILURE. 2 H 7 2 4R RT EXPA2H72 1996062000761 19960620 00761 EA 1996 6 20 96ZZZX3077 2 19960529 G 8530 CYLINDER CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA ROCKER STUD DEFECTIVE D O OTHER E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 SW 01 75616 209 05K21119 17267852 2205276 ROCKER STUD BACKED OUT CAUSING EXCESSIVE VALVE CLEARANCE WHICH CAUSED THE PUSHROD TO GET JAMMED AND BENT. CYLINDER WAS IN C/W SB 412B (AD 77-20-07) WHICH REQUIRES STUDS TO BE LOCKTITE INTO POSITION. CYLINDER WAS MARKED IAW THIS PROCEDURE. SUBMITTER SUGGESTS BETTER WAY OF SECURING STUD. 1 H 7 1 3O 3 O NT 3A12 E274 1996062000762 19960620 00762 SO 1996 6 20 96ZZZX3078 1 19960528 G 3246 40131 WHEEL PARKERHANFIN PIPER PA23 PA23250 7102308 SO MLG RIM MISSING D O OTHER O OTHER TX TAXI/GRND HDL 1 EA 09 6921A 3500 277954112 GROUND PERSONNEL STATED THAT THE LEFT WHEEL WAS WOBBLING ON TAXI. INSPECTION FOUND ONE-THIRD OF THE RIM OF THE WHEEL WH ICH HOLDS THE TIRE ON WAS MISSING. TIRE WAS RUBBING BRAKE CALIPER. SUBMITTER STATED TIRE COULD HAVE BLOWN COMPLETELY O FF RIM IF NOT SEEN BY GROUND PERSONNEL. 1 L 7 2 3O 1A10 1996062000763 19960620 00763 SO 1996 6 20 96ZZZX3079 1 19960425 G 2434 ALTERNATOR PIPER PA28 PA28140 7102802 SO DC SYSTEM FLUCTUATION D K NONE W INADEQUATE Q C IN INSP/MAINT 1 EA 23 55498 287325420 REMOVED ALTERNATOR DUE TO AMPMETER FLUCTUATION. INSPECTED AND DETERMINED AUTOMOTIVE TYPE. COOLING FINS WERE INSTALLED IN OPPOSITE DIRECTION AS COMPARED TO O/H AERO ELECTRIC UNITS. ALTERNATOR REMOVED, HAD NO DATA PLATE OR ANY MARKINGS. U NIT REMOVED AND DISCARDED. 1 L 7 1 3O 2A13 1996062000764 19960620 00764 CE 1996 6 20 96ZZZX3080 1 19960601 G 3233 24130023 FITTING CESSNA 172 172RG 2072438 CE NLG ACTUATOR LOOSE D K NONE O OTHER IN INSP/MAINT 1 SW 01 4636V 172RG0345 WHEN ON JACKS, FORE AND AFT FORCE ON THE NOSE GEAR REVEALED A ROCKING MOTION OF THE NOSE GEAR ACTUATOR REAR FITTING TO F USELAGE ON ITS 20 ATTACHMENT BOLTS. WITH NUTS TORQUED, COULD EASILY TURN BOLTS AS THEY HAD RUN OUT OF THREADS AND NUT W AS JAMMED AGAINST SHANK. ONE ADDITIONAL AN-960-10 WASHER IS REQUIRED UNDER EACH OF THE 20 NUTS. AD 72-7-9 REFERS TO LO OSE BOLTS THAT REQUIRES ANOTHER WASHER TO SECURE THEM. 1 H 7 1 3O 3A17 1996062000765 19960620 00765 GL 1996 6 20 96ZZZX3081 2 19960515 G 7322 CARBURETOR AMTR SONERI SONERAI GL AMTRVW VOLKS VW1700VOLKS 99999 GL ENGINE BLOCKED VENT D A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CL CLIMB 1 CE 05 283SX 55 283 DURING TAKEOFF ENGINE HAD POWER LOSS. FUEL STARVATION DUE TO BLOCKED VENT SUSPECTED. SPARK PLUGS CONFIRM EXCESSIVE LEA N MIXTURE CAUSED POWER LOSS. 1 M 7 1 3O 3 O EXPA1M71 EXP3O 1996062000768 19960620 00768 SO 1996 6 20 96ZZZX3084 1 19960513 G 5712 78475005 RIB PIPER PA28 PA28R201 7102816 SO RT WING CRACKED B OG5R K NONE O OTHER IN INSP/MAINT 1 GL 21 170ND 6357 2837005 FOUND RIB CRACKED DURING SCHEDULED INSPECTION. CRACK WAS ON RIB FLANGE WHERE BOLTS GO THROUGH DRAG BRACE FITTING THAT B OLTS TO WING SPAR. SUBMITTER STATES THIS OPERATOR HAS ALSO FOUND NUMEROUS NOSE RIBS CRACKED ON FORWARD SIDE OF SPAR WHE RE NOSE RIB BOLTS TO SAME GEAR FITTING. 1 L 7 1 3O 2A13 1996062000769 19960620 00769 EA 1996 6 20 96ZZZX3085 2 19960521 G 8550 STD1686 SCREEN PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA LT ENGINE DEFECTIVE B OG5R K NONE O OTHER IN INSP/MAINT 1 GL 21 63ND 178 317852098 L697361A DURING SCHEDULED MAINTENANCE FOUND SCREW AND GASKET MATERIAL IN SUCTION SCREEN. REMOVED OIL SUMP/PAN, INSTALLED SCREW P ER LYCOMING INSTRUCTIONS. 1 L 7 2 3O 3 O A20SO E14EA 1996062000770 19960620 00770 CE 1996 6 20 96ZZZX3086 1 19960603 G 2822 BOOST PUMP DUKES BEECH 58 58 1152740 CE FUEL BOOST LEAKING D K NONE K FLUID LOSS IN INSP/MAINT 1 WP 07 85BE 3696 1367 TH1455 FUEL LEAKING FROM BOOST PUMP DRAIN. 1 L 7 2 3O 3A16 1996062000771 19960620 00771 SO 1996 6 20 96ZZZX3087 1 19960531 G 3230 AN17633 BOLT PIPER PA23 PA23 7102302 SO LT MLG DRAG LINK SHEARED D O OTHER O OTHER LD LANDING 1 WP 13 2060P 1000 23647 LEFT MAIN GEAR DRAG LINK UPPER BOLT, ITEM NR 61, FIGURE NR 37, SHEARED IN CENTER ON LANDING. SUBSEQUENT GEAR COLLAPSE A ND PROPELLER STRIKE. SUBMITTER STATED POSSIBLE MANDATORY BOLT INSPECTION AND/OR REPLACEMENT AT 1,000 HRS MAY BE SUFFICI ENT. 1 L 7 2 3O 1A10 1996062000772 19960620 00772 SO 1996 6 20 96ZZZX3088 1 19960603 G 7922 53E19600 VALVE PIPER PA31 PA31350 7103110 SO THERMO BYPASS WORN B APCR K NONE O OTHER IN INSP/MAINT 1 NM 01 3582X 562 57328 318052105 INSPECTION FOUND THE CENTER SPRING ASSY RETAINING CLIP LOOSE ON THE VERNATHERM BODY. 1 L 7 2 3O A20SO 1996062000773 19960620 00773 CE 1996 6 20 96ZZZX3089 1 19960528 G 2434 902014 BEARING PRESTOLITE ALT9422 CESSNA 310 310R 2074245 CE RT ENG ALT FAILED D A UNSCHED LANDING B O H SMOKE/FUMES/ODORS/SPARKS OTHER ELECT. POWER LOSS-50 PC CL CLIMB 1 SO 11 610Z 319 310R0071 CATASTROPHIC BEARING FAILURE OF ALTERNATOR ON RIGHT ENGINE AFTER TAKEOFF. PILOT RETURNED TO AIRPORT WITHOUT COMMUNICATI ON RADIOS. ONLY ADF AND GPS WAS STILL WORKING. PILOT REPORTED SEEING SPARKS FROM THE ALTERNATOR AND INTERIOR LIGHT FLI CKERED. RADIOS WENT OUT AND RETURNED TO AIRPORT WITH NO PROBLEM LANDING. SUBMITTER STATED THIS IS THE SECOND LIKE INCI DENT REPORTED ON ALT 9422 ALTERNATORS. 1 L 7 2 3O 3A10 1996062000774 19960620 00774 CE 1996 6 20 96ZZZX3090 1 19960602 G 3220 WHEEL ASSY CESSNA 120 120 2071402 CE TAIL WHEEL DEPARTED D O OTHER D INFLIGHT SEPARATION CL CLIMB 1 NE 03 120PG 11978 TAIL WHEEL ASSY DEPARTED AIRCRAFT. LEAF SPRING WAS BROKEN. 1 H 7 1 3O A768 1996062000775 19960620 00775 SO 1996 6 20 96ZZZX3091 1 19960603 G 7922 53ED22144 VALVE PIPER PA31 PA31350 7103110 SO THERMO BYPASS NUT LOOSE B APCR K NONE O OTHER IN INSP/MAINT 1 NM 01 3582X 289 68464 318052105 THE END RETAINING NUT ON THE VERNATHERM IS LOOSE. LYCOMING SB 518C DOES NOT APPLY TO THIS PART NUMBERED VERNATHERM. 1 L 7 2 3O A20SO 1996062000776 19960620 00776 SO 1996 6 20 96ZZZX3092 1 19960603 G 7922 53E19600 VALVE PIPER PA31 PA31350 7103110 SO THERMO BYPASS NUT STRIPPED B APCR K NONE O OTHER IN INSP/MAINT 1 NM 01 777KT 531 317552053 VERNATHERM VALVE SEAT RETAINING NUT STRIPPED AND SEPARATED FOR SHAFT OF VALVE. ALSO, RETAINING CLIP FOR VERNATHERM BODY BROKEN INTO 2 PARTS, AND BODY BROKEN AT CLIP ATTACH AREA. 1 L 7 2 3O A20SO 1996062000777 19960620 00777 SO 1996 6 20 96ZZZX3093 1 19960603 G 7922 53E19600 VALVE PIPER PA31 PA31350 7103110 SO THERMO BYPASS NUT LOOSE B APCR K NONE O OTHER IN INSP/MAINT 1 NM 01 777KT 531 317552053 VERNATHERM VALVE SEAT RETAINING NUT LOOOSE AND WORKING ON RETAINING SHAFT THREADS. 1 L 7 2 3O A20SO 1996062000778 19960620 00778 NE 1996 6 20 96ZZZX3094 2 19960605 G 7414 GE52120 DISTRIBUTOR GEAR BOSCH 5B9RU3 BEECH 18 E18S 1151006 CE PWA R985 R985AN14B 52008 NE MAG TEETH SHEARED D K NONE O OTHER NR NOT REPORTED 1 SW 15 5611D 1228 B46676 BA316 22664 COMPLETE FAILURE OF THE MAGNETO DUE TO SHEARING OF ALL TEETH OF THE DISTRIBUTER GEAR. 1 L 7 2 3R 3 R A765 5E1 1996062700342 19960627 00342 EU 1996 6 27 96ZZZX3156 1 19960531 G 5521 10902000259 RIB 10902000293 AGUSTA A109 A109A2 0260120 EU LT SYNC ELEV CRACKED D K NONE O OTHER IN INSP/MAINT 1 NM 01 1YH 4183 EM151 7264 LEFT SYNC ELEVATOR CRACKS APPEARING ALONG EDGE OF THE INBOARD RIB, PN 109-0200-02-59, AND PN 109-0200-04-7. DISASSEMBLY REVEALED LOOSE ATTACH ANGLES ON SPAR. CRACKED FRONT AND REAR SPAR. CRACKED SPAR DOUBLERS, PN 109-0200-02-49 AND DASH 33. RECURRING PROBLEM, 5 THIS FLEET. 1 G 7 2 3U H7EU 1996062700343 19960627 00343 EU 1996 6 27 96ZZZX3157 1 19960531 G 5521 10902000259 RIB 10902000294 AGUSTA A109 A109A2 0260120 EU RT SYNC ELEV CRACKED D K NONE O OTHER IN INSP/MAINT 1 NM 01 1YH 4183 EM151 7264 RIGHT SYNC ELEVATOR CRACKS APPEARING ALONG EDGE OF THE INBOARD RIB, PN 109-0200-02-59 AND PN 109-0200-04-7. DISASSEMBLY REVEALED LOOSE ATTACH ANGLES AND CRACKS IN FRONT SPAR AREA. RECURRING PROBLEM. 1 G 7 2 3U H7EU 1996062700344 19960627 00344 WP 1996 6 27 96ZZZX3158 1 19960521 G 6720 369D21832 BEARING 369D21800501 HUGHES 369 369D 4470706 WP T/R PITCH LOOSE D A K NONE O OTHER IN INSP/MAINT 1 WP 07 911FT 811036D DURING ROUTINE INSPECTION OF AD 94-24-04, THE DUPLEX BEARING WAS LOOSE (AXIALLY) INSIDE OF PITCH CONTROL HOUSING (369A18 02) - THE ENTIRE BEARING INCLUDING THE OUTER HOUSING OF THE BEARING. THIS COULD ALLOW THE BEARING TO SPIN INSIDE THE HO USING. SUBMITTER STATED SHOULD BE PRESSURE FIT. 1 G 7 1 3U H3WE 1996062700345 19960627 00345 EU 1996 6 27 96ZZZX3159 1 19960531 G 3230 10905021515 BRACE AGUSTA A109 A109A2 0260120 EU MLG CRACKED D S A K NONE O OTHER IN INSP/MAINT 1 NM 01 55NW 3580 7267 MAIN LANDING GEAR BRACE HAS CRACK LOCATED AT OUTBOARD BEARING BORE. SUBMITTER STATED DIFFICULT TO SEE UNLESS UNIT IS RE MOVED. 1 G 7 2 3U H7EU 1996062700346 19960627 00346 SW 1996 6 27 96ZZZX3160 1 19960509 G 6230 206010335001 LEVER ASSY 206010350021 BELL 206 206L1 1182107 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 1081G 550 45405 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10 1 BEARING. SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT, 549.7 HOURS. 1 G 7 1 3U H2SW 1996062700347 19960627 00347 SW 1996 6 27 96ZZZX3161 1 19960509 G 6230 206010336005 LINK IDLER BELL 206 206L1 1182107 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 1081G 550 45405 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10 1 BEARING. SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT, 549.7 HOURS. 1 G 7 1 3U H2SW 1996062700349 19960627 00349 SW 1996 6 27 96ZZZX3164 1 19960507 G 6210 206015001107 BLADE BELL 206 206L3 1182108 SW M/R SKIN SEPARATED B A ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 365AL A720 51376 INSPECTION FOUND UPPER SURFACE SKIN SEPARATED FROM SPAR AT BLADE TIP. UPON FURTHER INSPECTION, INNER SPAR WAS FOUND HEA VILY CORRODED. SUBMITTER STATED BEFORE NEW BLADE IS PUT INTO SERVICE, REMOVE TIP WEIGHT ASSY, TREAT INSIDE OF SPAR WITH ALODINE AND KORPON PRIMER. WRAP TIP WEIGHTS WITH BARRIER TAPE. REINSTALL TIP WEIGHTS AND SEAL WITH 890 PROSEAL TO ELI MINATE MOISTURE INTRUSION. 1 G 7 1 3U H2SW 1996062700350 19960627 00350 SW 1996 6 27 96ZZZX3165 1 19960509 G 6230 2060103353001 LEVER ASSY 206010350021 BELL 206 206L1 1182107 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 5740L 600 45459 DAILY INSPECTION FOUND BUSHING AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 SP ACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-101 BEARING. SUBMITTER STATES NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 599.6 HOURS. 1 G 7 1 3U H2SW 1996062700351 19960627 00351 SW 1996 6 27 96ZZZX3166 1 19960509 G 6230 206010336005 LINK IDLER 206010350021 BELL 206 206L1 1182107 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 5740L 600 45459 DAILY INSPECTION FOUND BUSHING AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 SP ACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-101 BEARING. SUBMITTER STATES NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 599.6 HOURS. 1 G 7 1 3U H2SW 1996062700354 19960627 00354 EU 1996 6 27 96ZZZX3169 1 19960328 G 6240 117945641 INDICATOR BOLKMS 117 BK117B1 5626012 EU MAST MOMENT DEFECTIVE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 117VU 33 ED70655 7211 WHEN POWER IS APPLIED, RED LIGHT DOES NOT COME ON EACH TIME PRIOR TO TEST. REMOVED AND REPLACED. 1 G 7 2 3U H13EU 1996062700355 19960627 00355 1996 6 27 96ZZZX3170 4 19960323 G 3421 4021541671 GYRO BOLKMS 117 BK117B1 5626012 EU COCKPIT ATTITUDE DEFECTIVE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 214AE 4 84081138 7206 GYRO BACKLIGHTING INOPERATIVE. SLOW TO SPIN UP. REMOVED AND REPLACED. 1 G 7 2 3U H13EU 1996062700356 19960627 00356 1996 6 27 96ZZZX3171 4 19960424 G 2312 064101905 TRANSCEIVER BELL 222 222U 1182140 SW COCKPIT DEFECTIVE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 219HM 16181 47573 RADIO REC. AND CANNOT CHANGE FREQUENCY. REMOVED AND REPLACED. 1 G 7 2 3U H9SW 1996062700357 19960627 00357 1996 6 27 96ZZZX3172 4 19960503 G 3457 066040310111 GPS KLN90A BOLKMS 105 BO105S 5626006 EU COCKPIT DEFECTIVE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 495LF 13398 S645 SHOWS RECEIVER HARDWARE ERROR CODE 0200. REPAIR AS NECESSARY. 1 G 7 2 3U H3EU 1996062700358 19960627 00358 1996 6 27 96ZZZX3173 4 19960426 G 3421 5040017926 GYRO BOLKMS 117 BK117A3 5626015 EU COCKIT ATTITUDE FAILED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 527MB 144 3427 7103 SLOW TO OPERATE, PULL THREE OR FOUR TIMES TO ERECT. REPAIR AS NECESSARY. 1 G 7 2 3U H13EU 1996062700364 19960627 00364 1996 6 27 96ZZZX3179 4 19960214 G 2312 40001452500 TRANSCEIVER RT138F BOLKMS 117 BK117B1 5626012 EU CONTROL HEAD DEFECTIVE B TI1R K NONE N FALSE WARNING IN INSP/MAINT 1 SW 05 170MC 297 7217 ON INSTALLATION IN A/C, CONTROL HEAD GUARD INDICATOR LIGHT ILLUMINATED AND STAYED LIT EVEN WITH NO GUARD MODULE INSTALLE D. REMOVED AND REPLACED. 1 G 7 2 3U H13EU 1996062700365 19960627 00365 1996 6 27 96ZZZX3180 4 19960416 G 2312 40001452500 TRANSCEIVER RT138F BOLKMS 117 BK117B1 5626012 EU SIDE TONE POT MISSING B TI1R K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 05 170MC 269 7217 RECEIVED THIS UNIT WITH SIDE TONE ADJ. POT MISSING FROM AUDIO BOARD. INSTALLED AUDIO SIDE TONE MISSING POT, BENCH ALIGN AND CHECK. REMOVED AND REPLACED. 1 G 7 2 3U H13EU 1996062700366 19960627 00366 EU 1996 6 27 96ZZZX3181 1 19960406 G 5210 1172428111 CATCHER BOLKMS BK117 BK117C1 5626025 EU LT DOOR WORN B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 317MC 7505 WORN LT CATCHER. REMOVED AND REPLACED. 1 G 7 2 3U NC H13EU 1996062700367 19960627 00367 EU 1996 6 27 96ZZZX3182 1 19960406 G 5210 1172428211 CATCHER BOLKMS BK117 BK117C1 5626025 EU LT DOOR WORN B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 317MC 7505 WORN LT CATCHER. REMOVED AND REPLACED. 1 G 7 2 3U NC H13EU 1996062700368 19960627 00368 EU 1996 6 27 96ZZZX3183 1 19960412 G 6720 117317171 BELL CRANK BOLKMS BK117 BK117C1 5626025 EU T/R WORN B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 317MC 7505 BEARING WORN AND STIFF. REMOVED AND REPLACED. 1 G 7 2 3U NC H13EU 1996062700369 19960627 00369 EU 1996 6 27 96ZZZX3184 1 19960413 G 2430 171BS1011 POWER SUPPLY BOLKMS BK117 BK117C1 5626025 EU DC SYSTEM FAILED B TI1R K NONE J WARNING INDICATION IN INSP/MAINT 1 SW 05 317MC 1117 7505 WOULD NOT HOLD CHARGE. WARNING LIGHT CAME ON IN COCKPIT. NO CHARGE. REMOVED AND REPLACED. 1 G 7 2 3U NC H13EU 1996062700370 19960627 00370 1996 6 27 96ZZZX3185 4 19960325 G 2210 701240901 ACTUATOR BOLKMS BK117 BK117C1 5626025 EU DUPLEX PITCH DEFECTIVE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 317MC 94030194 7505 NR 1 AUTOPILOT FAILURE, 1E47. REMOVED AND REPLACED. 1 G 7 2 3U NC H13EU 1996062700371 19960627 00371 1996 6 27 96ZZZX3186 4 19960325 G 2210 7012693901 SERVO MONITOR BOLKMS BK117 BK117C1 5626025 EU NR 1 AUTOPILOT FAILED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 317MC 88110105 7505 NR 1 AUTOPILOT FAILURE, 1E47. REMOVED AND REPLACED. 1 G 7 2 3U NC H13EU 1996062700372 19960627 00372 EU 1996 6 27 96ZZZX3187 1 19960325 G 2140 HTE920018 VALVE BOLKMS BK117 BK117C1 5626025 EU HEAT SYSTEM STICKS B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 317MC 371 7505 VALVE STICKS OPEN. REMOVED AND REPLACED. 1 G 7 2 3U NC H13EU 1996062700373 19960627 00373 EU 1996 6 27 96ZZZX3188 1 19960307 G 2140 HTE920018 ACTUATOR VALVE BOLKMS BK117 BK117C1 5626025 EU CARGO HEAT STICKS B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 317MC 688GB2494 7505 STICKS OPEN. REMOVED AND REPLACED. 1 G 7 2 3U NC H13EU 1996062700374 19960627 00374 EU 1996 6 27 96ZZZX3189 1 19960227 G 2822 1176415103 PUMP BOLKMS BK117 BK117C1 5626025 EU BOOST DEFECTIVE B TI1R O OTHER J WARNING INDICATION CR CRUISE 1 SW 05 317MC 172207 7505 INTERMITTENT TRANSFER PUMP LIGHT IN-FLIGHT (FULL TANK). REMOVED AND REPLACED. 1 G 7 2 3U NC H13EU 1996062700375 19960627 00375 EU 1996 6 27 96ZZZX3190 1 19960326 G 3213 1175000212 SKID PLATE BOLKMS BK117 BK117C1 5626025 EU GEAR WORN B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 317MC 7505 WORN SKID PLATE. REMOVED AND REPLACED 2 EACH. 1 G 7 2 3U NC H13EU 1996062700376 19960627 00376 EU 1996 6 27 96ZZZX3191 1 19960202 G 5530 11730641 VERTICAL FIN BOLKMS BK117 BK117C1 5626025 EU V FIN PLUG LOOSE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 317MC 064 7505 BREAK OUT PLUG LOOSE. REMOVED AND REPLACED. 1 G 7 2 3U NC H13EU 1996062700377 19960627 00377 EU 1996 6 27 96ZZZX3192 1 19960413 G 5210 1172428212 CATCHER BOLKMS BK117 BK117C1 5626025 EU DOOR WORN B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 317MC 7505 WORN RT CATCHER. REMOVED AND REPLACED. 1 G 7 2 3U NC H13EU 1996062700640 19960627 00640 SO 1996 6 27 96ZZZX3193 1 19960516 G 3211 ATTACH FITTING PIPER PA34 PA34200T 7103406 SO MLG TRUNNION LOOSE BOLTS D K NONE O OTHER IN INSP/MAINT 1 GL 21 812JA 5394 347970422 PIPER SB956, PART 2, IS A PROCEDURE FOR PERMANENT COMPLIANCE WITH NEW THICKER BOLTS. THIS RELIEVES THE REPETITIVE INSPE CTIONS OF THE SB. SUBMITTER STATED THE NEW BOLTS ARE ALSO COMING LOOSE. THIS IS THE CONCERN OF THE SB. 1 L 7 2 3O A7SO 1996062700641 19960627 00641 GL 1996 6 27 96ZZZX3194 3 19960604 G 6111 S82NC4 BLADE MCAULY 3AF32C 3AF32C87 GL NR 1 CRACKED B ME4D K NONE O OTHER IN INSP/MAINT 1 SO 15 F03928YS 789172 UPON PROPELLER INSPECTION, NR 1 BLADE WAS FOUND CRACKED IN THE THREADS. BLADE HAS BEEN SCRAPPED. 5 C P22EA 1996062700642 19960627 00642 CE 1996 6 27 96ZZZX3195 1 19960511 G 3231 08411066 BELLCRANK CESSNA 421 421B 2076014 CE RT MLG DOOR BROKEN B EKIR K NONE O OTHER IN INSP/MAINT 1 WP 07 4050Q 5806 421B0274 RT MLG DOOR OPERATING BELLCRANK BROKEN. ARM THAT CONNECTS TO LINKAGE FOR DOOR BROKE OFF ALLOWING DOOR TO REMAIN OPEN. E VIDENCE OF SMALL PREVIOUS CRACK PRIOR TO FAILURE. 1 L 7 2 3O A7CE 1996062700643 19960627 00643 CE 1996 6 27 96ZZZX3196 1 19960603 G 3232 9581001723 ACTUATOR BEECH 33 F33A 1151425 CE GEAR DOOR BINDING D K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 07 8252T 96B033 CE1545 FOUND ACTUATOR HAS INTERNAL BIND - 4 TO 6 TURNS BEFORE UP AND 4 TO 6 TURNS BEFORE BOTTOMING ON THE DOWN SIDE. COMPONENT OVERHAULED BY BEECHCRAFT. 1 L 7 1 3O 3A15 1996062700644 19960627 00644 CE 1996 6 27 96ZZZX3197 1 19960603 G 3232 9581001723 ACTUATOR BEECH 33 F33A 1151425 CE GEAR DOORS INDEX WRONG D K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 07 8252T 94B560 CE1545 GEAR DOORS WILL NOT CLOSE PROPERLY. FOUND IMPROPER INDEXING ON ACTUATOR FROM BEECHCRAFT FOLLOWING OVERHAUL. 1 L 7 1 3O 3A15 1996062700645 19960627 00645 EA 1996 6 27 96ZZZX3198 2 19960530 G 7414 10382896 GEAR ASSY PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA RT MAG TEETH MISSING D K NONE O OTHER IN INSP/MAINT 1 AL 01 59829 1071 317652081 L521661A MAGNETO CHECK PRIOR TO TAKEOFF. ENGINE WOULD NOT RUN ON RT MAGNETO. INSPECTION OF MAGNETO FOUND 4 TEETH MISSING, RT SI DE DISTRIBUTOR GEAR ASSY. ALL TEETH ON RT AND LT GEAR ASSYS BADLY WORN AND CHIPPED. SUSPECT CAUSE, AGE, HEAT, AND LACK OF LUB ON DRIVE GEAR. CLOSER INSPECTION OF MAG GEARS ON INSPECTION. 1 L 7 2 3O 3 O A20SO E14EA 1996062700646 19960627 00646 EA 1996 6 27 96ZZZX3199 2 19960522 G 8530 PISTON PIPER PA32 PA32300 7103212 SO LYC O540 IO540K1A5 41532 EA NR 3 CYLINDER RINGS WORN D K NONE O OTHER IN INSP/MAINT 1 AL 03 4170R 4065 141 3240502 L465848A LOWER SPARK PLUG FOWLED WITH OIL. REMOVED CYLINDER ASSY AND FOUND UPPER FACE OF RINGS KNIFE EDGED. REMOVED AND REPLACE D CYLINDER ASSY. 1 L 7 1 3O 3 O A3SO 1E4 1996062700647 19960627 00647 CE 1996 6 27 96ZZZX3200 1 19960521 G 3230 00282001631 BRACE ASSY BEECH 55 95C55 1152708 CE RETRACT ROD FORK BROKE G K NONE O OTHER IN INSP/MAINT 1 SO 13 7959M 5952 TE189 THE FORK (FITTING) WHICH ATTACHES RETRACT ROD TO DRAG BRACE BROKE. ONE SIDE OF FORK APPEARED TO HAVE BEEN BROKEN FOR SO ME TIME. THIS WAS OLDER STYLE FITTING WELDED TO BRACE. THIS IS DIFFICULT TO INSPECT WITHOUT DISCONNECTING RETRACT ROD. 1 L 7 2 3O 3A16 1996062700648 19960627 00648 CE 1996 6 27 96ZZZX3201 1 19960425 G 7810 99102999 WYE PIPE CESSNA 414 414A 2075907 CE EXHAUST DIVIDER BROKE D K NONE R PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 SO 13 2735A 414A0463 THE FLOW DIVIDER IN THE WYE EXHAUST PIPE GOING TO THE TURBO SUPER CHARGER BROKE CAUSING A PIECE OF METAL APPROXIMATELY 1 .50 INCHES BY 2.50 INCHES LONG TO ENTER THE EXHAUST HOUSING SIDE OF THE TURBO. THIS LIMITED THE TURBOCHARGER MAX OUTPUT TO 5,000 FEET MSL. NO INTERNAL DAMAGE OF TURBOCHARGER TURBINE. SUBMITTER STATED SHOULD INSPECT INSIDE OF WYE PIPE IF MAXIMUM BOOST CANNOT BE ATTAINED. 1 L 7 2 3O A7CE 1996062700649 19960627 00649 CE 1996 6 27 96ZZZX3202 1 19960514 G 2720 04310031 BELLCRANK CESSNA 150 150D 2071810 CE RUDDER HOLES ELONGATED D K NONE O OTHER IN INSP/MAINT 1 SO 13 6006T 3977 15060706 DURING ANNUAL INSPECTION, HORIZONTAL STABILIZER WAS FOUND TO HAVE LOOSE MOTION. A DOUBLER KIT FROM CESSNA WAS INSTALLED TO CORRECT THIS PROBLEM. HOWEVER, DURING REPAIR, IT WAS NOTED THE RUDDER BELLCRANK HAD ELONGATED HOLES WHERE THE CABLE S ATTACHED AND THE TRIM TAB. HORN HAD AN ENLONGATED HOLE TO THE POINT IT WAS ALMOST BROKEN. THE BULKHEAD (REAR) HAD A CRACK .50 INCH LONG NEAR ONE NUTPLATE WHERE THE RUDDER ATTACHED. REPAIRS WERE MADE. TIME SINCE LAST ANNUAL, 195 HOURS. 1 H 7 1 3O 3A19 1996062700650 19960627 00650 CE 1996 6 27 96ZZZX3203 1 19960514 G 2721 04125271 TAB HORN CESSNA 150 150D 2071810 CE RUDDER HOLE ELONGATED D K NONE O OTHER IN INSP/MAINT 1 SO 13 6006T 3977 15060706 DURING ANNUAL INSPECTION, HORIZONTAL STABILIZER WAS FOUND TO HAVE LOOSE MOTION. A DOUBLER KIT FROM CESSNA WAS INSTALLED TO CORRECT THIS PROBLEM. HOWEVER, DURING REPAIR, IT WAS NOTED THE RUDDER BELLCRANK HAD ELONGATED HOLES WHERE THE CABLE S ATTACHED AND THE TRIM TAB. HORN HAD AN ENLONGATED HOLE TO THE POINT IT WAS ALMOST BROKEN. THE BULKHEAD (REAR) HAD A CRACK .50 INCH LONG NEAR ONE NUTPLATE WHERE THE RUDDER ATTACHED. REPAIRS WERE MADE. TIME SINCE LAST ANNUAL, 195 HOURS. 1 H 7 1 3O 3A19 1996062700651 19960627 00651 CE 1996 6 27 96ZZZX3204 1 19960514 G 5312 04121751 BULKHEAD CESSNA 150 150D 2071810 CE AFT CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 13 6006T 3977 15060706 DURING ANNUAL INSPECTION, HORIZONTAL STABILIZER WAS FOUND TO HAVE LOOSE MOTION. A DOUBLER KIT FROM CESSNA WAS INSTALLED TO CORRECT THIS PROBLEM. HOWEVER, DURING REPAIR, IT WAS NOTED THE RUDDER BELLCRANK HAD ELONGATED HOLES WHERE THE CABLE S ATTACHED AND THE TRIM TAB. HORN HAD AN ENLONGATED HOLE TO THE POINT IT WAS ALMOST BROKEN. THE BULKHEAD (REAR) HAD A CRACK .50 INCH LONG NEAR ONE NUTPLATE WHERE THE RUDDER ATTACHED. REPAIRS WERE MADE. TIME SINCE LAST ANNUAL, 195 HOURS. 1 H 7 1 3O 3A19 1996062700652 19960627 00652 SO 1996 6 27 96ZZZX3205 2 19960514 G 7322 3232 FLOAT SHAFT FACET MA35PA CESSNA 150 150D 2071810 CE CONT O200 O200A 17020 SO CARBURETOR BROKEN D K NONE O OTHER IN INSP/MAINT 1 SO 13 6006T 3978 1493 15060706 2048879A DURING CARBURETOR TEAR DOWN, FLOAT SHAFT WAS FOUND WITH ONE END BROKEN, PUMP PLUNGER, PN 194-593, WAS ALSO FOUND DETERIO RATED, AS WELL AS THE BOWL BEING FULL OF TRASH. SUBMITTER STATED CARBURETORS, AS WELL AS ALL OTHER ACCESSORIES, SHOULD BE OVERHAULED OR HAVE A CLOSE INSPECTION EACH 500-800 HRS OF OPERATION. 1 H 7 1 3O 3 O 3A19 E252 1996062700653 19960627 00653 CE 1996 6 27 96ZZZX3206 1 19960331 G 2810 FUEL CAP CESSNA 182 182L 2072726 CE WING WATER LEAK D K NONE O OTHER IN INSP/MAINT 1 CE 07 42876 18259229 FUEL CAPS LEAKING WATER INTO FUEL TANKS WHEN EXPOSED TO RAINY WEATHER. CORRECTED BY INSTALLING CESSNA 182L, SN 59229, ( WW OVAL PLATES) FROM MONARCH AIR AND DEVELOPMENT, INC. 1 H 7 1 3O NT 3A13 1996062700654 19960627 00654 SO 1996 6 27 96ZZZX3207 2 19960529 G 8550 FILL TUBE CONT O360 TSIO360FB 17025 SO ENGINE OIL RUSTY D K NONE O OTHER IN INSP/MAINT 1 NE 03 2135 305857 THE INSIDE OF THE OIL FILLER TUBE AND OIL CAP WERE RUSTED TO THE POINT OF FLAKES OF RUST BEING KNOCKED OFF OF THE SURFAC E AND FALLING INTO THE CRANKCASE. SUBMITTER STATED THESE ASSEMBLIES SHOULD PROBABLY BE MADE OF STAINLESS STEEL. THEY A RE CADMIUM PLATED WHEN NEW, AND THAT DOESN'T SEEM TO PREVENT THE CORROSION. 3 O E9CE 1996062700655 19960627 00655 SO 1996 6 27 96ZZZX3208 1 19960529 G 2821 144280 COVER PIPER PA28 PA28140 7102802 SO GASCOLATOR BOWED FIT D K NONE K FLUID LOSS IN INSP/MAINT 1 NM 01 432FL 4600 287125219 DURING 100-HOUR INSPECTION, NOTICED FUEL STAINS ON GASCOLATOR BOWL. REPLACED GASKET BETWEEN BOWL AND COVER, BUT COULD N OT SEAL. FURTHER INSPECTION WITH A STRAIGHT EDGE REVEALED COVER WAS BOWED, NOT FLAT AT MATING SURFACE. SUSPECT CAUSE: MANY YEARS OF OVERTIGHTENING THE BALE WIRE. FOUND SAME CONDITION ON 2 OTHER PA28140 AIRCRAFT. REPLACED GASCOLATOR COV ERS. RECOMMEND AN INITIAL AND EACH 500 HOURS, INSPECTION OF MATING SURFACES WITH A STRAIGHT EDGE. 1 L 7 1 3O 2A13 1996062700656 19960627 00656 CE 1996 6 27 96ZZZX3209 1 19960510 G 3230 204101743 SUPPORT CESSNA 177 177RG 2073709 CE LT MLG DOWNLOCK PIN CRACKED G K NONE O OTHER IN INSP/MAINT 1 GL 11 8271G 2486 177RG0171 DOWNLOCK SUPPORT LOWER PIN FOUND CRACKED. THIS CONDITION WAS FOUND AFTER FINDING RT DOWNLOCK SUPPORT LOWER PIN BROKEN O FF. THIS CRACK NOT VISIBLE WITH DOWNLOCK ASSEMBLED ON AIRCRAFT. SUSPECT CAUSE: AIRCRAFT OPERATED ON ROUGH LANDING STR IP. RECOMMEND DISASSEMBLY OF LOCK TO ZYGLOW PINS IF A/C IS OPERATED ON ROUGH LANDING STRIPS. 1 H 7 1 3O A20CE 1996062700657 19960627 00657 GL 1996 6 27 96ZZZX3210 1 19960509 G 2822 478360 PUMP FACET DIAMON DA20A1 DA20A1 05626UX GL FUEL DEFECTIVE H CB9T K NONE O OTHER IN INSP/MAINT 1 SW 15 524SS 10084 FUEL PUMP WILL NOT RUN AND TRIPS CIRCUIT BREAKER. 1 L 7 1 3O NT TA4CH 1996062700658 19960627 00658 EA 1996 6 27 96ZZZX3211 2 19960515 G 8530 LW19281 CYLINDER PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA NR 4 CYL EXH CRACKED B KD4R K NONE K FLUID LOSS NR NOT REPORTED 1 SO 17 350MP 342 318152116 L606961A PILOT REPORTED OIL LEAK ON THE LT ENGINE FOLLOWING A FLIGHT OF APPROXIMATELY 1 HOUR. MAINTENANCE UNCOWLED ENGINE AND DI SCOVERED AN EXHAUST STUD FROM THE NR 4 CYLINDER HAD BACKED OUT OF EXHAUST FLANGE. STUD BOUNCED AGAINST THE PUSH ROD HOU SING WEARING A HOLE THROUGH IT APPROX THE SAME SIZE AS THE STUD DIAMETER CAUSING THE OIL LEAK. ENGINE WAS OPERATING NOR MALLY WITH THE EXCEPTION OF THE REPORTED OIL LEAK. AN INVESTIGATION REVEALED A CRACK EXTENDING FROM THE EXHAUST PORT TO STUD RETENTION AREA. CRACK RELIEVED TENSION ON THE STUD CAUSING IT TO BECOME DISLODGED. FURTHER INVESTIGATION REVEALE D 4 OF 6 CYLINDERS HAD CRACKS IN SAME GENERAL AREA. 1 L 7 2 3O 3 O A20SO E14EA 1996062700659 19960627 00659 SW 1996 6 27 96ZZZX3212 1 19960530 G 3230 560247501 CONTROL CABLE MOONEY M20 M20J 5870219 SW EMERG EXTEND BROKEN D A K NONE O OTHER IN INSP/MAINT 1 NM 01 201QK 3524 240290 DURING A ROUTINE CHECK RIDE, PILOT COULD NOT EMERGENCY EXTEND THE GEAR. GEAR WAS EXTENDED ELECTRICALLY WITHOUT INCIDENT . DURING INSPECTION OF GEAR EMERGENCY CABLE ASSY, FOUND A BROKEN SWAGE FITTING AT GEAR MOTOR. CABLE ASSY WAS REPLACED. NO FURTHER ACTION TAKEN. 1 L 7 1 3O 2A3 1996062700660 19960627 00660 CE 1996 6 27 96ZZZX3213 1 19960603 G 2910 128050981 LINE CESSNA 210 T210M 2073451 CE MLG RUPTURED E L L O ABORTED APPROACH OTHER K P FLUID LOSS NO WARNING INDICATION AP APPROACH 1 GL 03 7398M 9000 G2018 SUBJECT HYDRAULIC LINE FAILED IN SERVICE CAUSING HYDRAULIC FLUID LEAK. LANDING GEAR COULD NOT BE HAND PUMPED DOWN. SUB MITTER RECOMMENDS CLOSE INSPECTION OF ALL HYDRAULIC LINES DURING ROUTINE INSPECTIONS. 1 H 7 1 3O 3A21 1996062700661 19960627 00661 CE 1996 6 27 96ZZZX3214 1 19960612 G 2710 CONTROL CABLE CESSNA 188 A188B 2073005 CE AILERON DEFECTIVE B P A FTUR K NONE O OTHER IN INSP/MAINT 1 NE 05 474 DURING ANNUAL INSPECTION, SERVICE BULLETINS WERE BEING REVIEWED. DURING REVIEW OF THESE BULLETINS, THERE WERE NUMEROUS REFERENCES TO PROBLEMS WITH PULLEYS AND CABLES IN THE AILERON SYSTEM. UPON INSPECTION OF THE AILERON CABLES, THERE WAS A CABLE FOUND TO BE AT LEAST 60 PERCENT COMPROMISED. THE SB RECOMMENDS REPLACEMENT OF THE CABLES ON OR BEFORE 500 HOURS . SUBMITTER STATED AFTER SEEING THE CONDITION OF THIS COMPROMISED CABLE, IT MIGHT BE WORTH REVIEWING THE RECOMMENDED TI ME CHANGE AND LOWERING THE HOURS. 1 L 7 1 3O A9CE 1996062700662 19960627 00662 SO 1996 6 27 96ZZZX3215 1 19960508 G 5730 6206102 SKIN PIPER PA28 PA28151 7102805 SO WING WALK CRACKED B S RMMR K NONE O OTHER IN INSP/MAINT 1 CE 01 1195X 9135 287515324 DURING NORMAL INSPECTION, CRACKS WERE FOUND IN STIFFENER CORRIGATION ENDS IN DOUBLER SKIN UNDER WING WALK. WING WALK WA S SOFT (SPRUNG DOWN) WHEN IT WAS STEPPED ON. THIS AIRCRAFT HAS INSPECTION HOLES BELOW AND OUTBOARD OF CRACKED PARTS. H OWEVER, MOST OF THE CRACKS WERE INBOARD OF A WING RIB INBOARD OF THESE INSPECTION HOLES. WING WAS REMOVED, PARTS REPLAC ED, AND AIRCRAFT RETURNED TO SERVICE. 1 L 7 1 3O 2A13 1996062700663 19960627 00663 SO 1996 6 27 96ZZZX3216 1 19960508 G 5730 6206104 SKIN PIPER PA28 PA28151 7102805 SO WING WALK CRACKED B RMMR K NONE O OTHER IN INSP/MAINT 1 CE 01 1195X 9135 287515324 DURING NORMAL INSPECTION, CRACKS WERE FOUND IN STIFFENER CORRIGATION ENDS IN DOUBLER SKIN UNDER WING WALK. WING WALK WA S SOFT (SPRUNG DOWN) WHEN IT WAS STEPPED ON. THIS AIRCRAFT HAS INSPECTION HOLES BELOW AND OUTBOARD OF CRACKED PARTS. H OWEVER, MOST OF THE CRACKS WERE INBOARD OF A WING RIB INBOARD OF THESE INSPECTION HOLES. WING WAS REMOVED, PARTS REPLAC ED, AND AIRCRAFT RETURNED TO SERVICE. 1 L 7 1 3O 2A13 1996062700664 19960627 00664 CE 1996 6 27 96ZZZX3217 1 19960604 G 7603 63255534 LEVER CESSNA 185 A185F 2072821 CE THROTTLE CABLE WORN D A A UNSCHED LANDING O OTHER CL CLIMB 1 AL 03 124KT 381 18503765 'AN' BOLT/CASTLE NUT RETAINING HARDWARE FOR THROTTLE CABLE ROD END TO LEVER, LOOSENED AND WORE ITSELF THROUGH LEVER. FA ILURE OCCURRED AT LIFT-OFF, SUCCESSFUL ON-FIELD LANDING WAS MADE. ASSY WAS 85 HOURS OUT OF 100 HOUR INSPECTION. SUBMIT TER SUGGESTS IMPROVING LEVER BY MANUFACTURING OUT OF STEEL INSTEAD OF BRASS WOULD HELP. 1 H 7 1 3O 3A24 1996062700665 19960627 00665 SO 1996 6 27 96ZZZX3218 1 19960606 G 2731 4173436 CONTROL CABLE PIPER PA31T PA31T1 7103126 SO ELEVATOR TRIM FRAYED D A K NONE O OTHER IN INSP/MAINT 1 SO 09 633AB 4509 31T8104021 ELEVATOR TRIM CABLE FRAYED AND BROKEN STRANDS AROUND THE TRIM DRUM - NOT VISIBLE TO INSPECTION UNLESS REMOVED FROM THE T RIM DRUM. SUBMITTER RECOMMENDS REMOVAL AND INSPECT EVERY 2,000 HOURS OR FIVE YEARS. 1 L 7 2 3T A8EA 1996062700666 19960627 00666 CE 1996 6 27 96ZZZX3219 1 19960525 G 7160 BA5110 FILTER ASSY BRACKETT CESSNA 172 172M 2072418 CE CARBURETOR AIR DEFECTIVE D A K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 01 20582 17261414 IN C/W AD 96-09-06 TO REPLACE BRACKETT FILTER ASSY, NEW OUT-OF-BOX INSPECTION FOUND GLUE USED FOR GASKET ON BACK SIDE OF MESH SCREEN. REMOVED DRIED GLUE MATERIAL AND INSTALLED. SUBMITTER STATED THIS I.A. HAS FOUND NEW PARTS INFERIOR IN QU ALITY CONTROL. JUST BECAUSE ITS NEW DOESN'T MEAN IT'S RIGHT. INSPECT IN DETAIL ANY NEW PART TO BE INSTALLED ON AIRCRAF T. MAKE USE OF M OR D'S IF A PART ISN'T RIGHT. ONLY THEN, CAN THE FAA DO THEIR JOB. 1 H 7 1 3O NT 3A12 1996062700667 19960627 00667 CE 1996 6 27 96ZZZX3220 1 19960618 G 2810 FUEL CAP CESSNA 185 A185F 2072821 CE WING TANK DEFECTIVE D K NONE O OTHER IN INSP/MAINT 1 CE 07 9463N 18504361 DESIGN OF THESE FUEL CAPS ALLOWS WATER TO COLLECT IN FILL AREA AFTER RAINS. NEXT REMOVAL OF CAP ALLOWS WATER TO ENTER F UEL TANK. 1 H 7 1 3O 3A24 1996062700668 19960627 00668 CE 1996 6 27 96ZZZX3221 1 19960603 G 7160 05521644 AIR BOX CESSNA 172 172P 2072436 CE CARBURETOR RIVETS LOOSE D A K NONE O OTHER IN INSP/MAINT 1 NE 05 62274 4228 17275240 WHILE DOING AN ANNUAL INSPECTION ON AIRCRAFT ENGINE, MECHANIC NOTICED 2 LOOSE RIVETS HOLDING AIR BOX TOGETHER. REMOVED AIR BOX TO REPAIR AND NOTICED THAT CARBURETOR HEAT FLAPPER WAS HELD BY ONLY ONE RIVET. SUSPECT CAUSE AS IMPROPER RIGGIN G OF CARBURETOR HEAT CONTROL CABLE. SUBMITTER ALSO FINDS THAT IF BOX WAS NOT REMOVED FOR REPAIR, THE FLAPPER DAMAGE MIG HT HAVE GONE UNNOTICED. 1 H 7 1 3O NT 3A12 1996062700669 19960627 00669 SO 1996 6 27 96ZZZX3222 1 19960528 G 3230 4198301 HOOK ASSY PIPER PA31 PA31350 7103110 SO RT DOWNLOCK REQUIRED LUBE D O OTHER J WARNING INDICATION AP APPROACH 1 NE 03 27475 4352 317852021 MAIN LANDING GEAR WOULD NOT LOCK IN THE DOWN POSITION. AFTER AN UNEVENTFUL LANDING, AIRCRAFT WAS PLACED ON JACKS AND TH E DOWNLOCKS WERE FOUND WITHOUT LUBRICATION AND STUCK IN THE UNLOCKED POSITION. IT WAS FOUND THE OPERATOR REQUIRES THE L ANDING GEAR TO BE CLEANED WEEKLY; THUS, REMOVING ALL LUBRICANT. IT IS RECOMMENDED THAT ALL LANDING GEAR PIVOT POINTS BE PROPERLY LUBED AFTER EACH CLEANING. 1 L 7 2 3O A20SO 1996062700670 19960627 00670 SO 1996 6 27 96ZZZX3223 1 19960528 G 3230 4198300 HOOK ASSY PIPER PA31 PA31350 7103110 SO LT DOWNLOCK REQUIRED LUBE D O OTHER J WARNING INDICATION AP APPROACH 1 NE 03 27475 4352 317852021 MAIN LANDING GEAR WOULD NOT LOCK IN THE DOWN POSITION. AFTER AN UNEVENTFUL LANDING, AIRCRAFT WAS PLACED ON JACKS AND TH E DOWNLOCKS WERE FOUND WITHOUT LUBRICATION AND STUCK IN THE UNLOCKED POSITION. IT WAS FOUND THE OPERATOR REQUIRES THE L ANDING GEAR TO BE CLEANED WEEKLY; THUS, REMOVING ALL LUBRICANT. IT IS RECOMMENDED THAT ALL LANDING GEAR PIVOT POINTS BE PROPERLY LUBED AFTER EACH CLEANING. 1 L 7 2 3O A20SO 1996062700671 19960627 00671 CE 1996 6 27 96ZZZX3224 1 19960529 G 3260 63210075 SWITCH CESSNA 414 414A 2075907 CE NLG UPLOCK WIRE BURNED B MGOR O OTHER N FALSE WARNING NR NOT REPORTED 1 CE 09 575JB 3538 414A0426 PILOT REPORTED ALL MLG GREEN LIGHTS ILLUMINATED AND GEAR UNSAFE LIGHT ILLUMINATED IN-FLIGHT. EMERGENCY EXTENSION PERFOR MED, NO CHANGE IN INDICATOR STATUS. AIRCRAFT LANDED WITHOUT INCIDENT. TROUBLESHOOTING REVEALED HIGH RESISTANCE IN THE NLG UPLOCK CIRCUITRY. FURTHER INVESTIGATION FOUND SEVERAL BURNED WIRES IIN THE HEATER BAY. WIRE REPAIRED, GEAR OPERATO NAL CHECK SATISFACTORY. 1 L 7 2 3O A7CE 1996062700672 19960627 00672 CE 1996 6 27 96ZZZX3225 1 19960501 G 3230 MS244614 BEARING 08421211 CESSNA 310 T310R 2074246 CE NLG RODS FAILED D K NONE O OTHER IN INSP/MAINT 1 WP 01 6126C 3811 310R1293 WHILE INSPECTING NOSE LANDING GEAR RODS AND ATTACHMENTS, FOUND NEEDLE BEARINGS SHOWING AND ROD END SITTING HIGHER THAN N ORMAL IN THE IDLER BELLCRANK. REMOVED BOLT RETAINING THE PUSH/PULL ROD AND FOUND BEARING RETAINER SHEARED ON THE UPPER SECTION OF BEARING. 1 L 7 2 3O 3A10 1996062700673 19960627 00673 EA 1996 6 27 96ZZZX3226 1 19960611 G 5510 FLANGE DHAV DHC3 DHC3 2800202 EA RIB ATTACH CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 99 84SF 6001 284 THE TAILPLANE STRUCTURE MAIN RIB FORWARD FLANGES AT THE TAILPLANE LOWER RIB ATTACHMENT FITTING FOUND CRACKED. THE CRACK ING IS FATIGUE RELATED. SUBMITTER STATED TO CORRECT PROBLEM, INSTALL MOD. 3/935 IAW DHC-3 SB 3/50. NOTE: THE DYE PENE TRANT METHOD PER SB 3/46 WOULD NOT DETECT CRACKING ON MAIN RIB DUE TO BEARING PLATES COVERING CRACKS. 1 H 7 1 3R A815 1996062700674 19960627 00674 CE 1996 6 27 96ZZZX3227 1 19960606 G 5210 99120754 SEAL 551123079 CESSNA 500 560CESSNA 2076750 CE CABIN ENTRY FAILED D B EMER. DESCENT O OTHER CR CRUISE 1 SW 05 898CB 2114 5600097 PRESSURIZED ENTRY DOOR SEAL FAILED AT CRUISE ALTITUDE. AIRCRAFT DESCENDED TO 22,000 FEET WHERE THE SECONDARY SEAL FAILE D. AFTER LANDING, WATER WAS DRAINED FROM SEAL CHECK VALVE DRAIN. BOTH SEALS AND AIR LINE GROMMET WERE FOUND WORN AND C RACKED. INSTALLED NEW SEALS AND GROMMET. RE-RIGGED DOOR TO ALLOW BETTER FIT OF SECONDARY SEAL. OPS CHECKS WITH GROUND PRESSURIZATION CART WERE NORMAL. SUSPECT CAUSE: WORN PARTS AND MIS-RIGGED DOOR ALLOWED WATER TO ENTER AND FREEZE IN P RESSURE SEAL; AND, MIS-RIGGED DOOR CAUSED SECONDARY SEAL TO FAIL. SUBMITTER RECOMMENDS CLOSER ATTENTION TO MAINTENANCE AND INSPECTION REQUIREMENTS; AND, TROUBLESHOOTING TECHNIQUES. 2 L 7 2 4F RT A22CE 1996062700675 19960627 00675 SO 1996 6 27 96ZZZX3228 1 19960530 G 3230 491949 SHUTTLE VALVE PIPER PA42 PA42720 7104212 SO NLG ACTUATOR CRACKED B SO5R K NONE K FLUID LOSS NR NOT REPORTED 1 NE 03 775CA 4000 281 425501004 NOSE GEAR SHUTTLE VALVE FITTING CRACKED (FRACTURED) CAUSING A HYDRAULIC LEAK. THE FITTING IN QUESTION SCREWS INTO THE N OSE GEAR ACTUATOR, PN 40874-5, PIPER SB 859 DATED, HAD BEEN COMPLETED. SB 859 CALLS FOR THE INSTALLATION OF A SUPPORT B RACKET. SHUTTLE VALVE, PIPER PN 491-949, WAS REPLACED WITH NEW PART. SUBMITTER STATED THE DEFECTIVE PART MAY HAVE BEEN DAMAGED BEFORE THE SB WAS C/W AND WAS UNDECTABLE. 1 L 7 2 4T A23SO 1996062700676 19960627 00676 SO 1996 6 27 96ZZZX3229 1 19960422 G 2430 BD63 CONNECTOR ELCON GULSTM G1159 G1159 3953505 SO NR 2 BATTERY LOOSE D C D ABORTED TAKEOFF RETURN TO BLOCK J WARNING INDICATION TX TAXI/GRND HDL 1 EA 23 565KC 046 ON TAXI FOR DEPARTURE, THE NR 2 ELECTRICAL SYSTEM WENT TO ZERO VOLTS. UPON INVESTIGATION, FOUND NR 2 BATTERY CONNECTOR SOCKETS LOOSE ACCORDING TO BATTERY TERMINAL GO-NO GO GAUGE. SUBMITTER SUGGESTS THAT ELCON TYPE CONNECTORS BE CHECKED PE RIODICALLY WITH TELEDYNE BATTERY GAUGE, PN TBP2132 OR EQUIVALENT. 2 L 7 2 4F RT A12EA 1996062700677 19960627 00677 SW 1996 6 27 96ZZZX3230 1 19960606 G 2432 SP900 BATTERY MARATHON SWRNGN SA226 SA226TC 8780404 SW NR 2-3 CELLS OVERHEAT B QTVR O OTHER J M WARNING INDICATION OVER TEMP NR NOT REPORTED 1 NM 11 341PL 100 9105060 TC334 BATTERY HOT LIGHT CAME ON DURING TRAINING FLIGHT. REMOVED BATTERY, FOUND 2 CELLS WENT THERMAL. INSTALLED SERVICEABLE B ATTERY. OPS CHECK GOOD. 2 L 7 2 4T RT A8SW 1996062700678 19960627 00678 CE 1996 6 27 96ZZZX3231 1 19960529 G 3230 MS287784 O-RING 66003616 LEAR 24 24B 5170306 CE MLG VALVE WORN C O OTHER K FLUID LOSS AP APPROACH 1 AL 03 335JW 226 O-RING IN MAIN GEAR CONTROL VALVE FAILED CAUSING LOSS OF HYDRAULIC FLUID. FLIGHT CREW BLEW GEAR DOWN. NO DAMAGE TO AIR CRAFT OCCURRED. SUBMITTER STATED O-RING WILL BE INSPECTED MORE FREQUENTLY. 2 L 7 2 4J A10CE 1996062700679 19960627 00679 NM 1996 6 27 96ZZZX3232 1 19960501 G 5753 CARRIAGE BOEING 747 747273C 1384896 NM RT INBD FOREFLAP SHEARED D K NONE O OTHER IN INSP/MAINT 1 SW 99 471EV 20651 FLAP SEQUENCE CARRIAGE FOUND SHEARED DURING INSPECTION. DAMAGE APPEARS TO HAVE HAPPENED A CONSIDERABLE TIME EARLIER. 2 L 7 4 4F A20WE 1996062700680 19960627 00680 CE 1996 6 27 96ZZZX3233 1 19960608 G 3230 1228200321 UPLOCK HOOK 1228200223 BEECH 2000 2000 1152000 CE NLG CRACKED B S PAIR K NONE O OTHER IN INSP/MAINT 1 SO 05 8025L 1027 NC19 A BULGE WAS FOUND WHERE THE UPLOCK ROLLER STRIKES THE UPLOCK HOOK. THE HOOK HAD STARTED CRACKING AT THE BULGE. REPLACE D UPLOCK HOOK. 1 L 7 2 4T RT A38ACE 1996062700681 19960627 00681 EU 1996 6 27 96ZZZX3234 1 19960509 G 2730 P310450002 GUST DAMPER BAG BAE146 BAE146200A 1500266 EU RT/LT ELEVATOR FAILED B A NO1Y K NONE F FLT CONT AFFECTED NR NOT REPORTED 1 EA 35 173US E48 E2031 ON ARRIVAL, ELEVATORS COULD MOVE UNDAMPED FROM STOP-TO-STOP. ON INVESTIGATION, THE HYDRAULIC GUST DAMPERS WERE FOUND FU LLY DISCHARGED AND INEFFECTIVE. THE RIGHT ELEVATOR NR 1 HINGE BRACKET ASSY WAS FRACTURED, REF IPC 55-50-01-05. THE RIG HT ELEVATOR FDR POSITION TRANSMITTER ROD WAS BROKEN AND SOME DAMAGE TO THE SKIN HAD OCCURRED DUE TO OVER-TRAVEL. INVEST IGATION CONTINUES. ON RECOVERY FROM STORAGE, ELEVATOR GUST DAMPERS SHOULD BE CHECKED FOR CHARGE AND LEAKAGE PRIOR TO FE RRY FLIGHT (S/N E48). 2 H 7 4 4F RT A49EU 1996062700682 19960627 00682 EU 1996 6 27 96ZZZX3235 1 19960509 G 2730 P310450002 GUST DAMPER BAG BAE146 BAE146200A 1500266 EU RT/LT ELEVATOR FAILED B A NO1Y K NONE F FLT CONT AFFECTED NR NOT REPORTED 1 EA 35 173US E73 E2031 ON ARRIVAL, ELEVATORS COULD MOVE UNDAMPED FROM STOP-TO-STOP. ON INVESTIGATION, THE HYDRAULIC GUST DAMPERS WERE FOUND FU LLY DISCHARGED AND INEFFECTIVE. THE RIGHT ELEVATOR NR 1 HINGE BRACKET ASSY WAS FRACTURED, REF IPC 55-50-01-05. THE RIG HT ELEVATOR FDR POSITION TRANSMITTER ROD WAS BROKEN AND SOME DAMAGE TO THE SKIN HAD OCCURRED DUE TO OVER-TRAVEL. INVEST IGATION CONTINUES. ON RECOVERY FROM STORAGE, ELEVATOR GUST DAMPERS SHOULD BE CHECKED FOR CHARGE AND LEAKAGE PRIOR TO FE RRY FLIGHT (S/N E73). 2 H 7 4 4F RT A49EU 1996062700683 19960627 00683 WP 1996 6 27 96ZZZX3236 1 19960607 G 6320 369D2512111 PINION SHAFT 369D28100507 HUGHES 369 369E 4470707 WP M/R GEARBOX WORN B A WG3R K NONE O OTHER IN INSP/MAINT 1 WP 27 220PD 1353 6655701000 509E OIL COOLER DRIVE BELT PULLEY HAD WORN THE SPLINES TO BELOW THE 'OVER-PIN' LIMITS. THE PULLEY WAS SEIZED ON THE PINION S HAFT. 1 G 7 1 3U H3WE 1996062700684 19960627 00684 WP 1996 6 27 96ZZZX3237 1 19960430 G 6220 5143711 HUB 5143915 HILLER UH12 UH12D 4360118 WP M/R CRACKED B PN5R K NONE O OTHER IN INSP/MAINT 1 NM 03 58BA 2279 586 2918B 969 WHILE C/W AD 73-20-03 10/30/73, DYE PEN AND VISUAL INSPECTION OF M/R HUB, A CRACK WAS FOUND ABOUT .75 INCHES LONG. M/R HUB WAS REMOVED AND SCRAPPED AND A SERVICEABLE ZERO TSO M/R HEAD ASSY WAS INSTALLED AND AIRCRAFT WAS RETURNED TO SERVICE . 1 G 7 1 3O 4H10 1996062700686 19960627 00686 1996 6 27 96ZZZX3239 4 19960520 G 2562 EB2BCD ELT BELL 206 206B 1181511 SW COCKPIT MALFUNCTION B PN5R K NONE O OTHER IN INSP/MAINT 1 NM 03 4TD 9431 35485 3431 ELT WENT OFF WHILE AIRCRAFT WAS IN HANGAR. ELT BATTERY WAS REMOVED TO TURN OFF UNIT. WHEN BATTERY WAS REINSTALLED, THE UNIT WENT OFF AGAIN. ELT WAS REPLACED WITH NEW INSTALLATION AND THIS ONE RETURNED TO MANUFACTURER FOR INSPECTION AND R EPAIR. 1 G 7 1 3U H2SW 1996062700687 19960627 00687 SW 1996 6 27 96ZZZX3240 1 19960529 G 7714 2060626273 GENERATOR GLOBE BELL 206 206B 1181511 SW GAS PROD TACH FAILED D K NONE N FALSE WARNING IN INSP/MAINT 1 CE 09 2778R 2646 2803 PART FAILED AT CRUISE POWER. ENGINE OUT LIGHT ILLUMINATED WITH AUDIO IN HEADSET. RECOMMEND A TIME REPLACEMENT CRITERIA BE ESTABLISHED. 1 G 7 1 3U H2SW 1996062700688 19960627 00688 EU 1996 6 27 96ZZZX3241 1 19960531 G 7120 SD3510005E SUPPORT TUBE STBROS SD3 SD360 8100606 EU ENG LT OTBD CORRODED B WVER K NONE O OTHER IN INSP/MAINT 1 EA 09 631KC SH3407 DURING A MAJOR MODIFICATION OF AIRCRAFT, FOUND CORROSION INSIDE LEFT LOWER OUTBOARD ENGINE SUPPORT TUBE WHERE TUBE JOINS FOOT MOUNT. CORROSION IS PITTED AREA ONE INCH BY ONE INCH. CORROSION MAY BE FROM WATER. 2 H 7 2 4T A41EU 1996062700689 19960627 00689 GL 1996 6 27 96ZZZX3242 1 19960501 G 2730 283M SLEEVE AMTR CH600 CH600 05623RC GL ELEVATOR CABLE MISINSTALLED D K NONE W INADEQUATE Q C NR NOT REPORTED 1 CE 05 596WC 6964 A-28-3M NICOPRESS SLEEVE WAS IMPROPERLY INSTALLED CAUSING CABLE TO RETRACT LEAVING ELEVATOR WITHOUT ANY CONTROL. THIS E ND OF CABLE IS NEXT TO CONTROL STICK. SUBMITTER RECOMMENDS ALL CABLE CONNECTIONS BE INSTALLED WITH TWO SLEEVES ON CONVE NTIONAL AIRCRAFT AS A SAFETY FACTOR. ALL CH-600 AND CH-601 ZODIAC AIRCRAFT. 1 L 7 1 30 NT EXPA1L71 1996070300069 19960703 00069 EU 1996 7 3 96ZZZX3244 1 19960422 G 7714 1179405303 INDICATOR BOLKMS 117 BK117B1 5626012 EU TRIPLE TACH STICKING B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 117LU 67 282 7144 TRIPLE TACHOMETER NR 2 NEEDLE STICKING. REMOVED AND REPLACED. 1 G 7 2 3U H13EU 1996070300070 19960703 00070 EU 1996 7 3 96ZZZX3245 1 19960510 G 3150 1179405211 PANEL BOLKMS 117 BK117A3 5626015 EU ANNUNCIATOR SEGMENTS BROKEN B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 117UC 0021 7098 SEVERAL SEGMENTS BROKEN ON ANNUNCIATOR PANEL. REMOVED AND REPLACED. 1 G 7 2 3U H13EU 1996070300071 19960703 00071 EU 1996 7 3 96ZZZX3246 1 19960519 G 3310 11792039 POWER SUPPLY BOLKMS 117 BK117B1 5626012 EU LIGHT DEFECTIVE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 117VU 19 1168 7211 LIGHTS WEAK. BATTERY WILL NOT CHARGE. SPARKS OCCUR WHEN UNIT IS TOUCHED TO A/C AND HOOKED UP. REMOVED AND REPLACED. 1 G 7 2 3U H13EU 1996070300072 19960703 00072 EU 1996 7 3 96ZZZX3247 1 19960416 G 7714 1179405303 INDICATOR BOLKMS 117 BK117A3 5626015 EU TRIPLE TACH NEEDLE STICKS B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 1140H 22 426 7078 NR NEEDLE STICKING WHEN STARTING ENGINES, 21.8 HOURS SINCE REPAIR. REMOVED AND REPLACED. 1 G 7 2 3U H13EU 1996070300073 19960703 00073 EU 1996 7 3 96ZZZX3248 1 19960404 G 7714 1179405303 INDICATOR BOLKMS 117 BK117A3 5626015 EU TRIPLE TACH READS HIGH B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 1140H 524 7078 NR TACHOMETER NEEDLE READING 15 PERCENT HIGH. REMOVED AND REPLACED. 1 G 7 2 3U H13EU 1996070300074 19960703 00074 EU 1996 7 3 96ZZZX3250 1 19960419 G 7931 53408A TRANSMITTER AEROSP SA365 SA365N1 8680668 EU ENG OIL PRESS DEFECTIVE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 365SC 1035 6298 OUT OF CALIBRATION. AT FLIGHT IDLE (70 PERCENT NG), OIL PRESSURE INDICATING AT BOTTOM RED LINE. SWAPPED ENGINES, SAME RESULTS. 1 G 7 2 3U H10EU 1996070300075 19960703 00075 NE 1996 7 3 96ZZZX3251 1 19960328 G 6420 7610305015104 RETAIN WASHER SKRSKY S76 S76 8143010 NE T/R LOOSE B A AC2R K NONE O OTHER IN INSP/MAINT 1 SW 03 5402T 760140 TAIL ROTOR PITCH BEAM WAS FOUND LOOSE ON PITCH SHAFT WITH .1250 INCH GAP BETWEEN WASHER-RETAINER AND NUT. INSPECTION RE VEALED PITCH BEAM NUT WAS BOTTOMING OUT ON PITCH SHAFT, PREVENTING PITCH BEAM AND WASHER FROM SEATING. THE PITCH SHAFT HAD 80 HOURS SINCE INSTALLATION WITH TAIL GEARBOX. (NUT WAS PROPERLY TORQUED). REPLACED PITCH SHAFT ASSY, PITCH BEAM A ND WASHER-RETAINER. 1 G 7 2 3U H1NE 1996070300076 19960703 00076 NE 1996 7 3 96ZZZX3252 1 19960328 G 6420 7635805121042 PITCH SHAFT SKRSKY S76 S76 8143010 NE T/R LOOSE B A AC2R K NONE O OTHER IN INSP/MAINT 1 SW 03 5402T 80 C06400165 760140 TAIL ROTOR PITCH BEAM WAS FOUND LOOSE ON PITCH SHAFT WITH .1250 INCH GAP BETWEEN WASHER AND NUT. INSPECTION REVEALED PI TCH BEAM NUT WAS BOTTOMING OUT ON PITCH SHAFT, PREVENTING PITCH BEAM AND WASHER-RETAINER FROM SEATING. THE PITCH SHAFT HAD 80 HOURS SINCE INSTALLATION WITH TAIL ROTOR. GEARBOX, PITCH SHAFT, PITCH BEAM, AND WASHER-RETAINER ARE WORN (NUT WA S PROPERLY TORQUED). REPLACED PITCH SHAFT ASSY, PITCH BEAM, AND WASHER-RETAINER. 1 G 7 2 3U H1NE 1996070300077 19960703 00077 NE 1996 7 3 96ZZZX3253 1 19960328 G 6420 7610305001101 PITCH BEAM SKRSKY S76 S76 8143010 NE T/R LOOSE B A AC2R K NONE O OTHER IN INSP/MAINT 1 SW 03 5402T D05700129 760140 TAIL ROTOR PITCH BEAM WAS FOUND LOOSE ON PITCH SHAFT, WITH .1250 INCH GAP BETWEEN WASHER-RETAINER AND NUT. INSPECTION R EVEALED PITCH BEAM NUT WAS BOTTOMING OUT ON PITCH SHAFT, PREVENTING PITCH BEAM AND WASHER FROM SEATING. THE PITCH SHAFT HAD 80 HOURS SINCE INSTALLATION WITH TAIL GEARBOX (NUT WAS PROPERLY TORQUED). REPLACED PITCH SHAFT ASSY, PITCH BEAM, A ND WASHER-RETAINER. 1 G 7 2 3U H1NE 1996070300078 19960703 00078 SW 1996 7 3 96ZZZX3254 1 19960511 G 6330 2060333506101 RESTRAINT BELL 206 206L1 1182107 SW M/R XMSN BEARING WORN B ZV1R K NONE O OTHER IN INSP/MAINT 1 SW 03 2618 586 LK2694 45503 RESTRAINT SPRING BEARINGS 2 EACH WORN BEYOND LIMITS. REPLACED BEARINGS, PN 206-033-509-003. 1 G 7 1 3U H2SW 1996070300079 19960703 00079 EU 1996 7 3 96ZZZX3255 1 19960210 G 2436 51530001EI REGULATOR BOLKMS BK117 BK117C1 5626025 EU DC GENERATOR DEFECTIVE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 317MC 1068 14031 7505 GENERATOR WILL NOT COME ON LINE. REMOVED AND REPLACED. 1 G 7 2 3U NC H13EU 1996070300080 19960703 00080 1996 7 3 96ZZZX3256 4 19960429 G 3416 B4553110004 ALTIMETER BOLKMS BK117 BK117C1 5626025 EU COCKPIT FAULTY B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 317MC 4877 7505 ADJUSTMENT KNOB DIFFICULT TO TURN. REMOVED AND REPLACED. 1 G 7 2 3U NC H13EU 1996070300081 19960703 00081 EU 1996 7 3 96ZZZX3257 1 19960425 G 5210 1172428403 STOP BOLKMS BK117 BK117C1 5626025 EU DOOR BROKE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 317MC 7505 DOOR STOP BROKE OFF REAR PART OF STOP. REMOVED AND REPLACED. 1 G 7 2 3U NC H13EU 1996070300082 19960703 00082 EU 1996 7 3 96ZZZX3258 1 19960315 G 3340 A490ATSCF POWER SUPPLY BOLKMS 105 BO105S 5626006 EU ANTI COLLISION INOPERATIVE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 911LF 03157 S663 UPPER ANTI-COLLISION LIGHT INOPERATIVE. REMOVED AND REPLACED. 1 G 7 2 3U H3EU 1996070300083 19960703 00083 SW 1996 7 3 96ZZZX3259 1 19960512 G 6330 222031605109 FLEXTURE BELL 222 222 1182122 SW M/R XMSN DEBONDED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 911LW LK0077 47520 BOTH UNITS DEBONDED AT END FITTING. 1 G 7 2 3U H9SW 1996070300084 19960703 00084 SW 1996 7 3 96ZZZX3260 1 19960512 G 6330 222031605109 FLEXTURE BELL 222 222 1182122 SW M/R XMSN DEBONDED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 911LW LK0063 47520 BOTH UNITS DEBONDED AT END FITTING. 1 G 7 2 3U H9SW 1996070300085 19960703 00085 SW 1996 7 3 96ZZZX3261 1 19960512 G 6330 222031605109 FLEXTURE BELL 222 222 1182122 SW M/R XMSN DEFECTIVE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 911LW 5 LK0126 47520 AS FLEXTURE ASSY MOVES AT END FITTING, ONE FITTING DOES NOT HAVE PROPER CLEARANCE CAUSING A LOUD 'POP' TO BE HEARD AND F ELT THROUGHOUT THE AIRFRAME. 1 G 7 2 3U H9SW 1996070300390 19960703 00390 SO 1996 7 3 96ZZZX3319 2 19960618 G 8530 653452A9 CYLINDER CESSNA 404 404CESSNA 2075901 CE CONT O520 GTSIO520M 17032 SO NR 2 HEAD CRACKED B S APCR K NONE O OTHER IN INSP/MAINT 1 NM 01 48SA 163 4040417 276408R FOUND NR 2 CYLINDER HEAD CRACKED AT LOWER SPARK PLUG HOLE. 1 L 7 2 3O 3 O A25CE E7CE 1996070300391 19960703 00391 CE 1996 7 3 96ZZZX3320 1 19960606 G 3252 22430151 ATTACH CLAMP 2243001203 CESSNA 182 TR182 2072735 CE SHIMMY DAMPENER FAILED D A K NONE O OTHER NR NOT REPORTED 1 GL 15 4594S 2742 R18201351 THE SHIMMY DAMPENER CLAMP ASSY, PN 2243015-1, ALIGNMENT PIN FAILED AND CAUSED THE SHIMMY DAMPENER TO ROTATE ON THE STRUT HOUSING AND IMPROPERLY ALIGN THE DAMPENER CAUSING THE DAMPENER TO JAM THE LANDING GEAR IN THE UP POSITION. NOTE: THE DAMPENER CLAMP LOOKS TO HAVE BEEN REPAIRED AT ONE TIME. 1 H 7 1 3O 3A13 1996070300392 19960703 00392 EA 1996 7 3 96ZZZX3321 2 19960503 G 8550 FITTING GULSTM AA5 AA5B 3960105 SO LYC O360 O360A4K 41514 EA ACCESSORY CASE FAILED D A K NONE K FLUID LOSS NR NOT REPORTED 1 SW 15 28462 125 AA5B0626 L2208436A OIL PRESSURE FITTING AT ENGINE TO GAUGE HAD BRASS FITTING AND THEN 90 DEGREE RESTRICTIVE FITTING. APPEARS TO HAVE BEEN TOO CLOSE TO MOUNT. BRASS FITTING BROKE FLUSH AT ACCESSORY CASE AND OIL PUMPED OUT OF ENGINE. BRASS FITTING APPEARED T O BE INCORRECT PART NUMBER. 1 L 7 1 3O 3 O A16EA E286 1996070300393 19960703 00393 CE 1996 7 3 96ZZZX3322 1 19960601 G 3260 608100832 SUPPORT ASSY BEECH 58 58TC 1152746 CE RT MLG WORN B L A GOGR O OTHER O OTHER AP APPROACH 1 SW 11 60234 2649 TK92 MLG MALFUNCTIONED, ACFT EXAMINED AND FND FOLLOWING PARTS DAMAGED: RT RETRACT ROD (35-81512547), RT INBD GEAR DOOR (35-8 150055-169), RT BRAKE ASSY (03014500) FLAP SHAFT (3X5K8720A63-5/16), AND FLAP ACT WIRES. RT WING, STEP, AILERON, PROP, AND ENG SUSTAINED DAMAGES. DAMAGED PARTS REPLACED. LANDING GEAR TESTED MANUALLY TO INVESTIGATE RIGGING OF SYS AND ELEC OPERATED 20 TIMES WHEN SYS AGAIN FAILED TO EXTEND BENDING RT RETRACT ROD (35-815125-47) AND PUSHING IT INTO REAR SPAR W EB OF FWD CABIN WING CARRY-THRU SPAR IN CENTER WING SECT DAMAGING SPAR WEB. FND RT GEAR (60-810028-17) HAD HUNG ON A NU T WHICH SECURES UPLOCK STOP (60-810092-14) WHICH IS ATTACHED TO DOWNLOCK SUPPORT ASSY (60-810083-2). 1 L 7 2 3O A23CE 1996070300394 19960703 00394 EA 1996 7 3 96ZZZX3323 2 19960618 G 8530 LW12993 CYLINDER MOONEY M20 M20J 5870219 SW LYC O360 IO360A3B6 41514 EA ROCKER BOX DRAIN CRACKED D S A K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 05 201RP A319521 240215 L1725451AC FOUR NEW LW-12993 CYLINDERS HAVE CRACKS AT THE ROCKER BOX DRAIN FITTING BOSS. THESE CRACKS OCCUR AT A CASTING FLAW. TH IS MAY BE CAUSED BY THE TAPERED THREAD OF THE MS-20823-6D ELBOW FITTING. 1 L 7 1 3O 3 O 2A3 1E10 1996070300395 19960703 00395 EA 1996 7 3 96ZZZX3324 2 19960618 G 8530 LW12993 CYLINDER MOONEY M20 M20J 5870219 SW LYC O360 IO360A3B6 41514 EA ROCKER BOX DRAIN CRACKED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 05 201RP A300517 240215 L1725451AC FOUR NEW LW-12993 CYLINDERS HAVE CRACKS AT THE ROCKER BOX DRAIN FITTING BOSS. THESE CRACKS OCCUR AT A CASTING FLAW. TH IS MAY BE CAUSED BY THE TAPERED THREAD OF THE MS-20823-6D ELBOW FITTING. 1 L 7 1 3O 3 O 2A3 1E10 1996070300396 19960703 00396 EA 1996 7 3 96ZZZX3325 2 19960618 G 8530 LW12993 CYLINDER MOONEY M20 M20J 5870219 SW LYC O360 IO360A3B6 41514 EA ROCKER BOX DRAIN CRACKED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 05 201RP A340519 240215 L1725451AC FOUR NEW LW-12993 CYLINDERS HAVE CRACKS AT THE ROCKER BOX DRAIN FITTING BOSS. THESE CRACKS OCCUR AT A CASTING FLAW. TH IS MAY BE CAUSED BY THE TAPERED THREAD OF THE MS-20823-6D ELBOW FITTING. 1 L 7 1 3O 3 O 2A3 1E10 1996070300397 19960703 00397 EA 1996 7 3 96ZZZX3326 2 19960618 G 8530 LW12993 CYLINDER MOONEY M20 M20J 5870219 SW LYC O360 IO360A3B6 41514 EA ROCKER BOX DRAIN CRACKED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 05 201RP A167521 240215 L1725451AC FOUR NEW LW-12993 CYLINDERS HAVE CRACKS AT THE ROCKER BOX DRAIN FITTING BOSS. THESE CRACKS OCCUR AT A CASTING FLAW. TH IS MAY BE CAUSED BY THE TAPERED THREAD OF THE MS-20823-6D ELBOW FITTING. 1 L 7 1 3O 3 O 2A3 1E10 1996070300398 19960703 00398 CE 1996 7 3 96ZZZX3327 1 19960603 G 2910 128050981 LINE CESSNA 210 T210M 2073451 CE HYDRAULIC SYS RUPTURED E O OTHER K J FLUID LOSS WARNING INDICATION AP APPROACH 1 GL 03 7398M 9000 21062018 HYDRAULIC LINE FAILED IN SERVICE CAUSING HYDRAULIC FLUID LEAK. LANDING GEAR COULD NOT BE HAND PUMPED DOWN. SUBMITTER R ECOMMENDS CLOSE INSPECTION OF ALL HYDRAULIC LINES DURING ROUTINE INSPECTIONS. 1 H 7 1 3O 3A21 1996070300400 19960703 00400 SO 1996 7 3 96ZZZX3329 1 19960601 G 5500 TUBE PIPER PA22 PA22150 7102210 SO TAIL POST CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 27 7257D 225084 CONVERTED FROM TRI-PACER TO PACER CONFIG BY STC 5A45RM, TIME AS PACER, APPROXIMATELY 1,220 HRS. TAIL POST TUBE CRACKED AT .25 INCH HOLE THAT FORMERLY HELD TAIL SKID IN PLACE, NO PROVISION IN STC TO BEEF UP HOLE AREA OF TAIL POST. 1 H 7 1 3O 1A6 1996070300401 19960703 00401 EA 1996 7 3 96ZZZX3330 3 19960601 G 6110 BOLT BEECH 23 B19 1151215 CE SNSNCH 74D 74DM EA PROPELLER ATTACH STRETCHED D K NONE O OTHER IN INSP/MAINT 1 SO 19 5098M MB889 A47894 DURING ANNUAL INSPECTION, COULD NOT DETERMINE PROPELLER TIME, SO REMOVED FOR GENERAL CLEAN UP PAINT AND INSPECTING. WHE N PROCEEDING TO INSTALL PROP, FOUND 2 BOLTS BADLY STRETCHED IN THREAD AREA. REPLACED ALL BOLTS WITH NEW. AIRCRAFT RECO RDS POOR, SO WOULD RECOMMEND COMPLETE INSPECTION OF PROP WHEN TIME UNKNOWN. 1 L 7 1 3O A1CE 5 N P88614 1996070300402 19960703 00402 SO 1996 7 3 96ZZZX3331 2 19960612 G 8520 628488 LIFTER CESSNA 210 210M 2073450 CE CONT O520 IO520L 17032 SO NR 7 CYLINDER CHIPPED D K NONE O OTHER IN INSP/MAINT 1 SO 15 732LW 1256 21061606 294583R WHILE CLEANING-INSPECTING LIFTER FOR REINSTALLATION, FOUND CAMSHAFT FACE OF LIFTER CHIPPED. 1 H 7 1 3O 3 O 3A21 E5CE 1996070300403 19960703 00403 CE 1996 7 3 96ZZZX3332 1 19960607 G 5320 071349566 STIFFENER 05133745 CESSNA 172 172M 2072418 CE AFT BULKHEAD CORRODED B CSVR K NONE O OTHER IN INSP/MAINT 1 CE 01 6702H 1285 17265545 UPON ANNUAL INSPECTION, RT WING STRUT LOWER AFT BULKHEAD STIFFENER WAS FOUND WITH SURFACE CORROSION (RUST) ON LOWER 60 P ERCENT OF PART. AIRCRAFT HANGARED ON FARM STRIP AND HAS HAD RODENT (MICE) PROBLEMS IN THE PAST. DROPPINGS AND ODOR ACC OUNT FOR THIS. COMBINATION OF RODENTS AND HUMIDITY SUSPECT CAUSE. RODENT CONTROL AND INSPECTION REQUIRED. 1 H 7 1 3O NT 3A12 1996070300404 19960703 00404 SO 1996 7 3 96ZZZX3333 1 19960606 G 2731 4173436 CONTROL CABLE PIPER PA31T PA31T1 7103126 SO ELEV TRIM RUSTED D K NONE O OTHER IN INSP/MAINT 1 SO 09 633AB 4509 31T8104021 RUDDER AND ELEVATOR TRIM CABLES RUSTED. LOCATED UNDER THE CABIN FLOORBOARD AREA. REMOVAL FROM THE AIRCRAFT GAVE A BETT ER VIEW OF THIS CORROSION. THESE CABLES WERE IN AN UNSAFE CONDITION. SUBMITTER SUGGESTS REMOVAL OF THESE CABLES EVERY 2,000 HOURS/5-YEAR INSPECTION. FAA AND NEW PIPER SHOULD RESPOND TO THIS SAFETY OF FLIGHT ITEM ASAP. 1 L 7 2 3T A8EA 1996070300405 19960703 00405 SO 1996 7 3 96ZZZX3334 1 19960606 G 2721 4173418 CONTROL CABLE PIPER PA31T PA31T1 7103126 SO RUDDER TRIM CORRODED D K NONE O OTHER IN INSP/MAINT 1 SO 09 633AB 4509 31T8104021 RUDDER AND ELEVATOR TRIM CABLES RUSTED. LOCATED UNDER THE CABIN FLOORBOARD AREA. REMOVAL FROM THE AIRCRAFT GAVE A BETT ER VIEW OF THIS CORROSION. THESE CABLES WERE IN AN UNSAFE CONDITION. SUBMITTER SUGGESTS REMOVAL OF THESE CABLES EVERY 2,000 HOURS/5-YEAR INSPECTION. FAA AND NEW PIPER SHOULD RESPOND TO THIS SAFETY OF FLIGHT ITEM ASAP. 1 L 7 2 3T A8EA 1996070300406 19960703 00406 1996 7 3 96ZZZX3335 4 19960620 G 6122 2102064 GEAR WOODWARD D210688 GOVERNOR WORN B ME4D K NONE O OTHER IN INSP/MAINT 1 SO 15 1949087M UPON INPSECTION, DRIVE GEAR SPLINE WAS FOUND WORN BEYOND REPAIR. PART HAS BEEN SCRAPPED. 1996070300407 19960703 00407 1996 7 3 96ZZZX3336 4 19960620 G 6122 C290D36T23 GOVERNOR MCAULY PUMP BODY EXCESS WEAR B DJFR K NONE O OTHER IN INSP/MAINT 1 EA 23 DISASSEMBLED GOVERNOR FOR INSPECTION AND FLUSH DUE TO USE OF MOBIL AV 1 OIL. FOUND SEVERE WEAR ON FLYWEIGHTS AND PINS N EARING FAILURE. EXCESSIVE TO SEVERE WEAR ON MAIN BODY DUE TO IDLER GEAR WEAR. PUMP BODY CAVITY WORN OVER SIZE AND EXCE SSIVE WEAR ON MAIN SHAFT SPLINE. WEAR APPEARS TO BE DUE TO LACK OF PROPER LUBRICATION. ADVISED CUSTOMER TO DO THOROUGH INSPECTIONS ON ENGINE AND PARTICULARLY THE COUNTERWEIGHTS. 1996070300409 19960703 00409 SO 1996 7 3 96ZZZX3338 2 19960614 G 8520 6525384 CRANKCASE BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO LT SIDE NR 4 CYL CRACKED B AU3R K NONE O OTHER IN INSP/MAINT 1 WP 15 114PC 1506 TH661 1260357C CRANKCASE FOUND CRACKED, LEFT SIDE, ABOVE NR 4 CYLINDER. THIS IS THE 'HEAVY' STYLE CRANKCASE AND IS NOT COVERED BY AD 7 7-13-22. SUBMITTER RECOMMENDS INCLUDING THIS SERIES CRANKCASE IN AD 77-13-22. 1 L 7 2 3O 3 O 3A16 E5CE 1996070300410 19960703 00410 GL 1996 7 3 96ZZZX3339 3 19960315 G 6114 A3267 BUSHING CESSNA 421 421C 2076016 CE MCAULY 3FF32 3FF32C501 GL HUB WORN D K NONE O OTHER IN INSP/MAINT 1 NM 03 250 804734 PROPELLER HAD AN INTERNAL LEAK AFTER 250 HRS OPERATION SINCE LAST OVERHAUL. THE ROD HAD BEEN RUBBING ON THE BUSHING IN THE BACK OF THE HUB WHICH IS A REPAIR FROM ORIGINAL MANUFACTURER OF ALL ALUMINUM HUBS. THE BUSHING INSTALLED FOR REPAIR IS MADE OF STEEL. MAXIMUM REPAIR DIMENSION FOR HUB OR REPLACEMENT OF BUSHING IS .754 INCH. THE BUSHING MEASURED .762 INCH AND THE ROD HAD WORN TO MINIMUM DIMENSION OF .748 INCH. THIS CAUSED LARGE TOLERANCE AND ALLOWED OIL INTO THE CAVIT Y OF HUB. ROD WAS REPLACED AND BUSHING WAS REPLACED WITH NEW AND RETURNED TO SERVICE. 1 L 7 2 3O A7CE 5 C P45GL 1996070300411 19960703 00411 EA 1996 7 3 96ZZZX3340 2 19960605 G 7414 P-LEAD PIPER PA24 PA24180 7102402 CE LYC O360 O360A1A 41514 EA LT MAGNETO DETERIORATED G K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 GL 05 5984P 2222 241077 L143836 ENGINE INTERMITTENT, ROUGHNESS, WAS BELIEVED CAUSED BY LEFT MAGNETO P-LEAD SHORTING OUT AGAINST OUTSIDE SHIELDING. BOTH LT AND RT P-LEADS INTERNAL INSULATION HAD DETERIORATED TO POWDER. THIS CONTRIBUTED TO ACCIDENT. P-LEADS APPEARED TO B E ORIGINAL EQUIPMENT ON AIRCRAFT. 1 L 7 1 3O 3 O NT 1A15 E286 1996070300412 19960703 00412 SO 1996 7 3 96ZZZX3341 1 19960611 G 7120 MOUNT PIPER PA30 PA30 7103002 SO RT ENGINE CRACKED D K NONE O OTHER IN INSP/MAINT 1 NM 09 411EL 30786 FOUND AT ANNUAL, A CRACK ACROSS THE RING ON RT ENGINE MOUNT LOWER RT SIDE. IT HAD BEEN OVERHAULED JUST 92 HRS BEFORE AN D REPAIRED IN THIS AREA. SUBMITTER STATED ENGINE MOUNTS SHOULD BE THOROUGHLY CHECKED WHEN REPAIRED IN THIS AREA. CRACK S NOT EASILY SEEN. PAINTING MOUNTS A DIFFERENT COLOR WOULD MAKE CRACKS MORE EASILY SEEN. WHITE WOULD BE HIGHLY RECOMME NDED. CRACK NOT ASSOCIATED WITH ANY WELD. 1 L 7 2 3O A1EA 1996070300413 19960703 00413 EA 1996 7 3 96ZZZX3342 2 19960424 G 8530 HELICOIL PIPER PA32 PA32300 7103212 SO LYC O540 IO540K1A5 41532 EA NR 6 CYL PLUG CAME LOOSE D K NONE O OTHER IN INSP/MAINT 1 AL 03 4170R 3965 41 3240502 L465848A SPARK PLUG UPPER HELICOIL CAME LOOSE WITH SPARK PLUG. REMOVED CYLINDER ASSEMBLY AND REPLACED WITH OVERHAULED CYLINDER A SSY. 1 L 7 1 3O 3 O A3SO 1E4 1996070300414 19960703 00414 EA 1996 7 3 96ZZZX3343 2 19960617 G 8530 LW11633 CYLINDER CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA NR 3 CYL LOWER HELICOIL FAILED B CBCR A UNSCHED LANDING E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 NM 03 93069 1356 1285389 L1405315 LOWER SPARK PLUG HELICOIL BLEW OUT ON NR 3 CYLINDER RESULTING IN LOSS OF THAT CYLINDER COMRPESSION AND LOSS OF ENGINE PO WER. AIRCRAFT LANDED ON HIGHWAY WITHOUT INCIDENT. SUSPECT CAUSE: OVERTORQUE OR UNDERTORQUE OF SPARK PLUG ALLOWING PLU G TO MOVE IF UNDERTORQUED, OR PULLED THREADS IF OVERTORQUED. THIS ENGINE HAS STC SE792NW AND SA1008NW - HIGHER COMPRESS ION PISTONS AND WOULD AGGRAVATE THE SUGGESTED CAUSE. 1 H 7 1 3O 3 O NT 3A19 E223 1996070300415 19960703 00415 GL 1996 7 3 96ZZZX3344 3 19960612 G 6114 HUB PIPER PA30 PA30 7103002 SO HARTZL HCE2Y HCE2YL2 GL BLADE SEAL CORRODED D K NONE K FLUID LOSS IN INSP/MAINT 1 NM 03 BG712 PROPELLER HAD LEAKY DOME PRESSURE. ENTIRE PROPELLER HAD BEEN PAINTED. AFTER TEAR DOWN, THE INTERNAL OF THE HUB ON BOTH PROPS HAD SEVERE CORROSION IN BLADE SEAL AREA AND NEAR OPENING WHERE BLADE COMES OUT OF HUB SOCKET. 1 L 7 2 3O A1EA 5 C P9EA 1996070300416 19960703 00416 CE 1996 7 3 96ZZZX3345 1 19960605 G 3500 C1660080101 FILLER VALVE CESSNA 310 310P 2074238 CE OXYGEN SYS GREASE CONTAM D K NONE O OTHER IN INSP/MAINT 1 EA 05 21012 310P0135 FOUND OXYGEN FILLER VALVE IN TOP OF GREASY NOSE WHEELWELL. FOUND VERY DIFFICULT LOCATION TO SERVICE OXYGEN AND KEEP OXY GEN SERVICE EQUIPMENT CLEAN WHILE DOING SERVICING. FEEL THIS IS A DANGEROUS LOCATION FOR OXYGEN EQUIPMENT TO BE INSTALL ED AND CERTIFIED. 1 L 7 2 3O 3A10 1996070300417 19960703 00417 CE 1996 7 3 96ZZZX3346 1 19960614 G 5743 MS21044N3 BOLT CESSNA 310 310Q 2074242 CE LT WS 57.50 LOOSE D K NONE O OTHER IN INSP/MAINT 1 SO 09 7754Q 310Q0254 GEAR SUPPORT LOCK NUTS WORKING LOOSE FROM BOLTS. SUBMITTER STATED ALSO HAVE FOUND BOLTS LOOSE ON OTHER AIRCRAFT. LOOSE NING MAY BE CAUSED BY FLEXING OF THIS AREA. 1 L 7 2 3O 3A10 1996070300418 19960703 00418 CE 1996 7 3 96ZZZX3347 1 19960614 G 5743 AN36A BOLT CESSNA 310 310Q 2074242 CE RT WS 57.50 LOOSE D K NONE O OTHER IN INSP/MAINT 1 SO 09 7754Q 310Q0254 GEAR SUPPORT LOCK NUTS WORKING LOOSE FROM BOLTS. SUBMITTER STATED ALSO HAVE FOUND BOLTS LOOSE ON OTHER AIRCRAFT. LOOSE NING MAY BE CAUSED BY FLEXING OF THIS AREA. 1 L 7 2 3O 3A10 1996070300419 19960703 00419 1996 7 3 96ZZZX3348 4 19960601 G 6113 35323800 BULKHEAD PIPER PA28 PA28161 7102803 SO PROPELLER CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 17 9888K 287816207 DURING ANNUAL INSPECTION, FOUND SEVERELY CRACKED FORWARD SPINNER BULKHEAD. 1 L 7 1 3O 2A13 1996070300420 19960703 00420 SW 1996 7 3 96ZZZX3349 1 19960111 G 3220 540015001 FITTING MOONEY M20 M20G 5870316 SW NLG RUSTY D K NONE O OTHER IN INSP/MAINT 1 SW 07 9145V 4850 690011 DISASSEMBLY TO CHANGE NLG BISCUITS FOUND CORROSION INSIDE FITTING WHICH GOES UP THROUGH BISCUIT. MLG OK. RUST HAS PENE TRATED THROUGH OVER ONE-HALF OF TUBE WELL. THIS TUBE WAS WET WITH MOISTURE AND HAD A RUSTY PASTE. NEW PART WAS UNPAINT ED INSIDE TUBE. SUBMITTER RECOMMENDS PERIODIC INSPECTION AND PERIODIC APPLICATION OF LINSEED OIL. EST PART TIS: 4,850 .0 HRS, 27 YEARS. 1 L 7 1 3O 2A3 1996070300421 19960703 00421 SO 1996 7 3 96ZZZX3350 1 19960515 G 3232 AN8374D FITTING OAS29241 PIPER PA31 PA31 7103102 SO GEAR DOOR CYL FAILED D O OTHER K FLUID LOSS AP APPROACH 1 NM 11 2336V 31135 WHEN LANDING GEAR WAS SELECTED DOWN, GEAR NEVER MOVED. EMERGENCY GEAR EXTENSION WORKED PROPERLY, BUT ALL FLUID WAS GONE WHEN THIRD GREEN LIGHT CAME ON. FOUND DOOR CLOSE 'AN' FITTING HAD BROKEN AND DUMPED FLUID WHEN GEAR COMPLETED UP CYCLE . PIPER PARTS LIST SHOWS AN ALUMINUM FITTING. TT ON ACFT, 7,151.7 HRS. TIME ON ACTUAL FITTING IS UNKNOWN. FITTING BR EAK LOOKED LIKE COMPLETE FAILURE SUDDENLY - NO PRIOR CRACK PATTERN SHOWN. GEAR WORKED NORMALLY AFTER FITTING REPLACED A ND FLUID REPLENISHED. 1 L 7 2 3O A20SO 1996070300422 19960703 00422 SO 1996 7 3 96ZZZX3351 1 19960520 G 5511 RIB AYRES S2 S2RNORMAL 7630202 SO HORZ STAB TUBES RUSTED B A ILIR K NONE O OTHER IN INSP/MAINT 1 WP 07 331U 2136S DURING HORIZ STAB FABRIC REMOVAL, FND RUST HAD STAINED THE WHITE FABRIC INTERIOR WHICH CONTACTS TUBING STRUCTURE. AFTER BEAD BLASTING PAINT OFF, 4 RIB TUBES WERE BLOWN THROUGH RUSTED FROM THE INSIDE OUT. REMAINING TUBES DRILLED TO FACILIT ATE OILING TUBE INTERIORS AS SPECIFIED IN AC 43-13-1A, CHAP 6. AS TUBES WERE BEING DRILLED, 1 ADDITIONAL RIB TUBE WAS C UT OFF STRUCTURE AND ITS INTERIOR WAS FND TO HAVE A CONSIDERABLE AMT OF RUST. 5 TUBES WERE REPLACED AND ALL TUBES WERE OILED AND PART WAS RECOVERED WITH FABRIC. RECOMMEND CLOSE INSPECTION DURING FABRIC REPLACEMENT FOR LEAKING OR RUSTING T UBES. 1 L 7 1 3R NC A3SW 1996070300423 19960703 00423 SO 1996 7 3 96ZZZX3352 1 19960612 G 7930 AN9111 NIPPLE PIPER PA38 PA38112 7103812 SO OIL INDICATOR BROKEN D A A UNSCHED LANDING Y K ENGINE STOPPAGE FLUID LOSS NR NOT REPORTED 1 SW 17 4327E 1049 3878A0553 DURING FLIGHT, THE NIPPLE THAT ATTACHES OIL PRESSURE SENDER AND HOBBS METER SWITCH ASSEMBLY TO A 90 DEGREE ELBOW, BROKE. THE BROKEN NIPPLE CAUSED COMPLETE ENGINE FAILURE. SUBMITTER RECOMMENDS, PN AN911-1J WHICH IS MADE OF STAINLESS STEEL, BE USED TO PREVENT RECURRENCE. NOTE: AN911-1 IS MADE OF COPPER ALLOY. 1 L 7 1 3O A18SO 1996070300424 19960703 00424 NM 1996 7 3 96ZZZX3353 1 19960605 G 2823 10844745 VALVE UNIVAR 108 1082 9230406 NM FUEL SELECTOR STUCK D A O OTHER O OTHER NR NOT REPORTED 1 EA 23 9609K 22 1082609 PILOT REPORTED FUEL SELECTOR VALVE STUCK BETWEEN DETENTS WHILE ATTEMPTING TO CHANGE FROM RT TO LT FUEL TANK. AFTER PUTT ING BOTH HANDS ON VALVE HANDLE, THE PASSENGER AND PILOT WERE ABLE TO ROTATE THE VALVE TO THE LT TANK. DISASSEMBLED THE VALVE AND FOUND SCORING AND GALLING BETWEEN THE VALVE BODY AND ROTATING PLUG, 'FUEL LUBE' WAS PRESENT. SUBMITTER STATES THIS VALVE WAS MANUFACTURED POORLY, PERHAPS A FINISHING STEP WAS MISSED. THIS IS THE SECOND VALVE SEEN DO THIS IN 1 YE AR (ALSO A STINSON). 1 H 7 1 3O A767 1996070300425 19960703 00425 SO 1996 7 3 96ZZZX3354 1 19960611 G 2910 465204 HOSE ASSY PIPER PA31 PA31350 7103110 SO RT MLG RUPTURED D A O OTHER P K NO WARNING INDICATION FLUID LOSS AP APPROACH 1 SO 05 3581C 5945 318052091 PILOT EXTENDED THE LANDING GEAR AND HAD NO NOSE GEAR DOWN AND LOCKED INDICATION. PILOT REPORTED LANDNG GEAR HANDLE FELT SOFT WHEN HANDLE MOVED TO THE NEUTRAL POSITION 'BY HAND'. MANY ATTEMPTS WERE MADE TO GET THE NOSE GEAR DOWN AND LOCKED . EMERGENCY GEAR HAD NO EFFECT. AIRCRAFT LANDED AND NOSE GEAR COLLAPSED. UPON INSPECTION, FOUND AIRCRAFT LOST HYDRAUL IC SYSTEM FLUID, RT MAIN GEAR ACTUATOR HOSE, PIPER PN 465-204 FAILED. THIS NOSE ASSY WAS MFG IN 1979. 1 L 7 2 3O A20SO 1996070300426 19960703 00426 SO 1996 7 3 96ZZZX3355 1 19960618 G 5711 BOLT PIPER PA34 PA34200T 7103406 SO WING SPAR BROKEN B A APCR K NONE O OTHER IN INSP/MAINT 1 NM 01 666HL 347770235 RIGHT WING SPAR LOWER BOLT BROKEN CAUSED BY MOISTURE SETTLING AROUND NUT AND THREADS AND CORRODING BOLT. CORROSION EVID ENT AT BREAK THROUGH 99 PERCENT OF BOLT DIAMETER. SUBMITTER STATES RECURRING PROBLEM ON OLDER AIRCRAFT. OPERATOR KNOWS OF MULTIPLE LIKE FAILURES. RECOMMEND TIME OR CALENDAR LEFT ON THESE BOLTS, 10,000 HRS OR 15 YEARS. 1 L 7 2 3O A7SO 1996070300427 19960703 00427 SO 1996 7 3 96ZZZX3356 1 19960618 G 2750 95509000 BRACKET PIPER PA34 PA34200T 7103406 SO FLAP DETENT CRACKED B A APCR K NONE O OTHER IN INSP/MAINT 1 NM 01 666HL 12035 347770235 FLAP HANDLE DETENT BRACKET CRACKED AT DETENT NOTCH RADII, AND AT LOWER BASE FLANGE RADII. OPERATOR KNOWS OF 2 OTHER SIM ILAR UNITS WITH SAME PROBLEM. 1 L 7 2 3O A7SO 1996070300428 19960703 00428 SO 1996 7 3 96ZZZX3357 1 19960529 G 3213 6792612 TRUNNION PIPER PA32 PA32RT300 7103215 SO LT MLG CRACKED D A K NONE O OTHER IN INSP/MAINT 1 EA 05 3421W 4715 32R7885276 LEFT MAIN GEAR STRUT FOUND COLLAPSED. FURTHER INSPECTION REVEALED TRUNNION ASSY PN 67926-12 CRACKED AND LEAKING. CRACK EXTENDED 90 PERCENT AROUND TRUNNION. CAUSE IS SUSPECTED TO BE FATIGUE. NOTE AD 94-13-11 ONLY EFFECTS PA34 AND PA44 AI RCRAFT. SUBMITTER STATED ATTENTION TO THIS AREA SHOULD BE KEPT IN MIND WHEN INSPECTING AIRCRAFT WITH EARLY/LIGHT TYPE S TYLE CASTINGS NOT EFFECTED BY AD 94-13-11 OR PIPER SB 787B. SUGGEST EXPANSION OF AD COVERAGE TO INCLUDE ALL AIRCRAFT WI TH LIGHT STYLE TRUNNIONS. 1 L 7 1 3O A3SO 1996070300429 19960703 00429 EA 1996 7 3 96ZZZX3358 2 19960426 G 7322 46A226 VENTURI MA45 CESSNA 172 172N 2072434 CE LYC O360 O360A4M 41514 EA CARBURETOR FRACTURED B S ZM3R K NONE O OTHER IN INSP/MAINT 1 WP 07 260ER 3991 1985 75034605 17270223 L3261636A DURING INSPECTION FOR OVERHAUL, VENTURI WAS FOUND BROKEN AT 3 SUPPORT LEGS AT CENTER OF THE VENTURI. 1 H 7 1 3O 3 O NT 3A12 E286 1996071000001 19960710 00001 SO 1996 7 10 96ZZZX3359 1 19960402 G 5720 6208605 STIFFENER PIPER PA28 PA28161 7102803 SO RT WING CRACKED D S K NONE O OTHER IN INSP/MAINT 1 EA 27 4325V 4402 288416017 FOUND LOWER INBOARD WING SKIN STIFFENER ON RT WING CRACKED. 1 L 7 1 3O 2A13 1996071000002 19960710 00002 SW 1996 7 10 96ZZZX3360 1 19960605 G 7160 INLET BBAVIA 8 8GCBC 1220803 SW CARBURETOR AIR CRACKED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 15 495DB 134 37295 DURING INSPECTION, THE BONDO OVERLAY ON FIBERGLASS CARBURETOR AIR INLET WAS FOUND CRACKING. FURTHER INSPECTION SHOWED T HE BONDO WAS LOOSE. USING A PICK, AN AREA .50 INCH BY 1.50 INCH WAS REMOVED. THERE WAS A LARGE AIR POCKET THE OVERLAY DID NOT ADHERE TO. IF THESE PIECES HAD COME LOOSE, THEY WOULD HAVE BEEN SUCKED INTO THE ENGINE. NOTE: AIRCRAFT IS ONL Y ONE YEAR OLD. 1 H 7 1 3O A21CE 1996071000003 19960710 00003 1996 7 10 96ZZZX3361 1 19960601 G 2432 VP400KH CELL SAFT 401767 BATTERY CRACKED B RD4D K NONE W INADEQUATE Q C IN INSP/MAINT 1 EA 25 9509010R INBOUND INSPECTON OF BATTERY SHOWS ALL 20 CELLS INSTALLED TO BE 'REBUILT'. DATA PLATE INSTALLED INDICATES BATTERY WAS ' FUNCTIONALLY BENCH CHECKED AND REBUILT' ON 2-28-95. BATTERY WAS FUNCTIONALLY CHECKED AND FAILED CAPACITY EACH TIME AFTE R 3 DEEP CYCLES. ALL HARDWARE (LINKS, NUTS, AND WASHERS) FOUND EXCESSIVELY CORRODED AND NICKELPLATING DELAMINATING AND PEELING FROM NUTS. SEVEN CELLS FOUND CRACKED AND LEAKING ELECTROLYTE. SAFT MM STATES SECTION 7, PARA 7.2 E. 'REPLACE EACH DEFECTIVE CELL WITH A FACTORY NEW SAFT CELL'. BATTERY FOUND ILLEGAL ACCORDING TO SAFT MANUAL, DOC N 09.94-V 220172 . 1996071000004 19960710 00004 SO 1996 7 10 96ZZZX3362 1 19960604 G 5520 717002 HINGE PIPER PA31 PA31350 7103110 SO LT OTBD STAB CRACKED E K NONE O OTHER IN INSP/MAINT 1 GL 25 28RW 3755 318152103 DURING PHASE 1 INSPECTION 'SMOKING' RIVETS WERE NOTED AT LEFT OUTBOARD ELEVATOR HINGE (ON HORIZONTAL STABILIZER). REMOV ED ELEVATORS AND FOUND HINGE CRACKED APPROXIMATELY '.25 INCH' VERTICALLY. HINGE WAS REPLACED. 1 L 7 2 3O A20SO 1996071000005 19960710 00005 1996 7 10 96ZZZX3363 4 19960611 G 6113 05503401 STABILIZER CESSNA 172 R172K 2072431 CE SPINNER MISSING B JGVR K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS AP APPROACH 1 CE 09 7334K R172258 CUSTOMER COMPLAINED OF ROUGH RUNNING ENGINE DURING SHORT FINAL UPON LANDING. FOUND SPINNER BULKHEAD TO BE CRACKED APPRO XIMATELY 95 PERCENT AROUND ATTACHMENT TO CRANKSHAFT. FURTHER INSPECTION FOUND THE SPINNER BULKHEAD STABILIZER MISSING FROM PROELLER HUB INSIDE SPINNER. BULKHEAD STABIIZER PN 0550340-1. 1 H 7 1 3O 3A17 1996071000006 19960710 00006 1996 7 10 96ZZZX3364 4 19960611 G 6113 05503391 BULKHEAD CESSNA 172 R172K 2072431 CE PROP SPINNER CRACKED B JGVR K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS AP APPROACH 1 CE 09 7334K R172258 CUSTOMER COMPLAINED OF ROUGH RUNNING ENGINE DURING SHORT FINAL UPON LANDING. FOUND SPINNER BULKHEAD TO BE CRACKED APPRO XIMATELY 95 PERCENT AROUND ATTACHMENT TO CRANKSHAFT. FURTHER INSPECTION FOUND THE SPINNER BULKHEAD STABILIZER MISSING FROM PROELLER HUB INSIDE SPINNER. BULKHEAD STABIIZER PN 0550340-1. 1 H 7 1 3O 3A17 1996071000007 19960710 00007 SO 1996 7 10 96ZZZX3365 1 19960531 G 5730 SKIN LUSCOM 8 8E 8190112 SO WING CORRODED D K NONE O OTHER IN INSP/MAINT 1 WP 07 2508K 1600 5235 CORROSION FOUND ON WING SKIN (LOWER) CAUSED BY MOUSE NEST. AIRCRAFT INACTIVE FOR 4 YEARS. INSTALLED WING INSPECTION KI T. 1 H 7 1 3O A694 1996071000008 19960710 00008 CE 1996 7 10 96ZZZX3366 1 19960611 G 3231 1048200503 RETRACT ARM BEECH 58 58P 1152744 CE NLG DOOR CRACKED D K NONE O OTHER IN INSP/MAINT 1 WP 07 1563L 3832 TJ84 DURING THE ANNUAL INSPECTION LANDING GEAR RETRACTION TEST, THE NOSE GEAR DOORS WERE OPEN 1.50 INCHES AND NOSE GEAR TIRE WAS MAKING CONTACT WITH THE RT GEAR DOOR. WITH A SLIGHT BIT OF HAND PRESSURE, THE NOSE GEAR RETRACTED AND DOORS CLOSED. A THOROUGH INVESTIGATION WAS PERFORMED AND FOUND NOSE GEAR RETRACT ARM ASSY SERIOUSLY CRACKED. A NEW PART WAS INSTALLE D AND GER FUNCTINED PROPERLY. DUE TO THE HEAVY WHITE PAINT ON THE DEFECTIVE PART, THE CRACK COULD HAE GONE UNNOTICED FO R QUITE SOME TIME. RECOMMEND THIS PART BE PAINTED WITH PRIMER PAINT ONLY. 1 L 7 2 3O A23CE 1996071000009 19960710 00009 NM 1996 7 10 96ZZZX3367 1 19960613 G 5102 13864 LINE HP3D RAVEN S57 S57A 7485057 NM BURNER LEAKING B GL5R K NONE O OTHER IN INSP/MAINT 1 GL 05 90792 129 HP3D3356 S57A3145 DURING PRESSURE CHECK OF FUEL LINES, DISCOVERED LEAKING THROUGH SHEATHING OF FUEL LINES. FUEL LINES AEROQUIP FC 321-06, MANFACTURED 2Q93. 1 B 0 0 A15CE 1996071000010 19960710 00010 CE 1996 7 10 96ZZZX3368 1 19960604 G 2133 10357620RX VALVE ALIDSIGNAL CESSNA 441 441 2076020 CE OUTFLOW FAILED B PAZR O OTHER J WARNING INDICATION CL CLIMB 1 CE 03 36955 250 32608 4410028 PILOT REPORTED AIRCRAFT WOULD PRESSURIZE ON TAKEOFF UNTIL MAXIMUM DIFFERENTIAL WAS REACHED AND SAFETY VALVE WOULD ACTUAT E. PILOT HAD NO CONTROL OVER RATE. GAINED ACCESS TO OUTFLOW VALVE AND FOUND SCREWS HOLDING THE DIFFERENTIAL SECTION OF CONTROLLER PULLED OUT OF VALVE ALLOWING SPRING TO UNSEAT THIS SECTION. SCREWS WERE NOT LOOSE, BUT HAD PULLED THE THREA DS OUT OF THE PLASTIC BODY OF VALVE. 1 L 7 2 3T RT A28CE 1996071000011 19960710 00011 SO 1996 7 10 96ZZZX3369 2 19960425 G 8520 642395 CRANKSHAFT CONT O520 TSIO520* 17040 SO NR 2 MAIN BRG CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 13 A132M2 REMOVED CRANKSHAFT FROM ENGINE AT 1,425 HOURS FOR OVERHAUL. VISIBLE CRACKS AROUND OIL TRANSFER HOLE AT MAIN BEARING BEH IND ALTERNATOR GEAR. VISIBLE WITH NAKED EYE. CONFIRMED WITH MAGNAFLUX. THIS WAS A FACTORY REBUILT ENGINE. 3 O E8CE 1996071000012 19960710 00012 SW 1996 7 10 96ZZZX3370 1 19960611 G 3220 540015001 FITTING MOONEY M20 M20C 5870208 SW NLG RUSTY D K NONE O OTHER IN INSP/MAINT 1 SW 07 9313V 2656 690091 ON DISASSEMBLY TO CHANGE NLG BISCUITS, FOUND CORROSION INSIDE FITTING WHICH GOES UP THROUGH BISCUITS - MAIN GEAR WERE OK . RUST APPEARS TO HAVE PENETRATED OVER HALF WAY THROUGH TUBE WALL. SUBMITTER RECOMMENDS PERIODIC INSPECTION AND PERIOD IC ADDITION OF LINSEED OIL IN CAVITY. NEW PARTS WERE PAINTED OUTSIDE, BUT NO PAINT IN TUBE. TUBE POINTS UPWARD, SO WAT ER OR MOISTURE WILL NOT DRAIN OUT. ESTIMATE PART TIS: 2,656.0/27 YEARS. 1 L 7 1 3O 2A3 1996071000013 19960710 00013 SO 1996 7 10 96ZZZX3371 2 19960426 G 8550 ENGINE BEECH 36 A36 1151604 CE CONT O520 IO520BB 17032 SO OIL SYSTEM EXCESS SLUDGE B ZM3R K NONE O OTHER IN INSP/MAINT 1 WP 07 3869A 1760 E1853 2745064 ENGINE WAS DISASSEMBLED FOR MAJOR OVERHAUL. FOUND EXCESSIVE SLUDGE BUILD-UP IN CRANKSHAFT AND OIL SUMP. SLUDGE BUILD-U P IN OIL SUMP HAD IMPACTED ALL P/U TUBE SCREENS TO THE POINT OF 80 PERCENT RESTRICTION. THE OIL DRAIN IS FORWARD OF THE OIL P/U TUBE, SO WHEN NOSE OF AIRCRAFT IS UP WHEN DRAINING OIL, IT DOES NOT ALLOW PROPER DRAINAGE OF CONTAMINATION. SU GGEST LOWERING NOSE OF AIRCRAFT AND ALLOWING OIL TO DRAIN OVERNIGHT. 1 L 7 1 3O 3 O 3A15 E5CE 1996071000015 19960710 00015 SO 1996 7 10 96ZZZX3373 2 19960610 G 7414 ES10349276 CONDENSER ELECTROSYS BEECH 55 95B55 1152706 CE CONT O470 IO470L 17026 SO ENGINE MAGNETO DEFECTIVE D K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 99DC TC1490 CS20158672L MAGNETOS OVERHAULED WITH NEW ELECTROSYSTEM CONDENSER, PN E510-349276, CODE NR 03108 AND NR 9544. MAGNETOS CHECKED ON TE ST STAND, OPERATED NORMALLY. MAGS INSTALLED AND TIMED TO ENGINE. DURING GROUND RUN, 3 MAGS CHECKED NORMAL. FOURTH MAG DEVELOPED A 1,000 RPM DROP. CHECKED MAG, FOUND BAD CONDENSER. REPLACED CONDENSER WITH NEW CONDENSER. GROUND RUN, SAM E PROBLEM DEVELOPED. REPLACED CONDENSER WITH A USED BENDIX CONDENSER. ENGINE RAN NORMAL. 1 L 7 2 3O 3 O 3A16 3E1 1996071000016 19960710 00016 CE 1996 7 10 96ZZZX3374 1 19960602 G 3710 442CW4 PUMP AIRBORNE BEECH 58 58P 1152744 CE GYRO PRESSURE DRIVE SHEARED D A K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 25 2110A 7 57651 TJ129 PILOT REPORTED LEFT GYRO PRESSURE INOPERATIVE. INSPECTED AND FOUND SHEARED LEFT PUMP. WHILE REPLACING SYSTEM FILTERS, FOUND IN-LINE FILTER INSTALLED BACKWARDS. THIS IS BELIEVED TO HAVE CAUSED FAILURE. 1 L 7 2 3O A23CE 1996071000017 19960710 00017 SO 1996 7 10 96ZZZX3375 1 19960607 G 3340 A490TCFM1428 POWER SUPPLY PIPER PA31 PA31350 7103110 SO STROBE BURNED D K NONE O OTHER IN INSP/MAINT 1 NE 05 984PA 295 00158 317305104 AIRCRAFT TAIL STROBE WAS OBSERVED NOT TO BE OPERATING. STROBE POWER UNIT WAS FOUND TO BE INOPERATIVE. REMOVED POWER SU PPLY AND REPLACED. POWER SUPPLY WAS OPENED AND FOUND CIRCUIT BOARD BURNED AROUND CAPACITOR. SUSPECT CAPACITOR NEVER DI SCHARGED CAUSING IT TO BECOME HOT. 1 L 7 2 3O A20SO 1996071000018 19960710 00018 SO 1996 7 10 96ZZZX3376 1 19960423 G 7920 HOSE AEROQUIP PIPER PA23 PA23250 7102308 SO RT OIL COOLER LEAKING D K NONE K FLUID LOSS IN INSP/MAINT 1 EA 23 412DC 1300 278054008 HOSE GOING TO OIL COOLER FOUND LEAKING. (AEROQUIP 303-8.) 1 L 7 2 3O 1A10 1996071000020 19960710 00020 CE 1996 7 10 96ZZZX3378 1 19960611 G 2810 531010 FUEL CAP CESSNA 210 210L 2073448 CE WING TANK DEFECTIVE B EATR K NONE O OTHER IN INSP/MAINT 1 GL 09 2220S 21061165 COMPLIANCE WITH AD 94-12-08. AD NO LONGER APPLIES TO THIS AIRCRAFT. 1 H 7 1 3O 3A21 1996071000021 19960710 00021 EA 1996 7 10 96ZZZX3379 2 19960411 G 8530 CYLINDER PIPER PA32 PA32300 7103212 SO LYC O540 IO540K1A5 41532 EA NR 2-6 CYLINDERS WORN D K NONE O OTHER IN INSP/MAINT 1 AL 03 9000N 148 3240883 L1338348A INSPECTION FOUND CYLINDER ASSEMBLIES WERE STEPPED AT TOP OF BORE. RINGS HAD KNIFE EDGE AT TOP FACE OF RING. 1 L 7 1 3O 3 O A3SO 1E4 1996071000022 19960710 00022 SO 1996 7 10 96ZZZX3380 2 19960610 G 8520 641931 BOLT CESSNA 185 A185F 2072821 CE CONT O520 IO520D 17032 SO ENG THROUGH-STUD FAILED D K NONE K FLUID LOSS IN INSP/MAINT 1 AL 05 1473F 637 18502851 293042R THIS THROUGH-BOLT HOLDS CYLINDERS NR 3 AND NR 2 TOGETHER AT TOP OF CLYLINDER, ALSO, BOLT CLAMPS THE CASE TOGETHER. THE THREADS ON THE STUD AND NUT FAILED CAUSING OIL TO LEAK. 1 H 7 1 3O 3 O 3A24 E5CE 1996071000023 19960710 00023 EU 1996 7 10 96ZZZX3381 1 19960420 G 5610 2601114711 CANOPY RAIL 260005001 MRCHTI SF260 SF260 8121206 EU COCKPIT LT DEPARTED G O OTHER D INFLIGHT SEPARATION CL CLIMB 1 EA 21 13FD 1912 1009 FIFTEEN MINUTES AFTER DEPARTURE, LEFT RAIL OF CANOPY FAILED. RIGHT SIDE OF CANOPY STAYED ATTACHED. INCURRED DAMAGE TO THE HORIZONTAL STABILIZER, LEFT SIDE RAIL NOT FOUND. INSPECTED MECHANICAL EMERGENCY RELEASE OF CANOPY. OPERATED NORMAL LY. SUSPECT EXCESSIVE WEAR OF A CRACK ON THE EYELET OF THE CANOPY RAIL. 1 L 7 1 3O A10EU 1996071000024 19960710 00024 CE 1996 7 10 96ZZZX3382 1 19960528 G 2434 1169 BRUSH BLOCK 649304R CESSNA 310 310R 2074245 CE ALTERNATOR EXCESS WEAR D K NONE O OTHER IN INSP/MAINT 1 GL 09 103FS 141 H3095080R 310R1834 DISASSEMBLY AFTER ALTERNATOR FAILURE REVEALED PREMATURE AND EXCESSIVE WEAR ON BRUSHES. TIME SINCE OVERHAUL 141.0 HOURS. SUBMITTER STATED POSSIBLE DEFECTIVE BRUSHES OR IMPROPER INSTALLATION. 1 L 7 2 3O 3A10 1996071000025 19960710 00025 SO 1996 7 10 96ZZZX3383 1 19960610 G 8120 TH08A60 TURBOCHARGER GARRTT PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA SHAFT FAILED D A K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 GL 25 123MA 20 40917D9001 318152024 L839961A TURBO OVERHAULED 12-7-92, PLACED IN SERVICE 5-17-96. AFTER TWENTY HOURS IN SERVICE, REPORTED INCREASED VIBRATION LEVEL, FOLLOWED BY MANIFOLD PRESSURE REDUCTION, THEN BY ENGINE COMPARMTENT FIRE. FOUND TURBOSHAFT SHEARED, COMPRESSOR AND TUR BINE WHEELS DAMAGED. ALL ATTACHING HARDWARE HAD SHAKEN LOOSE FROM TURBO, ALL SAFETY PLATES, LOCK WASHERS, ETC., FOUND I N PLACE. 1 L 7 2 3O 3 O A20SO E14EA 1996071000027 19960710 00027 CE 1996 7 10 96ZZZX3385 1 19960610 G 5330 SKIN CESSNA 170 170B 2072306 CE AFT LT MLG LEG CRACKED D K NONE O OTHER IN INSP/MAINT 1 GL 19 3487D 27030 UPON INSPECTION, A 3 INCH CRACK WAS DISCOVERED AFT OF THE LEFT LANDING GEAR LEG ADJACENT TO THE GEARBOX. WAS DIFFICULT TO SEE, DUE TO CLOSE PROXIMITY TO OVERLAPPING EXTERIOR GEARBOX SKIN. WOULD RECOMMEND USE OF LIGHT BELOW FUSELAGE WHILE INSPECTING THROUGH CABIN FLOOR PANELS. 1 H 7 1 3O A799 1996071000028 19960710 00028 1996 7 10 96ZZZX3386 1 19960501 G 2460 W31X2M1G5 BREAKER AMF HOUSING CRACKED G K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 07 WHEN PREPARING TO INSTALL BREAKER ON AN AIRCRAFT, ATTEMPTED TO REMOVE THE TERMINAL'S SCREWS ON BACK OF BREAKERS. ALL 4 BREAKER HOUSINGS CRACKED DUE TO THE SCREWS BEING TOO TIGHT FROM THE FACTORY. BEFORE REMOVING SCREWS, PLACE TERMINAL IN A VISE TO HOLD TERMINAL FROM TWISTING. 1996071000029 19960710 00029 WP 1996 7 10 96ZZZX3387 1 19960617 G 2910 15807D SEAL RING AV16A1173A DOUG DC8 DC8* WP HYD GATE VALVE FAILED B DM4R K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 19 TEN EACH NEW SEALS WERE RECEIVED FROM THE AUTHORIZED DISTRIBUTOR FOR THE MANUFACTURER. THIS SEAL IS USED IN SKYDROL HYD RAULIC FLUID, BUT THE NEW SEALS FAILED UPON INSTALLATION (WOULD NOT SEAL). THE SEALS SWELL WHEN INTRODUCED TO SKYDROL F LUID. SUBMITTER STATED SEAL IS MADE OF WRONG MATERIAL. 2 L 7 4 4J F 4A25 1996071000030 19960710 00030 SO 1996 7 10 96ZZZX3388 1 19960612 G 5751 902010501 SUPPORT ASSY GULSTM AA5 AA5B 3960105 SO LT AIL BRG OTBD CRACKED D A K NONE O OTHER IN INSP/MAINT 1 EA 25 4533Q 6549 1186 DURING ANNUAL INSPECTION ON GRUMMAN TIGER AA5B, FOUND LEFT AILERON OUTBOARD BEARING SUPPORT ASSY CRACKED APPROXIMATELY . 25 INCH INBOARD OF LOWER BOLT HOLE. 1 L 7 1 3O A16EA 1996071000031 19960710 00031 CE 1996 7 10 96ZZZX3389 1 19960613 G 7920 62402312D HOSE BEECH 200 200BEECH 1152920 CE OIL SYSTEM DISINTEGRATED D A A UNSCHED LANDING J WARNING INDICATION NR NOT REPORTED 1 SW 13 29HF 0280 BB685 INNER LINER OF AEROQUIP HOSE DISINTEGRATED, PLUGGED THE BYPASS VALVE AND SCREEN, AND CONTAMINATED OIL SYSTEM, TORQUEMETE R FLUCTUATED AND OIL PRESSURE FELL TO 60 PSI AND ENIGNE WAS SHUT DOWN IN-FLIGHT. PIECES OF HOSE WERE FOUND IN OIL COOLE R, 6 INCHES BY 1 INCH IN SIZE. ENGINE WAS REMOVED AND SENT TO PRATT AND WHITNEY FOR DISASSEMBLY, CLEAN AND REPAIR AS NE CESSARY. REPAIRS INCLUDED SUN GEAR, REDUCTION GEARS, OIL PUMP, PROP GOVERNOR, SCAVENGE PUMP, OIL COOLER, AND NOZZLE SCR EENS, ETC. 1 L 7 2 4T A24CE 1996071000033 19960710 00033 SO 1996 7 10 96ZZZX3391 1 19960610 G 2910 1159P2051813 TUBE ASSY GULSTM G1159 G1159A 3970109 SO LT PYLON CHAFED B S RO3R K NONE O OTHER IN INSP/MAINT 1 CE 03 XAMEY 252 WHILE GAINING ACCESS TO THE LT PYLON AREA, NOTED MAIN HYDRAULIC LINE LOCATED IN AFT SECTION OF PYLON AREA FOUND CHAFING THE OUTER WALL AT POINTS WHERE ADEL CLAMPS ATTACH. ALSO, ADDITIONAL CHAFING WAS FOUND ON THE SAME LINE WHICH APPEARED T O BE CAUSED BY WIRE BUNDLE STRAPS CHAFING AGAINST THE LINE. PROPER SIZE ADEL CLAMPS WITH PROPER PROTECTIVE COATINGS WER E INSTALLED (TEFLON COATED); MAIN HYDRAULIC LINE AND WIRE AND WIRE BUNDLE WERE REPOSITIONED TO PREVENT FUTURE CHAFING. 2 L 7 2 4F A12EA 1996071000034 19960710 00034 SO 1996 7 10 96ZZZX3392 1 19960610 G 2910 1159P2051814 TUBE ASSY GULSTM G1159 G1159A 3970109 SO RT PYLON CHAFED B S RO3R K NONE O OTHER IN INSP/MAINT 1 CE 03 375NM 375 WHILE GAINING ACCESS TO THE PYLON AREA, NOTED THE MAIN HYDRAULIC LINE LOCATED IN THE AFT SECTION OF THE PYLON AREA WAS F OUND CHAFING THE OUTER WALL. CHAFING APPEARED TO BE CAUSED BY WIRE BUNDLE STRAPS CHAFING AGAINST THE LINE. MAIN HYDRAU LIC LINE AND WIRE BUNDLE WERE REPOSITIONED TO PREVENT FUTURE CHAFING. 2 L 7 2 4F A12EA 1996071000035 19960710 00035 EU 1996 7 10 96ZZZX3393 1 19960531 G 3213 256UM57 PLUG BRAERO DH125 HS125700A 4230170 EU MLG STRUT CRACKED B EBVR K NONE O OTHER IN INSP/MAINT 1 GL 09 151AE 8728 NA0263 UPON SERVICING OF THE MAIN GEAR STRUTS, THE PLUGS THAT THE SHRADER VALVES SCREW INTO WERE FOUND CRACKED FROM THE THREADE D AREA OUTWARD. THE LT SIDE WAS FOUND VISUALLY, THE RT SIDE WAS FOUND WITH DYE PENETRANT. SUSPECT THE SHRADER VALVES M AY HAVE BEEN OVERTORQUED. 2 L 7 2 4F A3EU 1996071000036 19960710 00036 WP 1996 7 10 96ZZZX3394 2 19960604 G 7421 CH31815 IGNITER CHAMPION AMD FALC50 FALCON900 2700160 EU GARRTT TFE731 TFE7315BR WP ENGINE IGNITER FAILED D K NONE O OTHER IN INSP/MAINT 1 GL 09 523AC 852 139 DURING ROUTINE MAINTENANCE, THE IGNITER FIRING TIP OF THE CENTER ELECTRODE WAS FOUND LOOSE. THE IGNITER IS AN EXTENDED LIFE IRIDIUM IGNITER. THIS WAS A NON-SERIALIZED IGNITER, BUT THE 'TST' INDICATES PREVIOUS SPECIAL TESTING FOR LOOSE CEN TER ELECTRODE WAS COMPLIED WITH BY CHAMPION, THE MANUFACTURER. 2 L 7 3 4F 4 F RT A46EU E6WE 1996071000037 19960710 00037 EU 1996 7 10 96ZZZX3395 1 19960603 G 5620 FRAME AEROSP ATR42 ATR42300 8680920 EU CABIN WINDOW CORRODED B FI2R K NONE O OTHER IN INSP/MAINT 1 SW 17 19AE 015 TWENTY-SEVEN EACH CABIN WINDOW FRAMES CORRODED BEYOND LIMITS PER ATR42 SRM 53-51-00, FIGURE 301, PAGE 309, AT LOCATIONS WINDOW LT NRS 2, 3, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, AND 16; RT NRS 1, 2, 4, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, AND 17. THIS AIRCRAFT OPERATES IN A SALT WATER ENVIRONMENT AND IT APPEARS THE MOISTURE IS BEING TRAPPED BETWEEN THE WINDOW SEAL AND FRAME ALONG THE WINDOW LOWER RADIUS. 2 H 7 2 4T RT A53EU 1996071000038 19960710 00038 CE 1996 7 10 96ZZZX3396 1 19960618 G 3230 9000111 BEARING ELECTROMECH BEECH 100 A100 1152915 CE LG MOTOR FAILED G K NONE O OTHER IN INSP/MAINT 1 GL 05 100GV 200 69 B116 BEARING (AFT) FAILED. PART NUMBER AS ORDERED FROM BEECH WOULD BE 9000-11. BEARING SUPPLIED BY BEECH IS IDENTIFIED AS ( PEER CHINA 600ZD). SUBMITTER SUSPECTS QUALITY CONTROL MAY BE LACKING. 1 L 7 2 3T A14CE 1996071000039 19960710 00039 CE 1996 7 10 96ZZZX3397 1 19960608 G 3213 1228100791 AXLE A228100791 BEECH 2000 2000 1152000 CE RT MLG RUSTED B PAIR K NONE O OTHER IN INSP/MAINT 1 SO 05 8025L 1027 NC19 DURING AN ABC PHASE INSPECTION, THE RT OUTBOARD WHEEL AND BRAKE WERE REMOVED. CORROSION (RUST) WAS FOUND ON THE AXLE WH ERE THE BRAKE CALIPER RIDES. THE RUST WAS .300 INCH WIDE AND FORMED A BAND ALL THE WAY AROUND THE AXLE. THE DEPTH OF T HE PIT MEASURED .030 INCH. THE INBOARD SIDE OF AXLE SHOWED SIGNS OF CORROSION JUST BEGINNING. THE AXLE WAS REPLACED. 1 L 7 2 4T RT A38ACE 1996071000041 19960710 00041 CE 1996 7 10 96ZZZX3399 1 19960605 G 7620 99120142C VALVE CESSNA 500 500CESSNA 2076602 CE FIREWALL SOV FAILED D K NONE J WARNING INDICATION IN INSP/MAINT 1 SO 09 95Q 535 565 5000119 LEFT ENIGNE WOULD NOT START, LEFT LOW FUEL PRESSURE ANNUNCIATOR LIGHT DID NOT EXTINGUISH DURING START ATTEMPT. FOUND LE FT FIREWALL FUEL SHUT-OFF VALVE IN CLOSED POSITION. PILOT TESTED FIREWALL SHUT-OFF VALVES DURING PRE-FLIGHT. LEFT VALV E STAYED CLOSED AFTER SWITCH WAS RESET TO NORMAL. VALVE FAILED IN CLOSED POSITION. 1 L 7 2 4F A22CE 1996071000042 19960710 00042 NM 1996 7 10 96ZZZX3400 1 19960625 G 2121 13863352 BEARING SUNDSTRANDEM 5007024620 BOEING 727 727 1384001 NM CABIN FAN FAILED D A K NONE O OTHER IN INSP/MAINT 1 SO 19 69 AA31148 BEARING COMPLETELY DESTROYED. BEARING WAS INSTALLED NEW AND FAILED AFTER 69.02 HOURS OF OPERATION. CAUSED FAN TO OPERA TE LOUD AND SMELL LIKE IT IS BURNED. IMPELLER LOCKS UP. 2 L 7 3 4F A3WE 1996071000043 19960710 00043 NM 1996 7 10 96ZZZX3401 1 19960625 G 2121 13863352 BEARING SUNDSTRANDEM 5007024620 BOEING 737 737* NM CABIN FAN FAILED D K NONE O OTHER IN INSP/MAINT 1 SO 19 39 AA25289 BEARING VERY ROUGH CAUSING IMPELLER TO LOCK UP AND FAN PUTS OUT ELECTRICAL SMOKE. BEARING FAILED AFTER 39.01 HOURS OF O PERATION. 2 L 7 2 4F RT A16WE 1996071000044 19960710 00044 EA 1996 7 10 96ZZZX3402 2 19960315 G 7323 1412654 BEARING 8210002 PWA PT6 PT6* 52043 EA GOV FLYWEIGHT DEFECTIVE D K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 03 DURING ASSEMBLY OF AN 8210-002 GOVERNOR, THE FACTORY NEW 1412-654 BEARINGS JUST FELL APART. SUBMITTER RECOMMENDS NEW QC CONTROL. 3 T E2NE 1996071000045 19960710 00045 SW 1996 7 10 96ZZZX3403 1 19960513 G 6321 5009212 LINING 4000397 BELL 206 206L3 1182108 SW ROTOR BRAKE WORN HOLE B PN5R K NONE O OTHER IN INSP/MAINT 1 NM 03 617DE 51138 MOUNTING BAR CAME LOOSE FROM LINING ALLOWING IT TO FLOAT LOOSE BETWEEN PISTON AND BRAKE DISK. WHEN THE ROTOR BRAKE WAS APPLIED, THE LINING COULD BE FORCED DOWN AND WEDGE BETWEEN THE DISK AND THE CALIPER AND ACT LIKE THE BRAKE WAS ON. REPL ACED LININGS AND O-RINGS AND REASSEMBLED. OPS CHECKED OK. 1 G 7 1 3U H2SW 1996071000281 19960710 00281 SW 1996 7 10 96ZZZX3404 1 19960520 G 6320 206040151015 CASE ASSY BELL 206 206BELL 1181502 SW TRANSMISSION MFG DEFECT D A K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 01 B10881 PLUGS AT CASE-TO-MAST MATING SURFACE DRIVEN UP BY BOLTS DURING INSTALLATION OF MAST CHIP DETECTOR. DEBRIS IN PAN. SUBM ITTER STATED IT WAS DETERMINED TO BE MANUFACTURING DEFECT. 1 G 7 1 3U H2SW 1996071000283 19960710 00283 GL 1996 7 10 96ZZZX3406 1 19960618 G 6230 SHAFT AMTR RWEXEC ROTORWAYEXEC GL M/R FAILED G S O OTHER O OTHER NR NOT REPORTED 1 EA 21 7182Z 100 RW1522008 INVESTIGATION OF AN EXPERIMENTAL HELICOPTER ACCIDENT FOUND FOLLOWING PROBLEM: BEARING ASSY SHAFT INSERT BROKEN OFF INSI DE OF MAIN ROTOR SHAFT. STUB SHAFT FELL OUT THE MAIN ROTOR SHAFT. MAIN SHAFT AND SPROCKET AND CHAIN DUG INTO FUEL TANK . TOP OF MAIN BEARING WAS ALSO ROTATED TO REAR AND LEFT. COLLECTIVE SCISSORS BASE SUPPORT WAS BROKEN AND ROTATED UP, T HE 3-ROLLER DRIVE CHAIN JUMPED UP ONE SET OF ROLLERS ON THE SPROCKET. THIS MAIN ROTOR SHAFT ASSY WAS REPLACED ON 1-'95. THE REPLACEMENT ASSY INDICATIONS ARE THAT PARTS DO NOT MEET THE ORIGINAL SPECIFICATION. 1 G 7 1 3O EXPA1G71 1996071000285 19960710 00285 CE 1996 7 10 96ZZZX3408 1 19960502 G 2434 ES4118 BRUSH KIT FORD DOFF10300B CESSNA 172 172 2072402 CE ALTERNATOR FAILED B A ZM3R K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 07 163 508244T COMPONENT WAS RECENTLY OVERHAULED. INSPECTION REVEALED BRUSHES WERE INSTALLED UPSIDE DOWN CAUSING WEAR INTO BRUSH LEADS AND PREMATURE FAILURE. SUBMITTER STATED THIS IS THE FOURTH FAILURE IN THE LAST SIX MONTHS DUE TO IMPROPER BRUSH INSTAL LATION. ALL UNITS WERE OVERHAULED BY SAME OVERHAULER. ALL WITH LESS THAN 200 HOURS. 1 H 7 1 3O NT 3A12 1996071000286 19960710 00286 CE 1996 7 10 96ZZZX3409 1 19960612 G 2752 505212223 ACTUATOR BEECH 300 300BEECH 1152930 CE LT OTBD FLAP CRACKED D A K NONE O OTHER IN INSP/MAINT 1 CE 07 350TW 416 808J90 FM2 DURING INSPECTION FLAPS MOVED ERRATICALLY. UPON FURTHER INSPECTION OF LEFT OUTBOARD FLAP ACTUATOR, FOUND 5.50 INCH CRAC K RUNNING THE LENGTH OF THE PISTON ACTUATOR (REF: BEECH B300 IPC, CHAPTER 27-50-00, PAGE 2, ITEM NR 19). RECOMMEND CLO SER INSPECTION OF FLAP ACTUATOR PISTONS IN THE EXTENDED POSITION. 2 L 7 2 4T A24CE 1996071000287 19960710 00287 EU 1996 7 10 96ZZZX3410 1 19960614 G 3520 17408057 LANYARD AIRBUS 310 A310300 EU OXYGEN MASK FAIL TEST B S A GUMR K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 19 V8DPD 431 OXYGEN MASK LANYARDS FOR ACTIVATING PASSENGER OXYGEN SYSTEMS FAILED THE PULL TEST. INSPECTION OF ALL LANYARDS WITH THIS PART NUMBER BOX RESULTED IN IDENTIFYING 100 PERCENT DEFECTIVE, I.E., BAD CRIMPS AND CRIMPS SLIPPING. PURITAN BENNETT H AS BEEN NOTIFIED AND IS INVESTIGATING THE PROBLEM. 2 L 7 2 4F RT A35EU 1996071000288 19960710 00288 NE 1996 7 10 96ZZZX3411 2 19960503 G 7230 9136M89G19 ROTOR SPOOL GE CF6 CF650* 30018 NE HP COMP CRACKED G S K NONE O OTHER IN INSP/MAINT 1 EU 01 517842 DURING NDT INSPECTION, A CRACK WAS FOUND IN THE 3-9 HPC SPOOL. THE CRACK IS NOT IN THE AREA DESCRIBED IN THE AD ON SPOO LS. 4 F E23EA 1996071000289 19960710 00289 SW 1996 7 10 96ZZZX3412 1 19960501 G 3213 206030104023 FITTING BELL 206 206L4 1182110 SW FWD CROSSTUBE CRACKED B S ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 174AL 2528 52067 DURING SERVICE CHECK, NOTED FORWARD CROSSTUBE FITTING WAS CRACKED. FITTING WAS FOUND CRACKED IN THE SAME AREA AS REPORT ED ON MDR SUBMITTED ON 2-7-94. THE FITTING WAS MANUFACTURED IN OCTOBER, 1992, WHICH IS DIFFERENT FROM THE PREVIOUSLY RE PORTED CRACKED FITTINGS. 1 G 7 1 3U NC H2SW 1996071000292 19960710 00292 SW 1996 7 10 96ZZZX3415 1 19960506 G 6230 20601044304 DUPLEX BEARING 206010450117 BELL 206 206L3 1182108 SW SWASHPLATE FAILED D A K NONE O OTHER IN INSP/MAINT 1 SW 03 2616 1083 17620 51418 THIS IS THE SECOND DUPLEX BEARING FAILURE OF THIS TYPE IN LAST 6 MONTHS. BEARINGS FAILED WITH 1,000 HOURS OR LESS. PRE VIOUS BEARING, SN 17910, FAILED AT 915.1 HOURS. BEARINGS ARE NORMALLY CONDITIONAL ITEMS AND SELDOM NEED CHANGING AT 4,8 00-HOUR OVERHAUL PERIOD OF SWASHPLATE. 1 G 7 1 3U H2SW 1996071000294 19960710 00294 GL 1996 7 10 96ZZZX3417 2 19960424 G 7323 252466713 GOVERNOR BOLKMS 105 BO105CBS 5626008 EU ALLSN 250C 250C20B 03013 GL ENGINE DEFECTIVE B EOPR O OTHER R PARTIAL RPM/PWR LOSS AP APPROACH 1 AL 01 493HL 26236 S809 GOVERNOR REQUIRED TO BE RETRIMMED FREQUENTLY, THEN ENGINE FELL TO IDLE ON DESCENT FOR FINAL. GOVERNOR WAS CLOSE TO OVER HAUL, 56.0 HOURS LEFT. REPLACED GOVERNOR. 1 G 7 2 3U 3 U NC H3EU E4CE 1996071800007 19960718 00007 SO 1996 7 18 96ZZZX3419 2 19960508 G 8530 401852 STUDS MOONEY M20 M20K 5870220 SW CONT O360 TSIO360GB 17025 SO NR 1 CYL EXH RKR FAILED B A JC9R O OTHER E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CR CRUISE 1 SO 07 231PB 1729 552 250163 309837 ENGINE SUDDENLY STARTED RUNNING ROUGH, LOSS OF POWER (PARTIAL) WHILE IN CRUISE FLIGHT 210. FOUND NR 1 CYLINDER EXHAUST ROCKER SHAFT HOLD-DOWN STUDS BROKEN. INVESTIGATION REVEALED IMPROPER TORQUE ON ROCKER SHAFT HOLD-DOWN STUDS. 1 L 7 1 3O 3 O 2A3 E9CE 1996071800008 19960718 00008 EU 1996 7 18 96ZZZX3420 1 19960620 G 3520 C3512000 MASK BRAERO 1000 BAE1251000 1500287 EU PAX CABIN OXY TORN B S A YK1R K NONE O OTHER IN INSP/MAINT 1 SW 11 81AB 1142 259005 RUBBER FACE CUP TORN. FOUR EACH PASSENGER FACE MASKS. ALL TORN IN THE SAME LOCATION. FOUND DURING 12-MONTH INSPECTION . 2 L 7 2 4F RT A3EU 1996071800009 19960718 00009 GL 1996 7 18 96ZZZX3421 3 19960605 G 6111 BLADE CESSNA 150 152 2071835 CE MCAULY 1A103 1A103TCM GL NR 1 CRACKED B A HLWR K NONE O OTHER IN INSP/MAINT 1 SW 03 89922 2781 15282916 R774697 FOUND CRACK AT BOLT HOLE OF BLADE NR 1 LEADING EDGE BY LIQUID PENETRANT INSPECTION WHEN OVERHAULING PROPELLER. CRACK IS ABOUT .185 INCH LONG AND .060 INCH FROM EDGE OF BOLT HOLE. RETURNED TO SERVICE IAW AD 95-21-01 PER SB 219. RECOMMEND THAT LIQUID PENETRANT INSPECTION BE PERFORMED INSTEAD OF VISUAL INSPECTION PER SB 219. 1 H 7 1 3O NT 3A19 5 N P50GL 1996071800010 19960718 00010 EU 1996 7 18 96ZZZX3422 1 19960703 G 3520 C3512000 MASK BRAERO DH125 BAE125800A 1500285 EU PASSENGER CABIN TORN B S A UH6R K NONE O OTHER IN INSP/MAINT 1 SW 11 801CE 923 258253 RUBBER FACE CUP TORN. TWO EACH PASSENGER FACE MASKS. BOTH MASKS TORN IN SAME LOCATION. FOUND DURING 24-MONTH INSPECTI ON. MFG PURITAN BENNETT. 2 L 7 2 4F RT A3EU 1996071800012 19960718 00012 GL 1996 7 18 96ZZZX3424 3 19960604 G 6111 BEARING CESSNA 172 172RG 2072438 CE MCAULY 2D34C B2D34C220 GL BLADE BROKEN B HLWR K NONE O OTHER IN INSP/MAINT 1 SW 03 4929V 1470 172RG0148 941182 PROPELLER WAS NOT CYCLING PROPERLY. REMOVED TO BENCH TEST. BLADES WERE BINDING WHEN TESTED. DISASSEMBLED AND FOUND BL ADE BEARINGS DRY AND BROKEN, BALL BEARINGS PITTED, AND PITCH CHANGE LINKS AND ACTUATING PINS WORN BADLY. SUBMITTER STAT ED PROP MAY NOT HAVE BEEN LUBRICATED PROPERLY AT ASSEMBLY. THE PROPELLER SHOULD HAVE BEEN REMOVED AND REPAIRED WHEN PRO BLEMS WITH CYCLING FIRST STARTED. 1 H 7 1 3O 3A17 5 C P7EA 1996071800013 19960718 00013 CE 1996 7 18 96ZZZX3425 1 19960606 G 7920 S116720370 HOSE CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA OIL COOLER SOFT D A K NONE O OTHER IN INSP/MAINT 1 SW 03 69269 15282593 DURING ANNUAL INSPECTION, OIL COOLER HOSES WERE FOUND SOFT AND STICKY. HOSES WOULD NOT HAVE GONE ANOTHER YEAR. HOSES H AD BEEN REPLACED 5 YEARS AGO AND HAD ABOUT 250 HOURS ON THEM. INSTALLER REPLACED HOSES AND INSTALLED FIRE SHIELD ON THE M. INSTALLER RECOMMENDS THAT FIRE SHIELDS BE INSTALLED ON ALL HOSES BECAUSE OF PROXIMITY TO ENGINE AND HEAT. 1 H 7 1 3O 3 O NT 3A19 E223 1996071800014 19960718 00014 EA 1996 7 18 96ZZZX3426 2 19960601 G 8520 SL13792 SEAL CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA CRANKSHAFT LOOSE H K NONE O OTHER IN INSP/MAINT 1 SO 16 67658 15285305 1656615 OUTER CIRCUMFERENCE OF SEAL IS NOT A TIGHT FIT TO THE CRANKCASE. AFTER SEAL IS INSTALLED, SEAL IS ABLE TO ROTATE. NO S EALANT IS RECOMMENDED IN THE OVERHAUL OR SERVICE MANUALS, PN 13792 AND SL 13792 SEALS. 1 H 7 1 3O 3 O NT 3A19 E223 1996071800015 19960718 00015 EA 1996 7 18 96ZZZX3427 2 19960624 G 8520 LW13792 SEAL PIPER PA28 PA28161 7102803 SO LYC O320 O320D3G 41508 EA CRANKSHAFT LOOSE H K NONE O OTHER IN INSP/MAINT 1 SO 16 8318H 288116121 RL1077639A OUTER CIRCUMFERENCE OF SEAL IS NOT A TIGHT FIT TO THE CRANKCASE. AFTER SEAL IS INSTALLED, SEAL IS ABLE TO ROTATE. NO S EALANT IS RECOMMENDED IN THE OVERHAUL OR SERVICE MANUALS, P/N LW13792 AND SL 13792 SEALS. 1 L 7 1 3O 3 O 2A13 E274 1996071800016 19960718 00016 1996 7 18 96ZZZX3428 1 19960613 G 2822 1C610 PUMP AIRBORNE FUEL SYSTEM LEAD FAILED D K NONE O OTHER IN INSP/MAINT 1 GL 13 6AE259 FOUND LEAD WIRE TWISTED OFF. CAUSED BY INSTALLATION ERROR BY BOTTOMING OUT LEAD WIRE SCREW OR USING A FAULTY SCREW. TH IS CAUSED POWER LEAD TO TWIST OFF. 1996071800017 19960718 00017 1996 7 18 96ZZZX3429 1 19960527 G 2752 505212223 ACTUATOR BEECH FLAP MISLABELED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 13 3115943 ACTUATOR WAS OVERHAULED AS A 50-521222-3, BUT WAS LABELED AS A 101-521016-2. 1996071800018 19960718 00018 1996 7 18 96ZZZX3430 1 19960523 G 2822 1C1232 PUMP AIRBORNE FUEL SYSTEM IMPELLER BROKEN D K NONE O OTHER IN INSP/MAINT 1 GL 13 12AD169 MOLDED PLASTIC IMPELLER BROKEN AT ARMATURE 'D' CUT KEYWAY. SUBMITTER SUGGESTS STRONGER MATERIAL. 1996071800019 19960718 00019 1996 7 18 96ZZZX3431 1 19960523 G 2822 1C1232 PUMP AIRBORNE FUEL SYSTEM IMPELLER BROKEN D K NONE O OTHER IN INSP/MAINT 1 GL 13 11AD101 MOLDED PLASTIC IMPELLER BROKEN AT ARMATURE 'D' CUT KEYWAY. SUBMITTER SUGGESTS STRONGER MATERIAL. 1996071800020 19960718 00020 1996 7 18 96ZZZX3432 1 19960523 G 2822 1C1232 PUMP AIRBORNE FUEL SYSTEM IMPELLER BROKEN D K NONE O OTHER IN INSP/MAINT 1 GL 13 1AF3 MOLDED PLASTIC IMPELLER BROKEN AT ARMATURE 'D' CUT KEYWAY. SUBMITTER SUGGESTS STRONGER MATERIAL. 1996071800021 19960718 00021 CE 1996 7 18 96ZZZX3433 1 19960606 G 2710 CONTROL CABLE CESSNA 150 150G 2071816 CE AILERON CHAFED D A K NONE O OTHER IN INSP/MAINT 1 SO 21 64919 DURING A 100-HOUR INSPECTION, THE FOLLOWING DEFECTS WERE FOUND: THE AILERON CONTROL CABLE WAS SCRAPING THE PRIMER LINE( S) LOCATED IN THE FIREWALL AND A CRACK IN THE CONTROL CABLE SUPPORT BETWEEN THE INSTRUMENT PANEL AND THE FIREWALL ON THE PILOT'S SIDE. 1 H 7 1 3O 3A19 1996071800022 19960718 00022 CE 1996 7 18 96ZZZX3434 1 19960306 G 5320 SUPPORT CESSNA 150 150E 2071812 CE RUDDER CRACKED D A K NONE O OTHER IN INSP/MAINT 1 SO 21 61385 DURING A 100-HOUR INSPECTION A CRACK WAS FOUND IN THE SUPPORT UNDER THE RUDDER. 1 H 7 1 3O 3A19 1996071800023 19960718 00023 CE 1996 7 18 96ZZZX3435 1 19960601 G 2750 98600582 CONTROL CABLE CESSNA 207 207 2073602 CE FLAP FOLLOW-UP BINDS B A AX0R K NONE W INADEQUATE Q C IN INSP/MAINT 1 AL 03 1658U 20700258 CABLE WAS OF A DIFFERENT DESIGN THAN THE ORIGINAL CABLE REMOVED. NEW CABLE WOULD BIND IN THE HOUSING WHEN INSTALLED IN AIRCRAFT. A SECOND CABLE WAS PURCHASED AOG AND FOUND TO HAVE THE SAME PROBLEMS. 1 H 7 1 3O A16CE 1996071800024 19960718 00024 GL 1996 7 18 96ZZZX3436 3 19960323 G 6111 BLADE TCRAFK D DC65TCRAFT 8850402 EA UNIVAC 72 72A GL PROPELLER TIP DEPARTED G A O OTHER E VIBRATION/BUFFET NR NOT REPORTED 1 WP 27 36354 4091 A24608E PROPELLER'S METAL TIPPING BECAME LOOSE AND SEPARATED FROM PROPELLER IN-FLIGHT. THE SEPARATION WAS DUE TO WOOD DETERIORA TION. SUBMITTER RECOMMENDATION: INSPECT PROPELLER FOR DETERIORATION OF WOOD AND METAL TIPPING OR METAL TIPPING RIVETS FOR LOOSENESS. INDICATION: DARK STREAKS ALONG PROPELLER DARK LINES ALONG EDGE OF METAL TIPPING. 1 H 7 1 3O A746 5 N 802 1996071800025 19960718 00025 EA 1996 7 18 96ZZZX3437 2 19960613 G 8540 74996 GEAR CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA MAG DRIVE BROKEN B S CMXR K NONE O OTHER IN INSP/MAINT 1 CE 05 5109B 7761 15283750 L1377515 FOUND BROKEN IDLER GEAR IN THE ENGINE THAT DRIVES THE MAGNETO. 1 H 7 1 3O 3 O NT 3A19 E223 1996071800026 19960718 00026 SW 1996 7 18 96ZZZX3438 1 19960624 G 3230 5286501 DOWNLOCK MOONEY M20 M20C 5870208 SW MLG DISENGAGED D A K NONE O OTHER IN INSP/MAINT 1 SW 05 78981 5703 2015 DURING GROUND HANDLING AS PLANE WAS BEING PUSHED INTO HANGAR WHEN MAIN GEAR HIT THE HUMP AT HANGAR ENTRANCE, LANDING GEA R DISENGAGED AND AIRCRAFT SLOWLY SETTLED TO GROUND. SUSPECT DOWNLOCK NOT PROPERLY ENGAGED. 1 L 7 1 3O 2A3 1996071800027 19960718 00027 CE 1996 7 18 96ZZZX3439 1 19960606 G 8010 S1577A111 CONTACTOR CESSNA 182 TR182 2072735 CE STARTER FAILED D K NONE O OTHER IN INSP/MAINT 1 NM 11 2294R 1527 R18200584 AFTER A SCHEDULED OIL CHANGE, THE MASTER SWITCH WAS PLACED IN THE 'ON' POSITION FOR STARTING. AS SOON AS THE MASTER WAS TURNED ON, THE STARTER ROTATED THE PROPELLER. ROTATION OF THE PROPELLER COULD ONLY BE STOPPED BY TURNING THE MASTER SW ITCH TO THE 'OFF' POSITION. THE STARTER CONTACTOR ACTIVATION WIRE WAS DISCONNECTED TO CHECK FOR FAULTY SWITCH. THE PRO PELLER ROTATION CONTINUED. IT WAS FOUND THAT THE STARTER CONTACTOR HAD FAILED TO RETURN TO AN 'OPEN' POSITION. 1 H 7 1 3O 3A13 1996071800028 19960718 00028 CE 1996 7 18 96ZZZX3440 1 19960530 G 5720 0823400109 BULKHEAD CESSNA 340 340CESSNA 2076404 CE TIP TANK AFT MT CRACKED B CTUR K NONE O OTHER IN INSP/MAINT 1 GL 21 123KK 5497 3400251 FOUND TIP TANK MOUNTING BULKHEAD CRACKED. REPLACED BULKHEAD. SUBMITTER STATES CRACKING MAY HAVE BEEN CAUSED BY AN UPWA RD FORCE APPLIED TO AFT END OF TIP TANK. 1 L 7 2 3O 3A25 1996071800029 19960718 00029 SO 1996 7 18 96ZZZX3441 2 19960624 G 8530 648005CP RING CESSNA 206 U206F 2073333 CE CONT O520 IO520F 17032 SO PISTON BROKEN E O OTHER R PARTIAL RPM/PWR LOSS CR CRUISE 1 EA 25 33247 U20602692 553910 TEMPORARY POWER LOSS DURING CRUISE. SUSPECT CAUSE: BROKEN PISTON RING WHICH BECAME WEDGED BETWEEN PISTON AND CYLINDER WALL. REPLACED COMPLETE CYLINDER ASSY. 1 H 7 1 3O 3 O A4CE E5CE 1996071800030 19960718 00030 SO 1996 7 18 96ZZZX3442 2 19960212 G 8520 CRANKCASE BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO NR 1-2 CYLINDERS FAILED E A O OTHER O OTHER AP APPROACH 1 GL 25 4520S 1086 TH660 287021R DIPSTICK DEPARTED AIRCRAFT ON FINAL. MAINTENANCE UNCOWLED ENGINE TO PERFORM COMPRESSION TEST. ENGINE CRANKCASE HAD ERU PTED BETWEEN NR 1 AND NR 2 CYLINDER. BOTH MAGNETOS TORN FROM MOUNTING PADS NR 1 AND NR 2 CYLINDER ROD CAPS AND ROD BOLT S SHEARED FROM RODS AND 1 COUNTERWEIGHT DETACHED FROM CRANKSHAFT. SUSPECT CAUSE: COUNTERWEIGHT PIN FAILURE. ENGINE MA NUFACTURER NOTIFED AND REP TO EXAMINE ENGINE TEAR DOWN INSPECTION REQUESTED BY OWNER, OPERATOR, AND MAINTENANCE. 1 L 7 2 3O 3 O 3A16 E5CE 1996071800031 19960718 00031 SO 1996 7 18 96ZZZX3443 2 19960620 G 7322 182022111 SUPPORT CESSNA 182 182R 2072731 CE CONT O520 IO520D 17032 SO THROTTLE BODY CRACKED D K NONE O OTHER IN INSP/MAINT 1 NM 11 5442N 85 18267718 THIS AIRCRAFT IS MODIFIED PER STC SA00152W1 AND THE ITEM IS PART OF THE MODIFICATION. THE ENGINE QUIT IN-FLIGHT, AND WA S RESTARTED WITH NO OTHER PROBLEMS. THE PART WAS FOUND CRACKED IN TWO AND WAS THOUGHT TO CAUSE THE MIXTURE CONTROL TO L EAN THE MIXTURE BY LETTING THE FUEL CONTROL UNIT SLIP DOWN. (THIS PROBLEM TOOK PLACE IN MARCH OF '95). 1 L 7 1 3O 3 O NT 3A13 E5CE 1996071800032 19960718 00032 SO 1996 7 18 96ZZZX3444 2 19960530 G 8520 643202 CRANKCASE CESSNA 340 340CESSNA 2076404 CE CONT O520 TSIO520J 17040 SO LT HALF CRACKED B S CTUR K NONE O OTHER IN INSP/MAINT 1 GL 21 123KK 809 3400251 509176 ENGINE CRANKCASE WAS FOUND CRACKED FROM THE CRANKCASE THROUGH-BOLT AT CYLINDER NR 2. THE CASE WAS REPLACED 4-9-95. THE ENGINE CURRENTLY HAS 1,257 HOURS TSO. 1 L 7 2 3O 3 O 3A25 E8CE 1996071800033 19960718 00033 CE 1996 7 18 96ZZZX3445 1 19960613 G 2720 04115261 RUDDER BAR CESSNA 150 152 2071835 CE LT RD PEDAL BROKEN B S AKVR K NONE O OTHER IN INSP/MAINT 1 CE 05 67568 8022 15281917 LEFT RUDDER PEDAL ATTACHMENT LINK ON RUDDER BAR IS BROKEN. 1 H 7 1 3O NT 3A19 1996071800034 19960718 00034 CE 1996 7 18 96ZZZX3446 1 19960604 G 3230 128050981 LINE CESSNA 210 T210M 2073451 CE MLG HYD BROKEN D O OTHER K J FLUID LOSS WARNING INDICATION AP APPROACH 1 CE 05 7398M 21062018 ON APPROACH TO LAND, PILOT HAD A LANDING GEAR UNSAFE LIGHT INDICATION. PILOT NOTED THERE WAS NO GREEN LIGHT ILLUMINATED TO INDICATE THE LANDING GEAR WAS IN SAFE DOWN AND LOCK CONDITION. ALSO, AN INTERMITTENT FLICKERING LIGHT FOR THE LANDI NG GEAR 'UP' POSITION. AN EMERGENCY LANDING WAS CONDUCTED WITH THE ACFT RECEIVING MINOR DAMAGE TO THE FUSELAGE. ON EXA MINATION, FOUND A BROKEN LANDING GEAR HYDRAULIC LINE HAD RESULTED IN THE LOSS OF FLUID AND LANDING GEAR FAILURE. THIS L INE WAS REPLACED AND SEVERAL LANDING GEAR RETRACTION TEST OPERATIONS WERE CONDUCTED. 1 H 7 1 3O 3A21 1996071800035 19960718 00035 SO 1996 7 18 96ZZZX3447 1 19960625 G 2913 2720 MOTOR GARKENYON 953801 PIPER PA46 PA46310P 7104605 SO POWER PACK FAILED B JAVR O OTHER J WARNING INDICATION AP APPROACH 1 NE 01 9184F 3679 87 468408068 PILOT ATTEMPTED TO RETRACT LANDING GEAR, BUT HYDRAULIC POWER PACK DID NOT RUN. NOSE GEAR BECAME UNLOCKED DUE TO RESIDUA L HYDRAULIC PRESSURE. FREE FALL WOULD NOT LOCK NOSE GEAR. SEVERAL MANEUVERS CAUSED NOSE GEAR TO LOCK DOWN. AIRCRAFT L ANDED UNEVENTFULLY. FOUND HYDRAULIC PUMP MOTOR FAILED TO OPERATE. BRUSH CIRCUIT OPEN IN MOTOR. MOTOR TO BE REPLACED. 1 L 7 1 3O A25SO 1996071800036 19960718 00036 SO 1996 7 18 96ZZZX3448 2 19960620 G 7322 182022111 SUPPORT CESSNA 182 182Q 2072732 CE CONT O520 IO520D 17032 SO THROTTLE BODY CRACKED D K NONE O OTHER IN INSP/MAINT 1 NM 11 182PG 58 18266379 293230R THIS AIRCRAFT IS MODIFIED PER STC SA00152W1 AND THE ITEM IS PART OF THE MODIFICATION. THIS SUPPORT WAS CRACKED TWO-THIR DS THE WAY THROUGH; AND, IF HAD BROKEN OFF, WOULD HAVE LET THE FUEL CONTROL UNIT SLIP DOWN AND CAUSE A VERY LEAN MIXTURE AND A POSSIBLE ENGINE CUT-OFF. THE SUPPORT COULD BE REMOVED COMPLETELY OR MADE OF STEEL. 1 H 7 1 3O 3 O NT 3A13 E5CE 1996071800037 19960718 00037 1996 7 18 96ZZZX3449 1 19960523 G 2822 1C1232 PUMP AIRBORNE FUEL SYSTEM IMPELLER BROKEN D K NONE O OTHER IN INSP/MAINT 1 GL 13 2822 10AC65 MOLDED PLASTIC IMPELLER BROKEN AT ARMATURE 'D' CUT KEYWAY. SUBMITTER SUGGESTS STRONGER MATERIAL. 1996071800038 19960718 00038 1996 7 18 96ZZZX3450 1 19960612 G 2752 1015210162 ACTUATOR FLAP WRONG PART D K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 13 348I89 ACTUATOR APPEARED AS A FRESH OVERHAUL, BUT THE PISTON USED WAS AN INCORRECT PART NUMBER FOR THIS ACTUATOR. PART NUMBER INSTALLED WAS 50-521151-6 AND THE PART NUMBER TO BE USED IS 50-521195-8. 1996071800039 19960718 00039 CE 1996 7 18 96ZZZX3451 1 19960516 G 5751 169110000329 DOUBLER BEECH 23 B23 1151240 CE WING AIL BUSH WORN HOLE H K NONE O OTHER IN INSP/MAINT 1 NE 03 6996Q M1103 BUSHINGS 169-110000-347 FELL OUT OF DOUBLER WHEN LOOSE AILERONS REMOVED. NEW PARTS FOR MANUFACTURER FOUND TO HAVE A VER Y LOOSE INTERFERENCE FIT BETWEEN BUSHING AND DOUBLER. THIS COULD RESULT IN SAME PROBLEM IN A SHORT TIME. 1 L 7 1 3O A1CE 1996071800040 19960718 00040 CE 1996 7 18 96ZZZX3452 1 19960611 G 3260 010A391173 DRAG STRUT MTSBSI MU2 MU2B25 5780409 CE NLG MISINSTALLED B A SH5R O OTHER W INADEQUATE Q C LD LANDING 1 NE 03 728FN 303 DURING LANDING, THE NLG COLLAPSED RESULTING IN SKIN DAMAGE. INVESTIGATION REVEALED THAT DURING NLG REASSEMBLY, 50 HOURS PRIOR TO THIS INCIDENT, THE NOTED COMPONENTS WERE INSTALLED ON THE WRONG SIDES. THE DASH NUMBERS WERE NOT READABLE ON THE PARTS. THE MAINTENANCE MANUAL DOES NOT MAKE MENTION OF CORRECT POSITIONS FOR THESE COMPONENTS. SB 200A DOES IDENTI FY THE PARTS RELATIVE TO INSTALLATION POSITION, HOWEVER, DURING ROUTINE MAINTENANCE, THE SB WOULD NOT BE USED. 1 H 7 2 3T A2PC 1996071800041 19960718 00041 CE 1996 7 18 96ZZZX3453 1 19960410 G 3297 WIRE CESSNA 500 500CESSNA 2076602 CE MLG INTRANSIT BROKEN B OS5D K NONE O OTHER IN INSP/MAINT 1 GL 25 9AX 4127 5000016 DURING PHASES 1-4, FOUND GEAR INTRANSIT LIGHT INOPERATIVE. TROUBLESHOT SYSTEM, FOUND OPEN AT LIGHT AND FORWARD CONNECTO R PLUGS. TRACED POWER ROUTING AFT AND FOUND BROKEN WIRE AT AFT BULKHEAD CONNECTOR (P-48). REPAIRED BROKEN WIRE. FINAL OPERATIONAL CHECK FOUND SATISFACTORY. 1 L 7 2 4F A22CE 1996071800042 19960718 00042 CE 1996 7 18 96ZZZX3454 1 19960410 G 5320 551123924 ANGLE CESSNA 500 500CESSNA 2076602 CE STEP ATTACH CRACKED B S OS5D K NONE O OTHER IN INSP/MAINT 1 GL 25 9AX 4127 5000016 DURING A PHASE 1-4 INSPECTION, FOUND THE CABIN DOOR FRAME CRACKED AT LOWER STEP HINGE ATTACHMENT AT 2 PLACES. 1 L 7 2 4F A22CE 1996071800043 19960718 00043 SO 1996 7 18 96ZZZX3455 1 19960610 G 3241 4215919NC CIRCUIT BOARD LKHEED 1329 1329 5263102 SO ANTI SKID CONT FAILED B A AN3R K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 23 74AG 5072 THE CIRCUIT BOARD MAINTENANCE RELEASE TAG WAS IDENTIFIED WITH PN 42-15919NL, SN 351, ACTUAL UNIT WAS IDENTIFIED WITH PN 42-15919NL, SN 341. AFTER CIRCUIT BOARD WAS INSTALLED IN CONTROL BOX, IT WAS FOUND DURING SYSTEM CHECK-OUT THAT BOARD H AD A HARD FAILURE. 2 L 7 4 4J 2A15 1996071800044 19960718 00044 NM 1996 7 18 96ZZZX3456 1 19960628 G 2121 13863352 BEARING SUNDSTRANDEM 5007024620 BOEING 727 727 1384001 NM FAN MOTOR SHAFT ROUGH D K NONE O OTHER IN INSP/MAINT 1 SO 19 1279 AA81653 BEARING SHIELD PARTIALLY DISLODGED AND THERE WAS NO GREASE PRESENT. BEARING OPERATES ROUGH, CAUSED FAILURE OF FAN. 2 L 7 3 4F A3WE 1996071800045 19960718 00045 1996 7 18 96ZZZX3457 4 19960627 G 3418 170315 TRANSDUCER SAFEFLIGHT 170315 GULSTM 560 560 0141402 SW AOA OUT OF CALIB H A K NONE O OTHER IN INSP/MAINT 1 SO 15 611ST 1611 242 5600123 COMPARING AOA TRANSDUCER VANE WITH SISTER ACFT, FND VANE TRAVEL SUSPECT. CHECKED WITH ELEC PROTRACTOR, FND TRANSDUCER O UT OF CALIBRATION. INTERNAL STOPS HAD MOVED. ON PRE-FLIGHT, PILOT'S AOA ROTARY TEST WITH POWER ON ACFT SYS TESTS OK. S TICK SHAKER, IND, LIGHTS, BUT TEST DOES NOT INCLUDE TRANSDUCER. IF VANE IS OUT OF CALIBRATION, THERE ARE EXTERNAL LIMIT MARKS TO CHECK VISUALLY. ACFT FLEW OK WITH NO INDICATION OF PROBLEM AS CREW NEVER FLEW ACFT BELOW REF. SUBMITTER STAT ED THIS TRANSDUCER NEEDS AN EXTERNAL INDEX TO CHECK VANE FOR PROPER TRAVEL LIMIT. THIS SHOULD BE A GO-NO-GO ITEM. 1 H 7 2 3O 6A1 1996071800049 19960718 00049 SW 1996 7 18 96ZZZX3460 1 19960507 G 6230 206040078103 NUT 206040014103 BELL 206 206L3 1182108 SW MAST BEARING LOST TORQUE B A ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 343AL 4965 990 51372 WHEN REMOVING SWASHPLATE, MECHANIC FOUND NUT TO HAVE LOST TORQUE. (HAND TIGHT.) HAVE FOUND SEVERAL MAST NUTS ON 206L-3 'S AND 206L-4'S MAST ASSEMBLIES THAT HAVE LOST TORQUE. BELIEVE THE CONTACT AREA BETWEEN THE MAST NUT AND THE BEARING IN NER RACE IS TOO SMALL. THE 206B AND 206L-1 MAST NUTS HAVE A LARGER CONTACT AREA AND DO NOT CAUSE A PROBLEM. MODIFY MAS T NUT FOR GREATER CONTACT AREA. 1 G 7 1 3U H2SW 1996071800050 19960718 00050 EU 1996 7 18 96ZZZX3461 1 19960628 G 6310 4638202007 CLUTCH 4638001004 BOLKMS 105 BO105CBS 5626008 EU FREEWHEEL FAILED B A ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 5412J 1927 447 3200 S784 WHEN THROTTLES WERE CLOSED FOR SHUT DOWN, NR 2 ENGINE'S N2 NEEDLE ON TRIPLE TACH WAS OBSERVED TO REMAIN WITH THE ROTOR N EEDLE DURING COAST DOWN WHILE NR 1 ENGINE'S N2 NEEDLE SPLIT AND DECELERATED NORMALLY. FOUND NR 1 FWU CLUTCH LOCKED UP I N EITHER DIRECTION (NO FREEWHEELING CAPABILITY). REMOVED RIGHT FWU, FOUND CLUTCH BROKEN IN SEVERAL PIECES. 1 G 7 2 3U NC H3EU 1996012600424 19960126 00424 SO 1996 1 26 96ZZZX348 1 19960104 G 3240 4030103 BRAKE ASSY 403017502 GULSTM AA5 AA5 0631410 SO LT MLG DEFECTIVE D O OTHER O OTHER LD LANDING 1 EA 07 5893L AA50093 PILOT ATTEMPTED TO LAND. LEFT BRAKE WAS SOFT CAUSING AIRCRAFT TO SWERVE OFF RUNWAY AND HIT VASI BOARDS. DAMAGE TO RIGH T WING AND AILERON. 1 L 7 1 3O A16EA 1996071800106 19960718 00106 NE 1996 7 18 96ZZZX3484 1 19960610 G 6210 7615009100051A BLADE SPAR SKRSKY S76 S76A 8143006 NE M/R CRACKED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 376AL 4015 480 A08601314 760002 DISCOVERED DURING 500-HOUR INSPECTION, BLADE SPAR CRACKED AT ROOT END BUSHING HOLE. 1 G 7 2 3U H1NE 1996071800107 19960718 00107 SW 1996 7 18 96ZZZX3485 1 19960618 G 7120 214060211101 BEARING 214060209101 BELL 214 214ST 1182106 SW ENGINE AREA CHAFED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 391AL 28103 UNSCHEDULED MAINTENANCE, ENGINES REMOVED TO FACILITATE SHEET METAL REPAIRS TO LONGERON. FOUND BEARING BODY CHAFED BOTH SIDES BY CLEVIS. 2 G 7 2 4U H10SW 1996071800108 19960718 00108 GL 1996 7 18 96ZZZX3486 2 19960531 G 7323 2523240 BEARING 23007505 BOLKMS 105 BO105S 5626006 EU ALLSN 250C 250C20 03013 GL FLYWEIGHTS FROZEN B A ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 107AL 1447 S772 DURING TEAR DOWN INVESTIGATION OF UNIT, FOUND 2523240 BEARINGS FROZEN CAUSING FLYWEIGHTS TO STICK. 1 G 7 2 3U 3 U H3EU E4CE 1996071800109 19960718 00109 SW 1996 7 18 96ZZZX3487 1 19960517 G 5302 206032308103S FRAME BELL 206 206L3 1182108 SW TAILBOOM DEFECTIVE B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 366AL 51470 DURING REPLACEMENT OF PART DUE TO WEAR, FOUND EDGE DISTANCE AT HIGH SHEER INSTALLATION POINT TOO SHALLOW. 1 G 7 1 3U H2SW 1996072300001 19960723 00001 SW 1996 7 23 96ZZZX3512 1 19960614 G 7120 NAS627 BOLT LORD LM600SA9 SWRNGN SA227 SA227TT SW ENGINE MOUNT WRONG PART D K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 25 900AK TT424 DURING SCHEDULED INSPECTION, FOUND ENGINE SIDE MOUNT ISOLATOR THROUGH-BOLTS NOT PROPERLY ENGAGING LOCKING DEVICE IN TRUS S. VENDOR (LORD) SPECIFIES NAS627-H46 BOLT WITH .090 INCH BY 1.5 INCH WASHER, FAIRCHILD SPECIFIED NAS627-50 BOLT WITH A PPROXIMATELY .075 INCH BY .812 INCH WASHER. COMBINATION OF SHORTER BOLT WITH THICKER WASHER REDUCES EFFECTIVE LENGTH OF BOLT BY .265 INCH DUE TO VARIANCE IN WASHER THICKNESS. HAVE SEEN AS MUCH AS .300 INCH DIFFERENCE. THIS IS ON AIRCRAFT WITH HEAVY TRUSS 27-62078-231. IF BOLT HEAD HAS SAFETY WIRE HOLE, LOOK CLOSER, ITS THE WRONG BOLT. 2 L 7 2 4T RT A5SW 1996071800206 19960718 00206 CE 1996 7 18 96ZZZX3513 1 19960410 G 5551 5532000 STABILIZER CESSNA 500 500CESSNA 2076602 CE FWD ATTACH BOLTS LOOSE B OS5D K NONE O OTHER IN INSP/MAINT 1 GL 25 9AX 4127 5000016 WHILE REMOVING THE HORIZONTAL STABILIZER TO FACILITATE REPAIRS, NOTED THAT 6 OF THE 8 FORWARD ATTACH BOLTS WERE LOOSE. T WO OF THE SPACERS USED BETWEEN THE VERTICAL AND HORIZONTAL ATTACHMENT SHOWED SIGNS OF RUBBING. SUBMITTER RECOMMENDS THA T A ONE-TIME INSPECTION OF THE FORWARD AND AFT ATTACH BOLTS BE CHECKED FOR PROPER TORQUE. 1 L 7 2 4F A22CE 1996071800207 19960718 00207 CE 1996 7 18 96ZZZX3514 1 19960410 G 5510 553200019 STRINGER CESSNA 500 500CESSNA 2076602 CE HORIZ STAB BENT B OS5D K NONE O OTHER IN INSP/MAINT 1 GL 25 9AX 4127 5000016 WHILE PERFORMING A PHASE 1-4 INSPECTION, NOTICED TOP CENTER SKIN OF THE HORIZONTAL STABILIZER WAS BUCKLED BEYOND LIMITS AS STATED IN THE SRM. WHEN SKIN WAS REMOVED FOR REPLACEMENT, A HIDDEN DAMAGE INSPECTION REVEALED UPPER AFT STRINGER WAS ALSO BENT AND DISTORTED. REMOVED AND INSTALLED NEW CENTER SKIN (UPPER) AND UPPER AFT STRINGER. 1 L 7 2 4F A22CE 1996071800208 19960718 00208 CE 1996 7 18 96ZZZX3515 1 19960410 G 5512 553200063 SKIN CESSNA 500 500CESSNA 2076602 CE HORIZ STAB TOP BUCKLED B OS5D K NONE O OTHER IN INSP/MAINT 1 GL 25 9AX 4127 5000016 WHILE PERFORMING A PHASE 1-4 INSPECTION, NOTICED TOP CENTER SKIN OF THE HORIZONTAL STABILIZER WAS BUCKLED BEYOND LIMITS AS STATED IN THE SRM. WHEN SKIN WAS REMOVED FOR REPLACEMENT, A HIDDEN DAMAGE INSPECTION REVEALED UPPER AFT STRINGER WAS ALSO BENT AND DISTORTED. REMOVED AND INSTALLED NEW CENTER SKIN (UPPER) AND UPPER AFT STRINGER. 1 L 7 2 4F A22CE 1996071800209 19960718 00209 CE 1996 7 18 96ZZZX3516 1 19960626 G 7920 LINE BEECH 300 300BEECH 1152930 CE TORQUE MANIFOLD LOOSE G A UNSCHED LANDING Y K ENGINE STOPPAGE FLUID LOSS NR NOT REPORTED 1 GL 03 1250 FA88 OIL LINE CAME LOOSE AT TORQUE MANIFOLD LINE. ENGINE SHUT DOWN. AIRCRAFT LANDED WITHOUT INCIDENT. LEFT OIL LINE TIGHTE NED AT TORQUE MANIFOLD. NO FURTHER PROBLEMS NOTED. 2 L 7 2 4T A24CE 1996071800210 19960718 00210 NM 1996 7 18 96ZZZX3517 1 19960601 G 5320 WEB BOEING 727 7272J7 138400E NM FS 560-620 CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 129NA 20880 DURING C-CHECK INSPECTION, INTERGRANULAR CORROSION WAS NOTED ON FORWARD BAG PIT LOWER SILL CUT-OUT WEB. FROM STA 560 TO STA 620, LOCATED AT S26R. 2 L 7 3 4F A3WE 1996071800211 19960718 00211 NM 1996 7 18 96ZZZX3518 1 19960601 G 5320 FITTING BOEING 727 7272J7 138400E NM FS 570 S26R CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 129NA 20880 DURING C-CHECK INSPECTION, NOTED THE SECOND FROM FRONT TIE-DOWN MOUNT FITTING HAD INTERGRANULAR CORROSION AT STA 570 AND STA S26R. 2 L 7 3 4F A3WE 1996071800212 19960718 00212 NM 1996 7 18 96ZZZX3519 1 19960601 G 5320 FITTING BOEING 727 7272J7 138400E NM FS 560 S26R CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 129NA 20880 DURING C-CHECK INSPECTION, NOTED THE FORWARD TIE-DOWN MOUNT FITTING HAD INTERGRANULAR CORROSION AT STA 560, AT S26R. 2 L 7 3 4F A3WE 1996012600428 19960126 00428 1996 1 26 96ZZZX352 4 19960103 G 2562 7103 SWITCH LEIGH 7A1140 CESSNA 182 182P 2075816 CE G-SWITCH FAILED B YXUR K NONE L NO TEST IN INSP/MAINT 1 WP 07 58823 2921 21243 18262321 ELT G-SWITCH FAILED CRASH TEST IN ARM POSITION. CHECKED OK IN 'ON' POSITION. 1 H 7 1 3O NT TA13 1996071800213 19960718 00213 NM 1996 7 18 96ZZZX3520 1 19960601 G 5314 KEEL STRINGER BOEING 737 737212 1384461 NM FS 727A S27L CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 161FN 20521 DURING C-4 CHECK, CORROSION WAS NOTED ON KEEL STRINGER S27L. 2 L 7 2 4F A16WE 1996071800214 19960718 00214 NM 1996 7 18 96ZZZX3521 1 19960601 G 5320 SHEAR TIE BOEING 737 737212 1384461 NM FS 727A S27L CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 161FN 20521 DURING C-4 CHECK, CORROSION WAS NOTED ON SHEAR TIE STA 727A AT S27L. 2 L 7 2 4F A16WE 1996071800215 19960718 00215 CE 1996 7 18 96ZZZX3522 1 19960524 G 5720 552281063 STIFFENER CESSNA 500 550 2076604 CE WING FLAPWELL CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 03 26496 3286 5500607 THIS PART HAS BEEN FOUND CRACKED IN EACH OF FOUR 550'S. THE CRACKS ARE LOCATED ON THE FLANGES OF THE STIFFENER AND ARE VERY MINUTE. SUBMITTER STATED NOT SURE WHAT THE CAUSE OF THESE CRACKS ARE, THEY ARE ALL IN THE SAME LOCATION AND CAN BE SEEN BY LOOKING UP ABOVE THE FLAP INBOARD BELLCRANK. REF: SEE CESSNA PARTS ILLUSTRATED 57-20-05, FIGURE 01, ITEM 26. 1 L 7 2 4F A22CE 1996071800216 19960718 00216 NE 1996 7 18 96ZZZX3523 2 19960611 G 7230 COMPRESSOR RKWELL NA265 NA26540 6402608 CE PWA JT12 JT12A8 52042 NE ENGINE BINDING D K NONE O OTHER IN INSP/MAINT 1 SO 09 317NT 10605 322 282100 P637622NB COMPRESSOR VERY DIFFICULT TO ROTATE AND SPOOL DOWN VERY SHORT. INTERNAL BINDING COULD BE FELT WHEN ROTATING BY HAND. T HIS IS A MULTI-STAGE UNIT, SO VISUAL INSPECTION/DETECTION OF A PARTICULAR PARTS FAILURE IS VERY DIFFICULT. NO FOD NOTED AND NO DAMAGE OR DEFECTS NOTED IN TURBINE HOT SECTION. ALL IN-FLIGHT AND GROUND TEST PARAMETERS NORMAL. 2 L 7 2 4J 4 J A2WE 1E9 1996071800217 19960718 00217 NM 1996 7 18 96ZZZX3524 1 19960601 G 5312 CHORD BOEING 727 727243 138408D NM FS 950 S29R CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 34415 22167 DURING C-10 CHECK, CORROSION WAS NOTED ON THE 950 BULKHEAD LOWER CHORD AT S29R. 2 L 7 3 4F RT A3WE 1996071800218 19960718 00218 NM 1996 7 18 96ZZZX3525 1 19960528 G 5315 FLOOR BEAM BOEING 727 727243 138408D NM FS 1130 BL 24RT CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 34415 22167 EXFOLIATION CORROSION AT END OF SEAT TRACK FLOOR BEAM BL 24.75 RT WHERE IT ATTACHES TO STA 1130, FRAME RT. 2 L 7 3 4F RT A3WE 1996071800219 19960718 00219 SO 1996 7 18 96ZZZX3526 1 19960301 G 4990 37344420 GEAR ASSY GARRTT CTCP85291E LKHEED 188 188C 5262604 SO OIL PASSAGE FAILED B A A12R K NONE W INADEQUATE Q C IN INSP/MAINT 1 EA 21 P25816 THE MATING SURFACE OF THE APU FIRST STAGE COMPRESSOR INLET HOUSING AND PLANETARY GEAR ASSY HAVE A RECESSED OIL PASSAGE T O LOCATE A PACKING TO SEAL THE OIL PASSAGE. THE S9412-012 PACKING WAS INSTALLED WRONG OR SHRUNK AND WAS COVERING THE OI L PASSAGE. OIL STARVATION TO THE PLANETARY GEAR ASSY IS SUSPECTED FOR THE FAILURE. THIS COULD BE PREVENTED BY USING AL IGNMENT STUD TO HOLD ALIGNMENT WHILE INSTALLING. 2 L 7 4 4T 4A22 1996071800220 19960718 00220 EA 1996 7 18 96ZZZX3527 2 19960628 G 7414 M3006 BEARING SLICK 4270 CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA RT MAG ROUGH H O OTHER E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CR CRUISE 1 EA 01 92595 200 89020072 17261591 ENGINE SUDDENLY BECAME ROUGH. MAG CHECK INDICATED TROUBLE WITH RIGHT MAG, FLIGHT CONTINUED ON SINGLE MAG. OPERATION - AT TERMINATION OF FLIGHT, MAGS RE-CHECKED. RT MAG DEAD; OPENING UP MAG REVEALED 'BEARING' GREASE IN MAG HOUSINGS. COIL APPEARED INTACT, BUT DID NOT CHECK OUT. FRONT BEARING HAD 'ROUGH SPOTS'. TOTAL TIME SINCE NEW, 200 HOURS. 1 H 7 1 3O 3 O NT 3A12 E274 1996071800221 19960718 00221 EA 1996 7 18 96ZZZX3528 2 19960628 G 7414 M3525 COIL SLICK 4270 CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA RT MAG FAILED H O OTHER E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CR CRUISE 1 EA 01 92595 200 89020072 17261591 ENGINE SUDDENLY BECAME ROUGH. MAG CHECK INDICATED TROUBLE WITH RIGHT MAG, FLIGHT CONTINUED ON SINGLE MAG. OPERATION - AT TERMINATION OF FLIGHT, MAGS RE-CHECKED. RT MAG DEAD; OPENING UP MAG REVEALED 'BEARING' GREASE IN MAG HOUSINGS. COIL APPEARED INTACT, BUT DID NOT CHECK OUT. FRONT BEARING HAD 'ROUGH SPOTS'. TOTAL TIME SINCE NEW, 200 HOURS. 1 H 7 1 3O 3 O NT 3A12 E274 1996071800222 19960718 00222 EA 1996 7 18 96ZZZX3529 2 19960619 G 8520 CRANKCASE PIPER PA28 PA28R200 7102811 SO LYC O360 IO360C1C 41514 EA NR 2 CYLINDER CRACKED D S K NONE O OTHER IN INSP/MAINT 1 EA 21 75340 1000 28R7635292 RL1019351A DURING 100-HOUR INSPECTION, THE CRANKCASE WAS FOUND CRACKED (2 INCHES). THIS WAS THE SAME CRACK THAT WAS FOUND 2 YEARS AGO WHEN THE ENGINE HAD 1,500 HOURS TSMO. THE CASE HALVES WERE REPLACED AND NOW 1,000 HOURS LATER, THE SIMILAR CRACK HA S RE-APPEARED. SUSPECT VIBRATION PROBLEM. 1 L 7 1 3O 3 O 2A13 1E10 1996012600429 19960126 00429 CE 1996 1 26 96ZZZX353 1 19960102 G 2810 CAP CESSNA 182 182P 2075816 CE FUEL TANK DEFECTIVE D K NONE O OTHER IN INSP/MAINT 1 CE 07 91186 18261964 REPLACED DEFECTIVE STOCK GAS CAPS WITH MONARCH AIR AND DEV. CO., INC.'S CAPS. 1 H 7 1 3O NT TA13 1996071800223 19960718 00223 1996 7 18 96ZZZX3530 1 19960611 G 2432 2N5156 TRANSISTOR JET PS823 EMERG PWR SUPPLY DEFECTIVE B A JGVR K NONE W INADEQUATE Q C IN INSP/MAINT 1 CE 09 INVESTIGATION OF USERS COMPLAINT OF EMERGENCY POWER SUPPLY UNITS NOT HOLDING CAPACITY, REVEALED LOW RESISTANCE VALUES BE TWEEN COLLECTOR AND EMITTER OF THE ISOLATION/SWITCHING TRANSISTOR. THE DEFECT IS BELIEVED TO BE THE REASON FOR LOW CAPA CITY OF THE POWER SUPPLY UNITS. THE POWER SUPPLY IS USED FOR EMERGENCY POWER FOR FLIGHT GYROS, ETC. RECENTLY, 30 OF 54 NEW FROM STOCK TRANSISTORS WERE FOUND DEFECTIVE. 1996071800224 19960718 00224 GL 1996 7 18 96ZZZX3531 3 19960626 G 6114 HUB CESSNA 150 150L 2071826 CE MCAULY 1A100 1A100MCM GL PROPELLER CORRODED D S K NONE O OTHER IN INSP/MAINT 1 GL 13 PROPELLER WAS REMOVED IN ORDER TO STRIP AND PAINT. FOUND VERY HEAVILY CORRODED INSIDE OF THE CENTER HUB HOLE, 360 DEGRE ES ALL THE WAY AROUND. SOME PITS WERE .080 INCH - .090 INCH DEEP OR MORE. THERE WAS NO OTHER CORROSION FOUND ANYWHERE ELSE ON THE PROPELLER. 1 H 7 1 3O 3A19 5 N P918 1996071800225 19960718 00225 1996 7 18 96ZZZX3532 4 19960626 G 2562 7A1142 ELT NARCO SHARC7 CESSNA 150 150L 2071826 CE G-SWITCH MALFUNCTION D K NONE O OTHER IN INSP/MAINT 1 GL 13 23317 DURING ANNUAL INSPECTION, ELT WAS FUNCTION TESTED. SWITCHING UNIT TO ON, IT WOULD OPERATE FINE. HOWEVER, UNIT COULD NO T BE ACTIVATED BY THE BUMP TEST. SUBMITTER STATED THIS IS ABOUT THE 4TH UNIT IN THE LAST YEAR THAT COULD NOT PASS THIS TEST, ALL BEING THIS SAME MODEL. SENT UNIT TO MANUFACTURER FOR REPAIR. 1 H 7 1 3O 3A19 1996071800226 19960718 00226 GL 1996 7 18 96ZZZX3533 3 19960601 G 6114 D4883C55 HUB BEECH 95 95B55 1152729 CE MCAULY 2AF34C D2AF34C* GL PROPELLER CRACKED B MFNY K NONE K FLUID LOSS IN INSP/MAINT 1 EA 33 IEGEB 1272 175 791916 PROPELLER WAS SENT FOR INSPECTION BECAUSE RED OIL COMES OUT FROM THE HUB. THE REASON, THERE WAS A CRACK ON THE LOWER SI DE OF THE HUB IN THE AREA OF THE THREAD. 1 L 7 2 3O RT 3A16 5 C P5EA 1996071800227 19960718 00227 CE 1996 7 18 96ZZZX3534 1 19960601 G 3213 508100324 TORQUE KNEE BEECH 80 65A808800 CE UPPER LT MLG CRACKED D A K NONE O OTHER IN INSP/MAINT 1 GL 15 134BA LD202 WHILE INSPECTING THE LEFT MLG AREA DURING A ROUTINE INSPECTION, NOTED UPPER TORQUE KNEE WAS CRACKED IN TWO PLACES. SUBM ITTER STATED IF GONE UNNOTICED, IT COULD HAVE RESULTED IN THE LOSS OF THE LOWER STRUT ASSY AND SERIOUS DAMAGE TO AIRCRAF T. TOTAL TIME ON PART APPROXIMATELY 7,509 HOURS. A POSSIBLE RECOMMENDATION WOULD BE FOR A CLOSER EXAMINATION OF THE ML G AREAS DURING PRE-FLIGHT INSPECTION. 1 L 7 2 3O 3A20 1996071800228 19960718 00228 SW 1996 7 18 96ZZZX3535 1 19960702 G 8120 60051004 HOUSING ROTOMASTER 3AT6EE10J2 MOONEY M20 M20K 5870220 SW CONT O360 TSIO360GB 17025 SO TURBO CRACKED B A WTXR K NONE O OTHER IN INSP/MAINT 1 NM 07 123VW 222449 250447 309450 SUBMITTER RECOMMENDS THAT ROTO-MASTER TURBINE HOUSING P/N 600510-04 (TCM P/N 643931) BE ADDED TO ROTO-MASTER AD 82-27-03 . AD 82-27-03 STATES THIS INSPECTION MAY BE DISCONTINUED WITH THE INSTALLATION OF P/N 600510-04, BUT SUBMITTER HAS FOUN D THIS TURBINE HOUSING TO BE CRACKING IN THE SAME AREAS SHOWN IN FIGURE 2 OF AD 82-27-03. 1 L 7 1 3O 3 O 2A3 E9CE 1996071800229 19960718 00229 EA 1996 7 18 96ZZZX3536 2 19960702 G 8530 VALVE GULSTM AA5 AA5A 3960106 SO LYC O320 O320E2G 41508 EA NR 4 CYL INT BLOCKED OPEN D K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 26390 1961 AA5A0557 L4583127A ON INITIAL RUN-UP AFTER INSTALLING ENGINE AFTER MAJOR OVERHAUL, ENGINE WAS RUN AROUND 5 MINUTES AT 1,000-1,200 RPM'S. E NGINE RPM WAS INCREASED TO 1,700 FOR MAG CHECK. THE ENGINE STARTED TO RUN EXTREMELY ROUGH. ENGINE WAS SHUT DOWN. COMP RESSION CHECK SHOWED ZERO COMPRESSION ON NR 4 CYLINDER. FURTHER INSPECTION WAS CONDUCTED AND AN OBJECT WAS FOUND LODGED BETWEEN THE VALVE GUIDE BOSS AND THE VALVE WHICH HELD IT OPEN. IT APPEARED TO BE A ROUND SAND CAST ROD OF ALUMINUM. 1 L 7 1 3O 3 O A16EA E274 1996071800230 19960718 00230 1996 7 18 96ZZZX3537 4 19960613 G 6113 D5540 BULKHEAD BEECH 33 F33A 1151425 CE PROP SPINNER CRACKED B BXSR K NONE O OTHER IN INSP/MAINT 1 EA 09 3144M 1382 CE1206 SPINNER BULKHEAD IS CRACKED IN 6 PLACES, EACH AROUND THE PROPELLER ATTACH BOLT HOLES. 1 L 7 1 3O 3A15 1996071800231 19960718 00231 CE 1996 7 18 96ZZZX3538 1 19960522 G 3230 50450101 TORQUE TUBE CESSNA 401 401 207590C CE LT MLG CRACKED D O OTHER J WARNING INDICATION CL CLIMB 1 CE 05 401RW 3902 401118 LEFT MAIN FAILED TO RETRACT. TORQUE TUBE WAS FOUND TO HAVE A SPIRAL CRACK STARTING AT THE TOP BY THE BOLT, P/N 5243518- 3, AND TRAVELING AROUND THE TUBE AND TOWARD THE END OF THE TUBE. 1 L 7 2 3O A7CE 1996071800232 19960718 00232 CE 1996 7 18 96ZZZX3539 1 19960626 G 2810 CAP CESSNA 182 182P 2075816 CE WING TANK WATER LEAK D A K NONE O OTHER IN INSP/MAINT 1 CE 07 52876 1250 18262918 THIS AIRCRAFT HAS HAD A LONG HISTORY OF WATER IN THE FUEL. AD 84-10-01 ADDRESSES HOW TO DETERMINE HOW MUCH WATER AN AIR CRAFT WILL OR IS HOLDING, BUT DOES NOT SOLVE THE PROBLEM. NEW 'ZERO' RING (SEVERAL SETS) DID NOT HELP. WATER STILL SEE PED IN AROUND THE CAP. NEW CAPS AND PANELS FROM MONARCH AIR DEVELOPMENT WERE INSTALLED PER THEIR STC AND NO MORE WATER IN THE TANKS. 1 H 7 1 3O NT TA13 1996071800233 19960718 00233 CE 1996 7 18 96ZZZX3540 1 19960621 G 6121 SP105B CONTROL BOX CESSNA 340 340A 2076405 CE PROP SYNC SHORTED D H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 SO 03 6221C 3420 340A0426 DURING CRUISE FLIGHT, SMOKE FILLED THE CABIN. ELECTRICAL POWER WAS TURNED OFF. SMOKE CLEARED FROM CABIN. INVESTIGATIO N REVEALED THE PROPELLER SYNCROPHASER CONTROL BOX HAD SHORTED AND EMITTED SMOKE. THE NUTS THAT HOLD THE CANNON PLUG PIN S HAD VIBRATED OFF AND SHORTED THE CIRCUIT BOARD. 1 L 7 2 3O 3A25 1996071800234 19960718 00234 SO 1996 7 18 96ZZZX3541 1 19960610 G 7160 BA4101 GASKET BRACKETT BA4106 PIPER PA22 PA22150 7102210 SO AIR FILTER DEFECTIVE D K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 25 9721D 14 226638 GASKET SOFT AND CAME APART WHEN TOUCHED. AIRCRAFT USES AUTOGAS AND WHEN MANUFACTURER CALLED, THEY SAID THEY NEVER CHECK THE GASKETS WITH AUTO FUEL AND DID NOT KNOW ANYTHING ABOUT WHAT IT WOULD DO. THIS WAS FOUND WHILE C/W WITH AD 96-09-06 . SUBMITTER SUGGESTS ANY FILTER USED WITH AUTO FUEL BE CHECKED AS SOON AS POSSIBLE. 1 H 7 1 3O 1A6 1996071800235 19960718 00235 SO 1996 7 18 96ZZZX3542 1 19960619 G 5513 6358500 TRIM TAB PIPER PA28 PA28R200 7102811 SO LT STABILIZER CRACKED D S K NONE O OTHER IN INSP/MAINT 1 EA 21 75340 28R7635292 DURING 100-HOUR INSPECTION, THE TRIM TAB WAS DISCONNECTED TO ACCOMMODATE REPLACEMENT OF TRIM BARREL HARDWARE, THE TRIM T AB WAS FOUND CRACKED; UNDER THE ATTACH BRACKET, AT THE EDGE OF THE ATTACH BRACKET, INTO THE SUPPORTING RIBS, AND ON BOTH LEFT AND RIGHT TRIM TABS. 1 L 7 1 3O 2A13 1996071800236 19960718 00236 SO 1996 7 18 96ZZZX3543 1 19960619 G 5513 6358501 TRIM TAB PIPER PA28 PA28R200 7102811 SO RT STABILIZER CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 21 75340 28R7635292 DURING 100-HOUR INSPECTION, THE TRIM TAB WAS DISCONNECTED TO ACCOMMODATE REPLACEMENT OF TRIM BARREL HARDWARE, THE TRIM T AB WAS FOUND CRACKED; UNDER THE ATTACH BRACKET, AT THE EDGE OF THE ATTACH BRACKET, INTO THE SUPPORTING RIBS, AND ON BOTH LEFT AND RIGHT TRIM TABS. 1 L 7 1 3O 2A13 1996071800237 19960718 00237 CE 1996 7 18 96ZZZX3544 1 19960617 G 2434 PULLEY FORD DOFF10300 CESSNA 206 U206 2073306 CE ALTERNATOR SEPARATED D K NONE O OTHER IN INSP/MAINT 1 AL 01 8013Z A85562 U2060413 DRIVE PULLEY FOUND SEPARATED FROM VENT FAN DURING UNSCHEDULED MAINTENANCE. ALTERNATOR, 386.7 HOURS SINCE OVERHAUL. PUL LEY TIME UNKNOWN. CORROSION EVIDENT ON MATING SURFACES OF DETACHED PIECES. 1 H 7 1 3O A4CE 1996071800238 19960718 00238 SW 1996 7 18 96ZZZX3545 1 19960610 G 5210 206033636009 HINGE HALF BELL 206 206L1 1182107 SW PASSENGER DOOR LOOSE B QEVR K NONE O OTHER IN INSP/MAINT 1 CE 03 5753T 5837 45547 UPON DAILY INSPECTION OF AIRCRAFT, RIGHT PASSENGER DOOR LOWER HINGE FOUND LOOSE. AFT 2 CHERRY LOCK RIVETS PULLED THROUG H DOOR STRUCTURE WITH INDICATION OF PAINT MISSING AROUND AREA. SUSPECT CAUSE OF PROBLEM - DOORS NOT SECURED PROPERLY UN DER WINDY CONDITIONS ALLOWING DOOR TO OVERTRAVEL HINGE CAUSING EXCESSIVE PULL ON REAR RIVETS PULLING THROUGH DOOR STRUCT URE. SUBMITTER RECOMMENDED REPLACING RIVETS WITH 2 AN525-1032-R10 STRUCTURAL SCREWS WITH AN960-1032 WASHERS AND NAS 129 1-3 NUTS FOR GREATER STRENGTH AND MORE SURFACE CONTACT WITH DOOR AND SECURE DOOR PROPERLY IN WINDY CONDITIONS. 1 G 7 1 3U H2SW 1996071800239 19960718 00239 NE 1996 7 18 96ZZZX3546 1 19960614 G 5280 7620902019045 FITTING SKRSKY S76 S76B 8143007 NE LT MLG DOOR FAILED G A O OTHER O OTHER AP APPROACH 1 NE 03 9UT 2041 760379 LEFT MAIN GEAR DOOR LINK ATTACH FITTING FAILED DURING GEAR EXTENSION ON LANDING. COMPONENT HAS A HISTORY OF FAILURE AND MANUFACTURER HAS AN IMPROVED DASH 048 REPLACEMENT. THE PART HAS BEEN REDESIGNED TO BE STRUCTURALLY LARGER. THE ARICRA FT HAS BEEN FITTED WITH THE DASH 048 FITTINGS AND RETURNED TO SERVICE. SUBMITTER SUGGESTS OPERATORS OF THIS AIRCRAFT WI TH DASH 045 FITTINGS INSTALLED CONTACT MANUFACTURER FOR AVAILABILITY OF REPLACEMENT PARTS, AT THEIR CONVENIENCE. 1 G 7 2 4U H1NE 1996071800415 19960718 00415 EU 1996 7 18 96ZZZX3547 1 19960601 G 2720 STOP TRNSQP KR03A KR03A 1130847 EU RUDDER STOP BROKEN G A K NONE O OTHER IN INSP/MAINT 1 SO 13 210C 0315 EXAMINATION OF THE RUDDER SECTION DISCLOSED THE CASTELLATED NUTS ON THE RUDDER TOP COUNTERWEIGHT WAS STRIKING VERTICAL S KIN ON THE LEFT SIDE OF THE VERTICAL FIN CREATING SMALL PUNCTURE HOLES IN THE SKIN. THIS WAS CAUSED BY THE PHENOLIC STO PS BEING BROKEN DUE TO NOT USING GUSTLOCKS ON RUDDER DURING WINDY CONDITIONS. THIS ALLOWED THE RUDDER TO TRAVEL AN ADDI TIONAL .25 INCH CAUSING THE DAMAGE. SUBMITTER RECOMMENDATION: USE STRONGER TYPE MATERIAL FOR RUDDER STOP. 1 K 0 0 0 NC G56EU 1996071800417 19960718 00417 CE 1996 7 18 96ZZZX3549 1 19960410 G 3213 508100324 TORQUE KNEE BEECH 90 C90A 1152911 CE MLG CRACKED B L A NN3R K NONE O OTHER IN INSP/MAINT 1 WP 25 476JA LJ1161 INITIALLY IDENTIFIED A CRACK IN THE UPPER MAIN LANDING GEAR TORQUE KNEE OF ONE BEECHCRAFT C90A TRAINING AIRCRAFT WHILE L OOKING FOR CRACKS IN THE LOWER KNEE FOLLOWING A LOWER KNEE FAILURE. ALTHOUGH NO CRACKS OR IRREGULARITIES ON OTHER LOWER KNEES WERE FOUND, DETECTED SMALL CRACKS IN VIRTUALLY EVERY OTHER UPPER TORQUE KNEE, AT THE RADIUS OF THE CENTER ATTACH POINT IN FLEET OF 18 AIRCRAFT. ALTHOUGH ONLY ONE MALFUNCTION OR DEFECT REPORT INCLUDED, HAVE REPLACED A TOTAL OF 36 UPP ER TORQUE KNEES. 1 L 7 2 3T RT 3A20 1996071800418 19960718 00418 EU 1996 7 18 96ZZZX3550 1 19960327 G 5710 HOLE SEALS TRNSQP KR03A KR03A 1130847 EU SPOILER BOX DETACHED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 07 101TU 326 0405KP COTTON PATCHES GLUED TO THE FLANGED HOLES TO SEAL THE INSIDE OF THE WING AT THE SPOILER/SPEED BRAKE AREA WERE FALLING OU T. THE AIRCRAFT AT TIME OF ITS FIRST ANNUAL HAD LOST THREE-FOURTHS OF THE SEALS IN BOTH SPOILER BOXES. THESE COVERS PR EVENTED TURBULENT AIR FROM ENTERING THE INSIDE OF THE FABRIC COVERED SECTIONS OF THE WINGS DURING SPOILER DEPLOYMENTS. S UBMITTER STATED THE CONTINUED OPERATION WITHOUT THE COVERS MAY AT SOME POINT CAUSE THE FABRIC COVERING TO DISBOND FROM T HE RIBS. NOTE: THE MANUFACTURER DOES NOT USE RIB STITCHING ON THIS AEROBATIC CAPABLE AIRCRAFT. 1 K 0 0 0 NC G56EU 1996072200002 19960722 00002 SO 1996 7 22 96ZZZX3551 2 19960628 G 7421 SPARK PLUG CHAMPION CESSNA 185 A185F 2072821 CE CONT O520 IO520D 17032 SO ENGINE ELECTRODE LOOSE D K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 25 11174 18504435 282968R NEW SPARK PLUG HAS DEFECT, SIDE ELECTRODE LOOSE. 1 H 7 1 3O 3 O 3A24 E5CE 1996071800419 19960718 00419 1996 7 18 96ZZZX3552 4 19960307 G 2562 BP1020 BATTERY PACK DORNEMARGLN DMELT6 CESSNA 182 R182 2072734 CE ELT FAILED D K NONE O OTHER IN INSP/MAINT 1 GL 09 40AT 891 163 13482 R18200527 DURING ANNUAL, FOUND ELT INOPERATIVE ON BOTH MANUAL AND AUTOMATIC ACTIVATION TESTS PER 91.207. ELT REMOVED FOR REPAIRS AT THIS TIME. ELT WAS REPAIRED BY MANUFACTURER IN 1991, 163.2 HOURS AGO. TESTED BATTERY TO DETERMINE IF THERE WAS SUFF ICIENT VOLTAGE AND FOUND 1 BATTERY CELL WAS SHORTED. INSTALLED NEW BATTERY. OPS CHECK OK. 1 H 7 1 3O RT 3A13 1996071800420 19960718 00420 CE 1996 7 18 96ZZZX3553 1 19960308 G 5280 22130601 BRACKET CESSNA 182 R182 2072734 CE LT AFT NLG DOOR CRACKED D K NONE O OTHER IN INSP/MAINT 1 GL 09 40AT 891 R18200527 DURING ANNUAL INSPECTION, FOUND LEFT, CENTER, AFT BRACKET FOR NOSE LANDING GEAR DOOR HINGE CRACKED FROM LOWER RIVET HOLE EXTENDING INTO RADIUS OF 90 DEGREE BEND OF BRACKET. AT LAST ANNUAL, FOUND SAME BRACKET ON RIGHT CRACKED. SUSPECT CAUS E WAS VIBRATION/STRESS AT RIVET HOLE. 1 H 7 1 3O RT 3A13 1996071800421 19960718 00421 CE 1996 7 18 96ZZZX3554 1 19960611 G 5210 3540000812 HINGE BEECH 35 V35B 1151548 CE MAIN CABIN DOOR PIN FROZEN B SO5R K NONE O OTHER IN INSP/MAINT 1 NE 03 400LF 3900 D9825 MAIN CABIN LOWER DOOR HINGE WAS BINDING CAUSING DIFFICULT DOOR OPERATON. GAINED ACCESS TO HINGE ASSY. REMOVED HINGE, F OUND STEEL HINGE PIN PN MS20392-2C63 FROZEN IN PLACE BY SEVERE CORROSION (INTERGRANULAR). UPON REMOVAL, HINGE FRACTURED AT HINGE PIN RADIUS. INSPECTION OF AREA DIFFICULT WITHOUT REMOVAL OF DOOR. LUBRICATION ALSO DIFFICULT. SUBMITTER STA TED EVERY 1,000 HOURS REMOVE HINGE PIN AND DOOR, INSPECT AND APPLY ANTI-SEIZE LUBRICATION. 1 L 7 1 3O 3A15 1996071800422 19960718 00422 CE 1996 7 18 96ZZZX3555 1 19960319 G 7430 C12925010105 SWITCH GERDES A510 CESSNA 177 177RG 2073709 CE IGNITION WORN D K NONE O OTHER IN INSP/MAINT 1 GL 09 1989Q 3799 177RG0389 DURING PRE-BUY INSPECTION, FOUND IGNITION KEY COULD BE REMOVED FROM SWITCH IN ANY POSITION. DURING LOG BOOK REVIEW, FOU ND SWITCH HAD BEEN MODIFIED PER AD 93-05-06 BY INSTALLING ACS/GERDES KIT A-3600. THIS MODIFICATION WAS DONE AT LAST ANN UAL (8/95) 58 HOURS PREVIOUSLY. THIS CREATED A HAZARDOUS SITUATION AS KEY COULD BE REMOVED WITH MAGS STILL HOT. SUSPEC T CAUSE WAS HIGH TOTAL TIME. LACK OF PROPER MAINTENANCE/INSPECTION COULD HAVE CAUSED SERIOUS INJURY. 1 H 7 1 3O A20CE 1996071800423 19960718 00423 1996 7 18 96ZZZX3556 4 19960307 G 2562 CASE LEIGH SHARC7 CESSNA 177 177RG 2073709 CE ELT CRACKED D K NONE O OTHER IN INSP/MAINT 1 GL 09 1989Q 3800 17885 177RG0389 DURING PRE-BUY INSPECTION, FOUND ELT INOPERATIVE DURING IMPACT TEST REQUIRED BY 91.207. CORROSION FOUND ON CIRCUIT BOAR D. ELT SENT OUT FOR REPAIRS AND DETERMINED TO BE NON-REPAIRABLE DUE TO CRACKED CASE. 1 H 7 1 3O A20CE 1996071800424 19960718 00424 CE 1996 7 18 96ZZZX3557 1 19960316 G 3260 S20771 HORN CESSNA 177 177RG 2073709 CE GEAR WARNING INOPERATIVE D K NONE O OTHER IN INSP/MAINT 1 GL 09 1989Q 1960 177RG0389 DURING PRE-BUY INSPECTION, FOUND LANDING GEAR WARNING HORN INOPERATIVE. TROUBLESHOT SYSTEM AND FOUND GEAR HORN DEFECTIV E. OWNER CONFIRMED GEAR HORN HAD BEEN INOPERATIVE, BUT ANNUAL WAS SIGNED OFF 8/95 ANYWAY. SUSPECT CAUSE, VIBRATION CAU SED HORN TO COME APART INTERNALLY. 1 H 7 1 3O A20CE 1996071800425 19960718 00425 CE 1996 7 18 96ZZZX3558 1 19960628 G 2913 878H RELAY CESSNA 210 T210L 2073449 CE MLG POWER PACK STUCK D K NONE O OTHER IN INSP/MAINT 1 WP 17 29176 6033 21059828 GEAR POWER PACK RUNS ALL THE TIME WHEN RELAY IS IN STUCK POSITION. 1 H 7 1 3O 3A21 1996071800426 19960718 00426 CE 1996 7 18 96ZZZX3559 1 19960702 G 5210 LATCH PIN BEECH 99 99A 1154003 CE CREW DOOR BINDING B DQFR A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 NM 07 326CA U135 KING CARGO SYSTEMS COCKPIT CREW DOOR, STC SA1438GL. PILOT HAD DIFFICULTY LATCHING DOOR. TOOK OFF, DOOR CAME OPEN DURIN G CLIMB. AIRCRAFT LANDED WITHOUT INCIDENT. EXAMINATION FOUND LATCH PINS BINDING IN GUIDES; LUBRICATED AND INSTALLED LI GHT SPRINGS TO HOLD PINS IN ALIGNMENT. RECOMMEND STC HOLDER REDESIGN PIN GUIDES TO ALLOW FOR BETTER SUPPORT OF CATCH PI N. 1 L 7 2 3T A14CE 1996071800427 19960718 00427 CE 1996 7 18 96ZZZX3560 1 19960705 G 5312 17121541 BULKHEAD CESSNA 177 177B 2073708 CE FUSELAGE CRACKED B QH5R K NONE O OTHER IN INSP/MAINT 1 NM 07 34994 2752 17702144 BULKHEAD WAS INSPECTED AFTER GROUND ACCIDENT AND FOUND CRACKED AT LOWER INNER FLANGE. THIS PART WAS PENETRANT TESTED IA W MIL-STD-6866 NC/1, DATED OCTOBER 4, 1989. MECHANIC SAID CRACK WAS NOT CAUSED BY ACCIDENT. BULKHEAD WAS REPAIRED AND REINSTALLED. 1 H 7 1 3O A13CE 1996071800428 19960718 00428 NE 1996 7 18 96ZZZX3561 2 19960506 G 8530 CYLINDER SCWZER G164 G164A 3952704 EA PWA R1340 R1340* 52016 NE NR 1 CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 23 48395 261 1628 21888 INSPECTION FOUND NR 1 CYLINDER CRACKED HORIZONTALLY THROUGH SPARK PLUG BUSHING ON FORWARD FACE. 1 Q 7 1 3R 3 R 1A16 5E2 1996071800429 19960718 00429 EA 1996 7 18 96ZZZX3562 2 19960612 G 7323 70389 SHAFT PIPER PA23 PA23250 7102308 SO LYC O540 IO540C4B5 41532 EA RT ENGINE GOV SHEARED D E A ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 EA 23 5064C 1889 277405376 RL2477748A DURING FLIGHT, OVERSPEED CONDITION OCCURRED ON RT ENGINE. ENGINE WAS SHUT DOWN AND LANDED. MECHANIC FOUND GOVERNOR DRI VESHAFT SHEARED. 1 L 7 2 3O 3 O 1A10 1E4 1996071800430 19960718 00430 SO 1996 7 18 96ZZZX3563 2 19960627 G 7322 63255523 LEVER ARM CESSNA 210 P210N 2073454 CE CONT O520 TSIO520P 17040 SO AIR THROTTLE LOOSE B MZER K NONE O OTHER IN INSP/MAINT 1 GL 15 5469X 1864 491 P21000507 513515 WHILE C/W CESSNA SEB95-15R1, THROTTLE CONTROL LEVER INSPECTION. FOUND LEVER LOOSE AT SHAFT ATTACHMENT; ALSO, FOUND METE RING UNIT LEVER LOOSE ON ITS SHAFT. CESSNA SB ONLY DEALS WITH AIRFRAME CONTROL ATTACHMENT. SUSPECT CAUSE, INCORRECT OV ERHAUL PROCEDURES OR POOR WORKMANSHIP. 1 H 7 1 3O 3 O 3A21 E8CE 1996071800431 19960718 00431 CE 1996 7 18 96ZZZX3564 1 19960612 G 2410 LINK ARM CESSNA 150 152 2071835 CE START/ALT BOLT BROKEN D K NONE O OTHER IN INSP/MAINT 1 SO 16 69082 6000 15282477 STARTER TO ALTERNATOR LINK ARM BOLT FOUND BROKEN AND HELD IN PLACE BY SAFETY WIRE DURING ROUTINE INSPECTION. 1 H 7 1 3O NT 3A19 1996071800432 19960718 00432 EU 1996 7 18 96ZZZX3565 1 19960625 G 3222 5322012038 STRUT ASSY PILATS PC12 PC12 7090550 EU NLG BINDING B A FE6R K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 11 695WF 160 IL028 125 PILOTS REPORT ROUGHNESS IN RUDDER PEDALS WHICH GOT WORSE WITH TIME. INSPECTION REVEALED WHEN TURNING NOSE WHEEL WITH RU DDER PEDALS, SEVERE BINDING IN NOSE STRUT ASSEMBLY. CONTACTED PILATUS, THEY SENT A REPLACEMENT NOSE GEAR STRUT. PROBLE M SOLVED. PILATUS WILL DETERMINE WHAT WENT WRONG. SUSPECT PROBLEM FROM MANUFACTURER. 1 L 7 1 3T RT A78EU 1996071800433 19960718 00433 EA 1996 7 18 96ZZZX3566 2 19960313 G 7414 IMPULSE COUPLER SLICK 4371 CESSNA 172 172K 2072430 CE LYC O320 O320E2D 41508 EA MAGNETO EXCESS WEAR D K NONE O OTHER IN INSP/MAINT 1 GL 09 79301 115 95090178 17258030 L2497227A DURING ROUTINE MAINTENANCE (COMPRESSION CHECK) ENGINE 'LOCKED UP.' UPON INVESTIGATION/EXAMINATION, IMPULSE COUPLER PAWL AND PAWL AXIS FOUND EXTREMELY WORN ALLOWING IMPULSE COUPLING TO JAM INTERMITTENTLY WITH NO WARNING. 1 H 7 1 3O 3 O NT 3A12 E274 1996071800434 19960718 00434 CE 1996 7 18 96ZZZX3567 1 19960320 G 3232 521303810 BRACKET ASSY CESSNA 441 441 2076020 CE NLG RT DOOR BROKEN D O OTHER J WARNING INDICATION AP APPROACH 1 GL 09 83A 4170 4410050 NOSE GEAR WOULD NOT EXTEND, CYCLED SEVERAL TIMES. USED EMERGENCY BLOW-DOWN BOTTLE, NOSE GEAR STILL WOULD NOT EXTEND. A IRCRAFT LANDED WITH NOSE GEAR UP. RIGHT NOSE GEAR DOOR RETREAT BRACKET BROKEN. NOSE GEAR PULLED RT DOOR UP INTO NOSE G EAR WELL AND JAMMED GEAR IN WELL. 1 L 7 2 3T RT A28CE 1996071800435 19960718 00435 1996 7 18 96ZZZX3568 1 19960624 G 2822 1B56 PUMP AIRBORNE FUEL BOOST DEFECTIVE D K NONE O OTHER IN INSP/MAINT 1 GL 13 3AD18 FUEL PUMP ARMATURE OUT OF BALANCE RESULTING IN PUMP FAILURE. 1996071800436 19960718 00436 1996 7 18 96ZZZX3569 1 19960702 G 2822 9C52 PUMP AIRBORNE FUEL BOOST DAMAGED D K NONE O OTHER IN INSP/MAINT 1 GL 13 FUEL PUMP MAY HAVE RUN DRY CAUSING DAMAGE TO THE ARMATURE. 1996071800437 19960718 00437 1996 7 18 96ZZZX3570 1 19960702 G 2822 PUMP FUEL BOOST SHAFT WORN D K NONE O OTHER IN INSP/MAINT 1 GL 13 9E688 FUEL PUMP ARMATURE SHAFT HAS GROOVE WORN IN IT BY THE SPACERS. 1996071800438 19960718 00438 CE 1996 7 18 96ZZZX3571 1 19960709 G 2820 LINE CESSNA 182 182P 2075816 CE FWD RT DOOR POST CHAFED D K NONE O OTHER IN INSP/MAINT 1 EA 01 91389 18261995 DURING WINDSHIELD REPLACEMENT, FOUND AILERON CONTROL CABLE, WHICH TRAVELS UP THE FORWARD RIGHT DOOR POST, WAS CHAFING ON THE ADJACENT FUEL LINE. ORIGINAL WALL THICKNESS IS .030 INCH AND THE DEPTH OF THE CHAFE WAS .020 INCH. 1 H 7 1 3O NT TA13 1996071800439 19960718 00439 NM 1996 7 18 96ZZZX3572 1 19960701 G 5711 SPAR UNIVAR 415 415E 0420308 NM LT WING CORRODED D K NONE O OTHER IN INSP/MAINT 1 GL 13 94841 4914 INSPECTION REQUIRED IN AD 94-18-04. FOUND EVIDENCE OF CORROSION BETWEEN PARTS OF REAR SPAR IN LEFT WING. SAME CONDITIO N FOUND IN RIGHT WING AS WELL AS A PORTION OF EXFOLIATION FOUND IN BOTTOM SPAR CAP, AFT SIDE, ABOUT A FOOT FROM THE OUTB OARD END. 1 L 7 1 3O A787 1996071800440 19960718 00440 GL 1996 7 18 96ZZZX3573 3 19960501 G 6114 D6603 HUB CESSNA 210 210 2073402 CE MCAULY 3A32C D3A32C88 GL PROPELLER CORRODED B AQYR K NONE O OTHER IN INSP/MAINT 1 NE 03 750803 INSPECTION FOUND CORROSION ON EXTERIOR AND INTERIOR OF HUB. RECOMMEND ROUTINE MAINTENANCE. 1 H 7 1 3O RT 3A21 5 C P21EA 1996071800441 19960718 00441 GL 1996 7 18 96ZZZX3574 3 19960501 G 6114 D5897 HUB CESSNA 421 421B 2076014 CE MCAULY 3AF34C 3AF34C92 GL PROPELLER CORRODED B AQYR K NONE O OTHER IN INSP/MAINT 1 NE 03 421SM 42180889 748237 INSPECTION FOUND CORROSION THROUGHOUT HUB. RECOMMEND ROUTINE MAINTENANCE. 1 L 7 2 3O A7CE 5 C P22EA 1996071800442 19960718 00442 GL 1996 7 18 96ZZZX3575 3 19960617 G 6114 D5894 HUB CESSNA 421 421B 2076014 CE MCAULY 3AF34C 3AF34C92 GL PROPELLER CRACKED B AQYR K NONE O OTHER IN INSP/MAINT 1 NE 03 421BB 421B0967 739542 HUB EDDY CURRENT INSPECTION OF RETENTION THREADS REVEALED A CRACK. 1 L 7 2 3O A7CE 5 C P22EA 1996071800443 19960718 00443 GL 1996 7 18 96ZZZX3576 3 19960617 G 6114 D5894 HUB CESSNA 421 421B 2076014 CE MCAULY 3AF34C 3AF34C92 GL RETAIN THREADS CRACKED B AQYR K NONE O OTHER IN INSP/MAINT 1 NE 03 421BB 421B0967 751875 HUB EDDY CURRENT INSPECTION OF RETENTION THREADS REVEALED A CRACK. 1 L 7 2 3O A7CE 5 C P22EA 1996012600434 19960126 00434 NM 1996 1 26 96ZZZX358 1 19960109 G 2612 80380203 FIRE DET UNIT DOUG MD11 MD11 3023602 NM NR 1 ENGINE FAULTY G A O OTHER J WARNING INDICATION LD LANDING 1 GL 23 2FOR 48556 ENGINE NR 1 FIRE DURING LANDING ROLL OUT. ECL PROCEDURE COMPLETED(PAGE 34B). FIRE OUT AFTER A FEW SECONDS. MAINTENANC E VERIFIED ENGINE NR 1 DUCTING CONDITION AND FIRE LOOPS. ALL OK. PERFORMED RESISTANCE CHECK AT FDCU AT PINS J AND K PE R FIM. ALL READINGS WITHIN NORMAL. MAINTENANCE CREW REMOVED AND REPLACED FIRE DETECTION CONTROL UNIT. RAN ENGINE AND NO FURTHER INDICATIONS EXPERIENCED. PART REMOVED AND REPLACED WAS FIRE DETECTION CONTROL UNIT, MFG PN 8038-02-03, AND S N 796. MFG DATE, 7-93. TRIGGERED BOTH LOOPS 'A' AND 'B' AND TESTED OK DURING GROUND CHECK. 2 L 7 3 4F RT A22WE 1996071800669 19960718 00669 SW 1996 7 18 96ZZZX3602 1 19960503 G 7714 206070266009 INDICATOR BELL 206 206L1 1182107 SW COCKPIT N1 DEFECTIVE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 206MH 355D 45426 INTERNAL LIGHT INOPERATIVE. LOOSE CONNECTION WHERE WIRE ENTERS INDICATOR. MOUNTING WIRE BREAKS CONTINUITY. REMOVED AN D REPLACED. 1 G 7 1 3U H2SW 1996071800674 19960718 00674 EU 1996 7 18 96ZZZX3607 1 19960601 G 6730 741C000005 ACTUATOR BOLKMS 117 BK117A4 5626017 EU T/R LEAKING B TI1R K NONE K FLUID LOSS IN INSP/MAINT 1 SW 05 313LF 00446 7138 ACTUATOR LEAKING. 1 G 7 2 3U H13EU 1996071800675 19960718 00675 EU 1996 7 18 96ZZZX3608 1 19960503 G 6730 7012409901 ACTUATOR BOLKMS BK117 BK117C1 5626025 EU DUPLEX PITCH MALFUNCTION B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 317MC 91100172 7505 AP1 WILL NOT COME ON LINE. 1 G 7 2 3U NC H13EU 1996071800676 19960718 00676 EU 1996 7 18 96ZZZX3609 1 19960620 G 6730 7012409901 PITCH ACTUATOR BOLKMS BK117 BK117C1 5626025 EU DUPLEX PITCH MALFUNCTION B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 317MC 91050153 7505 ACTUATOR CAUSING AP1 AND AP2 TO GENERATE ERROR CODES, AP1 AND AP2 WILL NOT COME ON LINE. 1 G 7 2 3U NC H13EU 1996071800677 19960718 00677 1996 7 18 96ZZZX3610 4 19960503 G 2215 7012693901 SERVO MONITOR BOLKMS BK117 BK117C1 5626025 EU AUTOPILOT SHORTED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 317MC 90090152 7505 RZ-710 SHORTED, A/P WOULD NOT COME ON LINE. REMOVED AND REPLACED. 1 G 7 2 3U NC H13EU 1996071800678 19960718 00678 EU 1996 7 18 96ZZZX3611 1 19960612 G 3340 099799100 SEARCH LIGHT BOLKMS BK117 BK117C1 5626025 EU EXTERIOR LIGHT DEFECTIVE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 317MC 441 7505 SEARCH LIGHT WILL NOT TURN OFF. 1 G 7 2 3U NC H13EU 1996071800679 19960718 00679 EU 1996 7 18 96ZZZX3612 1 19960510 G 2840 1178978301 DETECTOR BOLKMS BK117 BK117C1 5626025 EU PUMP FAIL MALFUNCTION B TI1R K NONE N FALSE WARNING IN INSP/MAINT 1 SW 05 317MC 422 7505 FUEL PUMP FAIL LIGHT ACTIVATES WHEN RADIO IS TRANSMITTING. 1 G 7 2 3U NC H13EU 1996071800680 19960718 00680 EU 1996 7 18 96ZZZX3613 1 19960507 G 7714 645383051 INDICATOR AEROSP SA365 SA365N1 8680668 EU COCKPIT NG FAILED B TI1R K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 05 365SC 1128 6298 ORDERED EXCHANGE UNIT, BUT UNIT DOES NOT WORK PROPERLY (LIGHT WORKS, BUT DOES NOT ILLUMINATE GAUGE FACE). 1 G 7 2 3U H10EU 1996071800681 19960718 00681 1996 7 18 96ZZZX3614 4 19960522 G 3454 066401000 RECEIVER BOLKMS 117 BK117A3 5626015 EU R NAV DEFECTIVE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 4493X 4 3865 S7038 KNOB HARD TO TURN, FREQUENCY DOES NOT ADJUST PROPERLY, SOMETIMES UP, SOMETIMES DOWN. REMOVED AND REPLACED. 1 G 7 2 3U H13EU 1996071800682 19960718 00682 1996 7 18 96ZZZX3615 4 19960528 G 2211 11788292 COMPUTER BOLKMS 117 BK117A3 5626015 EU SPAS MALFUNCTION B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 4493X 14 S7038 COMPUTER CAUSING SPAS NOT TO TEST. UNIT ONLY HAS 13.90 HOURS, SINCE REPAIR. 1 G 7 2 3U H13EU 1996071800683 19960718 00683 1996 7 18 96ZZZX3617 4 19960529 G 3457 066040310111 GPS BOLKMS 105 BO105S 5626006 EU COCKPIT MALFUNCTION B TI1R K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 05 495LF 12083 S645 GPS HAD HARDWARE ERROR CODE 0010 ON INITIAL INSTALLATION AND START-UP. ALTHOUGH SATELLITE SIGNAL STRENGTHS WERE ALL IN THE 40'S, EVEN AFTER ALL SATELLITES WERE CAPTURED, UNIT DID NOT SHOW PRESENT POSITION AND MESSAGE CONTINUED TO SHOW ERRO R CODE, APPROXIMATELY 10 MINUTES. 1 G 7 2 3U H3EU 1996071800684 19960718 00684 1996 7 18 96ZZZX3618 4 19960528 G 3457 066040310111 GPS BOLKMS 105 BO105S 5626006 EU COCKPIT DEFECTIVE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 495LF 13398 S645 GPS VERY SLOW TO COME ON LINE AT 5 TO 6 MINUTES OR LONGER. PART WAS JUST SENT IN FOR REPAIR LAST MONTH. REMOVED AND RE PLACED. 1 G 7 2 3U H3EU 1996071800685 19960718 00685 1996 7 18 96ZZZX3619 4 19960522 G 3457 066040310111 GPS BOLKMS 105 BO105S 5626006 EU COCKPIT DISPLAY ERRATIC B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 911LF 13440 S663 COCKPIT GPS DISPLAY ERRATIC. 1 G 7 2 3U H3EU 1996071800686 19960718 00686 SW 1996 7 18 96ZZZX3620 1 19960617 G 6240 222375071105 INDICATOR BELL 222 222 1182122 SW TRIPLE TACH FLUCTUATES B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 911MK 083 47515 TRANSMISSION TORQUE NEEDLE FLUCTUATES 20 - 30 PERCENT, FALLS TO ZERO, AND THEN RETURNS AND BEGINS TO FLUCTUATE AGAIN. 1 G 7 2 3U H9SW 1996071800687 19960718 00687 EU 1996 7 18 96ZZZX3621 1 19960508 G 2435 200SGL115Q STARTER BOLKMS 105 BO105LSA3 5626020 EU DAMPER DEFECTIVE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 911SV 2282 1100 2033 FRICTION DAMPER LOOSE - STARTER BANGS ON START-UP. 1 G 7 2 3U H3AU 1996071800739 19960718 00739 EU 1996 7 18 96ZZZX3625 1 19960529 G 7830 INTERCOSTAL F10A5B20202 ISRAEL 1124 1124 4500102 EU LATCH SUPPORT CRACKED D S K NONE O OTHER IN INSP/MAINT 1 SW 07 269AJ 4400 276 INSPECTION FOUND RT T/R SECONDARY BRACKET LATCH INTERCOSTAL CRACKED. 2 M 7 2 4F A2SW 1996071800740 19960718 00740 SW 1996 7 18 96ZZZX3626 1 19960710 G 5751 2734023011 SPAR 2734000039 SWRNGN SA227 SA227AC 8780603 SW AILERON CRACKED D A K NONE O OTHER IN INSP/MAINT 1 SW 11 359AE AC674 DURING DISASSEMBLY OF AILERON FOR SKIN CHANGE, THE SPAR WAS FOUND CRACKED IN TWO PLACES AROUND OUTBOARD HINGE BRACKET. T HE CRACKS WERE THE FULL WIDTH OF THE SPAR WEB AND INTO THE RADIUS OF THE FLANGES. THIS IS THE SECOND SPAR FOUND CRACKED LIKE THIS RECENTLY. SUBMITTER SUGGESTED MANDATORY VISUAL INSPECTION OF THE AILERON SPAR IS STRONGLY RECOMMENDED. 2 L 7 2 4T RT A8SW 1996071800741 19960718 00741 CE 1996 7 18 96ZZZX3627 1 19960410 G 3213 6541000200 PISTON 554100017 CESSNA 500 500CESSNA 2076602 CE LT MLG BROKEN B S OS5D K NONE O OTHER IN INSP/MAINT 1 GL 25 9AX 4127 021 5000016 WHILE DISASSEMBLYING THE LEFT MAIN LANDING GEAR FOR AN AXLE CHANGE, FOUND ISOLATION PISTON STEM THAT THE DAMPENING SPRIN G SURROUNDS WAS BROKEN FLUSH AT THE PISTON HOUSING. SEE CITATION 500 COMPONENT MM, PAGE 32-10-00, FIGURE 1002, SHEET 2, ITEMS 110, 113, 114, 115. THIS STEM HAS BEEN CRACKED BROKEN FOR QUITE SOME TIME. POSSIBLE CAUSE, AIRCRAFT WAS LANDED WITH UNDERSERVICED STRUT OR WAS TAXI/TOWED WITH FLAT STRUTS. 1 L 7 2 4F A22CE 1996071800742 19960718 00742 EU 1996 7 18 96ZZZX3628 1 19960529 G 7830 INTERCOSTAL F10A5B20202 ISRAEL 1124 1124 4500102 EU LATCH SUPPORT CRACKED D S K NONE O OTHER IN INSP/MAINT 1 SW 07 98WW 3057 398 THRUST REVERSER SECONDARY BRACKET LATCH SUPPORT INTERCOSTAL FOUND CRACKED NUMEROUS PLACES. MATERIAL IS .032 INCH 2024T6 ALUMINUM. 2 M 7 2 4F A2SW 1996071800743 19960718 00743 SO 1996 7 18 96ZZZX3629 1 19960619 G 7732 INDICATOR GULSTM G1159 G1159 3953505 SO RT ENG TVI ERRATIC B GJQR E A ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 NM 01 26WP 9107 24 ON DEPARTURE, RIGHT ENGINE TVI INCREASED TO 2.2 THEN AT ABOUT 10,500 MSL, WENT TO 5. PLUS TVI READING. AFTER REDUCING P OWER, TVI VARIED FROM 2. TO 5 PLUS. THE CREW MADE A PRECAUTIONARY ENGINE SHUT DOWN AND RETURNED FOR INVESTIGATION TO TH E PROBLEM. CHECKED AND CLEANED RIGHT TVI AMPLIFIER, TRANSDUCER, OIL SYSTEM CHIP PLUGS, AND OIL FILTERS. GROUND OPERATI ONAL CHECK TVI OPERATED NORMALLY. SUSPECT HIGH RESISTANCE AT TVI TRANSDUCER OR AMPLIFIER CONNECTIONS WHICH CLEANING COR RECTED. 2 L 7 2 4F RT A12EA 1996071800744 19960718 00744 EU 1996 7 18 96ZZZX3630 1 19960313 G 5751 513501504 AILERON SKIN ISRAEL 1124 1124A 4500103 EU RT AILERON CRACKED B EBVR K NONE O OTHER IN INSP/MAINT 1 GL 09 551TP 2473 419 FOUND RIGHT AILERON TOP SKIN CRACKED AT OUTBOARD END. CRACK EXTENDED OUT FROM TWO SIDES OF A RIVET HEAD, APPROXIMATELY .1875 INCH IN BOTH DIRECTIONS. AILERON WAS REPAIRED AND WILL BE MONITORED FOR FURTHER CRACKING. 2 M 7 2 4F A2SW 1996071800745 19960718 00745 EU 1996 7 18 96ZZZX3632 2 19960507 G 7250 3013300650 SHAFT CFMINT CFM56 CFM563B2 13802 EU LPT ROTOR CRACKED B RD43 K NONE O OTHER IN INSP/MAINT 1 SW 05 28425 FN01136 721108 THE LPT SHAFT HAS 2 EACH CRACKS, ONE IS 5 AND ONE IS 7 INCHES LONG, ONE INCH APART STARTING APPROXIMATELY .50 INCH FROM THE AFT END OF THE SPLINES. INVESTIGATION IS IN PROGRESS BY CFMI. 4 F E21EU 1996071800746 19960718 00746 NE 1996 7 18 96ZZZX3633 2 19960607 G 7210 447245 BEARING PWA JT8 JT8D217A 52053 NE N2 GEARBOX FAILED B RD43 K NONE J WARNING INDICATION NR NOT REPORTED 1 SW 05 717374 ENGINE EXPERIENCED LOUD BANG AND EPR AND RPM WENT TO ZERO. ENGINE WAS REMOVED WITH INTERNAL AND EXTERNAL DAMAGE TO THE N2 GEARBOX. DISASSEMBLY OF THE GEARBOX REVEALED A FAILED BEARING. INVESTIGATION IS STILL UNDER WAY AT AVIALL. 4 F E9NE 1996071800747 19960718 00747 WP 1996 7 18 96ZZZX3634 1 19960705 G 5753 CLEVIS DOUG DC8 DC8F54 3021926 WP RT INBD FLAP CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 19 426FB 45667 DURING C-CHECK INSPECTION, A CRACK WAS FOUND EMANATING FROM A FASTENER HOLE IN THE LOWER TANG OF THE RIGHT WING INBOARD FLAP LOWER CLEVIS. REPAIRED CLEVIS BY INSTALLING A 2.0 INCH BY 2.0 INCH DOUBLER MADE OF .125 A1S1 301 1/2 H MATERIAL IA W EO 9606181. 8110-3 ISSUED BY DER SW-713. 2 L 7 4 4F 4A25 1996071800748 19960718 00748 WP 1996 7 18 96ZZZX3635 1 19960705 G 5753 CLEVIS DOUG DC8 DC8F54 3021926 WP LT INBD FLAP CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 19 426FB 45667 DURING C-CHECK INSPECTION, A CRACK WAS FOUND EMANATING FROM A FASTENER HOLE IN THE INBOARD FLAP. REPAIRED CLEVIS BY INS TALLING A 2.0 INCH BY 2.0 INCH DOUBLER MADE OF .125 A1S1 301 1/2 H MATERIAL IAW EO 960511. 8110-3 ISSUED BY DER SW-713. 2 L 7 4 4F 4A25 1996071800749 19960718 00749 SW 1996 7 18 96ZZZX3636 1 19960619 G 6230 412040101117 MAST BELL 412 412 1182202 SW M/R MISOVERHAULED B TI1R K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 05 117 N574X MAST RECEIVED FROM BELL AS SERVICEABLE REPAIRED. FOLLOWING DISCREPANCIES FOUND ON RECEIVING INSPECTION: 1. THE WORD ' REWORKED' NEVER WAS ENGRAVED ON FLANGE 'E' AS STATED ON BHT-C. R AND O MANUAL, SECTION 63-00-00, PAGE 62, PARAGRAPH 1, F IGURE 63-17. 2. INNER MAST AREA (BORE) WAS NEVER CLEANED AND CORE ON TOP SECTION IS MISSING. 3. FOUND PITTING CORROS ION ON SPLINES K-M, AREA 'A', SURFACE 'N', AND SPLINES 'O' AS MARKED ON MAST. 1 G 7 2 4U H4SW 1996012600442 19960126 00442 EA 1996 1 26 96ZZZX366 2 19960105 G 7322 377 PUG MA4SPA PIPER PA28 PA28140 7102802 SO LYC O320 O320E2A 41508 EA FUEL BOWL MISSING D K NONE W INADEQUATE Q C IN INSP/MAINT 1 NE 01 98242 290 CK34507 2826130 L2048027A CARBURETOR WAS FOUND TO HAVE A PLUG MISSING FROM FUEL BOWL. THE OPEN HOLE WAS ABOVE THE NORMAL FUEL LEVEL IN THE BOWL; HOWEVER, FUEL WAS FREE TO LEAK OUT WHEN THE A/C IS POSITIONED IN A NOSE DOWN PITCH. FUEL STAINS WERE NOTED. THIS PLUG WAS USED TO PLUG A HOLE MADE DURING THE MANUFACTURE OF THE CARBURETOR. 1 L 7 1 3O 3 O 2A13 E274 1996072500264 19960725 00264 1996 7 25 96ZZZX3667 4 19960402 G 3421 4021541671 GYRO BOLKMS 117 BK117A3 5626015 EU COCKPIT ATTITUDE DEFECTIVE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 911MZ 85101231 7098 ON INSTALLATION, GYRO UNIT WAS SLOW TO SPIN-UP AND GRADE-OFF. REMOVED AND REPLACED. 1 G 7 2 3U H13EU 1996072500265 19960725 00265 SW 1996 7 25 96ZZZX3668 1 19960430 G 6410 206016201103 BLADE 2060118103 BELL 206 206B 1181511 SW T/R DELAMINATED B CHIR K NONE O OTHER IN INSP/MAINT 1 NM 09 10ED 1516 TAH2340 1960 BOTH BLADES WERE FOUND DELAMINATED ON THE DOUBLERS AT THE BUTT END. NOTE: THE BLADES WERE REPAINTED IN 1991 - 353.7 HO URS AGO. REFERENCE: OPERATOR CONTROL NR CHI1543. (X) 1 G 7 1 3U H2SW 1996072500266 19960725 00266 1996 7 25 96ZZZX3669 4 19960525 G 2312 40001452500 TRANSCEIVER RT138F BOLKMS 117 BK117A3 5626015 EU COCKPIT FAILED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 911MZ 1263 7098 VHF-FM HI BAND RADIO WILL NOT TRANSMIT OR RECEIVE. REMOVED AND REPLACED. 1 G 7 2 3U H13EU 1996072500267 19960725 00267 1996 7 25 96ZZZX3670 4 19960619 G 3442 07113780D SENSOR RDS008100 BOLKMS 117 BK117A3 5626015 EU COCKPIT RADAR DEFECTIVE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 911MZ 12851 7098 TRANSMITTER FAULT. RADAR SENSOR. COLOR RADAR INDICATOR. 1 G 7 2 3U H13EU 1996072500268 19960725 00268 1996 7 25 96ZZZX3671 4 19960619 G 3442 066311400 INDICATOR RDS008100 BOLKMS 117 BK117A3 5626015 EU COCKPIT RADAR DEFECTIVE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 911MZ 13644 7098 TRANSMITTER FAULT. RADAR SENSOR. COLOR RADAR INDICATOR. 1 G 7 2 3U H13EU 1996072500378 19960725 00378 CE 1996 7 25 96ZZZX3673 1 19960604 G 7120 075100113 MOUNT CESSNA 180 180 2072602 CE FIREWALL CRACKED B S HE4R K NONE O OTHER IN INSP/MAINT 1 SO 11 UPPER LEFT AND RIGHT FIREWALL ATTACH BUSHINGS WERE FOUND CRACKED HORIZONTALLY. SUSPECT OVERTORQUING OF FIREWALL BOLTS A ND VIBRATION. 1 H 7 1 3O NC 5A6 1996072500379 19960725 00379 SO 1996 7 25 96ZZZX3674 1 19960619 G 2913 41130 ARMATURE HYC5005 PIPER PA28 PA28R200 7102811 SO POWER PACK FAILED D S K NONE O OTHER IN INSP/MAINT 1 NM 11 4290T 1048 ERH2506B 28R7235003 ARMATURE WAS NEW AT POWER PACK OVERHAUL AT 5,055 HOURS. ARMATURE FAILURE AT 6,103 HOURS. POWER PACK TT UNKNOWN. 1 L 7 1 3O 2A13 1996072500380 19960725 00380 CE 1996 7 25 96ZZZX3675 1 19960618 G 2720 35660031 CONTROL HORN BEECH 35 B35 1151506 CE RUDDERVATOR CRACKED D A K NONE O OTHER IN INSP/MAINT 1 SW 07 5269C D2663 DURING ANNUAL INSPECTION, CRACK FOUND COMING OUT OF BOLT HOLE WHERE HORN MOUNTS TO RUDDERVATOR. REPLACED WITH NEW PART. 1 L 7 1 3O A777 1996072500381 19960725 00381 CE 1996 7 25 96ZZZX3676 1 19960617 G 3230 S24266 ROD END CESSNA 177 177RG 2073709 CE MLG ACTUATOR BROKEN D A K NONE O OTHER IN INSP/MAINT 1 CE 07 52945 177RG1316 AT ANNUAL INSPECTION, THIS PART WAS FOUND BROKEN. SUBMITTER STATED SL SE79-37 OBVIOUSLY WAS NEVER COMPLIED WITH. SUGGE ST THAT THIS SERVICE LETTER BE MADE MANDATORY. 1 H 7 1 3O A20CE 1996072500382 19960725 00382 SO 1996 7 25 96ZZZX3677 1 19960621 G 7922 53E19600 VALVE PIPER PA31 PA31350 7103110 SO THERMO BYPASS NUT LOOSE D K NONE O OTHER IN INSP/MAINT 1 SW 07 35584 887 18135 318052076 THERMO BYPASS VALVE FAILED LYC SB 518C. LOCKNUT WAS SO LOOSE ITS REPAIR IAW SB 518C WAS NOT POSSIBLE. MOST OF THE VALV ES SUBMITTER REPORTS (APPROXIMATELY 85 TO 90 PERCENT) ARE FAILING THE INSPECTION AND REPAIRED ONLY 3 DUE TO THE EXTREMEL Y LOOSE LOCKNUTS. SUBMITTER STATED ANY VALVES WITH A LOOSE LOCKNUT SHOULD BE REPLACED. 1 L 7 2 3O A20SO 1996072500383 19960725 00383 SO 1996 7 25 96ZZZX3678 2 19960710 G 8530 530341 PISTON CESSNA 172 172E 2072412 CE CONT O300 O300D 17022 SO NR 1 CYLINDER CRACKED D K NONE O OTHER IN INSP/MAINT 1 NE 05 3793S 925 17250993 28332D3D DURING SCHEDULED OIL CHANGE, OWNER REQUESTED A COMPRESSION CHECK BE DONE. NR 1 CYLINDER WAS LOW AT 28/80. FURTHER INVE STIGATION REVEALED THE FOLLOWING: PISTON CRACKED FROM SKIRT TO FACE AT 6:00 O'CLOCK POSITION. TOP COMPRESSION RING BRO KEN AND CYLINDER WALL SCORED. THIS ENGINE ONLY HAD 30 HOURS SINCE PREVIOUS COMPRESSION CHECK WHICH WAS WELL WITHIN TCM CRITERIA. SUBMITTER RECOMMENDS COMPRESSION CHECKS BE DONE ON THESE OLDER ENGINES ESPECIALLY IF TOTAL TIME IS UNKNOWN AN D TSMOH IS MID-POINT OR BEYOND. 1 H 7 1 3O 3 O NT 3A12 E253 1996072500384 19960725 00384 1996 7 25 96ZZZX3679 4 19960705 G 2562 G SWITCH DORNEMARGLN DMELT6 CESSNA 182 182Q 2072732 CE ELT FAILED D K NONE O OTHER IN INSP/MAINT 1 NM 11 4743N 2338 39108 18267332 DURING 100-HOUR INSPECTION, PULLED ELT FOR FUNCTION CHECK, G-SWITCH WOULD NOT TRIGGER ON IMPACT. ELT WOULD FUNCTION IN ON POSITION. ELT REPLACED. 1 H 7 1 3O NT 3A13 1996012600444 19960126 00444 SO 1996 1 26 96ZZZX368 2 19960105 G 8530 6529551A CYLINDER PIPER PA34 PA34220T 7103420 SO CONT O360 TSIO360GB 17025 SO NR 5 HEAD SEPARATED D A UNSCHED LANDING O E R OTHER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CL CLIMB 1 WP 17 8335C 1473 348333056 309328 NR 5 CYLINDER HEAD SEPARATED FROM TIRE BARREL DURING TAKEOFF AT POWER REDUCTION. EMERGENCY LANDING MADE. NO FURTHER DA MAGE FOUND. 1 L 7 2 3O 3 O A7SO E9CE 1996072500385 19960725 00385 CE 1996 7 25 96ZZZX3680 1 19960708 G 2710 040010759 CONTROL CABLE CESSNA 150 152 2071835 CE LT AIL BALANCE FRAYED D K NONE O OTHER IN INSP/MAINT 1 SW 99 5403H 696 15284096 LEFT AILERON BALANCE CABLE FOUND FRAYED AT WS 56.87 ON CABLE SUPPORT BLOCK. THIS AIRCRAFT WAS ON 100-HOUR INSPECTION AN D ONCE CABLE STARTED FRAYING, CONDITION MUST HAVE ACCELERATED, CABLE WAS 50 PERCENT THROUGH. 1 H 7 1 3O NT 3A19 1996072500386 19960725 00386 SO 1996 7 25 96ZZZX3681 1 19960703 G 2750 62738000 BRACKET PIPER PA28 PA28140 7102802 SO FLAP HANDLE CRACKED D K NONE O OTHER IN INSP/MAINT 1 GL 03 98334 2826175 WHEN ACCOMPLISHING AD 96-10-03, FOUND FLAP HANDLE BRACKET CRACKED ONE-THIRD OF THE MOUNTING BOLT HEAD RADIUS, AROUND 3 O F THE 6 ATTACHING BOLTS. REPLACED BRACKET WITH FACTORY PART. 1 L 7 1 3O 2A13 1996072500387 19960725 00387 NM 1996 7 25 96ZZZX3682 1 19960702 G 7922 53E19600 VALVE CHILD S2 S2BPITTS 0110304 NM THERMO BYPASS CRIMP NUT LOOSE D K NONE O OTHER IN INSP/MAINT 1 NM 04 60823 70 57113 5269 INSPECTION FOUND LOOSE CRIMP NUT ON THERMOSTATIC BYPASS VALVE (EVEN WITH NEW STYLE PART). 1 Q 7 1 3O A8SO 1996072500388 19960725 00388 EA 1996 7 25 96ZZZX3683 2 19960601 G 8550 TUBE CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA OIL RUNBACK HOLE CHAFED D K NONE K FLUID LOSS IN INSP/MAINT 1 SO 16 69082 15282477 INSPECTION FOUND WIRING FOR ALTERNATOR MISROUTED, WORE HOLE IN OIL RUNBACK TUBE CAUSING OIL LEAK. 1 H 7 1 3O 3 O NT 3A19 E223 1996072500390 19960725 00390 1996 7 25 96ZZZX3685 4 19960628 G 6122 D20591 DRIVE GEAR MCAULY C290D4K GOVERNOR EXCESS WEAR B ME4D K NONE O OTHER IN INSP/MAINT 1 SO 15 785062 DURING INSPECTION OF PROPELLER GOVERNOR, FOUND EXCESSIVE WEAR ON SPLINE OF DRIVE GEAR. DRIVE GEAR WAS REPLACED WITH NEW D2088 DRIVE GEAR. 1996080600011 19960806 00011 EA 1996 8 6 96ZZZX3688 2 19960624 G 7414 10349271 COIL BENDIX S6LN1227 PIPER PA32 PA32300 7103212 SO LYC O540 IO540K1A5 41532 EA LT MAGNETO FAILED D K NONE O OTHER NR NOT REPORTED 1 NE 05 4135R 1677 17297 3240452 L547048 LEFT AND RIGHT MAGNETOS FAILED BECAUSE OF DEFECTIVE COILS WHEN HEATED FOR APPROXIMATELY 30 MINUTES. AIRCRAFT ON FERRY F LIGHT TO PERFORM ANNUAL INSPECTION. AD 94-01-03R2 REQUIRED AT ANNUAL OR 100 HOURS. AIRCRAFT HAS BEEN OUT OF ANNUAL FOR 4 YEARS. SUGGEST AD TO BE PERFORMED BEFORE FURTHER FLIGHT. 1 L 7 1 3O 3 O A3SO 1E4 1996072500393 19960725 00393 EA 1996 7 25 96ZZZX3689 2 19960624 G 7414 103493101 COIL BENDIX S6LN1209 PIPER PA32 PA32300 7103212 SO LYC O540 IO540K1A5 41532 EA RT MAGNETO FAILED D K NONE O OTHER NR NOT REPORTED 1 NE 05 4135R 1677 17209 3240452 L547048 LEFT AND RIGHT MAGNETOS FAILED BECAUSE OF DEFECTIVE COILS WHEN HEATED FOR APPROXIMATELY 30 MINUTES. AIRCRAFT ON FERRY F LIGHT TO PERFORM ANNUAL INSPECTION. AD 94-01-03R2 REQUIRED AT ANNUAL OR 100 HOURS. AIRCRAFT HAS BEEN OUT OF ANNUAL FOR 4 YEARS. SUGGEST AD TO BE PERFORMED BEFORE FURTHER FLIGHT. 1 L 7 1 3O 3 O A3SO 1E4 1996012600445 19960126 00445 SO 1996 1 26 96ZZZX369 2 19960110 G 8530 652955A1 CYLINDER CESSNA 172 R172K 2072431 CE CONT O360 IO360KB 17025 SO NR 1 HEAD SEPARATED D A UNSCHED LANDING B E R SMOKE/FUMES/ODORS/SPARKS VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CL CLIMB 1 EA 21 758FF 634 R1723055 355014 IMMEDIATELY AFTER LIFT OFF HEARD A LOUD BANG FROM ENGINE COMPARTMENT, 3 MORE ENTERED CABIN, ABORTED TAKEOFF AND SHUT DOW N ENGINE. REMOVED COWL AND FOUND NR 1 CYLINDER HEAD SEPARATED FROM BARREL. 1 H 7 1 3O 3 O 3A17 E1CE 1996072500394 19960725 00394 CE 1996 7 25 96ZZZX3690 1 19960708 G 2810 17260424 CAP CESSNA 177 177B 2073708 CE FUEL TANK WATER LEAK D K NONE O OTHER IN INSP/MAINT 1 SO 11 34873 17702058 FLUSH FUEL CAPS ALLOWING WATER TO LEAK INTO FUEL TANKS. BEING A WET WING AIRCRAFT, IT IS VERY DIFFICULT TO BE SURE ALL WATER IS REMOVED. INSTALLING NEW SEALS OR CAPS IS ONLY A TEMPORARY SOLUTION. PERMANENT FIX IS TO INSTALL STC SA2457CE PLATES AND CAPS OR OTHER TYPE RAISED INLET. 1 H 7 1 3O A13CE 1996072500395 19960725 00395 CE 1996 7 25 96ZZZX3691 1 19960705 G 5753 05239018 SUPPORT ASSY 0523901 CESSNA 172 172A 2072404 CE LT OTBD FLAP WORN D K NONE O OTHER IN INSP/MAINT 1 GL 25 7558T 4415 47158 DURING INSPECTION OF FLAPS PER CESSNA SEB95-3, FOUND ALL FLAP SUPPORTS HEAVILY WORN AND SEARED. INSTALLED FLAP SUPPORT KIT SK180-44. NEW SUPPORTS ARE HEAVIER AND FLANGED FOR STIFFNESS. SUBMITTER RECOMMENDS THIS SB BECOME AN AD. 1 H 7 1 3O 3A12 1996072500396 19960725 00396 CE 1996 7 25 96ZZZX3692 1 19960705 G 5753 05239019 SUPPORT ASSY 05239011 CESSNA 172 172A 2072404 CE RT OTBD FLAP WORN D K NONE O OTHER IN INSP/MAINT 1 GL 25 7558T 4415 47158 DURING INSPECTION OF FLAPS PER CESSNA SEB 95-3, FOUND ALL FLAP SUPPORTS HEAVILY WORN AND SCORED. INSTALLED FLAP SUPPORT KIT SK180-44. NEW SUPPORTS ARE HEAVIER AND FLANGED FOR STIFFNESS. SUBMITTER RECOMMENDS SB BECOME AN AD. 1 H 7 1 3O 3A12 1996072500397 19960725 00397 CE 1996 7 25 96ZZZX3693 1 19960705 G 5753 05239018 SUPPORT ASSY 0523901 CESSNA 172 172A 2072404 CE LT INBD FLAP WORN D K NONE O OTHER IN INSP/MAINT 1 GL 25 7558T 4415 45158 DURING INSPECTION OF FLAPS PER CESSNA SEB 95-3, FOUND ALL FLAP SUPPORTS HEAVILY WORN AND SCORED. INSTALLED FLAP SUPPORT KIT SK180-44. NEW SUPPORTS ARE HEAVIER AND FLANGED FOR STIFFNESS. SUBMITTER RECOMMENDS THIS SB BECOME AN AD. 1 H 7 1 3O 3A12 1996072500398 19960725 00398 EA 1996 7 25 96ZZZX3694 2 19960708 G 8520 CASE CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA NR 2 CYL LT SIDE CRACKED B DPOD K NONE O OTHER IN INSP/MAINT 1 NM 07 739PJ 1431 17270694 L607576T LEFT CASE CRACKED BELOW NR 2 CYLINDER BASE. CRACK WAS ABOUT 2.5 INCHES LONG. 1 H 7 1 3O 3 O NT 3A12 E274 1996072500400 19960725 00400 1996 7 25 96ZZZX3696 4 19960628 G 2562 BP1026 BATTERY MERL CIR11 PIPER PA23 PA23250 7102308 SO ELT LEAKING D K NONE O OTHER IN INSP/MAINT 1 NE 05 700Y 23437 277754076 OPEN ELT BATTERY TO CHANGE BATTERY AND C/W FAR 91.207. FOUND BATTERY PACK LEAKING AND ELT ITSELF JUST STARTING TO CORRO DE. SUSPECT CAUSE EITHER AGE OF HEAT FROM SUN. SUBMITTER RECOMMENDS TO KEEP COMPLYING WITH FAR 91-207. 1 L 7 2 3O 1A10 1996072500401 19960725 00401 EA 1996 7 25 96ZZZX3697 2 19960702 G 8530 434011 CYLINDER NAMER NA260 T28* GL WRIGHT R1820 R1820* 67020 EA FLANGE CRACKED D O OTHER B K SMOKE/FUMES/ODORS/SPARKS FLUID LOSS NR NOT REPORTED 1 SW 99 28YF 400 137799W ENGINE SHOWED EVIDENCE OF OIL LEAK. MECHANIC MUST HAVE THOUGHT HE HAD CURED PROBLEM. AIRCRAFT CLEARED FOR FLIGHT. NR 1 CYLINDER DEPARTED ENGINE SOME TIME AFTER PILOT NOTICED SMOKE IN COCKPIT. INSTRUMENTS SHOWED NORMAL READINGS. CYLINDE R HAD EVIDENCE OF OLD CRACK IN AREA OBSCURED BY COOLING FINS AND PROPELLER GOVERNOR. FOLLOWING MILITARY MAINTENANCE PRO GRAM, COULD (MIGHT) HAVE HELPED, BUT CYLINDER CRACKS OCCURRED IN MILITARY USE ALSO. 1 L 7 1 4R 4 R 1A18 5E10 1996072500402 19960725 00402 CE 1996 7 25 96ZZZX3698 1 19960629 G 3211 24411001 PIVOT CESSNA 172 172RG 2072438 CE LT MLG SHEARED D A O OTHER J WARNING INDICATION AP APPROACH 1 SW 99 6589V 6461 172RG0778 LEFT MLG COULD NOT BE FULLY EXTENDED. EVERY POSSIBLE ATTEMPT FAILED. DURING LAST ATTEMPT BEFORE GEAR-UP LANDING, PILOT PHYSICALLY REACHED OUT AND LOCKED GEAR. (FLIGHT INSPECTER WAS ALSO ON BOARD.) SAFE LANDING WAS MADE. UPON INSPECTION , PN 24411001 WAS FOUND SHEARED AT ACTUATOR GEAR ATTACH POINT. NO DEFINITE CAUSE WAS NOTED. TIME AND FATIGUE ARE SUSPE CT REASONS FOR PART FAILURE. THERE IS NO OTHER WAY OF DOWNLOCKING GEAR WITH THS TYPE OF FAILURE. 1 H 7 1 3O 3A17 1996072500403 19960725 00403 CE 1996 7 25 96ZZZX3699 1 19960705 G 5753 052390139 SUPPORT ASSY 0523901 CESSNA 172 172A 2072404 CE RT OTBD FLAP WORN D A K NONE O OTHER IN INSP/MAINT 1 GL 25 7558T 4415 47158 DURING INSPECTION OF FLAPS PER CESSNA SEB 95-3, FOUND ALL FLAP SUPPORTS HEAVILY WORN AND SCORED. INSTALLED FLAP SUPPORT KIT SK180-44. NEW SUPPORTS ARE HEAVIER AND FLANGED FOR STIFFNESS. SUBMITTER RECOMMENDS THIS SB BECOME AN AD. 1 H 7 1 3O 3A12 1996072500404 19960725 00404 EA 1996 7 25 96ZZZX3700 2 19960625 G 7414 M3065 ROTOR SLICK 4347 BEECH 95 D95A 1153408 CE LYC O360 IO360B1B 41514 EA MAGNETO SHAFT FAILED D S K NONE O OTHER IN INSP/MAINT 1 WP 13 199Q 205 94120022 TD581 L655351A ENGINE NO START. TROUBLESHOOTING ISOLATED TO MAGNETO. OPENED MAGNETO HOUSING TO INSPECT. REMOVED DISTRIBUTOR BLOCK AN D GEAR ASSEMBLY. NOTICED ROTOR GEAR APPEARED DETACHED. REMOVED GEAR AND FOUND SHAFT HAD BROKEN AT AREA BELOW POINT CAM SLOT. SLOTTED PORTION OF SHAFT REMAINED IN ROTOR GEAR. BREAK AREA APPEARED TO HAVE HAD MATERIAL DEFECT/CORROSION FROM DISCOLORED DARK AREA. SUBMITTER STATED DUE TO LOW TIME, SUSPECT DEFECTIVE MATERIAL. 1 L 7 2 3O 3 O 3A16 1E10 1996072500405 19960725 00405 1996 7 25 96ZZZX3701 4 19960601 G 3418 599160 TRANSDUCER PIPER PA46 PA46350P SO LT WING LIFT FAILED B A AMYR K NONE N FALSE WARNING NR NOT REPORTED 1 CE 05 9261Z 10 394 4636016 STALL WARNING FAIL LIGHT ON BECAUSE OF FAILED PRIMARY COIL OF LIFT TRANSDUCER. THIS IS THE SECOND ONE FAILED ON THIS AI RCRAFT. FIRST TRANSDUCER HAD 140 HOURS TTSN. THE SECOND LASTED 10.0 HOURS. BOTH FAILED FOR SAME MECHANICAL FAULT, PRI MARY COIL OPEN. AIRCRAFT MANUFACTURER HAS RECORDED SEVERAL OF THESE FAILURES. SUGGESTIONS ARE TO USE STALL TEST SWITCH FOR TESTS, AND TO NEVER TOUCH TRANSDUCER, ESPECIALLY DURING WASHING AIRCRAFT. 1 L 7 1 3O RT A25SO 1996072500406 19960725 00406 SO 1996 7 25 96ZZZX3702 2 19960703 G 8550 CH48108 FILTER CHAMPION BEECH 58 58P 1152744 CE CONT O520 TSIO520WB 17040 SO ENGINE OIL DEFECTIVE D K NONE W INADEQUATE Q C IN INSP/MAINT 1 NE 05 6648K TJ204 248173R OIL FILTER CUT OPEN AT OIL CHANGE. NOTICED INSIDE GASKET WAS CUT AND SLIGHTLY MISALIGNED. CLOSER LOOK REVEALED METAL P ORTION WAS CUT APPROXIMATELY ONE INCH AND ONE INCH SLIVER ABOUT .0625 INCH THICK WAS STICKING INTO OIL OUTLET PATH. HAD THIS SLIVER COME LOOSE, IT WOULD HAVE GONE INTO THE ENGINE, POSSIBLY CAUSING A CATASTROPHIC FAILURE. RECOMMEND STICKIN G FINGER INTO NEW FILTERS PRIOR TO INSTALLING TO CHECK FOR DEFECTS. 1 L 7 2 3O 3 O A23CE E8CE 1996072500564 19960725 00564 SW 1996 7 25 96ZZZX3718 1 19960710 G 5751 2734023011 SPAR 2734000039 SWRNGN SA227 SA227AC 8780603 SW OTBD HINGE CRACKED G P K NONE O OTHER IN INSP/MAINT 1 SW 11 359AE C096 AC674 DURING DISASSEMBLY OF AILERON FOR SKIN CHANGE, THE SPAR WAS FOUND CRACKED IN TWO PLACES AROUND OUTBOARD HINGE BRACKET. T HE CRACKS WERE THE FULL WIDTH OF THE SPAR WEB AND INTO THE RADIUS OF THE FLANGES. THIS IS THE SECOND SPAR FOUND CRACKED LIKE THIS RECENTLY. A MANDATORY VISUAL INSPECTION OF THE AILERON SPAR IS STRONGLY RECOMMENDED. 2 L 7 2 4T RT A8SW 1996072500565 19960725 00565 EA 1996 7 25 96ZZZX3719 1 19960627 G 2913 24535 FACE SEAL ABEX 6310806 CNDAIR CL600 CL6002A12 1900304 EA HYDRAULIC PUMP GOUGED B SH5R K NONE O OTHER IN INSP/MAINT 1 NE 03 CFURG 23534B 3063 DISASSEMBLED PUMP, FOUND THE NOSE SEAL AND FACE SEALS GOUGED. INSPECTED THE NOSE SEAL, FOUND THE COATING IN THE O-RING BOSS CRACKED AND LIFTING OFF. NO OTHER FOREIGN MATERIAL FOUND IN THE PUMP CAVITY. 2 L 7 2 4F RT A21EA 1996072500566 19960725 00566 EA 1996 7 25 96ZZZX3720 1 19960627 G 2913 24539 NOSE SEAL ABEX 6310806 CNDAIR CL600 CL6002A12 1900304 EA HYDRAULIC PUMP GOUGED B SH5R K NONE O OTHER IN INSP/MAINT 1 NE 03 CFURG 23534B 3063 DISASSEMBLED PUMP, FOUND THE NOSE SEAL AND FACE SEALS GOUGED. INSPECTED THE NOSE SEAL, FOUND THE COATING IN THE O-RING BOSS CRACKED AND LIFTING OFF. NO OTHER FOREIGN MATERIAL FOUND IN THE PUMP CAVITY. 2 L 7 2 4F RT A21EA 1996072500567 19960725 00567 SW 1996 7 25 96ZZZX3721 1 19960626 G 5330 PANEL MTSBSI MU2 MU2B20 5780407 SW AFT FUSELAGE WATER LEAK D K NONE O OTHER IN INSP/MAINT 1 SW 15 183MA 217 THE AIRCRAFT HAS HAD A HISTORY OF DIRECTIONAL GYRO FAILURE. AT INSPECTION, WATER WAS RUN OVER THE AFT FUSELAGE AND IT W AS DISCOVERED THAT WATER WAS COMING IN AT THE AFT FUSELAGE ATTACH HARDWARE ACCESS PANELS RUNNING DOWN THE STRINGER JUST UNDER ATTACHING HARDWARE AND DRIPPING ON TOP OF GYRO. THE PANEL WAS REMOVED, CLEANED, AND REINSTALLED WITH SEALANT. 1 H 7 2 3T A2PC 1996072500568 19960725 00568 EU 1996 7 25 96ZZZX3722 1 19960703 G 5522 46302402 ELEVATOR ISRAEL 1124 1124 4500102 EU RT ELEV TE DELAMINATED B GQFG K NONE O OTHER IN INSP/MAINT 1 SW 09 342AJ 4354 342 DELAMINATION ON UPPER AND LOWER SURFACES WITH A CRACK ON UPPER TRAILING EDGE. AIRCRAFT TT: 4,100 HOURS. LANDINGS, 3,3 40. 2 M 7 2 4F A2SW 1996072500569 19960725 00569 EA 1996 7 25 96ZZZX3723 1 19960624 G 3240 601R852001 SENSOR CNDAIR CL600 CL6002B19 EA BRAKE TEMP BROKEN B FZ1R K NONE O OTHER IN INSP/MAINT 1 EA 15 5100X 2754 7008 DURING ROUTINE BRAKE CHANGE, NOTICED THE BRAKE TEMPERATURE SENSOR WAS UNSERVICEABLE DUE TO A CRACK GOING ALL THE WAY ARO UND THE BASE OF THE PROBE. THE SENSOR WS REPLACED AND THE BRAKE CHANGE WAS COMPLETED. AIRCRAFT WAS RETURNED TO SERVICE . SUBMITTER RECOMMENDATION WOULD BE TO BEEF UP THE PROBE DIAMETER AT THE BASE. 2 L 7 2 4F RT A21EA 1996072500570 19960725 00570 EU 1996 7 25 96ZZZX3724 1 19960703 G 7830 2660042505 LONGERON ASSY ROHR 2660003505 BRAERO 1000 BAE1251000 1500287 EU LT ENG T/R CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 14 513QS 2983 CUM37 NA1004 FOUND CRACK ON LEFT ENGINE THRUST REVERSER UPPER DOOR INBOARD LONGERON ASSEMBLY, ABOUT 2 INCHES FROM BUMPER. LONGERON A SSEMBLY IS WEAK IN MACHINED AREA WHICH IS WHERE THE CRACK IS LOCATED. 2 L 7 2 4F RT A3EU 1996072500572 19960725 00572 SW 1996 7 25 96ZZZX3726 1 19960621 G 7120 NAS627H46 BOLT LORD LM600 SWRNGN SA227 SA227TT SW ENGINE MOUNT IMPROPER D K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 25 SECOND OCCURRENCE ON THIS TYPE AIRCRAFT WITH HEAVY TRUSS. SIDE MOUNT ISOLATOR THROUGH-BOLT DOES NOT ENGAGE LOCKING DEVI CE IN ENGINE MOUNT TRUSS. VENDOR (LORD) CALLS FOR NRS627-H46 AND LM427-10 WASHER. FAIRCHILD CALLS FOR NAS627-50 WITH M S20002C7 WASHER. USING VENDOR HARDWARE REDUCES LENGTH OF ENGAGEMENT BY .295 INCH. SAFETY WIRE HOLE IN HEAD OF BOLT ON THIS TYPE AIRCRAFT SHOULD BE REASON ENOUGH TO INSPECT MORE CLOSELY. 2 L 7 2 4T RT A5SW 1996072500573 19960725 00573 SW 1996 7 25 96ZZZX3727 1 19960627 G 2910 27810322682 LINE FRCHLD SA227 SA227DC 3377521 SW RT FIREWALL CRACKED D K NONE K FLUID LOSS NR NOT REPORTED 1 CE 01 3005W 2441 DC801M HYDRAULIC LINE CRACKED IN RADIUS OF 90 DEGREE BEND. ALL AIRCRAFT HYDRAULIC PRESSURE LOST WITHIN 10 MINUTES. THIS LINE AND OTHERS ARE SPECIFIED FOR REPLACEMENT AND/OR INSPECTION PER FAIRCHILD SB CC7-29-001 WITH NO SPECIFIC TIME REQUIREMENT . SUBMITTER RECOMMENDS AN AD TO AVOID CONTINUED USE OR PROLONGED USE BEFORE INSPECTION OR REPLACEMENT. 2 L 7 2 4T RT A18SW 1996072500574 19960725 00574 GL 1996 7 25 96ZZZX3728 2 19960607 G 7200 ENGINE DOUG DC10 DC1030 3023501 WP GE CF6 CF66D 30020 GL NR 3 FIRE B ZUFY K NONE A FLAME/FIRE IN INSP/MAINT 1 EA 35 833LA 46937 DURING ENGINE START ON PUSH-BACK, NR 3 ENGINE SUFFERED A JET-PIPE FIRE AT MANCHESTER. FIRE EXTINGUISHED BY AIRPORT FIRE SERVICE. NO DAMAGE. AIRCRAFT HISTORY OF FUEL FLOW PROBLEMS. FIRE OCCURRED ON SECOND ATTEMPT TO START. NR 3 ENGINE, NR 2 FIRE BOTTLE USED, NO EFFECT. NR 1 FIRED. OK. FULL REPORT TO FOLLOW. 2 L 7 3 4F 4 F A22WE E23EA 1996072500575 19960725 00575 SW 1996 7 25 96ZZZX3729 1 19960705 G 6310 206040118001 COUPLING BELL 206 206B 1181511 SW M/R DRIVE DEFECTIVE B GS1R K NONE W INADEQUATE Q C IN INSP/MAINT 1 EA 03 144H 18 A8966 4348 INSPECTION FOUND COUPLING NOT PROPERLY COATED. REPLACED WITH NEW COUPLING. 1 G 7 1 3U H2SW 1996012600449 19960126 00449 SO 1996 1 26 96ZZZX373 1 19960103 G 3230 4198301 HOOK ASSY PIPER PA31 PA31 7103102 SO RT MLG STUCK B CS3R O OTHER J WARNING INDICATION AP APPROACH 1 WP 17 310DS 4278 31579 RIGHT GEAR WOULD NOT INDICATE DOWN IN THE AIR. AIRCRAFT MADE EMERGENCY LANDING. INSPECTED RIGHT GEAR, FOUND DOWNLOCK H OOK STUCK. REMOVED PIVOT BOLT AND HOOK. CLEANED AND LUBED. REINSTALLED HOOK. GEAR SWING OK. 1 L 7 2 3O A20SO 1996072500576 19960725 00576 SW 1996 7 25 96ZZZX3730 1 19960604 G 2150 JBS2201 COMPRESSOR BELL 206 206B 1181511 SW COOLING SYSTEM INTERFERENCE D K NONE O OTHER IN INSP/MAINT 1 SO 09 BHT 206, TH-67 IFR AIRCRAFT WITH ENVIRONMENTAL COOLING SYSTEM OPERATING, WHEN THE HSI IS IN 'SLAVE' POSITION, THE HSI NE EDLE DRIFTS 4 TO 6 DEGREES. SUSPECT EMI FROM ENVIRONMENTAL COOLING SYSTEM COMPRESSOR CLUTCH ASSEMBLY. SUBMITTER STATES THE INTERFERENCE IS OCCURRING ON ALL 206B SERIES ROTORCRAFT. 1 G 7 1 3U H2SW 1996072500577 19960725 00577 GL 1996 7 25 96ZZZX3731 2 19960110 G 7323 A1AA1 GOVERNOR HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL N2 GOVERNOR SHAFT SEPARATED D P K NONE O OTHER NR NOT REPORTED 1 WP 13 8625F 1338 327 13605 470111D CAE830515 ENGINE RPM DROOPED. REMOVED N2 GOVERNOR AND FOUND DRIVE SPLINE, SPRING AND WASHERS HAD FALLEN OFF. 1 G 7 1 3U 3 U H3WE E4CE 1996072500579 19960725 00579 EU 1996 7 25 96ZZZX3733 1 19960712 G 2742 ACTUATOR ISRAEL 1124 1124 4500102 EU PITCH TRIM SHAFT SHEARED C A K NONE O OTHER IN INSP/MAINT 1 EA 25 317MB 2734 432 DURING A 600-HOUR ROUTINE INSPECTION, NOTED A PORTION OF THE HORIZONTAL STABILIZER WAS STRIKING THE FUSELAGE AND CAUSING PAINT DAMAGE. AFTER FURTHER INVESTIGATION DETERMINED THE PITCH TRIM ACTUATOR SHAFT HAD SHEARED. THE PITCH TRIM ACTUAT OR IS ATTACHED TO THE HORIZONTAL STABILIZER WITH 2 ROD END SHAFTS. PRESENTLY, THERE IS NO LIFE-LIMIT ON THIS PART. 2 M 7 2 4F A2SW 1996080200061 19960802 00061 EU 1996 8 2 96ZZZX3736 1 19960620 G 7712 30573136A INDICATOR SNIAS 350 AS350B 8680801 EU COCKPIT TORQUE FAILED B SZTR K NONE O OTHER IN INSP/MAINT 1 WP 07 911NW 1192 1605 PILOT REPORTED NO TORQUE INDICATION. REPLACED GAUGE. STILL NO TORQUE INDICATION. REPLACED GAUGE. OPS CHECKED GOOD. 1 G 7 1 3U H9EU 1996080200191 19960802 00191 NM 1996 8 2 96ZZZX3745 1 19960710 G 8012 2701321 HOUSING 2730426 BOEING 737 737* NM AIR START CRACKED H A K NONE O OTHER IN INSP/MAINT 1 NM 01 20280 015L THE START VALVE HOUSING, PN 2701321, IS CRACKED UNDER THE IDENTIFICATION PLATE CAUSING AIR TO ESCAPE THROUGH THE CRACK A ND THE VALVE TO MALFUNCTION. HAVE RECEIVED SEVERAL UNITS WITH THIS DEFECT/DAMAGE. THE SUSPECTED CAUSE IS THE OVERTORQU ING OF THE FILTER WHEN THE VALVE IS INSTALLED ON THE AIRCRAFT. SUBMITTER RECOMMENDS THE MANUFACTURER LOOK AT THE DESIGN OF THE HOUSING TO PREVENT AND CORRECT THE PROBLEM OF CRACKING. THE AREA OF THE HOUSING THAT IS CRACKING IS A THIN CAST ING AREA. 2 L 7 2 4F RT A16WE 1996080200192 19960802 00192 NM 1996 8 2 96ZZZX3746 1 19960710 G 3610 31737772 ROD ASSY 32895624 BOEING 737 737* NM COOLER VALVE CHAFED H S K NONE O OTHER IN INSP/MAINT 1 NM 01 693 960C MUTUAL CONTACT HAS CAUSED SEVERE CHAFING BETWEEN PIVOT ARMS OF ROD ASSY AND FLAT PIVOT AREA OF LEVER. THIS OCCURRED DUR ING NORMAL OPERATION. TOO SOFT STEEL USED IN MANUFACTURE. SUBMITTER STATED TO PREVENT RECURRENCE, HARDEN STEEL AND ALL OW PIVOT ARM ROD TO ROTATE. 2 L 7 2 4F RT A16WE 1996080200193 19960802 00193 NM 1996 8 2 96ZZZX3747 1 19960710 G 3610 31776561 LEVER 32895624 BOEING 737 737* NM COOLER VALVE CHAFED H K NONE O OTHER IN INSP/MAINT 1 NM 01 693 MUTUAL CONTACT HAS CAUSED SEVERE CHAFING BETWEEN PIVOT ARMS OF ROD ASSY AND FLAT PIVOT AREA OF LEVER. THIS OCCURRED DUR ING NORMAL OPERATION. TOO SOFT STEEL USED IN MANUFACTURE. SUBMITTER STATED TO PREVENT RECURRENCE, HARDEN STEEL AND ALL OW PIVOT ARM ROD TO ROTATE. 2 L 7 2 4F RT A16WE 1996080200194 19960802 00194 CE 1996 8 2 96ZZZX3748 1 19960618 G 3233 98820001 ACTUATOR CESSNA 210 P210N 2073454 CE LT MLG CRACKED B S BX4R K NONE O OTHER LD LANDING 1 NM 03 18DP 1125 2330 P21000086 AFTER A HARD OFF-FIELD LANDING, FOUND LEFT MAIN ACTUATOR HOUSING CRACKED ADJACENT TO AND ALONG THE AFT PART OF THE UPPER SEAM OF THE HOUSING. CRACK RUNS FROM AFT END, FORWARD TO THE BASE OF BOSS FOR 'AN' FITTING. ENTIRE LENGTH OF CRACK IS OPEN APPROXIMATELY .1250 INCH. 1 H 7 1 3O 3A21 1996080200195 19960802 00195 CE 1996 8 2 96ZZZX3749 1 19960418 G 5711 0411131 SPAR CESSNA 140 140 2071602 CE LT DOOR POST CRACKED D A K NONE O OTHER IN INSP/MAINT 1 EA 17 2408N 288 12657 THIS IS THE THIRD TIME THIS SPAR HAS BEEN CRACKED. THIS AIRCRAFT IS ON EDO 88-1650 FLOATS. IT IS NECESSARY TO REMOVE T HE FORWARD END OF THE HEADLINER TO INSPECT THIS AREA. AIRCRAFT TT, 3,042.39 HOURS. 1 H 7 1 3O NC A768 1996080200196 19960802 00196 SO 1996 8 2 96ZZZX3750 2 19960701 G 8550 15000793 NIPPLE CESSNA 337 T337C 2075714 CE CONT O360 TSIO360A 17025 SO ACCESSORY CASE FAILED B A DJ3R A E UNSCHED LANDING ENGINE SHUTDOWN K FLUID LOSS NR NOT REPORTED 1 WP 17 2522S 3370822 197111R THE RIGID PIPE NIPPLE THAT IS THREADED INTO ACCESSORY CASE BETWEEN MAGNETOS FAILED AT THE BOTTOM OF THE THREAD GROOVE FL USH WITH THE ACCESSORY CASE. THIS ALLOWED RETURN OIL FROM THE WASTEGATE CONTROLLERS TO GO OVERBOARD. THE PILOT SAW THE OIL PRESSURE DROPPING. SHUT DOWN ENGINE AND MADE A SAFE LANDING. THE PART INSTALLED IN FACTORY REBUILT ENGINE. ENGIN E TIME AT FAILURE 172 HOURS. FAILURE WAS CAUSED BY METAL FATIGUE AND CONCENTRATED STRESS OF A RIGID ARM PROTRUDING 8 IN CHES SUPPORTING A T-FITTING AND TWO HOSES. THIS IS A CESSNA PART ALTHOUGH IT CAME FROM CONTINENTAL ON THE ENGINE. 1 H 7 2 3O 3 O A6CE E9CE 1996080200197 19960802 00197 SO 1996 8 2 96ZZZX3751 1 19960624 G 2430 454712 BREAKER PIPER PA31 PA31350 7103110 SO ALT CIRCUIT FAILED B A HX1R K NONE O OTHER IN INSP/MAINT 1 EA 25 3529N 33 31792167 SUBMITTER REPORTS THIS IS THE 4TH CIRCUIT BREAKER SWITCH THAT FAILED INTERNALLY. BREAKERS HAVE ALL FAILED IN THE SAME M ANNER. IF HELD IN THE 'ON' POSITION, THEY WILL WORK, BUT AS SOON AS RELEASED, THEY STOP WORKING AND SHUT THE ALTERNATOR OFF. SUBMITTER STATED ALL 4 FAILURES ARE IN SAME AIRCRAFT AND HAVE TAKEN PLACE IN LAST 6 MONTHS. 1 L 7 2 3O A20SO 1996080200198 19960802 00198 SO 1996 8 2 96ZZZX3752 1 19960501 G 5210 4834800 MOUNT BRACKET PIPER PA31T PA31T 7103124 SO DOOR SNUBBER FAILED B A EBVR K NONE O OTHER IN INSP/MAINT 1 GL 09 618SW 4244 31T8166036 CABIN DOOR SNUBBER UPPER MOUNT BRACKET TORE AWAY FROM FORWARD DOOR FRAME BULKHEAD AS PASSENGER WAS EXITING THE AIRCRAFT. PASSENGER APPARENTLY DID NOT ALLOW DOOR TO FULLY OPEN BEFORE STEPPING OUT ONTO IT. FURTHER INVESTIGATION OF BULKHEAD SHOWED EVIDENCE OF PRE-EXISITNG CRACKS EMANATING FROM RIVETS IN THE SNUBBER MOUNT AREA. SUBMITTER RECOMMENDS PUBLISHING AN ALERT FOR THESE AIRCRAFT TO BE INSPECTED FOR CRACKS IN THIS AREA. ALSO, THESE CABIN DOORS SHOULD BE PLACARDED FOR C REW OPERATION ONLY. 1 L 7 2 3T A8EA 1996080200199 19960802 00199 1996 8 2 96ZZZX3753 4 19960521 G 2564 1021 CYLINDER HOOVERIND FR46 LIFE RAFT RUSTED B OD1R K NONE O OTHER IN INSP/MAINT 1 EA 25 A649687 THIS FACILITY RECEIVED A HOOVER IND MODEL FR-46, S/N J47 FOR OVERHAUL. UPON INSPECTION AND PRIOR TO PERFORMING A HYDROS TATIC RE-TEST, THE TWO INSTALLED INFLATION CYLINDERS WERE FOUND TO HAVE INTERNAL RUST. (CAUSE FOR REJECTION.) BOTH CY LINDERS HAVE A 521 94 RE-TESTER STAMP ON THE CYLINDERS. SUSPECT CAUSE FOR INTERNAL RUST COULD BE DUE TO NOT HAVING BEEN DRIED THOROUGHLY AFTER LAST HYDROSTATIC RE-TEST. 1996080200200 19960802 00200 1996 8 2 96ZZZX3754 4 19960521 G 2564 1021 CYLINDER HOOVERIND FR46 LIFE RAFT RUSTED B OD1R K NONE O OTHER IN INSP/MAINT 1 EA 25 A685062 THIS FACILITY RECEIVED A HOOVER IND MODEL FR-46, S/N J47 FOR OVERHAUL. UPON INSPECTION AND PRIOR TO PERFORMING A HYDROS TATIC RE-TEST, THE TWO INSTALLED INFLATION CYLINDERS WERE FOUND TO HAVE INTERNAL RUST. (CAUSE FOR REJECTION.) BOTH CY LINDERS HAVE A 521 94 RE-TESTER STAMP ON THE CYLINDERS. SUSPECT CAUSE FOR INTERNAL RUST COULD BE DUE TO NOT HAVING BEEN DRIED THOROUGHLY AFTER LAST HYDROSTATIC RE-TEST. 1996080200201 19960802 00201 1996 8 2 96ZZZX3755 4 19960521 G 2564 1021 CYLINDER HOOVERIND LIFE RAFT RUSTED B OD1R K NONE W INADEQUATE Q C IN INSP/MAINT 1 EA 25 D468310 TWO REPLACEMENT CYLINDERS RECEIVED FROM HOOVER IND FOR A MODEL FR-46 LIFE RAFT WERE FOUND TO BE UNACCEPTABLE. THESE CYL INDERS WERE MANUFACTURED IN 8/95 AND 1/96. THESE CYLINDERS WERE TO BE REPLACEMENTS FOR THE TWO INSTALLED ON THE RAFT AN D WERE FOUND TO HAVE INTERNAL RUST. 1996080200202 19960802 00202 1996 8 2 96ZZZX3756 4 19960521 G 2561 1021 CYLINDER HOOVERIND LIFE RAFT RUSTED B OD1R K NONE W INADEQUATE Q C IN INSP/MAINT 1 EA 25 D303107 TWO REPLACEMENT CYLINDERS RECEIVED FROM HOOVER IND FOR A MODEL FR-46 LIFE RAFT WERE FOUND UNACCEPTABLE. THESE CYLINDERS WERE MANUFACTURED IN 8/95 AND 1/96. THESE CYLINDERS WERE TO BE REPLACEMENTS FOR THE TWO INSTALLED ON THE RAFT AND WERE FOUND TO HAVE INTERNAL RUST. 1996080200203 19960802 00203 EA 1996 8 2 96ZZZX3757 2 19960318 G 7414 1016301010 MAGNETO S6L200 PIPER PA23 PA23250 7102308 SO LYC O540 TIO540C1A 41532 EA DRIVE FAILED D K NONE O OTHER IN INSP/MAINT 1 SW 99 123CF 550 J229127EX 278054017 MAGNETO WAS FOUND WITH DRIVE NUT HAVING NO THREADS AND NO THREADS ON DRIVE. 1 L 7 2 3O 3 O 1A10 E14EA 1996080200204 19960802 00204 SO 1996 8 2 96ZZZX3758 1 19960702 G 2752 489428 TRANSMISSION DUKES 121600011190 PIPER PA31T PA31T 7103124 SO RT FLAP FAILED D A UNSCHED LANDING F FLT CONT AFFECTED AP APPROACH 1 WP 19 155CA 6667 1190 31T7820024 ON APPROACH TO SVE WITH FLAPS FULLY EXTENDED, THE RT FLAP SUDDENTLY RETRACTED CAUSING SEVERE YAW. LT FLAP WAS RETRACTED AND REGAINED CONTROL. ABORTED LANDING AND RETURNED TO RNO. TRANSMISSION FAILED INTERNALLY. DRIVEN GEAR DISINTEGRATED . NOTE: WEAR CHECKS PERFORMED PER AD 82-27-13R2 EACH 100 HOURS. SUBMITTER RECOMMENDS REPLACING OLDER DUKES TRANSMISSI ONS AND DECREASING THE INTERNAL INSPECTION INTERVAL. 1 L 7 2 3T A8EA 1996080200205 19960802 00205 CE 1996 8 2 96ZZZX3759 1 19960711 G 5711 CARRY THROUGH BEECH 33 F33A 1151425 CE WING CRACKED D K NONE O OTHER IN INSP/MAINT 1 WP 07 1556A 7942 CE1318 INSPECTION FOUND CRACKS IN CARRY-THROUGH STRUCTURE. AD 95-04-03 NOT VALID BY SERIAL NUMBER. 1 L 7 1 3O 3A15 1996080200206 19960802 00206 CE 1996 8 2 96ZZZX3760 1 19960711 G 5711 CARRY THROUGH BEECH 33 F33A 1151425 CE WING CRACKED D K NONE O OTHER IN INSP/MAINT 1 WP 07 1564A 8241 CE1321 INSPECTION FOUND CRACKS IN CARRY-THROUGH STRUCTURE. AD 9504-03 NOT VALID BY SERIAL NUMBER. 1 L 7 1 3O 3A15 1996080200207 19960802 00207 CE 1996 8 2 96ZZZX3761 1 19960711 G 5711 CARRY THROUGH BEECH 33 F33A 1151425 CE WING CRACKED D K NONE O OTHER IN INSP/MAINT 1 WP 07 1570A 8242 CE1333 INSPECTION FOUND CRACKS IN CARRY-THROUGH STRUCTURE. AD 95-04-03 NOT VALID BY SERIAL NUMBER. 1 L 7 1 3O 3A15 1996080200208 19960802 00208 1996 8 2 96ZZZX3762 4 19960712 G 2562 7J4193 ELT LEIGH CESSNA 172 R172K 2072431 CE G-SWITCH MALFUNCTION D A K NONE O OTHER IN INSP/MAINT 1 NM 01 1609V 302112 R1722205 EMERGENCY LOCATER TRANSMITTER CESSNA P/N C589510-0209, WOULD NOT PASS G-SWITCH OPERATIONAL CHECK PER FAR 91.207(D). LIG HT TOO EXCESSIVE FORCE, WOULD NOT SET OFF G-SWITCH. ELT WOULD PUT OUT SIGNAL WHEN SWITCHED ON MANUALLY. 1 H 7 1 3O 3A17 1996080200209 19960802 00209 EA 1996 8 2 96ZZZX3763 2 19960705 G 8520 CRANKCASE CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA RT CASE NR 1 CYL CRACKED B DPOD K NONE O OTHER IN INSP/MAINT 1 NM 07 181SP 299 17268171 RL101576 RIGHT CRANKCASE CRACKED BELOW NR 1 CYLINDER BASE. CRACK WAS APPROXIMATELY 6 INCHES LONG. CASE WAS NOT REPAIRABLE. 1 H 7 1 3O 3 O NT 3A12 E274 1996080200210 19960802 00210 CE 1996 8 2 96ZZZX3764 1 19960316 G 3230 20410306 SHELL ASSY CESSNA 172 172RG 2072438 CE RT/LT MLG DETERIORATED D K NONE O OTHER IN INSP/MAINT 1 GL 09 1989Q 3799 177RG0389 DURING INSPECTION AND GEAR RETRACTION TEST, FOUND MLG TO HAVE EXCESSIVE FREE PLAY WHEN DOWN AND LOCKED. UPON INVESTIGA TION, FOUND MLG DOWNLOCK LATCHES WOULD NOT HOLD LANDING GEAR LEGS LATCHED DUE TO EXCESSIVE CLEARANCE BETWEEN LATCH AND P IN. THE SHELL ASSYS WERE FOUND WORN AND THE SHELL INSERT WAS MISSING FROM BOTH RIGHT AND LEFT SHELLS. AFTER INSTALLATI ON OF NEW SHELLS AND RIGGING OF MLG, SYSTEM WORKED OK. SUBMITTER STATES THIS CONDITION COULD HAVE CAUSED COLLAPSE OF TH E MLG AND INJURY. 1 H 7 1 3O 3A17 1996080200462 19960802 00462 SO 1996 8 2 96ZZZX3766 2 19960713 G 8530 627335D13B NOZZLE CESSNA 210 210L 2073448 CE CONT O520 IO520L 17032 SO FUEL INJ THREADS STRIPPED D K NONE O OTHER IN INSP/MAINT 1 SO 15 2013S 21060981 294685R WHEN REMOVING FUEL INJECTOR NOZZLE FOR CLEANING AT FIRST 91-HOUR TSMOH, FACTORY REMANUFACTURE, NOZZLE CAME OUT OF CYLIND ER HEAD WITH ALUMINUM, STRIPPED THREADS IN CLYINDER HEAD. 1 H 7 1 3O 3 O 3A21 E5CE 1996080200463 19960802 00463 CE 1996 8 2 96ZZZX3767 1 19960710 G 2823 45920036 FUEL SELECTOR BEECH 35 V35 1151538 CE RT TANK FEED O-RING DEFECTIVE G K NONE O OTHER IN INSP/MAINT 1 EA 17 2011W EM3065 D7989 FUEL SELECTOR O-RING FOR THE RIGHT TANK FEED WAS RAISED BETWEEN THE SELECTOR BODY AND PLATE ALLOWING CONTINUOUS FEED OF FUEL FROM THE RIGHT TANK. THE FUEL SELECTOR WAS NOT DETERMINED TO BE A FACTOR IN THIS ACCIDENT. 1 L 7 1 3O 3A15 1996080200464 19960802 00464 1996 8 2 96ZZZX3768 4 19960712 G 2562 7J4193 ELT LEIGH SHARC7 CESSNA 210 210 2073402 CE G SWITCH MALFUNCTION D A K NONE O OTHER IN INSP/MAINT 1 NM 01 210AK 301604 21061627 CESSNA PART NR C589510-0290. MANUFACTURED TO TSO-C91, WOULD NOT PASS G-SWITCH OPERATIONAL CHECK PER FAR 91.207(D) EVEN AFTER SLAMMING ELT INTO GROUND IN DIRECTION OF FLIGHT. ELT WOULD PUT OUT SIGNAL WHEN MANUALLY SWITCHED TO ON. 1 H 7 1 3O RT 3A21 1996080200465 19960802 00465 SO 1996 8 2 96ZZZX3769 1 19960710 G 3211 6704213 FITTING PIPER PA44 PA44180 7104402 SO AFT TRUNNION CRACKED B S YXUR K NONE O OTHER IN INSP/MAINT 1 WP 07 3062H 578 447995165 PIPER CASTING NR 67043-3 FACF B, CRACKED HORIZONTALLY AT TOP BEARING BOSS. SUSPECT CAUSE, HARD LANDINGS OR FATIGUED. I NSPECTED OTHER STRUCTURES FOR CRACKS. NONE NOTED AT THIS TIME. 1 L 7 2 3O A19S0 1996080200466 19960802 00466 CE 1996 8 2 96ZZZX3770 1 19960601 G 3213 0441140 AXLE CESSNA 140 140 2071602 CE RT MLG BROKE G A O OTHER O OTHER TO TAKEOFF 1 CE 09 3609V 3425 14877 DURING TAKEOFF FROM PRIVATE TURF STRIP, RT AXLE BROKE AT JUNCTURE OF TUBE AND MOUNTING FLANGE. RT WHEEL TIRE BRAKE ASSY DEPARTED AIRCRAFT. AIRCRAFT GROUND LOOPED CAUSING SUBSTANTIAL DAMAGE TO AIRCRAFT. INSPECTION OF AXLE INDICATED A CRAC K APPROXIMATELY 150 DEGREES OF CIRCUMFERENCE OF TUBE. CRACKED AREA DISCOLORED INDICATING IN EXISTENCE FOR SOME TIME AND WAS LOCATED ON BOTTOM IN THIS INSTALLATION. 1 H 7 1 3O NC A768 1996080200467 19960802 00467 SW 1996 8 2 96ZZZX3771 1 19960626 G 2820 FUEL LINE SLINDS 100 100180 0140208 SW DOOR POST PIERCED D K NONE K FLUID LOSS IN INSP/MAINT 1 NM 09 4078X 5178 DURING ANNUAL, A WET SPOT WAS NOTED ON LT DOOR NEXT TO REAR POST. ON INVESTIGATION, FOUND IT WAS FUEL FROM A PIN HOLE M ADE WHEN INSTALLING A RUG WITH STAPLING GUN. THE STAPLE WENT THROUGH THE FLOOR (PLYWOOD) INTO FUEL LINE. IT TOOK SEVER AL YEARS FOR STAPLE TO LOOSEN ENOUGH TO LEAK FUEL. SUBMITTER STATED STAPLING GUNS SHOULD NOT BE USED FOR INSTALLING RUG S. THOSE AIRCRAFT HAVING PLYWOOD FLOORS SHOULD BE CHECKED FOR THIS CONDITION. 1 H 7 1 3O 1A21 1996080200468 19960802 00468 CE 1996 8 2 96ZZZX3772 1 19960503 G 2821 075600514 STRAINER CESSNA 210 210N 2073453 CE FUEL SYSTEM CORRODED D K NONE O OTHER IN INSP/MAINT 1 GL 11 4636U 2400 21064794 FUEL STRAINER ASSEMBLY FOUND TO HAVE SEVERE CORROSION ON THE INLET TUBE WHERE THE FILTER TOUCHES IT. THIS CAUSED HOLES IN THE TUBE AND ALLOWED UNFILTERED FUEL TO THE ENGINE. SUBMITTER STATED SAME PART NUMBER IS USED ON ALL 82-84 C210'S. S USPECT DISSIMILAR METALS. 1 H 7 1 3O 3A21 1996080200469 19960802 00469 CE 1996 8 2 96ZZZX3773 1 19960711 G 5711 CARRY-THROUGH BEECH 33 F33A 1151425 CE WING CRACKED D K NONE O OTHER IN INSP/MAINT 1 WP 07 5544P 7592 CE1336 INSPECTION FOUND CRACKS IN CARRY-THROUGH STRUCTURE. AD 95-04-03 NOT VALID BY SERIAL NUMBER. 1 L 7 1 3O 3A15 1996080200470 19960802 00470 SO 1996 8 2 96ZZZX3774 2 19960711 G 8530 635448CP CYLINDER CESSNA 207 T207A 2073614 CE CONT O520 TSIO520H 17040 SO NR 3 SEPARATED D K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 WP 07 6308H 1018 20700476 506728 PILOT REPORTED ROUGH ENGINE AND LARGE RPM DROP ON MAG CHECK. INSPECTION FOUND NR 3 CYLINDER CRACKED. WHEN CYLINDER REM OVED, IT WAS DISCOVERED THE HEAD WAS COMPLETELY SEPARATED. BOTTOM SPARK PLUG WAS FOULED. 1 H 7 1 3O 3 O A16CE E8CE 1996080200471 19960802 00471 CE 1996 8 2 96ZZZX3775 1 19960705 G 5753 0529018 SUPPORT ASSY 05239011 CESSNA 172 172A 2072404 CE FLAP LT OTBD WORN D K NONE O OTHER IN INSP/MAINT 1 SW 01 7558T 4415 47158 DURING INSPECTION OF FLAPS PER CESSNA SEB 95-3, FOUND ALL FLAP SUPPORTS HEAVILY WORN AND SCORED. INSTALLED FLAP SUPPORT KIT SK180-44. NEW SUPPORTS ARE HEAVIER AND FLANGED FOR STIFFNESS. SUBMITTER RECOMMENDS THIS SB BECOME AN AD. 1 H 7 1 3O 3A12 1996080200472 19960802 00472 SO 1996 8 2 96ZZZX3776 1 19960624 G 3243 214351 CYLINDER ASSY BFGOODRICH PIPER PA31T PA31T2 7103127 SO LT MLG BRAKE SPLIT B JGVR K NONE O OTHER IN INSP/MAINT 1 CE 09 774KV 3487 377 31T8166057 DURING BRAKE TESTING AFTER OVERHAUL, HYDRAULIC PRESSURE EQUAL TO 150 PSI WAS APPLIED TO BRAKE CYLINDER LEAK CHECK. THE ACTUAL TEST PRESSURE IS 180 PSI PER MANUAL. AT 150 PSI, THE BRAKE CYLINDER ASSY SPLIT FROM ONE END OF BOLT HOLE APPROXI MATELY ONE-HALF WAY ACROSS CYLINDER ASSY. THIS PART APPEARS TO BE ORIGINAL PART ON A/C SINCE NEW. 1 L 7 2 3T RT A8EA 1996080200473 19960802 00473 SO 1996 8 2 96ZZZX3777 1 19960204 G 3230 837683D SEQUENCE VALVE PIPER PA46 PA46350P SO NLG LEAKING D K NONE K FLUID LOSS IN INSP/MAINT 1 GL 09 9167Q 354 215 4622031 DURING INVESTIGATION OF LANDING GEAR PROBLEMS, THE HYDRAULIC RESERVOIR WAS FOUND NEARLY EMPTY. FILLED RESERVOIR AND CHE CKED FOR LEAKS. FOUND NLG DOOR SEQUENCE VALVE LEAKING PAST THE PLUNGER. ALSO, FOUND SEVERAL HYDRAULIC LINES LEAKING AT MLG ACTUATORS, AND TWO LINES AT SEQUENCE VALVE. 1 L 7 1 3O RT A25SO 1996080200474 19960802 00474 CE 1996 8 2 96ZZZX3778 1 19960711 G 5711 CARRY-THROUGH BEECH 33 F33A 1151425 CE WING CRACKED D K NONE O OTHER IN INSP/MAINT 1 WP 07 8268T 5390 CE1547 INSPECTION FOUND CRACKS IN CARRY-THROUGH STRUCTURE. AD 95-04-03 NOT VALID BY SERIAL NUMBER. 1 L 7 1 3O 3A15 1996080200475 19960802 00475 1996 8 2 96ZZZX3779 4 19960626 G 2562 DMELT61 ELT MAULE M4 M4220C 5460114 SO G-SWITCH MALFUNCTION D A K NONE L NO TEST IN INSP/MAINT 1 NM 11 986R 4322 2081C REMOVED DORNE AND MARGOLIN EMERGENCY LOCATOR TRANSMITTER FOR ANNUAL INSPECTION/FUNCTION CHECK AND BATTERY INSPECTION. F OUND THAT FUNCTION CHECK WOULD NOT ACTIVATE ELT. ELT WOULD WORK IN 'ON' POSITION, BUT NOT IN 'ARM'. RETURN TO D AND F OR REPAIRS. INV NR 158190. 1 H 7 1 3O 3A23 1996080200476 19960802 00476 GL 1996 8 2 96ZZZX3780 1 19960622 G 2820 MILH6000 FUEL LINE AMTR KITFOX KITFOX 05613LZ GL ENGINE FUEL DETERIORATED D K NONE R PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 EA 21 90869 98891 S94070040 DURING RUN-UP TEST PRIOR TO TEST FLIGHT, ENGINE DEMONSTRATED SYMPTOMS OF FUEL STARVATION. REMOVED FUEL LINE AT SUPPLY O F FUEL FILTER. SIGNIFICANT AMOUNTS OF BLACKENED FUEL, RUBBER GLOBULES POURED OUT, FILTER FOULED. UNABLE TO BLOW AIR TH ROUGH FUEL LINE, USING 93 OCTANE AMECO WHITE GAS. (NO OXYIDIZATION ADDITIVE, BUT NOT SURE ABOUT THIS.) REMOVED ALL FUE L LINES IN AIRCRAFT AND SLIT OPEN. FOUND ONE TO HAVE DETERIORATED INSIDE. FURTHER TESTING OF FUEL LINE IN JAR OF GAS S HOWS SIGNIFICANT AND RAPID DETERIORATION. 1 H 7 1 3I NC EXPA1H71 1996080200477 19960802 00477 1996 8 2 96ZZZX3781 4 19960712 G 2562 7JH193 ELT LEIGH SHARC7 CESSNA 140 140A 2071604 CE G-SWITCH MALFUNCTION D A K NONE O OTHER IN INSP/MAINT 1 NM 01 9672A 15393 EMERGENCY LOCATOR TRANSMITTER INSTALLED AS AFTER-MARKET EQUIPMENT, WOULD NOT PASS G-SWITCH OPERATIONAL CHECK PER FAR 91. 207(D). LIGHT OR EXCESSIVE FORCE IN DIRECTION OF FLIGHT WOULD NOT SET OFF ELT. NOTE: ELT WOULD PUT OUT SIGNAL WHEN MA NUALLY SET TO 'ON' POSITION. 1 H 7 1 3O 5A2 1996080200478 19960802 00478 SW 1996 8 2 96ZZZX3782 1 19960701 G 5530 TAILPOST BBAVIA 8 8GCBC 1220803 SW TAILSPRING PAD CRACKED C K NONE O OTHER IN INSP/MAINT 1 NM 03 88352 9630 11674 TAILPOST DISCOVERED TO BE CRACKED AROUND THE CIRCUMFERENCE JUST ABOVE THE TAILSPRING PAD. SUBMITTER SUGGESTS CAUSE FOR CRACK DUE TO GROUND HANDLING OVER THE YEARS AND HIGH TIME ON THE AIRFRAME. THIS POINT IS STRESSED WHEN SWIVELLING THE TAILWHEEL DURING GROUND HANDLING. 1 H 7 1 3O A21CE 1996080200479 19960802 00479 1996 8 2 96ZZZX3783 1 19960715 G 8120 633358 CLAMP 6005739000 ENGINE TURBO NOT SAFTIED B APCR K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 01 ZE004706 CLAMP NOT SAFETY WIRED PER PIPER SB 884. THIS CLAMP SECURES THE COMPRESSOR TO THE TURBINE. 1996080200480 19960802 00480 SO 1996 8 2 96ZZZX3784 1 19960711 G 2820 6390115 HOSE ASSY PIPER PA28 PA28150 7102804 SO FUEL TANK DETERIORATED D A K NONE O OTHER IN INSP/MAINT 1 EA 05 5909W 3500 283032 FLEXIBLE FUEL LINE TO FUEL TANK IS HIGHLY CORRODED AND BRITTLE. BROKE IN HALF UPON TANK REMOVAL. HOST ASSY WAS ORIGINA L, DATE - 1965. 1 L 7 1 3O 2A13 1996080800036 19960808 00036 EU 1996 8 8 96ZZZX3785 1 19960514 G 3230 Z00N7070110709 COMPENSATOR SOCATA TB20 TB20TRINIDAD 8680695 EU NLG EXTEND FAILED G A O OTHER O OTHER NR NOT REPORTED 1 GL 11 20FF 1959 1032 ONE OF THE TWO NOSE GEAR EXTEND COMPENSATORS INSTALLED ON THIS AIRCRAFT LOST ITS AIR CHARGE. THE NOSE GEAR WOULD NOT EX TEND PROPERLY DURING AN EMERGENCY GEAR EXTENSION RESULTING FROM A FAILURE DURING NORMAL EXTENSION. THE AIRCRAFT HAD JUS T RECEIVED AN ANNUAL INSPECTION, BUT THE COMPENSATORS HAD NOT BEEN CHECKED. SUBMITTER STATED THE CURRENT MANUFACTURER'S MM PROCEDURES FOR EXTENSION/RETRACTION DID NOT SPECIFY THE NEED TO CHECK THEM, THOUGH IT WAS ON THEIR CHECKLIST, WHICH HAD NOT BEEN USED. 1 L 7 1 3O RT A51EU 1996080800037 19960808 00037 CE 1996 8 8 96ZZZX3786 1 19960616 G 3234 363800501 SWITCH BEECH 58 58 1152740 CE GEAR LEVER CAM FAILED G A O OTHER O OTHER TO TAKEOFF 1 EA 25 3174B 1341 TH1724 DURING TAKEOFF ROLL AT ROTATION SPEED, AIRCRAFT LANDING GEARS RETRACTED WHILE THE GEAR LEVER WAS IN THE 'DOWN' POSITION. PROPELLER TIPS STRUCK PAVEMENT AND PILOT RETARDED THROTTLES CAUSING THE AIRCRAFT TO SKID ON ITS LOWER FUSELAGE UNTIL I T CAME TO A STOP AT THE END OF THE RUNWAY. RECOMMEND THAT CAM ASSY ON GEAR LEVER SHAFT BE DRILLED AND A ROLL PIN INSTAL LED TO PREVENT CAM FROM COMING LOOSE ON SHAFT. IN THIS CASE, THE CAM CAME LOOSE AND ALLOWED THE MICROSWITCH TO STAY IN THE 'UP' POSITION ALLOWING GEARS TO RETRACT. 1 L 7 2 3O 3A16 1996080800038 19960808 00038 CE 1996 8 8 96ZZZX3787 1 19960625 G 5741 08113508 FITTING CESSNA 402 402C 207590R CE RT WING CORRODED H A K NONE O OTHER IN INSP/MAINT 1 NM 03 821AN 19463 402C0257 OWNER/OPERATOR FOUND RT WING WOULD CREAK AND GROAN WHEN WING WAS FLEXED. INSPECTION REVEALED THE LOWER FORWARD MAIN SPA R ATTACH FITTINGS WERE WORN AROUND THE ATTACH BOLT. THE BOLT WAS FOUND TO BE IN GOOD CONDITION. AFTER REMOVAL OF THE F ITTINGS, FOUND THE BOLT HOSE SLIGHTLY ELONGATED AND CORROSION WITH PITTING ON THE MATING SURFACES OF THE WING FITTINGS. SUBMITTER STATED AD 79-10-15/ME79-16AR4 AND CONTINUED AIRWORTHINESS 57-10-01 TOUCH ON THE SUBJECT OF SPAR FITTINGS, HOW EVER, NONE OF THE AFOREMENTIONED APPLY TO THE 402 'C' SERIES OF AIRCRAFT. 1 L 7 2 3O A7CE 1996080800039 19960808 00039 CE 1996 8 8 96ZZZX3788 1 19960625 G 5741 082255020 FITTING CESSNA 402 402C 207590R CE RT WING CORRODED H K NONE O OTHER IN INSP/MAINT 1 NM 03 821AN 19463 402C0257 OWNER/OPERATOR FOUND RT WING WOULD CREAK AND GROAN WHEN WING WAS FLEXED. INSPECTION REVEALED THE LOWER FORWARD MAIN SPA R ATTACH FITTINGS WERE WORN AROUND THE ATTACH BOLT. THE BOLT WAS FOUND TO BE IN GOOD CONDITION. AFTER REMOVAL OF THE F ITTINGS, FOUND THE BOLT HOSE SLIGHTLY ELONGATED AND CORROSION WITH PITTING ON THE MATING SURFACES OF THE WING FITTINGS. SUBMITTER STATED AD 79-10-15/ME79-16AR4 AND CONTINUED AIRWORTHINESS 57-10-01 TOUCH ON THE SUBJECT OF SPAR FITTINGS, HOW EVER, NONE OF THE AFOREMENTIONED APPLY TO THE 402 'C' SERIES OF AIRCRAFT. 1 L 7 2 3O A7CE 1996080800040 19960808 00040 CE 1996 8 8 96ZZZX3789 1 19960625 G 5741 082255026 FITTING CESSNA 402 402C 207590R CE RT WING CORRODED H K NONE O OTHER IN INSP/MAINT 1 NM 03 821AN 19463 402C0257 OWNER/OPERATOR FOUND RT WING WOULD CREAK AND GROAN WHEN WING WAS FLEXED. INSPECTION REVEALED THE LOWER FORWARD MAIN SPA R ATTACH FITTINGS WERE WORN AROUND THE ATTACH BOLT. THE BOLT WAS FOUND TO BE IN GOOD CONDITION. AFTER REMOVAL OF THE F ITTINGS, FOUND THE BOLT HOSE SLIGHTLY ELONGATED AND CORROSION WITH PITTING ON THE MATING SURFACES OF THE WING FITTINGS. SUBMITTER STATED AD 79-10-15/ME79-16AR4 AND CONTINUED AIRWORTHINESS 57-10-01 TOUCH ON THE SUBJECT OF SPAR FITTINGS, HOW EVER, NONE OF THE AFOREMENTIONED APPLY TO THE 402 'C' SERIES OF AIRCRAFT. 1 L 7 2 3O A7CE 1996080800041 19960808 00041 SO 1996 8 8 96ZZZX3790 1 19960715 G 3230 025702 FITTING PIPER PA32 PA32R301 7103218 SO NLG DRAG LINK CRACKED D S A K NONE W INADEQUATE Q C IN INSP/MAINT 1 EA 13 3327P 3213013 WHILE INSPECTING THE NOSE GEAR ASSY, FOUND THE SUPPORT ASSY THAT WAS INSTALLED IN PIPER KIT P/N 766-253 WAS CRACKED. TH IS KIT WAS INSTALLED TO C/W AD 93-05-10 AND SB 955. WHEN THE NOSE GEAR IS FULLY RETRACTED, THE DRAG LINK INTERFERES WIT H FITTING (P/N 02570-2) THAT WAS ALSO INSTALLED WITH THE KIT. THE FITTING DID NOT HAVE THE AREAS MILLED OUT. SUBMITTER STATED THIS IS THE SECOND TIME THE INCORRECT PARTS INSTALLED CAME WITH THE KIT FROM PIPER. AFTER CONTACTING PIPER ON T HE FIRST KIT, WAS TOLD SOME OF THE FIRST KITS DELIVERED MAY HAVE HAD A FITTING THAT WAS INCORRECTLY MILLED. 1 L 7 1 3O A3SO 1996080800042 19960808 00042 SO 1996 8 8 96ZZZX3791 1 19960618 G 5553 2074908 ANGLE PIPER PA24 PA24250 7102404 SO VERT STAB ATTACH CRACKED D S K NONE O OTHER IN INSP/MAINT 1 WP 01 6387P 3930 241497 DURING AN ANNUAL INSPECTION, A 0.300 INCH CRACK WAS FOUND IN THE FORWARD ATTACH SPAR (FUSELAGE) ANGLE AFT OF THE CHANNEL (P/N 20749-0). PIPER AD 75-12-06 REQUIRES INSPECTION OF THE BEND RELIEF HOLE IN THE CHANNEL AND STRAPS (PN 207 9-5 AND DASH 6). NO CRACKS WERE NOTED IN THESE PARTS. AIRCRAFT HAD NO RECORD OR INDICATIONS OF CRASH DAMAGE/GROUND DAMAGE. P ART REPLACED WITH SERVICEABLE ANGLE. 1 L 7 1 3O 1A15 1996080800043 19960808 00043 1996 8 8 96ZZZX3792 2 19960626 G 7414 M3529 IMPULSE COUPLING SLICK 4374 MAG FAILED G K NONE O OTHER IN INSP/MAINT 1 WP 17 140 93060026 THE FOLLOWING WAS NOTED DURING OVERHAUL OF SUBJECT MAGNETO. THE IMPULSE COUPLING ASSEMBLY HAD EVIDENCE OF FAILURE. THE PAWLS ROLLED OVER AND THE CAM ASSEMBLY CAME APART. 1996080800044 19960808 00044 1996 8 8 96ZZZX3793 2 19960626 G 7414 M3827 ROTOR GEAR SLICK 4373 MAG LOOSE G K NONE O OTHER IN INSP/MAINT 1 WP 17 140 93060026 THE FOLLOWING WAS NOTED DURING OVERHAUL OF SUBJECT MAGNETO. THE ROTOR SHAFT GEAR CAME LOOSE AND TRAVELLED ON THE SHAFT UNTIL CONTACT WAS MADE ON THE BLOCK. 1996080800045 19960808 00045 1996 8 8 96ZZZX3794 2 19960626 G 7414 M3485 BEARING CAP SLICK 4373 MAGNETO LOOSE G K NONE O OTHER IN INSP/MAINT 1 WP 17 140 93060026 THE FOLLOWING PROBLEM WAS NOTED DURING OVERHAUL OF SUBJECT MAGNETO. THE BEARING CAP ASSEMBLY WAS LOOSE IN THE HOUSING. 1996080800046 19960808 00046 SO 1996 8 8 96ZZZX3795 2 19960712 G 8530 653445 CYLINDER BEECH 58 58 1152740 CE CONT O520 IO520CB 17032 SO ENGINE CRACKED B LNCR K NONE O OTHER IN INSP/MAINT 1 SW 05 3695V 1315 TH1183 282448R ON INSPECTION, THE CYLINDER WAS FOUND TO HAVE A CRACK FROM THE SPARK PLUG BOSS TO THE FUEL NOZZLE. THE CRACK TRAVELS AL ONG THE CASTING MARK ON THE CYLINDER. THE CYLINDER WAS STILL HOLDING 78/80. SUBMITTER BELIEVES THAT THIS IS A MANUFACT URING PROBLEM. 1 L 7 2 3O 3 O 3A16 E5CE 1996080800047 19960808 00047 SO 1996 8 8 96ZZZX3796 1 19960710 G 5700 LIFT STRUT PIPER PA12 PA12 7101202 SO WING RT REAR CORRODED B CO4R K NONE O OTHER IN INSP/MAINT 1 AL 03 3155M 121857 INSPECTION FOUND RIGHT REAR STRUT WITH LARGE AMOUNT OF CORROSION, LOWER 15 INCHES OF STRUT. DENSITY CHECK: COMPARITOR SHIM = 3.69 H.D., CORROSION = 4.23 H.D. 1 H 7 1 3O A780 1996080800048 19960808 00048 NE 1996 8 8 96ZZZX3797 2 19960719 G 7322 PD12FS CARBURETOR BENDIX DOUG DC3 DC3 3021401 WP PWA R1830 R183090D 52020 NE ENGINE MALFUNCTION D K NONE O OTHER IN INSP/MAINT 1 SW 17 32MS 740817A 4978 CP350411 ENGINE WILL NOT IDLE, DIES/RESTARTS OK. WILL NOT TAKE THROTTLE. WANTS TO BACKFIRE THROUGH CARBURETOR. REMOVED CARBURE TOR. REPLACED WITH OVERHAULED UNIT. 2 L 7 2 4R 4 R A669 5E4 1996080800049 19960808 00049 EA 1996 8 8 96ZZZX3798 2 19960624 G 8520 11B200511SL CRANKCASE BEECH 23 A2324 1151226 CE LYC O360 IO360A1A 41514 EA NR 1 CYL AFT CRACKED D O OTHER E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CR CRUISE 1 WP 17 3675Q 773 313296 MA266 L549451A ENGINE RUN ROUGH DURING FLIGHT. NR 1 CYLINDER LOOSE, CRANKCASE FOUND CRACKED BETWEEN BOTTOM STUD HOLES. 1 L 7 1 3O 3 O A1CE 1E10 1996080800050 19960808 00050 NE 1996 8 8 96ZZZX3799 2 19960719 G 8530 333968 VALVE BEECH 18 E18S 1151006 CE PWA R985 R985AN14B 52008 NE NR 8 EXHAUST FAILED D O OTHER E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CR CRUISE 1 NM 03 5611D 600 BA316 22664 IN-FLIGHT FAILURE OF NR 8 CYLINDER EXHAUST VALVE. VALVE HEAD SNAPPED OFF. SUSPECT CAUSE OVERHEATED VALVE DUE TO REDUCE D LEAD IN FUEL. 1 L 7 2 3R 3 R A765 5E1 1996012600456 19960126 00456 CE 1996 1 26 96ZZZX380 1 19960109 G 2440 1093610165 CIRCUIT BOARD BEECH 1900 1900C 1154161 CE EXTERNAL POWER FAILED D K NONE O OTHER IN INSP/MAINT 1 NE 05 550CJ UC50 EXTERNAL POWER SYSTEM REPORTED INOPERATIVE. FOUND PC BOARD SOAKED WITH DEICE FLUID AND RESISTOR SHORTED. INSTALLED REP AIRED PC BOARD. EXTERNAL POWER LIGHT INOPERATIVE. TROUBLESHOT AND FOUND WIRE BROKEN OFF TERMINAL ON NEW BOARD AND ALL OTHER WIRES CORRODED AT TERMINAL. ALSO, FOUND WIRES FROM EXTERNAL PLUG TO PC BOARD CHAFED THROUGH AT LIGHTING HOLE. SP IRAL WRAP STRETCHED AND DID NOT DO ITS JOB. REPAIRED AND RETURNED TO SERVICE. 2 L 7 2 4T RT A24CE 1996080800051 19960808 00051 GL 1996 8 8 96ZZZX3800 3 19960702 G 6114 PROPELLER PIPER PA23 PA23250 7102308 SO HARTZL HCE2Y HCE2YR2 GL DOME REQUIRED SERVICE E E ENGINE SHUTDOWN J WARNING INDICATION CR CRUISE 1 GL 03 54808 3359 277554106 BP1998 ON 7-2-96, PILOT SHUT DOWN LEFT ENGINE IN-FLIGHT TO PREVENT AN OVERSPEED CONDITION. ENGINE WAS INSPECTED IAW LYCOMING S B 369H, PART I, NOTE 1. NO DEFECTS NOTED. SERVICED PROPELLER DOME, AIRCRAFT WAS TEST FLOWN AND RETURNED TO SERVICE. 1 L 7 2 3O 1A10 5 C P9EA 1996080800052 19960808 00052 CE 1996 8 8 96ZZZX3801 1 19960429 G 2822 41400039 PUMP DUKES BEECH 35 S35 1151532 CE FUEL SYSTEM PORT PLUGGED D K NONE O OTHER IN INSP/MAINT 1 EA 07 8992M 3536 145 D7315 FUEL PUMP REPLACED TO C/W BEECH SB N2526, REV II. WORKING WHEN REMOVED. FOUND OVERFLOW/RELIEF PORT PLUGGED WITH MATERI AL THAT APPEARS TO BE RUST. 1 L 7 1 3O 3A15 1996080800053 19960808 00053 CE 1996 8 8 96ZZZX3802 1 19960709 G 2430 DOFF10304B RECTIFIER ASSY FORD DOFF10300B CESSNA 210 210L 2073448 CE GROUND STUD FAILED B KC2R A UNSCHED LANDING H ELECT. POWER LOSS-50 PC CR CRUISE 1 GL 03 59210 100 A92243 21060161 THE PILOT EXPERIENCED AN ALTERNATOR FAILURE DURING AN IFR FLIGHT. A SUCCESSFUL EMERGENCY LANDING WAS MADE. AN INVESTIG ATION AS TO WHY THE ALTERNATOR FAILED REVEALED THAT ONE NEGATIVE RECTIFIER GROUND STUD HAD FAILED AND THE OTHER GROUND S TUD WAS LOOSE. THIS CONDITION CAUSED THE RECTIFIER ASSEMBLY TO LOSE ITS CIRCUIT TO GROUND RESULTING IN ELECTRICAL ARCIN G DAMAGE TO THE RECTIFIER AND FAILURE OF THE ALTERNATOR. SUBMITTER STATED THIS FAILURE COULD HAVE BEEN PREVENTED BY PRO PERLY TORQUING STUD HARDWARE AND FREQUENT INSPECTIONS. 1 H 7 1 3O 3A21 1996080800054 19960808 00054 NM 1996 8 8 96ZZZX3803 1 19960701 G 5541 41523004 SPAR UNIVAR 415 415E 0420308 NM RUDDER CRACKED H K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 13 94841 4914 PURCHASED NEW SPAR FOR RUDDER FROM UNIVAIR. FOUND CRACKS DURING PREP FOR INSTALLATION. INFORMED UNIVAIR AND REQUESTED REPLACEMENT. RECEIVED A TOTAL OF THREE CRACKED SPARS AND HAD THE FAA INVOLVED BEFORE RECEIVING A GOOD PART. HAD TO SEN D THAT BACK AND REQUEST A 'BLANK' IN ORDER TO GET ACCEPTABLE EDGE DISTANCES ON ALL HOLES. 1 L 7 1 3O A787 1996080800055 19960808 00055 SO 1996 8 8 96ZZZX3804 1 19960625 G 3246 WHEEL PARKERHANFIN GULSTM AA1 AA1C 0631214 SO MLG WRONG BOLTS D K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 05 9645U 1930 AA1C0083 OWNER/PILOT INSTALLED NEW TIRES AS PREVENTATIVE MAINTENANCE. WHILE INSTALLING NEW TIRES, HE NOTICED THE WHEEL ASSY THRO UGH-BOLTS WERE BADLY RUSTED . HE WENT TO LOCAL HARDWARE STORE, PURCHASED COMMON STEEL/GALVANIZED PLATED BOLTS AND REPLA CED ORIGINAL 'AN' CADMIUM PLATED BOLTS. DURING SUBSEQUENT ANNUAL INSPECTION, FOUND THESE BOLTS AND REPLACED THEM WITH ' AN' BOLTS OF CORRECT SIZE. THE ZINC PLATED BOLTS WERE BADLY CORRODED AND THE WHEEL HALVES WERE ALSO CORRODED. CLEANED AND TREATED CORROSION. 1 L 7 1 3O A11EA 1996080800056 19960808 00056 CE 1996 8 8 96ZZZX3805 1 19960705 G 2430 S15801A CONTACTOR CESSNA 182 R182 2072734 CE BATTERY FAILED B EVCR A UNSCHED LANDING H ELECT. POWER LOSS-50 PC CR CRUISE 1 CE 03 3132C 2263 R18200238 DURING NORMAL FLIGHT, VFR CONDITION, ALL ELECTRICAL WAS LOST. IMMEDIATELY, AIRCRAFT LANDED WITHOUT INCIDENT. FURTHER INVESTIGATION SHOWED MAIN BATTERY CONTACTOR FAILED AND SHOWED SIGNS OF BEING HOT. REPLACED CONTACTOR AND SYSTEM OPERATE D NORMALLY. 1 H 7 1 3O RT 3A13 1996080800057 19960808 00057 SO 1996 8 8 96ZZZX3806 1 19960619 G 2910 FITTING PIPER PA31 PA31 7103102 SO RT MLG DOOR ACT BROKE D A K NONE K FLUID LOSS IN INSP/MAINT 1 NM 08 2336V 31135 INSTALLED 'AERO CRAFTERS' CABIN HEATER MOD STC NR SA240CH. AFTER 42 FLIGHT HOURS, THE RIGHT GEAR DOOR CLOSED. HYDRAULI C FITTING BROKE AT ACTUATOR. FOUND THE SKEET HOSE INSTALLED IN FORWARD PART OF WHEELWELL INTERFERED WITH FREE MOVEMENT OF HYDRAULIC HOSE CAUSING STRESS TO FITTING. USED 90-DEGREE FITTING AND SHORTER HOSE TO CORRECT PROBLEM. HEATER KIT IN STALLED TO RIGHT ENGINE ONLY. RECOMMEND SPECIAL NOTICE BE GIVEN TO HOSE REACTION AFTER KIT INSTALLATION. 1 L 7 2 3O A20SO 1996080800058 19960808 00058 1996 8 8 96ZZZX3807 4 19960712 G 2562 AK450 ELT AMERIKING PIPER PA31T PA31T1 7103126 SO G-SWITCH FAILED D L A K NONE O OTHER IN INSP/MAINT 1 NE 05 149CC 100 4501340 31T7904036 G-SWITCH FAILS TO ACTIVATE UNIT IN THE 'ARMED' POSITION. IF UNIT IS TURNED 'ON' THE LIGHT ON THE ELT SHOWS THE UNIT IS TRANSMITTING, BUT, IN FACT, THE UNIT IS NOT TRANSMITTING ON 121.5 MHZ. 1 L 7 2 3T A8EA 1996080800059 19960808 00059 EA 1996 8 8 96ZZZX3808 2 19960510 G 8500 ENGINE SLNSBY T67 T67M260 8323006 EU LYC O540 AEIO540D4A5 41532 EA POWER SECTION STOPPAGE C O OTHER Y ENGINE STOPPAGE AB AEROBATIC 1 SW 17 3037C 2134 L2524848 ENGINE STOPPED DURING AEROBATIC MANEUVER. SUCCESSFUL RESTART AND RETURN TO BASE WITHOUT FURTHER INCIDENT. ALL INDICATI ONS NORMAL. PRELIMINARY ASSESSMENT IS THAT AIRCRAFT WAS PUT IN CONDITION KNOWN TO INDUCE ENGINE STOPPAGE. 1 L 7 1 3O 3 O NT A73EU 1E4 1996080800060 19960808 00060 EU 1996 8 8 96ZZZX3809 1 19960425 G 7931 SENDER SLNSBY T67 T67M260 8323006 EU LYC O540 AEIO540D4A5 41532 EA ENG OIL PRESS FAILED C A UNSCHED LANDING J WARNING INDICATION NR NOT REPORTED 1 SW 17 3037X 2137 L2557048A PILOT MADE AN EMERGENCY LANDING AT A SMALL AIRSTRIP. THE PILOT REPORTED LOW OIL PRESSURE AND RAISING OIL TEMPERATURE. A DOSS MAINTENANCE TEAM WAS SENT TO THE AIRSTRIP TO RECOVER THE AIRCRAFT. THE MAINTENANCE PERSONNEL REMOVED AND REPLACED THE OIL PRESSURE SENDING UNIT. GROUND RUN WAS ACCOMPLISHED, OPERATION CHECK GOOD. THE AIRCRAFT WAS FLOWN BACK TO HOND O AT APPROXIMATELY 1,500 HOURS, 25 APRIL 1996, WITH NO RETURN FLIGHT PROBLEMS. 1 L 7 1 3O 3 O NT A73EU 1E4 1996080800061 19960808 00061 EA 1996 8 8 96ZZZX3810 2 19960625 G 8500 ENGINE SLNSBY T67 T67M260 8323006 EU LYC O540 AEIO540D4A5 41532 EA POWERPLANT STOPPAGE C O OTHER Y ENGINE STOPPAGE AB AEROBATIC 1 SW 17 3192E 2227 L2257048A ENGINE STOPPED. DURING TRAFFIC PATTERN STALL MANEUVERS WITH THE ENGINE AT APPROXIMATELY IDLE. STARTER WAS ENGAGED FOR A SUCCESSFUL RESTART. DURING LANDING THE ENGINE STALLED AGAIN, NO RESTART WAS ATTEMPTED. AIRCRAFT LANDED WITHOUT INCID ENT. ALL OTHER INDICATIONS WERE NORMAL. NO KNOWN REASON AT THIS TIME. AIRCRAFT IMPOUND, PUT INTO DEPOT STATUS. DOSS AVIATION IS PERFORMING AN ENGINE STOPPAGE CHECK LIST. NO DISCREPANCIES FOUND AT THIS TIME. ENGINE AND AIRFRAME TIME IS 72.0 HOURS. 1 L 7 1 3O 3 O NT A73EU 1E4 1996080800062 19960808 00062 EA 1996 8 8 96ZZZX3811 2 19960515 G 8500 ENGINE SLNSBY T67 T67M260 8323006 EU LYC O540 AEIO540D4A5 41532 EA POWERPLANT STOPPAGE C O OTHER Y ENGINE STOPPAGE AB AEROBATIC 1 SW 17 3193K 2233 L2559748 ENGINE STOPPED AFTER PILOT REDUCED POWER IN SPIN. SUCCESSFUL RESTART AND RETURN TO BASE WITHOUT FURTHER INCIDENT. ALL INDICATIONS NORMAL. USAF CONDUCTING INVESTIGATION. MAINTENANCE IS IN PROCESS OF COMPLETING ENGINE STOPPAGE CHECK LIST. AIRCRAFT HAS 101.9 HOURS. 1 L 7 1 3O 3 O NT A73EU 1E4 1996080800063 19960808 00063 SO 1996 8 8 96ZZZX3812 1 19960701 G 3234 752629 O-RING GARKENYON 8376702 PIPER PA46 PA46310P 7104605 SO GEAR SELECTOR RUPTURED D S O OTHER O OTHER NR NOT REPORTED 1 EU 01 43362 468408025 DURING A CHECK-FLIGHT, THE EMERGENCY GEAR HANDLE WAS PULLED. THE GEAR EXTENDED, BUT THE HYDRAULIC POWER PUMP KEPT, AFTE R RETRACTION, PUMPING AND CYCLING. THE CIRCUIT BREAKER WAS PULLED TO KEEP PUMP/MOTOR FROM OVERHEATING. ON THE GROUND, THE LANDING GEAR RETRACTED, BUT THE PRESSURE WENT DOWN TO 1000-600 PSI. AFTER REPLACING THE VALVE ASSY, THE SAME THING HAPPENED AFTER AN EMERGENCY EXTENSION. WHEN THE VALVE ASSY LANDING GEAR SELECTOR WAS DISASSEMBLED, FOUND THE O-RING RUP TURED. SUBMITTER SUGGESTS TO HAVE THE HOUSING HOLES DEBURRED, A BETTER O-RING, OR EVEN BETTER - A NEW AND BETTER DESIGN . 1 L 7 1 3O A25SO 1996080800064 19960808 00064 NE 1996 8 8 96ZZZX3813 2 19960610 G 8530 CYLINDER SCWZER G164 G164A 3952704 EA PWA R985 R985AN1 52008 NE NR 4 HEAD LEAKAGE D K NONE O OTHER IN INSP/MAINT 1 SO 01 5296 580 24011 OVER LAST 200 HOURS, CYLINDER HEAD SEPARATED ON 3 CYLINDERS IN FLIGHT OR ON TAKEOFF. THE 4TH CYLINDER HAD STAINS AND LE AKAGE AND REMOVED BEFORE FAILURES, BUT WAS NOT BETWEEN NR 2 AND NR 3 FIN PER AD 78-08-07. IT WAS LEAKING BETWEEN TOP ST EEL FIN AND NR 1 ALUMINUM FIN. NONE OF FAILED CYLINDERS SHOWED LEAKAGE PRIOR TO FAILURE. 1 Q 7 1 3R 3 R 1A16 5E1 1996080800065 19960808 00065 1996 8 8 96ZZZX3814 4 19960710 G 2562 4530150 ELT ARTEX G-SWITCH MALFUNCTION D K NONE O OTHER IN INSP/MAINT 1 AL 01 10 56995 AIRCRAFT WAS PARKED ON THE RAMP AT NIGHT AND SOME TIME DURING THE NIGHT THE ELT STARTED TO TRANSMIT. THE FOLLOWING MORN ING, IT WAS RESET AND A NEW BATTERY WAS INSTALLED. TWO DAYS LATER, THE SAME CONDITION WAS EXPERIENCED. THE ELT WAS REP LACED. 1996080800066 19960808 00066 EU 1996 8 8 96ZZZX3815 1 19960718 G 5320 25FC7512 ANGLE BRAERO DH125 HS125700A 4230170 EU MLG WHEEL PAN CRACKED B S LEGR K NONE O OTHER IN INSP/MAINT 1 NE 03 7728 257028 A CRACK WAS FOUND IN ONE FLANGE OF ANGLE P/N 25-FC751-2. THIS ANGLE GOES OVER THE TOP OF THE MAIN WHEEL PAN. THE CRACK IS LOCATED IN AN AREA OF THE ANGLE WHERE ONE OF THE FLANGES IS GREATLY REDUCED IN WIDTH FOR TERMINATION OF SEAT TRACK R AIL. RAYTHEON HAS A REPAIR TO REPLACE THE CRACKED AREA WITH MATERIAL OF THE SAME TYPE AND SIZE AS PRESENTLY INSTALLED. A SUGGESTED REPAIR IS TO REMOVE THE SECTION OF SEAT TRACK IN THE AREA OF THE FLANGE, THUS, ALLOWING THE FLANGE TO MAINT AIN THE FULL FLANGE WIDTH AND STRENGTH THROUGHOUT THIS SECTION. 2 L 7 2 4F A3EU 1996080800067 19960808 00067 NM 1996 8 8 96ZZZX3816 1 19960610 G 5541 B62R0132 SPAR PROPJT 200 200D 0140312 NM RUDDER HINGE CRACKED B A OW2R K NONE O OTHER IN INSP/MAINT 1 GL 23 2956T 2750 329 RUDDER SPAR CRACKED AT TOP HINGE LOCATION. REPLACED SPAR P/N B62013-2, ADDED DOUBLER P/N 62013-23. CRACK WAS .75 INCH LONG FROM RIVET HOLES ON RIGHT SIDE. 1 L 7 1 3O 3A18 1996080800068 19960808 00068 1996 8 8 96ZZZX3817 4 19960628 G 6122 3535035 BETA FORK WOODWARD 8210007F BEECH 200 200BEECH 1152920 CE GOVERNOR SHEARED D K NONE O OTHER IN INSP/MAINT 1 NM 03 1747452 PROPELLER BETA FORK PLUNGER WAS FOUND COMPLETELY SHEARED AT THE PRESSED JOINT WHERE THE FORK AND PLUNGER MEET. SUBMITTE R STATED IF THIS WAS NOT FOUND AND PROPELLER WAS RETORQUED, TO SERVICE IT COULD HAVE CAUSED THE PROPELLER TO NOT RETURN FROM REVERSE. 1 L 7 2 4T A24CE 1996080800069 19960808 00069 EA 1996 8 8 96ZZZX3818 1 19960703 G 2710 272953 PCU LINK CNDAIR CL600 CL6002B19 EA RT AILERON DEFECTIVE B EZ1R K NONE O OTHER IN INSP/MAINT 1 EA 11 5100X 842 700 CREW REPORTED A HIGH PITCH NOISE COMING FROM THE RIGHT AILERON. INVESTIGATION PROVED THE AILERON PCU TO AILERON LINK WA S CHATTERING ON THE AILERON BOLT BUSHING. SPECIFICALLY, THE ANTI-ROTATION TABS OF THE LINK. THE BUSHINGS WERE REPLACED AS WELL AS THE LINK AND ASSOCIATED HARDWARE. HIGH TORQUE VALVES WERE SAID TO BE POSSIBLE CAUSE OF PROBLEM AS STATED BY ENGINEERING IN THE MM. RECOMMENDATION WOULD BE TO RE-EVALUATE TORQUE VALVES AND TOGGLE LINK DESIGN. 2 L 7 2 4F RT A21EA 1996080800070 19960808 00070 NM 1996 8 8 96ZZZX3819 1 19960701 G 5541 B62R0132 SPAR PROPJT 200 200D 0140312 NM RUDDER HINGE CRACKED B OW2R K NONE O OTHER IN INSP/MAINT 1 GL 23 2980T 2560 354 RUDDER SPAR CRACKED AT UPPER HINGE LOCATION. REPLACED SPAR P/N B62013-2, ADDED DOUBLER P/N B62013-23. WORK DONE IAW ME YERS AIRCRAFT DRAWINGS AND PROCEDURES. 1 L 7 1 3O 3A18 1996080800071 19960808 00071 NM 1996 8 8 96ZZZX3820 1 19960710 G 5541 B62R0132 SPAR PROPJT 200 200D 0140312 NM RUDDER HINGE CRACKED B OW2R K NONE O OTHER IN INSP/MAINT 1 GL 23 260M 1600 298 RUDDER SPAR BROKEN AT TOP HINGE LOCATION. REPLACED SPAR P/N B62R013-2, ADDED DOUBLER P/N B62R013-23. THIS DOUBLER ADDI TION WAS FIRST USED OVER 10 YEARS AGO ON A DIFFERENT MEYERS 200 WHICH HAS ACCUMULATED OVER 1,000 HOURS OF TROUBLE-FREE U SAGE. TECUMSEH AIRCRAFT, FORMERLY MEYERS AIRCRAFT. 1 L 7 1 3O 3A18 1996080800072 19960808 00072 1996 8 8 96ZZZX3821 4 19960624 G 2562 ELT1104 ELT ARTEX 4530150 BEECH MU300 400BEECH CE CRACKED B OG5R K NONE O OTHER IN INSP/MAINT 1 GL 21 3196N 595 55916 RK96 DURING ELT SCHEDULED INSPECTION, FOUND BATTERY CASE CRACKED. DISASSEMBLED ELT AND FOUND BOTH BATTERIES AT HEAD OF ELT L EAKING. REPLACED ELT. SUBMITTER STATED THIS IS SECOND OCCURENCE IN THIS AIRCRAFT AND THIRD OCCURRENCE BY THIS OPERATOR . 2 H 7 2 4F RT A16SW 1996080800073 19960808 00073 CE 1996 8 8 96ZZZX3822 1 19960624 G 2436 62581038 CAPACITOR ASSY CESSNA 500 S550 2076607 CE GENERATOR GCU EXPLODED D K NONE O OTHER IN INSP/MAINT 1 GL 07 260QS 5575 S5500060 GENERATOR AND GENERATOR CONTROL UNIT FILTER INSTALLATION, CAPACITOR ASSEMBLY. CAPACITOR PART NUMBER BLEW A HOLE IN THE END, BLEW ONE LEAD OFF ITS CONTACT, AND BURNED THE INSULATION FROM THE WIRE, FOR APPROXIMATELY 1 INCH. 1 L 7 2 4F RT A22CE 1996080800074 19960808 00074 NE 1996 8 8 96ZZZX3823 2 19960408 G 7250 566004 TURBINE RKWELL NA265 NA26540 6402608 CE PWA JT12 JT12A8 52042 NE 2ND STAGE FAILED D E F A ENGINE SHUTDOWN ACTIVATE FIRE EXT. UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 SO 09 307NT 1196 282072 P637801NB CLIMBING THROUGH 5,000 FEET, THE CREW HEARD AND FELT A LOUD REPORT FOLLOWED IMMEDIATELY BY THE LT ENGINE FIRE WARNING LI GHT. THE LT ENGINE SPEED ROLLED BACK TO APPROXIMATELY 12 PERCENT. PILOT SHUT ENGINE DOWN, DISCHARGED THE FIRE BOTTLE A ND MADE A SINGLE ENGINE LANDING. INSPECTION REVEALED NUMEROUS 1ST AND 2ND STAGE TURBINE BLADES MISSING AND EXTENSIVE DA MAGE TO 2ND STAGE DISK. 2 L 7 2 4J 4 J A2WE 1E9 1996080800077 19960808 00077 1996 8 8 96ZZZX3826 4 19960603 G 3418 556416 CONNECTOR PIPER PA42 PA42 7104202 SO PRESS BULKHEAD BURNT B GBBR O OTHER B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 NM 11 8RY 428001036 PILOT REPORTED ERRONEOUS RIGHT STALL WARNING AND A MOMENTARY 'PUFF' OF SMOKE FROM RT INSTRUMENT PANEL. INSPECTION REVEA LED PRESSURE BULKHEAD AREA BURNED. (CONNECTOR NR E339/439.) CONNECTOR WAS REPLACED AND GOLD PLATED PINS AND SOCKETS IN STALLED. 1 L 7 2 4T A23SO 1996080800078 19960808 00078 EU 1996 8 8 96ZZZX3827 1 19960712 G 2710 5135123 CONTROL SYSTEM ISRAEL 1124 1124 4500102 EU LT/RT AILERON CORROSION D K NONE O OTHER IN INSP/MAINT 1 GL 13 300LH 5950 312 INSPECTION FOUND AILERON CONTROL SYSTEM, LT AND RT, CORROSION. 2 M 7 2 4F A2SW 1996080800079 19960808 00079 EU 1996 8 8 96ZZZX3828 1 19960712 G 3230 283023501 CONTROL ROD ISRAEL 1124 1124 4500102 EU NLG FORWARD CORRODED D K NONE O OTHER IN INSP/MAINT 1 GL 13 300LH 5950 312 INSPECTION FOUND NLG CONTROL RODS FORWARD, CORROSION. 2 M 7 2 4F A2SW 1996080800080 19960808 00080 EU 1996 8 8 96ZZZX3829 1 19960712 G 3230 3900009231243 CONTROL ROD ISRAEL 1124 1124 4500102 EU NLG RT CORRODED D K NONE O OTHER IN INSP/MAINT 1 GL 13 300LH 5950 312 INSPECTION FOUND NLG CONTROL RODS RT, CORROSION. 2 M 7 2 4F A2SW 1996080800081 19960808 00081 EU 1996 8 8 96ZZZX3830 1 19960712 G 3230 3900009231288 CONTROL ROD ISRAEL 1124 1124 4500102 EU NLG LT/RT CORRODED D K NONE O OTHER IN INSP/MAINT 1 GL 13 300LH 5950 312 INSPECTION FOUND NLG CONTROL RODS LT AND RT, CORROSION. 2 M 7 2 4F A2SW 1996080800082 19960808 00082 NM 1996 8 8 96ZZZX3831 1 19960429 G 2820 5888D1 CHECK VALVE BOEING 727 72730 1384008 NM AUX FUEL SYS FAILED H K NONE O OTHER IN INSP/MAINT 1 EA 07 727BE 418 18933 CHECK VALVE FAILED IN OPEN POSITION. VALVE WAS INSTALLED IN AUXILIARY FUEL SYSTEM STC NR SA530NE CONFIGURATION NR 3. I NSTALLED PER DWG NR 200-1-503 FUEL SYSTEM. AUXILARY FUEL KIT INSTALLED PER INSTALLATION MDL-200-1-141, REV. 1, DATED MA Y 16, 1990. 2 L 7 3 4F A3WE 1996080800083 19960808 00083 CE 1996 8 8 96ZZZX3832 1 19960504 G 2432 24535020 BATTERY MARATHON MA520 CESSNA 500 550 2076604 CE CELLS OVERHEAT H H DEACTIVATE SYST/CIRCUITS M OVER TEMP CR CRUISE 1 GL 17 7ZU 233 9403362 5500433 BATTERY TEMPERATURE ROSE TO AN OVERHEAT CONDITION WITHIN 30 MINUTES AFTER DEPARTURE. CORRECTIVE PROCEDURE ISOLATED BATT ERY FROM GENERATOR CONTINUING TO HEAT BATTERY. BATTERY EXAMINED BY MAINTENANCE TECH AND DISCOVERED TO HAVE BAD CELLS. B AD BATTERY REPLACED WITH NEW ONE. 1 L 7 2 4F A22CE 1996080800084 19960808 00084 EU 1996 8 8 96ZZZX3833 1 19960329 G 7930 41SG107150G14 TRANSDUCER BAG JETSTM JETSTM3101 1500215 EU OIL SYSTEM DEFECTIVE G K NONE O OTHER IN INSP/MAINT 1 GL 17 829JS 713 FOUND TRANSDUCER WAS NOT PRODUCING THE CORRECT OUTPUTS UNDER KNOWN OIL QUANTITY AND PRESSURES. 2 L 7 2 4T RT A21EU 1996080800085 19960808 00085 NM 1996 8 8 96ZZZX3834 1 19960601 G 5541 B62R0132 SPAR PROPJT 200 200D 0140312 NM RUDDER HINGE CRACKED B OW2R K NONE O OTHER IN INSP/MAINT 1 GL 23 898LF 2130 323 RUDDER SPAR CRACKED AT TOP HINGE LOCATION. REPLACED SPAR P/N B62013-2, ADDED DOUBLER P/N B62013-23. WORK ACCOMPLISHED IAW MEYERS AIRCRAFT DRAWINGS AND PROCEDURES. 1 L 7 1 3O 3A18 1996080800086 19960808 00086 CE 1996 8 8 96ZZZX3835 1 19960711 G 2612 302158 DETECTOR BEECH 200 B200 1152922 CE LT ENG FIREWALL MALFUNCTION B LX5R K NONE N FALSE WARNING IN INSP/MAINT 1 GL 19 991LL BB1234 CREW REPORTED INTERMITTENT FIRE WARNING ON LEFT ENGINE. FOUND LOWER FIREWALL FIRE DETECTOR BAD. THIS DETECTOR HAS BEEN SUPERCEDED BY A NEW STYLE. 1 L 7 2 4T A24CE 1996080800087 19960808 00087 WP 1996 8 8 96ZZZX3836 1 19960610 G 6320 369A510923 PINION SHAFT 369A5100709 HUGHES 369 369HS 4470728 WP T/R & ACCY DRIVE WORN B A PN5R K NONE O OTHER IN INSP/MAINT 1 NM 03 369PF 2127 1020434 530473S MAIN ROTOR TRANSMISSION LOCKNUT LOST TORQUE AND ALLOWED BEARINGS TO FRET ON SHAFT WEARING THE SHAFT UNDER THE BEARINGS A ND ACCESSORY DRIVE GEAR. THIS ALLOWED THE DRIVE PIN TO SHEAR AND WHENEVER TORQUE WAS BELOW 6 PERCENT ENGINE TORQUE, THE OIL PUMP AND ROTOR TACHOMETER WOULD STOP TURNING. SHAFT IS TO BE REPAIRED, PIN REPLACED, AND TRANSMISSION REASSEMBLED. CHECKED AND RETURNED TO SERVICE TO FINISH ITS 273 HOURS TO OVERHAUL. 1 G 7 1 3U H3WE 1996080800088 19960808 00088 SW 1996 8 8 96ZZZX3837 1 19960611 G 6230 206040036103 BEARING 206040002007 BELL 206 206B3 1181506 SW MAST XMSN MAKING METAL B FW7D K NONE O OTHER IN INSP/MAINT 1 GL 03 16917 8961 850 NJF50813 2303 TRANSMISSION CHIP CAUTION LIGHT ILLUMINATED DURING FLIGHT. FOUND MULTIPLE FLAKES ON MAGNETO PLUGS. MAST BEARING FOUND TO BE CAUSE OF METAL. CAUSE UNDETERMINED. 1 G 7 1 3U H2SW 1996080800089 19960808 00089 SW 1996 8 8 96ZZZX3838 1 19960708 G 6420 MS208234 ELBOW 4762060029 BELL 47 47G5 1181032 SW TRANSMISSION WRONG PART B OUGR K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 17 J131224 DURING CLEAN-UP AND INSPECTION OF TRANSMISSION PARTS AT OVERHAUL, DISCOVERED TRANSMISSION OIL SUPPLY FITTING PN MS20823- 4 HAD RESTRICTOR ORIFICE SIMILAR TO PN 47-712-035-1 MANIFOLD PRESSURE GAUGE LINE RESTRICTOR. SUBMITTER STATED COULD CAU SE TRANSMISSION FAILURE FROM OIL STARVATION. 1 G 7 1 3O 2H3 1996080800090 19960808 00090 WP 1996 8 8 96ZZZX3839 1 19960611 G 6220 369H120331 LINK ASSY 369A1200501 HUGHES 369 369HS 4470728 WP M/R HUB LEAD/LAG BUSHING LOOSE B PN5R K NONE O OTHER IN INSP/MAINT 1 NM 03 42405 174 3562 920416S WHILE C/W WITH VISUAL INSPECTION PER AD 93-03-13 (R/D 3-21-95) TWO BLADE ATTACHMENT BUSHINGS WERE FOUND LOOSE IN ONE LEA D/LAG LINK ASSY. M/R HUB TO BE RETURNED TO A MDHS SERVICE CENTER FOR REPLACEMENT OF THIS LINK ASSY WITH A SERVICEABLE P ART. 1 G 7 1 3U H3WE 1996080800118 19960808 00118 SW 1996 8 8 96ZZZX3840 1 19960517 G 6230 2060104213 BOLT BELL 206 206L3 1182108 SW PYLON PILLOW BLK STEPPED B AC2R K NONE O OTHER IN INSP/MAINT 1 SW 03 6533Y 51457 PILLOW BLOCK BOLTS (3 EACH) FOUND STEPPED AND SCORED. 1 G 7 1 3U H2SW 1996080800119 19960808 00119 GL 1996 8 8 96ZZZX3841 2 19960422 G 7320 1564T1005 SERVO BOLKMS 105 BO105S 5626006 EU ALLSN 250C 250C20B 03013 GL ENGINE FAILED B AC2R K NONE O OTHER NR NOT REPORTED 1 SW 03 8776 1619 S776 SERVO MOTOR FAILED IN-FLIGHT. MOTOR SHORTED OUT CAUSING CIRCUIT BREAKER TO TRIP. 1 G 7 2 3U 3 U H3EU E4CE 1996080800120 19960808 00120 NE 1996 8 8 96ZZZX3842 1 19960624 G 3210 7625002102041 TUBE SKRSKY S76 S76A 8143006 NE MLG CORRODED B S A ZV1R K NONE O OTHER IN INSP/MAINT 1 SW 03 31211 8015 760225 DURING INSPECTION, FOUND HI-LOCK FASTENER ON RIGHT SIDE OF TUBE STICKING OUT APPROXIMATELY .0625 INCH ON BOTH ENDS. THE FASTENER HAD CORRODED IN THE CENTER AND BROKE. PART NUMBER OF THE FASTENER IS 1528-20 AND THE COLLAR IS NAS1080D8. SU BMITTER RECOMMENDS A ONE TIME INSPECTION AND REPLACEMENT OF ALL HI-LOCKS AND A 300 HOUR INSPECTION OF THE TUBE ASSY FOR CORROSION AND PITTING ON THE INSIDE. 1 G 7 2 3U H1NE 1996080800122 19960808 00122 SW 1996 8 8 96ZZZX3844 1 19960620 G 6230 206010336005 DRIVE LINK BELL 206 206L1 1182107 SW M/R MAST WORN B ZV1R K NONE O OTHER IN INSP/MAINT 1 SW 03 5007F 45186 PLAY IN EXCESS OF .025 INCH AT TWO PLACES. SEE BELL MM L3, FIGURE 62.21. AT TEAR DOWN, FOUND BEARING AND SPACERS WORN. TOTAL TIMES, LESS THAN 1,000 HOURS AND 1 YEAR SINCE REPLACED. 1 G 7 1 3U H2SW 1996080800123 19960808 00123 SW 1996 8 8 96ZZZX3845 1 19960620 G 6230 206010336005 DRIVE LINK BELL 206 206L1 1182107 SW M/R MAST WORN B ZV1R K NONE O OTHER IN INSP/MAINT 1 SW 03 2654 45482 PLAY IN EXCESS OF .025 INCH AT TWO PLACES. SEE BELL MM L3, FIGURE 62.21. AT TEAR DOWN, FOUND BEARING AND SPACERS WORN. TOTAL TIMES LESS THAN 1,000 HOURS AND 1 YEAR SINCE REPLACED. 1 G 7 1 3U H2SW 1996080800124 19960808 00124 SW 1996 8 8 96ZZZX3846 1 19960620 G 6230 206010336005 DRIVE LINK BELL 206 206L1 1182107 SW M/R MAST WORN B ZV1R K NONE O OTHER IN INSP/MAINT 1 SW 03 3899C 45596 PLAY IN EXCESS OF .025 INCH AT TWO PLACES. SEE BELL MM L3, FIGURE 62.21. AT TEAR DOWN, FOUND BEARING AND SPACERS WORN. TOTAL TIMES LESS THAN 1,000 HOURS AND 1 YEAR SINCE REPLACED. 1 G 7 1 3U H2SW 1996080800126 19960808 00126 SW 1996 8 8 96ZZZX3848 1 19960620 G 6230 206010336005 DRIVE LINK BELL 206 206L3 1182108 SW M/R MAST WORN B ZV1R K NONE O OTHER IN INSP/MAINT 1 SW 03 2619 51375 PLAY IN EXCESS OF .025 INCH AT TWO PLACES. SEE BELL MM L3, FIGURE 62.21. AT TEAR DOWN, FOUND BEARING AND SPACERS WORN. TOTAL TIMES LESS THAN 1,000 HOURS AND 1 YEAR SINCE REPLACED. 1 G 7 1 3U H2SW 1996080800724 19960808 00724 WP 1996 8 8 96ZZZX3858 1 19960628 G 5210 L3082511AT DRIVE MOTOR CHICAGOPNEU DOUG DC10 DC1030F 3023504 WP 4L DOOR FAILED D K NONE O OTHER IN INSP/MAINT 1 WP 13 10MB 887 B713614 47907 DOOR 4L FAILED TO OPEN IN EMERGENCY MODE DURING DITCHING DEMONSTRATION. TROUBLESHOOTING FOUND THE FAILURE OCCURRED IN T HE PNEU DRIVE MOTOR. PNEU DRIVE MOTOR IS 'ON CONDITION' WITH OPS CHECK DUE IN 1,000-HOUR INTERVALS. 2 L 7 3 4F RT A22WE 1996080800725 19960808 00725 CE 1996 8 8 96ZZZX3859 1 19960617 G 3240 20011610W FILTER 38675 BEECH MU300 400BEECH CE PWR BRAKE VALVE BLOCKED B A AKGR K NONE O OTHER IN INSP/MAINT 1 CE 05 203BA 3686 RJ3 AFTER STARTING ENGINE AND HYDRAULIC SYSTEM, PRESSURE WAS UP AND NORMAL (1,500 PSI), THE BRAKES LOCKED UP AND AIRCRAFT WO ULD NOT MOVE. FOUND THE POWER BRAKE VALVE RETURN FILTER BLOCKED. THESE FILTERS ARE CLEANED EVERY 24 MONTHS. NO HOUR R EQUIREMENT. SUBMITTER STATES THESE FILTERS NEED TO BE CLEANED AT 400-HOUR INTERVALS. 2 H 7 2 4F RT A16SW 1996080800728 19960808 00728 EA 1996 8 8 96ZZZX3862 2 19960718 G 8550 AN9151D ELBOW PIPER PA38 PA38112 7103812 SO LYC O235 O235L2C 41505 EA HOBBS SWITCH FAILED D K NONE K FLUID LOSS NR NOT REPORTED 1 GL 15 2606L 3879A0778 L2236015 ELBOW P/N AN915-1D WAS INSTALLED IN THE OIL PRESSURE/HOBBS SWITCH SYSTEM OFF THE BACK OF THE ACCESSORY CASE. THE INSTAL LATION OF THE HOBBS PRESSURE SWITCH WAS NOT DONE IAW THE MANUFACTURERS IPC. THE SWITCHES WERE NOT INSTALLED AND SUPPORT ED CORRECTLY. AFTER TIME AND ENGINE VIBRATION, THE FITTING BROKE CAUSING ALL THE ENGINE OIL TO BE PUMPED OUT. 1 L 7 1 3O 3 O A18SO E223 1996080800730 19960808 00730 EA 1996 8 8 96ZZZX3865 1 19960718 G 2720 37350 TORQUE TUBE CNDAIR CL600 CL6002B16 1900305 EA RUDDER CONTROL NOT SAFETIED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 07 309FX 5306 WHILE PERFORMING CANADAIR ALERT SERVICE BULLETIN A604-27-002, FOUND RUDDER CONTROL TORQUE TUBE LOWER ROD END ATTACH HARD WARE (SAFETY COTTER PIN) NOT INSTALLED AND THE NUT BACKED OFF ALLOWING THE BOLT TO PARTIALLY BACK OUT. THE NUT WAS TORQ UED AND COTTER PIN INSERTED. MANUFACTURER WAS NOTIFED OF DEFECT. 2 L 7 2 4F RT A21EA 1996080800731 19960808 00731 CE 1996 8 8 96ZZZX3866 1 19960715 G 2760 25CW904A BELLCRANK RAYTHN DH125 HAWKER800XP CE RT AIRBRAKE BINDING D K NONE F FLT CONT AFFECTED NR NOT REPORTED 1 GL 07 12F 1810 8182 FLIGHT CREW NOTICED AIRBRAKE HANDLE WAS STIFF AND HAD AN OCCASIONAL BIND. TWICE THEY COULD NOT GET LIFT DUMP. INVESTIG ATION FOUND THE UPPER AND LOWER BEARINGS IN THE RIGHT AIRBRAKE BELLCRANK VERY ROUGH AND BINDING. THESE BEARINGS ARE SEA LED AND NO LUBRICATION REQUIRED. POSSIBLE CAUSE IS TKS SOMEHOW GOT INTO THE BEARINGS CAUSING THEM TO CORRODE. 2 L 7 2 4F RT A3EU 1996080800732 19960808 00732 CE 1996 8 8 96ZZZX3867 1 19960715 G 3040 57033 FAN CESSNA 500 550 2076604 CE DEFOG MOTOR FAILED B A R3R2 B A EMER. DESCENT UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 SW 01 6763L 1216 550673 DEFOG FAN FAILED IN-FLIGHT FILLING CABIN WITH SMOKE. DEFOG AND OVERHEAD FANS ARE ON SAME CIRCUIT WHICH ALLOWS CONTINUED POWER TO FAILED UNIT WITHOUT TRIPPING CIRCUIT BREAKER. EMERGENCY DESCENT INITIATED AND LANDED SAFELY. RECOMMEND SB TO SPLIT CIRCUIT AND INSTALL CIRCUIT BREAKERS THAT WILL TRIP IF UNIT FAILS. SYSTEM IS CONFIGURED FROM FACTORY. SAME COND ITION EXPERIENCED AT LEAST TWICE PREVIOUSLY. RECOMMEND AIRWORTHINESS DIRECTIVE IF MFG DELAYS. 1 L 7 2 4F A22CE 1996080800733 19960808 00733 CE 1996 8 8 96ZZZX3868 1 19960606 G 3411 5120P1 DIGITIZER CESSNA 182 182 2072702 CE TOP PLATE STATIC LEAK D K NONE O OTHER NR NOT REPORTED 1 SW 17 9620E 500452 18268431 ALTITUDE DIGITIZER MADE OF PLASTIC, TOP PLATE AT STATIC INLET CRACKED CAUSING EXCESSIVE STATIC LEAK. SUBMITTER STATED T OP PLATE USED TO BE METAL, NOW IT IS GLASS FILLED NYLON. 1 H 7 1 3O NT 3A13 1996080800734 19960808 00734 SO 1996 8 8 96ZZZX3869 2 19960717 G 8520 CRANKCASE PIPER PA34 PA34200T 7103406 SO CONT O360 TSIO360EB 17025 SO LT ENG NR 5 CYL CRACKED B S APCR K NONE O OTHER IN INSP/MAINT 1 NM 01 36319 347870318 265936R THE INSPECTION FOUND CRANKCASE HAS A SMALL .3750 INCH CRACK NEXT TO THE UPPER BOLT JUST FORWARD OF CYLINDER NR 5. THIS IS CONSIDERED A NON-CRITICAL AREA PER SB M90-17. 1 L 7 2 3O 3 O A7SO E9CE 1996080800735 19960808 00735 SO 1996 8 8 96ZZZX3870 2 19960627 G 8530 PISTON CESSNA 172 R172K 2072431 CE CONT O360 IO360KB 17025 SO NR 6 OIL SCRAPER RING FAILED D S K NONE O OTHER IN INSP/MAINT 1 SO 13 758LR 1400 R1723185 356264 UPON DISASSEMBLY AFTER LOW COMPRESSION READING, FOUND THE LOWER PORTION BY OIL SCRAPER RING MISSING FROM THE PISTON. SU SPECT DUE TO THE OIL SCRAPER RING HANGING UP, THUS, STUCTRURAL MALFUNCTION. 1 H 7 1 3O 3 O 3A17 E1CE 1996080800736 19960808 00736 GL 1996 8 8 96ZZZX3871 1 19960701 G 3240 BRAKE AMTR EAGLE CHRISEAGLE2 GL MLG LOCK UP G O OTHER O OTHER TX TAXI/GRND HDL 1 GL 03 109BX 2 0245 DURING A HIGH SPEED TAXI SYSTEM CHECK OUT, PILOT EXPERIENCED BRAKE LOCK-UP. THE AMATEUR/EXPERIMENTAL CATEGORY AIRCRAFT SLID OFF RUNWAY WITH MINOR DAMAGE AND NO INJURY TO PILOT. PILOT, WHO ALSO BUILT AIRCRAFT, STATED BRAKE SYSTEM HAD NO DI SCREPANCIES NOTED DURING INSPECTION AFTER OCCURRENCE. PILOT ALSO STATED HIGH SPEED TAXIING WAS NOT INTENDED FOR FLIGHT. 1 Q 7 1 3O EXPA1Q71 1996080800737 19960808 00737 SO 1996 8 8 96ZZZX3872 1 19960716 G 7714 PS50048151 TACHOMETER BFGOODRICH 599282 PIPER PA32 PA32300 7103212 SO NEEDLE STOP DEFECTIVE D K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 15 2969Q 25180 327740056 REMOVED TACHOMETER FROM BOX. NEEDLE ON WRONG SIDE OF STOP. 1 L 7 1 3O A3SO 1996080800738 19960808 00738 CE 1996 8 8 96ZZZX3873 1 19960718 G 7810 STACK CESSNA 177 177B 2073708 CE MUFFLER SEPARATED D K NONE O OTHER IN INSP/MAINT 1 NM 01 34348 68 17701775 EXIT STACK OF MUFFLER SEPARATED FROM THE MUFFLER. APPEARS WELDS MAY NOT HAVE BEEN 'NORMALIZED' CAUSING A BRITTLE AREA A ROUND THE WELD. THIS WAS AN FAA/PMA PART. ENGINE SHOWED NO SIGNS OF VIBRATION. EXHAUST EXITED THE MUFFLER INTO COWLIN G, GASCOLATOR, AND CARBURETOR AREA. 1 H 7 1 3O A13CE 1996080800739 19960808 00739 CE 1996 8 8 96ZZZX3874 1 19960706 G 2436 99101263 REGULATOR CESSNA 414 414A 2075907 CE DC SYSTEM FAILED C O OTHER H ELECT. POWER LOSS-50 PC CR CRUISE 1 WP 13 4573V 414A0300 REGULATOR FAILED IN-FLIGHT. REGULATOR REPLACED AND ADJUSTMENTS MADE IAW CESSNA SM. 1 L 7 2 3O A7CE 1996080800740 19960808 00740 EA 1996 8 8 96ZZZX3875 2 19960723 G 8520 11F20022D3 CRANKCASE PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA NR 6 CYL STUDS FAILED B WC7R O OTHER R PARTIAL RPM/PWR LOSS CR CRUISE 1 GL 25 585DT 493 318052117 L172868A PILOT REPORTED HEARING A 'BOOM' AND A DECREASE IN MANIFOLD PRESSURE DURING FLIGHT. UPON INSPECTION, NR 6 CYLINDER OF RI GHT ENGINE WAS FOUND TO BE AWAY FROM CRANKCASE PAD. FIVE OUT OF EIGHT CYLINDER HOLD-DOWN STUDS HAD BROKEN OFF. TWO THR OUGH STUDS, AND ONE SHORT STUD REMAINED TO HOLD CYLINDER ON. SUSPECT CAUSE, NOT TORQUED PROPERLY. 1,454.3 HOBBS. 1 L 7 2 3O 3 O A20SO E14EA 1996080800741 19960808 00741 EA 1996 8 8 96ZZZX3876 2 19960701 G 8530 EC75971 CYLINDER BEECH 23 C23 1151242 CE LYC O360 O360A4K 41514 EA NR 4 CRACKED D K NONE O OTHER IN INSP/MAINT 1 GL 05 63TW 1209 M1762 L2069136A INSPECTION FOUND NR 4 CYLINDER CRACKED FROM OUTSIDE RADIUS OF INTAKE VALVE TO OUTSIDE RADIUS OF EXHAUST VALVE. CYLINDER HEAD SPLIT OPEN BLOWING BOTTOM SPARK PLUG FROM CYLINDER. 1 L 7 1 3O 3 O A1CE E286 1996080800742 19960808 00742 EA 1996 8 8 96ZZZX3877 2 19960715 G 8530 SL13790A ROCKER SHAFT LYC O320 O320* 41508 EA ENGINE BENT B CYKR K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 07 ROUTINE CHECK OF O320 SERIES ENGINE ROCKER SHAFTS FROM STOCK, FOUND P/N SL13790A, LOT NR 510924 DATED 4-30-96, 9 OUT OF 20 WERE FOUND BENT. 3 O E274 1996080800743 19960808 00743 1996 8 8 96ZZZX3878 1 19960722 G 2150 220470001 ACM ALIDSIGNAL THRUST BEARING FAILED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 05 14700 TWO EACH AIR CYCLE MACHINES THRUST BEARING FAILURES WITHIN 6 TO 8 HOURS OF OPERATION. ALLIED SIGNAL HAS TRACED THIS BAC K TO A THRUST BEARING FOIL COATING PROCESS PROBLEM IN MID-1994. 1996080800744 19960808 00744 1996 8 8 96ZZZX3879 1 19960722 G 2150 220470001 ACM ALIDSIGNAL THRUST BEARING FAILED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 05 103699 TWO EACH AIR CYCLE MACHINES THRUST BEARING FAILURES WITHIN 6 TO 8 HOURS OF OPERATION. ALLIED SIGNAL HAS TRACED THIS BAC K TO A THRUST BEARING FOIL COATING PROCESS PROBLEM IN MID-1994. 1996080800745 19960808 00745 1996 8 8 96ZZZX3880 1 19960716 G 2822 2B651 PUMP AIRBORNE ARMATURE FAILED D K NONE O OTHER IN INSP/MAINT 1 GL 13 2D100 PUMP ARMATURE OUT OF BALANCE CAUSING PREMATURE FAILURE OF PUMP. 1996080800746 19960808 00746 1996 8 8 96ZZZX3881 1 19960716 G 2822 10212 PUMP AIRBORNE ARMATURE FAILED D K NONE O OTHER IN INSP/MAINT 1 GL 13 1D114 PUMP ARMATURE OUT OF DYNAMIC BALANCE CAUSING PREMATURE FAILURE OF THE PUMP. 1996080800747 19960808 00747 1996 8 8 96ZZZX3882 1 19960712 G 2822 1D16 PUMP AIRBORNE ARMATURE FAILED D K NONE O OTHER IN INSP/MAINT 1 GL 15 6E166 WASHER WORN THROUGH RESULTING IN ARMATURE SHAFT BEING CUT AND SHEARED OFF, RESULTING IN COMPLETE LOSS OF FUEL PRESSURE A ND FLOW. 1996080800748 19960808 00748 1996 8 8 96ZZZX3883 1 19960716 G 2822 1B58 PUMP AIRBORNE ARMATURE FAILED D K NONE O OTHER IN INSP/MAINT 1 GL 15 1A6 PUMP MAY HAVE BEEN RUN DRY, THEN HEATING UP, AND CAUSING DAMAGE TO ARMATURE. 1996080800749 19960808 00749 CE 1996 8 8 96ZZZX3884 1 19960717 G 8011 MZ4224ECH STARTER PRESTOLITE CESSNA 172 172N 2072434 CE GEARBOX SCREWS STRIPPED D K NONE O OTHER IN INSP/MAINT 1 WP 15 733FU 12 17268268 THREE OF FOUR FORWARD CAP SCREWS HOLDING STARTER MOTOR TO GEARBOX HOUSING THE BENDIX - STRIPPED. 1 H 7 1 3O NT 3A12 1996080800750 19960808 00750 CE 1996 8 8 96ZZZX3885 1 19960717 G 2810 FUEL CAP CESSNA 182 182Q 2072732 CE WING SEAL FAILED D K NONE O OTHER IN INSP/MAINT 1 CE 07 97077 2930 18266966 FUEL CAP ASSY HAD TO BE REPLACED WITH MONARCH AIR AND DEVELOPMENT FUEL CAP AND INLET ASSY DUE TO THE UNAVAILABILITY OF R EPLACEMENT PARTS. LEAKING SEALS. 1 H 7 1 3O NT 3A13 1996080800751 19960808 00751 CE 1996 8 8 96ZZZX3886 1 19960717 G 7921 L639171 OIL COOLER LORINORDAM CESSNA 206 TU206G 2073357 CE ENGINE OIL LEAKED D K NONE W K INADEQUATE Q C FLUID LOSS IN INSP/MAINT 1 WP 07 P2NTM 94J067 U20603580 INSTALLED NEW LORI OIL COOLER, LEAKED IMMEDIATELY AT WELD AT BASE OF COOLER. SUBMITTER SUGGESTS TO IMPROVE TEST/QUALITY CONTROL BEFORE LEAVING FACTORY. 1 H 7 1 3O A4CE 1996080800752 19960808 00752 1996 8 8 96ZZZX3887 1 19960716 G 2822 2B729 PUMP AIRBORNE BRUSH BLOCK FAILED D K NONE O OTHER IN INSP/MAINT 1 GL 13 11E2892 PUMP MAY HAVE RUN DRY CAUSING PUMP TO HEAT UP AND DAMAGE BRUSH BLOCK. 1996080800753 19960808 00753 EA 1996 8 8 96ZZZX3888 2 19960718 G 8520 SL13884MO6 BEARING LYC O540 O540B2C5 41532 EA NR 2 JOURNAL FAILED B BG4R K NONE O OTHER IN INSP/MAINT 1 WP 17 2 L2295640A AFTER NORMAL TEST CELL RUN, ENGINE OIL WAS DRAINED AND THE OIL FILTER AND SUCTION SCREEN WAS INSPECTED AND A MASSIVE AMO UNT OF ALUMINUM WAS FOUND. UPON DISASSEMBLY, FOUND THE FRONT BEARING HAD FAILED AT THE NR 2 JOURNAL. THE BEARING HAD S MEARED AND TRANSFERRED TO THE CRANKSHAFT THRUST AREA AND NR 2 JOURNAL. ALL PARTS WERE INSPECTED TO DETERMINE THE CAUSE WITH NO FIRM CONCLUSION. SUBMITTER RECOMMENDS USING ONLY LYCOMING BEARINGS ON RE-GROUND CRANKSHAFTS. 3 O E295 1996080800754 19960808 00754 1996 8 8 96ZZZX3889 1 19960717 G 2434 ALX942513 ALTERNATOR ELECTROSYS 0 DRIVE DEFECTIVE B APCR K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 01 6042533 ALTERNATOR REPORTED TO BE 'FACTORY NEW' MISSING SHAFT-TO-DRIVE-COUPLING O-RING, P/N AN123864. MISING DRIVE-END SEAL, P/ N 352068. ROTOR 'DRAGS' AND BINDS WHEN SPUN BY HAND. PROBLEMS FOUND DURING ROUTINE NEW PARTS INSPECTION. 1996080800755 19960808 00755 CE 1996 8 8 96ZZZX3890 1 19960701 G 3230 6A07116002 CYLINDER WIPLINEINC 4000 CESSNA 206 TU206F 2073353 CE FLOAT CRACKED C S K NONE K FLUID LOSS IN INSP/MAINT 1 SW 99 7485Q U20602220 HYDRAULIC LEAK. CRACK INSIDE OF HYDRAULIC CYLINDER. REPLACED PART WITH NEW. INSPECTED, FOUND CORROSION, POSSIBLY CAUS ED BY GEAR INDICATOR LIGHT WIRES AND HYDRAULIC LINE BEING CLAMPED TO CYLINDER. A RUBBER/PLASTIC PAD HAD BEEN GLUED TO C YLINDER TO PREVENT CONTACT SO CORROSION OCCURRED AT PERIPHERY OF PAD. 1 H 7 1 3O A4CE 1996080800756 19960808 00756 1996 8 8 96ZZZX3891 4 19960715 G 6122 53914 STUD 4B21 DHAV DHC3 DHC3 2800202 EA PROP GOV BROKEN D K NONE K FLUID LOSS IN INSP/MAINT 1 AL 05 511BW 202 1121 35 ENGINE DEVELOPED AN OIL LEAK. PROBLEM FOUND TO BE A BROKEN BASE-TO-BODY ATTACH STUD ON THE PROPELLER GOVERNOR OF THE FO UR STUDS. ONE WAS BROKEN, AND ONE AN31-5 NUT WAS SLIGHTLY LOOSE. ALL 4 AN310-5 NUTS WERE SAFETIED. 1 H 7 1 3R A815 1996080800757 19960808 00757 NM 1996 8 8 96ZZZX3892 1 19960701 G 2550 106091129 HEAT BLANKET BOEING 727 727225 1384077 NM AFT BAG FS 950C BURNT HOLE B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 8882Z 1734 21579 DURING A C-5 CHECK, NOTED THAT AFT BAG PIT HEAT BLANKET, P/N 10-60911-20; (COX P/N 2137-29), HAD A 2 INCH BY .50 INCH BU RN THROUGH THE BLANKET. THE INSULATION BEHIND IT ALSO SHOWED SIGNS OF BURNING. 2 L 7 3 4F A3WE 1996081500073 19960815 00073 EU 1996 8 15 96ZZZX3893 1 19960620 G 2160 7847231 VALVE AMD FALC50 FALCON900 2700160 EU CABIN COOLING MISWIRED H A K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 09 5733 39 TURBINE ANTI-ICE VALVE WAS INSTALLED TO CORRECT UNCONTROLLABLE CABIN AND COCKPIT TEMPERATURE DISCREPANCY. VALVE OPERATE D BACKWARDS CAUSING CABIN TO BECOME EXTREMELY HOT. RECOMMENDATIONS BY TECH SERVICES TO CHECK VALVE FOR PROPER WIRING RE VEALED THAT VALVE DID, IN FACT, OPERATE BACKWARDS DUE TO INTERNAL REVERSED WIRING ON THE VALVE MOTOR. WERE ADVISED, AT THAT TIME, THAT 3 OR 4 OF THESE VALVES HAD BEEN FOUND WITH THE SAME PROBLEM COMING OUT OF OVERHAUL. 2 L 7 3 4F RT A46EU 1996081500074 19960815 00074 CE 1996 8 15 96ZZZX3894 1 19960621 G 2721 556544067 PUSH PULL ROD CESSNA 500 500CESSNA 2076602 CE RUDDER TAB CRACKED D A K NONE O OTHER IN INSP/MAINT 1 WP 07 52AJ 7506 5000061 DURING ROUTINE MAINTENANCE, RUDDER TAB PUSH/PULL RODS WERE REMOVED TO LUBRICATE TRIM ACTUATOR SCREWS. THE ROD WAS SPLIT 80 PERCENT OF THE LENGTH FROM WHAT APPEARED TO BE WATER FREEZING INSIDE THE TUBE. 1 L 7 2 4F A22CE 1996081500075 19960815 00075 CE 1996 8 15 96ZZZX3895 1 19960621 G 2731 PUSH PULL ROD CESSNA 500 500CESSNA 2076602 CE ELEVATOR TAB CRACKED D S K NONE O OTHER IN INSP/MAINT 1 WP 07 52AJ 7506 5000061 DURING ROUTINE MAINTENANCE, ELEVATOR TAB PUSH/PULL RODS WERE REMOVED TO LUBRICATE ACTUATOR SCREWS. THE ROD WAS FOUND TO HAVE BRAZE REPAIR OVER A CRACK AND WAS SPLIT OPEN. 1 L 7 2 4F A22CE 1996081500076 19960815 00076 CE 1996 8 15 96ZZZX3896 1 19960705 G 2430 035A8843421 WIRE MTSBSI MU2 MU2B40 5780440 CE START/GEN CABLE BROKEN B A ACOR K NONE O OTHER IN INSP/MAINT 1 SO 05 68CL 448SA LEFT ENGINE STARTER/CABLE COPPER CONNECTION LUG CONNECTED TO THE STARTERS GENERATOR, BROKE IN THE SHARP 90 DEGREE BEND S EPARATING THE STARTER-CABLE FROM THE STARTER GENERATOR. STARTER CABLE, AFTER SEPARATING FROM STARTER GENERATOR AND BEIN G RELEASED FROM STRESS, CAME TO REST ON FUEL CONTROL BELLCRANK. ELECTRICAL POWER SURGE ON ATTEMPTED ENGINE START DESTRO YED 3 CONTROL ROD ASSYS AND NECESSITATED FUEL CONTROL UNIT OVERHAUL. NOTE, THIS OCCURRED ON GROUND. FURTHER INVESTIGAT ION REVEALED CRACK IN STARTER GENERATOR GROUND CABLE LUG. SUBMITTER RECOMMENDS LONGER LENGTH CABLES TO REMOVE STRESS. 1 H 7 2 3T RT A10SW 1996081500077 19960815 00077 NE 1996 8 15 96ZZZX3897 2 19960621 G 7310 991202426 HOSE CESSNA 500 560CESSNA 2076750 CE PWA JT15 JT15D5 52112 NE MOTIVE FLOW FUEL CHAFED B A CNQR K NONE O OTHER IN INSP/MAINT 1 CE 07 323QS 785 5600323 FOUND THE LEFT ENGINE THRUST REVERSER CONTROL LINKAGE HAD CUT INTO THE OUTER PROTECTIVE COVER OF THE MOTIVE FLOW FUEL HO SE. THE FUEL HOSE ASSY WAS REPLACED AND THE T/R CONTROL LINKAGE SAFETY WIRE REPOSITIONED TO PREVENT IT FROM CHAFING THE HOSE. 2 L 7 2 4F 4 F RT A22CE E25EA 1996081500078 19960815 00078 CE 1996 8 15 96ZZZX3898 1 19960715 G 2810 66005004 CELL LEAR 60 60LEAR 5170707 CE FUSELAGE LEAKING D S K NONE K FLUID LOSS IN INSP/MAINT 1 EA 01 7US 1001 9270409 014 FUSELAGE FUEL CELL CAVITY DRAIN LEAKING. FOUND FORWARD FUSELAGE FUEL CELL NIPPLE CRACKED. THREE EACH FUSELAGE CELL FLA PPER VALVES DISCONNECTED. REF: LEAR SB60-28-5, INSPECTION OF AFT FUSELAGE CELL FLAPPER VALVES. 2 L 7 2 4F RT A10CE 1996081500079 19960815 00079 EU 1996 8 15 96ZZZX3899 1 19960719 G 2150 25VF1399AC DUCT HWKSLY DH125 BH125400A 4230138 EU RAM AIR CRACKED B S RO3R K NONE O OTHER IN INSP/MAINT 1 CE 03 4QB 9238 25255 WHILE ACCOMPLISHING AIRFRAME INSPECTION, ONE OF THE INSPECTION REQUIREMENTS CALLED OUT TO INSPECT THE APU. WHILE CONDUC TING THE INSPECTION, NOTED A LARGE CRACK ABOVE THE RAM AIR DUCT DOOR. THE APU WAS REMOVED WHICH REVEALED THE CRACKED RA M AIR DUCT ASSY. THE RIGHT SIDE OF THE DUCT CONTAINED A CRACK 7 INCHES - 10 INCHES LONG WITH ADDITIONAL CRACKS THROUGHO UT THE DUCT ASSY. THE APU IS NOT NORMALLY REMOVED DURING THIS INSPECTION WHICH COULD GO FOR NUMEROUS INSPECTIONS UNDETE CTED. IT IS BELIEVED THE HIGH VIBRATION LEVEL ASSOCIATED WITH THE APU CAUSED THE DUCT ASSY TO CRACK. 2 L 7 2 4J A3EU 1996081500080 19960815 00080 CE 1996 8 15 96ZZZX3900 1 19960715 G 2435 66085121 GENERATOR 400SG138Q LEAR 60 60LEAR 5170707 CE LT START/GEN DEFECTIVE C O OTHER E J VIBRATION/BUFFET WARNING INDICATION CR CRUISE 1 EA 01 7US 961 1184XL 014 VIBRATION THROUGH AIRCRAFT. LEFT GENERATOR LIGHT ILLUMINATED IN-FLIGHT. INSTALLED OVERHAULED STARTER 5-7-96. 2 L 7 2 4F RT A10CE 1996081500081 19960815 00081 CE 1996 8 15 96ZZZX3901 1 19960715 G 2435 60580031 STARTER 400SG138Q LEAR 60 60LEAR 5170707 CE LT ENGINE DEFECTIVE C K NONE O OTHER IN INSP/MAINT 1 EA 01 7US 20 1276XL 014 LEFT ENGINE SLOW TO START. INSTALLED SERVICEABLE STARTER GENERATOR 6-5-96. 2 L 7 2 4F RT A10CE 1996081500082 19960815 00082 CE 1996 8 15 96ZZZX3902 1 19960715 G 2435 6058031 GENERATOR 400SG138Q LEAR 60 60LEAR 5170707 CE RT START/GEN DEFECTIVE C K NONE O OTHER IN INSP/MAINT 1 EA 01 7US 9 1171XL 014 RIGHT STARTER GENERATOR VENT CAUSING SEVERE SOOTING ON LOWER COWL. FOUND .1875 INCH DIFFERENCE IN BRUSH LENGTH BETWEEN BRUSH SETS. 2 L 7 2 4F RT A10CE 1996081500083 19960815 00083 CE 1996 8 15 96ZZZX3903 1 19960715 G 2435 60580031 STARTER 400SG138Q LEAR 60 60LEAR 5170707 CE RT START/GEN DEFECTIVE C K NONE O OTHER IN INSP/MAINT 1 EA 01 7US 21 1276XL 014 RIGHT ENGINE SLOW TO START AFTER SHUT DOWN AND RE-START. ENGINE HANGS AT 4 TO 6 PERCENT N2. FIRST START NORMAL. 2 L 7 2 4F RT A10CE 1996081500084 19960815 00084 EU 1996 8 15 96ZZZX3904 1 19960711 G 2435 03601015 BEARING LUCAS 23080005 BRAERO DH125 BAE125800A 1500285 EU START/GEN DR END SEAL FAILED B JAVR K NONE O OTHER IN INSP/MAINT 1 NE 01 208R 868 2349 NA1003 RECEIVED SEVERAL STARTER/GENERATOR UNITS OF THIS MODEL TYPE WITH DRIVE END BEARING SEALS DISLODGED AND BEARING LUBRICATI ON LOST. THIS PROBLEM HAS BEEN ADDRESSED IN THE PAST BY THE O.E.M. WITH P/N UPGRADES, BUT THE PROBLEM STILL SEEMS TO EX IST. SUBMITTER RECOMMENDS OVERHAUL BE PERFORMED IN LESS TIME THAN O.E.M. RECOMMENDED HOURS TO PREVENT BEARING FAILURE. THIS COULD COINSIDE WITH NORMAL BRUSH WEAR AT APPROXIMATELY 700 HOURS. 2 L 7 2 4F RT A3EU 1996081500085 19960815 00085 CE 1996 8 15 96ZZZX3905 1 19960725 G 2913 MX211919A PUMP VICKERS RKWELL NA265 NA26540 6402608 CE HYDRAULIC SYS SEAL FAILED D O OTHER K FLUID LOSS CR CRUISE 1 SO 16 303NT 72 28229 HYDRAULIC PUMP SHAFT SEAL FAILURE IN-FLIGHT 'WITHOUT INCIDENT', BUT ELECTRIC DRIVE MOTOR AND SURROUNDING AFT FUSELAGE AR EA TO TAIL WAS SATURATED WITH APPROXIMATELY 2 GALLONS OF FLUID WHICH POSED A SEVERE FIRE HAZARD. 2 L 7 2 4J A2WE 1996081500086 19960815 00086 NE 1996 8 15 96ZZZX3906 2 19960710 G 7230 COMPRESSOR RKWELL NA265 NA26540 6402608 CE PWA JT12 JT12A8 52042 NE ENGINE BINDING D K NONE O OTHER IN INSP/MAINT 1 SO 09 309NT 11970 1398 28261 P638364NB COMPRESSOR VERY DIFFICULT TO ROTATE AND SPOOL DOWN VERY SHORT. INTERNAL BINDING COULD BE FELT WHEN ROTATING BY HAND. T HIS IS A MULTI-STAGE UNIT, SO VISUAL INSPECTION/DETECTION OF A PARTICULAR PART FAILURE IS VERY DIFFICULT. NO FOD NOTED AND NO DAMAGE OR DEFECTS NOTED IN TURBINE HOT SECTION. ALL IN-FLIGHT AND GROUND TEST PARAMETERS NORMAL. 2 L 7 2 4J 4 J A2WE 1E9 1996081500087 19960815 00087 EU 1996 8 15 96ZZZX3907 1 19960624 G 2820 L96Z31201 CHECK VALVE AMD FALC50 FALCON50MYST 2730106 EU PLUNGER WASHER FAILED B EBVR K NONE O OTHER IN INSP/MAINT 1 GL 09 48HB 21442 233 UPON FUELING AIRCRAFT FOR LEAK CHECKS OF FEEDER TANKS, THE CENTER FEEDER TANK OVERFILLED AND VENTED OVERBOARD. DEFUELED ACFT TO TROUBLESHOOT. AFTER T/S, FOUND PLUNGER WASHER OF A CHECK VALVE LODGED IN THE LT FEEDER TANK FUELING VALVE. AP PARENTLY, THE WASHER WAS INITIALLY LODGED IN THE CENTER FEEDER TANK SYSTEM CAUSING THE OVERFILL, THEN MOVED THROUGH THE FUELING MANIFOLD TO THE LT FEEDER TANK FUELING VALVE DURING THE DEFUEL, AND SUBSEQUENT TROUBLESHOOTING. THIS WASHER IS HELD ON THE CHECK VALVE PLUNGER BY A POP RIVET. SUBMITTER RECOMMENDS ANALYSIS OF HOW MANY OF THESE CHECK VALVES HAVE FA ILED LIKE THIS AND POSSIBLE REPLACMENT WITH NEW STYLE OR IMPROVEMENT OF EXISTING VALVES. 2 L 7 3 4F A46EU 1996081500088 19960815 00088 CE 1996 8 15 96ZZZX3908 1 19960718 G 2720 1303800033 TRANSDUCER BEECH B300 B300 1159232 CE RUDDER BOOST FAILED B A GJQR A H UNSCHED LANDING DEACTIVATE SYST/CIRCUITS F FLT CONT AFFECTED CL CLIMB 1 NM 01 4S 15 56305141 FL107 ON DEPARTURE, PILOT REPORTED RUDDER BOOST APPLIED RIGHT RUDDER. HAD TO USE DISCONNECT BUTTON TO DISCONNECT RUDDER BOOST SYSTEM AND RETURNED AND LANDED. TROUBLESHOOTING REVEALED TRANSDUCER GIVING FALSE SIGNAL. REPLACED TRANSDUCER AND FUNC TIONAL TESTS WERE NORMAL. APPARENTLY, BEECH IS ENCOUNTERING AN EPIDEMIC OF PROBLEMS WITH THESE TRANSDUCERS. SINCE IT A FFECTS THE RUDDER FLIGHT CONTROL SYSTEM, SUBMITTER CONSIDERS THIS A FLIGHT SAFETY ISSUE. 2 L 7 2 4T RT A24CE 1996081500089 19960815 00089 CE 1996 8 15 96ZZZX3909 1 19960718 G 2720 1303800031 TRANSDUCER BEECH B300 B300 1159232 CE RUDDER BOOST FAILED B GJQR K NONE F FLT CONT AFFECTED NR NOT REPORTED 1 NM 01 4S 658 459 FL107 RUDDER BOOST INOPERABLE. LEFT SIDE, NO SIGNAL, HARD RIGHT PEDAL ALL THE TIME. REPLACED RUDDER BOOST TRANSDUCER, SYSTEM FUNCTIONAL TESTED NORMALLY. 2 L 7 2 4T RT A24CE 1996081500090 19960815 00090 EA 1996 8 15 96ZZZX3910 2 19960613 G 8530 LW16475 SPRING SEAT PIPER PA44 PA44180T 7104404 SO LYC O360 LTO360E1A6 41515 EA VALVE FAILED B PAIR O OTHER Y ENGINE STOPPAGE CR CRUISE 1 SO 05 8269T 229 448107022 RL00026674T THE OPERATOR INCURRED AN IN-FLIGHT FAILURE. INSPECTION REVEALED VALVE SEAT FAILED. SUBMITTER STATED THIS UNIT WAS NOT REPLACED DURING LAST OVERHAUL BECAUSE LYCOMING SB 447A FAILED TO LIST LTO-360-E1A6D AS AN EFFECTED ENGINE. SUBMITTER ST ATED AD 80-14-07 NEGLECTED TO ADDRESS THIS ENGINE MODEL POSSIBLY IN ERROR. 1 L 7 2 3O 3 O A19SO E26EA 1996081500091 19960815 00091 EA 1996 8 15 96ZZZX3911 2 19960717 G 7414 10357592 OIL SEAL S4LN200 HUGHES 269 TH55A 4471004 WP LYC O360 HIO360B1A 41514 EA MAG DRIVE END FAILED D O OTHER E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 WP 07 331SD 450 00349 291105 L333351A DURING TRAINING FLIGHT, ENGINE ROUGHNESS 'FELT' IN-FLIGHT; FOUND MAGNETO POINTS SATURATED WITH OIL. REPLACED MAGNETO WI TH REBUILT UNIT. 1 G 7 1 3R 3 O 1E10 1996081500092 19960815 00092 SW 1996 8 15 96ZZZX3912 1 19960725 G 2910 MS8001F200A HOSE 206076056103 BELL 204 UH1H 1181407 SW HYD SYSTEM CHAFED B A LS1R A UNSCHED LANDING F J K FLT CONT AFFECTED WARNING INDICATION FLUID LOSS CR CRUISE 1 EA 13 51AG 4164 7120178 DURING STRAIGHT AND LEVEL FLIGHT, PILOT NOTICED FLIGHT CONTROLS STARTING TO FEEL STIFF. THIS WAS IMMEDIATELY FOLLOWED B Y A DROP IN HYDRAULIC PRESSURE. PILOT LANDED ACFT SAFELY IN A FIELD. MECHANIC WAS DISPATCHED AND FOUND A HYDRAULIC LIN E HAD RUPTURED DUE TO CHAFING. IN ADDITION, HYD LINE PN 205-076-201-1 HAD A SMALL CRACK UNDER THE B-NUT AT THE COMPRESS ION FITTING. NEW LINES WERE INSTALLED, HYDRAULIC SYSTEM SERVICED, AND AIRCRAFT RETURNED TO SERVICE. 1 G 7 1 4U EXPA1G71 1996081500093 19960815 00093 SW 1996 8 15 96ZZZX3913 1 19960709 G 6730 2140760291 HOUSING 214076014101 BELL 214 214ST 1182106 SW SERVO ACTUATOR CORRODED B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 11 7098 CORROSION WAS FOUND DURING FLUORESCENT PENETRANT INSPECTION AND WAS REJECTED PER HR-TEXTRON TD-WP-101-5. 2 G 7 2 4U H10SW 1996081500094 19960815 00094 SW 1996 8 15 96ZZZX3914 1 19960709 G 6730 2140760291 HOUSING 2140761461 BELL 214 214ST 1182106 SW SERVO ACTUATOR CORRODED B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 11 580B CORROSION WAS FOUND DURING FLUORESCENT PENETRANT INSPECTION AND WAS REJECTED PER NR-TEXTRON TD-WP-101-5. 2 G 7 2 4U H10SW 1996081500095 19960815 00095 SW 1996 8 15 96ZZZX3915 1 19960709 G 6730 214060281 RETAINER 214076146001 BELL 214 214ST 1182106 SW SERVO ACUATOR CORRODED B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 11 549 CORROSION WAS FOUND DURING FLUORESCENT PENETRANT INSPECTION AND WAS REJECTED PER HR-TEXTRON TD-WP-101-5. 2 G 7 2 4U H10SW 1996081500096 19960815 00096 SW 1996 8 15 96ZZZX3916 1 19960709 G 6730 2140760291 HOUSING BELL 214 214ST 1182106 SW SERVO ACTUATOR CORRODED B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 11 7057 CORROSION WAS FOUND DURING FLUORESCENT PENETRANT INSPECTION AND WAS REJECTED PER HR-TEXTRON TD-WP-101-5. 2 G 7 2 4U H10SW 1996081500097 19960815 00097 CE 1996 8 15 96ZZZX3917 1 19960718 G 5520 50350056 FITTING CESSNA 402 402C 207590R CE RT ELEVATOR CRACKED E A K NONE O OTHER IN INSP/MAINT 1 NM 09 305AT 4720 402C0030 WHILE C/W CESSNA SB MEB 95-10, FOUND RT ELEVATOR FITTING CRACKED AT AREA WHERE THE TAPER PIN COMES THROUGH. SUBMITTER S UGGESTS THAT THESE FITTINGS ARE INSPECTED ANYTIME THE TAIL CONE IS REMOVED. 1 L 7 2 3O A7CE 1996081500098 19960815 00098 SO 1996 8 15 96ZZZX3918 1 19960716 G 5712 708475004 RIB PIPER PA28 PA28R201 7102816 SO LT WING CRACKED B A OG5R K NONE O OTHER IN INSP/MAINT 1 GL 21 172ND 5813 2837007 FOUND RIB IN LEFT WING WHEELWELL CRACKED. CRACK LOCATED IN RIB FLANGE RADIUS AT FORWARD LOWER CORNER WHERE RIB RIVETS/B OLTS TO SPAR. DRAG LINK KNUCKLE ALSO ATTACHES AT THIS POINT. 1 L 7 1 3O 2A13 1996081500099 19960815 00099 GL 1996 8 15 96ZZZX3919 3 19960725 G 6114 DB2248 HUB CESSNA 340 340A 2076405 CE HARTZL HCC3Y PHCC3YF2 GL MOUNT BOLTS CRACKED H S A K NONE O OTHER IN INSP/MAINT 1 CE 01 8636K 1661 340A0562 EB2248 PROPELLER WAS INSTALLED 7-25-96 AT HOUR METER 1362.6. PROPELLER WAS NEW AT TIME OF INSTALL. PROPELLER REMOVED WITH 166 1.4 HOURS TOTAL TIME. FIRST INDICATION OF DEFECT WAS GREASE ON FRONT OF ENGINE COWLING. FOUND APPROXIMATE 4 INCH LONG CRACK ON AFT HUB BY MOUNTING BOLTS. 1 L 7 2 3O 3A25 5 C P25EA 1996081500100 19960815 00100 SO 1996 8 15 96ZZZX3920 1 19960724 G 2730 7105602 SPRING PIPER PA31 PA31325 7103105 SO ELEVATOR FAILED G S K NONE O OTHER IN INSP/MAINT 1 GL 15 979SP 3786 317812015 FAILED ELEVATOR STRING WAS FOUND DURING 100-HOUR INSPECTION. 1 L 7 2 3O A20SO 1996081500102 19960815 00102 CE 1996 8 15 96ZZZX3922 1 19960626 G 2823 C2915030101 VALVE CESSNA 210 P210N 2073454 CE FUEL SELECTOR LEAKING D A K NONE K FLUID LOSS IN INSP/MAINT 1 NM 11 4515K 23 6566 P21000205 FOLLOWING INSTALLATION OF FUEL VALVE, A FUEL SMELL WAS NOTICED IN AIRCAFT CABIN. INVESTIGATION REVEALED FUEL LEAKING FR OM THE AFT PLUG ADJACENT TO THE FUEL LINE FITTING PORT WHICH IS AFT WHEN VALVE IS INSTALLED. THIS PLUG IS APPARENTLY IN STALLED DURING MANUFACTURE OF THE FUEL VALVE, AND ONLY A CIRCULAR OUTLINE CAN BE DISTINGUISHED. IT IS DIFICULT TO SEE. THE CAUSE OF THIS LEAKAGE IS UNKNOWN, ALTHOUGH THE PLUG SEEMED TO BE TIGHT. 1 H 7 1 3O 3A21 1996081500104 19960815 00104 SO 1996 8 15 96ZZZX3924 1 19960725 G 7120 6129400 BRACKET PIPER PA25 PA25 7102502 SO ENGINE MOUNT BROKEN D S A K NONE O OTHER IN INSP/MAINT 1 NE 05 6270Z 3815 25335 TWO OF FOUR ENGINE MOUNT BRACKETS CRACKED AT BOLT HOLES. ONE MOUNT BRACKET BROKE IN HALF BY HAND WHEN REMOVED. FATIGUE SUSPECT CAUSE. THESE BRACKETS ALLOW THE ENGINE TO SWING AWAY FROM THE FIRE WALL. FAILURE IN-FLIGHT WOULD BE CATASTROP HIC. SUBMITTER RECOMMENDS GOOD INSPECTION OF MOUNTS. 1 L 7 1 3O 2A10 1996081500105 19960815 00105 SO 1996 8 15 96ZZZX3925 1 19960725 G 3211 AN626A BOLT PIPER PA25 PA25 7102502 SO MLG RT FWD SHEARED D A K NONE O OTHER IN INSP/MAINT 1 NE 05 6270Z 25335 RIGHT FORWARD LANDING GEAR BOLT WAS FOUND WITH HEAD SHEARED COMPLETELY OFF DURING ANNUAL INSPECTION OF WING ATTACH FITTI NGS. RECOMMEND GOOD INSPECTION OF GEAR ATTACH AREA. 1 L 7 1 3O 2A10 1996081500106 19960815 00106 CE 1996 8 15 96ZZZX3926 1 19960607 G 3230 98820201 PIN CESSNA 210 T210N 2073456 CE NLG DOWNLOCK FAILED D P O OTHER J WARNING INDICATION AP APPROACH 1 CE 05 6939N 1993 21063161 PILOT COULD NOT GEAR DOWN GREEN LIGHT AFTER REPEATED CYCLES AND EMERGENCY EXTENSION. AFTER FAILURE AND ON LANDING, ACFT PLACED ON JACKS AND GEAR CYCLED NORMAL UP AND DOWN OVER 20 TIMES WITH NO APPARENT PROBLEM. REMOVED NOSE GEAR ACTUATOR TO BENCH TEST, FOUND BOTH DOWNLOCK PINS IN NOSE GEAR ACTUATOR BEARING BROKEN AT ROLL PIN LOCATION. THE BROKEN PINS WOUL D NOT ALLOW ACTUATOR TO ENGAGE DOWNLOCK HOOKS ONTO PINS. JAM NUT ON ACTUATOR SHAFT WOULD NOT PASS TO ALLOW ACTUATOR TO FULLY RETRACT. THE ONLY WAY TO CHECK FOR THIS PROBLEM IS TO UNLOCK NOSE GEAR AND STOP IN MID-CYCLE SO AS TO ALLOW ACCES S TO PINS TO CHECK FOR MOVEMENT. 1 H 7 1 3O 3A21 1996081500107 19960815 00107 CE 1996 8 15 96ZZZX3927 1 19960612 G 3230 0842102497 BELLCRANK CESSNA 310 310N 2074234 CE NLG FAILED D K NONE O OTHER NR NOT REPORTED 1 WP 05 743JR 4400 310N0116 NOSE GEAR IDLER BELLCRANK LINKAGE FAILURE. 1 L 7 2 3O 3A10 1996081500108 19960815 00108 EA 1996 8 15 96ZZZX3928 2 19960722 G 7421 REM37BY SPARK PLUG PIPER PA38 PA38112 7103812 SO LYC O235 O235L2C 41505 EA NR 4 CYLINDER FOULED D A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CR CRUISE 1 SW 09 2416B 50 3879A0052 L1758615 WHILE FLYING, PILOT EXPERIENCED PARTIAL LOSS OF ENGINE RPM AND MADE A PRECAUTIONARY LANDING IN A FIELD. UPON INVESTIGAT ION, FOUND THE BOTTOM SPARK PLUG IN NR 4 CYLINDER WAS NOT GAPPED PROPERLY. A PIECE OF CARBON GOT STUCK BETWEEN THE ELEC TRODES OF THE SPARK PLUG ALLOWING IT TO BECOME OIL FOULED. THERE WAS NO DAMAGE TO AIRCRAFT OR PERSONS. 1 L 7 1 3O 3 O A18SO E223 1996081500109 19960815 00109 EA 1996 8 15 96ZZZX3929 2 19960701 G 7322 105267 CARBURETOR CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA FINGER SCREEN BLOCKAGE D K NONE R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 GL 05 3281R 15284363 L2106415 PARTIAL POWER LOSS. FINGER SCREEN WAS FOUND PARTIALLY FILLED WITH A LINT-LIKE SUBSTANCE TO THE POINT THAT FUEL FLOW WAS RESTRICTED. THE FUEL SYSTEM WAS CHECKED BY DRAINING FUEL FROM SUMPS, GASCOLATOR, FUEL LINE, CARBURETOR FLOAT BOWL. NO FURTHER CONTAMINATION WAS FOUND. GASCOLATOR WAS DISASSEBLED, AND SCREEN WAS FOUND TO BE CLEAN. THE GASOLATOR HAD FAIL ED TO TRAP CONTAMINATION. SYSTEM REASSEMBLED, AIRCRAFT GROUND RUN AND TEST FLOWN. OPERATION NORMAL, RETURNED TO SERVIC E. 1 H 7 1 3O 3 O NT 3A19 E223 1996081500110 19960815 00110 SO 1996 8 15 96ZZZX3930 1 19960718 G 3210 2082900 STUD PIPER PA24 PA24250 7102404 SO MLG SIDE BRACE CRACKED B R7LR K NONE O OTHER IN INSP/MAINT 1 WP 25 6476P 241592 ON C/W AD 95-20-07, BOTH MLG SIDE BRACE STUDS WERE FOUND CRACKED BY MPI. ONE STUD WAS NEW TYPE 487-596 WITH ZERK GREASE FITTING. CRACKS NOT VISIBLE WITHOUT MPI. CRACKS AT SHANK RADIUS. 1 L 7 1 3O 1A15 1996081500112 19960815 00112 NE 1996 8 15 96ZZZX3932 2 19960722 G 8530 399354 CYLINDER SCWZER G164 G164A 3952704 EA PWA R985 R985AN14B 52008 NE NR 1 CYLINDER CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 11 8605H 5000 1157 1432 13782 ENGINE INSPECTION FOUND NR 1 CYLINDER HEAD HAD CRACKED FROM FORWARD SPARK PLUG BOSS UP OVER CENTER OF CYLINDER HEAD AROU ND BELOW EXHAUST PORT, FORWARD AT CYLINDER HEAD/BARREL ATTACH AREA, BACK TO LOWER SIDE OF FORWARD SPARK PLUG BOSS. 1 Q 7 1 3R 3 R 1A16 5E1 1996081500113 19960815 00113 1996 8 15 96ZZZX3933 4 19960722 G 2562 AK450 ELT AMERIKING CESSNA 150 150F 2071814 CE G-SWITCH FAILED D K NONE O OTHER IN INSP/MAINT 1 NE 05 8749S 5 4502286 15062049 ELT SYSTEM INSTALLED AND INSPECTION IAW FAR 91.207.0. ELT SYSTEM CHECKED 60 DAYS LATER BY DEPRESSING TEST SWITCH. TEST LIGHT CAME ON, BUT NO AUDIO HEARD ON 121.5. ALSO 'G' SWITCH TURNS LIGHT ON, BUT NO AUDIO ON FREQUENCY. 1 H 7 1 3O 3A19 1996081500114 19960815 00114 GL 1996 8 15 96ZZZX3934 1 19960716 G 3221 SUPPORT AMTR LNCAIR 235LANCAIR 05612ML GL NLG BROKEN B A AW4R O OTHER J WARNING INDICATION AP APPROACH 1 WP 11 880RS 237 88 WHEN PILOT WENT TO LOWER GEAR DURING APPROACH, THE HANDLE ON THE GEAR CONTROL SWITCH BROKE OFF PREVENTING GEAR FROM LOWE RING USING THE NORMAL SYSTEM. MANUAL GEAR EXTENSION WAS INITIATED, BUT NOSE GEAR FAILED TO EXTEND. LANDING WAS MADE WI TH NLG RETRACTED. TWO PROBLEMS WERE NOTED UPON INITIAL EXAMINATION WHEN LOWER COWL WAS REMOVED, THE ENGINE MOUNT/NOSE GEAR SUPPORT WAS FOUND BROKEN AT LEFT SIDE OF NLG. IT IS SUSPECTED THIS BROKEN TUBE ALLOWED NLG TO SHIFT POSITION ENOUG H TO JAM THE WHEELWELL PREVENTING IT FROM MOVING INTO THE DOWN POSITION WHEN MANUAL EXTENSION SYSTEM WAS USED. CAUSE OF CRACKED TUBE HAS NOT BEEN DETERMINED. LAST CONDITION INSPECTION COMPLETED 10-95 AT 177.6 HOURS. 1 L 7 1 30 RT EXPA1L71 1996081500115 19960815 00115 GL 1996 8 15 96ZZZX3935 1 19960716 G 3230 SWITCH AMTR LNCAIR 235LANCAIR 05612ML GL MLG CONTROL FAILED B A AW4R O OTHER J WARNING INDICATION AP APPROACH 1 WP 11 880RS 237 88 WHEN PILOT WENT TO LOWER GEAR DURING APPROACH, THE HANDLE ON THE GEAR CONTROL SWITCH BROKE OFF PREVENTING GEAR FROM LOWE RING USING THE NORMAL SYSTEM. MANUAL GEAR EXTENSION WAS INITIATED, BUT NOSE GEAR FAILED TO EXTEND. LANDING WAS MADE WI TH NLG RETRACTED. 1 L 7 1 30 RT EXPA1L71 1996081500116 19960815 00116 1996 8 15 96ZZZX3936 1 19960723 G 2822 2B632 PUMP AIRBORNE FUEL BOOST ARMATURE FAILED D K NONE O OTHER IN INSP/MAINT 1 GL 13 12W322 INSPECTION FOUND ARMATURE OUT OF DYNAMIC BALANCE CAUSING PREMATURE FAILURE OF THE PUMP. 1996081500117 19960815 00117 1996 8 15 96ZZZX3937 1 19960723 G 2822 2B638 PUMP AIRBORNE FUEL BOOST ARMATURE FAILED D K NONE O OTHER IN INSP/MAINT 1 GL 13 12A23 INSPECTION FOUND ARMATURE OUT OF DYNAMIC BALANCE CAUSING PREMATURE FAILURE OF THE PUMP. 1996081500118 19960815 00118 1996 8 15 96ZZZX3938 1 19960723 G 2822 2B632 PUMP AIRBORNE FUEL BOOST ARMATURE FAILED D K NONE O OTHER IN INSP/MAINT 1 GL 13 12W342 ARMATURE OUT OF DYNAMIC BALANCE CAUSING PREMATURE FAILURE OF THE PUMP. 1996081500119 19960815 00119 1996 8 15 96ZZZX3939 1 19960723 G 2822 2B632 PUMP AIRBORNE FUEL BOOST ARMATURE FAILED D K NONE O OTHER IN INSP/MAINT 1 GL 13 12W355 ARMATURE OUT OF DYNAMIC BALANCE CAUSING PREMATURE FAILURE OF THE PUMP. 1996081500120 19960815 00120 1996 8 15 96ZZZX3940 1 19960723 G 2822 2B632 PUMP AIRBORNE FUEL BOOST ARMATURE FAILED D K NONE O OTHER IN INSP/MAINT 1 GL 13 4A149 ARMATURE OUT OF DYNAMIC BALANCE CAUSING PREMATURE FAILURE OF THE PUMP. 1996081500121 19960815 00121 1996 8 15 96ZZZX3941 1 19960723 G 2822 2B636 PUMP AIRBORNE FUEL BOOST ARMATURE FAILED D K NONE O OTHER IN INSP/MAINT 1 GL 13 5D72 ARMATURE OUT OF DYNAMIC BALANCE CAUSING PREMATURE FAILURE OF THE PUMP. 1996081500122 19960815 00122 1996 8 15 96ZZZX3942 1 19960701 G 2822 2B663 PUMP AIRBORNE FUEL BOOST SHAFT DAMAGED D K NONE O OTHER IN INSP/MAINT 1 GL 13 10AC101 ARMATURE SHAFT DAMAGED BY SPACER. 1996081500123 19960815 00123 1996 8 15 96ZZZX3943 1 19960701 G 2822 2B663 PUMP AIRBORNE FUEL BOOST SHAFT DAMAGED D K NONE O OTHER IN INSP/MAINT 1 GL 13 10AC114 ARMATURE SHAFT DAMAGED BY SPACER, DEEP GROOVE WORN IN SHAFT. 1996081500239 19960815 00239 GL 1996 8 15 96ZZZX3944 2 19960729 G 7230 6898607 BEARING 6896028 BELL 206 206L 1181522 SW ALLSN 250C 250C28B 03013 GL NR 1 FAILED B KUVR O OTHER J WARNING INDICATION NR NOT REPORTED 1 SO 19 165BH 2509 R1747 45249 CAE860728 AIRCRAFT EXPERIENCED 3 CHIP LIGHTS WITHIN 50 HOURS. AIRCRAFT GROUNDED PER ALLISON MM. UPON INVESTIGATION FOUND NR 1 BE ARING CAGE BROKEN INTO PIECES AND BEARING FELL APART. SIMPLE MECHANICAL FAILURE THAT COULD HAVE CAUSED ENGINE FLAME-OUT . 1 G 7 1 3U 3 U H2SW E1GL 1996081500240 19960815 00240 EA 1996 8 15 96ZZZX3945 2 19960718 G 7260 330170501 HOUSING 330160203 SKRSKY S76 S76B 8143007 NE PWA PT6 PT6B36 52043 EA NR 1 ENG AGB DAMAGED B EGRR K NONE O OTHER IN INSP/MAINT 1 EA 17 22CP 999 760425 36207 AIRCRAFT TT: 999.1 HOURS. NR 1 ENGINE TT, 999.1 HOURS. DURING REPLACEMENT OF NR 1 HMU, FOUND CORROSION DAMAGE IN THE BORE ON THE HOUSING WHERE HMU IS INSTALLED. CORROSION DAMAGE WAS AT THE 6 O'CLOCK POSITION, AND RANGED FROM MINOR TO SO ME DEEP PITS UP TO .140 INCH DEEP. ENGINE IS BEING REMOVED AND SENT FOR EVALUATION AND REPAIR. 1 G 7 2 4U 4 U H1NE E4EA 1996081500729 19960815 00729 CE 1996 8 15 96ZZZX3994 1 19960717 G 2150 585550273 PULLEY BEECH 58 58 1152740 CE AIR COND IDLER BEARING WORN D S K NONE O OTHER IN INSP/MAINT 1 GL 03 43240 151 TH1740 AIR CONDITIONER IDLER PULLEY WAS VERY LOOSE. FOUND THE PULLEY BOSS THAT FITS INSIDE OF THE BEARING (PN 203SZZ) WAS VERY WORN. BEARING COULD BE TURNED BY HAND, B4UT WAS ROUGH FEELING WHEN ROTATED. SUBMITTER SUGGESTS POSSIBLY A BETTER QUAL ITY BE6ARING AND A BETTER FIT BETWEEN THE PULLEY AND THIS BEARING WOULD HELP. 1 L 7 2 3O 3A16 1996081500730 19960815 00730 EA 1996 8 15 96ZZZX3995 2 19960702 G 8520 67204 LOCKWASHER BELL 47 47G5 1181032 SW LYC O435 VO435B1A 41516 EA CRANKSHAFT FAILED D L A A UNSCHED LANDING Y ENGINE STOPPAGE TO TAKEOFF 1 WP 17 7938J 3550 1035 25043 L359731 DURING TROUBLESHOOTING, METAL IN OIL SCREEN PROBLEM, A TANG WAS FOUND IN SUMP SUCTION SCREEN, BUT WAS UNABLE TO POSITIVE LY IDENTIFY THE SOURCE OF METAL. TENTATIVELY IDENTIFIED AND HELICOPTER RETURNED TO SERVICE. 6.5 HOURS LATER, THE ENGIN E QUIT SUDDENLY ON TAKEOFF. FORTUNATELY, NO DAMAGE TO HELICOPTER. ON INVESTIGATION OF PROBLEM, FOUND CRANKSHAFT GEAR A ND PARTS IN ACCESSORY HOUSING. SUSPECT IMPROPER INSTALLATION AT LAST OVERHAUL. 1 G 7 1 3O 3 O 2H3 E279 1996081500731 19960815 00731 SO 1996 8 15 96ZZZX3996 1 19960710 G 5330 99470001 SKIN PIPER PA34 PA34200 7103405 SO FS 215 CRACKED D L K NONE O OTHER IN INSP/MAINT 1 GL 15 94PG 3240 347450064 PILOTS PRE-FLIGHT INSPECTION FOUND RT SIDE OF AIRCRAFT AT STA 215 WITH SKIN CRACKED. FURTHER INVESTIGATION, STRINGER CR ACKED AT BULKHEAD STA 215. SUBMITTER STATED THIS AIRCRAFT USED FOR MULTI-ENGINE TRAINING, SUSPECT SINGLE ENGINE FLIGHT FATIGUES EMPENNAGE STRUCTURE. 1 L 7 2 3O A7SO 1996081500732 19960815 00732 SO 1996 8 15 96ZZZX3997 1 19960710 G 5313 78608003 STRINGER PIPER PA34 PA34200 7103405 SO BLKHD FS 215 CRACKED D K NONE O OTHER IN INSP/MAINT 1 GL 15 94PG 3240 347450064 PILOTS PRE-FLIGHT INSPECTION FOUND RT SIDE OF AIRCRAFT AT STA 215 WITH SKIN CRACKED. FURTHER INVESTIGATION, STRINGER CR ACKED AT BULKHEAD STA 215. SUBMITTER STATED THIS AIRCRAFT USED FOR MULTI-ENGINE TRAINING, SUSPECT SINGLE ENGINE FLIGHT FATIGUES EMPENNAGE STRUCTURE. 1 L 7 2 3O A7SO 1996081500733 19960815 00733 SO 1996 8 15 96ZZZX3998 1 19960719 G 5260 159AM100573 JACKSHAFT GULSTM G1159 G1159 3953505 SO MAIN ENTRY DOOR CRACKED B P A RO3R K NONE O OTHER IN INSP/MAINT 1 CE 03 2MIL 11611 045 WHILE CLOSING ACFT MAIN ENTRY DOOR, NOTED DOOR WOULD NOT PROPERLY CLOSE AND LOCK. DURING INVESTIGATION AND T/S OF MAIN ENTRY DOOR, JACKSHAFT ASSY PN 159AM10057-3 WAS FOUND TO HAVE A FRACTURE CRACK RUNNING THE FULL LENGTH. OLD JACKSHAFT WA S REMOVED AND REPLACED WITH P/N 159AM10057-5. AFTER FURTHER RESEARCH, ASC NR 146 ADDRESSES REWORK OF AIRSTAIR DOOR. TH IS ASC PROVIDES INSTRUCTION FOR REMOVAL AND REPLACEMENT OF JACKSHAFT AND ADDITIONAL COMPONENTS REQUIRED FOR REPLACEMENT OF NEW JACKSHAFT P/N. REMOVAL AND REPLACEMENT OF THE JACKSHAFT BY ITSELF COULD CAUSE FURTHER DAMAGE WITHOUT CHANGING AL REQUIRED COMPONENTS AS CALLED OUT IN ASC 146. CAUSE OF FAILURE IS UNKNOWN. 2 L 7 2 4F RT A12EA 1996081500734 19960815 00734 GL 1996 8 15 96ZZZX3999 3 19960716 G 6114 HUB MCAULY 3AF32C 3AF32C87 GL SOCKET PLUGS MISSING B F3PR K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 15 727049 INSPECTION FOUND IN ALL 3 BLADE SOCKETS WHERE BLADE NUT AND HUB SOCKETS MEET, EXPANSION PLUGS WERE NOT INSTALLED. PROPE LLER WAS RECENT AD COMPLIANCE BY SHOP IN KANSAS. 5 C P22EA 1996081500735 19960815 00735 GL 1996 8 15 96ZZZX4000 3 19960716 G 6114 HUB MCAULY 3AF32C 3AF32C87 GL SOCKET PLUGS MISSING B F3PR K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 15 722019 INSPECTION FOUND IN ALL 3 BLADE SOCKETS WHERE BLADE NUT AND HUB MEET, EXPANSION PLUGS WERE NOT INSTALLED. EXAMINATION S HOWS THAT PREVIOUS HOLES WERE DRILLED TOO CLOSE TOGETHER WHICH REJECTS HUB. ALSO, REAR HUB ADAPTER USED APPEARS TO BE B OGUS. PROPELLER WAS FRESH AD COMPLIANCE FROM SHOP IN KANSAS. 5 C P22EA 1996081500736 19960815 00736 SO 1996 8 15 96ZZZX4001 1 19960701 G 3213 BRACE PIPER PA34 PA34200T 7103406 SO MLG STRUT BINDING D K NONE O OTHER IN INSP/MAINT 1 SW 99 38679 347770332 INSPECTION FOUND BINDING ON GEAR STRUT BRACE. SUBMITTER STATED NEEDS TO BE REAMED TO FREE MOVEMENT. 1 L 7 2 3O A7SO 1996081500737 19960815 00737 CE 1996 8 15 96ZZZX4002 1 19960725 G 2821 331995 STRAINER CESSNA 180 180 2072602 CE FUEL SYSTEM MISSING D K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 25 3122C 3000 30921 PILOT REPORTED AFTER SOME TURBULENCE ON FINAL APPROACH, ENGINE QUIT. ON INVESTIGATION, DISCOVERED THE FUEL STRAINER BOW L AND CAP WERE MISSING. SUBMITTER RECOMMENDATION: PILOTS BE AWARE THAT FUEL DRAINS NEED TO BE SAFETIED AND CHECKED DUR ING PRE-FLIGHT. 1 H 7 1 3O NC 5A6 1996081500738 19960815 00738 SO 1996 8 15 96ZZZX4003 1 19960629 G 3230 9572400 MOUNT ASSY PIPER PA34 PA34200 7103405 SO NLG HYD JACK FAILED D K NONE O OTHER LD LANDING 1 WP 01 4484T 5662 347250110 NOSE GEAR COLLAPSE UNDER FULL POWER APPLICATON DURING A TOUCH-AND-GO LANDNG. MOUNT ASSY APPEARS TO HAVE FAILED AT BOLT HOLE, INBD SIDE, WHERE IT CONNECTS TO RETRACT LINK PN 9571200. SUSPECT REPEATED RETRACTION CYCLES CAUSED CRACK TO PROPA GATE FROM BOLT HOLE (FOR AN 23-25) FORWARD TO EDGE OF PART. AIRCRAFT WAS SEEN ON PREVIOUS LANDING TO HIT ON NOSE WHEEL FIRST. 1 L 7 2 3O A7SO 1996081500739 19960815 00739 SO 1996 8 15 96ZZZX4004 1 19960716 G 5712 78475005 RIB PIPER PA28 PA28R201 7102816 SO RT WING CRACKED B OG5R K NONE O OTHER IN INSP/MAINT 1 GL 21 170ND 6357 2837005 INSPECTION FOUND RIB IN WHEELWELL CRACKED. CRACK LOCATED IN RIB FLANGE RADIUS AT FORWARD LOWER CORNER WHERE RIB RIVETS/ BOLTS TO SPAR. DRAG LINK KNUCKLE ALSO ATTACHES AT THIS POINT. 1 L 7 1 3O 2A13 1996081500740 19960815 00740 CE 1996 8 15 96ZZZX4005 1 19960724 G 7331 543015 BRACKET CESSNA 182 TR182 2072735 CE TRANSDUCER MOUNT FAILED D K NONE O OTHER IN INSP/MAINT 1 CE 05 6323T 147 R18201480 FUEL FLOW TRANSDUCER MOUNT FAILED AFTER 147 HOURS OF OPERATION. SUBMITTER STATED LOCATION OF MOUNT SHOULD BE REVISED TO STRENGTHEN MOUNTING TO PREVENT BREAKAGE OF THE BRACKET. 1 H 7 1 3O 3A13 1996081500741 19960815 00741 1996 8 15 96ZZZX4006 4 19960701 G 3416 3431 CASTING UNITEDINST 5934P1 ATLIMTER CREEP B EI4R K NONE O OTHER IN INSP/MAINT 1 SO 15 THIS INSTRUMENT WAS A NEW FACTORY SEALED ALTIMETER. TWO SHAFT END-SHAKES WERE UNDER THE MINIMUM .0020 INCH CALLED OUT I N THE OVERHAUL MANUAL. THEY MEASURED .0006 INCH AND .0010 INCH. THE MANUFACTURER HAS INDICATED AN END-SHAKE OF .0004 I NCH OR LESS CAN CAUSE A POINTER HANG-UP DURING A NORMAL SPECIFIED COLD TEST. END-SHAKE CHANGES OF .0002 INCH TO .0003 I NCH HAVE BEEN MEASURED DURING DIFFERENT PRESSURE SETTINGS ON THE ALTIMETER. 1996081500742 19960815 00742 EA 1996 8 15 96ZZZX4007 2 19960719 G 8520 75154 STUD PIPER PA28 PA28161 7102803 SO LYC O320 O320D3G 41508 EA NR 4 BEARING CORRODED B OG5R K NONE O OTHER IN INSP/MAINT 1 GL 21 145ND 3197 796 2841226 RL1708539A DURING ENGINE TEAR DOWN FOLLOWING ACCIDENT, CRANKCASE HALF NUT ON NR 4 BEARING STUDS SEIZED RESULTING IN STUD BACKING OU T OF CRANKCASE. UPON REMOVAL, FOUND BOTH NR 4 BEARING CRANKCASE STUDS HEAVILY CORRODED/RUSTED. ALSO, HAD GLASS BEADS I N STUD RECEPTACLES. ENGINE WAS FACTORY OVERHAULED 11-18-94, INSTALLED 1-95. 1 L 7 1 3O 3 O 2A13 E274 1996081500743 19960815 00743 CE 1996 8 15 96ZZZX4008 1 19960729 G 1100 MARKING BEECH 36 A36 1151604 CE STAB ELEV TRIM MISSING D K NONE W INADEQUATE Q C IN INSP/MAINT 1 CE 03 4572S E744 AIRCRAFT RETURNED HOME AIRPORT AFTER REPAINTING. WHILE PERFORMING WALK-AROUND, NOTICED REQUIRED MARKINGS (STAB TRIM ACT UATOR) NOT IN PLACE PER AD 91-17-01. PAINT SHOP HAD COVERED THESE MARKINGS AND NOT REINSTALLED THEM. 1 L 7 1 3O 3A15 1996081500744 19960815 00744 1996 8 15 96ZZZX4009 2 19960530 G 7414 M3975 COIL SLICK 4381 MAGNETO FAILED B RL4R K NONE O OTHER IN INSP/MAINT 1 SO 17 92050067 MAGNETO SENT TO ACCESSORY SHOP TO T/S BECAUSE OF POOR RUNNING. FOUND SECONDARY WINDING OPEN IN COIL. SUBMITTER STATED ONCE AGAIN, SLICK COILS SEEM TO BE WEAKEST PART OF MAGNETO. 1996081500745 19960815 00745 GL 1996 8 15 96ZZZX4010 3 19960729 G 6111 PROPELLER CESSNA 402 402B 207590P CE MCAULY 3AF32C 3AF32C87 GL BLADE BEARINGS DRY B B2PR K NONE O OTHER IN INSP/MAINT 1 SO 17 350SP 6669 972 402B0580 776724 PROPELLER WAS EXPERIENCING SERVICE DIFFICULTIES. UPON REMOVAL, DISASSEMBLY AND INSPECTION, NOTED ALL OIL BATH PARTS HAD AN EXCESSIVE CLAY-LIKE SLUDGE BUILD-UP. ALL BEARING RACES WERE VOID OF GREASE AND SEVERELY RUSTED. THESE FINDINGS WOU LD DIRECTLY IMPEDE THE PROPELLERS ABILITY TO CHANGE PITCH. ROUTINE MAINTENANCE IS RECOMMENDED TO AVOID THIS PROBLEM IN THE FUTURE. 1 L 7 2 3O A7CE 5 C P22EA 1996081500746 19960815 00746 CE 1996 8 15 96ZZZX4011 1 19960725 G 3210 BOLT PIPER PA24 PA24180 7102402 CE MLG BRACE STUD CRACKED B DP2R K NONE O OTHER IN INSP/MAINT 1 SW 05 SURPLUS PARTS INSPECTED IAW AD 95-20-07, 1 OF 3 REJECTED DUE TO CRACK NEAR SHANK TO HEAD. APPROXIMATELY .25 INCH CIRCUM FERENCE. 1 L 7 1 3O NT 1A15 1996081500747 19960815 00747 CE 1996 8 15 96ZZZX4012 1 19960725 G 3210 BOLT PIPER PA24 PA24180 7102402 CE MLG BRACE STUD CRACKED B S DP2R K NONE O OTHER IN INSP/MAINT 1 SW 05 7214P 3500 242384 ONE BOLT REJECTED. INSPECTED IAW AD 95-20-07. MAGNETIC PARTICLE INSPECTION REVEALED LINEAR CRACK-LIKE INDICATION (CIRC UMFERENCIAL) NEAR SHANK TO HEAD RADIUS. 1 L 7 1 3O NT 1A15 1996081500748 19960815 00748 1996 8 15 96ZZZX4013 1 19960801 G 7810 62749 GASKET CONT A65 A658 17003 SO NR 2/3 CYL EXH MISMANUFACTURED D P K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 15 NEW EXHAUST GASKET IS MISMANUFACTURED .032 INCH LARGER THAN ORIGINAL. IT WILL FIT OK ON CYLINDERS 1 AND 4, BUT DUE TO C LEARANCE REQUIRED FOR FIT, IT IS TOO LARGE FOR CYLINDERS 2 AND 3. 3 O E205 1996081500749 19960815 00749 CE 1996 8 15 96ZZZX4014 1 19960808 G 3230 16001260 BREAKER BEECH B300 B300 1159232 CE MLG TRIPPED D A O OTHER J WARNING INDICATION AP APPROACH 1 NM 01 4S 11 FL107 AIRCRAFT ARRIVED AT DESTINATION AND REQUIRED LANDING GEAR TO BE PUMPED DOWN. INVESTIGATION REVEALED 60-AMP CIRCUIT BREA KER HAD TRIPPED. THIS IS POTENTIALLY AN ACCIDENT WAITING TO HAPPEN WHEN THE CREW HAS NO INDICATION THAT THIS 60-AMP BRE AKER LOCATED OUT IN THE WING HAS TRIPPED. 2 L 7 2 4T RT A24CE 1996081500750 19960815 00750 NE 1996 8 15 96ZZZX4015 2 19960730 G 7261 31B360801 PUMP LEAR 60 60LEAR 5170707 CE PWA 305 PW305 NE LT ENG OIL HOUSING CRACKED D K NONE K FLUID LOSS IN INSP/MAINT 1 SW 05 65BL 371 17A861 054 305218 EXCESSIVE OIL LEAK ON LEFT ENGINE. FOUND OIL PUMP HOUSING CRACKED AT UPPER LEFT BOLT HOLE AREA. SUBMITTER STATED THIS IS TURNING INTO A FLEET-WIDE CONCERN AS THIS CAN CAUSE AN ENGINE SHUTDOWN IN FLIGHT. OTHER OPERATORS HAVE EXPERIENCED T HIS SAME CRACK. AD RECOMMENDED. 2 L 7 2 4F 4 F RT A10CE E35NE 1996081500751 19960815 00751 NE 1996 8 15 96ZZZX4016 2 19960606 G 7230 798209 BLADE PWA JT8 JT8D17 52049 NE HPC STAGE 9 CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 99 709688 AFTER DISASSEMBLY OF THE 9TH STAGE COMPRESSOR DISK, FOUND 3 BLADES WITH CRACKS IN THE ROOTS. THESE CRACKS ARE ON THE CO NCAVE SIDE OF THE BLADE, BEGINS AT THE TRAILING EDE OF THE ROOTS, AND RUNS ALONG THE PRESSURE SIDE. ONE OF THESE BLADES IS ALMOST TOO LOOSE, NEARLY A THIRD OF THE ROOT. 4 F E2EA 1996081500752 19960815 00752 NE 1996 8 15 96ZZZX4017 2 19960515 G 7250 596968 SPACER PWA JT8 JT8D15 52051 NE TURB RING SEAL DISPLACED D K NONE O OTHER IN INSP/MAINT 1 SW 99 708355 DURING DISASSEMBLY OF NGV3, FOUND THE RING SPACER AIR SEAL, PN 596968, HAD DEPARTED FROM HOUSING. THIS RING WAS FOUND B ETWEEN DISK AND NGV3. DAMAGE (IMPACTS, CRACS, ETC.) ARE VISIBLE ON STAGE 2 BLADES AND STAGE 3 NGVS. 4 F E2EA 1996082200061 19960822 00061 NM 1996 8 22 96ZZZX4018 1 19960710 G 5755 651734748 SPOILER BOEING 727 727 1384001 NM SKINS DELAMINATED B IU6D K NONE O OTHER IN INSP/MAINT 1 NM 01 RR2502 ENTIRE HONEYCOMB CORE IS CORRODED. BEARINGS, BUSHINGS, SEALS, AND ATTACHING HARDWARE SEVERELY WORN. DELAMINATION ON UP PER AND LOWER SKINS. 2 L 7 3 4F A3WE 1996082200062 19960822 00062 NM 1996 8 22 96ZZZX4019 1 19960710 G 5755 651734748 SPOILER BOEING 727 727 1384001 NM SKINS DELAMINATED B IU6D K NONE O OTHER IN INSP/MAINT 1 NM 01 2402 LEFT AND RIGHT SPOILER STOPS WORN BEYOND ALLOWABLE LIMITS. UPPER AND LOWER SKINS SEVERELY DELAMINATED. ENTIRE HONEYCOM B CORE IS CORRODED. INTERNAL DOUBLER HAS A PREVIOUS REPAIR THAT IS NOT PER TECHNICAL DATA. BEARINGS, BUSHINGS, SEALS, AND ATTACH HARDWARE ARE WORN BEYOND LIMITS. 2 L 7 3 4F A3WE 1996082200063 19960822 00063 NM 1996 8 22 96ZZZX4020 1 19960710 G 5755 651734748 SPOILER BOEING 727 727 1384001 NM SKINS CORRODED B IU6D K NONE O OTHER IN INSP/MAINT 1 NM 01 RR2503 SEVERAL DELAMINATIONS ON UPPER AND LOWER SKINS. BOTH SURFACES HAVE NUMEROUS DENTS. 2 L 7 3 4F A3WE 1996082200064 19960822 00064 NM 1996 8 22 96ZZZX4021 1 19960710 G 5755 651734748 SPOILER BOEING 727 727 1384001 NM SKIN DELAMINATED B IU6D K NONE O OTHER IN INSP/MAINT 1 NM 01 2348 LOWER SKIN DELAMINATED ALONG ENTIRE LENGTH OF LEADING EDGE. BUSHINGS, BEARINGS, SEALS, ATTACHING HARDWARE ARE EXCESSIVE LY WORN. 2 L 7 3 4F A3WE 1996082200065 19960822 00065 NM 1996 8 22 96ZZZX4022 1 19960710 G 5755 651734748 SPOILER BOEING 727 727 1384001 NM DELAMINATED WORN B IU6D K NONE O OTHER IN INSP/MAINT 1 NM 01 R2319 HINGE FITTINGS, BUSHINGS AND BEARINGS ARE EXCESSIVELY WORN. UPPER AND LOWER SKINS DELAMINATED. HONEYCOMB CORE CORRODED AND FILLED WITH WATER. CENTER HINGE FITTINGS IS LOOSE. 2 L 7 3 4F A3WE 1996082200066 19960822 00066 NM 1996 8 22 96ZZZX4023 1 19960710 G 5755 651734748 SPOILER BOEING 727 727 1384001 NM HONEYCOMB CORE CORRODED B IU6D K NONE O OTHER IN INSP/MAINT 1 NM 01 R2319 INTERNAL DOUBLERS AT HINGES AND DOWNSTOPS ARE MISSING. HONEYCOMB CORE IS CORRODED. UPPER AND LOWER SKINS ARE DELAMINAT ED. CENTER HINGE FITTING BEARING WELLS ARE CORRODED. TRAILING EDGE OF UPPER SKIN DELAMINATED ALONG 85 PERCENT OF ITS S PAN. 2 L 7 3 4F A3WE 1996082200067 19960822 00067 NM 1996 8 22 96ZZZX4024 1 19960710 G 5755 651734748 SPOILER BOEING 727 727 1384001 NM SKINS DELAMINATED B IU6D K NONE O OTHER IN INSP/MAINT 1 NM 01 TC523 SKIN DELAMINATED AROUND CENTER HINGE FITTING. SURFACE CORROSION NEAR LAP JOINTS AND RIBS. OUTBOARD HINGE FITTINGS WORN BEYOND ALLOWABLE LIMITS. 2 L 7 3 4F A3WE 1996082200068 19960822 00068 NM 1996 8 22 96ZZZX4025 1 19960710 G 5755 651734748 SPOILER BOEING 727 727 1384001 NM HONEYCOMB CORE CORRODED B IU6D K NONE O OTHER IN INSP/MAINT 1 NM 01 TC525 HONEYCOMB CORE CORRODED WITH WATER DAMAGE NEAR CENTER HINGE FITTING. BEARINGS EXCESSIVELY WORN. UPPER AND LOWER SKINS DELAMINATED. 2 L 7 3 4F A3WE 1996082200069 19960822 00069 NM 1996 8 22 96ZZZX4026 1 19960710 G 5755 651734748 SPOILER BOEING 727 727 1384001 NM SKIN CORRODED B IU6D K NONE O OTHER IN INSP/MAINT 1 NM 01 RR1455 DELAMINATION AT CENTER HINGE FITTING. HONEYCOMB CORE UPPER SKIN, UPPER INTERNAL DOUBLER AND LOWER SKIN ARE CORRODED IN OVER 60 PERCENT OF THE TOTAL AREA. 2 L 7 3 4F A3WE 1996082200070 19960822 00070 NM 1996 8 22 96ZZZX4027 1 19960710 G 5753 652163429 INTERNAL DOUBLER 652163480 BOEING 727 727 1384001 NM ATTACH FITTING CRACKED B IU6D K NONE O OTHER IN INSP/MAINT 1 NM 01 BN80 INTERNAL DOUBLER THAT SUPPORTS ATTACH FITTING AND TIES LEADING EDGE SPLICE TOGETHER IS CRACKED AT BOTH LOWER RADII. BOT H CRACKS FOLLOW MATERIAL GRAIN REARWARDS APPROXIMATELY .75 INCH EACH. SUSPECT CAUSE: MATERIAL FATIGUE DUE TO EXCESSIVE LOADS AT LEADING EDGE SPLICE. DOUBLER MATERIAL GAUGE IS NOT THICK ENOUGH. NOTE: DOUBLER HAD PROPER CLEARANCE FROM FI TTING AND CORNERS WERE PROPERLY RADIUSED. 2 L 7 3 4F A3WE 1996082200071 19960822 00071 NM 1996 8 22 96ZZZX4028 1 19960710 G 5753 652163429 INTERNAL DOUBLER 652163491 BOEING 727 727 1384001 NM CARRIAGE FITTING CRACKED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 BN407 INTERNAL DOUBLER THAT SUPPORTS ATTACH FITTING AND TIES LEADING EDGE SPLICE TOGETHER IS CRACKED AT BOTH LOWER RADII. BOT H CRACKS FOLLOW MATERIAL GRAIN REARWARDS APPROXIMATELY .75 INCH EACH. SUSPECT CAUSE: MATERIAL FATIGUE DUE TO EXCESSIVE LOADS AT LEADING EDGE SPLICE. DOUBLER MATERIAL GAUGE IS NOT THICK ENOUGH. NOTE: DOUBLER HAD PROPER CLEARANCE FROM FI TTING AND CORNERS WERE PROPERLY RADIUSED. 2 L 7 3 4F A3WE 1996082200072 19960822 00072 NM 1996 8 22 96ZZZX4029 1 19960710 G 5753 652163429 DOUBLER 6521634149 BOEING 727 727 1384001 NM CARRIAGE FITTING CRACKED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 BN33 THERE ARE 3 CRACKS .25 INCH, .50 INCH AND 1.0 INCH LONG IN LOWER END OF LEADING EDGE SKIN SPLICE DOUBLER. TWO CRACKS EX TEND THROUGH NEAREST FASTENER HOLES. DOUBLER IS LOCATED AT NR 2 CARRIAGE FITTING. THE CRACKS RUN PARALLEL TO GRAIN OF MATERIAL. LEADING EDGE SKIN IS SPLICED AT THIS POINT CAUSING A STRESS POINT DURING FLEXING OF FLAP. SUBMITTER SUGGESTS MAKING DOUBLER OUT OF THICKER GAUGE MATERIAL. 2 L 7 3 4F A3WE 1996082200073 19960822 00073 NM 1996 8 22 96ZZZX4030 1 19960710 G 5753 652163482 SKIN 652163480 BOEING 727 727 1384001 NM FLAP T/E ASSY DELAMINATED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 BN3 DURING TEAR-DOWN INSPECTION, DELAMINATION WAS NOTED ON BOTH UPPER AND LOWER SURFACES. UPON REMOVAL OF DELAMINATED SKINS , IT WAS REVEALED THAT BONDING PRIMER HAD NOT BEEN USED AT TIME OF INSTALLATION OF UPPER AND LOWER SKINS. SEVERE CORROS ION WAS PRESENT THROUGHOUT T/E BONDED ASSY. THE T/E BONDED ASSY ITSELF WAS A CONGLOMERATION OF ALUMINUM HONEYCOMB, NOME X HONEYCOMB, POTTING COMPOUND, FIBERGLASS RESIN, AND FOAM. SUSPECT CAUSE, THE PREVIOUS REPAIRS DOWN TO T/E BONDED ASSY WERE DONE INCORRECTLY. 2 L 7 3 4F A3WE 1996082200074 19960822 00074 CE 1996 8 22 96ZZZX4031 1 19960716 G 5720 316321 STRUT FITTING BBAVIA 8 8KCAB 2110612 CE LIFT STRUT CRACKED D A K NONE O OTHER IN INSP/MAINT 1 CE 05 419JR 34 34 75995 INSPECTED THE LIFT STRUT FITTINGS (PN 3-1632-1 AND PN 316322) IAW AD 96-03-11 PER AMERICAN CHAMPION SERVICE LETTER NR 40 8. FOUND TWO OF THE FOUR FITTINGS CRACKED AT THE RADIUS AS SHOWN IN THE ILLUSTRATION. INSTALLED THE NEW STYLE FITTINGS (PN 3-1691) PER AMERICAN CHAMPION. THESE FITTINGS ONLY HAD A TOTAL TIME OF 33.6 HOURS SINCE NEW WITH NO HARD AEROBATIC S. SUBMITTER STATED THE POOR DESIGN OF THE OLD FITTINGS WAS THE MAJOR CONTRIBUTING FACTOR TO THE CRACKING OF THE FITTIN GS. THE FITTINGS (PN 3-1632-1 AND PN 3-1632-2) SHOULD BE REMOVED FROM SERVICE IMMEDIATELY. 1 H 7 1 3O A21CE 1996082200075 19960822 00075 CE 1996 8 22 96ZZZX4032 1 19960716 G 5720 316322 STRUT FITTING BBAVIA 8 8KCAB 2110612 CE LIFT STRUT CRACKED D K NONE O OTHER IN INSP/MAINT 1 CE 05 419JR 34 34 75995 INSPECTED THE LIFT STRUT FITTINGS (PN 3-1632-1 AND PN 316322) IAW AD 96-03-11 PER AMERICAN CHAMPION SERVICE LETTER NR 40 8. FOUND TWO OF THE FOUR FITTINGS CRACKED AT THE RADIUS AS SHOWN IN THE ILLUSTRATION. INSTALLED THE NEW STYLE FITTINGS (PN 3-1691) PER AMERICAN CHAMPION. THESE FITTINGS ONLY HAD A TOTAL TIME OF 33.6 HOURS SINCE NEW WITH NO HARD AEROBATIC S. SUBMITTER STATED THE POOR DESIGN OF THE OLD FITTINGS WAS THE MAJOR CONTRIBUTING FACTOR TO THE CRACKING OF THE FITTIN GS. THE FITTINGS (PN 3-1632-1 AND PN 3-1632-2) SHOULD BE REMOVED FROM SERVICE IMMEDIATELY. 1 H 7 1 3O A21CE 1996082200076 19960822 00076 CE 1996 8 22 96ZZZX4033 1 19960717 G 3241 9542039 TRANSDUCER RKWELL NA265 NA26540 6402608 CE ANTISKID FAILED D K NONE O OTHER IN INSP/MAINT 1 SO 16 304NT JUL6560E 2822 UNIT WAS INSTALLED IN THE AIRCRAFT, TESTED, AND FOUND TO BE INOPERATIVE. UNIT WAS TESTED AGAIN (IN OPPOSITE POSITION ON SAME AIRCRAFT) AND WAS STILL INOPERABLE. UNIT WAS TESTED AND RELEASED BY REPAIR STATION ON 7-9-96. AIRCRAFT TOTAL TIM E: 12,813.4 HRS. 2 L 7 2 4J A2WE 1996082200077 19960822 00077 NE 1996 8 22 96ZZZX4034 2 19960621 G 7230 COMPRESSOR RKWELL NA265 NA26540 6402608 CE PWA JT12 JT12A8 52042 NE ENGINE BINDING D K NONE O OTHER IN INSP/MAINT 1 SO 16 312NT 9217 950 28232 P637745NB COMPRESSOR VERY DIFFICULT TO ROTATE AND SPOOL DOWN VERY SHORT. INTERNAL BINDING COULD BE FELT WHEN ROTATING BY HAND. TH IS IS A MULTI 9-STAGE UNIT, SO VISUAL INSPECTION/DETECTION OF A PARTICULAR PARTS FAILURE IS VERY DIFFICULT. NO FOD NOTE D AND NO DAMAGE OR DEFECTS NOTED IN TURBINE HOT SECTION. ALL IN-FLIGHT AND GROUND TEST PARAMETERS NORMAL. 2 L 7 2 4J 4 J A2WE 1E9 1996082200078 19960822 00078 NE 1996 8 22 96ZZZX4035 2 19960614 G 7230 COMPRESSOR RKWELL NA265 NA26540 6402608 CE PWA JT12 JT12A8 52042 NE ENGINE BINDING D K NONE O OTHER IN INSP/MAINT 1 SO 16 302NT 6995 1300 28281 P672928NB COMPRESSOR VERY DIFFICULT TO ROTATE AND SPOOL DOWN VERY SHORT. INTERNAL BINDING COULD BE FELT WHEN ROATING BY HAND. TH IS IS A MULTI 9-STAGE UNIT, SO VISUAL INSPECTION/DETECTION OF A PARTICULAR PARTS FAILURE IS VERY DIFFICULT. NO FOD NOTE D AND NO DAMAGE OR DEFECTS NOTED IN TURBINE HOT SECTION. ALL IN-FLIGHT AND GROUND TEST PARAMETERS NORMAL. 2 L 7 2 4J 4 J A2WE 1E9 1996082200080 19960822 00080 NE 1996 8 22 96ZZZX4037 2 19960725 G 7250 805172 VANE PWA JT8 JT8D217A 52053 NE N1 TURBINE FAILED D E ENGINE SHUTDOWN O OTHER NR NOT REPORTED 1 SW 05 709893 ENGINE WAS REMOVED FROM SERVICE DUE TO A LOUD BANG AND ENGINE EXPERIENCED AN IN-FLIGHT SHUT DOWN. DISASSEMBLY OF THE EN GINE REVEALED A SECOND STAGE VANE CLUSTER WAS MISSING AND THE REMAINDER OF THE N1 TURBINE HAD MASSIVE DAMAGE. THE CAUSE FOR THE FAILURE IS STILL UNDER INVESTIGATION. 4 F E9NE 1996082200081 19960822 00081 EU 1996 8 22 96ZZZX4038 1 19960718 G 2750 SD345032XA BRACKET STBROS SD3 SD360 8100606 EU LT WS 71.25 AFT CRACKED D L K NONE O OTHER IN INSP/MAINT 1 EA 09 913SB 17929 SH3403 LEFT CENTER WING REAR SPAR AT STA 71.25, THE INNER FLAP OPERATING ARM LEVER BRACKET WAS FOUND CRACKED. CRACK CAUSED BY CONTACT WITH FLAP OPERATING ARM LEVER DUE TO EXCESSIVE WEAR ON THE BRACKET WHERE THE LEVER ATTACHES. BEARINGS INSIDE OF THE LEVER WERE FOUND FROZEN WHICH CAUSED THE EXCESSIVE WEAR TO THE BRACKET WHICH CAUSED CONTACT BETWEEN THE LEVER AND T HE BRACKET WHICH CAUSED THE CRACK. PART TC: 24,254. 2 H 7 2 4T A41EU 1996082200082 19960822 00082 CE 1996 8 22 96ZZZX4039 1 19960724 G 1100 PLACARD CESSNA 210 210 2073402 CE COCKPIT IMPROPER D A A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CL CLIMB 1 SW 11 6909 57514 AIRCRAFT MADE AN EMERGENCY RETURN TO AIRPORT LANDING (GEAR UP) DUE TO ENGINE POWER LOSS ON TAKEOFF/CLIMB. INVESTIGATION FOUND INDUCTION AIR FLAPPER IN 'HOT' POSITION. THIS IS AN INJECTED ENGINE. AIRCRAFT PLACARD FOR TAKEOFF LANDING CHECK LIST IMPROPERLY WORDED VERSUS TC DATA SHEET. SUBMITTER STATED PROPER CHECK LIST NOT AVAILABLE FROM CESSNA. 1 H 7 1 3O RT 3A21 1996082200220 19960822 00220 NE 1996 8 22 96ZZZX4042 2 19960701 G 7230 COVER SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1B 6OO30 NE CENTRIFUGAL COMP FAILED B A R7MR K NONE O OTHER IN INSP/MAINT 1 NM 11 5771C 392 1369 639 UPON DAILY INSPECTION, A METAL PIECE WAS FOUND ON THE ENGINE DECK THAT APPEARED TO BE PART OF THE ENGINE. VISUAL INSPEC TION DETERMINED THE OBJECT DID NOT COME FROM THE EXTERNAL PORTION OF THE ENGINE. THE OBJECT WAS SENT TO THE MFG WHO DET ERMINED IT WAS A CENTRIFUGAL COMPRESSOR COVER BRIDGE WHICH HAD EXITED THROUGH THE BLEED VALVE. THE ENGINE WAS INSPECTED PER THE MANUFACTURER'S REQUEST AND INSTRUCTIONS AND RETURNED TO SERVICE. SUGGEST PERIODIC INSPECTION OF CENTRIFUGAL CO MPRESSOR COVER DURING BORESCOPE INSPECTION. 1 G 7 1 3U 3 U H9EU E19EU 1996082900153 19960829 00153 CE 1996 8 29 96ZZZX4050 1 19960626 G 2520 SEAT CESSNA 421 421B 2076014 CE CABIN WRONG PART D K NONE W INADEQUATE Q C IN INSP/MAINT 1 EA 25 620TQ 2533 421B0919 WHILE PERFORMING ANNUAL INSPECTION, FOUND A FORWARD FACING SEAT INSTALLED IN AN AFT FACING SEAT POSITION. THERE IS A ST RUCTURAL DIFFERENCE BETWEEN AN AFT FACING AND A FORWARD FACING SEAT. AD 78-13-05 AND MEB 78-17 REFERENCE THIS, HOWEVER, AD 78-13-05, IS A ONE-TIME ONLY AD. SUBMITTER STATED THIS SHOULD BE MADE A RECURRING AD TO APPLY WHENEVER SEATS ARE RE MOVED. THIS AD APPLIES TO VARIOUS TWIN ENGINE CESSNA. 1 L 7 2 3O A7CE 1996082900154 19960829 00154 1996 8 29 96ZZZX4051 4 19960329 G 3416 3431 CASTING UNITEDINST 5934P1 PIPER PA28 PA28140 7102802 SO ALTIMETER OUT OF SPEC B EI4R K NONE O OTHER IN INSP/MAINT 1 SO 15 3489K 1E723 2823582 WHEN RECEIVED, THIS WAS A FACTORY SEALED INSTRUMENT. WHEN BENCH TESTED, IT HAD STICK AND JUMP FRICTION OF 100 FEET TO 1 50 FEET. WHEN DISASSEMBLED, 3 DEFECTS WERE FOUND. THERE WAS A CIRCULAR SCRATCH ON THE BACK OF THE DISC POINTER. THE M OLY/KOTE IN THE TOP PLATE HAD COAGULATED. THE TOP PLATE BREAK-FREE TORQUE WAS 5 TIMES THE PROPER SAFE VALUE. ONE MECHA NISM SHAFT END SHAKE MEASURED .0006 INCH, THE OVERHAUL SPEC CALLS FOR .0020 INCH MINIMUM. ANY ONE OF THESE DEFECTS OR A COMBINATION OF THESE DEFECTS COULD CAUSE A POINTER HANG-UP AT A LATER DATE. 1 L 7 1 3O 2A13 1996082900155 19960829 00155 1996 8 29 96ZZZX4052 4 19960605 G 3416 3431 CASTING UNITEDINST 593RPA1 PIPER PA28 PA28140 7102802 SO ALTIMETER CREEP B EI4R K NONE O OTHER IN INSP/MAINT 1 SO 15 4569X 7B871 287625057 THE END SHAKES ON ALL 3 OF THE CRITICAL SHAFTS IN THE MECHANISM WERE UNDER THE .0020 INCH CALLED OUT IN THE OVERHAUL MAN UAL. THESE MEASURED (.0003 INCH), (.0004 INCH), AND (.0015 INCH). ACCORDING TO THE MANUFACTURER, ANY END SHAKE BELOW . 0004 INCH WILL CAUSE THE POINTERS TO HANG UP DURING THE LOW SPECIFIED OPERATING TEMPERATURE. 1 L 7 1 3O 2A13 1996082900156 19960829 00156 GL 1996 8 29 96ZZZX4053 1 19960703 G 2430 W23XA1AG2 BREAKER AMF DIAMON DA20A1 DA20A1 05626UX GL GEN CONTROL DEFECTIVE D K NONE O OTHER NR NOT REPORTED 1 SW 15 518SS 366 10073 DURING THE DAY, THESE PLANES ARE HAVING PROBLEMS WITH CIRCUIT BREAKERS TRIPPING. THIS USUALLY OCCURS DURING THE HOTTEST PART OF THE DAY. WHEN THE PART COOLS DOWN THEY WILL RESET AND SHOW NO INDICATION OF ANY PROBLEMS WITHIN THE SYSTEM. S UBMITTER STATES IT IS SUSPECTED THAT AS THE DAY GETS HOTTER AND THE DASH WARMS UP, THEN THE CIRCUIT BREAKERS LOSE RESIST ANCE AND FAIL. 1 L 7 1 3O NT TA4CH 1996082900157 19960829 00157 SO 1996 8 29 96ZZZX4054 1 19960729 G 2410 6519905 BRACKET PIPER PA28 PA28236 7102815 SO ALTERNATOR CRACKED D O OTHER J WARNING INDICATION TX TAXI/GRND HDL 1 EA 21 611AJ 287911172 ALTERNATOR FAILED ON TAXI AFTER FUELING. MAINTENANCE FOUND ALTERNATOR BELT LOOSE. FURTHER INSPECTION REVEALED ENGINE T O ALTERNATOR MOUNT BRACKET BROKEN. EVIDENCE SHOWED BRACKET HAD BEEN CRACKED FOR SOME TIME. ALTERNATOR CHANGED 20 HOURS PREVIOUSLY. SUBMITTER STATED CAUSE OF BRACKET FAILURE MAY BE ALTERNATOR WAS SECURED IMPROPERLY (NOT PER PA28 IPC). AL TERNATOR HAD TO BE REPLACED DUE TO DAMAGED HOLES IN CASE. CORRECT MOUNT KIT NEEDS TO BE INSTALLED. CLOSE INSPECTION OF BRACKET RECOMMENDED AT ALTERNATOR CHANGE. 1 L 7 1 3O 2A13 1996082900158 19960829 00158 CE 1996 8 29 96ZZZX4055 1 19960723 G 3213 AXLE NUT CESSNA 172 172M 2072418 CE LANDING GEAR MISINSTALLED D O OTHER O OTHER TX TAXI/GRND HDL 1 SO 16 64117 6429 17265033 DURING GROUND TAXI OPERATIONS, THE RT AXLE NUT SEPARATED FROM THE AXLE. UPON RETURN FROM FLIGHT, THE NUT WAS FOUND MISS ING BY THE PILOT. THE AXLE NUT WITH COTTER PIN INSTALLED WAS RECOVERED BY UNKNOWN PERSONS. THE WHEEL WAS DISASSEMBLED, INSPECTED, AND RE-ASSEMBLED WITH NO DEFECTS NOTED. THE AXLE AND NUT WERE ALSO INSPECTED AND RETURNED TO SERVICE. UPON INSTALLATION OF THE WHEEL ASSY, NOTED THE DIAMETER OF HOLE IN THE AXLE NUT IS SUCH THAT WHEN FULLY INSTALLED, THE END O F THE AXLE IS EXPOSED IN THE COTTER PIN HOLE PERMITTING INCORRECT INSTALLATION OF THE COTTER PIN THROUGH THE NUT, BUT MI SSING THE AXLE. 1 H 7 1 3O NT 3A12 1996082900159 19960829 00159 GL 1996 8 29 96ZZZX4056 3 19960809 G 6111 BLADE CESSNA 150 152 2071835 CE MCAULY 1A103 1A103TCM GL PROPELLER CRACKED B UP7R K NONE O OTHER IN INSP/MAINT 1 EA 13 6497M 7453 15284757 R776850 PROPELLER WAS REMOVED TO FIX A NICK IN THE LEADING EDGE OF ONE BLADE. ALL PAINT WAS REMOVED AND UPON INSPECTION, THE EV IDENCE OF A CRACK APPEARS TO BE SEEN IN ONE BLADE APPROXIMATELY 5 INCHES FROM THE CENTER OF THE HUB HOLE. SUBMITTER REC OMMENDATIONS: INCREASE INSPECTION BOX IN SB 219A AND PUT DIMENSIONS ON BOX. INSPECT 7 INCHES ON EACH SIDE OF CENTER HO LE. 1 H 7 1 3O NT 3A19 5 N P50GL 1996082900160 19960829 00160 CE 1996 8 29 96ZZZX4057 1 19960720 G 2810 MDI DRAIN VALVE CESSNA 150 150H 2071818 CE RT TANK CORRODED B CWQR K NONE O OTHER IN INSP/MAINT 1 GL 05 6520S S21061 15067320 THE RIGHT SIDE FUEL TANK SUMP DRAIN VALVE DIFFICULT TO CLOSE AFTER SUMPING FUEL TANK. FINALLY BECAME IMPOSSIBLE TO OPEN . REPLACED DRAIN VALVE. FOUND DRAIN VALVE CORRODED BETWEEN PLUNGER AND VALVE BODY. DRAIN VALVE NEEDS TO BE MORE CORRO SION RESISTANT. THE RIGHT SIDE FUEL TANK ALWAYS IS THE SIDE THAT HAS WATER IN IT. 1 H 7 1 3O 3A19 1996082900161 19960829 00161 CE 1996 8 29 96ZZZX4058 1 19960607 G 5753 24250012 FLAP TRACK CESSNA 150 152 2071835 CE RT INBD CORRODED B LCPR K NONE O OTHER IN INSP/MAINT 1 SO 17 69219 773 15285350 DURING 100-HOUR INSPECTION, THE RIGHT INBOARD FLAP TRACK WAS FOUND WITH INTERGRANULAR CORROSION ALONG THE BOTTOM. PART WAS INSTALLED 23 MONTHS EARLIER. 1 H 7 1 3O NT 3A19 1996082900162 19960829 00162 EA 1996 8 29 96ZZZX4059 2 19960716 G 8520 72877 CAM FOLLOWER LYC O540 O540B2C5 41532 EA CYLS 1,3,5 BROKEN D P K NONE O OTHER IN INSP/MAINT 1 NM 07 1481540 CAM FOLLOWERS BROKEN ON NR 1 CYLINDER EXHAUST NR 3, EXHAUST AND INTAKE, NR 5 CYLINDER-INTAKE. REST OF CAM FOLLOWERS PIT TED OR SPALLED. NR 2 CYLINDER DROPPED THE EXHAUST VALVE. OIL SUMP REMOVED FOR INSPECTION AND CLEANING. FOUND PIECES O F CAM FOLLOWERS IN SUMP. ENGINE DISASSEMBLED FOR OVERHAUL. ALL SIX ROD CAPS DAMAGED. ALL PIECES RETAINED AND ARE AVAI LABLE FOR SCRUTINY. 3 O E295 1996082900163 19960829 00163 1996 8 29 96ZZZX4060 1 19960725 G 3150 6838 LAMP WARNING PANEL FAILED B A XEFR K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 03 INSTALLED LAMPS AS REPLACEMENTS IN ANTI-SKID, PITOT HEAT, AND LT AIR IGNITION ANNUNCIATORS. WHEN POWER WAS TURNED ON TO TEST LAMPS, LAMPS BECAME VERY BRIGHT AND THEN FAILED. SUSPECT LAMPS WERE MISLABELED AT VENDOR. CORRECT LAMPS AND F/T OK. 1996082900164 19960829 00164 GL 1996 8 29 96ZZZX4061 3 19960723 G 6111 C84686R BLADE HARTZL HCE2Y HCE2YR2 GL PITCH CHANGE KNOB BROKEN B P PS4R C D ABORTED TAKEOFF RETURN TO BLOCK O OTHER TO TAKEOFF 1 SO 05 B52644 DJ5494 DURING POWER-UP FOR TAKEOFF, THE PILOT REPORTED HEARING A LOUD POP. HE PULLED POWER OFF AND TAXIED TO THE LOCAL FBO. A FTER SHUT DOWN, ONE BLADE WAS IN FEATHER. THE PROPELLER WAS REMOVED AND BROUGHT TO OUR SHOP. UPON TEAR DOWN, THE PITCH CHANGE KNOB ON THE BLADE HAD BROKEN OFF. NO OTHER DAMAGE WAS NOTICED. CAUSE IS UNKNOWN AND THE BLADE HAS BEEN SENT TO THE FACTORY. 5 C P9EA 1996082900165 19960829 00165 1996 8 29 96ZZZX4062 4 19960730 G 6122 D20591 DRIVE GEAR MCAULY C290D5GT17 PROP GOVERNOR CRACKED B ME4D K NONE O OTHER IN INSP/MAINT 1 SO 15 91041 DURING INSPECTION OF PROPELLER GOVERNOR, DRIVE GEAR WAS FOUND CRACKED IN SPLINE. GOVERNOR RETURNED TO CUSTOMER WITHOUT REPAIR. 1996082900166 19960829 00166 1996 8 29 96ZZZX4063 4 19960709 G 2562 E01 ELT ACK CASE HALF MISASSEMBLED D P K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 14 PRIOR TO INSTALLATION, AN ELT WAS NOTED TO BE HOT. INVESTIGATION FOUND 4 OF BATTERIES WERE SHORTED DUE MIS-ASSEMBLY OF THE ELT CASE HALVES. SUBMITTER STATES MIS-ASSEMBLY IS EASY TO DO WHEN BATTERY INSTALLATION INSTRUCTIONS NOT FOLLOWED. 1996082900167 19960829 00167 SW 1996 8 29 96ZZZX4064 1 19960723 G 3340 930021507 CONNECTOR MOONEY M20 M20J 5870219 SW INST PANEL MELTED D P A K NONE O OTHER IN INSP/MAINT 1 SO 15 191ER 5055 243252 DUE TO LARGE AMP DRAW, 34-PIN CONNECTOR IS MELTING. AT LANDING/TAXI, LIGHT PIN CONTACTS. SUBMITTER SUGGESTS REWIRING W IRES OUTSIDE CONNECTOR OR LARGE PINS FOR CONNECTOR. THIS IS SECOND AIRCRAFT IN FLEET TO HAVE THIS PROBLEM. M20J MODEL ACFT WITH WING MOUNTED TAXI AND LANDING LIGHTS. 1 L 7 1 3O 2A3 1996082900168 19960829 00168 SW 1996 8 29 96ZZZX4065 1 19960723 G 3340 930021508 CONNECTOR MOONEY M20 M20J 5870219 SW INST PANEL MELTED D K NONE O OTHER IN INSP/MAINT 1 SO 15 191ER 243252 DUE TO LARGE AMP DRAW, 34-PIN CONNECTOR IS MELTING. AT LANDING/TAXI, LIGHT PIN CONTACTS. SUBMITTER SUGGESTS REWIRING W IRES OUTSIDE CONNECTOR OR LARGER PINS FOR CONNECTOR. THIS IS SECOND AIRCRAFT IN FLEET TO HAVE THIS PROBLEM. M20J MODEL ACFT WITH WING MOUNTED TAXI AND LANDING LIGHTS. 1 L 7 1 3O 2A3 1996082900169 19960829 00169 CE 1996 8 29 96ZZZX4066 1 19960730 G 7120 643816 BAR BEECH 36 A36TC 1151603 CE ENGINE STAB CRACKED D S K NONE O OTHER IN INSP/MAINT 1 EA 25 3685W 1912 EA113 DUE TO LOCATION OF ENGINE STABILIZER BAR, CRACK COULD NOT BE SEEN AT FIRST INSPECTION, ONLY FOUND UPON REMOVAL. LAST PA RT INSPECTION AT LAST ENGINE OVERHAUL, 387 HOURS. 1 L 7 1 3O 3A15 1996082900170 19960829 00170 CE 1996 8 29 96ZZZX4067 1 19960730 G 7810 642465 WYE PIPE BEECH 36 A36TC 1151603 CE MT SUPPORT CRACKED D S K NONE O OTHER IN INSP/MAINT 1 EA 25 3685W 1912 387 EA113 CRACKED IN FRONT OF ASSY NEAR CENTER SUPPORT BOSS. SUBMITTER STATES VERY HARD TO SEE DUE TO LOCATION AND BLACK COATING OF PART. SUGGEST DIFFERENT COLOR AND REDESIGNED PART MADE OUT OF THICKER MATERIAL. 1 L 7 1 3O 3A15 1996082900171 19960829 00171 CE 1996 8 29 96ZZZX4068 1 19960722 G 5712 51220252 RIB CESSNA 414 414A 2075907 CE RT OTBD WING CRACKED B A FTKR K NONE O OTHER IN INSP/MAINT 1 GL 19 543AC 4098 414A0103 DURING ANNUAL INSPECTION, A CRACK WAS DISCOVERED IN RT OUTBOARD WING RIB WHERE AILERON HINGE BEARING BLOCK ATTACHES. CR ACK IS HARD TO DETECT WITH AILERON INSTALLED. SUSPECT CAUSE IS THOUGHT TO BE FLYING IN TURBULENT AIR ABOVE MANEUVERING SPEED. 1 L 7 2 3O A7CE 1996082900172 19960829 00172 CE 1996 8 29 96ZZZX4069 1 19960722 G 2730 50350054 FITTING CESSNA 414 414A 2075907 CE RT ELEV TORQUE CRACKED B A FTKR K NONE O OTHER IN INSP/MAINT 1 GL 19 5431C 4098 4098 414A0103 DURING ANNUAL INSPECTION, A CRACK WAS DISCOVERED IN THE RT ELEVATOR TORQUE TUBE ATTACH FITTING. CRACK RADIATED FROM TAP ERED HOLE. NEW FITTING DELIVERED FROM CESSNA WAS OF DIFFERENT DESIGN AND REQUIRED NEW HOLE DRILLED IN TORQUE TUBE FOR T APERED PIN INSTALLATION. PART NUMBER STAMPED ON OLD FITTING WAS FOR A MODEL 421B SERIES AIRPLANE. CRACK POSSIBLY HAPPE NED DURING INSTALLATION. 1 L 7 2 3O A7CE 1996082900173 19960829 00173 CE 1996 8 29 96ZZZX4070 1 19960724 G 3246 C1630060103 WHEEL CESSNA 210 210L 2073448 CE MLG ASSY FAILED D A K NONE O OTHER TX TAXI/GRND HDL 1 SO 15 5489V 7188 21060961 WHEEL ASSY BLEW APART ON TAXI, DISC SIDE OF WHEEL. SUSPECT CAUSE, THREADS WEAK ON 12-BOLT, 3-PIECE, MCCAULEY WHEEL ASSY . REPLACED WHEEL ASSY, 3-PIECE, WITH 2-PIECE CLEVELAND AFTER 2,500 HOURS TIS. 1 H 7 1 3O 3A21 1996082900174 19960829 00174 CE 1996 8 29 96ZZZX4071 1 19960701 G 3230 AN512A BOLT CESSNA 402 402B 207590P CE NLG LINK ATTACH BROKEN D S K NONE O OTHER IN INSP/MAINT 1 WP 19 69PB 402B1248 DURING SCHEDULED INSPECTION, THE NOSE LANDING GEAR LOWER ATTACH BOLT FOR DRAG LINK FOUND BROKEN. INSPECTED OTHER 10 ACF T IN FLEET, NO OTHERS BROKEN OR DAMAGED. SUBMITTER STATED IF UNDETECTED, NLG WILL COLLAPSE. 1 L 7 2 3O A7CE 1996082900175 19960829 00175 EA 1996 8 29 96ZZZX4072 2 19960517 G 8520 CRANKCASE PIPER PA28 PA28R200 7102811 SO LYC O360 IO360C1C 41514 EA LT NR 2 CYL FWD CRACKED B DPOD K NONE O OTHER IN INSP/MAINT 1 NM 07 2141T 1058 28R7135144 L619151A LEFT CRANKCASE CRACKED BELOW NR 2 CYLINDER, FORWARD LOWER BASE STUD. CRACK WAS APPROXIMATELY 2 INCHES LONG. CASE WAS R EPAIRED. 1 L 7 1 3O 3 O 2A13 1E10 1996082900176 19960829 00176 CE 1996 8 29 96ZZZX4073 1 19960726 G 3246 C1630060103 WHEEL CESSNA 210 210L 2073448 CE MLG ASSY FAILED D K NONE O OTHER LD LANDING 1 SO 15 2667S 2806 21061347 WHEEL ASSY BLEW APART ON LANDING. (DISC SIDE.) SUSPECT CAUSE, THREADS WEAK ON 12-BOLT, 3-PIECE MCCAULEY WHEEL ASSY. R EPLACED 3-PIECE WHEEL ASSY WITH 2-PIECE CLEVELAND AFTER 2,500 HRS TIS. 1 H 7 1 3O 3A21 1996082900177 19960829 00177 CE 1996 8 29 96ZZZX4074 1 19960722 G 8120 CLAMP CESSNA 404 404CESSNA 2075901 CE CONT O520 GTSIO520M 17032 SO TURBO FAILED G E A ENGINE SHUTDOWN UNSCHED LANDING E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CR CRUISE 1 GL 09 28SA 4040072 276238R CLAMP CAME LOOSE AND DUCT BETWEEN TURBO AND INTAKE THROAT LEAKED CAUSING ENGINE TO RUN ROUGH. PILOT CHOSE TO SHUT DOWN ENGINE IN-FLIGHT AND MADE SAFE SINGLE ENGINE LANDING. NEW CLAMP WAS INSTALLED AND TORQUED TO SPECS. 1 L 7 2 3O 3 O A25CE E7CE 1996082900178 19960829 00178 CE 1996 8 29 96ZZZX4075 1 19960710 G 3211 MS2446112 BEARING CESSNA 310 310R 2074245 CE LT MLG AFT BINDING D K NONE O OTHER IN INSP/MAINT 1 EA 01 3420G 310R1229 BEARING BINDING UP CAUSING TWISTING MOVEMENT ON TRUNNION PIN, PN 0841011-1, SHEARING SLOTTED PIN, PN NAS561P4-28, ALLOWI NG TRUNNION PIN TO SLIDE OUT OF TRUNNION. SUBMITTER STATED TO PREVENT, REPLACE WITH NEW TRUNNION PINS WITH GREASE FITTI NGS. 1 L 7 2 3O 3A10 1996082900179 19960829 00179 EA 1996 8 29 96ZZZX4076 2 19960701 G 7414 10682016 GEAR PIPER PA32 PA32RT300T 7103216 SO LYC O540 TIO540S1AD 41532 EA MAGNETO FAILED D K NONE O OTHER IN INSP/MAINT 1 NE 03 36201 529 32R7887027 L697961A MAGNETO DISTRIBUTOR GEAR FAILED. 1 L 7 1 3O 3 O A3SO E14EA 1996082900180 19960829 00180 CE 1996 8 29 96ZZZX4077 1 19960723 G 3213 5041182 BEARING CESSNA 340 340CESSNA 2076404 CE LT/RT STRUT CRACKED B BXSR K NONE O OTHER IN INSP/MAINT 1 EA 09 40BA 5102 3400046 ONE BEARING IN EACH GEAR WAS CRACKED. INSPECTION PERFORMED PER CESSNA SB ME B88-7 AND AD 90-02-13. ONE BEARING CRACKED IN ONE PLACE. ONE BEARING CRACKED IN TWO PLACES. LAST INSPECTION C/W 1,000 HOURS. 1 L 7 2 3O 3A25 1996082900181 19960829 00181 SO 1996 8 29 96ZZZX4078 1 19960718 G 2750 63900174 BUSHING 6378100 PIPER PA28 PA28140 7102802 SO FLAP CONTROL WORN D K NONE O OTHER IN INSP/MAINT 1 EA 25 56678 1574 287425016 BUSHING WORN OUT AFTER 1,573 HOURS. SHOULD KEEP 500-HOUR INSPECTION OF BOLT AND BUSHING PER PIPER INSPECTION FORM EVEN IF MODIFIED IAW PIPER SB 965. 1 L 7 1 3O 2A13 1996082900183 19960829 00183 CE 1996 8 29 96ZZZX4080 1 19960724 G 3231 08411066 BELLCRANK CESSNA 310 310R 2074245 CE RT MLG DOOR BROKEN D K NONE O OTHER IN INSP/MAINT 1 GL 09 6181C 310R1320 PILOT HEARD LOUD POP WHEN LOWERING THE LANDING GEAR. HAD 3 GREEN LIGHTS, VERIFIED GEAR DOWN AND LOCKED. UPON LANDING, RT GEAR DOOR WAS NOT CLOSED. INSPECTION REVEALED BROKEN GEAR DOOR BELLCRANK. PART HAD INDICATIONS OF A CRACK THAT WAS OLD. SUBMITTER RECOMMENDS MORE FREQUENT INSPECTION OF THIS AREA. 1 L 7 2 3O 3A10 1996082900184 19960829 00184 EA 1996 8 29 96ZZZX4081 2 19960730 G 7414 10682016 GEARTOOTH D6LN3000 CESSNA 182 TR182 2072735 CE LYC O540 O540L3C5 41532 EA MAGNETO FAILED D K NONE O OTHER IN INSP/MAINT 1 EA 01 6339T E029002GR R18201986 RL2385940A DURING C/W AD 96-12-07, DISCOVERED DISTRIBUTOR GEAR MISSING A TOOTH, DID NOT AFFECT ENGINE OPS. REPLACED BOTH DISTRIBUT OR GEARS WITH NEW. REASON FOR FAILURE UNKNOWN, NO OTHER DEFECTS NOTED. 1 H 7 1 3O 3 O 3A13 E295 1996082900185 19960829 00185 EU 1996 8 29 96ZZZX4082 1 19960725 G 3250 GA58122 ROD END AMD FALC10 FALCON10 2730101 EU STEER ACTUATOR FAILED B A K NONE O OTHER IN INSP/MAINT 1 GL 25 73B 8338 79 WHILE TAXIING AFTER LANDING, THE FLIGHT CREW HEARD A SNAPPING NOISE AND LOST NORMAL STEERING CONTROL. FOUND THE STEERIN G ACTUATOR ROD END SHEARED ON THE STEERING ACTUATOR. THE THREAD AREA WHERE THE FAILURE OCCURRED CANNOT BE INSPECTED UNL ESS THE SEALER IS REMOVED. 2 L 7 2 4F A33EU 1996082900186 19960829 00186 SO 1996 8 29 96ZZZX4083 1 19960723 G 2721 63457003 ARM ASSY PIPER PA32 PA32301 7103207 SO RUDDER TRIM BROKEN D K NONE O OTHER IN INSP/MAINT 1 EA 01 8309A 2031 328106026 ATTACH ARM FOR RUDDER TRIM BROKE AWAY FROM ARM ASSY. 1 L 7 1 3O A3SO 1996082900187 19960829 00187 CE 1996 8 29 96ZZZX4084 1 19960720 G 3246 C1630060103 WHEEL CESSNA 210 210M 2073450 CE MLG ASSY FAILED D K NONE O OTHER IN INSP/MAINT 1 SO 15 8427M 21062043 WHEEL ASSY BLEW APART ON TAXI ON BRAKE DISC SIDE. SUSPECT CAUSE, WEAK THREADS ON 12-BOLT, 3-PIECE MCCAULEY WHEEL ASSY. REPLACED WHEEL ASSY WITH 2-PIECE, CLEVLAND. 1 H 7 1 3O 3A21 1996082900188 19960829 00188 GL 1996 8 29 96ZZZX4085 3 19960731 G 6114 D32517 HUB CESSNA 340 340A 2076405 CE HARTZL HCC3Y PHCC3YF2 GL NR 1 SOCKET CRACKED B UF2R K NONE O OTHER IN INSP/MAINT 1 GL 15 8636K EB2248 340A0562 EB2248 HUB CRACK FOUND BECAUSE OF LEAKING GREASE. CRACK IS PERMEATING FROM SLINGER RING ATTACHING HOLE IN REAR OF HUB TRANSGRE SSING 4 INCHES IN HUB SOCKET ON INSIDE OF HUB. 1 L 7 2 3O 3A25 5 C P25EA 1996082900189 19960829 00189 CE 1996 8 29 96ZZZX4086 1 19960618 G 3246 C1630060103 WHEEL CESSNA 210 210L 2073448 CE MLG ASSY THREADS FAILED D K NONE O OTHER LD LANDING 1 SO 15 93887 21060445 WHEEL ASSY BLEW APART ON LANDING, RT BRAKE DISC SIDE OF WHEEL. SUSPECT CAUSE, THREADS WEAK ON 12-BOLT, 3-PIECE MCCAULEY WHEEL ASSY. REPLACED WHEEL ASSY, 3-PIECE, WITH 2-PIECE, CLEVELAND. 1 H 7 1 3O 3A21 1996082900190 19960829 00190 SO 1996 8 29 96ZZZX4087 1 19960430 G 3211 9529900 STUD PIPER PA34 PA34200T 7103406 SO MLG SIDE BRACE CRACKED B A CTKR K NONE O OTHER IN INSP/MAINT 1 WP 07 9565K 347670209 MAIN LANDING GEAR SIDE BRACE, 2 EACH, STUDS LEFT AND RIGHT FOUND CRACKED AT RADIUS OF HEAD. REF: AD 95-20-07 N/R. 1 L 7 2 3O A7SO 1996082900191 19960829 00191 CE 1996 8 29 96ZZZX4088 1 19960729 G 3230 GEAR HANDLE BEECH 58 58P 1152744 CE EMERG EXTEND NOT FUNCTIONAL D A K NONE W INADEQUATE Q C IN INSP/MAINT 1 CE 03 36EB TJ465 DURING ANNUAL INSPECTION, FOUND EMERGENCY GEAR HANDLE TRAPPED UNDER FORWARD SPAR COVER. EMERGENCY EXTENSION WOULD HAVE BEEN IMPOSSIBLE. SUBMITTER STATED SPAR COVER INSTALLED INCORRECTLY BY PERSONS UNKNOWN. 1 L 7 2 3O A23CE 1996082900192 19960829 00192 SO 1996 8 29 96ZZZX4089 1 19960814 G 7160 AIR BOX PIPER PA32 PA32260 7103206 SO CARB ATTACH CRACKED D A K NONE O OTHER IN INSP/MAINT 1 SO 16 3755W 3500 32670 DURING SERVICING OF NOSE STRUT, DISCOVERED AIR BOX CRACKED AROUND CARBURETOR ATTACH FLANGE. CRACK WAS 270 DEGREES (FRON T, RIGHT, REAR). THIS ASSY IS QUITE HEAVY AND PUTS A STRAIN ON THIS WELD IN ALUMINUM PART. PART RE-WELDED AND RE-INSTA LLED. 1 L 7 1 3O A3SO 1996082900193 19960829 00193 CE 1996 8 29 96ZZZX4090 1 19960701 G 3246 WHEEL BEECH 58 58 1152740 CE NLG BROKEN D P O OTHER O OTHER LD LANDING 1 GL 15 4016A 7599 TH9 INNER HALF OF NOSE WHEEL BROKE WHEN AIRCRAFT LANDED. STRUCTURAL INSPECTION OF NOSE LANDING GEAR STRUT REVEALED NO DAMAG E TO AIRCRAFT. SUBMITTER STATED CAUSE OF FAILURE UNKNOWN, BUT INSPECTION OF NOSE WHEEL REVEALED SOME PITTING CORROSION ON INSIDE OF WHEEL. 1 L 7 2 3O 3A16 1996082900194 19960829 00194 CE 1996 8 29 96ZZZX4091 1 19960723 G 7603 C2995050102 CONTROL CABLE CESSNA 172 172M 2072418 CE THROTTLE DETERIORATED D A K NONE O OTHER IN INSP/MAINT 1 NM 01 64108 4615 17265024 INSPECTION FOUND THROTTLE OUTER CABLE HOUSING VERY DETERIORATED DUE TO AGE/HEAT EXPOSURE. INNER HOUSING LOOSE AT FORWAR D END, ABOUT TO SEPARATE. SUBMITTER STATED IF NOT CORRECTED, LOSS OF THROTTLE CONTROL AND ENGINE POWER WILL RESULT. TH IS IS THE SECOND REPORT SUBMITTER HAS FILED ON THIS PART. THIS IS THE FOURTH CABLE SUBMITTER HAS FOUND IN BAD CONDITION IN APPROXIMATELY ONE AND ONE-HALF YEARS. SUBMITTER STATED CABLES SHOULD BE REPLACED WITH NEW PARTS WHICH ARE OF DIFFER ENT CONSTRUCTION. 1 H 7 1 3O NT 3A12 1996082900195 19960829 00195 SO 1996 8 29 96ZZZX4092 1 19960724 G 2410 757388 BOLT PRESTOLITE 4111810 PIPER PA28 PA28181 7102807 SO ALTERNATOR MOUNT SEPARATED B WC7R K NONE O OTHER IN INSP/MAINT 1 GL 25 8444S 2090476 288290025 DURING AN OIL CHANGE, THE MECHANIC NOTICED A BOLT WITH A SECURE NUT PROTRUDING FORWARD FROM THE BASE OF THE ALTERNATOR. A CLOSER LOOK INDICATED THE HEAD OF THE ALTERNATOR MOUNT BOLT HAD SEPARATED FROM THE SHANK ALLOWING THE BOLT TO VIBRATE FORWARD TOWARD THE STARTER FLYWHEEL. REPLACED BOLT WITH NEW PART AND SECURED. TACHOMETER: 484.8. HOBBS: 181.8. 1 L 7 1 3O 2A13 1996082900196 19960829 00196 CE 1996 8 29 96ZZZX4093 1 19960729 G 3230 131553FGB17 ROD END BEECH 23 C24R 1151254 CE LT MLG ACTUATOR FAILED B AKGR O A OTHER UNSCHED LANDING J WARNING INDICATION NR NOT REPORTED 1 CE 05 5246M 4844 MC564 LEFT MAIN GEAR CAME DOWN WHILE IN-FLIGHT. CYCLED GEAR DOWN AND BACK UP, AND IT STAYED DOWN. CYCLED GEAR DOWN AND LANDE D. WITH AIRCRAFT IN SHOP, FOUND THE ROD END ON THE ACTUATOR BROKEN. IT APPEARS TO HAVE BEEN CRACKED AT THE GREASE ZERK FIRST THEN, IN TIME, FAILED. 1 L 7 1 3O A1CE 1996082900197 19960829 00197 CE 1996 8 29 96ZZZX4094 1 19960729 G 3710 B904 HOSE CESSNA 150 152 2071835 CE VACUUM SYSTEM DETERIORATED D K NONE O OTHER IN INSP/MAINT 1 SO 05 93114 15285404 TWO EACH CESSNA 152 FLIGHT SCHOOL AIRCRAFT REPORTED VACUUM INSTRUMENT PROBLEMS. FOUND VACUUM SYSTEM HOSES WERE CRUMBLIN G AND IN VERY POOR CONDITION, ALSO, ONE VACUUM PUMP FAILURE DUE TO INJESTION OF RED INNER SLEEVE PARTICLES FROM HOSES. C ESSNA SEB 96-10 COVERS THE FAILURE ON THIS SERIES OF HOSE. 1 H 7 1 3O NT 3A19 1996082900198 19960829 00198 SO 1996 8 29 96ZZZX4095 1 19960801 G 8011 MHB4014 STARTER PIPER PA31 PA31350 7103110 SO BENDIX DRIVE BOLTS FAILED B APCR K NONE O OTHER IN INSP/MAINT 1 NM 01 777KT 547 317552053 RIGHT ENGINE STARTER WOULD NOT ENGAGE. FOUND MOTOR HOUSING SEPARATED FROM BENDIX DRIVE SECTION DUE TO BROKEN ATTACH BOL TS. SECOND UNIT WITH THIS PROBLEM IN OUR FLEET. 1 L 7 2 3O A20SO 1996082900199 19960829 00199 SO 1996 8 29 96ZZZX4096 1 19960806 G 2820 K2406SAE2 RING NUT 451103 PIPER PA28 PA28161 7102803 SO FUEL PRIMER DEFECTIVE D K NONE O OTHER IN INSP/MAINT 1 NE 03 109GP 287816287 FUEL PRIMER LOCKING RING NUT WAS MISSING APPROXIMATELY 180 DEGREES OF MATERIAL. THIS PREVENTED THE PLUNGER FROM LOCKING IN. THE NORMAL LOCKING AREA IS THE WIDTH OF THE PIN ON THE PLUNGER, THE AMOUNT OF LOCK MISSING WAS APPROXIMATELY 10 TI MES THE WIDTH OF THE PIN. 1 L 7 1 3O 2A13 1996082900200 19960829 00200 1996 8 29 96ZZZX4097 4 19960701 G 3416 3431 CASTING UNITEDINST 5934P1 ALTIMETER CREEP B EI4R K NONE O OTHER IN INSP/MAINT 1 SO 15 AG131 THIS INSTRUMENT WAS A NEW FACTORY SEALED ALTIMETER. TWO SHAFT END SHAKES WERE UNDER THE MINIMUM .0020 INCH CALLED OUT IN THE OVERHAUL MANUAL. THEY MEASURED .0006 INCH AND .0010 INCH. THE MANUFACTURER HAS INDICATED AN END SHAKE OF .0004 INCH OR LESS CAN CAUSE A POINTER HANG-UP DURING A NORMAL SPECIFIED COLD TEST. END SHAKE CHANGES OF .0002 INCH TO .0003 INCH HAVE BEEN MEASURED DURING DIFFERENT PRESSURE SETTINGS ON THE ALTIMETER. SUBMITTER STATED THIS INSTRUMENT COULD HAN G UP DURING NORMAL COLD OPERATION. 1996082900201 19960829 00201 1996 8 29 96ZZZX4098 4 19960626 G 2350 215640026 CAPACITOR PIPER PA32 PA32300 7103212 SO AUDIO PANEL SHORTED E O OTHER B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 SO 13 2351M 327840047 AFTER TAKEOFF, PILOT SMELLED SOMETHING ELECTRICAL BURNING AND THEN SMOKE CAME FROM AROUND AUDIO PANEL. NARCO CP 135 TSO . FOUND C9 CAPACITOR COMING OFF OF 9.6 VOLT LINE TO GROUND SHORTED AND SMOKED COCKPIT. 1 L 7 1 3O A3SO 1996082900202 19960829 00202 1996 8 29 96ZZZX4099 4 19960611 G 3416 3431 CASTING UNITEDINST 5934P PIPER PA28 PA28140 7102802 SO ALTIMETER CREEP B EI4R K NONE O OTHER IN INSP/MAINT 1 SO 15 2385T 72453 287225064 FRICTION IN ALTIMETER REPORTED 200 FEET. BENCH TEST CONFIRMED 160 FEET OF FRICTION. THE END SHAKES ON TWO OF THE MECHA NISM CRITICAL SHAFTS MEASURED .00085 INCH AND ZERO. THE OVERHAUL MANUAL CALLS OUT .0020 INCH MINIMUM. THE ZERO END SHA KE WOULD CLOSE IN UNDER A COLD CONDITION AND LOCK UP THE POINTERS AS PROVEN AND DOCUMENTED BY THE MANUFACTURER'S TESTS. 1 L 7 1 3O 2A13 1996082900203 19960829 00203 SW 1996 8 29 96ZZZX4100 1 19960610 G 5302 206033004045 TAIL BOOM BELL 206 206L3 1182108 SW DRIVESHAFT COVER CRACKED D L A K NONE O OTHER IN INSP/MAINT 1 SO 01 10SP 5822 01278 51064 WHILE PERFORMING A 300-HOUR INSPECTION, CRACKS WERE FOUND IN THE TAIL BOOM. THESE CRACKS WERE FOUND ONLY AFTER THE RT F RONT TAIL ROTOR DRIVESHAFT COVER CLIP WAS DRILLED OFF TO REPLACE A LOOSE RIVET. THE CRACKS WERE NOT VISIBLE UNTIL THE C LIP WAS REMOVED. THE CRACKS WERE VISIBLE FROM THE BACK SIDE. TOTAL TIME ON THE HELICOPTER IS 5,821.8 HOURS. 1 G 7 1 3U H2SW 1996082900204 19960829 00204 SW 1996 8 29 96ZZZX4101 1 19960717 G 5302 206033004045 TAIL BOOM BELL 206 206L3 1182108 SW DRIVESHAFT COVER CRACKED D L A K NONE O OTHER IN INSP/MAINT 1 SO 01 3KY 3443 51113 WHILE PERFORMING A 100-HOUR INSPECTION, 4 CRACKS WERE FOUND IN THE TAIL BOOM PER ASB 206L-8447, REV C. THESE CRACKS WER E NOT VISIBLE FROM THE OUTSIDE. HOWEVER, DUE TO THE PREVIOUS CRACKS, INSPECTED THIS TAIL BOOM FROM THE INSIDE. THESE C RACKS WERE FROM THE RIVET HOLES ON THE TWO FRONT TAIL ROTOR DRIVESHAFT COVER CLIPS. 1 G 7 1 3U H2SW 1996082900205 19960829 00205 SW 1996 8 29 96ZZZX4102 1 19960723 G 6520 206040405101 SHAFT BELL 206 206BELL 1181502 SW T/R GEARBOX MISMANUFACTURED B ETRR K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 09 A2738 NEW SHAFT RECEIVED FROM BELL FOUND TO BE MACHINED IMPROPERLY. 1 G 7 1 3U H2SW 1996082900206 19960829 00206 WP 1996 8 29 96ZZZX4103 1 19960726 G 6320 369H5656 PULLEY ASSY 369A5100709 HUGHES 369 369HS 4470728 WP XMSN GEARSHAFT BOTTOM OUT C A K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 09 820413 ON SOME MAIN ROTOR TRANSMISSION ASSEMBLIES, THE SPLINES ON THE PULLEY ASSEMBLY DRIVER BOTTOM OUT ON THE SPLINES OF THE G EARSHAFT INPUT BEVEL PINION (369A5107-21). THIS RESULTS IN A GAP BETWEEN THE GUARD (369H5657) AND THE SPACER (369A5165) . OPERATING WITH THIS CONDITION WILL DAMAGE THE INPUT PINION AND THE PULLEY ASSEMBLY. SUBMITTER RECOMMENDATIONS, CHECK FOR THIS CONDITION WITH ANY REPLACEMENT TRANSMISSION ASSEMBLY, MAIN ROTOR. 1 G 7 1 3U H3WE 1996082900207 19960829 00207 EA 1996 8 29 96ZZZX4104 2 19960708 G 8530 68795 ROCKER COVER ENSTRM F28 F28F 3300412 GL LYC O360 HIO360F1AD 41514 EA ENGINE GROOVED B NQ2R K NONE O OTHER IN INSP/MAINT 1 WP 05 210PD 547 805 L25515S1A ENGINE DISASSEMBLED DUE TO ROTOR BLADE STRIKE. FOUND SEVERAL DEEP RINGS WORN IN ROCKER COVERS WHERE ROCKER SHAFTS RIDE. (NOT CAUSED BY ACCIDENT.) SUBMITTER STATED THIS PROBLEM HAS BEEN CORRECTED ON OTHER TYPES OF LYCOMINGS BY INSTALLATIO N OF PLASTIC THRUST BUTTONS, BUT NOT ON THIS TYPE. 1 G 7 1 3O 3 O H1CE 1E10 1996082900208 19960829 00208 EU 1996 8 29 96ZZZX4105 1 19960123 G 6520 350A5302005 GEARBOX SNIAS 350 AS350B1 8680811 EU T/R MAKING METAL B VE3R K NONE O OTHER IN INSP/MAINT 1 WP 23 216LA 155 M2041 2251 TAIL ROTOR GEAR BOX RECENTLY OVERHAULED. MADE METAL AFTER 154.8 HOURS SINCE OVERHAUL. TAIL ROTOR GEARBOX WAS REPLACED. AIRCRAFT TT: 6,253.8 HOURS. 1 G 7 1 3U H9EU 1996082900209 19960829 00209 SW 1996 8 29 96ZZZX4106 1 19960123 G 5302 206031004115 TAIL BOOM BELL 206 206B3 1181506 SW T/R GEARBOX CRACKED D K NONE O OTHER IN INSP/MAINT 1 WP 01 2044C 7226 3363 DURING 100-HOUR INSPECTION, FOUND CRACK APPROXIMATELY 1.5 INCHES AT FORWARD LEFT MOUNTING HOLE OF TAIL ROTOR GEARBOX ON TAIL BOOM. SUSPECT CAUSED BY FATIGUE. SUBMITTER STATED NO OUT OF BALANCE CONDITION EXISTED OR REPORTED. NO OTHER DAMA GE NOTED. 1 G 7 1 3U H2SW 1996082900210 19960829 00210 SW 1996 8 29 96ZZZX4107 1 19960123 G 6210 206010200133 BLADE BELL 206 206B 1181511 SW M/R CORRODED B VE3R K NONE O OTHER IN INSP/MAINT 1 WP 23 3202X 3200 A448 3939 DURING A 1,200-HOUR INSPECTION, MAIN ROTOR BLADES WERE REJECTED DUE TO EXFOLIATION ON LEADING EDGE. TSN: 3,200. THESE BLADES HAVE A LIFE OF 5,000.0 HOURS. ACFT TT: 13,200.0 HOURS. 1 G 7 1 3U H2SW 1996082900211 19960829 00211 SW 1996 8 29 96ZZZX4108 1 19960123 G 6210 206010200133 BLADE BELL 206 206B 1181511 SW M/R CORRODED B VE3R K NONE O OTHER IN INSP/MAINT 1 WP 23 3202X 3200 A440 3939 DURING A 1,200-HOUR INSPECTION, MAIN ROTOR BLADES WERE REJECTED DUE TO EXFOLIATION ON LEADING EDGE. TSN: 3,200. THESE BLADES HAVE A LIFE OF 5,000.0 HOURS. ACFT TT: 13,200.0 HOURS. 1 G 7 1 3U H2SW 1996082900212 19960829 00212 SW 1996 8 29 96ZZZX4109 1 19960725 G 7160 476150041 GASKET BELL 47 47G5 1181032 SW CARB INLET MISINSTALLED H A A R UNSCHED LANDING AUTOROTATION R W PARTIAL RPM/PWR LOSS INADEQUATE Q C NR NOT REPORTED 1 WP 17 7885S 190 7873 DURING INVESTIGATION FOR CAUSE OF POWER LOSS AND AUTOROTATION OF AIRCRAFT, DISCOVERED GASKET BETWEEN AIR FILTER HOUSING AND CARBURETOR INLET HAD ONE CORNER FOLDED OVER ALLOWING DIRT TO ENTER AND BLOCK CARBURETOR AIR PASSAGES. SUBMITTER SUS PECTS IMPROPER INSTALLATION WHEN CARBURETOR WAS INSTALLED 190.4 HOURS PREVIOUSLY. 1 G 7 1 3O 2H3 1996082900213 19960829 00213 EU 1996 8 29 96ZZZX4110 1 19960718 G 5720 21211151052 STIFFENER CASA C212 C212200 2410304 EU LT/RT WINGS CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 15 311ST 9077 292 INSPECTION OF BOTH RIGHT AND LEFT WINGS PER CASA COM LETTER 212-224, FOUND STIFFENER ANGLES AFT OF FALSE SPAR CRACKED. 2 H 7 2 4T A43EU 1996082900214 19960829 00214 EU 1996 8 29 96ZZZX4111 1 19960718 G 5720 21211151061 STIFFENER CASA C212 C212200 2410304 EU LT/RT WINGS CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 15 311ST 9077 292 INSPECTION OF BOTH RIGHT AND LEFT WINGS PER CASA COM LETTER 212-224, FOUND STIFFENER ANGLES AFT OF FALSE SPAR CRACKED. 2 H 7 2 4T A43EU 1996082900215 19960829 00215 EU 1996 8 29 96ZZZX4112 1 19960718 G 5720 21211151072 STIFFENER CASA C212 C212200 2410304 EU LT/RT WINGS CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 15 311ST 9077 292 INSPECTION OF BOTH RIGHT AND LEFT WINGS PER CASA COM LETTER 212-224, FOUND STIFFENER ANGLES AFT OF FALSE SPAR CRACKED. 2 H 7 2 4T A43EU 1996082900216 19960829 00216 EU 1996 8 29 96ZZZX4113 1 19960718 G 5720 21211151082 STIFFENER CASA C212 C212200 2410304 EU LT/RT WINGS CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 15 311ST 9077 292 INSPECTION OF BOTH RIGHT AND LEFT WINGS PER CASA COM LETTER 212-224, FOUND STIFFENER ANGLES AFT OF FALSE SPAR CRACKED. 2 H 7 2 4T A43EU 1996082900217 19960829 00217 EU 1996 8 29 96ZZZX4114 1 19960718 G 5720 21211151092 STIFFENER CASA C212 C212200 2410304 EU LT/RT WINGS CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 15 311ST 9077 292 INSPECTION OF BOTH RIGHT AND LEFT WINGS PER CASA COM LETTER 212-224, FOUND STIFFENER ANGLES AFT OF FALSE SPAR CRACKED. 2 H 7 2 4T A43EU 1996082900218 19960829 00218 EU 1996 8 29 96ZZZX4115 1 19960718 G 5720 21211151101 STIFFENER CASA C212 C212200 2410304 EU LT/RT WINGS CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 15 311ST 9077 292 INSPECTION OF BOTH RIGHT AND LEFT WINGS PER CASA COM LETTER 212-224, FOUND STIFFENER ANGLES AFT OF FALSE SPAR CRACKED. 2 H 7 2 4T A43EU 1996082900219 19960829 00219 EU 1996 8 29 96ZZZX4116 1 19960718 G 5720 21211151102 STIFFENER CASA C212 C212200 2410304 EU LT/RT WINGS CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 15 311ST 9077 292 INSPECTION OF BOTH RIGHT AND LEFT WINGS PER CASA COM LETTER 212-224, FOUND STIFFENER ANGLES AFT OF FALSE SPAR CRACKED. 2 H 7 2 4T A43EU 1996082900220 19960829 00220 EU 1996 8 29 96ZZZX4117 1 19960718 G 5720 21211151112 STIFFENER CASA C212 C212200 2410304 EU LT/RT WINGS CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 15 311ST 9077 292 INSPECTION OF BOTH RIGHT AND LEFT WINGS PER CASA COM LETTER 212-224, FOUND STIFFENER ANGLES AFT OF FALSE SPAR CRACKED. 2 H 7 2 4T A43EU 1996082900221 19960829 00221 EU 1996 8 29 96ZZZX4118 1 19960718 G 5720 21211151121 STIFFENER CASA C212 C212200 2410304 EU LT/RT WINGS CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 15 311ST 9077 292 INSPECTION OF BOTH RIGHT AND LEFT WINGS PER CASA COM LETTER 212-224, FOUND STIFFENER ANGLES AFT OF FALSE SPAR CRACKED. 2 H 7 2 4T A43EU 1996082900222 19960829 00222 EU 1996 8 29 96ZZZX4119 1 19960718 G 5720 21211151122 STIFFENER CASA C212 C212200 2410304 EU LT/RT WINGS CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 15 311ST 9077 292 INSPECTION OF BOTH RIGHT AND LEFT WINGS PER CASA COM LETTER 212-224, FOUND STIFFENER ANGLES AFT OF FALSE SPAR CRACKED. 2 H 7 2 4T A43EU 1996082900223 19960829 00223 EU 1996 8 29 96ZZZX4120 1 19960718 G 5720 21211151132 STIFFENER CASA C212 C212200 2410304 EU LT/RT WINGS CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 15 311ST 9077 292 INSPECTION OF BOTH RIGHT AND LEFT WINGS PER CASA COM LETTER 212-224, FOUND STIFFENER ANGLES AFT OF FALSE SPAR CRACKED. 2 H 7 2 4T A43EU 1996082900224 19960829 00224 EU 1996 8 29 96ZZZX4121 1 19960718 G 5720 21211151141 STIFFENER CASA C212 C212200 2410304 EU LT/RT WINGS CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 15 311ST 9077 292 INSPECTION OF BOTH RIGHT AND LEFT WINGS PER CASA COM LETTER 212-224, FOUND STIFFENER ANGLES AFT OF FALSE SPAR CRACKED. 2 H 7 2 4T A43EU 1996082900225 19960829 00225 EU 1996 8 29 96ZZZX4122 1 19960718 G 5720 21211151142 STIFFENER CASA C212 C212200 2410304 EU LT/RT WINGS CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 15 311ST 9077 292 INSPECTION OF BOTH RIGHT AND LEFT WINGS PER CASA COM LETTER 212-224, FOUND STIFFENER ANGLES AFT OF FALSE SPAR CRACKED. 2 H 7 2 4T A43EU 1996082900226 19960829 00226 EU 1996 8 29 96ZZZX4123 1 19960718 G 5720 21211151152 STIFFENER CASA C212 C212200 2410304 EU LT/RT WINGS CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 15 311ST 9077 292 INSPECTION OF BOTH RIGHT AND LEFT WINGS PER CASA COM LETTER 212-224, FOUND STIFFENER ANGLES AFT OF FALSE SPAR CRACKED. 2 H 7 2 4T A43EU 1996082900227 19960829 00227 EU 1996 8 29 96ZZZX4124 1 19960718 G 5720 21211151162 STIFFENER CASA C212 C212200 2410304 EU LT/RT WINGS CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 15 311ST 9077 292 INSPECTION OF BOTH RIGHT AND LEFT WINGS PER CASA COM LETTER 212-224, FOUND STIFFENER ANGLES AFT OF FALSE SPAR CRACKED. 2 H 7 2 4T A43EU 1996082900228 19960829 00228 EU 1996 8 29 96ZZZX4125 1 19960718 G 5720 21211151192 STIFFENER CASA C212 C212200 2410304 EU LT/RT WINGS CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 15 311ST 9077 292 INSPECTION OF BOTH RIGHT AND LEFT WINGS PER CASA COM LETTER 212-224, FOUND STIFFENER ANGLES AFT OF FALSE SPAR CRACKED. 2 H 7 2 4T A43EU 1996082900229 19960829 00229 EU 1996 8 29 96ZZZX4126 1 19960718 G 5720 21213201061 STIFFENER CASA C212 C212200 2410304 EU LT/RT WINGS CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 15 311ST 9077 292 INSPECTION OF BOTH RIGHT AND LEFT WINGS PER CASA COM LETTER 212-224, FOUND STIFFENER ANGLES AFT OF FALSE SPAR CRACKED. 2 H 7 2 4T A43EU 1996082900231 19960829 00231 WP 1996 8 29 96ZZZX4128 1 19960808 G 2921 43645082 DIAPHRAGM 43442795002 DOUG DC8 DC871F 302199D WP HYD ACCUMULATOR RUPTURED B DM4R K NONE O OTHER IN INSP/MAINT 1 SO 19 8076U 225 85319028 45941 INSTALLED NEW DIAPHRAGM AND ACCUMULATOR INSTALLED IN AIRCRAFT 6-5-61. ACCUMULATOR REMOVED 7-25-96 FOR INTERNAL FAILURE. FOUND DIAPHRAGM RUPTURED AFTER 225 HOURS TIME IN SERVICE. 2 L 7 4 4F RT 4A25 1996082900232 19960829 00232 SW 1996 8 29 96ZZZX4129 1 19960802 G 3230 75006131 ARM ASSY GULSTM 690TP 695A 7630519 SW NLG LINKAGE CRACKED B IUMR K NONE O OTHER IN INSP/MAINT 1 SW 11 20GT 3400 96036 FOUND NLG ARM ASSY CRACKED FROM BOTH BOLT HOLES AND ALONG TUBE PORTION. TWO CRACKS FROM BOLT HOLES OUTBOARD AND ONE CRA CK FROM OUTER EDGE .75 INCH INBOARD ON PART. BOLT HOLE CRACKS FROM THESE BOLTS DO NOT APPEAR TO BE DEBURRS FROM INSTALL ATION. FOUND ON 100-HOUR INSPECTION. 1 H 7 2 4T 2A4 1996082900233 19960829 00233 EU 1996 8 29 96ZZZX4130 1 19960715 G 2910 751112 TUBE AMD FALC50 FALCON50MYST 2730106 EU HYDRAULIC PRESS CHAFE/LEAK B AMCR K NONE K FLUID LOSS IN INSP/MAINT 1 GL 09 254DV 6250 85 AFTER RETURNING FROM A FLIGHT, GROUND CREW NOTICED HYDRAULIC FLUID ON BOTTOM OF NR 1 PYLON. INVESTIGATION REVEALED THE HYDRAULIC SUPPLY AND PRESSURE LINES WERE CHAFING. BOTH LINES WERE CHAFED EVENLY, BUT THE PRESSURE LINE JUST STARTED TO LEAK. THE LINES WERE RUBBING AT APPROXIMATELY 3 INCHES FORWARD OF THE AFT BEND WHERE IT COMES OUT OF THE FUSELAGE AND S TARTS TO GO FORWARD THROUGH THE PYLON. NOTHING WAS OUT OF PLACE INCLUDING THE LINE CLAMPS. INSPECTION OF THE RIGHT PYL ON REVEALED GOOD CLEARANCE. INSTALLATION OF THE NEW LINES IN THE NR 1 PYLON RENDERED GOOD CLEARANCE. 2 L 7 3 4F A46EU 1996082900234 19960829 00234 EU 1996 8 29 96ZZZX4131 1 19960715 G 2910 751103 TUBE AMD FALC50 FALCON50MYST 2730106 EU HYDRAULIC SUPPLY CHAFE/LEAK B AMCR K NONE O OTHER IN INSP/MAINT 1 GL 09 254DV 6250 85 AFTER RETURNING FROM A FLIGHT, GROUND CREW NOTICED HYDRAULIC FLUID ON BOTTOM OF NR 1 PYLON. INVESTIGATION REVEALED THE HYDRAULIC SUPPLY AND PRESSURE LINES WERE CHAFING. BOTH LINES WERE CHAFED EVENLY, BUT THE PRESSURE LINE JUST STARTED TO LEAK. THE LINES WERE RUBBING AT APPROXIMATELY 3 INCHES FORWARD OF THE AFT BEND WHERE IT COMES OUT OF THE FUSELAGE AND S TARTS TO GO FORWARD THROUGH THE PYLON. NOTHING WAS OUT OF PLACE INCLUDING THE LINE CLAMPS. INSPECTION OF THE RIGHT PYL ON REVEALED GOOD CLEARANCE. INSTALLATION OF THE NEW LINES IN THE NR 1 PYLON RENDERED GOOD CLEARANCE. 2 L 7 3 4F A46EU 1996082900236 19960829 00236 SW 1996 8 29 96ZZZX4133 1 19960729 G 2434 ALV8402 ALTERNATOR PRESTOLITE GULSTM 500 500S 0141107 SW CASE MOUNT LUG BROKEN D K NONE O OTHER IN INSP/MAINT 1 EA 21 47RF 700 8000020 3261 WHILE COMPLETING 100-HOUR FACTORY INSPECTION, FOUND ALTERNATOR MOUNT LUG ON LEFT ALTERNATOR BROKEN, ALTERNATOR SYSTEM WA S OPERATING. MOUNTING LUG WAS BROKEN OFF CASE OF ALTERNATOR. EXCHANGE ALTERNATOR INSTALLED. 1 H 7 2 3O 6A1 1996082900237 19960829 00237 SO 1996 8 29 96ZZZX4134 1 19960727 G 3250 285692 VALVE LKHEED 1049 1049H82 5262122 SO NLG STEERING DEFECTIVE G O OTHER O OTHER LD LANDING 1 GL 15 6937C 5 4830 DURING LANDING AFTER FLY-BY DEMONSTRATION, ACFT VEERED OFF THE RUNWAY TO THE LEFT AND COMPLETED ROLL-OUT IN THE GRASS. A IRCRAFT WAS ABLE TO TAXI TO DISPLAY/TIE-DOWN AREA WITHOUT FURTHER INCIDENT. FIELD INVESTIGATION REVEALED THE NOSE GEAR STEERING VALVE PRESENTED A HYDRAULIC CONDITION THAT MADE THE NOSE GEAR DEFLECT HARD OVER TO THE LEFT. MINOR DAMAGE WAS DONE TO THE RIGHT NOSE TIRE AND WHEEL WHEN IT HIT A RUNWAY MARKER LIGHT. SUBMITTER STATED SINCE THIS UNIT WAS RECENTLY OVERHAULED, TESTING PROCEDURES MAY NOT BE ADEQUATE PRIOR TO INSTALLATION. 2 L 7 4 4R 6A5 1996082900238 19960829 00238 CE 1996 8 29 96ZZZX4135 1 19960722 G 3230 711701 VALVE RKWELL NA265 NA26540 6402608 CE MLG HYDRAULIC FAILED B EBVR K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 09 7KG 3 1177H 282111 AIRCRAFT WAS INITIALLY EXPERIENCING LANDING GEAR OPERATION PROBLEMS. PROBLEM WAS TROUBLESHOT TO A BAD LANDING GEAR HYDR AULIC CONTROL VALVE. REQUIRED A REPAIRED VALVE AND INSTALLED. ALL OPS CHECKS WERE GOOD. ON THE FIRST TRIP, PILOT REPO RTED HEARING THE HYDRAULIC POWERPACK CYCLING EXCESSIVELY. FOUND NEWLY INSTALLED REPAIRED VALVE TO BE BYPASSING INTERNAL LY. REMOVED AND REPLACED VALVE WITH ANOTHER REPAIRED VALVE. VALVE OPERATION WAS NORMAL. AIRCRAFT WAS RETURNED TO SERV ICE. 2 L 7 2 4J A2WE 1996082900239 19960829 00239 NM 1996 8 29 96ZZZX4136 1 19960701 G 5320 HAT CHANNEL BOEING 727 727243 138408D NM FS 1136-1166 CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 12411 22052 RT AFT LAVATORY HAT CHANNEL CORRODED BL 20R, STA 1136 TO STA 1166. FOUND DURING C10 CHECK ON CPCP INSPECTION. 2 L 7 3 4F RT A3WE 1996082900240 19960829 00240 WP 1996 8 29 96ZZZX4137 1 19960716 G 3610 AAM74141 DUCT DOUG DC10 DC10* WP BLEED SYSTEM FLANGE BROKEN B L4PR K NONE O OTHER IN INSP/MAINT 1 SW 01 THE DUCT WAS RECEIVED WITH ONE FLANGE RUPTURED AT A PREVIOUS WELD REPAIR LOCATION. ALL OTHER HIDDEN DAMAGE INSPECTION T O THE DUCT ASSEMBLY DID NOT REVEAL ANY SUBSEQUENT DAMAGE AS A RESULT OF THE DUCT FAILURE. WELD WAS AT A RADIUS OF THE F LANGE IN AN AREA NOT NORMALLY REPAIRABLE. 2 L 7 3 4F A22WE 1996082900241 19960829 00241 WP 1996 8 29 96ZZZX4138 1 19960801 G 3320 BR9708001 POWER LAMPHOLDER BRUCE BR9702931NW DOUG DC9 DC931 3022065 WP LIGHT SYSTEM BURN DAMAGE B ZZBR K NONE M OVER TEMP IN INSP/MAINT 1 WP 11 STC NR ST00092LA. TWO ITEMS RETURNED, BOTH WITH DATE CODE 9521. BOTH WITH SIMILAR DAMAGE. BURN DAMAGE RESTRICTED TO T HE LAMPHOLDER CONTACTS AND SURROUNDING AREA WITH AN 0.1 INCH AT THE LAMP CONTACT LOCATION. SUSPECT CAUSE IS ON INTERMIT TENT CONNECTION BETWEEN THE LAMP AND LAMPHOLDER. 2 L 7 2 4F A6WE 1996082900242 19960829 00242 WP 1996 8 29 96ZZZX4139 1 19960801 G 3320 BR9708001 POWER LAMPHOLDER BRUCE BR9702931NW DOUG DC9 DC931 3022065 WP LIGHT SYSTEM BURN DAMAGE B ZZBR K NONE O OTHER NR NOT REPORTED 1 WP 11 STC NR ST00092LA. BURN DAMAGE INCLUDED THE LAMPHOLDER FACEPLATE AND THE PRINTED CIRCUIT BOARD. THE FACEPLATE WAS DAMAG ED IN THE AREA BETWEEN BOTH CONTACTS AND EXTENDED TO ONE EDGE. THE CIRCUIT BOARD WAS BURNED THROUGH. THE HEAT GENERATI ON POINT APPEARS TO HAVE BEEN THE ELECTRICAL CONTACT BETWEEN THE LAMPHOLDER AND THE LAMP. SUSPECT CAUSE IS AN INTERMITT ENT CONNECTION BETWEEN THE COMPONENTS. DAMAGE TO THE CIRCUIT BOARD MAY INDICATE A SECONDARY FAILURE. 2 L 7 2 4F A6WE 1996082900333 19960829 00333 1996 8 29 96ZZZX4140 4 19960812 G 6122 D20594 DRIVE GEAR MCAULY DCFTS290D10 PROPELLER WORN B ME4D K NONE O OTHER IN INSP/MAINT 1 SO 15 820155 DURING INSPECTION OF GOVERNOR, SPLINE IN DRIVE GEAR WAS FOUND WORN. GOVERNOR WAS RETURNED TO CUSTOMER. 1996082900334 19960829 00334 CE 1996 8 29 96ZZZX4141 1 19960802 G 3220 074214610 BRACKET CESSNA 185 A185F 2072821 CE TAIL STINGER CRACKED D A K NONE O OTHER IN INSP/MAINT 1 AL 01 1047F 18502704 FREE-PLAY WAS OBSERVED IN TAIL WHEEL STINGER DURING SERVICING OF TAIL WHEEL. TAIL CONE WAS REMOVED AND BRACKET FOUND CR ACKED AROUND BOLT HOLE UNDER NUT. PART WAS REPLACED WITH NEW FROM FACTORY. 1 H 7 1 3O 3A24 1996082900335 19960829 00335 EA 1996 8 29 96ZZZX4142 2 19960418 G 8530 LW14115 CYLINDER PIPER PA31 PA31P 7103120 SO LYC O541 TIGO541E1A 41539 EA NR 1 CYL SLEEVE CRACKED H K NONE K FLUID LOSS IN INSP/MAINT 1 GL 25 17PS 321 31P7630008 RL62362 HOBBS - 3,213.6 HOURS. OIL APPEARED AROUND NR 1 CYLINDER PUSH ROD TUBES. SEALS REPLACED, GROUND CHECK OPS GOOD. AFTER FLIGHT, OIL APPEARED AGAIN. REMOVED NR 1 CYLINDER, FOUND CYLINDER SLEEVE CRACKED APPROXIMATELY THREE-FOURTHS OF CIRCUM FERENCE. LOG REVEALED THIS TO BE THE 3RD CYLINDER ON NR 1 IN 4 YEARS. PISTON P/N LW 10545 SHOWED SIGNS OF BEING HOT. S USPECT OIL NOZZLE FOR PISTON COOLING INOPERATIVE. REPLACED NOZZLE, P/N 73772. REPLACED CYLINDER KIT, P/N 05K21116-3, A ND ASSOCIATED SEALS AND GASKETS. PISTON SKIRT WAS OIL COKED AND DISCOLORED. 1 L 7 2 3O 3 O A8EA E19EA 1996082900336 19960829 00336 SO 1996 8 29 96ZZZX4143 1 19960703 G 3230 6703102 FITTING PIPER PA34 PA34200T 7103406 SO GEAR RETRACT BROKEN B MN3R O OTHER P NO WARNING INDICATION AP APPROACH 1 WP 11 2191Z 3677 347970212 DURING APPROACH TO LANDING AND GEAR EXTENSION, LEFT MLG FAILED TO INDICATE DOWN AND LOCKED (NO GREEN LIGHT). LANDING GE AR UNSAFE LIGHT AND GEAR PUMP BOTH REMAINED ON. UNEVENTFUL LANDING MADE, MAINTENANCE FOUND GEAR UNLOCKED AND FITTINGS H OLES BROKEN OUT (LOCK TURNBUCKLE HOLES). ONE SIDE SHOWED INTERGRANULAR CORROSION ALONG CRACK, OTHER SIDE HAD CLEAN BREA K. 1 L 7 2 3O A7SO 1996082900337 19960829 00337 SO 1996 8 29 96ZZZX4144 1 19960521 G 3230 5541602 CONTROL CABLE PIPER PA31 PA31325 7103105 SO MLG CONTROL BROKEN H A O OTHER O OTHER AP APPROACH 1 GL 25 732WC 7629 317512049 WHEN PILOT SELECTED GEAR DOWN POSITION, HE HEARD A SNAP AND HANDLE FELL LOOSELY TO DOWN POSITION. UNABLE TO LOWER GEAR. GEAR 'UP' LANDING WAS PERFORMED. FOUND LANDING GEAR CONTROL CABLE BROKEN INSIDE THE OUTER HOUSING NEAR GEAR HANDLE EN D. SUSPECT CABLE FAILED DUE TO FATIGUE DUE TO AGE AND NUMBER OF CYCLES. NO EVIDENCE OF CORROSION OR OTHER DAMAGE WERE FOUND. 1 L 7 2 3O A20SO 1996082900339 19960829 00339 EA 1996 8 29 96ZZZX4146 2 19960410 G 7420 P-LEAD PIPER PA32 PA32RT300 7103215 SO LYC O540 IO540K1G5 41532 EA FIREWALL SHORTING H K NONE O OTHER IN INSP/MAINT 1 GL 25 376AA 32R7885094 L1803048A TROUBLESHOOTING FOR INTERMITTENT INOPERATIVE CONDITION ON RT MAGNETO FOUND P-LEAD SHORTING WHERE IT EXITS THROUGH FIREWA LL. REPLACED P-LEADS AND INSTALLED PLASTIC SLEEVING. 1 L 7 1 3O 3 O A3SO 1E4 1996082900340 19960829 00340 SO 1996 8 29 96ZZZX4147 1 19960718 G 2140 B3040 HEATER JANITROL PIPER PA31 PA31325 7103105 SO AIR INLET BIRD NEST D P A K NONE O OTHER IN INSP/MAINT 1 SW 13 4074K 318112019 PILOT REPORTED GRASS BLOWING OUT OF DEFROSTER. FOUND BIRD NEST INSIDE OF HEATER INLET, IN BLOWER FAN, AND INSIDE HEATER AROUND BURNER CAN. SUGGEST SCREEN INSTALLED IN INLET TO HEATER AND MORE THOROUGH PRE-FLIGHT. 1 L 7 2 3O A20SO 1996082900341 19960829 00341 EA 1996 8 29 96ZZZX4148 2 19960812 G 7414 1035110 BEARING D4RN1021 CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA MAG REAR FAILED H K NONE O OTHER IN INSP/MAINT 1 SW 99 4949G 822 4083837 17273496 L537776 MAGNETO POINTS WERE NOT OPENING DUE TO EXCESSIVE WEAR ON THE POINTS' CAM FOLLOWER. THIS WEAR WAS ACCELERATED BY A HEAT BUILD-UP ON THE MAGNETO SHAFT GENERATED BY A FAILED REAR BEARING. 1 H 7 1 3O 3 O NT 3A12 E274 1996082900342 19960829 00342 SO 1996 8 29 96ZZZX4149 1 19960718 G 2750 6378100 FLAP HANDLE PIPER PA28 PA28140 7102802 SO CABLE ATTACH WORN D K NONE O OTHER IN INSP/MAINT 1 EA 25 56678 5055 287425016 C/W PIPER SB 965 ON 10-29-93 AT 3,481.3 HOURS. C/W AD 96-10-03 ON 7-18-96 AT 5,054.8 HOURS. FOUND FLAP HANDLE, BUSHING INSTALLED IAW SB 965 AND BOLT AT CABLE ATTACH WORN ALMOST THROUGH. PART LASTED 3,481 HOURS WITH NO PROBLEM. C/W SB 96 5 AND PART WAS WORN OUT IN 1,753 HOURS. SUBMITTER SUGGESTS ADDING 500-HOUR INSPECTION INTERVALS TO AD 96-10-03. 1 L 7 1 3O 2A13 1996082900343 19960829 00343 CE 1996 8 29 96ZZZX4150 1 19960726 G 5520 59343001 ELEVATOR CESSNA 425 425 2076018 CE LT SIDE MISMANUFACTURED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 01 6773L 4250073 RECEIVED 'NEW' PART, DROP SHIPPED FROM CESSNA AIRCRAFT. PREPPED AND PAINTED TO MATCH AIRCRAFT. PLACED CONTROL SURFACE ON BALANCING JIG. PART REQUIRED 6 OUNCES OF ADDITIONAL COUNTERWEIGHT TO BRING WITHIN PRESCRIBED LIMITS. REMOVED EXISTI NG LT ELEVATOR DUE TO MINOR HANGAR DAMAGE. ATTEMPTED TO INSTALL 'NEW' PART ON ACFT. HINGE BOLTS WERE INSTALLED AND IT WAS DETERMINED THERE WAS INSUFFICIENT CLEARANCE BETWEEN THE WEIGHT RIB AND HORIZONTAL STABILIZER. ALSO, THE TORQUE TUBE FLANGE WAS NOT PROPERLY INDEXED AND COULD NOT BE CORRECTED BY NORMAL RIGGINGS. 1 L 7 2 3T RT A7CE 1996082900344 19960829 00344 SO 1996 8 29 96ZZZX4151 2 19960807 G 7310 6410321147 VALVE PIPER PA34 PA34200T 7103406 SO CONT O360 TSIO360EB 17025 SO FUEL MANIFOLD LEAKING B APCR K NONE K FLUID LOSS IN INSP/MAINT 1 NM 01 666HL 54 ED89606CK 347770235 809072R FUEL MANIFOLD VALVE HAS FUEL LEAKING FROM TOP OF UNIT. INCREASE TORQUE VALUE FOR SCREWS. 1 L 7 2 3O 3 O A7SO E9CE 1996082900345 19960829 00345 SO 1996 8 29 96ZZZX4152 1 19960729 G 2750 480715 PIN PIPER PA28 PA28140 7102802 SO FLAP CONTROL SHEARED D L A K NONE O OTHER IN INSP/MAINT 1 EA 07 8159N 2825354 THE RECENT AD 96-10-03 ADDRESSES THE ATTACHMENT OF THE FLAP CONTROL CABLE TO THE FLAP HANDLE ON THE PA28 SERIES AIRCRAFT . WHILE COMPLYING WITH THIS AD, FOUND THE PIN (WHICH FORMS PART OF THE RATCHETING MECHANISM TO SELECT FLAPS DOWN) SHEAR ED INTO TWO PARTS. SUBMITTER STATED THIS IS 3RD TIME TO FIND A SHEARED PIN ON THIS MODEL OF PIPER. 1 L 7 1 3O 2A13 1996082900346 19960829 00346 CE 1996 8 29 96ZZZX4153 1 19960701 G 2810 369200152 FUEL TANK USRUBBER BEECH 58 58 1152740 CE ANTI-SLOSH DETERIORATED B P A DVPR K NONE O OTHER IN INSP/MAINT 1 SO 03 9737S TH671 THE SPONGE-LIKE MATERIAL USED IN THIS TANK BEGAN TO DETERIORATE/DISENTEGRATE. THIS BECAME APPARENT WHEN PILOT BEGAN NOT ICING SMALL DARK PARTICLES IN FUEL SAMPLE OF RT INBOARD QUICK DRAIN ON PRE-FLIGHT INSPECTION. PARTICLE QUANTITY INCREAS ED AND RAN SAMPLE THROUGH A FILTER AND DETERMINED WHAT PARTICLES WERE. UPON REMOVAL, FOUND MOST OF SPONGE MATERIAL LOOS E IN TANK. SUBMITTER FEELS THIS CAME ABOUT AS A RESULT OF AGE ON TANK (24 YEARS) AND 100LL GAS ACTING ON PLASTIC-LIKE S PONGE MATERIAL. 1 L 7 2 3O 3A16 1996082900347 19960829 00347 CE 1996 8 29 96ZZZX4154 1 19960710 G 2750 2111031001 FLAP FOLLOW-UP STEC 602 BEECH 35 S35 1151532 CE LT WING FLAP SEIZED D O OTHER F FLT CONT AFFECTED NR NOT REPORTED 1 GL 17 5826K D7842 FLAPS FAILED TO EXTEND. FOUND AUTOPILOT FOLLOW-UP IN LEFT WING SEIZED IN THE AFT POSITION ALLOWING THE ACTUATING WIRE T O MOVE OVER FLAP MICROSWITCH AND NOT ALLOWING FLAP TO EXTEND. LUBRICATED SHAFT OF FOLLOW-UP AND SYSTEM OPERATES CORRECT LY. NEW SERVO FOLLOW-UP ON ORDER. 1 L 7 1 3O 3A15 1996082900348 19960829 00348 1996 8 29 96ZZZX4155 4 19960808 G 2562 BP1025 BATTERY COMMUNCOMP CIR10 BEECH 95 95B55 1152729 CE ELT CORRODED H K NONE O OTHER IN INSP/MAINT 1 GL 15 712BP 4155 TC1520 REPLACED BATTERY (ELT) BP-1025 PURCHASED FROM TRIM-CRAFT, JUNE, 1994. ELT TESTED OK; THEN, JUNE, 1995 WAS OK AT THAT AN NUAL TIME. AT THIS YEAR'S ANNUAL, TESTED ELT. SIGNAL OK, BUT FOUND CASE AND AREA OF ELT MOUNTING LOCATION FULL OF CORR OSION. CALLED COMMUNICATION CORP AND WAS TOLD THEY NEVER HEARD OF THAT. UNIT WAS SENT TO THEM FOR ANALYSIS OF UNIT. 1 L 7 2 3O RT 3A16 1996082900349 19960829 00349 EA 1996 8 29 96ZZZX4156 2 19960728 G 7414 M3081 CONTACT POINTS SLICK 4373 CESSNA 172 172P 2072436 CE LYC O320 O320D2J 41508 EA MAGNETO SPRING DEFECT D K NONE O OTHER IN INSP/MAINT 1 SO 13 73785 239 94090132 17267677 AIRCRAFT LANDED AFTER CROSS-COUNTRY. WHEN THE PILOT ATTEMPTED TO DEPART, ENGINE WOULD NOT START. TROUBLESHOOTING DETER MINED THE POINTS IN THE LEFT MAGNETO WOULD NOT CLOSE COMPLETELY. GAP WAS WITHIN TOLERANCE. RETURN SPRING APPEARED TO B E BOWED, NOT SUPPLYING ENOUGH TENSION. INSTALLED NEW CONTACT KIT. 1 H 7 1 3O 3 O NT 3A12 E274 1996082900350 19960829 00350 SO 1996 8 29 96ZZZX4157 1 19960806 G 8120 3AT6EE10J2 TURBOCHARGER GARRTT PIPER PA34 PA34200T 7103406 SO CONT O360 TSIO360EB 17025 SO RT ENGINE LOCKED UP E K NONE P NO WARNING INDICATION IN INSP/MAINT 1 SW 11 98HD 1258 347870461 PILOT APPLIED POWER TO RIGHT ENGINE FOR PRE-FLIGHT CHECK. ENGINE WOULD ONLY TURN UP TO 26 INCHES MAN/PRESSURE. FOUND T URBO HAD LOCKED UP. INSTALLED OVERHAULED TURBO, ENGINE GROUND RAN, CHECKED NORMAL. AIRCRAFT TEST FLOWN, ALL CONDITIONS NORMAL. 1 L 7 2 3O 3 O A7SO E9CE 1996082900351 19960829 00351 1996 8 29 96ZZZX4158 4 19960530 G 3416 3431 CASTING UNITEDINST 593RPA56 MOONEY M22 M22 5870402 SW ALTIMETER CREEP B EI4R K NONE O OTHER IN INSP/MAINT 1 SO 15 E54 THE END SHAKE ON THE THREE CRITICAL MECHANISM SHAFTS WERE MEASURED. TWO OF THE SHAFTS HAD END SHAKES OF .0003 INCH. AN ALERT SERVICE BULLETIN PUT OUT BY THE MANUFACTURER INDICATED THAT AN END SHAKE OF .0004 INCH OR LESS WOULD CAUSE POINTE R HANG-UP AT THE LOW OPER TEMPERTURE. 1 L 7 1 3O A6SW 1996082900352 19960829 00352 NM 1996 8 29 96ZZZX4159 1 19960701 G 5711 SPAR UNIVAR 415 415E 0420308 NM LT/RT WING AFT CORRODED D K NONE O OTHER IN INSP/MAINT 1 SW 99 4914 REPORTING FINDINGS OF INSPECTION REQUIRED IN AD 94-18-04. EVIDENCE FOUND OF CORROSION BETWEEN PARTS OF REAR SPAR IN LEF T WING. SAME CONDITION FOUND IN RIGHT WING AS WELL AS A PORTION OF EXFOLIATION FOUND IN BOTTOM SPAR CAP, AFT SIDE, ABOU T A FOOT FROM THE OUTBOARD END. 1 L 7 1 3O A787 1996082900353 19960829 00353 WP 1996 8 29 96ZZZX4160 1 19960804 G 3246 9560892 BOLT GY189 DOUG DC9 DC9* WP WHEEL TIE BOLT FAILED D K NONE O OTHER NR NOT REPORTED 1 GL 17 DEFECT: WHEEL TIE BOLT FAILURE. SUSPECT CAUSE: FATIGUE. 2 L 7 2 4F A6WE 1996082900354 19960829 00354 NM 1996 8 29 96ZZZX4161 1 19960807 G 5753 6521758 FITTING 652163475 BOEING 707 727100 1384036 NM INBD AFT FLAP CORRODED H K NONE O OTHER IN INSP/MAINT 1 SW 13 BN77 AFT PORTION OF ONE CARRIAGE SUPPORT FITTING FOUND EXFOLIATION ONCE THE LEADING EDGE CAP WAS REMOVED FROM SPAR. FND CORR OSION ON MATING SURFACES OF L/E CAP AND SPAR. FLAP IN SHOP FOR COMPLETE HONEYCOMB/SKIN REPLACMENT AND OVERHAUL. DUE TO DESIGN, AFT PORTION OF FITTING AND FWD FACE OF SPAR FITTING CANNOT BE INSPECTED DUE TO INACCESSABILITY. OHM HAS NOTHIN G ON INSP OF THESE FITTINGS AND FWD FACE OF SPAR IN AREAS THAT ARE INACCESSIBLE, AND NOTHING ABOUT SEPARATING L/E FROM S PAR FOR INSP. SUBMITTER RECOMMENDS OHM BE AMENDED TO INCLUDE SEPARATION OF L/E CAP FROM SPAR FOR FURTHER INSP ON ALL FL APS OF THIS DESIGN. 2 L 7 3 4F RT A3WE 1996082900355 19960829 00355 NM 1996 8 29 96ZZZX4162 1 19960801 G 5320 SHEAR WEB BOEING 727 727243 138408D NM FS 1136-1166 CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 12411 22052 RIGHT AFT LAVATORY SHEAR WEB CORRODED FROM STA 1136 TO STA 1166, BL 20R TO BL 45R. FOUND ON CPCP INSPECTION UNDER C10 C HECK. 2 L 7 3 4F RT A3WE 1996082900356 19960829 00356 CE 1996 8 29 96ZZZX4163 1 19960802 G 2435 1545924 BAND ALIDSIGNAL 30B10719A LEAR 55 55LEAR 5170702 CE GENERATOR ROTOR SEPARATED B PW2R K NONE W INADEQUATE Q C NR NOT REPORTED 1 CE 07 127GT 122 1333 067 BAND SEPARATED FROM ROTOR CAUSING CATASTROPHIC FAILURE OF ROTOR AND STATOR. BAND IS NOT AS SPECIFIED OR SUPPLIED ON THE GENERATOR BY ALLIED SIGNAL. PART DOES NOT CONFORM TO DESIGN DATA. APPEARS UNAUTHORIZED REPAIR MADE TO ROTOR USING UNA UTHORIZED PARTS. REPAIR OF ROTOR NOT AUTHORIZED BY REPAIR MANUAL. 2 L 7 2 4F A10CE 1996082900357 19960829 00357 NM 1996 8 29 96ZZZX4164 1 19960809 G 2121 13B63352 BEARING SUNDSTRANDEM 5007024620 BOEING 737 737210C 1384459 NM GASPER FAN FAILED B DM4R K NONE O OTHER IN INSP/MAINT 1 SO 19 290 AA51542 BEARING COMPLETELY DESTROYED. BEARING INSTALLED NEW AND FAILED AFTER 289.80 HOURS OF OPERATION. FAN TRIPPED CIRCUIT BR EAKER, IMPELLER OF FAN RUBS ON FAN HOUSING. 2 L 7 2 4F A16WE 1996082900358 19960829 00358 WP 1996 8 29 96ZZZX4165 1 19960726 G 3320 BR9708001 POWER LAMPHOLDER BRUCE BR9702931NW DOUG DC9 DC931 3022065 WP LIGHT SYSTEM BURNED B L ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 MAIN HOUSING HAS A BURN HOLE APPROX 1 INCH BY 0.5 INCH ON RT HAND SIDE WHICH EXPOSED INTERNAL CIRCUITRY. REMAINING MAJO RITY OF PLASTIC HOUSING DISTORTED WITH BULGING OF CONTOUR SURFACE IN A FEW LOCATIONS, AND DISCOLORATION FROM OVERHEATING . INDUCTOR AND OVERCURRENT FUSE ARE VISIBLE THROUGH BURN HOLE. FUSE METAL END CAP AND ITS ASSOC AXIAL LEAD HAVE MELTED . THERE ARE 2 DISTINCT FAILURE MODES IN EVIDENCE; CAPACITOR FAILURE AND A SHORT CIRCUIT BETWEEN THE OVERCURRENT FUSE AN D INDUCTOR. DEGREE OF FAILURE IS UNPRECEDENTED DUE TO COMBINED FAILURE MODES. WHEN OVERCURRENT FUSE SHORTED TO THE IND UCTOR, IT ALSO SHORTED OUT THERMOSTAT AND THERMAL FUSE LEAVING CIRCUIT UNPROTECTED FROM CAPACITOR FAILING. THERE IS INS 2 L 7 2 4F A6WE 1996082900359 19960829 00359 CE 1996 8 29 96ZZZX4166 1 19960628 G 2842 EA8182069 SENSOR RKWELL NA265 NA26540 6402608 CE NR 7 TANK INOPERATIVE B OPER K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 09 B1919141 RECEIVING INSPECTION CONDUCTED BY RAYTHON AEROSPACE. THERE IS 'NO WAY' THAT THIS NR 7 FUEL QUANTITY TANK UNIT COULD HAV E BEEN BENCH CHECKED/FUNCTIONAL TESTED. RECEIVING INSPECTION READINGS WERE 35MMF'S AND WOULD NOT 'NULL' READINGS SUGGES T THAT THE UNIT IS WIRED IN REVERSE. 2 L 7 2 4J A2WE 1996082900360 19960829 00360 EA 1996 8 29 96ZZZX4167 2 19960608 G 7313 3035228 FUEL NOZZLE PWA PT6 PT6A65B 52043 EA RT ENGINE DEFECTIVE B MASR O OTHER M J OVER TEMP WARNING INDICATION CL CLIMB 1 SW 01 2FOR 1195 97169 AT CLIMB-OUT THE CREW NOTICED THE RT ITT CLIMBING PAST RED LINE. POWER LEVER WAS PULLED BACK UNTIL ITT WAS RED LINE. T HERE WAS ONLY 1,200 POUNDS OF TORQUE NOTED. WHEN THE ENGINE HOT SECTION WAS REMOVED, THE CT VANE RING HAD ONE VANE WITH 99 PERCENT OF THE VANE AREA MELTED OR BURNED AWAY. THE CT BLADES WERE DISCOLORED DUE TO HIGH TEMP. AT THIS POINT OF T HE INVESTIGATION, THE FUEL NOZZLE SET IS THE SUSPECTED CAUSE FOR FOR THE HOT SECTION DAMAGE. 4 T E4EA 1996082900364 19960829 00364 CE 1996 8 29 96ZZZX4168 1 19960630 G 2710 656501620 CONTROL CABLE CESSNA 500 S550 2076607 CE INBD AILERON FRAYED B A CWQR K NONE O OTHER IN INSP/MAINT 1 GL 05 157QS 4402 S5500157 DURING PHASE 12 INSPECTION, FOUND LOWER INBOARD AILERON CABLE WITH BROKEN WIRES. THIS WEAR/DAMAGE OCCURS AT FAIRLEADS P /N S338-1. INSPECTION FOUND TEFLON FAIRLEAD DAMAGES THIS CABLE ABOUT 75 PERCENT OF THE TIME. SUBMITTER STATED SOMETHIN G NEEDS TO BE DONE ABOUT THE WEAR/DAMAGE CAUSED BY THIS FAIRLEAD. 1 L 7 2 4F RT A22CE 1996082900365 19960829 00365 SO 1996 8 29 96ZZZX4169 1 19960729 G 3222 6705403 TRUNNION 6710008 PIPER PA44 PA44180 7104402 SO NLG FAILED D A O OTHER J WARNING INDICATION AP APPROACH 1 SO 15 22390 5031 447995066 AFTER VARIOUS ATTEMPTS TO GET A LOCKED INDICATION (GREEN LIGHT) FOR THE NOSE GEAR, A GREEN INDICATION WAS NOTED AND A NO RMAL LANDING WAS ACCOMPLISHED. AIRCRAFT MAINTENANCE FOUND THE ALUMINUM CASTING FOR THE NLG TRUNNION ASSY HAD FAILED WHE RE THE CENTERING SPRING ASSY, PN 86636-02, ATTACH BRACKET ASSY, PN 67114-00, BOLTS TO THE NLG TRUNNION. THIS ALLOWED TH E CENTERING SPRING TO ROTATE AND JAM THE NOSE GEAR IN WHEELWELL. SUBMITTER SUGGESTS INSPECTION OF THIS AREA AT 100-HOUR INTERVALS. 1 L 7 2 3O A19S0 1996082900366 19960829 00366 EU 1996 8 29 96ZZZX4170 1 19960809 G 5553 3301028709 ATTACH FITTING FOKKER F27 F27MK200 4990620 EU VERTICAL STAB CRACKED B S MJ7R K NONE O OTHER IN INSP/MAINT 1 GL 05 279MA 10297 WHILE PERFORMING A C-CHECK ON THIS AIRCRAFT, DISCOVERED THROUGH AN EDDY CURRENT INSPECTION THAT A VERTICAL CRACK EMITTIN G FROM THE ATTACH BOLT TO OUTER EDGE, TYPE 'A' AS DEFINED IN SB F27/55-48, LOCATED IN RIGHT REAR FORWARD ATTACH FITTING LUG. UPON CONFERENCING WITH EAGLE AIR, THE DETERMINATION WAS MADE TO REPLACE THE ENTIRE RIGHT REAR ATTACH FITTING. 2 H 7 2 4T A817 1996082900367 19960829 00367 CE 1996 8 29 96ZZZX4171 1 19960812 G 3830 17000382 PUMP CESSNA 500 S550 2076607 CE TOILET FLUSH MOTOR SEIZED B CWQR K NONE O OTHER IN INSP/MAINT 1 GL 05 299QS 7773 1949 S5500099 CREW REPORTED TOILET WOULD NOT FLUSH. FOUND MOTOR/PUMP ASSEMBLY LOCKED UP TIGHT. THIS IS A COMMON OCCURRENCE AS THE PU MP IMPELLER SWELLS AND JAMS IN THE PUMP HOUSING. NEED TO USE A MOTOR/PUMP ASSEMBLY THAT IS RESISTANT TO 'BLUE WATER'. 1 L 7 2 4F RT A22CE 1996082900368 19960829 00368 CE 1996 8 29 96ZZZX4172 1 19960806 G 2430 M22759749 WIRE BEECH 100 B100 1152919 CE LT/RT START/GEN CRACKED B A VO2R K NONE O OTHER IN INSP/MAINT 1 WP 01 300R 4793 BE110 THE STARTER/GENERATOR 4-GAUGE WIRES THAT RUN FROM FIREWALL POWER CONNECTOR AND GENERATOR GROUND TO THE STARTER/GENERATOR , WERE FOUND WITH CRACKED INSULATION. THE CRACKS RUN PARALLEL WITH THE WIRE. SOME OF THE CRACKS ARE OVER 3 INCHES IN L ENGTH EXPOSING THE CENTER CONDUCTOR. THE CRACKS ARE ON THE OUTSIDE OF BENDS AND IN STRAIGHT SECTIONS. ON THE LEFT AND RIGHT ENGINES THE WIRE NUMBERS OF THE DEFECTIVE WIRES ARE K2D4, K2F4, P10A4, P10C4, P10E4, K17A4N, K17B4N, AND K17C4N. 1 L 7 2 4T A14CE 1996082900369 19960829 00369 NM 1996 8 29 96ZZZX4173 1 19960814 G 5314 65564417 KEELBEAM BOEING 727 727230 1384080 NM BS 950 CORRODED B EB1R K NONE O OTHER IN INSP/MAINT 1 EA 13 360PA 20676 WHILE PERFORMING A KEELBEAM INSPECTION DURING A C-CHECK, THE LT KEELBEAM WAS FOUND WITH SEVERE CORROSION OVER THE ENTIRE LENGTH OF THE BEAM MAINLY ON THE LT MOUNTING FLANGE AREA AND THE VERTICAL LEG. AT ONE POINT BETWEEN BS 950F AND BS 970 , CORROSION HAD EATEN COMPLETELY THROUGH THE VERTICAL LEG OF THE BEAM CREATING A HOLE 5 INCHES IN LENGTH WITH CRACKS EXT ENDING FROM THE ENDS OF THE HOLE. NUMEROUS CRACKS WERE NOTED IN THE LOWER RADIUS OF THE VERTICAL LEG. TYPES OF CORORSI ON NOTED EXFOLIATION, INTERGRANULAR, SURFACE, AND SEVERE PITTING. KEELBEAM WAS REMOVED AND REPLACED. 2 L 7 3 4F A3WE 1996082900370 19960829 00370 SO 1996 8 29 96ZZZX4174 1 19960809 G 5755 400502 SPOILER GULSTM G1159 GIV 3980115 SO LT INBOARD SCRAPED D K NONE O OTHER IN INSP/MAINT 1 EA 25 399CC 3560 063398897 1051 UPON COMPLETION OF MAJOR REFURBISH AND EXTERIOR PAINT, ACFT RETURNED TO EWR. AFTER SEVERAL FLIGHTS, BOTH LEFT AND RIGHT INBOARD FLIGHT SPOILERS DAMAGED DUE TO INSUFFICIENT CLEARANCE BETWEEN SPOILER LEADING EDGE AND WING SKIN. SUSPECT EXCE SSIVE PAINT BUILD-UP ABSORBING REQUIRED CLEARANCE. 2 L 7 2 4F RT A12EA 1996082900371 19960829 00371 SO 1996 8 29 96ZZZX4175 1 19960809 G 5755 400502 SPOILER GULSTM G1159 GIV 3980115 SO RT INBOARD SCRAPED D K NONE O OTHER IN INSP/MAINT 1 EA 25 399CC 3560 03598897 1051 UPON COMPLETION OF MAJOR REFURBISH AND EXTERIOR PAINT, ACFT RETURNED TO EWR. AFTER SEVERAL FLIGHTS, BOTH LEFT AND RIGHT INBOARD FLIGHT SPOILERS DAMAGED DUE TO INSUFFICIENT CLEARANCE BETWEEN SPOILER LEADING EDGE AND WING SKIN. SUSPECT EXCE SSIVE PAINT BUILD-UP ABSORBING REQUIRED CLEARANCE. 2 L 7 2 4F RT A12EA 1996082900372 19960829 00372 SW 1996 8 29 96ZZZX4176 1 19960729 G 2720 53006515 BRACKET GULSTM 500 500S 0141107 SW RUDDER PULLEY CRACKED D A K NONE O OTHER IN INSP/MAINT 1 EA 21 47RF 11068 3261 WHILE COMPLETING 200-HOUR FACTORY INSPECTION OF NOSE AREA, FOUND BOTH PULLEY BRACKETS CRACKED AT BEND RADIUS. PULLEY IS FOR RUDDER CABLE AND IS SUPPORTED BY THESE TWO BRACKETS. REPLACED CRACKED BRACKETS WITH SUPERCEDING PART NUMBERS FROM MANUFACTURER. SUBMITTER SUGGESTS CLOSE INSPECTION OF BRACKETS AND REPLACMENT IF CRACKS ARE FOUND. NO SERVICE BULLETIN EXISTS ON THESE BRACKETS. 1 H 7 2 3O 6A1 1996082900373 19960829 00373 SW 1996 8 29 96ZZZX4177 1 19960729 G 2720 53006516 BRACKET GULSTM 500 500S 0141107 SW RUDDER PULLEY CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 21 47RF 11068 3261 WHILE COMPLETING 200-HOUR FACTORY INSPECTION OF NOSE AREA, FOUND BOTH PULLEY BRACKETS CRACKED AT BEND RADIUS. PULLEY IS FOR RUDDER CABLE AND IS SUPPORTED BY THESE TWO BRACKETS. REPLACED CRACKED BRACKETS WITH SUPERCEDING PART NUMBERS FROM MANUFACTURER. SUBMITTER SUGGESTS CLOSE INSPECTION OF BRACKETS AND REPLACMENT IF CRACKS ARE FOUND. NO SERVICE BULLETIN EXISTS ON THESE BRACKETS. 1 H 7 2 3O 6A1 1996082900375 19960829 00375 CE 1996 8 29 96ZZZX4178 1 19960724 G 7830 650161 SWITCH ROHR 225012509 BEECH MU300 400A 1155402 CE T/R DEPLOY FAILED B KI2R K NONE O OTHER IN INSP/MAINT 1 CE 01 85CR 1220 RK22 THRUST REVERSER CONTROL CIRCUIT BREAKER ON LEFT SIDE 'POPPED' WHEN REVERSERS WERE ACTUATED. TROUBLESHOOTING DETERMINED THRUST REVERSER CONTROL BOX, P/N 45A5888656-5, HAD BURNT RESISTOR AND TRANSISTOR IN THE THROTTLE T/R LOCK HOLDING SOLENO ID CIRCUITS. T/R THROTTLE LOCK SOLENOID MEASURED AND FOUND RESISTANCE TO BE EXTREMELY LOW. (P/N 18578-01.) FURTHER TR OUBLESHOOTING DETERMINED REVERSER DEPLOY LIMIT SWITCH TO HAVE STUCK CONTACTS THAT, CONSEQUENTLY, KEPT LOCK SOLENOID ACTU ATED. 2 H 7 2 4F RT A16SW 1996082900604 19960829 00604 SW 1996 8 29 96ZZZX4183 1 19960413 G 6230 206010336005 DRIVE LINK BELL 206 206L1 1182107 SW M/R MAST WORN B ZV1R K NONE O OTHER IN INSP/MAINT 1 SW 03 5000G 45163 PLAY IN EXCESS OF .025 INCH AT TWO PLACES. SEE BELL MM L3, FIGURE 62.21. AT TEAR DOWN FOUND BEARINGS AND SPACERS WORN. TOTAL TIMES LESS THAN 1,000 HOURS AND 1 YEAR SINCE REPLACED. 1 G 7 1 3U H2SW 1996082900605 19960829 00605 EU 1996 8 29 96ZZZX4184 1 19960701 G 7714 65201008 INDICATOR BOLKMS 105 BO105S 5626006 EU TRIPLE TACH MALFUNCTION B AC2R K NONE O OTHER IN INSP/MAINT 1 SW 03 5366Y 7655 104 S782 TACHOMETER GAVE A FALSE READING OF 105 PERCENT PERCENT DURING FLIGHT. REPLACED TACHOMETER. 1 G 7 2 3U H3EU 1996090500127 19960905 00127 CE 1996 9 5 96ZZZX4219 1 19960807 G 2730 05130631 BRACKET CESSNA 172 172F 2072414 CE ELEV BELLCRANK RIVETS PULLED B S A B5XR K NONE F FLT CONT AFFECTED IN INSP/MAINT 1 WP 07 8831U 17252740 INVESTIGATION FOR A SAGGING ELEVATOR WITH GUST LOCK IN PLACE, FOUND BRACKET ASSY MOUNTING RIVETS PULLED. BRACKET ASSY I S MOUNT POINT FOR ELEVATOR BELLCRANK. WITH BELLCRANK BRACKET LOOSE, ELEVATOR CABLE GAINS SLACK. LOSS OF EFFECTIVE ELEV ATOR CONTROL HAD BEEN NOTED ON A PREVIOUS FLIGHT WHEN WIND SHEAR OCCURRED DURING LANDING. REPLACEMENT PART IS SUPERCEDE D BY A HEAVIER DASH 3 PART. SUBMITTER RECOMMENDS AD CONSIDERATION. 1 H 7 1 3O NT 3A12 1996090500128 19960905 00128 EA 1996 9 5 96ZZZX4220 1 19960723 G 5412 60137003162 FIREWALL CNDAIR CL600 CL6002B16 1900305 EA PYLON RT LOWER CHAFE/BURNED B A B5XR K NONE O OTHER IN INSP/MAINT 1 WP 07 309FX 5306 WHILE PERFORMING SB A604-27-002, THE RT LOWER PYLON PANEL HEAT SHIELD HAD EVIDENCE OF ELECTRICAL SHORT DAMAGE. UPON FUR THER INVESTIGATION, RT ENGINE GENERATOR WIRE HARNESS WAS FOUND NEARLY SEVERED FROM CHAFING ON THE HEAT SHIELD. THE CLAM P SECURING THE WIRE HARNESS WAS ROTATED FORCING THE HARNESS INTO THE EDGE OF THE HEAT SHIELD. THE WIRE HARNESS AND HEAT SHIELD WERE REPLACED AND THE SECURING CLAMP WAS ROTATED 45 DEGREES TO CLEAR THE HEAT SHIELD. 2 L 7 2 4F RT A21EA 1996090500129 19960905 00129 1996 9 5 96ZZZX4221 4 19960412 G 6122 3020166 SHAFT ASSY WOODWARD 8210176 PROP GOVERNOR CRACKED B S OL3R K NONE O OTHER IN INSP/MAINT 1 WP 27 9025 2346724C FOUND CRACK ON GEROTOR FACE GOING OUT FROM KEYWAY CORNER. CRACK EXTENDED THROUGH GEAR. 1996090500130 19960905 00130 CE 1996 9 5 96ZZZX4222 1 19960731 G 5553 04310093 ATTACH FITITNG CESSNA 150 152 2071835 CE VERT STAB CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 05 64971 4511 15281505 WHILE C/W WITH AD 80-11-04 NUTPLATES, INSPECTION FOUND A .8750 INCH LONG CRACK ON THE LEFT FIN ATTACH FITTING (LOWER OUT BOARD SIDE.) BROKE IN HALF UPON REMOVAL. 1 H 7 1 3O NT 3A19 1996090500131 19960905 00131 SO 1996 9 5 96ZZZX4223 1 19960804 G 2410 69113 BRACKET PIPER PA22 PA22135 7102206 SO ALTERNATOR BROKEN C S K NONE O OTHER IN INSP/MAINT 1 SW 17 1213C 3390 221021 DURING ANNUAL INSPECTION, GENERATOR FELT LOOSE. FURTHER INVESTIGATION REVEALED THE GENERATOR BRACKET HAD BROKEN. 1 H 7 1 3O 1A6 1996090500132 19960905 00132 EA 1996 9 5 96ZZZX4224 2 19960804 G 8510 69340 SUPPORT PIPER PA22 PA22135 7102206 SO LYC O290 O290D2 41506 EA START RING GEAR CRACKED D S K NONE O OTHER IN INSP/MAINT 1 SW 17 1213C 3390 221021 495821 DURING AN ANNUAL INSPECTION, A CRACK WAS NOTICED ON THE FACE OF THE STARTER RING SUPPORT ASSY. A DYE PENETRANT TEST WAS DONE. THE TEST REVEALED THE CRACK WAS HALF-WAY AROUND THE STARTER RING GEAR SUPPORT, BUT NOT THROUGH THE RING GEAR ITS ELF. 1 H 7 1 3O 3 O 1A6 E229 1996090500133 19960905 00133 EU 1996 9 5 96ZZZX4225 1 19960701 G 7603 AN4864 CONTROL FORK WSK M18 M18DROMADER 9810102 EU THROTTLE STRIPPED G S K NONE O OTHER IN INSP/MAINT 1 GL 13 2047S 1200509 THROTTLE CONTROL THREADS STRIPPED OUT OF TERMINAL END (FORK). THREAD DAMAGE INDICATED THE MALE END OF THROTTLE CONTROL WAS NOT TURNED INTO THREADED PORTION OF FORK TO THE INDICATOR HOLES. 1 L 7 1 3O A47EU 1996090500135 19960905 00135 1996 9 5 96ZZZX4227 4 19960808 G 6113 22501215 BACKPLATE CESSNA 182 R182 2072734 CE SPINNER CRACKED D S K NONE O OTHER IN INSP/MAINT 1 WP 21 6347T R18201990 INSPECTION FOUND PROPELLER SPINNER BULKHEAD CRACKED. SUBMITTER STATED REPLACING THESE BULKHEADS IS AN ANNUAL OCCURRENCE . BOTH HALVES EACH TIME. SUSPECT POOR DESIGN, SPINNER FLEXES FORE AND AFT, NEED A RIGID FRONT PLATE OR .25 INCH BACKPL ATE. TT AIRFRAME: 2,450 HOURS. TT THIS PART: 100 HOURS. 1 H 7 1 3O RT 3A13 1996090500136 19960905 00136 GL 1996 9 5 96ZZZX4228 1 19960804 G 3250 1945330 COLLAR 194391 BLANCA 17 1731A 1220435 GL NLG WELD CRACKED D S K NONE O OTHER IN INSP/MAINT 1 SW 17 4205B 1997 7532146 WHILE PUTTING A HAND TOW BAR ON THE NOSE FORK, NOTICED PAINT FLAKING OFF THE FRONT STEERING COLLAR. REMOVED ALL THE PAI NT OFF THE COLLAR AND NOTICED THE WELD WAS CRACKED FROM SIDE TO SIDE. P/N 19453-30. TT: 1,996.6 HOURS. 1 L 7 1 3O A18CE 1996090500137 19960905 00137 CE 1996 9 5 96ZZZX4229 1 19960701 G 5540 AG752001 HORN BOEING 75 A75N1 1380134 CE RUDDER FAILED G S A K NONE O OTHER IN INSP/MAINT 1 GL 13 58712 75341 RUDDER HORN FAILURE. CORROSION HAD DETERIORATED THE WALL THICKNESS OF THE RUDDER HORN. ALSO, RUST INDICATED THE HORN W AS CRACKED PRIOR TO FAILURE. 1 Q 7 1 3R A743 1996090500138 19960905 00138 CE 1996 9 5 96ZZZX4230 1 19960821 G 5320 00244000029 DOUBLER BEECH 36 A36 1151604 CE FS 272 CRACKED B L NN3R K NONE O OTHER IN INSP/MAINT 1 WP 25 8165Q 2484 E5292 DURING INSPECTION OF EMPENNAGE, CRACK WAS DISCOVERED IN THE DOUBLER LOCATED JUST FORWARD OF STA 272, BULKHEAD. THE CRAC K WAS IN THE RADIUS OF CUT-OUT AREA OF DOUBLER ON THE LEFT SIDE. INSPECTION OF OTHER AIRCRAFT IN THE FLEET FOUND 5 OTHE RS WITH THE SAME DEFECTS, SERIAL NUMBERS RANGED FROM E2592 TO E2667, TOTAL TIME FROM 2,300 - 2,600 HOURS. 1 L 7 1 3O 3A15 1996090500139 19960905 00139 1996 9 5 96ZZZX4231 4 19960802 G 3410 B904 HOSE CESSNA 150 A152 2071836 CE INSTRUMENTS DETERIORATED D K NONE O OTHER IN INSP/MAINT 1 WP 21 152J A1520963 1981 - 1,425 HOURS TT. TOTAL DETERIORATION OF OUTER LAYER, REINFORCING THREADS, AND INNER LAYER. HOSE IS OF A PLASTIC TYPE, APPEARS TO BE ORIGINAL. REPLACED WITH AEROQUIP 306 INSTRUMENT HOSE. 1 H 7 1 3O 3A19 1996090500140 19960905 00140 EA 1996 9 5 96ZZZX4232 2 19960821 G 8520 LW17060 CRANKSHAFT PIPER PA28 PA28161 7102803 SO LYC O320 O320D3G 41508 EA FLANGE CRACKED D S A UNSCHED LANDING K FLUID LOSS NR NOT REPORTED 1 NE 03 84652 6047 288216062 L947639A THE AIRCRAFT COMPLETED AN UNSCHEUDLED ON AIRPORT EMERGENCY LANDING DUE TO OIL SPRAYING ON THE WINDSHIELD. THE CRANKSHAF T WAS FOUND CRACKED AT THE RADIUS BY THE PROPELLER FLANGE. (APPROXIMATELY 1.75 INCH VISIBLE.) 1 L 7 1 3O 3 O 2A13 E274 1996090500141 19960905 00141 1996 9 5 96ZZZX4233 4 19960805 G 3416 D120P2T DIGITIZER TRANSCAL SOCATA TB20 TB20TRINIDAD 8680695 EU ALTIMETER STATIC LEAK D K NONE O OTHER IN INSP/MAINT 1 SW 17 5546A 70279 1241 ALTITUDE DIGITIZER HAS PLASTIC GLASS FILLED NYLON HEADER. THE STATIC INLET PORT CRACKED CAUSING LEAK. SUBMITTER STATED THIS IS A RECURRING PROBLEM WITH THIS ITEM WHICH WAS ORIGINALLY METAL. 1 L 7 1 3O RT A51EU 1996090500142 19960905 00142 CE 1996 9 5 96ZZZX4234 1 19960801 G 2820 LINES CESSNA 180 180H 2072618 CE DOOR POST CHAFED D A K NONE O OTHER IN INSP/MAINT 1 NE 05 2461F 18051663 IN LT DOOR POST, THE AILERON CABLE WAS RUBBING ON THE FUEL LINE. UNDER THE FLOOR, THE FUEL LINES WERE CHAFING ON THE BU LKHEADS WHERE THEY PENETRATED. SUBMITTER RECOMMENDS CLOSE INSPECTION OF THESE AREAS WITH A MIRROR AND LIGHT. INTERIOR PANELS MUST BE MOVED TO PROPERLY INSPECT DOOR POST AREAS. RECOMMENDED SOLUTION IS INSTALLATION OF RUBBER GROMMETS OR CHA FE SEAL AND/OR SECURING THE LINES TO PREVENT MOVEMENT AGAINST AIRFRAME. 1 H 7 1 3O 5A6 1996090500143 19960905 00143 CE 1996 9 5 96ZZZX4235 1 19960625 G 2750 51152532 CAM ASSY CESSNA 402 402C 207590R CE FLAP ACTUATOR LOOSE D K NONE O OTHER IN INSP/MAINT 1 SO 21 2717B 402C0221 CAM WAS LOOSE ON SHAFT. FAILED TO LIMIT FLAP TRAVEL TO THE DOWN SIDE AND BROKE DRIVE CHAIN TO FLAP CABLE. TAT: 12,176 .3 HOURS. LAST INSPECTED ON 12,020.5 HRS, CHECK NR 2. PROGRESSIVE CARE ITEM NR 16. CAM ITSELF NOT SPECIFICALLY CALLED OUT IN INSPECTION. 1 L 7 2 3O A7CE 1996090500144 19960905 00144 SO 1996 9 5 96ZZZX4236 1 19960724 G 2510 510232827 BRACKET GRUMAN 5102349501 GULSTM AA5 AA5B 3960105 SO PILOT SEAT FAILED D A K NONE O OTHER IN INSP/MAINT 1 WP 01 28618 3400 AA5B0707 DURING GROUND RUN-UP, THE SEAT BRACKETS FAILED ALMOST SIMULTANEOUSLY ALLOWING THE PILOT'S SEAT BACK TO FALL INTO THE REA R SEAT AREA. FAILURE APPEARS TO BE BENDING FATIGUE, A FLEXURE OF THESE ALUMINUM BRACKETS IS NOTED WHEN THE TOP OF THE S EAT IS PULLED AFT (PASSENGER EXITING THE AIRCRAFT). THE LATER MODEL, AG5-B, HAS STEEL BRACKETS. THERE WAS NO EVIDENCE OF A PREVIOUS CRACK PRIOR TO FAILURE. 1 L 7 1 3O A16EA 1996090500145 19960905 00145 SO 1996 9 5 96ZZZX4237 1 19960724 G 2510 510232828 BRACKET GRUMAN 5102349501 GULSTM AA5 AA5B 3960105 SO PILOT SEAT FAILED D K NONE O OTHER IN INSP/MAINT 1 WP 01 28618 3400 AA5B0707 DURING GROUND RUN-UP, THE SEAT BRACKETS FAILED ALMOST SIMULTANEOUSLY ALLOWING THE PILOT'S SEAT BACK TO FALL INTO THE REA R SEAT AREA. FAILURE APPEARS TO BE BENDING FATIGUE, A FLEXURE OF THESE ALUMINUM BRACKETS IS NOTED WHEN THE TOP OF THE S EAT IS PULLED AFT (PASSENGER EXITING THE AIRCRAFT). THE LATER MODEL, AG5-B, HAS STEEL BRACKETS. THERE WAS NO EVIDENCE OF A PREVIOUS CRACK PRIOR TO FAILURE. 1 L 7 1 3O A16EA 1996090500149 19960905 00149 1996 9 5 96ZZZX4241 4 19960122 G 2210 P2110311 SWITCH STD9891 BEECH B300 B300 1159232 CE AUTOPILOT FROZEN D K NONE O OTHER IN INSP/MAINT 1 NM 01 4S FL107 ON PRE-FLIGHT, FOUND AUTOPILOT DISCONNECT SWITCH FROZEN. THE SPRING LOADED PUSH BUTTON IS FIXED OR FROZEN SOLID. SUBMI TTER STATED EVEN BEFORE IT FROZE, IT FELT CATCHY OR SCRATCHY WHEN BUTTON WAS DEPRESSED. 2 L 7 2 4T RT A24CE 1996090500150 19960905 00150 GL 1996 9 5 96ZZZX4242 3 19960723 G 6114 CYLINDER HARTZL HCB3R HCB3R304 GL PROP PISTON DENTED D K NONE O OTHER IN INSP/MAINT 1 NM 03 200 EMA054 PROPELLER WAS BROUGHT BACK TO SHOP AFTER OVERHAUL BECAUSE HIGH RPM COULD NOT BE ESTABLISHED UNTIL TAKEOFF ROLL AND TAIL WAS LIFTED. AT DISASSEMBLY, THE CYLINDER WAS FOUND TO HAVE A DENT WHICH CAUSED THE PISTON TO HANG UP AND NOT ALLOW THE PROP TO GO TO LOW PITCH POSITION. WHEN CENTRIFIGAL TWISTING MOMENT WAS HIGH ENOUGH, PISTON WOULD GO PAST THE DENT BY FO RCE. DURING INSTALLATION, THE MOUNTING NUT HAD BEEN DAMAGED BECAUSE OF USE OF IMPROPER INSTALLATION TOOLS. THIS CAUSED THE DENT ON THE CYLINDER AND ALSO DESTROYED THE MOUNTING NUT. 5 C P28EA 1996090500351 19960905 00351 NE 1996 9 5 96ZZZX4273 1 19960709 G 6210 7615009100051 BLADE SKRSKY S76 S76A 8143006 NE M/R LE STRIP DEFECTIVE B A ZV1R K NONE O OTHER IN INSP/MAINT 1 SW 03 31211 2487 A08601079 760225 FOUND APPROXIMATELY 8.50 INCH SECTION OF MAIN ROTOR BLADE NICKLE LEADING EDGE STRIP MISSING APPROXIMATELY 48 INCHES FROM THE TIP CAP. THIS AREA HAD A CRACK IN THE LEADING EDGE AND IT WAS REPAIRED PER THE COMPOSITE REPAIR MANUAL. SUSPECT D ISBONDING UNDER THE STRIP FROM CRACK. RECOMMEND A BETTER PROCEDURE FOR SEALING CRACKS IN LEADING EDGE ABRASION STRIPS. 1 G 7 2 3U H1NE 1996090500352 19960905 00352 SW 1996 9 5 96ZZZX4274 1 19960730 G 6230 206010443001 DUPLEX BEARING BELL 206 206L1 1182107 SW SWASHPLATE FAILED B A ZV1R K NONE O OTHER IN INSP/MAINT 1 SW 03 2654 546 18490 45482 SWASHPLATE REMOVED DUE TO BINDING AND ROUGHNESS. ON DISASSEMBLY, FOUND DUPLEX BEARING FLAKING AND CHIPPING. BEARING CA GE HAS SEPARATED AND CAUSED DAMAGE TO INNER RING OF SWASHPLATE. SUBMITTER STATED THIS IS THE THIRD BEARING IN LAST 12 M ONTHS WITH LESS THAN 1,000 HOURS. 1 G 7 1 3U H2SW 1996090500353 19960905 00353 SW 1996 9 5 96ZZZX4275 1 19960716 G 6320 206040032011 DUPLEX BEARING BELL 206 206L1 1182107 SW TRANSMISSION FAILED B ZV1R K NONE J WARNING INDICATION IN INSP/MAINT 1 SW 03 5759M 703 50980 45555 TRANSMISSION MAKING METAL AT 702.5 TSO. FOUND DEFECTIVE LOWER DUPLEX BEARING. BEARING HAD 702.5 HOURS SINCE NEW. 1 G 7 1 3U H2SW 1996090500664 19960905 00664 EU 1996 9 5 96ZZZX4276 1 19960513 G 2432 16061 BATTERY SAFT SNIAS 350 AS350B2 8680813 EU RT BAG COMPT SHORTED H A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 WP 07 6103X 900 2723 A BATTERY TEMP LIGHT ILLUMINATED DURING FLIGHT. EMERGENCY PROCEDURES INITIATED. FOUND ACFT BATTERY SHORTED. A SECONDA RY LEAD IS ATTACHED TO ACFT BATTERY USING A METAL TAB LUG WHICH IS CONNECTED TO THE WIRE END CONNECTOR USING A NUT AND B OLT WHICH IS PROTECTED BY HEAT SHRINK INSULATOR. THIS NUT AND BOLT CONNECTING THE WIRE END CONNECTOR AND TAB LUG WEARS THROUGH THE INSULATION AND CONTACTS THE NICAD BATTERY'S CASE SHORTING THE BATTERY AND OVERHEATING IT. REPLACED THE WIRE TERMINAL CONNECTOR AND TAB LUG WITH A SINGLE APPROPRIATE SIZE WIRE AND TERMINAL. REPAIRED 2 OTHER ACFT WITH SAME PROBL EM. 1 G 7 1 3U H9EU 1996090500665 19960905 00665 WP 1996 9 5 96ZZZX4277 1 19960729 G 6710 10064603 SWITCH HUGHES 369 369E 4470707 WP CYCLIC TRIM DEFECTIVE D K NONE F FLT CONT AFFECTED NR NOT REPORTED 1 WP 07 503MP 0414E PILOT'S CYCLIC TRIM SWITCH FREQUENTLY BECOMES INTERMITTENT. PILOT FIRST REPORTS A STIFF CYCLIC. SOMETIMES TRIM RUNS AW AY IN ANY ONE OF FOUR DIRECTIONS. THIS CAUSES MUCH STICK FORCE. FLIGHT MUST BE TERMINATED DUE TO FATIGUE. RETURN TO H OME BASE. AVERAGE LIFE OF SWITCH IS 150 TO 250 HOURS. TEN SWITCHES HAVE BEEN CHANGED IN LAST SIX MONTHS. 1 G 7 1 3U H3WE 1996090500666 19960905 00666 WP 1996 9 5 96ZZZX4278 1 19960813 G 6710 A21810064603 SWITCH HUGHES 369 369E 4470707 WP CYCLIC TRIM FAILED D O OTHER F FLT CONT AFFECTED NR NOT REPORTED 1 WP 07 504MP 388 0523E PILOT REPORTED NO TRIM IN FORE/AFT DIRECTION. DURATION OF FLIGHT HAD TO FIGHT HIGH FORE/AFT STICK FORCES. SUBMITTER ST ATED A COMMON PROBLEM, SWITCH IS TOO LIGHT-DUTY FOR APPLICATION. 1 G 7 1 3U H3WE 1996090500667 19960905 00667 SW 1996 9 5 96ZZZX4279 1 19960810 G 6520 476452691 SHAFT VENY 476400751 BELL 47 47G5 1181032 SW T/R GEARBOX PLUGGED B A OUGR K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 17 7885S A133111 7873 RECEIVED NEW REPLACMENT PART FROM BELL. DURING RECEIVING INSPECTION, NOTICED .1250 INCH HOLE DRILLED IN SHAFT TO VENT G EARBOX WAS PLUGGED SOLID WITH GRAY COATING THAT WAS APPLIED TO INTERIOR OF SHAFT FOR CORROSION PROTECTION. SUBMITTER ST ATED THIS COULD POSSIBLY CAUSE OIL LEAKS IN SERVICE. 1 G 7 1 3O 2H3 1996090500668 19960905 00668 EU 1996 9 5 96ZZZX4280 1 19960717 G 6322 1090401211 BOLT A090600109 AGUSTA A109 A109A2 0260120 EU OIL COOLER SHAFT SHEARED B KUVR K NONE O OTHER IN INSP/MAINT 1 SO 19 169BH 1705 6290 ON DAILY INSPECTION, MECHANIC NOTICED EXCESSIVE MOVEMENT OF OIL COOLER DRIVESHAFT UNDER ENGINE. FOUND BOLT TYING FORWAR D OUTPUT COUPLING TO AFT COUPLING THROUGH ENGINE. PTO GEARSHAFT SHEARED FLUSH WITH BOTTOM OF RETENTION NUT. COTTER PIN WAS STILL INSTALLED IN BOLT END THROUGH-NUT. OIL COOLER SHAFT CONTAINED AFT ADAPTER IN GEARBOX, SO DID NOT FAIL COMPLE TELY. SUBMITTER SUGGESTS BOLT AGE AND/OR IMPROPER INSTALLATION CAUSED BOLT TO FAIL. 1 G 7 2 3U H7EU 1996090500669 19960905 00669 SW 1996 9 5 96ZZZX4281 1 19960805 G 6710 A21810064603 SWITCH GUARDIAN HUGHES 500N 500N 3027374 SW CYCLIC TRIM STICKING D K NONE F FLT CONT AFFECTED NR NOT REPORTED 1 WP 07 527FB 286 LN007 SWITCH STICKS IN ALL POSITIONS AFTER 1 HOUR OF FLIGHT. IN-FLIGHT CAUSES TRIM TO RUN AWAY OR BURN UP TRIM MOTOR. SWITCH PLATING COMES OFF AND BINDS TRIGGER. 1 G 7 1 3U NC H3WE 1996090500670 19960905 00670 WP 1996 9 5 96ZZZX4282 1 19960729 G 6320 369D25100901 TRANSMISSION HUGHES 369 369E 4470707 WP TACHOMETER DRIVE SEAL LEAK D A K NONE K FLUID LOSS IN INSP/MAINT 1 WP 07 503MP 271 0414E ROTOR TACHOMETER GEN SEAL LEAKS INTO OIL COOLER BLOWER INLET, AIR/OIL MIX TURE GETS DISTRIBUTED OVER HOT 250C20R ENGINE. REMAINDER OF AIR OIL MIXTURE ENTERS HEATER DUCTS. WHEN PILOT SELECTS HEATER, HAZARDOUS AIR/OIL MIXTURE FILLS COCKPIT. THIS PAD SHOULD HAVE A SCUPPER DRAIN LINE OVERBOARD LIKE THE 2 OTHER SEALS IN SAME PROXIMITY. 1 G 7 1 3U H3WE 1996090500672 19960905 00672 SW 1996 9 5 96ZZZX4284 1 19960821 G 3340 A469B LAMP WHELEN A470 BELL 206 206L1 1182107 SW STROBE FAILED D K NONE O OTHER IN INSP/MAINT 1 SO 09 911SA 20 45383 ANTI-COLLISION LIGHT FAILED, FOUND LAMP ASSY, A469B, INOPERATIVE. THIS IS FOURTH LAMP TO FAIL, ALL WITH LESS THAN 20-30 FLIGHT HOURS. 1 G 7 1 3U H2SW 1996090500673 19960905 00673 1996 9 5 96ZZZX4285 1 19960730 G 2822 2B69 PUMP AIRBORNE FUEL BOOST FAILED D K NONE O OTHER IN INSP/MAINT 1 GL 13 10E8 ARMATURE OUT OF DYNAMIC BALANCE CAUSING PREMATURE FAILURE OF THE PUMP. 1996090500674 19960905 00674 1996 9 5 96ZZZX4286 1 19960810 G 2822 2B663 PUMP AIRBORNE ARMATURE OUT OF BALANCE D K NONE O OTHER IN INSP/MAINT 1 GL 23 6AD96 INSPECTION FOUND PUMP ARMATURE OUT OF BALANCE. 1996090500675 19960905 00675 EA 1996 9 5 96ZZZX4287 2 19960814 G 8530 LW11634 VALVE LW11633 PIPER PA38 PA38112 7103812 SO LYC O235 O235L2C 41505 EA NR 1 CYL EXH FAILED G K NONE O OTHER IN INSP/MAINT 1 CE 05 33BA 200 511561 3879A0021 L1598715 EXHAUST VALVE FAILURE, 200 HOURS AFTER CYLINDER OVERHAUL. YELLOW TAG INDICATES CYLINDER WAS REBUILT USING SERVICEABLE P ARTS. REBUILDER WAS CONTACTED, BUT COULD NOT DETERMINE TOTAL NUMBER OF HOURS ON VALVE WHEN INSTALLED. LYC SB NR 301B ST ATES EXHAUST VALVES SHOULD NOT BE RE-USED UNLESS THEY HAVE BEEN RECENTLY INSTALLED AND MEET INSPECTION CRITERIA. 1 L 7 1 3O 3 O A18SO E223 1996090500676 19960905 00676 SO 1996 9 5 96ZZZX4288 1 19960520 G 3211 452368 BEARING PIPER PA28 PA28R200 7102811 SO RT/LT MLG WORN D K NONE O OTHER IN INSP/MAINT 1 GL 09 33075 4888 28R7535116 FOUND BOTH MLG'S COULD BE MOVED SIDE TO SIDE BECAUSE OF PLAY IN THE TRUSS BEARING (ROD END). SUSPECT LACK OF REGULAR LU BRICATION AND HIGH TOTAL TIME. 1 L 7 1 3O 2A13 1996090500678 19960905 00678 SO 1996 9 5 96ZZZX4290 2 19960730 G 8530 22250 GASKET CESSNA 172 172H 2072424 CE CONT O300 O300D 17022 SO INDUCTION ELBOW FAILED D K NONE O OTHER IN INSP/MAINT 1 NE 01 3707R 391 17255507 025665R ENGINE REPORTED TO RUN ROUGH AT LOW RPM'S AND HAVE POPPING SOUND. TROUBLESHOOTING FOUND THAT CYLINDERS', NR 1, NR 3, AN D NR 5, INDUCTION ELBOW GASKETS HAD BEEN SUCKED IN. ENGINE HAS 391.0 HOURS SINCE FACTORY REMANUFACTURE. ATTACHING HARD WARE WAS FOUND TO BE PROPERLY TORQUED. 1 H 7 1 3O 3 O NT 3A12 E253 1996090500679 19960905 00679 SO 1996 9 5 96ZZZX4291 1 19960719 G 2810 1609700 FUEL CAP PIPER PA23 PA23250 7102308 SO RT OTBD NOT SECURE H A UNSCHED LANDING K FLUID LOSS CL CLIMB 1 NE 05 40571 277405313 DURING TAKEOFF, THE RIGHT FUEL CAP COVER OPENED AND FUEL STARTED COMING OUT. PILOT RETURNED TO SECURE THE FUEL CAP, AND ADD APPROXIMATELY 10 GALLONS OF FUEL. 1 L 7 2 3O 1A10 1996090500680 19960905 00680 SO 1996 9 5 96ZZZX4292 2 19960201 G 8530 646100A1 CYLINDER CESSNA 404 404CESSNA 2075901 CE CONT O520 GTSIO520M 17032 SO SPARK PLUG HOLE CRACKED B S APCR K NONE O OTHER IN INSP/MAINT 1 NM 01 41SA 1449 4040023 276274R DURING A ROUTINE ENGINE COMPRESSION TEST, CYLINDER NR 1 SHOWED 10/80. A VISUAL INSPECTION CONFIRMED A CRACK EMANATING F ROM THE LOWER SPARK PLUG HOLE TO THE COOLING FINS, APPROXIMATELY 1.50 INCHES LONG. THIS IS A RECURRING ITEM, OPERATOR K NOWS OF AT LEAST 12 OCCURRENCES OVER THE LAST 2 YEARS. 1 L 7 2 3O 3 O A25CE E7CE 1996090500682 19960905 00682 CE 1996 9 5 96ZZZX4294 1 19960808 G 2820 51001107 LINE CESSNA 421 421C 2076016 CE RT TANK HOLE CHAFED D A K NONE O OTHER IN INSP/MAINT 1 EA 25 421RL 3437 421C1081 WHILE C/W AD 95-09-13, THE FUEL LINE GOING TO THE FORWARD RIGHT WING INLET VALVE WAS FOUND NOT CENTERED GOING THROUGH A BULKHEAD THROUGH-HOLE. REMOVING THE LINE, A HOLE WAS FOUND CHAFED THROUGH. IF THE FUEL LEVEL HAD GONE BELOW THIS LINE, A FUEL STARVATION WOULD HAVE DEVELOPED. A NEW LINE WAS INSTALLED AND PROPER CLEARANNCE WAS ESTABLISHED. THIS AREA SHO ULD BE CHECKED ANY TIME THE FUEL TANKS ARE OPENED. 1 L 7 2 3O A7CE 1996090500683 19960905 00683 SW 1996 9 5 96ZZZX4295 1 19960729 G 5410 26002024 FRAME GULSTM 500 500S 0141107 SW RT NACELLE CORRODED D K NONE O OTHER IN INSP/MAINT 1 EA 21 47RF 11068 3261 WHILE COMPLETING 100-HOUR FACTORY INSPECTION, NOTED CORROSION BUILD-UP AFT OF EXHAUST ON TOP OF RT NACELLE. REMOVED COR ROSION AND FOUND 1 INCH HOLE. BOTH SKIN AND FRAME HAD BEEN EATEN THROUGH. REPLACED FRAME WITH NEW AND C/W RIVETED PATC H REPAIR ON NACELLE SKIN. SUGGEST PEROXIDE CLEANING INSPECTION AND PAINTING OF THIS AREA. 1 H 7 2 3O 6A1 1996090500684 19960905 00684 NM 1996 9 5 96ZZZX4296 1 19960810 G 7160 HINGE PIPER PA60 PA60600 7106001 NM ALTERNATE AIR SEPARATED D A O OTHER O OTHER CR CRUISE 1 EA 13 600VF 600757806122 IN-FLIGHT, THE THROTTLE COULD NOT BE REDUCED BELOW 22 INCHES OF MANIFOLD PRESSURE DUE TO A RESTRICTION IN THE FUEL INJEC TOR SERVO BUTTERFLY. THE BLOCKAGE WAS THE ALTERNATE AIR DOOR THAT HAD SEPARATED FROM THE HINGE AND WENT DOWN LINE IN TH E INDUCTION SYSTEM TO BLOCK THROTTLE. FURTHER INVESTIGATION SHOWS THE AEROSTARS OWNERS GROUP HAD IDENTIFIED THIS AS AN ONGOING PROBLEM IN THE 600 NON-TURBO MODELS ONLY. RECOMMEND A 50-HOUR INSPECTION OF ALTERNATE AIR DOORS. 1 M 7 2 3O RT A17WE 1996090500685 19960905 00685 CE 1996 9 5 96ZZZX4297 1 19960808 G 3340 08701321 LANDING LIGHT GRIMES G3600A1 CESSNA 310 310R 2074245 CE LT WING FAILED D K NONE O OTHER IN INSP/MAINT 1 GL 09 6181C 1 94902 310R1320 PART FAILED AFTER 2 CYCLES. LIGHT WOULD NOT RETRACT. FOUND INTERNAL SWITCH LINKAGE LOOSE. SUSPECT MICROSWITCHES INOPE RABLE DUE TO POOR WORKMANSHIP AND PARTS MISALIGNED. 1 L 7 2 3O 3A10 1996090500686 19960905 00686 EU 1996 9 5 96ZZZX4298 1 19960815 G 7603 T67G150525 PUSH ROD SLNSBY T67 T67M260 8323006 EU LT SIDE COCKPIT BROKEN B A UNER O OTHER O OTHER NR NOT REPORTED 1 NM 03 3104L 580 2164 THE AIRCREW DECLARED AN IN-FLIGHT EMERGENCY AFTER ACFT ENGINE WOULD NOT RESPOND TO THROTTLE APPLICATION FROM IP'S REMOTE THROTTLE HANDLE AND LINKAGE LOCATED ON LT SIDE OF COCKPIT. REMOTE THROTTLE LEVER/HANDLE IS ATTACHED TO LT SIDE OF AIRF RAME. IT IS ATTACHED TO THE THROTTLE PUSH ROD, PN T67G-150-525. THIS PUSH ROD IS A STEEL TUBE WHICH HAS A M5 THREAD SC REW WELDED TO THE STEEL ROD. A FORK-END TRAVELS ON THE THREAD FOR ADJUSTMENT. THE THREAD BREAKS NEAR OR AT THE WELD AS OPPOSING FORCES ARE PLACED ON THE TWO THROTTLE LEVERS AND LINKAGE. THIS IS THE SECOND OCCURRENCE. A ONE-TIME INSPECTI ON REVEALED SEVEN BENT THREADED ROD ENDS. THE THROTTLE LINKAGE MAY NEED A STOP INSTALLED ON THE REMOTE THROTTLE LEVER. 1 L 7 1 3O NT A73EU 1996090500687 19960905 00687 EU 1996 9 5 96ZZZX4299 1 19960710 G 7603 T67G150525 PUSH ROD SLNSBY T67 T67M260 8323006 EU LT SIDE COCKPIT BROKEN B UNER O OTHER O OTHER NR NOT REPORTED 1 NM 03 3172R 314 2193 THE AIRCREW DECLARED AN IN-FLIGHT EMERGENCY AFTER ACFT ENGINE WOULD NOT RESPOND TO THROTTLE APPLICATION FROM IP'S REMOTE THROTTLE HANDLE AND LINKAGE LOCATED ON LT SIDE OF COCKPIT. REMOTE THROTTLE LEVER/HANDLE IS ATTACHED TO LT SIDE OF AIRF RAME. IT IS ATTACHED TO THE THROTTLE PUSH ROD, PN T67G-150-525. THIS PUSH ROD IS A STEEL TUBE WHICH HAS A M5 THREAD SC REW WELDED TO THE STEEL ROD. A FORK-END TRAVELS ON THE THREAD FOR ADJUSTMENT. THE THREAD BREAKS NEAR OR AT THE WELD AS OPPOSING FORCES ARE PLACED ON THE TWO THROTTLE LEVERS AND LINKAGE. THIS IS THE SECOND OCCURRENCE. A ONE-TIME INSPECTI ON REVEALED SEVEN BENT THREADED ROD ENDS. THE THROTTLE LINKAGE MAY NEED A STOP INSTALLED ON THE REMOTE THROTTLE LEVER. 1 L 7 1 3O NT A73EU 1996090500688 19960905 00688 1996 9 5 96ZZZX4300 1 19960807 G 2822 1D217 ARMATURE AIRBORNE FUEL BOOST FAILED D K NONE O OTHER IN INSP/MAINT 1 GL 13 1AA35 ARMATAURE OUT OF DYNAMIC BALANCE CAUSING PREMATURE FAILURE OF THE PUMP. 1996090500689 19960905 00689 1996 9 5 96ZZZX4301 1 19960820 G 2822 2B738 ARMATURE AIRBORNE FUEL BOOST DAMAGED D K NONE O OTHER IN INSP/MAINT 1 GL 13 1AD44 PUMP MAY HAVE BEEN RUN DRY CAUSING SEVERE DAMAGE TO ARMATURE. 1996090500690 19960905 00690 1996 9 5 96ZZZX4302 1 19960820 G 2822 2B738 PUMP AIRBORNE FUEL BOOST FAILED D K NONE O OTHER IN INSP/MAINT 1 GL 13 1AD71 PUMP FAILURE. PUMP WAS POSSIBLY RUN DRY CAUSING DAMAGE TO ARMATURE. 1996090500691 19960905 00691 1996 9 5 96ZZZX4303 1 19960807 G 2822 1D217 ARMATURE AIRBORNE FUEL PUMP FAILURE D K NONE O OTHER IN INSP/MAINT 1 GL 13 3AH31 ARMATURE OUT OF DYNAMIC BALANCE CAUSING PREMATURE FAILURE OF THE PUMP. 1996090500692 19960905 00692 1996 9 5 96ZZZX4304 1 19960820 G 2822 1B58 ARMATURE AIRBORNE FUEL SYSTEM DAMAGED D K NONE O OTHER IN INSP/MAINT 1 GL 13 5C32 PUMP OVERHEATED, MAY HAVE BEEN RUN DRY CAUSING DAMAGE TO ARMATURE 1996090500693 19960905 00693 1996 9 5 96ZZZX4305 1 19960820 G 2822 2B664 ARMATURE AIRBORNE FUEL PUMP DAMAGED D K NONE O OTHER IN INSP/MAINT 1 GL 13 2AK61 ARMATURE SHAFT HAS DAMAGE TO IT. GROOVE WORN IN BY SPACER AND OTHER WEAR MARKS ON SHAFT. 1996090500694 19960905 00694 1996 9 5 96ZZZX4306 1 19960807 G 2822 1D217 ARMATURE AIRBORNE FUEL PUMP OUT OF BLAANCE D K NONE O OTHER IN INSP/MAINT 1 GL 13 11AH66 ARMATURE OUT OF DYNAMIC BALANCE CAUSING PREMATURE FAILURE OF THE PUMP. 1996090500695 19960905 00695 1996 9 5 96ZZZX4307 1 19960820 G 2822 2B738 BRUSH BLOCK AIRBORNE FUEL PUMP DAMAGED D K NONE O OTHER IN INSP/MAINT 1 GL 13 1AD44 OVERHEATING OF THE PUMP CAUSED DAMAGE TO THE BRUSH BLOCK. 1996090500696 19960905 00696 1996 9 5 96ZZZX4308 1 19960808 G 2822 2B663 ARMATURE AIRBORNE FUEL PUMP FAILED D K NONE O OTHER IN INSP/MAINT 1 GL 13 9E517 ARMATURE OUT OF DYNAMIC BALANCE CAUSING PREMATURE FAILURE OF THE PUMP. 1996090500697 19960905 00697 CE 1996 9 5 96ZZZX4309 1 19960806 G 2730 05130631 BRACKET CESSNA 172 172G 2072420 CE CENTER FUSELAGE FAILED D K NONE O OTHER IN INSP/MAINT 1 EA 23 1130F 17254725 ELEVATOR BELLCRANK BRACKET LOCATED UNDER FLOOR AT CENTER FUSELAGE FS 27, BROKEN AT ATTACHMENT BULKHEAD. REPLACEMENT PAR T IS CONSTRUCTED OF HEAVIER MATERIAL AND IS A DASH 3 PART NUMBER. 1 H 7 1 3O NT 3A12 1996090500698 19960905 00698 SO 1996 9 5 96ZZZX4310 1 19960814 G 3340 3012905 LIGHT GRIMES PIPER PA31 PA31350 7103110 SO RECOG LIGHT CONTACT BURNS B APCR K NONE O OTHER IN INSP/MAINT 1 NM 01 3582X 318052105 ELECTRICAL CONTACT BUTTON FOR LAMP CENTER ELECTRODE IS INADEQUATE TO SUPPORT HIGH HEAT GENERATED BY HIGH AMPERAGE FLOW T HROUGH LAMP. CONTACT BUTTON BURNS AWAY REQUIRING REPLACEMENT OF (EXPENSIVE) LIGHT BASE ASSEMBLY. MULTIPLE FLEET FAILUR ES. 1 L 7 2 3O A20SO 1996090500700 19960905 00700 CE 1996 9 5 96ZZZX4312 1 19960807 G 7602 VERNIER CONTROL CESSNA 172 R172E 2072413 CE MIXTURE FAILED D O OTHER R PARTIAL RPM/PWR LOSS CR CRUISE 1 SW 01 7898N R1720289 WHILE IN CRUISE FLIGHT, AN ATTEMPT TO LEAN THE MIXTURE WAS MADE. AFTER ABOUT THREE TURNS OF THE VERNIER CONTROL KNOB, A PUSH WAS FELT AND CONTROL WENT TO IDLE CUT-OFF. ATTEMPTS TO PUSH THE CONTROL IN FAILED. AN AIRPORT LANDING WAS MADE W ITH PARTIAL POWER OBTAINED. AFTER LANDING, THE CONTROL WAS CYCLED, A CLICKING WAS HEARD, AND NORMAL OPERATION HAD RETUR NED. THE CONTROL WAS REPLACED WITH A NEW PART. THE FAILED CONTROL WAS SENT TO CESSNA FOR EVALUATION. THE CONTROL HAD FAILED INTERNALLY. ANY BINDING OF AN ENGINE CONTROL SHOULD BE INVESTIGATED AND CORRECTED PRIOR TO FURTHER FLIGHT. **S/ D** CESSNA'S EVALUATION DETERMINED THAT THE CONTROL WAS NOT P/N S1818-1, NOR WAS THE VENDOR A CESSNA APROVED SUPPLIER. 1 H 7 1 3O 3A17 1996090500701 19960905 00701 EA 1996 9 5 96ZZZX4313 2 19960812 G 8550 CH48111 FILTER CHAMPION CESSNA 172 172P 2072436 CE LYC O320 O320D2J 41508 EA ENGINE OIL LEAKING D S K NONE K FLUID LOSS IN INSP/MAINT 1 GL 15 99604 63 F11F181 172766477 WHEN OIL FILTER WAS REMOVED, MECHANIC NOTICED THE CAN AREA OF THE FILTER TURNED, BUT THE ATTACH MOUNTING (CRIMPED FLANGE END BRACKET) STAYED STATIONARY. 1 H 7 1 3O 3 O NT 3A12 E274 1996090500702 19960905 00702 SO 1996 9 5 96ZZZX4314 2 19960809 G 8550 ADAPTER CESSNA 206 U206F 2073333 CE CONT O520 IO520F 17032 SO OIL FILTER NUT LOOSE B LX5R K NONE O OTHER IN INSP/MAINT 1 GL 19 35945 201 U20602819 553686 DURING COMPLIANCE OF AD 96-12-22, OIL FILTER ADAPTER INSPECTION, FOUND RETAINING NUT TORQUE LOOSE. REMOVAL OF OIL FILTE R ADAPTER ASSY REVEALED BOTTOM THREAD OF ADAPTER ASSY CRACKED. THIS PART WAS INSTALLED NEW ON 6-6-95 DUE TO CRACKED THR EADS DURING C/W CESSNA SEB 93-1R, PARAGRAPH B2 (600 HRS INSP). 1 H 7 1 3O 3 O A4CE E5CE 1996090500703 19960905 00703 EA 1996 9 5 96ZZZX4315 2 19960703 G 8520 78027 CONNECTIING ROD CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA NR 1 CYLINDER BOLT FAILED D A UNSCHED LANDING E R K VIBRATION/BUFFET PARTIAL RPM/PWR LOSS FLUID LOSS CR CRUISE 1 SO 11 1493V 1301 17263623 L4160927A ENGINE FAILED IN-FLIGHT WITH LOUD BANG. AIRPLANE FORCE LANDED ON ROAD. INSPECTION REVEALED NR 1 CYLINDER ROD HAD COME LOOSE FROM CRANK AND PUNCHED HOLE IN BOTTOM OF CASE. INSPECTION OF ENGINE FOUND CONNECTING ROD BOLTS, P/N 78027, ON NR 1 AND NR 4 CYLINDERS' CONNECTING RODS HAD BROKEN IN HALF. 1 H 7 1 3O 3 O NT 3A12 E274 1996091200048 19960912 00048 SO 1996 9 12 96ZZZX4316 2 19960731 G 7310 60100040234 HOSE CESSNA 206 U206F 2073333 CE CONT O520 TSIO520C 17040 SO FUEL SYSTEM LEAKING G K NONE K FLUID LOSS IN INSP/MAINT 1 EA 07 2316U U20602360 HOSE ASSY FAILED AFTER 2 YEARS AND LESS THAN 200 HOURS OF OPERATION. HOSE TSO: C531, MFG DATE A1094, LOT NR 06827. 1 H 7 1 3O 3 O A4CE E8CE 1996091200049 19960912 00049 SO 1996 9 12 96ZZZX4317 2 19960731 G 7310 60100040286 HOSE ASSY AEROQUIP CESSNA 206 U206F 2073333 CE CONT O520 TSIO520C 17040 SO FUEL SYSTEM LEAKING D L K NONE K FLUID LOSS IN INSP/MAINT 1 EA 07 2316U U20602360 HOSE ASSY FAILED AFTER 2 YEARS AND LESS THAN 200 HOURS OF OPERATION. HOSE IS TSO C53A, MFG DATE A1094, LOT NR 06827. 1 H 7 1 3O 3 O A4CE E8CE 1996091200050 19960912 00050 CE 1996 9 12 96ZZZX4318 1 19960710 G 5700 NAS679AW NUT CESSNA 206 U206F 2073333 CE LIFT STRUT FRACTURED D S K NONE O OTHER IN INSP/MAINT 1 NM 03 50939 3065 U20601954 LIFT STRUT HAS 5 BOLTS, AN5, THROUGH TOP AND BOTTOM. TOTAL OF '5' NUTS HAD FAILED (FIFTY PERCENT). RIGHT LIFT STRUT AL L NORMAL. CAUSE UNKNOWN, NUT P/N NAS679AW. 1 H 7 1 3O A4CE 1996091200051 19960912 00051 SO 1996 9 12 96ZZZX4319 1 19960624 G 3211 AN510A TRUNNION ATTACH PIPER PA34 PA34200T 7103406 SO MLG BOLTS LOOSE D K NONE O OTHER IN INSP/MAINT 1 GL 21 47611 6090 347770418 PIPER SB 956, PART II, WAS C/W AT 4,914 HOURS TT ON 5-92. PART II IS PERMANENT COMPLIANCE AND BOLTS USED WERE LOOSE ON ATTACH FITTINGS. THESE ARE A LARGER BOLT THAN ORIGINAL WITH AIRCRAFT. RETORQUED ALL BOLTS PER SB 956, PART II. 1 L 7 2 3O A7SO 1996020200066 19960202 00066 GL 1996 2 2 96ZZZX432 2 19960109 G 7510 6856983 VALVE HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL ENGINE ANTI-ICE LEAKING B EOOR K NONE O OTHER IN INSP/MAINT 1 AL 03 5074R 1151D CAE830750 ANTI-ICE VALVE WAS LEAKING. FOUND THE PLUNGER WAS WORN ON ONE SIDE ALLOWING THE VALVE TO BE COCKED OFF ITS SEAT. REPLA CED PART. 1 G 7 1 3U 3 U H3WE E4CE 1996091200052 19960912 00052 WP 1996 9 12 96ZZZX4320 1 19960813 G 5320 738080 PLATFORM HAMSTD LKHEED 1011 1011* WP APU DAMAGED B S SI3R K NONE W INADEQUATE Q C IN INSP/MAINT 1 NE 03 GBBAF ED55196 RIVET INSTALLATION TOOL MARKS EVIDENT ON REAR PANEL OF APU PLATFORM (SURGE SYSTEM SIDE). SUSPECT RIVET INSTALLATION TOO L RUBBED AGAINST PLATFORM DURING INSTALLATION OF RIVETS. REF: OHM 49-00-01, PAGE 1138B, FIGURE 9B. 2 L 7 3 4F A23WE 1996091200053 19960912 00053 NE 1996 9 12 96ZZZX4321 2 19960819 G 7210 77577511 HOUSING HAMSTD 77580010 SAAB SF340 SF340A 7850100 EU GE CT7TP CT79B 30030 NE GC 49 GEARCASE HOLE B S SI3R K NONE O OTHER IN INSP/MAINT 1 NE 03 8439 143 GEE785328 DURING PERFORMANCE OF AN AS RECEIVED TEST, OIL WAS NOTED COMING FROM THE ATMOSPHERIC VENT. THE DISASSEMBLY OF THE GEAR CASE REVEALED THE AFT HOUSING TRANSFER TUBE BORE AREA SHOWED A HOLE IN THE HOUSING ALLOWING OIL TO ENTER THE ADS AREA OF THE GEARBOX. EXAMINATION OF THE AREA WHERE THE HOLE IS SHOWS THAT LOCAL HAND BLENDING HAD BEEN PERFORMED ON THE CASTIN G RESULTING IN A THIN WALL. THE BLENDED AREA APPEARED TO HAVE BEEN ANODIZED DURING THE ORIGINAL MANUFACTURING PROCESS. 2 L 7 2 4T 4 T RT A52EU E8NE 1996091200054 19960912 00054 EU 1996 9 12 96ZZZX4322 1 19960731 G 3230 258UN4871A BRIDGE CASTING 258UN3143A BRAERO DH125 BAE125800A 1500285 EU NLG DRAG LINK BEARING DAMAGED B JGVR K NONE W INADEQUATE Q C IN INSP/MAINT 1 CE 09 CGCIB SAM2402 258048 NOSE LANDING GEAR DRAG LINK, ALL 3 ROLLER BEARINGS IN NEW STEEL CASTING WERE DAMAGED WHEN INSTALLED BY FACTORY. THIS CA USED BINDING OF THE PIVOT SHAFT. 2 L 7 2 4F RT A3EU 1996091200055 19960912 00055 NE 1996 9 12 96ZZZX4323 2 19960701 G 7230 536210 LOCK PWA JT12 JT12A8 52042 NE 3RD STAGE DISK MISSING B JV2R K NONE O OTHER IN INSP/MAINT 1 CE 03 322 P637622NB INTERNAL BLADE RUBBING, BINDING, AND LOCKING UP. AN INDUCTION TEST RUN WAS PEFORMED ON 6-20-96. DURING THE TEST, VIBRA TION OF 3.8 MIL AT 75 PERCENT WAS NOTED. (3.2 MIL IS MAXIMUM ALLOWABLE). ENGINE WAS DISASSEMBLED AS NECESSARY TO ACCE SS COMPRESSOR ASSY. COMPRESSOR WAS DISASSEMBLED TO ELEVATE RUBBING CONDITION. P/N 536203, 3RD STAGE COMPRESSOR BLADE W AS FOUND LOOSE IN THE BLADE SLOT OF 3RD STAGE DISK. BLADE HAD MOVED AFT MAKING CONTACT WITH COMPRESSOR STATOR, P/N 3855 03, DAMAGING EVERY VANE. BLADE LOCK COULD NOT BE FOUND AND SUSPECT IT MAY HAVE FAILED AND EXITED ENGINE ALLOWING BLADE TO WORK LOOSE. NO OBVIOUS DAMAGE FROM LOCK WAS NOTED. CAUSE OF LOCK FAILURE IS UNKNOWN AT THIS TIME. ONE EACH P/N 536 4 J 1E9 1996091200057 19960912 00057 CE 1996 9 12 96ZZZX4325 1 19960725 G 3230 12805201 LOCK VALVE CESSNA 177 177RG 2073709 CE MLG MALFUNCTION B L CGFR O OTHER J WARNING INDICATION AP APPROACH 1 GL 03 1566H 177RG0740 PILOT WAS UNABLE TO EXTEND LANDING GEAR EITHER BY THE NORMAL OR THE EMERGENCY HYDRAULIC SYSTEM. A GEAR UP LANDING WAS M ADE AND MINOR DAMAGE. WHEN ACFT WAS JACKED UP PRIOR TO REMOVING IT, NOTED THE LANDING GEAR COULD NOT BE PUSHED INTO LOC KS. WHEN MAIN GEAR WAS MOVED TO DOWN AND LOCK POSITION, NOSE GEAR WOULD RETRACT, AND WHEN MAINS WERE MOVED TO WHEELWELL S, NOSE WOULD GO INTO ITS DOWN AND LOCKED POSITION. HYDRAULIC PRESSURE WAS TRAPPED IN RETRACT 'SIDE' OF HYD SYS. A B-N UT ON THE RETRACT PORT OF NOSE GEAR HYD ACTUATOR WAS LOOSENED TO ALLOW FLUID TO ESCAPE AND THE HAND PUMP WAS THEN USED T O PUMP LANDING GEAR TO A 'DOWN AND LOCKED' POSITION ALLOWING ACFT TO BE TOWED FROM RUNWAY. 1 H 7 1 3O A20CE 1996091200059 19960912 00059 EU 1996 9 12 96ZZZX4327 1 19960725 G 2751 LEVER ARM AMD FALC20 FALCON20FS 2730105 EU WING FLAP SWITCH WORN B A JGVR K NONE N FALSE WARNING CR CRUISE 1 CE 09 148MC 6470 428 AIRCRAFT FLYING IN A CLEAN CONFIGURATION WITH G-LOADS WOULD GET A GEAR WARNING HORN THAT COULD NOT BE CANCELLED. PROBLE M COULD NOT BE DUPLICATED ON JACKS IN THE HANGAR, BUT HAPPENED ON EVERY FLIGHT. FINALLY, THE 24G 280 DEGREE FLAP SWITCH ES, MOUNTED ON THE WING, PIVOT ARM LEVER AND THE FLAP MOUNTED SWITCH ACTUATION RAMP, WERE FOUND AT MAXIMUM ADJUSTMENT. I NSPECTION REVEALED PIVOT LEVER ROLLER WAS FLAT SPOTTED AND CENTER HOLE WORN OVERSIZE. 2 L 7 2 4F RT A7EU 1996091200060 19960912 00060 GL 1996 9 12 96ZZZX4328 3 19960812 G 6111 BLADE BEECH 200 200BEECH 1152920 CE HARTZL HCB3T HCB3TN3 GL PROPELLER TIP FLUTTER D A K NONE E VIBRATION/BUFFET IN INSP/MAINT 1 SO 07 1660W 620 BB390 RBU15955 BOTH PROPELLERS GO INTO TIP FLUTTER AT ENGINE POWER SETTINGS AT AND ABOVE 1,800 FEET/POUNDS OF TORQUE. HIGH FREQUENCY V IBRATION CAN BE FELT THROUGHOUT THE ENTIRE AIRCRAFT. BLADE TIPS TOO THIN AT TIPS. MANUFACTURER HAS NO STANDARDS FOR MI NIMUM THICKNESS AT THIS BLADE STATION. 1 L 7 2 4T A24CE 6 C P15EA 1996091200061 19960912 00061 EU 1996 9 12 96ZZZX4329 1 19960819 G 5753 BEARING FOKKER F27 F27MK200 4990620 EU FLAP HINGE WRONG PART A S A MJ4R K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 19 279MA 10297 DURING A C-CHECK INSPECTION, NOTED THAT AN INCORRECT BEARING WAS INSTALLED IN THE LEFT FLAP CENTER HINGE. THE PART WAS UNIDENTIFIABLE AND NO PART OR SERIAL NUMBERS WERE PRESENT. PART APPEARED TO COME FROM A NON-AIRCRAFT PARTS SOURCE. 2 H 7 2 4T A817 1996020200067 19960202 00067 GL 1996 2 2 96ZZZX433 2 19960102 G 7321 23033917 FUEL CONTROL BELL 206 206B 1181511 SW ALLSN 250C 250C20J 03013 GL ENGINE DEFECTIVE A EJYA O OTHER J WARNING INDICATION IN INSP/MAINT 1 WP 07 90328 1935 335870 1853 830842 PILOT ABORTED START WHEN TOT WENT PAST 850 DEGREES RAPIDLY DURING START ATTEMPT. TROUBLESHOOTING REVEALED FAULTY FUEL C ONTROL. REPLACED FUEL CONTROL IAW ALLISON AND BELL MM. LEAK AND FUNCTIONAL CHECKS GOOD. 1 G 7 1 3U 3 U H2SW E4CE 1996091200062 19960912 00062 CE 1996 9 12 96ZZZX4330 1 19960807 G 2821 306051 FILTER ASSY BEECH 36 A36 1151604 CE FUEL SYSTEM BOWL LOOSE B CB5Y K NONE X ENGINE FLAMEOUT IN INSP/MAINT 1 EA 35 250TP 208 E2408 ENGINE FLAME-OUT ON POWER CHECK. FUEL FILTER BOWL FOUND LOOSE, SUFFICIENT TO ALLOW ENGINE FUEL STARVATION. FUEL BOWL I S TORQUED TO 25 INCH/POUND (THE LOWER TORQUE VALUE) AS HAD EXPERIENCED A CRACKED FILTER HOUSING WHEN TORQUED TO THE HIGH LIMITS. FILTER LOCKING WIRE FRACTURED RESULTING IN THE BOWL VIBRATING LOOSE. SUSPECT TOO MANY TWISTS TO THE INCH AT T HE TOP END OF THE LOCKING WIRE. 1 L 7 1 3O 3A15 1996091200063 19960912 00063 NE 1996 9 12 96ZZZX4331 2 19960808 G 7230 COMPRESSOR RKWELL NA265 NA26540 6402608 CE PWA JT12 JT12A8 52042 NE ENGINE BINDING D K NONE O OTHER IN INSP/MAINT 1 SO 09 302NT 5836 420 28281 P672953NB COMPRESSOR VERY DIFFICULT TO ROTATE, IINTERNAL BINDING COULD BE FELT WHEN ROTATING BY HAND WITH SHORT SPOOL DOWN TIME. N O FOD NOTED, NO DAMAGE OR VISUAL DEFECTS NOTED IN TURBINE HOT SECTION. ALL IN-FLIGHT AND GROUND TEST PARAMETERS NORMAL. ENGINE WAS REMOVED FROM SERVICE AND RETURNED TO SABERLINER FOR TEAR DOWN INSPECTION. 2 L 7 2 4J 4 J A2WE 1E9 1996091200064 19960912 00064 CE 1996 9 12 96ZZZX4332 1 19960807 G 3233 265580125 ACTUATOR RKWELL NA265 NA26540 6402608 CE NLG LEAK D K NONE K FLUID LOSS IN INSP/MAINT 1 SO 09 301NT 2829 ACTUATOR WAS INSTALLED ON THE AIRCRAFT, OPERATIONALLY CHECKED, AND REMOVED DUE TO LEAKAGE THROUGH A HOLE (OR CRACK) IN T HE ACTUATOR CYLINDER (BARREL) WALL. THE ACTUATOR WAS OVERHAULED 9-7-95. ACTUATOR TIME SINCE OVERHAUL WHEN REMOVED: ZE RO HOURS. AIRCRAFT TOTAL TIME: 14,208.5 HOURS. 2 L 7 2 4J A2WE 1996091200065 19960912 00065 SW 1996 9 12 96ZZZX4333 1 19960801 G 2435 23046007 GENERATOR LEARSIEGLER GULSTM 680TP 680W 0141716 SW START/GEN BEARING FAILED B ESMR A UNSCHED LANDING H ELECT. POWER LOSS-50 PC CR CRUISE 1 SO 11 54163 10 2097 177412 GENERATOR STOPPED OPERATING IN-FLIGHT. AFTER LANDING, CHECKED STARTER/GENERATOR AND FOUND LOCKED UP. 1 H 7 2 3T 2A4 1996091200066 19960912 00066 EU 1996 9 12 96ZZZX4334 1 19960808 G 3244 DR6385T TIRE DUNLOP HWKSLY DH125 BH125400A 4230138 EU SIDEWALL FAILED D K NONE O OTHER IN INSP/MAINT 1 SO 03 68CB 206 95206281 NA765 TIRE LOST 25 POUNDS PRESSURE OVERNIGHT. FOUND HOLE IN SIDEWALL. REPLACED TIRE WHICH HAD 199 LANDINGS. NORMAL USAGE GI VES 500 LANDINGS. TIRE SENT TO DUNLOP FOR EXAMINATION. 2 L 7 2 4J A3EU 1996091200068 19960912 00068 NE 1996 9 12 96ZZZX4336 2 19960719 G 7230 3021436 BYPASS DUCT MTSBSI MU300 MU300 5780602 CE PWA JT15 JT15D4 52112 NE LT ENGINE FAILED D A K NONE O OTHER IN INSP/MAINT 1 SO 03 83BG 452 A018SA PCE70623 A CRACK DEVELOPED AT THE FORWARD FLANGE OF THE AFT INNER BYPASS DUCT AT THE 6 O'CLOCK POSITION ALLOWING IT TO COME OUT O F THE MATING FLANGE AND ENTER THE AIR FLOW, THEREBY CAUSING A 3 INCH (APPROX) SECTION TO PEEL BACK AND CAUSE A 2 INCH (A PPROX) TEAR ALONG THE RADIUS OF THE BEND. THE PILOT NOTICED THE PIECE HANGING DOWN DURING PRE-FLIGHT INSPECTION AND ASS Y WAS REPLACED BEFORE FURTHER FLIGHT. 2 H 7 2 4F 4 F RT A14SW E1NE 1996091200069 19960912 00069 NE 1996 9 12 96ZZZX4337 3 19960801 G 6114 PROPELLER HAMSTD AIRTRC AT300 AT301 0390103 SW HAMSTD 12D 12D40 NE COUNTERWEIGHT BOLT BROKE H A UNSCHED LANDING O OTHER NR NOT REPORTED 1 CE 07 8883S 3010226 728749 COUNTERWEIGHT BOLT BROKE CAUSING AIRCRAFT TO PERFORM AN EMERGENCY LANDING AND NOSING OVER ON ITS BACK CAUSING EXTENSIVE DAMAGE TO THE AIRCRAFT. 1 L 7 1 3R A9SW 5 C P257 1996091200070 19960912 00070 CE 1996 9 12 96ZZZX4338 1 19960729 G 7830 202SR00113 BUMPER PAD ROHR 65550291 CESSNA 500 550 2076604 CE THRUST REV DEFECTIVE D K NONE O OTHER IN INSP/MAINT 1 EA 23 87SF 320 0218 5500096 PILOTS REPORTED LT REVERSER WOULD INTERMITTENTLY 'HANG UP' WHILE OPENING, BUT CLOSE AND LOCKING WERE NORMAL. 319.7 HRS, 490 CYCLES PRIOR TO THIS OCCURRENCE, ROHR SB CIT 78-8R1 WAS C/W WHICH INSTALLS NEW DOOR BUMPERS OVER OLD BUMPERS. THIS DECREASES CLEARANCE BETWEEN INBD UPPER STANG FAIRING SUPPORT AND DOOR BUMPER. OVER TIME, NEW BUMPER MUSHROOMED SLIGHTL Y ALLOWING DOOR TO CATCH ON SUPPORT SKIN. INSPECTION OF RT SIDE SHOWED SIGNS OF SAME PROBLEM BEGINNING TO OCCUR. ROUTI NG OUT FORWARD SKIN OF BOTH SUPPORTS FOR EXTRA CLEARANCE RECTIFIED PROBLEM. SUBMITTER SUGGESTS SB BE REVISED TO INSPECT THIS AREA AND ALLOW A MINIMUM OF .25 INCH CLEARANCE. 1 L 7 2 4F A22CE 1996091200071 19960912 00071 CE 1996 9 12 96ZZZX4339 1 19960729 G 7830 202SR00114 BUMPER PAD ROHR 65550291 CESSNA 500 550 2076604 CE THRUST REV DEFECTIVE D K NONE O OTHER IN INSP/MAINT 1 EA 23 87SF 320 0218 5500096 PILOTS REPORTED LT REVERSER WOULD INTERMITTENTLY 'HANG UP' WHILE OPENING, BUT CLOSE AND LOCKING WERE NORMAL. 319.7 HRS, 490 CYCLES PRIOR TO THIS OCCURRENCE, ROHR SB CIT 78-8R1 WAS C/W WHICH INSTALLS NEW DOOR BUMPERS OVER OLD BUMPERS. THIS DECREASES CLEARANCE BETWEEN INBD UPPER STANG FAIRING SUPPORT AND DOOR BUMPER. OVER TIME, NEW BUMPER MUSHROOMED SLIGHTL Y ALLOWING DOOR TO CATCH ON SUPPORT SKIN. INSPECTION OF RT SIDE SHOWED SIGNS OF SAME PROBLEM BEGINNING TO OCCUR. ROUTI NG OUT FORWARD SKIN OF BOTH SUPPORTS FOR EXTRA CLEARANCE RECTIFIED PROBLEM. SUBMITTER SUGGESTS SB BE REVISED TO INSPECT THIS AREA AND ALLOW A MINIMUM OF .25 INCH CLEARANCE. 1 L 7 2 4F A22CE 1996091200072 19960912 00072 NM 1996 9 12 96ZZZX4340 1 19960813 G 2810 25W357450003 DRAIN LINE ISRAEL 1125 1125 NM REFUEL PORT CRACKED B JGVR K NONE O OTHER IN INSP/MAINT 1 CE 09 91FD 2109 045 DURING OTHER MAINTENANCE,THE DRAIN LINE FOR THE GRAVITY REFUEL PORT WAS FOUND CRACKED IN 4 PLACES. THIS COULD ALLOW FU EL TO LEAK INTO THE TAILCONE/BAGGAGE AREA. DEBRIS WAS FOUND NEAR OUTLET. LINE WAS REPLACED AND A LOW SPOT WAS ELIMINAT ED. THE GRAVITY FUEL CAP IS ALSO A RELIEF VALVE IN CASE OF FUEL EXPANSION. THE EXPANDED FUEL WOULD DRAIN INTO THE AFFE CTED DRAIN TUBE. 2 L 7 2 4F RT A16NM 1996091200073 19960912 00073 1996 9 12 96ZZZX4341 4 19960815 G 2562 AK450 ELT AMERIKING WIRING DEFECTIVE C L K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 13 INSPECTION FOUND WIRING EMPLOYED BETWEEN THE CIRCUIT BOARD AND THE BATTERY CASE DEFECTIVE. THE SLIP-ON CONNECTOR WAS AS SEMBLED WITH APPROXIMATELY 2MM OF THE CONTACT LUGS PROTRUDING FROM THE PLASTIC HOUSING LEAVING THESE METAL ENDS VERY CLO SE AND IN DANGER OF SHORTING. SINGLE STRAND WIRE IS USED. THIS IS INAPPROPRIATE FOR THE TYPE OF CRIMP CONNECTOR USED, AND WOULD ALSO BE OF CONCERN FOR FATIGUE LIFE. THE CRIMP ON ONE OF THE CONNECTORS IS LOOSE. THE OTHER ENDS OF THE WIRE S WERE LOOPED AROUND THE BATTERY SPRING ENDS, THE WIRES BEING SOLDERED. BOTH WIRES WERE EASILY SLIPPED OFF THE SPRINGS WITHOUT UNSOLDERING THEM, OBVIOUSLY THE TYPE OF PLATING ON THE SPRINGS IS INAPPROPRIATE FOR RELIABLE SOLDER ADHESION. 1996091200074 19960912 00074 NE 1996 9 12 96ZZZX4342 2 19960711 G 7230 536211 LOCK PWA JT12 JT12A8 52042 NE 4TH STAGE DISK MISSING B L JV2R K NONE O OTHER IN INSP/MAINT 1 CE 03 1300 P672928NB METAL-TO-METAL CONTACT, BIND, BLADE RUB. INVESTIGATION FINDINGS: AN INDUCTION TEST RUN COULD NOT BE ACCOMPLISHED DUE T O RUBBING CONDITION. THE ENGINE AND COMRPESSOR ASSEMBLY WERE DISASSEMBLED TO IDENTIFY CAUSE OF DISCREPANCY. INVESTIGAT ION REVELAED THAT P/N 536204, FOURTH STAGE COMPRESSOR BLADE, WAS FOUND LOOSE IN THE BLADE SLOT OF THE FOURTH STAGE DISK. THE BLADE HAD MOVED AFT MAKING CONTACT WITH THE INNER SEAL AREA OF THE FOURTH STAGE COMPRESSOR STATOR, P/N 542274. P/ N 536211, BLADE LOCK, COULD NOT BE FOUND AND SUSPECT IT MAY HAVE FAILED AND LEFT THE ENGINE ALLOWING THE BLADE TO WORK L OOSE. NO OBVIOUS DAMAGE FROM THE LOCK WAS NOTED. 4 J 1E9 1996091200075 19960912 00075 CE 1996 9 12 96ZZZX4343 1 19960624 G 7714 22A667 TACH GENERATOR BEECH 58 58 1152740 CE STATOR WINDING INOPERATIVE B L FFKR K NONE O OTHER NR NOT REPORTED 1 SO 05 11HW 65 8060 TH271 THE TACHOMETER GENERATOR FAILED DURING NORMAL OPERATING CONDITIONS. THE SUSPECT CAUSE IS PHASE 'A' OPEN CIRCUIT, WITHIN STATOR WINDING. 1 L 7 2 3O 3A16 1996091200076 19960912 00076 CE 1996 9 12 96ZZZX4344 1 19960808 G 2820 TRANSFER PUMP CESSNA 206 U206F 2073333 CE TIP TANK CORRODED G L A K NONE O OTHER IN INSP/MAINT 1 NM 01 CGVQG U20602082 MALFUNCTION AND DEFECT REPORT RECEIVED FROM TRANSPORT CANADA ON A CESSNA U206 IN WHICH CHECK VALVES, FUEL LEVEL TRANSMIT TERS, AND TRANSFER PUMPS WERE FOUND CORRODED IN THE AUXILIARY FUEL TIP TANKS INSTALLED IAW STC SA4368WE. HAVE DETERMINE D THE CORROSION RESULTED FROM CONDENSATION WITHIN THE TANKS DUE TO LOW FUEL LEVELS OVER AN EXTENDED PERIOD OF TIME. NOT E THAT THIS PHENOMENON IS NOT UNIQUE TO THE FLINT AUXILIARY FUEL TIP TANK INSTALLATION. 1 H 7 1 3O A4CE 1996091200077 19960912 00077 CE 1996 9 12 96ZZZX4345 1 19960624 G 7714 H60050 TACH GENERATOR BEECH 58 58 1152740 CE TACH DRIVE SHAFT SHEARED B L FFKR K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 05 11HW 1 239102 TH271 THE TACHOMETER GENERATOR FAILED UNDER NORMAL OPERATING CONDITIONS. THE SUSPECT CAUSE IS A SMALL O-RING FITTED ON THE DR IVESHAFT AND INSIDE THE ROTOR SHAFT IS AN UNSPECIFIED PART. (DOES NOT APPEAR IN PARTS BREAKDOWN.) THIS O-RING RESTRICT ED THE SELF-CENTERING ACTION OF THE DRIVESHAFT WITH MATING DRIVE ON THE AIRCRAFT. THIS CAUSED THE DRIVESHAFT TO FAIL. 1 L 7 2 3O 3A16 1996091200122 19960912 00122 SW 1996 9 12 96ZZZX4348 1 19960621 G 6210 47110250023 BLADE BELL 47 OH13H 1180820 SW M/R DEFECTIVE B L A WG3R K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 27 67154 253 A1149 585377 RECEIVED THE NEW BLADES AND REINSTALLED. WERE UNABLE TO TRACK AND BALANCE THE M/R SYSTEM TO AN ACCEPTABLE LEVEL DUE TO ONE BLADE BEING OUT OF TRACK AND WAS UNABLE TO CONTROL THIS PROBLEM WITH STANDARD ADJUSTMENTS. 1 G 7 1 3O H1 1996091200188 19960912 00188 SW 1996 9 12 96ZZZX4367 1 19960717 G 6310 28952017 SEAL BELL 206 206B 1181511 SW FREEWHEEL LEAKING B WG3R K NONE K FLUID LOSS IN INSP/MAINT 1 WP 27 82HH 212 4337 PILOT REPORTED FREEWHEELING ASSY LEAKING OIL. FOUND INPUT SEAL LEAKING. REMOVED SEAL, P/N 28905-2017, AND INSTALLED NE W SEAL, P/N 206-340-204-101, WITH O-RINGS MB3248/1-237 AND MB248/1-215. 1 G 7 1 3U H2SW 1996091200189 19960912 00189 SW 1996 9 12 96ZZZX4368 1 19960717 G 7110 50007A26 STUD BELL 206 206B 1181511 SW COWLING LOOSE B WG3R K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 27 82HH 212 4337 PILOT REPORTED THAT COWLING STUDS WERE LOOSE WHEN FASTENED. INSPECTED AND FOUND ENGINE COWL STUDS TO BE TOO LONG. REMO VED AND INSTALLED NEW STUDS, P/N 50-007-15, AND GROMMET, P/N 50-009-2 ( 5 EACH). TWO EACH P /N 50007A26 AND P/N 50007A 22. 1 G 7 1 3U H2SW 1996091200190 19960912 00190 1996 9 12 96ZZZX4369 4 19960717 G 2312 90367 SWITCH BELL 206 206B 1181511 SW PILOT TRANSMIT DEFECTIVE B WG3R K NONE O OTHER IN INSP/MAINT 1 WP 27 82HH 212 4337 PILOT REPORTED THE PILOT'S TRANSMIT SWITCH WAS INOPERATIVE, INTERMITTENT. INSPECTED TRANSMIT SWITCH AND FOUND CONTACT BENT. INSTALLED NEW SWITCH, P/N 90-367, AND OPS TESTED. 1 G 7 1 3U H2SW 1996091200529 19960912 00529 CE 1996 9 12 96ZZZX4370 1 19960425 G 3233 9910002RX ACTUATOR CESSNA 310 310L 2074230 CE MLG PIN SHEARED D K NONE O OTHER IN INSP/MAINT 1 WP 27 3315X 149 1776 310L0165 THE GEAR ACTUATOR STOP PIN WAS FOUND SHEARED. THE SUSPECT CAUSE WAS FROM THE GEAR MOTOR NOT STOPPING AND SHEARING THE S TOP PIN. THE COAST TIME IN THE CW DIRECTION WAS EXCESSIVE. 1 L 7 2 3O 3A10 1996091900001 19960919 00001 EA 1996 9 19 96ZZZX4371 2 19960824 G 8530 CYLINDER PIPER PA28 PA28181 7102807 SO LYC O360 O360A4M 41514 EA SPARK PLUG HOLE CRACKED D A UNSCHED LANDING E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 SO 16 30230 287990088 L2558336A CYLINDER CRACKED FROM TOP SPARK PLUG HOLE AROUND SIDE TO BOTTOM SPARK PLUG HOLE. AIRCRAFT LANDED SAFELY WITHOUT FURTHER PROBLEMS (LOSS OF RPM). ENGINE TT, 2,601.4 HOURS. TSMOH: 607.7 HOURS. SUBMITTER STATED THIS IS THE THIRD CRACKED CY LINDER ON THIS AIRCRAFT SINCE OVERHAUL. 1 L 7 1 3O 3 O 2A13 E286 1996091900002 19960919 00002 CE 1996 9 19 96ZZZX4372 1 19960823 G 2434 ALV9510 ALTERNATOR PRESTOLITE CESSNA 421 421B 2076014 CE AUXILIARY CIRC WIRE BROKEN D O OTHER J WARNING INDICATION CR CRUISE 1 SW 13 41055 63 5100914 421B0576 RIGHT ALTERNATOR 'FAIL' LIGHT FLICKERED AND CAME ON IN-FLIGHT, ALTERNATOR SHOWED TO HAVE CORRECT OUTPUT. REMOVED SAME W ITH ANOTHER. AFTER 38 HOURS, THE REPLACEMENT ALTERNATOR HAD THE SAME PROBLEM. CALLED ELECTRO SYSTEMS AND CONVEYED PROB LEM TO SERVICE REP. HE CHECKED THE PROBLEM ON FIRST ALTERNATOR AND FOUND WIRE TO AUXILILARY TERMINAL BROKEN. HE GAVE P ERMISSION TO DISASSEMBLE PRESENT ALTERNATOR. FOUND THE SAME PROBLEM. AFTER RE-SOLDER OF AUXILIARY WIRE AND REASSEMBLY, RAN A/C. THE PROBLEM WAS CURED. 1 L 7 2 3O A7CE 1996091200530 19960912 00530 SO 1996 9 12 96ZZZX4373 2 19960813 G 8530 635448CP CYLINDER CESSNA 188 A188B 2073005 CE CONT O520 IO520D 17032 SO NR 4 FAILED D A UNSCHED LANDING E R K VIBRATION/BUFFET PARTIAL RPM/PWR LOSS FLUID LOSS CR CRUISE 1 SW 17 9370R 450 5538AA620 18802262T 563670 NR 4 CYLINDER HEAD SEPARATED FROM BARREL CAUSING ENGINE FAILURE IN-FLIGHT RESULTING IN FORCED LANDING (I-35 SOUTH, SAN A NTONIO). R2 CYLINDER ASSY OPS CHECK OK. 1 L 7 1 3O 3 O A9CE E5CE 1996091200531 19960912 00531 CE 1996 9 12 96ZZZX4374 1 19960822 G 3710 3P194FA PUMP PESCO CESSNA 182 182J 2072722 CE CONT O470 O470N 17026 SO VACUUM SYSTEM DRIVE SHEARED D K NONE O OTHER NR NOT REPORTED 1 CE 07 2714F PE09124FDG 18256814 1319985R VACUUM PUMP DRIVESHAFT SHEARED AND SPLINES EXTREMELY WORN. IT STILL MADE VACUUM PRESSURE. SUBMITTER RECOMMENDS MORE FR EQUENT INSPECTIONS OF DRIVE SPLINE ASSY (NOTE: WET DRIVE VACUUM PUMP). 1 H 7 1 3O 3 O NT 3A13 E273 1996091200532 19960912 00532 GL 1996 9 12 96ZZZX4375 3 19960731 G 6111 1301 CLAMP PIPER PA31T PA31T1 7103126 SO HARTZL HCB3T HCB3TN3 GL BLADE CORRODED D K NONE O OTHER IN INSP/MAINT 1 NM 03 BU12340 PROPELLERS WERE IN FOR TIME OVERHAUL. THREE OF THE BLADE CLAMPS WERE REJECTED FOR CORROSION INSIDE THE CLAMP WHERE CONT ACT IS MADE WITH THE BLADE THRUST BEARING. ONE CLAMP WAS REJECTED FOR A CRACK THAT RAN PARALLEL TO THE CLAMP HAD SPLIT. IT WAS ALSO FOUND THAT THE WRONG SPRING ASSY WAS INSTALLED IN BOTH PROPELLERS. THE WRONG SPRING ASSY HAS HIGHER SPRIN G TENSION THAN THE ONE THAT SHOULD HAVE BEEN INSTALLED. THE SPRING ASSYS WERE CHANGED AND THE FOUR CLAMP ASSYS WERE REP LACED ALONG WITH OVERHAUL OF THE PROPS AND RETURNED TO SERVICE. 1 L 7 2 3T A8EA 6 C P15EA 1996091200533 19960912 00533 CE 1996 9 12 96ZZZX4376 1 19960801 G 3250 59420011 BRACKET CESSNA 310 T310P 2074240 CE NLG STRUT CRACKED D S K NONE O OTHER IN INSP/MAINT 1 NM 08 AFTER FINDING A CRACKED STEERING BRACKET ON A CESSNA 401, INSPECTED A CE310 AND FOUND BRACKET CRACKED IN RADIUS. BRACKE T LOCATED ON TOP OF NOSE STRUT. TTAF: 3,826. 1 L 7 2 3O 3A10 1996091200534 19960912 00534 1996 9 12 96ZZZX4377 2 19960709 G 7322 CF131520 SHAFT FACET MA3PA THROTTLE MISDRILLED D P K NONE W INADEQUATE Q C IN INSP/MAINT 1 EA 23 PURCHASED CARBURETOR THROTTLE SHAFT KIT, P/N CF 778-1006, NEW FROM AVSCO. ON INSPECTION OF PART BEFORE INSTALLATION, FOU ND PART ASSEMBLED IMPROPERLY, P/N CF13-1520. THE HOLE IN THE THROTTLE STOP WAS DRILLED CROOKED AND STILL ASSEMBLED ONTO THE SHAFT. BECAUSE OF THIS, THE SERRATED THROTTLE LEVER WOULD NOT FIT SQUARELY, AND THE SERRATED PARTS DID NOT LINE UP AND ENGAGE EACH OTHER PROPERLY. THROTTLE LEVER, P/N 12-B57. SUBMITTER STATED PROPER QUALITY CONTROL WOULD SOLVE THIS PROBLEM. 1996091200535 19960912 00535 EA 1996 9 12 96ZZZX4378 3 19960801 G 6110 PROPELLER PIPER PA28 PA28161 7102803 SO SNSNCH 74D 74DM EA FLANGE MISINSTALLED D L K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 99 SUBMITTER REPORTS FINDING PIPER PA 28-161 PROPELLERS INCORRECTLY INSTALLED PER SERVICE MANUAL INSTRUCTIONS. SHOULD BE INDEXED WITH PROPELLER BLADES AT 2 AND 8 O'CLOCK POSITIONS AS VIEWED FROM COCKPIT. 1 L 7 1 3O 2A13 5 N P88614 1996091200536 19960912 00536 CE 1996 9 12 96ZZZX4379 1 19960718 G 2820 MS28775111 O-RING CCA3400 BEECH 36 A36 1151604 CE DRAIN VALVE WRONG PART D L K NONE W INADEQUATE Q C IN INSP/MAINT 1 NE 03 3122U 95 E2431 THE FUEL DRAIN VALVES MANUFACTURED BY CURTIS USE SPECIAL SEALS THAT ARE COMPOUNDED OF MATERIALS SPECIFICALLY DESIGNED TO RESIST AVIATION FUEL. MORE IMPORTANTLY, THE SEALS ARE SPECIALLY SHAPED (MOST LOOK LIKE A SMALL PANCAKE WITH A HOLE IN THE MIDDLE) TO FIT CURTIS VALVES. THE CORRECT REPLACEMENT SEAL FOR THIS VALVE IS P/N CCA1319. GENERIC O-RINGS MAY NOT PROVIDE ADEQUATE SEALING OR PROTECTION AGAINST CHEMICAL ATTACK BY AVIATION FUEL. IN-FLIGHT LEAKAGE COULD RESULT IN A RE DUCTION OF AN AIRCRAFT'S RANGE OR ENDURANCE, OR CREATE FIRE HAZARD. 1 L 7 1 3O 3A15 1996091200537 19960912 00537 NE 1996 9 12 96ZZZX4380 2 19960814 G 7313 231009801 NOZZLE 216362036 BAG BAE146 BAE146100A 1500260 EU LYC ALF502 ALF502R 41580 NE FUEL MANIFOLD CRACKED B S A PGLR K NONE O OTHER IN INSP/MAINT 1 SO 13 82F001 OVERTORQUED CONDITION RESULTING IN CRACKED FLANGE AREA. RECOMMEND USE OF PROPER TORQUE DURING INSTALLATION OF NOZZLE IN TO MANIFOLD ASSY. 2 H 7 4 4F 4 F RT A49EU E6NE 1996091200538 19960912 00538 SO 1996 9 12 96ZZZX4381 1 19960524 G 2720 TORQUE TUBE PIPER PA31T PA31T 7103124 SO RUDDER BAR BEARING DETACHED C L A O OTHER B SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 EA 25 809SW 31T8020082 SPARKS AROUND THE PILOT'S FEET WHEN HE WAS USING THE RUDDER PEDALS TO TURN THE ACFT FOR BACK-TRACKING DOWN THE RUNWAY TO EXIT POINT. REMOVED PILOT'S SEAT AND CARPET, FOUND RUDDER TORQUE TUBE BEARING ADRIFT FROM THE FLOOR LETTING THE RUDDER BAR ASSEMBLY LIFT AND SHORT OUT ONTO THE AVIONICS BUSS BAR. 1 L 7 2 3T A8EA 1996091200539 19960912 00539 EA 1996 9 12 96ZZZX4382 2 19960820 G 8530 CYLINDER CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA NR 2 CRACKED D C ABORTED TAKEOFF E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS TO TAKEOFF 1 NM 01 46758 15283101 L1612315 TAKEOFF ABORTED FOR LOSS OF POWER/ROUGH RUNNING ENGINE. POST-FLIGHT MAINTENANCE INSPECTION REVEALED 3 INCH HAIR LINE CR ACK RUNNING CIRCUMFERENTIALLY, BETWEEN NR 14 AND NR 15 FIN (COUNTING DOWN FROM TOP) OF NR 2 CYLINDER. SMALL BURN AREA O BSERVED ON NR 4 CYLINDER INTAKE PUSH ROD TUBE. REPLACED ENGINE. 1 H 7 1 3O 3 O NT 3A19 E223 1996091200540 19960912 00540 SO 1996 9 12 96ZZZX4383 2 19960801 G 8520 6436511 STUD PIPER PA28 PA28RT201T 7102817 SO CONT O360 TSIO360FB 17025 SO CYLINDER BASE STRETCH B P A YYBR K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 03 2847J 28R7931221 24809612 ENGINE WAS BEING REPAIRED FOR SEVERAL BROKEN CYLINDERS, BASE STUDS, AND LOOSE NUTS. MECHANIC RECEIVED 36 BRAND NEW STUD S FROM THREE DIFFERENT VENDORS IN TCM PACKAGING. UPON TORQUING TO THE REQUIRED MINIMUM TORQUE VALVE, A TOTAL OF 12 STRE TCHED. THEY WERE ALL REMOVED. TWO WERE SUBMITTED TO TCM FOR ANALYSIS. 1 L 7 1 3O 3 O 2A13 E9CE 1996091200542 19960912 00542 CE 1996 9 12 96ZZZX4385 1 19960806 G 3340 612008 POWER SUPPLY RKWELL NA265 NA26540 6402608 CE STROBE FAILED D K NONE O OTHER IN INSP/MAINT 1 SO 16 303NT 25 12381C 28229 STROBE POWER SUPPLY WAS INSTALLED IN THE AIRCRAFT, OPERATED FOR 25 HOURS, AND WAS REMOVED FOR INTERNAL FAILURE WITH NO P OWER OUTPUT. UNIT WAS OVERHAULED ON 10-18-95. RELIABILITY OF OVERHAULED UNITS FROM THIS REPAIR STATION HAS BEEN POOR. AIRCRAFT TT: 10,625.8 HRS. 2 L 7 2 4J A2WE 1996091200543 19960912 00543 1996 9 12 96ZZZX4386 4 19960817 G 3414 2014001210 INDICATOR AEROSONIC BEECH 200 B200 1152922 CE PILOT AIRSPEED GASKET FAILED C K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 11 44NL 209 W20644 BB1492 BEZEL GASKET ROLLED FROM SEAT ALLOWING PRESSURIZATION TO ENTER AIRSPEED INDICATOR. THIS CUASED LARGE ERROR IN AIRSPEED, ALTIMETER, AND V.S.I. DURING FLIGHT. UNIT HAD BEEN REPAIRED PRIOR TO FLIGHT. RECOMMEND A POST-ASSEMBLY INSPECTION TO DESIGN PRESSURE LIMITS TO DETECT SIGNS OF INTERNAL LEAKS. 1 L 7 2 4T A24CE 1996091200544 19960912 00544 EU 1996 9 12 96ZZZX4387 1 19960815 G 7830 2660042505 LONGERON ROHR 26600021M BRAERO 1000 BAE1251000 1500287 EU T/R DOOR CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 14 514QS 2854 CUM101001 NA1005 FOUND CRACK ON LEFT ENGINE THRUST REVERSER UPPER DOOR INBOARD LONGERON ASSEMBLY ABOUT TWO INCHES FROM BUMPER. LONGERON ASSY IS WEAK IN MACHINED AREA WHICH IS WHERE THE CRACK IS LOCATED. SUBMITTER STATED IF THE BUMPER IS MODIFIED TO EXTEND PAST THE WEAK AREA, THE PROBLEM WILL PROBABLY GO AWAY. 2 L 7 2 4F RT A3EU 1996091200546 19960912 00546 GL 1996 9 12 96ZZZX4389 1 19960806 G 7810 EXHAUST AMTR VECITY VELOCITY 05612DU GL CYLINDERS 1-3 BROKEN G S K NONE M OVER TEMP NR NOT REPORTED 1 SO 11 637KM DMO63 EXHAUST FROM NR 1 CYLINDER AND NR 3 CYLINDER BROKE OFF AT FLANGE CAUSING HIGH HEAT INSIDE COWL CAUSING IGNITION TO HEAT UP, OIL TEMPERATURE TO BE EXCESSIVELY HIGH, PLUS LOOSE EXHAUST ASSY JAMMED AILERON CONTROLS. ERRATIC EGT ALSO NOTED. 1 M 7 1 3O NT EXPA1M71 1996091200547 19960912 00547 CE 1996 9 12 96ZZZX4390 1 19960624 G 2434 30B10719A GENERATOR BENDIX LEAR 35 35A 5170602 CE RT ENGINE FAILED A A GQVR O OTHER E H VIBRATION/BUFFET ELECT. POWER LOSS-50 PC NR NOT REPORTED 1 SW 05 1AH 128 2319 398 THE AIRCRAFT EXPERIENCED VIBRATION THEN GENERAL FAILURE ON THE RIGHT SIDE. BEARING FAILURE WAS THE CAUSE OF THE PROBLEM S. THIS WAS THE SECOND TIME IN 130 FLIGHT HOURS SINCE GENERATOR OVERHAUL. 2 L 7 2 4F A10CE 1996091200548 19960912 00548 CE 1996 9 12 96ZZZX4391 1 19960722 G 2434 30B1077F GENERATOR BENDIX LEAR 35 36A 5170603 CE RT ENGINE FAILED A A GQVR K NONE E VIBRATION/BUFFET NR NOT REPORTED 1 SW 05 53JA 201 912 043 THE AIRCRAFT EXPERIENCED VIBRATIONS AND AMP FLUCTUATIONS. THE PROBLEM WAS ISOLATED TO THE RIGHT GENERATOR. GENERATOR R EMOVAL REVEALED BEARING FAILURE. THIS WAS THE SECOND FAILURE WITHIN 200 FLIGHT HOURS OF OVERHAUL. THE LEFT GENERATOR, S/N 2400, HAD THE IDENTICAL PROBLEM TWICE WITHIN 600 FLIGHT HOURS OF OVERHAUL. 2 L 7 2 4F A10CE 1996091200549 19960912 00549 CE 1996 9 12 96ZZZX4392 1 19960807 G 3240 BRAKE DISC BEECH 55 D55 1152730 CE RT MLG CHAFE SCISSORS B BVMR K NONE W INADEQUATE Q C IN INSP/MAINT 1 EA 07 25JK TE533 FOUND RIGHT BRAKE DISC RUBBING GEAR SCISSORS. SUSPECT DISC ORDERED UNDER WRONG SERIAL NUMBERED AIRCRAFT. BRAKE DISC OF FSET .1250 INCH FROM PROPER P/N 164-27 DISC. AXLE SPACER AND SHIMS NOT PROPERLY INSTALLED TO MAKE UP CLEARANCE. FOUND DURING ANNUAL INSPECTION. 1 L 7 2 3O 3A16 1996091200550 19960912 00550 CE 1996 9 12 96ZZZX4393 1 19960807 G 3040 RESERVOIR BEECH 55 D55 1152730 CE DE-ICE TANK AV GAS FILLED B A BVMR K NONE W INADEQUATE Q C IN INSP/MAINT 1 EA 07 25JK TE533 ANNUAL INSPECTION FOUND PROPELLER AND WINDSHIELD ALCOHOL RESERVOIRS FILLED WITH 100LL AV GAS. SUSPSECT TANK MISTAKEN FO R HEATER FUEL TANK. FIRE HAZARD IF SYSTEM USED WITH ENGINES RUNNING. TANK IS PROPERLY MARKED FOR DE-ICER FLUID. 1 L 7 2 3O 3A16 1996091200551 19960912 00551 1996 9 12 96ZZZX4394 4 19960124 G 3416 JEWEL ASSY UNITEDINST 5934 ALTIMETER MISSING D K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 01 N2035 INACCURATE READINGS PLUS OR MINUS 60 FEET CAUSED BY INCORRECT JEWEL ASSY MISSING A CAP JEWEL. THIS ALLOWED PIVOT SHOULD ER TO RIDE AGAINST JEWEL FACE. SUBMITTER STATED FROM THE LOOKS OF WORK DONE, IT INDICATES POOR WORKMANSHIP AND LACK OF TRAINING. RECOMMEND THAT ONLY QUALIFIED PERSONNEL WORK ON CRITICAL DEVICES. 1996091200553 19960912 00553 CE 1996 9 12 96ZZZX4396 1 19960731 G 5720 041332511 CHANNEL CESSNA 150 152 2071835 CE LT WING FWD SPAR CORRODED B LCPR K NONE O OTHER IN INSP/MAINT 1 SO 17 5521H 7966 15284111 WHEN LEFT DOORPOST TRIM WAS REMOVED FOR WINDSHIELD CHANGE, CORROSION WAS FOUND AT LEFT WING FORWARD SPAR CARRY-THROUGH A REA. WING WAS REMOVED. BRACE AND CHANNEL WERE REPLACED. 1 H 7 1 3O NT 3A19 1996091200554 19960912 00554 CE 1996 9 12 96ZZZX4397 1 19960731 G 5720 0411132 CHANNEL CESSNA 150 152 2071835 CE LT WG CARRY THRU CORRODED B LCPR K NONE O OTHER IN INSP/MAINT 1 SO 17 5521H 7966 15284111 WHEN LEFT DOORPOST TRIM WAS REMOVED FOR WINDSHIELD CHANGE, CORROSION WAS FOUND AT LEFT WING FORWARD SPAR CARRY-THROUGH A REA. WING WAS REMOVED. BRACE AND CHANNEL WERE REPLACED. 1 H 7 1 3O NT 3A19 1996091200555 19960912 00555 EA 1996 9 12 96ZZZX4398 2 19960722 G 7414 103493576 IMPULSE CAM 1038255511 CESSNA 177 177RG 2073709 CE LYC O360 IO360A1B 41514 EA MAGNETO WORN B K NONE O OTHER IN INSP/MAINT 1 SW 99 52073 426 177RG1161 L1696551A INSPECTED MAGNETO RIVETED CAM ASSY AND FOUND WORN BEYOND 'X' PLUS .014 INCH. SUBMITTER STATES THESE EARLY RIVETED UNITS SHOULD BE CHANGED OUT TO THE SNAP RING STYLE AT 500 HOURS. NEW STYLE FOR THIS APPLICATION IS 10-400167-9. 1 H 7 1 3O 3 O A20CE 1E10 1996091200556 19960912 00556 SO 1996 9 12 96ZZZX4399 2 19960725 G 8530 625393 SPRING RETAINER BEECH 58 58P 1152744 CE CONT O520 TSIO520U 17040 SO EXH VALVE NR 3 FAILED B QL5R K NONE O OTHER IN INSP/MAINT 1 NM 05 112Z 1336 TJ371 274153R WHILE CHANGING VALVE COVER GASKET ON NR 3 CYLINDER, MECHANIC FOUND TWO SMALL PIECES OF METAL IN VALVE COVER. INVESTIGAT ED AND DETERMINED PIECES CAME FROM THE EXHAUST VALVE INNER VALVE SPRING RETAINER TCM. PERFORMED HIDDEN DAMAGE INSPECTIO N. INSPECTED AND CHECKED OK. INSTALLED NEW SPRING RETAINER. ENGINE IS A TCM FACTORY REMANUFACTURED WITH 1,336 HOURS T SMOH. 1 L 7 2 3O 3 O A23CE E8CE 1996091200557 19960912 00557 EU 1996 9 12 96ZZZX4400 2 19960627 G 8530 PISTON AMTR 500 MINI500 13015HW GL ROTAX 582 ROTAX582 55555 EU SKIRT UNDERSIZE F L A K NONE R PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 CE 05 500ZZ 0000 4655214 THE ENGINE BACKFIRED AND MOMENTARILY HAD A LOSS OF POWER. THE PISTONS WERE FOUND UNDERSIZED AT THE SKIRT END. THIS COU LD HAVE POSSIBLY BEEN CAUSED BY IMPROPER BREAK IN PROCEDURES. 1 G 7 1 3I 3 I NC EXPA1G71 EXPE3I 1996091200558 19960912 00558 EA 1996 9 12 96ZZZX4401 2 19960807 G 7414 1038255514 MAGNETO BEECH 76 76 1153005 CE LYC O360 IO360A1G6 41514 EA RT ENGINE SEPARATED D O OTHER Y ENGINE STOPPAGE TO TAKEOFF 1 WP 27 66291 ME224 MAGNETO SEPARATED FROM ENGINE ON TAKEOFF CAUSING ENGINE TO STOP. THIS IS A DUAL MAGNETO ON A SINGLE DRIVE. IT WAS DETE RMINED THE NUTS HAD LOOSENED AND ALLOWED MAG TO COME OFF. THERE IS NO TORQUE LISTED FOR THIS MAGNETO EXCEPT STANDARD TO RQUE. RECOMMEND THAT MAGNETO ATTACHMENTS BE CHECKED AT 50-HOUR INTERVALS. ALSO, MAG NEEDS TO BE CHECKED FOR NEW STYLE HOLD-DOWN BRACKETS. TIME SINCE LAST CHECK OF HOLD-DOWN NUTS WAS APPROXIMATELY 80 HOURS. 1 L 7 2 3O 3 O A29CE 1E10 1996091200559 19960912 00559 EA 1996 9 12 96ZZZX4402 2 19960729 G 8520 CRANKSHAFT BOEING 75 A75N1 1380134 CE WRIGHT R975 R975* 67012 EA HUB SOCKET SCREWS FAILED D A UNSCHED LANDING Y ENGINE STOPPAGE CL CLIMB 1 WP 27 68251 700 757976 78224 AFTER TAKEOFF, ENGINE STOPPED. AIRCRAFT CRASH LANDED IN A FIELD. AIRCRAFT DESTROYED BY POST-FIRE. INVESTIGATION FOUND CRANKSHAFT GEAR ASSEMBLY HUB SOCKET SCREWS SHEARED. P/N 401337. TSO: 700 HOURS. TT: UNKNOWN. 1 Q 7 1 3R 3 R A743 ATC21 1996091200560 19960912 00560 EA 1996 9 12 96ZZZX4403 2 19960801 G 8550 68759 LINE CESSNA 182 R182 2072734 CE LYC O540 O540J3C5 41532 EA NR 1 CYL OIL CHAFED D K NONE O OTHER IN INSP/MAINT 1 NE 05 738WK R18200969 L2099840A WHILE TROUBLESHOOTING AN ALTERNATOR PROBLEM, FOUND THE OIL RETURN LINE ON NR 1 CYLINDER HAD ALTERNATOR WIRE HARNESS TY-W RAP TO IT. REMOVED TY-WRAP TO INSPECT THE WIRE HARNESS, AND THE LINE WAS FOUND CHAFED MORE THAN 75 PERCENT THROUGH THE WALL THICKNESS. SUBMITTER STATED TY-WRAPPING WIRES DIRECTLY TO THESE ALUMINUM LINES IS COMMON, BUT SHOULD HAVE SOME KIN D OF PROTECTION FROM CHAFING. 1 H 7 1 3O 3 O RT 3A13 E295 1996091200561 19960912 00561 CE 1996 9 12 96ZZZX4404 1 19960809 G 5712 95110014191 RIB BEECH 60 B60 1153605 CE LT-RT WS 64 CRACKED D K NONE O OTHER IN INSP/MAINT 1 NE 05 75RL P390 WHILE PERFORMING ANNUAL INSPECTION, THE WING TRAILING EDGE RIBS AND ATTACHING CLIPS AT STA'S 64, 74, AND 89 WERE FOUND C RACKED ON LEFT AND RIGHT WINGS. SUBMITTER STATED IT APPEARED DURING REMOVAL THE RIBS WERE STRESSED TO OBTAIN PROPER ALI GNMENT. THIS AREA IS DIFFICULT TO SEE WITH FLAPS INSTALLED, BUT NOT IMPOSSIBLE. MOST CRACKS WERE AT THE NOTCH-OUT AREA FOR THE SKIN STIFFENER. 1 L 7 2 3O A12CE 1996091200562 19960912 00562 CE 1996 9 12 96ZZZX4405 1 19960809 G 5712 95110014129 RIB BEECH 60 B60 1153605 CE LT-RT WS 74 CRACKED D K NONE O OTHER IN INSP/MAINT 1 NE 05 75RL P390 WHILE PERFORMING ANNUAL INSPECTION, THE WING TRAILING EDGE RIBS AND ATTACHING CLIPS AT STA'S 64, 74, AND 89 WERE FOUND C RACKED ON LEFT AND RIGHT WINGS. SUBMITTER STATED IT APPEARED DURING REMOVAL THE RIBS WERE STRESSED TO OBTAIN PROPER ALI GNMENT. THIS AREA IS DIFFICULT TO SEE WITH FLAPS INSTALLED, BUT NOT IMPOSSIBLE. MOST CRACKS WERE AT THE NOTCH-OUT AREA FOR THE SKIN STIFFENER. 1 L 7 2 3O A12CE 1996091200563 19960912 00563 CE 1996 9 12 96ZZZX4406 1 19960809 G 5712 95110014153 RIB BEECH 60 B60 1153605 CE LT-RT WS 89 CRACKED D K NONE O OTHER IN INSP/MAINT 1 NE 05 75RL P390 WHILE PERFORMING ANNUAL INSPECTION, THE WING TRAILING EDGE RIBS AND ATTACHING CLIPS AT STA'S 64, 74, AND 89 WERE FOUND C RACKED ON LEFT AND RIGHT WINGS. SUBMITTER STATED IT APPEARED DURING REMOVAL THE RIBS WERE STRESSED TO OBTAIN PROPER ALI GNMENT. THIS AREA IS DIFFICULT TO SEE WITH FLAPS INSTALLED, BUT NOT IMPOSSIBLE. MOST CRACKS WERE AT THE NOTCH-OUT AREA FOR THE SKIN STIFFENER. 1 L 7 2 3O A12CE 1996091200564 19960912 00564 CE 1996 9 12 96ZZZX4407 1 19960805 G 2752 C3010020103 MOTOR CESSNA 150 150L 2071826 CE CONT O200 O200A 17020 SO FLAP SHORTED D K NONE O OTHER NR NOT REPORTED 1 EA 07 7513G 4089 15074679 242709R FLAPS EXCEEDED THE LIMIT SWITCH, STOPS, AND BROKE THE DOWN-LIMIT SWITCH AND FUSE BLEW. PROBLEM WAS CAUSED BY FLAP MOTOR DEVELOPED AN INTERNAL SHORT WHICH PROVIDED THE GROUND NORMALLY WHICH IS PROVIDED THROUGH THE LIMIT SWITCH CIRCUIT. THI S MOTOR IS A REVERSING 12V DC MOTOR WHICH CHANGES POWER AND GROUND CIRCUIT THROUGH THE SWITCH AND LIMIT SWITCHES NORMALL Y. NO LOG ENTRY SHOWS MOTOR CHANGED PREVIOUSLY. 1 H 7 1 3O 3 O 3A19 E252 1996091200565 19960912 00565 SO 1996 9 12 96ZZZX4408 2 19960625 G 8550 CH48109 FILTER CHAMPION PIPER PA46 PA46310P 7104605 SO CONT O520 TSIO520BE 17040 SO ENGINE OIL BROKEN B JAVR K NONE W INADEQUATE Q C IN INSP/MAINT 1 NE 01 94MA 23 F11E111 468608056 273793R AFTER CUTTING OIL FILTER OPEN, THE MANUFACTURER'S ANTI-DRAIN BACK VALVE ROLLED EDGE WAS FOUND CRACKED APPROXIMATELY ONE- HALF WAY AROUND AND A PIECE, APPROXIMATELY 1 INCH LONG, HAD BROKEN OFF. BROKEN PIECES WERE FOUND AFTER OIL COOLER WAS R EMOVED AND BACK-FLUSHED. 1 L 7 1 3O 3 O A25SO E8CE 1996091200566 19960912 00566 CE 1996 9 12 96ZZZX4409 1 19960613 G 3211 05411212 SUPPORT CESSNA 172 172G 2072420 CE MLG OTBD RT CRACKED D K NONE O OTHER IN INSP/MAINT 1 GL 09 173DA 4500 17253664 WHILE CHANGING A BROKEN U-BOLT, NOTICED POSSIBLE CRACK ON MLG OUTBOARD SUPPORT AT FORWARD HOLE WHERE U-BOLT ATTACHES. C RACK CONFIRMED BY NDT. SUSPECT CAUSE WAS BROKEN U-BOLT CONCENTRATING STRESSES AT FORWARD HOLE. 1 H 7 1 3O NT 3A12 1996091200567 19960912 00567 CE 1996 9 12 96ZZZX4410 1 19960613 G 3211 0541153 U-BOLT CESSNA 172 172G 2072420 CE RT MLG BROKEN D K NONE O OTHER IN INSP/MAINT 1 GL 09 173DA 4500 17253664 DURING 100-HOUR INSPECTION, FOUND RIGHT MLG U-BOLT BROKEN. UPON INSPECTION OF BOLT, SUBMITTER STATED IT APPEARS A CRACK HAD BEEN EVIDENT AND HAD FINALLY FAILED POSSIBLY DUE TO A HARD LANDING. 1 H 7 1 3O NT 3A12 1996091200568 19960912 00568 CE 1996 9 12 96ZZZX4411 1 19960713 G 7160 HEAT VALVE CESSNA 150 150L 2071826 CE CARBURETOR INLET LOOSE B A PN9R K NONE R PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 GL 13 18071 15073773 ENGINE WAS NOT DEVELOPING POWER. UPON INSPECTION, FOUND THE CARBURETOR HEAT DOOR HAD BECOME LOOSE ON THE SHAFT GIVING N O CONTROL TO THE CARBURETOR HEAT. SUBMITTER STATED THIS WAS CAUSED BY CORROSION UNDER THE WELD THAT ATTACHES THE DOOR T O THE SHAFT. TO PREVENT THIS, THE DOOR SHOULD BE RIVETED TO THE SHAFT. 1 H 7 1 3O 3A19 1996091200569 19960912 00569 SO 1996 9 12 96ZZZX4412 1 19960813 G 2810 FUEL CAP PIPER PA38 PA38112 7103812 SO LT WING WATER LEAK G L A A UNSCHED LANDING Y ENGINE STOPPAGE CL CLIMB 1 CE 05 2466D 3879A0324 WATER IN LEFT WING FUEL TANK RESULTED IN AN EMERGENCY LANDING WITH THE LEFT WING TIP RECEIVING MINOR DAMAGE. SUSPECT DUE TO FUEL CAP NOT PROPERLY INSTALLED. 1 L 7 1 3O A18SO 1996091200570 19960912 00570 SO 1996 9 12 96ZZZX4413 1 19960802 G 5280 4205907 HINGE PIPER PA31T PA31T 7103124 SO RT OTBD GR DOOR FAILED B AU3R K NONE O OTHER IN INSP/MAINT 1 WP 15 6080A 2275 31T7820077 PILOT REPORTED FINDING OUTBOARD GEAR DOOD HINGE FAILED DURING PRE-FLIGHT. IT IS ASSUMED HINGE FAILED ON LAST FLIGHT. F AILED AREA SHOWED SIGNS OF BEING CRACKED PREVIOUSLY. OTHER 3 REMAINING HINGES INSPECTED, NO DEFECTS NOTED. 1 L 7 2 3T A8EA 1996091200571 19960912 00571 SW 1996 9 12 96ZZZX4414 1 19960802 G 2436 800331721 ADAPTER ELECTRODELTA VR415F MOONEY M20 M20C 5870208 SW DC SYSTEM MISINSTALLED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 EA 07 6980V 201195 QEM REGULATOR, P/N 20082, WAS NOT AVAILABLE SO A ELECTRODELTA REGULATOR, P/N VR415F, THAT HAS A DIFFERENT CONNECTOR WAS INSTALLED WITH ADAPTER CABLE, P/N 800331-721. THE QEM REGULATOR INTERNAL GROUND ORIGINALLY ATTACHED TO SHELL OF ALUMINU M MS TYPE CANNON PLUG, ADAPTER ELIMINATES GROUND PATH. AFTER INSTALLATION, MS PORTION OF PLUG WAS LAYING AGAINST REGULA TOR MAKING HIGH RESISTANCE CONTACT CAUSING ERRATIC OPERATION OF CHARGING SYSTEM. RE-LOCATING GROUND CORRECTED CONDITION . MANUFACTURER OF REGULATOR SHOULD CAUTION ABOUT THIS. 1 L 7 1 3O 2A3 1996091200572 19960912 00572 SO 1996 9 12 96ZZZX4415 2 19960117 G 8530 538283 CYLINDER CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO CYLS 1,3,4, EXH CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 99 1321G 310R0701 565272 FOUND SMALL CRACKS LEADING FROM SPARK PLUG HOLES AROUND TO THE EXHAUST PORTS ON NR 1, NR 3, AND NR 4 CYLINDERS. A BRIGH T FLASHLIGHT AND MAGNIFING GLASS WERE USED TO FIND THE CRACKS DURING A 100-HOUR INSPECTION. DYE CHECK WOULD NOT PICK UP ONE CRACK. 1 L 7 2 3O 3 O 3A10 E5CE 1996091200574 19960912 00574 CE 1996 9 12 96ZZZX4417 1 19960717 G 3242 16432505 DISC PARKERHANFIN BEECH 36 A36 1151604 CE RT BRAKE FAILED D S K NONE O OTHER NR NOT REPORTED 1 SW 03 21VR 1755 E2468 DISC TORN OFF WHEEL LEAVING METAL UNDER BOLTS INTACT ON WHEEL. THIS IS THE SECOND DISC TO FAIL ON THIS AIRCRAFT. ON 12 -26-95, THE LEFT BRAKE DISC FAILED UNDER SIMILAR CONDITIONS (1,617 TIS). SUBMITTER STATED COULD BE CAUSED BY IMPROPER A LLOY CASTINGS OR BY CRACKS AROUND BOLT HOLE. 1 L 7 1 3O 3A15 1996091200575 19960912 00575 SO 1996 9 12 96ZZZX4418 1 19960312 G 2810 461722 CELL PIPER PA31T PA31T2 7103127 SO LT INBOARD LEAKING B ESMR K NONE K FLUID LOSS IN INSP/MAINT 1 SO 11 2501Y 74231 31T8166013 LEFT INBOARD FUEL CELL LEAKING AT PUMP MOUNTING PAD. 3-12-96- REMOVED. 1 L 7 2 3T RT A8EA 1996091200576 19960912 00576 SO 1996 9 12 96ZZZX4419 1 19960313 G 2810 527784 FUEL CELL PIPER PA31T PA31T2 7103127 SO PUMP PAD MOUNT SEPARATED B ESMR K NONE O OTHER IN INSP/MAINT 1 SO 11 2501Y 7616399 31T8166013 AFT FUEL PUMP MOUNTING PAD SEPARATED FROM FUEL CELL, LOWER LEFT CORNER. 3-13-96 INSTALLED. 1 L 7 2 3T RT A8EA 1996091200578 19960912 00578 SO 1996 9 12 96ZZZX4421 2 19960616 G 7314 LW15473 PUMP MOONEY M20 M20J 5870219 SW CONT O360 IO360A 17025 SO ENGINE FUEL FAILED D A A UNSCHED LANDING Y ENGINE STOPPAGE NR NOT REPORTED 1 SO 09 5774J 98 154739510 241509 L223909 AIRCRAFT FORCED LANDING DUE TO FUEL STARVATION TO ENGINE. INVESTIGATION REVEALED THAT NO FUEL COULD BE PUMPED THROUGH T HE ENGINE DRIVEN PUMP. APPEARED TO BE BLOCKED INTERNALLY. NO OTHER DEFECTS WERE FOUND IN THE FUEL SYSTEM. ALL SCREENS WERE FOUND TO BE CLEAN. BOOST PUMP OPERATION OK AS WELL. 1 L 7 1 3O 3 O 2A3 E1CE 1996091200579 19960912 00579 CE 1996 9 12 96ZZZX4422 1 19960816 G 2510 HARNESS CESSNA 188 T188C 2073012 CE PILOT FAILED G A K NONE O OTHER NR NOT REPORTED 1 GL 15 2081J T18803371T PILOT'S SHOULDER HARNESS WEBBING BROKE. WAS NOTED DURING ACCIDENT INVESTIGATION. SUBMITTER STATED COULD BE A RESULT OF FORCES DURING IMPACT. WEBBING MAY HAVE BEEN 'SUN' DETERIORATED. 1 L 7 1 3O A9CE 1996091200580 19960912 00580 GL 1996 9 12 96ZZZX4423 1 19960716 G 7603 2076000113 CONTROL CABLE DIAMON DA20A1 DA20A1 05626UX GL THROTTLE WIRE BROKEN B TV3R K NONE O OTHER IN INSP/MAINT 1 WP 15 614P 1203 10014 THROTTLE CONTROL PIANO WIRE BROKE WHERE HOUSING PASSES THROUGH FIREWALL. WIRE APPEARS TO BE WORK HARDENED AND BRITTLE. HOUSING TAKES HARD BEND AFTER PASSING THROUGH FIREWALL. 1 L 7 1 3O NT TA4CH 1996091200582 19960912 00582 SO 1996 9 12 96ZZZX4425 2 19960801 G 7414 10400309 IMPULSE COUPLER BEECH 95 95B55 1152729 CE CONT O470 IO470L 17026 SO ENGINE MAG CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 99 255EM TC1552 WHILE C/W AD 78-09-07R3, AN IMPULSE COUPLER WAS FOUND TO NEED REPLACEMENT. A NEW PART WAS INSTALLED ON MAG. WHILE TIGH TENING NUT ON COUPLER TO 240 INCH/POUNDS, THE COUPLER CRACKED WHERE IT SLIDES ON THE TAPERED SHAFT. SUBMITTER FOUND THA T IMPULSE COUPLERS THAT ARE CHECKED ARE ONLY LASTING FOR ONE CYCLE (500 HOURS) OF AD INSPECTION, WHERE IN THE PAST, AN I MPULSE COUPLER WOULD OFTEN LAST FOR 1,000 HOURS OR MORE. SUBMITTER SUSPECTS THE MATERIAL USED FOR NEW UNITS IS NOT AS G OOD A MATERIAL AS WAS USED IN THE PAST. 1 L 7 2 3O 3 O RT 3A16 3E1 1996091200583 19960912 00583 1996 9 12 96ZZZX4426 1 19960410 G 3320 BC10047005 LAMP HOLDER BRUCE CABIN LIGHTS BROKEN B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE. REPORTED OPERATOR: SKYWEST. 1996091200584 19960912 00584 1996 9 12 96ZZZX4427 1 19960419 G 3320 BC10047005 LAMP HOLDER BRUCE CABIN LIGHTS BURNT B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE. REPORTED OPERATOR: WESTAIR. 1996091200585 19960912 00585 1996 9 12 96ZZZX4428 1 19960419 G 3320 BC10047005 LAMP HOLDER BRUCE CABIN LIGHTS BROKEN B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE. REPORTED OPERATOR: WESTAIR. 1996091200586 19960912 00586 1996 9 12 96ZZZX4429 1 19960426 G 3320 BC10047005 LAMP HOLDER BRUCE CABIN LIGHTS BURNT B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE. REPORTED OPERATOR: SKYWEST. 1996091200587 19960912 00587 1996 9 12 96ZZZX4430 1 19960507 G 3320 BC10047005 LAMP HOLDER BRUCE CABIN LIGHTS BURNT B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE. REPORTED OPERATOR: SKYWEST. 1996091200588 19960912 00588 1996 9 12 96ZZZX4431 1 19960509 G 3320 BC10047005 LAMP HOLDER BRUCE CABIN LIGHTS BROKEN B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE. REPORTED OPERATOR: SKYWEST. 1996091200589 19960912 00589 1996 9 12 96ZZZX4432 1 19960501 G 3320 BC10047005 LAMP HOLDER BRUCE CABIN LIGHTS BROKEN B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE. REPORTED OPERATOR: SKYWEST. SIX UNITS FAIL ED OR WERE DEFECTIVE. 1996091200590 19960912 00590 1996 9 12 96ZZZX4433 1 19960509 G 3320 BC10047005 LAMP HOLDER BRUCE CABIN LIGHTS BROKEN B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE. REPORTED OPERATOR: WESTAIR. 1996091200591 19960912 00591 1996 9 12 96ZZZX4434 1 19960514 G 3320 BC10047005 LAMP HOLDER BRUCE CABIN LIGHTS BROKEN B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE. REPORTED OPERATOR: SKYWEST. 1996091200592 19960912 00592 1996 9 12 96ZZZX4435 1 19960514 G 3320 BC10047005 LAMP HOLDER BRUCE CABIN LIGHTS BROKEN B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE. REPORTED OPERATOR: SKYWEST. 1996091200593 19960912 00593 1996 9 12 96ZZZX4436 1 19960419 G 3320 BC10047005 LAMP HOLDER BRUCE CABIN LIGHTS BROKEN B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE. REPORTED OPERATOR: WESTAIR. 1996091200594 19960912 00594 1996 9 12 96ZZZX4437 1 19960520 G 3320 BC10047005 LAMP HOLDER BRUCE CABIN LIGHTS BURNT B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE. REPORTED OPERATOR: WESTAIR. 1996091200595 19960912 00595 1996 9 12 96ZZZX4438 1 19960528 G 3320 BC10047005 LAMP HOLDER BRUCE CABIN LIGHTS BROKEN B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE. REPORTED OPERATOR: DELTA. 1996091200596 19960912 00596 1996 9 12 96ZZZX4439 1 19960612 G 3320 BC10047005 LAMP HOLDER BRUCE CABIN LIGHTS BURNT B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE. REPORTED OPERATOR: SKYWEST. 1996091200597 19960912 00597 1996 9 12 96ZZZX4440 1 19960620 G 3320 BC10047005 LAMP HOLDER BRUCE CABIN LIGHTS BROKEN B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE. REPORTED OPERATOR: SKYWEST. 1996091200598 19960912 00598 1996 9 12 96ZZZX4441 1 19960621 G 3320 BC10047005 LAMP HOLDER BRUCE CABIN LIGHTS BROKEN B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE. REPORTED OPERATOR: WESTAIR. 1996091200599 19960912 00599 1996 9 12 96ZZZX4442 1 19960514 G 3320 BR6303102 LAMP HOLDER BRUCE CABIN LIGHTS INOPERATIVE B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE. REPORTED OPERATOR: PIEDMONT. 1996091200600 19960912 00600 1996 9 12 96ZZZX4443 1 19960620 G 3320 BR6303102 LAMP HOLDER BRUCE CABIN LIGHTS BURNT B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE. REPORTED OPERATOR: PIEDMONT. 1996091200601 19960912 00601 1996 9 12 96ZZZX4444 1 19960620 G 3320 BR6303102 LAMP HOLDER BRUCE CABIN LIGHTS BUTTON MISSING B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE. REPORTED OPERATOR: PIEDMONT. 1996091200602 19960912 00602 1996 9 12 96ZZZX4445 1 19960507 G 3320 BR63031021 LAMP HOLDER BRUCE CABIN LIGHTS INOPERATIVE B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE. REPORTED OPERATOR: PANOR. 1996091200603 19960912 00603 1996 9 12 96ZZZX4446 1 19960507 G 3320 BR63031021 LAMP HOLDER BRUCE CABIN LIGHTS INOPERATIVE B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE. REPORTED OPERATOR: PANOR. 1996091200604 19960912 00604 1996 9 12 96ZZZX4447 1 19960507 G 3320 BR63031021 LAMP HOLDER BRUCE CABIN LIGHTS INOPERATIVE B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE. REPORTED OPERATOR: PANOR. 1996091200605 19960912 00605 1996 9 12 96ZZZX4448 1 19960509 G 3320 BR63031021 LAMP HOLDER BRUCE CABIN LIGHTS INOPERATIVE B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE. REPORTED OPERATOR: PIEDMONT. 1996091200606 19960912 00606 1996 9 12 96ZZZX4449 1 19960514 G 3320 BR63031021 LAMP HOLDER BRUCE CABIN LIGHTS BURNT B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE. REPORTED OPERATOR: PIEDMONT. 1996091200607 19960912 00607 1996 9 12 96ZZZX4450 1 19960507 G 3320 BR63031021 LAMP HOLDER BRUCE CABIN LIGHTS INOPERATIVE B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE. REPORTED OPERATOR: PANOR. 1996091200608 19960912 00608 1996 9 12 96ZZZX4451 1 19960426 G 3320 BR63031023 LAMP HOLDER BRUCE CABIN LIGHTS INOPERATIVE B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE. REPORTED OPERATOR: PIEDMONT. 1996091200609 19960912 00609 1996 9 12 96ZZZX4452 1 19960628 G 3320 BR63031023 LAMP HOLDER BRUCE CABIN LIGHTS INOPERATIVE B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE. REPORTED OPERATOR: PIEDMONT. 1996091200610 19960912 00610 1996 9 12 96ZZZX4453 1 19960509 G 3320 BR63031023 LAMP HOLDER BRUCE CABIN LIGHTS INOPERATIVE B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE. REPORTED OPERATOR: PIEDMONT. 1996091200611 19960912 00611 1996 9 12 96ZZZX4454 1 19960509 G 3320 BR63031023 LAMP HOLDER BRUCE CABIN LIGHTS INOPERATIVE B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE. REPORTED OPERATOR: PIEDMONT. 1996091200612 19960912 00612 1996 9 12 96ZZZX4455 1 19960617 G 3320 BR63031023 LAMP HOLDER BRUCE CABIN LIGHTS WILL NOT LOCK B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE. REPORTED OPERATOR: PIEDMONT. 1996091200727 19960912 00727 1996 9 12 96ZZZX4471 1 19960104 G 3320 BC10047005 LAMP HOLDER BRUCE CABIN LIGHTS BROKEN B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: SKYWEST. 1996091200728 19960912 00728 1996 9 12 96ZZZX4472 1 19960112 G 3320 BC10047005 LAMP HOLDER BRUCE CABIN LIGHTS BROKEN B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: SKYWEST. 1996091200729 19960912 00729 1996 9 12 96ZZZX4473 1 19960111 G 3320 BC10047005 LAMP HOLDER BRUCE CABIN LIGHTS BROKEN B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: SKYWEST. 1996091200730 19960912 00730 1996 9 12 96ZZZX4474 1 19960123 G 3320 BC10047005 LAMP HOLDER BRUCE CABIN LIGHTS BURNT B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: WESTAIR. 1996091200731 19960912 00731 1996 9 12 96ZZZX4475 1 19960123 G 3320 BC10047005 LAMP HOLDER BRUCE CABIN LIGHTS BROKEN B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: SKYWEST. 1996091200732 19960912 00732 1996 9 12 96ZZZX4476 1 19960126 G 3320 BC10047005 LAMP HOLDER BRUCE CABIN LIGHTS BROKEN B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: SKYWEST. 1996091200733 19960912 00733 1996 9 12 96ZZZX4477 1 19960201 G 3320 BC10047005 LAMP HOLDER BRUCE CABIN LIGHTS BROKEN B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: SKYWEST. 1996091200734 19960912 00734 1996 9 12 96ZZZX4478 1 19960207 G 3320 BC10047005 LAMP HOLDER BRUCE CABIN LIGHTS BROKEN B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: SKYWEST. 1996091200735 19960912 00735 1996 9 12 96ZZZX4479 1 19960207 G 3320 BC10047005 LAMP HOLDER BRUCE CABIN LIGHTS DEFECTIVE B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: SKYWEST. 1996091200736 19960912 00736 1996 9 12 96ZZZX4480 1 19960215 G 3320 BC10047005 LAMP HOLDER BRUCE CABIN LIGHTS BROKEN B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: SKYWEST. 1996091200737 19960912 00737 1996 9 12 96ZZZX4481 1 19960318 G 3320 BC10047005 LAMP HOLDER BRUCE CABIN LIGHTS BROKEN B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: SKYWEST. 1996091200738 19960912 00738 1996 9 12 96ZZZX4482 1 19960315 G 3320 BC10047005 LAMP HOLDER BRUCE CABIN LIGHTS BURNT B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: SKYWEST. 1996091200739 19960912 00739 1996 9 12 96ZZZX4483 1 19960102 G 3320 BR63031021 LAMP HOLDER BRUCE CABIN LIGHTS INOPERATIVE B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: AGES GROUP. 1996091200740 19960912 00740 1996 9 12 96ZZZX4484 1 19960103 G 3320 BR63031021 LAMP HOLDER BRUCE CABIN LIGHTS INOPERATIVE B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT. 1996091200741 19960912 00741 1996 9 12 96ZZZX4485 1 19960103 G 3320 BR63031021 LAMP HOLDER BRUCE CABIN LIGHTS INOPERATIVE B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT. 1996091200742 19960912 00742 1996 9 12 96ZZZX4486 1 19960122 G 3320 BR63031021 LAMP TAB BRUCE CABIN LIGHTS MISSING B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT. 1996091200743 19960912 00743 1996 9 12 96ZZZX4487 1 19960122 G 3320 BR63031021 LAMP TAB BRUCE CABIN LIGHTS MISSING B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT. 1996091200744 19960912 00744 1996 9 12 96ZZZX4488 1 19960201 G 3320 BR63031021 LAMP HOLDER BRUCE CABIN LIGHTS INOPERATIVE B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: AGES GROUP. 1996091200745 19960912 00745 1996 9 12 96ZZZX4489 1 19960212 G 3320 BR63031021 LAMP HOLDER BRUCE CABIN LIGHTS BURNT B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT. 1996091200746 19960912 00746 1996 9 12 96ZZZX4490 1 19960213 G 3320 BR63031021 LAMP HOLDER BRUCE CABIN LIGHTS BROKEN B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT. 1996091200747 19960912 00747 1996 9 12 96ZZZX4491 1 19960214 G 3320 BR63031021 LAMP HOLDER BRUCE CABIN LIGHTS DEFECTIVE B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT. 1996091200748 19960912 00748 1996 9 12 96ZZZX4492 1 19960223 G 3320 BR6303102 LAMP HOLDER BRUCE CABIN LIGHTS BROKEN B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT. 1996091200749 19960912 00749 1996 9 12 96ZZZX4493 1 19960223 G 3320 BR63031021 LAMP HOLDER BRUCE CABIN LIGHTS BURNT B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT. 1996091200750 19960912 00750 1996 9 12 96ZZZX4494 1 19960311 G 3320 BR63031021 LAMP HOLDER BRUCE CABIN LIGHTS DEFECTIVE B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT. 1996091200751 19960912 00751 1996 9 12 96ZZZX4495 1 19960313 G 3320 BR63031021 LAMP HOLDER BRUCE CABIN LIGHTS DEFECTIVE B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: AGES GROUP. 1996091200752 19960912 00752 1996 9 12 96ZZZX4496 1 19960313 G 3320 BR63031021 LAMP HOLDER BRUCE CABIN LIGHTS DEFECTIVE B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: AGES GROUP. 1996091200753 19960912 00753 1996 9 12 96ZZZX4497 1 19960313 G 3320 BR63031021 LAMP HOLDER BRUCE CABIN LIGHTS DEFECTIVE B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: AGES GROUP. 1996091200754 19960912 00754 1996 9 12 96ZZZX4498 1 19960318 G 3320 BR63031021 LAMP HOLDER BRUCE CABIN LIGHTS BROKEN B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT. 1996091200755 19960912 00755 1996 9 12 96ZZZX4499 1 19960318 G 3320 BR63031021 LAMP HOLDER BRUCE CABIN LIGHTS BROKEN B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT. 1996091200807 19960912 00807 1996 9 12 96ZZZX4551 1 19960222 G 3320 BR63031021 LAMP HOLDER BRUCE CABIN LIGHTS BURNT B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE OR FAILURE. REPORTED OPERATOR: PIEDMONT. 1996091900236 19960919 00236 WP 1996 9 19 96ZZZX4607 1 19960730 G 3246 2601483 BOLT 2608871 DOUG DC9 DC9* WP WHEEL FAILED B LU5R K NONE O OTHER IN INSP/MAINT 1 GL 17 FATIGUE RELATED FAILURE OF MD80 WHEEL TIE BOLTS. INSUFFICIENT TIE BOLT PRELOAD TORQUE. SUBMITTER SUGGESTS PREVENTIVE A CTION, USE SNUG ANGLE TORQUE METHOD. 2 L 7 2 4F A6WE 1996091900238 19960919 00238 NM 1996 9 19 96ZZZX4609 1 19960719 G 2761 654494711 HOUSING 65448517 BOEING 737 737300 1384610 NM SPOILER CRACKED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 4475 HOUSING IS CRACKED IN THE BEARING RECESS AREA EXTENDING LATERALLY FROM THE RETRACT PRESSURE PORT. THIS MAY BE CAUSED BY A LACK OF PISTON SNUBBING ACTION DURING GROUND NO-LOAD CONDITIONS. SUBMITTER RECOMMENDS A RE-DESIGN OF THE HOUSING ASS EMBLY BY STRENGTHENING THE BEARING RECESS AREA AND RESTRICTING SPOILER MOVEMENT DURING NO-LOAD GROUND OPERATIONS. 2 L 7 2 4F RT A16WE 1996091900239 19960919 00239 NM 1996 9 19 96ZZZX4610 1 19960719 G 2782 69358861 RESTRICTOR PLUG 65446517 BOEING 737 737* NM LE SLAT ACTUATOR DEBRIS PLUGGED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 448 RETRICTOR PLUGS (8) WERE PLUGGED UP WITH DEBRIS. 2 L 7 2 4F RT A16WE 1996091900240 19960919 00240 NM 1996 9 19 96ZZZX4611 1 19960719 G 2782 71001291 ACTUATOR BOEING 727 727 1384001 NM TRUNNION CRACKED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 0043 SLAT ACTUATOR CRACKED INSIDE TRUNNION. SUBMITTER RECOMMENDS MANUFACTURING PROCESS TO SMOOTH OUT SHARP EDGES OF PORT. 2 L 7 3 4F A3WE 1996020200275 19960202 00275 SW 1996 2 2 96ZZZX462 1 19960109 G 7160 600118015 DOOR MOONEY M20 M20J 5870219 SW ALT AIR DOOR WORN D K NONE O OTHER IN INSP/MAINT 1 GL 03 4566H 2626 240848 DURING C/W AD 95-26-16, RIVETS HOLDING NUTPLATE TO ALTERNATE AIR DOOR WERE FOUND LOOSE ALLOWING NUTPLATE TO WEAR THROUGH APPROXIMATELY ONE-HALF OF THICKNESS AT THE DOOR. MOONEY SB M20-250B AND SB M20-253A AND AD 95-26-16R1, ADDRESS THIS PR OBLEM. 1 L 7 1 3O 2A3 1996091900249 19960919 00249 1996 9 19 96ZZZX4620 1 19960801 G 2822 1B58 PUMP AIRBORNE ARMATURE DAMAGED D K NONE O OTHER IN INSP/MAINT 1 GL 13 8M43 BOOST PUMP POSSIBLY WAS RUN DRY, CAUSING SEVERE DAMAGE TO ARMATURE. 1996091900251 19960919 00251 CE 1996 9 19 96ZZZX4622 1 19960803 G 2910 LINE CESSNA 206 206CESSNA 2073302 CE HYD PUMP CHAFE/LEAK D A O OTHER K FLUID LOSS NR NOT REPORTED 1 SW 99 HYDRAULIC LINE CHAFED ON HYDRAULIC PUMP WITH LOSS OF FLUID. AIRCRAFT GEAR-UP LANDING WITH ONLY NOSE WHEEL EXTENDED. DA MAGE TO GEAR DOORS AND RIGHT HORIZONTAL STABILIZER. ALSO, AFT BULKHEAD DAMAGED. 1 H 7 1 3O A4CE 1996091900252 19960919 00252 SO 1996 9 19 96ZZZX4623 2 19960801 G 7322 39077 NEEDLE VALVE BENDIX NAS3A1 CESSNA 140 140 2071602 CE CONT C90 C9012F 17009 SO FLOAT CHAMBER SWELLED UP G C D ABORTED TAKEOFF RETURN TO BLOCK R PARTIAL RPM/PWR LOSS TO TAKEOFF 1 NM 06 CARBURETOR FLOAT CHAMBER NEEDLE VALVE TIP SWELLED UP, PROBABLY DUE TO 100 LL OR AUTOGAS. ENGINE FALTERED AT HIGH POWER SETTINGS. TAKEOFF ABORTED. 1 H 7 1 3O 3 O NC A768 E252 1996091900253 19960919 00253 1996 9 19 96ZZZX4624 1 19960807 G 2822 1D217 PUMP AIRBORNE FUEL BOOST FAILED D K NONE O OTHER IN INSP/MAINT 1 GL 13 11AE106 FUEL PUMP ARMATURE OUT OF DYNAMIC BALANCE CAUSING PREMATURE FAILURE OF THE PUMP. 1996091900254 19960919 00254 NM 1996 9 19 96ZZZX4625 1 19960720 G 6320 A0061 TRANSMISSION ROBSIN R22 R22BETA NM M/R LEAKING D K NONE K FLUID LOSS IN INSP/MAINT 1 SO 11 22640 2120 120 0502 DURING PRE-FLIGHT INSPECTION, PILOT NOTICED A PUDDLE OF OIL (BLUE IN COLOR) ON THE GROUND BENEATH THE HELICOPTER. INSPE CTION OF THE HELICOPTER BY A MAINTENANCE TECHNICIAN REVEALED TRANSMISSION OIL WAS LEAKING FROM THE LOWER TRANSMISSION H OUSING COVER PARTING SURFACE. INSPECTION OF TRANSMISSION COVER AFTER DISASSEMBLY REVEALED POROSITY IN AREA OF O-RING SE ALING SURFACE OF THE COVER. THE O-RING SHOWS INDICATION OF POROSITY TRANSFER MARKS IN O-RING. 1 G 7 1 3O H10WE 1996091900255 19960919 00255 NM 1996 9 19 96ZZZX4626 1 19960821 G 6310 A0511 CLUTCH ACTUATOR ROBSIN R22 R22BETA NM M/R DRIVE BLOWS FUSES D A O OTHER O OTHER CR CRUISE 1 WP 23 8338Q 21 3273 2614 THE NEW AIRCRAFT WAS BEING FERRIED FROM CALIFORNIA TO NEBRASKA. DURING A FUEL STOP, THE 1.5 AMP FUSE FOR THE CLUTCH ACT UATOR WAS FOUND 'BLOWN'. THE FUSE WAS REPLACED BY THE PILOT WITH A 1 AMP. DURING A LATER FUEL STOP, THE FUSE WAS FOUND BLOWN AGAIN AND THE PILOT NOTICED THE A190-2 V-BELTS WERE SEVERELY DAMAGED. FURTHER INSPECTION SHOWED THE CLUTCH ACTUA TOR SPRINGS POPPED WEAKLY WHEN THE BOLTS WERE TENSIONED, BUT CONTINUED TO INCREASE THE TENSION UNTIL THE FUSE BLEW. THE V-BELTS AND CLUTCH ACTUATOR WERE REPLACED WITH NEW, AND THE FLIGHT WAS COMPLETED. 1 G 7 1 3O H10WE 1996091900256 19960919 00256 NM 1996 9 19 96ZZZX4627 1 19960821 G 6310 A1902 BELT ROBSIN R22 R22BETA NM M/R DRIVE DAMAGED D A O OTHER O OTHER CR CRUISE 1 WP 23 8338Q 21 2614 THE NEW AIRCRAFT WAS BEING FERRIED FROM CALIFORNIA TO NEBRASKA. DURING A FUEL STOP, THE 1.5 AMP FUSE FOR THE CLUTCH ACT UATOR WAS FOUND 'BLOWN'. THE FUSE WAS REPLACED BY THE PILOT WITH A 1 AMP. DURING A LATER FUEL STOP, THE FUSE WAS FOUND BLOWN AGAIN AND THE PILOT NOTICED THE A190-2 V-BELTS WERE SEVERELY DAMAGED. FURTHER INSPECTION SHOWED THE CLUTCH ACTUA TOR SPRINGS POPPED WEAKLY WHEN THE BOLTS WERE TENSIONED, BUT CONTINUED TO INCREASE THE TENSION UNTIL THE FUSE BLEW. THE V-BELTS AND CLUTCH ACTUATOR WERE REPLACED WITH NEW, AND THE FLIGHT WAS COMPLETED. 1 G 7 1 3O H10WE 1996091900258 19960919 00258 SO 1996 9 19 96ZZZX4629 1 19960809 G 3320 BR9800005 LAMP BRUCE BCI0047005 EMB 120 EMB120RT SO CABIN LIGHT BURN DAMAGE B ZZBR K NONE M OVER TEMP IN INSP/MAINT 1 WP 11 FOUND LAMP UNIT WITH BURN DAMAGE. REFER TO BRUCE INDUSTRIES, INC., DOCUMENT NR 350-149. A DESIGN CHANGE WAS INCORPORAT ED ON BRUCE IND. INC., DRAWING BR9800 TO REDUCE THE LENGTH AT THE STARTING AID BY .9 INCH (11-13-95). 2 L 7 2 4T RT A31SO 1996091900259 19960919 00259 EU 1996 9 19 96ZZZX4630 1 19960809 G 3320 BV501258 LAMP HOLDER BRUCE BCI0004001 BAC 146 AVRO146RJ100 1500096 EU CABIN BURN DAMAGE B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 FOUND LAMP HOLDER WITH BURN DAMAGE. APPARENTLY EXTERNAL HEAT SOURCE. 2 H 7 4 4F RT A49EU 1996091900260 19960919 00260 NM 1996 9 19 96ZZZX4631 1 19960827 G 2121 71912 END BELL SUNDSTRANDEM 65771 BOEING 727 727 1384001 NM BEARING BORE WORN B DM4R K NONE O OTHER IN INSP/MAINT 1 SO 19 546 888 FAN END BELL BEARING BORE WORN OVERSIZE AFTER 545.5 HOURS OF OPERATION. 2 L 7 3 4F A3WE 1996091900261 19960919 00261 NE 1996 9 19 96ZZZX4632 2 19960812 G 7230 771706 BLADE PWA JT8 JT8D219 52053 NE LOW COMP C6 FAILED B VV1R K NONE O OTHER IN INSP/MAINT 1 SW 19 60 725425 THE ENGINE WAS INSPECTED FOR CUSTOMER WHO REPORTED 'SURGE DURING CRUISE', AND C6, 7 AND 13 STAGE BLADE DAMAGE. DISASSEM BLY FINDINGS REVEALED 2 EACH LIBERATED C6 BLADES AND EXTENSIVE DAMAGE TO HPC. THE FAILED BLADES ARE UNDER INVESTIGATION AT GREENWICH-TEXAS. 4 F E9NE 1996091900478 19960919 00478 SW 1996 9 19 96ZZZX4642 1 19960720 G 6330 206033506101 RESTRAINT SPRING LK0104 BELL 206 206L3 1182108 SW TRANSMISSION BEARING WORN B ZV1R K NONE O OTHER IN INSP/MAINT 1 SW 03 2616 550 51418 RESTRAINT SPRING BEARINGS WORN BEYOND LIMITS. REPLACED BEARINGS, 2 EACH, P/N 206-033-509-003. 1 G 7 1 3U H2SW 1996091900479 19960919 00479 SW 1996 9 19 96ZZZX4643 1 19960705 G 6330 206033506101 RESTRAINT SPRING BELL 206 206L1 1182107 SW TRANSMISSION BEARING WORN B ZV1R K NONE O OTHER IN INSP/MAINT 1 SW 03 5759M 729 LK3115 45555 RESTRAINT SPRING BEARINGS WORN BEYOND LIMITS. REPLACED BEARINGS, P/N 206-033-509-003. 1 G 7 1 3U H2SW 1996091900480 19960919 00480 SW 1996 9 19 96ZZZX4644 1 19960705 G 6320 206040032011 BEARING 206040004111 BELL 206 206L1 1182107 SW M/R XMSN FAILED B ZV1R K NONE O OTHER IN INSP/MAINT 1 SW 03 5759M 12948 J0980 45555 LOWER DUPLEX BEARING BAD. CONTAMINATED TRANSMISSION, DAMAGING OIL PUMP, AND GEARSHAFT ROLLER BEARING. TRANSMISSION COM PLETELY TORN DOWN, INSPECTED, CLEANED, AND REASSEMBLED. TSO: 702.5 HOURS TOTAL TIME OF DEFECTIVE DUPLEX BEARING. 702 .5 HOURS AND 9 MONTHS SINCE NEW. 1 G 7 1 3U H2SW 1996091900481 19960919 00481 SW 1996 9 19 96ZZZX4645 1 19960717 G 3213 AXEL BELL 206 206B 1181511 SW PIN HOLE MISMANUFACTURED B WG3R K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 27 82HH 4337 OWNER REPORTED THAT GROUND HANDLING WHEELS WERE UNABLE TO LOCK BECAUSE MISALIGNMENT AT AXEL PIN HOLE. RESHIMMED TO CORR ECT PROBLEM. 1 G 7 1 3U H2SW 1996091900482 19960919 00482 EU 1996 9 19 96ZZZX4646 1 19960715 G 6720 741C000005 ACTUATOR BOLKMS 117 BK117A1 5626010 EU TAIL ROTOR LEAKS B TI1R K NONE K FLUID LOSS IN INSP/MAINT 1 SW 05 117LF 00248 7013 ACTUATOR LEAKS. 1 G 7 2 3U H13EU 1996091900483 19960919 00483 EU 1996 9 19 96ZZZX4647 1 19960606 G 6410 11731742 BLADE BOLKMS 117 BK117B1 5626012 EU TAIL ROTOR PAINT PEEL B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 217MC 4251 286 7195 TAIL ROTOR BLADE PAINT PEELING OFF LESS THAN 90 DAYS INSTALLED. 107.8 ACFT HRS. 1 G 7 2 3U H13EU 1996091900484 19960919 00484 EU 1996 9 19 96ZZZX4648 1 19960606 G 6410 11731742 BLADE BOLKMS 117 BK117B1 5626012 EU TAIL ROTOR PAINT PEEL B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 217MC 3779 509 7195 TAIL ROTOR BLADE PAINT PEELING OFF LESS THAN 90 DAYS INSTALLED. 107.8 ACFT HRS. 1 G 7 2 3U H13EU 1996091900485 19960919 00485 1996 9 19 96ZZZX4649 4 19960731 G 3450 066303402 INDICATOR BOLKMS 117 BK117B1 5626012 EU COCKPIT NAV ERRORS B TI1R K NONE O OTHER NR NOT REPORTED 1 SW 05 213AE 50271 7219 IINDICATOR 50 DEGREES OFF. NAVIGATOR WILL NOT RETRACT. 1 G 7 2 3U H13EU 1996091900486 19960919 00486 1996 9 19 96ZZZX4650 4 19960731 G 3421 5050031904 GYRO BOLKMS 117 BK117B1 5626012 EU COCKPIT DEFECTIVE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 213AE 959 7219 GYRO PRECESSES - RECALIBRATE. 1 G 7 2 3U H13EU 1996091900487 19960919 00487 EU 1996 9 19 96ZZZX4651 1 19960801 G 6240 117945641 INDICATOR BOLKMS 117 BK117B1 5626012 EU MAST MOMENT FAULTY B TI1R K NONE P NO WARNING INDICATION IN INSP/MAINT 1 SW 05 213AE E030585 7219 MAST MOMENT LIMIT LIGHT DOES NOT ILLUMINATE WHEN POWER IS APPLIED. 1 G 7 2 3U H13EU 1996091900488 19960919 00488 EU 1996 9 19 96ZZZX4652 1 19960801 G 2822 1176415103 PUMP BOLKMS 117 BK117B1 5626012 EU FUEL BOOST LEAKING B TI1R K NONE K FLUID LOSS IN INSP/MAINT 1 SW 05 213AE 172203 7219 BOOST PUMP LEAKING FROM SEAL DRAIN. 1 G 7 2 3U H13EU 1996091900489 19960919 00489 EU 1996 9 19 96ZZZX4653 1 19960720 G 3310 1179203903 POWER SUPPLY BOLKMS 117 BK117B1 5626012 EU LIGHTS INOPERATIVE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 213AE 1069 7219 COCKPIT LIGHTING POWER SUPPLY INOPERATIVE. 1 G 7 2 3U H13EU 1996091900490 19960919 00490 SW 1996 9 19 96ZZZX4654 1 19960626 G 2435 23032048 STARTER BELL 222 222U 1182140 SW START/GEN VIBRATION B TI1R K NONE E VIBRATION/BUFFET IN INSP/MAINT 1 SW 05 219HM 205 23014 47573 STARTER HAS 0.24 IPS VIBRATION. 1 G 7 2 3U H9SW 1996091900491 19960919 00491 SW 1996 9 19 96ZZZX4655 1 19960729 G 6310 222044672101S COUPLING BELL 222 222U 1182140 SW ENGINE/XMSN CORRODED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 219HM 296 A000877 47573 CORROSION ON INSIDE DIAMETER OF OUTER COUPLING. 1 G 7 2 3U H9SW 1996091900492 19960919 00492 SW 1996 9 19 96ZZZX4656 1 19960730 G 6410 2220167001111 BLADE BELL 230 230 1182149 SW TAIL ROTOR DEFECTIVE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 230JP 310 A532 23019 BLADE S/N A532 HAD FILLER COMING OFF OF BLADE AND S/N A528 WAS REMOVED PER ASB 23595-8. 1 G 7 2 3U NC H9SW 1996091900493 19960919 00493 1996 9 19 96ZZZX4657 4 19960711 G 2210 741C000005 ACTUATOR BOLKMS 117 BK117A3 5626015 EU YAW DEFECTIVE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 312LF 00305 7083 ACTUATOR MAKES COMPUTER CLATTER INSIDE. 1 G 7 2 3U H13EU 1996091900494 19960919 00494 1996 9 19 96ZZZX4658 4 19960710 G 2211 117884141 COMPUTER BOLKMS 117 BK117A3 5626015 EU YAW/CSAS INOPERATIVE B TI1R K NONE B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 SW 05 312LF 018609010 7083 COMPUTER INOPERATIVE, UNIT SMOKING. 1 G 7 2 3U H13EU 1996091900495 19960919 00495 1996 9 19 96ZZZX4659 4 19960706 G 2211 117884141 COMPUTER BOLKMS 117 BK117A3 5626015 EU YAW/CSAS DEFECTIVE B TI1R K NONE O OTHER NR NOT REPORTED 1 SW 05 312LF 018609001 7083 YAW KICKS IN-FLIGHT. 1 G 7 2 3U H13EU 1996020200279 19960202 00279 SO 1996 2 2 96ZZZX466 2 19960115 G 7421 RHB32S SPARK PLUG CESSNA 185 185F 2072820 CE CONT O520 IO520D 17032 SO ELECTRODE SPLIT B CS3R K NONE O OTHER IN INSP/MAINT 1 WP 17 11174 1401 1M92 18504435 282968R FOUND 2 SPARK PLUGS WITH ROUND ELECTRODES SPLIT. SUBMITTER STATED MORE THAN 20 OF THE PART NUMBERS HAVE BEEN FOUND. 1 H 7 1 3O 3 O 3A24 E5CE 1996091900496 19960919 00496 EU 1996 9 19 96ZZZX4660 1 19960708 G 6520 4639311043 BEVEL GEAR TOOTH BOLKMS BK117 BK117C1 5626025 EU TAIL ROTOR PITTED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 317MC 1318 784 7505 PITTING ON TOOTH FACE IS REASON FOR REJECTION. 1 G 7 2 3U NC H13EU 1996091900497 19960919 00497 EU 1996 9 19 96ZZZX4661 1 19960708 G 6520 4639310012 BEARING BOLKMS BK117 BK117C1 5626025 EU TAIL ROTOR SCORED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 317MC 1318 1519 7505 BEARING ROLLERS ARE SCORED. 1 G 7 2 3U NC H13EU 1996091900498 19960919 00498 EU 1996 9 19 96ZZZX4662 1 19960708 G 6520 4639311003 BEARING BOLKMS BK117 BK117C1 5626025 EU TAIL ROTOR SCORED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 317MC 1318 751 7505 BEARING ROLLERS ARE SCORED. 1 G 7 2 3U NC H13EU 1996091900499 19960919 00499 EU 1996 9 19 96ZZZX4663 1 19960802 G 7120 117601091 FORK BOLKMS BK117 BK117C1 5626025 EU ENGINE MOUNT WORN B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 317MC 7505 UPON REMOVAL OF NR 1 ENGINE, FOUND TRANSIT ENGINE MOUNT FORK WORN BEYOND LIMITS. 1 G 7 2 3U NC H13EU 1996091900500 19960919 00500 EU 1996 9 19 96ZZZX4664 1 19960729 G 6520 4639311005 SHAFT BOLKMS BK117 BK117C1 5626025 EU T/R OUTPUT PLATING MISSING B TI1R K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 05 317MC 1088 7505 TAIL ROTOR GEARBOX OUTPUT SHAFT, SILVER PLATING IS MISSING ON ONE SPOT ON INSIDE DIAMETER OF SHAFT. NOT ACCEPTABLE IAW CURRENT REM 305 MANUAL. PART IS NO GOOD AS IS. 1 G 7 2 3U NC H13EU 1996091900501 19960919 00501 EU 1996 9 19 96ZZZX4665 1 19960521 G 5210 T6301107 HANDLE BOLKMS BK117 BK117C1 5626025 EU DOOR DEFECTIVE B TI1R K NONE O OTHER NR NOT REPORTED 1 SW 05 317MC 7505 HANDLE ASSY NOT MAKING POSITIVE CONTACT AND SOMETIMES VIBRATES OPEN. 1 G 7 2 3U NC H13EU 1996091900502 19960919 00502 EU 1996 9 19 96ZZZX4666 1 19960607 G 6720 11731821 PITCH LINK BOLKMS BK117 BK117C1 5626025 EU TAIL ROTOR BEARING PLAY B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 317MC 7505 TAIL ROTOR CONTROL PLAY IN BEARINGS (2 EACH). 1 G 7 2 3U NC H13EU 1996091900503 19960919 00503 1996 9 19 96ZZZX4667 4 19960805 G 2211 117884141 COMPUTER BOLKMS 117 BK117A4 5626017 EU YAW/CSAS DEFECTIVE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 313LF 68 5034 7138 YAW/CSAS OSCILLATES LEFT TO RIGHT ON GROUND AND IN-FLIGHT. 1 G 7 2 3U H13EU 1996091900504 19960919 00504 EU 1996 9 19 96ZZZX4668 1 19960729 G 6520 4639311005 SHAFT BOLKMS 117 BK117A3 5626015 EU T/R GEARBOX PLATING MISSING B TI1R K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 05 4493X 1179 S7038 TAIL ROTOR GEARBOX OUTPUT SHAFT SILVER PLATING MISSING ON THREE SPOTS ON INSIDE DIAMETER OF SHAFT. NOT ACCEPTABLE IAW C URRENT REM 305 MANUAL. PART IS NO GOOD AS IS. 1 G 7 2 3U H13EU 1996091900505 19960919 00505 SW 1996 9 19 96ZZZX4669 1 19960709 G 3510 IDP5 INDICATOR BELL 206 206L1 1182107 SW OXYGEN SYSTEM READS LOW B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 519EH 6160833 45429 OXYGEN INDICATOR READS 150 TO 200 PSI LOW. WILL NOT WORK ON INTERNAL CALIBRATION MODE. 1 G 7 1 3U H2SW 1996020200280 19960202 00280 EA 1996 2 2 96ZZZX467 2 19960102 G 7322 2271683 THROTTLE BODY MA45 LYC O360 O360* 41514 EA CARBURETOR CRACKED F K NONE O OTHER IN INSP/MAINT 1 WP 05 75049602 L3475436A INSPECTION FOUND THROTTLE BODY IS CRACKED ABOVE P/N 43-648 IDLE MIXTURE ADJUSTING NEEDLE. THE CRACK EXTENDS FROM THE MO UNTING FACE DOWN TO THE IDLE MIXTURE BOSS AND BACK TO THE MOUNTING FACE. 3 O E286 1996091900506 19960919 00506 EU 1996 9 19 96ZZZX4670 1 19960617 G 2435 23032022 GENERATOR BOLKMS 117 BK117A3 5626015 EU START/GEN ARMATURE SCORED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 527MB 324 21976 7103 START/GENERATOR ARMATURE SCORED DUE TO BRUSH HOLDER BENT. 1 G 7 2 3U H13EU 1996091900507 19960919 00507 CE 1996 9 19 96ZZZX4671 1 19960602 G 3244 22X675108TL TIRE BEECH 200 B200 1152922 CE GEAR DEFECTIVE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 75LV 31172342 BB1075 TIRE DEVEOPED BUMP. SUPSECT CORD SEPARATION. 1 L 7 2 4T A24CE 1996091900508 19960919 00508 1996 9 19 96ZZZX4672 4 19960704 G 2312 4000103001 TRANSCEIVER BOLKMS 105 BO105S 5626006 EU COCKPIT FAILED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 911LF 613 S663 TRANSCEIVER WILL NOT TRANSMIT WHEN UNIT GETS HOT. 1 G 7 2 3U H3EU 1996091900509 19960919 00509 1996 9 19 96ZZZX4673 4 19960621 G 2312 3130001010111 CONTROL UNIT BOLKMS 105 BO105S 5626006 EU COCKPIT VHF DEFECTIVE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 911LF 176 S663 ENTER KNOB INOPERATIVE. 1 G 7 2 3U H3EU 1996091900510 19960919 00510 1996 9 19 96ZZZX4674 4 19960627 G 2312 40001452500 TRANSCEIVER BOLKMS 117 BK117A3 5626015 EU COCKPIT VHF DEFECTIVE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 911MZ 269 7098 TRANSCEIVER WILL NOT TRANSMIT CLEAR, BUT RECEIVES OK. PART WAS JUST IN FOR REPAIR 5-14-96. 1 G 7 2 3U H13EU 1996091900511 19960919 00511 EU 1996 9 19 96ZZZX4675 1 19960701 G 7120 1176272102 LINK BOLKMS 117 BK117A3 5626015 EU MOUNT CRACKED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 950MB 0059 7061 FOUND ENGINE MOUNT EAR CRACKED INTO TWO PIECES. 1 G 7 2 3U H13EU 1996020200281 19960202 00281 EA 1996 2 2 96ZZZX468 2 19960108 G 7322 2271683 THROTTLE BODY MA45 LYC O360 O360* 41514 EA CARBURETOR CRACKED F K NONE O OTHER IN INSP/MAINT 1 WP 05 75049615 L3478536A INSPECTION FOUND THROTTLE BODY IS CRACKED ABOVE P/N 43-648 IDLE MIXTURE ADJUSTING NEEDLE. THE CRACK EXTENDS FROM THE MO UNTING FACE DOWN TO THE IDLE MIXTURE BOSS AND BACK TO THE MOUNTING FACE. THIS IS THE SECOND OCCURRENCE THIS MONTH. 3 O E286 1996091900519 19960919 00519 EU 1996 9 19 96ZZZX4683 1 19960821 G 3320 350A64518205 PC BOARD AEROSP AS355 AS355F1 8680810 EU CABIN LIGHTS FAILED B SZTR K NONE O OTHER IN INSP/MAINT 1 WP 07 5789X 40 5100 INTERIOR LIGHTS INOPERATIVE. REPLACED P.C. BOARD. LIGHTS OPS CHECKED GOOD. 1 G 7 2 3U H11EU 1996091900520 19960919 00520 WP 1996 9 19 96ZZZX4684 1 19960821 G 6320 369D25149 BEARING 369D25100505 HUGHES 369 369D 4470706 WP M/R XMSN DEFECTIVE B EOOR K NONE J WARNING INDICATION IN INSP/MAINT 1 AL 03 5074R 9102 1151D DURING INSPECTION OF MAIN ROTOR TRANSMISSION AFTER CHIP LIGHT, FOUND 369D25149 OUTPUT SHAFT BALL BEARING TO BE SEVERELY ETCHED ON ONE BALL. 1 G 7 1 3U H3WE 1996091900521 19960919 00521 WP 1996 9 19 96ZZZX4685 1 19960820 G 6320 369D2514C BEARING 369D25100505 HUGHES 369 369D 4470706 WP MR GRBOX CRACKED B S A EOOR K NONE O J OTHER WARNING INDICATION IN INSP/MAINT 1 AL 03 5074R 1190 1151D DISASSEMBLED MAIN ROTOR TRANSMISSION AFTER CHIP LIGHT. FOUND THE FORWARD SUPPORT BEARING FOR THE TAIL ROTOR O/P SHAFT H AD A CRACKED INNER RACE AND THAT IT HAD FORCED THE SNAP RING OFF OF THE END OF THE SHAFT AND THEN THE INNER RACE GOUGED INTO THE COVER ASSEMBLY ABOUT .125 INCH DEEP. 1 G 7 1 3U H3WE 1996091900523 19960919 00523 1996 9 19 96ZZZX4687 4 19960514 G 3422 40205773 GYRO BOLKMS BK117 BK117C1 5626025 EU COCKPIT DIR INTERMITTENT B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 317MC 92015145 7505 COCKPIT DIRECTIONAL GYRO, INTERMITTENT FAILURES. REMOVED AND REPLACED. 1 G 7 2 3U NC H13EU 1996091900576 19960919 00576 EU 1996 9 19 96ZZZX4688 1 19960316 G 2612 CONNECTOR BRAERO DH125 HS125700A 4230170 EU LT ENG FIRE WARN CONTAMINATED D E F ENGINE SHUTDOWN ACTIVATE FIRE EXT. N FALSE WARNING CR CRUISE 1 EA 01 193RC 9660 NA0258 FIRE BELL RANG WITH NO OTHER INDICATIONS. THROUGH ISOLATION SWITCH MOVEMENT, CONDITION WAS DETERMINED TO BE ON LEFT ENG INE. ENGINE AND FIRE DETECTION SYSTEM EXAMINED. NO DEFECTS NOTED. LT ENG FIRE SYS LIGHTS AND BELL CAME ON. ENGINE SE CURED AND NR 1 FIRE BOTTLE FIRED. LIGHTS AND BELL EVENTUALLY WENT OUT. FOUND SMALL AMT OF SEMI-CONDUCTIVE BLK GREASE I N CONNECTOR PLUG IN LT ENG PLYON. CLEANED PLUG, SYS NOW NORMAL. PROBLEM OCCURRED APPROX 45 HRS AFTER ENG CHANGE AND TH IS PLUG WAS DISCONNECTED AT THAT TIME. 2 L 7 2 4F A3EU 1996020200282 19960202 00282 SO 1996 2 2 96ZZZX469 2 19960109 G 7322 390077 SEAT VALVE BBAVIA 7 7AC 2110102 SW CONT C85 C858 17008 SO CARBURETOR LOOSE D C ABORTED TAKEOFF Y W ENGINE STOPPAGE INADEQUATE Q C TO TAKEOFF 1 GL 27 83975 5 2661 3070788 ENGINE QUIT ON TAKEOFF. DISASSEMBLED CARBURETOR AND INSPECTION FOUND SEAT VALVE HAD NOT BEEN PROPERLY TORQUED. SEAT WO RKED LOOSE AND LOWERED FLOAT LEVEL TO WHERE ENGINE COULD NOT DEVELOP FULL POWER. CARBURETOR OVERHAULED 10-95. 1 H 7 1 3O 3 O A759 E233 1996091900578 19960919 00578 EU 1996 9 19 96ZZZX4690 1 19960828 G 3320 6900080 LIGHT SAAB SF340 SF340A 7850100 EU LAVATORY OVERHEATED B PJ2R K NONE M OVER TEMP IN INSP/MAINT 1 CE 07 39MB 3000 PW3888 340A022 P/N 6900080, 28V, FOR FLUORESCENT LIGHTS. SUBMITTER STATED THE LIGHTS ARE A PROBLEM IN THAT THEY DO NOT LAST BEFORE FAI LURE OR BECOMING INOPERABLE. ONE SPECIFIC OCCURRENCE IN THAT UNIT OVERHEATED, BURNED WITH BAD ODOR AND DISCOLORATION AR OUND INSTALLATION, INTERNAL FAILURE. 2 L 7 2 4T RT A52EU 1996091900579 19960919 00579 EU 1996 9 19 96ZZZX4691 1 19960729 G 5753 25WS21AD FLAP VANE HWKSLY DH125 BH125400A 4230138 EU RT FLAP CRACKED A S A FE6R K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 11 456WH 6348 NA760 THE LT AND RT OTBD FLAP VANE SKINS AND VANE SPARS HAVE BEEN ALTERED FROM THE ORIGINAL. A RADIUS APPROX 1 INCH WIDE AND .6250 INCH DEEP HAS BEEN GROUND INTO THE FLAP VANES IN THE AREA OF THE OTBD FLAP HINGE. ONE RIVET HAS BEEN REMOVED. I T IS BELIEVED THIS 'MODIFICATION' HAS BEEN INCORPORATED TO ALLOW REMOVAL OF THE OTBD FLAP HINGE RETAINING PIN WITHOUT TI LTING VANE. CRACKS ARE NOTED IN THE LEFT VANE, IN THE AREA OF THE ALTERATION POSSIBLY DUE TO DECREASED SPAR WEB STRENGT H. THE MANUFACTURER IS PRESENTLY EVALUATING THE SITUATION FOR A POSSIBLE REPAIR. REPLACEMENT OF BOTH OTBD FLAP VANES I S ALSO BEING CONSIDERED. 2 L 7 2 4J A3EU 1996091900580 19960919 00580 EU 1996 9 19 96ZZZX4692 1 19960729 G 5753 25WS22AD FLAP VANE HWKSLY DH125 BH125400A 4230138 EU LT FLAP CRACKED A A FE6R K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 11 456WH 6348 NA760 THE LT AND RT OTBD FLAP VANE SKINS AND VANE SPARS HAVE BEEN ALTERED FROM THE ORIGINAL. A RADIUS APPROX 1 INCH WIDE AND .6250 INCH DEEP HAS BEEN GROUND INTO THE FLAP VANES IN THE AREA OF THE OTBD FLAP HINGE. ONE RIVET HAS BEEN REMOVED. I T IS BELIEVED THIS 'MODIFICATION' HAS BEEN INCORPORATED TO ALLOW REMOVAL OF THE OTBD FLAP HINGE RETAINING PIN WITHOUT TI LTING VANE,. CRACKS ARE NOTED IN THE LEFT VANE, IN THE AREA OF THE ALTERATION POSSIBLY DUE TO DECREASED SPAR WEB STRENG TH. THE MANUFACTURER IS PRESENTLY EVALUATING THE SITUATION FOR A POSSIBLE REPAIR. REPLACEMENT OF BOTH OTBD FLAP VANES IS ALSO BEING CONSIDERED. 2 L 7 2 4J A3EU 1996091900581 19960919 00581 EU 1996 9 19 96ZZZX4693 1 19960227 G 2422 ASH6641PF STATIC INVERTER BRAERO DH125 BAE125800A 1500285 EU TAIL COMPARTMENT WATER SOAKED B MJQR K NONE O OTHER IN INSP/MAINT 1 GL 13 60PM 2445 DK905 NA0453 AIRCRAFT SAT ON GROUND OVERNIGHT IN RAIN STORM. INVERTER WAS SATURATED WITH WATER. UNIT WOULD NOT OPERATE. 2 L 7 2 4F RT A3EU 1996091900582 19960919 00582 EU 1996 9 19 96ZZZX4694 1 19960227 G 2450 LDA150A8C CONTACTOR BRAERO DH125 BAE125800A 1500285 EU BUS TIE FAILED B MJQR K NONE O OTHER IN INSP/MAINT 1 GL 13 60PM 3155 7930 NA0453 INTERMITTENT TRIPPING OF CIRCUIT BREAKER (B85). BUS TIE OPEN. REPLACED BUS TIE CONTACTOR. PROBLEM WENT AWAY. 2 L 7 2 4F RT A3EU 1996091900584 19960919 00584 CE 1996 9 19 96ZZZX4696 1 19960820 G 5730 26513008 SKIN RKWELL NA265 NA26580 7630108 CE LT L/E WS 236.9 CRACKED C L K NONE O OTHER IN INSP/MAINT 1 SW 15 7148J 12563 38033 WHILE PERFORMING PRE-FLIGHT INSP, MECH NOTICED PAINT CRACKED AND CHIPPED ON L/E OF WING ABOUT SS 236.9. UPON FURTHER IN SP FOUND A CRACK, ABOUT 8.5 INCHES, THROUGH FIRST STIFFENER AND 4.0 INCHES AND 5.0 INCHES THROUGH SECOND STIFFENER ON BO TTOM OF L/E UNDER DE-ICE BOOT OTBD TO ABOUT WS 264. THIS AREA CLOSED OUT BY RIBS ONE EACH SIDE OF SLAT TRACKS. CRACK A REA COULD NOT BE FELT THROUGH DE-ICE BOOT. AFTER REMOVING CRACKED PORTION OF L/E FROM WING, FOUND 4 EACH STIFFENERS AND RIB CRACKED BEYOND REPAIR. ALSO, FOUND SLAT ATTACH FITTING IN NR 2 SLAT, P/N FITTING 246-17050-5, LOOSE IN SLAT. A CR ACK ALSO RADIATED OUT FROM ATTACH BOLT HOLE THROUGH ATTACH RIB. 2 L 7 2 4F A2WE 1996091900585 19960919 00585 EU 1996 9 19 96ZZZX4697 1 19960729 G 5755 258W851A AIR BRAKE BRAERO DH125 BAE125800A 1500285 EU PANEL LT T/E CRACKED B FE6R K NONE O OTHER IN INSP/MAINT 1 NM 11 85DW 3917 DHP59 258034 THE LEFT HAND UPPER AIR BRAKE PANEL FOUND WITH A 5.5 INCH CRACK IN THE CENTER OF THE AIR BRAKE AT THE TRAILING EDGE OF T HE LOWER SKIN, AT THE JOGGLE BEND. FACTORY NEW PART NOT READILY AVAILABLE. REPAIRED PER BAE 800 SRM, P/N SRM 125-800, REV 25, DATED APRIL 30, 1995, CHAPTER 51-10-03, AND OTHERS, AS APPLICABLE. 2 L 7 2 4F RT A3EU 1996091900586 19960919 00586 EU 1996 9 19 96ZZZX4698 1 19960729 G 5730 S258WS50022A SKIN BRAERO DH125 BAE125800A 1500285 EU LE TKS REBATE CORRODED B FE6R K NONE O OTHER IN INSP/MAINT 1 NM 11 85DW 1121 AST93B062 258034 ALL WING LEADING EDGES WERE REPLACED WITH FACTORY NEW ON 7-10-93, PER MANDATORY SB 57-77, DUE TO CORROSION. UNTIL THIS TIME, SUBSEQUENT INSPECTIONS REQUIRED BY AD 95-15-04, AMDT 39-9307, DATED 8-23-95, AND MANDATORY SB 57-77, REV 1, DATED 10-28-93, HAVE SHOWN NO CORROSION. THESE INSPECTIONS ARE NO LONGER REQUIRED. AT THIS TIME, THE WING LEADING EDGES ARE INSPECTED PER THE STRUCTURAL INSPECTIONS, ITEMS 570019/570021, APPROX 3 YEARS PRIOR TO REQUIREMENT, FOR SCHEDULING PURPO SES. MINOR CORROSION IS NOTED, AT THE TKS REBATES. CORROSION IS BLENDED AND REMOVED PER MFG REPAIR INSTRUCTION LETTER, RIL 25W AND 279, REV 3, DATED 4-30-93. 2 L 7 2 4F RT A3EU 1996091900587 19960919 00587 EU 1996 9 19 96ZZZX4699 1 19960729 G 5730 S25BWS50026AX SKIN BRAERO DH125 BAE125800A 1500285 EU LE TKS REBATE CORRODED B FE6R K NONE O OTHER IN INSP/MAINT 1 NM 11 85DW 1121 DHB081 258034 ALL WING LEADING EDGES WERE REPLACED WITH FACTORY NEW ON 7-10-93, PER MANDATORY SB 57-77, DUE TO CORROSION. UNTIL THIS TIME, SUBSEQUENT INSPECTIONS REQUIRED BY AD 95-15-04, AMDT 39-9307, DATED 8-23-95, AND MANDATORY SB 57-77, REV 1, DATED 10-28-93, HAVE SHOWN NO CORROSION. THESE INSPECTIONS ARE NO LONGER REQUIRED. AT THIS TIME, THE WING LEADING EDGES ARE INSPECTED PER THE STRUCTURAL INSPECTIONS, ITEMS 570019/570021, APPROX 3 YEARS PRIOR TO REQUIREMENT, FOR SCHEDULING PURPO SES. MINOR CORROSION IS NOTED, AT THE TKS REBATES. CORROSION IS BLENDED AND REMOVED PER MFG REPAIR INSTRUCTION LETTER, RIL 25W AND 279, REV 3, DATED 4-30-93. 2 L 7 2 4F RT A3EU 1996091900588 19960919 00588 EU 1996 9 19 96ZZZX4700 1 19960729 G 5730 S258WS50041A SKIN BRAERO DH125 BAE125800A 1500285 EU LE TKS REBATE CORRODED B FE6R K NONE O OTHER IN INSP/MAINT 1 NM 11 85DW 1121 AST93E180 258034 ALL WING LEADING EDGES WERE REPLACED WITH FACTORY NEW ON 7-10-93, PER MANDATORY SB 57-77, DUE TO CORROSION. UNTIL THIS TIME, SUBSEQUENT INSPECTIONS REQUIRED BY AD 95-15-04, AMDT 39-9307, DATED 8-23-95, AND MANDATORY SB 57-77, REV 1, DATED 10-28-93, HAVE SHOWN NO CORROSION. THESE INSPECTIONS ARE NO LONGER REQUIRED. AT THIS TIME, THE WING LEADING EDGES ARE INSPECTED PER THE STRUCTURAL INSPECTIONS, ITEMS 570019/570021, APPROX 3 YEARS PRIOR TO REQUIREMENT, FOR SCHEDULING PURPO SES. MINOR CORROSION IS NOTED, AT THE TKS REBATES. CORROSION IS BLENDED AND REMOVED PER MFG REPAIR INSTRUCTION LETTER, RIL 25W AND 279, REV 3, DATED 4-30-93. 2 L 7 2 4F RT A3EU 1996091900589 19960919 00589 EU 1996 9 19 96ZZZX4701 1 19960729 G 5730 S258WS50045A SKIN BRAERO DH125 BAE125800A 1500285 EU LE TKS REBATE CORRODED B FE6R K NONE O OTHER IN INSP/MAINT 1 NM 11 85DW 1121 AST93E178 258034 ALL WING LEADING EDGES WERE REPLACED WITH FACTORY NEW ON 7-10-93, PER MANDATORY SB 57-77, DUE TO CORROSION. UNTIL THIS TIME, SUBSEQUENT INSPECTIONS REQUIRED BY AD 95-15-04, AMDT 39-9307, DATED 8-23-95, AND MANDATORY SB 57-77, REV 1, DATED 10-28-93, HAVE SHOWN NO CORROSION. THESE INSPECTIONS ARE NO LONGER REQUIRED. AT THIS TIME, THE WING LEADING EDGES ARE INSPECTED PER THE STRUCTURAL INSPECTIONS, ITEMS 570019/570021, APPROX 3 YEARS PRIOR TO REQUIREMENT, FOR SCHEDULING PURPO SES. MINOR CORROSION IS NOTED, AT THE TKS REBATES. CORROSION IS BLENDED AND REMOVED PER MFG REPAIR INSTRUCTION LETTER, RIL 25W AND 279, REV 3, DATED 4-30-93. 2 L 7 2 4F RT A3EU 1996091900590 19960919 00590 EU 1996 9 19 96ZZZX4702 1 19960817 G 7921 5711012334 INLET FENCE PILATS PC12 PC12 7090550 EU OIL COOLER CRACKED B LF1R K NONE O OTHER IN INSP/MAINT 1 EA 07 117WF 328 117 DURING SCHEDULED INSPECTION, FOUND OIL COOLER INLET FENCE CRACKED ON BOTTOM NOSE COWLING. POSSIBLE TURBULENT AREA CAUSI NG VIBRATION AND CRACKING. SUBMITTER RECOMMENDS CLOSE INSPECTION DURING PRE-FLIGHT AND DURING SCHEDULED MAINTENANCE. 1 L 7 1 3T RT A78EU 1996091900591 19960919 00591 SO 1996 9 19 96ZZZX4703 1 19960801 G 5412 WEB PIPER PA42 PA42 7104202 SO ENGINE FIREWALL CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 25 123AG 6410 428001031 INSPECTION FOUND A CRACKED WEB AT BOTH ENGINE FIREWALLS AT ENGINE MOUNT AREA. 1 L 7 2 4T A23SO 1996091900592 19960919 00592 GL 1996 9 19 96ZZZX4704 2 19960322 G 7210 23035178 GEARBOX BELL 206 206L3 1182108 SW ALLSN 250C 250C30 03013 GL MOUNT PAD CORRODED D K NONE O OTHER IN INSP/MAINT 1 EU 01 722H 3546 CAG95568 51452 PITTED CORROSION ON RT GEARBOX BOSS OCCURRED DURING NORMAL OPERATION. FOUND DURING ROUTINE INSPECTION. RECOMMENDED SUP PLIER CHECK MATERIALS FOR DEFECTS. SIMILAR PROBLEM FOUND ON THREE GEARBOXES. 1 G 7 1 3U 3 U H2SW E1GL 1996091900593 19960919 00593 EU 1996 9 19 96ZZZX4705 1 19960820 G 6320 4638001004 CHAFE TAPE BOLKMS 105 BO105C 5626005 EU M/R XMSN DETACHED D A A UNSCHED LANDING F J FLT CONT AFFECTED WARNING INDICATION CR CRUISE 1 EA 27 60EG 158 1038 S556 DURING CRUISE FLIGHT, ACFT EXPERIENCED A SUDDEN RIGHT YAW, A RAPID RISE IN TURBINE OUTLET TEMPERATURE (TOT), AND A TORQU E REDUCTION IN THE NR 1 ENGINE. REDUCING THE POWER LEVER TO IDLE ARRESTED THE RISE IN TOT AND AN UNEVENTFUL EMERGENCY L ANDING WAS MADE. NO LIMITS WERE EXCEEDED. INSPECTION DETERMINED THE NR 1 ENGINE AIR INLET WAS 25 TO 50 PERCENT BLOCKED BY AN 11 INCH BY 3 INCH PIECE OF ANTI-CHAFE TAPE. THE MANUFACTURER INSTALLED TAPE HAD COME LOOSE FROM THE TRANSMISSIO N BY THE INLET DEFLECTOR SHIELD HOUSING AND WAS ALMOST INGESTED INTO THE COMPRESSOR. RECOMMEND CLOSELY CHECKING THE ANT I-CHAFE TAPE DURING THE DAILY, PRE-FLIGHT, AND 50-HOUR INSPECTIONS. 1 G 7 2 3U H3EU 1996091900594 19960919 00594 NM 1996 9 19 96ZZZX4706 1 19960812 G 2133 7786863 VALVE HAMSTD DHAV DHC8 DHC8201 2809001 NM HI PRESS SOV STUD BROKEN B WVER K NONE O OTHER IN INSP/MAINT 1 EA 09 986HA 66 960115 421 SHUT-OFF VALVE STUD FOUND BROKEN DURING POST-FLIGHT INSPECTION. NO IN-FLIGHT INDICATIONS WERE OBSERVED. CAUSE UNKNOWN. VALVE ASSY WAS REPLACED AND ALL SYSTEMS FUNCTIONED NORMALLY. 2 H 7 2 4T RT A13NM 1996091900595 19960919 00595 CE 1996 9 19 96ZZZX4707 1 19960826 G 2810 10038000015 FUEL CELL BEECH 90 F90 1152909 CE PROBE MOUNT MISMANUFACTURED B ESMR K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 11 600WM R504 LA75 FUEL CELL PROBE MOUNTING PORTS WERE .75 INCH TOO CLOSE TOGETHER. FUEL CELL SUPPOSEDLY NEW FROM MANUFACTURER. 1 L 7 2 4T A31CE 1996091900597 19960919 00597 SO 1996 9 19 96ZZZX4709 2 19960807 G 8520 CRANKCASE CESSNA 310 310R 2074245 CE CONT O520 IO520BB 17032 SO NR 2 CYLINDER CRACKED G K NONE O OTHER IN INSP/MAINT 1 GL 19 2636Y 2181 367 310R1652 573827 CRANKCASE CRACKED IN ON-CRITICAL AREA AS DEFINED BY M90-17. CRACK IN EXCESS OF 2 INCHES EXTENDING FROM NR 2 CYLINDER ST UD UP THROUGH TOP OF CRANKCASE TOWARD MAGNETOS. ENGINE REMOVED FOR REPAIRS TO CRANKCASE BY OVERHAUL SHOP. 1 L 7 2 3O 3 O 3A10 E5CE 1996091900598 19960919 00598 NM 1996 9 19 96ZZZX4710 1 19960822 G 2782 FITTING BOEING 737 737284 138448R NM SLAT ACT SUPPORT CORRODED D K NONE O OTHER IN INSP/MAINT 1 SW 01 310VA 21501 DURING SB INSPECTION OF NR 1 AND NR 5 LEADING EDGE SLAT ACTUATOR SUPPORT FITTINGS, FITTINGS WERE REMOVED TO REPLACE ATTA CH HARDWARE. CORROSION WAS FOUND AT BOTH POSITIONS SEVERE ENOUGH TO REQUIRE REPAIR. SUBSEQUENT INSPECTION UNDER REMAIN ING FITTINGS REVEALED CORROSION AT NR 3 POSITION NOT SERIOUS ENOUGH TO REQUIRE REPAIR. SUGGEST SPECIAL ATTENTION TO SEA LING PRIMING AND CORROSION PREVENTION IN ACTUATOR SUPPORT FITTINGS. 2 L 7 2 4F A16WE 1996092300001 19960923 00001 CE 1996 9 23 96ZZZX4711 1 19960827 G 2437 MS915872 SHUNT BEECH 90 B90 1152912 CE AMMETER BROKEN D K NONE O OTHER IN INSP/MAINT 1 NE 01 40CK 8415 LJ358 MOUNTING BASE OF AMMETER SHUNT BROKE UP AROUND THE 2 MOUNTING SCREWS ALLOWING THE SHUNT TO MOVE ABOUT. THE BASE OF THE MOUNT IS HOLLOW EXPOSING THE SCREWS THAT HOLD THE TERMINAL BLOCKS TO THE BASE. THESE SCREWS CONTACTED THE BASE MOUNTING SCREWS ARCING TO GROUND. THE REPLACEMENT SHUNT HAS A SOLID BASE MAKING IT STRONGER. THERE ARE NO EXPOSED SCREWS ON TH E BOTTOM OF THE BASE OF THE NEW UNIT. BOTH SHUNTS HAVE THE SAME PART NUMBER. 1 L 7 2 3T 3A20 1996091900601 19960919 00601 WP 1996 9 19 96ZZZX4714 1 19960826 G 2700 34856 BODY 428007 LKHEED 1011 1011* WP CONTROL DAMPER CORROSION B DM4R K NONE O OTHER IN INSP/MAINT 1 SO 19 2435 CONTROL SURFACE DAMPER'S ALUMINUM BODY HAS EXCESSIVE CORROSION IN THE INSIDE DIAMETER. 2 L 7 3 4F A23WE 1996091900602 19960919 00602 CE 1996 9 19 96ZZZX4715 1 19960809 G 2931 PT50018LMBE INDICATOR BEECH 200 B200 1152922 CE MLG ACCUM PRESS FAILED B LX5R K NONE O OTHER NR NOT REPORTED 1 GL 19 961LL 304 BB1139 LANDING GEAR ACCUMULATOR PRESSURE GAUGE WAS PEGGED OUT ON THE HIGH SIDE. THE ABOVE PRESSURE GAUGE IS PART OF THE 'AVIAD ESIGN HYDRUALIC LANDING GEAR' MODIFICATION FOR BEECH 200 SERIES AIRCRAFT. STC SA4378WP. 1 L 7 2 4T A24CE 1996091900603 19960919 00603 CE 1996 9 19 96ZZZX4716 1 19960831 G 2910 25057014939 LINE LEAR 24 24D 5170311 CE HYDRAULIC TEE FAILED D A K NONE K FLUID LOSS NR NOT REPORTED 1 WP 27 98WJ 6675 268 FAILED ALUMINUM HYDRAULIC LINE IS LOCATED BETWEEN THE AUXILIARY HYDRUALIC PUMP PRESSURE SWITCH TEE FITTING AND THE THRUS T REVERSER ACCUMULATOR. THE LINE FAILED AT THE FLARE UNDER THE B-NUT ON THE PRESSURE SWITCH FITTING, WHICH RESULTED IN A SUBSEQUENT HYDRAULIC SYSTEM FLUID LOSS. SUBMITTER SUGGESTS REPLACING THIS LINE WITH A STAINLESS STEEL BRAIDED FLEX LI NE DUE TO THE HYDRAULIC PANEL VIBRATION DURING THRUST REVERSER ACTUATION. 2 L 7 2 4J A10CE 1996091900604 19960919 00604 WP 1996 9 19 96ZZZX4717 2 19960821 G 7250 30733543 AIR SEAL 30727262 GARRTT TFE731 TFE73122B 01518 WP TRANSITION DUCT DEFECTIVE B L IY2R K NONE O OTHER IN INSP/MAINT 1 SW 15 4225 463 1013453990 P74146 DURING AN UNSCHEDULED MAINTENANCE EVENT, FOUND AN P/N 3073354-3, AIR SEAL WAS INSTALLED IN THE TRANSITION DUCT, P/N 3072 726-2, S/N 1-01345-3990. SB TFE731-72-3577, REV ZERO, ADDRESSES THIS SUBJECT. 4 F E6WE 1996091900605 19960919 00605 SW 1996 9 19 96ZZZX4718 1 19960806 G 6710 A21810064603 SWITCH GUARDIAN HUGHES 500N 500N 3027374 SW CYCLIC TRIM STICKS G K NONE O OTHER IN INSP/MAINT 1 WP 07 521FB 811 LN001 SWITCH STICKS IN LEFT POSITION. RESULTS IN BURNT TRIM MOTOR (ELECTRICALLY) INOPERATIVE. SWITCH PLATING COMES OFF AND B ONDS TRIGGER. 1 G 7 1 3U NC H3WE 1996091900606 19960919 00606 1996 9 19 96ZZZX4719 1 19960815 G 3710 D9181 FILTER PARKER VACUUM SYSTEM DETERIORATED D S K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 01 VACUUM SYSTEM FILTER UPPER BLACK RUBBER CAP WILL CRUMBLE IN YOUR FINGERS. NOT CURED. BOTTOM APPEARS OK. SUBMITTER STA TED VERY DANGEROUS, WILL BLOCK DOWN STREAM INSTRUMENTS. LABEL ON BOX HAD DATE 8/94 ON IT. 1996020200285 19960202 00285 SO 1996 2 2 96ZZZX472 2 19960108 G 8550 58551761 OIL SEPARATOR CESSNA 404 404CESSNA 2075901 CE CONT O520 GTSIO520M 17032 SO ENGINE OIL FROZE D O OTHER E R K VIBRATION/BUFFET PARTIAL RPM/PWR LOSS FLUID LOSS NR NOT REPORTED 1 NM 11 409EX 4040436 241003R AIR/OIL SEPARATOR OUTLET FROZE SHUT. ENGINE PUMPED OIL OVERBOARD. ENGINE FAILED, THREW ROD THROUGH CASE. 1 L 7 2 3O 3 O A25CE E7CE 1996091900607 19960919 00607 1996 9 19 96ZZZX4720 1 19960830 G 3710 441CC7 PUMP AIRBORNE PNEU SYSTEM SHAFT SEIZED B APCR K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 01 4AM103 DRIVE SHAFT IS SEIZED SOLID. UNDERSTAND THIS MAY OR MAY NOT BE NORMAL. SOME AIRBORNE REPS SAY IT IS OK. HOWEVER, MOST NEW PUMPS TURN FREELY. TECHNICIANS HAVE NO WAY TO IDENTIFY A GOOD/BAD NEW PUMP UNLESS TORQUE CRITERIA SUPPLIED. ALL A PPEARANCES INDICATE SEIZED/UNAIRWORTHY UNIT. 1996091900608 19960919 00608 GL 1996 9 19 96ZZZX4721 3 19960522 G 6114 C4716C98 HUB CESSNA 188 188B 2073007 CE MCAULY 2A34C D2A34C98 GL BLADE RETAIN CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 1220 890754 INSPECTION FOUND BLADE RETENTION THREADS IN HUB SOCKET ARE CRACKED. 1 L 7 1 3O A9CE 5 C P3EA 1996091900610 19960919 00610 CE 1996 9 19 96ZZZX4723 1 19960124 G 3230 HMX5FG ROD END BEECH 58 58P 1152744 CE NLG RETRACT FRACTURED B FC6R A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 NM 11 121Z TJ285 ROD END FAILED (FRACTURED) WHILE RETRACTING LANDING GEAR. PILOT HAD AN UNSAFE NOSE GEAR LIGHT, PILOT REPOSITIONED GEAR HANDLE TO THE DOWN POSITION. PUSH ROD TRAVELLED FORWARD PUSHING AGAINST NOSE GEAR EXTENDING AND LOCKING GEAR IN THE DOW N POSITION. CAUSE OF FAILURE WAS A CRACK IN THE NECK OF THE BEARING HOUSING. SUBMITTER RECOMMENDATION NDI TESTING OR T IME CHANGE ROD END ON AS SCHEDULED BASIS. 1 L 7 2 3O A23CE 1996091900613 19960919 00613 SO 1996 9 19 96ZZZX4726 1 19960625 G 5712 6206102 WING WALK RIB 6659501 PIPER PA28 PA28R200 7102811 SO RT WING CRACKED D K NONE O OTHER IN INSP/MAINT 1 GL 23 33075 4900 28R7535116 DURING INSPECTION, FOUND WING WALK DOUBLER RIBS CRACKED. THREE OF THE RIBS WERE CRACKED AT OUTBOARD EDGE. SUSPECT CAUS E WAS HIGH TOTAL TIME AND POSSIBLY STRESS INDUCED DURING FORMING OF STIFFENER RIBS. SUBMITTER STATED THIS SEEMS TO BE A COMMON OCCURRENCE ON PIPER PA28 SERIES WITH AT LEAST 4,000 HOURS. 1 L 7 1 3O 2A13 1996091900614 19960919 00614 CE 1996 9 19 96ZZZX4727 1 19960814 G 7714 22A667 TACH GENERATOR CESSNA 340 340A 2076405 CE ENGINE RPM INOPERATIVE B DYPR K NONE O OTHER IN INSP/MAINT 1 NM 09 340FP 10 340A0298 TACHOMETER GENERATOR FAILED 10 HOURS AFTER OVERHAUL. 1 L 7 2 3O 3A25 1996091900615 19960919 00615 CE 1996 9 19 96ZZZX4728 1 19960325 G 3230 35825094 RETRACT ROD BEECH 35 35BEECH 1151502 CE MLG BROKEN G K NONE O OTHER IN INSP/MAINT 1 EA 07 3941N 5200 D1257 INVESTIGATION OF INCIDENT SHOWS THE ROD END HAD BROKEN AT THE BOLT HOLE. THE ROD END SHOWED SIGNS OF COLD WORKING. SUB MITTER RECOMMENDS A NDI TEST BE PERFORMED ON THIS PART OR A TIME LIFE BE PLACED ON THE PART. 1 L 7 1 3O A777 1996091900616 19960919 00616 SO 1996 9 19 96ZZZX4729 2 19960819 G 7310 HOSE CESSNA 210 210E 2073416 CE CONT O520 IO520A 17032 SO ENGINE FUEL DETERIORATED G K NONE O OTHER IN INSP/MAINT 1 WP 23 4931U 21058631 1108644A FUEL HOSES NON-OPERATONAL FOR 3 YEARS ALLOWING NON-PRESSURE SIDE OF FUEL HOSES TO DRY OUT AND INSIDE OF HOSE TO DETERIOR ATE. SMALL PIECES OF RUBBER HOSE BROKE OFF AND CLOGGED FUEL LINES IN FUEL INJECTION SYSTEM. 1 H 7 1 3O 3 O 3A21 E5CE 1996091900617 19960919 00617 CE 1996 9 19 96ZZZX4730 1 19960811 G 3230 52435181 FORK BOLT CESSNA 310 310P 2074238 CE RT MLG BROKEN G K NONE O OTHER NR NOT REPORTED 1 GL 23 5741M 310P0041 BOLT BROKE AND CAUSED AFT ROD ASSY (P/N 0840125-13) TO JAM AND RT MLG WOULD NOT EXTEND FULLY. FORK BOLT WAS PREVIOUSLY CRACKED FOR SOME TIME, BUT CRACK WAS HIDDEN BY TORQUE TUBE AND NOT DETECTABLE BY VISUAL INSPECTION. 1 L 7 2 3O 3A10 1996091900620 19960919 00620 CE 1996 9 19 96ZZZX4733 1 19960829 G 7810 K1250860104 EXHAUST SYSTEM CESSNA 210 T210L 2073449 CE TURBO INLET CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 01 613CW 274 21059920 NEW EXHAUST SYSTEM WAS INSTALLED AT ENGINE CHANGE. 274 HOURS LATER DURING 100-HOUR INSPECTION, NUMEROUS CRACKS WERE FOU ND ON RIGHT SIDE OF EXHAUST, BY TURBO INLET AND FRONT RISER. 1 H 7 1 3O 3A21 1996091900622 19960919 00622 CE 1996 9 19 96ZZZX4735 1 19960831 G 2436 VR500 REGULATOR AUXILEC CESSNA 210 T210M 2073451 CE DC SYSTEM FAILED B L YWYR K NONE O OTHER NR NOT REPORTED 1 SW 09 732TG 1700 21061757 REGULATOR FIELD LINE WENT TO FULL VOLTAGE CONDITION CAUSING OVERVOLTAGE PROTECTION TO DISABLE SYSTEM. REPLACED VOLTAGE REGULATOR TO SOLVE PROBLEM. 1 H 7 1 3O 3A21 1996020200287 19960202 00287 1996 2 2 96ZZZX474 4 19960104 G 2564 1021 CYLINDER HOOVERIND 4600107 LIFE RAFT FAIL TEST B OD1R K NONE L NO TEST IN INSP/MAINT 1 EA 25 A649700 INFLATION CYLINDER FAILED HYDROSTATIC RETEST DUE TO EXCESSIVE ELASTIC EXPANSION. HOOVER IND. P/N 102-1 (165 CUBIC INCHE S), S/N A649700. CAUSE WOULD BE IN MANUFACTURING. RECOMMEND MANUFACTURER BE CONTACTED. DATE OF MFG IS 7-93, THIS WAS ITS FIRST RETEST. 1996091900927 19960919 00927 SO 1996 9 19 96ZZZX4742 2 19960806 G 8530 ROCKER BOSS CESSNA 404 404CESSNA 2075901 CE CONT O520 GTSIO520M 17032 SO NR 3 CYL EXH FAILED D K NONE E R K VIBRATION/BUFFET PARTIAL RPM/PWR LOSS FLUID LOSS NR NOT REPORTED 1 AL 01 105AK 40400833 243227R ROCKER BOSS FAILED (CRACKED) ON EXHAUST SIDE ON CYLINDER NR 3. ROCKER SHAFT PUNCHED THROUGH VALVE COVER. INSPECTED MAG NETO DRIVE COUPLING PER SB M90-11, FOUND OK. 1 L 7 2 3O 3 O A25CE E7CE 1996091900930 19960919 00930 GL 1996 9 19 96ZZZX4745 3 19960521 G 6114 D7015C87 HUB CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL BLADE SOCKET CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 220BR 832 774447 310R0973 774447 BLADE RETENTION THREADS IN ALL THREE SOCKETS ARE CRACKED. 1 L 7 2 3O 3A10 5 C P22EA 1996020200288 19960202 00288 CE 1996 2 2 96ZZZX475 1 19960105 G 5753 0523920 ROLLER ASSY 052390138 CESSNA 172 172RG 2072438 CE RT FLAP INBOARD FROZEN D K NONE O OTHER IN INSP/MAINT 1 SO 17 9627B 369 172RG0928 DURING 100-HOUR INSPECTION, NOTICED THE RT FLAP VIBRATING AS IT WAS LOWERED. INSPECTION FOUND THE AFT INBOARD ROLLER WA S FROZEN. UPON REMOVAL OF THE ROLLER, FOUND THE OUTER BRASS (?) RING HAD PARTIALLY SLID OFF OF THE INNER BEARING ASSY C AUSING THE ROLLER TO CUT INTO THE ADJOINING PLASTIC SPACER (PN S1450-5N12-050). FRICTION EVENTUALLY CAUSED THE ROLLER T O STOP TURNING. SUBMITTER STATED THIS IS THE THIRD SUCH OCCURRENCE ON DIFFERENT AIRCRAFT. PART TOTAL TIME: 368.5 HOUR S. INSTALLED WITH SERVICE KIT SK180-44. 1 H 7 1 3O 3A17 1996091900935 19960919 00935 CE 1996 9 19 96ZZZX4750 1 19960508 G 8011 MHB4016 STARTER PRESTOLITE CESSNA 172 172N 2072434 CE DRIVE END ARMATURE OPEN D K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 05 2212W 2L000488 17271516 STARTER REMOVED DUE TO OPEN IN ARMATURE. FOUND WIRE WINDINGS OF ARMATURE ON DRIVE END WERE POTTED WITH MATERIAL RESEMBL ING BODY PUTTY TO INSULATE THE WIRES. ALSO, A PIECE OF A CARDBOARD BOX WAS INSERTED BETWEEN THE COPPER FIELD LEAD AND T HE CASE FOR INSULATION. 1 H 7 1 3O NT 3A12 1996091900936 19960919 00936 EA 1996 9 19 96ZZZX4751 2 19960821 G 8520 AS16507A01 CAMSHAFT PIPER PA44 PA44180 7104402 SO LYC O360 O360E1A6 41514 EA LT ENGINE BROKE D K NONE O OTHER IN INSP/MAINT 1 SO 15 2110F 1897 WB1122M182 447995152 L45377T ENGINE WAS REMOVED FOR CAM FAILURE AT 299.20 TSMOH. A RE-GROUND CAM WAS INSTALLED BY CRS. AT 2,195.50 TSMOH, ENGINE W AS REMOVED FOR OVERHAUL AND DISASSEMBLY REVEALED CAM HAD BROKEN IN 2 PIECES WHERE THE PROP GOVERNOR GEAR P/N LW-15274 IS INSTALLED AND CRACKED WHERE THE WOODRUFF KEY P/N STD-96 IS INSTALLED TO SECURE THE PROP GOVERNOR DRIVE GEAR. THE ORIGI NAL PART NUMBER FOR THIS CAM BEFORE IT WAS RE-GROUND AND INSTALLED BY THE CRS WAS AS16508. NOTE: THIS ENGINE NEVER GAV E AN INDICATION OF FAILURE/METAL IN OIL. 1 L 7 2 3O 3 O A19S0 E286 1996091900937 19960919 00937 CE 1996 9 19 96ZZZX4752 1 19960821 G 3246 D30256 HUB ASSY MCAULY C1630030101 CESSNA 172 172M 2072418 CE MLG CRACKED D S K NONE O OTHER IN INSP/MAINT 1 SO 14 23470 5000 743933 17264090 FOUND ON TIRE CHANGE, HUB ASSY HAS 4 CRACKS ON ONE SIDE AND TWO CRACKS ON THE BACK SIDE. ALL CRACKS ARE AT BOLT HOLES. 1 H 7 1 3O NT 3A12 1996091900938 19960919 00938 CE 1996 9 19 96ZZZX4753 1 19960827 G 3230 57412026 UPLOCK HOOK CESSNA 414 414A 2075907 CE LT MLG CRACKED H A O OTHER J WARNING INDICATION CL CLIMB 1 GL 13 26635 4552 414A0531 UPLOCK HOOK FOUND CRACKED AFTER GEAR WOULD NOT RETRACT AND REMAIN IN UPLOCK. ALSO, FOUND P/N 5141204-3, CRACKED AT FORW ARD BLOCK ATTACH HOLE. HOOK CRACKED AT RADIUS OF MLG RETAINING CUT OUT. UNABLE TO DETERMINE IF DAMAGE OCCURRED UPON LA ST EXTENSION OR RETRACTION. SUBMITTER SUSPECTS WEAK HOOK DESIGN AND INADEQUATE MATERIAL THICKNESS ON SUPPORT COMPOUNDED BY AGE. 1 L 7 2 3O A7CE 1996091900940 19960919 00940 CE 1996 9 19 96ZZZX4755 1 19960821 G 3222 108820010653 NOSE GEAR BEECH 77 77 1153007 CE PISTON CLAMP FAILED G O OTHER O OTHER LD LANDING 1 EA 23 3868J 4403 WA258 AIRCRAFT LANDED, BOUNDED HARD, THEN HIT NOSE GEAR FIRST. NOSE GEAR SHEARED OFF. NO INJURIES. AIRCRAFT DAMAGE TO NOSE GEAR, PROPELLER STRIKE, AND ENGINE SUDDEN STOPPAGE. 1 L 7 1 3O A30CE 1996091900941 19960919 00941 SO 1996 9 19 96ZZZX4756 2 19960811 G 8530 BALANCE TUBE CESSNA 182 182Q 2072732 CE CONT O470 O470R 17026 SO COWL MOUNT CHAFED D P K NONE O OTHER IN INSP/MAINT 1 SW 09 414SC 18266352 BOTTOM COWL SHOCK MOUNT WAS FOUND CHAFING AGAINST INTAKE BALANCE TUBE ON THE ENGINE. THIS WOULD CAUSE AN INDUCTION LEAK . SAME CONDITION NOTICED ON SEVERAL 182'S. ACTT: 1,281 HOURS. SHOCK MOUNT, P/N S1115-29. 1 H 7 1 3O 3 O NT 3A13 E273 1996091900942 19960919 00942 CE 1996 9 19 96ZZZX4757 1 19960814 G 2434 649304 ALTERNATOR CESSNA 421 421C 2076016 CE DC SYSTEM INOPERATIVE B DYPR K NONE O OTHER IN INSP/MAINT 1 NM 09 421CW 39 E030305360 421C0137 ALTERNATOR FAILED WITHIN 40 HOURS OF OVERHAUL. A/E SN: A-80319. ARSNV2R045L. 1 L 7 2 3O A7CE 1996091900943 19960919 00943 SO 1996 9 19 96ZZZX4758 1 19960820 G 2822 2B664 PUMP PIPER PA31 PA31350 7103110 SO LT FUEL INLINE LOW PRESSURE D K NONE O OTHER IN INSP/MAINT 1 SW 99 59987 317552081 RIGHT FUEL IN-LINE PUMP, FOUND TO OPERATE INTERMITTENTLY. LEFT FUEL IN-LINE PUMP, FUEL PRESSURE WAS VERY LOW. 1 L 7 2 3O A20SO 1996091900944 19960919 00944 SO 1996 9 19 96ZZZX4759 1 19960820 G 2822 2B650 PUMP PIPER PA31 PA31350 7103110 SO RT FUEL INLINE INTERMITTENT D K NONE O OTHER IN INSP/MAINT 1 SW 99 59987 317552081 RIGHT FUEL IN-LINE PUMP, P/N 2B6-50, FOUND TO OPERATE INTERMITTENTLY. LEFT FUEL IN-LINE PUMP, P/N 2B6-64, FUEL PRESSURE WAS VERY LOW. 1 L 7 2 3O A20SO 1996091900945 19960919 00945 1996 9 19 96ZZZX4760 3 19960822 G 6112 660712268 DEICE BOOT PIPER PA42 PA421000 7104225 SO LT PROPELLER SHORTED B A GFER O OTHER B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 NM 09 431MC 1600 425527031 WHILE IN-FLIGHT, THE CREW NOTICED A SUDDEN SHOWER OF SPARKS FROM THE LEFT PROPELLER. A QUICK CHECK OF THE AMMETER SHOWE D NO UNUSUAL CURRENT DRAW. THE PROPELLER DEICE SYSTEM SHUT ITSELF OFF BEFORE THE CREW COULD TURN IT OFF. AFTER LANDING , THE PROPELLER WAS INSPECTED, A DEICE BOOT HAD SHORTED AND BURNED A HOLE APPROXIMATELY .25 INCH DEEP AND 1.50 INCH LONG ON THE LEADING EDGE APPROXIMATELY 9 INCHES FROM THE BLADE ROOT AND INTO THE COMPOSITE STRUCTURE OF THE BLADE. THE BLAD E WAS REMOVED AND SHIPPED TO AN OEM APPROVED REPAIR FACILITY FOR EVALUATION AND/OR REPAIR. IT WAS LIKELY THE SHORT WAS THE RESULT OF A SMALL FOD STRIKE. 1 L 7 2 4T RT A23SO 1996091900946 19960919 00946 CE 1996 9 19 96ZZZX4761 1 19960816 G 5541 04330106 SPAR CESSNA 150 150M 2071830 CE RUDDER CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 15 63651 4158 15077456 WHILE INSPECTING RUDDER SPAR IAW SEB94-3, 3 CRACKS WERE FOUND AROUND THE EDGE OF THE 1 INCH HOLE AT THE TOP OF THE SPAR. REPLACED SPAR IAW CESSNA SB SEB94-3. THE NEW SPAR DOES NOT HAVE THE HOLE INSTALLED. 1 H 7 1 3O 3A19 1996091900947 19960919 00947 CE 1996 9 19 96ZZZX4762 1 19960820 G 2720 081309032 BRACKET CESSNA 310 310R 2074245 CE RUDDER CONTROL FAILED B A SBVR A UNSCHED LANDING F FLT CONT AFFECTED CR CRUISE 1 GL 17 677WC 310R0100 PILOT REPORTED LOSS OF RUDDER CONTROL IN-FLIGHT. THE AIRCRAFT WAS LANDED SAFELY AND DELIVERED TO MAINTENANCE. INSPECTI ON REVEALED THE RUDDER PULLEY BRACKET L OCATED AT STA 1.67 HAD PULLED FREE FROM THE FORWARD BULKHEAD. THIS ALLOWED MISA LIGNMENT OF THE CABLES ON THE PULLEYS AND ONE PULLEY , P/N MS20220-2, FAILED CAUSING LOSS OF RUDDER CONTROL. CAUSE OF T HIS WAS UNDETERMINED. AS ACCESS TO THIS AREA IS VERY LIMITED, RECOMMEND INSTALLATION OF AN ACCESS PANEL BELOW THE AREA TO FACILITATE FUTURE INSPECTION. 1 L 7 2 3O 3A10 1996091900948 19960919 00948 CE 1996 9 19 96ZZZX4763 1 19960726 G 7921 AN9121D FITTING 635996 BEECH 36 A36 1151604 CE OIL COOLER CRACKED D S K NONE K FLUID LOSS IN INSP/MAINT 1 SW 11 7214Y E2169 UPON RETURN OF FLIGHT, MECHANIC NOTICED SUBSTANTIAL AMOUNT OF OIL ON THE BELLY OF ACFT. UPON INVESTIGATION, FOUND A FIT TING (AN912-1D) THAT EXITS THE OIL COOLER WAS CRACKED IN HALF. THIS ENGINE HAS BEEN RECONFIGURED TO A FLIGHTCRAFT TURBO , TURBO NORMALIZED SYSTEM. IT IS RECOMMENDED THIS FITTING SHOULD BE REPLACED WITH ONE MANUFACTURED FROM STEEL. 1 L 7 1 3O 3A15 1996091900949 19960919 00949 CE 1996 9 19 96ZZZX4764 1 19960724 G 7160 12503005 AIR BOX CESSNA 210 210 2073402 CE FLAPPER VALVE DEFECTIVE D O OTHER R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 SW 11 6909 2192 57514 FLAPPER VALVE IN AIR BOX WAS IN CLOSED POSITION CAUSING INDUCTION HEAT TO BE SUPPLIED TO ENGINE WITH CONTROL IN THE INDU CTION HEAT OFF POSITION. SUSPECT CAUSE, CONTROL CABLE SLIPPAGE ALLOWING INDUCTION AIR TO BE CLOSED OFF AND INDUCTION HE A T TO BE SUPPLIED TO ENGINE. SUBMITTER RECOMMENDATION, REMOVE INDUCTION HEAT SYSTEM FROM AIRCRAFT. INDUCTION AIR IS T AKEN FROM BACK OF ENGINE ANYWAY AND THIS IS A FUEL INJECTED ENGINE NOT REQUIRING INDUCTION HEAT FOR ICING CONDITIONS. 1 H 7 1 3O RT 3A21 1996091900950 19960919 00950 SO 1996 9 19 96ZZZX4765 2 19960826 G 8520 LIFTER CESSNA 182 182P 2075816 CE CONT O470 O470R 17026 SO VALVES SPALLED D K NONE O OTHER IN INSP/MAINT 1 NM 11 7466Q 215 18261106 288361R CYLINDER REMOVED FOR LOW COMPRESSION. FOUND BOTH LIFTERS STARTING TO SPALL. CHECKED ALL LIFTERS, 9 OF 12 LIFTERS SHOWE D EVIDENCE OF SPALLING. FACTORY NEW LIFTERS (ALL 12) INSTALLED. CAM APPEARS OK. THIS ENGINE FACTORY REMANUFACTURED, 6 /95. 1 H 7 1 3O 3 O NT TA13 E273 1996091900979 19960919 00979 1996 9 19 96ZZZX4768 4 19960801 G 2312 064101905 TRANSCEIVER KY196 BOLKMS 117 BK117A4 5626017 EU COCKPIT DEFECTIVE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 117NG 16305 7083 TRANSCEIVER INTERMITTENTLY SCRATCHY AND WILL NOT PICK UP STATIONS. NO CHARGE WARRANTY REPAIR. 1 G 7 2 3U H13EU 1996091900980 19960919 00980 1996 9 19 96ZZZX4769 4 19960716 G 2312 40001452500 TRANSCEIVER RT138F BOLKMS 117 BK117A1 5626010 EU COCKPIT VHF FAILED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 117M 297 S7023 INSTALLED UNIT, TURNED ON POWER, CONTROL HEAD GUARD INDICATOR LIGHTS ILLUMINATED, AND STAYED LIT EVEN WITH NO GUARD MODU LE INSTALLED. 1 G 7 2 3U H13EU 1996092600120 19960926 00120 SO 1996 9 26 96ZZZX4783 2 19960826 G 8530 VALVE GUIDE CESSNA 182 182P 2075816 CE CONT O470 O470R 17026 SO NR 1 CYLINDER OVERSIZE D K NONE O OTHER IN INSP/MAINT 1 NM 11 7466Q 215 18261106 288361R CYLINDER REMOVED FOR LOW COMPRESSION. FOUND EXT VALVE GUIDE .012 INCH OVERSIZE AT ONE END ALLOWING EXT VALVE EXCESS MOV EMENT CAUSING IMPROPER VALVE SEATING. FACTORY NEW CYLINDER INSTALLED. THIS ENGINE FACTORY REMANUFACTURED 6/95. 1 H 7 1 3O 3 O NT TA13 E273 1996092600122 19960926 00122 EA 1996 9 26 96ZZZX4785 2 19960705 G 7414 1051324 SPRING CESSNA 172 172 2072402 CE LYC O320 O320H2AD 41508 EA IMPULSE COUPLING BROKEN D L K NONE O OTHER IN INSP/MAINT 1 EA 21 75814 578 17267971 CHECKED IGNITION TIMING. FOUND APROXIMATELY 90 DEGREES OFF. REMOVED MAGNETO, FOUND IMPULSE COUPLING SPRING BROKEN. CH ECKED I-C PER AD 78-09-07R3/AD 96-12-0-7 AND FOUND SATISFACTORY. REVIEWED MAG O/H DATE FAXED BY INS. ADJ. FOUND I-C S PRING, INSP AND REUSED, CONTRARY TO MANUFACTURER'S DATA TO "REPLACE AT EACH DIS ASSEMBLY WITH NEW PARTS." 1 H 7 1 3O 3 O NT 3A12 E274 1996092600124 19960926 00124 SO 1996 9 26 96ZZZX4787 1 19960820 G 5751 88639803 RIB PIPER PA32 PA32R301 7103218 SO AILERON CRACKED D A K NONE O OTHER IN INSP/MAINT 1 SO 15 886JH 3167 32R8213006 RIB WAS FOUND CRACKED FROM NUTPLATE RIVET. AFTER REMOVING HINGE FITTING 86392-02, A 1.25 INCH CRACK WAS FOUND RUNNING A LONG THE BOTTOM OF THE NUTPLATE. USING A BORESCOPE, THE INBOARD NOSE RIB WAS ALSO FOUND TO HAVE A 1 INCH CRACK RUNNING THROUGH THE LOWER BOLT HOLE. ALTHOUGH NOT AS BAD, THE OTHER AILERON WAS IN THE SAME CONDITION. 1 L 7 1 3O A3SO 1996092600126 19960926 00126 CE 1996 9 26 96ZZZX4789 1 19960813 G 5511 07326117 RIB CESSNA 185 A185F 2072821 CE HORIZ STAB CRACKED B DYPR K NONE O OTHER IN INSP/MAINT 1 NM 09 93055 5122 18503173 WHILE DOING THE CESSNA CONTINUAL AIRWORTHINESS PROGRAM, FOUND LEADING EDGE RIB BROKEN. THIS IS A PUBLIC AIRCRAFT AND IS SUBJECTED TO MANY HOURS OF LOW LEVEL FLYING. 1 H 7 1 3O 3A24 1996092600127 19960926 00127 CE 1996 9 26 96ZZZX4790 1 19960813 G 5511 07326118 RIB CESSNA 185 A185F 2072821 CE HORIZ STAB CRACKED B DYPR K NONE O OTHER IN INSP/MAINT 1 NM 09 93055 5122 18503173 WHILE DOING THE CESSNA CONTINUAL AIRWORTHINESS PROGRAM, FOUND LEADING EDGE RIB BROKEN. THIS AIRCRAFT IS SUBJECTED TO MA NY HOURS OF LOW LEVEL FLYING. 1 H 7 1 3O 3A24 1996092600128 19960926 00128 CE 1996 9 26 96ZZZX4791 1 19960813 G 5511 073261111 RIB CESSNA 185 A185F 2072821 CE HORIZ STAB CRACKED B DYPR K NONE O OTHER IN INSP/MAINT 1 NM 09 93055 5122 18503173 WHILE DOING THE CESSNA CONTINUAL AIRWORTHINESS PROGRAM, FOUND LEADING EDGE RIB BROKEN. THIS IS A PUBLIC AIRCRAFT AND IS SUBJECTED TO MANY HOURS OF LOW LEVEL FLYING. 1 H 7 1 3O 3A24 1996092600129 19960926 00129 CE 1996 9 26 96ZZZX4792 1 19960813 G 5511 07326119 RIB CESSNA 185 A185F 2072821 CE HORIZ STAB CRACKED B DYPR K NONE O OTHER IN INSP/MAINT 1 NM 09 93055 5122 18503173 WHILE DOING THE CESSNA CONTINUAL AIRWORTHINESS PROGRAM, FOUND LEADING EDGE RIB BROKEN. THIS IS A PUBLIC AIRCRAFT AND IS SUBJECTED TO MANY HOURS OF LOW LEVEL FLYING. 1 H 7 1 3O 3A24 1996092600130 19960926 00130 CE 1996 9 26 96ZZZX4793 1 19960813 G 5511 073261110 RIB CESSNA 185 A185F 2072821 CE HORIZ STAB CRACKED B DYPR K NONE O OTHER IN INSP/MAINT 1 NM 09 93055 5122 18503173 WHILE DOING THE CESSNA CONTINUAL AIRWORTHINESS PROGRAM, FOUND LEADING EDGE RIB BROKEN. THIS IS A PUBLIC AIRCRAFT AND IS SUBJECTED TO MANY HOURS OF LOW LEVEL FLYING. 1 H 7 1 3O 3A24 1996092600133 19960926 00133 1996 9 26 96ZZZX4796 4 19960824 G 6113 0550321 BULKHEAD CESSNA 172 172Q 2072437 CE SPINNER WRONG HOLES D A K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 15 918AT 17275933 SPINNER BULKHEAD FOR THE 172Q IS THE SAME PART NUMBER AS FOR THE OTHER MODELS, 172. THE 172Q USES LARGER DIAMETER BOLTS TO ATTACH THE PROPELLER. THE BOLT HOLES IN THE SPINNER BULKHEAD ARE FOR THE SMALLER BOLTS. THE LARGER BOLTS CAN BE FO RCED INTO POSITION, DEFORMING THE BULKHEAD. 1 H 7 1 3O NT 3A12 1996092600134 19960926 00134 1996 9 26 96ZZZX4797 1 19960904 G 2822 2B664 PUMP AIRBORNE BOOST SHAFT DAMAGE D K NONE O OTHER IN INSP/MAINT 1 GL 13 2F198 PUMP SHAFT HAD DAMAGE TO IT. PUMP MAY HAVE BEEN RUN DRY. 1996092600136 19960926 00136 SW 1996 9 26 96ZZZX4799 1 19960830 G 7810 649263 EXHAUST TUBE MOONEY M20 M20K 5870220 SW NR 3 CYLINDER FLANGE FAILED D A K NONE O OTHER IN INSP/MAINT 1 WP 27 CGLEE 113 251042 APPROXIMATELY ONE-HALF OF INTAKE PIPE TO CYLINDER FLANGE BROKE OFF. FOUND ON INSPECTION BY FUEL STAINS AT FLANGE. THIS IS THE 8TH NR 3 INTAKE TUBE ON THIS ENGINE. TT: 1,037.0 HOURS. TUBES WERE CHANGED AT THE FOLLOWING TIMES/HOURS: 30. 0, 77.5, 156.0, 197.1, 225.0, 306.5, 794.3, 924.0, AND AT 1,037.2. A PREVIOUS MDR SUBMITTED BY THIS SHOP DETAILED 17 N R 3 INTAKE TUBES REPLACED ON 3 OTHER MB-1 ENGINES, IN ALL CASES DUE TO A BROKEN FLANGE, ALL IN THE SAME PLACE. RECOMME ND THAT TCM SHORTEN THE OPPOSITE END OF THE TUBE WHERE IT SLIDES IN THE COUPLING. FOUND NO CLEARANCE BETWEEN THE TUBE E ND AND THE THROTTLE BODY. ALL TCM SB/S C/W. 1 L 7 1 3O 2A3 1996092600137 19960926 00137 CE 1996 9 26 96ZZZX4800 1 19960723 G 3244 650X108PLY TIRE CESSNA 414 414A 2075907 CE MLG RUBS PLATE D L A K NONE O OTHER IN INSP/MAINT 1 CE 07 116HA 414A0501 DURING INSPECTION, BOTH GOODYEAR 6:50 X 10 8-PLY FLT CUSTOMER II TUBE TYPE TIRES FOUND DAMAGED BY BRAKE ASSY BACK PLATES . AFTER WORN PARTS OF BRAKE ASSY WERE REPLACED, NEW TIRES WERE INSTALLED. (SAME MAKE, GOODYEAR.) TIRES STILL RUBBED. INSPECTED TWO OTHER 400 SERIES AIRCRAFT ON FIELD WITH SAME TYPE GOODYEAR TIRES AND ALL WERE FOUND TO RUB ON BACK PLATES . ONE OTHER AIRCRAFT WAS CHECKED ON ANOTHER AIR FIELD WITH NO PROBLEM. NEW CONDOR BRAND TIRES WERE INSTALLED ON AIRCRA FT AND FOUND TO HAVE PLENTY OF CLEARANCE FROM BACK PLATE ASSYS. 1 L 7 2 3O A7CE 1996092600138 19960926 00138 EA 1996 9 26 96ZZZX4801 1 19960502 G 3213 FORK FRCHLD M62 M62C 3374004 EA LOWER LT MLG FAILED C O OTHER O OTHER TO TAKEOFF 1 CE 07 67481 T434341 LOWER LEFT LANDING GEAR FORK FAILED APPARENTLY DUE TO 'INTERNAL' CORROSION. DURING TAKEOFF ROLL (TIME OF FAILURE), THE LEFT TIRE WAS CAUSED TO WEDGE AGAINST UPPER STRUT. THIS EFFECTED SEVERE LEFT BRAKING AND CAUSING ACFT TO DEPART RUNWAY TO LEFT. 1 L 7 1 3R A724 1996092600139 19960926 00139 1996 9 26 96ZZZX4802 1 19960911 G 2810 CCA1550 DRAIN VALVE FUEL SUMP FAILED G S A K NONE O OTHER NR NOT REPORTED 1 EA 17 RETRAINING FEATURE ON END OF VALVE FAILED CAUSING PLUNGER TO DROP OUT. 1996092600140 19960926 00140 SO 1996 9 26 96ZZZX4803 2 19960910 G 7414 1015828Y MAGNET BENDIX SFS4RNR CONT A75 A75* 17005 SO ENGINE MAG SHAFT FAILED H A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CR CRUISE 1 EA 07 80998 MAGNETO FAILED IN-FLIGHT. MAGNET, P/N 10-15828Y, SHAFT FAILED. BROKE IN TWO PIECES AT THE INNER WOODRUFF KEY SLOT AT T HE OUTER EDGE OF THE SLOT. THIS FAILURE WAS INSIDE THE MAGNETO SO THE GEAR AND OUTWARD END OF THE SHAFT CONTINUED TO RO TATE. THE ENGINE CONTINUED RUNNING UNTIL A SUCCESSFUL LANDING WAS MADE. THE MAGNETO DRIVE GEAR TILTED PARTIALLY GRINDI NG ALUMINUM FROM THE ACCESSORY CASE CONTAMINATING THE OIL AND RESULTING IN SUBSEQUENT ENGINE OVERHAUL. THERE IS NO EVID ENCE OF A LOCK-UP OF THE MAGNETO CAUSING THE SHAFT TO SHEAR THE WAY IT DID. THE BEARINGS WERE VERY ROUGH, BUT INTACT. M AGNETO MAINTENANCE HISTORY IS UNKNOWN AND TOTAL TIME IS UNKNOWN. THE MAGNETO WAS USED ON A HOMEBUILT. ENGINE, CONTINE 3 O E213 1996092600141 19960926 00141 GL 1996 9 26 96ZZZX4804 1 19960904 G 2810 V0064 FUEL SYSTEM AMTR FALCXP FALCONXP 05658MR GL CAP VENT MALFUNCTION F O OTHER O OTHER LD LANDING 1 WP 07 647AA 200 600137 AIRCRAFT ENGINE LOST POWER ON LANDING AND COLLIDED WITH TREE DUE TO FUEL STARVATION OF ENGINE CAUSED BY LOSS OF FUEL SYS TEM VENTING. FUEL CAP LOOSES VENT FUNCTION WHEN TIGHTENED (SCREWED IN) TO FUEL TANK FILLER NECK. CAP IS THERMOS TYPE T HAT EXPANDS AS IT IS TIGHTENED. WHEN CAP IS UNSCREWED FROM FILLER NECK, VENT FUNCTION RETURNS. 1 H 7 1 3I NT EXPA1H71 1996092600142 19960926 00142 1996 9 26 96ZZZX4805 1 19960816 G 2560 B79229 BATTERY BE369 NEG LEAD DEFECTIVE D K NONE W INADEQUATE Q C IN INSP/MAINT 1 EU 01 21428 DURING OVERHAUL OF RESCUE BEACON, FOUND FAILURE WAS DUE TO BATTERY NEG LEAD FAILURE. REMAINING STOCK CHECKED AND FOUND OTHERS DEFECTIVE. BATTERIES RETURNED TO MFG AND FOUND THOSE UNITS, S/N 21425 THROUGH S/N 21527, WERE SUSPECT TO FAILURE DUE TO A PRODUCTION PROBLEM. 1996092600143 19960926 00143 CE 1996 9 26 96ZZZX4806 1 19960905 G 5330 07107005 SKIN CESSNA 182 182P 2075816 CE CENTER SECTION CORRODED D P K NONE O OTHER IN INSP/MAINT 1 NM 09 21150 18261448 BOTH CENTER SECTION SKIN AND CENTER SECTION DOUBLER BADLY CORRODED (WITH HOLES). CORROSION IS APPARENTLY DUE TO 'DRIZ-A IR' DESICCANT SPILLING ONTO CARPET, AND THEN FLOWING BETWEEN SKINS INTO GEARBOX. 1 H 7 1 3O NT TA13 1996092600144 19960926 00144 EA 1996 9 26 96ZZZX4807 2 19960528 G 8530 05K21120 CYLINDER PIPER PA28 PA28RT201 7102818 SO LYC O360 IO360C1C6 41514 EA NRS 1-2/3-4 WORN D L K NONE O OTHER IN INSP/MAINT 1 NM 09 377LC 4950 110 28R7918120 L1501751A COMPRESSION CHECK INDICATES ALL 4 CYLINDERS NOT SERVICEABLE DUE TO LOW COMPRESSION AT 110 HOURS TSO. TT: 4,950 HOURS. 1 L 7 1 3O 3 O 2A13 1E10 1996092600145 19960926 00145 EA 1996 9 26 96ZZZX4808 2 19960528 G 8530 05K21120 CYLINDER PIPER PA28 PA28RT201 7102818 SO LYC O360 IO360C1C6 41514 EA NRS 1/2-3/4 WORN D K NONE O OTHER IN INSP/MAINT 1 NM 09 377LC 4544 689 28R7918120 L277151A COMPRESSION CHECK INDICATES ALL 4 CYLINDERS NOT SERVICEABLE DUE TO LOW COMPRESSION. TSO: 689 HOURS. TT: 4,544 HOURS. 1 L 7 1 3O 3 O 2A13 1E10 1996092600146 19960926 00146 SO 1996 9 26 96ZZZX4809 1 19960801 G 8120 46C19839 TURBO PIPER PA46 PA46350P SO RT ENGINE WORN BEARINGS B MZER O OTHER J WARNING INDICATION CR CRUISE 1 GL 15 463WP 955 XFL30850 4622173 MANIFIOLD PRESSURE LOSS AT 13,000 FEET. FOUND TURBO BLADES MACHINING INTO HOUSING. (BEARING FAILURE.) THIS IS THE THI RD FAILURE OF THIS PART SUBMITTER IS AWARE OF. OTHERS RESULTED IN DEPLETION OF OIL SUPPLY TO THE POINT OF ENGINE FAILUR E. 1 L 7 1 3O RT A25SO 1996092600147 19960926 00147 EU 1996 9 26 96ZZZX4810 1 19960801 G 7921 5711012334 INLET FENCE PILATS PC12 PC12 7090550 EU OIL COOLER BROKEN B S5YR K NONE O OTHER IN INSP/MAINT 1 EA 05 62JT 677 107 PILOT PRODUCED BROKEN PART WHEN ARRIVING FOR INSPECTION. POSSIBLE TURBULENT AREA CAUSING VIBRATION AND FAILURE OF PART. SUBMITTER RECOMMENDS INSPECTING THIS AREA DURING PRE-FLIGHT AND PAY CLOSE ATTENTION DURING INSPECTION TIMES. 1 L 7 1 3T RT A78EU 1996092600148 19960926 00148 CE 1996 9 26 96ZZZX4811 1 19960830 G 2140 RE65G3R00 RESISTOR BEECH 95 E95 1153410 CE CABIN HEAT BURNED G O OTHER B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 EA 01 729EM TD713 A RESISTOR IN CABIN HEATER OVERHEAT WARNING SYSTEM FAILED AND BURNED CAUSING SMOKE IN THE CABIN 1 L 7 2 3O 3A16 1996092600149 19960926 00149 SW 1996 9 26 96ZZZX4812 1 19960813 G 2810 630183 FUEL SUMP GULSTM 500 500S 0141107 SW BAG COMP CORRODED D K NONE K FLUID LOSS IN INSP/MAINT 1 SW 15 800CB 1100 17847 HOLE CORRODED THROUGH FUSELAGE FUEL SUMP. THE DRAIN VALVE WAS REPLACED TO CORRECT A FUEL LEAK, BUT FUEL CONTINUED TO LE AK FROM THE SUMP BY THE DRAIN VALVE. WHILE WIPING FUEL OFF OF THE SUMP, THE MECHANICS FINGER POKED THROUGH THE SUMP BY THE DRAIN VALVE. THE CORROSION HAD WORKED THROUGH FROM THE INSIDE TO THE POINT THAT THE PAINT WAS ALL THERE WAS LEFT AT THAT AREA HOLDING THE FUEL IN. 1 H 7 2 3O 6A1 1996092600150 19960926 00150 SO 1996 9 26 96ZZZX4813 2 19960514 G 7322 30764 FLOAT ASSY FACET MA45 CESSNA 182 182A 2072704 CE CONT O470 O470L 17026 SO CARBURETOR DETACHED B YECR K NONE O OTHER IN INSP/MAINT 1 NM 09 88MA 850 3997983 34691 CARBURETOR WAS REMOVED AT ANNUAL INSPECTION FOR EXCESSIVE WEAR ON THROTTLE SHAFT. UPON DISASSEMBLY, ONE OF THE FLOATS W AS FOUND BROKEN FROM THE ACTUATING ARM. IT WAS NOT RUPTURED OR WORN THROUGH. FLOAT WAS DATE CODED 4-84. SUSPECT A ROU GH RUNNING ENGINE AND/OR A BAD SOLDER POINT ON THE FLOAT TO BRACKET. NOTE: THE ENGINE WAS 'OVERHAULED' 77 HOURS AGO. T HE CARBURETOR WAS NOT. 1 H 7 1 3O 3 O NT 3A13 E273 1996092600151 19960926 00151 SO 1996 9 26 96ZZZX4814 1 19960826 G 7921 455192 COOLER PIPER PA32 PA32301 7103207 SO ENGINE OIL SPLIT D O OTHER K FLUID LOSS NR NOT REPORTED 1 SO 09 8442H 1465 81E871 328106098 OIL COOLER SPLIT AND ALLOWED A VERY LARGE AMOUNT OF ENGINE OIL TO EXIT THE LOWER COWLING WITHOUT ANY VISUAL INFORMATION TO THE PILOT. 1 L 7 1 3O A3SO 1996092600152 19960926 00152 EA 1996 9 26 96ZZZX4815 2 19960720 G 7230 3108301 CT BLADE BEECH 1900 1900C 1154161 CE PWA PT6 PT6A65B 52043 EA GAS GEN FAILED A A MASR E ENGINE SHUTDOWN O OTHER CR CRUISE 1 SW 07 156YV 3059 UC156 32460GG AN IN-FLIGHT SHUT DOWN OF THE RIGHT ENGINE DUE TO THE FAILURE OF THE HOT SECTION CT BLADE. AT THE ENGINE TEAR DOWN, NOT ED ONE CT BLADE HAD LIBERATED AT THE ROOT AND ALL THE OTHER CT BLADES WERE SEVERELY DAMAGED DUE TO THE CONTACT WITH THE LIBERATED BLADE. THE CT BLADE REMAINING ROOT SECTION WAS SENT TO PRATT AND WHITNEY FOR FURTHER INVESTIGATION 2 L 7 2 4T 4 T RT A24CE E4EA 1996092600153 19960926 00153 EA 1996 9 26 96ZZZX4816 2 19960507 G 7210 310076701 SUN GEAR BEECH 1900 1900C 1154161 CE PWA PT6 PT6A65B 52043 EA POWER SECTION FAILED A A MASR E ENGINE SHUTDOWN O OTHER NR NOT REPORTED 1 SW 01 157YV 13550 13550 55C036 UC157 32512PS AN IN-FLIGHT SHUT DOWN OF THE LT ENGINE DUE TO THE FAILURE OF THE POWER SECTION. AT THE ENGINE TEAR DOWN, THE INVESTIGA TION REVEALED THE 1ST STAGE SUN GEAR HAD FAILED AND IS BEING CONSIDERED THE CAUSE OF THE SHUT DOWN. 2 L 7 2 4T 4 T RT A24CE E4EA 1996092600154 19960926 00154 NM 1996 9 26 96ZZZX4817 1 19960824 G 3232 400089002 BELLCRANK PIPER PA60 PA60601 7106010 NM GEAR DOOR FAILED B TRKR A UNSCHED LANDING P NO WARNING INDICATION CL CLIMB 1 SO 15 42WH 3969 610533131 AFTER TAKEOFF, PILOT RETRACTED GEAR AND GOT NO UP LIGHT. COULD SEE INBOARD DOOR TRAILING. PILOT LOWERED AND LANDED. B ELLCRANK WAS FOUND IN SEVERAL PIECES. OUTBOARD ROD, 400006-11, WAS BENT AND INBOARD GEAR DOOR WAS OPEN ON LANDING, SCRA PED RUNWAY, AND HAD TO BE REPLACED. NO OTHER DAMAGE FOUND AND NO MIS-RIGGING WAS FOUND. 1 M 7 2 3O RT A17WE 1996092600155 19960926 00155 CE 1996 9 26 96ZZZX4818 1 19960730 G 3710 S250016 HOSE CESSNA 182 182R 2072731 CE VACUUM FILTER DETERIORATED D K NONE O OTHER IN INSP/MAINT 1 SO 01 1481E 1676 18268180 VACUUM HOSE FROM CENTER VACUUM FILTER TO ATTITUDE INDICATOR HAS CRUMBLED, FALLING APART. NAME ON WHAT IS LEFT OF HOSES IS REDI-SEAL OR IMPERIAL EAST MAT. 1 L 7 1 3O NT 3A13 1996092600156 19960926 00156 EA 1996 9 26 96ZZZX4819 2 19960801 G 8530 VALVE PIPER PA28 PA28161 7102803 SO LYC O320 O320E3D 41508 EA ENGINE EXHAUST FAILED B BXPR A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CL CLIMB 1 EA 09 32490 1709 287515169 L3989027A ENGINE LOST POWER ON TAKEOFF. PILOT ABLE TO MAINTAIN ALTITUDE AND RETURN TO AIRPORT. VALVE APPEARS TO BE P/N 75068 WH ICH IS PRONE TO BREAKAGE WHEN USING FUEL HIGHER THAN 80/87 (REF: LYCOMING SB 404). ANY VALVES STILL IN SERVICE SHOULD BE REPLACED. 1 L 7 1 3O 3 O 2A13 E274 1996020200295 19960202 00295 CE 1996 2 2 96ZZZX482 1 19960109 G 2750 0512129 BRACKET CESSNA 185 A185F 2072821 CE FS 65.33 RT FLAP BROKEN D A A O UNSCHED LANDING OTHER F FLT CONT AFFECTED NR NOT REPORTED 1 GL 15 105NR 6106 18503956 CESSNA 185 WITH ROBERTSON STOL KIT INSTALLED WAS AIRBORNE WHEN PILOT APPLIED FLAPS AND THE AIRCRAFT STARTED TO ROLL TO T HE RIGHT. A PASSENGER REPORTED HEARING A SOUND COMING FROM THE FLOOR OF THE AIRCRAFT. PILOT PUT FLAPS BACK UP AND LAND ED AT NEAREST AIRPORT. A MECHANIC INVESTIGATED THE PROBLEM AND FOUND THE PULLEY BRACKET FOR THE RIGHT FLAP HAD COMPLETE LY BROKEN OFF, ALSO, THE PULLEY BRACKET FOR THE LEFT FLAP WAS STARTING TO CRACK. THE LOCATION OF THE PULLEY BRACKETS IS IN THE BELLY UNDER THE MIDDLE PASSENGER SEAT MOUNTED IN CENTER OF THE FUSELAGE BULKHEAD STATION 65.33. 1 H 7 1 3O 3A24 1996092600157 19960926 00157 SO 1996 9 26 96ZZZX4820 1 19960820 G 7120 MOUNT PIPER PA28 PA28R180 7102809 SO ENGINE LOWER LT CRACKED D P K NONE O OTHER IN INSP/MAINT 1 EA 23 4598J 2271 28R30475 ENGINE MOUNT WAS CRACKED AT THE CROSS-OVER TUBE AT THE LOWER LEFT SIDE OF MOUNT. MOUNT HAD BEEN PREVIOUSLY REPAIRED IN A DIFFERENT LOCATION. 1 L 7 1 3O 2A13 1996092600158 19960926 00158 GL 1996 9 26 96ZZZX4821 1 19960918 G 3230 RETRACT CYLINDER YAKLEV YAK983 YAK50 9830220 GL LT MLG MALFUNCTION D O OTHER O OTHER LD LANDING 1 CE 01 50RK 381 812001 LEFT MLG COLLAPSED AFTER LANDING ON ROLL-OUT. LANDING GEAR WAS INSPECTED FOR DAMAGE, LUBED LT GEAR AT HINGE POINTS AND CYCLED. VERIFIED GEAR WAS DOWN AND LOCKED. SAFTIED GEAR HANDLE IN DOWN POSITION FOR FERRY FLIGHT. AIRCRAFT TOTAL TIME 381.4 HOURS. ACFT IS CERTIFIED EXPERIMENTAL, EXHIBITION. IT APPEARS THE INTERNAL DOWNLOCKS IN THE LANDING GEAR RETRAC T CYLINDER DID NOT POSITIVELY ENGAGE AS GEAR WORKED PROPERLY ON JACKS. ONLY THE LEFT GEAR RETRACTED ON ROLL-OUT. 1 L 7 1 3R RT EXPA1L71 1996092600159 19960926 00159 SO 1996 9 26 96ZZZX4822 1 19960801 G 3234 752303 SELECTOR PIPER PA23 PA23250 7102308 SO MLG LEVER FAILED H L A O OTHER O OTHER AP APPROACH 1 EA 23 5064C 277405376 AIRCRAFT WAS MAKING AN APPROACH TO LANDING WHEN THE PILOT SELECTED THE LANDING GEAR DOWN POSITION. WHEN OPERATING THE L ANDING GEAR SELECTOR LEVER THE COMPONENT BROKE AWAY INTO THE PILOT'S HAND AND AS A RESULT BECAME DISCONNECTED FROM THE R EST OF THE LANDING GEAR SYSTEM. UNABLE TO LOWER THE GEAR, THE PILOT CRAWLED UNDER THE PANEL AND MANUALLY SELECTED THE G EAR DOWN POSITION FROM THE REMAINING PORTION OF THE LEVER UTILIZING A FUEL TESTER. THE GEAR WAS LOWERED AND THE AIRCRAF T LANDED WITHOUT INCIDENT. THE FAILED LANDING GEAR SELECTOR LEVER, PIPER P/N 752303, WAS THE SUBJECT OF SB NR 635, DATE D 1-3-79, AND A SUBSEQUENT AD NR 79-11-06. 1 L 7 2 3O 1A10 1996092600160 19960926 00160 GL 1996 9 26 96ZZZX4823 3 19960827 G 6111 S84B2 BLADE BEECH 35 V35A 1151544 CE MCAULY 2A36C 2A36C82 GL RETAIN THREAD CRACKED B ZJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 7917R C70591YS D8940 685951 PROPELLER SUBMITTED FOR OVERHAUL/COMPLIANCE WITH AD 89-26-08, OIL FILL MODIFICATION TO DETECT BLADE/HUB CRACKS. UPON PE NETRANT INSPECTION OF BLADE, A 1.25 INCH LONG CRACK WAS DISCOVERED IN THE SECOND RETENTION THREAD. ALSO, THE PROPELLER HUB, S/N 685951, WAS FOUND WITH SEVERE EXTERNAL CORROSION. SUBMITTER STATED CAUSE OF CRACK UNKNOWN. RECOMMEND OPERATO RS CHECK C/W AD 89-26-08. 1 L 7 1 3O 3A15 5 C P880 1996092600161 19960926 00161 SO 1996 9 26 96ZZZX4824 1 19960813 G 3211 2082900 SIDE BRACE PIPER PA24 PA24250 7102404 SO LT/RT MLG STUD CRACKED B CTKR K NONE O OTHER IN INSP/MAINT 1 WP 07 8300P 243549 SIDE BRACE STUD INSPECTED IAW AD 95-20-07. BOTH LEFT AND RIGHT STUDS CRACKED AT RADIUS OF HEAD. 1 L 7 1 3O 1A15 1996092600162 19960926 00162 EA 1996 9 26 96ZZZX4825 2 19960504 G 7414 1068255511 MAGNETO D4KB3999 MOONEY M20 M20J 5870219 SW LYC O360 IO360A3B6 41514 EA DIST BLOCK DEFECTIVE D K NONE O OTHER IN INSP/MAINT 1 SO 11 91307 K20882G 243201 L2556651A INSPECTED MAG IAW 500-HOUR INSPECTION AT 1,057 HRS TTSN AND FOUND DISTRIBUTOR BLOCK DRIVEN GEAR BEARING BROKEN LOOSE FRO M BLOCK (BROWN BLOCK). REPLACED WITH 10-682054 BLOCK. ENGINE STILL HAD ACCEPTABLE MAG DROP. APPROXIMATELY 500 HRS SINC E LAST 500-HOUR COMPLYING INSPECTION. NO 500-HOUR INSPECTION LISTED FOR MAGNETO IN LOG BOOKS. 1 L 7 1 3O 3 O 2A3 1E10 1996092600163 19960926 00163 EA 1996 9 26 96ZZZX4826 2 19960809 G 8530 CYLINDER PIPER PA23 PA23250 7102308 SO LYC O540 IO540C4B5 41532 EA NR 2 PISTON FAILED G A E UNSCHED LANDING ENGINE SHUTDOWN D E K INFLIGHT SEPARATION VIBRATION/BUFFET FLUID LOSS CR CRUISE 1 EA 13 2343Z 4191 20 278054018 L1195648A AIRCRAFT MADE EMERGENCY LANDING. RIGHT ENGINE FAILED DUE TO NR 2 CYLINDER AND PISTON DEPARTING AIRCRAFT IN-FLIGHT. CYL INDER PARTS AND SIDE COWL NEVER RECOVERED. TEAR-DOWN INSPECTION REVEALED NO APPARENT REASON FOR FAILURE. 1 L 7 2 3O 3 O 1A10 1E4 1996092600164 19960926 00164 1996 9 26 96ZZZX4827 4 19960801 G 3457 TNL2101IO GPS SYSTEM TRBNAV CESSNA 650 650 2076802 CE ACFT NAV ERRORS D K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 11 334H 650071 UNIT DOES NOT CONFORM TO ARINC 419 DATABUS STANDARDS. WHEN UNIT WAS PROPERLY INSTALLED AND CONFIGURED TO SUPPLY NAVIGAT ION INFO TO THE EFIS SYSTEM, SOME UNITS OF INFORMATION WERE ERRONEOUS. 2 L 7 2 4F A9NM 1996092600165 19960926 00165 1996 9 26 96ZZZX4828 4 19960801 G 3457 TNL2101IO GPS SYSTEM TRBNAV CESSNA 650 650 2076802 CE ACFT NAV ERRORS D K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 11 434H 6500123 UNIT DOES NOT CONFORM TO ARINC 419 STANDARDS WHEN THE UNIT WAS PROPERLY INSTALLED AND CONFIGURED TO SUPPLY NAVIGATION IN FO TO THE EFIS SYSTEM, SOME BITS OF INFORMATION WERE ERRONEOUS. 2 L 7 2 4F A9NM 1996092600166 19960926 00166 GL 1996 9 26 96ZZZX4829 2 19960202 G 7250 6877736 LABYRINTH SEAL 6898735 ALLSN 250C 250C20B 03013 GL GP TURBINE FRACTURED B YKER K NONE O OTHER IN INSP/MAINT 1 EA 17 TURBINE WAS REMOVED DUE TO RUB. UPON DISASSEMBLY, FOUND THE GP STATOR SEAL HAD FRACTURED AT THE FORWARD END OF THE BEAR ING BORE. THIS TURBINE HAD THE NEW NR 8 BEARING AND RETAINING PLATE INCORPORATED PER CEB 1326. CAUSE OF FAILURE UNKNOW N. 3 U E4CE 1996020200296 19960202 00296 CE 1996 2 2 96ZZZX483 1 19960108 G 2910 MS2951207 PLUG SEAL 51170111 CESSNA 414 414A 2075907 CE HYD FILLER FAILED B A DJFR K NONE O OTHER IN INSP/MAINT 1 EA 23 25SC 414A114 HYDRAULIC FILLER PLUG SEAL LEAKED WATER WHILE ACFT PARKED OUTSIDE. WATER WAS CIRCULATED THROUGH HYD SYSTEM DURING NORMA L OPERATION. ACFT REPOSITIONED FROM WARM HANGAR TO FREEZING TEMP. UPON PRE-FLIGHT, 1 MLG DOWNLOCK LIGHT WAS OUT AND GE AR UNSAFE LIGHT WAS LIT. UPON TROUBLESHOOTING, WATER FOUND IN ALL LANDING GEAR ACTUATORS. WHEN WATER FROZE, IT ACTUATE D DOWNLOCK SWITCH AND GAVE FALSE GEAR UNSAFE INDICATION. THIS IS SECOND OCCURRENCE ON THIS ACFT. HYD SYS CLEANED AND R EPAIRED. FILLER PLUG SEAL REPLACED. ACFT RETURNED TO SERVICE. SUBMITTER SUGGESTS REGULAR INSP OF FILLER PLUG SEAL ON ALL 400 SERIES CESSNA ACFT. 1 L 7 2 3O A7CE 1996092600167 19960926 00167 CE 1996 9 26 96ZZZX4830 1 19960830 G 2435 SWITCH WIRE LEARSIEGLER 23080002 RKWELL NA265 NA26565 7630107 CE GEN HOT LIGHT LOOSE G E ENGINE SHUTDOWN E VIBRATION/BUFFET CR CRUISE 1 EA 13 265A 1024 272 1609 46547 GENERATOR 'HOT LIGHT' CAME ON THE ANNUNCIATOR PANEL. REDUCING ENGINE POWER, LIGHT WENT OUT. CAME BACK IN WITH POWER, L IGHT CAME BACK ON. ENGINE WAS SHUT DOWN IAW FLIGHT MANUAL. STARTER/GENERATOR WAS SENT TO OVERHAUL FACILITY FOR REPAIR AND TEAR-DOWN REPORT. IT WAS NOTED THAT THERMAL SWITCH WIRE WAS LOOSE INSIDE STARTER/GENERATOR. REPAIR WAS MADE AND UN IT TESTED GOOD. 2 L 7 2 4J A2WE 1996092600168 19960926 00168 SW 1996 9 26 96ZZZX4831 1 19960904 G 2435 300SG119Q STARTER GULSTM 690TP 695A 7630519 SW START/GEN WRONG PART B GFER K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 09 695NC 893 1463 96032 DURING INSPECTION, NOTED ONE OF THE STARTER/GENERATORS HAD A DATA TAG ISSUED BY AIRCRAFT PARTS CORPORATION AND IDENTIFIE D WITH P/N 300.S.G.119Q, NOT THE LEAR SIEGLER (LUCAS) P/N 23079-000-1 REQUIRED BY THE IPC. APC CONTACTED TO INQUIRE IF EVER AN STC OR A PAH LETTER OF EQUIVALENCY HAD BEEN ISSUED AGAINST STARTER/GENERATORS FOR INSTALLATION ON COMMANDER MODE L 695A, NONE HAD. P/N 300.S.G.119Q IS SIMILAR IN MOST RESPECTS TO OTHER LEAR SIEGLER STARTER/GENERATORS INSTALLED ON ME TROLINERS AND JETSTREAM 31'S, AND APPROVALS FOR THEIR USE ON ACFT HAVE BEEN SECURED, BUT NOT FOR THE 695A. UNAPPROVED P ART INSTALLED IN AUSTRIALIA 10-92 AND WENT UNDETECTED DURING IMPORT IN 1-95, AT 1ST 100-HR INSP AFTER IMPORT AND AT FAA 1 H 7 2 4T 2A4 1996092600211 19960926 00211 EU 1996 9 26 96ZZZX4833 1 19960709 G 3243 T67G73231 MASTER CYLINDERS SLNSBY T67 T67M260 8323006 EU BRAKE FAILED B UNER K NONE O OTHER IN INSP/MAINT 1 NM 03 3102J 802 2162 AIR CREWS HAVE REPORTED AIRCRAFT BRAKE PEDALS WERE SPONGY OR HAVE FADED/FAILED DURING BRAKING APPLICATIONS. AFTER 20,00 0 HOURS OF OPERATION AT THE USAFA, BRAKE SYSTEMS STARTED TO DEVELOP PROBLEMS. REVISED BRAKE BLEEDING PROCEDURES WERE DE VELOPED, OPERATOR BRAKING APPLICATION TECHNIQUE IMPROVED AND AIRCRAFT KEPT FLYING WHILE MORE EMERGENCIES WERE DELCARED F OR BRAKE FAILURES. FINALLY, THE MASTER BRAKE CYLINDER WAS MODIFIED UNDER SAL MOD 726 (P/N T67G73213). THE ENTIRE FLEET IS BEING UPGRADED TO THE MODIFIED MASTER CYLINDER WHILE ACCUMULATING 50,000 FLYING HOURS. SAL AND PARKER/CLEVELAND HAV E BEEN TASKED TO IMPROVE THE CURRENT BRAKING SYSTEM. 1 L 7 1 3O NT A73EU 1996092600212 19960926 00212 EU 1996 9 26 96ZZZX4834 1 19960829 G 2822 2B66 FUEL PUMP SLNSBY T67 T67M260 8323006 EU FUEL BOOST FAILED B UNER K NONE O OTHER IN INSP/MAINT 1 NM 03 30723 802 2154 THE AIR CREW REPORTED LOW OR NO FUEL PRESSURE INDICATION/RISE DURING PRE-FLIGHT CHECK. FURTHER INSPECTION BY UNC MAINTE NANCE TECHNICIANS REVEALED THE FUEL PUMP DID NOT PRODUCE ANY NOISE WHEN THE FUEL PUMP BOOST SWITCH WAS TURNED ON. THERE HAVE BEEN 6 AIRBORNE ELECTRIC FUEL BOOST PUMPS (P/N 2B6-6, SAL P/N 12634036) FAILURES AT THE USAFA. AIRBORNE HAS REPOR TED THE PUMPS ARE CONTAMINATED AND HAVE FAILED. AFTER 2 YEARS AND 30,000 FLYING HOURS AT THE USAFA, ONLY 6 AIRBORNE ELE CTRIC FUEL PUMPS (P/N 2B6-6) HAVE FAILED ON 55 AIRCRAFT. THE T-3A FUEL TANK ARE FABRICATED FROM GRP (FIBERGLASS) AND SE ALED WITH FUEL RESISTANCE SEALANT. 1 L 7 1 3O NT A73EU 1996092600213 19960926 00213 EU 1996 9 26 96ZZZX4835 1 19960829 G 3242 16402000 BRAKE DISC 16402000 SLNSBY T67 T67M260 8323006 EU MLG WARPED B UNER K NONE O OTHER IN INSP/MAINT 1 NM 03 3102J 704 2162 THE AIR CREW REPORTED THE ACFT BRAKES WERE SPONGY DURING BRAKING APPLICATION. THERE HAVE BEEN MANY REPORTS BY USAF PILO TS IN THE T-3A PROGRAM PERTAINING TO SPONGY OR DEFECTIVE BRAKES. A DETAILED INSPECTION OF THIS AIRCRAFT'S BRAKING SYSTE M REVEALED A WARPED BRAKE DISC. AFTER 2 YEARS AND 30,000 FLYING HOURS AT THE USAFA, ONLY 5 CLEVELAND BRAKE DISCS (P/N 1 64-02000) HAVE WARPED ON 54 AIRCRAFT. THERE HAVE BEEN PROLBLEMS WITH THE T-3A BRAKING SYSTEM AND THE SLINGSBY MANUFACTU RED MASTER CYLINDERS (P/N T67G73231 NOW REVISED TO P/N T67G73213 LATEST REVISION). THIS OCCURRENCE DID NOT APPEAR TO IN VOLVE THE MASTER CYLINDERS AS THE DEFECTIVE COMPONENT IN THE BRAKING SYSTEM. 1 L 7 1 3O NT A73EU 1996092600214 19960926 00214 EU 1996 9 26 96ZZZX4836 1 19960829 G 3242 16402000 BRAKE DISC SLNSBY T67 T67M260 8323006 EU MLG WARPED B UNER K NONE O OTHER IN INSP/MAINT 1 NM 03 31398 537 2176 THE AIR CREW REPORTED THE AIRCRAFT BRAKES WERE SPONGY DURING BRAKING APPLICATION. THERE HAVE BEEN MANY REPORTS BY USAF PILOTS IN THE T-3A PROGRAM PERTAINING TO SPONGY OR DEFECTIVE BRAKES. A DETAILED INSPECTION OF THIS AIRCRAFT'S BRAKING S YSTEM REVEALED A WARPED BRAKE DISC. AFTER 2 YEARS AND 30,000 FLYING HOURS AT THE USAFA, ONLY 5 CLEVELAND BRAKE DISCS (P /N 164-02000) HAVE WARPED ON 54 AIRCRAFT. THERE HAVE BEEN PROBLEMS WITH THE T-3A BRAKING SYSTEM AND THE SLINGSBY MANUFA CTURED MASTER CYLINDERS (P/N T67G73231 NOW REVISED TO P/N T67G73213 LATEST REVISION). THIS IS SECOND OCCURRENCE AND DID NOT APPEAR TO INVOLVE THE MASTER CYLINDERS AS THE DEFECTIVE COMPONENT IN THE BRAKING SYSTEM. 1 L 7 1 3O NT A73EU 1996092600216 19960926 00216 GL 1996 9 26 96ZZZX4838 2 19960729 G 7412 6899093 EXCITER BOLKMS 105 BO105S 5626006 EU ALLSN 250C 250C20B 03013 GL ENGINE IGNITION FAILED B JSNR K NONE O OTHER IN INSP/MAINT 1 NM 09 204PC 648 S895 836679 START CIRCUIT BREAKER OPENED 1-2 SECONDS AFTER START INITIATED. TROUBLESHOT AND FOUND HIGH TENSION SIDE OF IGNITION EXC ITER SHORTED OUT. REPLACED EXCITER. THIS AIRCRAFT HAS CONTINUOUS IGNITION SYSTEM WHICH MUST BE OPERATED WHEN FLYING IN FALLING SNOW. THIS SYSTEM OPERATES APPROXIMATELY 25 OF LAST 30 FLIGHT HOURS. PERHAPS TOO MUCH FOR EXCITER UNIT. AIRC RAFT SHOULD INCORPORATE AUTO-RELIGHT INSTEAD. 1 G 7 2 3U 3 U H3EU E4CE 1996092600217 19960926 00217 EU 1996 9 26 96ZZZX4839 1 19960729 G 6710 D133145401E GUIDE ASSY BOLKMS 105 BO105S 5626006 EU M/R FAILED B JSNR A UNSCHED LANDING J WARNING INDICATION NR NOT REPORTED 1 NM 09 204PC 644 S895 PILOT EXPERIENCED SWITCH OVER TO SYSTEM 2 HYDRAULICS DURING FLIGHT. AIRCRAFT LANDED. RESET TO SYSTEM 1. SYSTEM SWITCH ED TO NR 2. TROUBLESHOT AND FOUND SWITCH IN 10DB4 GUIDE ASSY SHORTED. GUIDE ASSY HAD LOTS OF MOISTURE UNDER COVER. GU IDE ASSY REPLACED. AIRCRAFT HAD BEEN OPERATING IN HIGH HUMIDITY, RAIN, AND SNOW. 1 G 7 2 3U H3EU 1996020200297 19960202 00297 SO 1996 2 2 96ZZZX484 1 19960102 G 2810 710282LH TANK PIPER PA31 PA31350 7103110 SO LT WING INBD CHAFED B A WC7R K NONE K FLUID LOSS IN INSP/MAINT 1 GL 25 711LH 8111762 318152174 PILOT REPORTED 'FUEL LEAK, LEFT WING'. SEAM TAPE ON FUEL TANK BED WAS FOUND MISSING. BLADDER TANK HAD CHAFED THROUGH O N ROUGH EDGES (2 PLACES). REMOVED BLADDER AND REPLACED WITH NEW BLADDER. SUBMITTER STATED TO MAKE SURE ALL SEAMS ARE T APED TO PREVENT CHAFING. HOBBS, 2,766.8. 1 L 7 2 3O A20SO 1996092600219 19960926 00219 GL 1996 9 26 96ZZZX4841 2 19960725 G 7230 6871259 TIE BOLT 6890550 BOLKMS 105 BO105S 5626006 EU ALLSN 250C 250C20B 03013 GL COMP ROTOR UNDERSIZE B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 107AL 59038 S772 821484 DISCOVERED DEFECT DURING TOLERANCE INSPECTION. THE TIE BOLT SHOULDER UNDER SIZE BY .002 INCH, .440 INCH, BPS .4420 INCH TO .4425 INCH. 1 G 7 2 3U 3 U H3EU E4CE 1996092600220 19960926 00220 GL 1996 9 26 96ZZZX4842 2 19960719 G 7314 216002 DRIVE SHAFT 6896822 BELL 206 206L4 1182110 SW ALLSN 250C 250C30P 03013 GL FUEL PUMP WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 170AL 2991 1186 52063 DURING DISASSEMBLY FOR OVERHAUL, FOUND WORN DRIVESHAFT SPLINES (SMALL END) AND WORN INTERNAL GEAR SPLINE. (PARTS SCRAPP ED). SUSPECT IMPROPER LUBRICATION. 1 G 7 1 3U 3 U NC H2SW E1GL 1996092600221 19960926 00221 EU 1996 9 26 96ZZZX4843 1 19960719 G 6330 10510156 SUPPORT BOLKMS 105 BO105C 5626005 EU TRANSMISSION DAMAGED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 205BB 603 S58 SCHEDULED INSPECTION FOUND TRANSMISSION SUPPORT WITH MECHANICAL DAMAGE BEYOND LIMITS, CAUSED BY VIBRO-ETCHING IN TOP FLA NGE AREA. 1 G 7 2 3U H3EU 1996092600222 19960926 00222 EU 1996 9 26 96ZZZX4844 1 19960719 G 6330 10510155 SUPPORT BOLKMS 105 BO105C 5626005 EU TRANSMISSION DAMAGED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 205BB 590 S58 SCHEDULED INSPECTION FOUND TRANSMISSION SUPPORT WITH MECHANICAL DAMAGE BEYOND LIMITS - CAUSED BY VIBRO-ECTHING IN TOP FL ANGE AREA. 1 G 7 2 3U H3EU 1996092600223 19960926 00223 EU 1996 9 26 96ZZZX4845 1 19960719 G 6330 10510155 SUPPORT BOLKMS 105 BO105C 5626005 EU TRANSMISSION DAMAGED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 352TT 2519 1450 633 S59 SCHEDULED INSPECTION FOUND TRANSMISSION SUPPORT WITH MECHANICAL DAMAGE BEYOND LIMITS CAUSED BY VIBRO-ETCHING IN TOP FLAN GE AREA. 1 G 7 2 3U H3EU 1996092600224 19960926 00224 EU 1996 9 26 96ZZZX4846 1 19960719 G 6330 10510156 SUPPORT BOLKMS 105 BO105C 5626005 EU TRANSMISSION DAMAGED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 352TT 3368 1450 617 S59 INSPECTION FOUND TRANSMISSION SUPPORT WITH MECHANICAL DAMAGE BEYOND LIMITS CAUSED BY VIBRO-ETCHING IN TO FLANGE AREA. 1 G 7 2 3U H3EU 1996092600225 19960926 00225 EU 1996 9 26 96ZZZX4847 1 19960719 G 7120 10560371 LT BIPOD BOLKMS 105 BO105C 5626005 EU ENGINE MOUNTS CRACKED B S ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 352TT 10489 S59 SHOP INSPECTION (MAJOR AIRFRAME), FOUND ENGINE LT BIPOD CRACKED. 1 G 7 2 3U H3EU 1996092600226 19960926 00226 SW 1996 9 26 96ZZZX4848 1 19960625 G 6210 206010200133 BLADE BELL 206 206B 1181511 SW MAIN ROTOR CRACKED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 42AL 2827 A954 918 DAILY SERVICE CHECK FOUND M/R BLADE CRACKED ABOUT 2.50 INCHES TO ABOUT 3 INCHES RUNNING SPAN-WISE JUST OUTBOARD OF FINGE RS. 1 G 7 1 3U H2SW 1996092600227 19960926 00227 GL 1996 9 26 96ZZZX4849 2 19960719 G 7261 23030994 SCAVENGE TUBE 23035179 SKRSKY S76 S76 8143010 NE ALLSN 250C 250C30S 03013 GL GEARBOX BRACKET BROKEN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 702AL 4117 760243 CAE890588S UPON DISASSEMBLY OF GEARBOX, REMOVED OIL PUMP ASSY AND SCAVENGE TUBE. FOUND ALIGNMENT BRACKET ON SCAVENGE BROKEN. 1 G 7 2 3U 3 U H1NE E1GL 1996020200298 19960202 00298 CE 1996 2 2 96ZZZX485 1 19960101 G 2820 070009916 FUEL LINE CESSNA 182 182 2072702 CE RT SIDE CHAFED D A K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 03 3393Y 18254393 FOUND RIGHT SIDE FUEL LINE CHAFED FROM ELEVATOR CABLE. THE LINE IS BEFORE FUEL SELECTOR AND IF IT LEAKED, WOULD BE IMPO SSIBLE TO STOP DURING FLIGHT. DAMAGE OCCURRED DUE TO IMPROPER CABLE ROUTING WHILE REPAIRING EXTENSIVE FIRE WALL DAMAGE. SUBMITTER RECOMMENDS CHECKING ALL ASSOCIATED SYSTEMS WHENEVER EXTENSIVE DISASSEMBLY AND REASSEMBLY HAVE BEEN ACCOMPLIS HED. 1 H 7 1 3O NT 3A13 1996092600228 19960926 00228 NE 1996 9 26 96ZZZX4850 1 19960725 G 5510 7620205002103 TIP CAP SKRSKY S76 S76A 8143006 NE STABILIZER CORRODED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 709AL 12969 760278 DURING SCHEDULED MAINTENANCE, FOUND STABILIZER INSTALLATION WITH EXCESSIVE CORROSION. 1 G 7 2 3U H1NE 1996092600229 19960926 00229 NE 1996 9 26 96ZZZX4851 1 19960725 G 5510 7620105001107 DOUBLER SKRSKY S76 S76A 8143006 NE STABILIZER CORRODED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 709AL 12969 760278 DURING SCHEDULED MAINTENANCE, FOUND STABILIZER DOUBLER WITH EXCESSIVE CORROSION. COMPONENT P/N 7600006003011. 1 G 7 2 3U H1NE 1996092600230 19960926 00230 NE 1996 9 26 96ZZZX4852 1 19960725 G 5510 7620204001147 LONGERON SKRSKY S76 S76A 8143006 NE LT STABILIZER CORRODED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 709AL 12969 760278 DURING SCHEDULED MAINTENANCE, FOUND LT STABLIZER LONGERON WITH EXCESSIVE CORROSION. 1 G 7 2 3U H1NE 1996092600231 19960926 00231 NE 1996 9 26 96ZZZX4853 1 19960725 G 5511 762010500118 SPAR RIB SKRSKY S76 S76A 8143006 NE STABILIZER CORRODED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 709AL 12969 760278 DURING SCHEDULED MAINTENANCE, FOUND STABILIZER SPAR RIB WITH EXCESSIVE CORROSION. COMPONENAT P/N 7600006003011. 1 G 7 2 3U H1NE 1996092600232 19960926 00232 NE 1996 9 26 96ZZZX4854 1 19960725 G 5511 7620205001109 RIB SKRSKY S76 S76A 8143006 NE STABILIZER CORRODED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 709AL 12969 760278 DURING SCHEDULED MAINTENANCE, FOUND STABILIZER RIB WITH EXCESSIVE CORROSION. COMPONENT P/N 7600006003011. 1 G 7 2 3U H1NE 1996092600233 19960926 00233 NE 1996 9 26 96ZZZX4855 1 19960725 G 2520 806131 SEAT BACK ASSY SKRSKY S76 S76 8143010 NE CABIN CORRODED B S ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 769AL 6131 760048 DURING ROUTINE MAINTENANCE, FOUND SEAT BACK FRAME CORRODED THROUGH. 1 G 7 2 3U H1NE 1996092600234 19960926 00234 EU 1996 9 26 96ZZZX4856 1 19960719 G 6330 10510156 SUPPORT BOLKMS 105 BO105C 5626005 EU TRANS AREA DAMAGED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 1818X 4106 985 440 S103 A/C TRANSMISSION WAS REMOVED FOR INSPECTION. AT THIS TIME, BOTH A-FRAME STRUTS WERE REMOVED. UPON REINSTALLATION, THE STRUTS WERE INSPECTED AND PROBLEM WAS FOUND. PART AND SERIAL NUMBERS WERE ETCHED INTO TOP OF A-FRAME STRUT. THIS IS CO NSIDERED MECHANICAL DAMAGE AND IS BEYOND DAMAGE LIMITS SET IN THE BO-105 MM. 1 G 7 2 3U H3EU 1996092600235 19960926 00235 SW 1996 9 26 96ZZZX4857 1 19960817 G 6330 206033506101 RESTRAINT SPRING BELL 206 206L1 1182107 SW M/R XMSN WORN B ZV1R K NONE O OTHER IN INSP/MAINT 1 SW 03 2654 184 LK1533 45482 RESTRAINT SPRING BEARINGS WORN BEYOND LIMITS. REPLACED 2 EACH BEARINGS, P/N 206-033-509-003. 1 G 7 1 3U H2SW 1996092600236 19960926 00236 SW 1996 9 26 96ZZZX4858 1 19960727 G 6230 206010443001 DUPLEX BEARING BELL 206 206L1 1182107 SW SWASHPLATE FAILED B ZV1R K NONE O OTHER IN INSP/MAINT 1 SW 03 2654 547 1849D 45482 SWASHPLATE REMOVED DUE TO BEARING ROUGHNESS. FOUND DUPLEX BEARING BAD. BEARING PARTS DAMAGE INNER RING. INNER RING RE PLACED. SUBMITTER STATES THE THIRD BEARING FAILURE IN PAST 12 MONTHS WITH LESS THAN 1,000 HOURS TT. 1 G 7 1 3U H2SW 1996092600237 19960926 00237 SW 1996 9 26 96ZZZX4859 1 19960722 G 6330 206033506101 RESTRAINT SPRING BELL 206 206L1 1182107 SW TRANSMISSION WORN B ZV1R K NONE O OTHER IN INSP/MAINT 1 SW 03 5007F 820 LK3183 45186 RESTRAINT SPRING BEARINGS WORN BEYOND LIMITS. REPLACED BEARINGS, P/N 206-033-509-003. 1 G 7 1 3U H2SW 1996020200299 19960202 00299 CE 1996 2 2 96ZZZX486 1 19960105 G 3230 AN425A BOLT 08412259 CESSNA 310 310 2074202 CE LT MLG BELLCRANK FAILED G A K NONE O OTHER LD LANDING 1 SO 17 8199M 4500 3100199 UPON LANDING, LEFT MLG COLLAPSED. AN INSPECTION OF LANDING GEAR REVEALED THE BOLT THAT ATTACHES THE BELLCRANK ASSY TO M LG HAD FAILED. CLOSER INSPECTION OF THE BOLT REVEALED THE SHANK HAD CORROSION AND PITTING. SUBMITTER SUGGESTS TO HAVE BOLT REMOVED AT EVERY THIRD ANNUAL AND INSPECTED. 1 L 7 2 3O RT 3A10 1996092600238 19960926 00238 EU 1996 9 26 96ZZZX4860 1 19960728 G 6410 10531980 BLADE BOLKMS 105 BO105S 5626006 EU TAIL ROTOR PAINT PEEL B AC2R K NONE O OTHER IN INSP/MAINT 1 SW 03 8775 133 527 S775 THESE TWO BLADES WERE REPAIRED BY EUROCOPTERS ONLY 35.8 HOURS AGO FOR THE SAME PROBLEM. PAINT PEELING OFF EXCESSIVELY. SUBMITTER SUGGESTION: USE SUPER KOROPON AS BASE PRIMER. 1 G 7 2 3U H3EU 1996092600239 19960926 00239 EU 1996 9 26 96ZZZX4861 1 19960728 G 6410 10531980 BLADE BOLKMS 105 BO105S 5626006 EU TAIL ROTOR PAINT PEEL B AC2R K NONE O OTHER IN INSP/MAINT 1 SW 03 8775 133 528 S775 THESE TWO BLADES WERE REPAIRED BY EUROCOPTERS ONLY 35.8 HOURS AGO FOR THE SAME PROBLEM. PAINT PEELING OFF EXCESSIVELY. SUBMITTER SUGGESTION: USE SUPER KOROPON AS BASE PRIMER. 1 G 7 2 3U H3EU 1996092600240 19960926 00240 EU 1996 9 26 96ZZZX4862 1 19960508 G 6410 10531980 BLADE BOLKMS 105 BO105S 5626006 EU TAIL ROTOR PAINT PEEL B AC2R K NONE O OTHER IN INSP/MAINT 1 SW 03 8776 97 527 S776 PAINT PEELING OFF IN SHEETS. SENDING BACK FOR WARRANTY REPAIR. 1 G 7 2 3U H3EU 1996092600241 19960926 00241 EU 1996 9 26 96ZZZX4863 1 19960508 G 6410 10531980 BLADE BOLKMS 105 BO105S 5626006 EU TAIL ROTOR PAINT PEEL B AC2R K NONE O OTHER IN INSP/MAINT 1 SW 03 8776 97 528 S776 PAINT PEELING OFF IN SHEETS. SENDING BACK FOR WARRANTY REPAIR. 1 G 7 2 3U H3EU 1996092600252 19960926 00252 EU 1996 9 26 96ZZZX4867 1 19960905 G 7931 30600018 SENDER SLNSBY T67 T67M260 8323006 EU ENGINE OIL FAILED B UNER K NONE O OTHER IN INSP/MAINT 1 NM 03 3064Q 602 2151 AIRCREWS REPORT ENGINE OIL PRESSURE TOO LOW OR TOO HIGH DURING GROUND AND FLIGHT OPERATIONS. ERRONEOUS OIL PRESSURE GA UGE NEEDLE INDICATIONS HAVE CAUSED EMERGENCY LANDINGS. THE OIL PRESSURE SENDER/TRANSDUCER IS MANUFACTURED BY VDO IN GER MANY AND DISTRIBUTED/TESTED BY B. F. GOODRICH AND INSTRUMENT TECH (P/N 3060-0018, SAL P/N 12634096BFG AND 12634041IT). T HE USAFA CO AND HONDO, TX HAVE REPLACED 210 SENDER UNITS. THE SENDER IS CONNECTED TO A ROCHESTER INSTRUMENT CLUSTER. TH E SENDING UNIT AND OIL PRESSSURE GAUGE MAY HAVE AN ELECTRICAL RESISTANCE MISMATCH. THE CIRCUIT MAY BE UNBALANCED. IT I S POSSIBLE A 1050 OHM RESISTOR ADDED TO THE CIRCUIT MAY PROVIDE BETTER LASTING RESULTS. TWO YEARS AND 50,00 FLYING HO 1 L 7 1 3O NT A73EU 1996092600253 19960926 00253 GL 1996 9 26 96ZZZX4868 2 19960910 G 7323 23057869 GOVERNOR BELL 206 206B 1181511 SW ALLSN 250C 250C20J 03013 GL ENGINE MALFUNCTION D O OTHER R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 NE 05 221GP 863 BR40733 4309 CAE270674 ENGINE RPM BLEEDS OFF. UNABLE TO ADJUST, DROOPS IN-FLIGHT. REPLACED GOVERNOR. 1 G 7 1 3U 3 U H2SW E4CE 1996092600254 19960926 00254 EU 1996 9 26 96ZZZX4869 1 19960911 G 6420 109013305101 BEARING 109013305101 AGUSTA A109 A109K2 0260502 EU T/R SWASHPLATE FAILED H K NONE O OTHER IN INSP/MAINT 1 NM 08 911RX 888 10017 DURING THE PRE-FLIGHT INSPECTION, THE SEAL OF THE DUPLEX BEARING WAS OBSERVED TO BE DETACHED FROM THE BEARING. DISASSEM BLY SHOWED A TOTAL LOSS OF LUBRICANT AND SEVERAL BALLS MISSING FROM THE OUTER DUPLEX BEARING. 1 G 7 2 3U RT H7EU 1996092600256 19960926 00256 WP 1996 9 26 96ZZZX4871 1 19960822 G 6710 A21810064603 SWITCH GUARDIAN HUGHES 369 369E 4470707 WP CYCLIC TRIM MALFUNCTION D K NONE O OTHER IN INSP/MAINT 1 WP 07 503MP 201 0414E TRIM SWITCH IS INTERMITTENT. PILOT REPORTS CYCLIC WAS VERY STIFF IN THE FORE/AFT DIRECTION. REPLACED SWITCH, STICK FOR CE IS GONE, WORKS AS IT SHOULD. THIS SWITCH IS A CHRONIC PROBLEM, TOO LIGHT DUTY FOR THIS APPLICATION. 1 G 7 1 3U H3WE 1996092600257 19960926 00257 1996 9 26 96ZZZX4872 4 19960729 G 2210 391110002 ACTUATOR SPAS FAILED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 161 109 UNIT FAILED AFTER 161.1 HOURS. SPAS IS INTERMITTENT TO TEST, LIGHT COMES ON AS SOON AS SWITCH IS PUT IN TEST POSITION. 1996092600258 19960926 00258 SW 1996 9 26 96ZZZX4873 1 19960713 G 6230 206010336005 LINK ASSY BELL 206 206L1 1182107 SW PYLON WORN B ZV1R K NONE O OTHER IN INSP/MAINT 1 SW 03 PLAY IN EXCESS OF .025 INCH AT TWO PLACES. SEE BELL MM L3, FIG 62.21. AT TEAR DOWN FOUND BEARING AND SPACERS WORN. TO TAL TIME LESS THAN 1,000 HOURS AND 1 YEAR SINCE REPLACED. REPLACED 5 EACH. 1 G 7 1 3U H2SW 1996092600259 19960926 00259 1996 9 26 96ZZZX4874 4 19960809 G 2562 0025004 BATTERY MARTECH EB2BCD CESSNA 182 182A 2072704 CE ELT SPLIT H K NONE O OTHER IN INSP/MAINT 1 NM 11 3959D 4482 34659 REMOVED BATTERY FOR REPLACEMENT DURING SCHEDULED MAINTENANCE AND FOUND BATTERY PACK HAD SPLIT AND EMITTING ACID. SPLIT WAS ALONG NARROW SIDE, RUNNING APPROXIMATELY 1.50 INCH. SUSPECT CAUSE APPEARED TO BE POOR EPOXY SURROUNDING BATTERY PAC K. 1 H 7 1 3O NT 3A13 1996092600260 19960926 00260 EU 1996 9 26 96ZZZX4875 1 19960821 G 3020 AC1192 LIP HEATER STBROS SD3 SD360 8100606 EU AIR INTAKE WIRE CHAFED B WVER K NONE O OTHER IN INSP/MAINT 1 EA 09 UPON TEAR DOWN OF SHORTS 360 AIRCRAFT FOR CONVERSION TO C-23B+, IT HAS BEEN OBSERVED ON ALL MOD AIRCRAFT THAT WIRING TO THE ENGINE INTAKE LIP HEATER IS CHAFED TO BARE WIRE CONDITION AS IT EXITS THE CONDUIT TO THE HEATER IN THE LOWER ENGINE COWLS. ALSO, WIRING AFTER THE CONDUIT IS CHAFING ON THE COWL FLOOR BEFORE IT CONNECTS TO AIR INTAKE TERMINAL BOARDS NR 1 AND NR 2. SUSPECT CAUSE: WIRE HARNESS INADEQUATELY SECURED. SUBMITTER RECOMMENDS MORE FREQUENT INSPECTION. 2 H 7 2 4T A41EU 1996092600261 19960926 00261 EA 1996 9 26 96ZZZX4876 2 19960904 G 7230 ENGINE BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA RT ENG COMP FAILED H O OTHER Y ENGINE STOPPAGE CR CRUISE 1 WP 07 200FV BB299 80637 WHILE IN-FLIGHT, THE RIGHT PROPELLER STOPPED TURNING SUDDENLY. INITIAL INSPECTION REVEALED A FAILURE OF THE COMPRESSOR SECTION OF THE RIGHT ENGINE CAUSING COMPLETE STOPPAGE. ENGINE WAS REMOVED AND SENT TO PRATT AND WHITNEY, CANADA, FOR EV ALUATION. 1 L 7 2 4T 4 T A24CE E4EA 1996092600262 19960926 00262 NM 1996 9 26 96ZZZX4877 1 19960904 G 2822 1C552 PUMP AIRBORNE ISRAEL 1125 1125 NM FUEL BOOST SCREEN LOOSE B JGVR K NONE O OTHER IN INSP/MAINT 1 CE 09 232S 3961 5AB6 032 REMOVED FUEL BOOST PUMPS FOR 2,000 HOUR JET PUMP INSPECTION. FOUND INLET SCREEN ON BOOST PUMP COMING APART. LOOSE INLE T SCREEN WIRES COULD ENTER INLET OF BOOST PUMP. IAI, P/N V25W652003-503. HAVE SEEN THIS PROBLEM ON ANOTHER ASTRA. OPP OSITE BOOST PUMP INLET SCREEN IS STARTING TO FALL APART ALSO. 2 L 7 2 4F RT A16NM 1996092600263 19960926 00263 SW 1996 9 26 96ZZZX4878 1 19960826 G 3250 7500801 SPACER ASSY GULSTM 690TP 695 7630518 SW STUD STUD MISSING D K NONE O OTHER IN INSP/MAINT 1 SW 99 3U 3428 95041 NOSE WHEEL STEERING CYLINDER ACTUATOR ROD END ATTACHES TO A STUD THAT IS HELD IN PLACE BY A COLLAR ASSEMBLY USED FOR SHI MMY DAMPENING. THE STUD WAS FOUND MISSING FROM THE SPACER ASSEMBLY. SUSPECT CAUSE UNCERTAIN, POSSIBLY FAILURE OF STUD ROLL PIN BREAKAGE. STEERING CYLINDER ROD IS CLEAR OF ANY MECHANICAL LINES, ETC. DID NOT CAUSE ANY OTHER FAILURES OR BR EAKAGE. FAILURE WAS DISCOVERED ON AIRCRAFT POST-FLIGHT INSPECTION. 1 H 7 2 3T 2A4 1996092600264 19960926 00264 SO 1996 9 26 96ZZZX4879 1 19960807 G 3610 DE25479 CLAMP GULSTM G1159 G1159 3953505 SO BLEED DUCT FAILED D P O OTHER J WARNING INDICATION NR NOT REPORTED 1 GL 03 420JM 094 WHILE IN-FLIGHT, A VEE JOINT CLAMP FAILED ON THE BLEED AIR DUCT FROM THE LEFT ENGINE PYLON. THE DUCT SHIFTED, BLEED AIR LEAKED INTO THE AFT COMPARTMENT. UPON EXAMINATION, NOTICED THE EXPANSION LIMITER HAD BROKEN. WHILE REPLACING VEE CLAM P, NOTICED THE DUCTING WAS PRE-LOADED AND NEEDED TO BE LOOSENED UP CONSIDERABLY FOR THE DUCT TO LINE UP. 2 L 7 2 4F RT A12EA 1996092600265 19960926 00265 CE 1996 9 26 96ZZZX4880 1 19960710 G 4960 2T29941 RELAY CESSNA 425 425 2076018 CE APU CUT OUT FAILED D O OTHER H ELECT. POWER LOSS-50 PC CR CRUISE 1 WP 15 425BZ 4251040 RELAY CONTROLS THE APU CUT-OUT RELAY TO PREVENT USE OF WINDSHIELD HEAT WITHOUT THE GENERATOR OR APU ON-LINE. THIS RELAY SHORTED INTERNALLY WHICH POSSIBLY SENT A FALSE SIGNAL TO THE GCU WHICH CAUSED THE GENERATORS* TO GO OFF LINE IN-FLIGHT. AFTER EXTENSIVE TROUBLESHOOTING WITH CESSNA TECH SUPPORT, COULD NOT EXPLAIN WHY THIS HAPPENED IN-FLIGHT NOR COULD FIND ANY OTHER REPEATABLE CAUSE. ALL OTHER SYSTEMS OPERATE PROPERLY. *BOTH GENERATORS WENT OFF-LINE AND COULD NOT BE RESET . 1 L 7 2 3T RT A7CE 1996092600266 19960926 00266 EU 1996 9 26 96ZZZX4881 1 19960906 G 3010 LINE BAG JETSTM JETSTM3101 1500215 EU DEICE CORRODED B IUMR K NONE O OTHER IN INSP/MAINT 1 SW 11 618JX 618 FOUND ALL DEICE LINES FROM TAIL TO DISTRIBUTER VALVE CORRODED FROM INSIDE. APPROXIMATELY 20 EACH HOLES FOUND. .25 INCH - .020 INCH DIAMETER IN THE TOTAL RUN OF TUBING. 2 L 7 2 4T RT A21EU 1996092600267 19960926 00267 CE 1996 9 26 96ZZZX4882 1 19960828 G 2810 ELBOW CESSNA 441 441 2076020 CE LT WING VENT PLUGGED D K NONE O OTHER IN INSP/MAINT 1 WP 07 832AD 2894 4410311 INSPECTING LEFT WING FUEL VENT SYSTEM FOR OBSTRUCTION, FOUND MUD NEST IN ELBOW OF LINE, P/N 5700113-28, ABOUT 2.50 FEET IN FROM INLET. ALSO, FOUND OUTBOARD RIB COLLAPSED. 1 L 7 2 3T RT A28CE 1996092600268 19960926 00268 CE 1996 9 26 96ZZZX4883 1 19960828 G 3010 3D235306 FLOW CONTROL VLV CESSNA 441 441 2076020 CE RT WING DEICE PLUGGED D A O OTHER O OTHER CR CRUISE 1 WP 07 832AD 2894 4410311 WING BOOTS INFLATED AND REMAINED INFLATED UNTIL ENGINE SHUT-DOWN. THEY WOULD NOT RESET. REMOVED FLOW CONTROL EJECTOR V ALVE AND FOUND OVERBOARD PORT PLUGGED WITH MUD AND INSECT EGG SACKS. 1 L 7 2 3T RT A28CE 1996092600269 19960926 00269 CE 1996 9 26 96ZZZX4884 1 19960828 G 2810 570011327 LINE CESSNA 441 441 2076020 CE RT WING VENT PLUGGED D A A UNSCHED LANDING F FLT CONT AFFECTED CR CRUISE 1 WP 07 832AD 2894 4410311 PILOT REPORTED LOUD BANG IN-FLIGHT AND NOTED RT OUTBOARD WING WAS CAVED IN AND AILERONS WERE VERY HARD TO MOVE. SAFE LA NDING WAS MADE. BOTH TOP AND BOTTOM OF RT OUTBOARD WING PANEL WERE COLLAPSED WITH RIBS COMPRESSED FROM OUTBOARD RIB OF FUEL BAY, INBOARD 8.50 FEET, AND FROM FORWARD SPAR TO AFT SPAR. FOUND A MUD NEST IN VENT LINE 3 FEET INSIDE OF RT VENT SYSTEM. 1 L 7 2 3T RT A28CE 1996092600270 19960926 00270 WP 1996 9 26 96ZZZX4885 1 19960801 G 7710 96641754G06 PROBE DOUG DC10 DC1030 3023501 WP NR 1 ENG PT 5.4 PLUG MISSING B AY54 K NONE M W OVER TEMP INADEQUATE Q C IN INSP/MAINT 1 EA 35 832LA 46931 NR 1 ENGINE PT 5.4 PROBE WAS FOUND INSTALLED WITHOUT BLANK. AS EPR INDICATION SYSTEM IS NOT INSTALLED ON THIS AIRCRAFT, THE OPEN PORT ALLOWED HPT OUTLET GASSES TO IMPINGE ON THE CORE COWL (TITANIUM). SLIGHT LOCAL HEAT DISCOLORATION AND SO OT DEPOSITS FOUND. IT APPEARS THIS ENGINE WAS CONFIGURED FOR A/C WITH EPR SYSTEM. (BORESCOPE PLUG IS NORMALLY INSTALLE D). 2 L 7 3 4F A22WE 1996092600271 19960926 00271 CE 1996 9 26 96ZZZX4886 1 19960828 G 7830 202000331 SUPPORT FORMER 2250007 BEECH MU300 400A 1155402 CE THRUST REV CRACKED B KI2R K NONE O OTHER IN INSP/MAINT 1 CE 01 85CR 1270 2380 RK22 IN PROCESS OF ROUTINE INSPECTION, NOTICED THE STANG FAIRING SUPPORT FORMERS, OUTBOARD SIDE OF EACH ENGINE, WERE CRACKED WHERE THEY ATTACH TO STANG. BEECH SB NR 2674 APPLIES TO THIS SUBJECT, HOWEVER, NOT TO THIS SPECIFIC REVERSER PART NUMB ER. RECOMMEND REVISING SB AND REQUIRING MANDATORY INSPECTION NOT TO EXCEED 200-HOUR INTERVALS UNTIL MODIFICATION KIT IS INSTALLED. 2 H 7 2 4F RT A16SW 1996020200302 19960202 00302 NE 1996 2 2 96ZZZX489 2 19960117 G 7250 34A0062 BOLT IAE V2500 V2500A1 NE LPT ROTOR FAILED D K NONE E VIBRATION/BUFFET IN INSP/MAINT 1 SW 05 14279 50XV0014 ENGINE WAS REMOVED FROM SERVICE DUE TO VIBRATION, DISASSEMBLY OF THE ENGINE REVEALED LPT GAS PATH DAMAGE. INVESTIGATION DETERMINED SEVEN OF THIRTY-SIX, 6TH TO 7TH STAGE DISK BOLTS HAD FAILED. PRELIMINARY ANALYSIS INDICATE THE BOLTS FAILED WITH THE CHARACTERISTICS OF A STRESS CORROSION MECHANISM. 4 F E311NE 1996020200305 19960202 00305 NE 1996 2 2 96ZZZX492 2 19960105 G 7321 105970 NOZZLE HAMSTD JFC3123 BAG BAE146 BAE146200A 1500266 EU LYC ALF502 ALF502R 41580 NE PUMP FRACTURED D O OTHER R PARTIAL RPM/PWR LOSS CR CRUISE 1 WP 05 8822 F9341 2082 ENGINE ROLL-BACK IN FLIGHT. FUEL CONTROL PUMP NOZZLE IS FRACTURED CAUSING SEVERE CONTAMINATION. 2 H 7 4 4F 4 F RT A49EU E6NE 1996100300413 19961003 00413 CE 1996 10 3 96ZZZX4924 1 19960815 G 3230 12802091 DOWNLOCK PIN 123805149 CESSNA 182 R182 2072734 CE NLG ACTUATOR FAILED D A K NONE O OTHER TX TAXI/GRND HDL 1 NM 01 7362X 4890 R18200087 BOTH DOWNLOCK PINS BROKE AND KEPT NOSE GEAR FROM LOCKING. GEAR COLLAPSED DURING TAXI. CESSNA SEB 95-20 WAS C/W BY INSP ECTION 80 HOURS PRIOR. SUBMITTER SUGGES TS BAGGING THE INSPECTIONS AND MODIFYING WITH NEW DESIGN PINS AS SOON AS POSSIB LE. THESE INSPECTIONS ARE TO RECUR EACH 200 HOURS. 1 H 7 1 3O RT 3A13 1996100300414 19961003 00414 GL 1996 10 3 96ZZZX4925 3 19960913 G 6114 D5892C87 HUB MCAULY 3AF32C 3AF32C87 GL NR 1 SOCKET CRACKED B A ME4R K NONE O OTHER IN INSP/MAINT 1 SO 19 795594 DISASSEMBLED MCCAULEY PROPELLER FOR OVERHAUL - C/W AD 95-24-05R1. AFTER STRIPPING HUB, A CRACK DISCOVERED IN NR 1 BLADE SOCKET, 3 THREADS IN, 2 INCHES LONG AT THE 7 O'CLOCK POSITION. CRACK DISCOVERED USING A VISUAL 10X POWER MICROSCOPE. 5 C P22EA 1996100300415 19961003 00415 1996 10 3 96ZZZX4926 1 19960816 G 2435 03601015 BEARING LUCAS 230650181 BRUSH DRIVE END FAILED B ED2R K NONE O OTHER IN INSP/MAINT 1 SW 09 500 STARTER/GENERATOR DRIVE END BEARING FAILURE. TWO UNITS HAD BEARING FAIL AND ONE UNIT BEARING COVER DEFECTIVE. 1996100300416 19961003 00416 1996 10 3 96ZZZX4927 1 19960816 G 2435 03601015 BEARING LUCAS 230650181 BRUSH DRIVE END FAILED B ED2R K NONE O OTHER IN INSP/MAINT 1 SW 09 500 3670 STARTER/GENERATOR DRIVE END BEARING FAILURE. TWO UNITS HAD BEARING FAIL AND ONE UNIT BEARING COVER DEFECTIVE. 1996100300417 19961003 00417 1996 10 3 96ZZZX4928 1 19960816 G 2435 03601015 BEARING LUCAS 230650181 DRIVE END LOST COVER B ED2R K NONE O OTHER IN INSP/MAINT 1 SW 09 500 STARTER/GENERATOR DRIVE END BEARING FAILURE. TWO UNITS HAD BEARING FAIL AND ONE UNIT BEARING COVER DEFECTIVE. 1996100300418 19961003 00418 1996 10 3 96ZZZX4929 1 19960909 G 2822 2B664 PUMP AIRBORNE FUEL BOOST DAMAGED D K NONE O OTHER IN INSP/MAINT 1 GL 13 UPTR00139 INSPECTION FOUND PUMP WAS POSSIBLY RUN DRY CAUSING DAMAGE TO ARMATURE. SHAFT IS ALSO BADLY WORN. 1996100300419 19961003 00419 EA 1996 10 3 96ZZZX4930 2 19960909 G 8530 LW11775 PIN PLUG PIPER PA28 PA28* SO LYC O360 IO360C1C 41514 EA ENGINE CYLINDERS FAILED B PB2R K NONE O OTHER IN INSP/MAINT 1 GL 23 450 CYLINDER REMOVED FROM ENGINE DUE TO ALUMINUM IN OIL SCREEN. FOUND PIN PLUG SHAVED COMPLETELY OFF ON NR 3 CYLINDER ALLOW ING PIN TO RUB AGAINST CYLINDER WALL. THESE TYPES OF PIN PLUGS ARE A LOOSE FIT UNLIKE SUPERIOR AIR PARTS, INC., STYLE A ND WERE INSTALLED WITH CORRECT LYCOMING PART NUMBER AND FIT. REMAINING PIN PLUGS SHAVED ALSO. 1 L 7 1 3O 3 O 2A13 1E10 1996100300420 19961003 00420 GL 1996 10 3 96ZZZX4931 3 19960905 G 6114 C4716C98 HUB CESSNA 188 A188 2073004 CE MCAULY 2A34C D2A34C98 GL BLADE RETAIN CRACKED B B2PR K NONE O OTHER IN INSP/MAINT 1 SO 17 783528 783528 UPON CHEMICAL STRIPPING AND VISUAL INSPECTION, A CRACK WAS DISCOVERED IN THE BLADE RETENTION THREADS. 1 L 7 1 3O A9CE 5 C P3EA 1996100300421 19961003 00421 NE 1996 10 3 96ZZZX4932 2 19960911 G 8520 AT90114 CRANKSHAFT PWA R1340 R1340AN1 52016 NE AFT CNTRWEIGHT CRACKED B A EJ4R K NONE O OTHER IN INSP/MAINT 1 SW 11 1800 900 RE56 18171 ENGINE RECEIVED FOR OVERHAUL DUE TO CRACK IN REAR COUNTERWEIGHT. UPON INSPECTION, FOUND THE REAR COUNTERWEIGHT CRACKED IN THE 4-1/2 ORDER FLYWEIGHT LINER AREA OF CRANKSHAFT. THIS SAME CRANKSHAFT WAS FOUND CRACKED IN THE SAME AREA AT THE PR EVIOUS OVERHAUL, 900 HOURS. AT THAT TIME, CRANKSHAFT WAS RETURNED TO AIR TRACTOR TO HAVE SNOW ENGINEERING CO. SL NR 134 C/W. AD NOTE 96-15-02 DID NOT APPLY TO THIS CRANKSHAFT AS IT ALREADY HAD THE LATE PART NUMBERED COUNTERWEIGHTS INSTALL ED (AT 90133-1 AND AT 90134-1). 3 R 5E2 1996100300422 19961003 00422 EA 1996 10 3 96ZZZX4933 2 19960224 G 8520 LW17676 CRANKSHAFT BNORM BN2 BN2 1520202 EU LYC O540 O540E4C5 41532 EA FRONT MAIN CORROSION PITS B P YECR K NONE O OTHER IN INSP/MAINT 1 NM 09 XCDUT L2223640A ENGINE DISASSEMBLED AT O/H, CRANKSHAFT INSPECTED. FRONT MAIN ID FND WITH NUMEROUS CORROSION PITS, APPROX 2.0 INCHES AFT OF FRONT EDGE OF FLANGE PILOT. CRANK ASSY LW 17676, SN V721 (CRANK AND BUSHING SUBASSY LW17622) HAS ALWAYS OPERATED WI TH CONSTANT-SPEED PROP AND IS NOT INCLUDED BY MDL OR DESIGN IN INSP REQUIREMENTS OF LYC SB 505A. THIS REPAIR STATION I NSPECTS ALL CRANKS FOR INTERNAL CORROSION REGARDLESS OF MDLS AND THIS IS 2ND CONSTANT-SPEED PROP CRANK SUBMITTER HAS SEE N IN PAST MONTH WITH SERIOUS INTERNAL CORROSION. CRANKSHAFT SUGGESTS ENVIRONMENT AND OPERATION ARE KEY FACTORS IN AFFEC TING CORROSION AS WELL AS CONSTANT-SPEED/FIXED PITCH APPLICATION. SUBJECT ACFT OPERATED IN MEXICO AND HAWAII. 1 H 7 2 3O 3 O A17EU E295 1996100300423 19961003 00423 GL 1996 10 3 96ZZZX4934 1 19960901 G 7602 CONTROL CABLE AMTR VAREZE VARIEZE GL MIXTURE FAILED G K NONE O OTHER IN INSP/MAINT 1 SW 99 3LV 627 1 MIXTURE CABLE HOUSING FAILED AT BRACKET ASSY WHERE CABLE IS SECURED TO THE CARBURETOR. CABLE COULD PULL LEVER TO 'LEAN' , BUT COULD NOT PUSH TO 'RICH'. CABLE ALSO APPEARED TO BE TOO SHORT AS IT ENTERED THE BRACKET AT AN ACUTE ANGLE. THIS PREVENTED THE RETURN SPRING FROM OVERRIDING THE FRICTION OF THE CABLE HOUSING ON THE CABLE. 1 M 7 1 3O EXPA1M71 1996100300424 19961003 00424 CE 1996 10 3 96ZZZX4935 1 19960807 G 8011 36E141C STARTER BENDIX BEECH 35 C35BEECH 1151508 CE ENGINE FAILED B CKYR K NONE O OTHER IN INSP/MAINT 1 NM 03 5931C A113452 D3292 STARTER RECEIVED FROM OVERHAUL REPAIR STATION. INSTALLED AND MADE ONE START AND UNIT FAILED. STARTER SPINS, BUT WILL N OT ENGAGE. REMOVED, RETURNED TO REPAIR STATION FOR REWORK. RECOMMEND THAT REPAIR STATION CHECK OUT QUALITY OF REPAIRS/ OVERHAUL. 1 L 7 1 3O A777 1996100300425 19961003 00425 CE 1996 10 3 96ZZZX4936 1 19960806 G 3230 50452112 FORK BOLT CESSNA 402 402B 207590P CE NLG BROKEN E S K NONE O OTHER IN INSP/MAINT 1 NM 09 106GP 10509 402B1235 DURING PRE-FLIGHT AWAY FROM HOME STATION, PILOT FOUND THE NOSE LANDING GEAR FORK BOLT BROKEN AND PULLED AWAY FROM BELLCR ANK, PN 0842104-3. THE AREA WHERE THE BREAK WAS FOUND CANNOT BE INSPECTED WITHOUT REMOVING IT FROM THE BELLCRANK. 1 L 7 2 3O A7CE 1996100300426 19961003 00426 CE 1996 10 3 96ZZZX4937 1 19960911 G 5280 082210045 BRACKET CESSNA 310 310R 2074245 CE RT INB GEAR DOOR CRACKED D O OTHER J WARNING INDICATION AP APPROACH 1 EA 05 181A 11482 310R0014 WHEN PILOT SELECTED GEAR DOWN, HAD A RIGHT GEAR UNSAFE LIGHT. CYCLING AND CRANKING GEAR DID NOT HELP. LANDING WAS MADE WITHOUT INCIDENT. THE SIDE BRACE WAS OVER CENTER, BUT THE DOWNLOCK WAS NOT MADE. THE CAUSE WAS THE INBOARD GEAR DOOR FORWARD HINGE BRACKET WAS CRACKED AND PULLED OFF OF BOTTOM ATTACHING SCREWS ALLOWING DOOR TO PIVOT FORWARD AND HANG-UP O N LOWER SKIN PREVENTING THE RIGHT GEAR FROM FULLY LOCKING. 1 L 7 2 3O 3A10 1996100300427 19961003 00427 SO 1996 10 3 96ZZZX4938 1 19960813 G 2810 FUEL SYSTEM PIPER PA38 PA38112 7103812 SO LT WING WATER CONTAM D A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CL CLIMB 1 CE 05 2466D 3063 3879A0324 DURING TAKEOFF AND CLIMB, ENGINE SUFFERED A LOSS OF POWER AND STOPPAGE CAUSING AN EMERGENCY LANDING. ENGINE REGAINED PO WER AS TOUCH DOWN WAS MADE. FOUND EVIDENCE OF WATER IN LEFT FUEL TANK. PILOT STATED TANKS HAD BEEN SAMPLED PRIOR TO TA KEOFF. HIGH HUMIDITY HAD BEEN IN THE AREA FOR SEVERAL DAYS. 1 L 7 1 3O A18SO 1996100300428 19961003 00428 SO 1996 10 3 96ZZZX4939 1 19960829 G 2730 7784402 BRACKET PIPER PA38 PA38112 7103812 SO FS 134 ELEV CTL BROKEN B A EDER K NONE O OTHER IN INSP/MAINT 1 SO 15 2321D 10617 3879A0272 FOUND EXCESSIVE PLAY IN ELEVATOR CONTROL SYSTEM. FOUND BOTH PULLEY BRACKETS BROKE WHERE BOLT GOES THROUGH FIVE PULLEYS. (TRIM, RUDDER, ELEVATOR, CABLES) AT FS 134. SUBMITTER SUGGESTED DYE CHECK FOR CRACKS IMMEDIATELY. 1 L 7 1 3O A18SO 1996100300429 19961003 00429 SO 1996 10 3 96ZZZX4940 1 19960829 G 2730 7784403 BRACKET PIPER PA38 PA38112 7103812 SO FS 134 ELEV CTL BROKEN B A EDER K NONE O OTHER IN INSP/MAINT 1 SO 15 2321D 10617 3879A0272 FOUND EXCESSIVE PLAY IN ELEVATOR CONTROL SYSTEM. FOUND BOTH PULLEY BRACKETS BROKE WHERE BOLT GOES THROUGH FIVE PULLEYS. (TRIM, RUDDER, ELEVATOR, CABLES) AT FS 134. SUBMITTER SUGGESTED DYE CHECK FOR CRACKS IMMEDIATELY. 1 L 7 1 3O A18SO 1996100300430 19961003 00430 SO 1996 10 3 96ZZZX4941 1 19960826 G 3246 0313A1 WHEEL BFGOODRICH PIPER J5 J5A 7100702 SO HUB GROOVE CRACKED D K NONE O OTHER IN INSP/MAINT 1 GL 25 26946 2875 516 DURING ANNUAL INSPECTION, A 2.50 INCH CRACK WAS FOUND IN GROOVE FOR THE SNAP RING WHICH RETAINS THE OUTBOARD WHEEL FLANG E. THE WHEEL WAS REPLACED. 1 H 7 1 3O A725 1996100300431 19961003 00431 1996 10 3 96ZZZX4942 4 19960918 G 3416 3431 CASTING UNITEDINST 5934P1 CESSNA 210 210L 2073448 CE END SHAKE CREEP B EI4R K NONE O OTHER IN INSP/MAINT 1 SO 15 218SG 1031 21061225 THIS WAS A FACTORY SEALED INSTRUMENT. THE NORMAL MFG NAME TAG WAS NOT ON THE INST. A FABRICATED NAME TAG WAS ON THE TO P SURFACE OF THE INST. (A DATE OF 3-12-85 WAS STAMPED ON THE CASE). TWO CRITICAL END SHAKES MEASURED ).0005 INCH AND . 0010 INCH). SPEC CALLS FOR .0020 INCH TO .0030 INCH END SHAKE. THIS UNDER MINIMUM END SHAKE CONDITION COULD POSSIBLY C AUSE A POINTER HANG UP, (ESPECIALLY UNDER COLD OPERATING CONDITIONS). THIS INSTRUMENT ALSO HAD A CIRCULAR SCRATCH MARK ON THE BACK OF THE DISC POINTER WHICH WAS CAUSED BY THE BINDER HEAD SCREWS THAT SECURE THE DIAL OF THE INST. 1 H 7 1 3O 3A21 1996100300432 19961003 00432 1996 10 3 96ZZZX4943 4 19960918 G 3416 3431 CASTING UNITEDINST 5934P1 CESSNA 206 P206A 2073308 CE END SHAKE CREEP B EI4R K NONE O OTHER IN INSP/MAINT 1 SO 15 4654F R4957 P2060254 THIS ALTIMETER WAS RECEIVED IN A PARTICULARLY HAZARDOUS CONDITOIN. ALL THREE END SHAKES ON THE CRITICAL ROTATING SHAFTS WERE UNDER THE MINIMUM TOLERANCE. THEY MEASURED .0000 INCH, .0006 INCH, AND .0008 INCH. THE HAIR SPRING WHEEL SHAFT I S THE ONE THAT MEASURED .0000 INCH. THE FACTORY RAN COLD TESTS ON THIS PARTICULAR TYPE ATLIMETER, AND FOUND IF THE END SHAKE WAS .0004 INCH OR LESS, THE INSTRUMENTS WOULD HANG UP. FROM THIS FACTORY TEST INFORMATION, THIS INSTRUMENT WOULD DEFINITELY HANG UP UNDER A COLD ENVIRONMENT. 1 H 7 1 3O A4CE 1996100300433 19961003 00433 CE 1996 10 3 96ZZZX4944 1 19960830 G 3710 HOSE CESSNA 182 TR182 2072735 CE VACUUM DETERIORATED B LN7R K NONE O OTHER IN INSP/MAINT 1 EA 13 4952T R18201802 VACUUM HOSES NEEDED TO BE REMOVED FROM THE AIRCRAFT INSTRUMENT GYROS FOR INSTRUMENT REPLACEMENT. UPON REMOVAL, THE HOSE INNER AND OUTER CASINGS CRUMBLED. SUGGEST REPLACEMENT OF IMPERIAL EASTMAN HOSE WITH AEROQUIP '306' LOW PRESSURE HOSE. CONDITION IS NOT READILY DETECTABLE EXTERNALLY. THE HOSE CAN BE IDENTIFIED BY A RED INNERTUBE COVERED WITH FABRIC AND A BLACK OUTER CASING. 1 H 7 1 3O 3A13 1996100300435 19961003 00435 SO 1996 10 3 96ZZZX4946 1 19960828 G 2820 492052 BUSHING SCOTT 4600 PIPER PA23 PA23250 7102308 SO CROSSFEED VALVE CRACKED D S K NONE K FLUID LOSS NR NOT REPORTED 1 EA 25 40510 5214 277405241 CROSSFEED VALVE FITTING HAD NOT BEEN DISTURBED FOR AT LEAST 6 YEARS PRIOR TO A SUDDEN FAILURE WITH A BAD FUEL LEAK (ONTO STROBE POWER SUPPLY) DURING BOOST PUMP USE DURING LANDING. COULD NOT OBTAIN REPLACEMENT FITTING FROM PIPER, HAD TO REP LACE ENTIRE CROSSFEED VALVE. 1 L 7 2 3O 1A10 1996100300436 19961003 00436 CE 1996 10 3 96ZZZX4947 1 19960903 G 5540 043100127 RUDDER ASSY CESSNA 150 150 2071802 CE RUDDER SPAR ATTACH CRACKED D S A K NONE O OTHER IN INSP/MAINT 1 GL 25 5802E 1784 17302 BOTTOM RUDDER SPAR ATTACHMENT TO RUDDER HORN HAS SMALL HAIR LINE CRACK DUE TO IMPROPER FIT AT SPAR AND RIB ASSEMBLY AT R IVETS. 1 H 7 1 3O NT 3A19 1996100300437 19961003 00437 CE 1996 10 3 96ZZZX4948 1 19960903 G 5540 043100117 RUDDER ASSY CESSNA 150 150 2071802 CE RUDDER HORN ATTACH CRACKED D K NONE O OTHER IN INSP/MAINT 1 GL 25 5802E 1784 17302 BOTTOM RUDDER SPAR ATTACHMENT TO RUDDER HORN HAS SMALL HAIR LINE CRACK DUE TO IMPROPER FIT AT SPAR AND RIB ASSEMBLY AT R IVETS. 1 H 7 1 3O NT 3A19 1996100300438 19961003 00438 EA 1996 10 3 96ZZZX4949 2 19960806 G 8530 75413 PISTON CESSNA 172 172P 2072436 CE LYC O320 O320D2J 41508 EA CYLINDERS WRONG PART B PB2R K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 23 52219 250 17274443 L1227539A CUSTOMER COMPLAINED OF LOW STATIC RPM AND SLUGGISH PERFORMANACE OF AIRCRAFT. THIS CORRESPONDED WITH APPROXIMATE TIME OF A TOP OVERHAUL. PROPELLER AND TACHOMETER WERE CHECKED AND WITHIN SPECIFICATIONS. LOG BOOK ENTRIES STATING WORK DONE W AS VERY VAGUE AND NO PARTS LIST PROVIDED. ONE CYLINDER WAS REMOVED TO EXAMINE INTERNAL ENGINE CONDITION AND PARTS INSTA LLED. LOW COMPRESSION (150 HP) PISTON P/N LW75413 WERE INSTALLED INSTEAD OF HIGH COMPRESSION (160 HP) PISTON PN 75089. 1 H 7 1 3O 3 O NT 3A12 E274 1996100300439 19961003 00439 CE 1996 10 3 96ZZZX4950 1 19960610 G 5720 0823400109 BULKHEAD CESSNA 402 402B 207590P CE TIP TANK MOUNT CRACKED D A K NONE O OTHER IN INSP/MAINT 1 GL 23 6387X 3450 402B1350 DURING SCHEDULED INSPECTION, BULKHEAD WAS FOUND CRACKED AND BUCKLED AT UPPER INBD ATTACHMENT TO FUEL TANK. INITIAL CRAC K APPEARS TO HAVE STARTED AT RIVET HOLE ON FLANGE ATTACHING TANK SKIN TO BULKHEAD. THIS RIVET HOLE HAD INSUFFICIENT EDG E DISTANCE. CRACK PROGRESSED TO NUTPLATE FOR BONDING STRAP ATTACHMENT AND BEYOND. THE WEAKNESS CAUSED TWO MORE CRACKS AT UPPER ATTACHMENT OF BULKHEAD TO TANK & SUBSEQUENT BUCKLING. THE AFT TIP TANK ATTACHMENT HAD LOST 50 PERCENT OF ITS I NTEGRITY AND WAS IN DANGER OF FAILURE. BULKHEAD WAS REPLACED. 1 L 7 2 3O A7CE 1996100300440 19961003 00440 NM 1996 10 3 96ZZZX4951 1 19960819 G 2820 50520 LINE UNIVAR 415 A2ALON 0540102 NM TANK DRAIN CORRODED H A K NONE K FLUID LOSS IN INSP/MAINT 1 CE 09 6567Q 2785 A67 FUEL SMELL IN CABIN. ALUMINUM TUBING FOR FUSELAGE TANK DRAIN LINE IN CONTACT WITH FRESH AIR LINE HOSE. CORROSIVE ACTIO N BETWEEN LINE AND HOSE ALLOWED FUEL TO LEAK FROM DRAIN LINE. 1 L 7 1 3O A787 1996100300441 19961003 00441 CE 1996 10 3 96ZZZX4952 1 19960810 G 5543 3566004323 HORN BEECH 35 S35 1151532 CE LT RUD TRIM TAB BROKEN D A UNSCHED LANDING E VIBRATION/BUFFET CL CLIMB 1 SW 99 6851Q 3485 D7500 SHORTLY AFTER TAKEOFF, PLANE STARTED TO SHUDDER VIOLENTLY. PILOT THOUGHT PROPELLER TIP BROKE. AN IMMEDIATE EMRGENCY LA NDING WAS MADE ON AN INTERSECTING RUNWAY. UPON INSPECTION, LEFT TRIM TAB HORN FOUND BROKEN AND TRIM WIRE LOOSE PART BRO KE MIDWAY BETWEEN RVET AND BOLT HOLE. 1 L 7 1 3O 3A15 1996100300442 19961003 00442 SO 1996 10 3 96ZZZX4953 2 19960610 G 8540 643259AD ADAPTER CESSNA 421 421B 2076014 CE CONT O520 GTSIO520D 17032 SO STARTER DRIVE FAILED D K NONE O OTHER IN INSP/MAINT 1 GL 23 65AE 857 421B0953 219417R DURING SCHEDULED OIL CHANGE, A LARGE QUANTITY OF FERROUS PARTICLES WERE FOUND IN OIL FILTER AND ON DRAIN PLUG. INVESTIG ATION REVEALED BEARING FAILURE OF STARTER DRIVE ADAPTER. FORWARD PILOT BEARING WAS COMPLETELY GONE AND CASE BORE DAMAGE D. AFT BEARING SUPPORTING COUNTERWEIGHT WAS WORN AND SLOPPY. COMPLETE ENGINE SENT FOR REPAIR. 1 L 7 2 3O 3 O A7CE E7CE 1996100300443 19961003 00443 EA 1996 10 3 96ZZZX4954 2 19960619 G 7414 K3822 DISTRIBUTOR BLK SLICK 4250 BEECH 23 C23 1151242 CE LYC O360 O360A4K 41514 EA RT MAGNETO DEFECTIVE G K NONE O OTHER IN INSP/MAINT 1 WP 01 66343 1188 4040022 M2206 L12681936A DISASSEMBLED RT MAGNETO. FOUND EXCESSIVE CARBON RESIDUE IN COIL AREA. FURTHER INVESTIGATION REVEALED THE ROTOR ARM ON GEAR ASSY HAD BECOME LOOSE ALLOWING APPROXIMATELY 30 DEGREE MOVEMENT SIDE TO SIDE. SUBMITTER RECOMMENDS 500-HOUR INSPEC TION OF BLOCK AND GEAR ASSY IN FAA SAFETY RECOMMENDATION. 1 L 7 1 3O 3 O A1CE E286 1996100300444 19961003 00444 CE 1996 10 3 96ZZZX4955 1 19960831 G 3246 D302529 HUB CESSNA 172 172M 2072418 CE WHEEL CRACKED B BXSR K NONE O OTHER IN INSP/MAINT 1 EA 09 6814H 2734 17265594 INSPECTION FOUND HUB CRACKED 2 PLACES. 1 H 7 1 3O NT 3A12 1996100300445 19961003 00445 SO 1996 10 3 96ZZZX4956 1 19960809 G 5540 54030987 HINGE AYRES S2 S2RNORMAL 7630202 SO RUDDER TOP FAILED G P A UNSCHED LANDING D INFLIGHT SEPARATION NR NOT REPORTED 1 EA 23 5521X 857 1721R THE TOP HALF OF THE RUDDER SEPARATED AND DEPARTED ACFT LANDING ON NEW YORK THRUWAY. UNEVENTFUL LANDING MADE. INVESTIGA TION FOUND THE TOP RUDDER HINGE ('NEW' TYPE TRIPLE DESIGN) FAILED FIRST FOLLOWED BY STRUCTURAL OVERLOAD OF RUDDER TUBULA R SPAR, AND SUBSEQUENT RUDDER SEPARATION APPROXIMATELY 6 INCHES BELOW TOP HINGE. 'NEW' TYPE TRIPLE HINGE INSTALLED PER AD 79-10-10 ON 6-15-91. TRIPLE HINGE TT: 857 HOURS. TOTAL ACFT TIME: 5,420.7 HOURS. 1 L 7 1 3R NC A3SW 1996100300447 19961003 00447 SO 1996 10 3 96ZZZX4958 2 19960705 G 8520 631716 CRANKSHAFT CESSNA 210 T210M 2073451 CE CONT O520 TSIO520H 17040 SO PROPELLER FLANGE FAILED B MW2R K NONE O OTHER NR NOT REPORTED 1 GL 17 7398M 21062018 506302 PROPELLER AND CRANKSHAFT PROPELLER FLANGE SEPARATED FROM ENGINE. 1 H 7 1 3O 3 O 3A21 E8CE 1996100300669 19961003 00669 GL 1996 10 3 96ZZZX4959 3 19960819 G 6110 AN6H34A BOLT UNIVAR 415 A2ALON 0540102 NM MCAULY 1A105 1A105SCM GL PROPELLER FAILED H A K NONE W INADEQUATE Q C IN INSP/MAINT 1 CE 09 6567Q 2785 A67 WHEN BOLT WAS REINSTALLED AND PROPELLER TORQUE APPLIED, THE BOLT BROKE. FURTHER INSPECTION OF THE BOLT REVEALED A MANUF ACTURER'S DEFECT. THE BOLT CHANGES FROM COARSE THREAD TO FINE THREAD. THERE ARE NO LOG BOOK ENTRIES SHOWING THE BOLT E VER BEING CHANGED OUT. THE CHANGE OVER FROM COARSE TO FINE THREAD ALSO NARROWS THE DIAMETER OF THE BOLT. 1 L 7 1 3O A787 5 N P918 1996100300670 19961003 00670 CE 1996 10 3 96ZZZX4960 1 19960705 G 5753 05239018 SUPPORT ASSY 05239011 CESSNA 172 172A 2072404 CE RT FLAP ASSY EXCESS WEAR H A K NONE O OTHER IN INSP/MAINT 1 GL 25 7558T 4415 47158 DURING INSPECTION OF FLAPS PER CESSNA SEB 95-3, FOUND ALL FLAP SUPPORTS HEAVILY WORN AND SCORED. INSTALLED FLAP SUPPORT KIT SK180-44. NEW SUPPORTS ARE HEAVIER AND FLANGED FOR STIFFNESS. SUBMITTER RECOMMENDS THIS SB BECOME AN AD. 1 H 7 1 3O 3A12 1996100300671 19961003 00671 CE 1996 10 3 96ZZZX4961 1 19960705 G 5753 05239019 SUPPORT ASSY 0523901 CESSNA 172 172A 2072404 CE LT FLAP ASSY EXCESS WEAR H K NONE O OTHER IN INSP/MAINT 1 GL 25 7558T 4415 47158 DURING INSPECTION OF FLAPS PER CESSNA SEB 95-3, FOUND ALL FLAP SUPPORTS HEAVILY WORN AND SCORED. INSTALLED FLAP SUPPORT KIT SK 180-44. NEW SUPPORTS ARE HEAVIER AND ARE FLANGED FOR STIFFNESS. SUBMITTER RECOMMENDS THIS SB BECOME AN AD. 1 H 7 1 3O 3A12 1996100300672 19961003 00672 CE 1996 10 3 96ZZZX4962 1 19960705 G 5753 05239019 SUPPORT ASSY 05239011 CESSNA 172 172A 2072404 CE RT FLAP ASSY EXCESS WEAR H K NONE O OTHER IN INSP/MAINT 1 GL 25 7558T 4415 47158 DURING INSPECTION OF FLAPS PER CESSNA SEB 95-3, FOUND ALL FLAP SUPPORTS HEAVILY WORN AND SCORED. INSTALLED FLAP SUPPORT KIT SK 180-44. NEW SUPPORTS ARE HEAVIER AND FLANGED FOR STIFFNESS. SUBMITTER RECOMMENDS THIS SB BECOME AN AD. 1 H 7 1 3O 3A12 1996100300673 19961003 00673 CE 1996 10 3 96ZZZX4963 1 19960903 G 5511 043200117 SPAR CESSNA 150 150 2071802 CE HORIZ STAB CRACKED H S A K NONE O OTHER IN INSP/MAINT 1 GL 25 7734E 5817 17534 CRACK FOUND IN LT FRONT SPAR OF HORIZONTAL STABILIZER JUST INBOARD OF LT ATTACH RIB. CRACK APPEARED TO STOP UNDER SIDE AT FUSELAGE CONTACT POINT 2 INCHES FROM FRONT SPAR. SUSPECT CAUSE WAS WEAR INTO STABILIZER SKIN FROM FUSELAGE SKIN EDGE CONTACT. FUSELAGE SKIN RELIEVED TO PREVENT CONTACT. SEE FIGURE 8, CESSNA IPC MODEL 150. 1 H 7 1 3O NT 3A19 1996100300674 19961003 00674 CE 1996 10 3 96ZZZX4964 1 19960903 G 5512 043200146 SKIN CESSNA 150 150 2071802 CE HORIZ STAB CRACKED H K NONE O OTHER IN INSP/MAINT 1 GL 25 7734E 5817 17534 CRACK FOUND IN LT FRONT SPAR OF HORIZONTAL STABILIZER JUST INBOARD OF LT ATTACH RIB. CRACK APPEARED TO STOP UNDER SIDE AT FUSELAGE CONTACT POINT 2 INCHES FROM FRONT SPAR. SUSPECT CAUSE WAS WEAR INTO STABILIZER SKIN FROM FUSELAGE SKIN EDGE CONTACT. FUSELAGE SKIN RELIEVED TO PREVENT CONTACT. SEE FIGURE 8, CESSNA IPC MODEL 150. 1 H 7 1 3O NT 3A19 1996100300675 19961003 00675 SO 1996 10 3 96ZZZX4965 1 19960906 G 3246 HORN 2400 MAULE M7 M7235 5460170 SO WATER RUDDER ATTACH FAILED D S K NONE O OTHER NR NOT REPORTED 1 NM 03 77627 876 1155 4104C THIS PART IS THE EXTEND/RETRACT HORN ON THE WATER RUDDER OF CAPRE, INC., STRAIGHT FLOATS, MODEL 2400, SN'S 1155, 1156, I NSTALLED ON THIS MAULE. THE SPRING ATTACH POINT FAILED AS A RESULT OF MATERIAL LOSS DUE TO RUST/CORROSION. SUBMITTER W OULD SUGGEST MORE MATERIAL IN THE PART, GREATER HOLE TO EDGE DISTANCE. THE AIRCRAFT HAD SEEN SALT WATER SERVICE, BUT IS CURRENTLY IN A FRESH WATER LAKE. 1 H 7 1 3O NC 3A23 1996100300676 19961003 00676 SO 1996 10 3 96ZZZX4966 1 19960706 G 2410 9907200 PULLEY PIPER PA32 PA32R301 7103218 SO ALTERNATOR BELT FAILED D O OTHER H ELECT. POWER LOSS-50 PC AP APPROACH 1 SO 03 1334 IDLER PULLEY FAILED CAUSING ELECTRICAL FAILURE. 1 L 7 1 3O A3SO 1996100300677 19961003 00677 1996 10 3 96ZZZX4967 1 19960910 G 2437 3E13898 AMMETER BFGOODRICH PROP DEICE MISMARKED B APCR K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 01 5260713 AMMETER FOR PROPELLER DEICE SYSTEM, PIPER PN 548-084, APPEARS MIS-MARKED. OLD UNIT GREEN ARC IS FROM 20-24 AMPS. NEW U NIT MARKED 17-24 AMPS. NORMAL DRAW ON SYSTEM IS 17-18 AMPS. OLD METER SHOWS 17 AMPS, BUT THAT IS BELOW GREEN ARC, WHIC H CAUSES PILOTS TO SQUAWK SYSTEM, EVEN THOUGH IT WORKS PROPERLY. 1996100300678 19961003 00678 CE 1996 10 3 96ZZZX4968 1 19960912 G 7160 12507024 AIR BOX CESSNA CESSNA 207 207 2073602 CE CARB INLET DOOR LOOSE D K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 01 INSPECTION OF AIR BOX FOUND ALTERNATE AIR DOOR LOOSE ON SHAFT WITH NUTS AND SCREWS TIGHT, AND AT OTHER END OF DOOR, DOES NOT SEAL ALLOWING UNFILTERED AIR INJESTED. CONFIRMED ALTERNATE AIR DOOR SHOULD BE TIGHT ON SHAFT, WITH CESSNA TECH SER VICES. SUSPECT HOLES IN SHAFT FOR DOOR ELONGATED TO FIT SCREWS WHICH REDUCES NEEDED MATERIAL ON THE SHAFT. IF SHAFT BR EAKS, PIECES OF MATERIAL WILL BE INJESTED CAUSING A LACK OF POWER OR LOSS OF POWER. 1 H 7 1 3O A16CE 1996100300679 19961003 00679 SO 1996 10 3 96ZZZX4969 1 19960822 G 5320 86444802 SPAR 86444800 PIPER PA44 PA44180 7104402 SO NOSE CONE CRACKED D S K NONE O OTHER IN INSP/MAINT 1 SW 99 2153B 5900 447995099 DURING 100-HOUR INSPECTION, BOTH SPARS WERE DETERMINED TO HAVE CRACKS IN THE 'S' ANGLE REINFORCEMENT AT LOWER AFT BOLT H OLE FOR DRAG LINK MOUNTING BRACKET. CRACKS RAN LENTGHWISE AND EXTENDED PAST BOLT HOLE IN BOTH DIRECTIONS APPROXIMATELY ONE INCH. THIS IS THE SECOND SEMINOLE FOUND WITH THIS ON, AND IT IS A VERY DIFFICULT AREA TO ACCESS AND INSPECT. 1 L 7 2 3O A19S0 1996020200310 19960202 00310 SO 1996 2 2 96ZZZX497 1 19960118 G 3246 GYS187C35 BOLT GULSTM G1159 G1159 3953505 SO WHEEL HALF BROKEN B GJQR K NONE O OTHER IN INSP/MAINT 1 NM 01 26WP 24 AFTER WHEEL CHANGE WHEN REMOVING NUTS FROM WHEEL HALF RETAINER BOLTS, 1 BOLT WAS FOUND BROKEN. WAS STILL IN BOLT HOLE, BUT BECAME 2 PIECES WHEN PUTTING WRENCH ON NUT TO REMOVE. THIS BOLT HAD 281.5 HOURS AND 228 LANDINGS SINCE LAST MAGNAFL UXED. INSPECTION AND ESTIMATED TOTAL TIME OF 840 HOURS AND 660 LANDINGS. 2 L 7 2 4F RT A12EA 1996100300681 19961003 00681 WP 1996 10 3 96ZZZX4971 2 19960906 G 7230 3101375 BEARING MTSBSI MU2 MU2B20 5780407 SW GARRTT TPE331 TPE3311 01514 WP COMPRESSOR FAILED D K NONE O OTHER IN INSP/MAINT 1 SW 15 89CR 1246 233 34008 89CR FAILURE. ENGINE S/N 34008. THE DATE OF THE FAILURE WAS 6-28-96. THE ENGINE TOTAL TIME SINCE OVERHAUL WAS 2,603.5 HOURS AND THE AIRCRAFT TOTAL TIME WAS 5,554.1 HOURS. THE TOTAL CYCLES SINCE OVERHAUL ON THE ENGINE WERE 3,315.1 HOURS. TORE THE ENGINE DOWN AND DISCOVERED THE COMPRESSOR BEARING HAD FAILED. COMPRESSOR BEARING HAD 246.5 HOURS SINCE NEW W HEN IT WAS INSTALLED ON THIS ENGINE AT TOTAL TIME SINCE OVERHAUL 1,604.4 HOURS ON 8-24-94. THE COMPRESSOR BEARING HAD1, 245.6 HOURS IN IT AT THE TIME OF THE FAILURE. 1 H 7 2 3T 3 T A2PC E3WE 1996100300683 19961003 00683 1996 10 3 96ZZZX4973 1 19960913 G 2822 2B664 PUMP AIRBORNE FUEL BOOST DAMAGED D K NONE O OTHER IN INSP/MAINT 1 GL 13 6E415 INSPECTION FOUND ARMATURE SHAFT DAMAGE BY SPACERS WEARING A GROOVE IN SHAFT. 1996100300684 19961003 00684 1996 10 3 96ZZZX4974 1 19960913 G 2822 2B729 PUMP AIRBORNE FUEL BOOST SHAFT WORN D K NONE O OTHER IN INSP/MAINT 1 GL 13 7E1240 INSPECTION FOUND HIGH WEAR ON ARMATURE SHAFT. PUMP MAY HAVE BEEN RUN DRY. 1996100300685 19961003 00685 1996 10 3 96ZZZX4975 1 19960913 G 2822 2B633 PUMP AIRBORNE FUEL BOOST DAMAGE D K NONE O OTHER IN INSP/MAINT 1 GL 13 8W132 INSPECTION FOUND ARMATURE SHAFT SHOWS CONSIDERABLE AMOUNT OF DAMAGE. 1996100300686 19961003 00686 1996 10 3 96ZZZX4976 1 19960913 G 2822 2B729 PUMP AIRBORNE FUEL BOOST SHAFT DAMAGE D K NONE O OTHER IN INSP/MAINT 1 GL 13 2J116 INSPECTION FOUND PUMP MAY HAVE BEEN RUN DRY. DAMAGE TO ARMATRUE SHAFT RESULTED. 1996100300687 19961003 00687 1996 10 3 96ZZZX4977 1 19960913 G 2822 2B664 PUMP AIRBORNE FUEL BOOST SHAFT DAMAGE D K NONE O OTHER IN INSP/MAINT 1 GL 13 7AC53 INSPECTION FOUND DAMAGE TO THE PUMP ARMATURE SHAFT. A GROOVE WORN BY SPACERS. 1996100300688 19961003 00688 1996 10 3 96ZZZX4978 1 19960913 G 2822 2B664 PUMP AIRBORNE FUEL BOOST SHAFT WORN D K NONE O OTHER IN INSP/MAINT 1 GL 13 6E415 INSPECTION FOUND ARMATURE SHAFT BADLY WORN. PUMP MAY HAVE BEEN RUN DRY. 1996100300689 19961003 00689 EU 1996 10 3 96ZZZX4979 1 19960919 G 7110 5711012278 COWL 5711012002 PILATS PC12 PC12 7090550 EU DEICE LIP LOOSE RIVETS D K NONE W INADEQUATE Q C IN INSP/MAINT 1 EA 07 124BW 207 124 OWNER REQUESTED THAT LOOSE RIVETS IN COWLING ASSEMBLY BE ADDRESSED AND FIXED DURING THE ANNUAL INSPECTION. INVESTIGATIO N REVEALED THE RIVETS HAD BEEN INSUFFICIENTLY DRIVEN AT TIME OF MANUFACTURE. 1 L 7 1 3T RT A78EU 1996020200311 19960202 00311 CE 1996 2 2 96ZZZX498 1 19960109 G 2810 FUEL CELL CESSNA 650 650 2076802 CE WINGS CONTAMINATED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 CE 09 9KL 6500068 WHILE PERFORMING A PHASE 5 INSPECTION WHERE ALL THE FUEL PANELS ARE OPENED UP, THERE WERE APPROXIMATELY 8 FUEL IDENTIFIC ATION LABELS LOCATED LOOSELY INSIDE WING. IN THE SUMP AREA THERE WERE 2 LABELS STUCK IN A FLAPPER VALVE. THE LABELS AR E APPROXIMATELY 1 INCH BY 6 INCHES. 2 L 7 2 4F A9NM 1996100300690 19961003 00690 EU 1996 10 3 96ZZZX4980 1 19960919 G 3020 5302412082 DEICE LIP 5711012278 PILATS PC12 PC12 7090550 EU COWL FWD WELD CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 07 124BW 207 124 UPON INVESTIGATION OF A LOOSE RIVET, AN EXHAUST GAS STREAK WAS NOTED ON THE INNER DEICE LIP. FURTHER DISASSEMBLY REVEAL ED A CRACKED WELDED JOINT. SUBMITTER STATED CLOSE INSPECTION OF THE PART IS RECOMMENDED AT EACH SCHEDULED INSPECTION. 1 L 7 1 3T RT A78EU 1996100300691 19961003 00691 SO 1996 10 3 96ZZZX4981 1 19960820 G 3250 9539400 CHANNEL PIPER PA34 PA34200 7103405 SO NLG STEERING BOLT BROKEN D A O OTHER O OTHER LD LANDING 1 SO 15 15445 347350065 NOSE GEAR DID NOT FULLY EXTEND. AIRCRAFT LANDED, DAMAGING NOSE. THE FORWARD BOLT (AN4-7A) WAS FOUND BROKEN, AFT BOLT ( AN4-7A) WAS BENT. THESE BOLTS ATTACH THE STEERING CHANNEL. THE FORWARD BOLT BROKE ALLOWING THE STEERING CHANNEL TO TUR N APPROXIMATELY 90 DEGREES AND PREVENTING THE NOSE GEAR TO GO FULL DOWN AND LOCK. AIRCRAFT TOTAL TIME: 7,051.2 HOURS. 1 L 7 2 3O A7SO 1996100300692 19961003 00692 CE 1996 10 3 96ZZZX4982 1 19960917 G 2810 50260141 GASKET CESSNA 421 421B 2076014 CE AUXILIARY FUEL CRACKED B QY5R K NONE K FLUID LOSS IN INSP/MAINT 1 NE 01 1950G 10 421B0849 AUXILIARY TANK GASKET REPLACED AT FUEL TANK CHANGE. RADIAL CRACKS DEVELOPED CAUSING FUEL LEAK. GASKET REPLACED WITH NE W. NEW GASKET FAILED IN SAME MANNER. CRACKS STARTED AT ALL SCREW HOLES IN GASKETS. REPLACEMENT GASKETS WERE WHAT APPE ARED TO BE NEOPRENE. ORIGINAL GASKET WAS CORK. 1 L 7 2 3O A7CE 1996100300693 19961003 00693 CE 1996 10 3 96ZZZX4983 1 19960814 G 5520 HINGE BEECH 58 58 1152740 CE ELEV LT INBD BUSHING WORN D A O OTHER F E FLT CONT AFFECTED VIBRATION/BUFFET IN INSP/MAINT 1 WP 01 23704 3487 TH900 DURING AN ANNUAL INSPECTION, THE LT INBD ELEVATOR HINGE BUSHING WAS FOUND TO HAVE ITS INNER RACE WORN TO THE POINT THAT IT ALLOWED THE ELEVATOR ADDITIONAL MOVEMENT PAST THE NORMAL TRAVEL. BUSHING WAS REPLACED WITH NEW. WHEN QUESTIONING TH E PILOT ABOUT THE AIRCRAFT'S FLIGHT CHARACTERISTICS, IT WAS INDICATED THE EMPENNAGE WOULD SHUDDER ON LANDINGS. THE SHUD DER CEASED AFTER THE REPLACEMENT OF THE BUSHING. 1 L 7 2 3O 3A16 1996100300694 19961003 00694 CE 1996 10 3 96ZZZX4984 1 19960906 G 2820 070009924 LINE CESSNA 182 182G 2072716 CE DOOR POST FWD CHAFING D K NONE O OTHER IN INSP/MAINT 1 NM 02 2444R 5076 18255544 INSPECTION FOUND THE PINS ON THE JUMP DOOR THAT EXTEND INTO THE DOOR POSTS WERE HITTING THE FUEL LINES THAT RUN PARALLEL WITH THE DOOR POST, BOTH FORWARD AND AFT, ON THE RIGHT SIDE. SPLICED IN A NEW SECTION OF TUBING AND ROUTED THE LINES O UT AND AROUND THE PINS. USED UNIONS AND TUBING NUTS TO SPLICE IN THE NEW TUBING. 1 H 7 1 3O NT 3A13 1996100300695 19961003 00695 CE 1996 10 3 96ZZZX4985 1 19960906 G 2820 070009919 LINE CESSNA 182 182G 2072716 CE DOOR POST AFT CHAFING D K NONE O OTHER IN INSP/MAINT 1 NM 02 2444R 5076 18255544 INSPECTION FOUND THE PINS ON THE JUMP DOOR THAT EXTEND INTO THE DOOR POSTS WERE HITTING THE FUEL LINES THAT RUN PARALLEL WITH THE DOOR POST, BOTH FORWARD AND AFT, ON THE RIGHT SIDE. SPLICED IN A NEW SECTION OF TUBING AND ROUTED THE LINES O UT AND AROUND THE PINS. USED UNIONS AND TUBING NUTS TO SPLICE IN THE NEW TUBING. 1 H 7 1 3O NT 3A13 1996100300696 19961003 00696 CE 1996 10 3 96ZZZX4986 1 19960919 G 5320 121141426 TUNNEL ASSY CESSNA 210 210J 2073439 CE OTBD LT SIDE CRACKED D K NONE O OTHER IN INSP/MAINT 1 CE 01 3356S 1293 21059156 DURING ANNUAL INSPECTION AND GEAR SADDLE INSPECTION PER AD 76-14-7R2, THE OUTBOARD LT TUNNEL ASSEMBLY WAS FOUND CRACKED OUT FROM AN INSPECTION HOLE TO THE OUTER SKIN. THE CRACK STARTED JUST AFT OF A FACTORY INSTALLED DOUBLER PLATE. THE GE AR SADDLE ON THIS SIDE WAS ALSO FOUND TO HAVE A CRACK, REPLACEMENT OF BOTH PANEL AND SADDLE WERE ACCOMPLISHED. SUBMITTE R STATED CAREFUL INSPECTION AT ANNUAL OR 100-HOUR INTERVALS WOULD DETECT THIS TYPE CRACK BELIEVED TO BE CAUSED BY A HARD L ANDING. NO DAMAGE NOTED ON RT SIDE. EXTENSION OF THE DOUBLER WOULD POSSIBLY ELIMINATE THE STRESS CONCENTRATION IN T HIS AREA. 1 H 7 1 3O 3A21 1996100300697 19961003 00697 CE 1996 10 3 96ZZZX4987 1 19960919 G 3213 SADDLE CESSNA 210 210J 2073439 CE LT GEAR CRACKED D K NONE O OTHER IN INSP/MAINT 1 CE 01 3356S 1293 21059156 DURING ANNUAL INSPECTION AND GEAR SADDLE INSPECTION PER AD 76-14-7R2, THE OUTBOARD LT TUNNEL ASSEMBLY WAS FOUND CRACKED OUT FROM AN INSPECTION HOLE TO THE OUTER SKIN. THE CRACK STARTED JUST AFT OF A FACTORY INSTALLED DOUBLER PLATE. THE GE AR SADDLE ON THIS SIDE WAS ALSO FOUND TO HAVE A CRACK, REPLACEMENT OF BOTH PANEL AND SADDLE WERE ACCOMPLISHED. SUBMITTE R STATED CAREFUL INSPECTION AT ANNUAL OR 100-HOUR INTERVALS WOULD DETECT THIS TYPE CRACK BELIEVED TO BE CAUSED BY A HARD L ANDING. NO DAMAGE NOTED ON RT SIDE. EXTENSION OF THE DOUBLER WOULD POSSIBLY ELIMINATE THE STRESS CONCENTRATION IN T HIS AREA. 1 H 7 1 3O 3A21 1996100300698 19961003 00698 EA 1996 10 3 96ZZZX4988 2 19960911 G 7414 ES1068291012 MAGNETO D6LN3200 PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA MOUNT FLANGE CHAFED D S K NONE O OTHER IN INSP/MAINT 1 NE 05 3587P 112 5032447 318052120 RL263261A LEFT ENGINE WITH LESS THAN 100 HOURS SINCE OVERHAUL HAD NAGGING SMALL LEAK AT MAGNETO, WAS THOUGHT TO BE IMPROPER INSTAL LATION, MAG GASKET GETTING DAMAGED. UPON FURTHER INVESTIGATION, FOUND MOUNTING FLANGE WORN AT SPOT WHERE CLAMP GOES. O RDERED NEW BENDIX SHELL PN 10-682001-1, AND FOUND FLANGE TO BE MUCH THICKER. ALSO, BEFORE MAG WAS REMOVED, IT SHOWED SI GNS OF BEING LOOSE. ALSO, FOUND ONE OTHER MAG OF SAME TYPE STARTING TO WEAR AT SAME SPOT PN ES10-382910-12. 1 L 7 2 3O 3 O A20SO E14EA 1996100300699 19961003 00699 EA 1996 10 3 96ZZZX4989 2 19960911 G 7414 ES10398291012 MAGNETO D6LN3200 PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA MOUNT FLANGE CHAFED D K NONE O OTHER IN INSP/MAINT 1 NE 05 3587P 112 R011355010 318052120 RL263261A LEFT ENGINE WITH LESS THAN 100 HOURS SINCE OVERHAUL HAD NAGGING SMALL LEAK AT MAGNETO, WAS THOUGHT TO BE IMPROPER INSTAL LATION, MAG GASKET GETTING DAMAGED. UPON FURTHER INVESTIGATION, FOUND MOUNTING FLANGE WORN AT SPOT WHERE CLAMP GOES. O RDERED NEW BENDIX SHELL PN 10-682001-1, AND FOUND FLANGE TO BE MUCH THICKER. ALSO, BEFORE MAG WAS REMOVED, IT SHOWED SI GNS OF BEING LOOSE. ALSO, FOUND ONE OTHER MAG OF SAME TYPE STARTING TO WEAR AT SAME SPOT PN ES10-382910-12. 1 L 7 2 3O 3 O A20SO E14EA 1996100300700 19961003 00700 CE 1996 10 3 96ZZZX4990 1 19960918 G 5510 07321014 BRACKET CESSNA 182 R182 2072734 CE H STAB REINFORC CRACKED B A VIB3 K NONE O OTHER IN INSP/MAINT 1 SO 03 37G 4505 R18202024 A CRACK WAS FOUND IN A BEND RADIUS OF THE LEFT HAND REAR SPAR ATTACHMENT REINFORCEMENT BRACKET ADJACENT TO THE BEND RADI US HOLE. SUBMITTER RECOMMENDS THE MFG TO MAKE LARGER BRACKET EXTENDING PAST THE LIGHTNING HOLE. 1 H 7 1 3O RT 3A13 1996100300701 19961003 00701 SO 1996 10 3 96ZZZX4991 1 19960910 G 3231 DOOR PIPER PA31 PA31350 7103110 SO RT MLG OUT OF ADJUST B APCR O OTHER O OTHER CL CLIMB 1 NM 01 40ST 317405183 RIGHT MAIN GEAR FAILED TO RETRACT FULLY AND FELL OUT OF UP POSITION DUE TO BINDING/MISADJUSTMENT OF OUTER DOOR. 1 L 7 2 3O A20SO 1996100300702 19961003 00702 SO 1996 10 3 96ZZZX4992 1 19960622 G 3260 565288 HORN PAC PIPER PA28 PA28R201T 7102813 SO GEAR WARNING INOPERATIVE G O OTHER P NO WARNING INDICATION LD LANDING 1 GL 25 47230 3092 28R7703355 DURING LANDING GEAR-UP INCIDENT INVESTIGATION, THE GEAR WARNING HORN WAS FOUND INOPERATIVE. WARNING LIGHT FUNCTIONED, B UT NOT HORN. 1 L 7 1 3O 2A13 1996100300703 19961003 00703 SO 1996 10 3 96ZZZX4993 1 19960909 G 3250 AN47A BOLT 9539400 PIPER PA34 PA34200T 7103406 SO STEERING CHANNEL CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 15 53BD 2923 347970114 THE BOLTS ATTACHING THE STEERING CHANNEL WERE REMOVED FOR INSPECTION. THE FORWARD BOLT WAS FOUND BENT AND CRACKED 75 PE RCENT OF THE WAY THROUGH, THE AFT BOLT BENT. INSTALLED 2 EACH NEW 'AN' 4-7A BOLTS AND RETURNED TO SERVICE. AIRCRAFT TO TAL TIME: 2,922.8 HOURS. 1 L 7 2 3O A7SO 1996101000094 19961010 00094 CE 1996 10 10 96ZZZX4994 1 19960814 G 2510 04140071 SEAT ASSY CESSNA 150 150K 2071822 CE PILOT CRACKED D A K NONE O OTHER IN INSP/MAINT 1 WP 01 5852G 5203 15071352 DURING A 100-HOUR INSPECTION, FOUND PILOT AND COPILOT SEATS TO HAVE NUMEROUS CRACKS STARTING AT SEAT BACK TO BOTTOM SUPP ORTS AND AT THE RECLINING MECHANISM SUPPORTS. ALSO, ON THE COPILOT'S SEAT, FOUND RECLINE ADJUSTER SHAFT WORN OUT. THIS SHAFT ALSO WORE OUT ITS CORRESPONDING SUPPORT BRACKETS. ALL PARTS REPAIRED IAW CESSNA MM AND AC 43.13. 1 H 7 1 3O 3A19 1996101000095 19961010 00095 CE 1996 10 10 96ZZZX4995 1 19960814 G 2510 0414072 SEAT ASSY CESSNA 150 150K 2071822 CE COPILOT CRACKED D K NONE O OTHER IN INSP/MAINT 1 WP 01 5852G 5203 15071352 DURING A 100-HOUR INSPECTION, FOUND PILOT AND COPILOT SEATS TO HAVE NUMEROUS CRACKS STARTING AT SEAT BACK TO BOTTOM SUPP ORTS AND AT THE RECLINING MECHANISM SUPPORTS. ALSO, ON THE COPILOT'S SEAT, FOUND RECLINE ADJUSTER SHAFT WORN OUT. THIS SHAFT ALSO WORE OUT ITS CORRESPONDING SUPPORT BRACKETS. ALL PARTS REPAIRED IAW CESSNA MM AND AC 43.13. 1 H 7 1 3O 3A19 1996101000096 19961010 00096 CE 1996 10 10 96ZZZX4996 1 19960814 G 2510 04111051 ADJUSTER SHAFT CESSNA 150 150K 2071822 CE COPILOT RECLINE WORN D K NONE O OTHER IN INSP/MAINT 1 WP 01 5852G 5203 15071352 DURING A 100-HOUR INSPECTION, FOUND PILOT AND COPILOT SEATS TO HAVE NUMEROUS CRACKS STARTING AT SEAT BACK TO BOTTOM SUPP ORTS AND AT THE RECLINING MECHANISM SUPPORTS. ALSO, ON THE COPILOT'S SEAT, FOUND RECLINE ADJUSTER SHAFT WORN OUT. THIS SHAFT ALSO WORE OUT ITS CORRESPONDING SUPPORT BRACKETS. ALL PARTS REPAIRED IAW CESSNA MM AND AC 43.13. 1 H 7 1 3O 3A19 1996101000097 19961010 00097 CE 1996 10 10 96ZZZX4997 1 19960917 G 3246 95301078 WHEEL HALF BEECH 18 E18S 1151006 CE NO BRAKE SIDE CRACKED C K NONE O OTHER IN INSP/MAINT 1 GL 09 5867 BA333 CRACK IN WHEEL HALF NO BRAKE SIDE. FOUND ON PRE-FLIGHT. 1 L 7 2 3R A765 1996101000098 19961010 00098 SO 1996 10 10 96ZZZX4998 1 19960803 G 8120 4091709001 TURBOCHARGER GARRTT PIPER PA31 PA31350 7103110 SO BEARING FAILED D E ENGINE SHUTDOWN R PARTIAL RPM/PWR LOSS CL CLIMB 1 WP 01 59826 1936 VHL0177 317652077 PILOT REPORTS A DROP IN MANIFOLD PRESSURE AFTER TAKEOFF TO 18 INCHES AND THE LEFT ENGINE WAS FEATHERED. UPON INSPECTION , THE TURBOCHARGER SHAFT, BEARING/HOUSING HAD FAILED. NO OIL RESTRICTION IN THE SUPPLY HOSE WAS FOUND. 1 L 7 2 3O A20SO 1996101000099 19961010 00099 SO 1996 10 10 96ZZZX4999 2 19960911 G 8530 646678 SEAL PIPER PA34 PA34220T 7103420 SO CONT O360 LTSIO360KB 17025 SO INT VALVE STEM FAILED D K NONE O OTHER IN INSP/MAINT 1 SW 17 64TP 129 3447003 320270 DURING AN ANNUAL INSPECTION, THE ENGINE OIL SUCTION SCREEN WAS FOUND TO CONTAIN A SPRING AND FRAGMENTS OF A RUBBER COMPO UND. TELEDYNE CONTINENTAL SB CSB 95-4 PERTAINS TO THIS SUBJECT, BUT IS NOT SUBJECT TO MODELS AFFECTED BY SERIAL NUMBER. THE SB WAS C/W ON BOTH ENGINES, AND EACH SEAL WAS FOUND DEFECTIVE IN EACH ENGINE. SUGGEST REVISING SERIAL NUMBER APPL ICABILITY OF SB. 1 L 7 2 3O 3 O A7SO E9CE 1996102300004 19961023 00004 SO 1996 10 23 96ZZZX5000 2 19960911 G 8530 646678 SEAL PIPER PA34 PA34220T 7103420 SO CONT O360 LTSIO360KB 17025 SO INT VALVE STEM FAILED D K NONE O OTHER IN INSP/MAINT 1 SW 17 64TP 129 3447003 319279 DURING AN ANNUAL INSPECTION, THE ENGINE OIL SUCTION SCREEN WAS FOUND TO CONTAIN A SPRING AND FRAGMENTS OF A RUBBER COMPO UND. TELEDYNE CONTINENTAL SB CSB 95-4 PERTAINS TO THIS SUBJECT, BUT IS NOT SUBJECT TO MODELS AFFECTED BY SERIAL NUMBER. THE SB WAS C/W ON BOTH ENGINES, AND EACH SEAL WAS FOUND DEFECTIVE IN EACH ENGINE. SUGGEST REVISING SERIAL NUMBER APPL ICABILITY OF SB. 1 L 7 2 3O 3 O A7SO E9CE 1996101000100 19961010 00100 CE 1996 10 10 96ZZZX5001 1 19960807 G 3230 504501018 TORQUE TUBE CESSNA 310 310Q 2074242 CE RT MLG CRACKED D A K NONE O OTHER IN INSP/MAINT 1 GL 03 7743Q 3470 310Q0243 DURING 100-HOUR INSPECTION, FOUND BOTH LT AND RT TORQUE TUBES CRACKED (SMALL CRACKS) AT THE AREA WHERE THE FORK BOLT BOS S IS WELDED TO THE TUBE. HAVE SEEN THIS PROBLEM IN THE AIRWORTHINESS ALERTS BEFORE AND PAID CLOSE ATTENTION TO THIS ARE A. THE PROBLEM WAS NOT DISCOVERED DURING A PRE-BUY BECAUSE THE AREA WAS NOT CLEANED WELL ENOUGH. RECOMMEND CLEANING AN D INSPECTING THIS AREA WELL DURING INSPECTIONS. ALSO, NEW TORQUE TUBES DASH 32 AND DASH 33 ARE REINFORCED IN THIS AREA. 1 L 7 2 3O 3A10 1996101000101 19961010 00101 CE 1996 10 10 96ZZZX5002 1 19960807 G 3230 504501019 TORQUE TUBE CESSNA 310 310Q 2074242 CE LT MLG CRACKED D K NONE O OTHER IN INSP/MAINT 1 GL 03 7743Q 3470 310Q0243 DURING 100-HOUR INSPECTION, FOUND BOTH LT AND RT TORQUE TUBES CRACKED (SMALL CRACKS) AT THE AREA WHERE THE FORK BOLT BOS S IS WELDED TO THE TUBE. HAVE SEEN THIS PROBLEM IN THE AIRWORTHINESS ALERTS BEFORE AND PAID CLOSE ATTENTION TO THIS ARE A. THE PROBLEM WAS NOT DISCOVERED DURING A PRE-BUY BECAUSE THE AREA WAS NOT CLEANED WELL ENOUGH. RECOMMEND CLEANING AN D INSPECTING THIS AREA WELL DURING INSPECTIONS. ALSO, NEW TORQUE TUBES DASH 32 AND DASH 33 ARE REINFORCED IN THIS AREA. 1 L 7 2 3O 3A10 1996101000102 19961010 00102 SO 1996 10 10 96ZZZX5003 2 19960916 G 8550 CH48109 FILTER BEECH 55 95C55 1152708 CE CONT O520 IO520C 17032 SO ENGINE OIL MISMANUFACTURED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 CE 01 782B 84 TE247 240532R DURING A ROUTINE OIL CHANGE, EXAMINATION OF THE OIL FILTER REVEALED THE RUBBER GASKET BETWEEN THE FILTER ELEMENT AND THE FILTER END HOUSING HAD SHIFTED, APPARENTLY DURING MANUFACTURE, AND COVERED APPROXIMATELY 75 PERCENT OF THE OIL IN HOLE AND 100 PERCENT OF TWO OIL OUT HOLES. PART REMOVED FROM SERVICE. SUBMITTER STATED STIFFER QA GUIDELINES ARE NEEDED TO PREVENT RECURRENCE. 1 L 7 2 3O 3 O 3A16 E5CE 1996101000103 19961010 00103 CE 1996 10 10 96ZZZX5004 1 19960901 G 3211 08221804 SUPPORT CESSNA 310 310Q 2074242 CE MLG DEFORMED D S A K NONE O OTHER IN INSP/MAINT 1 EA 23 85DS 310Q0080 DURING INSTALLATION OF LANDING GEAR KIT SK-414, FOUND SUPPORT DEFORMED AND STRUCTURE AT POINT OF ATTACH CRACKED. SUBMIT TER URGENTLY RECOMMENDS THIS MODIFICATION BE MADE AN AIRWORTHINESS DIRECTIVE FOR ALL CESSNA 300 AND CESSNA 400 SERIES AI RCRAFT USING ELECTRIC MECHANICAL LANDING GEAR REGARDLESS OF AIRCRAFT TIME OR AGE. 1 L 7 2 3O 3A10 1996101000104 19961010 00104 CE 1996 10 10 96ZZZX5005 1 19960731 G 5741 AN824A BOLT CESSNA 150 152 2071835 CE FWD WING ATTACH RUSTED D A K NONE O OTHER IN INSP/MAINT 1 SO 25 89969 7006 15282934 WHILE REMOVING BOTH WINGS FROM ACFT, FOUND FORWARD WING ATTACH BOLT EXTREMELY DIFFICULT TO TURN. AFTER LUBRICATION, BOL T STILL HARD TO TURN. AFTER BOLT WAS REMOVED, PLATING WAS OBSERVED TO BE GONE, THE BOLT WAS BENT, AND IT HAD SEVERE PIT TING FROM RUST, WITH A POSSIBLE CRACK. AT LEAST ONE OTHER WING ATTACH BOLT FROM THE SAME ACFT HAS THIS SITUATION. SUBM ITTER RECOMMENDS WING ATTACHMENT BOLT INSPECTION AT PERIODIC INTERVALS. LUBRICATING BOLTS UPON INSTALLATION SHOULD BE A CCOMPLISHED. NOTE: THIS CONDITION COULD ONLY BE OBSERVED BY REMOVAL OF THE BOLT. THIS PARTICULAR AIRCRAFT SHOWED NO E XTERNAL SIGNS OF THIS DETERIORATION. 1 H 7 1 3O NT 3A19 1996101000105 19961010 00105 CE 1996 10 10 96ZZZX5006 1 19960904 G 3310 XR7200B RHEOSTAT BEECH 35 K35 1151524 CE INST PNL LIGHTS OVERHEATED D A K NONE M OVER TEMP IN INSP/MAINT 1 EA 21 9538R D6094 ALL FOUR LIGHTING DIMMER RHEOSTAT/TRANSISTOR ASSEMBLIES WERE SUBJECTED TO EXCESSIVE HEAT DURING NORMAL OPERATION. THERE WAS NOT A SHORTED WIRE CONDITION CAUSING THIS HEAT. THE POTTING COMPOUND FORMING THE UNIT MELTED (DRIPPING DOWN ONTO T HE FLOOR) EVENTUALLY CAUSING THE FAILURE OF THE RHEOSTAT. SUBMITTER STATED THIS ASSEMBLY POSES A SAFETY HAZARD AND SHOU LD BE REPLACED WITH ONE THAT CAN HANDLE THE LOAD AND DISSIPATE THE HEAT EFFECTIVELY. 1 L 7 1 3O 3A15 1996101000106 19961010 00106 SO 1996 10 10 96ZZZX5007 2 19960918 G 7322 643085 BRACKET CESSNA 210 210M 2073450 CE CONT O520 IO520L 17032 SO THROTTLE BODY SEPARATED D S K NONE O OTHER IN INSP/MAINT 1 SW 99 9489M 157 21062081 294714R THROTTLE BODY SUPPORT BRACKET FOUND SEPARATED AT ANNUAL INSPECTION. TIS: 156.5 HOURS, SEPARATED AT SPOT WELDS. 1 H 7 1 3O 3 O 3A21 E5CE 1996101000107 19961010 00107 SO 1996 10 10 96ZZZX5008 1 19960910 G 2434 DOFF103005 ALTERNATOR FORD GULSTM AA5 AA5A 3960106 SO DC SYSTEM FAILED D O OTHER H ELECT. POWER LOSS-50 PC TO TAKEOFF 1 NE 01 9860U AA5A0260 ALTERNATOR FAILED ON TAKEOFF. IFR ALTERNATOR HAD OVER 1,000 HOURS SINCE REBUILD. AVERAGE TIME FOR ACCESSORIES IS ABOUT 1,000 HOURS. IFR AIRCRAFT ESPECIALLY SHOULD BE CAREFULLY LOOKED AT IN REGARDS TO ACCESSORY TIMES. 1 L 7 1 3O A16EA 1996101000109 19961010 00109 1996 10 10 96ZZZX5010 4 19960621 G 3442 ART2100 ART SENSOR BENDIX 07101550101 BEECH 200 B200 1152922 CE RADAR ANT STAB DEFECTIVE B FR2R K NONE O OTHER NR NOT REPORTED 1 SW 01 38V P1009 BB1412 ANTENNA STABLIZATION WORKS ONLY IN LEVEL FLIGHT AUTOTILT STILL DROPS ANTENNA. S/W-01/12 SOFTWARE LEVEL DID NOT FIX PROB LEMS OF THE ORIGINAL RADAR UNIT. INSTALLED REPLACEMENT ART 2100, SN 1036, WITH THIRD BENDIX/KING SOFTWARE UPGRADE S/W-0 1/03 AND MOD STATUS 2. 1 L 7 2 4T A24CE 1996101000110 19961010 00110 1996 10 10 96ZZZX5011 4 19960130 G 3442 ART2100 ART SENSOR BENDIX 07101550101 BEECH 200 B200 1152922 CE ARDAR ANT STAB MALFUNCTION B FR2R K NONE O OTHER IN INSP/MAINT 1 SW 01 38V 1016 BB1412 ANTENNA STABILIATION TOO SENSITIVE. RADAR PAINTS HEAVY LEFT AND RIGHT. AUTOTILT DROPS ANTENNA. 1 L 7 2 4T A24CE 1996101000111 19961010 00111 1996 10 10 96ZZZX5012 4 19960819 G 3442 ART2100 ART SENSOR BENDIX 07101550101 BEECH 200 B200 1152922 CE RADAR ANT STAB MALFUNCTION B FR2R K NONE O OTHER IN INSP/MAINT 1 SW 01 38V 1036 BB1412 TEN MONTHS AFTER CHANGING ART 2100'S, BENDIX/KING STILL HAS NOT COME OUT WITH A GOOD FIX. BASIC PROBLEM IS THE SOFTWARE WHICH CANNOT KEEP UP WITH 'GYRO PRECESSION'. FAULT LABEL: 'ANT FLT'. 1 L 7 2 4T A24CE 1996101000112 19961010 00112 1996 10 10 96ZZZX5013 4 19960918 G 3442 ART2100 ART SENSOR BENDIX 07101550101 BEECH 200 B200 1152922 CE RADAR ANT STAB MALFUNCTION B FR2R K NONE O OTHER IN INSP/MAINT 1 SW 01 38V 1044 BB1412 STABILIZATION TOO SENSITIVE. AUTOTILT DROPS ANTENNA. STAB OFF AND INFLIGHT 6. 1 L 7 2 4T A24CE 1996101000114 19961010 00114 CE 1996 10 10 96ZZZX5015 1 19960902 G 7120 9401120 MOUNT CESSNA 172 172N 2072434 CE ENGINE DEFECTIVE D A K NONE W INADEQUATE Q C IN INSP/MAINT 1 EA 21 1558E 17271046 AFTER ORDERING LORD MOUNTS J-9613-49 FOR REPLACMENT OF CESSNA 172N ENGINE, BARRY MOUNTS WERE AUTOMATICALLY SUBSTITUTED B Y THE SUPPLIER. SUBMITTER STATED ALTHOUGH THESE ARE APPROVED BY FAA, THEY DO LACK THE CENTER (DAMPER BAG) AND CESSNA RE COMMENDS NOT DOING WITHOUT. LORD CLAIMS THE NEED DURING START-UP AND SHUT DOWN. 1 H 7 1 3O NT 3A12 1996101000115 19961010 00115 SO 1996 10 10 96ZZZX5016 1 19960901 G 7120 MOUNT GULSTM AA5 AA5B 3960105 SO ENGINE CRACKED D P K NONE O OTHER IN INSP/MAINT 1 GL 09 1562R AA5B0062 ENGINE MOUNT WAS DISCOVERED CRACKED ON THE CROSS-OVER SUPPORT BRACE JUST INBOARD OF THE WELD JOINT. NO SIGNIFICANT INBO ARD CORROSION WAS DISCOVERED. IT APPEARS THE CRACK WAS CAUSED BY METAL FATIGUE. 1 L 7 1 3O A16EA 1996101000116 19961010 00116 GL 1996 10 10 96ZZZX5017 3 19960901 G 6111 BLADE BEECH 35 V35B 1151548 CE MCAULY 3A32C 3A32C76 GL PROPELLER BEARING FAILED D L K NONE O OTHER IN INSP/MAINT 1 SW 99 3161W 445 D9572 781089 MAINTENANCE REMOVED THE PROPELLER FOR INSPECTION AND FOUND ALL THE BEARINGS, BEARING RACE FOR THE BLADES, WERE TOTALLY C ORRODED AND THE PISTON AND SPRING AND THE DOME WERE TOTALLY UNSERVICEABLE. 1 L 7 1 3O 3A15 5 C P21EA 1996101000118 19961010 00118 GL 1996 10 10 96ZZZX5019 1 19960812 G 2720 2027200100 CONTROL CABLE DIAMON DA20 DA20A1 2990000 GL RUDDER BROKEN D K NONE O OTHER IN INSP/MAINT 1 WP 15 402KT 766 10039 PILOT'S LEFT OUTBOARD RUDDER CABLE BROKE AT NICO PRESSURE FITTING. WITH RUDDER PEDALS ADJUSTED FULL FORWARD POSITION, S -TUBE MAKES CONTACT WITH NICO-PRESSURE FITTING. S-TUBE WORE THROUGH THE CABLE. AIRCRAFT WAS ON THE GROUND. 1 L 7 1 3O NT TA4CH 1996101000119 19961010 00119 CE 1996 10 10 96ZZZX5020 1 19960901 G 3110 INSTRUMENT PANEL BEECH 35 G35 1151516 CE COCKPIT POOR SUPPORT B UQ2R K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 03 4645D D4840 A PORTION OF TOP FUSELAGE SKIN EXTENDING FROM WINDSHIELD LINE AFT TO INSTRUMENT PANEL WAS REMOVED. SUBMITTER SUSPECTS T HIS SECTION OF SKIN REMOVED TO MAKE IT EASIER TO INSTALL A NEW 1-PIECE SPEED SLOPE WINDSHIELD. THIS SECTION PROVIDES ST RUCT STRENGTH AND SUPPORT FOR INSTR PANEL AND SHOCK MOUNTED SUB-PANEL. THE TOP OF INSTR PANEL HAD LITTLE FORE AND AFT SUPPORT AND ENTIRE PANEL WEAKLY SUPPORTED BY CHANNEL THAT RUNS ALONG BOTTOM OF PANEL ATTACHED TO LT AND RT SIDEWALLS. B Y MOVING CONTROL COLUMN UP AND DOWN, ENTIRE INSTR PANEL WOULD FLEX AT LEAST .50 INCH. SUBMITTER RECOMMENDS WHEN OLDER BONANZA'S HAVE WINDSHIELD MODS DONE, TAKE PRECAUTIONS NOT TO LOSE INSTRUMENT PANEL STRUCTURAL STRENGTH. 1 L 7 1 3O A777 1996101000122 19961010 00122 EA 1996 10 10 96ZZZX5023 2 19960820 G 8530 PISTON PIPER PA14 PA14 7101402 SO LYC O290 O290D 41506 EA NR 3 CYLINDER FAILED D P A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 NM 11 5196H 2286 14493 188521 DURING FLIGHT, THE PILOT REPORTED HEARING A SLIGHT KNOCKING IN THE ENGINE AND NOTED A 20 PSI DROP IN OIL PRESSURE. A PR ECAUTIONARY LANDING WAS MADE WITHOUT INCIDENT. COMPRESSION CHECK REVEALED NR 3 CYLINDER LOW AT 50/80. CYLINDER REMOVAL REVEALED NR 3 PISTON SKIRT BROKE WITH 2 INCH BY 3 INCH PIECE LOCATED IN OIL SUMP OF ENGINE. 1 H 7 1 3O 3 O A797 E229 1996101000123 19961010 00123 EU 1996 10 10 96ZZZX5024 1 19960711 G 2460 727727 BREAKER HWKSLY DH125 HS125600A 4230158 EU COMM NR 2 FAILED G A O OTHER O OTHER CR CRUISE 1 GL 03 600G 256066 COMM 2 CIRCUIT BREAKER OPENED DURING FLIGHT AND WOULD NOT RESET. CIRCUIT BREAKER WAS REPLACED WITH NEW BREAKER. 2 L 7 2 4J A3EU 1996101000125 19961010 00125 CE 1996 10 10 96ZZZX5026 1 19960819 G 2842 169380066 TRANSMITTER BEECH 23 C23 1151242 CE FUEL QUANTITY LEAKING H P K NONE B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 CE 09 6519R 2432 M1542 FUEL SMELL IN CABIN. LEFT AND RIGHT FUEL QUANTITY TRANSMITTERS LEAKING FUEL FROM CENTER POST OF TRANSMITTER. FUEL APPEA RS TO BE LEAKING FROM INTERNAL SEALS. PARTS TO BE REMOVED AND REPLACED. 1 L 7 1 3O A1CE 1996101000126 19961010 00126 CE 1996 10 10 96ZZZX5027 1 19960918 G 2760 0148 WORM GEAR CESSNA 210 P210N 2073454 CE SPEED BRAKE SCREW LOOSE D A O OTHER O OTHER NR NOT REPORTED 1 NM 01 731MV 4455 P21000512 STC SA2602NM. SPEED BRAKES FAILED TO DEPLOY. SET SCREW PART NUMBER UNKNOWN USED TO SECURE WORM GEAR TO GEAR MOTOR SHAF T. HAD ALLOWED WORM GEAR TO SLIP OFF OF SHAFT. SHAFT HAD SMALL DRILL SPOT ON OUTSIDE DIAMETER AS DETENT FOR SET SCREW . SET SCREW IS LARGER IN DIAMETER THAN DRILL SPOT. SET SCREW DID NOT PENETRA TE INTO SHAFT AREA ALLOWING WORM GEAR TO WORK OFF OF SHAFT. SUBMITTER STATED THIS CONDITION, BECAUSE ONE MOTOR IS INSTALLED IN EACH SPEED BRAKE, COULD ALLOW ASY MMETRICAL LIFT CONDITION TO EXIST. 1 H 7 1 3O 3A21 1996101000127 19961010 00127 NE 1996 10 10 96ZZZX5028 2 19960902 G 8520 20506 LINK ROD DOUG DC3 DC3C 3021457 WP PWA R1830 R183090B 52020 NE NR 7 CYLINDER BROKEN E O OTHER E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CR CRUISE 1 GL 05 8187E 6179 181 25285 BP307288 IN CRUISE POWER, LT ENGINE STARTED RUNNING ROUGH. FOUND NR 7 CYLINDER LINK ROD BROKEN. 2 L 7 2 4R 4 R A669 5E4 1996101000180 19961010 00180 SO 1996 10 10 96ZZZX5029 1 19960902 G 7160 MS202531 HINGE PIN PIPER PA28 PA28R200 7102811 SO ALT AIR DOOR FAILED D A K NONE R PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 EA 21 75340 600 28R7635292 DURING PRE-FLIGHT RUN UP, POWER WAS LIMITED TO 1,900 RPM. THE ALTERNATE AIR DOOR WAS FOUND IN THE FUEL METERING UNIT, T HE HINGE PIN HAD WORN COMPLETELY THROUGH IN 600 HOURS OF OPERATION. (ONE YEAR AT FLIGHT SCHOOL). SUBMITTER RECOMMENDAT ION, A TAB ON THE ALTERNATE AIR DOOR COULD PROVIDE BOTH A PUSH/PULL TEST OF THE HINGE AND AN ATTACH POINT FOR A COUPE LE ASH. 1 L 7 1 3O 2A13 1996101000181 19961010 00181 SO 1996 10 10 96ZZZX5030 1 19960701 G 5523 6358501 TRIM TAB 6358500 PIPER PA28 PA28R200 7102811 SO STABILATOR CRACKED D P K NONE O OTHER IN INSP/MAINT 1 EA 21 75340 6100 28R7635292 DURING 100-HOUR INSPECTION, THE TRIM TAB WAS DISCONNECTED TO ACCOMODATE REPLACEMENT OF TRIM BARREL HARDWARE, THE TRIM TA B WAS FOUND TO BE CRACKED: UNDER THE ATTACH BRACKET, AT THE EDGE OF THE ATTACH BRACKET, INTO THE SUPPORTING RIBS., ON BOTH LT AND RT TRIM TAB. 1 L 7 1 3O 2A13 1996101000183 19961010 00183 CE 1996 10 10 96ZZZX5032 1 19960827 G 3230 504501019 TORQUE TUBE CESSNA 310 310Q 2074242 CE LT MLG CRACKED B L CSLR O OTHER O OTHER CR CRUISE 1 CE 01 7872Q 5000 310Q0653 DURING FLIGHT, PILOT NOTED THE ACFT SEEMED SLOWER AND YAWING TO THE LEFT. FLYBY INDICATED THE LEFT MAIN LANDING GEAR WA S DOWN WHILE THE RT AND NOSE WERE RETRACTED GEAR. SELECTED DOWN, ALL THREE INDICATED DOWN AND LOCKED. ACFT LANDED AT M AINTENANCE BASE WITHOUT INCIDENT. INVESTIGATION REVEALED THE LEFT MAIN GEAR TORQUE TUBE HAD CRACKED AT THE FORK BOLT BO SS AND THE CRACK HAD PROGRESSED AROUND THE TORQUE TUBE IN A SPIRAL MANNER. 1 L 7 2 3O 3A10 1996101000184 19961010 00184 SO 1996 10 10 96ZZZX5033 1 19960820 G 3297 WIRE PIPER PA24 PA24250 7102404 SO NLG SWITCH BURNED D P K NONE O OTHER IN INSP/MAINT 1 EA 23 8230P 243483 WIRES LEADING TO NOSE GEAR SWITCHES WERE FOUND CHARRED BARE WHERE THEY WERE SECURED BEHIND MUFFLER. WIRES WERE ROUTED T O OUTBOARD SIDE OF ENGINE COMPARTMENT TO REMOVE THEM FROM HOT AREA. 1 L 7 1 3O 1A15 1996101000185 19961010 00185 CE 1996 10 10 96ZZZX5034 1 19960917 G 2710 2300003142 CONTROL CABLE LEAR 24 24B 5170306 CE AILERON FRAYED E K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 15 83HC 193 CABLE WAS INSTALLED TO AIRCRAFT. PRE-TENSIONED TO 200 FEET/POUNDS (PER MM) WHILE AILERON CONTROLS WERE RUN THROUGH WHIL E CABLE WAS UNDER TENSION AT 200 POUNDS, A SMALL 'BULGE' WAS NOTED AT APPROIXMATELY MID-CABLE LENGTH. AN INTERNAL CABLE STRAND HAD BROKEN (APPARENTLY) UNDER THE PRE-TENSION LOAD. ANOTHER NEW CABLE WAS INSTALLED. LEARJET FIELD SERVICE WAS INFORMED. 2 L 7 2 4J A10CE 1996101000186 19961010 00186 1996 10 10 96ZZZX5035 4 19960901 G 2562 4530150 ELT ARTEX 52770 PIPER PA46 PA46350P SO CASE BATTERY FAULTY B P SJ7R K NONE O OTHER IN INSP/MAINT 1 SO 01 9250B 500 4622161 ELT BATTERY, ONE BATTERY SHOWED EVIDENCE OF HIGH HEAT, AND EXCESS CORROSION CRACKING BATTERY CASE. ELT MANUFACTURED '94 . 1 L 7 1 3O RT A25SO 1996101000187 19961010 00187 SO 1996 10 10 96ZZZX5036 1 19960905 G 7810 1245712 STACK PIPER PA18 PA18A150 7101837 SO NR 2 CYL EXH CRACKED D K NONE O OTHER IN INSP/MAINT 1 NM 01 9295D 201 186602 THE NR 2 EXHAUST PORT STACK CRACKED AT MOUNTING FLANGE. THIS PART WAS NEW FROM UNIVAIR. THE EXHAUST STACK ONLY HAD 200 HOURS SINCE NEW. SUBMITTER STATED UNIVAIR STATES THEY HAVE HAD CRACKING PROBLEMS BEFORE. THIS PART IS MANUFACUTRED BY A SUB-CONTRACTOR TO UNIVAIR. 1 H 7 1 3O 1A2 1996101000188 19961010 00188 SO 1996 10 10 96ZZZX5037 1 19960818 G 2750 6270600 LEVER ASSY PIPER PA28 PA28140 7102802 SO FLAP CONTROL CRACKED D S K NONE O OTHER IN INSP/MAINT 1 GL 19 9851W 5000 2823364 WHILE C/W AD 96-10-03 FLAP ATTACH BOLT, DISCOVERED THE BRACKET THE FLAP HANDLE ATTACHES TO HAD 4 CRACKS IN IT, ONE AT EA CH CORNER. 1 L 7 1 3O 2A13 1996101000189 19961010 00189 EA 1996 10 10 96ZZZX5038 2 19960618 G 8540 76327 DRIVE GEAR BELL 47 47G5 1181032 SW LYC O435 VO435B1A 41516 EA ACCY DRIVE BOLTS SHEARED H K NONE O OTHER IN INSP/MAINT 1 GL 27 1449W 530 7931 2345331 GEAR AND SHAFT ASSEMBLY IS A TWO-PART GEAR HELD TOGETHER BY SIX .25 INCH BOLTS AND THREE .25 INCH PILOT PINS. IT APPEAR S THE SIX .25 INCH BOLTS WERE NOT PROPERLY TORQUED AT OVERHAUL AND THEY SHEARED OFF AT 529.6 HOURS SMOH. 1 G 7 1 3O 3 O 2H3 E279 1996101000190 19961010 00190 NE 1996 10 10 96ZZZX5039 2 19960829 G 7261 ENGINE KAMAN K1200 K1200 05625F6 SW LYC T53 T5317A 41549 NE N1 GEARBOX OIL VENTING D K NONE O OTHER IN INSP/MAINT 1 NM 10 311KA 409 A940017 LE81016 ENGINE WAS VENTING OIL OVERBOARD FROM LARGE VENT LINE CONNECTED TO N1 GEARBOX. ALL POSSIBLE STEPS TO CORRECT WERE NOT S UCCESSFUL. ENGINE WAS REPLACED AUGUST 29, 1996. 1 G 7 1 4F 4 U NT TR7BO E17EA 1996101000191 19961010 00191 SW 1996 10 10 96ZZZX5040 1 19960829 G 6220 K913014001 DROOP STOP K913001004 KAMAN K1200 K1200 05625F6 SW RT HUB ASSY BENT D K NONE O OTHER IN INSP/MAINT 1 NM 10 311KA 409 8BM A940017 DROOP STOP ON RT SIDE HUB WAS BENT BY PILOT WHEN ATTEMPTING TO INSTALL TEETER LOCKS DURING ACFT TY-DOWN PROCEDURE. CREW CHIEF HAD REPAIRED STOP, BUT STOP WAS TWEAKED FORE AND AFT AS WELL AS UP AND DOWN. STOP HUNG UP DURING COAST DOWN AND R/S ROTOR BLADES CHAFED OPPOSING HUB. AFTER THOROUGH INSPECTION, ONLY R/S ROTOR BLADES (TWO EACH) WERE REPLACED. 1 G 7 1 4F NT TR7BO 1996101000192 19961010 00192 SW 1996 10 10 96ZZZX5041 1 19960904 G 6520 2060404103 DUPLEX BEARING 206040400013 BELL 206 206B3 1181506 SW T/R TRANSMISSION ROUGH B PN5R K NONE O OTHER IN INSP/MAINT 1 NM 03 11CQ 4678 1677 A49 3778 COULD NOT BALANCE T/R DUE TO ROUGH BEARING GIVING FALSE SIGNALS TO BALANCE EQUIPMENT. REPLACED BEARING AND REINSTALLED GEARBOX ON AIRCRAFT AND BALANCED T/R IN NORMAL MANNER WITH GOOD RESULTS. 1 G 7 1 3U H2SW 1996101000193 19961010 00193 SW 1996 10 10 96ZZZX5042 1 19960917 G 5302 206031329103 FITTING 206033410001 BELL 206 206L1 1182107 SW TAILBOOM CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 99 613 45287 ACFT TT: 7,745.2 HOURS. DURING 300-HOUR INSPECTION, FOUND CRACK IN T/B FITTING. AIRCRAFT HAS BEEN DOING SLING WORK. S UBMITTER RECOMMENDATION WOULD BE TO INSPECT MORE FREQUENTLY UNTIL A STRONGER FITTING IS MADE. 1 G 7 1 3U H2SW 1996101000194 19961010 00194 NE 1996 10 10 96ZZZX5043 2 19960912 G 7250 834401 BLADE PWA JT8 JT8D9A 52048 NE N2 TURBO T1 FAILURE B SQ5R K NONE E VIBRATION/BUFFET IN INSP/MAINT 1 NE 03 P674220 ENGINE EXHIBITED HIGH VIBRATION IN SERVICE. DISASSEMBLY INSPECTION REVEALED T-2 BLADE FAILURE AND CONSEQUENTIAL DAMAGE TO THE 2ND, 3RD, AND 4TH AIRFOILS. THE CAUSE OF FAILURE IS UNDER INVESTIGATION. 4 F E2EA 1996101000195 19961010 00195 NE 1996 10 10 96ZZZX5044 2 19960912 G 7240 628748001 T-DUCT PWA JT8 JT8D9A 52048 NE COMB CHAMBER FAILURE B SQ5R K NONE O OTHER IN INSP/MAINT 1 NE 03 P674220 DISASSEMBLY INSPECTION OF ENGINE AFTER HPT BLADE FAILURE REVEALED FAILURE OF THE COMBUSTION CHAMBER SUPPORT/INNER C.C. C ASE ATTACHMENT FINGERS. SUSPECT CAUSE OF FAILURE WAS RELATED TO SHORT TERM OPERATION OF MALFUNCTIONING ENGINE AFTER HPT BLADE FAILURE. 4 F E2EA 1996101000196 19961010 00196 CE 1996 10 10 96ZZZX5045 1 19960819 G 3260 MS243311 SWITCH BEECH MU300 400A 1155402 CE LT MLG DOWNLOCK INTERMITTENT D K NONE O OTHER IN INSP/MAINT 1 GL 21 3196N 349 RK96 LEFT GEAR DOWN INDICATION INTERMITTENT. PROBLEM TRACED TO DOWN SWITCH ON GEAR. THIS IS 3RD OCCURRENCE ON THIS AIRCRAFT IN 14 MONTHS. ANOTHER B-400A IN FLEET HAS HAD 3 SWITCHES FAIL ALSO. IN MOST CASES, DOWN AND LOCKED LIGHT WOULD COME O N WHEN SWITCH WAS LIGHTLY TAPPED. RIGGING WAS WITHIN SPECS ON ALL OCCURRENCES. 2 H 7 2 4F RT A16SW 1996101000197 19961010 00197 NE 1996 10 10 96ZZZX5046 2 19960902 G 7250 3115154 NOZZLE BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE PT HOUSING OIL PLUGGED A A MASR K NONE O OTHER IN INSP/MAINT 1 SW 01 35YV 9267 1156 UE35 114031 AT DISASSEMBLY, THE NR 3 BEARING WAS FOUND COMPLETELY DESTROYED. IT APPEARS TO BE OIL STARVATION DUE TO THE NR 3 AND NR 4 BEARING OIL NOZZLE BEING PLUGGED. WHEN THE NOZZLE WAS FLOW CHECKED, IT REVEALED 3 OF THE 4 OIL PORTS WERE PLUGGED. T HE BLOCKAGE APPEARS TO BE CARBON BUILD-UP INSIDE THE NOZZLE. THE OIL NOZZLE WAS SENT TO PRATT AND WHITNEY FOR INVESTIGA TION ALONG WITH THE FAILED NR 3 BEARING REMAINS. 2 L 7 2 4T 4 T RT A24CE E26NE 1996101000198 19961010 00198 NM 1996 10 10 96ZZZX5047 1 19960901 G 5311 FRAME BOEING 727 727224 1384076 NM FS 219.8 CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 32719 20388 DURING C-CHECK INSPECTION, LEVEL 2 CORROSION WAS FOUND ON FRAME 219.8, LT SIDE OF LOWER NOSE COMPARTMENT DOOR CUT-OUT. 2 L 7 3 4F A3WE 1996101000199 19961010 00199 CE 1996 10 10 96ZZZX5048 1 19960725 G 3244 301393190 TIRE BEECH 300 300BEECH 1152930 CE NLG DEFECTIVE D A UNSCHED LANDING E VIBRATION/BUFFET CL CLIMB 1 NM 09 488GA FA125 PILOT REPORTED VIBRATION ON TAKEOFF ROLL. LANDED WITHOUT INCIDENT. INSPECTION REVEALED NOSE TIRE INTERNAL BALANCE PATC H HAD COME LOOSE. SUSPECT HIGH OAT AS CAUSE. 2 L 7 2 4T A24CE 1996101000200 19961010 00200 NE 1996 10 10 96ZZZX5049 2 19960913 G 8530 CYLINDER DOUG DC3 DC3C 3021457 WP PWA R1830 R183092 52020 NE RT ENG NR 2 CRACKED E E A ENGINE SHUTDOWN UNSCHED LANDING E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CR CRUISE 1 SW 11 59316 950 18986 359283 RIGHT ENGINE STARTED TO RUN ROUGH AND BACKFIRE IN-FLIGHT. ENGINE SHUT DOWN AND AN UNEVENTFUL LANDING WAS MADE. INVESTI GATION FOUND NR 2 CYLINDER CRACKED. CYLINDER WAS REMOVED AND REPLACED WITH A YELLOW TAGGED UNIT. ENGINE GROUND RAN, CH ECKED SATISFACTORY. AIRCRAFT RETURNED TO SERVICE. SUSPECT FATIGUE AS CAUSE OF CRACK. 2 L 7 2 4R 4 R A669 5E4 1996101000201 19961010 00201 CE 1996 10 10 96ZZZX5050 1 19960828 G 3010 3D235306 FLOW CONTROL CESSNA 441 441 2076020 CE LT WING DEICE PLUGGED D O OTHER O OTHER NR NOT REPORTED 1 WP 07 832AD 2894 4410311 WING BOOTS INFLATED AND STAYED INFLATED UNTIL ENGINE SHUT DOWN. THEY WOULD NOT RESET. REMOVED FLOW CONTROL EJECTOR VAL VE AND FOUND OVERBOARD PORT PLUGGED WITH MUD AND INSECT EGG SACKS. 1 L 7 2 3T RT A28CE 1996101000202 19961010 00202 CE 1996 10 10 96ZZZX5051 1 19960820 G 3240 G51710917 LINE CESSNA 500 S550 2076607 CE LT BRAKE CHAFE/FAIL B A EB1R O OTHER O OTHER LD LANDING 1 EA 13 91ML S550132 BRAKE PRESSURE LOST ON LANDING. INVESTIGATION OF PROBLEM REVEALED THE BRAKE LINE GOING TO THE LT BRAKE HAD BEEN CHAFED THROUGH BY AN ELEVATOR CONTROL CABLE. THE LINE WAS REMOVED AND REPLACED. THE NEW LINE WAS INSTALLED WITH ADEQUATE CLEA RANCE BETWEEN THE BRAKE LINE AND CABLE TO PREVENT RECURRENCE. THE CABLE WAS NOT DAMAGED. THE LOCATION OF THE PROBLEM W AS UNDER THE FLOOR JUST INSIDE THE MAIN ENTRANCE DOOR. 1 L 7 2 4F RT A22CE 1996101000203 19961010 00203 NE 1996 10 10 96ZZZX5052 2 19960820 G 7250 ENGINE PWA JT8 JT8D219 52053 NE TURBINE FAILURE B RH2R E ENGINE SHUTDOWN O OTHER NR NOT REPORTED 1 SO 19 11588 725447 IN-FLIGHT SHUTDOWN AND ENGINE WAS REMOVED FROM AIRCRAFT DUE TO TURBINE FAILURE. 1ST, 2ND, 3RD, AND 4TH TURBINE BLADES A ND 2ND, 3RD, AND 4TH NOZZLE GUIDE VANES SUSTAINED EXTENSIVE DAMAGE. EXACT CAUSE HAS NOT BEEN DETERMINED AT THIS TIME. I T IS SUSPECTED THE 2ND NGV'S MADE CONTACT WITH THE T-2 BLADES CAUSING FAILURE. SB'S 5830, 5840, AND 5891 HAD BEEN PREVI OUSLY C/W AND ASB 5782 WAS CURRENT. 4 F E9NE 1996101000204 19961010 00204 NM 1996 10 10 96ZZZX5053 1 19960725 G 3610 797839 VALVE SHAFT HAMSTD 77385618 BOEING 747 747* NM PRESS CHECK WORN B SI3R K NONE O OTHER IN INSP/MAINT 1 NE 03 DL22 ANTI-ROTATION SLOTS ARE WORN AWAY ON VALVE SHAFT CAUSING SHAFT TO ROTATE AND SHAFT SHOULDER TO WEAR EXCESSIVELY. REF: O HM 36-12-06, PAGE 606, FIGURE 603. 2 L 7 4 4F RT A20WE 1996101000363 19961010 00363 CE 1996 10 10 96ZZZX5055 1 19960913 G 2150 75065912 SWITCH CESSNA 650 650 2076802 CE PAC OVERHEAT FAILED D K NONE N FALSE WARNING CR CRUISE 1 GL 09 2UP 1780 6500227 FLIGHT CREW REPORTED COCKPIT PAC OVERHEAT LIGHT ON AT FL 410. LIGHT STAYED ON AFTER LANDING. INVESTIGATION FOUND FAULT Y PAC OVERHEAT SWITCH. REPLACEMENT SWITCH CLEARED PROBLEM. 2 L 7 2 4F A9NM 1996101000364 19961010 00364 SO 1996 10 10 96ZZZX5056 1 19960918 G 3500 8RC1500HT CYLINDER FR149A2114 GULSTM G1159 G1159 3953505 SO OXYGEN SYSTEM MISMARKED B LC2R K NONE W INADEQUATE Q C IN INSP/MAINT 1 CE 01 125JJ 961751P 15 SECTIONS 173.34(3) (13) (1V). MARKING D.O. T3HT SPECIFICATION CYLINDERS WITH A HIGH STRESS MARKING STAMP. CYLINDERS ARE REQUIRED TO BE MARKED WITH A LOW STRESS MARKING STAMP. EX: 8-16-96 TEST NRS. 7 AND 8. 2 L 7 2 4F RT A12EA 1996101000365 19961010 00365 SO 1996 10 10 96ZZZX5057 1 19960918 G 3500 8RC1500HT CYLINDER FR149A2114 GULSTM G1159 G1159 3953505 SO OXYGEN SYSTEM MISMARKED B LC2R K NONE W INADEQUATE Q C IN INSP/MAINT 1 CE 01 125JJ 961700P 15 SECTIONS 173.34(3) (13) (1V). MARKING D.O. T3HT SPECIFICATION CYLINDERS WITH A HIGH STRESS MARKING STAMP. CYLINDERS ARE REQUIRED TO BE MARKED WITH A LOW STRESS MARKING STAMP. EX: 8-16-96 TEST NRS. 7 AND 8. 2 L 7 2 4F RT A12EA 1996101000366 19961010 00366 CE 1996 10 10 96ZZZX5058 1 19960913 G 2612 99140921 FIRE LOOP CESSNA 650 650 2076802 CE LT ENG DETECTOR FAULTY D K NONE N FALSE WARNING IN INSP/MAINT 1 GL 09 1UP 1836 6500224 FLIGHT CREW REPORTED LEFT FIRE DETECTOR FAIL ANNUNCIATOR LIGHT ON. FIRE TEST NORMAL. INVESTIGATION REVEALED FIRE DETEC TOR LOOP RUBBED THROUGH INBOARD SIDE UNDER AFT ENGINE SHROUD. REPLACEMENT LOOP CLEARED PROBLEM. 2 L 7 2 4F A9NM 1996101000367 19961010 00367 CE 1996 10 10 96ZZZX5059 1 19960913 G 3040 99141242 VALVE CESSNA 650 650 2076802 CE ANTI-ICE MASTER FAULTY D K NONE O OTHER IN INSP/MAINT 1 GL 09 1UP 1787 6500224 FLIHGT CREW REPORTED LEFT EMERGENCY PRESSURIZATION WOULD NOT WORK UNLESS WINDSHIELD AIR SELECTOR ON. INVESTIGATION REVEA LED FAULTY ANTI-ICE MASTER VALVE. REPLACEMENT VALVE CLEARED PROBLEM. 2 L 7 2 4F A9NM 1996101000368 19961010 00368 CE 1996 10 10 96ZZZX5060 1 19960730 G 5210 10143014253 DOOR BEECH 200 200CBEECH 1152926 CE CABIN DR HINGE CRACKED D A K NONE O OTHER IN INSP/MAINT 1 NM 09 111NS 5877 BL36 FLIGHT CREW REPORTED SEEING LIGHT THROUGH CABIN DOOR AROUND HINGE AREA. ON INSPECTION, FOUND DOOR CRACKED OVER 10 INCHES LONG ABOVE HINGE ATTACHMENT. THE DOOR WAS REPLACED. 1 L 7 2 4T A24CE 1996101000369 19961010 00369 1996 10 10 96ZZZX5061 4 19960522 G 3442 ART2100 SENSOR BENDIX 07101550101 BEECH 200 B200 1152922 CE RADAR ANT STAB MALFUNCTIONED B FR2R K NONE O OTHER IN INSP/MAINT 1 SW 01 128V 1016 BB1442 ART-2100, SN 1016, SAME OLD PROBLEMS. STABILIZATION TOO SENSITIVE. PAINT HEAVY IN ROLL LEFT OR RIGHT. AUTOTILT DROPS ANTENNA. BENDIX/KING RECOMMENDED FACTORY EXCHANGE ART-2100, SN 1016. INSTALLED ART-2100, SN 1044. 1 L 7 2 4T A24CE 1996101000371 19961010 00371 1996 10 10 96ZZZX5063 4 19960625 G 3442 ART2100 SENSOR BENDIX 07101550101 BEECH 200 B200 1152922 CE RADAR ANT STAB MALFUNCTIONED B FR2R K NONE O OTHER IN INSP/MAINT 1 SW 01 128V 1044 BB1442 ART-2100, SN 1044, SAME OLD STAB PROBLEMS. ALSO, PAINTS SQUIGGLES BEYOND 40 MILE RANGE IN 'HEAVY THUNDERSTORMS'. BENDI X/KING RECOMMENDED STC MOD. EXCHANGED ART-2100 WITH NEW SOFTWARE LEVEL 01/03 AND MOD 2 FOR STC COMPENSATION. INSTALLED ART-2100, SN 1026. 1 L 7 2 4T A24CE 1996101000372 19961010 00372 1996 10 10 96ZZZX5064 4 19960405 G 3442 ART2100 SENSOR BENDIX 07101550101 BEECH 200 B200 1152922 CE RADAR ANT STAB MALFUNCTIONED B FR2R K NONE O OTHER IN INSP/MAINT 1 SW 01 128V 1018 BB1442 ART-2100, SN 1018, SAME PROBLEMS AFTER PREVIOUS SOFTWARE CHANGE. STABLIZATION TOO SENSISTIVE. PAINTS HEAVY LEFT OR RIG HT. AUTOTILT DROPS ANTENNA. INSTALLED ART-2100, SN 1016, SN DASH 01/02 MOD DASH 1. 1 L 7 2 4T A24CE 1996101000373 19961010 00373 1996 10 10 96ZZZX5065 4 19960130 G 3442 ART2100 SENSOR BENDIX 07101550101 BEECH 200 B200 1152922 CE RADAR ANT STAB MALFUNCTIONED B FR2R K NONE O OTHER IN INSP/MAINT 1 SW 01 128V 1018 BB1442 ART-2100, SN 1018 SOFTWARE S/W DASH 01/01, MOD 1. STABILIZATION TOO SENSITIVE. PAINTS HEAVY LEFT/RIGHT. AUTOTILT DRO PS ANTENNA. BENDIX/KING RECOMMENDED SOFTWARE CHANGE. INSTALLED ART-2100. NEW SOFTWARE LEVEL S/W DASH 01/02, MOD 1. N O ATTEMPT WAS MADE TO FIX 'AUTOTILT'. 1 L 7 2 4T A24CE 1996101000375 19961010 00375 WP 1996 10 10 96ZZZX5067 2 19960901 G 7310 300297719 MANIFOLD AMD FALC20 FALCON200 2730150 EU GARRTT ATF3 ATF36A4 29002 WP LT ENGINE CRACKED B GQRR K NONE O OTHER IN INSP/MAINT 1 SW 05 200WY P426C P21122 509 FUEL MANIFOLD SHROUD WAS FOUND CRACKED. REPLACED WITH SERVICEABLE UNIT. UNKNOWN IF FUEL WAS LEAKING FROM MANIFOLD. AF TT: 3,358 HOURS. LE TT: 3,653 HOURS. TC LE: 2,655. 2 L 7 2 4F 4 F RT A7EU E7WE 1996101000376 19961010 00376 WP 1996 10 10 96ZZZX5068 2 19960901 G 7240 300174517 LINER AMD FALC20 FALCON200 2730150 EU GARRTT ATF3 ATF36A4 29002 WP COMB LINER CRACKED B GQRR K NONE O OTHER IN INSP/MAINT 1 SW 05 200WY 509 P21122 DURING ROUTINE 600 HOUR INSPECTION, DISCOVERED SEVERAL COMBUSTION LINER CRACKS OUTSIDE OF MM LIMITATIONS. REMOVED AND R EPLACED LINER. AFTT: 3,358 HOURS. LE TT: 3,653 HOURS. TC: 2,655. 2 L 7 2 4F 4 F RT A7EU E7WE 1996101000377 19961010 00377 WP 1996 10 10 96ZZZX5069 2 19960901 G 7250 30031522 MID FRAME AMD FALC20 FALCON200 2730150 EU GARRTT ATF3 ATF36A4 29002 WP LT ENGINE CERAMIC FLAKING B GQRR K NONE O OTHER IN INSP/MAINT 1 SW 05 200WY 5P3930 509 P21122 BLADE TIP SEALING CERAMIC FLAKED OFF 30 TO 40 PERCENT OF AREA. NO DETECTABLE RESULTING DISCREPANCY. DISCOVERED DURING SCHEDULED 600 HOUR INSPECTION BORESCOPE INSPECTION. NEW INNER MID-FRAME ASSY INSTALLED TO CORRECT PROBLEM. AFTT: 3,35 8 HOURS. LE TT: 3,653 HOURS. TC: 2,655. 2 L 7 2 4F 4 F RT A7EU E7WE 1996101000378 19961010 00378 CE 1996 10 10 96ZZZX5070 1 19960913 G 3240 07515500 TORQUE PLATE PARKERHANFIN 19990 BEECH 90 C90A 1152911 CE WHEEL BRAKE CRACKED B S DYTR K NONE O OTHER IN INSP/MAINT 1 SO 15 301ER 1767 LJ1286 DURING A ROUTINE PHASE INSPECTION, A WHEEL BRAKE GUIDE PIN BUSHING WAS FOUND LOOSE. CLEANING AND INSPECTION REVEALED A CRACK WITH A WIDE GAP IN THE CASTING. STC NR SA619GL. 1 L 7 2 3T RT 3A20 1996101000379 19961010 00379 NM 1996 10 10 96ZZZX5071 1 19960807 G 2612 FIRE WARNING BOEING 747 747SP09 1384903 NM AFT CARGO ACTIVATED D F ACTIVATE FIRE EXT. N FALSE WARNING CR CRUISE 1 SW 99 4522V 22805 SIN/JNB - FLT CI-091 - 8-7-96, AFTER FLIGHT OF 9 HOURS 20 MINUTES, FL 4,300 FEET, AFT CARGO FIRE WARNING LIGHT ILLUMINAT ED. BOTH FIRED BOTTLES DISCHARGED. BOTH FIRE BOTTLES CHANGED. NR 3 AND NR 4 SMOKE DETECTOR CHANGED. FIRE WARNING AMP LIFIER CHANGED. ALL FUNCTIONAL TESTS PASSED IAW MM 26-16-00. 2 L 7 4 4F A20WE 1996101000380 19961010 00380 CE 1996 10 10 96ZZZX5072 1 19960918 G 3230 42000118 RELIEF VALVE 2129402 CESSNA 500 550 2076604 CE EMERG GEAR BOTL LEAKING D A K NONE O OTHER IN INSP/MAINT 1 GL 25 602AT 626 5500606 UPON ACTIVATION OF GEAR BLOW-DOWN TO TEST NEWLY INSTALLED BOTTLE, AFTER 3 GREENS WERE OBTAINED THE BODY OF THE RELIEF VA LVE WAS LEAKING AROUND SEAM QUICKLY DEPLETING SUPPLY OF NITROGEN. THIS OCCURRED ON 3 BOTTLES IN A ROW FROM SAME VENDOR. 1 L 7 2 4F A22CE 1996101000381 19961010 00381 SO 1996 10 10 96ZZZX5073 1 19960920 G 2421 28B13512GA ALTERNATOR GULSTM G1159 G1159B 3953535 SO LT GENERATOR FAILED D O OTHER H ELECT. POWER LOSS-50 PC CR CRUISE 1 NM 01 812RS 15 243M 098 LEFT AC GENERATOR SUSPECT FAILED. DROPPED OFF LINE IN-FLIGHT. TVI FROM .5 TO 2.0 IPS. NOTED DEBRIS AROUND MOUNTING FL ANGE UPON INSPECTION. REPLACED ALTERNATOR. THIS IS THE 3RD AC GENERATOR FAILURE WITH A REAL LOW TSO IN THE LAST 6 MONT HS, BEARINGS FAILED. 2 L 7 2 4F RT A12EA 1996101000382 19961010 00382 EA 1996 10 10 96ZZZX5074 2 19960913 G 7200 ENGINE BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA RT ENGINE FAILED B L PIQR O OTHER J WARNING INDICATION CR CRUISE 1 EA 21 859CC BB389 80383 ACFT HAD IN-FLT FAILURE OF RT ENG, AS ACFT REACHED CRUISE ALTITUDE. ENG HAS TTSN 7,559.4, TSHSI 120.9, TSO1605.3. A PR ELIM INSP OF ENG FND LARGE OIL STAIN ACROSS TOP OF NACELLE AND OIL DRIPPING FROM COWLING. PROP WOULD NOT ROTATE IN NORM AL DIRECTION OF ROTATION, BUT WOULD ROTATE COUNTERCLOCKWISE WITH GRINDING SOUND. INTERIOR OF EXH STACKS FND TO CONTAIN MANY SMALL CHUNKS OF METAL. UPON OPENING COWLING, COMP HOUSING FND DISTORTED AND ALL INLET SUPPORT STRUTS HAD FAILED. C OMP MAIN SHAFT OFF CENTER AND ALL BLADES DESTROYED. AFT SECT OF COMP HOUSING AND ACCY GRBX SHIFTED 3 INCHES AFT. APPE ARS MOST OF OIL LOSS OCCURRED WHEN ACCY GRBX SHIFTED, DISCONNECTING EXT OIL PRESS AND RETURN TUBES. 1 L 7 2 4T 4 T A24CE E4EA 1996101000383 19961010 00383 SO 1996 10 10 96ZZZX5075 1 19960918 G 3230 WTC22171 SHUTTLE VALVE PIPER PA42 PA42 7104202 SO RT MLG ACTUATOR DAMAGED D K NONE K FLUID LOSS NR NOT REPORTED 1 SW 15 930CA 428001030 NIPPLE OF VALVE TO MAIN GEAR ACTUATOR BROKE OFF CAUSING LOSS OF FLUID AND FAILURE OF RIGHT GEAR TO DOWNLOCK. 1 L 7 2 4T A23SO 1996101000384 19961010 00384 CE 1996 10 10 96ZZZX5076 1 19960911 G 2612 302158 FLAME DETECTOR PYROTECTOR BEECH 200 B200 1152922 CE LT ENGINE MALFUNCTIONED B LX5R K NONE N FALSE WARNING NR NOT REPORTED 1 GL 19 991LL 6546 79373 BB1234 LEFT ENGINE FIRE LIGHT CAME ON, SIGNAL VOLTAGE TOO HIGH. BEECH HAS NEW STYLE FLAME DETECTOR FOR BETTER RELIABILITY. 1 L 7 2 4T A24CE 1996101000385 19961010 00385 1996 10 10 96ZZZX5077 4 19960907 G 2565 60322103 ASPIRATOR AIRCRUISERS AIRBUS 320 A320231 3930325 EU EVAC SLIDE DAMAGED A A ET3R K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 21 45114 EVACUATION SLIDE DEFECTIVE. NO MALFUNCTION OCCURRED. DAMAGE WAS DISCOVERED DURING ROUTINE OVERHAUL. SUSPECT CAUSE: I MPROPER PACKING PROCEDURES CAUSING BOTH ASPIRATOR BODIES TO BE DEFORMED. ONE SO BADILY STRESSED, A WELD WAS BROKEN. REC OMMENDATION: ENSURE PROPER PACKING PROCEDURES ARE FOLLOWED. VISUALLY INSPECT ASPIRATORS AFTER PACKING. DISTORTION CAN BE FOUND BY LOOKING INSIDE WITH LIGHT. 2 L 7 2 4F RT A28NM 1996101000386 19961010 00386 NM 1996 10 10 96ZZZX5078 1 19960916 G 2782 1103044 BODY ASSY 1U11032 BOEING 727 727 1384001 NM SLAT ACTUATOR CHROME FLAKE B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 175 ACTUATOR CHROME FLAKING FROM INSIDE MAIN CYLINDER BORE/POOR ADHESION UPON RECHROME. 2 L 7 3 4F A3WE 1996101000387 19961010 00387 NE 1996 10 10 96ZZZX5079 2 19960827 G 7210 7757582 BEARING HAMSTD 7757582 SAAB SF340 SF340A 7850100 EU GE CT7TP CT79B 30030 NE GC 49 GEARCASE SPALLED B S A K NONE O OTHER IN INSP/MAINT 1 SW 99 11502 8137 GEE785540 DISASSEMBLY OF GEARCASE REVEALED THE AFT ROLLER BEARING ASSEMBLY SHOWED HEAVY SPALLING OF ALL BEARING COMPONENTS (775758 -2) (ITEM 10, FIG 7, AND ITEM 110, FIG 8 IPL). 2 L 7 2 4T 4 T RT A52EU E8NE 1996101000388 19961010 00388 NE 1996 10 10 96ZZZX5080 2 19960916 G 7210 7757651 ROLLER BEARING HAMSTD 7758001 SAAB SF340 SF340A 7850100 EU GE CT7TP CT79B 30030 NE GC 49 GEARCASE CAGE BROKEN A A SI3R K NONE O OTHER IN INSP/MAINT 1 NE 03 13095 5237 GEE367358 DISASSEMBLY OF GEARCASE REVEALED THE FORWARD INPUT ROLLER BEARING CAGE WAS BROKEN (775765-1, FIG 5, ITEM 180 OF 72-11-02 PARTS LIST). ALSO,THE INPUT PINION GEAR HAS STARTED TO HAVE SEVERE TOOTH BREAK DOWN (775755-3, FIG 3, ITEM 1558). BOT H IDLER GEARS ALSO HAD TOOTH WEAR. LT IDLER SN 1C6411358A (775753-5, FIG 8-40B). RT IDLER SN 1C64411268A (775754-5, FI G 8-75B).` 2 L 7 2 4T 4 T RT A52EU E8NE 1996101000389 19961010 00389 NM 1996 10 10 96ZZZX5081 1 19960725 G 3610 797839 VALVE SHAFT HAMSTD 77385618 BOEING 747 747* NM PRESS CK VLV WORN B SI3R K NONE O OTHER IN INSP/MAINT 1 NE 03 830716 ANTI-ROTATION SLOTS ARE WORN AWAY ON VALVE SHAFT CAUSING SHAFT TO ROTATE AND SHAFT SHOULDER TO WEAR EXCESSIVELY. REF: O HM 36-12-06, PAGE 606, FIGURE 603. 2 L 7 4 4F RT A20WE 1996101000390 19961010 00390 NM 1996 10 10 96ZZZX5082 1 19960725 G 3610 797839 VALVE SHAFT HAMSTD 77385618 BOEING 747 747* NM PRESS CHK VLV WORN B SI3R K NONE O OTHER IN INSP/MAINT 1 NE 03 830913 ANTI-ROTATION SLOTS ARE WORN AWAY ON VALVE SHAFT CAUSING SHAFT TO ROTATE AND SHAFT SHOULDER TO WEAR EXCESSIVELY. REF: O HM 36-12-06, PAGE 606, FIGURE 603. 2 L 7 4 4F RT A20WE 1996101000391 19961010 00391 SO 1996 10 10 96ZZZX5083 1 19960916 G 3710 MILH6000 HOSE PIPER PA34 PA34200T 7103406 SO LOW PRESS PNEU DEFECTIVE B APCR K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 01 PURSUANT TO BEECHCRAFT SAFETY COMMUNIQUE DATED 8, 1996,AIRCRAFT AND PARTS INVENTORY ARE BEING INSPECTED FOR BAD HOSE STO CK WITH DATE CODE AS LISTED IN COMMUNIQUE. TEN FEET OF THIS HOSE FOUND IN STOCK INVENTORY. SUGGEST AD NOTE ON HOSE. A S MANY AIRCRAFT OTHER THAN BEECH/RAYTHEON MAY BE AFFECTED DUE TO COMMON HOSE USAGE. 1 L 7 2 3O A7SO 1996101000392 19961010 00392 GL 1996 10 10 96ZZZX5084 2 19960911 G 7313 5233414 FILTER ASSY 6890917 HUGHES 369 369E 4470707 WP ALLSN 250C 250C20B 03013 GL FUEL NOZZLE CRUSHED E K NONE R PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 EA 23 577DB 296 AG45257 0381E CAE836296 PILOT EXPERIENCED N2 DROOP ON TAKEOFF WITH SLOW RECOVERY. CONDITION WORSENED DURING TROUBLESHOOTING UNTIL ENGINE WOULD NOT ACHIEVE IDLE SPEED. FUEL NOZZLE REMOVED AND DISASSEMBLED. FILTER ELEMENT FOUND CRUSHED AND TWISTED, RESTRICTING FU EL FLOW AT SPEEDS ABOVE IDLE SPEED. NO FUEL CONTAMINATION EVIDENT IN AIRFRAME FILTER OR FCU FILTER. IT IS POSSIBLE FIL TER ELEMENT WAS CRUSHED AT TIME OF OVERHAUL AND IS NOT A REGULAR INSP ITEM EXCEPT FOR CLEANING. SUBMITTER RECOMMENDS FI LTER BE INSP AT 100-HOUR INTERVALS PAYING ATTN TO SEATING FILTER ELEMENT BEFORE FURTHER ASSY IAW MDHC/ACT MM AND INSPECT ANY NOZZELS IN STOCK OR UPON RECEIVING FROM O/H FOR THIS CONDITION. 1 G 7 1 3U 3 U H3WE E4CE 1996101000395 19961010 00395 1996 10 10 96ZZZX5087 4 19960901 G 3421 KG258 GYRO KING COCKPIT HORIZ MISMODIFIED H K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 99 9437 GYRO MODIFIED FORM ZERO DEGREES TILT PANEL TO 8 DEGREES TILT PANEL. TALKED TO KING. THIS IS NOT AN AUTHORIZED MOD PART NUMBER AND DECAL CHANGED. INDICATOR OUT OF TOLERANCE. 1996101000396 19961010 00396 CE 1996 10 10 96ZZZX5088 1 19960706 G 2612 302158 FIRE DETECTOR BEECH 200 200BEECH 1152920 CE RT ENGINE MOISTURE CONTAM E A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 WP 23 12NG 7086 BB581 AIRCRAFT DEPARTED WARNER ROBBINS AFB IN LIGHT RAIN SHOWERS. AS ACFT BROKE THREW OVERCAST LAYER, RT ENG FIRE WARNING LIG HT ILLUMINATED. FLIGHT CREW MONITORED ENG PARAMETERS AND ENG COWLING. NO ABNORMAL CONDITIONS NOTED. CHECK LIST REVIEW ED AND ACFT RETURNED TO WARNER ROBBINS AFB, UNEVENFUL LANDING MADE. ACFT TURNED OVER TO MAINTENANCE. INSP FOUND MOISTU RE CONTAMINATION OF THE UPPER AFT. FIRE DETECTOR, PIN 30-215-8. NECESSARY REPAIRS MADE AND ACFT RETURNED FOR SERVICE. SUBMITTER SUGGESTS MFG IMPROVE SEALING METHOD OF WIRING TO DETECTOR. 1 L 7 2 4T A24CE 1996101000456 19961010 00456 CE 1996 10 10 96ZZZX5099 1 19960910 G 3260 1SE13 SWITCH CESSNA 340 340A 2076405 CE RT MLG DOWNLOCK FAILED D L ABORTED APPROACH P NO WARNING INDICATION AP APPROACH 1 EA 03 1232K 4015 340A1815 UPON LANDING, THE GEAR WAS EXTENDED AND NO RIGHT MAIN INDICATION WAS NOTED THAT IT WAS DOWN AND LOCKED. AFTER A FLY-BY THE TOWER, THE GEAR WAS DETERMINED TO BE DOWN. THE AIRCRAFT WAS LANDED SAFELY. PART FAILED DUE TO AGE. 1 L 7 2 3O 3A25 1996101000457 19961010 00457 CE 1996 10 10 96ZZZX5100 1 19960917 G 3231 35815125602 RETRACT ROD BEECH 35 V35B 1151548 CE LT MLG DEFECTIVE D K NONE O OTHER IN INSP/MAINT 1 CE 05 2021E 1586 D10158 BEARING SUPPORT IN INBOARD END OF RETRACT ROD FOUND LOOSE. ROD REPLACED WITH NEW PART FROM BEECH. SUBMITTER STATED THI S IS THE SECOND AIRCRAFT OF THIS TYPE TO HAVE THE SAME DEFECT IN TWO MONTHS. 1 L 7 1 3O 3A15 1996101000458 19961010 00458 CE 1996 10 10 96ZZZX5101 1 19960917 G 3251 STEERING CAP BEECH 35 V35B 1151548 CE NLG BOLTS LOOSE D K NONE O OTHER IN INSP/MAINT 1 CE 05 2021E 1586 D10158 BOLTS IN NOSE GAR STEERING CAP FOUND LOOSE. SUBMITTER STATED THIS IS THE SECOND AIRCRAFT OF THIS TYPE TO HAVE THIS DEFE CT IN TWO MONTHS. 1 L 7 1 3O 3A15 1996101000459 19961010 00459 CE 1996 10 10 96ZZZX5102 1 19960923 G 5510 17320312 BRACKET CESSNA 177 177RG 2073709 CE STAB AFT WT ARM CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 07 2023Q 3417 177RG0423 DURING ANNUAL INSPECTION, CRACKS WERE NOTED ON (3 OF THE 4) STABILATOR WEIGHT ARM MOUNT BRACKETS. CAUSE, NORMAL WEAR AN D VIBRATION. SUBMITTER RECOMMMENDS CLOSER INSPECTION AND DYE CHECK. ALSO INCLUDES FORWARD MOUNT P/N 1732010-1 AND DASH 2. 1 H 7 1 3O A20CE 1996101000460 19961010 00460 CE 1996 10 10 96ZZZX5103 1 19960923 G 5510 17320311 BRACKET CESSNA 177 177RG 2073709 CE STAB AFT WT ARM CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 07 2023Q 3417 177RG0423 DURING ANNUAL INSPECTION, CRACKS WERE NOTED ON (3 OF THE 4) STABILATOR WEIGHT ARM MOUNT BRACKETS. CAUSE, NORMAL WEAR AN D VIBRATION. SUBMITTER RECOMMMENDS CLOSER INSPECTION AND DYE CHECK. ALSO INCLUDES FORWARD MOUNT P/N 1732010-1 AND DASH 2. 1 H 7 1 3O A20CE 1996101000461 19961010 00461 SO 1996 10 10 96ZZZX5104 1 19960604 G 5751 86396803 RIB PIPER PA44 PA44180 7104402 SO RT AILERON LE CRACKED D A K NONE O OTHER IN INSP/MAINT 1 WP 17 2199Z 5100 447995297 DURING A ROUTINE INSPECTION (100 HOUR), EXCESSIVE LATERIAL PLAY WAS DISCOVERED AT RT AILERON TO THE POINT OF CONTACTING WING TIP. FURTHER INVESIGATION FOUND ALL 3 LEADING EDGE RIBS WHICH SUPPORT THE HINGES CRACKED. THESE RIBS ARE DIFFICUL T TO INSPECT DUE TO THE LEADING EDGE SKIN COVERING THE AREA AND NO INSPECTION PANELS ARE AVAILABLE. ALL 5,100 HOURS IN SERVICE WERE FLIGHT TRAINING. 1 L 7 2 3O A19S0 1996101000462 19961010 00462 SO 1996 10 10 96ZZZX5105 1 19960604 G 5751 86398803 RIB PIPER PA44 PA44180 7104402 SO RT AILERON LE CRACKED D K NONE O OTHER IN INSP/MAINT 1 WP 17 2199Z 5100 447995297 DURING A ROUTINE INSPECTION (100 HOUR), EXCESSIVE LATERIAL PLAY WAS DISCOVERED AT RT AILERON TO THE POINT OF CONTACTING WING TIP. FURTHER INVESIGATION FOUND ALL 3 LEADING EDGE RIBS WHICH SUPPORT THE HINGES CRACKED. THESE RIBS ARE DIFFICUL T TO INSPECT DUE TO THE LEADING EDGE SKIN COVERING THE AREA AND NO INSPECTION PANELS ARE AVAILABLE. ALL 5,100 HOURS IN SERVICE WERE FLIGHT TRAINING. 1 L 7 2 3O A19S0 1996101000463 19961010 00463 SO 1996 10 10 96ZZZX5106 1 19960604 G 5751 86399803 RIB PIPER PA44 PA44180 7104402 SO RT AILERON LE CRACKED D K NONE O OTHER IN INSP/MAINT 1 WP 17 2199Z 5100 447995297 DURING A ROUTINE INSPECTION (100 HOUR), EXCESSIVE LATERIAL PLAY WAS DISCOVERED AT RT AILERON TO THE POINT OF CONTACTING WING TIP. FURTHER INVESIGATION FOUND ALL 3 LEADING EDGE RIBS WHICH SUPPORT THE HINGES CRACKED. THESE RIBS ARE DIFFICUL T TO INSPECT DUE TO THE LEADING EDGE SKIN COVERING THE AREA AND NO INSPECTION PANELS ARE AVAILABLE. ALL 5,100 HOURS IN SERVICE WERE FLIGHT TRAINING. 1 L 7 2 3O A19S0 1996101000464 19961010 00464 EU 1996 10 10 96ZZZX5107 1 19960719 G 2701 TB1023012100 SUPPORT SOCATA TB9 TB9 8680694 EU YOKE LT/RT CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 07 28216 2885 1063 DURING ROUTINE 100-HOUR ANNUAL INSPECTION, FOUND BOTH RT AND LT YOKE SUPPORTS CRACKED IN RADIUS OF BEND WHICH FORMS AFT FLANGE OF SUPPORT. THE CRACKS WERE QUITE SEVERE, ONE SIDE BEING COMPLETELY SEVERED, AND THE OTHER SIDE BEING VERY CLOSE TO SEVERED. THE CRACKS ARE IMPOSSIBLE TO SEE WITHOUT TILTING THE PILOT'S INSTRUMENT PANEL. CORRECTIVE ACTION CONSISTS OF REPLACING LT AND RT SUPPORTS WITH NEW UNITS. IT IS THE SUBMITTER'S OPINION THIS DAMAGE IS CAUSED BY THE TRANSFERRIN G OF LOADS FROM THE CONTROL LOCK ASSEMBLY. 1 L 7 1 3O NT AS1EU 1996101000465 19961010 00465 EU 1996 10 10 96ZZZX5108 1 19960719 G 2701 TB1023012101 SUPPORT SOCATA TB9 TB9 8680694 EU YOKE LT/RT CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 07 28216 2885 1063 DURING ROUTINE 100-HOUR ANNUAL INSPECTION, FOUND BOTH RT AND LT YOKE SUPPORTS CRACKED IN RADIUS OF BEND WHICH FORMS AFT FLANGE OF SUPPORT. THE CRACKS WERE QUITE SEVERE, ONE SIDE BEING COMPLETELY SEVERED, AND THE OTHER SIDE BEING VERY CLOSE TO SEVERED. THE CRACKS ARE IMPOSSIBLE TO SEE WITHOUT TILTING THE PILOT'S INSTRUMENT PANEL. CORRECTIVE ACTION CONSISTS OF REPLACING LT AND RT SUPPORTS WITH NEW UNITS. IT IS THE SUBMITTER'S OPINION THIS DAMAGE IS CAUSED BY THE TRANSFERRIN G OF LOADS FROM THE CONTROL LOCK ASSEMBLY. 1 L 7 1 3O NT AS1EU 1996101000466 19961010 00466 EU 1996 10 10 96ZZZX5109 1 19960919 G 2701 TB1023012100 SUPPORT SOCATA TB9 TB9 8680694 EU YOKE LT/RT CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 07 28199 2970 1062 DURING ROUTINE 100-HOUR INSPECTION, FOUND BOTH RT AND LT YOKE SUPPORTS CRACKED IN RADIUS OF BEND WHICH FORMS AFT FLANGE OF SUPPORT. THE CRACKS WERE QUITE SEVERE, ONE SIDE BEING COMPLETELY SEVERED, AND THE OTHER SIDE BEING VERY CLOSE TO SEV ERED. THE CRACKS ARE IMPOSSIBLE TO SEE WITHOUT TILTING THE PILOT'S INSTRUMENT PANEL. CORRECTION ACTION CONSISTS OF REP LACING LT AND RT SUPPORTS WITH NEW UNITS. IT IS THE SUBMITTER'S OPINION THIS DAMAGE IS CAUSED BY THE TRANSFERRING OF LO ADS FROM THE CONTROL LOCK ASSEMBLY. 1 L 7 1 3O NT AS1EU 1996101000467 19961010 00467 EU 1996 10 10 96ZZZX5110 1 19960919 G 2701 TB1023012101 SUPPORT SOCATA TB9 TB9 8680694 EU YOKE LT/RT CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 07 28199 2970 1062 DURING ROUTINE 100-HOUR INSPECTION, FOUND BOTH RT AND LT YOKE SUPPORTS CRACKED IN RADIUS OF BEND WHICH FORMS AFT FLANGE OF SUPPORT. THE CRACKS WERE QUITE SEVERE, ONE SIDE BEING COMPLETELY SEVERED, AND THE OTHER SIDE BEING VERY CLOSE TO SEV ERED. THE CRACKS ARE IMPOSSIBLE TO SEE WITHOUT TILTING THE PILOT'S INSTRUMENT PANEL. CORRECTION ACTION CONSISTS OF REP LACING LT AND RT SUPPORTS WITH NEW UNITS. IT IS THE SUBMITTER'S OPINION THIS DAMAGE IS CAUSED BY THE TRANSFERRING OF LO ADS FROM THE CONTROL LOCK ASSEMBLY. 1 L 7 1 3O NT AS1EU 1996101000468 19961010 00468 CE 1996 10 10 96ZZZX5111 1 19960810 G 3244 650X10 TIRE CESSNA 402 402C 207590R CE LT MLG FLAT I K NONE O OTHER IN INSP/MAINT 1 NE 05 3249M 196 B3M6274 402C0296 AFTER COMPLETION OF FLIGHT AT THE GATE, FLIGHT CREW NOTICED LT MAIN TIRE FLAT. UPON TEAR-DOWN INSPECTION, NOTED WIRE FR OM SIDE WALL DAMAGED THE TUBE. TOTAL TIME ON TIRE, 196 HOURS. MCCRARY 6.50X10, 8-PLY RECAP. 1 L 7 2 3O A7CE 1996101000469 19961010 00469 EA 1996 10 10 96ZZZX5112 2 19960920 G 8520 LIFTER PIPER PA28 PA28151 7102805 SO LYC O320 O320E3D 41508 EA CYL NR 4 LOBE FAILED B CB1R K NONE O OTHER IN INSP/MAINT 1 GL 05 43125 2243 287415430 L3796827A LIFTER FAILED AT NR 4 CYLINDER CAM LOBE. LOBE DAMAGED AND PEENED ON CAMSHAFT. CRANKSHAFT PILOT END, BENT OVER LIMITS. FLANGE ON CRANKSHAFT OUT OF LIMITS ON RUN-OUT. FINDINGS RESULT OF ENGINE, TIME EXPIRED INSPECTION. 1 L 7 1 3O 3 O 2A13 E274 1996101000470 19961010 00470 CE 1996 10 10 96ZZZX5113 1 19960923 G 5712 57222061 RIB CESSNA 441 441 2076020 CE RT WING CANTED CRACKED B WTXR K NONE O OTHER IN INSP/MAINT 1 NM 07 441LL 5923 4410139 DURING PHASE INSPECTION, FOUND 1.5 INCH CRACK IN RT WING CANTED RIB TOP CAP. CRACK STARTS AT AFT SIDE OF FORWARD SPAR A ND RUNS AFT PARALLEL TO THE BEND RADIUS. STOP DRILL CRACK PER CESSNA INSTRUCTIONS. 1 L 7 2 3T RT A28CE 1996101000471 19961010 00471 SO 1996 10 10 96ZZZX5114 2 19960916 G 8530 ROCKER CESSNA 210 P210N 2073454 CE CONT O520 TSIO520P 17040 SO NR 2 CYL EXH FAILED B GNER A UNSCHED LANDING E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CR CRUISE 1 SW 01 4930K 333 P21000372 513389 WHEN AIRCRAFT WAS FLYING, A LOUD BANG WAS HEARD. MAP WENT FROM 27 INCHES TO 20 INCHES WITH NOTICEABLE LOSS OF POWER AND INCREASED VIBRATION. AIRCRAFT WAS LANDED WITHOUT DAMAGE. NR 2 ROCKER COVER REMOVED AND BALL JOINT OF EXHAUST ROCKER F OUND LAYING IN COVER. LOOKED LIKE PART HAD CRACK IN IT FOR A WHILE AND FINALLY LET GO UNDER STRESS. SUBMITTER RECOMMEN DS MAGNAFLUXING PART BEFORE INSTALLATION. 1 H 7 1 3O 3 O 3A21 E8CE 1996101000472 19961010 00472 EA 1996 10 10 96ZZZX5115 2 19960903 G 7310 S1236C30420 HOSE CESSNA 177 177RG 2073709 CE LYC O360 IO360A1B6 41514 EA FLOW DIVIDER DEFECTIVE D A A UNSCHED LANDING J K WARNING INDICATION FLUID LOSS CL CLIMB 1 EA 07 520 299 177RG1164 PILOT REPORTED A TOTAL DROP IN FUEL PRESSURE DURING CLIMB-OUT LANDING WITHOUT INCIDENT. UPON INSPECTION, FOUND FUEL PRE SSURE HOSE FROM FIREWALL TO FLOW DIVIDER LEAKING PROFUSELY WHERE THE RE-USABLE SOCKET THREADS TO HOSE. THIS HOSE WAS PU RCHASED FROM CESSNA ON 8-93 AND INSTALLED. THE METAL IDENTIFICATION BAND HAD AN ASSEMBLY DATE OF 4-85. RECOMMEND CESSN A REVIEW THEIR POLICY ON SHELF LIFE OF HOSES WHICH AT PRESENT IS CONTRARY TO THE HOSE MANUFACTURER. SUBMITTER STATED THI S SITUATION COULD HAVE BEEN CATASTROPHIC. 1 H 7 1 3O 3 O A20CE 1E10 1996101000473 19961010 00473 CE 1996 10 10 96ZZZX5116 1 19960828 G 3246 D306601 WHEEL MCAULY AN441A CESSNA 150 A150L 2071828 CE MLG BOLT SEPARATED D K NONE O OTHER NR NOT REPORTED 1 SO 16 6005J 4000 A1500305 WHEEL BOLT AND NUT SEPARATED POSSIBLY DUE TO WORN THREADS. BOLT WAS INSERTED FROM BRAKE ROTOR SIDE. WHEN NUT LEFT BOLT , BOLT HIT TORQUE LINK AND DEFORMED TORQUE LINK. IF INSTALLED FROM OUTSIDE OF WHEEL, THIS WOULD NOT OCCUR. MFG'S DRAWI NG SHOWS BOLT INSERTED FROM OUTSIDE WITH NUT ON ROTOR SIDE OF WHEEL. 1 H 7 1 3O 3A19 1996101000475 19961010 00475 CE 1996 10 10 96ZZZX5118 1 19960909 G 3230 51412044 SUPPORT CESSNA 414 414A 2075907 CE RT MLG UPLOCK CRACKED B VA1R K NONE O OTHER IN INSP/MAINT 1 SW 19 711HN 2520 414A0108 SUPPORT CRACKED/SPLIT FROM THE AFT BOLT HOLE TO FORWARD BOLT HOLE AND OUT THE FRONT. LANDING GEAR UPLOCK HAS MOVED UPWA RD ALLOWING LANDING GEAR STRUT TO CONTACT UPPER WING SKIN. WING SKIN DENTED SLIGHTLY OVER MAIN WHEEL AXLE. SUPPORT IS LATE STYLE WITH LARGER BOLTS THAN ORIGINAL. SUBMITTER STATED HAS SEEN MANY EARLY SUPPORTS FAIL, BUT THIS IS THE FIRST H EAVY SUPPORT FOUND. 1 L 7 2 3O A7CE 1996101000476 19961010 00476 CE 1996 10 10 96ZZZX5119 1 19960524 G 2434 DOFF10300B ALTERNATOR CESSNA 206 U206G 2073356 CE DC SYSTEM MALFUNCTION D K NONE H ELECT. POWER LOSS-50 PC IN INSP/MAINT 1 WP 07 756HQ 124 U20604107 PILOT ATTEMPTED START, START SOLENOID CLICKING. LOW BATTERY OUTPUT TO LOW TO CLOSE SOLENOID. ALTERNATOR CHECKED FOR CH ARGING. ALTERNATOR OUTPUT APPROXIMATELY 19.3 VDC FOR 24 VDC SYSTEM. ALTERNATOR REPLACED WITH OVERHAULED UNIT. 1 H 7 1 3O A4CE 1996101000479 19961010 00479 SO 1996 10 10 96ZZZX5122 1 19960829 G 5542 SKIN PIPER PA32 PA32R301 7103218 SO TE RUDDER CRACKED B S DFKR K NONE O OTHER IN INSP/MAINT 1 CE 05 8147B 6913 6913 32R8013048 THREE CRACKS WERE NOTICED IN SKIN OF RUDDER POSSIBLY DUE TO FATIGUE OVER TIME. REMOVED SKIN, NO INTERNAL DAMAGE FOUND. NEW SKIN INSTALLED. CRACK LENGTHS APPROXIMATELY 1 INCH. 1 L 7 1 3O A3SO 1996101000480 19961010 00480 SO 1996 10 10 96ZZZX5123 1 19960909 G 5751 8639202 FITTING PIPER PA32 PA32R301 7103218 SO LT AIL OUTBOARD LOOSE B A AMYR K NONE O OTHER IN INSP/MAINT 1 CE 05 9259V 218 3246011 DURING A 100-HOUR INSPECTION, NOTICED THE LEFT AILERON WOULD STILL MOVE AFTER STOPS WERE CONTACTED. THE OUTBOARD ATTACH FITTING WAS FOUND LOOSE AND WORKING. BOTH BOLTS THAT ATTACH THE FITTING TO THE AILERON WERE FOUND LOOSE. NO TORQUE SE AL FOUND ON ANY OF THE 4 ATTACH FITTING BOLTS ON EITHER AILERON. THE OTHER 3 FITTING BOLTS WERE CHECKED AND FOUND PROPE RLY TORQUED. TORQUING THE 2 LOOSE BOLTS SOLVED THE PROBLEM. TORQUE SEAL WAS APPLIED TO ALL 8 BOLT HEADS. SUBMITTER RE COMMENDS ALL NEW PIPER AILERON ATTACHMENT FITTINGS BE CHECKED AT THE FIRST SCHEDULED INSPECTION. 1 L 7 1 3O A3SO 1996101000844 19961010 00844 SO 1996 10 10 96ZZZX5124 1 19960916 G 7120 MOUNT PIPER PA12 PA12 7101202 SO LT BOTTOM TUBE CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 23 98922 3485 12275 AT ANNUAL INSPECTION, BOTTOM LEFT ENGINE MOUNT TUBE WAS FOUND CRACKED AT ENGINE MOUNTING FLANGE. ENGINE PREVIOUSLY CHAN GED TO LYC 0320 IN C/W STC SA-4-456. REINFORCEMENT TUBING HAD NOT BEEN EXTENDED FULL LENGTH ON BOTTOM TUBE. WELDED LEN GTH OF .8750 INCH TUBING IN PLACE TO C/W STC DRAWING. 1 H 7 1 3O A780 1996101000845 19961010 00845 SW 1996 10 10 96ZZZX5125 1 19960917 G 3340 LANDING LIGHT MOONEY M20 M20J 5870219 SW NR 1 CYL EXH WIRE CHAFED D K NONE O OTHER IN INSP/MAINT 1 EA 23 991CC 1745 241054 AN INSPECTION OF THE LANDING LIGHT CIRCUIT REVEALED THE WIRE FROM THE ENGINE COWL TO THE LIGHT CAME IN CONTACT WITH NR 1 CYLINDER EXHAUST STACK. THIS IS A RECURRING PROBLEM. THERE HAD BEEN A PREVIOUS REPAIR. THE PROBLEM AREA CAN BE VIEWE D THROUGH THE RIGHT COWL FLAP OPENING TO OBSERVE EXHAUST PIPE/WIRE CLEARANCE. 1 L 7 1 3O 2A3 1996101000846 19961010 00846 EA 1996 10 10 96ZZZX5126 2 19961002 G 7322 666915 FLOAT PIPER PA18 PA18135 7101820 SO LYC O290 O290D2 41506 EA CARBURETOR FAILED D A A UNSCHED LANDING Y ENGINE STOPPAGE CR CRUISE 1 SW 99 261 AN AIRCRAFT EXPERIENCED TOTAL POWER LOSS DURING A PERSONAL FLIGHT. AN EMERGENCY WAS DECLARED AND THE AIRCRAFT LANDED WI THOUT INCIDENT. INVESTIGATION OF THE ENGINE INCIDENT REVEALED THE FAILURE WAS CAUSED BY A FAULTY METAL FLOAT ON CARBURE TOR. THE METAL FLOAT WAS FOUND FULL OF FUEL WHICH CAUSED FLOAT SINKING. THE METAL FLOAT PN 666-915 HAD BEEN REPLACED F ROM COMPOSITE TYPE FLOAT ACCORDING TO MANUFACTURE SB MSA-1 AND IT WAS NOT AFFECTED BY THE AD 93-19-04 SB CF 1 92 DUE TO DIFFERENT CODE STAMP. 1 H 7 1 3O 3 O 1A2 E229 1996101000847 19961010 00847 CE 1996 10 10 96ZZZX5127 1 19960923 G 2510 CHEST BELT CESSNA 150 152 2071835 CE COCKPIT DEFECTIVE H K NONE O OTHER IN INSP/MAINT 1 SO 13 SUBMITTER STATED IF THE CHEST BELT IS MANDATORY, IT SHOULD BE FUNCTIONAL AND RELIABLE. IT IS NOT. SOMEONE EVEN PUT A T IE WRAP ON THE SEAT BELT CLIP POST. IT KEEPS THE CHEST BELT ATTACHED A WHILE LONGER, BUT IT IS NOT A RELIABLE CLIP. 1 H 7 1 3O NT 3A19 1996101000848 19961010 00848 CE 1996 10 10 96ZZZX5128 1 19960913 G 5520 04320031 BUSHING CESSNA 150 150L 2071826 CE ELEV RT OTBD FAILED G P A A UNSCHED LANDING F FLT CONT AFFECTED CR CRUISE 1 CE 07 18132 7706 15073810 ELEVATOR BROKE LOOSE FROM THE OUTBOARD HINGE BOLT. THE REMAINING INBOARD BRACKET BROKE OUT OF THE SPAR. 1 H 7 1 3O 3A19 1996101000849 19961010 00849 CE 1996 10 10 96ZZZX5129 1 19960913 G 5520 043200124 HINGE HALF 043200152 CESSNA 150 150L 2071826 CE ELEV RT OTBD FAILED G A A UNSCHED LANDING F FLT CONT AFFECTED CR CRUISE 1 CE 07 18132 7706 15073810 ELEVATOR BROKE LOOSE FROM THE OUTBOARD HINGE BOLT. THE REMAINING INBOARD BRACKET BROKE OUT OF THE SPAR. 1 H 7 1 3O 3A19 1996101000850 19961010 00850 EA 1996 10 10 96ZZZX5130 2 19960828 G 7310 LW120980100 LINE PIPER PA32 PA32RT300T 7103216 SO LYC O540 TIO540S1AD 41532 EA NR 3 FUEL INJ FAILED D L K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 GL 21 39603 1767 32R7887119 1554961A AIRCRAFT OPERATOR REPORTED ROUGH RUNNING ENGINE. OWNER REMOVED TOP COWL AND FOUND NR 3 FUEL INJECTION LINE COMPLETELY B ROKEN OFF AT AND JUST BEHIND WHERE NUT AND FITTING ARE WELDED TO LINE. FURTHER INSPECTION REVEALED NR 4 CYLINDER OIL RE TURN TUBE CHAFED THROUGH BY FUEL INJECTION LINE AT THIS AREA (VIBRATING). OIL RETURN LINE AND FUEL INJECTION LINE BOTH REPLACED WITH NEW PARTS. FUEL INJECTION T-FITTING ON 2ND, 4TH, AND 6TH BANK OF CYLINDERS WAS FOUND LOOSE AT THIS TIME A ND RESECURED. 1 L 7 1 3O 3 O A3SO E14EA 1996101000851 19961010 00851 SO 1996 10 10 96ZZZX5131 1 19960923 G 5711 SPAR PIPER PA28 PA28180 7102808 SO LT/RT WING CORRODED D L K NONE O OTHER IN INSP/MAINT 1 SW 15 5349L 284652 DURING FUEL TANK REMOVAL FOR DETERIORATED HOSE REPLACEMENT, FOUND CORROSION ON WING SPAR. 1 L 7 1 3O 2A13 1996101000852 19961010 00852 EU 1996 10 10 96ZZZX5132 1 19960719 G 2701 TB1023012100 SUPPORT SOCATA TB9 TB9 8680694 EU YOKE LT/RT CRACKED D S A K NONE O OTHER IN INSP/MAINT 1 EA 07 55372 3470 1188 DURING ROUTINE 100-HOUR ANNUAL INSPECTION, FOUND BOTH RT AND LT YOKE SUPPORTS CRACKED IN RADIUS OF BEND WHICH FORMS AFT FLANGE OF SUPPORT. THE CRACKS WERE QUITE SEVERE, ONE BEING COMPLETELY SEVERED, AND THE OTHER SIDE BEING VERY CLOSE TO S EVERED. THE CRACKS ARE IMPOSSIBLE TO SEE WITHOUT TILTING THE PILOT'S INSTRUMENT PANEL. CORRECTIVE ACTION CONSISTS OF R EPLACING LT AND RT SUPPORTS WITH NEW UNITS. IT IS THE SUBMITTER'S OPINION THIS DAMAGE IS CAUSED BY THE TRANSFERRING OF LOADS FROM THE CONTROL LOCK ASSEMBLY. 1 L 7 1 3O NT AS1EU 1996101000853 19961010 00853 EU 1996 10 10 96ZZZX5133 1 19960719 G 2701 TB1023012101 SUPPORT SOCATA TB9 TB9 8680694 EU YOKE LT/RT CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 07 55372 3470 1188 DURING ROUTINE 100-HOUR ANNUAL INSPECTION, FOUND BOTH RT AND LT YOKE SUPPORTS CRACKED IN RADIUS OF BEND WHICH FROMS AFT FLANGE OF SUPPORT. THE CRACKS WERE QUITE SEVERE, ONE BEING COMPLETELY SEVERED, AND THE OTHER SIDE BEING VERY CLOSE TO S EVERED. THE CRACKS ARE IMPOSSIBLE TO SEE WITHOUT TILTING THE PILOT'S INSTRUMENT PANEL. CORRECTIVE ACTION CONSISTS OF R EPLACING LT AND RT SUPPORTS WITH NEW UNITS. IT IS THE SUBMITTER'S OPINION THIS DAMAGE IS CAUSED BY THE TRANSFERRING OF LOADS FROM THE CONTROL LOCK ASSEMBLY. 1 L 7 1 3O NT AS1EU 1996101000854 19961010 00854 CE 1996 10 10 96ZZZX5134 1 19960911 G 7820 125025116R MUFFLER CESSNA 206 U206G 2073356 CE BAFFLE CONE MISSING H K NONE W INADEQUATE Q C IN INSP/MAINT 1 EA 05 206PB 230 U20603781 ON AN ANNUAL INSPECTION, FOUND CONE BAFFLE 'INTERNAL PART MISSING' ON LT MUFFLER. THIS UNIT WAS OVERHAULED AT 230 HOURS PREVIOUSLY AND WAS INSTALLATED 2 YEARS PREV ANNUAL. 1 H 7 1 3O A4CE 1996101000855 19961010 00855 GL 1996 10 10 96ZZZX5135 1 19960924 G 5540 RUDDER AMTR GAIR GLASAIRIII 05691HK GL TRAILING EDGE CONCAVE D K NONE F FLT CONT AFFECTED IN INSP/MAINT 1 GL 13 231YE 26 5192 AT APPROXIMATELY 120 MPH, THE RUDDER WOULD 'WALK' BECOMING MORE VIOLENT AS THE SPEED INCREASED. AN INSPECTION OF THE RU DDER FOUND THE RUDDER SKIN WAS SLIGHTLY CONCAVE. THE RUDDER WAS REMOVED AND THE TRAILING EDGE WAS 'SQUEEZED' IN A PRESS URE BRAKE. THIS ELIMINATED THE CONCAVE SHAPE. A FLIGHT TEST UP TO 150 MPH DETERMINED THE PROBLEM NO LONGER EXISTS. NO TE: THE CONSTRUCTION MANUAL CALLS FOR INSPECTING FOR THIS CONDITION AND DETAILS THE CORRECTIVE PROCEDURE. 1 L 7 1 3O RT EXPA1L71 1996101000856 19961010 00856 SW 1996 10 10 96ZZZX5136 1 19960903 G 3230 102053 CLUTCH SPRING 1020001 MOONEY M20 M20K 5870220 SW LT MLG ACTUATOR FAILED D A O OTHER J WARNING INDICATION AP APPROACH 1 SO 16 32DG 1426 251126 NO-BACK CLUTCH SPRING TANG BROKE OFF AND JAMMED EMERGENCY EXTENSION SYSTEM COMPLETELY. THIS PART IS SUBJECT OF MOONEY S I M20-52A DATED 10-25-94, RECOMMENDING CHANGE AT 1,000 HOURS. SUBMITTER STATED THIS SHOULD BE AN AD. OPERATOR SUCCESSF ULLY EXTENDED GEAR AFTER CIRCUIT BREAKER TRIPPED BY RESETTING BREAKER SEVERAL TIMES. (DISCOVERED DURING INSPECTION AFTE R SWITCH REPAIR). 1 L 7 1 3O 2A3 1996101000859 19961010 00859 SO 1996 10 10 96ZZZX5139 2 19960910 G 8530 649543A3 CYLINDER CESSNA 150 150M 2071830 CE CONT O200 O200A 17020 SO EXH VALVE GUIDE WORN H K NONE O OTHER IN INSP/MAINT 1 EA 05 704LY 547 15078707 255111A48 TCM CYLINDER KITS (2) PN 649543A3, 547 HOURS SINCE NEW, EXHAUST VALVE GUIDES WORE OUT (VALVE SWIMS IN GUIDES). SUSPECT CAUSE - GUIDES MADE OF POOR MATERIAL. RECOMMENDATION - BETTER QUALITY CONTROL BY TCM. 1 H 7 1 3O 3 O 3A19 E252 1996101000860 19961010 00860 EU 1996 10 10 96ZZZX5140 2 19960913 G 8530 924540 EQUALIZER TUBE DIAMON DA20A1 DA20A1 05626UX GL ROTAX 912 ROTAX912 55555 EU MANIFOLD PRESS BLOCKED D K NONE O OTHER IN INSP/MAINT 1 EA 07 854DF 17 10181 4412618 FOUND EQUALIZER TUBE BLOCKAGE AT SMALL HOLE WHERE MANIFOLD PRESSURE LINE CONNECTS. BLOCKED BY CONTAMINATES PERHAPS DUE TO MANUFACTURING. 1 L 7 1 3O 3 I NT TA4CH EXPE3I 1996101000861 19961010 00861 NE 1996 10 10 96ZZZX5141 2 19960923 G 7240 97861798P02 SCREW GE CFM56 CFM563B1 13802 NE COMBUSTION SECT FAILED B L LY2R C D ABORTED TAKEOFF RETURN TO BLOCK J WARNING INDICATION TO TAKEOFF 1 CE 07 10390 724982 ABORTED TAKEOFF DUE TO HIGH EGT. INVESIGATION FOUND DAMAGE TO HPTR BLADES. FOUND COMBUSTION SECTION SCREWS HAD BEEN RE USED AND FAILED. MANUAL CALLS FOR CENTER PUNCHING SCREW LEAKS TO AID IN REMOVAL OF THE SCREW. MANUAL CALLS FOR SCREWS TO BE DISCARDED AFTER REMOVAL. IN THIS CASE TWO SCREWS WERE REINSTALLED. 4 F E2GL 1996101000862 19961010 00862 CE 1996 10 10 96ZZZX5142 1 19960923 G 2730 265522077 CONTROL CABLE RKWELL NA265 NA26540 6402608 CE ELEV CONT FRAYED D A K NONE O OTHER IN INSP/MAINT 1 SO 16 305NT 13237 28266 LOWER AFT ELEVATOR CONTROL CABLE, FS 388 TO FS 457, SHOWED SIGNS OF CORROSION ON UPPER SURFACE 'ONLY' JUST AFT OF THE FI BERGLASS PROTECTIVE CABLE SHROUD PN 265-540425-37, FS 368 TO FS 390. CABLES ARE VISUALLY INSPECTED AT 150-HOUR INTERVAL S. CABLES ARE MANUFACTURED OF CARBON STEEL .3125 INCH IN DIAMETER WITH 10 STRANDS PRIOR TO REMOVAL. 'NO' BROKEN WIRES OR STRANDS WERE NOTED 'SMOOTH' SURFACE. REMOVED CABLE FOR FURTHER INSPECTION, FLEXED CABLE IN A MILD 'U' AND 15 WIRES I N DIFFERENT STRANDS IN A 1 INCH AREA BROKE WITH SEVERE INNER CORROSION. NOTE: CORROSION COULD BE OVERLOOKED DUE TO SMA LL SURFACE AREA EFFECTED. REMOVED CABLE FROM SERVICE. 2 L 7 2 4J A2WE 1996101000863 19961010 00863 EA 1996 10 10 96ZZZX5143 1 19960912 G 3231 600861165 UNLOCK LEVER CNDAIR CL600 CL6002B16 1900305 EA NLG DOOR STUCK B L QU2R A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 EA 17 307FX 600 600 5179 ACFT DEPARTED AFTER A 300 HR/600 HR INSPECTION . CREW SELECTED 'GEAR UP' AND HAD A RED LIGHT. CREW SELECTED 'GEAR DOWN '. HAD 3 GREEN ON MAIN GEAR. ACFT LANDED WITHOUT INCIDENT. JACKED ACFT, FOUND NLG DOOR UNLO CK LEVER STUCK IN AN 'INT ERMEDIATE' UP POSITION CAUSING RT NLG DOOR TO NOT GO FULLY CLOSED. CHECKED RIGGING OF MANUAL RELEASE CABLE TO NLG DOOR UNLOCK LEVER. FOUND LEVER WOULD NOT RETURN TO FULL DOWN POSITION WHICH IS SLIGHTLY OFF A STOP. LUBED NLG DOOR UNLOCK L EVER PIVOT POINT AND 'FREED UP' LEVER. SPRINGS ATTACHED TO LEVER RETURNED IT TO PROPER POSITION. PERFORMED GEAR RETRAC T AND EXT CKS. ACFT RETURNED TO SERVICE. 2 L 7 2 4F RT A21EA 1996101000864 19961010 00864 CE 1996 10 10 96ZZZX5144 1 19960924 G 2730 265522077 CONTROL CABLE RKWELL NA265 NA26540 6402608 CE ELEV CONT BROKEN D S A K NONE O OTHER IN INSP/MAINT 1 SO 16 312NT 10001 28232 LOWER AFT ELEVATOR CONTROL CABLE FS 388 TO FS 457, SHOWED SIGNS OF CORROSION ON UPPER SURFACE 'ONLY' JUST AFT OF FIBERGL ASS PROTECTIVE CABLE SHROUD PN 265-540425-37, FS 368 TO FS 390. CABLES ARE VISUALLY INSPECTED AT 150-HR INTERVALS. CAB LES ARE MANUFACTURED OF CARBON STEEL .3125 INCH IN DIAMETER WITH 10 STRANDS. PRIOR TO REMOVAL 'NO' BROKEN WIRES OR STRA NDS NOTED 'SMOOTH' SURFACE. REMOVED CABLE FOR FURTHER INSPECTION. FLEXED CABLE IN A MILD 'U' AND 13 BROKEN WIRES IN DI FFERENT STRANDS BROKE IN A 1 INCH AREA WITH SEVERE INNER CORROSION. NOTE: CORROSION COULD BE OVERLOOKED DUE TO SMALL SURFACE AREA EFFECTED. REMOVED CABLE FROM SERVICE. 2 L 7 2 4J A2WE 1996101000865 19961010 00865 CE 1996 10 10 96ZZZX5145 1 19960923 G 2730 265522077 CONTROL CABLE RKWELL NA265 NA26540 6402608 CE ELEV CONT FRAYED D A K NONE O OTHER IN INSP/MAINT 1 SO 16 316NT 28260 LOWER AFT ELEVATOR CONTROL CABLE FS 388 TO FS 457, SHOWED SIGNS OF CORROSION ON UPPER SURFACE 'ONLY' JUST AFT OF FIBERGL ASS PROTECTIVE CABLE SHROUD PN 265-540425-37, FS 368 TO FS 390. CABLES ARE VISUALLY INSPECTED AT 150-HR INTERVALS. CAB LES ARE MANUFACTURED OF CARBON STEEL .3125 INCH IN DIAMETER WITH 10 STRANDS. PRIOR TO REMOVAL 'NO' BROKEN WIRES OR STRA NDS NOTED 'SMOOTH' SURFACE. REMOVED CABLE FOR FURTHER INSPECTION. FLEXED CABLE IN A MILD 'U' AND 1 COMPLETE BROKEN STR AND AND 10 DIFFERENT WIRES IN DIFFERENT STRANDS IN A 1 INCH AREA BROKE WITH SEVERE INNER CORROSION. NOTE: CORROSION CO ULD BE OVERLOOKED DUE TO SMALL SURFACE AREA EFFECTED. REMOVED CABLE FROM SERVICE. 2 L 7 2 4J A2WE 1996101000867 19961010 00867 CE 1996 10 10 96ZZZX5147 1 19960829 G 3222 PISTON TUBE 62420106 CESSNA 650 650 2076802 CE NLG STRUT DISCONNECTED D K NONE O OTHER NR NOT REPORTED 1 EA 11 40N 1036 039 6507031 NOSE GEAR PISTON-TUBE DISCONNECTED FROM UPPER BARREL. LOCKING ASSY, PN 6242124-1, BACKED OFF FROM PISTON TUBE, PN 62421 22-2. THE AFT TORQUE LINK WAS THE ONLY THING WHICH PREVENTED THE PISTON TUBE, WHEEL FORK, AND NOSE WHEEL FROM SEPARATIN G FROM AIRCRAFT. LOCKING ASSY, PN 6242124-1, IS SECURED TO PISTON ASSY, PN 6242122-2, WITH 150 INCH/POUNDS OF TORQUE AN D LOCTITE 609. NO MEANS OF SAFETYING. TORQUE LINKS WERE ALSO BENT AND HAD TO BE REPLACED. 2 L 7 2 4F A9NM 1996101000868 19961010 00868 CE 1996 10 10 96ZZZX5148 1 19960904 G 3240 244537 CARRIER 99141362 CESSNA 650 650 2076802 CE NR 1 BRAKE BROKEN D K NONE O OTHER IN INSP/MAINT 1 EA 11 40N 1036 6507031 NR 1 BRAKE MAKES NOISES WHILE TOWING AIRCRAFT. FOUND FIRST CARRIER AND LINING ASSY BROKEN IN THREE PIECES. BRAKE ASSY P N 2-15-02 B. F. GOODRICH. AIRCRAFT TOTAL TIME: 1,036.9 HOURS. 753 LANDINGS. 2 L 7 2 4F A9NM 1996101000869 19961010 00869 CE 1996 10 10 96ZZZX5149 1 19960911 G 3230 12838002117 CONTROL CABLE BEECH MU300 400A 1155402 CE RT MLG EMERG FRAYED B ERYR K NONE O OTHER IN INSP/MAINT 1 SO 11 401EE 731 RK6 RIGHT LANDING GEAR UPLOCK EMERGENCY RELEASE CABLE FOUND KINKED AND FRAYED AT UPLOCK RELEASE MECHANISM. EXCESS SLACK IN CABLE MAY ALLOW CABLE END TO BEND IN EXCESS OF 90 DEGREES KINKING CABLE AND CREATING 'MEMORY' TO CAUSE CABLE TO REPEAT T HIS MOTION EVERY TIME LANDING GEAR IS CYCLED. FAILURE OF CABLE WILL PREVENT RIGHT MAIN GEAR FROM EXTENDING USING EMERGE NCY PROCEDURES. SUBMITTER STATED A THICKER CABLE OR A 360 DEGREE CABLE GUIDE MAY PREVENT RECURRENCE. FOUND DEFECT DURI NG A/B INSPECTION. IN THIS SHOP, HAVE FOUND AT LEAST 2 COMPLETE FAILURES (CABLE BROKEN) PREVIOUSLY. REF: 400A ILLUST PARTS CAT. 32-30-32, ITEM NR 95. 2 H 7 2 4F RT A16SW 1996101000870 19961010 00870 CE 1996 10 10 96ZZZX5150 1 19960920 G 2150 24540200 COUPLING HAMSTD CESSNA 500 550 2076604 CE ACM OVERTORQUE D P K NONE O OTHER IN INSP/MAINT 1 SW 03 5314J 2339 2339 5500663 WHILE PERFORMING MAINTENANCE TO ACM, COUPLING (V-BAND CLAMP) WAS FOUND SEVERELY OVERTORQUED ALMOST TO THE POINT OF FAILU RE. CLAMP WAS REPLACED USING CORRECT TORQUE, OPS CHECK GOOD. SUBMITTER RECOMMENDS MAINTENANCE PERSONNEL ADHERE TO PROP ER CLAMP TORQUE PROCEDURES ESPECIALLY CLAMPS USED ON EXHAUST SYSTEMS. THIS CLAMP WAS USED ON A PRESSURIZATION DUCT AND COULD HAVE CAUSED PRESSURE LOSS HAD IT FAILED. 1 L 7 2 4F A22CE 1996101000871 19961010 00871 EU 1996 10 10 96ZZZX5151 1 19960807 G 2720 ACTUATOR AIRBUS 300 A300B4622R EU RUDDER MALFUNCTIONED D K NONE J WARNING INDICATION NR NOT REPORTED 1 SW 99 88881 743 HKG/TPE - FLT CI-618 - AUGUST 7, 1996, RUDDER TRAVEL SYSTEMS 1 AND 2 FAULT. RUDDER TRAVEL ACTUATOR CHANGED. ARTF FEEL LIMITING COMPUTER CHANGE. 309CY1 AND 309CY2 RELAY CHANGE. FUNCTIONAL TEST OK PER A300-600R AMM 27-23-00. 2 L 7 2 4F RT A35EU 1996101000872 19961010 00872 EU 1996 10 10 96ZZZX5152 1 19960910 G 3244 181K632 TIRE GOODYEARAERO BRAERO DH125 BAE125800A 1500285 EU TIRE BALANCE PATCH LOOSE D K NONE O OTHER IN INSP/MAINT 1 CE 05 195KC 61020501 NA0455 BALANCE PATCH CAME OPFF AFTER 97 LANDINGS. THIS IS SECOND TIME HAVE HAD PROBLEMS WITH THIS PART NUMBERED TIRE IN 6 MON THS. LAST TIRE HAD EXCESSIVE SIDE WALL VENTING (ALSO AT 97 LANDINGS). 2 L 7 2 4F RT A3EU 1996101000873 19961010 00873 NM 1996 10 10 96ZZZX5153 1 19960905 G 2742 BEARING 12970008 BOEING 727 727 1384001 NM CLUTCH LEAKING GREASE D K NONE O OTHER IN INSP/MAINT 1 NM 01 STAB ACTUATOR CLUTCH BEARINGS MIGRATE SMALL AMOUNT OF GREASE THAT COATS THE SLIP RING AND BRUSHES REDUCING D.C. CURRENT TO THE CLUTCHES EFFECTING THE UNITS OUTPUT TORQUE. 2 L 7 3 4F A3WE 1996101000874 19961010 00874 WP 1996 10 10 96ZZZX5154 1 19960912 G 5320 6224415 BALLAST WEIGHT HILLER UH12 UH12E 4360122 WP TAIL BOOM DISLODGED B L A BHHR A UNSCHED LANDING O OTHER NR NOT REPORTED 1 EA 21 156HA 6068 6068 HA3056 ON SEPTEMBER 12, 1996, A HILLER MODEL UH-12 ET OPERATED BY SUMMIT HELICOPTERS CRASHED, COMPLETELY DESTROYING THE HELICOP TER AND SERIOUSLY INJURING THE PILOT. THE CAUSE OF THE CRASH WAS BALLAST WEIGHT P/N 62244-15 MADE CONTACT WITH TAIL ROT OR BLADES CAUSING LOSS OF TAIL ROTOR ASSEMBLY AND TAIL ROTOR GEARBOX. INVESTIGATION DETERMINED ONE OF THE QUICK RELEASE PINS PART NUMBER NAS 1334A2825 THAT HOLD THE BALLAST WEIGHT IN PLACE DISLODGED FROM BALLAST MOUNTING STUD CAUSING STUD TO TURN IN TAIL BOOM AND BALLAST WEIGHT TO CONTACT TAIL ROTOR SYSTEM CAUSING LOSS OF DIRECTIONAL CONTROL WHICH RESULTED IN THE HELICOPTER CRASHING INTO THE TREES. 1 G 7 1 3O 4H11 1996101000879 19961010 00879 WP 1996 10 10 96ZZZX5159 1 19960926 G 6320 369F5100503 TRANSMISSION HUGHES 369 369E 4470707 WP M/R NOISE/LEAK G K NONE K FLUID LOSS IN INSP/MAINT 1 WP 21 911RP 100 0055700001 526E DURING 3,000-HOUR OVERHAUL TIME, FOUND NOISE AND WHINE IN TRANSMISSION AND LEAK ING INPUT SEAL. COMPLETE REPLACEMENT OF TRANSMISSION. 1 G 7 1 3U H3WE 1996101000880 19961010 00880 WP 1996 10 10 96ZZZX5160 1 19960926 G 6310 369F54501 HOUSING HUGHES 369 369E 4470707 WP OVERRUN CLUTCH CRACKED G K NONE O OTHER IN INSP/MAINT 1 WP 21 911RP 93 0099990011 526E FACTORY RECALL OF OVERRUN CLUTCH, P/N 369F5453-1. SUSPECT CRACK IN P/N 369F5450-1. PART FOUND CRACKED. SUSPECT REASON OF FAILURE DUE TO IMPROPER HEAT TREATING. 1,800-HOUR OVERHAUL REQUIREMENTS, NEW CLUTCH MODEL 'F' TYPE. 1 G 7 1 3U H3WE 1996101000881 19961010 00881 NE 1996 10 10 96ZZZX5161 2 19960925 G 7320 CONTROL CABLE SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1B 6OO30 NE ANTICIPATOR BINDING D O OTHER O OTHER AP APPROACH 1 SO 17 54EW 1936 949 ON FINAL APPROACH, COLLECTIVE WAS LOWERED TO START A DESCENT, ROTOR RPM OBSERVED HIGHER THAN NORMAL. THE COLLECTIVE WAS RAISED TO RESTORE ROTOR RPM TO NORMAL, BUT NO CHANGE WAS OBSERVED. PER THE MANUFACTURER'S FLIGHT MANUAL, THE FUEL FLOW CONTROL LEVER WAS USED TO SLOW RPM. THIS RESULTED IN AN OPPOSITE PROBLEM IN SLOWING THE RPM TOO MUCH. UPON LANDING, A IRCRAFT WAS GROUNDED UNTIL MAINTENANCE COULD LOOK AT THE AIRCRAFT, THEY DISCOVERED THE CABLE THAT ATTACHES TO THE FFC WA S BINDING, AND REPLACED THE CABLE. 1 G 7 1 3U 3 U H9EU E19EU 1996101700246 19961017 00246 NE 1996 10 17 96ZZZX5162 1 19960913 G 6210 7615009100051A BLADE SKRSKY S76 S76B 8143007 NE M/R CRACKED B EGRR K NONE O OTHER IN INSP/MAINT 1 EA 17 5NJ 4289 A08601121 760346 BLADE WAS BEING INSPECTED AFTER BEING USED AS A RENTAL UNIT. WHILE INSPECTING M/R BLADE ROOT END IAW SIKORSKY COMPOSITE MANUAL, SA 4047-76-5, PARAGRAPHS 2-7, A CRACK WAS FOUND COMING OUT FROM UNDERNEATH THE PHOENLIC BLOCK. BLADE REMOVED FR OM SERVICE. 1 G 7 2 4U H1NE 1996101700247 19961017 00247 NE 1996 10 17 96ZZZX5163 1 19960913 G 6210 7615009100041A BLADE SKRSKY S76 S76B 8143007 NE MAIN ROTOR CRACKED B EGRR K NONE O OTHER IN INSP/MAINT 1 EA 17 5NJ 4802 A08600513 760346 BLADE BEING INSPECTED AFTER BEING USED AS RENTAL UNIT. WHILE INSPECTING M/R BLADE ROOT END IAW SIKORSKY COMPOSITE MANUA L, SA 4047-76-5, PARAGRAPHS 2-7, A CRACK WAS FOUND COMING OUT FROM UNDERNEATH THE PHOENLIC BLOCK. BLADE REMOVED FROM SE RVICE. 1 G 7 2 4U H1NE 1996101700248 19961017 00248 EU 1996 10 17 96ZZZX5164 1 19960901 G 5320 DECK AEROSP SA365 SA365N1 8680668 EU LT TRANSMISSION CRACKED D K NONE O OTHER IN INSP/MAINT 1 GL 03 365UC 1919 6329 250 MM CRACK FOUND LT SIDE TRANSMISSION DECK AT STA 3826.7. REPAIR MADE PER EUROCOPTER REPAIR DATA SHEET. MANUFACTURER ISSUED AIRFRAME SB 05.00.36. OPERATOR RECOMMENDS THAT SB 05.00.36 CHANGE FROM A RECOMMENDED TO A MANDATORY SB AND HOUR S BE DECREASED FROM 2,000 TO SOMETHING LESS. 1 G 7 2 3U H10EU 1996101700260 19961017 00260 SW 1996 10 17 96ZZZX5173 1 19960909 G 6730 206076062003 CYLINDER BELL 206 206L1 1182107 SW COLLECTIVE SERVO DEFECTIVE B GCHR O OTHER F FLT CONT AFFECTED NR NOT REPORTED 1 WP 19 2072M 3088 388 RH301 45720 PILOT REPORTED LOSS OF COLLECTIVE CONTROL ON AIRCRAFT. ARRIVED AT SCENE AND INSPECTED AND FOUND COLLECTIVE SERVO PISTON UNSCREWS FROM ROD END BEARING. CAUSE OF INCIDENT WAS NO SAFETY WAS FOUND ON FWD SERVO PISTON. INSPECTED COLLECTIVE SE RVO FOR DAMAGE AND PISTON FOR STRAIGHTNESS, AND DAMAGE. NO DEFECTS FOUND. INSPECTED CONTROL TUBES FOR CRACKS, NICKS, A ND STRAIGHTNESS, OPENED VERTICAL TUNNEL, INSPECTED CONTROL TUBES FOR CRACKS AND DAMAGE. NO DEFECT FOUND. 1 G 7 1 3U H2SW 1996101700262 19961017 00262 WP 1996 10 17 96ZZZX5174 1 19960823 G 6320 369D25143 BEARING 369D25100505 HUGHES 369 369D 4470706 WP M/R XMSN FAILED B EOOR K NONE J WARNING INDICATION IN INSP/MAINT 1 AL 03 5074R 82 1151D DURING INSPECTION OF M/R TRANSMISSION AFTER CHIP LIGHT, THE FORWARD INPUT PINION BEARING WAS FOUND CONTAMINATED WITH IMP REGNATED METAL. 1 G 7 1 3U H3WE 1996101700264 19961017 00264 GL 1996 10 17 96ZZZX5176 1 19960521 G 6710 KUP14D5524 RELAY ENSTRM F28 F28F 3300412 GL CYCLIC TRIM STUCK CONTACTS C PP0M O OTHER F FLT CONT AFFECTED NR NOT REPORTED 1 WP 01 8626S 1057 786 POINTS IN RELAY FUSE TOGETHER CAUSING RUNAWAY TRIM ACTION RESULTING IN UNCONTROLLED ATTITUDES OF AIRCRAFT. REQUIRES BOT H PILOTS ON CYCLIC TO OVERRIDE. RELAY MFG HAS INDICATED THIS IS NOT THE CORRECT RELAY FOR THIS APPLICATION. INSTALLED NEW RELAY PER MM. 1 G 7 1 3O H1CE 1996101700272 19961017 00272 SW 1996 10 17 96ZZZX5178 1 19960719 G 5311 212030367004S FRAME BELL 212 212 1181420 SW RT ROOF CRACKED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 68AL 15619 30934 MAJOR INSPECTION, FOUND FRAME WAS CRACKED ACROSS UPPER FLANGE AND 3.2 INCHES DOWN VERTICAL FLANGE R.H.F.S. 118. DURING REMOVAL OF DAMAGE, 6 MS20470ADS RIVETS WERE FOUND LOOSE whICH PERMITTED UPPER FLANGE TO CHAFE. CRACK DID NOT START OR C ROSS CHAFED AREA. CAUSE UNKNOWN. 1 G 7 1 4U H4SW 1996101700273 19961017 00273 SW 1996 10 17 96ZZZX5179 1 19960710 G 6230 206040032101 DUPLEX BEARING BELL 206 206B 1181511 SW SWASHPLATE FAILED B AC2R K NONE O OTHER IN INSP/MAINT 1 SW 03 3181B 466 MB742 3770 DUPLEX BEARING BREAKING DOWN WITH ONLY 465.9 HOURS. 1 G 7 1 3U H2SW 1996101700274 19961017 00274 SW 1996 10 17 96ZZZX5180 1 19960710 G 6320 206040002029 TRANSMISSION BELL 206 206B 1181511 SW M/R MAKING METAL B AC2R K NONE O OTHER IN INSP/MAINT 1 SW 03 3181B 13795 BKW11485 3770 INSTALLED DUPLEX BEARING 206-040-032-101, SN MB472, INTO ABOVE TRANSMISSION WHEN BEARING WAS NEW. AIRCRAFT FLEW 465.9 H OURS AND BEARING MAKING METAL. 1 G 7 1 3U H2SW 1996101700275 19961017 00275 NE 1996 10 17 96ZZZX5181 2 19960329 G 7230 536210 TABLOCK SKRSKY S64 S64E 8142604 NE PWA JFTD12 JFTD12A4A 52047 NE 3RD STAGE DISK MISSING B JYDR K NONE O OTHER IN INSP/MAINT 1 NM 09 154AC 575 64037 672566 TABLOCK MISSING AT POST-FLT INSP ON 3-29-96. LAST O/H PERFORMED BY EAC ON 3-23-95. WHEN INSP COMP THRU INLET, CONTACT OF 3RD STG BLD NOTED ON FACE OF 4TH STG STATOR NEAR CENTERLINE OF ENG (ROOT END OF BLD). BLD MOVED AFT CONTACTING FRONT OF STATOR DUE TO TABLOCK FAILURE. ERICKSON ALSO DOCUMENTED DIMENSIONAL VARIANCES FND ON TABLOCKS SUPPLIED BY TP&M, SE NT A PIECE OF FRACTURED TABLOCK TO P&W FOR LAB ANALYSIS. WHEN CORRECTIVE ACTION WAS NOT FORTHCOMING FROM P&W, REMAINING PIECE OF TABLOCK SENT TO OUTSIDE LAB FOR METALLURGICAL ANALYSIS. RESULTS SHOWED MICRO CRACKING ON EDGES OF TABLOCKS WH ICH ARE A MFG DEFECT. 2 G 7 2 4U 4 U H4EA E15EA 1996101700506 19961017 00506 NE 1996 10 17 96ZZZX5187 1 19960723 G 6410 73676HA78 BLADE BOLT SKRSKY S64 S64F NE RED T/R BLADE FRACTURED B JYDR K NONE O OTHER IN INSP/MAINT 1 NM 09 158AC 64081 DURING INSPECTION OF TAIL ROTOR ASSY DURING POST-FLIGHT INSPECTION, TWO BOLTS FOUND FRACTURED. THE RED T/R BLADE AND AL L EIGHT BOLTS WERE REPLACED. THERE WAS NO DAMAGE TO THE AIRCRAFT EXCEPT AS NOTED HEREIN. 2 G 7 2 4U H6EA 1996101700507 19961017 00507 NE 1996 10 17 96ZZZX5188 1 19960726 G 6410 73676HA78 BLADE BOLT SKRSKY S64 S64F NE RED T/R BLADE FRACTURED B L JYDR A UNSCHED LANDING E VIBRATION/BUFFET CL CLIMB 1 NM 09 178AC 76 64097 CLIMB, 50-60 KTS IAS ABOUT 1K FPM RATE , PILOT NOTED VIBRATION IN T/R. RETURNED ORIG TAKEOFF POINT, LANDED. VIBRATION BECAME STRONGER DURING DESCENT. FOUND 8 BOLTS RETAINING T/R BLADE, 1 EA BOLT HEAD MISSING AND NEVER FOUND. 3 EA BOLT HEADS BROKEN ABOUT 3RD THREAD OTBD FROM SHANK, AND 2 BOLTS HAD NO TORQUE REMAINING. RED T/R BLADE REPLACED AND ACFT INSPECTED FOR PROBLEMS, NONE FOUND. THIS IS UPDATED MDR. 2 G 7 2 4U H6EA 1996101700508 19961017 00508 NE 1996 10 17 96ZZZX5189 1 19960723 G 6410 7376HA78 BLADE BOLT SKRSKY S64 S64F NE YELLOW T/R BLADE FRACTURED B JYDR K NONE O OTHER IN INSP/MAINT 1 NM 09 178AC 64097 TWO BOLTS WERE FOUND FRACTURED ON THE YELLOW T/R BLADE AT THE PITCH CHANGE ATTACH LOCATION WHEN THE T/R WAS INSPECTED AT THE NOON SHUT-DOWN. THIS IS A GENERAL INSPECTION INTERVAL FOR THE T/R. THE BLADE WAS CHANGED OUT AND ALL 8 BOLTS REPL ACED ON THE YELLOW BLADE. ADDITIONALLY, ALL OTHER BOLTS ON THE OTHER 3 T/R BLADES WERE ALSO REPLACED. THERE WAS NO DAM AGE TO ANY OTHER PART OF THE A/C. 2 G 7 2 4U H6EA 1996101700509 19961017 00509 NE 1996 10 17 96ZZZX5190 2 19960625 G 7230 536210 TABLOCK SKRSKY S64 S64F NE PWA JFTD12 JFTD12A5A 52047 NE 3RD STAGE DISK MISSING B L JYDR K NONE O OTHER IN INSP/MAINT 1 NM 09 178AC 423 64097 677799 TABLOCK FOUND MISSING AT POST-FLIGHT INSPECTION ON 6-25-96. THE LAST OVERHAUL WAS PERFORMED BY SABRELINER. WHEN INSPEC TING THE COMPRESSOR THROUGH THE INLET, CONTACT OF 3RD STAGE BLADE NOTED ON FACE OF 4TH STAGE STATOR NEAR CENTERLINE OF E NGINE (ROOT END OF BLADE). THE BLADE MOVED AFT CONTACTING FRONT OF STATOR DUE TO TABLOCK FAILURE. THIS IS THE 7TH OCCU RRENCE OF TABLOCK FAILURE NOTED BY ERICKSON SINCE 1994. ALL PROBLEMS HAVE BEEN REPORTED TO THE MANUFACTURER. 2 G 7 2 4U 4 U H6EA E15EA 1996101700510 19961017 00510 NE 1996 10 17 96ZZZX5191 2 19960426 G 7230 536210 TABLOCK SKRSKY S64 S64F NE PWA JFTD12 JFTD12A5A 52047 NE 3RD STAGE DISK MISSING B L JYDR K NONE O OTHER IN INSP/MAINT 1 NM 09 178AC 581 64097 677770 TABLOCK FOUND MISSING AT PRE-FLIGHT INSPECTION CONDUCTED ON 4-26-96. THE LAST OVERHAUL PERFORMED BY EAC ON 8-4-94. WHE N INSPECTING THE COMPRESSOR THROUGH THE INLET, CONTACT OF 3RD STAGE BLADE WAS NOTED ON FACE OF 4TH STAGE STATOR NEAR CEN TERLINE OF ENGINE (ROOT END OF BLADE). THE BLADE MOVED AFT CONTACTING FRONT OF STATOR DUE TO TABLOCK FAILURE. THIS IS THE 6TH OCCURRENCE OF TABLOCK FAILURE NOTED BY ERICKSON SINCE 1994. ALL PROBLEMS HAVE BEEN REPORTED TO THE MANUFACTURER . 2 G 7 2 4U 4 U H6EA E15EA 1996101700513 19961017 00513 NE 1996 10 17 96ZZZX5194 2 19960704 G 7230 536210 TABLOCK SKRSKY S64 S64E 8142604 NE PWA JFTD12 JFTD12A4A 52047 NE 3RD STAGE DISK MISSING B L JYDR K NONE O OTHER IN INSP/MAINT 1 NM 09 194AC 2203 64017 676463 TABLOCK FOUND MISSING AT POST-FLIGHT INSPECTION ON 7-4-96 DUE TO NOISE FROM STATOR RUBBING. LAST OVERHAUL PERFORMED BY SABRELINER. WHEN INSPECTING COMPRESSOR THROUGH INLET, CONTACT OF 3RD STAGE BLADE NOTED ON FACE OF 4TH STAGE STATOR NEAR CENTERLINE OF ENGINE (ROOT END OF BLADE). THE BLADE MOVED AFT CONTACTING FRONT OF STATOR DUE TO TABLOCK FAILURE. THIS IS THE 8TH OCCURRENCE OF TABLOCK FAILURE NOTED BY ERICKSON SINCE 1994. ALL PROBLEMS HAVE BEEN REPORTED TO THE MANUFACT URER. 2 G 7 2 4U 4 U H4EA E15EA 1996101700858 19961017 00858 1996 10 17 96ZZZX5205 1 19960927 G 2822 2B729 PUMP AIRBORNE FUEL BOOST ARMATURE DAMAGE D K NONE O OTHER IN INSP/MAINT 1 GL 13 7H587 FOUND DAMAGE TO SHAFT. PUMP MAY HAVE BEEN DRY. 1996101700859 19961017 00859 1996 10 17 96ZZZX5206 1 19960930 G 2822 2B616 PUMP AIRBORNE ARMATUARE SHAFT BENT D K NONE O OTHER IN INSP/MAINT 1 GL 13 10AG3 FOUND PUMP KEYED END OF SHAFT IS BENT. 1996101700860 19961017 00860 CE 1996 10 17 96ZZZX5207 1 19960918 G 7120 26510264 MOUNT BOLT LEAR 35 35LEAR 5170600 CE ENGINE HEAD CRACKED H GQFG K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 09 FOUND CRACKED HEAD ON NEW ENGINE MOUNT BOLT PURCHASED FROM LEAR IN KIT NR 2695006-1 FOR SB 35/36-71-5, REV 2, 6-18-93. B ATCH NR SPS18. 2 L 7 2 4F A10CE 1996101700861 19961017 00861 EA 1996 10 17 96ZZZX5208 2 19960903 G 7322 MA45 CARBURETOR PRECISION LYC O360 O360A4A 41514 EA BOWL DRAIN LEAK D K NONE K FLUID LOSS IN INSP/MAINT 1 NM 11 100 K33508 FOUND LEAK IN BOWL DRAIN WHEN REBUILT CARBURETOR INSTALLED. REMOVED DRAIN, RESEAL. 3 O E286 1996101700862 19961017 00862 SO 1996 10 17 96ZZZX5209 2 19960906 G 7322 MA45 CARBURETOR CONT O470 O470U 17026 SO BOWL DRAIN LEAK D K NONE K FLUID LOSS IN INSP/MAINT 1 NM 11 C00308 FOUND LEAK IN BOWL DRAIN. REMOVED PLUG, SEAL, AND REINSTALLED. 3 O E273 1996101700864 19961017 00864 CE 1996 10 17 96ZZZX5211 1 19960808 G 7120 075100331 MOUNT CESSNA 185 A185E 2072818 CE ENGINE BROKE B V2AR K NONE O OTHER IN INSP/MAINT 1 AL 03 1950U 18501659 IO550 INSTALLED IAW STC SA2933S0. INSTALLATION INSTRUCTIONS UTILIZE MCAULEY D3A34C401 THREE-BLADE PROPELLER WITH EXISIT NG ENGINE MOUNT. AIRCRAFT WITH TWO-BLADE ENGINE MOUNTS ARE APPLICABLE. CESSNA SL SE79-62 REQUIRES ENGINE MOUNT BE CHAN GED TO A 0751007-16 MOUNT. N1950U WAS EQUIPPED WITH 0751003-31 MOUNT. MOUNT WAS CRACKED. FUEL HEADER TANK WAS CRACKED , EXHAUST WAS CRACKED. IO550 AND THREE-BLADE PROP WERE INSTALLED 205 HOURS PREVIOUSLY. ACFT TT WAS 2,701.9 HRS. 1 H 7 1 3O 3A24 1996101700865 19961017 00865 CE 1996 10 17 96ZZZX5212 1 19960901 G 8120 4066109025 TURBOCHARGER CESSNA 402 402CESSNA 207590K CE CONT O520 TSIO520E 17040 SO NR 1 ENGINE FAILED D A UNSCHED LANDING D R INFLIGHT SEPARATION PARTIAL RPM/PWR LOSS CR CRUISE 1 WP 19 82TA 454 SHR1829 4020156 22356872E WHILE IN-FLIGHT, NR 1 TURBOCHARGER FAILED. THE AIRCRAFT LANDED WITHOUT DAMAGE. UPON INSPECTION BY MAINTENANCE, DISCOVE RED TURBO MAIN SHAFT HAD BROKEN AND WHEEL ON THE EXHAUST SIDE WAS MISSING. IT APPEARS TO HAVE GONE OUT THE OVERBOARD ST ACK. THE OTHER WHEEL WAS STILL IN THE TURBO. CAUSE: UNKNOWN. 1 L 7 2 3O 3 O A7CE E8CE 1996101700866 19961017 00866 SO 1996 10 17 96ZZZX5213 2 19960808 G 8530 CYLINDER CESSNA 185 A185E 2072818 CE CONT O520 IO520D 17032 SO 1 THRU 6 SCORED B V2AR K NONE O OTHER IN INSP/MAINT 1 AL 03 1950U 203 18501659 284035R AT ANNUAL INSPECTION ENGINE COMPRESSION READINGS SHOWED THE FOLLOWING: NR 1, 70/80, NR 2, 58/80, NR 3, 72/80, NR 4, 56/ 80, NR 5, 64/80, AND NR 6, 70/80. ALL LEAKAGE WAS PAST PISTON RINGS. BORESCOPE INSPECTION REVEALED SCORING ON ALL CYLI NDERS. AN INSPECTION ON 7-21-95 AT 159 TSOH REVEALED THE FOLLOWING NR 1, 70/80, NR 2, 72/80, NR 3, 76/80, NR 4, 72/80, NR 5, 72/80, AND NR 6, 72/80. 1 H 7 1 3O 3 O 3A24 E5CE 1996101700867 19961017 00867 CE 1996 10 17 96ZZZX5214 1 19960906 G 2810 3540002 BLADDER BEECH 35 S35 1151532 CE RT TANK BAFFFLE CRUMBLE D K NONE O OTHER IN INSP/MAINT 1 NM 09 3MG 383 07856 FUEL BLADDER INNER BAFFLING DISENTEGRATING INTO SAND-SIZE PARTICLES. PARTICLES FOUND AT SUMP AND STRAINER. COULD CAUSE FUEL STARVATION. DETERMINED TO BE INNER BAFFLE FOAM. 1 L 7 1 3O 3A15 1996101700868 19961017 00868 NM 1996 10 17 96ZZZX5215 1 19960910 G 5102 C16151J TANK RAVEN S50 S50A 05604XW NM GONDOLA CHAFE DOOR D P A K NONE O OTHER IN INSP/MAINT 1 GL 19 1235R 166 S50A275 UPON INSPECTION OF FLOOR ASSY, VISUAL CHAFING OF STRUCTURAL ALUMINUM U-TUBING WAS OCCURRING DUE TO ABRASION BY PROPANE F UEL TANK. WICKER WAS ALREADY BROKEN. SUGGEST THOROUGH INSPECTION AT ANNUALS AND APPLICATION OF ANTI-CHAFE MATERIAL (SP LIT HOSE) TO TANK BASE. 1 B 0 0 A15CE 1996101700869 19961017 00869 CE 1996 10 17 96ZZZX5216 1 19960805 G 2810 S14958 HOSE CESSNA 182 182J 2072722 CE LT TANK VENT SPLIT D K NONE K FLUID LOSS IN INSP/MAINT 1 NM 11 3119F 2509 18257219 AFTER EACH FLIGHT, PILOT REPORTED HAD TO WIPE FUEL STAIN FROM TRAILING EDGE OF LT WING. INSPECTION OF LT FUEL BLADDER M ADE AND FOUND HOSE CONNECTING TANK VENT LINE TO THE LT FUEL TANK WAS SPLIT AND ALLOWING FUEL TO VENT INTO THE WING BAY O UTBOARD OF LT TANK. THE AGE OF THE RUBBER HOSE WAS DETERMINED TO BE THE CAUSE OF FAILURE. 1 H 7 1 3O NT 3A13 1996101700870 19961017 00870 CE 1996 10 17 96ZZZX5217 1 19960723 G 3230 1315531F66M ROD END BEECH 33 F33A 1151425 CE RT MLG ACTUATOR FAILED D O OTHER J WARNING INDICATION AP APPROACH 1 WP 09 3133W CE465 WHILE MAKING NORMAL LANDING, PILOT LOWERED GEAR AND HEARD A LOUD 'POP' FROM RT MAIN GEAR. WHEN GEAR WAS RETRACTED, GEAR INTRANSIT LIGHT WOULD NOT GO OFF. GEAR SELECTOR PLACED BACK IN DOWN POSITION AND AIRCRAFT WAS FLOWN TO HOME AIRFIELD W ITH GEAR DOWN. AFTER LANDING, INSPECTION FOUND RT MAIN OUTBOARD ACTUATOR ROD END BROKEN. THE ROD END WAS DRY AND LACKE D LUBE (WAS RUSTED IN BEARING SURFACE). SUBMITTER SUGGESTS LUBE AT 100-HOUR INTERVALS. NEW PART HAS GREASE FITTING INS TALLED. 1 L 7 1 3O 3A15 1996101700871 19961017 00871 SO 1996 10 17 96ZZZX5218 1 19960925 G 2140 A23D0475 REGULATOR JANITROL PIPER PA31 PA31350 7103110 SO HEATER PRESSURE GASKET LEAK B APCR K NONE K FLUID LOSS IN INSP/MAINT 1 NM 01 36PB 20 317405128 JANITROL HEATER FUEL PRESSURE REGULATOR WAS INSTALLED NEW 8-22-96. ON 9-19-96 WITH 20.1 HRS TIME IN SERVICE, UNIT FAILE D CAUSING FLUCTUATION OF RT FUEL SYSTEM PRESSURE. WHEN REMOVED, FOUND FUEL LEAKING AROUND GASKET. 1 L 7 2 3O A20SO 1996101700872 19961017 00872 SO 1996 10 17 96ZZZX5219 1 19960924 G 2140 A23D0475 REGULATOR PIPER PA31 PA31350 7103110 SO HEATER PRESSURE LEAKING B APCR K NONE K FLUID LOSS IN INSP/MAINT 1 NM 01 36PB 317405128 FUEL PRESSURE REGULATOR FOR COMBUSTION HEATER CAUSED FUEL PRESSURE GAUGE FLUCTUATIONS. EXAMINATION FOUND REGULATOR LEAK ING EXTERNALLY. OPERATOR HAS RECORDS OF MULTIPLE FAILURES OF THESE UNITS. 1 L 7 2 3O A20SO 1996101700873 19961017 00873 SO 1996 10 17 96ZZZX5220 1 19960926 G 3260 67411008 SWITCH PIPER PA34 PA34200T 7103406 SO LT MLG OUT OF ADJUST B APCR A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 NM 01 36319 347870318 AIRCRAFT TOOK OFF, PILOT SELECTED 'GEAR UP', GEAR DID NOT MOVE. WARNING HORN AND LIGHT CAME ON. AIRCRAFT LANDED WITHOU T INCIDENT. MAINTENANCE FOUND GEAR SAFETY 'SQUAT' SWITCH OUT OF ADJUSTMENT. RE-ADJUSTMENT CURED PROBLEM. 1 L 7 2 3O A7SO 1996101700875 19961017 00875 CE 1996 10 17 96ZZZX5222 1 19960901 G 5510 STABILIZER CESSNA 210 P210N 2073454 CE HORZ STAB LE LOOSE RIVETS H K NONE O OTHER IN INSP/MAINT 1 SW 99 4752K 1850 P21000283 FOUND LOOSE RIVETS ON LEADING EDGE OF HORIZONTAL STABILIZER ON THE FIRST TWO RIBS OUT FORM THE FUSELAGE. REMOVED AND RE PLACED RIVETS WITH NEW. AIRCRAFT EQUIPPPED WITH DE-ICE BOOTS. 1 H 7 1 3O 3A21 1996101700876 19961017 00876 CE 1996 10 17 96ZZZX5223 1 19960924 G 2571 07120591 SUPPORT 07120741 CESSNA 182 182Q 2072732 CE BATTERY BOX CRACKED D S K NONE O OTHER IN INSP/MAINT 1 EA 25 501AC 1208 18266922 INSPECTION FOUND BATTERY SUPPORT CRACKED. SUSPECT CAUSE IS TIME IN SERVICE. SHOULD BE THICKER MATERIAL. 1 H 7 1 3O NT 3A13 1996101700877 19961017 00877 CE 1996 10 17 96ZZZX5224 1 19960930 G 2820 040034321 PRIMER ASSY CESSNA 150 152 2071835 CE CYLINDER NR 2 SEPARATED G A UNSCHED LANDING E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CR CRUISE 1 EA 09 5297M 5554 15284518 STUDENT PILOT ON SOLO CROSS-COUNTRY EXPERIENCED ROUGH ENGINE OPERATION. AIRCRAFT RETURNED TO AIRPORT. INSPECTION REVEA LED PRIMER LINE ASSY AT NR 2 AND NR 4 CYLINDERS SEPARATED AT SOLDER JOINT OF THREADED CONNECTOR OF CYLINDER. FRACTURES ARE CONSISTENT WITH CYCLIC FATIGUE. SUBMITTER RECOMMENDS SECURITY INSPECTION ANY TIME COWLING REMOVED. TOTAL ACFT TIS: 5,554.0 HOURS ESTIMATED. 1 H 7 1 3O NT 3A19 1996101700878 19961017 00878 CE 1996 10 17 96ZZZX5225 1 19960930 G 2820 040034322 PRIMER ASSY CESSNA 150 152 2071835 CE CYLINDER NR 4 SEPARATED G A UNSCHED LANDING E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CR CRUISE 1 EA 09 5297M 5554 15284518 STUDENT PILOT ON SOLO CROSS-COUNTRY EXPERIENCED ROUGH ENGINE OPERATION. AIRCRAFT RETURNED TO AIRPORT. INSPECTION REVEA LED PRIMER LINE ASSY AT NR 2 AND NR 4 CYLINDERS SEPARATED AT SOLDER JOINT OF THREADED CONNECTOR OF CYLINDER. FRACTURES ARE CONSISTENT WITH CYCLIC FATIGUE. SUBMITTER RECOMMENDS SECURITY INSPECTION ANY TIME COWLING REMOVED. TOTAL ACFT TIS: 5,554.0 HOURS ESTIMATED. 1 H 7 1 3O NT 3A19 1996101700879 19961017 00879 EA 1996 10 17 96ZZZX5226 2 19960926 G 8530 74541 VALVE CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA NR 3 CYL EXH STEM FAILED G A UNSCHED LANDING E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 EA 09 737FP 1855 17269385 L220576 PRECAUTIONARY LANDING MADE DUE TO POWER LOSS AND FLUCTUATING OIL PRESSURE. ENGINE WOULD MAINTAIN 1,800 RPM, AT FULL THR OTTLE. NR 3 CYLINDER EXHAUST VALVE FAILED JUST ABOVE HEAD/STEM RADIUS. SECONDARY CYLINDER AND PISTON DAMAGE REMNENTS O F VALVE FOUND IN MUFFLER. STEM REMAINED FROZEN IN VALVE GUIDE. RECOMMENDATIONS: LYC SI 1425. SL L197. 1 H 7 1 3O 3 O NT 3A12 E274 1996101700880 19961017 00880 EA 1996 10 17 96ZZZX5227 2 19960802 G 7310 HOSE CESSNA 182 TR182 2072735 CE LYC O540 O540L3C5 41532 EA FIREWALL DETERIORATED D K NONE O OTHER IN INSP/MAINT 1 WP 25 738FH 3025 4Q78 R18200920 L2106640A AIRCRAFT IS 1979 MODEL. ALL HOSES FORWARD OF FIREWALL, DATED 4Q78. REPLACED HOSES. SUBMITTER STATED MECHANICS MUST CH ECK HOSE CONDITION AND DATES ON A REGULAR BASIS TO AVOID BURST HOSES. 1 H 7 1 3O 3 O 3A13 E295 1996101700881 19961017 00881 EA 1996 10 17 96ZZZX5228 2 19960802 G 8530 LW15605 VALVE CESSNA 182 TR182 2072735 CE LYC O540 O540L3C5 41532 EA ENG EXHAUST WORN D K NONE O OTHER IN INSP/MAINT 1 WP 25 738FH 3025 1082 R18200920 L2106640A PEFORMED SB 388B ON ALL 6 CYLINDERS AT ANNUAL INSPECTION, 4 OF 6 CYLINDER EXHAUST VALVE AND GUIDES WORN BEYOND SPECS. R EMOVED CYLINDERS, FOUND 2 CYLINDERS WITH BROKEN RINGS, AND 6 CYLINDERS WERE CRACKED. REPLACED CYLINDER ASSY. SUBMITTER STATED SB 88B IS A GOOD TOOL TO PREVENT ENGINE FAILURE. 1 H 7 1 3O 3 O 3A13 E295 1996101700882 19961017 00882 CE 1996 10 17 96ZZZX5229 1 19960802 G 5330 SKIN CESSNA 182 TR182 2072735 CE FWD FUSELAGE CORRODED D K NONE O OTHER IN INSP/MAINT 1 WP 25 738FH 3025 R18200920 AT ANNUAL INSPECTION, FOUND SEVERE CORROSION UNDER SOUND DEADENER SHEETS IN FORWARD FUSELAGE SIDE PANELS. REMOVED DEADE NER SHEETS, TREATED AND PAINTED WITH CHROMATE PAINT. CESSNA ADDRESSES THIS PROBLEM IN SERVICE NEWS LETTER SNL 93-3, DAT ED JUNE, 1993. IF NOT CAUGHT, THIS CORROSION WOULD HAVE REQUIRED REPLACEMENT OF FORWARD FUSELAGE SKINS. 1 H 7 1 3O 3A13 1996101700883 19961017 00883 CE 1996 10 17 96ZZZX5230 1 19960802 G 5511 0700099101 RIB CESSNA 182 TR182 2072735 CE RT H STAB NR 2 CRUSHED D K NONE O OTHER IN INSP/MAINT 1 WP 25 738FH 3025 R18200920 RIGHT STABILIZER'S 2ND NOSE RIB CRUSHED BY USING TAIL TO GROUND HANDLE AIRCRAFT. SUBMITTER STATED THIS IS RECURRING PRO BLEM. HERE IS ANOTHER REMINDER. 1 H 7 1 3O 3A13 1996101700885 19961017 00885 EA 1996 10 17 96ZZZX5232 3 19960920 G 6111 BLADE BEECH 23 A23 1151204 CE SNSNCH 74DC M74DC EA PROPELLER FAILED G A A UNSCHED LANDING E Y VIBRATION/BUFFET ENGINE STOPPAGE CR CRUISE 1 SO 05 8879M 1851 M626 B920 WITH AIRCRAFT AT CRUISE, 2,500 RPM., ONE BLADE FAILED AT 14.6250 INCHES FORM CENTER OF HUB. IT WAS A CLEAN BREAK WITH N O SIGN OF NICK OR SCRATCH ANYWHERE ON THE BLADE. ENGINE VIBRATION BROKE ALL 4 ENGINE MOUNTS. ENGINE DROPPED INTO BOTTO M OF COWLING AND SHUT-DOWN. PILOT DEAD STICKED AIRCRAFT TO AIRPORT AND MADE AN UNEVENTFUL LANDING. NO INJURIES. NTSB IS INVESTIGATING BLADE FAILURE. 1 L 7 1 3O A1CE 5 N P88614 1996101700887 19961017 00887 SW 1996 10 17 96ZZZX5233 1 19960118 G 7160 600355507 PLATE ASSY MOONEY M20 M20J 5870219 SW ALT AIR DOOR RIVETS FAULTY D K NONE O OTHER IN INSP/MAINT 1 NE 05 9138Z 243219 WHILE C/W AD 95-26-16R1, FOUND 2 OF THE 4 RIVETS SECURING PLATE ASSY 600355-507 MISSING HEAD. APPARENTLY WORN AWAY BY C HAFING AGAINST RIVETS THAT SECURE DOUBLER TO AIR BOX. RECOMMEND ANTI-CHAFE MATERIAL OR REPLACING RIVETS WITH FLUSH HEAD S. 1 L 7 1 3O 2A3 1996101700888 19961017 00888 SO 1996 10 17 96ZZZX5234 1 19961001 G 2720 9621200 TUBE ASSY PIPER PA34 PA34220T 7103420 SO RUDDER ELONGATED HOLES D K NONE O OTHER IN INSP/MAINT 1 EA 07 9249N 3448048 AIRCRAFT TOTAL TIME: 470.2 HOURS, 1995 SENECA IV. FOUND DURING ANNUAL INSPECTION, RUDDER HAD 3 TO 4 DEGREE MOVEMENT WI THIN THE MOUNT FITTING, PN 96319-802. FURTHER INSPECTION (RUDDER REMOVED) TORQUE TUBE ASSY HAD WORN, ELONGATED BOLT HOL ES (4). CAUSE - VIBRATION, WINDLOAD, WEAK TUBE CONSTRUCTION. SUBMITTER RECOMMENDS RE-ISSUE PIPER SB 899, DATED 2-10-89 , TO COVER SENECA IV MAKING THIS AREA A 50-HOUR INSPECTION ITEM. 1 L 7 2 3O A7SO 1996101700889 19961017 00889 CE 1996 10 17 96ZZZX5235 1 19960731 G 2842 C6680020301 TRANSMITTER STWARNER CESSNA 150 152 2071835 CE FUEL QUANTITY FLOAT DETACHED D A K NONE O OTHER IN INSP/MAINT 1 SO 05 93114 5700 15285404 DISCREPANCY WAS FOUND ON PRE-FLIGHT THAT LEFT HAND FUEL GAUGE READING WAS ZERO WHEN TANK WAS FULL OF FUEL. REMOVED TANK TRANSMITTER AND FOUND FLOAT MISSING FROM ARM OF TRANSMITTER. RETRIEVED FLOAT FROM TANK, FOUND CONDITION OF FLOAT OK. R E-ATTACHED WITH EXISTING WASHERS, INSTALLED, AND SYSTEM CHECKED OK. 1 H 7 1 3O NT 3A19 1996101700890 19961017 00890 SO 1996 10 17 96ZZZX5236 1 19961004 G 5311 226667 TUBULAR FRAME PIPER PA22 PA22160 7102214 SO DOOR POST FATIGUE HOLE D K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 05 9753D 3438 226667 MANUFACTURER USED A SMALL WELD DOT TO SNUB VIBRATION IN THE TOP OF THE LOWER FRONT DOOR CHANNEL. VIBRATION IN THE COWL WRAPPER/DOOR CHANNEL FATIGUED A .1250 INCH BY .25 INCH HOLE IN THE DOOR TUBE. THIS TUBE CONNECTS THE FRONT WING FITTING TO THE LOWER LONGERON. FOUND ON TEAR DOWN FOR REBUILD. WOULD NOT NORMALLY BE INSPECTED. 1 H 7 1 3O 1A6 1996101700891 19961017 00891 SO 1996 10 17 96ZZZX5237 1 19961004 G 5311 226667 FRAME PIPER PA22 PA22160 7102214 SO LOWER RT LONG PITTED D S K NONE O OTHER IN INSP/MAINT 1 SW 05 9753D 3438 226667 A COMBINATION OF AN UNCORRECTED WATER LEAK AT A WINDOW AND DIRT HELD BETWEEN THE LONGERON/INTERIOR FABRIC RESULTED IN A BADLY PITTED LONGERON. SUBMITTER STATED SHOULD FIX LEAKS AND CLEAN. 1 H 7 1 3O 1A6 1996101700892 19961017 00892 SO 1996 10 17 96ZZZX5238 1 19961004 G 5311 226667 TUBE FRAME PIPER PA22 PA22160 7102214 SO INST PANEL CRACKED D S K NONE O OTHER IN INSP/MAINT 1 SW 05 9753D 3438 226667 INSTRUMENT PANEL CROSS-TUBE CRACKED AT BRAKE LEVER MOUNTING BRACKET WELD (MORE THAN ONE-FOURTH OF CIRCUMFERENCE). THE B RAKE LEVER PUTS A HIGH STRESS ON THE MOUNTING BRACKET WHEN THE BRAKES ARE APPLIED. THE CRACK IS LOCATED UNDER THE INSTR UMENT PANEL AND VERY DIFFICULT TO SEE. 1 H 7 1 3O 1A6 1996101700894 19961017 00894 SO 1996 10 17 96ZZZX5240 1 19960225 G 2437 3733700 AMMETER PIPER PA34 PA34200T 7103406 SO DC SYSTEM WRONG PART B A LC1R K NONE W INADEQUATE Q C IN INSP/MAINT 1 EA 07 33156 347570096 PIPER PARTS CATALOG HAS NOT YET BEEN UPDATED TO REFLECT AMMETER REPLACEMENT IAW AD 86-17-01. PARTS SUPPLIERS ARE USING OLD FICHE TO SEND OUT OLD STYLE AMMETERS WHICH DO NOT COMPLY WITH PREVIOUSLY STATED AD. IN THE EVENT ONE OF THESE OLD S TYLE AMMETERS IS INSTALLED, IT COULD CAUSE A POSSIBLE SHORT CIRCUIT AND/OR SMOKE AND FIRE IN THE COCKPIT. OLD STYLE PAR T NR 37337-00. 1 L 7 2 3O A7SO 1996101700895 19961017 00895 EA 1996 10 17 96ZZZX5241 1 19960921 G 5700 AN677AC16300 FLYING WIRE SCWZER G164 G164B 3952802 EA WING LT AFT BROKE D K NONE O OTHER NR NOT REPORTED 1 SW 11 3629K 748B WIRE BROKE 10 INCHES FROM WING ATTACH (BROKE FROM TOP TO BOTTOM). PART APPEARS TO HAVE BEEN CRACKED ONE-HALF THROUGH FO R SOME TIME PRIOR TO FAILURE. 1 Q 7 1 3R 1A16 1996101700896 19961017 00896 CE 1996 10 17 96ZZZX5242 1 19960909 G 3234 A4503M95 GEAR CONTROL BEECH 200 A200 1152921 CE MLG MISWIRED D A K NONE W INADEQUATE Q C IN INSP/MAINT 1 NE 05 2MIL 660 BJ24 UPON INSPECTION OF REPAIRED PART PRIOR TO INSTALLATION, DISCOVERED THE LANDING GEAR CONTROL WAS WIRED INCORRECTLY. PART HAD BEEN REPAIRED BY REPAIR STATION PRZR073K. ANOTHER CONTROL REMOVED FROM SUPPLY WAS ALSO WIRED INCORRECTLY. 1 L 7 2 4T A24CE 1996101700897 19961017 00897 EA 1996 10 17 96ZZZX5243 2 19960629 G 8520 LW13809 CRANKCASE AMTR ACROSP ACROSPORT GL LYC O360 IO360B1F 41514 EA OIL SUMP BROKEN D K NONE K FLUID LOSS IN INSP/MAINT 1 GL 09 4362D 1346 780 L619836C NOTED OIL LEAK ON LT SIDE OF OIL SUMP. FOUND THE CRANKCASE HAD MISSING PIECES AT LT REAR OIL SUMP MOUNTING STUD. ENGI NE WAS CONVERTED TO IO-360 APPROXIMATELY 100 HOURS PREVIOUSLY. A NEW OIL SUMP WAS INSTALLED AT THAT TIME. SUSPECT OIL SUMP TO CASE BOLTS WERE OVERTORQUED CAUSING A CRACK AND EVENTAULLY VIBRATION CAUSED PIECE TO DEPART CASE. 1 Q 7 1 3O 3 O NC EXPA1Q71 1E10 1996102400011 19961024 00011 CE 1996 10 24 96ZZZX5254 1 19960821 G 2130 26195009 VALVE LEAR 35 35A 5170602 CE LT PRESS SYS MALFUNCTIONED E A UNSCHED LANDING B J SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CL CLIMB 1 SW 99 21NG 4251 343 DUDRING TAKEOFF FROM BINGHAMTON REGIONAL AIRPORT, LEFT EMERGENCY PRESSURIZATION 3-WAY VALVE WENT TO EMERGENCY POSITION. PROBLEM INTRODUCED HOT AIR AND SMOKE INTO CABIN. VALVE WOULD NOT SHUT OFF. EMERGENCY DECLARED AND ACFT RETURNED AND A N UNEVENTFUL LANDING MADE. AIRCRAFT TURNED OVER TO MAINTENANCE. THE LT EMERGENCY PRESSURIZATION 3-WAY VALVE WAS REPLA CED. 2 L 7 2 4F A10CE 1996102400012 19961024 00012 NE 1996 10 24 96ZZZX5255 2 19960830 G 7412 3033378 EXCITER LUCAS CESSNA 500 S550 2076607 CE PWA JT15 JT15D4 52112 NE ENGINE INOPERATIVE B CWQR K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 05 111QS 9769 K7837 S5500111 DURING OPERATIONAL CHECK OF NEW ENGINE IGNITER, IGNITION EXCITER FAILED TO FIRE IGNITER. PROPER VOLTAGE OBSERVED AT CAN NON PLUG. INTERNAL PROBLEM WITH EXCITER BOX. 1 L 7 2 4F 4 F RT A22CE E1NE 1996102400013 19961024 00013 CE 1996 10 24 96ZZZX5256 1 19960823 G 3010 P067L015 SWITCH CESSNA 500 S550 2076607 CE TKS DEICE CORRODED B CWQR K NONE O OTHER IN INSP/MAINT 1 GL 05 112QS 9613 B16286 S5500112 DURING PHASE 5 INSPECTION, FOUND LT WING CUFF TKS PANEL PRESSURES SWITCH BADLY CORRODED AND METAL EXFOLIATED ON THE SURF ACE OF THE SWITCH. SUBMITTER STATED POOR QUALITY OF METAL USED IN MAKING SWITCH BODY WITH POSSIBLE TKS FLUID LEAKAGE LI KELY CAUSE. 1 L 7 2 4F RT A22CE 1996102400014 19961024 00014 NM 1996 10 24 96ZZZX5257 1 19960830 G 3397 WIRE ISRAEL 1125 1125 NM CABIN LIGHTS WRONG PART H K NONE W INADEQUATE Q C IN INSP/MAINT 1 CE 09 121GV 32 082 PER AD 95-22-01, HI-VOLTAGE WIRE MUST MEET A CERTAIN SPEC. THIS AIRCRAFT APPEARS TO HAVE STANDARD 20-GAUGE TEFLON WIRE INSTALLED WHICH DOES NOT MEET THAT STANDARD. 2 L 7 2 4F RT A16NM 1996102400015 19961024 00015 CE 1996 10 24 96ZZZX5258 1 19960807 G 2910 LINE CESSNA 650 650 2076802 CE AFT BAG COMP CRACKED D O OTHER K J FLUID LOSS WARNING INDICATION NR NOT REPORTED 1 NM 05 17TE 6500011 RIGHT STAINLESS STEEL HYDRAULIC LINE COMPRESSED FITTING CRACKED, SOME HYDRAULIC FLUID WAS LOST AND SYSTEM PRESSURE DROPP ED. REASON FITTING CRACKED IS UNKNOWN. LINE WAS REPAIRED BY CESSNA AIRCRAFT PERSONNEL AND DISPATCHED BY THEM. 2 L 7 2 4F A9NM 1996102400016 19961024 00016 SW 1996 10 24 96ZZZX5259 1 19960828 G 3245 600X6 TUBE MCCREARY 7500681 GULSTM 690TP 690B 7630516 SW NLG FAILED G C ABORTED TAKEOFF E VIBRATION/BUFFET TO TAKEOFF 1 GL 05 177EM 270 772015 11471 AIRCRAFT ABORTED TAKEOFF DUE TO NOSE WHEEL SHIMMY. FULL REVERSE AND BRAKES APPLIED. NOSE GEAR COLLAPSED. MCCREARY 6.0 0 X 6 TUBE APPEARS TO HAVE FAILED ALONG A MOLD LINE. TUBE IS MARKED 77-2-015 AND 120 113 09E. THE OPERATOR WILL SEND T HE TUBE OUT FOR EVALUATION. 1 H 7 2 3T 2A4 1996102400017 19961024 00017 CE 1996 10 24 96ZZZX5260 1 19960917 G 2720 BOLT CESSNA 500 550 2076604 CE RUD TORQUE TUBE WRONG PART B CWQR K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 05 6862Q 5500265 DURING PHASE 5 INSPECTION, FOUND INCORRECT BOLT AND NUTS INSTALLED IN RUDDER TORQUE TUBE WHERE IT ATTACHED TO BELLCRANK. THREE DIFFERENT TYPES OF LOCKING NUTS USED IN PLACE OF CASTLE NUTS THAT ARE REQUIRED. MOST LIKELY INSTALLED BY PAINT SHOP WHEN AIRCRAFT WAS REPAINTED. 1 L 7 2 4F A22CE 1996102400019 19961024 00019 SO 1996 10 24 96ZZZX5262 1 19960901 G 3244 706C861 TIRE GOODYEARAERO PIPER PA23 PA23250 7102308 SO MLG CHAFE GROOVE H K NONE O OTHER IN INSP/MAINT 1 SW 99 888RJ 277305139 THE MAIN LANDING GEAR TIRE HAS 2 EACH GROOVES WORN IN SIDEWALLS, 1.3750 INCH AND 7.8750 INCH FROM INNER EDGE OF BEAD OUT WARD ON SIDEWALL APPROXIMATELY .1250 INCH DEEP IN AREAS. THE TIRES HAVE TOO MUCH ROUNDNESS AT SIDEWALLS. NOTE: CONDOR TIRES INSTALLED AND CLEARANCE BETWEEN BRAKE PAD ABOUT .50 INCH. TIRE WOULD RUB ON SIDEWALL, COULD NOT TURN WHEEL BY HA ND. APPROXIMATELY 10 LANDINGS. 1 L 7 2 3O 1A10 1996102400020 19961024 00020 SO 1996 10 24 96ZZZX5263 2 19960927 G 7414 10357426 DISTRIBUTOR BLOC S6RN25 PIPER PA34 PA34200T 7103406 SO CONT O360 LTSIO360EB 17025 SO MAG OVERHEAT B SMTR K NONE M OVER TEMP IN INSP/MAINT 1 EA 17 91284 1 A233618 347970111 306764 DISTRIBUTOR BLOCK AND DISTRIBUTOR GEAR HAD EXCESSIVE HEAT BUILD-UP AND MELTING OF GEAR POSSIBLY DUE TO LACK OF SUFFICIEN T CLEARANCE DURING MANUFACTURE OR IMPROPER OIL IMPREGNATION DURING MANUFACTURE. 1 L 7 2 3O 3 O A7SO E9CE 1996102400025 19961024 00025 CE 1996 10 24 96ZZZX5268 1 19960910 G 2770 65652752 SLIDE ASSY CESSNA 500 550 2076604 CE GUST LOCK SPLIT B EBVR K NONE O OTHER IN INSP/MAINT 1 GL 09 1886G 1348 5500722 WHILE ACCOMPLISHING A PHASE INSPECTION, FLIGHT CONTROL GUST LOCK WAS ENGAGED AND FOUND SLOPPY AND OUT OF RIG. FURTHER I NVESTIGATION FOUND THE GUST LOCK SLIDE ASSY HAD SPLIT IN HALF WHERE THE RT ELEVATOR CABLE PASSES THROUGH. ONLY THE FORW ARD SIDE OF THE SLIDE ASSY WAS HOLDING IT TOGETHER. THE APPEARANCE OF THE FAILURE INDICATED AN EXCESSIVE ELEVATOR DOWN FORCE WAS APPLIED WHILE THE GUST LOCK WAS ENGAGED. SUBMITTER STATED SYSTEM SHOWED NO SIGNS OF BEING RIGGED IMPROPERLY. ALL FLIGHT CONTROL SYSTEMS WERE CHECKED FOR DAMAGE. FAILED SLIDE ASSY WAS REPLACED WITH NEW FLIGHT CONTROL AND GUST LO CK SYSTEMS WERE ALL RIGGED. 1 L 7 2 4F A22CE 1996102400026 19961024 00026 CE 1996 10 24 96ZZZX5269 1 19961001 G 3260 J3A CONNECTOR CESSNA 500 550 2076604 CE GEAR INDICATOR MISWIRED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 2734K 3497 5500595 PILOT REPORTED 'GEAR UNSAFE' LIGHT REMAINS 'DIMLY' LIT AFTER GEAR UP WITH PANEL LIGHTS ON. FOUND WIRE 'D41' FROM GEAR UNSAFE LIGHT ASSY PINNED INTO 'F2' INSTEAD OF 'A2' OF CONNECTOR J3A AS SCHEMATIC SHOWS ON P3A SIDE, WIRE IDENTIFIED AS F 2P3APP4 WAS PINNED IN COMING FROM 5VDC COPILOT INST LIGHT DIMMER SOURCE. COULD NOT FIND THIS WIRE IN ANY DRAWINGS, BUT SINCE GEAR POSITION LIGHTS ARE 28VDC, THE 5VDC INPUT EXPLAINS THE DIMLY ILLUMINATED CONDITION. WIRING CORRECTED AND LIG HTS FUNCTIONED NORMALLY. 1 L 7 2 4F A22CE 1996102400027 19961024 00027 CE 1996 10 24 96ZZZX5270 1 19960930 G 2730 2655221303 BELLCRANK RKWELL NA265 NA26540 6402608 CE ELEV STAB CORRODED D K NONE O OTHER IN INSP/MAINT 1 SO 16 301NT 14458 14458 28229 SEVERELY CORRODED MAGNESIUM BELLCRANK WHICH OPERATES THE BIAS BUNGEE FOR ELEVATOR TO STABILIZER LONGITUDINAL CONTROL. T HIS UNIT IS LOCATED IN THE AFT LOWER LEFT SIDE OF FS 457. VISUAL INSPECTION IS VERY DIFFICULT DUE TO LOCATION AND POSITI ON OF ROD END ATTACHMENT POINTS. SUBMITTER SUGGESTS THIS ITEM BE REMOVED AND INSPECTED AT NEXT SCHEDULED INSPECTION. B ELLCRANKS FAILURE WOULD CAUSE LIMITED ELEVATOR TRAVEL AND LOSS OF ELEVATOR TO STABILIZER CONTROL FOR TRIMMING. 2 L 7 2 4J A2WE 1996102400028 19961024 00028 CE 1996 10 24 96ZZZX5271 1 19960924 G 2730 265522007 CONTROL CABLE RKWELL NA265 NA26540 6402608 CE ELEV CONTROL CORRODED D S K NONE O OTHER IN INSP/MAINT 1 SO 16 303NT 10833 28229 LOWER AFT ELEV CONTROL CABLE FS 388 TO FS 457 SHOWED SIGNS OF CORROSION ON UPPER SURFACE 'ONLY' JUST AFT OF FIBERGLASS P ROTECTIVE CABLE SHROUD PN 265-540425-37 FS 368 TO FS 390. CABLES ARE VISUALLY INSPECTED AT 150 HR INTERVALS. CABLES AR E MANUFACTURED OF CARBON STEEL .1562 INCH DIAMETER WITH 10 STRANDS. PRIOR TO REMOVAL, 'NO' BROKEN WIRES OR STRANDS WERE NOTED 'SMOOTH' SURFACE. REMOVED CABLE FOR FURTHER INSPECTION, FLEXED CABLE IN A MILD 'U' AND 12 BROKEN WIRES IN DIFFER ENT STRANDS BROKE IN A 1 INCH AREA WITH SEVERE INNER CORROSION. NOTE: CORROSION COULD BE OVERLOOKED DUE TO SMALL SURFA CE AREA EFFECTED. REMOVED CABLE FROM SERVICE. 2 L 7 2 4J A2WE 1996102400029 19961024 00029 CE 1996 10 24 96ZZZX5272 1 19960927 G 2730 265522007 CONTROL CABLE RKWELL NA265 NA26540 6402608 CE ELEV CONT CORRODED D S K NONE O OTHER IN INSP/MAINT 1 SO 16 309NT 10508 28261 LOWER AFT ELEV CONTROL CABLE FS 388 TO FS 457 SHOWED SIGNS OF CORROSION ON UPPER SURFACE 'ONLY' JUST AFT OF THE FIBERGLA SS PROTECTIVE CABLE SHROUD PN 265-540425-37, FS 368 TO FS 390. CABLES ARE VISUALLY INSPECTED AT 150-HOUR INTERVALS. CA BLES ARE MANUFACTURED OF CARBON STEEL .1562 INCH DIAMETER WITH 10 STRANDS PRIOR TO REMOVAL. 'NO' BROKEN WIRES OR STRAND S WERE NOTED, 'SMOOTH' SURFACE. REMOVED CABLE FOR FURTHER INSPECTION, FLEXED CABLE IN A MILD 'U' AND 1 COMPLETE BROKEN STRAND AND 15 DIFFERENT WIRES IN DIFFERENT STRANDS IN A 1 INCH AREA BROKE, WITH SEVERE INNER CORROSION. NOTE: CORROSI ON COULD BE OVERLOOKED DUE TO SMALL SURFACE AREA EFFECTED. REMOVED CABLE FROM SERVICE. 2 L 7 2 4J A2WE 1996102400030 19961024 00030 CE 1996 10 24 96ZZZX5273 1 19960925 G 2730 2655221303 BELLCRANK RKWELL NA265 NA26540 6402608 CE ELEV STAB CORRODED D S K NONE O OTHER IN INSP/MAINT 1 SO 16 314NT 14458 14458 28228 SEVERELY CORRODED MAGNESIUM BELLCRANK WHICH OPERATES THE BIAS BUNGEE FOR ELEVATOR TO STABILIZER LOCATED IN AFT LOWER LEF T SIDE OF FS 457. VISUAL INSPECTION IS VERY DIFFFICULT DUE TO LOCATION AND POSITION OF ROD END ATTACHMENT POINTS. SUBM ITTER SUGGESTS THIS ITEM BE REMOVED AND INSPECTED AT NEXT SCHEDULED INSPECTION. BELLCRANKS FAILURE WOULD CAUSE LIMITED ELEV TRAVEL AND LOSS OF ELEV TO STABILIZER CONTROL FOR TRIMMING PURPOSES. BELLCRANK REMOVED FROM SERVICE. 2 L 7 2 4J A2WE 1996102400031 19961024 00031 CE 1996 10 24 96ZZZX5274 1 19960926 G 2730 265522007 CONTROL CABLE RKWELL NA265 NA26540 6402608 CE ELEV CONT CORRODED D S K NONE O OTHER IN INSP/MAINT 1 SO 16 314NT 14458 28228 LOWER AFT ELEV CONTROL CABLE FS 388 TO FS 457 SHOWED SIGNS OF CORROSION ON UPPER SURFACE 'ONLY' JUST AFT OF FIBERGLASS P ROTECTIVE CABLE SHROUD PN 265-540425-37, FS 368 TO FS 390. CABLES ARE VISUALLY INSPECTED AT 150-HOUR INTERVALS. CABLES ARE MANUFACTURED OF CARBON STEEL .1562 INCH DIAMETER WITH 10 STRANDS. PRIOR TO REMOVAL 'NO' BROKEN WIRES OR STRANDS NO TED, SMOOTH SURFACE. REMOVED CABLE FOR FURTHER INSPECTION. FLEXED CABLE IN A MILD 'U' AND 14 BROKEN WIRES IN DIFFERENT STRANDS BROKE IN A 1 INCH AREA, WITH SEVERE INNER CORROSION. NOTE: CORROSION COULD BE OVERLOOKED DUE TO SMALL SURFACE AREA EFFECTED. REMOVED CABLE FROM SERVICE. 2 L 7 2 4J A2WE 1996102400032 19961024 00032 CE 1996 10 24 96ZZZX5275 1 19960916 G 2910 1303800033 SWITCH BEECH B300 B300 1159232 CE LT PRESS FAILED D A K NONE F FLT CONT AFFECTED IN INSP/MAINT 1 NM 01 4S 22 FL207 PILOT REPORTED INTERMITTENT RUDDER BOOST ACTIVATION. BOOST WAS ON FOR TAKEOFF AND INTO 10 MINUTES OF FLIGHT. YAW DAMP WAS INOP THIS TIME. RECYCLING RUDDER BOOST SWITCH TURN THE BOOST OFF AND THEN BACK ON. AUTOPILOT WORKED, BUT WITHOUT R UDDER BOOST. AFTER ABOUT 10 MINUTES, RUDDER BOOST STARTED WORKING AGAIN PROPERLY AS WELL AS THE YAW DAMPENER. DETERMIN ED LEFT PRESSURE SWITCH FAULTY. REPLACED PRESSURE SWITCH AND FUNCTIONALLY TESTED NORMAL. 2 L 7 2 4T RT A24CE 1996102400034 19961024 00034 EU 1996 10 24 96ZZZX5276 1 19961003 G 2150 25VF1399AB DUCT HWKSLY DH125 BH125400A 4230138 EU RAM AIR CRACKED B L A K5SR K NONE O OTHER IN INSP/MAINT 1 NM 11 89SR 7034 NA778 AIR CONDITIONING RAM AIR INTAKE TO REFRIGERATION UNIT INLET DUCT SEVERELY CRACKED ON LT AND RT SIDES LOWER AREA. RT SID E LOWER CONNECTION PORT (CAPPED FOR THIS INSTALLATION) COMPLETELY SEPARATED FROM DUCT AND FOUND LAYING ON ELEVATOR FLIGH T CONTROL CABLES DURING A PRE-FLIGHT INSPECTION. BAE 125 1-600 AIRCRAFT MAINTENANCE SCHEDULE MAKES NO SPECIFIC INSPECTI ON NOTES TO THIS DUCT, ONLY GENERAL - 'INSPECT AIR CONDITIONING PIPES, DUCTS, ETC.' DUE TO DUCT LOCATION, A DETAILED IN SPECTION IS NOT POSSIBLE WITHOUT DISASSMEBLY AND REMOVAL OF OTHER AIR CONDITIONING SYSTEM COMPONENTS. 2 L 7 2 4J A3EU 1996102400085 19961024 00085 1996 10 24 96ZZZX5277 2 19960913 G 7314 5006485 DRIVE SHAFT LUCAS 5009986 FUEL PUMP FAILED H C D ABORTED TAKEOFF RETURN TO BLOCK O OTHER TO TAKEOFF 1 WP 27 1836 FUEL PUMP FAILED ON TAKEOFF ROLL. FOUND THERE IS NO SPLINE LEFT ON DRIVE SHAFT OR DRIVE GEAR. DRIVE SHAFT TURNS EASILY BY HAND. 1996102400086 19961024 00086 1996 10 24 96ZZZX5278 2 19960913 G 7314 5006484 DRIVE GEAR LUCAS FUEL PUMP FAILED H C D ABORTED TAKEOFF RETURN TO BLOCK O OTHER TO TAKEOFF 1 WP 27 1836 FUEL PUMP FAILED ON TAKEOFF ROLL. FOUND THERE IS NO SPLINE LEFT ON DRIVE SHAFT OR DRIVE GEAR. DRIVE SHAFT TURNS EASILY BY HAND. 1996102400087 19961024 00087 1996 10 24 96ZZZX5279 2 19960923 G 7314 5006485 DRIVE SHAFT LUCAS 5009986 FUEL PUMP FAILED H K NONE O OTHER NR NOT REPORTED 1 WP 27 1601 FUEL PUMP HAS NO FUEL FLOW. FOUND THERE WAS NO SPLINE LEFT ON DRIVE SHAFT OR DRIVE GEAR. DRIVE SHAFT EASILY TURNS BY H AND. SUBMITTER STATED C/W P & W SB NR 21087R6 COULD HAVE PREVENTED EXCESSIVE WEAR ON DRIVE SHAFT INTERNAL SPLINE. 1996102400088 19961024 00088 1996 10 24 96ZZZX5280 2 19960923 G 7314 5006484 DRIVE GEAR LUCAS 5009986 FUEL PUMP FAILED H K NONE O OTHER NR NOT REPORTED 1 WP 27 1601 FUEL PUMP HAS NO FUEL FLOW. FOUND THERE WAS NO SPLINE LEFT ON DRIVE SHAFT OR DRIVE GEAR. DRIVE SHAFT EASILY TURNS BY H AND. SUBMITTER STATED C/W P & W SB NR 21087R6 COULD HAVE PREVENTED EXCESSIVE WEAR ON DRIVE SHAFT INTERNAL SPLINE. 1996102400089 19961024 00089 1996 10 24 96ZZZX5281 1 19960901 G 2822 2B761 PUMP AIRBORNE FUEL BOOST SHAFT DAMAGED D K NONE O OTHER IN INSP/MAINT 1 GL 13 6AA17 BOOST PUMP ARMATURE SHAFT DAMAGED, SPACER WORE GROOVE IN SHAFT. 1996102400090 19961024 00090 1996 10 24 96ZZZX5282 1 19961009 G 2822 2B729 PUMP AIRBORNE FUEL BOOST SHAFT DAMAGED D K NONE O OTHER IN INSP/MAINT 1 GL 13 1AH6 BOOST PUMP ARMATURE SHAFT DAMAGED BY SPACER. 1996102400091 19961024 00091 1996 10 24 96ZZZX5283 1 19961007 G 2822 2B673 PUMP AIRBORNE FUEL BOOST OUT OF BALANCE D K NONE O OTHER IN INSP/MAINT 1 GL 13 11F7 FOUND ARMATURE OUT OF DYNAMIC BALANCE CAUSING PREMATURE FAILURE OF THE PUMP. 1996102400092 19961024 00092 1996 10 24 96ZZZX5284 1 19961009 G 2822 2B729 PUMP FUEL BOOST DAMAGED H K NONE O OTHER IN INSP/MAINT 1 GL 13 6AG94 FOUND BOOST PUMP HAS DAMAGE TO ARMATURE SHAFT. 1996102400093 19961024 00093 1996 10 24 96ZZZX5285 1 19961009 G 2822 2B729 PUMP FUEL BOOST DAMAGED H K NONE O OTHER IN INSP/MAINT 1 GL 13 7AC292 BOOST PUMP HAS DAMAGE TO ARMATURE SHAFT. 1996102400094 19961024 00094 CE 1996 10 24 96ZZZX5286 1 19960901 G 7603 CABLE BEECH 18 H18 1151012 CE POWER LEVER SLIPPED D E ENGINE SHUTDOWN O OTHER NR NOT REPORTED 1 SW 99 508FS BA688 PILOT COULD NOT REDUCE POWER TO RT ENGINE DURING FLIGHT, RT ENGINE WAS FEATHERED FOR LANDING. INSPECTION REVEALED POWE R CABLE ATTACH POINT AT FUEL CONTROL UNIT JAM NUT BACKED OFF ALLOWING THE CABLE TO SLIP. TIGHTENED JAM NUT. CHECKED RI GGING, OPS CHECK GOOD. 1 L 7 2 3R A765 1996102400095 19961024 00095 EA 1996 10 24 96ZZZX5287 2 19960127 G 7314 LW15473 PUMP PIPER PA34 PA34200 7103405 SO LYC O360 IO360C1E6 41514 EA ENGINE FUEL PORT BLOCKED G O OTHER Y ENGINE STOPPAGE NR NOT REPORTED 1 EA 13 2FOR 7 7 347350236 L1054451A AN AUSTRALIAN BASED PA-34 PILOT REPORTED ENGINE FAILURE DUE TO FUEL STARVATION. CAUSE WAS A RUBBER WASHER BLOCKING THE FUEL OUTLET PORT OF A NEW TEXTRON FUEL PUMP. TEXTRON SB 525 ADDRESSES THE PROBLEM. NO AIRWORTHINESS DIRECTIVE HAS BEEN ISSUED TO DATE. SUBMITTER STATED THERE ARE 4 KNOWN FAILURES FROM SAME CAUSE. NOTE: SAME PROBLEM AS MOONEY M20J IN OC T '96 ALERTS. 1 L 7 2 3O 3 O A7SO 1E10 1996102400096 19961024 00096 SO 1996 10 24 96ZZZX5288 1 19960805 G 3231 8626203 TUBE PIPER PA44 PA44180 7104402 SO GEAR DOOR ARM BROKE D O OTHER O OTHER NR NOT REPORTED 1 WP 05 144RJ 447995323 THE ARM THAT HOLDS THE ROD FOR THE GEAR DOOR BROKE. THIS JAMMED THE GEAR DOOR IN THE UP POSITION NOT LETTING THE GEAR G O DOWN. 1 L 7 2 3O A19S0 1996102400097 19961024 00097 SO 1996 10 24 96ZZZX5289 2 19961001 G 7414 107902010 IMPULSE COUPLING S6RN2510 CESSNA 180 180H 2072618 CE CONT O470 O470R 17026 SO RT MAGNETO SPRING BROKEN D K NONE O OTHER IN INSP/MAINT 1 NM 02 2700X 125 I059114DR 18051500 1311175R5 FOUND IMPULSE COUPLING, SPRING BROKEN DUE TO CORROSION. 1 H 7 1 3O 3 O 5A6 E273 1996102400098 19961024 00098 SO 1996 10 24 96ZZZX5290 2 19961001 G 7414 107902010 IMPULSE COUPLING S6RN2510 CESSNA 180 180H 2072618 CE CONT O470 O470R 17026 SO LT MAGNETO SPRING BROKEN D K NONE O OTHER IN INSP/MAINT 1 NM 02 2700X 125 H089109DR 18051500 1311175R5 FOUND IMPULSE COUPLING, SPRING BROKEN DUE TO CORROSION. 1 H 7 1 3O 3 O 5A6 E273 1996102400099 19961024 00099 SO 1996 10 24 96ZZZX5291 2 19960928 G 8530 CYLINDER CONT O520 IO520* 17032 SO NR 4 CYL EXH SEAT WORN D K NONE O OTHER IN INSP/MAINT 1 SW 99 2FOR 422 291369R THE AIRCRAFT ARRIVED FOR 100-HOUR INSPECTION. COMPRESSION CHECK SHOWED NR 4 CYLINDER 55/80. ALL OTHER CYLINDERS WERE I N THE MID 70'S. THE CYLINDER WAS REMOVED. EXHAUST VALVE AND SEAT WERE WORN EXCESSIVELY. THIS IS A FACTORY RE-MANUFACTU RED ENGINE. ALSO, FOUND, EXHAUST GUIDE WORN EXCESSIVELY, CYLINDER CHOKE AT MINIMUM SERVICE LIMIT, AND CYLINDER .0015 I NCH OUT OF ROUND. ALL OTHER CYLINDERS APPEAR TO BE NORMAL. 3 O E5CE 1996102400100 19961024 00100 EA 1996 10 24 96ZZZX5292 2 19960814 G 7314 LW154731095 PUMP PIPER PA32 PA32300 7103212 SO LYC O540 IO540K1G5 41532 EA ENGINE FUEL PORT BLOCKED G O OTHER Y ENGINE STOPPAGE NR NOT REPORTED 1 EA 13 29145 30 327940128 L1932048A PILOT REPORTED ENGINE FAILURE DUE TO FUEL STARVATION. CAUSE WAS A RUBBER WASHER BLOCKING THE FUEL OUTLET PORT OF A NEW TEXTRON FUEL PUMP. TEXTRON SB 525 ADDRESSES THE PROBLEM. NO AIRWORTHINESS DIRECTIVE HAS BEEN ISSUED TO DATE. SUBMITTE R STATED THERE ARE 4 KNOWN FAILURES FROM SAME CAUSE. NOTE: SAME PROBLEM AS MOONEY M20J IN OCT '96 ALERTS. 1 L 7 1 3O 3 O A3SO 1E4 1996102400101 19961024 00101 EU 1996 10 24 96ZZZX5293 1 19961003 G 2720 T67M45209 CRANK SLNSBY T67 T67M260 8323006 EU RUDDER BAR CHAFING D K NONE O OTHER IN INSP/MAINT 1 SW 17 3189N 289 2213 WHILE PERFORMING AN ANNUAL INSPECTION, NOTICED LT RUDDER BAR CRANK WAS CHAFING ON RUDDER BAR WHEN BRAKE WAS APPLIED. SU SPECT RUDDER BAR CRANK WAS IMPROPERLY INSTALLED IN PRODUCTION. SLINGSBY IPC CHAPTER 19, PAGES 19, 20, ITEMS 5 AND 2. 1 L 7 1 3O NT A73EU 1996102400102 19961024 00102 EU 1996 10 24 96ZZZX5294 1 19960907 G 3242 30305500 BRAKE CALIPER PARKERHANFIN SLNSBY T67 T67M260 8323006 EU RT MLG LEAKING D K NONE K FLUID LOSS IN INSP/MAINT 1 SW 17 3192X 197 2231 DURING 100-HOUR INSPECTION, RT BRAKE CALIPER FOUND LEAKING THROUGH CASE, WHEN BRAKE WAS APPLIED. HYDRAULIC FLUID WAS SE EN LEAKING FROM CASE. SUBMITTER SUSPECTS POSSIBLE IMPURITIES IN MOLD WHEN BEING MADE. THIS IS THE SECOND OCCURRENCE. 1 L 7 1 3O NT A73EU 1996102400103 19961024 00103 CE 1996 10 24 96ZZZX5295 1 19961002 G 3230 12414231 SADDLE ASSY CESSNA 210 210D 2073414 CE LT MLG ACT BROKEN G A A UNSCHED LANDING O OTHER CL CLIMB 1 NM 11 3815Y 3008 21058315 LEFT LANDING GEAR WOULD NOT EXTEND OR RETRACT AFTER TAKEOFF. AN EMERGENCY LANDING WAS MADE WITH THE GEAR IN THE UP POSI TION. MINOR DAMAGE TO BELLY OF AIRCRAFT AND BENT PROPELLER BLADES. FOUND BROKEN GEAR SADDLE THAT ATTACHES TO GEAR ACTU ATOR. 1 H 7 1 3O 3A21 1996102400104 19961024 00104 SO 1996 10 24 96ZZZX5296 1 19960921 G 2510 AF35 HARNESS PIPER J3 J3L 7100542 SO COCKPIT IMPROPER D A K NONE W INADEQUATE Q C IN INSP/MAINT 1 NE 01 38345 6953 WHEN SHOULDER HARNESS IS INSTALLED PER STC NR SA 1581 GL, IT PREVENTS THE SOLO PILOT, SITTING IN THE AFT SEAT, FROM OPER ATING EITHER THE FUEL SHUT-OFF VALVE OR THE CARBURETOR HEAT VALVE. ONLY AN INERTIA REEL TYPE HARNESS WOULD ALLOW THIS T YPE OF INSTALLATION TO MEET THE AIRWORTHINESS (CONTROL ACCESSIBILITY) REQUIREMENTS OF C.A.R.4A. SUBMITTER BELIEVES THIS STC SHOULD BE REVIEWED ON THIS BASIS. P/N AF35 OR AF36. 1 H 7 1 3O A698 1996102400105 19961024 00105 CE 1996 10 24 96ZZZX5297 1 19960912 G 8120 TURBOCHARGER CESSNA 401 401 207590C CE CONT O520 TSIO520E 17040 SO WASTEGATE FAILED D O OTHER R PARTIAL RPM/PWR LOSS CR CRUISE 1 WP 19 401LF 40180018 PILOT COMPLAINED OF LOOSING POWER IN BOTH ENGINES ALTHOUGH NOT SIMULTANEOUSLY. DURING GROUND RUN BOTH WASTEGATES WERE F OUND STUCK IN THE OPEN POSITION. AFTER LUBRICATING WASTEGATE SHAFTS AND MOVING THEM BY HAND, SUBSEQUENT GROUND RUNS SHO WED NORMAL OPERATION. FAILURE INITIALLY OCCURRED EN ROUTE AT 19,000 FEET. MOUSE MILK WAS USED TO LUBE. RECOMMEND REGU LAR LUBRICATION. 1 L 7 2 3O 3 O A7CE E8CE 1996102400106 19961024 00106 SO 1996 10 24 96ZZZX5298 1 19960501 G 7430 A1502 SWITCH GERDES PIPER PA38 PA38112 7103812 SO IGNITION FAILED D K NONE O OTHER IN INSP/MAINT 1 GL 23 4276E 3454 2317F 3878A0522 IN THE OFF POSITION, ENGINE WOULD CONTINUE TO RUN ON RIGHT MAGNETO. PROPER MAGNETO DROP OCCURRED ON EITHER LEFT OR RIGH T MAGNETO. 1 L 7 1 3O A18SO 1996102400107 19961024 00107 SO 1996 10 24 96ZZZX5299 1 19960626 G 5712 6206102 RIB PIPER PA28 PA28151 7102805 SO RT WINGWALK CRACKED D K NONE O OTHER IN INSP/MAINT 1 GL 09 43456 4940 287415499 DURING 100-HOUR INSPECTION, FOUND WING-WALK DOUBLER RIBS CRACKED. FIVE OF THE RIBS WERE CRACKED AT OUTBOARD EDGE. SUBM ITTER SUSPECTS CAUSE WAS TOTAL TIME AND POSSIBLY STRESS INDUCED DURING FORMING OF RIBS. 1 L 7 1 3O 2A13 1996102400108 19961024 00108 CE 1996 10 24 96ZZZX5300 1 19960614 G 3222 AN547A BOLT CESSNA 172 172M 2072418 CE NLG FORK BENT D K NONE O OTHER IN INSP/MAINT 1 GL 09 4468R 4428 17263210 DURING ANNUAL INSPECTION AND INSTALLATION OF WHEEL PANTS, FOUND AN5-47A BOLT BENT AFTER REMOVAL. THIS BOLT RETAINS THE FORK TO THE LOWER BARREL AND SECURES THE PIN BASE PLUG IN PLACE. SUBMITTER SUSPECTS CAUSE IS HIGH TOTAL TIME WITH POSSI BLY HARD LANDINGS 1 H 7 1 3O NT 3A12 1996102400109 19961024 00109 CE 1996 10 24 96ZZZX5301 1 19960621 G 7810 15550142 CLAMP CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA EXHAUST SYSTEM CRACKED D K NONE O OTHER IN INSP/MAINT 1 GL 09 5249P 5047 15284901 L1451415 DURING INSPECTION, FOUND SIX EXHAUST CLAMP HALVES CRACKED. SUBMITTER SUSPECTS HIGH TOTAL TIME AND CORROSION OF EXHAUST PARTS. 1 H 7 1 3O 3 O NT 3A19 E223 1996102400110 19961024 00110 SO 1996 10 24 96ZZZX5302 1 19960805 G 7810 7846310 TAILPIPE PIPER PA34 PA34200 7103405 SO LT ENGINE BAFFLE DETACHED D K NONE R PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 GL 09 56676 5945 347450020 WHILE TROUBLESHOOTING INTERMITTENT LOSS OF POWER, FOUND BAFFLE INSIDE OF TAILPIPE HAD BROKEN LOOSE AND WEDGED NEAR OUTLE T OF TAILPIPE. THIS CAUSED AN INCREASE I N BACK PRESSURE WHICH CAUSED THE ENGINE TO NOT DEVELOP RATED POWER. SUBMITTER SUSPECTS CAUSE, HIGH TOTAL TIME, VIBRATION, HEAT. 1 L 7 2 3O A7SO 1996102400111 19961024 00111 SO 1996 10 24 96ZZZX5303 2 19960910 G 8530 642410CN CYLINDER CESSNA 182 182M 2072728 CE CONT O470 O470R 17026 SO INT RKR SHAFT OUT OF SPEC D K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 09 71136 28 18259509 1949268R CYLINDER CLASS 68-1 RECEIVED WITH INTAKE ROCKER SHAFT END-PLAY IN EXCESS OF (SIDE CLEARANCE). .040 INCH RECEIVED FROM EC SW, 8-13-96. 1 H 7 1 3O 3 O NT 3A13 E273 1996102400112 19961024 00112 EA 1996 10 24 96ZZZX5304 2 19960501 G 7314 LW15473 PUMP PIPER PA28 PA28R180 7102809 SO LYC O360 IO360B1E 41514 EA ENGINE FUEL PORT BLOCKED G A O OTHER Y ENGINE STOPPAGE NR NOT REPORTED 1 EA 13 7567J 12 28R30946 L556251 PILOT REPORTED ENGINE FAILURE DUE TO FUEL STARVATION. CAUSE WAS A RUBBER WASHER BLOCKING FUEL OUTLET PORT OF A NEW TEXT RON FUEL PUMP. TEXTRON SB 525 ADDRESSES THE PROBLEM. NO AIRWORTHINESS DIRECTIVE HAS BEEN ISSUED TO DATE. SUBMITTER ST ATES THERE ARE 4 KNOWN FAILURES FROM SAME CAUSE. NOTE: SAME PROBLEM AS MOONEY M20J IN OCT '96 ALERTS. 1 L 7 1 3O 3 O 2A13 1E10 1996102400113 19961024 00113 SO 1996 10 24 96ZZZX5305 1 19960920 G 7921 8529245 COOLER PIPER PA28 PA28236 7102815 SO ENGINE OIL WELD SPLIT D A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 WP 07 8181H 791462 288011073 AIRCRAFT LOST OIL PRESSURE IN-FLIGHT. RETURNED TO AIRPORT FOR A SAFE LANDING. INVESTIGATION FOUND OLD WELD REPAIR ON O IL COOLER LET GO. METAL FOUND IN OIL FILTER. ENGINE BEING DISASSEMBLED FOR INSPECTION. 1 L 7 1 3O 2A13 1996102400114 19961024 00114 CE 1996 10 24 96ZZZX5306 1 19961002 G 3260 YZ2RN7T SWITCH CESSNA 182 R182 2072734 CE MLG DOWNLOCK CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 19 7571W 1261 R18200062 DURING ANNUAL INSPECTION, FOUND BOTH MAIN LANDING GEAR DOWNLOCK INDICATOR SWITCHES CRACKED. BY APPLYING VERY SLIGHT SID E PRESSURE TO SWITCHES, THEY BOTH BROKE APART. SUSPECT CAUSE: BOTH LEFT AND RIGHT DOWNLOCK PADS, CESSNA P/N 2241105-5, WERE FOUND WORN. THIS CONDITION CAUSED THE MAIN LANDING GEAR TO STRIKE THE SWITCHES WITH TOO MUCH FORCE CAUSING THE SU BSEQUENT CRACKS TO THE SWITCHES. SUBMITTER RECOMMENDS REPLACEMENT OF WORN DOWNLOCK PADS OR INSTALLING CESSNA SK P/N SK1 82-8014, TO UPGRADE THE DOWNLOCK SWITCHES AND DOWNLOCK PADS, IF NOT PREVIOUSLY INSTALLED. 1 H 7 1 3O RT 3A13 1996102400116 19961024 00116 SO 1996 10 24 96ZZZX5308 1 19960916 G 7713 6333 INDICATOR MAULE M7 M7235 5460170 SO ENG MAN PRESS STUCK D K NONE O OTHER IN INSP/MAINT 1 GL 09 9234N 259 175369 4119C INDICATOR M.P. NEEDLE BECAME SLOW TO MOVE, THEN STUCK AT 25 INCHES. DATE STAMPED 1091. IN USE SINCE 1993. 1 H 7 1 3O NC 3A23 1996102400117 19961024 00117 SO 1996 10 24 96ZZZX5309 1 19960901 G 3250 3519200 HORN ASSY PIPER PA28 PA28151 7102805 SO NLG STEERING CRACKED D S A K NONE O OTHER IN INSP/MAINT 1 EA 11 9217K 4500 287615183 DURING ANNUAL INSPECTION OF AIRCRAFT, NOSE WHEEL STEERING HORN ASSEMBLY PIPER P/N 35 192-00, WAS FOUND TO HAVE A CRACK W HERE IT ATTACHES TO THE OLEO STRUT. SUSPECT CAUSE, PILOT APPLYING PRESSURE TO RUDDER PEDAL WITHOUT MOVING AIRCRAFT 1 L 7 1 3O 2A13 1996102400118 19961024 00118 NM 1996 10 24 96ZZZX5310 1 19960605 G 7920 HOSE AEROQUIP CHILD S2 S2APITTS 0110201 NM ENGINE STIFF D K NONE O OTHER IN INSP/MAINT 1 EA 09 80032 457 2054 REMOVED VERY RIGID/STIFF OIL AND FUEL HOSES, REPLACED WITH NEW ASSEMBLIES. HOSES WERE DATED 1971 AND 1972. THE AIRPLAN E IS A 1973 MODEL. SUBMITTER CONTINUES TO FIND OLD STIFF/BRITTLE HOSES ON ANNUAL INSPECTIONS. (THIS AIRCRAFT HAS 2 OIL COOLERS). 1 Q 7 1 3O A8SO 1996102400119 19961024 00119 EA 1996 10 24 96ZZZX5311 2 19960902 G 7414 MAGNETO CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA CAM FOLLOWER FAILED D L A UNSCHED LANDING Y ENGINE STOPPAGE CR CRUISE 1 SO 08 4696G 304 67119 17273322 RL18276T DURING CRUISE FLIGHT, ENGINE STOPPED PRODUCING POWER. AN OFF-AIRPORT LANDING MADE WITHOUT INCIDENT. MAINTENANCE INSPEC TION REVEALED BOTH SETS OF POINTS IN THE DUAL 2000 SERIES MAGNETO HAD CLOSED CAUSING ENG TO STOP. POINTS WERE RESET AND ENG RAN AND PRODUCED NORMAL POWER. 2.1 HRS LATER, WHILE FLYING ACFT HOME FROM THIS INCIDENT, ENG AGAIN STOPPED PRODUCI NG POWER AND ANOTHER OFF-AIRPORT LANDING MADE WITHOUT INCIDENT. MAINTENANCE INVEST REVEALED ONCE AGAIN POINTS HAD CLOSE D CAUSING ENG TO STOP. NYLON CAM FOLLOWER ON BOTH SETS OF POINTS WERE WORN COMPLETELY OFF. 1 H 7 1 3O 3 O NT 3A12 E274 1996102400120 19961024 00120 EA 1996 10 24 96ZZZX5312 2 19960927 G 7414 MAGNETO CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA CAM FOLLOWER EXCESS WEAR D L O OTHER R PARTIAL RPM/PWR LOSS TO TAKEOFF 1 SO 08 4696G 27 H019606GR 17273322 RL18276T AFTER INSTALLING A FACTORY REBUILT 3000 SERIES, MAGNETO AIRCRAFT WAS PLACED BACK ON RENTAL STATUS ON 9-27-96, A FLIGHT I NSTRUCTOR NOTICED TAKEOFF POWER WAS DOWN BY APPROXIMATELY 200 RPM AT FULL THROTTLE. MAINTENANCE INVESTIGATION REVEALED BOTH SETS OF MAGNETO POINTS HAD CLOSED TO APPROXIMATELY .005 INCH TO .006 INCH. CAM FOLLOWERS ON BOTH POINTS SHOWED AN ABNORMAL AMOUNT OF WEAR AND THE CAM SURFACE APPEARED ROUGH AND GRAINEY. ANOTHER REBUILT MAGNETO WAS SUPPLIED BY TCM WHI CH HAD AN EVEN ROUGHER CAM. BOTH MAGNETOS WERE RETURNED. 1 H 7 1 3O 3 O NT 3A12 E274 1996102400364 19961024 00364 NE 1996 10 24 96ZZZX5313 2 19960126 G 7230 536210 TABLOCK SKRSKY S64 S64F NE PWA JFTD12 JFTD12A5A 52047 NE THIRD STAGE DISK MISSING B L JYDR K NONE O OTHER IN INSP/MAINT 1 NM 09 159AC 1100 64084 677815 TABLOCK FOUND MISSING AT HIDDEN DAMAGE INSPECTION CONDUCTED ON COMPRESSOR BEING PROCESSED INTO THE REPAIR STATION ON 1-2 6-96. THE LAST OVERHAUL WAS PERFORMED BY EAC ON 8-4-94. WHEN INSPECTING THE COMPRESSOR THROUGH THE INLET, CONTACT OF 3 RD STAGE BLADE NOTED ON FACE OF 4TH STAGE STATOR NEAR CENTERLINE OF ENGINE (ROOT END OF BLADE). THE BLADE MOVED AFT CON TACTING FRONT OF STATOR DUE TO TABLOCK FAILURE. THIS IS THE 4TH OCCURRENCE OF TABLOCK FAILURE NOTED BY ERICKSON SINCE 1 994. ALL PROBLEMS HAVE BEEN REPORTED TO THE MANUFACTURER. 2 G 7 2 4U 4 U H6EA E15EA 1996102400373 19961024 00373 NE 1996 10 24 96ZZZX5316 3 19961010 G 6111 7826761 BEARING RACE RFC11M16A EMB 120 EMB120RT SO HAMSTD 14RF 14RF9 NE PROPELLER BLADE CRACKED B S NQ3R K NONE O OTHER IN INSP/MAINT 1 NM 01 503AS 854349 120275 CRACK INDICATION IN BLADE FILLET AND BUTT AREA OF SHANK ON BOTH SIDES OF GOUGE LINE IN FILLET AREA FROM EDGE OF SPLIT RA CES. 2 L 7 2 4T RT A31SO 6 C P11NE 1996102400741 19961024 00741 CE 1996 10 24 96ZZZX5318 1 19961008 G 2731 07612059 SHAFT CESSNA 185 A185F 2072821 CE ELEV TRIM WHEEL PIN SHEARED D L A UNSCHED LANDING F FLT CONT AFFECTED CL CLIMB 1 SO 11 1206F 2575 18502769 AIRCRAFT LOST ELEVATOR TRIM FUNCTION IN-FLIGHT AFTER TAKEOFF TRIMMED FOR CLIMB. THE AIRCRAFT WAS VERY DIFFICULT TO FLY LEVEL AT ANYTHING LESS THAN LOW POWER. INVESTIGATION OF THE ELEVATOR TRIM WHEEL SYS SHOWED ROLL PIN, CNAS 561-3-8, HOLD ING THE SHAFT TO THE TRIM CHAIN SPROCKET, WAS SHEARED ALLOWING SHAFT TO ROTATE INSIDE THE SPROCKET. REMOVAL OF THE SHAF T FOUND THE HOLE HOLDING ROLL PIN WAS ELONGATED, LARGER THAN THE HOLE IN THE SPROCKET. THIS IS DIFFICULT TO INSPECT, BU T ROCKING THE TRIM WHEEL BACK AND FORTH INDICATES IF THE ROLL PIN IS LOOSE (IT SHOULD BE A TIGHT FIT). ANY BINDING OF S TAB JACK SCREWS PUTS A LOT OF STRAIN ON THESE ROLL PINS. SUBMITTER STATED THIS IS A POTENTIALLY DANGEROUS SITUATION. 1 H 7 1 3O 3A24 1996102400742 19961024 00742 WP 1996 10 24 96ZZZX5319 2 19960928 G 7313 8682421 NOZZLE GARRTT TPE331 TPE331* 01514 WP ENG FUEL THREADS CRACKED B IUMR K NONE O OTHER IN INSP/MAINT 1 SW 11 DEFECT - CRACKS IN THE NOZZLE THREADS. THESE ARE VERY NOTICEABLE UPON ASSEMBLY WHEN BEING TORQUED, THEY TWIST OFF. THE SE TIPS COULD HAVE SEVERAL THOUSAND HOURS AND PREVIOUSLY OVERTORQUED. A LOT OF ENGINE DAMAGE CAN BE DONE IF THESE SEPAR ATE IN-FLIGHT. SUBMITTER RECOMMENDATION: CLOSE INSPECTGION OF THREAD AREA AFTER CLEANING, BEFORE ASSEMBLY. NOTE: OTH ER ACCESSORY SHOPS ARE ALSO FINDING THIS PROBLEM WITH CRACKING. 3 T E2WE 1996102400743 19961024 00743 WP 1996 10 24 96ZZZX5320 2 19960928 G 7313 8687521 NOZZLE GARRTT TPE331 TPE331* 01514 WP ENG FUEL THREADS CRACKED B IUMR K NONE O OTHER IN INSP/MAINT 1 SW 11 DEFECT - CRACKS IN THE NOZZLE THREADS. THESE ARE VERY NOTICEABLE UPON ASSEMBLY WHEN BEING TORQUED, THEY TWIST OFF. THE SE TIPS COULD HAVE SEVERAL THOUSAND HOURS AND PREVIOUSLY OVERTORQUED. A LOT OF ENGINE DAMAGE CAN BE DONE IF THESE SEPAR ATE IN-FLIGHT. SUBMITTER RECOMMENDATION: CLOSE INSPECTION OF THREAD AREA AFTER CLEANING, BEFORE ASSEMBLY. NOTE: OTHE R ACCESSORY SHOPS ARE ALSO FINDING THIS PROBLEM WITH CRACKING. 3 T E2WE 1996102400744 19961024 00744 NM 1996 10 24 96ZZZX5321 1 19961007 G 2823 9785AR INPUT GEAR 107796A110 BOEING 737 737* NM FUEL SOV BINDING B DM4R K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 19 1073 FUEL SHUTOFF ACTUATOR ASSY WOULD STALL WITH A SLIGHT INWARD PRESSURE ON OUTPUT SHAFT. RECENTLY OVERHAULED BY ANOTHER RE PAIR STATION (6-20-96). IMPROPER SHIMMING OF ARMATURE ASSY CAUSED INPUT GEAR TO RUB AGAINST ARMATURE SHAFT, ALSO, EXCES SIVE PLAY AT OUTPUT SHAFT ALLOWED GEAR TRAIN TO MOVE AGAINST INPUT GEAR. INCORRECT GREASE AND PACKINGS WERE USED, LOCK SCREWS ARE NOT HOLDING. NOT ALL PACKINGS REPLACED. 2 L 7 2 4F RT A16WE 1996102400745 19961024 00745 NE 1996 10 24 96ZZZX5322 2 19960802 G 7313 814358 NOZZLE PWA JT8 JT8D217 52053 NE FUEL NOZZLE NUT DETACHED D K NONE O OTHER IN INSP/MAINT 1 GL 09 5195 THE FUEL NOZZLE AS RECEIVED CONDITION FOR OVERHAUL TO CMM73-13-02 BY FST REPAIR STATION - IUR 948M WITH THE NUT COMPLET ELY DETACHED FROM THE NOZZLE ASSY. THE NUT HAD LOOSENED AND MANY AREAS OF THE NUT, NOZZLE, AND SUPPORT SHOW AREAS OF SE VERE WEAR. SOME OF THESE AREAS ARE OVER FUEL PASSAGES, INTERNAL TO THE NOZZLE ASSY, AD 94-14-16 WAS C/W IN '95. P AND W SB 6240 WAS ISSUED SUBSEQUENT TO THE LAST OVERHAUL. 4 F E9NE 1996102400746 19961024 00746 SW 1996 10 24 96ZZZX5323 1 19961007 G 2820 AN82112 ELBOW GULSTM 560 560 0141402 SW FUEL DIST LOOSE D S K NONE W INADEQUATE Q C IN INSP/MAINT 1 EA 13 183AJ 1008 5600276 DURING REPAIR OF FUEL PANEL, PN 611BB, RT CENTER STUB WING, THE STATED ELBOW WAS FOUND LOOSE AT BOTH B-NUTS, ONE ONLY EN GAGED BY HALF OF A TURN. NUTS WERE TIGHTENED AND TORQUED IAW MAINTENCE. THIS AREA IS NOT INSPECTED UNTIL THE PHASE 5 1 ,200-HOUR INSPECTION. SUBMITTER SUSPECTS LOOSE NUTS WERE NEVER TIGHTENED AT FACTORY. 1 H 7 2 3O 6A1 1996102400747 19961024 00747 CE 1996 10 24 96ZZZX5324 1 19961004 G 3233 B543 BEARING 99810057603 BEECH 200 B200 1152922 CE RT MLG INBD FAILED D K NONE O OTHER IN INSP/MAINT 1 WP 15 113GW 2195 BB541 DURING MAINTENANCE AND LUBRICATION OF MAIN LANDING GEAR ACTUATORS AND INSPECTION, BEARING FELL APART ON REMOVAL. RACE, OUTER PORTION OF BEARING WAS BROKEN IN HALF. BEARING SCORED. PLATE, PN 115-811046-1, AND PLATE HAD TO BE REPLACED. 1 L 7 2 4T A24CE 1996102400748 19961024 00748 EA 1996 10 24 96ZZZX5325 2 19961003 G 7261 3026889 RETAIN RING BEECH 90 C90 1152913 CE PWA PT6 PT6A21 52043 EA ENG OIL VALVE DETACHED D K NONE O OTHER IN INSP/MAINT 1 WP 07 3263C 30 LJ1432 PCE25909 ON ENGINE START-UP TO IDLE, ENGINE OIL PRESSURE GAUGE SHOWED NO OIL PRESSURE. FOUND OIL PRESSURE RELIEF VALVE RETAINING RING WAS NOT SEATED IN HOUSING AND RELIEF VALVE HAD FALLEN PART WAY OUT OF HOUSING. SUBMITTER STATED WHEN INSTALLING P RESSURE RELIEF VALVE CHECK FOR PROPER ENGAGEMENT OF RETAINING RING WITH SMALL MIRROR AND FLASHLIGHT. 1 L 7 2 3T 4 T 3A20 E4EA 1996102400749 19961024 00749 CE 1996 10 24 96ZZZX5326 1 19961004 G 2730 2655221303 BELLCRANK RKWELL NA265 NA26540 6402608 CE ELEVATOR CONTROL CORRODED D A K NONE O OTHER IN INSP/MAINT 1 SO 16 307NT 13742 28272 SEVERELY CORRODED MAGNESIUM BELLCRANK, PN 265-522130-3, WHICH OPERATES THE BIAS BUNGEE FOR ELEVATOR TO STABILIZER LONGIT UDINAL CONTROL. THIS UNIT IS LCOATED IN THE AFT LOWER LEFT SIDE OF FS 457. VISUAL INSPECTION IS VERY DIFFICULT DUE TO L OCATION AND POSITION OF ROD END ATTACHMENT POINTS. SUBMITTER SUGGESTS THIS ITEM BE REMOVED AND INSPECTED AT THE NEXT SC HEDULED INSPECTION. BELLCRANKS FAILURE WOULD CAUSE LIMITED ELEVATOR TRAVEL AND LOSS OF ELEVTOR TO STABILIZER CONTROL FO R TRIMMING PURPOSES. BELLCRANK REMOVED FROM SERVICE. 2 L 7 2 4J A2WE 1996102400750 19961024 00750 CE 1996 10 24 96ZZZX5327 1 19961004 G 2730 2655221303 BELLCRANK RKWELL NA265 NA26540 6402608 CE ELEV CONTROL CORRODED D K NONE O OTHER IN INSP/MAINT 1 SO 16 317NT 8024 282100 SEVERELY CORRODED MAGNESIUM BELLCRANK PN 265-522130-3 WHICH OPERATES THE BIAS BUNGEE ELEVATOR TO STABILIZER LONGITUDINAL CONTROL. THIS UNIT IS LOCATED IN THE AFT LOWER LEFT SIDE OF FS 457. VISUAL INSPECTION IS VERY DIFFICULT DUE TO LOCATI ON AND POSITION OF ROD END ATTACHMENT POINTS. SUBMITTER SUGGESTS THIS ITEM BE REMOVED AND INSPECTED AT THE NEXT SCHEUDL ED INSPECTION. BELLCRANKS FAILURE WOULD CAUSE LIMITED ELEVATOR TRAVEL AND LOSS OF ELEVATOR TO STABILIZER CONTROL FOR TR IMMING PURPOSES. BELLCRANK REMOVED FROM SERVICE. 2 L 7 2 4J A2WE 1996102400751 19961024 00751 CE 1996 10 24 96ZZZX5328 1 19960923 G 2150 1179100609 PIVOT PLATE BEECH B300 B300 1159232 CE LT ENG ACCY BOX EAR BROKEN D A K NONE O OTHER IN INSP/MAINT 1 GL 23 550TP 1224 FL35 AIR CONDITIONER COMPRESSOR PIVOT PLATE HAD EAR BROKEN OFF THAT MOUNTS THE COMPRESSOR ONTO THE ENGINE ACCESSORY AREA. TH IS IS THE THIRD SUCH DEFECT FOUND ON THIS PART, ALSO, FOUND COMPRESSOR DRIVE BELT BROKEN AND DRIVE BELT PULLEY DESTROYE D BY OVERHEATED BEARING. BEARING PIN IS 206S22C AND MADE BY (MRC BEARINGS INC.) BEARING ONLY HAD 200 HOURS TOTAL ON IT . SUBMITTER SUGGESTS ALL FAILURES ARE RELATED TO ONE ANOTHER. 2 L 7 2 4T RT A24CE 1996102400752 19961024 00752 CE 1996 10 24 96ZZZX5329 1 19960922 G 3213 508100324 TORQUE KNEE BEECH 90 E90 1152914 CE RT MLG BROKE D A C ABORTED TAKEOFF O OTHER TO TAKEOFF 1 NM 03 5911P 7522 LW70 RT UPPER TORQUE KNEE BROKE AT PIVOT POINT WHERE THE LOWER TORQUE KNEE ATTACHES TO IT. THE PILOT WAS ON TAKEOFF ROLL WHE N HE THOUGHT HE HAD A RT MAIN TIRE BLOW. HE THEN BROUGHT THE ACFT TO A STOP. WHEN THE TORQUE KNEE BROKE, THE TIRE SPUN AROUND AND RIPPED HALF THE TREAD OFF THE TIRE. AIRCRAFT TOTAL LANDINGS, 8,499. 1 L 7 2 3T 3A20 1996102400755 19961024 00755 SW 1996 10 24 96ZZZX5331 1 19960223 G 5320 4715011713 SLEEVE ASSY BELL 47 47G2A 1181012 SW FUSELAGE WELD FAILED B MT1R K NONE O OTHER IN INSP/MAINT 1 EA 07 8522F 4768 7800 BRACKET WELDS EXHIBIT FAILURE AT TOE OF WELD AT SLEEVE. FAILURE OBSERVED VIA FLUORESCENT MAGNETIC PARTICLE INSPECTION. 1 G 7 1 3O 2H3 1996102400756 19961024 00756 SO 1996 10 24 96ZZZX5332 1 19960910 G 5741 404532V NUTS PIPER PA34 PA34200T 7103406 SO LT WING SPAR CRACKED H AY8V K NONE O OTHER IN INSP/MAINT 1 CE 07 68KS 347770252 FOUND 2 NUTS SPLIT ON LT LOWER WING SPAR ATTACH POINT OUTSIDE CABIN. NUTS WERE CRACKED WHEN A/C WAS PAINTED 3 YEARS AGO . PIPER SB 602 COVERS INSPECTION OF THESE NUTS, NO RECORD OF COMPLIANCE. 1 L 7 2 3O A7SO 1996102400757 19961024 00757 1996 10 24 96ZZZX5333 1 19961009 G 6123 D5012 HOUSING FEATHER SPRING CRACKED B ME4D K NONE O OTHER IN INSP/MAINT 1 SO 15 UPON TEAR-DOWN AND INSPECTION OF PROPELLER, FEATHER SPRING HOUSING WAS FOUND CRACKED. PART HAS BEEN SCRAPPED. 1996102400760 19961024 00760 CE 1996 10 24 96ZZZX5336 1 19960826 G 2810 GASKET CESSNA 180 180F 2072614 CE FUEL CAP FAILED C K NONE K FLUID LOSS IN INSP/MAINT 1 GL 21 2125Z 18051225 UMBRELLA-TYPE FUEL CAP GASKET WAS WEATHERED AND CRACKED AROUND RADIUS. ONE CRACK WAS COMPLETELY THROUGH THE GASKET CAUS ING FUEL SYPHONING. SUBMITTER STATED INSPECT GASKET DURING PRE-FLIGHT INSPECTIONS. REPLACE AS NECESSARY. 1 H 7 1 3O 5A6 1996102400761 19961024 00761 SO 1996 10 24 96ZZZX5337 2 19961002 G 8520 CRANKCASE BEECH 33 F33A 1151425 CE CONT O520 IO520BA 17032 SO NR 5 CYL STUD CRACKED D K NONE K FLUID LOSS IN INSP/MAINT 1 SW 05 1096W 417 CE436 S69112 ON 10-2-96 MAINTENANCE WAS NOTIFIED OF AN OIL LEAK ON THE ENGINE. UPON FURTHER INVESTIGATION, A CRACK WAS NOTED ABOVE T HE TOP FORWARD CYLINDER HOLD DOWN STUD OF THE NR 5 CYLINDER. SUSPECT CAUSE OVERTORQUEING OR TORQUEING SEQUENCE. SUBMIM TTER STATED CLOSE INSPECTION OF THESE AREAS WILL PREVENT FURTHER DAMAGE. 1 L 7 1 3O 3 O 3A15 E5CE 1996102400762 19961024 00762 SO 1996 10 24 96ZZZX5338 1 19960715 G 3211 402960 BOLT PIPER PA28 PA28R200 7102811 SO MLG TRUNNION WRONG PART D K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 09 33075 28R7535116 WHILE REPAIRING MLG, ORDERED 2 BOLTS, PIPER PN 402-960 (NAS 464P8A-44) THAT ATTACHES THE MAIN GEAR TRUSS ASSY (452-368) TO THE MLG TRUNNION. WHEN INSTALLED, THESE BOLTS INTERFERE WITH GEAR RETRACTION BECAUSE THE HEX HEAD CONTACTS THE GEAR DOOR RETRACTION ROD. FURTHER INVESTIGATION DISCOVERED THE OLD P/N 400-810 (AN28-50A) AS THE ONLY BOLT THAT WILL WORK DU E TO CLEVIS HEAD BEING A SMALLER DIMENSION THAN THE HEX HEAD NAS BOLT. BOTH PART NUMBERS WERE STILL VALID WITH PIPER. 1 L 7 1 3O 2A13 1996102400763 19961024 00763 CE 1996 10 24 96ZZZX5339 1 19960913 G 3260 SWITCH CESSNA 310 310R 2074245 CE RT MLG WIRE DETACHED D O OTHER P NO WARNING INDICATION AP APPROACH 1 GL 07 3700G 310R0899 (OMA) RT MAIN GEAR HAS NO DOWN AND LOCK INDICATIONS. RT GEAR SWITCH GROUND WIRE PULLED FROM LUG. REPAIRED GROUND WIRE, PERFORMED RETRACTION, CHECK OK. 1 L 7 2 3O 3A10 1996102400764 19961024 00764 SO 1996 10 24 96ZZZX5340 1 19960930 G 3231 DOOR PIPER PA31 PA31350 7103110 SO MLG MALFUNCTIONED D O OTHER O OTHER CL CLIMB 1 GL 07 3547C 318052018 (CMH) GEAR DOORS DID NOT COME UP ON GEAR RETRACTION. CYCLED GEAR WORKED NORMALLY. 1 L 7 2 3O A20SO 1996102400765 19961024 00765 SO 1996 10 24 96ZZZX5341 2 19960907 G 8530 646657A2 CYLINDER CESSNA 210 P210N 2073454 CE CONT O520 TSIO520P 17040 SO NR 5 HEAD SEPARATED G A UNSCHED LANDING E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CR CRUISE 1 GL 03 44C P21000311 513319 DURING CRUISE ENGINE BECAME ROUGH RUNNING. EMERGENCY LANDING WAS MADE. INVESTIGATION REVEALED HEAD SEPARATION OF CYLIN DER. 1 H 7 1 3O 3 O 3A21 E8CE 1996102400767 19961024 00767 GL 1996 10 24 96ZZZX5343 1 19961011 G 3710 EGB03003 FILTER BLANCA 17 1730 1220432 GL VACUUM INLET BLOCKED YOKE H A K NONE F FLT CONT AFFECTED NR NOT REPORTED 1 GL 03 6667V 30018 FILTER PREVENTED YOKE FROM FORWARD MOVEMENT. WHEN FILTER WAS INSTALLED IT WAS NOT HARD MOUNTED. HOSES WERE HOLDING FIL TER. HOSE CLAMP LOOSENED ALLOWING FILTER TO MOVE. HARD MOUNTED FILTER TO AIRCRAFT FRAME USING LOCKNUT AND ADEL CLAMP. REPLACED HOSES. SUBMITTER STATED NO LOCATION FOUND IN AIRCRAFT MANUALS FOR FILTER INSTALL. 1 L 7 1 3O 1A3 1996102400768 19961024 00768 NM 1996 10 24 96ZZZX5344 1 19960918 G 3260 588244 SWITCH PIPER PA60 PA60600 7106001 NM NLG WOW WIRE BROKEN D O OTHER P NO WARNING INDICATION NR NOT REPORTED 1 GL 07 6896B 600919816126 NO GEAR DOWN AND LOCK INDICATION. FOUND BROKEN WIRE ON NOSE GEAR SQUAT SWITCH. REMOVED AND REPLACED SWITCH. OPS CHECK S GOOD. 1 M 7 2 3O RT A17WE 1996102400769 19961024 00769 CE 1996 10 24 96ZZZX5345 1 19961011 G 2841 SK172118A GAUGE ROCHSTRGAUGE C669562019 CESSNA 172 172N 2072434 CE LT FUEL FAILED D K NONE O OTHER IN INSP/MAINT 1 CE 07 739TX 394 17270803 OUT OF BOX FAILURE OF LT FUEL GAUGE. NEED SOME QUALITY CONTROL. ROCHESTER, P/N 6247-00133. 1 H 7 1 3O NT 3A12 1996102400770 19961024 00770 CE 1996 10 24 96ZZZX5346 1 19961011 G 2841 SK172118A GAUGE ROCHSTRGAUGE C669562019 CESSNA 172 172N 2072434 CE LT FUEL FAILED D K NONE O OTHER IN INSP/MAINT 1 CE 07 739TX 398 17270803 THE FUEL GAUGE FAILED OUT OF THE BOX. THE GAUGE FAILED BEFORE INSTALLATION. RECOMMEND BETTER QUALITY CONTROL. ROCHEST ER, P/N 6247-00133. 1 H 7 1 3O NT 3A12 1996102400771 19961024 00771 CE 1996 10 24 96ZZZX5347 1 19961011 G 2841 SK172118A GAUGE ROCHSTRGAUGE C669562019 CESSNA 172 172N 2072434 CE RT FUEL FAILED D K NONE O OTHER IN INSP/MAINT 1 CE 07 739TX 403 17270803 THIRD OUT OF BOX FAILURE FOR THIS TYPE GAUGE IN THREE DIFFERENT FUEL GAUGE KITS. ROCHESTER, P/N 6247-00133. 1 H 7 1 3O NT 3A12 1996102400772 19961024 00772 GL 1996 10 24 96ZZZX5348 3 19961003 G 6111 V84337 BLADE U84337 PIPER PA24 PA24250 7102404 SO HARTZL HC82V HC82V* GL PROPELLER CRACKED B A W59R K NONE O OTHER IN INSP/MAINT 1 WP 07 7662P 665 242875 1556 PROPELLER WAS SUBMITTED FOR OVERHAUL BY OWNER AND FBO DUE TO AGE. PROPELLER HAD BEEN OVERHAULED 5 YEARS AGO AND 665.26 H RS AND THE OWNER AND MECHANICS FELT AN INSP WAS IN ORDER. UPON DISASSEMBLY AND INSPECTION OF BLADE SHANKS PER AD 68-19- 04, THE SHANKS WERE FOUND CRACKED IN RADII REFERENCED IN AD AND IN SERVICE DOCUMENTS LISTED IN AD. EDDY CURRENT INSP CO NFIRMED PENETRANT INSP RESULTS. SUBMITTER'S OPINION THAT HAD THE OWNER DECIDED TO FLY UNTIL REACHING THE HOUR LIMIT OF 1000 HRS ALLOWED BY AD 68-19-04, ONE OR MORE OF THE BLADES WOULD HAVE SEPARATED, AS THE SHANKS ARE CRACKED APPROX ONE-HA LF THE CIRCUMFERENCE OF THE SHANK. 1 L 7 1 3O 1A15 5 C P23EA 1996102400773 19961024 00773 GL 1996 10 24 96ZZZX5349 3 19961003 G 6111 V84337 BLADE U84337 PIPER PA24 PA24250 7102404 SO HARTZL HC82V HC82V* GL PROPELLER CRACKED B A W59R K NONE O OTHER IN INSP/MAINT 1 WP 07 7662P 665 242875 1556 PROPELLER WAS SUBMITTED FOR OVERHAUL BY OWNER AND FBO DUE TO AGE. PROPELLER HAD BEEN OVERHAULED 5 YEARS AGO AND 665.26 H RS AND THE OWNER AND MECHANICS FELT AN INSP WAS IN ORDER. UPON DISASSEMBLY AND INSPECTION OF BLADE SHANKS PER AD 68-19- 04, THE SHANKS WERE FOUND CRACKED IN RADII REFERENCED IN AD AND IN SERVICE DOCUMENTS LISTED IN AD. EDDY CURRENT INSP CO NFIRMED PENETRANT INSP RESULTS. SUBMITTER'S OPINION THAT HAD THE OWNER DECIDED TO FLY UNTIL REACHING THE HOUR LIMIT OF 1000 HRS ALLOWED BY AD 68-19-04, ONE OR MORE OF THE BLADES WOULD HAVE SEPARATED, AS THE SHANKS ARE CRACKED APPROX ONE-HA LF THE CIRCUMFERENCE OF THE SHANK. 1 L 7 1 3O 1A15 5 C P23EA 1996102400774 19961024 00774 SW 1996 10 24 96ZZZX5350 1 19961003 G 2752 240014025 BRACKET MOONEY M20 M20C 5870208 SW FLAP ACTUATOR CORRODED D A K NONE O OTHER IN INSP/MAINT 1 SW 11 7150V 4345 200037 INSPECTION FOUND BOTH FLAP ACTUATOR BRACKETS WITH INNER GRANULAR CORROSION. 1 L 7 1 3O 2A3 1996102400775 19961024 00775 SW 1996 10 24 96ZZZX5351 1 19961003 G 2752 240014026 BRACKET MOONEY M20 M20C 5870208 SW FLAP ACTUATOR CORRODED D K NONE O OTHER IN INSP/MAINT 1 SW 11 7150V 4345 200037 INSPECTION FOUND BOTH FLAP ACTUATOR BRACKETS WITH INNER GRANULAR CORROSION. 1 L 7 1 3O 2A3 1998042300054 19980423 00054 WP 1998 4 23 96ZZZX5352 2 19960905 G 7230 BLADE LEAR 35 35LEAR 5170600 CE GARRTT TFE731 TFE73122B 01518 WP RT ENGINE FOD H O OTHER C F.O.D. TO TAKEOFF 1 GL 07 130F 044 874216 RT ENGINE BIRD FOD ON TAKEOFF. BENT 7-8 FAN BLADES. HAD GARRETT IN LONG ISLAND REMOVE AND REPLACE BLADES AND C/W BALAN CE. 2 L 7 2 4F 4 F A10CE E6WE 1998042300056 19980423 00056 NM 1998 4 23 96ZZZX5354 1 19960920 G 5320 FLANGE BOEING 727 72722C 138400F NM FS 940 RT CRACKED B XE4R K NONE O OTHER IN INSP/MAINT 1 SO 19 427EX 19090 INSPECTION FOUND 1.50 INCH CRACK AT BS 940, RT SIDE FWD FLANGE. FLOOR LEVEL. SUSPECT CAUSE FATIGUE. 2 L 7 3 4F A3WE 1998042300057 19980423 00057 NM 1998 4 23 96ZZZX5355 1 19960918 G 5320 INTEGRAL RIB BOEING 727 72722C 138400F NM FS 950 LT CRACKED B XE4R K NONE O OTHER IN INSP/MAINT 1 SO 19 427EX 19090 INSPECTION FOUND 3 INCH CRACK AT BS 950 LT/INTEGRAL RIB, STR 13L. SUSPECT CAUSE: FATIGUE. 2 L 7 3 4F A3WE 1998042300058 19980423 00058 NM 1998 4 23 96ZZZX5356 1 19960918 G 5320 INTEGRAL RIB BOEING 727 72722C 138400F NM FS 870 RT CRACKED B XE4R K NONE O OTHER IN INSP/MAINT 1 SO 19 427EX 19090 INSPECTION FOUND 1.50 INCH CRACK AT BS 870 RT, INTEGRAL RIB STR 13R. SUSPECT CAUSE: FATIGUE. 2 L 7 3 4F A3WE 1998042300059 19980423 00059 NM 1998 4 23 96ZZZX5357 1 19960920 G 5320 FLANGE BOEING 727 72722C 138400F NM FS 940 LT CRACKED B XE4R K NONE O OTHER IN INSP/MAINT 1 SO 19 427EX 19090 INSPECTION FOUND .50 INCH CRACK AT BS 940 LT SIDE AFT FLANGE AT FLOOR BEAM LEVEL. SUSPECT CAUSE: FATIGUE. 2 L 7 3 4F A3WE 1998042300060 19980423 00060 SW 1998 4 23 96ZZZX5358 1 19961002 G 5541 5533110148 RIB GULSTM 560 560 0141402 SW RUD INTERSPAR CRACKED B PAZR K NONE O OTHER IN INSP/MAINT 1 CE 03 560GL 1658 5600079 DURING PHASE INSPECTION, FOUND RUDDER TO HAVE UNUSUAL NOISE WHEN MOVED. NO EXTERNAL DEFECTS NOTED. INSPECTED WITH BORE SCOPE AND FOUND RIB WITH APPROXIMATELY 2.3750 INCH CRACK ORIGINATING AT FORWARD LIGHTENING HOLE. NEW RIB INSTALLED AND RUDDER BALANCED. 1 H 7 2 3O 6A1 1998042300061 19980423 00061 NE 1998 4 23 96ZZZX5359 2 19960913 G 7310 AN62353A FILTER BEECH 300 300BEECH 1152930 CE PWA PT6 PT6A60A 52043 NE FUEL DISCHARGE MISINSTALLED H L K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 17 79TE 2 FA67 PCE95140 FILTER PACKING WAS INSTALLED AT 150-HOUR NR 2 INTERIM INSP. O-RING HAD BEEN ROLLED DURING INSTALLATION 1.8 HRS. TOO SM ALL OF SAFETY WIRE USED ON RT ENGINE ON FUEL FILTER BOWL ALSO. 2 L 7 2 4T 4 T A24CE E4EA 1998042300062 19980423 00062 NM 1998 4 23 96ZZZX5360 1 19960903 G 2751 S508315 SUPPORT BOEING 707 707* NM AILERON CRACKED H K NONE O OTHER IN INSP/MAINT 1 SO 19 19295 WHILE REPLACING L/E WEBS IN HINGE AREA, NOTED FITTING (SUPPORT WAS CRACKED IN AREAS OF FASTENER HOLES. POSSIBLE CAUSE, SHOOTING 'D' RIVETS IN MAGNESIUM SUPPORT. RECOMMEND USING 'B' RIVETS. 2 L 7 4 4J RT 4A21 1998042300063 19980423 00063 NM 1998 4 23 96ZZZX5361 1 19960920 G 2620 HOSE ISRAEL 1125 1125 NM APU FIRE EXT BLOCKED B L A JGVR K NONE W INADEQUATE Q C IN INSP/MAINT 1 CE 09 THE BLOCKAGE WAS DISCOVERED DURING THE MODIFICATION PROCESS. THE TECHNICIAN HAD CUT THE HOSE ON A BAND SAW, INSTALLED T HE SOCKET PORTION OF THE FITTING AND STARTED TO INSTALL THE B-NUT, ONLY 1 OR 2 TURNS. TECH DECIDED TO CHAMFER INSIDE OF HOSE TO ALLOW EASIER INSTALLATION OF FITTING. TECH REMOVED FITTNG AND INSERTED A SMALL ROUND FILE INTO OPEN END OF HOS E. THE FILE WOULD NOT PASS THROUGH THE HOSE. AT THIS TIME, NOTED THE INNER HOSE HAD RETRACTED ABOUT .50 INCH FROM THI S CUT-OFF. THE HOSE WAS CUT LENGTHWISE TO EXPOSE THE BLOCKAGE. IT APPEARS THE INNER HOSE WAS TWISTED 90-DEGREES DURING MFG PROCESS CAUSING IT TO KINK AND CLOSE INTERNALLY. 2 L 7 2 4F RT A16NM 1998042300064 19980423 00064 GL 1998 4 23 96ZZZX5362 2 19960516 G 7250 6870832 COUPLING ALLSN 250C 250C20 03013 GL POWER TURBINE DAMAGED SPLINES D L K NONE O OTHER IN INSP/MAINT 1 EA 17 26903 THE DEFECT WAS DISCOVERED DURING INSPECTION OF THE PART ON RECEIPT FROM A 3RD PARTY VENDOR. THE ALLISON GAS TURBINE 250 -C20 SERIES OVERHAUL MANUAL PROVIDES IN TABLE VI-19 INSPECTION CRITERIA FOR POWER TURBINE COUPLINGS. ITEM 58 OF THIS TA BLE, ON PAGE 6-119 ALLOWS NO DAMAGE SUCH AS 'NICK, CHIPS, GROOVES' IN THE SPLINE TEETH. THE DAMAGED TOOTH CLEARLY RENDE RS THIS SHAFT UNSERVICEABLE. 3 U E4CE 1998042300065 19980423 00065 GL 1998 4 23 96ZZZX5363 2 19960516 G 7250 23037403 INNER SHAFT ALLSN 250C 250C20B 03013 GL POWER TURBINE PITTED D L K NONE O OTHER IN INSP/MAINT 1 EA 17 74872 THE DEFECT DESCRIBED BELOW WAS DISCOVERED DURING INSPECTION OF THE PART ON RECEIPT FROM A 3RD PARTY VENDOR. THE ALLISON GAS TURBINE 250-C20 SERIES OVERHAUL MANUAL, TABLE VI-19, PAGE 6-114, PROVIDES INSPECTION CRITERIA FOR POWER TURBINE INN ER SHAFTS. ITEM 27A PROVIDES THE BEARING RACE PITTING SERVICEABLE LIMITS. 'NO PIT LARGER THAN 0.006 INCH WHICH CAN DEF INITELY BE FELT WITH A 0.030 INCH RADIUS SCRIBER' IS ALLOWED. SEVERAL PITS CAN BE DETECTED WITH A 0.030 INCH SCRIBER, T HEREFORE, THIS SHAFT IS NOT SERVICEABLE. 3 U E4CE 1998042300066 19980423 00066 CE 1998 4 23 96ZZZX5364 1 19960925 G 3211 9012006092 SUPPORT 901200602 BEECH 90 C90A 1152911 CE RT MLG OTBD CRACKED B S A DYTR K NONE O OTHER IN INSP/MAINT 1 SO 15 301ER 2833 LJ1286 DURING A ROUTINE PHASE INSPECTION, RT MLG RETRACT CLYINDER SUPPORT BRACKETS (ONE INBOARD, ONE OUTBOARD) WERE FOUND CRACK ED 50 PERCENT OF THEIR LENGTH. DURING LANDING GEAR RETRACT TEST ON JACKS, CRACKS WERE OBSERVED OPENING WIDE. AIRCRAFT SENT TO DEALERSHIP MAINTENANCE SHOP FOR REPAIR. 1 L 7 2 3T RT 3A20 1998042300067 19980423 00067 CE 1998 4 23 96ZZZX5365 1 19960925 G 3211 9012006094 SUPPORT 901200602 BEECH 90 C90A 1152911 CE RT MLG INBD CRACKED B A DYTR K NONE O OTHER IN INSP/MAINT 1 SO 15 301ER 2833 LJ1286 DURING A ROUTINE PHASE INSPECTION, RT MLG RETRACT CLYINDER SUPPORT BRACKETS (ONE INBOARD, ONE OUTBOARD) WERE FOUND CRACK ED 50 PERCENT OF THEIR LENGTH. DURING LANDING GEAR RETRACT TEST ON JACKS, CRACKS WERE OBSERVED OPENING WIDE. AIRCRAFT SENT TO DEALERSHIP MAINTENANCE SHOP FOR REPAIR. 1 L 7 2 3T RT 3A20 1998042300068 19980423 00068 CE 1998 4 23 96ZZZX5366 1 19961004 G 5210 1313232C15 PIN 1014300301 BEECH 200 200BEECH 1152920 CE CABIN DOOR HOOK BROKEN D K NONE O OTHER IN INSP/MAINT 1 WP 15 113GW 5802 BB541 MAINTENANCE FOUND FORWARD CABIN DOOR HOOK-PIN MOVING. DISASSEMBLED, PIN WORN ABOUT HALF WAY INTO AND BROKEN IN HALF, FA ILED. SUBMITTER SUGGESTS CAUSE MAY BE POOR LUBRICATION OR NOT DONE AT PROPER INTERVALS, AND NEEDS TO BE INSPECTED AT PR OPER HOURS. 1 L 7 2 4T A24CE 1996110100367 19961101 00367 CE 1996 11 1 96ZZZX5400 1 19961007 G 2810 10132006121 VALVE BEECH 200 200BEECH 1152920 CE FUEL ANTISIPHON DAMAGED B A HBKR K NONE O OTHER IN INSP/MAINT 1 SW 11 6HU BB319 DURING INSP BOTH ANTI-SIPHON VALVES AT THE LT AND RT FUEL FILLER PORTS WERE FOUND DAMAGED. FLAPPER-TYPE VALVES ARE INTE NDED TO PREVENT FUEL LOSS AND FUEL CELL DAMAGE IF THE FUEL CAPS ARE LEFT OFF PRIOR OR LEAK DURING FLIGHT. DIFFICULT TO INSERT STANDARD SIZE JET FUEL NOZZLE INTO THE CELL WITHOUT DAMAGING THE ANTI-SIPHON VALVE. THE NOZZLE MUST BE INSERTED AT AN ANGLE AND WEDGED INTO THE VALVE ASSEMBLY TO PREVENT FUEL FROM SPRAYING BACK ON THE FUELLER. THE VALVES SOON BECOM E DAMAGED TO THE POINT THEY NO LONGER SEAL AFTER THE NOZZLE HAS BEEN REMOVED. SUBMITTER STATED MUST INSTALL NEW VALVES AT NEARLY EVERY KING-AIR 200 INSPECTION. 1 L 7 2 4T A24CE 1996110100368 19961101 00368 SO 1996 11 1 96ZZZX5401 1 19960901 G 7197 WIRE PIPER PA31T PA31T 7103124 SO ENGINE COMP SHORTED B XZJR K NONE M OVER TEMP IN INSP/MAINT 1 SO 17 737WB 31T7620052 WIRES IN THE ENGINE COMPARTMENTS RUNNING BY EXHAUST DUCTS ARE MELTING AND SHORTING OUT DUE TO LONG TERM EXPOSURE TO HEAT . SUBMITTER RECOMMENDS INSULATED WIRES WITH FIRE SLEEVE BE INSTALLED TO PREVENT RECURRENCE. 1 L 7 2 3T A8EA 1996110100369 19961101 00369 SO 1996 11 1 96ZZZX5402 1 19961001 G 5280 6709304 DOOR ASSY PIPER PA32 PA32R301 7103218 SO LT MLG DOOR CRACKED D A K NONE O OTHER IN INSP/MAINT 1 EA 07 226DT 3246006 LEFT MLG DOOR CRACKED JUST ABOVE ROD END ATTACH POINT. EXCESSIVE VIBRATION FROM SLIP STREAM, SUSPECT CAUSE OF THE CRACK . NOTE: SUBMITTER STATED THIS DEFECT HAS BEEN OBSERVED BEFORE. RECOMMEND REINFORCING AFFECTED AREAS OF THE DOOR OR RE PLACE WITH AN ALUMINUM DOOR. PART TOTAL TIME IN SERVICE 187.2 HOURS. 1 L 7 1 3O A3SO 1996110100370 19961101 00370 GL 1996 11 1 96ZZZX5403 3 19960901 G 6111 517 BLADE PIPER PA32 PA32300 7103212 SO HARTZL HCC2Y HCC2YR1 GL PROPELLER TIP LOST D O OTHER E VIBRATION/BUFFET AP APPROACH 1 SW 99 32139 517 327540017 CH20126 LOST APPROXIMATELY 6.5 INCHES OF PROPELLER TIP JUST PRIOR TO LANDING AFTER A 30-MINUTE FLIGHT. NO OTHER DAMAGE FOUND TO AIRCRAFT AFTER COMPLETE INSPECTION. 1 L 7 1 3O A3SO 5 C P920 1996110100371 19961101 00371 SO 1996 11 1 96ZZZX5404 2 19961009 G 8520 643207 CRANKCASE CESSNA 414 414A 2075907 CE CONT O520 TSIO520NB 17040 SO NR 2 MAIN CRACKED H K NONE O OTHER IN INSP/MAINT 1 WP 17 37U 1379 414A0010 276971R AFTER REMOVAL OF CYLINDER NR 4 DUE TO A LEAKING EXHAUST VALVE, A 4 INCH CRACK WAS FOUND STARTING AT THE NR 2 MAIN JOURNA L. THIS CRACK STARTED AT THE BEARING SURFACE AND PROGRESSED TO THE INSIDE OF THE CASE BETWEEN CYLINDERS NR 2 AND 4. NO EVIDENCE OF A CRACK WAS FOUND ON THE OUTSIDE OF THE CASE. SUBMITTER STATED THIS IS THE 3RD CRACK FOUND IN THIS AREA ON 3 DIFFERENT ENGINES. 1 L 7 2 3O 3 O A7CE E8CE 1996110100372 19961101 00372 CE 1996 11 1 96ZZZX5405 1 19961016 G 7160 165201338 DUCT ADAPTER CESSNA 182 182Q 2072732 CE ALTERNATE AIR DOOR BROKEN B A P3NR K NONE O OTHER IN INSP/MAINT 1 EA 13 5144N 587 18267543 DURING AN INVESTIGATION FOR DAMAGE FROM AN INTAKE FIRE, THE ALTERNATE AIR DOOR WAS FOUND BROKEN LOOSE FROM THE FIBERGLAS S AIR DUCT. THIS AIRCRAFT HAS BEEN MODIFIED IAW A PETERSON 260 SE/STOL CONVERSION. THIS DOOR COULD BLOCK THE AIR FLOW TO THE INTAKE SYSTEM. SUBMITTER RECOMMENDS PERIODIC INSPECTION OF THE ALTERNATE AIR DOOR MOUNTING SECURITY. ALSO, RECO MMEND A DRAIN SYSTEM TO PREVENT FIRE HAZARD DURING STARTING. 1 H 7 1 3O NT 3A13 1996110100374 19961101 00374 CE 1996 11 1 96ZZZX5407 1 19960927 G 3244 800X6X6 TIRE MCCREARY CESSNA 172 172M 2072418 CE LT MLG RUBS CALIPER E K NONE O OTHER IN INSP/MAINT 1 SW 11 20109 17261017 BRAKE CALIPER DRAGS WHEN TIRE INSTALLED ON AIRCRAFT. MEASURED LEFT AND RIGHT HAND TIRE SIDEWALL WHEN PRESSURED TO 28 PS I. LEFT TIRE SIDEWALL 1.25 INCH WIDER THAN RIGHT TIRE. 1 H 7 1 3O NT 3A12 1996110100375 19961101 00375 CE 1996 11 1 96ZZZX5408 1 19961004 G 3211 2411001 PIVOT ASSY CESSNA 172 172RG 2072438 CE LT MLG SHAFT SHEARED H A OQDV O OTHER P NO WARNING INDICATION AP APPROACH 1 CE 07 5204U 6790 172RG0282 LEFT MAIN GEAR WOULD NOT INDICATE DOWN AND LOCK WHEN THE GEAR WAS SELECTED DOWN. THE PILOT LANDED WITH GEAR UP. THE LT MAIN GEAR ASSY WAS REMOVED FROM THE AIRCRAFT AND IT WAS DISCOVERED THE PIVOT SHAFT OF THE PIVOT ASSY HAD SHEARED FROM T HE MAIN BODY OF THE PIVOT ASSY. 1 H 7 1 3O 3A17 1996110100376 19961101 00376 EA 1996 11 1 96ZZZX5409 2 19961006 G 8520 LW11750 CONNECT ROD PIPER PA23 PA23250 7102308 SO LYC O540 IO540J4A5 41532 EA NR 6 CYL FAILED D K NONE O OTHER NR NOT REPORTED 1 NM 03 6730Y 991 274062 L647748 ROD FOR CYLINDER NR 6 FAILED AT CRANKSHAFT END. UNABLE TO TELL IF ROD OR ROD BOLTS FAILED BECAUSE OF DAMAGE. 1 L 7 2 3O 3 O 1A10 1E4 1996110100377 19961101 00377 GL 1996 11 1 96ZZZX5410 3 19961009 G 6114 D32512 HUB PIPER PA44 PA44180T 7104404 SO HARTZL HCC3Y HCC3YR GL PROPELLER CORRODED D K NONE O OTHER IN INSP/MAINT 1 NM 03 838PC 2000 448107056 CK2593 AFTER CLEANING OF HUB AND NDT, HUB WAS CORRODED BADLY ON THE INSIDE OF THE HUB ONLY. THE CAUSE OF THIS IS THE USE OF NO N-APPROVED AUTO GREASE. SUBMITTER STATED IF THIS WAS NOT FOUND, IT IS POSSIBLE A CRACK AND FAILURE OF THE HUB WOULD OCC UR. 1 L 7 2 3O A19SO 5 C P25EA 1996110100379 19961101 00379 CE 1996 11 1 96ZZZX5412 1 19961001 G 5320 STRUCTURE CESSNA 414 414A 2075907 CE NOSE WHEELWELL CORRODED D S A K NONE O OTHER IN INSP/MAINT 1 CE 09 414JK 414A0626 CORROSION FOUND AROUND THE HOLES (WHEELWELL-NOSE) AREA WHERE THE BLACK HEAT DUCT TUBING THAT RUNS THROUGH STRUCTURE MAKE S CONTACT WITH THE ALUMINUM. FOUND THIS ON A 1981 CESSNA 414A WITH A TOTAL TIME OF 4900 HRS AND ALSO 1981 CESSNA 425 W ITH 6203 HRS. 1 L 7 2 3O A7CE 1996110100380 19961101 00380 CE 1996 11 1 96ZZZX5413 1 19961004 G 3230 51001116 NITROGEN LINE CESSNA 414 414A 2075907 CE BLOW DOWN BOTTLE RUPTURED D A K NONE O OTHER IN INSP/MAINT 1 CE 09 414JK 4900 414A0626 FOUND CORROSION ON THE NITROGEN LINE FROM THE EMERGENCY GEAR BLOW DOWN BOTTLE WHERE IT WAS IN CONTACT WITH BLACK HEAT DU CT. THERE WAS NO CORROSION FOUND ON THE LINE EXCEPT WHERE IT MADE CONTACT WITH THE HEAT DUCT. WHEN THE EMERGENCY GEAR DOWN BOTTLE ACTIVATED, THIS NITROGEN LINE RUPTURED AT THE CORRODED AREA. THIS WAS ON A 1981 CESSNA 414A WITH TOTAL TIME OF 4900 HRS. 1 L 7 2 3O A7CE 1996110100381 19961101 00381 NE 1996 11 1 96ZZZX5414 2 19960906 G 7322 2523973 SPOOL BEARING BENDIX 430124803 LYC LTS101 LTS101750B2 41560 NE FUEL CONTROL NOT LUBED B A ESER K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 11 86010299 USCG FUEL CONTROL RECEIVED FROM BENDIX WEST COAST AS ZERO HOURS TSO REQUIRED UPGRADE IAW GT 264 AND GT 279. IN THE PROC ESS OF DISASSEMBLY DISCOVERED THE BLUE GREASE RESERVOIR IN THE SPOOL BEARING CAP HAD NEVER BEEN FILLED. THIS CONDITION HAS BEEN CITIED IN THE PAST AS BEING A CAUSE OF SPOOL BEARING FAILURE. 3 U E5NE 1996110100382 19961101 00382 CE 1996 11 1 96ZZZX5415 1 19960830 G 3213 6041100018 MAIN GEAR LEAR 60 60LEAR 5170707 CE RT MLG MALFUNCTION D A O OTHER O OTHER CL CLIMB 1 SW 05 63BL 532 014 051 LANDING GEAR OVER EXTENDED, CONTACTED MAIN FUEL LINES IN WHEELWELL WHICH PREVENTED COMPLETE RETRACTION. THIS CAUSED THE STRUT TO DEFLATE ALONG WITH LOSS OF FLUID WHICH, IN TURN, CAUSED A COLLAPSED STRUT ON LANDING. IT WAS ALSO NOTED THAT THE MAIN FUEL LINE WAS CROSSED LT RT, RT LT. REMOVED AND REPLACED GEAR AND FUEL LINES. 2 L 7 2 4F RT A10CE 1996110100525 19961101 00525 EU 1996 11 1 96ZZZX5417 1 19960913 G 2720 F10A755401 LINE AMD FALC10 FALCON10 2730101 EU V STAB RUD SERVO PIN HOLE B L GFER K NONE K FLUID LOSS IN INSP/MAINT 1 NM 09 163AV 5033 163 UPON LANDING, THE FLT CREW NOTICED HYD FLUID IN THE AREA OF THE VERT STAB. INVEST REVEALED THE RUD SERVO HYD RETURN LINE HAD BEEN CHAFED BY THE BRAIDED STEEL RUD SERVO LINE PN 000AE90-4-0232 WHERE A PIN HOLE HAD DEVELOPED. LINE WAS REPLACE D AND PROTECTED WITH A STRIP OF 'SPIRAL WRAP', ALSO, THE FLEX LINE WAS FOUND TO HAVE A SLIGHT TWIST FROM INSTALLATION WH ICH ALLOWED THE LINE TO RUB HARD IN CERTAIN RUD POSITIONS, THIS DEFECT WAS FIXED. THE PIN HOLE DEVELOPED IN AN AREA NOT ACCESSIBLE TO VISUAL INSP EVEN WITH THE LEAD EDGE OF THE V STAB ACCESS PANEL REMOVED. REF ALSO FALCON 10 IPC 27-23-05 PG 1-0, ITEMS 144 AND 140. 2 L 7 2 4F A33EU 1996110100526 19961101 00526 NM 1996 11 1 96ZZZX5418 1 19961012 G 5711 SPAR CAP UNIVAR 415 415C 0420302 NM RT WING CORRODED D K NONE O OTHER IN INSP/MAINT 1 SW 01 2576H 1938 3201 UPON PREPPING WINGS FOR RE-COVER, EXFOLIATION DISCOVERED IN STBD WING MAIN SPAR CAP UPPER. SEVERAL LAYERS OF VARIOUS TY PES OF TAPE HID THE CORROSION UNTIL REMOVED FOR INSPECTION. EXFOLIATION RUNS FULL LENGTH OF SPAR CAP, VARYING IN DEPTH TO .0625 INCH. 1 L 7 1 3O A718 1996110100527 19961101 00527 EU 1996 11 1 96ZZZX5419 1 19961009 G 3020 5302412082 DEICE LIP PILATS PC12 PC12 7090550 EU DEICE LIP COWL BROKEN JOINTS B LF1R K NONE O OTHER IN INSP/MAINT 1 EA 07 121RF 357 114 DISCOLORATION AND EXHAUST STREAKS LED TO FURTHER INVESTIGATION OF THE DE-ICE LIP ASSEMBLY. INVESTIGATION REVEALED BROKE N SLIP JOINTS AT THE DE-ICE LIP JOINT, LT SIDE. SUBMITTER STATES IMMEDIATE INSPECTION RECOMMENDED ON ALL PC12'S. 1 L 7 1 3T RT A78EU 1996110100528 19961101 00528 EU 1996 11 1 96ZZZX5420 1 19961008 G 5220 5222012036 EMERGENCY EXIT PILATS PC12 PC12 7090550 EU CABIN SEAL LEAKS B LF1R K NONE O OTHER IN INSP/MAINT 1 EA 07 121RF 357 114 INVESTIGATION OF MOISTURE REPORT REVEALED THAT ALL INSULATION FROM THE EMERGENCY EXIT TO THE AFT PRESSURE BULKHEAD IN TH E BELLY OF THE AIRCRAFT WAS DETERIORATED AND SOAKED IN WATER. LEAKY EMERGENCY EXIT, FAULTY SEALING SUSPECTED. SUBMITTE R STATED INSPECTION RECOMMENDED. PILATUS ACFT ADVISED. 1 L 7 1 3T RT A78EU 1996110100529 19961101 00529 EU 1996 11 1 96ZZZX5421 1 19961008 G 5220 5522012036 EMERGENCY EXIT PILATS PC12 PC12 7090550 EU CABIN SEAL LEAKS B LF1R K NONE O OTHER IN INSP/MAINT 1 EA 07 124BW 207 124 124 INVESTIGATION OF MOISTURE REPORT REVEALED ALL INSULATION FROM EMERGENCY EXIT TO AFT PRESSURE BULKHEAD DETERIORATED AND S OAKING IN WATER. SUBMITTER STATED IMMEDIATE INSPECTION RECOMMENDED; FAULTY SEAL. 1 L 7 1 3T RT A78EU 1996110100530 19961101 00530 SO 1996 11 1 96ZZZX5422 2 19961017 G 8520 CRANKCASE ARONCA 15 15AC 0191202 EA CONT O300 O300* 17022 SO ENGINE FAILURE G O OTHER E R K VIBRATION/BUFFET PARTIAL RPM/PWR LOSS FLUID LOSS NR NOT REPORTED 1 AL 03 1132H 15AC145 PUSH ROD FAILURE RESULTED IN ENGINE STOPPING AND SUBSEQUENT CRANKCASE FAILURE. (ROD THROUGH CASE.) SUBMITTER SUSPECTS OIL PUMP FAILURE, ENGINE OVERHEAT. 1 H 7 1 3O 3 O A802 E253 1996110100531 19961101 00531 CE 1996 11 1 96ZZZX5423 1 19961016 G 3246 201302591 WHEEL CESSNA 182 182P 2075816 CE RT MLG CRACKED D K NONE O OTHER IN INSP/MAINT 1 GL 15 1307S 3887 18264872 DURING TIRE CHANGE ON RT MAIN, 3 CRACKS FOUND AT VARIOUS BOLT HOLES IN THE CENTER WHEEL BODY SECTION OF THE 3-PIECE WHEE L ASSY. POSSIBLE CAUSES INCLUDE OVERTORQUING DURING INSTALLATION COMBINED WITH HARD LANDINGS. THIS SHOP EXPECTS TO SEE 1 TO 2 CRACKED WHEEL BODIES A YEAR AND INSPECTS THESE WHEEL SECTIONS CAREFULLY DURING WHEEL/TIRE MAINTENANCE. SUBMITTE R RECOMMENDS CAREFUL ADHERENCE TO PROPER WHEEL ASSY TORQUES UPON INSTALLATION OF TIRES. ALSO SUGGEST THE APPROVAL OF A 2-PIECE RATHER THAN A 3-PIECE WHEEL ASSY FOR THIS INSTALLATION. 1 H 7 1 3O NT TA13 1996110100532 19961101 00532 EA 1996 11 1 96ZZZX5424 2 19961017 G 8530 73806 PUSH ROD CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA NR 1 CYL EXH CHAFED D K NONE O OTHER IN INSP/MAINT 1 NE 01 25813 6000 15280797 L1416215 UNDER NORMAL OPERATING CONDITIONS, REMOVED NR 1 CYLINDER EXHAUST SIDE PUSH ROD AND NOTICED SHINEY CHAFE MARK. THE CAUSE IS UNKNOWN. THERE WAS NO DENT IN THE PUSH ROD TUBE. SUBMITTER STATED THIS IS THE THIRD OCCURRENCE ON THE O-235 ENGINE AT THE NR 1 CYLINDER LOCATION. 1 H 7 1 3O 3 O NT 3A19 E223 1996110100533 19961101 00533 CE 1996 11 1 96ZZZX5425 1 19960907 G 5312 05121083 BULKHEAD CESSNA 170 170B 2072306 CE FS 228.687 CRACKED D K NONE O OTHER IN INSP/MAINT 1 AL 03 2269D 3050 20421 REAR BULKHEAD WAS FOUND CRACKED AT THE TAIL WHEEL MOUNTING SHEAR BRACKET. THE SKIN ON BOTH SIDES OF THE TAIL WHEEL MOUN TING BRACKET WERE FOUND CRACKED UPON DISASSEMBLY WITH CORROSION BETWEEN THE BRACKET AND SKIN. SUSPECT CAUSE WAS THE WEA RING OF THE SKIN BY THE CORROSION. THE OLD STYLE TAIL WHEEL BRACKET IS STEEL, THE NEW ONE IS ALUMINUM. THIS SHOULD PRE VENT THE DISSIMILAR METAL CORROSION WHICH MAY HAVE CAUSED THE PROBLEM. NOTE: THE PART WAS 44 YEARS OLD. 1 H 7 1 3O A799 1996110100534 19961101 00534 CE 1996 11 1 96ZZZX5426 1 19960907 G 5330 051200080 SKIN CESSNA 170 170B 2072306 CE FS 205-228 CRACKED D K NONE O OTHER IN INSP/MAINT 1 AL 03 2269D 3050 20421 REAR BULKHEAD WAS FOUND CRACKED AT THE TAIL WHEEL MOUNTING SHEAR BRACKET. THE SKIN ON BOTH SIDES OF THE TAIL WHEEL MOUN TING BRACKET WERE FOUND CRACKED UPON DISASSEMBLY WITH CORROSION BETWEEN THE BRACKET AND SKIN. SUSPECT CAUSE WAS THE WEA RING OF THE SKIN BY THE CORROSION. THE OLD STYLE TAIL WHEEL BRACKET IS STEEL, THE NEW ONE IS ALUMINUM. THIS SHOULD PRE VENT THE DISSIMILAR METAL CORROSION WHICH MAY HAVE CAUSED THE PROBLEM. NOTE: THE PART WAS 44 YEARS OLD. 1 H 7 1 3O A799 1996110100535 19961101 00535 CE 1996 11 1 96ZZZX5427 1 19961001 G 8011 639153 DRIVE MZ4214 CESSNA 150 150M 2071830 CE STARTER CLUTCH SEIZED D K NONE O OTHER NR NOT REPORTED 1 EA 17 9440U 15078388 STARTER CLUTCH WAS FOUND LOCKED UP SOLID CAUSING STARTER TO ROTATE ALL THE TIME THE ENGINE WAS RUNNING. 1 H 7 1 3O 3A19 1996110100536 19961101 00536 CE 1996 11 1 96ZZZX5428 1 19961010 G 5310 TRUSS BEECH 35 35BEECH 1151502 CE LT FWD UPPER WELD CRACKED B L QISR K NONE O OTHER IN INSP/MAINT 1 EA 23 3079V D494 A CRACKED WELD WAS DISCOVERED ON THE PORT SIDE UPPER WELD JOINT OF THE FORWARD TRUSS AND A CRACKED WELD ON THE LOWER STA RBOARD REAR TRUSS CLIP. SUBMITTER STATED THIS AIRCRAFT IS OUT-OF-SERVICE AND HAS BEEN FOR APPROXIMATELY 15 YEARS. OWNE R IS INTERESTED IN RESTORING THIS AIRCRAFT. INSPECTION WAS PERFORMED AS REQUIRED BY SB NR 24 AND AD 63-25-01. 1 L 7 1 3O A777 1996110100537 19961101 00537 CE 1996 11 1 96ZZZX5429 1 19961010 G 5310 TRUSS CLIP BEECH 35 35BEECH 1151502 CE RT AFT CLIP WELD CRACKED B QISR K NONE O OTHER IN INSP/MAINT 1 EA 23 3079V D494 A CRACKED WELD WAS DISCOVERED ON THE PORT SIDE UPPER WELD JOINT OF THE FORWARD TRUSS AND A CRACKED WELD ON THE LOWER STA RBOARD REAR TRUSS CLIP. SUBMITTER STATED THIS AIRCRAFT IS OUT-OF-SERVICE AND HAS BEEN FOR APPROXIMATELY 15 YEARS. OWNE R IS INTERESTED IN RESTORING THIS AIRCRAFT. INSPECTION WAS PERFORMED AS REQUIRED BY SB NR 24 AND AD 63-25-01. 1 L 7 1 3O A777 1996110100538 19961101 00538 1996 11 1 96ZZZX5430 4 19961008 G 6122 CONTROL ARM V54 PIPER PA32 PA32R301 7103218 SO PROP GOVERNOR CHAFE BAFFLE B LF1R K NONE O OTHER IN INSP/MAINT 1 EA 07 32WF 127 A952JPC10 3246026 CONTROL ARM OF PROPELLER GOVERNOR RUBBING THROUGH BAFFLING. AIR FLOW PUSHES BAFFLING INTO STUD ON CONTROL ARM AND IS WE ARING THROUGH. SUBMITTER STATED MAKE BRACKET TO HOLD BAFFLES BACK. 1 L 7 1 3O A3SO 1996110100539 19961101 00539 1996 11 1 96ZZZX5431 4 19960813 G 6113 3532312 SPINNER PIPER PA28 PA28151 7102805 SO FWD BULKHEAD CRACKED D S K NONE O OTHER IN INSP/MAINT 1 GL 09 43456 1700 287415499 DURING ANNUAL INSPECTION, FOUND FRONT SPINNER BULKHEAD CRACKED. A CRACK HAD PREVIOUSLY BEEN STOP DRILLED. 1 L 7 1 3O 2A13 1996110100540 19961101 00540 SO 1996 11 1 96ZZZX5432 1 19961001 G 7921 89082003 CLIP PIPER PA46 PA46350P SO LT INTERCOOLER SEPARATED B S LF1R K NONE O OTHER IN INSP/MAINT 1 EA 07 46PM 4622081 NOTED DURING ANNUAL, LT INTERCOOLER 'CLIP' SEPARATED LEAVING ONLY SCREW AND WELD BUSHING. SUBMITTER STATED THIS IS A RE CURRING PROBLEM. A FIX WOULD BE TO BOND CLIP TO SIDE OF INTERCOOLER UPON INSTALLATION WITH HIGH TEMP RED SILICONE ADHES IVE. 1 L 7 1 3O RT A25SO 1996110100541 19961101 00541 SO 1996 11 1 96ZZZX5433 1 19960930 G 3250 AN47A BOLT PIPER PA34 PA34200T 7103406 SO NLG STEERING CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 15 53BD 2923 347970114 DURING AN ANNUAL INSPECTION, NOSE GEAR STEERING BOLTS (2 EACH) SECURING THE STEERING CHANNEL WERE REMOVED FOR INSPECTION AND FOUND 1 BOLT CRACKED APPROXIMATELY 75 PERCENT THROUGH SHANK, OTHER BOLT WAS FOUND BENT. INSTALLED NEW BOLTS. SUBM ITTER IS OF THE OPINION THESE BOLTS WERE OVERSTRESSED FROM TOWING LIMITS BEING EXCEEDED. 1 L 7 2 3O A7SO 1996110100542 19961101 00542 SO 1996 11 1 96ZZZX5434 1 19960919 G 5711 SPAR PIPER PA28 PA28180 7102808 SO FUEL TANK ATTACH DELAMINATED D K NONE O OTHER IN INSP/MAINT 1 SW 15 5349L 284652 FOUND SEVERE SPAR DELAMINATION ON UPPER OUTBOARD FUEL TANK ATTACH POINTS. SUBMITTER STATED APPEARS TO BE RESULT OF EXPO SURE TO SALT AIR NEAR SEACOAST IN FLORIDA. SUBMITTER SUGGESTS TANK REMOVAL AND INSPECTION OF AREA EVERY 5 YEARS. AIRCR AFT WAS BASED IN SALT ENVIRONMENT 22 OF 28 YEARS. PART TOTAL TIME APPROXIMATELY 2,200 HRS. 1 L 7 1 3O 2A13 1996110100543 19961101 00543 SO 1996 11 1 96ZZZX5435 1 19960824 G 7110 96506000 HINGE ASSY PIPER PA34 PA34200 7103405 SO LT ENG OTBD COWL CRACKED D K NONE O OTHER IN INSP/MAINT 1 GL 23 56676 5990 347450020 UPON INVESTIGATION AS TO WHY COWLING WAS CHAFING AND WEARING THROUGH THE ALUMINUM, FOUND HINGE ASSY CRACKED WHICH ALLOWE D THE SIDE COWL ASSY TO MOVE AND CHAFE AGAINST UPPER COWL ASSY. THIS P/N HINGE ASSY IS LOCATED AT FWD OTBD ON LT ENGINE . SUBMITTER STATES THE HINGE APPEARED TO HAVE BEEN CRACKED AND BROKEN FOR QUITE SOME TIME. 1 L 7 2 3O A7SO 1996110100544 19961101 00544 SO 1996 11 1 96ZZZX5436 1 19960824 G 7110 96506001 HINGE ASSY PIPER PA34 PA34200 7103405 SO LT ENG INBD COWL CRACKED D K NONE O OTHER IN INSP/MAINT 1 GL 23 56676 5990 347450020 UPON INVESTIGATION AS TO WHY COWLING WAS CHAFING AND WEARING THROUGH THE ALUMINUM, FOUND HINGE ASSYS CRACKED WHICH ALLOW ED THE SIDE COWL ASSY TO MOVE AND CHAFE AGAINST UPPER COWL ASSY. THIS P/N HINGE ASSY IS LOCATED AT FWD INBD ON LT ENGIN E AND FWD OTBD ON RT ENGINE. THE HINGES APPEARED TO HAVE BEEN CRACKED AND BROKEN FOR QUITE SOME TIME. 1 L 7 2 3O A7SO 1996110100920 19961101 00920 CE 1996 11 1 96ZZZX5437 1 19960621 G 7160 04500705 BUTTERFLY VALVE 04500523 CESSNA 150 152 2071835 CE AIR BOX SCREWS WORN D A K NONE O OTHER IN INSP/MAINT 1 GL 23 5249P 5047 15284901 DURING INSPECTION, FOUND THE TWO SCREWS WHICH SECURE THE CARBURETOR HEAT BUTTERFLY VALVE TO THE SHAFT WERE LOOSE. UPON REMOVAL, FOUND SCREWS WORN APPROXIMATELY 80 PERCENT THROUGH. SUBMITTER STATED APPEARS THEY HAD BEEN LOOSE FOR SOME TIME . FAILURE OF SCREWS COULD CAUSE LOSS OF POWER DUE TO RESTRICTION OF AIR FLOW AND INJESTION OF SCREWS INTO ENGINE. 1 H 7 1 3O NT 3A19 1996110100921 19961101 00921 CE 1996 11 1 96ZZZX5438 1 19960926 G 5553 04320049 BRACKET 04320019 CESSNA 150 152 2071835 CE V STAB ASSY CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 17 49158 7297 7297 15281171 WHILE INSPECTING HORIZONTAL STABILIZER TO VERTICAL FIN ATTACH NUTPLATES PER AD 80-11-4 FOR CRACKS, NUTPLATES WERE FOUND OK, BUT THE BRACKET THE NUTPLATES ARE RIVETED TO WAS CRACKED IN TWO SPOTS, RADIATING FROM THE BOLT HOLE. 1 H 7 1 3O NT 3A19 1996110100922 19961101 00922 CE 1996 11 1 96ZZZX5439 1 19960926 G 5210 504300431207 BRAZE ASSY BEECH 90 C90 1152913 CE CABIN DOOR BOLT FAILED B S A IA4R K NONE O OTHER IN INSP/MAINT 1 SO 09 438SP LJ1108 PILOT LOCKED CABIN DOOR AND SECURED AIRCRAFT. THE NEXT MORNING THE CABIN DOOR COULD NOT BE OPENED. THE UPPER FORWARD H OOK AND ROD LINK WAS NOT MOVING WHEN THE HANDLE WAS TURNED. AFTER 3 HOURS OF TRYING TO GET THE DOOR OPEN, A DECISION WA S MADE TO CUT THE RT AFT CABIN WINDOW TO GAIN ACCESS TO THE EMERGENCY EXIT RELEASE HANDLE. ENTERED THE CABIN THROUGH TH E EMERGENCY EXIT AND REMOVED DOOR PANELS. FOUND THE UPPER BRAZE ASSY ATTACHMENT HOLE FOR THE UPPER LINK SEVERELY ELONGA TED AND BOLT HAD FAILED. PART TOTAL TIME APPROXIMATELY 4,900 HRS. SUBMITTER RECOMMENDATION: PANELS SHOULD BE REMOVED DURING INSPECTION AND ATTACHMENT BOLTS INSPECTED AND LUBED. 1 L 7 2 3T 3A20 1996110100923 19961101 00923 CE 1996 11 1 96ZZZX5440 1 19960913 G 3230 DOWNLOCK BEECH 76 76 1153005 CE NLG MALFUNCTION D A O OTHER O OTHER LD LANDING 1 GL 03 6017U ME159 NOSE GEAR COLLAPSED DURING A TOUCH-AND-GO WHEN POWER WAS APPLIED FOR A TAKEOFF. INVEST REVEALED: LT FWD DRAG BRACE ATT ACH BOLT LOOSE (COTTER PIN WAS INSTALLED), INCORRECT WASHERS WERE INSTALLED (BASED ON PARTS MANUAL). DOWNLOCK HOOK PIVO T BOLT WAS PARTIALLY SEIZED (HOOK VERY SLOW TO LOCK EVEN WITH ACTUATOR DISCONNECTED). THE PIVOT BOLT AND BUSHINGS BETWE EN THE UPPER AND LOWER DRAG BRACE WERE VERY WORN AT DOWNLOCK ASSY. NOSE GEAR DOWNLOCK SWITCH WAS NOT ADJUSTED PER THE M M. ALL THE PARTS STATED ABOVE ARE TO BE REPLACED AND/OR LUBRICATED AND REINSTALLED IAW MM. 1 L 7 2 3O A29CE 1996110100924 19961101 00924 CE 1996 11 1 96ZZZX5441 1 19960920 G 3710 442CW4 PUMP AIRBORNE BEECH 58 58P 1152744 CE VACUUM SYSTEM FAILED B CGOR K NONE O OTHER IN INSP/MAINT 1 GL 03 6371V 490 07AH000102 TJ417 VACUUM SYSTEM FAILED PER PILOT REPORT. GAINED ACCESS TO VACUUM PUMPS, FOUND DRIVE SHAFTS SHEARED. REPLACED BOTH PUMPS, FILTERS, AND EVACUATED LINES AS REQUIRED. (NOTE: IT WOULD BE POSSIBLE THAT ONE PUMP HAD BEEN INOPERABLE FOR SOME TIME .) 1 L 7 2 3O A23CE 1996110100925 19961101 00925 CE 1996 11 1 96ZZZX5442 1 19960920 G 3710 442CW4 PUMP AIRBORNE BEECH 58 58P 1152744 CE VACUUM SYSTEM FAILED B CGOR K NONE O OTHER IN INSP/MAINT 1 GL 03 6371V 490 07AH000099 TJ417 VACUUM SYSTEM FAILED PER PILOT REPORT. GAINED ACCESS TO VACUUM PUMPS, FOUND DRIVE SHAFTS SHEARED. REPLACED BOTH PUMPS, FILTERS, AND EVACUATED LINES AS REQUIRED. (NOTE: IT WOULD BE POSSIBLE THAT ONE PUMP HAD BEEN INOPERABLE FOR SOME TIME .) 1 L 7 2 3O A23CE 1996110100926 19961101 00926 CE 1996 11 1 96ZZZX5443 1 19960928 G 3230 1CH16 SWITCH 99101393 CESSNA 414 414A 2075907 CE NLG ACTUATOR WIRE TORN LOOSE H A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 WP 13 6604C CE271 414A0030 LANDING GEAR FAILED TO RETRACT. AIRCRAFT LANDED WITHOUT INCIDENT. IT WAS DISCOVERED THE WIRING HARNESS HAD TORN LOOSE FROM THE MICROSWITCH. HYD ACTUATOR WAS REPLACED. OPERATIONAL CHECK PERFORMED AND IS OKAY. 1 L 7 2 3O A7CE 1996110100927 19961101 00927 SO 1996 11 1 96ZZZX5444 1 19961015 G 7603 555815 CONTROL CABLE PIPER PA32 PA32R300 7103213 SO THROTTLE BROKEN D K NONE O OTHER IN INSP/MAINT 1 NE 01 7236U 4930 32R7780298 THROTTLE CABLE BROKE AT QUADRANT END WHERE CABLE MEETS END. CABLE BROKE ON FIRST COLD MORNING OF FALL. WAS NOT EXCESSI VELY STIFF AT NORMAL TEMPS. 1 L 7 1 3O A3SO 1996110100928 19961101 00928 CE 1996 11 1 96ZZZX5445 1 19960627 G 2750 FUSE CESSNA 150 150H 2071818 CE FLAP CONT BLOWN G A UNSCHED LANDING F FLT CONT AFFECTED CL CLIMB 1 WP 15 7260S 15067960 DURING A GO-AROUND, THE FLAPS WERE STUCK IN THE 40 DEGREE POSITION. THIS MALFUNCTION CAUSED THE PILOT TO MAKE AN EMERGE NCY LANDING WHICH RESULTED IN AN ACCIDENT. AN INSPECTION OF THE FUSE FOR THE FLAP SYSTEM REVEALED CORROSION ON THE FUSE WHICH HAD CORRODED ITSELF TO THE FUSE CAP AND THE FUSE WAS BLOWN. IT WAS ALSO NOTED THE FUSE WAS THE WRONG AMPERAGE. 1 H 7 1 3O 3A19 1996110100929 19961101 00929 SO 1996 11 1 96ZZZX5446 1 19961015 G 5210 8732910 LOCK ASSY 9691700 PIPER PA34 PA34200T 7103406 SO DOOR ASSY FAILS TEST B APCR K NONE O OTHER IN INSP/MAINT 1 NM 01 8107D PK565 348070010 KEY CAN BE REMOVED FROM DOOR LOCK WHEN LOCK IS IN OPEN POSITION REGARDLESS OF DOOR LATCH POSTION. FAILS TESTS PER AD 88 -04-05. SUBMITTER STATED THE AD SHOULD BE A 100-HOUR RECURRING MAINTENANCE REQUIREMENT. MOST PILOTS UNAWARE OF NEED FO R PRE/POST-FLIGHT CHECKS PER PAPER SB 633B. 1 L 7 2 3O A7SO 1996110100930 19961101 00930 SO 1996 11 1 96ZZZX5447 1 19960927 G 2842 548671 SENSOR PIPER PA28 PA28151 7102805 SO FUEL QUANTITY FLOAT DETACHED D K NONE O OTHER IN INSP/MAINT 1 SO 19 8403C 1466 287615102 ZERO FUEL QUANTITY INDICATED WITH FULL TANK PROMPTED INSPECTION OF FUEL QUANTITY SENDING UNIT. FLOAT WAS FOUND COMPLETE LY DETACHED FROM WIRE LEVER ARM AND FLOATING IN TANK. HOLE THROUGH WHICH WIRE PASSED IS WORN SUFFICIENTLY TO ALLOW RETA INING WASHER TO PASS THROUGH ALSO. 1 L 7 1 3O 2A13 1996110100931 19961101 00931 SO 1996 11 1 96ZZZX5448 2 19961008 G 8520 CRANKSHAFT PIPER PA28 PA28R201T 7102813 SO CONT O360 TSIO360FB 17025 SO NR 2 CON ROD BROKEN B CR1R A UNSCHED LANDING R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 GL 25 99TM 28R7703073 248145R ENGINE LOST POWER IN-FLIGHT. ACFT ABLE TO LAND AND TAXIED IN UNDER ITS OWN POWER. ENG INSP REVEALED PROP COULD BE MOVE D 15 TO 20 DEGREES WITHOUT RESISTANCE. WITH PLUGS REMOVED, FND THE FRONT 4 PISTONS WOULD MOVE IN THAT 15 TO 20 DEGREES, BUT NR 1 AND NR 2 CYL PISTON WOULD NOT. REMOVED TIMING PLUG AND FND CRANKSHAFT HAD A ROCKING MOTION WHILE MOVING PROP IN THAT FREE-PLAY AREA. THE ENGINE NOT TORN DOWN AT TIME OF REPORT, BUT IT APPEARS THE CRANKSHAFT BROKE JUST FWD OF WHE RE THE NR 2 CONNECTING ROD ATTACHES. 1 L 7 1 3O 3 O 2A13 E9CE 1996110100932 19961101 00932 GL 1996 11 1 96ZZZX5449 2 19960923 G 7250 6892832 NOZZLE SHIELD ALLSN 250C 250C30P 03013 GL 3RD STAGE ELONGATED HOLES B YKER K NONE O OTHER IN INSP/MAINT 1 EA 17 CAE895208 UPON DISASSEMBLY OF THE TURBINE FOR REPLACEMENT OF THE FIRST STAGE NOZZLE, FOUND FRETTING WEAR ON THE SHEATHS OF THE TOT HARNESS PROBES, AND ELONGATED HOLES IN THE THIRD STAGE NOZZLE SHIELD WHERE THE PROBES PASS THROUGH. TOT HARNESS REQUIR ED REPLACEMENT. 3 U E1GL 1996110100933 19961101 00933 1996 11 1 96ZZZX5450 1 19960923 G 7722 6893072 HARNESS ALLSN 250C 250C30P 03013 GL ENG TOT PROBE FRETTED B YKER K NONE O OTHER IN INSP/MAINT 1 EA 17 FF4311E CAE895208 UPON DISASSEMBLY OF THE TURBINE FOR REPLACEMENT OF THE FIRST STAGE NOZZLE, FOUND FRETTING WEAR ON THE SHEATHS OF THE TOT HARNESS PROBES, AND ELONGATED HOLES IN THE THIRD STAGE NOZZLE SHIELD WHERE THE PROBES PASS THROUGH. TOT HARNESS REQUIR ED REPLACEMENT. 3 U E1GL 1996110100934 19961101 00934 WP 1996 11 1 96ZZZX5451 1 19961021 G 2750 37741723 BELLCRANK 5772691 DOUG DC8 DC8* WP FLAP ACTUATOR BROKEN B DM4R K NONE O OTHER IN INSP/MAINT 1 SO 19 H058594 BELLCRANK ARRIVED BROKEN. SUSPECT CAUSE WAS STRESS AND CORROSION. 2 L 7 4 4J F 4A25 1996110100935 19961101 00935 CE 1996 11 1 96ZZZX5452 1 19961015 G 3411 D37C15 SWITCH CESSNA 500 560CESSNA 2076750 CE PITOT DIFF PRESS DEFECTIVE D K NONE P NO WARNING INDICATION IN INSP/MAINT 1 SW 05 277RC 1277 0751 5600210 LANDING GEAR WARNING HORN FAILED PRE-FLIGHT CHECK. HORN WOULD SOUND WHEN EACH THROTTLE WAS RETARDED SEPARATELY, BUT FAI LED TO SOUND WHEN BOTH THROTTLES WERE RETARDED TOGETHER. TROUBLESHOOTING FOUND PITOT/STATIC DIFFERENTIAL PRESSURE SWITC H (150 KNOT AIRSPEED SWITCH) WITH HIGHER THAN NORMAL INTERNAL RESISTANCE. INSTALLED NEW SWITCH. ALL GROUND OPS AND LE AK CHECKS WERE NORMAL PER CITATION 560 MM, CHAPTERS 32-60-00 AND 34-11-00. 2 L 7 2 4F RT A22CE 1996110100936 19961101 00936 EU 1996 11 1 96ZZZX5453 1 19960913 G 3242 5003340 ROTATING DISC 50028053 ISRAEL 1124 1124 4500102 EU BRAKE ASSY BROKEN B XZAR K NONE O OTHER IN INSP/MAINT 1 EA 17 38AE 140 5626 318 ON PRE-FLIGHT, FOUND ROTATING DISC BROKEN, WHICH, IN TURN, BROKE THE WHEEL HALF. LANDINGS, 72. 2 M 7 2 4F A2SW 1996110100937 19961101 00937 NM 1996 11 1 96ZZZX5454 1 19961010 G 3230 F6137 UPLOCK AMD FALC50 FALCON2000 2730170 NM MLG MALFUNCTION B YL1R K NONE O OTHER CL CLIMB 1 SW 11 790M 10 U402 19 LANDING GEAR DOORS WOULD NOT RETRACT AFTER GEAR UP SELECTED. RED LIGHTS ON GEAR PANEL WERE ON, GEAR HANDLE LIGHT FLASHI NG. THE CREW INDICATED THEY HAVE HAD SIMILAR PROBLEMS WITH THE LANDING GEAR ON THIS AIRCRAFT BEFORE. THEY REPLACED THE GEAR UPLOCK. UNABLE TO DUPLICATE PROBLEM ON THE GROUND. ALL TESTS INDICATE NO PROBLEM WITH SYSTEM. 3 EACH GEAR UPLOC KS CHANGED OUT AS BEFORE. 2 K 7 3 4F RT A50NM 1996110100938 19961101 00938 NM 1996 11 1 96ZZZX5455 1 19961010 G 3230 F6137 UPLOCK AMD FALC50 FALCON2000 2730170 NM MLG MALFUNCTION B YL1R K NONE O OTHER CL CLIMB 1 SW 11 790M 10 U249 19 LANDING GEAR DOORS WOULD NOT RETRACT AFTER GEAR UP SELECTED. RED LIGHTS ON GEAR PANEL WERE ON, GEAR HANDLE LIGHT FLASHI NG. THE CREW INDICATED THEY HAVE HAD SIMILAR PROBLEMS WITH THE LANDING GEAR ON THIS AIRCRAFT BEFORE. THEY REPLACED THE GEAR UPLOCK. UNABLE TO DUPLICATE PROBLEM ON THE GROUND. ALL TESTS INDICATE NO PROBLEM WITH SYSTEM. 3 EACH GEAR UPLOC KS CHANGED OUT AS BEFORE. 2 K 7 3 4F RT A50NM 1996110100939 19961101 00939 NM 1996 11 1 96ZZZX5456 1 19961010 G 3230 F6137 UPLOCK AMD FALC50 FALCON2000 2730170 NM MLG MALFUNCTION B YL1R K NONE O OTHER CL CLIMB 1 SW 11 790M 10 U673 19 LANDING GEAR DOORS WOULD NOT RETRACT AFTER GEAR UP SELECTED. RED LIGHTS ON GEAR PANEL WERE ON, GEAR HANDLE LIGHT FLASHI NG. THE CREW INDICATED THEY HAVE HAD SIMILAR PROBLEMS WITH THE LANDING GEAR ON THIS AIRCRAFT BEFORE. THEY REPLACED THE GEAR UPLOCK. UNABLE TO DUPLICATE PROBLEM ON THE GROUND. ALL TESTS INDICATE NO PROBLEM WITH SYSTEM. 3 EACH GEAR UPLOC KS CHANGED OUT AS BEFORE. 2 K 7 3 4F RT A50NM 1996110100940 19961101 00940 CE 1996 11 1 96ZZZX5457 1 19961011 G 2430 P41K16 WIRE BEECH 200 200BEECH 1152920 CE RT GEN GCU BURNED B FGQR K NONE H ELECT. POWER LOSS-50 PC NR NOT REPORTED 1 SO 01 93ME 2509 BB1345 RIGHT GEAR FAILED. TROUBLESHOOTING FOUND ALL COMPONENTS OPERATIONAL. HIGH RESISTANCE FOUND FROM PIN 33 ON RELAY PANEL A123 AND PIN B AT GCU. CAUSE FOUND IN WIRE P41R16 WITHIN THE BUNDLE RUNNING FROM RELAY PANEL A123 WHERE WIRE HAD BEEN S TAMPED BY LABELING MACHINE CAUSING AN INDENTATION IN SHIELDED WIRE WHICH APPARENTLY ALLOWED ARCING TO OCCUR AND EVENTUAL LY BURNED THROUGH THE CONDUCTOR. WIRE WAS SPLICED AND SYSTEM OPERATED NORMALLY. 1 L 7 2 4T A24CE 1996110100941 19961101 00941 SO 1996 11 1 96ZZZX5458 1 19960620 G 2435 230801971 BRUSH LUCAS 23080013 EMB 120 EMB120RT SO START/GEN EXCESS WORN B XC4R K NONE O OTHER IN INSP/MAINT 1 SO 19 261CA 660 3852 120254 BRUSHES FAILED PREMATURELY. BRUSHES WORN 85 PERCENT, BRUSH SHUNTS BROKEN OFF BRUSHES. BRUSHES BURNED, ARMATURE OVERHEAT ED, SUBMITTER STATED POOR DESIGN OF BRUSH. RECOMMENDED RE-DESIGN OF BRUSH. 2 L 7 2 4T RT A31SO 1996110700105 19961107 00105 NM 1996 11 7 96ZZZX5466 1 19961017 G 2121 X11374 BEARING SUNDSTRANDEM 215201 BOEING 727 727 1384001 NM COOL FAN FAILED B A DM4R K NONE B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 SO 19 1571 AVIONIC COOLING FAN BEARING FAILED AFTER 1,571.22 HRS OF OPERATION. INNER BALL RACE DISTORTED AND BALLS MISSING. FLIGH T ATTENDANTS REPORTED SMOKE IN CABIN DUE TO FAN FAILURE. 2 L 7 3 4F A3WE 1996110700107 19961107 00107 GL 1996 11 7 96ZZZX5468 3 19961017 G 6114 D4344 HUB MCAULY 3AF32C 3AF32C87 GL NR 3 SOCKET CRACKED B DJFR K NONE O OTHER IN INSP/MAINT 1 EA 23 800240 800240 DURING C/W AD 95-24-05, SL 93-11A OIL FILL. HUB FOUND CRACKED IN NR 3 BLADE SOCKET. 5 C P22EA 1996110700109 19961107 00109 1996 11 7 96ZZZX5469 4 19960905 G 6122 D20271 GOVERNOR BODY MCAULY C290D3T22 PROPELLER WORN B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 820303 PROPELLER GOVERNOR BODY WORN IN GEAR POCKET. SUSPECT CAUSE, IDLER GEAR STUD WORN ALLOWED GEAR TO RUN OFFSET. 1996110700110 19961107 00110 SO 1996 11 7 96ZZZX5470 2 19960910 G 8530 501867 LOCK TAB PIPER PA28 PA28R201T 7102813 SO CONT O360 TSIO360F 17025 SO RKR SHAFT BOLT FAILED D K NONE O OTHER IN INSP/MAINT 1 SW 03 CYLINDERS WERE SENT OUT FOR CHROMING AND OVERHAUL. CYLINDERS WERE RECEIVED BACK READY TO INSTALL. NEW SUPERIOR AIR PAR TS ROCKER ARM SHAFT BOLT LOCK TABS WERE INSTALLED. UPON BENDING TANGS OVER BOLT HEADS, ALL TANGS EITHER CRACKED OR BROK E OFF COMPLETELY. SUBMITTER STATES, APPARENTLY, A STOCK METAL WAS TEMPERED WRONG AND WAS TOO BRITTLE. CONTINENTAL LOCK TABS WERE INSTALLED AND OPERATED FINE. 1 L 7 1 3O 3 O 2A13 E9CE 1996110700111 19961107 00111 GL 1996 11 7 96ZZZX5471 3 19961015 G 6114 C4850 GASKET CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROP CYL DOME LEAK D K NONE K FLUID LOSS IN INSP/MAINT 1 SW 07 RED DYE LEAKAGE FROM THE PROP CYLINDER 'DOME' GASKETS. SPECIFICALLY WHERE THE DOWL PINS ARE. HAS BEEN A RECURRING PROB LEM JUST AFTER OVERHAUL. SUBMITTER STATES THIS SHOP HAS SEEN 7 PROPS LEAK AFTER THE OIL-FILL MOD. THESE OVERHAULS WERE PERFORMED BY 4 DIFFERENT PROPELLER REPAIR STATIONS. AFTER RESEAL, 2 OF THE 7 HAVE SHOWN SUBSEQUENT LEAKAGE AND NEED FO R RESEAL. SUGGEST MCCAULEY HAVE AN O-RING INCORPORATED WITH OIL-FILL MOD. 1 L 7 2 3O 3A10 5 C P22EA 1996110700112 19961107 00112 GL 1996 11 7 96ZZZX5472 1 19961001 G 5541 RIB AMTR BEDE4 BEDEBD4 GL RUDDER CRACKED D K NONE O OTHER IN INSP/MAINT 1 WP 25 2831W 692 RUDDER TOP RIB CRACKED, DISCOVERED DURING INSPECTION. RUDDER BALANCE WEIGHT IS RIVETED TO RIB. RIB WAS BUILT BY OWNER IAW INSTRUCTIONS. RIB BUILT FROM .025 INCH 2024. APPEARS NOT TO BE STRONG ENOUGH TO HOLD BALANCE WEIGHT. NEW RIB FABR ICATED FROM .032 INCH WITH DOUBLERS. 1 H 7 1 3O EXPA1H71 1996110700113 19961107 00113 EA 1996 11 7 96ZZZX5473 1 19961008 G 2910 MS219266D ELBOW CNDAIR CL600 CL6001A11 1900302 EA LT WELL HYD LEAKING D K NONE K FLUID LOSS IN INSP/MAINT 1 GL 25 100LR 1064 50 HRS AFTER MAJOR INSP, DEVELOPED LEAK IN LT WHEELWELL. FOUND NR 6 ELBOW CRACKED AND LEAKING. NEXT DAY FOUND HYD FLUI D LEAKING OUT OF LT WHEELWELL AGAIN. FOUND NR 6 TEE FITTING CRACKED AND LEAKING. REPLACED BOTH. PRE-FLIGHTED A/C ON T HIRD DAY FOR TRIP AND NOTICED FLUID LEAKING FROM RT WHEELWELL AFTER PREFLIGHT. FOUND NR 4 TEE FITTING CRACKED AND LEAKI NG. CANCELLED TRIP. REPLACED NR 4 TEE FITTING. NO MORE PROBLEMS. SUSPECT CAUSE WAS NR 3 HYD RES IN WHEELWELL WAS REM OVED TO PERFORM SB AND ALL THE FITTINGS WERE REMOVED TO GAIN ACCESS TO RES. ALL FITTINGS ARE ALUM AND HYD LINES ARE STA INLESS STEEL. SUGGEST REPLACEMENT OF ALUM FITTINGS AROUND HYD RES ANYTIME IT IS REMOVED. 2 L 7 2 4F RT A21EA 1996110700114 19961107 00114 EA 1996 11 7 96ZZZX5474 1 19961008 G 2910 MS21905D TEE FITTING CNDAIR CL600 CL6001A11 1900302 EA LT WELL HYD LEAKING D K NONE K FLUID LOSS IN INSP/MAINT 1 GL 25 100LR 1064 50 HRS AFTER MAJOR INSP, DEVELOPED LEAK IN LT WHEELWELL. FOUND NR 6 ELBOW CRACKED AND LEAKING. NEXT DAY FOUND HYD FLUI D LEAKING OUT OF LT WHEELWELL AGAIN. FOUND NR 6 TEE FITTING CRACKED AND LEAKING. REPLACED BOTH. PRE-FLIGHTED A/C ON T HIRD DAY FOR TRIP AND NOTICED FLUID LEAKING FROM RT WHEELWELL AFTER PREFLIGHT. FOUND NR 4 TEE FITTING CRACKED AND LEAKI NG. CANCELLED TRIP. REPLACED NR 4 TEE FITTING. NO MORE PROBLEMS. SUSPECT CAUSE WAS NR 3 HYD RES IN WHEELWELL WAS REM OVED TO PERFORM SB AND ALL THE FITTINGS WERE REMOVED TO GAIN ACCESS TO RES. ALL FITTINGS ARE ALUM AND HYD LINES ARE STA INLESS STEEL. SUGGEST REPLACEMENT OF ALUM FITTINGS AROUND HYD RES ANYTIME IT IS REMOVED. 2 L 7 2 4F RT A21EA 1996110700115 19961107 00115 EA 1996 11 7 96ZZZX5475 1 19961008 G 2910 MS21909D TEE FITTING CNDAIR CL600 CL6001A11 1900302 EA RT WELL HYD LEAKING D K NONE K FLUID LOSS IN INSP/MAINT 1 GL 25 100LR 1064 50 HRS AFTER MAJOR INSP, DEVELOPED LEAK IN LT WHEELWELL. FOUND NR 6 ELBOW CRACKED AND LEAKING. NEXT DAY FOUND HYD FLUI D LEAKING OUT OF LT WHEELWELL AGAIN. FOUND NR 6 TEE FITTING CRACKED AND LEAKING. REPLACED BOTH. PRE-FLIGHTED A/C ON T HIRD DAY FOR TRIP AND NOTICED FLUID LEAKING FROM RT WHEELWELL AFTER PREFLIGHT. FOUND NR 4 TEE FITTING CRACKED AND LEAKI NG. CANCELLED TRIP. REPLACED NR 4 TEE FITTING. NO MORE PROBLEMS. SUSPECT CAUSE WAS NR 3 HYD RES IN WHEELWELL WAS REM OVED TO PERFORM SB AND ALL THE FITTINGS WERE REMOVED TO GAIN ACCESS TO RES. ALL FITTINGS ARE ALUM AND HYD LINES ARE STA INLESS STEEL. SUGGEST REPLACEMENT OF ALUM FITTINGS AROUND HYD RES ANYTIME IT IS REMOVED. 2 L 7 2 4F RT A21EA 1996120300039 19961203 00039 CE 1996 12 3 96ZZZX5476 1 19961001 G 3610 66002552 CHECK VALVE LEAR 24 24D 5170311 CE ENG BLEED SYS FLAP BROKEN D A K NONE O OTHER IN INSP/MAINT 1 WP 21 101VS 6941 218 THERE ARE 2 EACH PN 6600255-2 HOT AIR CHECK VALVES INSTALLED AS PARTS OF KIT PN 2881701-1 FOR AMR 79-8 FOR LEAR 28229 AI RCRAFT. BOTH CHECK VALVES HAD FAILURES OF THE RETENTION SPRING AND MOUNT PIN OF THE HINGED PORTION OF THE FLAPPER IN TH E CHECK VALVE. THIS ALLOWED THE FLAPPER TO MOVE AROUND RANDOMLY WITHIN THE CHECK VALVE HOUSING. THE PIN AND SPRING WER E MISSING. SUBMITTER STATES THIS IS A POSSIBLE ENGINE FOD PROBLEM. 2 L 7 2 4J A10CE 1996110700116 19961107 00116 SO 1996 11 7 96ZZZX5477 1 19961017 G 3213 083114 FORK END LUSCOM 8 8A 8190104 SO LT MLG JACK STRU SHEARED D A K NONE O OTHER IN INSP/MAINT 1 EA 25 1294M 8800 4021 LT GEAR JACK STRUT LOOSE WHEN USING ENTRY STEP. FOUND FORK END SHEARED OFF (IN THREADED AREA) WHERE JACK STRUT ATTACHES TO MAIN GEAR LEG. 1 H 7 1 3O A694 1996110700117 19961107 00117 SO 1996 11 7 96ZZZX5478 1 19961009 G 2913 HYC5005 PUMP PRESTOLITE PIPER PA44 PA44180 7104402 SO HYD PACK FAILED H K NONE O OTHER IN INSP/MAINT 1 GL 25 25PE 317 AH1318 447995184 POWER PACK PUMP LASTED ONLY 317.13 HRS. SUBMITTER STATED PUMP SHOULD HAVE LASTED LONGER. 1 L 7 2 3O A19S0 1996110700118 19961107 00118 SO 1996 11 7 96ZZZX5479 1 19960905 G 5751 6071417 SPAR ASSY 6071403 PIPER PA18 PA18150 7101828 SO RT AIL CRACKED C K NONE O OTHER IN INSP/MAINT 1 AL 03 2561N 3314 188009038 FOUND THE SPAR CRACKED ON RT AILERON PN 60 714-03 AT CENTER HORN AND HINGE ASSY AT THE SPAR ATTACH. SUSPECT FAULT LIES IN DESIGN AS THE AILERON SPAR WAS CUT OUT BY FACTORY ON THE OTBD EDGES OF THE 'U' CHANNGEL SPAR TO ACCOMMODATE THE AILER ON HORN ASSY. THIS WEAKENS SPAR AND CONTRIBUTES TO CRACKS. CAN ONLY BE DETECTED IN EARLY STAGES BY DRILLING OFF THE HI NGE ASSY PN 41891-00 AND INSPECTING THE SPAR. 1 H 7 1 3O 1A2 1996110700119 19961107 00119 SO 1996 11 7 96ZZZX5480 1 19960905 G 5751 6071416 SPAR ASSY 6071402 PIPER PA18 PA18150 7101828 SO LT AIL CRACKED C A K NONE O OTHER IN INSP/MAINT 1 AL 03 2561N 3314 188009038 FOUND THE SPAR CRACKED ON LT AILERON AT CENTER HORN AND HINGE ASSY AT THE SPAR ATTACH. SUSPECT FAULT LIES IN DESIGN AS THE AILERON SPAR WAS CUT OUT ON THE OTBD EDGES OF THE 'U' CHANNEL SPAR TO ACCOMODATE THE AILERON ASSY. THIS WEAKENS THE SPAR AND CONTRIBUTES TO THE CRACKS. CAN ONLY BE DETECTED IN EARLY STAGES BY DRILLING OFF THE HINGE ASSY PN 41891-00 AN D SUSPECT THE SPAR. 1 H 7 1 3O 1A2 1996110700120 19961107 00120 SO 1996 11 7 96ZZZX5481 1 19961008 G 2912 28110H FILTER FACET PIPER PA31 PA31350 7103110 SO HYD SYS THREADS BROKEN D O OTHER K FLUID LOSS AP APPROACH 1 AL 01 3582P 17561 318052103 LANDING GEAR WOULD NOT EXTEND WITHOUT USING EMERGENCY HAND PUMP. FOUND HYD LEAK AT LT HYD FILTER ASSY. O-RING WAS BLOW N AND UPON REMOVING FILTER BOWL, THREADS ON FILTER BOWL WERE FOUND BROKEN. SUSPECT CAUSE THREADS SEPARATED FROM METAL F ATIGUE OR OVERTORQUING. 1 L 7 2 3O A20SO 1996110700121 19961107 00121 SO 1996 11 7 96ZZZX5482 1 19961015 G 8120 LW315531 BOLT PIPER PA31 PA31350 7103110 SO TURBO MOUNT BROKEN B A K NONE O OTHER IN INSP/MAINT 1 NM 01 36PB 900 317405128 TURBO SUPPORT BOLT FOUND BROKEN 3 INCHES FROM HEAD. BROKEN IN SHEAR. SUBMITTER STATED THIS IS RECURRING PROBLEM WITH U PPER LT MOUNT BOLT FOR TURBO SUPPORT ASSY. SUBMITTER SUGGESTS BOLT WITH MORE STRENGTH. 1 L 7 2 3O A20SO 1996110700122 19961107 00122 SO 1996 11 7 96ZZZX5483 2 19961022 G 7310 111F4174S HOSE STRATOFLEX CESSNA 188 T188C 2073012 CE CONT O520 TSIO520T 17040 SO FUEL MANIFOLD LEAKING G A A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 GL 07 3619J T18803655T THE ENGINE LOST POWER, AN EMERGENCY LANDING ACCOMPLISHED WITH SMOKE COMING FROM THE ENGINE. AN EXAMINATION OF THE ENGIN E FOUND THE FUEL HOSE BETWEEN THE THROTTLE AND CONTROL ASSY AND THE FUEL MANIFOLD LEAKING AT A 20 PSI CHECK. THE BAND O N THE HOSE INDICATED A 1Q8R DATE. 1 L 7 1 3O 3 O A9CE E8CE 1996110700123 19961107 00123 SO 1996 11 7 96ZZZX5484 1 19961017 G 2436 B002881 REGULATOR PIPER PA34 PA34200T 7103406 SO DC SYS ERRATIC B APCR K NONE H ELECT. POWER LOSS-50 PC NR NOT REPORTED 1 NM 01 36319 1700 475 AR5761 347870318 VOLTAGE REGULATOR BECAME UNSTABLE ALLOWING ALTERNATOR TO DROP OFF-LINE. REGULATOR WOULD NOT ADJUST, REQUIRED REPLACEMEN T. UNIT LAST OVERHAULED BY NV2R045L. 1 L 7 2 3O A7SO 1996110700124 19961107 00124 EA 1996 11 7 96ZZZX5485 2 19961015 G 8550 78619 PUMP PIPER PA28 PA28235 7102810 SO LYC O540 O540B4B5 41532 EA ENG OIL FAILED B PB2R K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 23 4232T 1700 287210005 L1475740 DURING OVERHAUL DISASSEMBLY OF OIL PUMP, DISCOVERED WOODRUFF KEY DRIVE SHAFT AND SINTERED IRON GEARS. AD 75-08-09 REQUI RES REMOVAL OF THIS STYLE, BUT THIS SERIAL NUMBER IS OUTSIDE OF THOSE SPECIFIED BY LYCOMING. AD 81-18-04 CALLS FOR REPL ACEMENT AT 2,000 HRS OR AT ACCY CASE DISASSEMBLY FOR SINTERED IRON OIL PUMP IMPELLERS. CURRENT AD 96-09-10 DOES SPECIFI CY THIS ENGINE AS HAVING SINTERED IRON, BUT THIS STYLE OF DRIVE SHOULD HAVE BEEN REPLACED PER 75-08-09. 1 L 7 1 3O 3 O 2A13 E295 1996110700126 19961107 00126 CE 1996 11 7 96ZZZX5486 1 19960509 G 5751 122005211 HINGE CESSNA 206 206CESSNA 2073302 CE AIL LT WING CRACKED B S A K NONE O OTHER IN INSP/MAINT 1 SW 15 5065U 2913 2060065 INSPECTION FOUND CRACKS AT LOWER OTBD AILERON HINGE ANGLES, CRACKS RADIATE UPWARD. RIGHT WING HAS 2 CRACKS, LEFT WING H AS 1 CRACK ON SIDE. 1 H 7 1 3O A4CE 1996110700127 19961107 00127 CE 1996 11 7 96ZZZX5487 1 19960509 G 5751 122005212 HINGE ASSY CESSNA 206 206CESSNA 2073302 CE AIL RT WING CRACKED B T4OR K NONE O OTHER IN INSP/MAINT 1 NE 03 5065U 2913 2060065 INSPECTION FOUND CRACKS AT LOWER OTBD AILERON HINGE ANGLES, CRACKS RADIATE UPWARD. RIGHT WING HAS 2 CRACKS, LEFT WING H AS 1 CRACK ON SIDE. 1 H 7 1 3O A4CE 1996110700128 19961107 00128 SO 1996 11 7 96ZZZX5488 1 19960920 G 2434 1965276 BRUSH 110077 PIPER PA23 PA23250 7102308 SO RT ENG ALT FAILED D O OTHER H ELECT. POWER LOSS-50 PC CR CRUISE 1 SO 11 6039Y 278 A98864 273224 RIGHT ENGINE ALTERNATOR FAILED DURING FLIGHT. WHEN ALTERNATOR FAILED, IT ALSO DAMAGED MAIN VOLTAGE REGULATOR. THE ALTE RNATOR WAS OVERHAULED BY AERO ELECTRIC, INC., ON 11-17-94, AND INSTALLED ON 11-28-94. IT APPEARS ONE BRUSH FAILED AND GOUGED THE ROTOR. 1 L 7 2 3O 1A10 1996110700129 19961107 00129 CE 1996 11 7 96ZZZX5489 1 19961004 G 3211 24411001 PIVOT ASSY CESSNA 172 172RG 2072438 CE LT MLG BROKEN D A O OTHER J WARNING INDICATION AP APPROACH 1 CE 07 5204U 6790 1009 172RG0282 LT GEAR WOULD NOT RETRACT OR EXTEND. AIRCRAFT LANDED GEAR UP. SOME DAMAGE TO PROP AND BELLY. AFTER RECOVERY, REMOVED LEFT MAIN GEAR. THE GEAR PIVOT ASSY WAS SHEARED AT THE SPLINES TO THE MAIN BODY. BEFORE THE FLIGHT, THE BRAKES WERE NO T SPONGY. AFTER FAILURE, THERE WERE NO BRAKES. THIS PROBLEM IS ADDRESSED BY CESSNA SB SEB 90-1. 1 H 7 1 3O 3A17 1996110700130 19961107 00130 CE 1996 11 7 96ZZZX5490 1 19961014 G 3211 22411027 PIVOT ASSY CESSNA 182 R182 2072734 CE LT MLG CRACKED D K NONE O OTHER IN INSP/MAINT 1 NM 01 6110T 4240 R18201906 PIVOT ASSY CRACKED UNDER INBOARD PRESSED-ON BEARING. BRAKE HYD FLUID LEAKS FROM CRACK INTO SECTOR GEAR HOUSING. SYMPTO MS ARE A RECURRING SPONGY BRAKE. SECOND TIME THIS CRACK HAS OCCURRED ON ONE OF THESE PIVOT ASSYS. BOTH IN SAME PLACE. THIS FORM WAS SUBMITTED ON PREVIOUS OCCASION. 1 H 7 1 3O RT 3A13 1996110700131 19961107 00131 1996 11 7 96ZZZX5491 4 19961014 G 6113 C5046 ATTACH PLATE CESSNA 182 R182 2072734 CE SPINNER CRACKED H K NONE O OTHER IN INSP/MAINT 1 NM 01 6110T R12801906 PROP SPINNER BULKHEAD CRACKED. SUBMITTER STATES ON FLEET OF R182'S, THIS PART IS CRACKING WITH GREAT FREQUENCY. THIS I S THE 4TH TIME IN 2 YEARS. MUST BE MADE FROM DIFFERENT MATERIAL. 1 H 7 1 3O RT 3A13 1996110700132 19961107 00132 CE 1996 11 7 96ZZZX5492 1 19961017 G 2434 E3FF10300AA ALTERNATOR FORD CESSNA 210 T210M 2073451 CE DC SYS FAILED D A UNSCHED LANDING H ELECT. POWER LOSS-50 PC CR CRUISE 1 NM 01 6161N 5090432 21062932 FAILURE DURING IFR CONDITIONS. OPS CHECK AFTER LANDING SHOWED NORMAL VOLTAGE AND CHARGING RATE. SECOND FAILURE IN IFR AND A/C LANDED. OPS CHECK SHOWED ERRATIC VOLTAGE AND HIGH CHARGE RATE. A/C FERRIED IFR TO REPAIR FACILITY 10 MINUTES A WAY WITH ALT ON LINE IT FAILED AFTER TAKEOFF. OPS CHECK SHOWED ALT TOTALLY INOP. SUBMITTER SUSPECTS ALT BRUSH NOT INST ALLED PROPERLY. NEW OVHL UNIT INSTALLED. OPS CHECK NORMAL. 1 H 7 1 3O 3A21 1996110700133 19961107 00133 CE 1996 11 7 96ZZZX5493 1 19961002 G 7120 051313211 BRACKET CESSNA 175 175 2072502 CE ENG MOUNT FAILED D S K NONE O OTHER IN INSP/MAINT 1 NM 08 6624E 3969 56124 ENG MOUNT BRACKET LOCATED AT UPPER RT SIDE FUSELAGE IMMEDIATELY AFT OF FIREWALL. NUT AND WASHER OF ENGINE MOUNT BOLT PU LLED THROUGH BRACKET, BOWED FIREWALL, AND PRODUCED CRACKS IN FIREWALL DOUBLER PN 0513109-29. NOTED LACK OF TACHOMETER M ARKINGS REQUIRED BY STC SA777CE DENOTING LIMITED OPERATION 2000-2350 RPM. 1 H 7 1 3O NT 3A17 1996110700134 19961107 00134 CE 1996 11 7 96ZZZX5494 1 19960903 G 5540 SPAR ATTACH CESSNA 150 150 2071802 CE RUD SPAR CRACKED D S K NONE O OTHER IN INSP/MAINT 1 GL 25 7734E 5827 17534 RUDDER BOTTOM SPAR ATTACHMENT TO RUDDER HORN, HAIR LINE CRACKED AT RIVETS DUE TO IMPROPER FIT AT SPAR AND RIB ASSY. (RE PAIR REINFORCMENT PREVIOUSLY INSTALLED) AND IT CRACKED ALSO. 1 H 7 1 3O NT 3A19 1996110700135 19961107 00135 SO 1996 11 7 96ZZZX5495 1 19961008 G 3610 2H2216 REGULATOR VALVE PIPER PA34 PA34200T 7103406 SO 2 STAGE PNEU FAILED B APCR K NONE O OTHER IN INSP/MAINT 1 NM 01 8107D 9E336 3480170010 THE SHUT-OFF FUNCTION IS INOP ON THE LOW PRESSURE REGULATOR OF THE 2-STAGE PNEUMATIC REGULATOR VALVE ASSY. WHEN ACTIVAT ED VALVE DOES NOT ALLOW SUFFICIENT PNEUMATIC PRESSURE FOR OPERATION OF THE SURFACE DEICE BOOTS. 1 L 7 2 3O A7SO 1996110700136 19961107 00136 SO 1996 11 7 96ZZZX5496 1 19961015 G 5230 9694300 LATCH ASSY PIPER PA34 PA34200T 7103406 SO FWD-BAG DOOR DEFECTIVE B APCR K NONE O OTHER IN INSP/MAINT 1 NM 01 8107D 348070010 LOWER LATCH ASSY IS ELONGATING HOLE IN LOWER SILL OF FWD BAGGAGE DOOR ASSY. FAILS TESTS PER AD 88-04-05 EVEN THOUGH AD PREVIOUSLY C/W. SUBMITTER STATES INSPECTIONS REQUIRED BY AD SHOULD BE 100-HR MAINTENANCE REQUIREMENTS. MOST PILOTS UNA WARE OF NEED FOR PRE/POST-FLIGHT CHECK PER PIPER SB 633B. 1 L 7 2 3O A7SO 1996110700137 19961107 00137 SO 1996 11 7 96ZZZX5497 1 19961011 G 3310 LIGHTING PIPER PA28 PA28161 7102803 SO COCKPIT OVERHEAD SHORTING D K NONE O OTHER IN INSP/MAINT 1 EA 21 9089N 5150 2816003 REPORT BY PILOT THAT OVERHEAD LIGHT INOP. REPAIR/SIGN OFF - BY MECHANIC STATED 'DID NOT HAVE SWITCH TURNED ON. WORKS F INE'. AFTER SEEING THIS AND BEING FAMILIAR WITH CESSNA SEB 92-33, REV 2, TOOK ANOTHER LOOK AT OVERHEAD PANEL AND FOUND THAT YOU HAD TO HIT THE PANEL TO GET THE LIGHT TO COME ON AND THE RHEOSTAT ASSY WAS ROTATING FREELY EXCEPT FOR THE TANGL ED WIRES. 1 L 7 1 3O 2A13 1996110700138 19961107 00138 EA 1996 11 7 96ZZZX5498 2 19961016 G 8530 ENGINE CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA PIN BUSHING MAKING METAL D K NONE O OTHER IN INSP/MAINT 1 SW 03 93772 2403 800 15285549 L231015 DURING OIL CHANGE, REMOVED AND CUT OPEN OIL FILTER, FOUND COMPLETELY CONTAMINATED WITH NONFERROUS MATERIAL. APPEARED TO BE ALUMINUM. LYCOMING NOTIFIED, INFORMED OUR SHOP THAT MATERIAL PROBABLY WAS PISTON WRIST PIN OUTER BUSHINGS. AIRCRAF T GROUNDED, WAITING ON REPLACEMENT ENGINE. NOTE: CONDITION DID NOT DEGRADE-PREVIOUS OIL CHANGE (50 HRS) DID NOT SHOW M ATERIAL OF ANY SORT. LYC SB 525 AND SB 527 A AND B ARE SIMILAR. (FACTORY REBUILT/OVERHAULED ENGINE.) 1 H 7 1 3O 3 O NT 3A19 E223 1996110700271 19961107 00271 WP 1996 11 7 96ZZZX5499 1 19961015 G 6320 369A51893 SEAL HUGHES 369 369D 4470706 WP MR XMSN TACH GEN LEAKING B EOOR K NONE K FLUID LOSS IN INSP/MAINT 1 AL 03 5074R 236 1151D M/R TRANSMISSION WAS LEAKING AND SUBSEQUENT INSPECTION FOUND THE TACHOMETER GENERATOR SEAL WAS LEAKING. THE SEAL EDGE S EEMED TO BE ROUGH AND BURNT LOOKING. REPLACED SEAL. 1 G 7 1 3U H3WE 1996110700274 19961107 00274 GL 1996 11 7 96ZZZX5502 2 19960705 G 7240 23031260 COMBUSTION CASE BOLKMS 105 BO105CBS 5626008 EU ALLSN 250C 250C20B 03013 GL ARM PIT CRACKED B EOPR K NONE O OTHER IN INSP/MAINT 1 AL 01 493HL S809 ENGINE COMBUSTION CASE CRACKED AT 'ARMPIT' THROUGH WIRE MESH REINFORCEMENT. ENGINE SHOWED A CONTINUING TREND OF LOW POW ER. REPLACED CASE. 1 G 7 2 3U 3 U NC H3EU E4CE 1996110700275 19961107 00275 GL 1996 11 7 96ZZZX5503 2 19961001 G 7230 6870992 CAN 6890550 BOLKMS 105 BO105CBS 5626008 EU ALLSN 250C 250C20B 03013 GL COMPRESSOR CRACKED B EOPR K NONE O OTHER IN INSP/MAINT 1 AL 01 493HL 4917 41732 S809 TURBINE 'CAN' PN 6870992 WAS FOUND CRACKED TWO TIMES IN APPROXIMATELY 100 HOURS. VIBRATION ANALYSIS SHOWED HIGH VIBRATI ON LEVELS, .8IPS AT 48,000 RPM (N-1 SPEED) ON THE COMPRESSOR. REPLACED COMPRESSOR AND HAVE HAD NO MORE CRACKING. NOTE: TURBINE VIBRATION LEVEL NORMAL. REPLACED COMPRESSOR FOR REPAIR. 1 G 7 2 3U 3 U NC H3EU E4CE 1996110700276 19961107 00276 SW 1996 11 7 96ZZZX5504 1 19960911 G 2430 SM20ACD200A21 RELAY BELL 206 206L1 1182107 SW DC SYS INOPERATIVE B ZV1R K NONE O OTHER IN INSP/MAINT 1 SW 03 2618 115 45503 REMOVED RELAY FOR INOPERATIVE DC SYS. 1 G 7 1 3U H2SW 1996110700277 19961107 00277 SW 1996 11 7 96ZZZX5505 1 19960829 G 6330 206033509003 BEARING 206033506101 BELL 206 206L3 1182108 SW XMSN RESTRAINT WORN B ZV1R K NONE O OTHER IN INSP/MAINT 1 SW 03 2619 460 LK2004 51375 RESTRAINT BEARINGS WORN BEYOND LIMITS. REPLACED 2 EACH BEARINGS, PN 206-033-509-003. 1 G 7 1 3U H2SW 1996110700278 19961107 00278 SW 1996 11 7 96ZZZX5506 1 19960918 G 3340 A402AR STROBE BELL 206 206L3 1182108 SW LIGHT LENS CRACKED B AC2R K NONE O OTHER IN INSP/MAINT 1 SW 03 7159J 5473 51408 LENS CRACKED IN HALF. THE REFLECTOR FELL OUT. 1 G 7 1 3U H2SW 1996110700280 19961107 00280 SW 1996 11 7 96ZZZX5507 1 19960815 G 6230 206010335001 LINK ASSY 206010350021 BELL 206 206L1 1182107 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 1078N 241 45389 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10 1 BEARING. SUBMITTER STATED NORMAL USE CAUSED PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 241.0. 1 G 7 1 3U H2SW 1996110700281 19961107 00281 SW 1996 11 7 96ZZZX5508 1 19960815 G 6230 206010336005 LEVER IDLER 206010350021 BELL 206 206L1 1182107 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 1078N 241 45389 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10 1 BEARING. SUBMITTER STATED NORMAL USE CAUSED PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 241.0. 1 G 7 1 3U H2SW 1996110700282 19961107 00282 SW 1996 11 7 96ZZZX5509 1 19960903 G 6230 206010335001 LEVER ASSY 206010350021 BELL 206 206L1 1182107 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 1084Y 45433 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10 1 BEARING. SUBMITTER STATED NORMAL USE CAUSED PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 655.1. 1 G 7 1 3U H2SW 1996110700283 19961107 00283 SW 1996 11 7 96ZZZX5510 1 19960903 G 6230 206010336005 LINK IDLER 206010350021 BELL 206 206L1 1182107 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 1084Y 45433 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10 1 BEARING. SUBMITTER STATED NORMAL USE CAUSED PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 655.1. 1 G 7 1 3U H2SW 1996110700284 19961107 00284 SW 1996 11 7 96ZZZX5511 1 19960815 G 6230 206010335001 LEVER ASSY 206020350021 BELL 206 206L4 1182110 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 175AL 323 52117 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10 1 BEARING. SUBMITTER STATED NORMAL USE CAUSED PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 322.7 1 G 7 1 3U NC H2SW 1996110700285 19961107 00285 SW 1996 11 7 96ZZZX5512 1 19960815 G 6230 206010336005 LINK IDLER 206010350021 BELL 206 206L4 1182110 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 175AL 323 52117 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10 1 BEARING. SUBMITTER STATED NORMAL USE CAUSED PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 322.7. 1 G 7 1 3U NC H2SW 1996110700286 19961107 00286 SW 1996 11 7 96ZZZX5513 1 19960917 G 6230 206010335001 LEVER ASSY 206010350021 BELL 206 206L4 1182110 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 177AL 296 52157 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10 1 BEARING. SUBMITTER STATED NORMAL USE CAUSED PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 296.2. 1 G 7 1 3U NC H2SW 1996110700287 19961107 00287 SW 1996 11 7 96ZZZX5514 1 19960903 G 6230 2106010335001 LEVER ASSY 206010350021 BELL 206 206L3 1182108 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 187AL 364 51135 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10 1 BEARING. SUBMITTER STATED NORMAL USE CAUSED PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 363.9. 1 G 7 1 3U H2SW 1996110700288 19961107 00288 SW 1996 11 7 96ZZZX5515 1 19960903 G 6230 206010335001 LEVER ASSY 206010350021 BELL 206 206L1 1182107 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 27554 400 45246 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10 1 BEARING. SUBMITTER STATED NORMAL USE CAUSED PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 399.7. 1 G 7 1 3U H2SW 1996110700289 19961107 00289 SW 1996 11 7 96ZZZX5516 1 19960903 G 6230 206010335001 LEVER ASSY 206010350021 BELL 206 206L1 1182107 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 2762D 791 45280 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10 1 BEARING. SUBMITTER STATED NORMAL USE CAUSED PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 790.7 1 G 7 1 3U H2SW 1996110700290 19961107 00290 SW 1996 11 7 96ZZZX5517 1 19960917 G 6230 206010335001 LEVER ASSY 206010350021 BELL 206 206L1 1182107 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 3186P 430 45776 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10 1 BEARING. SUBMITTER STATED NORMAL USE CAUSED PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 429.5. 1 G 7 1 3U H2SW 1996110700291 19961107 00291 SW 1996 11 7 96ZZZX5518 1 19960815 G 6230 206010335001 LEVER ASSY 206010350021 BELL 206 206L3 1182108 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 350AL 462 51429 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10 1 BEARING. SUBMITTER STATED NORMAL USE CAUSED PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 461.9. 1 G 7 1 3U H2SW 1996110700292 19961107 00292 SW 1996 11 7 96ZZZX5519 1 19960815 G 6230 206010336005 LINK IDLER 206010350021 BELL 206 206L3 1182108 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 350AL 462 51429 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10 1 BEARING. SUBMITTER STATED NORMAL USE CAUSED PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 461.9 1 G 7 1 3U H2SW 1996110700293 19961107 00293 SW 1996 11 7 96ZZZX5520 1 19960917 G 6230 206010335001 LEVER ASSY 206010350021 BELL 206 206L3 1182108 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 351AL 593 51431 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10 1 BEARING. SUBMITTER STATED NORMAL USE CAUSED PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 593.3. 1 G 7 1 3U H2SW 1996110700294 19961107 00294 SW 1996 11 7 96ZZZX5521 1 19960903 G 6230 206010335001 LEVER ASSY 206010350021 BELL 206 206L3 1182108 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 367AL 452 51443 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10 1 BEARING. SUBMITTER STATED NORMAL USE CAUSED PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 451.7. 1 G 7 1 3U H2SW 1996110700295 19961107 00295 NE 1996 11 7 96ZZZX5522 1 19960815 G 5531 7620205002108 RIB SKRSKY S76 S76A 8143006 NE VERT PYLON CRACKED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 376AL 760002 MAJOR INSPECTION, VERTICAL PYLON RIB CORRODED INNER GRANULAR, CRACKED, NORMAL WEAR AND TEAR. 1 G 7 2 3U H1NE 1996110700296 19961107 00296 NE 1996 11 7 96ZZZX5523 1 19960815 G 5530 7620204002101 SHEAR DECK SKRSKY S76 S76A 8143006 NE VERT PYLON CRACKED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 376AL 760002 MAJOR INSPECTION, FOUND VERTICAL PYLON SHEAR DECK CRACKED, NORMAL WEAR AND TEAR. 1 G 7 2 3U H1NE 1996110700297 19961107 00297 NE 1996 11 7 96ZZZX5524 1 19960815 G 5530 7620204011120 FITTING SKRSKY S76 S76A 8143006 NE VERT PYLON DEFECTIVE B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 376AL 760002 MAJOR INSPECTION, VERT PYLON FITTING BOLT HOLE DIAMETER BEYOND LIMITS. NORMAL WEAR AND TEAR. 1 G 7 2 3U H1NE 1996110700298 19961107 00298 NE 1996 11 7 96ZZZX5525 1 19960815 G 5530 7608020046102 ANGLE SKRSKY S76 S76A 8143006 NE VERT PYLON CORRODED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 376AL 760002 MAJOR IN SPECTION, FOUND VERT PYLON ANGLE CORRODED BEYOND LIMITS, IMPROPER CORROSION PREVENTION, INNER GRANULAR CORROSIO N, NORMAL WEAR AND TEAR. 1 G 7 2 3U H1NE 1996110700299 19961107 00299 NE 1996 11 7 96ZZZX5526 1 19960815 G 5530 7608020046101 ANGLE SKRSKY S76 S76A 8143006 NE VERT PYLON CORRODED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 376AL 760002 MAJOR INSPECTION, FOUND VERT PYLON LT ANGLE CORRODED BEYOND LIMITS, INNER GRANULAR CORROSION, NORMAL WEAR AND TEAR. 1 G 7 2 3U H1NE 1996110700300 19961107 00300 NE 1996 11 7 96ZZZX5527 1 19960815 G 5531 7620205002109 RIB SKRSKY S76 S76A 8143006 NE VERT PYLON CRACKED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 376AL 760002 MAJOR INSPECTION, FOUND VERT PYLON RIB CRACKED, NORMAL WEAR AND TEAR. 1 G 7 2 3U H1NE 1996110700301 19961107 00301 NE 1996 11 7 96ZZZX5528 1 19960815 G 5530 7620124010101 BULKHEAD SKRSKY S76 S76A 8143006 NE VERT PYLON CRACKED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 376AL 760002 MAJOR INSPECTION, FOUND VERT PYLON BULKHEAD CRACKED, NORMAL WEAR AND TEAR. 1 G 7 2 3U H1NE 1996110700302 19961107 00302 NE 1996 11 7 96ZZZX5529 1 19960815 G 5530 7620105002105 DOUBLER SKRSKY S76 S76A 8143006 NE VERT PYLON CRACKED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 376AL 760002 MAJOR INSPECTION, FOUND VERT PYLON DOUBLER CRACKED, NORMAL WEAR AND TEAR. 1 G 7 2 3U H1NE 1996020900018 19960209 00018 CE 1996 2 9 96ZZZX553 1 19960101 G 7110 55521106 SEAL 555211077 CESSNA 500 560CESSNA 2076750 CE LT INBD COWL CORROSION B BXSR K NONE O OTHER IN INSP/MAINT 1 EA 09 500UB 1613 5600052 OUTSIDE OF COWLING SHOWED THREE SMALL SPOTS OF CORROSION. FOUND THE SEAL ON THE INSIDE OF THE COWLING WAS HOLDING MOIST URE AND HAD CAUSED CORROSION TO PENETRATE ALL THE WAY THROUGH. 2 L 7 2 4F RT A22CE 1996110700303 19961107 00303 NE 1996 11 7 96ZZZX5530 1 19960815 G 5530 7620124009101 BULKHEAD SKRSKY S76 S76A 8143006 NE VERT PYLON CORRODED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 376AL 760002 MAJOR INSPECTION, FOUND VERT PYLON BULKHEAD CORRODED BEYOND LIMITS, INNER GRANULAR CORROSION, NORMAL WEAR AND TEAR. 1 G 7 2 3U H1NE 1996110700304 19961107 00304 NE 1996 11 7 96ZZZX5531 1 19960815 G 5530 7620105001112 WEB DOUBLER SKRSKY S76 S76A 8143006 NE VERT PYLON CRACKED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 376AL 760002 MAJOR INSPECTION, FOUND VERT PYLON WEB DOUBLER CORRODED AND CRACKED, NORMAL WEAR AND TEAR. 1 G 7 2 3U H1NE 1996110700305 19961107 00305 NE 1996 11 7 96ZZZX5532 1 19960815 G 5530 620105001101 WEB SKRSKY S76 S76A 8143006 NE VERT PYLON CRACKED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 376AL 760002 MAJOR INSPECTION, FOUND VERT PYLON WEB CORRODED AND CRACKED, NORMAL WEAR AND TEAR 1 G 7 2 3U H1NE 1996110700306 19961107 00306 NE 1996 11 7 96ZZZX5533 1 19960815 G 5530 7620105001104 CAP ANGLE SKRSKY S76 S76A 8143006 NE VERT PYLON CORRODED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 376AL 760002 MAJOR INSPECTION, FOUND VERT PYLON CAP ANGLE CORRODED BEYOND LIMITS, INNER GRANULAR CORROSION, IMPROPER CORROSION PREVEN TION, NORMAL WEAR AND TEAR. 1 G 7 2 3U H1NE 1996110700307 19961107 00307 EU 1996 11 7 96ZZZX5534 1 19960815 G 6230 350A37100206 STAR AEROSP AS355 AS355F1 8680810 EU SWASHPLATE BROKEN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 376E 1732 M2257 5213 REPAIR IN OVERHAUL SHOP FOUND SWASHPLATE NON-ROTATING STAR BRIDGES (PN 350A37-1 515-20) WORN THROUGH AND BROKEN. 1 G 7 2 3U H11EU 1996110700308 19961107 00308 SW 1996 11 7 96ZZZX5535 1 19960917 G 6230 206010335001 LEVER ASSY 206010350021 BELL 206 206B 1181511 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 42AL 707 918 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10 1 BEARING. SUBMITTER STATED NORMAL USE CAUSED PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 706.7. 1 G 7 1 3U H2SW 1996110700309 19961107 00309 SW 1996 11 7 96ZZZX5536 1 19960917 G 6230 206010336005 LINK IDLER 206010350021 BELL 206 206B 1181511 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 42AL 707 918 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10 1 BEARING. SUBMITTER STATED NORMAL USE CAUSED PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 706.7. 1 G 7 1 3U H2SW 1996110700310 19961107 00310 SW 1996 11 7 96ZZZX5537 1 19960815 G 6230 206010335001 LEVER ASSY 206010350021 BELL 206 206L1 1182107 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 5740L 506 45459 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10 1 BEARING. SUBMITTER STATED NORMAL USE CAUSED PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 505.9. 1 G 7 1 3U H2SW 1996110700311 19961107 00311 SW 1996 11 7 96ZZZX5538 1 19960815 G 6230 206010336005 LINK IDLER 206010350021 BELL 206 206L1 1182107 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 5740L 506 45459 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10 1 BEARING. SUBMITTER STATED NORMAL USE CAUSED PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 505.9. 1 G 7 1 3U H2SW 1996110700312 19961107 00312 GL 1996 11 7 96ZZZX5539 2 19960909 G 7250 23032264 NOZZLE 23035128 SKRSKY S76 S76 8143010 NE ALLSN 250C 250C30S 03013 GL OUTER BAND/WEB CRACKED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 702AL 4667 1448 X59426 760243 CAE890287S UPON MAJOR REPAIR OF TURBINE, FOUND WEB OF OUTER BAND SEEMS TO HAVE BEEN MACHINED BELOW SPECS AND REPLATED. THIS CAUSED A WEAK SPOT IN FLANGE OF NOZZLE THAT CRACKED AND WENT INTO BOTH BLADE TIP PATHS. NOZZLE IS TO BE SCRAPPED. ASSURE THA T PARENT METAL IS MACHINED BELOW SPECS. 1 G 7 2 3U 3 U H1NE E1GL 1996020900019 19960209 00019 CE 1996 2 9 96ZZZX554 1 19960105 G 3230 51410521 FORK BOLT CESSNA 402 402B 207590P CE LT MLG RETRACT ELONGATED HOLE D K NONE O OTHER IN INSP/MAINT 1 SW 19 3131K 1650 402B0248 DURING A ROUTINE INSPECTION, THE LEFT LANDING GEAR RETRACT LINKAGE HAD EXCESSIVE PLAY. INVESTIGATION REVEALED THE LEFT MAIN GEAR TORQUE TUBE FORK BOLT HOLE WAS SEVERELY ELONGATED. FORK BOLT IS COVERED UNDER AD 76-13-07 WHICH REQUIRES REPL ACEMENT AT 5,000 HOUR INTERVALS. THIS PART HAD BEEN REPLACED 1,650 HOURS PREVIOUSLY. SUSPECT ATTACH HOLE DRILLED OVERS IZE DURING MANUFACTURE. IMPROPER HEAT TREATMENT. SUBMITTER SUGGESTS MORE FREQUENT REPLACEMENT AND INSPECTION INTERVALS . 1 L 7 2 3O A7CE 1996110700313 19961107 00313 GL 1996 11 7 96ZZZX5540 1 19960607 G 6230 2816119 YOKE ENSTRM F28 F28F 3300412 GL SWASHPLATE CRACKED C L A PP0M K NONE O OTHER IN INSP/MAINT 1 WP 01 890JR 4393 1189488H 764 CRACKS FOUND BETWEEN CONTROL ROD AND UNIVERSAL YOKES. CRACK RUNS DOWN THE WEB BETWEEN BOTH AT 2 LOCATIONS. SUBMITTER S TATED THIS IS SECOND FOUND THIS MONTH. THE OTHER CRACKED SWASHPLATE IS S/N 11-897-88H WITH SIMILAR TIME IN SERVICE. CR ACKED SWASHPLATE YOKE REMOVED FROM SERVICE. NEW YOKE PURCHASED AND INSTALLED. 1 G 7 1 3O H1CE 1996110700466 19961107 00466 CE 1996 11 7 96ZZZX5544 1 19960905 G 3610 10138001313 VALVE BEECH 200 200BEECH 1152920 CE LT ENG FLOW CONT MALFUNCTION D K NONE O OTHER IN INSP/MAINT 1 SW 03 30PH 250 BB635 PILOT REPORTS WARM AIR INFLOW TO CABIN AT FLOOR VENTS AND AT EYEBALL VENTS AT GLARESHIELD. SHUTTING OFF LEFT SOURCE OF BLEED AIR, AIR FLOW RETURNS TO NORMAL TEMPERATURE. RIGHT SIDE TURNED OFF, AIR TEMP BECOMES EXCESSIVELY WARM. CHANGED P NEUMOSTAT, AIR-TO-AIR COOLER, ETC. CHECKED ENTIRE BLEED AIR SYSTEM, COULD NOT LOCATE DEFECT. DECIDED TO CHANGE LT FLOW CONTROL VALVE FOR TROUBLESHOOTING PURPOSES. PROBLEM WENT AWAY. ALSO NOTED LT ENGINE PARAMETERS MATCHED RT ENGINE MORE CLOSELY AFTER FLOW CONTROL VALVE WAS CHANGED. VALVE IN QUESTION WAS OPERATING NORMALLY EXCEPT FOR TEMP OF AIR GOING IN TO CABIN. 1 L 7 2 4T A24CE 1996110700467 19961107 00467 CE 1996 11 7 96ZZZX5545 1 19960711 G 5320 504300431183 INTERCOSTAL BEECH 100 A100 1152915 CE CABIN DOOR CRACKED D K NONE O OTHER IN INSP/MAINT 1 NE 03 4475W 9858 B208 THIS PART SUPPORTS THE AFT CABIN DOOR CABLE POST BRACKET (PN 50-430043-1259). OVERLOADING OF DOOR IS THE SUSPECT CAUSE. SUBMITTER SUGGESTS MANUFACTURING INTERCOSTAL FROM STRONGER MATERIAL. 1 L 7 2 3T A14CE 1996110700469 19961107 00469 1996 11 7 96ZZZX5547 1 19960917 G 6230 206010336005 DRIVE LINK M/R BEARINGS WORN B ZV1R K NONE O OTHER IN INSP/MAINT 1 SW 03 PLAY IN EXCESS OF .025 INCH AT TWO PLACES. SEE BELL MM L3 FIG 62.21. AT TEAR DOWN FOUND BEARINGS AND SPACES WORN. TOT AL TIME OF BEARINGS AND SPACERS LESS THAN 100 HOURS AND 1 YEAR SINCE REPLACED. REPLACED 4 EACH. 1996110700470 19961107 00470 GL 1996 11 7 96ZZZX5548 2 19961009 G 7230 23050833 MODULE AGUSTA A109 A109C 0260118 EU ALLSN 250C 250C20 03013 GL AXIAL COMP FOD DAMAGE H K NONE O OTHER IN INSP/MAINT 1 EU 01 109TW 683 15299 7650 CAE295180 DURING A ROUTINE 100-HOUR INSPECTION, FOD DAMAGE FOUND TO RT ENGINE AXIAL COMPRESSOR ROTORS AND STATOR VANES. UNABLE TO ESTABLISH EXACT SOURCE OF FOD. OPERATOR TO REVIEW CURRENTLY USED LANDING SITES. 1 G 7 2 3U 3 U H7EU E4CE 1996110700471 19961107 00471 NE 1996 11 7 96ZZZX5549 1 19960926 G 5302 7610205004110 PRESSURE PAD SKRSKY S76 S76A 8143006 NE T/R WRONG SIZE B EGRR K NONE W INADEQUATE Q C IN INSP/MAINT 1 EA 17 274TC 760274 PAD NORMAL THICKNESS IS .122 INCH. DEFECTIVE ONE MEASURES .135 INCH CAUSING INCORRECT CLAMP UPON T/R SPAR. 1 G 7 2 3U H1NE 1996110700473 19961107 00473 SO 1996 11 7 96ZZZX5551 1 19961001 G 5730 83127002 SKIN PIPER PA46 PA46310P 7104605 SO LT WING ROOT CRACKED B S A MZER K NONE O OTHER IN INSP/MAINT 1 GL 15 286CM 1530 468608043 INSP OF LT AND RT WING FOUND SKIN CRACKED AT THE POINT WHERE BONDED STRINGER DOES NOT ATTACH TO INBOARD RIB. SKIN CRACK S AT THE .1875 INCH GAP BETWEEN STRINGER AND RIB. 1 L 7 1 3O A25SO 1996110700474 19961107 00474 SO 1996 11 7 96ZZZX5552 1 19961001 G 5730 83127003 SKIN PIPER PA46 PA46310P 7104605 SO RT WING ROOT CRACKED B MZER K NONE O OTHER IN INSP/MAINT 1 GL 15 286CM 1530 468608043 INSP OF LT AND RT WING FOUND SKIN CRACKED AT THE POINT WHERE BONDED STRINGER DOES NOT ATTACH TO INBOARD RIB. SKIN CRACK S AT THE .1875 INCH GAP BETWEEN STRINGER AND RIB. 1 L 7 1 3O A25SO 1996110700475 19961107 00475 1996 11 7 96ZZZX5553 1 19961024 G 2140 45C40 COMBUSTION TUBE JANITROL D83A28 HEATER BLOWN OUT D P A K NONE O OTHER IN INSP/MAINT 1 SO 09 7650194 COMBUSTION TUBE REMOVED FROM D83A28 JANITROL HEATER, MODEL NR S-50. OUTSIDE SKIN OF COMBUSTION TUBE BLOWN THROUGH AT CR OSS-OVER PORT LOCATIONS. SUSPECT CAUSE IS DUE TO LACK OF MAINTENANCE AND NOT BEING OVERHAULED AT RECOMMENDED INTERVALS. THESE TUBES ARE INSTALLED IN BEECHCRAFT A55, B55, 56TC AIRCRAFT. SUBMITTER STATED TO PREVENT THESE OCCURRENCES, AN AD WOULD BE REQUIRED. THESE HEATERS ARE NOT BEING TAKEN CARE OF PER THE JANITROL AND BEECHCRAFT SM'S. PRESSURE DECAY TES TING WOULD FIND THE BAD TUBES. 1996110700476 19961107 00476 CE 1996 11 7 96ZZZX5554 1 19961023 G 3213 51411036 TRUNNION ASSY CESSNA 421 421C 2076016 CE RT MLG CRACKED B S HLFR K NONE O OTHER IN INSP/MAINT 1 SW 17 148MA 5129 421C0078 INSP FOUND RT MLG TRUNNION ASSY UPPER BARREL CRACKED. 1 L 7 2 3O A7CE 1996110700477 19961107 00477 1996 11 7 96ZZZX5555 4 19961014 G 6113 15573005 BULKHEAD CESSNA 337 337G 2075730 CE SPINNER DEFECTIVE D K NONE W INADEQUATE Q C IN INSP/MAINT 1 EA 11 31ME 33701524 SPINNER BULKHEAD RECEIVED FORM CESSNA WITH HEAVY TOOL MARKS IN THE RADIUS OF THE INNER FLANGE. THE MOUNTING BOLT HOLES DO NOT LINE UP BETWEEN THE FLANGE AND FLANGE DOUBLER. ALSO, DEEP SANDING MARKS AT BOLT HOLE AREA AND UNDER AND AROUND R IVET BUCK TAILS OF FLANGE DOUBLER. 1 H 7 2 3O A6CE 1996110700478 19961107 00478 SO 1996 11 7 96ZZZX5556 2 19961025 G 8530 631521 SPRING CESSNA 402 402B 207590P CE CONT O520 TSIO520EB 17040 SO INT VALVE BROKEN D L K NONE O OTHER IN INSP/MAINT 1 GL 23 33NC 402B0825 271359R DURING A ROUTINE COMP CHECK, NR 6 CYL WAS NOTED TO HAVE LOW COMP. THE ROCKER COVER WAS REMOVED TO STACK VALVE. AT THAT POINT, IT WAS NOTED THAT THE INT VALVE SPRING WAS BROKEN. THE ADJACENT ROCKER WAS THEN REMOVED AND ANOTHER SPRING WAS FOUND TO BE BROKEN AS WELL. AT THIS POINT, THE REMAINING COVERS WERE REMOVED AND SPRINGS WERE FOUND TO BE BROKEN ON ALL REMAINING CYLINDERS. 1 L 7 2 3O 3 O A7CE E8CE 1996110700479 19961107 00479 CE 1996 11 7 96ZZZX5557 1 19961010 G 2750 LIMIT SWITCH CESSNA 402 402C 207590R CE FLAP GEARBOX ARMS LOOSE H K NONE O OTHER IN INSP/MAINT 1 SW 01 402MQ 402C095 FLAPS FOUND HANGING DOWN APROXIMATELY 1 INCH AT INSPECTION. DISCOVERED FLAP GEARBOX LIMIT SWITCH ACTUATING ARM LOOSE ON SHAFT. FLAP PRE-SELECT SWITCH FAILED AND FLAPS DID NOT STOP. REPLACED BENT PUSH/PULL TUBES AND GEARBOX RIGGED AND OPS CHECKED SYSTEM. 1 L 7 2 3O A7CE 1996110700480 19961107 00480 CE 1996 11 7 96ZZZX5558 1 19961001 G 3230 368200113 RETRACT TUBE BEECH 36 A36 1151604 CE NLG RETRACT FAILED D O OTHER O OTHER LD LANDING 1 SW 11 47KA 5341 E530 DURING ROLL-OUT AFTER NORMAL LANDING, THE NLG COLLAPSED. FURTHER INVESTIGATION REVEALED THE AFT NOSE GEAR RETRACT ROD H AD FAILED AT A POINT APPROXIMATELY 1 INCH ONTO THE THREADED PORTION OF THE ROD WHERE P/N ARHT5ECR ROD END THREADS ENDED IN THE ROD. 1 L 7 1 3O 3A15 1996110700481 19961107 00481 SO 1996 11 7 96ZZZX5559 2 19961022 G 8530 653446A11 CYLINDER CESSNA 210 T210N 2073456 CE CONT O520 TSIO520R 17040 SO NR 2 BROKEN D A UNSCHED LANDING O OTHER CL CLIMB 1 NM 11 4856U 1470 21064825 517396 AFTER DEPARTURE, THE PILOT RETURNED AND LANDED DUE TO AN UNUSUAL NOISE FROM THE ENGINE. HE STATED THAT HE BELIEVED THE EXHAUST SYSTEM HAD PROBABLY BROKEN. UPON INVESTIGATION OF THE ENGINE, DISCOVERED THE NR 2 CYL HAD CRACKED 3/4 OF THE WA Y AROUND THE CIRCUMFERENCE OF THE COMBUSTION CHAMBER. COMBUSTION PRESSURE AND EXH GAS BURNED A HOLE THROUGH THE COOLING FINS OF THE NR 4 CYL. COMBUSTION GAS EXITING THE BROKEN CYL WAS DIRECTED ON TO THE STAINLESS STEEL FUEL INJECTION NOZZ LE LINE. CONTINUED FLIGHT AND WOULD MOST PROBABLY HAVE RESULTED IN AN ENGINE FIRE. 1 H 7 1 3O 3 O 3A21 E8CE 1996110700482 19961107 00482 SO 1996 11 7 96ZZZX5560 2 19961004 G 7313 633723019A INJECTOR CESSNA 421 421B 2076014 CE CONT O520 GTSIO520H 17032 SO NR 3 CYLINDER MISDRILLED B S EVCR K NONE W INADEQUATE Q C IN INSP/MAINT 1 CE 03 915DW 846 421B0914 634835R WHILE PERFORMING REPAIR IN ADJACENT AREA, FUEL STAINS WERE NOTED AT NR 3 CYLINDER INJECTOR WHERE IT THREADS INTO CYLINDE R HEAD. WHILE REMOVING THE INJECTOR, IT BROKE OFF AT THREADS. FURTHER INSP OF INJECTOR REVEALED THE ORIFICE IN THE OUTL ET OF THE INJECTOR IS DRILLED OFF-CENTER. SUBMITTER STATED FAILURE OF INJECTOR IN THIS AREA IS POTENTIALLY CATASTROPHIC DUE TO RAW FUEL LEAKING OVER THE TOP OF THE ENGINE. INJECTORS SHOULD BE INSP CLOSELY WHEN CLEANED OR AFTER RECEIVING FR OM OVERHAUL FACILITY. 1 L 7 2 3O 3 O A7CE E7CE 1996110700483 19961107 00483 SO 1996 11 7 96ZZZX5561 2 19961001 G 8530 537750 BOLT CESSNA 421 421C 2076016 CE CONT O520 GTSIO520L 17032 SO NR 4 CYL EXH RKR FAILED D E ENGINE SHUTDOWN E R K VIBRATION/BUFFET PARTIAL RPM/PWR LOSS FLUID LOSS NR NOT REPORTED 1 WP 17 98PJ 421C0824 272345R NR 4 CYLINDER ROCKER SHAFT BOLTS BROKE. LOOSE ROCKER PUNCHED A HOLE THROUGH VALVE COVER. ROUGH RUNNING AND SMOKE IS REA SON FOR IN-FLIGHT SHUT DOWN. 1 L 7 2 3O 3 O A7CE E7CE 1996110700485 19961107 00485 1996 11 7 96ZZZX5562 4 19961001 G 3457 GPS90 YOKE MOUNT GARMIN INTL PIPER PA24 PA24260 7102406 SO POWER WIRE FOULS YOKE D P A O OTHER F FLT CONT AFFECTED AP APPROACH 1 GL 15 9137P 244618 YOKE MOUNT CLAMP INSTALLED BY OWNER GOT FOULED IN THE POWER WIRE TO PORTABLE GPS. RESTRICTED YOKE MOVEMENT. PILOT MAKE HARD LANDING. WIRE FINALLY BROKE IN TWO ALLOWING A/C TO BE 'FLARED'. PILOTS SHOULD BE MADE AWARE TO CHECK YOKE MOVEME NT ON PRE-FLIGHT. YOKE MODIFIED WITH CURLEY CORD TO PREVENT RECURRENCE. 1 L 7 1 3O 1A15 1996110700486 19961107 00486 GL 1996 11 7 96ZZZX5563 2 19960831 G 7230 9380M28P05 SPOOL GE CF6 CF680C GL 3-9 HPC CRACKED H L K NONE O OTHER IN INSP/MAINT 1 EU 01 16197 VOLO3872 31X95154 THE HPC 3-9 SPOOL IS REJECTED DUE TO CRACK INDICATION PER SB 72-812. INDICATION IS LOCATED ON STAGE 9 FORWARD FACE APPR OXIMATELY 0.170 INCH FROM OUTSIDE DIAMETER AND APPROX 220 DEGREES FROM SERIAL NUMBER. INDICATION HAS A DEPTH OF 0.030 I NCH AND DISPLAYS AN AMPLITUDE OF 50 PERCENT FSII AT 2416 DB. THE SURFACED AREA AROUND THE INDICATION EXHIBITED A RIPPLE EFFECT ON INITIAL INSPECTION. THE SURFACE WAS BLENDED TO A SMOOTH FINISH AND RE-INSPECTED WITH NO CHANGE TO THE INDICA TION AMPLITUDE. 4 F E23EA 1996110700487 19961107 00487 WP 1996 11 7 96ZZZX5564 1 19961001 G 2410 696747B SUPPORT SUNDSTRANDEM 696233B DOUG DC9 DC9 3022002 WP CSD MISINSTALLED B KQ4R K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 17 D529 5 EA BOLTS USED TO MOUNT THE GOVERNOR SUPPORT ASSY TO THE OUTPUT HOUSING WERE SAFETY WIRED TOGETHER. THIS PRACTICE IS N OT SPECIFIED IN THE OEM MANUAL. 2 L 7 2 4F A6WE 1996110700488 19961107 00488 SO 1996 11 7 96ZZZX5565 1 19961010 G 3230 400235 BOLT PIPER PA23 PA23250 7102308 SO NLG DRAG LINK BROKEN D L O OTHER J WARNING INDICATION TX TAXI/GRND HDL 1 EA 23 2556Z 8500 278054048 ACFT IS USED IN A PART 135 CHARTER OPERATION. THE ACFT WAS RETURNING WITH ONE PILOT AND ONE PAX ABOARD. THE ACFT MADE A NORMAL LANDING AND ROLL-OUT, HOWEVER, WHILE TAXIING TO PARKING THE LANDING GEAR UNSAFE HORN BECAME AUDIBLE AND THE PIL OT NOTICED THE NLG (DOWN AND LOCKED) GREEN LIGHT INDICATOR WAS NOT LIGHTED. THE ACFT WAS STOPPED IMMEDIATELY AND SHUT-D OWN. AN INITIAL INSP BY A MECH REVEALED THAT THE BOLT SECURING THE UPPER DRAG LINK TO THE AIRFRAME WAS CRACKED AND PART IALLY SHIFTED FROM ITS ORIGINAL LOCATION. THE ATTACH FITTINGS WHICH CONNECT THE UPPER DRAG LINK TO THE AIRFRAME WERE CR ACKED AND PARTIALLY TWISTED FROM ORIGINAL POSITION. 1 L 7 2 3O 1A10 1996110700489 19961107 00489 WP 1996 11 7 96ZZZX5566 1 19961001 G 2410 695855 DISCONNECT CLAMP SUNDSTRANDEM 696233B DOUG DC9 DC9 3022002 WP CSD WRONG PART B KQ4R K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 17 1526 BOLT USED TO CONNECT CLAMP ON DISCONNECT PLUNGER SHAFT PROTRUDES .5 INCH INTO CAVITY. OEM MANUAL SPECIFIES NAS1352-3-8, FOUND DASH 12 TO BE INSTALLED IN UNIT. 2 L 7 2 4F A6WE 1996110700490 19961107 00490 SW 1996 11 7 96ZZZX5567 1 19961023 G 7922 53E19600 VALVE MOONEY M20 M20J 5870219 SW THERMO BYPASS FAILED D L A UNSCHED LANDING M OVER TEMP CR CRUISE 1 WP 25 1148N 340 241208 20 MINUTES INTO A FLT, THE OIL TEMP WENT FULL HOT. A CROSS CHECK OF INSTRUMENTS REVEALED ALL CYL TEMPERATURES NORMAL. T HERE WAS NO LOSS OF ENG POWER, HOWEVER, OIL PRESS WAS LOWER THAN NORMAL. THE ONLY WAY TO LOWER THE OIL TEMP WAS TO REDU CE POWER AND PUT THE AIRCRAFT INTO A GLIDE. RETURN TO THE AIRPORT WAS MADE. THE VERNATHERM VLV WAS REMOVED AND UPON CH ECKING IT IN HOT WATER, FOUND TO BE DEFECTIVE. 1 L 7 1 3O 2A3 1996110700491 19961107 00491 CE 1996 11 7 96ZZZX5568 1 19960402 G 3020 10191012323 ICE VANE DOOR 10191011215 BEECH 300 300BEECH 1152930 CE LT COWL BROKEN D S A K NONE O OTHER IN INSP/MAINT 1 NE 05 250PD FA33 UPON INSPECTION OF AIRCRAFT (150 HR 2ND INTERIM) LEFT COWL FWD LOWER ICE VANE DOOR OUTER EDGE (4 INCH BY 8 INCH) FOUND M ISSING FROM ASSEMBLY. LEFT ENGINE 1ST STAGE COMPRESSOR INSPECTED FOR FOD. ONE BLADE FOUND LEADING EDGE BENT AND TORN R EQUIRING ENGINE TEAR DOWN AND REPAIR OF FOD PER P & W MM 3034342. ON FURTHER INSPECTION, ICE VANE DOOR ON RT COWL FOUND CRACKING IN SAME AREA. ICE VANE AFT BLOCKER DOOR (PN 101-910124-51). ALSO FOUND CRACKING ON LT/RT COWLS. RECOMMEND D OOR 'BOND ASSEMBLY' MADE THICKER WHERE ACTUATOR BRACKETS ARE ATTACHED. 2 L 7 2 4T A24CE 1996110700492 19961107 00492 CE 1996 11 7 96ZZZX5569 1 19961010 G 2750 CONTROL CABLE CESSNA 402 402C 207590R CE RT FLAP RETURN FRAYED H K NONE O OTHER IN INSP/MAINT 1 SW 01 5820C 402C0047 DURING INSPECTION RIGHT HAND FLAP RETURN CABLE WAS FOUND FRAYED. SEVERAL STRANDS BROKEN AT A PULLEY. REPLACED CABLE, R IGGED PER MM. SUGGEST CLOSE INSPECTION OF CABLES AT PULLEYS. 1 L 7 2 3O A7CE 1996110700493 19961107 00493 EU 1996 11 7 96ZZZX5570 1 19961001 G 2422 ASH6641PF INVERTER BRAERO DH125 BAE125800A 1500285 EU INST AC SYS FAILED C A K NONE B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 EA 17 600J 1267 MJ870M NA0470 INVERTER OUTPUT RAN UNDER VOLTAGE AND UNDER FREQ AND SUBSEQUENTLY THE UNIT BURNED, CAUSING DUAL ALTIMETER FAILURES. SUB MITTER STATED THIS FAILURE TOOK PLACE ON FEBRUARY 24, 1996 AND AS OF OCTOBER 14, 1996 NO CORRECTIVE ACTION FROM THE COMP ONENT MANUFACTURER OR THE ARIFRAME MANUFACTURER HAS BEEN BROUGHT FWD. THIS IS THE SECOND FAILURE OF THIS TYPE ON A 125- 800. 2 L 7 2 4F RT A3EU 1996110700494 19961107 00494 SO 1996 11 7 96ZZZX5571 1 19961022 G 3213 452838 BUSHING 8360503 PIPER PA46 PA46350P SO RT MLG WORN D L A K NONE O OTHER IN INSP/MAINT 1 NM 11 711BL 322 4622175 DURING AN ANNUAL INSPECTION, VERTICAL FREE PLAY OF THE RIGHT MAIN LANDING GEAR TRUNNION PIN TO BUSHING TO PIN CLEARANCE MEASURED .025 INCH GREATER THAN THE LEFT MAIN LANDING GEAR. NO TOLERANCE FOR VERTICAL MOVEMENT COULD BE FOUND IN THE AI RCRAFT MANUFACTURERS SM. A NEW FORWARD AND AFT BUSHING WERE ORDERED AND RECEIVED FROM THE MANUFACTURER. WHEN THE SM WA S AGAIN PERUSED FOR A BUSHING REPLACEMENT PROCEDURE, NONE WAS FOUND. THE AIRCRAFT MANUFACTURER'S ENGINEERING DEPARTMENT WAS CONSULTED FOR A PROCEDURE. ENGINEERING INFORMED US THAT THEY HAD NOT ANTICIPATED THAT REPLACEMENT OF THE BUSHING W OULD EVER BE REQUIRED, AND THEREFORE HAD NO PROCEDURE AVAILABLE. 1 L 7 1 3O RT A25SO 1996110700495 19961107 00495 CE 1996 11 7 96ZZZX5572 1 19961010 G 3010 2H598 FLOW VALVE CESSNA 402 402C 207590R CE LT WING DEICE STICKING H K NONE O OTHER NR NOT REPORTED 1 SW 01 747WS 402C0080 WING DEICE BOOTS DID NOT FULLY DEFLATE AFTER NORMAL CYCLE. LEFT FLOW VALVE STUCK PARTIALLY OPEN. INSTALLED NEW VALVE. OPS CHECKED NORMAL. 1 L 7 2 3O A7CE 1996020900023 19960209 00023 1996 2 9 96ZZZX558 4 19960117 G 3452 6221270001 TRANSPONDER COLLINS CESSNA 650 650 2076802 CE NR 2 FAILED D K NONE O OTHER IN INSP/MAINT 1 NM 01 39WP 511 6500039 REINSTALLED ADC AFTER MOD STATUS UPGRADE AND CERTIFICATION. WHILE COMPLYING WITH CFR SECTION 91.411/91.413 FUNCTION TES T, NOTED NR 2 TRANSPONDER ALTITUDE READ-OUT WAS INVALID FROM 500 FEET TO 1,000 FEET AND AT EACH ASCENDING 500 FOOT INCRE MENT TO THE NEXT THOUSAND. IN DESCENDING ALTITUDE TESTS, THE NR 2 TRANSPONDER READ INVALID FROM EACH 1,000 FOOT ALTITUD E READING THROUGH EACH 500 FOOT ALTITUDE LEVEL. REMOVED AND REPLACED TRANSPONDER AND REQUESTED SHOP BENCH REPORT ON FIN DINGS. 2 L 7 2 4F A9NM 1996110700704 19961107 00704 SW 1996 11 7 96ZZZX5582 1 19960917 G 6230 206010335001 LEVER ASSY 206010350021 BELL 206 206L1 1182107 SW SPACERS/BUSHINGS WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 1075W 296 45377 DAILY INSPECTION FOUND BEARINGS AND SPACERS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 SP ACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH NAS6605D64 BOLTS. NORMAL WEAR CAUSES PARTS TO WEAR OUT TOO SOON. WORN P ARTS TT 296.2. 1 G 7 1 3U H2SW 1996111400298 19961114 00298 CE 1996 11 14 96ZZZX5584 1 19961008 G 3240 61706917 CONTROL CABLE CESSNA 501 501 2076603 CE PARK BRAKE FAILED D K NONE O OTHER NR NOT REPORTED 1 CE 09 101RR 4186 5010241 WHEN THE PILOT ATTEMPTED TO SET THE PARK BRAKE, THE ATTEMPT PULLED THE KNOB AN D APPROXIMATELY 18 INCHES OF CABLE FROM T HE HOUSING. 1 L 7 2 4F A27CE 1996111400299 19961114 00299 EA 1996 11 14 96ZZZX5585 1 19961027 G 3411 601A51631 MANIFOLD CNDAIR CL600 CL6002B16 1900305 EA STATIC SYSTEM MISINSTALLED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 NE 03 612CC 5186 CREW COMPLAINED OF EXCESSIVE ALTIMETER SPLITS AT ALTITUDE. FOUND STATIC MANIFOLD (TIE POINT OF ALL 3 STATIC SYSTEMS) MO UNTED BACKWARDS. FOUND THE ARROW INDICATING FWD 180 DEGREES OUT. 2 L 7 2 4F RT A21EA 1996111400300 19961114 00300 1996 11 14 96ZZZX5586 4 19961025 G 2562 DMU1581 BATTERY PACK DORNEMARGLN ELT1411 LEAR 60 60LEAR 5170707 CE ELT FAULTY D K NONE O OTHER IN INSP/MAINT 1 NM 11 618R 656 1053A 044 DURING A SCHEDULED ELT FUNCTIONAL CHECK, THERE WAS NO DOWNWARD SWEEPING TONE. DURING THE TROUBLESHOOTING OF THE ELT, IT WAS FOUND THAT THE BATTERY PACK WAS AT 6.8 VOLTS. (SUPPOSED TO BE 9 VOLTS). THE REPLACE ON/OR BEFORE DATE IS FEB '97. DATE OF INSTALL WAS JAN '95. 2 L 7 2 4F RT A10CE 1996111400301 19961114 00301 CE 1996 11 14 96ZZZX5587 1 19961025 G 5712 57222061 RIB CESSNA 441 441 2076020 CE RT WING CRACK B WTXR K NONE O OTHER IN INSP/MAINT 1 NM 07 81WS 4724 4410181 DURING A PHASE INSPECTION, FOUND A 1.5 INCH CRACK IN RT WING CANTED RIB TOP CAP. CRACK STARTS AT AFT SIDE OF FWD WING S PAR AND RUNS AFT PARALLEL TO THE BEND RADIUS. STOP DRILLED CRACK PER CESSNA INSTRUCTIONS. 1 L 7 2 3T RT A28CE 1996111400302 19961114 00302 GL 1996 11 14 96ZZZX5588 2 19961025 G 7320 23033400 FILTER ELEMENT BELL 206 206L3 1182108 SW ALLSN 250C 250C30P 03013 GL FCU PC FILTER CRACKED H K NONE O OTHER IN INSP/MAINT 1 NM 11 937S 3271 51258 CAE895318 FILTER ELEMENT CRACKED WHERE END CAP IS ATTACHED TO ELEMENT. SOME PIN HOLES AND CORROSION AROUND FILTER TO END CAP BOND . ELEMENT MAY HAVE BEEN FROM ENGINE OPERATED IN SALT LADEN ATMOSPHERE AND INSTALLED WHEN ENGINE WAS TORN DOWN FOR INSPE CTION BY OUTSIDE VENDOR. RECOMMEND INSP WITH 10X MAGNIFYING GLASS EACH INSP INTERVAL. 1 G 7 1 3U 3 U H2SW E1GL 1996111400303 19961114 00303 CE 1996 11 14 96ZZZX5589 1 19961017 G 5347 870106 SAF T STOP CESSNA 172 172M 2072418 CE SEAT RAIL STOP MISUSE D K NONE W INADEQUATE Q C IN INSP/MAINT 1 CE 07 THE SAF-T-STOP ITSELF IS NOT THE PROBLEM. IT IS THE WAY IT IS INSTALLED ON SEAT RAILS. OWNERS AND OPERATORS ARE USING THE SAF-T-STOP FOR PRIMARY SEAT STOPS EVEN THOUGH INSTRUCTIONS STATE OTHERWISE. SUBMITTER STATES ONLY FIX IS TO REMOVE PRODUCT FROM SERVICE. 1 H 7 1 3O NT 3A12 1996111400304 19961114 00304 CE 1996 11 14 96ZZZX5590 1 19961008 G 2121 BC61A9012 BLOWER CESSNA 501 501 2076603 CE CABIN FAILED D K NONE O OTHER CR CRUISE 1 CE 09 101RR 1 5010241 THE CABIN BLOWER ASSY WAS INSTALLED AND CHECKED FOR OPERATION. LESS THAN AN HOUR INTO THE NEXT FLIGHT, THE BLOWER FAILE D. WHEN THE BLOWER WAS EXAMINED, THE ELECTRICAL LEADS COULD BE FELT CONTACTING THE ARMATURE WHEN THE BLOWER WAS TURNED. THE ASSY WAS NOT DISASSEMBLED DUE TO WARRANTY CONSIDERATIONS. 1 L 7 2 4F A27CE 1996111400305 19961114 00305 1996 11 14 96ZZZX5591 1 19961021 G 7100 4914 FITTING AEROQUIP HOSE BROKE D K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 11 PART OF FITTING THAT GOES INSIDE 303 HOSE BROKE BEFORE IT WAS SCREWED ALL THE WAY IN. IT WAS NOT CROSS-THREADED. IT BR OKE AT THE END OF THE THREADS. THREE FITTINGS BROKE IN A ROW. ALL AEROQUIP FITTING TAGS WERE HAND WRITTEN 491-4. DIAM ETER OF BREAK .253 INCH. FITTINGS WERE PURCHASED FROM AUSCO COLLEGE PARK, GA. 1996111400306 19961114 00306 EA 1996 11 14 96ZZZX5592 2 19961025 G 7310 883410000600094 HOSE DEUTSCH CESSNA 177 177 2073704 CE LYC O360 O360A1F6 41514 EA PUMP TO CARB LEAK H K NONE K FLUID LOSS IN INSP/MAINT 1 NM 11 19974 30 17702617 NOTICED FUEL STAIN ON STEEL BRAID HOSE. REMOVED AND TESTED. FOUND SEEP HOLE. NOTIFIED SUPPLIER AND SENT FOR FACTORY I NSPECTION. (SEEP WAS DETECTABLE WITH SHOP AIR AND SOAPY WATER.) 1 H 7 1 3O 3 O NT A13CE E286 1996111400307 19961114 00307 NE 1996 11 14 96ZZZX5593 2 19960718 G 8520 VALVE SCWZER G164 G164A 3952704 EA PWA R985 R985AN14B 52008 NE NR 4 EXH STRETCHED D A UNSCHED LANDING E R K VIBRATION/BUFFET PARTIAL RPM/PWR LOSS FLUID LOSS AG AGRICULTURE 1 NM 04 5291 624 572 JP205327 DURING SPRAY APPLICATION, CYLINDER HOLD-DOWN STUDS SHEARED 8 OF 10. THE CYLINDER CAME LOOSE RESULTING IN LOSS OF POWER AND FORCED PRECAUTIONARY LANDING. NO RECOMMENDATION. 1 Q 7 1 3R 3 R 1A16 5E1 1996111400308 19961114 00308 GL 1996 11 14 96ZZZX5594 3 19961015 G 6111 S84B BLADE MCAULY 2A36C 2A36C23 GL THREADS CRACKED B DJFR K NONE K FLUID LOSS IN INSP/MAINT 1 EA 23 676355 FOUND RED DYED OIL LEAK NR 2 BLADE. DISASSEMBLED PROP, REMOVED FERRULE, FOUND CRACK IN BLADE THREADS. 5 C P880 1996111400309 19961114 00309 CE 1996 11 14 96ZZZX5595 1 19960628 G 3213 NAS50200 SNAP RING BEECH 35 J35 1151522 CE LT MLG STRUT DISENGAGED D L K NONE O OTHER IN INSP/MAINT 1 NM 04 3029C 3187 D5694 THE SNAP RING DISENGAGED FROM THE GROOVE IN THE LT MLG STRUT WHICH ALLOWED THE END PLUG P/N 45-815224 TO BE EXPELLED WIT H GREAT FORCE THROUGH THE TOP OF THE WING WHILE THE AIRCRAFT WAS PARKED ON THE RAMP. MANUFACTURER'S TECH SUPPORT INDICA TES 3 POSSIBLE REASONS THE SNAP RING CAN BE DISLOGED. 1. THE WRONG PART NUMBER SNAP RING. 2. THE SNAP RING WAS INSTA LLED UPSIDE DOWN, I.E., THE BEVELED SIDE UP. 3. THE SNAP RING WAS DISTORTED WHEN IT WAS INSTALLED, ALL OF WHICH CAN BE LAID AT THE FAULT OF THE MAINTENANCE FACILITY THAT LAST INSTALLED THE SNAP RING. ACCORDING TO THE AIRCRAFT RECORDS THE STRUT WAS SERVICED 49.6 HOURS. 1 L 7 1 3O 3A15 1996111400310 19961114 00310 CE 1996 11 14 96ZZZX5596 1 19961001 G 5311 12124139 FRAME CESSNA 210 P210N 2073454 CE FS 166.40 CRACKED B JZRR K NONE O OTHER IN INSP/MAINT 1 EA 07 40RC 6995 P21000261 REMOVED ANTENNA FROM TOP OF TAILCONE, FOUND CRACKS IN SKINS P/N 1210504-4 AND P/N 1210504-6. FURTHER INVESTIGATION REVE ALED REPAIRED BULKHEAD. PREVIOUSLY INSTALLED REPAIR AND SKIN DOUBLER FOUND CRACKED AS WELL. POOR LOCATION FOR ANTENNA INSTALLATION DUE TO LIGHT STRUCTURE. CONTRIBUTING WAS POOR QUALITY OF REPAIR TO BULKHEAD AND SKIN DOUBLER. 1 H 7 1 3O 3A21 1996111400311 19961114 00311 NM 1996 11 14 96ZZZX5597 1 19961001 G 5711 11121460 SPAR UNIVAR 108 1083 9230408 NM LT WING FORE CORRODED D L K NONE O OTHER IN INSP/MAINT 1 NM 04 6093M 1084093 INSPECTION OF LT WING AFTER INCIDENCE OF STORM DAMAGE TO TIP BOW, FOUND HEAVY CORROSION TO BOTH SPARS. RT WING WAS THEN INSPECTED AND SPAR CORROSION WAS ALSO FOUND. LT WING CORROSION WAS ACCELERATED BY A LARGE BIRD NEST INSIDE. REPLACED SPARS WITH NEW. 1 H 7 1 3O A767 1996111400312 19961114 00312 NM 1996 11 14 96ZZZX5598 1 19961001 G 5711 11121470 SPAR UNIVAR 108 1083 9230408 NM LT WING AFT CORRODED D K NONE O OTHER IN INSP/MAINT 1 NM 04 6093M 1084093 INSPECTION OF LT WING AFTER INCIDENCE OF STORM DAMAGE TO TIP BOW, FOUND HEAVY CORROSION TO BOTH SPARS. RT WING WAS THEN INSPECTED AND SPAR CORROSION WAS ALSO FOUND. LT WING CORROSION WAS ACCELERATED BY A LARGE BIRD NEST INSIDE. REPLACED SPARS WITH NEW. 1 H 7 1 3O A767 1996111400313 19961114 00313 CE 1996 11 14 96ZZZX5599 1 19961024 G 2740 NAS314251411 CONTROL CABLE BEECH 23 C23 1151242 CE STABILATOR FRAYED B S A AKGR K NONE O OTHER IN INSP/MAINT 1 CE 05 6711C 5572 M2116 DURING ANNUAL INSPECTION, STABILATOR DOWN CABLE WAS FOUND FRAYED AT FORWARD PULLEY BEHIND FIRE WALL UNDER CONTROL COLUMN . SEVERAL STRANDS WERE BROKEN. REPLACED CABLE. SUGGEST CLOSE INSPECTION AT EACH ANNUAL INSPECTION. 1 L 7 1 3O A1CE 1996111400314 19961114 00314 CE 1996 11 14 96ZZZX5600 1 19961029 G 3245 15X6006 TUBE PARKERHANFIN 4090B CESSNA 414 414A 2075907 CE NLG STEM FAILED H O OTHER O OTHER LD LANDING 1 WP 13 4573V 414A0300 ON LANDING ROLL-OUT, NOSE TIRE DEFLATED. FENDER P/N 5042022-9 WAS TORN FROM THE NOSE GEAR ASSEMBLY. IT WAS DISCOVERED THE VALVE STEM WAS MISSING FROM THE NOSE TIRE. NOSE TIRE P/N 600-6-8-330 HAD BEEN REPLACED 8-10-95. THE TOTAL TIME ON THE TIRE SINCE REPLACEMENT 715.5 HRS. 1 L 7 2 3O A7CE 1996111400315 19961114 00315 CE 1996 11 14 96ZZZX5601 1 19961008 G 3231 12838002143 CONTROL CABLE MTSBSI MU300 MU300 5780602 CE MLG DR EMERG EXT FAILED B A PIQR K NONE O OTHER IN INSP/MAINT 1 EA 21 75BL 1988 1988 A017SA DURING ROUTINE A-CHECK INSPECTION WHILE PERFORMING EMERGENCY GEAR EXTENSION CHECK, RIGHT HAND GEAR DOOR WOULD NOT OPEN. INVESTIGATED DISCREPANCY AND FOUND SWAGED TERMINAL END ON DOOR CABLE BROKEN OFF. IN AN ACTUAL IN-FLIGHT EMERGENCY, THE RT MAIN LANDING GEAR WOULD NEVER EXTEND. 2 H 7 2 4F RT A14SW 1996111400317 19961114 00317 CE 1996 11 14 96ZZZX5603 1 19961101 G 8011 66082686 STARTER LEAR 35 35A 5170602 CE RT ENGINE DEFECTIVE D K NONE O OTHER IN INSP/MAINT 1 SO 11 815L 71 468U 142 STARTER VERY SLOW IN BRINGING ENGINE UP TO START SPEED. 2 L 7 2 4F A10CE 1996111400318 19961114 00318 CE 1996 11 14 96ZZZX5604 1 19961023 G 7620 MS924529 COTTER PIN 310281201 CESSNA 500 550 2076604 CE RT ENG NR 4 BRG WORN D A E A ENGINE SHUTDOWN UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CL CLIMB 1 EA 23 6846T 286 5500625 ON CLIMB-OUT AFTER TAKEOFF, RT ENGINE OIL TEMPERATURE BEGAN TO RISE AND PRESSURE BEGAN TO FALL. PILOT IMMEDIATELY SHUT DOWN RT ENGINE AND RETURNED TO AIRPORT WHERE AN UNEVENTFUL LANDING WAS MADE. LOSS OF ENGINE OIL WAS DISCOVERED TO BE CO MING FROM THE NR 4 BEARING HOUSING AREA. THE COTTER PINS HOLDING THE PIN FOR THE EMERGENCY FUEL SHUT-OFF LEVER ON THE N R 4 BEARING HOUSING HAD FAILED (WORN) ALLOWING THE LEVER PIN, LEVER, AND ACTUATOR ROD TO FALL OUT, WHICH ALLOWED OIL TO ESCAPE THROUGH THE ACTUATOR ROD HOLE. C/W SB7384R3 TO RECTIFY PROBLEM. SUBMITTER SUGGESTS THIS SB BE C/W AT EARLIEST O PPORTUNITY. 1 L 7 2 4F A22CE 1996111400319 19961114 00319 NM 1996 11 14 96ZZZX5605 1 19961001 G 3244 6053P00139 TIRE BFGOODRICH BOEING 757 757* NM MLG LEAK B UQER K NONE O OTHER IN INSP/MAINT 1 EA 25 2FOR Q5124 DUNLOP EQUIPPED BOEING 757 MAIN WHEEL ASSEMBLIES LEAKING. SUSPECT CAUSE WAS MICHELIN TIRE HAS A SMALL PROCESS CONTROL S TICKER INSTALLED ON THE INSIDE TIRE WALL TO ENSURE PROPER CURE MOLD. THIS STICKER HAS DETERIORATED ONCE IN SERVICE AND MAY LODGE IN VALVE CORE SEAT WHEN TIRE PRESSURE IS CHECKED CAUSING SLOW LEAKAGE. TIRE IS MANUFACTURED BY MICHELIN FOR B FG. 2 L 7 2 4F RT A2NM 1996111400320 19961114 00320 CE 1996 11 14 96ZZZX5606 1 19961030 G 2750 58651053 BELLCRANK CESSNA 441 441 2076020 CE LT/RT FLAP IDLER WORN B P A FE6R K NONE O OTHER IN INSP/MAINT 1 NM 11 2722Y 3944 4410173 THE LT AND RT FLAP IDLER BELLCRANKS, BOTH P/N 5865105-3, ARE FOUND TO BE WORKING BETWEEN THE CAST ARM AND THE TUBULAR BE ARING SUPPORT COLUMN. THE 4 SECURING RIVETS ALSO APPEAR TO BE LOOSE, BUT NOT SHEARED. IT IS BELIEVED THAT RIVET FAILUR E WOULD RESULT IN FLAP BINDING. THESE WERE FOUND ON A RELATIVELY LOW TIME AIRCRAFT (UNDER 4,000 HRS). SERVICEABLE BELL CRANKS ARE INSTALLED. 1 L 7 2 3T RT A28CE 1996111400321 19961114 00321 EA 1996 11 14 96ZZZX5607 2 19961023 G 8530 VALVE CESSNA 172 172RG 2072438 CE LYC O360 O360F1A6 41514 EA NR 4 EXH STRETCHED B FSER O OTHER E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 NE 05 6344V 624 172RG0635 L2881936A PILOT REPORTED THAT THE ENGINE RAN ROUGH AT FULL POWER. REMOVED VALVE COVERS AND FOUND NR 4 CYLINDER EXHAUST VALVE HAD NO CLEARANCE BETWEEN THE VALVE AND ROCKER ARM. THE VALVE HEAD WAS STRETCHED. 1 H 7 1 3O 3 O 3A17 E286 1996111400484 19961114 00484 WP 1996 11 14 96ZZZX5608 1 19960930 G 6320 369D251253 SHAFT HUGHES 369 369D 4470706 WP T/R O/P DAMAGED B S EOOR K NONE O OTHER IN INSP/MAINT 1 AL 03 5074R 778 715 1151D DURING OVERHAUL INSPECTION OF M/R TRANS, THE T/R OUTPUT PINION SHAFT WAS FOUND DAMAGED BEYOND LIMITS FROM A BROKEN BEARI NG RACE GOUGING THE BEARING LAND AND RETAINING RING LIP. 1 G 7 1 3U H3WE 1996111400485 19961114 00485 GL 1996 11 14 96ZZZX5609 2 19960930 G 7321 23057344 FCU HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL ENGINE FAILED B EOOR K NONE O OTHER IN INSP/MAINT 1 AL 03 5074R 440 329147 1151D CAE832750 FCU CAUSED DELAYED LIGHT-OFF WHEN AT AMBIENT TEMP. UNITS REPLACED, STARTS NORMAL. 1 G 7 1 3U 3 U H3WE E4CE 1996111400486 19961114 00486 WP 1996 11 14 96ZZZX5610 1 19960930 G 6320 369D251141 HOUSING HUGHES 369 369D 4470706 WP M/R XMSN DAMAGED B EOOR K NONE O OTHER IN INSP/MAINT 1 AL 03 5074R 8534 2433 1151D DURING OVERHAUL INSPECTION OF M/R TRANSMISSION, A DEEP GOUGE .137 INCH WAS FOUND IN THE HOUSING COVER IN THE FWD T/R O/P PINION BEARING BOX CAUSED BY THE BEARING FAILURE. 1 G 7 1 3U H3WE 1996111400487 19961114 00487 GL 1996 11 14 96ZZZX5611 2 19960930 G 7323 23057869 GOVERNOR HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL ENGINE ERRATIC B EOOR K NONE O OTHER NR NOT REPORTED 1 AL 03 5074R 1100 27963 1151D CAE832750 PILOT COMPLAINED OF ERRATIC OPERATION AND CONSTANT BEEP ADJUSTMENT. UNIT IS 344.6 HOURS SINCE REPAIR. THIS IS ANOTHER OF NUMEROUS GOVERNOR PROBLEMS. 1 G 7 1 3U 3 U H3WE E4CE 1996111400488 19961114 00488 WP 1996 11 14 96ZZZX5612 1 19961008 G 6320 B3148A DRAIN VALVE HUGHES 369 369D 4470706 WP M/R XMSN CRACKED B S A EOOR K NONE O OTHER IN INSP/MAINT 1 AL 03 5074R 2433 1151D DURING OVERHAUL, FOUND THE M/R TRANS DRAIN PLUGS CRACKED AT THE FLANGE COMPLETELY AROUND, BUT NOT YET ALL THE WAY THROUG H THE WALL. REPLACED PART. 1 G 7 1 3U H3WE 1996111400489 19961114 00489 1996 11 14 96ZZZX5613 4 19961029 G 3451 KI572 CONTROL HEAD KING SNIAS 350 AS350B2 8680813 EU DME MISWIRED B EOOR K NONE W INADEQUATE Q C IN INSP/MAINT 1 AL 03 4035W 56 2912 DME WOULD NOT WORK ON SEVERAL CHANNELS. THE AIRCRAFT WAS RECENTLY DELIVERED FROM MANUFACTURING AND WAS MISSING JUMPER I N CONTROL HEAD K1572 BETWEEN PINS 30 AND 47. THIS APPEARS TO BE A REVISION THAT WAS NOT INCORPORATED BY THE INSTALLER. THE OLD INSTALL MANUAL DOES NOT INDICATE THIS JUMPER. 1 G 7 1 3U H9EU 1996111400490 19961114 00490 WP 1996 11 14 96ZZZX5614 1 19961001 G 6710 A218100646 TRIM SWITCH HUGHES 369 369E 4470707 WP PILOT CYCLIC INTERMITTENT D O OTHER O OTHER NR NOT REPORTED 1 WP 07 503MP 295 0414E WHEN TRIM SWITCH WAS RELEASED FROM AFT POSITION, FORWARD TRIM STARTED TO RUN AWAY, SWITCH INTERMITTENT. 1 G 7 1 3U H3WE 1996111400491 19961114 00491 WP 1996 11 14 96ZZZX5615 1 19960909 G 6220 369H120351 LEAD LAG LINK 369D21200501 HUGHES 369 369D 4470706 WP M/R HUB LOOSE BUSHING D K NONE O OTHER IN INSP/MAINT 1 WP 07 911FT 1958 811036D DURING REMOVAL OF M/R BLADES, FOUND ONE OF THE LEAD LAG/LINK BUSHINGS LOOSENED FROM LINK. PART REJECTED BY MDHS FIELD SE RVICE REP. REPLACED DEFECTIVE LINK ASSY W/SERVICEABLE UNIT. 1 G 7 1 3U H3WE 1996111400492 19961114 00492 SW 1996 11 14 96ZZZX5616 1 19960925 G 6420 206011811009 YOKE 206011810015 BELL 206 206B 1181511 SW T/R CRACKED D A K NONE O OTHER IN INSP/MAINT 1 EA 21 777CP 4559 1233 GDLG11652 3429 DURING DAILY CLEANING OF HELICOPTER, PILOT NOTICED WHAT APPEARED TO BE A CRACK IN TH E T/R YOKE. AFTER REMOVING PAINT A ND INSPECTING WITH A MAGNIFYING GLASS, A CRACK WAS DEFINITELY VISIBLE. CRACK STARTED AT CENTER LINE OF OUTBOARD BOLT HO LE, EXTENDIING TO OUTER END OF YOKE AND STARTING TO TRAVEL TO OTHER SIDE OF YOKE. 1 G 7 1 3U H2SW 1996111400493 19961114 00493 WP 1996 11 14 96ZZZX5617 1 19961001 G 2424 369A4652H REGULATOR VR214 HUGHES 369 OH6A WP STATIC VOLTS FAILED H A H UNSCHED LANDING DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 WP 07 446SD 42942 6716286 SHORTLY AFTER TAKEOFF, VOLTAGE REGULATOR FAILURE CONTRIBUTED TO SLIGHT SMOKE EMITTING FROM COMPONENT. PRECAUTIONARY LAN DING MADE, W/H CONNECTOR DISCONNECTED FROM VRS. A/C FLOWN TO HOME BASE, 5-MINUTE FLIGHT, A/C BATTERY UTILIZED. AT THIS TIME VOLTAGE REGULATOR FAILURE UNKNOWN. 1 G 7 1 3U H3WE 1996111400494 19961114 00494 NE 1996 11 14 96ZZZX5618 1 19961009 G 3213 S61255030411 CYLINDER SKRSKY S61 S61N 8142104 NE LT MLG LEG CRACKED D K NONE K FLUID LOSS IN INSP/MAINT 1 EA 05 7011M 4730 61216 DURING A POST-FLIGHT INSPECTION, HYDRAULIC FLUID WAS NOTICED SEEPING OUT FROM THE LT MAIN OLEO, JUST BELOW THE LOWER ATT ACHMENT LUG. A CLOSE VISUAL INSPECTION REVEALED A .50 INCH LONG CRACK IN THE CYLINDER. 2 G 7 2 4U 1H15 1996111400495 19961114 00495 CE 1996 11 14 96ZZZX5619 1 19961015 G 2750 035A961001003 CONTROL CABLE MTSBSI MU2 MU2B35 5780411 CE FLAP FLEX DRIVE FAILED B IZ2R K NONE O OTHER IN INSP/MAINT 1 SW 15 6569L 1588 390 645 DURING ROUTINE 500-HOUR INSPECTION, FLAPS WERE OPERATED TO VERIFY PROPER FUNCTION. DURING OPERATION, A 'POP' WAS HEARD AND THE LEFT OUTBOARD FLAP WAS NO LONGER MOVING. INSPECTION REVEALED THE FLEX CABLE INNER SHAFT HAD FAILED. CABLE WAS INSTALLED 2-8-88, AD 87-04-03, PERFORMED AT 4,113.0 HRS. BOTH LEFT AND RIGHT CABLES REPLACED WITH NEW AT THIS TIME. 1 H 7 2 3T RT A10SW 1996111400496 19961114 00496 CE 1996 11 14 96ZZZX5620 1 19961025 G 2430 M22759749 WIRE BEECH 100 B100 1152919 CE START/GEN CRACKED B UO2R K NONE O OTHER IN INSP/MAINT 1 GL 19 1807H 5464 BE119 THE STARTER/GENERATOR 4 GAUGE WIRES THAT RUN FROM THE FIREWALL POWER CONNECTOR AND GENERATOR GROUND TO THE STARTER/GENER ATOR WERE FOUND WITH CRACKED INSULATION. THE CRACKS RUN PARALLEL WITH THE WIRE. SOME OF THE CRACKS ARE OVER 3 INCHES I N LENGTH EXPOSING THE CENTER CONDUCTOR. ON THE LT AND RT ENGINES, THE WIRE NUMBERS OF THE DEFECTIVE WIRES ARE K2D4, K2F 4, P10A4, P10C4, P10E4, K17A4N, K17B4N, AND K17C4N. THIS IS THE SECOND B100 FOUND LIKE THIS. 1 L 7 2 4T A14CE 1996111400497 19961114 00497 EU 1996 11 14 96ZZZX5621 1 19961017 G 3020 HEATED LIP PILATS PC12 PC12 7090550 EU COWLING EXH LEAKS B LF1R K NONE O OTHER IN INSP/MAINT 1 EA 07 62JT 107 EXHAUST LEAKS SHOWING AROUND LOWER COWLING HEATED LIP. REMOVED LIP INNER PANEL. LEAKING EXHAUST PAST THE RIVETS AND IN SULATION. FOIL HEAT SHIELD AND INSULATION BURNED. SUBMITTER RECOMMENDS 50-HOUR INSPECTION BE MANDATORY. ACFT TOTAL TI ME, 827.1 HRS. 1 L 7 1 3T RT A78EU 1996111400498 19961114 00498 1996 11 14 96ZZZX5622 4 19961031 G 3414 C6610630103 INDICATOR AEROSONIC 202401189 AIR SPEED BENT SHAFT H K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 25 RECENTLY HAVED RECEIVED FROM THE VENDOR, SEVERAL AIRSPEED INDICATORS WITH BENT SHAFTS ON FLT INDEX KNOB ASSY. SUBMITTER SUGGESTS TO PAY CLOSE ATTENTION TO THIS UPON RECEIPT FROM VENDOR BEFORE INSTALLING UNIT. CREDIT IS NOT GIVEN ONCE INST ALLED. 1996111400499 19961114 00499 1996 11 14 96ZZZX5623 4 19961031 G 3414 202401189 INDICATOR AEROSONIC AIR SPEED BENT SHAFT G K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 25 RECENTLY SUBMITTER HAS RECEIVED FROM THE VENDOR SEVERAL AIRSPEED INDICATORS WITH BENT SHAFTS ON SET INDEX KNOB ASSY. SU BMITTER SUGGESTS TO PAY CLOSE ATTENTION TO THIS UPON RECEIPT FROM VENDOR BEFORE INSTALLING UNIT. CREDIT IS NOT GIVEN ON CE INSTALLED. 1996111400500 19961114 00500 SO 1996 11 14 96ZZZX5624 2 19960829 G 8520 6419441048 THROUGH-BOLT CESSNA 337 T337G 2075726 CE CONT O360 TSIO360C 17025 SO NR 2 CYL BASE BROKEN C K NONE O OTHER IN INSP/MAINT 1 GL 17 8CE 198 P3370144 224343R INSPECTION FOUND LOWER THROUGH-BOLT IN NR 2 CYLINDER BASE BROKEN. 1 H 7 2 3O 3 O A6CE E9CE 1996112700247 19961127 00247 NE 1996 11 27 96ZZZX5625 3 19961015 G 6111 EROSION STRIP SAAB 2000 2000SAAB 7860200 EU ROTOL R381 R3816123F5 NE LT PROP CRACKED D K NONE O OTHER IN INSP/MAINT 1 GL 23 5124 697 2000027 DAP0063 DURING A POST-FLIGHT INSPECTION, A LEFT PROP BLADE EROSION STRIP WAS FOUND CRACKED. THE CRACK WAS APPROXIMATELY 4.1 INC HES LONG AND PARALLEL TO THE LEADING EDGE. REPLACED THE PROPELLER PER SAAB 2000 MM AND PERFORMED GROUND CHECKS. 2 L 7 2 4T RT A47NM 6 C P6BO 1996112700248 19961127 00248 EU 1996 11 27 96ZZZX5626 1 19961024 G 5520 ELEVATOR GROB ASTIR G102IIIB EU EMPENNAGE FLUTTER D O OTHER F E FLT CONT AFFECTED VIBRATION/BUFFET CR CRUISE 1 WP 11 851BG 1842 5639CB ELEVATOR FLUTTER CAUSED MULTIPLE FRACTURES AND DELAMINATIONS IN ELEVATOR SKINS INCLUDING SEPARATION OF INBOARD HINGES ON HORIZONTAL STABILIZER. PILOT REPORTED A VIBRATION AT 120 KTS AND 10,000 FEET IN SMOOTH AIR. REDLINE AT 10,000 FEET IS 128 KTS. POST-INSPECTION OF ELEVATOR BALANCE SUGGESTS THAT SPECIFICATIONS IN MM TO BE INACCURATE AND/OR INADEQUATE. E LEVATOR BY DESIGN HAS NO COUNTERWEIGHTS INSTALLED. OTHER CASES OF FLUTTER ON THIS MODEL GROB HAVE BEEN REPORTED. 1 K 0 0 0 0 G33EU 1996112700249 19961127 00249 WP 1996 11 27 96ZZZX5627 1 19961008 G 5400 58950815 SPAR DOUG DC8 DC8F54 3021926 WP NR 1 PYLON CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 19 57FB 45669 DURING C-CHECK INSPECTION, FOUND NR 1 PYLON UPPER OUTBOARD SPAR CRACKED. REMOVED AND REPLACED NR 1 PYLON UPPER OTBD SPA R IAW DOUGLAS DRAWING 5895081. 2 L 7 4 4F 4A25 1996112700250 19961127 00250 SO 1996 11 27 96ZZZX5628 2 19961028 G 8530 653453 VALVE SEAT CONT O520 GTSIO520* 17032 SO INT VALVE MISINSTALLED B VA1R K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 19 613067 CYLINDER INTAKE SEAT NOT SEATED INTO MACHINED PORTION OF CYLINDER HEAD ALL THE WAY IN. UPON INSTALLATION AT FACTORY, NO T TAPPED IN COMPLETELY OR SEATED TO MACHINED HOLE. SUBMITTER STATES ALWAYS INSPECT NEW CYLINDERS FOR CORRECT SEATING OF VALVE SEAT INTO CYLINDERS. 3 O E7CE 1996112700251 19961127 00251 SO 1996 11 27 96ZZZX5629 2 19961028 G 8530 653445 VALVE SEAT CONT O520 TSIO520* 17040 SO EXH VALVE MISINSTALLED B VA1R K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 19 519648 CYLINDER EXHAUST SEAT NOT SEATED INTO MACHINED PORTION OF CYLINDER HEAD ALL THE WAY IN. SUSPECT CAUSE: UPON INSTALLATI ON AT FACTORY, SEATS ARE NOT TAPPED IN, BUT DROPPED IN ASSUMING INSTALLED. SUBMITTER STATED ALWAYS INSPECT NEW CYLINDER S FOR GOOD SEATING OF SEAT INTO CYLINDER. 3 O E8CE 1996112700252 19961127 00252 SO 1996 11 27 96ZZZX5630 1 19961004 G 2710 520235501 AILERON GULSTM AA5 AA5B 3960105 SO TORQ TUBE LT RIVETS LOOSE D P A K NONE O OTHER IN INSP/MAINT 1 NM 09 28519 5307 AA5B0658 DURING ANNUAL INSPECTION, FOUND BOTH AILERONS TO HAVE CONTROL LOOSENESS INTERNALLY. REMOVED AILERON ASSYS AND FOUND BOT H TO HAVE LOOSE RIVETS AT TORQUE TUBE TO AILERON ATTACHMENT. SUSPECT AIRCRAFT EXPERIENCED HIGH WINDS FROM REAR WHILE PA RKED. GUST LOCKS ON AILERONS PROPER, WOULD PREVENT THIS. 1 L 7 1 3O A16EA 1996112700253 19961127 00253 SO 1996 11 27 96ZZZX5631 1 19961004 G 2710 5202035502 AILERON GULSTM AA5 AA5B 3960105 SO TORQ TUBE RT RIVETS LOOSE D K NONE O OTHER IN INSP/MAINT 1 NM 09 28519 5307 AA5B0658 DURING ANNUAL INSPECTION, FOUND BOTH AILERONS TO HAVE CONTROL LOOSENESS INTERNALLY. REMOVED AILERON ASSYS AND FOUND BOT H TO HAVE LOOSE RIVETS AT TORQUE TUBE TO AILERON ATTACHMENT. SUSPECT AIRCRAFT EXPERIENCED HIGH WINDS FROM REAR WHILE PA RKED. GUST LOCKS ON AILERONS PROPER, WOULD PREVENT THIS. 1 L 7 1 3O A16EA 1996112700254 19961127 00254 SO 1996 11 27 96ZZZX5632 1 19961004 G 2752 56040091 BRACKET GULSTM AA5 AA5B 3960105 SO FLAP ACTUATOR BROKEN D P A K NONE O OTHER IN INSP/MAINT 1 NM 09 28519 5307 AA5B0658 FLAP ACTUATOR TRANSMISSION SUPPORT MOUNT AFT ATTACH POINT TAB FOUND BROKEN OFF AND HAD BEEN FOR SOME TIME. FLAPS HAD EX CESSIVE UP AND DOWN FREE TRAVEL. SUSPECT EXPOSURE TO TAIL WINDS ON THE PARKING AREA. 1 L 7 1 3O A16EA 1996112700256 19961127 00256 CE 1996 11 27 96ZZZX5634 1 19961021 G 2422 KGSSPC38B INVERTER CESSNA 500 550 2076604 CE NR 1 POS FAILED B L A VXWR O OTHER H ELECT. POWER LOSS-50 PC NR NOT REPORTED 1 EA 21 24E 1737 5500651 INVESTIGATION FOR A DOUBLE INVERTER FAILURE FOUND OPTIC COUPLER IN PHASE LOCK CIRCUIT FALIED. WITH COUPLER FAILED FREQ OUTPUT UNREGULATED, CAUSING PHASE LINK TO DISCONNECT THE OTHER INVERTER. PHASE LINK NOT PROTECTED BY FAULT MONITOR AND CAN FAIL BOTH INVERTERS. SUBMITTER SUGGESTS REDESIGN FAULT CKT TO PROTECT UNIT FROM DUAL FAILURE. 1 L 7 2 4F A22CE 1996112700257 19961127 00257 EA 1996 11 27 96ZZZX5635 2 19960914 G 7414 M3548 ROTOR SLICK 4270 CHILD S1 S1SPITTS 0110301 NM LYC O360 IO360B4A 41514 EA ENGINE MAGNETO BROKEN D K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 WP 15 205 90030130 INVESTIGATION FOR ROUGH RUNNING ENGINE FOUND MAGNETO OUT OF TIME DUE TO BROKEN ROTOR. 1 Q 7 1 3O 3 O A8SO 1E10 1996112700258 19961127 00258 GL 1996 11 27 96ZZZX5636 3 19961107 G 6111 C4503 FORK HARTZL HCC4Y HCC4YR2 GL PITCH CONT CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 99 1735 901N FH516 DURING OVERHAUL OF THE PROPELLER, MAGNETIC PARTICLE INSPECTION REVEALED TWO INDICATIONS RADIATING FROM THE PITCH ROD BOR E ACROSS THE FORWARD SURFACE OF THE FORK. THE INDICATIONS WERE LOCATED IN THE FORGED SURFACE AND DID NOT PROTRUDE INTO THE PITCH ROD BORE. THE FORK WAS FORWARDED TO THE MANUFACTURER FOR EVALUATION. 5 C P52GL 1996112700259 19961127 00259 CE 1996 11 27 96ZZZX5637 1 19961101 G 7603 16991001723 BRACKET SUPPORT BEECH 23 B24R 1151253 CE THROTTLE CABLE FAILED D S K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 15 1957L 1501 MC423 THROTTLE SUPPORT BRACKET THAT BOLTS TO OIL SUMP FAILED AND ALSO GROOVED AT POINT OF CABLE CLAMP ATTACH. SUBMITTER STATE S LOOSE BOLT AND INCORRECT PART AS CONTRIBUTING FACTOR. CORRECT P/N 169-910017-45. 1 L 7 1 3O A1CE 1996112700260 19961127 00260 CE 1996 11 27 96ZZZX5638 1 19961008 G 3310 05701661 DIMMING ASSY CESSNA 172 172RG 2072438 CE PANEL LIGHT OVERHEATED B AQHD K NONE B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 WP 11 111HP 5583 172RG1153 SMOKE IN COCKPIT DURING FLIGHT. OVERHEATED TRANSISTORIZED DIMMING ASSY LIKELY CAUSED BY ADDED ELECTRICAL LOAD DUE TO RE CENTLY ADDED RADIO EQUIPMENT. SUBMITTER STATED AN EVALUATION NEEDED OF CURRENT DRAW ON SUBJECT SYSTEM. THAT DETERMINAT ION HAS NOT YET BEEN MADE ON THIS AIRCRAFT. THIS AIRCRAFT DELIVERED NEW IN 1984 WITHOUT RADIO. THE AVIONICS AND RADIO GEAR HAVE BEEN ADDED TO OVER THE YEARS WITHOUT BENEFIT OF ENGINEERING REQUIREMENTS OF SUBJECT CIRCUIT. 1 H 7 1 3O 3A17 1996112700262 19961127 00262 SO 1996 11 27 96ZZZX5640 1 19961001 G 7931 486440 TRANSDUCER PIPER PA38 PA38112 7103812 SO ENG OIL PRESS FAILED D K NONE O OTHER CR CRUISE 1 SW 99 2489P 3879A1003 OIL PRESSURE TRANSDUCER APPEARS TO HAVE GROUNDED ITSELF INTERNALLY CAUSING AN INDICATION OF NO OIL PRESSURE WHILE IN-FLI GHT. 1 L 7 1 3O A18SO 1996112700263 19961127 00263 CE 1996 11 27 96ZZZX5641 1 19961104 G 2750 500000861CR CONTROL CABLE CESSNA 421 421C 2076016 CE FLAP FRAYED D K NONE O OTHER IN INSP/MAINT 1 EA 03 247CB 7765 421C0299 UPON INSPECTION OF FLAP CABLES AFTER REMOVAL, SEVERAL BROKEN WIRES WERE DISCOVERED. ALSO NOTE THAT LOCATION OF DAMAGE A REAS WERE UNDETECTABLE WITHOUT CABLE REMOVAL. BENDING OF CABLES REVEALED SEVERITY OF BROKEN WIRES NOT EVIDENT BY EXTERN AL VISUAL INSPECTION OF CABLES. 1 L 7 2 3O A7CE 1996112700264 19961127 00264 CE 1996 11 27 96ZZZX5642 1 19961104 G 2750 500000862 CONTROL CABLE CESSNA 421 421C 2076016 CE FLAP FRAYED D K NONE O OTHER IN INSP/MAINT 1 EA 03 247CB 7765 421C0299 UPON INSPECTION OF FLAP CABLES AFTER REMOVAL, SEVERAL BROKEN WIRES WERE DISCOVERED. ALSO NOTE THAT LOCATION OF DAMAGE A REAS WERE UNDETECTABLE WITHOUT CABLE REMOVAL. BENDING OF CABLES REVEALED SEVERITY OF BROKEN WIRES NOT EVIDENT BY EXTERN AL VISUAL INSPECTION OF CABLES. 1 L 7 2 3O A7CE 1996112700265 19961127 00265 CE 1996 11 27 96ZZZX5643 1 19961104 G 2750 500000863CR CONTROL CABLE CESSNA 421 421C 2076016 CE FLAP FRAYED D K NONE O OTHER IN INSP/MAINT 1 EA 03 247CB 7765 421C0299 UPON INSPECTION OF FLAP CABLES AFTER REMOVAL, SEVERAL BROKEN WIRES WERE DISCOVERED. ALSO NOTE THAT LOCATION OF DAMAGE A REAS WERE UNDETECTABLE WITHOUT CABLE REMOVAL. BENDING OF CABLES REVEALED SEVERITY OF BROKEN WIRES NOT EVIDENT BY EXTERN AL VISUAL INSPECTION OF CABLES. 1 L 7 2 3O A7CE 1996112700266 19961127 00266 CE 1996 11 27 96ZZZX5644 1 19961029 G 2750 500000862 CABLE ASSY CESSNA 414 414A 2075907 CE PRESELECT CLAMP BROKE D O OTHER F FLT CONT AFFECTED AP APPROACH 1 EA 03 2688D 6775 414A0332 A SPLIT FLAP CONDITION OCCURRED ON FINAL APPROACH. FLAP EXTEND CABLE WAS FOUND BROKEN ON INBOARD SIDE OF PRE-SELECT CON TROL ATTACH CLAMP. PRE-SELECT CABLE IS NOT RUNNING PARALLEL TO FLAP CABLE. THIS EXTEND CABLE WAS ALSO FOUND TO HAVE IN TERNAL WEAR AT PULLEY LOCATIONS. 1 L 7 2 3O A7CE 1996112700267 19961127 00267 CE 1996 11 27 96ZZZX5645 1 19961029 G 2750 500000863 CABLE ASSY CESSNA 414 414A 2075907 CE FLAP PULLEYS FRAYED D O OTHER F FLT CONT AFFECTED AP APPROACH 1 EA 03 2688D 6775 414A0332 A SPLIT FLAP CONDITION OCCURRED ON FINAL APPROACH. AFTER CHECKING SYSTEM, ALL CABLES WERE REMOVED FROM AIRCRAFT FOR REP LACEMENT. INTERNAL CABLE WEAR WAS FOUND AT ALL PULLEY LOCATIONS. HIGH CABLE SYSTEM TENSION IS REQUIRED ON THESE CABLES . SUBMITTER SUGGESTS LIFE LIMIT. 1 L 7 2 3O A7CE 1996112700268 19961127 00268 CE 1996 11 27 96ZZZX5646 1 19961029 G 2750 51152242 CONTROL CESSNA 414 414A 2075907 CE FS 166 WORN D O OTHER F FLT CONT AFFECTED AP APPROACH 1 EA 03 2688D 414A0332 A SPLIT FLAP CONDITION OCCURRED ON FINAL APPROACH. THE OUTER HOUSING OF THE PRE-SELECT CONTROL IS BADLY WORN WHERE IT M OUNTS TO BULKHEAD AT STA 166. FLAP CABLE AND PRE-SELECT ARE NOT RUNNING PARALLEL WITH EACH OTHER. SUBMITTER STATED A S TRONGER MOUNTING MIGHT HELP AT BULKHEAD. 1 L 7 2 3O A7CE 1996112700269 19961127 00269 SO 1996 11 27 96ZZZX5647 1 19961023 G 7922 53E19600 VERNATHERM PIPER PA31 PA31350 7103110 SO THERMO BYPASS CONE WORN B APCR K NONE O OTHER IN INSP/MAINT 1 NM 01 40ST 454 63888 317405183 DURING VALVE INSPECTION IAW LYCOMING SB 518C, EXCESSIVE WEAR ON THE CONE AREA WAS NOTED WHERE CONE CONTACTS SEAT. WEAR MEASURED FROM .06 INCH TO .1 INCH AROUND CIRCUMFERENCE OF THE CONE. THE SEAT AREA INSIDE THE ACCESSORY CASE ALSO SHOWED EXCESSIVE WEAR AND 'SLOPE' CAUSED BY CONTACT WITH THE CONE. SUBMITTER SUGGESTS SOME THROUGHT BE GIVEN TO SOME TYPE OF NEW SEAT SINCE THIS SEEMS TO BE THE ROOT OF ALL THE VERNATHERM PROBLEMS. 1 L 7 2 3O A20SO 1996112700270 19961127 00270 1996 11 27 96ZZZX5648 4 19961004 G 6113 4393308 BULKHEAD PIPER PA31 PA31310 7103103 SO RT PROP FAILED G A UNSCHED LANDING D INFLIGHT SEPARATION CL CLIMB 1 EA 07 4081F 85 318112036 SPINNER BULKHEAD FAILED RIGHT AFTER TAKEOFF DAMAGING THE PROPELLER AND THE FUSELAGE. THE BULKHEAD SHOWED SIGNS OF STRES S CRACKS. THERE WAS NO SIGN OF OVERTORQUEING OR MIS-ALIGNMENT. 1 L 7 1 3O RT A20SO 1996112700271 19961127 00271 SW 1996 11 27 96ZZZX5649 1 19961024 G 3233 EA1165 CYLINDER GULSTM 680 680E 0141604 SW RT MLG FAILED B A MV1R O OTHER K FLUID LOSS AP APPROACH 1 EA 17 50 7 628 680E81862 INTERNAL FAILURE OF RT MLG ACTUATOR CAUSED TOTAL HYDRAULIC FLUID DEPLETION WITH SUBSEQUENT EMERGENCY EXTENSION OF LANDIN G GEAR WITHOUT INCIDENT. ACTUATOR WAS RECEIVED NEW. ASSEMBLY DATE IS 1/90. INSTALLED 10-9-96. TSN IS 7.4 AND 3 LANDI NGS. OZONE INDUSTRIES, INC. 1 H 7 2 3O 2A4 1996112700272 19961127 00272 EA 1996 11 27 96ZZZX5650 2 19961029 G 8530 LW12416 VALVE CESSNA 172 172P 2072436 CE LYC O320 O320D2J 41508 EA NR 3 CYL EXH STUCK H K NONE E R K VIBRATION/BUFFET PARTIAL RPM/PWR LOSS FLUID LOSS NR NOT REPORTED 1 SO 17 52276 5091 602 17274476 L1376139A NR 3 CYLINDER EXHAUST VALVE STUCK, AND BENT PUSH ROD AND PUSH ROD HOUSING. THIS CAUSED ROUGH ENGINE AND AN OIL LEAK. C YLINDER WAS REPLACED WITH OVERHAULED UNIT. 1 H 7 1 3O 3 O NT 3A12 E274 1996112700274 19961127 00274 CE 1996 11 27 96ZZZX5652 1 19961101 G 3230 582212715 ANGLE CESSNA 441 441 2076020 CE RT UPLOCK HOOK CRACKED B S WTXR K NONE O OTHER IN INSP/MAINT 1 NM 07 555WA 8283 4410219 DURING A PHASE INSPECTION, FOUND A CRACK IN THE OUTBOARD END OF THE RT AND LT MAIN GEAR UPLOCK HOOK SUPPORT ANGLE THAT A TTACHES TO THE FORWARD WING SPAR WEB. CRACK ORIGINATES AT THE OUTBOARD HILOCK HOLE AND EXTENDS FOR A TOTAL LENGTH OF 1. 25 INCHES. INSTALLED NEW ANGLES. 1 L 7 2 3T RT A28CE 1996112700275 19961127 00275 CE 1996 11 27 96ZZZX5653 1 19961101 G 3230 582212716 ANGLE CESSNA 441 441 2076020 CE LT UPLOCK HOOK CRACKED B WTXR K NONE O OTHER IN INSP/MAINT 1 NM 07 555WA 8283 4410219 DURING A PHASE INSPECTION, FOUND A CRACK IN THE OUTBOARD END OF THE RT AND LT MAIN GEAR UPLOCK HOOK SUPPORT ANGLE THAT A TTACHES TO THE FORWARD WING SPAR WEB. CRACK ORIGINATES AT THE OUTBOARD HILOCK HOLE AND EXTENDS FOR A TOTAL LENGTH OF 1. 25 INCHES. INSTALLED NEW ANGLES. 1 L 7 2 3T RT A28CE 1996112700276 19961127 00276 CE 1996 11 27 96ZZZX5654 1 19961101 G 5712 57222061 CANTED RIB CESSNA 441 441 2076020 CE RT WING TOP CAP CRACKED B WTXR K NONE O OTHER IN INSP/MAINT 1 NM 07 555WA 8283 4410219 DURING A PHASE INSPECTION FOUND BOTH RT AND LT WING CANTED RIB TOP CAP CRACKED. CRACK STARTS AT AFT SIDE OF FWD WING SP AR AND RUNS AFT PARALLEL TO THE BEND RADIUS. STOP-DRILLED ENDS OF CRACKS PER CESSNA INSTRUCTIONS. 1 L 7 2 3T RT A28CE 1996112700277 19961127 00277 CE 1996 11 27 96ZZZX5655 1 19961101 G 5712 57222062 CANTED RIB CESSNA 441 441 2076020 CE LT WING TOP CAP CRACKED B WTXR K NONE O OTHER IN INSP/MAINT 1 NM 07 555WA 8283 4410219 DURING A PHASE INSPECTION FOUND BOTH RT AND LT WING CANTED RIB TOP CAP CRACKED. CRACK STARTS AT AFT SIDE OF FWD WING SP AR AND RUNS AFT PARALLEL TO THE BEND RADIUS. STOP-DRILLED ENDS OF CRACKS PER CESSNA INSTRUCTIONS. 1 L 7 2 3T RT A28CE 1996112700278 19961127 00278 CE 1996 11 27 96ZZZX5656 1 19961023 G 2730 115610010325 TORQUE TUBE 115610010368 BEECH 99 C99 1154006 CE RT ELEV CASTING CRACKED B EHHR K NONE O OTHER IN INSP/MAINT 1 EA 17 6656N 5729 U213 WHILE COMPLYING WITH BEECH MANDATORY SB 2145, RT ELEVATOR TORQUE TUBE OUTBOARD CASTING WAS FOUND CRACKED FROM ONE OF THE TAPER PIN HOLES. 1 L 7 2 3T A14CE 1996112700281 19961127 00281 SO 1996 11 27 96ZZZX5659 2 19961101 G 8550 646253 ADAPTER ASSY CESSNA 172 R172K 2072431 CE CONT O360 IO360KB 17025 SO OIL FILTER WORN B S G9NR K NONE O OTHER IN INSP/MAINT 1 EA 07 758RV 365 R1723308 288547R BYPASS PLUG CAME OUT OF HOUSING. FOUND WORN PLUG AND DAMAGED HOUSING. PLUG IS STAKED IN IF BYPASS VALVE IS NOT USED. F OUND METAL IN OIL FILTER AT PREVIOUS OIL CHANGE 10 HRS PRIOR AND AT THIS OIL CHANGE. SUBMITTER STATED MFG NEEDS BETTER WAY TO SECURE PLUG. 1 H 7 1 3O 3 O 3A17 E1CE 1996112700316 19961127 00316 EU 1996 11 27 96ZZZX5691 1 19960616 G 3340 11159851 LAMP BOLKMS 105 BO105S 5626006 EU STROBE FAILED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 105NG 15 G5280 S632 LIGHT INOPERATIVE. THIS LAMP WAS A NO COST WARRANTY REPLACMENT LAMP AND IT ONLY LASTED 14.8 HRS AFTER INSTALLED. 1 G 7 2 3U H3EU 1996112700317 19961127 00317 EU 1996 11 27 96ZZZX5692 1 19960913 G 6410 11731747 BLADE BOLKMS 117 BK117A3 5626015 EU T/R CRACKED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 1140H 536 1118 7078 SUSPECT BLADE IS CRACKED AT BOLT HOLE. 1 G 7 2 3U H13EU 1996112700318 19961127 00318 EU 1996 11 27 96ZZZX5693 1 19960913 G 6410 11731747 BLADE BOLKMS 117 BK117A3 5626015 EU T/R DEFECTIVE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 1140H 536 1116 7078 REMOVED AS MATCHED SET WITH BLADE S/N 1118, REF MMIR 78798. 1 G 7 2 3U H13EU 1996112700319 19961127 00319 EU 1996 11 27 96ZZZX5694 1 19960920 G 6720 741C000005 ACTUATOR BOLKMS 117 BK117A1 5626010 EU T/R LEAKING B TI1R K NONE K FLUID LOSS IN INSP/MAINT 1 SW 05 117M 00212 S7023 ACTUATOR EXCESSIVE LEAKAGE. 1 G 7 2 3U H13EU 1996112700320 19961127 00320 EU 1996 11 27 96ZZZX5695 1 19960927 G 6520 4639310062 BEVEL GEAR BOLKMS 117 BK117A1 5626010 EU T/R GRBOX DEFECTIVE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 117M 821 S7023 UNABLE TO GET CORRECT CONTACT PATTERN. ONLY A SPLIT PATTERN. 1 G 7 2 3U H13EU 1996112700321 19961127 00321 EU 1996 11 27 96ZZZX5696 1 19960927 G 6520 46393100 BEVEL GEARSHAFT BOLKMS 117 BK117A1 5626010 EU TR GRBOX DEFECTIVE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 117M 842 S7023 UNABLE TO GET CORRECT CONTACT PATTERN. ONLY A SPLIT CONTACT PATTERN. 1 G 7 2 3U H13EU 1996112700322 19961127 00322 1996 11 27 96ZZZX5697 4 19961022 G 3160 066040211111 SYMBOL GENERATOR SG465 BELL 230 230 1182149 SW COCKPIT MALFUNCTION B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 230JP 94 1945 23019 SYMBOL GENERATOR CHECK CONFIG MESSAGE COMES ON INTERMITTENTLY. 1 G 7 2 3U NC H9SW 1996112700323 19961127 00323 SW 1996 11 27 96ZZZX5698 1 19960805 G 6200 222310503101 BEARING PAD BELL 230 230 1182149 SW M/R DEBONDED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 230JP 310 LK0007 23019 BEARING PAD DEBONDED. 1 G 7 2 3U NC H9SW 1996112700324 19961127 00324 SW 1996 11 27 96ZZZX5699 1 19960831 G 2150 2730502 VALVE BELL 230 230 1182149 SW BLEED FAILED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 230JP 391 1384 23019 VALVE CAUSING ECU BREAKER TO P0P. 1 G 7 2 3U NC H9SW 1996112700325 19961127 00325 SW 1996 11 27 96ZZZX5700 1 19960816 G 3350 214175140101 POWER SUPPLY BELL 230 230 1182149 SW CABIN EEL DEFECTIVE B TI1R K NONE L NO TEST IN INSP/MAINT 1 SW 05 230JP 1069 23019 EMERGENCY CABIN LIGHTING DIM. 1 G 7 2 3U NC H9SW 1996112700326 19961127 00326 1996 11 27 96ZZZX5701 4 19961104 G 3452 071015071301 TRANSPONDER BELL 230 230 1182149 SW COCKPIT DEFECTIVE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 230JP 488 1388 23019 TRANSPONDER NUMBERS WILL NOT CHANGE. 1 G 7 2 3U NC H9SW 1996112700327 19961127 00327 1996 11 27 96ZZZX5702 4 19960906 G 2211 117884141 COMPUTER BOLKMS 117 BK117A4 5626017 EU YAW CSAS MALFUNCTION B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 313LF 6 018609010 7138 YAW/CSAS OSCILLATES LEFT AND RIGHT ON GROUND. ONLY LASTED 5.8 HRS SINCE INSTALLED IN A/C. 1 G 7 2 3U H13EU 1996112700328 19961127 00328 1996 11 27 96ZZZX5703 4 19960905 G 2211 117884141 COMPUTER BOLKMS 117 BK117A4 5626017 EU YAW CSAS MALFUNCTION B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 313LF 018609001 7138 YAW CSAS OSCILLATES LEFT AND RIGHT ON THE GROUND. DID NOT WORK CORRECTLY UPON INSTALLATION. 1 G 7 2 3U H13EU 1996112700329 19961127 00329 1996 11 27 96ZZZX5704 4 19960905 G 3421 5040017926 GYRO BOLKMS 117 BK117A4 5626017 EU COCKPIT ATTITUDE INOPERATIVE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 117NG 90 3428 7083 ATTITUDE GYRO INOPERATIVE. ONLY 89.9 HRS SINCE INSTALLED IN A/C. 1 G 7 2 3U H13EU 1996112700330 19961127 00330 EU 1996 11 27 96ZZZX5705 1 19960809 G 3310 1179203103 CONTROL UNIT BOLKMS 117 BK117B1 5626012 EU COCKPIT MALFUNCTION B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 170MC 5 0141 7217 LIGHTS WILL NOT TURN 'ON'. NO OUTPUT VOLTAGE. INSTALLED ONLY 4.5 HRS BEFORE FAILURE. LOOSE PARTS INSIDE UNIT. 1 G 7 2 3U H13EU 1996112700331 19961127 00331 EU 1996 11 27 96ZZZX5706 1 19960815 G 3310 1179203103 CONTROL UNIT BOLKMS 117 BK117A3 5626015 EU LIGHTS INOPERATIVE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 118LL 0106 7097 INOP WORKED LESS THAN TWO MINUTES AFTER INSTALLED. 1 G 7 2 3U H13EU 1996112700514 19961127 00514 CE 1996 11 27 96ZZZX5707 1 19961030 G 2750 50000063 CONTROL CABLE CESSNA 421 421C 2076016 CE FLAP PULLEY WORN D K NONE O OTHER IN INSP/MAINT 1 EA 03 782LC 7193 421C0486 ALL FLAP SYSTEM CABLES WERE REMOVED AS A PRECAUTIONARY MEASURE FOR A VISUAL INSPECTION. BOTH FLAP EXTEND CABLES WERE FO UND TO HAVE A GREAT DEAL OF INTERNAL WEAR AT PULLEY LOCATIONS. SUBMITTER SUGGESTS LIFE LIMIT ON CABLES. 1 L 7 2 3O A7CE 1996112700515 19961127 00515 CE 1996 11 27 96ZZZX5708 1 19961030 G 2750 50000062 CONTROL CABLE CESSNA 421 421C 2076016 CE FLAP PULLEY WORN D K NONE O OTHER IN INSP/MAINT 1 EA 03 782LC 7193 421C0486 ALL FLAP SYSTEM CABLES WERE REMOVED AS A PRECAUTIONARY MEASURE FOR A VISUAL INSPECTION. BOTH FLAP EXTEND CABLES WERE FO UND TO HAVE A GREAT DEAL OF INTERNAL WEAR AT PULLEY LOCATIONS. SUBMITTER SUGGESTS LIFE LIMIT ON CABLES. 1 L 7 2 3O A7CE 1996112700516 19961127 00516 SO 1996 11 27 96ZZZX5709 1 19961104 G 7810 LW15806 ELBOW PIPER PA32 PA32R301T 7103220 SO TURBO INLET CRACKED B BONR K NONE O OTHER IN INSP/MAINT 1 GL 19 8314B 1676 32R8129021 DURING ROUTINE OIL CHANGE, NOTICED EXHAUST RESIDUE AROUND WASTEGATE ASSEMBLY. FOUND INLET ELBOW FROM CYLINDERS NR 1, NR 3, AND NR 5 CRACKED. THIS PART IS NOT PART OF AD REQUIRING COMPONENT CHANGE. SUBMITTER RECOMMENDS MAKING REPLACMENT P ART OF THICKER MATERIAL. 1 L 7 1 3O A3SO 1996112700517 19961127 00517 1996 11 27 96ZZZX5710 4 19961015 G 3425 52D1371120 HSI CENTURY NSD360 PIPER PA34 PA34200T 7103406 SO COCKPIT HEADING FAILED B APCR O OTHER O OTHER NR NOT REPORTED 1 NM 01 8407C 966 I1234C 347670137 HEADING FUNCTION OF HSI FAILED JUST PRIOR TO ENTERING IMC. MOTOR INSIDE INSTRUMENT BURNED OUT. SUBMITTER STATED OPERAT OR'S FLEET HAS MANY, MANY FAILURES OF NSD-360 TYPE UNITS. VIRTUALLY ALL INTERNAL SYSTEM FAIL AT DIFFERENT TIMES. 1 L 7 2 3O A7SO 1996112700518 19961127 00518 SO 1996 11 27 96ZZZX5711 1 19961015 G 3210 9652200 CENTERING SPRING PIPER PA34 PA34200T 7103406 SO NLG SHAFT BROKEN B S APCR K NONE O OTHER IN INSP/MAINT 1 NM 01 8407C 347670167 CENTER SHAFT OF NOSE GEAR CENTERING SPRING FOUND SHEARED AT ROD END FITTING. VISUAL INSPECTION INDICATED SHAFT HAD BEE N CRACKED VERTICALLY ON BOTH SIDES OF CENTER FOR SOME TIME PRIOR TO FINALLY BREAKING. SUSPECT THIS WAS CAUSED BY UTILIZ ATION OF A TOWING TUG AND TURNING NOSE GEAR TOO FAR SIDE TO SIDE. RECOMMEND FREQUENT INSPECTION. 1 L 7 2 3O A7SO 1996112700519 19961127 00519 SO 1996 11 27 96ZZZX5712 1 19961024 G 3260 BRACKET PIPER PA34 PA34200T 7103406 SO RT MLG UP SWITCH CRACKED B APCR A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 NM 01 8407C 15400 347670137 RIGHT MAIN GEAR 'UP' LIGHT SWITCH MOUNTING BRACKET CRACKED ALLOWING SWITCH TO FLEX AWAY FROM TRUNNION ON RETRACTION. TH IS CAUSED RED 'UNSAFE' LIGHT TO STAY 'ON'. AIRCRAFT RETURNED TO AIRPORT WITHOUT INCIDENT. GEAR EXTENDED AND LOCKED NOR MALLY. 1 L 7 2 3O A7SO 1996112700520 19961127 00520 SO 1996 11 27 96ZZZX5713 2 19961030 G 7314 6493682 PUMP PIPER PA34 PA34200T 7103406 SO CONT O360 TSIO360EB 17025 SO ENG FUEL FAILED B APCR K NONE O OTHER IN INSP/MAINT 1 NM 01 8407C 443 K139506BR 347670137 265901R ENGINE DRIVEN FUEL PUMP DEVELOPED EXCESSIVE OUTPUT. (HIGH PRESSURE) FOUND FUEL IN DECK REFERENCE LINE, INDICATING INTER NAL LEAKAGE. 1 L 7 2 3O 3 O A7SO E9CE 1996112700521 19961127 00521 CE 1996 11 27 96ZZZX5714 1 19961018 G 5312 07136172 BULKHEAD CESSNA 182 182P 2075816 CE FS 17 RT CORRODED D K NONE O OTHER IN INSP/MAINT 1 GL 19 8431Q 18263546 AT FUSELAGE STA 17.00 RT SIDE WHERE BULKHEAD AND SUPPORT CONNECT TOGETHER BENEATH FLOORBOARD, IT WAS FOUND TO BE BADLY C ORRODED IN AN AREA OF ABOUT 4 INCHES IN DIA AND LIGHTER CORROSION FOR ABOUT A 12 INCH DIAMETER. SUBMITTER STATED THAT S OMETHING WAS SPILLED IN THIS AREA. THE AIRFRAME HAS NO OTHER CORROSION. 1 H 7 1 3O NT TA13 1996112700522 19961127 00522 CE 1996 11 27 96ZZZX5715 1 19961018 G 5320 07137875 SUPPORT CESSNA 182 182P 2075816 CE FS 17 RT CORRODED D K NONE O OTHER IN INSP/MAINT 1 GL 19 8431Q 18263546 AT FUSELAGE STA 17.00 RT SIDE WHERE BULKHEAD AND SUPPORT CONNECT TOGETHER BENEATH FLOORBOARD, IT WAS FOUND TO BE BADLY C ORRODED IN AN AREA OF ABOUT 4 INCHES IN DIA AND LIGHTER CORROSION FOR ABOUT A 12 INCH DIAMETER. SUBMITTER STATED THAT S OMETHING WAS SPILLED IN THIS AREA. THE AIRFRAME HAS NO OTHER CORROSION. 1 H 7 1 3O NT TA13 1996112700523 19961127 00523 SW 1996 11 27 96ZZZX5716 1 19961002 G 5522 430026001 ELEVATOR MOONEY M20 M20J 5870219 SW LT ELEV LOOSE SKIN D A K NONE O OTHER IN INSP/MAINT 1 GL 17 88EY 925 243128 BOTH ELEVATORS ON THIS 1989 AIRCRAFT WITH ONLY 925 HRS HAVE LOOSE SKINS. THE RT ELEVATOR TOP SKIN IS LOOSE AT THE ROW O F RIVETS ALONG THE SPAR; THE LT ELEVATOR IS THE SAME EXCEPT THE BOTTOM SKIN IS LOOSE. THE BALANCE WEIGHTS AT THE ELEVAT OR TIPS CAN BE FLEXED UP AND DOWN AT LEAST AN INCH IN EACH DIRECTION. SUBMITTER STATES THE ELEVATORS HAVE LOST ALL RIGI DITY WHICH COULD EASILY CONTRIBUTE TO OR PRECIPITATE A FLUTTER. NO APPARENT CAUSE CAN BE DETERMINED. 1 L 7 1 3O 2A3 1996112700524 19961127 00524 SW 1996 11 27 96ZZZX5717 1 19961002 G 5522 430026002 ELEVATOR MOONEY M20 M20J 5870219 SW RT ELEV LOOSE SKIN D K NONE O OTHER IN INSP/MAINT 1 GL 17 88EY 925 243128 BOTH ELEVATORS ON THIS 1989 AIRCRAFT WITH ONLY 925 HRS HAVE LOOSE SKINS. THE RT ELEVATOR TOP SKIN IS LOOSE AT THE ROW O F RIVETS ALONG THE SPAR; THE LT ELEVATOR IS THE SAME EXCEPT THE BOTTOM SKIN IS LOOSE. THE BALANCE WEIGHTS AT THE ELEVAT OR TIPS CAN BE FLEXED UP AND DOWN AT LEAST AN INCH IN EACH DIRECTION. SUBMITTER STATES THE ELEVATORS HAVE LOST ALL RIGI DITY WHICH COULD EASILY CONTRIBUTE TO OR PRECIPITATE A FLUTTER. NO APPARENT CAUSE CAN BE DETERMINED. 1 L 7 1 3O 2A3 1996112700525 19961127 00525 CE 1996 11 27 96ZZZX5718 1 19961008 G 5712 95110026603 RIB BEECH 58 58 1152740 CE WS 45 LT CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 05 4494A TH30 DURING A 100-HOUR INSPECTION, FOUND LT WING STA 45 RIB ASSY HAS 3 CRACKS ALONG UPPER SKIN RIVET ROW ON RIB, 1 PULLED RIV ET AT FORWARD LOWER CORNER ATTACH TO SPAR. RIB IS DEFORMED IN THE CENTER AREA AT RIB. AILERON TRIM CABLES WEARING HOLE S IN RIB. SUSPECT CAUSE POSSIBLE HARD LANDING. SUBMITTER STATED CLOSER INSP OF THESE AREAS. 1 L 7 2 3O 3A16 1996112700526 19961127 00526 CE 1996 11 27 96ZZZX5719 1 19961008 G 5751 451350309 SKIN BEECH 58 58 1152740 CE LT AILERON CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 05 4494A 8311 TH30 DURING 100-HOUR INSPECTION, FOUND .25 INCH CRACK IN OUTBOARD UPPER TRAILING EDGE OF SKIN OF THE LT AILERON. SUSPECT CAU SE DUE TO VIBRATION. SUBMITTER RECOMMENDATION IS CLOSE INSPECTION OF THE AILERONS. 1 L 7 2 3O 3A16 1996020900282 19960209 00282 CE 1996 2 9 96ZZZX572 1 19960112 G 2933 P50018LMBE GAUGE BEECH 200 B200 1152922 CE HYD PRESSURE STUCK B LX5R K NONE O OTHER IN INSP/MAINT 1 GL 19 961LL 222 BB1139 THIS GAUGE IS PART OF STC-SA4378-WP, HYDRAULIC LANDING GEAR RETRACTION SYSTEM. GAUGE FOUND STUCK AT 500 P.S.I. DURING A IRCRAFT INSPECTION. SUBMITTER RECOMMENDS A BETTER QUALITY GAUGE BE USED IN SYSTEM. 1 L 7 2 4T A24CE 1996112700527 19961127 00527 CE 1996 11 27 96ZZZX5720 1 19961008 G 5712 95110014167 RIB BEECH 58 58 1152740 CE LT WS 136.188 CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 05 4494A 8311 TH30 DURING A 100-HOUR INSPECTION, FOUND CRACK IN RIB/FORMER AT LOCATION LT WING STA 136.188. SUSPECT CAUSE DUE TO VIBRATION . REPLACE RIB/FORMER. 1 L 7 2 3O 3A16 1996112700528 19961127 00528 CE 1996 11 27 96ZZZX5721 1 19961105 G 2913 99101372 PUMP CESSNA 414 414A 2075907 CE RT HYD PUMP SEAL FAILED H O OTHER J K WARNING INDICATION FLUID LOSS CR CRUISE 1 WP 13 5614C 386 414A0203 LT AND RT HYD LOW FLOW LITES CAME ON IN FLIGHT. LANDING GEAR HAD TO BE EXTENDED USING THE LANDING GEAR EMERGENCY PROCED URE. ACFT LANDED WITHOUT INCIDENT. RIGHT HYD PUMP NOSE SEAL LEAKED HYDRAULIC FLUID OVERBOARD THROUGH THE NOSE CASE DRA IN. PUMP REPLACED. AIRCRAFT RETURNED TO SERVICE. 1 L 7 2 3O A7CE 1996112700529 19961127 00529 SO 1996 11 27 96ZZZX5722 2 19961107 G 8530 653426A13 CYLINDER CESSNA 172 172 2072402 CE CONT O300 O300A 17022 SO EXH GUIDE EXCESS WEAR D L K NONE O OTHER IN INSP/MAINT 1 SW 99 14 THIS FACILITY INSTALLED SIX CYL ASSEMBLIES PREASSEMBLED BY TCM ON AN O300A ENGINE (CESSNA 172). ENGINE WAS OPERATED ON 80/87 AVIATION FUEL AND AEROSHELL 80 MINERAL OIL. AFTER 14 HOURS TOTAL TIME IN SERVICE (TWO MONTHS ELAPSED TIME) LOW CO MPRESSION WAS EXPERIENCED ON THREE CYLINDERS. FURTHER EXAMINATION REVEALED EXHAUST GUIDES WORN BEYOND LIMITS IN ALL SIX CYLINDERS. .007L TO APPROXIMATELY .014L AT THE COMBUSTION END. 1 H 7 1 3O 3 O NT 3A12 E253 1996112700530 19961127 00530 GL 1996 11 27 96ZZZX5723 3 19961018 G 6111 SCM7154 BLADE GULSTM AA1 AA1B 0631206 SO MCAULY 1A105 1A105SCM GL NR 1 BLADE TIP SEPARATED D S A UNSCHED LANDING E D VIBRATION/BUFFET INFLIGHT SEPARATION CR CRUISE 1 EA 17 1447R 193 AA1B0547 G19493 DURING FLIGHT, THE AIRCRAFT BEGAN TO SHAKE VIOLENTLY. AFTER A PRECAUTIONARY LANDING IT WAS FOUND THAT APPROXIMATELY 4.5 INCHES OF THE NR 1 BLADE TIP HAD SEPARATED. A 1.1250 INCH CIRCUMFERENCE BY .0156 INCH DEPTH/NICK WAS LOCATED AT THE PO INT OF SEPARATION. PROPAGATION WAS PROBABLY CAUSED BY EITHER EXCESSIVE STRESS DURING OVERHAUL OR FATIGUE. RECOMMENDATI ON: CLOSER EXAMINATION DURING OVERHAUL TO IDENTIFY STRESS RISERS OR FRACTURES. 1 L 7 1 3O A11EA 5 N P918 1996112700531 19961127 00531 SO 1996 11 27 96ZZZX5724 1 19961104 G 2720 6342002 BAR ASSY 6345905 PIPER PA32 PA32260 7103206 SO RUDDER PEDAL CRACKED D A O OTHER F FLT CONT AFFECTED NR NOT REPORTED 1 SO 19 3927W 4061 4061 32874 PILOT REPORTS EXCESSIVE RT RUDDER APPLICATION WITH LITTLE CONTROL. CLOSE INSPECTION REVEALED RUDDER CONTROL BAR ASSY WA S CRACKED AT LEFT WELD AREA OF CROSS-OVER BAR. SUSPECT CAUSE OF FAILURE MAY HAVE BEEN THE RESULT OF OVER TOW-LIMITS DUR ING GROUND HANDLING OR LACK OF LUBRICATION BETWEEN ROTATING BARS. SUBMITTER RECOMMENDS PERIODIC LUBRICATION AND INSPECT ION OF WELD AREAS. 1 L 7 1 3O A3SO 1996112700532 19961127 00532 CE 1996 11 27 96ZZZX5725 1 19961104 G 2820 040034317 FUEL LINE CESSNA 150 152 2071835 CE LT HAND LEAKING D A K NONE B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 GL 25 6529B 15283944 FUEL FUMES IN CABIN. INSPECTION FOUND FUEL LINE CORROSION PIN HOLE IN LT FUEL LINE. CARPET SATURATED WITH FUEL. REPLA CEMENT OF FUEL LINE REQUIRED. SCHOOL AIRPLANE - ON TIE DOWN OUTSIDE, TRAPPED MOISTURE BEHIND CARPET. 1 H 7 1 3O NT 3A19 1996112700533 19961127 00533 GL 1996 11 27 96ZZZX5726 3 19961114 G 6114 E3943 HUB CESSNA 210 T210K 2073447 CE MCAULY 3A32C D3A32C88 GL MOUNT STUD CRACKED G S K NONE O OTHER IN INSP/MAINT 1 SW 03 8237M 40 T21059237 740765 THE PROPELLER HUB WAS FOUND CRACKED AT 5 OF THE 6 MOUNTING STUDS. THE PROPELLER HAD ACCUMULATED APPROXIMATELY 40 HOURS OF OPERATING TIME SINCE THE LAST OVERHAUL PERFORMED ON 1-10-96. THE CRACKS WERE DISCOVERED BY AN IA WHILE PERFORMING TH E ANNUAL INSPECTION. THE TOTAL TIME OF THE PROPELLER HUB WAS NOT DETERMINED DUE TO INCOMPLETE RECORDS. 1 H 7 1 3O 3A21 5 C P21EA 1996112700534 19961127 00534 SO 1996 11 27 96ZZZX5727 1 19961014 G 2430 6661602 TERMINAL STRAP PIPER PA34 PA34200T 7103406 SO BATTERY BURNED B S APCR K NONE O OTHER NR NOT REPORTED 1 NM 01 8407C 347670137 BRAIDED-WIRE-TYPE BATTERY TERMINAL STRAP BECAME LOOSE AT NEGATIVE TERMINAL CAUSING HIGH RESISTANCE, HEAT, AND ARCING, AN D TOTAL ELECTRICAL SYSTEM FAILURE (INTERMITTENT). SUBMITTER STATED CONCERNS: POSSIBLE EXPLOSION DUE TO BATTERY GASSES. RECURRING PROBLEMS WITH BRAIDED BATTERY TERMINAL STRAP - NUT TORQUE CAUSES DEFORMATION - SHOULD BE CHANGED TO SOLID-TY PE WIRING. SAME FAILURE OCCURRED ON PA31-350 AIRCRAFT. 1 L 7 2 3O A7SO 1996112700535 19961127 00535 EA 1996 11 27 96ZZZX5728 2 19961025 G 7414 10382585 CONTACT POINTS ELECTROSYS LW685124 MOONEY M20 M20J 5870219 SW LYC O360 IO360A3B6 41514 EA MAG FAILED D A UNSCHED LANDING Y ENGINE STOPPAGE CR CRUISE 1 CE 05 1163Z 2361 3012013 241285 L1412151A ENGINE QUIT DURING ROUTINE FLIGHT. REMOVED MAGNETO AFTER FORCED LANDING. FOUND CONTACT POINTS PITTED AN CAM FOLLOWERS WORN OUT TO THE POINT THAT THEY WOULD NO LONGER OPEN THE CONTACTS. SUBMITTER STATED MAGNETOS SHOULD BE INSPECTED ON 500 -HOUR INTERVALS AND POINTS SHOULD BE REPLACED ON CONDITION DURING THESE INSPECTIONS. THE POINTS IN THIS MAG HAD A T.I.S . OF 2361.0 HRS. 1 L 7 1 3O 3 O 2A3 1E10 1996112700536 19961127 00536 SW 1996 11 27 96ZZZX5729 1 19961009 G 6420 212011702001 YOKE BELL 412 412 1182202 SW T/R REQ REPLACEMENT B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 3187 A100062 COMPLY WITH ASB412-96-89 INSPECTION OF T/R YOKE. YOKE REPLACED. 1 G 7 2 4U H4SW 1996020900283 19960209 00283 CE 1996 2 9 96ZZZX573 1 19960117 G 3010 45AS66010005 HORN TIP BEECH MU300 400BEECH CE LT ELEV HEAT ELEMENT FAILED B OG5R K NONE O OTHER IN INSP/MAINT 1 GL 21 3038V 572 9583237 RK93 LEFT HEATED HORN ON ELEVATOR FAILED. INSTALLED NEW HEATED TIP. KIT NR 128-4015-5 PREVIOUSLY INSTALLED. (HORIZONTAL ST ABILIZER LEADING EDGE KIT). 2 H 7 2 4F RT A16SW 1996112700537 19961127 00537 NM 1996 11 27 96ZZZX5730 1 19961029 G 2720 596005003 HYD SOLENOID 65C370529 BOEING 737 7372A6 138448B NM RUDDER PCU CONTAMINATED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 2181A RUDDER PCU INVESTIGATION, FLUID FOUND IN SOLENOID COIL CAUSING FAILURE. 2 L 7 2 4F A16WE 1996112700538 19961127 00538 NM 1996 11 27 96ZZZX5731 1 19961028 G 2710 3170286 FWD MANIFOLD BENDIX 31701203 BOEING 747 747* NM FILTER PORT CRACKED B A IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 7950898 AS DETERMINED BY NDI, AILERON PCU MANIFOLD IS CRACKED IN FILTER PORT ADJACENT CHECK VALVE AND INLET PORTS. SUBMITTER ST ATES THIS IS A CONTINUING DEFECT WITH THIS PART. 2 L 7 4 4F RT A20WE 1996112700539 19961127 00539 NM 1996 11 27 96ZZZX5732 1 19961028 G 2710 3170317 AFT MANIFOLD BENDIX 31701203 BOEING 747 747* NM FILTER PORT CRACKED B A IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 7950898 AS DETERMINED BY NDI, AILERON PCU MANIFOLD IS CRACKED IN FILTER PORT ADJACENT CHECK VALVE AND INLET PORTS. SUBMITTER ST ATED THIS IS A CONTINUING DEFECT WITH THIS PART. 2 L 7 4 4F RT A20WE 1996112700540 19961127 00540 NE 1996 11 27 96ZZZX5733 2 19961011 G 7250 775404 BLADE PWA JT8 JT8D217A 52053 NE TURBINE T4 FAILED H K NONE R PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 SW 05 708485 ENGINE WAS REMOVED FROM SERVICE DUE TO LOST POWER, LOW SPEED AND TURBINE DAMAGE. THE ENGINE WAS DISASSEMBLED TO DETERMI NE CAUSE OF THE TURBINE DAMAGE. ONE T4 BLADE HAD FRACTURED IN HIGH CYCLE FATIGUE CAUSING MASSIVE TURBINE DAMAGE. THE F AILURE IS STILL UNDER INVESTIGATION AT GREENWICH, TX. 4 F E9NE 1996112700541 19961127 00541 SO 1996 11 27 96ZZZX5734 1 19961021 G 7120 553344 BOLT 74888002 PIPER PA42 PA42 7104202 SO LT ENG LT MT FRACTURED B L A GW1R K NONE O OTHER IN INSP/MAINT 1 EA 03 29TF 5338 425501003 DURING ROUTINE INSPECTION THE LEFT ENGINE, LEFT OUTBOARD UPPER ENGINE MOUNT TO FIREWALL RETENTION BOLT, P/N 553-344 WAS FOUND FRACTURED. PART TOTAL TIME WAS 5338.1 HRS. LIFE LIMIT FOR THE PART PER PIPER MTC. MANUAL (P/N 761.523 CHAPTER 5 IS 7,500 HRS. IT WAS DECIDED TO REPLACE ALL ENGINE MOUNT TO FIREWALL BOLTS (P/N 553-344) AT THIS TIME.) 1 L 7 2 4T A23SO 1996112700542 19961127 00542 EU 1996 11 27 96ZZZX5735 1 19961106 G 3320 61213 BALLAST BAC106075213 HWKSLY DH125 DH125400A 4230140 EU CABIN LIGHTS FAILED D A K NONE B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 SW 05 45NQ 11522 3501 NA749 DURING PRE-FLIGHT INSPECTION, CABIN FILLED WITH SMOKE. BALLAST CASE WAS CRACKED AND MATERIAL RUNNING OUT. SUBMITTER SU GGESTS DISABLING THE INTERIOR LIGHTING SYSTEM. NOTE: REF AD 95-22-01. 2 L 7 2 4J A3EU 1996112700544 19961127 00544 EU 1996 11 27 96ZZZX5737 1 19960901 G 3213 350A41108601 CROSS TUBE SNIAS 350 AS350B1 8680811 EU LANDING GEAR CORRODED H L K NONE O OTHER IN INSP/MAINT 1 EA 31 2FOR 1948 2233 SEVERE CORROSIONS FOUND UNDER THE CHAFING STRIPS OF THE LANDING GEAR CROSS TUBES. 1 G 7 1 3U H9EU 1996112700545 19961127 00545 EU 1996 11 27 96ZZZX5738 1 19960901 G 3213 350A41108700 CROSS TUBE SNIAS 350 AS350B1 8680811 EU LANDING GEAR CORRODED H K NONE O OTHER IN INSP/MAINT 1 EA 31 2FOR 1948 2233 SEVERE CORROSIONS FOUND UNDER THE CHAFING STRIPS OF THE LANDING GEAR CROSS TUBES. 1 G 7 1 3U H9EU 1996112700546 19961127 00546 NE 1996 11 27 96ZZZX5739 2 19961017 G 7320 5225742 VALVE WOODWARD 8061531 GE CFM56 CFM565A 13802 NE HMU MISMANUFACTURED D L K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 03 1119 WOODWARD HMU WAS RECENTLY RETURNED FROM SINGAPORE AIRLINES DUE TO A REPORTED COMPLAINT OF 'HP FUEL VALVE DID NOT OPEN DU RING ENG START'. THE SUBSEQUENT INVESTIGATION REVEALED THAT THE FUNCTIONAL OBSERVATION WAS THE RESULT OF AN IMPROPERLY MACHINED PART. P/N 5225-742 FEATURES A THRUST BEARING DIAMETER WHICH EXTENDS TO AN ADJACENT SHOULDER (RELIEF GROOVE). T HE SHOULDER POSITIONS THE BEARING AND WITHSTANDS THE OPERATING THRUST LOADS. IN THE CASE OF THE IMPROPERLY MACHINED PAR T, THE BEARING DIAMETER WAS THE PROPER SIZE BUT DID NOT FULLY EXTEND INTO A GRINDING RELIEF GROOVE. 4 F E29NE 1996112700547 19961127 00547 EU 1996 11 27 96ZZZX5740 1 19961004 G 3411 PITOT TYS AIRBUS 300 A300B4203 3930306 EU CAPT AIRSPEED OBSTRUCTED D C D ABORTED TAKEOFF RETURN TO BLOCK O OTHER TO TAKEOFF 1 SW 99 225KW 093 ABORTED TAKEOFF DUE NO AIRSPEED IND ON CAPT AND F/O AIRSPEED IND. BLEW OUT DEBRIS (BUG DEBRIS) FROM CAPTS AND F/O'S PIT OT LINES AND TUBES. FUNCTIONAL CHECK OF AIRSPEED INDICATORS OK. LEAK CHECK OK. 2 L 7 2 4F A35EU 1996112700548 19961127 00548 CE 1996 11 27 96ZZZX5741 1 19961105 G 2121 BWT141100121B SILENCER BEECH 60 60 1153602 CE BLEED AIR RUPTURED D K NONE O OTHER IN INSP/MAINT 1 SW 05 211FX 315 076 WHILE PERFORMING FINAL ENGINE RUNS AND AIRFRAME SYSTEMS CHECK OUT FOLLOWING INITIAL 300/600 HOUR INSPECTIONS, BOTH ENGIN E BLEED AIR SOURCES WERE TURNED ON TO CHECK AIR DISTRIBUTION SYSTEM. CABIN AND COCKPIT WERE SHOWERED WITH FIBERGLASS FR OM AIR DUCTS. FOUND LT BLEED DUCT AIR SILENCER, LT SIDE OF AFT CABIN BAGGAGE COMPARTMENT, HAD RUPTURED. CLEANED AIRCRA FT AND DUCTS. INSTALLED NEW SILENCER. OPS CHECKS NORMAL. RECOMMENDATION: NEED TO ADD VISUAL INSPECTION OF THESE DUCT S TO 300 OR 600 HOUR INSPECTION GUIDE. 1 L 7 2 3O A12CE 1996112700549 19961127 00549 CE 1996 11 27 96ZZZX5742 1 19961023 G 5313 STRINGER BEECH 200 200BEECH 1152920 CE AFT FUSELAGE CRACKED B A BDTR K NONE O OTHER IN INSP/MAINT 1 SO 09 607KW 5918 BB977 AD 93-25-07. SB 2472RII. VISUAL INSPECTION C/W 8-28-96 AT 5845.3 HOURS. AT TIME OF 5918.1 AND 10-22-96, THE NR 9 AND NR 10 STRINGERS WERE FOUND CRACKED UNDER THE SEALER (RIGHT SIDE). SUBMITTER STATED NOTIFIED BEECH TECH REP ABOUT THIS P ROBLEM AND DO BELIEVE THAT THE AD AND SB MUST BE CHANGED TO REFLECT THE CRACKS BEING CONCEALED UNDER THE SEALER. NEITHE R AD OR SB ARE REQUESTING THAT THE SEALER BE REMOVED FOR THE USUAL INSPECTION. 1 L 7 2 4T A24CE 1996112700551 19961127 00551 EA 1996 11 27 96ZZZX5744 2 19961122 G 8530 PISTON P IN PIPER PA34 PA34200 7103405 SO LYC O360 LIO360C1E6 41515 EA ENG CYL FAILED B A KM5R K NONE O OTHER IN INSP/MAINT 1 GL 15 55425 215 347350213 L70461A PISTON PIN BROKE IN 2 PIECES CAUSING A CATASTROPHIC ENGINE FAILURE. OCTOBER 8, 1996, LYCOMING ISSUED A MANDATORY SB NR 527B PERTAINING TO THIS SUBJECT. THE PISTON PIN THAT FAILED HAD THE SAME CODE MARKED ON IT (17328) THAT THE SERVICE BUL LETIN STATED MUST BE REPLACED. SUBMITTER RECOMMENDS SB 527B BE REPLACED WITH AN AD. MAINTENANCE RECORD REPORT NR 96-01 1-8520. 1 L 7 2 3O 3 O A7SO 1E10 1996112700552 19961127 00552 SO 1996 11 27 96ZZZX5745 1 19961112 G 2740 481640 PULLEY PIPER PA32 PA32300 7103212 SO STABILATOR TRIM WORN B S A AJ4R K NONE O OTHER IN INSP/MAINT 1 WP 21 4272R 3509 3240647 AT THE ANNUAL INSPECTION WHILE CHECKING AND LUBING TRIM CABLE PULLEY FOR STABILATOR, FOUND RIGHT PULLEY WORN IN HALF. B EARING CHECKED GOOD. CABLE CHECKED GOOD. PART TOTAL TIME 3509 HRS. 1 L 7 1 3O A3SO 1996112700553 19961127 00553 SO 1996 11 27 96ZZZX5746 1 19961111 G 3411 5631903 GAUGE PIPER PA31T PA31T 7103124 SO PNEU PRESS CRACKED B S DYPR K NONE O OTHER IN INSP/MAINT 1 NM 09 47CA 3195 31T7920043 PILOT REPORTED THAT THE PRESSURIZATION WOULD NOT REACH 5.5 DIFFERENTIAL PRESSURE, BUT THE CABIN ALTITUDE WAS CORRECT FOR THE AIRCRAFT ALTITUDE. FOUND THE INSTRUMENT PRESSURE GAUGE CRACKED BEHIND THE BEZEL. THIS IS CONNECTED INTO THE ALTIM ATIC STATIC SYSTEM AND IS INSIDE THE CABIN PRESSURE VESSEL AND WAS LEAKING CABIN AIR INTO THE SYSTEM. 1 L 7 2 3T A8EA 1996120500001 19961205 00001 EU 1996 12 5 96ZZZX5747 1 19960812 G 3310 1179203103 CONTROL UNIT BOLKMS 117 BK117A3 5626015 EU LIGHTS FAILED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 118LL 5 0858 7097 INTERNAL ELECTRICAL DAMAGE. POPS CIRCUIT BREAKER. INSTALLED ONLY 4.9 HRS BEFORE FAILURE. 1 G 7 2 3U H13EU 1996120500002 19961205 00002 EU 1996 12 5 96ZZZX5748 1 19960816 G 2150 JBS141161 COMPRESSOR BOLKMS BK117 BK117C1 5626025 EU CABIN SEIZED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 317MC 0151304100 7505 COMPRESSOR WILL NOT TURN - LOCKED UP - CLUTCH. 1 G 7 2 3U NC H13EU 1996120500003 19961205 00003 EU 1996 12 5 96ZZZX5749 1 19960708 G 6520 4639310006 BEARING BOLKMS BK117 BK117C1 5626025 EU T/R SCORED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 317MC 1318 2224 7505 BEARING ROLLERS ARE SCORED. 1 G 7 2 3U NC H13EU 1996120500004 19961205 00004 EU 1996 12 5 96ZZZX5750 1 19960817 G 6520 4639310005 BEARING BOLKMS BK117 BK117C1 5626025 EU T/R DAMAGED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 317MC 1452 7505 DAMAGE TO OUTER RACE FROM METAL CONTAMINATION. 1 G 7 2 3U NC H13EU 1996120500005 19961205 00005 EU 1996 12 5 96ZZZX5751 1 19960708 G 6520 4639306006 BEARING BOLKMS BK117 BK117C1 5626025 EU T/R SCORED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 317MC 1318 1729 7505 BEARING ROLLERS ARE SCORED. 1 G 7 2 3U NC H13EU 1996120500006 19961205 00006 EU 1996 12 5 96ZZZX5752 1 19960708 G 6520 4639311005 SHAFT BOLKMS BK117 BK117C1 5626025 EU T/R OUTPUT DAMAGED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 317MC 1318 350 7505 HEAVY SCRAPE MARK ON I.D. OF SHAFT GOES THROUGH SILVER PLATING INTO THE BARE METAL AND THIS IS REASON FOR REJECTION IAW CORRECT REM 3095 MANUAL. 1 G 7 2 3U NC H13EU 1996120500007 19961205 00007 EU 1996 12 5 96ZZZX5753 1 19960802 G 5412 1176625502 FIREWALL BOLKMS BK117 BK117C1 5626025 EU ENGINE CRACKED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 317MC 7505 FIREWALL CRACKED. 1 G 7 2 3U NC H13EU 1996120500008 19961205 00008 EU 1996 12 5 96ZZZX5754 1 19960802 G 5412 1176625501 FIREWALL BOLKMS BK117 BK117C1 5626025 EU ENGINE CRACKED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 317MC 7505 FIREWALL CRACKED. 1 G 7 2 3U NC H13EU 1996120500009 19961205 00009 EU 1996 12 5 96ZZZX5755 1 19961007 G 6720 117317171 BELLCRANK BOLKMS BK117 BK117C1 5626025 EU T/R BEARING WORN B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 317MC 7505 T/R BELLCRANK BEARINGS WORN. 1 G 7 2 3U NC H13EU 1996120500010 19961205 00010 EU 1996 12 5 96ZZZX5756 1 19960614 G 6320 4639305011 SPACER TUBE BOLKMS BK117 BK117C1 5626025 EU M/R GRBOX WORN B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 317MC 1355 7505 SPACER TUBE WORN BEYOND LIMITS. 1 G 7 2 3U NC H13EU 1996120500011 19961205 00011 EU 1996 12 5 96ZZZX5757 1 19960614 G 6210 10514101111 BLADE BOLT BOLKMS BK117 BK117C1 5626025 EU M/R WORN B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 317MC 7505 BLADE BOLT WORN BEYOND LIMITS. SCRAPED PARTS ON SITE. REPLACED 2 EA. 1 G 7 2 3U NC H13EU 1996120500012 19961205 00012 EU 1996 12 5 96ZZZX5758 1 19960614 G 6220 1051418206 RING BOLKMS BK117 BK117C1 5626025 EU M/R GROOVED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 317MC 1355 7505 GROOVED RING. REPLACED 4 EA. 1 G 7 2 3U NC H13EU 1996120500013 19961205 00013 EU 1996 12 5 96ZZZX5759 1 19960810 G 6730 7012693901 SERVO BOLKMS BK117 BK117C1 5626025 EU SERVO SYS DEFECTIVE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 317MC 90100154 7505 SERVO MOTOR CAUSES ERROR CODES. 1 G 7 2 3U NC H13EU 1996120500014 19961205 00014 EU 1996 12 5 96ZZZX5760 1 19961007 G 6720 11731822 PITCH LINK BOLKMS BK117 BK117C1 5626025 EU T/R CONT BEARING PLAY B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 317MC 7505 PLAY IN BEARINGS, 2 EA PITCH LINK ASSY. 1 G 7 2 3U NC H13EU 1996120500015 19961205 00015 EU 1996 12 5 96ZZZX5761 1 19961010 G 6320 1179586901 WIRE BOLKMS BK117 BK117C1 5626025 EU NR 1 TRANS SHORTED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 317MC 1637 7505 NR 1 TRANS PRESSURE PLUG SHORTING OUT CAUSING FLUCTUATION IN GAUGE. 1 G 7 2 3U NC H13EU 1996120500016 19961205 00016 EU 1996 12 5 96ZZZX5762 1 19960825 G 7714 1179405303 TRIPLE TACH BOLKMS 117 BK117A3 5626015 EU NR 2 ENG NEEDLE STICKS B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 4493X 390 170 S7038 NR 2 ENGINE NEEDLE STICKS - SUBMITTER STATES UNIT WAS REPAIRED FOR SAME DISCREPANCY LAST REPAIR. 1 G 7 2 3U H13EU 1996120500017 19961205 00017 1996 12 5 96ZZZX5763 4 19960813 G 3421 40205773 GYRO BOLKMS 117 BK117A3 5626015 EU COCKPIT MALFUNCTION B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 4493X 375 80031622 S7038 RMI AND HSI CARDS WANDER. 1 G 7 2 3U H13EU 1996121800001 19961218 00001 EU 1996 12 18 96ZZZX5764 1 19960901 G 7714 32005008 TACH GENERATOR BOLKMS 105 BO105S 5626006 EU ENG FAILED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 495LF 2 164718 S645 TACH GEN DRIVE SHAFT DISENGAGED FROM INTERNAL DRIVE PIN. 1 G 7 2 3U H3EU 1996120500018 19961205 00018 SW 1996 12 5 96ZZZX5765 1 19961011 G 7810 206064300005 EXHAUST BELL 206 206L1 1182107 SW FLANGE WELD CRACKED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 721SP 45486 EXHAUST CRACKED AT FLANGE ALONG WELD. 1 G 7 1 3U H2SW 1996120500019 19961205 00019 CE 1996 12 5 96ZZZX5766 1 19960817 G 2422 PC17A INVERTER BEECH 200 B200 1152922 CE AC SYS INOPERATIVE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 75LV 86 7407A BB1075 INVERTER INOP. NO AC OUTPUT. 1 L 7 2 4T A24CE 1996120500020 19961205 00020 1996 12 5 96ZZZX5767 4 19960819 G 3421 222375033101 INDICATOR BELL 222 222 1182122 SW COCKPIT ATTITUDE FAILED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 911LW 1 0143 47520 INDICATOR WILL NOT DROP 'OFF' FLAG. PRECESSES AFTER 4-5 MINUTES. 1 G 7 2 3U H9SW 1996120500021 19961205 00021 1996 12 5 96ZZZX5768 4 19960817 G 3421 222375033101 INDICATOR BELL 222 222 1182122 SW COCKPIT ATTITUD MALFUNCTION B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 911LW 3 0188 47520 PRECESSES 8 TO 10 DEGREES NOSE DOWN IN 3 TO 4 MINUTES. DOES NOT FULLY RECOVER FROM NOSE DOWN ATTITUDE. 1 G 7 2 3U H9SW 1996120500022 19961205 00022 SW 1996 12 5 96ZZZX5769 1 19960823 G 7331 912042T38D METER BELL 222 222 1182122 SW LYC LTS101 LTS101750C1 41560 NE FUEL FLOW MALFUNCTION B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 911LW 78 1252 47520 FUEL FLOW METER WILL NOT COMPLETE SELF-TEST. FAILED AFTER ONLY 77.8 HRS INSTALLED. 1 G 7 2 3U 3 U H9SW E5NE 1996020900287 19960209 00287 SO 1996 2 9 96ZZZX577 2 19960110 G 8530 646101CN CYLINDER CESSNA 421 421B 2076014 CE CONT O520 GTSIO520H 17032 SO CYLINDERS 1-6 COATING FAILED D A K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 11 707SP 49 421B0411 267057R INSPECTION FOUND CERMINIL CYLINDER PROCESS HAS FAILED. PARTICLES COMING LOOSE IN SMALL PIECES. CONTAMINATION IS PASSIN G THROUGH ENTIRE OIL SYSTEM. BEARINGS ARE DAMAGED BEYOND FURTHER USE. CAMSHAFT AND LIFTERS ARE DAMAGED. SUBMITTER STA TED ALL ACCESSORIES THROUGH WHICH OIL HAS PASSED MUST BE INSPECTED AND/OR REPAIRED. 1 L 7 2 3O 3 O A7CE E7CE 1996120500023 19961205 00023 1996 12 5 96ZZZX5770 4 19960922 G 2312 40001452500 TRANSCEIVER BOLKMS 117 BK117A3 5626015 EU COCKPIT INOPERATIVE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 911MZ 294 7098 INOP WHEN INSTALLED IN A/C - WILL NOT TRANSMIT. 1 G 7 2 3U H13EU 1996120500024 19961205 00024 EU 1996 12 5 96ZZZX5771 1 19960720 G 6240 10594564 INDICATOR BOLKMS 105 BO105LSA3 5626020 EU MAST MOMENT INTERMITTENT B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 911SV 172 1881 2033 SYSTEM OPERATES INTERMITTENTLY. UNIT LASTED LESS THAN 4 MO. IN OPERATION. 1 G 7 2 3U H3AU 1996120500025 19961205 00025 EU 1996 12 5 96ZZZX5772 1 19960720 G 6240 10594575 TRANSMITTER BOLKMS 105 BO105LSA3 5626020 EU MAST MOMENT INTERMITTENT B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 911SV 172 1881 2033 SYSTEM OPERATES INTERMITTENTLY. UNIT LASTED LESS THAN 4 MO. IN OPERATION. 1 G 7 2 3U H3AU 1996020900288 19960209 00288 SO 1996 2 9 96ZZZX578 1 19960104 G 3213 75215004 HOUSING PIPER PA42 PA421000 7104225 SO LT MLG STRUT FAILED B A AU3R O OTHER O OTHER TO TAKEOFF 1 WP 15 42MD 2284 425527015 AIRCRAFT WAS MODIFIED WITH LONG RANGE FUEL TANKS FOR FLIGHT TO AUKLAND, NEW ZEALAND FROM OAKLAND, CALIFORNIA. AIRCRAFT WAS APPROVED FOR OVERWEIGHT TAKEOFF. DURING TAKEOFF ROLL, LEFT MLG COLLAPSED CAUSING EXTENSIVE DAMAGE TO AIRCRAFT. MLG HOUSING WAS INSPECTED APPROXIMATELY 10 HOURS EARLIER IAW PIPER SB 929A. METALLURGICAL EXAM REVEALED FAILURE OF HOUSING BEGAN AT THE AREA ADDRESSED BY SB 929A. SUBMITTER RECOMMENDS EITHER INCREASING THE INSPECTION INTERVAL OF SB 929A, OR REPLACING HOUSINGS WITH NEW IMPROVED STYLE, DASH 006 HOUSING OR MORE THOROUGH INSPECTION PROCESS. 1 L 7 2 4T RT A23SO 1996020900289 19960209 00289 SO 1996 2 9 96ZZZX579 1 19960104 G 3230 40336000 LINK PIPER PA42 PA42 7104202 SO NLG RT DRAG LINK CRACKED B A AU3R K NONE O OTHER IN INSP/MAINT 1 WP 15 700VF 3763 428001053 DURING A SCHEDULED INSPECTION, THE RIGHT NLG DRAG LINK WAS FOUND CRACKED ON THE FORWARD SIDE OF THE INBOARD LUG THAT THE NLG ACTUATOR ATTACHES TO. SUBMITTER RECOMMENDS SCHEDULED INSPECTIONS OF THIS AREA. THIS IS THE SECOND OCCURRENCE. 1 L 7 2 4T A23SO 1996020900290 19960209 00290 SO 1996 2 9 96ZZZX580 1 19960122 G 3222 9572300 TRUNNION PIPER PA34 PA34200 7103405 SO NLG CRACKED D S A K NONE O OTHER IN INSP/MAINT 1 EA 21 16LL 5633 347250050 DURING ANNUAL INSPECTION, THE NLG TRUNNION WAS FOUND CRACKED .25 INCH AT THE RIGHT STAY ARM WELD JOINT. 1 L 7 2 3O A7SO 1996120500134 19961205 00134 NE 1996 12 5 96ZZZX5800 2 19960729 G 7250 414129001 PT ROTOR BOLKMS 117 BK117A3 5626015 EU LYC LTS101 LTS101650B1 41560 NE ENG DEFECTIVE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 03 311LF 1890 SC12211 7070 LE45121 C/W SB 0153 R1. PT ROTOR REPLACED. 1 G 7 2 3U 3 U H13EU E5NE 1996120500318 19961205 00318 1996 12 5 96ZZZX5801 1 19961016 G 2822 2B6540 PUMP AIRBORNE FUEL SYS FAILURE D K NONE O OTHER NR NOT REPORTED 1 GL 13 7B166 FUEL PUMP ARMATURE OUT OF DYNAMIC BALANCE CAUSING PREMATURE FAILURE OF THE PUMP. 1996120500319 19961205 00319 EU 1996 12 5 96ZZZX5802 1 19961105 G 7160 115C6602 AIR BOX GROB G115 G115C 1660303 EU INDUCTION AIR CRACKED D A K NONE O OTHER IN INSP/MAINT 1 NM 03 115AK 72 82054C2 DURING ACCEPTANCE INSPECTION ON NEW GROB AIRCRAFT WITH 72.2 HOURS SINCE NEW, FOUND INDUCTION AIR BOX CRACKED IN NUMEROUS LOCATIONS. LT AND RT FWD SIDES CRACKED, TOP L SIDE DOUBLER FWD OF CARBURETOR ADAPTOR CRACKED. CRACKS ARE ATTRIBUTED T O PROPELLER/ENGINE VIBRATION. BOTH ENGINE AND PROPELLER HAVE 72.2 HOURS SINCE NEW. DYNAMIC BALANCE TO BE ACCOMPLISHED TO REMEDY CRACKING. 1 L 7 1 3O NT A57EU 1996120500320 19961205 00320 SO 1996 12 5 96ZZZX5803 2 19961018 G 8550 538937 TUBE BEECH 35 K35 1151524 CE CONT O470 IO470C 17026 SO OIL SUMP BROKEN D S K NONE O OTHER IN INSP/MAINT 1 GL 19 192AA 4306 D5964 716589C DISASSEMBLING ENG FOR OVERHAUL FOUND THE OIL SUCTION TUBE WAS BROKEN IN 2 PLACES. TUBE WAS BROKE OFF FROM SCREEN AND ON E OF THE ATTACHING ANGLES WAS BROKEN BY BOLT HOLE. TT ENG 4306.44. SMOH 1448.84. 1 L 7 1 3O 3 O 3A15 E273 1996120500321 19961205 00321 CE 1996 12 5 96ZZZX5804 1 19961030 G 2750 58651053 BELLCRANK CESSNA 441 441 2076020 CE LT-RT FLAP IDLER LOOSE B FE6R K NONE O OTHER IN INSP/MAINT 1 NM 11 2722Y 3944 4410173 THE LEFT AND RIGHT FLAP IDLER BELLCRANKS, BOTH P/N 5865105-3, ARE FOUND TO BE WORKING BETWEEN THE CAST ARM AND THE TUBUL AR BEARING SUPPORT COLUMN. THE 4 SECURING RIVETS ALSO APPEAR TO BE LOOSE BUT NOT SHEARED. SUBMITTED STATED IT IS BELIE VED THAT RIVET FAILURE WOULD RESULT IN FLAP BINDING. THESE WERE FOUND ON A RELATIVELY LOW TIME AIRCRAFT (UNDER 4000 HRS ). SERVICEABLE BELLCRANKS WERE INSTALLED. 1 L 7 2 3T RT A28CE 1996120500322 19961205 00322 SO 1996 12 5 96ZZZX5805 1 19961028 G 3260 1CH214 SWITCH PIPER PA31 PA31350 7103110 SO RT MLG DEFECTIVE D O OTHER P NO WARNING INDICATION AP APPROACH 1 GL 23 35871 313052123 RIGHT MAIN GEAR FAILED TO SHOW GEAR DOWN AND LOCKED UPON LANDING. RETRACTION TEST ON GROUND FOUND SWITCH PIPER PN 487-8 62 DEFECTIVE. REMOVED AND REPLACED WITH NEW PART. SYSTEM CHKS NORMAL. 1 L 7 2 3O A20SO 1996120500323 19961205 00323 SO 1996 12 5 96ZZZX5806 2 19961106 G 8530 630046 PISTON PIN PIPER PA46 PA46310P 7104605 SO CONT O520 TSIO520BE 17040 SO NR 4 CYL BROKEN G K NONE O OTHER IN INSP/MAINT 1 GL 19 37VM 1779 468508002 273577R REMOVED NR 4 CYLINDER FOR MAINTENANCE. FOUND PISTON PIN INTERNAL PIN BROKEN. INSTALLED NEW P/N 630046 PIN ASSY WITH EX CHANGE CYLINDER ASSY. 1 L 7 1 3O 3 O A25SO E8CE 1996120500324 19961205 00324 EA 1996 12 5 96ZZZX5807 2 19961024 G 7310 60100030092 HOSE CESSNA 177 177B 2073708 CE LYC O360 O360A1F6 41514 EA ENG FUEL LEAKING B BXSR K NONE K FLUID LOSS IN INSP/MAINT 1 EA 09 34933 17702099 PILOT REPORTED A FUEL LEAK FROM THE ENGINE COMPARTMENT. FOUND THE FUEL PRESSURE HOSE LEAKING. THIS PROBLEM HAS BEEN AD DRESSED BY AEROQUIP SB AA135. THIS HOSE WAS DATED 2Q86. ALTERNATE P/N FROM CESSNA: S1236-3-0092. 1 H 7 1 3O 3 O A13CE E286 1996120500325 19961205 00325 EA 1996 12 5 96ZZZX5808 2 19961004 G 7414 M3215 CARBON BRUSH SLICK 6393 PIPER PA23 PA23250 7102308 SO LYC O540 IO540C4B5 41532 EA ENG MAG EXCESS WORN D K NONE O OTHER IN INSP/MAINT 1 EA 05 415CC 336 91110003 273908 RL1063248 OWNER REPORTED EXCESSVIE MAG DROP INTERMITTENTLY RIGHT ENG LEFT MAG. NOTICED EXCESSIVE CARBON DUST AROUND MAG VENT. PUL LED MAG AND OPENED UP EVERYTHING COATED WITH CARBON DUST. SUBMITTER STATED BRUSH WORN TOO QUICKLY. MANUFACTURE BRUSH F ROM HARDER SUBSTANCE. 1 L 7 2 3O 3 O 1A10 1E4 1996120500326 19961205 00326 SO 1996 12 5 96ZZZX5809 2 19961106 G 7310 646425 LINE PIPER PA46 PA46310P 7104605 SO CONT O520 TSIO520BE 17040 SO NR 5 CYL INJ BROKE G K NONE O OTHER IN INSP/MAINT 1 GL 19 4323D 3475 1884 468408018 528375 NR 5 CYLINDER FUEL INJECTOR LINE BROKE. SUBMITTER RECOMMENDS DIFFERENT TYPE CLAMPING SYSTEM BE USED ON THESE FUEL INJEC TION LINES. CURRENT SYSTEM ALLOWS FOR ALOT OF VIBRATION. 1 L 7 1 3O 3 O A25SO E8CE 1996020900291 19960209 00291 CE 1996 2 9 96ZZZX581 1 19960104 G 3233 3A0540201 BARREL 3A0500002 CESSNA 185 185 2072802 CE LT MLG ACTUATOR CRACKED B OG5R K NONE K FLUID LOSS IN INSP/MAINT 1 GL 21 185ND 2030 18504369 HYDRAULIC FLUID WAS OBSERVED DRIPPING FROM LEFT GEAR WELL DURING 100-HOUR ANNUAL INSPECTION. OPERATIONAL CHECK OF GEAR FOUND MAIN GEAR ACTUATOR BARREL CRACKED. BARREL PART NUMBER IS 3A05402-01. CRACK LOCATED AT MIDDLE AREA AND EXTENDS LE NGTHWISE APPROXIMATELY 1 INCH. THERE DOES NOT APPEAR TO BE ANY MARKS IN THIS AREA TO CAUSE CRACK. 1 H 7 1 3O NC 3A24 1996120500327 19961205 00327 SO 1996 12 5 96ZZZX5810 1 19961104 G 2913 HYC5005 POWER PACK PIPER PA34 PA34200T 7103406 SO MLG FAILED D O OTHER O OTHER NR NOT REPORTED 1 GL 21 47611 268 1803 347770418 LANDING GEAR POWER RACK WOULD NOT PUT GEAR IN EXTENDED POSITION - UPON DISASSEMBLY - COMMUTATOR ARMATURE SEEMED TO BE 'O UT OF ROUND DUE TO THE BRUSH MARKS. THE BRUSHES WERE NOT WORN EXCESSIVE. 1 L 7 2 3O A7SO 1996120500328 19961205 00328 EA 1996 12 5 96ZZZX5811 2 19961101 G 7322 105135 CARBURETOR FACET PIPER PA28 PA28140 7102802 SO LYC O320 O320E2D 41508 EA GASKET MISOVERHAULED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 EA 07 5AU 289 CK35802 287725339 CARBURETOR RUNNING OVER RICH. AFTER DISASSEMBLY, FOUND STICKY MATERIAL (PROBABLY FUEL LUBE TM) ON PARTING SURFACE GASKE T COVERING ENTIRE GASKET. THIS CARB HAS HAD OTHER WORK DONE SINCE GASKET WAS INSTALLED. SUBMITTER STATED MECHANIC ERRO R? 1 L 7 1 3O 3 O 2A13 E274 1996120500329 19961205 00329 SW 1996 12 5 96ZZZX5812 1 19961017 G 3233 EA1165 ACTUATOR OZONE 631 GULSTM 680 680E 0141604 SW RT MLG FAILED H O OTHER K FLUID LOSS AP APPROACH 1 EA 17 50 9 680E81862 INTERNAL FAILURE OF RT MLG ACTUATOR CAUSED TOTAL HYDRAULIC FLUID DEPLETION WITH SUBSEQUENT EMERGENCY EXTENSION OF LANDIN G GEAR WITHOUT INCIDENT. ACTUATOR WAS RECEIVED NEW. ASSEMBLY DATE IS 1/90 AND WAS INSTALLED 6/96. TSN IS 8.6 HRS AND 6 LANDINGS. 1 H 7 2 3O 2A4 1996120500330 19961205 00330 GL 1996 12 5 96ZZZX5813 3 19961111 G 6111 7666A BLADE PIPER PA28 PA28R180 7102809 SO HARTZL HCC2Y HCC2YK1 GL SHANK CRACKED B QV9R O OTHER E VIBRATION/BUFFET CR CRUISE 1 EA 13 7527J 1994 28R30898 CH11993 PROPELLER EXPERIENCED VIBRATION DURING FLIGHT. PROPELLER REMOVED FOR INSPECTION FOR CAUSE OF VIBRATION. FOUND BLADE SH ANK FAILURE AS DESCRIBED IN AD 77-12-06. 1 L 7 1 3O 2A13 5 C P920 1996120500331 19961205 00331 SW 1996 12 5 96ZZZX5814 1 19961106 G 3243 35202 PISTON PARKERHANFIN 305 MOONEY M20 M20B 5870206 SW LT MLG BRAKE STUCK G O OTHER O OTHER LD LANDING 1 NM 09 74796 1796 DURING LANDING, THE LEFT BRAKE LOCKED AT FIRST APPLICATION. THE LEFT TIRE SKIDDED AND THE AIRCRAFT LEFT THE RUNWAY. LA TER, THE BRAKE RELEASED AND THE AIRCRAFT WAS TAXIED TO MAINT. A MECH DETERMINED THAT HYD FLUID SEEPAGE HAD CONGEALED AR OUND THE PISTON, PREVENTING ITS RETRACTION. 1 L 7 1 3O 2A3 1996120500332 19961205 00332 SO 1996 12 5 96ZZZX5815 1 19961112 G 7603 3092902 CONTROL CABLE PIPER PA25 PA25235 7102504 SO THROTTLE BROKEN D A K NONE O OTHER IN INSP/MAINT 1 GL 21 77852 253989 WHILE RUNNING UP ENGINE AFTER ANNUAL, THROTTLE CABLE BROKE INSIDE THE HOUSING BECAUSE OF EXCESSIVE WEAR. BECAUSE OF THE INCIDENT, INSPECTED 2ND ACFT AND FOUND CABLE WORN THROUGH IN THE SAME SPOT, CABLE IS NEARLY IMPOSSIBLE TO INSPECT. SUB MITTER RECOMMENDS THROTTLE CABLES BE REPLACED ON AIRCRAFT WITH 300 HRS OR MORE. 1 L 7 1 3O 2A10 1996120500333 19961205 00333 CE 1996 12 5 96ZZZX5816 1 19961111 G 3213 508100324 TORQUE KNEE BEECH 90 E90 1152914 CE RT MLG UPPER CRACKED H K NONE O OTHER IN INSP/MAINT 1 SW 99 87CH 10078 LW20 AFTER AN INCIDENT CAUSED BY AN UPPER TORQUE KNEE FAILURE, OTHER AIRCRAFT IN THE FLEET ARE BEING INSPECTED. DURING THIS INSPECTION THE UPPER TORQUE KNEE ON THE RIGHT GEAR WAS VISUALLY FOUND TO BE CRACKED. A NEW UNIT WAS INSTALLED. BOTH TH E NEW UNIT AND THE OLD UNIT ARE OF THE SAME P/N BUT THE NEW UNIT IS DIFFERENT THAN THE OLD. 1 L 7 2 3T 3A20 1996120500334 19961205 00334 EA 1996 12 5 96ZZZX5817 2 19961104 G 7314 LW15473 PUMP PIPER PA32 PA32301 7103207 SO LYC O540 IO540K1G5 41532 EA ENG FUEL SEAL FAILED D K NONE O OTHER IN INSP/MAINT 1 EA 07 80426 1670 328306028 L2213948A TROUBLESHOOTING REASON FOR SPORADIC/INTERMITTENT FUEL FLOW INDICATIONS. FOUND FLOW WAS LOW AND WAS CHANGING - FOUND ME CHANICAL FUEL PUMP SEAL FAILED ALLOWING ENGINE OIL TO FILL MOST BOTTOM CHAMBER OF PUMP BELOW LOWEST DIAPHRAGM. SUSPECT THAT THIS WAS NOT ALLOWING DIAPHRAGM FULL MOVEMENT AND THUS RESTRICTING FUEL FLOW. 1 L 7 1 3O 3 O A3SO 1E4 1996120500335 19961205 00335 SO 1996 12 5 96ZZZX5818 1 19961101 G 2140 A08D49 BLOWER MOTOR PIPER PA34 PA34200T 7103406 SO COMBUSTION AIR FAILED D K NONE O OTHER CR CRUISE 1 GL 21 812JA 440 1025931 347970422 COMBUSTION AIR BLOWER MOTOR QUIT DURING FLIGHT. BRUSHES WERE OK. REPLACMENT WAS ACCOMPLISHED. HEATER OPERATION NORMAL . 1 L 7 2 3O A7SO 1996120500336 19961205 00336 SO 1996 12 5 96ZZZX5819 2 19961105 G 8530 630046 PISTON PIN PIPER PA46 PA46310P 7104605 SO CONT O520 TSIO520BE 17040 SO NR 4 CYL BROKEN G K NONE O OTHER IN INSP/MAINT 1 GL 19 9133G 808 4608111 528427 REMOVED NR 4 CYLINDER FOR MAINTENANCE FOUND PISTON PIN INTERNAL PIN BROKEN. INSTALLED NEW P/N 630046 PIN ASSY WITH EXCH ANGE CYLINDER ASSY. 1 L 7 1 3O 3 O A25SO E8CE 1996020900292 19960209 00292 SO 1996 2 9 96ZZZX582 1 19960120 G 2820 HOSE PIPER PA28 PA28140 7102802 SO WING FUEL BAY DETERIORATED D K NONE O OTHER IN INSP/MAINT 1 SO 14 4347T 3134 287125510 INSPECTION FOUND ALL HOSES EXCEPT BRAKE AND OIL COOLER HOSES WERE ORIGINAL EQUIPMENT PARTS AT LEAST 25 YEARS OLD. WITH 3,134 HOURS TT, THE HOSES WERE ALL IN A STATE OF DETERIORATION. THE WING BAY FUEL HOSES AT TANKS WERE CORRODED AT SOCKE TS. SERVICE MANUAL CHECK LIST RECOMMENDS HOSE REPLACEMENT AT 1,000 HOURS OR 5 YEARS CALENDAR LIFE. 1 L 7 1 3O 2A13 1996120500337 19961205 00337 CE 1996 12 5 96ZZZX5820 1 19961105 G 2910 26070144 LINE ASSY LEAR 35 35A 5170602 CE HYD WORN B DJFR K NONE O OTHER IN INSP/MAINT 1 EA 23 425AS 8394 281 UPON INSPECTION DISCOVERED LINE CHAFED UNDER ADEL CLAMP. REMOVAL DISCLOSED RUBBER FROM CLAMP PARTIALLY MISSING AND LINE WORN 50 PERCENT OF WALL THICKNESS. RUBBER ON OUTSIDE OF CLAMP STILL IN PLACE MAKING IT HARD TO NOTICE. 2 L 7 2 4F A10CE 1996120500338 19961205 00338 CE 1996 12 5 96ZZZX5821 1 19961104 G 5102 SUSPENSION CABLE HEAD AX888 AX888HEAD 05637T7 CE ENVELOPE DEFECTIVE B S RG1R K NONE O OTHER IN INSP/MAINT 1 SW 01 8307M 104 218 THE SERVING AROUND THE KEVLAR SUSPENSION CABLE WHICH FORMS THE EYE AT THE BASE OF THE CABLE HAS COME APART. THE MANUFAC TURER HAS REFUSED TO SUPPLY INFORMATION ON THE REPAIR OF THIS ITEM. THIS ITEM IS NOT MENTIONED IN THE MAINTENANCE MANUA L. 1 B 0 0 A29SO2 1996120500339 19961205 00339 CE 1996 12 5 96ZZZX5822 1 19961107 G 3230 504501019 TORQUE TUBE CESSNA 340 340CESSNA 2076404 CE MLG CORRODED B L A DYPR K NONE O OTHER IN INSP/MAINT 1 NM 09 100HJ 2659 3400334 DURING ANNUAL INSPECTION AND INSTALLATION OF KIT SK 414-8E FOUND MLG TORQUE TUBE HAD INTERNAL RUST/CORROSION WITH WALL P ITTING IN EXCESS OF 10 PERCENT. 1 L 7 2 3O 3A25 1996120500340 19961205 00340 GL 1996 12 5 96ZZZX5823 2 19961023 G 7210 A6887772 BEARING ALLSN 250C 250C20B 03013 GL PTO GEARSHAFT MAKING METAL B YKER K NONE O OTHER IN INSP/MAINT 1 EA 17 033 832429 ENGINE WAS REPORTEDLY MAKING METAL. FOUND THE CAUSE TO BE THE PTO GEARSHAFT FORWARD BEARING WHICH HAD A SEVERELY SPALLE D INNER RACE. THE BEARING IS AN FAA-PMA PART, MANUFACTURED BY SUPERIOR. 3 U E4CE 1996120500341 19961205 00341 GL 1996 12 5 96ZZZX5824 2 19961104 G 7230 6898607 BEARING ALLSN 250C 250C30P 03013 GL COMPRESSOR FAILED B YKER K NONE O OTHER IN INSP/MAINT 1 EA 17 CAE895060 ENGINE WAS RECEIVED FOR METAL GENERATION. FOUND THE NR 1 BEARING HAD FAILED (SPALLING ON BALLS AND RACES; SEPARATOR IN PIECES). 3 U E1GL 1996120500342 19961205 00342 NM 1996 12 5 96ZZZX5825 1 19961025 G 2711 65255467 PULLEY 65742841 BOEING 727 727227 1384078 NM LT INBD AIL BEARING FAILED B A YN4R K NONE O OTHER IN INSP/MAINT 1 SO 05 76753 21249 DURING MID-D CHECK INSPECTION, LT INBD AIL TAB CONTROL CABLE TURNAROUND PULLEY WAS FOUND TO HAVE A RUSTED AND FAILED BEA RING. SUSPECT CAUSES ARE WATER INTRUSTION OR INSUFFICIENT LUBRICATION DURING BEARING MANUFACTURE. SUBMITTER STATED SPE CIAL ATTENTION SHOULD BE GIVEN TO THIS PULLEY BEARING DURING INSPECTION TO DETECT EARLY SIGNS OF RUSTING OR WEAR. REF I PC 27-10-0-24. 2 L 7 3 4F A3WE 1996120500343 19961205 00343 NM 1996 12 5 96ZZZX5826 1 19961025 G 2711 65255467 PULLEY 65742842 BOEING 727 727227 1384078 NM RT INB AIL BEARING FAILED B A YN4R K NONE O OTHER IN INSP/MAINT 1 SO 05 76753 21249 DURING MID-D CHECK INSPECTION, RT INBD AILERON TAB CONTROL CABLE TURNAROUND PULLEY WAS FOUND TO HAVE A RUSTED AND FROZEN BEARING. SUSPECT CAUSES ARE WATER INTRUSION OR INSUFFICIENT LUBRICATION DURING MANUFACTURE. SUBMITTER STATED SPECIAL ATTENTION SHOULD BE GIVEN TO THIS PULLEY BEARING DURING INSPECTION TO DETECT EARLY SIGNS OF RUSTING OR WEAR. REF IPC 27 -10-0-24. AC TT 50080. AC CYC 32554. 2 L 7 3 4F A3WE 1996120500344 19961205 00344 NM 1996 12 5 96ZZZX5827 1 19961025 G 2711 65742842 BRACKET ASSY BOEING 727 727227 1384078 NM RT INBD AIL WORN BOLT HOLE B A VN4R K NONE O OTHER IN INSP/MAINT 1 SO 19 76753 21249 DURING MID-D CHECK INSPECTION, RT INBD AILERON TAB CONTROL CABLE TURNAROUND PULLEY MOUNTING BRACKET WAS FOUND WITH ELONG ATED PULLEY MOUNT BOLT HOLES. CAUSE WAS A RUSTED AND FROZEN BEARING IN P/N 65-25546-7 PULLEY. SPECIAL ATTENTION SHOULD BE GIVEN TO THE PULLEY TO DETECT EARLY SIGNS OF RUST AND FAILURE OF THE BEARING. REF IPC 27-10-0-24. AC TT 50080. AC CYC 32554. 2 L 7 3 4F A3WE 1996120500345 19961205 00345 GL 1996 12 5 96ZZZX5828 2 19960925 G 7200 ENGINE CESSNA 525 525 2076601 CE WILINT FJ44 FJ44 66000 GL M50 BEARING MAKING METAL B MUCR K NONE O OTHER IN INSP/MAINT 1 GL 13 525FS 5250026 1022 ROUTINE OIL ANALYSIS REVEALED SMALL SHINY PLATELETS OF M-50 BEARING MATERIAL. ENGINE MANUFACTURER ADVISES ENGINE IS TO BE REMOVED FOR TEAR DOWN EVALUATION. 1 L 7 2 4F 4 F RT A1WI E3GL 1996120500346 19961205 00346 WP 1996 12 5 96ZZZX5829 1 19961030 G 5312 TEE CAP DOUG DC8 DC861 3021952 WP AFT PRESS LKHD CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 99 30UA 45888 DURING INSPECTION OF AFT PRESSURE BULKHEAD AT STA Y=1766 IAW PSI 53.08.009/010C AND NDI 53-10-18, FOUND TWO CRACKS AT CO RNER RADIUS OF THE TEE CAP AT LONGERON 10 RT AND LONGERON 10 LEFT. REPAIRED CRACKS BY INSTALLING A REPAIR ANGLE IAW SRM 53-2-5, PAGES 15 AND 16. 2 L 7 4 4F 4A25 1996020900293 19960209 00293 SO 1996 2 9 96ZZZX583 2 19960110 G 8530 530658 BUSHING CESSNA 421 421B 2076014 CE CONT O520 GTSIO520H 17032 SO NR 6 CYL PIN CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 11 707SP 49 421B0411 267057R UPON REMOVAL OF NR 6 CYLINDER, THE CONNECTING ROD PISTON PIN BUSHING WAS FOUND CRACKED. 1 L 7 2 3O 3 O A7CE E7CE 1996120500347 19961205 00347 CE 1996 12 5 96ZZZX5830 1 19961108 G 2130 261950010 VALVE LEAR 35 36A 5170603 CE EMERG PRESS LOOSE CONNECTOR E O OTHER J WARNING INDICATION CR CRUISE 1 SW 99 71CK O35 EMERGENCY PRESSURIZATION KICKED ON AT 14,500. TIGHTENED AND RE-SAFTIED CONNECTOR ON RT EMERGENCY BLEED VALVE. GROUND A ND TEST FLIGHT CHECK NORMAL. 2 L 7 2 4F A10CE 1996120500348 19961205 00348 NE 1996 12 5 96ZZZX5831 3 19961105 G 6111 RFC11T10C BLADE PIN HAMSTD 8022581 SAAB SF340 340B 7860101 EU HAMSTD 14RF 14RF19 NE SHANK CRACKED B A H2SR K NONE O OTHER IN INSP/MAINT 1 SO 13 11238 5788 864231 BLADE WAS RECEIVED FOR MAJOR INSPECTION. DURING DYE PENETRANT CHECK OF THE SHANK, TWO INDICATIONS APPEARED, ONE WAS APPR OXIMATELY 180 DEGREES FROM THE BLADE PIN AND THE OTHER WAS APPROXIMATELY 120 DEGREES FROM THE PIN. EACH INDICATION HAD THE FOLLOWING CHARACTERISTICS: TWO PARALLEL LINES, ONE IN THE RACE FILLET RADIUS, AND ONE ON THE SHANK BUTT O.D., EACH END OF THE INDICATIONS WERE CONNECTED BY LINES RUNNING FROM THE FILLET RADIUS OVER THE 90 DEGREE TRANSITION, AND INTO TH E SHANK BUTT O.D. 2 L 7 2 4T RT A52EU 6 C P11NE 1996120500351 19961205 00351 1996 12 5 96ZZZX5834 4 19961031 G 2562 SHARC7 ELT LEIGH G SWITCH FAILED D K NONE O OTHER IN INSP/MAINT 1 EA 05 IN C/W FAR 91-207 AT ANNUAL INSPECTIONS, 9 ELT'S HAVE FAILED THIS PAST YEAR DUE TO G-SWITCH FAILURE TO OPERATE WHEN TEST ED. ALL HAVE BEEN LEIGH SHARC 7 ELTS. RECOMMEND CLOSE ATTENTION BE GIVEN TO TESTING OF G-SWITCH TO MAKE SURE THEY WILL ACTIVATE WHEN PROPERLY TESTED. 1996120500352 19961205 00352 1996 12 5 96ZZZX5835 4 19961106 G 2350 M64151 MIC JACKS CESSNA 172 172N 2072434 CE HEADPHONE MIC LOOSE D K NONE O OTHER IN INSP/MAINT 1 EA 21 1558E 17271046 THE HEADPHONE AND MICROPHONE JACKS HAVE BEEN 'VIBRATING LOOSE'. CIRCUIT BREAKERS OF THE SAME ATTACHMENT NUT SIZE POSSESS A THIN WALLED LOCK WASHER WHICH PREVENT THIS LOOSENING TREND. 1 H 7 1 3O NT 3A12 1996120500353 19961205 00353 CE 1996 12 5 96ZZZX5836 1 19961106 G 2120 1570401 PLENUM ASSY CESSNA 172 172N 2072434 CE RADIO COOLING JAMMED YOKE D S A K NONE F FLT CONT AFFECTED IN INSP/MAINT 1 EA 21 1558E 3133 17271046 DURING PRE-FLIGHT 'CONTROL FREEDOM CHECK', THE FLIGHT CONTROLS BECAME JAMMED IN THE NOSE DOWN POSITION! THE RADIO RACK COOLING PLENUM HAD FALLEN INTO THE YOKE PATH. UPON FURTHER INVESTIGATION, ONLY ONE OF THE FOUR RETAINING CLAMPS/SPRINGS WAS FOUND AND IT WAS NOT ATTACHED PROPERLY. SUBMITTER STATED INSPECTION AND ADHERANCE TO CESSNA'S AVIONICS INSTALLATIO N MANUAL IS RECOMMENDED. 1 H 7 1 3O NT 3A12 1996120500354 19961205 00354 SO 1996 12 5 96ZZZX5837 1 19961030 G 3710 842CW PUMP AIRBORNE PIPER PA31 PA31P 7103120 SO VAC SYS SHAFT SHEARED B EKIR K NONE O OTHER IN INSP/MAINT 1 WP 07 110SK 370 04AK000053 31P7630006 PUMP WAS INSTALLED ON FRESH O/H ENG 9-15-95, PUMP NEW FROM AIRBORNE, FAILED AT 369.6 HRS 10-30-96. SEIZED AND SHEARED S HAFT. FAILURE RATE ON THESE PUMPS FROM SUBMITTERS EXPERIENCE IS QUITE HIGH. ABOUT 50 PERCENT FAIL JUST PAST THIS WARRA NTY TIME OF 1 YR OR 400 HRS. 1 L 7 2 3O A8EA 1996120500355 19961205 00355 EA 1996 12 5 96ZZZX5838 2 19961111 G 8520 78290 PLUNGER ASSY PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA NR 1 CYL EXH LIFTER BROKEN B P3NR O OTHER K FLUID LOSS NR NOT REPORTED 1 EA 13 27236 1097 317752111 L249268A PILOT NOTICED OIL COMING FROM COWLING. INVESTIGATION REVEALED NR 1 CYLINDER EXHAUST VALVE TRAIN FAILURE, PUSH ROD BENT, AND HYDRAULIC LIFTER BROKEN. CAUSE UNKNOWN. EXHAUST VALVE TO GUIDE CLEARANCE OKAY. 1 L 7 2 3O 3 O A20SO E14EA 1996120500356 19961205 00356 GL 1996 12 5 96ZZZX5839 2 19961113 G 7210 6705924 OIL PLUG 6854702 CVAC 440 440 2422902 WP ALLSN 501D 501D13D 03004 GL COMP DRV ASSY DETACHED G K NONE O OTHER IN INSP/MAINT 1 EA 25 49 866 479 501422 AS PART OF TROUBLESHOOTING FOR AN ENGINE OIL QUANTITY PROBLEM, OIL PLUG, WAS FOUND MISSING FROM THE ENGINE DRIVEN COMPRE SSOR DRIVE ASSEMBLY. ALLISON P/N 6854702. OIL PLUG WAS RETRIEVED FROM THE REDUCTION GEARBOX LOW POINT DRAIN. OIL PLUG IS PRESS-FIT INTO DRIVE ASSEMBLY SHAFT AT MANUFACTURE, AND SEPARATED FROM SHAFT FOR UNKOWN REASONS. REDUCTION GEARBOX SPLIT, INSPECTED, REPAIRED AND RETURNED TO SERVICE. ENGINE TSO 865.8. 2 L 7 2 4R 4 T 6A6 E282 1996020900294 19960209 00294 SO 1996 2 9 96ZZZX584 2 19960119 G 8530 CYLINDER ASSY CESSNA 182 182P 2075816 CE CONT O470 O470R 17026 SO NR 5 EXH ROCKER BOSS BROKE C HNXG K NONE O OTHER NR NOT REPORTED 1 NM 11 91130 875 18261955 451117 FOUND NR 5 CYLINDER ROCKER ARM BOSSES BROKEN OFF ON EXHAUST VALVE. 1 H 7 1 3O 3 O NT TA13 E273 1996120500357 19961205 00357 CE 1996 12 5 96ZZZX5840 1 19961104 G 2721 043213822 CHAIN ASSY 12606732 CESSNA 206 U206G 2073356 CE RUDDER TRIM LOCK MISSING D K NONE F FLT CONT AFFECTED NR NOT REPORTED 1 WP 07 756HQ 3947 420604107 PILOT REPORTED RUDDER TRIM INOPERATIVE, BUT WOULD TURN WHEEL. MASTER LINK LOCK MISSING, INSTALLED NEW MASTER LINK ASSY. (ADJUSTED CHAIN TENSION). 1 H 7 1 3O A4CE 1996120500640 19961205 00640 EU 1996 12 5 96ZZZX5842 1 19960824 G 7714 1179405303 TRIPLE TACH BOLKMS 117 BK117A3 5626015 EU ENG N2 INTERMITTENT B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 911MZ 24 282 7098 INTERMITTENT N2 - NR 2 DROP OF 2 PERCENT AT 100 PERCENT. 1 G 7 2 3U H13EU 1996020900297 19960209 00297 SO 1996 2 9 96ZZZX587 2 19960116 G 8520 CRANKSHAFT CESSNA 207 207A 2073604 CE CONT O520 IO520F 17032 SO ENGINE BROKE G A UNSCHED LANDING J R WARNING INDICATION PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 SW 99 70076 2643 950 20700547 286336R PERFORMED EMERGENCY LANDING ON FROZEN LAKE. DURING THE LANDING ROLL, THE RIGHT WING TIP STRUCK A SPRUCE TREE. THE AIRC RAFT RECEIVED DAMAGE TO THE RIGHT WING AND AILERON. THE ENGINE WAS REPLACED WITH THE AIRCRAFT ON THE FROZEN LAKE. THE EMERGENCY LANDING WAS FORCED DUE TO LOSS OF OIL PRESSURE AND ENGINE RPM AT THE SAME TIME. THIS WAS THE RESULT OF THE CR ANKSHAFT BEING BROKEN IN TWO. NOTE: VAR CRANKSHAFT INSTALLED IN THIS IO-520 ENGINE. 1 H 7 1 3O 3 O A16CE E5CE 1996121200069 19961212 00069 GL 1996 12 12 96ZZZX5874 2 19961017 G 7250 68777362 STATOR SEAL ALLSN 250B 250B17 03012 GL GAS PROD AFT CRACKED B YKER K NONE O OTHER IN INSP/MAINT 1 EA 17 CAE870101 DURING PARTIAL DISASSEMBLY OF TURBINE TO REPLACE THE FIRST STAGE NOZZLE, FOUND CRACKS IN BEARING BORE AREA OF SEAL. UPO N REMOVAL OF SEAL, NOTICED FRETTING ON OUTER DIAMETER. SUSPECT IMPROPER FIT OF SEAL IN SUPPORT. 3 T E10CE 1996121200070 19961212 00070 EA 1996 12 12 96ZZZX5875 2 19961113 G 8540 75288 DRIVE ASSY CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA ASSORY CASE DEFECTIVE D K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 17 19956 17260886 L3181427A WHILE C/W AD 960910C, IT WAS DISCOVERED AD 75-8-9R3 HAD NOT BEEN C/W. (REQUIRED REPLACEMENT OF DRIVE ASSY 75288 WITH DR IVE ASSY PN 61174) A CHECK OF AD 75-8-9R3 AND RELATED SB. ENG S/N WAS NOT LISTED. AD APPLICABLE TO S/N 33229-27A TO 41 054-27A. NO RECORD OF ENG OVH OR ANY MAINT ON OIL PUMP GEARS. ENG TOTAL TIME 625. 1 H 7 1 3O 3 O NT 3A12 E274 1996121200071 19961212 00071 EA 1996 12 12 96ZZZX5876 2 19961112 G 8550 06B21326 GASKET 06B21326 CESSNA 182 R182 2072734 CE LYC O540 O540J3C5 41532 EA OIL SUMP DETERIORATED D K NONE O OTHER IN INSP/MAINT 1 EA 07 3626C 431 R18200284 L1983640A OIL SUMP GASKET DETERIORATED AND TURNED TO MUSH LIKE SUBSTANCE CAUSIING GASKET INGESTION AND LOSS OF GASKET SEAL AT OIL PICK UP GALLEY CAUSING LOW OIL PRESSURE. OIL PUMP CAVITATED AND SUCKED AIR INSTEAD OF OIL. 1 H 7 1 3O 3 O RT 3A13 E295 1996121200072 19961212 00072 CE 1996 12 12 96ZZZX5877 1 19961101 G 7120 40043 MOUNT CESSNA 172 172G 2072420 CE ENG FWD RT CORRODED D P K NONE O OTHER IN INSP/MAINT 1 SW 99 3918L 1628 17254087 INSPECTION FOUND MOTOR MOUNT THROUGH-BOLTS HOLES WERE CORRODED. FWD RIGHT MOUNT AND LEFT AFT MOUNT. 1 H 7 1 3O NT 3A12 1996121200073 19961212 00073 CE 1996 12 12 96ZZZX5878 1 19961101 G 7120 40044 MOUNT CESSNA 172 172G 2072420 CE ENG LT AFT CORRODED D K NONE O OTHER IN INSP/MAINT 1 SW 99 3918L 1628 17254087 INSPECTION FOUND MOTOR MOUNT THROUGH-BOLTS HOLES WERE CORRODED. FWD RIGHT MOUNT AND LEFT AFT MOUNT. 1 H 7 1 3O NT 3A12 1996121200074 19961212 00074 SO 1996 12 12 96ZZZX5879 1 19961114 G 3240 BRAKE SYS PIPER PA31 PA31350 7103110 SO MLG WATER CONTAM D L A K NONE O OTHER IN INSP/MAINT 1 EA 25 515RM 317405159 INSP FOR BRAKE PEDALS LOCKED AND BRAKE DRAG, IT WAS DISCOVERED THAT THE ENTIRE BRAKE SYSTEM, EXCEPT FOR ABOUT A QUARTER OF A PINT, WAS FULL OF WATER WHICH HAD FROZEN THE NIGHT BEFORE WHEN THE TEMPERATURE HAD DROPPED BELOW FREEZING. HEAT WA S APPLIED TO THE ACCESSIBLE AREAS OF BRAKE LINES AND THE RESERVOIR TO THAW THEM. THE SYSTEM WAS THEN FLUSHED OUT AND SE RVICED WITH THE CORRECT FLUID AND CHECKED FOR LEAKS. ALL TOGETHER ABOUT A QUART OF WATER WAS DRAINED FROM THE SYSTEM. 1 L 7 2 3O A20SO 1996020900298 19960209 00298 CE 1996 2 9 96ZZZX588 1 19960105 G 5312 511201144 BULKHEAD CESSNA 421 421C 2076016 CE FS 373.56 CRACKED B R2JR K NONE O OTHER IN INSP/MAINT 1 EA 21 685GF 5579 421C0680 WHILE PERFORMING INSPECTION REQUIRED BY CESSNA SB 95-10A, FOUND CRACK IN TAIL BULKHEAD AT STA 373.56. NEW BULKHEAD INST ALLED AND AREA REINFORCED WITH SK 421-143 KIT INSTALLATION. SUBMITTER SUGGESTS INSPECTION PER SB 95-10A AND KIT INSTALL ATION ON 400 SERIES CESSNAS. 1 L 7 2 3O A7CE 1996121200075 19961212 00075 SO 1996 12 12 96ZZZX5880 1 19960129 G 2823 236405 SELECTOR O-RING SCOTT PIPER PA34 PA34200T 7103406 SO LT & RT WING FAILED B CEKR K NONE O OTHER NR NOT REPORTED 1 SO 13 2119C 347970015 FUEL DRAINED FROM ONE SIDE TO OTHER CAUSING LOW TANK TO FLOOD. UNABLE TO MOVE FUEL SELECTORS TO OFF POSITION. REMOVED SELECTOR AND FOUND BOTH LEFT AND RIGHT SELECTOR O-RINGS IN A MELTED STATE, PARTS OF O-RINGS IN SELECT OR RACK GEAR. ONE SET OF O-RINGS HAVE DISINTEGRATED. APPEARS THE LACK OF USE AND TIME WERE A CONTRIBUTING FACTOR. (REFERENCE AD 80-18-1 0 AND PIPER SB 648A. (THESE ARE ON A PA31). THE VALVE IS SIMILAR AND THE PROBLEM THE SAME). 1 L 7 2 3O A7SO 1996121200076 19961212 00076 SW 1996 12 12 96ZZZX5881 1 19960724 G 3340 93235140 CIRCUIT BOARD 930500251 BELL 206 206B 1181511 SW SEARCH LIGHT BURNED D K NONE O OTHER IN INSP/MAINT 1 SO 09 67172 456 1964 5118 THE AIRCRAFT SEARCHLIGHT WAS REPORTED AS BEING INOP--THE BULB WOULD NOT ILLUMINATE. INVESTIGATION REVEALED THAT THE PRO BLEM WAS IN THE PRINTED CIRCUIT BOARD. THE PRINTED CIRCUIT TRACK WAS FOUND TO BE BURNED IN TWO BETWEEN THE RELAY 30 AND POINT 13. 1 G 7 1 3U H2SW 1996121200077 19961212 00077 SW 1996 12 12 96ZZZX5882 1 19960804 G 3340 93235140 CIRCUIT BOARD 930500151 BELL 206 206B 1181511 SW SEARCH LIGHT BURNED D K NONE O OTHER IN INSP/MAINT 1 SO 09 67476 187 1982 5158 THE AIRCRAFT SEARCHLIGHT WAS REPORTED AS BEING INOP--THE BULB WOULD NOT ILLUMINATE. INVESTIGATION REVEALED THAT THE PRO BLEM WAS IN THE PRINTED CIRCUIT BOARD. THE PRINTED CIRCUIT TRACK WAS FOUND TO BE BURNED IN TWO BETWEEN THE RELAY 30 AND POINT 13. 1 G 7 1 3U H2SW 1996121200078 19961212 00078 SW 1996 12 12 96ZZZX5883 1 19960417 G 3340 930500251 SEARCH LIGHT BELL 206 206B 1181511 SW EXT LIGHT CONTACT BURNED D K NONE O OTHER IN INSP/MAINT 1 SO 09 67118 768 1914 5112 THE AIRCRAFT SEARCHLIGHT WAS REPORTED AS BEING INOP. INVESTIGATION REVEALED THAT THE SEARCHLIGHT CONTACT WAS BURNED AND OPEN. 1 G 7 1 3U H2SW 1996121200079 19961212 00079 SW 1996 12 12 96ZZZX5884 1 19960227 G 3340 930500251 SEARCH LIGHT BELL 206 206B 1181511 SW EXT LIGHT CONTACT BURNED D K NONE O OTHER IN INSP/MAINT 1 SO 09 67176 457 1909 5119 THE AIRCRAFT SEARCHLIGHT WAS REPORTED AS BEING INOP. INVESTIGATION REVEALED THAT THE SEARCHLIGHT CONTACT WAS BURNED AND OPEN. 1 G 7 1 3U H2SW 1996121200080 19961212 00080 SW 1996 12 12 96ZZZX5885 1 19960729 G 3340 93235140 CIRCUIT BOARD 930500151 BELL 206 206B 1181511 SW SEARCH LIGHT BURNED D K NONE O OTHER IN INSP/MAINT 1 SO 09 67301 888 1029 5135 THE AIRCRAFT SEARCHLIGHT WAS REPORTED AS BEING INOP--THE BULB WOULD NOT ILLUMINATE. INVESTIGATION REVEALED THAT THE PRO BLEM WAS IN THE PRINTED CIRCUIT BOARD. THE PRINTED CIRCUIT TRACK WAS FOUND TO BE BURNED IN TWO BETWEEN THE RELAY 30 AND POINT 13. 1 G 7 1 3U H2SW 1996121200081 19961212 00081 WP 1996 12 12 96ZZZX5886 1 19960826 G 6310 369F54531 SHAFT 369F54501 HUGHES 369 369E 4470707 WP OVERUN CLUTCH CRACKED D K NONE O OTHER IN INSP/MAINT 1 WP 09 911RP 93 0099990088 526E REMOVED OVERUNNING CLUTCH SUB-ASSEMBLY PER MDHC, FOUND OUTER RACE SHAFT CRACKED AT SPLINE RADIUS. 1 G 7 1 3U H3WE 1996121200082 19961212 00082 GL 1996 12 12 96ZZZX5887 2 19961001 G 7260 6854424 SEAL 6886442 HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL START/GEN MT PAD FAILED D A UNSCHED LANDING J K WARNING INDICATION FLUID LOSS CR CRUISE 1 WP 09 268ST 2 AG35540 470122D CAE830599 DURING NORMAL CRUISE FLIGHT, PILOT NOTICED A LOW TORQUE PRESSURE INDICATION, FURTHER EXAMINATION OF ENGINE INSTRUMENTS R EVEALED ENGINE OIL PRESSURE STEADILY DROPPING. PILOT PROCEEDED TO IMMEDIATELY LAND HELICOPTER. AFTER AIRCRAFT WAS SHUT DOWN PILOT FOUND OIL LEAK IN ENGINE AREA AT THE ENGINE GEARBOX STARTER GENERATOR MOUNT PAD. WHEN STARTER GENERATOR WAS REMOVED, THE P/N 6854424 SEAL WAS LAYING ON THE STARTER GENERATOR SPLINED SHAFT. FURTHER INVESTIGATION OF THE FAILED S EAL REVEALED THAT THE OUTER DIAMETER OF SEAL WAS SMALLER THAN THREE OTHER SAME P/N SEALS INCLUDING ANOTHER PREVIOUSLY IN STALLED SEAL. SEAL TOTAL TIME WAS 1.5 HOURS. 1 G 7 1 3U 3 U H3WE E4CE 1996121200083 19961212 00083 SO 1996 12 12 96ZZZX5888 1 19961122 G 5720 ABRASION STRIP PIPER PA28 PA28140 7102802 SO WING-STAB LE DETERIORATED D L A K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 09 4170J 2822505 DEFECTIVE/UNAPPROVED DUCT TAPE ABRASION STRIPS FOUND ON LEADING EDGES OF WINGS AND STABILATOR. STRIPS DEBONDED AND BADL Y DETERIORATED. 1 L 7 1 3O 2A13 1996121200084 19961212 00084 SO 1996 12 12 96ZZZX5889 2 19961125 G 8530 539467 PISTON PIN CONT O470 IO470D 17026 SO ENG CYL MISMFG D K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 01 BOUGHT 6 EACH 539467 PISTON PINS. 4 OF THEM WERE WAY TOO LONG. 2 OF THEM WERE CORRECT. RETURNED AND FOUND OUT ALL OF THEM IN STOCK THAT WERE LONG HAD HG CODE ON THE BOX. THE ONES WITH DG AND JG CODES WERE THE CORRECT LENGTH. 3 O 3E1 1996121200085 19961212 00085 CE 1996 12 12 96ZZZX5890 1 19961101 G 5510 07321014 REINFORCEMENT 12320008 CESSNA 185 A185F 2072821 CE CONT O520 IO520D 17032 SO HORIZ STAB CRACKED D S A K NONE O OTHER IN INSP/MAINT 1 NE 01 9F 4283 18502855 282576R AT 50 HR INSP, NOTICED REINFORCEMENT CRACKED AT BOTTOM FLANGE WHERE HINGE BOLTS TO STABILIZER. INSTALLED NEW REINFORCEM ENT FROM CESSNA. SUBMITTER STATED HINGE BOLTS WERE NOT LOOSE, SO CRACK MUST HAVE OCCURRED DUE TO FATIGUE. 1 H 7 1 3O 3 O 3A24 E5CE 1996121200086 19961212 00086 SO 1996 12 12 96ZZZX5891 1 19961122 G 7160 3563104 HEAT MUFF 3563100 PIPER PA28 PA28161 7102803 SO CARB HEAT SCREEN FAILED D P A K NONE O OTHER IN INSP/MAINT 1 GL 13 3024S 3886 287916297 CARB HEAT MUFF SCREEN BROKEN AND INJESTED. DURING ANNUAL INSPECTION, SCREEN LOCATED IN MUFFLER HEAT EXCHANGER FOUND TO BE DETERIORATED. SUSPECT CAUSE IS HEAT AND AGE. SUGGEST INSPECTION OF SCREEN EACH TIME MUFFLER SHROUD IS REMOVED. 1 L 7 1 3O 2A13 1996121200087 19961212 00087 CE 1996 12 12 96ZZZX5892 1 19961031 G 3252 04425121 DAMPENER CESSNA 150 150G 2071816 CE NLG FAILED D O OTHER O OTHER LD LANDING 1 GL 03 2951J 15065751 AIRCRAFT LANDED, RAN OFF RUNWAY PUSHING NOSE GEAR UNDER FUSELAGE. OWNER SAID PLANE DEVELOPED SHIMMY AND HE COULDN'T KEE P ON RUNWAY. CHECKED SHIMMY DAMPENER AND FOUND ONE-HALF AIR IN IT. SUBMITTER STATED SHOULD MAYBE CHECK SHIMMY DAMPENER MORE OFTEN FOR FLUID LEVEL. 1 H 7 1 3O 3A19 1996121200088 19961212 00088 CE 1996 12 12 96ZZZX5893 1 19961101 G 7810 265401818 EXHAUST DUCT CESSNA 208 208B 2073701 CE SECONDARY EXH CRACKED D P A K NONE O OTHER IN INSP/MAINT 1 SW 99 1040W 2285 208B0336 AN EXHAUST STAIN WAS OBSERVED ON ENGINE COWLING DURING A PRE-FLIGHT WALK-AROUND. CLOSER INSPECTION BY MAINT PERSONNEL D ISCOVERED A LARGE CRACK IN THE UPPER SURFACE OF THE EXHAUST DUCT. PART WAS REMOVED FOR REPAIR AND REPLACED WITH A SERVI CEABLE UNIT. 1 H 7 1 3T A37CE 1996121200089 19961212 00089 GL 1996 12 12 96ZZZX5894 1 19961013 G 2510 BELT ATTACH AMTR TAILWD TAILWINDW8 GL COCKPIT SEAT FAILED G P A A UNSCHED LANDING O OTHER NR NOT REPORTED 1 SO 15 91323 83 001 AIRPLANE CRASHED BECAUSE OF ENGINE FAILURE BUT THE SEAT BELTS FAILED BECAUSE OF POOR WELDS. ATTACHMENT LUGS BROKE LOOSE FROM STRUCTURE, ALLOWING PILOT TO BE EJECTED INTO INSTRUMENT PANEL. SUBMITTER RECOMMENDS THAT AMATEUR AIRCRAFT BUILDER S MAKE GOOD WELDS. 1 H 7 1 3O EXPA1H71 1996121200090 19961212 00090 GL 1996 12 12 96ZZZX5895 3 19961122 G 6114 C4716C58 HUB MCAULY 2A34C D2A34C58 GL NR 1 SOCKET CRACKED B ME4R K NONE O OTHER IN INSP/MAINT 1 SO 19 1439 701466 PROPELLER RECEIVED FOR OVERHAUL. DURING INSPECTION, HUB DISCOVERED CRACKED IN NR 1 BLADE SOCKET, NR 1 THROUGH NR 5 THRE ADS ABOUT 5 TO 7 O'CLOCK POSITION. NOTE: OIL FILL AD'S 78020-0 AND 91-15-04 WERE C/W. NO OIL NOTED LEAKING FROM THE P ROPELLER BEFORE DISASSEMBLY. 5 C P3EA 1996121200091 19961212 00091 1996 12 12 96ZZZX5896 4 19961104 G 3457 071015530200 ANTENNA KING COCKPIT GPS DEFECTIVE B AMVR K NONE W INADEQUATE Q C IN INSP/MAINT 1 CE 05 08885 GPS KA92 L1 ACTIVE ANTENNA IS FOR THE KLN 90B IFR APPROACH GPS. IT WAS INSTALLED ACCORDING TO THE KLN 90B INSTALL MANUA L P/N 006-10521-0002 REV 2 FEB. 1995. UPON TESTING THE INSTALLED EQUIPMENT, THE ANTENNA WAS FOUND TO BE DEFECTIVE NEW O UT OF THE BOX. IT WOULD RECEIVE NO SATELLITES. 1996121200092 19961212 00092 CE 1996 12 12 96ZZZX5897 1 19961101 G 7120 9691000575 MOUNT BEECH 95 95B55 1152729 CE ENGINE CHAFE DAMAGE B S UWDR K NONE O OTHER IN INSP/MAINT 1 GL 15 18388 TC2081 INSPECTION FOUND ENG MOUNT WITH HEAVY CHAFE DAMAGE AT LOWER RT FIREWALL ATTACH. 1 L 7 2 3O RT 3A16 1996121200093 19961212 00093 1996 12 12 96ZZZX5898 4 19961104 G 3457 071015530200 ANTENNA KING KA92 COCKPIT GPS DEFECTIVE B AMVR K NONE W INADEQUATE Q C IN INSP/MAINT 1 CE 05 08381 GPS KA92 L1 ACTIVE ANTENNA IS FOR THE KLN 90B IFR APPROACH GPS. IT WAS INSTALLED ACCORDING TO THE KLN 90B INSTALL MANUA L P/N 006-10521-0002 REV 2, FEB, 1995. UPON TESTING THE INSTALLED EQUIPMENT, THE ANTENNA WAS FOUND TO BE DEFECTIVE NEW OUT OF THE BOX. IT WOULD RECEIVE NO SATELLITES. 1996121200094 19961212 00094 SO 1996 12 12 96ZZZX5899 2 19961120 G 8530 625432A2 CYLINDER BEECH 45 D45 1152012 CE CONT O470 O4704 17026 SO NR 4 RKR BOSS CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 07 111JH 237 BG392 116049 INSP FOUND ALL FOUR ROCKER BOSSES CRACKED OFF CYLINDER. 1 L 7 1 3O 3 O 5A3 E269 1996020900300 19960209 00300 SW 1996 2 9 96ZZZX590 1 19960112 G 3230 540002020 TRUSS MOONEY M20 M20C 5870208 SW NLG RIGHT BROKE D K NONE O OTHER TX TAXI/GRND HDL 1 SW 17 6604U 3970 M20C2391 AIRCRAFT WAS BEING TAXIED OUT FOR A POST-ANNUAL TEST FLIGHT WHEN THE NOSE GEAR FOLLOWED BY THE RIGHT THEN LEFT MAIN GEAR COLLAPSED. FOUND NOSE GEAR RETRACTION TRUSS HAD FAILED (BROKE) AT THE RIGHT RETRACT ROD. THE ASSY TUBE THAT CANTS INW ARD SHOWS SIGNS OF INTERNAL CORROSION AND THE ONLY EVIDENCE OF CORROSION ON THE OUTSIDE IS A SMALL AREA OF DISCOLORATION AT A PLACE WHERE IT CANNOT BE SEEN BECAUSE OF THE TIGHTNESS OF THE AREA. 1 L 7 1 3O 2A3 1996121200095 19961212 00095 1996 12 12 96ZZZX5900 4 19961029 G 2562 569950102 BATTERY NARCO 910 PIPER PA28 PA28R200 7102811 SO ELT DEFECTIVE D K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 09 15919 11288 28R7335106 AFTER INSTALLING A NEW NARCO ELT BATTERY, THE ELT COULD NOT BE RESET AFTER ACTIVATING THE ELT. REPLACEMENT DATE OF BATT ERY WAS 10-1-98. BATTERIES HAVE A COMPUTER CHIP IN THEM SO ONLY NARCO BATTERIES CAN BE UTILIZED. APPARENTLY FAULT WAS IN THIS CHIP. AFTER INSTALLING ANOTHER NEW NARCO BATTERY, OPERATION WAS SATISFACTORY. 1 L 7 1 3O 2A13 1996121200096 19961212 00096 EA 1996 12 12 96ZZZX5901 2 19961119 G 8520 75359 DOWEL 75670 PIPER PA31 PA31P 7103120 SO LYC O541 TIGO541E1A 41539 EA CRANKSHAFT LOOSE B EKIR K NONE O OTHER IN INSP/MAINT 1 WP 07 18MC 3235 99 31P7300143 2L48862 FOUND DOWEL FOR CRANKSHAFT SPLINE BUSHING IN SUMP AT OIL SCREEN. UPON TEAR DOWN FOUND ONLY 1 OF 3 DOWELS STILL IN CRANK SHAFT. BUSHING WAS STARTING TO TWIST IN BETWEEN CRANKSHAFT AND SPLINE BUSHING. NO OTHER INDICATION OF PROBLEMS. ENGIN E RAN GOOD, FILTER WAS CLEAR. 1 L 7 2 3O 3 O A8EA E19EA 1996121200097 19961212 00097 CE 1996 12 12 96ZZZX5902 1 19961025 G 7920 6010008018 HOSE ASSY BEECH 95 B95 1153404 CE OIL COOLER CHAFE LEAK E A UNSCHED LANDING K FLUID LOSS CR CRUISE 1 SW 11 2012C TD430 WHILE EN ROUTE ON A ROUTINE FLIGHT, THE PILOT NOTICED OIL LEAKING FROM THE RIGHT ENGINE. THE AIRCRAFT DIVERTED TO AWN W HERE UPON INSPECTION IT WAS DISCOVERED THAT THE OIL COOLER OUTLET LINE P/N (AEROQUIP 950012-4-0090) HAD A SMALL HOLE DUE TO CHAFING WHICH WAS POSSIBLY CAUSED BY A BROKEN CLAMP P/N MS 21919DG10 WHICH ALLOWED THE LINE TO CHAFE AGAINST THE INT AKE TUBE. A NEW LINE WAS INSTALLED, OIL FILTER WAS INSPECTED FOR METAL, ENGINE WAS RUN AND LEAK CHECKED. NO LEAKS WERE NOTED. AIRCRAFT WAS THEN RELEASED FOR FURTHER FLIGHT. (IT SHOULD BE NOTED THAT THE OIL LEVEL WAS ONLY DOWN BY 2.5 QUA RTS). 1 L 7 2 3O 3A16 1996121200098 19961212 00098 GL 1996 12 12 96ZZZX5903 3 19961029 G 6114 D7015C87 HUB CESSNA 402 402B 207590P CE MCAULY 3AF32C 3AF32C87 GL PROP CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 23NC 6552 330 734266 402B0419 734266 PROP INSP FOUND HUB CRACKED IN THREAD AREA. 1 L 7 2 3O A7CE 5 C P22EA 1996121800006 19961218 00006 EU 1996 12 18 96ZZZX5906 1 19961107 G 7810 12634912 MUFFLER WALLCOLMNY SLNSBY T67 T67M260 8323006 EU FIREWALL FRAME CHAFED D K NONE O OTHER IN INSP/MAINT 1 SW 17 3004H 790 2126 ON ANNUAL INSPECTION THE MUFFLER TAILPIPE WAS FOUND CHAFING ON FRAME NR 1 (FIREWALL). THE HEAT EXPANDS THE TAILPIPE WHI CH CAUSED IT TO HIT THE BOTTOM OF FRAME NR 1. 1 L 7 1 3O NT A73EU 1996121200101 19961212 00101 EU 1996 12 12 96ZZZX5907 1 19961107 G 2720 T67M45245 SUPPORT BRACKET SLNSBY T67 T67M260 8323006 EU RUDDER BAR CRACKED D A K NONE O OTHER IN INSP/MAINT 1 SW 17 31917 158 2224 ON ANNUAL INSPECTION THE INBD STBD RUDDER BAR SUPPORT BRACKET WAS FOUND CRACKED. PRESSURE APPLIED TO RUDDER PEDAL PUTS PRESSURE ON BRACKET CAUSING IT TO CRACK. SUBMITTER RECOMMENDS A HEAVIER DUTY BRACKET. 1 L 7 1 3O NT A73EU 1996121200102 19961212 00102 CE 1996 12 12 96ZZZX5908 1 19961109 G 2720 35524106 CONTROL ROD BEECH 35 E35 1151512 CE RUDDERVATOR CORRODED D K NONE O OTHER IN INSP/MAINT 1 CE 01 3247C 3233 D3912 DURING AN ANNUAL INSP THE TWO CONTROL RODS THAT CONNECT TO THE RUDDERVATORS WERE REMOVED TO C/W SB NR 2668. HEAT HAD TO BE APPLIED TO REMOVE THE ROD ENDS. THREADS WERE CORRODED AND INSIDE OF TUBES PITTED CORROSION WAS FOUND. BOTH CONTROL ROD ASSEMBLIES WERE REPLACED WITH NEW PARTS FROM BEECH. THIS AIRCRAFT HAS ALWAYS BEEN HANGARED. RECOMMEND SB 2668 BEC OME AN AD. THIS BRINGS UP A QUESTION ABOUT OTHER AIRCRAFT THAT USE CONTROL TUBES. 1 L 7 1 3O A777 1996020900301 19960209 00301 SO 1996 2 9 96ZZZX591 1 19960104 G 3230 40336000 LINK PIPER PA31T PA31T 7103124 SO RT NLG DRAG LINK CRACKED B A AU3R K NONE O OTHER IN INSP/MAINT 1 WP 15 44HT 5407 31T7920061 DURING A SCHEDULED INSPECTION, THE RIGHT NLG DRAG LINK WAS FOUND CRACKED ON THE INBOARD LUG FORWARD SIDE WHERE THE NLG A CTUATOR ATTACHES. SUBMITTER RECOMMENDS SCHEDULED INSPECTIONS OF THIS AREA. THIS IS THE SECOND OCCURRENCE. 1 L 7 2 3T A8EA 1996121200104 19961212 00104 SO 1996 12 12 96ZZZX5910 1 19961029 G 3230 LINKAGE PIPER PA31 PA31350 7103110 SO MLG DOWNLOCK REQ LUBE B BSYR O OTHER J WARNING INDICATION AP APPROACH 1 GL 07 35871 318052123 GEAR HANDLE DID NOT RETURN TO NEUTRAL, GEAR HORN BLEW, INBD GEAR DOORS DID NOT CLOSE. FOUND DOWN AND LOCK LINKAGE STIFF , LUBED AND SWUNG GEAR. OPS CHECKED GOOD. 1 L 7 2 3O A20SO 1996121200105 19961212 00105 SO 1996 12 12 96ZZZX5911 1 19961028 G 3260 487862 SWITCH PIPER PA31 PA31350 7103110 SO RT MLG FAILED B BSYR O OTHER P NO WARNING INDICATION AP APPROACH 1 GL 07 35871 318052123 NO RT MAIN DOWN AND LOCK. INBD GEAR DOORS WILL NOT CLOSE. FOUND RT MAIN DOWN AND LOCK SWITCH BAD, ALSO, CORRODED SPLIC ES IN WHEELWELL. SWITCH MFG P/N 1CH21-4. 1 L 7 2 3O A20SO 1996121200106 19961212 00106 CE 1996 12 12 96ZZZX5912 1 19961101 G 7120 9691000575 MOUNT BEECH 95 95B55 1152729 CE ENG DAMAGED B S UWDR K NONE O OTHER IN INSP/MAINT 1 GL 15 42P TC2244 INSP FOUND ENGINE MOUNT WITH HEAVY CHAFE DAMAGE AT LOWER RT FIREWALL ATTACH POINT. 1 L 7 2 3O RT 3A16 1996121200107 19961212 00107 CE 1996 12 12 96ZZZX5913 1 19961105 G 7120 07516001 MOUNT CESSNA 182 182L 2072726 CE BRACE TUBES CORRODED B AJ4R K NONE O OTHER IN INSP/MAINT 1 WP 21 42036 4217 18258822 DURING ANNUAL INSPECTION, FOUND HEAVY CORROSION AT FORWARD END OF ENGINE MOUNT MAIN BEAMS AND DIAGONAL BRACE TUBES ON BO TH SIDES. CAUSE OF CORROSION-PROXIMITY OF EXHAUST COLLECTORS TO MOUNT. CORRECTIVE ACTION-INSTALL HEAT SHIELDS AFTER PA INTING WITH HEATPROOF PAINT. 1 H 7 1 3O NT 3A13 1996020900303 19960209 00303 SO 1996 2 9 96ZZZX593 1 19960116 G 2750 95504000 BRACKET PIPER PA34 PA34200T 7103406 SO FLAP LEVER CRACK B APCR K NONE O OTHER IN INSP/MAINT 1 NM 01 4377X 16429 347670035 THE FLAP LEVER ATTACH BRACKET IS CRACKED AT THE FORWARD LOWER BEND RADIUS, ADJACENT TO THE ATTACH POINT TO THE FLOOR. 1 L 7 2 3O A7SO 1996020900304 19960209 00304 EA 1996 2 9 96ZZZX594 2 19960118 G 7310 6390156 HOSE PIPER PA28 PA28180 7102808 SO LYC O360 O360A3A 41514 EA ENGINE OVER AGE D K NONE W INADEQUATE Q C IN INSP/MAINT 1 EA 21 1989 NEW ENGINE HOSES RECEIVED FROM PIPER WERE FOUND TO BE 6 YEARS OLD. THE DISTRIBUTOR AGREED THIS WAS UNSATISFACTORY SAYIN G AT FIRST THAT 5 YEARS WAS THE MAXIMUM SHELF LIFE; BUT, AFTER CONTACTING PIPER, FAX'ED A STATEMENT THAT PIPER'S PROPRIE TARY INFORMATION ALLOWED AN 8-YEAR SHELF LIFE. NO WONDER PIPER'S SERVICE MANUALS LIMIT THE SERVICE LIFE TO 3 YEARS. 1 L 7 1 3O 3 O 2A13 E286 1996121200155 19961212 00155 WP 1996 12 12 96ZZZX5940 1 19961109 G 5302 AN517A BOLT HILLER UH12 UH12E 4360122 WP TAIL BOOM ATTACH FAILED B CHIR A UNSCHED LANDING O OTHER EX EXTERNAL LOAD 1 NM 09 9749C 33 2146 IN CLIMB-OUT FROM LOG LANDING WITH EXT LOAD AT AN ALT OF APPROX 400 FEET AND 69.5 PSI TORQ, PILOT HEARD A 'BANG' FOLLOWE D BY A HIGH FREQ VIBR. AFTER CHECKING ALL INST (NORMAL) PILOT JETTISONED EXT LOAD AND LONG LINE. PILOT EXECUTED A PREC AUTIONARY LANDING TO THE LOG LANDING WITHOUT INCIDENT. HELICOPTER INSP AFTER SHUT DOWN DISCOVERED BOTH UPPER LT HAND TA IL BOOM TO FUSELAGE ATTACH BOLTS BROKEN. REPLACED ALL TAIL BOOM ATTACHMENT BOLTS (6 EA), 5 INCH DRIVE SHAFT, SLIDER COU PLING AND ENG TO TRANSMISSION DRIVE SHAFT. NOTE - THOROUGH INSP OF ACFT AND DYE PENETRANT INSP OF ATTACHMENT FITTINGS D ID NOT TURN UP ANY DAMAGE TO THE AIRFRAME OR ENG MOUNTS. A/C TEST FLIGHT CHECKED GOOD. 1 G 7 1 3O 4H11 1996121200156 19961212 00156 WP 1996 12 12 96ZZZX5941 1 19961109 G 5302 AN520A BOLT HILLER UH12 UH12E 4360122 WP TAIL BOOM ATTACH FAILED B CHIR A UNSCHED LANDING O OTHER EX EXTERNAL LOAD 1 NM 09 9749C 33 2146 IN CLIMB-OUT FROM LOG LANDING WITH EXT LOAD AT AN ALT OF APPROX 400 FEET AND 69.5 PSI TORQ, PILOT HEARD A 'BANG' FOLLOWE D BY A HIGH FREQ VIBR. AFTER CHECKING ALL INST (NORMAL) PILOT JETTISONED EXT LOAD AND LONG LINE. PILOT EXECUTED A PREC AUTIONARY LANDING TO THE LOG LANDING WITHOUT INCIDENT. HELICOPTER INSP AFTER SHUT DOWN DISCOVERED BOTH UPPER LT HAND TA IL BOOM TO FUSELAGE ATTACH BOLTS BROKEN. REPLACED ALL TAIL BOOM ATTACHMENT BOLTS (6 EA), 5 INCH DRIVE SHAFT, SLIDER COU PLING AND ENG TO TRANSMISSION DRIVE SHAFT. NOTE - THOROUGH INSP OF ACFT AND DYE PENETRANT INSP OF ATTACHMENT FITTINGS D ID NOT TURN UP ANY DAMAGE TO THE AIRFRAME OR ENG MOUNTS. A/C TEST FLIGHT CHECKED GOOD. 1 G 7 1 3O 4H11 1996121200157 19961212 00157 WP 1996 12 12 96ZZZX5942 1 19961113 G 6220 5143711 HUB HILLER UH12 UH12E 4360122 WP M/R HEAD CRACKED D K NONE O OTHER IN INSP/MAINT 1 WP 17 180HA 823 346 HA3080 CRACK FOUND INSIDE CONICAL SURFACE DURING PRE-FLIGHT INSPECTION. CRACKING IN THIS AREA IS COMMON. 1 G 7 1 3O 4H11 1996121200158 19961212 00158 CE 1996 12 12 96ZZZX5943 1 19961119 G 2437 MTA206R SWITCH CESSNA 425 425 2076018 CE BAT/GEN MALFUNCTION B DJFR K NONE O OTHER IN INSP/MAINT 1 EA 23 35TK 3337 4250088 LEFT HAND GENERATOR APPEARED TO CARRY ONLY 60 AMP LOAD. TROUBLESHOT TO AN INDICATION ERROR. FOUND BAT/GEN SWITCH TO CA USE LEFT GENERATOR AMMETER INDICATION ERROR. INSTALLED NEW SWITCH OPERATIONAL TEST GOOD. THIS IS THE SECOND TIME THIS FACILITY HAS FOUND THIS PROBLEM. 1 L 7 2 3T RT A7CE 1996121200349 19961212 00349 SO 1996 12 12 96ZZZX5945 1 19960717 G 3340 6537200 RETAIN ASSY PIPER PA28 PA28151 7102805 SO LANDING LIGHT CRACKED D A K NONE O OTHER IN INSP/MAINT 1 GL 09 43456 287415499 WHILE CHANGING LANDING LIGHT, FOUND LAMP RETAINER CRACKED AROUND UPPER STUD AND AROUND SCREW HOLE. THIS CONDITION CAUS ED LANDING LIGHT TO VIBRATE EXCESSIVELY, PREMATURELY BURNING OUT BULB. SUBMITTER STATED THIS RETAINER SHOULD BE CHECKED AT EVERY INSPECTION, INCLUDING PRE-FLIGHT. IF RETAINER BROKE LOOSE, IT AND THE LANDING LIGHT COULD POSSIBLY BECOME ENT ANGLED IN THE PROP. 1 L 7 1 3O 2A13 1996121200350 19961212 00350 SO 1996 12 12 96ZZZX5946 2 19961119 G 7310 646432 PRIMER LINE PIPER PA46 PA46310P 7104605 SO CONT O520 TSIO520BE 17040 SO TOP OF ENG CRACKED D A K NONE O OTHER IN INSP/MAINT 1 EA 07 4323B 468408009 AIRCRAFT ENGINE HARD TO START AND RUNNING LEAN WITH HIGH TIT READING WHEN FLYING. INSPECTED ENGINE AND FOUND CLAMP P/N 24609 (CONTINENTAL) WAS BROKEN THROUGH AND PRIMER VALVE WAS MOVING AROUND UNSUPPORTED. THIS CAUSED THE PRIMER LINE TO W ORK-HARDEN AND AT THE B-NUT CONNECTION. SUBMITTER STATED THIS CAN CAUSE ENGINE FIRE AT A HOT START CONDITION. 1 L 7 1 3O 3 O A25SO E8CE 1996121200351 19961212 00351 SO 1996 12 12 96ZZZX5947 2 19961120 G 8540 GEAR SHAFT CESSNA 421 421B 2076014 CE CONT O520 GTSIO520H 17032 SO LT START ADAPTER WORN D K NONE O OTHER IN INSP/MAINT 1 SW 03 511LC 310 421B0423 1881017A STARTER ADAPTER SHAFT GEAR WAS REMOVED FOR INSPECTION AND FOUND TO BE WORN BEYOND ACCEPTABLE LIMITS IAW CSB94-4A. 1 L 7 2 3O 3 O A7CE E7CE 1996121200352 19961212 00352 EA 1996 12 12 96ZZZX5948 2 19960621 G 8530 73806 PUSHROD CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA ENG CYL WORN D K NONE O OTHER IN INSP/MAINT 1 EA 09 5249P 4284 15284901 L1451415 DURING 100-HOUR INSPECTION, NOTICED FOUR PUSHROD TUBES WERE DENTED. UPON FURTHER INVESTIGATION, FOUND THAT THREE OF THE FOUR PUSHRODS WERE WORN DUE TO RUBBING ON THE PUSHROD SHROUD. THE THREE PUSHRODS WERE WORN FROM 25 PERCENT TO 80 PERCE NT THROUGH WALL THICKNESS. SUSPECT CAUSE OF BENT PUSHROD SHROUDS WAS MECHANICS LAYING TOOLS AND EQUIPMENT ON ENGINE DUR ING MAINTENANCE. 1 H 7 1 3O 3 O NT 3A19 E223 1996121200353 19961212 00353 CE 1996 12 12 96ZZZX5949 1 19961023 G 2820 0403434 LINE CESSNA 150 152 2071835 CE CABIN LT FWD LEAK D K NONE K FLUID LOSS IN INSP/MAINT 1 GL 03 6101Q 8174 15285126 FUEL LEAK IN CABIN. LT FORWARD LOWER FUEL LINE FOUND LEAKING DUE TO CORROSION CAUSED BY MOISTURE UNDER LOOSE FITTING PL ASTIC SLEEVE. RT ALSO CORRODED. REPLACED BOTH FUEL LINES AND REMOVED PLASTIC SLEEVE. PROTECTED LINE WITH SPIRAL WRAP. 1 H 7 1 3O NT 3A19 1996121200354 19961212 00354 CE 1996 12 12 96ZZZX5950 1 19961023 G 2820 0403433 LINE CESSNA 150 152 2071835 CE CABIN RT FWD CORRODED D K NONE K FLUID LOSS IN INSP/MAINT 1 GL 03 6101Q 8174 15285126 FUEL LEAK IN CABIN. LT FORWARD LOWER FUEL LINE FOUND LEAKING DUE TO CORROSION CAUSED BY MOISTURE UNDER LOOSE FITTING PL ASTIC SLEEVE. RT ALSO CORRODED. REPLACED BOTH FUEL LINES AND REMOVED PLASTIC SLEEVE. PROTECTED LINE WITH SPIRAL WRAP. 1 H 7 1 3O NT 3A19 1996121200356 19961212 00356 CE 1996 12 12 96ZZZX5952 1 19961115 G 5753 3516505084 RIB BEECH 35 V35 1151538 CE FLAP CRACKED B BX4R K NONE O OTHER IN INSP/MAINT 1 NM 03 6238V 2638 D8588 DURING RE-SKIN OF HAIL DAMAGED FLAP, FOUND NOSE RIB AT ACTUATOR ATTACH POINT CRACKED. CRACK IS IN WEB OF RIB AT THE REL IEF OF THE CAP FORMATION, LOWER FORWARD. SUBMITTER STATED THIS IS NOT AN UNCOMMON FIND. THIS CAN ONLY BE DETECTED IF T HE SKIN IS REMOVED. 1 L 7 1 3O 3A15 1996121200357 19961212 00357 EA 1996 12 12 96ZZZX5953 2 19961111 G 8530 SL134441 PISTON PIN CESSNA 172 172P 2072436 CE LYC O320 O320D2J 41508 EA NR 3 CYL BROKEN B PP4R K NONE O OTHER IN INSP/MAINT 1 SO 05 65665 1055 17275810 L1336139A NR 3 CYL HAS BROKEN PISTON PIN. SUSPECT CAUSE - MANUFACTURER'S DEFECT. 1 H 7 1 3O 3 O NT 3A12 E274 1996121200358 19961212 00358 EA 1996 12 12 96ZZZX5954 2 19961023 G 8550 RJ10251 PUMP PIPER PA60 PA60700P 7106023 NM LYC O540 LTIO540U2A 41533 EA OIL SCAV WASHER WORN D K NONE O OTHER IN INSP/MAINT 1 GL 17 6905A 3268 608423001 L271568A IN C/W AEROSTAR SB600-131 INSPECTION OF TURBO OIL SCAVENGE PUMP, FOUND WASHER UNDER RETAINING RING OF SCAVENGE PUMP EMP ELLER WORN AWAY LEAVING RING TO FLOAT IN COUPLING AREA. SUBMITTER STATED THIS CONDITION APPARENTLY SHOULD NOT HAPPEN IF PROPER GARLOCK SEAL IS INSTALLED IN ENGINE ADAPTER WHICH, ON THIS PARTICULAR APPLICATION, THE PROPER SEAL IS INSTALLED. PART TOTAL TIME 784.1 HRS. 1 M 7 2 3O 3 O RT A17WE E14EA 1996121200359 19961212 00359 SO 1996 12 12 96ZZZX5955 2 19961107 G 8540 GEAR SHAFT CESSNA 421 421B 2076014 CE CONT O520 GTSIO520H 17032 SO LT START ADAPTER WORN D K NONE O OTHER IN INSP/MAINT 1 SW 03 707DM 550 421B0145 218419R STARTER ON THE RIGHT ENGINE BEGAN TO WORK INTERMITTENTLY. THE PILOT SAID THE STARTER HAD BEEN TURNING SLOW AND MAKING N OISE. WHEN THE STARTER WAS REMOVED AND TESTED, IT WORKED FINE. THE STARTER ADAPTER SHAFT GEAR WAS REMOVED AND FOUND TO BE WORN BEYOND ACCEPTABLE LIMITS, IT ALSO DAMAGED THE REST OF THE ENGINE. 1 L 7 2 3O 3 O A7CE E7CE 1996121200360 19961212 00360 SO 1996 12 12 96ZZZX5956 2 19961112 G 8530 653446 VALVE CESSNA 206 TU206G 2073357 CE CONT O520 TSIO520M 17040 SO NR 1 CYL EXH LEAKAGE B FE6R K NONE O OTHER IN INSP/MAINT 1 NM 11 717CM 40 U20604988 230184R ENGINE HAS 40.0 HRS SINCE MAJOR OVERHAUL AT WHICH TIME NEW TCM CYLINDERS WERE INSTALLED. COMPRESSION CHECK SHOWS NR 1 C YLINDER AT 40/80 LEAKING THROUGH EXHAUST VALVE AND CYLINDERS NR 2, 3, 5, AND 6 TO BE AT 70/80 WITH SLIGHT EXHAUST VALVE LEAKAGE. BORESCOPE INSPECTION SHOWS NR 1 CYLINDER TO HAVE A VERY NARROW EXHAUST VALVE SEAT WITH LIGHT CONTACT. COMPRES SION READINGS ON THE ABOVE CYLINDERS ARE OUTSIDE THE LIMITS SPECIFIED IN TCM SB M84-15, DATED DEC 21, 1984. 1 H 7 1 3O 3 O A4CE E8CE 1996121200361 19961212 00361 SW 1996 12 12 96ZZZX5957 1 19961114 G 5730 STITSHS90X FABRIC BBAVIA 7 7AC 2110102 SW RT INB WING LOOSE D A K NONE O OTHER IN INSP/MAINT 1 GL 05 72468 450 7AC5450 DURING FLIGHT, UNUSUAL NOISE WAS HEARD. IT WAS FOUND THAT FABRIC WAS LOOSE ON 1ST AND 2ND RIBS ON RT WING, AND NR 4 AND NR 8 SCREWS HAD PULLED OUT OF RIBS. SUBMITTER STATED IT IS BELIEVED THAT SCREW HOLES WERE SLIGHTLY OVERSIZE AND FABRIC WEAVE WAS FORCED INTO HOLES DURING INSTALLATION GIVING FALSE SENSE OF TIGHTNESS. 1 H 7 1 3O A759 1996121800017 19961218 00017 EA 1996 12 18 96ZZZX5959 2 19961113 G 7322 24A56 SPRING FACET MA4SPA CESSNA 172 172L 2072432 CE LYC O320 O320E2D 41508 EA CARB IDLE ADJ WEAK D O OTHER E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 SW 13 7624G 4043 10 BL224699 17259324 L2833127A INSTALLED OVERHAULED CARBURETOR AND RIGGED. WITHIN 10 HOURS, OWNER REPORTED ENGINE VERY ROUGH AT LOW POWER SETTINGS OR WOULD NOT EVEN IDLE. FOUND IDLE MIXTURE ADJUST SCREW GONE. NOTIFIED OVERHAULER WHO SENT NEW CARB. UPON INSTALLATION O F NEW UNIT, SPRING TENSION ON AJUST SCREW FOUND TO BE WEAK OR NON-EXISTANT AT CORRECT SETTING. OVERHAULER RECOMMENDED S TRETCHING SPRING. 1 H 7 1 3O 3 O NT 3A12 E274 1996121200363 19961212 00363 CE 1996 12 12 96ZZZX5960 1 19961016 G 3230 08421042 BELLCRANK CESSNA 310 310Q 2074242 CE NLG FAILED D A O OTHER P NO WARNING INDICATION AP APPROACH 1 SW 07 7935Q 6484 310Q0667 PILOT HEARD A POP DURING GEAR EXTENSION. PILOT RETRACTED AND EXTENDED GEAR AND NOSE GEAR WAS NOT DOWN AND LOCKED. NO G REEN LIGHT, GEAR TRAILING AT A 45 DEGREE ANGLE. UPON LANDING, THE NOSE GEAR FOLDED AFT. INVESTIGATION REVEALED THAT TH E BELLCRANK NEAR THE AFT END OF THE NOSE GEAR WELL HAD FAILED AT THE FORK BOLT. NO EVIDENCE OF PRIOR CRACK ON THE BELLC RANK. THIS AIRCRAFT HAD EXPERIENCED A BELLY LANDING WHERE IT APPEARED THAT THE GEAR WAS BEGINNING TO EXTEND WHEN THE RU NWAY WAS CONTACTED. THAT BELLY-IN WAS JUST HOURS PRIOR TO THIS FAILURE. THE ABOVE BELLCRANK WAS INSPECTED VISUALLY, AN D NOT REPLACED DURING REPAIRS. SUSPECT STRESS OF BELLY-IN CAUSED FAILURE. SUGGEST BETTER INSPECTION. 1 L 7 2 3O 3A10 1996121200364 19961212 00364 SO 1996 12 12 96ZZZX5961 1 19961118 G 2820 MIL6000 HOSE PIPER PA18 PA18150 7101828 SO HEADER TANK DETERIORATED D A K NONE O OTHER IN INSP/MAINT 1 WP 21 9798P 1350 187609031 THE ENGINE WOULD STARVE FOR FUEL WHEN THE RIGHT TANK WAS SELECTED. THE RIGHT FUEL HEADER TANK (REAR) WAS REMOVED. BOTH LINES INTO THE HEADER TANK WERE PLUGGED WITH MIL-6000 HOSE COUPLING MATERIAL. THE EXPOSED HOSE INTERIOR WAS NOTICEABLY DETERIORATED. IF HOSES WERE ORIGINAL, THEY COULD BE 20 YEARS OLD. THE A/C WAS APPROVED FOR AUTO GAS. IT HAD ALSO USE D 100LL. 1 H 7 1 3O 1A2 1996121200365 19961212 00365 CE 1996 12 12 96ZZZX5962 1 19961105 G 3211 63411121 PIN CESSNA 525 525 2076601 CE MLG ATTACH DEFECTIVE B EBVR K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 09 DURING COMPLETION OF CESSNA SB SB 525-32-08, THE REQUIRED KIT WAS ORDERED AND RECEIVED. UPON INSPECTION OF THE KIT PART S, ALL FOUR MAIN LANDING GEAR PINS WERE FOUND UNSERVICEABLE. 3 PINS (PN 6341112-1) WERE FOUND WITH LABELING IDENTIFYING THEM AS BAD FROM STOCK AND THE FOURTH WAS SCRATCHED AND NICKED. A REPLACMENT KIT WAS ORDERED FROM CESSNA, INSPECTED, A ND THE BULLETIN COMPLETED. 1 L 7 2 4F RT A1WI 1996121200367 19961212 00367 CE 1996 12 12 96ZZZX5964 1 19960927 G 2150 4573150 CLAMP CESSNA 525 525 2076601 CE RAM AIR PRECOOL BROKEN B EBVR K NONE O OTHER IN INSP/MAINT 1 GL 09 195ME 5250110 AIRCRAFT WAS HAVING A HEATING PROBLEM. (COULD NOT GET HEAT INTO CABIN) WHILE TROUBLESHOOTING. MAINTENANCE FOUND A CLAM P LAYING ON THE REAR COMPARTMENT FLOOR BROKEN. THE CLAMP CAME FROM THE FWD SIDE OF THE RAM-AIR PRECOOLER, HOWEVER, THE HEATING PROBLEM WAS NOT CAUSED BY THE BROKEN CLAMP. MAINTENANCE FOUND A BAD RAM AIR MODULATING VALVE. 1 L 7 2 4F RT A1WI 1996121200368 19961212 00368 CE 1996 12 12 96ZZZX5965 1 19960927 G 2150 VALVE CESSNA 525 525 2076601 CE RAM AIR MOD FAILED B EBVR K NONE O OTHER IN INSP/MAINT 1 GL 09 195ME 5250110 AIRCRAFT WAS HAVING A HEATING PROBLEM. (COULD NOT GET HEAT INTO CABIN) WHILE TROUBLESHOOTING. MAINTENANCE FOUND A CLAM P LAYING ON THE REAR COMPARTMENT FLOOR BROKEN. THE CLAMP CAME FROM THE FWD SIDE OF THE RAM-AIR PRECOOLER, HOWEVER, THE HEATING PROBLEM WAS NOT CAUSED BY THE BROKEN CLAMP. MAINTENANCE FOUND A BAD RAM AIR MODULATING VALVE. 1 L 7 2 4F RT A1WI 1996121200369 19961212 00369 SW 1996 12 12 96ZZZX5966 1 19960821 G 7160 65525062 DUCT GULSTM 560 560 0141402 SW LT/RT ENG CRACKED B EBVR K NONE O OTHER IN INSP/MAINT 1 GL 09 444GG 1300 5600262 DURING A PHASE INSPECTION, BOTH THE LT AND RT ENGINE INLET OUTER DUCT SKINS WERE FOUND TO HAVE SEVERAL CRACKS EMANATING FROM THE RIVET HOLES TO THE SKIN EDGES WHERE THE DUCT IS RIVETED TO THE INLET LIP. DISCUSSION WITH MANUFACTURER DETERMI NED THE SUSPECT CAUSE OF CRACKING WAS DUE TO IMPROPER ASSEMBLY AT THE TIME THE AIRCRAFT WAS BUILT. SUBMITTER RECOMMENDS OWNER/OPERATOR INSPECT FOR THIS CONDITION AT FIRST AVAILABLE OPPORTUNITY. 1 H 7 2 3O 6A1 1996121200370 19961212 00370 NE 1996 12 12 96ZZZX5967 2 19961025 G 7200 ENGINE LEAR 25 25 5170506 CE GE CJ610 CJ6106 30006 NE PWR SECT MALFUNCTION E O OTHER R PARTIAL RPM/PWR LOSS CR CRUISE 1 SW 09 345MC 046 251164 DURING CRUISE, ENGINE ROLL BACK AT FL 380. INSPECTED ENGINE BLADES T-GUIDE VANES AND FUEL CONTROL FOR CAUSE. NO DEFECT S NOTED. FLIGHT TEST A/C TO FL 410, NO DEFECTS NOTED. 2 L 7 2 4J 4 J A10CE 1E16 1996121200371 19961212 00371 CE 1996 12 12 96ZZZX5968 1 19960917 G 3211 63411121 PIN 6322000801S CESSNA 525 525 2076601 CE RT MLG ATTACH RUSTED B EBVR K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 09 525KA 5250019 AFT PIN IN RT MAIN LANDING GEAR WAS RUSTED AND PITTED. THIS IS FROM A NEW WING ASSY WITH ZERO TIME SINCE NEW. SUBMITTE R RECOMMENDS RUST INHIBITOR APPLICATION DURING ASSEMBLY. 1 L 7 2 4F RT A1WI 1996121200372 19961212 00372 CE 1996 12 12 96ZZZX5969 1 19961123 G 3040 WARN LIGHT BEECH 60 60 1153602 CE DEICER LOW LEVEL STAYS ARMED D A O OTHER N FALSE WARNING TO TAKEOFF 1 NM 03 164PA 030 THE DE-ICE ALCOHOL LOW LEVEL WARNING LIGHT ILLUMINATES ON THE MASTER WARNING PANEL AT AIRCRAFT ROTATION DURING TAKEOFF. ONCE ACTIVATED, THE LIGHT STAYS ILLUMINATED UNTIL POWER IS REMOVED FROM THE AIRCRAFT. LEARJET ISSUED OPTIONAL SERVICE BULLETIN 60-30-1 TO ADDRESS THE PROBLEM. SINCE THE ILLUMINATION OF A CAUTION LIGHT OCCURS AT SUCH A CRITICAL POINT IN T HE FLIGHT, SUBMITTER'S OPINION IS THIS IS A SAFETY OF FLIGHT ISSUE. SUBMITTER RECOMMENDS THAT LEARJET RE-CLASSIFY THE B ULLETIN TO MANDATORY, OR THE FAA SHOULD CONSIDER ISSUING AN AD. 1 L 7 2 3O A12CE 1996020900307 19960209 00307 CE 1996 2 9 96ZZZX597 1 19960115 G 2434 1101900 GENERATOR DELCO BEECH 23 23 1151202 CE REAR HOUSING BRUSHES FAILED D O OTHER H ELECT. POWER LOSS-50 PC NR NOT REPORTED 1 EA 05 8722M M511 GENERATOR WENT 'OFF LINE'. DISASSEMBLY FOUND BRUSH LEADS CUT AND FRAYED BY BRUSH HOLDERS. REAR BEARING FOUND LOOSE IN REAR HOUSING CAUSING ROTATIONAL VIBRATION WHICH CAUSED BRUSH LEADS TO HIT BRUSH HOLDERS. 1 L 7 1 3O A1CE 1996121200373 19961212 00373 CE 1996 12 12 96ZZZX5970 1 19961119 G 2430 M22759749 WIRE BEECH 100 B100 1152919 CE START/GEN CRACKED B A UO2R K NONE O OTHER IN INSP/MAINT 1 GL 19 87NW 5675 BE42 THE STARTER/GENERATOR 4 GAUGE WIRES THAT RUN FROM THE FIREWALL POWER CONNECTOR TO THE STARTER/GENERATOR WERE FOUND WITH CRACKED INSULATION. THE CRACKS ARE 2 INCHES TO 4 INCHES IN LENGTH, EXPOSING THE CENTER CONDUCTOR. ON THE LT AND RT ENG INE, THE DEFECTIVE WIRE IS LABELED P10C4. SOME OF THE WIRING ON THIS AND OTHER B100'S IS M22759/8 OR /16. THESE 2 SHOW NO SIGNS OF SPLITTING OR CRACKING. ONLY THE TYPE M22759/7 HAS BEEN FOUND WITH CRACKS. TEMP RATING ON THESE WIRE TYPES ARE PLUS 150 DEGRESS CELSIUS FOR THE /16, PLUS 200 DEGREES CELSIUS FOR THE /7 AND PLUS 260 DEGREES CELSIUS FOR THE /8. THIS IS THE FOURTH B100 FOUND WITH THIS PROBLEM. 1 L 7 2 4T A14CE 1996121200374 19961212 00374 CE 1996 12 12 96ZZZX5971 1 19961110 G 5712 5522620 RIB STRAP CESSNA 500 550 2076604 CE LT WS 91 MISINSTALLED H S K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 99 101KK 5500209 LEFT WING RIB AT WS 91 UPPER STRAP IS JOGGLED TO FIT BETWEEN SPAR AND RIB. ASSEMBLY AT FACTORY PUT STRAP ABOVE SPAR, CR EATING A 0.050 INCH BUMP IN WING. SUBMITTER STATES CESSNA RESEARCHED AIRCRAFT BUILD RECORDS AND COULD NOT FIND ANYTHING SHOWING WHY THIS WAS ASSEMBLED THAT WAY. RECOMMEND ALL 500 OPERATORS CHECK FOR THIS CONDITION. 1 L 7 2 4F A22CE 1996121200375 19961212 00375 NE 1996 12 12 96ZZZX5972 2 19961120 G 7200 ENGINE AEROSP 601 SN601 8680661 EU PWA JT15 JT15D4 52112 NE RT ENG FAILED G A O OTHER O OTHER CR CRUISE 1 GL 05 200MT 2040 606 40 PCE70080 PILOT EXPERIENCED SUDDEN RT ENGINE FAILURE AT 27,000 FEET ALTITUDE WITH NO WARNING OR PREVIOUS INDICATIONS. PRELIMINARY INSPECTION BY CREW AFTER LANDING DISCLOSED DAMAGED PARTS COMING OUT ENGINE TAIL SECTION. 2 L 7 2 4F 4 F A37EU E1NE 1996121200376 19961212 00376 SO 1996 12 12 96ZZZX5973 1 19960720 G 7332 320283 SWITCH GULSTM G159 G159 3952202 SO FUEL PRESS CRACKED D K NONE K FLUID LOSS IN INSP/MAINT 1 SO 09 3NA 92 FUEL DIFFERENTIAL PRESSURE SWITCH CRACKED 1/2 WAY AROUND AT POINT OF CONNECTOR PLUG ATTACH, THIS ALLOWED FUEL TO LEAK ON TO TOP OF ENGINE. 2 L 7 2 4T 1A17 1996121200378 19961212 00378 CE 1996 12 12 96ZZZX5975 1 19961106 G 5311 FRAME MTSBSI MU2 MU2B60 5780460 CE RT FS 4850 CRACKED D A K NONE O OTHER IN INSP/MAINT 1 GL 25 33EW 3264 1519SA AFTER REMOVING THE RT SIDE WALL OF CABIN INTERIOR, CRACKS WERE FOUND IN FS 4850. MUII SB 073/53-002A, FUSELAGE FRAME IN SP AND REPAIR ADDRESSES THIS PROBLEM. THE SB WAS C/W AT 2606.0 AFTT. REINSPECTION IS DUE AT 4606.0 HRS. ACFT ONLY HAS 3264.0 HRS. SUBMITTER STATED THIS IS THE SECOND ACFT WITH CRACKS FOUND AT THIS STATION THAT HAVE HAD SB P/C/W AND BEFO RE REINSPECTION WAS DUE. 1 H 7 2 3T RT A10SW 1996121200379 19961212 00379 GL 1996 12 12 96ZZZX5976 3 19961126 G 6111 BEARING MTSBSI MU2 MU2B60 5780460 CE HARTZL HCB4T HCB4TN5 GL PROP BLADE DEFECTIVE D K NONE O OTHER IN INSP/MAINT 1 SO 03 429WM 1520SA CDA3351 HUB TT 486.7 BLADES, 946.0 TT. ONE BLADE STICKS IN ONE POSITION AND 2 BLADES ROUGH, HARTZELLS REPLY WAS A FLAT SPOT ON BEARINGS OR BEARINGS STEPPING ACROSS SPLIT IN RACE, OR MISMATCHED SET OF RACES. BEARING AND RACES TT IS UNKNOWN DUE TO NO ENTRY IN LOG BOOK OR WORK ORDER. PROBLEM FOUND DURING 100 HOUR INSPECTION. PROP SENT TO HARTZELL NOV 26, 1996. 1 H 7 2 3T RT A10SW 6 C P40EA 1996121200380 19961212 00380 NM 1996 12 12 96ZZZX5977 1 19961115 G 3210 65195173 SIDE BRACE 65195177 BOEING 727 72761 1384017 NM LT MLG BROKEN B A VN4R K NONE O OTHER IN INSP/MAINT 1 SO 19 530KF 19176 AFTER LANDING, LEFT MLG DOOR STARTED CYCLING OPEN AND CLOSED. DURING TROUBLESHOOTING OF DOOR PROBLEM, LEFT MLG UPPER SI DE BRACE SEGMENT WAS FOUND BROKEN AT THE FWD TRUNNION. REF IPC 32-10-1, FIGURE 4, ITEM 310. A/C HOURS 31,889. A/C CYC LES 71,297. 2 L 7 3 4F A3WE 1996121200381 19961212 00381 CE 1996 12 12 96ZZZX5978 1 19961031 G 2430 M22759749 WIRE BEECH 100 B100 1152919 CE LT ENG START/GEN CRACKED B A UO2R K NONE O OTHER IN INSP/MAINT 1 GL 19 6241P BE130 THE STARTER/GENERATOR 4 GAUGE WIRES, THAT RUN FROM THE FIREWALL POWER CONNECTOR TO THE STARTER/GENERATOR, WERE FOUND WIT H CRACKED INSULATION. THE CRACKS RUN PARALLEL WITH THE WIRE. SOME OF THE CRACKS ARE OVER 3 INCHES IN LENGTH EXPOSING T HE CENTER CONDUCTOR. ON THE LEFT ENGINE, THE WIRE NUMBERS OF THE DEFECTIVE WIRES ARE K2D4, K2F4, P10A4, P10C4, AND P10E 4. THIS IS THE THIRD B100 FOUND WITH THIS DEFECT. 1 L 7 2 4T A14CE 1996121200382 19961212 00382 CE 1996 12 12 96ZZZX5979 1 19961025 G 5512 23320007 SKIN LEAR 25 25D 5170514 CE HORIZ STAB CORRODED H K NONE O OTHER IN INSP/MAINT 1 NM 03 70JF 7096 278 FOUND CORROSION ON LEADING EDGE SKIN WHEN STAB BOOTS WERE BEING REPLACED. COULD HAVE BEEN CAUSED BY METAL NOT BEING PRO PERLY TREATED WHEN MANUFACTURED OR BOOTS GOT HOLES IN THEM LETTING MOISTURE IN. SUBMITTER STATES PROPER TREATMENT OF ME TAL AND/OR GOOD BOOTS INSTALLED AT ALL TIMES. 2 L 7 2 4J A10CE 1996020900308 19960209 00308 CE 1996 2 9 96ZZZX598 1 19960118 G 7430 C2925010106 SWITCH GERDES CESSNA 150 152 2071835 CE MAG IGNITION DEFECTIVE D K NONE O OTHER IN INSP/MAINT 1 EA 21 4847B 5574 15283670 DURING RUN-UP/MAG CHECK, THE IGNITION KEY COULD BE EASILY REMOVED (IN ANY POSITION). CESSNA SEB 92-29 AND TCM SB 636 CL EARLY CITES THIS AS A MANDATORY INSPECTION, AND A 'HOT MAG' IS NOT SAFE. YET, AD 93-05-06 'GERDES SWITCH INSPECTION', H AD BEEN SIGNED OFF. 1 H 7 1 3O NT 3A19 1996121200384 19961212 00384 NM 1996 12 12 96ZZZX5981 1 19961024 G 5311 FRAME BOEING 727 727276 138408R NM FS 227.8 CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 908PG 20951 DURING C-CHECK INSPECTION, LEVEL 2 CORROSION WAS NOTED ON FUSELAGE FRAME 227.8 FROM WL 208 TO WL 225. 2 L 7 3 4F RT A3WE 1996121200385 19961212 00385 NM 1996 12 12 96ZZZX5982 1 19961024 G 5311 FRAME BOEING 727 727276 138408R NM FS 219.8 CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 908PG 20951 DURING C-CHECK INSPECTION, LEVEL 2 CORORSION WAS NOTED ON FUSELAGE FRAME 219.8, AT WL 220. 2 L 7 3 4F RT A3WE 1996020900309 19960209 00309 CE 1996 2 9 96ZZZX599 1 19960109 G 2913 24343RAB PUMP CESSNA 421 421C 2076016 CE HYD/AIR COND SHAFT RUSTED B R2JR K NONE K FLUID LOSS IN INSP/MAINT 1 EA 21 940WP 4037 421C0228 NR 2 ENGINE AIR CONDITIONER HYDRAULIC PUMP FOUND LEAKING OUT CASE DRAIN. WHILE ATTEMPTING TO REMOVE PUMP, FOUND SHAFT R USTED ONTO AIRCRAFT HYDRAULIC PUMP AND AIRCRAFT HYDRAULIC SHAFT RUSTED SOLID ONTO ENGINE DRIVE ADAPTER. DRIVE SHAFT HAD TO BE FORCIBLY REMOVED FROM ENGINE AND ADAPTER BEARING REPLACED. THESE TWO HYDRAULIC PUMPS ARE 'PIGGY-BACKED' ONTO THE SAME ENGINE DRIVE PAD. MANUFACTURER REQUIRES NO INSPECTION OR LUBE OF THESE DRIVE SHAFT SPLINES. SUBMITTER SUGGESTS C ESSNA REVISE INSPECTION PROGRAM TO PERIODICALLY REMOVE, INSPECT, AND LUBE THESE SPLINES. 1 L 7 2 3O A7CE 1996121200492 19961212 00492 1996 12 12 96ZZZX5991 4 19961018 G 2312 4000103000 TRANSCEIVER RT450 BOLKMS 117 BK117A3 5626015 EU COCKPIT VHF FAILED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 117CH 202 7061 TRANSCEIVER WILL NOT TRANSMIT. IN A/C ONLY 3.5 HRS BEFORE FAILURE. 1 G 7 2 3U H13EU 1996121200493 19961212 00493 1996 12 12 96ZZZX5992 4 19961016 G 2312 4000103000 TRANSCEIVER RT450 BOLKMS 117 BK117A3 5626015 EU COCKPIT VHF FAILED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 117CH 778 7061 TRANSCEIVER WILL NOT TRANSMIT. 1 G 7 2 3U H13EU 1996121200495 19961212 00495 NM 1996 12 12 96ZZZX5993 1 19960823 G 5530 6516829 FITTING BOEING 727 727251 138408H NM VERT STAB CORROSION B EF2R K NONE O OTHER IN INSP/MAINT 1 SW 05 280US 21159 VERTICAL STABILIZER HINGE FITTINGS HAVE CORROSION DAMAGE AT THE BEARING HOLES. REPAIRED FITTINGS PER DALFORT AVIATION X EA NR X1-55-130. 2 L 7 3 4F A3WE 1996121200496 19961212 00496 NM 1996 12 12 96ZZZX5994 1 19960823 G 5530 6516873 FITTING BOEING 727 727251 138408H NM VERT STAB CORROSION B EF2R K NONE O OTHER IN INSP/MAINT 1 SW 05 280US 21159 VERTICAL STABILIZER HINGE FITTINGS HAVE CORROSION DAMAGE AT THE BEARING HOLES. REPAIRED FITTINGS PER DALFORT AVIATION X EA NR X1-55-130. 2 L 7 3 4F A3WE 1996121200497 19961212 00497 NM 1996 12 12 96ZZZX5995 1 19960823 G 5320 65C290802 ANGLE BOEING 727 727251 138408H NM BS 1183 CRACK B EF2R K NONE O OTHER IN INSP/MAINT 1 SW 05 280US 21159 BS 1183 BULKHEAD FORWARD SIDE VERTICAL SUPORT ANGLE HAS .3750 INCH LONG CRACK ON RBL 10 AS SEEN FROM AFT BAG BIN. REPAI RED ANGLE PER BOEING SB 727-53-0175. 2 L 7 3 4F A3WE 1996121200649 19961212 00649 CE 1996 12 12 96ZZZX5996 1 19961127 G 7160 1211282 AIR FILTER AIRMAZE BEECH 58 58P 1152744 CE ELEMENT FRAME RIVETS PULLED D L A K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 25 NEW ENGINE AIR FILTERS WERE ORDERED FROM BEECH. WHILE INSTALLING A FILTER, IT WAS DISCOVERED THAT THE FRAME WAS ASSEMBL ED WITH A PULLED 'POP' RIVET. THE RIVET STEM WAS NOT REMOVED FROM THE RIVET AFTER IT WAS PULLED. ONE STEM FELL TO THE FLOOR. FURTHER INVESTIGATION FOUND ONE STEM LODGED TO THE FILTER ELEMENT 'FINS' AND 2 OTHERS STILL IN RIVETS, BUT LOOSE . 1 L 7 2 3O A23CE 1996121200650 19961212 00650 SO 1996 12 12 96ZZZX5997 1 19961112 G 3213 2001 STRUT FORK MAULE M7 M7235 5460170 SO MLG DEFECTIVE D K NONE W INADEQUATE Q C IN INSP/MAINT 1 AL 03 INSP OF NEW STRUT FORK FOUND UNUSEABLE DUE TO THREADS FILLED WITH CAD PLATING. ALSO FORK PORTION WAS POORLY MACHINED AN D WAS GROOVED. 1 H 7 1 3O NC 3A23 1996121200651 19961212 00651 1996 12 12 96ZZZX5998 1 19961111 G 2822 1B56 PUMP AIRBORNE ENG FUEL FAILED D K NONE O OTHER IN INSP/MAINT 1 GL 13 1C55 ARMATURE OUT OF DYNAMIC BALANCE CAUSING PREMATURE FAILURE OF THE FUEL PUMP. 1996121200652 19961212 00652 SO 1996 12 12 96ZZZX5999 1 19960927 G 5610 54901006 WINDOW PIPER PA31T PA31T1 7103126 SO PILOT SIDE BLEW OUT B A ATZR O OTHER O OTHER CR CRUISE 1 CE 09 2552Y 4200 31T8104061 PILOT'S SIDE WINDOW BLEW OUT AT 19,000 FEET ON CLIMB. STORM WINDOW AND SOME PARTS OF SIDE WINDOW DID NOT LEAVE AIRCRAFT . ALL SYSTEMS SEEMED TO BE FUNCTIONING NORMAL AND NO WARNING JUST BLEW OUT. AC AND PART TT: 4200.0. 1 L 7 2 3T A8EA 1996121200653 19961212 00653 CE 1996 12 12 96ZZZX6000 1 19961117 G 3222 DC630C VALVE RAYTHN DH125 HAWKER800XP CE NLG STRUT LEAKING G O OTHER O OTHER LD LANDING 1 SW 11 291XP 270 258291 ON 11-17-96 DURING ROLL-OUT, NOSE STRUT COLLAPSED. AFTER A/C RETURNED, INSP FOUND SCHRADER VALVE LEAKING. REPLACED VAL VE AND LEAK CHECKED FOR 24 HRS. CYCLES, 156. 2 L 7 2 4F RT A3EU 1996121200654 19961212 00654 GL 1996 12 12 96ZZZX6001 3 19961111 G 6114 D5892C93 HUB CESSNA 402 402C 207590R CE MCAULY 3AF32C 3AF32C93 GL NR 2 SOCKET CRACKED B ME4R K NONE O OTHER IN INSP/MAINT 1 SO 19 2717B 4021 1379 402C0221 796457 PROPELLER RECEIVED FOR OVERHAUL. AFTER DISASSEMBLY, DISCOVERED HUB CRACK IN NR 2 BLADE SOCKET, 2 THREADS IN 3 DEGREE TO 5 DEGREE POSITION. ALSO, BLADE RACES AND BALLS CORRODED. (WATER IN THE HUB). 1 L 7 2 3O A7CE 5 C P22EA 1996121200655 19961212 00655 CE 1996 12 12 96ZZZX6002 1 19961122 G 8011 641500 CLUTCH ASSY CESSNA 150 150L 2071826 CE CONT O200 O200A 17020 SO STARTER FAILED D L K NONE O OTHER IN INSP/MAINT 1 NE 03 21968 15074576 250816A48 ENGINE WAS INSTALLED IN TEST CELL AFTER OVERHAUL AND RUN FOR OVER 1 HR WITH AT LEAST 4 STARTS. CUSTOMER THEN INSTALLED ON AIRCRAFT, STARTED IT TO TAXI, PILOT SAID IT SEEMED ROUGH. ENGINE WAS SHUT DOWN. VISUAL CHECKS REVEALED NOTHING. TI MING WAS OK. HARNESS WAS ROUTED CORRECTLY. PILOT AGAIN ATTEMPTED TO START ENGINE. AFTER SEVERAL REVOLUTIONS PROP STOP PED AND HE SAID IT BRACKED UP BUT STARTER MOTOR CONTINUED TO TURN FREELY NOW WITHOUT TURNING CRANKSHAFT. STARTER WAS RE MOVED AND CLUTCH WAS FOUND WITH THE PILOT CENTER SHAFT BROKEN OFF AND ALL GEAR TEETH BROKEN OFF AND THE GEAR BODY SPLIT AT FRONT BUSHING HOLE LOCATION. 1 H 7 1 3O 3 O 3A19 E252 1996121200656 19961212 00656 EU 1996 12 12 96ZZZX6003 1 19961112 G 3210 TB1041033000 SCISSORS SOCATA TB9 TB9 8680694 EU LT MLG FAILED G L A K NONE O OTHER LD LANDING 1 EA 05 3040X 1503 THE LOWER SCISSORS ON THE LEFT MAIN GEAR CRACKED UPON TOUCH-DOWN, AND THE WHEEL TURNED CAUSING THE A/C TO SLIDE TO A STO P. INSPECTION REVEALED THE OUTBOARD SIDE OF THE LOWER SCISSORS WHERE IT ATTACHED TO THE STRUT HAD BEEN CRACKED FOR SOME TIME. THE ATTACHMENT PINS THAT HOLD THE SCISSORS WERE CORRODED DUE TO LACK OF GREASE. THIS CAUSED UNDUE STRESS ON THE SCISSORS WHICH WERE VERY HARD TO MOVE. THE GREASE FITTING IN THE SCISSORS WOULD NOT TAKE GREASE AT TIME OF INSPECTION. 1 L 7 1 3O NT AS1EU 1996121200657 19961212 00657 EA 1996 12 12 96ZZZX6004 2 19961015 G 7414 M3056 DISTRIBUTOR GEAR SLICK 631 MOONEY M20 M20M 5870222 SW LYC O540 TIO540AF1A 41532 EA LT MAG DETERIORATED C K NONE O OTHER IN INSP/MAINT 1 SO 15 530JP 631 92080001 270114 L928361A INVESTIGATION FOR DETERIORATED LT MAG FOUND LEFT MAG WAS (PRESSURIZED) FROM SAME 'T' FITTING AS RIGHT MAG BUT HAS MORE H EAT. LEFT MAG HAS B AND D TACHOMETER PICK UP WITH LARGER ORIFICE WHICH ALLOWS ALMOST TWICE THE AIRFLOW ALLOWING MORE HE AT INTO MAG. SUBMITTER STATED SLICK REPORTED OVER 1 YR AGO THEY WERE AWARE OF PROBLEM AND IT WOULD BE CORRECTED. THIS IS THE 2ND TIME HAVE HAD THIS PROBLEM WHICH IS SHARED BY MANY MOONEY OWNERS. 1 L 7 1 30 3 O RT 2A3 E14EA 1996121200658 19961212 00658 SO 1996 12 12 96ZZZX6005 2 19961115 G 7414 10349237 GEAR TOOTH 103493505 CESSNA 210 T210N 2073456 CE CONT O520 TSIO520R 17040 SO RT MAG BROKEN D K NONE O OTHER IN INSP/MAINT 1 WP 07 6506G 1330 653290R 21064406 269905R DURING INSP OF MAG FOR POINT WEAR AND CONDITION, A TOOTH WAS FOUND BROKEN FROM THE DIST GEAR. A NEW GEAR, CONDENSOR, AN D POINT WAS INSTALLED. THE MAG WAS RUN ON A TEST BENCH WITH NORMAL OPERATION. A POSSIBLE FLAW IN MATERIAL OR A GEAR HO LDING TOOL NOT BEING USED PROPERLY IS SUSPECT CAUSE OF THIS DEFECT. SUBMITTER STATED IF YOU USE A HOLDING TOOL, PAY CLO SE ATTENTION NOT TO TWIST THE MAG. ON REINSTALLATION! 1 H 7 1 3O 3 O 3A21 E8CE 1996121200659 19961212 00659 CE 1996 12 12 96ZZZX6006 1 19960731 G 2150 8820K16 SWITCH CESSNA 404 404CESSNA 2075901 CE AIR COND BURNED D H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS AP APPROACH 1 GL 17 37167 1352 4040129 PRIOR TO LANDING, THE PILOT NOTICED SMOKE IN THE COCKPIT COMING FROM THE PILOT'S SWITCH PANEL. THE PILOT THEN TURNED TH E MASTER OFF AND MADE A SAFE LANDING. INVESTIGATION FOUND THAT THE AIR COND TOGGLE SWITCH HAD FAILED AND BURNT. REPLAC EMENT OF THE SWITCH ALLOWED THE SYSTEM TO OPERATE NORMALLY. NOTED THAT THE SWITCH USED IS A 20-AMP SWITCH WHICH IS PROT ECTED BY A 20 AMP CIRCUIT BREAKER. 1 L 7 2 3O A25CE 1996121200660 19961212 00660 CE 1996 12 12 96ZZZX6007 1 19961107 G 2750 31B1642 TORQUE TUBE CESSNA 340 340A 2076405 CE FLAP ACTUATOR DAMAGE BY SEAL H A K NONE O OTHER IN INSP/MAINT 1 WP 17 6341X 3371 340A0510 CESSNA 340A, WITH ROBERTSON STOL KIT, NOW OWNED BY SIERRA INDUSTRIES, STC SA474NW. ALUMINUM FLAP ACTUATOR TORQUE TUBE F OUND NEARLY SEVERED BY A WORN PRESSURIZATION SEAL. DEFECT WAS ONLY FOUND BECAUSE OWNER REPORTED POOR PRESSURIZATION DIF FERENTIAL AND ALL FUSELAGE LEAKS WERE BEING CORRECTED. IT IS NOT VISIBLE WITHOUT DISASSEMBLY OF PARTS. FAILURE OF PART WOULD CERTAINLY RESULT IN ASYMMETRICAL FLAPS. SUBMITTER STATED TORQUE TUBE SHOULD HAVE A STAINLESS STEEL SLEEVE AS THE SOFT ALUMINUM TUBE WAS CUT BY STEEL IN THE SEAL. 1 L 7 2 3O 3A25 1996121200661 19961212 00661 SO 1996 12 12 96ZZZX6008 2 19961111 G 8520 646778 CONNECT ROD CESSNA 210 T210M 2073451 CE CONT O520 TSIO520R 17040 SO ENG FAILED G O OTHER E R K VIBRATION/BUFFET PARTIAL RPM/PWR LOSS FLUID LOSS CR CRUISE 1 WP 17 732LR 1633 21061601 512467 ENGINE OPERATED 233 HOURS OVER MFG RECOMMENDED OVERHAUL TIME OF 1400 HRS. REF SB NR M91-8, 10JULY91. CONNECTING ROD FA ILED IN NORMAL CRUISE AT 8,000 FEET ALTITUDE. ENGINE HAD A 100 HR INSPECTION WITHIN PREVIOUS 25 HRS OF OPERATION. COMP RESSION REPORTED 72/80 ALL CYLINDERS. NOTE: ENGINE HAD A PROP STRIKE IN EARLY LIFE. 1 H 7 1 3O 3 O 3A21 E8CE 1996121200662 19961212 00662 CE 1996 12 12 96ZZZX6009 1 19961107 G 5320 STRUCTURE CESSNA 340 340A 2076405 CE RT ENG SUPPORT CRACKED H S K NONE O OTHER IN INSP/MAINT 1 WP 17 6341X 4574 340A0510 INSP FOUND 1.5 INCH CRACK ON AIRFRAME STRUCTURE SUPPORTING RIGHT ENGINE AND TURBOCHARGER. CESSNA REPORTS THAT THEY HAVE NOT SEEN THIS PROBLEM ON 340'S, BUT THEY HAVE SEEN IT ON 400 SERIES. THIS AIRCRAFT HAS RAM ENGINES OF INCREASED HP/STR ESS. 1 L 7 2 3O 3A25 1996121200663 19961212 00663 SO 1996 12 12 96ZZZX6010 1 19961105 G 5730 6206102 SKIN PIPER PA28 PA28181 7102807 SO WING WALK PANEL CRACKED D A K NONE O OTHER IN INSP/MAINT 1 NM 11 8285Y 6248 288190023 ROUTINE 100 HR INSPECTION REVEALED MULTIPLE CRACKS ON THE BOTTOM OF THE FWD WING WALK PANEL. THESE CRACKS ARE FOUND AT THE INBD AND OTBD ENDS OF THE CORRUGATIONS STAMPED IN THE PANEL. THESE ARE QUITE DIFFICULT TO INSPECT VISUALLY, HOWEVER , USING YOUR HANDS, THE CRACKS CAN USUALLY BE FELT BY YOUR FINGERNAILS CATCHING ON THE EDGE OF THE CRACKS. SUBMITTER ST ATED THIS IS THE 6TH SUCH AIRCRAFT FOUND WITH THIS PROBLEM. ALL AIRCRAFT WERE USED IN FLIGHT TRAINING AND HAD APPROX 5, 000 HRS TTIS. SIMILAR CRACKS WERE ALSO FOUND IN THE AFT WING WALK PANEL. 1 L 7 1 3O 2A13 1996121200664 19961212 00664 SO 1996 12 12 96ZZZX6011 1 19961105 G 5730 6206104 SKIN PIPER PA28 PA28181 7102807 SO WING WALK PANEL CRACKED D K NONE O OTHER IN INSP/MAINT 1 NM 11 8285Y 6248 288190023 ROUTINE 100 HR INSPECTION REVEALED MULTIPLE CRACKS ON THE BOTTOM OF THE FWD WING WALK PANEL. THESE CRACKS ARE FOUND AT THE INBD AND OTBD ENDS OF THE CORRUGATIONS STAMPED IN THE PANEL. THESE ARE QUITE DIFFICULT TO INSPECT VISUALLY, HOWEVER , USING YOUR HANDS, THE CRACKS CAN USUALLY BE FELT BY YOUR FINGERNAILS CATCHING ON THE EDGE OF THE CRACKS. SUBMITTER ST ATED THIS IS THE 6TH SUCH AIRCRAFT FOUND WITH THIS PROBLEM. ALL AIRCRAFT WERE USED IN FLIGHT TRAINING AND HAD APPROX 5, 000 HRS TTIS. SIMILAR CRACKS WERE ALSO FOUND IN THE AFT WING WALK PANEL. 1 L 7 1 3O 2A13 1996121200665 19961212 00665 CE 1996 12 12 96ZZZX6012 1 19960901 G 3230 08421022 BELLCRANK IDLER CESSNA 320 320B 2074508 CE NLG FAILED D A O OTHER J WARNING INDICATION AP APPROACH 1 SW 99 99004 3677 320B0013 UPON LOWERING LANDING GEAR, BELLCRANK IDLER FAILED NOT ALLOWING NOSE GEAR TO EXTEND FULLY AND LOCK IN POSITION. SUSPECT CAUSE DUE TO METAL FATIGUE. 1 L 7 2 3O 3A25 1996121200666 19961212 00666 CE 1996 12 12 96ZZZX6013 1 19960919 G 3211 24411001 PIVOT CESSNA 172 172RG 2072438 CE RT MLG SPLINE CRACKED D A O OTHER O OTHER AP APPROACH 1 GL 09 9365D 2200 172RG1138 RIGHT LANDING GEAR FAILED TO EXTEND TO THE DOWN AND LOCKED POSITION. AFTER ATTEMPTS TO SECURE/ACTUATE TO SAFE DOWNLOCK POSITION FAILED, A SUCCESSFUL GEAR UP BELLY LANDING WAS MADE. PROPELLER AND BELLY SKIN DAMAGE RESULTED, NO INJURY TO FL IGHT CREW. INSPECTION REVEALED THE RT LANDING GEAR PIVOT ASSY HAD CRACKED IN THE SPLINE AREA NEXT TO THE INNER BEARING RACE RESULTING IN FAILURE OF THE RT GEAR TO ACTUATE TO THE DOWNLOCK POSITION. 981 HRS SINCE PART INSPECTED PER CESSNA S B SEB90-1. 1 H 7 1 3O 3A17 1996121200667 19961212 00667 SO 1996 12 12 96ZZZX6014 1 19961122 G 7160 BA6110 AIR FILTER BRACKETT MAULE M5 M5235C 5460135 SO INTAKE DEFECTIVE D K NONE W INADEQUATE Q C IN INSP/MAINT 1 AL 01 402X 99 7035C DURING ANNUAL INSPECTION, FOUND BRACKETT AIR FILTER WITH ALUMINUM SCREEN. AD 81-15-03 (EFFECTIVE 7-20-81) REQUIRED REPL ACEMENT OF ALUMINUM SCREEN. THIS ASSEMBLY WAS INSTALLED 5-6-87 (NEARLY 6 YEARS LATER). ACCORDING TO AD, NO ALUMINUM SC REENS WERE MADE AFTER AUGUST OF '78. SUBMITTER RECOMENDATION: REVISE AD TO INCLUDE ALL AIRCRAFT THIS FILITER ASSEMBLY IS NOW APPROVED FOR. 1984 CATALOG DOES NOT LIST IT AS APPROVED ON MAULE. ROTATE STOCK AND CHECK SHELF STOCK FOR AD COM PLIANCE. 1 H 7 1 3O 3A23 1996121200668 19961212 00668 SO 1996 12 12 96ZZZX6015 1 19961127 G 5751 6237201 BRACKET PIPER PA32 PA32300 7103212 SO LT AIL OB HINGE CRACKED D K NONE O OTHER IN INSP/MAINT 1 WP 21 2205U 3586 327940064 DURING ANNUAL INSPECTION, FOUND LEFT OUTER AILERON HINGE 'SPAR SIDE' BRACKET COMPLETELY CRACKED IN RADIUS AREA WHERE ATT ACHMENTS SCREWS ARE LOCATED. 1 L 7 1 3O A3SO 1996121800021 19961218 00021 SO 1996 12 18 96ZZZX6016 1 19961023 G 2730 2020302 TORQUE TUBE PIPER PA24 PA24250 7102404 SO ELEV RUSTED D K NONE O OTHER IN INSP/MAINT 1 SO 13 6996P 242139 REMOVED ELEV FROM STABILATOR TUBE FOR PAINTING AIRCRAFT. HAD TO REMOVE INSIDE BLOCK ASSY FIRST DUE TO ELEV WOULD NOT SL IDE OFF. ELEV WOULD NOT SLIDE OFF DUE TO RUST BUILD-UP ON STAB TUBE. SUSPECT CAUSE OF RUST BUILD-UP IS MOISTURE IN ELE V. SUBMITTER RECOMMENDS REMOVAL OF ELEV ONCE EVERY 2 YEARS FOR INSP AND CLEANING OF TUBES. 1 L 7 1 3O 1A15 1996121200669 19961212 00669 SO 1996 12 12 96ZZZX6017 1 19961127 G 7810 6366602 PIPE PIPER PA28 PA28140 7102802 SO NR 1 CYL EXH CRACKED G S O OTHER O OTHER CR CRUISE 1 GL 19 5677U 2346 2826474 PILOT HEARD NOISE DURING FLIGHT. AIRCRAFT LANDED WITHOUT INCIDENT. FOUND NR 1 CYLINDER EXHAUST PIPE CRACKED AROUND REI NFORCEMENT. 1 L 7 1 3O 2A13 1996121200670 19961212 00670 SO 1996 12 12 96ZZZX6018 1 19961115 G 5510 MS210694 NUTPLATE 5302042501 GULSTM AA5 AA5B 3960105 SO HORIZ STAB CRACKED B S A SL5R K NONE O OTHER IN INSP/MAINT 1 NE 03 74420 3388 AA5B0222 DURING REPAIR OF HORIZ STAB, FOUND STRUCTURAL NUTPLATES CRACKED THROUGH THREADS. NUTPLATES ARE USED TO ATTACH ELEVATOR HINGE BRACKETS AND FORWARD STAB SPAR TO FUSELAGE. THESE PARTS CANNOT BE SEEN DURING ROUTINE INSPECTIONS. ATTEMPTED TO REUSE ONE PREVIOUSLY UNCRACKED NUTPLATE WHICH CRACKED WHEN STANDARD TORQUE WAS APPLIED TO BOLT. INSTALLED ALL NEW NUTPL ATES AND TORQUES TO STANDARD TORQUE. SUBMITTER STATED FAILURE OF THESE NUTPLATES COULD LEAD TO LOSS OF ELEVATOR AND/OR HORIZ STABILIZER. 1 L 7 1 3O A16EA 1996121200671 19961212 00671 CE 1996 12 12 96ZZZX6019 1 19961121 G 3221 07436062 FORGING CESSNA 182 182P 2075816 CE NLG ATTACH CRACKED D S K NONE O OTHER IN INSP/MAINT 1 GL 19 8431Q 1547 18263546 DURING ANNUAL INSPECTION, CRACK WAS DISCOVERED IN LOWER NOSE FORGING OF NOSE GEAR. NO OTHER DEFECTS WERE FOUND IN LANDI NG GEAR. TTAF 1547. 1 H 7 1 3O NT TA13 1996020900312 19960209 00312 CE 1996 2 9 96ZZZX602 1 19960113 G 2810 07213032 CAP CESSNA 182 182C 2072708 CE FUEL TANK WATER LEAK H K NONE O OTHER IN INSP/MAINT 1 NM 01 8561T 52461 FUEL CAP LEAKED RAIN WATER THROUGH CAP WHICH HAS A BUILT-IN WATER TRAP. SUBMITTER RECOMMENDS REPLACEMENT OF CAP AND ADA PTER WITH DESIGN WHICH DOES NOT TRAP RAIN WATER. 1 H 7 1 3O NT 3A13 1996121200672 19961212 00672 EA 1996 12 12 96ZZZX6020 2 19961120 G 8530 PISTON PIPER PA60 PA60601P 7106012 NM LYC O540 IO540S1A5 41532 EA NR 2 CYL HOLE IN SIDE D E A ENGINE SHUTDOWN UNSCHED LANDING K FLUID LOSS NR NOT REPORTED 1 NE 03 771LB 61P059979632 L2086348A DURING TEST FLIGHT, A LARGE STREAM OF OIL, FROM OIL DOOR OF RIGHT ENGINE WAS NOTICED. SUBSEQUENTLY, ENGINE SHUT DOWN WA S PERFORMED AND AN UNEVENTFUL LANDING WAS MADE. TROUBLESHOOTING REVEALED A DIME SIZE HOLE IN NR 2 CYLINDER PISTON AND S IGNS OF SEVER DETONATION. CAUSE UNKNOWN. ENGINE WAS REMOVED FOR REPAIR/OVERHAUL. 1 M 7 2 3O 3 O RT A17WE 1E4 1996121200673 19961212 00673 1996 12 12 96ZZZX6021 1 19961127 G 3320 BAO80061 BALLAST BRUCE CABIN LIGHTS CABIN ODOR B L ZZBR A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 WP 11 LIGHTING BALLAST RETURNED TO MFG'R FOR INSPECTION FOLLOWING A REPORTED IN FLIGHT EMERGENCY LANDING DUE TO BURNING SMELL IN CABIN. AIR ONTARIO 303 REF BFM-96-11040. 1996121200674 19961212 00674 NE 1996 12 12 96ZZZX6022 3 19961017 G 6111 RFC11N16A BLADE PIN HAMSTD EMB 120 EMB120 3260201 SO HAMSTD 14RF 14RF9 NE PIN BOSS CRACKED B H2SR K NONE O OTHER IN INSP/MAINT 1 SO 13 17344 857677 BLADE WAS RECEIVED FROM THE OPERATOR WITH A REPORT OF CRACK INDICATED AT BLADE PIN BOSS. VISUAL EXAMINATION CONFIRMED A LINEAR INDICATION LOCATED AT THE RADIUS OF THE PIN BOSS-TO-BUTT AREA, APPROXIMATELY 1.300 INCHES IN LENGTH. THE INDICA TION ALSO EXTENDED SLIGHTLY INTO THE PLUG SEAL AREA, TO THE SNAP RING GLAND. 2 L 7 2 4T RT A31SO 6 C P11NE 1996121200675 19961212 00675 CE 1996 12 12 96ZZZX6023 1 19961119 G 3230 MS3567514 ROLL PIN CESSNA 500 500CESSNA 2076602 CE EMERG EXTENSION SHEARED B R2JR K NONE O OTHER IN INSP/MAINT 1 EA 21 153JP 5617 5000153 DURING PHASE INSPECTION LANDING GEAR EMERGENCY EXTENSION CHECK - BOTTLE WOULD NOT ACTUATE AND HANDLE WOULD NOT LOCK OUT. FOUND GROOVED PIN INSIDE EMERG GEAR HANDLE MECHANISM BROKEN. REPLACED PIN - SYSTEM RETESTED OK. SUBMITTER STATED FAI LURE WAS BELIEVED TO BE CAUSED BY IMPROPER RESET OF THE SYSTEM DURING MAINT AFTER SYSTEM ACTIVATION SEVERAL MONTHS EARLI ER. MM SHOULD BE CONSULTED. 1 L 7 2 4F A22CE 1996121200676 19961212 00676 CE 1996 12 12 96ZZZX6024 1 19961119 G 2721 556544067 TAB ROD CESSNA 500 500CESSNA 2076602 CE RUD TRIM CORRODED B A R2JR K NONE O OTHER IN INSP/MAINT 1 EA 21 153JP 5617 500153 FOUND RUDDER TRIM TAB ACTUATOR ROD CORRODED THROUGH DUE TO CORROSION. TUBE IS HOLLOW AND MAY HAVE CORRODED FROM THE INS IDE OUT. FOUND DURING LUBE REQUIREMENT OF PHASE 1 THROUGH 4 AIRFRAME INSPECTION. REPLACED WITH NEW PART. CLOSE INSPEC TION OF THIS AREA SUGGESTED. 1 L 7 2 4F A22CE 1996121200677 19961212 00677 CE 1996 12 12 96ZZZX6025 1 19961119 G 5711 552211210 SPAR CAP CESSNA 500 500CESSNA 2076602 CE RT WING CORRODED B A R2JR K NONE O OTHER IN INSP/MAINT 1 EA 21 153JP 5617 5000153 FOUND CORROSION ON RT WING SPAR FITTING INSIDE RT FUEL TANK WHILE C/W PHASE 50H INSPECTION AND SB 28-10 FOAM REMOVAL. C LEANED CORROSION TO .040 INCH DEPTH. REMOVED ALL PITTING. CONTRACTED FACTORY. MAJOR REPAIR REQUIRED EVEN THOUGH AREA OF CORROSION WAS LESS THAN 1 SQUARE INCH. STRAP HAD TO BE INSTALLED ON FORWARD FLANGE TO REINFORCE CORRODED AREA. SUBM ITTER STATED CAUSE OF CORROSION WAS DUE TO WATER CONTAINED AND TRAPPED IN FOAM COVERING THIS AREA. SUGGEST REMOVING FOA M AND CLOSE INSPECTION OF AREA FOR POWDERY CORROSION. 1 L 7 2 4F A22CE 1996121200678 19961212 00678 CE 1996 12 12 96ZZZX6026 1 19961117 G 2730 26315041 DRAW BOLT LEAR 35 35A 5170602 CE ELEV DOWN SPRING MISMFG D K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 07 388PD 630 ELEVATOR DRAW BOLT NEW FROM STOCK. FWD ATTACH HOLE WAS MEASURED .323 INCH PER DRAWING NR 2631504. THIS FWD HOLE SHOULD BE .316 (PLUS .004 INCH/MINUS .000 INCH). PART NOT MADE PER SPECS. COULD NOT USE THIS NEW PART. 2 L 7 2 4F A10CE 1996121200679 19961212 00679 CE 1996 12 12 96ZZZX6027 1 19961119 G 5754 55251411 SLAT CESSNA 501 501 2076603 CE LT WING CRACKED B R2JR K NONE O OTHER IN INSP/MAINT 1 EA 21 888MJ 7358 5010446 DURING PHASE 1 INSPECTION FOUND LT FLAP SLAT 552S141-1 CRACKED AT WELDS AT SEVERAL PLACES. NO SPARES AVAILABLE, HAD TO BE REMOVED FOR REPAIR BY MANUFACTURER DUE TO BEING MADE FROM MAGNESIUM ALLOY. SPECIAL ATTENTION NEEDS TO BE PAID TO THI S UNIT DURING PHASE 1 AND 2 INSPECTIONS. SLAT REPAIRED BY WELDING. 1 L 7 2 4F A27CE 1996121200680 19961212 00680 SW 1996 12 12 96ZZZX6028 1 19961112 G 2422 412075101103 INVERTER BELL 412 412EP 1182205 SW STATIC AC FAILED B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 6267J 10 36130 STATIC INVERTER FAILED. REPLACED WITH NEW STATIC INVERTER. 1 G 7 2 4U H4SW 1996121200681 19961212 00681 SW 1996 12 12 96ZZZX6029 1 19961112 G 6730 212076005105 CYLINDER BELL 412 412EP 1182205 SW SERVO SYS LEAKING B GS1R K NONE K FLUID LOSS IN INSP/MAINT 1 EA 03 6267J 14 HR9043 36130 SERVO LEAKING. REPLACED WITH NEW CYLINDER. 1 G 7 2 4U H4SW 1996121200682 19961212 00682 1996 12 12 96ZZZX6030 4 19961112 G 3410 7002353913 SENSOR BELL 412 412EP 1182205 SW AIR DATA FAILED B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 6266T 13 95111255 36124 AIR DATA SENSOR FAILED. REPLACED WITH NEW AIR DATA SENSOR. 1 G 7 2 4U H4SW 1996121200683 19961212 00683 1996 12 12 96ZZZX6031 4 19961112 G 3421 1113034 INDICATOR BELL 412 412EP 1182205 SW COCKPIT ATT STICKS B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 6266T 13 91871 36124 ATTITUDE INDICATOR STICKS IN PITCH. REPLACED WITH NEW ATTITUDE INDICATOR. 1 G 7 2 4U H4SW 1996121200686 19961212 00686 SW 1996 12 12 96ZZZX6034 1 19961112 G 7714 407365008103 INDICATOR BELL 407 407 SW DUAL TACH FAILED B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 407NA 55 0012 53012 INDICATOR FAILED. REPLACED WITH NEW DUAL TACH IND. 1 G 7 1 3U O H2SW 1996121200687 19961212 00687 SW 1996 12 12 96ZZZX6035 1 19961112 G 2844 407375007101 INDICATOR BELL 407 407 SW FUEL PRESS FAILED B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 6198V 13 0026 53020 INDICATOR FAILED. REPLACED WITH NEW FUEL PRESSURE IND. 1 G 7 1 3U O H2SW 1996121200688 19961212 00688 SW 1996 12 12 96ZZZX6036 1 19961112 G 6220 206011005015 COLLAR SET BELL 206 206L4 1182110 SW M/R MIS MFG B GS1R K NONE W INADEQUATE Q C IN INSP/MAINT 1 EA 03 62673 17 17 52176 INSP FOUND M/R COLLAR SET DEFECTIVE. REPLACED WITH NEW COLLAR SET. 1 G 7 1 3U NC H2SW 1996121200690 19961212 00690 SW 1996 12 12 96ZZZX6038 1 19961112 G 6220 222031662105 ROD END BEARING BELL 222 222U 1182140 SW M/R DEFECTIVE B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 911EC 256 0843 47505 INSP FOUND ROD END BEARING DEFECTIVE. REPLACED WITH NEW ROD END BEARING. 1 G 7 2 3U H9SW 1996020900314 19960209 00314 CE 1996 2 9 96ZZZX604 1 19960105 G 2710 CONTROL CABLE CESSNA 172 172M 2072418 CE RIGHT AILERON FAILED C A K NONE O OTHER IN INSP/MAINT 1 NE 01 21258 2220 17263917 ON NOVEMBER 11, 1995, AIRCRAFT EXPERIENCED WIND GUSTS AS HIGH AS 70 MPH FROM THE SOUTHEAST. THE AIRPLANE WAS TIED DOWN HEADING 330 DEGREES AND BOTH THE RUDDER GUST LOCK AND THE PIN IN THE YOKE WERE IN PLACE. THE NEXT DAY, THE RIGHT AILERO N WAS DROOPING SLIGHTLY AND UPON GRASPING IT, THERE WAS NO QUESTION OF A SERIOUS PROBLEM. UPON DISASSEMBLY, THE SHOP FO UND THE RIGHT AILERON CABLE BROKEN COMPLETELY. THERE WAS EVIDENCE OF CONSIDERABLE RUST WHERE THE CABLE RUNS OVER THE OV ERHEAD PULLEY AND IT IS PROBABLE SOME STRANDS OF THE CABLE WERE ALREADY BROKEN. IT ALSO APPEARED THE PULLEY ITSELF WAS FROZEN OR TURNED VERY HARD. EVERYTHING ON THE LEFT SIDE WAS OKAY. 1 H 7 1 3O NT 3A12 1996020900315 19960209 00315 NE 1996 2 9 96ZZZX605 2 19960115 G 7261 65B90115176 OIL TUBE BOEING 747 7472B4B 138481B NM PWA JT9 JT9D7J 52054 NE NR 1 ENG PRESS CRACKED H L A A E UNSCHED LANDING ENGINE SHUTDOWN K FLUID LOSS CR CRUISE 1 SW 99 202AE 21097 689476 AIRCRAFT EXPERIENCED HEAVY OIL LOSS ON NR 1 ENGINE 40 MINUTES AFTER TAKEOFF WHICH RESULTED IN NR 1 ENGINE IFSD AND ACFT AIR TURN BACK. UPON ACFT ARRIVAL, BEY GROUND INVESTIGATION REVEALED CRACKED NR 1 ENGINE DELTA PRESSURE SWITCH OIL TUBE. ITEM 150 REF: IPC 79 - 31 - 02 - 01, PAGE 1, NO EVIDENCE OF CHAFING OR INTERFERING. PIPE ASSY REPLACED AND ACFT RETU RNED TO SERVICE. 2 L 7 4 4F 4 F RT A20WE E20EA 1996020900316 19960209 00316 1996 2 9 96ZZZX606 4 19960108 G 3160 EFD871 MFD COLLINS BEECH MU300 400BEECH CE COCKPIT FAILED D P A K NONE O OTHER IN INSP/MAINT 1 NM 01 440DS 1152 369 RK8 FOUND MULTI-FUNCTION DISPLAY (MFD) FOR A 3-TUBE COLLINS SYSTEM, ON THE LEFT SIDE OF THE MFD, THE AIR INLET FOR COOLING I S 75 PERCENT OR MORE COVERED WITH LINT, DIRT, AND CARPET FIBERS. THE COOLING FANS OR EACH CRT IN THE COCKPIT DO NOT HAV E ANY KIND OF FILTER TO PREVENT THIS PROBLEM BEFORE REACHING THE UNITS. SUBMITTER STATED OPERATORS SHOULD CHECK THIS TO PREVENT OVERHEAT FAILURES. 2 H 7 2 4F RT A16SW 1996020900317 19960209 00317 CE 1996 2 9 96ZZZX607 1 19960122 G 2430 BD161 CONNECTOR ELCON CESSNA 500 S550 2076607 CE BATTERY CORRODED B CWQR K NONE O OTHER IN INSP/MAINT 1 GL 05 98QS 8667 S5500098 CREW REPORTED THEY COULD NOT BATTERY START ENGINE. FOUND BATTERY CONNECTOR CORRODED AND BURNED. REMOVED AND REPLACED E LCON CONNECTOR AND REPLACED BATTERY. CONNECTOR FAILED GO, NO-GO CHECK. LOOSE CONNECTOR CAUSED ARCING AND CORROSION. 1 L 7 2 4F RT A22CE 1996121900272 19961219 00272 CE 1996 12 19 96ZZZX6072 1 19961011 G 7160 1019100207 DOOR SEAL BEECH 200 B200 1152922 CE ICE VANE DOOR FAILED D K NONE O OTHER IN INSP/MAINT 1 GL 11 200PU 1117 BB1477 BRISTLE MATERIAL ON SIDE OF INLET COWLING THAT SEALS ICE DEFLECTOR DOOR CAME LOOSE FROM ITS RETAINER STRIP SENDING NYLON HAIRS TOWARD ENGINE INLET SCREEN. A LARGE VOLUME OF THE HAIRS WERE INJESTED BY THE ENGINE AND ENGINE WAS SPLIT AT THE 'C' FLANGE FOR INSPECTION AFTER THE OCCURRENCE. MELTED NYLON MATERIAL WAS FOUND IN ENGINE, BUT NO OTHER DAMAGE. 1 L 7 2 4T A24CE 1996121900274 19961219 00274 CE 1996 12 19 96ZZZX6074 1 19961121 G 5610 5042006930 WINDSHIELD PPG BEECH 90 C90 1152913 CE OUTER PANE CRACKED D O OTHER O OTHER CR CRUISE 1 CE 01 660GW 5005 84H10209 LJ673 WINDSHIELD OUTER HEATED PANE CRACKED. CAUSE: ICE BUILD-UP, PILOT SELECTED ELECT. HEAT ON, AND FULL WINDSHIELD DEFROST. OUTER PANE CRACKED FROM POSSIBLE OLD AGE, PRESSURE CYCLES, AND HEAT SHOCK DUE TO DIFFERENTIAL IN OAT AND HEAT APPLIED TO INSIDE. 1 L 7 2 3T 3A20 1996121900275 19961219 00275 NM 1996 12 19 96ZZZX6075 1 19961114 G 5313 STRINGER BOEING 727 727225 1384077 NM BS 940 18A LT CRACKED B XE4R K NONE O OTHER IN INSP/MAINT 1 SO 19 806MA 22437 FOUND 1.25 INCH CRACK IN STR 18A LT AT AFT LOWER ATTACH BOLT HOLE TO BS 940 FITTING. 2 L 7 3 4F A3WE 1996121900276 19961219 00276 NM 1996 12 19 96ZZZX6076 1 19961114 G 2782 69734941 SEAL PLATE 65447607 BOEING 737 7373B7 1384580 NM SLAT ACTUATOR DETERIORATED B IU6R K NONE K FLUID LOSS IN INSP/MAINT 1 NM 01 0240 SLAT ACTUATOR HAS BEEN IN REPAIR TWICE ON WARRANTY. BOTH TIMES SEAL PLATES WERE CA USING UNIT TO LEAK. 2 L 7 2 4F RT A16WE 1996121900277 19961219 00277 NM 1996 12 19 96ZZZX6077 1 19961114 G 2782 69734961 SEAL PLATE BOEING 737 7373B7 1384580 NM SLAT ACTUATOR DETERIORATED B IU6R K NONE K FLUID LOSS IN INSP/MAINT 1 NM 01 SLAT ACTUATOR HAS BEEN IN REPAIR TWICE ON WARRANTY. BOTH TIMES SEAL PLATES WERE CAUSING UNIT TO LEAK. 2 L 7 2 4F RT A16WE 1996121900278 19961219 00278 NM 1996 12 19 96ZZZX6078 1 19961112 G 2720 65448671 PISTON 65448617 BOEING 737 7372A6 138448B NM RUDDER PCU CHROME CHIPPED B L IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 777A THE CHROME PLATING ON THE CHAMFER IS CHIPPED OFF CAUSING CHROME PARTICLES TO FLOW THROUGHOUT THE INSIDE OF THE UNIT. TH IS WAS CAUSED WHEN THE FWD PISTON (FIG 1103 IT. 14) WAS TORQUED ONTO THE AFT PISTON AND THE CHROME ON THE CHAMFER CHIPPE D OFF DUE TO PRESSURE. RECOMMENDATION: HAVE ZERO CHROME RUN OUT ON CHAMFER WHEN RECHROMED. 2 L 7 2 4F A16WE 1996121900279 19961219 00279 GL 1996 12 19 96ZZZX6079 3 19961129 G 6114 C2835C23 HUB MCAULY 2A36C 2A36C23 GL NR 2 SOCKET CRACKED B ME4R K NONE O OTHER IN INSP/MAINT 1 SO 19 238 671575 PROPELLER RECEIVED FOR INSPECTION DUE TO RED DYE OIL LEAK. AD NOTE 89-26-08 WAS C/W. AFTER DISASSEMBLY, HUB WAS STRIPP ED AND A CRACK DISCOVERED IN NR 2 BLADE SOCKET, THREE THREADS IN 6 TO 7 O'CLOCK POSITION ABOUT .50 INCH LONG CRACK DISCO VERED USING A 10X POWER MICROSCOPE. 5 C P880 1996020900318 19960209 00318 NE 1996 2 9 96ZZZX608 2 19960122 G 7412 3033378A EXCITER LUCAS CESSNA 500 S550 2076607 CE PWA JT15 JT15D4 52112 NE LEFT IGNITION SHORTED B CWQR O OTHER O OTHER NR NOT REPORTED 1 GL 05 98QS 8667 K8951 S5500098 FLIGHT CREW REPORTED LEFT IGNITION CIRCUIT BREAKER TRIPS. DISCONNECTED UPPER IGNITION EXCITER BOX. CIRCUIT BREAKER STA YED IN AND OTHER EXCITER BOX CHECKED SATISFACTORY. REMOVED AND REPLACED. INTERNAL SHORT IN IGNITION EXCITER BOX. 1 L 7 2 4F 4 F RT A22CE E1NE 1996121900280 19961219 00280 EA 1996 12 19 96ZZZX6080 2 19961202 G 7414 ES10382681 CAPACITOR D3000 PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA LT MAG FAILED D K NONE R PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 SO 01 135JP 7952034 LT MAG CAPACITOR P/N ES10-382681, FAILED. FOUND CENTER THREADED PORTION LOOSE FROM OUTER PART. MAG DROP WAS 400 PLUS. NEW TCM 10-382681 FIXED IT. 1 L 7 2 3O 3 O A20SO E14EA 1996121900281 19961219 00281 SO 1996 12 19 96ZZZX6081 1 19961127 G 7120 6871000 MOUNT PIPER PA32 PA32300 7103212 SO LOW LT MT BRACE CRACKED D K NONE O OTHER IN INSP/MAINT 1 WP 21 2205U 3586 327940064 DURING ANNUAL INSPECTION FOUND LOWER LEFT ENGINE MOUNT BRACE CRACKED AT NOSE GEAR STRUT HOUSING WELD. 1 L 7 1 3O A3SO 1996121900282 19961219 00282 EA 1996 12 19 96ZZZX6082 2 19961122 G 8530 71894 VALVE SEAT PIPER PA31 PA31P 7103120 SO LYC O541 TIGO541E1A 41539 EA NR 5 CYL EXH LOOSE B EKIR K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 WP 07 252MA 31P33 L52162 ENGINE RUN-UP AND ROUGH. CHECKED COMPRESSION, FOUND NR 5 CYLINDER 0/80. REMOVED CYLINDER, FOUND EXHAUST VALVE SEAT LOO SE IN HEAD FOLLOWING VALVE DURING VALVE MOVEMENT. 1 L 7 2 3O 3 O A8EA E19EA 1996121900283 19961219 00283 SO 1996 12 19 96ZZZX6083 1 19961122 G 3211 6704213 TRUNNION FITTING PIPER PA44 PA44180 7104402 SO MLG RT AFT CRACKED B S YXUR K NONE O OTHER IN INSP/MAINT 1 WP 07 3062H 5861 447995165 FOUND CRACK ON 100-HR INSPECTION. 1 L 7 2 3O A19S0 1996121900284 19961219 00284 SO 1996 12 19 96ZZZX6084 1 19961116 G 2460 POWER BUSS PIPER PA34 PA34200T 7103406 SO AVIONICS MASTER LOOSE CONNECTION B HBKR K NONE O OTHER CR CRUISE 1 SW 11 33809 347570165 AVIONICS FAILED IN-FLIGHT. TROUBLESHOT AND FOUND SEVERAL BAD CONNECTIONS IN AVIONICS MASTER POWER BUSS. REPAIRED ALL O PEN CONNECTIONS. CHECKED GOOD. APPARENT PROBLEM WAS CORROSION ON CONNECTOR. 1 L 7 2 3O A7SO 1996121900285 19961219 00285 SO 1996 12 19 96ZZZX6085 1 19961106 G 3230 4179300 FORK ASSY PIPER PA31 PA31350 7103110 SO RT MLG DOWNLOCK BROKE D A A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 NM 01 3535F 317952200 UPON PILOT CYCLING GEAR UP, RT GEAR STAYED EXTENDED AND DOWN, GREEN LIGHT REMAINED ON. PILOT RETURNED AND LANDED WITH N O INCIDENT. UPON MAINT INSPECTION, RT GEAR DOWNLOCK ROD FORK WAS FOUND BROKEN. ROD FORK BOLT WAS NOT WORN AS IS A USUA L FINDING. MAINT. REMOVED THESE AT DETAILED GEAR INSPECTIONS TO CHECK WEAR. THIS SUMITTER BELIEVES FORK BOLT WAS OVERT ORQUED DURING INSTALLATION AND CRACKED AT THAT TIME. SUBMITTER RECOMMENDS ENSURING PROPER AMOUNT OF WASHERS ARE USED TO KEEP NUT FROM BOTTOMING OUT, AS WELL AS ENSURING THAT FORK WILL TURN FREELY WHEN INSTALLED. 1 L 7 2 3O A20SO 1996121900286 19961219 00286 SO 1996 12 19 96ZZZX6086 1 19961121 G 2822 2B663 PUMP PIPER PA31 PA31350 7103110 SO FUEL BOOST FAILED B APCR K NONE O OTHER IN INSP/MAINT 1 NM 01 36PB 2E79 317405128 BOOST PUMP INOPERATIVE. ELECTRIC MOTOR DOES NOT RUN. 1 L 7 2 3O A20SO 1996121900287 19961219 00287 SO 1996 12 19 96ZZZX6087 1 19961120 G 3710 442CW6 PUMP AIRBORNE PIPER PA34 PA34200T 7103406 SO PNEU SYS SEIZED B APCR K NONE O OTHER IN INSP/MAINT 1 NM 01 36319 540 8AK501 347870318 PUMP SEIZED AND DRIVE SHAFT BROKEN. 1 L 7 2 3O A7SO 1996121900288 19961219 00288 1996 12 19 96ZZZX6088 4 19961125 G 2350 COIL CORD PIPER PA31 PA31350 7103110 SO PILOT YOKE SET PARK BRAKE B A APCR K NONE O OTHER IN INSP/MAINT 1 NM 01 36PB 317405128 AIRCRAFT STUCK ON RUNWAY DUE TO 'LOCKED BRAKES' ON TWO FLIGHTS. MAINTENANCE FOUND NO DEFECTS IN BRAKE SYSTEMS. FOUND P USH TO TALK COIL CORD FROM PILOT'S YOKE WOULD WRAP AROUND PARKING BRAKE 'T' HANDLE AND ENGAGE PARKING BRAKE WHEN YOKE PU LLED AFT. 1 L 7 2 3O A20SO 1996121900289 19961219 00289 EA 1996 12 19 96ZZZX6089 2 19961109 G 8530 73806 PUSH ROD PIPER PA38 PA38112 7103812 SO LYC O235 O235L2C 41505 EA NR 1 CYL INT BENT D P A UNSCHED LANDING E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CR CRUISE 1 SW 15 38PT 3616 3878A0042 L1533715 PILOT NOTED A SUDDEN ROUGHNESS IN THE ENGINE FOLLOWED BY A 200-300 RPM LOSS. MADE A SAFE EMERGENCY LANDING. DISPATCHED A MECHANIC TO DETERMINE CAUSE. THE INTAKE PUSHROD AND TUBE WERE SEVERELY BENT. THE LOWER SPARK PLUG WAS BADLY LEAD FO ULED. SUSPECT CAUSE WAS DETERMINED TO BE EITHER DETONATION OR THE INTAKE VALVE STICKING MOMENTARILY. THE ENGINE WAS RE MOVED FOR OVERHAUL. 1 L 7 1 3O 3 O A18SO E223 1996121900290 19961219 00290 SO 1996 12 19 96ZZZX6090 1 19961120 G 3710 2H2211 REGULATOR PIPER PA31 PA31350 7103110 SO PNEU SYS LEAKING B APCR K NONE O OTHER IN INSP/MAINT 1 NM 01 40ST 7E911 317405183 PNEUMATIC REGULATOR LEAKS BADLY AT LOW PRESSURE SIDE. KEEPS PNEUMATIC SYSTEM FROM DEVELOPING PRESSURE. 1 L 7 2 3O A20SO 1996121900291 19961219 00291 SO 1996 12 19 96ZZZX6091 1 19961120 G 3710 441CC7 PUMP PIPER PA34 PA34200T 7103406 SO LT ENG PNEU SEIZED B APCR O OTHER O OTHER CR CRUISE 1 NM 01 4490F 571 10AK759 347670339 LEFT ENGINE PNEUMATIC PUMP SEIZED AND FAILED DURING PNEUMATIC DE-ICE OPERATION DURING IFR/ICING CONDITIONS. 1 L 7 2 3O A7SO 1996121900292 19961219 00292 1996 12 19 96ZZZX6092 3 19961204 G 6112 RA12884 DEICE BOOT RAPCO BEECH 80 65A80 1152808 CE PROP WIRES BREAK D S K NONE O OTHER IN INSP/MAINT 1 GL 15 55SA LD243 PROP DE-ICE BOOT OTB, INB, AND GRD WIRES BREAK 12 INCHES FROM THE TERMINALS. THE LEAD IS REQUIRED TO BEND IN THIS AREA. THIS IS THE 8TH BOOT WHICH HAS FAILED IN THIS AREA IN THE LAST TWO WEEKS. 1 L 7 2 3O 3A20 1996121900293 19961219 00293 CE 1996 12 19 96ZZZX6093 1 19961120 G 3230 20430156 BOLT CESSNA 177 177RG 2073709 CE DRAG LINK BROKEN B S MZER K NONE O OTHER IN INSP/MAINT 1 GL 15 53257 177RG1363 INSP FOUND DRAG LINK ASSY BOLT BROKEN. 1 H 7 1 3O A20CE 1996121900294 19961219 00294 SO 1996 12 19 96ZZZX6094 1 19960831 G 3230 2572000 GEAR EXTENSION PIPER PA24 PA24250 7102404 SO MLG MOTOR FAILED D O OTHER J WARNING INDICATION AP APPROACH 1 NM 11 5909P 24995 THE LANDING GEAR WOULD NOT FULLY EXTEND OR RETRACT WITH THE ELECTRICAL SYSTEM. THE EMERGENCY SYSTEM WAS ACTUATED AND DI D NOT EXTEND THE GEAR. IT WAS DETERMINED THE LANDING GEAR MOTOR FAILED TO FUNCTION UNDER THE LOAD REQUIRED TO ACTUATE T HE GEAR. AFTER EXTENSIVE INSP AND OPERATION OF THE EMERGENCY GEAR SYSTEM, IT WAS UNDETERMINED AS TO WHY THE GEAR FAILED TO EXTEND. IT IS SPECULATED EMERGENCY GEAR EXT WAS ACTUATED WITH THE GEAR PARTIALLY EXTENDED. THIS IS BASED ON THE FA CT WHEN THE AIRCRAFT WAS JACKED FOR RECOVERY, THE LINKAGE WAS RELEASED BY THE MECHANIC AND THE GEAR EXTENDED FULLY. 1 L 7 1 3O 1A15 1996121900295 19961219 00295 EA 1996 12 19 96ZZZX6095 1 19961202 G 3230 555402 SELECTOR VALVE CNDAIR CL600 CL6002A12 1900304 EA NLG MALFUNCTION C K NONE O OTHER NR NOT REPORTED 1 SW 05 601TX 303 3005 THE NOSE GEAR SELECTOR VALVE FAILS ON THE RETRACT MODE. IF IT FAILS AFTER THE GEAR HAS ALREADY EXT., THE ONLY SYMPTOM I S A LOSS OF NOSE STEERING. NOSE STEERI NG CAN BE MEL'D. IF THE AIRCRAFT DISPATCHES PER THE MEL, THE NOSE GEAR WILL RET RACT, BUT WILL NOT EXTEND NORMALLY. A MANUAL FREE FALL WOULD HAVE TO BE PERFORMED. 2 L 7 2 4F RT A21EA 1996121900296 19961219 00296 CE 1996 12 19 96ZZZX6096 1 19961113 G 3211 24411001 FITTING CESSNA 172 172RG 2072438 CE MLG CRACKED G K NONE O OTHER IN INSP/MAINT 1 GL 19 6352V 172RG0640 DURING 100 HR INSPECTION, MECHANIC NOTICED PAINT MISSING FROM AROUND AREA THAT ALUMINUM CASTING (FITTING, AXLE) ATTACHES TO MAIN GEAR LEG - CLOSER INSPECTION OF THIS AREA REVEALED CRACK RUNNING FROM TOP OF CASTING DOWN TO ATTACH BOLT HOLE. ZYGLO FOUND DEFINITE CRACK COMPLETELY THROUGH CASTING. AIRCRAFT IS TRAINING AIRCRAFT AND PART AFFECTED IS BELIEVED TO BE ORIGINAL PART. 1 H 7 1 3O 3A17 1996121900297 19961219 00297 SO 1996 12 19 96ZZZX6097 2 19961126 G 7314 6462108 PUMP CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO RT ENG FUEL FAILED B A FE6R O OTHER Y ENGINE STOPPAGE TO TAKEOFF 1 NM 11 7011X J20902513 402C0255 L290329R ON TAKEOFF ROLL, THE RIGHT ENGINE QUIT. THE PILOT MADE REJECTED TAKEOFF PROCEDURES. NO DAMAGE TO A/C OR PERSONAL. INVE STIGATION SHOWED THE ENG DRIVEN PUMP FAILED. A TEAR DOWN INSPECTION REVEALED SOME WEAR AND TWO BROKEN BLADES. NO CONCL USIONS WERE DRAWN ON THE CAUSE FOR FAILURE. THERE WERE NO INDICATIONS PRIOR TO FAILURE. 1 L 7 2 3O 3 O A7CE E8CE 1996121900298 19961219 00298 EA 1996 12 19 96ZZZX6098 2 19961024 G 8520 74644 ROD BOLT PIPER PA25 PA25235 7102504 SO LYC O540 O540B2B5 41532 EA NR 4 CYL STRIPPED D K NONE O OTHER IN INSP/MAINT 1 GL 15 7545Z 51 253591 L988640 ROD BOLT APPEARS TO BE TOO SOFT. THREADS STRIPPED CAUSING NR 4 CONNECTING ROD CAP TO COME LOOSE MAKING CONTACT WITH CAS E AND NR 3 PISTON. THIS CAUSED MAJOR DAMAGE TO ENGINE. 1 L 7 1 3O 3 O 2A10 E295 1996121900299 19961219 00299 EA 1996 12 19 96ZZZX6099 2 19961122 G 8520 75637 COUNTER WEIGHT PIPER PA31 PA31P 7103120 SO LYC O541 TIGO541E1A 41539 EA NR 5 CYL CRACKED B EKIR K NONE O OTHER IN INSP/MAINT 1 WP 07 252MA 641 75670 31P33 L52162 PULLED SUCTION SCREEN FOLLOWING OIL CHANGE, FOUND BROKEN PIECE OF SNAP RING, P/N 71906. REMOVED SUMP, FOUND COUNTER WT NR 5 SNAP RING AFT SIDE INBOARD BROKE AND COUNTER WT CRACKED AT BUSHING HOLE. SCREEN WAS PULLED FOLLOWING FAILURE OF NR 5 CYL (DROPPED EXHAUST VALVE SEAT). 1 L 7 2 3O 3 O A8EA E19EA 1996121900300 19961219 00300 SO 1996 12 19 96ZZZX6100 2 19961121 G 7322 63357310 FUEL CONTROL CESSNA 404 404CESSNA 2075901 CE CONT O520 GTSIO520M 17032 SO RT ENG MIX DEFECTIVE B APCR O OTHER R PARTIAL RPM/PWR LOSS TO TAKEOFF 1 NM 01 48SA 706 G119402AR 4040417 276387R PILOT REPORTED ENGINE STUMBLE ON TAKEOFF AND AT CLIMB POWER SETTING. EXTENSIVE TROUBLESHOOTING FOUND LOOSE BUSHING AT R IGHT ENGINE. MIXTURE CONTROL SHAFT INSTALLED USED SERVICEABLE FUEL CONTROL ASSY. TEST FLOWN OK. 1 L 7 2 3O 3 O A25CE E7CE 1996121900301 19961219 00301 CE 1996 12 19 96ZZZX6101 1 19961023 G 5320 521304029 TEE STRUCTURE CESSNA 441 441 2076020 CE NLG TUNNEL CRACKED B A DJFR K NONE O OTHER IN INSP/MAINT 1 EA 23 489CE 4902 4410027 NOSE GEAR TUNNEL FORWARD SUPPORT 'TEE' WAS FOUND CRACKED IN THE RADIUS OF THE 'TEE' STRUCTURE. THIS IS THE THIRD CRACKE D 'TEE' THAT HAS BEEN FOUND ON THIS TYPE OF AIRCRAFT. SUSPECT GROUND HANDLING MAY CONTRIBUTE TO CAUSE. INSPECT ANYTIME NOSE BAY FLOORS ARE REMOVED. 1 L 7 2 3T RT A28CE 1996121900302 19961219 00302 SO 1996 12 19 96ZZZX6102 2 19961202 G 7310 6343264 MANIFOLD CESSNA 340 340CESSNA 2076404 CE CONT O520 TSIO520NB 17040 SO ENG FUEL CLOGGED B AM2R K NONE O OTHER IN INSP/MAINT 1 SW 15 69520 20 A167532C 3400353 311659 FUEL MANIFOLD WAS ONLY ABLE TO SUPPLY FUEL TO 3 OF THE ENGINES CYLINDER. THREE OF THE FUEL LINES WERE CLOGGED. THE MAN IFOLD HAD LESS THAN 20 HRS SINCE OVERHAUL. 1 L 7 2 3O 3 O 3A25 E8CE 1996121900303 19961219 00303 1996 12 19 96ZZZX6103 4 19961121 G 3418 C522074 LIFT DETECTOR SAFEFLIGHT PIPER PA31 PA31350 7103110 SO RT WING SWITCH WATER CONTAM B APCR O OTHER N FALSE WARNING NR NOT REPORTED 1 NM 01 777KT 330937 317552053 STALL VANE/LIFT DETECTOR GAVE COUNTINUOUS STALL WARNING DUE TO WATER ENTRY INTO SWITCH. 2ND FAILURE. OPERATOR HAS NUME ROUS FAILURES OF SAME TYPE VANES WHENEVER AIRCRAFT FLY IN RAIN. SUBMITTER STATED UNITS NEED TO BE WATERPROOFED. VERY D ANGEROUS FAILURE MODE, AS PILOT'S MUST PULL CIRCUIT BREAKER TO SHUT OFF STALL HORN, WHICH LEAVES THEM NO STALL WARNING A T ALL. 1 L 7 2 3O A20SO 1996121900304 19961219 00304 1996 12 19 96ZZZX6104 4 19961120 G 3418 C522074 LIFT DETECTOR SAFEFLIGHT PIPER PA31 PA31350 7103110 SO RT WING SWITCH WATER CONTAM B APCR K NONE O OTHER NR NOT REPORTED 1 NM 01 777KT 317552053 STALL VANE/LIFT DETECTOR GAVE CONTINUOUS STALL WARNING DUE TO WATER ENTRY INTO SWITCH. SUBMITTER STATED OPERATOR HAS NU MEROUS FAILURES OF SAME TYPE UNITS WHENEVER IT RAINS. UNITS NEED TO BE WATERPROOFED. 1ST FAILURE. 1 L 7 2 3O A20SO 1996121900305 19961219 00305 SO 1996 12 19 96ZZZX6105 1 19961119 G 3230 NOSE GEAR PIPER PA34 PA34200T 7103406 SO NLG WELL FROZEN B A APCR O OTHER O OTHER NR NOT REPORTED 1 NM 01 8407C 15429 347670137 AIRCRAFT DEPARTED BOEING FIELD WITH SNOW ON TAXIWAY AND RUNWAY. SNOW SLUSH ENTERED NOSE WHEEL WELL AND FROZE GEAR IN 'U P' POSITION. AIRCRAFT LANDED ON RUNWAY WITH MAINS DOWN AND NOSE GEAR UP. MODERATE DAMAGE TO NOSE CONE FROM RUNWAY CONT ACT. 1 L 7 2 3O A7SO 1996121900306 19961219 00306 SO 1996 12 19 96ZZZX6106 1 19961120 G 2434 ALX9425 ALTERNATOR PRESTOLITE PIPER PA34 PA34200T 7103406 SO DRIVE END CASE CRACKED B S APCR K NONE O OTHER IN INSP/MAINT 1 NM 01 8407C 49 A112746 347670137 ALTERNATOR REMOVED DUE TO DEFECTIVE DIODES, BUT ALSO FOUND CRACK IN CASE AT DRIVE END. 1 L 7 2 3O A7SO 1996121900307 19961219 00307 SO 1996 12 19 96ZZZX6107 2 19961112 G 8520 CONNECT ROD CESSNA 310 310Q 2074242 CE CONT O470 IO470VO 17026 SO NR 5-6 CYL FAILED D E A ENGINE SHUTDOWN UNSCHED LANDING B J SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CL CLIMB 1 SO 03 7700Q 1180 310Q0410 L149140VO AFTER DEPARTURE, OIL PRESSURE ON RIGHT ENGINE DROPPED. ENGINE BEGAN TO SMOKE POSSIBLE BLEED OIL FIRE AND SMOKE WERE NOT ED. ENGINE WAS SHUT DOWN AND FEATHERED. NORMAL LANDING WAS MADE. DAMAGE TO AIRCRAFT RESTRICTED TO ENGINE AND PROP. F IRST INSPECTION REVEALED NR 6 AND NR 5 RODS BROKEN WITH A PORTION OF BOTH CASE HALVES EJECTED FROM THE TOP OF THE MOTOR. PROP HAS SEVERAL NICKS POSSIBLY CAUSED BY EJECTED MATERIAL. 1 L 7 2 3O 3 O 3A10 3E1 1996121900308 19961219 00308 CE 1996 12 19 96ZZZX6108 1 19961119 G 7120 255100317 MOUNT CESSNA 303 T303 2073820 CE RT ENG CORRODED B A FE6R K NONE O OTHER IN INSP/MAINT 1 NM 11 727RT 1413 T30300090 FOUND SEVERE CORROSION ON THE ENGINE MOUNT, BELOW THE ENGINE SUPERCHARGER, ON THE RIGHT ENGINE. THE ENGINE MOUNT HAS BE EN PREVIOUSLY REPAIRED, WITH A FISHMOUTH REINFORCEMENT, FOR PRESUMABLY THE SAME PROBLEM. THE LEFT ENGINE MOUNT HAS THE SAME PROBLEM BUT IS NOT AS SEVERE. CORROSION AND RUST HAVE PENETRATED THE REPAIR. THE ENGINE MOUNT IS AGAIN REPAIRED B UT BY REPLACEMENT OF ENTIRE TUBE SECTIONS. MOST INSTALLATIONS OF THIS TYPE HAVE A HEAT SHIELD INSTALLED. 1 L 7 2 3O A34CE 1996121900341 19961219 00341 NM 1996 12 19 96ZZZX6109 1 19961202 G 3320 BR63031021 LUMINAIRE BRUCE DHAV DHC8 DHC8102 2809003 NM CABIN BURN DAMAGE B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 934HA 139 PIEDMONT AIRLINES RETURNED LIGHTING UNIT FOR ARCING AND BURN DAMAGE AT LAMP HOLDER. 2 H 7 2 4T RT A13NM 1996020900627 19960209 00627 WP 1996 2 9 96ZZZX611 1 19960119 G 6220 369H120321 LEAD LAG LINK HUGHES 369 369D 4470706 WP M/R CRACKED B MMZR K NONE O OTHER IN INSP/MAINT 1 GL 05 88SE 2027 1888 800775D INSPECTION FOUND BUSHING LOOSE AND CRACK IN LEAD LAG LINK ORIGINATING FROM BUSHING. 1 G 7 1 3U H3WE 1996121900744 19961219 00744 EU 1996 12 19 96ZZZX6110 1 19960819 G 5720 21211151102 STIFFENER CASA C212 C212CC 2410204 EU WING FALSE SPAR CRACKED B ST9R K NONE O OTHER IN INSP/MAINT 1 SO 15 349TA 3244 349 INSP FOUND STIFFENERS LOCATED ON REAR FALSE SPAR CRACKED. REFERENCE CASA COM LETTER 212-224. 2 H 7 2 4T A43EU 1996121900745 19961219 00745 EU 1996 12 19 96ZZZX6111 1 19960819 G 5720 21211151142 STIFFENER CASA C212 C212CC 2410204 EU WING FALSE SPAR CRACKED B ST9R K NONE O OTHER IN INSP/MAINT 1 SO 15 349TA 3244 349 INSP FOUND STIFFENERS LOCATED ON REAR FALSE SPAR CRACKED. REFERENCE CASA COM LETTER 212-224. 2 H 7 2 4T A43EU 1996121900746 19961219 00746 EU 1996 12 19 96ZZZX6112 1 19960819 G 5720 21211151122 STIFFENER CASA C212 C212CC 2410204 EU WING FALSE SPAR CRACKED B ST9R K NONE O OTHER IN INSP/MAINT 1 SO 15 349TA 3244 349 INSP FOUND STIFFENERS LOCATED ON REAR FALSE SPAR CRACKED. REFERENCE CASA COM LETTER 212-224. 2 H 7 2 4T A43EU 1996121900747 19961219 00747 EU 1996 12 19 96ZZZX6113 1 19960819 G 5720 21211151112 STIFFENER CASA C212 C212CC 2410204 EU WING FALSE SPAR CRACKED B ST9R K NONE O OTHER IN INSP/MAINT 1 SO 15 349TA 3244 349 INSP FOUND STIFFENERS LOCATED ON REAR FALSE SPAR CRACKED. REFERENCE CASA COM LETTER 212-224. 2 H 7 2 4T A43EU 1996121900748 19961219 00748 EU 1996 12 19 96ZZZX6114 1 19960819 G 5720 21211151062 STIFFENER CASA C212 C212CC 2410204 EU WING FALSE SPAR CRACKED B ST9R K NONE O OTHER IN INSP/MAINT 1 SO 15 349TA 3244 349 INSP FOUND STIFFENERS LOCATED ON REAR FALSE SPAR CRACKED. REFERENCE CASA COM LETTER 212-224. 2 H 7 2 4T A43EU 1996121900749 19961219 00749 EU 1996 12 19 96ZZZX6115 1 19960819 G 5720 21211151072 STIFFENER CASA C212 C212CC 2410204 EU WING FALSE SPAR CRACKED B ST9R K NONE O OTHER IN INSP/MAINT 1 SO 15 349TA 3244 349 INSP FOUND STIFFENERS LOCATED ON REAR FALSE SPAR CRACKED. REFERENCE CASA COM LETTER 212-224. 2 H 7 2 4T A43EU 1996121900750 19961219 00750 SW 1996 12 19 96ZZZX6116 1 19961112 G 7712 430375009101 INDICATOR BELL 430 430 1182150 SW TRIPLE TORQ FAILED B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 6283T 21 E006 49007 INDICATOR FAILED. REPLACED WITH NEW TRIPLE TORQUE IND. 1 G 7 2 3U RT H9SW 1996121900752 19961219 00752 EA 1996 12 19 96ZZZX6118 1 19961114 G 3320 2927300 CAPACITOR BRUCE BR95005 CNDAIR CL600 CL6002B19 EA CABIN FAILED B L ZZBR K NONE B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 WP 11 411SW 7067 BALLAST UNIT RECEIVED FOR INSP FOLLOWING REPORT OF CABIN SMOKE. FOUND CAPACITOR C1 FAILED. 2 L 7 2 4F RT A21EA 1996121900753 19961219 00753 SO 1996 12 19 96ZZZX6119 1 19961202 G 3320 BC10047005 LUMINAIRE BRUCE BR99002 EMB 120 EMB120ER 3260203 SO LAMP HOLDER BURN DAMAGE B ZZBR K NONE O OTHER IN INSP/MAINT 1 WP 11 214SW 120280 ULTRALIGHT LIGHTING SYSTEM FROM SKYWEST RETURNED FOR 'BROKEN END'. BURN DAMAGE AT LAMP HOLDER NOTED AT INITIAL INSP. 2 L 7 2 4T RT A31SO 1996020900628 19960209 00628 WP 1996 2 9 96ZZZX612 1 19960117 G 6210 369D21100516 BLADE HUGHES 369 369D 4470706 WP M/R DELAMINATED B EOOR K NONE O OTHER IN INSP/MAINT 1 AL 03 5313Y 596 2022226095 490496D DURING ANNUAL INSPECTION, FOUND M/R BLADE WAS DELAMINATED UNDER THE ABRASION STRIP ON THE UPPER SURFACE OF THE BLADE FOR ABOUT 6 SQUARE INCHES. BLADE REMOVED AND SENT IN FOR REPAIR. 1 G 7 1 3U H3WE 1996121900754 19961219 00754 SW 1996 12 19 96ZZZX6120 1 19961101 G 7120 2762114083 MOUNT SWRNGN SA227 SA227AC 8780603 SW ENG TRUSS CRACKED B A H7NR K NONE O OTHER IN INSP/MAINT 1 SW 17 407012 CRACK IN THE TUBE P/N 27-62114-021 WHERE IT IS MATED TO TUBES P/N 27-62114-019 AND 27-62114-023. THIS IS WHERE PLATE 27 -62114-073/074 IS ATTACHED. THE TUBES UNDER THE PLATE ATTACH POINT ARE NOT WELDED. SUBMITTER BELIEVES THESE TUBES NOT BEING WELDED ALLOW FLEX THAT LEADS TO CRACKS. 2 L 7 2 4T RT A8SW 1996121900755 19961219 00755 SW 1996 12 19 96ZZZX6121 1 19961211 G 5753 652513020 FLAP GULSTM 560 560 0141402 SW RT INBD SKIN SEPARATED D A A UNSCHED LANDING D INFLIGHT SEPARATION CR CRUISE 1 SO 06 1217V 38160 5600001 ON FIRST FLIGHT AFTER AIRCRAFT WAS REPAINTED, AT AN ALTITUDE OF 15,000 FEET, RIGHT INBOARD FLAP SKIN SEPARATED INTERNALL Y FROM THE FLAP RIBS. AIRCRAFT MADE EMERGENCY LANDING AT RIC. INVESTIGATION REVEALED VENT HOLES IN FLAP WERE CLOGGED W ITH FOREIGN MATTER WHICH WOULD HAVE PREVENTED THE FLAP FROM VENTING EXCESS PRESSURE. CESSNA M/M 56MM064F SECTION 20-330 0, PAGE 704, ADDRESS THIS SUBJECT. 1 H 7 2 3O 6A1 1996121900756 19961219 00756 NE 1996 12 19 96ZZZX6122 2 19961211 G 7270 5757513501 DUCT DOUG DC8 DC862 3021970 WP PWA JT3D JT3D7 52039 NE FAN BYPASS FAILED B UMXR K NONE O OTHER NR NOT REPORTED 1 SO 19 1808E 130 46105 FAILURE OF DUCT, P/N 5757513-501, CAUSED BY COMPRESSOR STALL/SURGE. REPORT ON FILE AT REPAIR STATION UMXR629L. 2 L 7 4 4F 4 F 4A25 1E8 1996121900757 19961219 00757 CE 1996 12 19 96ZZZX6123 1 19961203 G 2910 2607003453 LINE LEAR 35 35A 5170602 CE LT HYD PUMP CHAFED D K NONE O OTHER IN INSP/MAINT 1 WP 23 510SG 4806 268 LT PUMP HYD LINE WAS WORN THROUGH BY SCREW IN ELECTRICAL WIRE BUNDLE ON ENGINE BEAM. SUSPECT CAUSE, WIRING WAS PROBABLY UNCLAMPED FOR ACCESS TO EITHER FIRE BOTTLE OR 3-WAY VALVE AND UPON INSTALLATION, WIRING WAS ROUTED TOO CLOSE TO HYD PIP E. SUBMITTER STATED TO PREVENT: CLOSER INSPECTION SHOULD BE MADE ON INSTALLATION OF WIRING AFTER WIRE MOVEMENT. 2 L 7 2 4F A10CE 1996121900758 19961219 00758 CE 1996 12 19 96ZZZX6124 1 19961202 G 5712 017A12054 RIB MTSBSI MU2 MU2B60 5780460 CE RT WING OUTER CRACKED E K NONE O OTHER IN INSP/MAINT 1 SO 03 941S 738SA DISCOVERED BY CREW DURING POST-FLIGHT INSP, CAUSE AT THIS TIME IS UNDETERMINED. BOTH OUTER RIBS CRACKED, ON RT WING. 1 H 7 2 3T RT A10SW 1996121900759 19961219 00759 CE 1996 12 19 96ZZZX6125 1 19961202 G 5712 017A127046 RIB MTSBSI MU2 MU2B60 5780460 CE RT WING OUTER CRACKED E K NONE O OTHER IN INSP/MAINT 1 SO 03 941S 738SA DISCOVERED BY CREW DURING POST-FLIGHT INSP, CAUSE AT THIS TIME IS UNDETERMINED. BOTH OUTER RIBS CRACKED, ON RT WING. 1 H 7 2 3T RT A10SW 1996121900760 19961219 00760 NE 1996 12 19 96ZZZX6126 2 19961111 G 7230 793015 DISC BOEING 747 747136 1384883 NM PWA JT9 JT9D7 52054 NE STAGE 15 HPC CRACKED H S K NONE O OTHER IN INSP/MAINT 1 SW 99 79240 B85733 685824 DISC HAS .1875 INCH LONG CIRCUMFERENTIAL CRACK IN FRONT SNAP DIAMETER (I.E. IN AN UNUSUAL LOCATION NOT PREDICTED BY ASB 4908). PART CYCLES, 9,092. 2 L 7 4 4F 4 F A20WE E20EA 1996121900761 19961219 00761 NE 1996 12 19 96ZZZX6127 2 19961013 G 7510 7958591503 DUCT 13277503 DOUG MD88 MD88 3023688 NM PWA JT8 JT8D219 52053 NE NR 2 ENG AI B NUT LOOSE H A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 SW 99 12FQ 15021 49766 718244 AFTER TAKEOFF, PILOT REPORTED NR 2 ENGINE OVERHEAT LIGHTS CAME ON ONE AFTER THE OTHER. AIRCRAFT LEVELED OFF. NR 2 THRO TTLE RETARDED AND OVERHEAT CONDITION DISAPPEARED. AIRCRAFT RETURNED TO DEPARTING AIRPORT AND NORMAL LANDING PERFORMED. INSPECTION REVEALED THAT NOSE COWL ANTI-ICE DUCT'S FORWARD ATTACH B-NUT DESINTEGRATED CAUSING 13TH STAGE BLEED AIR TO H EAT UP THE 'A' AND 'B' LOOPS. MDC S/N 3061 NOT C/W AT THE TIME OF INCIDENT. 2 L 7 2 4F 4 F RT A6WE E9NE 1996121900763 19961219 00763 EU 1996 12 19 96ZZZX6128 1 19961030 G 7700 CONNECTOR BAC 146 AVRO146RJ100 1500096 EU ENG 1,2,3,4 DIRTY W ANCF A UNSCHED LANDING E VIBRATION/BUFFET CR CRUISE 1 SO 23 504MM E3221 45 MIN AFTER T/O FROM SKBO AT FL 280. VIBRATION FOR ENG NR 3 SHOWED 2.0 WITH MWS CALL OUT. SOON AFTER ENG 1 SHOWED 1.3 VIBR, ENG 2 AND 4 SHOWED 1.4. ALSO, ALL ENG TEMP SHOWED ZERO, AND ALL ENG OIL PRESS IND SHOWED FULL SCALE. INDICATION PROBLEM SUSPECTED. DIVERTED TO AND LANDED AT SKBO. INSPECTED OIL SYSTEM PER SB 19-5. FLUSHED OIL SYSTEM ALL ENGINES. CHANGED OIL FILTER ALL ENGINES. TEST ON GROUND OK. CHANGED VIBRATION UNIT, NO HELP. CLEANED CONNECTORS OF ENG AND C HECKED WIRING IAW AMM. ENGINES RUN-UP IN T/O POWER, WITH PUMPS AND GENERATOR ON, ALL PARAMETERS OK AND IN LIMITS. 2 H 7 4 4F RT A49EU 1996121900764 19961219 00764 EU 1996 12 19 96ZZZX6129 1 19961116 G 3234 LANDING GEAR BAC 146 AVRO146RJ100 1500096 EU LYC LF507 LF5071F NE MLG LACK OF LUBE W ANCF A UNSCHED LANDING O OTHER CL CLIMB 1 SO 23 504MM E3221 LF07320 AFTER TAKEOFF, LANDING GEAR LEVER DIDN'T COME UP AND SPOILER LIGHT ON MWS CAME ON. RETURNED TO AIRPORT. LUBRICATED LAN DING GEAR LEVER MECHANISM. CHECKED SPOILER AND FOUND NORMAL. 2 H 7 4 4F 4 F RT A49EU E6NE 1996020900629 19960209 00629 EU 1996 2 9 96ZZZX613 1 19960122 G 5311 1052050172RE FRAME BOLKMS 105 BO105CBS 5626008 EU RT SHELL 9V CRACKED E K NONE O OTHER IN INSP/MAINT 1 SW 03 5366Y 7024 S782 DURING A ROUTINE INSPECTION, A CRACK WAS FOUND IN THE UPPER END OF FRAME 9V IN THE RIGHT SIDE SHELL. THE CRACK WAS APPR OXIMATELY 2.5 INCHES LONG. THE CRACK EXTENDED UNDER THE ATTACHMENT OF THE INBOARD WEB ATTACHED TO THE RIGHT AFT MAIN GE ARBOX ATTACHMENT FITTING IN THE AIRFRAME. REPAIRED PER FIELD APPROVED 337 AND BOLKOW SB SI-BO105-142. 1 G 7 2 3U NC H3EU 1996121900765 19961219 00765 NE 1996 12 19 96ZZZX6130 2 19961117 G 7200 ENGINE BAC 146 AVRO146RJ100 1500096 EU LYC LF507 LF5071F NE NR 2 VIBRATION W ANCF C D ABORTED TAKEOFF RETURN TO BLOCK E J VIBRATION/BUFFET WARNING INDICATION TO TAKEOFF 1 SO 23 508MM E3247 LF73062 DURING TAKEOFF ROLL, ENGINE VIBRATION WARNING LIGHT CAME ON. ENGINE NR 2 REACHED 2.2. TAKEOFF WAS REJECTED. ENGINE NR 2 WAS CHANGED. TEST WAS PERFORMED ACCORDING TO AMM 72-00-00. 2 H 7 4 4F 4 F RT A49EU E6NE 1996121900766 19961219 00766 NE 1996 12 19 96ZZZX6131 2 19961110 G 7200 ENGINE BAC 146 AVRO146RJ100 1500096 EU LYC LF507 LF5071F NE NR 3 BIRD STRIKE W ANCF K NONE C F.O.D. IN INSP/MAINT 1 SO 23 508MM 4014 222 E3247 LF07320 PERFORMING WALK-AROUND IN SAN JOSE, A BIRD WAS FOUND INGESTED IN ENG NR 3. ACCOMPLISHED ENGINE BORESCOPIC INSPECTION DU E TO BIRD STRIKE, NO DAMAGE FOUND ON THE ENGINE. ENGINE RUN-UP. ALL PARAMETERS WITHIN LIMITS. 2 H 7 4 4F 4 F RT A49EU E6NE 1996121900767 19961219 00767 EU 1996 12 19 96ZZZX6132 1 19961114 G 5270 WARNING LIGHT BAC 146 AVRO146RJ100 1500096 EU LOWER DOOR ILLUMINATED W ANCF C D ABORTED TAKEOFF RETURN TO BLOCK J WARNING INDICATION TO TAKEOFF 1 SO 23 504MM E3221 DURING TAKEOFF ROLL, THE LOWER DOOR NOT SHUT LIGHT CAME ON. TAKEOFF WAS REJECTED. ALL LOWER DOORS HYDRAULIC, ELECTRICA L AND CARGO WERE CHECKED AND FOUND OK. RESET THE CONTACTORS ON ALL DOORS. 2 H 7 4 4F RT A49EU 1996121900768 19961219 00768 WP 1996 12 19 96ZZZX6133 1 19961204 G 6220 369H120351 LINK HUGHES 369 369E 4470707 WP M/R HUB CRACKED D K NONE O OTHER IN INSP/MAINT 1 WP 09 440TJ 4982 0442E CRACKED LINK DISCOVERED ON PRE-FLIGHT INSP. 1 G 7 1 3U H3WE 1996121900769 19961219 00769 SW 1996 12 19 96ZZZX6134 1 19961111 G 6510 L NUT 2060403709 BELL 206 206L1 1182107 SW DRIVE SHAFT DETACHED B KBTR K NONE O OTHER IN INSP/MAINT 1 NM 07 5746N 45461 DURING RUN-UP, NUT CAME OFF AND DRIVE SHAFT SEGMENT CAME OFF. NUT APPEARS TO HAVE LOST TARE TORQUE. CHECK FOR ADEQUATE TARE TORQUE PRIOR TO INSTALLING SELF LOCKING NUTS. 1 G 7 1 3U H2SW 1996122600001 19961226 00001 1996 12 26 96ZZZX6135 1 19961210 G 2911 1456613267 END CAP PARKERHANFIN 26604725 ACCUMULATOR BLEW OFF B DM4R K NONE O OTHER IN INSP/MAINT 1 SO 19 107 GAS END CAP BLEW OFF THE ASSY. DURING TEST, ON INSPECTION, FOUND PREVIOUS INTERNAL CRACK IN THE CIRCUMFERENCE ON THE I/ D OF CAP. TEST BEING PERFORMED WAS PRELIMINARY BEFORE DISASSEMBLY. 1996122600002 19961226 00002 GL 1996 12 26 96ZZZX6136 3 19961207 G 6114 D3944C88 HUB MCAULY 3A32C D3A32C88 GL NR 2 BLD SOCKET CRACKED B ME4R K NONE O OTHER IN INSP/MAINT 1 SO 19 512 692219 PROPELLER RECEIVED FOR OVERHAUL. AFTER DISASSEMBLY, THE FOLLOWING PARTS WERE CONDEMNED DUE TO CORROSION. RACES, BALLS, CYLINDER, BLADE PINS, AND BLADE NUTS. 1 EACH FERRULE CONDEMNED DUE TO CRACK IN BLADE PIN HOLE, RACE SIDE. HUB CRACKED IN NR 2 BLADE SOCKET, 5 THREADS IN, 2 INCHES LONG. CRACK DISCOVERED USING A 10X DOWEL MICROSCOPE. 5 C P21EA 1996122600003 19961226 00003 GL 1996 12 26 96ZZZX6137 3 19961209 G 6114 C4716C98 HUB MCAULY 2A34C D2A34C98 GL NR 1 BLD SOCKET CRACKED B ME4R K NONE O OTHER IN INSP/MAINT 1 SO 19 789111 PROP RECEIVED FROM OVERSEAS CUSTOMER FOR 5 YEAR OVERHAUL. AFTER DISASSEMBLY, HUB WAS STRIPPED AND INSPECTED. A CRACK W AS DISCOVERED IN NR 1 BLADE SOCKET, NR 1 TO NR 2 THREAD AT THE 7 O'CLOCK POSITION ABOUT 1 INCH LONG. NO LOG BOOK AVAILA BLE FOR FURTHER INFORMATION. 5 C P3EA 1996122600004 19961226 00004 GL 1996 12 26 96ZZZX6138 3 19961210 G 6114 D5892C93 HUB MCAULY 3AF32C 3AF32C93 GL NR 3 BLD SOCKET CRACKED B ME4R K NONE O OTHER IN INSP/MAINT 1 SO 19 794515 PROPELLER RECEIVED FOR OVERHAUL. DURING HUB MICROSCOPIC INSPECTION (10X POWER), HUB DISCOVERED CRACKED IN NR 3 BLADE SO CKET, NR 3 THREAD IN 7 O'CLOCK POSITION ABOUT 1 INCH LONG. NO PROPELLER LOG BOOK PROVIDED FOR FURTHER INFORMATION. 5 C P22EA 1996122600005 19961226 00005 SO 1996 12 26 96ZZZX6139 1 19961205 G 3710 842CW PUMP AIRBORNE PIPER PA31 PA31P 7103120 SO VAC SYS FAILED B EKIR K NONE O OTHER IN INSP/MAINT 1 WP 07 18MC 315 12AK000076 31P7300143 VAC PUMP REMOVED FOR ENGINE REPAIR. SHAFT VERY HARD TO TURN AND UNIT SQUEALED. 1 L 7 2 3O A8EA 1996122600006 19961226 00006 EA 1996 12 26 96ZZZX6140 2 19961205 G 8510 75562 GEAR TOOTH PIPER PA31 PA31P 7103120 SO LYC O541 TIGO541E1A 41539 EA PROP SHAFT BROKEN B EKIR K NONE O OTHER IN INSP/MAINT 1 WP 07 18MC 4117 50 246 31P7300143 L38662 ENGINE SOUNDED ROUGH ON SHUT DOWN. FOUND EXCESSIVE PLAY IN PROPELLER. DRAINED OIL, PULLED SUCTION SCREEN, FOUND PIECE OF TOOTH IN SCREEN. ENGINE TORN DOWN, FOUND BROKEN TEETH ON PROP SHAFT DRIVE GEAR, ALSO, DRIVE GEAR DAMAGED. SUBMITTER SUSPECTS PREVIOUS CRACK CAUSED TOOTH TO BREAK OFF. 1 L 7 2 3O 3 O A8EA E19EA 1996122600007 19961226 00007 EA 1996 12 26 96ZZZX6141 2 19961212 G 7322 15B395 RETAIN SCREW FACET HA6 GULSTM AA5 AA5B 3960105 SO LYC O360 O360A4K 41514 EA MIX CONTROL LOOSE D K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 SW 07 28794 1014 CH101834 AA5B0819 L249536A PILOT REPORTED ENIGNE HAD STARTED RUNNING ROUGH AND EGT AT PEAK WITH MIXTURE FULL RICH. INVESTIGATION REVEALED MIXTURE CONTROL VALVE END PLAY OF APPROX .0625 INCH. PRECISION AIRMOTIVE SB MSA-6 HAD NOT BEEN C/W. RETENTION SCREW P/N 15-B3 95 WAS FOUND TO HAVE PIN SEPARATED FROM END AND FLOATING IN HOLE. PIN AND SCREW APPEAR TO HAVE BEEN WELDED IN MANUFACTU RE AND SEPARATED AT WELD. INSTALLATION OF RETENTION KIT PER MSA-6 RETURNED NORMAL OPERATION. 1 L 7 1 3O 3 O A16EA E286 1996122600008 19961226 00008 SO 1996 12 26 96ZZZX6142 1 19961116 G 2913 POWER PAC PIPER PA23 PA23250 7102308 SO NLG FAILED C O OTHER J WARNING INDICATION AP APPROACH 1 SW 99 329SD 273512 NOSE GEAR WOULD NOT COME DOWN. EMERGENCY BOTTLE USED TO LOCK GEAR. HYD POWER PAC FAILURE. 1 L 7 2 3O 1A10 1996122600009 19961226 00009 1996 12 26 96ZZZX6143 4 19961203 G 2562 7B1115 G SWITCH LEIGH SHARC7 CESSNA 182 182K 2072724 CE ELT INOPERATIVE D K NONE O OTHER IN INSP/MAINT 1 NE 05 3047Q 2000 4254 18258047 DURING ANNUAL INSPECTION, G-SWITCH WAS FOUND TO BE INOPERATIVE. 1 COVER SCREW BOSS CRACKED, O-RING BROKEN. 1 H 7 1 3O NT 3A13 1996122600010 19961226 00010 SO 1996 12 26 96ZZZX6144 1 19961128 G 2821 CCA1550 DRAIN VALVE CURTIS PIPER PA28 PA28R200 7102811 SO FUEL GASCOLATOR STEM FAILED C A K NONE O OTHER IN INSP/MAINT 1 SO 15 55177 5800 28R7335190 ON PRE-FLIGHT THIS VALVE WHICH IS ATTACHED TO AN ELBOW ATTACHED TO GASCOLATOR; WAS DIFFICULT TO PUSH IN TO DRAIN. A SLI GHT PULL WAS MADE AND THE STEM CAME OUT IN HAND. FUEL BEGAN TO DRAIN AND THE FUEL SELECTOR HAD TO BE SHUT OFF. VALVE W AS REMOVED AND THE RETAINING COLLAR WAS FOUND SEPARATED FROM STEM END. SUBMITTER STATED IF STEM FELL OUT IN-FLIGHT - TH E ENGINE WOULD STOP. THE VALVE WAS REPLACED. 1 L 7 1 3O 2A13 1996122600011 19961226 00011 SO 1996 12 26 96ZZZX6145 1 19961206 G 5751 4020043 SPAR PIPER PA31 PA31310 7103103 SO RT AILERON CRACKED D K NONE O OTHER IN INSP/MAINT 1 CE 09 578F 9037 317712004 DURING C/W AD 96-21-03, A CRACK WAS DETECTED IN THE AILERON SPAR AND REINFORCEM ENT DOUBLER IN BOTTOM BRACKET ATTACH HOL E. 1 L 7 1 3O RT A20SO 1996020900631 19960209 00631 GL 1996 2 9 96ZZZX615 1 19960124 G 8120 28125523 WASTEGATE ENSTRM F28 F28F 3300412 GL TUBRO WARPED H K NONE O OTHER IN INSP/MAINT 1 WP 23 8626S 900 786 BUTTERFLY IN WASTEGATE FOUND WARPED AT EACH 100-HOUR INSPECTION. WARPED WASTEGATE AND WORN BUTTERFLY AND SHAFT CAUSE TH ROTTLE BINDING. BUTTERFLY MUST BE STRAIGHTENED FOR PROPER RIGGING. ON SOME AIRCRAFT, BUTTERFLIES COME OFF OF SHAFT AND BIND THROTTLE. COMMON TO ALL 'F' AND 'FX' MODELS. SUBMITTER STATED WASTEGATES NEED TO BE REPLACED AT 900 HOURS MAXIMU M TIME IN SERVICE. 1 G 7 1 3O H1CE 1996122600404 19961226 00404 CE 1996 12 26 96ZZZX6153 1 19961121 G 3211 SK4148 REINFORCEMENT CESSNA 402 402A 207590M CE LT/RT MLG CRACKED D K NONE O OTHER IN INSP/MAINT 1 WP 01 186BA 402A0110 CESSNA SERVICE KIT SK414-8 WAS INSTALLED ON THIS AIRCRAFT IN 1982. DURING A 100-HOUR INSPECTION, CRACKS WERE DISCOVERED IN THE DOUBLER ON THE LEFT AND RIGHT MAIN GEAR SIDE BRACE BRACKETS. 1 L 7 2 3O A7CE 1996122600405 19961226 00405 CE 1996 12 26 96ZZZX6154 1 19960926 G 7120 10291002638 TRUSS BEECH 58 58P 1152744 CE LT ENG MOUNT LOOSE B JA1R K NONE O OTHER IN INSP/MAINT 1 EA 25 2056N 2823 TJ156 ON ANNUAL INSPECTION, RIGHT TRUSS WAS FOUND LOOSE AT FORWARD END ATTACHMENT TO MOUNT. NUT ON HILOCK WAS FINGER TIGHT ON LY AND REMOVED BY HAND. REMOVAL OF HILOCK REVEALED .031 INCH DEEP SLOT WORN IN SHANK. WEAR IS IN AREA THAT CONTACTS MO UNTS. NO WEAR IN AREA THAT CONTACTS TRUSS FORK OR IN TRUSS. SUBMITTER RECOMMENDS INSPECTION FOR MOVEMENT OF TRUSS TO M OUNT ATTACHMENT EACH 100 HOURS. 1 L 7 2 3O A23CE 1996122600406 19961226 00406 EA 1996 12 26 96ZZZX6155 2 19961120 G 7322 25244919 INJECTOR SERVO BENDIX RSA10ED1 PIPER PA60 PA60601P 7106012 NM LYC O540 IO540S1A5 41532 EA ENGINE FAILED D K NONE R PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 NE 03 3646N 1768 63 64435 61P085881634 L2051648A INJECTOR SERVO 'SHUT DOWN' DURING ACTUAL FUEL FLOW TEST', ALLOWING ONLY A DRIBBLE OF FUEL THROUGH WITH FULL THROTTLE AND FULL MIXTURE AND FUEL PUMP ON. HAD THIS HAPPENED IN-FLIGHT, ENGINE WOULD HAVE STOPPED. 1 M 7 2 3O 3 O RT A17WE 1E4 1996122600407 19961226 00407 EA 1996 12 26 96ZZZX6156 2 19961101 G 7322 VALVE TANG FACET HA6 CESSNA 172 172RG 2072438 CE LYC O360 O360F1A6 41514 EA FUEL CUT OFF WORN B S ATZR K NONE O OTHER IN INSP/MAINT 1 CE 09 5099U 4986 1015 DL0414 172RG0223 L2782536A TANG OF FUEL CUT OFF VALVE ASSY WORE DEEPLY INTO FULL RICH STOP AREA ALLOWING APPROX ONE-QUARTER TURN MORE THAN NORMAL. ENGINE WENT EXTREMELY LEAN. TAKEOFF ABORTED. 1 H 7 1 3O 3 O 3A17 E286 1996122600408 19961226 00408 1996 12 26 96ZZZX6157 4 19961122 G 2562 DMELT83 WIRE DORNEMARGLN DMELT81 CESSNA 210 P210R 2073455 CE ELT ANTENNA SHORTED D K NONE O OTHER IN INSP/MAINT 1 NM 09 5522A P21000860 WHEN CHECKING ELT OUTPUT PER FAR 91.207(D)(4), UNIT COULD NOT BE HEARD ON NEARBY AM RADIO, BUT COULD BE RECEIVED ON AIRC RAFT'S VHF RADIO. FOUND ANTENNA CABLE CENTER CONDUCTOR INTERNALLY SHORTED TO GROUND. PROPERLY OPERATING ELT SHOULD BLE ED OVER ON AN AM RADIO. 1 H 7 1 3O RT 3A21 1996122600410 19961226 00410 CE 1996 12 26 96ZZZX6159 1 19961209 G 5711 SPAR BEECH 58 58 1152740 CE CARRY THRU WEB CRACKED D A K NONE O OTHER IN INSP/MAINT 1 SW 03 7234K 2886 TH1479 INSP SPAR CARRY-THROUGH WEB STRUCTURE. FOUND LT FWD AND AFT RT FWD CORNERS CRACKED. THIS AIRCRAFT IS 4 SERIAL NUMBERS NEWER THAN BEECH AD 90-18-14 APPLIES TO. SUBMITTER STATED AD 90-18-14 NEEDS REVISING TO INCLUDE NEW AIRCRAFT. 1 L 7 2 3O 3A16 1996122600412 19961226 00412 SO 1996 12 26 96ZZZX6160 2 19961116 G 8540 643259AZ DRIVE ADAPTER CESSNA 421 421C 2076016 CE CONT O520 GTSIO520N 17032 SO STARTER DRV END WORN G K NONE O OTHER IN INSP/MAINT 1 WP 09 749CA 3707 724 421C1239 608257 STARTER DRIVE GEAR WEAR UNACCEPTABLE IAW TELEDYNE CONTINENTAL CSB 94-4 EVEN THOUGH THE SERVICE KIT REQUIRED BY TCM CSB 9 4-4 HAD BEEN PREVIOUSLY INSTALLED AT THE ENGINE OVERHAUL. SUSPECT CAUSE: CSB 94-4 MAY NOT BE SUFFICIENT. SUBMITTER RE COMMENDS FLEET DATA BE EXAMINED TO DETERMINE NUMBER OF OCCURRENCES. 1 L 7 2 3O 3 O A7CE E7CE 1996122600413 19961226 00413 EA 1996 12 26 96ZZZX6161 2 19961115 G 7322 DISCHARGE TUBE CESSNA 172 172L 2072432 CE LYC O320 O320E2D 41508 EA CARB HEAT BOX BROKEN B A M6MR A UNSCHED LANDING O OTHER NR NOT REPORTED 1 GL 09 7916G 17259616 L2213727A THROTTLE JAMMED IN-FLIGHT. SAFE LANDING MADE. FOUND CARB DISCHARGE TUBE BENT AND BROKEN IN CARB HEAT BOX. FOUND THROT TLE SHAFT BUSHINGS EXCESSIVELY WORN AND LEAKING. AIRCRAFT 4.6 HOURS SINCE 'OWNER ASISTED ANNUAL' WAS COMPLETED. THESE ITEMS ARE PART OF ANNUAL CHECK LIST AND SHOULD HAVE BEEN FOUND AT ANNUAL AS AD 93-18-03 WAS SIGNED OFF, THE AREA WAS SU PPOSED TO BE INSPECTED. 1 H 7 1 3O 3 O NT 3A12 E274 1996122600414 19961226 00414 CE 1996 12 26 96ZZZX6162 1 19961115 G 2720 031019612 SPRING CESSNA 172 172L 2072432 CE RUDDER CONTROL BROKEN B A M6MR K NONE O OTHER IN INSP/MAINT 1 GL 09 7916G 17259616 OPERATOR COMPLAINED OF HEAVY RUDDER AND OUT OF TRIM. UPON INSPECTION, FOUND RT RUDDER CENTERING SPRING BROKEN AT AFT AT TACHMENT. AIRCRAFT 4.6 HOURS SINCE 'OWNER ASSISTED ANNUAL INSPECTION' WAS COMPLETED. AREA IS AWKWARD TO INSPECT UNLESS AREA PANELS ARE REMOVED INCLUDING CENTER PANEL FORWARD OF CENTER PEDESTAL. SPRING EXHIBITS WEAR IN AREA WHERE IT BROKE . AREA SHOULD BE INSPECTED AT 100 HR AND ANNUAL INSPECTIONS. THIS WAS THE SECOND 'SAFETY OF FLIGHT' CONDITION FOUND TH IS DATE. 1 H 7 1 3O NT 3A12 1996122600415 19961226 00415 CE 1996 12 26 96ZZZX6163 1 19961213 G 3233 98820152 ACTUATOR CESSNA 172 172RG 2072438 CE RT MLG CRACKED D O OTHER J WARNING INDICATION AP APPROACH 1 SO 13 9310D 3569 172RG1116 RIGHT MAIN GEAR ACTUATOR HOUSING CRACK AT SMALL END WHERE GEAR ATTACHES TO ACTUATOR. ACTUATOR CRACKED IN THREE DIRECTIO NS ALLOWING PINION TO DISENGAGE FROM ACUTATOR. GEAR FAILED TO EXTEND FOR LANDING. 1 H 7 1 3O 3A17 1996122600416 19961226 00416 CE 1996 12 26 96ZZZX6164 1 19961120 G 3230 PAD CESSNA 172 172RG 2072438 CE NLG UPSTOP WORN D A O OTHER J WARNING INDICATION AP APPROACH 1 SW 99 9574B 6128 172RG0891 GEAR WAS RETRACTED AND EXTENDED SEVERAL TIMES DURING FLIGHT. AFTER RETRACTION, GEAR WOULD NOT INDICATE GREEN LIGHT ON D OWN AND LOCKED POSITION. FOUND THE UPSTOP PAD WORN TO APPROX .25 INCH THICK, ALLOWED GEAR TO GO BEYOND NORMAL UP POSITI ON. NOSE WHEEL FORK BOUND ITSELF IN WHEELWELL AREA. MANUFACTURER MM DOES NOT LIST MIN THICKNESS OR ANY INFO ON CONDITI ON OR INSPECTION OF THE UPSTOP PADS OR BUMPERS. IT IS SUGGESTED THAT THESE COMPONENTS ARE INSPECTED FOR THICKNESS AND C ONDITION EACH 100 HRS. 1 H 7 1 3O 3A17 1996122600417 19961226 00417 EA 1996 12 26 96ZZZX6165 1 19961122 G 3350 5521981 BATERY PACK GRIMES 6013211 CNDAIR CL601 CL6013A 8070802 EA CABIN SHORTED B SH5R K NONE O OTHER IN INSP/MAINT 1 NE 03 2FOR 18115 5092 THE NEW BATTERY PACKS USED BY GRIMES WHICH ARE MFG'D BY E.A.C., USE A METAL STRAP BETWEEN POSITIVE AND NEGATIVE TERMINAL S WITH A SMALL PIECE OF HEAT SHRINK ON THEM. THE PROBLEM IS THE HEAT SHRINK SHRINKS AT TEMPERATURE AND THE STRAPS CUT T HE HEAT SHRINK AND SHORT THE TERMINALS TO THE BATTERY CAUSING SHORTS AND THE PACKS OVERHEAT. 2 L 7 2 4F RT A21EA 1996122600418 19961226 00418 CE 1996 12 26 96ZZZX6166 1 19961108 G 3213 010A38371012 YOKE MTSBSI MU2 MU2B26A 5780414 CE RT MLG FAILED D A O OTHER O OTHER LD LANDING 1 WP 09 333WF 5700 387 YOKE ASSY FAILED DURING LANDING ALLOWING THE RIGHT MAIN WHEEL ASSY TO ROTATE APPROXIMATELY 90 DEGREES. THIS GROUND THE TIRE, WHEEL ASSY, AND BRAKE DISC TO THE POINT OF RENDERING THESE PARTS UNSERVICEABLE. SUBMITTER RECOMMENDATION: ESTABL ISH AN INSPECTION TIME LIMIT ON THE ABOVE PART AFTER SO MANY LANDINGS OR HOURS WHICHEVER COMES FIRST AND TO MAGNAFLUX TH E RESPECTIVE PART. 1 H 7 2 3T A10SW 1996122600421 19961226 00421 CE 1996 12 26 96ZZZX6168 1 19961204 G 7810 1019500171 STACK BEECH 300 300BEECH 1152930 CE RT ENG INB CRACKED D A K NONE O OTHER IN INSP/MAINT 1 GL 25 195AL 78 FA102 THE RIGHT ENGINE INBOARD EXHAUST STACK WAS FOUND TO HAVE A CRACK 10 INCHES LONG PARALLEL WITH THE HORIZONTAL WELD ON THE FORWARD SIDE. THIS IS THE SECOND NEW EXHAUST STACK THAT HAS CRACKED AND ONLY AFTER 78.1 HRS OF OPERATION. 2 L 7 2 4T A24CE 1996122600422 19961226 00422 CE 1996 12 26 96ZZZX6169 1 19961101 G 2910 1145800501 LINE ASSY BEECH 1900 1900D 1154162 CE PWR PACK FILL CRACKED B S ATZR O OTHER J WARNING INDICATION NR NOT REPORTED 1 CE 09 225GL UE225 FILL LINE TUBES ASSY CRACKED AT FLARE. LOSS OF FLUID IN HYDRAULIC SYSTEM SUFFICIENT TO ILLUMINATE LOW FLUID LIGHT. GEA R EXTENDED NORMALLY. 2 L 7 2 4T RT A24CE 1996020900633 19960209 00633 EA 1996 2 9 96ZZZX617 2 19960116 G 8530 77160 VALVE GUIDE GULSTM AA5 AA5B 3960105 SO LYC O360 O360A4K 41514 EA CYLINDERS 1-3 EXCESS WEAR D K NONE O OTHER IN INSP/MAINT 1 WP 05 74608 413 AA5B0282 3295236A NR 1 AND NR 3 CYLINDERS FAILED LYC SB 388B TEST FOR EXCESS WEAR (.035 INCH AND .043 INCH RESPECTIVELY). THESE EXACT SAM E TWO GUIDES AND CORRESPONDING VALVES HAD BEEN PREVIOUSLY REPLACED AT 408 HOURS SINCE NEW ENGINE. FOUR-PROBE EGT/CHT SH OWED ALL TEMPS NORMAL AND BAFFLE SEALS WERE GOOD. GROUND RUN ENGINE AND COLLECTED OIL FROM ROCKER BOXES OF THE 4 CYLIND ERS. FOUND NR 1 AND NR 3 CYLINDERS GETTING MUCH LESS THAN NR 2 AND NR 4. NR 2 AND NR 4 GUIDES PASSES SB 388B TESTS AND THEY HAVE 821 HOURS TTSN. IN THAT TIME, 2 SETS OF NR 1 AND NR 3 EXHAUST VALVES/GUIDES HAVE FAILED THE TEST IN SB 388B. SUBMITTER SUSPECTS POSSIBLE DESIGN PROBLEM THAT PROVIDES INSUFFICIENT OIL TO NR 1 AND NR 3 CYLINDERS. 1 L 7 1 3O 3 O A16EA E286 1996122600423 19961226 00423 CE 1996 12 26 96ZZZX6170 1 19961203 G 5542 553300013 SKIN 553300095 CESSNA 500 560CESSNA 2076750 CE RUD LT SIDE LE CRACKED B DXTR K NONE O OTHER IN INSP/MAINT 1 GL 07 327QS 1383 5600327 LT SIDE OF BOTTOM L/E SKIN HAS A CRACK ALONG THE RIVET LINE THAT IS 2.25 INCHES LONG. THIS IS THE 7TH OCCURRENCE OF THI S PROBLEM. 2 L 7 2 4F RT A22CE 1996122600424 19961226 00424 CE 1996 12 26 96ZZZX6171 1 19961030 G 5542 553300095 RUDDER SKIN CESSNA 500 560CESSNA 2076750 CE LT BELOW TAB CRACKED B A DXTR K NONE O OTHER IN INSP/MAINT 1 GL 07 330QS 1277 5600329 LT RUDDER SKIN HAS 2 INCH CRACK APPROX 3 INCHES BELOW TRIM TAB FWD OF HINGE LINE. THIS IS THE SECOND DISCOVERED VERTICA L CRACK, AND THE SIXTH RUDDER SKIN CRACK OVERALL. CESSNA WAS NOTIFIED BY SERVICE CONDITION REPORT. 2 L 7 2 4F RT A22CE 1996122600425 19961226 00425 CE 1996 12 26 96ZZZX6172 1 19961209 G 5542 553300013 SKIN 553300095 CESSNA 500 560CESSNA 2076750 CE RUD LT SIDE LE CRACKED B DXTR K NONE O OTHER IN INSP/MAINT 1 GL 07 348QS 1035 5600348 LT SIDE OF BOTTOM L/E SKIN HAS A 1 INCH HORIZONTAL CRACK ALONG THE RIVET LINE. THIS IS THE SAME AREA OF MANY OTHER RUDD ERS, AND IS THE EIGHTH (8) OCCURRENCE OF THIS PROBLEM. 2 L 7 2 4F RT A22CE 1996122600426 19961226 00426 CE 1996 12 26 96ZZZX6173 1 19961112 G 7810 TAILPIPE LEAR 24 24 5170302 CE LT ENG CRACKED D O OTHER J WARNING INDICATION CR CRUISE 1 SW 99 555LB 177 LT FIRE LIGHT ILLUMINATED AT ALTITUDE. REPLACED CRACKED TAIL PIPE WITH SERVICEABLE UNIT. 2 L 7 2 4J A10CE 1996122600527 19961226 00527 WP 1996 12 26 96ZZZX6174 2 19961211 G 7210 3072178 GEAR ASSY LEAR 35 31A 5170531 CE GARRTT TFE731 TFE7312 01518 WP RT ENG PLANETARY DAMAGED E L A O OTHER O OTHER DE DESCENT 1 CE 07 112FX 347 347 116 P99348 DURING DESCENT INTO ICT, PILOT REPORTED UNUSUAL NOISE FROM RT ENGINE. AFTER LANDING AND SHUT DOWN, ROTATION OF FAN BY L EAR JET MECHANIC CONFIRMED NOISE. INSP FOUND A BAYONET FROM A STUD IN THE TEETH OF THE FAN SUPPORT RING GEAR FOR GEARBO X. INSPECTION FOUND THE STUD THAT WAS MISSING THE BAYONET, THE STUD WAS REPLACED AND NO OTHER DAMAGE WAS NOTED. 2 L 7 2 4F 4 F RT A10CE E6WE 1996122600529 19961226 00529 1996 12 26 96ZZZX6175 4 19961101 G 3441 5H120 CELL MARATHON CA54 GULSTM G1159 G1159A 3970109 SO INS STDBY BAT DEFECTIVE D K NONE O OTHER IN INSP/MAINT 1 NM 03 93CX 1285 314 BATTERY CELL LIFE IS TOO SHORT. THIS BATTERY WAS RECELLED 10/96, 1/95, 5/94. SUBMITTER STATED POSSIBLY REDUCING CHARGE RATE TO THIS BATTERY OR INSTALL A STRONGER CELL (SUPER POWER). POSSIBLY A 20 CELL MODIFICATION WOULD HELP, PRESENTLY 1 9 CELL. 2 L 7 2 4F A12EA 1996122600530 19961226 00530 CE 1996 12 26 96ZZZX6176 1 19961028 G 5542 553300095 RUDDER SKIN CESSNA 500 560CESSNA 2076750 CE LT BELOW TAB CRACKED B DXTR K NONE O OTHER IN INSP/MAINT 1 GL 07 341QS 5600341 FOUND 4 INCH VERTICAL CRACK ON LT SKIN OF RUDDER APPROXIMATELY 3 INCHES BELOW HINGE LINE OF TRIM TAB. SKIN REMOVED AND REPLACED. THIS IS THE 5TH INCIDENT OF A LT RUDDER SKIN CRACK. 2 L 7 2 4F RT A22CE 1996122600531 19961226 00531 CE 1996 12 26 96ZZZX6177 1 19961028 G 5542 553300095 RUDDER SKIN CESSNA 500 560CESSNA 2076750 CE LT BELOW TAB CRACKED B DXTR K NONE O OTHER IN INSP/MAINT 1 GL 07 ES7QS 5600307 A LT RUDDER SKIN CRACK HORIZONTAL, ABOUT 2 INCHES LONG, AND ALONG THE RIB LINE OF THE RUDDER RIB BELOW THE TRIM TAB. 2 L 7 2 4F RT A22CE 1996122600532 19961226 00532 CE 1996 12 26 96ZZZX6178 1 19961028 G 5542 553300095 RUDDER SKIN CESSNA 500 560CESSNA 2076750 CE LT BELOW TAB CRACKED B DXTR K NONE O OTHER IN INSP/MAINT 1 GL 07 317QS 5600317 A LT RUDDER SKIN CRACK HORIZONTAL, ABOUT 2 INCHES LONG, AND ALONG THE RIB LINE OF THE RUDDER RIB BELOW THE TRIM TAB. 2 L 7 2 4F RT A22CE 1996122600533 19961226 00533 CE 1996 12 26 96ZZZX6179 1 19961028 G 5542 553300095 RUDDER SKIN CESSNA 500 560CESSNA 2076750 CE LT BELOW TAB CRACKED B DXTR K NONE O OTHER IN INSP/MAINT 1 GL 07 344QS 5600344 A LT RUDDER SKIN CRACK. HORIZONTAL, ABOUT 2 INCHES LONG, AND ALONG THE RIB LINE OF THE RUDDER RIB BELOW THE TRIM TAB. 2 L 7 2 4F RT A22CE 1996020900634 19960209 00634 CE 1996 2 9 96ZZZX618 1 19960106 G 2710 NAS304220255 CABLE ASSY BEECH 33 3533 1151402 CE AILERON MISINSTALLED D A K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 09 915T CD115 DURING ANNUAL INSPECTION, FOUND AILERON TRAVEL TO BE 14 DEGREES UP AND DOWN WHILE SPEC IS 20 DEGREES. STOPS ON AILERON BELLCRANK WERE NOT CONTACTING. UPON CLOSER INSPECTION, FOUND AILERON CABLE WEDGED BETWEEN 2 PULLEYS AT STA 51.5. THE P ARTS CATALOG CALLS FOR 2 AN392-35 CLEVIS PINS TO BE INSTALLED FORWARD AND BELOW THE PULLEYS TO PREVENT THE CABLE FROM CO MING OFF PULLEYS. THE PINS WERE MISSING AND IT APPEARED THEY HAD BEEN MISSING FOR SOME TIME. INSTALLED CABLE AND WAS A BLE TO GET FULL AILERON TRAVEL. 1 L 7 1 3O 3A15 1996122600534 19961226 00534 CE 1996 12 26 96ZZZX6180 1 19961028 G 5542 553300095 RUDDER SKIN CESSNA 500 560CESSNA 2076750 CE LT BELOW TAB CRACKED B DXTR K NONE O OTHER IN INSP/MAINT 1 GL 07 375QS 5600375 A LT RUDDER SKIN CRACK. HORIZONTAL, ABOUT 2 INCHES LONG, AND ALONG THE RIB LINE OF THE RUDDER RIB BELOW THE TRIM TAB. 2 L 7 2 4F RT A22CE 1997010200343 19970102 00343 SW 1997 1 2 96ZZZX6182 1 19961007 G 6410 206016201131 BLADE BELL 206 206L1 1182107 SW T/R BEARING WORN B ZV1R K NONE O OTHER IN INSP/MAINT 1 SW 03 2611 1081 CS452 45417 T/R BLADES REMOVED DUE TO FEATHERING BEARINGS WORN AND EXCESSIVE AXIAL MOVEMENT OF THE BLADES. INSPECTED BLADE FEATHERI NG BEARINGS PER BELL 206L MM, CH 65-30-00, PG 65-49 PARA 65-62 ITEM 6 AXIAL LOOSENESS EXCEEDED .190 INCHES AT BLADE TIP. BEARINGS REPLACED. TOTAL TIME OF OLD BEARINGS 537.7. 1 G 7 1 3U H2SW 1997010200344 19970102 00344 SW 1997 1 2 96ZZZX6183 1 19961007 G 6410 206016201131 BLADE BELL 206 206L1 1182107 SW T/R BEARING WORN B ZV1R K NONE O OTHER IN INSP/MAINT 1 SW 03 2611 538 CS446 45417 T/R BLADES REMOVED DUE TO FEATHERING BEARINGS WORN AND EXCESSIVE AXIAL MOVEMENT OF THE BLADES. INSPECTED BLADE FEATHERI NG BEARINGS PER BELL 206L MM, CH 65-30-00, PG 65-49 PARA 65-62 ITEM 6 AXIAL LOOSENESS EXCEEDED .190 INCHES AT BLADE TIP. BEARINGS REPLACED. TOTAL TIME OF OLD BEARINGS 537.7. 1 G 7 1 3U H2SW 1997010200345 19970102 00345 SW 1997 1 2 96ZZZX6184 1 19961107 G 2430 SM20ACD200A21 RELAY BELL 206 206L1 1182107 SW DC SYS CORRODED B ZV1R K NONE O OTHER IN INSP/MAINT 1 SW 03 2618 MFD9624 45503 RELAY COMING APART. CORROSION ON INSIDE. 1 G 7 1 3U H2SW 1997010200346 19970102 00346 NE 1997 1 2 96ZZZX6185 1 19960925 G 2910 0711311005 MODULE SKRSKY S76 S76 8143010 NE HYD LEAKING B AC2R K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 5401G 0447B 760137 HYDRAULIC MODULE ASSEMBLY PN 76650-09801-104 WAS REPORTED LEAKING AT CYLINDER OF MODULE. REMOVED CYLINDER PN 0711311-20 2 O-RING PN 0711311-237 AND INSTALLED ANOTHER SERVICEABLE CYLINDER AND O-RING. C/W LEAK CHECK OF MODULE ASSY. FOUND TO BE SERVICEABLE. 1 G 7 2 3U H1NE 1997010200347 19970102 00347 SW 1997 1 2 96ZZZX6186 1 19961009 G 6330 206033509203 BEARING 206033506101 BELL 206 206L1 1182107 SW XMSN RESTRAINT WORN B ZV1R K NONE O OTHER IN INSP/MAINT 1 SW 03 3899C 332 LK3115 45596 TRANSMISSION RESTRAINT BEARINGS WORN BEYOND LIMITS. REPLACED 2 EACH BEARINGS. 1 G 7 1 3U H2SW 1996020900635 19960209 00635 CE 1996 2 9 96ZZZX619 1 19960102 G 3246 101028 WHEEL HALF BFGOODRICH 31255 BEECH 18 E18S 1151006 CE LT MLG BROKEN D K NONE O OTHER TX TAXI/GRND HDL 1 AL 03 700WA BA28 INNER WHEEL HALF FAILED DURING TAXI. TIME SINCE LAST INSPECTION, 25.9 HOURS. SUBMITTER SUGGESTED CHECKING WHEELS AND W HEEL BOLTS FOR CONDITION AND SECURITY. 1 L 7 2 3R A765 1996020900636 19960209 00636 SO 1996 2 9 96ZZZX620 1 19960120 G 3213 STRUT HEAD PIPER PA28 PA28140 7102802 SO MLG RUSTED D L K NONE O OTHER IN INSP/MAINT 1 SO 14 4347T 287125510 THE CYLINDER HEADS WHICH ARE THE CAPS TO THE MLG STRUTS WERE FOUND SEVERELY RUSTED. THE ATTACHING BOLTS WERE RUSTED BAD LY ALSO. THIS AREA HAS A BUILT-IN WELL AREA WHICH ALLOWS WATER TO ACCUMULATE AND JUST SIT THERE. THERE IS A METAL PLUG BUTTON USED TO COVER THIS AREA AND FILL THE HOLE IN THE WING OVER THE FILL VALVE. 1 L 7 1 3O 2A13 1996020900638 19960209 00638 1996 2 9 96ZZZX622 4 19960116 G 2312 466920000 SWITCH SIGMATEK RT385A NAV/COM DEFECTIVE B L A JA3R K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 21 17996 WHILE REPAIRING CESSNA RT385 AIRCRAFT RADIOS, FOUND SIGMATEK CORP IS SHIPPING DEFECTIVE SWITCHES FOR THE CESSNA RT385 NA V COM THAT POSE AN ONGOING HAZARD TO FLIGHT SAFETY. THE SIGMATEK PART NUMBERS ARE 46692-0000, 46659-0000, 46693-0000, A ND 46481-0000. THE DANGER IS SEPARATE SECTIONS OF EACH SWITCH CONTROL SEPARATE FUNCTIONS OF THE RADIO. ONE PART OF THE SWITCH CONTROLS FREQUENCY DISPLAY AND THE OTHER PART CONTROLS ACTUAL FREQUENCY OF THE RADIO. IT HAS HAPPENED THAT ONE NAVIGATION FACILITY CAN BE DISPLAYED AND ANOTHER RECEIVED. IN OTHER WORDS, THE RADIO WILL BE RELAYING INFO FOR WHAT THE PILOT WOULD ASSUME TO REPRESENT A SOUTHERN APPROACH, BUT IN REALITY, IS RELAYING INFO FOR AN EASTERN APPROACH. 1996021600001 19960216 00001 WP 1996 2 16 96ZZZX626 1 19960115 G 7160 369A8448 PULLEY HUGHES 369 369D 4470706 WP ALT AIR DOOR SEIZED B EOOR K NONE O OTHER IN INSP/MAINT 1 AL 03 5074R 1151D DURING DAILY INSPECTION, ONE OF THE PULLEYS FOR THE ALTERNATE AIR DOOR CABLE WAS FOUND SEIZED. REPLACED THE PULLEY. 1 G 7 1 3U H3WE 1996021600002 19960216 00002 WP 1996 2 16 96ZZZX627 1 19960115 G 7933 369A4533 SENSOR HUGHES 369 369D 4470706 WP ENG OIL OUT OF CALIB B EOOR K NONE O OTHER IN INSP/MAINT 1 AL 03 5074R 1151D PILOT COMPLAINED THE ENGINE OIL TEMP WAS TOO LOW. SUBSEQUENT INSPECTION FOUND TEMP BULB RESISTANCE TOO HIGH AND IT READ LOW ON FUNCTIONAL BENCH CHECK. REPLACED TEMP BULB. 1 G 7 1 3U H3WE 1996021600003 19960216 00003 WP 1996 2 16 96ZZZX628 1 19960110 G 6320 369D25100505 TRANSMISSION HUGHES 369 369D 4470706 WP M/R LEAKING B EOOR K NONE K FLUID LOSS IN INSP/MAINT 1 AL 03 5074R 40893 1151D DURING INSPECTION, A LEAKY SEAL WAS DISCOVERED ON THE INPUT SHAFT OF THE TRANSMISSION. REPLACED TRANSMISSION. 1 G 7 1 3U H3WE 1996021600004 19960216 00004 WP 1996 2 16 96ZZZX629 1 19960116 G 6210 369D51321100 BLADE HUGHES 369 369D 4470706 WP MR OTBD LE STRIP ERODED D K NONE O OTHER IN INSP/MAINT 1 WP 07 911FT 2016 B786 811036D MAIN ROTOR BLADE L/E ABRASION STRIP ERODED AT THE OUTBOARD END OF M/R BLADE NEAR THE TIP. CAUSE OF EROSION - OPERATING IN AND AROUND SAND AND DIRT DURING OFF-AIRPORT LANDINGS. REPAIR MADE TO AREA PER APPROVED ENG. DATA - 8110-3. M/R BLAD E RETURNED TO SERVICE. 1 G 7 1 3U H3WE 1996021600005 19960216 00005 GL 1996 2 16 96ZZZX630 2 19960108 G 7261 1740364 OUTLET STRAINER 174000103 HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL LUBE FILTER MISSING D A K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 07 911FT 2856 811036D CAE836410 DURING ROUTINE/RECOMMENDED 1,000-HOUR INSPECTION OF THE OUTLET STRAINER ASSEMBLY, THE SCREEN WAS NOT INSTALLED, RATHER A N INLET FITTING, PN 1740235, WAS INSTALLED. THIS UNIT IS APPROXIMATELY 980 HOURS TSN. SUBMITTER RECOMMENDS COMPLETE IN SPECTION OF ASSY (FILTER, SCREEN, PACKINGS, ETC.) PRIOR TO INSTALLATION. STC NR SH401GL. 1 G 7 1 3U 3 U H3WE E4CE 1996021600657 19960216 00657 SO 1996 2 16 96ZZZX670 1 19960105 G 7922 53E19600 VALVE PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA THERMO BYPASS CRIMP NUT DETACH D L K NONE O OTHER IN INSP/MAINT 1 SO 05 4093W 62939 318152176 L291068A PILOT REPORTS TO MAINTENANCE THE RT ENGINE WAS VERY SLOW TO WARM UP TO NORMAL OIL TEMP RANGE, AND OIL PRESSURE STAYED IN HIGH RANGE. ALSO WHILE IN A DESCENT, THE OIL TEMP WOULD INDICATE BELOW OPERATING TEMP. REMOVED THERMOSTATIC BYPASS VA LVE FOR INSPECTION. UPON REMOVAL, THIS ASSY CAME OUT OF ENG CAVITY IN SEVERAL PIECES. THE CRIMP NUT WAS MISSING. AT T HIS POINT WE CONTACTED TEXTRON LYC & SPOKE WITH A TECH/REP. HE SAID TO REMOVE OIL FILTER & FILTER ATTACHMENT BACKPLATE. ALSO, TO CHECK OIL COOLER LINES IN THE EFFORT TO LOCATE CRIMPED NUT. WE DID LOCATE CRIMPED NUT IN THE OIL LINE TO OIL COOLER. 1 L 7 2 3O 3 O A20SO E14EA 1996021600658 19960216 00658 EA 1996 2 16 96ZZZX671 2 19960101 G 8530 ENGINE FRCHLD M62 PT26 3371622 EA FCD 6440 6440C5 26003 EA CYLINDERS MISOVERHAULED D L K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 17 WHILE DISASSEMBLING THE ENGINE, THE CAM, ROCKER ARM SUPPORTS, AND CAM HOUSING WERE FOUND EXCESSIVELY WORN, METAL TRANSFE R FROM THE CASE TO THE CAM, GALLING OF JOURNALS, ALL SEVEN BEARING SUPPORTS WERE DAMAGED. IT WAS ALSO NOTED THE ROCKER SUPPORTS THAT FORM A PART OF THE CAM BEARING, WERE INSTALLED IN REVERSE ORDER. ACTT 1,680 HRS. 1 L 7 1 3I 3 I A724 E216 1996021600661 19960216 00661 CE 1996 2 16 96ZZZX674 1 19960129 G 3242 16402706 DISC PARKERHANFIN BEECH 55 95C55 1152708 CE MLG CHAFE WHEELS D K NONE O OTHER IN INSP/MAINT 1 NM 03 153NL TE5 CLEVELAND BRAKE DISCS WERE REMOVED DUE TO WEAR. AFTER VERIFYING PART NUMBER AND INSTALLING NEW DISCS, AIRCRAFT WAS TAXI -TESTED. PILOT COMPLAINED THAT BRAKING WAS INADEQUATE. INSPECTION SHOWED MODERATE TO SEVERE CHAFE DAMAGE TO BOTH WHEEL S AND TIRES FROM BRAKE ASSY. AVAILL AND CLEVELAND VERIFIED BRAKE DISC PART NUMBER. MEASUREMENTS SHOW THAT NEW DISC IS MORE SHALLOW THAN OLD DISC WHICH PLACES THE FLANGE TOO CLOSE TO THE WHEEL AND TIRE ASSY. 1 L 7 2 3O 3A16 1996021600662 19960216 00662 SO 1996 2 16 96ZZZX675 1 19960113 G 5751 4244100 HINGE FITTING 4255500 PIPER PA12 PA12 7101202 SO AILERON CENTER CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 99 7561H 2380 12430 DURING INSPECTION, CRACKS WERE NOTED IN RADIUS OF FITTING ATTACHED TO AILERON SPAR. SUBMITTER SUSPECT CAUSE IS POOR ALI GNMENT OF AILERON ATTACH FITTINGS THROUGH FALSE SPAR AFTER C/W AD 51-21-02 OR, SIMPLY, WEAK AREA IN DESIGN OF AILERON FI TTING. 1 H 7 1 3O A780 1996021600663 19960216 00663 SO 1996 2 16 96ZZZX676 1 19960113 G 5751 4188100 HINGE FITTING 4255501 PIPER PA12 PA12 7101202 SO AILERON INB/OTBD CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 99 7561H 2380 12430 DURING INSPECTION, CRACKS WERE NOTED IN RADIUS OF FITTING ATTACHED TO AILERON SPAR. SUBMITTER SUSPECTS CAUSE IS POOR AL IGNMENT OF AILERON ATTACH FITTINGS THROUGH FALSE SPAR AFTER C/W AD 51-21-02 OR, SIMPLY, WEAK AREA IN DESIGN OF AILERON F ITTING. 1 H 7 1 3O A780 1996021600664 19960216 00664 CE 1996 2 16 96ZZZX677 1 19960124 G 5753 FLAP CESSNA 180 180J 2072622 CE RT/LT TE CRACKED D K NONE O OTHER IN INSP/MAINT 1 GL 15 9798G 18052298 DURING ANNUAL INSPECTION, SEVERAL CRACKS AT FLAP TRAILING EDGE RIVETS WERE FOUND. CRACKS WERE FROM .0625 INCH TO .75 IN CH LONG. AIR LOADS FROM PROP WASH AND OPERATION ABOVE STATED FLAP SPEEDS ARE SUSPECT. SUBMITTER STATED THIS AREA SHOUL D BE CLOSELY CHECKED FOR CRACKS. PART TOTAL TIME 2,150.0 HOURS. 1 H 7 1 3O 5A6 1996021600666 19960216 00666 GL 1996 2 16 96ZZZX679 3 19960124 G 6110 PROPELLER HARTZL HCC3Y HCC3YR GL HUB/BLADES MISOVERHAULED H K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 03 CK4332A FBO PURCHASED 2 EACH ZERO TSO PROPELLERS FROM A PROPELLER SHOP AND SENT TO LOCAL PROP SHOP TO HAVE THE CORRECT HUB BOLTS INSTALLED. AFTER RECEIPT BY PROP SHOP, THE FOLLOWING DISCREPANCIES WERE NOTED. HUB BOLTS INSTALLED WERE WRONG PART NU MBER. THE WRONG BOOT PART NUMBER WAS INSTALLED. THE HUB MODEL WAS INCORRECTLY STAMPED. ANGLES BETWEEN BLADES WERE OUT OF TOLERANCE (MEASURED 6/10THS OF A DEGREE, 2/10THS ALLOWED). PROPELLER WAS RETURNED TO FBO. 5 C P25EA 1996021600668 19960216 00668 SO 1996 2 16 96ZZZX681 2 19960110 G 8540 642087 STARTER ADAPTER BEECH 58 58P 1152744 CE CONT O520 TSIO520WB 17040 SO LT ENGINE FAILED D K NONE K W FLUID LOSS INADEQUATE Q C IN INSP/MAINT 1 SO 13 18FF 1365 TJ218 237585P LOST OIL PRESSURE ON LT ENGINE DUE TO LOSS OF OIL VIA BROKEN STARTER ADAPTER. AIR CONDITIONER DRIVEN PULLEY AND DRIVE S HAFT HAD BROKEN LOOSE FROM STARTER/ADAPTER ALLOWING OIL TO ESCAPE OUT DRIVE AREA. WRONG TYPE BELT INSTALLED FOR THE TYP E DRIVE PULLEYS USED. SUBMITTER RECOMMENDS ALL MAINTENANCE PERSONNEL BECOME FAMILIAR WITH CURRENT SB'S AND AD'S IN THIS AREA. 1 L 7 2 3O 3 O A23CE E8CE 1996021600672 19960216 00672 EA 1996 2 16 96ZZZX685 2 19960115 G 7414 LW12707 ADAPTER CONAER LA4 LA4250 5110320 NE LYC O540 IO540C4B5 41532 EA LT ENG MAG WRONG PART D K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 07 8435H 900 102 L2417648A THE MAG ADAPTER INSTALLED WAS THE WRONG P/N LW-12706 WHICH IS THINNER. WHEN A NEW MAG WAS INSTALLED TO REPLACE THE OLD MAG (WHICH WAS REMOVED DUE TO A BAD BEARING AND RACE), THE NEW MAG BEARINGS LASTED ABOUT 2 MINUTES. INVESTIGATION FOUND THE WRONG PART NUMBERED ADAPTER. THE MAGS HAD NEVER BEEN REMOVED FROM THE ENGINE SINCE FACTORY NEW. SUBMITTER STATED THIS LEADS ONE TO BELIEVE THE WRONG PART NUMBER WAS ORIGINALLY INSTALLED AT THE FACTORY ON THIS LEFT SIDE. THE RT SIDE HAD THE CORRECT PART. ALSO, THIS BRINGS TO ATTENTION THE LACK OF MAINTENANCE TO THE MAGS, I.E., 500-HOUR INSPECTION. 1 H 7 1 3O 3 O 1A13 1E4 1996021600673 19960216 00673 1996 2 16 96ZZZX686 2 19960101 G 7322 8211 COTTER PIN PREAIR MA45 FLOAT SHAFT MISSING B NE2R K NONE W INADEQUATE Q C IN INSP/MAINT 1 CE 07 75041009 RECEIVED CARBURETOR FROM CUSTOMER WITH THE FOLLOWING SQUAWK: 'AIRCRAFT WON'T IDLE, CAN'T SHUT DOWN WITH FUEL MIXTURE. S EEMS TO RUN AT HIGH RPM. WHEN SHUT OFF WITH SWITCH, FUEL RUNS OUT OF CARBURETOR. 6.0 HOURS SINCE INSTALLED ON AIRCRAFT '. TESTED CARBURETOR FOR FLOAT VALVE LEAKAGE, CARBURETOR OVERFLOWED. DISASSEMBLY REVEALED COTTER PIN MISSING FLOAT SHA FT ALLOWING SHAFT TO SLIDE OUT OF BRACKET. 1996021600677 19960216 00677 NM 1996 2 16 96ZZZX690 1 19960115 G 2710 CONTROL CABLE UNIVAR 108 1081 9230404 NM AILERON FRAYED D A K NONE O OTHER IN INSP/MAINT 1 GL 25 8893K 2458 1081893 DURING REPLACEMENT OF ORIGINAL CABLES, PARTS (CABLES) UNDER BALL ATTACHMENT WERE FOUND BROKEN AND FRAYED. CABLE WAS SEV ERELY KINKED DURING ORIGINAL INSTALLATION AND EVENTUALLY BROKEN. NORMAL INSPECTION WOULD NOT SHOW DAMAGE. SUBMITTER SU GGESTS REMOVAL OF COTTER PINS, 4 EACH, LEFT AND RIGHT. LIFT OUT CABLE TO INSPECT, THEN, REINSTALL IF CABLES ARE FOUND A CCEPTABLE. 1 H 7 1 3O A767 1996021600680 19960216 00680 1996 2 16 96ZZZX693 4 19960112 G 2562 MN1300 BATTERY ACK E01 ELT LEAK D A K NONE O OTHER IN INSP/MAINT 1 AL 03 WHILE PERFORMING NEW FAR 91.207(D) ELT CHECKS ON FLEET, DISCOVERED NEARLY ONE-HALF OF ACK E-01 ELT'S HAVE LEAKY BATTERIE S. ACK CALLS FOR THE USE OF DURACELL MN 1300 1.5 VOLT D-CELL BATTERIES. SUBMITTER SUGGESTS, APPARENTLY, THESE BATTERIE S CANNOT WITHSTAND ALASKA'S WINTER CLIMATE, AND COULD CAUSE CORROSION PROBLEMS INSIDE OF THE ELT. ELT BATTERY REQUIREME NTS FOR ALASKA SHOULD BE COMPATIBLE WITH OUR ENVIRONMENT INCLUDING TEMPERATURES TO MINUS 50 DEGREES. BATTERY REPLACEMEN T IS YEARLY. 1996021600682 19960216 00682 SO 1996 2 16 96ZZZX695 1 19960110 G 8120 07A19870 BRACKET PIPER PA46 PA46350P SO LYC O540 TIO540AE2A 41532 EA LT TURBO BROKEN D A K NONE O OTHER IN INSP/MAINT 1 SO 11 1818W 401 4622151 L946761A INSPECTION FOUND LEFT TURBOCHARGER SUPPORT BRACKET BROKEN JUST BELOW TOP MOUNT LUG ALLOWING WEIGHT OF TURBOCHARGER TO ON LY BE CARRIED BY LOWER ATTACHMENT. BRAKE APPEARS TO HAVE ORIGINATED FROM FACTORY WELD. SUGGEST CLOSE INSPECTIONS UNTIL FACTORY STRENGTHENS PART. 1 L 7 1 3O 3 O RT A25SO E14EA 1996021600683 19960216 00683 CE 1996 2 16 96ZZZX696 1 19960101 G 2750 BRACKET CESSNA 185 185 2072802 CE FLAP FWD PULLEY FAILED D A O OTHER F FLT CONT AFFECTED NR NOT REPORTED 1 GL 15 105NR 18503956 RIGHT FORWARD PULLEY BRACKET ON ROBERTSON EQUIPMENT FLAP CABLE ASSEMBLY FAILED RESULTING IN ASYMMETRICAL FLAP POSITION D URING FLAP EXTENSION. TOTAL TIME, 6,000 HOURS. 1 H 7 1 3O NC 3A24 1996021600684 19960216 00684 CE 1996 2 16 96ZZZX697 1 19960104 G 2910 AE1005816G0166 HOSE CESSNA 414 414A 2075907 CE RT ENGINE HYD RUPTURED H A K NONE K FLUID LOSS IN INSP/MAINT 1 WP 13 6604C 1289 414A0030 HOSE ASSEMBLY P/N AE1005816G0166 LOCATED BETWEEN THE RT HYDRAULIC PUMP P/N 9910137-2 AND HYDRAULIC FILTER ASSEMBLY P/N A N6234-2 RUPTURED APPROXIMATELY 3 INCHES FROM THE HYDRAULIC PUMP. IT APPEARED THE TOP ENGINE COWLING HAD CHAFED THROUGH THE FIRE SHIELD AND STEEL BRAIDS OF THE NOSE ASSY. SUBMITTER RECOMMENDS PROPER CLEARANCE BETWEEN HOSE ASSY AND ENGINE C OWL BE CHECKED AND MAINTAINED. 1 L 7 2 3O A7CE 1996021600687 19960216 00687 SO 1996 2 16 96ZZZX700 2 19960130 G 8530 652960 VALVE GUIDE CESSNA 337 T337G 2075726 CE CONT O360 TSIO360CB 17025 SO EXHAUST EXCESS WEAR D L K NONE O OTHER IN INSP/MAINT 1 SW 13 777NB 808 P3370180 26122R FREQUENT FINDING OF LOW COMPRESSION ON EITHER FRONT OR REAR ENGINE WITH ONLY 808 HOURS TT. EACH TIME REPAIR WAS ACCOMPL ISHED DUE TO THIS HISTORY, COMPLETE CYLINDER TEAR DOWN REVEALED EXCESS WEAR TO EXHAUST VALVES AND EXHAUST VALVE GUIDES. SUBMITTER SUSPECTS MFG DEFECT OR A MATERIAL INCOMPATIBILITY CAUSING ACCELERATED WEAR. 1 H 7 2 3O 3 O A6CE E9CE 1996021600688 19960216 00688 SO 1996 2 16 96ZZZX701 2 19960130 G 8530 646460 VALVE CESSNA 337 T337G 2075726 CE CONT O360 TSIO360CB 17025 SO EXHAUST EXCESS WEAR D K NONE O OTHER IN INSP/MAINT 1 SW 13 777NB 808 P3370180 26122R FREQUENT FINDING OF LOW COMPRESSION ON EITHER FRONT OR REAR ENGINE WITH ONLY 808 HOURS TT. EACH TIME REPAIR WAS ACCOMPL ISHED DUE TO THIS HISTORY, COMPLETE CYLINDER TEAR DOWN REVEALED EXCESS WEAR TO EXHAUST VALVES AND EXHAUST VALVE GUIDES. SUBMITTER SUSPECTS MFG DEFECT OR A MATERIAL INCOMPATIBILITY CAUSING ACCELERATED WEAR. 1 H 7 2 3O 3 O A6CE E9CE 1996022300001 19960223 00001 EA 1996 2 23 96ZZZX708 2 19960109 G 8520 LW11754 CAMSHAFT ROBSIN R22 R22BETA NM LYC O320 O320B2C 41508 EA NR 3 INTAKE WORN D K NONE O OTHER IN INSP/MAINT 1 SO 11 54BA 1145 1888 L1690239A DURING REMOVAL OF NR 1 AND NR 3 CYLINDERS FOR MAINTENANCE, INTERNAL INSPECTION OF THE CAMSHAFT AND TAPPET BODIES REVEALE D EXCESSIVELY WORN CAMSHAFT LOBE AT THE NR 3 INTAKE POSITION. THE TAPPET BODY WHICH CONTACTS AND RIDES ON THE CAMSHAFT LOBE WAS HEAVILY SPALLED ON THE FACE OF THE TAPPET BODY AS WELL. 1 G 7 1 3O 3 O H10WE E274 1996022300003 19960223 00003 SO 1996 2 23 96ZZZX710 1 19960116 G 2810 2379901 CELL PIPER PA24 PA24260 7102406 SO RT INBD TANK FUEL WEEP D K NONE B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 SW 99 8632P 244074 PILOT REPORTED FUEL SMELL. INSPECTION FOUND RT INBOARD TANK WEEPING THROUGH FABRIC OF FUEL CELL ENOUGH TO GENERATE SMEL L, BUT NOT ENOUGH TO LEAK OR CAUSE EXCESSIVE FUEL STAINS. 1 L 7 1 3O 1A15 1996022300011 19960223 00011 EA 1996 2 23 96ZZZX718 2 19960126 G 8530 7380685 PUSH ROD CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA NR 2 CYL EXH VLV DEFECTIVE D K NONE O OTHER IN INSP/MAINT 1 SO 15 68919 2400 15282402 L1764515 ON INSPECTION OF AD 95-03-10, PUSH ROD OF ACCEPTABLE PART NUMBER PER AD WAS FOUND TO HAVE A LOOSE BALL END AND TUBE WAS MUSHROOMED. THIS ENGINE WAS DUE FOR OVERHAUL IN 42 HOURS AT NEXT 100-HOUR INSPECTION, AND THE HIGH TIS WAS SUSPECT CAUS E OF DEFECT. 1 H 7 1 3O 3 O NT 3A19 E223 1996022300012 19960223 00012 CE 1996 2 23 96ZZZX719 1 19960101 G 3213 50411081 BEARING CESSNA 421 421C 2076016 CE LT MLG LEG WORN D K NONE O OTHER IN INSP/MAINT 1 SW 99 146TJ 1858 421C0500 AIRCRAFT OWNER REPORTED HOUR METER RUNNING CONSTANTLY. FOUND LEFT MLG EXTENDED FULLY, ALLOWING SQUAT SWITCH TO BE UNACT UATED AND HOUR METER TO RUN CONSTANTLY. REMOVED LOWER LEG AND FOUND INNER, UPPER BEARING WORN/GALLED AND BINDING IN BAR REL. THE AIRCRAFT HAS 1,857.8 HOURS TOTAL TIME AND AD 90-02-13 IS DUE AT 2,128.0 HOURS. SUBMITTER RECOMMENDATION IS TO DECREASE NUMBER OF HOURS AT INITIAL INSPECTION OR TO MAKE REPLACEMENT MANDITORY. 1 L 7 2 3O A7CE 1996022300013 19960223 00013 CE 1996 2 23 96ZZZX720 1 19960101 G 3213 50411082 BEARING CESSNA 421 421C 2076016 CE LT MLG LEG GALLED D K NONE O OTHER IN INSP/MAINT 1 SW 99 146TJ 1858 421C0500 AIRCRAFT OWNER REPORTED HOUR METER RUNNING CONSTANTLY. FOUND LEFT MLG EXTENDED FULLY, ALLOWING SQUAT SWITCH TO BE UNACT UATED AND HOUR METER TO RUN CONSTANTLY. REMOVED LOWER LEG AND FOUND INNER, UPPER BEARING WORN/GALLED AND BINDING IN BAR REL. THE AIRCRAFT HAS 1,857.8 HOURS TOTAL TIME AND AD 90-02-13 IS DUE AT 2,128.0 HOURS. SUBMITTER RECOMMENDATION IS TO DECREASE NUMBER OF HOURS AT INITIAL INSPECTION OR TO MAKE REPLACEMENT MANDITORY. 1 L 7 2 3O A7CE 1996022300019 19960223 00019 CE 1996 2 23 96ZZZX726 1 19960201 G 2460 6041H144 RELAY CUTLERHAM CESSNA 208 208B 2073701 CE STANDBY POWER FAILED D K NONE O OTHER IN INSP/MAINT 1 NE 01 958FE 208B0071 STANDBY POWER REPORTED INOPERATIVE. NO POWER OUTPUT TO BUS FROM ALTERNATOR. FOUND DEFECTIVE STANDBY POWER RELAY. THE RELAY SOLENOID SHAFT HAD DISCONNECTED FROM THE CONTACTOR BAR. SUBMITTER STATED THIS IS THE 4TH OCCURRENCE ON DIFFERENT SERIAL NUMBERED AIRCRAFT. 1 H 7 1 3T A37CE 1996022300021 19960223 00021 CE 1996 2 23 96ZZZX728 1 19960125 G 5521 043200121 SPAR CESSNA 150 150L 2071826 CE OTBD ELEV HINGE CRACKED D A K NONE O OTHER IN INSP/MAINT 1 GL 05 18519 4838 15073909 AIRCRAFT USED AS A TRAINER. ELEVATOR HINGE (RIB) FOR BOLT HOLE BECAME WORN. BUSHING AND BEARING BECAME WORN. BOLT WAS FOUND WORN. BRACKET BECAME WORN. BOLT HOLE IN RIB WAS WORN EXCESSIVELY (.25 INCH OR BETTER). WITH OUTBOARD RIB WORN , THIS PUT MORE SUPPORT ON BRACKET WHICH PUT MORE STRESS ON THE SPAR WHICH CAUSED SPAR TO CRACK. SUBMITTER RECOMMENDS O PEN ELEVATOR EVERY 1,000 HOURS TO INSPECT SPAR. 1 H 7 1 3O 3A19 1996022300116 19960223 00116 SW 1996 2 23 96ZZZX732 1 19960108 G 6410 206016201127 BLADE BELL 206 206L1 1182107 SW T/R BEARING CRACKED B ZV1R K NONE O OTHER IN INSP/MAINT 1 SW 03 2618 1761 CS4768 45503 TAIL ROTOR BLADES, 2 EACH, HAVE BEARINGS CRACKED. TSI, 739.1 HOURS. 1 G 7 1 3U H2SW 1996022300117 19960223 00117 SW 1996 2 23 96ZZZX733 1 19960108 G 6410 206016201127 BLADE BELL 206 206L1 1182107 SW T/R BEARING CRACKED B ZV1R K NONE O OTHER IN INSP/MAINT 1 SW 03 2618 1761 CS4769 45503 TAIL ROTOR BLADES, 2 EACH, HAVE BEARINGS CRACKED. TSI, 739.1 HOURS. 1 G 7 1 3U H2SW 1996022300118 19960223 00118 SW 1996 2 23 96ZZZX734 1 19960113 G 6230 206010335001 LINK ASSY BELL 206 206L1 1182107 SW PYLON WORN B ZV1R K NONE O OTHER IN INSP/MAINT 1 SW 03 5007F 268 3126 45186 DRIVE LINK ASSY HAS PLAY IN EXCESS OF .25 INCH AT TWO PLACES. SEE BELL MM L3, FIGURE 62.21. WORN BEARINGS AND SPACERS. 1 G 7 1 3U H2SW 1996022300119 19960223 00119 SW 1996 2 23 96ZZZX735 1 19960111 G 6230 206040576103 BEARING BELL 206 206L3 1182108 SW MAST FAILED B WG3R K NONE O OTHER IN INSP/MAINT 1 WP 27 6516K 1991 ZV1401 51391 REMOVED MAST BEARING DUE TO MAST BEARING OUTER RACE FAILURE. INSTALLED NEW BEARING, PN 206-040-576-105, SN MB349. FAIL ED BEARING, TSN 1991.1 HOURS. 1 G 7 1 3U H2SW 1996022300123 19960223 00123 NE 1996 2 23 96ZZZX739 1 19960109 G 7120 7630907017044 MOUNT SKRSKY S76 S76A 8143006 NE FWD RT ENG COMP HOLES WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 1547N 760088 DURING SCHEDULED INSPECTION, FOUND THE ATTACHMENT HOLE IN OUTSIDE RT FWD TRIPOD SUPPORT TUBES WORN BEYOND LIMITS. 1 G 7 2 3U H1NE 1996022300124 19960223 00124 NE 1996 2 23 96ZZZX740 1 19960109 G 7120 7630907017043 MOUNT SKRSKY S76 S76A 8143006 NE FWD LT ENG COMP HOLES WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 1547N 760088 DURING SCHEDULED INSPECTION FOUND ATTACHMENT HOLES IN OUTSIDE LT FWD TRIPOD SUPPORT TUBES WORN BEYOND LIMITS. 1 G 7 2 3U H1NE 1996022300130 19960223 00130 GL 1996 2 23 96ZZZX746 2 19960104 G 7321 25490923 FUEL CONTROL 23005290 SKRSKY S76 S76 8143010 NE ALLSN 250C 250C30 03013 GL NR 1 ENGINE WATER CONTAM B ALGR A UNSCHED LANDING R PARTIAL RPM/PWR LOSS HO HOVERING 1 SW 03 701AL 5992 331729 760238 890101S DURING FLIGHT CHECK/HOVER, COMPRESSOR STALLED. REMOVED FROM ENGINE, INSPECTED PX-AIR CIRCUIT ON FUEL CONTROL, FOUND EXC ESSIVE AMOUNT OF WATER. 1 G 7 2 3U 3 U H1NE E1GL 1996022300384 19960223 00384 EU 1996 2 23 96ZZZX748 1 19960125 G 3230 C23554104 ACTUATOR AMD FALC10 FALCON10 2730101 EU RT MLG DEFECTIVE D L O OTHER J WARNING INDICATION AP APPROACH 1 GL 23 191MC 9828 23 45 30 UNABLE TO OBTAIN RT MLG GREEN LIGHT. FLYBY INDICATED GEAR DOWN - UNABLE TO VERIFY LOCKED. RT MLG FOLDED ON LANDING. I NVESTIGATION REVEALED RT MLG DOWNLOCK WAS NOT LOCKING. RT MLG ACTUATOR DEFECTIVE. 2 L 7 2 4F A33EU 1996022300385 19960223 00385 NE 1996 2 23 96ZZZX749 2 19960117 G 7210 7757964 TAB WASHER HAMSTD GC49 SAAB SF340 SF340A 7850100 EU GE CT7TP CT75A 30030 NE DRV GR RET NUT BROKEN B S SI3R K NONE O OTHER IN INSP/MAINT 1 NE 03 95MQ UDAG0356 340A095 GEARBOX RETURNED FOR: PROP SHAFT SEAL RUNNER HAS CADMIUM PLATING MISSING. AT DISASSEMBLY, DISCOVERED TABBED WASHER WAS BROKEN INTO 3 PIECES. DRIVE GEAR RETENTION NUT WAS REMOVED WITH NO TORQUE APPLIED. THE TABBED WASHER HAS BEEN SUPERSE DED BY 7895922. 2 L 7 2 4T 4 T RT A52EU E8NE 1996022300390 19960223 00390 SO 1996 2 23 96ZZZX754 1 19960128 G 5610 1159SCB31023 WINDSHIELD PPG GULSTM G1159 G1159A 3970109 SO COPILOT CRACKED E B A EMER. DESCENT UNSCHED LANDING O OTHER CR CRUISE 1 SW 05 300WY 3633 85H616058 427 AT CRUISE, FL 410, WITH WINDSHIELD HEAT ON, OUTER PANE OF COPILOT'S WINDSHIELD SPIDER-CRACKED. THE CREW BEGAN A DESCENT AND LANDED AT THE NEAREST AIRPORT, INSPECTED THE WINDOW AND WITH FLIGHT MANUAL PROVISO, FLEW TO HOME BASE. NO PRIOR WA RNING OR INDICATION OF FAILURE WAS PRESENT. 2 L 7 2 4F A12EA 1996022300391 19960223 00391 CE 1996 2 23 96ZZZX755 1 19960105 G 2434 15838162 ROTOR ASSY 30B10719A LEAR 35 35A 5170602 CE DC GENERATOR FAILED B BHKR O OTHER H ELECT. POWER LOSS-50 PC CR CRUISE 1 EA 21 190DA 49 1691 156 DC GENERATOR SOLD AS OVERHAULED EXCHANGE UNIT. FAILED IN-FLIGHT. BEARINGS DID NOT FAIL. SUSPECT THE ROTOR ASSY RETAIN ING BAND/BANDS SEPARATED CAUSING SEVERE DAMAGE TO THE GENERATOR SUB-ASSEMBLIES. FUTURE OVERHAULS/REPAIRS WILL REQUIRE 1 0X MAG AND PROBE INSPECTION TO ENSURE INTEGRITY OF SPOT WELDS. 2 L 7 2 4F A10CE 1996022300394 19960223 00394 SW 1996 2 23 96ZZZX758 1 19960123 G 3230 750069501 SHAFT GULSTM 690TP 690A 0141722 SW NLG DRAG BRACE CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 15 53RF 11153 REMOVED SHAFT DURING 5-YEAR GEAR INSPECTION. FOUND CRACKED AT ATTACH BOLT HOLES FOR DRAG BRACE ON NOSE LANDING GEAR. T HIS SHAFT IS NOT PART OF GEAR INSPECTION, BUT SHOULD BE. SUSPECT IMPROPER DRAG BRACE PRELOAD AND/OR HARD NOSE LANDINGS OVER A PERIOD OF TIME. SUBMITTER SUGGESTED PART SHOULD BE REMOVED AND INSPECTED DURING ANY NOSE GEAR REPAIR AND DURING 5-YEAR GEAR INSPECTION. 1 H 7 2 3T 2A4 1996022300396 19960223 00396 EU 1996 2 23 96ZZZX760 1 19960117 G 5400 HC361C0043000 BRACKET BAG BAE146 BAE146200A 1500266 EU NR 4 PYLON BROKEN B A6WR K NONE O OTHER IN INSP/MAINT 1 GL 31 292UE E2087 DURING SCHEDULED INSPECTION, FOUND BOTH LEFT SIDE BRACKETS SUPPORTING PRESSURE REGULATING/ISOLATION VALVE BROKEN IN NR 4 PYLON. REPLACED BRACKETS. REFERENCE: OPERATOR CONTROL NR A6WR95059. 2 H 7 4 4F RT A49EU 1996022300397 19960223 00397 EU 1996 2 23 96ZZZX761 1 19960117 G 2710 HC270H0135006 CONTROL CABLE BAG BAE146 BAE146200A 1500266 EU AILERON CORRODED B A6WR K NONE O OTHER IN INSP/MAINT 1 GL 31 292UE E2087 DURING SCHEDULED INSPECTION FOUND AILERON INTERCONNECT CABLES CORRODED AT WING ROOT PULLEYS. REPLACED CABLES. REFERENC E: OPERATOR CONTROL NR A6WR95063. 2 H 7 4 4F RT A49EU 1996022300398 19960223 00398 SW 1996 2 23 96ZZZX762 1 19960201 G 3260 WIRE GULSTM 560 560 0141402 SW RT WS 54.07 CHAFED B CNQR O OTHER N FALSE WARNING NR NOT REPORTED 1 CE 07 502T 3166 5600153 FLIGHT CREW REPORTED A GEAR UNSAFE LIGHT WITH GEAR DOWN AND THREE GREEN (NO HYDRAULIC POWER ON LIGHT), ANTI-SKID INOPERA TIVE LIGHT ON AND GEAR HORN SOUNDING. FOUND WIRING CHAFED/DAMAGED AT RT WS 54.07 RIB FEED-THROUGH IN THE TRAILING EDGE. REPAIRED WIRING, SECURED AND PROTECTED IAW CESSNA SB 560-24-15, REVISION 1. 1 H 7 2 3O 6A1 1996022300402 19960223 00402 WP 1996 2 23 96ZZZX766 2 19960108 G 7250 31038391 ROTATING SEAL 31070852 GARRTT TPE331 TPE33112UAR 01514 WP 1ST STAGE TURB FLANGE CRACKED B DSCR K NONE O OTHER IN INSP/MAINT 1 GL 25 9888 9233151431 P70015 DURING SCHEDULED HOT SECTION INSPECTION, FOUND PART CRACKED AT SEAL FLANGE. NO SIGNS OF ABNORMAL OPERATION WERE EVIDENT . SUBMITTER STATED THIS IS A CRITICAL LIFE-LIMITED COMPONENT. LIMIT IS 10,000 CYCLES. THIS IS THE 25TH MALFUNCTION/DE FECT REPORT SUBMITTED BY THIS REPAIR STATION ON THIS PROBLEM. CYCLES, 10,291. 4 T E4WE 1996022300403 19960223 00403 WP 1996 2 23 96ZZZX767 1 19960126 G 3246 2601483 BOLT BENDIX 2608891 DOUG DC9 DC982 3022082 WP WHEEL FAILED D K NONE O OTHER IN INSP/MAINT 1 SW 09 FATIGUE RELATED FAILURE OF MD80 WHEEL TIE BOLTS. INSUFFICIENT TIE BOLT PRELOAD TORQUE. SUBMITTER STATED TO USE SNUG AN GLE TORQUE METHOD. 2 L 7 2 4F A6WE 1996022300404 19960223 00404 WP 1996 2 23 96ZZZX768 1 19960123 G 2612 355900575 FIRE LOOP CVAC 440 440 2422902 WP NR 1 ENG NACELLE CHAFED C OGCB K NONE N FALSE WARNING IN INSP/MAINT 1 GL 23 171FL 318 FIRE LOOP HAD 3 CHAFE MARKS CAUSING A FALSE FIRE WARNING, LIGHT AND BELL TO SOUND. FOUND LOOSE MOUNTING CLAMP ON FIRE L OOP, LETTING LOOP CHAFE ON SCAT TUBING. FOUND WEAK MOUNTING CLAMP. REPLACED WITH A NEW CLAMP. REFERENCE: OPER CONTRO L NR DJSA95. 2 L 7 2 4R 6A6 1996022300406 19960223 00406 CE 1996 2 23 96ZZZX770 1 19960123 G 5610 1013840258 WINDSHIELD BEECH 300 300BEECH 1152930 CE COPILOT CRACKED D K NONE O OTHER NR NOT REPORTED 1 NM 09 84 88H0403469 FF19 COPILOT'S WINDSHIELD CRACKED IN CENTER OF WINDOW - TOP-TO-BOTTOM (OUTSIDE PLY ONLY). SUBMITTER STATED IT LOOKS LIKE A B UILD-UP OF STATIC ELECTRICITY. 2 L 7 2 4T A24CE 1996022300408 19960223 00408 SO 1996 2 23 96ZZZX772 2 19960101 G 8530 5397402 SHAFT CESSNA 340 340A 2076405 CE CONT O520 TSIO520NB 17040 SO ROCKER SHAFT WORN B ADKR K NONE O OTHER IN INSP/MAINT 1 SW 05 6824Z 1286 340A1202 276659R DURING REMOVAL OF A CYLINDER FOR REPAIR, THE ROCKER ARM SHAFTS WERE FOUND WORN DOWN .035 INCH ON ONE SIDE OF THE SHAFT. THIS CONDITION WAS FOUND ON ALL 12 SHAFTS FOR THIS ENGINE. 1 L 7 2 3O 3 O 3A25 E8CE 1996022300679 19960223 00679 CE 1996 2 23 96ZZZX773 1 19960130 G 2520 521912514 SEAT CESSNA 402 402C 207590R CE PASSENGER SEPARATED E A K NONE O OTHER IN INSP/MAINT 1 WP 19 2610Z 107 402C0068 WHILE LOADING PASSENGERS FOR A ROUTINE FLIGHT, ONE PASSENGER (WEIGHT, APPROX 200 POUNDS) PUSHED HIMSELF BACK AGAINST THE SEAT BACK AND THE SEAT SEPARATED FROM ITS BASE. SEATS INSTALLED IN THIS AIRCRAFT ARE THE 'ENVIROFORM' SEATS THAT HAVE BEEN STC'D TO ELIMINATE CESSNA MEB 87-9, REVISION 2, DATED 12-16-88. UPON INSPECTION OF THIS SEAT, DETERMINED THAT APPR OXIMATELY 75 PERCENT OF THE MATERIAL USED TO BOND THE SEAT TO ITS BASE WAS STUCK TO THE SEAT BUCKET. VERY LITTLE BONDIN G MATERIAL WAS FOUND ON THE SEAT BASE. STRONGLY RECOMMEND FREQUENT INSPECTION OF THESE SEATS AND IF ANY CRACKS OR OTHER ABNORMALITIES ARE FOUND, THAT CESSNA SERVICE KIT 421-135A BE INSTALLED AS SOON A POSSIBLE. 1 L 7 2 3O A7CE 1996022300680 19960223 00680 CE 1996 2 23 96ZZZX774 1 19960108 G 2820 05160161 LINE CESSNA 172 172P 2072436 CE LT AFT TANK FEED CLOGGED D A K NONE O OTHER IN INSP/MAINT 1 SW 07 52119 6800 17274418 TWO SEPARATE OCCURRENCES OF THE ENGINE 'SURGING' AT FULL POWER WITH LESS THAN 16 GALLONS TOTAL FUEL ON BOARD. COULD NOT DUPLICATE ON THE GROUND. WITH FULL TANKS, COULD NOT DUPLICATE AT NORMAL FLIGHT ATTITUDES. ENTIRE FUEL SYSTEM DISASSEM BLED AND CLEANED, FOUND INSECT NEST AT AFT LEFT FUEL TANK FEED LINE. RESEARCHED LOGS, WINGS WERE REMOVED DUE TO ACCIDEN T (5-88), AIRCRAFT WAS REPAIRED AND RETURNED TO SERVICE (1-89). SUSPECT INSECT NEST HAS BEEN THERE SINCE '89. (AIRCRAF T TT AT WING REMOVAL, 3,814.0 HOURS. CURRENT AIRCRAFT TT, 6,800.0 HOURS. 1 H 7 1 3O NT 3A12 1996022300681 19960223 00681 EA 1996 2 23 96ZZZX775 2 19960201 G 8530 7380685 PUSHROD LYC O235 O235L2C 41505 EA CYLINDER BALL SEPARATION D A K NONE E VIBRATION/BUFFET IN INSP/MAINT 1 WP 11 L1840015 370 HOURS AFTER OVERHAUL, ENGINE VIBRATION WAS DETERMINED TO BE CAUSED BY BALL END SEPARATION FROM PN 73806-85 PUSHROD. PUSHROD WAS REPLACED AND ENGINE VIBRATION WAS BACK TO NORMAL. AD'S 80-25-02R2 AND 95-03-10 DO NOT PERTAIN TO THESE PUS HRODS. 3 O E223 1996022300682 19960223 00682 SO 1996 2 23 96ZZZX776 1 19960129 G 7110 9856212 COWL SEAL 9856202 PIPER PA32 PA32301T 7103209 SO ENG TOP COWL CHAFE PROP LEAD B S A EHHR K NONE O OTHER IN INSP/MAINT 1 EA 17 8210H 2100 32R8229064 AS AIRCRAFT ACCUMULATES HOURS, THE LONG HEAVY ENGINE SAGS ALLOWING TOP COWL PROP SHAFT SEAL TO RUB PROP SHAFT. THIS RUB HAS REMOVED ALL INSULATION FROM PROP DEICE LEADS RUNNING ALONG PROP SHAFT EXPOSING THE BARE WIRES. TRIED PUSHING UP ON NOSE OF COWL AND THEN TIGHTENING COWL TO FUSELAGE SCREWS. THIS IS A TEMPORARY FIX FOR THE ATTACH SCREW HOLES ARE ELONG ATED WHICH ALLOWS THE COWL TO AGAIN SAG OVER A SHORT PERIOD OF TIME. SUBMITTER STATED EITHER THE SEAL SHOULD BE REMOVED OR THE LOWER COWL HAVE A SUPPORT ADDED. 1 L 7 1 3O A3SO 1996022300684 19960223 00684 SO 1996 2 23 96ZZZX778 2 19960101 G 7322 CARBURETOR CESSNA 172 172H 2072424 CE CONT O300 O300A 17022 SO CARB THROAT MOUSE FOD D A A UNSCHED LANDING Y ENGINE STOPPAGE NR NOT REPORTED 1 NE 05 2754L 17255954 INVESTIGATION AFTER ENGINE FAILURE DISCOVERED A MOUSE LODGED IN THE CARBURETOR THROAT. THE DESIGN OF THE CABIN/CARBURET OR HEAT SYSTEM LEAVES AN OPEN PATH FROM THE CARBURETOR AIR BOX TO THE CABIN HEAT CONTROL VALVE ASSEMBLY. MICE CAN ENTER VIA THE CABIN OR THE ENGINE COMPARTMENT. SUBMITTER STATED SOME TYPE OF SCREEN COULD PREVENT THIS. 1 H 7 1 3O 3 O NT 3A12 E253 1996022300685 19960223 00685 EA 1996 2 23 96ZZZX779 2 19960123 G 7322 13662 FLOAT BRACKET MA45 CESSNA 177 177 2073704 CE LYC O360 O360A1F6 41514 EA CARBURETOR BROKEN B S SL5R A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CR CRUISE 1 NE 03 34102 500 75020609 17701642 L1573636A ENGINE LOST POWER IN CRUISE FLIGHT. AFTER SAFE LANDING AT NEARBY AIRPORT, REMOVED CARBURETOR AND DISASSEMBLED. FOUND FLOAT BRACKET BROKEN IN BEND RADIUS ALLOWING EXCESS FUEL TO ENTER CARBURETOR WHEN FLOAT VALVE COULD NOT SEAT. BEND RADI US OF FLOAT BRACKET APPEARED TO BE 90 DEGREES. SUBMITTER STATED LARGER BEND RADIUS MIGHT PREVENT UNUSUAL STRESSES IN TH E METAL REDUCING THE POSSIBILITY OF BREAKAGE. 1 H 7 1 3O 3 O NT A13CE E286 1996022300686 19960223 00686 EA 1996 2 23 96ZZZX780 2 19960125 G 7210 BEARING BEECH 90 65A90 1152908 CE PWA PT6 PT6A20 52043 EA RED GEAR 1ST STG FAILED D K NONE Y ENGINE STOPPAGE NR NOT REPORTED 1 CE 01 5WG LJ289 PCE21824 FIRST STAGE REDUCTION GEAR BEARING FAILED CAUSING GEAR TO BIND OR SEIZE CAUSING POWER TURBINE SHAFT TO SHEAR CAUSING ENG INE TO STOP. CAUSE OF BEARING FAILURE UNKNOWN. 1 L 7 2 3T 3 T 3A20 E4EA 1996022300689 19960223 00689 SO 1996 2 23 96ZZZX783 1 19960124 G 3260 487869 SWITCH PIPER PA23 PA23250 7102308 SO NLG OUT OF ADJUST E O OTHER N FALSE WARNING AP APPROACH 1 GL 03 54231 277554025 PILOT COULD NOT GET DOWN AND LOCKED INDICATION OF THE NOSE GEAR. UPON SUCCESSFUL LANDING (GEAR WAS, IN FACT, DOWN AND L OCKED), IT WAS NOTED THE SWITCH AND BRACKET ASSEMBLY WERE NOT MAKING CONTACT. SWITCH IS ADJUSTABLE AND SUBMITTER SUGGES TS CAREFUL INSPECTION BE MADE AT SCHEDULED INSPECTIONS TO VERIFY SWITCH IS MAKING POSITIVE CONTACT. 1 L 7 2 3O 1A10 1996022300691 19960223 00691 SO 1996 2 23 96ZZZX785 1 19960125 G 3231 91929 SWITCH LSM100297 PIPER PA24 PA24260 7102406 SO NLG DOOR FAILED D A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 SO 25 8665P 138 244112 PILOT REPORTED SELECTING GEAR UP AND HAVING GEAR SOLENOID AND LIGHTS' CIRCUIT BREAKER TRIP. AIRCRAFT HAS A WHOLLY COWL CONVERSION FROM LOPRESTI. PILOT EXPERIENCED REDUCED RUDDER CONTROL, BUT WAS ABLE TO MAKE AN UNEVENTFUL LANDING. AIRCRA FT WAS FOUND TO HAVE HAD THE NOSE GEAR DOORS CLOSE ON THE EXTENDED NOSE GEAR CAUSING THE CIRCUIT BREAKER TO OVERLOAD AND REDUCING RUDDER CONTROL THROUGH NOSE GEAR INTERCONNECT. FOUND THE UP-LIMIT SWITCH ON NOSE GEAR DOOR MOTOR HAD FAILED G IVING A FALSE READING TO THE RELAY BOX ALLOWING THE DOORS TO GO OUT OF SEQUENCE. 1 L 7 1 3O 1A15 1996022300692 19960223 00692 EA 1996 2 23 96ZZZX786 2 19960201 G 8530 73806V PUSHROD LYC O235 O235L2C 41505 EA CYLINDER WRONG PART D K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 11 L1610415 ENGINE WAS OVERHAULED BY FACTORY 2-20-95. DURING STC'D CONVERSION PRIOR TO INSTALLATION IN AIRCRAFT, ALL EIGHT PUSHRODS WERE FOUND TO BE P/N 73806 'V' PUSHRODS. SUBMITTER STATED AD 95-03-10 DOES NOT COVER THIS ENGINE (BUT SHOULD). FACTOR Y WAS NOTIFIED AND REPLACEMENT PUSHRODS INSTALLED. 3 O E223 1996022300693 19960223 00693 SO 1996 2 23 96ZZZX787 1 19960131 G 6120 554070 CONTROL CABLE PIPER PA31 PA31P 7103120 SO RT PROP CONTROL BROKEN B EKIR K NONE O OTHER NR NOT REPORTED 1 WP 07 110SK 4742 31P7630006 RIGHT PROPELLER CONTROL CABLE BROKE ABOUT 12 INCHES AFT OF GOVERNOR ATTACHMENT. NO PRIOR INDICATION OF CABLE FAILURE. P ROPELLER CONTROL OPERATED SMOOTHLY. 1 L 7 2 3O A8EA 1996022300694 19960223 00694 CE 1996 2 23 96ZZZX788 1 19960201 G 2731 1695240871 ROD BEECH 23 C23 1151242 CE TAB PUSH/PULL END DETACHED B AKGR K NONE O OTHER IN INSP/MAINT 1 CE 05 5167M 6932 M2043 DURING PRE-FLIGHT, THE ELEVATOR TRIM TAB TO TRIM ACTUATOR PUSH/PULL ROD FOUND WITH AFT CLEVIS PUSHED OUT OF ROD SHEARING 2 RIVETS. ROD WAS ICE FILLED DUE TO NO DRAIN HOLES TO PERMIT WATER TO DRAIN. SUBMITTER SUGGESTS PUSH/PULL ROD ASSY BE MODIFIED TO LET WATER DRAIN OUT. 1 L 7 1 3O A1CE 1996022300695 19960223 00695 EA 1996 2 23 96ZZZX789 2 19960111 G 8520 LW16514 CAMSHAFT PIPER PA44 PA44180 7104402 SO LYC O360 O360E1A6 41514 EA GOV DRV END CRACKED D K NONE O OTHER IN INSP/MAINT 1 WP 17 2199Z 1020 447995297 L52672T AT AN ANNUAL INSPECTION, THE GOVERNOR DRIVE COVER PLATE WAS REMOVED IN AN ATTEMPT TO STOP AN OIL LEAK. THIS EXPOSES THE FWD END OF THE CAM AND A CRACK WAS DISCOVERED EXTENDING FROM A SHARP CORNER IN THE KEYWAY. RECOMMEND A MODIFIED KEYWAY WITH A RADIUS IN THE CORNERS TO RELIEVE STRESS AREA. ALSO, RECOMMEND PERIODIC INSPECTION OF AREA. 1 L 7 2 3O 3 O A19S0 E286 1996022300703 19960223 00703 CE 1996 2 23 96ZZZX797 1 19960129 G 5740 50110241 FITTING CESSNA 402 402C 207590R CE RT REAR WING CORRODED D K NONE O OTHER IN INSP/MAINT 1 SO 17 6838A 4047 402C0470 AT ANNUAL INSPECTION, CORROSION WAS FOUND ON THE BOTTOM RIGHT REAR WING SPAR ATTACH FITTING. THE FITTING WAS REPLACED. 1 L 7 2 3O A7CE 1996022300704 19960223 00704 SO 1996 2 23 96ZZZX798 2 19960126 G 8540 63217H QUILL SHAFT CESSNA 421 421A 2076012 CE CONT O520 GTSIO520D 17032 SO LT ENG DRV GEAR FAILED B EKIR A UNSCHED LANDING Y ENGINE STOPPAGE CL CLIMB 1 WP 07 200CH 1320 481 421A0102 219168R LEFT ENGINE QUIT ON CLIMB-OUT. PROP FEATHERED AIRCRAFT, MADE SAFE LANDING. FOUND HOLE IN CASE UNDER INTERCOOLER FROM F AILED CONNECTING ROD. PROP TURNS FREELY. ENGINE NOT TORN DOWN AT THIS DATE. SUBMITTER SUSPECTS QUILL SHAFT FAILED ALL OWING ENGINE TO OVERSPEED. WILL SUBMIT FOLLOW-UP M OR D WHEN ENGINE IS TORN DOWN. 1 L 7 2 3O 3 O A7CE E7CE 1996022300709 19960223 00709 SO 1996 2 23 96ZZZX803 1 19960122 G 3320 BULB GULSTM G1159 G1159B 3953535 SO CABIN BURNING END D K NONE O OTHER IN INSP/MAINT 1 SO 03 48EC 009 AEROSPACE LIGHTING AD'S HAVE BEEN ISSUED, BUT THIS HAS NOT CORRECTED THE PROBLEM. FLUORESCENT BULB ENDS ARE STILL BURNI NG OFF. SUBMITTER SUGGESTS POSSIBLE CABIN FIRE COULD RESULT. 2 L 7 2 4F RT A12EA 1996022300710 19960223 00710 EU 1996 2 23 96ZZZX804 1 19960118 G 2435 23080005 STARTER/GEN BRAERO DH125 BAE125800A 1500285 EU LT START/GEN BEARING FAILED H A UNSCHED LANDING E VIBRATION/BUFFET CR CRUISE 1 GL 07 600LS 607 3031 NA0411 AIRCRAFT INCURRED VIBRATION IN-FLIGHT CAUSING DEVIATION TO NEAREST AIRPORT. UPON INVESTIGATION, FOUND LEFT STARTER/GENE RATOR BEARING DETERIORATED. STARTER/GENERATOR HAD LATEST BEARING INSTALLED SB 23080-XXX-24-01. REPLACED STARTER/GENERA TOR WITH OVERHAULED UNIT. OPS CHECK GOOD. 2 L 7 2 4F RT A3EU 1996022300711 19960223 00711 SO 1996 2 23 96ZZZX805 1 19960123 G 2820 6010026D0150 HOSE GULSTM G1159 GIV 3980115 SO FUEL PUMP LEAKING H K NONE K FLUID LOSS IN INSP/MAINT 1 SO 11 971L 3431 1116 PERFORMED A 72-MONTH INSPECTION. DURING DOWN TIME, AIRCRAFT WAS DEFUELED AFTER COMPLETION OF INSPECTION. WHEN THE AIRC RAFT WAS REFUELED, ALL 4 FUEL BOOST PUMP VAPOR HOSES WERE NOTED LEAKING UNDER STATIC PRESSURE. CUSTOMER BULLETIN NR 15 IS ASSOCIATED WITH THESE NOSES, BUT DOES NOT INCLUDE THIS PRODUCTION NR 1116. 2 L 7 2 4F RT A12EA 1996022300712 19960223 00712 EU 1996 2 23 96ZZZX806 1 19960113 G 3231 283002401 CONTROL ROD ISRAEL 1124 1124A 4500103 EU NLG DOOR BROKE H K NONE O OTHER NR NOT REPORTED 1 GL 25 730CA 5100 295 LEFT NOSE GEAR DOOR VERTICAL CONTROL ROD - ROD END BROKE OFF WHEN GEAR LOWERED. ROD END CRACKED IN THREAD LINE WHERE SC REWED INTO ACTUAL ROD END. DARK LINE ON CROSS SECTION INDICATED CRACK NOT NEW. SUBMITTER STATED STRESS POSSIBLE FROM D OORS BEING ADJUSTED TOO TIGHT. REPLACED ROD WITH NEW PART AND ADJUSTED IAW MM 32-20-00, PAGE 217. 2 M 7 2 4F A2SW 1996022300713 19960223 00713 CE 1996 2 23 96ZZZX807 1 19960104 G 5312 551104013 BOX CESSNA 500 500CESSNA 2076602 CE INST PANEL CRACKED B R2JR K NONE O OTHER IN INSP/MAINT 1 EA 21 891CA 6541 6541 5000168 WHILE PERFORMING PHASE 1-5 INSPECTION, FOUND CRACK ON FORWARD PRESSURE BULKHEAD BOX. CRACK WAS AT RIVET WHICH CONNECTS INSTRUMENT PANEL ANGLE TO BULKHEAD. FACTORY HAD NO APPROVED REPAIR. DER FORM 8110 OBTAINED FOR REPAIR. SUBMITTER STAT ED THIS IS THE SECOND AIRCRAFT FOUND BY THIS STATION WITH THE SAME EXACT CRACKED PRESSURE BULKHEAD WITHIN THE LAST YEAR. 1 L 7 2 4F A22CE 1996022300714 19960223 00714 SO 1996 2 23 96ZZZX808 1 19960104 G 5620 56676002 WINDOW PIPER PA42 PA42 7104202 SO FUSELAGE SIDE CRACKED B R2JR K NONE O OTHER IN INSP/MAINT 1 EA 21 18AF 3608 428001063 WHILE PERFORMING PIPER SB 984, INSPECTION OF FUSELAGE SIDE WINDOWS, FOUND ALL WINDOWS HAD CRACKS IDENTIFIED IN SB 984. A LL BUT 3 WERE BEYOND LIMITS. ALL COCKPIT AND SIDE WINDOWS WERE REPLACED WHEN PARTS BECAME AVAIILABLE. SUBMITTER SUGGES TS C/W MANDATORY SB 984 AS SOON AS POSSIBLE. CRACKS ARE NOT VISIBLE WITHOUT PROPER INSPECTION TOOL CALLED OUT IN SERVIC E BULLETIN. 1 L 7 2 4T A23SO 1996022300715 19960223 00715 GL 1996 2 23 96ZZZX809 3 19960124 G 6114 HUB HARTZL HCC3Y HCC3YR GL PROPELLER WRONG BOLTS C K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 03 CK4333A FBO PURCHASED 2 ZERO TSO PROPELLERS FROM A PROPELLER SHOP AND SENT TO LOCAL PROP SHOP TO HAVE THE CORRECT HUB BOLTS INST ALLED. AFTER RECEIPT BY PROP SHOP, THE FOLLOWING DISCREPANCIES WERE NOTED. HUB BOLTS INSTALLED WERE WRONG PART NUMBER. THE WRONG BOOT PART NUMBER WAS INSTALLED. THE HUB MODEL WAS INCORRECTLY STAMPED. THE TRACK BETWEEN BLADES WAS MEASUR ED AT .2812 INCH, .0625 INCH IS ALLOWED. PROPELLER WAS RED TAGGED AND RETURNED TO FBO. 5 C P25EA 1996022300718 19960223 00718 CE 1996 2 23 96ZZZX812 1 19960124 G 2434 66082019 GENERATOR BENDIX 30310719A LEAR 35 35A 5170602 CE LT ENGINE FAILED B GW4R K NONE O OTHER NR NOT REPORTED 1 SO 11 190DA 1691 156 CATASTROPHIC FAILURE OF NR 1 DC GENERATOR. LOG BOOKS WERE NOT AVAILABLE, BUT ESTIMATED TSO TO BE 45-50 HOURS. CAUSE UN KNOWN DUE TO SEVERE DAMAGE OF THE GENERATOR. 2 L 7 2 4F A10CE 1996022300719 19960223 00719 WP 1996 2 23 96ZZZX813 2 19960103 G 7250 31038393 ROTATING SEAL GARRTT TPE331 TPE33112UAR 01514 WP 1ST STAGE TURB FLANGE CRACKED B DSCR K NONE O OTHER IN INSP/MAINT 1 GL 25 7218 P70104 DURING INSPECTION FOR METAL CONTAMINATION, FOUND PART CRACKED AT SEALING FLANGE. THIS IS A CRITICAL LIFE-LIMITED COMPON ENT. LIFE-LIMIT IS 20,000 CYCLES. SUBMITTER STATED THIS IS THE 24TH MALFUNCTION/DEFECT REPORT SUBMITTED ON THIS PART B Y THIS REPAIR STATION. 4 T E4WE 1996022300724 19960223 00724 EU 1996 2 23 96ZZZX818 1 19960123 G 5542 S5547000001600 SKIN AEROSP ATR42 ATR42300 8680920 EU RUD LT/RT WL7058 CRACKED B FI2R K NONE O OTHER IN INSP/MAINT 1 SW 17 4211G 12903 178 RUDDER SKIN HAS CRACKS COMING FROM THE LEFT AND RIGHT SPRING TAB WEIGHT CUT OUTS. THE CRACKS ARE APPROXIMATELY 1.2 INCH ES TO 1.5 INCHES AND ARE EMITTING FROM THE AFT SIDE OF CUT OUTS. SUSPECT CAUSE IS THE WEIGHT SUPPORT ROD IS HITTING THE RUDDER SKIN. RECOMMEND PERIODIC INSPECTION OF RUDDER SKIN AREA UNDER FAIRING. 2 H 7 2 4T RT A53EU 1996030100218 19960301 00218 EU 1996 3 1 96ZZZX819 1 19960115 G 7921 TB1053015101 BAFFLE SOCATA TB9 TB9 8680694 EU OIL COOLER CRACKED B DYTR K NONE O OTHER IN INSP/MAINT 1 SO 15 144ER 591 1339 BAFFLE OIL COOLER IS CRACKING AROUND OIL COOLER MOUNT POINT. SUBMITTER STATED BAFFLE NEEDS TO BE MADE FROM THICKER MATE RIAL. THIS PROBLEM IS A COMMON OCCURRENCE. (SEE PREVIOUS M OR D REPORTS). 1 L 7 1 3O NT AS1EU 1996030100219 19960301 00219 1996 3 1 96ZZZX820 4 19960117 G 2210 065504601 TRIM MONITOR KING KTA435 LEAR 35 31A 5170531 CE AUTOPILOT FAILED C A O OTHER O OTHER CL CLIMB 1 CE 07 92UG 610 1319 050 ON THREE SEPARATE OCCASIONS, AIRCRAFT HAS BEEN DEICED. ON ALL THREE OCCASIONS, THE AUTOPILOT QUIT SHORTLY AFTER TAKEOFF . INVESTIGATION REVEALED THE TRIM MONITOR BOX MOUNTED AT THE BASE OF VERTICAL FIN SPAR (AFT SIDE) WAS SATURATED WITH DE ICING FLUID. KING RADIO AND LEARJET WERE CONTACTED ABOUT THE PROBLEM. SUBMITTER RECOMMENDS 1) SHIELD THE MONITOR BOX WITH A MOISTURE GUARD, OR, 2) RELOCATE MONITOR BOX INTO THE AFT EQUIPMENT BAY WHERE IT IS DRY. AFTER THE ACFT SAT IN T HE HANGAR OVERNIGHT AND DRIED OUT, THE AUTOPILOT FUNCTIONED NORMALLY. 2 L 7 2 4F RT A10CE 1996030100220 19960301 00220 EU 1996 3 1 96ZZZX821 2 19960125 G 7230 BUSHING GULSTM G1159 G1159 3953505 SO RROYCE SPEY SPEY5118 54523 EU HP COMPRESSOR SHIFTED B L GJQR O OTHER E VIBRATION/BUFFET DE DESCENT 1 NM 01 26WP 8630 1920 024 8576 ENGINE HAD INTERMTTENT HIGH VIBRATION READINGS. CREW REPORTED A BUZZ ON DESCENT AT 79 PERCENT HI PRESS ROTOR SPEED. IN -FLT VIB SURVEY SHOWED VIB PEAK OF 1.3 MILS CORRESPONDING TO HP ROTATIONAL FREQ AT THAT POWER SETTING. SECONDARY SMALLE R PEAK CORRESPONDING TO LP ROTOR NOTED. ENG DISASSEMBLED. SEVERAL 1ST STG HI PRESS COMPR BLADES WERE BOUND UP. ROTOR DISASSEMBLED, MTNG BUSHINGS FND BACKED OUT OF PIN HOLES. BUSHINGS SHOWED EVIDENCE OF CONTACT WITH ROTOR HUB. LOW PRESS COMPR BLADE PINS CONTAMINATED WITH DIRT & RUST. 1ST STAGE HAD HEAVIEST ACCUMULATION. 2 BRACKETS HOLD OUTER DUCT TO EN G BROKEN. BRACKETS NEAR MNT LOC FOR AFT VIB PICK-UP. LOCALIZED THERMAL DISTRESS TO NOZZLE GUIDE VANES & COMB CANS. 2 L 7 2 4F 4 F RT A12EA E2EU 1996030100223 19960301 00223 EU 1996 3 1 96ZZZX824 1 19960117 G 5320 HC536B1427000 PLATE BAG BAE146 BAE146200A 1500266 EU FR 15-18 CORRODED B A6WR K NONE O OTHER IN INSP/MAINT 1 GL 31 292UE E2087 DURING STRUCTURAL INSPECTION, FOUND TWO SUPPORT PLATES AT 3RD INTERCOSTAL INBOARD FROM LT FORWARD PASSENGER DOOR BETWEEN FUSELAGE FRAMES 15 AND 18 CORRODED. REPLACED BOTH PLATES. REFERENCE: OPERATOR CONTROL NR A6WR95065. (X) 2 H 7 4 4F RT A49EU 1996030100224 19960301 00224 1996 3 1 96ZZZX825 1 19960208 G 2421 952B9561 WEDGE SUNDSTRANDEM 915F7181 ARMATURE ROTOR MISSING B MG4R K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 19 ARMATURE ROTOR HAS BEEN REWOUND BY PERSONS UNKNOWN, WITHOUT 8 EACH BOTTOM WEDGES AS CALLED OUT IN THE SUNDSTRAND DRAWING . ARMATURE ROTOR WAS RECEIVD FROM NORTHWEST AIRLINES UNDER WORK ORDER NR 63336400 (R542). 1996030100225 19960301 00225 SW 1996 3 1 96ZZZX826 1 19960114 G 6240 222375013103 TORQUE SENSOR BELL 222 222U 1182140 SW MAST FAILED B A EFLR K NONE O OTHER IN INSP/MAINT 1 WP 21 415MA 604 9402R005 47658 MAST TORQUE METER FAILED AFTER 604.9 HOURS IN SERVICE. SUBMITTER STATES EXPERIENCING FREQUENT SENSOR FAILURES. 1 G 7 2 3U H9SW 1996030100470 19960301 00470 NE 1996 3 1 96ZZZX829 2 19960116 G 7250 BLADE CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE ENGINE HPT FAILURE B L DJFR K NONE O OTHER IN INSP/MAINT 1 EA 23 120JP 550468 71331 ENGINE SOUNDED STRANGE AFTER START. TROUBLESHOT TO ENGINE INTERNAL. SENT OUT FOR OVERHAUL. FOUND 3 HT BLADES FAILED. 1 L 7 2 4F 4 F A22CE E1NE 1996030100471 19960301 00471 CE 1996 3 1 96ZZZX830 1 19960105 G 2510 59711 SEAT ASSY 59739 RKWELL NA265 NA26540 6402608 CE PILOT SEAT WELD BROKEN D S A K NONE O OTHER IN INSP/MAINT 1 SO 16 314NT 282028 PILOT'S SEAT WOULD NOT ADJUST FORWARD AND AFT OR VERTICALLY, AND SEAT WOULD NOT SIT LEVEL. INSPECTION FOUND SEAT STRUCT URAL MEMBERS (WELD ASSYS) BROKEN AT WELDED AREAS. SEPARATION OF THESE SUPPORT MEMBERS ALLOWS THE SEAT TO PARTIALLY COLL APSE AND PREVENTS THE SEAT FROM SUPPORTING THE FULL WEIGHT OF THE PILOT. ALSO, ANY PRESSURE APPLIED TO THE RUDDER OR BR AKE PEDALS BY THE PILOT CAUSES THE SEAT TO SEPARATE AND MOVE. ALL DEFECTIVE PARTS ARE TO BE REPLACED. RECOMMEND INSPEC TION OF PILOT'S AND COPILOT'S SEAT STRUCTURES AT NEXT SCHEDULED INSPECTION OF SABRELINER AIRCRAFT EQUIPPED WITH THIS MOD EL SEAT. 2 L 7 2 4J A2WE 1996030100472 19960301 00472 CE 1996 3 1 96ZZZX831 1 19960105 G 2510 59701 SEAT ASSY 59731 RKWELL NA265 NA26540 6402608 CE PILOT SEAT WELD BROKEN D K NONE O OTHER IN INSP/MAINT 1 SO 16 314NT 282028 PILOT'S SEAT WOULD NOT ADJUST FORWARD AND AFT OR VERTICALLY, AND SEAT WOULD NOT SIT LEVEL. INSPECTION FOUND SEAT STRUCT URAL MEMBERS (WELD ASSYS) BROKEN AT WELDED AREAS. SEPARATION OF THESE SUPPORT MEMBERS ALLOWS THE SEAT TO PARTIALLY COLL APSE AND PREVENTS THE SEAT FROM SUPPORTING THE FULL WEIGHT OF THE PILOT. ALSO, ANY PRESSURE APPLIED TO THE RUDDER OR BR AKE PEDALS BY THE PILOT CAUSES THE SEAT TO SEPARATE AND MOVE. ALL DEFECTIVE PARTS ARE TO BE REPLACED. RECOMMEND INSPEC TION OF PILOT'S AND COPILOT'S SEAT STRUCTURES AT NEXT SCHEDULED INSPECTION OF SABRELINER AIRCRAFT EQUIPPED WITH THIS MOD EL SEAT. 2 L 7 2 4J A2WE 1996030100473 19960301 00473 SO 1996 3 1 96ZZZX832 1 19960130 G 2911 1356593105 ACCUMULATOR PARKERHANFIN LKHEED 1329 132925 5263125 SO LT WING INBD LEAK B FGQR K NONE K FLUID LOSS IN INSP/MAINT 1 SO 01 701JH 58 544 5230 WHEN SECURING THE AIRCRAFT, THE AUXILIARY HYDRAULIC SYSTEM WAS PRESSURIZED TO RETRACT THE SPEED BRAKE. WHEN EXITING THE PLANE, A PUDDLE OF HYDRAULIC FLUID WAS NOTICED UNDER THE LT WING INBOARD OF THE MLG. THE LEAK WAS TRACED TO THE UPLOCK ACCUMULATORS RELIEF HOLE INDICATING INTERNAL SEAL FAILURE. THIS ACCUMULATOR HAD BEEN OVERHAULED 1/94 AND BOUGHT ON EXC HANGE BASIS AND INSTALLED 9/95. 2 L 7 4 4F 2A1SO 1996030100474 19960301 00474 CE 1996 3 1 96ZZZX833 1 19960118 G 5412 251921617 GASKET LEAR 25 25B 5170511 CE FIREWALL WRONG PART B IY2R K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 15 911JG 147 INTERNAL GASKET, PN 2519216-17, WAS INSTALLED ON THE EXTERNAL SIDE OF THE LT PYLON FIREWALL. EXTERNAL GASKET, PN 245201 2-1, SHOULD HAVE BEEN INSTALLED. DUE TO THIS INSTALLATION AND THE NATURAL DETERIORATION OF THESE GASKETS, SEVERE FIREWA LL DAMAGE OCCURRED. SUBMITTER RECOMMENDS A TIME CHANGE FOR THE GASKETS AND PARTICULAR INSPECTION IN THIS AREA DURING EN GINE INSPECTIONS. AFTT: 5,190.8 HOURS. LANDINGS, 5,145. 2 L 7 2 4J A10CE 1996030100475 19960301 00475 CE 1996 3 1 96ZZZX834 1 19960202 G 3230 NAS538816075 BUSHINGS MTSBSI MU300 MU300 5780602 CE TORQUE KNEE SEIZED D K NONE O OTHER IN INSP/MAINT 1 SO 11 399RP 3562 A020SA UPPER TORQUE KNEE PIVOT BUSHINGS WOULD NOT ACCEPT GREASE. DISASSEMBLED TORQUE KNEE FROM AIRCRAFT AND FOUND GREASE HOLE IN BUSHING NOT ALIGNED WITH GALLERY IN CASTING. BUSHINGS SHOW NO EVIDENCE OF SPINNING IN CASTINGS. THIS CONDITION FOUN D ON BOTH MAIN GEAR TORQUE LINKS. 2 H 7 2 4F RT A14SW 1996030100476 19960301 00476 SW 1996 3 1 96ZZZX835 1 19960206 G 3610 2481048 DIAPHRAGM BENDIX 38E852B GULSTM 690TP 690A 0141722 SW BLEED AIR REG RUPTURED D K NONE O OTHER IN INSP/MAINT 1 SW 15 66GW 11174 DURING THE COURSE OF A 100-HOUR INSPECTION, FOUND BLEED AIR REGULATOR TO HAVE A BLOWN DIAPHRAGM. THIS IS THE REGULATOR LOCATED IN AFT BAGGAGE AREA THAT REDUCES THE BLEED AIR FROM THE ENGINE DOWN TO 18 PSI TO INFLATE THE DOOR SEAL AND DEICE BOOTS. SUBMITTER STATED THEY HAVE FOUND MANY REGULATORS IN THIS CONDITION. INSTALLED AND OPS CHECKED AN OVERHAULED RE GULATOR. SUGGEST THE MANUFACTURER PROVIDE IMPROVED DIAPHRAGM TO BETTER HANDLE THE HEAT, AS THIS MAY BE THE CAUSE OF THE NUMEROUS FAILURES. 1 H 7 2 3T 2A4 1996030100477 19960301 00477 CE 1996 3 1 96ZZZX836 1 19960207 G 6123 AUTOFEATHER BEECH 200 200BEECH 1152920 CE LT ENGNE MALFUNCTION E K NONE O OTHER NR NOT REPORTED 1 EA 21 87BP BB34 PILOT REPORTED DURING TRAINING, LEFT ENGINE WAS SHUT DOWN USING AUTOFEATHER. ON ENGINE RESTART, LEFT PROP WOULD NOT COM E OUT OF FEATHER. ACFT LANDED WITHOUT INCIDENT. NOTE: AUTOFEATHER CHECKED OK PRE-FLIGHT RUNUP CHECK. MAINTENANCE TRO UBLESHOT AUTOFEATHER SYSTEM. CHECKED DUMP SOLENOID, PRESSURE SWITCHES, RELAYS, AND WIRING. NO DISCREPANCIES FOUND. GR OUND CHECKED SYSTEM - SYSTEM CHECK NORMAL PER CHAPTER 61 OF MM. SWAPPED K2 AND K3 RELAYS FROM LEFT TO RIGHT SIDE FOR FU RTHER TROUBLESHOOTING. 1 L 7 2 4T A24CE 1996030100478 19960301 00478 CE 1996 3 1 96ZZZX837 1 19960212 G 3320 6900026 POWER SUPPLY BEECH 200 B200 1152922 CE CABIN LT NR 5 FAILED D K NONE B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 EA 25 8049H 812 BB1395 CABIN FLUORESCENT LIGHTS WERE TURNED ON FOR AN OPERATIONAL CHECK DURING A POST-FLIGHT INSPECTION. THE LIGHTS CAME ON, B LINKED SEVERAL TIMES, AND THE CIRCUIT BREAKER TRIPPED. SMOKE WAS NOTED AT THE REAR OF THE CABIN. POWER WAS IMMEDIATELY REMOVED FROM THE ACFT AND PROBLEM WAS TRACED TO FLUORESCENT LIGHT ASSY AT THE NR 5 LT PASSENGER WINDOW. POWER SUPPLY W AS FOUND BURNED AND WINDOW TRIM BURNED NEXT TO POWER SUPPLY. THE REPLACEMENT PART SUPERSEDED TO P/N 6900080. INSTALLED NEW LIGHT ASSY. NO FURTHER DEFECTS NOTED. 1 L 7 2 4T A24CE 1996030100481 19960301 00481 NM 1996 3 1 96ZZZX840 1 19960122 G 3310 761272 LIGHT ASSY 579458 PIPER PA60 PA60601P 7106012 NM ANUN PANEL SHORTED B P3NR K NONE B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 EA 13 3638T 2001 61P080180634 PILOT NOTICED AN ELECTRICAL ARCING WHEN PUSHING ON ANNUNCIATOR PANEL DURING A NIGHT FLIGHT. FOUND A LIGHT ASSY MOUNTED BEHIND ANNUNCIATOR PANEL, HAD INSUFFICIENT CLEARANCE TO THE SOLDER JOINT ON THE UPPER LEFT ANNUNCIATOR LIGHT. RECOMMEND AN INSPECTION IN THIS AREA AND REMOVAL OF THE SPACER ON THE LIGHT ASSY SHAFT AND/OR SHIMMING WITH WASHERS OF THE ANNUNC IATOR PANEL AT THE TWO MOUNTING POINTS TO ACHIEVE SOME CLEARANCE. 1 M 7 2 3O RT A17WE 1996030100482 19960301 00482 CE 1996 3 1 96ZZZX841 1 19960205 G 2130 66002073 VALVE LEAR 35 35LEAR 5170600 CE CABIN PRESS DEFECTIVE B BSYR K NONE O OTHER IN INSP/MAINT 1 GL 07 813AS 10416 47319 167 PRESSURIZATION SAFETY VALVE WILL NOT SEAT PROPERLY. SUSPECT CAUSE IS INTERNAL DAMAGE. FOUND DURING SCHEDULED 600-HOUR OR 1200-HOUR INSPECTION CYCLE. AD 94-26-01 IS APPLICABLE. 2 L 7 2 4F A10CE 1996030100483 19960301 00483 NE 1996 3 1 96ZZZX842 2 19960116 G 7230 310463301 ANTIROTATE RING CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE ENGINE FAILED B DJFR K NONE O OTHER IN INSP/MAINT 1 EA 23 511AB 550299 70350 AFTER ENGINE START, ENGINE SOUNDED STRANGE (LIKE VACUUM CLEANER). TROUBLESHOT AND SUSPECTED INTERNAL DAMAGE. ENGINE RE MOVED AND SENT FOR OVERHAUL. FOUND THE ANTI-ROTATION RING HAD FAILED. 1 L 7 2 4F 4 F A22CE E1NE 1996030100484 19960301 00484 EU 1996 3 1 96ZZZX843 1 19960129 G 3010 T700A3013002100 DEICE PIPE SOCATA TBM TBM700 8682000 EU ELEVATOR HORN CHAFE THROUGH B A LF1R K NONE O OTHER IN INSP/MAINT 1 EA 07 700GJ 230 102 REMOVED ELEVATOR FOR C/W SOCATA SB 70-053. UPON REMOVAL, FOUND LT DEICE PIPE FOR ELEVATOR HORN WORN THROUGH AT ENTRANCE TO HORN. THIS INSTALLATION WAS DONE AT FACTORY. WEAR CAUSED BY LACK OF CLEARANCE AT PASS-THROUGH. SUBMITTER STATED T BM NEEDS TO ISSUE A SL OR SB TO IMPROVE CLEARANCE. ALSO, REPLACED RT DEICE PIPE. 1 L 7 1 3T RT A60EU 1996030100486 19960301 00486 EU 1996 3 1 96ZZZX845 1 19960106 G 5400 F50B258700A2AAA S-DUCT AMD FALC50 FALCON50MYST 2730106 EU INTAKE LT SIDE CRACKED B S JGVR K NONE O OTHER IN INSP/MAINT 1 CE 09 16R 5766 141 DURING 2C INSPECTION, NOTICED CRACKED SPOT WELDS ON THE FORWARD S-DUCT OUTER SKIN. SUBMITTED FINDINGS TO FALCON JET. D OOR '350A' MUST BE REMOVED TO VIEW THIS AREA. THIS PROBLEM IS NOT CURRENTLY ADDRESSED IN AN AD OR SB. 2 L 7 3 4F A46EU 1996030100487 19960301 00487 NE 1996 3 1 96ZZZX846 2 19960206 G 7210 7895922 TAB WASHER HAMSTD 775800 SAAB SF340 SF340A 7850100 EU GE CT7TP CT75A2 30030 NE GC49 GEARBOX CRACKED B S SI3R K NONE O OTHER IN INSP/MAINT 1 NE 03 3903G 11548 340A0227 GEE785278 GEARBOX RETURNED TO HAMILTON STANDARD FOR FAILED BORESCOPE REPAIR. AT DISASSEMBLY OF THE DRIVE (BULL) GEAR, HAMILTON ST ANDARD DISCOVERED THE TABBED WASHER WAS CRACKED. THE CRACK IS ADJACENT TO A TAB AND EXTENDS THROUGH TO THE INSIDE DIAME TER TAB. THE DRIVE GEAR RETENTION NUT REQUIRED 1,600 FEET/POUNDS OF TORQUE TO REMOVE. THIS PART SUPERSEDED P/N 775796- 4. 2 L 7 2 4T 4 T RT A52EU E8NE6 1996030100488 19960301 00488 CE 1996 3 1 96ZZZX847 1 19960112 G 2120 355505242 SHUT OFF DOOR LEAR 35 35LEAR 5170600 CE FIREWALL INOPERATIVE D S A K NONE O OTHER IN INSP/MAINT 1 SO 16 3818N 2700 D1047 ON ANNUAL INSPECTION, EMERGENCY AIR SHUT-OFF TO COCKPIT WAS DETERMINED NOT TO BE OPERATIVE. FURTHER INSPECTION FOUND BE LLCRANK LOOSE FROM 'DOOR' BY RIVETS IN BELLCRANK HAVING COME OUT OF BELLCRANK. WHEN REMOVING UNIT FOR REPLACEMENT OF RI VETS, HINGE HOLDING DOOR IN PLACE HAD RIVETS, ALSO PULLED OUT, LEAVING DOOR AND ONE-HALF HINGE LOOSE. OTHER ONE-HALF OF HINGE ON DUCT FOUND CORRECTLY ATTACHED. MADE REPAIRS PER 43.13 AND RETURNED TO SERVICE. SYSTEM OPERATES NORMALLY. 2 L 7 2 4F A10CE 1996030100489 19960301 00489 WP 1996 3 1 96ZZZX848 2 19960117 G 7250 8683793 STATOR GULSTM 690TP 690A 0141722 SW GARRTT TPE331 TPE3315 01514 WP HOT SECTION DEFECTIVE B L DJFR K NONE W INADEQUATE Q C IN INSP/MAINT 1 EA 23 690HF 11298 P06541C DURING C/W WITH AD 95-16-08, FOUND HOT SECTION 3RD STATOR WAS IMPROPER DUE TO NOT BEING STAMPED OR SIGNED AND SERIAL NUM BER OF PART NOT ENTERED. 1 H 7 2 3T 4 T 2A4 E4WE 1996030100492 19960301 00492 SO 1996 3 1 96ZZZX851 2 19960117 G 8520 CRANKCASE CESSNA 421 421B 2076014 CE CONT O520 GTSIO520H 17032 SO NR 3 CYLINDER CRACKED D K NONE K FLUID LOSS IN INSP/MAINT 1 SO 06 7560Q 421B0346 600641 UPON INSPECTION IAW AD 77-13-22 CRANKCASE CRACKS, CRACK FOUND AT NR 3 CYLINDER UPWARDS UNDER ENGINE DATA PLATE, LENGTH U NDETERMINED, BUT LEAKING OIL MAKES UNAIRWORTHY. ENGINE REMOVED FROM LEFT POSITION. ENT TT, 3,334.2 HOURS. ENG TSMOH, 916.3 HOURS. NOTE: RIGHT ENGINE HAS HEAVY CASE INSTALLED. 1 L 7 2 3O 3 O A7CE E7CE 1996030100493 19960301 00493 EA 1996 3 1 96ZZZX852 2 19960126 G 7414 1052947 SHAFT S6LN200 PIPER PA23 PA23250 7102308 SO LYC O540 IO540C4B5 41532 EA MAGNET WORN D K NONE O OTHER IN INSP/MAINT 1 NM 03 5729Y 312 3080084 272853 L122448 REMOVED MAGNETO DURING ANNUAL INSPECTION AND NOTICED SHAFT NUT WAS COMPLETELY STRIPPED AND HELD IN PLACE ONLY BY BROKEN COTTER PIN. REMOVED COTTER PIN AND NUT, FOUND SHAFT COMPLETELY STRIPPED AND BUSHING VERY LOOSE AND SLOPPY ON SHAFT. RE MOVED BUSHING AND FOUND SHAFT UNDER BUSHING WORN APPROXIMATELY HALF-WAY THROUGH AND WOODRUFF KEY SEVERELY DEFORMED. DRI VE PLATE AND SHAFT AREA UNDER DRIVE PLATE APPEAR NORMAL. 1 L 7 2 3O 3 O 1A10 1E4 1996030100494 19960301 00494 EA 1996 3 1 96ZZZX853 2 19960210 G 7414 66M21195 CLAMP NUT SLICK 4370 CESSNA 172 172N 2072434 CE LYC O360 O360A4M 41514 EA RT MAG ATTACH MISSING G K NONE O OTHER IN INSP/MAINT 1 GL 13 734FH 95040291 17268817 L2821736A RIGHT MAGNETO TOP ATTACHMENT MISSING. CLAMP, 66M21195. WASHER, STD-475. WASHER, STD-1727. NUT, STD-1410. RIGHT MAGN ETO INSTALLED 10-12-95. TOTAL TIME 168 HOURS. ACFT TT 4,328.5 HOURS. 1 H 7 1 3O 3 O NT 3A12 E286 1996030100495 19960301 00495 SO 1996 3 1 96ZZZX854 1 19960104 G 8011 MHB4014 STARTER PRESTOLITE PIPER PA31 PA31350 7103110 SO ENGINE BURNED B L APCR A UNSCHED LANDING H ELECT. POWER LOSS-50 PC CL CLIMB 1 NM 01 3582X 318052105 ADDENDUM TO SDR DATED 1-4-96. RT ENGINE STARTER MOTOR FIELD WINDINGS FAILED, APPARENTLY WHILE STARTER ENGAGED TO CRANK THE ENG RESULTING IN A SHORT-TO-GROUND OF STARTER POWER CIRCUIT. PILOT HAD NO INDICATIONS OF TROUBLE, AND ENG STARTED N ORMALLY AND CONTINUED TO RUN NORMALLY DURING PRE-FLT RUN-UP. HEAT IN STARTER CIRCUIT CAUSED STARTER SOLENOID CONTACTS T O STICK CAUSING POWER TO CONTINUE TO FLOW TO STARTER MOTOR EVEN THOUGH STARTER SWITCH HAD BEEN RELEASED. THE SHORT-TO-G ROUND INSIDE THE STARTER MOTOR DELETED ACFT BATTERY AND ALTERNATORS COULD NOT KEEP UP WITH THE LOAD AND ALL ACFT SYSTEMS DROPPED OFF-LINE. OCCURRED AT ROTATION ON T/O, & PILOT RETURNED TO AIRPORT. LANDED WITHOUT RADIO COMM. 1 L 7 2 3O A20SO 1996030100496 19960301 00496 SO 1996 3 1 96ZZZX855 1 19960209 G 3210 2082900 BRACE STUD PIPER PA24 PA24250 7102404 SO RT/LT MLG CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 13 6498P 5093 241618 REMOVED SIDE BRACE STUDS TO C/W AD 95-20-07 AND FOUND BOTH OF THEM CRACKED IN THE AREA DEPICTED IN THE AD. 1 L 7 1 3O 1A15 1996030100497 19960301 00497 EA 1996 3 1 96ZZZX856 2 19960206 G 8520 CRANKSHAFT PIPER PA28 PA28161 7102803 SO LYC O320 O320D3G 41508 EA ENGINE PITTED B LK1R K NONE O OTHER IN INSP/MAINT 1 NE 01 4333C 1679 288416039 L1319839A DURING 100-HOUR ENGINE INSPECTION FOR AIRCRAFT ANNUAL INSPECTION, LYC SB 505A WAS C/W AND THE CRANKSHAFT FOUND PITTED IN THE AREA NOTED IN SB 505A. ENGINE WAS REMOVED AND REPLACED WITH A LYC FACTORY OVERHAULED. AFTER REMOVAL OF THE CRANKS HAFT PLUG, THE INTERIOR OF THE CRANKSHAFT WAS FOUND COMPLETELY PLUGGED WITH SLUDGE (1.25 POUNDS). GENERAL CONDITION AND RECORDS INDICATE A WELL MAINTAINED AIRCRAFT WITH MULTI-VISCOSITY OIL CHANGES AS REQUIRED. 1 L 7 1 3O 3 O 2A13 E274 1996030100498 19960301 00498 CE 1996 3 1 96ZZZX857 1 19960201 G 2750 0512128 BRACKET CESSNA 185 A185F 2072821 CE RT FLAP PULLEY BROKEN D K NONE O OTHER IN INSP/MAINT 1 GL 15 205NR 3910 FLAP PULLEY BRACKET FOUND BROKEN ON RIGHT FORWARD SIDE OF FUSELAGE AT STATION 65.33. TANGS WERE BROKEN OFF OF BRACKET. AIRCRAFT HOURS, 7,000. 1 H 7 1 3O 3A24 1996030100499 19960301 00499 SO 1996 3 1 96ZZZX858 1 19960209 G 3231 9850602 DOOR PIPER PA32 PA32RT300T 7103216 SO LT NLG MISADJ D K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 11 39526 32R7887102 LEFT NOSE LANDING GEAR DOOR ADJUSTED TOO TIGHT AGAINST AFT TOP PLATE IN WHEELWELL. AFTER SEVERAL RETRACTIONS, DOOR PULL ED OVER STOP PLATE AND WEDGED INTO WHEELWELL PREVENTING NLG EXTENSION. RECOMMENDATION: IMPROVE INSTRUCTIONS TO PIPER M M. 1 L 7 1 3O A3SO 1996030100501 19960301 00501 CE 1996 3 1 96ZZZX860 1 19960130 G 3250 508201883 BRACKET BEECH 200 200BEECH 1152920 CE STEERING SUPPORT BROKEN B S A VE2R K NONE O OTHER IN INSP/MAINT 1 SW 05 74GS 3006 BB429 CUSTOMER REPORTED AIRCRAFT YAWS TO THE RIGHT WHEN LANDING GEAR IS SELECTED DOWN. DURING TROUBLESHOOTING, FOUND STEERING LINKAGE SUPPORT BRACKET BROKEN AT FORWARD ATTACH POINT. 1 L 7 2 4T A24CE 1996030100504 19960301 00504 CE 1996 3 1 96ZZZX863 1 19960206 G 2820 36700 VALVE CESSNA 340 340CESSNA 2076404 CE VAPOR RETURN LEAKING B A DYPR K NONE O OTHER IN INSP/MAINT 1 NM 09 100HJ 2503 3400334 WHILE PERFORMING AN ANNUAL INSPECTION ON A TWIN CESSNA, NOTED THAT FUEL WAS LEAKING FROM THE VAPOR RETURN LINE ON THE LT ENGINE. UPON INVESTIGATION, DISCOVERED THE VAPOR RETURN CHECK VALVE SEAL WAS DETERIORATED ALLOWING FUEL FROM THE FULL MAIN FUEL TANK TO LEAK BACK DOWN THE LINE. WHEN THE RT VALVE WAS CHECKED, IT WAS FOUND IN THE SAME CONDITION. IT WAS F URTHER NOTED WHEN THE FUEL QUANTITY IN THE FUEL TANKS IS LOW, FUEL WILL NOT LEAK BACK DOWN THE LINE EVEN THOUGH THE VALV E SEAL IS FAULTY. 1 L 7 2 3O 3A25 1996030100505 19960301 00505 CE 1996 3 1 96ZZZX864 1 19960101 G 3297 WIRE BEECH 55 95C55 1152708 CE DOWN LIMIT SW SHORTED D A A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS LD LANDING 1 WP 01 12DK TE290 PILOT MADE UNEVENTFUL LANDING AFTER REPORTING SMOKE IN COCKPIT. INVESTIGATION REVEALED A WIRE SHORTED AS IT PASSED THRO UGH LIGHTNING HOLE BEHIND BATTERY SWITCH. ONE SIDE OF WIRE WAS CONNECTED TO COMMON TERMINAL OF LANDING GEAR DOWN LIMIT SWITCH AND OTHER SIDE OF WIRE FOUND HANGING FREE WITH TERMINAL LUG STILL ATTACHED. IT IS SPECULATED THE WIRE WAS DISCON NECTED FROM THE POSITIVE UNPROTECTED (NO CIRCUIT BREAKER) SIDE OF BUSS PRIOR TO ENTERING REPAIR STATION. THE NON-FACTOR Y WIRE DID NOT CONFORM TO BEECHCRAFT WIRING DIAGRAM. REPAIRS MADE TO BRING ACFT BACK INTO CONFORMITY. 1 L 7 2 3O 3A16 1996030100508 19960301 00508 CE 1996 3 1 96ZZZX867 1 19960130 G 2410 5395473000 BELT BEECH 55 95B55 1152706 CE ALTERNATOR BROKEN B EIYR K NONE H ELECT. POWER LOSS-50 PC NR NOT REPORTED 1 WP 07 812D 5 TC1839 PILOT REPORTED LEFT ALTERNATOR OUT. INSPECTION REVEALED THAT NEW CONTINENTAL ALTERNATOR BELT HAD FAILED. 1 L 7 2 3O 3A16 1996030100510 19960301 00510 SO 1996 3 1 96ZZZX869 2 19960208 G 8530 646279 PISTON CESSNA 175 175A 2072504 CE CONT O300 GO300C 17022 SO CYL BORE MISMFG D K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 11 6950E 56450 53078C PURCHASED 6 EACH CYLINDER POWER PACKS FROM SUPERIOR AIR PARTS. P/N SA10200A23P. CONTINENTAL PISTONS WERE SUPPLIED WITH THE POWER PACKS. PISTONS ARE TOO LARGE FOR CYLINDER BORE AND CANNOT GET PROPER PISTON CYLINDER CLEARANCE BELOW 3RD RIN G. CONTINENTAL OVERHAUL MANUAL CALLS FOR 4.0476 INCH TO 4.0486 INCH BELOW THIRD RING. NEW PISTON DIMENSIONS ARE 4.051 INCH. OVERHAUL MANUAL CALLS FOR .0134 INCH - .0164 INCH CLEARANCE. ONLY HAVE .0128 INCH. 1 H 7 1 3O 3 O 3A17 E298 1996030100511 19960301 00511 SW 1996 3 1 96ZZZX870 1 19960126 G 3210 52352 BOLT SLINDS 100 100ACMDR 0140202 SW MLG CORRODED D K NONE O OTHER IN INSP/MAINT 1 SW 05 631PF 742 742 189 INSPECTION FOUND (CORROSION) FERROUS OXIDE DAMAGE TO BOLT ASSEMBLIES (BOTH MAIN LANDING GEAR) TO THE EXTENT THAT STRUCTU RAL INTEGRITY HAS BEEN SERIOUSLY COMPROMISED. P/N 52352, P/N 55450, AND P/N 58792. 1 H 7 1 3O 1A21 1996030100514 19960301 00514 SO 1996 3 1 96ZZZX873 2 19960123 G 8550 CH48108 FILTER CHAMPION CESSNA 340 340CESSNA 2076404 CE CONT O520 TSIO520NB 17040 SO ENGINE OIL RING BROKEN D K NONE O OTHER IN INSP/MAINT 1 SW 03 3LN 49 F04C211 3400301 DURING INSPECTION OF OIL FILTER, THE METAL RETAINING RING BETWEEN FILTER AND RUBBER GASKET (ALL PARTS INTERNAL) WAS FOUN D BROKEN WITH ONE-THIRD OF THE RING MISSING. THE REMAINING PARTS OF THE RING WERE FOUND IN FILTER, ALL PIECES. FOUND O N TWO FILTERS. 1 L 7 2 3O 3 O 3A25 E8CE 1996030100515 19960301 00515 SO 1996 3 1 96ZZZX874 1 19960115 G 5700 LIFT STRUT MAULE M5 M5180C 5460204 SO WING CORRODED D K NONE O OTHER IN INSP/MAINT 1 EA 07 66VJ 8077C WHILE PERFORMING MAULE SB NR 11 (WING LIFT STRUT ASSY INSP/REPL), THREE OF THE FOUR LIFT STRUTS FAILED THE INSPECTION, B OTH FRONT AND RIGHT REAR FAILED. THERE WAS NO EXTERNAL VISIBILITY OF THIS PROBLEM. THE AIRCRAFT HAS ALSO BEEN HANGARED SINCE NEW. THE TOTAL TIME IN SERVICE OF THE AIRCRAFT IS 700.9 HOURS. 1 H 7 1 3O 3A23 1996030100516 19960301 00516 CE 1996 3 1 96ZZZX875 1 19960201 G 2730 05130633 BRACKET CESSNA 172 172F 2072414 CE ELEV BELLCRANK CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 23 5648R 4000 17253275 ELEVATOR BELLCRANK ASSY BRACKET FOUND CRACKED. REPLACEMENT PART IS MUCH HEAVIER. 1 H 7 1 3O NT 3A12 1996030100517 19960301 00517 CE 1996 3 1 96ZZZX876 1 19960205 G 5511 053200150 RIB 2432000201 CESSNA 172 172M 2072418 CE LT HORIZ STAB DAMAGED D K NONE O OTHER IN INSP/MAINT 1 NE 01 92747 5855 17261613 LEFT HORIZONTAL STABILIZER HAD DAMAGE TO THE RIB AND THE LEADING EDGE. THE RIB HAD BEEN CRUSHED AND THE SKIN AT THE RIB HAD A SMALL CRACK. SUBMITTER STATED THIS DAMAGE DEVELOPED FROM THE IMPROPER HANDLING OF THE AIRCRAFT ON THE GROUND. A LL OTHER AREAS OF TAIL WERE INSPECTED FOR DAMAGE AND NONE WERE DETECTED. 1 H 7 1 3O NT 3A12 1996030100518 19960301 00518 CE 1996 3 1 96ZZZX877 1 19960205 G 5512 053200176 SKIN CESSNA 172 172M 2072418 CE LT HORIZ STAB CRACKED D K NONE O OTHER IN INSP/MAINT 1 NE 01 92747 5855 17261613 LEFT HORIZONTAL STABILIZER HAD DAMAGE TO THE RIB AND THE LEADING EDGE. THE RIB HAD BEEN CRUSHED AND THE SKIN AT THE RIB HAD A SMALL CRACK. SUBMITTER STATED THIS DAMAGE DEVELOPED FROM THE IMPROPER HANDLING OF THE AIRCRAFT ON THE GROUND. A LL OTHER AREAS OF TAIL WERE INSPECTED FOR DAMAGE AND NONE WERE DETECTED. 1 H 7 1 3O NT 3A12 1996030100519 19960301 00519 1996 3 1 96ZZZX878 4 19960207 G 3441 7884604021 AMPLIFIER DELCO 7890860511 INU STAB AMP DEFECTIVE B CW7R K NONE O OTHER IN INSP/MAINT 1 GL 25 0402423 INERTIAL NAV SYSTEM DEVELOPS 100 KNOT GROUND SPEED WITHIN 10 MINUTES WHILE AIRCRAFT IS STATIONARY. STAB AMP-AZ FOUND AS FAULT. STAB AMP REPLACED, SYSTEM RECALIBRATED AND TESTED TO SPECS. UNIT HAD 3.6 HOURS SINCE LAST SERVICE AT MFG. 1996030100521 19960301 00521 EA 1996 3 1 96ZZZX880 2 19960123 G 8520 SL78027 ROD BOLT PIPER PA44 PA44180T 7104404 SO LYC O360 TO360E1A6 41514 EA CONNECT ROD NOT MARKED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 15 8264F 448107027 L13673 UPON INSPECTION OF NEW ROD BOLTS BEFORE INSTALLATION, DISCOVERED ONE OF EIGHT ROD BOLTS, SL78027, HAD NO HEAD MARKINGS I DENTIFYING THE PART. 1 L 7 2 3O 3 O A19SO E26EA 1996030100522 19960301 00522 SO 1996 3 1 96ZZZX881 1 19960131 G 5312 380082 BULKHEAD LUSCOM 8 8A 8190104 SO FS 2.5 CRACKED D S K NONE O OTHER IN INSP/MAINT 1 GL 15 28916 1679 DURING ANNUAL INSPECTION, CRACKS WERE FOUND ON BULKHEAD AT FS 2.5 WHERE JACK STRUT ATTACHES. JACK STRUT FITTINGS WERE A LSO FOUND CORRODED AND WORN. SUSPECT ROUGH OPERATION ON SKIS CAUSED CRACKS. 1 H 7 1 3O A694 1996030100523 19960301 00523 CE 1996 3 1 96ZZZX882 1 19960201 G 5343 05430131 FITTING CESSNA 172 172P 2072436 CE NLG UPPER LOOSE E K NONE O OTHER IN INSP/MAINT 1 NM 09 5453K 7199 17274119 NLG FITTING IS ATTACHED BY RIVETS AND 2 NAS BOLTS. ALL THE RIVETS WERE LOOSE AND FRETTING. 1 H 7 1 3O NT 3A12 1996030100524 19960301 00524 1996 3 1 96ZZZX883 4 19960207 G 2562 4520130D BATTERY PACK ARTEX ELT1104 PIPER PA46 PA46350P SO ELT LEAKING D K NONE O OTHER IN INSP/MAINT 1 CE 01 9275D 118 54555 4636002 INSPECTION OF ELT CONDITION REVEALED BATTERY PACK LEAKING ELECTROLYTES FROM BATTERY CELLS. ELT MFG DATE 1-3-95. ELT WA S STILL FUNCTIONAL. 1 L 7 1 3O RT A25SO 1996030100525 19960301 00525 CE 1996 3 1 96ZZZX884 1 19960125 G 5342 53120252 ATTACH PAN CESSNA 340 340CESSNA 2076404 CE HORIZ AFT CRACKED D K NONE O OTHER IN INSP/MAINT 1 GL 11 4515Q 4500 3400097 ROUTINE INSPECTION FOUND HORIZONTAL AFT ATTACH BRACE (FORWARD OF BULKHEAD) WITH 2 CRACKS IN CORNERS. 1 L 7 2 3O 3A25 1996030100526 19960301 00526 CE 1996 3 1 96ZZZX885 1 19960131 G 6120 C299506B0104 CONTROL CABLE CESSNA 172 R172K 2072431 CE GOVERNOR SEIZED D K NONE O OTHER IN INSP/MAINT 1 WP 21 7585X 2 R1723334 INSTALL NEW CONTROL CABLE ASSY AS SUPPLIED BY CESSNA AIRCRAFT. INSTALLED AND RIGGED PER CESSNA R172K SM. ALL OPS CHECK OK ON GROUND. RUN-UP OPS CHECK OK. FLOWN FOR 2.0 HOURS, NO ATTEMPT TO MOVE CONTROL WHILE IN-FLIGHT. UPON RETURN TO G ROUND, GOVERNOR CONTROL CABLE ASSY FROZEN SOLID. CABLE REMOVED AND INSPECTED. NO DAMAGE, NO MARKS OF ANY KIND, NO KINK S. SUSPECT HEAT AFFECTING INTERNAL COMPONENTS. RETURNED TO CESSNA FOR EVALUATION. 1 H 7 1 3O 3A17 1996030100527 19960301 00527 EA 1996 3 1 96ZZZX886 2 19960130 G 8530 73413 PUSHROD PIPER PA22 PA22 7102202 SO LYC O320 O320A1A 41508 EA CYLINDER NR 2 DEFECTIVE D K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 11 5788D 224464 4850 FOUND PUSHROD HOLDING VALVE OPEN. CLEARANCE .000 INCH, CYLINDER NR 2 CLEARANCE .013 INCH SHOULD BE .028 INCH. SEVEN HO URS SINCE SUDDEN STOPPAGE. 1 H 7 1 3O 3 O 1A6 E274 1996030100528 19960301 00528 EU 1996 3 1 96ZZZX887 1 19960115 G 5522 SKIN BNORM BN2 BN2A26 1520226 EU ELEVATOR CORRODED D K NONE O OTHER IN INSP/MAINT 1 AL 05 9995A 4000 897 INSPECTED ELEVATOR AND TABS IAW SB 190 AND SB 142. STRIPPED PAINT ON ALL HORIZONTAL TAIL FEATHERS. FOUND NUMEROUS POIN TS OF CORROSION. IT EXTENDED INSIDE WHERE NOT VISIBLE FOR NORMAL INSPECTION PROCEDURES. RIBS, REAR STRINGER, SKIN PIEC ES. ALL HAD CORROSION HIDDEN UNDER APPLIED PREVENTATIVE PRIMER. INSPECTION CAN ONLY BE ACCOMPLISHED BY DISASSEMBLY. V ERTICAL INSPECTED PREVIOUSLY, NO CORROSION. 1 H 7 2 3O A17EU 1996030100529 19960301 00529 SO 1996 3 1 96ZZZX888 1 19960124 G 2434 BRUSH HOLDER DELCO 1101915 PIPER PA30 PA30 7103002 SO RT ENG GEN BROKEN D K NONE O OTHER IN INSP/MAINT 1 GL 27 8383Y 10255 301538 RIGHT ENGINE GENERATOR INOPERATIVE. FOUND BRUSH HOLDER BROKEN AND PIECES HAD SHORTED OUT ARMATURE. INSTALLED REBUILT U NIT. 1 L 7 2 3O A1EA 1996030100531 19960301 00531 NE 1996 3 1 96ZZZX890 2 19960115 G 7210 310835601 SUN GEAR BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE POWER SECTION DEFECTIVE B MASR K NONE O OTHER IN INSP/MAINT 1 SW 01 5YV 6668 21C611 UE05 114046 ALTHOUGH ALL INDICATIONS POINT TO AN ELECTRICAL DISCHARGE, THE POSSIBILITY OF A SUN GEAR FAILURE IS NOT BEING RULED OUT. THE NR 6 BEARING AND THE SUN GEAR WILL BE SHIPPED FOR FURTEHR INVESTIGATION. 2 L 7 2 4T 4 T RT A24CE E26NE 1996030800141 19960308 00141 WP 1996 3 8 96ZZZX920 1 19960109 G 5320 PANEL DOUG DC10 DC1030 3023501 WP FS 1420 CRACKED B ZJ4R K NONE O OTHER IN INSP/MAINT 1 SO 13 229NW 88344 23313 46551 DURING L-CHECK, FOUND RIGHT MLG WHEELWELL OUTBOARD PANEL IN SCW 118, FS 1420, HAS A .50 INCH CRACK IN LEFT CORNER. FABR ICATED DOUBLER, STOP DRILLED CRACK, SEALED AND INSTALLED DOUBLER IAW SRM 53-00-01. 2 L 7 3 4F A22WE 1996030800543 19960308 00543 CE 1996 3 8 96ZZZX931 1 19960118 G 7900 58551761 SEPARATOR CESSNA 404 404CESSNA 2075901 CE ENG AIR/OIL FROZE H A O OTHER K FLUID LOSS NR NOT REPORTED 1 NM 03 409EX 4040436 THE AIR OUTLETS OF THE AIR/OIL SEPARATORS FROZE OVER, APPARENTLY, FROM INTERNAL MOISTURE CAUSING ALL ENGINE OIL TO BE PU MPED OVERBOARD ON THE LEFT ENGINE AND ALL BUT 3 QUARTS ON RIGHT ENGINE. LEFT ENGINE FAILED DUE TO OIL STARVATION. 1 L 7 2 3O A25CE 1996030800544 19960308 00544 CE 1996 3 8 96ZZZX932 1 19960209 G 5711 SPAR BEECH 33 F33A 1151425 CE WING CARRY-THRU CRACKED B A VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 8253C 5583 CE1546 FOUND CRACKS IN WING SPAR CARRY-THROUGH STRUCTURE. AD 95-04-03, NOT APPLICABLE BY SERIAL NUMBER OF AIRCRAFT. 1 L 7 1 3O 3A15 1996030800548 19960308 00548 CE 1996 3 8 96ZZZX937 1 19960131 G 3213 51411035 BARREL ASSY 51411011 CESSNA 402 402C 207590R CE LT MLG CRACKED D K NONE O OTHER IN INSP/MAINT 1 AL 03 6878L 11549 402C0607 TRUNNION BARREL ASSY CRACKED AT THE TORQUE LINKS/LUGS AND IS COVERED BY CESSNA SB MEB 89-2. SUSPECT WORN OUT OF ROUND T ORQUE LINKS/LUGS AND TORQUE LINK BUSHINGS CAUSING SEVERE MLG SHIMMY. 1 L 7 2 3O A7CE 1996030800549 19960308 00549 SO 1996 3 8 96ZZZX938 2 19960130 G 7324 LINE PIPER PA34 PA34200T 7103406 SO CONT O360 TSIO360E 17025 SO NR 6 NOZ B-NUT BROKE H O OTHER E R K VIBRATION/BUFFET PARTIAL RPM/PWR LOSS FLUID LOSS NR NOT REPORTED 1 SO 01 999CC 347570159 303156 FUEL LINE FROM FLOW DIVIDER TO NR 6 NOZZLE BROKE AT B-NUT NOZZLE AND SPRAYED RAW FUEL ON ENGINE. ENGINE ROUGH, BUT NOT SHUT DOWN AND LANDED OK WITH NO FIRE. VERY LUCKY! 1 L 7 2 3O 3 O A7SO E9CE 1996030800551 19960308 00551 CE 1996 3 8 96ZZZX940 1 19960209 G 5711 SPAR BEECH 33 F33A 1151425 CE WING CARRY-THRU CRACKS B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 8251C 5840 CE1543 FOUND CRACKS IN WING SPAR CARRY-THROUGH STRUCTURE, AD 95-04-03. NOT APPLICABLE BY SERIAL NUMBER OF AIRCRAFT. 1 L 7 1 3O 3A15 1996030800552 19960308 00552 EA 1996 3 8 96ZZZX941 2 19960220 G 8530 73806 PUSHROD CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA NR 4 CYL EXH FAILED G A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CL CLIMB 1 SW 99 6110Q 15285135 L1545415 AIRCRAFT CRASHED AFTER TAKEOFF. POST-CRASH INSPECTION REVEALED NR 4 CYLINDER EXHAUST PUSHROD BROKEN AT VALVE END. NR 4 EXHAUST VALVE NOT IN OPERATION DUE TO BREAK OF PUSHROD. AD 80-25-02 AND AD 95-03-10 WERE ISSUED PERTAINING O-235 PUSHR ODS. TWO OTHER PUSHROD INCIDENTS WERE NOTED FROM CESSNA OWNER'S ORGANIZATION MAGAZINE, MARCH '96 ISSUE. SUBJECT PUSHRO D IAW OF AD 80-25-02 AND AD 95-03-10. 1 H 7 1 3O 3 O NT 3A19 E223 1996030800553 19960308 00553 CE 1996 3 8 96ZZZX942 1 19960222 G 5347 05112408 TRACK CESSNA 172 172K 2072430 CE RT PAX SIDE CORRODED B EVGR K NONE O OTHER IN INSP/MAINT 1 SO 05 7381G 17259081 INTERGRANULAR CORROSION FOUND 8 INCHES AFT OF LEADING EDGE ON SEAT TRACK, RT PASSENGER SIDE. 1 H 7 1 3O NT 3A12 1996030800554 19960308 00554 CE 1996 3 8 96ZZZX943 1 19960222 G 2731 051010545 CONTROL CABLE CESSNA 172 172K 2072430 CE RIM AFT PULLEY BROKEN B EVGR K NONE O OTHER IN INSP/MAINT 1 SO 05 7381G 1725081 TRIM CABLE FOUND RUSTED AND PULLEY 'FROZEN'. THE CABLE BROKE WHEN THE TRIM WAS ACTUATED. 1 H 7 1 3O NT 3A12 1996030800556 19960308 00556 SO 1996 3 8 96ZZZX945 2 19960131 G 8520 BOLT CONT O520 IO520L 17032 SO CRANK GEAR WRONG PART D K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 11 4591 1105 567254 THIS ENGINE WAS RECEIVED FOR A CASE CHANGE. THE CRANKSHAFT WAS A NON VAR. REMOVED THE 6 BOLTS THAT ATTACH THE CRANK GE AR AND BOLTS FOUND APROXIMATELY .25 INCH SHORTER THAN REQUIRED. SUBMITTER STATES WHOEVER ASSEMBLED THIS ENGINE PUT ROCK ER SHAFT BOLTS, PN 537019, INSTEAD OF PN 536379, AS REQUIRED. LOG BOOKS WERE NOT SENT. 3 O E5CE 1996030800557 19960308 00557 1996 3 8 96ZZZX946 4 19960213 G 3416 3431 CASTING UNITEDINST 5934P1 BEECH 33 3533 1151402 CE END SHAKE OUT OF TOLERANCE B EI4R K NONE O OTHER IN INSP/MAINT 1 SO 15 316Z J1083 CD213 THE CRITICAL SHAFT END SHAKES WERE CHECKED ON THIS INSTRUMENT. OVERHAUL MANUAL CALLS OUT .002 INCH TO .003 INCH. THESE END SHAKES MEASURED .0010 INCH, .0012 INCH, AND .0003 INCH. THE .0003 INCH END SHAKE COULD CAUSE THE POINTERS TO HANG UP IN THE LOWER TEMP. SUBMITTER STATES ACCORDING TO A FACTORY ALERT SERVICE BULLETIN, A FIX WAS IMPLEMENTED (FAA APPROV ED), AND THIS ELIMINATED THE UNDER TOLERANCE CONDITION. 1 L 7 1 3O 3A15 1996030800558 19960308 00558 SO 1996 3 8 96ZZZX947 1 19960106 G 5542 6339600 SKIN PIPER PA28 PA28R200 7102811 SO RUDDER CRACKED D K NONE O OTHER IN INSP/MAINT 1 NE 01 4524X 287635069 RUDDER SKIN CRACKED AT AFT END OF SKIN DIMPLES. SUBMITTER SUSPECTS FAILURE CAUSED BY PILOTS GRIPPING SKIN TO CHECK RUDD ER ON PRE-FLIGHT. 1 L 7 1 3O 2A13 1996030800559 19960308 00559 SO 1996 3 8 96ZZZX948 2 19960213 G 8530 653445STL CYLINDER BEECH 58 58 1152740 CE CONT O520 IO520CB 17032 SO SPARK PLUG BOSS CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 07 3695V TH1183 282448R CYLINDER CRACKED IN SPARK PLUG BOSS. CRACK WAS HEADING TO FUEL INJECTOR BOSS. ENGINE ONLY HAD 1,078.7 HOURS TOTAL TIME . 1 L 7 2 3O 3 O 3A16 E5CE 1996030800560 19960308 00560 SO 1996 3 8 96ZZZX949 1 19960106 G 2510 9809300 FRAME ASSY PIPER PA28 PA28R200 7102811 SO COPILOT SEAT CRACKED D K NONE O OTHER IN INSP/MAINT 1 NE 01 4524X 6603 28R7635069 CO-PILOT'S SEAT BACK FRAME CRACKED AND BROKEN ABOVE HINGE POINTS. LEFT SIDE COMPLETELY SEPARATED. RIGHT SIDE CRACKED T HREE-FOURTHS WAY AROUND FRAME MEMBER. DISCOVERED DURING ANNUAL INSPECTION. SUBMITTER SUSPECTS STRESS AND FATIGUE FROM EXIT AND ENTRANCE. 1 L 7 1 3O 2A13 1996030800563 19960308 00563 CE 1996 3 8 96ZZZX952 1 19960215 G 5312 12134072 BULKHEAD CESSNA 206 U206B 2073322 CE STRUT ATTACH CRACKED D K NONE O OTHER IN INSP/MAINT 1 AL 03 3870G 3845 U2060870 ANNUAL INSPECTION REVEALED BOTH LEFT AND RIGHT SIDES OF LOWER FORWARD DOORPOST BULKHEAD (PN 1213407-2) CRACKED AS SHOWN IN CESSNA SEB 93-5R1. ALTHOUGH ACFT IS BELOW THE 4,000-HOUR TOTAL TIME SHOWN IN SERVICE BULLETIN, EXTENSIVE FLOAT OPERA TION AND PRIOR DAMAGE HISTORY CONTRIBUTED TO EARLY CRACKING. THIS INSPECTION IS EASILY ACCOMPLISHED DURING ANNUAL INSPE CTION AND SHOULD BE ACCOMPLISHED ON ALL AIRCRAFT OPERATED ON FLOATS. 1 H 7 1 3O A4CE 1996030800564 19960308 00564 CE 1996 3 8 96ZZZX953 1 19960201 G 2912 30018 FILTER HOUSING LEAR 25 25 5170506 CE HYDRAULIC SYSTEM FAILED C O OTHER J WARNING INDICATION AP APPROACH 1 SO 17 155AG 037 AFTER GEAR EXTENSION, ALL HYDRAULIC PRESSURE WAS LOST. EMERGENCY PROCEDURES WERE CARRIED OUT PER THE AFM AND LANDING WA S ACCOMPLISHED WITHOUT INCIDENT USING EMERGENCY AIR PRESSURE FOR BRAKING. FOUND HYDRAULIC PRESSURE WAS LOST DUE TO HYDR AULIC FILTER HOUSING FAILING. 2 L 7 2 4J A10CE 1996030800565 19960308 00565 CE 1996 3 8 96ZZZX954 1 19960218 G 2752 99120071 ACTUATOR CESSNA 500 S550 2076607 CE RT FLAP DEFECTIVE B CWQR K NONE O OTHER IN INSP/MAINT 1 GL 05 274QS 3899 S5500074 DURING PHASE 12 INSPECTION, RIGHT FLAP ACTUATOR FAILED INTERNAL LEAKAGE CHECK. REPLACED ACTUATOR. ACTUATOR INTERNAL O- RING FAILURE SUSPECTED CAUSE. THIS IS THE FIRST TIME AN ACTUATOR HAS FAILED THIS TEST ON A PHASE 12 INSPECTION HERE. 1 L 7 2 4F RT A22CE 1996030800566 19960308 00566 CE 1996 3 8 96ZZZX955 1 19960218 G 2430 BD161 CONNECTOR CESSNA 500 S550 2076607 CE BATTERY DEFECTIVE B CWQR K NONE O OTHER IN INSP/MAINT 1 GL 05 112QS 9105 S5500112 DURING INSPECTION, FOUND BATTERY ELCON CONNECTOR NOT LOCKING PROPERLY. FOUND WEAR ON CONNECTOR LOCKING LUGS. THIS IS T HE THIRD TIME THIS HAS BEEN FOUND IN THE LAST 3 MONTHS. 1 L 7 2 4F RT A22CE 1996030800570 19960308 00570 EU 1996 3 8 96ZZZX959 1 19960216 G 2750 MS21027F271 SWITCH ISRAEL 1124 1124 4500102 EU FLAP TEST FAILED B WC7R K NONE O OTHER IN INSP/MAINT 1 GL 25 516AC 33 187 WRITE UP: 'FLAPS UNBALANCED'. WILL NOT TEST. TROUBLESHOOTING REVEALED THE FLAP UNBALANCED TEST SWITCH HAD FAILED INTE RNALLY. 2 M 7 2 4F A2SW 1996030800572 19960308 00572 CE 1996 3 8 96ZZZX961 1 19960209 G 2841 4413041 GAUGE STWARNER CESSNA 206 206CESSNA 2073302 CE LT FUEL FAILED D K NONE O OTHER IN INSP/MAINT 1 AL 01 2070K 821 813192 2060196 LEFT FUEL GAUGE SHOWED FULL DEFLECTION WHENEVER POWER WAS ON. JUMPER WIRE CONNECTION TO RT TRANSMITTER WITH AN EMPTY TA NK AND TO A NEW TRANSMITTER GOT SAME RESULT, GAUGE WAS EXCHANGED FOR NEW SURPLUS AND OPS CHECK OK FOR FULL RANGE OF TRAN SMISSION FLOAT TRAVEL. 1 H 7 1 3O A4CE 1996030800574 19960308 00574 CE 1996 3 8 96ZZZX963 1 19960209 G 2750 031212325Y004 FLEX DRIVE BEECH 90 6590 1152904 CE RT OTBD FLAP NUT CRACKED D K NONE O OTHER IN INSP/MAINT 1 AL 01 5245F LJ92 B-NUT SECURING RIGHT OUTBOARD FLAP FLEXIBLE DRIVE TO FLAP ACTUATOR FOUND CRACKED DURING SCHEDULED INSPECTION. DEFECTIVE PART REPLACED WITH NEW. 1 L 7 2 3T 3A20 1996030800575 19960308 00575 CE 1996 3 8 96ZZZX964 1 19960205 G 7830 REVERSER LEAR 55 55LEAR 5170702 CE LT ENG T/R MALFUNCTION B CW1R O OTHER O OTHER LD LANDING 1 EA 25 725K 6959 5131 093 UPON LANDING, THRUST REVERSER FAILED TO STOW ALL THE WAY, PILOT TRIED TO CYCLE T/R SEVERAL TIMES WITH NO SUCCESS, CAUSIN G MORE DAMAGE. APPEARS BLOCKER DOORS DID NOT GET CLOSED ALL THE WAY BEFORE STOWING AND CAUGHT ON LIP OF THE T/R STRUCTU RE. 2 L 7 2 4F A10CE 1996030800576 19960308 00576 CE 1996 3 8 96ZZZX965 1 19960220 G 3230 UPLOCK SYSTEM CESSNA 525 525 2076601 CE MLG MALFUNCTIONED B CNQR O OTHER J WARNING INDICATION CR CRUISE 1 CE 07 70KW 5250050 BOTH MAIN LANDING GEAR DROPPED FROM THE WHEELWELLS AT FL 350 WITH THE GEAR UNLOCK LIGHT AND HYDRAULIC PRESSURE ON LIGHT ILLUMINATED. CHECKED ALL LANDING GEAR WIRING AND SWITCHES. REPLACED THE LANDING GEAR CONTROL VALVE AND HYDRAULIC PRESS URE RELIEF VALVE. PERFORMED A SATISFACTORY OPERATIONAL CHECK OF THE LANDING GEAR SYSTEM. AIRCRAFT TOTAL TIME, 440.9 HO URS AND 365 LANDINGS. 1 L 7 2 4F RT A1WI 1996030800577 19960308 00577 CE 1996 3 8 96ZZZX966 1 19960214 G 2720 717 SOLENOID BEECH 200 B200 1152922 CE LT RUD BOOST FAILED B FGQR K NONE F FLT CONT AFFECTED NR NOT REPORTED 1 SO 01 700WP 2132 5616 BB1313 AIRCRAFT YAWS TO LEFT IN-FLIGHT AND VEERS LEFT ON GROUND. FOUND LEFT RUDDER BOOST CONTROL SOLENOID FAILED IN OPEN POSIT ION ALLOWING BLEED AIR TO THE BOOST ACTUATOR. REGARDLESS OF RUDDER BOOST SWITCH ON OR OFF, RIGHT RUDDER BOOST SOLENOID PREVIOUSLY HAD SAME PROBLEM. TOTAL TIME, 2,066.1 HOURS. SUSPECT CAUSE - MOISTURE CONTAMINATION. SUBMITTER STATES TO M AKE SURE, PN 101-524009-91, RUDDER BOOST AIR FILTER IS INSTALLED. FILTER HAS A MOISTURE DRAIN BEECH SERVICE COMMUNIQUE, NR 60 REFERENCES THIS. 1 L 7 2 4T A24CE 1996030800579 19960308 00579 EU 1996 3 8 96ZZZX968 1 19960126 G 2810 9870019B RELIEF VALVE BRAERO 1000 BAE1251000 1500287 EU FUEL TANK LEAKING D K NONE K W FLUID LOSS INADEQUATE Q C IN INSP/MAINT 1 SW 11 533QS 259033 THE AIRCRAFT WAS DETERMINED TO HAVE LEAKING THERMAL RELIEF VALVE. ORDERED REPLACEMENT PART. RECEIVED 4 EACH NEW RELIEF VALVES. ALL 4 EACH LEAKED. SUBMITTER SUSPECTS SPRING IS WEAK OR POOR FIT OF PISTON. 2 L 7 2 4F RT A3EU 1996030800580 19960308 00580 NM 1996 3 8 96ZZZX969 1 19960110 G 5320 CHORD BOEING 737 737247 138448D NM BS 727 STR 20L CRACKED B S5WR K NONE O OTHER IN INSP/MAINT 1 SW 01 302VA 20126 BS 727 CHORD CRACKED STR 29L - STR 21L. REPAIRED IAW VISCOUNT AIR SERV. E.O. 53-10-03. REF SB 737-53-1088. 2 L 7 2 4F A16WE 1996030800584 19960308 00584 CE 1996 3 8 96ZZZX973 1 19960215 G 3240 07515500 TORQUE PLATE PARKERHANFIN 03014400 BEECH 90 E90 1152914 CE RT BRAKE CRACKED C S K NONE O OTHER IN INSP/MAINT 1 WP 07 228RA 1128 2346 LW197 OUTER PORTION OF UPPER FORWARD BUSHING BOSS OF BRAKE IS CRACKED CLEAN THROUGH. SUSPECT EXCESSIVELY HARD BRAKING WHILE B RAKE IS HOT. INFORMATION RETRIEVED FROM CLEVELAND INSTALLATION MANUAL FOR CONVERSION KIT NR 199-90/199-90A. 1 L 7 2 3T 3A20 1996031500077 19960315 00077 WP 1996 3 15 96ZZZX974 1 19960213 G 6210 369D21100517 BLADE HUGHES 369 369E 4470707 WP M/R DEFECTIVE G L CHIR K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 07 1611W 198 H992 0319E ABRASION STRIPS ON 3 BLADES WERE NOT INSTALLED CORRECTLY. THEY DO NOT GO ALL THE WAY TO THE EDGE. BLADES ARE BEING SE NT TO RBI FOR REPAIR. SERIAL NUMBERS, H992, H991, AND H990. REFERENCE: OPERATOR CONTROL NR MLTA960213. 1 G 7 1 3U H3WE 1996031500078 19960315 00078 WP 1996 3 15 96ZZZX975 1 19960205 G 6210 369D21100517 BLADE HUGHES 369 369E 4470707 WP M/R DEBONDED B CHIR K NONE O OTHER IN INSP/MAINT 1 NM 09 1611W 198 0319E ABRASION STRIP WAS FOUND DEBONDED, BOTTOM AREA OF 1 INCH BY 19 INCHES. BLADE SENT TO RBI FOR REPAIR. REFERENCE: OPERA TOR CONTROL NR MLTA960205. 1 G 7 1 3U H3WE 1996031500079 19960315 00079 WP 1996 3 15 96ZZZX976 1 19960206 G 6410 369A16197 ARM HUGHES 369 369E 4470707 WP TAIL ROTOR CRACKED B S CHIR K NONE O OTHER IN INSP/MAINT 1 NM 09 1611W 3394 22221331 0319E TAIL ROTOR GRIP ARM, PN 369A1619-7, FOUND CRACKED AT ONE OF THE RIVET HOLES. PART SENT TO MANUFACTURER FOR INVESTIGATIO N. NOTE: THIS IS THE 4 BLADE INSTALLATION. REFERENCE: OPERATOR CONTROL NR MLTA960206. 1 G 7 1 3U H3WE 1996031500097 19960315 00097 GL 1996 3 15 96ZZZX994 2 19960209 G 7323 23007505 GOVERNOR BOLKMS 105 BO105S 5626006 EU ALLSN 250C 250C20B 03013 GL ENGINE FAIL B AC2R K NONE O OTHER IN INSP/MAINT 1 SW 03 5059C 1499 86090389 S779 GOVERNOR SHAFT FAILED. REPLACED GOVERNOR. 1 G 7 2 3U 3 U H3EU E4CE 1996031500098 19960315 00098 NE 1996 3 15 96ZZZX995 1 19960129 G 3340 A402AR LIGHT SKRSKY S76 S76A 8143006 NE ANTI COLLISION LENS CRACKED B AC2R K NONE O OTHER IN INSP/MAINT 1 SW 03 7266K 398 760283 ANTI-COLLISION LIGHT LENS CAME UNGLUED AT SEAMS. REPLACED LENS. 1 G 7 2 3U H1NE 1997010900094 19970109 00094 EA 1997 1 9 97ZZZX1 2 19961021 G 7420 M6083 HARNESS SLICK 6351 AMTR 540 EDGE540 056020M GL LYC O540 IO540* 41532 EA TERMINAL CAP NU DEFECTIVE D K NONE O OTHER IN INSP/MAINT 1 NM 11 42GP 130 95060063 ALTHOUGH THIS PROBLEM OCCURRED ON AN EXPERIMENTAL ACROBATIC AIRCRAFT, IT IS BELIEVED IT COULD OCCUR ON ANY NEW ENGINE AP PLICATION. THE SPARK PLUG NUT IS SEIZED TO THE DRIVE FERRULE MAKING REMOVAL FROM THE SPARK PLUG IMPOSSIBLE WITHOUT HOLD ING THE DRIVE FERRULE. IT APPEARS THE SPARK PLUG NUT IS PLATED TOO HEAVILY RESULTING IN GALLING OF THE NUT TO THE DRIVE FERRULE. THE PLATING ALSO FORMS SLIVERS OF METAL WHICH DROP INTO THE SPARK PLUG CERAMIC. AFTER REMOVAL, THE DRIVE FER RULE IS COATED WITH AN ANTI-SEIZE COMPOUND. SUBSEQUENT OPERATION NORMAL. 1 M 7 1 3O 3 O NC EXPA1M71 1E4 1997010900103 19970109 00103 SO 1997 1 9 97ZZZX10 2 19961105 G 8530 641066 O-RING 649358A2 BEECH 36 36BEECH 1151602 CE CONT O550 IO550B SO CYL BASES MISSING D K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 69277 683 E2148 675571 FOUND CYLINDER BASE O-RING MISSING ON NR 5 CYLINDER. REMOVED NR 2 CYL. ALSO, NO O-RING ON CYL BASE. CHECK REMAINING C YLINDERS AFTER TALKING TO CONTINENTAL AND FOUND NO O-RINGS ON 3 CYLINDERS, NR 3 NR 4, AND NR 6. 1 L 7 1 3O 3 O 3A15 E3SO 1997010900435 19970109 00435 SW 1997 1 9 97ZZZX100 1 19961125 G 6330 LB61010161V LINK LORD 206033500006 BELL 206 206L1 1182107 SW XMSN MOUNT BEARING FAILED D A UNSCHED LANDING E VIBRATION/BUFFET TO TAKEOFF 1 SW 99 911SA 867 LK8423 45383 BACK SEAT CREW MEMBERS REPORTED VIBRATION IN AIRFRAME DURING TAKEOFF AND LANDING. INSPECTION OF PYLON MOUNT REVEALED LT AFT LINK HAD PLAY AND RUBBER EXTRUDING FROM UPPER BEARING. REPLACED LINK AND OPERATIONAL CHECK SHOWS VIBRATIONS FROM P REVIOUS FLIGHT MISSING. SUBMITTER STATED THIS IS A COMMON AND TYPICAL PROBLEM THAT ONLY REQUIRES GOOD VISUAL INSPECTION . 1 G 7 1 3U H2SW 1997010900436 19970109 00436 SW 1997 1 9 97ZZZX101 1 19961203 G 3310 2060755581 PANEL BELL 206 206B 1181511 SW COCKPIT SHORTED B A GJOR A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 NM 01 1076G 2495 2831 WHILE IN-FLIGHT, THE PILOT NOTICED SMOKE AT THE CABIN OVERHEAD. AFTER MAKING PRECAUTIONARY LANDING, IT WAS NOTED THAT T HE INSTRUMENT CIRCUIT BREAKER HAD POPPED. INVESTIGATION BY MAINT. REVEALED THAT THE LIGHTED PANEL HAD INTERNALLY SHORTE D. THE PANEL WAS REPLACED AND NO FURTHER DISCREPANCIES WERE FOUND. 1 G 7 1 3U H2SW 1997031300152 19970313 00152 NE 1997 3 13 97ZZZX1014 2 19960229 G 7322 CONTROL ROD BEECH 200 B200C 1152924 CE PWA PT6 PT6A42 52043 NE LT ENG FCU HUNG UP D A E ENGINE SHUTDOWN J WARNING INDICATION CR CRUISE 1 NM 05 107Z BL124 LEFT ENGINE CRUISE POWER REMAINED STEADY AFTER PILOT PULLED BACK POWER LEVER TO BEGIN DESCENT. ENGINE REACHED HIGH TORQ UE LIMIT AND HAD TO BE SHUT DOWN IN-FLIGHT. MAINTENANCE INSPECTED ENGINE AND FOUND THE COTTER PIN ON THE CASTELLATED NU T RETAINING THE FCU CONTROL ROD TO THE FUEL CONTROL ACTUATING LEVER ON THE CAM BOX HAD CAUGHT AND HUNG UP IN THE ENGINE COWLING. INSTALLED NEW COTTER PIN AND CORRECTLY SET SAME SO IT COULD NOT SNAG COWLING. 1 L 7 2 4T 4 T A24CE E4EA 1997031300154 19970313 00154 NE 1997 3 13 97ZZZX1016 2 19961212 G 7250 50L195 AIR SEAL PWA 4158 PW4158 NE 2ND STAGE HPTR CRACKED B DLAZ K NONE O OTHER IN INSP/MAINT 1 EA 33 PKGAN 11265 4726 T44897 724812 INSPECTED 2ND STAGE HPTR AIR SEAL AND FOUND CRACK INDICATION AS DESCRIBED IN PW4000 ALL OPER WIRE NOV 14, 1996 NR C301G9 61114XFR. MFG RECOMMENDATIONS SEE ASB PW4 ENGA72-628. 4 F E24NE 1997031300155 19970313 00155 NE 1997 3 13 97ZZZX1017 2 19961212 G 7250 50L195 AIR SEAL PWA 4158 PW4158 NE 2ND STAGE HPTR CRACKED B DLAZ K NONE O OTHER IN INSP/MAINT 1 EA 33 PKGAS 10370 4331 C332AA0166 724840 INSPECTED 2ND STAGE HPTR AIR SEAL AND FOUND CRACK INDICATION AS DESCRIBED IN PW4000 ALL OPER WIRE NOV 14, 1996 NR C301G9 61114XFR. MFG RECOMMENDATIONS SEE ASB PW4 ENGA72-628. 4 F E24NE 1997031300156 19970313 00156 NE 1997 3 13 97ZZZX1018 2 19961212 G 7250 50L195 AIR SEAL PWA 4158 PW4158 NE 2ND STAGE HPTR CRACKED B DLAZ K NONE O OTHER IN INSP/MAINT 1 EA 33 PKGAT 9313 3612 S72690 724088 INSPECTED 2ND STAGE HPTR AIR SEAL AND FOUND CRACK INDICATION AS DESCRIBED IN PW4000 ALL OPER WIRE NOV 14, 1996 NR C301G9 61114XFR. MFG RECOMMENDATIONS SEE ASB PW4 ENGA72-628. 4 F E24NE 1997031300157 19970313 00157 NE 1997 3 13 97ZZZX1019 2 19961212 G 7250 50L195 AIR SEAL PWA 4158 PW4158 NE 2ND STAGE HPTR CRACKED B DLAZ K NONE O OTHER IN INSP/MAINT 1 EA 33 PKGAN 12278 5015 T44846 724811 INSPECTED 2ND STAGE HPTR AIR SEAL AND FOUND CRACK INDICATION AS DESCRIBED IN PW4000 ALL OPER WIRE NOV 14, 1996 NR C301G9 61114XFR. MFG RECOMMENDATIONS SEE ASB PW4ENG172-628. 4 F E24NE 1997031300158 19970313 00158 NE 1997 3 13 97ZZZX1020 2 19961212 G 7250 50L195 AIR SEAL PWA 4158 PW4158 NE 2ND STAGE HPTR CRACKED B DLAZ K NONE O OTHER IN INSP/MAINT 1 EA 33 PKGAS 10774 4402 C332AA0128 724839 INSPECTED 2ND STAGE HPTR AIR SEAL AND FOUND CRACK INDICATION AS DESCRIBED IN PW4000 ALL OPER WIRE NOV 14, 1996 NR C301G9 61114XFR. MFG RECOMMENDATIONS SEE ASB PW4 ENGA72-628. 4 F E24NE 1997031300225 19970313 00225 1997 3 13 97ZZZX1045 1 19960203 G 4940 473682 HOUSING ALIDSIGNAL 5198022 APU STARTER DEFECTIVE B KQ4R K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 17 107269 INSIDE DIAMETER OF END BELL WHICH RECEIVES THE INSERT IS OVERSIZED BY .1245 INCH. A BUSHING FABRICATED FROM WHAT APPEAR S TO BE STEEL WAS FOUND INSTALLED IN PLACE OF THE REQUIRED OEM INSERT. THIS IS CONTRARY TO THE OEM MANUAL. ATA 49-20-0 8, PAGE 626, FIGURE 607. HOUSING HAS BEEN REJECTED ALONG WITH FABRICATED BUSHINGS AT THIS FACILITY. 1997010900441 19970109 00441 NE 1997 1 9 97ZZZX106 2 19961104 G 7250 783319 LPT SHAFT PWA JT8 JT8D217A 52053 NE N1 TURBINE DISTORTED D K NONE E VIBRATION/BUFFET IN INSP/MAINT 1 SW 05 20159 3206 R69021 708414 ENGINE WAS REMOVED FROM SERVICE DUE TO VIBRATION. DISASSEMBLY OF THE ENGINE REVEALED THAT AN OIL FIRE HAD OCCURRED IN T HE N2 COMPRESSOR CENTER TUBE CAUSING THE LPT SHAFT TO DISTORT AND RUB WHICH RESULTED IN ENGINE VIBRATION. THE FAILURE I S STILL UNDER INVESTIGATION. 4 F E9NE 1997031300246 19970313 00246 NE 1997 3 13 97ZZZX1064 2 19960915 G 8530 CYLINDER SCWZER G164 G164A 3952704 EA PWA R985 R985AN14B 52008 NE NR 4 CRACKED H K NONE O OTHER IN INSP/MAINT 1 SO 05 8866H 361 1553 21433 INSPECTION FOUND NR 4 CYLINDER CRACKED AROUND HEAD OF CYLINDER JUST ABOVE THE TOP OF THE CYLINDER BARREL. 1 Q 7 1 3R 3 R 1A16 5E1 1997010900442 19970109 00442 NE 1997 1 9 97ZZZX107 2 19961108 G 7230 500588701 STATOR VANE PWA JT8 JT8D219 52053 NE C7 STATOR FAILED D K NONE O OTHER IN INSP/MAINT 1 SW 05 TV9031 716792 ENGINE WAS REMOVED FROM SERVICE DUE TO COMRPESSOR STALLS, IN-FLIGHT SHUT DOWN AND HEAVY TURBINE DAMAGE. DISASSEMBLY OF THE ENGINE REVEALED THAT THE C7 STATOR HAD LIBERATED A VANE CAUSING HEAVY N2 COMPRESSOR DAMAGE WHICH RESULTED IN STALLS AND N1 AND N2 TURBINE DAMAGE. THE FAILURE IS UNDER INVESTIGATION. 4 F E9NE 1997010900443 19970109 00443 NE 1997 1 9 97ZZZX108 2 19961121 G 7313 5004308032 NOZZLE SUPPORT PWA JT8 JT8D219 52053 NE NR 3 POS NOZZLE NUT LOOSE D K NONE O OTHER IN INSP/MAINT 1 SW 03 5494 BV5444 709702 INSPECTION OF THE NR 3 POSITION FUEL NOZZLE AND SUPPORT ASSEMBLY REVEALED THAT THE NUT WAS LOOSE. THE INSPECTOR WAS ABL E TO REMOVE THE NUT FROM THE SUPPORT BY HAND. THREADS WERE BADLY WORN. CONDITION IS UNDER INVESTIGATION BY P AND W. 4 F E9NE 1997011400007 19970114 00007 SW 1997 1 14 97ZZZX109 1 19961101 G 5741 NAS15033 BOLT SWRNGN SA226 SA226AT 8780405 SW WING ATTACH CORRODED D K NONE O OTHER IN INSP/MAINT 1 SW 03 1YC T26131 AIRCRAFT HAS IN EXCESS OF 5,000 HRS. REMOVED WING ATTACH BOLTS AT CUSTOMER'S REQUEST AND FOUND SEVERE CORROSION AND PIT TING. REPLACED BOLTS WITH NEW. RECOMMEND INSPECTING BOLTS ANNUALLY. 2 L 7 2 4T RT A5SW 1997010900104 19970109 00104 SO 1997 1 9 97ZZZX11 1 19961201 G 2436 X16300B REGULATOR PIPER PA32 PA32260 7103206 SO DC SYS INOPERATIVE B GOGR K NONE O OTHER IN INSP/MAINT 1 SW 11 7731J 321134 TROUBLESHOT ELECTRICAL SYSTEM AND FOUND VOLTAGE REGULATOR TO BE INOPERATIVE. 1 L 7 1 3O A3SO 1997010900444 19970109 00444 NM 1997 1 9 97ZZZX110 1 19961218 G 3240 211473 BRAKE ASSY BFGOODRICH BOEING 727 727 1384001 NM MLG LOCK UP B QVIR K NONE O OTHER NR NOT REPORTED 1 SO 19 2FOR 7472 BRAKE LOCKED UP. HIGH TEMPERATURE. 2 L 7 3 4F A3WE 1997010900445 19970109 00445 NM 1997 1 9 97ZZZX111 1 19961219 G 3230 65800519 DRAG BRACE BOEING 737 737297 1384480 NM NLG DAMAGED B B4GR K NONE O OTHER IN INSP/MAINT 1 SO 19 147AW 339 22630 DRAG BRACE SENT TO BFG FOR REPAIR. FOUND BEARING MIGRATED FROM LOCATION CAUSING DAMAGE TO BRACE DURING GEAR ACTUATION. BEARING INSTALLATION RECORDS NOT AVAILABLE TO BFG AT THIS TIME. CAUSE UNKNOWN. (REP STA NR B4GR448J). 2 L 7 2 4F A16WE 1997010900446 19970109 00446 NM 1997 1 9 97ZZZX112 1 19961219 G 3230 658005118 DRAG BRACE BOEING 737 73733A 1384673 NM NLG DAMAGED B B4GR K NONE O OTHER IN INSP/MAINT 1 SO 19 173AW 588728 23632 SENT FOR REPAIR. BEARING MIGRATED FROM LOCATION CAUSING DAMAGE TO BRACE DURING ACTUATION. BEARING INSTALLED AND TESTED PER BAC 0HM 32-10-03. CAUSE OF MIGRATION IS UNKNOWN. ( REP STA NR B4GR448J). 2 L 7 2 4F RT A16WE 1997032000701 19970320 00701 GL 1997 3 20 97ZZZX1129 1 19961016 G 7910 DRAIN EXTENSION AMTR MINEAR PIETENPOL 7040220 GL OIL SUMP FAILED H P A A UNSCHED LANDING K FLUID LOSS NR NOT REPORTED 1 SW 99 63SB 120 FORCED LANDING (ENG FAILED). INVESTIGATION REVEALED THAT THE OIL DRAIN EXTENSION, WHICH WAS MADE OF COPPER TUBING, HAD BROKEN OFF AT THE ADAPTER ON THE BOTTOM OF THE OIL SUMP CAUSING THE TOTAL LOSS OF LUBRICATING OIL. A REVIEW OF THE AIRC RAFT PLANS SHOWED NO EXTENSION, BUT THE ORIGINAL DRAIN PLUG ONLY. 1 H 7 1 3O NC EXPA1H71 1997010900447 19970109 00447 NM 1997 1 9 97ZZZX113 1 19961219 G 3230 658005118 DRAG BRACE BOEING 737 7373S3 1384711 NM NLG DAMAGED B B4GR K NONE O OTHER IN INSP/MAINT 1 SO 19 313AW 23712 DRAG BRACE SENT FOR REPAIR. BEARING MIGRATED FROM LOCATION CAUSING DAMAGE TO BRACE DURING GEAR ACTUATION. BEARING INST ALLED AND TESTED PER BAC OHM 32-01-03. CAUSE OF MIGRATION IS UNKNOWN. 2 L 7 2 4F RT A16WE 1997010900448 19970109 00448 CE 1997 1 9 97ZZZX114 1 19961125 G 7830 66082313 SLIDE TRACK LEAR 35 35A 5170602 CE LT ENG TR REQUIRED LUBE G C D ABORTED TAKEOFF RETURN TO BLOCK J WARNING INDICATION TO TAKEOFF 1 GL 03 500HG 238 DURING TAXI TO TAKEOFF, FLIGHT CREW NOTICED T/R LIGHT ON, P.I.C. ABORTED TAKEOFF. MAINTENANCE PERSONNEL DISCOVERED T/R SLIDE TRACKS AND INDICATING SWITCHES WERE IN NEED OF LUBRICATION. MAINTENANCE CREW LUBE T/R SYSTEM. OPERATIONAL CHECK GOOD. 2 L 7 2 4F A10CE 1997010900449 19970109 00449 CE 1997 1 9 97ZZZX115 1 19961125 G 7830 66082314 SLIDE TRACK LEAR 35 35A 5170602 CE RT ENG TR REQUIRED LUBE G C D ABORTED TAKEOFF RETURN TO BLOCK J WARNING INDICATION TO TAKEOFF 1 GL 03 500HG 238 DURING TAXI TO TAKEOFF, FLIGHT CREW NOTICED T/R LIGHT ON, P.I.C. ABORTED TAKEOFF. MAINTENANCE PERSONNEL DISCOVERED T/R SLIDE TRACKS AND INDICATING SWITCHES WERE IN NEED OF LUBRICATION. MAINTENANCE CREW LUBE T/R SYSTEM. OPERATIONAL CHECK GOOD. 2 L 7 2 4F A10CE 1997010900450 19970109 00450 GL 1997 1 9 97ZZZX116 3 19961209 G 6110 BEARING MTSBSI MU2 MU2B60 5780460 CE HARTZL HCB4T HCB4TN5 GL PROP BLADE WORN D A K NONE O OTHER IN INSP/MAINT 1 GL 25 802SM 1622 1515SA CDA3194 DURING A ROUTINE 100 HR INSPECTION, IT WAS DISCOVERED THAT 2 OF THE 4 BLADES ON EACH OF THE 2 HARTZELL PROPELLERS HAD A ROUGH MOVEMENT WHEN ROTATED FROM REVERSE PITCH TO FEATHER POSITION AND BACK AGAIN. SENT BOTH PROPS TO A PROPELLER O/H F ACILITY AND FOUND THE BEARINGS ON THE ROUGH BLADES WERE WORN TO THE LIMITS. THIS IS THE SECOND TIME DISCOVERED THIS PRO BLEM ON THE 4 BLADED HARTZELL PROPELLERS INSTALLED ON THE MU-2 AIRCRAFT. 1 H 7 2 3T RT A10SW 6 C P40EA 1997032700238 19970327 00238 CE 1997 3 27 97ZZZX1168 1 19960730 G 2133 13035615 CONTROLLER GARRTT CESSNA 500 550 2076604 CE OUTFLOW VLV MISOVERHAULED H A A UNSCHED LANDING W INADEQUATE Q C CL CLIMB 1 SW 09 26621 193 79323 5500593 ACFT CLLIMBED TO FL 260. CREW NOTICED A DISCREPANCY IN THE CABIN PRESSURE DIFFERENTIAL, ALTITUDE AND CONTROLLER INDICAT ION. AFTER INVESTIGATION AND COMPARISON WITH ANOTHER ACFT, IT WAS FOUND DURING OVERHAUL THE INCORRECT FACE HAD BEEN INS TALLED ON THE RATE CONTROLLER. 1 L 7 2 4F A22CE 1997032700239 19970327 00239 CE 1997 3 27 97ZZZX1169 1 19960613 G 3230 S13771 SWITCH CESSNA 210 210M 2073450 CE RT MLG UPLOCK FAILED H O OTHER J WARNING INDICATION NR NOT REPORTED 1 SW 09 6265B 92 21062727 LANDING GEAR WOULD NOT EXTEND WHEN SELECTOR SWITCH WAS PLACED IN THE DOWN POSITION. AIRCRAFT PLACED ON JACKS TO TROUBLE SHOOT GEAR SYSTEM. RIGHT MAIN GEAR UPLOCK MICROSWITCH FOUND DEFECTIVE. REPLACED S1377-1 MICROSWITCH, AND RIGGED. OPER ATIONAL CHECK, GOOD. 1 H 7 1 3O 3A21 1997011400008 19970114 00008 SW 1997 1 14 97ZZZX117 1 19961110 G 5741 NAS15033 BOLT SWRNGN SA226 SA226AT 8780405 SW WING ATTACH CORROSION D K NONE O OTHER IN INSP/MAINT 1 SW 09 345T T26105 AIRCRAFT HAS IN EXCESS OF 5,000 HRS. REMOVED WING ATTACH BOLTS AT CUSTOMER'S REQUEST AND FOUND SEVERE CORROSION AND PIT TINGS. REPLACED BOLTS WITH NEW. RECOMMEND INSPECTING BOLTS ANNUALLY. 2 L 7 2 4T RT A5SW 1997010900451 19970109 00451 GL 1997 1 9 97ZZZX118 2 19961115 G 7250 23008020 TIE BOLT ALLSN 250C 250C20B 03013 GL GAS PROD FAILED B L HEER K NONE O OTHER IN INSP/MAINT 1 SW 03 1306 CAT36754 IN PROCESS OF REPAIRING A C20B TURBINE, FOR UNUSUAL NOISE AND CHIP LIGHT, FOUND GP TIE BOLT SN DJ 59 BROKEN APPROXIMATEL Y .6250 INCH BELOW SPANNER NUT ON NR 1 WHEEL SIDE. CANNOT READ THE COMPLETE SERIAL NUMBER AS IT IS COVERED WITH CARBON. CROSS SECTION OF THE BOLT IS HALF DARK, ONE-QUARTER LIGHTER AND REMAINING SECTION VERY LIGHT COLOR. NO BEARING FAILUR E OR WHEELS DISINTEGRATION HAD OCCURRED. NO OTHER DAMAGE TO ENGINE OR HELICOPTER WAS EXPERIENCED. THE INCIDENT HAPPENE D ON THE COAST DOWN WHEN UNUSUAL 'CLUNKING' NOISE WAS HEARD. TURBINE S/N IS CAT 36754. 3 U E4CE 1997010900456 19970109 00456 EU 1997 1 9 97ZZZX119 1 19961217 G 5320 25FN4735 WINDOW PAN HWKSLY DH125 DH1251A 4230106 EU LT DV WINDOW CRACKED B FE6R K NONE O OTHER IN INSP/MAINT 1 NM 11 125JR 25052 DURING A REPETITIVE 4-YEAR INSPECTION OF THE LEFT AND RIGHT DIRECT VISION WINDOW PANS (PN 25FN4735 AND 25FN4736) A 22 IN CH CRACK IS NOTED IN THE RIGHT PAN ALONG THE LOWER RADIUS. AN 8 INCH CRACK IS NOTED IN THE SAME LOCATION ON THE LEFT SI DE. SOME EXFOLIATION CORROSION IS NOTED ON THE FRAMES. AIRCRAFT WAS MANUFACTURED IN 1965 AND IS REPORTED TO HAVE 8658. 5 HRS AND APPROX 8300 AIRFRAME CYCLES, WHICH IS CERTAINLY NOT EXCESSIVE FOR ITS AGE AND PURPOSE. IT IS DIFFICULT TO IMA GINE THE RIGHT WINDOW CRACK PROGRESSING TO THIS LENGTH IN 4 YEARS. THE MANUFACTURER OF THE AIRCRAFT HAD TO RETOOL TO PR ODUCE THE REPLACEMENT PARTS. 2 L 7 2 4J A3EU 1997010900457 19970109 00457 EU 1997 1 9 97ZZZX120 1 19961217 G 5320 25FN4736 WINDOW PAN HWKSLY DH125 DH1251A 4230106 EU RT DV WINDOW CRACKED B FE6R K NONE O OTHER IN INSP/MAINT 1 NM 11 125JR 25052 DURING A REPETITIVE 4- YEAR INSPECTION OF THE LEFT AND RIGHT DIRECT VISION WINDOW PANS (PN 25FN4735 AND 25FN4736) A 22 I NCH CRACK IS NOTED IN THE RIGHT PAN ALONG THE LOWER RADIUS. AN 8 INCH CRACK IS NOTED IN THE SAME LOCATION ON THE LEFT S IDE. SOME EXFOLIATION CORROSION IS NOTED ON THE FRAMES. AIRCRAFT WAS MANUFACTURED IN 1965 AND IS REPORTED TO HAVE 8658 .5 HRS AND APPROX 8300 AIRFRAME CYCLES, WHICH IS CERTAINLY NOT EXCESSIVE FOR ITS AGE AND PURPOSE. IT IS DIFFICULT TO IM AGINE THE NIGHT WINDOW CRACK PROGRESSING TO THIS LENGTH IN 4 YEARS. THE MANUFACTURER OF THE AIRCRAFT HAD TO RETOOL TO P RODUCE THE REPLACEMENT PARTS. 2 L 7 2 4J A3EU 1997011400011 19970114 00011 SW 1997 1 14 97ZZZX122 1 19961125 G 2910 70053H000A100 HOSE ASSY BELL 206 206L3 1182108 SW HYD PUMP LEAKING H L N1UM A UNSCHED LANDING K FLUID LOSS CR CRUISE 1 EA 11 608PD 2739 51270 DURING RETURN TO BASE, COMPLETE HYD SYS LOSS. AFTER LANDING, SEVERE HYD LEAK NOTED, BUT NO CAUSE FOUND PRIOR TO CLEAN U P. AFTER SERVICE AND RUN-UP, FOUND LINE TO HYD PUMP RUPTURED. SUBMITTER BELIEVES LINE DAMAGED DURING 300 HR SPLINE CHE CK INSP WHERE PUMP IS SEPARATED FROM TACH GEN. METHOD FLEXES LINE. 1 G 7 1 3U H2SW 1997010900767 19970109 00767 GL 1997 1 9 97ZZZX123 3 19961105 G 6111 C2987 BEARING CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL BLADE CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 795375 INSPECTION FOUND BLADE BEARING RACE CORROSION. P/N C2987. 1 L 7 2 3O 3A25 5 C P22EA 1997010900768 19970109 00768 GL 1997 1 9 97ZZZX124 3 19961105 G 6111 C4451 FERRULE CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL BLADE CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 795375 INSPECTION FOUND FERRULE CORRODED. P/N C4451. 1 L 7 2 3O 3A25 5 C P22EA 1997040300306 19970403 00306 EU 1997 4 3 97ZZZX1249 1 19960915 G 7830 54535111 ACTUATOR AMD FALC20 FALCON20F5 2730105 EU T REV FAN FLAP LEAKING D K NONE K FLUID LOSS IN INSP/MAINT 1 GL 17 305AR 66 378 9-15-96 FOUND FAN FLAP ACTUATOR LEAKING BADLY ON T/R DEPLOY. ACTUATOR WAS REPAIRED 6-21-96. P/N AND S/N LISTED. 6-29- 96. APPROX 66 HOURS AND 74 CYLCES PRIOR TO CURRENT TIME, FOUND SAME P/N AND POSITION, ACTUATOR LEAKING. THIS ACTUATOR S/N 735 HAD APPROX 123 HRS, 130 CYCLES ON IT AND WAS INSTALLED ON 1-10-96. PRIOR TO THIS ACTUATOR, INSTALLED A LIKE ACT UATOR WHICH WAS JUST REPAIRED. THIS ACTUATOR LEAKED STRAIGHT OUT OF THE BOX, WORSE THAN THE ONE BEING REPLACED. 2 L 7 2 4F RT A7EU 1997010900769 19970109 00769 GL 1997 1 9 97ZZZX125 3 19961105 G 6114 D7015C93 HUB MCAULY 3AF32C 3AF32C93 GL PROPELLER DEFECTIVE B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 795369 INSPECTION FOUND HUB DEFECTIVE. BUSHING HOLE OVERSIZE. 5 C P22EA 1997010900770 19970109 00770 GL 1997 1 9 97ZZZX126 3 19961105 G 6111 82NC55 BLADE CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 K82853YS 795369 INSPECTION FOUND BLADE CORROSION. 1 L 7 2 3O 3A25 5 C P22EA 1997040300641 19970403 00641 WP 1997 4 3 97ZZZX1265 1 19961215 G 5320 T ANGLE DOUG DC10 DC1010 3022110 WP CTR CARGO DOOR CORRODED B MZAR K NONE O OTHER IN INSP/MAINT 1 SO 09 1837U 47969 DURING MPV MAINTENANCE CHECK, FOUND CENTER CARGO DOOR FRAME LOWER T-ANGLE EXFOLIATED, STA 1681, STR 44R. SUSPECT CAUSE WAS STRESS RELATED. APPLICATION OF CORROSION PREVENTIVE COULD PREVENT RECURRENCE. 2 L 7 3 4F A22WE 1997040300642 19970403 00642 WP 1997 4 3 97ZZZX1266 1 19961215 G 5313 LONGERON DOUG DC10 DC1010 3022110 WP FS 1506 CORRODED B MZAR K NONE O OTHER IN INSP/MAINT 1 SO 09 1837U 47969 DURING MPV MAINTENANCE CHECK, FOUND CENTER W/W TUNNEL LONGERON 48L LOWER FLANGE BADLY CORRODED, STA 1506. SUSPECT CAUSE WAS MOISTURE. PROPER APPLICATION OF CORROSION PREVENTIVE COULD PREVENT RECURRENCE. 2 L 7 3 4F A22WE 1997040300643 19970403 00643 WP 1997 4 3 97ZZZX1267 1 19961215 G 5313 LONGERON DOUG DC10 DC1010 3022110 WP FS 1521 CORRODED B MZAR K NONE O OTHER IN INSP/MAINT 1 SO 09 1837U 47969 DURING MPV MAINTENANCE CHECK, FOUND CENTER W/W TUNNEL, LONGERON 50L END FITTINGS CORRODED ALONG OTBD FLANGE, STA 1521. S USPECT CAUSE WAS MOISTURE. PROPER APPLICATION OF CORROSION PREVENTIVE COULD PREVENT RECURRENCE. 2 L 7 3 4F A22WE 1997040300644 19970403 00644 WP 1997 4 3 97ZZZX1268 1 19961215 G 5313 LONGERON DOUG DC10 DC1010 3022110 WP FS 1521 48L CORRODED B MZAR K NONE O OTHER IN INSP/MAINT 1 SO 09 1837U 47969 DURING MPV MAINTENANCE CHECK, FOUND CENTER W/W TUNNEL, 48L END FITTING AT STA 1521 BADLY PITTED ALONG OTBD FLANGE. SUSP ECT CAUSE WAS MOISTURE. PROPER APPLICATION OF CORROSION PREVENTIVE COULD PREVENT RECURRENCE. 2 L 7 3 4F A22WE 1997040300645 19970403 00645 WP 1997 4 3 97ZZZX1269 1 19961215 G 5330 SKIN DOUG DC10 DC1010 3022110 WP FS 1519 L49R CORRODED B MZAR K NONE O OTHER IN INSP/MAINT 1 SO 09 1837U 47969 DURING MPV MAINTENANCE CHECK, FOUND CENTER W/W TUNNEL SKIN CORRODED OTBD SIDE OF LONGERON 49R, STA 1519. SUSPECT CAUSE W AS MOISTURE. PROPER APPLICATION OF CORROSION PREVENTIVE COULD PREVENT RECURRENCE. 2 L 7 3 4F A22WE 1997010900771 19970109 00771 GL 1997 1 9 97ZZZX127 3 19961105 G 6111 82NC55 BLADE CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLLER CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 K82928YS 795369 INSPECTION FOUND BLADE CORROSION. 1 L 7 2 3O 3A25 5 C P22EA 1997010900772 19970109 00772 GL 1997 1 9 97ZZZX128 3 19961105 G 6110 A1896 PROP ASSY CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 795369 INSPECTION FOUND P/N A1896 PROP ASSY CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997010900773 19970109 00773 GL 1997 1 9 97ZZZX129 3 19961105 G 6110 A4191 PROP ASSY CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 795369 INSPECTION FOUND PROP ASSY P/N A4191 CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997010900106 19970109 00106 EA 1997 1 9 97ZZZX13 2 19961218 G 8550 LW14492 SUMP PIPER PA32 PA32301T 7103209 SO LYC O540 TIO540S1AD 41532 EA OIL SYS CRACKED D K NONE K W FLUID LOSS INADEQUATE Q C IN INSP/MAINT 1 SW 13 8339Z 114 328124013 L202761A THIS SUMP WAS INSTALLED ON AN ENGINE THAT CAME FROM LYCOMING AS A FACTORY OVERHAUL. THERE WOULD BE A SMALL PUDDLE OF OI L UNDER THE ACFT AFTER IT SAT IDLE FOR A FEW DAYS, BUT DURING OPERATION, NO APPRECIABLE AMOUNT WOULD SHOW UP ON IT. CRA CK WAS LOCATED WITH PENETRANT DEVELOPER. AFTER REMOVAL, IT WAS NOTED THAT THIS CRACK WAS IN AN AREA WHERE IT HAD BEEN G ROUND (ON THE INSIDE) DURING MANUFACTURE OR REPAIR. 1 L 7 1 3O 3 O A3SO E14EA 1997010900774 19970109 00774 GL 1997 1 9 97ZZZX130 3 19961105 G 6111 C2987 BEARING CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL BLADE CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 795369 INSPECTION FOUND BEARING RACE CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997010900775 19970109 00775 GL 1997 1 9 97ZZZX131 3 19961105 G 6110 B3490 PROP ASSY CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 795369 INSPECTION FOUND PROP ASSY P/N B3490 CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997040300833 19970403 00833 SO 1997 4 3 97ZZZX1314 1 19961231 G 2410 LW18129 BELT PIPER PA31 PA31350 7103110 SO RT ALTERNATOR FAILED B DQFR K NONE O OTHER NR NOT REPORTED 1 NM 07 27354 317752180 LEFT AND RIGHT ALTERNATOR BELTS WERE REPLACED WITH NEW BELTS AT PROPELLER OVERHAUL. WITHIN APPROXIMATELY 3 HRS, THE RT BELT FAILED DUE TO UNKNOWN REASONS AND LT BELT WAS SLIPPING DUE TO METEROLOGICAL CONDITIONS WHICH RESULTED IN LOSS OF EL ECTRICAL POWER. RE-ADJUSTED TENSION ON LT BELT AND INSTALLED NEW BELT ON RT SIDE AND ADJUSTED TENSION. PERFORMED ABOUT A 15-MINUTE RUN-UP AND RE-CHECKED TENSIONS. RECOMMEND CHECKING BELT ALIGNMENT AND RE-CHECKING BELT TENSION AFTER A GOO D GROUND RUN. 1 L 7 2 3O A20SO 1997040300835 19970403 00835 SO 1997 4 3 97ZZZX1316 2 19961005 G 8540 22532 BOLT CESSNA 150 150H 2071818 CE CONT O200 O200A 17020 SO ASSORY GRBOX FAILED G A UNSCHED LANDING Y ENGINE STOPPAGE CR CRUISE 1 EA 13 6741S 2450 356 15067541 674327A THE ENGINE QUIT SUDDENLY IN CRUISE FLIGHT WITHOUT WARNING AND WOULD NOT RESPOND TO RESTART ATTEMPTS. A NORMAL LANDING W AS MADE IN A FARM FIELD. DISASSEMBLY INSPECTION INDICATED THE FOUR BOLTS (22532) USED TO SECURE THE CRANKSHAFT CLUSTER GEAR (35016) BROKE OFF ALLOWING THE GEAR TO ROTATE INDEPENDENTLY OF THE CRANKSHAFT. PROPER ASSEMBLY WAS INDICATED BY RE MAINING SAFETY WIRE ON BOLT HEADS. FATIGUE FAILURE INDICATIONS WERE NOTED ON ONE BOLT IN THE THREADED AREA. REMAINING BOLT FRACTURE FACES WERE SMEARED. THE ENGINE MAY HAVE HAD A PREVIOUS SUDDEN STOPPAGE. REUSE OF THE BOLTS IS NOT CONTRA RY TO THE OVERHAUL MANUAL. RECOMMEND REPLACEMENT OF THESE BOLTS EACH ENGINE OVERHAUL OR PROPELLER STRIKE. 1 H 7 1 3O 3 O 3A19 E252 1997010900776 19970109 00776 GL 1997 1 9 97ZZZX132 3 19961105 G 6110 D3474 PROP ASSY CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER DEFECTIVE B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 795369 INSPECTION FOUND PROPELLER ASSEMBLY P/N D3474 DEFECTIVE. 1 L 7 2 3O 3A25 5 C P22EA 1997010900777 19970109 00777 GL 1997 1 9 97ZZZX133 3 19961105 G 6111 C4451 FERRULE CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 795369 INSPECTION FOUND BLADE FERRULE CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997041000041 19970410 00041 EU 1997 4 10 97ZZZX1334 1 19961023 G 3150 1179405201 ANNUNCIATOR BOLKMS 117 BK117B1 5626012 EU COCKPIT DEFECTIVE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 214AE 48 0104 7206 ONE SEGMENT DOES NOT LIGHT UP. SOME SEGMENT ROWS WILL NOT LOCK IN PLACE. ONLY INSTALLED FOR 47.9 HOURS BEFORE FAILED. 1 G 7 2 3U H13EU 1997041000042 19970410 00042 EU 1997 4 10 97ZZZX1335 1 19961223 G 6720 741C000005 ACTUATOR BOLKMS 117 BK117B1 5626012 EU T/R DEFECTIVE B TI1R K NONE F FLT CONT AFFECTED NR NOT REPORTED 1 SW 05 214AE 00248 7206 ON TEST FLIGHT AFTER INSTALLATION OF ACTUATOR, THE T/R PEDAL WAS STIFF IN LEFT FORWARD QUADRANT. 1 G 7 2 3U H13EU 1997041000043 19970410 00043 EU 1997 4 10 97ZZZX1336 1 19960927 G 6710 1174123101 STRAP ASSY BOLKMS BK117 BK117C1 5626025 EU CYCLIC CRACKED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 317MC 1600 7505 CYCLIC CENTERING STRAP ASSY CRACKED. 1 G 7 2 3U NC H13EU 1997041000044 19970410 00044 EU 1997 4 10 97ZZZX1337 1 19961212 G 6720 741C000005 ACTUATOR BOLKMS BK117 BK117C1 5626025 EU T/R LEAKING B TI1R K NONE K FLUID LOSS IN INSP/MAINT 1 SW 05 317MC 00506 7505 LEAKING ACTUATOR. 1 G 7 2 3U NC H13EU 1997041000045 19970410 00045 1997 4 10 97ZZZX1338 4 19961031 G 2312 069102525 DISPLAY KX165 BOLKMS BK117 BK117C1 5626025 EU COCKPIT VHF WEAK B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 317MC 7505 DISPLAY WEAK, SEGMENTS OUT. 1 G 7 2 3U NC H13EU 1997010900778 19970109 00778 GL 1997 1 9 97ZZZX134 3 19961105 G 6110 66070924017 PROP ASSY BAG JETSTM JETSTM3101 1500215 EU ROTOL R333 R333482F12 GL PROPELLER DAMAGED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 15075 5209 DRG60686 INSPECTION FOUND PROPELLER ASSY DAMAGED. 2 L 7 2 4T RT A21EU 6 C P61GL 1997041000048 19970410 00048 EU 1997 4 10 97ZZZX1341 1 19961213 G 6240 117945641 INDICATOR BOLKMS 117 BK117A3 5626015 EU MAST MOMENT DEFECTIVE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 911MZ E200830 7098 INDICATOR TESTS PASSED THE CALIBRATION LINE. 1 G 7 2 3U H13EU 1997041000051 19970410 00051 EU 1997 4 10 97ZZZX1344 1 19960929 G 6320 DK040 TRANSMITTER BOLKMS 105 BO105S 5626006 EU OIL PRESSURE DEFECTIVE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 105NG 151 7598 S632 OIL PRESSURE TRANSMITTER CAUSING OIL PRESSURE TO SPIKE INTERMITTENTLY. 1 G 7 2 3U H3EU 1997041000052 19970410 00052 1997 4 10 97ZZZX1345 4 19961125 G 2312 4000103000 TRANSCEIVER BOLKMS 117 BK117A3 5626015 EU COCKPIT VHF FAILED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 117CH 236 7061 TRANSCEIVER WILL NOT TRANSMIT. 1 G 7 2 3U H13EU 1997041000053 19970410 00053 1997 4 10 97ZZZX1346 4 19961112 G 2312 4000103001 TRANSCEIVER RT450 BOLKMS 117 BK117A3 5626015 EU COCKPIT FAILED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 117CH 613 7061 TRANSCEIVER WILL NOT RECEIVE. DID NOT WORK WHEN INSTALLED. 1 G 7 2 3U H13EU 1997041000054 19970410 00054 1997 4 10 97ZZZX1347 4 19961125 G 2312 4000103000 TRANSCEIVER RT450 BOLKMS 117 BK117A3 5626015 EU COCKPIT VHF INOPERATIVE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 117CH 642 7061 INOPERABLE COCKPIT VHF. 1 G 7 2 3U H13EU 1997041000056 19970410 00056 EU 1997 4 10 97ZZZX1349 1 19960813 G 2432 RG390E BATTERY BOLKMS 117 BK117A1 5626010 EU DC SYSTEM FAILED B LI1R K NONE O OTHER IN INSP/MAINT 1 EA 07 117LF 108 CBC261076 7013 BATTERY FAILED. BUSS TIE TRIPS. WILL NOT START A/C. VOTLAGE DROPS TO ZERO. 1 G 7 2 3U H13EU 1997010900779 19970109 00779 GL 1997 1 9 97ZZZX135 3 19961105 G 6110 660709612 PROP ASSY BAG JETSTM JETSTM3101 1500215 EU ROTOL R333 R333482F12 GL PEOPELLER DEFECTIVE B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 21893 5973 DRG936282 INSPECTION FOUND PROPELLER ASSY DEFECTIVE. 2 L 7 2 4T RT A21EU 6 C P61GL 1997041000058 19970410 00058 EU 1997 4 10 97ZZZX1351 1 19961212 G 2822 1176415103 PUMP BOLKMS 117 BK117B1 5626012 EU FUEL INTERMITTENT B TI1R K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 05 170MC 140700 7217 PUMP INTERMITTENT WHEN A/C RUNNING. ZERO TIME SINCE OVERHAUL. 1 G 7 2 3U H13EU 1997041000059 19970410 00059 EU 1997 4 10 97ZZZX1352 1 19961212 G 3310 117923103 CONTROL BOLKMS 117 BK117B1 5626012 EU LIGHTS SMOKES B TI1R K NONE B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 SW 05 170MC 15 0858 7217 LIGHT CONTROL UNIT SMOKES WHEN TURNED ON. CIRCUIT BREAKER TRIPS. 1 G 7 2 3U H13EU 1997041000060 19970410 00060 EU 1997 4 10 97ZZZX1353 1 19961214 G 2435 23032022 STARTER BOLKMS 117 BK117A3 5626015 EU ENGINE MALFUNCTIONED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 118LL 442 23946 7097 STARTER/GENERATOR MALFUNCTION. ENGINE SLOW TO START. 1 G 7 2 3U H13EU 1997041000061 19970410 00061 NE 1997 4 10 97ZZZX1354 2 19961120 G 7321 430128307 FUEL CONTROL BOLKMS 117 BK117B1 5626012 EU LYC LTS101 LTS101750B1 41560 NE ENGINE LEAK B TI1R K NONE K FLUID LOSS IN INSP/MAINT 1 SW 05 217MC 585 51638 7195 LE45602 FUEL CONTROL LEAK UNDER PX PY CAP. 1 G 7 2 3U 3 U H13EU E5NE10 1997041000062 19970410 00062 1997 4 10 97ZZZX1355 4 19961103 G 3421 222375033101 INDICATOR BELL 222 222U 1182140 SW COCKPIT ATTITUDE MALFUNCTIONED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 219HM 0143 47573 ATTITUDE INDICTOR 'OFF' WARNING FLAG WILL NOT PULL. 1 G 7 2 3U H9SW 1997010900780 19970109 00780 GL 1997 1 9 97ZZZX136 3 19961105 G 6110 860014002 PROP ASSY BAG JETSTM JETSTM3101 1500215 EU ROTOL R333 R333482F12 GL PROPELLER DEFECTIVE B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 21893 5973 DRG936282 INSPECTION FOUND PROPELLER ASSY DEFECTIVE. 2 L 7 2 4T RT A21EU 6 C P61GL 1997010900781 19970109 00781 GL 1997 1 9 97ZZZX137 3 19961105 G 6110 860013002 PROP ASSY BAG JETSTM JETSTM3101 1500215 EU ROTOL R333 R333482F12 GL PROPELLER DEFECTIVE B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 21893 5973 DRG936282 INSPECTION FOUND PROPELLER ASSY DEFECTIVE. 2 L 7 2 4T RT A21EU 6 C P61GL 1997041000078 19970410 00078 CE 1997 4 10 97ZZZX1371 1 19960731 G 3230 20430156 BOLT CESSNA 177 177RG 2073709 CE NLG DRAG LINK BROKEN D A K NONE O OTHER IN INSP/MAINT 1 EA 07 33224 3800 177RG0928 BOLT WHICH CONNECTS THE FORWARD AND AFT NOSE LANDING GEAR DRAG LINKS WAS FOUND LOOSE. FURTHER INSPECTION SHOWED BOLT HA D BROKEN THROUGH THE CENTER OF LUBRICATION PORT WHICH IS A HOLE DRILLED INTO THE DIAMETER OF THE BOLT WHICH MEETS A HOLE DRILLED IN THE AXIS OF THE BOLT. NLG FAILURE WAS IMMINENT. 1 H 7 1 3O A20CE 1997041000081 19970410 00081 GL 1997 4 10 97ZZZX1374 2 19960829 G 7313 23008054 NOZZLE ALLSN 250C 250C28B 03013 GL NR 1 MELTED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 1 MK169833 NR 1 NOZZLE BRAZE JOINTS MELTED. ONLY RAN .6 HOURS ON TEST CELL RUN. 3 U E1GL 1997041000082 19970410 00082 EU 1997 4 10 97ZZZX1375 1 19961216 G 6520 463900300 GEARBOX BOLKMS 117 BK117A3 5626015 EU T/R GEARBOX WRONG PART B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 910 478 GEARBOX WAS REMOVED FROM BK117, S/N 7146, AND ASB BK117-10-109 WAS NOT C/W DURING OVERHAUL. THIS GEARBOX WAS TO BE USED ON A BO105S, S/N 2033, AND IS NOT ALLOWED TO BE IAW THIS ASB. 1 G 7 2 3U H13EU 1997041000083 19970410 00083 EU 1997 4 10 97ZZZX1376 1 19961105 G 7120 1176270101 SUPPORT BOLKMS 117 BK117B1 5626012 EU ENGINE TRUSS OUT OF LIMITS B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 1313 ENGINE TRUSS SUPPORT DIMENSIONS OUT OF LIMITS. 1 G 7 2 3U H13EU 1997041000084 19970410 00084 EU 1997 4 10 97ZZZX1377 1 19961106 G 7120 1176272101 MOUNT LINK BOLKMS 117 BK117A3 5626015 EU ENGINE OUT OF LIMITS B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 0339 ENGINE MOUNT LINK DIMENSIONS OUT OF LIMITS. 1 G 7 2 3U H13EU 1997010900782 19970109 00782 GL 1997 1 9 97ZZZX138 3 19961105 G 6110 B5177 PROP ASSY CESSNA 208 208 2073702 CE MCAULY 3G34C7 3GFR34C701 GL PROPELLER CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 2688 910855 INSPECTION FOUND PROPELLER ASSY P/N B5177 CORRODED. 1 H 7 1 3T NT A37CE 5 C P60GL 1997041000096 19970410 00096 EU 1997 4 10 97ZZZX1389 1 19961220 G 7933 117904221 SENSOR BOLKMS BK117 BK117C1 5626025 EU OIL SYSTEM BROKEN B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 317MC 7505 TEMPERATURE SENSOR PROBE BROKEN. 1 G 7 2 3U NC H13EU 1997010900783 19970109 00783 GL 1997 1 9 97ZZZX139 3 19961105 G 6110 A1896 PROP ASSY CESSNA 421 421C 2076016 CE MCAULY 3FF32 3FF32C501 GL PROPELLER CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 768385 INSPECTION FOUND PROPELLER ASSY P/N A1896 CORRODED. 1 L 7 2 3O A7CE 5 C P45GL 1997041000098 19970410 00098 EU 1997 4 10 97ZZZX1391 1 19961211 G 6220 10513143 BALL END ASSY BOLKMS BK117 BK117C1 5626025 EU MAIN ROTOR WORN B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 317MC 1054 7505 BEARINGS WORN ON BALL END ASSY ON MAIN ROTOR HEAD. REPLACED 4 EACH. 1 G 7 2 3U NC H13EU 1997041000099 19970410 00099 EU 1997 4 10 97ZZZX1392 1 19961211 G 6220 10513144 BALL END ASSY BOLKMS BK117 BK117C1 5626025 EU MAIN ROTOR WORN B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 317MC 1054 7505 BEARINGS WORN ON MAIN ROTOR HEAD, BALL END ASSY. REPLACED 4 EACH. 1 G 7 2 3U NC H13EU 1997041000100 19970410 00100 EU 1997 4 10 97ZZZX1393 1 19961005 G 3310 1179203103 CONTROL UNIT BOLKMS BK117 BK117C1 5626025 EU LIGHTS TRIPS BREAKER B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 317MC 1021 7505 LIGHTING CONTROL UNIT TRIPS CIRCUIT BREAKER. 1 G 7 2 3U NC H13EU 1997041000101 19970410 00101 SW 1997 4 10 97ZZZX1394 1 19961211 G 2432 RG222 BATTERY BELL 206 206L1 1182107 SW DC SYSTEM FAILED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 400SL 229 CBC261763 45235 SUBMITTER STATED THERE IS POSSIBILITY THAT BATTERY IS LEAKING. WILL NOT HOLD CHARGE. 1 G 7 1 3U H2SW 1997041000102 19970410 00102 EU 1997 4 10 97ZZZX1395 1 19961215 G 5230 116201118 ACTUATOR BOLKMS 117 BK117A3 5626015 EU CARGO DOOR LEAKED B TI1R K NONE K FLUID LOSS IN INSP/MAINT 1 SW 05 4493X S7038 CARGO DOOR STRUT LEAKED OVERNIGHT AFTER INSTALLING NEW. 1 G 7 2 3U H13EU 1997041000104 19970410 00104 CE 1997 4 10 97ZZZX1397 1 19961116 G 2422 PC17A INVERTER BEECH 200 B200 1152922 CE AC SYSTEM DEFECTIVE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 75LV 117 9717A BB1075 AUTOPILOT DISCONNECTED, FOUND DEFECTIVE INVERTER. 1 L 7 2 4T A24CE 1997041000105 19970410 00105 1997 4 10 97ZZZX1398 4 19961212 G 3422 222375034101 INDICATOR BELL 222 222 1182122 SW COCKPIT DG MALFUNCTION B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 911LW 22 8593 47520 DG INDICATOR'S OFF FLAG DOES NOT RETRACT. 1 G 7 2 3U H9SW 1997041000106 19970410 00106 SW 1997 4 10 97ZZZX1399 1 19961022 G 6330 222031605109 FLEXTURE BELL 222 222 1182122 SW TRANSMISSION MT DEBONDED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 911LW 274 LK0078 47520 FLEXTURE END FITTINGS DEBONDED. 1 G 7 2 3U H9SW 1997010900107 19970109 00107 GL 1997 1 9 97ZZZX14 3 19961031 G 6114 HUB CESSNA 210 T210K 2073447 CE CONT O520 TSIO520H 17040 SO MCAULY 3A32C D3A32C88 GL MOUNT HOLES CRACKED D S K NONE O OTHER IN INSP/MAINT 1 SW 03 8237M 3700 100 T21059237 1985719H 740765 DURING 100 HOUR INSPECTION, FOUND PROP HUB CRACKED AT 5 OF THE 6 MOUNTING STUDS. 1 H 7 1 3O 3 O 3A21 E8CE 5 C P21EA 1997010900784 19970109 00784 GL 1997 1 9 97ZZZX140 3 19961105 G 6110 A4191 PROPELLER ASSY CESSNA 421 421C 2076016 CE MCAULY 3FF32 3FF32C501 GL PROPELLER CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 768385 INSPECTION FOUND PROPELLER ASSY P/N A4191 CORRODED. 1 L 7 2 3O A7CE 5 C P45GL 1997010900785 19970109 00785 GL 1997 1 9 97ZZZX141 3 19961105 G 6110 D3474 PROPELLER ASSY CESSNA 421 421C 2076016 CE MCAULY 3FF32 3FF32C501 GL PROPELLER WORN B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 768385 INSPECTION FOUND PROPELLER ASSY P/N D3474 WORN. 1 L 7 2 3O A7CE 5 C P45GL 1997041000324 19970410 00324 NM 1997 4 10 97ZZZX1416 1 19961004 G 5711 SPAR CAP BOEING 727 727243 138408D NM WS 519 CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 12411 22052 DURING C-10 INSPECTION, CORROSION WAS NOTED ON RT WING LOWER CAP OF FRONT SPAR, WS 519, AFT OF NR 6 L/E SLAT ACTUATOR. 2 L 7 3 4F RT A3WE 1997041000325 19970410 00325 NM 1997 4 10 97ZZZX1417 1 19961003 G 5330 SKIN BOEING 727 727243 138408D NM BS 1050-1070 CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 12411 22052 DURING C-10 INSPECTION, CORROSION WAS NOTED ON EXTERNAL SKIN BETWEEN STA 1050 AND STA 1070 AT S28L. 2 L 7 3 4F RT A3WE 1997041000326 19970410 00326 NM 1997 4 10 97ZZZX1418 1 19961003 G 5330 SKIN BOEING 727 727243 138408D NM BS 720B CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 12411 22052 DURING C-10 INSPECTION, CORROSION WAS NOTED ON BOTH LT AND RT SIDES OF AIR CONDITIONING FROM AIR INLET ACTUATOR ACCESS P ANELS AT STA 720B, FROM RBL 10 TO LBL 10. 2 L 7 3 4F RT A3WE 1997041000327 19970410 00327 NM 1997 4 10 97ZZZX1419 1 19961003 G 5315 FLOOR BEAM BOEING 727 727243 138408D NM BS 400 WL 208 CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 12411 22052 DURING C-10 INSPECTION, CORROSION WAS NOTED ON FLOOR BEAM UPPER CORD, FS 400, WL 208. 2 L 7 3 4F RT A3WE 1997010900786 19970109 00786 GL 1997 1 9 97ZZZX142 3 19961105 G 6110 D5878C501 PROP ASSY CESSNA 421 421C 2076016 CE MCAULY 3FF32 3FF32C501 GL PROPELLER CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 767592 INSPECTION FOUND PROPELLER ASSY P/N D5878/C501 CORRODED. 1 L 7 2 3O A7CE 5 C P45GL 1997041000328 19970410 00328 NM 1997 4 10 97ZZZX1420 1 19961003 G 5720 CAP BOEING 727 727243 138408D NM LT WING WS 437 CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 12411 22052 DURING C-10 INSPECTION, CORROSION WAS NOTED ON LT WING LOWER CAP AT WS 437. REF: SI 104 2 L 7 3 4F RT A3WE 1997041000329 19970410 00329 NM 1997 4 10 97ZZZX1421 1 19961003 G 5743 FITTING BOEING 727 727243 138408D NM LT MLG WELL CRACKED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 12411 22052 DURING C-10 INSPECTION, THE LEFT MAIN LANDING GEAR REAR TRUNNION BEAM OUTBOARD ATTACH FITTING WAS FOUND CRACKED. REF: S I 106. 2 L 7 3 4F RT A3WE 1997041000330 19970410 00330 NM 1997 4 10 97ZZZX1422 1 19961002 G 5320 WEB BOEING 727 727243 138408D NM BS 1136 CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 12411 22052 DURING C-10 INSPECTION, CORROSION WAS NOTED ON WEB FROM FS 1136 TO FS 1166, FROM BL 20 RT TO BL 45 RT. 2 L 7 3 4F RT A3WE 1997041000331 19970410 00331 NM 1997 4 10 97ZZZX1423 1 19961002 G 5320 HAT CHANNEL BOEING 727 727243 138408D NM BS 1136 BL20R CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 12411 22052 DURING C-10 INSPECTION, CORROSION WAS NOTED ON HAT CHANNEL AT STA 1136, FROM BL 20R TO BL 45R. 2 L 7 3 4F RT A3WE 1997041000332 19970410 00332 NM 1997 4 10 97ZZZX1424 1 19961002 G 5320 HAT CHANNEL BOEING 727 727243 138408D NM BS 1136-1160 CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 12411 22052 DURING C-10 INSPECTION, CORROSION WAS NOTED ON HAT CHANNEL FROM STA 1136 - STA 1166, AT BL 20R. 2 L 7 3 4F RT A3WE 1997041000333 19970410 00333 NM 1997 4 10 97ZZZX1425 1 19961002 G 5320 6549914545 TIE FITTING BOEING 737 737212 1384461 NM BS 1016 S27R CORROSION B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 161FN 20521 DURING C-4 INSPECTION, CORROSION WAS NOTED ON STRINGER TIE FITTING AT FS 1016 AT S27R. 2 L 7 2 4F A16WE 1997041000334 19970410 00334 NM 1997 4 10 97ZZZX1426 1 19961003 G 5311 FRAME BOEING 737 737212 1384461 NM BS 787 S26R CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 161FN 20521 DURING C-4 INSPECTION, CORROSION WAS NOTED ON FORWARD FRAME STA 787 BETWEEN S26R AND S27R. 2 L 7 2 4F A16WE 1997041000335 19970410 00335 NM 1997 4 10 97ZZZX1427 1 19961003 G 5320 SHEAR TIE BOEING 737 737212 1384461 NM BS 727A CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 161FN 20521 DURING C-4 INSPECTION, CORROSION WAS NOTED ON SHEAR TIES, FORWARD AND BACK SIDE OF FRAME 727A. 2 L 7 2 4F A16WE 1997041000337 19970410 00337 NM 1997 4 10 97ZZZX1429 1 19961002 G 5320 SHEAR TIE BOEING 727 7272M7 138407S NM BS 351.2 S22F CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 725RW 21502 DURING C-5 INSPECTION, CORROSION WAS NOTED ON SHEAR TIE AT FS 351.2 BETWEEN S22R AND S23R. 2 L 7 3 4F A3WE 1997010900787 19970109 00787 GL 1997 1 9 97ZZZX143 3 19961105 G 6110 D3474 PROP ASSY CESSNA 421 421C 2076016 CE MCAULY 3FF32 3FF32C501 GL PROPELLER WORN B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 767592 INSPECTION FOUND PROPELLER ASSY P/N D3474 WORN. 1 L 7 2 3O A7CE 5 C P45GL 1997041000338 19970410 00338 NM 1997 4 10 97ZZZX1430 1 19961002 G 5320 ANGLE BOEING 727 7272M7 138407S NM BS 351.2 WEB CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 725RW 21502 DURING C-5 INSPECTION, CORROSION WAS NOTED ON ANGLE SUPPORTING RT FLOOR WEB TO FORWARD SIDE FS 351.2 WEB. 2 L 7 3 4F A3WE 1997041000339 19970410 00339 NM 1997 4 10 97ZZZX1431 1 19961002 G 5320 WEB BOEING 727 7272M7 138407S NM BS 351.2 S22R CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 725RW 21502 DURING C-5 INSPECTION, CORROSION WAS NOTED ON WEB FORWARD SIDE 351.2 FRAME FROM S22R TO S23R. 2 L 7 3 4F A3WE 1997041000340 19970410 00340 NM 1997 4 10 97ZZZX1432 1 19961009 G 5311 FRAME BOEING 727 727225 1384077 NM BS 344 S25R CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 8880Z 21453 DURING C-2 INSPECTION, CORROSION WAS NOTED ON FRAME 344 AT S25R. 2 L 7 3 4F A3WE 1997041000341 19970410 00341 NM 1997 4 10 97ZZZX1433 1 19961009 G 5320 SHEAR TIE BOEING 727 727225 1384077 NM BS 344 NLG BOX CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 8880Z 21453 DURING C-2 INSPECTION, CORROSION WAS NOTED ON SHEAR TIE STA 344 AT THE RT SIDE OF THE NOSE GEARBOX. 2 L 7 3 4F A3WE 1997041000342 19970410 00342 NM 1997 4 10 97ZZZX1434 1 19961009 G 5312 BULKHEAD BOEING 727 727225 1384077 NM BS 294.5 RBL 25 CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 8880Z 21453 DURING C-2 INSPECTION, CORROSION WAS NOTED ON THE BACKSIDE BULKHEAD STA 294.5 EXTENDING FROM RBL 25 TO RBL 45. 2 L 7 3 4F A3WE 1997041000343 19970410 00343 NM 1997 4 10 97ZZZX1435 1 19961009 G 5313 STRINGER BOEING 727 727225 1384077 NM BS 420 S27R CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 8880Z 21453 DURING C-2 INSPECTION, CORROSION WAS NOTED ON S27R JUST FORWARD OF STA 420. 2 L 7 3 4F A3WE 1997041000344 19970410 00344 NM 1997 4 10 97ZZZX1436 1 19961002 G 5311 FRAME BOEING 727 727224 1384076 NM BS 380 S6R CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 32719 20388 DURING C-10 INSPECTION, CORROSION WAS NOTED ON FRAME FS 380 BETWEEN S6R AND S7R. 2 L 7 3 4F A3WE 1997041000345 19970410 00345 NM 1997 4 10 97ZZZX1437 1 19961002 G 5311 FRAME BOEING 727 727224 1384076 NM BS 219.8 S25L CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 32719 20388 DURING C-10 INSPECTION, CORROSION WAS NOTED ON FRAME 219.8 AT S25L. 2 L 7 3 4F A3WE 1997041000346 19970410 00346 NM 1997 4 10 97ZZZX1438 1 19961009 G 5320 TEE FITTING BOEING 727 727224 1384076 NM BS 265 CORROSION B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 32719 20388 DURING C-10 INSPECTION, LEVEL 2 CORROSION WAS NOTED ON COCKPIT FLOOR SUPPORT BEAM TRIPLE TEE FITTING AT STA 265. 2 L 7 3 4F A3WE 1997041000347 19970410 00347 NM 1997 4 10 97ZZZX1439 1 19961009 G 5330 SKIN BOEING 727 727224 1384076 NM BS 1130-1150 CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 32719 20388 DURING C-10 INSPECTION, LEVEL 2 CORROSION WAS NOTED ON AIRCRAFT SKIN BETWEEN STA 1130 AND STA 1150 BETWEEN S24R AND S25R . 2 L 7 3 4F A3WE 1997010900788 19970109 00788 GL 1997 1 9 97ZZZX144 3 19961105 G 6111 D7015C93 BLADE CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL NR 3 SOCKET CRACKED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 795375 INSPECTION FOUND BLADE P/N D70151/C93 BLADE, NR 3 SOCKET CRACKED. 1 L 7 2 3O 3A25 5 C P22EA 1997041000348 19970410 00348 NM 1997 4 10 97ZZZX1440 1 19961009 G 5330 SKIN BOEING 727 727224 1384076 NM BS 328-344 CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 32719 20388 DURING C-10 INSPECTION, LEVEL 2 CORROSION WAS NOTED ON AIRCRAFT SKIN BETWEEN STA 328 AND STA 344 AT S24R. 2 L 7 3 4F A3WE 1997041000349 19970410 00349 NM 1997 4 10 97ZZZX1441 1 19961009 G 5330 SKIN BOEING 727 727224 1384076 NM BS 580-720 CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 32719 20388 DURING C-10 INSPECTION, LEVEL 2 CORROSION WAS NOTED ON AIRCRAFT SKIN BETWEEN STA 580 AND STA 720 AT S9R. 2 L 7 3 4F A3WE 1997041000350 19970410 00350 NM 1997 4 10 97ZZZX1442 1 19961009 G 5330 SKIN BOEING 727 727224 1384076 NM BS 1172 S17L CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 32719 20388 DURING C-10 INSPECTION, LEVEL 2 CORROSION WAS NOTED ON AIRCRAFT SKIN AT BELT FRAME TIE AT STA 1172 AT S17L. 2 L 7 3 4F A3WE 1997041000351 19970410 00351 NM 1997 4 10 97ZZZX1443 1 19961003 G 5320 SILL WEB BOEING 727 727243 138408D NM BS 380 S17R CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 14416 22168 DURING C-10 INSPECTION, CORROSION WAS NOTED ON THE R-1 DOOR BOTTOM SILL WEB BETWEEN STA 380 AND STA 420 AT S17R. 2 L 7 3 4F RT A3WE 1997041000352 19970410 00352 NM 1997 4 10 97ZZZX1444 1 19961009 G 5315 FLOOR BEAM BOEING 727 727243 138408D NM BS 1130 RBL 24 CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 14416 22168 DURING C-10 INSPECTION, CORROSION WAS NOTED ON UPPER SURFACE OF FLOOR BEAM AT FS 1130 AT RBL 24. 2 L 7 3 4F RT A3WE 1997041000353 19970410 00353 NM 1997 4 10 97ZZZX1445 1 19961009 G 3233 69181941 FITTING BOEING 727 727243 138408D NM NLG ACTUATOR CRACKED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 14416 22168 DURING C-10 INSPECTION, NOSE LANDING GEAR ACTUATOR FITTING FOUND CRACKED AT UPPER ACTUATOR ATTACH BOLT HOLE. 2 L 7 3 4F RT A3WE 1997041000354 19970410 00354 NM 1997 4 10 97ZZZX1446 1 19961003 G 5311 FRAME BOEING 727 727243 138408D NM BS 372 S16R-S17R CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 14416 22168 DURING C-10 INSPECTION, CORROSION WAS NOTED ON FRAME AT STA 372 BETWEEN S16R AND S17R. 2 L 7 3 4F RT A3WE 1997041000355 19970410 00355 NM 1997 4 10 97ZZZX1447 1 19961004 G 5530 STRINGER BOEING 727 727243 138408D NM V STAB 8L RIB 7 CRACKED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 14416 22168 DURING C-10 INSPECTION, A CRACK WAS NOTED ON VERTICAL STABILIZER, STR 8L AT RIB NR 7. 2 L 7 3 4F RT A3WE 1997041000356 19970410 00356 NM 1997 4 10 97ZZZX1448 1 19961004 G 5320 WEB SUPPORTS BOEING 727 727243 138408D NM RT TORQ BOX CRACKED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 14416 22168 DURING C-10 INSPECTION, THREE CRACKS WERE NOTED ON RT HAND LOWER TORQUE BOX HORIZONTAL WEB SUPPORTS BELOW AIRSTAIR TORQU E TUBE SUPPORT FITTING. 2 L 7 3 4F RT A3WE 1997010900789 19970109 00789 GL 1997 1 9 97ZZZX145 3 19961105 G 6110 D3474 PROPELLER ASSY CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER WORN B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 795375 INSPECTION FOUND PROPELLER ASSY P/N D3474 WORN. 1 L 7 2 3O 3A25 5 C P22EA 1997041000434 19970410 00434 NM 1997 4 10 97ZZZX1455 1 19961004 G 5330 SKIN BOEING 727 7272J7 138400E NM BS 344 S24L CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 129NA 20880 DURING C-10 INSPECTION, CORROSION WAS NOTED IN EXTERNAL SKIN AT FS 344 AT S24L. 2 L 7 3 4F A3WE 1997041000435 19970410 00435 NM 1997 4 10 97ZZZX1456 1 19961004 G 5313 STRINGER BOEING 727 7272J7 138400E NM BS 340 S23R CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 129NA 20880 DURING C-10 INSPECTION, CORROSION WAS NOTED ON S23R AT STA 340. 2 L 7 3 4F A3WE 1997041000436 19970410 00436 NM 1997 4 10 97ZZZX1457 1 19961004 G 5320 WEB BOEING 727 7272J7 138400E NM BS 1070 S17L CORODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 129NA 20880 DURING C-10 INSPECTION, CORROSION WAS NOTED AT L-2 DOOR FRAME CUT-OUT, LOWER AFT SIDE, STA 1070 AT S17L. 2 L 7 3 4F A3WE 1997041000437 19970410 00437 NM 1997 4 10 97ZZZX1458 1 19961006 G 5313 STRINGER BOEING 727 7272J7 138400E NM BS 328 S26L CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 129NA 20880 DURING C-10 INSPECTION, CORROSION WAS NOTED ON STR 26L AT FS 328 UNDER FLOOR WEB. 2 L 7 3 4F A3WE 1997041000438 19970410 00438 NM 1997 4 10 97ZZZX1459 1 19961004 G 5347 SEAT TRACK BOEING 727 7272J7 138400E NM BS 1030-1110 CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 129NA 20880 DURING C-10 INSPECTION, CORROSION WAS NOTED ON CABIN SEAT TRACK FROM STA 1030 TO STA 1110 AT LBL 40. 2 L 7 3 4F A3WE 1997010900790 19970109 00790 GL 1997 1 9 97ZZZX146 3 19961105 G 6110 A1896 PROPELLER ASSY CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 795375 INSPECTION FOUND PROPELLER ASSY P/N A1896 CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997041000439 19970410 00439 NM 1997 4 10 97ZZZX1460 1 19961004 G 5320 T CHORD BOEING 727 7272J7 138400E NM BS 1070 CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 129NA 20880 DURING C-10 INSPECTION, CORROSION WAS NOTED ON LOWER T-CHORD, FLOOR BEAM STA 1070 AT LBL 30. 2 L 7 3 4F A3WE 1997041000440 19970410 00440 NM 1997 4 10 97ZZZX1461 1 19961008 G 5320 69191222 CHANNEL BOEING 727 7272J7 138400E NM NLG LOCK ACT CRACKED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 129NA 20880 DURING C-10 INSPECTION, A CRACK WAS NOTED IN THE NOSE GEAR LOCK ACTUATOR CHANNEL. 2 L 7 3 4F A3WE 1997041000441 19970410 00441 NM 1997 4 10 97ZZZX1462 1 19961004 G 5330 SKIN BOEING 727 7272J7 138400E NM BS 344 S23R DAMAGED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 129NA 20880 DURING C-10 INSPECTION, 6 EACH FASTENER HOLES FOUND KNIFE-EDGED THROUGH SKIN AT LAP SEAM, STA 344, S23R. REF: C53-100 -01. 2 L 7 3 4F A3WE 1997041000442 19970410 00442 NM 1997 4 10 97ZZZX1463 1 19961004 G 5320 ANGLE BOEING 727 7272J7 138400E NM BS 1273 CRACKED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 129NA 20880 DURING C-10 INSPECTION, A CRACK WAS NOTED IN ANGLE BELOW AFT AIRSTAIR ACTUATOR SUPPORT FITTING AT FS 1273. REF: C53-13 7-01. 2 L 7 3 4F A3WE 1997041000443 19970410 00443 NM 1997 4 10 97ZZZX1464 1 19961004 G 5320 WEB BOEING 727 7272J7 138400E NM BS 870 CRACKED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 129NA 20880 DURING C-10 INSPECTION, A 3.50 INCH CRACK WAS NOTED IN FS 870 WEB, FORWARD SIDE OF LT MAIN WHEELWELL. REF: C53-100-01. 2 L 7 3 4F A3WE 1997041000444 19970410 00444 NM 1997 4 10 97ZZZX1465 1 19961004 G 5330 SKIN BOEING 727 7272J7 138400E NM BS 1090 S18L DENTED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 129NA 20880 DURING C-10 INSPECTION, A DENT WAS NOTED ON FUSELAGE EXTERNAL AT STA 1090 AT S18L AND S19L. 2 L 7 3 4F A3WE 1997041000445 19970410 00445 NM 1997 4 10 97ZZZX1466 1 19961008 G 5330 SKIN BOEING 727 7272J7 138400E NM BS 340 S22L CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 129NA 20880 DURING C-10 INSPECTION, CORROSION WAS NOTED ON SKIN PANEL AT FS 340 BETWEEN S22F AND S23R. 2 L 7 3 4F A3WE 1997041000446 19970410 00446 NM 1997 4 10 97ZZZX1467 1 19961008 G 5315 FLOOR BEAM BOEING 727 7272J7 138400E NM BS 1166 BL ZERO CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 129NA 20880 DURING C-10 INSPECTION, CORROSION WAS NOTED ON LOWER FLOOR BEAM CHORD AT FS 1166 AT BL ZERO. 2 L 7 3 4F A3WE 1997041000448 19970410 00448 NM 1997 4 10 97ZZZX1469 1 19961127 G 2430 A1SA DIODE ROBSIN R22 R22BETA NM BATTERY SOLENOID SHORTED D A A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 WP 13 83154 2470 TEN MINUTES AFTER DEPARTURE FROM PHOG CFI, NOTICED SMOKE COMING FROM CONSOLE. MASTER WAS SWITCHED OFF BUT AFTER A PRECA UTIONARY LANDING IN FIELD, MECHANIC FOUND OVER 20 WIRES WITH MELTED INSULATION FROM VARIOUS LOCATIONS FROM THE UPPER CON SOLE THROUGH-WIRE LOOM TO ELECT COMPONENTS. SEVERAL COMPONENTS WERE SHORTED AND DAMAGED. APPARENTLY A DIODE ON BATTERY SOLENOID SHORTED CAUSING HIGH CURRENT FLOW THROUGH MASTER SWITCH WIRE WHICH HEATED HARNESS BUNDLE AND OTHER COMPONENTS. SUBMITTER RECOMMENDED INSTALLING CIRCUIT PROTECTION TO MASTER SWITCH. 1 G 7 1 3O H10WE 1997010900791 19970109 00791 GL 1997 1 9 97ZZZX147 3 19961105 G 6110 A4191 PROPELLER ASSY CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 795375 INSPECTION FOUND PROPELLER ASSY P/N A4191 CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997041000454 19970410 00454 NM 1997 4 10 97ZZZX1475 1 19961021 G 5320 CHORD BOEING 727 727276 138408R NM BS 1177 BL50L CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 908PG 20951 STA 1127, CHORD CORRODED BL 50L. 2 L 7 3 4F RT A3WE 1997041000455 19970410 00455 NM 1997 4 10 97ZZZX1476 1 19961021 G 5320 CHORD BOEING 727 727276 138408R NM BS 1177 BL25R CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 908PG 20951 STA 1177, CHORD CORRODED BETWEEN BL 25R TO BL 50R. 2 L 7 3 4F RT A3WE 1997041000456 19970410 00456 NM 1997 4 10 97ZZZX1477 1 19961021 G 5311 FRAME BOEING 727 727276 138408R NM BS 1183 CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 908PG 20951 STA 1183 FRAME CORRODED LEFT SIDE. 2 L 7 3 4F RT A3WE 1997041000457 19970410 00457 NM 1997 4 10 97ZZZX1478 1 19961017 G 5315 FLOOR BEAM BOEING 727 727276 138408R NM BS 1130 LBL 10 CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 908PG 20951 DURING C-7 INSPECTION, LEVEL 2 CORROSION NOTED ON LOWER CHORD OF CABIN FLOOR BEAM AT STA 1130 AT LBL 10. 2 L 7 3 4F RT A3WE 1997010900792 19970109 00792 GL 1997 1 9 97ZZZX148 3 19961105 G 6110 C2715C33 PROPELLER ASSY CESSNA 210 210 2073402 CE MCAULY 2A36C D2A36C33 GL PROPELLER CRACKED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 61811 INSPECTION FOUND PROPELLER ASSY C2715/C33 NR 1 SOCKET CRACKED. 1 H 7 1 3O RT 3A21 5 C P880 1997041000517 19970410 00517 NM 1997 4 10 97ZZZX1489 1 19961002 G 5320 STRINGER TIE BOEING 727 727224 1384076 NM BS 560 S19R CORROSION B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 32719 20388 DURING C-10 INSPECTION, CORROSION WAS NOTED ON STR TIE S19R AT FS 560. 2 L 7 3 4F A3WE 1997010900793 19970109 00793 GL 1997 1 9 97ZZZX149 3 19961105 G 6111 S90M8 BLADE CESSNA 210 210 2073402 CE MCAULY 2A36C D2A36C33 GL PROPELLER BELOW SPEC B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 C999 61811 INSPECTION FOUND PROPELLER BLADE P/N S90M8 BELOW MINIMUM. 1 H 7 1 3O RT 3A21 5 C P880 1997041000518 19970410 00518 NM 1997 4 10 97ZZZX1490 1 19961004 G 5320 I BEAM BOEING 727 727243 138408D NM BS 1166 RBL 45 CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 14416 22168 DURING C-10 INSPECTION, CORROSION WAS NOTED ON UPPER I-BEAM AT STA 1166, AT RBL 45. 2 L 7 3 4F RT A3WE 1997041000519 19970410 00519 NM 1997 4 10 97ZZZX1491 1 19961004 G 5313 STRINGER BOEING 727 727243 138408D NM BS 950F S28L CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 14416 22168 DURING C-10 INSPECTION, CORROSION WAS NOTED ON S28L FROM STA 950F TO STA 970. 2 L 7 3 4F RT A3WE 1997041000520 19970410 00520 NM 1997 4 10 97ZZZX1492 1 19961004 G 5313 STRINGER BOEING 727 727243 138408D NM BS950F-1010 KEEL CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 14416 22168 DURING C-10 INSPECTION, CORROSION WAS NOTED ON KEEL STRINGER S29L FROM STA 950F TO STA 1010. 2 L 7 3 4F RT A3WE 1997041000521 19970410 00521 NM 1997 4 10 97ZZZX1493 1 19961004 G 5330 SKIN BOEING 727 727243 138408D NM BS 950F S28L CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 14416 22168 DURING C-10 INSPECTION, CORROSION WAS NOTED ON EXTERNAL SKIN AT STA 950F AT S28L. 2 L 7 3 4F RT A3WE 1997041000522 19970410 00522 NM 1997 4 10 97ZZZX1494 1 19961003 G 5320 652558910 SUPPORT BOEING 727 727243 138408D NM BS 848.95 BL 0 CRACKED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 14416 22168 DURING C-10 INSPECTION, A CABIN FLOOR SUPPORT WAS CRACKED AT STA 848.95 AT BL ZERO. REF: SI-158.1. 2 L 7 3 4F RT A3WE 1997041000523 19970410 00523 NM 1997 4 10 97ZZZX1495 1 19961003 G 5320 65255896 SUPPORT BOEING 727 727243 138408D NM BS 760.95 BL 0 CRACKED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 14416 22168 DURING C-10 INSPECTION, A CRACK WAS NOTED IN CABIN FLOOR SUPPORT AT STA 760.95 AT BL ZERO. REF: SI-158.1. 2 L 7 3 4F RT A3WE 1997041000524 19970410 00524 NM 1997 4 10 97ZZZX1496 1 19961009 G 5330 SKIN BOEING 727 727251 138408H NM BS 294 S19R CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 267US 20289 DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON SKIN, RT FORWARD FUSELAGE STA 294 TO STA 360, EXTENDING UNDER LAP S19R . 2 L 7 3 4F A3WE 1997041000525 19970410 00525 NM 1997 4 10 97ZZZX1497 1 19961009 G 5330 SKIN BOEING 727 727251 138408H NM BS 440 S18R CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 267US 20289 DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON SKIN RT FORWARD FUSELAGE AT STA 440 EXTENDING FROM S18R TO S21R. 2 L 7 3 4F A3WE 1997041000526 19970410 00526 NM 1997 4 10 97ZZZX1498 1 19961009 G 5330 SKIN BOEING 727 727251 138408H NM BS 1166 S22L CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 267US 20289 DURING C-CHECK INSPECTION, BROKEN FASTENERS AND CORROSION WAS NOTED UNDER SKIN PANEL BELOW LT AFT LAV SERVICE COMPARTMEN T, STA 1166, S22L. 2 L 7 3 4F A3WE 1997041000527 19970410 00527 NM 1997 4 10 97ZZZX1499 1 19961009 G 5312 BULKHEAD BOEING 727 727251 138408H NM BS 351 S21L CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 267US 20289 DURING C-CHECK INSPECTION, INTERGRANULAR CORROSION WAS NOTED ON LOWER CHORD OF BULKHEAD STA 351 BETWEEN S21L EXTENDING T O S26L. 2 L 7 3 4F A3WE 1997010900108 19970109 00108 EA 1997 1 9 97ZZZX15 2 19961201 G 8550 77527 FILLER TUBE PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA DIPSTICK CRACKED D S K NONE K FLUID LOSS IN INSP/MAINT 1 SO 09 949SS 317752070 L731661A PLASTIC FILLER TUBE CRACKED AT TOP WHERE DIPSTICK SNAPS IN PLACE CAUSING OIL LEAK. SUSPECT CAUSE OF PROBLEM: UNIT MADE OF PLASTIC. SUBMITTER STATED SHOULD BE MADE OF CAST OR MALLEABLE MATERIAL. 1 L 7 2 3O 3 O A20SO E14EA 1997010900794 19970109 00794 GL 1997 1 9 97ZZZX150 3 19961105 G 6111 S90M8 BLADE CESSNA 210 210 2073402 CE MCAULY 2A36C D2A36C33 GL PROPELLER BELOW SPEC B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 C983 61811 INSPECTION FOUND BLADE P/N S90M8 BELOW MINIMUM. 1 H 7 1 3O RT 3A21 5 C P880 1997041000528 19970410 00528 NM 1997 4 10 97ZZZX1500 1 19961009 G 5313 STRINGER BOEING 727 727251 138408H NM BS 312 S21L CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 267US 20289 DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON STRINGER S21L EXTENDING FROM STA 312 - STA 344. 2 L 7 3 4F A3WE 1997041000529 19970410 00529 NM 1997 4 10 97ZZZX1501 1 19961009 G 5313 STRINGER BOEING 727 727251 138408H NM BS 312 S20L CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 267US 20289 DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON STRINGER S20L FORWARD OF STA 312. 2 L 7 3 4F A3WE 1997041500054 19970415 00054 NM 1997 4 15 97ZZZX1502 1 19961009 G 5313 STRINGER BOEING 727 727251 138408H NM BS 312 S22L CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 267US 20289 DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON STRINGER S22L FORWARD OF STA 312 2 L 7 3 4F A3WE 1997041000530 19970410 00530 NM 1997 4 10 97ZZZX1503 1 19961009 G 5313 STRINGER BOEING 727 727251 138408H NM BS 380 S22R CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 267US 20289 DURING C-CHECK INSPECTION, CORROSION WASNOTED ON STRINGER S22R EXTENDING FROM STA 380 TO STA 440. 2 L 7 3 4F A3WE 1997041000531 19970410 00531 NM 1997 4 10 97ZZZX1504 1 19961009 G 5311 FRAME BOEING 727 727251 138408H NM BS 420 S21R CRACKED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 267US 20289 DURING C-CHECK INSPECTION, A CRACK WAS NOTED IN FRAME 420 AT S21R. 2 L 7 3 4F A3WE 1997041000532 19970410 00532 NM 1997 4 10 97ZZZX1505 1 19961009 G 5313 STRINGER BOEING 727 727251 138408H NM BS 380 S21R CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 267US 20289 DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON STRINGER S21R EXTENDING FROM STA 380 - STA 440. 2 L 7 3 4F A3WE 1997041000533 19970410 00533 NM 1997 4 10 97ZZZX1506 1 19961009 G 5313 STRINGER BOEING 727 727251 138408H NM BS 440 S23R CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 267US 20289 DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON STRINGER S23R EXTENDING FROM STA 360 - STA 440. 2 L 7 3 4F A3WE 1997041000534 19970410 00534 NM 1997 4 10 97ZZZX1507 1 19961009 G 5313 STRINGER BOEING 727 727251 138408H NM BS 312 S19R CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 267US 20289 DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON STRINGER S19R EXTENDING FROM STA 312 TO STA 344. 2 L 7 3 4F A3WE 1997041000535 19970410 00535 NM 1997 4 10 97ZZZX1508 1 19961009 G 5320 GEARBOX BOEING 727 727251 138408H NM NLG BS 320-328 CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 267US 20289 DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON LOWER NOSE LANDING GEAR BOX CHORD FROM STA 320 TO STA 328. 2 L 7 3 4F A3WE 1997041000536 19970410 00536 NM 1997 4 10 97ZZZX1509 1 19961009 G 5313 STRINGER BOEING 727 727251 138408H NM BS 312 S18R CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 267US 20289 DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON STRINGER S18R EXTENDING FROM STA 312 TO STA 328. 2 L 7 3 4F A3WE 1997010900795 19970109 00795 GL 1997 1 9 97ZZZX151 3 19961105 G 6110 C1976 PROPELLER ASSY CESSNA 210 210 2073402 CE MCAULY 2A36C D2A36C33 GL PROPELLER CRACKED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 61811 INSPECTION FOUND PROPELLER ASSY P/N C1976 CRACKED. 1 H 7 1 3O RT 3A21 5 C P880 1997041000537 19970410 00537 NM 1997 4 10 97ZZZX1510 1 19961009 G 5313 STRINGER BOEING 727 727251 138408H NM BS 360 S20R CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 267US 20289 DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON STRINGER S20R EXTENDING FROM STA 360 TO STA 380. 2 L 7 3 4F A3WE 1997041000538 19970410 00538 NM 1997 4 10 97ZZZX1511 1 19961009 G 5313 STRINGER BOEING 727 727251 138408H NM BS 460 S28R CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 267US 20289 DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON STRINGER S28R EXTENDING FROM STA 460 TO STA 480. 2 L 7 3 4F A3WE 1997041000539 19970410 00539 NM 1997 4 10 97ZZZX1512 1 19961009 G 5311 FRAME BOEING 727 727251 138408H NM BS 360 RBL 10 CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 267US 20289 DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON TOP CHORD OF FRAME STA 360 APPROXIMATE RBL 10. 2 L 7 3 4F A3WE 1997041000540 19970410 00540 NM 1997 4 10 97ZZZX1513 1 19961009 G 5313 STRINGER BOEING 727 727251 138408H NM BS 420 S27R CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 267US 20289 DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON STRINGER S27R EXTENDING FROM STA 420 TO STA 480. 2 L 7 3 4F A3WE 1997041000541 19970410 00541 NM 1997 4 10 97ZZZX1514 1 19961009 G 5313 STRINGER BOEING 727 727251 138408H NM BS 400 S25R CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 267US 20289 DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON STRINGER S25R EXTENDING FROM STA 400 TO STA 440. 2 L 7 3 4F A3WE 1997041000542 19970410 00542 NM 1997 4 10 97ZZZX1515 1 19961009 G 5313 STRINGER BOEING 727 727251 138408H NM BS 400 S24R CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 267US 20289 DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON STRINGER S24R EXTENDING FROM STA 400 TO STA 440. 2 L 7 3 4F A3WE 1997041000543 19970410 00543 NM 1997 4 10 97ZZZX1516 1 19961009 G 5313 STRINGER BOEING 727 727251 138408H NM BS 360 S25L CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 267US 20289 DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON STRINGER S25L JUST FORWARD OF STA 360. 2 L 7 3 4F A3WE 1997041000544 19970410 00544 NM 1997 4 10 97ZZZX1517 1 19961009 G 5313 STRINGER BOEING 727 727251 138408H NM BS 277 S25L CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 267US 20289 DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON STRINGER S25L FROM STA 277 TO STA 294. 2 L 7 3 4F A3WE 1997041000545 19970410 00545 NM 1997 4 10 97ZZZX1518 1 19961009 G 5313 STRINGER BOEING 727 727251 138408H NM BS 360 S26R CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 267US 20289 DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON STRINGER S26R EXTENDING FROM STA 360 TO STA 380. 2 L 7 3 4F A3WE 1997041000546 19970410 00546 NM 1997 4 10 97ZZZX1519 1 19961009 G 5313 STRINGER BOEING 727 727251 138408H NM BS 360 S24L CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 267US 20289 DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON STRINGER S24L AFT OF STA 360. 2 L 7 3 4F A3WE 1997010900796 19970109 00796 GL 1997 1 9 97ZZZX152 3 19961105 G 6110 A4001 DOWEL PIN CESSNA 182 182R 2072731 CE MCAULY 2A34C C2A34C204 GL PROPELLER CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 3080 1478 901245 INSPECTION FOUND PROPELLER ASSY DOWEL PIN CORRODED. 1 L 7 1 3O NT 3A13 5 C P3EA 1997041000547 19970410 00547 NM 1997 4 10 97ZZZX1520 1 19961009 G 5313 STRINGER BOEING 727 727251 138408H NM BS 380 S21L CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 267US 20289 DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON STRINGER S21L EXTENDING FROM STA 380 TO STA 400. 2 L 7 3 4F A3WE 1997041000548 19970410 00548 NM 1997 4 10 97ZZZX1521 1 19961009 G 5313 STRINGER BOEING 727 727251 138408H NM BS 360 S18L CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 267US 20289 DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON STRINGER S18L EXTENDING FROM STA 360 TO STA 380. 2 L 7 3 4F A3WE 1997041000549 19970410 00549 NM 1997 4 10 97ZZZX1522 1 19961009 G 5313 STRINGER BOEING 727 727251 138408H NM BS 360 S19L CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 267US 20289 DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON STRINGER S29L EXTENDING FROM STA 360 TO STA 380. 2 L 7 3 4F A3WE 1997041000550 19970410 00550 NM 1997 4 10 97ZZZX1523 1 19961009 G 5320 WEB BOEING 727 727251 138408H NM BS 243-259 CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 267US 20289 DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON RT SIDE NOSE WHEELWELL BOX EXTENDING FROM STA 243 TO STA 259. 2 L 7 3 4F A3WE 1997041000551 19970410 00551 NM 1997 4 10 97ZZZX1524 1 19961009 G 5330 SKIN BOEING 727 727230 1384080 NM BS 294 S21R-S22R CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 357KP 20675 DURING C-CHECK INSPECTION, CORROSION WAS NOTED AT SKIN BULGE FUSELAGE STA 294 EXTENDING FROM S21R TGO S22R. 2 L 7 3 4F A3WE 1997041000552 19970410 00552 NM 1997 4 10 97ZZZX1525 1 19961009 G 5320 SHEAR TIE BOEING 727 727230 1384080 NM BS 328 S26L CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 357KP 20675 DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON SHEAR TIE AFT SIDE OF FRAME STA 328 BETWEEN NOSE GEARBOX AND S26L. 2 L 7 3 4F A3WE 1997041000553 19970410 00553 NM 1997 4 10 97ZZZX1526 1 19961009 G 5320 BOX WEB BOEING 727 727230 1384080 NM BS 294.5-312 CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 357KP 20675 DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON THE LT SIDE OF THE NOSE GEARBOX WEB (FROM E/E BAY) FROM STA 294.5 TO S TA 312. 2 L 7 3 4F A3WE 1997041000554 19970410 00554 NM 1997 4 10 97ZZZX1527 1 19961009 G 5311 FRAME BOEING 727 727230 1384080 NM BS 380 S24R CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 357KP 20675 DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON FRAME STA 380 AT S24R. 2 L 7 3 4F A3WE 1997041700001 19970417 00001 WP 1997 4 17 97ZZZX1528 1 19961009 G 5311 BELT FRAME CVAC 440 440 2422902 WP BS 319 S30R CRACKED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 582P 475 DURING C-CHECK INSPECTION, A CRACK WAS NOTED IN BELT FRAME STA 319 AT S30R. 2 L 7 2 4R 6A6 1997041700002 19970417 00002 WP 1997 4 17 97ZZZX1529 1 19961009 G 5330 SKIN CVAC 440 440 2422902 WP BS 730 S8L CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 582P 475 DURING C-CHECK INSPECTION, SCAB PATCH WAS REMOVED AT FS 730, S8L AND S9L, AND AIRCRAFT SKIN WAS FOUND CORRODED BEYOND L IMITS. 2 L 7 2 4R 6A6 1997010900797 19970109 00797 GL 1997 1 9 97ZZZX153 3 19961105 G 6110 B5177 PROPELLER ASSY CESSNA 208 208 2073702 CE MCAULY 3G34C7 3GFR34C701 GL PROPELLER CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 2760 900938 INSPECTION FOUND PROPELLER ASSY P/N 35177 CORRODED. 1 H 7 1 3T NT A37CE 5 C P60GL 1997041700003 19970417 00003 WP 1997 4 17 97ZZZX1530 1 19961009 G 5315 FLOOR BEAM CVAC 440 440 2422902 WP BS 718 RBL 8 CRACKED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 582P 475 DURING C-CHECK INSPECTION, A CRACK WAS NOTED IN CABIN FLOOR BEAM STA 718 AT RBL 8 TO RBL 12. 2 L 7 2 4R 6A6 1997041700004 19970417 00004 WP 1997 4 17 97ZZZX1531 1 19961009 G 5311 FRAME CVAC 440 440 2422902 WP BS 641 S25L CRACKED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 582P 475 DURING C-CHECK INSPECTION, A CRACK WAS NOTED IN OUTBOARD FRAME FLANGE, STA 641 AT S25L. 2 L 7 2 4R 6A6 1997041700005 19970417 00005 WP 1997 4 17 97ZZZX1532 1 19961009 G 5313 STRINGER CVAC 440 440 2422902 WP BS 712 10R CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 582P 475 DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON S10R AT FS 712. 2 L 7 2 4R 6A6 1997010900798 19970109 00798 GL 1997 1 9 97ZZZX154 3 19961105 G 6110 D5010 PROPELLER ASSY CESSNA 208 208 2073702 CE MCAULY 3G34C7 3GFR34C701 GL PROPELLER CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 2760 900938 INSPECTION FOUND PROPELLER ASSY P/N D5010 CORRODED. 1 H 7 1 3T NT A37CE 5 C P60GL 1997010900799 19970109 00799 GL 1997 1 9 97ZZZX155 3 19961105 G 6110 D3474 PROPELLER CESSNA 421 421C 2076016 CE MCAULY 3FF32 3FF32C501 GL PROPELLER WORN B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 789223 INSPECTION FOUND PROPELLER ASSY P/N 3474 WORN. 1 L 7 2 3O A7CE 5 C P45GL 1997010900800 19970109 00800 GL 1997 1 9 97ZZZX156 3 19961105 G 6111 B48201 BLADE CESSNA 421 421C 2076016 CE MCAULY 3FF32 3FF32C501 GL PROPELLER CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 789223 INSPECTION FOUND PROPELLER BLADE CORRODED. 1 L 7 2 3O A7CE 5 C P45GL 1997010900801 19970109 00801 GL 1997 1 9 97ZZZX157 3 19961105 G 6111 C5270 BEARING CESSNA 421 421C 2076016 CE MCAULY 3FF32 3FF32C501 GL BLADE CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 789223 INSPECTION FOUND BLADE BEARING CORRODED. 1 L 7 2 3O A7CE 5 C P45GL 1997010900802 19970109 00802 GL 1997 1 9 97ZZZX158 3 19961105 G 6111 B4426 BLADE CESSNA 421 421C 2076016 CE MCAULY 3FF32 3FF32C501 GL PROPELLER CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 789223 INSPECTION FOUND PROPELLER BLADE ASSY B4426 CORRODED. 1 L 7 2 3O A7CE 5 C P45GL 1997010900803 19970109 00803 GL 1997 1 9 97ZZZX159 3 19961105 G 6110 8382 PROPELLER ASSY PIPER PA24 PA24250 7102404 SO HARTZL HCA2X HCA2XK1 GL PROPELLER CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 J477 INSPECTION FOUND PROPELLER ASSY P/N 838-2 CORRODED. 1 L 7 1 3O 1A15 5 C P908 1997041700190 19970417 00190 NM 1997 4 17 97ZZZX1596 1 19961009 G 5320 GEARBOX BOEING 727 727230 1384080 NM NLG BS 294.5 CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 357KP 20675 DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON TOP NLG BOX LT SIDE (FROM E/E BAY) EXTENDING FROM STA 294.5 TO STA 312 . 2 L 7 3 4F A3WE 1997041700191 19970417 00191 NM 1997 4 17 97ZZZX1597 1 19961009 G 5313 STRINGER BOEING 727 727230 1384080 NM BS 360 S19R CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 357KP 20675 DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON S19R BETWEEN STA 360 AND STA 380. 2 L 7 3 4F A3WE 1997041700192 19970417 00192 NM 1997 4 17 97ZZZX1598 1 19961009 G 5313 STRINGER BOEING 727 727230 1384080 NM BS 360 S20R CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 357KP 20675 DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON S20R BETWEEN STA 360 AND STA 380. 2 L 7 3 4F A3WE 1997041700193 19970417 00193 NM 1997 4 17 97ZZZX1599 1 19961009 G 5313 STRINGER BOEING 727 727230 1384080 NM BS 380 S18R CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 357KP 20675 DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON S18R BETWEEN STA 360 AND STA 380. 2 L 7 3 4F A3WE 1997010900109 19970109 00109 1997 1 9 97ZZZX16 4 19961025 G 2210 SUSIII SHUTTLE VALVE PIPER PA28 PA28R200 7102811 SO AUTOFLT FAILED D S K NONE O OTHER IN INSP/MAINT 1 NM 09 1043X 1895 28R7535224 INTERNAL VALVE FAILED IN THE PRECISE FLIGHT SUSIII SHUTTLE VALVE. A RIVET HEAD MIGRATED DOWNSTREAM TO THE ENGINE DRIVEN VACUUM PUMP. THE VACUUM PUMP SUBSEQUENTLY FAILED DUE TO FOREIGN OBJECT INJESTION. SUBMITTER STATED CHECK SYSTEM VISUA LLY ON AN ANNUAL BASIS REMOVING THEM FROM SERVICE AFTER 1,000 HRS. 1 L 7 1 3O 2A13 1997010900804 19970109 00804 GL 1997 1 9 97ZZZX160 3 19961105 G 6110 971 PROPELLER ASSY PIPER PA24 PA24250 7102404 SO HARTZL HCA2X HCA2XK1 GL PROPELLER CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 J477 INSPECTION FOUND PROPELLER ASSY P/N 971 BEARING CORRODED. 1 L 7 1 3O 1A15 5 C P908 1997041700194 19970417 00194 NM 1997 4 17 97ZZZX1600 1 19961009 G 5320 BOX WEB BOEING 727 727230 1384080 NM BS 312-328 CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 357KP 20675 DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON RT NLG BOX WEB BETWEEN STA 312 AND STA 328 (NOTED FORM E/E BAY AREA). 2 L 7 3 4F A3WE 1997041700195 19970417 00195 NM 1997 4 17 97ZZZX1601 1 19961009 G 5330 SKIN BOEING 727 727230 1384080 NM BS 680 S26R CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 357KP 20675 DURING C-CHECK INSPECTION, CORROSION WAS NOTED AT SKIN BULGE FS 680 AT S26R. 2 L 7 3 4F A3WE 1997041700196 19970417 00196 NM 1997 4 17 97ZZZX1602 1 19961009 G 5330 SKIN BOEING 727 727230 1384080 NM BS 340-350 CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 357KP 20675 DURING C-CHECK INSPECTION, CORROSION WAS NOTED AT SKIN BULGE EXTENDING FROM STA 340 TO STA 350 AT S26R. 2 L 7 3 4F A3WE 1997041700197 19970417 00197 NM 1997 4 17 97ZZZX1603 1 19961009 G 5313 STRINGER BOEING 727 727230 1384080 NM BS 312 S22L CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 357KP 20675 DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON S22L AT STA 312. 2 L 7 3 4F A3WE 1997041700198 19970417 00198 NM 1997 4 17 97ZZZX1604 1 19961008 G 5330 SKIN BOEING 727 727243 138408D NM BS 1130 DAMAGED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 58414 22166 DURING C-CHECK INSPECTION, A LONG DENT AND CREASE WAS NOTED IN LT AFT AIRCRAFT SKIN AT FS 1130. 2 L 7 3 4F RT A3WE 1997041700199 19970417 00199 NM 1997 4 17 97ZZZX1605 1 19961008 G 5320 SHEAR TIE BOEING 727 727243 138408D NM BS 950F CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 58414 22166 DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON SHEAR TIE AT FRAME 950F AT S28R. 2 L 7 3 4F RT A3WE 1997041700200 19970417 00200 NM 1997 4 17 97ZZZX1606 1 19961008 G 5320 SUPPORT CHANNEL BOEING 727 727243 138408D NM BS 1030 S30L CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 58414 22166 DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON SUPPORT CHANNEL AT FS 1030 FROM S30 TO S29R. 2 L 7 3 4F RT A3WE 1997041700201 19970417 00201 NM 1997 4 17 97ZZZX1607 1 19961008 G 5315 FLOOR BEAM BOEING 727 727243 138408D NM BS 344 CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 58414 22166 DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON UPPER CHORD OF CABIN FLOOR BEAM FS 344. 2 L 7 3 4F RT A3WE 1997041700202 19970417 00202 NM 1997 4 17 97ZZZX1608 1 19961009 G 5315 FLOOR BEAM BOEING 727 727243 138408D NM BS 890 BL ZERO CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 58414 22166 DURING C-CHECK INSPECTION, A CRACK WAS NOTED IN FLOOR BEAM UPPER CHORD AT FS 890, BL ZERO. 2 L 7 3 4F RT A3WE 1997041700203 19970417 00203 NM 1997 4 17 97ZZZX1609 1 19961009 G 5320 CAP BOEING 727 727243 138408D NM B S 328 LBL 20 CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 58414 22166 DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON UPPER CAP STA 328 AT LBL 20. 2 L 7 3 4F RT A3WE 1997010900805 19970109 00805 GL 1997 1 9 97ZZZX161 3 19961105 G 6110 13333 PROPELLER ASSY PIPER PA24 PA24250 7102404 SO HARTZL HCA2X HCA2XK1 GL PROPELLER CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 J477 INSPECTION FOUND PROPELLER ASSY P/N 13333 CORRODED. 1 L 7 1 3O 1A15 5 C P908 1997041700204 19970417 00204 NM 1997 4 17 97ZZZX1610 1 19961008 G 5347 SEAT TRACK BOEING 727 727243 138408D NM BS 45.5-344 CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 58414 22166 DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON 4 EACH CABIN SEAT TRACKS FROM FS 344 GTO FS 45.5 IN THE FOLLOWING BL L OCATIONS: LBL 45.5. RBL 45.5. LBL 24.75. RBL 24.75. 2 L 7 3 4F RT A3WE 1997041700205 19970417 00205 SO 1997 4 17 97ZZZX1611 1 19960429 G 3030 464357 ELEMENT PIPER PA34 PA34200T 7103406 SO REAR PITOT HEAT OPEN D K NONE O OTHER IN INSP/MAINT 1 NM 05 81070 7 348070013 LOSS OF AIRSPEED - TRACED TO OPEN PITOT HEAT ELEMENT. REPLACED REAR ELEMENT 4-29-96. 1 L 7 2 3O A7SO 1997041700206 19970417 00206 SO 1997 4 17 97ZZZX1612 1 19960402 G 3030 464357 ELEMENT PIPER PA34 PA34200T 7103406 SO REAR PITOT HEAT OPEN D K NONE O OTHER IN INSP/MAINT 1 NM 05 81070 348070013 LOSS OF AIRSPEED - TRACED TO OPEN PITOT HEAT ELEMENT. REPLACED REAR ELEMENT 4-2-96. 1 L 7 2 3O A7SO 1997041700211 19970417 00211 EU 1997 4 17 97ZZZX1617 1 19961210 G 5311 FRAME AMD FALC50 FALCON50MYST 2730106 EU FS 34 RIVETS MISSING B EBVR K NONE O OTHER IN INSP/MAINT 1 GL 09 1902W 2246 209 WHILE ACCOMPLISHING SB F50-218, THREE RIVETS WERE FOUND MISSING AT FUSELAGE FRAME 34; LEFT SIDE ABOVE BAGGAGE DOOR. RI VETS APPEAR TO HAVE BEEN MISSING SINCE MANUFACTURE OF AIRCRAFT. 2 L 7 3 4F A46EU 1997041700212 19970417 00212 1997 4 17 97ZZZX1618 4 19961121 G 3455 G686201 CONTROL HEAD AMD FALC50 FALCON50MYST 2730106 EU DUAL ADF SHORTED B AMCR K NONE B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 GL 09 254DV 119 85 DURING COCKPIT PREFLIGHT, CREW HEARD ADF NR 1 CIRCUIT BREAKER TRIP. WITHIN A FEW MOMENTS, THE ODOR OF SOMETHING BURNING WAS DETECTED. REMOVING THE ADF HEAD, THE UNIT SMELLED BURNT. THIS SAME S/N HEAD EXPERIENCED THE SAME THING A YEAR AND A HALF AGO, (545 FLT HRS). PREVIIOUS REPAIR REPORT INDICATED A FAILED POWER SUPPLY BOARD, P/N 701-0314-01. 2 L 7 3 4F A46EU 1997041700213 19970417 00213 1997 4 17 97ZZZX1619 4 19960410 G 2210 6225029001 SERVO MOUNT COLLINS SMT85B BRAERO DH125 BAE125800A 1500285 EU ELEV CONTROL MALFUNCTION B A EBVR O OTHER F FLT CONT AFFECTED AP APPROACH 1 GL 09 410BT 1722 2062 NA0468 PILOT NOTED THAT ON APPROACHES WITH THE AUTOPILOT DISENGAGED, THE ELEVATOR CONTROLS WOULD CATCH WHEN SLIGHT ADJUSTMENTS WERE MADE. THE SMALL AMOUNT OF PRESSURE NEEDED TO BREAK IT LOOSE WOULD CAUSE THE AIRCRAFT TO PORPOISE A FEW TIMES. SUS PECT INTERNAL PROBLEMS IN THE SERVO MOUNT ASSY. 2 L 7 2 4F RT A3EU 1997010900806 19970109 00806 GL 1997 1 9 97ZZZX162 3 19961105 G 6110 13336 PROPELLER ASSY PIPER PA24 PA24250 7102404 SO HARTZL HCA2X HCA2XK1 GL PROPELLER CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 J477 INSPECTION FOUND PROPELLER ASSY P/N 13336 CORRODED. 1 L 7 1 3O 1A15 5 C P908 1997041700218 19970417 00218 CE 1997 4 17 97ZZZX1624 1 19961209 G 3020 99120867 REGULATOR VALVE CESSNA 500 560CESSNA 2076750 CE ENG INLET LIP FAILED B A EBVR K NONE O OTHER IN INSP/MAINT 1 GL 09 90MF 1062 5600060 DURING PHASE INSPECTION, THE RT ENGINE INLET WAS FOUND TO HAVE BULGE SPOTS AT LIP SEAM INSIDE THE INLET. SEVERAL RIVETS HAD MISSING HEADS AROUND BULGE SPOTS AND SEVERAL MORE RIVETS HAD HEADS THAT WERE PARTIALLY PULLED OFF. THE RT ENGINE I NLET BLEED AIR REGULATING VALVE WAS FOUND TO HAVE FAILED AND NO LONGER WOULD PROPERLY REGULATE BLEED AIR TO THE INLET LI P CAUSING THE DAMAGE. REPLACEMENT OF ENTIRE INLET ASSEMBLY AND BLEED AIR VALVE WAS NECESSARY. 2 L 7 2 4F RT A22CE 1997010900807 19970109 00807 GL 1997 1 9 97ZZZX163 3 19961105 G 6110 J2016 PROPELLER ASSY PIPER PA24 PA24250 7102404 SO HARTZL HCA2X HCA2XK1 GL PROPELLER CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 J477 INSPECTION FOUND PROPELLER ASSY P/N J2016 CORRODED. 1 L 7 1 3O 1A15 5 C P908 1997010900808 19970109 00808 GL 1997 1 9 97ZZZX164 3 19961105 G 6110 3496 PROPELLER ASSY STBROS SD3 SD360 8100606 EU HARTZL HCB5M HCB5MP3 GL PROPELLER CRACKED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 15791 4474 EV711 INSPECTION FOUND PROPELLER ASSY P/N 3496 CRACKED. 2 H 7 2 4T A41EU 6 C P44GL 1997010900809 19970109 00809 GL 1997 1 9 97ZZZX165 3 19961105 G 6110 3807 PROPELLER ASSY HARTZL HCC2Y HCC2YR4 GL PROPELLER CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 903 DN374 INSPECTION FOUND PROPELLER ASSY P/N 3807 CORRODED. 5 C P920 1997041700503 19970417 00503 SW 1997 4 17 97ZZZX1655 1 19961219 G 2460 1101461S RELAY BELL 230 230 1182149 SW ELECTRICAL SYST INOPERABLE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 4UV 604 23019 INOPERABLE RELAY. 1 G 7 2 3U NC H9SW 1997041700505 19970417 00505 SW 1997 4 17 97ZZZX1657 1 19961025 G 6320 222375023111 INDICATOR BELL 230 230 1182149 SW MGT GAUGE READS HIGH B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 4UV 501 9209110 23019 MGT READS 50 DEGREES CELSIUS HIGH ALL THE TIME. 1 G 7 2 3U NC H9SW 1997041700506 19970417 00506 SW 1997 4 17 97ZZZX1658 1 19960928 G 3340 7028511 STROBE BELL 230 230 1182149 SW BEACON TRIPS BREAKER B TI1R K NONE O OTHER TX TAXI/GRND HDL 1 SW 05 4UV 02514 23019 STROBE LIGHT TRIPS CIRCUIT BREAKER. 1 G 7 2 3U NC H9SW 1997010900810 19970109 00810 GL 1997 1 9 97ZZZX166 3 19961105 G 6110 3807 PROPELLER ASSY HARTZL HCC2Y HCC2YR4 GL PROPELLER CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 804 DN942 INSPECTION FOUND PROPELLER ASSY P/N 3807 CORRODED. 5 C P920 1997010900811 19970109 00811 GL 1997 1 9 97ZZZX167 3 19961105 G 6110 3807 PROPELLER ASSY HARTZL HCC2Y HCC2YR4 GL PROPELLER CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 635 AU7576 INSPECTION FOUND PROPELLER ASSY P/N 3807 CORRODED. 5 C P920 1997010900812 19970109 00812 GL 1997 1 9 97ZZZX168 3 19961105 G 6110 3807 PROPELLER ASSY HARTZL HCC2Y HCC2YR4 GL PROPELLER CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 616 DN1712 INSPECTION FOUND PROPELLER ASSY 3807 CORRODED. 5 C P920 1997041700564 19970417 00564 EU 1997 4 17 97ZZZX1681 1 19961205 G 6240 350A08386100 WARN HORN SNIAS 350 AS350B2 8680813 EU ROTOR RPM FAILED D K NONE O OTHER IN INSP/MAINT 1 WP 09 4055L 2916 THERE ARE 2 TYPES OF WARNING HORNS. ONE MANUFACTURER IS KLAXON, THE OTHER IS VOXBELL. BOTH OF THE HORNS ARE FAILING DU E TO POOR WORKMANSHIP. ITEMS CAUSING FAILURE ARE POOR SOLDERING POINTS AND RIVETS NOT FULLY SQUEEZED WHICH SHOULD MAKE CONTACT TO ACTIVATE THE HORN WHEN ROTOR RPM FALLS BELOW MINIMUM. HAVE HAD TO ORDER 4 HORNS IN SIXTY-DAY PERIOD. 1 G 7 1 3U H9EU 1997010900813 19970109 00813 GL 1997 1 9 97ZZZX169 3 19961105 G 6110 3807 PROPELLER ASSY HARTZL HCC2Y HCC2YR4 GL PROPELLER CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 843 D1961 INSPECTION FOUND PROPELLER ASSY P/N 3807 CORRODED. 5 C P920 1997042400005 19970424 00005 CE 1997 4 24 97ZZZX1694 1 19961027 G 3213 NAS464322 BOLT CESSNA 150 150 2071802 CE NLG TORQ LINK DETACHED D A K NONE O OTHER IN INSP/MAINT 1 SO 06 BOLT CAME OUT OF JUNCTURE OF UPPER AND LOWER TORQUE LINK ASSY ON NOSE GEAR ALLOWING NOSEWHEEL TO TURN 90 DEGREES RIGHT O F CENTER AND COLLAPSE. SUBMITTER SUGGESTED TO SPECIAL CHECK THIS BOLT AS PART OF PILOT'S PRE-FLIGHT INSPECTION. 1 H 7 1 3O NT 3A19 1997010900110 19970109 00110 SO 1997 1 9 97ZZZX17 1 19961205 G 5522 722404 ELEVATOR PIPER PA42 PA421000 7104225 SO CTWT CHANNEL CRACKED B A FEHR K NONE O OTHER IN INSP/MAINT 1 SO 13 124DP 425527018 AFTER PAINT WAS CHEMICALLY REMOVED, 3 CRACKS WERE FOUND IN THE SKIN AT THE COUNTERWEIGHT CHANNEL RUNNING AFT. 2 MORE CR ACKS WERE FOUND IN THE STRINGER AFT OF THAT CHANNEL. LOOKING THROUGH THE ACCESS PANEL, IT WAS ALSO FOUND THAT THE STRIN GER WAS BROKEN. 1 L 7 2 4T RT A23SO 1997010900814 19970109 00814 EA 1997 1 9 97ZZZX170 2 19961218 G 8530 SL134441 PISTON PIN PIPER PA60 PA60600A 7106002 NM LYC O540 IO540K1J5 41532 EA CYL NR 1 FAILED D K NONE O OTHER IN INSP/MAINT 1 NE 03 L1817348A INVEST OF TOO MUCH PISTON TO PIN CLEARANCE REVEALED A PISTON PIN BROKEN IN TWO IN THE MIDDLE. IT WAS THE NR SL13444-1 P IN MFG BY CARL BRUCHNER IN GERMANY, IDENTIFIED BY 'CB-3' ON ONE END. INSTALLED IN CYL NR 1. IT HAD DAMAGED THE CONNECT ING ROD AND PISTON. THE PINS (P/N SL13444-1) WERE REPLACED AT AT OVERHAUL 2 YEARS AND 200 HOURS PREVIOUSLY AS NEW PARTS IN ALL 6 CYLS. SUPERIOR AIR PARTS, INC., HAS BEEN NOTIFIED OF THIS CONDITION. IT SHOULD BE NOTED THAT PINS SPECIFICAL LY SUPERIOR NR SA629690, MFG BY THE SAME COMPANY (CARL BRUCHNER), WERE THE SUBJECT OF A RECALL, REF: SUPERIOR MANDATORY SB NR 96-001, 8-5-96. 1 M 7 2 3O 3 O RT A17WE 1E4 1997010900815 19970109 00815 SO 1997 1 9 97ZZZX171 1 19961218 G 3230 76426 LINK ASSY PIPER PA28 PA28R201 7102816 SO NLG CRACKED B A UC2R K NONE O OTHER IN INSP/MAINT 1 GL 19 11562 28R7837194 FOUND THE LINK ASSY CRACKED IN THE RADIUS JUST FWD OF THE ATTACH POINT FOR THE DOWNLOCK ASSY. THIS IS ONE OF THE AREAS THAT NEEDS TO BE CHECKED PER SB 724A (AD 82-06-11R1), PART II, ITEM NR 3, SKETCH 3. THIS IS A ONE-TIME INSPECTION THAT HAD BEEN DONE PRIOR TO THIS PART CRACKING. SUBMITTER SUGGESTS MAKING IT A RECURRING AD EVERY 100 HOURS OR BY PARTS REPL ACEMENT. THE NEW LINK AND BRACE ASSEMBLY PN 76426-803 IS A MUCH BETTER PART. PIPER HAS ADDED A SUBSTANTIAL AMOUNT OF M ATERIAL TO THE ABOVE MENTIONED AREA. 1 L 7 1 3O 2A13 1997010900816 19970109 00816 CE 1997 1 9 97ZZZX172 1 19961216 G 2710 0422162 BELLCRANK CESSNA 140 140 2071602 CE RT AILERON WRONG PART D L A K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 01 1772V 13907 DURING RIGGING CHECK AT ANNUAL INSPECTION FOUND THAT AILERONS COULD NOT REACH FULL TRAVEL UP OR DOWN. THE LT AILERON TR AVEL 21 DEGREES UP AND 11 DEGREES DOWN AND THE RT AILERON TRAVEL ONLY 13 DEGREES UP AND 18 DEGREES DOWN. INV. FOUND INC ORRECT BELLCRANK INSTALLED ON RT WING AILERON. 1 H 7 1 3O NC A768 1997010900817 19970109 00817 CE 1997 1 9 97ZZZX173 1 19961001 G 2710 AN410A BOLT CESSNA 177 177A 2073706 CE LT AIL HORN FELL OUT D L K NONE O OTHER IN INSP/MAINT 1 GL 25 30567 17701332 DURING AN ANNUAL INSPECTION IT WAS FOUND THAT THE AN 4-10A BOLT CONNECTING THE PUSH/PULL ROD TO THE LEFT AILERON HORN HA D BACKED OUT TO THE POINT THAT BY MOVING THE AILERON BY HAND, THE BOLT FELL OUT COMPLETELY. THE BOLT WAS NOT SAFTIED. F URTHER INSPECTION OF THE RIGHT AILERON FOUND THAT THE BOLT WAS LOOSE AND WAS ALSO AN 4-10A AND NOT SAFETIED. BOTH AN 4- 10A BOLTS WERE REPLACED WITH AN 4H-10A AND PROPERLY SAFETIED. 1 H 7 1 3O A13CE 1997010900818 19970109 00818 CE 1997 1 9 97ZZZX174 1 19961201 G 5320 07106082 ANGLE CESSNA 182 182E 2072712 CE BULKHEAD RUSTED D L K NONE O OTHER IN INSP/MAINT 1 WP 17 69EL 18254060 INSPECTION OF LDG GEARBOX BULKHEAD LOWER AFT SIDE, FOUND ANGLES RUSTED COMPLETELY THROUGH IN SEVERAL LOCATIONS ON FLANGE S. SUBMITTER SUGGESTED CAUSE IS DUE TO TRAPPED DIRT AND WATER AND INADEQUATE DRAIN HOLES OR LOCATION. 1 H 7 1 3O NT 3A13 1997042400283 19970424 00283 NM 1997 4 24 97ZZZX1740 1 19961106 G 5280 65216361 DOOR SPAR BOEING 727 727251 138408H NM MLG CRACKED B EG4R K NONE O OTHER IN INSP/MAINT 1 SO 25 800716 DURING REPAIR OF MLG DOOR, FOUND CRACKS IN REAR SPAR ON 2 UNITS. CRACKS ARE AT LOCATION WHERE THE UP-STOP ATTACHES TO D OOR. BOEING HAS BEEN ASKED FOR REPAIR. 2 L 7 3 4F A3WE 1997010900819 19970109 00819 EA 1997 1 9 97ZZZX175 2 19961219 G 8520 LIFTER CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA INTAKE SPALLED D L K NONE O OTHER IN INSP/MAINT 1 GL 09 73462 17267479 RL5028827A FERROUS METAL FOUND IN OIL SCREEN AT INSPECTION. AFTER FURTHER INVESTIGATION, FOUND ALL 4 INTAKE LIFTER BODIES SEVERELY SPALLED AND THE 2 CAM LOBES THAT OPERATE THEM WORN. 1 H 7 1 3O 3 O NT 3A12 E274 1997010900820 19970109 00820 CE 1997 1 9 97ZZZX176 1 19961226 G 2720 04115264 BAR ASSY CESSNA 150 152 2071835 CE RT RUD PEDAL BROKEN D L A K NONE O OTHER IN INSP/MAINT 1 WP 15 89955 8923 15282926 PILOT REPORTED THAT DURING RUN-UP PRIOR TO FLIGHT, RIGHT RUDDER PEDAL WOULD NOT MOVE RUDDER SURFACE. INSPECTION REVEALE D A WELD IN RUDDER BAR ASSY HAD BROKEN AT THE ARM WHICH CONNECTS IT TO THE RUDDER PEDAL (PILOT'S RIGHT RUDDER). CAUSE O F BREAK: SUSPECTED METAL FATIGUE OF WELD AREA. FAILURE IS EXACTLY AS SHOWN IN ALERT NR 215 DATED JUNE 1996, PAGE 7, AC NR 73-16. 1 H 7 1 3O NT 3A19 1997010900821 19970109 00821 EA 1997 1 9 97ZZZX177 2 19961231 G 7314 LW15473 PUMP PIPER PA28 PA28R201 7102816 SO LYC O360 IO360C1C6 41514 EA ENG FUEL MALFUNCTION B ESMR K NONE O OTHER NR NOT REPORTED 1 SO 11 9185P 427 2837032 L2507551A FUEL PUMP MALFUNCTION. TWO SMALL PIECES OF A BUSHING ON THE TIP OF THE PLUNGER ASSEMBLY BROKE OFF AND WERE FOUND IN THE SUCTION SCREEN. DATE CODE ON THE PUMP REVEALED MANUFACTURE WAS IN 1994. 1 L 7 1 3O 3 O 2A13 1E10 1997010900823 19970109 00823 CE 1997 1 9 97ZZZX179 1 19961205 G 2720 15371 PEDAL BBAVIA 8 8KCAB 2110612 CE RUD LT FWD FAILED G P A K NONE O OTHER NR NOT REPORTED 1 NE 02 5061K 56079 THE OPERATOR REPORTS A THIRD FAILURE OF THE LEFT FORWARD RUDDER PEDAL AT THE LOWER LEFT HAND CORNER AT 65 HOURS TIMES IN SERVICE. THIS FIRST AND S ECOND FAILURE OCCURRED AT 147 AND 86 HOURS RESPECTIVELY. PART TOTAL TIME AVERAGE = 93 HOURS . 1 H 7 1 3O A21CE 1997010900111 19970109 00111 SO 1997 1 9 97ZZZX18 1 19961212 G 2810 6399816 TANK PIPER PA28 PA28140 7102802 SO LT FUEL CORRODED D A K NONE O OTHER IN INSP/MAINT 1 NE 03 15488 3017 287325078 UPON REMOVAL OF THE LT WING FUEL TANK FOR REPLACEMENT OF FUEL VENT HOSES, CORROSION WAS NOTED AT THE OUTBOARD SIDE FALSE RIB (NOSE RIB) SECTION OF THE FUEL TANK. THE CORROSION WAS BLISTERED. AFTER PROBING WITH THE POINT OF A METAL SCRIBE, IT WAS FOUND THE METAL COULD BE PENETRATED WITH LIGHT HAND PRESSURE. THERE WAS NO EVIDENCE OF FUEL LEAKAGE. 1 L 7 1 3O 2A13 1997010900824 19970109 00824 SO 1997 1 9 97ZZZX180 1 19961205 G 5320 6797202 STIFFENER 76436000 PIPER PA28 PA28R201 7102816 SO NLG WELL MISSING B UC2R O OTHER J WARNING INDICATION AP APPROACH 1 GL 19 40024 2472 28R7737128 THE PILOT REPORT NO DWN AND LK IND FOR THE NLG. THE ACFT INTO THE SHOP FOR AN INSP OF THE NLG TO ID DIFFICULTY. FOUND THAT THE STRUCT ABOVE THE NLG ACT ATTACH BRKT; PN 67271-800 WAS PUSHED UP APPROX .25 INCH AND IT BUCKLED THE WELL ASSY I N SUCH A WAY THAT IT ALLOWED THE DWN AND LK SW TO NOT MAKE CONTACT. THE SUSPECT CAUSE OF THE DAMAGE IS THE COMBINATION OF THE PRESSURE EXERTED BY THE NLG ACT IN THE UP POSIT AND LACK OF ADEQUATE STRUCTURE IN THAT AREA. THIS ACT ATTACH AL SO DOUBLES AS THE FWD JACK POINT AND COULD HAVE BEEN WEAKENED BY REPEATED USE. UPON FURTHER INVEST, IT WAS FOUND THAT A STIFFENER WAS MISSING FROM WELL ASSEMBLY; PN 76436-000, AS PER FIG 8, ITEM 47, PG 1B15 OF THE PTS MAN. 1 L 7 1 3O 2A13 1997010900825 19970109 00825 SO 1997 1 9 97ZZZX181 2 19961226 G 8520 6436511 STUD CONT O360 TSIO360EB 17025 SO CYL HOLD DOWN STRETCH D A K NONE O OTHER IN INSP/MAINT 1 NM 11 1762 265972R DURING THE COURSE OF A NORMAL ENG OVERHAUL, IT WAS FOUND THAT ABOUT ONE-THIRD OF THE CYL DECK STUDS WOULD NOT HOLD SPECI FIED TORQUE WITHOUT STRETCHING. THE STUDS ARE A NEWER 'NECKED DOWN' DESIGN. THE MECH REPLACED ALL CYL DECK STUDS WITH AN OLDER STRAIGHT DESIGN AND TORQUED THEM TO SPEC. IT IS CRITICAL THAT THESE STUDS HOLD TORQUE. SUBMITTER STATED IT IS LIKELY THAT THE REASON THAT THE STUDS WOULD NOT HOLD TORQUE IS THAT THEY WERE NOT MFG WITH THE CORRECT HARDNESS. RECOM MENDED THAT ALL CYL DECK STUDS BE CHECKED AT THE SPECIFIED TORQUE BEFORE FINAL ASSEMBLY AT OVERHAUL OR AT A CYLINDER CHA NGE. 3 O E9CE 1997010900826 19970109 00826 EA 1997 1 9 97ZZZX182 2 19960904 G 7414 103828204 HOUSING PIPER PA32 PA32R301T 7103220 SO LYC O540 TIO540S1AD 41532 EA ENG MAG BROKEN B A OF1R A UNSCHED LANDING Y ENGINE STOPPAGE NR NOT REPORTED 1 EA 25 8186G 32R8029079 L699361A AIRCRAFT TACK TIME 2951.81. ENG FAILURE RESULTED IN OFF AIRPORT LANDING CAUSING DAMAGE TO AIRCRAFT OF UNREPAIRABLE AMOU NT. FAILURE CAUSED BY DUAL MAGNETO FALLING OFF OF ACCESSORY CASE AND DRIVE GEAR DISENGAGING FROM ENG. EXAM SHOWS LOWER MAG HOLD DOWN STUD INTACT BUT NUT, WASHER, LOCKWASHER, AND HOLD DOWN CLIP MISSING. UPPER MAG HOLD DOWN STUD INTACT WIT H NUT, WASHER, LOCKWASHER, AND CLIP INSTALLED BUT SIGNIFICANT SECTION OF MAG HOUSING HOLD DOWN FLANGE BROKEN OFF. 1 L 7 1 3O 3 O A3SO E14EA 1997010900827 19970109 00827 SO 1997 1 9 97ZZZX183 2 19961202 G 7322 MA3SPA CARBURETOR FACET CESSNA 150 150L 2071826 CE CONT O200 O200A 17020 SO FLOAT BOWL MALFUNCTION D O OTHER R PARTIAL RPM/PWR LOSS CR CRUISE 1 NM 09 16125 2493 15073494 20559270A PILOT REPORTS TWO OR THREE HARD JOLTS FROM TURBULENCE WITH NEG G-FORCE. THE ENGINE WENT TO NEAR IDLE POWER. DISASSEMBL Y OF THE CARB REVEALED THE PRESENCE OF A SILT CLOD IN MAIN JET. SUBMITTER RECOMMENDS PERIODIC CLEANING OF FLOAT BOWL TO REMOVE BUILD UP OF SILT. DRAINING OF THE BOWL DOES NOT REMOVE BUILD UP. 1 H 7 1 3O 3 O 3A19 E252 1997010900829 19970109 00829 EA 1997 1 9 97ZZZX184 2 19961202 G 7322 MA4SPA CARBURETOR TUBE FACET PIPER PA28 PA28161 7102803 SO LYC O320 O320D3G 41508 EA ACCEL PUMP LOOSE B NE2R O OTHER J WARNING INDICATION NR NOT REPORTED 1 CE 07 21428 1886 CK611417 28796039 L851839A IN FLIGHT, RPM WOULD NOT DECREASE BELOW 2000 RPM. INVESTIGATION FOUND ACCELERATOR PUMP NOZZLE DISLODGED AND LYING IN AI R BOX. CARBURETOR SENT TO REPAIR STA. FOR OVERHAUL. SUSPECT NOZZLE ADHESIVE BROKEN LOOSE WHEN SINGLE PIECE VENTURI WAS INSTALLED AT 1865 HRS. LANDING WAS SAFE. NO DAMAGE ENGINE KILLED ON FINAL, WITH MIXUTRE CONTROL. 1 L 7 1 3O 3 O 2A13 E274 1997010900830 19970109 00830 SW 1997 1 9 97ZZZX185 1 19961003 G 5320 340117119 TUBE MOONEY M20 M20E 5870212 SW LT CABIN FRAME SPLIT D K NONE O OTHER IN INSP/MAINT 1 GL 27 333WS 4200 323 DURING ANNUAL INSPECTION, FOUND CABIN STRUCTURAL TUBE NR 340117-119 LT HAD FILLED WITH WATER, FROZEN AND SPLIT OPEN. RE PAIRED IAW 43.13-1A. INSPECTED AND SEALED STRUCTURES IAW M20-208B. 1 L 7 1 3O 2A3 1997010900833 19970109 00833 CE 1997 1 9 97ZZZX188 1 19961219 G 2140 RESISTOR JANITROL BEECH 60 B60 1153605 CE HEATER CKT FAILED D A H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 SW 13 4646M B3040 P464 PILOT REPORTED CABIN HEATER INOPERATIVE AND HAD SMELLED SMOKE IN CABIN. FOUND CABIN VENTILATION BLOWER INOPERATIVE WHIC H CAUSED OVERTEMP CONDITION. WHEN OVERTEMP SWITCH TRIPPED, RATHER THAN OPENING HEAT FUSE (5 AMP), 10 WATT, 3 OHM RESIST OR BURNED AND OPENED. THIS RESISTOR BEING OPEN PROHIBITS NORMAL FUNCTION OF OVERTEMP PROTECTION CIRCUIT. HEATER WAS SH UT DOWN BY PILOT WITH NO FURTHER DAMAGE. APPARENTLY THIS RESISTOR BURNED BEFORE FUSES OPENED. EXPERIENCED IDENTICAL PR OBLEM ON 9B655 BARON, BUT DUCT WORK WAS DAMAGED THROUGHOUT AIRCRAFT. 1 L 7 2 3O A12CE 1997010900834 19970109 00834 1997 1 9 97ZZZX189 4 19961211 G 3120 587961 TRANSDUCER PIPER PA28 PA28R200 7102811 SO HOBBS METER LEAK C O OTHER K FLUID LOSS TX TAXI/GRND HDL 1 SO 15 55177 7335190 ON TAXI OUT PILOT FELT LIQUID ON HIS LEFT FOOT. HE LOOKED AT HIS FOOT AND FOUND IT COVERED WITH ENGINE OIL. HE SHUT DO WN THE ENGINE AND DISCOVERED SOURCE OF OIL TO BE THE HOBB'S TRANSDUCER. ABOUT THREE-FOURTHS OF A QUART OF OIL WAS SPILL ED ON PILOT'S FOOT IN CABIN. 1 L 7 1 3O 2A13 1997010900112 19970109 00112 SO 1997 1 9 97ZZZX19 1 19961212 G 2810 63913194 HOSE DEUTSCH PIPER PA28 PA28140 7102802 SO FUEL VENT DRY ROT D K NONE O OTHER IN INSP/MAINT 1 NE 03 15488 3017 287325078 FUEL VENT HOSES AND FUEL SUPPLY HOSES AT FUEL TANK OUTLET FOUND WITH DRY-ROT, HARD AND BRITTLE. DATE CODE ON FUEL SUPPL Y HOSES, 1972. NO SIGN OF FUEL LEAKS. 1 L 7 1 3O 2A13 1997010900835 19970109 00835 NE 1997 1 9 97ZZZX190 2 19961003 G 8520 72877 LIFTER LW19340 MAULE M5 M5235C 5460135 SO LYC O540 IO540W1A5 41532 NE CAMSHAFT SPALLED D K NONE O OTHER IN INSP/MAINT 1 GL 27 5643N 383 A7361C L2120448A DURING ANNUAL INSPECTION FOUND STEEL IN OIL FILTER. ENGINE DISASSEMBLED, ALL LIFTERS AND CAMSHAFT BADLY SPALLED. THESE COMPONENTS HAD A TT OF 383 HRS SINCE REGRIND AND AEROLUBE PROVIDED BY AIR SUPPORT INTERNATIONAL. 1 H 7 1 3O 3 O 3A23 1E4 1997010900837 19970109 00837 CE 1997 1 9 97ZZZX192 1 19961216 G 2130 99100181 AIR FILTER 511725811 CESSNA 421 421C 2076016 CE HEAT EXCHANGE FAILED D K NONE O OTHER IN INSP/MAINT 1 NE 01 88604 3147 421C0604 CABIN PRESSURIZATION WEAK, INSPECTED PRESSURIZATION HEAT EXCHANGER IN WING. BOTH EXCHANGERS PLUGGED WITH FELT MATERIAL. SUSPECT FELT MATERIAL CAME FROM ENDS OF PAPER AIR FILTERS. VACUUM AND CLEANED HEAT EXCHANGERS, TEST FLIGHT CHECK, AND NORMAL. 1 L 7 2 3O A7CE 1997010900838 19970109 00838 CE 1997 1 9 97ZZZX193 1 19961101 G 3211 24411009 PIVOT CESSNA 172 172RG 2072438 CE RT MLG LEG SHEARED D O OTHER J WARNING INDICATION AP APPROACH 1 SW 15 95208 1612 172RG0851 SPLINE PORTION OF PIVOT ASSY SHEARED DURING NORMAL OPERATIONAL USE. RIGHT MAIN GEAR LEG WOULD NOT LOCK DOWN. PILOT DID A GREAT JOB OF MINIMIZING DAMAGE TO A/C. RECOMMEND FLUORESCENT PENETRANT INSPECT DURING ANNUAL INSPECTION OF SPLINE SH AFT WHERE IT MEETS THE REST OF THE PIVOT ASSY. 1 H 7 1 3O 3A17 1997050800009 19970508 00009 CE 1997 5 8 97ZZZX1931 1 19961216 G 3234 2MD31AX287 SWITCH A4503M95 BEECH 100 B100 1152919 CE GEAR MOTOR CONT STUCK CLOSED H L A K NONE O OTHER IN INSP/MAINT 1 NM 03 500KD 7971 BE79 MECHANICS WERE WORKING ON LANDING GEAR DOWNLOCK (J-HOOK) SOLENOID. THEY WERE CHECKING OPERATION OF THE SOLENOID BY AC TIVATING THE RIGHT SQUAT SWITCH. ACFT WAS NOT ON JACKS AT THAT POINT. GEAR HANDLE WAS VERIFIED IN DOWN POSITION PRIOR TO ACTIVATION OF THE SQUAT SWITCH. AS MECHANICS ACTIVATED SQUAT SWITCH, GEAR MOTOR STARTED TO RUN IN THE RETRACT DIREC TION. LANDING GEAR MOVED ENOUGH TO BREAK OVER CENTER POSITION ON BOTH MAIN GEARS AND ACFT COLLAPSED ONTO THE FLOOR. NL G ACTIVATED OVER CENTER, BUT NOT ENOUGH TO CAUSE GEAR TO COLLAPSE. MAJOR LANDING GEAR DAMAGE, ENGINE WHEELWELL NACELLE DAMAGE, FLAP DAMAGE, HORIZ STAB DAMAGE FROM COLLAPSING ONTO THE NOSE OF ANOTHER ACFT, BUT NO ENGINE DAMAGE. 1 L 7 2 4T A14CE 1997010900839 19970109 00839 CE 1997 1 9 97ZZZX194 1 19961228 G 2436 DGR6 REGULATOR CESSNA 182 182P 2075816 CE DC SYS MALFUNCTION D K NONE O OTHER IN INSP/MAINT 1 WP 23 9970E 64 2374 18264030 INSTALLED OVERHAULED ALTERNATOR AND NEW VOLT REGULATOR AT 769 TTSN. AT 833 HRS REGULATOR FAILED. INSTALLED THE OLD ORI GINAL REGULATOR AND SYSTEM FUNCTIONS PROPERLY. SUBMITTER SUGGESTS RECALL ALL PFT, INC. REGULATORS IN SAME BATCH FOR CON FORMITY INSPECTION AND TEST. 1 H 7 1 3O NT TA13 1997010900840 19970109 00840 CE 1997 1 9 97ZZZX195 1 19961003 G 2821 GASCOLATOR BBAVIA 11 11BC 0191106 CE FUEL FILTER LEAKING D K NONE K FLUID LOSS IN INSP/MAINT 1 GL 27 9502E 11AC1137 WHILE INSPECTING A/C FOR FERRY FLIGHT FUEL WAS FOUND DRIPPING FROM GASCOLATOR. GASCOLATOR BOWL WAS NOT PROPERLY SEATED ON GASKET AND BAIL NUT WAS NOT SAFTIED. AD 47-20-01 HAD BEEN C/W 4 HRS PRIOR BY REPAIR STATION DVOR3450. 1 H 7 1 3O A761 1997010900841 19970109 00841 EU 1997 1 9 97ZZZX196 1 19961129 G 3242 50028053 BRAKE ASSY ISRAEL 1124 1124 4500102 EU LT MLG DISK BROKEN B VT2R O OTHER O OTHER LD LANDING 1 CE 09 72787 84 MAY86539 240 LEFT HAND BRAKE ASSEMBLY FAILED UPON LANDING. SUBSEQUENT INVESTIGATION DISCLOSED A BROKEN STATIONARY DISK ASSEMBLY. A TWO INCH SECTION OF THE DISK ASSEMBLY WAS SEPARATED. NOTIFIED AIRCRAFT BRAKING SYSTEMS. THE BRAKE ASSEMBLY WAS SHIPPED TO ABS FOR EVALUATION. LNDS: 72. PART TSN: 84.3 HRS. 2 M 7 2 4F A2SW 1997010900843 19970109 00843 1997 1 9 97ZZZX198 4 19961210 G 2562 ELT910 ELT NARCO BELL 204 204B 1181404 SW ACFT MALFUNCTION D K NONE O OTHER IN INSP/MAINT 1 WP 23 204SH 500 13406 2019 FAA REPORTED ELT SIGNALS IN AREA; CHIEF PILOT CHECK ALL 4 OF OUR AIRCRAFT AND CHECKED THAT ALL SWITCHES WERE IN 'OFF' PO SITION. FAA CAME OUT AND DETERMINED THAT THIS ELT WAS OPERATING AND THAT THE SWITCH WAS 'OFF'. REMOVED ELT FROM AIRCRA FT AND REMOVED BATTERY TO STOP ELT SIGNAL. 1 G 7 1 4U H1SW 1997010900844 19970109 00844 SW 1997 1 9 97ZZZX199 1 19961212 G 6320 70061F3352080A HOSE BELL 206 206L1 1182107 SW FREEWHEEL LEAKING D K NONE K FLUID LOSS IN INSP/MAINT 1 SW 09 5748H 45490 TRANSMISSION TO FREEWHEELING UNIT HOSE WAS SEEPING AT MIDDLE OF LINE DUE TO DEFECT. HOSE WAS REPLACED WITH SERVICEABLE HOSE. 1 G 7 1 3U H2SW 1997010900095 19970109 00095 1997 1 9 97ZZZX2 1 19961114 G 2434 ALU23 SPACER ELECTROSYS ALT9422 ALTERNATOR MISMANUFACTURED B KC2R K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 03 4082087 THIS ALTERNATOR IS AN ELETROSYSTEMS NEW UNIT. THE O-RING GROOVE WAS MACHINED INCORRECTLY ON THE ALU-23 SPACER ALLOWING ENGINE OIL TO LEAK PAST THE XA-744AZ O-RING AND CONTAMINATING THE X-4087 DRIVE END BEARING. THIS ALTERNATOR WAS REMOVED FOR A 500-HOUR BEARING INSPECTION WHEN THIS DEFECT WAS FOUND. 1997010900113 19970109 00113 SO 1997 1 9 97ZZZX20 1 19961212 G 2810 63913193 HOSE DEUTSCH PIPER PA28 PA28140 7102802 SO FUEL VENT DRY ROT D A K NONE O OTHER IN INSP/MAINT 1 NE 03 15488 3017 287325078 FUEL VENT HOSES AND FUEL SUPPLY HOSES AT FUEL TANK OUTLET FOUND WITH DRY-ROT, HARD AND BRITTLE. DATE CODE ON FUEL SUPPL Y HOSES, 1972. NO SIGN OF FUEL LEAKS. 1 L 7 1 3O 2A13 1997010900845 19970109 00845 WP 1997 1 9 97ZZZX200 1 19961129 G 6420 369H1801 SWASHPLATE HUGHES 369 369HS 4470728 WP T/R HEAD BUSHING DETACHED D K NONE E VIBRATION/BUFFET NR NOT REPORTED 1 SW 99 9244F 350722S VIBRATION FELT THROUGH T/R PEDALS, SPECIFICALLY LEFT PEDALS. UPON INSPECTION, BUSHING AT INBOARD END OF T/R SWASHPLATE T-HEAD HAD COME OUT, SLID INBOARD ON T/R OUTPUT SHAFT AND DAMAGED T/R OUTPUT SHAFT SEAL. 1 G 7 1 3U H3WE 1997010900846 19970109 00846 SW 1997 1 9 97ZZZX201 1 19961216 G 2913 01434430001 PUMP BELL 206 206B 1181511 SW HYD SYS SEAL LEAK D K NONE K FLUID LOSS IN INSP/MAINT 1 SW 09 108FH 3348 05228 2770 HYDRAULIC PUMP LEAKING STATICALLY AT INPUT SEAL. TBO TIME IS 3600 HRS ON THIS COMPONENT. REPLACED WITH SERVICEABLE UNI T. 1 G 7 1 3U H2SW 1997010900847 19970109 00847 GL 1997 1 9 97ZZZX202 2 19961213 G 7230 23057142 CASE HALF HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL COMP CRACKED B EOOR K NONE O OTHER IN INSP/MAINT 1 AL 03 5074R 656 14830 1151D CAE832750 DURING ANNUAL INSPECTION THE ENG COMPRESSOR CASE HALVES WERE INSPECTED AND FOUND TO BE CRACKED AND LIFTING. REPLACED CA SE HALVES. 1 G 7 1 3U 3 U H3WE E4CE 1997010900848 19970109 00848 GL 1997 1 9 97ZZZX203 2 19961218 G 7210 23034787 BEARING 6894171 HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL ENG GEARBOX SPALLED B EOOR K NONE J WARNING INDICATION IN INSP/MAINT 1 AL 03 5074R 3859 1151D CAE832750 PILOT HAD JUST RUN THE ENGINE UP TO FLIGHT IDLE IN PREPARATION FOR TAKEOFF WHEN THE ENGINE CHIP LIGHT ILLUMINATED. A LA RGE CHIP .0937 INCH BY .0625 INCH WAS FOUND ON THE UPPER CHIP PLUG AND SUBSEQUENT INSPECTION FOUND 2 ROLLERS WITH DEEPLY SPALLED AREAS ON THE WORKING SURFACES. 1 G 7 1 3U 3 U H3WE E4CE 1997010900849 19970109 00849 WP 1997 1 9 97ZZZX204 1 19961209 G 6320 369D2516421 NOZZLE 369D25100505 HUGHES 369 369D 4470706 WP XMSN OIL BENT B EOOR K NONE O OTHER IN INSP/MAINT 1 AL 03 5074R 8534 2433 1260044 1151D DURING OVERHAUL OIL NOZZLE WAS FOUND BENT - PART WAS REPLACED. 1 G 7 1 3U H3WE 1997010900850 19970109 00850 NE 1997 1 9 97ZZZX205 1 19961213 G 6320 7635109002050 HOUSING SKRSKY S76 S76B 8143007 NE M/R GEARBOX CRACKED B EGRR K NONE O OTHER IN INSP/MAINT 1 EA 17 76RP 2337 C00100027 760349 WHILE PERFORMING 150 HR INSPECTION A CRACK WAS FOUND ON THE UPPER HOUSING AFT RIGHT FOOT OF THE MAIN GEARBOX. (UPPER HO USING TT 2336.7). REPLACED MAIN GEARBOX ASSEMBLY WITH A SERVICEABLE GEARBOX IAW SIKORSKY MM. A/C TT 3091.8 HRS. GRBOX P/N 76351-09600-042. 1 G 7 2 4U H1NE 1997010900851 19970109 00851 GL 1997 1 9 97ZZZX206 2 19961211 G 7310 70009H75W204 HOSE BELL 206 206B 1181511 SW ALLSN 250C 250C18 03011 GL FUEL PUMP LEAKING D K NONE K FLUID LOSS IN INSP/MAINT 1 SW 09 7929J 663 ENGINE DRIVEN FUEL PUMP INLET LINE LEAKING AT FLARE FITTING DUE TO A CRACK. REPLACED WITH SERVICEABLE LINE. 1 G 7 1 3U 3 U H2SW E4CE 1997010900852 19970109 00852 SW 1997 1 9 97ZZZX207 1 19961205 G 6210 206010154003 WASHER BELL 206 206B 1181511 SW M/R BLADE BOLT CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 09 18FH 2599 DURING A WEEKLY INSPECTION THE M/R BLADE BOLT LOWER WASHER WAS FOUND CRACKED. REMOVED WASHER. INSTALLED SERVICEABLE WA SHER. ACFT TT 8079.6. 1 G 7 1 3U H2SW 1997010900853 19970109 00853 1997 1 9 97ZZZX208 4 19961216 G 3457 TNL2000T GPS BELL 206 206B 1181511 SW COCKPIT MALFUNCTION D K NONE O OTHER IN INSP/MAINT 1 SW 09 108FH 102 6153477 2770 GPS CONTINUALLY DUMPS ALL INFORMATION WITHOUT WARNING AND DISPLAYS A FAILURE CODE. NR 08. REPLACED WITH SERVICEABLE UN IT. 1 G 7 1 3U H2SW 1997010900854 19970109 00854 EA 1997 1 9 97ZZZX209 2 19961216 G 8530 05K21124 GUIDE HUGHES 269 269C 4470504 WP LYC O360 HIO360D1A 41514 EA NR 3 CYL EXH WORN B MQ2R K NONE O OTHER IN INSP/MAINT 1 CE 09 8666F 174 970634 L864751A FOUND LOW COMPRESSION (30/80) DURING NORMAL MAINT INSPECTION. REMOVED CYL AND FOUND .009 INCH WEAR AT PORT END OF EX GU IDE AND .002 INCH WEAR ON VALVE STEM. THIS WAS A LYCOMING FACTORY NEW CYL KIT INSTALLED DURING RECENT MAJOR OVERHAUL. 1 G 7 1 3O 3 O 4H12 1E10 1997010900114 19970109 00114 SO 1997 1 9 97ZZZX21 1 19961112 G 2740 1604000 BEARING BLOCK PIPER PA23 PA23250 7102308 SO STAB WORN D O OTHER E F VIBRATION/BUFFET FLT CONT AFFECTED DE DESCENT 1 GL 17 22TD 277854103 STABILATOR VIBRATION, FLUTTER IN DESCENT (AT HIGH SPEED) TRACED TO MOVEMENT IN ABOVE PIVOT JOINT. HOLE IN BLOCK, BUSHIN G, AND BOLT ALL SEVERELY WORN. PLAY IN JOINT NOT IMMEDIATELY EVIDENT BECAUSE OF SPRING LOADING ON BELLCRANK. RT SIDE N OT WORN. WEAR ALLOWS TAB TO MOVE AND FLUTTER, INDUCING MOVEMENT IN STAB. 1 L 7 2 3O 1A10 1997010900855 19970109 00855 WP 1997 1 9 97ZZZX210 1 19961209 G 3213 369H60024 STRUT 369H600152 HUGHES 369 369D 4470706 WP RT AFT CRACKED G K NONE O OTHER IN INSP/MAINT 1 WP 13 58267 390473D DURING POST-FLIGHT INSPECTION, A CRACK WAS DETECTED EMANATING FROM THE BRACE LOWER ATTACH HOLE EXTENDING 3 INCHES UPWARD TOWARD THE DAMPER ATTACH POINT. RECOMMEND REMOVING BRACE FROM STRUT AND INSPECTING BOLT HOLES EVERY 100 HRS. 1 G 7 1 3U H3WE 1997010900856 19970109 00856 CE 1997 1 9 97ZZZX211 1 19960814 G 3211 24411001 PIVOT CESSNA 172 172RG 2072438 CE LT MLG LEG SHEARED D A O OTHER J WARNING INDICATION AP APPROACH 1 CE 07 9865B 5062 172RG1061 A SUCCESSFUL CRASH LANDING WAS ACCOMPLISHED WITH THE LANDING GEAR SELECTED UP FOLLOWING A FAILURE OF THE LT MLG LEG TO COMPLETELY LOCK DOWN. THIS EVENT HAPPENED FOLLOWING MULTIPLE TAKEOFF AND LANDINGS DURING A TRAINING FLIGHT. UPON THE L AST LANDING PRIOR TO THE GEAR-UP LANDING, THE LT BRAKE WENT COMPLETELY SOFT AND SPONGY. SEVERAL ATTEMPTS WERE MADE TO L OCK THE LT MAIN GEAR DOWN-AND-LOCKED, HOWEVER, THEY WERE UNSUCCESSFUL. DAMAGE OCCURRED TO THE BELLY, ENGINE AND PROPELL ER. INVESTIGATION REVEALED THE LT MLG PIVOT ASSY SHEARED AT THE BASE OF THE SPLINED SURFACE. PIVOT ASSY SENT TO CESSNA M AND P FOR ANALYSIS AND TESTING. PIVOT ASSY INSPECTED PREVIOUSLY BY SEB 90-1, REV 2, FOR CRACKS. 1 H 7 1 3O 3A17 1997010900858 19970109 00858 NE 1997 1 9 97ZZZX213 2 19961220 G 7260 107006204 GEAR 107022013 KAMAN K1200 K1200 05625F6 SW LYC T53 T5317A 41549 NE ACCY DRIVE PIN FAILED D K NONE J WARNING INDICATION IN INSP/MAINT 1 NM 09 311KA 443 A940017 LE81016 N2 FAILURE OCCURRED. UPON ENGINE DISASSEMBLY AND INSP, FAILURE WAS CAUSED BY LOCK PIN AN 122683 HOLDING BEARING SLEEVE IN GEAR 1-070-062-04 FALLING OUT ALLOWING GEAR POSITION TO CHANGE AND SUBSEQUENT N2 DRIVE TO FAIL. GEAR IS COMPONENT OF CARRIER ASSY 1-070-220-13. 1 G 7 1 4F 4 U NT TR7BO E17EA 1997011600012 19970116 00012 SW 1997 1 16 97ZZZX218 1 19961107 G 6230 206010335001 LEVER ASSY BELL 206 206L1 1182107 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 1081G 481 45405 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10 1 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 480.6 HOURS. 1 G 7 1 3U H2SW 1997011600013 19970116 00013 SW 1997 1 16 97ZZZX219 1 19961107 G 6230 206010336005 LINK IDLER BELL 206 206L1 1182107 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 1081G 481 45405 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10 1 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 480.6 HOURS. 1 G 7 1 3U H2SW 1997010900115 19970109 00115 SO 1997 1 9 97ZZZX22 1 19961112 G 2740 3397208 BELLCRANK PIPER PA23 PA23250 7102308 SO STAB WORN D O OTHER E F VIBRATION/BUFFET FLT CONT AFFECTED DE DESCENT 1 GL 17 22TD 277854103 STABILATOR VIBRATION, FLUTTER IN DESCENT (AT HIGH SPEED) TRACED TO MOVEMENT IN ABOVE PIVOT JOINT. HOLE IN BLOCK, BUSHIN G, AND BOLT ALL SEVERELY WORN. PLAY IN JOINT NOT IMMEDIATELY EVIDENT BECAUSE OF SPRING LOADING ON BELLCRANK. RT SIDE N OT WORN. WEAR ALLOWS TAB TO MOVE AND FLUTTER, INDUCING MOVEMENT IN STAB. 1 L 7 2 3O 1A10 1997011600014 19970116 00014 SW 1997 1 16 97ZZZX220 1 19961107 G 6230 206010335001 LEVER ASSY BELL 206 206L4 1182110 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 174AL 341 341 52067 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10 1 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 341.1 HOURS. 1 G 7 1 3U NC H2SW 1997011600015 19970116 00015 SW 1997 1 16 97ZZZX221 1 19961107 G 6230 206010336005 LINK IDLER BELL 206 206L4 1182110 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 174AL 341 52067 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10 1 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 341.1 HOURS. 1 G 7 1 3U NC H2SW 1997011600016 19970116 00016 SW 1997 1 16 97ZZZX222 1 19961021 G 6230 2065010335001 LEVER ASSY BELL 206 206L1 1182107 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 206SL 690 45245 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10 1 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 690 HOURS. 1 G 7 1 3U H2SW 1997011600017 19970116 00017 SW 1997 1 16 97ZZZX223 1 19961021 G 6230 206010336005 LINK IDLER BELL 206 206L1 1182107 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 206SL 45245 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10 1 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 690 HOURS. 1 G 7 1 3U H2SW 1997011600018 19970116 00018 SW 1997 1 16 97ZZZX224 1 19961113 G 6230 206010335001 LEVER ASSY BELL 206 206L3 1182108 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 350AL 361 51429 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D6 BOLTS, 1 EACH 206-010-470-10 1 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 360.5 HOURS. 1 G 7 1 3U H2SW 1997011600019 19970116 00019 SW 1997 1 16 97ZZZX225 1 19961113 G 6230 206010336005 LINK IDLER BELL 206 206L3 1182108 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 350AL 361 51429 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10 1 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 360.5 HOURS. 1 G 7 1 3U H2SW 1997011600020 19970116 00020 SW 1997 1 16 97ZZZX226 1 19961021 G 6230 206010335001 LEVER ASSY BELL 206 206L1 1182107 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 57334 548 45445 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10 1 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 548.2 HOURS. 1 G 7 1 3U H2SW 1997011600021 19970116 00021 SW 1997 1 16 97ZZZX227 1 19961021 G 6230 206010336005 LINK IDLER BELL 206 206L1 1182107 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 57334 548 45445 DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 S PACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-10 1 BEARING. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 548.2 HOURS. 1 G 7 1 3U H2SW 1997011600023 19970116 00023 NE 1997 1 16 97ZZZX229 1 19961104 G 6210 7615009100051A BLADE SKRSKY S76 S76A 8143006 NE M/R CRACKED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 1547N 13028 466 A08601369 760088 DURING 500 HOUR INSPECTION FOUND BLADE LEADING EDGE CRACKED AND SEPARATED AT RIGHT STATION 114 AND RIGHT STATION 154, LE ADING EDGE LOWER SURFACE DEBONDED AT RIGHT STANDARD 100, TRAILING EDGED CRACKED AT RIGHT STATION 62. 1 G 7 2 3U H1NE 1997010900116 19970109 00116 SO 1997 1 9 97ZZZX23 1 19961112 G 2740 2183103 BUSHING PIPER PA23 PA23250 7102308 SO STAB WORN D S A O OTHER E F VIBRATION/BUFFET FLT CONT AFFECTED DE DESCENT 1 GL 17 22TD 277854103 STABILATOR VIBRATION, FLUTTER IN DESCENT (AT HIGH SPEED) TRACED TO MOVEMENT IN ABOVE PIVOT JOINT. HOLE IN BLOCK, BUSHIN G, AND BOLT ALL SEVERELY WORN. PLAY IN JOINT NOT IMMEDIATELY EVIDENT BECAUSE OF SPRING LOADING ON BELLCRANK. RT SIDE N OT WORN. WEAR ALLOWS TAB TO MOVE AND FLUTTER, INDUCING MOVEMENT IN STAB. 1 L 7 2 3O 1A10 1997011600024 19970116 00024 NE 1997 1 16 97ZZZX230 1 19961023 G 6410 7610105101041 PADDLE SKRSKY S76 S76A 8143006 NE T/R DEBONDED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 1547N 8314 482 A13700670X 760088 DISCOVERED DURING 500 HOUR INSPECTION, T/R PADDLE 'A' TIP CAP DEBONDED. PADDLE 'B' PIVOT BEARING RETAINERS DEBONDED. 1 G 7 2 3U H1NE 1997011600025 19970116 00025 NE 1997 1 16 97ZZZX231 1 19960805 G 6210 7615009100051A BLADE SKRSKY S76 S76A 8143006 NE M/R DEBONDED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 1547N 13028 466 A08601369 760088 DURING 500 HOUR INSPECTION FOUND BLADE LEADING EDGE CRACKED AND DEBONDED AT RIGHT STA 114, AND STA 154. 1 G 7 2 3U H1NE 1997011600026 19970116 00026 SW 1997 1 16 97ZZZX232 1 19961021 G 6230 206010335001 LEVER ASSY 206010350021 BELL 206 206L4 1182110 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 171AL 293 52064 DAILY INSPECTION FOUND BEARINGS AND SPACERS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 SP ACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH NAS6605D64 BOLTS. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PA RTS TT 293.1 HOURS. 1 G 7 1 3U NC H2SW 1997011600027 19970116 00027 SW 1997 1 16 97ZZZX233 1 19961021 G 6230 206010335001 LEVER ASSY 206010350021 BELL 206 206L4 1182110 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 173AL 330 52066 DAILY INSPECTION FOUND BEARINGS AND SPACERS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 SP ACERS, 4 EACH 206010-337-001 BEARINGS, 2 EACH NAS6605D64 BOLTS. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PAR TS TT 330.3 HOURS. 1 G 7 1 3U NC H2SW 1997011600029 19970116 00029 SW 1997 1 16 97ZZZX235 1 19961021 G 6230 206010335001 LEVER ASSY 206010350021 BELL 206 206L4 1182110 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 175AL 310 52117 DAILY INSPECTION FOUND BEARINGS AND SPACERS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-01 SPA CERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH NAS6605D64 BOLTS. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PAR TS TT 310.3 HOURS. 1 G 7 1 3U NC H2SW 1997011600030 19970116 00030 SW 1997 1 16 97ZZZX236 1 19961107 G 6230 206010335001 LEVER ASSY 206010350021 BELL 206 206L1 1182107 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 2018R 390 45681 DAILY INSPECTION FOUND BEARINGS AND SPACERS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 SP ACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH NAS6605D64 BOLTS. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PA RTS TT 390.0 HOURS. 1 G 7 1 3U H2SW 1997052900292 19970529 00292 NE 1997 5 29 97ZZZX2374 2 19961211 G 7230 0292152880 COMPRESSOR SNIAS 350 AS350B1 8680811 EU TMECA ARRIEL ARRIEL1D NE ENGINE COVER BROKEN B VE3D K NONE E VIBRATION/BUFFET IN INSP/MAINT 1 WP 01 215LA 2965 2143 7157 ENGINE WAS PRODUCING AN ODD NOISE AND HAD A HIGH FREQUENCY VIBRATION. PREVIOUS VIBRATION CHECK WITH BRUEL AND KSAER VIB METER 64.4 HRS EARLIER WAS WITHIN LIMITS. INSPECTED COMPRESSOR WITH BORESCOPE THROUGH BLEED VALVE HOLE AND FOUND TAB O N CENTRIFUGAL COMPRESSOR COVER BROKE LOOSE AND WAS INGESTED BY IMPELLER CAUSING SIGNIFICANT DAMAGE. SL 1708/96/ARR/31 A DDRESSES THIS PROBLEM, BUT THE CHECKS CALL-OUT WAS NOT WHAT THIS ENGINE WAS EXPERIENCING. THE S/L SHOULD BE CHANGED TO REFLECT OTHER WAYS TO INSPECT FOR THIS PROBLEM. ALSO, PROCEDURES TO FIND IT BEFORE DAMAGE OCCURS. 1 G 7 1 3U 3 U H9EU E19EU 1997052900293 19970529 00293 NE 1997 5 29 97ZZZX2375 2 19961101 G 7412 9580115210 HE GENERATOR SNIAS 350 AS350B1 8680811 EU TMECA ARRIEL ARRIEL1D NE ENGINE IGNITER FAILED B VE3D K NONE O OTHER IN INSP/MAINT 1 WP 01 2127S 399 2213 7119 ACFT TT 5,043.8 HOURS. HELICOPTER FAILED TO START. AFTER TROUBLESHOOTING, FOUND BOTH IGNITERS DEFECTIVE AND H.E. GENER ATOR (EXECUTER BOX) INOPERATIVE. H.E. GENERATOR HAD 399.0 HRS SINCE NEW. PAPERWORK WAS SUBMITTED TO MANUFACTURE FOR WA RRANTY. 1 G 7 1 3U 3 U H9EU E19EU 1997011600032 19970116 00032 SW 1997 1 16 97ZZZX238 1 19961031 G 6210 206010200133 BLADE BELL 206 206B 1181511 SW M/R CORRODED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 2295F 2706 A863 3579 DURING DAILY INSPECTION, BLADE TIP BLOCK AND WEIGHT PACKAGE CORRODED CAUSING DEFORMATION OF SPAR AT TIP. 1 G 7 1 3U H2SW 1997010900117 19970109 00117 CE 1997 1 9 97ZZZX24 1 19961213 G 3211 0541153 U-BOLT CESSNA 182 182B 2072706 CE MLG CRACKED D A K NONE O OTHER IN INSP/MAINT 1 NM 11 2340G 3278 51640 DURING ANNUAL INSPECTION, THE MLG U-BOLT NUTS WERE CHECKED FOR SECURITY. THE REAR RIGHT U-BOLT NUT WAS FOUND TO BE LOOS E. SUBSEQUENT INSPECTION REVEALED A PRE-EXISTING CRACK HAD ALLOWED THE U-BOLT TO STRETCH. THE U-BOLT WAS FOUND TO BE CR ACKED APPROXIMATELY 60 PERCENT THROUGH THE DIAMETER OF THE BOLT. THE CRACK WAS LOCATED THREE THREADS FROM THE BOTTOM OF THE THREADED PORTION OF THE BOLT, AT THE BOTTOM OF THE NUT. 1 H 7 1 3O NT 3A13 1997011600035 19970116 00035 SW 1997 1 16 97ZZZX241 1 19961121 G 6210 206015001107 BLADE 206011100025 BELL 206 206L1 1182107 SW M/R TIP CORRODED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 2758L 2534 A1310 45266 ROUTINE INSPECTION FOUND CORROSION AT TIP OF BLADE. 1 G 7 1 3U H2SW 1997011600036 19970116 00036 SW 1997 1 16 97ZZZX242 1 19961113 G 6230 206010335001 LEVER ASSY 206010350021 BELL 206 206L1 1182107 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 3185P 487 45775 DAILY INSPECTION FOUND BEARINGS AND SPACERS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-10-338-001 SPA CERS, 4 EACH 206-010-337-001 BEARINGS. 2 EACH NAS6605D64 BOLTS. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PA RTS TT 486.9 HOURS. 1 G 7 1 3U H2SW 1997011600037 19970116 00037 SW 1997 1 16 97ZZZX243 1 19961107 G 6230 206010335001 LEVER ASSY 206010350021 BELL 206 206L1 1182107 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 3190P 475 45779 DAILY INSPECTION FOUND BEARINGS AND SPACERS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 SP ACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH NAS6605D64 BOLTS. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PA RTS TT 475.0 HOURS. 1 G 7 1 3U H2SW 1997011600038 19970116 00038 SW 1997 1 16 97ZZZX244 1 19961030 G 6210 206015001107 BLADE BELL 206 206L1 1182107 SW M/R CORRODED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 3190P 3394 A467 45779 DURING DAILY INSPECTION, FOUND M/R BLADE SPAR LEADING EDGE CORRODED BEYOND LIMITS. 1 G 7 1 3U H2SW 1997011600040 19970116 00040 SW 1997 1 16 97ZZZX246 1 19961107 G 6230 2060103335001 LEVER ASSY 206010350021 BELL 206 206L3 1182108 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 349AL 296 51388 DAILY INSPECTION FOUND BEARINGS AND SPACERS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 SP ACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH NAS6605D64 BOLTS. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PA RTS TT 295.8 HOURS. 1 G 7 1 3U H2SW 1997011600041 19970116 00041 SW 1997 1 16 97ZZZX247 1 19961110 G 6230 206010335001 LEVER ASSY 206010350021 BELL 206 206L3 1182108 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 355AL 285 51444 DAILY INSPECTION FOUND BEARINGS AND SPACERS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 SP ACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH NAS6605DC64 BOLTS. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN P ARTS TT 285.1 HOURS. 1 G 7 1 3U H2SW 1997011600042 19970116 00042 SW 1997 1 16 97ZZZX248 1 19961107 G 6230 206010335001 LEVER ASSY 206010350021 BELL 206 206L3 1182108 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 362AL 397 51471 DAILY INSPECTION FOUND BEARINGS AND SPACERS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 SP ACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH NAS6605D64 BOLTS. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PA RTS TT 396.6 HOURS. 1 G 7 1 3U H2SW 1997010900118 19970109 00118 SO 1997 1 9 97ZZZX25 2 19961218 G 8530 646032 RETAINER MOONEY M20 M20K 5870220 SW CONT O360 TSIO360LB 17025 SO CYL ROCKER ARM BROKEN D K NONE O OTHER IN INSP/MAINT 1 SO 09 1167H 1746 250689 FOUND 3 ROCKER ARM RETAINERS BROKEN AND 2 CRACKED DURING ANNUAL INSPECTION. PARTS HAD NOT COME LOOSE YET. 1 L 7 1 3O 3 O 2A3 E9CE 1997011600045 19970116 00045 SW 1997 1 16 97ZZZX251 1 19961107 G 6230 206010335001 LEVER ASSY 206010350021 BELL 206 206B 1181511 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 5008K 645 2524 DAILY INSPECTION FOUND BEARING AND SPACERS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 SPA CERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH NAS6605D64 BOLTS. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PAR TS TT 645.2 HOURS. 1 G 7 1 3U H2SW 1997011600048 19970116 00048 SW 1997 1 16 97ZZZX254 1 19961107 G 6230 206010335001 LEVER ASSY BELL 206 206L1 1182107 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 5750Y 395 45517 DAILY INSPECTION FOUND BEARINGS AND SPACERS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 SP ACERS, 4 EACH 206-010-337-001, 2 EACH NAS6605D64 BOLTS. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PARTS TT 39 5.0 HOURS. 1 G 7 1 3U H2SW 1997011600049 19970116 00049 SW 1997 1 16 97ZZZX255 1 19961021 G 6230 206010335001 LEVER ASSY 206010350021 BELL 206 206L1 1182107 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 5760A 451 45538 DAILY INSPECTION FOUND BEARINGS AND SPACERS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 SP ACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH NAS6605D64 BOLTS. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN PA RTS TT 450.7 HOURS. 1 G 7 1 3U H2SW 1997060500460 19970605 00460 GL 1997 6 5 97ZZZX2555 1 19960506 G 6230 28161191 UNIVERSAL HSNG ENSTRM F28 F28F 3300412 GL SWASHPLATE CRACKED C PP0M K NONE O OTHER AP APPROACH 1 WP 01 8626S 3710 1189788Y 786 MOUNTING WEBS FOR CONTROL ROD BEARINGS AND UNIVERSAL JOINT OF LOWER SWASHPLATE FOUND CRACKED AT INSPECTION. THIS IS A P RIMARY FLIGHT CONTROL PART. THIS PART HAS A RETIREMENT LIFE OF 17,700 HOURS. PART NON-REPAIRABLE. REPLACED WITH SERVI CEABLE PART 28-16119-1. 1 G 7 1 3O H1CE 1997011600050 19970116 00050 SW 1997 1 16 97ZZZX256 1 19961016 G 6310 206040221003 OUTER SHAFT 206040270003 BELL 206 206B 1181511 SW FREEWHEEL UNIT MAKING METAL B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 59541 1795 B129175 1412 FIELD REPORTED FREEWHEEL ASSEMBLY 'MAKING METAL'. FOUND ROLLER BEARING P/N 206-040-205-005 SPINNING IN OUTER SHAFT, GAL LING SHAFT I.D. MAKING METAL. 1 G 7 1 3U H2SW 1997011600051 19970116 00051 NE 1997 1 16 97ZZZX257 1 19961018 G 6210 7615009100049A BLADE SKRSKY S76 S76 8143010 NE M/R DEBONDED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 705AL 9749 421 A08600883 760267 DURING 500 HOUR INSPECTION FOUND UPPER SURFACE SKIN DEBONDED APPROXIMATELY 5 INCHES BY 6.50 INCHES AT RIGHT STA 53. SKI N CRACKED AT FORWARD EDGE OF TRIM TAB. 1 G 7 2 3U H1NE 1997011600052 19970116 00052 NE 1997 1 16 97ZZZX258 1 19961021 G 6210 7615009100049A BLADE SKRSKY S76 S76A 8143006 NE M/R DEBONDED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 712AL 6408 454 A08600858 760280 DURING 500 HOUR INSPECTION FOUND BLADE TIP RIB DEBONDED. 1 G 7 2 3U H1NE 1997060500486 19970605 00486 CE 1997 6 5 97ZZZX2582 1 19961030 G 7160 BA8101 GASKET BA8110 BBAVIA 8 8KCAB 2110612 CE INDUCTION AIR DETERIORATED D A K NONE O OTHER IN INSP/MAINT 1 WP 01 444PF 638 54379 UPON ANNUAL INSPECTION, THE INDUCTION AIR FILTER GASKET WAS FOUND DETERIORATED, LOOSE ON FILTER ASSY. BRACKET AD 96-09- 06 DOES NOT COVER THIS ASSY MODEL. SUGGEST INCLUDING MODEL IN AD AND/OR INSPECTING ALL BRACKET AIR FILTER ASSEMBLIES FO R AD 96-09-06 CONDITION. 1 H 7 1 3O A21CE 1997060500490 19970605 00490 CE 1997 6 5 97ZZZX2586 1 19960909 G 2820 S5110 HOSE CESSNA 208 208B 2073701 CE FUEL SUPPLY FAILED B A FE4R K NONE O OTHER IN INSP/MAINT 1 AL 03 746FX 250 208B0498 DURING COMPLIANCE OF CESSNA SB CAB 96-15 'FUEL HOSE INSPECTION-REPLACEMENT', FOUND ONE OF THE MAIN FUEL SUPPLY HOSES WAS DETERIORATED TO THE POINT THAT FUEL FLOW WAS RESTRICTED. SUBMITTER FEELS THIS CONDITION COULD LEAD TO AN ENGINE SHUT D OWN IN-FLIGHT. 1 H 7 1 3T A37CE 1997060500491 19970605 00491 CE 1997 6 5 97ZZZX2587 1 19960911 G 5553 BOLT CESSNA 208 208 2073702 CE VERT STAB ATTACH LOOSE B A FE4R K NONE O OTHER IN INSP/MAINT 1 AL 03 9617F 5513 20800107 INSPECTION FOUND VERTICAL STABILIZER ATTACH BOLTS LOOSE. SUBMITTER STATED THIS IS NOT THE FIRST OCCURRENCE ON 208 MODEL S SERVICED. 1 H 7 1 3T NT A37CE 1997011600053 19970116 00053 NE 1997 1 16 97ZZZX259 1 19961021 G 6210 7615009000049A BLADE SKRSKY S76 S76A 8143006 NE M/R CRACKED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 712AL 13691 454 A08600210 760280 DISCOVERED DURING 500 HOUR INSPECTION, FOUND BLADE SKIN CRACKED ALONG FORWARD EDGE OF TRIM TAB. 1 G 7 2 3U H1NE 1997060500496 19970605 00496 SO 1997 6 5 97ZZZX2592 2 19960704 G 8520 649130 CRANKSHAFT CESSNA 185 A185F 2072821 CE CONT O520 IO520D 17032 SO NR 3 CHEEK FAILURE D L A UNSCHED LANDING O OTHER CR CRUISE 1 AL 03 185CA 1449 1289007N 18504445 282598R IN-FLIGHT FAILURE OF CRANKSHAFT RESULTED IN FORCED LANDING. AIRCRAFT WAS DESTROYED. PILOT HAD REPORTED INCREASE IN OIL TEMPERATURE (NOT ABOVE RED LINE, BUT HIGHER THAN NORMAL). NO OTHER SYMPTOMS REPORTED, AND MAINTENANCE COULD NOT IDENTI FY A PROBLEM. ENGINE WAS TCU REMANUFACTURE WHICH HAD A USED CRANK INSTALLED. 1 H 7 1 3O 3 O 3A24 E5CE 1997010900119 19970109 00119 EA 1997 1 9 97ZZZX26 2 19961215 G 8530 SL134441 PISTON PIN PIPER PA44 PA44180 7104402 SO LYC O360 TO360E1A6 41514 EA NR 2 CYLINDER FAILED B MX3R C ABORTED TAKEOFF Y E K ENGINE STOPPAGE VIBRATION/BUFFET FLUID LOSS TO TAKEOFF 1 WP 11 8532Z 275 447995280 RL00013572T ENGINE FAILED ON TAKEOFF DUE TO BROKEN PISTON PIN IN NR 2 CYLINDER, RT ENGINE. ENGINE DESTROYED, BROKEN RODS AND CASES, ETC. RUINED CRANKSHAFT. SUSPECTED CAUSE, MANUFACTURER'S DEFECT. 1 L 7 2 3O 3 O A19S0 E26EA 1997011600054 19970116 00054 NE 1997 1 16 97ZZZX260 1 19960920 G 6210 7615009100049A BLADE SKRSKY S76 S76A 8143006 NE M/R DEBONDED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 768AL 10167 238 A08600881 760031 DURING DAILY INSPECTION, FOUND UPPER SURFACE SKIN DEBONDED APPROXIMATELY 20 INCHES BY 8.50 INCHES NEAR BLADE TIP. 1 G 7 2 3U H1NE 1997011600055 19970116 00055 EU 1997 1 16 97ZZZX261 1 19961018 G 5330 1053025158 SKIN 10530102 BOLKMS 105 BO105CBS 5626008 EU TAILBOOM CORRODED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 5412J 6451 S784 DAILY INSPECTION FOUND TAILBOOM HAS EXCESSIVE CORROSION AT CAMLOCK HOLES ON UPPER SKIN. 1 G 7 2 3U NC H3EU 1997011600161 19970116 00161 CE 1997 1 16 97ZZZX265 1 19961202 G 2822 503801775 PUMP AIRBORNE BEECH 200 B200 1152922 CE NAC TANK DEFECTIVE B L DINR K NONE O OTHER IN INSP/MAINT 1 EA 17 260G 99 5AL78 BB1525 INVESTIGATION FOR DEFECTIVE STANDBY FUEL PUMP FOUND OVERSIZE VANES IN PUMP STICKING. PUMP OK WHEN NEW, BUT VANES SWELL UP WHEN IN JET FUEL. SUGGEST TO ORDER NEW PUMPS FROM BATCH S/N 8AMXXX, AND 9AMXXX. 1 L 7 2 4T A24CE 1997061200145 19970612 00145 CE 1997 6 12 97ZZZX2657 1 19960505 G 5531 07310331 RIB CESSNA 185 A185F 2072821 CE VERTICAL STAB CORRODED D K NONE O OTHER IN INSP/MAINT 1 NM 13 6964N 2400 18504318 DURING ANNUAL INSPECTION OF AIRCRAFT, FOUND CORROSION ON RIB AT BASE OF VERTICAL STABILIZER. FORWARD 6 INCHES OF RIB WA S COMPLETELY DELAMINATED. AIRCRAFT HAD BEEN ON FLOATS IN SALT WATER ENVIRONMENT. REST OF AIRCRAFT IN GOOD CONDITION. 1 H 7 1 3O 3A24 1997011600162 19970116 00162 CE 1997 1 16 97ZZZX266 1 19961202 G 2822 503801775 PUMP AIRBORNE BEECH 200 B200 1152922 CE NAC TANK DEFECTIVE B A DINR K NONE O OTHER IN INSP/MAINT 1 EA 17 260G 99 10AL102 BB1525 INVESTIGATION FOR DEFECTIVE STANDBY FUEL PUMP FOUND OVERSIZE VANES IN PUMP STICKING. PUMP OK WHEN NEW, BUT VANES SWELL UP WHEN IN JET FUEL. SUGGEST TO ORDER NEW PUMPS FROM BATCH S/N 8AMXXX, AND 9AMXXX. 1 L 7 2 4T A24CE 1997011600163 19970116 00163 EU 1997 1 16 97ZZZX267 2 19961223 G 7321 5225126 JUMP RATE ASSY WOODWARD 8063215 CFMINT CFM56 CFM563C 13802 EU ORIFICE PLATE DISBONDED B UU2D K NONE O OTHER IN INSP/MAINT 1 GL 03 85913 TWO FUEL CONTROLS WERE RECENTLY REJECTED DURING THE BOEING FLIGHT TEST DUE TO A REPORTED PROBLEM OF FLAMEOUT DURING TAXI . SUBSEQUENT INVESTIGATION AT WOODWARD REVEALED A DISBONDED JUMP AND RATE ORIFICE. THE ABSENCE OF A RATE ORIFICE RESUL TS IN A MUCH MORE RAPID TRANSITION TO THE DECELERATION SCHEDULE THAN DESIRED. THE CHARACTERISTICS OF THE DISBONDMENT IN DICATED THAT ONE SURFACE OF THE JOINT DID NOT ADHERE; MOST LIKELY DUE TO INADEQUATE CLEANING OR RECONTAMINATION AFTER CL EANING. GEAE IS PUBLISHING A SERVICE BULLETIN RECOMMENDING IMMEDIATE REPLACMENT OF THE SUSPECT HARDWARE. 4 F E21EU 1997061200160 19970612 00160 SW 1997 6 12 97ZZZX2672 1 19961011 G 6310 214040841101 SEAL BELL 206 206L4 1182110 SW T/R OUTPUT DRIVE LEAKING D K NONE K FLUID LOSS IN INSP/MAINT 1 GL 03 696BA 52166 REPLACED FREE WHEELING UNIT TAIL ROTOR OUTPUT DRIVE SEAL DUE TO LEAKING OIL. 1 G 7 1 3U NC H2SW 1997011600164 19970116 00164 EU 1997 1 16 97ZZZX268 2 19961223 G 7321 5225126 JUMP RATE ASSY WOODWARD 8063215 CFMINT CFM56 CFM563C 13802 EU ORIFICE PLATE DISBONDED B UU2D K NONE O OTHER IN INSP/MAINT 1 GL 03 85782 TWO FUEL CONTROLS WERE RECENTLY REJECTED DURING THE BOEING FLIGHT TEST DUE TO A REPORTED PROBLEM OF FLAMEOUT DURING TAXI . SUBSEQUENT INVESTIGATION AT WOODWARD REVEALED A DISBONDED JUMP AND RATE ORIFICE. THE ABSENCE OF A RATE ORIFICE RESUL TS IN A MUCH MORE RAPID TRANSITION TO THE DECELERATION SCHEDULE THAN DESIRED. THE CHARACTERISTICS OF THE DISBONDMENT IN DICATED THAT ONE SURFACE OF THE JOINT DID NOT ADHERE; MOST LIKELY DUE TO INADEQUATE CLEANING OR RECONTAMINATION AFTER CL EANING. GEAE IS PUBLISHING A SERVICE BULLETIN RECOMMENDING IMMEDIATE REPLACMENT OF THE SUSPECT HARDWARE. 4 F E21EU 1997011600165 19970116 00165 NE 1997 1 16 97ZZZX269 2 19961214 G 7420 5306721 LEAD CESSNA 500 S550 2076607 CE PWA JT15 JT15D4 52112 NE LT ENG IGNITER DEFECTIVE B CWQR K NONE O OTHER IN INSP/MAINT 1 GL 05 101QS 7705 S5500101 PCE102267 DURING INSPECTION, LEFT ENGINE OUTBOARD IGNITER WOULD NOT OPS CHECK. FOUND IGNITION CABLE DEFECTIVE DUE TO AN INTERNAL FAULT. COULD NOT DETERMINE CAUSE AS EXTERNAL INSPECTION OF IGNITION CABLE APPEARED SERVICEABLE. 1 L 7 2 4F 4 F RT A22CE E1NE 1997010900120 19970109 00120 SO 1997 1 9 97ZZZX27 1 19961125 G 2410 BRACKET PIPER PA28 PA28160 7102806 SO ALT BELT ADJ CRACKED D A K NONE O OTHER IN INSP/MAINT 1 NE 03 5JN 281528 ALTERNATOR BRACKET CITED IS ONE HAVING ELONGATED HOLE FOR ADJUSTING BELT TENSION. THE CRACK LOCATION WAS AT THE ENGINE SIDE OF THE BRACKET, AND CRACKED COMPLETELY THROUGH. NO REPAIR OTHER THAN REPLACEMENT. 1 L 7 1 3O 2A13 1997011600166 19970116 00166 CE 1997 1 16 97ZZZX270 1 19961231 G 2197 13H37A1 WIRE CESSNA 501 501 2076603 CE AFT CABIN A/C MELTED D K NONE B W SMOKE/FUMES/ODORS/SPARKS INADEQUATE Q C NR NOT REPORTED 1 CE 03 70CG 5010187 PILOT REPORTED SMELL IN CABIN WITH AIR CONDITIONER ON. FOUND MAIN POWER WIRE TO MOTOR FROM CURRENT LIMITER MELTED CAUSE D BY THE REQUIRED LIMITER OF 150 AMP BEING REPLACED WITH A 175 AMP LIMITER. COMPRESSOR ASSY REPLACED 3-27-96 BY CESSNA TELEDO SERVICE CENTER. AFT EVAPORATION BLOWER REPLACED 6-30-95 BY GREENSBORO CESSNA SERVICE CENTER. 1 L 7 2 4F A27CE 1997061200779 19970612 00779 GL 1997 6 12 97ZZZX2707 2 19961108 G 7250 23009630 THRUST PLATE ALLSN 250C 250C20B 03013 GL NR 8 BEARING WORN B YKER K NONE O OTHER IN INSP/MAINT 1 EA 17 TURBINE WAS GENERATING METAL. FOUND THE BEARING CLAMPING SURFACE OF THE THRUST PLATE WORN DUE TO SPINNING OF THE NR 8 B EARING OUTER RACE. FRETTING ON THE OPPOSITE SIDE OF THE THRUST PLATE INDICATED THERE MAY HAVE BEEN INSUFFICIENT TORQUE ON THE NR 8 BEARING SUMP NUT. 3 U E4CE 1997061200786 19970612 00786 EU 1997 6 12 97ZZZX2714 1 19960910 G 2742 5435021 ACTUATOR LEARSIEGLER ISRAEL 1124 1124 4500102 EU HORZ STAB TRIM BROKEN B L A QU2R K NONE O OTHER IN INSP/MAINT 1 EA 17 87NS 2005 708208AA 432 UPON INSPECTION FOUND LEFT HAND JACK SCREW ON PITCH TRIM ACTUATOR S/N 7082-08AA BROKEN. HIGH CYCLES AND HEAVY USE OF TH RUST REVERSERS CAUSE VIBRATION IN THE TAIL WHICH COULD HAVE RESULTED IN THIS FAILURE. INSTALLED 4-3-86. LANDINGS SOH, 3,457. 2 M 7 2 4F A2SW 1997061200787 19970612 00787 EU 1997 6 12 97ZZZX2715 1 19960911 G 2742 5435021 ACTUATOR LEARSIEGLER ISRAEL 1124 1124 4500102 EU HORZ STAB TRIM BROKEN B L A QU2R K NONE O OTHER IN INSP/MAINT 1 EA 17 317MQ 4123 077800AA 421 THE BROKEN STABILIZER JACK SCREW WAS FOUND DURING A 400-HOUR AIRFRAME INSPECTION. ISRAEL AIRCRAFT IND RELEASED A MANDAT ORY SB RECENTLY TO INSPECT COMPONENTS WITHIN 50 HOURS OR AT THE NEXT INSPECTION. SUBMITTER'S CONCERN IS THE METHOD THAT IS USED TO DETECT A DISCREPANCY IS NOT THOROUGH ENOUGH, AND SOME OPERATORS WILL NOT COMPLY UNLESS IT IS AN AD. THIS CO MPONENT SHOULD BE LIFE LIMITED AND INSPECTED USING NON-DESTRUCTIVE TESTING. 2 M 7 2 4F A2SW 1997011600170 19970116 00170 EA 1997 1 16 97ZZZX274 2 19961218 G 8530 76189 CYLINDER GULSTM 500 500B 0141106 SW LYC O540 IO540E1A5 41532 EA NR 6 CRACKED E O OTHER J K WARNING INDICATION FLUID LOSS NR NOT REPORTED 1 SW 15 315TG 1239 1460163 L1459348 PILOT REPORTED DROPPING CHT ON LEFT ENGINE. POST-FLIGHT REPORTED LARGE OIL LEAK. FOUND NR 6 CYLINDER HAD A CRACK THROU GH UPPER BASE FLANGE. FORWARD THREE CYLINDER HOLD DOWN STUDS WERE BROKEN. THIS CYLINDER WAS PURCHASED NEW FROM LYCOMIN G AT OVERHAUL. STUDS AND CYLINDER WERE REPLACED AND AIRCRAFT WAS RELEASED. 1 H 7 2 3O 3 O 6A1 1E4 1997011600173 19970116 00173 SO 1997 1 16 97ZZZX277 1 19961221 G 8011 EBB75A BENDIX DRIVE MZ4206 PIPER PA24 PA24250 7102404 SO LYC O540 O540A1B5 41532 EA STARTER EXCESS WORN D K NONE O OTHER IN INSP/MAINT 1 SW 05 5259P 83800483 24293 L612440 FOUND STARTER BENDIX DRIVE NOT ENGAGING THE RING GEAR ASSEMBLY WITH THE BENDIX GEAR TEETH TORN OFF ABOUT 50 PERCENT, AND THE END BRONZE BUSHING EATEN UP. ALSO, DAMAGE TO THE TEETH OF THE RING GEAR. THE STARTER COMMUTATOR SHOWS IT WAS FRES HLY POLISHED WITH GOOD BRUSHES; THE GEARBOX WAS FRESHLY PACKED WITH GREASE. THIS ENGINE HAD BEEN OVEHAULED WITHIN THE P AST YEAR. 1 L 7 1 3O 3 O 1A15 E295 1997061200843 19970612 00843 GL 1997 6 12 97ZZZX2770 1 19960506 G 6230 28161191 UNIVERSAL HSNG ENSTRM F28 F28F 3300412 GL SWASHPLATE CRACKED C A PP0M K NONE O OTHER IN INSP/MAINT 1 WP 01 8626S 3710 1189788H 786 MOUNTING WEBS FOR CONTROL ROD BEARINGS AND UNIVERSAL JOINT OF LOWER SWASHPLATE FOUND CRACKED AT INSPECTION. THIS IS A P RIMARY FLIGHT CONTROL PART. THIS PART HAS A RETIREMENT LIFE OF 17,700 HOURS. PART NON-REPAIRABLE. REPLACED WITH SERVI CEABLE PART 28-16119-1. 1 G 7 1 3O H1CE 1997011600174 19970116 00174 SO 1997 1 16 97ZZZX278 1 19960911 G 2434 4111810 ALTERNATOR PIPER PA28 PA28RT201 7102818 SO BATTERY LUG DEFECTIVE B BJFR K NONE O OTHER IN INSP/MAINT 1 EA 23 8108M 95 5091990 28R8018006 ALTERNATOR FALLING APART AFTER 95 HRS IN SERVICE. PART OVERHAULED BY ELECTROSYSTEMS. CERTIFICATE NR UT2R226L. 1 L 7 1 3O 2A13 1997011600175 19970116 00175 SO 1997 1 16 97ZZZX279 1 19960821 G 2434 ALU8421 ALTERNATOR PIPER PA23 PA23250 7102308 SO BRUSH BLOCK FAILED B UKJR O OTHER J WARNING INDICATION NR NOT REPORTED 1 EA 23 27CY 37 A6960101 277654118 PILOT REPORTED LT ALTERNATOR LIGHT FLICKERED DURING TURBULENCE. LIGHT CAME ON STEADY ON THE WAY TO MAINTENANCE. REMOVE D ALTERNATOR, HEARD SOMETHING RATTLING INSIDE. REMOVED COOLING SHROUD AND FOUND ONE BRUSH INSIDE. REMOVED BRUSH BLOCK AND FOUND A PIECE OF IT AROUND THE BRUSH HAD BROKEN AWAY. REPLACED ALTERNATOR WITH O/H UNIT, OPS CK NORMAL. 1 L 7 2 3O 1A10 1997010900121 19970109 00121 SO 1997 1 9 97ZZZX28 1 19961117 G 3250 9506128 CHANNEL PIPER PA34 PA34220T 7103420 SO NLG CRACKED E A A UNSCHED LANDING O OTHER CL CLIMB 1 EA 05 8381M 5310 348133086 PILOT NOTED A LOUD BANG IN NOSE GEAR AS HE TAXIED ONTO RUNWAY FOR TAKEOFF. AFTER TAKEOFF, HE NOTICED THE NOSE WHEEL WAS TURNED 90 DEGREES TO THE AIRCRAFT. PILOT DID NOT RETRACT LANDING GEAR. AFTER LANDING, WAS UNABLE TO STEER AIRCRAFT. S TEERING CHANNEL WAS CRACKED BOTH SIDES AT AFT END. CRACKS ALLOWED THE NOSE GEAR STEERING BALL TO EXIT THE CHANNEL. 1 L 7 2 3O A7SO 1997061900383 19970619 00383 EU 1997 6 19 97ZZZX2826 1 19960609 G 6520 350A33215300 LAMINATE HINGE SNIAS 350 AS350B 8680801 EU T/R CRACKED B FF6R K NONE O OTHER IN INSP/MAINT 1 NM 11 911NT 139 1556 RUBBER LAMINATE IS CRACKED 360 DEGREES AROUND PART. 1 G 7 1 3U H9EU 1997061900461 19970619 00461 GL 1997 6 19 97ZZZX2833 1 19960514 G 5720 V61 BLOCK AMTR EAGLE CHRISEAGLE2 GL OUTER WING SYS FAILED H A K NONE O OTHER IN INSP/MAINT 1 SW 99 2FOR AUS - DURING INVESTIGATION OF A WRINKLE IN THE FABRIC COVERING ON THE TOP WING (INBOARD) TRAILING EDGE, THE DRAG/ANTI-DR AG WIRE REAR ATTACHMENT BLOCK AT REAR SPAR WAS FOUND BROKEN WHICH, IN TURN, CAUSED THE TRAILING EDGE TO CENTRE HOOP ATTA CHMENT BLOCK TO FAIL. 1 Q 7 1 3O EXPA1Q71 1997010900122 19970109 00122 SW 1997 1 9 97ZZZX29 1 19961211 G 7810 30503502 MOUNT TUBE 300MISSLE MOONEY M20 M20J 5870219 SW MUFFLER MOUNT BROKEN TAB H A K NONE O OTHER IN INSP/MAINT 1 EA 05 9932S 3000024 241096 DURING ANNUAL INSPECTION, FOUND RT HAND FORWARD EXHAUST MUFFLER SUPPORT TUBE BROKEN AT LOWER ATTACH TAB. THIS TUBE ASSY IS THE SAME ONE USED ON ROCKET ENGINEERING 305 - ROCKET CONVERSION ON M20K SERIES MOONEY. THIS TUBE IS OF THE NEWER HE AVY DUTY TYPE DESIGN THAT DOES NOT REQUIRE A REPETATIVE INSPECTION AS OUTLINED IN ROCKER M5B 95-305-01, OR AD 95-17-06 F OR THE M20K CONVERTED TO ROCKET 305. SUBMITTER RECOMMENDS INCREASED INSPECTION OF THESE MOUNTS ANY TIME LOWER COWLING I S REMOVED, UNTIL IT IS DETERMINED IF THIS WILL BE A RECURRING PROBLEM ON THE M20J - 300 MISSLE CONVERSION. 1 L 7 1 3O 2A3 1997010900096 19970109 00096 CE 1997 1 9 97ZZZX3 1 19961220 G 3231 08411066 BELLCRANK CESSNA 421 421B 2076014 CE RT MLG DOOR BROKEN D S O OTHER O OTHER NR NOT REPORTED 1 GL 27 100DG 421B0905 AFTER LANDING THE A/C, THE PILOT NOTICED THAT THE RT IB MLG DOOR WAS NOT CLOSED. AFTER INSPECTION OF THE AIRCRAFT, THE MAIN GEAR DOOR IDLER BELLCRANK WAS FOUND BROKEN. NO OTHER DAMAGE TO THE RETRACTION LINKAGE WAS NOTED. IF THIS PROBLEM HAD NOT BEEN NOTICED BY THE PILOT, IT WOULD HAVE CAUSED THE GEAR TO BIND AND JAM AGAINST THE DOOR AND POSSIBLY NOT ALLOW THE GEAR TO EXTEND. AIRFRAME TOTAL KNOWN TIME 3,300 PLUS HOURS. 1 L 7 2 3O A7CE 1997010900123 19970109 00123 CE 1997 1 9 97ZZZX30 1 19961213 G 3610 1989001 VALVE DUKES CESSNA 525 525 2076601 CE RT WING ANTI-ICE CRACKED D K NONE O OTHER IN INSP/MAINT 1 CE 07 229CJ 370 289 5250129 AIRCRAFT HAD NO BLEED AIR TO RIGHT WING FOR ANTI-ICE PROTECTION. FOUND SEVERAL BROKEN WELDS AT GUSSETS HOLDING STATIONA RY PART OF VALVE CAUSING VALVE TO MOVE, AND NOT ALLOWING THE CHECK PORTION OF VALVE TO OPEN ALLOWING BLEED AIR TO THE AN TI-ICE WING VALVE. 1 L 7 2 4F RT A1WI 1997071000268 19970710 00268 EU 1997 7 10 97ZZZX3034 1 19961217 G 3222 200876004 STRUT BAG BAE146 BAE146200A 1500266 EU NLG CRACKED B S LVTR K NONE O OTHER IN INSP/MAINT 1 WP 01 178US DRG261983 E2040 WHILE PERFORMING A RETURN-TO-SERVICE INSPECTION ON THE AIRCRAFT, A 4 INCH LONG CRACK WAS FOUND IN THE NLG STRUT. THE CR ACK WAS LOCATED APPROXIMATELY 8 INCHES BELOW TOP END OF STRUT. TOTAL PART TIME: 8,840 HOURS, TOTAL PART CYCLES: 9,105 . AIRCRAFT HAD BEEN IN STORAGE APPROXIMATELY 6 YEARS. 2 H 7 4 4F RT A49EU 1997071700105 19970717 00105 CE 1997 7 17 97ZZZX3068 1 19960606 G 2133 45AS630199 VALVE BEECH MU300 400A 1155402 CE PRESS REG SOV FAILED D O OTHER J WARNING INDICATION NR NOT REPORTED 1 WP 01 8167Y 101 RK67 PILOT REPORTED LOSS OF PRESSURIZATION ACCOMPANIED BY NIL AIRFLOW INTO CABIN. PILOT SELECTED EMERGENCY PRESSURIZATION. A IRFLOW INTO CABIN SUPPLIED BY EMERGENCY SYSTEM AND PRESSURIZATION CONTROL RESTORED. 2 H 7 2 4F RT A16SW 1997071700106 19970717 00106 SO 1997 7 17 97ZZZX3069 1 19960111 G 5346 1159BM20518XX FITTING GULSTM G1159 G1159B 3953535 SO RT ENG STRUT CORRODED B S C9FR K NONE O OTHER IN INSP/MAINT 1 WP 01 8490P 10974 004 DURING PROCESS OF REMOVING RT THRUST STRUT FOR NDT, DISCOVERED SEVERE INTERGRANULAR CORROSION AT AFT/UPPER THRUST STRUT/ FUSELAGE ATTACH FITITNG, PN 1159BM20518-XX. BRACKET IS LOCATED IN PYLON. AREA AFFECTED SURROUNDS STRUT ATTACH BOLT/BUS H BRACKET LOCATION, RT PYLON FS 584. AFFECTED AREA IS COVERED BY BOLT SAFETY BRACKET, AND SURROUNDING STRUCTURE, DUCTIN G, DIRT, ETC., MAKING INSPECTION DIFFICULT. SUGGEST PAYING SPECIAL ATTENTION TO THIS AREA BY REMOVING RETAINING BOLT AN D BUSHING TO INSPECT FOR CORROSION AT ATTACH LUGS. 2 L 7 2 4F RT A12EA 1997011600380 19970116 00380 SW 1997 1 16 97ZZZX307 1 19961107 G 6230 206010335001 LEVER ASSY BELL 206 206L1 1182107 SW PYLON WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 27483 454 45230 DAILY INSPECTION FOUND BEARINGS AND SPACERS WORN BEYOND LIMITS. PARTS REQUIRING REPLACEMENT: 4 EACH 206-010-338-001 SP ACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH NAS6605DC64 BOLTS. NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON. WORN P ARTS TT 453.5. 1 G 7 1 3U H2SW 1997011600381 19970116 00381 NE 1997 1 16 97ZZZX308 1 19961014 G 6210 802324 SCREWS SKRSKY S76 S76 8143010 NE TIP CAP DEFECTIVE B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 707AL A08602256 760189 DURING 500 HR INSPECTION OF BLADES AS SCREWS WERE BEING INSTALLED TORQUE VALUE WAS REACHED WITH ONLY APPROXIMATELY ONE-T HIRD THREAD ENGAGEMENT OF ENTIRE GRIP LENGTH. DISTORTED THREADS IN ONE AXIAL LOCATION ALONG GRIP LENGTH. 1 G 7 2 3U H1NE 1997011600382 19970116 00382 NE 1997 1 16 97ZZZX309 1 19961014 G 6210 802324 SCREWS SKRSKY S76 S76 8143010 NE TIP CAP DEFECTIVE B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 707AL A08602211 760189 DURING 500 HR INSPECTION OF BLADES AS SCREWS WERE BEING INSTALLED TORQUE VALUE WAS REACHED WITH ONLY APPROXIMATELY ONE-T HIRD THREAD ENGAGEMENT OF ENTIRE GRIP LENGTH. DISTORTED THREADS IN ONE AXIAL LOCATION ALONG GRIP LENGTH. 1 G 7 2 3U H1NE 1997011600383 19970116 00383 NE 1997 1 16 97ZZZX310 1 19961014 G 6210 802324 SCREWS SKRSKY S76 S76 8143010 NE TIP CAP DEFECTIVE B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 707AL A08601362 760189 DURING 500 HR INSPECTION OF BLADES AS SCREWS WERE BEING INSTALLED TORQUE VALUE WAS REACHED WITH ONLY APPROXIMATELY ONE-T HIRD THREAD ENGAGEMENT OF ENTIRE GRIP LENGTH. DISTORTED THREADS IN ONE AXIAL LOCATION ALONG GRIP LENGTH. 1 G 7 2 3U H1NE 1997011600384 19970116 00384 NE 1997 1 16 97ZZZX311 1 19961014 G 6210 802324 SCREWS SKRSKY S76 S76 8143010 NE TIP CAP DEFECTIVE B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 707AL A08600684 760189 DURING 500 HR INSPECTION OF BLADES AS SCREWS WERE BEING INSTALLED TORQUE VALUE WAS REACHED WITH ONLY APPROXIMATELY ONE-T HIRD THREAD ENGAGEMENT OF ENTIRE GRIP LENGTH. DISTORTED THREADS IN ONE AXIAL LOCATION ALONG GRIP LENGTH. 1 G 7 2 3U H1NE 1997011600839 19970116 00839 SW 1997 1 16 97ZZZX346 1 19961114 G 6210 206011119101 BOLT NUT 20601110021 BELL 206 206B 1181511 SW M/R BLADE MISMANUFACTURED B A ENRR K NONE W INADEQUATE Q C IN INSP/MAINT 1 AL 03 301MH RILM11682 2371 PURCHASE NEW MAIN ROTOR BLADE NUT FROM BELL SERVICE CENTER. DURING INSTALLATION, IT BECAME EVIDENT THAT THREADED BORE O F NUT WAS NOT PERPENDICULAR TO BEARING FACE OF NUT. TORQUING NUT TO REQUIRED 215 FOOT/POUND WOULD PUT EXTREME STRESS LO ADS ON NUT AND HOLLOW BOLT POSSIBLY RESULTING IN FAILURE OF PARTS AND CATASTROPHIC FAILURE OF AIRCRAFT. 1 G 7 1 3U H2SW 1997080700342 19970807 00342 EA 1997 8 7 97ZZZX3468 2 19960926 G 8520 10321700 BOLT PARKERHANFIN 40124 PIPER PA60 PA60700P 7106023 NM LYC O540 LTIO540U2A 41533 EA CYL NR 6 CRACKED D K NONE O OTHER IN INSP/MAINT 1 WP 23 6907A 787 82 608423022 L293468A DURING ENGINE INSPECTION, FOUND NR 6 CYLINDER STUD AND CASE THROUGH-BOLT CRACKED. 1 M 7 2 3O 3 O RT A17WE E14EA 1997011600840 19970116 00840 NE 1997 1 16 97ZZZX347 2 19961215 G 7323 116085025 GOVERNOR KAMAN K1200 K1200 05625F6 SW LYC T53 T5317A 41549 NE ENGINE FAILED D O A OTHER UNSCHED LANDING J WARNING INDICATION EX EXTERNAL LOAD 1 NM 09 311KA 630 5ADY1950 A940017 LE81016 OVERSPEED GOVERNOR FAILED. PILOT WAS FORCED TO JETTISON LONG LINE, HOOKS, AND LOGS. PILOT AUTOROTATED TOWARDS SERVICE LANDING, WENT T EMERGENCY GOVERNOR SETTING, AND LANDED WITH POWER. NO DAMAGE WAS SUSTAINED. ENGINE BEING REPAIRED BY ALLIED SIGNAL. 1 G 7 1 4F 4 U NT TR7BO E17EA 1997011600841 19970116 00841 NE 1997 1 16 97ZZZX348 2 19961201 G 7230 430109102 BEARING LYC LTS101 LTS101650B1 41560 NE NR 2 DAMAGED B YKER K NONE O OTHER IN INSP/MAINT 1 EA 17 LE45068 ENGINE REPORTEDLY MADE UNUSUAL NOISE FOLLOWED BY CHIP LIGHT DURING ENGINE START. DISASSEMBLED, AND FOUND SEVERELY DAMAG ED NR 2 BEARING, PN 4-301-091-02, AND NR 3 BEARING. ALSO, FOUND PT ROTOR BLADES SHIFTED (WITHIN LIMITS), HEAVY RUB ON P T ROTOR BLADE TIPS AND SEAL KNIVES, AND ON GAS GENERATOR ROTOR AND AXIAL ROTOR BLADE TIPS. SUBMITTER SUSPECTS PT ROTOR SHIFTED FORWARD DURING START, UNLOADING THE NR 3 BEARING AND ALLOWING EXCESSIVE RADIAL MOVEMENT OF PT ROTOR. 3 U E5NE 1997080700358 19970807 00358 CE 1997 8 7 97ZZZX3484 1 19961202 G 3213 50450182 WASHER CESSNA 421 421C 2076016 CE MLG SCISSORS FAILED D A O OTHER O OTHER LD LANDING 1 WP 03 234CN 421C0404 ON LANDING ROLL-OUT, RT MAIN LANDING GEAR ROTATED 90 DEGREES AND BACK AGAIN. INVESTIGATION FOUND MAIN GEAR SCISSOR CEN TER BOLT AND BUSHING RETAINING WASHER FAILED AND ALLOWED BUSHING TO 'WALK' AND SCISSOR TO DISCONNECT, ALLOWING TIRE TO R OTATE. NEW P/N S1450-5H12-063 WASHERS ARE TWICE AS THICK AS THE OLD ONES. IF OLD THINNER P/N 5045018-2 ARE WORN, THEY WOULD BE REPLACED WITH NEWER. 1 L 7 2 3O A7CE 1997011600843 19970116 00843 WP 1997 1 16 97ZZZX350 2 19961106 G 7200 ENGINE LEAR 35 35A 5170602 CE GARRTT TFE731 TFE73122B 01518 WP LT ENG FAILED D E ENGINE SHUTDOWN J WARNING INDICATION NR NOT REPORTED 1 GL 07 27TT 12820 2864 0122 P74505 LEFT ENG TEMPS WENT UP AND ENG STARTED MAKING NOISE, SHUT DOWN ENG. REMOVED AND REPLACED ENG. CAUSE UNKNOWN AT THIS TI ME. 2 L 7 2 4F 4 F A10CE E6WE 1997011600844 19970116 00844 CE 1997 1 16 97ZZZX351 1 19961130 G 2430 BD161 CONNECTOR CESSNA 500 S550 2076607 CE BATTERY MELTED B CWQR K NONE O OTHER IN INSP/MAINT 1 GL 05 299QS S5500099 DURING INSPECTION, FOUND BATTERY CONNECTOR CORRODED AND MELTED. CAUSE IS BELIEVED TO BE EXCESSIVE LOOSENESS OF PLUGS. C LOSELY INSPECTED BATTERY CONNECTOR FOR CONDITION AND LOOSENESS. 1 L 7 2 4F RT A22CE 1997011600845 19970116 00845 SW 1997 1 16 97ZZZX352 1 19961130 G 5220 NAS623211 SCREW CESSNA 500 560CESSNA 2076750 CE EXIT HANDLE BROKEN B A CWQR K NONE O OTHER IN INSP/MAINT 1 GL 05 36H 3235 3235 5600035 DURING PRE-PURCHASE INSPECTION FOUND EMERGENCY EXIT HANDLE ATTACH SCREW BROKEN AT THE SCREW THREADS. THE LOWER PART OF SCREW WITH NUT WAS MISSING. APPEARED TO BE AN INCORRECT SCREW INSTALLED. 2 L 7 2 4F RT A22CE 1997011600846 19970116 00846 CE 1997 1 16 97ZZZX353 1 19961214 G 3010 1106P55 SWITCH CESSNA 500 550 2076604 CE DE-ICE BOOT FAILED B CWQR K NONE O OTHER NR NOT REPORTED 1 GL 05 6862Q 9148 3761 5500265 FLIGHT CREW REPORTED NO 'SURFACE DE-ICE' LIGHT WHEN DE-ICE BOOTS INFLATED. DETERMINED WING AND TAIL DE-ICE BOOT PRESSUR E SWITCHES DEFECTIVE, MOST LIKELY DUE TO WATER CONTAMINATION. SUBMITTER SUGGESTS SWITCHES NEED TO BE INSTALLED IN A POS ITION THAT WILL LIMIT WATER ACCESS. 1 L 7 2 4F A22CE 1997011600847 19970116 00847 CE 1997 1 16 97ZZZX354 1 19961214 G 3010 1106P55 SWITCH CESSNA 500 550 2076604 CE DE-ICE BOOT FAILED B CWQR K NONE O OTHER NR NOT REPORTED 1 GL 05 6862Q 1178 1178 5500265 FLIGHT CREW REPORTED NO 'SURFACE DE-ICE' LIGHT WHEN DE-ICE BOOTS INFLATED. DETERMINED WING AND TAIL DE-ICE BOOT PRESSUR E SWITCHES DEFECTIVE, MOST LIKELY DUE TO WATER CONTAMINATION. SUBMITTER SUGGESTS SWITCHES NEED TO BE INSTALLED IN A POS ITION THAT WILL LIMIT WATER ACCESS. 1 L 7 2 4F A22CE 1997011600848 19970116 00848 CE 1997 1 16 97ZZZX355 1 19961118 G 3830 1700079 TANK 17000017 CESSNA 500 S550 2076607 CE AFT CABIN LEAKING B CWQR K NONE K FLUID LOSS IN INSP/MAINT 1 GL 05 86QS 7804 S5500086 DURING AIRCRAFT CLEANING, FOUND AIRCRAFT TOILET LEAKING. FOUND TANK UNIT LEAKING FROM IMPROPER REPAIR. TOILET MAINTENA NCE MANUAL DOES NOT PERMIT SEALING OF THE TANK UNIT. TANK UNIT SHOULD BE REPLACED IF FOUND LEAKING DUE TO THE VERY REAL CORROSION PROBLEM FOUND IN THE BELLIES OF S550 AIRCRAFT. 1 L 7 2 4F RT A22CE 1997011600850 19970116 00850 CE 1997 1 16 97ZZZX356 1 19961217 G 3240 AN8374D ELBOW BEECH 58 58P 1152744 CE RT MLG CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 15 1858G 1699 TJ383 PILOT REPORTED RIGHT MAIN STRUT BOTTOMED ON LANDING AND RIGHT BRAKE FAILED. ON INSPECTION, THE FITTING ON THE WHEEL CYL INDER WAS FOUND CRACKED. FURTHER INVESTIGATION FOUND WHEN STRUT WAS FULLY COMPRESSED, BRAKE LINE CONTACTED GEAR DOOR LI NK ASSY. PN 35-815056-16 CAUSING FITTING ON BRAKE CYL TO FAIL. SUBMITTER SUGGESTS INSPECTING ALL 58 SERIES ACFT WITH C LEVELAND 30-93 BRAKES FOR CLEARANCE BETWEEN DOOR LINK ASSY AND BRAKE LINE WITH STRUT COMPRESSED AT EACH INSPECTION. 1 L 7 2 3O A23CE 1997011600851 19970116 00851 CE 1997 1 16 97ZZZX357 1 19961127 G 3233 169380060 ACTUATOR GERDES BEECH 23 B24R 1151253 CE LT MLG FAILED B BVMR O A OTHER UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 EA 07 9196S 8915 0493 MC370 FIFTEEN MINUTES INTO FLIGHT PILOT HEARD LOUD BANG, NOTED GEAR DOWN AND LOCKED. UNABLE TO RETRACT GEAR. AFTER AN UNEVEN TFUL LANDING, AIRCRAFT TURNED OVER TO MAINTENANCE. INSP FOUND NO HYDRAULIC LEAKS. GEAR WOULD NOT RETRACT. FOUND LEFT GEAR ACTUATOR'S PISTON BROKEN OFF INSIDE ACTUATOR ALLOWING FLUID TO CIRCULATE WITH NO PRESSURE. AIRCRAFT USED FOR FLIGH T TRAINING. GEAR CYCLED OFTEN. 1 L 7 1 3O A1CE 1997011600852 19970116 00852 EA 1997 1 16 97ZZZX358 2 19961204 G 7414 M3548 ROTOR SLICK 4370 CESSNA 172 172P 2072436 CE LYC O360 O360A4M 41514 EA RT MAG BROKEN D K NONE O OTHER IN INSP/MAINT 1 GL 11 193SP 201 95060109 17276346 RL3460236A PERFORMED NORMAL RUN-UP PROCEDURES AND FOUND RIGHT MAG INOP. DISASSEMBLED MAG AND FOUND ROTOR GEAR AND END OF ROTORSHAF T LOOSE IN MAG. POSSIBLE DEFECTIVE ROTOR MANUFACTURE OR MACHINING OF SLOT FOR CAM. 1 H 7 1 3O 3 O NT 3A12 E286 1997011600853 19970116 00853 CE 1997 1 16 97ZZZX359 1 19961216 G 7921 652541 NUT CESSNA 206 TU206G 2073357 CE OIL COOLER STUD BROKEN D K NONE O OTHER IN INSP/MAINT 1 WP 17 199F 1006 U20606137 NUT IS CRACKED (BROKEN) AND FOUND IN THE BOTTOM OF COWLING. CAUSED OIL LEAK. 1 H 7 1 3O A4CE 1997011600854 19970116 00854 CE 1997 1 16 97ZZZX360 1 19961218 G 2430 CIRCUIT BREAKER BEECH 58 58 1152740 CE DC SYSTEM FAILED D O OTHER H ELECT. POWER LOSS-50 PC CR CRUISE 1 SO 03 258TJ 4629 TH988 TOTAL LOSS OF DC POWER 10 MINUTES INTO FLIGHT. REPAIRED INOPERATIVE BATTERIES. REPAIRED INOPERATIVE ALTERNATOR FIELD C IRCUIT BREAKER. REPLACED. (CAUSE - CORROSION). 1 L 7 2 3O 3A16 1997011600855 19970116 00855 CE 1997 1 16 97ZZZX361 1 19961112 G 2910 51011199 LINE CESSNA 402 402C 207590R CE INBD WING LEAKS I K NONE K FLUID LOSS IN INSP/MAINT 1 NE 05 3249M 10728 402C0296 FLIGHT CREW NOTICED HYD LEAKAGE INBD WING. INSPECTION NOTED PIN HOLE IN LINE AT HYD FLOW SWITCH AREA. REPLACED LINE AN D SERVICED SYSTEM. DETERIORATION OF LINE WAS CAUSE FOR LEAKAGE. SUBMITTER RECOMMENDS PRESSURE TESTS CONTINUE, BUT PREV ENTIVE MAINT SHOULD BE CONSIDERED (16 YEAR OLD PART.) 1 L 7 2 3O A7CE 1997011600856 19970116 00856 SO 1997 1 16 97ZZZX362 2 19961218 G 8540 632018 DRIVE GEAR BEECH 58 58 1152740 CE CONT O520 IO520CB 17032 SO ALT DRIVE BOLTS FAILED D O OTHER J WARNING INDICATION NR NOT REPORTED 1 SO 03 4675S 656 656 TH689 298719R PILOT REPORTED LOW OIL PRESSURE, AND ALTERNATOR INOP. FOLLOWED MM FOR OIL PRESSURE RELIEF VALVE AND FOUND METAL. REMOV ED ALTERNATOR AND FOUND GEAR, FACE, ALTERNATOR DRIVE BOLTS HAD SHEARED. 1 L 7 2 3O 3 O 3A16 E5CE 1997011600857 19970116 00857 EA 1997 1 16 97ZZZX363 2 19961230 G 7414 1038255514 MAGNETO CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA LT-RT MAG COIL CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 15 738YY 861 19844K 17270353 L24576T INSP FOUND LT AND RT COILS CRACKED. LT AND RT BREAKERS BURNED, LT AND RT ROTORS BURNED AND DISTRIBUTER BLOCK BURNED POS TS. 1 H 7 1 3O 3 O NT 3A12 E274 1997011600858 19970116 00858 SO 1997 1 16 97ZZZX364 2 19961201 G 8550 AM207835AO SEPARATOR AIRMAZE CESSNA 421 421C 2076016 CE CONT O520 GTSIO520L 17032 SO AIR OIL STEP FAILED D K NONE K FLUID LOSS IN INSP/MAINT 1 SW 99 726RT 416 4F13 421C0087 604196 ENGINE OIL PUMPING OVERBOARD. FOUND OIL AIR SEPARATOR INTERNAL SCREEN (SMALL) FAILED AND WAS BLOCKING OIL RETURN TO CRA NKCASE. ENGINE DAMAGE AT THIS TIME UNKNOWN. SEPARATOR INSTALLED 411 HRS AGO NEW. ONLY SERVICES WET VACUUM PUMP. WENT TO DRY PUMP. 1 L 7 2 3O 3 O A7CE E7CE 1997011600859 19970116 00859 GL 1997 1 16 97ZZZX365 3 19961105 G 6110 3807 PROP ASSY HARTZL HCC2Y HCC2YR4 GL PROP CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 1048 358 DN921 INSPECTION FOUND PROP ASSY P/N 3807 CORRODED. 5 C P920 1997011600860 19970116 00860 NE 1997 1 16 97ZZZX366 3 19961105 G 6110 51171 PROP ASSY BEECH 1900 1900D 1154162 CE HARTZL HCE4A HCE4A3A NE PROP CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 5420 HJ297 INSP FOUND PROP ASSY P/N 5117-1 CORRODED. 2 L 7 2 4T RT A24CE 5 C P10NE 1997011600861 19970116 00861 GL 1997 1 16 97ZZZX367 3 19961105 G 6110 2421 PROP ASSY MOONEY M20 M20E 5870212 SW HARTZL HCC2Y HCC2YK1 GL PROP CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 CA132 INSP FOUND PROP ASSY P/N 2421 CORRODED. 1 L 7 1 3O 2A3 5 C P920 1997011600862 19970116 00862 GL 1997 1 16 97ZZZX368 3 19961105 G 6110 24281 CYLINDER PIPER PA28 PA28R201T 7102813 SO HARTZL HCC2Y BHCC2YF1 GL PROP ASSY WORN B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 AM2596 INSP FOUND PROP ASSY CYLINDER P/N 2428-1 WORN. 1 L 7 1 3O 2A13 5 C P920 1997011600863 19970116 00863 GL 1997 1 16 97ZZZX369 3 19961105 G 6110 2421 PROP ASSY PIPER PA28 PA28R201T 7102813 SO HARTZL HCC2Y BHCC2YF1 GL PROP CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 AM2596 INSP FOUND PROP ASSY P/N 2421 CORRODED. 1 L 7 1 3O 2A13 5 C P920 1997011600864 19970116 00864 GL 1997 1 16 97ZZZX370 3 19961105 G 6111 BLADE MOONEY M20 M20 5870202 SW HARTZL HCC2Y HCC2YK1 GL PROP DAMAGED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 1829 288 F93576 AW1974 INSP FOUND PROP BLADE WITH IMPACT DAMAGE. 1 L 7 1 3O 2A3 5 C P920 1997011600865 19970116 00865 GL 1997 1 16 97ZZZX371 3 19961105 G 6111 BLADE MOONEY M20 M20 5870202 SW HARTZL HCC2Y HCC2YK1 GL PROP DAMAGED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 1829 288 F94306 AW1974 INSP FOUND PROP BLADE WITH IMPACT DAMAGE. 1 L 7 1 3O 2A3 5 C P920 1997011600866 19970116 00866 GL 1997 1 16 97ZZZX372 3 19961105 G 6110 3064 PROP ASSY BEECH 100 100BEECH 1152916 CE HARTZL HCB3T HCB3TN3 GL PROP CRACKED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 9815 1746 BU5621 INSP FOUND PROP ASSY P/N 3064 CRACKED. 1 L 7 2 3T A14CE 6 C P15EA 1997011600867 19970116 00867 GL 1997 1 16 97ZZZX373 3 19961105 G 6110 3475A2 PROP ASSY BEECH 100 100BEECH 1152916 CE HARTZL HCB3T HCB3TN3 GL PROP CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 9815 1746 BU5621 INSP FOUND PROP ASSY P/N 3475A-2 CORRODED. 1 L 7 2 3T A14CE 6 C P15EA 1997082800025 19970828 00025 SW 1997 8 28 97ZZZX3732 1 19960921 G 6230 206040576103 BEARING BELL 206 206L1 1182107 SW M/R MAST PITTED D K NONE J WARNING INDICATION IN INSP/MAINT 1 AL 03 600CK 830 45787 AFTER THE THIRD CHIP LIGHT, THE MAST WAS REMOVED FOR INSPECTION. ON INSPECTION OF THE BEARING, THE OUTER RACE WAS FOUND PITTED. BEARING S/N ZV-1423. 1 G 7 1 3U H2SW 1997082800059 19970828 00059 SO 1997 8 28 97ZZZX3739 2 19961231 G 8530 STUD PIPER PA28 PA28201T 7102819 SO CONT O360 TSIO360F 17025 SO ROCKER SHAFT FAILED G A UNSCHED LANDING Y ENGINE STOPPAGE NR NOT REPORTED 1 SW 01 40437 350 28R7703304 305289 AS A RESULT OF AN ACCIDENT, FOLLOW-UP INVESTIGATION REVEALED THE ENGINE LOST POWER DUE TO FAILURE OF THE ROCKER ARM SHAF T HOLD-DOWN STUDS ON NR 2 CYLINDER. AD 92-04-09 WAS C/W. THE CYLINDER WAS AN EXCHANGE INSTALLED AT THE LAST OVERHAUL. STUDS FAILED MOST LIKELY DUE TO OVERTORQUING. THE HISTORY OF THE CYLINDER ASSEMBLY IS UNKNOWN. SUBMITTER RECOMMENDATI ON, MANDATORY STUD REPLACEMENT AT OVERHAUL. 1 L 7 1 3O 3 O 2A13 E9CE 1997011600868 19970116 00868 CE 1997 1 16 97ZZZX374 1 19961217 G 5610 1013840257 WINDSCREEN BEECH 200 200BEECH 1152920 CE LT PILOT CRACKED B CWQR A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 GL 05 202KA 2489 89043H2107 BB272 AT FL 22,000 IN ICING CONDITIONS, OUTER PANE OF LEFT PILOT POSITION WINDSCREEN CRACKED, DUE TO ANTI-ICE ELEMENT ANOMALY, WHICH CAUSED A TEMPERATURE DIFFERENTIAL. ABOUT 80 EACH INSTANTANEOUS CRACKS OCCURRED. FLIGHT DISCONTINUED. REPLACED WINDSCREEN WITH NEW. 1 L 7 2 4T A24CE 1997011600869 19970116 00869 NE 1997 1 16 97ZZZX375 2 19961216 G 7320 124KDC01005P EEC LEAR 60 60LEAR 5170707 CE PWA 305 PW305 NE LT ENG FAILED C A O OTHER J X WARNING INDICATION ENGINE FLAMEOUT CL CLIMB 1 CE 05 8271 325 325 066 252 DURING INITIAL CLIMB, AT 15,500 FEET, THE LT ENGINE AMBER COMPUTER LIGHT ILLUMINATED. FIFTEEN SECONDS LATER THE LT ENGI NE FLAMED OUT. TWO RESTART ATTEMPTS WERE UNSUCCESSFUL. INVESTIGATION REVEALED A BLEED AIR CLAMP HAD COME OFF ALLOWING BLEED AIR TO FLOW INTO THE NACELLE. TEAR DOWN OF THE FADEC FOUND THERMAL FUSES (110 DEGREES CELCIUS) IN BOTH CHANNELS H AD OPENED WHICH CAUSED ENGINE TO SHUT DOWN. 2 L 7 2 4F 4 F RT A10CE E35NE 1997011600870 19970116 00870 GL 1997 1 16 97ZZZX376 3 19961105 G 6111 T101738 BLADE BEECH 100 100BEECH 1152916 CE HARTZL HCB3T HCB3TN3 GL PROP BELOW SPEC B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 9815 1746 C94159 BU5621 INSP FOUND PROP ASSY P/N T10173-8 BLADE BELOW MINIMUM SPECS. 1 L 7 2 3T A14CE 6 C P15EA 1997011600871 19970116 00871 GL 1997 1 16 97ZZZX377 3 19961105 G 6111 T101738 BLADE BEECH 100 100BEECH 1152916 CE HARTZL HCB3T HCB3TN3 GL PROP BELOW SPEC B EY2R D RETURN TO BLOCK O OTHER IN INSP/MAINT 1 GL 03 9815 1746 C87412 BU5621 INSP FOUND PROP ASSY P/N T10173-8 BLADE BELOW MINIMUM SPECS. 1 L 7 2 3T A14CE 6 C P15EA 1997011600872 19970116 00872 GL 1997 1 16 97ZZZX378 3 19961105 G 6111 F84772 BLADE PIPER PA32 PA32260 7103206 SO HARTZL HCC2Y HCC2YK1 GL PROP BELOW SPEC B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 C58495 CH9554 INSP FOUND PROP ASSY P/N F8477-2 BLADE BELOW MINIMUM SPECS. 1 L 7 1 3O A3SO 5 C P920 1997011600873 19970116 00873 GL 1997 1 16 97ZZZX379 3 19961105 G 6111 F84772 BLADE PIPER PA32 PA32260 7103206 SO HARTZL HCC2Y HCC2YK1 GL PROP BELOW SPEC B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 C58894 CH9554 INSP FOUND PROP ASSY P/N F8477-2 BLADE BELOW MINIMUM SPECS. 1 L 7 1 3O A3SO 5 C P920 1997011600874 19970116 00874 GL 1997 1 16 97ZZZX380 3 19961105 G 6110 806 PROP ASSY PIPER PA24 PA24250 7102404 SO HARTZL HC82X HC82XK1 GL PROP CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 4516 143G INSP FOUND PROP ASSY P/N 806 CORRODED. 1 L 7 1 3O 1A15 5 C P878 1997011600875 19970116 00875 GL 1997 1 16 97ZZZX381 3 19961105 G 6110 8382 PROP ASSY PIPER PA24 PA24250 7102404 SO HARTZL HC82X HC82XK1 GL PROP CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 4516 143G INSP FOUND PROP ASSY P/N 838-2 CORRODED. 1 L 7 1 3O 1A15 5 C P878 1997011600876 19970116 00876 GL 1997 1 16 97ZZZX382 3 19961105 G 6110 14B PROP ASSY PIPER PA24 PA24250 7102404 SO HARTZL HC82X HC82XK1 GL PROP CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 4516 143G INSP FOUND PROP ASSY P/N 14B CORRODED. 1 L 7 1 3O 1A15 5 C P878 1997011600877 19970116 00877 GL 1997 1 16 97ZZZX383 3 19961105 G 6110 5002 PROP ASSY PIPER PA28 PA28R201T 7102813 SO HARTZL HCC2Y BHCC2YF1 GL PROP CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 764 356 AM1751 INSP FOUND PROP ASSY P/N 5002 CORRODED. 1 L 7 1 3O 2A13 5 C P920 1997011600878 19970116 00878 GL 1997 1 16 97ZZZX384 3 19961105 G 6114 15941 HUB PIPER PA31 PA31P350 7103111 SO HARTZL HCI3Y HCI3YR2 GL PROP ASSY CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 F5177A INSP FOUND PROP ASSY P/N 1594-1 CORRODED. 1 L 7 2 3O RT A8EA 5 C P33EA 1997011600880 19970116 00880 NE 1997 1 16 97ZZZX386 3 19961105 G 6110 5133 PROP ASSY BEECH 1900 1900D 1154162 CE HARTZL HCE4A HCE4A3A NE PROP CRACKED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 5420 HJ297 INSP FOUND PROP ASSY P/N 5133 CRACKED. 2 L 7 2 4T RT A24CE 5 C P10NE 1997012300327 19970123 00327 GL 1997 1 23 97ZZZX399 3 19960102 G 6111 57C083867 CLAMP HARTZL HCB3T HCB3TN3 GL PROP BLADE CRACKED B DJFR K NONE O OTHER IN INSP/MAINT 1 EA 23 245 CC4782 BU13301 BLADE CLAMP FOUND CRACKED 2 INCHES STARTING AT COUNTERWEIGHT DOWEL PIN HOLE. 6 C P15EA 1997010900097 19970109 00097 CE 1997 1 9 97ZZZX4 1 19961203 G 5741 AN823EA BOLT CESSNA 182 182B 2072706 CE RT WING SPAR CORRODED D K NONE O OTHER IN INSP/MAINT 1 CE 09 2405G 4863 51705 FOUND THE RT WING SPAR BOLT HEAD CORRODED DURING INSPECTION. AFTER REMOVAL SHANK ALSO CORRODED. SUBMITTER RECOMMENDS L IBERAL POLICY OF REPLACING HARDWARE ON OLD AIRCAFT WHEN CORROSION IS SHOWING. 1 H 7 1 3O NT 3A13 1997012300328 19970123 00328 EU 1997 1 23 97ZZZX400 1 19961220 G 2701 L13401Z1 CONTROL BRIDGE LET L13 L13BLANIK 1360306 EU CONTROL STICK CRACKED D A K NONE O OTHER IN INSP/MAINT 1 CE 09 99950 025823 DURING ANNUAL INSPECTION, FOUND BRACKET CRACKED AT REAR CONTROL STICK ATTACHMENT ON THE CONTROL BRIDGE PART. FAILURE OF PART IN THIS AREA WOULD CAUSE LOSS OF AILERON AND ELEVATOR CONTROL. 1 K 0 0 G24EU 1997012300332 19970123 00332 NM 1997 1 23 97ZZZX404 1 19961210 G 2430 A7807 TERMINAL ROBSIN R22 R22BETA 7640110 NM BATTERY B+ LUG BROKEN D S A A UNSCHED LANDING H ELECT. POWER LOSS-50 PC CR CRUISE 1 SW 05 40419 2785 1617 FLAT TERMINAL ON B+ BATTERY POST BROKE IN-FLIGHT CAUSING A TOTAL ELECTRICAL FAILURE INCLUDING ROTOR AND ENGINE TACHS. 1 G 7 1 3O H10WE 1997012300334 19970123 00334 SW 1997 1 23 97ZZZX406 1 19961216 G 5302 TAIL BOOM BELL 222 222B 1182124 SW BS 219.40 CRACKED H A K NONE O OTHER IN INSP/MAINT 1 SW 15 911RA 47150 PILOT FOUND CRACK ON PRE-FLIGHT CHECK. CRACK WAS FOUND ON RIGHT HAND SIDE OF TAIL BOOM FORWARD OF HORIZ STAB AT BSTA 21 9.40, WL 75. CRACK RUNS FORE AND AFT AND IS 1.25 INCHES LONG. A/C TOTAL TIME 2353.8. THIS CRACK IS FORWARD OF PREVIOU S REPAIR FOR A VERTICAL CRACK AT BSTA 232, WL 75. 1 G 7 2 3U H9SW 1997012300335 19970123 00335 EU 1997 1 23 97ZZZX407 1 19961223 G 6320 4638304001 SUN GEAR BOLKMS 105 BO105S 5626006 EU MR GR BOX DEFECTIVE B EOPR K NONE W INADEQUATE Q C IN INSP/MAINT 1 AL 01 RECEIVED 2 EACH NEW SUN GEARS S/N'S 1389 AND 1368. PERFORMED MAGNAFLUX INSPECTION ON GEARS DUE TO COMPANY POLICY. BOTH FOUND TO HAVE DEFECT INDICATIONS. VISUAL INSPECTION REVEALED NOTHING. RETURNED TO MANUFACTURER FOR EVALUATION. 1 G 7 2 3U H3EU 1997012300338 19970123 00338 EA 1997 1 23 97ZZZX408 2 19961226 G 8540 76327 GEAR BELL 47 47G5 1181032 SW LYC O435 VO435B1A 41516 EA ACCSORY DRIVE FAILED G A A UNSCHED LANDING Y ENGINE STOPPAGE AG AGRICULTURE 1 GL 27 7925J 425 25041 RL380031 DURING SPRAY RUN WHEN CROSSING THE FENCE, THE ENGINE BACKFIRED AND QUIT. THE HELICOPTER TRAVELED APPROX 150 FEET IN THE AIR BEFORE THE SKIDS CONTACTED THE GROUND, SKIPPED 75 FEET AND STRUCK A SMALL HILL WHICH BROKE THE SKID AND THE TAIL BO OM AND TAIL ROTOR. THE ACFT CAME TO REST FACING THE OPPOSITE DIRECTION. TEAR DOWN INSP OF ENGINE REVEALED THAT THE ACC ESSORY DRIVE GEAR HAD FAILED DUE TO SIX BOLTS SHEARED AND THREE DOWELS FELL OUT OF PLACE. SUBMITTER STATES ONLY THE VO- 435-B1A ENGINE HAS THIS GEAR ASSY, AND THIS ACCIDENT WOULD MAKE THE THIRD OCCURRENCE THAT HAD BEEN REPORTED TO THE FAA S INCE MARCH 1996. 1 G 7 1 3O 3 O 2H3 E279 1997013000004 19970130 00004 SO 1997 1 30 97ZZZX415 2 19961220 G 8530 653191D GASKET CONT O470 O470* 17026 SO VALVE COVER DETERIORATED D K NONE W K INADEQUATE Q C FLUID LOSS IN INSP/MAINT 1 SW 07 2 UPON USING A NEW SERIES VALVE COVER GASKET 653191D, FOUND THAT ALL OF THE GASKETS RECEIVED FROM THE VENDOR LEAKED. ALL OF THE GASKETS WERE FOUND TO DEVELOP AN AREA WHERE THE GASKET WAS LITERALLY FALLING APART. THERE DID NOT APPEAR TO BE A NY LONG FIBER MATERIAL IN THE FAILED SEGMENTS THAT WOULD PROVIDE A COHESIVE PRODUCT. THE SEGMENTS WOULD TOTALLY COLLAPS E WITH FINGER PRESSURE. SUBMITTER STATED THERE IS ENOUGH EVIDENCE TO SHOW THAT QUALITY CONTROL WAS NOT MAINTAINED DURIN G MANUFACTURE OF THESE GASKETS. 3 O E273 1997013000005 19970130 00005 SO 1997 1 30 97ZZZX416 1 19961210 G 2820 412306 LINE PIPER PA31 PA31310 7103103 SO RT WING FUEL LEAKING B A VT3R K NONE K FLUID LOSS IN INSP/MAINT 1 WP 09 16TR 5326 317812088 FUEL STAINS FOUND ON BOTTOM OF RIGHT WING, NEAR WING ROOT. FURTHER INSPECTION REVEALED LEAKING FUEL LINE IN RIGHT WING ROOT AREA. NOTE THAT THE CURE DATE ON THE FUEL LINE WAS THE THIRD QTR OF 1977. REPLACED DEFECTIVE FUEL LINE WITH A NEW ONE AND TESTED IT WITH PUMP ON. NEW LINE IS GOOD. RECOMMEND CLOSER AND MORE FREQUENT INSPECTION OF THESE FUEL LINES. 1 L 7 1 3O RT A20SO 1997013000006 19970130 00006 1997 1 30 97ZZZX417 4 19961209 G 6122 C29003GT23 HOUSING BEECH 36 A36 1151604 CE GOV SPEED LEVER CRACKED B VT3R K NONE O OTHER IN INSP/MAINT 1 WP 09 2531U 1436 850573 E2301 DURING INVESTIGATION OF PROP RPM PROBLEM, IT WAS NOTED THE RPM INDICATION AT FULL THROTTLE WAS ONLY 2100 RPM. GAINED AC CESS TO THE GOVERNOR AND NOTED THE SPEED LEVER SHAFT WAS LOOSE AND THE END HOUSING CRACKED 360 DEGREES AROUND ITS BASE. NOTE: THIS HOUSING IS MADE OF PLASTIC. 1 L 7 1 3O 3A15 1997013000007 19970130 00007 SO 1997 1 30 97ZZZX418 1 19961223 G 5520 7170002 HINGE ASSY PIPER PA31 PA31350 7103110 SO RT OTBD ELEV CRACKED D A K NONE O OTHER IN INSP/MAINT 1 SW 99 3581C 1243 318052091 SUBMITTER OPERATES TWO PIPER NAVAJO CHIEFTAIN AIRCRAFT DAILY DURING THE WORK WEEK AND FINDS THAT THE RT OUTBOARD ELEVATO R HINGE ATTACHMENT TO THE HORIZ STAB IS AN AREA OF CONCERN DUE TO THE FREQUENCY OF THESE HINGES CRACKING. FIND THESE HI NGES ARE CRACKING IN THE AREAS OF THE BEND RADIUS OF THE HINGE MOUNTING FLANGES. THESE HINGES ARE OF THE IMPROVED TYPE IAW WITH PIPER SB NR G87. IT IS SUBMITTER'S OPINION THAT THESE HINGES BE MADE OF CAST MATERIAL OR CONSTRUCTED OF HEAVIE R MATERIAL AND FIT IMPROVED. 1 L 7 2 3O A20SO 1997013000009 19970130 00009 GL 1997 1 30 97ZZZX419 3 19961217 G 6111 A1851T BEARING LT10282NB53R MTSBSI MU2 MU2B60 5780460 CE HARTZL HCB4T HCB4TN5 GL PROP BLADES DEFECTIVE B RG4R K NONE O OTHER IN INSP/MAINT 1 SO 03 429WM 1520SA CDA3351 DEFECTIVE BLADE BEARINGS ON LT PROP. 1 BLADE STICKS IN ONE POSITION AND 2 BLADES ROUGH, FOUND DURING INSPECTION. REPAI RED BY HARTZELL, RETURNED AND SAME PROBLEM STILL EXISTS. TSN 486.7 HUB. TSN 946.0 BLADES. 1 H 7 2 3T RT A10SW 6 C P40EA 1997013000010 19970130 00010 SO 1997 1 30 97ZZZX420 2 19961216 G 8520 35972 BOLT CONT O470 O470R 17026 SO CON ROD NUT DEFECT D L K NONE W INADEQUATE Q C IN INSP/MAINT 1 CE 01 846403R4 DURING INSTALLATION AND TORQUE OF NEW CONTINENTAL P/N 35972 CON ROD BOLT, IT WAS FOUND NUT WAS DEFECTIVE. NUT SLIPPED P RIOR TO 39 FEET/POUNDS. BOLT P/N 35972. NUT P/N 626140. 3 O E273 1997013000011 19970130 00011 NE 1997 1 30 97ZZZX421 2 19961201 G 8520 CAM BEECH 18 B18S 1150806 CE PWA R985 R985AN14B 52008 NE NOSE CASE RIVETS LOOSE B L A UNSCHED LANDING R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 SW 17 1020 PILOT EXPERIENCED LOSS OF POWER AND MADE EMERGENCY LANDING. FOUND VALVES NOT FUNCTIONING PROPERLY. REMOVED PLUG IN NOS E CASE. INSP OF CAM RING FOUND RIVETS MISSING AND OTHERS LOOSE. ALL 35 RIVETS WERE SHEARED AND ONLY 5 STILL THERE. 1 L 7 2 3R 3 R TC710 5E1 1997013000012 19970130 00012 SO 1997 1 30 97ZZZX422 1 19961201 G 3246 WHEEL PIPER PA25 PA25 7102502 SO RT MLG BOLTS SHEARED D L K NONE O OTHER IN INSP/MAINT 1 SW 17 6304Z 239 25388 INSPECTION FOUND UPON REMOVAL OF RT MAIN GEAR WHEEL COVER, ONE OF THE THREE BOLTS THAT HOLD THE WHEEL HALVES TOGETHER WA S SHEARED OFF. THE NUT AND END OF THE BOLT WERE INSIDE THE WHEEL ENTRAPPED BY THE WHEEL COVER. ACFT TT 4171. 1 L 7 1 3O 2A10 1997013000013 19970130 00013 EA 1997 1 30 97ZZZX423 1 19960501 G 3243 MASTER CYL SCWZER G164 G164A 3952704 EA LT BRAKE SCREWS FAILED D L A K NONE O OTHER TX TAXI/GRND HDL 1 SW 17 4300 AFTER LANDING, THE PILOT WAS TURNING THE AIRPLANE AROUND ON THE GROUND TO TAXI BACK FOR ANOTHER LOAD, WHEN THE LEFT BRAK E PEDAL TIPPED FORWARD BEYOND THE NORMAL BRAKING ACTION AND SEEMED DISCONNECTED, AND THE BRAKE DID NOT WORK ANYMORE. IN SP FOUND THE THREE SCREWS THAT HOLD THE TOP OF THE BRAKE MASTER CYL IN PLACE HAD RIPPED OUT OF THE CYLINDER BASE, THUS, DISCONNECTING THE BRAKE MASTER CYLINDER. THIS WILL ALSO AFFECT THE RUDDER OPERATION, AS THE PEDAL FLIPS FORWARD AND LIM ITS THE RUDDER PEDAL TRAVEL. 1 Q 7 1 3R 1A16 1997013000014 19970130 00014 GL 1997 1 30 97ZZZX424 3 19961105 G 6111 S82NB6 BLADE BEECH 58 58 1152740 CE MCAULY 3AF32C D3AF32C35 GL PROPELLER BELOW SPEC B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 K73819YS 76870 INSPECTION FOUND PROPELLER BLADE BELOW MINIMUM. 1 L 7 2 3O 3A16 5 C P22EA 1997013000015 19970130 00015 GL 1997 1 30 97ZZZX425 3 19961105 G 6111 S82NB6 BLADE BEECH 58 58 1152740 CE MCAULY 3AF32C D3AF32C35 GL PROPELLER BELOW SPEC B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 F72048YS 776920 INSPECTION FOUND PROPELLER BLADE BELOW SPECS. 1 L 7 2 3O 3A16 5 C P22EA 1997013000016 19970130 00016 GL 1997 1 30 97ZZZX426 3 19961105 G 6111 S82NB6 BLADE BEECH 58 58 1152740 CE MCAULY 3AF32C D3AF32C35 GL PROPELLER BELOW SPEC B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 F72065YS 776920 INSPECTION FOUND PROPELLER BLADE BELOW SPECS. 1 L 7 2 3O 3A16 5 C P22EA 1997013000017 19970130 00017 GL 1997 1 30 97ZZZX427 3 19961105 G 6111 S82NB6 BLADE BEECH 58 58 1152740 CE MCAULY 3AF32C D3AF32C35 GL PROPELLER BELOW SPEC B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 F72066YS 776920 INSPECTION FOUND PROPELLER BLADE BELOW SPECS. 1 L 7 2 3O 3A16 5 C P22EA 1997013000018 19970130 00018 GL 1997 1 30 97ZZZX428 3 19961105 G 6110 A18996 PROP ASSY BEECH 58 58 1152740 CE MCAULY 3AF32C D3AF32C35 GL HUB CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 776920 INSPECTION FOUND PROPELLER ASSY CORRODED. 1 L 7 2 3O 3A16 5 C P22EA 1997013000019 19970130 00019 GL 1997 1 30 97ZZZX429 3 19961105 G 6114 A4001 DOWEL PIN BEECH 58 58 1152740 CE MCAULY 3AF32C D3AF32C35 GL PROPELLER CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 776920 INSPECTION FOUND PROPELLER ASSY DOWEL PIN CORRODED. 1 L 7 2 3O 3A16 5 C P22EA 1997013000020 19970130 00020 GL 1997 1 30 97ZZZX430 3 19961105 G 6111 C4451 FERRULE BEECH 58 58 1152740 CE MCAULY 3AF32C D3AF32C35 GL PROPELLER DEFECTIVE B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 776920 INSPECTION FOUND PROPELLER ASSY BLADE FERRULE DEFECTIVE. 1 L 7 2 3O 3A16 5 C P22EA 1997013000021 19970130 00021 GL 1997 1 30 97ZZZX431 3 19961105 G 6111 C4451 FERRULE BEECH 58 58 1152740 CE MCAULY 3AF32C D3AF32C35 GL PROPELLER DEFECTIVE B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 768730 INSPECTION FOUND PROPELLER BLADE FERRULE DEFECTIVE. 1 L 7 2 3O 3A16 5 C P22EA 1997013000022 19970130 00022 GL 1997 1 30 97ZZZX432 3 19961105 G 6110 A4191 PROP ASSY BEECH 58 58 1152740 CE MCAULY 3AF32C D3AF32C35 GL HUB CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 768730 INSPECTION FOUND PROPELLER ASSY CORRODED. 1 L 7 2 3O 3A16 5 C P22EA 1997013000023 19970130 00023 GL 1997 1 30 97ZZZX433 3 19961105 G 6110 A1896 PROP ASSY BEECH 58 58 1152740 CE MCAULY 3AF32C D3AF32C35 GL HUB CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 768730 INSPECTION FOUND PROPELLER ASSY CORRODED. 1 L 7 2 3O 3A16 5 C P22EA 1997013000024 19970130 00024 GL 1997 1 30 97ZZZX434 3 19961105 G 6111 S82NB6 BLADE BEECH 58 58 1152740 CE MCAULY 3AF32C D3AF32C35 GL PROPELLER BELOW SPEC B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 K73820YS 768730 INSPECTION FOUND PROPELLER BLADE BELOW MINIMUM. 1 L 7 2 3O 3A16 5 C P22EA 1997013000025 19970130 00025 GL 1997 1 30 97ZZZX435 3 19961105 G 6111 S82NB6 BLADE BEECH 58 58 1152740 CE MCAULY 3AF32C D3AF32C35 GL PROPELLER BELOW SPEC B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 K74310YS 768730 INSPECTION FOUND PROPELLER BLADE BELOW MINIMUM. 1 L 7 2 3O 3A16 5 C P22EA 1997013000145 19970130 00145 SO 1997 1 30 97ZZZX440 2 19961217 G 7314 6462121 PUMP CESSNA 210 210D 2073414 CE CONT O520 IO520A 17032 SO ENG FUEL FAILED D K NONE O OTHER IN INSP/MAINT 1 NM 01 3908Y 1150 21058408 112585R PILOT REPORTED THAT ENGINE WOULD NOT RUN BELOW 1500 RPM ON START DUE TO FUEL PUMP INTERNAL FAILURE. 1 H 7 1 3O 3 O 3A21 E5CE 1997013000146 19970130 00146 SO 1997 1 30 97ZZZX441 2 19961231 G 7414 10357586 DISTRIBUTOR GEAR 101630203 CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO LT MAG STRIPPED D A UNSCHED LANDING E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CL CLIMB 1 NE 01 406BK 1966 D0690101ER 402C0807 278289 AFTER TAKEOFF, THE RIGHT ENGINE STARTED RUNNING ROUGH. PILOT RECEIVED CLEARANCE TO LAND. AFTER LANDING, PILOT PERFORME D MAG CHECK TAXIING BACK TO GATE. LEFT MAG WAS DEAD. MECHANIC CHANGED MAGNETO, TIMED TO ENGINE, RAN UP GOOD. ON DISAS SEMBLY OF MAG, FOUND DISTRIBUTOR GEAR MISSING 5 TEETH. GEAR WAS INSTALLED 6 YEARS AGO. 1 L 7 2 3O 3 O A7CE E8CE 1997013000147 19970130 00147 SO 1997 1 30 97ZZZX442 1 19961201 G 5712 78475005 RIB PIPER PA28 PA28R200 7102811 SO RT WS 49.25 CRACKED D K NONE O OTHER IN INSP/MAINT 1 GL 19 40724 28R7435116 DURING C/W AD 95 20-07 (SIDE BRACE STUD INSPECTION), IT WAS DISCOVERED THAT THE ADJACENT RIB (WS 49.25) WAS CRACKED IN T HE LOWER PORTION OF THE RADIUS FOR THE FORWARD FLANGE. THE SIDE BRACE STUD BRACKET ASSEMBLY MOUNTS ON TOP OF THE RIB FL ANGE MAKING INSPECTION OF THIS AREA IMPOSSIBLE WITH THE SIDE BRACE STUD BRACKET ASSEMBLY INSTALLED. THIS CONDITION WAS FOUND ON BOTH WINGS. THE CRACKS START AT THE BOTTOM EDGE OF THE FLANGE RADIUS AND EXTEND UPWARD APPROXIMATELY ONE INCH. 1 L 7 1 3O 2A13 1997013000148 19970130 00148 SO 1997 1 30 97ZZZX443 1 19961201 G 5712 78475005 RIB PIPER PA28 PA28R200 7102811 SO LT WS 49.25 CRACKED D A K NONE O OTHER IN INSP/MAINT 1 GL 19 40724 28R7435116 DURING C/W AD 95 20-07 (SIDE BRACE STUD INSPECTION), IT WAS DISCOVERED THAT THE ADJACENT RIB (WS 49.25) WAS CRACKED IN T HE LOWER PORTION OF THE RADIUS FOR THE FORWARD FLANGE. THE SIDE BRACE STUD BRACKET ASSEMBLY MOUNTS ON TOP OF THE RIB FL ANGE MAKING INSPECTION OF THIS AREA IMPOSSIBLE WITH THE SIDE BRACE STUD BRACKET ASSEMBLY INSTALLED. THIS CONDITION WAS FOUND ON BOTH WINGS. THE CRACKS START AT THE BOTTOM EDGE OF THE FLANGE RADIUS AND EXTEND UPWARD APPROXIMATELY ONE INCH. 1 L 7 1 3O 2A13 1997013000151 19970130 00151 SO 1997 1 30 97ZZZX446 1 19961223 G 2140 B304090D381 HEATER JANITROL PIPER PA34 PA34200T 7103406 SO BURNER CAN CRACKED B APCR K NONE O OTHER IN INSP/MAINT 1 NM 01 4490F 1483 7781395 347670339 HEATER FAILED P.D.T. PER AD 96-20-07. BURNER CAN CRACKED. TSOH TRACKED VIA AIRCRAFT FLIGHT TIME = (2966 HRS) (DIVIDED BY 2) = 1483 HRS ON HEATER. 1 L 7 2 3O A7SO 1997013000152 19970130 00152 EA 1997 1 30 97ZZZX447 2 19961124 G 8520 CONNECT ROD PIPER PA28 PA28R200 7102811 SO LYC O360 IO360C1C 41514 EA NR 4 CYL FAILED D A UNSCHED LANDING E K R VIBRATION/BUFFET FLUID LOSS PARTIAL RPM/PWR LOSS CR CRUISE 1 NM 01 4830T 28R7235119 L2307251A AIRCRAFT WAS FLYING 5 MILES NW OF OGD WHEN PILOT REPORTED SUDDEN OIL PRESSURE DROP. UPON INSPECTION AFTER LANDING, THE ENGINE CASE WAS FOUND CRACKED. AFTER REMOVING CYLINDERS FOUND THAT NR 4 CONNECTING ROD WAS BROKE OFF AT THE CAP. IT IS UNKNOWN WHETHER THIS HAPPENED BEFORE OR AFTER OIL PRESSURE LOSS. 1 L 7 1 3O 3 O 2A13 1E10 1997013000154 19970130 00154 SO 1997 1 30 97ZZZX449 1 19961231 G 7810 STACK ASSY PIPER PA28 PA28140 7102802 SO NR 1 CYL EXH CRACKED D K NONE O OTHER IN INSP/MAINT 1 GL 03 5677U 2346 2826474 STACK ASSY HAS HAIR-LINE FRACTURE ALONG WELD ATTACHING OVERLAY AT EXHAUST PORT FLANGE. 1 L 7 1 3O 2A13 1997102300432 19971023 00432 NM 1997 10 23 97ZZZX4490 1 19961205 G 3233 65B105059 SUPPORT FITTING BOEING 747 747121 1384871 NM LT BODY LG CRACKED C K NONE O OTHER IN INSP/MAINT 1 SW 99 747GE 19651 LEFT BODY LANDING GEAR ACTUATOR ATTACH FITTING ON THE STA 1480 BULKHEAD WAS FOUND TO HAVE THE INBOARD LUG OF THE FITTING CRACKED. BOEING SM 747-53-2298 WAS NOT TERMINATED. 2 L 7 4 4F A20WE 1997102300433 19971023 00433 NM 1997 10 23 97ZZZX4491 1 19961205 G 2730 936005009 ELEVATOR PCP BOEING 747 747121 1384871 NM LT INBD ELEVATOR MALFUNCTION C L A K NONE F FLT CONT AFFECTED IN INSP/MAINT 1 SW 99 747GE 19651 WHILE TROUBLESHOOTING FOR AN UNCOMMANDED AUTOPILOT PITCH UP WHEN THE FLAPS WERE RETRACTED FROM 1 TO ZERO, A DISCREPANCY WAS DISCOVERED IN THE LT INBOARD ELEVATOR POWER CONTROL PACKAGE. WITH ALL HYDRUALIC POWER OFF TO THE TAIL AND CONTROL C OLUMN IN THE FULL FORWARD POSITION, WHEN THE NR 3 AND NR 4 HYDRAULIC SYSTEMS WERE PLACED ON (ONE AT A TIME), THE LT INBO ARD ELEVATOR WENT TO THE FULL DOWN POSITION RAPIDLY. CHANGED ELEVATOR PCP AND FLIGHT TESTED OK. 2 L 7 4 4F A20WE 1997013000155 19970130 00155 CE 1997 1 30 97ZZZX450 1 19961224 G 3246 16201700 WHEEL PARKERHANFIN 40135 CESSNA 421 421B 2076014 CE RIM CRACKED G S K NONE O OTHER IN INSP/MAINT 1 GL 17 65AE 421B0953 THREE INCH LONG CRACK FOUND IN WHEEL RIM. 1 L 7 2 3O A7CE 1997013000156 19970130 00156 SO 1997 1 30 97ZZZX451 1 19961231 G 3230 AN625 BOLT PIPER PA28 PA28R201 7102816 SO NLG DRAG LINK MISINSTALLED G K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 25 78QB 1498 28R7837308 BOTH NOSE GEAR UPPER DRAG LINKS TO ENGINE MOUNT BOLTS INSTALLED BACKWARDS. WASHER STACK ARRANGEMENT INCORRECT ALSO PER PIPER CHEROKEE SERVICE MANUAL. 1 L 7 1 3O 2A13 1997013000158 19970130 00158 CE 1997 1 30 97ZZZX453 1 19961201 G 7160 VALVE CESSNA 172 172N 2072434 CE CARB HEAT GASKET LOOSE D A K NONE O OTHER IN INSP/MAINT 1 SW 99 9419E 17272255 CARB HEAT VALVE ASSY'S FELT BROKE FREE OF VALVE ASSY. NOTICED DURING 100 HR INSP. LOOSENED TO THE POINT OF POSSIBLE IN GESTION IN THE INTAKE SYSTEM. 1 H 7 1 3O NT 3A12 1997013000159 19970130 00159 CE 1997 1 30 97ZZZX454 1 19961231 G 2822 41400015 PUMP DUKES CESSNA 185 A185F 2072821 CE CASTING SEAM LEAK B L A CF4R K NONE W INADEQUATE Q C IN INSP/MAINT 1 AL 03 9452N 409 32100 18504359 DURING ANNUAL INSPECTION, FOUND FUEL STAIN/WEEPING ON AUX FUEL BOOST PUMP HEAD. UPON INVESTIGATION, FOUND HEAD TO BE WE EPING AT A CASTING SEAM ON HEAD IN A VISABLE LINE ABOUT .25 INCH LONG. SUSPECT FLAW IN CASTING SEAM. REPLACED PUMP WIT H ZERO TIME OVERHAUL. CESSNA P/N C291504-0201. 1 H 7 1 3O 3A24 1997013000160 19970130 00160 CE 1997 1 30 97ZZZX455 1 19961114 G 3411 S10711 TUBE CESSNA 172 172P 2072436 CE PITOT MELTED D K NONE O OTHER IN INSP/MAINT 1 NM 03 97LP 6567 17274398 DURING A 100 HOUR INSPECTION, DISCOVERED THAT THE TWO WIRES FOR THE PITOT HEAT HAD CONTACTED AND MELTED 90 PERCENT OF TH E WAY THROUGH THE PITOT POLYETHYLENE TUBE. MELTING OCCURRED ONE INCH ABOVE TUBE NUT ON TOP OF PITOT TUBE BODY. RECOMME NDATION: ROUTE WIRES AWAY FROM TUBE TO PREVENT WIRES FROM MELTING TUBING. 1 H 7 1 3O NT 3A12 1997013000167 19970130 00167 EU 1997 1 30 97ZZZX462 1 19961105 G 7603 BRACKET GROB G115 G115C 1660303 EU CABLE SUPPORT CRACKED D K NONE O OTHER IN INSP/MAINT 1 NM 03 115AK 72 82054C2 DURING ACCEPTANCE INSPECTION ON NEW GROB AIRCRAFT WITH 72.2 HOURS SINCE NEW, FOUND THROTTLE CABLE SUPPORT BRACKET THAT A TTACHES TO CARBURETOR CRACKED AT LOWER CARBURETOR MOUNT. CRACK IS ATTRIBUTED TO PROPELLER/ENGINE VIBRATION. BOTH ENGIN E AND PROPELLER HAVE 72.2 HOURS SINCE NEW. DYNAMIC BALANCE TO BE ACCOMPLISHED NEXT TO REMEDY CRACKING. 1 L 7 1 3O NT A57EU 1997013000168 19970130 00168 NE 1997 1 30 97ZZZX463 3 19961202 G 6111 SFA13M1R0A BLADE HAMSTD HAMSTD 14SF 14SF5 NE PIN BOSS CRACKED B H2SR K NONE O OTHER IN INSP/MAINT 1 SO 13 14397 8397 BLADE WAS RECEIVED FOR A MAJOR INSPECTION. DURING DYE CHECK OF THE BLADE SHANK AS REQUIRED DURING MI, TWO LINEAR INDICA TIONS WERE FOUND AND VERIFIED WITH FLUORESCENT PENETRANT INSPECTION. BOTH INDICATIONS WERE ON THE BLADE PIN BOSS AREA. ONE IS ON THE THRUST WASHER SURFACE AND IS APPROXIMATELY .1875 INCH IN LENGTH. THE OTHER INDICATION IS JUST BELOW THE T HRUST WASHER SURFACE AND IS APPROXIMATELY .2187 INCH IN LENGTH. THESE INDICATIONS ARE LOCATED APPROXIMATELY 90 DEGREES IN RESPECT TO EACH OTHER. 6 C P7NE 1997013000231 19970130 00231 GL 1997 1 30 97ZZZX480 2 19961104 G 7530 23001804 TUBE 23005367 BELL 206 206L1 1182107 SW ALLSN 250C 250C28B 03013 GL BLEED VALVE LEAK H K NONE M OVER TEMP NR NOT REPORTED 1 SO 11 911SA FF27824 45383 860170 AIRCRAFT EXPERIENCED TRANSIENT OVER TEMP. HOT SECTION INSPECTION C/W, NO DAMAGE NOTED FROM OCCURRENCE. SUSPECT CAUSE I S AIR LEAK AT BLEED VALVE PR LINE. LEAK CHECK MUST BE DONE WITH BLEED CONTROL SOLENOID IN OPEN POSITION. 1 G 7 1 3U 3 U H2SW E1GL 1997013000232 19970130 00232 CE 1997 1 30 97ZZZX481 1 19960106 G 2434 26012717 DRIVE C6115050201 CESSNA 208 208B 2073701 CE STDBY ALTERNATOR FAILED G O OTHER J WARNING INDICATION CR CRUISE 1 WP 17 762FE 351 258 208B0255 PILOT REPORTED WHILE EN ROUTE, STAND-BY POWER OFF LIGHT ILLUMINATED. THE STAND-BY ALTERNATOR POWER WAS CHECKED AND STAN D-BY POWER DID NOT COME ON LINE. MAINTENANCE WAS DISPATCHED TO THE AIRCRAFT AND CONFRIMED STAND-BY POWER FAILURE. THE STAND-BY ALTERNATOR SYSTEM WAS INSPECTED AND FOUND THE ALTERNATOR DRIVE SHAFT FAILED AT THE SHEAR POINT. THE STAND-BY A LTERNATOR DRIVE ASSEMBLY WAS REPLACED AND THE STAND-BY POWER SYSTEM WAS FUNCTIONALLY CHECKED AND NO DISCREPANCIES WERE F OUND. THE AIRCRAFT WAS RETURNED TO SERVICE. 1 H 7 1 3T A37CE 1997013000233 19970130 00233 CE 1997 1 30 97ZZZX482 1 19961218 G 3230 084012515 PUSH PULL ROD CESSNA 310 310R 2074245 CE LT MLG FAILED D A K NONE O OTHER IN INSP/MAINT 1 GL 07 6102X 6218 310R1269 DURING AN OPS NR 1 INSP, FOUND THE LT MLG PUSH/PULL ROD LOOSE AT ROD END. DURING GEAR RETRACTION TO GAIN ACCESS TO PART FOR REPLACEMEN, TOTAL FAILURE OF THE ROD END OCCURRED CAUSING LOSS OF MOVEMENT OF THE LEFT MAIN GEAR ASSY TO THE UP OR DOWNLOCK POSITION. SUBMITTER RECOMMENDS CLOSE INSP OF THIS AND ALL OTHER GEAR RODS' LINKAGES AND BELLCRANKS DURING INSP . REF AD 76-13-07 WHICH APPLIES TO SOME 400 SERIES A/C. THIS AD DOES NOT APPLY TO THE 310 WHICH HAS THE SAME STYLE GEA R SYSTEM. OTHER RECOMMENDATIONS ARE POSSIBLE LIFE LIMITS SET ON THIS AND OTHER RODS AND BELLCRANKS OF THE GEAR SYSTEM. 1 L 7 2 3O 3A10 1997013000242 19970130 00242 CE 1997 1 30 97ZZZX487 1 19961217 G 2460 SPLICE CESSNA 500 560CESSNA 2076750 CE FS 234 FAILED C L A K NONE H ELECT. POWER LOSS-50 PC IN INSP/MAINT 1 GL 05 68881 560173 INVESTIGATION FOR COMPLETE POWER FAILURE OF FWD LT GALLEY, FOUND AN INADEQUATE SINGLE WIRE CRIMP AT FS 234.0 UNDER PANEL 261AT. IMPROPER GAUGE SPLICE CONNECTOR ALLOWED WIRE TO PULL FREE. 2 L 7 2 4F RT A22CE 1997120400508 19971204 00508 SW 1997 12 4 97ZZZX4908 1 19960924 G 6510 406040340101 DISC PAK BELL 407 407 SW T/R DISC PAK CRACKED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 437AL 53141 SCHEDULED INSPECTION, T/R DRIVE DISC FOUND CRACKED AND SCRATCHED. REMOVED AND REPLACED. 1 G 7 1 3U O H2SW 1997013000338 19970130 00338 CE 1997 1 30 97ZZZX491 1 19961230 G 3260 426EN98 SWITCH LEAR 25 25B 5170511 CE LT MLG SQUAT FAILED B L4JR K NONE O OTHER LD LANDING 1 NM 03 627WS 170 THE LT MLG SQUAT SWITCH FAILED CAUSING THE THRUST REVERSERS NOT TO DEPLOY. 2 L 7 2 4J A10CE 1997013000339 19970130 00339 1997 1 30 97ZZZX492 4 19961127 G 2216 49A26 CAPSTAN SIGMATEK 1C4691377 GULSTM 690TP 690B 7630516 SW TRIM SERVO MISINSTALLED B B2PR K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 17 690NA 2339 11359 PILOT REPORTED A FRAYED CABLE IN AFT FUSELAGE. THE CABLE FOR THE ELEVATOR TRIM WAS FRAYED AT ELECTRIC ELEVATOR TRIM SER VO LOCATION. CAUSE OF FRAYING WAS DUE TO AN IMPROPERLY INSTALLED CAPSTAN, P/N 49A26, ON THE SERVO ASSY WHICH CAUSED THE GROOVE IN THE CAPSTAN TO WEAR AND CABLE TO FRAY. SUBMITTER RECOMMENDS INSPECTION OF CABLE AND CAPSTAN INSTALLATION TO ASSURE PROPER INSTALLATION. SERVO, P/N 1C469-1-377, EDO-AIRE. SERVO CHANGED ABOUT 6 MOS PRIOR TO MALFUNCTION. 1 H 7 2 3T 2A4 1997013000340 19970130 00340 SW 1997 1 30 97ZZZX493 1 19961127 G 2731 5000115091387 CONTROL CABLE GULSTM 690TP 690B 7630516 SW ELEV TRIM FRAYED B B2PR K NONE O OTHER IN INSP/MAINT 1 SO 17 690NA 11359 PILOT REPORTED A FRAYED CABLE IN AFT FUSELAGE. THE CABLE FOR THE ELEVATOR TRIM WAS FRAYED AT ELECTRIC ELEVATOR TRIM SER VO LOCATION. CAUSE OF FRAYING WAS DUE TO AN IMPROPERLY INSTALLED CAPSTAN, P/N 49A26, ON THE SERVO ASSY WHICH CAUSED THE GROOVE IN THE CAPSTAN TO WEAR AND CABLE TO FRAY. SUBMITTER RECOMMENDS INSPECTION OF CABLE AND CAPSTAN INSTALLATION TO ASSURE PROPER INSTALLATION. SERVO, P/N 1C469-1-377, EDO-AIRE. SERVO CHANGED ABOUT 6 MOS PRIOR TO MALFUNCTION. 1 H 7 2 3T 2A4 1997013000344 19970130 00344 SO 1997 1 30 97ZZZX497 1 19961219 G 5320 674202 STIFFENER 7643600 PIPER PA28 PA28R201 7102816 SO NLG WELL MISSING B L A UC2R K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 19 3420Q 2616 28R7737054 INSP OF ACFT FOR NOSE WHEELWELL STRUCTURE DAMAGE DUE TO MISSING STIFFENER. (P/N 6747202). REF: SL 832 DATED JAN 25, 197 8. SUBMITTER SUGGESTS ONE TIME INSP OF PA28R201 ACFT FOR STIFFENER INSTALLATION. 1 L 7 1 3O 2A13 1997013000345 19970130 00345 NM 1997 1 30 97ZZZX498 1 19961226 G 2750 FLAP ARM CHRIS HUSKY A1 221020X NM WING BELLCRANK BOLTS INCORRECT B A V2AR K NONE W INADEQUATE Q C IN INSP/MAINT 1 AL 03 9622V 595 1154 FLAP CABLE ATTACH BOLTS AT WING BELLCRANK FOUND TO BE INSTALLED UPSIDE DOWN. IPC SHOWS BOLTS INSTALLED HEAD UP. NUT S TRIKES ADJACENT RIB AT FLAPS DOWN POSITION. NO RECORD OF FLAP MAINTENANCE IN A/C RECORDS. 1 H 7 1 3O NC A22NM 1997013000346 19970130 00346 CE 1997 1 30 97ZZZX499 1 19961231 G 2822 41400015 PUMP CESSNA 185 A185F 2072821 CE FUEL BOOST LEAKING B S CF4R K NONE K FLUID LOSS IN INSP/MAINT 1 AL 03 9452N 409 32100 18504359 DURING ANNUAL INSPECTION, FOUND FUEL STAIN/WEEPING ON AUX FUEL BOOST PUMP HEAD. UPON INVESTIGATION, FOUND HEAD TO BE WE EPING AT A CASTING SEAM ON HEAD, IN A VISABLE LINE ABOUT .25 INCH LONG. SUSPECT FLAW IN CASTING SEAM. REPLACED PUMP WI TH ZERO TIME OVERHAUL. 1 H 7 1 3O 3A24 1997010900098 19970109 00098 SO 1997 1 9 97ZZZX5 2 19961213 G 8530 VALVE CESSNA 180 180H 2072618 CE CONT O470 O470L 17026 SO CYL INTAKE LEAK D K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 11 2467F 18051699 694745LR CONTINENTAL CYLINDER ASSY PN 653443A13. 2 OUT OF 6 CYLINDERS HAD UNACCEPTABLE LEAKS FROM INTAKE VALVES. ABOUT 1 DROP L IQUID SOLVENT PER MINUTE WITH VALVE SPRINGS INSTALLED. ALSO, VALVE GUIDES ARE HOURGLASS SHAPED. ABOUT .002 INCH SMALLE R IN CENTER THAN ON ENDS. THESE ARE ALL OEM NEW PARTS. 1 H 7 1 3O 3 O 5A6 E273 1997013000347 19970130 00347 SW 1997 1 30 97ZZZX500 1 19961204 G 8010 301265AA DIODE A1077V BELL 206 206L3 1182108 SW BATTERY RELAY FAILED D A K NONE B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 SW 99 94WP 1741 51360 WHILE ATTEMPTING A START THE PILOT REPORTS SMOKE. INVESTIGATION FOUND THE FOLLOWING WIRES BURNT, P16A22, P17A22, AND P1 8A22N, ALONG WITH DIODE 30-126-5AA (MM WIRING DIAGRAM NR 2CR1) FOUND DIODE ALLOWING CURRENT TO FLOW BOTH DIRECTIONS CRE ATING A SHORT TO GROUND. DIODE FAILED FOR UNKNOWN REASONS. 1 G 7 1 3U H2SW 1997013000348 19970130 00348 1997 1 30 97ZZZX501 4 19961216 G 3421 501120401 GYRO LEAR 35 35A 5170602 CE COCKPIT VG DEFECTIVE D L K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 05 230R 1420 130 A VERTICAL GYRO WAS INSTALLED IN AIRCRAFT IN LATE AUGUST. THIS UNIT FAILED IN LATE OCT AND SHOWED SIGNS OF BEING HOT IN TERNALLY (CANNON PLUG RING HAD BLUED). THIS UNIT HAD BEEN OVERHAULED IN JUNE '96. WAS SENT A REPLACEMENT (OVERHAULED) GYRO. 2 L 7 2 4F A10CE 1997013000349 19970130 00349 1997 1 30 97ZZZX502 4 19961222 G 2562 AK450 ELT AMTR VANS RV6 05608 GL FUSELAGE FAILED G K NONE O OTHER IN INSP/MAINT 1 WP 09 961CP 4502256 23938 ON ACCIDENT SITE, ELT WAS REMOVED FROM FUSELAGE AND SWITCH WAS IN 'ARM'. NO OUTPUT FROM TRANSMITTER ON 121.5 WAS DETECT ED BY RADIO RECEIVERS AT ACCIDENT SITE. WHEN ELT WAS SHAKEN FORE AND AFT IN THE PROPER IMPACT MOTION BY HAND AT SITE, N OTHING WAS EMITTED ON 121.5. 1 L 7 1 3O NC EXPA1L71 1997121100121 19971211 00121 NE 1997 12 11 97ZZZX5036 2 19960708 G 8520 STUD DHAV DHC2 DHC2* 2800108 EA PWA R985 R985* 52008 NE NR 1 CYLINDER DEFECTIVE H K NONE O OTHER IN INSP/MAINT 1 AL 03 38938 98 424 JP201806 NR 1 CYLINDER STUD DEFECTIVE. THIS IS A COMMON PROBLEM TO THESE ENGINES. THE BASIC PROBLEM HERE IS HOW THE AD READS. S UBMITTER BELIEVES THERE IS A NEED TO REVISE THE WORDING. 1 H 7 1 3R 3 R A806 5E1 1997013000432 19970130 00432 SO 1997 1 30 97ZZZX504 2 19961118 G 8520 CRANKSHAFT CESSNA 210 T210L 2073449 CE CONT O520 TSIO520R 17040 SO ENGINE BROKEN D A UNSCHED LANDING Y ENGINE STOPPAGE CR CRUISE 1 NM 01 2076S 21061043 ENGINE QUIT IN-FLIGHT AND IT WAS DISCOVERED THE CRANKSHAFT HAD BROKEN IN TWO PLACES, JUST AFT OF THE FWD THRUST BEARING. RESEARCH OF LOGS SHOWS THAT THE AIRCRAFT WAS BELLIED 891 HOURS PRIOR TO THE CRANKSHAFT BREAKAGE, AT WHICH POINT THE BE LLY WAS REPAIRED, A NEW PROPELLER INSTALLED, AND NO TEAR DOWN INSPECTION OF THE ENGINE PERFORMED. LUCKILY, NO ONE WAS I NJURED DURING THE FORCED LANDING (IFR AT NIGHT), BUT THERE NEEDS TO BE A REGULATION REQUIRING A TEAR-DOWN INSPECTION OF AN ENGINE FOLLOWING A PROP STRIKE. TCM BULLETIN M84-16 RECOMMENDS TEAR DOWN IF THE PROP HAS TO BE REMOVED FOR REPAIR, B UT IS NOT REQUIRED. A REQUIREMENT FOR TEAR DOWN BASED ON THIS RECOMMENDATION WOULD ELIMINATE THIS 'GREY AREA'. 1 H 7 1 3O 3 O 3A21 E8CE 1997013000437 19970130 00437 SO 1997 1 30 97ZZZX509 1 19961216 G 5320 6252200 SUPPORT PIPER PA28 PA28140 7102802 SO LT WINDSHIELD ERODED D K NONE O OTHER IN INSP/MAINT 1 NE 03 15488 287325078 BRACKET LOCATED ON LT SIDE OF WINDSHIELD, PILOT'S SIDE AT LOWER AFT CORNER. YEARS OF LEAKING WINDSHIELDS IN CONJUNCTION WITH FOAM IN CONTACT WITH BRACKET. RUSTY BRACKET ERODED TO ONE-HALF ORIGINAL WALL THICKNESS. BOLT HEADS OF AN-3 BOLTS RUSTED AND REDUCED TO APPROXIMATELY .030 INCH IN WEIGHT. 1 L 7 1 3O 2A13 1997013000440 19970130 00440 SO 1997 1 30 97ZZZX512 1 19961211 G 2430 66616002 WIRE PIPER PA34 PA34200T 7103406 SO BATTERY BURNED B A APCR K NONE O OTHER IN INSP/MAINT 1 NM 01 8107D 348070010 BRAIDED WIRE TYPE BATTERY CABLES LOOSE AT BATTERY TERMINALS, CAUSES SEVERE VOLTAGE FLUCTUATIONS AND FLIGHT INTERRUPTION. OPERATOR REPORTS NUMEROUS PROBLEMS WITH THIS TYPE CABLE. EXTREMELY DANGEROUS CONDITIONS RESULT WHEN BRAIDING COMES UN DONE AND BATTERY TERMINALS GET LOOSE. 1 L 7 2 3O A7SO 1997013000441 19970130 00441 SO 1997 1 30 97ZZZX513 1 19961125 G 3230 LANDING GEAR PIPER PA34 PA34200T 7103406 SO MLG MALFUNCTION B APCR O OTHER J WARNING INDICATION CL CLIMB 1 NM 01 8107D 348070010 PILOT DEPARTED FIELD WITH SNOW ON TAXIWAYS AND RUNWAY. LANDING GEAR FAILED TO FULLY RETRACT DUE TO BLOCKAGE BY CHUNKS O F ICE AND SNOW. SUBMITTER SUGGESTS P.O.H. REVISION TO PRECLUDE OPERATION OF THIS MODEL AIRCRAFT FROM FIELDS WITH ANY FO RM OF ICE, SNOW, SLUSH. 1 L 7 2 3O A7SO 1997013000444 19970130 00444 SO 1997 1 30 97ZZZX516 1 19960107 G 7714 TACHOMETER PIPER PA34 PA34200T 7103406 SO LT ENG RPM DEFECTIVE B DYPR K NONE O OTHER IN INSP/MAINT 1 NM 09 30964 856 347870233 WHEN THE AIRCRAFT TACHOMETER INDICATES 2,300 RPM, THE EXTERNAL CALIBRATED TACHOMETER SHOWED THE ACTUAL ENGINE RPM AT 2,4 40 RPM. THIS MAY HAVE BEEN A LONG TIME PROBLEM AS THE ENGINE HAS BEEN TOP OVERHAULED AT LEAST TWICE IN 1546 HRS. 1 L 7 2 3O A7SO 1997013000445 19970130 00445 SO 1997 1 30 97ZZZX517 1 19960107 G 7714 TACHOMETER PIPER PA34 PA34200T 7103406 SO RT ENG RPM DEFECTIVE B DYPR K NONE O OTHER IN INSP/MAINT 1 NM 09 30964 1546 347870233 WHEN THE AIRCRAFT TACHOMETER INDICATES 2,300 RPM, THE EXTERNAL CALIBRATED TACHOMETER SHOWED THE ACTUAL ENGINE RPM AT 2,4 60 RPM. THIS MAY HAVE BEEN A LONG TERM PROBLEM AS THE ENGINE HAS BEEN TOP OVERHAULED TWICE IN 1546 HRS. 1 L 7 2 3O A7SO 1997013000446 19970130 00446 CE 1997 1 30 97ZZZX518 1 19961201 G 2434 ALV8402 ALTERNATOR CESSNA 310 310Q 2074242 CE LT ENG LOOSE TERMINAL G K NONE O OTHER IN INSP/MAINT 1 GL 03 6248Q 25839 310Q0746 ALTERNATOR'S LOOSE CONNECTION CAUSED TERMINAL TO ARC AND BURN, AND DISCONNECT. 1 L 7 2 3O 3A10 1997013000447 19970130 00447 NE 1997 1 30 97ZZZX519 2 19961015 G 8530 91532 CYLINDER SCWZER G164 G164B 3952802 EA PWA R1340 R1340AN1 52016 NE NR 7 ROCKER CRACKED G O OTHER R PARTIAL RPM/PWR LOSS CR CRUISE 1 SW 03 54229 865 160B 13823 ENGINE LOST POWER IN-FLIGHT. INVESTIGATION REVEALED THAT THE EXHAUST ROCKER HOUSING WAS CRACKED ON THE NR 7 CYLINDER. 1 Q 7 1 3R 3 R 1A16 5E2 1997013000448 19970130 00448 NE 1997 1 30 97ZZZX520 2 19961201 G 8520 327626 CYLINDER CVAC 340 340CVAC 242270A WP PWA R2800 CB16 52026 NE NR 8 CYL ROD FAILED B DJSR E A ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 GL 23 7813B 265 P32162 ON LEVEL FLIGHT AT 6,000 MSL, ENGINE BACKFIRED AND LOSS OF OIL PRESSURE. ENGINE SHUT DOWN AND RETURN TO PTK. 2 L 7 2 4R 4 R 6A6 E264 1997013000453 19970130 00453 CE 1997 1 30 97ZZZX525 1 19960120 G 2130 2481172823 MOD VALVE LEAR 35 35A 5170602 CE CABIN WIRE SHORTED B GG5R B EMER. DESCENT B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 GL 05 230R 130 WHILE ON A FLIGHT THE LEFT BLEED AIR SYSTEM WENT INTO EMERGENCY. THE AIR IN EMERGENCY IS EXTREMELY HOT. WHILE IN EMERG ENCY, THE AIRCRAFT FILLED WITH THICK SMOKE AND EMERGENCY DESCENT WAS PERFORMED. A LANDING WAS MADE WITHOUT INCIDENT. I NVESTIGATION FOUND PROBLEM OF THE AIRCRAFT GOING INTO EMERGENCY WAS CAUSED BY WIRING GOING TO MOD VALVE RELAY BRACKET (L EFT) GOT AGAINST A LINE GOING TO WINDSHIELD HEAT SYSTEM. THE SMOKE WAS CAUSED BY AN IMPROPERLY INSTALLED CARPET FROM A RECENT INTERIOR JOB BLOCKING HEAT DUCTS. 2 L 7 2 4F A10CE 1997020600180 19970206 00180 SO 1997 2 6 97ZZZX527 1 19961129 G 5245 9956100 BEARING ASSY PIPER PA32 PA32301 7103207 SO AC COND DOOR FAILED B A C7MR A UNSCHED LANDING E F VIBRATION/BUFFET FLT CONT AFFECTED CR CRUISE 1 SO 11 8470P 2710 328206010 BEARING ASSY BROKE CAUSING AIR CONDITIONER CONDENSOR DOOR TO DROP INTO THE AIRSTREAM. THIS CAUSED HEAVY VIBRATION AND A IRCRAFT BECAME HARD TO CONTROL. PILOT LANDED AT NEAREST AIRPORT. THIS HAS HAPPENED TWICE BEFORE ON THIS AIRCRAFT. SUS PECT IMPROPER DOOR RIGGING AS A FACTOR. 1 L 7 1 3O A3SO 1997020600183 19970206 00183 1997 2 6 97ZZZX529 4 19960118 G 3197 WIRE HARNESS CESSNA 650 650 2076802 CE CB PANEL ASSY SHORTED B L GJQR K NONE N FALSE WARNING IN INSP/MAINT 1 NM 01 39WP 6500039 RT HAND ENGINE FAN (N1) INDICATOR CIRCUIT BREAKER TRIPPED AND WILL NOT RESET. FOUND WIRING HARNESS IN PILOT'S CIRCUIT B REAKER PANEL ASSEMBLY CHAFING AND SHORTING TO GROUND. THE CHAFED WIRES AT THE AURAL WARNING NR 1 AND WARNING LIGHTS NR 1 CIRCUIT BREAKERS WERE FOUND TO BE CAUSED BY THE PANEL ASSEMBLY MOUNTING BRACKET AND ATTACHING HARDWARE. REPLACED AFFE CTED WIRING. REROUTED AND SECURED WIRING TO PRECLUDE ANY FURTHER PROBLEMS. 2 L 7 2 4F A9NM 1997020600184 19970206 00184 1997 2 6 97ZZZX530 4 19960118 G 3197 WIRE CESSNA 650 650 2076802 CE CB PANEL CHAFED B GJQR K NONE O OTHER IN INSP/MAINT 1 NM 01 38WP 6500039 INSP OF CB PANEL ASSY FOLLOWING FINDING CHAFED WIRING ON ANOTHER CE 650, FOUND LIKE CONDITION ON THIS ACFT. INSP CONDUC TED AT CESSNA SERVICE CENTER SACRAMENTO, CA. 2 L 7 2 4F A9NM 1997020600186 19970206 00186 CE 1997 2 6 97ZZZX531 1 19961203 G 5741 FITTING CESSNA 177 177B 2073708 CE LT WING ATTACH LOOSE D A K NONE O OTHER IN INSP/MAINT 1 EA 17 13468 2609 2609 17702424 DURING ANNUAL INSPECTION, IT WAS DISCOVERED THAT THERE WAS MOVEMENT IN THE WING ATTACH FITTINGS WHERE ATTACH PIN ATTACHE S WING TO FUSELAGE. THE AMOUNT OF MOVEMENT WAS .0035 INCH BY MEASUREMENT. 1 H 7 1 3O A13CE 1997020600189 19970206 00189 1997 2 6 97ZZZX534 4 19961231 G 3414 S1470N8 INDICATOR CESSNA 150 150D 2071810 CE AIR SPEED MISMARKED D L A K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 03 4191U 15060191 DURING ANNUAL INSP IT WAS FOUND A PIPER AIR SPEED IND WAS INSTALLED AND INCORRECTLY MARKED. CESSNA AIR SPEED IND LOCATE D AND INSTALLED. FACTORY DATA FOR MARKINGS MATCHED OLDER INST. TCD SHEET LISTS A DIFFERENT SET OF MARKINGS TO BE DISPL AYED ON INST. UNIT SENT FOR CALIB. 1 H 7 1 3O 3A19 1997020600190 19970206 00190 EU 1997 2 6 97ZZZX535 1 19961119 G 3710 211CC PUMP AIRBORNE SOCATA TB20 TB20TRINIDAD 8680695 EU PNEU SYS FAILED D K NONE O OTHER IN INSP/MAINT 1 EA 17 470SP 128 6AM2159 456 PNEUMATIC PUMP INSTALLED ON AIRCRAFT 8-5-96 ALONG WITH NEW VACUUM FILTERS. ON 11-15-96 AT 128.4 HOURS PUMP FAILED BY SE IZING AND SHEERING DRIVE SHAFT. PUMP WAS REPLACED WITH ANOTHER NEW UNIT WITH NO SYSTEM DEFECTS NOTED. (NOTE ORIGINAL P UMP REPLACED AT 1002 HOURS TIME IN SERVICE.). 1 L 7 1 3O RT A51EU 1997020600246 19970206 00246 NM 1997 2 6 97ZZZX543 1 19961220 G 5320 CHORD BOEING 727 727227 1384078 NM FS 950 STR 29R CORRODED B ERKR K NONE O OTHER IN INSP/MAINT 1 WP 07 555PE 41912 20837 DURING D-CHECK INSPECTION, DISCOVERED CORROSION ON THE STA 950, STR 29R, BELLY SKIN. A SECTION OF THE LOWER FRAME CHORD WAS TRIMMED AWAY AND REPAIR FILLERS/ANGLES WERE INSTALLED WET WITH SEALANT. REPAIR ACCOMPLISHED IAW EVERGREEN AIR CENT ER - ENGINEERING CHANGE REPAIR AUTHORIZATION NR N927TS-53-002-EAC. 2 L 7 3 4F A3WE 1997020600391 19970206 00391 CE 1997 2 6 97ZZZX547 1 19960329 G 5711 CARRY THRU SPAR BEECH 33 F33A 1151425 CE FUSELAGE CRACKED B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 5599P 6624 CE1344 INSP FOUND CRACKS IN CARRY THRU STRUCTURE. AD 95-0-03 NOT VALID BY SERIAL NUMBER. 1 L 7 1 3O 3A15 1997020600394 19970206 00394 SO 1997 2 6 97ZZZX550 1 19961126 G 3260 SWITCH PIPER PA44 PA44180 7104402 SO GEAR WARN WORN B DYTR K NONE O OTHER IN INSP/MAINT 1 SO 15 923ER 200 4496010 SWITCH ACTUATOR IS CUTTING A GROOVE IN THROTTLE RAMPS. AS IT WEARS, IT CHANGES WHEN THE GEAR HORN SOUNDS TO A POINT WHE RE IT WILL NOT SOUND AT ALL. WE MAINTAIN 5 NEW AIRCRAFT OF THIS TYPE. ALL HAVE HAD GEAR WARNING PROBLEMS. SUBMITTER R ECOMMENDS CHANGING THROTTLE RAMP MATERIAL TO SOMETHING HARDER THAN ALUMINUM. 1 L 7 2 3O A19S0 1997020600398 19970206 00398 EA 1997 2 6 97ZZZX554 1 19961126 G 5312 BULKHEAD 269D82203 SCWZER 269 269D 8059501 EA BELLCRANK PIVOT CRACKED B S A EGRR K NONE O OTHER IN INSP/MAINT 1 EA 17 330ST 870 870 0001 DURING A 100 HOUR INSPECTION A BULKHEAD CRACK WAS FOUND ON THE RIGHT SIDE OF THE LATERAL PITCH BELLCRANK. THE MOVEMENT OF THE CYCLIC LT AND RT WILL FLEX THE BULKHEAD THAT THE BELLCRANK SUPPORT IS ATTACHED. THE BELLCRANK NOW MOVES FROM SID E TO SIDE WHILE FLEXING THE CRACKS. AIRCRAFT TIME 870 HRS. SUBMITTER RECOMMENDATION. THE BULKHEAD SHOULD BE MADE OUT OF THICKER METAL AT LEAST .025 INCH. 1 G 7 1 3U 0 4H12 1997020600399 19970206 00399 EA 1997 2 6 97ZZZX555 1 19961126 G 5312 BULKHEAD SCWZER 269 269D 8059501 EA LT CYCLIC BRG CRACKED B S EGRR K NONE O OTHER IN INSP/MAINT 1 EA 17 330ST 869 869 0001 DURING 100 HR INSPECTION A CRACK WAS FOUND ON THE FWD BULKHEAD WHERE THE CYCLIC BEARING SUPPORT ATTACHES. MOVING CYCLIC FWD AND AFT YOU CAN SEE THIS LOWER LEFT CORNER FLEX, THE CRACK CAN ONLY BE SEEN FROM UNDER THE LEFT SEAT AREA. AIRCRAF T TIME 870 HRS. SUBMITTER STATES NEEDS TO HAVE THICKER METAL IN THIS AREA. 1 G 7 1 3U 0 4H12 1997020600400 19970206 00400 EA 1997 2 6 97ZZZX556 1 19961203 G 6710 BRACKET SCWZER 269 269D 8059501 EA IDLER BELLCRANK EARS CRACKED B S A EGRR K NONE O OTHER IN INSP/MAINT 1 EA 17 330ST 870 0001 INSP FOUND FWD MOUNTING EARS CRAKCED ALL THE WAY ACROSS TOP AND BOTTOM OF THE CYCLIC LATERAL PITCH IDLER BELLCRANK BRACK ET. TT 870 HRS. LOCATED UNDER CENTER SEAT. 1 G 7 1 3U 0 4H12 1997020600401 19970206 00401 SO 1997 2 6 97ZZZX557 2 19961216 G 8530 6674 VALVE UNIVAR 415 415C 0420302 NM CONT C85 C8512F 17008 SO NR 1 CYL EXH FAILED D K NONE O OTHER IN INSP/MAINT 1 SW 13 87226 399 71092 NR 1 CYLINDER SWALLOWED EXHAUST VALVE. HEAD OF VALVE EMBEDDED IN PISTON. 1 L 7 1 3O 3 O A718 E233 1997020600383 19970206 00383 SO 1997 2 6 97ZZZX570 1 19961202 G 2510 551599 HARNESS PIPER PA46 PA46350P SO PILOT LT SEAT REEL FAILED G P A A UNSCHED LANDING O OTHER LD LANDING 1 EA 13 394PM 4622153 DURING OFF-AIRPORT IMPACT WITH DAMAGE NOT CONSIDERED TO BE MAJOR, THE PILOT SHOULDER HARNESS INERTIA REEL DETACHED FROM ATTACH BRACKET. PILOT DID RECEIVE HEAD INJURIES BY IMPACT ON THE DASH. 1 L 7 1 3O RT A25SO 1997020600545 19970206 00545 1997 2 6 97ZZZX581 4 19961022 G 2565 23D182132 DISCHARGE VALVE AIRCRUISERS 22D22901151 SLIDE SPRING MISSING B ET3D K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 01 206741281 DURING OVERHAUL OF ESCAPE SLIDE ASSEMBLY FOUND DISCHARGE VALVE MISSING ITS BALL SPRING P/N 504S0023. CAUSE FOR CONDITIO N IS DUE TO ASSEMBLY ERROR DURING LAST OVERHAUL OR VALVE SERVICING. CONDITION AS STATED COULD HAVE RESULTED IN LOSS OF STORED GASSES FROM SLIDE'S INFLATION BOTTLE AND/OR HAD THE POTENTIAL FOR AN UNCOMMANDED INFLATION OF THE ESCAPE SLIDE AS SEMBLY. SUBMITTED BY B. F. GOODRICH AES SEATTLE SERVICE CENTER, REPAIR STATION NR ET3D487L. ADDITIONAL DETAILS, SKETCH ES, DRAWINGS OR COMPONENT OVERHAUL MANUAL SPECIFICATIONS ARE AVAILABLE UPON REQUEST. BFG REF SO NR 201293. 1997020600547 19970206 00547 WP 1997 2 6 97ZZZX583 1 19961115 G 5400 BANJO FITTING DOUG DC10 DC1015 3022118 WP NR 2 ENGINE DAMAGED B M2AY K NONE O OTHER IN INSP/MAINT 1 SW 07 1003L 48258 NR 4 BANJO FITTING ON NR 2 ENGINE UPPER FWD HOLE SCRATCHED. COINED AND STRESS RELIEVED AND REAMED HOLE PER S/B 5523. I NSTALLED REPAIR BUSHINGS PER DOUGLAS ACTION NR 314520. 2 L 7 3 4F A22WE 1997020600548 19970206 00548 WP 1997 2 6 97ZZZX584 1 19961115 G 5320 DOUBLER DOUG DC10 DC1015 3022118 WP FS 555-575 CORRODED B M2AY K NONE O OTHER IN INSP/MAINT 1 SW 07 1003L 48258 NOSE LANDING GEAR AREA STA 555-575 HAS POPPED RIVETS. REMOVED RIVETS, FOUND EXFOLIATED INTERNAL DOUBLER. REMOVED DOUBL ER, FABRICATED DOUBLER IAW DOUGLAS ACTION NR 315097. ALODINED AND PRIMED FILLER AND DOUBLER IAW DC 10 SRM 51-10-01 AND INSTALLED PER DOUGLAS ACTION NR 315097 AND DC10 SRM 51-41-01 AND SRM 51-31-01. 2 L 7 3 4F A22WE 1997020600549 19970206 00549 WP 1997 2 6 97ZZZX585 1 19961115 G 5347 SEAT TRACK DOUG DC10 DC1015 3022118 WP FS 279 NR 3 CRACKED B M2AY K NONE O OTHER IN INSP/MAINT 1 SW 07 1003L 48258 SEAT TRACK CRACKED AT STA 279, NR 3 TRACK. REMOVED CRACKED SECTION OF TRACK. INSTALLED NEW SECTION OF TRACK AND SPLICE S IAW DC10 SRM'S 53-70-00, 51-21-01, AND 51-31-01. 2 L 7 3 4F A22WE 1997020600550 19970206 00550 WP 1997 2 6 97ZZZX586 1 19961115 G 5347 SEAT TRACK DOUG DC10 DC1015 3022118 WP FS 899 NR 6 CRACKED B M2AY K NONE O OTHER IN INSP/MAINT 1 SW 07 1003L 48258 SEAT TRACK NR 6 AT STA 899 HAS DAMAGED HOLE. REMOVED AND REPLACED SEAT TRACK FROM STA 791-910, XS-25 IAW DC10 SRM 53-70 -00 VOL I, 51-00-00, 51-21-01, 51-31-01. 2 L 7 3 4F A22WE 1997020600551 19970206 00551 WP 1997 2 6 97ZZZX587 1 19961115 G 5330 SKIN DOUG DC10 DC1015 3022118 WP FS 1850 CORRODED B M2AY K NONE O OTHER IN INSP/MAINT 1 SW 07 1003L 48258 TEMPORARY REPAIR INSTALLED ON FUSELAGE OUTER SKIN AT STA 1850, LONGERON 31-32 RT. REMOVED TEMP REPAIR, FABRICATED REPAI R DOUBLERS IAW DC10 SRM 51-35-02 AND 53-20-00 VOL I AND INSTALLED PER DC10 SRM 51-31-01. 2 L 7 3 4F A22WE 1997020600552 19970206 00552 WP 1997 2 6 97ZZZX588 1 19961115 G 5320 FLOOR SUPPORT DOUG DC10 DC1015 3022118 WP FS 879 CORRODED B M2AY K NONE O OTHER IN INSP/MAINT 1 SW 07 1003L 48258 TEMPORARY REPAIR INSTALLED ON FLOOR SUPPORT STA 879 BETWEEN SEAT TRACKS 2 AND 3. REMOVED AND REPLACED FLOOR SUPPORT IAW DC10 SRM 51-21-01 AND 51-31-01. 2 L 7 3 4F A22WE 1997020600553 19970206 00553 WP 1997 2 6 97ZZZX589 1 19961115 G 5320 DOOR FRAME DOUG DC10 DC1015 3022118 WP CARGO DOOR CORRODED B M2AY K NONE O OTHER IN INSP/MAINT 1 SW 07 1003L 48258 TEMP REPAIR INSTALLED ON FWD CARGO DOOR FRAME Y-886 BETWEEN LONGERONS 40 AND 42R. REMOVED TEMP REPAIR, FABRICATED AND I NSTALLED PERMANENT REPAIR DOUBLERS IAW DC10 SRM 53-30-00, 51-21-01, 51-40-01 VOL I, AND 53-50-00. 2 L 7 3 4F A22WE 1997020600554 19970206 00554 WP 1997 2 6 97ZZZX590 1 19961115 G 5320 T-ANGLE DOUG DC10 DC1015 3022118 WP FS 1079 CRACKED B M2AY K NONE O OTHER IN INSP/MAINT 1 SW 07 1003L 48258 PASS COMP STA 1079 LONGERON 23-24 LT CRACKED T-ANGLE. REMOVED SHEAR TIE. STEPPED UP HOLE AT END OF CRACK IAW DC10 SRM 52-10-00. FABRICATED DOUBLERS IAW DC10 SRM 52-10-00 FIG 2 VOL I. INSTALLED DOUBLERS IAW SRM 51-21-01 VOL II, 53-00-01 FIG 2. 2 L 7 3 4F A22WE 1997020600555 19970206 00555 WP 1997 2 6 97ZZZX591 1 19961115 G 5320 SUPPORT WEB DOUG DC10 DC1015 3022118 WP FS 330-394 CRACKED B M2AY K NONE O OTHER IN INSP/MAINT 1 SW 07 1003L 48258 FLIGHT COMP FLOOR SUPPORT WEB CRACKED STA 330 AND 394 UNDER FLIGHT ENGINEER'S SEAT. STOP DRILLED CRACK IAW DC10 SRM 53- 00-01. FABRICATED DOUBLER AND INSTALLED IAW DC10 SRM 53-00-01, 51-21-01, 51-31-01. 2 L 7 3 4F A22WE 1997020600559 19970206 00559 EU 1997 2 6 97ZZZX594 1 19960809 G 5350 J3081X9FT SEAL STRIP BRAERO DH125 HS125700A 4230170 EU WING TO FUSE DEBONDED B PCPR K NONE O OTHER IN INSP/MAINT 1 WP 25 91CM 62 NA0265 WING TO FUSELAGE RUBBER SEALING STRIPS BEGAN TO UNBOND AND PULL AWAY. STRIPS WERE INSTALLED 5-7-96. PILOT REPORTED THE Y ARE A POST-FLIGHT ITEM AND WERE SECURE AT LAST PREVIOUS POST-FLIGHT. SUSPECTED CAUSE OF FAILURE TO BE IMPROPER BONDIN G OF RUBBER TO WING SURFACE. RECOMMEND BETTER GLUING TECHNIQUE. 2 L 7 2 4F A3EU 1997020600560 19970206 00560 WP 1997 2 6 97ZZZX595 1 19961115 G 5347 SEAT TRACK DOUG DC10 DC1015 3022118 WP FS 1844-2007 CORRODED B M2AY K NONE O OTHER IN INSP/MAINT 1 SW 07 1003L 48258 STA 2007 ANGLE REPAIR HAS IMPROPER FASTENERS AND INSUFFICIENT AMOUNT OF FASTENERS INSTALLED AND SEAT TRACK IS CORRODED F ROM STA 1844-2007. REMOVED AND REPLACED SEAT TRACK IAW DC10 SRM 53-70-00 VOL 1. INSTALLED CORRECT AMOUNT AND TYPE OF F ASTENERS IN ANGLE REPAIR IAW DC10 SRM 51-35-01. 2 L 7 3 4F A22WE 1997020600561 19970206 00561 WP 1997 2 6 97ZZZX596 1 19961115 G 5320 FLOOR SUPPORT DOUG DC10 DC1015 3022118 WP FS 475 CRACKED B M2AY K NONE O OTHER IN INSP/MAINT 1 SW 07 1003L 48258 FLOOR SUPPORT STA 475 LT AND RT OF TRACK NR 2 CRACKED. REMOVED AND FABRICATED NEW SUPPORT IAW DC10 SRM 51-30-01 VOL II. ALODINED AND PRIMED AND INSTALLED SUPPORT IAW DC10 SRM 51-21-01 AND 51-31-01 VOL II. 2 L 7 3 4F A22WE 1997021300046 19970213 00046 EU 1997 2 13 97ZZZX599 1 19961104 G 7120 MOUNT GENAVI F22B F22B 3840101 EU ABOVE NLG STRUT CRACKED B BONR K NONE O OTHER IN INSP/MAINT 1 GL 19 706LA 347 003 DURING PRE-FLIGHT, STUDENT NOTICED ENGINE MOUNT CRACKED ABOVE NLG STRUT. OPENED LT COWL AND FOUND MOUNT ALSO CRACKED BE LOW LT LOWER CLUSTER WELD. RECOMMEND MAKING MOUNT OUT OF HEAVIER MATERIAL. 1 L 7 1 3O NT A75EU 1997010900099 19970109 00099 CE 1997 1 9 97ZZZX6 1 19961213 G 2730 081308114 ROD ASSY CESSNA 310 310R 2074245 CE ELEV BOB WT RUSTED B AZVR K NONE O OTHER IN INSP/MAINT 1 SO 01 3687G 4224 310R0893 ROD ASSY WHICH HOLDS ELEVATOR BOB WEIGHT FOUND RUSTED THROUGH. APPEARS TO HAVE RUSTED FROM INSIDE TUBE AS WELL AS SURFA CE RUST ON OUTSIDE. HOLE COMPLETELY THROUGH WALL THICKNESS OF TUBE. 1 L 7 2 3O 3A10 1997021300052 19970213 00052 CE 1997 2 13 97ZZZX605 1 19961218 G 5541 04330106 SPAR CESSNA 150 152 2071835 CE RUDDER CRACKED D S K NONE O OTHER IN INSP/MAINT 1 EA 25 49158 838 15281171 WHILE PERFORMING 100 HR INSP RUDDER SPAR FOUND WITH 4 CRACKS RADIATING FROM STAMPED HOLE NEAR UPPER HINGE BRACKET. 1 H 7 1 3O NT 3A19 1997021300053 19970213 00053 CE 1997 2 13 97ZZZX606 1 19961226 G 2410 COUPLING LORD CESSNA 421 421C 2076016 CE ALTERNATOR FAILED D E A ENGINE SHUTDOWN UNSCHED LANDING J H WARNING INDICATION ELECT. POWER LOSS-50 PC CL CLIMB 1 GL 19 421HP 795 421C0831 ON CLIMB-OUT THE RIGHT ALTERNATOR WENT OFF LINE. SOON AFTER THE OIL PRESSURE STARTED TO DECREASE AND THE OIL TEMP START ED TO INCREASE, THE PILOT FEATHERED THE RIGHT ENGINE AND LANDED AT NEXT AIRPORT. INVESTIGATION REVEALED THAT THE ALTERN ATOR HAD FAILED INTERNALLY AT THE DRIVE HUB ASSY, P/N 646655. RED RUBBER MATERIAL DISINTEGRATED AND WENT INTO THE OIL P AN AND WAS SUCKED INTO THE OIL SUMP PLUGGING THE SCREEN. 1 L 7 2 3O A7CE 1997021300057 19970213 00057 WP 1997 2 13 97ZZZX610 1 19961115 G 5730 RETAIN RING DOUG DC10 DC1015 3022118 WP WS XORS 750 DAMAGED B M2AY K NONE O OTHER IN INSP/MAINT 1 SW 07 1003L 48258 DAMAGED AND ELONGATED HOLE AT WING. STA XORS 750 ON FUEL PLATE RETAINING RING STRUCTURE. COLD WORKED HOLE PER DOUGLAS ACTION NR 312451. FABRICATED AND INSTALLED BUSHING PER DOUGLAS ACTION NR 312451. INSTALLED RUB STRIP IAW DC10 SRM 51-4 2-04. 2 L 7 3 4F A22WE 1997021300060 19970213 00060 1997 2 13 97ZZZX613 4 19960120 G 3442 POWER SUPPLY CESSNA 208 208B 2073701 CE WX RADAR FAILED D K NONE B SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 SW 15 750FX 453 453 208B0511 PILOT REPORTED WHILE TAXIING ACFT, HEARD A LOUD 'POP' AND THE COCKPIT FILLED WITH ELECTRICAL SMOKE. MAINT WAS DISPATCHE D TO THE ACFT. UPON ARRIVAL, FOUND NO SMOKE OR ELECTRICAL SMELL IN THE CABIN. MX STARTED THE ACFT ENG AND ALL SYSTEMS, NO DISCREPANCIES NOTED. REMOVED CIRCUIT BREAKER PANEL AND GAINED ACCESS TO CIRCUIT BREAKERS, BUSS BARS AND ASSOCIATED WIRING, INST PANEL SWITCHES, AND NO DISCREPANCIES NOTED. TEST FLIGHT COULD NOT DUPLICATE THE PROBLEM. IT WAS NOTED THE WEATHER RADAR INDICATOR WAS INTERMITTENT. THE SYS WAS PROPERLY DEFERRED AND ACFT WAS RETURNED TO SERVICE. UPON REPAIR OF THE WX RADAR INDICATOR IT WAS NOTED THE POWER SUPPLY WAS SHORTED. 1 H 7 1 3T A37CE 1997010200641 19970102 00641 NE 1997 1 2 97ZZZX6189 3 19961211 G 6111 SFA13M10A BLADE HAMSTD 14SF 14SF5 NE SHANK CRACKED H K NONE O OTHER IN INSP/MAINT 1 WP 05 8983 8761645 INSPECTION FOUND BLADE SHANK CRACKED AT FILLET AREA. BLADE RETURNED TO HAM STD FOR EVALUATION. 6 C P7NE 1997021300066 19970213 00066 CE 1997 2 13 97ZZZX619 1 19960101 G 5330 SKIN MTSBSI MU2 MU2B36A 5780413 CE FS 4610 CRACKED D A K NONE O OTHER IN INSP/MAINT 1 NE 05 994PE 714SA PERFORMING 100 HR INSPECTION, DEFORMATION OF FUSELAGE SKIN WAS NOTED ABOVE BOTH MAIN GEAR ATTACH POINTS. FURTHER INSP W AS REQUIRED AND THE INTERIOR WALLS OF THE ACFT WERE REMOVED. CRACKS WERE FOUND IN FUSELAGE FRAMES AT FS 4610, 4850, AND 5605. INSPECT AND REPAIR OF THIS AREA IS COVERED MITSUBISHI SB NR 073/53-002A, DATED 8-12-94. THIS PARTICULAR ACFT HA S DAMAGE IN THESE AREAS BEYOND THE APPROVED REPAIRABLE LIMITS IN THE SB. 1 H 7 2 3T A10SW 1997010200642 19970102 00642 EA 1997 1 2 97ZZZX6190 2 19961201 G 8520 LW12186 BOLT PIPER PA28 PA28180 7102808 SO LYC O360 O360A4A 41514 EA CON ROD FAILED G K NONE O OTHER IN INSP/MAINT 1 SO 19 9545J 283693 L1040436A ROD BOLT NUTS BACKED OFF AND CONNECTING ROD BOLTS BROKE. SUSPECT CAUSE WAS IMPROPER INSTALLATION OF CONNECTING ROD BOLT NUTS. RECOMMENDATION: RE-VISIT OR RE-ISSUE LYCOMING SI NR 1106D, DATED 6-9-72. 1 L 7 1 3O 3 O 2A13 E286 1997010200643 19970102 00643 WP 1997 1 2 97ZZZX6191 2 19961113 G 7260 31030351 BEARING 31036016 GARRTT TPE331 TPE33112UHR WP ASSORY GRBOX FAILED B AE0R K NONE O OTHER IN INSP/MAINT 1 SO 03 689 951991425009 P66362C ENGINE RECEIVED FROM AIR CARRIER FOR THIS REPAIR. REPAIR STA NOT SURE IF THERE WAS AN IN-FLIGHT SHUT DOWN OCCURRENCE. R EPAIR OF ENGINE WAS TO REPLACE ACCESSORY GEAR ASSEMBLY WITH OVERHAULED UNIT OF SAME PART NUMBER, CONTAINING NEW 3103035- 1 BEARINGS. THESE BEARINGS ARE LIFE LIMITED PARTS. (CURRENTLY TIED TO OVERHAUL OR CAM INTERVAL). ALLIED SIGNAL HAS IS SUED A SB, TPE331-72-0997, THAT SUPERSEDES THE ACCESSORY GEAR ASSEMBLY WITH AN IMPROVED PART, USING LARGER BEARINGS. RE PAIR STA DID NOT INCORPORATE THIS SB, HOWEVER. 4 T E4WE 1997010200644 19970102 00644 CE 1997 1 2 97ZZZX6192 1 19961127 G 7500 635404767 TUBE CESSNA 525 525 2076601 CE WILINT FJ44 FJ44 66000 GL RT ENG BLEED BROKEN D K NONE O OTHER IN INSP/MAINT 1 CE 07 229CJ 361 5250129 1268 PILOT REPORTED RT ENG ITT PROBLEMS. INSP FOUND RT ENG OUTB BLEED AIR TUBE BROKEN IN FLEX TUBE AREA. REPLACED TUBE, OPS CHECK OK. 1 L 7 2 4F 4 F RT A1WI E3GL 1997010200645 19970102 00645 GL 1997 1 2 97ZZZX6193 3 19961105 G 6110 A4001 DOWEL PIN CESSNA 337 337 2075702 CE MCAULY 2AF34C D2AF34C61 GL PROPELLER CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 753558 INSPECTION FOUND DOWEL PIN CORRODED. 1 H 7 2 3O A6CE 5 C P5EA 1997010200646 19970102 00646 GL 1997 1 2 97ZZZX6194 3 19961105 G 6110 C3274 CYLINDER CESSNA 337 337 2075702 CE MCAULY 2AF34C D2AF34C61 GL PROP WORN B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 753558 INSPECTION FOUND PROPELLER CYLINDER WORN. 1 H 7 2 3O A6CE 5 C P5EA 1997010200647 19970102 00647 GL 1997 1 2 97ZZZX6195 3 19961105 G 6114 A3267 BUSHING CESSNA 337 337 2075702 CE MCAULY 2AF34C D2AF34C61 GL HUB WORN B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 753558 INSPECTION FOUND PROPELLER BUSHING WORN. 1 H 7 2 3O A6CE 5 C P5EA 1997010200648 19970102 00648 GL 1997 1 2 97ZZZX6196 3 19961105 G 6110 C3550 CYLINDER CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL HUB CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 2780 1480 746034 INSPECTION FOUND PROP CYLINDER CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997010200649 19970102 00649 GL 1997 1 2 97ZZZX6197 3 19961105 G 6114 D7015C87 HUB CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER DEFECTIVE B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 2780 1480 746034 INSPECTION FOUND HUB ASSY DEFECTIVE (WRONG APLICATION). 1 L 7 2 3O 3A10 5 C P22EA 1997010200650 19970102 00650 GL 1997 1 2 97ZZZX6198 3 19961105 G 6110 A1896 PROP ASSY CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL HUB CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 2780 771292 INSPECTION FOUND PROP ASSY P/N A1896 CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997010200651 19970102 00651 GL 1997 1 2 97ZZZX6199 3 19961105 G 6110 A4191 PROP ASSY CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL HUB CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 2780 771292 INSPECTION FOUND PROP ASSY P/N A4191 CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997010200652 19970102 00652 GL 1997 1 2 97ZZZX6200 3 19961105 G 6110 D3474 PROP ASSY CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL HUB WORN B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 2780 771292 INSPECTION FOUND PRO ASSY P/N D3474 WORN. 1 L 7 2 3O 3A10 5 C P22EA 1997010200653 19970102 00653 GL 1997 1 2 97ZZZX6201 3 19961105 G 6111 S82NC55 BLADE CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROP DAMAGED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 2780 F73000YS 771292 INSPECTION FOUND PROP BLADE DAMAGED. 1 L 7 2 3O 3A10 5 C P22EA 1997010200654 19970102 00654 GL 1997 1 2 97ZZZX6202 3 19961105 G 6114 D7015C87 HUB CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL NR 1 SOCKET CRACKED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 791322 INSPECTION FOUND NR 1 BLADE SOCKET CRACKED. 1 L 7 2 3O 3A10 5 C P22EA 1997010200655 19970102 00655 GL 1997 1 2 97ZZZX6203 3 19961105 G 6114 D7015C87 HUB CESSNA 310 310P 2074238 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 1229 673758 INSPECTION FOUND PROP HUB CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997010200656 19970102 00656 GL 1997 1 2 97ZZZX6204 3 19961105 G 6111 C4451 FERRULE CESSNA 310 310P 2074238 CE MCAULY 3AF32C 3AF32C87 GL BLADE CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 1229 673758 INSPECTION FOUND BLADE FERRULE CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997010200657 19970102 00657 GL 1997 1 2 97ZZZX6205 3 19961105 G 6114 B4459 ACTUATOR PIN CESSNA 310 310P 2074238 CE MCAULY 3AF32C 3AF32C87 GL HUB CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 696 727378 INSPECTION FOUND ACTUATOR PIN CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997010200658 19970102 00658 GL 1997 1 2 97ZZZX6206 3 19961105 G 6110 B3490 PROP ASSY CESSNA 310 310P 2074238 CE MCAULY 3AF32C 3AF32C87 GL HUB CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 696 727378 INSPECTION FOUND PROP ASSY CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997010200659 19970102 00659 GL 1997 1 2 97ZZZX6207 3 19961105 G 6110 C3550 CYLINDER CESSNA 310 310P 2074238 CE MCAULY 3AF32C 3AF32C87 GL HUB CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 696 727378 INSPECTION FOUND PROP CYLINDER CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997010200660 19970102 00660 GL 1997 1 2 97ZZZX6208 3 19961105 G 6110 A1896 PROP ASSY CESSNA 310 310P 2074238 CE MCAULY 3AF32C 3AF32C87 GL HUB CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 696 727378 INSPECTION FOUND PROP ASSY CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997010200661 19970102 00661 GL 1997 1 2 97ZZZX6209 3 19961105 G 6110 A4191 PROP ASSY CESSNA 310 310P 2074238 CE MCAULY 3AF32C 3AF32C87 GL HUB CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 696 727378 INSPECTION FOUND PROP ASSY CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997010200662 19970102 00662 GL 1997 1 2 97ZZZX6210 3 19961105 G 6111 S82NC4 BLADE CESSNA 310 310P 2074238 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 696 BG397YS 727378 INSPECTION FOUND PROPELLER BLADE CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997010200663 19970102 00663 GL 1997 1 2 97ZZZX6211 3 19961105 G 6111 C4451 FERRULE CESSNA 310 310P 2074238 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER DEFECTIVE B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 696 727378 INSPECTION FOUND PROP BLADE FERRULE CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997010200664 19970102 00664 GL 1997 1 2 97ZZZX6212 3 19961105 G 6110 A1896 PROP ASSY CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL HUB CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 2780 1480 746034 INSPECTION FOUND PROP ASSY CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997010200665 19970102 00665 GL 1997 1 2 97ZZZX6213 3 19961105 G 6110 A4191 PROP ASSY CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL HUB CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 2780 1480 746034 INSPECTION FOUND PROP ASSY CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997010200666 19970102 00666 GL 1997 1 2 97ZZZX6214 3 19961105 G 6110 B2345 PISTON ROD CESSNA 182 182R 2072731 CE MCAULY 2D34C B2D34C219 GL PROPELLER CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 7910786 PROPELLER INSPECTION FOUND PISTON ROD CORRODED. 1 L 7 1 3O NT 3A13 5 C P7EA 1997010200667 19970102 00667 1997 1 2 97ZZZX6215 4 19961105 G 6113 C5046 BULKHEAD CESSNA 182 182R 2072731 CE MCAULY 2D34C B2D34C219 GL SPINNER CRACKED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 7910786 INSPECTION FOUND PROPELLER SPINNER BULKHEAD CRACKED. 1 L 7 1 3O NT 3A13 5 C P7EA 1997010200668 19970102 00668 GL 1997 1 2 97ZZZX6216 3 19961105 G 6110 C2463 NUT BEECH 36 36BEECH 1151602 CE MCAULY 2A36C 2A36C23 GL PROPELLER CRACKED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 641006 INSPECTION FOUND PROPELLER RETAIN NUT CRACKED. 1 L 7 1 3O 3A15 5 C P880 1997010200669 19970102 00669 GL 1997 1 2 97ZZZX6217 3 19961105 G 6110 B2345 PISTON ROD CESSNA 182 182P 2075816 CE MCAULY 2A34C 2A34C203 GL PROPELLER WORN B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 870628 INSPECTION FOUND PISTON ROD WORN. 1 H 7 1 3O NT TA13 5 C P3EA 1997010200670 19970102 00670 GL 1997 1 2 97ZZZX6218 3 19961105 G 6114 A4001 DOWEL PIN CESSNA 182 182P 2075816 CE MCAULY 2A34C 2A34C203 GL PROPELLER CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 870628 PROPELLER INSPECTION FOUND DOWEL PIN CORRODED. 1 H 7 1 3O NT TA13 5 C P3EA 1997010200671 19970102 00671 GL 1997 1 2 97ZZZX6219 3 19961105 G 6111 BLADE BEECH 33 F33A 1151425 CE MCAULY 3A32C 3A32C76 GL PROPELLER CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 K91889YS 781601 PROPELLER INSPECTION FOUND BLADE CORROSION. 1 L 7 1 3O 3A15 5 C P21EA 1997010200672 19970102 00672 GL 1997 1 2 97ZZZX6220 3 19961105 G 6111 BLADE BEECH 33 F33A 1151425 CE MCAULY 3A32C 3A32C76 GL PROPELLER CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 K92027YS 781601 PROPELLER INSPECTION FOUND BLADE CORROSION. 1 L 7 1 3O 3A15 5 C P21EA 1997010200673 19970102 00673 GL 1997 1 2 97ZZZX6221 3 19961105 G 6111 BLADE BEECH 33 F33A 1151425 CE MCAULY 3A32C 3A32C76 GL PROPELLER CORRODED B EY2R K NONE O OTHER IN INSP/MAINT 1 GL 03 K91828YS 781601 PROPELLER INSPECTION FOUND BLADE CORROSION. 1 L 7 1 3O 3A15 5 C P21EA 1997021300070 19970213 00070 CE 1997 2 13 97ZZZX623 1 19960120 G 3240 S288930103 LINE 26820011 CESSNA 208 208B 2073701 CE BRAKE CYL COLLAPSED D A K NONE W INADEQUATE Q C TX TAXI/GRND HDL 1 SW 15 886FE 3982 208B0190 PILOT REPORTED UPON LANDING AND MAKING A HARD RIGHT TURN AND HARD BRAKING THE RIGHT BRAKE WOULD NOT RELEASE. MAINT FOUN D THE RIGHT BRAKE RELEASED. UPON FURTHER INSPECTION, MAINT FOUND THE RIGHT BRAKE MASTER CYLINDER UPPER SUPPLY FLEXIBLE LINE COLLAPSED AT THE BEND RADIUS. 1 H 7 1 3T A37CE 1997021300462 19970213 00462 WP 1997 2 13 97ZZZX676 1 19961223 G 5330 59363603 SKIN DOUG DC9 DC983 3022083 WP BS 817 CORRODED B K NONE O OTHER IN INSP/MAINT 1 WP 07 9420D 19271 49824 DURING C-CHECK INSPECTION, DISCOVERED EXFOLIATION CORROSION ON THE LOWER FUSELAGE KEEL BEAM EXTERNAL SKIN ALONG THE AREA OF CONTACT BETWEEN THE WING/BODY FAIRING. THE CORRODED AREA IS LOCATED AT THE CENTER OF THE EXTERNAL KEEL BEAM SKIN SU RFACE AT LONGERON 30L, 4.0 INCHES AFT OF BS 817. BLENDED, NDT INSPECTED AND INSTALLED REPAIR DOUBLER. ACCOMPLISHED IAW EVERGREEN AIR CENTER - ENGINEERING CHANGE/REPAIR AUTHORIZATION NR N9420-53-003-EAC. 2 L 7 2 4F RT A6WE 1997021300463 19970213 00463 WP 1997 2 13 97ZZZX677 1 19961223 G 5330 593666751 SKIN DOUG DC9 DC983 3022083 WP BS 1211-1231 CORRODED B K NONE O OTHER IN INSP/MAINT 1 WP 07 9420D 19271 49824 DURING C-CHECK INSPECTION, DISCOVERED EXFOLIATION CORROSION ON THE FUSELAGE SKIN AT STA 1211 - STA 1231, BETWEEN LONGERO NS 29R AND 30R. TRIMMED OUT DAMAGE, NDT INSPECTED AND INSTALLED REPAIR FILLERS AND DOUBLERS. ACCOMPLISHED IAW EVERGREE N AIR CENTER - ENGINEERING CHANGE/REPAIR AUTHORIZATION NR N9420-53-010-EAC. 2 L 7 2 4F RT A6WE 1997021300465 19970213 00465 CE 1997 2 13 97ZZZX679 1 19960607 G 2750 MS252015 SWITCH CESSNA 172 172M 2072418 CE FLAP MALFUNCTION G L A A UNSCHED LANDING O OTHER CL CLIMB 1 NM 11 9594V 17264396 THE AIRPLANE CRASHED 18-19 SECONDS AFTER BECOMING AIRBORNE. THE AIRCRAFT IMPACTED TERRAIN BEYOND THE DEPARTURE END OF T HE RUNWAY. FLAPS WERE FULLY DOWN AT THE ACCIDENT SCENE. THE FLAP SWITCH WAS REMOVED AND SENT TO CESSNA FOR FUNCTIONAL TESTING. THIS SWITCH INCORPORATES A 'SPRING-RETURN' MECHANISM TO RETURN IT TO NEUTRAL POSITION AFTER BEING RELEASED FRO M THE EXTEND POSITION. CESSNA REPORTED THAT THE SWITCH DEMONSTRATED PROPER ELECTRICAL FUNCTION, BUT IMPROPER MECHANICAL OPERATION (THE SWITCH DID NOT RETURN TO NEUTRAL WHEN RELEASED FROM EXTEND) 'DUE TO THE SPRING RETURN MECHANISM MALFUNCT IONING'. 1 H 7 1 3O NT 3A12 1997021300468 19970213 00468 1997 2 13 97ZZZX682 1 19960916 G 3710 2B729 PUMP AIRBORNE VAC SYS SHAFT WORN D K NONE O OTHER IN INSP/MAINT 1 GL 13 6AC232 VAC PUMP ARMATURE SHAFT WORN. PUMP MAY HAVE BEEN RUN DRY. 1997021300472 19970213 00472 CE 1997 2 13 97ZZZX686 1 19961111 G 5712 05232332 RIB CESSNA 172 172I 2072426 CE RT WING CORRODED B A5OR K NONE O OTHER IN INSP/MAINT 1 SO 09 894 5154 17257119 FOUND SURFACE TRAILING EDGE RIB'S CORRODED THROUGH IN RT WING. REPLACED PARTS WITH NEW CESSNA PARTS. PARTS NOT PROTECT EDY WITH PRIMER BY CESSNA. 1 H 7 1 3O NT 3A12 1997021300473 19970213 00473 CE 1997 2 13 97ZZZX687 1 19961111 G 5511 053200150 RIB CESSNA 172 172I 2072426 CE HORIZ STAB CORRODED B A5OR K NONE O OTHER IN INSP/MAINT 1 SO 09 894 5154 17257119 FOUND HEAVY INTERGRANULAR CORROSION IN HORIZONTAL STABILIZER NOSE RIBS. REMOVED AND REPLACED PARTS. AIRCRAFT WAS BASED IN CENTRAL FLORIDA. PARTS HAD NO PRIMER PROTECTION AT TIME OF MANUFACTURE. 1 H 7 1 3O NT 3A12 1997021300474 19970213 00474 CE 1997 2 13 97ZZZX688 1 19961111 G 5711 05230413 SPAR CESSNA 172 172I 2072426 CE LT WS 137-148 CORRODED B A5OR K NONE O OTHER IN INSP/MAINT 1 SO 09 894 5154 17257119 HEAVY SURFACE CORROSION ON AFT SPAR OF LT WING BETWEEN STA 148-137. REMOVED AND REPLACED PART. AIRCRAFT WAS BASED IN C ENTRAL FLORIDA. PART HAD NO PRIMER PROTECTION FROM FACTORY. 1 H 7 1 3O NT 3A12 1997021300475 19970213 00475 CE 1997 2 13 97ZZZX689 1 19961111 G 5711 05230413 SPAR CESSNA 172 172I 2072426 CE WS 105 CORRODED B A5OR K NONE O OTHER IN INSP/MAINT 1 SO 09 894 5154 17257119 CORROSION ON AFT SPAR CHANNEL STA 105. REMOVED AND REPLACED PART. AIRCRAFT WAS BASED IN CENTRAL FLORIDA. PARTS DID NO T HAVE ANY PRIMER PROTECTION FROM FACTORY. 1 H 7 1 3O NT 3A12 1997021300476 19970213 00476 CE 1997 2 13 97ZZZX690 1 19961111 G 5711 05230151 SPAR CESSNA 172 172I 2072426 CE LT WING CORRODED B A5OR K NONE O OTHER IN INSP/MAINT 1 SO 09 894 5154 17257119 HEAVY INTERGRANULAR CORROSION ON OUTBOARD SPAR CHANNEL LT WING. RMEOVED ADN REPLACED PART. AIRCRAFT BASED IN CENTRAL F LORIDA. WINGS DID NOT HAVE ANY PRIMER PROTECTION FROM FACTORY. 1 H 7 1 3O NT 3A12 1997021300477 19970213 00477 CE 1997 2 13 97ZZZX691 1 19961111 G 2752 05226304 BRACKET CESSNA 172 172I 2072426 CE FLAP MOTOR CORRODED B A5OR K NONE O OTHER IN INSP/MAINT 1 SO 09 894 5154 17257119 HEAVY INTERGRANULAR CORROSION FOUND ON LOWER FLAP MOTOR BRACKET AT BOLT HOLE. REMOVED AND REPLACED PART. AIRCRAFT WAS BASED IN CENTRAL FLORIDA. PARTS WERE NOT PROTECTED WITH PRIMER AT TIME OF MANUFACTURE. 1 H 7 1 3O NT 3A12 1997021300478 19970213 00478 CE 1997 2 13 97ZZZX692 1 19961111 G 5712 05235154 RIB CESSNA 172 172I 2072426 CE WS 190 CORRODED B A5OR K NONE O OTHER IN INSP/MAINT 1 SO 09 894 5154 17257119 NOSE RIB CORRODED THROUGH AT STA 190 OF LT WING. AIRCRAFT WAS BASED IN FLORIDA WITH NO FACTORY PROTECTION OF PARTS INSI DE OF WINGS. 1 H 7 1 3O NT 3A12 1997021300479 19970213 00479 CE 1997 2 13 97ZZZX693 1 19961111 G 5720 05230142 CHANNEL CESSNA 172 172I 2072426 CE RT WS 26 CORRODED B A5OR K NONE O OTHER IN INSP/MAINT 1 SO 09 894 5154 17257119 FOUND RIVETS POPPED ON THE LEADING EDGE OF RT WING AT STA 26. RMEOVED AND REPLACED PART. AIRCRAFT WAS BASED IN CENTRAL FLORIDA. PARTS WERE NOT PROTECTED WITH PRIMER AT TIME OF MANUFACTURE. 1 H 7 1 3O NT 3A12 1997021300480 19970213 00480 CE 1997 2 13 97ZZZX694 1 19961111 G 5711 052302012 SPAR CAP CESSNA 172 172I 2072426 CE RT WING CORRODED B A5OR K NONE O OTHER IN INSP/MAINT 1 SO 09 894 5154 17257119 HEAVY INTERGRANULAR AND SURFACE CORROSION FOUND IN RT WING FWD SPAR CAP. REMOVED AND PRELACED PART WITH NEW CESSNA PART . AIRCRAFT WAS BASED IN CENTRAL FLORIDA. PARTS WERE NOT PROTECTED WITH PRIMER AT TIME OF MANUFACTURE. 1 H 7 1 3O NT 3A12 1997021300481 19970213 00481 CE 1997 2 13 97ZZZX695 1 19961111 G 5711 05230142 SPAR CHANNEL CESSNA 172 172I 2072426 CE RT WING CORRODED B A5OR K NONE O OTHER IN INSP/MAINT 1 SO 09 894 5154 17257119 HEAVY INTERGRANULAR AND SURFACE CORROSION WAS FOUND ON FWD SPAR CHANNEL OF RT WING. REMOVED AND REPLACED PART WITH NEW CESSNA PART. AIRCRAFT WAS BASED IN CENTRAL FLORIDA. NO PRIMER PROTECTION. 1 H 7 1 3O NT 3A12 1997021300482 19970213 00482 CE 1997 2 13 97ZZZX696 1 19961111 G 5711 05230152 SPAR CHANNEL CESSNA 172 172I 2072426 CE RT WING CORRODED B A5OR K NONE O OTHER IN INSP/MAINT 1 SO 09 894 5154 17257119 HEAVY INTERGRANULAR AND SURFACE CORROSION WAS FOUND ON FWD SPAR CHANNEL OF RT WING. REMOVED AND REPLACED SPAR CHANNEL W ITH NEW CESSNA PART. AIRCRAFT WAS BASED IN CENTRAL FLORIDA. PARTS NOT PROTECTED WITH PRIMER BY CESSNA. 1 H 7 1 3O NT 3A12 1997021300483 19970213 00483 CE 1997 2 13 97ZZZX697 1 19961111 G 5711 05111625 SPAR CESSNA 172 172I 2072426 CE FWD CABIN CORRODED B A5OR K NONE O OTHER IN INSP/MAINT 1 SO 09 894 5154 17257119 DURING A PRELIMINARY INSPECTION ON THE AIRCRAFT, HEAVY INTERGRANULAR CORROSION WAS FOUND IN THE FWD CABIN SPAR. PART WA S REMOVED AND REPLACED. AIRCRAFT WAS BASED IN CENTRAL FLORIDA. NO PRIMER ON INTERNAL PARTS BY CESSNA. 1 H 7 1 3O NT 3A12 1997021300484 19970213 00484 CE 1997 2 13 97ZZZX698 1 19961111 G 5711 051212478 SPAR CESSNA 172 172I 2072426 CE AFT CABIN CORRODED B A5OR K NONE O OTHER IN INSP/MAINT 1 SO 09 894 5154 17257119 DURING A PRELIMINARY INSPECTION OF AIRCRAFT. HEAVY INTERGRANULAR CORROSION WAS FOUND IN THE AFT CABIN SPAR HAT SECTION. PART WAS REMOVED AND REPLACED. AIRCRAFT WAS BASED IN CENTRAL FLORIDA. NO PRIMER PROTECTION NOTED. 1 H 7 1 3O NT 3A12 1997021300485 19970213 00485 CE 1997 2 13 97ZZZX699 1 19961218 G 5712 05230271 RIB CESSNA 172 172P 2072436 CE LT WING CORRODED B A5OR K NONE O OTHER IN INSP/MAINT 1 SO 09 64688 5864 17275609 FOUND HEAVY TO SEVERE CORROSION, POPPED RIVETS, THROUGHOUT WING. INTERNAL PARTS WERE NOT PRIMED DURING MANUFACTURE. RE PLACED PART, CLEANED, TREATED, AND PRIMED WITH EPOXY PRIMER. RECOMMEND CESSNA DO LIKEWISE. 1 H 7 1 3O NT 3A12 1997010900100 19970109 00100 CE 1997 1 9 97ZZZX7 1 19961216 G 3213 12414232 SADDLE CESSNA 210 210D 2073414 CE MLG CRACKED B FC6R K NONE O OTHER IN INSP/MAINT 1 NM 11 3815Y 1547 21058315 INSPECTION FOUND LANDING GEAR SADDLE CRACKED AT ACTUATOR ATTACH. 1 H 7 1 3O 3A21 1997021300486 19970213 00486 CE 1997 2 13 97ZZZX700 1 19961218 G 5730 05230119 SKIN CESSNA 172 172P 2072436 CE LT WING CORRODED B A5OR K NONE O OTHER IN INSP/MAINT 1 SO 09 67688 5864 17275609 FOUND HEAVY TO SEVERE CORROSION, POPPED RIVETS, THROUGHOUT THIS WING ASSY. THE INTERNAL PARTS OF WING WERE NOT PROTECTE D FROM CORROSION DURING MANUFACTURE. REPLACED PART, CLEANED, TREATED, AND PRIMED WITH EPOXY PRIMER. RECOMMEND CESSNA D O LIKEWISE. 1 H 7 1 3O NT 3A12 1997021300487 19970213 00487 CE 1997 2 13 97ZZZX701 1 19961218 G 5730 05230295 SKIN CESSNA 172 172P 2072436 CE LT WING LE CORRODED B A5OR K NONE O OTHER IN INSP/MAINT 1 SO 09 64688 5864 17275609 FOUND HEAVY TO SEVERE CORROSION, POPPED RIVETS, THROUGHOUT WING ASSEMBLY. THE INTERNAL PARTS OF WING WERE NOT PROTECTED FROM THE DAMAGING EFFECTS OF CORROSION DURING MANUFACTURE. REPLACED PART, CLEANED, TREATED, AND PRIMED WITH EPOXY PRIM ER. RECOMMEND CESSNA DO LIKEWISE. 1 H 7 1 3O NT 3A12 1997021300488 19970213 00488 CE 1997 2 13 97ZZZX702 1 19961218 G 5730 052302825 SKIN CESSNA 172 172P 2072436 CE LT WING LE CORRODED B A5OR K NONE O OTHER IN INSP/MAINT 1 SO 09 64688 5864 17275609 FOUND HEAVY TO SEVERE CORROSION, POPPED RIVETS THROUGHOUT WING ASSEMBLY. THE INTERNAL PARTS OF WING WERE NOT PROTECTED FROM THE DAMAGING EFFECTS OF CORROSION DURING MANUFACTURE. REPLACED PART, CLEANED, TREATED, AND PRIMED WITH EPOXY PRIME R. RECOMMEND CESSNA DO LIKEWISE. 1 H 7 1 3O NT 3A12 1997021300489 19970213 00489 CE 1997 2 13 97ZZZX703 1 19961218 G 5730 05230118 SKIN CESSNA 172 172P 2072436 CE RT WING CORRODED B A5OR K NONE O OTHER IN INSP/MAINT 1 SO 09 64688 5864 17275609 FOUND HEAVY TO SEVERE CORROSION, POPPED RIVETS, THROUGHOUT WING ASSEMBLY. THE INTERNAL PARTS OF THE WING WERE NOT PROTE CTED FROM THE DAMAGING EFFECTS OF CORROSION DURING MANUFACTURE. REPLACED PART, CLEANED, TREATED, AND PRIMED WITH EPOXY PRIMER. RECOMMEND CESSNA DO LIKEWISE. 1 H 7 1 3O NT 3A12 1997021300490 19970213 00490 CE 1997 2 13 97ZZZX704 1 19961218 G 5730 05230294 SKIN CESSNA 172 172P 2072436 CE RT WING LE CORRODED B A5OR K NONE O OTHER IN INSP/MAINT 1 SO 09 64688 5864 17275609 FOUND HEAVY TO SEVERE CORROSION THROUGHOUT WING ASSEMBLY. INTERNAL PARTS OF WING WERE NOT PROTECTED FROM THE DAMAGING E FFECTS OF CORROSION DURING MANUFACTURE. REPLACED PART, CLEANED, TREATED, AND PRIMED WITH EPOXY PRIMER. RECOMMEND CESSN A DO LIKEWISE. 1 H 7 1 3O NT 3A12 1997021300491 19970213 00491 CE 1997 2 13 97ZZZX705 1 19961218 G 5730 052302826 SKIN CESSNA 172 172P 2072436 CE RT WING LE CORRODED B A5OR K NONE O OTHER IN INSP/MAINT 1 SO 09 64688 5864 17275609 FOUND HEAVY TO SEVERE CORROSION THROUGHOUT WING ASSEMBLY. INTERNAL PARTS OF WING WERE NOT PROTECTED FROM THE DAMAGING E FFECTS OF CORROSION DURING MANUFACTURE. REPLACED PART, CLEANED, TREATED, AND PRIMED WITH EPOXY PRIMER. RECOMMEND THAT THE MANUFACTURE DO LIKEWISE. 1 H 7 1 3O NT 3A12 1997021300492 19970213 00492 CE 1997 2 13 97ZZZX706 1 19961218 G 5712 05230273 RIB CESSNA 172 172P 2072436 CE RT WING NOSE CORRODED B A5OR K NONE O OTHER IN INSP/MAINT 1 SO 09 64688 5864 17275609 FOUND HEAVY SURFACE CORROSION THROUGHOUT WING ASSEMBLY. INTERNAL PARTS OF WING WERE NOT PROTECTED FROM THE DAMAGING EFF ECTS OF CORROSION DURING MANUFACTURE. REPLACED PART, CLEANED, TREATED, AND PRIMED WITH EPOXY PRIMER. RECOMMEND MANUFAC TURE DO LIKEWISE. 1 H 7 1 3O NT 3A12 1997021300493 19970213 00493 CE 1997 2 13 97ZZZX707 1 19961218 G 5522 DEV0550442 SKIN CESSNA 172 172P 2072436 CE ELEV CORRODED B A5OR K NONE O OTHER IN INSP/MAINT 1 SO 09 64688 5864 17275609 FOUND HEAVY TO SEVERE CORROSION, POPPED RIVETS, THROUGHOUT THE ELEV. CESSNA DID NOT PRIME ANY INTERNAL PARTS DURING MAN UFACTURE RESULTING IN AN UNSAFE CONDITION. REPLACED PART, CLEANED, TREATED, AND PRIMED WITH EPOXY PRIMER. RECOMMEND CE SSNA DO LIKEWISE. 1 H 7 1 3O NT 3A12 1997021300494 19970213 00494 CE 1997 2 13 97ZZZX708 1 19961218 G 5520 052300129 CHANNEL CESSNA 172 172P 2072436 CE ELEV CORRODED B A5OR K NONE O OTHER IN INSP/MAINT 1 SO 09 64688 5864 17275609 FOUND HEAVY TO SEVERE CORROSION, POPPED RIVETS, THROUGHOUT THE ELEV. CESSNA DID NOT PRIME ANY INTERNAL PARTS DURING MAN UFACTURE RESULTING IN AN UNSAFE CONDITION. REPLACED PART, CLEANED, TREATED AND PRIMED WITH EPOXY PRIMER. RECOMMEND CES SNA DO LIKEWISE 1 H 7 1 3O NT 3A12 1997021300495 19970213 00495 CE 1997 2 13 97ZZZX709 1 19961223 G 5520 24320011 FAIRING CESSNA 172 172P 2072436 CE ELEV CORRODED B A5OR K NONE O OTHER IN INSP/MAINT 1 SO 09 64688 5864 17275609 FOUND HEAVY TO SEVERE CORROSION, POPPED RIVETS, THROUGHOUT THE ELEV. CESSNA DID NOT PRIME ANY INTERNAL PARTS DURING MAN UFACTURE RESULTING IN AN UNSAFE CONDITION. REPLACED PART, CLEANED, TREATED, AND PRIMED WITH EPOXY PRIMER. RECOMMEND CE SSNA DO LIKEWISE. 1 H 7 1 3O NT 3A12 1997021300496 19970213 00496 CE 1997 2 13 97ZZZX710 1 19961218 G 5531 05310341 RIB CESSNA 172 172P 2072436 CE VERT STAB CORRODED B A5OR K NONE O OTHER IN INSP/MAINT 1 SO 09 64688 5864 17275609 FOUND HEAVY TO SEVERE CORROSION, POPPED RIVETS, THROUGHOUT THE VERT FIN. CESSNA DID NOT PRIME ANY INTERNAL PARTS DURING MANUFACTURE RESULTING IN AN UNSAFE CONDITION. REPLACED PART, CLEANED, TREATED, AND PRIMED WITH EPOXY PRIMER. RECOMMEN D CESSNA DO LIKEWISE. 1 H 7 1 3O NT 3A12 1997021300497 19970213 00497 CE 1997 2 13 97ZZZX711 1 19961218 G 5512 053200176 SKIN CESSNA 172 172P 2072436 CE HORIZ STAB LE CORRODED B A5OR K NONE O OTHER IN INSP/MAINT 1 SO 09 64688 5864 17275609 FOUND HEAVY TO SEVERE CORROSION THROUGHOUT THE HORIZ STAB. CESSNA DID NOT PROVIDE ANY CORROSION PROTECTION AT TIME OF M ANUFACTURE. REPLACED PART, CLEANED, TREATED, AND PRIMED WITH EPOXY PRIMER. RECOMMEND CESSNA DO LIKEWISE. 1 H 7 1 3O NT 3A12 1997021300498 19970213 00498 CE 1997 2 13 97ZZZX712 1 19961218 G 5532 053100696 SKIN CESSNA 172 172P 2072436 CE VERT FIN LE CORRODED B A5OR K NONE O OTHER IN INSP/MAINT 1 SO 09 64688 5864 17275609 FOUND HEAVY TO SEVERE CORROSION, POPPED RIVETS, THROUGHOUT THE VERT FIN. CESSNA DID NOT PRIME ANY INTERNAL PARTS DURING MANUFACTURE RESULTING IN AN UNSAFE CONDITION. REPLACED PART, CLEANED, TREATED, AND PRIMED WITH EPOXY PRIMER. RECOMMEN D CESSNA DO LIKEWISE. 1 H 7 1 3O NT 3A12 1997021300499 19970213 00499 CE 1997 2 13 97ZZZX713 1 19961218 G 5522 DEV0550444 SKIN CESSNA 172 172P 2072436 CE ELEV CORRODED B A5OR K NONE O OTHER IN INSP/MAINT 1 SO 09 64688 5864 17275609 FOUND HEAVY TO SEVERE CORROSION, POPPED RIVETS, THROUGHOUT THE ELEV. CESSNA DID NOT PRIME ANY INTERNAL PARTS DURING MAN UFACTURE RESULTING IN AN UNSAFE CONDITION. REPLACED PART, CLEANED, TREATED, AND PRIMED WITH EPOXY PRIMER. RECOMMEND CE SSNA DO LIKEWISE. 1 H 7 1 3O NT 3A12 1997022000124 19970220 00124 CE 1997 2 20 97ZZZX751 1 19961223 G 2752 HE6311 DRIVE ASSY 505211531 BEECH 80 65A80 1152808 CE FLAP FAILED D K NONE O OTHER IN INSP/MAINT 1 GL 15 134BA 21 405191 LD202 SOMETHING WITHIN THE 90 DEGREE DRIVE ASSY FAILED WHICH MADE THE FLAP FAIL TO EXTEND OR RETRACT. THE ACTUATOR WAS OH 20. 6 HRS AGO. 1 L 7 2 3O 3A20 1997022000131 19970220 00131 1997 2 20 97ZZZX758 3 19961227 G 6112 RA12884 BOOT RAPCO BEECH 80 65A80 1152808 CE PROP DEICE LEAD BROKEN D K NONE O OTHER IN INSP/MAINT 1 GL 15 95LL LD235 THE LEADS ARE BREAKING 12 INCHES FROM THE TERMINALS. THE LEAD IS REQUIRED TO BEND IN THIS AREA. SUBMITTER STATED THIS IS THE 10TH BOOT WHICH HAS FAILED IN THIS AREA IN THE LAST FIVE WEEKS. 1 L 7 2 3O 3A20 1997022000137 19970220 00137 EU 1997 2 20 97ZZZX764 1 19960226 G 2422 ASH6641PF INVERTER LELAND BRAERO DH125 BAE125800A 1500285 EU NR 1 FAILED H L A O OTHER B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 SW 15 DURING GND. RUN WITH ENG.'S RUNNING AND AVIONICS POWER UP, CREW STARTED THE APU. THE NR 1 INVERTER FLUCTUATED VIOLENTLY AND WAS SELECTED 'OFF'. WHEN ATTEMPT WAS MADE TO REINSTATE NR 1 INVERTER, BOTH ALTIMETERS WENT TO 60,000 FEET AND STAY ED THERE. WHEN THE A/C WAS SHUT DOWN, SMOKE WAS COMING OUT OF THE REAR EQUIPMENT BAY. SOURCE WAS FOUND TO BE THE NR 1 INVERTER. INVERTER AND BOTH ALTIMETERS WERE CHANGED. 2 L 7 2 4F RT A3EU 1997022000143 19970220 00143 WP 1997 2 20 97ZZZX770 2 19961105 G 7250 31010922 BEARING 310331923 GARRTT TPE331 TPE33112UHR WP TURBINE AFT FAILED B DSCR K NONE O OTHER NR NOT REPORTED 1 GL 25 6864 P823 P70129 REAR TURBINE BEARING FAILED RESULTING IN MOVEMENT OF MAIN ROTATING GROUP. SECONDARY DAMAGE INCLUDED SEVERE RUBBING OF A LL ROTATING COMPONENTS DUE TO FREE MOVEMENT OF MAINSHAFT CAUSED BY BEARING FAILURE. IMPACT DAMAGE ALSO AFFECTED EXHAUST GAS TEMPERATURE HARNESS. BEARING FAILURE ALSO RESULTED IN OIL SYSTEM METAL CONTAMINATION. PART TOTAL CYCLES, 7,084. 4 T E4WE 1997022000144 19970220 00144 WP 1997 2 20 97ZZZX771 2 19961224 G 7250 31070852 SEAL 31038393 GARRTT TPE331 TPE33112UHR WP 1ST STG TURB CRACKED B DSCR K NONE O OTHER NR NOT REPORTED 1 GL 25 10816 6180402135 P70046 SEAL CRACKED AT FLANGE. SB 72-0840 AUTHORIZES INSTALLATION OF THIS PART TO PROVIDE INCREASED SEAL PLATE TENSION AGAINST THE 1ST STAGE ROTOR ASSY. INCREASED TENSION CAUSES CRACKING AT FLANGE. THIS IS A CRITICAL LIFE-LIMITED COMPONENT. LI MIT 20,000 CYCLES. PART TOTAL CYCLES, 12,410. 4 T E4WE 1997022000145 19970220 00145 WP 1997 2 20 97ZZZX772 2 19961115 G 7250 31070852 SEAL GARRTT TPE331 TPE33112UHR WP 1ST STG TURB CRACKED B DSCR K NONE O OTHER IN INSP/MAINT 1 GL 25 10257 P70048 SEAL FOUND CRACKED AT SEALING FLANGE. SB 72-0840 AUTHORIZES INSTALLATION OF THIS PART TO PROVIDE INCREASED SEAL TENSION AGAINST FIRST ROTOR ASSY. INCREASED TENSION RESULTS IN CRACKING AT FLANGE. PART IS A CRITICAL LIFE LIMITED ROTATING G ROUP COMPONENT. LIMIT 20,000 CYCLES. PART TOTAL CYCLES, 10,462. 4 T E4WE 1997022000149 19970220 00149 EU 1997 2 20 97ZZZX776 1 19961119 G 3710 4051 VALVE SOCATA TB20 TB20TRINIDAD 8680695 EU STANDBY VAC MALFUNCTION H L K NONE O OTHER IN INSP/MAINT 1 EA 17 470SP 268 456 PRECISE FLIGHT STANDBY VACUUM SYSTEM FAILED TO OPERATE WHEN SELECTED. SUBSEQUENT INSPECTION REVEALED ACTUATION CONTROL CABLE TO BE LIMITED IN TRAVEL DUE TO INTERFERENCE WITH CONTROL VALVE LEVER. PREVIOUS EXPERIENCES WITH INSTALLING THIS S YSTEM HAVE FOUND THIS AREA TO BE TROUBLESOME TO ADJUST AND ALIGN. ANY MOVEMENT OF CABLE SUPPORT CLAMP CAN ADVERSELY AFF ECT SYSTEM OPERATION. 1 L 7 1 3O RT A51EU 1997022000150 19970220 00150 SO 1997 2 20 97ZZZX777 1 19961219 G 8011 STARTER GULSTM G1159 GIV 3980115 SO RT ENG DEFECTIVE C K NONE O OTHER IN INSP/MAINT 1 GL 03 540W 303 1265 DURING 300 HR STARTER OIL LEVEL CHECK, OIL WAS FOUND TO BE BLACK IN COLOR. SUSPECT BAD BEARINGS. REMOVED AND REPLACED STARTER, SYSTEM OPERATES NORMALLY. 2 L 7 2 4F RT A12EA 1997022000151 19970220 00151 SO 1997 2 20 97ZZZX778 1 19961219 G 3250 SERVO VALVE GULSTM G1159 GIV 3980115 SO NLG STEERING MISADJUSTED C K NONE O OTHER IN INSP/MAINT 1 GL 03 540W 303 1265 NOSE WHEEL STEERING SYSTEM KEPT TRIPPING OFF LINE. UPON EXTENSIVE TROUBLESHOOTING, FOUND NWS SERVO VALVE WAS CAUSING MA LFUNCTION. ALSO, WHEN SYSTEM WOULD TRIP OFF, IT WOULD KICK RIGHT. FOUND THAT THE NWS RUDDER POTENTIOMETER WAS ADJUSTED BACKWARDS (MINUS 30MV RATHER THAN PLUS 30MV). THIS TOLD THE SYSTEM TO TURN RIGHT WHEN THE SERVO FAILED. RE-ADJUSTED P OTENTIOMETER. OPS CHECKS GOOD. 2 L 7 2 4F RT A12EA 1997022000152 19970220 00152 SO 1997 2 20 97ZZZX779 1 19961217 G 2822 RG52400B PUMP PIPER PA31T PA31T 7103124 SO FUEL BOOST WIRE CHAFE D A K NONE O OTHER IN INSP/MAINT 1 SO 17 737WB 7620052 DURING AN EVENT 1 INSP, FOUND THE NR 1 BOOST PUMP MAIN POWER WIRE WHERE IT COMES OUT OF THE BACK OF THE PUMP HAD CHAFED THROUGH ON PUMP HOUSING. EVIDENCE OF BURNED AND MELTED SHIELDING. PUMP LOCATED IN RIGHT WING ROOT. SUSPECT CAUSE: PO WER WIRE NOT PROPERLY SECURED. 1 L 7 2 3T A8EA 1997022000155 19970220 00155 WP 1997 2 20 97ZZZX782 2 19960930 G 7260 31030351 BEARING 31032321 GARRTT TPE331 TPE33110U 01514 WP ACCESSORY GRBOX FAILED B DSCR O OTHER Y ENGINE STOPPAGE CR CRUISE 1 GL 25 3793 P374 P63074 ACCESSORY GEAR BEARING FAILED RESULTING IN LOSS OF FUEL CONTROL DRIVE AND SUBSEQUENT ENGINE SHUT DOWN IN-FLIGHT. FAILUR E OCCURRED UNDER NORMAL OPERATING CONDITIONS WITHIN BEARING TIME-LIFE LIMITATIONS. SUBMITTER SUGGESTS BEARING REPLACEME NT AT 3500 HOUR GEARBOX INSPECTION. 4 T E4WE 1997022000473 19970220 00473 GL 1997 2 20 97ZZZX786 2 19961218 G 7261 6854424 SEAL BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL START/GEN MT UNDER SPEC D K NONE K FLUID LOSS IN INSP/MAINT 1 SO 03 90215 3 1698 CAE822907 3 HOURS AFTER SEAL INSTALLATION, PILOT NOTICED OIL LEAK IN STARTER/GEN AREA DURING PREFLIGHT INSP. DURING GROUND RUN, E NG OIL WAS FOUND TO BE LEAKING AT A RATE OF 12 DROPS PER MINUTE. STARTER/GEN WAS REMOVED AND P/N A6854424 WAS FOUND HAL F OUT OF SEAL BORE. DURING ENG INSTALLATION, SEAL WAS VERIFIED FOR PROPER INSTALLATION, 3.2 HOURS PRIOR. SEAL IS AN FA A PMA SEAL. SEAL WAS REMOVED FROM ENG AND OUTER DIAMETER MEASURED AT THREE DIFFERENT DEPTHS ON METAL BAND. EACH OF THE MEASURED DIMENSIONS WERE UNDER THE REQUIRED MINIMUM SPECIFIED BY ALLISON. SUBMITTER RECOMMENDS THAT ALL P/N 6854424 SE ALS BE MEASURED FOR PROPER DIMENSION PRIOR TO INSTALLATION. 1 G 7 1 3U 3 U H2SW E4CE 1997022000479 19970220 00479 SO 1997 2 20 97ZZZX792 2 19961029 G 7310 FC30004 HOSE CESSNA 337 337 2075702 CE CONT O360 IO360C 17025 SO FUEL SYS WRONG PART B V2AR K NONE W INADEQUATE Q C IN INSP/MAINT 1 AL 03 2285X 3370185 AEROQUIP FC 300-04 HOSE MEETING SAE 100R5-23 WAS FOUND INSTALLED IN REAR ENGINE FUEL SYSTEM. THIS HOSE IS INDUSTRIAL AI R BRAKE HOSE AND THE END FITTINGS MAY NOT BE COMPATIBLE WITH AN/MS FITTINGS. SUBMITTER STATES THIS IS THE SECOND HOSE O F THIS TYPE FOUND ON AN A/C. 1 H 7 2 3O 3 O A6CE E1CE 1997022000481 19970220 00481 1997 2 20 97ZZZX794 4 19961018 G 3452 KT76A TRANSPONDER BENDIX CESSNA 340 340A 2076405 CE C441/C437 DEFECTIVE B DWSR K NONE O OTHER IN INSP/MAINT 1 SO 05 340EC 34931 340A0258 TRANSPONDER REPLIED ERRATICALLY. REPLIES WERE NOT SYNCHRONIZED WITH INTERROGATIONS. REPLACED LEAKY CAPACITOR C441. DE FECTIVE PART HAD BLACK EPOXY COATING. REPLACEMENT PART HAD TAN COATING. PROBLEM DISAPPEARED. IN ADDITION, TRANSPONDER AUTOMATIC OVERLOAD CONTROL WAS INEFFECTIVE. REPLACED LEAKY CAPACITOR C437. SAME COLORS AS ABOVE. PROBLEM DISAPPEARED . VERY COMMON PROBLEM. 1 L 7 2 3O 3A25 1997022000482 19970220 00482 SO 1997 2 20 97ZZZX795 2 19960928 G 8530 111071 CYLINDER CESSNA 185 A185F 2072821 CE CONT O550 IO550* SO NR 2 LOW COMPRESSION B V2AR K NONE O OTHER IN INSP/MAINT 1 AL 03 4698C 18502598 264051R COMPRESSION CHECK REVEALED NR 2 CYL LOW. SUBMITTER STATES THIS IS THE SECOND CE 185 IO550 INSTALLED BY STC TO HAVE LOW COMPRESSION AT 200 HRS, FOUND IN LAST 2 MONTHS. 1 H 7 1 3O 3 O 3A24 E3SO 1997022000489 19970220 00489 CE 1997 2 20 97ZZZX802 1 19961220 G 7603 07501957 BRACKET CESSNA 185 A185E 2072818 CE THROTTLE BROKEN B L PCYR K NONE O OTHER IN INSP/MAINT 1 NM 05 70194 18502047 ENGINE FAILED TO RESPOND ON TAKEOFF. SMALL BRACKET ATTACHED TO THROTTLE BRACKET 0750195-7, ONE ARM BROKEN AND SEVERELY WORN WHERE THROTTLE CONTROL CABLE ATTACHES WITH SAFETY WIRE. BRACKET (SMALL) NOT SHOWN IN PARTS BOOK. SAME BRACKET IS USED ON PROP CONTROL CABLE AND WAS BROKEN AND WORN. REPLACED 200 HOURS PREVIOUSLY. APPEARED THAT ALL CABLES WERE PROPE RLY INSTALLED AND RIGGED (FACTORY). 1 H 7 1 3O 3A24 1997022700058 19970227 00058 WP 1997 2 27 97ZZZX811 1 19961016 G 2121 58861 BEARING SUNDSTRANDEM 251301 DOUG DC9 DC983 3022083 WP AVION COOLING FAILED B DM4R K NONE O OTHER IN INSP/MAINT 1 SO 19 2127 2497 FAN BEARING FAILED. BEARING INNER RACE IS BLUE FROM HEAT. BEARING WILL NOT TURN. BEARING TT SINCE INSTALLATION 2127 H RS. FAN IS FOR AVIONIC COOLING AND CARGO HEAT. BEARING INSTALLED NEW. 2 L 7 2 4F RT A6WE 1997022700059 19970227 00059 EU 1997 2 27 97ZZZX812 1 19960910 G 2620 2591C VALVE CASA C212 C212200 2410304 EU NR1 ENG FIRE EXT FAILED B AL5R K NONE O OTHER IN INSP/MAINT 1 SO 09 424CA 9063 1594 242 THE PURPOSE OF THE TWO EXTINGUISHING VALVES IS TO LEAD BY MEANS OF ITS COORDINATE ACTION, THE DISCHARGE OF EXTINGUISHING AGENT TOWARDS THE DESIRED ENGINE. NR 1 ENG VALVE DISK WAS FROZEN ON SHAFT. NR 2 ENG VALVE DISK WAS PREVENTED FROM SEA TING DUE MILD CORROSION. RECOMMEND: FREQ BE CHANGED FROM EVERY 6 YEARS TO 1 YEAR FOR FUNCTIONAL TEST OF SYSTEM. 2 H 7 2 4T A43EU 1997010900417 19970109 00417 NE 1997 1 9 97ZZZX82 1 19961211 G 6210 6515000003 BOLT 641520601042 SKRSKY S64 S64F NE M/R BLADE CRACKED B JYDR K NONE O OTHER IN INSP/MAINT 1 NM 09 2938 64M25901126 AN ULTRASONIC (UT) INSPECTION OF THE M/R BLADE BOLTS RETAINING THE MAIN ROTOR BLADE SPAR TO THE BLADE CUFF WAS PERFORMED IAW THE MANUFACTURER'S INSTRUCTIONS. DURING THE UT INSPECTION, CRACKS WERE DETECTED ON ONE OR MORE BOLTS ON EACH BLADE . BOLTS THAT WERE REMOVED FOR CRACK CONFIRMATION, CORROSION WAS EVIDENT ON THE BOLT SHANK APPROXIMATELY .500 INCH BELOW THE BOLT HEAD AND EXTENDING FOR APPROXIMATELY 1.000 INCH ALONG THE SHANK. THE CRACKS WERE NOTED TO OCCUR WITHIN THE CO RRODED AREAS. NO CRACKING WAS NOTED OUTSIDE OF THE CORRODED AREAS. 2 G 7 2 4U H6EA 1997022700069 19970227 00069 SO 1997 2 27 97ZZZX822 1 19961227 G 2913 318002 POWER PACK PIPER PA23 PA23250 7102308 SO MLG FAILED D A O OTHER J WARNING INDICATION AP APPROACH 1 NE 05 40571 277405313 PILOT HAD TO USE EMERGENCY GEAR EXTENSION IN ORDER TO EXTEND GEAR. THE CO2 BOTTLE DISCHARGED, BUT THE PRIORITY VALVE DI D NOT WORK. THE CABLE RIGGING WAS INCORRECT DUE TO CABLE SLIPPAGE WHEN RING WAS PULLED. HYDRAULIC POWER PACK WAS REPLA CED DUE TO INTERNAL PROBLEMS. IMPROPER EMERGENCY CABLE RIGGING OR CABLE SLIPPAGE MADE FOR INCORRECT EMERGENCY GEAR EXTE NSION. 1 L 7 2 3O 1A10 1997022700070 19970227 00070 EA 1997 2 27 97ZZZX823 2 19961220 G 8520 LW17249 CRANKSHAFT MOONEY M20 M20J 5870219 SW LYC O360 IO360A3B6 41514 EA NR 3 CRANK PIN BROKEN D A UNSCHED LANDING E Y VIBRATION/BUFFET ENGINE STOPPAGE CR CRUISE 1 GL 19 4566H 2734 713 240848 L2071451A ENGINE SEIZED IN-FLIGHT WITH NO WARNING (APPROX 5 SECONDS OF ROUGH OPERATION). PILOT MADE UNEVENTFUL LANDING IN THE FIE LD. ENGINE WAS REMOVED AND DISASSEMBLED. CRANKSHAFT FOUND BROKEN IN TWO BETWEEN NR 3 AND NR 4 CONNECTING RODS. ENGINE INSPECTED FOR PROP STRIKE 253.8 HOURS PRIOR. 1 L 7 1 3O 3 O 2A3 1E10 1997022700075 19970227 00075 EA 1997 2 27 97ZZZX828 2 19961004 G 7322 229164 DISCHARGE TUBE MA4SPA CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA CARB PUMP DETACHED D A UNSCHED LANDING R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 NM 01 5115E A105126 17271717 L504376 CARBURETOR PUMP DISCHARGE TUBE ASSY CAME ADRIFT INGESTING IN ENGINE, KNOCKING LOOSE THE SOLID COMBUSTION PARTICLES IN TH E COMBUSTION CHAMBER WHICH FOULED A NUMBER OF THE SPARK PLUGS SIMULTANEOUSLY LOSING 50 PERCENT OR MORE OF THE POWER. BE ING NEXT TO THE AIRSTRIP, SAFE LANDING WAS MADE. 1 H 7 1 3O 3 O NT 3A12 E274 1997010900418 19970109 00418 NE 1997 1 9 97ZZZX83 1 19961211 G 6210 6515000003 BOLT 641520601042 SKRSKY S64 S64F NE M/R BLADE CRACKED B JYDR K NONE O OTHER IN INSP/MAINT 1 NM 09 2569 64M24571092 AN ULTRASONIC (UT) INSPECTION OF THE M/R BLADE BOLTS RETAINING THE MAIN ROTOR BLADE SPAR TO THE BLADE CUFF WAS PERFORMED IAW THE MANUFACTURER'S INSTRUCTIONS. DURING THE UT INSPECTION, CRACKS WERE DETECTED ON ONE OR MORE BOLTS ON EACH BLADE . BOLTS THAT WERE REMOVED FOR CRACK CONFIRMATION, CORROSION WAS EVIDENT ON THE BOLT SHANK APPROXIMATELY .500 INCH BELOW THE BOLT HEAD AND EXTENDING FOR APPROXIMATELY 1.000 INCH ALONG THE SHANK. THE CRACKS WERE NOTED TO OCCUR WITHIN THE CO RRODED AREAS. NO CRACKING WAS NOTED OUTSIDE OF THE CORRODED AREAS. 2 G 7 2 4U H6EA 1997022700181 19970227 00181 CE 1997 2 27 97ZZZX839 1 19961127 G 2440 1093610165 MODULE BEECH 1900 1900C 1154161 CE EXT POWER WIRE BROKEN B A ZKGR K NONE W INADEQUATE Q C IN INSP/MAINT 1 NE 05 RECEIVED PART FROM REPAIR FACILITY WITH ONLY FUNCTIONAL TEST PERFORMED. WHEN REMOVED FROM PACKAGE, FOUND NR 1 WIRE BROK EN FROM POST ON MODULE. RECOMMEND REPAIR FACILITY PHYSICALLY MOVE WIRE CONNECTION TO CHECK TO SEE IF THEY MAY BE BAD. S ECOND P.C. BOARD RECEIVED IN THIS CONDITION. 2 L 7 2 4T RT A24CE 1997010900419 19970109 00419 NE 1997 1 9 97ZZZX84 1 19961211 G 6210 6515000003 BOLT 641520601042 SKRSKY S64 S64F NE M/R BLADE CRACKED B JYDR K NONE O OTHER IN INSP/MAINT 1 NM 09 2500 64M24721036 AN ULTRASONIC (UT) INSPECTION OF THE M/R BLADE BOLTS RETAINING THE MAIN ROTOR BLADE SPAR TO THE BLADE CUFF WAS PERFORMED IAW THE MANUFACTURER'S INSTRUCTIONS. DURING THE UT INSPECTION, CRACKS WERE DETECTED ON ONE OR MORE BOLTS ON EACH BLADE . BOLTS THAT WERE REMOVED FOR CRACK CONFIRMATION, CORROSION WAS EVIDENT ON THE BOLT SHANK APPROXIMATELY .500 INCH BELOW THE BOLT HEAD AND EXTENDING FOR APPROXIMATELY 1.000 INCH ALONG THE SHANK. THE CRACKS WERE NOTED TO OCCUR WITHIN THE CO RRODED AREAS. NO CRACKING WAS NOTED OUTSIDE OF THE CORRODED AREAS. 2 G 7 2 4U H6EA 1997022700185 19970227 00185 CE 1997 2 27 97ZZZX843 1 19961230 G 2121 50041 MOTOR BEECH 200 200BEECH 1152920 CE CABIN BLOWER SEIZED E O OTHER B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 SW 09 200AJ 1309 BB378 SMOKE FILLED CABIN ON A FLIGHT 12-30-96. AIRCRAFT RETURNED. DETERMINED FRONT EVAPORATIVE BLOWER SEIZED. BLOWER ONLY HAD 396.8 HOURS LOGGED. 1 L 7 2 4T A24CE 1997010900420 19970109 00420 NE 1997 1 9 97ZZZX85 1 19961211 G 6210 6515000003 BOLT 641520601042 SKRSKY S64 S64F NE M/R BLADE CRACKED B JYDR K NONE O OTHER IN INSP/MAINT 1 NM 09 2463 64M24761104 AN ULTRASONIC (UT) INSPECTION OF THE M/R BLADE BOLTS RETAINING THE MAIN ROTOR BLADE SPAR TO THE BLADE CUFF WAS PERFORMED IAW THE MANUFACTURER'S INSTRUCTIONS. DURING THE UT INSPECTION, CRACKS WERE DETECTED ON ONE OR MORE BOLTS ON EACH BLADE . BOLTS THAT WERE REMOVED FOR CRACK CONFIRMATION, CORROSION WAS EVIDENT ON THE BOLT SHANK APPROXIMATELY .500 INCH BELOW THE BOLT HEAD AND EXTENDING FOR APPROXIMATELY 1.000 INCH ALONG THE SHANK. THE CRACKS WERE NOTED TO OCCUR WITHIN THE CO RRODED AREAS. NO CRACKING WAS NOTED OUTSIDE OF THE CORRODED AREAS. 2 G 7 2 4U H6EA 1997010900421 19970109 00421 NE 1997 1 9 97ZZZX86 1 19961211 G 6210 6515000003 BOLT 641520601042 SKRSKY S64 S64F NE M/R BLADE CRACKED B JYDR K NONE O OTHER IN INSP/MAINT 1 NM 09 2727 64M25471133 AN ULTRASONIC (UT) INSPECTION OF THE M/R BLADE BOLTS RETAINING THE MAIN ROTOR BLADE SPAR TO THE BLADE CUFF WAS PERFORMED IAW THE MANUFACTURER'S INSTRUCTIONS. DURING THE UT INSPECTION, CRACKS WERE DETECTED ON ONE OR MORE BOLTS ON EACH BLADE . BOLTS THAT WERE REMOVED FOR CRACK CONFIRMATION, CORROSION WAS EVIDENT ON THE BOLT SHANK APPROXIMATELY .500 INCH BELOW THE BOLT HEAD AND EXTENDING FOR APPROXIMATELY 1.000 INCH ALONG THE SHANK. THE CRACKS WERE NOTED TO OCCUR WITHIN THE CO RRODED AREAS. NO CRACKING WAS NOTED OUTSIDE OF THE CORRODED AREAS. 2 G 7 2 4U H6EA 1997010900422 19970109 00422 NE 1997 1 9 97ZZZX87 1 19961211 G 6210 6515000003 BOLT 641520601042 SKRSKY S64 S64F NE M/R BLADE CRACKED B JYDR K NONE O OTHER IN INSP/MAINT 1 NM 09 2992 64M33811174 AN ULTRASONIC (UT) INSPECTION OF THE M/R BLADE BOLTS RETAINING THE MAIN ROTOR BLADE SPAR TO THE BLADE CUFF WAS PERFORMED IAW THE MANUFACTURER'S INSTRUCTIONS. DURING THE UT INSPECTION, CRACKS WERE DETECTED ON ONE OR MORE BOLTS ON EACH BLADE . BOLTS THAT WERE REMOVED FOR CRACK CONFIRMATION, CORROSION WAS EVIDENT ON THE BOLT SHANK APPROXIMATELY .500 INCH BELOW THE BOLT HEAD AND EXTENDING FOR APPROXIMATELY 1.000 INCH ALONG THE SHANK. THE CRACKS WERE NOTED TO OCCUR WITHIN THE CO RRODED AREAS. NO CRACKING WAS NOTED OUTSIDE OF THE CORRODED AREAS. 2 G 7 2 4U H6EA 1997010900423 19970109 00423 NE 1997 1 9 97ZZZX88 2 19961112 G 7230 COVER TAB SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1B 6OO30 NE CENTRIFUGAL COMP BROKEN B A R7MD K NONE O OTHER IN INSP/MAINT 1 SO 13 21UM 3335 2489 1674 241 PERFORMING A DAILY ON A/C, NOTED TWO METAL TABS LYING ON ENG DECK. AFTER INQUIRING ABOUT THEM, FOUND OUT THAT THE CENTR IFUGAL COMPRESSOR COVER WAS CRACKING AROUND CIRCUMFERENCE AND RELEASING THESE TABS FROM COVER. THE BROKEN TABS FORTUNAT ELY BLEW OUT BLEED VALVE AND WERE NOT INJESTED THROUGH ENGINE 1 G 7 1 3U 3 U H9EU E19EU 1997010900424 19970109 00424 SW 1997 1 9 97ZZZX89 1 19961029 G 3213 206324004 SKID TUBE BELL 206 206L1 1182107 SW FLOAT SKID CRACKED D S A K NONE O OTHER IN INSP/MAINT 1 SW 03 2150M 2734 691 45703 UPON ROUTINE EMERGENCY FLOAT SYSTEM 6 MONTH/500 HOUR INSPECTION, THE SKID TUBE WAS FOUND CRACKED IN THREE PLACES. UPON FURTHER INSPECTION OF TUBE, THE CRACKS APPEAR TO ORIGINATE FROM THE INSERTS DUE TO IMPROPER INSTALLATION OR HOLE PREPARA TION RATHER THAN DAMAGE FROM LANDING OR DEBRIS. TUBE SN 702 WAS NOT CRACKED, BUT WAS ALSO CONDEMNED DUE TO UNREPAIRABLE CORROSION. BOTH PARTS WERE RECEIVED PRIMED, PAINTED, AND READY TO INSTALL INCLUDING MANUFACTURER SUPPLIED/PRE-INSTALLE D SKID SHOES. BOTH TUBES RETURNED TO AERO ACCESSORIES FOR EVALUATION 10-29-96. 1 G 7 1 3U H2SW 1997030600299 19970306 00299 NE 1997 3 6 97ZZZX895 2 19961118 G 7250 770102 BLADE PWA JT9 JT9D7 52054 NE C MOD T2 OVERTEMP B K NONE O OTHER IN INSP/MAINT 1 EU 03 SUBMITTER CHECKED A NUMBER OF SERVICEABLE JT9D ST2 TURBINE BLADES OF PWA 1455 MATERIAL P/N 770102 WHICH HAD BEEN REMOVED FROM PREVIOUSLY OPERATED ENGINES AND FOUND THEM ALL TO EXHIBIT SIGNS OF AN OVERTEMPERATURE CONDITION AS DETAILED IN THE OEM ENGINE MANUAL. HAS BEEN ADVISED THAT NO REPORT OF AN OVERTEMPERATURE DURING OPERATION HAD BEEN MADE BY THE PREVIOU S OPERATOR. THE ENGINE MANUFACTURER PWA HAS BEEN NOTIFIED. THIS OVERTEMP PROBLEM WITH PWA 1455 MATERIAL BLADES WAS DIS CUSSED AT THE OPERATORS CONFERENCE OCTOBER, 1996. GEAESL HAS INTRODUCED A POLICY OF CHECKING ALL USED SERVICEABLE P/N 7 70102 BLADES PURCHASED FOR POSSIBLE OVERTEMPERATURE CONDITION. 4 F E20EA 1997030600300 19970306 00300 SW 1997 3 6 97ZZZX896 1 19961031 G 6510 406040339105 BEARING BELL 407 407 SW T/R DRIVE SEAL TORN B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 1099R 12 53042 FOUND T/R DRIVE SHAFT BEARING SEAL TORN. REPLACED WITH NEW BEARING. 1 G 7 1 3U O H2SW 1997010900102 19970109 00102 1997 1 9 97ZZZX9 4 19961125 G 6113 6663000 BULKHEAD PIPER PA28 PA28160 7102806 SO FWD SPINNER CRACKED D K NONE O OTHER IN INSP/MAINT 1 NE 03 5JN 281528 THE FORWARD SPINNER BOLT HOLES WERE 'DISHED' AT EACH HOLE LOCATION. AT ONE LOCATION, THE METAL ON THE BULKHEAD WAS SO T HIN A CRACK HAD DEVELOPED THROUGH THE HOLE. SUBMITTER STATED OVERTORQUE OF THE PROP BOLTS WAS THE CAUSE OF THIS METAL S TRETCHING. THE MM LISTS THE TORQUE FOR THE .50 INCH D-BOLTS IN THE SAME AREA AS THE 3 INCH D-BOLTS. 1 L 7 1 3O 2A13 1997030600307 19970306 00307 SW 1997 3 6 97ZZZX903 1 19961204 G 6520 206040402101 GEARBOX BELL 206 206L3 1182108 SW T/R DEFECTIVE B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 3CW 2403 AFS2836 51420 REPLACED DUE TO NUMEROUS ALIGNMENT BEARING CHANGES. REPLACED WITH NEW T/R GEARBOX ASSY. 1 G 7 1 3U H2SW 1997030600308 19970306 00308 EU 1997 3 6 97ZZZX904 1 19960906 G 2150 CCA6299 BELT SNIAS 350 AS350BA 8680817 EU AIR COND DRIVE FAILED D A K NONE O OTHER IN INSP/MAINT 1 GL 03 32FX 1 2791 SUSPECT AIR CONDITIONER COMP BELT BROKE AND TOOK OUT HYD BELT. FOUND BELT (AC) RUNNING TOO CLOSE TO DRIVESHAFT COUPLING BOLTS. SHIMMED AC COMPRESSOR BRACKET TO OBTAIN PROPER CLEARANCE. CHECKED COMP PULLEY TO DRIVESHAFT FOR PARALLELISM. S UGGEST INSP OF AC BELT FOR PROPER CLEARANCE. AIR CONDITIONER SYSTEM IS A CASEY-COPTER ACCESSORIES, P/N 350-CCA-102-24, STC NR SH 686NE. 1 G 7 1 3U NC H9EU 1997030600309 19970306 00309 EU 1997 3 6 97ZZZX905 1 19960906 G 2913 704A33690004 BELT SNIAS 350 AS350BA 8680817 EU HYD DRIVE FAILED D A K NONE O OTHER IN INSP/MAINT 1 GL 03 32FX 1 2791 SUSPECT AIR CONDITIONER COMP BELT BROKE AND TOOK OUT HYD BELT. FOUND BELT (AC) RUNNING TOO CLOSE TO DRIVESHAFT COUPLING BOLTS. SHIMMED AC COMPRESSOR BRACKET TO OBTAIN PROPER CLEARANCE. CHECKED COMP PULLEY TO DRIVESHAFT FOR PARALLELISM. S UGGEST INSP OF AC BELT FOR PROPER CLEARANCE. AIR CONDITIONER SYSTEM IS A CASEY-COPTER ACCESSORIES, P/N 350-CCA-102-24, STC NR SH 686NE. 1 G 7 1 3U NC H9EU 1997030600312 19970306 00312 WP 1997 3 6 97ZZZX908 1 19961210 G 7330 369H81443 SWITCH HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL FUEL BYPASS INOPERATIVE B A GHHR A UNSCHED LANDING P NO WARNING INDICATION NR NOT REPORTED 1 NM 01 5225C 633 590497D CAE830420 AIRCRAFT SUSTAINED MAJOR DAMAGE WHEN FUEL NOZZLE SCREEN BECAME CLOGGED AND COLLAPSED CAUSING LOSS OF POWER. POST ACCIDE NT INVESTIGATION BY MCDONNEL DOUGLAS AND FAA FOUND FUEL FILTER BYPASS SWITCH WAS NOT CLOSING SO PILOT HAD NO INDICATION THAT THE FUEL FILTER WAS IN BYPASS. 1 G 7 1 3U 3 U H3WE E4CE 1997010900426 19970109 00426 WP 1997 1 9 97ZZZX91 1 19961127 G 2842 774000190 FUEL SENDER HUGHES 269 269C 4470504 WP MAIN FUEL TANK ARM BENT B L HIAR A UNSCHED LANDING J WARNING INDICATION NR NOT REPORTED 1 WP 27 61404 980 0010 PILOTS MADE PRECAUTIONARY LANDING DUE TO ILLUMINATION OF LOW FUEL LIGHT. AFTER INVESTIGATION, FOUND THAT THE FUEL SENDE R FLOAT CONTACTED THE LOW FUEL SENDING UNIT NOT ALLOWING THE FLOAT TO DROP ANY FURTHER,THEREFORE, THE GAUGE CONTINUED TO READ APPROX 8 GALLONS. AFTER REMOVAL, FOUND SENDING UNIT ARM BENT. 1 G 7 1 3O 4H12 1997030600319 19970306 00319 EU 1997 3 6 97ZZZX915 1 19960322 G 6320 350A32106320 GASKET 350A32011000 SNIAS 350 AS350B2 8680813 EU EPICYCLIC MISFIT D K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 07 6095U 2699 NEW GASKET FROM MFG DOES NOT FIT PROPERLY. SUBMITTER STATED THESE PARTS WHEN RECEIVED FROM A.E.C. ARE TOO SMALL IN DIAM ETER TO CORRECTLY FIT. AMER EUROCOPTER SAYS TO SOAK THE GASKET OR TO TEAR THE OUTSIDE PART OF THE BOLT HOLES TO MAKE IT FIT. AFTER TRYING TO GET THE GASKET TO SWELL BY SOAKING, THE GASKET STILL TORE. AMER EUROCOPTER IS AWARE OF THIS PROB LEM, BUT AS OF LAST PHONE CALL HAS NOT DEVELOPED CORRECTION TO THE PROBLEM OF BAD FITTING GASKETS. 1 G 7 1 3U H9EU 1997010900427 19970109 00427 SW 1997 1 9 97ZZZX92 1 19960612 G 6220 412018056105 CONE SEAT BELL 412 412 1182202 SW M/R HEAD MISMANUFACTURED H K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 416EH 10307 AAD00095M 33011 MALFUNCTION: RECEIVED LOWER CONE SEAT FOR M/R HEAD THAT WAS NOT PROPERLY TAPPED AND THREADED. SUBMITTER SUGGESTION: T HAT BELL QUALITY CONTROL CHECK LOWER CONE SEAT THOROUGHLY BEFORE SHIPPING TO CUSTOMER. 1 G 7 2 4U H4SW 1997030600703 19970306 00703 SW 1997 3 6 97ZZZX926 1 19961029 G 3213 206324003 SKID TUBE BELL 206 206L1 1182107 SW MLG CRACKED D A K NONE O OTHER IN INSP/MAINT 1 SW 03 2150M 2734 45703 UPON ROUTINE EMERGENCY FLOAT SYSTEM 6 MONTH/500 HOUR INSPECTION, THE SKID TUBE WAS FOUND CRACKED IN THREE PLACES AS SKET CHED. UPON FURTHER INSPECTION OF TUBE, THE CRACKS APPEAR TO ORIGINATE FROM THE INSERTS DUE TO IMPROPER INSTALLATION OR HOLE PREPARATION RATHER THAN DAMAGE FROM LANDING ON DEBRIS. TUBE S/N 702 WAS NOT CRACKED, BUT WAS ALSO CONDEMNED DUE TO UNREPAIRABLE CORROSION. BOTH PARTS WERE RECEIVED PRIMED, PAINTED, AND READY TO INSTALL INCLUDING MANUFACTURER SUPPLIED /PRE-INSTALLED SKID SHOES. 3 INCH LONG CRACKS. 1 G 7 1 3U H2SW 1997010900428 19970109 00428 EA 1997 1 9 97ZZZX93 2 19961108 G 8500 ENGINE HUGHES 269 269C 4470504 WP LYC O360 HIO360D1A 41514 EA POWER SECTION FAILED H A FW7L K NONE E VIBRATION/BUFFET IN INSP/MAINT 1 EA 07 6053U S1623 L2654851A THE ENGINE WAS REMOVED FROM THE A/C FOR A VIBRATION OF UNKNOWN CAUSE WHICH WAS DISCOVERED DURING A POST-INSPECTION RUN-U P. THE USUAL TROUBLESHOOTING PROCEDURES DID NOT PRODUCE SATISFACTORY RESULTS. THE COMPLETE ENGINE WAS SENT BACK TO THE LYCOMING FACTORY FOR ANALYSIS. LYCOMING REPORTED BACK TO US THAT THE ENGINE 'FAILED' IN THE TEST CELL AND THEY WERE NO T SURE OF THE CAUSE. ENGINE TOTAL TIME AT REMOVAL 880.5 HOURS. 1 G 7 1 3O 3 O 4H12 1E10 1997030600710 19970306 00710 SW 1997 3 6 97ZZZX933 1 19961122 G 6210 206015001107 BLADE BELL 206 206L1 1182107 SW M/R DEBONDED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 1078N 1825 A1081 45389 LIGHTNING STRIKE INSPECTION FOUND M/R BLADE CORRODED AND DEBONDED AT TIP OF BLADE. 1 G 7 1 3U H2SW 1997030600711 19970306 00711 SW 1997 3 6 97ZZZX934 1 19961122 G 6210 206015001107 BLADE BELL 206 206L1 1182107 SW M/R DEBONDED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 1078N 3494 A495 45389 DURING A LIGHTNING STRIKE INSPECTION, FOUND CORROSION AND DEBONDING OVER SPAR AT TIP (SKIN). 1 G 7 1 3U H2SW 1997030600712 19970306 00712 SW 1997 3 6 97ZZZX935 1 19961227 G 6220 206310005101 BOLT 206011100159 BELL 206 206L1 1182107 SW M/R HUB BROKE B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 1084Y 948 AAB00059 45433 M/R HUB CAME INTO OVERHAUL SHOP FOR REPAIR DUE TO LEAKING GREASE. TECHNICIAN DID A ROUTINE TORQUE CHECK OF PILLOW BLOCK BOLTS. ONE BOLT BROKE BEFORE REACHING 120 INCH/POUNDS WHICH IS MINIMUM TORQUE. THE BOLT BROKE IN THREADS APPROXIMATEL Y .3750 INCH FROM END. THE BOLT SHOWED SIGNS OF CORROSION IN THREADS AT THIS POINT. CORROSION WAS PRESENT IN THE BREAK AREA. THE THREE REMAINING BOLTS WERE REPLACED. CORROSION WAS PRESENT IN ONE OTHER BOLT IN THE SAME LOCATION. 1 G 7 1 3U H2SW 1997030600714 19970306 00714 GL 1997 3 6 97ZZZX937 2 19961223 G 7260 216002 DRIVE SHAFT 6896 BELL 206 206L4 1182110 SW ALLSN 250C 250C30P 03013 GL FUEL PUMP WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 176AL 1458 52146 DURING 1500 HOUR FUEL PUMP DRIVE SHAFT INSPECTION FOUND P/N 216002 DRIVE SHAFT WORN AND P/N 215988-1 GEAR WORN BEYOND LI MITS. THIS UNIT WOULD PROBABLY NOT HAVE MADE OVERHAUL WITHOUT RAILING. 1 G 7 1 3U 3 U NC H2SW E1GL 1997030600715 19970306 00715 SW 1997 3 6 97ZZZX938 1 19961105 G 5320 212030495001S WEB ASSY BELL 212 212 1181420 SW HELL HOLE CRACKED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 29AL 30569 MAJOR INSPECTION FOUND WEB CRACKED LOWER LEFT CORNER OF AFT WEB. C/W T.B. 212-76-18. 1 G 7 1 4U H4SW 1997030600716 19970306 00716 SW 1997 3 6 97ZZZX939 1 19961122 G 6210 206015001107 BLADE BELL 206 206L1 1182107 SW M/R CORRODED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 3190P 3394 A450 45779 DISCOVERED DURING DAILY INSPECTION, FOUND TIP BLOCK AND WEIGHT PACKAGE CORRODED AND CAUSED SPAR TO BECOME DEFORMED AT TI P. 1 G 7 1 3U H2SW 1997030600717 19970306 00717 SW 1997 3 6 97ZZZX940 1 19961219 G 5311 206032308103 FRAME BELL 206 206L3 1182108 SW FS 231.48 CRACKED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 346AL 7821 51378 AT MAJOR INSPECTION FOUND CRACK AT BOLT ATTACH ON FRAME P/N 206-032-308-103. SUBMITTER STATED T.B. 206L-94-169 WAS ISSU ED TO REDUCE CRACKING OF FRAME P/N 206-032-308-103. THIS IS NOT ADEQUATE. 1 G 7 1 3U H2SW 1997030600718 19970306 00718 SW 1997 3 6 97ZZZX941 1 19961017 G 6420 206011819109 YOKE 206011810145 BELL 206 206L3 1182108 SW T/R HUB MISMANUFACTURED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 358AL 549 549 AFS7556 51460 WHILE TRYING TO SET FLAP ANGLE ON BLADES, FOUND YOKE INBOARD WHERE BLADE MOUNTS ARE NOT MILLED OUT ENOUGH TO PROPERLY SE T BLADE FLAP ANGLE. YOKE NOT AIRWORTHY. 1 G 7 1 3U H2SW 1997030600719 19970306 00719 EU 1997 3 6 97ZZZX942 1 19960828 G 6210 355A11002006 BLADE AEROSP AS355 AS355F 8680806 EU M/R CRACKED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 378E 3880 5214 DURING DAILY INSPECTION FOUND LOWER BLADE SURFACE CRACKED CHORDWISE AT STA 1397 MM. CRACK EXTENDS FROM TRAILING EDGE FO RWARD 110 MM. 1 G 7 2 3U H11EU 1997030600720 19970306 00720 SW 1997 3 6 97ZZZX943 1 19961122 G 6210 206010200033 BLADE BELL 206 206B 1181511 SW M/R SEPARATION B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 3912Q 4137 CS1577 3271 DISCOVERED DURING DAILY INSPECTION FOUND CORROSION AND SEPARATION BENEATH LOWER GRIP DOUBLES AND BETWEEN LOWER SKIN AND SPAR. CORROSION ON TRAILING EDGE UPPER AND LOWER SURFACES. 1 G 7 1 3U H2SW 1997030600721 19970306 00721 NE 1997 3 6 97ZZZX944 1 19961014 G 6410 BEARING SKRSKY S76 S76A 8143006 NE T/R WORN B ALGR D RETURN TO BLOCK O OTHER IN INSP/MAINT 1 SW 03 710AL 760279 DISCOVERED DURING 500 HOUR INSPECTION, T/R PADDLE 'A' PIVOT BEARING WORN EXCESSIVELY. PADDLE 'B' LEADING EDGE STRIP CRA CKED AT TIP. 1 G 7 2 3U H1NE 1997030600722 19970306 00722 NE 1997 3 6 97ZZZX945 1 19960922 G 5414 SKIN SKRSKY S76 S76A 8143006 NE TAIL PYLON CRACKED B S ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 768AL 760031 DURING PHASE INSPECTION, FOUND CRACK IN PYLON SKIN ACROSS RIVET HOLE. THIS CRACK EMANATED FROM CORROSION OF THE SKIN. F URTHER INSPECTION REVEALED CORROSION ON VARIOUS MEMBERS IN THE PYLON. 1 G 7 2 3U H1NE 1997030600726 19970306 00726 EU 1997 3 6 97ZZZX949 1 19961227 G 3212 C178131 HOSE BOLKMS 105 BO105S 5626006 EU FLOAT FAILED B AC2R K NONE O OTHER IN INSP/MAINT 1 SW 03 8775 S775 HIGH FAILURE RATE OF NR 1 AND NR 4 HOSES ON BO105 FLOATS, P/N D24873-101 AND 102 DUE TO KINKS. REPLACED HOSES. 1 G 7 2 3U H3EU 1997010900430 19970109 00430 WP 1997 1 9 97ZZZX95 1 19961127 G 6510 24597 DRIVESHAFT HILLER UH12 UH12E 4360122 WP T/R CRACKED B S NTWR K NONE O OTHER IN INSP/MAINT 1 NM 01 65NW 1338 2364 DURING POST-FLIGHT INSPECTION, PILOT FOUND 1 INCH CRACKS EMANATING FROM RIVETS THAT ATTACH BALANCE WEIGHTS TO INTERIOR T O DRIVESHAFT. SUBMITTER RECOMMENDS THIS AREA BE DYE-PENETRANT INSPECTED DURING 1800 HR INSPECTION OF DRIVESHAFT. SHAFT INSTALLED ON TURBINE CONVERTED AIRCRAFT. (STC S4178WE). 1 G 7 1 3O 4H11 1997030600844 19970306 00844 SW 1997 3 6 97ZZZX956 1 19961125 G 2910 70053H000A100 LINE BELL 206 206L3 1182108 SW HYD PUMP LEAK H L N1UM O OTHER K FLUID LOSS AP APPROACH 1 EA 11 608PD 2735 51270 WHILE FLYING BACK TO BASE, PILOT REPORTED COMPLETE HYDRAULIC FAILURE APPROX 3 MINUTES OUT. HE CONTINUED TO BASE AND A N ON-EVENTFUL LANDING WAS MADE. MAINT NOTED FLUID RUNNING DOWN SIDES OF HELICOPTER. AFTER ENTIRE DECK AREA WAS CLEANED, VISUAL INSPECTION REVEALED NO OBVIOUS DAMAGE. SYSTEM SERVICED AND A/C RUN-UP PERFORMED. AS SYSTEM PRESSURE BEGAN TO RI SE, HYD FLUID SPRAYED IN ALL DIRECTIONS FROM THE PRESSURE LINE OFF THE PUMP IN THE AREA WHERE IT IS CLAMPED TO THE LINE ABOVE IT. LINE REMOVED AND REPLACED. SYSTEM SERVICED AND DECK CLEANED. RUN-UP PERFORMED. NO LEAKS NOTED. 1 G 7 1 3U H2SW 1997030600846 19970306 00846 SW 1997 3 6 97ZZZX958 1 19961230 G 6520 206011731001 BEARING BELL 407 407 SW T/R GEARBOX MISMANUFACTURED B L A HEER K NONE O OTHER IN INSP/MAINT 1 SW 03 427PH 14 53059 TAIL ROTOR GEARBOX PITCH CHANGE MECHANISM WOULD NOT TAKE GREASE. BELL REPRESENTATIVE HAS CONFIRMED THAT BEARING RACE DI D NOT HAVE REQUIRED HOLE. BELL HAS CHANGED BEARING MANUFACTURERS. THIS BEARING IS FROM NEW MANUFACTURER. VENDOR: PIT CH LIGN RBC. VENDOR P/N : HRBC-ORSJ-7133.1. NOTE: THIS BEARING IS USED IN ALL 206L SERIES AND 407 AIRCRAFT UNDER P/N 206-011-731-001. 1 G 7 1 3U O H2SW 1997010900431 19970109 00431 EU 1997 1 9 97ZZZX96 1 19961206 G 6220 601741 BEARING 10581022 BOLKMS 105 BO105LSA3 5626020 EU VIB ABSORBER ROUGH D K NONE O OTHER IN INSP/MAINT 1 SW 99 911SV 3430 3542 2033 WHILE ROTATING VIBRATION ABSORBER, BEARINGS FELT ROUGH. AFTER PRESSING BEARING OUT OF VIB. ABS. HOUSING FOUND OUTER RAC E CRACKED. CORRESPONDING MARK ON HOUSING SHOWED THAT CRACK DID NOT OCCUR DURING REMOVAL. 1 G 7 2 3U H3AU 1997030600849 19970306 00849 EA 1997 3 6 97ZZZX961 2 19961223 G 8530 CYLINDER HUGHES 269 269C 4470504 WP LYC O360 HIO360D1A 41514 EA NR 2 BASE STUDS BROKE D K NONE O OTHER IN INSP/MAINT 1 GL 07 19CP 932 S1644 L2539051A ON TWO DIFFERENT SCHWEIZER HELICOPTERS EQUIPPED WITH HIO360D1A ENGINES, NR 2 CYLINDER BROKE 6 BASE STUDS. THE TWO THROU GH-STUDS REMAINED INTACT IN BOTH CASES. ONE ENGINE HAD 932 HOURS AND THE OTHER 1,424 HOURS SINCE MAJOR OVERHAUL. BREAK S ARE CLEAN WITH NO SIGNS OF WORKING OR LOOSENESS AND OCCURS JUST BELOW NUT. 1 G 7 1 3O 3 O 4H12 1E10 1997030600850 19970306 00850 EA 1997 3 6 97ZZZX962 2 19961223 G 8530 CYLINDER HUGHES 269 269C 4470504 WP LYC O360 HIO360D1A 41514 EA NR 2 BASE STUDS BROKE D K NONE O OTHER IN INSP/MAINT 1 GL 07 396CP 1425 S1683 L2583151A ON TWO DIFFERENT SCHWEIZER HELICOPTERS EQUIPPED WITH HIO360D1A ENGINES, NR 2 CYLINDER BROKE 6 BASE STUDS. THE TWO THROU GH-STUDS REMAINED INTACT IN BOTH CASES. ONE ENGINE HAD 932 HOURS AND THE OTHER 1,424 HOURS SINCE MAJOR OVERHAUL. BREAK S ARE CLEAN WITH NO SIGNS OF WORKING OR LOOSENESS AND OCCURS JUST BELOW NUT. 1 G 7 1 3O 3 O 4H12 1E10 1997030600860 19970306 00860 SO 1997 3 6 97ZZZX972 2 19960725 G 8550 6422118 CHECK VALVE MOONEY M20 M20K 5870220 SW CONT O360 TSIO360LB 17025 SO TURBO OIL CHAFED D K NONE K FLUID LOSS NR NOT REPORTED 1 NE 03 57195 1307 250791 316011 BOTH TURBO CHARGER OIL LINE CHECK VALVES OUTER SURFACE WORN THROUGH BY CLAMPS CAUSING SEVERE OIL LEAK (2 QUARTS AN HOUR) . 1 L 7 1 3O 3 O 2A3 E9CE 1997030600861 19970306 00861 SO 1997 3 6 97ZZZX973 2 19960725 G 8550 641068 CHECK VALVE MOONEY M20 M20K 5870220 SW CONT O360 TSIO360LB 17025 SO TURBO OIL CHAFED D K NONE K FLUID LOSS NR NOT REPORTED 1 NE 03 57195 1307 250791 316011 BOTH TURBO CHARGER OIL LINE CHECK VALVES OUTER SURFACE WORN THROUGH BY CLAMPS CAUSING SEVERE OIL LEAK (2 QUARTS AN HOUR) . 1 L 7 1 3O 3 O 2A3 E9CE 1997010900433 19970109 00433 SW 1997 1 9 97ZZZX98 1 19960826 G 2823 10648BH11 SWITCH BELL 222 222U 1182140 SW FUEL VALVE DEFECTIVE D K NONE O OTHER IN INSP/MAINT 1 NM 09 885AL 5227 47552 FUEL VALVE SWITCH IS SPRING-LOADED TO FAIL IN THE 'OFF' POSITION. IF SWITCH IS WORN, IN-FLIGHT VIBRATION COULD CAUSE SW ITCH TO POP INTO OFF POSITION RESULTING IN IMMEDIATE ENGINE SHUT-DOWN. 1 G 7 2 3U H9SW 1997010900434 19970109 00434 SW 1997 1 9 97ZZZX99 1 19960909 G 6510 DRIVESHAFT BELL 206 206L3 1182108 SW SPLINE ADAPTER BOLT LOOSE D A K NONE O OTHER IN INSP/MAINT 1 NM 05 215KH 51215 BOLT ON THE SPLINE ADAPTER TO THOMAS COUPLING CAME LOOSE CAUSING T/R SHAFT DAMAGE. SUSPECT CAUSE WAS LOW TORQUE TO NUT. TARE TORQUE ON NUT WAS CHECKED TO BE 5 INCH/POUND AT RE-ASSEMBLY. SUBMITTER SUGGESTED USE OF NEW HARDWARE EACH TIME S HAFT COMPONENTS ARE DISASSEMLBED FOR MAINTENANCE. 1 G 7 1 3U H2SW 1997031300061 19970313 00061 SW 1997 3 13 97ZZZX991 1 19961114 G 6210 107015001117 BLADE BELL 407 407 SW M/R PAINT FLAKE B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 407AL 109 A209 53044 PAINT FLAKING OFF LEADING EDGE AT TIP. 1 G 7 1 3U O H2SW 1997031300062 19970313 00062 SW 1997 3 13 97ZZZX992 1 19961114 G 6210 407015001117 BLADE BELL 407 407 SW M/R PAINT FLAKE B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 407AL 109 A338 53044 PAINT FLAKING OFF LEADING EDGE AT TIP. 1 G 7 1 3U O H2SW 1998010800420 19980108 00420 1998 1 8 98ZZZX118 4 19960628 G 2297 WIRE BRAERO 1000 BAE1251000 1500287 EU PILOT SIDE PANEL DAMAGED D K NONE O OTHER IN INSP/MAINT 1 NE 03 548QS 250 259048 HOSE CLAMP HOLDING CUSTOM MADE AIRBOX TO PILOTS SIDE PANEL WAS POSITIONED SO THAT WORM SCREW OF CLAMP FOR SCREWDRIVER SL OT END WAS CUTTING INTO WIRES ON TERMINAL BLOCK MOUNTED BELOW BOX CAUSING FAILURE OF AUTOPILOT TRIM SYSTEM. THIS CONDIT ION EXISTED ON PILOTS AND COPILOTS SIDE PANELS. THE REPAIR WAS TO POSITION HOSE CLAMP WORM SCREW AT TOP OF AIRBOX AND C OVERING WIRE TERMINAL BLOCK WITH PROTECTIVE TEFLON SHEET. DAMAGED WIRES REPAIRED AS REQUIRED. 2 L 7 2 4F RT A3EU 1998012200141 19980122 00141 CE 1998 1 22 98ZZZX226 1 19960515 G 2810 SEAL CESSNA 182 182P 2075816 CE TANK CAP LEAK D K NONE O OTHER IN INSP/MAINT 1 CE 07 182DL 18264512 SEALS FOR PLASTIC TYPE FUEL CAPS SUPPLIED WITH AIRCRAFT ARE NO LONGER AVAILABLE. DESIGN OF FUEL TANK OPENINGS (FLUSH MOU NT) ALLOWS WATER TO ENTER FUEL TANK IF SEAL INTEGRITY IS LOST. 1 H 7 1 3O NT TA13 1998100200073 19981002 00073 CE 1998 10 2 98ZZZX3578 1 19960709 G 7120 AN746A BOLT CESSNA 185 A185F 2072821 CE ENGINE BROKEN B CY4R K NONE O OTHER IN INSP/MAINT 1 AL 03 6166N 164 18504302 WHEN ATEMPTING TO LOCATE AN OIL LEAK, NOTICED THE ENGINE MOVED FAIRLY EASY ON THE MOUNTS. FURTHER INSPECTION OF THE 'LO OSE ENGINE' PROBLEM REVEALED THE RIGHT REAR BOLT SECURING THE ENGINE TO THE AIRCRAFT MOTOR MOUNT HAD BROKEN AT THE BEGIN NING OF THE THREADS. 164.3 HOURS EARLIER, NEW BOLTS HAD BEEN INSTALLED IAW CESSNA 185 PARTS AND SERVICE MANUALS. WHEN ATTEMPTING TO REPLACE THE BOLT, THE THREADED END WAS FOUND 'BOTTOMED OUT' IN THE MOUNT BRACKET. ALL 4 ENGINE MOUNTING B OLTS WERE REPLACED WITH THE LOCKING HARDWARE. 1 H 7 1 3O 3A24 1998121100007 19981211 00007 SO 1998 12 11 98ZZZX4450 2 19961204 G 7311 63917 OIL COOLER CESSNA 182 182P 2075816 CE CONT O470 O470S 17026 SO ENGINE CRACKED B MK5R K NONE K FLUID LOSS IN INSP/MAINT 1 GL 23 952CC 1003 18263638 269332R DURING A ROUTINE INSPECTION, THE OIL COOLER WAS FOUND CRACKED AT A WELD ON ONE OF ITS SUPPORT STRUTS. SUBMITTER SUGGEST ED CAUSE AS DEFECTIVE PARTS AND/OR RE-MANUFACTURE PROCESS FROM THE FACTORY. 1 H 7 1 3O 3 O NT TA13 E273 1998121100008 19981211 00008 SO 1998 12 11 98ZZZX4451 2 19960311 G 8520 641963 VALVE GUIDE CESSNA 182 182P 2075816 CE CONT O470 O470S 17026 SO ENGINE WORN B MK5R K NONE O OTHER IN INSP/MAINT 1 GL 23 952CC 400 18263638 269332R DURING A ROUTINE COMPRESSION CHECK, THE EXHAUST VALVE WAS FOUND LEAKING ON THE NR 5 CYLINDER. THE REMOVED CYLINDER, EXH AUST VALVE AND GUIDE WERE FOUND WORN OUT. SUBMITTER SUGGESTED CAUSE AS DEFECTIVE PARTS AND/OR ASSEMBLY PROCESS FROM THE FACTORY. 1 H 7 1 3O 3 O NT TA13 E273 1998121100024 19981211 00024 SO 1998 12 11 98ZZZX4467 2 19961115 G 8520 649478 CAMSHAFT CESSNA 182 182Q 2072732 CE CONT O470 O470U 17026 SO ENGINE SCORED B MK5R K NONE O OTHER IN INSP/MAINT 1 GL 23 954CC 800 18265290 286937R A ROUTINE OIL CHANGE AND OIL FILTER INSPECTION REVEALS EXCESSIVE METAL. FURTHER INVESTIGATION FINDS THE CAMSHAFT HAS FA ILED ON CERTAIN CAM LOBES. ENGINE IS REMOVED FROM SERVICE. SUBMITTER SUGGESTED POSSIBLE CAUSE AS DEFECTIVE PART. 1 H 7 1 3O 3 O NT 3A13 E273 1998121100027 19981211 00027 SO 1998 12 11 98ZZZX4470 2 19960907 G 8530 649168 VALVE GUIDE CESSNA 182 182Q 2072732 CE CONT O470 O470U 17026 SO ENGINE EXHAUST WORN B MK5R K NONE O OTHER IN INSP/MAINT 1 GL 23 954CC 700 18265290 286937R DURING A ROUTINE COMPRESSION CHECK, LEAKAGE WAS FOUND ON THE EXHAUST VALVES ON THE NR 1 AND NR 3 CYLINDERS. THE REMOVED CYLINDERS, EXHAUST VALVES AND GUIDES WERE FOUND WORN OUT. SUBMITTER SUGGESTED POSSIBLE CAUSE AS DEFECTIVE PARTS AND/OR ASSSEMBLY PROCES FROM THE FACTORY. 1 H 7 1 3O 3 O NT 3A13 E273 1998121100030 19981211 00030 SO 1998 12 11 98ZZZX4473 2 19960214 G 8530 653443 VALVE GUIDE CESSNA 182 182P 2075816 CE CONT O470 O470S 17026 SO ENGINE EXHAUST WORN B MK5R K NONE O OTHER IN INSP/MAINT 1 GL 23 953CC 814 18264109 269314R DURING A ROUTINE COMPRESSION CHECK, THE EXHAUST VALVE ON THE NR 2 CYLINDER WAS FOUND LEAKING. THE REMOVED CYLINDER, EXH AUST VALVE AND GUIDE WERE FOUND WORN OUT. SUBMITTER SUGGESTED POSSIBLE CAUSE AS DEFECTIVE PARTS OR ASSEMBLY PROCESS AT THE FACTORY. 1 H 7 1 3O 3 O NT TA13 E273 1999051400482 19990514 00482 CE 1999 5 14 99ZZZX2002 1 19960307 G 7500 45A403061 DUCT BEECH MU300 400A 1155402 CE BLEED AIR FAILED H K NONE O OTHER IN INSP/MAINT 1 GL 05 1594 DURING THE PHASE 4 INSPECTION, DISCOVERED THE DUCT ASSEMBLY HAD FAILED AND SEPARATED. THE DUCT ASSEMBLY CENTER BLEED AI R CROSS-OVER FAILED AT THE FLEX JOINT AREA WHERE WIRE MESH IS INSTALLED. (BEECHJET 400T - COMMERCIAL COUNTERPART BEECHJ ET 400A). 2 H 7 2 4F RT A16SW 1999052100084 19990521 00084 EU 1999 5 21 99ZZZX2052 1 19960401 G 2910 LINE DUNLOP BRAERO DH125 HS125700A 4230170 EU HYDRAULIC SYSTEM CORRODED H A K NONE K FLUID LOSS IN INSP/MAINT 1 SO 17 500EF 257086 HYDRAULIC HOSE FAILURE DUE TO CORROSION OF METAL BRAID AND SWAGE. THIS IS COVERED BY PLASTIC MATERIAL IN WHICH UNABLE T O SEE UNLESS THE PLASTIC IS PEELED BACK. NOTE: SAME P/N HOSES ON EARLY RAYTHEON MODELS HAVE A MANDATORY LIFE LIMITATIO N, BUT THE 700 SERIES AIRCRAFT WAS NOT INCLUDED. 2 L 7 2 4F A3EU 1996110700104 19961107 00104 WP 1996 11 7 A3L2207J 1 19961104 G 3246 2601483 BOLT BENDIX 2608891 DOUG DC9 DC981 3022081 WP WHEEL FAILURE B A3L2 K NONE O OTHER IN INSP/MAINT 1 SW 09 B1097 FATIGUE RELATED FAILURE OF MD80 WHEEL TIE BOLTS. SUSPECT INSUFFICIENT TIE BOLT PRELOAD TORQUE. SUBMITTER SUGGESTS TO U SE SNUG ANGLE TORQUE METHOD. (X) 2 L 7 2 4F A6WE 1996022300409 19960223 00409 EU 1996 2 23 A6WR95050 1 19960117 G 2730 SL442804 ROD END BAG BAE146 BAE146200A 1500266 EU ELEV G-WEIGHT WORN B A6WR K NONE O OTHER IN INSP/MAINT 1 GL 31 292UE E2087 FOUND WORN ROD-END ON ELEVATOR G-WEIGHT CONNECTING ROD. REPLACED ROD-END AND RIGGED SYSTEM IAW AMM. (X) 2 H 7 4 4F RT A49EU 1996022300725 19960223 00725 EU 1996 2 23 A6WR95051 1 19960117 G 5320 HC536B0444000 FREIGHT ANGLE BAG BAE146 BAE146200A 1500266 EU FS FR 21 CRUSHED B A6WR K NONE O OTHER IN INSP/MAINT 1 GL 31 292UE E2087 FORWARD CARGO BAY FREIGHT ANGLE AT FRAME 21 CRUSHED. REPLACED FREIGHT ANGLE. (X) 2 H 7 4 4F RT A49EU 1996020200312 19960202 00312 EU 1996 2 2 A6WR95052 1 19960117 G 5520 HC551B0087000 BOLT BAG BAE146 BAE146200A 1500266 EU LT ELEV HINGE DAMAGED B A6WR K NONE O OTHER IN INSP/MAINT 1 GL 31 292UE E2087 DURING STRUCTURAL INSPECTION, FOUND LT ELEVATOR NR 2 HINGE LOWER A-FRAME BOLT TO HAVE DAMAGED THREADS AND CORROSION. RE PLACED BOLTS. (X) 2 H 7 4 4F RT A49EU 1996030100226 19960301 00226 EU 1996 3 1 A6WR95053 1 19960117 G 5520 HC551B0087000 BOLT BAG BAE146 BAE146200A 1500266 EU LT ELEV HINGE CORRODED B A6WR K NONE O OTHER IN INSP/MAINT 1 GL 31 292UE E2087 DURING STRUCTURAL INSPECTION, FOUND CORROSION ON LT ELEVATOR NR 2 HINGE UPPER A-FRAME BOLT. REPLACED BOLT. (X) 2 H 7 4 4F RT A49EU 1996030100227 19960301 00227 EU 1996 3 1 A6WR95054 1 19960117 G 5520 HC551B0086000 BOLT BAG BAE146 BAE146200A 1500266 EU RT ELEV HINGE CORRODED B A6WR K NONE O OTHER IN INSP/MAINT 1 GL 31 292UE E2087 DURING STRUCTURAL INSPECTION, FOUND RT ELEVATOR NR 1 HINGE A-FRAME LOWER BOLT CORRODED. REPLACED BOLT. (X) 2 H 7 4 4F RT A49EU 1996020900319 19960209 00319 EU 1996 2 9 A6WR95055 1 19960117 G 5520 HC551B0087000 BOLT BAG BAE146 BAE146200A 1500266 EU RT ELEV HINGE CORRODED B A6WR K NONE O OTHER IN INSP/MAINT 1 GL 31 5520 E2087 DURING STRUCTURAL INSPECTION, FOUND RIGHT ELEVATOR NR 2 HINGE A-FRAME UPPER BOLT CORRODED. REPLACED BOLT. (X) 2 H 7 4 4F RT A49EU 1996022300410 19960223 00410 EU 1996 2 23 A6WR95056 1 19960117 G 4930 SA767006158 HOSE BAG BAE146 BAE146200A 1500266 EU APU FUEL DEFECTIVE B A6WR K NONE O OTHER IN INSP/MAINT 1 GL 31 292UE E2087 DURING SCHEDULED INSPECTION, FOUND EXTERIOR COVERING OF APU FUEL SUPPLY HOSE BROKEN OPEN. REPLACED FUEL HOSE. (X) 2 H 7 4 4F RT A49EU 1996020900028 19960209 00028 EU 1996 2 9 A6WR95057 1 19960117 G 5751 HC572H0910004 BOLT BAG BAE146 BAE146200A 1500266 EU RT AIL RIB CORRODED B A6WR K NONE O OTHER IN INSP/MAINT 1 GL 31 292UE E2087 DURING STRUCTURAL INSPECTION, FOUND RIGHT AILERON RIB 18 UPPER A-FRAME BOLT CORRODED. REPLACED BOLT. (X) 2 H 7 4 4F RT A49EU 1996022300411 19960223 00411 NE 1996 2 23 A6WR95058 2 19960117 G 7240 COMBUSTION CASE BAG BAE146 BAE146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE NR 1 ENGINE FLANGE CRACKED B A6WR K NONE O OTHER IN INSP/MAINT 1 GL 31 292UE E2087 LF05442A DURING SCHEDULED INSPECTION, FOUND BLEED AIR FLANGE AT 3 O'CLOCK POSITION ON COMBUSTION CASE CRACKED. REPAIRED IAW TEXT RON (ALLIED SIGNAL) ENGINE MM. (X) 2 H 7 4 4F 4 F RT A49EU E6NE 1996022300412 19960223 00412 EU 1996 2 23 A6WR95059 1 19960117 G 5400 HC361C0042000 BRACKET BAG BAE146 BAE146200A 1500266 EU NR 4 PYLON BROKEN B A6WR K NONE O OTHER IN INSP/MAINT 1 GL 31 292UE E2087 DURING SCHEDULED INSPECTION, FOUND BOTH LEFT SIDE BRACKETS SUPPORTING PRESSURE REGULATING/ISOLATION VALVE BROKEN IN NR 4 PYLON. REPLACED BRACKETS. REFERENCE: OPERATOR CONTROL NR 96ZZZX760. (X) 2 H 7 4 4F RT A49EU 1996022300413 19960223 00413 EU 1996 2 23 A6WR95060 1 19960117 G 5400 PYLON BAG BAE146 BAE146200A 1500266 EU NR 4 RIVETS SHEARED B A6WR K NONE O OTHER IN INSP/MAINT 1 GL 31 292UE E2087 DURING SCHEDULED INSPECTION, FOUND 3 RIVETS SHEARED OFF IN NR 4 PYLON BOX AT POSITIONS B, C, D. REPLACED FASTENERS IAW AVRO RL HC546H9009. (X) 2 H 7 4 4F RT A49EU 1996020200313 19960202 00313 EU 1996 2 2 A6WR95061 1 19960117 G 5755 HC276H0075002 BOLT BAG BAE146 BAE146200A 1500266 EU LT WING SPOILER CRACKED B A6WR K NONE O OTHER IN INSP/MAINT 1 GL 31 292UE E2087 DURING SCHEDULED NDT INSPECTION, FOUND CRACK INDICATION ON LEFT WING INBOARD AFT SPOILER JACK ATTACH BOLT. REPLACED BOL T. (X) 2 H 7 4 4F RT A49EU 1996020900029 19960209 00029 EU 1996 2 9 A6WR95062 1 19960117 G 5753 HC579L0097000 PIVOT PIN BAG BAE146 BAE146200A 1500266 EU RT FLAP NR 3 CRACKED B A6WR K NONE O OTHER IN INSP/MAINT 1 GL 31 292UE E2087 DURING SCHEDULED NDT INSPECTION, FOUND NR 3 RIGHT FLAP TRACK TAB OPERATING ROD-TO-CROSSHEAD, PIVOT PIN WITH CRACK INDICA TION. REPLACED PIN. (X) 2 H 7 4 4F RT A49EU 1996022300414 19960223 00414 EU 1996 2 23 A6WR95063 1 19960117 G 2710 HC270H0135004 CONTROL CABLE BAG BAE146 BAE146200A 1500266 EU AILERON CORRODED B A6WR K NONE O OTHER IN INSP/MAINT 1 GL 31 292UE E2087 DURING SCHEDULED INSPECTION FOUND AILERON INTERCONNECT CABLES CORRODED AT WING ROOT PULLEYS. REPLACED CABLES. REFERENC E: OPERATOR CONTROL NR 96ZZZX761. (X) 2 H 7 4 4F RT A49EU 1996020900030 19960209 00030 EU 1996 2 9 A6WR95064 1 19960117 G 5320 H5113381C7 JO-BOLT BAG BAE146 BAE146200A 1500266 EU FR 29, STR 12 RT FAILED B A6WR K NONE O OTHER IN INSP/MAINT 1 GL 31 292UE E2087 DURING SCHEDULED INSPECTION, FOUND BROKEN HEAD ON JO-BOLT AT FRAME 29, STR 12 RIGHT. REPLACED JO-BOLT. (X) 2 H 7 4 4F RT A49EU 1996030100228 19960301 00228 EU 1996 3 1 A6WR95065 1 19960117 G 5320 HC537H0654000 PLATE BAG BAE146 BAE146200A 1500266 EU FR 15-18 CORRODED B A6WR K NONE O OTHER IN INSP/MAINT 1 GL 31 292UE E2087 DURING STRUCTURAL INSPECTION, FOUND TWO SUPPORT PLATES AT 3RD INTERCOSTAL INBOARD FROM LT FORWARD PASSENGER DOOR BETWEEN FUSELAGE FRAMES 15 AND 18 CORRODED. REPLACED BOTH PLATES. REFERENCE: OPERATOR CONTROL NR 96ZZZX824. (X) 2 H 7 4 4F RT A49EU 1996030100229 19960301 00229 EU 1996 3 1 A6WR95066 1 19960117 G 5320 HC537H0650006 INTERCOSTAL BAG BAE146 BAE146200A 1500266 EU LT FWD FR 15-18 CORRODED B A6WR K NONE O OTHER IN INSP/MAINT 1 GL 31 292UE E2087 DURING STRUCTURAL INSPECTION, FOUND 2ND INTERCOSTAL INBOARD FROM LT FORWARD PASSENGER DOOR, BETWEEN FRAMES 15 AND 18, CO RRODED. REPLACED INTERCOSTAL. (X) 2 H 7 4 4F RT A49EU 1996022300726 19960223 00726 EU 1996 2 23 A6WR95067 1 19960117 G 5400 HC546C0075002 BRACKET BAG BAE146 BAE146200A 1500266 EU PYLON COWL MT CRACKED B A6WR K NONE O OTHER IN INSP/MAINT 1 GL 31 292UE E2087 DURING SCHEDULED INSPECTION, FOUND NR 1 PYLON SHOULDER COWL LORD MOUNT ATTACHMENT BRACKET CRACKED. REPLACED BRACKET. ( X) 2 H 7 4 4F RT A49EU 1996030100230 19960301 00230 EU 1996 3 1 A6WR95068 1 19960117 G 5400 HC546C0075002 BRACKET BAG BAE146 BAE146200A 1500266 EU NR 2 PYLON MOUNT CRACKED B A6WR K NONE O OTHER IN INSP/MAINT 1 GL 31 292UE E2087 DURING SCHEDULED INSPECTION, FOUND NR 2 PYLON LORD MOUNT EYE BOLT BRACKET CRACKED. REPLACED BRACKET. (X) 2 H 7 4 4F RT A49EU 1996020900031 19960209 00031 EU 1996 2 9 A6WR95069 1 19960117 G 5400 RIVETS BAG BAE146 BAE146200A 1500266 EU NR 3 PYLON SHEARED B A6WR K NONE O OTHER IN INSP/MAINT 1 GL 31 292UE E2087 DURING SCHEDULED INSPECTION, FOUND 4 RIVETS SHEARED OFF IN NR 3 PYLON BOX AT POSITIONS A, B, C, AND D. REPLACED FASTENE RS IAW AVRO RIL HC546H9009. (X) 2 H 7 4 4F RT A49EU 1996022300727 19960223 00727 EU 1996 2 23 A6WR95070 1 19960117 G 5400 RIVETS BAG BAE146 BAE146200A 1500266 EU NR 2 PYLON BOX SHEARED B A6WR K NONE O OTHER IN INSP/MAINT 1 GL 31 292UE E2087 DURING SCHEDULED INSPECTION FOUND 2 RIVETS SHEARED OFF IN NR 2 PYLON BOX AT POSITIONS C AND D. REPLACED FASTENERS IAW A VRO RIL HC546H9009. (X) 2 H 7 4 4F RT A49EU 1997041600001 19970416 00001 NM 1997 4 16 ANCF9600001 1 19960919 G 3240 BRAKE BENDIX BOEING 767 767383 1385214 NM MLG OVERHEATED W ANCF C D ABORTED TAKEOFF RETURN TO BLOCK J WARNING INDICATION TO TAKEOFF 1 SO 23 984AN 24357 FLT 014 BOG-PAR. DURING T/O ROLL AFTER PASSING 80 KNOTS, THE BRAKE TEMP LIGHT CAME ON. WAS NECESSRY TO MAKE A REJECTED T/O. INSPECTION ACCOMPLISHED ACCORDING MM 32-42800. ALL NORMAL. TIRES NRS 1, 2, 6, 7, AND 8 WERE CHANGED. (X) 2 L 7 2 4F RT A1NM 1997041600002 19970416 00002 NM 1997 4 16 ANCF9600002 1 19961003 G 5210 DOOR BOEING 767 767383 1385214 NM LT FWD UNLOCKED W ANCF B A EMER. DESCENT UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 SO 23 984AN 24357 AIR RETURN: DURING FLIGHT FROM SKGT TO SKBO AT 28,000 FEET, FWD ENTRY DOOR LIGHT ILLUMINATED WITH EICAS MESSAGE. FLIGH T ATTENDANT REPORTED THE DOOR HANDLE COMING OUT OF LOCKED POSITION AND STRONG NOISE. CABIN ALTITUDE INCREASED RAPIDLY, BUT WAS CONTROLLED IN MANUAL. EMERGENCY DESCENT EXECUTED. CABIN ALT DID NOT EXCEDE 10,000 FEET. AIRCRAFT RETURNED TO SKGT. CHECKED DOOR LOCK MECHANISM, AND FOUND LOCK OF THE DOOR LEVER (EXTERIOR SIDE) UNLOCKED. IT WAS REPOSITIONED. (X ) 2 L 7 2 4F RT A1NM 1996060600137 19960606 00137 WP 1996 6 6 ARWR960356 1 19960513 G 5754 SKIN DOUG DC8 DC862 3021970 WP STA XW 217.875 GOUGED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND LEFT OUTBOARD FLAP APPROXIMATE STA XW217.875 ICE SHIELD LEADING EDGE FLAP CUT-OUT AREA WITH GOUGES AT UPPER SKIN AREA (FRONT SPAR). REPAIRED AREA IAW DER DWG MHA3052. APPLIED CORROSION X IAW SRM 51-1-8 AND CLOSED L/E PANEL IAW SRM 51-3-0. (X) 2 L 7 4 4F 4A25 1996060600138 19960606 00138 WP 1996 6 6 ARWR960395 1 19960513 G 5330 SKIN DOUG DC8 DC862 3021970 WP C4 DOOR CUT-OUT CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND LOWER AFT FUSELAGE C-4 CARGO DOOR CUT-OUT HAS CORROSION THROUGH. CUT-OUT DAMAGED SECTION, FABRICA TED DOUBLER AND TRIPLER AND INSTALLED IAW DER NR MHA 3057. TREATED AND PRIMED IAW SRM 51-1-8, SEALED AREA IAW SRM 51-1- 14. REPAIRED UNDER DAC GLP 1748-96-05-02-009. (X) 2 L 7 4 4F 4A25 1996060600139 19960606 00139 WP 1996 6 6 ARWR960418 1 19960513 G 5330 SKIN DOUG DC8 DC862 3021970 WP FS 1180 L36 MISREPAIRED B ARWR K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND LOWER AFT FUSELAGE HAS TEMP PLUG AT STA FS 1180.000 AND L36 APPROXIMATELY. FABRICATED AND INSTALL ED DOUBLER IAW DER NR M.H.A. 3061. TREATED AND PRIMED IAW SRM 51-1-8. INSTALLED IAW 51-1-21. (X) 2 L 7 4 4F 4A25 1996061300056 19960613 00056 WP 1996 6 13 ARWR960442 1 19960514 G 5240 DOOR DOUG DC8 DC862 3021970 WP AFT ACCESS CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 47060 DURING C-CHECK, FOUND AFT FUSELAGE ACCESS DOOR, NR 60, HAS CORROSION. REMOVED DOOR, CLEANED CORROSION, FABRICATED DOUBL ER PER DER ARW 950082-1420. INSTALLED REPAIR PER DER ARW 950085-1420. (X) 2 L 7 4 4F 4A25 1996061300057 19960613 00057 WP 1996 6 13 ARWR960447 1 19960514 G 5320 DOUBLER DOUG DC8 DC862 3021970 WP FS 1520-1530 CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND AFT FUSELAGE SKIN DOUBLER HAS CORROSION FROM FS 1520.000 AND FS 1530.000 AND BETWEEN L23L AND L23R . REMOVED DOUBLER, REMOVED CORROSION, FABRICATED AND INSTALLED IAW DER NR 96IALE-005D-10, TREATED AND PRIMED IAW SRM 51 -1-8 AND SEALED AREA IAW SRM 51-1-4. (X) 2 L 7 4 4F 4A25 1996060600140 19960606 00140 WP 1996 6 6 ARWR960454 1 19960515 G 5247 DOOR DOUG DC8 DC862 3021970 WP AFT FUS NR 62 CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND AFT FUSELAGE ACCESS DOOR NR 62 AND DOOR CUT-OUT HAVE CORROSION. REMOVED CORROSION ON DOOR CUT-OUT IAW SRM 51-1-8, FOUND WITHIN LIMITS IAW SRM 53-2-0. REPAIRED DOOR IAW ARW 950082-1420. (X) 2 L 7 4 4F 4A25 1996061300058 19960613 00058 WP 1996 6 13 ARWR960467 1 19960514 G 5330 SKIN DOUG DC8 DC862 3021970 WP FS 1438-1480 CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND AFT LOWER FUSELAGE SKIN JOINT HAS CORROSION AT L31R FROM FS 1380.000 TO FS 1480.000. CUT OUT DAMA GED SECTION, FABRICATED FILLER AND DOUBLER, AND INSTALLED IAW DER NR 96IALE-0050-12. TREATED AND PRIMED IAW SRM 51-1-8. SEALED AREA IAW SRM 51-1-14. (X) 2 L 7 4 4F 4A25 1996060600141 19960606 00141 WP 1996 6 6 ARWR960493 1 19960508 G 5330 SKIN DOUG DC8 DC862 3021970 WP MAIN ENT DOOR DAMAGED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 WHILE PERFORMING C-CHECK INSPECTION, FOUND MAIN ENTRY DOOR CUT-OUT, LOWER AFT DOUBLER REPAIR, NEEDS APPROVED REPAIR COMP LIANCE VERTIFICATION. CUT OUT DAMAGED SECTION, FABRICATED DOUBLER AND INSTALLED IAW DER DOUGLAS NR 96-03-07-007. TREAT ED AND PRIMED IAW SRM 51-1-8. REMOVED AND INSTALLED SCUFF PLATE IAW SRM 51-1-21. (X) 2 L 7 4 4F 4A25 1996060600142 19960606 00142 WP 1996 6 6 ARWR960595 1 19960513 G 5320 DOUBLER DOUG DC8 DC862 3021970 WP FS 1200-1260 CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND UPPER FUSELAGE SKIN DOUBLER REPAIR NEEDS APPROVED REPAIR VERIFICATION BETWEEN FS 1200.000 - FS 126 0.000, LONGERON 21L. INSTALLED REPAIR IAW DER NR MHA 3060. (X) 2 L 7 4 4F 4A25 1996060600143 19960606 00143 WP 1996 6 6 ARWR960606 1 19960522 G 5320 WINDOW FRAME DOUG DC8 DC862 3021970 WP RT FS 1020 CRACKED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND WORKING FASTENERS AND CRACK AROUND WINDOW FRAME, RT STA 1020.00. REPAIRED IAW DER DRAWING NR GLP 1681, SRM 51-1-8 AND SRM 51-11-40. (X) 2 L 7 4 4F 4A25 1996061300059 19960613 00059 WP 1996 6 13 ARWR960609 1 19960514 G 5330 SKIN DOUG DC8 DC862 3021970 WP FS 1130-1140 MISREPAIR B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND UPPER FUSELAGE SKIN DOUBLER REPAIR BETWEEN FS 1130.000 AND FS 1140.000 AT L21R NEED APPROVED REPAI R VERIFICATION. REMOVED DOUBLER, FABRICATED WITH 7075-T6. TREATED AREAS WITH ALODINE AND F.R. PRIMER IAW SRM 51-1-8. I NSTALLED REPAIR DOUBLER WITH FASTENERS AS REQUESTED. ALL WORK PERFORMED PER D.E.R. ARW NR 950082-0677. (X) 2 L 7 4 4F 4A25 1996060600144 19960606 00144 WP 1996 6 6 ARWR960645 1 19960515 G 5330 SKIN DOUG DC8 DC862 3021970 WP FS 270 L16R GOUGED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND UPPER FUSELAGE SKIN GOUGED AT FS 270.000 AND L16R. REMOVED DAMAGE, FABRICATED, TREATED AND PRIMED DOUBLER. INSTALLED DOUBLER IAW DER 950082-0548. (X) 2 L 7 4 4F 4A25 1996061300060 19960613 00060 WP 1996 6 13 ARWR960655 1 19960514 G 5330 SKIN DOUG DC8 DC862 3021970 WP FS 857-1000 DAMAGE B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND UPPER FUSELAGE SKIN HAS AREAS WITH HEAVY BLEND-OUTS. NEEDS TO BE CHECKED FOR LIMITS BETWEEN FS 85 7.000 AND FS 1000.000 AND BETWEEN L17R AND L21R. FABRICATED AND INSTALLED DOUBLERS AT STA 857 IAW DER NR 96IALE-005D-11 AND AT STA 902 IAW DER NR 961ALE-005D-9. SEALED AREAS IAW SRM 51-1-16. (X) 2 L 7 4 4F 4A25 1996061300415 19960613 00415 WP 1996 6 13 ARWR960657 1 19960522 G 5330 SKIN DOUG DC8 DC862 3021970 WP FS 980-1000 CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK INSPECTION, FOUND UPPER FUSELAGE SKIN AROUND FASTENERS HAS CORROSION AND WORKING FASTENERS, RT FUSELAGE, STA 980.000 TO STA 1000.000. REPAIRED IAW DER DRAWING NR GLP 1681/96-22-14-003. TREATED AND PRIMED IAW SRM 51-1-8. 2 L 7 4 4F 4A25 1996053000058 19960530 00058 WP 1996 5 30 ARWR960700 1 19960426 G 5530 SKIN DOUG DC8 DC862 3021970 WP V-FIN LE ATTACH CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND VERTICAL FIN LEADING EDGE LOWER PANEL LOWER ATTACH SCREW HOLE AREA HAS CORROSION. REMOVED DAMAGED AREA IAW SRM 55-2-1, FABRICATED FILLER AND DOUBLER IAW SRM 55-2-1, PAGES 17-18, ALODINED AND PRIMED IAW SRM 51-1-8. IN STALLED REPAIR IAW SRM 55-2-1. REF: OPERATOR CONTROL NR 0700. (X) 2 L 7 4 4F 4A25 1996082900363 19960829 00363 WP 1996 8 29 ARWR9607001 1 19960730 G 5330 SKIN DOUG DC8 DC862 3021970 WP FS 255-265 CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 1808E 6255 46105 INNER SKIN BETWEEN FS 255 AND FS 265 CORRODED AT LONGERON 21R. CUT OUT AREA OF CORROSION, FABRICATED AND INSTALLED 7075 .T6 .025 INCH FILLER AND 7075.T6 .032 INCH DOUBLER IAW MHA ENGINEERING, INC., E. O. MHA-3066 UNDER AMRC W. O. 960165. ( X) 2 L 7 4 4F 4A25 1996082900362 19960829 00362 WP 1996 8 29 ARWR9607002 1 19960730 G 5320 ANGLE DOUG DC8 DC862 3021970 WP FS 225R-275R CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 1808E 6255 46105 FLOOR PANEL SUPPORT ANGLE AT FS 225R TO FS 273R CORRODED AT FLOOR LEVEL. CUT OUT CORRODED AREA. FABRICATED AND INSTALL ED 2024.T3 .063 INCH FILLER AND 2024.T3 .071 INCH DOUBLER IAW MHA ENG. INC., E. O. MHA-3065 UNDER AMRC W. O. 960165. (X ) 2 L 7 4 4F 4A25 1996082900361 19960829 00361 WP 1996 8 29 ARWR9607003 1 19960730 G 5315 FLOOR BEAM DOUG DC8 DC862 3021970 WP FS 235 LBL 66 CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 1808E 6255 46105 FLOOR BEAM AT STA 235 AT LBL 66 CORRODED SECTION AT DUCT CUT-OUT. MECHANICALLY REMOVED CORRODED SECTION. FABRICATED AN D INSTALLED 7075.T6 .090 INCH DOUBLER IAW MHA ENGINEERING, INC., E. O. MHA-3067 UNDER AMRC W.O. 960165. (X) 2 L 7 4 4F 4A25 1996060600145 19960606 00145 WP 1996 6 6 ARWR960706 1 19960515 G 5330 SKIN DOUG DC8 DC862 3021970 WP FS 822-857 L22R CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND UPPER FUSELAGE SKIN HAS CORROSION BETWEEN FS 822.500 AND FS 857.125, L22R. CUT OUT DAMAGED SECTIO N, FABRICATED FILLER AND DOUBLER. INSTALLED REPAIR IAW DER NR ARW 95 0082-1004. TREATED AND PAINTED AREA IAW SRM 51-1- 8. SEALED AREAS ARE IAW SRM 51-1-14. (X) 2 L 7 4 4F 4A25 1996060600146 19960606 00146 WP 1996 6 6 ARWR960712 1 19960508 G 5754 SLOT DOOR DOUG DC8 DC862 3021970 WP LT WING INBD CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 WHILE PERFORMING C-CHECK, FOUND LEFT WING, INBOARD SLOT DOOR TOPSIDE, HAS EXFOLIATION CORROSION IN AREAS MARKED. REMOVE D CORROSION, FABRICATED AND INSTALLED DOUBLER IAW DOUBLAS AIRCRAFT ROD SKETCH NR 96-04-01-0002, AND SRM 51-1-20D AND INS TALLED SLOT DOOR IAW SRM 51-3-0. (X) 2 L 7 4 4F 4A25 1996060600147 19960606 00147 WP 1996 6 6 ARWR960818 1 19960515 G 5730 SKIN DOUG DC8 DC862 3021970 WP STUB WING CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND RT WING UPPER SURFACE NR 3 STUB WING T/E HAS CORROSION. REMOVED DAMAGED AREA, FABRICATED DOUBLER IAW DER ARW 950082-1011, TREATED AND PRIMED IAW SRM 51-1-8 AND INSTALLED IAW DER NR ARW 950082-1011. (X) 2 L 7 4 4F 4A25 1996061300062 19960613 00062 WP 1996 6 13 ARWR960947 1 19960514 G 5754 SKIN DOUG DC8 DC862 3021970 WP INB SLOT OTB TE DAMAGED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND RT WING UPPER SURFACE INBOARD SLOT, OUTBOARD TRAILING EDGE, HAS TEMPORARY REPAIR. REMOVED TEMPORA RY REPAIR, FABRICATED AND INSTALLED NEW REPAIR IAW DER NR 950082-1046. TREATED AND PRIMED IAW SRM 51-1-8. (X) 2 L 7 4 4F 4A25 1996060600148 19960606 00148 WP 1996 6 6 ARWR961076 1 19960515 G 5330 SKIN DOUG DC8 DC862 3021970 WP FS 173R-270R CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DUE TO EXCESSIVE REPAIRS AND CORROSION ON SKIN FROM FS 173R TO FS 270R, STR 21R TO STR 31R, REMOVED AND REPLACED SKIN. R EMOVED SKIN FROM FS 178.R TO FS 270.R FROM L21R TO L31 AND INSTALLED NEW SKIN IAW DER 950087-0028. (X) 2 L 7 4 4F 4A25 1996060600149 19960606 00149 WP 1996 6 6 ARWR961141 1 19960515 G 5320 56417832 CAP DOUG DC8 DC862 3021970 WP FS 208 L31R-36R CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND FUSELAGE RT SIDE FRAME AT FS 208 HAS CORROSION APPROXIMATELY BETWEEN L21R AND 36R. REMOVED AND CU T CAP AT FS 208 FROM L17R AND L23R. FABRICATED NEW IAW DAC 288851 AND DER 950087-0035A. HEAT TREATED, TREATED AND PRIM ED IAW SRM 51-1-8. INSTALLED IAW DER 950087-0035A. (X) 2 L 7 4 4F 4A25 1996053000059 19960530 00059 WP 1996 5 30 ARWR961166 1 19960426 G 5711 SPAR DOUBLER DOUG DC8 DC862 3021970 WP LT WS XCW 60 CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND LEFT WHEELWELL WING REAR SPAR DOUBLER AT STA XCW 60 HAS LOCAL CORROSION AT UPPER AREA. REMOVED CO RROSION, FOUND AREA BEYOND LIMITS IAW SRM 53-2-0. FABRICATED MACHINED DOUBLER AND CLIP. TREATED AND PRIMED IAW SRM 52- 1-8. INSTALLED REPAIR IAW SRM 57-2-6. REF: OPERATOR CONTROL NR 1166. (X) 2 L 7 4 4F 4A25 1996061300063 19960613 00063 WP 1996 6 13 ARWR961354 1 19960514 G 5330 SKIN DOUG DC8 DC862 3021970 WP FS 1530-1620 CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 REMOVED AND REPLACED SKIN FROM FS 1530 TO FS 1620 AT L32R TO L32L, DUE TO CORROSION. REMOVED AND REPLACED SKIN FROM FS 1530 TO FS 1620 AT L32R TO L32L IAW SRM'S 53-5-2, 51-1-21, AND 51-1-20D. TREATED AND PRIMED IAW SRM 51-1-8. SEALED ARE A IAW SRM 51-1-16. SPLICE IAW DER NR 950087-0064. (X) 2 L 7 4 4F 4A25 1996061300064 19960613 00064 WP 1996 6 13 ARWR961425 1 19960514 G 5313 5705593504 LONGERON DOUG DC8 DC862 3021970 WP FS 380 L29R CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND FS 380, L29R, FORWARD BASKET DOOR RT JAMB, HAS CORROSION. CUT OUT DAMAGED AREA, FABRICATED REPAIR ANGLES IAW DER ARW 950178-0067. INSTALLED REPAIR PER DER ARW 950178-0067. (X) 2 L 7 4 4F 4A25 1996053000290 19960530 00290 WP 1996 5 30 ARWR961433 1 19960426 G 5320 5614739 BRACKET DOUG DC8 DC862 3021970 WP AC COMP RT SIDE CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND FUSELAGE RT SIDE A/C COMPARTMENT AREA SUPPORT BRACKET FOR THE AIR CONDITIONING MIXING VALVE HAS CO RROSION IN DIFFERENT LOCATIONS. REMOVED CORRODED BRACKET. INSTALLED SERVICEABLE BRACKET, PN 5614739 IAW SRM 51-30 AND DC-8 MM 21-60-1. (X) 2 L 7 4 4F 4A25 1996060600150 19960606 00150 WP 1996 6 6 ARWR961744 1 19960515 G 5751 SKIN DOUG DC8 DC862 3021970 WP LT OTBD AIL LE CRACKED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND LT OUTBOARD AILERON UPPER SURFACE AT OUTBOARD ATTACHING FITTING, L/E SKIN HAS A CRACK. CUT DAMAGE D SECTION, FABRICATED AND INSTALLED DOUBLER IAW DER NR 950082-1567. TREATED AND PRIMED IAW SRM 51-1-8. (X) 2 L 7 4 4F 4A25 1996060600151 19960606 00151 WP 1996 6 6 ARWR961748 1 19960513 G 5311 FRAME DOUG DC8 DC862 3021970 WP C4 DOOR CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND LOWER AFT FUSELAGE C-4 DOOR CUT-OUT INNER SKIN CUT-OUT FRAME HAS HOLE AND CORROSION AROUND FRAME S KIN. REMOVED CORROSION IN AREA. FOUND WITHIN LIMITS, STOP DRILLED CRACK, FABRICATED DOUBLER. INSTALLED IAW DER NR MHA 3062. (X) 2 L 7 4 4F 4A25 1996060600152 19960606 00152 WP 1996 6 6 ARWR961753 1 19960513 G 5320 FRAME DOUG DC8 DC862 3021970 WP C4 DOOR PAN CRACKED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND LOWER AFT FUSELAGE C-4 INTERIOR SKIN PAN (FRAME) HAS CRACKS IN DIFFERENT LOCATIONS AROUND PAN (FRA ME). STOP DRILLED CRACK AND REPAIRED IAW DER NR MHA 3062. (X) 2 L 7 4 4F 4A25 1996060600153 19960606 00153 WP 1996 6 6 ARWR961760 1 19960513 G 5320 FRAME DOUG DC8 DC862 3021970 WP C2 DOOR PAN CRACKED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, RT LOWER FUSELAGE C-2 DOOR INTERIOR SKIN PAN (FRAME) HAS CRACK AT CENTER BOTTOM. STOP-DRILLED CRACK AND INSTALLED DOUBLER IAW DER NR M.H.A. 3064. (X) 2 L 7 4 4F 4A25 1996060600154 19960606 00154 WP 1996 6 6 ARWR961783 1 19960513 G 5730 161E PANEL DOUG DC8 DC862 3021970 WP WING CENTER WRONG PART B ARWR K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND WING CENTER SECTION PANEL NR 161E, IS THE IMPROPER PANEL IN THAT LOCATION. FABRICATED NEW PANEL I AW DER M.H.A. 3063 AND SRM 51-1-8 AND SRM 51-1-30. (X) 2 L 7 4 4F 4A25 1996061300065 19960613 00065 WP 1996 6 13 ARWR961861 1 19960514 G 5313 5754184505 LONGERON DOUG DC8 DC862 3021970 WP FS 145 L35R CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND AFT BAGGAGE COMPARTMENT, LONGERON 35R, FS 1145, CORRODED, RIVETS POPPED. REPAIRED LONGERON IAW D. A.C. GLP 1745/96-04-25-002, GLP 1749 96-05-06-004. (X) 2 L 7 4 4F 4A25 1996060600155 19960606 00155 WP 1996 6 6 ARWR961896 1 19960508 G 5730 SKIN DOUG DC8 DC862 3021970 WP LT WS XFS 560 LE CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 WHILE PEFORMING C-CHECK, FOUND CORROSION ON LT WING L/E AT APPROXIMATELY STA XFS 560. INSTALLED REPAIR (DOUBLER) WITH F ASTENERS AS REQUIRED IAW SRM 57-2-1, SEALED AREAS WITH P.R.C. 1422-B2 IAW SRM 51-1-16. (X) 2 L 7 4 4F 4A25 1996061300066 19960613 00066 WP 1996 6 13 ARWR961934 1 19960514 G 5320 3705592 FITTING DOUG DC8 DC862 3021970 WP FS 1145-1160 CORRODED B ARWR K NONE O OTHER IN INSP/MAINT 1 SO 19 8969U 46070 DURING C-CHECK, FOUND AFT BAGGAGE COMPARTMENT L34R FITTING LOCATED BETWEEN FS 1145 AND FS 1160 HAS CORROSION. REPAIRED END FITTING IAW DER ARW 95002-1747. (X) 2 L 7 4 4F 4A25 1996091900005 19960919 00005 SO 1996 9 19 AU960001 1 19960102 G 3232 11027240306 SUPPORT EMB 110 EMB110P1 3260122 SO LG DOOR ACT CRACKED W K NONE O OTHER LD LANDING 1 AU S (AUS) LANDING GEAR DOOR ACTUATOR SUPPORT ASSEMBLY CRACKED INTO THREE PARTS - DOOR ACTUATOR ROD PNO 110-2721-68-07 BENT 1 L 7 2 4T A21SO 1996091900006 19960919 00006 EA 1996 9 19 AU960002 2 19960102 G 8520 74309 BEARING LYC O540 TIO540J2BD 41532 EA NR 4 CON ROD FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S L462561A (AUS) ENGINE NO4 CONNECTING ROD BEARING FAILED IN AREA OF RELIEF FOR CONNECTING ROD BOLT SHANK 3 O E14EA 1996091900007 19960919 00007 EU 1996 9 19 AU960003 1 19960103 G 7160 352002034 HOSE BNORM BN2 BN2B20 1520302 EU LYC O540 IO540K1B5 41532 EA ENG AIR INT COLLAPSED W O OTHER E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS TO TAKEOFF 1 AU S L2549448A (AUS) LH ENGINE INDUCTION HOSE BETWEEN ALTERNATE AIR BOX AND FUEL CONTROL COLLAPSED - SUSPECT CAUSED BY FAULTY BATCH OF SCAT HOSES 1 H 7 2 3O 3 O A17EU 1E4 1996091900008 19960919 00008 SO 1996 9 19 AU960004 1 19960104 G 3230 487155 SOLENOID PIPER PA31 PA31 7103102 SO LG EXT-RETRACT S FAULTY W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S NA (AUS) LANDING GEAR SELECTION LEVER SAFETY SOLENOID ACTUATOR HAD BEEN CABLE TIED IN A POSITION WHERE THE LANDING GEAR COU LD BE SELECTEDTO THE 'UP' POSITION ON THE GROUND - PERSONNEL/MAINTENANCE ERROR - UNAPPROVED MODIFICATION 1 L 7 2 3O A20SO 1996091900009 19960919 00009 CE 1996 9 19 AU960005 1 19960104 G 5610 99110032 WINDSHIELD CESSNA 441 441 2076020 CE COCKPIT RT CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RH WINDSHIELD CRACKED IN LOWER INBOARD CORNER - FOUND DURING X-RAY INSPECTION - INSPECTION FOUND THAT THE OUTER LA MINATE HADBROKEN OFF ACROSS THE CORNER 1 L 7 2 3T RT A28CE 1996091900010 19960919 00010 EU 1996 9 19 AU960006 1 19960103 G 2731 HZ010H8012006 ROD BAC 146 146200A 1500266 EU ELEVATOR CONTROL CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RH ELEVATOR TRIM CONNECTING RODS CRACKED IN AREA OF AFT SWAGES - FOUND DURING INSPECTION IAW ER BA6-27-00-5A 2 H 7 4 4F A49EU 1996091900011 19960919 00011 EA 1996 9 19 AU960007 2 19960101 G 8530 73456 PUSHROD PARTEN P68 P68B EU LYC O360 IO360A1B6 41514 EA RT ENG NR 2 CYL DISTORTED W K NONE E VIBRATION/BUFFET CR CRUISE 1 AU S L1603751A (AUS) NO2 CYLINDER EXHAUST VALVE PUSHROD BENT - SUSPECT PUSHROD WAS SLIGHTLY BENT WHEN FITTED AT RECENT OVERHAUL 1 H 7 2 3O 3 O A31EU 1E10 1996091900012 19960919 00012 CE 1996 9 19 AU960008 1 19960103 G 2422 PC17 INVERTER BEECH 200 200BEECH 1152920 CE DC POWER DISTRIB CONTAM-WATER W K NONE H ELECT. POWER LOSS-50 PC CR CRUISE 1 AU S 23315382A (AUS) NO1 AND NO2 INVERTERS FAILED DURING FLIGHT IN HEAVY RAIN - WHEN AIRCRAFT RETURNED TO CLEAR AIR BOTH INVERTERS OPE RATED NORMALLY -ON RETURN TO BRISBANE BOTH INVERTERS WERE CHECKED - ONE INVERTER WAS SENT FOR REPAIR DUE TO DETERIORATIO N OF PROTECTIVE COATING - THE OTHER INVERTER WAS REFITTED SERVICEABLE 1 L 7 2 4T A24CE 1996091900013 19960919 00013 CE 1996 9 19 AU960009 1 19960104 G 5711 SPAR BEECH 55 D55 1152730 CE OUTER WING SYS CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH WING SPAR CORRODED IN AREA BEHIND LH ENGINE - FOUND DURING INSPECTION IAW AD/B55/29 AMDT1 - AIRCRAFT HAD BEEN PREVIOUSLYOPERATED IN A SALT LADEN ENVIRONMENT BY THE LAST OWNER 1 L 7 2 3O 3A16 1996091900014 19960919 00014 EU 1996 9 19 AU960010 1 19960103 G 7110 7271110505 COWLING SAAB SF340 SF340A 7850100 EU GE CT7TP CT75A2 30030 NE ENGINE COWL SYS DAMAGED W K NONE E D VIBRATION/BUFFET INFLIGHT SEPARATION CL CLIMB 1 AU S 367303K (AUS) LH ENGINE INBOARD COWL UNLATCHED - PROPELLER SLIPSTREAM HAD DISTORTED THE COWL CRACKING SEVERAL INTERNAL STIFFENE R FRAMES -SUSPECT LATCHES LEFT UNLOCKED FOLLOWING ENGINE SERVICING - PERSONNEL/MAINTENANCE ERROR 2 L 7 2 4T 4 T RT A52EU E8NE6 1996091900015 19960919 00015 NM 1996 9 19 AU960011 1 19960107 G 5720 85711069 PLATE DHAV DHC8 DHC8102 2809003 NM OUTER WING SYS DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S 151 (AUS) RH LADDER PLATE HAD EXCESSIVELY WORN PANEL SCREW HOLES - INSPECTION FOUND CORROSION REMOVAL REPAIR CARRIED OUT PRE VIOUSLY BUT NOT IN ACCORDANCE WITH APPROVED REPAIR SCHEME - PERSONNEL/MAINTENANCE ERROR - LADDER PLATE IS A STRUCTURAL PLATE LOCATED ON THE UPPER WING BETWEEN THE RIGHT AND LEFT ENGINE NACELLES 2 H 7 2 4T RT A13NM 1996091900016 19960919 00016 SO 1996 9 19 AU960012 1 19960109 G 3260 CONNECTOR PIPER PA34 PA34200 7103405 SO LG SQUAT SW CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH MAIN LANDING GEAR SQUAT SWITCH WIRING CONNECTOR LOCATED AT LH WING DISCONNECT EXCESSIVELY CORRODED AND OVERHEAT ED - FURTHERINVESTIGATION FOUND RH MLG CONNECTOR AT RH WING DISCONNECT IN A SIMILAR CONDITION 1 L 7 2 3O A7SO 1996091900017 19960919 00017 SO 1996 9 19 AU960013 1 19960110 G 6120 D20816 ACCUMULATOR MCAULY D20816 PIPER PA34 PA34220T 7103420 SO HARTZL HCC2Y BHCC2YF2 GL PROP CNTRL SYS FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S 820123 AN6929A (AUS) PROPELLER ACCUMULATOR EXTERNAL CASING SEVERELY CORRODED AND CHROME FINISH DELAMINATED - WHEN THE END CAPS WERE RE MOVED IT WASFOUND THAT THE CHROME FINISH OF THE INTERNAL BORE WAS SEVERELY DELAMINATED AND THE ACCUMULATOR WAS HEAVILY C ONTAMINATED WITHCHROME FLAKES ON BOTH SIDES OF THE FLOATING PISTON FURTHER EXAMINATION OF THE OIL SYSTEM COULD FIND NO M ORE CONTAMINATION - SUSPECT UNIT WAS NOT NEW WHEN FITTED AND CHROME PLATING WAS POORLY APPLIED 1 L 7 2 3O A7SO 5 C P920 1996091900018 19960919 00018 NM 1996 9 19 AU960014 1 19960110 G 3210 400033501 SIDE BRACE PIPER PA60 PA60601P 7106012 NM MAIN GEAR SYS BROKEN W K NONE O OTHER LD LANDING 1 AU S (AUS) LH AND RH MAIN LANDING GEAR LOWER SIDE BRACES BROKEN AT CENTRE PIVOT POINT 1 M 7 2 3O RT A17WE 1996091900019 19960919 00019 CE 1996 9 19 AU960015 1 19960112 G 7110 1213261216 FLAP CESSNA 206 U206G 2073356 CE ENGINE COWL SYS CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE RH COWL FLAP ASSEMBLY CORRODED INTERNALLY BEYOND REPAIR - AIRCRAFT OPERATES AS A SEAPLANE IN A SALT LADEN E NVIRONMENT 1 H 7 1 3O A4CE 1996091900020 19960919 00020 CE 1996 9 19 AU960016 1 19960112 G 7160 12507058 DUCT CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO ENG AIR INT CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) AIRBOX DUCT ASSEMBLY CRACKED BEYOND REPAIR - DUCT ASSEMBLY HAS BEEN PREVIOUSLY REPAIRED 1 H 7 1 3O 3 O A4CE E5CE 1996091900021 19960919 00021 CE 1996 9 19 AU960017 1 19960111 G 2720 965240262 BELLCRANK BEECH 55 D55 1152730 CE RUDDER CONTROL S CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH RUDDER BELLCRANK SEVERELY CORRODED - AIRCRAFT IS USED TO CARRYLIVE SEAFOOD WITH SUBSEQUENT CONTAMINATION BY SAL T LADEN PRODUCTS 1 L 7 2 3O 3A16 1996091900022 19960919 00022 CE 1996 9 19 AU960018 1 19960109 G 5312 12124027 BULKHEAD CESSNA 210 210L 2073448 CE MAIN FRAME SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUSELAGE REAR BULKHEAD CRACKED IN AREA OF RH HORIZONTAL STABILISER FORWARD ATTACHMENT FITTING 1 H 7 1 3O 3A21 1996091900023 19960919 00023 CE 1996 9 19 AU960019 1 19960111 G 5523 4562 TRIM TAB BBAVIA 8 8KCAB 2110612 CE ELEVATOR STRUCT DISTORTED W K NONE W INADEQUATE Q C NR NOT REPORTED 1 AU S (AUS) ELEVATOR TRIM TAB DAMAGED AT INBOARD END - LOWER TRIM CABLE TURNBUCKLE SEPARATED AT TURN BARREL - RIVETS ATTACHIN G TRIM TAB TO TAB HINGE REPLACED APPROXIMATELY 700 HOURS PREVIOUSLY - RIVET TAILS HAD WORKED EXTENSIVELY AND WERE NOT HO LDING THE STRUCTURETOGETHER - ONLY TWO RIVETS AT THE CONTROL ARM WERE SATISFACTORY -THE SKIN HAS TORN AWAY FROM THESE TW O RIVETS DURING FINAL FAILURE- PERSONNEL/MAINTENANCE ERROR 1 H 7 1 3O A21CE 1996100200001 19961002 00001 SO 1996 10 2 AU960020 1 19960114 G 2916 RESERVOIR PIPER PA31 PA31 7103102 SO MAIN HYD SYS LOW QUANTITY W K NONE O OTHER DE DESCENT 1 AU S (AUS) HYDRAULIC RESERVOIR LOW QUANTITY - SUSPECT FAULTY MICROSWITCH PREVENTED CORRECT OPERATION OF LANDING GEAR 1 L 7 2 3O A20SO 1996091900024 19960919 00024 EA 1996 9 19 AU960021 2 19960109 G 8550 NOZZLE PIPER PA36 PA36285 7103610 SO LYC O720 IO720A1B 41546 EA ENGINE OIL SYS FAILED W K NONE O OTHER CR CRUISE 1 AU S L12775AA (AUS) ENGINE OIL SYSTEM CONTAMINATED BY METAL - NO3 CYLINDER OIL SQUIRT NOZZLE MISSING - THE NOZZLE BALL WAS FOUND IN TH E CRANKCASE ANDTHE REMAINDER OF THE NOZZLE WAS FOUND IN THE SUMP FOLLOWING REMOVAL - INVESTIGATION FOUND THAT THE NOZZL E HAD BEEN CRUSHED BETWEEN THE CONNECTING ROD CAP AND THE CRANKCASE AND DESTROYED - SUSPECT THE NOZZLE WAS UNDERTORQUED DURING ASSEMBLY 1 L 7 1 3O 3 O A10SO 1E15 1996091900025 19960919 00025 CE 1996 9 19 AU960022 1 19960102 G 5310 24120201 STRUCTURE CESSNA 172 172RG 2072438 CE TAIL CONE TUNNEL CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) AFT FUSELAGE TAILCONE TUNNEL CONTAINED SEVERE CORROSION AT THE AFT END 1 H 7 1 3O 3A17 1996091900026 19960919 00026 CE 1996 9 19 AU960023 1 19960112 G 3230 TERMINAL BEECH 76 76 1153005 CE LG EXT-RETRACT S BROKEN W K NONE O OTHER CL CLIMB 1 AU S (AUS) LANDING GEAR SELECTOR RELAY TO POWER PACK CONNECTION BROKEN AT TERMINAL 1 L 7 2 3O A29CE 1996091900027 19960919 00027 SO 1996 9 19 AU960024 2 19960101 G 8530 646286 EXHAUST VALVE CONT VALVEGUIDE CESSNA 182 182P 2075816 CE CONT O470 O470R 17026 SO ENGINE CYL SEC WORN W K NONE O OTHER IN INSP/MAINT 1 AU S 100 B4593B4597 451133 (AUS) ENGINE CYLINDERS HAD WORN EXHAUST VALVES PN 646286 AND VALVE GUIDES PN 643767 - VALVE STEMS ALSO NECKED - SUSPECT CAUSED BY USE OF MOGAS 1 H 7 1 3O 3 O NT TA13 E273 1996091900028 19960919 00028 SW 1996 9 19 AU960025 1 19960108 G 2910 2781032682 PIPE FRCHLD SA227 SA227DC 3377521 SW MAIN HYD SYS HOLED W K NONE O K OTHER FLUID LOSS IN INSP/MAINT 1 AU S (AUS) HYDRAULIC PIPE LEAKING - INSPECTION FOUND PIN HOLE PERFORATION ONOUTSIDE RADIUS OF BEND 2 L 7 2 4T RT A18SW 1996091900029 19960919 00029 1996 9 19 AU960026 1 19960115 G 7603 565549004 CABLE POWER CONTROL SY STIFF W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) THROTTLE CABLE STIFF IN OPERATION - CABLE WAS NEW FITMENT - INVESTIGATION FOUND THAT THE ROD END ATTACHING THE CA BLE TO THE CARBURETTOR HAD BEN BENT EITHER DURING MANUFACTURE OR DURING PACKAGING/TRANSPORT 1996091900030 19960919 00030 CE 1996 9 19 AU960027 1 19960110 G 5320 BULKHEAD CESSNA 182 182H 2072718 CE FWD DOOR POST CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FORWARD DOOR POST BULKHEAD CRACKED AT BEND RELIEF NOTCH ON RH SIDE - CRACK DISAPPEARS BEHIND DOUBLER 1 H 7 1 3O NT 3A13 1996091900031 19960919 00031 EU 1996 9 19 AU960028 1 19960112 G 7160 352002034 HOSE BNORM BN2 BN2B20 1520302 EU LYC O540 IO540K1B5 41532 EA ENG AIR INT RT FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RH ENGINE INDUCTION HOSE COLLAPSED IN MID SECTION - INNER WIRE SEPARATED FROM OUTER WALL 1 H 7 2 3O 3 O A17EU 1E4 1996091900032 19960919 00032 EU 1996 9 19 AU960029 1 19960112 G 7160 352002034 HOSE BNORM BN2 BN2B20 1520302 EU LYC O540 IO540K1B5 41532 EA ENG AIR INT LT FAILED W K NONE O E R OTHER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 AU S (AUS) LH ENGINE INDUCTION HOSE COLLAPSED 1 H 7 2 3O 3 O A17EU 1E4 1996091900033 19960919 00033 EU 1996 9 19 AU960030 1 19960112 G 7160 352002034 HOSE BNORM BN2 BN2B20 1520302 EU LYC O540 IO540K1B5 41532 EA ENG AIR INT RT FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RH ENGINE INDUCTION HOSE BETWEEN AIR FILTER AND FUEL SERVO UNIT INTERNAL WIRE DISPLACED 1 H 7 2 3O 3 O A17EU 1E4 1996091900034 19960919 00034 SW 1996 9 19 AU960031 1 19960115 G 5720 STRAP GULSTM 500 500S 0141107 SW OUTER WING SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH WING AUXILIARY SPAR TO INBOARD RIB DOUBLER CRACKED IN RADIUS -CRACK LENGTH 5MM (0.196IN) - WING TO FUSELAGE STR AP CRACKED -FOUND DURING INSPECTION IAW AD/AC/93 1 H 7 2 3O 6A1 1996091900035 19960919 00035 CE 1996 9 19 AU960032 1 19960103 G 2910 58171028 PIPE CESSNA 404 404CESSNA 2075901 CE MAIN HYD SYS CRACKED W K NONE O K OTHER FLUID LOSS NR NOT REPORTED 1 AU S (AUS) HYDRAULIC PRESSURE PIPE CRACKED IN AREA OF BEND RADIUS - LOSS OF HYDRAULIC FLUID 1 L 7 2 3O A25CE 1996091900036 19960919 00036 CE 1996 9 19 AU960033 1 19960116 G 5312 BULKHEAD BEECH 55 D55 1152730 CE FS257-271 CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUSELAGE BULKHEADS LOCATED AT FS 257.6 AND FS 271.92 CRACKED - BULKHEADS ARE LOCATED AT THE FORWARD AND AFT HORIZO NTALSTABILISER STUB SPARS - FURTHER INVESTIGATION FOUND THAT THE CRACK WAS IDENTIFIED AS A SCORE MARK 1 L 7 2 3O 3A16 1996091900037 19960919 00037 1996 9 19 AU960034 4 19960116 G 2562 ELT1104 ELT CESSNA 421 421C 2076016 CE EMERGENCY EQUIP ACTIVATED W K NONE O OTHER IN INSP/MAINT 1 AU S 55101 (AUS) ELT ACTIVATED 4 HOURS AFTER LAST FLIGHT - NO INDICATION EVIDENT ON REMOTE SWITCH - THE UNIT WAS TURNED OFF AS PER INSTRUCTIONS BUT STILL CONTINUED TO TRANSMIT - THE UNIT WAS THEN TURNED OFF BYDISCONNECTING THE BATTERY 1 L 7 2 3O A7CE 1996091900038 19960919 00038 EA 1996 9 19 AU960035 2 19960111 G 7414 M3485 BEARING SLICK 4371 LYC O360 O360A4K 41514 EA ENG MAG LOOSE W K NONE O OTHER IN INSP/MAINT 1 AU S 92020112 L2674136A (AUS) MAGNETO DISTRIBUTOR END BEARING LOOSE AND SPINNING IN HOUSING - MAGNETO FILLED WITH BLACK DUST 3 O E286 1996091900039 19960919 00039 EU 1996 9 19 AU960036 2 19960101 G 7200 MAKILA1A ENGINE TMECA MAKILA1A SNIAS AS332 AS332L 8680809 EU TMECA MAKILA MAKILA1A 60040 EU ENGINE (TURBINE OVER TEMP W K E NONE ENGINE SHUTDOWN M OVER TEMP NR NOT REPORTED 1 AU S 877 241 241 (AUS) ENGINE OVERTEMPED ON START - EGT WAS BELOW 900 DEGREES C FOR 38 SECONDS - EGT LIMITS ON START 810 DEGREES C TO 90 0 DEGREES C FOR 2 SECONDS - SUSPECT START FOLLOWED ABORTED START WHICH LEFT A SUBSTANTIAL AMOUNT OF FUEL IN THE ENGINE 2 G 7 2 4U 4 U H4EU E12NE 1996091900040 19960919 00040 EU 1996 9 19 AU960037 1 19960116 G 7160 352002034 HOSE BNORM BN2 BN2B20 1520302 EU LYC O540 IO540K1B5 41532 EA ENG AIR INT RT FAILED W K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS TO TAKEOFF 1 AU S (AUS) LH ENGINE INDUCTION AIR HOSE BETWEEN AIR BOX AND FUEL CONTROL COLLAPSED - RH ENGINE INDUCTION HOSE INSPECTED AND WAS FOUND TOBE ALSO CLOSE TO FAILURE - NUMEROUS OTHER FAILURES RECORDED IN FLEET 1 H 7 2 3O 3 O A17EU 1E4 1996091900041 19960919 00041 CE 1996 9 19 AU960038 1 19960112 G 2434 BRUSH ALTERNATOR CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA GENERATOR-ALT WORN W K NONE O OTHER IN INSP/MAINT 1 AU S 1850 L330176 (AUS) ALTERNATOR BRUSHES WORN EXCESSIVELY - PIGTAIL JUNCTION WORN INTO SLIP RING 1 H 7 1 3O 3 O NT 3A12 E274 1996091900042 19960919 00042 CE 1996 9 19 AU960039 1 19960112 G 5320 DOOR POST CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA FS 65.3 CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 1850 (AUS) AFT DOOR POST ASSEMBLY CRACKED IN AREA OF INNER RELIEF AT FS 65.3 TOWARDS OUTBOARD LANDING GEAR HOUSING FASTENERS 1 H 7 1 3O 3 O NT 3A12 E274 1996091900043 19960919 00043 SW 1996 9 19 AU960041 1 19960104 G 2560 412419 ARM BELL 412 412 1182202 SW EMERGENCY EQUIP CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) HOIST ARM CRACKED - SOME CORROSION EVIDENT IN AREA OF CRACKING - ARM IS USED TO ATTACH A LUCAS WESTERN RESCUE WINC H TO THEAIRCRAFT 1 G 7 2 4U H4SW 1996091900044 19960919 00044 SO 1996 9 19 AU960042 1 19960109 G 5342 FITTING PIPER PA32 PA32300 7103212 SO LYC O540 IO540K1G5 41532 EA ATTACH FITTINGS CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) UPPER STABILATOR ATTACHMENT FITTINGS CORRODED - AIRCRAFT HAD BEEN SITTING DORMANT FOR APPROXIMATELY 12 MONTHS - CO RROSION FORMED BETWEEN ALUMINIUM SKIN AND STEEL FITTINGS 1 L 7 1 3O 3 O A3SO 1E4 1996091900045 19960919 00045 CE 1996 9 19 AU960043 1 19960112 G 5751 AILERON BEECH 95 95B55 1152729 CE WING AIL RT OUT OF BALANCE W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) FOLLOWING REPAINTING WHEN THE CONTROLS WERE CHECKED FOR BALANCE IT WAS FOUND THAT THE RH AILERON WAS 0.5 INLBS NO SE HEAVY AND THELH AILERON WAS 8 INLBS TRAILING EDGE HEAVY - CHECKS ON AN AILERON FROM ANOTHER AIRCRAFT FOUND THAT IT WA S ALSO OUT OF BALANCE -FOLLOWING INVESTIGATION IT IS SUSPECTED THAT THE AILERONS HAVE BEEN THAT WAY SINCE MANUFACTURE AN D THAT IT IS THE MAINTENANCE MANUAL AILERON BALANCE PARAMETERS THAT HAVE CHANGED 1 L 7 2 3O RT 3A16 1996091900046 19960919 00046 SW 1996 9 19 AU960044 1 19960105 G 3230 SEAL SWRNGN SA227 SA227AC 8780603 SW LT MLG JACK FAULTY W K NONE O OTHER CL CLIMB 1 AU S (AUS) LH MAIN LANDING GEAR RETRACTION JACK SEALS SUSPECT FAULTY 2 L 7 2 4T RT A8SW 1996091900047 19960919 00047 CE 1996 9 19 AU960045 1 19960110 G 5720 STRUT BOEING 75 B75N1 1380144 CE OUTER WING SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) WING INTERPLANE STRUT CRACKED ON FORWARD FACE AT TOP END OF STRUT- CRACK EXTENDS APPROXIMATELY 50.8MM (2IN) DOWN L EADING EDGE 1 Q 7 1 3R A743 1996091900048 19960919 00048 SO 1996 9 19 AU960046 1 19960105 G 5521 SPAR ELEVATOR PIPER PA31 PA31350 7103110 SO ELT-RT ELEV CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH AND RH ELEVATOR SPARS CRACKED AT TIPS ON BOTH SIDES OF TOP ANDBOTTOM FLANGES 1 L 7 2 3O A20SO 1996091900049 19960919 00049 EA 1996 9 19 AU960047 2 19960111 G 7230 BLADE PWA PT6 PT6A34 52043 EA T ENG CMPRSR/FAN FOD W K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CL CLIMB 1 AU S 40582 (AUS) ENGINE GAS GENERATOR 1ST STAGE COMPRESSOR BLADES (15OFF) CONTAIND FOD TO THE LEADING EDGES - INVESTIGATION FOUND T HAT THE 1ST STAGECOMPRESSOR SPACER RUBBED ON THE STATOR AND CRACKED CIRCUMFERENTIALLY LIBERATING A PIECE OF MATERIAL APP ROXIMATELY 12.7MM (0.5IN) WIDE AND 76.2MM (3IN) LONG WHICH WAS INGESTED THROUGH THE COMPRESSOR - DAMAGE TO THE TRAILING EDGES OF THE 1ST STAGE STATOR BLADES - EVIDENCE OF FURTHER DAMAGE DOWNSTREAM - ONE COMPRESSOR BLADE HAD FORE AND AFT MOV EMENT OF APPROXIMATELY5.08MM TO 7.62MM (0.2IN TO 0.3IN) 4 T E4EA 1996091900050 19960919 00050 NM 1996 9 19 AU960048 1 19960111 G 3246 AN535A BOLT PIPER PA60 PA60600 7106001 NM LG WHEEL/BRAKE S FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MAIN WHEEL HUB TIE BOLTS FAILED - BOLTS HAD EITHER HEADS MISSING OR HEADS SEPARATED DURING REMOVAL - SUSPECT CAUSE D BY BOLTS BEING OVERTORQUED 1 M 7 2 3O RT A17WE 1996091900051 19960919 00051 SO 1996 9 19 AU960049 1 19960108 G 5521 SPAR PIPER PA31 PA31350 7103110 SO LT-RT ELEV CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH AND RH ELEVATOR SPARS CRACKED AT OUTBOARD TIP IN BOTH TOP AND BOTTOM RADII - CRACKS RANGE FROM 19MM TO 39MM (0. 75IN TO 1.75IN) - BOTH LH AND RH SPARS ALSO CRACKED APPROXIMATELY 9MM TO 13MM (0.375IN TO 0.5IN) IN LENGTH AT THE OUTBO ARD HINGE AREA 1 L 7 2 3O A20SO 1996091900052 19960919 00052 CE 1996 9 19 AU960050 1 19960112 G 7603 CABLE BEECH 95 95B55 1152729 CE CONT O470 IO470L 17026 SO THROTTLE BROKEN W K NONE O OTHER DE DESCENT 1 AU S 272978R (AUS) THROTTLE INNER CABLE BROKE APPROXIMATELY 25MM (1IN) FROM SLIDING SLEEVE INSIDE FLEXIBLE PART OF CABLE ON THE ENGIN E SIDE - CABLE HAD A VERY MINOR KINK NEAR THE ATTACHMENT BRACKET - SUSPECT INCORRECT INSTALLATION - PERSONNEL/MAINTENAN CE ERROR 1 L 7 2 3O 3 O RT 3A16 3E1 1996091900053 19960919 00053 CE 1996 9 19 AU960051 1 19960118 G 5533 04310093 FITTING CESSNA 150 A152 2071836 CE VERT STAB STRUCT CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) VERTICAL STABILISER LH AND RH FITTINGS CORRODED - THE STABILIZER BRACKETS HAD NEVER BEEN PAINTSTRIPPED - FOUND DUR ING INSPECTIONIAW AD/150/31 AMDT3 (REQUIREMENTS 2A AND 2B) - PERSONNEL/MAINTENANCE ERROR 1 H 7 1 3O 3A19 1996100300812 19961003 00812 SO 1996 10 3 AU960052 1 19960117 G 5521 SPAR PIPER PA31 PA31350 7103110 SO ELT OUTB ELEV CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH OUTBOARD ELEVATOR SPAR WEB CRACKED - CRACK LENGTH 19.05MM (0.75IN) - FOUND DURING INSPECTION IAW AD/PA31/126 AM DT1 1 L 7 2 3O A20SO 1996100300813 19961003 00813 EU 1996 10 3 AU960053 1 19960112 G 3210 NB40075 BRACKET BNORM BN2 BN2A8 1520209 EU LYC O540 O540E4C5 41532 EA MAIN GEAR SYS BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH MLG SUPPORT BRACKET FLANGES BROKEN AWAY FROM THE COLLAR IN TWOPLACES OPPOSITE ONE ANOTHER - ONE SECTION BREAK I S APPROXIMATELY 100MM (4IN) AND THE OPPOSITE BREAK IS APPROXIMATELY 77MM (3IN) - THERE ARE CLEAR SIGNS OF INTERGRANNULAR CORROSION THROUGH THEBREAK AREAS - THE SUPPORT BRACKET HAS BEEN FITTED TO THE AIRCRAFTFOR 8106 HOURS - THE AIRCRAFT OPE RATES FROM ROUGH LANDING STRIPS IN THE TORRES STRAIT AREA 1 H 7 2 3O 3 O A17EU E295 1996100300814 19961003 00814 EU 1996 10 3 AU960054 1 19960101 G 5520 ELEVATOR FOKKER F28 F28MK4000 4990810 EU ELEVATOR STRUCT OUT OF BALANCE W O OTHER F FLT CONT AFFECTED CR CRUISE 1 AU S (AUS) PILOT EXPERIENCED FLUTTER THROUGH THE CONTROL COLUMN AND AIRFRAMEWHICH COMMENCED AT MACH 0.67 TO 0.69 - FLUTTER WO RSENED TO PUMPING ACTION AND CEASED WHEN SPEED WAS REDUCED TO BELOW 0.67 MACH - SUSPECT LH ELEVATOR UNBALANCED - WEIGHTS ADDED TO LHELEVATOR 2 L 7 2 4F RT A20EU 1996100300815 19961003 00815 NE 1996 10 3 AU960055 2 19960121 G 7260 GEAR BAG BAE146 BAE146100A 1500260 EU LYC ALF502 ALF502R3A 41580 NE T ENG AUX DRIVE SEPARATED W K E NONE ENGINE SHUTDOWN E VIBRATION/BUFFET CR CRUISE 1 AU S LF050235 (AUS) NO3 ENGINE ACCESSORY GEARBOX INPUT BEVEL GEAR SEPARATED FROM THE MOUNTING FLANGE IN THE CASE - THE SLIMSERTS AND B OLTS WERE STILL ATTACHED TO THE GEAR AND BEARING HOUSING - METAL CONTAMINATION OFENGINE OIL SYSTEM 2 H 7 4 4F 4 F RT A49EU E6NE 1996100300816 19961003 00816 NE 1996 10 3 AU960056 2 19960120 G 7200 ENGINE BAC 146 146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE ENGINE SYS BIRD STRIKE W K NONE E C VIBRATION/BUFFET F.O.D. TO TAKEOFF 1 AU S (AUS) DURING TAKEOFF THE AIRCRAFT HIT A FLOCK OF GALAHS - ALL ENGINE PARAMETERS REMAINED NORMAL FOLLOWING INGESTION - NO 1 ENGINE REQUIRED MAINTENANCE AND NO3 ENGINE WAS REMOVED FOR RECTIFICATION DUE TO MINOR DAMAGE - SEE MDR 96/0176 FOR ADD ITIONAL INFORMATION 2 H 7 4 4F 4 F A49EU E6NE 1996101000314 19961010 00314 NM 1996 10 10 AU960057 1 19960111 G 5210 80330034 RESERVOIR BOEING 747 747438 NM CREW-PASS DOOR S EMPTY W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S 20 (AUS) MAIN ENTRY DOOR EMERGENCY POWER RESERVOIR BOTTLE REQUISITIONED FROM STORES (WITH SERVICEABLE TAG) WAS EMPTY - INVE STIGATION FOUND THAT THERE WAS A LEAK FROM THE PRESSURE GAUGE ADAPTER - SUSPECT CAUSED BY DROPPING OR DAMAGING THE BOTT LE AND GAUGESOMEWHERE IN THE PERIOD FOLLOWING OVERHAUL AND BEFORE DELIVERY TOTHE AIRCRAFT 2 L 7 4 4F RT A20WE 1996100900004 19961009 00004 1996 10 9 AU960058 4 19960114 G 2330 6224096001 CLIP BOEING 747 747338 NM PA & ENTERTAINME MISSING W K NONE O OTHER DE DESCENT 1 AU S (AUS) NO3 PA SYSTEM MIGRATED FROM ITS RACK DUE TO THE ABSENCE OF A CAMLOCK CLIP RETAINER - NO AUDIBLE PA SYSTEM ON UPPER DECK - PERSONNEL/MAINTENANCE ERROR 2 L 7 2 4F RT A20WE 1996100300817 19961003 00817 NM 1996 10 3 AU960059 1 19960118 G 2701 5110001 CONTROL COLUMN CHILD S2 S2APITTS 0110201 NM LYC O360 IO360A1A 41514 EA ELEVATOR CONTROL BROKEN W O OTHER F FLT CONT AFFECTED AB AEROBATIC 1 AU S (AUS) AFT CONTROL COLUMN BROKE IN AREA IN LINE WITH FORE AND AFT GUSSETWELD AND PRESS TO TALK (PTT) WIRING HOLE AT BOTTO M OF STICK 1 Q 7 1 3O 3 O A8SO 1E10 1996101000315 19961010 00315 EA 1996 10 10 AU960060 2 19960118 G 8520 75061 BOLT LYC O360A1D MOONEY M20 M20C 5870208 SW LYC O360 O360A1D 41514 EA NR 3CYL CON ROD BROKEN W K NONE E Y K VIBRATION/BUFFET ENGINE STOPPAGE FLUID LOSS LD LANDING 1 AU S L665036 L665036 (AUS) NO3 CYLINDER CONNECTING ROD BOLT BROKE CAUSING OTHER BOLT TO BEND AND THEN BREAK - CONNECTING ROD WAS TORN FROM PI STON - MAJOR INTERNAL DAMAGE TO ENGINE AND CRANKCASE 1 L 7 1 3O 3 O 2A3 E286 1996101000316 19961010 00316 SO 1996 10 10 AU960061 1 19960121 G 2612 1734361450F FIRE DETECTOR GRUMAN G73 G73T SO PWA PT6 PT6A34 52043 EA RT ENG FAULTY W K NONE N FALSE WARNING IN INSP/MAINT 1 AU S (AUS) RH ENGINE FIRE DETECTOR GIVING FALSE FIRE INDICATION - RESISTANCECHECK OF DETECTOR WAS 8.5K OHMS 1 H 7 2 3R 4 T A783 E4EA 1996101000317 19961010 00317 WP 1996 10 10 AU960062 1 19960115 G 5720 SBEHB5195 EYE BOLT DHAVXX DH82 DH82AROBRTSN 2801002 WP OUTER WING SYS MISMODIFIED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) DURING WIRE REPAIR ALL EYEBOLTS WERE REMOVED FROM THE LOWER STARBOARD FRONT MAIN SPAR AT THE WING STRUT ATTACHMEN T POINT - INSPECTION OF THE EYEBOLTS FOUND THAT ONE IS SUSPECTED TO HAVE A HOME MADE 'T' SECTION ATTACHED TO THE HEAD OF THE BOLT WITHSOLDER - UNAPPROVED PART - UNAPPROVED MODIFICATION - SEE MDR 96/0083 FOR FURTHER INFORMATION - DEFECTS APP EAR TO BE FOR THE SAME PART ALTHOUGH DIFFERENT PART NUMBERS ARE RECORDED 1 Q 7 1 3I A8EU 1996101000318 19961010 00318 CE 1996 10 10 AU960063 1 19960122 G 7820 075016189 MUFFLER CESSNA 185 185B 2072806 CE CONT O470 IO470F 17026 SO ENG NOISE SUPPRS CRACKED W K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CL CLIMB 1 AU S 76735 (AUS) ENGINE MUFFLER TO OVERBOARD PIPE WELDED JOINT CRACKED - SCORCHINGOF LOWER COWL IN AREA OF CRACK - A NEW EXHAUST MU FFLER HAD BEENFITTED AT THE LAST PERIODIC INSPECTION 8 HOURS PREVIOUS - SUSPECT PIPE CONTACTED COWL IN AREA OF CUTOUT - PERSONNEL/MAINTENANCEERROR 1 H 7 1 3O 3 O 3A24 3E1 1996101000319 19961010 00319 SW 1996 10 10 AU960064 1 19960117 G 2910 27810322684 PIPE FRCHLD SA227 SA227DC 3377521 SW MAIN HYD SYS CRACKED W K NONE K FLUID LOSS DE DESCENT 1 AU S (AUS) STAINLESS STEEL HYDRAULIC PIPE LOCATED IN THE RH ENGINE NACELLE AT THE REAR OF THE FIREWALL CRACKED AND LEAKING O N BEND RADIUS - TOTAL LOSS OF HYDRAULIC PRESSURE 2 L 7 2 4T RT A18SW 1996101000320 19961010 00320 SW 1996 10 10 AU960065 1 19960119 G 6720 KP4 BEARING BELL 47 47G3B 1181026 SW TAIL RTR CNTRLS SEIZED W K NONE F FLT CONT AFFECTED DE DESCENT 1 AU S (AUS) TAIL ROTOR CONTROL BARREL BEARING SEIZED - BEARINGS ARE SEALED UNITS 1 G 7 1 3O 2H3 1996101000321 19961010 00321 NE 1996 10 10 AU960066 1 19960114 G 3150 OL327 LIGHT SKRSKY S76 S76A 8143006 NE CENTRAL WARNING FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MASTER CAUTION AND CAUTION ADVISORY PANEL DIODES (5OFF) BLOWN - SUSPECT FAULTY LAMP 1 G 7 2 3U H1NE 1996101000322 19961010 00322 EU 1996 10 10 AU960067 1 19960110 G 3222 8804200410 AXLE SOCATA MS893 MS893E 8402838 EU HARTZL NOSE-TAIL GEAR S CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NOSE LANDING GEAR AXLE CRACKED - FOUND DURING INSPECTION IAW AD/MSR/32 1 L 7 1 3O 7A14 1996101000323 19961010 00323 EU 1996 10 10 AU960068 1 19960122 G 5720 82051C2 WING GROB G115 G115C 1660303 EU LYC OUTER WING SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 82051C2 (AUS) LH AND RH WINGS CRACKED IN AREA OF LANDING GEAR ATTACHMENT 1 L 7 1 3O NT A57EU 1996101000324 19961010 00324 NE 1996 10 10 AU960069 2 19960122 G 7240 LINER PWA PW4000 PWA 4056 PW4056 NE T ENG BURNER SEC CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 0 P727316 (AUS) LH ENGINE OUTER COMBUSTION LINER CONTAINED CRACKS IN THREE ADJACENT LOUVRES (NO7, NO8 AND NO9) IN THE 5 O'CLOCK PO SITION -NO1 IGNITOR PLUG GUIDE MISSING - NO2 IGNITOR PLUG GUIDE CRACKED FOR 75% OF CIRCUMFERENCE 4 F E24NE 1996101000325 19961010 00325 1996 10 10 AU960070 4 19960111 G 3450 066400900 CONVERTER KN72 GULSTM GA7 GA7 3960401 SO LYC DEPDNT POSN DATA FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S 3682 (AUS) VOR/LOC CONVERTER FAULTY - CAUSED BY FAILURE OF IC105 1 L 7 2 3O A17SO 1996102300006 19961023 00006 NE 1996 10 23 AU960071 2 19960102 G 7321 R6409 FCU BOEING 747 747312 1384932 NM PWA JT9 JT9D7R4G2 52054 NE ENG FUEL CONTROL FAULTY W K NONE R PARTIAL RPM/PWR LOSS AP APPROACH 1 AU S R6409 P715083 (AUS) NO4 ENGINE FUEL CONTROL UNIT SUSPECT FAULTY DUE TO INTERNAL LINKAGE WEAR 2 L 7 4 4F 4 F RT A20WE E3NE 1996101000326 19961010 00326 EA 1996 10 10 AU960072 2 19960122 G 8530 SL134441 PIN BEECH 76 76 1153005 CE LYC O360 O360A1G 41514 EA ENG NR 1 CYL FRACTURED W K NONE O OTHER IN INSP/MAINT 1 AU S 372 L54171A (AUS) ENGINE NO1 PISTON PIN FRACTURED IN CENTRE CAUSING PISTON PIN BOSSTO BREAK EVENLY ON BOTH SIDES OF PISTON - DURING THE 100 HOURLYINSPECTION THE OIL PRESSURE FILTER WAS FOUND TO CONTAIN LARGE AMOUNTS OF STEEL AND ALLOY AND THE ENGINE W AS STRIPPED - DAMAGETO TAPPET BODIES, CAMSHAFT, CONNECTING RODS, CRANKCASE AND CYLINDER SKIRTS - MEF INVESTIGATION FOUND THAT FAILURE WAS CAUSEDBY FATIGUE ORIGINATING FROM CORROSION PITTING ON THE SURFACE OF THE PISTON PIN 1 L 7 2 3O 3 O A29CE E286 1996101000327 19961010 00327 CE 1996 10 10 AU960073 1 19960123 G 2730 071250011 TRIM JACK CESSNA 185 A185F 2072821 CE MCAULY ELEVATOR CONTROL WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ELEVATOR TRIM JACK SCREWS LOOSE AND WORN - SPROCKET ROLL PIN LOOSE - SUSPECT LUBRICANT ON SCREW JACK DRIED OUT RES ULTING IN PREMATURE WEAR OF SCREW AND NUT ASSEMBLIES - AIRCRAFT OPERATES INA DUSTY ENVIRONMENT 1 H 7 1 3O 3A24 1996101000328 19961010 00328 NE 1996 10 10 AU960074 2 19960116 G 7230 SEAL BAC 146 146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE NR 2 BEARING LEAKING W K NONE B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 AU S LF05896A (AUS) NO3 ENGINE NO2 BEARING PACK SEAL FLATTENED AND LEAKING 2 H 7 4 4F 4 F A49EU E6NE 1996101000329 19961010 00329 CE 1996 10 10 AU960075 1 19960119 G 2730 040010730 CONTROL CABLE 040010728 CESSNA 150 A150L 2071828 CE CONT O200 O200A 17020 SO ELEVATOR CONTROL CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S 0 (AUS) ELEVATOR REAR TRIM CABLES PN 0400107-28 AND PN 0400107-30 SEVERELY RUSTED AND FRAYED - 75% OF STRANDS BROKEN - PR OBLEM SHOULD HAVE BEEN FOUND DURING PERIODIC INSPECTIONS - PERSONEL/MAINTENANCE ERROR 1 H 7 1 3O 3 O 3A19 E252 1996101000330 19961010 00330 EU 1996 10 10 AU960076 1 19960116 G 2530 WIRE FOKKER F28 F28MK1000 4990808 EU GALLEY SHORTED W K NONE B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 AU S (AUS) NR 2 GALLEY CONTROL PANEL PLUG PO 6 WIRING SHORT CIRCUITED ACROSS CORNER OF REAR CONTROL PANEL. 2 L 7 2 4F RT A20EU 1996101000331 19961010 00331 EU 1996 10 10 AU960077 1 19960101 G 5520 ELEVATOR FOKKER F28 F28MK4000 4990810 EU ELEVATOR STRUCT OUT OF BALANCE W K NONE F E FLT CONT AFFECTED VIBRATION/BUFFET CR CRUISE 1 AU S (AUS) LH ELEVATOR STATIC BALANCE INCORRECT - ELEVATOR CONTROL FLUTTER THROUGH CONTROL COLUMN AND AIRFRAME BETWEEN MACH 0.67 AND MACH 0.69 - SEE MDR 96/0054 FOR ADDITIONAL INFORMATION 2 L 7 2 4F RT A20EU 1996101000332 19961010 00332 SO 1996 10 10 AU960078 2 19960119 G 8530 TM649317 CYLINDER CONT TSIO520N CESSNA 340 340A 2076405 CE CONT O520 TSIO520N 17040 SO MCAULY RT ENG CYL SEC CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 771 L514918 (AUS) ENGINE CYLINDER CRACKED IN AREA BETWEEN THE SPARK PLUG HOLE AND THE EXHAUST VALVE SEAT - CRACK LENGTH 30MM (1.18I N) 1 L 7 2 3O 3 O 3A25 E8CE 1996101000333 19961010 00333 CE 1996 10 10 AU960079 1 19960124 G 3220 NAS464P5A42 BOLT CESSNA 206 U206G 2073356 CE CONT NLG DRAG LINK SHEARED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NOSE LANDING GEAR DRAG LINK BOLT SHEARED AT NUT END ADJACENT TO THE LAST THREADED PORTION PRIOR TO THE BOLT SHANK 1 H 7 1 3O A4CE 1996101700152 19961017 00152 SO 1996 10 17 AU960080 2 19960112 G 8550 276338R FILTER CONT GTS10520M CESSNA 404 404CESSNA 2075901 CE CONT O520 GTSIO520M 17032 SO R ENGINE OIL SYS CONTAM-METAL W K NONE O OTHER IN INSP/MAINT 1 AU S 276338R 276338R (AUS) ENGINE OIL FILTER CONTAINED HIGHER THAN NORMAL LEVELS OF FERROUS METAL - SUSPECT ALTERNATOR BEARING FAILURE 1 L 7 2 3O 3 O A25CE E7CE 1996101000334 19961010 00334 SW 1996 10 10 AU960081 1 19960123 G 6410 206010765001 BEARING BELL TRBLADE BELL 206 206L3 1182108 SW TAIL ROTOR BLADE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S CS3336 (AUS) TAIL ROTOR BLADE FEATHERING BEARING CRACKED RADIALLY 1 G 7 1 3U H2SW 1996101000335 19961010 00335 SW 1996 10 10 AU960082 1 19960123 G 6710 206001554001 SUPPORT BELL 206 206L3 1182108 SW ALLSN M/R CONTROL CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 2830 (AUS) MAIN ROTOR CONTROL BELLCRANK SUPPORT WEB CRACKED ON INSIDE SURFACE - CRACK IS THROUGH THE WEB ON THE SHORTER FLANG E OF THESUPPORT WHERE THE THICKNESS HAS BEEN REDUCED OUTBOARD OF THE LINKPIVOT POINT - CRACK LENGTH 25.4MM (1IN) - CRACK HAS PROPAGATED THROUGH 90% OF WEB THICKNESS 1 G 7 1 3U H2SW 1996101000336 19961010 00336 WP 1996 10 10 AU960083 1 19960115 G 5720 H35195 EYE BOLT DHAVXX DH82 DH82AROBRTSN 2801002 WP OUTER WING SYS MISMODIFIED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) WING LOWER RH FRONT MAIN SPAR EYEBOLT LOCATED AT THE WING STRUT ATTACHMENT POINT HAD A HOME MADE 'T' SECTION ATTAC HED TO BOLTHEAD WITH SOLDER - EYEBOLT IS INCIDENCE WIRE ATTACHMENT POINT AT INTERPLANE STRUT POSITION ON LOWER FRONT MAI N SPAR - UNAPPROVEDPART/MODIFICATION - PERSONNEL/MAINTENANCE ERROR - SEE MDR 96/0062FOR FURTHER INFORMATION 1 Q 7 1 3I A8EU 1996101000337 19961010 00337 CE 1996 10 10 AU960084 1 19960126 G 2150 73838415 AIRCYCLE MACHINE CESSNA 441 441 2076020 CE CABIN COOLING SY SEIZED W K NONE B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 AU S 3221 41280 (AUS) AIR CYCLE MACHINE SEIZED 1 L 7 2 3T RT A28CE 1996101000338 19961010 00338 CE 1996 10 10 AU960085 1 19960122 G 5312 62368 BULKHEAD DOORPOST CESSNA 182 182P 2075816 CE MAIN FRAME SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 62368 (AUS) LH LOWER FORWARD DOORPOST BULKHEAD CRACKED FROM BEND RELIEF NOTCH- FOUND DURING INSPECTION IAW AD/C180/74 AMDT1 AN D CESSNA SEB95-19 1 H 7 1 3O NT TA13 1996101000339 19961010 00339 EA 1996 10 10 AU960086 2 19960112 G 8540 AN381210 SPLIT PIN LYC VO540B1B3 BELL 47 47J2A 1181106 SW LYC O540 VO540B1B3 41532 EA R ENGINE REAR SE MISSING W K NONE O OTHER IN INSP/MAINT 1 AU S 940 L (AUS) MAGNETO IDLER GEAR RETAINING NUT PN STD 43 SEPARATED FROM BOLT PN STD 1860 - NUT AND WASHER PNO 68545 FOUND IN AC CESSORY HOUSING - SUSPECT CAUSED BY LACK OF SPLIT PIN TO LOCK NUT - CARBON DEPOSITS IN SPLIT PIN HOLE INDICATE SPLIT PI N HAD BEEN MISSING FOR SOME CONSIDERABLE TIME 1 G 7 1 3O 3 O 2H1 E304 1996101000340 19961010 00340 EA 1996 10 10 AU960087 2 19960127 G 7314 15473 PUMP VALVE LYC IO360C1E6 PIPER PA34 PA34200 7103405 SO LYC O360 IO360C1E6 41514 EA LT ENGFUEL BLOCKED W O OTHER E Y VIBRATION/BUFFET ENGINE STOPPAGE TO TAKEOFF 1 AU S L1054451A L1054451A (AUS) LH ENGINE DRIVEN FUEL PUMP OUTLET VALVE BLOCKED BY FOREIGN OBJECT- ROUND RUBBER WASHER 19MM (0.74IN) IN DIAMETER W ITH A 6MM (0.236IN) HOLE WHICH SEPARATED FROM THE DIAPHRAGM ASSEMBLY - INVESTIGATION FOUND NO DAMAGE TO THE RUBBER WASHE R AND IT IS SUSPECTED THAT THE WASHER WAS INCORRECTLY FITTED DURING ASSEMBLY 1 L 7 2 3O 3 O A7SO 1E10 1996101000341 19961010 00341 CE 1996 10 10 AU960088 1 19960118 G 2432 TERMINAL CESSNA 152 CESSNA 150 152 2071835 CE BATTERY/CHARGER BROKEN W K NONE B SMOKE/FUMES/ODORS/SPARKS TO TAKEOFF 1 AU S 0 (AUS) BATTERY CABLE POSITIVE TERMINAL BROKEN - FREE END OF CABLE SHORT CIRCUITED ALTERNATOR OUTPUT TO BATTERY BOX 1 H 7 1 3O NT 3A19 1996101000342 19961010 00342 SO 1996 10 10 AU960089 2 19960112 G 8540 537721 BEARING CESSNA 404 404CESSNA 2075901 CE CONT O520 GTSIO520M 17032 SO MCAULY R ENGINE REAR SE DISINTEGRATED W K NONE O OTHER IN INSP/MAINT 1 AU S 276338R (AUS) CRANKCASE STARTER ADAPTER GEAR SHAFT NEEDLE BEARING DISINTEGRATED- CRANKCASE DAMAGED - OTHER COMPONENTS DAMAGED WE RE OIL PUMP HOUSING, IMPELLERS, ENGINE BEARINGS, STARTER ADAPTER KIT SHAFT PNO EQ6642 AND CRANKSHAFT GEAR - METAL CONTAM INATION OF OILSYSTEM - ENGINE HAD BEEN MODIFIED AND COMPLIED WITH AD/CON/71 1 L 7 2 3O 3 O A25CE E7CE 1996101000343 19961010 00343 CE 1996 10 10 AU960090 1 19960122 G 7921 635996 OIL COOLER CONT IO520M CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO MCAULY AC,ENG OIL DIST LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S 786 565768 LH565768 (AUS) ENGINE OIL COOLER CORE LEAKING - LOSS OF 5 QUARTS OF OIL 1 L 7 2 3O 3 O 3A10 E5CE 1996101000344 19961010 00344 NE 1996 10 10 AU960092 2 19960123 G 7260 BEARING DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE T ENG AUX DRIVE FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S PCE120282 (AUS) LH ENGINE ACCESSORY DRIVE SHAFT UPPER BEARING FAILED 2 H 7 2 4T 4 T RT A13NM E20NE 1996101000345 19961010 00345 EU 1996 10 10 AU960093 1 19960130 G 3213 115C5201 FORK GROB G115 G115C 1660303 EU LYC HARTZL NOSE-TAIL GEAR S CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NOSE LANDING GEAR WHEEL FORK CRACKED AND DELAMINATED - SUSPECT CAUSED BY UNREPORTED HEAVY LANDING 1 L 7 1 3O NT A57EU 1996101000346 19961010 00346 GL 1996 10 10 AU960094 3 19960123 G 6111 FC84756 BLADE HARTZL BHCC2YF2 BEECH 55 E55 1152732 CE CONT O520 IO520C 17032 SO HARTZL HCC2Y BHCC2YF2 GL PROPELLER ASSY S DISTORTED W K NONE O OTHER IN INSP/MAINT 1 AU S 80 AN694 AN694 (AUS) BOTH PROPELLER BLADES BENT AND TWISTED - NO IMPACT DAMAGE VISIBLE- SUSPECT DAMAGE CAUSED BY MISUSE OF BLADE BATS 1 L 7 2 3O 3 O 3A16 E5CE 5 C P920 1996101000347 19961010 00347 NE 1996 10 10 AU960095 2 19960122 G 8520 12081 STUD AYRES S2 S2RNORMAL 7630202 SO PWA R1340 R1340AN1 52016 NE HAMSTD R ENGINE POWER S BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S 17590 17590 (AUS) NO4 CYLINDER REAR HOLD DOWN STUD BROKEN - SUSPECT STUD PREVIOUSLYCRACKED 1 L 7 1 3R 3 R NC A3SW 5E2 1996101000348 19961010 00348 SW 1996 10 10 AU960096 1 19960130 G 5302 206031004071 TAIL BOOM BELL 206B BELL 206 206B 1181511 SW ALLSN MAIN FRAME SYS CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S BOJNO692 (AUS) TAILBOOM ASSEMBLY CONTAINED EXFOLIATION CORROSION IN THE TOP LH SECTION ADJACENT TO THE FIRST HANGER BEARING SUPP ORT - FURTHER INVESTIGATION FOUND SIGNIFICANT EXFOLIATION CORROSION AND TWO CRACKS - CRACK LENGTHS 20MM (0.787IN) AND 1 5MM (0.59IN) - SUSPECTCAUSED BY A RIVET WITH A MISSING HEAD ALLOWING WATER TO INGRESS BETWEEN THE SKIN AND A RIB WITH C ORROSION CAUSING THE SKIN TOBULGE AND CRACK 1 G 7 1 3U H2SW 1996101000349 19961010 00349 WP 1996 10 10 AU960097 2 19960109 G 7261 300143619AA1150C FILTER GULSTM 690TP 690A 0141722 SW GARRTT TPE331 TPE3315 01514 WP T ENGINE OIL SYS DISINTEGRATED W K NONE O OTHER IN INSP/MAINT 1 AU S P0684M (AUS) LH ENGINE OIL FILTER ELEMENT DISINTEGRATING - METAL FROM FILTER ELEMENT CASING CONTAMINATED ENGINE OIL SYSTEM 1 H 7 2 3T 4 T 2A4 E4WE 1996101000350 19961010 00350 CE 1996 10 10 AU960098 1 19960131 G 5320 1054200111 FITTING BEECH 76 BEECH 76 76 1153005 CE MAIN FRAME SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S ME358 (AUS) LH FUSELAGE FRAME SHEAR FITTING CRACKED IN RADIUS OF CUTOUT - CRACK LENGTH 5MM (0.196IN) 1 L 7 2 3O A29CE 1996101000351 19961010 00351 EU 1996 10 10 AU960099 1 19960105 G 3240 S876060317 HOSE AIRBUS 300 A300B4203 3930306 EU GE LG WHEEL/BRAKE S WORN W K NONE K J FLUID LOSS WARNING INDICATION LD LANDING 1 AU S (AUS) NO5 BRAKE HYDRAULIC PRESSURE HOSE WORN THROUGH - LOSS OF GREEN SYSTEM HYDRAULIC FLUID 2 L 7 2 4F A35EU 1996101000352 19961010 00352 EU 1996 10 10 AU960100 1 19960125 G 2780 1905 SCREWJACK AIRBUS 300 A300B4203 3930306 EU GE LIFT AUGMNT SYS WORN W K NONE O OTHER IN INSP/MAINT 1 AU S 29286 1905 (AUS) LH SLAT NO3 SCREWJACK EXCESSIVELY WORN - SUSPECT SCREWJACK WAS WORN WHEN FITTED - FOUND DURING INSPECTION IAW AB3- 27-2A 2 L 7 2 4F A35EU 1996101000353 19961010 00353 EU 1996 10 10 AU960101 2 19960128 G 7321 8063210 FCU CFMINT CFM56 CFM563C 13802 EU ENG,FUEL CONTROL FAULTY W K NONE R PARTIAL RPM/PWR LOSS TO TAKEOFF 1 AU S WYG76817 856531 (AUS) NO1 ENGINE FUEL CONTROL UNIT FAULTY - INVESTIGATION FOUND WEAR INTHE CDP PILOT BUSHING, NEEDLE BEARINGS AND BUSHIN G AND CDP LEVER ASSEMBLY 4 F E21EU 1996101000354 19961010 00354 EA 1996 10 10 AU960102 2 19960119 G 7322 60260 BUSHING FACET MA45PA CESSNA 172 172P 2072436 CE LYC O320 O320D2J 41508 EA MCAULY ENG,FUEL CONTROL WORN W K NONE O OTHER IN INSP/MAINT 1 AU S CK817203 (AUS) CARBURETTOR THROTTLE SHAFT PNO 13-1521 AND BUSHINGS PNO 60-260 HAD EXCESSIVE CLEARANCE DUE TO WEAR IN THE BUSHINGS WHICH WERE WORN THROUGH CAUSING WEAR IN THE BODY OF THE CARBURETTOR AS WELL - ACCELERATOR PUMP LEVER PNO 155-226 AND CO NNECTING ROD PNO17-372 WERE ALSO EXCESSIVELY WORN - PERSONNEL/MAINTENANCE ERROR 1 H 7 1 3O 3 O NT 3A12 E274 1996101000355 19961010 00355 CE 1996 10 10 AU960104 1 19960110 G 2720 03101965 SPRING CESSNA 172 172M 2072418 CE MCAULY RUDDER CONTROL S BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RUDDER RETURN SPRING BROKEN 1 H 7 1 3O NT 3A12 1996101000356 19961010 00356 EU 1996 10 10 AU960105 1 19960129 G 2821 GASCOLATOR BNORM BN2 BN2B20 1520302 EU LYC O540 IO540K1B5 41532 EA HARTZL ENG,FUEL DIST SY LEAKING W K NONE K FLUID LOSS TO TAKEOFF 1 AU S (AUS) RH ENGINE GASCOLATOR LOOSE DUE TO RETAINER ARM MOVING AND ALLOWING BOWL TO MOVE SIDEWAYS - FUEL LEAKING FROM GASC OLATOR -SUSPECT CAUSED BY OVERTORQUEING OF THE RETAINER ARM CAUSING DISTORTION OF THE ARM 1 H 7 2 3O 3 O A17EU 1E4 1996091900054 19960919 00054 SO 1996 9 19 AU960106 2 19960205 G 8520 CASTINGNO631649 CRANKSHAFT CONT IO520R CONT O520 IO520F 17032 SO RT ENG CTWT DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S 291023R 291023R (AUS) CRANKSHAFT COUNTERWEIGHT FERRULE HOLES ON WEBS CHIPPED DURING REMOVAL OF COUNTERWEIGHT BUSHES 3 O E5CE 1996101000357 19961010 00357 SO 1996 10 10 AU960107 1 19960130 G 3240 16815 BRAKE DISC EMB 110 EMB110P2 3260124 SO PWA HARTZL LG WHEEL/BRAKE S WORN W K NONE O OTHER IN INSP/MAINT 1 AU S 1447 (AUS) LH MAIN WHEEL BRAKE DISC CRACKED IN TWO 1 L 7 2 4T A21SO 1996101000358 19961010 00358 NE 1996 10 10 AU960108 2 19960120 G 7321 F4305ANSSN06 FCU LYC ALF502 ALF502R5 41580 NE ENG,FUEL CONTROL FAULTY W K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CR CRUISE 1 AU S F4305ANSS LF05589A (AUS) NO1 ENGINE FUEL CONTROL UNIT FAULTY 4 F E6NE 1996101000359 19961010 00359 NM 1996 10 10 AU960109 1 19960109 G 2913 183840ANSSN1 SEAL BOEING 727 727277 138408S NM MAIN HYD SYS FAILED W K NONE K FLUID LOSS CL CLIMB 1 AU S 16405 183840ANSS (AUS) NO1 ENGINE DRIVEN HYDRAULIC PUMP DRIVE PAD SEAL FAILED - SYSTEM 'A' HYDRAULIC LEVEL DROPPED TO 1.8 GALLONS - CREW SHUT OFF FLUID SUPPLY TO PUMP CAUSING PUMP TO RUN DRY AND SELF DESTRUCT 2 L 7 3 4F RT A3WE 1996101000360 19961010 00360 NE 1996 10 10 AU960110 2 19960120 G 7261 AL366 PUMP BAC 146 146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE TURBINE ENGINE O FAILED W K NONE K FLUID LOSS DE DESCENT 1 AU S AL366 LF05582A (AUS) NO3 ENGINE DRIVEN OIL PUMP FAILED DUE TO GEAR WEAR AND EROSION OFTHE HOUSING GEAR POCKETS - ALUMINIUM METAL CONTAM INATION OF OILFILTER 2 H 7 4 4F 4 F A49EU E6NE 1996102300008 19961023 00008 NE 1996 10 23 AU960111 2 19960130 G 7250 COUPLING 9272M76G02 GE CF6 CF680A 30025 NE T ENG TURBINE SE FAILED W K NONE K FLUID LOSS CL CLIMB 1 AU S 580187 (AUS) NO2 ENGINE CONTAINED A MASSIVE OIL LEAK IN THE INTAKE AREA - INSPECTION OF THE OIL SCAVENGE PUMP FOUND THE PUMP CO NTAMINATEDWITH BRAIDED SEAL MATERIAL - HP TURBINE COUPLING NUT PRESSURE TUBE RUPTURED AT THE TUBE TO AFT FLANGE WELDED JOINT - A CIRCUMFERENTIAL CRACK OF APPROXIMATELY 228.6MM (9IN) WAS FOUND WITH TWO PIECES OF THE TUBE APPROXIMATELY 19.0 5MM BY 19.05MM (0.75IN BY 0.75IN) AND 63.5MM BY 12.7MM (2.5IN BY 0.5IN) MISSING - THIS ALLOWED HIGH TEMPERATURE AND PRES SURE COMPRESSOR DISCHARGEAIR TO ESCAPE INTO THE COOLING AIR CAVITY OF THE HPC AND HPT ROTORS AND THEN CHANNELED FORWARD TO THE NO3 AIR/OIL SEAL CAUSINGTHE SEAL TO FAIL 4 F E13NE 1996101000361 19961010 00361 CE 1996 10 10 AU960112 1 19960131 G 2820 60920000249 FITTING BEECH 60 B60 1153605 CE LYC FUEL DISTRBUTION CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S (AUS) FUEL LINE LOCATED IN RH WHEEL WELL CRACKED AND LEAKING AT FITTING 1 L 7 2 3O A12CE 1996101700153 19961017 00153 CE 1996 10 17 AU960113 1 19960131 G 5712 9511002615 RIB BEECH 60 B60 1153605 CE LYC OUTER WING SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) WING RIB LOCATED IN WHEEL WELL CRACKED FROM RIVET HOLES 1 L 7 2 3O A12CE 1996101700154 19961017 00154 CE 1996 10 17 AU960114 1 19960131 G 5720 609800323 RIB BEECH 60 B60 1153605 CE LYC OUTER WING SYS CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RH WING NACELLE SIDE RIB CONTAINED EXFOLIATION CORROSION 1 L 7 2 3O A12CE 1996101700155 19961017 00155 CE 1996 10 17 AU960115 1 19960131 G 5340 041342622 HINGE CESSNA 150 152 2071835 CE ATTACH FITTINGS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) TOP DOOR HINGE CRACKED IN AFT SECTION - DOOR HINGE PIN ALSO SHEARED 1 H 7 1 3O NT 3A19 1996101700156 19961017 00156 CE 1996 10 17 AU960116 1 19960131 G 3230 358100763 DRIVE BEECH 60 B60 1153605 CE LYC LG EXT-RETRACT S SHEARED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LANDING GEAR EMERGENCY EXTENSION SYSTEM WORM DRIVE COUPLING SHEARED - SUSPECT CAUSED BY HAVING EMERGENCY DRIVE CO NNECTED DURING NORMAL OPERATION 1 L 7 2 3O A12CE 1996101700157 19961017 00157 CE 1996 10 17 AU960117 1 19960129 G 7922 75944 NUT LYC VERNATHERM CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA AC ENG OIL DIST LOOSE W K NONE O OTHER IN INSP/MAINT 1 AU S 471 (AUS) ENGINE THERMOSTATIC OIL COOLER BYPASS VALVE (VERNATHERM) NUT LOOSE - FOUND DURING INSPECTION IAW AD/LYC/78 1 H 7 1 3O 3 O NT 3A19 E223 1996101700158 19961017 00158 EU 1996 10 17 AU960118 1 19960131 G 3520 592 HOUSING PURITANBENN REGULATOR ISRAEL 1124 1124 4500102 EU CREW&PASS OXYGEN CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 592 (AUS) AIRCRAFT CABIN CREW OXYGEN REGULATOR OUTLET HOUSING CRACKED - OXYGEN LEAKING WHEN SELECTED 'ON' - SUSPECT CRACKIN G CAUSED BY OVERTIGHTENING OF THE FITTING INTO THE REGULATOR - PERSONNEL/MAINTENANCE ERROR 2 M 7 2 4F A2SW 1996101700159 19961017 00159 CE 1996 10 17 AU960119 1 19960109 G 5312 0713608 BULKHEAD CESSNA R182 CESSNA 182 R182 2072734 CE MAIN FRAME SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 01464 (AUS) FUSELAGE FORWARD DOOR POST BULKHEAD CRACKED IN BOTH RELIEF NOTCHES - CRACK LENGTH 5MM (0.196IN) 1 H 7 1 3O RT 3A13 1996091900055 19960919 00055 EU 1996 9 19 AU960120 1 19960205 G 3220 115C5201 FORK GROB G115 G115C 1660303 EU LYC O360 O360A1F6 41514 EA NOSE GEAR SYS DELAMINATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NOSE LANDING GEAR FORK DELAMINATED - AIRCRAFT NLG HAD BEEN BOGGED IN SAND - SEE MDR 96/0093 AND MDR 96/0121 FOR FU RTHER INFORMATION 1 L 7 1 3O 3 O NT A57EU E286 1996091900056 19960919 00056 EU 1996 9 19 AU960121 1 19960202 G 3220 115C5201 FORK GROB G115 G115C 1660303 EU LYC O360 O360A1F6 41514 EA NOSE GEAR SYS CRACKED W K NONE O OTHER LD LANDING 1 AU S 82032C2 (AUS) NOSE LANDING GEAR FORK CRACKED AND DELAMINATED - FOUND DURING INSPECTION FOLLOWING REPORTED HEAVY LANDING - SEE M DR 96/0093 ANDMDR 96/0120 FOR FURTHER INFORMATION 1 L 7 1 3O 3 O NT A57EU E286 1996091900057 19960919 00057 CE 1996 9 19 AU960122 1 19960202 G 6120 S139117 CONTROL CABLE CESSNA 337 337G 2075730 CE MCAULY 2AF34C D2AF34C306 GL PROP CNTRL SYS CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FORWARD ENGINE PROPELLER PITCH CONTROL CABLE CORRODED INTERNALLY AND STIFF TO OPERATE - CABLE WAS PURCHASED NEW ON 14/1195 AND HAS BEEN IN SERVICE FOR LESS THAN THREE MONTHS - SUSPECT CABLE WAS INSUFFICIENTLY LUBRICATED AT MANUFACTURE WHICH ALLOWED CORROSION TO DEVELOPE DURING STORAGE 1 H 7 2 3O A6CE 5 C P5EA 1996101700160 19961017 00160 NM 1996 10 17 AU960123 1 19960129 G 5315 FLOORBEAM BOEING 747 747338 NM CARGO COMPT DAMAGED W K NONE O OTHER NR NOT REPORTED 1 AU S (AUS) FORWARD CARGO CONTAINER AT POSITION 21R JUMPED FORWARD OF RESTRAINTS AND MOVED FORWARD CONTACTING THE CENTERLINE R ESTRAINT AT BS 635 - DAMAGE WAS CAUSED TO LONGITUDINAL FALSE FLOORBEAM BOX SECTION - ALL RESTRAINTS AND LOCKS SERVICEABL E - SUSPECT CONTAINER BASE WARPED. 2 L 7 2 4F RT A20WE 1996091900058 19960919 00058 NM 1996 9 19 AU960124 1 19960205 G 5730 RIVET PIPER PA60 PA60601P 7106012 NM OUTER WING SYS LOOSE W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LOWER WING SKIN TO MAIN SPAR CHERRY RIVETS LOOSE AND WORKING - SKIN IN NACELLE AREA SAGGING APPROXIMATELY 4.762MM (0.1875IN) 1 M 7 2 3O RT A17WE 1996091900059 19960919 00059 NE 1996 9 19 AU960125 2 19960201 G 7261 P20066C OIL SYSTEM GARRTT TPE3316252M MTSBSI MU2 MU2B35 5780411 CE GARRTT TPE331 TPE3316252M 01514 NE RT ENG OIL SYS CONTAM-METAL W K NONE O OTHER IN INSP/MAINT 1 AU S P20066C PZ0066C (AUS) RH ENGINE OIL SYSTEM METAL CONTAMINATION 1 H 7 2 3T RT A10SW E2WE 1996101700161 19961017 00161 CE 1996 10 17 AU960126 1 19960103 G 5330 0713343 SKIN 0713344 CESSNA 182 182Q 2072732 CE EXT PLATES/SKIN CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) SKIN CORRODED IN AREA BENEATH SOUND INSULATION COMPOUND - SKIN PNO 071334-3 AND PNO 071334-4 - FOUND DURING INSPEC TION IAWAD/C180/75 1 H 7 1 3O NT 3A13 1996101700162 19961017 00162 CE 1996 10 17 AU960127 1 19960103 G 5330 221300011 SKIN CESSNA 22130005 CESSNA 182 R182 2072734 CE LYC O540 O540J3C5 41532 EA EXT PLATES/SKIN CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) AIRCRAFT SKIN CORRODED UNDER SOUND INSULATION COMPOUND - LOWER LHFORWARD BELLY SKIN ALSO CORRODED - SKIN PNO 22130 00-11, PNO2213000-5 AND PNO 2213000-6 - FOUND DURING INSPECTION IAW AD/C180/75 1 H 7 1 3O 3 O RT 3A13 E295 1996101700163 19961017 00163 WP 1996 10 17 AU960128 2 19960126 G 7230 31011607 SEAL GARRTT TPE331 TPE33110U 01514 WP T ENG CMPRSR/FAN LEAKING W K NONE O J OTHER WARNING INDICATION CR CRUISE 1 AU S 1816 (AUS) RH ENGINE COMPRESSOR SEAL LEAKING 4 T E4WE 1997010200020 19970102 00020 EU 1997 1 2 AU960129 1 19960203 G 3230 LANDING GEAR BAG JETSTM JETSTM3107 1500215 EU LG EXT RETRACT S FAULTY W A UNSCHED LANDING O OTHER CL CLIMB 1 AU S (AUS) LANDING GEAR WOULD NOT RETRACT - GROUND TESTING COULD FIND NO FAULT - SEE MDR 96/0091 AND MDR 96/0161 FOR FURTHER INFORMATION 2 L 7 2 4T RT BA15CAA 1996091900060 19960919 00060 NM 1996 9 19 AU960130 1 19960204 G 3230 DOOR DHAV DHC8 DHC8102 2809003 NM LG EXT-RETRACT S FAULTY W K NONE O OTHER CL CLIMB 1 AU S (AUS) LANDING GEAR HYDRAULIC BYPASS DOOR INCORRECTLY POSITIONED PREVENTING CORRECT LANDING GEAR RETRACTION - PERSONNEL/ MAINTENANCE ERROR 2 H 7 2 4T RT A13NM 1996102300009 19961023 00009 NM 1996 10 23 AU960131 2 19960122 G 7210 31030351 BEARING GARRTT TORQUESENSOR GULSTM 690TP 690A 0141722 SW GARRTT TPE331 TPE3315251K NM ENGINE REDUCTION FAILED W K NONE E R J VIBRATION/BUFFET PARTIAL RPM/PWR LOSS WARNING INDICATION TO TAKEOFF 1 AU S P8240 P06269C (AUS) RH ENGINE TORQUE SENSOR BEARING FAILED - METAL CONTAMINATION OF OIL SYSTEM - INVESTIGATION FOUND THAT THE CHIP DE TECTOR WIRING WAS CROSSED AT THE FIREWALL PREVENTING OPERATION OF THE CHIP DETECTOR LIGHT 1 H 7 2 3T 4 T 2A4 E2WE 1996102300010 19961023 00010 SO 1996 10 23 AU960132 1 19960129 G 6123 PUMP EMB 120 EMB120 3260201 SO PWA 118 PW118A NE HAMSTD 14SF 14SF* NE PROP CNTRL SYS FAILED W K NONE O OTHER DE DESCENT 1 AU S (AUS) BURNT OUT RH PROPELLER UNFEATHERING PUMP CAUSED NO2 EMERGENCY DC BUS CIRCUIT BREAKER CB470 (80AMP) TO TRIP 2 L 7 2 4T 4 T RT A31SO E20NE 6 C P7NE 1996101700164 19961017 00164 NE 1996 10 17 AU960133 2 19960104 G 7310 HOSE EMB 120 EMB120 3260201 SO PWA 118 PW118A NE ENG,FUEL DIST SY LOOSE W K NONE K R J FLUID LOSS PARTIAL RPM/PWR LOSS WARNING INDICATION TO TAKEOFF 1 AU S (AUS) RH ENGINE FUEL LINE TO HMU LOOSE - FUEL LEAKING FROM HOSE - HOSE HAD BEEN REPLACED DURING OVERNIGHT MAINTENANCE - SUSPECT HOSEINCORRECTLY TIGHTENED ALLOWING FITTING TO LOOSEN ON START - PERSONNEL/MAINTENANCE ERROR 2 L 7 2 4T 4 T RT A31SO E20NE 1997010200021 19970102 00021 EU 1997 1 2 AU960134 1 19960125 G 2460 A2036 RELAY BAG JETSTM JETSTM3107 1500215 EU DC POWER DIST FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RELAY A2036 FAULTY - SEE MDR 96/0137 FOR ADDITIONAL INFORMATION 2 L 7 2 4T RT BA15CAA 1997010200022 19970102 00022 EU 1997 1 2 AU960135 1 19960125 G 2460 A2036 RELAY BAG JETSTM JETSTM3107 1500215 EU ROTOL R333 R333482F12 GL DC POWER DIST FAULTY W K NONE O OTHER CL CLIMB 1 AU S (AUS) RELAY A2036 FAULTY - SEE MDR 96/0134 AND MDR 96/0137 FOR FURTHER INFORMATION 2 L 7 2 4T RT BA15CAA 6 C P61GL 1996101700165 19961017 00165 NM 1996 10 17 AU960136 1 19960201 G 2910 82970010149 PIPE DHAV DHC8 DHC8102 2809003 NM MAIN HYD SYS WORN W K NONE K FLUID LOSS CR CRUISE 1 AU S (AUS) NO2 HYDRAULIC SYSTEM PRESSURE PIPE FROM ENGINE DRIVEN HYDRAULIC PUMP TO PRESSURE MANIFOLD CHAFED AND HOLED ON RET AINING CLAMP -RUBBER CUSHION LOST FROM CLAMP - SEE MDR 96/0201 FOR SIMILAR DEFECT 2 H 7 2 4T RT A13NM 1997010200023 19970102 00023 EU 1997 1 2 AU960137 1 19960124 G 2435 23079005 GENERATOR BAG JETSTM JETSTM3107 1500215 EU ROTOL R333 R333482F12 GL STARTER-GEN FAULTY W K NONE H J ELECT. POWER LOSS-50 PC WARNING INDICATION DE DESCENT 1 AU S 3469 (AUS) STARTER/GENERATOR FAILED - CAUSED BY INTERMITTENT OPERATION OF RELAY PNO A2036 - SEE MDR 96/0134 AND MDR 96/0135 F OR ADDITIONAL INFORMATION 2 L 7 2 4T RT BA15CAA 6 C P61GL 1996101700166 19961017 00166 SW 1996 10 17 AU960138 1 19960113 G 7120 2762114003 MOUNT SWRNGN SA227 SA227AC 8780603 SW ENGINE MOUNTING CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) UPPER LH ENGINE MOUNT FOOT CRACKED IN AREA OF FLANGE WELD TO TUBECLUSTER - CRACK APPEARS TO BE LACK OF FUSION BETW EEN THE WELD ANDTHE FLANGE/WASHER - WELD APPEARS TO BE ORIGINAL 2 L 7 2 4T RT A8SW 1996101700167 19961017 00167 EU 1996 10 17 AU960139 1 19960201 G 7110 365A24100503 COWLING 36010A AEROSP SA365 SA365C 8680667 EU TMECA ARRIEL ARRIEL1A 60030 NE NAC PYLON FAIRNG DAMAGED W K NONE D INFLIGHT SEPARATION CR CRUISE 1 AU S (AUS) TRANSMISSION RH COWLING FORWARD LATCH ASSEMBLY PNO 360-10A LOCKING PIN SHEARED ALLOWING FORWARD EDGE OF COWL TO LI FT ANDEVENTUALLY SEPARATE FROM AIRCRAFT 1 G 7 2 3U 3 U H10EU E19EU 1996101700168 19961017 00168 EU 1996 10 17 AU960140 2 19960111 G 8520 BEARING RROYCE GIPSY GIPSY30* 20005 EU R ENGINE POWER S FAILED W K NONE O OTHER CL CLIMB 1 AU S 1289 66850 (AUS) LH ENGINE OIL FILTER METAL CONTAMINATION - SUSPECT FAILED MAIN BEARING 3 I E294 1996091900061 19960919 00061 EA 1996 9 19 AU960141 2 19960208 G 7414 8120404 BEARING SLICK 4150 GULSTM GA7 GA7 3960401 SO LYC O320 O320D1D 41508 EA MAGNETO FAILED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S 8120404 (AUS) MAGNETO BEARING FAILED - AD/ELEC/18 AMDT3 HAS NOT BEEN COMPLIED WITH - PERSONNEL/MAINTENANCE ERROR - SEE MDR 96/0 142 FOR SIMILAR DEFECT 1 L 7 2 3O 3 O A17SO E274 1996091900062 19960919 00062 EA 1996 9 19 AU960142 2 19960208 G 7414 4150 MAGNETO SLICK 4150 GULSTM GA7 GA7 3960401 SO LYC O320 O320D1D 41508 EA ENGINE FAULTY W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S 8120388 L887939A (AUS) MAGNETO FAILED TO COMPLY WITH AD/ELEC/18 AMDT3 - PERSONNEL/MAINTENANCE ERROR 1 L 7 2 3O 3 O A17SO E274 1996091900063 19960919 00063 EU 1996 9 19 AU960143 1 19960207 G 2750 SCREWJACK BAC 146 146100A 1500260 EU FLAP SYS OUT OF ADJUST W K NONE F FLT CONT AFFECTED CL CLIMB 1 AU S (AUS) LH WING FLAP NO3 SCREW JACK DRIVE CHAINS SLACK - RH WING FLAP NO3SCREW JACK INCORRECTLY RIGGED 2 H 7 4 4F RT A49EU 1996091900064 19960919 00064 CE 1996 9 19 AU960144 1 19960207 G 2460 70HF10 DIODE BEECH 200 B200C 1152924 CE DC POWER DISTRIB FAULTY W K NONE H ELECT. POWER LOSS-50 PC CL CLIMB 1 AU S (AUS) NO1 ELECTRICAL BUS FEEDER DIODE FAULTY 1 L 7 2 4T A24CE 1996101700169 19961017 00169 EA 1996 10 17 AU960145 2 19960209 G 8520 75060 BOLT LYC CONROD PIPER PA23 PA23250 7102308 SO LYC O540 IO540C4B5 41532 EA R ENGINE POWER S UNAPPROVED PART W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S L1080840 (AUS) NO2 CYLINDER CONNECTING ROD PNO 74502 BOLT INCORRECT PART - BOLT PNO 75060/1 FITTED - CORRECT PNO 74644 - INCORREC T BOLT IS LONGERTHAN THE CORRECT ONE - IPC IS UNCLEAR ON CORRECT PART NUMBER BOLTTO BE FITTED - UNAPPROVED PART - PERSON NEL/MAINTENANCE ERROR 1 L 7 2 3O 3 O 1A10 1E4 1996101700170 19961017 00170 SO 1996 10 17 AU960146 1 19960131 G 3210 78717O2 STUD PIPER ARROW PIPER PA28 PA28RT201 7102818 SO LYC O360 IO360C1C6 41514 EA MAIN GEAR SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 3840 (AUS) RH MAIN LANDING GEAR SIDE BRACE STUD CRACKED IN AREA UNDER SHOULDER - FOUND DURING INSPECTION IAW AD/PA28/91 1 L 7 1 3O 3 O 2A13 1E10 1996101700171 19961017 00171 EA 1996 10 17 AU960147 2 19960126 G 7310 D2310 GASKET ROMEC FUELPUMP GULSTM 680 680FLP 0141610 SW LYC O720 IO720B1B 41546 EA ENG,FUEL DIST SY LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S D2310 L75754 (AUS) ENGINE DRIVEN FUEL PUMP RELIEF VALVE GASKET LEAKING 1 H 7 2 3O 3 O 2A4 1E15 1996101700172 19961017 00172 NE 1996 10 17 AU960148 1 19960110 G 6320 763510960044 OIL SYSTEM SKRSKY MAINGEARBOX SKRSKY S76 S76C 8143008 NE MAIN ROTOR TRANS LOW PRESSURE W K NONE O OTHER CR CRUISE 1 AU S A2310136 (AUS) MAIN TRANSMISSION GEARBOX OIL PRESSURE FELL TO 44PSI - OIL FILTERAND CHIP DETECTORS CHECKED OK - AFTER THE OIL WAS DRAINED AND THEGEARBOX REFILLED THE PRESSURE RETURNED TO NORMAL 1 G 7 2 3U NC H1NE 1996101700173 19961017 00173 GL 1996 10 17 AU960149 3 19960212 G 6110 783473 PROPELLER MCAULY 3AF32C87N MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY S SEIZED W K NONE O OTHER IN INSP/MAINT 1 AU S 783473 783473 (AUS) PROPELLER SEIZED DUE TO INTERNAL CORROSION - BLADE 'O' RINGS PNO A1633-52 NOT FITTED 5 C P22EA 1996101700174 19961017 00174 GL 1996 10 17 AU960150 3 19960207 G 6110 085033427 PROPELLER MCAULY 3FF32C501 CESSNA 404 404CESSNA 2075901 CE MCAULY 3FF32 3FF32C501 GL PROPELLER ASSY S FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S 806461 (AUS) PROPELLER WOULD NOT GO TO FULL FEATHER POSITION - ONLY SLIGHT RESISTANCE FELT WHEN PROPELLER WAS MANUALLY MOVED F ROM FEATHER TO FINE USING BLADE BATS - FOUND DURING INSPECTION IAW AD/PROP/2 1 L 7 2 3O A25CE 5 C P45GL 1996101700175 19961017 00175 EU 1996 10 17 AU960151 1 19960129 G 5210 F5106043427 SEAL FOKKER F27 F27MK500 4990629 EU CREW-PASS DOOR S INCORRECT FIT W K NONE W INADEQUATE Q C CR CRUISE 1 AU S (AUS) LH REAR DOOR SEAL INCORRECTLY INSTALLED - SEAL WAS FITTED UPSIDE DOWN - NEW SEAL ASSEMBLY HAD BEEN FITTED ON 12/9/ 95 -PERSONNEL/MAINTENANCE ERROR 2 H 7 2 4T A817 1996101700176 19961017 00176 GL 1996 10 17 AU960152 2 19960202 G 7230 6871443 BLADE ALLSN 250C18B BELL 47 47G3B1 1181028 SW ALLSN 250C 250C18 03011 GL T ENG CMPRSR/FAN FAILED W O OTHER E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS TO TAKEOFF 1 AU S 1030 CAC22003B 800621B (AUS) COMPRESSOR NO2/3 ROTOR ASSEMBLY BLADE FAILED - BLADES EXITED THROUGH BOTH COMPRESSOR CASE HALVES - FURTHER DAMAGE TO TURBINESECTION DUE TO FOD AND OVERTEMPERATURE - AIRCRAFT IS A SOLOY TURBINE ENGINE MODIFICATION ALLISON 250C18B POWER ED BELL 47G3B1 1 G 7 1 3O 3 U 2H3 E4CE 1996101700177 19961017 00177 GL 1996 10 17 AU960153 3 19960207 G 6111 787699 BLADE MCAULY 3AF32C87N CESSNA 310 310R 2074245 CE CONT O520 TSIO520M 17040 SO MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY S LOOSE W K NONE E VIBRATION/BUFFET TO TAKEOFF 1 AU S 271 787699 787699 (AUS) PROPELLER BLADE LOOSE - BLADE COULD BE ROTATED ABOUT 50.8MM (2IN)FROM FINE PITCH TO FEATHER - INVESTIGATION FOUND BLADE ACTUATING PIN FAILURE IN AREA ABOVE THREAD - MENTION WAS ALSO MADE OF FINDING FLAKES OF CHROME PLATING AND EVIDEN CE OF SCUFFING 1 L 7 2 3O 3 O 3A10 E8CE 5 C P22EA 1996101700178 19961017 00178 EU 1996 10 17 AU960154 1 19960205 G 6230 47896WVC47820X BEARING AEROSP MAINMAST SNIAS 350 AS350B 8680801 EU TMECA M/R MAST/SWASHPL FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S M1071 (AUS) MAIN ROTOR MAST BEARING FAILED - EVIDENCE OF EXTENSIVE PITTING AND BRINNELLING WITH CORROSION ALSO PRESENT - SUSPE CT CORROSIONINITIATED BY CONDENSATION - AIRCRAFT IS IDLE FOR LONG PERIODS OF TIME - METAL CONTAMINATION OF MAIN TRANSMIS SION 1 G 7 1 3U H9EU 1996101700179 19961017 00179 1996 10 17 AU960155 4 19960121 G 3452 205ANSSN005 CONTROLLER BOEING 737 737377 NM DEPDNT POSN DATA FAULTY W K NONE O OTHER CR CRUISE 1 AU S 3316 205ANSSN (AUS) A.T.C. TRANSPONDER CONTROLLER FAULTY 2 L 7 2 4F RT A16WE 1996102300011 19961023 00011 NM 1996 10 23 AU960156 1 19960201 G 3510 14326 HOSE BOEING 737 737376 NM CREW STA OXYGEN FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S 563 14326 (AUS) CAPTAINS OXYGEN MASK LOWER HOSE BURST 2 L 7 2 4F RT A16WE 1996101700180 19961017 00180 SO 1996 10 17 AU960157 2 19960131 G 8520 CRANKCASE BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO MCAULY 3AF34C 3AF34C502 GL R ENGINE POWER S CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 1665 565559 (AUS) CRANKCASE CRACKED IN AREA OF NO4 CYLINDER - CRACK RADIATES FORWARD FROM THE FORWARD OIL FILTER STUD - CRACK LENGTH 135MM(5.314IN) - AIRCRAFT IS USED FOR TRAINING PURPOSES 1 L 7 2 3O 3 O 3A16 E5CE 5 C P22EA 1996101700181 19961017 00181 SO 1996 10 17 AU960158 1 19960205 G 7170 PIPE PIPER PA28 PA28RT201 7102818 SO LYC O360 IO360C1C6 41514 EA ENG FLUID DRAIN/ INCORRECT FIT W K NONE W K INADEQUATE Q C FLUID LOSS IN INSP/MAINT 1 AU S L2006651A (AUS) ENGINE INTAKE FUEL DRAIN LINE INCORRECTLY FITTED - LINE WAS DOUBLED UP INTO A KINK PREVENTING FUEL FROM DRAINING - FUELLEAKED INSIDE COWLING - PERSONNEL/MAINTENANCE ERROR 1 L 7 1 3O 3 O 2A13 1E10 1996101700182 19961017 00182 SO 1996 10 17 AU960159 2 19960204 G 8520 6419311075 BOLT CONT TSIO520E CESSNA 402 402B 207590P CE CONT O520 TSIO520E 17040 SO MCAULY 3AF32C 3AF32C87 GL R ENGINE POWER S FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S 1179 275233R (AUS) ENGINE CRANKCASE THROUGH BOLT SHEARED AT BASE OF NUT - BOLT GOES FROM NO2 CYLINDER LOWER FORWARD POSITION TO N03 C YLINDER LOWER AFT POSITION - CRANKCASE ALSO CRACKED 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 1996101700183 19961017 00183 SO 1996 10 17 AU960160 1 19960205 G 7112 BAFFLE PIPER PA28 PA28RT201 7102818 SO LYC O360 IO360C1C6 41514 EA ENGINE COWL SYS INCORRECT FIT W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S L2006651A (AUS) ENGINE FRONT BAFFLE LOWER SIDE SEALING STRIPS INCORRECTLY FITTED - BAFFLE LOWER SIDE MATES WITH LOWER COWL - RAM A IR ENTEREDUNDERSIDE OF ENGINE PREVENTING CORRECT COOLING - PERSONNEL/MAINTENANCE ERROR 1 L 7 1 3O 3 O 2A13 1E10 1997010200024 19970102 00024 EU 1997 1 2 AU960161 1 19960203 G 3230 7445B VALVE BAG JETSTM JETSTM3107 1500215 EU LG EXT-RETRACT S FAULTY W K NONE O OTHER TO TAKEOFF 1 AU S LK8509192 (AUS) EMERGENCY UNDERCARRIAGE HYDRAULIC RELEASE VALVE FAULTY - SEE MDR 96/0091 FOR FURTHER INFORMATION 2 L 7 2 4T RT BA15CAA 1996101700184 19961017 00184 SO 1996 10 17 AU960163 1 19960205 G 2510 SEAT PIPER PA28 PA28RT201 7102818 SO FLIGHT COMPARTME INCORRECT MOD W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) PILOTS SEAT HYDRAULIC ADJUSTMENT UNITS FAULTY - SEAT HAS BEEN LOCKED IN A SINGLE POSITION BY FITTING TUBE SPACERS OVER THE PISTON RODS - WITH THE SEAT LOCKED IN A HIGH POSITION THE PILOTS HEAD IS IN CLOSE PROXIMITY TO THE CABIN ROOF - UNAPPROVEDMODIFICATION - PERSONNEL/MAINTENANCE ERROR 1 L 7 1 3O 2A13 1996101700185 19961017 00185 EA 1996 10 17 AU960164 2 19960205 G 7421 RME38E SPARK PLUG CHAMPION REM38E PIPER PA28 PA28RT201 7102818 SO LYC O360 IO360C1C6 41514 EA ENG,IGNITN DISTR FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S IO360CIC6 (AUS) SPARK PLUGS (6OFF) FAULTY - CENTRE ELECTRODE WAS BEYOND LIMITS FOR RECONDITIONING - NO1 CYLINDER TOP SPARK PLUG HA D TWO COPPERWASHERS FITTED - NO1 CYLINDER LOWER SPARK PLUG HAD CORE LEAKAGE -ENGINE HAD COMPLETED ONLY 38 HOURS SINCE OV ERHAUL -PERSONNEL/MAINTENANCE ERROR 1 L 7 1 3O 3 O 2A13 1E10 1996101700186 19961017 00186 SO 1996 10 17 AU960165 1 19960205 G 2434 DAIE949 CONDENSER BOSCH ALTERNATOR PIPER PA28 PA28RT201 7102818 SO LYC DC GENERATOR-ALT FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S DAIE949 (AUS) ALTERNATOR CONDENSER FAULTY - OUTER CASING WAS HOLED DUE TO WEAR CAUSED BY BEING LOOSE IN THE CLAMP BRACKET - PERS ONNEL/MAINTENANCE ERROR 1 L 7 1 3O 2A13 1996101700187 19961017 00187 EU 1996 10 17 AU960166 1 19960122 G 5540 A06002011 BUSHING FOKKER RUDDERSHAFT FOKKER F28 F28MK4000 4990810 EU RUDDER STRUCT SY MISSING W K NONE F FLT CONT AFFECTED CR CRUISE 1 AU S 8595 AFW197ANS (AUS) RUDDER SHAFT PNO A06020-15 UPPER LUG INNER BUSH PNO A06020-11 MISSING - FLANGED BUSH PNO A06020-13 BADLY WORN - E DDY CURRENT INSPECTION OF SHAFT ASSEMBLY FOUND UPPER AND LOWER LUGS CRACKED IN 3 TO 4 PLACES RANGING FROM 4MM TO 5MM (0 .157IN TO 0.196IN) IN LENGTH - CRACKS WERE CORROSION RELATED - RUDDER ACTUATOR CHANGED ON 19/3/95 - PERSONNEL/MAINTENANC E ERROR 2 L 7 2 4F RT A20EU 1996101700188 19961017 00188 GL 1996 10 17 AU960167 3 19960123 G 6111 FC84756 BLADE HARTZL HCC2YF2CHUF BEECH 55 E55 1152732 CE CONT O520 IO520C 17032 SO HARTZL HCC2Y HCC2YF2 GL PROPELLER ASSY S DAMAGED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S 80 AN694 AN694 (AUS) PROPELLER BLADE CONTAINED TOOLING MARK DAMAGE IN BALANCE CAVITY -SUSPECT CAUSED DURING REMOVAL OF BALANCE LEAD - B LADE SNO C49080 1 L 7 2 3O 3 O 3A16 E5CE 5 C P920 1996101700189 19961017 00189 CE 1996 10 17 AU960168 1 19960201 G 5720 08225501926 FITTING CESSNA 402A CESSNA 402 402A 207590M CE OUTER WING SYS CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) WING FITTINGS/STIFFENERS CONTAINED EXFOLIATED INTERGRANNULAR CORROSION - DURING FITTING REPLACEMENT EXTENSIVE CORR OSION WAS ALSO FOUND IN LOWER WING STRINGERS PARTICULARLY IN AREA UNDER FUEL CELL BAYS - AIRCRAFT PREVIOUSLY OPERATED I N SALT LADENENVIRONMENT 1 L 7 2 3O A7CE 1996102300012 19961023 00012 1996 10 23 AU960169 4 19960209 G 2565 CABLE BOEING 767 767238 1385114 NM ESCAPE SLIDE MISINSTALLED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) LT OFF WING ESCAPE SLIDE SEPARATED FROM STOWAGE COMPARTMENT BUT DID NOT INFLATE AND DEPLOY AS REQUIRED - INVESTIG ATION FOUND THATTHE FAILURE WAS IN THE TRANSFER OF FORCE FROM THE INFLATION TRIGGER TO THE FIRING MECHANISM WITH THE TR IGGER CABLE BEING FED DOWN THE INCORRECT SIDE OF THE REGULATOR HOUSING SECTOR 2 L 7 2 4F RT A1NM 1996101700190 19961017 00190 NE 1996 10 17 AU960170 2 19960202 G 7230 701509 DISC BOEING 727 727277 138408S NM PWA JT8 JT8D15 52051 NE T ENG CMPRSR/FAN CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S P76768 687560 (AUS) ENGINE 9TH STAGE HIGH PRESSURE COMPRESSOR DISC CONTAINED CORROSION PITTING IN THE BLADE SLOT PRESSURE FACES AND BL ADE SLOTSIDES IN EXCESS OF LIMITS - FOUND DURING INSPECTION IAW PWA SB 6038 AND AD/JT8D/29 - ENGINE HAD BEEN FITTED TO A LOW UTILISATIONAIRCRAFT 2 L 7 3 4F 4 F RT A3WE E2EA 1996101700191 19961017 00191 1996 10 17 AU960171 4 19960124 G 2562 69B562875 TRANSMITTER BOEING 747 747238B 1384828 NM EMERGENCY EQUIP MISSING W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NO EMERGENCY RADIO BEACONS FITTED TO DOORS 2R, 4L AND 4R - SUSPECT BEACONS REMOVED DURING RECONFIGURATION AND FITM ENT OF NEWTYPE ESCAPE SLIDES OR REMOVED LATER BY UNAUTHORISED PERSONS PROBABLY FOR PERSONAL USE 2 L 7 4 4F A20WE 1996101700192 19961017 00192 SO 1996 10 17 AU960173 1 19960119 G 3260 ICH214 SWITCH PIPER PA31 PA31350 7103110 SO LG EXT-RETRACT S FAULTY W K NONE O OTHER CL CLIMB 1 AU S (AUS) LANDING GEAR SQUAT SWITCH FAULTY 1 L 7 2 3O A20SO 1996101700193 19961017 00193 SO 1996 10 17 AU960174 1 19960127 G 7922 NUT LYC VERNATHERM PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA AC,ENG OIL DIST LOOSE W K NONE O OTHER IN INSP/MAINT 1 AU S L566061A (AUS) ENGINE THERMOSTATIC OIL COOLER BYPASS VALVE (VERNATHERM) NUT LOOSE - FOUND DURING INSPECTION IAW AD/LYC/78 1 L 7 2 3O 3 O A20SO E14EA 1996101700194 19961017 00194 NE 1996 10 17 AU960175 2 19960122 G 7260 86A002 GEAR LYC ALF502R3A BAC 146 146100A 1500260 EU LYC ALF502 ALF502R3A 41580 NE T ENG AUX DRIVE SEPARATED W K NONE E K VIBRATION/BUFFET FLUID LOSS CR CRUISE 1 AU S (AUS) ENGINE ACCESSORY GEARBOX INPUT BEVEL GEAR SEPARATED FROM MOUNTINGFLANGE - BOLTS WERE STILL ATTACHED TO THE GEAR AN D BEARING HOUSING - FOUND WHEN ENGINE STRIPPED FOLLOWING OIL PRESSURE LOSS - SUSPECT CAUSED BY INSUFFICIENT BACKLASH BET WEEN THE SPIRAL INPUT GEAR AND THE BEVEL GEAR DURING INSTALLATION 2 H 7 4 4F 4 F RT A49EU E6NE 1996101700195 19961017 00195 NE 1996 10 17 AU960176 2 19960121 G 7250 HOT SECTION BAC 146 146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE T ENG TURBINE SE DETERIORATED W K NONE O OTHER IN INSP/MAINT 1 AU S LF05869A (AUS) ENGINE HOT SECTION DETERIORATED BEYOND LIMITS - FOUND DURING STRIP INSPECTION FOLLOWING BIRDSTRIKE 2 H 7 4 4F 4 F A49EU E6NE 1996102300013 19961023 00013 NM 1996 10 23 AU960177 1 19960131 G 2897 WIRE BOEING 767 767277 1385128 NM FUEL INDICATION DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) WIRES DAMAGED IN AREA BEHIND FLIGHT ENGINEERS PANEL - WIRES DAMAGED WERE:- 1. SINGLE TWISTED WIRE WITH TWO WIRES SEVERED - P61 RH SIDE PANEL WIRE NO W062-209R18 - FUEL TEMPERATURE INDICATOR - ATA 28 WIRE NOW062-209R18 - FUEL TEMPERA TURE INDICATOR - ATA 28 2. SINGLE WIRE SEVERED- P61 RH SIDE PANEL WIRE NO W062-615-22 - RH FUEL PRESSURE PUMP LOW PRESSU RE - ATA 28 3. SINGLE SHEILDED WIRE SEVERED - P61 RH SIDE PANEL WIRE NO W062-81G-24 - SECOND OBSERVERS FLIGHT INTERPHONE - ATA 23 SUSPECT DELIBERATE DAMAGE BY PERSONS UNKNOWN 2 L 7 2 4F RT A1NM 1996101700196 19961017 00196 CE 1996 10 17 AU960178 1 19960215 G 2731 12321391 BRACKET CESSNA U206E CESSNA 206 U206E 2073350 CE CONT O520 IO520F 17032 SO ELEVATOR CONTROL BROKEN W K NONE F FLT CONT AFFECTED DE DESCENT 1 AU S (AUS) ELEVATOR TRIM TAB CONTROL ACTUATOR MOUNTING BRACKET BROKEN AWAY FROM TAILPLANE CONNNECTION - AIRCRAFT IS USED FOR PARACHUTEOPERATIONS WITH THE DOORS OFF AND A WIND DEFLECTOR FITTED - SUSPECT CAUSED BY EMPENNAGE BUFFETING DUE TO FITM ENT OF WIND DEFLECTOR - SEE MDR 96/0257 FOR ADDITIONAL INFORMATION 1 H 7 1 3O 3 O A4CE E5CE 1996101700197 19961017 00197 SW 1996 10 17 AU960179 1 19960130 G 5720 STRUT AIRPTS A A9A 0144204 SW OUTER WING SYS CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH WING AFT WING STRUT AND TWO BRACES CONTAINED LIGHT CORROSION -FOUND DURING X-RAY INSPECTION 1 L 7 1 3O A4WE 1996101700198 19961017 00198 NM 1996 10 17 AU960180 1 19960210 G 3240 DSC252A40230 HOSE G831810A DHAV DHC8 DHC8102 2809003 NM LG WHEEL/BRAKE S RUPTURED W K NONE K FLUID LOSS CR CRUISE 1 AU S 3892 (AUS) LH OUTBOARD BRAKE ASSEMBLY HYDRAULIC HOSE RUPTURED - LOSS OF NO1 SYSTEM HYDRAULIC FLUID DUE TO FAILURE OF HYDRAULI C FUSE TO OPERATE AND PREVENT LOSS - SUSPECT CAUSED BY HYDRAULIC BRAKE HOSERUBBING ON THE TYRE DURING LANDING AND TAKEOF F 2 H 7 2 4T RT A13NM 1996101700199 19961017 00199 CE 1996 10 17 AU960181 1 19960204 G 3260 1SE13 MICROSWITCH CESSNA 310 310R 2074245 CE LG POSITION IND INTERMITTENT W K NONE N FALSE WARNING CR CRUISE 1 AU S (AUS) LH MAIN LANDING GEAR DOWNLOCK MICROSWITCH INTERMITTENT IN OPERATION - LH MLG SIDEBRACE LOCK LINK TENSION TOO HIGH 1 L 7 2 3O 3A10 1996101700200 19961017 00200 EA 1996 10 17 AU960182 2 19960123 G 8540 67542 BEARING PIPER PA32 PA32300 7103212 SO LYC O540 IO540K1G5 41532 EA R ENGINE REAR SE FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S L1914048A (AUS) LH MAGNETO DRIVE BEARING LOCATED IN THE ENGINE ACCESSORY HOUSING FAILED - METAL CONTAMINATION OF OIL SYSTEM 1 L 7 1 3O 3 O A3SO 1E4 1996101700201 19961017 00201 WP 1996 10 17 AU960183 1 19960125 G 7620 3141665 CABLE LKHEED 1049 C121C 5262118 WP WRIGHT R3350 R3350* 67040 EA EMER SHUTDOWN SY BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NO3 ENGINE EMERGENCY SHUTOFF CABLE FAILED - SUSPECT CABLE FAILED AT A POINT WITHIN A PULLEY BLOCK WHERE THE CABLE HAD BEEN DAMAGED- NO CORROSION OR WEAR WAS EVIDENT 2 L 7 4 4R 4 R 6A5 E272 1996101700202 19961017 00202 SW 1996 10 17 AU960184 1 19960215 G 6510 WASHER BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL T/R DRIVE SHAFT UNAPPROVED PART W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S 820269 (AUS) TAIL ROTOR DRIVE TRAIN AFT SHORT SHAFT TO LONG TAIL ROTOR DRIVE SHAFT DISC ASSEMBLY FITTED WITH INCORRECT TYPE FL AT WASHERSINSTEAD OF WITH CORRECT TYPE BEVELLED WASHERS AS REQUIRED BY THE MAINTENANCE MANUAL - UNAPPROVED PART - PERSON NEL/MAINTENANCE ERROR 1 G 7 1 3U 3 U H2SW E4CE 1996101700203 19961017 00203 CE 1996 10 17 AU960185 1 19960220 G 5510 1236232 BRACKET CESSNA 210 210L 2073448 CE CONT O520 IO520L 17032 SO MCAULY 2A34C E2A34C73 GL HORZ STAB SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) HORIZONTAL STABILISER REAR CENTRE SPAR REINFORCEMENT BRACKET CRACKED IN AREA OF LOWER LH FLANGE - INITIAL POINT OF CRACKAPPEARS TO BE AT THE BOLT HOLE WITH SECONDARY CRACKING IN BRACKETRADIUS - SUSPECT CAUSED BY PUSHING DOWN ON STABIL ISER DURING GROUND HANDLING 1 H 7 1 3O 3 O 3A21 E5CE 5 C P3EA9 1996101700204 19961017 00204 EU 1996 10 17 AU960186 1 19960124 G 3240 3034 HOSE PARTEN P68 P68B EU LG WHEEL/BRAKE S WORN W K NONE O OTHER IN INSP/MAINT 1 AU S 72 (AUS) HYDRAULIC HOSES (3OFF) CHAFED BY METAL IDENTIFICATION TAG - HOSESWERE LOCATED AT LH AND RH BRAKES AND BETWEEN COPI LOTS LH PEDAL AND PARK BRAKE - FOUND DURING INSPECTION IAW AD/HOSE/2 1 H 7 2 3O A31EU 1996101700205 19961017 00205 EU 1996 10 17 AU960187 2 19960122 G 7320 WYG56065 FCU CFMINT CFM56 CFM563C1 13802 EU ENG,FUEL CONTROL FAULTY W K NONE X ENGINE FLAMEOUT NR NOT REPORTED 1 AU S 16253 WYG56065 725496 (AUS) ENGINE FUEL CONTROL UNIT FAULTY 4 F E21EU 1996101700206 19961017 00206 NE 1996 10 17 AU960188 2 19960214 G 7261 235237790 CHIP DETECTOR TMECA ARRIEL1S1 SKRSKY S76 S76C 8143008 NE TMECA ARRIEL ARRIEL1S 60030 NE T ENGINE OIL SYS SHORT CIRCUIT W K NONE J WARNING INDICATION TO TAKEOFF 1 AU S 15515 15515 (AUS) NO2 ENGINE FREE TURBINE CHIP DETECTOR HAD INTERNAL SHORT CIRCUIT 1 G 7 2 3U 3 U NC H1NE E19EU 1996101700207 19961017 00207 CE 1996 10 17 AU960189 1 19960215 G 3230 11972 SOLENOID CESSNA CONTROLASSY CESSNA 425 425 2076018 CE LG EXT-RETRACT S INTERMITTENT W K NONE O OTHER NR NOT REPORTED 1 AU S 987 (AUS) LANDING GEAR EXTENSION SOLENOID INTERMITTENT IN OPERATION 1 L 7 2 3T RT A7CE 1996101700208 19961017 00208 SW 1996 10 17 AU960190 1 19960202 G 6120 4GBU80M GOVERNOR GULSTM G73 G73 3951802 SW PWA R1340 R1340AN1 52016 NE HAMSTD 23D 23D40 NE PROP CNTRL SYS FAULTY W K NONE O OTHER CR CRUISE 1 AU S 291735 ZP10966 210267 (AUS) RH ENGINE PROPELLER GOVERNOR TRANSFER VALVE FAULTY - VALVE ALLOWED FEATHER PUMP PRESSURE TO PARTIALLY BYPASS PREVE NTING UNFEATHERING OF PROPELLER 1 H 7 2 3R 3 R A783 5E2 6 C P719 1996101700209 19961017 00209 WP 1996 10 17 AU960191 1 19960215 G 6510 369A5518601 DRIVE SHAFT HUGHES 369 369HS 4470728 WP ALLSN 250C 250C18 03011 GL T/R DRIVE SHAFT SHEARED W O OTHER F FLT CONT AFFECTED TO TAKEOFF 1 AU S (AUS) TAIL ROTOR DRIVE SHAFT SHEARED APPROXIMATELY 457.2MM (18IN) FROM THE FORWARD END - SEVERAL LONGITUDINAL CRACKS WER E EVIDENT IN THEAREA OF THE FAILURE WHEN VIEWED UNDER X10 MAGNIFICATION 1 G 7 1 3U 3 U H3WE E4CE 1996101700210 19961017 00210 WP 1996 10 17 AU960192 1 19960215 G 5530 369A2129 HOUSING HUGHES 369 369HS 4470728 WP ALLSN 250C 250C18 03011 GL ATTACH FITTING S CORRODED W O OTHER F E FLT CONT AFFECTED VIBRATION/BUFFET TO TAKEOFF 1 AU S (AUS) STABILIZER STRUT DAMPER SHAFT PULLED FROM FITTING DURING HEAVY VIBRATION FOLLOWING TAIL ROTOR DRIVE SHAFT FAILURE (MDR 96/0191) - FITTING EXHIBITED SIGNS OF SEVERE INTERGRANNULAR CORROSION - AIRCRAFT OPERATES IN A SALT LADEN ENVIRONME NT 1 G 7 1 3U 3 U H3WE E4CE 1996101700211 19961017 00211 CE 1996 10 17 AU960193 1 19960215 G 2432 CB24380E BATTERY CESSNA 208 208 2073702 CE PWA PT6 PT6A114 52043 NE BATTERY/CHARGER LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S (AUS) BATTERY LEAKING ACID IN AREA AROUND POSITIVE TERMINAL SEAL - SUSPECT MANUFACTURING FAULT 1 H 7 1 3T 3 T NT A37CE E4EA 1996101700212 19961017 00212 NE 1996 10 17 AU960194 1 19960219 G 6730 SS275761024 BOLT SKRSKY S76 S76C 8143008 NE TMECA ARRIEL ARRIEL1S 60030 NE R-CRAFT SERVO SY WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FORWARD MAIN ROTOR SERVO LOWER MOUNT BOLT BADLY WORN - WORN BOLT AND REMAINING TWO SERVO BOLTS WERE ALSO FOUND TO BE INCORRECTLYINSTALLED 1 G 7 2 3U 3 U NC H1NE E19EU 1996101700213 19961017 00213 CE 1996 10 17 AU960195 1 19960111 G 2710 051010224 CONTROL CABLE 051010513 CESSNA 172 172M 2072418 CE AILERON CONTROL CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) AILERON CABLES PNO 0501015-224 (2OFF) AND AILERON BALANCE CABLE PNO 0510105-13 (1OFF) CORRODED - TURNBARRELS PNO AN155B32L (1OFF), PNO AN155B165 (2OFF) AND PNO AN155B8L CORRODED - SUSPECT CAUSED BY POOR PREPARATION PRIOR TO PAINT STR IPPING AND THE USEOF BICARBONATE OF SODA FOR STRIPPING - PERSONNEL/MAINTENANCE ERROR 1 H 7 1 3O NT 3A12 1996101700214 19961017 00214 CE 1996 10 17 AU960196 1 19960111 G 5530 SKIN CESSNA 172 172M 2072418 CE VERT STAB STRUCT CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) VERTICAL STABILIZER LEADING EDGE SKIN PN 0531006-96 AND LEADING EDGE RIB PN 0531006-5 CORRODED IN AREA WHERE MASK ED BY DORSAL FINSKIN - SUSPECT CAUSED BY INADEQUATE PROTECTION AND PROCEDURES DURING PAINT STRIPPING - PERSONNEL/MAINTE NANCE ERROR - SEE MDR 96/0195 FOR ADDITIONAL INFORMATION 1 H 7 1 3O NT 3A12 1996101700215 19961017 00215 CE 1996 10 17 AU960197 1 19960111 G 5511 053200197 SPAR CESSNA 172 172M 2072418 CE HORZ STAB CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) HORIZONTAL STABILIZER SKIN AND SPAR CRACKED IN AREA OF LIGHTENINGHOLE - FOUND DURING INSPECTION IAW CESSNA SERVICE BULLETIN SE94-8 1 H 7 1 3O NT 3A12 1996101700216 19961017 00216 CE 1996 10 17 AU960198 1 19960111 G 2730 051010545 CONTROL CABLE 051010544 CESSNA 172 172M 2072418 CE ELEVATOR CONTROL CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ELEVATOR TRIM CABLES PNO 0510105-44 AND PNO 0510105-45 AND ELEVATOR CONTROL CABLES PNO 0510105-291 AND PNO 0510105 -290CORRODED - SUSPECT CAUSED BY POOR PREPARATION PRIOR TO PAINT STRIPPING - SEE MDR 96/0195 FOR ADDITIONAL INFORMATION 1 H 7 1 3O NT 3A12 1996101700217 19961017 00217 CE 1996 10 17 AU960199 1 19960111 G 2750 051010594 CONTROL CABLE 051010593 CESSNA 172 172M 2072418 CE FLAP SYS CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FLAP CABLES PNO 0510105-93 (2OFF) AND PNO 0510105-94 (2OFF) CORRODED - SUSPECT CAUSED BY POOR PREPARATION PRIOR T O PAINT STRIPPING - SEE MDR 96/0195 FOR ADDITIONAL INFORMATION 1 H 7 1 3O NT 3A12 1996101700218 19961017 00218 NE 1996 10 17 AU960200 1 19960216 G 2560 WB5379 CABLE SKRSKY S76 S76A 8143006 NE HOIST DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S 033 (AUS) HOIST CABLE DAMAGED - 15 OF 19 STRANDS DAMAGED - MEF INVESTIGATION FOUND FAILURE WAS DUE TO OVERLOAD 1 G 7 2 3U H1NE 1996101700219 19961017 00219 NM 1996 10 17 AU960201 1 19960206 G 2910 82970010149 PIPE DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE MAIN HYD SYS HOLED W K NONE K FLUID LOSS LD LANDING 1 AU S (AUS) ALUMINIUM ALLOY HYDRAULIC PRESSURE PIPE LOCATED BETWEN THE ENGINE DRIVEN PUMP AND THE PRESSURE MANIFOLD HOLED DUE TO RUBBING ONSTRUCTURE IN AREA OF NACELLE ABOVE THE JET PIPE - LOSS OF NO2 SYSTEM HYDRAULIC FLUID 2 H 7 2 4T 4 T RT A13NM E20NE 1996101700220 19961017 00220 CE 1996 10 17 AU960202 1 19960221 G 5312 BULKHEAD CESSNA 182 182M 2072728 CE CONT O470 O470R 17026 SO MAIN FRAME SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH AND RH SIDE FORWARD DOORPOST BULKHEAD CRACKED - FOUND DURING INSPECTION IAW AD/C180/75 AMDT1 1 H 7 1 3O 3 O NT 3A13 E273 1996101700221 19961017 00221 CE 1996 10 17 AU960203 1 19960219 G 5312 07136084 BULKHEAD CESSNA 182 R182 2072734 CE LYC O540 O540J3C5 41532 EA MCAULY MAIN FRAME SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) STRUT ATTACHMENT BULKHEAD CRACKED ON LH SIDE - CRACK STARTS AT BEND RELIEF NOTCH AND GOES UNDER THE STRUT ATTACHME NT FITTING -CRACK LENGTH APPROXIMATELY 9.525MM (0.375IN) 1 H 7 1 3O 3 O RT 3A13 E295 1996101700222 19961017 00222 EU 1996 10 17 AU960204 1 19960119 G 5330 SEAL AIRBUS 320 A320212 EU EXT PLATES/SKIN DETERIORATED W K NONE E VIBRATION/BUFFET CL CLIMB 1 AU S (AUS) AIRCRAFT VIBRATING BADLY DURING CLIMB - INVESTIGATION FOUND WING TO FUSELAGE BELLY SEALS ON PANELS 192ET AND 191ET DETERIORATED AND BOTH LH AND RH RAM AIR INLET DOORS HAD EXCESSIVE PLAY 2 L 7 2 4F RT A28NM 1996102300014 19961023 00014 NM 1996 10 23 AU960205 1 19960119 G 5320 148T274010 CHORD BOEING 767 767277 NM GE MAIN FRAME SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 23934 (AUS) AFT FUSELAGE BULKHEAD CHORD LOCATED AT STN BS1809.5 WL250 RH CRACKED THROUGH FASTENER HOLE - CRACK LENGTH 59.69MM (2.35IN) 2 L 7 2 4F RT A1NM 1996101700223 19961017 00223 WP 1996 10 17 AU960206 2 19960215 G 7230 8962233 BLADE CESSNA 441 441 2076020 CE GARRTT TPE331 TPE3318 01514 WP T ENG CMPRSR/FAN DAMAGED W K NONE O E R OTHER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 AU S 8035019787 P31286 (AUS) LH ENGINE 1ST STAGE IMPELLER DAMAGED - SECONDARY DAMAGE CAUSED TO 2ND STAGE IMPELLER 1 L 7 2 3T 4 T RT A28CE E4WE 1996101700224 19961017 00224 EU 1996 10 17 AU960207 1 19960126 G 3230 E26000330H SOLENOID AIRBUS 320 A320212 EU LG EXT-RETRACT S FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S 0047ANSSN (AUS) LANDING GEAR HYDRAULIC SUPPLY SAFETY VALVE SOLENOID INTERMITTENT FAULT - INTERNAL LEAKAGE WITHIN MAIN VALVE WITH S OLENOID OPENCAUSED CUTOFF OF LANDING GEAR HYDRAULIC SUPPLY 2 L 7 2 4F RT A28NM 1996101700225 19961017 00225 SO 1996 10 17 AU960208 2 19960219 G 7310 633958 SEAL 628556 CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO ENG,FUEL DIST SY UNAPPROVED PART W K NONE E VIBRATION/BUFFET CL CLIMB 1 AU S 514615 (AUS) RH ENGINE FUEL NOZZLE SEALS PNO 633958-3 AND WASHERS PNO 640612 DETERIORATED AND IN POOR CONDITION - ON TWO NOZZL ES THE 'O' RING PNO 630979-9 HAD BEEN SUBSTITUTED BY AN UNKNOWN BLACK RUBBER 'O' RING WHICH HAD HARDENED TO A BRITTLE CO NDITION - TWO NOZZLES WEREPARTLY BLOCKED BY RUBBER DEPOSITS - UNAPPROVED PART 1 L 7 2 3O 3 O A7CE E8CE 1996102200002 19961022 00002 CE 1996 10 22 AU960209 1 19960211 G 7603 AN35A BOLT CESSNA 150 A150M 2071831 CE CONT O200 O200A 17020 SO POWER CONTROL SY MISSING W K NONE O OTHER LD LANDING 1 AU S 205388 (AUS) BOLT ATTACHING THROTTLE CABLE TO CARBURETTOR ARM MISSING CAUSING LOSS OF ENGINE CONTROL AND FORCED LANDING 1 H 7 1 3O 3 O 3A19 E252 1996102300015 19961023 00015 NM 1996 10 23 AU960210 1 19960115 G 5410 311T31021 PIN BOEING 767 767277 NM GE CF6 CF680A 30025 NE NAC-PYL M-FRAME CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH ENGINE PYLON MID SPAR FITTING FUSE PIN CRACKED ON INNER BORE APPROXIMATELY 23MM (0.90IN) IN FROM THE HEAD OF T HE PIN - CRACK LENGTH APPROXIMATELY 12MM (0.47IN) - FOUND DURING EDDY CURRENT INSPECTION IAW B76-54-40-4D - CRACK CONFIR MED BY MAGNETICPARTICLE INSPECTION 2 L 7 2 4F 4 F RT A1NM E13NE 1996101700226 19961017 00226 SO 1996 10 17 AU960211 1 19960221 G 5751 RIB PIPER PA44 PA44180 7104402 SO WING AIL/ELV SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RH AILERON NOSE RIBS CRACKED - FOUND DURING INSPECTION IAW AD/PA44/16 1 L 7 2 3O A19S0 1996101700227 19961017 00227 NM 1996 10 17 AU960212 1 19960111 G 2913 20894 BEARING ABEX ELECMOTOR BOEING 737 737377 NM MAIN HYD SYS INCORRECT ASSY W K NONE O OTHER DE DESCENT 1 AU S 223336ANSS (AUS) HYDRAULIC SYSTEM 'A' ELECTRIC PUMP THRUST BEARING PNO 20894 INCORRECTLY ASSEMBLED CAUSING IMPELLER PNO 66410 TO R UB ON COVER PNO 57976 DUE TO INSUFFICIENT CLEARANCE - METAL CONTAMINATION OF SYSTEM 'A' - PERSONNEL/MAINTENANCE ERROR 2 L 7 2 4F RT A16WE 1996101700228 19961017 00228 1996 10 17 AU960213 4 19960123 G 6113 08550303 SUPPORT CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY S CRACKED W K NONE E VIBRATION/BUFFET CR CRUISE 1 AU S (AUS) RH PROPELLER SPINNER SUPPORT CRACKED AND DISLODGED FROM PROPELLER DOME - SUPPORT IS CONSTRUCTED OF NYLON MATERIAL 1 L 7 2 3O 3A10 5 C P22EA 1996101700229 19961017 00229 SW 1996 10 17 AU960214 1 19960112 G 2910 27810322682 PIPE SWRNGN SA227DC FRCHLD SA227 SA227DC 3377521 SW GARRTT MAIN HYD SYS WORN W K NONE K FLUID LOSS CR CRUISE 1 AU S 851B (AUS) LH HYDRAULIC PIPE LEAKING FROM PIN HOLE - RH HYDRAULIC PIPE WORN AND LEAKING FROM RUBBING ON FUEL SUPPLY LINE PNO 27-62026-273 2 L 7 2 4T RT A18SW 1996101700230 19961017 00230 EU 1996 10 17 AU960215 2 19960215 G 7230 P132P04 BLADE CFMINT CFM56 CFM563B2 13802 EU T ENG CMPRSR/FAN CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 18236 720483 (AUS) ENGINE HP COMPRESSOR 2ND STAGE BLADE CRACKED IN DOVETAIL AREA 4 F E21EU 1996101700231 19961017 00231 SW 1996 10 17 AU960216 1 19960110 G 2730 2744046053 QUADRANT FRCHLD SA227 SA227DC 3377521 SW ELEVATOR CONTROL FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FLEET CHECK CARRIED OUT ON ELEVATOR QUADRANT STEPS FOR LOOSE OR MISSING ATTACHMENT BOLT NUT - NIL DEFECTS FOUND 2 L 7 2 4T RT A18SW 1996101700232 19961017 00232 EU 1996 10 17 AU960217 2 19960216 G 7250 3053556220 BEARING CFMINT CFM56 CFM563C1 13802 EU TURBINE SECTION FAILED W K NONE E VIBRATION/BUFFET CR CRUISE 1 AU S 725278 (AUS) NO1 ENGINE VIBRATION AT APPROXIMATELY 70% N1 - CREW ADVISED OF 4-5 LARGE ILLUMINATIONS FROM LEFT WING AREA - ENGIN E REDUCED TOIDLE WHERE OPERATION APPEARED NORMAL - SUSPECT NO4 BEARING FAILURE 4 F E21EU 1996101700233 19961017 00233 EU 1996 10 17 AU960218 1 19960220 G 3240 215042 BRAKE PILATS PC12 PC12 7090550 EU LG WHEEL/BRAKE S HIGH TEMPERATURE W K NONE O OTHER TX TAXI/GRND HDL 1 AU S 83 (AUS) BRAKES OVERHEATED DURING TAXI - TWO FLAT TYRES DUE TO FUSEABLE PLUGS MELTING - IT WAS REPORTED THAT NO EXCESSIVE B RAKING WASUSED - SUSPECT FAULTY FUSEABLE PLUGS FITTED 1 L 7 1 3T RT A78EU 1996101700234 19961017 00234 EU 1996 10 17 AU960219 1 19960130 G 3230 C242450061 UPLOCK AMD FALC50 FALCON900 2700160 EU LG EXT-RETRACT S FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S U378 (AUS) NOSE LANDING GEAR UPLOCK UNIT INTERNAL FAILURE - THIS DEFECT WAS RECEIVED FROM NO34 SQN RAAF AND IS FOR INFORMATIO N ONLY 2 L 7 3 4F RT A46EU 1996101700235 19961017 00235 SO 1996 10 17 AU960220 1 19960221 G 7110 COWLING EMB 120 EMB120 3260201 SO PWA 118 PW118A NE HAMSTD 14RF 14RF9 NE ENGINE COWL SYS BIRD STRIKE W K NONE C F.O.D. TO TAKEOFF 1 AU S (AUS) RH ENGINE UPPER INTAKE COWL DAMAGED BY BIRDSTRIKE 2 L 7 2 4T 4 T RT A31SO E20NE 6 C P11NE 1996101700236 19961017 00236 CE 1996 10 17 AU960221 1 19960226 G 5510 123262Y1 BRACKET CESSNA 210 210N 2073453 CE CONT O520 IO520L 17032 SO HORZ STAB SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) HORIZONTAL STABILIZER AFT LH MOUNTING REINFORCING BRACKET CRACKED ALONG BEND RADIUS ADJACENT TO LOWER OUTBOARD BOL T - CRACK LENGTH 25MM (0.98IN) 1 H 7 1 3O 3 O 3A21 E5CE 1996101700237 19961017 00237 EA 1996 10 17 AU960222 2 19960201 G 7414 103493108 MAGNETO BENDIX 103493108 BNORM BN2 BN2A26 1520226 EU LYC O540 O540E4C5 41532 EA ELEC PWR SUPPLY CONTAM WATER W O OTHER E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS TO TAKEOFF 1 AU S 1729 F098914F RL1378340A (AUS) RH ENGINE RH MAGNETO FAULTY - INVESTIGATION FOUND WATER CONTAMINATION SUSPECT CAUSED BY BLOCKAGE OF GAUZE SCREEN 1 H 7 2 3O 3 O A17EU E295 1996101700238 19961017 00238 SO 1996 10 17 AU960223 1 19960223 G 7120 8621202 MOUNT PIPER PA44 PA44180 7104402 SO LYC O360 LO360E1A6 41514 EA ENGINE MOUNTING CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S L12272 (AUS) RH ENGINE MOUNT ASSEMBLY CRACKED IN TWO PLACES - CRACKS START IN OPPOSITE SIDES OF THE TUBE JUST BELOW THE LH TOP ENGINE MOUNTATTACHMENT RING BUT ABOVE THE GUSSETT PN 86212-22V - ONE CRACK HAD PROPAGATED HALF WAY AROUND THE TUBE - THE OTHER CRACK HADTRAVELLED INTO THE TUBE BACK TO THE FIREWALL ATTACHMENT POINT - CRACK LENGTH APPROXIMATELY 25.4MM (1IN) - AD/PA44/10 (1) SB719 HAD BEEN PREVIOUSLY CARRIED OUT 1 L 7 2 3O 3 O A19S0 E286 1996101700239 19961017 00239 SO 1996 10 17 AU960224 1 19960227 G 5751 8639702 RIB PIPER SEMINOLE PIPER PA44 PA44180 7104402 SO WING AIL/ELV SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) AILERON NOSE RIBS PNO 86397-02 AND PNO 86397-03 CRACKED - FOUND DURING INSPECTION IAW AD/PA44/16 1 L 7 2 3O A19S0 1996101700240 19961017 00240 CE 1996 10 17 AU960225 1 19960228 G 3210 10581002367 A FRAME BEECH B76 BEECH 76 76 1153005 CE MAIN GEAR SYS BROKEN W K NONE O OTHER LD LANDING 1 AU S 575 AAC078 (AUS) LH MAIN LANDING GEAR 'A' FRAME ASSEMBLY BROKEN AT CORROSION TREATMENT HOLE AS INDICATED IN BEECH SB 2361 (AD/BEEC H76/18) 1 L 7 2 3O A29CE 1996101700241 19961017 00241 SO 1996 10 17 AU960226 1 19960229 G 5711 6658200 SPAR PIPER PA28 PA28235 7102810 SO OUTER WING SYS CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH WING MAIN SPAR CONTAINED EXFOLIATION CORROSION IN AREA OF REAROUTBOARD ATTACHMENT BOLT HOLE - FOUND WHEN WING R EMOVED FROM FUSELAGE - AIRCRAFT WAS MANUFACTURED IN 1963 AND HAD BEEN PARKED IN THE OPEN FOR THE LAST 12 MONTHS - SEE MD R 96/0227 AND MDR 96/0228 FOR ADDITIONAL INFORMATION 1 L 7 1 3O 2A13 1996101700242 19961017 00242 SO 1996 10 17 AU960227 1 19960229 G 5320 6241100 CHANNEL PIPER PA28235 PIPER PA28 PA28235 7102810 SO LYC MAIN FRAME SYS CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S 2100 2810173 (AUS) LH SIDE FUSELAGE CHANNEL SEVERELY CORRODED IN AREA ADJACENT TO THE STEEL REAR WING SPAR ATTACHMENT POINT - CHANNEL METAL HADCOMPLETELY OXIDISED - SUSPECT CORROSION HAD BEEN KNOWN ABOUT FOR SOME TIME AS AN AMATEURISH ATTEMPT HAD BEEN M ADE TO TREAT THECORROSION - PERSONNEL/MAINTENANCE ERROR - SEE ALSO MDR 96/0226 AND MDR 96/0227 FOR ADDITIONAL INFORMATIO N 1 L 7 1 3O 2A13 1996101700243 19961017 00243 SO 1996 10 17 AU960228 1 19960229 G 5711 6205401 SPAR PIPER PA28 PA28235 7102810 SO OUTER WING SYS CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S 2100 (AUS) RH WING AFT SPAR TO STEEL PLATE PN 66762-00 SEPARATED DUE TO CORROSION OF JOINING RIVETS - WHEN THE PLATE WAS REMO VED SEVERECORROSION WAS ALSO FOUND ON THE REAR SPAR - CAUSED BY CORROSION ACTION BETWEEN SPAR AND STEEL PLATE - SEE MDR 96/0226 AND MDR96/0227 FOR ADDITIONAL INFORMATION 1 L 7 1 3O 2A13 1996101700244 19961017 00244 GL 1996 10 17 AU960229 3 19960221 G 6110 A3205 SCREW BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO HARTZL HCJ3Y PHCJ3YF2 GL PROPELLER ASSY S LOOSE W K NONE O OTHER IN INSP/MAINT 1 AU S ED1641 (AUS) PROPELLER SCREW LOOSE AND CONTACTING LOW PITCH STOP CAUSING PROPELLER TO FEATHER ON SHUTDOWN 1 L 7 2 3O 3 O 3A16 E5CE 5 C P36EA 1996101700245 19961017 00245 1996 10 17 AU960230 4 19960222 G 6113 SUPPORT BEECH 35 M35 1151526 CE CONT O470 IO470C 17026 SO MCAULY 2A36C 2A36C23 GL PROPELLER ASSY S FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S 742410 (AUS) PROPELLER SPINNER SUPPORT FAILED - SPINNER BULKHEAD CRACKED - THIS IS THE SECOND SIMILAR OCCURRENCE ON THIS AIRCR AFT (LAST TIMEIN AUGUST 1992) - SUSPECT CAUSED COMBINATION OF OUT OF BALANCE PROPELLER AND LOSS OF PRELOAD DUE TO EXCESS IVE HOURS BETWEEN INSPECTIONS 1 L 7 1 3O 3 O 3A15 E273 5 C P880 1996102200003 19961022 00003 SO 1996 10 22 AU960231 2 19960303 G 7320 3010466 ARM PWA 324483432 EMB 110 EMB110P1 3260122 SO PWA PT6 PT6A34 52043 EA HARTZL HCB3T HCB3TN3 GL POWER CONTROL SY CRACKED W K NONE R PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 AU S A59370 (AUS) LH ENGINE FUEL CONTROL UNIT (FCU) CONTROL ARM CRACKED AND FAILED 1 L 7 2 4T 4 T A21SO E4EA 6 C P15EA 1998042300011 19980423 00011 CE 1998 4 23 AU960232 2 19960219 G 8530 317206 CYLINDER CONT MOONEY M20 M20K 5870220 SW CONT O360 TSIO360MB 17025 CE ENG CYL SEC SEPARATED W K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CL CLIMB 1 AU S 430 317206 317206 (AUS) NO4 CYLINDER HEAD SEPARATED FROM CYLINDER BARREL IN AREA OF SCREWTHREADS - PRE-EXISTING CRACK IN SCREW THREAD AREA 1 L 7 1 3O 3 O 2A3 E9CE 1998042300012 19980423 00012 SO 1998 4 23 AU960235 1 19960303 G 5751 SPAR PIPER PA31 PA31350 7103110 SO RT AILERON CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RH AILERON SPAR CRACKED IN AREA BEHIND INBOARD HINGE ARM ATTACHMENT POINT - FOUND DURING INSPECTION IAW AD/PA31/11 8 1 L 7 2 3O A20SO 1998042300013 19980423 00013 NM 1998 4 23 AU960237 1 19960228 G 6710 A4372 BRACKET ROBSIN ROBSIN R22 R22BETA NM MAIN RTR CNTRL BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S 1805 (AUS) COLLECTIVE CONTROL SYSTEM BRACKET BROKEN - SUSPECT FAILURE INITIATED DUE TO INCORRECT ASSEMBLY AND LOCKING OF THE EYE END WHICH PASSES THROUGH THE BRACKET 1 G 7 1 3O H10WE 1998042300014 19980423 00014 WP 1998 4 23 AU960238 1 19960204 G 6310 23623 LOCKNUT HILLER TRANSMISSION HILLER UH12 UH12E 4360122 WP ENG/TRANS CPLNG LOOSE W K NONE O OTHER DE DESCENT 1 AU S 1034 708 (AUS) TRANSMISSION CLUTCH BEARING RETENTION NUT LOCKWIRE BROKEN ALLOWING THE OUTER CLUTCH HOUSING TO BIND AGAINST THE F IRST STAGECARRIER - SUSPECT CAUSED BY INSUFFICIENT TORQUE ON NUT DURING LAST TRANSMISION OVERHAUL, NUT AND/OR BEARINGS NOT CORRECTLY SEATED DURING ASSEMBLY AT OVERHAUL OR LOCKWIRE PICKING UP ON SLEEVE AND BREAKING ALLOWING NUT TO LOOSEN DU RING FREQUENT AUTOROTATIONS - TRANSMISSION FREEWHEEL LOCKUP - METAL CONTAMINATION OF TRANSMISSION OIL FILTER 1 G 7 1 3O 4H11 1998042300015 19980423 00015 GL 1998 4 23 AU960239 3 19960228 G 6114 220117 HUB HARTZL MOONEY M20 M20E 5870212 SW LYC O360 IO360A1A 41514 EA HARTZL HCC2Y HCC2YK1 GL PROPELLER ASSY CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S 817 CH1151 CH1151 (AUS) PROPELLER HUB SEVERELY CORRODED INTERNALLY IN HUB CAVITY AND AROUND ATTACHMENT BOLT FILLETS 1 L 7 1 3O 3 O 2A3 1E10 5 C P920 1998042300016 19980423 00016 EA 1998 4 23 AU960240 2 19960301 G 7421 RHM38E SPARK PLUG CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA MCAULY 1A103 1A103TCM GL ENG,IGNITN DISTR FOULED W K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CR CRUISE 1 AU S 30 (AUS) BOTTOM SPARK PLUGS IN ENGINE FOULED 1 H 7 1 3O 3 O NT 3A19 E223 5 N P50GL 1998042300017 19980423 00017 EU 1998 4 23 AU960241 1 19960215 G 3040 350A89103701 WIPER ARM AEROSP AS355 AS355F2 8680812 EU WINDOW AI/DE-ICE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) WINDSHIELD WIPER ARM CRACKED THROUGH PIN HOLE THAT SECURES SPRINGTO WIPER ARM 1 G 7 2 3U H11EU 1998042300018 19980423 00018 EU 1998 4 23 AU960242 1 19960227 G 7160 352002034 HOSE LYC BNORM BN2 BN2B20 1520302 EU LYC O540 IO540K1B5 41532 EA ENG AIR INT FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S L25473L2547 (AUS) LH AND RH ENGINE AIR INDUCTION HOSES FAULTY AS PER AD/BN2/57 AND SB BN2-95 - LH ENGINE HOSE WIRE SEPARATING - RH E NGINE HOSE WIRE SEPARATING AND HOSE PARTIALLY COLLAPSED - BOTH HOSES WERE SERVICEABLE AT LAST 50 HOUR SERVICING 1 H 7 2 3O 3 O A17EU 1E4 1998042300019 19980423 00019 CE 1998 4 23 AU960243 1 19960217 G 2810 BAFFLE BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO FUEL STORAGE SYS DISINTEGRATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RH WING FUEL SYSTEM RESERVOIR FOAM BAFFLE DISINTEGRATED - FOUND DURING INSPECTION IAW SB 2109 PARA 1 - SUSPECT BA FFLE HAD NOTBEEN REPLACED IAW BEECH SB 2109 PART 2 - PERSONNEL/MAINTENANCE ERROR 1 L 7 2 3O 3 O 3A16 E5CE 1998042300020 19980423 00020 SO 1998 4 23 AU960244 1 19960306 G 3211 401335 BOLT 6750200 PIPER PA28 PA28RT201 7102818 SO LYC O360 IO360C1C6 41514 EA RT MLG INCORRECT FIT W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RH MAIN LANDING GEAR TRUNNION PIN RETAINING BOLT PNO 401335 NOT FITTED OR INCORRECTLY TORQUED FOLLOWING MAINTENAN CE - AFTTRUNNION RETAINER PIN PNO 67502-00 DISLODGED - DAMAGE TO WING UPPER SKIN - PERSONNEL/MAINTENANCE ERROR 1 L 7 1 3O 3 O 2A13 1E10 1998042300021 19980423 00021 SO 1998 4 23 AU960245 1 19960216 G 5343 AN411A BOLT PIPER PA28 PA28161 7102803 SO LT MLG FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH MAIN LANDING GEAR OUTBOARD ATTACHMENT BOLT FAILED - BOLT WAS PROTRUDING FROM SKIN 1 L 7 1 3O 2A13 1998042300022 19980423 00022 CE 1998 4 23 AU960246 1 19960227 G 3244 TIRE 5003064 CESSNA 404 404CESSNA 2075901 CE MCAULY 3FF32 3FF32C501 GL LG WHEEL/BRAKE S DEFLATED W K NONE O OTHER LD LANDING 1 AU S 87 (AUS) RH MAIN WHEEL TYRE DEFLATED DUE TO HEAVY APPLICATION OF BRAKES CAUSING FLAT SPOT - OCCURRED DURING CREW TRAINING 1 L 7 2 3O A25CE 5 C P45GL 1998042300023 19980423 00023 1998 4 23 AU960247 4 19960218 G 6122 DCFU290D13T6 DRIVE SHAFT CESSNA 404 404CESSNA 2075901 CE MCAULY 3FF32 3FF32C501 GL PROP CNTRL SYS SHEARED W K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CR CRUISE 1 AU S 7 00753 794309 (AUS) PROPELLER GOVERNOR (CSU) DRIVE SHAFT SHEARED 1 L 7 2 3O A25CE 5 C P45GL 1998042300024 19980423 00024 GL 1998 4 23 AU960248 1 19960123 G 3220 SPRING AMTR MAXAIR XP503 9570746 GL TAIL WHEEL BROKEN W K NONE O OTHER LD LANDING 1 AU S (AUS) TAIL WHEEL SPRING FAILED DURING LANDING - THIS DEFECT WAS RECEIVED FROM THE AUF AND IS FOR INFORMATION ONLY 1 H 7 1 3I NT EXPA1H71 1998042300025 19980423 00025 EU 1998 4 23 AU960250 2 19960128 G 8530 PISTON AMTR MAXAIR XP503 9570746 GL ROTAX 582 ROTAX582 55555 EU ENGINE CYL SEC CRACKED W K NONE E Y VIBRATION/BUFFET ENGINE STOPPAGE CR CRUISE 1 AU S (AUS) ENGINE PISTON CROWN CRACKED - THIS DEFECT WAS RECEIVED FROM THE AUF AND IS FOR INFORMATION ONLY 1 H 7 1 3I 3 I NT EXPA1H71 EXPE3I 1998042300026 19980423 00026 SO 1998 4 23 AU960253 1 19960306 G 3210 2251200 STUD PIPER PA30 PA30 7103002 SO MAIN GEAR SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH AND RH MAIN LANDING GEAR SIDE BRACE STUDS CRACKED - FOUND DURING MAGNETIC PARTICLE INSPECTION IAW AD/PA30/34 1 L 7 2 3O A1EA 1998042300027 19980423 00027 SO 1998 4 23 AU960256 2 19960207 G 8530 646283 EXHAUST VALVE CONT VALVEGUIDE CESSNA 182 182K 2072724 CE CONT O470 O470R 17026 SO RT ENG CYLINDER WORN W K NONE O OTHER IN INSP/MAINT 1 AU S 91 451050 451050 (AUS) ENGINE EXHAUST VALVES PNO 646283 AND VALVE GUIDES PNO 643766 WORNAND LEAKING 1 H 7 1 3O 3 O NT 3A13 E273 1998042300028 19980423 00028 CE 1998 4 23 AU960257 1 19960301 G 5510 12321391 BRACKET CESSNA STABILISER CESSNA 206 U206E 2073350 CE CONT O520 IO520F 17032 SO HORZ STAB SYS BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) HORIZONTAL STABILISER TRIM ACTUATOR MOUNT BRACKET BROKEN - AIRCRAFT IS USED FOR SKYDIVING WITH DOORS REMOVED AND D EFLECTORFITTED - SUSPECT TURBULANCE CAUSED BY DEFLECTORS CAUSES EXCESSIVETURBULANT AIRFLOW OVER EMPENNAGE - SEE MDR 96/0 178 FOR FURTHER INFORMATION 1 H 7 1 3O 3 O A4CE E5CE 1998042300029 19980423 00029 CE 1998 4 23 AU960258 1 19960308 G 2810 41423 FUEL CELL CESSNA 402 402B 207590P CE FUEL STORAGE SYS DETERIORATED W K NONE O K OTHER FLUID LOSS IN INSP/MAINT 1 AU S (AUS) LH AUXILIARY FUEL CELL DISINTEGRATING IN AREA OF CONTACT WITH GASKET SEALER - FUEL CELLS ARE A RELATIVELY NEW ITE M 1 L 7 2 3O A7CE 1998042300031 19980423 00031 SW 1998 4 23 AU960260 1 19960213 G 2435 2008 STARTER AIRPRTSCORP STARTERGEN FRCHLD SA227 SA227DC 3377521 SW GARRTT TPE331 TPE33112UA 01514 WP STARTER-GENERATO FAULTY W K NONE E VIBRATION/BUFFET NR NOT REPORTED 1 AU S 2008 (AUS) RH ENGINE STARTER/GENERATOR WOULD NOT ROTATE ENGINE WHEN ENGAGED 2 L 7 2 4T 4 T RT A18SW E4WE 1998042300032 19980423 00032 NE 1998 4 23 AU960261 2 19960220 G 7260 22080 RETAINER PWA BOEING 727 7272J4 1384006 NM PWA JT8 JT8D17 52049 NE T ENG AUX DRIVE FAILED W K NONE E X VIBRATION/BUFFET ENGINE FLAMEOUT CR CRUISE 1 AU S 22080 688015 (AUS) NO1 ENGINE FAILED IN FLIGHT - SUSPECT CAUSED BY FAILURE OF THE CONSTANT SPEED DRIVE (CSD) SHAFT REAR BEARING RETAI NER ALLOWINGTHE RETAINING NUT TO LOOSEN AND THE CSD SHAFT TO MOVE FORWARD ANDDISENGAGE THE DRIVE GEARS 2 L 7 3 4F 4 F RT A3WE E2EA 1998042300033 19980423 00033 SO 1998 4 23 AU960262 1 19960127 G 3222 702057505 STRUT GULSTM AA5 AA5 0631410 SO NLG FAILED W K NONE O OTHER TX TAXI/GRND HDL 1 AU S (AUS) NOSE LANDING GEAR TUBULAR STRUT FAILED DUE TO INTERNAL CORROSION CAUSED BY WATER ENTRAPMENT IN COVERING BOOT - NLG COLLAPSED -PROPELLER CONTACTED GROUND - SUSPECT BOOT HAD NOT BEEN REMOVED TOINSPECT NLG FOR SOME CONSIDERABLE TIME - PE RSONNEL/MAINTENANCE ERROR 1 L 7 1 3O A16EA 1996121900096 19961219 00096 NM 1996 12 19 AU960263 1 19960229 G 2460 CONNECTOR BOEING 737 737476 NM DC PWR DISTR ARCED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) CABIN AFT VACUUM CLEANER OUTLET CONNECTOR ON RH SIDE OF PASSENGER CABIN SHOWED EVIDENCE OF ARCING BETWEEN THE CONN ECTOR LIVE TERMINAL AND THE MOUNTING TRIM PANEL WITH A 25.4MM (1IN) DIAMETER BURN ON THE ADJACENT SOUND PROOFING BLANKET - INVESTIGATION FOUND MANUFACTURER HAD FITTED INCORRECT PANELS - UNAPPROVED PART - MANUFACTURING ERROR 2 L 7 2 4F RT A16WE 1998042300034 19980423 00034 NE 1998 4 23 AU960264 2 19960228 G 7320 WYG33234 CONTROLLER GE CF6 CF680A 30025 NE POWER CONTROL SY SEIZED W K NONE E VIBRATION/BUFFET DE DESCENT 1 AU S WYG33234 580242 (AUS) LH ENGINE MAIN ENGINE CONTROL (MEC) POWER LEVER SEIZED - STRIP INSPECTION OF MEC COULD FIND NO FAULTS 4 F E13NE 1998042300035 19980423 00035 1998 4 23 AU960265 1 19960304 G 7810 EXHAUST PIPE GARRTT TPE331 TPE33112UA 01514 WP T ENG CONE-PIPE CRACKED W K E NONE ENGINE SHUTDOWN M B OVER TEMP SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 AU S (AUS) RH ENGINE EXHAUST STUB CRACKED AROUND CIRCUMFERENCE OF THE FLANGE ALLOWING HOT EXHAUST GAS TO BURN THE PAINT ON TH E COWLING 4 T E4WE 1998042300036 19980423 00036 CE 1998 4 23 AU960266 1 19960306 G 3246 D30256 HUB MCAULY WHEEL CESSNA 172 172N 2072434 CE LG WHEEL/BRAKE S CORRODED W K NONE O OTHER LD LANDING 1 AU S (AUS) WHEEL HUB CORRODED - THREADS STRIPPED ALLOWING WHEEL FLANGE AND TYRE TO SEPARATE FROM HUB 1 H 7 1 3O NT 3A12 1998042300037 19980423 00037 WP 1998 4 23 AU960267 1 19960314 G 5342 ADAPTER DOUG DC3 DC3CS1C3G 3021458 WP ATTACH FITTING CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) VERTICAL FIN REAR ATTACHMENT ADAPTER CONTAINS SEVERE EXFOLIATION CORROSION IN AREA ADJACENT TO LH AND RH ATTACHMEN T BOLTS 2 L 7 2 4R A669 1998042300038 19980423 00038 SO 1998 4 23 AU960268 2 19960313 G 8520 CRANKSHAFT CONT CONT O300 O300C 17022 SO ENGINE SYS WORN W K NONE O OTHER IN INSP/MAINT 1 AU S 32067D3C 32067D3C (AUS) ENGINE CONTAINED NUMEROUS DEFICIENCIES MAKING IT UNSERVICEABLE FOR USE: 1. CRANKSHAFT 0.0254MM TO 0.0508MM (0.001I N TO 0.002IN) UNDER MINIMUM LIMITS2. CRANKCASE MAIN TUNNELS 0.0254MM TO 0.0508MM (0.001IN TO0.002IN) OUT OF LIMITS3. CYL INDERS (3OFF) REQUIRED GRINDING TO P015 4. COUNTERWEIGHTS UNSERVICEABLE AS PER CONTINENTAL SERVICE BULLETIN 5. OIL PU MP ACCESSORY HOUSING DAMAGED BEYOND REPAIR6. CYLINDERS (2OFF) STAMPED 'MT' UNSERVICEABLE AS PER SERVICE BULLETIN7. CYLIN DER (1OFF) OUT OF P015 LIMITS 8. CAMSHAFT LOBES DAMAGED9. OIL PUMP IMPELLERS DAMAGED BEYOND REPAIR 3 O E253 1998042300039 19980423 00039 CE 1998 4 23 AU960271 1 19960305 G 2820 10092004115 PIPE BEECH 200 B200C 1152924 CE FUEL DISTRBUTION WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MAIN FUEL PIPE CHAFING ON STRUCTURE IN AREA BETWEEN MAIN LANDING GEAR BAY AND WING FUEL TANK - FUEL PIPE ON VH-AMM IN SIMILAR CONDITION 1 L 7 2 4T A24CE 1998042300040 19980423 00040 GL 1998 4 23 AU960272 3 19960312 G 6110 A163352 O-RING MCAULY CESSNA 402 402B 207590P CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY WRONG PART W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S 940 760875 760875 (AUS) PROPELLER RETENTION NUT 'O' RING SEALS INCORRECT - PNO A1633-52 SEALS USED IN OIL FILLED HUBS FITTED INSTEAD OF C ORRECT PNOA1633-38 SEALS - INCORRECT SEALS BIND ON THE FERRULE CAUSING EXCESSIVE FRICTION DURING OPERATION AND PREVENTIN G FEATHERING -UNAPPROVED PART - PERSONNEL/MAINTENANCE ERROR 1 L 7 2 3O A7CE 5 C P22EA 1998042300041 19980423 00041 EA 1998 4 23 AU960273 2 19960227 G 8520 L2809236A CAM FOLLOWER LYC 0360A4A PIPER PA28 PA28180 7102808 SO LYC O360 O360A4A 41514 EA ENGINE FAILED W A UNSCHED LANDING E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CL CLIMB 1 AU S L2809236A L2809236A (AUS) ENGINE CAM FOLLOWERS FAILED - SEVERE INTERNAL DAMAGE TO ENGINE - METAL CONTAMINATION OF OIL SYSTEM 1 L 7 1 3O 3 O 2A13 E286 1996110100177 19961101 00177 CE 1996 11 1 AU960274 1 19960313 G 5312 12121273 DOUBLER CESSNA BULKHEAD CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO MAIN FRAME SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) REAR BULKHEAD RH TAILPLANE ATTACHMENT BRACKET DOUBLER CRACKED THROUGH - FURTHER INSPECTION FOUND REAR BULKHEAD CR ACKED IN THESAME AREA 1 H 7 1 3O 3 O A4CE E5CE 1996110100178 19961101 00178 GL 1996 11 1 AU960275 2 19960103 G 7250 TURBINE ALLSN SERIES11 ALLSN 250C 250C20 03013 GL T ENG TURBINE SE FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S CAT34207 (AUS) ENGINE GAS PRODUCER TURBINE ASSEMBLY FAULTY - TURBINE ASSEMBLY HAD NIL HOURS SINCE OVERHAUL - GP SUPPORT MOUNTING FLANGE BENT - DURING DISMANTLING TO CHANGE THE SUPPORT THE FOLLOWING DEFECTIVE ITEMS WERE FOUND :-1. 1ST STAGE NGV PNO 6 895021 - CRACKED AND VALVE DAMAGED 2. 1ST STAGE NGV HEAT SHIELD PNO 6890040 - CRACKED AND WARPED3. POSITION PLUGS (2OFF) PNO 6845899 - WORN 4. NO8 SUMP PNO 6845632 - EXCESSIVELY DENTED PERSONNEL/MAINTENANCE ERROR 3 U E4CE 1996111300007 19961113 00007 SO 1996 11 13 AU960276 2 19960206 G 8520 626739 COLLAR CONT CRANKSHAFT CESSNA 185 A185F 2072821 CE CONT O520 IO520D 17032 SO MCAULY 2A34C D2A34C98 GL R ENGINE POWER S WRONG PART W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S 566900 (AUS) CRANKSHAFT FITTED WITH INORRECT OIL TRANSFER COLLAR - STANDARD COLLAR PNO 626739 FITTED TO M10 CRANKSHAFT RESULTIN G IN EXCESSIVECLEARANCE - LOG BOOK ENTRY ALSO DETAILED FITMENT OF STANDARD SIZEBEARINGS FITTED ALTHOUGH THE ACTUAL BEARI NGS WERE M010 SIZE -UNAPPROVED PART - PERSONNEL/MAINTENANCE ERROR 1 H 7 1 3O 3 O 3A24 E5CE 5 C P3EA 1996110100179 19961101 00179 EA 1996 11 1 AU960277 2 19960308 G 7314 RG17980 PUMP ROMEC RG17980 LYC O720 IO720A1A 41546 EA ENG,FUEL DIST SY LEAKING W K NONE B K SMOKE/FUMES/ODORS/SPARKS FLUID LOSS CR CRUISE 1 AU S C542 L106854A (AUS) ENGINE DRIVEN FUEL PUMP LEAKING FROM REAR OF PUMP 3 O 1E15 1996111300010 19961113 00010 CE 1996 11 13 AU960278 1 19960206 G 2810 509200106 FUEL TANK GOODYEAR 50920010 BEECH 65 65 1152802 CE LYC O480 IGSO480A1E6 41529 EA HARTZL HCB3Z HCB3Z202 GL FUEL STORAGE SYS LEAKING W K NONE O K OTHER FLUID LOSS IN INSP/MAINT 1 AU S 7689016 (AUS) LH WING INBOARD FUEL TANK DETERIORATED AND LEAKING - THE TANK WAS REMOVED AND FOUND TO BE SEALED EXTERNALLY IN NUM EROUS PLACES WITHPR1422 COMPOUND - 2 BUTTONS FOUND ON LOWER FLOOR OF TANK BAY - TANK MANUFACTURED IN 1976 - SUSPECT TANK HAD BEEN LEFT NEAR EMPTYFOR AN EXTENDED TIME CAUSING THE RUBBER TO DRY OUT 1 L 7 2 3O 3 O 3A20 E284 5 C P907 1996110100180 19961101 00180 CE 1996 11 1 AU960279 1 19960206 G 5720 082217564 RIB CESSNA 402B CESSNA 402 402B 207590P CE MCAULY 3AF32C 3AF32C87 GL OUTER WING SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 002 (AUS) LH AND RH WHEEL WELL LANDING GEAR SUPPORT RIBS PNO 0822175-65 (LH) AND PNO 0822175-65 (RH) CRACKED AND DISTORTED - UNDER SKINDISTORTED IN AREA OF LANDING GEAR DOOR ATTACHMENT - NUMEROUS RIVETS MISSING - AIRCRAFT IS USED FOR SHORT HAU L OPERATIONS AT MAXIMUM WEIGHTS - SUSPECT CAUSED BY HEAVY LANDINGS 1 L 7 2 3O A7CE 5 C P22EA 1996110100181 19961101 00181 CE 1996 11 1 AU960280 1 19960314 G 5412 12534096 BULKHEAD CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO MAIN FRAME SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FIREWALL AND RH BULKHEAD CRACKED IN AREA OF EXHAUST MOUNT ATTACHMENT - AIRCRAFT IS USED AS A FLOAT PLANE 1 H 7 1 3O 3 O A4CE E5CE 1996110100182 19961101 00182 CE 1996 11 1 AU960281 1 19960314 G 5412 12534095 BULKHEAD CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO MAIN FRAME SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FIREWALL AND LH BULKHEAD CRACKED AT EXHAUST MOUNT ATTACHMENT - AIRCRAFT IS USED AS A FLOAT PLANE 1 H 7 1 3O 3 O A4CE E5CE 1996110100183 19961101 00183 CE 1996 11 1 AU960282 1 19960206 G 5347 002 SEAT TRACK CESSNA 402B CESSNA 402 402B 207590P CE MAIN FRAME SYS CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S 002 (AUS) SEAT TRACKS LOCATED NEAR AFT ENTRY DOOR EXTENSIVELY CORRODED AT AFT END - WHEN THE SEAT TRACKS WERE REMOVED IT WA S FOUND THAT THE FLOOR BENEATH THE TRACKS WAS ALSO CORRODED - FORWARD BAGGAGE FLOOR ALSO SHOWS SIGNS OF CORROSION - AIRC RAFT IS USED TO CARRY SEAFOOD WITHOUT ADEQUATE PROTECTION FROM LEAKING SALT PRODUCTS 1 L 7 2 3O A7CE 1996110100184 19961101 00184 CE 1996 11 1 AU960283 1 19960314 G 2730 12346506 TORQUE TUBE CESSNA ELEVATOR CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO ELEVATOR STRUCT LOOSE RIVETS W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RH ELEVATOR ASSEMBLY TORQUE TUBE PNO 1234650-6 TO ELEVATOR ATTACHMENT RIVETS LOOSE AND WORKING - AIRCRAFT IS OPERA TED AS AFLOAT PLANE 1 H 7 1 3O 3 O A4CE E5CE 1996110100185 19961101 00185 1996 11 1 AU960284 4 19960315 G 2561 PO723 LIFEVEST BOEING 747 747* NM EMERGENCY EQUIP INCORRECT ASSY W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) LIFE JACKET CO2 CYLINDER FIRING HEAD INCORRECTLY ASSEMBLED - THE HEAD WAS WIRED CLOSED WITH COPPER WIRE INSTEAD OF WITH THE CORRECT PLASTIC CLIP - RISK OF WIRE ENDS PUNCTURING BLADDER - PERSONNEL/MAINTENANCE ERROR 2 L 7 4 4F RT A20WE 1996110100186 19961101 00186 CE 1996 11 1 AU960285 1 19960228 G 5711 SPAR CESSNA 402 402B 207590P CE MCAULY 3AF32C 3AF32C87 GL OUTER WING SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) WING MAIN SPAR CONTAINED MULTIPLE CRACKS IN AREA AT TOP IN SPAR WEB 1 L 7 2 3O A7CE 5 C P22EA 1996110100187 19961101 00187 CE 1996 11 1 AU960286 1 19960318 G 5320 DOOR POST CESSNA 182 182E 2072712 CE CONT O470 O470R 17026 SO MAIN FRAME SYS CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH REAR DOOR POST CORRODED THROUGH IN AREA OF ATTACHMENT TO UNDERCARRIAGE BULKHEAD IN UNDER FLOOR AREA 1 H 7 1 3O 3 O NT 3A13 E273 1996110100188 19961101 00188 EU 1996 11 1 AU960287 1 19960316 G 7160 352002034 HOSE LYC IO540K1B5 BNORM BN2 BN2B20 1520302 EU LYC O540 IO540K1B5 41532 EA ACFT ENG AIR INT COLLAPSED W K NONE O OTHER IN INSP/MAINT 1 AU S L2550048A (AUS) RH ENGINE INDUCTION HOSE COLLAPSED DUE TO INTERNAL WIRE SEPARATING FROM THE HOSE - SLIGHT CORROSION WAS ALSO FOUN D ON THEWIRE IN THE AFFECTED AREA - FOUND DURING INSPECTION IAW AD/BN2/57- LH ENGINE HOSE WAS INSPECTED AND FOUND TO BE SERVICEABLE - LHENGINE INTAKE HOSE BETWEEN AIR BOX AND FUEL CONTROL COLLAPSED ON THE NEXT FLIGHT - RH HOSE THEN INSPECTE D AND FOUND TO BE COLLAPSING ALSO 1 H 7 2 3O 3 O A17EU 1E4 1996110100189 19961101 00189 GL 1996 11 1 AU960288 3 19960314 G 6110 B15921 SPRING HARTZL HCC2YK2CUF PARTEN P68 P68B EU LYC O360 IO360A1B6 41514 EA HARTZL HCC2Y HCC2YK2 GL PROPELLER ASSY S WRONG PART W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S 1350 AU5509 AU5509 (AUS) PROPELLER RETAINER SPRING INCORRECT PART - EARLY MODEL SPRING PNOB1594 IN LATE MODEL SPRING RETAINER PNO B1592-1 - UNAPPROVED PART- PERSONNEL/MAINTENANCE ERROR 1 H 7 2 3O 3 O A31EU 1E10 5 C P920 1996110100190 19961101 00190 CE 1996 11 1 AU960289 1 19960312 G 6120 DCF290D2BT3 CSU MCAULY DCF290D2BT3 CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO MCAULY 3AF32C 3AF32C505 GL PROP CNTRL SYS CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S 1510 762113 248434R 950621 (AUS) PROPELLER CSU END CAP CRACKED AND LEAKING - THE CRACK COMMENCED AT THE FULL FINE CONTROL STOPS AND RADIATED AROUN D THE CENTRECOLLAR AND WAS HIDDEN BY THE CONTROL ARM RETURN SPRING - THE END CAP IS MANUFACTURED FROM A BRITTLE PLASTIC TYPE MATERIAL 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 1996110100191 19961101 00191 CE 1996 11 1 AU960290 1 19960312 G 8120 47090813 VALVE GARRTT 47090813 CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO TURBO SUPERCHRGR LEAKING W K NONE E K VIBRATION/BUFFET FLUID LOSS CR CRUISE 1 AU S RHR0102 290447R (AUS) WASTEGATE VALVE LEAKING OIL - OIL WAS DUMPED OVERBOARD VIA THE WASTEGATE VALVE DRAIN TUBE 1 L 7 2 3O 3 O A7CE E8CE 1996110100192 19961101 00192 NM 1996 11 1 AU960291 1 19960313 G 3220 NLG PIPER PA60 PA60600A 7106002 NM NOSE-TAIL GEAR S COLLAPSED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) NOSE LANDING GEAR COLLAPSED - DAMAGE TO NOSE GEAR DOORS - INVESTIGATION FOUND THAT THE NOSE LANDING GEAR DRAG BRA CE ASSEMBLY REPLACEMENT IAW AD/TSA-600/41 AMDT 2 HAD NOT BEEN CARRIED OUT - PERSONNEL/MAINTENANCE ERROR 1 M 7 2 3O RT A17WE 1996110100193 19961101 00193 CE 1996 11 1 AU960292 1 19960203 G 3210 BUSHING CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO MCAULY MAIN GEAR SYS SEPARATED W K NONE O OTHER LD LANDING 1 AU S (AUS) LANDING GEAR PIVOT TORQUE LINK ATTACHMENT BOLT PULLED THE BUSH THROUGH THE CENTRE OF THE TORQUE LINK ALLOWING THE WHEEL ASSEMBLYTO TURN 90 DEGREES TO THE FORWARD DIRECTION OF THE AIRCRAFT - CAUSED BY WHEEL SHIMMY - SUSPECT A NON STAN DARD BUSH WAS FITTED APPROXIMATELY 4 YEARS PREVIOUS WITH A DIAMETER CLOSE TO THAT OF THE BOLT HEAD - FRETTING IN SERVIC E EVENTUALLY ALLOWED THE BOLTTO PULL THROUGH - UNAPPROVED PART - PERSONNEL/MAINTENANCE ERROR 1 L 7 2 3O 3 O 3A10 E5CE 1996110100194 19961101 00194 SO 1996 11 1 AU960293 2 19960201 G 8540 539800 SPRING CONT IO520M CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO R ENGINE REAR SE MISALIGNED W K NONE O OTHER IN INSP/MAINT 1 AU S 12 L565777 (AUS) ENGINE STARTER ADAPTER SPRING TWISTED IN HOUSING 1 L 7 2 3O 3 O 3A10 E5CE 1996110100195 19961101 00195 EU 1996 11 1 AU960295 1 19960319 G 3220 68231152 FRAME PARTEN P68 P68B EU NOSETAIL GEAR S CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NOSE LANDING GEAR SUPPORT FRAME CENTRE TUBE CRACKED IN AREA AFT OF CLAMP PNO 68-2-3115-3 - AIRCRAFT IS USED FOR T RAINING 1 H 7 2 3O A31EU 1996110100196 19961101 00196 EA 1996 11 1 AU960296 2 19960314 G 8530 CYLINDER PIPER PA30 PA30 7103002 SO LYC O320 IO320B1A 41508 EA R ENGINE CYL SEC CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S L104555 (AUS) LH ENGINE NO3 CYLINDER CRACKED IN AREA OF EXHAUST PORT - CRACK LENGTH 50.8MM (2IN) 1 L 7 2 3O 3 O A1EA 1E12 1996110100197 19961101 00197 SO 1996 11 1 AU960297 2 19960213 G 8520 652541 NUT CESSNA 210 210M 2073450 CE CONT O520 IO520L 17032 SO R ENGINE POWER S CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 570318 (AUS) ENGINE CYLINDER HOLD DOWN NUT CRACKED 1 H 7 1 3O 3 O 3A21 E5CE 1996110100198 19961101 00198 EA 1996 11 1 AU960298 2 19960316 G 8530 SL14995 RETAINER CESSNA 172 172RG 2072438 CE LYC O360 O360F1A6 41514 EA R ENGINE CYL SEC CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S L2817336A (AUS) ENGINE PUSH ROD TUBE RETAINERS (4OFF) CRACKED - RETAINERS WERE SHIPPED WITH GASKET SET PNO SL 75439-1 1 H 7 1 3O 3 O 3A17 E286 1996110100199 19961101 00199 EA 1996 11 1 AU960299 2 19960315 G 8530 L201552 PISTON LYC VO435A1F BELL 47 47G3B1 1181028 SW LYC O435 VO435A1F 41516 EA R ENGINE CYL SEC WORN W K NONE O E R OTHER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 AU S 117 L201552 L201552 (AUS) ALL SIX CYLINDERS FOUND TO HAVE EXCESSIVE WEAR TO PISTONS, RINGS AND VALVE TRAIN INCONSISTANT WITH TIME SINCE OVER HAUL - SUSPECTCAUSED BY UNREPORTED ENGINE OVERSPEED 1 G 7 1 3O 3 O 2H3 E279 1996110100200 19961101 00200 CE 1996 11 1 AU960300 1 19960215 G 3233 12810012 ACTUATOR CESSNA RHLGACTUATOR CESSNA 210 210N 2073453 CE CONT O520 IO520L 17032 SO LG EXT-RETRACT S CRACKED W K NONE O OTHER CL CLIMB 1 AU S 7316 (AUS) RH MAIN LANDING GEAR ACTUATOR CRACKED ALLOWING DRIVE GEAR TO DISENGAGE FROM DRIVEN GEAR 1 H 7 1 3O 3 O 3A21 E5CE 1996110100201 19961101 00201 1996 11 1 AU960301 1 19960318 G 7110 365A58106221 FAIRING AEROSP RHENGINECOWL TMECA ARRIEL ARRIEL1A 60030 NE ENGINE COWL SYS BROKEN W K NONE D INFLIGHT SEPARATION CR CRUISE 1 AU S (AUS) RH ENGINE COWL HINGE ASSEMBLY BROKEN 3 U E19EU 1996110100202 19961101 00202 CE 1996 11 1 AU960302 1 19960211 G 2750 SWITCH CESSNA 401 401A 207590D CE MCAULY 3AF32C 3AF32C505 GL FLAP SYS BROKEN WIRE W K NONE F FLT CONT AFFECTED LD LANDING 1 AU S (AUS) FLAP SELECTOR DOWN MICROSWITCH WIRE BROKEN 1 L 7 2 3O A7CE 5 C P22EA 1996110100203 19961101 00203 SO 1996 11 1 AU960303 1 19960305 G 3211 9529900 SIDE BRACE 9529902 PIPER PA34 PA34200 7103405 SO MLG SYS LT/RT CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT AND RT MAIN LANDING GEAR SIDE BRACE STUDS P/N 95299-00 AND P/N 95299-0 2 CRACKED - FOUND DURING MAGNETIC PARTIC LE INSPECTION IAW AD/PA34/46. 1 L 7 2 3O A7SO 1996110100204 19961101 00204 1996 11 1 AU960304 3 19960318 G 6114 D70151C87HUB HUB MCAULY 3AF32C87 CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO MCAULY PROPELLER ASSY S LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S 366 (AUS) PROPELLER HUB LEAKING RED DYE - STRIP INSPECTION FOUND THAT THE BLADE NUT EXPANSION LOCKING PLUGS OVERLAPPED - PR OPELLER MANUAL710930 REQUIRES A MINIMUM HOLE SPACING OF 4.762MM (0.1875IN) - PERSONNEL/MAINTENANCE ERROR 1 L 7 2 3O 3 O 3A10 E5CE 1996110100205 19961101 00205 EA 1996 11 1 AU960305 2 19960201 G 7320 3008787 ROD END EMB 110 EMB110P1 3260122 SO PWA PT6 PT6A34 52043 EA HARTZL HCB3T HCB3TN3 GL POWER CONTROL SY STIFF W K NONE E VIBRATION/BUFFET NR NOT REPORTED 1 AU S 57092 (AUS) ENGINE FUEL CONTROL UNIT CONTROL ROD CONNECTOR ROD END STIFF 1 L 7 2 4T 4 T A21SO E4EA 6 C P15EA 1996110100206 19961101 00206 GL 1996 11 1 AU960306 3 19960319 G 6110 C3475 BLADE NUT MCAULY 3AF32C87 CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY S FAULTY W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S 366 791363 791363 (AUS) PROPELLER BLADE NUTS HAD NOT BEEN REWORKED IAW THE MANUAL - PROPELLER HAS BEEN MODIFIED TO AN OIL FILLED MODEL AT WHICH TIME THE 'O' RING GROOVES ARE SUPPOSED TO BE MACHINED OUT - PERSNNEL/MAINTENANCE ERROR 1 L 7 2 3O 3 O 3A10 E5CE 5 C P22EA 1996110100207 19961101 00207 SO 1996 11 1 AU960307 1 19960216 G 5551 FITTING PIPER PA34 PA34200T 7103406 SO ATTACH FITTING S CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) TOP RH STABILATOR ATTACHMENT FITTING CORRODED - STABILATOR AND ALL FOUR FITTINGS REMOVED FOR FURTHER INSPECTION - INSPECTION OF TOP RH POSITION REVEALED EXTENSIVE CORROSION TO SKIN FLANGE AND CRACKING - CRACK LENGTH 19.05MM (0.75IN) - FOUND DURINGINSPECTION IAW AD/PA34/40 1 L 7 2 3O A7SO 1996110100208 19961101 00208 CE 1996 11 1 AU960308 1 19960301 G 5741 12107041 DOWEL CESSNA DOWEL CESSNA 210 210L 2073448 CE ATTACH FITTING S WORN W K NONE O OTHER IN INSP/MAINT 1 AU S 21061159 (AUS) WING TO FUSELAGE LOCATING DOWEL PINS WORN ALLOWING MOVEMENT AT ATTACHMENT POINTS - SUSPECT CAUSED BY USE OF ACF 50 MATERIAL WORKING BETWEEN MATING SURFACES AND CAUSING MOVEMENT 1 H 7 1 3O 3A21 1996110100209 19961101 00209 EA 1996 11 1 AU960309 2 19960213 G 7310 LW120980210 PIPE PIPER PA32 PA32R300 7103213 SO LYC O540 IO540K1G5 41532 EA ENG,FUEL DIST SY CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 764 L1607348A (AUS) FUEL INJECTION LINES ON NO2, NO3, NO5 AND NO6 CYLINDERS CRACKED IN AREA OF SOLDER LINE JOINT TO THE FLANGE - FOUN D DURINGINSPECTION IAW AD/LYC/90 1 L 7 1 3O 3 O A3SO 1E4 1996110100210 19961101 00210 SW 1996 11 1 AU960310 1 19960311 G 2435 03601008 BEARING LUCAS STARTERGENE FRCHLD SA227 SA227DC 3377521 SW GARRTT TPE331 TPE33112UA 01514 WP STARTER-GENERATO COLLAPSED W K NONE E J VIBRATION/BUFFET WARNING INDICATION CR CRUISE 1 AU S 94028 P70215 (AUS) LH ENGINE DRIVEN STARTER/GENERATOR REAR BEARING COLLAPSED - INTERNAL DAMAGE TO STARTER/GENERATOR - AIR DUCT DAMAG ED BY COOLING FAN 2 L 7 2 4T 4 T RT A18SW E4WE 1996110100211 19961101 00211 CE 1996 11 1 AU960311 1 19960220 G 2730 NAS77497 BEARING BEECH 95610005603 BEECH 55 95C55 1152708 CE CONT O520 IO520C 17032 SO ELEVATOR CONTROL SEIZED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH ELEVATOR PUSH-PULL ROD BEARING PNO NAS77-4-97 SEIZED AND WORKING IN FITTING PNO 95-610005-3 - ELONGATED HOLE W ORN INFITTING 1 L 7 2 3O 3 O 3A16 E5CE 1996110100212 19961101 00212 CE 1996 11 1 AU960312 1 19960310 G 2432 1013642105 CIRCUIT BOARD BEECH 200 B200C 1152924 CE PWA PT6 PT6A41 52043 EA BATTERY/CHARGER FAULTY W K NONE H N ELECT. POWER LOSS-50 PC FALSE WARNING CR CRUISE 1 AU S (AUS) BATTERY CHARGE SYSTEM PRINTED WIRING BOARD FAULTY 1 L 7 2 4T 4 T A24CE E4EA 1996110100213 19961101 00213 CE 1996 11 1 AU960313 1 19960131 G 5720 PLATE 00243001811 BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO MCAULY 3AF34C 3AF34C502 GL CENTRE WING SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) WING CENTRE SECTION FORWARD SPAR WEB PLATE LOCATED AT RH UPPER WING ATTACHMENT AREA CRACKED 1 L 7 2 3O 3 O 3A16 E5CE 5 C P22EA 1996110100214 19961101 00214 CE 1996 11 1 AU960314 1 19960223 G 3260 13771 SWITCH CESSNA 210 210L 2073448 CE CONT O520 IO520L 17032 SO LG POSITION IND FAULTY W K NONE O P OTHER NO WARNING INDICATION DE DESCENT 1 AU S (AUS) LH MAIN LANDING GEAR DOWNLOCK MICROSWITCH FAULTY - NLG MICROSWITCH SUSPECT FAULTY 1 H 7 1 3O 3 O 3A21 E5CE 1996110100215 19961101 00215 CE 1996 11 1 AU960315 1 19960310 G 5720 PLATE 00243001811 BEECH 58 58 1152740 CE CONT CENTRE WING SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) WING CENTRE SECTION FORWARD SPAR WEB PLATE CRACKED IN AREA OF LH UPPER WING ATTACHMENT AREA - CRACK LENGTH 25MM (0 .98IN) - SEVERALSMALLER CRACKS WERE FOUND AROUND THE LOCK BOLT HOLES - CRACK LENGTHS APPROXIMATELY 7MM (0.275IN) 1 L 7 2 3O 3A16 1996110100216 19961101 00216 SO 1996 11 1 AU960316 2 19960229 G 8520 CRANKCASE CONT GTSIO520M CESSNA 404 404CESSNA 2075901 CE CONT O520 GTSIO520M 17032 SO R ENGINE POWER S CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 276412R (AUS) LH ENGINE CRANKCASE CRACKED - CRACK STARTED ABOVE AND FORWARD OF NO5 CYLINDER AND EXTENDED DOWNWARDS TO THE ALTERN ATOR ATTACHMENT PAD - VISIBLE CRACK LENGTH 110MM (4.33IN) 1 L 7 2 3O 3 O A25CE E7CE 1996110100217 19961101 00217 SO 1996 11 1 AU960317 2 19960310 G 7414 104001667 SPRING BENDIX 103493505 BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO LT ENG MAG BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S 4719 1263468C (AUS) LH ENGINE LH MAGNETO IMPULSE COUPLING SPRING BROKEN - ENGINE HAD NOT OPERATED FOR APPROXIMATELY 8 MONTHS WHILE AIR CRAFT WAS WAITING FOR FITMENT OF THE RH ENGINE - ENGINE WAS GROUND RUN ON AWEEKLY BASIS - SUSPECT CORROSION AS CAUSE OF FAILURE 1 L 7 2 3O 3 O 3A16 E5CE 1996110100218 19961101 00218 SW 1996 11 1 AU960318 1 19960216 G 6220 412010190103 SPINDLE BELL 412 412 1182202 SW MAIN ROTOR HEAD FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S CH219 (AUS) MAIN ROTOR HEAD SPINDLE ASSEMBLY ELASTOMERIC DAMPER BEARING SHEARED 1 G 7 2 4U H4SW 1996110100219 19961101 00219 SW 1996 11 1 AU960319 1 19960219 G 6220 412010412101 BEARING BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE MAIN ROTOR HEAD DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MAIN ROTOR BLADE PITCH LINK ELASTOMERIC BEARING FAILED AROUND INNER RACE 1 G 7 2 4U 4 U H4SW E22EA 1996110100220 19961101 00220 SW 1996 11 1 AU960320 1 19960212 G 3210 4751211113 CROSS TUBE BELL FIXEDFLOATS BELL 47 47G3B2 1181029 SW MAIN GEAR SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FLOAT LANDING GEAR SYSTEM REAR CROSS TUBE CRACKED AROUND CIRCUMFERENCE IN AREA APPROXIMATELY 304.8MM (12IN) OUTBOA RD FROM THE LH MOUNT - CRACK ORIGINATED AT PREVIOUSLY DRILLED HOLE 1 G 7 1 3O 2H3 1996110100221 19961101 00221 SO 1996 11 1 AU960321 2 19960312 G 8530 648029P015 PISTON CESSNA 182 182Q 2072732 CE CONT O470 O470U 17026 SO R ENGINE CYLINDE BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S 465968 (AUS) NO5 CYLINDER PISTON SKIRT BROKEN - METAL CONTAMINATION OF OIL SYSTEM 1 H 7 1 3O 3 O NT 3A13 E273 1996110100222 19961101 00222 EU 1996 11 1 AU960322 1 19960304 G 2510 SEAT BELT MRCHTI S205 S20520F EU FLIGHT COMPARTME WRONG PART W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) SEAT BELTS DO NOT COMPLY WITH AD/RES/29 AMDT 1 - AUTOMOTIVE HARDWARE USED WITH NON MIL SPEC WEBBING - UNAPPROVED PART 1 L 7 1 3O A9EU 1996110100223 19961101 00223 SW 1996 11 1 AU960323 1 19960320 G 2510 SEAT BELT BELL 47 47G3B 1181026 SW FLIGHT COMPARTME WRONG PART W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) SEAT BELTS DO NOT COMPLY WITH NOTE 2 OF AD/RES/27 AMDT1 - UNAPPROVED PART 1 G 7 1 3O 2H3 1996110100224 19961101 00224 EA 1996 11 1 AU960324 2 19960209 G 7240 PCE56614 CASE PWA PT6A34 EMB 110 EMB110P2 3260124 SO PWA PT6 PT6A34 52043 EA TURBINE ENGINE C CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 1211 PCE56614 PCE56614STB (AUS) RH ENGINE GAS GENERATOR CASE CRACKED IN AREA AROUND THE UPPER ENGINE LORD MOUNT BRACKET ATTACHMENT RUNNING ALONG THE INNER EDGEOF THE WELD BEAD - CRACK LENGTH 25.4MM (1IN) 1 L 7 2 4T 4 T A21SO E4EA 1996110100225 19961101 00225 SW 1996 11 1 AU960325 1 19960204 G 5720 PANEL GULSTM G73 GULSTM G73 G73 3951802 SW PWA CENTRE WING SYS FAULTY W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S JZZ (AUS) WING CENTRE SECTION TOP HAT SECTIONS FOUND IN ANNEALED (SOFT) CONDITION FOLLOWING HEAT TREATMENT - SUSPECT HEAT T REATMENTINCOMPLETE 1 H 7 2 3R A783 1996110100226 19961101 00226 CE 1996 11 1 AU960326 1 19960312 G 5312 BULKHEAD CESSNA 182 182Q 2072732 CE MAIN FRAME SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FORWARD DOOR POST BULKHEAD CRACKED IN BEND RELIEF NOTCHES ON LH AND RH SIDES 1 H 7 1 3O NT 3A13 1996111300011 19961113 00011 WP 1996 11 13 AU960327 2 19960311 G 7240 8697281 PLENUM GARRTT TPE3311151A MTSBSI MU2 MU2B30 5780410 SW GARRTT TPE331 TPE33111U 01514 WP T ENG BURNER SEC CRACKED W K NONE E B VIBRATION/BUFFET SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 AU S P90181 P90181 (AUS) RH ENGINE PLENUM CHAMBER CRACKED AROUND DRAIN FITTING TAKEOFF FLANGE - CRACK LENGTH 50.8MM (2IN) - RH ENGINE BLEE D AIR TUBECHAFED AND LEAKING - PERSONNEL/MAINTENANCE ERROR 1 H 7 2 3T 4 T A2PC E4WE 1996110100227 19961101 00227 CE 1996 11 1 AU960328 1 19960305 G 2121 15205100109 VALVE 1520T100109 BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A42 52043 NE AIR DISTRIBUTION FAULTY W K NONE O OTHER CR CRUISE 1 AU S 2788 (AUS) PRESSURISATION SYSTEM LH FLOW PACK LOW ON FLOW - RH FLOW PACK SOLENOID STICKING CAUSING INTERMITTENT OPERATION - BLEED AIR DUCTFAIL LIGHT WIRE LOOSE 1 L 7 2 4T 4 T A24CE E4EA 1996110100228 19961101 00228 SO 1996 11 1 AU960329 2 19960227 G 8550 402711 STUD CONT HOUSING CESSNA 414 414 2075908 CE CONT O520 TSIO520J 17040 SO R ENGINE OIL SYS SEPARATED W K NONE K FLUID LOSS CR CRUISE 1 AU S 726 510412 (AUS) LH ENGINE DRIVEN OIL PUMP HOUSING STUD SEPARATED CAUSING OIL LEAK- STUD IS NOT USED ON THIS INSTALLATION 1 L 7 2 3O 3 O RT A7CE E8CE 1996110100229 19961101 00229 SO 1996 11 1 AU960330 1 19960201 G 2720 9621200 TORQUE TUBE PIPER PA34 PA34220T 7103420 SO RUDDER STRUCT SY FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RUDDER TORQUE TUBE ASSEMBLY FAILED - FOUND FOLLOWING VERY STRONG WIND GUSTS WITH NO GUST LOCKS FITTED - INSPECTION FOUND OLDCRACKS IN TORQUE TUBE SUSPECT CAUSED BY BENDING STRESSES IMPOSED BY POOR ALIGNMENT OF RUDDER HINGE LINE AND/OR WIND GUST DAMAGE 1 L 7 2 3O A7SO 1996110100230 19961101 00230 EA 1996 11 1 AU960331 2 19960317 G 7322 MA3PA CARBURETTOR FACET MA3PA CESSNA 150 A152 2071836 CE LYC O235 O235L2C 41505 EA ENG FUEL CONTROL CONTAMINATED W K NONE E Y VIBRATION/BUFFET ENGINE STOPPAGE CL CLIMB 1 AU S DT0269 L2303015 (AUS) CARBURETTOR MIXTURE/CUTOFF VALVE CONTAMINATED BY TWO LUMPS OF BROWN PARTICLES APPROXIMATELY 3MM (0.118IN) IN DIAM ETER -INVESTIGATION FOUND CORROSION IN THE CARBURETTOR AND FUEL FILTER ASSEMBLIES AND THE PARTICLES INDICATE THAT THEY A RE THE RESULT OFCORROSION OR WEAR 1 H 7 1 3O 3 O 3A19 E223 1996110100231 19961101 00231 NE 1996 11 1 AU960332 2 19960226 G 7320 PROBE BOEING 727 727277 138408S NM PWA JT8 JT8D15 52051 NE ENG,FUEL CONTROL BLOCKED W K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS TO TAKEOFF 1 AU S 687513 (AUS) NO1 ENGINE PT2 PROBE BLOCKED WITH INSECT REMAINS 2 L 7 3 4F 4 F RT A3WE E2EA 1996110100232 19961101 00232 EU 1996 11 1 AU960333 1 19960321 G 4900 PANEL BAC 146 146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE MAIN FRAME SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) APU CENTRAL FIRE BOX PANEL CRACKED IN THREE PLACES - FOUND DURING INSPECTION IAW AD/BAE146/53 AMDT1 2 H 7 4 4F 4 F A49EU E6NE 1996110100233 19961101 00233 SW 1996 11 1 AU960334 1 19960313 G 3213 540004501 MLG 540001503 MOONEY M20 M20J 5870219 SW MAIN GEAR SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 0 (AUS) MAIN LANDING GEAR LEG ASSEMBLY PNO 540004-501 CRACKED ADJACENT TO BOTTOM WELD ATTACHING LOWER PIVOT SUPPORT PLATE TO CROSS TUBE -TRUSS ASSEMBLY PNO 540001-503 DIAGONAL TUBES CRACKED ADJACENT TO WELDS 1 L 7 1 3O 2A3 1996110100234 19961101 00234 NM 1996 11 1 AU960335 1 19960223 G 2170 281135 CLAMP GARRTT SEPARATOR BOEING 737 737377 NM HUMIDITY CONTROL STRIPPED W K NONE O OTHER IN INSP/MAINT 1 AU S 67 281135 (AUS) LH AIRCONDITIONING PACK WATER SEPARATOR CLAMP SEPARATED AND SEAL DISPLACED - INVESTIGATION FOUND CLAMP THREAD STRI PPED 2 L 7 2 4F RT A16WE 1996110100235 19961101 00235 SO 1996 11 1 AU960336 2 19960313 G 8520 1265879C CRANKCASE CONT IO520C BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO R ENGINE POWER S CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 544 1265879C 126879C (AUS) CRANKCASE CRACKED FROM NO6 CYLINDER TOP REAR STUD - FURTHER INVESTIGATION FOUND CRANKCASE WAS CRACKED IN FOUR ARE AS -CRACKING CAUSED BY THERMAL STRESS DUE TO POWER AND TEMPERATURE LOADS IMPOSED DURING FLIGHT TRAINING 1 L 7 2 3O 3 O 3A16 E5CE 1996110100236 19961101 00236 EU 1996 11 1 AU960337 1 19960218 G 2910 A71671683 PIPE FOKKER F28 F28MK4000 4990810 EU MAIN HYD SYS CRACKED W K NONE K FLUID LOSS CR CRUISE 1 AU S (AUS) NO2 HYDRAULIC SYSTEM PIPE TO HYDRAULIC ACCUMULATOR CRACKED AND LEAKING AT FLARE 2 L 7 2 4F RT A20EU 1996110100237 19961101 00237 EU 1996 11 1 AU960338 1 19960321 G 5720 BOLT BAC 146 146200A 1500266 EU OUTER WING SYS BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) WING REAR SPAR ROOT JOINT ATTACHMENT FITTING BOLT BROKEN AT POSITION 'A' AS REFERRED TO IN BAE SB57-33 REV3 - FOU ND DURING INSPECTION IAW AD/BAE146/016 AMDT3 2 H 7 4 4F A49EU 1996110100238 19961101 00238 EU 1996 11 1 AU960339 1 19960219 G 2822 354301015 PUMP BNORM BN2 BN2B20 1520302 EU FUEL DISTRBUTION FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RH WING TIP FUEL TRANSFER PUMP FAILED 1 H 7 2 3O A17EU 1996110100239 19961101 00239 NE 1996 11 1 AU960340 2 19960316 G 7321 FCU BAC 146 146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE ENG,FUEL CONTROL FAULTY W K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 AU S (AUS) NO4 ENGINE FUEL CONTROL UNIT SUSPECT FAULTY - TGT ROSE TO APPROXIMATELY 700 DEGREES C - ENGINE DISPLAY PANEL SHOW ED TGTREACHED 929 DEGREES C FOR 3 SECONDS 2 H 7 4 4F 4 F A49EU E6NE 1996110100432 19961101 00432 SW 1996 11 1 AU960341 1 19960223 G 6310 476205321 BEARING BELL TRANSMISSION BELL 47 47G3B 1181026 SW LYC O435 TVO435D1B 41516 EA ENG/TRANS CPLNG WORN W K NONE F FLT CONT AFFECTED CR CRUISE 1 AU S 448 32078018 (AUS) MAIN ROTOR TRANSMISSION PNO 47-620-600-27 MAIN DRIVE FLANGE SHEARBOLTS PNO 047-620-485-009 SHEARED - DAMAGE TO MAI N ROTOR SWASHPLATE AND CONTROL RODS - TAIL ROTOR DRIVE SHAFT FAILED AT FORWARD HANGER BEARING - INSPECTION FOUND THAT TH E ROLLER BEARINGS PNO 47-620-532-1 IN THE FREEWHEEL UNIT PNO 47-620-536-7 WERE UNDERSIZE WITH THE CLUTCH DRUM BEING BEIN G UNEVENLY WORN ANDMATCHING WEAR ON THE BRAKE SHOES - SUSPECT FAILURE CAUSED BY SLIPPING OF THE FREEWHEEL UNIT DURING FL IGHT CAUSING A RAPID `POWER ON/POWER OFF' CONDITION TO BE APPLIED TO THE MAIN ROTOR WHICH WOULD BE FELT BY THE FLANGE DR IVE SHEAR BOLTS CAUSING EVENTUAL FAILURE - SEE MDR 96/0433 FOR SIMILAR OCCURRENCE 1 G 7 1 3O 3 O 2H3 1E13 1996110100433 19961101 00433 CE 1996 11 1 AU960342 1 19960228 G 5540 25330161 BALANCE WEIGHT CESSNA 303 T303 2073820 CE CONT O520 TSIO520AE 17040 SO RUDDER STRUCT MISSING W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RUDDER MASS BALANCE WEIGHT MISSING 1 L 7 2 3O 3 O A34CE E8CE 1996110100434 19961101 00434 EA 1996 11 1 AU960343 2 19960130 G 7414 S6LN1227 MAGNETO BENDIX S6LN1227 BNORM BN2MK3 BN2AMK3 1520203 EU LYC O540 O540E4C5 41532 EA HARTZL ENG IGNITION FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S A110031 (AUS) MAGNETO CAPACITOR LEAKING - CONTACT GAP LESS THAN 0.304MM (0.012IN) 1 H 7 3 3O 3 O A29EU E295 1996110100435 19961101 00435 SO 1996 11 1 AU960344 2 19960228 G 8530 SA643767P5 VALVE GUIDE CESSNA 303 T303 2073820 CE CONT O520 TSIO520AE 17040 SO R ENGINE CYLINDE WORN W K NONE O OTHER IN INSP/MAINT 1 AU S 161 246053 (AUS) NO2, NO4 AND NO6 CYLINDER EXHAUST VALVE GUIDES WORN BEYOND LIMITS 1 L 7 2 3O 3 O A34CE E8CE 1996110100436 19961101 00436 EA 1996 11 1 AU960345 2 19960130 G 7414 IO349371 COUPLING BENDIX S6LN1227 BNORM BN2MK3 BN2AMK3 1520203 EU LYC O540 O540E4C5 41532 EA ENG IGNITION WORN W K NONE O OTHER IN INSP/MAINT 1 AU S A275228 (AUS) MAGNETO IMPULSE COUPLING WORN IN EXCESS OF 0.3556MM (0.014IN) - INTERNAL TIMING GEAR OUT ONE TOOTH - FOUND DURING INSPECTION IAW AD/ELECT/27 AMDT6 1 H 7 3 3O 3 O A29EU E295 1996110100437 19961101 00437 EA 1996 11 1 AU960346 2 19960130 G 7414 S6LN1227 MAGNETO BENDIX S6LN1227 BNORM BN2MK3 BN2AMK3 1520203 EU LYC O540 O540E4C5 41532 EA ENG IGNITION OUT OF ADJUST W K NONE O OTHER IN INSP/MAINT 1 AU S A94453 (AUS) MAGNETO CONTACT GAP LESS THAN 0.3048MM (0.012IN) - INTERNAL TIMING GEAR OUT BY ONE TOOTH 1 H 7 3 3O 3 O A29EU E295 1996110100438 19961101 00438 CE 1996 11 1 AU960347 1 19960318 G 7603 12504012 BRACKET CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO THROTTLE CONTROL BROKEN W K NONE O OTHER DE DESCENT 1 AU S (AUS) THROTTLE CONTROL CABLE ATTACHMENT BRACKET BROKEN ALLOWING INNER AND OUTER CABLES TO MOVE TOGETHER - BRACKET WAS M ANUFACTURED FROM0.8128MM (0.032IN) ALCLAD 1 H 7 1 3O 3 O A4CE E5CE 1996110100439 19961101 00439 CE 1996 11 1 AU960348 1 19960314 G 3411 LINE CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA PITOT SYS SEPARATED W K NONE O OTHER TO TAKEOFF 1 AU S (AUS) PITOT SYSTEM PRESSURE LINE SEPARATED FROM CONNECTION TO HOURMETER AIRSPEED SWITCH - SUSPECT LINE DISCONNECTED DURI NG REFITMENT OF TACH INDICATOR DURING AD/INST/9 CALIBRATION CHECK WHICH WAS CARRIED OUT FOLLOWING PITOT/STATIC CALIBRATI ON CHECK 1 H 7 1 3O 3 O NT 3A12 E274 1996110100440 19961101 00440 GL 1996 11 1 AU960349 1 19960318 G 3230 ACTUATOR AMTR LNCAIR 320LANCAIR 056129G GL LG EXT-RETRACT S INCORRECT RIGGED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) NOSE LANDING GEAR ACTUATOR INCORRECTLY RIGGED - ACTUATOR RAM PUSHED MOUNTING PLATE IN THE NLG WHEEL TUNNEL THROUGH THEFIBREGLASS WALL 1 L 7 1 3O RT EXPA1L71 1996110100441 19961101 00441 NE 1996 11 1 AU960350 2 19960314 G 7230 FAN BLADE RROYCE RB211524G RROYCE RB211 RB211524D419 54555 NE T ENG CMPRSR/FAN INCORRECT FIT W K NONE E W VIBRATION/BUFFET INADEQUATE Q C CL CLIMB 1 AU S (AUS) NO4 ENGINE FAN BLADES (4OFF) FITTED TO INCORRECT POSITION CAUSING VIBRATIONS - PERSONNEL/MAINTENANCE ERROR 4 F E12EU 1996110100442 19961101 00442 CE 1996 11 1 AU960351 1 19960317 G 2460 70HF10 DIODE BEECH 99 C99 1154006 CE PWA PT6 PT6A36 52043 NE DC POWER DISTRIB FAILED W K NONE O H OTHER ELECT. POWER LOSS-50 PC IN INSP/MAINT 1 AU S (AUS) NO2 ELECTRICAL BUS FEEDER DIODE 70HF10 FAILED 1 L 7 2 3T 4 T A14CE E4EA 1996110100443 19961101 00443 CE 1996 11 1 AU960352 1 19960318 G 2610 WIRE AMPLFIER BEECH 99 C99 1154006 CE PWA PT6 PT6A36 52043 NE FIRE DETECTION S SHORTED W K NONE N FALSE WARNING IN INSP/MAINT 1 AU S (AUS) RH ENGINE FIRE DETECTOR CONTROL AMPLIFIER SUSPECT FAULTY - FURTHER INVESTIGATION FOUND A SHORT CIRCUIT IN THE WIRE BETWEENTHE AMPLIFIER AND THE 'T' HANDLE 1 L 7 2 3T 4 T A14CE E4EA 1996110100444 19961101 00444 WP 1996 11 1 AU960353 1 19960225 G 6220 5143711 HUB HILLER HEAD HILLER UH12 UH12E 4360122 WP LYC O540 VO540C2A 41532 EA MAIN ROTOR HEAD CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 189 1959 (AUS) MAIN ROTOR HUB CRACKED - FOUND DURING INSPECTION IAW AD/HIL12/22A 1 G 7 1 3O 3 O 4H11 E304 1996111300015 19961113 00015 NE 1996 11 13 AU960354 2 19960306 G 7240 13146 LINER RROYCE RB211524G2 RROYCE RB211 RB211524G19 NE TURBINE ENGINE C FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S 13146 13146 (AUS) ENGINE COMBUSTION LINER HEAD BREAKING UP IN AREA BETWEEN NO2 AND NO5 BLEED STRUTS - FOUND DURING BORESCOPE INSPECT ION IAW AD/RB211/19 AMDT1 (ROLLS ROYCE SB RB211-72-B482) 4 F E30NE 1996110100445 19961101 00445 NM 1996 11 1 AU960355 1 19960317 G 3510 OXYGEN BOTTLE BOEING 747 747438 NM CREW STA OXYGEN EMPTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) CREW OXYGEN BOTTLE EMPTY - 2ND OBSERVERS OXYGEN SELECTOR FOUND INEMERGENCY POSITION - SUSPECT SELECTOR LEFT IN EME RGENCY POSITION FOLLOWING PRE-FLIGHT CHECK 2 L 7 4 4F RT A20WE 1996110100446 19961101 00446 NM 1996 11 1 AU960356 1 19960317 G 2435 300SGL127Q GENERATOR DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE STARTER-GEN FAULTY W K NONE H ELECT. POWER LOSS-50 PC CL CLIMB 1 AU S 5 1116XL (AUS) ENGINE STARTER/GENERATOR FAULTY - INSPECTION FOUND EXTENSIVE INTERNAL ARCING AND HEAT DAMAGE 2 H 7 2 4T 4 T RT A13NM E20NE 1996110100447 19961101 00447 NE 1996 11 1 AU960357 2 19960319 G 7320 3035381 PIPE DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE ENG,FUEL CONTROL BROKEN W K NONE E VIBRATION/BUFFET DE DESCENT 1 AU S 120201 (AUS) NO2 ENGINE P3 SENSE LINE FROM COMPRESSOR TO HMU FRACTURED AT HMU 'T' FITTING - VIBRATION FROM FAILED RH STARTER/GE NERATOR MAY HAVECONTRIBUTED TO FAILURE (MDR 96/0356) 2 H 7 2 4T 4 T RT A13NM E20NE 1996110100448 19961101 00448 1996 11 1 AU960358 1 19960308 G 7720 6131508523 HARNESS 733M71 CFMINT CFM56 CFM563C1 13802 EU ENG TEMP IND SYS FAULTY W K NONE O OTHER CR CRUISE 1 AU S 85635 (AUS) NO1 ENGINE CORE HARNESS FAULTY 4 F E21EU 1996110100449 19961101 00449 CE 1996 11 1 AU960359 1 19960313 G 7602 S17771 CABLE CESSNA 172 172I 2072426 CE LYC O320 O320E2D 41508 EA POWER CONTROL SY FAILED W K NONE O R OTHER PARTIAL RPM/PWR LOSS CR CRUISE 1 AU S L2185827A E9671 (AUS) ENGINE MIXTURE CONTROL CABLE FAILED AT WORN SECTION OF EXPOSED CABLE 1 H 7 1 3O 3 O NT 3A12 E274 1996110100450 19961101 00450 EA 1996 11 1 AU960360 2 19960318 G 7414 10382681 CAPACITOR BENDIX MAGNETO PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA ENG IGNITION FAILED W K NONE O R OTHER PARTIAL RPM/PWR LOSS TO TAKEOFF 1 AU S (AUS) LH MAGNETO CAPACITOR FAILED 1 L 7 2 3O 3 O A20SO E14EA 1996110100451 19961101 00451 SO 1996 11 1 AU960363 1 19960325 G 6120 B24914S ROD PIPER PA30 PA30 7103002 SO LYC O320 IO320B1A 41508 EA HARTZL HCE2Y HCE2YL2 GL PROPELLER ASSY S FAULTY W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S CH2018 (AUS) PROPELLER PITCH CHANGE ROD SUSPECT FAULTY - DIMENSION FROM REAR PISTON SHOULDER TO FRONT RETAINER GROOVE AS ADVIS ED BY HARTZELLPROPELLERS IS 10.960INCHES (278.384MM) - MEASUREMENTS ON AFFECTED ROD WAS 10.85INCHES (275.59MM) RESULTING IN OVER COMPRESSION OF FEATHER SPRINGS CAUSING SLOW UNFEATHERING OPERATION 1 L 7 2 3O 3 O A1EA 1E12 5 C P9EA 1996110100452 19961101 00452 CE 1996 11 1 AU960365 1 19960306 G 3245 TUBE GOODYEAR FLIGHTCUSTOM BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO LT MLG DEFLATED W K NONE O OTHER LD LANDING 1 AU S (AUS) LH MAIN LANDING GEAR TYRE DEFLATED DURING LANDING ROLL - INVESTIGATION COULD FIND NO FAULT WITH THE TYRE BUT THE T UBE CONTAINED A SMALL TEAR SUSPECT CAUSED FOLLOWING DEFLATION AS TYREWAS BADLY DAMAGED DURING LANDING ROLL WHILE FLAT 1 L 7 2 3O 3 O 3A16 E5CE 1996110100453 19961101 00453 CE 1996 11 1 AU960366 1 19960308 G 2710 500000896 CONTROL CABLE CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO AILERON CONTROL FRAYED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH FORWARD AILERON CONTROL CABLE CONTAINED NUMEROUS BROKEN WIRES OVER A 100MM (4IN) LENGTH AT THE PULLEY LOCATED A T THE FIREWALLAREA AT FS 100.00 1 L 7 2 3O 3 O A7CE E8CE 1996110100454 19961101 00454 CE 1996 11 1 AU960367 1 19960229 G 5347 50150191 CHANNEL CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO SEAT SUPPORT DESTROYED W K NONE O OTHER IN INSP/MAINT 1 AU S ITEM22 (AUS) PILOT SEAT SUPPORT STRUCTURE CHANNEL DESTROYED DUE TO PROLONGED MOVEMENT WITH THE MOUNTING SCREWS UNDONE - LOOSE MOUNTING SCREWS ALSO FOUND ON SIMILAR AIRCRAFT - SUSPECT DUE TO PILOTS EXCERTING PRESSURE AGAINST SEATS DURING ENTRY/EXI T OF AIRCRAFT 1 L 7 2 3O 3 O A7CE E8CE 1996110100455 19961101 00455 EA 1996 11 1 AU960368 2 19960130 G 8530 L71455 CYLINDER LYC O320B1A PIPER PA30 PA30 7103002 SO LYC O320 IO320B1A 41508 EA RT ENGI CYL SEC OVER TEMP W K NONE O OTHER IN INSP/MAINT 1 AU S 1027 L71455 STBDL7145 (AUS) RH ENGINE INTERNAL COMPONENTS EXHIBITED SIGNS OF OVERHEATING - STEEL ITEMS BLUED AND CYLINDER BORES GLAZED - SUSPE CT ENGINE OVERHEATED DURING EXTENSIVE GROUND RUNNING AT HIGH POWER DURING FAULT FINDING OF THE ELECTICAL POWER SUPPLY S YSTEM - SEE MDR 96/0369 FOR SIMILAR DEFECTS ON LH ENGINE 1 L 7 2 3O 3 O A1EA 1E12 1996110100456 19961101 00456 EA 1996 11 1 AU960369 2 19960130 G 8530 L70155 CYLINDER LYC IO320B1A PIPER PA30 PA30 7103002 SO LYC O320 IO320B1A 41508 EA LT ENG CYL SEC OVER TEMP W K NONE O OTHER IN INSP/MAINT 1 AU S 1365 L70155 L70155 (AUS) LH ENGINE INTERNAL COMPONENTS EXHIBITED SIGNS OF OVERHEATING - STEEL ITEMS BLUED - ENGINE CYLINDER BORES GLAZED - SUSPECT CAUSEDBY GROUND RUNNING AT HIGH POWER SETTINGS DURING FAULT FINDING OF THE ELECTRICAL POWER SUPPLY SYSTEM - SEE MDR 96/0368 FOR SIMILAR DEFECT ON RH ENGINE 1 L 7 2 3O 3 O A1EA 1E12 1996110100457 19961101 00457 NM 1996 11 1 AU960370 1 19960301 G 6310 A1882 CLUTCH ROBSIN FREEWHEEL ROBSIN R22 R22BETA NM LYC O320 O320B2C 41508 EA ENG/TRANS CPLNG DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S 0274 (AUS) ENGINE TO TRANSMISSION SPRAG CLUTCH ASSEMBLY DAMAGED - WEAR EVIDENT ON CLUTCH SHAFT, CLUTCH HOUSING AND SPRAG ROL LERS -SUSPECT CLUTCH SLIPPAGE CONTRIBUTED TO THE FAILURE OF THE FORWARDFLEX PLATE 1 G 7 1 3O 3 O H10WE E274 1996110100458 19961101 00458 NM 1996 11 1 AU960371 1 19960228 G 6310 A9471 FLEX PLATE ROBSIN A9471 ROBSIN R22 R22BETA NM LYC O320 O320B2C 41508 EA ENG/TRANS CPLNG FAILED W K NONE O OTHER TO TAKEOFF 1 AU S 1946 (AUS) CLUTCH TO TRANSMISSION FLEX PLATE FAILED AT ALL FOUR ATTACHMENT POINTS - TWO LOOSE BOLTS WERE FOUND ON THE FORWAR D YOKE ON THE TRANSMISSION - FLEX PLATE WAS A PRE 'F' MODEL 1 G 7 1 3O 3 O H10WE E274 1996110100459 19961101 00459 SW 1996 11 1 AU960372 1 19960326 G 3213 54530011 HOUSING OZONE RHMLG SWRNGN SA226 SA226TC 8780404 SW ARSRCH MAIN GEAR SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 159 (AUS) RH MAIN LANDING GEAR STRUT HOUSING CRACKED AT AFT END OF RH AND LH SIDE DRAG BRACES 2 L 7 2 4T RT A8SW 1996110100460 19961101 00460 SW 1996 11 1 AU960373 1 19960312 G 5341 201751 ANGLE AIRTRC AT400 AT401 0390204 SW ATTACH FITTING S CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) WING ATTACHMENT ANGLES (2OFF) CRACKED ON INSIDE FACE AND CORRODED AROUND MOUNT HOLES AND LOWER HOLES 1 L 7 1 3R A17SW 1996110100461 19961101 00461 GL 1996 11 1 AU960375 1 19960306 G 3213 GM1 MLG AMTR LANCAR LANCAIR 05616TS GL MAIN GEAR SYS DISTORTED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LANDING GEAR LEG BENT IN AREA ABOVE OVERCENTRE LINK 1 L 7 1 3O RT EXPA1L71 1996110100462 19961101 00462 WP 1996 11 1 AU960376 2 19960326 G 7310 15740021 HEATER MTSBSI MU2 MU2B30 5780410 SW GARRTT TPE331 TPE3311151A 01514 WP ENG,FUEL DIST SY STRIPPED W K NONE K W FLUID LOSS INADEQUATE Q C TX TAXI/GRND HDL 1 AU S 1010 301118 PQ0181C (AUS) RH ENGINE OIL/FUEL HEATER OIL OUTLET FITTING PNO AN815-8J LOOSE AND LEAKING DUE TO STRIPPED THREADS IN THE HEATER HOUSING -PERSONNEL/MAINTENANCE ERROR 1 H 7 2 3T 4 T A2PC E3WE 1996110100463 19961101 00463 EU 1996 11 1 AU960377 1 19960123 G 2610 M390166109M RELAY 73040102 AIRBUS 320 A320211 3930320 EU FIRE DETECTION S FAULTY W K NONE N FALSE WARNING CR CRUISE 1 AU S 19775 227 (AUS) NO1 ENGINE FIRE WARNING SYSTEM FAULTY OPERATION - CAUSED BY FIRE DETECTION UNIT RELAY K1 CONTACTS BEING CLOSED 2 L 7 2 4F RT A28NM 1996110100464 19961101 00464 SO 1996 11 1 AU960378 2 19960324 G 7314 PUMP CESSNA 206 P206C 2073312 CE CONT O520 IO520A 17032 SO ENG,FUEL DIST SY FAULTY W K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CR CRUISE 1 AU S (AUS) ENGINE LOST POWER - FOLLOWING FITMENT OF A NEW FUEL PUMP THE LOW POWER WAS STILL EVIDENT - ANOTHER FUEL PUMP WAS F ITTED AND THE POWER LOSS RETURNED AFTER A SHORT PERIOD OF OPERATION - A THIRD FUEL PUMP RECTIFIED THE POWER LOSS - INVE STIGATION OF THE FIRST REPLACEMENT PUMP WHICH WAS A NIL TSO ITEM WHICH HAD BEEN ON THE SHELF FOR APPROXIMATELY THREE YE ARS REVEALED EVIDENCE OF INTERNAL CORROSION ON THE WORKING SURFACES - INVESTIGATION OF THE OTHER PUMP REVEALED DEBRIS IN THE VAPOUR RETURN 1 H 7 1 3O 3 O A4CE E5CE 1996110100465 19961101 00465 NM 1996 11 1 AU960379 1 19960222 G 5720 5711098007 PANEL DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE CENTRE WING SYS CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) CENTRE WING INNER ACCESS PANEL EXCESSIVELY CORRODED ON THE INNER BONDED EDGE DOUBLER 2 H 7 2 4T 4 T RT A13NM E20NE 1996111300016 19961113 00016 SO 1996 11 13 AU960380 1 19960319 G 5540 FITTING AYRES S2 S2RG10 SO ATTACH FITTING S CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S (AUS) TAILPLANE LH FORWARD ATTACHMENT FITTING CRACKED - ATTACHMENT BOLT LOOSE AND THIN WASHER BETWEEN TAILPLANE AND FITT ING WORN - PERSONNEL/MAINTENANCE ERROR 1 L 7 1 3T NC A4SW 1996110100466 19961101 00466 SO 1996 11 1 AU960381 1 19960327 G 3211 2251200 STUD PIPER PA30 PA30 7103002 SO MAIN GEAR SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MAIN LANDING GEAR SIDE BRACE STUDS CRACKED IN RADIUS - FOUND DURING MAGNETIC PARTICLE INSPECTION IAW AD/PA30/34 1 L 7 2 3O A1EA 1996110100467 19961101 00467 CE 1996 11 1 AU960382 1 19960227 G 5312 121341244 BULKHEAD CESSNA U206G CESSNA 206 U206G 2073356 CE MAIN FRAME SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S U20605004 (AUS) RH FORWARD DOOR POST BULKHEAD CRACKED IN AREA OF BEND RELIEF NOTCH - AD/CESSNA206/48 AMDT1 CARRIED OUT APPROXIMATE LY 200 HOURSPREVIOUS 1 H 7 1 3O A4CE 1996111300017 19961113 00017 NM 1996 11 13 AU960383 1 19960308 G 7120 65B903633 MOUNT 65B903632 BOEING 747 747312 1384932 NM PWA JT9 JT9D7R4G2 52054 NE ENGINE MOUNTING WORN W K NONE O OTHER IN INSP/MAINT 1 AU S 65B903632 P715159 (AUS) NO4 ENGINE FORWARD ENGINE MOUNT ASSEMBLY PNO 65B90363-3 AND AFT ENGINE MOUNT ASSEMBLY PNO 65B90363-2 ATTACHMENT L UG BUSHES WORN -WEAR ALSO TO AFT MOUNT ATTACHMENT BOLTS 2 L 7 4 4F 4 F RT A20WE E3NE 1996110100468 19961101 00468 SW 1996 11 1 AU960384 1 19960321 G 3211 S2735011055M SUPPORT SWRNGN SA226 SA226TC 8780404 SW GARRTT TPE331 TPE3313UW 01514 WP MAIN FRAME SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RH MAIN LANDING GEAR OUTBOARD UPPER DRAG BRACE SUPPORT STRUCTURE CRACKED - PART NUMBERS OF CRACKED COMPONENTS:- 1. HAT SECTION PNO S27-35011-055M - CRACKED 2. T DOUBLER PNO S27-35011-23M - CRACKED3. DOUBLER PNO S27-35011-017M - CRAC KED 4. DOUBLER PNO S27-35011-074M - WORN DRAG BRACE BUSHING ATTACHMENT HOLES 2 L 7 2 4T 4 T RT A8SW E4WE 1996110100469 19961101 00469 SO 1996 11 1 AU960385 1 19960325 G 5751 37210 BRACKET PIPER PA34 PA34200T 7103406 SO WING AIL/ELV SYS CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH AILERON CENTRE AND INBOARD HINGE BRACKETS CORRODED - RH AILERON CENTRE HINGE BRACKET CORRODED 1 L 7 2 3O A7SO 1996110100470 19961101 00470 CE 1996 11 1 AU960386 1 19960326 G 5320 081308929 DOUBLER CESSNA 310R CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO MAIN FRAME SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 1310 (AUS) NOSE WHEEL WELL LH AND RH DOUBLERS CRACKED FORE AND AFT ALONG RIVET LINE IN AREA OF STEERING BRACKET ATTACHMENT ( STEERINGBRACKET PNO 5013040-41) 1 L 7 2 3O 3 O 3A10 E5CE 1996110100471 19961101 00471 1996 11 1 AU960387 4 19960130 G 3431 4366941 SELECTOR SWITCH BOEING ILSCONTROL BOEING 767 767277 NM LANDING DATA SYS FAILED W K NONE O OTHER AP APPROACH 1 AU S 31660 151ANSETTS (AUS) ILS CONTROL PANEL 36 POSITION ROTARY COURSE SELECTOR SWITCH (S2) FAILED MIDWAY BETWEEN TWO POSITIONS 2 L 7 2 4F RT A1NM 1996110100472 19961101 00472 1996 11 1 AU960388 4 19960229 G 2312 TRANSCEIVER BEECH 200 200BEECH 1152920 CE VHF COMMUNICATIO FAULTY W K NONE O OTHER CL CLIMB 1 AU S (AUS) INTERMITTENT HASH ON VHF - VHF TRANSCEIVER REPLACED - GROUND TESTOF REPLACED ITEM COULD NOT DUPLICATE PROBLEM - AV IONICS CIRCUITBREAKER TRIPPED - INVESTIGATION FOUND THAT REPEATED STORING AND REMOVAL ACTIONS OF HEADSET MECHANICALLY C AUGHT AND TRIPPED CIRCUIT BREAKER ON REMOVAL - HEADSET STORAGE 'HANGER' ADJUSTED TOELIMINATE PROBLEM 1 L 7 2 4T A24CE 1996110100473 19961101 00473 CE 1996 11 1 AU960389 1 19960115 G 5320 05121871 DOOR POST 05121872 CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA MAIN FRAME SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH AND RH DOOR POST CRACKED FROM RELIEF RADIUS AT FLOOR LEVEL TO HIGH SHEAR FASTENER HOLE ON LH POST AND EXTENDING APPROXIMATELY7.937MM (0.3125IN) PAST HIGH SHEAR FASTENER HOLE ON RH POST - MAXIMUM CRACK LENGTH OF 31.75MM (1.25IN) EX TENDING OUTBOARD FROM RELIEF RADIUS 1 H 7 1 3O 3 O NT 3A12 E274 1996110100474 19961101 00474 EA 1996 11 1 AU960390 2 19960315 G 8520 AS16508 CAMSHAFT PIPER PA44 PA44180 7104402 SO LYC O360 O360E1A6 41514 EA R ENGINE POWER S WORN W K NONE O OTHER IN INSP/MAINT 1 AU S L31377 L31377 (AUS) ENGINE CAMSHAFT LOBES WORN - FOUND DURING PERIODIC INSPECTION 1 L 7 2 3O 3 O A19S0 E286 1996110100475 19961101 00475 EA 1996 11 1 AU960391 2 19960315 G 8520 LW15014 CAM FOLLOWER PIPER PA44 PA44180 7104402 SO LYC O360 O360E1A6 41514 EA R ENGINE POWER S WORN W K NONE O OTHER IN INSP/MAINT 1 AU S L31377 L31377L2 (AUS) LH AND RH ENGINE CAM FOLLOWERS WORN BEYOND LIMITS - LH ENGINE CAMSHAFT REQUIRES REPLACEMENT - BOTH ENGINES HAVE H AD LW16702ADDITIVE IAW SB 446B AND OIL CHANGE EACH 50 HOURS SINCE OVERHAUL 1 L 7 2 3O 3 O A19S0 E286 1996110100476 19961101 00476 WP 1996 11 1 AU960392 1 19960313 G 5520 HINGE DOUG DC3 DC3CS1C3G 3021458 WP PWA ELEVATOR STRUCT WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH ELEVATOR MID AND OUTBOARD HINGES EXCESSIVELY WORN - APPROXIMATELY 25.4MM (1IN) MOVEMENT FORWARD AND AFT - INBOA RDELEVATOR ATTACHMENT BRACKET PNO 1115188 WAS FOUND WITH HEAVY EXFOLIATION CORROSION - BEARING WAS ALSO UNSERVICEABLE 2 L 7 2 4R A669 1996110100477 19961101 00477 CE 1996 11 1 AU960393 1 19960311 G 2731 TRIM TAB CESSNA 206 U206G 2073356 CE ELEVATOR CONTROL INCORRECT RIGGED W K NONE F W FLT CONT AFFECTED INADEQUATE Q C DE DESCENT 1 AU S (AUS) ELEVATOR TRIM TAB INCORRECTLY RIGGED - DURING INVESTIGATION IT WAS FOUND THAT THE ELEVATOR TRIM TAB WAS SET AT 5 D EGREES 'UP' AND 25 DEGREES 'DOWN' - THE CORRECT TRAVEL SHOULD HAVE BEEN 25 DEGREES 'UP' AND 5 DEGREES 'DOWN' - AIRCRAFT HAS DONEAPPROXIMATELY 10 HRS SINCE LAST INSPECTION - PERSONNEL/MAINTENANCE ERROR 1 H 7 1 3O A4CE 1996110100478 19961101 00478 WP 1996 11 1 AU960394 1 19960313 G 5520 BRACKET DOUG DC3 DC3CS1C3G 3021458 WP PWA ELEVATOR STRUCT CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ELEVATOR STOP BRACKET AND INBOARD ELEVATOR ATTACHMENT BRACKET RIBS CORRODED 2 L 7 2 4R A669 1996110100972 19961101 00972 WP 1996 11 1 AU960395 1 19960313 G 5520 ELEVATOR DOUG DC3 DC3CS1C3G 3021458 WP ELEVATOR STRUCT DETERIORATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH ELEVATOR UNSERVICEABLE DUE TO POOR CONDITION AND FABRIC DETERIORATION - DRAIN HOLES WERE BLOCKED AND WATER WAS TRAPPED INSIDE 2 L 7 2 4R A669 1996110100973 19961101 00973 WP 1996 11 1 AU960396 1 19960313 G 5530 VERTICAL FIN DOUG DC3 DC3CS1C3G 3021458 WP VERT STAB STRUCT CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) VERTICAL FIN AND LH AND RH STRINGERS CONTAINED EXFOLIATION CORROSION 2 L 7 2 4R A669 1996110100974 19961101 00974 WP 1996 11 1 AU960397 1 19960313 G 5540 31151251 BRACKET DOUG DC3 DC3CS1C3G 3021458 WP RUDDER STRUCT SY CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RUDDER BRACKETS PNO 3115125-1 CONTAINED SEVERE EXFOLIATION CORROSION - IN THE AREA WHERE THE TOP BRACKET HAD CORRO DED THROUGH THE BEARING DROPPED ONTO THE LOWER BRACKET WHICH ALSO CONTAINED SEVERE EXFOLIATION CORROSION WHICH HAD REDU CED THE THICKNESS TO 1.587MM (0.0625IN) - THE TOP BEARING HAD FAILED AND THE BALLS HAD FALLEN OUT ALLOWING FOWARD AND AF T MOVEMENT OF THE RUDDER CAUSING THE MID AND LOWER BEARINGS TO ALSO FAIL 2 L 7 2 4R A669 1996110100975 19961101 00975 CE 1996 11 1 AU960398 1 19960301 G 2510 5000B2500950 BUCKLE CESSNA 182 182H 2072718 CE FLIGHT COMPARTME UNSAFE W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FRONT SEATS BELT BUCKLES FAULTY - BUCKLES UNDO AT THE SLIGHTEST TOUCH WITHOUT ANY SIGNIFICANT LIFTING OF LEVER - THE SEAT BELTS HAVE COME UNDONE DESPITE PROPER TENSION ADJUSTMENT OF BELTS - BUCKLES ARE MANUFACTURED BY `AMSAFE' AND W ERE FITTED FOLLOWING CARRYING OUT OF AD/RES/29 1 H 7 1 3O NT 3A13 1996110100976 19961101 00976 WP 1996 11 1 AU960399 1 19960313 G 5540 31151251 HINGE DOUG DC3 DC3CS1C3G 3021458 WP VERT STAB STRUCT CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ONE REMOVAL OF THE RUDDER, SEVERE EXFOLIATE CORROSION WAS FOUND ON THE FORWARD END OF THE TOP RUDDER HINGE ARM PN O 3115125-1 THE FOLLOWING DEFECTS WERE ALSO FOUND: 1. FIN TOP WAS REMOVED AND FOUND TO HAVE SEVERE CORROSION ON THE STR UCTURE 2. REAR RIB REQUIRED REPLACEMENT 3. VERTICAL RIB REQUIRED EXTENSIVE REPAIR AND ALL OTHER AREAS REQUIRED CORROSION REMOVAL AND REPROTECTION 4. BOTH LH AND RH SKINS REQUIRED REPAIR AND REPROTECTION 2 L 7 2 4R A669 1996110100977 19961101 00977 WP 1996 11 1 AU960400 1 19960313 G 5713 STRINGER DOUG DC3 DC3CS1C3G 3021458 WP OUTER WING SYS CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH WING CONTAINED EXFOLIATION CORROSION IN THE FOLLOWING AREAS BETWEEN STN 53 AND STN 107 (LH LANDING LIGHT CUT OU T)1. STRINGERS NO3, NO4 AND NO5 IN UPPER SECTION OF THE OUTER WING 2. STRINGERS NO53, NO54 AND NO55 IN LOWER SECTION OF THE OUTER WING 2 L 7 2 4R A669 1996110100978 19961101 00978 WP 1996 11 1 AU960401 1 19960313 G 5330 SKIN DOUG DC3 DC3CS1C3G 3021458 WP EXT PLATES/SKIN CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) SEVERE EXFOLIATION CORROSION IN BOTH THE FRONT AND REAR SKINS, ATTACHMENT ANGLES AND DOUBLERS LOCATED IN TAIL WHEE L BAY 2 L 7 2 4R A669 1996111300018 19961113 00018 EU 1996 11 13 AU960402 1 19960321 G 2510 94231 SEAT BELT SAAB SF340 340B 7860101 EU FLIGHT COMPARTME INCORRECT REPAIR W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) SEAT BELTS REWEBBED USING AUTOMOTIVE WEBBING - UNAPPROVED REPAIR - UNAPPROVED PART - PERSONNEL/MAINTENANCE ERROR 2 L 7 2 4T RT A52EU 1996110100979 19961101 00979 GL 1996 11 1 AU960403 3 19960307 G 6111 C4451 FERRULE MCAULY BLADE MCAULY 3A32C D3A32C90 GL PROPELLER ASSY S CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 890699 (AUS) PROPELLER BLADE FERRULES LOCATED IN HUB BLADE SOCKETS CRACKED THROUGH OLD DISUSED ACTUATING PIN HOLES 5 C P21EA 1996110100980 19961101 00980 GL 1996 11 1 AU960404 3 19960307 G 6114 D5904 PROPELLER HUB MCAULY D3A32C90R MCAULY 3A32C D3A32C90 GL PROPELLER ASSY S CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 890699 890699 (AUS) PROPELLER HUB CRACKED IN THREADED AREAS IN ALL BLADE SOCKETS - FURTHER INVESTIGATION FOUND THAT IT MAY NOT BE CRAC KING BUTDAMAGE - MEF INVESTIGATION PENDING 5 C P21EA 1996110100981 19961101 00981 GL 1996 11 1 AU960405 2 19960327 G 7320 CONNECTOR 206062721103 BELL 206 206L1 1182107 SW ALLSN 250C 250C28B 03013 GL ENG,FUEL CONTROL HIGH RESISTANCE W K NONE O OTHER LD LANDING 1 AU S (AUS) GOVERNOR LINEAR ACTUATOR (PNO 206062721103) EARTH TERMINAL CRIMP HAD HIGH RESISTANCE PREVENTING ACTUATOR FROM WORK ING DURINGLANDING 1 G 7 1 3U 3 U H2SW E1GL 1996110100982 19961101 00982 EU 1996 11 1 AU960406 1 19960401 G 5341 TB2011001006 FITTING TB2011001007 SOCATA TB10 TB10TOBAGO 8680696 EU ATTACH FITTING S WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH AND RH WING REAR ATTACHMENT FITTINGS PNO TB2011001006 AND PNO TB2011001007 HAD LOOSE BUSHINGS AND WORN HOLES 1 L 7 1 30 NT A51EU 1996110100983 19961101 00983 SW 1996 11 1 AU960407 1 19960319 G 3230 ED12402 BODY 4001391BR GULSTM 690TP 690A 0141722 SW MAIN GEAR SYS BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S GA33 (AUS) MAIN LANDING GEAR INNER DRAG BRACE ATTACHMENT FLANGE BROKEN OFF MLG BODY - VICE JAW MARKS FOUND ON OUTER SURFACE 1 H 7 2 3T 2A4 1996110100984 19961101 00984 SO 1996 11 1 AU960408 1 19960330 G 2750 D15224 MOTOR EMB 110 EMB110P1 3260122 SO HARTZL HCB3T HCB3TN3 GL FLAP SYS FAULTY W K NONE F FLT CONT AFFECTED LD LANDING 1 AU S (AUS) FLAP MOTOR ASSYMETRY WIRING BROKEN 1 L 7 2 4T A21SO 6 C P15EA 1996110100985 19961101 00985 SO 1996 11 1 AU960409 1 19960401 G 3230 14805A CYLINDER EMB 110 EMB110P1 3260122 SO PWA LG EXT RETRACT S CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 110253 (AUS) NOSE LANDING GEAR ROTATING CYLINDER CRACKED ON RH SIDE UPPER WELDED AREA - CRACK LENGTH 15MM (0.59IN) - TWO SMALLE R CRACKS WERE ALSO FOUND IN THE SAME AREA - FOUND DURING INSPECTION IAW SB110-032-0053 REV 7 PT 2 PARA 2.2.6. 1 L 7 2 4T A21SO 1996110100986 19961101 00986 SO 1996 11 1 AU960410 2 19960322 G 8530 646680 CYLINDER CONT O470U CESSNA 182 182Q 2072732 CE CONT O470 O470U 17026 SO R ENGINE CYL SEC WRONG PART W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S 230 466437 (AUS) CYLINDER AND PISTON FITTED TO NO3 POSITION WERE INCORRECT PARTS -INCORRECT CYLINDER PNO 646680 HAD A SHORT REACH S PARK PLUG - CORRECT PNO 653444 CYLINDER HAS A LONG REACH SPARK PLUG AND PISTON PNO 648029 WITH STEEL INSERT - DIFFERENC E IN PISTON WEIGHTS WAS 315 GRAMS - PERSONNEL/MAINTENANCE ERROR - UNAPPROVED PART 1 H 7 1 3O 3 O NT 3A13 E273 1996110100987 19961101 00987 CE 1996 11 1 AU960411 1 19960315 G 3230 50410051 SPRING CESSNA LHMLGSTRUT CESSNA 310 310R 2074245 CE LG EXT-RETRACT S BROKEN W K NONE N FALSE WARNING LD LANDING 1 AU S (AUS) LH MAIN LANDING GEAR DOWNLOCK SPRING BROKEN 1 L 7 2 3O 3A10 1996110100988 19961101 00988 1996 11 1 AU960412 4 19960322 G 3410 PIPE CESSNA 182 182Q 2072732 CE ENVIRONMENT DATA DISTORTED W K NONE O I W OTHER FLT. ATTITUDE INST. INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) INSTRUMENT STATIC SYSTEM PIPE BETWEEN ALTIMETER AND VSI KINKED INTHREE PLACES - PERSONNEL/MAINTENANCE ERROR 1 H 7 1 3O NT 3A13 1996110100989 19961101 00989 EA 1996 11 1 AU960413 2 19960226 G 7314 RA8987 GASKET ROMEC FUELPUMP PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA ENG,FUEL DIST SY FAILED W K NONE O K OTHER FLUID LOSS IN INSP/MAINT 1 AU S 209 D2499 L108268A (AUS) RH ENGINE DRIVEN FUEL PUMP GASKET RUPTURED AND LEAKING FUEL - AD/FSM/25 HAD BEEN CARRIED OUT 25.2 HOURS PREVIOUSL Y 1 L 7 2 3O 3 O A20SO E14EA 1996110100990 19961101 00990 SO 1996 11 1 AU960414 1 19960221 G 3230 4194902 ROD PIPER PA31 PA31350 7103110 SO LG EXT-RETRACT S SEIZED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RH MAIN LANDING GEAR TELESCOPIC DOWNLOCK ROD SEIZED IN THE EXTENDED POSITION - THIS AREA OF THE ROD IS COVERED BY A RUBBERBOOT AND WAS FOUND TO BE CORRODED AND THE BOOT CONTAINED A QUANTITY OF RED DUST - FURTHER INVESTIGATION FOUND TH AT THE NLGDOWNLOCK ROD WAS LACKING IN LUBRICATION AND BINDING BUT WAS NOT SEIZED 1 L 7 2 3O A20SO 1996110100991 19961101 00991 CE 1996 11 1 AU960415 1 19960320 G 2742 99140563 ACTUATOR CESSNA 650 650 2076802 CE HORIZ STAB SYS FAILED W K NONE F FLT CONT AFFECTED CR CRUISE 1 AU S 2522 (AUS) HORIZONTAL STABILISER PRIMARY TRIM ACTUATOR FAILED INTERNALLY 2 L 7 2 4F A9NM 1996110100992 19961101 00992 NM 1996 11 1 AU960416 1 19960202 G 2460 BACC18AE35 CIRCUIT BREAKER BOEING 737 737377 NM DC POWER DISTRIB TRIPPED W K NONE H ELECT. POWER LOSS-50 PC CR CRUISE 1 AU S (AUS) NO1 NORMAL TRANSFER CIRCUIT BREAKER C819 FAULTY - CIRCUIT BREAKER FAILED WORKSHOP CALIBRATION TESTS FOLLOWING REMO VAL 2 L 7 2 4F RT A16WE 1996111300019 19961113 00019 NM 1996 11 13 AU960417 1 19960323 G 2920 6510 SWITCH BOEING 767 76733A NM PWA 4056 PW4056 NE AUX HYD SYS FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S 6510 (AUS) RAM AIR TURBINE (RAT) AIRSPEED SWITCH FAULTY - SUSPECT FAULTY DIODE - RAT FAILED TO AUTODEPLOY 2 L 7 2 RT 4 F RT A1NM E24NE 1996110100993 19961101 00993 EU 1996 11 1 AU960418 1 19960401 G 7714 408106008 GEAR LYC LTS101750B1 BOLKMS 117 BK117B1 5626012 EU LYC LTS101 LTS101750B1 41560 NE ENG PWR IND SYS FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S LE45818E LE45818E (AUS) ENGINE NG SPEED PICKUP GEAR PLATE RIVETS LOOSE 1 G 7 2 3U 3 U H13EU E5NE10 1996110100994 19961101 00994 SW 1996 11 1 AU960419 1 19960215 G 5210 2724152051 BELLCRANK FRCHLD SA227 SA227DC 3377521 SW CREW-PASS DOOR S BROKEN W K NONE O OTHER CR CRUISE 1 AU S (AUS) CABIN ENTRY DOOR SEAL VALVE ACTUATING TAB BROKEN FROM BELLCRANK ASSEMBLY - DOOR SEAL WOULD NOT INFLATE - SUSPECT INCORRECT RIGGING AT MANUFACTURE 2 L 7 2 4T RT A18SW 1996110100995 19961101 00995 GL 1996 11 1 AU960420 3 19960329 G 6114 C98 HUB MCAULY D2A34C980 CESSNA 188 A188A 2073008 CE MCAULY 2A34C D2A34C98 GL PROPELLER ASSY S CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 711953 711953 (AUS) PROPELLER HUB CRACKED IN THREADED AREA OF NO2 BLADE SOCKET 1 L 7 1 3O A9CE 5 C P3EA 1996110100996 19961101 00996 GL 1996 11 1 AU960421 3 19960329 G 6111 90AT BLADE MCAULY D2A34C98 CESSNA 188 A188B 2073005 CE MCAULY 2A34C D2A34C98 GL PROPELLER ASSY S CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S 711953 711953 (AUS) PROPELLER BLADES (2OFF) CORRODED IN AREA OF BLADE BUTT OUTER FOUR THREADS 1 L 7 1 3O A9CE 5 C P3EA 1996110100997 19961101 00997 CE 1996 11 1 AU960422 1 19960329 G 2510 SEAT BELT CESSNA 150 150 2071802 CE FLIGHT COMPARTME WRONG PART W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) SEAT BELTS WERE CONSTRUCTED FROM AUTOMOTIVE HARDWARE USED WITH NON MIL-SPEC WEBBING AND HAVE NO FORM OF IDENTIFICA TION - FOUNDDURING INSPECTION IAW WITH AD/RES/29 AMDT 1 - UNAPPROVED PART - PERSONNEL/MAINTENANCE ERROR 1 H 7 1 3O NT 3A19 1996110100998 19961101 00998 SO 1996 11 1 AU960423 1 19960311 G 7922 CIRCLIP LYC VERNATHERM PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA AC,ENG OIL DIST FAILED W K NONE E VIBRATION/BUFFET CL CLIMB 1 AU S 0 L761861A (AUS) LH ENGINE OIL COOLER BYPASS VALVE (VERNATHERM) BODY CIRCLIP BROKEN - ONE PIECE OF BROKEN CIRCLIP LODGED IN OIL PR ESSURE RELIEF VALVE - SUSPECT CIRCLIP INCORRECTLY HEAT TREATED - RH ENGINE VERNATHERM SIMILARLY AFFECTED 1 L 7 2 3O 3 O A20SO E14EA 1998043001174 19980430 01174 SW 1998 4 30 AU960424 1 19960311 G 3250 2782792001 STEERING SYSTEM SWRNGN 2782792001 FRCHLD SA227 SA227DC 3377521 SW ACFT STEERING SY MALFUNCTIONED W K NONE O OTHER TX TAXI/GRND HDL 1 AU S 191 (AUS) NOSE WHEEL STEERING FAILED TO RESPOND TO PILOTS INPUT WHEN SPEED LEVERS SET TO HIGH AND STEERING PARK BUTTON DEPRE SSED - GREEN NWSANNUNCIATOR LIGHT STAYED ILLUMINATED AND NO INDICATION OF AMBER NWS FAIL LIGHT 2 L 7 2 4T RT A18SW 1998043001175 19980430 01175 SW 1998 4 30 AU960425 1 19960318 G 2844 27191523 TRANSDUCER EDCLIFF 4901 FRCHLD SA227 SA227DC 3377521 SW FUEL INDICATION FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S 36385 (AUS) FUEL PRESSURE TRANSDUCER FAULTY - RH BOOST PUMPS INDICATED LOW FUEL PRESSURE 2 L 7 2 4T RT A18SW 1998043001176 19980430 01176 CE 1998 4 30 AU960426 1 19960322 G 2110 1138000 COMPRESSOR 1138000 BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA CABIN AIR COND FAILED W K NONE E B A VIBRATION/BUFFET SMOKE/FUMES/ODORS/SPARKS FLAME/FIRE CR CRUISE 1 AU S 07055A (AUS) RH ENGINE DRIVEN AIRCONDITIONING COMPRESSOR FAILED DUE TO SEVERE OVERHEATING - COMPRESSOR PULLEY BEARING COLLAPSED - COMPRESSOR CLUTCH SECTION SEPARATED FROM THE PULLEY ASSEMBLY BUT WAS STILL CONNECTED TO THE DRIVE SHAFT AND WAS SWUN G AROUND CONTRIBUTING TO THE VIBRATION 1 L 7 2 4T 4 T A24CE E4EA 1998043001177 19980430 01177 EU 1998 4 30 AU960427 1 19960225 G 3245 50028221 WHEEL 50028062 ISRAEL 1124 1124 4500102 EU LG WHEEL/BRAKE S DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S 287 DEC86319 (AUS) MAIN LANDING GEAR WHEEL TYRE FILL VALVE THREAD STRIPPED - THE TYRE FILL GAUGE PN GP10-105-158 CAME OUT WITH THE W HEEL THREAD STILL IN THE THREAD ON THE FILL VALVE - SUSPECT INCORRECT FITMENT OF VALVE 2 M 7 2 4F A2SW 1998043001178 19980430 01178 CE 1998 4 30 AU960428 1 19960402 G 3260 JE1 MICROSWITCH CESSNA 310 310R 2074245 CE LG POSITION IND FAULTY W K NONE O N OTHER FALSE WARNING LD LANDING 1 AU S (AUS) RH MAIN LANDING GEAR DOWNLOCK MICROSWITCH ACTUATOR LEAF BROKEN OFF 1 L 7 2 3O 3A10 1998043001179 19980430 01179 NE 1998 4 30 AU960429 2 19960326 G 7210 BEARING 310820701 STBROS SD3 SD360 8100606 EU PWA PT6 PT6A67R 52043 NE TURBINE ENG. RED SEIZED W K E NONE ENGINE SHUTDOWN O OTHER CL CLIMB 1 AU S 0 106183 (AUS) LH ENGINE WAS SHUT DOWN AND FEATHERED FOR TRAINING PURPOSES - THE FEATHERED ENGINE CONTINUED TO ROTATE AT APPROXIM ATELY 100RPM - INVESTIGATION FOUND THE MAIN OIL FILTER HEAVILY CONTAMINATED WITH METAL - CAUSED BY PLANET GEAR (PNO 3108 207-01) BEARING AND STEEL SLEEVE SEIZING 2 H 7 2 4T 4 T A41EU E26NE 1998043001180 19980430 01180 EU 1998 4 30 AU960431 1 19960328 G 7160 352002034 HOSE LYC IO540K1B5 BNORM BN2 BN2B20 1520302 EU LYC O540 IO540K1B5 41532 EA ACFT,ENG AIR INT FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S L2552648A (AUS) RH ENGINE INDUCTION HOSE INTERNAL WIRE SEPARATING FROM HOSE - FOUND DURING INSPECTION IAW AD/BN2/57 1 H 7 2 3O 3 O A17EU 1E4 1998043001181 19980430 01181 EA 1998 4 30 AU960432 2 19960330 G 7322 C15159 CARBURETOR FACET MABA CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA ENGINE CONTAMINATED W K NONE E VIBRATION/BUFFET DE DESCENT 1 AU S C15159 L1675415 (AUS) CARBURETTOR BOWL AND VENTURI CONTAMINATED - FLOAT MOUNTING SHAFT SLIGHTLY WORN 1 H 7 1 3O 3 O NT 3A19 E223 1998043001182 19980430 01182 SW 1998 4 30 AU960433 1 19960328 G 6310 B121892 BEARING 0476204859 BELL 47 47G3B 1181026 SW ENG/TRANS CPLNG UNDERSIZE W K NONE O OTHER IN INSP/MAINT 1 AU S B121892 (AUS) MAIN ROTOR TRANSMISSION DRIVE FLANGE SHEAR SCREWS DISTORTED - SUSPECT DUE TO SLIPPAGE OF THE FREEWHEEL UNIT DUE T O FITMENT OF UNDERSIZE BEARING ROLLERS AND SUBSEQUENT SHOCK LOADING DURING RE-ENGAGEMENT - SEE ALSO MDR 96/0435 AND MDR 96/0341 1 G 7 1 3O 2H3 1996110100999 19961101 00999 EA 1996 11 1 AU960434 2 19960401 G 7322 CK13983 CARBURETTOR FACET MA4SPA CESSNA 172 172N 2072434 CE LYC O320 O320E2D 41508 EA ENG,FUEL CONTROL FAULTY W K NONE E VIBRATION/BUFFET DE DESCENT 1 AU S CK13983 L4388427A (AUS) CARBURETTOR FAULTY - SUSPECT TEMPORARY CONTAMINATION OR INTERMITTENT FAILURE COMBINED WITH NON FIRING OF NO4 CYLI NDERCAUSED ROUGH RUNNING ENGINE - CARBURETTOR ICING WAS DISMISSED AS THE CAUSE 1 H 7 1 3O 3 O NT 3A12 E274 1996110700139 19961107 00139 SW 1996 11 7 AU960435 1 19960328 G 6310 B121892 BEARING 0476206831 BELL 47 47G3B 1181026 SW LYC O435 TVO435D1A 41516 EA ENG/TRANS CPLNG UNDERSIZE W K NONE O OTHER IN INSP/MAINT 1 AU S 300 B121892 (AUS) MAIN ROTOR FREE WHEEL UNIT BEARING ROLLERS UNDERSIZE - SEE MDR 96/0433 FOR ADDITIONAL INFORMATION 1 G 7 1 3O 3 O 2H3 1E13 1996120300040 19961203 00040 1996 12 3 AU960436 1 19960402 G 7120 AN650A BOLT ENGINE MOUNTING BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE FRAME LOWER RH ATTACHMENT BOLT BROKEN - WHEN REMOVING THE REMAINING BOLTS FOR INSPECTION, IT WAS FOUND THAT THE TORQUE ONTHE LOWER LH LOCK NUT WAS BELOW STANDARD PRACTISES 1996110700140 19961107 00140 SW 1996 11 7 AU960437 1 19960402 G 3246 16210 WHEEL AIRPTS A A9A 0144204 SW LYC O540 O540B2B5 41532 EA LG WHEEL/BRAKE S BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MAIN WHEEL FLANGE FAILED AND BROKE AWAY DURING TYRE INFLATION - DYE PENETRANT CHECK HAD FOUND NO INDICATION OF CR ACKING - PIECEOF FLANGE BROKEN AWAY WAS APPROXIMATELY 100MM (4IN) - SUSPECT A CRACK APPROXIMATELY 76.2MM (3IN) LONG HAD EXISTED FOR SOME TIMEPRIOR TO FAILURE AS OXIDATION OF THE CENTRE SECTION OF THE BROKENFLANGE PORTION WAS PRESENT 1 L 7 1 3O 3 O A4WE E295 1996110700141 19961107 00141 SO 1996 11 7 AU960438 1 19960326 G 2740 62701047 CONTROL CABLE PIPER PA28 PA28161 7102803 SO LYC O320 O320D3G 41508 EA HORIZ STAB SYS FRAYED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) STABILATOR TRIM CABLE FRAYED AROUND TURN BARREL AT THE AIRCRAFT TAIL - THE CABLE WAS FRAYED FOR APPROXIMATELY A Q UARTER OF THE CABLE DIAMETER 1 L 7 1 3O 3 O 2A13 E274 1996110700142 19961107 00142 CE 1996 11 7 AU960439 1 19960407 G 5720 FITTING 71521 BBAVIA 8 8KCAB 2110612 CE LYC OUTER WING SYS WORN W K NONE O OTHER IN INSP/MAINT 1 AU S NSN (AUS) WING STRUT ATTACHMENT FITTINGS (4OFF) FOUND WITH CHAFE MARKS - ALSO TWO OF THE FITTINGS HAVE SEVERAL BOLT HOLES NO T DEBURRED -FOUND DURING INSPECTION IAW AD/CHA/25 AMDT 1 1 H 7 1 3O A21CE 1996110700143 19961107 00143 CE 1996 11 7 AU960440 1 19960401 G 2410 646655 DRIVE CONT ALTERNATOR CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO ALT-GEN DRIVE SY SEPARATED W K NONE H ELECT. POWER LOSS-50 PC CR CRUISE 1 AU S 447 B2189170 (AUS) LH ALTERNATOR DRIVE COUPLING RUBBER AND DRIVE CASING DEBONDED 1 L 7 2 3O 3 O A7CE E8CE 1996110700144 19961107 00144 NE 1996 11 7 AU960441 3 19960228 G 6110 70096 BEARING AIRTRC AT300 AT301 0390103 SW PWA R1340 R1340AN1 52016 NE HAMSTD 23D 23D40 NE PROPELLER ASSY S BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S N216907 (AUS) PROPELLER BLADE THRUST ROLLER BEARING PNO 70096 BROKEN INTO FIVE PIECES - THE OTHER BEARING WAS CRACKED, CORRODED AND HAD PIECESMISSING FROM THE ROLLER - INVESTIGATION FOUND MOISTURE HAD CAUSEDTHE BEARING TO RUST WHICH LED TO THE EVEN TUAL BEARING FAILURE -AIRCRAFT HAS A LOW UTILISATION RATE AND HAD BEEN ORIGINALLY FITTED TO AN OTTER SEAPLANE IN CANADA BEFORE BEING PURCHASED BYTHE PRESENT OWNER 1 L 7 1 3R 3 R A9SW 5E2 6 C P719 1996110700145 19961107 00145 GL 1996 11 7 AU960442 2 19960212 G 7260 23034601 OIL JET ALLSN 250C30 SNIAS 350 AS350B 8680801 EU ALLSN 250C 250C30 03013 GL T ENG AUX DRIVE UNAPPROVED PART W A K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S CAG95590 CAE895582 (AUS) DURING ENGINE INSPECTION FOLLOWING AN AIRCRAFT WIRE STRIKE, THE PINION OIL NOZZLE WAS FOUND TO BE THE INCORRECT PA RT NUMBER ITEM FOR THE TURBINE TO GEARBOX CONFIGURATION - THE TURBINE HAD BEEN MODIFIED IAW ALLISON 250C30 SBS 72-3158 A ND 72-3193 - THE OILNOZZLE SHOULD HAVE BEEN REPLACED AT THAT TIME WITH ITEM PNO 23035174 - PERSONNEL/MAINTENANCE ERROR - UNAPPROVED PART. 1 G 7 1 3U 3 U H9EU E1GL 1996110700146 19961107 00146 SO 1996 11 7 AU960443 2 19960308 G 8520 530182 CRANKSHAFT CESSNA 150 150G 2071816 CE CONT O200 O200A 17020 SO MCAULY 1A101 1A101DCM GL R ENGINE POWER S WORN W K NONE O OTHER IN INSP/MAINT 1 AU S 45 661037A (AUS) ENGINE SUFFERED TWO CRANKSHAFT MAIN BEARING EXCESSIVE WEAR INCIDENTS IN APPROXIMATELY 50 HOURS OPERATION: 1. FIRST OCCURRENCE WAS AT 8.5 HOURS AFTER INSTALLATION FOLLOWING OVERHAUL - ENGINE WAS INSPECTED/CHECKED, NEW BEARINGS AND A U SED SERVICEABLE CRANKSHAFT FITTED AND RETURNED TO SERVICE 2. SECOND OCCURRENCE, SHOWS IDENTICAL WEAR PATTERNS TO THE FI RST - METAL CONTAMINATION OF OIL SYSTEM - METAL WAS IDENTIFIED AS COMING FROM WORN CYLINDER BORES - BEARING SET PNO SA5 30058A6 WAS FITTED ON BOTH OCCASIONS 1 H 7 1 3O 3 O 3A19 E252 5 N P918 1996110700147 19961107 00147 CE 1996 11 7 AU960444 1 19960325 G 3211 1058100203 CONNECTOR BEECH 76 76 1153005 CE MAIN GEAR SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MAIN LANDING GEAR CONNECTOR PNO 105-810020.3 CRACKED ON THE INBOARD LUG ADJACENT TO THE CLEVIS PIN LOCATING HOLE - CAUSED BY CORROSION OF LOCATING ROLL PIN IN CONNECTOR 1 L 7 2 3O A29CE 1996120300041 19961203 00041 CE 1996 12 3 AU960445 1 19960322 G 7120 J96134950 MOUNT BEECH 1059100101 BEECH 76 76 1153005 CE ENGINE MOUNTING INCORRECT FIT W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S 0 (AUS) DURING REPLACEMENT OF THE ENGINE LORD MOUNTS THE FOLLOWING DEFECTS WERE FOUND:1. NO1 ENGINE MOUNTS WERE CORRECTLY ASSEMBLED BUT TRANSPOSED, PNO J9613-49 WAS INSTALLED IN THE PNO J9613-50 POSITION AND VICE VERSA 2. NO2 ENGINE LOWER M OUNTS DID NOT HAVE THE LARGER WASHERS (2IN BY 0.1175IN) POSITIONED BETWEEN THE ENGINE CRANKCASE ANDTHE BISCUIT MOUNT, C AUSING THE ENGINE TO ADOPT A NOSE DOWN ATTITUDE THE INBOARD LOWER MOUNT WAS FITTED WITH THE WASHER INCORRECTLY POSITIONE D UNDER THE BOLT HEADPERSONNEL/MAINTENANCE ERROR 1 L 7 2 3O A29CE 1996110700148 19961107 00148 WP 1996 11 7 AU960446 1 19960302 G 5320 591142917 TEE SECTION DOUG DC9 DC933F 302207A WP MAIN FRAME SYS CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUSELAGE SKIN BULGING AT L25 BETWEEN STN 1070 AND STN 1081 - WHENTHE SKIN WAS LIFTED BACK THE FOLLOWING CORROSION WAS FOUND:1. FILIFORM CORROSION ON FACE OF 'T' SECTION BETWEEN STN 1070 AND STN 10762. EXFOLIATION CORROSION ON ONE SIDE OF THE BACK FACE OF THE 'T'BETWEEN STN 1076 AND STN 1081 2 L 7 2 4F A6WE 1996110700149 19961107 00149 SO 1996 11 7 AU960447 2 19960315 G 8520 649163 CRANKCASE CESSNA 150 A150M 2071831 CE CONT O200 O200A 17020 SO R ENGINE POWER S DEFECTIVE W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S 772 25471450 25471450 (AUS) DURING RECIFICATION FOR A LEAKING PUSHROD TUBE AND REPLACEMENT OF NO1 CYLINDER, A LOWER CRANKCASE THROUGH STUD PUL LED OUT - THE CRANK CASE WAS SPLIT AND IT WAS THEN FOUND THE FRONT BEARING HOUSING WAS 0.0010IN OUT OF ROUND AND THE MID DLE HOUSING WAS +0.0005IN ON ONE SIDE AND -0.005IN ON THE OTHER - PERSONNEL/MAINTENANCE ERROR 1 H 7 1 3O 3 O 3A19 E252 1996120300042 19961203 00042 NM 1996 12 3 AU960448 1 19960320 G 7120 BOLT BOEING 747 747312 1384932 NM ENGINE MOUNTING WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NO2 ENGINE UPPER AFT MOUNT FITTING BOLTS AND BUSHES WORN - APPROXIMATE AMOUNT OF VERTICAL MOVEMENT WAS 0.060IN DUR ING INVESTIGATION THE FOLLOWING OTHER PROBLEMS WERE FOUND: 1. BOTH AFT FITTING ATTACHMENT BOLTS PNO 65B90383-2 WERE EXC ESSIVELY WORN AND STEPPED 2. BUSHINGS IN THE REAR ENGINE UPPER FITTING PNO 65B90356-35 (4 OFF) AND PNO 65B90356-36 (2 OFF) WERE WORN FOUND DURING INSPECTION AIW ER B747-71-20-4 FOLLOWING ENGINE REMOVAL 2 L 7 4 4F RT A20WE 1996110700150 19961107 00150 GL 1996 11 7 AU960449 3 19960404 G 6111 813827 BLADE MCAULY 3AF32C508 PIPER PA34 PA34220T 7103420 SO MCAULY 3AF32C 3AF32C508 GL PROPELLER ASSY S FOD TEAR W K NONE C F.O.D. TO TAKEOFF 1 AU S 346 813827 813827 (AUS) FOREIGN OBJECT IMPACTED WITH BLADE TIP CAUSING TEAR IN BLADE - SUSPECT FOD CAME FROM SURFACE OF AIRFIELD 1 L 7 2 3O A7SO 5 C P22EA 1996110700151 19961107 00151 SO 1996 11 7 AU960450 2 19960324 G 7310 627346 DIAPHRAGM CONT MANIFOLDVALV BEECH 36 A36 1151604 CE CONT O520 IO520BA 17032 SO ENG,FUEL DIST SY LEAKING W K NONE E R K VIBRATION/BUFFET PARTIAL RPM/PWR LOSS FLUID LOSS CR CRUISE 1 AU S 1448 I158114C 571950 (AUS) FUEL MANIFOLD VALVE DIAPHRAGM LEAKING AT THE SHAFT ASSEMBLY 1 L 7 1 3O 3 O 3A15 E5CE 1996110700152 19961107 00152 EU 1996 11 7 AU960451 1 19960225 G 3520 E0390DD01S2A12A CONNECTOR 01P2B12A AIRBUS 320 A320212 EU CREW&PASS OXY HIGH RESISTANCE W K NONE O OTHER IN INSP/MAINT 1 AU S 0 (AUS) DURING AN OPERATIONAL TEST OF THE MANUAL MASK RELEASE FOR PASSENGER OXYGEN, A NUMBER OF MASK PANELS FAILED TO REL EASE -INVESTIGATION FOUND THAT CONNECTOR 2773VC AT STN 925 HAD A HIGH RESISTANCE CAUSING A FLOATING VOLTAGE 2 L 7 2 4F RT A28NM 1996110700153 19961107 00153 SO 1996 11 7 AU960452 1 19960404 G 3211 9529902 STUD PIPER PA34 PA34200 7103405 SO LYC O360 IO360C1E6 41514 EA MAIN GEAR SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MAIN LANDING GEAR SIDE BRACE STUD CRACKED - FOUND DURING MAGNETIC PARTICLE INSPECTION (MPI) IAW AD/PA34/46 1 L 7 2 3O 3 O A7SO 1E10 1996110700154 19961107 00154 SO 1996 11 7 AU960453 1 19960404 G 5741 9010443 BOLT GULSTM AA5 AA5A 3960106 SO LYC O320 O320E2G 41508 EA ATTACH FITTING S CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) WING SHOULDER BOLTS (2OFF) CRACKED - FOUND DURING MAGNETIC PARTICLE INSPECTION (MPI) 1 L 7 1 3O 3 O A16EA E274 1996110700155 19961107 00155 GL 1996 11 7 AU960454 3 19960327 G 6110 CYLINDER HARTZL HC92Z HC92ZK8 GL PROPELLER ASSY S WRONG PART W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S 1201L (AUS) DURING PROPELLER OVERHAUL IT WAS FOUND THAT AN INCORRECT CYLINDER ASSEMBLY HAD BEEN FITTED NON-STANDARD SPACERS HA D ALSO BEEN FITTED IN ORDER TO CHANGE THE EFFECTIVE LENGTH OF THE PITCH CONTROL RODS - UNAPPROVED PART - PERSONNEL/MAIN TENANCE ERROR 5 C P892 1996110700156 19961107 00156 SO 1996 11 7 AU960455 1 19960409 G 2750 MICROSWITCH PIPER PA31 PA31350 7103110 SO HARTZL HCE3Y HCE3YR2 GL FLAP SYS FAULTY W K NONE F FLT CONT AFFECTED IN INSP/MAINT 1 AU S (AUS) FLAPS JAMMED IN THE 'UP' POSITION DUE TO THE INTERMITTENT OPERATION OF THE 'UP' LIMIT MICROSWITCH - FLAP OVERTRAV EL BURNT OUT MOTOR ARMATURE 1 L 7 2 3O A20SO 5 C P33EA 1996110700157 19961107 00157 NM 1996 11 7 AU960457 1 19960321 G 3040 SYLZ50970 TEMP CONTROLLER DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE WINDOW AI/DE-ICE FAULTY W K NONE O OTHER CR CRUISE 1 AU S (AUS) WINDSHIELD HEATING TEMPERATURE CONTROLLER APPLIED FULL HEAT WHEN NORMAL SELECTED DUE TO SUSPECT DEFECTIVE WARMUP S ELECTION - THE'R WSHLD HOT' CAUTION WARNING LIGHT ILLUMINATED AND THE RH WINDSHIELD OUTER PANE CRACKED 2 H 7 2 4T 4 T RT A13NM E20NE 1996110700158 19961107 00158 NE 1996 11 7 AU960458 2 19960407 G 7250 TURBINE BLADE PWA 4056 PW4056 NE TURBINE SECTION FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S P724208 (AUS) NO1 ENGINE FIRST STAGE HPT MISSING APPROXIMATELY HALF A BLADE - FOUND DURING BORESCOPE INSPECTION 4 F E24NE 1996110700159 19961107 00159 GL 1996 11 7 AU960459 2 19960331 G 7421 CH31772A IGNITOR PLUG GE CF6 CF680C GL ENG,IGNITN DISTR WORN W K NONE E VIBRATION/BUFFET TO TAKEOFF 1 AU S (AUS) LH ENGINE 'A' AND 'B' SYSTEM IGNITION PLUGS WERE FOUND TO BE SEVERELY ERODED WITH EVIDENCE OF SPARK TRACKING THROU GH A CRACKIN THE CERAMIC INSULATOR OF THE 'B' SYSTEM PLUG 4 F E23EA 1996110700160 19961107 00160 CE 1996 11 7 AU960460 1 19960404 G 3297 WIRE BEECH 1900 1900D 1154162 CE LG POSITION IND BROKEN W K NONE N FALSE WARNING LD LANDING 1 AU S (AUS) NLG INDICATION SYSTEM WIRE BROKEN ON LAMP HOUSING 2 L 7 2 4T RT A24CE 1996110700161 19961107 00161 NM 1996 11 7 AU960461 1 19960304 G 3233 NAS161133 O-RING 65449121 BOEING 737 737377 NM LG EXT-RETRACT S INCORRECT FIT W A K NONE W INADEQUATE Q C TO TAKEOFF 1 AU S 13946 TSC1583ANS (AUS) LH MLG RETRACTION ACTUATOR 'O' RING PACKING PNO NAS1611-33 ON PISTON PNO 65-44912-1 WAS FOUND SEPARATED AND FRACTU RED IN A NUMBER OF AREAS AND THE INNER FACE WAS BADLY DAMAGED - FURTHER INVESTIGATION FOUND THAT THE SEAL INSTALLATION W AS INCORRECT - THE DAMAGED PACKING HAD INCORRECT BACKUP RINGS - THESE RINGS WOULD NORMALLY ONLY BE USED WHEN USING G.T. SEAL PNO 7336M59521 -UNAPPROVED PART - PERSONNEL/MAINTENANCE ERROR. 2 L 7 2 4F RT A16WE 1996110700162 19961107 00162 EU 1996 11 7 AU960462 1 19960409 G 5350 36010A LATCH AEROSP SA365 SA365C 8680667 EU FAIRING SYS FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) DURING TURN AROUND INSPECTION, THE PILOT DISCOVERED THE LH MAIN GEARBOX FORWARD COWL HANDLE MISSING - THE ROLL PIN ATTACHING THE HANDLE TO THE CENTRE LOCKING SHAFT HAD SHEARED 1 G 7 2 3U H10EU 1996110700163 19961107 00163 EU 1996 11 7 AU960463 1 19960101 G 5753 SKIN FOKKER F27 F27MK600 4990706 EU RROYCE WING TE SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) STARBOARD OUTER FLAP SKIN CRACKED AT STN 340 - WHEN THE FLAP WAS DISMANTLED CRACKS WERE ALSO FOUND IN THE RIB - FO UND DURINGINSPECTION IAW SB F27-57-67 - AIRCRAFT HAS BEEN PARKED IN THE OPEN AT BRISBANE AIRPORT FOR APPROXIMATELY 6 YE ARS 2 H 7 2 4T A817 1996110700164 19961107 00164 WP 1996 11 7 AU960464 1 19960208 G 6230 269A530511 DRIVE SHAFT HUGHES 269 269C 4470504 WP LYC O360 HIO360D1A 41514 EA M/R MAST/SWASHPL RUSTED W K NONE O OTHER IN INSP/MAINT 1 AU S 618270 (AUS) MAIN ROTOR DRIVE SHAFT (MAST) BORE BADLY RUSTED 1 G 7 1 3O 3 O 4H12 1E10 1996110700165 19961107 00165 SW 1996 11 7 AU960465 1 19960314 G 8010 H2211 SWITCH SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE33111U 01514 WP ENGINE CRANKING FAULTY W A K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH ENGINE BEGAN TO ROTATE RAPIDLY WHEN AIRCRAFT BATTERY SWITCHES SELECTED ON - SUSPECT INTERNAL SHORT ACROSS THE S TARTER SWITCH CONTACTS CAUSED CONTACTS TO STICK 2 L 7 2 4T 4 T RT A8SW E4WE 1996110700166 19961107 00166 SW 1996 11 7 AU960466 1 19960331 G 2930 SS10127 PRESSURE SWITCH FRCHLD SA227 SA227DC 3377521 SW GARRTT HYD IND SYS FAILED W K NONE K N FLUID LOSS FALSE WARNING CR CRUISE 1 AU S (AUS) LH HYDRAULIC PRESSURE SWITCH FAILED - HYDRAULIC PRESSURE ON GAUGE READING NORMAL AT 1850 PSI 2 L 7 2 4T RT A18SW 1996110700167 19961107 00167 1996 11 7 AU960467 4 19960404 G 2312 RADIO SYSTEM BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA VHF COMMUNICATIO FAULTY W K NONE O OTHER CL CLIMB 1 AU S (AUS) RADIO SYSTEM JAMMED IN TRANSMIT MODE ON THREE OCCASIONS - ON LANDING, AFTER EACH FAILURE THE SYSTEM OPERATED NOR MALLY 1 L 7 2 4T 4 T A24CE E4EA 1996110700168 19961107 00168 CE 1996 11 7 AU960468 1 19960411 G 2612 302158 FIRE DETECTOR BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA FIRE DET SYS FAULTY W K NONE N FALSE WARNING CR CRUISE 1 AU S (AUS) RH ENGINE FIRE WARNING ILLUMINATED - ON LANDING THERE WAS NO EVIDENCE OF FIRE - FIRE WARNING SENSORS REPLACED BY A NEW TYPE PNO 473275 1 L 7 2 4T 4 T A24CE E4EA 1996110700169 19961107 00169 EA 1996 11 7 AU960469 2 19960411 G 7414 LW18378 CLAMP CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA ELEC PWR SUPPLY FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S L49576T (AUS) DUAL MAGNETO RETAINING CLAMP ALLOWED MAGNETO TO ROTATE ON THE MOUNTING 1 H 7 1 3O 3 O NT 3A12 E274 1996110700170 19961107 00170 EU 1996 11 7 AU960470 1 19960315 G 2610 WIRE BAC 146 146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE FIRE DETECTION S WORN W A K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) DURING MAINTENANCE UNDER NO2 PYLON (ENGINE REMOVED), A NUMBER OF FIRE/OVERHEAT DETECTOR WIRES WERE FOUND CHAFED WH ERE THEY ENTER THE SUPPORT SLEEVE OF THE LEADING EDGE PYLON FIRESEAL 'F' - THE OTHER THREE PYLONS WERE INSPECTED AND TW O HAD SIMILAR CHAFING -THE MAJORITY OF WIRES WERE CHAFED MORE THAT 50% THROUGH THE CONDUCTORS - FOUND DURING A SCHEDULE D 4C CHECK 2 H 7 4 4F 4 F A49EU E6NE 1996110700171 19961107 00171 SO 1996 11 7 AU960471 1 19960411 G 5753 6232002 RIB 2232002 PIPER PA28 PA28235 7102810 SO LYC O540 O540B4B5 41532 EA WING TE SYS CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RH WING FLAP HAS EXTENSIVE CORROSION BETWEEN THE STEEL ATTACHMENT BRACKETS AND THE INTERNAL NOSE RIBS - ALL RIBS H AD PARTED FROM THE ATTACHMENT BRACKETS - THE TRAILING SKIN RIB SITUATED UNDER AND ON THE OUTER END OF THE STRENGTHENED W ALKWAY PORTION OF THE FLAP HAD CORRODED AWAY TO VIRTUALLY NOTHING - AIRCRAFT IS OF 1963VINTAGE WITH ONLY 2100 HOURS TTIS - NO CORROSION PROTECTION WAS APPLIED DURING MANUFACTURE 1 L 7 1 3O 3 O 2A13 E295 1996110700172 19961107 00172 SO 1996 11 7 AU960472 1 19960411 G 5753 6232000 RIB PIPER PA28 PA28235 7102810 SO LYC O540 O540B4B5 41532 EA HARTZL HCC2Y HCC2YK1 GL WING TE SYS CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH WING FLAP HAS EXTENSIVE CORROSION MAINLY BETWEEN THE STEEL ATTACHMENT BRACKETS AND INTERNAL NOSE RIBS - ALL OF WHICH HADDEPARTED FROM THEIR ATTACHING SURFACES DUE TO THE CORROSION - SEEMDR 96/0471 FOR FURTHER INFORMATION 1 L 7 1 3O 3 O 2A13 E295 5 C P920 1996110700173 19961107 00173 SO 1996 11 7 AU960473 1 19960403 G 3246 300608 WHEEL EMB 110 EMB110P1 3260122 SO LG WHEEL/BRAKE S FAILED W K NONE O OTHER TX TAXI/GRND HDL 1 AU S (AUS) LH MAIN WHEEL TYRE RETAINING BEAD HAD SEPARATED FROM THE INNER WHEEL HALF 1 L 7 2 4T A21SO 1996110700174 19961107 00174 EU 1996 11 7 AU960474 1 19960229 G 3213 5321012180 SHOCK ABSORBER PILATS PC12 PC12 7090550 EU MAIN GEAR SYS FAULTY W K NONE K FLUID LOSS TO TAKEOFF 1 AU S (AUS) RH MAIN LANDING GEAR STRUT STAGE 1 AND 2 PRESSURES BOTH FOUND TO BE 1000 PSI - UNABLE TO SERVICE SHOCK ABSORBER - SUSPECT ANINTERNAL FAILURE 1 L 7 1 3T RT A78EU 1996110700175 19961107 00175 CE 1996 11 7 AU960475 1 19960404 G 5312 0513006103 BULKHEAD CESSNA 172 172 2072402 CE MAIN FRAME SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH AND RH DOOR POST BULKHEADS AND PLATES CRACKED BETWEEN NOTCH AND VACANT BOLT HOLE 1 H 7 1 3O NT 3A12 1996110700176 19961107 00176 CE 1996 11 7 AU960476 1 19960410 G 5312 BULKHEAD CESSNA 182 R182 2072734 CE LYC O540 O540J3C5 41532 EA MAIN FRAME SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FORWARD DOOR POST BULKHEAD CRACKED ON BOTH SIDES - FOUND DURING INSPECTION IAW AD/C180/75 AMDT 1 1 H 7 1 3O 3 O RT 3A13 E295 1996110700177 19961107 00177 SO 1996 11 7 AU960477 1 19960409 G 3250 31812 COLLAR PIPER PA23 PA23250 7102308 SO ACFT STEERING SY CRACKED W K NONE O OTHER LD LANDING 1 AU S (AUS) NOSE LANDING GEAR STEERING COLLAR FRACTURED AT THE LH ATTACHMENT LUG - SUSPECT DAMAGE CAUSED BY EXCEEDING STEERING LIMITS DURING GROUND HANDLING 1 L 7 2 3O 1A10 1996120300043 19961203 00043 EA 1996 12 3 AU960478 1 19960330 G 2842 39108703082 SENSOR DHAV DHC6 DHC6300 EA PWA PT6 PT6A27 52043 EA FUEL INDICATION BLOCKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) AFT FUEL QUANTITY INDICATOR OVERREADING BY 125LBS IN THE LOWER END RANGE - INVESTIGATION FOUND NO5 FUEL CELL (COLL ECTOR TANK) FUEL QUANTITY CAPACITANCE PROBE LOWER DRAIN HOLE BLOCKED WITH FOREIGN MATERIAL 1 H 7 2 3T 4 T A9EA E4EA 1996110700178 19961107 00178 SO 1996 11 7 AU960479 2 19960325 G 8520 642396 CRANKSHAFT CONT IO520M CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO R ENGINE POWER S BROKEN W O OTHER E VIBRATION/BUFFET CR CRUISE 1 AU S 565246 565246 (AUS) ENGINE CRANKSHAFT BROKEN AT NO9 CHEEK 1 L 7 2 3O 3 O 3A10 E5CE 1996110700179 19961107 00179 CE 1996 11 7 AU960480 1 19960415 G 5711 35410217 SPAR BEECH 35 V35A 1151544 CE CONT O520 IO520B 17032 SO MAIN FRAME SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUSELAGE FRONT SPAR CARRY THROUGH SECTION CRACKED AT BOTH OUTBOARD SIDES 1 L 7 1 3O 3 O 3A15 E5CE 1996110700180 19961107 00180 CE 1996 11 7 AU960481 1 19960212 G 5711 3511006178 SPAR CAP BEECH 35 V35 1151538 CE CONT O520 IO520B 17032 SO OUTER WING SYS CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RH WING LOWER SPAR CAP CORRODED 1 L 7 1 3O 3 O 3A15 E5CE 1996110700181 19961107 00181 CE 1996 11 7 AU960482 1 19960415 G 2820 F123660156 HOSE F123660144 CESSNA 182 R182 2072734 CE LYC O540 O540J3C5 41532 EA FUEL DISTRBUTION LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S (AUS) FUEL HOSE LEAKING BETWEEN FITTING AND HOSE - FOUND DURING INSPECTION IAW AD/HOSE/3 AMDT5 1 H 7 1 3O 3 O RT 3A13 E295 1996121900097 19961219 00097 NM 1996 12 19 AU960483 1 19960410 G 2912 271T00703 FILTER BOWL BOEING 767 767338 NM MAIN HYD SYS SEPARATED W K NONE K FLUID LOSS LD LANDING 1 AU S (AUS) AIRCRAFT LANDED WITH CENTRE HYDRAULIC SYSTEM LOW PRESSURE AND QUANTITY - INVESTIGATION FOUND THE ADP (AIR DRIVEN PUMP) PRESSURE FILTER BOWL SEPARATED FROM THE MODULE DUE TO FATIGUE CRACKING IN THE LAST THREAD OF THE BOWL - TOTAL LOSS OF HYDRAULIC FLUID 2 L 7 2 4F RT A1NM 1996121900098 19961219 00098 NM 1996 12 19 AU960484 1 19960403 G 5754 SKIN BOEING 767 767338 NM WING LE FLAP DELAMINATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NO6 LE FLAP TRAILING UPPER SKIN HAS EXCESSIVE DELAMINATION 2 L 7 2 4F RT A1NM 1996110700182 19961107 00182 CE 1996 11 7 AU960485 1 19960416 G 2910 571702214 PIPE CESSNA 441 441 2076020 CE MAIN HYD SYS CRACKED W K NONE J K WARNING INDICATION FLUID LOSS LD LANDING 1 AU S (AUS) HYDRAULIC PRESSURE PIPE BETWEEN PUMP AND HYDRAULIC POWER PACK CRACKED AT BEND 1 L 7 2 3T RT A28CE 1996110700183 19961107 00183 CE 1996 11 7 AU960486 1 19960416 G 2820 510011084 PIPE CESSNA 421 421C 2076016 CE CONT O520 GTSIO520N 17032 SO FUEL DISTRBUTION CORRODED W K NONE O K OTHER FLUID LOSS IN INSP/MAINT 1 AU S (AUS) LH NACELLE FUEL TANK TRANSFER PUMP TO 'T' FITTING PIPE LEAKING FUEL FROM PIN HOLE DUE TO INTERNAL CORROSION 1 L 7 2 3O 3 O A7CE E7CE 1996110700184 19961107 00184 EA 1996 11 7 AU960487 2 19960418 G 7414 10349271 COIL BENDIX S6LN1208 BEECH 60 A60 1153604 CE LYC O541 TIO541E1C4 41536 EA ELEC PWR SUPPLY CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 742 A65367 L89959 (AUS) RH ENGINE LH MAGNETO 'CLEAR CASE' COIL DETERIORATED AND CASE SEVERLY CRACKED - FOUND DURING INSPECTION IAW AD/ELEC T/66 AMDT 1 - AIRCRAFT WAS PREVIOUSLY REGISTERED AS VH-EZT 1 L 7 2 3O 3 O A12CE E10EA 1996110700185 19961107 00185 CE 1996 11 7 AU960488 1 19960418 G 2810 CAP CESSNA 182 182H 2072718 CE CONT O470 O470R 17026 SO FUEL STORAGE SYS LEAKING W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUEL TANK CAPS LEAKING - REPLACED BY TYPE PNO SK182-8513 - FOUND DURING INSPECTION IAW AD/CESSNA180/70 AMDT 1 1 H 7 1 3O 3 O NT 3A13 E273 1996111400001 19961114 00001 CE 1996 11 14 AU960489 1 19960418 G 2161 7468331 SWITCH CESSNA 441 441 2076020 CE CABIN TEMP. CONT FAULTY W K NONE N FALSE WARNING NR NOT REPORTED 1 AU S PNHS738443 (AUS) PRESSURISATION SYSTEM AIRCYCLE MACHINE OVERTEMPERATURE SWITCH FAULTY GIVING FALSE ACM OVERTEMPERATURE INDICATION, CAUSINGCONSEQUENT CABIN PRESSURE FAILURE AND EMERGENCY PRESSURISATION ACTUATION 1 L 7 2 3T RT A28CE 1996111400002 19961114 00002 WP 1996 11 14 AU960490 1 19960321 G 5311 FRAME DOUG DC3 DC3CS1C3G 3021458 WP ATTACH FITTING S CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) SEVERE EXFOLIATION CORROSION FOUND IN THE FOLLOWING LOCATIONS: 1. TAIL SECTION FRAME STN 703 AT THE TWO ATTACHING BOLT LOCATION WITH AREA OF CORROSION COVERING APPROXIMATELY FOUR (4) SQUARE INCHES AT EACH LOCATION - DEPTH OF CORROSIO N HAD PENETRATED RIGHT THROUGH THE FRAME 2. LH ENGINE NACELLE AT STN 174 TO STN 200 STRINGERS 2 L 7 2 4R A669 1996111400003 19961114 00003 CE 1996 11 14 AU960491 1 19960416 G 5720 316321 FITTING 316322 BBAVIA 8 8KCAB 2110612 CE LYC O320 AEIO320E2B 41508 EA OUTER WING SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) BOTH FORWARD WING STRUT FITTINGS PNO 3-1362-1 AND PNO 3-1632-2 CRACKED - ALL FOUR FORWARD AND REAR FITTING PIECES CRACKED - FOUND DURING DYE PENETRANT INSPECTION 1 H 7 1 3O 3 O A21CE 1E12 1996111400004 19961114 00004 CE 1996 11 14 AU960492 1 19960415 G 5551 1231325KAO FITTING CESSNA 206 U206G 2073356 CE LYC O540 TIO540F2BD 41532 EA HORZ STAB SYS LOOSE W K NONE O OTHER IN INSP/MAINT 1 AU S 567898 (AUS) HORIZONTAL STABILISER WAS REMOVED DUE TO EXCESSIVE MOVEMENT - INVESTIGATION FOUND THAT EACH OF THE TWO FORWARD AT TACHMENT FITTINGS HAD FOUR OF THE FIVE RIVETS SHEARED - SUSPECT INCORRECT GROUND HANDLING TECHNIQUE 1 H 7 1 3O 3 O A4CE E14EA 1996111400005 19961114 00005 SO 1996 11 14 AU960493 1 19960325 G 2822 751799 FILTER PIPER PA34 PA34200T 7103406 SO FUEL XSFER PUMP MISSING W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RH NACELLE TANK ELECTRIC TRANSFER PUMP FILTER ELEMENT PNO 751-799MISSING - PERSONNEL/MAINTENANCE ERROR 1 L 7 2 3O A7SO 1996111400006 19961114 00006 SO 1996 11 14 AU960494 1 19960325 G 5553 6244404 FITTING PIPER PA34 PA34200T 7103406 SO VERT STAB STRUCT CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) VERTICAL STABILISER FORWARD SPAR ATTACHMENT FITTING CORRODED AT FRAME STN 259.31 1 L 7 2 3O A7SO 1996111400007 19961114 00007 SO 1996 11 14 AU960495 1 19960325 G 5541 9620900 RIB PIPER PA34200T PIPER PA34 PA34200T 7103406 SO RUDDER STRUCT SY CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RUDDER LOWER RIB CORRODED IN AREA OF STEEL TORQUE TUBE ASSEMBLY DUE TO DISSIMILAR METAL CONTACT 1 L 7 2 3O A7SO 1996111400008 19961114 00008 SO 1996 11 14 AU960496 1 19960325 G 3211 6704013 FITTING PIPER PA34 PA34200T 7103406 SO MAIN GEAR SYS LOOSE W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) RH MLG FORWARD TRUNNION FITTING LOOSE - 3 OF 4 ATTACHMENT BOLTS LOOSE AND OTHER BOLT MISSING - ATTACHMENT BOLT HO LES ELONGATED DUE TO MOVEMENT OF FITTING - FITTING WAS ATTACHED BY NAS TYPE BOLTS INSTEAD OF WITH THE CORRECT AN TYPE A S PER THE IPC - UNAPPROVED PART - PERSONNEL/MAINTENANCE ERROR 1 L 7 2 3O A7SO 1996111400009 19961114 00009 CE 1996 11 14 AU960497 1 19960418 G 5341 EB126 NUT BEECH 33 F33A 1151425 CE ATTACH FITTING S CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) WING ATTACHMENT BOLT NUT CRACKED - FOUND DURING MAGNETIC PARTICLE INSPECTION IAW AD/BEECH33/41 - AIRCRAFT IS FOREI GN REGISTERED N93RS 1 L 7 1 3O 3A15 1996111400010 19961114 00010 CE 1996 11 14 AU960498 1 19960419 G 2110 2322A2 HOSE CESSNA 208 208B 2073701 CE CABIN COMPRESSOR SEPARATED W K NONE O OTHER CL CLIMB 1 AU S (AUS) AIRCONDITIONING SYSTEM COMPRESSOR DISCHARGE SERVICE VALVE HOSE 'BLEW OFF' ELBOW FITTING CAUSING LOSS OF FREON AND COMPRESSOR OIL- DISCHARGE PIPE IS CLAMPED TO THE DISCHARGE SERVICE VALVE 1 H 7 1 3T A37CE 1996111400011 19961114 00011 SO 1996 11 14 AU960499 1 19960411 G 8011 ESEBB75A DRIVE UNIT PRESTOLITE NO1724206 PIPER PA30 PA30 7103002 SO LYC O320 IO320C1A 41508 EA ENGINE CRANKING MALFUNCTIONED W K NONE O OTHER NR NOT REPORTED 1 AU S IF000589 (AUS) ENGINE STARTER MOTOR DRIVE LOCKED IN THE ENGAGED POSITION 1 L 7 2 3O 3 O A1EA 1E12 1996111400012 19961114 00012 EU 1996 11 14 AU960500 1 19960416 G 7170 0174078010 DRAIN VALVE SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1B 6OO30 NE ENG FLUID DRAIN/ INCORRECT ASSY W K NONE W K INADEQUATE Q C FLUID LOSS IN INSP/MAINT 1 AU S 0174078010 585 (AUS) ENGINE STARTER DRAIN VALVE LEAKING FUEL AT BODY SPLIT LINE - CAUSED BY INCORRECT ASSEMBLY AT OVERHAUL - PERSONNEL/ MAINTENANCE ERROR 1 G 7 1 3U 3 U H9EU E19EU 1996111400013 19961114 00013 EU 1996 11 14 AU960501 1 19960310 G 5340 FITTING SOCATA TB10 TB10TOBAGO 8680696 EU LYC O360 O360A1A 41514 EA ATTACH FITTING S DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH FRONT WING ATTACHMENT FITTING AT FUSELAGE DAMAGED - FUSELAGE PANELS LH AND RH SIDE ABOVE MAIN SPARS DISTORTED 1 L 7 1 30 3 O NT A51EU E286 1997010200025 19970102 00025 EU 1997 1 2 AU960502 1 19960412 G 2120 DUCT BAG JETSTM JETSTM3107 1500215 EU AIR DISTRIBUTION BLEW OUT W K NONE O OTHER CL CLIMB 1 AU S (AUS) PRESSURISATION SYSTEM LH AIR CYCLE MACHINE (ACM) SUPPLY DUCT SPLIT AND BLEW OFF - RH FLOW CONTROL VALVE WAS REPLAC ED DUE TO INADEQUATE AIR SUPPLY FLOW TO MAINTAIN PRESSURISATION 2 L 7 2 4T RT BA15CAA 1996111400014 19961114 00014 SO 1996 11 14 AU960503 2 19960416 G 8530 EXHAUST VALVE CESSNA 310 310J 2074226 CE CONT O470 IO470V 17026 SO R ENGINE CYL SEC LEAKING W K NONE O OTHER IN INSP/MAINT 1 AU S 147669 (AUS) ENGINE COMPRESSION LEAKAGE FROM EXHAUST VALVES ON ALL 6 CYLINDERS- FOUND DURING COMPRESSION CHECK IAW AD/ENG/4 AMD T 5 - ENGINECALENDER TIME SINCE OVERHAUL WAS 19 YEARS 1 L 7 2 3O 3 O 3A10 3E1 1996111400015 19961114 00015 EA 1996 11 14 AU960504 2 19960417 G 7414 10682054 DISTRIBUTOR BENDIX DARN2021 CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA ELEC PWR SUPPLY DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S 348 5026468R (AUS) MAGNETO RH SIDE DISTRIBUTOR GEAR BUSHING LOOSE CAUSING DAMAGE TO THE GEAR SHAFT - MAGNETO CAPACITOR OPEN CIRCUITED 1 H 7 1 3O 3 O NT 3A12 E274 1996111400016 19961114 00016 CE 1996 11 14 AU960505 1 19960419 G 5720 3163212 FITTING 316322 BBAVIA 8 8KCAB 2110612 CE LYC O360 AEIO360H1A 41514 EA OUTER WING SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 75295LAND (AUS) WING STRUT FITTINGS (4OFF) PNO 3-1632-1 AND PNO 3-1632-2 CRACKED IN THE CORNER OF THE RECTANGULAR HOLLOW SECTIONS - FOUND DURINGINSPECTION IAW AD/CHA/25 AND SL408 - AIRCRAFT HAS ONLY 103 HOURS TIME SINCE NEW WITH 20 HOURS OF AEROBATIC TIME 1 H 7 1 3O 3 O A21CE 1E10 1996111400017 19961114 00017 CE 1996 11 14 AU960506 1 19960423 G 7120 630694 BRACKET 630695 BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO ENGINE MOUNTING BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S 172700R (AUS) LH ENGINE LOWER MOUNT BRACKETS PNO 630694 AND PNO 630695 BROKEN 1 L 7 2 3O 3 O 3A16 E5CE 1996111400018 19961114 00018 CE 1996 11 14 AU960507 1 19960404 G 5312 BULKHEAD CESSNA 182 182P 2075816 CE MAIN FRAME SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FORWARD DOOR BULKHEAD CRACKED 1 H 7 1 3O NT TA13 1996111400019 19961114 00019 NM 1996 11 14 AU960508 1 19960411 G 2920 BACR13CG2A RELAY BOEING 767 767238 NM AUX HYD SYS FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RAM AIR TURBINE (RAT) FAILED TO DEPLOY DURING TEST DUE TO FAILUREOF THE AIR/GROUND SYSTEM 2 RELAY K213 2 L 7 2 4F RT A1NM 1996111400020 19961114 00020 WP 1996 11 14 AU960509 2 19960315 G 7210 GEAR GARRTT TPE331 TPE33110U 01514 WP ENGINE REDUCTION PITTED W K NONE C F.O.D. CL CLIMB 1 AU S P42106 (AUS) ENGINE SUFFERED A LIGHTNING STRIKE - DOME REMOVED AND GEARING FOUND TO BE PITTED 4 T E4WE 1996111400021 19961114 00021 NE 1996 11 14 AU960510 2 19960415 G 7261 OIL SYSTEM PWA PWA120 PW125B NE TURBINE ENGINE O CONTAM-METAL W K NONE O OTHER IN INSP/MAINT 1 AU S TM124027 (AUS) ENGINE OIL FILTER CONTAMINATED WITH METAL 4 T E20NE 1996111400022 19961114 00022 EU 1996 11 14 AU960511 1 19960418 G 2910 F8553048401 HOSE FOKKER F27 F27MK50 EU MAIN HYD SYS FAILED W K NONE O K OTHER FLUID LOSS DE DESCENT 1 AU S (AUS) HYDRAULIC HOSE IN LH WHEEL WELL RUPTURED - LOSS OF HYDRAULIC FLUID CAUSED ENGINE DRIVEN HYDRAULIC PUMP TO RUN DRY AND FAIL -SUSPECT HOSE FAILURE CAUSED BY INTERFERENCE WITH THE MLG LOCK LINK DURING THE RETRACTION CYCLE - HOSE IS OF T EFLON CONSTRUCTIONWITH METAL BRAIDED REINFORCEMENT WITH A WORKING PRESSURE OF 3500PSI 2 H 7 2 4T RT A817 1996111400023 19961114 00023 SO 1996 11 14 AU960512 2 19960402 G 8530 643767P005 VALVE GUIDE CONT O470R CESSNA 182 182H 2072718 CE CONT O470 O470R 17026 SO R ENGINE CYLINDE WORN W K NONE O OTHER IN INSP/MAINT 1 AU S 1317665P 1317665P (AUS) NO1 CYLINDER EXHAUST VALVE GUIDE AND VALVE STEM WORN AND LEAKING - VALVE GUIDE AND VALVE ARE ONLY 70 HOURS TSN 1 H 7 1 3O 3 O NT 3A13 E273 1996111400024 19961114 00024 EU 1996 11 14 AU960513 1 19960411 G 5610 NF20216402 WINDSHIELD BAC 146 146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE FLT CMPT WINDOW DELAMINATED W K NONE O OTHER CR CRUISE 1 AU S 235789 (AUS) RH `B' WINDSCREEN OUTER PANE DELAMINATED AND A LARGE SECTION SEPARATED 2 H 7 4 4F 4 F A49EU E6NE 1996111400025 19961114 00025 EA 1996 11 14 AU960515 2 19960126 G 7310 LW120980200 PIPE ENSTRM F28 280C 3300505 GL LYC O360 HIO360E1AD 41514 EA ENG,FUEL DIST SY WRONG PART W K NONE W INADEQUATE Q C CR CRUISE 1 AU S 133 L1723151A (AUS) NO1 CYLINDER EXHAUST VALVE SEAT DROPPED CONTACTING THE PISTON AND CAUSING CYLINDER FAILURE - ENGINE WAS BULK STRI PPED AND INVESTIGATION OF NO1 CYLINDER ASSEMBLY FOUND: 1. EXTERNAL SIGNS OF OVERHEATING 2. FUEL INJECTION PIPE FLOW 7PP H - NORMAL IS 30PPH - FURTHERINVESTIGATION FOUND THE OUTSIDE DIAMETER OF THE PIPE WAS 0.124IN COMPARED TO THE OTHER CYLI NDER PIPE DIAMETERS OF 0.128IN. ENGINE WAS OVERHAULED IN CANADA - SUSPECT WRONG PIPE FITTED CAUSING LOWER FUEL FLOW RE SULTING IN CYLINDER OVERHEAT - UNAPPROVED PART - PERSONNEL/MAINTENANCE ERROR 1 G 7 1 3O 3 O H1CE 1E10 1996111400026 19961114 00026 SO 1996 11 14 AU960516 1 19960412 G 2740 26701111 CONTROL CABLE PIPER PA28 PA28R201 7102816 SO LYC O360 IO360C1C6 41514 EA HORIZ STAB SYS BROKEN W O OTHER F FLT CONT AFFECTED CR CRUISE 1 AU S (AUS) HORIZONTAL STABILISER TRIM CABLE BROKEN IN AREA WHERE CABLE PASSES THROUGH THE SERVO TRIM PULLEYS AND CAPSTAN 1 L 7 1 3O 3 O 2A13 1E10 1996111400027 19961114 00027 EU 1996 11 14 AU960517 2 19960307 G 7310 9375M18G01 MANIFOLD CFMINT CFM56 CFM563C1 13802 EU ENG,FUEL DIST SY CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 721762 (AUS) ENGINE FUEL MANIFOLD 'Y' TUBE CRACKED - CRACK LENGTH 19.05MM (0.75IN) - FOUND DURING FLUORESCENT PENETRANT INSPECT ION 4 F E21EU 1996111400028 19961114 00028 NM 1996 11 14 AU960518 1 19960415 G 4930 36080004 FCU BOEING 737 737376 NM APU POWER PLANT FAULTY W K NONE O OTHER CR CRUISE 1 AU S 453 (AUS) APU SHUTDOWN DUE TO FLUCTUATING EGT, FREQUENCY AND VOLTAGE - SUSPECT FAULTY FCU 2 L 7 2 4F RT A16WE 1996111400029 19961114 00029 EU 1996 11 14 AU960519 1 19960417 G 3241 322 INDICATOR AIRBUS 300 A300B4203 3930306 EU LG WHEEL/BRAKE S FAULTY W K NONE O OTHER LD LANDING 1 AU S 322 (AUS) BRAKING SYSTEM ANTI-SKID INDICATOR/TEST PANEL FAULTY DUE TO SUSPECTED SHORTING TEST SWITCH - AUTO-BRAKE SYSTEM WO ULD NOT OPERATE 2 L 7 2 4F A35EU 1996111400030 19961114 00030 EU 1996 11 14 AU960520 1 19960406 G 4990 O-RING GTCP36150M BAC 146 146300A 1500267 EU LYC ALF502 ALF502R5 41580 NE APU OIL SYS FAILED W K NONE B K SMOKE/FUMES/ODORS/SPARKS FLUID LOSS TO TAKEOFF 1 AU S P210UC (AUS) APU ENGINE OIL SYSTEM QUANTITY LOW - SMOKE OBSERVED FROM EXHAUST - GENERATOR DRIVE CARBON SEAL LEAKING - MAIN CAUS E OF OIL LOSS ISCONSIDERED TO BE A FAILED `O' RING SEAL ON THE OIL FILLER/DIPSTICK 2 H 7 4 4F 4 F RT A49EU E6NE 1996111400031 19961114 00031 EU 1996 11 14 AU960521 1 19960303 G 2750 FLAP AIRBUS 320 A320212 EU FLAP SYS OUT OF ADJUST W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) LH TRAILING EDGE FLAP INTERCONNECT STRUT MISRIGGED 2 L 7 2 4F RT A28NM 1996111400032 19961114 00032 1996 11 14 AU960522 4 19960423 G 6122 8971613T GOVERNOR WOODWARD 210739 CESSNA 441 441 2076020 CE PROP CNTRL SYS FAULTY W K NONE O OTHER DE DESCENT 1 AU S 2461 1434511M (AUS) LH ENGINE PROPELLER GOVERNOR (CSU) FAULTY 1 L 7 2 3T RT A28CE 1996111400033 19961114 00033 SO 1996 11 14 AU960523 2 19960412 G 8530 6480291 PISTON CESSNA 182 182Q 2072732 CE CONT O470 O470U 17026 SO R ENGINE CYL SEC FAILED W K NONE E R K VIBRATION/BUFFET PARTIAL RPM/PWR LOSS FLUID LOSS CL CLIMB 1 AU S 1233 286636R (AUS) ENGINE NO5 PISTON DISINTEGRATED - RH CRANKCASE HALF CRACKED IN AREA BELOW PUSH ROD TUBES TO FRONT ENGINE MOUNT - C RACK LENGTH 76.2MM (3IN) - ENGINE WAS A CONTINENTAL REMANUFACTURED UNIT 1 H 7 1 3O 3 O NT 3A13 E273 1996111400034 19961114 00034 EU 1996 11 14 AU960525 1 19960422 G 5713 STRINGER PARTEN P68 P68B EU LYC O360 IO360A1B6 41514 EA OUTER WING SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH AND RH WING STRINGERS CRACKED FROM RIVET HOLES - ALL CRACKS WERE LESS THAN 12.7MM (0.5IN) IN LENGTH - FOUND DUR ING INSPECTIONIAW AD/P68/42 1 H 7 2 3O 3 O A31EU 1E10 1996111400035 19961114 00035 SW 1996 11 14 AU960526 1 19960313 G 5710 WING MOONEY M20 M20E 5870212 SW LYC O360 IO360A1A 41514 EA CENTRE WING SYS CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) WING CENTRE SECTION SEVERELY CORRODED - THE FOLLOWING ITEMS NEEDED REPAIR: 1.PNO 210022-091 - WING RIB INBOARD FU SELAGE ATTACHMENT - LH 2. PNO 210022-901 - WING RIB INBOARD FUSELAGE ATTACHMENT - RH 3.PNO 210029-4 - WING RIB INBOARD UNDERCARRIAGE BAY 4. PNO 210104-000 - HINGE ARM FLAP INBOARD5.PNO 210105-501 - HINGE ARM FLAP OUTBOARD 6. PNO 210059- 007 - FITTING WING ATTACHMENT REAR SPAR - LH7.PNO 210059-007 - FITTING WING ATTACHMENT REAR SPAR - RH 8. PNO 210011-00 0 - SPLICE PLATE SPAR CAP UPPER 9.PNO 210010-000 - SPLICE PLATE SPAR CAP LOWER 10. PNO 210054-505 - STUB SPAR ASSEMBLY11 . PNO 210000-111 - STRINGER SPAR WEB 12. PNO 210000-112 - STRINGER SPAR WEB 13. PNO 210020-007 - WEB REAR SPAR 1 L 7 1 3O 3 O 2A3 1E10 1996111400036 19961114 00036 SO 1996 11 14 AU960527 1 19960406 G 3010 36E966A REGULATOR EMB 120 EMB120 3260201 SO PWA 118 PW118A NE ICE-RAIN PROTECT LEAKING W K NONE J WARNING INDICATION CR CRUISE 1 AU S RF1812 (AUS) RH DE-ICE SYSTEM PRESSURE REGULATOR LEAKING AIR 2 L 7 2 4T 4 T RT A31SO E20NE 1996111400037 19961114 00037 SO 1996 11 14 AU960528 1 19960422 G 3230 12038594001 MODULE EMB 120 EMB120 3260201 SO LG EXT-RETRACT S FAULTY W K NONE O OTHER CL CLIMB 1 AU S 120186 (AUS) LANDING GEAR CONTROL MODULE FAULTY 2 L 7 2 4T RT A31SO 1996111400038 19961114 00038 SO 1996 11 14 AU960529 1 19960428 G 8120 LW127996S116 HOSE PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA TURBO SUPERCHRGR DETERIORATED W K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS TO TAKEOFF 1 AU S (AUS) ENGINE LOST POWER DUE TO FAILURE OF HOSE BETWEEN AIRBOX PNO LW-12799-6S116 AND DIFFERENTIAL CONTROLLER - STRATOFL EX 193.4HOSE HAD DETERIORATED DUE TO HEAT FROM ADJACENT TURBOCHARGER 1 L 7 2 3O 3 O A20SO E14EA 1996111400039 19961114 00039 SO 1996 11 14 AU960530 1 19960320 G 5753 FLAP PIPER PA32 PA32300 7103212 SO LYC O540 IO540K1A5 41532 EA WING TE SYS CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) WING FLAPS CORRODED IN AREA BETWEEN STEEL HINGE FITTINGS AND NOSERIBS AND SPARS 1 L 7 1 3O 3 O A3SO 1E4 1996111400040 19961114 00040 SO 1996 11 14 AU960531 1 19960320 G 5711 62054 SPAR PIPER PA32 PIPER PA32 PA32300 7103212 SO LYC O540 IO540K1A5 41532 EA OUTER WING SYS CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) WING REAR SPARS CORRODED IN AREA BENEATH STEEL FITTINGS AS REFERRED TO IN AD/PA28/40 AND AD/PA32/27 - THE CORROSIO N WAS ONLYFOUND FOLLOWING REMOVAL OF THE FITTINGS 1 L 7 1 3O 3 O A3SO 1E4 1996111400041 19961114 00041 CE 1996 11 14 AU960532 1 19960320 G 5343 15411211 FITTING CESSNA 182 182E 2072712 CE CONT O470 O470R 17026 SO ATTACH FITTING S CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH MAIN LANDING GEAR FORGED ALUMINIUM ATTACHMENT FITTING CORRODEDON THE UPPER EDGE BENEATH THE FLOOR SHEETING 1 H 7 1 3O 3 O NT 3A13 E273 1996111400042 19961114 00042 SO 1996 11 14 AU960533 1 19960320 G 5541 63544 RIB PIPER PA32 PIPER PA32 PA32300 7103212 SO LYC O540 IO540K1A5 41532 EA RUDDER STRUCT SY CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RUDDER BUTT RIB CORRODED BENEATH TORQUE TUBE STEEL PLATE 1 L 7 1 3O 3 O A3SO 1E4 1996111400043 19961114 00043 CE 1996 11 14 AU960534 1 19960429 G 3260 MICROSWITCH CESSNA 210 210L 2073448 CE CONT O520 IO520L 17032 SO LG POSITION IND FAULTY W K NONE P NO WARNING INDICATION LD LANDING 1 AU S 294632R (AUS) LANDING GEAR MICROSWITCH ACTUATING ARM BROKEN OFF - WARNING HORN FAILED TO OPERATE AND AIRCRAFT LANDED WITH GEAR R ETRACTED 1 H 7 1 3O 3 O 3A21 E5CE 1996111400044 19961114 00044 CE 1996 11 14 AU960535 1 19960429 G 2897 WIRE CESSNA 402 402B 207590P CE FUEL INDICATION WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) WING TIP FUEL TANK CONTENTS WIRE WORN BY TIP TANK LOWER SKIN INNER SURFACE - WIRE WAS INADEQUATELY RESTRAINED AND CLAMPED 1 L 7 2 3O A7CE 1996111400045 19961114 00045 CE 1996 11 14 AU960536 1 19960419 G 3260 1CH1066 SWITCH WESTERNHYD NLGACTUATOR CESSNA 421 421C 2076016 CE CONT O520 GTSIO520L 17032 SO LG EXT-RETRACT S FAULTY W K NONE O P OTHER NO WARNING INDICATION LD LANDING 1 AU S 1409 (AUS) NOSE LANDING GEAR DOWNLOCK SWITCH FAULTY 1 L 7 2 3O 3 O A7CE E7CE 1996111400046 19961114 00046 SW 1996 11 14 AU960537 1 19960416 G 6230 471501841 PLATE BELL SWASHPLATE BELL 47 47G3B 1181026 SW M/R MAST/SWASHPL CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S ASP20 (AUS) MAIN ROTOR SWASHPLATE CONTROL PLATE FORE/AFT CYCLIC INPUT HORN LUG CRACKED AND BROKEN ON LH SIDE 1 G 7 1 3O 2H3 1996111400047 19961114 00047 CE 1996 11 14 AU960538 1 19960328 G 8120 BEARING GARRTT TURBOCHARGER CESSNA 340 340A 2076405 CE CONT O520 TSIO520N 17040 SO TURBO SUPERCHRGR FAILED W K NONE R K PARTIAL RPM/PWR LOSS FLUID LOSS CR CRUISE 1 AU S (AUS) ENGINE TURBOCHARGER IMPELLER BEARING FAILED 1 L 7 2 3O 3 O 3A25 E8CE 1996111400048 19961114 00048 CE 1996 11 14 AU960539 1 19960330 G 5720 50110231 FITTING CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO OUTER WING SYS CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH STUB WING ATTACHMENT FITTING CONTAINED EXFOLIATION CORROSION - FURTHER CORROSION FOUND FOLLOWING REMOVAL OF TH E FITTING 1 L 7 2 3O 3 O A7CE E8CE 1996111400049 19961114 00049 CE 1996 11 14 AU960540 1 19960417 G 2510 SEAT BELT CESSNA 182 182P 2075816 CE CONT O470 O470R 17026 SO FLIGHT COMPARTME WRONG PART W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) SEAT BELTS USED AUTOMOTIVE HARDWARE WITH NON MIL-SPEC WEBBING - UNAPPROVED PART - PERSONNEL/MAINTENANCE ERROR 1 H 7 1 3O 3 O NT TA13 E273 1996121900099 19961219 00099 SO 1996 12 19 AU960541 2 19960328 G 8500 ENGINE CESSNA 207 207 2073602 CE CONT O520 IO520F 17032 SO HARTZL HCC3Y PHCC3YF1 GL ENGINE (RECIPROC FAILED W A UNSCHED LANDING O OTHER IN INSP/MAINT 1 AU S 284712 EE2125A (AUS) ENGINE FAILED - AIRCRAFT CRASHED - SUSPECT ENGINE STARVED OF FUEL DURING RH TURN 1 H 7 1 3O 3 O A16CE E5CE 5 C P25EA 1996121900100 19961219 00100 CE 1996 12 19 AU960542 1 19960222 G 3244 TIRE CESSNA 404 404CESSNA 2075901 CE MCAULY 3AF34C 3AF34C74 GL MAIN GEAR SYS FOULED W K NONE O OTHER TO TAKEOFF 1 AU S (AUS) RH MAIN LANDING GEAR TYRE FOULING ON AFT EDGE OF WHEEL WELL - TYRE HAD BEEN RECENTLY FITTED 1 L 7 2 3O A25CE 5 C P22EA 1996121900101 19961219 00101 NE 1996 12 19 AU960543 2 19960308 G 7261 SEAL SAAB SF340 340B 7860101 EU GE CT7TP CT79B 30030 NE ROTOL R375 R3754123F21 NE T ENGINE OIL SYS LEAKING W K NONE O OTHER IN INSP/MAINT 1 AU S 785597 (AUS) LH ENGINE INTERNAL OIL LEAK DUE TO CARBON BUILDUP IN THE MIDFRAME ASSEMBLY - NO1 CARBON SEAL WORN 2 L 7 2 4T 4 T RT A52EU E8NE 6 C P17NE 1996121900102 19961219 00102 NM 1996 12 19 AU960544 1 19960206 G 3230 R291206EE0260T HOSE BOEING 737 737377 NM LG EXT-RETRACT S FAILED W K NONE O K OTHER FLUID LOSS CL CLIMB 1 AU S (AUS) RH MAIN LANDING GEAR ACTUATOR UP HYDRAULIC HOSE BURST AT A POINT APPROXIMATELY MIDWAY ALONG ITS LENGTH - LOSS OF S YSTEM 'A' HYDRAULICS 2 L 7 2 4F RT A16WE 1996121900103 19961219 00103 NE 1996 12 19 AU960545 2 19960318 G 7230 DAMPER SAAB SF340 340B 7860101 EU GE CT7TP CT79B 30030 NE ROTOL R375 R3754123F21 NE T ENG CMPRSR/FAN BROKEN W K NONE E J VIBRATION/BUFFET WARNING INDICATION NR NOT REPORTED 1 AU S 785592 (AUS) RH ENGINE NO3 BEARING LOCKNUT INERTIA DAMPER BROKEN - METAL CONTAMINATION OF ENGINE OIL SYSTEM 2 L 7 2 4T 4 T RT A52EU E8NE 6 C P17NE 1996121900104 19961219 00104 NE 1996 12 19 AU960546 2 19960415 G 7261 CHIP DETECTOR SAAB SF340 340B 7860101 EU GE CT7TP CT79B 30030 NE ROTOL R375 R3754123F21 NE T ENGINE OIL SYS CONTAM-METAL W K NONE E J VIBRATION/BUFFET WARNING INDICATION LD LANDING 1 AU S 785604 (AUS) RH ENGINE OIL SYSTEM CHIP DETECTOR CONTAMINATED WITH METAL 2 L 7 2 4T 4 T RT A52EU E8NE 6 C P17NE 1996121900105 19961219 00105 EU 1996 12 19 AU960547 1 19960429 G 3060 DS2336 FILTER FOKKER F27 F27MK50 EU PROP/ROTOR AI-DI SPARKING W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE DE-ICE WIRING LOOM RF FILTER WIRE RUBBING ON PROPELLER SHAFT - SUSPECT WIRING LOOM TOO LONG - PERSONNEL/MA INTENANCE ERROR 2 H 7 2 4T RT A817 1996121900106 19961219 00106 SO 1996 12 19 AU960548 1 19960218 G 2434 12872 BEARING PRESTOLITE ALTERNATOR PIPER PA32 PA32R301 7103218 SO LYC O540 IO540K1G5 41532 EA HARTZL HCC2Y HCC2YK1 GL AC GENERATOR-ALT FAILED W K NONE H ELECT. POWER LOSS-50 PC CR CRUISE 1 AU S 12872 (AUS) ALTERNATOR REAR BEARING FAILED - BRUSHES WORN OUT 1 L 7 1 3O 3 O A3SO 1E4 5 C P920 1996121900107 19961219 00107 NM 1996 12 19 AU960549 1 19960429 G 7931 APT761000100D TRANSMITTER DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE ENG OIL IND SYS FAULTY W K NONE E K VIBRATION/BUFFET FLUID LOSS NR NOT REPORTED 1 AU S (AUS) RH ENGINE OIL PRESSURE TRANSMITTER FAULTY 2 H 7 2 4T 4 T RT A13NM E20NE 1996121900108 19961219 00108 SO 1996 12 19 AU960550 2 19960422 G 8520 646778 CONNECTING ROD CESSNA 402 402B 207590P CE CONT O520 TSIO520E 17040 SO MCAULY 3AF32C 3AF32C87 GL R ENGINE POWER S DISTORTED W K NONE E VIBRATION/BUFFET NR NOT REPORTED 1 AU S 211176 (AUS) RH ENGINE NO6 CYLINDER CONNECTING ROD BENT DUE TO HYDRAULIC LOCK DUE TO EXCESSIVE FUEL IN CYLINDER 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 1996121900109 19961219 00109 SO 1996 12 19 AU960551 1 19960328 G 3230 67748003 VALVE PIPER PA28 PA28RT201 7102818 SO LYC O360 IO360C1C6 41514 EA MCAULY 2D34C 2D34C215 GL LG EXT-RETRACT S LEAKING W K NONE K FLUID LOSS NR NOT REPORTED 1 AU S (AUS) LANDING GEAR EMERGENCY EXTENSION VALVE LEAKING DUE TO FAULTY 'O' RING SEALS 1 L 7 1 3O 3 O 2A13 1E10 5 C P7EA 1996121900110 19961219 00110 EA 1996 12 19 AU960552 2 19960329 G 8520 LW72877 TAPPET LYC CAMSHAFT PIPER PA28 PA28R200 7102811 SO LYC O360 IO360C1C 41514 EA HARTZL HCC2Y HCC2YK1 GL R ENGINE POWER S SPALLED W K NONE O OTHER IN INSP/MAINT 1 AU S L1097351A (AUS) NO1 AND NO2 CYLINDER TAPPET BODIES PNO LW72877 SPALLED - CAMSHAFT PNO LW18840 FORWARD LOBE WORN 1 L 7 1 3O 3 O 2A13 1E10 5 C P920 1996121900111 19961219 00111 SO 1996 12 19 AU960553 1 19960430 G 5712 RIB PIPER PA25 PA25150 7102503 SO LYC O320 O320A2B 41508 EA MCAULY 1A170 1A170GM GL OUTER WING SYS CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH AND RH WING RIBS AND STIFFENERS CONTAINED SEVERE EXFOLIATION CORROSION AND CRACKING OF INBOARD TRAILING EDGE A SSEMBLIES PNO 61217-000 AND PNO 61217-001 - CORROSION ALSO FOUND IN NUMEROUS WING WALK RIBS PNO 61224-000 - WING SKINS P NO 61158-010, PNO 61158-011, PNO 61329-000 AND PNO 61329-001 - RH WING INTERNAL STRUT PNO 61101-000 CONTAINED SEVERE CO RROSION IN AREA WHERE THE REAR SPAR ATTACHMENT FITTING IS RIVETTED TO THE STRUT - AIRCRAFT WAS CONSTRUCTED IN 1959 AND I S USED FOR AGRICULTURAL SPRAYING 1 H 7 1 3O 3 O EXPA1H71 E274 5 N P857 1996121900112 19961219 00112 EU 1996 12 19 AU960554 1 19960221 G 7712 CTOT SYSTEM SAAB SF340 340B 7860101 EU GE CT7TP CT79B 30030 NE ROTOL R390 R3904123F27 NE POWER CONTROL SY INOPERATIVE W K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS TO TAKEOFF 1 AU S 785465785 DRG143990DA (AUS) LH ENGINE CTOT (CONSTANT TORQUE ON TAKE-OFF SYSTEM) INOPERATIVE DUE TO INTERMITTENT ELECTRICAL PROBLEM 2 L 7 2 4T 4 T RT A52EU E8NE 6 C P31NE 1996121900113 19961219 00113 CE 1996 12 19 AU960555 1 19960420 G 3230 9880710116530004 SWITCH CESSNA 210 210L 2073448 CE CONT O520 IO520L 17032 SO MCAULY 2A34C E2A34C73 GL LG EXT-RETRACT S FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LANDING GEAR MOTOR PRESSURE SWITCH WIRE BROKEN AT SOLDERED JOINT - FAILURE WAS COVERED BY HEAT SHRINK MAKING IT DI FFICULT TODETECT 1 H 7 1 3O 3 O 3A21 E5CE 5 C P3EA9 1996121900114 19961219 00114 CE 1996 12 19 AU960556 1 19960423 G 2434 5061369 DIODE ALTERNATOR CESSNA 401 401A 207590D CE MCAULY 3AF32C 3AF32C505 GL DC GENERATOR-ALT FAULTY W K NONE H ELECT. POWER LOSS-50 PC CL CLIMB 1 AU S 118 5061369 (AUS) LH ALTERNATOR DIODES LOOSE AND BROKEN 1 L 7 2 3O A7CE 5 C P22EA 1996121900115 19961219 00115 EU 1996 12 19 AU960557 1 19960415 G 3211 NB40075 BRACKET RHMLG BNORM BN2 BN2A8 1520209 EU LYC O540 O540E4C5 41532 EA HARTZL HCC2Y HCC2YK2 GL MAIN GEAR SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RH MAIN LANDING GEAR BRACKET CRACKED AND BROKEN 1 H 7 2 3O 3 O A17EU E295 5 C P920 1996121900116 19961219 00116 SO 1996 12 19 AU960558 1 19960502 G 6120 B3804T SPRING HARTZL GOVERNOR PIPER PA31 PA31350 7103110 SO HARTZL HCE3Y HCE3YR2 GL PROP CNTRL SYS FAULTY W K NONE O OTHER TO TAKEOFF 1 AU S 6 B3804T (AUS) PROPELLER GOVERNOR SPEEDER SPRING FAILED 1 L 7 2 3O A20SO 5 C P33EA 1996121900117 19961219 00117 SO 1996 12 19 AU960559 1 19960404 G 7120 8621202V MOUNT PIPER PA44 PA44180 7104402 SO LYC O360 O360E1A6 41514 EA HARTZL HCE2Y HCE2YR2 GL ENGINE MOUNTING CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH AND RH ENGINE MOUNT FRAMES CRACKED 1 L 7 2 3O 3 O A19S0 E286 5 C P9EA 1996121900118 19961219 00118 WP 1996 12 19 AU960560 2 19960426 G 7260 310183616 HOUSING GARRTT TPE33110UA SWRNGN SA226 SA226TC 8780404 SW GARRTT TPE331 TPE33110UA 01514 WP HARTZL HCB3T HCB3TN5 GL T ENG AUX DRIVE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 2870 P54299 P54299 (AUS) ENGINE ACCESSORY HOUSING CRACKED IN GUSSET CASTING ADJACENT TO THE RH ENGINE MOUNTING PAD - CRACK LENGTH 25.4MM (1 IN) 2 L 7 2 4T 4 T RT A8SW E4WE 6 C P15EA 1996121900119 19961219 00119 SW 1996 12 19 AU960561 1 19960131 G 5340 RIVET MOONEY M20 M20F 5870214 SW LYC O360 IO360A1A 41514 EA HARTZL HCC2Y HCC2YK1 GL ATTACH FITTING S SHEARED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) HORIZONTAL STABILISER RH ATTACHMENT BRACKET RIVETS (8OFF) SHEARED 1 L 7 1 3O 3 O 2A3 1E10 5 C P920 1996121900120 19961219 00120 1996 12 19 AU960562 4 19960425 G 3140 6226190204 COMPUTER EMB 120 EMB120 3260201 SO PWA 118 PW118A NE HAMSTD 14RF 14RF9 NE CENTRAL COMPUTER FAULTY W K NONE O J OTHER WARNING INDICATION CR CRUISE 1 AU S 2084 (AUS) NO2 AHRS COMPUTER FAULTY - BENCH CHECK COULD FIND NO FAULTS 2 L 7 2 4T 4 T RT A31SO E20NE 6 C P11NE 1996121900121 19961219 00121 SO 1996 12 19 AU960563 1 19960420 G 3230 2060500005 ACTUATOR EMB 120 EMB120 3260201 SO PWA 118 PW118A NE LG EXT-RETRACT S OUT OF ADJUST W K NONE O OTHER CL CLIMB 1 AU S 344 (AUS) NOSE LANDING GEAR ACTUATOR OUT OF ADJUSTMENT 2 L 7 2 4T 4 T RT A31SO E20NE 1996121900122 19961219 00122 SO 1996 12 19 AU960564 1 19960501 G 3211 9529902 SIDE BRACE PIPER PA34 PA34200 7103405 SO LYC O360 IO360C1E6 41514 EA HARTZL HCC2Y HCC2YK2 GL MAIN GEAR SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH AND RH MAIN LANDING GEAR SIDE BRACE STUDS CRACKED IN RADIUS - FOUND DURING MAGNETIC PARTICLE INSPECTION IAW AD/ PA34/46 1 L 7 2 3O 3 O A7SO 1E10 5 C P920 1996121900123 19961219 00123 NM 1996 12 19 AU960565 1 19960426 G 5753 65B15946 FITTING BOEING 747 747238B 1384828 NM WING TE SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FLAP SYSTEM NO2 TRACK AFT SUPPORT FITTING FRACTURED AT FASTENER BOLT HOLE - CRACKING WAS INITIATED BY CORROSION A T THE FASTENER BOLT HOLE - AFT FLAP DRIVE ROD PNO 65B15651-3 ALSO FOUND BENT 2 L 7 4 4F A20WE 1996121900124 19961219 00124 CE 1996 12 19 AU960566 1 19960417 G 3210 10581002367 A FRAME BEECH 76 76 1153005 CE MAIN GEAR SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH MAIN LANDING GEAR ASSEMBLY 'A' FRAME CRACKED IN WELDED AREA AND THE CORROSION TREATMENT HOLE - FOUND DURING INS PECTION IAW AD/B76/18 AND SB 2361 1 L 7 2 3O A29CE 1996121900125 19961219 00125 EU 1996 12 19 AU960567 1 19960327 G 5320 TB1021029165 STIFFENER SOCATA TB10 TB10TOBAGO 8680696 EU LYC O360 O360A1A 41514 EA HARTZL HCC2Y HCC2YK2 GL MAIN FRAME SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUSELAGE STIFFENER LH CRACKED IN AREA OF TORQUE TUBE SUPPORT REAR ANCHOR NUT HOLE - FOUND DURING INSPECTION IAW SO CATA 10-77-53 1 L 7 1 30 3 O NT A51EU E286 5 C P920 1996121900126 19961219 00126 CE 1996 12 19 AU960568 1 19960429 G 2710 1260505187 CABLE CESSNA 210 210L 2073448 CE CONT O520 IO520L 17032 SO MCAULY D3A34 D3A34C404 GL AILERON CONTROL FRAYED W K NONE O OTHER IN INSP/MAINT 1 AU S REARENGINE 286357R 941620 (AUS) RH AILERON/RUDDER INTERCONNECT CABLE FRAYED DUE TO CHAFING ON EACH END OF THE STEEL TUBE COVERING THE CABLE 1 H 7 1 3O 3 O 3A21 E5CE 5 C P47GL 1996121900127 19961219 00127 EU 1996 12 19 AU960569 1 19960302 G 5210 254ANSSNO04 CYLINDER AIRBUS 320 A320212 EU CREW-PASS DOOR S CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S 254ANSSNO (AUS) L1 DOOR ASSIST CYLINDER CORRODED IN AREA OF MANIFOLD CONNECTED TOTHE GAUGE - CORROSION RAN RADIALLY AROUND THE END FACE - LOSS OF CYLINDER PRESSURE 2 L 7 2 4F RT A28NM 1996121900128 19961219 00128 NM 1996 12 19 AU960570 1 19960316 G 3213 19335LH193 TRUNNION BOEING 767 767277 NM GE CF6 CF680A 30025 NE MAIN GEAR SYS CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S 19335LH (AUS) LH AND RH MAIN LANDING GEAR OUTER CYLINDER AFT TRUNNIONS CONTAINED UNACCEPTABLE CORROSION DURING ULTRASONIC AND ED DY CURRENT INSPECTIONS IAW ER B76-32-10-24 - RH OUTER CYLINDER CORRODED IN AREA OF JOURNAL CHAMFER AT THE 2 O'CLOCK POS ITION -LH TRUNNION CORRODED IN AREA OF INBOARD CROSS BOLT HOLE AT THE 6 O'CLOCK POSITION - SUSPECT CAUSED BY CRACKING OF THE FILLET SEAL ALLOWING MOISTURE INGRESS 2 L 7 2 4F 4 F RT A1NM E13NE 1996121900129 19961219 00129 GL 1996 12 19 AU960571 2 19960401 G 7320 6876376 PIPE GOVT N22 N22B 3880102 WP ALLSN 250B 250B17B 03010 GL HARTZL HCA3V HCA3VF7 GL ENG,FUEL CONTROL CRACKED W K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CR CRUISE 1 AU S 880049 DS95 (AUS) COMPRESSOR SCROLL TO PC FILTER INLET PIPE CRACKED ACROSS FLARE AND PARTIALLY BLOCKED WITH CARBON 1 H 7 2 3T 3 T A7PC E10CE 5 C P6EA 1996121900130 19961219 00130 EU 1996 12 19 AU960572 1 19960422 G 3060 9682913221 TIMER SWITCH PILATS PC12 PC12 7090550 EU PROP/ROTOR AI-DI FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S U0029 (AUS) PROPELLER DE-ICE SYSTEM TIMER FAULTY - TIMER NOT SWITCHING BETWEEN BLADES - TIMER IS PERMANENTLY POWERED EVEN WHEN SWITCHED OFF 1 L 7 1 3T RT A78EU 1996121900131 19961219 00131 EU 1996 12 19 AU960573 1 19960401 G 2750 9787320012 WARNING UNIT FDWU95 PILATS PC12 PC12 7090550 EU FLAP DRIVE SYS FAULTY W K NONE N FALSE WARNING CR CRUISE 1 AU S 3326 (AUS) FLAP DRIVE WARNING UNIT FAULTY 1 L 7 1 3T RT A78EU 1996121900132 19961219 00132 EU 1996 12 19 AU960574 1 19960428 G 5720 109 WINGLET PILATS PC12 PC12 7090550 EU WING TIP SYS DAMAGED W K NONE C F.O.D. TX TAXI/GRND HDL 1 AU S 109 (AUS) LH WINGLET STRUCK RUDDER OF A STATIONARY PC-12 (VH-FMP) DURING TAXI - WINGLET DAMAGED - DAMAGE ALSO TO UPPER RUDDE R HINGE AND RUDDER TRIM TAB ACTUATOR SUPPORT OF THE STATIONARY AIRCRAFT 1 L 7 1 3T RT A78EU 1996121900133 19961219 00133 CE 1996 12 19 AU960575 1 19960504 G 5312 FS15576 BULKHEAD CESSNA 441 441 2076020 CE HARTZL HCB3T HCB3TN5 GL MAIN FRAME SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUSELAGE BULKHEAD LOCATED AT FS 155.76 CRACKED AT LOWER RH CORNER- CRACK EXTENDED FOR THE FULL WIDTH OF THE ANGLE 1 L 7 2 3T RT A28CE 6 C P15EA 1996121900134 19961219 00134 GL 1996 12 19 AU960576 1 19960425 G 3222 76053 FORK NAMER NA260 T28B 6402506 GL HAMSTD 43D 43D50 NE NOSE-TAIL GEAR S CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NOSE LANDING GEAR FORK CRACKED IN TWO PLACES: 1. IN THE RADIUS OF THE UPPER FORK SWIVEL SHAFT2. IN THE RADIUS ADJ ACENT TO THE FORK OF THE NLG WHEEL SPINDLE(AXLE)FOUND DURING MAGNETIC PARTICLE INSPECTION (MPI) 1 L 7 1 4R RT EXPA1L71 6 C P8879 1996121900135 19961219 00135 SO 1996 12 19 AU960577 2 19960329 G 8530 646100 CYLINDER CESSNA 404 404CESSNA 2075901 CE CONT O520 GTSIO520M 17032 SO MCAULY 3FF32 3FF32C501 GL R ENG CYL SEC CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 576 239180H (AUS) NO3 CYLINDER EXTENSIVELY CRACKED IN THE AREA AT THE TOP OF THE CYLINDER BORE WITH A TOTAL OF THREE CRACKS 1 L 7 2 3O 3 O A25CE E7CE 5 C P45GL 1996121900136 19961219 00136 NE 1996 12 19 AU960578 1 19960429 G 5210 7620903902107 LATCH SKRSKY S76 S76C 8143008 NE TMECA ARRIEL ARRIEL1S 60030 NE CREW-PASS DOOR S UNLOCKED W K NONE D INFLIGHT SEPARATION CR CRUISE 1 AU S (AUS) CABIN SLIDING DOOR OPENED IN FLIGHT - INVESTIGATION FOUND THAT EITHER THE DOOR LATCH WAS NOT FULLY LOCKED OR A PAS SENGER OPERATED THE LATCH DURING FLIGHT 1 G 7 2 3U 3 U NC H1NE E19EU 1996121900137 19961219 00137 GL 1996 12 19 AU960579 3 19960502 G 6110 692935 O-RING MCAULY 3AF32C75LW BEECH 55 D55 1152730 CE CONT O520 IO520C 17032 SO MCAULY 3AF32C 3AF32C75 GL PROPELLER ASSY S WRONG PART W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S 692935 692935 (AUS) PROPELLER BLADE RETENTION NUT 'O' RINGS WERE THE INCORRECT TYPE CAUSING EXCESSIVE BINDING ON FERRULE - PERSONNEL/ MAINTENANCE ERROR - UNAPPROVED PART 1 L 7 2 3O 3 O 3A16 E5CE 5 C P22EA 1996121900138 19961219 00138 EA 1996 12 19 AU960580 2 19960417 G 8520 LW1883785 CAMSHAFT LYC O320B2C ROBSIN R22 R22BETA NM LYC O320 O320B2C 41508 EA R ENGINE POWER S WRONG PART W K NONE E R W VIBRATION/BUFFET PARTIAL RPM/PWR LOSS INADEQUATE Q C NR NOT REPORTED 1 AU S 198 RL1220239A RL1220239A (AUS) CAMSHAFT SUSPECT FAULTY - COMPARISON WITH A NEW ITEM FOUND THAT THE CAM PROFILE WAS DIFFERENT - INVESTIGATION FOU ND THAT THE CAMSHAFT WAS MARKED IN SMALL LETTERS WITH THE PNO LW18837-85 BUT WAS ALSO MARKED WITH THE PNO 76097 WHICH IS THE PART NUMBER FOR INSTALLATION IN FIXED WING APPLICATIONS - THERE IS ALSO EVIDENCE THAT THE CAMSHAFT HAS BEEN REGROUN D - UNAPPROVED PART -PERSONNEL/MAINTENANCE ERROR 1 G 7 1 3O 3 O H10WE E274 1996121900139 19961219 00139 CE 1996 12 19 AU960581 1 19960417 G 7603 AH37A BOLT NUT CESSNA 421 421C 2076016 CE CONT O520 GTSIO520L 17032 SO MCAULY 3FF32 3FF32C501 GL POWER CONTROL SY SEPARATED W K NONE E VIBRATION/BUFFET DE DESCENT 1 AU S 604164 (AUS) ENGINE THROTTLE CONTROL UNIT ARM PNO 5055002-1 ATTACHMENT NUT PNOMS21044N3 AND BOLT PNO AH37A SEPARATED FROM ARM A ND WERE FOUND ONTHE FLOOR OF THE ENGINE BAY - THE NUT WAS OF THE METAL LOCK TYPE AND INVESTIGATION FOUND THAT IT COULD B E SPUN ONTO THE BOLT BY HAND - PERSONNEL/MAINTENANCE ERROR 1 L 7 2 3O 3 O A7CE E7CE 5 C P45GL 1996121900140 19961219 00140 EU 1996 12 19 AU960582 1 19960429 G 5755 A16053410 HINGE FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU WING SPOILER SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S SH47 (AUS) RH WING OUTBOARD LIFT DUMPER NO5 PANEL INBOARD HINGE LUG CRACKED 2 L 7 2 4F 4 F RT A20EU E2EU 1996121900141 19961219 00141 1996 12 19 AU960583 1 19960421 G 7160 365A54103301 AIR INTAKE TMECA ARRIEL ARRIEL1A 60030 NE ACFT,ENG AIR INT SEPARATED W K NONE O OTHER IN INSP/MAINT 1 AU S 275 (AUS) ENGINE INTAKE FLANGE LOWER PORTION BROKE AWAY AND ENTERED THE ENGINE CAUSING DAMAGE TO THE COMPRESSOR 3 U E19EU 1996121900142 19961219 00142 SO 1996 12 19 AU960584 2 19960425 G 8530 648045 PISTON CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO R ENGINE CYLINDE DAMAGED W K NONE R E PARTIAL RPM/PWR LOSS VIBRATION/BUFFET CL CLIMB 1 AU S 1005 552607 (AUS) NO2 CYLINDER PISTON SEVERELY ERODED AND HOLED IN THE AREA OF THE OIL RING GROOVE - METAL CONTAMINATION OF OIL SYST EM - NO4CRANKSHAFT BEARING ALSO TURNED 1 H 7 1 3O 3 O A4CE E5CE 1996121900143 19961219 00143 CE 1996 12 19 AU960585 1 19960424 G 7603 1005241771 LEVER BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL POWER CONTROL SY BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH FUEL CONTROL LEVER FAILED IN AN AREA LEVEL WITH THE PEDESTAL QUADRANT - LEVER EXHIBITED ADVANCED WEAR IN AREA OF FAILURE -FURTHER INVESTIGATION SHOWED SIMILAR WEAR IN THE RH LEVER - SUSPECT LEVER HAD BEEN BENT AND RESTRAIGHTENED AT ONE TIME WHICH CAUSED CRACKING AND EVENTUAL FAILURE 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 1996121900144 19961219 00144 CE 1996 12 19 AU960586 1 19960506 G 3260 ICH1066 MICROSWITCH CESSNA MLGACTUATOR CESSNA 425 425 2076018 CE PWA PT6 PT6A112 52043 NE HARTZL HCB3T HCB3TN3 GL LG POSITION IND FAULTY W K NONE O N OTHER FALSE WARNING NR NOT REPORTED 1 AU S 3747 (AUS) RH MAIN LANDING GEAR DOWNLOCK MICROSWITCH FAULTY 1 L 7 2 3T 3 T RT A7CE E4EA 6 C P15EA 1996121900145 19961219 00145 SO 1996 12 19 AU960587 1 19960504 G 3230 1159H200116 O-RING GULSTM G1159 GIV 3980115 SO RROYCE TAY TAY6118 EU LG EXT-RETRACT S DETERIORATED W K NONE K W FLUID LOSS INADEQUATE Q C CL CLIMB 1 AU S (AUS) LANDING GEAR UP MANIFOLD TO PIPE PNO 1159H-40016-238 LGU6 UNION 'O' RING SEAL DETERIORATED DUE TO SKYDROL CONTAMI NATION - THEREWAS ALSO EVIDENCE OF THE MANIFOLD HAVING BEEN INCORRECTLY MASKED/PAINTED DURING MANUFACTURE PREVENTING CO RRECT SEATING OFTHE UNION AND THE SQUEEZING OUT OF THE 'O' RING - LOSS OF HYDRAULIC FLUID - PERSONNEL/MAINTENANCE ERROR - MANUFACTURINGERROR 2 L 7 2 4F 4 F RT A12EA E25NE 1996121900146 19961219 00146 CE 1996 12 19 AU960588 1 19960320 G 5720 NAS15237M BOLT BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO HARTZL HCJ3Y PHCJ3YF2 GL OUTER WING SYS CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) WING BOLTS CORRODED DUE TO COVERING OF BARIUM CHROMATE 1 L 7 2 3O 3 O 3A16 E5CE 5 C P36EA 1996121900147 19961219 00147 CE 1996 12 19 AU960589 1 19960401 G 5711 SPAR CESSNA 182 182N 2072730 CE CONT O470 O470R 17026 SO MCAULY 2A34C 2A34C203 GL OUTER WING SYS CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH WING CONTAINED SEVERE EXFOLIATION CORROSION IN THE UPPER FORWARD SPAR EXTRUSIONS, EXFOLIATION CORROSION AND CR ACKING IN THE MAIN SPAR AND CORROSION IN THE INNER SPAR WEB - CORROSION APPEARS TO HAVE BEEN PREVIOUSLY TREATED WITH LP S TYPE COMPOUND 1 H 7 1 3O 3 O NT 3A13 E273 5 C P3EA 1996121900148 19961219 00148 EA 1996 12 19 AU960590 2 19960430 G 7261 CHIP DETECTOR BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL TURBINE ENGINE O CONTAMINATED W K NONE J WARNING INDICATION CL CLIMB 1 AU S 80713 (AUS) LH ENGINE CHIP DETECTOR ILLUMINATED - INSPECTION FOUND A VERY FINE METALLIC HAIR ACROSS THE PROBES - AFTER CLEANI NG AND REINSTALLING IAW PRATT AND WHITNEY MAINTENANCE MANUAL THE AIRCRAFT WAS OPERATED FOR 15 FLIGHT HOURS AND THE CHIP DETECTORREINSPECTED WITH NO CONTAMINATION EVIDENT 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 1996121900149 19961219 00149 CE 1996 12 19 AU960591 1 19960509 G 2612 302158 FIRE DETECTOR BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A42 52043 NE HARTZL HCB3T HCB3TN3 GL FIRE DETECT SYS CONTAM-WATER W K NONE F N FLT CONT AFFECTED FALSE WARNING TO TAKEOFF 1 AU S (AUS) RH ENGINE FIRE DETECTOR ACTIVATED DUE TO MOISTURE ON THE SENSORS - FIRE BOTTLE DISCHARGED 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 1996121900150 19961219 00150 EU 1996 12 19 AU960592 1 19960507 G 3260 A204D14 SCREW ROTOL 200921732 STBROS SD3 SD360 8100606 EU PWA PT6 PT6A65R 52043 EA HARTZL HCB5M HCB5MP3 GL LG POSITION IND LOOSE W K NONE N FALSE WARNING CR CRUISE 1 AU S (AUS) NOSE LANDING GEAR ABUTTMENT PLATE OUT OF ADJUSTMENT 2 H 7 2 4T 4 T A41EU E4EA 6 C P44GL 1996121900151 19961219 00151 NM 1996 12 19 AU960593 1 19960422 G 3260 INDICATION SYS DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE LG POSITION IND FAULTY W K NONE N FALSE WARNING DE DESCENT 1 AU S (AUS) NOSE LANDING GEAR INDICATION SYSTEM FAULTY - EXTENSIVE INVESTIGATION COULD FIND NO FAULT WITH THE SYSTEM 2 H 7 2 4T 4 T RT A13NM E20NE 1996121900152 19961219 00152 NM 1996 12 19 AU960594 1 19960402 G 7710 ENGINE DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE ENG PWR IND SYS FLUCTUATES W K NONE E VIBRATION/BUFFET TO TAKEOFF 1 AU S (AUS) RH ENGINE EXPERIENCED TORQUE FLUCTUATIONS - EXTENSIVE INVESTIGATION COULD FIND NO FAULTS 2 H 7 2 4T 4 T RT A13NM E20NE 1996121900153 19961219 00153 CE 1996 12 19 AU960595 1 19960429 G 2730 040010762 CONTROL CABLE CESSNA 150 152 2071835 CE MCAULY 1A103 1A103TCM GL ELEVATOR CONTROL FRAYED W K NONE O OTHER IN INSP/MAINT 1 AU S LCO29 (AUS) ELEVATOR CONTROL CABLES WORN AND FRAYED - AIRCRAFT IS USED FOR AEROBATICS 1 H 7 1 3O NT 3A19 5 N P50GL 1996121900154 19961219 00154 EA 1996 12 19 AU960597 2 19960507 G 8530 VALVE GUIDE LYC O320 O320D1A 41508 EA R ENGINE CYLINDE WORN W K NONE O OTHER IN INSP/MAINT 1 AU S L1620439A (AUS) ENGINE CYLINDER EXHAUST VALVE GUIDES (3OFF) EXCESSIVELY WORN - VALVE GUIDES WERE WITHIN SERVICE LIMITS BUT WOULD N OT LAST TO THENEXT TOP END OVERHAUL 3 O E274 1996121900155 19961219 00155 WP 1996 12 19 AU960598 2 19960501 G 7210 31039401 SUPPORT GARRTT TPE331 FRCHLD SA227 SA227DC 3377521 SW GARRTT TPE331 TPE33112UA 01514 WP MCAULY 4HFR34 4HFR34C652 NE ENGINE REDUCTION FAULTY W K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CR CRUISE 1 AU S P70144 P70144 (AUS) ENGINE TORQUE RING SUPPORT ASSEMBLY FAULTY 2 L 7 2 4T 4 T RT A18SW E4WE 6 C 3PNE 1996121900156 19961219 00156 CE 1996 12 19 AU960599 1 19960116 G 2823 VALVE CESSNA 441 441 2076020 CE HARTZL HCB3T HCB3TN5 GL FUEL DISTRBUTION FAULTY W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) ENGINE FUEL SHUTOFF VALVE FAULTY - PERSONNEL/MAINTENANCE ERROR 1 L 7 2 3T RT A28CE 6 C P15EA 1996121900157 19961219 00157 SO 1996 12 19 AU960600 1 19960406 G 3220 6708403 TRUNNION PIPER PA44 PA44180 7104402 SO LYC O360 O360E1A6 41514 EA NOSE-TAIL GEAR S DAMAGED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) NOSE LANDING GEAR DRAG BRACE ATTACHMENT TRUNNION DAMAGED - ALLOY CASTING APPEARS TO BE CRYSTALLISED AT THE DRAG BR ACE ATTACHMENTPOINT - SUSPECT CAUSED BY LOCALISED HEATING TO REMOVE/REPLACE BUSHES - PERSONNEL/MAINTENANCE ERROR - UNAP PROVED PROCEDURE 1 L 7 2 3O 3 O A19S0 E286 1996121900158 19961219 00158 CE 1996 12 19 AU960601 1 19960424 G 5343 MS2047069 RIVET CESSNA SUPPORT CESSNA 182 182Q 2072732 CE MCAULY 2A34C 2A34C203 GL ATTACH FITTING S SHEARED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH MAIN LANDING GEAR STRUT SUPPORT LOWER ATTACHMENT RIVET (1OFF) SHEARED - DURING REPLACEMENT OF THE RIVET THE HEA DS OF THE RIVETSEACH SIDE OF THE SHEARED RIVET ALSO FELL OFF 1 H 7 1 3O NT 3A13 5 C P3EA 1996121900159 19961219 00159 CE 1996 12 19 AU960602 1 19960510 G 6120 B3529 LINK MCAULY D3A32C88M CESSNA 210 T210L 2073449 CE CONT O520 TSIO520H 17040 SO MCAULY 3A32C D3A32C88 GL PROPELLER ASSY S BROKEN W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S 390 743799 743799 (AUS) PROPELLER NO1 BLADE PITCH CHANGE LINK BROKEN - FURTHER INSPECTION FOUND INCORRECT BLADE RETENTION NUT 'O' RINGS FI TTED - PROPELLER IS GREASE FILLED WITH OIL FILLED PROPELLER 'O' RINGS FITTED TO UNMODIFIED GROOVES - PERSONNEL/MAINTENAN CE ERROR - UNAPPROVEDPART 1 H 7 1 3O 3 O 3A21 E8CE 5 C P21EA 1996121900160 19961219 00160 EU 1996 12 19 AU960603 1 19960314 G 5320 40875 RIB 40876 GROB G115 G115C 1660303 EU SNSNCH 72C 72CK EA MAIN FRAME SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH AND RH FLOOR RIBS PNO 40875 AND PNO 40876 CRACKED - CRACKS START IN THE RIB ANGLE AND FOLLOW NEAR THE EDGE OF THE FRONT FLOOR FRAME PNO 40882 - HONEYCOMB CORES ALSO PARTLY SEPARATED AT THE CRACKS - SUSPECT CAUSED BY HARD LANDINGS 1 L 7 1 3O NT A57EU 5 N P9045 1996121900161 19961219 00161 CE 1996 12 19 AU960604 1 19960424 G 5312 07125033 BULKHEAD CESSNA 182 182Q 2072732 CE MCAULY 2A34C 2A34C203 GL MAIN FRAME SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUSELAGE BULKHEAD CRACKED IN AREA OF LOWER CURVED SECTION - CRACKLENGTH 6.35MM (0.25IN) 1 H 7 1 3O NT 3A13 5 C P3EA 1996121900162 19961219 00162 NM 1996 12 19 AU960605 1 19960509 G 5510 348AR FAIRING BOEING 767 767284 NM PWA 4056 PW4056 NE HORZ STAB SYS DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RH HORIZONTAL STABILISER TIP DAMAGED BY COLLISION WITH TOWED 747 AIRCRAFT - DAMAGE TO THE FOLLOWING AREAS:- 1. END TIP CLOSURE FAIRING FIBREGLASS PANEL SEVERED 2. LOWER FIBREGLASS PANEL SEVERED AT OUTBOARD EDGE 3. END CLOSURE TIP ASS EMBLY TORN AND DISTORTED TOWING ACCIDENT - PERSONNEL/MAINTENANCE ERROR 2 L 7 2 4F 4 F RT A1NM E24NE 1996121900163 19961219 00163 SO 1996 12 19 AU960606 1 19960509 G 2612 1734361450F FIRE DETECTOR GRUMAN G73 G73T SO PWA PT6 PT6A34 52043 EA HARTZL HCB3T HCB3TN3 GL FIRE DETECTION S FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE FIRE DETECTOR FAULTY - SUSPECT DUE TO SALT/WATER/OIL CONTAMINATION 1 H 7 2 3R 4 T A783 E4EA 6 C P15EA 1996121900164 19961219 00164 SO 1996 12 19 AU960607 1 19960429 G 3211 20829000 STUD PIPER PA24 PA24250 7102404 SO LYC O540 O540A1D5 41532 EA MCAULY 2D36C 2D36C28 GL MAIN GEAR SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MAIN LANDING GEAR SIDE BRACE STUD CRACKED - FOUND DURING MAGNETIC PARTICLE INSPECTION IAW AD/PA24/44 1 L 7 1 3O 3 O 1A15 E295 5 C P901 1996121900165 19961219 00165 CE 1996 12 19 AU960608 1 19960426 G 3260 INDICATOR BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO MCAULY 3AF34C 3AF34C502 GL LG POSITION IND BROKEN WIRE W K NONE O P OTHER NO WARNING INDICATION DE DESCENT 1 AU S (AUS) RH MAIN LANDING GEAR INDICATOR LAMP WIRE BROKEN 1 L 7 2 3O 3 O 3A16 E5CE 5 C P22EA 1996121900166 19961219 00166 SO 1996 12 19 AU960612 1 19960501 G 3230 4198300 HOOK PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2B 41532 EA HARTZL HCE3Y HCE3YR2 GL LG EXT-RETRACT S SEIZED W K NONE O P OTHER NO WARNING INDICATION LD LANDING 1 AU S (AUS) LH MAIN LANDING GEAR DOWNLOCK HOOK STIFF ON PIVOT BOLT PNO AN5-46- AIRCRAFT OPERATES FROM UNPREPARED STRIPS IN A S ALT LADEN ENVIRONMENT WITH HIGH HUMIDITY 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 1996121900167 19961219 00167 SO 1996 12 19 AU960613 2 19960502 G 8500 ENGINE CESSNA 210 210N 2073453 CE CONT O520 IO520L 17032 SO ENGINE (RECIPROC LOW POWER W K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CR CRUISE 1 AU S 567451 (AUS) ENGINE POWER LOSS - INVESTIGATION COULD FIND NO CAUSE FOR THE PROBLEM - A SMALL AMOUNT OF WATER WAS FOUND IN THE LH FUEL TANK 1 H 7 1 3O 3 O 3A21 E5CE 1996121900168 19961219 00168 EU 1996 12 19 AU960618 1 19960317 G 2120 14SNO009 VALVE AIRBUS 320 A320212 EU AIR DISTRIBUTION FAULTY W K NONE J WARNING INDICATION CL CLIMB 1 AU S 14SNO00 (AUS) SKIN AIR OUTLET VALVE ACTUATOR FAULTY - FURTHER INVESTIGATION FOUND AN OPEN CIRCUIT COMMUTATOR BAR ON THE CLOSED DRIVE END 2 L 7 2 4F RT A28NM 1996121900169 19961219 00169 EU 1996 12 19 AU960619 1 19960429 G 2520 833455 DIAPHRAGM AIRBUS 320 A320212 EU PASSENGER COMPAR CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ECONOMY PASSENGER SEAT PAN DIAPHRAGMS (20OFF) CRACKED IN AREA BELOW RIVET LINE ATTACHING DIAPHRAGM TO REAR TUBULA R SEAT BEAM 2 L 7 2 4F RT A28NM 1996121900170 19961219 00170 SO 1996 12 19 AU960620 2 19960510 G 8530 PISTON RING CESSNA 182 182E 2072712 CE CONT O470 O470R 17026 SO HARTZL HCC2Y BHCC2YF1 GL R ENGINE CYLINDE WRONG PART W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S 987337R (AUS) INCORRECT PISTON RING SETS FITTED TO ALL PISTONS - PNO 632932 PISTONS FITTED WHICH SHOULD HAVE RECTANGULAR TOP RI NGS AS PER SB M91-4 - PISTONS WERE FITTED WITH TAPERED RINGS - DAMAGE TO PISTONS AND MINOR SCORING TO CYLINDERS - VALVE SEATS APPEAR TO BEINCORRECTLY CUT - 3 PISTON PINS HAVE LOOSE PLUGS - NO1 CYLINDER HAS VERY DEEP SCORING FROM PREVIOUS H ONING - UNAPPROVED PART - PERSONNEL/MAINTENANCE ERROR 1 H 7 1 3O 3 O NT 3A13 E273 5 C P920 1996121900171 19961219 00171 CE 1996 12 19 AU960621 1 19960508 G 5311 RIB CESSNA 172 172M 2072418 CE MCAULY 1C160 1C160DTM GL MAIN FRAME SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUSELAGE RIB LOCATED AT STN 81 IN AREA OF REAR SEAT FORWARD ATTACHMENT NUTS CRACKED LONGITUDINALLY IN SEVERAL PLA CES - CRACK LENGTHS 50.8MM TO 76.2MM (2IN TO 3IN) 1 H 7 1 3O NT 3A12 5 N P910 1996121900172 19961219 00172 NM 1996 12 19 AU960622 1 19960513 G 2434 948F4582 GENERATOR BOEING 737 737476 NM DC GENERATOR-ALT FAULTY W K NONE H ELECT. POWER LOSS-50 PC CL CLIMB 1 AU S ZG10586 (AUS) NO1 GENERATOR FAILED AND DROPPED OFF LINE - INTERMITTENT APU DELAY OFF SYSTEM 2 L 7 2 4F RT A16WE 1996121900173 19961219 00173 SO 1996 12 19 AU960623 2 19960501 G 8530 629404 EXHAUST VALVE CONT O200A CESSNA 150 A150M 2071831 CE CONT O200 O200A 17020 SO MCAULY 1A102 1A102OCM GL R ENGINE CYLINDE SEIZED W K NONE E VIBRATION/BUFFET CR CRUISE 1 AU S 252880 (AUS) EXHAUST VALVE STICKING IN VALVE GUIDE DUE TO CARBON BUILDUP 1 H 7 1 3O 3 O 3A19 E252 5 N P918 1996121900174 19961219 00174 NE 1996 12 19 AU960624 2 19960509 G 7240 LINER RROYCE RB211524G RROYCE RB211 RB211524G19 NE T ENG BURNER SEC FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE COMBUSTION LINER HEAD SECTION BREAKING UP - FOUND DURING BORESCOPE INSPECTION IAW AD/RB211/19A1 AND ROLLS ROYCE SERVICE BULLETIN RB211-72-B482 4 F E30NE 1996121900175 19961219 00175 CE 1996 12 19 AU960625 1 19960502 G 3260 404EN16 SWITCH BEECH 200 B200C 1152924 CE PWA PT6 PT6A42 52043 NE LG POSITION IND FAILED W K NONE N FALSE WARNING CL CLIMB 1 AU S (AUS) LH MAIN LANDING GEAR DOWNLOCK MICROSWITCH INTERNAL FAILURE 1 L 7 2 4T 4 T A24CE E4EA 1997010200026 19970102 00026 NE 1997 1 2 AU960626 2 19960507 G 8550 827 SEAL PWA DOUG DC4 C54E 3021530 WP PWA R2000 2SD13G 52021 NE HAMSTD 23E 23E50 NE R ENGINE INT OIL FAILED W K NONE E K VIBRATION/BUFFET FLUID LOSS CL CLIMB 1 AU S P107816 P107816 (AUS) NO4 ENGINE OIL SYSTEM NOSE SCAVENGE SYSTEM PIPE UNION SEAL FAILED- LOSS OF ENGINE OIL 2 L 7 4 4R 4 R A762 E230 6 C P603 1996121900176 19961219 00176 CE 1996 12 19 AU960627 1 19960502 G 2121 1013841001 BLOWER BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL AIR DISTRIBUTION FAULTY W K NONE B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 AU S 1100ECH (AUS) AIRCONDITIONING SYSTEM FORWARD EVAPORATOR VENT BLOWER FAN FAULTY - SUSPECT BURNT OUT CIRCUIT 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 1997010200027 19970102 00027 NE 1997 1 2 AU960628 2 19960503 G 7414 SF14RN MAGNETO DOUG DC4 C54E 3021530 WP PWA R2000 R2000* 52023 NE HAMSTD 23E 23E50 NE NR 3&4 ENG CONTAM-WATER W K NONE E VIBRATION/BUFFET TX TAXI/GRND HDL 1 AU S P108363P107 (AUS) NO3 AND NO4 ENGINE MAGNETOS CONTAMINATED WITH MOISTURE 2 L 7 4 4R 4 R A762 5E5 6 C P603 1996121900177 19961219 00177 CE 1996 12 19 AU960629 1 19960503 G 2120 5055434 VALVE BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL AIR DISTRIBUTION FAULTY W K NONE O OTHER CL CLIMB 1 AU S 1619 (AUS) RH BLEED AIR BYPASS VALVE FAULTY - INVESTIGATION FOUND VALVE BUTTERFLY DAMAGED DUE TO A LOOSE SECURING SCREW ALLOW ING THE PLATE TO ROTATE OUT OF ALIGNMENT WITH THE VALVE BORE 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 1996121900178 19961219 00178 CE 1996 12 19 AU960630 1 19960502 G 2610 DETECTOR BEECH 99 C99 1154006 CE PWA PT6 PT6A36 52043 NE HARTZL HCB3T HCB3TN3 GL FIRE DETECTION S CONTAM-WATER W K NONE F B N FLT CONT AFFECTED SMOKE/FUMES/ODORS/SPARKS FALSE WARNING DE DESCENT 1 AU S (AUS) LH ENGINE FIRE DETECTION SYSTEM CONTAMINATED WITH WATER WHEN FLYING THROUGH HEAVY RAIN - FALSE FIRE WARNING CAUSED ENGINE TOBE SHUT DOWN AND FIRE BOTTLE OPERATED 1 L 7 2 3T 4 T A14CE E4EA 6 C P15EA 1996121900179 19961219 00179 SW 1996 12 19 AU960631 1 19960510 G 2120 880276 PIPE GULSTM 690TP 690 0141720 SW HARTZL HCB3T HCB3TN5 GL CABIN PRESSURE C CRACKED W K NONE O OTHER CR CRUISE 1 AU S (AUS) AIRCONDITIONING BLEED AIR SYSTEM SUSPECT LEAKING AT CONNECTION - AD/AC/95 HAD BEEN CARRIED OUT TWO MONTHS PREVIOUS LY -INVESTIGATION FOUND THAT BLEED AIR LINE PNO 880276 WAS CRACKED ATTHE BASE OF THE FLARE WHERE IT CONNECTS TO THE VALV E ASSEMBLY PNO880228-1 1 H 7 2 3T 2A4 6 C P15EA 1996121900180 19961219 00180 CE 1996 12 19 AU960632 1 19960505 G 2610 DETECTOR BEECH 99 C99 1154006 CE PWA PT6 PT6A36 52043 NE HARTZL HCB3T HCB3TN3 GL FIRE DETECTION S CONTAM-WATER W E ENGINE SHUTDOWN F B N FLT CONT AFFECTED SMOKE/FUMES/ODORS/SPARKS FALSE WARNING DE DESCENT 1 AU S (AUS) RH ENGINE FIRE WARNING SYSTEM CONTAMINATED WITH WATER WHEN FLYINGTHROUGH HEAVY RAIN - FALSE FIRE WARNING CAUSED EN GINE TO BE SHUT DOWN AND FIRE BOTTLE OPERATED - DURING REPLACEMENT OF FIRE BOTTLEIT WAS FOUND THAT THE BOTTLE DID NOT DI SCHARGE 1 L 7 2 3T 4 T A14CE E4EA 6 C P15EA 1996121900181 19961219 00181 CE 1996 12 19 AU960633 1 19960418 G 5312 0713608 BULKHEAD CESSNA 182P CESSNA 182 182P 2075816 CE MAIN FRAME SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 61428 (AUS) FORWARD DOORPOST BULKHEAD CRACKED AT RELIEF NOTCHES ON BOTH LH AND RH SIDES - CRACK LENGTH 7MM (0.275IN) 1 H 7 1 3O NT TA13 1996121900182 19961219 00182 GL 1996 12 19 AU960634 2 19960504 G 7261 890274 CHIP DETECTOR ALLSN 250C30S SKRSKY S76 S76A 8143006 NE ALLSN 250C 250C30 03013 GL TURBINE ENGINE O CONTAM-METAL W K NONE J WARNING INDICATION CR CRUISE 1 AU S 890274 890274 (AUS) ENGINE CHIP DETECTOR CONTAINED A FINE SLIVER OF METAL - CHIP DETECTOR WAS CLEANED AND AN ENGINE SERVICEABILITY CHE CK WASPERFORMED - NO FURTHER CONTAMINATION WAS FOUND AND AIRCRAFT RETURNED TO SERVICE 1 G 7 2 3U 3 U H1NE E1GL 1996121900183 19961219 00183 EU 1996 12 19 AU960635 1 19960418 G 5730 SKIN BNORM BN2MK3 BN2AMK3 1520203 EU LYC O540 O540E4C5 41532 EA HARTZL HCE2Y HCE2YK2 GL OUTER WING SYS DAMAGED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) RH WING INTERIOR SKIN DAMAGED IN AREA ADJACENT TO REAR WING ATTACHMENT DUE TO ANGLE GRINDER DIGGING INTO AND THRO UGH INTERIORSKIN - FOUND DURING INSPECTION IAW AD/BNT/17-2 - PERSONNEL/MAINTENANCE ERROR 1 H 7 3 3O 3 O A29EU E295 5 C P9EA 1996121900184 19961219 00184 SO 1996 12 19 AU960636 1 19960322 G 2810 FUEL TANK PIPER PA28 PA28181 7102807 SO LYC O360 O360A4M 41514 EA SNSNCH 76E 76EM8S5 EA FUEL STORAGE SYS EMPTY W K NONE E VIBRATION/BUFFET NR NOT REPORTED 1 AU S (AUS) ENGINE SURGED DUE TO LACK OF FUEL 1 L 7 1 3O 3 O 2A13 E286 5 N P4EA 1996121900185 19961219 00185 SO 1996 12 19 AU960637 1 19960515 G 3230 1217222123 HOSE EMB 110 EMB110P1 3260122 SO PWA PT6 PT6A34 52043 EA HARTZL HCB3T HCB3TN3 GL LG EXT-RETRACT S RUPTURED W K NONE K J FLUID LOSS WARNING INDICATION CR CRUISE 1 AU S (AUS) LH MAIN LANDING GEAR DOWNLOCK HOSE RUPTURED - LOSS OF HYDRAULIC FLUID 1 L 7 2 4T 4 T A21SO E4EA 6 C P15EA 1996121900186 19961219 00186 WP 1996 12 19 AU960638 2 19960129 G 7250 30747553 BLADE AMD FALC50 FALCON900 2700160 EU GARRTT TFE731 TFE7315R 01518 WP TURBINE SECTION FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S P97270 (AUS) NO1 ENGINE THIRD STAGE LOW PRESSURE TURBINE BLADE SHROUD TIP SEPARATED - MINOR DAMAGE TO OTHER LP TURBINE BLADES - THIS DEFECTWAS RECEIVED FROM 34 SQN RAAF AND IS FOR INFORMATION ONLY 2 L 7 3 4F 4 F RT A46EU E6WE 1996121900187 19961219 00187 SO 1996 12 19 AU960639 1 19960515 G 2910 MS287785 SEAL EMB 110 EMB110P1 3260122 SO PWA PT6 PT6A34 52043 EA HARTZL HCB3T HCB3TN3 GL MAIN HYD SYS DISTORTED W K NONE O OTHER CL CLIMB 1 AU S (AUS) RH MAIN LANDING GEAR DOOR DROPPED INTO AIRFLOW - INVESTIGATION FOUND PRESSURE SIDE HYDRAULIC SERVICE COUPLING LEAK ING UNDER PRESSURE DUE TO FLATTENED 'O' RING SEAL 1 L 7 2 4T 4 T A21SO E4EA 6 C P15EA 1996121900188 19961219 00188 EA 1996 12 19 AU960640 2 19960302 G 8530 LW12966 VALVE SEAT LYC TIO540J2BD PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL R ENGINE CYLINDE SEPARATED W K NONE E VIBRATION/BUFFET CR CRUISE 1 AU S 1298 L810361A L810361A (AUS) NO1 CYLINDER VALVE SEAT SEPARATED - NO2 CYLINDER PISTON RING LANDWORN 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 1996121900189 19961219 00189 1996 12 19 AU960641 1 19960214 G 7603 CABLE ROTAX 503 ROTAX503 55555 EU POWER CONTROL SY FAILED W K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 AU S (AUS) ENGINE THROTTLE CONTROL CABLE FAILED - THIS DEFECT WAS RECEIVED FROM THE AUF AND IS FOR INFORMATION ONLY 3 I EXPE3I 1996121900190 19961219 00190 SO 1996 12 19 AU960642 1 19960314 G 6120 7489410 CONTROL CABLE PIPER PA31 PA31350 7103110 SO HARTZL HCE3Y HCE3YR2 GL PROP CNTRL SYS BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH ENGINE PROPELLER PITCH CONTROL CABLE BROKE AT THE FORWARD ENGINE CABLE MOUNT UNDER THE PROPELLER GOVERNOR 1 L 7 2 3O A20SO 5 C P33EA 1996121900191 19961219 00191 SO 1996 12 19 AU960643 1 19960313 G 3210 40284300 LINK PIPER PA31 PA31350 7103110 SO HARTZL HCE3Y HCE3YR2 GL MAIN GEAR SYS INCORRECT MOD W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) LANDING GEAR LOWER SIDE BRACE LINK ASSEMBLY ILLEGALLY MODIFIED BY ADHERING A SPACER PLATE TO THE BUTT JOINT OF THE OVER CENTRE JOINT FACE - FOUND DURING INSPECTION IAW AD/PA31/114 - UNAPPROVEDPART - UNAPPROVED MODIFICATION - PERSONNEL /MAINTENANCE ERROR 1 L 7 2 3O A20SO 5 C P33EA 1996121900192 19961219 00192 NE 1996 12 19 AU960644 2 19960503 G 7260 3087 SEAL TMECA NO1MODULE SKRSKY S76 S76A 8143006 NE TMECA ARRIEL ARRIEL1S 60030 NE TURBINE ENG. ACC LEAKING W K NONE O K OTHER FLUID LOSS CR CRUISE 1 AU S 827 3087 3527 (AUS) NO2 ENGINE NO1 MODULE AIR/OIL SUPERIOR DRIVE CARBON SEAL SUSPECT LEAKING - FACTORY STRIP INSPECTION COULD FIND NO REAL PROBLEMS BUT COMMENTED THAT THE ACCESSORY GEARBOX BREATHER PIPE MAY HAVE BEEN POSITIONED TOO FAR FORWARD CAUSING H IGH OIL CONSUMPTION 1 G 7 2 3U 3 U H1NE E19EU 1996121900193 19961219 00193 SO 1996 12 19 AU960645 1 19960518 G 7120 7197204 BRACKET PIPER PA42 PA42 7104202 SO PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL ENGINE MOUNTING CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH ENGINE UPPER OUTBOARD ENGINE MOUNT TO FIREWALL ATTACHMENT BRACKET CRACKED THROUGH VERTICAL FACE FROM TOP WELD L INE EXTENDING DOWN BETWEEN RIVET HOLES - CRACK LENGTH 9MM (0.35IN) 1 L 7 2 4T 4 T A23SO E4EA 6 C P15EA 1996121900194 19961219 00194 NM 1996 12 19 AU960646 1 19960304 G 7720 11046 PROBE BOEING 737 737377 NM CFMINT CFM56 CFM563B2 13802 EU ENG TEMP IND SYS BROKEN W K NONE E VIBRATION/BUFFET CL CLIMB 1 AU S 11046 (AUS) NO2 ENGINE THERMOCOUPLE 'G' PROBE HAD APPROXIMATELY 3/4 OF ITS LENGTH BROKEN OFF - TGT HARNESS LOWER SECTION FAILE D RESISTANCECHECKS 2 L 7 2 4F 4 F RT A16WE E21EU 1997010200028 19970102 00028 NM 1997 1 2 AU960647 1 19960514 G 4930 PIPE DHAV DHC8 DHC8103 1386005 NM PWA PW121 PW121 52124 NE APU FUEL DIST CHAFED W K NONE O K OTHER FLUID LOSS IN INSP/MAINT 1 AU S (AUS) APU FUEL FEED PIPE LOCATED IN RH WING CHAFED THROUGH BY MAIN BLEED AIR SUPPLY DUCT SHROUD - FUEL LEAKING - SUSPECT CAUSED BYINCORRECT POSITIONING OF FUEL LINE 2 H 7 2 4T 4 T RT A13NM E20NE 1997010200029 19970102 00029 EU 1997 1 2 AU960648 1 19960513 G 4990 SP3967464 BEARING SUNDSTRANDEM 4500506 BAC 146 146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE APU OIL SYS INCORRECT FIT W A K NONE E B VIBRATION/BUFFET SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 AU S SP3967464 (AUS) APU OIL COOLER FAN THRUST BEARING FAILED DUE TO INCORRECT FITMENT(FITTED BACK TO FRONT) - METAL CONTAMINATION OF A PU OIL COOLER MATRIX, OIL FILTERS (2OFF) AND CHIP DETECTOR 2 H 7 4 4F 4 F A49EU E6NE 1996091900065 19960919 00065 NE 1996 9 19 AU960649 2 19960519 G 7321 216381021 FCU LYC ALF502R5 BAC 146 146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE NR 3 ENG FAULTY W O OTHER E VIBRATION/BUFFET CR CRUISE 1 AU S 8276 LF05091 (AUS) NO3 ENGINE FUEL CONTROL UNIT INTERNAL LEAKAGE PAST SERVO PISTON SEALS TOGETHER WITH DAMAGED SERVO SPOOL, PLATE AN D SLEEVE 2 H 7 4 4F 4 F A49EU E6NE 1996091900066 19960919 00066 EA 1996 9 19 AU960650 2 19960520 G 7310 HOSE LYC O360 O360A1F6 41514 EA ENG,FUEL DIST SY SEPARATED W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S (AUS) ENGINE FUEL SYSTEM HOSE BETWEEN PRIMER SOLENOID VALVE AND PRIMER SYSTEM 'T' FITTING SEPARATED AT HOSE FITTING AT ' T' END 3 O E286 1997010200030 19970102 00030 CE 1997 1 2 AU960651 1 19960516 G 2820 0800400238 PIPE CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO MCAULY 3AF32C 3AF32C87 GL FUEL DISTRBUTION CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUEL PIPE BETWEEN WING ROOT AND FUSELAGE BULKHEAD CORRODED THROUGH WALL THICKNESS - OTHER FUEL PIPES CONTAINED SUR FACECORROSION WITHIN LIMITS 1 L 7 2 3O 3 O 3A10 E5CE 5 C P22EA 1997010200031 19970102 00031 CE 1997 1 2 AU960652 1 19960510 G 5712 RIB CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO MCAULY 3AF32C 3AF32C87 GL OUTER WING SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH AND RH MAIN LANDING GEAR WHEEL WELL WING RIBS AND SKINS CRACKED 1 L 7 2 3O 3 O 3A10 E5CE 5 C P22EA 1997010200032 19970102 00032 CE 1997 1 2 AU960653 1 19960510 G 5711 512203112 SPAR CAP CESSNA RHSPARCAP CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO MCAULY 3AF32C 3AF32C87 GL OUTER WING SYS CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH AND RH WING SPAR CAPS PNO 5122031-1 (LH) AND PNO 512203-2 (RH)CORRODED IN AREA OF NACELLE FUEL TANKS - WING SKI NS AND CHANNELS ALSO CORRODED 1 L 7 2 3O 3 O 3A10 E5CE 5 C P22EA 1996091900067 19960919 00067 CE 1996 9 19 AU960654 1 19960520 G 2820 O8OO4OO238 PIPE CESSNA 310 310R 2074245 CE FUEL DISTRBUTION CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUEL PIPE FROM WING ROOT TO FUSELAGE BULKHEAD CORRODED THROUGH WALL THICKNESS - OTHER FUEL PIPES CONTAINED SURFACE CORROSIONWITHIN LIMITS 1 L 7 2 3O 3A10 1997010200033 19970102 00033 WP 1997 1 2 AU960655 1 19960515 G 5530 TAILPLANE GOVT N22 N22B 3880102 WP ALLSN 250B 250B17B 03010 GL HARTZL HCA3V HCA3VF7 GL VERT STAB STRUCT CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH AND RH SECTIONS OF TAILPLANE CRACKED IN EIGHT PLACES - MOST CRACKING WAS FOUND TO ORIGINATE FROM RIVETS IN RIBS AND INTERCOSTAL ANGLES - TWO CRACKS WERE ALSO FOUND IN THE SKIN - NUMEROUS RIVETS WORKING - FOUND DURING INSPECTION IA W NMD-55-34 1 H 7 2 3T 3 T A7PC E10CE 5 C P6EA 1997010200034 19970102 00034 EA 1997 1 2 AU960656 2 19960513 G 7414 A197987 CONDENSER BENDIX SLN20 PIPER PA25 PA25235 7102504 SO LYC O540 O540B2B5 41532 EA MCAULY 1A200 1A200FA GL ELEC PWR SUPPLY FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S A197987 L1968540 (AUS) MAGNETO CONDENSER SEPARATED FROM MOUNTING LUG - PIGTAIL BROKEN - POINTS BURNT 1 L 7 1 3O 3 O 2A10 E295 5 N P874 1997010200035 19970102 00035 SO 1997 1 2 AU960657 1 19960517 G 5320 ANGLE PIPER PA44 PA44180 7104402 SO LYC O360 O360E1A6 41514 EA HARTZL HCE2Y HCE2YR2 GL NLG WELL CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NOSE LANDING GEAR WHEEL WELL LH AND RH LOWER ANGLES CRACKED IN AREA WHERE NLG DRAG BRACE PIVOT BRACKET ATTACHES AN D TO WHICH THENOSE GEAR DOOR HINGES ATTACH 1 L 7 2 3O 3 O A19S0 E286 5 C P9EA 1996091900068 19960919 00068 1996 9 19 AU960658 1 19960520 G 7713 6111 GAUGE ENG PWR IND SYS CONTAMINATED W K NONE O OTHER NR NOT REPORTED 1 AU S 173572 (AUS) MANIFOLD PRESSURE GAUGE AND LINE CONTAMINATED WITH OIL 1997010200036 19970102 00036 EA 1997 1 2 AU960659 2 19960423 G 7210 SN91C8083024765 GEAR PWA PWA PT6 PT6A27 52043 EA ENG RED GR BOX DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S PCE42228 PCE42228 (AUS) ENGINE REDUCTION GEARBOX 1ST STAGE SUN GEAR DAMAGED - RELATED PARTS HAD SECONDARY DAMAGE - ENGINE WAS FITTED TO M ALAYSIAN AIRLINES 9M-MDO 4 T E4EA 1997010200037 19970102 00037 1997 1 2 AU960660 1 19960112 G 7160 AIR BOX LYC O360 O360A1F6 41514 EA HARTZL HCF2Y HCF2YR1 GL ACFT,ENG AIR INT CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE INTAKE SYSTEM AIR BOX FAULTY - CRACKS IN AREA OF AIR FILTER - CARBURETTOR ATTACHMENT RING BROKEN OFF 3 O E286 5 C P27EA 1997010200038 19970102 00038 EU 1997 1 2 AU960661 1 19960515 G 3220 FORK GROB G115 G115C 1660303 EU LYC O360 O360A1F6 41514 EA HARTZL HCF2Y HCF2YR1 GL NOSE-TAIL GEAR S DELAMINATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NOSE LANDING GEAR FORK ASSEMBLY DELAMINATING IN AREA OF RADIUS 1 L 7 1 3O 3 O NT A57EU E286 5 C P27EA 1996091900069 19960919 00069 EU 1996 9 19 AU960662 1 19960521 G 2842 TRANSMITTER GROB G115 G115C 1660303 EU LYC O360 O360F1A6 41514 EA FUEL INDICATION FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH AND RH FUEL TRANSMITTER FLOATS DETERIORATED 1 L 7 1 3O 3 O NT A57EU E286 1997010200039 19970102 00039 NM 1997 1 2 AU960663 1 19960517 G 5710 WING DHAV DHC8 DHC8103 1386005 NM PWA PW121 PW121 52124 NE WING LE SYS BIRD STRIKE W K NONE C F.O.D. DE DESCENT 1 AU S (AUS) AIRCRAFT SUFFERED A BIRDSTRIKE BY A LARGE WEDGETAIL EAGLE - THE EAGLE GLANCED OFF THE LH WINDSCREEN AND STRUCK TH E LH WING LEADING EDGE BETWEEN THE FUSELAGE AND THE ENGINE JUST INBOARD OF THE PROPELLER ARC CAUSING SEVERE DAMAGE TO TH E LEADING EDGESTRUCTURE, ELECTRICAL WIRING AND PLUMBING BETWEEN STN YW57.20 ANDYW42.00 - MAJOR DAMAGE ALSO OCCURRED TO T HE FRONT SPAR AND LOWER WING SKIN IN THE SAME AREA INCLUDING SEPARATION OF THE LOWER SPARBOOM FROM THE MACHINED WEB AND BUCKLING OF THE LOWER SKIN 2 H 7 2 4T 4 T RT A13NM E20NE 1997010200040 19970102 00040 CE 1997 1 2 AU960664 1 19960507 G 3231 ARB4EDUS ROD END CESSNA CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO MCAULY 3AF32C 3AF32C87 GL LG EXT-RETRACT S FAILED W K NONE O OTHER CL CLIMB 1 AU S 402C0049 (AUS) LH MAIN LANDING GEAR DOOR LINK ASSEMBLY INBOARD RODEND FAILED IN THE AREA OF THE NUT 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 1997010200041 19970102 00041 1997 1 2 AU960665 4 19960503 G 2562 MN1300 BATTERY E01 CESSNA 182 182M 2072728 CE CONT O470 O470R 17026 SO MCAULY 2A34C 2A34C203 GL ELT EQUIP LEAKING W K NONE O OTHER IN INSP/MAINT 1 AU S 003441 (AUS) REMOTE ELT BATTERIES LEAKING CAUSING CORROSION DAMAGE TO THE ENTIRE UNIT 1 H 7 1 3O 3 O NT 3A13 E273 5 C P3EA 1996091900070 19960919 00070 NE 1996 9 19 AU960666 3 19960522 G 6111 6607132766 BLADE ROTOL R389 R3894123F25 NE PROPELLER ASSY S CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S SF34013217 DRG202188 (AUS) PROPELLER BLADE SUSPECT CRACKED - FOUND DURING ULTRASONIC FLAW DETECTION OF THE INNER AND OUTER ROOT SLEEVES IAW N DT TECHNIQUEP20/0H6 - FURTHER INVESTIGATION FOUND THE INDICATIONS TO BE RESIN CRACKING WHICH IS NOT CONSIDERED TO BE A D EFECT 6 C P30NE 1996091900071 19960919 00071 1996 9 19 AU960667 1 19960520 G 7820 MUFFLER ROTAX 912 ROTAX912 55555 EU ENG EXH SEPARATED W K NONE O OTHER DE DESCENT 1 AU S (AUS) ENGINE EXHAUST SYSTEM MUFFLER SEPARATED FROM NO4 CYLINDER SUPPORT AND EXHAUST PIPE AT THE WELDED JOINT BETWEEN MUF FLER AND PIPE -MUFFLER WAS RETAINED BY NO2 CYLINDER PIPE AND THE FIREWALL SHOCK MOUNT 3 I EXPE3I 1996091900072 19960919 00072 EA 1996 9 19 AU960668 2 19960523 G 8530 F1890 CYLINDER PIPER PA28 PA28161 7102803 SO LYC O320 O320D3G 41508 EA RT ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 747 F1890 L1226539A (AUS) NO2 CYLINDER CRACKED IN AREA OF EXHAUST PORT - CRACKING ALSO FOUND BETWEEN THE VALVE SEATS 1 L 7 1 3O 3 O 2A13 E274 1997010200042 19970102 00042 EA 1997 1 2 AU960669 2 19960518 G 7322 75029611 BRACKET LYC O360 O360A1F6 41514 EA HARTZL HCF2Y HCF2YR1 GL ENG,FUEL CONTROL FRACTURED W K NONE O OTHER IN INSP/MAINT 1 AU S 75029611 L3406836A (AUS) CARBURETTOR FLOAT PIVOT PIN BRACKET FRACTURED - CARBURETTOR FLOODING 3 O E286 5 C P27EA 1996091900073 19960919 00073 EA 1996 9 19 AU960670 2 19960523 G 7310 HOSE LYC O360 O360A1F6 41514 EA ENG FUEL DIST SY FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE PRIMER HOSE FAULTY - END FITTINGS CAN BE PULLED AWAY FROM HOSE 3 O E286 1996091900074 19960919 00074 EU 1996 9 19 AU960671 1 19960522 G 2730 CONTROL ROD GROB G115 G115C 1660303 EU ELEV CONTROL WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ELEVATOR PUSH-PULL CONTROL ROD WORN AND SCORED BY POP RIVETS HOLDING THE PLASTIC TUBE GUIDE - RIVETS EXTEND TOO FA R AND WORE INTO CONTROL ROD 1 L 7 1 3O NT A57EU 1996091900075 19960919 00075 EU 1996 9 19 AU960672 1 19960523 G 2810 FUEL TANK GROB G115 G115C 1660303 EU FUEL STORAGE SYS LEAKING W K NONE O K OTHER FLUID LOSS IN INSP/MAINT 1 AU S (AUS) RH FUEL TANK LEAKING AT RH AFT TANK FITTING 1 L 7 1 3O NT A57EU 1996091900076 19960919 00076 SO 1996 9 19 AU960673 2 19960520 G 8530 353395 CYLINDER CONT IO360HB CONT O360 IO360HB 17025 SO RT ENGINE CYL FAILED W O OTHER E K B VIBRATION/BUFFET FLUID LOSS SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 AU S 353395 353395 (AUS) ENGINE NO2 CYLINDER HAD NIL COMPRESSION - LOSS OF OIL QUANTITY AND PRESSURE - METAL CONTAMINATION OF OIL FILTER 3 O E1CE 1997010200043 19970102 00043 SO 1997 1 2 AU960674 2 19960425 G 7314 6307514 PUMP CESSNA 421 421B 2076014 CE CONT O520 GTSIO520H 17032 SO MCAULY 3AF34C 3AF34C92 GL ENG,FUEL DIST SY FAILED W K NONE E VIBRATION/BUFFET TO TAKEOFF 1 AU S 8 A2675278 218478R (AUS) RH ENGINE DRIVEN FUEL PUMP FAILED DUE TO FOD 1 L 7 2 3O 3 O A7CE E7CE 5 C P22EA 1996091900077 19960919 00077 EU 1996 9 19 AU960675 1 19960523 G 3222 AXLE GROB G115 G115C 1660303 EU NOSE WHEEL FAULTY W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) NOSE WHEEL AXLE SUSPECT INCORRECT SIZE - AXLE WAS APPROXIMATELY 10MM (0.393IN) SHORTER THAN NEW ITEM 1 L 7 1 3O NT A57EU 1996091900078 19960919 00078 EA 1996 9 19 AU960676 2 19960523 G 7310 HOSE LYC O360 O360A1F6 41514 EA ENG FUEL DIST SY SEPARATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE PRIMER HOSE PULLED OFF END FITTING PNO 311-2D AT SOLENOID VALVE CONNECTION 3 O E286 1997010200044 19970102 00044 EA 1997 1 2 AU960677 2 19960418 G 8530 EXHAUST VALVE LYC O360 O360A4K 41514 EA MCAULY 1A170 1A170FFA GL R ENG CYL NR 1 FAILED W K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CR CRUISE 1 AU S L2704436A (AUS) NO1 CYLINDER EXHAUST VALVE HAD APPROXIMATELY 33% OF THE VALVE HEAD MISSING 3 O E286 5 N P857 1997010200045 19970102 00045 EU 1997 1 2 AU960678 1 19960518 G 7930 230384601 PROCESSOR LYC BAC 146 146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE ENG OIL IND SYS FAULTY W K NONE E K VIBRATION/BUFFET FLUID LOSS TX TAXI/GRND HDL 1 AU S LF05863A (AUS) NO2 ENGINE DUAL LOW OIL PRESSURE PROCESSOR FAULTY - CAUSES INTERFERENCE WITH MASTER WARNING SYSTEM - LYCOMING MODI FICATION79-2-0013D HAD BEEN CARRIED OUT 2 H 7 4 4F 4 F A49EU E6NE 1996091900079 19960919 00079 SO 1996 9 19 AU960679 2 19960520 G 8520 63026143 BEARING CONT COUNTERWGHT CONT O360 IO360HB 17025 SO RT ENG CTRWT WRONG PART W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S 353395 (AUS) CRANKSHAFT COUNTERWEIGHT ROLLER BEARING PNO 630261-43 INCORRECT PART - CORRECT PART NUMBER FITTED SHOULD HAVE BEE N PNO 630261-44 - COUNTERWEIGHT RETAINING WASHER WORN INTO COUNTERWEIGHT - UNAPPROVED PART - PERSONNEL/MAINTENANCE ERROR 3 O E1CE 1997010200046 19970102 00046 SO 1997 1 2 AU960680 1 19960516 G 3230 O-RING EMB 110 EMB110P1 3260122 SO PWA PT6 PT6A34 52043 EA HARTZL HCB3T HCB3TN3 GL LG EXT-RETRACT S FAILED W K NONE O OTHER CL CLIMB 1 AU S (AUS) LANDING GEAR HYDRAULC SYSTEM PRESSURE REDUCER VALVE 'O' RING SEAL FAILED 1 L 7 2 4T 4 T A21SO E4EA 6 C P15EA 1996091900080 19960919 00080 EU 1996 9 19 AU960681 1 19960521 G 3240 50028202 WHEEL ISRAEL 1124 1124 4500102 EU LG WHEEL/BRAKE S FRACTURED W A K NONE O OTHER NR NOT REPORTED 1 AU S 312 INNERWHEEL (AUS) MAIN LANDING GEAR WHEEL BRAKE DRIVE PAD KEY SECTION SEPARATED FROM WHEEL (ONE PIECE CASTING) - OVERLOAD FRACTURE CAUSED BY REDUCTION IN WHEEL CROSS SECTION DUE TO GROOVING FROM LOOSE DUST/WATER SHIELD 2 M 7 2 4F A2SW 1997010200047 19970102 00047 SW 1997 1 2 AU960682 1 19960208 G 5340 51700365165 BRACKET 51700367165 GULSTM 500 500S 0141107 SW LYC O540 IO540E1B5 41532 EA HARTZL HCA3V HCA3VK2 GL ATTACH FITTING S CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH WING ROOT BRACKETS PNO 5170036-5-165 AND PNO 5170036-7-165 CRACKED - FOUND DURING INSPECTION IAW AD/AC/93 1 H 7 2 3O 3 O 6A1 1E4 5 C P6EA 1997010200048 19970102 00048 SW 1997 1 2 AU960683 1 19960209 G 5340 51700367165 BRACKET 51700367165 GULSTM 500 500S 0141107 SW LYC O540 IO540E1B5 41532 EA HARTZL HCA3V HCA3VK2 GL ATTACH FITTING S CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH WING ROOT BRACKETS PNO 5170036-5-165 AND PNO 5170036-7-165 CRACKED - FOUND DURING INSPECTION IAW AD/AC/93 1 H 7 2 3O 3 O 6A1 1E4 5 C P6EA 1997010200049 19970102 00049 CE 1997 1 2 AU960684 1 19960503 G 2434 A103214 BEARING PRESTOLITE CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO MCAULY 3AF32C 3AF32C87 GL AC GENERATOR-ALT FAILED W K NONE H ELECT. POWER LOSS-50 PC CR CRUISE 1 AU S 1368 A103214 (AUS) RH ENGINE ALTERNATOR BEARINGS DESTROYED - DRIVE AND DRIVEN GEARS DAMAGED - METAL CONTAMINATION OF OIL SYSTEM 1 L 7 2 3O 3 O 3A10 E5CE 5 C P22EA 1997010200050 19970102 00050 SO 1997 1 2 AU960685 1 19960411 G 5520 MS202533 PIN AYRES AYRES S2 S2RT34NORMAL 0970106 SO PWA PT6 PT6A34AG 52053 NE HARTZL HCB3T HCB3TN3 GL ELEVATOR STRUCT DISPLACED W K NONE O OTHER IN INSP/MAINT 1 AU S PCE57394 BU17835 (AUS) RH ELEVATOR TRIM TAB HINGE PIN MOVED INBOARD 1 L 7 1 3T 4 T A3SW E4EA 6 C P15EA 1997010200051 19970102 00051 CE 1997 1 2 AU960686 1 19960513 G 5320 07136381 REINFORCEMENT 07136382 CESSNA 182 182Q 2072732 CE MAIN FRAME SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUSELAGE REINFORCEMENTS PNO 0713638-1 (LH) AND PNO 0713638-2 (RH), SUPPORT ANGLES PNO 0753600-11 (LH) AND PNO 0753 600-12 (RH),TUNNEL BULKHEADS PNO 0713631-1 (LH) AND PNO 0713631-6 (RH) WERE BENT, DISTORTED AND CRACKED - FIREWALL DIST ORTED AFT BY 12.7MM (0.5IN) IN THE AREA OF THE UPPER NOSE LANDING GEAR SUPPORT CASTING - SUSPECT CAUSED BY HEAVY LANDING 1 H 7 1 3O NT 3A13 1996091900081 19960919 00081 GL 1996 9 19 AU960687 3 19960522 G 6114 D220116 HUB HARTZL HCC2YK2 PIPER PA34 PA34200 7103405 SO HARTZL HCC2Y HCC2YK2 GL BLADE SOCKET CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S 311 AV3856 AV3856 (AUS) PROPELLER HUB SEVERELY CORRODED IN AREA OF BLADE SOCKETS 1 L 7 2 3O A7SO 5 C P920 1997010200052 19970102 00052 NE 1997 1 2 AU960688 2 19960108 G 7250 AS3218173 RING PWA PWA PT6 PT6A42 52043 NE TURBINE SECTION MISSING W K NONE O OTHER IN INSP/MAINT 1 AU S 4405 94202 94202 (AUS) ENGINE POWER TURBINE DISC NO3 BEARING COVER PNO 3103204-01 MOVED REARWARDS CONTACTING THE 2ND STAGE POWER TURBINE DISC RIM PNO3029313 - SUSPECT RETAINING RING PNO AS3218-173 NOT FITTED AT LAST ASSEMBLY - PERSONNEL/MAINTENANCE ERROR 4 T E4EA 1996091900082 19960919 00082 SW 1996 9 19 AU960689 1 19960521 G 6320 0476206283 BEARING BELL TRANSMISSION BELL 47 47G3B 1181026 SW MAIN ROTOR XMSN FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S 80 B12344 (AUS) MAIN TRANSMISSION LOWER SUN GEAR BEARING CAGE DISINTEGRATED - BEARING OIL PRESSURE JETS WERE ALSO FOUND TO BE BLO CKED WITH A NON FERROUS METAL (METAL DID NOT ORIGINATE FROM THE TRANSMISSION)- TRANSMISSION HAD BEEN FITTED FOR APPROXIM ATELY 80 HOURS -FURTHER INVESTIGATION FOUND THAT THE PREVIOUS TRANSMISSION FITTEDALSO HAD BLOCKED OIL JETS - IT IS SUSPE CTED THAT AS THEHELICOPTER HAD PREVIOUSLY HAD AN ENGINE FAILURE FOR METAL IN THE FILTER, THE COSHARED ENGINE/TRANSMISSIO N OIL COOLER HAD NOT BEEN CLEANED OR REPLACED - METAL CONTAMINATION OF TRANSMISSION OIL SYSTEM 1 G 7 1 3O 2H3 1996091900083 19960919 00083 EU 1996 9 19 AU960690 1 19960527 G 6210 1178016602 BRACKET BOLKMS 117 BK117B2 5626013 EU M/R BLADE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MAIN ROTOR BLADE PENDULUM VIBRATION ABSORBER ASSEMBLIES (4OFF) LOWER PLATE BRACKETS CRACKED IN AREA OF INBOARD FLA NGE DUE TOEXFOLIATION CORROSION 1 G 7 2 3U NC H13EU 1996091900084 19960919 00084 GL 1996 9 19 AU960692 3 19960522 G 6114 D220116 HUB HARTZL HCC2YK2CUF BNORM BN2 BN2A26 1520226 EU HARTZL HCC2Y HCC2YK2 GL PROPELLER ASSY CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 1698 AU7431 AU7431 (AUS) PROPELLER HUB CRACKED FROM HUB MOUNTING AREA TO BLADE SOCKET - CRACK LENGTH 35MM (1.37IN) 1 H 7 2 3O A17EU 5 C P920 1996091900085 19960919 00085 NM 1996 9 19 AU960693 1 19960520 G 6710 BOLT ROBSIN A2051 ROBSIN R22 R22BETA NM MAIN RTR CNTRL S MISSING W K NONE O OTHER IN INSP/MAINT 1 AU S 204 0 (AUS) COLLECTIVE CONTROL SYSTEM YOKE P/N A205-1 HAD BOLT, JOURNALS, WASHERS AND NUTS MISSING - ITEMS FOUND IN AREA OF B ELLY PANEL 1 G 7 1 3O H10WE 1997010200053 19970102 00053 NM 1997 1 2 AU960695 1 19960511 G 4920 TURBINE GARRTT GTCP85129K BOEING 737 737476 NM APU ENGINE SYS SEPARATED W A K NONE O E OTHER VIBRATION/BUFFET IN INSP/MAINT 1 AU S (AUS) APU FAILED DURING GROUND RUN - INVESTIGATION FOUND LARGE PIECES OF METAL IN THE MUFFLER AND THE LOWER SHROUD - SU BSTANTIAL EXTERNAL DAMAGE WAS ALSO PRESENT - FURTHER INSPECTION FOUND THAT THE APU HAD MOVED IN ITS MOUNTS - SUSPECT FAI LURE DUE TO SEPARATION OF THE TURBINE WHEEL 2 L 7 2 4F RT A16WE 1997010200054 19970102 00054 1997 1 2 AU960696 1 19960513 G 7830 SLIDER CFMINT CFM56 CFM563C 13802 EU T ENG THRUST REV SEPARATED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) ENGINE THRUST REVERSER NO2 OUTBOARD REVERSER HALF LOWER SLIDER SEPARATED FROM THE SLIDER TRACK - TRANSLATING COWL HAD BEEN RECENTLY REMOVED TO CARRY OUT A LOWER BLOCKER DOOR HINGE REPLACEMENT - PERSONEL/MAINTENANCE ERROR 4 F E21EU 1997010200055 19970102 00055 NM 1997 1 2 AU960697 1 19960429 G 5510 7575564511 BEAM BOEING 737 737377 NM HORZ STAB SYS CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH HORIZONTAL STABILISER LOWER TRAILING EDGE BEAM COVER PLATE CONTAINED SEVERE EXFOLIATION CORROSION 2 L 7 2 4F RT A16WE 1997010200056 19970102 00056 EU 1997 1 2 AU960698 1 19960503 G 5750 68160351 PLATE PARTEN P68 P68B EU LYC O360 IO360A1B6 41514 EA HARTZL HCC2Y HCC2YK2 GL WING TE SYS CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FLAP SYSTEM HINGE PLATES BADLY CORRODED IN AREA OF PIVOT BOLT HOLES - UPPER ATTACHMENT BEARING SEIZED DUE TO LACK OF LUBRICATION 1 H 7 2 3O 3 O A31EU 1E10 5 C P920 1997010200057 19970102 00057 EU 1997 1 2 AU960699 1 19960503 G 7120 J961340 MOUNT PARTEN P68 P68B EU LYC O360 IO360A1B6 41514 EA ENGINE MOUNTING CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH ENGINE TOP OUTBOARD LORD MOUNT PLATE CONTAINED EXFOLIATION CORROSION - PLATE WAS ALSO SEPARATED FROM THE RUBBE R MOUNT ASSEMBLY 1 H 7 2 3O 3 O A31EU 1E10 1997010200058 19970102 00058 EU 1997 1 2 AU960700 1 19960412 G 3230 SA7670006123 HOSE BAC 146 146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE LG EXT-RETRACT S FAILED W K NONE K FLUID LOSS CR CRUISE 1 AU S (AUS) RH MAIN LANDING GEAR ACTUATOR DOWN LINE FLEXIBLE HOSE BURST IN AREA JUST BELOW 90 DEGREE UNION WHERE HOSE ATTACHES TO MANIFOLD -LOSS OF GREEN SYSTEM HYDRAULIC FLUID 2 H 7 4 4F 4 F A49EU E6NE 1997010200059 19970102 00059 EU 1997 1 2 AU960701 1 19960503 G 7120 J961340 MOUNT PARTEN P68 P68B EU LYC O360 IO360A1B6 41514 EA HARTZL HCC2Y HCC2YK2 GL ENGINE MOUNTING DETERIORATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE MOUNT RUBBERS DETERIORATED 1 H 7 2 3O 3 O A31EU 1E10 5 C P920 1997010800002 19970108 00002 EU 1997 1 8 AU960702 1 19960314 G 2750 GEARBOX AIRBUS 320 A320212 EU RTINB FLAP MIS RIGGED W A K NONE F FLT CONT AFFECTED NR NOT REPORTED 1 AU S (AUS) RH INBOARD FLAP OUTER ROTARY GEARBOX MISRIGGED 2 L 7 2 4F RT A28NM 1997010200060 19970102 00060 EU 1997 1 2 AU960703 1 19960503 G 5540 68340451 BRACKET PARTEN P68 P68B EU LYC O360 IO360A1B6 41514 EA HARTZL HCC2Y HCC2YK2 GL RUDDER STRUCT SY CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RUDDER HINGE BRACKET CONTAINED EXFOLIATION CORROSION IN THE AREA BETWEEN THE HINGE UPPER FORK LUGS - CORROSION ALS O IN THE AREA OFTHE PIVOT BOLT HOLE - PIVOT BUSH SEIZED DUE TO LACK OF LUBRICATION - THE HINGE FITTING FAILED THROUGH TH E PIVOT BOLTHOLE WHEN ATTEMPTING TO REMOVE THE BOLT 1 H 7 2 3O 3 O A31EU 1E10 5 C P920 1997010200061 19970102 00061 1997 1 2 AU960704 4 19960517 G 3452 AT150 TRANSPONDER PIPER PA32 PA32260 7103206 SO LYC O540 O540E4A5 41532 EA HARTZL HCC2Y HCC2YK1 GL DEPDNT POSN DATA FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S 25256 (AUS) TRANSPONDER FAILED TO OPERATE DUE TO A FAULTY CAVITY BAND PASS FILTER IN THE RECEIVER 1 L 7 1 3O 3 O A3SO E295 5 C P920 1997010200062 19970102 00062 1997 1 2 AU960705 4 19960517 G 3452 RT359A TRANSPONDER CESSNA 182 182R 2072731 CE DEPDNT POSN DATA FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S 29367 (AUS) TRANSPONDER FAILED DUE TO UNSERVICEABLE CAVITY 1 L 7 1 3O NT 3A13 1997010200063 19970102 00063 EU 1997 1 2 AU960706 1 19960503 G 3242 16424A BRAKE DISC PARTEN P68 P68B EU LYC O360 IO360A1B6 41514 EA HARTZL HCC2Y HCC2YK2 GL LG WHEEL/BRAKE S CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH AND RH BRAKE DISCS CORRODED THROUGH IN AREA OF WELD 1 H 7 2 3O 3 O A31EU 1E10 5 C P920 1997010200064 19970102 00064 NM 1997 1 2 AU960707 1 19960127 G 5720 CHORD BOEING 727 727277 138408S NM PWA JT8 JT8D15 52051 NE WING LE SYS CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RH WING LEADING EDGE RIB 'T' AT STN 269.298 CORRODED ON THE BOTTOM FLANGE - FURTHER INVESTIGATION FOUND A SECTION OF THE CHORD APPROXIMATELY 152.4MM (6IN) FROM THE WING FRONT SPAR AND APPROXIMATELY 50.8MM (2IN) IN LENGTH COMPLETELY C ORRODED AWAY 2 L 7 3 4F 4 F RT A3WE E2EA 1997010200065 19970102 00065 EA 1997 1 2 AU960708 2 19960503 G 8540 GEAR PARTEN P68 P68B EU LYC O360 IO360A1B6 41514 EA HARTZL HCC2Y HCC2YK2 GL R ENGINE REAR SE WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH ENGINE STARTER RING GEAR WORN - BENDIX DRIVE GEAR ON STARTER MOTOR ALSO WORN - ENGINE HAD DIFFICULTY IN CRANKI NG 1 H 7 2 3O 3 O A31EU 1E10 5 C P920 1997010200066 19970102 00066 EU 1997 1 2 AU960709 1 19960503 G 2434 ALTERNATOR PARTEN P68 P68B EU LYC O360 IO360A1B6 41514 EA HARTZL HCC2Y HCC2YK2 GL AC GENERATOR-ALT FAULTY W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) LH ENGINE DRIVEN ALTERNATOR FAULTY - ALTERNATOR HOUSING LOOSE DUETO LOOSE RETAINING BOLTS AND A WORN ALTERNATOR AT TACHMENT HOUSING- THE REPLACEMENT ALTERNATOR WAS SUPPLIED WITHOUT TAGS AND ON INSPECTION WAS FOUND TO BE INCORRECTLY AS SEMBLED AND THE ATTACHMENT HOLE IN THE HOUSING HAD BEEN ILLEGALY REWORKED - SUSPECT BY AN AUTOMOTIVE REPAIRER - PERSONN EL/MAINTENANCE ERROR -UNAPPROVED PART 1 H 7 2 3O 3 O A31EU 1E10 5 C P920 1997010200067 19970102 00067 EU 1997 1 2 AU960710 1 19960503 G 7110 COWLING PARTEN P68 P68B EU LYC O360 IO360A1B6 41514 EA HARTZL HCC2Y HCC2YK2 GL ENGINE COWL SYS CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH AND RH ENGINE TOP COWLS BADLY CORRODED AND CRACKED - LH ENGINEOIL DIPSTICK ACCESS DOOR TORN AND ALMOST SEPARATE D 1 H 7 2 3O 3 O A31EU 1E10 5 C P920 1997010200068 19970102 00068 GL 1997 1 2 AU960711 3 19960503 G 6110 PROPELLER LYC PARTEN P68 P68B EU LYC O360 IO360A1B6 41514 EA HARTZL HCC2Y HCC2YK2 GL PROPELLER ASSY S INCORRECT ASSY W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S AV3743 (AUS) LH ENGINE PROPELLER INCORRECTLY ASSEMBLED - PROPELLER FEATHERED DURING LANDING CAUSING ENGINE TO STALL - PROPELLE R WOULD NOT FULLY FEATHER AND WOULD NOT RELATCH INTO NORMAL POSITION WHEN UNFEATHERED - INVESTIGATION FOUND INCORRECT A SSEMBLY, LEAKINGGREASE, INOPERATIVE LATCHING MECHANISM, WORN PISTON AND INCORRECTBLADE ANGLES - PERSONNEL/MAINTENANCE ER ROR 1 H 7 2 3O 3 O A31EU 1E10 5 C P920 1997010200069 19970102 00069 EU 1997 1 2 AU960712 1 19960503 G 2710 CONTROL CABLE PARTEN P68 P68B 6780104 EU LYC O360 IO360A1B6 41514 EA HARTZL HCC2Y HCC2YK2 GL AILERON CONTROL WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) AILERON BALANCE CABLE FAULTY - CABLE WORN BEYOND LIMITS IAW AD/P68/23 AMDT2 - TURNBUCKLE NOT IN SAFETY (TOO SHORT ) - SIX THREADS SHOWING EITHER SIDE OF TURNBUCKLE - PERSONNEL/MAINTENANCEERROR 1 H 7 2 3O 3 O A31EU 1E10 5 C P920 1997010200070 19970102 00070 EA 1997 1 2 AU960713 2 19960503 G 8500 ENGINE LYC PARTEN P68 P68B EU LYC O360 IO360A1B6 41514 EA HARTZL HCC2Y HCC2YK2 GL ENGINE (RECIPROC INCORRECT DATA W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH AND RH ENGINE DATA PLATES CONTAINED DIFFERENT TIMING DATA - BOTH ENGINES ARE IDENTICAL TYPES - ONE DATA PLATE S TATES 20DEGREES WHILE THE OTHER STATES 25 DEGREES 1 H 7 2 3O 3 O A31EU 1E10 5 C P920 1997010200071 19970102 00071 EU 1997 1 2 AU960714 1 19960503 G 2822 C8100F PUMP WELDON C8100F PARTEN P68 P68B EU LYC O360 IO360A1B6 41514 EA HARTZL HCC2Y HCC2YK2 GL FUEL DISTRBUTION LEAKING W K NONE O K OTHER FLUID LOSS IN INSP/MAINT 1 AU S 13A1229 (AUS) LH AND RH FUEL PUMPS LEAKING EXCESSIVELY FROM GRAVITY DRAINS - PUMPS ARE LOCATED IN THE ENGINE BAY ADJACENT TO THE MUFFLERSYSTEM 1 H 7 2 3O 3 O A31EU 1E10 5 C P920 1997010200072 19970102 00072 EA 1997 1 2 AU960715 2 19960503 G 8530 LW12987 CYLINDER PARTEN P68 P68B EU LYC O360 IO360A1B6 41514 EA HARTZL HCC2Y HCC2YK2 GL R ENG CYLINDER CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE CYLINDERS CRACKED AND CORRODED:- 1. TWO CYLINDERS EXCESSIVELY CORRODED/RUSTED IN AREA OF CYLINDER BASE 2 . ONE CYLINDER CRACKED IN AREA OF UPPER SPARK PLUG HOLE 3. ONE CYLINDER CRACKED FROM EXHAUST PORT BETWEEN COOLING FINSAN D BADLY CORRODED IN THE AREA OF THE EXHAUST PORT FLANGE 1 H 7 2 3O 3 O A31EU 1E10 5 C P920 1997010200073 19970102 00073 EU 1997 1 2 AU960716 1 19960503 G 5712 RIB PARTEN P68 P68B EU LYC O360 IO360A1B6 41514 EA HARTZL HCC2Y HCC2YK2 GL OUTER WING SYS INCORRECT MOD W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) RH WING RIB LOCATED IN ENGINE BAY ILLEGALLY MODIFIED - A HOLE HAD BEEN DRILLED THROUGH THE RIB STAINLESS STEEL FIR E BARRIER TO FACILITATE PUSHROD REMOVAL - THE HOLE WAS LEFT UNCOVERED ALLOWINGA POSSIBLE ENGINE FIRE TO PENETRATE TO THE FIBREGLASS LEADINGEDGE AREA CONTAINING FUEL PLUMBING - PERSONNEL/MAINTENANCE ERROR - UNAPPROVED MODIFICATION 1 H 7 2 3O 3 O A31EU 1E10 5 C P920 1997010200074 19970102 00074 EU 1997 1 2 AU960717 1 19960503 G 6120 75167 PIPE PARTEN P68 P68B EU LYC O360 IO360A1B6 41514 EA HARTZL HCC2Y HCC2YK2 GL PROP CNTRL SYS CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) PROPELLER CONSTANT SPEED UNIT (CSU) RIGID PIPE, STEEL 'B' NUTS AND SLEEVE BADLY CORRODED/RUSTED 1 H 7 2 3O 3 O A31EU 1E10 5 C P920 1997010200075 19970102 00075 EA 1997 1 2 AU960718 2 19960503 G 7314 AC6441271 PUMP PARTEN P68 P68B EU LYC O360 IO360A1B6 41514 EA HARTZL HCC2Y HCC2YK2 GL ENG,FUEL DIST SY LOOSE SCREWS W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH AND RH ENGINE DRIVEN FUEL PUMP COVER SCREWS LOOSE 1 H 7 2 3O 3 O A31EU 1E10 5 C P920 1997010200076 19970102 00076 EA 1997 1 2 AU960719 2 19960417 G 8520 72877 TAPPET PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA HARTZL HCE3Y HCE3YR2 GL R ENGINE POWER S FAILED W K NONE E VIBRATION/BUFFET CR CRUISE 1 AU S 1739 L254668A (AUS) RH ENGINE NO4 CYLINDER EXHAUST TAPPET BODY FAILED ALLOWING EXHAUST VALVE TO REMAIN CLOSED 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 1997010200077 19970102 00077 SO 1997 1 2 AU960720 1 19960123 G 5720 62129008 STIFFENER PIPER PA32 PA32300 7103212 SO LYC O540 IO540K1A5 41532 EA HARTZL HCC2Y HCC2YK1 GL OUTER WING SYS CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH WING REAR SPAR STIFFENER CRACKED AND CORRODED - STEEL REAR SPAR BRACKET CONTAINED MINOR CORROSION - FOUND DURI NG INSPECTION IAW AD/PA32/27 AMDT1 1 L 7 1 3O 3 O A3SO 1E4 5 C P920 1997010200078 19970102 00078 EA 1997 1 2 AU960721 2 19960525 G 7414 M3525 COIL SLICK LYC O360 AEIO360B2F 41514 EA ELEC PWR SUPPLY CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 89090006 L2368351A (AUS) RH MAGNETO COIL CRACKED 3 O 1E10 1997010200079 19970102 00079 NM 1997 1 2 AU960722 1 19960111 G 5330 SKIN BOEING 727 727277 138408S NM PWA JT8 JT8D15 52051 NE EXT PLATES/SKIN CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) AIRCRAFT LOWER SKIN CORRODED AND SPLIT IN THE AREA OF THE LH RAM AIR INTAKE BETWEEN STRINGERS 27LH AND 28LH AT FRA ME AT STN 700 - AREA OF CORROSION APPROXIMATELY 50.8MM BY 76.2MM (2IN BY 3IN) - INVESTIGATION FOUND THAT THE EXFOLIATIO N CORROSION WAS CAUSED BY A SALT WATER SPILL ORIGINATING FROM THE CARGO 2 L 7 3 4F 4 F RT A3WE E2EA 1997010200080 19970102 00080 EU 1997 1 2 AU960723 1 19960331 G 2435 8374 GENERATOR LEARSIEGLER 23079005 BAG JETSTM JETSTM3107 1500215 EU ROTOL R333 R333482F12 GL START/GENERATO FAILED W K NONE H ELECT. POWER LOSS-50 PC CL CLIMB 1 AU S 457 8374 (AUS) LH ENGINE STARTER/GENERATOR FAILED 2 L 7 2 4T RT BA15CAA 6 C P61GL 1997010200081 19970102 00081 1997 1 2 AU960724 4 19960504 G 3130 1574 RECORDER GARRTT 9804100FHV BAG JETSTM JETSTM3107 1500215 EU ROTOL R333 R333482F12 GL DATA RECORDER SY FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S 763 1574 (AUS) FLIGHT DATA RECORDER FAULTY - FAILURE WARNING LIGHT ILLUMINATED 2 L 7 2 4T RT BA15CAA 6 C P61GL 1997010200082 19970102 00082 SO 1997 1 2 AU960725 2 19960524 G 8530 646657 CYLINDER CESSNA 185 A185F 2072821 CE CONT O520 IO520D 17032 SO MCAULY D3A34 D3A34C403 GL R ENGINE CYLINDE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 780 552106 (AUS) ENGINE CYLINDER CRACKED FROM SPARK PLUG HOLE 1 H 7 1 3O 3 O 3A24 E5CE 5 C P47GL 1997010200083 19970102 00083 SO 1997 1 2 AU960726 2 19960317 G 8550 SPRING CONT CESSNA 402 402B 207590P CE CONT O520 TSIO520E 17040 SO MCAULY 3AF32C 3AF32C87 GL R ENGINE INT OIL WRONG PART W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S 275442R 275442R (AUS) ENGINE OIL PRESSURE RELIEF VALVE SPRING WAS AN INCORRECT PART - FOUND DURING POST INSTALLATION GROUND RUN - ENGIN E WAS A FACTORY REMANUFACTURED ENGINE - PERSONNEL/MAINTENANCE ERROR - UNAPPROVED PART 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 1997010200084 19970102 00084 1997 1 2 AU960727 1 19960528 G 7820 MUFFLER LYC O360 O360A1F6 41514 EA HARTZL HCF2Y HCF2YR1 GL ENG NOISE SUPPRS FAILED W K NONE E VIBRATION/BUFFET LD LANDING 1 AU S (AUS) RH EXHAUST MUFFLER ASSEMBLY FAILED AT FORWARD END IN AREA OF INLET PIPE TO END PLATE WELDED JOINT 3 O E286 5 C P27EA 1997010200085 19970102 00085 EU 1997 1 2 AU960728 1 19960528 G 3201 11505012 SUPPORT GROB G115 G115C 1660303 EU LYC O360 O360A1F6 41514 EA HARTZL HCF2Y HCF2YR1 GL FAIRING SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH WHEEL SPAT SUPPORT BRACKET CRACKED 1 L 7 1 3O 3 O NT A57EU E286 5 C P27EA 1997010200086 19970102 00086 EU 1997 1 2 AU960729 1 19960527 G 3201 11505013 SUPPORT GROB G115 G115C 1660303 EU LYC O360 O360A1F6 41514 EA HARTZL HCF2Y HCF2YR1 GL FAIRING SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RH WHEEL SPAT SUPPORT BRACKET CRACKED 1 L 7 1 3O 3 O NT A57EU E286 5 C P27EA 1997010200087 19970102 00087 NM 1997 1 2 AU960730 1 19960521 G 5610 8SC0043012 WINDSHIELD DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE FLT CMPT WINDOW FAILED W K NONE B A SMOKE/FUMES/ODORS/SPARKS FLAME/FIRE CR CRUISE 1 AU S (AUS) RH FORWARD COCKPIT WINDSCREEN SHORT CIRCUITED WHEN HEATER TURNED FROM 'WARM UP' TO 'NORMAL' - FLASH FROM TERMINALS WAS FOLLOWED BYA FIRE - WINDSCREEN WAS ALSO CRACKED CIRCUMFERENTIALLY FOLLOWED BY SHATTERING OF THE OUTER PANEL - SUSP ECT CAUSED BY MOISTURE INGRESS INTO THE INTERNAL BUSBAR CAUSING SHORT CIRCUIT 2 H 7 2 4T 4 T RT A13NM E20NE 1997010200088 19970102 00088 NM 1997 1 2 AU960731 1 19960513 G 7910 3006084 CAP DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE AC,ENG OIL TANK DAMAGED W K NONE E K J VIBRATION/BUFFET FLUID LOSS WARNING INDICATION CL CLIMB 1 AU S 120032 (AUS) ENGINE OIL FILLER CAP LUG BROKEN - LOSS OF APPROXIMATELY THREE LITRES OF OIL 2 H 7 2 4T 4 T RT A13NM E20NE 1997010200089 19970102 00089 EU 1997 1 2 AU960732 1 19960529 G 2730 115C4412 CONTROL ROD GROB G115 G115C 1660303 EU LYC O360 O360F1A6 41514 EA HARTZL HCF2Y HCF2YR1 GL ELEVATOR CONTROL DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ELEVATOR CONTROL ROD DAMAGED BY POP RIVET IN AREA OF FUSELAGE STATION ME 6150MM - THE POP RIVET IS USED AS A LIMI T STOP FOR ASLIDING TUBE BEARING 1 L 7 1 3O 3 O NT A57EU E286 5 C P27EA 1997010200090 19970102 00090 NM 1997 1 2 AU960733 1 19960516 G 3244 319K281 TYRE 314353 DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE LG WHEEL/BRAKE S LEAKING W K NONE O OTHER IN INSP/MAINT 1 AU S 1926 (AUS) RH MAIN LANDING GEAR INBOARD TYRE LEAKING EXCESSIVELY THROUGH SIDEWALL PLY VENTS - TYRE WENT COMPLETELY FLAT 2 H 7 2 4T 4 T RT A13NM E20NE 1997010200091 19970102 00091 1997 1 2 AU960734 1 19960529 G 7160 115C6662 AIR BOX LYC O360 O360A1F6 41514 EA HARTZL HCF2Y HCF2YR1 GL ACFT,ENG AIR INT CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) CARBURETTOR AIR BOX CRACKED FROM BEND RELIEF HOLES 3 O E286 5 C P27EA 1997010200092 19970102 00092 1997 1 2 AU960735 4 19960530 G 3452 TR661A TRANSPONDER PIPER PA28 PA28151 7102805 SO LYC O320 O320E3D 41508 EA DEPDNT POSN DATA FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S 5024 (AUS) TRANSPONDER NOT WORKING - INVESTIGATION FOUND OFF/ON/MODEC/TEST SELECTOR ON FRONT FACE NOT CONNECTED TO SWITCH WA FER ON PCB DUETO OVERLOAD FAILURE OF THE SWITCH SHAFT 1 L 7 1 3O 3 O 2A13 E274 1997010200093 19970102 00093 SO 1997 1 2 AU960736 2 19960529 G 8520 CRANKCASE CESSNA 182 182K 2072724 CE CONT O470 O470R 17026 SO MCAULY 2A34C 2A34C66 GL R ENGINE POWER S CRACKED W K NONE E K VIBRATION/BUFFET FLUID LOSS NR NOT REPORTED 1 AU S 191100 (AUS) CRANKCASE CRACKED IN AREA OF NO1 BEARING - CRACK ALSO IN CRANKCASE TOP FLANGE AT 7TH HOLE FROM THE FRONT - NO1 BEA RINGSPINNING AND BREAKING UP - FRETTING OF CRANKCASE MATING FACES INDICATES EXCESSIVE MOVEMENT POSSIBLY DUE TO INSUFFIC IENT THROUGHBOLT TENSION 1 H 7 1 3O 3 O NT 3A13 E273 5 C P3EA 1997010200094 19970102 00094 GL 1997 1 2 AU960737 3 19960524 G 6110 O-RING MCAULY CESSNA 310 310L 2074230 CE CONT O470 IO470U 17026 SO MCAULY 3AF32C D3AF32C80 GL PROPELLER ASSY S WRONG PART W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S 711057 711057 (AUS) PROPELLER CONTAINED THE FOLLOWING FAULTS:- 1. INCORRECT RETENTION NUT 'O' RINGS FITTED2. RETENTION NUT NOT TORQUED 3. NO MOLY KOTE LUBRICANT ON FERRULE THREADS OR BLADE THREADS4. OLD TYPE PRESSURE LATCH STILL FITTED - SHOULD HAVE BEEN REPLACED WITH LATEST CENTRIFUGAL LATCH AS PER MANUAL 710930 5. ACTUATING PIN DEPTH IN FERRULE EXCEEDS MAXIMUM PERMITTED PERSONNEL/MAINTENANCE ERROR - UNAPPROVED PART 1 L 7 2 3O 3 O 3A10 3E1 5 C P22EA 1997010200095 19970102 00095 GL 1997 1 2 AU960738 3 19960523 G 6114 AU3908 HUB PIPER PA34 PA34200 7103405 SO CONT O360 IO360C 17025 SO HARTZL HCC2Y HCC2YK2 GL PROPELLER ASSY S ILLEGAL REPAIR W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S AU3908 AU3908 (AUS) PROPELLER LEAKING OIL - INVESTIGATION FOUND THAT THE PROPELLER HUB HAD BEEN ILLEGALY REPAIRED/MODIFIED BY MACHININ G IN THEPRELOAD PLATE AREA - SUSPECT HUB HAD SUFFERED FROM A PREVIOUS GROUND STRIKE - PERSONNEL/MAINTENANCE ERROR - UNA PPROVED REPAIR 1 L 7 2 3O 3 O A7SO E1CE 5 C P920 1997010200096 19970102 00096 SW 1997 1 2 AU960739 1 19960228 G 6120 7715979002 VALVE GARRTT FRCHLD SA227 SA227DC 3377521 SW MCAULY 4HFR34 4HFR34C652 NE PROP CNTRL SYS STICKING W K NONE E VIBRATION/BUFFET TO TAKEOFF 1 AU S 931689 (AUS) PROPELLER CONTROL UNIT CHECK VALVE STICKING 2 L 7 2 4T RT A18SW 6 C 3PNE 1997010200097 19970102 00097 NM 1997 1 2 AU960740 1 19960517 G 2140 DUCT PIPER PA60 PA60600A 7106002 NM LYC O540 IO540S1A5 41532 EA HEATING SYSTEM CRACKED W A K NONE B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 AU S (AUS) CABIN HEATER DUCTING CRACKED - HOT AIR CAUSED FREIGHT TO SMOULDER 1 M 7 2 3O 3 O RT A17WE 1E4 1997010200098 19970102 00098 1997 1 2 AU960741 4 19960515 G 2565 B101124 SLIDE BOEING 767 767238 NM PWA JT9 JT9D7R4E 52054 NE EMERGENCY EQUIP FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S B101124 (AUS) LH OFF WING SLIDE FAULTY - SLIDING SURFACE DEFECTIVE 2 L 7 2 4F 4 F RT A1NM E3NE 1997010200099 19970102 00099 NM 1997 1 2 AU960742 1 19960512 G 3210 BOLT BOEING 747 747238B 1384828 NM MAIN GEAR SYS LOOSE W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NO10 MAIN WHEEL RETAINING AXLE NUT LOCKING BOLTS LOOSE - HUBCAP CRACKED IN SEVERAL PLACES 2 L 7 4 4F A20WE 1997010200100 19970102 00100 1997 1 2 AU960743 4 19960523 G 2565 SLIDE BOEING 747 747438 NM EMERGENCY EQUIP FAULTY W A K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH AND RH NO3 MAIN ENTRY DOOR ESCAPE SLIDES WOULD NOT DEPLOY DURING TEST - DOOR POWER ASSIST BOTTLES WOULD NOT FIR E 2 L 7 4 4F RT A20WE 1997010200101 19970102 00101 NE 1997 1 2 AU960744 2 19960509 G 7240 LINER RROYCE RB211 RB211524G19 NE TURBINE ENGINE C DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S 13059 (AUS) NO1 ENGINE COMBUSTION LINER HEAD DAMAGE EXCEEDED MAINTENANCE MANUAL LIMITS - FOUND DURING BOROSCOPE INSPECTION IAW AD/RB211/19AMDT1 AND ROLLS ROYCE SERVICE BULLETIN RB211-72-B482 4 F E30NE 1997010200102 19970102 00102 SO 1997 1 2 AU960745 1 19960514 G 7931 APT79100080D TRANSMITTER EMB 120 EMB120 3260201 SO PWA 118 PW118A NE ENG OIL IND SYS FLUCTUATES W K NONE O OTHER CL CLIMB 1 AU S 338612179 (AUS) RH ENGINE OIL PRESSURE TRANSMITTER FLUCTUATING 2 L 7 2 4T 4 T RT A31SO E20NE 1997010200103 19970102 00103 WP 1997 1 2 AU960746 1 19960526 G 6220 362093 CONTROL ROTOR HILLER HILLER UH12 UH12E 4360122 WP LYC O540 VO540C2A 41532 EA MAIN ROTOR HEAD CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 10068 (AUS) MAIN ROTOR HEAD CONTROL ROTOR CRACKED AT SPAR END THROUGH THE FIRST BOLT HOLE FOR APPROXIMATELY 50% OF CIRCUMFERE NCE - FOUND DURING INSPECTION IAW AD/HIL12/17 AMDT4 1 G 7 1 3O 3 O 4H11 E304 1997010200104 19970102 00104 CE 1997 1 2 AU960747 1 19960521 G 2720 12604188 TORQUE TUBE CESSNA 210 210N 2073453 CE CONT O520 IO520L 17032 SO MCAULY D3A34 D3A34C404 GL RUDDER CONTROL S BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RH RUDDER TORQUE TUBE FAILED IN AREA OF WELD ATTACHING THE MAIN TUBE TO THE SHORT VERTICAL STUB - VERTICAL STUB I S BOLTED TO THE RH RUDDER PEDAL 1 H 7 1 3O 3 O 3A21 E5CE 5 C P47GL 1997010200105 19970102 00105 WP 1997 1 2 AU960748 1 19960402 G 6220 5143711 ROTOR HUB HILLER HILLER UH12 UH12E 4360122 WP LYC O540 VO540C2A 41532 EA MAIN ROTOR HEAD CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 773 10452 (AUS) MAIN ROTOR HUB CRACKED IN AREA OF THREADED CUFF AND TRUNNION BOLTHOLE EXTENDING DOWN THE INNER HUB SURFACE - CRACK LENGTH APPROXIMATELY 6.35MM (0.25IN) - FOUND DURING INSPECTION IAW AD/HIL12/22A 1 G 7 1 3O 3 O 4H11 E304 1997010200106 19970102 00106 SO 1997 1 2 AU960749 2 19960522 G 8540 531178 RETAINER CONT CESSNA 404 404CESSNA 2075901 CE CONT O520 GTSIO520M 17032 SO MCAULY 3FF32 3FF32C501 GL R ENGINE REAR SE BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S 1458 606607 606607 (AUS) ENGINE LH MAGNETO DRIVE CUSHION RETAINER FAILED 1 L 7 2 3O 3 O A25CE E7CE 5 C P45GL 1997010200107 19970102 00107 CE 1997 1 2 AU960750 1 19960520 G 2910 510011171 PIPE CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO MCAULY 3AF32C 3AF32C505 GL MAIN HYD SYS FRACTURED W K NONE O K J OTHER FLUID LOSS WARNING INDICATION DE DESCENT 1 AU S (AUS) LH HYDRAULIC SYSTEM PRESSURE PIPE LEAKING - LOSS OF HYDRAULIC FLUID 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 1997010200108 19970102 00108 1997 1 2 AU960751 1 19960528 G 6120 G9811P16 PIN HAMSTD 14SF 14SF23 NE PROP CNTRL SYS FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NO2 ENGINE PROPELLER FEATHER CONTROLLER PLUG FAULTY DUE TO UNDERSIZE PIN AT G9811-P16 6 C P7NE 1997010200109 19970102 00109 EU 1997 1 2 AU960752 1 19960517 G 5713 STRINGER PARTEN P68B PARTEN P68 P68B EU LYC O360 IO360A1B6 41514 EA HARTZL HCC2Y HCC2YK2 GL OUTER WING SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) WING UPPER SKIN STRINGERS CRACKED - UPPER WING SKIN ALSO CRACKED - FOUND DURING INSPECTION IAW AD/P68/42 1 H 7 2 3O 3 O A31EU 1E10 5 C P920 1997010200110 19970102 00110 SW 1997 1 2 AU960753 1 19960314 G 3230 790270505 CYLINDER GULSTM 500 500S 0141107 SW LYC O540 IO540K1A5 41532 EA HARTZL HCA3V HCA3VK2 GL LG EXT-RETRACT S DAMAGED W K NONE O OTHER LD LANDING 1 AU S (AUS) NOSE LANDING GEAR RETRACTION CYLINDER SHAFT BENT - NOSE LANDING GEAR COLLAPSED DURING LANDING ROLL - SUSPECT SHAF T PREVIOUSLY BENT BY TOWING INCIDENT OR HEAVY LANDING 1 H 7 2 3O 3 O 6A1 1E4 5 C P6EA 1997010200111 19970102 00111 EU 1997 1 2 AU960754 1 19960425 G 2150 8182833ANSN TURBINE NORMALAIR BAC 146 146300A 1500267 EU LYC ALF502 ALF502R5 41580 NE CABIN COOLING SY SEIZED W A K NONE O OTHER CL CLIMB 1 AU S 10814 8182833AN (AUS) RIVET ATTACHING BAFFLE TO PLENUM/TORUS FAILED AND WAS INGESTED BYTHE RH AIRCONDITIONING PACK COOLING TURBINE CAUSI NG IT TO SEIZE -INVESTIGATION FOUND THAT THE PLENUM/TORUS BAFFLE ASSEMBLY PNO 1344D710 CAME LOOSE DUE TO THE FAILURE OF THE ATTACHMENT RIVETS AND HAD CUT THROUGH THE PLENUM/TORUS OUTER SKIN ALLOWING THE RIVET HEADS TO ENTER AND DAMAGE THE TURBINE - THE MUFF INLET PIPEWAS ALSO FOUND TO BE CRACKED DUE TO THE SEVERE VIBRATION 2 H 7 4 4F 4 F RT A49EU E6NE 1997010200112 19970102 00112 SW 1997 1 2 AU960755 1 19960603 G 3240 2785004079 PIPE FRCHLD SA227 SA227DC 3377521 SW GARRTT TPE331 TPE33112UA 01514 WP MCAULY 4HFR34 4HFR34C652 NE LG WHEEL/BRAKE S CHAFED THRU W K NONE O OTHER LD LANDING 1 AU S (AUS) LH BRAKE SYSTEM HYDRAULIC PIPE CHAFED THROUGH BY ELEVATOR CONTROL CABLE - LOSS OF HYDRAULIC FLUID - SUSPECT PIPE D AMAGED DURING AIRCRAFT ASSEMBLY CAUSING IT TO COME IN CONTACT WITH THE ELEVATOR CABLE 2 L 7 2 4T 4 T RT A18SW E4WE 6 C 3PNE 1997010200113 19970102 00113 NM 1997 1 2 AU960756 1 19960601 G 2612 8987322 CIRCUIT BOARD V61423 BOEING 767 76733A NM PWA 4056 PW4056 NE FIRE DETECTION S FAULTY W F ACTIVATE FIRE EXT. N FALSE WARNING DE DESCENT 1 AU S 2518M683P P727317 (AUS) RH ENGINE FIRE DETECTION SYSTEM PRINTED CIRCUIT CARD M683 IN P54 CARD RACK FAULTY - FALSE FIRE WARNING ON RH ENGIN E RESULTED IN DISCHARGE OF BOTH FIRE BOTTLES 2 L 7 2 RT 4 F RT A1NM E24NE 1997010200114 19970102 00114 1997 1 2 AU960757 4 19960525 G 2213 6224717003 MODE CONTROL BOEING 757 757200 1384950 NM FLIGHT CONTROLLE FAULTY W K NONE F FLT CONT AFFECTED CL CLIMB 1 AU S 6224717003 (AUS) AUTOPILOT SYSTEM MODE CONTROL PANEL (MCP) FAULTY DUE TO FAILURE OF 'POWER DROP OUT TEST' - A9Q204AND M12 REPLACED 2 L 7 2 4F RT A2NM 1997010200115 19970102 00115 SO 1997 1 2 AU960758 1 19960516 G 3211 225200 STUD PIPER PA30 PA30 7103002 SO LYC O320 IO320B1A 41508 EA HARTZL HCE2Y HCE2YL2 GL MAIN GEAR SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH AND RH MAIN LANDING GEAR SIDE BRACE STUDS CRACKED - FOUND DURING MAGNETIC PARTICLE INSPECTION IAW AD/PA30/34 1 L 7 2 3O 3 O A1EA 1E12 5 C P9EA 1997010200116 19970102 00116 SO 1997 1 2 AU960759 2 19960331 G 8530 629404 VALVE CESSNA 172 172 2072402 CE CONT O300 O300A 17022 SO MCAULY 1C172 1C172EM GL R ENG CYL EXH STICKING W K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CR CRUISE 1 AU S 100 12091D6B (AUS) EXHAUST VALVE STUCK - OTHER FIVE VALVES TIGHT IN VALVE GUIDES 1 H 7 1 3O 3 O NT 3A12 E253 5 N P910 1997010800003 19970108 00003 NE 1997 1 8 AU960761 2 19960509 G 8530 166313 PISTON PWA R2000 DOUG DC4 C54E 3021530 WP PWA R2000 R2000* 52023 NE HAMSTD 23E 23E50 NE R ENGINE CYLINDE BURNT W K NONE E K VIBRATION/BUFFET FLUID LOSS CL CLIMB 1 AU S 889 P107816 P107816 (AUS) NO4 ENGINE NO 10 CYLINDER PISTON BURNT - ENGINE OIL VENTING OVERBOARD 2 L 7 4 4R 4 R A762 5E5 6 C P603 1997010200117 19970102 00117 SO 1997 1 2 AU960762 1 19960528 G 5751 86399803 RIB PIPER 8656219 PIPER PA44 PA44180 7104402 SO LYC O360 O360E1A6 41514 EA HARTZL HCC2Y HCC2YR2 GL WING AIL/ELV SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 448195001 (AUS) AILERON RIBS PNO 86399-803 AND PNO 86399-003 CRACKED 1 L 7 2 3O 3 O A19S0 E286 5 C P920 1997010800011 19970108 00011 EU 1997 1 8 AU960763 1 19960529 G 7712 97521206 TRANSMITTER PILATS PC12 PC12 7090550 EU PWA PT6 PT6A67 52043 NE ENG PWR IND SYS FAULTY W K NONE O OTHER CR CRUISE 1 AU S (AUS) ENGINE TORQUE PRESSURE TRANSMITTER INTERNAL FAILURE 1 L 7 1 3T 4 T RT A78EU E26NE 1997010200459 19970102 00459 NM 1997 1 2 AU960764 1 19960520 G 5530 220000 HINGE 220018201 PIPER PA60 PA60600 7106001 NM LYC O540 IO540K1J5 41532 EA VERT STAB STRUCT CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FIN HINGE ASSEMBLIES CORRODED 1 M 7 2 3O 3 O RT A17WE 1E4 1997010200460 19970102 00460 NM 1997 1 2 AU960765 1 19960506 G 5330 SKIN BOEING 727 727277 138408S NM PWA JT8 JT8D15 52051 NE EXT PLATES-SKIN CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) REAR FUSELAGE LOWER SKIN CONTAINED EXFOLIATION CORROSION AT FUSELAGE STATION 1050 AND BENEATH STRINGER 27 - DURIN G PROBING INSPECTION SKIN BROKE AWAY LEAVING A 12.7MM (0.5IN) HOLE - SUSPECT CAUSED BY SALT WATER SPILLAGE 2 L 7 3 4F 4 F RT A3WE E2EA 1997010200461 19970102 00461 NE 1997 1 2 AU960766 2 19960519 G 7230 FAN BLADE BOEING 737 737377 NM GE CFM56 CFM563B1 13802 NE TURBINE ENGINE C BIRD STRIKE W K NONE E C VIBRATION/BUFFET F.O.D. TO TAKEOFF 1 AU S 721553 (AUS) NO2 ENGINE SUFFERED A BIRD STRIKE CAUSING SEVERE FAN BLADE DAMAGE - ONE FAN BLADE FRAGMENT EXITED FORWARD OF THE E NGINE AND PENETRATED THE NOSE AND FAN COWLS 2 L 7 2 4F 4 F RT A16WE E2GL 1997010200462 19970102 00462 NM 1997 1 2 AU960767 1 19960103 G 5320 BEAM BOEING 727 727277 138408S NM PWA JT8 JT8D15 52051 NE MAIN FRAME SYS CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) AIRCRAFT CONTAINED LEVEL 2 CORROSION ON LOWER CHORD OF CABIN FLOOR BEAM IN SECTION 46 - AREA OF CORROSION 508MM BY 25.4MM BY2.032MM (20IN BY 1IN BY 0.80IN) 2 L 7 3 4F 4 F RT A3WE E2EA 1997010200463 19970102 00463 EU 1997 1 2 AU960768 1 19960529 G 3150 TB11512 CONNECTOR PILATS PC12 PC12 7090550 EU CENTRAL WARNING FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) CENTRAL ADVISORY WARNING SYSTEM (CAWS) CONNECTOR HAD TWO PINS SHORTING OUT DUE TO FAILURE OF CONNECTOR INSULATION 1 L 7 1 3T RT A78EU 1997010200464 19970102 00464 EA 1997 1 2 AU960769 2 19960501 G 8520 LW11036S CRANKCASE GULSTM 500 500S 0141107 SW LYC O540 IO540E1B5 41532 EA R ENGINE POWER S CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 503 L632748C (AUS) ENGINE CRANKCASE CRACKED IN AREA OF NO2 CYLINDER FORWARD UPPER HOLD DOWN STUD HOLE - CRACK LENGTH 31.75MM (1.25IN) 1 H 7 2 3O 3 O 6A1 1E4 1997010200465 19970102 00465 SO 1997 1 2 AU960770 1 19960218 G 5610 8660804 WINDOW 8660217 PIPER PA44 PA44180 7104402 SO LYC O360 O360E1A6 41514 EA HARTZL HCC2Y HCC2YR2 GL FLT CMPT WINDOW BROKEN W K NONE D INFLIGHT SEPARATION CR CRUISE 1 AU S (AUS) PILOTS PERSPEX SIDE WINDOW FAILED AND PARTS SEPARATED FROM AIRCRAFT DUE TO CRAZING - WINDOW IS PART OF THE EMERGEN CY EXIT DOOR ASSEMBLY 1 L 7 2 3O 3 O A19S0 E286 5 C P920 1997010200466 19970102 00466 NM 1997 1 2 AU960771 1 19960103 G 5310 FUSELAGE BOEING 737 737377 NM FUSELAGE STRUCT CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUSELAGE CONTAINED LEVEL 2 CORROSION 2 L 7 2 4F RT A16WE 1997010200467 19970102 00467 NM 1997 1 2 AU960772 1 19960103 G 5310 FUSELAGE BOEING 737 737377 NM FUSELAGE STRUCT CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) AIRCRAFT CONTAINED LEVEL 2 CORROSION 2 L 7 2 4F RT A16WE 1997010200468 19970102 00468 CE 1997 1 2 AU960773 1 19960503 G 3230 12802061 GUIDE CESSNA 182 R182 2072734 CE LYC O540 O540J3C5 41532 EA LG EXT-RETRACT S DETERIORATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NOSE LANDING GEAR DOWNLOCK MECHANISM SPRING GUIDE CRACKED AND DISTORTED 1 H 7 1 3O 3 O RT 3A13 E295 1997010200469 19970102 00469 EU 1997 1 2 AU960774 2 19960329 G 7250 9527M50G07 NGV CFMINT CFM56 CFM563C 13802 EU TURBINE SECTION DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S 315 720724 (AUS) ENGINE HIGH PRESSURE TURBINE NOZZLE GUIDE VANES (23OFF) DAMAGED -NGVS HAD SEVERE TRAILING EDGE FALLOUT AND WERE DI STORTED 4 F E21EU 1997010200470 19970102 00470 CE 1997 1 2 AU960775 1 19960607 G 2430 WIRE CESSNA 210 210N 2073453 CE CONT O520 IO520L 17032 SO MCAULY D3A34 D3A34C404 GL AC GENERATOR-ALT DETERIORATED W K NONE O OTHER IN INSP/MAINT 1 AU S 280208R D3A34C4048 (AUS) ALTERNATOR BATTERY WIRE DETERIORATED INTERNALLY - WIRE FRACTURED AND ARCING 1 H 7 1 3O 3 O 3A21 E5CE 5 C P47GL 1997010200471 19970102 00471 CE 1997 1 2 AU960776 1 19960603 G 3222 NLG CESSNA 182 182M 2072728 CE CONT O470 O470R 17026 SO MCAULY 2A34C 2A34C66 GL NOSE-TAIL GEAR S SEPARATED W K NONE O D OTHER INFLIGHT SEPARATION LD LANDING 1 AU S (AUS) NOSE LANDING GEAR SEPARATED FROM AIRCRAFT DURING LANDING (TORN OFF) - SUSPECT CAUSED BY HEAVY LANDING AND/OR INCOR RECT LANDINGTECHNIQUE - PILOT ERROR 1 H 7 1 3O 3 O NT 3A13 E273 5 C P3EA 1997010200472 19970102 00472 SO 1997 1 2 AU960777 2 19960603 G 8530 649163A2 CYLINDER CONT IO470V0 CESSNA 310 310Q 2074242 CE CONT O470 IO470V 17026 SO MCAULY 3AF32C 3AF32C87 GL R ENGINE NR 5 SEPARATED W K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CR CRUISE 1 AU S 520 455399 520 (AUS) RH ENGINE NO5 CYLINDER HEAD SEPARATED FROM BARREL - SUSPECT PRE-EXISTING CRACK 1 L 7 2 3O 3 O 3A10 3E1 5 C P22EA 1997010200473 19970102 00473 SW 1997 1 2 AU960778 1 19960606 G 6220 206011113103 TRUNNION BELL BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL MAIN ROTOR HEAD CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S GDLM122299 833095 (AUS) MAIN ROTOR HUB TRUNNION CRACKED IN RADIUS - FAILURE ANALYSIS GROUP COULD FIND NO EVIDENCE OF CRACKING USING BOTH F LUORESCENTDYE PENETRANT AND MAGNETIC PARTICLE INSPECTION TECHNIQUES - THERE WAS EVIDENCE OF REWORK BY POLISHING - PART RETURNED TO BELLHELICOPTER FOR FURTHER INVESTIGATION 1 G 7 1 3U 3 U H2SW E4CE 1997010200474 19970102 00474 EA 1997 1 2 AU960779 2 19960530 G 7414 M3548 ROTOR SLICK 4370 PIPER PA28 PA28161 7102803 SO LYC O320 O320D3G 41508 EA SNSNCH 74D 74DM EA ELEC PWR SUPPLY FAILED W K NONE E VIBRATION/BUFFET TO TAKEOFF 1 AU S 238 95100288 L1185439A (AUS) MAGNETO ROTOR FAILED AT THE BASE OF THE CAM RECESS 1 L 7 1 3O 3 O 2A13 E274 5 N P88614 1997010200475 19970102 00475 CE 1997 1 2 AU960780 1 19960603 G 2612 303267 AMPLIFIER BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL FIRE DETECTION S FAULTY W K NONE O N OTHER FALSE WARNING CL CLIMB 1 AU S (AUS) RH ENGINE FIRE WARNING SYSTEM FIRE CONTROL AMPLIFIER FAULTY 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 1997010200476 19970102 00476 CE 1997 1 2 AU960781 1 19960601 G 2612 302158 FIRE DETECTOR BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL FIRE DETECTION S FAULTY W K NONE N FALSE WARNING CR CRUISE 1 AU S (AUS) RH ENGINE FORWARD UPPER DETECTOR FAULTY 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 1997010200477 19970102 00477 CE 1997 1 2 AU960782 1 19960606 G 2612 DETECTION SYSTEM BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL FIRE DETECTION S FAULTY W K NONE O N OTHER FALSE WARNING CR CRUISE 1 AU S (AUS) RH ENGINE FIRE DETECTION SYSTEM FAULTY - SEE MDR 96/0780 AND MDR 96/0781 FOR FURTHER INFORMATION 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 1997010200478 19970102 00478 CE 1997 1 2 AU960783 1 19960513 G 5340 0512122 BLOCK CESSNA CESSNA 172 172D 2072410 CE CONT O300 O300C 17022 SO MCAULY 1C172 1C172EM GL ATTACH FITTING S CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) CENTRE WING SPAR BEARING BLOCK CONTAINS SEVERE INTERGRANNULAR EXFOLIATION CORROSION 1 H 7 1 3O 3 O NT 3A12 E253 5 N P910 1997010200479 19970102 00479 CE 1997 1 2 AU960784 1 19960422 G 3230 583800901 MOTOR BEECH 58 58 1152740 CE CONT O520 IO520F 17032 SO LG EXT-RETRACT S FAULTY W K NONE O OTHER CL CLIMB 1 AU S 3976 (AUS) LANDING GEAR ELECTRIC MOTOR ARMATURE SEGMENT FAULTY 1 L 7 2 3O 3 O 3A16 E5CE 1997010200480 19970102 00480 SO 1997 1 2 AU960785 1 19960604 G 3213 TORQUE LINK PIPER PIPER PA28 PA28161 7102803 SO LYC O320 O320D3G 41508 EA SNSNCH 74D 74DM EA MAIN GEAR SYS SHEARED W K NONE O D OTHER INFLIGHT SEPARATION TO TAKEOFF 1 AU S (AUS) RH MAIN LANDING GEAR SEPARATED FROM AIRCRAFT DUE TO OLEO TOP TORQUE LINK SHEARING 1 L 7 1 3O 3 O 2A13 E274 5 N P88614 1997010200481 19970102 00481 SO 1997 1 2 AU960786 1 19960418 G 2432 G35 BATTERY PIPER PA28 PA28181 7102807 SO LYC O360 O360A4M 41514 EA SNSNCH 76E 76EM8 EA BATTERY/CHARGER OVERHEAT FIRE W K NONE B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 AU S (AUS) BATTERY CAUGHT FIRE DUE TO INCORRECT STARTING TECHNIQUE - START HELD ON CONTINUOUSLY - PERSONNEL ERROR 1 L 7 1 3O 3 O 2A13 E286 5 N P4EA 1997010200482 19970102 00482 GL 1997 1 2 AU960787 3 19960516 G 6110 A163570 SCREW MOONEY M20 M20J 5870219 SW LYC O360 IO360A3B6 41514 EA MCAULY 2D34C B2D34C214 GL PROPELLER ASSY S FAILED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S 832220 (AUS) PROPELLER CYLINDER RETAINING SCREWS (3OFF14) BROKEN - OTHER SCREWS (9OFF14) LOOSE - SUSPECT INSUFFICIENT TORQUE O N SCREWS AT LAST INSTALLATION - SOME FRETTING DAMAGE TO GASKET 1 L 7 1 3O 3 O 2A3 1E10 5 C P7EA 1997010200483 19970102 00483 CE 1997 1 2 AU960788 1 19960304 G 2913 105932E POWER PACK CESSNA 177 177RG 2073709 CE LYC O360 IO360A1B6 41514 EA MCAULY 2D34C B2D34C207 GL LG EXT-RETRACT S FAULTY W K NONE O OTHER LD LANDING 1 AU S 105932E (AUS) HYDRAULIC POWER PACK ELECTRIC MOTOR RUNNING SLOW - SLOW TO BUILD UP HYDRAULIC PRESSURE 1 H 7 1 3O 3 O A20CE 1E10 5 C P7EA 1997010200484 19970102 00484 SO 1997 1 2 AU960789 1 19960530 G 3411 FITTING PIPER PA28 PA28180 7102808 SO LYC O360 O360A3A 41514 EA SNSNCH 76E M76EMMS EA ENVIRONMENT DATA WRONG PART W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) AIRSPEED INDICATOR PITOT LINE FITTING AND PIPE INCORRECT AUTOMOTIVE PARTS - PERSONNEL/MAINTENANCE ERROR - UNAPPROV ED PART - FOUND DURING PITOT SYSTEM LEAK CHECK IAW AD/INST/8 1 L 7 1 3O 3 O 2A13 E286 5 N P4EA4 1997010200485 19970102 00485 SO 1997 1 2 AU960790 1 19960530 G 2820 PIPE PIPER PA28 PA28180 7102808 SO LYC O360 O360A3A 41514 EA SNSNCH 76E M76EMMS EA FUEL DISTRBUTION DAMAGED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) FUEL SUPPLY PIPE BETWEEN FUEL SHUTOFF AND FIREWALL BULKHEAD FITTING KINKED FROM HAND BENDING - PIPE IS MALLEABLE COPPER FITTED DURING MODIFICATION FOR USE OF MOGAS IAW FAA STC SA2660CE,SE2563CE AND SE2587CE - PERSONNEL/MAINTENANCE ER ROR 1 L 7 1 3O 3 O 2A13 E286 5 N P4EA4 1997010200486 19970102 00486 GL 1997 1 2 AU960793 1 19960509 G 5343 FITTING DHAV DHC1 DHC1TMK10 2801712 GL ATTACH FITTING S CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH MAIN LANDING GEAR SUPPORT CASTING CRACKED BEYOND LIMITS - FURTHER INVESTIGATION ALSO FOUND CRACKING IN THE RH M LG SUPPORTCASTING WHICH WAS WITHIN LIMITS - FOUND DURING X-RAY INSPECTION IAW AD/DHC1/28-4 1 L 7 1 3O EXPA1L71 1997010200487 19970102 00487 EU 1997 1 2 AU960794 1 19960604 G 2730 TRIM SYSTEM STBROS SD3 SD360 8100606 EU PWA PT6 PT6A65R 52043 EA HARTZL HCB5M HCB5MP3 GL ELEVATOR CONTROL STUCK W K NONE F FLT CONT AFFECTED TO TAKEOFF 1 AU S (AUS) ELEVATOR TRIM SYSTEM JAMMED - INVESTIGATION FOUND THE METAL PORTION OF A SMALL GLOBE IN THE CONSOLE WHICH MAY HAV E BEENCAUGHT IN THE CHAIN CAUSING THE PROBLEM BUT COULD FIND NO OTHER FAULTS WITH THE SYSTEM WHICH THEN OPERATED NORMAL LY 2 H 7 2 4T 4 T A41EU E4EA 6 C P44GL 1997010200488 19970102 00488 GL 1997 1 2 AU960795 3 19960611 G 6110 PROPELLER AMTR LNCAIR 320LANCAIR 056129G GL HARTZL HCF2Y HCF2Y* GL PROPELLER ASSY S WRONG PART W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S FE239 (AUS) INCORRECT PROPELLER FITTED TO AIRCRAFT - PROPELLER FITTED WAS A HARTZELL MODEL HC-F2YL-2/F7666A-4 - CORRECT PROPE LLER MODEL IS A HARTZELL MODEL HC-F2YL-1/F8468D-14 (DIFFERENT HUB, BLADES AND ANGLE SETTINGS) - HUB PNO C3230-6 - BLADE PNO F7666A-4 - PERSONNEL/MAINTENANCE ERROR - UNAPPROVED PART 1 L 7 1 3O RT EXPA1L71 5 C P27EA 1997010200489 19970102 00489 EU 1997 1 2 AU960796 1 19960510 G 5610 92274H8274ANS WINDSHIELD BAC 146 146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE FLT CMPT WINDOW FAILED W K NONE O OTHER LD LANDING 1 AU S 92274H8274 (AUS) LH `B' WINDSCREEN ARCED AT TOP LEFT HAND CORNER AND THEN THE OUTER GLASS PLY SHATTERED - SUSPECT FAILURE WAS HEAT RELATED 2 H 7 4 4F 4 F A49EU E6NE 1997010200490 19970102 00490 EA 1997 1 2 AU960797 2 19960606 G 8520 LW17760 CRANKSHAFT PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL R ENGINE POWER S FAILED W K NONE Y ENGINE STOPPAGE TO TAKEOFF 1 AU S L720561A (AUS) ENGINE CRANKSHAFT FAILED THROUGH WEBS OF NO1 AND NO2 BIG END JOURNALS - NO1 AND NO2 CYLINDERS AND CONNECTING RODS DAMAGED 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 1997010200491 19970102 00491 EU 1997 1 2 AU960798 1 19960429 G 5610 NP1701022 WINDSHIELD BAC 146 146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE FLT CMPT WINDOW FAILED W K NONE O OTHER CL CLIMB 1 AU S 90218H3813A (AUS) RH `B' WINDSCREEN OUTER GLASS PLY SHATTERED - SUSPECT CAUSED BY ARCING 2 H 7 4 4F 4 F A49EU E6NE 1997010200492 19970102 00492 SO 1997 1 2 AU960799 1 19960607 G 7602 24894007 CABLE PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA HARTZL HCE2Y HCE2YK2 GL POWER CONTROL SY BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RH ENGINE MIXTURE CONTROL INNER CABLE BROKEN APPROXIMATELY 10MM (0.39IN) FROM SWAGING TO CABLE CONTROL ROD AT THE ENGINE END 1 L 7 2 3O 3 O A20SO E14EA 5 C P9EA 1997010200493 19970102 00493 NM 1997 1 2 AU960800 1 19960601 G 2424 RH747 GCU BOEING 737 737476 NM AC REGULATOR FAULTY W K NONE H ELECT. POWER LOSS-50 PC CL CLIMB 1 AU S RH747 (AUS) ELECTRICAL SYSTEM SUFFERED MOMENTARY LOSS OF POWER ON SEVERAL OCCASIONS - SUSPECT CAUSED BY RH GENERATOR CONTROL UNIT (GCU) 2 L 7 2 4F RT A16WE 1997010200494 19970102 00494 CE 1997 1 2 AU960801 1 19960605 G 5730 SKIN CESSNA 402 402B 207590P CE MCAULY 3AF32C 3AF32C87 GL OUTER WING SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) UPPER WING SKINS CRACKED - WING ANGLE TO SKIN ATTACHMENT RIVET HOLES ELONGATED- FOUND DURING INSPECTION IAW AD/C40 0/105 AMDT1 (NOT APPLICABLE TO THIS AIRCRAFT SERIAL NUMBER) 1 L 7 2 3O A7CE 5 C P22EA 1997010200495 19970102 00495 1997 1 2 AU960802 4 19960531 G 3425 NK11062 EFIS SYSTEM BOEING 737 737376 NM INSTRUMENT PANEL FAILED W K NONE I FLT. ATTITUDE INST. CR CRUISE 1 AU S NK11062 (AUS) AUTOPILOT `B' DISCONNECTED - EFIS DISPLAYS BLANK - FLIGHT INSTRUMENTS FAILED - NIL CBS TRIPPED - AFTER 15 SECONDS NORMAL OPERATION WAS RESUMED - SUSPECT CAUSED BY FAULTY GCU 2 L 7 2 4F RT A16WE 1997010200496 19970102 00496 SO 1997 1 2 AU960803 1 19960605 G 5520 317912110 ELEVATOR PIPER PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2B 41532 EA HARTZL HCE3Y HCE3YR2 GL ELEVATOR STRUCT CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 317912110 (AUS) LH AND RH ELEVATORS CRACKED - FOUND DURING RADIOGRAPHIC INSPECTION IAW AD/PA31/126 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 1997010200497 19970102 00497 NE 1997 1 2 AU960804 2 19960604 G 7412 3038137 EXCITER DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE ELEC PWR SUPPLY FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S 2406 120122 (AUS) ENGINE IGNITION EXCITER BOX FAULTY 2 H 7 2 4T 4 T RT A13NM E20NE 1997010200498 19970102 00498 1997 1 2 AU960805 1 19960323 G 7930 230376303 HARNESS LYC ALF502 ALF502R5 41580 NE ENG OIL IND SYS DAMAGED W K NONE O K OTHER FLUID LOSS CR CRUISE 1 AU S LF05506A (AUS) NO1 ENGINE OIL INDICATION SYSTEM HARNESS DAMAGED AND SHORT CIRCUITING ON PYLON DRAIN PIPE ON FRONT RH COWLING 4 F E6NE 1997010200499 19970102 00499 NM 1997 1 2 AU960807 1 19960602 G 2913 GENM29503011 PUMP BOEING 737 737376 NM MAIN HYD SYS LEAKING W K NONE K FLUID LOSS CL CLIMB 1 AU S 157225B (AUS) ENGINE DRIVEN HYDRAULIC PUMP LEAKING FROM SPLINE DRIVE CAVITY - LOSS OF 'A' SYSTEM PRESSURE AND HYDRAULIC FLUID 2 L 7 2 4F RT A16WE 1997010200500 19970102 00500 SO 1997 1 2 AU960808 2 19960528 G 8530 646460 EXHAUST VALVE CONT PIPER PA34 PA34200T 7103406 SO CONT O360 TSIO360E 17025 SO HARTZL HCC2Y BHCC2YF2 GL R ENGINE CYLINDE FAILED W K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CR CRUISE 1 AU S 237339R AN444913 (AUS) LH ENGINE NO5 CYLINDER EXHAUST VALVE FAILED - SUSPECT CAUSED BY EXCESSIVE LEANING OF ENGINE 1 L 7 2 3O 3 O A7SO E9CE 5 C P920 1997010200501 19970102 00501 SO 1997 1 2 AU960809 1 19960503 G 5310 TUBE PIPER PA23 PA23250 7102308 SO LYC O540 IO540C4B5 41532 EA HARTZL HCE2Y HCE2YK2 GL MAIN FRAME SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUSELAGE STEP TUBE CRACKED - AIRCRAFT HAS BEEN MODIFIED IAW SB672AND AD/PA28/81 1 L 7 2 3O 3 O 1A10 1E4 5 C P9EA 1997010200502 19970102 00502 SO 1997 1 2 AU960810 1 19960503 G 3230 1742002 BRACE PIPER PA23 PA23250 7102308 SO LYC O540 IO540C4B5 41532 EA HARTZL HCE2Y HCE2YK2 GL MAIN GEAR SYS CRACKED W A K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MAIN LANDING GEAR DRAG LINK FITTING SUPPORT BRACE CRACKED IN AREA OF ATTACHMENT BOLT 1 L 7 2 3O 3 O 1A10 1E4 5 C P9EA 1997010200503 19970102 00503 SW 1997 1 2 AU960812 1 19960522 G 7810 4606AC CLAMP BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL T ENG CONE-PIPE FAILED W K NONE O OTHER LD LANDING 1 AU S CAE830380 (AUS) ENGINE EXHAUST CLAMP FAILED IN RIVETTED AREA DUE TO CORROSION FROM EXHAUST GASSES 1 G 7 1 3U 3 U H2SW E4CE 1997010200504 19970102 00504 1997 1 2 AU960813 4 19960301 G 6113 BULKHEAD BEECH 95 95B55 1152729 CE CONT O470 IO470L 17026 SO MCAULY 2AF34C 2AF34C55 GL PROPELLER ASSY S CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH AND RH SPINNER BULKHEADS CRACKED - SUSPECT CAUSED BY ROUGH RUNNING ENGINES 1 L 7 2 3O 3 O RT 3A16 3E1 5 C P5EA 1997010200505 19970102 00505 CE 1997 1 2 AU960814 1 19960301 G 5720 HINGE BEECH 95 95B55 1152729 CE CONT O470 IO470L 17026 SO MCAULY 2AF34C 2AF34C55 GL OUTER WING SYS WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH AND RH WING LOWER FORWARD SPAR TO LEADING EDGE `D' SECTION HINGE AND HINGE PINS WORN - MAXIMUM AMOUNT OF WEAR IS LOCATED BETWEEN WING ROOT TO JUST OUTBOARD OF ENGINE 1 L 7 2 3O 3 O RT 3A16 3E1 5 C P5EA 1997010200506 19970102 00506 CE 1997 1 2 AU960815 1 19960301 G 5540 NIAS5054J BEARING BEECH 95 95B55 1152729 CE CONT O470 IO470L 17026 SO MCAULY 2AF34C 2AF34C55 GL RUDDER STRUCT SY CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RUDDER BEARINGS (2OFF) CORRODED INTERNALLY - AIRCRAFT OPERATES IN A SALT LADEN ENVIRONMENT - SUSPECT BEARINGS ORIG INAL FITMENT 1 L 7 2 3O 3 O RT 3A16 3E1 5 C P5EA 1997010200507 19970102 00507 EU 1997 1 2 AU960816 1 19960611 G 2720 PEDAL FOKKER F27 F27MK50 EU COPILOT RUDDER MALFUNCTION W K NONE O OTHER CL CLIMB 1 AU S (AUS) INTERMITTENT KNOCKING NOISE COMING FROM COPILOTS RUDDER PEDAL AREA - INVESTIGATION COULD FIND NO FAULTS 2 H 7 2 4T RT A817 1997010200508 19970102 00508 EU 1997 1 2 AU960817 1 19960612 G 3234 114044003 VALVE FOKKER F27 F27MK50 EU LG EXT-RETRACT S FAULTY W K NONE O OTHER CL CLIMB 1 AU S (AUS) LANDING GEAR SELECTOR VALVE FAULTY - LANDING GEAR WOULD NOT RETRACT FOLLOWING `UP' SELECTION 2 H 7 2 4T RT A817 1997010200509 19970102 00509 SO 1997 1 2 AU960818 1 19960607 G 3230 14595 ACTUATOR EMB 110 EMB110P1 3260122 SO PWA PT6 PT6A34 52043 EA HARTZL HCB3T HCB3TN3 GL LG EXT-RETRACT S FAULTY W K NONE O N OTHER FALSE WARNING CR CRUISE 1 AU S 1454 (AUS) LH MAIN LANDING GEAR DOWNLOCK ACTUATOR FAULTY - MICROSWITCH STRIKER NOT ACTIVATING MICROSWITCH 1 L 7 2 4T 4 T A21SO E4EA 6 C P15EA 1997010200510 19970102 00510 SW 1997 1 2 AU960819 1 19960530 G 6320 3076 BEARING BELL BELL 47 47G3B 1181026 SW LYC O435 TVO435D1A 41516 EA MAIN ROTOR TRANS FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S 3076 (AUS) TRANSMISSION FAN DRIVE BEARING FAILED - METAL CONTAMINATION OF OIL SYSTEM 1 G 7 1 3O 3 O 2H3 1E13 1997010200511 19970102 00511 EA 1997 1 2 AU960820 2 19960613 G 7322 252405411 FCU PARTEN P68 P68B EU LYC O360 IO360A1B6 41514 EA HARTZL HCC2Y HCC2YK2 GL ENG,FUEL CONTROL FAULTY W K NONE O Y OTHER ENGINE STOPPAGE LD LANDING 1 AU S 75654 RL2427351A (AUS) RH ENGINE FUEL CONTROL UNIT FUEL/AIR MIXTURE SUSPECT OUT OF ADJUSTMENT - PERSONNEL/MAINTENANCE ERROR 1 H 7 2 3O 3 O A31EU 1E10 5 C P920 1997010200512 19970102 00512 SW 1997 1 2 AU960821 1 19960514 G 2910 79024681 PIPE GULSTM 500 500S 0141107 SW LYC O540 IO540E1B5 41532 EA HARTZL HCA3V HCA3VK2 GL MAIN HYD SYS CORRODED W K NONE K FLUID LOSS DE DESCENT 1 AU S (AUS) HYDRAULIC PIPE LOCATED IN WING ROOT AREA CONTAINED A PINHOLE LEAK DUE TO CORROSION ON THE OUTER RADIUS OF THE 90 D EGREE BEND 1 H 7 2 3O 3 O 6A1 1E4 5 C P6EA 1997010200513 19970102 00513 SW 1997 1 2 AU960822 1 19960520 G 6320 476205521 BEARING BELL 47 47G3B 1181026 SW LYC O435 TVO435D1A 41516 EA MAIN ROTOR TRANS FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S 75 B12344 (AUS) MAIN TRANSMISSION COOLING FAN DRIVE BEARING FAILED - METAL CONTAMINATION OF TRANSMISSION OIL SYSTEM 1 G 7 1 3O 3 O 2H3 1E13 1997010200514 19970102 00514 SW 1997 1 2 AU960823 1 19960412 G 6230 0471301101 BEARING BELL 47 47G3B 1181026 SW LYC O435 TVO435D1A 41516 EA M/R MAST/SWASHPL FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S 1166 047130114 (AUS) MAIN ROTOR MAST BEARING FAILED - SUSPECT CAUSED BY HEAVY LANDING - METAL CONTAMINATION OF OIL SYSTEM 1 G 7 1 3O 3 O 2H3 1E13 1997010200515 19970102 00515 CE 1997 1 2 AU960824 1 19960607 G 3250 24670031 BUNGEE CESSNA 172 172RG 2072438 CE LYC O360 O360F1A6 41514 EA MCAULY 2D34C B2D34C220 GL ACFT STEERING SY BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) AIRCRAFT STEERING SYSTEM BUNGEE JACK SCREW BROKEN DUE TO A WORN HOUSING - SYSTEM HAD BEEN MODIFIED IAW AD/CESSNA1 70/45 1 H 7 1 3O 3 O 3A17 E286 5 C P7EA 1997010200516 19970102 00516 EA 1997 1 2 AU960825 2 19960607 G 8520 CRANKSHAFT LYC PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL R ENGINE POWER S BROKEN W K NONE E VIBRATION/BUFFET TO TAKEOFF 1 AU S L720561A (AUS) ENGINE CRANKSHAFT BROKEN - CRANKCASE BROKEN - CAMSHAFT DAMAGED - NO1 AND NO2 CYLINDERS DAMAGED - CONNECTING RODS B ENT - SEE MDR 96/0797 FOR FURTHER INFORMATION 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 1997010200517 19970102 00517 NM 1997 1 2 AU960826 1 19960513 G 7910 3006084 CAP DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE AC,ENG OIL TANK DAMAGED W K NONE O K OTHER FLUID LOSS CL CLIMB 1 AU S 120032 (AUS) RH ENGINE OIL FILLER CAP DAMAGED - ONE LOCKING LUG BROKEN OFF - APPROXIMATELY 3 LITRES OF OIL LOST - DUPLICATE OF MDR 96/0731 2 H 7 2 4T 4 T RT A13NM E20NE 1997010200518 19970102 00518 NM 1997 1 2 AU960827 1 19960529 G 2750 745583A CONTROL CABLE DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE FLAP SYS FAILED W A K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FLAP CABLE SWAGED END FITTING SEPARATED FROM CABLE OUTER SHEATH -INNER CABLE DAMAGED - FOUND DURING INSPECTION IAW AD/DHC8/8 2 H 7 2 4T 4 T RT A13NM E20NE 1997010200519 19970102 00519 SO 1997 1 2 AU960828 2 19960613 G 8540 653583 SHAFT CONT CESSNA 404 404CESSNA 2075901 CE CONT O520 GTSIO520M 17032 SO MCAULY 3FF32 3FF32C501 GL R ENGINE REAR SE WORN W K NONE O OTHER IN INSP/MAINT 1 AU S 4527 239145R (AUS) ENGINE STARTER SHAFT AND CRANKSHAFT GEAR TEETH WORN - STARTER KIT PNO EQ6642 - SEE MDR 96/0908 FOR FURTHER INFORMA TION 1 L 7 2 3O 3 O A25CE E7CE 5 C P45GL 1997010200520 19970102 00520 CE 1997 1 2 AU960829 1 19960606 G 5712 RIB CESSNA 310 310Q 2074242 CE CONT O470 IO470V 17026 SO MCAULY 3AF32C 3AF32C87 GL OUTER WING SYS MIS MFG W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) LH WING END RIB NOT RIVETTED TO THE MAIN SPAR - SUSPECT RIVETS NOT INSTALLED AT MANUFACTURE 1 L 7 2 3O 3 O 3A10 3E1 5 C P22EA 1997010200521 19970102 00521 SW 1997 1 2 AU960830 1 19960614 G 2520 2790567033 SEAT SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE33111U 01514 WP PASSENGER COMPAR BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) PASSENGER SEAT BACK BROKEN 2 L 7 2 4T 4 T RT A8SW E4WE 1997010200522 19970102 00522 SO 1997 1 2 AU960831 1 19960610 G 3260 6741103 SWITCH JE73 PIPER PA28 PA28R201 7102816 SO LYC O360 IO360C1C6 41514 EA HARTZL HCC2Y HCC2YK1 GL LG POSITION IND BROKEN W K NONE O P OTHER NO WARNING INDICATION DE DESCENT 1 AU S (AUS) NOSE LANDING GEAR DOWNLOCK MICROSWITCH LEAF ACTUATOR BROKEN 1 L 7 1 3O 3 O 2A13 1E10 5 C P920 1997010200523 19970102 00523 SW 1997 1 2 AU960832 1 19960605 G 7810 PIPE SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE33111U 01514 WP T ENG CONE-PIPE CRACKED W K NONE F B J FLT CONT AFFECTED SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION NR NOT REPORTED 1 AU S (AUS) ENGINE EXHAUST SYSTEM SHORT PIPE CRACKED - HOT EXHAUST GASSES ACTIVATED FIRE WARNING SYSTEM AND FIRE BOTTLE WAS D ISCHARGED 2 L 7 2 4T 4 T RT A8SW E4WE 1997010200524 19970102 00524 SW 1997 1 2 AU960833 1 19960607 G 7712 27191587 INDICATOR 6112104 SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE33111U 01514 WP ENG PWR IND SYS FLUCTUATES W K NONE O OTHER TO TAKEOFF 1 AU S PORT77102 (AUS) LH ENGINE TORQUE INDICATOR FLUCTUATING 2 L 7 2 4T 4 T RT A8SW E4WE 1997010800012 19970108 00012 SO 1997 1 8 AU960834 2 19960601 G 7322 2523047 NEEDLE NA53A1 CESSNA 140 140 2071602 CE CONT C90 C90* 17009 SO ENG,FUEL CONTROL DETERIORATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) CARBURETTOR FLOAT NEEDLE RUBBER TIP HARDENED AND DEFORMED - OBSOLETE PART 1 H 7 1 3O 3 O NC A768 E252 1997010200525 19970102 00525 GL 1997 1 2 AU960835 2 19960606 G 7240 6899081 LINER SNIAS 350 AS350B 8680801 EU ALLSN 250C 250C30 03013 GL TURBINE ENGINE C FAILED W K NONE O OTHER NR NOT REPORTED 1 AU S 941 CAT890502 (AUS) ENGINE COMBUSTION ASSEMBLY AIR SURROUND TO COMBUSTION LINER ATTACHMENT SADDLES (3OFF) FAILED AT WELDS - SADDLES W ERE INGESTEDTHROUGH THE ENGINE 1 G 7 1 3U 3 U H9EU E1GL 1997011600471 19970116 00471 NM 1997 1 16 AU960836 1 19960614 G 3246 AN35A BOLT PIPER PA60 PA60600 7106001 NM LYC O540 IO540G1B5 41532 EA LG WHEEL/BRAKE S FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) WHEEL RIM TIE BOLT HEAD SEPARATED 1 M 7 2 3O 3 O RT A17WE 1E4 1997011600472 19970116 00472 NE 1997 1 16 AU960837 3 19960523 G 6111 SFA13M10A BLADE DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE PROPELLER ASSY S FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S 5380 644 (AUS) PROPELLER BLADE FAILED NDT INSPECTION AS PER HS ASB 14SF-61-A95 - AD/PHS/21 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 1997011600473 19970116 00473 EU 1997 1 16 AU960838 1 19960509 G 3230 C242450061 UPLOCK AMD FALC50 FALCON900 2700160 EU LG EXT-RETRACT S FAULTY W K NONE O N OTHER FALSE WARNING CL CLIMB 1 AU S (AUS) NOSE LANDING GEAR UPLOCK UNIT FAULTY - THIS DEFECT WAS RECEIVED FROM NO34 SQUADRON RAAF AND IS FOR INFORMATION ON LY 2 L 7 3 4F RT A46EU 1997011600474 19970116 00474 EU 1997 1 16 AU960839 1 19960307 G 3230 9036001 CLUTCH BAC 146 146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE LG EXT-RETRACT S SLIPPED W K NONE O N OTHER FALSE WARNING CL CLIMB 1 AU S 13079 487GB170H (AUS) LANDING GEAR SELECTOR VALVE ACTUATOR CLUTCH SLIPPING 2 H 7 4 4F 4 F A49EU E6NE 1997011600475 19970116 00475 EU 1997 1 16 AU960840 2 19960418 G 7322 CARBURETTOR ROTAX 912 ROTAX912 55555 EU ENG,FUEL CONTROL LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S (AUS) CARBURETTOR LEAKING FUEL INTO AIR FILTER BOX VIA CARBURETTOR COMPENSATING LINE - THIS DEFECT WAS RECEIVED FROM THE AUF AND IS FOR INFORMATION ONLY 3 I EXPE3I 1997011600476 19970116 00476 CE 1997 1 16 AU960841 1 19960613 G 5330 081125077 SKIN CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO MCAULY 3AF32C 3AF32C87 GL EXT PLATES/SKIN CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUSELAGE SKIN CORRODED IN AREA OF LH LOWER BELLY - INVESTIGATION FOUND EXTENSIVE CORROSION IN THE AREA BENEATH THE HEATER DUCTING PNO 0813769-1 1 L 7 2 3O 3 O 3A10 E5CE 5 C P22EA 1997011600477 19970116 00477 SO 1997 1 16 AU960842 1 19960619 G 2810 527881 FUEL CELL PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA HARTZL HCE3Y HCE3YR2 GL FUEL STORAGE SYS FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S 7716216 (AUS) FUEL CELL SPLIT AT DRAIN FITTING NIPPLE - CELL WAS FITTED IN 1978 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 1997011600478 19970116 00478 CE 1997 1 16 AU960843 1 19960516 G 7120 MS2000646M BOLT BEECH 55 95C55 1152708 CE CONT O520 IO520C 17032 SO MCAULY 2AF34C 2AF34C55 GL ENGINE MOUNTING CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 555307 (AUS) ENGINE MOUNT ATTACHMENT BOLT CRACKED UNDER HEAD - FOUND DURING NDT INSPECTION IAW AD/B55/74 1 L 7 2 3O 3 O 3A16 E5CE 5 C P5EA 1997011600479 19970116 00479 CE 1997 1 16 AU960844 1 19960515 G 7120 9691001061 MOUNT BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO MCAULY 3AF32C 3AF32C512 GL ENGINE MOUNTING CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 287203R (AUS) ENGINE MOUNT STRUCTURE CRACKED IN FOUR PLACES - FOUND DURING NDT INSPECTION IAW AD/B55/74 1 L 7 2 3O 3 O 3A16 E5CE 5 C P22EA 1997011600480 19970116 00480 EU 1997 1 16 AU960845 1 19960618 G 2750 ACTUATOR BAC 146 146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE FLAP SYS CONTAM-WATER W K NONE F FLT CONT AFFECTED DE DESCENT 1 AU S (AUS) FLAPS LOCKED IN ZERO DEGREES POSITION - INVESTIGATION FOUND WATER INGRESS INTO FLAP ACTUATOR BALLNUTS - AEROSHELL 7 GREASE USED 2 H 7 4 4F 4 F A49EU E6NE 1997011600481 19970116 00481 EU 1997 1 16 AU960846 1 19960608 G 3230 SEAL SOCATA TB20 TB20TRINIDAD 8680695 EU LYC O540 IO540C4D5 41532 EA HARTZL HCC2Y HCC2YK1 GL LG EXT-RETRACT S DETERIORATED W K NONE W INADEQUATE Q C LD LANDING 1 AU S (AUS) RH MAIN LANDING GEAR ACTUATOR SEALS DETERIORATED AND LEAKING - CAUSED BY FAILURE TO CORRECTLY MASK LANDING GEAR RA M DURING PAINTING ALLOWING RAM SHAFT TO BE COVERED IN PAINT WHICH DAMAGED RAM SEALS - PERSONNEL/MAINTENANCE ERROR 1 L 7 1 3O 3 O RT A51EU 1E4 5 C P920 1997011600482 19970116 00482 CE 1997 1 16 AU960847 1 19960618 G 3230 1055800015 PIPE BEECH B76 BEECH 76 76 1153005 CE LG EXT-RETRACT S CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S (AUS) LANDING GEAR HYDRAULIC 'UP' PIPE FLARE CRACKED AND LEAKING AT CONNECTION TO POWER PACK - INVESTIGATION FOUND POOR QUALITY FLARE- PIPE HAD BEEN REFLARED ON 20 OCTOBER 1992 - PERSONNEL/MAINTENANCE ERROR 1 L 7 2 3O A29CE 1997011600483 19970116 00483 SO 1997 1 16 AU960848 1 19960619 G 3260 487820 SWITCH PIPER PA24 PA24 7102402 SO LYC O360 O360A1A 41514 EA LG POSITION IND SEIZED W K NONE N FALSE WARNING IN INSP/MAINT 1 AU S (AUS) LANDING GEAR WARNING MICROSWITCH SEIZED IN 'SAFE' POSITION 1 L 7 1 3O 3 O 1A15 E286 1997011600484 19970116 00484 CE 1997 1 16 AU960849 1 19960619 G 3230 HMXFG ROD END BEECH 58 58 1152740 CE CONT O520 IO520F 17032 SO LG EXT-RETRACT S FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NOSE LANDING GEAR RETRACTION ACTUATOR FORWARD RODEND FAILED 1 L 7 2 3O 3 O 3A16 E5CE 1997011600485 19970116 00485 EA 1997 1 16 AU960850 2 19960609 G 7320 FCU BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL ENG,FUEL CONTROL FAULTY W K NONE O R OTHER PARTIAL RPM/PWR LOSS TO TAKEOFF 1 AU S 80438 (AUS) ENGINE LOST POWER DURING TAKEOFF - INVESTIGATION COULD FIND NO FAULTS - SUSPECT FUEL CONTROL PROBLEM 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 1997011600486 19970116 00486 CE 1997 1 16 AU960851 1 19960616 G 2612 302158 DETECTOR BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL FIRE DETECTION S FAULTY W K NONE N FALSE WARNING IN INSP/MAINT 1 AU S (AUS) ENGINE FIRE DETECTORS FAULTY - CONTINUING FALSE FIRE WARNING INDICATIONS 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 1997011600487 19970116 00487 EA 1997 1 16 AU960852 2 19960410 G 7322 30766 FLOAT FACET MA4SPA PIPER PA28 PA28140 7102802 SO LYC O320 O320E2A 41508 EA SNSNCH 74DM M74DM EA ENG,FUEL CONTROL DETERIORATED W K NONE E VIBRATION/BUFFET TO TAKEOFF 1 AU S 2000 (AUS) CARBURETTOR FLOAT DETERIORATED - FLOAT ABSORBING FUEL CAUSING EXCESSIVELY RICH CONDITION 1 L 7 1 3O 3 O 2A13 E274 5 N P88614 1997011600488 19970116 00488 SO 1997 1 16 AU960853 2 19960519 G 7421 RHM40E SPARK PLUG CONT TSIO350EB PIPER PA34 PA34200T 7103406 SO CONT O360 LTSIO360E 17025 SO MCAULY 3AF34C 3AF34C502 GL ENG,IGNITN DISTR WRONG PART W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) ENGINE HAD INCORRECT SPARK PLUGS FITTED - PERSONNEL/MAINTENANCE ERROR - UNAPPROVED PART 1 L 7 2 3O 3 O A7SO E9CE 5 C P22EA 1997011600489 19970116 00489 SO 1997 1 16 AU960854 2 19960507 G 8520 649478 CAMSHAFT CONT O470U CESSNA 182 182R 2072731 CE CONT O470 O470U 17026 SO MCAULY 2A34C C2A34C204 GL R ENGINE POWER S PITTED W K NONE O OTHER IN INSP/MAINT 1 AU S 470326 470326 821588 (AUS) ENGINE CAMSHAFT LOBE FOR NO5 CYLINDER EXHAUST VALVE AND CORRESPONDING LIFTER BADLY PITTED AND GALLED 1 L 7 1 3O 3 O NT 3A13 E273 5 C P3EA 1997011600490 19970116 00490 CE 1997 1 16 AU960855 1 19960318 G 3211 24411001 PIVOT CESSNA 172 172RG 2072438 CE LYC O360 O360F1A6 41514 EA MCAULY 2D34C B2D34C220 GL MAIN GEAR SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RH MAIN LANDING GEAR PIVOT CRACKED AT THE OUTBOARD END OF THE SPLINED AREA - FURTHER INVESTIGATION FOUND LH MLG P IVOT ALSO CRACKED 1 H 7 1 3O 3 O 3A17 E286 5 C P7EA 1997011600491 19970116 00491 EA 1997 1 16 AU960856 2 19960425 G 8540 LW13796 SHAFT LYC O320A2D BBAVIA 7 7GCBC 1220601 SW LYC O320 O320A2D 41508 EA R ENGINE REAR SE WORN W K NONE O OTHER NR NOT REPORTED 1 AU S (AUS) ENGINE CRANKSHAFT LH IDLER GEAR SHAFT ATTACHMENT HOLES ELONGATED,LOCKWIRE BROKEN, BOLTS NECKED AND SHAFT LOOSE 1 H 7 1 3O 3 O NC A759 E274 1997011600492 19970116 00492 CE 1997 1 16 AU960857 1 19960620 G 2612 64123473275 FIRE DETECTOR BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA FIRE DETECTION S FAULTY W K NONE N FALSE WARNING CR CRUISE 1 AU S (AUS) LH ENGINE FIRE DETECTION SYSTEM FAULTY - INVESTIGATION COULD FIND NO FAULTS WITH THE SYSTEM - A LEAKING GASKET ON THE FLOW PACK MAYHAVE ALLOWED HOT AIR ONTO THE LOWER REAR SENSOR - FOLLOWING REPLACEMENT OF THE FLOW PACK ON THE NEXT F LIGHT THE FIRE WARNING SYSTEM AGAIN ACTIVATED - FURTHER INVESTIGATION FOUND THE TWO REAR BULKHEAD FIRE SENSORS TO BE FAU LTY 1 L 7 2 4T 4 T A24CE E4EA 1997011600493 19970116 00493 EA 1997 1 16 AU960858 2 19960616 G 8520 CONNECTING ROD CESSNA 172 172N 2072434 CE LYC O360 O360A4M 41514 EA MCAULY 1C160 1C160DTM GL R ENGINE POWER S FAILED W C D ABORTED TAKEOFF RETURN TO BLOCK E Y VIBRATION/BUFFET ENGINE STOPPAGE TO TAKEOFF 1 AU S (AUS) NO3 CYLINDER CONNECTING ROD FAILED IN AREA APPROXIMATELY HALF WAY BETWEEN THE BIG END AND THE GUDGEON PIN BUSHING - FAILURE INVESTIGATION FOUND EVIDENCE OF A PRE-EXISTING FLAW IN THE PISTON PIN BEARING HOUSING WHICH WAS HEAVILY OXIDIS ED 1 H 7 1 3O 3 O NT 3A12 E286 5 N P910 1997011600494 19970116 00494 SO 1997 1 16 AU960859 1 19960619 G 3230 DOWNLOCK HOOK PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2B 41532 EA HARTZL HCE3Y HCE3YR2 GL LG EXT-RETRACT S MALFUNCTION W K NONE O J OTHER WARNING INDICATION LD LANDING 1 AU S (AUS) LH MAIN LANDING GEAR DOWNLOCK HOOK STIFF - HOOK DID NOT FULLY ENGAGE 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 1997012200004 19970122 00004 SO 1997 1 22 AU960860 2 19960607 G 8530 649317P010 CYLINDER CONT IO520BE BEECH 36 A36 1151604 CE CONT O520 IO520B 17032 SO MCAULY 3A32C 3A32C76 GL R ENGINE CYLINDE SEPARATED W K NONE O OTHER IN INSP/MAINT 1 AU S 513 571950 571950 (AUS) NO2 CYLINDER HEAD SEPARATED FROM BARREL 1 L 7 1 3O 3 O 3A15 E5CE 5 C P21EA 1997011600495 19970116 00495 EU 1997 1 16 AU960861 1 19960621 G 2110 MOTOR 021003 BNORM BN2 BN2B20 1520302 EU LYC O540 IO540K1B5 41532 EA HARTZL HCC2Y HCC2YK2 GL CABIN COMPRESSOR FAILED W K NONE B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 AU S (AUS) AIRCONDITIONING SYSTEM DISCHARGE PIPE BURST - FAILURE WAS DUE TO FAILURE OF THE CONDENSER COOLING FAN MOTOR RESULT ING IN AN INCREASE OF DISCHARGE PRESSURE 1 H 7 2 3O 3 O A17EU 1E4 5 C P920 1997011600496 19970116 00496 CE 1997 1 16 AU960862 1 19960430 G 7120 J1245412 MOUNT CESSNA 206 U206F 2073333 CE CONT O520 IO520F 17032 SO MCAULY 3A32C D3A32C90 GL ENGINE MOUNTING DETERIORATED W K NONE O OTHER IN INSP/MAINT 1 AU S 1210 286011R (AUS) FORWARD LH RUBBER ENGINE MOUNT PERISHED AND HOLED - SUSPECT CAUSED BY EXHAUST AFTER PROTECTIVE HEAT SHROUD FELL O FF 1 H 7 1 3O 3 O A4CE E5CE 5 C P21EA 1997011600497 19970116 00497 1997 1 16 AU960863 1 19960624 G 7120 14W677 MOUNT 14W678A LYC O540 IO540K1C5 41532 EA HARTZL HCA3V HCA3VK2 GL ENGINE MOUNTING CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH OUTBOARD LOWER ENGINE MOUNT ATTACHMENT FITTING CRACKED - CRACK LENGTH 38.1MM (1.5IN) - AIRCRAFT IS A RILEY CONV ERSION AND THE DEFECT IS PART OF THAT CONVERSION 3 O 1E4 5 C P6EA 1997011600498 19970116 00498 EU 1997 1 16 AU960864 1 19960603 G 6320 711 BOLT AEROSP BEVELGEARBOX SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1B 6OO30 NE MAIN ROTOR XMSN LOOSE W K NONE O OTHER IN INSP/MAINT 1 AU S 711 945 (AUS) MAIN GEARBOX BEVEL GEAR BOLTS LOOSE - FOUND DURING INSPECTION IAWAD/ECUR/21 1 G 7 1 3U 3 U H9EU E19EU 1997011600499 19970116 00499 WP 1997 1 16 AU960865 1 19960620 G 2910 467031 UNION BENDIX REGULATOR DOUG DC4 C54E 3021530 WP MAIN HYD SYS CRACKED W K NONE K FLUID LOSS LD LANDING 1 AU S 8V0202 (AUS) HYDRAULIC PRESSURE REGULATOR `T' UNION CRACKED AND LEAKING FROM THE AREA OF THE UNION NECK IN THE VICINITY OF A P REVIOUS WELD REPAIR - CRACK LENGTH 20MM (0.787IN) - LOSS OF HYDRAULIC FLUID 2 L 7 4 4R A762 1997011600500 19970116 00500 EU 1997 1 16 AU960866 1 19960621 G 5620 SD3117982 WINDOW STBROS SD3 SD360 8100606 EU PWA PT6 PT6A65R 52043 EA HARTZL HCB5M HCB5MP3 GL PAX COMPT WINDOW SEPARATED W K NONE O D OTHER INFLIGHT SEPARATION CR CRUISE 1 AU S (AUS) PASSENGER OUTER WINDOW AT SEAT POSITION 7A SEPARATED DURING FLIGHT - INSPECTION FOUND THAT THE WINDOW PANE AND TH E RUBBER SEAL WERE MISSING - THIS WINDOW HAD BEEN REPLACED ON 04 JUNE 1996- LOSS ATTRIBUTED TO REUSE OF ORIGINAL SEAL DU RING WINDOW REPLACEMENT - SUSPECT SEAL HAD BEEN DETERIORATED BY ENGINE EXHAUST GASSES 2 H 7 2 4T 4 T A41EU E4EA 6 C P44GL 1997011600501 19970116 00501 1997 1 16 AU960867 4 19960621 G 6113 22501215 BULKHEAD CESSNA 182 R182 2072734 CE LYC O540 O540J3C5 41532 EA MCAULY PROPELLER ASSY CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) PROPELLER SPINNER BULKHEAD CRACKED IN AREA OF INNER RING - MOUNT BACK PLATES PNO C504-6/2 ALSO CRACKED 1 H 7 1 3O 3 O RT 3A13 E295 1997011600502 19970116 00502 GL 1997 1 16 AU960868 1 19960221 G 3246 WHEEL AMTR MAXAIR XP503 9570746 GL ROTAX 503 ROTAX503 55555 EU LG WHEEL/BRAKE S FAILED W K NONE W INADEQUATE Q C LD LANDING 1 AU S (AUS) LH WHEEL FAILED DUE TO INSUFFICIENT WELD - PERSONNEL/MAINTENANCE ERROR - THIS DEFECT WAS RECEIVED FROM THE AUF AND IS FOR INFORMATION ONLY 1 H 7 1 3I 3 I NT EXPA1H71 EXPE3I 1997011600503 19970116 00503 1997 1 16 AU960872 1 19960331 G 7820 MUFFLER ROTAX 912 ROTAX912 55555 EU ENG NOISE SUPPRS FAILED W K E NONE ENGINE SHUTDOWN O OTHER CR CRUISE 1 AU S (AUS) ENGINE TAIL PIPE SEPARATED FROM MUFFLER - THIS DEFECT WAS RECEIVED FROM THE AUF AND IS FOR INFORMATION ONLY 3 I EXPE3I 1997011600504 19970116 00504 GL 1997 1 16 AU960873 1 19960406 G 3213 AXLE AMTR MAXAIR XP503 9570746 GL ROTAX 503 ROTAX503 55555 EU MAIN GEAR SYS FAILED W K NONE O D OTHER INFLIGHT SEPARATION CL CLIMB 1 AU S (AUS) LH AXLE FAILED - LH WHEEL AND AXLES SEPARATED FROM LANDING GEAR LEG HELD ONLY BY BRAKE CABLE - AIRCRAFT HAD HEAVY LANDING TWO DAYS PREVIOUS - THIS DEFECT WAS RECEIVED FROM THE AUF AND IS FOR INFORMATION ONLY 1 H 7 1 3I 3 I NT EXPA1H71 EXPE3I 1997011600505 19970116 00505 EU 1997 1 16 AU960874 2 19960401 G 8500 ENGINE AMTR MAXAIR XP503 9570746 GL ROTAX 582 ROTAX582 55555 EU ENGINE (RECIPROC FAILED W A UNSCHED LANDING E Y VIBRATION/BUFFET ENGINE STOPPAGE CL CLIMB 1 AU S (AUS) ENGINE RAN ROUGH AND STOPPED - AIRCRAFT LANDED IN SHALLOW WATER ON BEACH DAMAGING ELEVATOR AND ELEVATOR CONTROL R OD - THIS DEFECT WAS RECEIVED FROM THE AUF AND IS FOR INFORMATION ONLY 1 H 7 1 3I 3 I NT EXPA1H71 EXPE3I 1997011600506 19970116 00506 EU 1997 1 16 AU960875 1 19960622 G 5210 LOCK BAC 146 146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE CREW-PASS DOOR S REQ LUBE W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FORWARD PASSENGER DOOR COULD NOT BE OPENED FROM INSIDE AIRCRAFT -WHEN OPENED FROM OUTSIDE THE DOOR MECHANISM SOUND ED ROUGH IN OPERATION - MECHANISM WAS LUBRICATED AND EXERCISED AND NOW OPERATES NORMALLY 2 H 7 4 4F 4 F A49EU E6NE 1997011600507 19970116 00507 CE 1997 1 16 AU960876 1 19960412 G 5712 RIB CESSNA 310 310R 2074245 CE CONT O520 IO520C 17032 SO MCAULY 3AF32C 3AF32C87 GL OUTER WING SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) WING RIBS AND SKINS CRACKED IN AREA OF WHEEL WELLS 1 L 7 2 3O 3 O 3A10 E5CE 5 C P22EA 1997011600508 19970116 00508 1997 1 16 AU960877 4 19960610 G 2565 3499 SLIDE AIRBUS 300 A300B4203 3930306 EU GE CF6 CF650C2 30018 NE EMERGENCY EQUIP FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S 877 3499 (AUS) DOOR 3R SLIDE FAILED TO DROP OUT OF CONTAINER 2 L 7 2 4F 4 F A35EU E23EA 1997011600509 19970116 00509 EA 1997 1 16 AU960878 2 19960621 G 7310 3040637 FUEL LINE PWA PT6A65 BEECH 1900 1900C 1154161 CE PWA PT6 PT6A65B 52043 EA ENG,FUEL DIST SY WORN W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S 32212 32212 (AUS) PIPE BETWEEN FUEL FLOW TRANSMITTER AND FUEL CONTROL UNIT WORN THROUGH IN THREE PLACES DUE TO CONTACT WITH GENERAT OR COOLINGDUCT - FUEL LEAKING FROM PIPE 2 L 7 2 4T 4 T RT A24CE E4EA 1997011600510 19970116 00510 NM 1997 1 16 AU960879 1 19960622 G 3231 82910010177 PIPE DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE LG EXT-RETRACT S LEAKING W K NONE O K OTHER FLUID LOSS IN INSP/MAINT 1 AU S (AUS) NOSE LANDING GEAR DOOR ALUMINIUM HYDRAULIC PIPE LEAKING FROM PIN HOLE ON BEND RADIUS 2 H 7 2 4T 4 T RT A13NM E20NE 1997011600511 19970116 00511 NM 1997 1 16 AU960880 1 19960625 G 3244 319K281 TYRE DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE LG WHEEL/BRAKE S DEFLATED W K NONE O OTHER IN INSP/MAINT 1 AU S 550 1777 (AUS) LH MAIN LANDING GEAR OUTER TYRE DEFLATED - CARCASS PLY SEPARATION CAUSED LEAKAGE FROM INNER LINER VENT HOLES 2 H 7 2 4T 4 T RT A13NM E20NE 1997011600512 19970116 00512 SO 1997 1 16 AU960881 2 19960618 G 8530 CYLINDER BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO MCAULY 3AF34C 3AF34C502 GL R ENG CYL NR 6 SEPARATED W K NONE E VIBRATION/BUFFET CR CRUISE 1 AU S 243678R (AUS) LH ENGINE NO6 CYLINDER SEPARATED - SEE MDR 96/0906 FOR FURTHER INFORMATION 1 L 7 2 3O 3 O 3A16 E5CE 5 C P22EA 1997011600513 19970116 00513 CE 1997 1 16 AU960882 1 19960621 G 7500 DUCT CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE ENG,BLEED AIR SY LEAKING W K E NONE ENGINE SHUTDOWN J WARNING INDICATION TO TAKEOFF 1 AU S PCE70273 (AUS) RH ENGINE FIRE WARNING SYSTEM ACTIVATED - INVESTIGATION COULD FIND NO FAULTS EXCEPT FOR A FEW MINOR LEAKS FROM TH E BLEED AIR DUCTS WHICH MAY OR MAY NOT HAVE CAUSED THE FIRE WARNING 1 L 7 2 4F 4 F A22CE E1NE 1997011600514 19970116 00514 1997 1 16 AU960883 1 19960619 G 7820 MAI10 DIFFUSER MAIRHS ROTAX 912 ROTAX912 55555 EU ENG NOISE SUPPRS CRACKED W K NONE O OTHER CR CRUISE 1 AU S 283 4380796 (AUS) MUFFLER FORWARD INLET DIFFUSER CRACKED AND SEPARATED FROM MUFFLER BODY 3 I EXPE3I 1997011600515 19970116 00515 CE 1997 1 16 AU960884 1 19960501 G 3220 11582006821 PLATE BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL NOSE-TAIL GEAR S CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 1037 (AUS) NOSE LANDING GEAR SHOCK ABSORBER REINFORCEMENT PLATE CRACKED IN LOWER WELDED AREA - CRACK LENGTH 28MM (1.1IN) 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 1997011600516 19970116 00516 1997 1 16 AU960885 1 19960619 G 7820 MAI10 DIFFUSER MAI ROTAX 912 ROTAX912 55555 EU ENG NOISE SUPPRS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 174 4076053 (AUS) MUFFLER FORWARD DIFFUSER CRACKED RADIALLY FROM DIFFUSER HOLE 3 I EXPE3I 1997011600517 19970116 00517 1997 1 16 AU960886 1 19960619 G 7820 MAI10 DIFFUSER MAILHSRHS ROTAX 912 ROTAX912 55555 EU ENG NOISE SUPPRS BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S 291 4380746 (AUS) MUFFLER FORWARD DIFFUSER CRACKED AND SEPARATED FROM MUFFLER BODY 3 I EXPE3I 1997011600518 19970116 00518 EU 1997 1 16 AU960887 1 19960411 G 3240 LOOM AIRBUS 320 A320212 EU LG WHEEL/BRAKE S TRANSPOSED W K NONE O W OTHER INADEQUATE Q C LD LANDING 1 AU S (AUS) LH MAIN LANDING GEAR WHEEL SPEED TRANSDUCER HARNESSES TRANSPOSED - NO1 WHEEL TRANSDUCER LOOM CONNECTED TO NO2 WHEE L AND VICE VERSARESULTING IN NO1 BRAKE RELEASING WHEN NO2 WHEEL SKIDDING - NO2 TYRE BLEW OUT DAMAGING NO1 WHEEL AND NO2 BRAKE ASSEMBLY -PERSONNEL/MAINTENANCE ERROR 2 L 7 2 4F RT A28NM 1997011600519 19970116 00519 EU 1997 1 16 AU960888 1 19960504 G 2782 02832ANSSN01 ACTUATOR AIRBUS 320 A320212 EU NR 2 SLAT OUTB FAULTY W A K NONE F FLT CONT AFFECTED NR NOT REPORTED 1 AU S 02832ANSS (AUS) NO2 SLAT RH OUTBOARD SLAT ACTUATOR FAULTY - SUSPECT MOISTURE INGRESS CAUSED FREEZING AT ALTITUDE PREVENTING SLAT A CTUATION 2 L 7 2 4F RT A28NM 1997012800005 19970128 00005 GL 1997 1 28 AU960889 3 19960508 G 6110 3AF32C504C PROPELLER MCAULY 3AF32C504C CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO MCAULY 3AF32C 3AF32C* GL PROPELLER ASSY S FOD DAMAGE W K NONE C F.O.D. LD LANDING 1 AU S 36 930486 1266139C 930486 (AUS) RH PROPELLER STUCK SHEEP ON LANDING ROLL - SUBSEQUENT INSPECTION FOUND BLADE LOOSE IN HUB 1 L 7 2 3O 3 O 3A10 E5CE 5 C P22EA 1997012300047 19970123 00047 SO 1997 1 23 AU960890 2 19960428 G 8530 276347R BOLT CONT CYLINDER CESSNA 404 404CESSNA 2075901 CE CONT O520 GTSIO520M 17032 SO MCAULY 3FF32 3FF32C501 GL R ENGINE CYLINDE FAILED W K NONE E VIBRATION/BUFFET LD LANDING 1 AU S 1198 276347R 276347R (AUS) ENGINE CYLINDER ROCKER SHAFT RETAINING BOLTS FAILED 1 L 7 2 3O 3 O A25CE E7CE 5 C P45GL 1997012300048 19970123 00048 GL 1997 1 23 AU960891 3 19960627 G 6111 FC76632R BLADE BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO HARTZL HCJ3Y PHCJ3YF2 GL PROPELLER ASSY S UNDERSIZE W K NONE O OTHER IN INSP/MAINT 1 AU S 42 AA ED3061 (AUS) PROPELLER BLADES UNDERSIZE AS PER MANUFACTURERS MINIMUM LIMITS INMANUAL - PROPELLER MODEL IN LOGBOOK INCORRECT - C YLINDER PRESSUREDECAL INCORRECT - PERSONEL/MAINTENANCE ERROR 1 L 7 2 3O 3 O 3A16 E5CE 5 C P36EA 1997012300049 19970123 00049 NE 1997 1 23 AU960892 2 19960625 G 7321 WYG29323ANSETT FCU GE CF6 CF680A 30025 NE ENG,FUEL CONTROL FAULTY W K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 AU S WYG29323ANS 580169 (AUS) LH ENGINE FUEL CONTROL UNIT FAULTY 4 F E13NE 1997012300050 19970123 00050 CE 1997 1 23 AU960893 1 19960627 G 5530 9664000011 RIB BEECH 96640000608 BEECH 55 D55 1152730 CE CONT O520 IO520C 17032 SO MCAULY 3AF32C 3AF32C75 GL VERT STAB STRUCT CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S TE750 (AUS) VERTICAL STABILISER AFT SPAR UPPER RIB PNO 96-640000-11 AND LOWERRIB PNO 96-640000-105 SEVERELY CORRODED - RIBS SU PPORT RUDDER PIVOT FLANGES - INVESTIGATION FOUND MORE CORROSION IN FUSELAGE AND AFT CABIN FLOOR STRUCTURE, LUGGAGE DOOR FRAME - STEP SUPPORT,WINGS, NACELLES AND LH ENGINE MOUNT STRUCTURE BEHIND FIREWALL - AIRCRAFT HAS OPERATED IN A SALT WA TER ENVIRONMENT SINCE 1980 1 L 7 2 3O 3 O 3A16 E5CE 5 C P22EA 1997012300051 19970123 00051 CE 1997 1 23 AU960894 1 19960611 G 5711 5122031 SPAR CAP CESSNA 402 CESSNA 402 402CESSNA 207590K CE MCAULY 3AF32C 3AF32C87 GL OUTER WING SYS CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH WING MAIN SPAR UPPER SPAR CAP CONTAINED SCATTERED PATCHES OF EXFOLIATION CORROSION IN AREA FROM OUTBOARD OF EN GINE NACELLE TO THE WING TIP 1 L 7 2 3O A7CE 5 C P22EA 1997012300052 19970123 00052 SO 1997 1 23 AU960895 2 19960603 G 7414 91090044 SHAFT SLICK 4347 HUGHES 269 269C 4470504 WP CONT O360 IO360C 17025 SO ELEC PWR SUPPLY FRACTURED W K NONE O OTHER IN INSP/MAINT 1 AU S 91090044 L3455336A (AUS) LH MAGNETO BREAKER POINT DRIVE SHAFT FRACTURED IN AREA OF CAM SLOT 1 G 7 1 3O 3 O 4H12 E1CE 1997012300053 19970123 00053 GL 1997 1 23 AU960896 3 19960627 G 6110 C83860 CLAMP BEECH 80 65B80 1152812 CE LYC O720 IO720A1B 41546 EA HARTZL HCA3V HCA3VK2 GL PROPELLER ASSY S FAULTY W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S BJ1511 (AUS) PROPELLER CLAMP FAULTY - CLAMP APPEARS TO HAVE FORGING FLAW - SUSPECT MANUFACTURING FAULT 1 L 7 2 3O 3 O 3A20 1E15 5 C P6EA 1997012300054 19970123 00054 NM 1997 1 23 AU960897 1 19960509 G 3213 015T15048 CYLINDER BOEING 767 767277 NM GE CF6 CF680A 30025 NE MAIN GEAR SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 4576ANSETT (AUS) RH MAIN LANDING GEAR OUTER CYLINDER AFT TRUNNION CRACKED AND CORRODED IN AREA OF FILLET SEAL 2 L 7 2 4F 4 F RT A1NM E13NE 1997012300055 19970123 00055 NM 1997 1 23 AU960898 1 19960406 G 3213 R7904ANSETTSN CYLINDER BOEING 767 767277 NM GE CF6 CF680A 30025 NE MAIN GEAR SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 33912 R7904ANSETT (AUS) RH MAIN LANDING GEAR OUTER CYLINDER AFT TRUNNION CRACKED AND CORRODED IN AREA OF FILLET SEAL 2 L 7 2 4F 4 F RT A1NM E13NE 1997012300056 19970123 00056 SO 1997 1 23 AU960899 2 19960623 G 7414 103493932 COVER BENDIX S6RN1205 CONT O520 IO520B 17032 SO MCAULY 3A32C 3A32C76 GL ELEC PWR SUPPLY CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S A27432 (AUS) MAGNETO CORRODED BETWEEN MAGNETO COVER PNO 10-349393-2 AND CAPACITOR PNO 10-349276 3 O E5CE 5 C P21EA 1997012300057 19970123 00057 NE 1997 1 23 AU960900 2 19960627 G 7260 601017079 SEAL ROTOL GEARBOX FOKKER F27 F27MK500 4990629 EU RROYCE DART DART5357R 54509 NE ROTOL R4304 R1934304 EU TURBINE ENG. ACC LEAKING W K NONE E K J VIBRATION/BUFFET FLUID LOSS WARNING INDICATION CL CLIMB 1 AU S EWA1897 (AUS) NO2 ENGINE ACCESSORY GEARBOX ALTERNATOR DRIVE PAD 'GITZ' SEAL DAMAGED AND LEAKING - LOSS OF APPROXIMATELY 3.5 PIN TS OF OIL 2 H 7 2 4T 4 T A817 E297 6 C P899 1997012300058 19970123 00058 GL 1997 1 23 AU960901 3 19960627 G 6110 B3807 NUT BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO HARTZL HCJ3Y PHCJ3YF2 GL PROPELLER ASSY S LOOSE W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S 42 AA ED3061 (AUS) PROPELLER PISTON UNIT LOOSE ON CONTROL ROD DUE TO INSUFFICIENT TORQUE ON THE NUT PNO B3807 - PERSONNEL/MAINTENANCE ERROR - SEEALSO MDR 96/0891 1 L 7 2 3O 3 O 3A16 E5CE 5 C P36EA 1997012300059 19970123 00059 EU 1997 1 23 AU960902 1 19960629 G 2434 503106680003 GENERATOR BAC 146 146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE DC GENERATOR-ALT DISINTEGRATED W K NONE J WARNING INDICATION CR CRUISE 1 AU S TE1117 (AUS) NO1 ENGINE DRIVEN GENERATOR DISINTEGRATED - DAMAGE CAUSED TO NO1 ENGINE THROTTLE CABLE - INVESTIGATION FOUND DEFOR MATION OF THE BACK PLATE CASTING WHICH MAY HAVE ALLOWED A MISALIGNMENT RESULTING IN INTERNAL FAILURE 2 H 7 4 4F 4 F A49EU E6NE 1997012300060 19970123 00060 CE 1997 1 23 AU960903 1 19960618 G 3240 1280509102 PIPE CESSNA 210 210M 2073450 CE CONT O520 IO520L 17032 SO MCAULY D3A34 D3A34C404 GL LG WHEEL/BRAKE S CRACKED W K NONE K FLUID LOSS TO TAKEOFF 1 AU S 62530 931710 (AUS) BRAKE PIPE FAILED AT FLARE - LOSS OF HYDRAULIC FLUID CAUSED BRAKE FAILURE ALLOWING AIRCRAFT TO RUN OFF AIRSTRIP AN D DAMAGE PROPELLER - SUSPECT CAUSED BY ROCKS ON LANDING STRIP 1 H 7 1 3O 3 O 3A21 E5CE 5 C P47GL 1997012300061 19970123 00061 EU 1997 1 23 AU960904 1 19960614 G 2842 NB57D2411 TRANSMITTER BNORM BN2 BN2B20 1520302 EU LYC O540 IO540K1B5 41532 EA HARTZL HCC2Y HCC2YK2 GL FUEL INDICATION FAULTY W K NONE O OTHER CR CRUISE 1 AU S (AUS) RH TIP TANK FUEL CONTENTS TRANSMITTER FLOAT MISSING - THE FLOAT RETAINING CLIP WAS STILL IN POSITION SUGGESTING T HAT THE FLOAT HAD DISINTEGRATED 1 H 7 2 3O 3 O A17EU 1E4 5 C P920 1997012300062 19970123 00062 EA 1997 1 23 AU960905 2 19960625 G 8520 LW14658 CRANKSHAFT LYC O320H2AD LYC O320 O320H2AD 41508 EA R ENGINE POWER S FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S RL428076T RL428076T (AUS) CRANKSHAFT HAD 0.9144MM (0.036IN) RUNOUT AT PROPELLER FLANGE - CAMSHAFT LOBES (2OFF0 BADLY WORN - LIFTER BODIES BA DLY PITTED -FOUND DURING ENGINE BULK STRIP 3 O E274 1997012300063 19970123 00063 SO 1997 1 23 AU960906 2 19960608 G 8520 243678R GEAR CONT IO520CB BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO MCAULY 3AF34C 3AF34C502 GL R ENGINE POWER S DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S 243678R 243678R (AUS) CRANKCASE CRACKED - CAMSHAFT GEAR AND MAGNETO IDLER GEAR DAMAGED - MAGNETO IDLER GEAR SHAFT BENT - MAGNETO DRIVE G EARS BADLYSPALLED - FOUND DURING ENGINE BULK STRIP FOLLOWING DISCOVERY OF SEVERAL BROKEN CYLINDER BASE STUDS - PERSONNE L/MAINTENANCE ERROR 1 L 7 2 3O 3 O 3A16 E5CE 5 C P22EA 1997012300064 19970123 00064 SO 1997 1 23 AU960907 2 19960613 G 8540 653583 GEAR CONT GTSIO520M CESSNA 404 404CESSNA 2075901 CE CONT O520 GTSIO520M 17032 SO MCAULY 3FF32 3FF32C501 GL R ENGINE REAR SE WORN W K NONE O OTHER IN INSP/MAINT 1 AU S 4456 276021R (AUS) ENGINE STARTER SHAFT GEAR AND CRANKSHAFT GEAR TEETH WORN ABNORMALLY - ENGINE STARTER KIT PNO EQ6642 1 L 7 2 3O 3 O A25CE E7CE 5 C P45GL 1997012300065 19970123 00065 SO 1997 1 23 AU960908 2 19960426 G 8540 653583 SHAFT CONT GTSIO520M CESSNA 404 404CESSNA 2075901 CE CONT O520 GTSIO520M 17032 SO MCAULY 3FF32 3FF32C501 GL R ENGINE REAR SE WORN W K NONE O OTHER IN INSP/MAINT 1 AU S 4541 239180H (AUS) ENGINE STARTER SHAFT AND CRANKSHAFT GEAR TEETH WORN EXCESSIVELY -FOUND DURING ENGINE BULK STRIP FOR CRACKED CRANKC ASE IN AREA OFNO4 CYLINDER BASE STUDS - THIS ASSEMBLY IS THE IMPROVED TYPE PURCHASED IN KIT FORM FROM CONTINENTAL AS PNO EQ6042 1 L 7 2 3O 3 O A25CE E7CE 5 C P45GL 1997012800006 19970128 00006 SO 1997 1 28 AU960910 2 19960605 G 7314 A227413 PUMP CESSNA 210 210N 2073453 CE CONT O520 IO520L 17032 SO ENG,FUEL DIST SY FAULTY W K NONE O OTHER CR CRUISE 1 AU S 129 A227413 294578R (AUS) ENGINE DRIVEN FUEL PUMP SUSPECT FAULTY - STRIP INSPECTION COULD FIND NO FAULTS 1 H 7 1 3O 3 O 3A21 E5CE 1997012300066 19970123 00066 SW 1997 1 23 AU960911 1 19960614 G 6220 47120252011 GRIP BELL 4763BKH4 BELL 47 47G3B 1181026 SW LYC O435 TVO435D1B 41516 EA MAIN ROTOR HEAD CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S K363 RL314952 (AUS) MAIN ROTOR HEAD GRIPS CRACKED - FOUND DURING EDDY CURRENT INSPECTION IAW AD/BELL47/92 AMDT4 1 G 7 1 3O 3 O 2H3 1E13 1997012300067 19970123 00067 CE 1997 1 23 AU960912 1 19960625 G 2720 505243263 ARM 505243264 BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO MCAULY 3AF34C 3AF34C502 GL RUDDER CONTROL S CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) PILOTS RUDDER PEDAL ARMS BOTH CRACKED IN UPPER AREA OF THE 'I' SECTION - FOUND DURING INSPECTION IAW AD/BEECH55/69 AMDT2 1 L 7 2 3O 3 O 3A16 E5CE 5 C P22EA 1997012300068 19970123 00068 SO 1997 1 23 AU960913 1 19960603 G 5310 FUSELAGE PIPER PA30 PA30 7103002 SO LYC O320 IO320C1A 41508 EA HARTZL HCE2Y HCE2YL2 GL FUSELAGE STRUCT CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) AIRFRAME STRUCTURE CONTAINED NUMEROUS TYPES OF CORROSION IN ALL AREAS 1 L 7 2 3O 3 O A1EA 1E12 5 C P9EA 1997012300069 19970123 00069 CE 1997 1 23 AU960914 1 19960702 G 3297 ISEI3 WIRE CESSNA 310R CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO MCAULY 3AF32C 3AF32C87 GL LG POSITION IND SEPARATED W K NONE O P OTHER NO WARNING INDICATION DE DESCENT 1 AU S (AUS) LH MAIN LANDING GEAR DOWNLOCK MICROSWITCH WIRE PULLED OUT OF PREVIOUS BUTT CONNECTOR REPAIR 1 L 7 2 3O 3 O 3A10 E5CE 5 C P22EA 1997012300070 19970123 00070 GL 1997 1 23 AU960915 3 19960507 G 6110 A3237 PISTON HARTZL HCC2YK2CFU PARTEN P68 P68B EU LYC O360 IO360A1B6 41514 EA HARTZL HCC2Y HCC2YK2 GL PROPELLER ASSY S WORN W K NONE O OTHER IN INSP/MAINT 1 AU S AV3743 AV3743 (AUS) PROPELLER PISTON WORN THROUGH ANODISING - CYLINDER SLUDGED - DURING ASSEMBLY THE FEATHER AND LATCH ANGLES WERE FOU ND TO BE APPROXIMATELY 2 DEGREES TOO FINE 1 H 7 2 3O 3 O A31EU 1E10 5 C P920 1997012300071 19970123 00071 CE 1997 1 23 AU960916 1 19960531 G 3230 224110213 PIVOT CESSNA R182 CESSNA 182 R182 2072734 CE LYC O540 O540J3C5 41532 EA LG EXT-RETRACT S CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S (AUS) LH MAIN LANDING GEAR ACTUATOR GEAR PLATE BEARING SPIGOT ON THE PIVOT ASSEMBLY CRACKED - LOSS OF HYDRAULIC BRAKE FL UID 1 H 7 1 3O 3 O RT 3A13 E295 1997012300072 19970123 00072 NE 1997 1 23 AU960917 3 19960624 G 6111 851630 DEICE BOOT HAMSTD BLADE DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE PROPELLER ASSY S SHORT CIRCUIT W K NONE O OTHER IN INSP/MAINT 1 AU S 8278 851630 RH860108 (AUS) PROPELLER BLADE DE-ICE BOOT BURNT OUT - BLADE HOLED 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 1997012300073 19970123 00073 EA 1997 1 23 AU960918 2 19960614 G 8530 75089 PISTON CESSNA 172 172P 2072436 CE LYC O320 O320D2J 41508 EA MCAULY 1C160 1C160DTM GL R ENGINE CYLINDE DAMAGED W K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CR CRUISE 1 AU S 826 109153 L10560 (AUS) ENGINE NO3 CYLINDER PISTON RING FOUND BROKEN AND PISTON DAMAGED IN LINE WITH EXHAUST VALVE - SUSPECT CAUSED BY DE TONATION 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 1997012300074 19970123 00074 CE 1997 1 23 AU960919 1 19960703 G 3297 D6H22 WIRE BEECH 1900 1900C 1154161 CE PWA PT6 PT6A65B 52043 EA LG POSITION IND CHAFED W K NONE N FALSE WARNING LD LANDING 1 AU S (AUS) LANDING GEAR POSITION INDICATOR CIRCUIT BREAKER TRIPPED FOLLOWING GEAR SELECTION 'DOWN' - INVESTIGATION FOUND WIRE NO.D6H22 HAD CHAFED AGAINST THE OXYGEN BOTTLE LH SIDE ZONE 121 APPROXIMATELY 152MM (6IN) FROM J162 2 L 7 2 4T 4 T RT A24CE E4EA 1997012300075 19970123 00075 NM 1997 1 23 AU960920 1 19960618 G 2613 116982195 CONNECTOR BOEING 737 737376 NM FIRE DETECT SYS FAULTY W K NONE N FALSE WARNING CL CLIMB 1 AU S 116982195 (AUS) NO1 ENGINE OVERHEAT WARNING SYSTEM FAULTY - LOOP A AND B CORE DETECTOR, CONNECTORS D3088 AND D3096 AND ASSOCIATED WIRING REPLACED 2 L 7 2 4F RT A16WE 1997012300076 19970123 00076 NM 1997 1 23 AU960921 1 19960617 G 2730 029 SPRING BOEING 737 737376 NM ELEVATOR CONTROL BROKEN W K NONE O F OTHER FLT CONT AFFECTED IN INSP/MAINT 1 AU S 20496 029 (AUS) CO-PILOT'S CONTROL COLUMN ELEVATOR FEEL AND CENTERING UNIT PRIMARY SPRING BROKEN 2 L 7 2 4F RT A16WE 1997012300077 19970123 00077 WP 1997 1 23 AU960922 1 19960617 G 5315 992239501 FLOORBEAM DOUG DC9 DC933F 302207A WP PWA JT8 JT8D9A 52048 NE BS 937 CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LEVEL 2 CORROSION ON LOWER `T' OF FLOORBEAM AT FUSELAGE STN 937. 2 L 7 2 4F 4 F A6WE E2EA 1997012300078 19970123 00078 WP 1997 1 23 AU960923 1 19960617 G 5320 1766648 ANGLE DOUG DC9 DC933F 302207A WP PWA JT8 JT8D9A 52048 NE ATTACH FITTING S CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LEVEL 2 EXFOLIATION CORROSION AT BOTTOM OF `T' ANGLE (ATTACHMENT ANGLE) OF FUSELAGE TO CANTED PRESSURE PANEL IN RH WHEEL WELL 2 L 7 2 4F 4 F A6WE E2EA 1997012300079 19970123 00079 EU 1997 1 23 AU960924 1 19960413 G 2910 PTU BAC 146 146300A 1500267 EU LYC ALF502 ALF502R5 41580 NE MAIN HYD SYS MALFUNCTIONED W K NONE J WARNING INDICATION CL CLIMB 1 AU S (AUS) HYDRAULIC SYSTEM POWER TRANSFER UNIT (PTU) CAUSING HIGH TEMPERATURE WARNING IN THE 'YELLOW' HYDRAULIC SYSTEM 2 H 7 4 4F 4 F RT A49EU E6NE 1997012300080 19970123 00080 EA 1997 1 23 AU960925 2 19960617 G 8520 SL13884M03 BEARING PIPER PA23 PA23250 7102308 SO LYC O540 TIO540C1A 41532 EA HARTZL HCE2Y HCE2YK2 GL R ENGINE POWER S SEIZED W K NONE O OTHER IN INSP/MAINT 1 AU S L251261 (AUS) ENGINE NO1 MAIN BEARING SEIZED TO CRANKSHAFT DURING START - ENGINE HAD DONE 17.5 HOURS SINCE A TOP OVERHAUL WAS C ARRIED OUT 1 L 7 2 3O 3 O 1A10 E14EA 5 C P9EA 1997012300081 19970123 00081 SO 1997 1 23 AU960926 1 19960630 G 3710 PUMP PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA HARTZL HCE3Y HCE3YR2 GL PRESS-VAC DIST S INCORRECT FIT W K NONE K FLUID LOSS CR CRUISE 1 AU S L466461 (AUS) LH ENGINE VACUUM PUMP INCORRECTLY SEATED ON ACCESSORY PLATE - THEPUMP WAS RESTING ON AN ACCESSORY CASE OIL HOSE 45 DEGREE FITTING - THE VACUUM PUMP HAD BEEN FITTED JUST PRIOR TO FLIGHT - ENGINE OIL LEAKING - PERSONNEL/MAINTENANCE ERR OR 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 1997012300082 19970123 00082 EU 1997 1 23 AU960927 1 19960705 G 3230 HTE210014 ACTUATOR HTE96811 BAC 146 146100A 1500260 EU LYC ALF502 ALF502R5 41580 NE LG EXT-RETRACT S FAULTY W K NONE O OTHER DE DESCENT 1 AU S (AUS) LANDING GEAR SELECTOR VALVE ACTUATOR (MOTOR) WAS DEFECTIVE - THE ACTUATOR WAS CHANGED AND GROUND CHECKS CARRIED OU T - ON 'DOWN' SELECTION THE POWER TRANSFER UNIT RAN CONTINUOUSLY - THE FAULT WAS TRACED TO THE LANDING GEAR SELECTOR VAL VE - THE VALVE WAS REPLACED - LANDING GEAR SYSTEM CHECKED SERVICEABLE 2 H 7 4 4F 4 F RT A49EU E6NE 1997012300083 19970123 00083 SO 1997 1 23 AU960928 2 19960606 G 8530 649317CEAI CYLINDER CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO MCAULY D3A34 D3A34C404 GL R ENGINE CYLINDE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 1428 247926R (AUS) ENGINE NO2 ENGINE CYLINDER CRACKED IN THE INLET PORT - CRACK LENGTH APPROXIMATELY 40MM (1.5IN) - THE CRACK WAS DIF FICULT TO SEE DUE TO THE ENGINE BAFFLING 1 H 7 1 3O 3 O A4CE E5CE 5 C P47GL 1997012300084 19970123 00084 EA 1997 1 23 AU960929 2 19960618 G 8520 LW18402 CRANKCASE CESSNA 172 172P 2072436 CE LYC O320 O320D2J 41508 EA MCAULY 1C160 1C160DTM GL R ENGINE POWER S CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S L10013394 (AUS) ENGINE CRANKCASE CRACKED IN THE LH FORWARD SECTION - CRACK LENGTH APPROXIMATELY 32MM (1.25IN) - CRANKCASE HAD BEEN WELD REPAIRED IN THIS AREA AT LAST OVERHAUL - SUSPECT INCORRECT HEAT TREATMENT FOLLOWING WELD REPAIR 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 1997012300085 19970123 00085 GL 1997 1 23 AU960930 1 19960514 G 5720 V61 BLOCK AMTR EAGLE CHRISEAGLE2 GL LYC O360 IO360A1A 41514 EA SNSNCH 76E 76EM8 EA OUTER WING SYS FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S V61 (AUS) DURING INVESTIGATION OF A WRINKLE IN THE FABRIC COVERING ON THE TOP WING (INBOARD) TRAILING EDGE, THE DRAG/ANTI-D RAG WIRE REAR ATTACHMENT BLOCK AT REAR SPAR WAS FOUND BROKEN WHICH IN TURN CAUSED THE TRAILING EDGE TO CENTRE HOOP ATTAC HMENT BLOCK TO FAIL 1 Q 7 1 3O 3 O EXPA1Q71 1E10 5 N P4EA 1997012300086 19970123 00086 GL 1997 1 23 AU960931 1 19960708 G 2120 INTAKE AMTR VAREZE VARIEZE GL LYC O320 O320D3G 41508 EA AIR DISTRIBUTION BLOCKED OFF W K NONE O OTHER CR CRUISE 1 AU S (AUS) COCKPIT AIR INTAKE ILLEGALLY MODIFIED (SEALED OFF) PREVENTING AIR INTAKE INTO COCKPIT AND CAUSING LACK OF OXYGEN T O PILOT AND PASSENGER - TWO MONTHS PRIOR TO THIS INCIDENT THE PILOT SEALED THE COCKPIT AIR INTAKE OPENING LOCATED IN FRO NT OF THE NOSE WHEELCOMPARTMENT WITH MASKING TAPE - TO COMPENSATE FOR THE AIR LOSS, THE PILOT WOULD OPEN THE LANDING LI GHT TO RECEIVE COOLING AIR INTO THE CABIN - BECAUSE THIS FLIGHT WAS GOING TO BE AROUND 9500 FT AND HEADING SOUTH (FROM N ORTHERN QUEENSLAND) THE LANDING LIGHTWAS CLOSED CAUSING THE LACK OF AIR TO THE COCKPIT - UNAPPROVED PART/MODIFICATION 1 M 7 1 3O 3 O EXPA1M71 E274 1997012300087 19970123 00087 CE 1997 1 23 AU960932 1 19960301 G 3230 98812021 SOLENOID CESSNA 210 210L 2073448 CE CONT O520 IO520L 17032 SO MCAULY 3A32C D3A32C88 GL LG EXT-RETRACT S FAULTY W O OTHER J WARNING INDICATION DE DESCENT 1 AU S 27006112 (AUS) LANDING GEAR CONTROL SOLENOID PNO 9881202-1 HAD INSULATION BREAKDOWN - LANDING GEAR FAILED TO EXTEND ELECTRICALLY - EXTENDED SAFELY WITH MECHANICAL HYDRAULIC HAND PUMP 1 H 7 1 3O 3 O 3A21 E5CE 5 C P21EA 1997012300088 19970123 00088 EA 1997 1 23 AU960933 2 19960503 G 8530 LW16740 VALVE PARTEN P68 P68C 6780105 EU LYC O360 IO360A1B6 41514 EA HARTZL HCC2Y HCC2YK2 GL R ENGINE CYL EXH BROKEN W K NONE E VIBRATION/BUFFET CR CRUISE 1 AU S L2162651A L2162651A (AUS) ENGINE NO3 CYLINDER EXHAUST VALVE BROKEN - DAMAGE TO PISTON AND CYLINDER BORE - SUSPECT CAUSED BY OPERATING ENGIN E AT CONTINUOUS HIGH TEMPERATURES WITH LEAN MIXTURES 1 H 7 2 3O 3 O A31EU 1E10 5 C P920 1997012300089 19970123 00089 CE 1997 1 23 AU960934 1 19960702 G 2450 TR992 POWER UNIT CESSNA 500 560CESSNA 2076750 CE PWA JT15 JT15D4 52112 NE AC POWER DISTRIB BURNT OUT W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RH NO4 POWER UNIT BURNT OUT CAUSING COMPLETE FAILURE TO THE RH CABIN LIGHTING CIRCUIT - INVERTER PNO 18-994 FOUND UNSERVICEABLE PROBABLY DUE TO THE FAILURE OF POWER UNIT - FOUND DURING INSPECTION IAW AD/ELECT/67 AND ALC IB 90-001 2 L 7 2 4F 4 F RT A22CE E1NE 1997012300090 19970123 00090 CE 1997 1 23 AU960935 1 19960703 G 5511 53200197 SPAR CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA MCAULY 1C160 1C160DTM GL HORZ STAB SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) TAILPLANE FORWARD SPAR AND CENTRE SKIN CRACKED - FOUND DURING INSPECTION IAW AD/C170/59 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 1997012800007 19970128 00007 NE 1997 1 28 AU960936 2 19960703 G 7200 ENGINE PWA PW120 PW123 NE ENGINE (TURBINE/ POWER LOSS W C D ABORTED TAKEOFF RETURN TO BLOCK R PARTIAL RPM/PWR LOSS TO TAKEOFF 1 AU S PCE123269 (AUS) NO1 ENGINE POWER LOSS - ON TAKE-OFF ENGINE POWER SET AT 90% TORQUE - POWER ROLLED BACK ON NO1 ENGINE BY 2% THEN R ECOVERED -TORQUE INCREASED TO 100% - TAKE-OFF WAS ABORTED AT APPROXIMATELY 85 KNOTS 4 T E20NE 1997012300091 19970123 00091 WP 1997 1 23 AU960938 2 19960526 G 7261 8650914 GASKET GARRTT TPE331 TPE33110U 01514 WP ROTOL R333 R333482F12 GL TURBINE ENGINE O DETERIORATED W K NONE K J FLUID LOSS WARNING INDICATION DE DESCENT 1 AU S P42140 (AUS) TURBINE OIL SYSTEM SCAVENGE PUMP COVER GASKET DETERIORATED AND LEAKING - COVER WAS LOOSE ALTHOUGH THE RETAINING SC REWS WERE STILL TIGHT 4 T E4WE 6 C P61GL 1997012300092 19970123 00092 NE 1997 1 23 AU960939 2 19960527 G 7260 3022375 OIL SEAL PWA PWA120 PW125B NE TURBINE ENG. ACC DAMAGED W K NONE K J FLUID LOSS WARNING INDICATION DE DESCENT 1 AU S TM124050 (AUS) ENGINE DRIVEN HYDRAULIC PUMP DRIVE SEAL LEAKING - PARTIAL LOSS OF ENGINE OIL 4 T E20NE 1997012300093 19970123 00093 EA 1997 1 23 AU960940 2 19960709 G 7414 M3548 ROTOR SLICK 4270 CESSNA 172 172P 2072436 CE LYC O360 O360A4M 41514 EA MCAULY 1A170 1A170FFA GL ELEC PWR SUPPLY BROKEN W K NONE O OTHER CR CRUISE 1 AU S 920 92100032 L3256036A DJ049 (AUS) MAGNETO ROTOR SHAFT FAILED AT THE CONTACT BREAKER END AT BASE OF CUTOUT FOR FIBRE CAM CAUSING TOTAL FAILURE OF MAG NETO - UNIT HAD OPERATED FOR 312 HRS SINCE INSPECTION IAW AD/ELEC/48 1 H 7 1 3O 3 O NT 3A12 E286 5 N P857 1997012300534 19970123 00534 SO 1997 1 23 AU960941 1 19960705 G 7922 L153668A VALVE PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA HARTZL HCE3Y HCE3YR2 GL AC,ENG OIL DIST FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S L153668A L153668A (AUS) ENGINE OIL COOLER THERMOSTATIC BYPASS VALVE (VERNATHERM) RETENTION NUT SEPARATED FROM UNIT - THE NUT WAS LOCATED I N THE OIL SUPPLY LINE TO THE OIL COOLER - SUSPECT AD/LYC/78 HAD NOT BEEN COMPLIED WITH 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 1997012300535 19970123 00535 CE 1997 1 23 AU960942 1 19960704 G 3230 HM4 ROD END CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO MCAULY 3AF32C 3AF32C87 GL LG EXT-RETRACT S FAILED W K NONE O OTHER DE DESCENT 1 AU S (AUS) LH MLG UPLOCK PUSH/PULL ROD ASSEMBLY PNO 0641142-1 FAILED AT ROD END IN THE AREA JUST OUTBOARD OF CHECKNUT PNO AN3 16-4R ON THE INBOARD RODEND - SUSPECT CAUSED BY SLIGHT MISRIGGING OF LANDING GEAR 1 L 7 2 3O 3 O 3A10 E5CE 5 C P22EA 1997012300536 19970123 00536 1997 1 23 AU960943 1 19960626 G 6120 70953 NUT MCAULY C290D2T4 PROP CNTRL SYS SEPARATED W K NONE O OTHER IN INSP/MAINT 1 AU S 1930 70953 (AUS) PROPELLER CONSTANT SPEED UNIT (CSU) FLYWEIGHT PIN NUT SEPARATED -THE PIN SECURES THE FLYWEIGHT AND DISC TOGETHER ( FLYWEIGHT ASSEMBLY PNO A20063) - THE PIN THEN MOVED OUT DUE TO CENTRIFUGAL FORCE CONTACTING THE INSIDE BODY AND WORE A G ROOVE 0.794MM (0.0312IN) DEEP - THE HEAD OF THE PIN HAD ALSO WORN AWAY - THE NUT TAB WASHER WAS FOUND JAMMED BETWEEN THE SPEEDER SPRING AND THE END FITTING - THE FLYWEIGHT SPACERS WERE FOUND LOOSE IN FLYWEIGHT CHAMBER BUT THERE WAS NO SIGN OF THE NUT 1997012300537 19970123 00537 EA 1997 1 23 AU960944 2 19960705 G 8520 LW17060 CRANKSHAFT LYC O320 O320D3G 41508 EA R ENGINE POWER S CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 2000 (AUS) CRANKSHAFT CRACKED INTERNALLY - CRACK LENGTH APPROXIMATELY 50MM (2IN) - THE CRACK WAS LOCATED AT THE BASE OF A CO RROSION PIT AND WAS FOUND AFTER THE INTERNAL DIAMETER WAS HONED TO REMOVE THE PIT - FOUND DURING INTERNAL CORROSION INS PECTION OF A CRANKSHAFT IAW LYCOMING SB 505A 3 O E274 1997012300538 19970123 00538 1997 1 23 AU960945 1 19960628 G 6120 B20897 COVER MCAULY DCFS290D7T3 PROP CNTRL SYS OVERSIZE W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S 97 790876 (AUS) PROPELLER CONSTANT SPEED UNIT (CSU) CONTROL SHAFT AND COVER LEAKING OIL - THE CSU WAS RETURNED TO THE OVERHAUL FA CILITY WHEREIT WAS DISMANTLED - INSPECTION OF THE COVER BORE FOUND IT OVERSIZE BY 0.0762MM (0.003IN) - INSPECTION FOUND 22 OTHER COVERS IN STOCK TO BE ALSO OVERSIZE - MANUFACTURING ERROR/QUALITY CONTROL PROBLEM 1997012300539 19970123 00539 SO 1997 1 23 AU960946 2 19960705 G 8520 6461402 STUD CESSNA 210 210E 2073416 CE CONT O520 IO520A 17032 SO MCAULY 2A34C E2A34C73 GL R ENGINE POWER S SHEARED W K NONE O OTHER IN INSP/MAINT 1 AU S 76 1106324A (AUS) NO5 CYLINDER BASE STUD (1OFF) SHEARED OFF - STUD WAS FOUND IN BOTTOM COWL 1 H 7 1 3O 3 O 3A21 E5CE 5 C P3EA9 1997012300540 19970123 00540 EU 1997 1 23 AU960947 1 19960711 G 5713 0303 STRINGER PARTEN P68 P68B EU LYC O360 IO360A1B6 41514 EA HARTZL HCC2Y HCC2YK2 GL OUTER WING SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH AND RH WING AND ENGINE NACELLE UPPER EIGHT STRINGERS (4OFF EACH SIDE) BETWEEN RIBS 6 AND 8 CRACKED - FOUND DUR ING INSPECTION IAW PARTENAVIA SB93 AND AD/P68/42 1 H 7 2 3O 3 O A31EU 1E10 5 C P920 1997012300541 19970123 00541 1997 1 23 AU960949 4 19960626 G 3418 450742 DETECTOR C522014 PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA HARTZL HCE3Y HCE3YR2 GL ELEVATOR CONTROL FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) STALL WARNING SYSTEM LIFT DETECTOR MICROSWITCH OPEN CIRCUITED 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 1997012300542 19970123 00542 EU 1997 1 23 AU960950 1 19960424 G 5711 SPAR WEB FOKKER F28 F28MK4000 4990810 EU RROYCE SPEY SPEY55515 54521 EU OUTER WING SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH OUTER WING REAR SPAR WEB CRACKED AT APPROXIMATELY STN 5115 RUNNING FROM LOWEST RIVET - CRACK LENGTH 5MM (0.196 IN) - FOUND DURING EDDY CURRENT INSPECTION IAW ER F28-57-10-22C PART 2 2 L 7 2 4F 4 F RT A20EU E2EU 1997012300543 19970123 00543 EU 1997 1 23 AU960951 1 19960503 G 2450 72741484OAV2 TERMINAL BAC 146 146300A 1500267 EU LYC ALF502 ALF502R5 41580 NE AC POWER DISTRIB ARCING W K NONE H ELECT. POWER LOSS-50 PC CR CRUISE 1 AU S (AUS) NO1 AC GENERATOR BUS TERMINAL BLOCK `A' PHASE `B' STUD ARCING 2 H 7 4 4F 4 F RT A49EU E6NE 1997012300544 19970123 00544 SO 1997 1 23 AU960952 2 19960214 G 8520 629726AB CAMSHAFT CONT TSIO520E CESSNA 402 402A 207590M CE CONT O520 TSIO520E 17040 SO MCAULY 3AF32C 3AF32C87 GL R ENGINE POWER S FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S 1232 183701R (AUS) RH ENGINE CAMSHAFT FAILED AND COMPLETELY SEPARATED APPROXIMATELY 30MM (1.18IN) FROM THE FORWARD END CONTAINING THE EXPANSION PLUG 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 1997012300545 19970123 00545 CE 1997 1 23 AU960953 1 19960709 G 2721 12614715 WHEEL 12614621 CESSNA 210 210N 2073453 CE CONT O520 IO520L 17032 SO MCAULY D3A34 D3A34C404 GL RUDDER CONTROL S WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RUDDER TRIM WHEEL GEAR PNO 1261471-5 AND SPROCKET PNO 1261462-1 HAD WORN TEETH - TEETH WERE WORN TO THE EXTENT TH AT THE TEETH SLIPPED PAST EACH OTHER WITHOUT ACTIVATING THE CHAIN 1 H 7 1 3O 3 O 3A21 E5CE 5 C P47GL 1997012300546 19970123 00546 SO 1997 1 23 AU960954 1 19960701 G 3260 451848 MICROSWITCH PIPER PA32 PA32R301 7103218 SO LYC O540 IO540K1G5 41532 EA LG POSITION IND ARM BROKEN W K NONE O N OTHER FALSE WARNING LD LANDING 1 AU S (AUS) NOSE LANDING GEAR DOWNLOCK MICROSWITCH ACTUATING LEVER ARM BROKEN OFF 1 L 7 1 3O 3 O A3SO 1E4 1997012300547 19970123 00547 CE 1997 1 23 AU960955 1 19960630 G 3244 277K061 TYRE GOODYEAR 5003064 CESSNA 404 404CESSNA 2075901 CE MCAULY 3FF32 3FF32C501 GL LG WHEEL/BRAKE S FAULTY W K NONE O OTHER CR CRUISE 1 AU S SAM13 (AUS) LH MAIN LANDING GEAR TYRE JAMMED IN WING CUTOUT PREVENTING LANDING GEAR FROM LOCKING IN THE `UP' POSITION - SUSPEC T CAUSED BY OUTSIDE DIAMETER OF TYRE BEING TOO LARGE - TYRE WAS R1 (1ST RETREAD) 1 L 7 2 3O A25CE 5 C P45GL 1997012300548 19970123 00548 1997 1 23 AU960956 4 19960113 G 2561 9409871940986 CYLINDER DUNLOP LIFEJACKET SNIAS AS332 AS332L 8680809 EU TMECA MAKILA MAKILA1A 60040 EU EMERGENCY EQUIP LOOSE W K NONE O OTHER IN INSP/MAINT 1 AU S 940987194 (AUS) LIFE JACKET CO2 INFLATION BOTTLES UNSCREWED FROM FIRING MECHANISM- LIFE JACKET SERIAL NUMBERS 9409871 AND 9409866 - ANTI-TAMPERING INDICATORS WERE STILL IN PLACE 2 G 7 2 4U 4 U H4EU E12NE 1997012300549 19970123 00549 EU 1997 1 23 AU960957 1 19960703 G 2910 332A75211100 PIPE SNIAS AS332 AS332L 8680809 EU TMECA MAKILA MAKILA1A 60040 EU MAIN HYD SYS CRACKED W K NONE K J FLUID LOSS WARNING INDICATION CR CRUISE 1 AU S (AUS) NO2 HYDRAULIC SYSTEM PIPE CRACKED AND LEAKING - LOSS OF HYDRAULICFLUID 2 G 7 2 4U 4 U H4EU E12NE 1997012300550 19970123 00550 SO 1997 1 23 AU960958 1 19960703 G 2425 AMMETER PIPER PA32 PA32300 7103212 SO LYC O540 IO540K1A5 41532 EA HARTZL HCC2Y HCC2YK1 GL AC INDICATING SY FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) AMMETER FLUCTUATING OVER 20 AMPS 1 L 7 1 3O 3 O A3SO 1E4 5 C P920 1997012800014 19970128 00014 GL 1997 1 28 AU960959 2 19960712 G 7320 6870035 PIPE ALLSN 250C20R HUGHES 369 369E 4470707 WP ALLSN 250C 250C20R2 GL ENG,FUEL CONTROL LOOSE W K NONE O OTHER IN INSP/MAINT 1 AU S CAE295286 CAE295286 (AUS) ENGINE POWER TURBINE GOVERNOR TO FUEL CONTROL UNIT PIPE (PC LINE)LOOSE AT FCU END - `B' NUT HOLDING BY APPROXIMATE LY HALF A THREAD 1 G 7 1 3U 3 U H3WE E4CE 1997012300551 19970123 00551 GL 1997 1 23 AU960960 2 19960626 G 7240 6899081 LINER ALLSN 250C30 SNIAS 350 AS350B 8680801 EU ALLSN 250C 250C30 03013 GL TURBINE ENGINE C FAILED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S 921 CAT90303 CAE890502 (AUS) ENGINE COMBUSTION LINER FAILED - SPACER CLIPS (6OFF) PNO 23003111SEPARATED FROM LINER PRIMARY SECTION PNO 23004562 AT THE VACUUM BRAZED JOINT ALLOWING THE WATER SHIELD TO SEPARATE FROM THE LINER AND AT LEAST ONE CLIP TO CONTACT THE TU RBINE CAUSING FOD - PERSONNEL/MAINTENANCE ERROR - DEFECTIVE REPAIRS CARRIED OUT IN USA 1 G 7 1 3U 3 U H9EU E1GL 1997012300552 19970123 00552 SO 1997 1 23 AU960961 2 19960712 G 8550 N3N SPRING CESSNA 12509211 CESSNA 210 210M 2073450 CE CONT O520 IO520L 17032 SO MCAULY D3A34 D3A34C404 GL R ENGINE INT OIL BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S N3N 240713R 942330 (AUS) ENGINE OIL FILTER ADAPTER PNO 1250921-1 BYPASS SPRING BROKEN INTOTHREE PIECES - VALVE CAP PNO 0756022-1 FOUND ON O IL PRESSURE RELIEF VALVE SEAT - FURTHER INSPECTION FOUND SPRINGS ON TWO OTHER AIRCRAFT BADLY WORN 1 H 7 1 3O 3 O 3A21 E5CE 5 C P47GL 1997012300553 19970123 00553 SW 1997 1 23 AU960963 1 19960615 G 6320 214040118001 BEARING BELL TRANSMISSION BELL 212 212 1181420 SW PWA PT6T PT6T3B 52045 NE MAIN ROTOR TRANS FAULTY W K NONE J WARNING INDICATION CR CRUISE 1 AU S 3944 ABW45031 CPPS60614 (AUS) TRANSMISSION MAIN INPUT QUILL DUPLEX BEARING CONTAINED ONE DELAMINATED BALL - NIL DAMAGE TO INNER RACE 1 G 7 1 4U 4 U H4SW E22EA 1997012300554 19970123 00554 1997 1 23 AU960964 4 19960521 G 2370 CVR SYSTEM FRCHLD A100A SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE33111U 01514 WP AUDIO/VIDEO MONI INCORRECT WIRED W A K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) COCKPIT VOICE RECORDER INCORRECTLY WIRED - RECORDS ONLY AREA MICROPHONE CHANNEL - PERSONNEL/MAINTENANCE ERROR 2 L 7 2 4T 4 T RT A8SW E4WE 1997012300555 19970123 00555 CE 1997 1 23 AU960965 1 19960623 G 3230 8A0900046 HOSE 8000 CESSNA 208 208 2073702 CE PWA PT6 PT6A114 52043 NE LG EXT-RETRACT S INCORRECT REPAIR W K NONE W K INADEQUATE Q C FLUID LOSS TO TAKEOFF 1 AU S 80068 (AUS) RH MAIN LANDING GEAR FLOAT RETRACTION ACTUATOR LEAKING FROM `UP' PRESSURE HOSE - LOSS OF HYDRAULIC FLUID - INVESTI GATION FOUNDTHAT HOSE BRAIDING HAD BEEN DAMAGED SOME TIME PREVIOUSLY AND DAMAGE HAD BEEN REPAIRED WITH AN UNKNOWN BLACK SUBSTANCE AND WRAPPED WITH PVC TAPE - SUSPECT DAMAGE AND REPAIR DONE DURING FLOAT ASSEMBLY - THIS AIRCRAFT IS FITTED WI TH WIPLINE FLOATS - PERSONNEL/MAINTENANCE ERROR - UNAPPROVED REPAIR 1 H 7 1 3T 3 T NT A37CE E4EA 1997012300556 19970123 00556 CE 1997 1 23 AU960966 1 19960620 G 2510 SEAT BELT CESSNA 182 182 2072702 CE FLIGHT COMPARTME WRONG PART W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) SEAT BELT HARDWARE AND WEBBING WAS OF AUTOMOTIVE ORIGIN - PERSONNEL/MAINTENANCE ERROR - UNAPPROVED PART 1 H 7 1 3O NT 3A13 1997012300557 19970123 00557 SO 1997 1 23 AU960967 2 19960702 G 8520 COLLAR BEECH 95 95B55 1152729 CE CONT O470 IO470L 17026 SO HARTZL HCC2Y BHCC2YF2 GL R ENGINE POWER S WORN W K NONE K J FLUID LOSS WARNING INDICATION CR CRUISE 1 AU S 9175244 (AUS) ENGINE LOW OIL PRESSURE - SUSPECT CRANKSHAFT TRANSFER COLLAR OR MAIN BEARINGS WORN 1 L 7 2 3O 3 O RT 3A16 3E1 5 C P920 1997012300558 19970123 00558 SO 1997 1 23 AU960968 2 19960625 G 8530 646743 PISTON CONT TSIO360GB4 MOONEY M20 M20K 5870220 SW CONT O360 TSIO360G 17025 SO HARTZL HCC2Y BHCC2YF1 GL R ENGINE CYLINDE WRONG PART W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S 1000 309728 (AUS) NO3 CYLINDER/PISTON COMBINATION INCORRECT - A +015IN OVERSIZE PISTON PNO 646743 WAS FITTED TO A STANDARD SIZE CYL INDER PNO 649484 - PISTON HAD PICKED UP IN CYLINDER BORE - METAL CONTAMINATION OF OIL SYSTEM - CYLINDER HAD BEEN CHANGED ON 13NOVEMBER 1995 AT 2027 HOURS - PERSONNEL/MAINTENANCE ERROR - UNAPPROVED PART 1 L 7 1 3O 3 O 2A3 E9CE 5 C P920 1997012300559 19970123 00559 SO 1997 1 23 AU960969 2 19960624 G 7414 1051324 SPRING BENDIX S6RN25 CESSNA 180 180 2072602 CE CONT O470 O470J 17026 SO MCAULY 2A36C 2A36C29 GL ELEC PWR SUPPLY BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S 510001 403623A 621508 (AUS) LH MAGNETO IMPULSE COUPLING SPRING BROKEN 1 H 7 1 3O 3 O NC 5A6 E273 5 C P880 1997012800015 19970128 00015 EA 1997 1 28 AU960970 2 19960701 G 7414 91050078 POINTS SLICK 4347 HUGHES 269 269C 4470504 WP LYC O360 HIO360C1A 41514 EA ELEC PWR SUPPLY OUT OF ADJUST W E ENGINE SHUTDOWN Y ENGINE STOPPAGE NR NOT REPORTED 1 AU S 91050078 (AUS) MAGNETO POINTS GAP TOO SMALL 1 G 7 1 3O 3 O 4H12 1E10 1997012300560 19970123 00560 CE 1997 1 23 AU960971 1 19960628 G 7430 A1196A SWITCH CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA MCAULY 1C160 1C160DTM GL IGNITION SWITCH BURNT W K NONE O OTHER IN INSP/MAINT 1 AU S L240676 (AUS) ENGINE IGNITION SWITCH CONTACT CUPS (3OFF) PNO A-1196-A AND TERMINAL BOARD PNO A-546-A WORN AND BURNT - FOUND DUR ING INSPECTION IAW AD/ELEC/59 AMDT1 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 1997012300561 19970123 00561 CE 1997 1 23 AU960972 1 19960501 G 2510 SEAT BELT CESSNA 150 150G 2071816 CE CONT O200 O200A 17020 SO MCAULY 1A101 1A101DCM GL FLIGHT COMPARTME WRONG PART W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) SEAT BELTS CONTAINED NON APPROVED HARDWARE AND WEBBING - UNAPPROVED PART - PERSONNEL/MAINTENANCE ERROR 1 H 7 1 3O 3 O 3A19 E252 5 N P918 1997012300562 19970123 00562 CE 1997 1 23 AU960973 1 19960704 G 2510 SEAT BELT CESSNA 172 172G 2072420 CE CONT O300 O300C 17022 SO MCAULY 1C172 1C172EM GL FLIGHT COMPARTME WRONG PART W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) SEAT BELTS MANUFACTURED FROM AUTOMOTIVE HARDWARE AND WEBBING - UNAPPROVED PART - PERSONNEL/MAINTENANCE ERROR 1 H 7 1 3O 3 O NT 3A12 E253 5 N P910 1997012300563 19970123 00563 1997 1 23 AU960974 4 19960703 G 2562 506590101 BATTERY NARCO ELT CESSNA 206 U206F 2073333 CE CONT O520 TSIO520C 17040 SO MCAULY 3A32C D3A32C88 GL EMERGENCY LOCATO LEAKING W K NONE O OTHER IN INSP/MAINT 1 AU S 22042 (AUS) ELT BATTERY PACK LEAKING - CORROSIVE MATERIAL FROM THE BATTERY HAD LEAKED ONTO THE AIRFRAME STRUCTURE CAUSING CORR OSION - EXPIRRATION DATE OF BATTERY IS 22 MAY 1996 1 H 7 1 3O 3 O A4CE E8CE 5 C P21EA 1997012300564 19970123 00564 SO 1997 1 23 AU960975 2 19960621 G 7414 A27432 CAPACITOR BENDIX 1200SERIES CONT O520 IO520B 17032 SO MCAULY 3A32C 3A32C76 GL ELEC PWR SUPPLY CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S A27432 1219148B 735437 (AUS) RH MAGNETO CAPACITOR CORRODED IN AREA OF CONTACT WITH CASE 3 O E5CE 5 C P21EA 1997012300565 19970123 00565 NM 1997 1 23 AU960978 1 19960609 G 2910 82940010107 PIPE DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE MAIN HYD SYS LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S 17897 (AUS) HYDRAULIC PIPE LEAKING FROM PIN HOLE IN PIPE - LOSS OF HYDRAULIC FLUID 2 H 7 2 4T 4 T RT A13NM E20NE 1997012300566 19970123 00566 EU 1997 1 23 AU960979 1 19960715 G 3210 BEARING BAC 146 146300A 1500267 EU LYC ALF502 ALF502R5 41580 NE MAIN GEAR SYS REQ LUBE W K NONE O OTHER NR NOT REPORTED 1 AU S (AUS) RH AND LH MAIN LANDING GEAR SIDE STAY BEARINGS STIFF - AN ATTEMPTTO REGREASE THE BEARINGS FOUND THAT THE GREASE WO ULD NOT ENTER TH INNER BEARINGS - REMOVAL OF THE SIDE STAYS FOUND THAT THE EXISTING GREASE WAS HARD AND DETERIORATED - BEARINGS LAST GREASEDIN APRIL 1996 - AIRCRAFT HAS A LOW UTILISATION RATE 2 H 7 4 4F 4 F RT A49EU E6NE 1997012300567 19970123 00567 NM 1997 1 23 AU960980 1 19960602 G 2782 111015 PISTON BOEING 727 727277 138408S NM PWA JT8 JT8D15 52051 NE LIFT AUGMNT SYS FRACTURED W K NONE F J FLT CONT AFFECTED WARNING INDICATION AP APPROACH 1 AU S ANSETTSN0 (AUS) NO6 LEADING EDGE KRUEGER FLAP ACTUATOR PISTON PNO 1110-15 BROKEN IN TWO IN THE RADIUS OF THE EXTENDED LOCKING KEY GROOVE 2 L 7 3 4F 4 F RT A3WE E2EA 1997012300568 19970123 00568 NM 1997 1 23 AU960981 1 19960626 G 3246 0534 WHEEL BOEING 737 737376 NM LG WHEEL/BRAKE S CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 0534 (AUS) LH OUTBOARD MAIN WHEEL ASSEMBLY OUTBOARD HALF CRACKED IN SPOKE - FOUND DURING ROUTINE TYRE CHANGE 2 L 7 2 4F RT A16WE 1997012300569 19970123 00569 NM 1997 1 23 AU960982 1 19960506 G 2820 69588063 DIODE BOEING 737 737377 NM FUEL DISTRBUTION BURNT OUT W A K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NO1 REFUELLING VALVE DIODE ASSEMBLY M565 BURNT OUT - SUSPECT CAUSED BY MOISTURE INGRESS WITH SUBSEQUENT FREEZING A T ALTITUDE 2 L 7 2 4F RT A16WE 1997012300570 19970123 00570 NE 1997 1 23 AU960983 2 19960624 G 7261 O-RING BAC 146 146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE TURBINE ENGINE O DAMAGED W K NONE K FLUID LOSS DE DESCENT 1 AU S LF05597A (AUS) NO4 ENGINE MAIN OIL FILTER CAP `O' RING SEAL DAMAGED (CUT) - LOSSOF ENGINE OIL 2 H 7 4 4F 4 F A49EU E6NE 1997012300571 19970123 00571 1997 1 23 AU960984 4 19960618 G 2216 7002800914 ACTUATOR AMD FALC50 FALCON900 2700160 EU AUTOPILOT TRIM S FAULTY W K NONE F W FLT CONT AFFECTED INADEQUATE Q C NR NOT REPORTED 1 AU S 18 (AUS) AUTOMATIC FLIGHT CONTROL SYSTEM (AFCS) YAW DAMPER LINEAR ACTUATOR PIN G TO ACTUATOR HOUSING HAD NO INTERNAL CONNEC TION THEREFORE THE ACTUATOR WAS NOT ELECTRICALLY BONDED TO THE AIRCRAFT MAKING THE SYSTEM SUSCEPTIBLE TO INDUCED VOLTAGE . 2 L 7 3 4F RT A46EU 1997012300572 19970123 00572 GL 1997 1 23 AU960985 3 19960501 G 6140 86595610 SWITCH CESSNA 441 441 2076020 CE HARTZL HCB3T HCB3TN5 GL PROP CNTRL SYS FAULTY W K NONE N FALSE WARNING IN INSP/MAINT 1 AU S (AUS) PROPELLER BETA PRESSURE SWITCH FAULTY 1 L 7 2 3T RT A28CE 6 C P15EA 1997012300573 19970123 00573 GL 1997 1 23 AU960986 3 19960702 G 6140 8659565 SWITCH CESSNA 441 441 2076020 CE HARTZL HCB3T HCB3TN5 GL PROP CNTRL SYS FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) PROPELLER BETA PRESSURE SWITCH FAULTY 1 L 7 2 3T RT A28CE 6 C P15EA 1997012300574 19970123 00574 CE 1997 1 23 AU960987 1 19960709 G 6120 8659565 SWITCH CESSNA 441 441 2076020 CE HARTZL HCB3T HCB3TN5 GL PROP CNTRL SYS FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) PROPELLER BETA PRESSURE SWITCH FAULTY 1 L 7 2 3T RT A28CE 6 C P15EA 1997012800016 19970128 00016 EU 1997 1 28 AU960988 1 19960509 G 2782 02967SN012 ACTUATOR AIRBUS 320 A320212 EU WING TE SYS FAULTY W K NONE F FLT CONT AFFECTED NR NOT REPORTED 1 AU S 02967SN01 (AUS) WING LHS OUTBOARD NO2 AND NO5 SLAT ACTUATORS FAULTY - SUSPECT CAUSED BY INCREASED BREAKOUT TORQUE AT LOW TEMPERAT URES 2 L 7 2 4F RT A28NM 1997012300575 19970123 00575 EU 1997 1 23 AU960989 1 19960305 G 5220 DOOR FOKKER F28 F28MK4000 4990810 EU RROYCE SPEY SPEY55515 54521 EU CABIN EMERG DOOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH AND RH OVERWING EMERGENCY EXIT DOOR OUTER RADIUS CRACKED IN THE FOLLOWING AREAS:-1. RH FORWARD EMERGENCY EXIT C RACKED IN FORWARD AND AFT LOWER CORNERS - CRACK LENGTH 25.4MM (1IN) 2. LH REAR EMERGENCY EXIT CRACKED IN LOWER AFT CORNE R - CRACK LENGTH 6.35MM (0.25IN) 2 L 7 2 4F 4 F RT A20EU E2EU 1997012300576 19970123 00576 EU 1997 1 23 AU960990 1 19960305 G 5312 WEB FOKKER F28 F28MK4000 4990810 EU RROYCE SPEY SPEY55515 54521 EU MAIN FRAME SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) REAR PRESSURE BULKHEAD WEB LOCATED BETWEEN HORIZONTAL BEAMS II AND III AND VERTICAL BEAMS 425L AND 1050L CRACKED V ERTICALLY - CRACK LENGTH 52MM (2IN) - FOUND DURING EDDY CURRENT INSPECTION IAW ER F28-53-10-15K PART 4 2 L 7 2 4F 4 F RT A20EU E2EU 1997012300577 19970123 00577 NM 1997 1 23 AU960991 1 19960701 G 5310 A0202 FRAME ROBSIN R22 R22BETA NM LYC O320 O320B2C 41508 EA MAIN FRAME SYS BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S 1170 (AUS) FUSELAGE UPPER FRAME TUBE BROKEN IN AREA OF LH GEARBOX MOUNT CLUSTER 1 G 7 1 3O 3 O H10WE E274 1997012300578 19970123 00578 CE 1997 1 23 AU960992 1 19960501 G 3260 12430192 BRACKET CESSNA 210 210N 2073453 CE CONT O520 IO520L 17032 SO MCAULY D3A34 D3A34C404 GL LG EXT-RETRACT S DISTORTED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LANDING GEAR SQUAT SWITCH BRACKET BENT 1 H 7 1 3O 3 O 3A21 E5CE 5 C P47GL 1997012300579 19970123 00579 GL 1997 1 23 AU960993 3 19960626 G 6114 HUB CESSNA 206 U206F 2073333 CE CONT O520 IO520F 17032 SO MCAULY 3A32C D3A32C90 GL PROPELLER ASSY S CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S 235 691800 (AUS) PROPELLER HUB CRACKED AND LEAKING IN TWO PLACES 1 H 7 1 3O 3 O A4CE E5CE 5 C P21EA 1997012300580 19970123 00580 EA 1997 1 23 AU960994 2 19960501 G 7320 3024973 COUPLING EMB 110 EMB110P1 3260122 SO PWA PT6 PT6A34 52043 EA HARTZL HCB3T HCB3TN3 GL ENG,FUEL CONTROL SHEARED W E ENGINE SHUTDOWN O OTHER DE DESCENT 1 AU S 57172 (AUS) RH ENGINE DRIVEN FUEL PUMP TO FCU DRIVE COUPLING SHEARED - SUSPECT CAUSED BY FAILURE OF FCU FRONT BEARING - ENGINE SUFFERED A MAJOR OVERTEMPERATURE, OVERTORQUE AND OVERSPEED 1 L 7 2 4T 4 T A21SO E4EA 6 C P15EA 1997012300581 19970123 00581 CE 1997 1 23 AU960995 1 19960628 G 3230 1018100211 TORQUE TUBE BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL LG EXT-RETRACT S WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MAIN LANDING GEAR RETRACTION MECHANISM TORQUE TUBE HAD A GROOVE WORN AROUND ONE END - SUSPECT CAUSED BY DISPLACED /INCORRECTLYFITTED ADEL CLIP 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 1997012300582 19970123 00582 CE 1997 1 23 AU960996 1 19960626 G 5312 121340711 BULKHEAD CESSNA 206 U206F 2073333 CE CONT O520 IO520F 17032 SO MCAULY 3A32C D3A32C90 GL MAIN FRAME SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FORWARD DOORPOST BULKHEAD CRACKED 1 H 7 1 3O 3 O A4CE E5CE 5 C P21EA 1997012300583 19970123 00583 CE 1997 1 23 AU960997 1 19960704 G 3231 08411065 BELLCRANK CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO MCAULY 3AF32C 3AF32C87 GL LG EXT-RETRACT S BROKEN W K NONE O OTHER NR NOT REPORTED 1 AU S (AUS) LH MAIN LANDING GEAR INNER DOOR OPERATING LINKAGE IDLER BELLCRANKBROKEN 1 L 7 2 3O 3 O 3A10 E5CE 5 C P22EA 1997012300584 19970123 00584 SW 1997 1 23 AU960999 1 19960722 G 7712 2060704481 PIPE BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL ENG PWR IND SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE TORQUE SYSTEM ALUMINIUM PIPE CRACKED AND LEAKING - AIRCRAFT IMPORTED FROM SOUTH AFRICA 1 G 7 1 3U 3 U H2SW E4CE 1997012300585 19970123 00585 WP 1997 1 23 AU961000 2 19960719 G 7261 OIL SYSTEM GARRTT TPE33110UF GARRTT TPE331 TPE33110U 01514 WP ROTOL R333 R333482F12 GL TURBINE ENGINE O CONTAM-METAL W K NONE O J OTHER WARNING INDICATION NR NOT REPORTED 1 AU S 3207 P42036 P42036 (AUS) ENGINE OIL SYSTEM CONTAMINATED WITH METAL PARTICLES 4 T E4WE 6 C P61GL 1997012300586 19970123 00586 EU 1997 1 23 AU961001 1 19960716 G 2910 HTE8815 VALVE BAG JETSTM JETSTM3107 1500215 EU ROTOL R333 R333482F12 GL MAIN HYD SYS FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RH HYDRAULIC SHUT-OFF VALVE FAILED TO OPERATE 2 L 7 2 4T RT BA15CAA 6 C P61GL 1997012300587 19970123 00587 NM 1997 1 23 AU961002 1 19960614 G 6710 A4372 LOCATING TAB ROBSIN JACKSHAFT ROBSIN R22 R22BETA NM LYC O320 O320B2C 41508 EA MAIN RTR CNTRL S BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) COLLECTIVE JACKSHAFT LOCATING TAB BROKEN ALLOWING JACKSHAFT TO FLOAT AND THE MAIN ROTOR REAR CONTROL PUSH-PULL TUB E TO CONTACTTHE LOWER FAIRING FRAME 1 G 7 1 3O 3 O H10WE E274 1997012800017 19970128 00017 EU 1997 1 28 AU961003 1 19960601 G 2910 EO2001170 HOUSING AIRBUS 320 A320212 EU MAIN HYD SYS CRACKED W K NONE K J FLUID LOSS WARNING INDICATION CL CLIMB 1 AU S 0092ANSETT (AUS) YELLOW HYDRAULIC SYSTEM GROUND SERVICING MANIFOLD CRACKED ON REAR FACE IN AREA OF FOUR HOLE PLUGS - REMOVAL OF PLU GS REVEALED THAT THE MANIFOLD HOUSING AND PLUG THREADS WERE CRACKED COMPLETELY THROUGH - LOSS OF HYDRAULIC FLUID 2 L 7 2 4F RT A28NM 1997012300588 19970123 00588 SO 1997 1 23 AU961004 2 19960508 G 8520 IO520F CRANKCASE CESSNA 206 U206F 2073333 CE CONT O520 IO520F 17032 SO MCAULY 3A32C D3A32C90 GL R ENGINE POWER S CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 538 572674 (AUS) CRANKCASE CRACKED FROM NO2 CYLINDER MOUNT PAD 1 H 7 1 3O 3 O A4CE E5CE 5 C P21EA 1997012300589 19970123 00589 NM 1997 1 23 AU961005 1 19960513 G 2612 894481 DETECTOR BOEING 737 737377 NM FIRE DETECTION S CONTAM-WATER W O OTHER N FALSE WARNING CR CRUISE 1 AU S (AUS) APU FIRE DETECTOR CONTAMINATED WITH MOISTURE AND OTHER FOREIGN MATERIAL - FALSE FIRE WARNING CAUSED EXTINGUISHER T O BEDISCHARGED 2 L 7 2 4F RT A16WE 1997012300590 19970123 00590 NM 1997 1 23 AU961006 1 19960528 G 2913 20894 BEARING ABEX 56193 BOEING 737 737377 NM MAIN HYD SYS FAILED W A K NONE K J FLUID LOSS WARNING INDICATION DE DESCENT 1 AU S 220500MFS (AUS) SYSTEM 'A' HYDRAULIC PUMP ELECTRIC MOTOR FAILED - INVESTIGATION FOUND METAL CONTAMINATION - FURTHER INVESTIGATION FOUND THAT THE LOCKWIRE ON TWO ATTACHMENT SCREWS PNO NAS1352-08H6 SECURING CYLINDER BARREL PNO 56550 TO CYLINDER BEARI NG PNO 56445 WASMISSING - LOCKWIRE ON THE REMAINING FOUR SCREWS WAS BROKEN - IN ADDITION THE TRUNNION BEARING PNO 21830 WAS BRINNELED - PUMP HOUSING THRUST BEARING PNO 20894 BREAKING UP 2 L 7 2 4F RT A16WE 1997012300591 19970123 00591 EA 1997 1 23 AU961007 2 19960722 G 8550 LW13388 SEAL PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL R ENGINE INT OIL FAILED W K NONE K FLUID LOSS CR CRUISE 1 AU S L381661A (AUS) ENGINE OIL FILTER ADAPTER SEAL SPLIT AND LEAKING - SUSPECT DUE TO DETERIORATION CAUSED BY OLD AGE 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 1997012300592 19970123 00592 NE 1997 1 23 AU961008 2 19960416 G 7230 310454601 BEARING PWA PWA120 PW125B NE TURBINE ENGINE C WORN W E ENGINE SHUTDOWN O OTHER DE DESCENT 1 AU S 124027 (AUS) RH ENGINE NO4 BEARING FAILED - COMPRESSOR AND TURBINE RUBBING 4 T E20NE 1997012300593 19970123 00593 NM 1997 1 23 AU961009 1 19960717 G 3520 E28180 PBE DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE CREW&PASS OXYGEN FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S ARHH0308 (AUS) PROTECTIVE BREATHING EQUIPMENT (PBE) HAD UNCOMMANDED EXPANSION INSTORAGE CASE 2 H 7 2 4T 4 T RT A13NM E20NE 1997012300594 19970123 00594 SO 1997 1 23 AU961010 2 19960722 G 8550 SPRING CONT TS10520EB CONT O520 TSIO520E 17040 SO R ENGINE INT OIL WRONG PART W K NONE W INADEQUATE Q C TX TAXI/GRND HDL 1 AU S 271406R (AUS) ENGINE OIL PRESSURE RELIEF VALVE SPRING WAS INCORRECT PART - CORRECT SPRING PNO 634150 - UNAPPROVED PART - ENGINE WAS A CONTINENTAL REBUILD ENGINE - SEE ALSO MDR 96/0726 3 O E8CE 1997012300595 19970123 00595 CE 1997 1 23 AU961011 1 19960621 G 5712 A120119 WEB CESSNA 441 CESSNA 441 441 2076020 CE HARTZL HCB3T HCB3TN5 GL OUTER WING SYS DEBONDED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH WING REAR SPAR WEB DISBONDED IN AREA BEHIND ENGINE FIRE BOTTLE- FOUND DURING ULTRASONIC INSPECTION IAW AD/CESSN A400/103 AMDT2 1 L 7 2 3T RT A28CE 6 C P15EA 1997012300596 19970123 00596 CE 1997 1 23 AU961012 1 19960719 G 3233 98820212 BEARING CESSNA 210 210N 2073453 CE CONT O520 IO520L 17032 SO MCAULY D3A34 D3A34C404 GL LG EXT-RETRACT S CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NOSE LANDING GEAR ACTUATOR BEARING END CRACKED IN AREA OF ROLL PINS AS INDICATED IN CESSNA SB95-20 1 H 7 1 3O 3 O 3A21 E5CE 5 C P47GL 1997012300597 19970123 00597 SW 1997 1 23 AU961014 1 19960627 G 2436 484183 RELAY GULSTM 112 114 7630314 SW LYC O540 IO540T4B5 41532 EA HARTZL HCC2Y HCC2YR1 GL DC REGULATOR MIS WIRED W K NONE H W ELECT. POWER LOSS-50 PC INADEQUATE Q C DE DESCENT 1 AU S (AUS) OVERVOLTAGE RELAY INCORRECTLY WIRED - 'BATTERY' AND 'LOAD' LEADS TRANSPOSED CAUSING OVERVOLTAGE RELAY TO MALFUNCTI ON - LOSS OF BATTERY VOLTAGE - LOGBOOK FAILED TO REVEAL ANY WORK CARRIED OUT IN THIS AREA - PERSONNEL/MAINTENANCE ERROR 1 L 7 1 3O 3 O A12SO 1E4 5 C P920 1997012300598 19970123 00598 SO 1997 1 23 AU961015 2 19960528 G 8520 BOLT CESSNA 182 182Q 2072732 CE CONT O470 O470U 17026 SO MCAULY 2A34C 2A34C203 GL R ENGINE POWER S BROKEN W K NONE O OTHER CR CRUISE 1 AU S 286610R (AUS) ENGINE NO5 CYLINDER HOLDDOWN NUTS MISSING AND THROUGH BOLTS BROKEN - CRANKCASE CRACKED 1 H 7 1 3O 3 O NT 3A13 E273 5 C P3EA 1997012300599 19970123 00599 CE 1997 1 23 AU961016 1 19960625 G 2510 SEAT BELT CESSNA 182 182K 2072724 CE CONT O470 O470R 17026 SO MCAULY 2A34C 2A34C66 GL FLIGHT COMPARTME WRONG PART W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) UNAPPROVED SEAT BELT WEBBING AND HARDWARE - UNAPPROVED PART 1 H 7 1 3O 3 O NT 3A13 E273 5 C P3EA 1997012300600 19970123 00600 SO 1997 1 23 AU961017 1 19960702 G 2120 MS3505821 SWITCH PIPER PA28 PA28236 7102815 SO LYC O540 O540J3A5 41532 EA HARTZL HCF2Y HCF2YR1 GL AIR DISTRIBUTION BURNT W K NONE B SMOKE/FUMES/ODORS/SPARKS LD LANDING 1 AU S (AUS) CABIN FRESH AIR BLOWER SWITCH FAULTY - SWITCH WIRES BURNT 1 L 7 1 3O 3 O 2A13 E295 5 C P27EA 1997012300601 19970123 00601 CE 1997 1 23 AU961018 1 19960619 G 3222 12430211 BEARING CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO MCAULY 2A34C D2A34C58 GL NOSE-TAIL GEAR S INCORRECT FIT W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) NOSE LANDING GEAR OLEO UPPER BEARING PNO 1243021-1 AND RETAINER PNO 841200-19 SEPARATED - INVESTIGATION FOUND THA T THE BEARING HAD BEEN INSTALLED UPSIDE DOWN PREVENTING CORRECT SEATING OF THE RETAINER - PERSONNEL/MAINTENANCE ERROR 1 H 7 1 3O 3 O A4CE E5CE 5 C P3EA 1997012300602 19970123 00602 SO 1997 1 23 AU961019 2 19960715 G 7414 10357586 GEAR BENDIX S6RN205 CESSNA 402 402A 207590M CE CONT O520 TSIO520E 17040 SO MCAULY 3AF32C 3AF32C87 GL ELEC PWR SUPPLY STRIPPED W E ENGINE SHUTDOWN O OTHER CR CRUISE 1 AU S 6279008ER (AUS) MAGNETO DISTRIBUTOR GEAR TEETH STRIPPED 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 1997012300603 19970123 00603 SO 1997 1 23 AU961020 2 19960715 G 7414 10382584 POINTS BENDIX SGRN205 CESSNA 402 402A 207590M CE CONT O520 TSIO520E 17040 SO MCAULY 3AF32C 3AF32C87 GL ELEC PWR SUPPLY WORN W K NONE O OTHER CR CRUISE 1 AU S A103642 (AUS) MAGNETO POINTS WORN 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 1997012800018 19970128 00018 SO 1997 1 28 AU961021 2 19960726 G 7414 10357592 SEAL BENDIX S6RSC205 CESSNA 402 402B 207590P CE CONT O520 TSIO520E 17040 SO MCAULY 3AF32C 3AF32C87 GL ELEC PWR SUPPLY LOOSE W K NONE K FLUID LOSS TO TAKEOFF 1 AU S 15 D309606ER (AUS) MAGNETO OIL SEAL LOOSE IN HOUSING ALLOWING MAGNETO TO FILL WITH OIL 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 1997012300604 19970123 00604 EA 1997 1 23 AU961022 2 19960612 G 8530 LW11633 CYLINDER PIPER PA38 PA38112 7103812 SO LYC O235 O235L2C 41505 EA SNSNCH 72C 72CK EA R ENG CYLINDER CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 1159 L1726815 (AUS) ENGINE CYLINDER CRACKED FROM EXHAUST VALVE SEAT THROUGH SPARK PLUG HOLE 1 L 7 1 3O 3 O A18SO E223 5 N P9045 1997012300605 19970123 00605 NM 1997 1 23 AU961023 1 19960716 G 2910 AS116080264 HOSE BOEING 737 737376 NM MAIN HYD SYS BURST W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S (AUS) HYDRAULIC 'B' SYSTEM ENGINE DRIVEN PUMP PRESSURE HOSE BURST - LOSS OF HYDRAULIC FLUID 2 L 7 2 4F RT A16WE 1997012300606 19970123 00606 EU 1997 1 23 AU961024 1 19960720 G 2750 CHA722438 TORQUE TUBE AIRBUS 300 A300B4203 3930306 EU GE CF6 CF650C2 30018 NE FLAP SYS SHEARED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH FLAP TORQUE TUBE SHEARED IN AREA OF ATTACHMENT TO LH SHOCK ABSORBER 2 L 7 2 4F 4 F A35EU E23EA 1997012300607 19970123 00607 EU 1997 1 23 AU961025 1 19960726 G 3246 AHA1489 WHEEL BAC 146 146300A 1500267 EU LG WHEEL/BRAKE S FAILED W K NONE O OTHER LD LANDING 1 AU S MO187 (AUS) NO4 WHEEL ASSEMBLY HAD APPROXIMATELY 381MM TO 457.2MM (15IN TO 18IN) OF THE OUTER RIM MISSING - TYRE WAS STILL INF LATED 2 H 7 4 4F RT A49EU 1997012300608 19970123 00608 SO 1997 1 23 AU961026 1 19960625 G 2822 10470 CIRCLIP WELDON BOOSTPUMP PIPER PA28 PA28180 7102808 SO FUEL DISTRBUTION FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S 139 15626 (AUS) FUEL BOOST PUMP BLADE CIRCLIP SNAPPED 1 L 7 1 3O 2A13 1997012300609 19970123 00609 EU 1997 1 23 AU961027 1 19960722 G 6410 330A12000534 BLADE SNIAS SA330 SA330J 8680612 EU TMECA TURMO4 TURMO4C 60008 EU TAIL ROTOR BLADE FAULTY W K NONE E VIBRATION/BUFFET CL CLIMB 1 AU S WAC6143 (AUS) TAIL ROTOR BLADE LEADING EDGE EROSION STRIP SEPARATED FROM BLADE CAUSING HIGH FREQUENCY VIBRATION - SUSPECT CAUSED BY DEFECTIVE BOND BETWEEN BLADE LEADING EDGE AND EROSION STRIP 2 G 7 2 4U 4 U H4EU E10EU 1997012300610 19970123 00610 SO 1997 1 23 AU961028 1 19960723 G 3213 5768006 HOUSING PIPER PA42 PA42 7104202 SO PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL MAIN GEAR SYS CRACKED W K NONE O OTHER LD LANDING 1 AU S (AUS) RH MAIN LANDING GEAR OLEO HOUSING ASSEMBLY CRACKED FROM TOP TO BOTTOM THROUGH THE SHARP RADIUS AT THE BASE OF THE SIDE BRACE ATTACHMENT LUG - LOSS OF OLEO PRESSURE 1 L 7 2 4T 4 T A23SO E4EA 6 C P15EA 1997012300611 19970123 00611 EA 1997 1 23 AU961029 2 19960717 G 7314 75247 PUMP PIPER PA32 PA32R301 7103218 SO LYC O540 IO540K1G5 41532 EA HARTZL HCC2Y HCC2YK1 GL ENG,FUEL DIST SY FAULTY W K NONE K J FLUID LOSS WARNING INDICATION CR CRUISE 1 AU S L2173248A (AUS) ENGINE DRIVEN FUEL PUMP PUMPING FUEL INTO OIL SUMP LOWERING OIL VISCOSITY AND SUBSEQUENTLY LOWERING OIL PRESSURE - INVESTIGATION FOUND THE PUMP DRAIN LINE BLOCKED INSIDE PUMP AND FAILURE OF BOTH OIL AND FUEL DIAPHRAGMS 1 L 7 1 3O 3 O A3SO 1E4 5 C P920 1997012300612 19970123 00612 EU 1997 1 23 AU961030 1 19960701 G 2820 F128271 HOSE FOKKER F27 F27MK100 4990617 EU RROYCE DART DART5147 EU ROTOL R4304 R1934304 EU FUEL DISTRBUTION FRAYED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUEL PUMP COLLECTOR TANK TO FIREWALL FUEL HOSE LOCATED IN RH WHEEL WELL FRAYED AND WORN - CAUSED BY INCORRECT FITM ENT OF GREASE NIPPLE ON LANDING GEAR - PERSONNEL/MAINTENANCE ERROR 2 H 7 2 4T 4 T A817 E283 6 C P899 1997012300613 19970123 00613 EU 1997 1 23 AU961031 1 19960717 G 3260 RL980961 RELAY STBROS SD3 SD360 8100606 EU PWA PT6 PT6A65R 52043 EA HARTZL HCB5M HCB5MP3 GL LG POSITION IND FAULTY W K NONE O N OTHER FALSE WARNING NR NOT REPORTED 1 AU S (AUS) NOSE LANDING GEAR RELAY FAULTY 2 H 7 2 4T 4 T A41EU E4EA 6 C P44GL 1997012300614 19970123 00614 CE 1997 1 23 AU961032 1 19960715 G 2731 TRIM WHEEL BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL ELEVATOR CONTROL MIS INSTALLED W K NONE F W FLT CONT AFFECTED INADEQUATE Q C TO TAKEOFF 1 AU S (AUS) TRIM WHEEL INCORRECTLY INSTALLED DURING PREVIOUS MAINTENANCE - INCORRECT ORIENTATION OF TRIM INDICATION IN RELATIO N TO TRIM TAB - PERSONNEL/MAINTENACE ERROR 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 1997012300615 19970123 00615 1997 1 23 AU961033 4 19960714 G 2210 AUTOPILOT BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL AUTOPILOT SYSTEM FAULTY W K NONE O OTHER NR NOT REPORTED 1 AU S (AUS) AUTOPILOT SUSPECT FAULTY - GROUND CHECK COULD FIND NO FAULTS - DEFECT NOT CONFIRMED 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 1997012300616 19970123 00616 SO 1997 1 23 AU961034 1 19960625 G 2434 30081001 GENERATOR EMB 120 EMB120 3260201 SO PWA 118 PW118A NE DC GENERATOR-ALT FAULTY W K NONE H ELECT. POWER LOSS-50 PC CL CLIMB 1 AU S 555 (AUS) RH DC GENERATOR FAULTY 2 L 7 2 4T 4 T RT A31SO E20NE 1997012300617 19970123 00617 CE 1997 1 23 AU961035 1 19960724 G 7160 BALANCE TUBE CESSNA 182 182F 2072714 CE CONT O470 O470L 17026 SO MCAULY 2A34C 2A34C66 GL ENG,FUEL DIST SY SEPARATED W K NONE O OTHER CL CLIMB 1 AU S 069700R 735173 (AUS) ENGINE INDUCTION SYSTEM BALANCE TUBE SEPARATED AT ONE END - MOUNT ALSO BROKEN AWAY FROM TUBE 1 H 7 1 3O 3 O NT 3A13 E273 5 C P3EA 1997012300618 19970123 00618 CE 1997 1 23 AU961036 1 19960724 G 6120 8692454 VALVE CESSNA 441 441 2076020 CE HARTZL HCB3T HCB3TN5 GL PROP CNTRL SYS WORN W K NONE O OTHER IN INSP/MAINT 1 AU S 4213 (AUS) PROPELLER FEATHERING VALVE WORN IN ROLL PIN AREA OF THE REAR CLEVIS 1 L 7 2 3T RT A28CE 6 C P15EA 1997012300619 19970123 00619 CE 1997 1 23 AU961037 1 19960702 G 2720 35524138 BELLCRANK BEECH B58 BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO MCAULY 3AF34C 3AF34C502 GL RUDDER CONTROL S FAILED W K NONE F FLT CONT AFFECTED NR NOT REPORTED 1 AU S (AUS) COPILOTS RUDDER BELLCRANK BROKEN IN THE VICINITY OF THE CROSSOVER PUSHROD ATTACHMENT HORN - FURTHER INVESTIGATION FOUND THAT THE FAILURE WAS CAUSED BY THE INCORRECT REMOVAL OF THE RUDDER STOP BAR AND EMBRITTLEMENT OF THE BAR 1 L 7 2 3O 3 O 3A16 E5CE 5 C P22EA 1997012300620 19970123 00620 CE 1997 1 23 AU961038 1 19960724 G 3411 STATIC SYSTEM CESSNA 172 172RG 2072438 CE LYC O360 O360F1A6 41514 EA MCAULY 2D34C B2D34C220 GL ENVIRONMENT DATA MIS INSTALLED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) UNAPPROVED INSTALLATION OF INSTRUMENT STATIC LINE SYSTEM - PERSONNEL/MAINTENANCE ERROR - UNAPPROVED PART 1 H 7 1 3O 3 O 3A17 E286 5 C P7EA 1997012300621 19970123 00621 EU 1997 1 23 AU961039 1 19960723 G 2731 TRIM BAC 146 146100A 1500260 EU LYC ALF502 ALF502R5 41580 NE ELEVATOR CONTROL FOD JAMMED W A K NONE F FLT CONT AFFECTED TO TAKEOFF 1 AU S (AUS) ELEVATOR TRIM JAMMED - INSPECTION FOUND A 100MM (4IN) PAPER CLIP LODGED IN THE CONTROL CABLES ADJACENT TO THE ELEV ATOR TRIM CHAIN (CLIP IS PART OF THE AIRCRAFT TRIM AND IS NORMALLY ATTACHED TO A BULKHEAD IN THE FLIGHT DECK) - INVESTIG ATION ALSO FOUND THEGEARBOX CHAIN LOWER ATTACHMENT BOLT CASTELLATED NUT AND WASHER MISSING 2 H 7 4 4F 4 F RT A49EU E6NE 1997012300622 19970123 00622 GL 1997 1 23 AU961040 2 19960728 G 7323 23007506 GOVERNOR ALLSN 250C20 BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL ENG,FUEL CONTROL FAULTY W K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CR CRUISE 1 AU S 172 CAE821056 CAE821056 (AUS) ENGINE N2 GOVERNOR FAULTY - SUSPECT INTERNAL FAILURE 1 G 7 1 3U 3 U H2SW E4CE 1997012300623 19970123 00623 GL 1997 1 23 AU961041 3 19960726 G 6110 PROPELLER PIPER PA31 PA31350 7103110 SO HARTZL HCE3Y HCE3YR2 GL PROPELLER ASSY S SLUDGED W K NONE O OTHER CL CLIMB 1 AU S DJ10647A107 (AUS) LH AND RH PROPELLERS SLUDGED - PROPELLERS WOULD NOT FEATHER 1 L 7 2 3O A20SO 5 C P33EA 1997012300624 19970123 00624 GL 1997 1 23 AU961042 3 19960722 G 6110 PROPELLER PIPER PA31 PA31350 7103110 SO HARTZL HCE3Y HCE3YR2 GL PROPELLER ASSY S SLUDGED W K NONE O OTHER CR CRUISE 1 AU S DJ8817A (AUS) LH PROPELLER SLUDGED - PROPELLER WOULD NOT FEATHER 1 L 7 2 3O A20SO 5 C P33EA 1997012300625 19970123 00625 EA 1997 1 23 AU961043 2 19960422 G 8520 LW16514 CAMSHAFT LYC LW16507 PIPER PA44 PA44180 7104402 SO LYC O360 O360E1A6 41514 EA HARTZL HCC2Y HCC2YR2 GL R ENGINE POWER S SPALLED W K NONE O OTHER IN INSP/MAINT 1 AU S L54272TL L54272T (AUS) LH AND RH ENGINES HAD SPALLED CAMSHAFT EXHAUST LOBES AND ASSOCIATED TAPPETS - BOTH THE ENGINES ARE OF LATE MODIFI CATION STATUS WITH LARGE TAPPETS AND LUBRICATING SLOTS IN THE TAPPET GUIDE BORES - LW16702 ADDITIVE IS USED AT EACH OIL CHANGE - METAL CONTAMINATION OF OIL SYSTEM 1 L 7 2 3O 3 O A19S0 E286 5 C P920 1997012300626 19970123 00626 EA 1997 1 23 AU961044 2 19960613 G 8530 3116 STUD PIPER PA44 PA44180 7104402 SO LYC O360 O360E1A6 41514 EA HARTZL HCC2Y HCC2YR2 GL R ENGINE CYLINDE BROKEN W K NONE E K VIBRATION/BUFFET FLUID LOSS CR CRUISE 1 AU S (AUS) ENGINE ROCKER ARM STUD BROKEN - PUSHROD BENT - LOSS OF ENGINE OIL 1 L 7 2 3O 3 O A19S0 E286 5 C P920 1997012300627 19970123 00627 EA 1997 1 23 AU961045 2 19960726 G 7322 13662 BRACKET MA45 LYC O360 O360A1F6 41514 EA HARTZL HCF2Y HCF2YR1 GL ENG,FUEL CONTROL CRACKED W K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS DE DESCENT 1 AU S 7503812 L3414636A (AUS) CARBURETTOR FLOAT BRACKET CRACKED CAUSING CARBURETTOR FLOODING 3 O E286 5 C P27EA 1997012300628 19970123 00628 CE 1997 1 23 AU961046 1 19960710 G 5312 BULKHEAD CESSNA 206 TU206G 2073357 CE CONT O520 TSIO520M 17040 SO MCAULY D3A34 D3A34C402 GL MAIN FRAME SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUSELAGE FRONT DOOR POST BULKHEAD CRACKED ON BOTH SIDES - CRACK LENGTHS - RH SIDE 6.35MM (0.25IN) - LH SIDE 4.762 MM (0.1875IN) 1 H 7 1 3O 3 O A4CE E8CE 5 C P47GL 1997020600195 19970206 00195 NM 1997 2 6 AU961047 1 19960723 G 3230 54C546349 VALVE DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE LG EXT-RETRACT S FAULTY W K NONE O J OTHER WARNING INDICATION CL CLIMB 1 AU S (AUS) NOSE LANDING GEAR DOOR SEQUENCING VALVE (SOLENOID) FAULTY 2 H 7 2 4T 4 T RT A13NM E20NE 1997020600196 19970206 00196 WP 1997 2 6 AU961048 1 19960727 G 6220 269A1329 DROOP STOP HUGHES 269A10025 HUGHES 269 269C 4470504 WP LYC O360 HIO360D1A 41514 EA M/R CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MAIN ROTOR DROOP STOP RING CRACKED IN SEVERAL PLACES 1 G 7 1 3O 3 O 4H12 1E10 1997020600197 19970206 00197 NM 1997 2 6 AU961049 1 19960726 G 3234 NA16126 O-RING AN8156D DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE LG EXT-RETRACT S DETERIORATED W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S (AUS) LANDING GEAR SELECTOR VALVE HYDRAULIC UNION (PNO AN815-6D) `O' RING SEAL DETERIORATED AND LEAKING 2 H 7 2 4T 4 T RT A13NM E20NE 1997020600198 19970206 00198 EA 1997 2 6 AU961050 2 19960711 G 8530 145644 VALVE GUIDE CURTIS LKHEED 1049 C121C 5262118 WP WRIGHT R3350 R3350* 67040 EA HAMSTD 43E 43E60 NE R ENGINE CYLINDE WORN W K NONE O OTHER IN INSP/MAINT 1 AU S 946 A613 W560299 (AUS) ENGINE CYLINDER EXHAUST VALVE GUIDE WORN AND LOOSE IN CYLINDER HEAD 2 L 7 4 4R 4 R 6A5 E272 6 C P871 1997020600199 19970206 00199 EU 1997 2 6 AU961051 1 19960730 G 2820 NB57A42463 GASCOLATOR BNORM BN2 BN2B20 1520302 EU LYC O540 IO540K1B5 41532 EA HARTZL HCC2Y HCC2YK2 GL FUEL DISTRBUTION LEAKING W K NONE K FLUID LOSS CR CRUISE 1 AU S L2550048A (AUS) RH ENGINE GASCOLATOR BOWL DISLODGED AND THE CLAMP SPRING ARM DISCONNECTED - FUEL LEAKING 1 H 7 2 3O 3 O A17EU 1E4 5 C P920 1997020600200 19970206 00200 EU 1997 2 6 AU961052 1 19960701 G 2150 B31WA3023 SEPARATOR AMD FALC50 FALCON900 2700160 EU CABIN COOLING SY FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S T556 (AUS) CABIN COOLING SYSTEM LOW PRESSURE WATER SEPARATOR INTERNAL COALESCER SWIRL VANE COLLAPSED - THIS DEFECT WAS RECEIV ED FROM NO34 SQUADRON RAAF AND IS FOR INFORMATION ONLY 2 L 7 3 4F RT A46EU 1997020600201 19970206 00201 EU 1997 2 6 AU961053 1 19960711 G 3230 C242450061 UPLOCK AMD FALC50 FALCON900 2700160 EU LG EXT-RETRACT S FAULTY W K NONE O J OTHER WARNING INDICATION CL CLIMB 1 AU S U375 (AUS) NOSE LANDING GEAR UPLOCK UNIT INTERNAL FAILURE - THIS DEFECT WAS RECEIVED FROM NO34 SQUADRON RAAF AND IS FOR INFOR MATION ONLY 2 L 7 3 4F RT A46EU 1997020600202 19970206 00202 SW 1997 2 6 AU961054 1 19960615 G 2910 2781032273 PIPE FRCHLD SA227 SA227DC 3377521 SW GARRTT TPE331 TPE33112UA 01514 WP MCAULY 4HFR34 4HFR34C652 NE MAIN HYD SYS CRACKED W K NONE O K OTHER FLUID LOSS IN INSP/MAINT 1 AU S (AUS) HYDRAULIC PIPE LOCATED IN LH ENGINE NACELLE AREA CRACKED AND LEAKING ON BEND RADIUS 2 L 7 2 4T 4 T RT A18SW E4WE 6 C 3PNE 1997020600203 19970206 00203 CE 1997 2 6 AU961055 1 19960326 G 3210 BUSHING CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO MCAULY 3AF32C 3AF32C87 GL MAIN GEAR SYS MIS MFG W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) MAIN LANDING GEAR SIDE BRACE BUSHES WORN - INVESTIGATION FOUND THAT BUSHES WERE MANUFACTURED FROM INCORRECT MATERI AL (PHOSPHORBRONZE) - UNAPPROVED PART 1 L 7 2 3O 3 O 3A10 E5CE 5 C P22EA 1997020600204 19970206 00204 CE 1997 2 6 AU961056 1 19960327 G 2750 0860207134 CONTROL CABLE 0860207135 CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO MCAULY 3AF32C 3AF32C87 GL FLAP SYS FRAYED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FLAP CABLES PNO 0860207-134 AND PNO 0860207-135 FRAYED 1 L 7 2 3O 3 O 3A10 E5CE 5 C P22EA 1997022000001 19970220 00001 EU 1997 2 20 AU961057 1 19960520 G 7540 M61069002 CONTACTOR SAAB SF340 340B 7860101 EU GE CT7TP CT79B 30030 NE ROTOL R375 R3754123F21 NE ENG,BLEEDAIR IND OPEN CIRCUIT W K NONE O P OTHER NO WARNING INDICATION NR NOT REPORTED 1 AU S (AUS) LH ENGINE ANTI-ICE SYSTEM CONTACTOR OPEN CIRCUIT 2 L 7 2 4T 4 T RT A52EU E8NE 6 C P17NE 1997020600205 19970206 00205 CE 1997 2 6 AU961058 1 19960705 G 2140 G721526 PUMP CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO MCAULY 3AF32C 3AF32C87 GL HEATING SYSTEM FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S 309 (AUS) CABIN HEATER FUEL PUMP DIAPHRAGM RUPTURED AND LEAKING FUEL INTO SHROUD - SHROUD DRAIN BLOCKED BY WASP NEST 1 L 7 2 3O 3 O 3A10 E5CE 5 C P22EA 1997020600206 19970206 00206 1997 2 6 AU961059 4 19960119 G 2561 80MK2 LIFEVEST SKRSKY S76 S76A 8143006 NE EMERGENCY EQUIPM FAULTY W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) PILOT REPORTED THAT LIFEJACKET MAIN WEBBING RESTRAINING STRAP WAS MISSING (FOUND ON FLOOR OF AIRCRAFT) - FURTHER C HECKING OF AIRCRAFT FLEET FOUND THAT THE STRAP WAS NOT ATTACHED (STITCHED) TO THE JACKET ON A FURTHER SIXTEEN LIFE JACK ETS - ON THREE OFTHESE JACKETS THE STRAP WAS ROUTED THROUGH THE JACKET OUTER VALISE ONLY AND NOT THROUGH THE JACKET ATT ACHMENT POINT -PERSONNEL/MAINTENANCE ERROR 1 G 7 2 3U H1NE 1997020600207 19970206 00207 SO 1997 2 6 AU961060 2 19960710 G 8530 125834CCM CYLINDER CONT IO520M CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO MCAULY 3AF32C 3AF32C87 GL R ENGINE CYLINDE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 66 125834CCM 1258347 (AUS) ENGINE CYLINDER CRACKED IN AREA OF TOP SPARK PLUG HOLE 1 L 7 2 3O 3 O 3A10 E5CE 5 C P22EA 1997020600208 19970206 00208 SO 1997 2 6 AU961061 2 19960711 G 8520 CRANKSHAFT CONT IO470L CONT O470 IO470L 17026 SO R ENGINE POWER S WORN W K NONE O OTHER IN INSP/MAINT 1 AU S CS917524L CS917524L (AUS) CRANKSHAFT MAIN BEARING JOURNALS 0.0508MM (0.002IN) UNDER MINIMUMALLOWABLE LIMITS - CONNECTING ROD JOURNALS 0.0127 MM (0.0005IN) UNDER MINIMUM ALLOWABLE LIMITS - CRANKCASE MAIN TUNNELS ALSO OUT OF LIMITS 3 O 3E1 1997020600209 19970206 00209 WP 1997 2 6 AU961062 2 19960701 G 7510 VALVE CESSNA 441 441 2076020 CE GARRTT TPE331 TPE3318 01514 WP HARTZL HCB3T HCB3TN5 GL ENG,AIR ANTI-ICE FAULTY W K NONE E VIBRATION/BUFFET CR CRUISE 1 AU S P31286 (AUS) RH ENGINE ANTI-ICE VALVE AND PLENUM DRAIN VALVE FAULTY 1 L 7 2 3T 4 T RT A28CE E4WE 6 C P15EA 1997020600210 19970206 00210 WP 1997 2 6 AU961063 2 19960703 G 7230 DIFFUSER CESSNA 441 441 2076020 CE GARRTT TPE331 TPE3318 01514 WP HARTZL HCB3T HCB3TN5 GL TURBINE ENGINE C BIRD STRIKE W K NONE E C VIBRATION/BUFFET F.O.D. TO TAKEOFF 1 AU S P31182 (AUS) LH ENGINE SUFFERED BIRDSTRIKE - COMPRESSOR DIFFUSER VANE LEADING EDGES ROLLED BACK - BIRD REMAINS FOUND IN DIFFUSE R, FUEL NOZZLES AND TURBINE EXHAUST PATH 1 L 7 2 3T 4 T RT A28CE E4WE 6 C P15EA 1997020600211 19970206 00211 CE 1997 2 6 AU961064 1 19960730 G 5753 35165050611 FLAP BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE WING TE SYS DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) WING FLAP DAMAGED BY CONTACT WITH UNKNOWN OBJECT - IMPACT DAMAGE ON UNDERSIDE CAUSED BENDING FROM CENTRE WITH BUCK LING TO THE SPAR AND SKINS MAKING IT UNREPAIRABLE - NO DAMAGE TO MOUNTING POIUNTS OR WING 2 L 7 2 4T 4 T RT A24CE E26NE 1997020600212 19970206 00212 SO 1997 2 6 AU961065 2 19960720 G 8520 530386 BEARING CONT O470L CESSNA 180 180 2072602 CE CONT O470 O470L 17026 SO HARTZL HC82X HC82XF1 GL R ENGINE POWER S SPALLED W K NONE O OTHER IN INSP/MAINT 1 AU S 600345 6003405 (AUS) ENGINE NO3 MAIN BEARING SPALLED - BEARING HAD ROTATED 1 H 7 1 3O 3 O NC 5A6 E273 5 C P878 1997020600213 19970206 00213 NE 1997 2 6 AU961066 2 19960719 G 7261 230361401 VALVE GARRTT 230349102 BAC 146 146100A 1500260 EU LYC ALF502 ALF502R5 41580 NE TURBINE ENGINE O FAULTY W K NONE O K J OTHER FLUID LOSS WARNING INDICATION CR CRUISE 1 AU S LF5935A (AUS) NO2 ENGINE OIL/FUEL HEATER BYPASS VALVE FAULTY 2 H 7 4 4F 4 F RT A49EU E6NE 1997020600214 19970206 00214 CE 1997 2 6 AU961067 1 19960618 G 3260 602EN16 SWITCH BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE LG POSITION IND FAULTY W K NONE O N OTHER FALSE WARNING DE DESCENT 1 AU S (AUS) NOSE LANDING GEAR DOWNLOCK MICROSWITCH HAD HIGH RESISTANCE IN THE`DOWN' POSITION 2 L 7 2 4T 4 T RT A24CE E26NE 1997020600215 19970206 00215 NM 1997 2 6 AU961068 1 19960723 G 4940 AJA4N176 CONTACTOR DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE APU START-IGN SY SEIZED W K NONE O B OTHER SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 AU S 00191 (AUS) APU STARTER CONTACTOR SEIZED 2 H 7 2 4T 4 T RT A13NM E20NE 1997020600216 19970206 00216 EU 1997 2 6 AU961069 1 19960725 G 3230 1849E UPLOCK BAG JETSTM JETSTM3107 1500215 EU ROTOL R333 R333482F12 GL LG EXT-RETRACT S FAULTY W K NONE O J OTHER WARNING INDICATION LD LANDING 1 AU S LK8607621 (AUS) NOSE LANDING GEAR UPLOCK HOOK FAULTY 2 L 7 2 4T RT BA15CAA 6 C P61GL 1997020600217 19970206 00217 CE 1997 2 6 AU961070 1 19960629 G 3220 FRICTION BRAKE CESSNA 650 650 2076802 CE NOSE-TAIL GEAR S CONTAM-WATER W K NONE O OTHER CL CLIMB 1 AU S (AUS) NOSE LANDING GEAR CENTERING AND FRICTION BRAKE DAMPER SYSTEM CONTAMINATED WITH WATER CAUSING LUBRICATION TO BE WAS HED OUT AND PREVENTING NLG FROM RETRACTING - AIRCRAFT WAS LANDING AND TAKING OFF IN HEAVY RAIN 2 L 7 2 4F A9NM 1997020600218 19970206 00218 NM 1997 2 6 AU961071 1 19960713 G 2434 WIRE BOEING 747 747438 NM DC GENERATOR-ALT WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NO4 GENERATOR FEED WIRE CHAFED THROUGH BY CONTACT WITH CARGO ACCESS DOOR UPPER LATCH 2 L 7 4 4F RT A20WE 1997020600219 19970206 00219 CE 1997 2 6 AU961072 1 19960805 G 3233 99810057651 ACTUATOR BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL MLG FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S 2332 ALG1197 (AUS) RT MAIN LANDING GEAR ACTUATOR INTERNAL GEARS STRIPPED - SUSPECT CAUSED BY ADJUSTMENT OF UPLOCK MICROSWITCH ALLOWI NG OVERTRAVEL OFTHE ACTUATOR 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 1997020600220 19970206 00220 NM 1997 2 6 AU961073 1 19960620 G 3250 276005M7 VALVE BOEING 747 747438 NM ACFT STEERING SY INCORRECT ASSY W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) NOSE WHEEL STEERING SYSTEM METERING VALVE FAULTY - INVESTIGATION FOUND AN INCORRECTLY ASSEMBLED CHECK VALVE 2 L 7 4 4F RT A20WE 1997020600221 19970206 00221 NE 1997 2 6 AU961074 2 19960614 G 7320 REGULATOR BOEING 747 747238B 1384828 NM RROYCE RB211 RB211524D419 54555 NE ENG,FUEL CONTROL FAULTY W K NONE O M OTHER OVER TEMP TO TAKEOFF 1 AU S (AUS) NO1 ENGINE FUEL FLOW REGULATOR FAULTY - ENGINE OVERSPED TO 107% FOR APPROXIMATELY 10 SECONDS - EGT 710 DEGREES C 2 L 7 4 4F 4 F A20WE E12EU 1997020600222 19970206 00222 NM 1997 2 6 AU961075 1 19960503 G 5754 FLAP BOEING 747 747438 NM WING LE SYS DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NO11 AND NO16 LEADING EDGE FLAPS DAMAGED 2 L 7 4 4F RT A20WE 1997022000002 19970220 00002 1997 2 20 AU961076 1 19960504 G 7830 FAIRING RROYCE RB211 RB211524G19 NE T ENG THRUST REV SEPARATED W K NONE O OTHER LD LANDING 1 AU S (AUS) NO3 ENGINE THRUST REVERSER TRANSFER DRIVE FAIRING ADRIFT IN FAN EXIT - DAMAGE TO BLOCKER DOORS, OIL FEED LINE AND ONE FUEL VENTDRAIN 4 F E30NE 1997020600223 19970206 00223 NM 1997 2 6 AU961077 1 19960523 G 3244 TYRE BOEING 747 747438 NM LG WHEEL/BRAKE S DAMAGED W K NONE O OTHER CR CRUISE 1 AU S (AUS) RH WING LANDING GEAR LEFT FORWARD TYRE (7F) DAMAGED - LARGE GASH EVIDENT IN SIDEWALL 2 L 7 4 4F RT A20WE 1997020600224 19970206 00224 EA 1997 2 6 AU961078 2 19960618 G 7322 105199 CARBURETTOR CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA MCAULY 1A103 1A103TCM GL ENG,FUEL CONTROL FAULTY W K NONE E Y VIBRATION/BUFFET ENGINE STOPPAGE CL CLIMB 1 AU S CR27633 (AUS) CARBURETTOR SUSPECT FAULTY 1 H 7 1 3O 3 O NT 3A19 E223 5 N P50GL 1997020600225 19970206 00225 CE 1997 2 6 AU961079 1 19960715 G 2910 S1236C60155 HOSE CESSNA 404 404CESSNA 2075901 CE MCAULY 3FF32 3FF32C501 GL MAIN HYD SYS DETERIORATED W K NONE O K OTHER FLUID LOSS IN INSP/MAINT 1 AU S (AUS) HYDRAULIC HOSE FAILED - LOSS OF HYDRAULIC FLUID - DURING PRESSURETESTING THE HOSE EXPANDED BETWEEN THE BRAIDING - HOSE INTERIOR DETERIORATED AND CONTAMINATED THE HYDRAULIC SYSTEM 1 L 7 2 3O A25CE 5 C P45GL 1997020600226 19970206 00226 CE 1997 2 6 AU961080 1 19960805 G 5730 SKIN CESSNA 404 404CESSNA 2075901 CE MCAULY 3FF32 3FF32C501 GL OUTER WING SYS CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH AND RH OUTER WING LEADING EDGE AND LOWER WING SKINS CORRODED IN AREA BETWEEN SKIN, BONDING AGENT AND WAFFLE DO UBLER 1 L 7 2 3O A25CE 5 C P45GL 1997020600227 19970206 00227 CE 1997 2 6 AU961081 1 19960718 G 3230 50450101 TORQUE TUBE CESSNA 310 310L 2074230 CE CONT O470 IO470U 17026 SO MCAULY 2AF34C D2AF34C81 GL LG EXT-RETRACT S FAILED W K NONE O OTHER DE DESCENT 1 AU S (AUS) LH MAIN LANDING GEAR RETRACTION SYSTEM TORQUE TUBE SPLIT - INBOARD LANDING GEAR DOOR ACTUATING ROD ROD-END PNO 504 5025-1MISSING FROM MLG RETRACTION LINKAGE IDLER BELLCRANK PNO 0841106-5DUE TO LOSS OF TORQUE OF THE ATTACHMENT NUT 1 L 7 2 3O 3 O 3A10 3E1 5 C P5EA 1997020600228 19970206 00228 CE 1997 2 6 AU961082 1 19960726 G 3260 1SE13 SWITCH CESSNA 310 310L 2074230 CE CONT O470 IO470U 17026 SO MCAULY 2AF34C D2AF34C81 GL LG POSITION IND DIRTY W K NONE O P OTHER NO WARNING INDICATION DE DESCENT 1 AU S (AUS) RH MAIN LANDING GEAR DOWNLOCK MICROSWITCH DIRTY 1 L 7 2 3O 3 O 3A10 3E1 5 C P5EA 1997020600229 19970206 00229 1997 2 6 AU961083 4 19960731 G 6113 085503014 SPINNER BLKHD 085503015 CESSNA 310 310L 2074230 CE CONT O470 IO470U 17026 SO MCAULY 2AF34C D2AF34C81 GL PROPELLER ASSY S CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 1367 722224 (AUS) PROPELLER SPINNER BULKHEAD CRACKED FROM ATTACHMENT SCREW HOLES - SUSPECT CRACKS HAD EXISTED FOR SOME TIME - INVEST IGATION FOUND THAT THE DOUBLER ASSEMBLY PNO 0895008-4 HAD NOT BEEN FITTED - PERSONNEL/MAINTENANCE ERROR 1 L 7 2 3O 3 O 3A10 3E1 5 C P5EA 1997020600230 19970206 00230 CE 1997 2 6 AU961084 1 19960804 G 3310 E50R1325A RHEOSTAT CESSNA 414 414A 2075907 CE CONT O520 TSIO520N 17040 SO MCAULY 3AF32C 3AF32C505 GL CREW STA LIGHT S BURNT W K NONE B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 AU S (AUS) PILOTS PANEL LIGHTING RHEOSTAT SHORT CIRCUITED 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 1997020600231 19970206 00231 SW 1997 2 6 AU961085 1 19960807 G 5342 301971 BRACKET AIRTRC AT500 AT502 0390303 SW PWA PT6 PT6A15AG 52043 NE HARTZL HCB3T HCB3TN3 GL ATTACH FITTING S BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FORWARD FIN ATTACHMENT BRACKET BROKEN IN AREA DESCRIBED IN AIRTRACTOR SB 138 - AIRCRAFT IS FITTED WITH A 6.35MM (0 .25IN)PLATE 1 L 7 1 3T 4 T NC A9SW E4EA 6 C P15EA 1997020600232 19970206 00232 CE 1997 2 6 AU961086 1 19960729 G 6120 CONTROL CABLE BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO MCAULY 3AF32C 3AF32C512 GL PROP CNTRL SYS SEPARATED W C ABORTED TAKEOFF W INADEQUATE Q C TO TAKEOFF 1 AU S (AUS) LT ENGINE CONSTANT SPEED UNIT (CSU) CONTROL CABLE SEPARATED FROM CSU AND RODEND AND BOLT ASSEMBLY MISSING - INVEST IGATION FOUND THAT MAINTENANCE HAD BEEN CARRIED OUT ON THE CSU PRIOR TO THE OCCURRENCE (CSU ADJUSTMENT) 1 L 7 2 3O 3 O 3A16 E5CE 5 C P22EA 1997020600233 19970206 00233 EA 1997 2 6 AU961087 2 19960802 G 7261 OIL SYSTEM STBROS SD3 SD360 8100606 EU PWA PT6 PT6A65R 52043 EA HARTZL HCB5M HCB5MP3 GL TURBINE ENGINE O LOW PRESSURE W K NONE O K OTHER FLUID LOSS TX TAXI/GRND HDL 1 AU S (AUS) RH ENGINE OIL PRESSURE LOSS 2 H 7 2 4T 4 T A41EU E4EA 6 C P44GL 1997020600234 19970206 00234 EA 1997 2 6 AU961088 2 19960619 G 8520 11F20022S3 CRANKCASE LYC TIO540A2C PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2B 41532 EA HARTZL HCE3Y HCE3YR2 GL R ENGINE POWER S CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 1456 L629061A L629061A (AUS) ENGINE CRANKCASE CRACKED FROM NO6 CYLINDER FORWARD UPPER CYLINDERFLANGE STUD TO NO6 CYLINDER INLET VALVE TAPPER GU IDE 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 1997020600235 19970206 00235 SW 1997 2 6 AU961089 1 19960802 G 3213 S0310335R SEAL OZONE MLG GULSTM 690TP 695B 3970610 SW ROTOL R306 R306382F7 GL MAIN GEAR SYS WORN W K NONE O OTHER TO TAKEOFF 1 AU S 802 (AUS) RH MAIN LANDING GEAR OLEO SEAL FAILED - INSUFFICIENT OLEO EXTENSION AFTER TAKEOFF RESULTED IN THE RH MAIN WHEEL C ONTACTING THE RH MLG DOOR CAUSING SLIGHT DAMAGE 1 H 7 2 4T RT 2A4 6 C P8EU 1997020600236 19970206 00236 WP 1997 2 6 AU961090 1 19960719 G 5412 FIREWALL ROBSIN R44 R44 7640120 WP LYC O540 O540F1B5 41532 EA NAC-PYL M-FRAME DAMAGED W K NONE O OTHER LD LANDING 1 AU S (AUS) VERTICAL FIREWALL LOWER DIAGONAL CENTRAL TUBE AND ATTACHING DOUBLERS SEPARATED FROM FIREWALL DURING HARD LANDING 1 G 7 1 3O 3 O H11NM E295 1997020600237 19970206 00237 NM 1997 2 6 AU961091 1 19960728 G 2760 SWITCH DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE DRAG-SPOILER SYS OUT OF ADJUST W K NONE F J FLT CONT AFFECTED WARNING INDICATION TO TAKEOFF 1 AU S (AUS) LH AND RH OUTBOARD ROLL SPOILER JAM SWITCHES OUT OF ADJUSTMENT 2 H 7 2 4T 4 T RT A13NM E20NE 1997020600238 19970206 00238 CE 1997 2 6 AU961092 1 19960726 G 2910 572710012 HOSE CESSNA 404 404CESSNA 2075901 CE MCAULY 3FF32 3FF32C501 GL MAIN HYD SYS DETERIORATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) HYDRAULIC HOSE DETERIORATED AND BREAKING DOWN INTERNALLY - RUBBER PARTICLES CONTAMINATED HYDRAULIC SYSTEM 1 L 7 2 3O A25CE 5 C P45GL 1997020600239 19970206 00239 EA 1997 2 6 AU961093 2 19960701 G 8520 76097 CAMSHAFT CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA MCAULY 1C160 1C160DTM GL R ENGINE POWER S WORN W K NONE O OTHER IN INSP/MAINT 1 AU S 1587 L4968027A (AUS) CAMSHAFT EXHAUST VALVE LOBES AND ASSOCIATED TAPPETS PNO 72877 WORN - WEAR WAS BETWEEN 4.572MM AND 5.08MM (0.180IN AND 0.200IN) 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 1997020600240 19970206 00240 CE 1997 2 6 AU961094 1 19960805 G 7120 BOLT 9401120 CESSNA 172 172P 2072436 CE LYC O320 O320D2J 41508 EA MCAULY 1C160 1C160DTM GL ENGINE MOUNTING WRONG PART W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S L1105839A (AUS) ENGINE VIBRATION ISOLATOR MOUNT BOLTS INCORRECT PART (INCORRECT LENGTH) - SPACERS BETWEEN ENGINE AND MOUNTS NOT I NSTALLED - RH UPPER MOUNT BOLT NUT SEPARATED - LH LOWER MOUNT BOLT NUT SPLIT - SUSPECT NUTS ALSO INCORRECT PART AS THEY ARE DIFFERENT TO THENUTS SPECIFIED IN THE IPC - PERSONNEL/MAINTENANCE ERROR - UNAPROVED PART 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 1997020600241 19970206 00241 CE 1997 2 6 AU961095 1 19960806 G 2410 640934 GEAR PRESTOLITE CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO MCAULY 3AF32C 3AF32C87 GL ALT-GEN DRIVE SY SEPARATED W K NONE O H OTHER ELECT. POWER LOSS-50 PC IN INSP/MAINT 1 AU S 1313 IOK00008 (AUS) ALTERNATOR DRIVE GEAR FAILED - GEAR FACE HAD SEPARATED FROM HUB ALLOWING GEAR TO FREEWHEEL 1 L 7 2 3O 3 O 3A10 E5CE 5 C P22EA 1997020600242 19970206 00242 CE 1997 2 6 AU961096 1 19960725 G 2434 ALT9422R BEARING CONT CESSNA 401 401A 207590D CE MCAULY 3AF32C 3AF32C505 GL DC GENERATOR-ALT LOOSE W K NONE H J ELECT. POWER LOSS-50 PC WARNING INDICATION CR CRUISE 1 AU S 555171 (AUS) RH ENGINE DRIVEN ALTERNATOR SLIP RING END BEARING LOOSE IN END HOUSING - BEARING HOUSING SUPPORT WEBS CRACKED AND BROKEN 1 L 7 2 3O A7CE 5 C P22EA 1997020600564 19970206 00564 SW 1997 2 6 AU961097 1 19960801 G 6322 476618015 COOLING FAN BELL 47 47G3B 1181026 SW LYC O435 TVO435A1A 41516 EA ENG ASSRY COOL S CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 298 476618015 L24752 (AUS) ENGINE COOLING FAN BLADE CRACKED AT BASE 1 G 7 1 3O 3 O 2H3 1E13 1997020600565 19970206 00565 NE 1997 2 6 AU961098 2 19960622 G 7240 9192M65G06 COMBUSTOR GE CF6 CF680A 30025 NE TURBINE ENGINE C CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 4601 LH (AUS) ENGINE COMBUSTOR OUTER COWL CRACKED AND BROKEN 4 F E13NE 1997020600566 19970206 00566 EU 1997 2 6 AU961099 2 19960730 G 7320 L923ANSETTSNO REGULATOR FOKKER F28 F28MK4000 4990810 EU RROYCE SPEY SPEY55515 54521 EU ENG,FUEL FLOW FAULTY W K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS TO TAKEOFF 1 AU S 2516 L923ANSETT 9688 (AUS) NO2 ENGINE FUEL FLOW REGULATOR (FFR) SUSPECT FAULTY 2 L 7 2 4F 4 F RT A20EU E2EU 1997020600567 19970206 00567 NM 1997 2 6 AU961100 1 19960723 G 2710 BACC13AP4E5371 CONTROL CABLE BOEING 747 747312 1384932 NM AILERON CONTROL FRAYED W A K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) AILERON CABLE AB13 LOCATED IN AREA OF LH REAR SPAR HAD SIX OF SEVEN STRAND BROKEN AT CABLE DRUM AT WS 776.98 - CA BLE AA11 ALSO DAMAGED WITH NUMEROUS BROKEN STRANDS - SUSPECT CAUSED BY INCORRECT INSTALLATION AND ALIGNMENT WITH BOTH CA BLES BEING IN THE SAME DRUM GROOVE - PERSONNEL/MAINTENANCE ERROR 2 L 7 4 4F RT A20WE 1997020600568 19970206 00568 EU 1997 2 6 AU961101 1 19960730 G 5220 A322520843 STRAP AIRBUS 320 A320212 EU CABIN EMERG DOOR FOUL RUD PEDAL W K NONE F FLT CONT AFFECTED LD LANDING 1 AU S (AUS) CABIN ACCESS HATCH SAFETY STRAP CENTRE EYELETS MISSING ALLOWING STRAP TO HANG DOWN AND CONTACT INBOARD RUDDER CAB LE AT FAIRLEAD JUNCTION AT FUSELAGE FRAME 23 - RUDDER PEDALS JAMMED 2 L 7 2 4F RT A28NM 1997020600569 19970206 00569 SO 1997 2 6 AU961102 1 19960623 G 5741 640030X2 FITTING PIPER PA25235 PIPER PA25 PA25235 7102504 SO LYC O540 O540B2C5 41532 EA MCAULY 1A200 1A200FA GL OUTER WING SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 7095 254396 L1146840 J1017 (AUS) LH AND RH WING FRONT SPARS CRACKED ON LOWER RADIUS OF FRONT AND REAR WING TO FUSELAGE ATTACHMENT LUGS 1 L 7 1 3O 3 O 2A10 E295 5 N P874 1997020600570 19970206 00570 EU 1997 2 6 AU961103 1 19960409 G 3230 HTE2501A MOTOR HTE21004 BAC 146 146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE LG EXT-RETRACT S DEFECTIVE W K NONE O OTHER NR NOT REPORTED 1 AU S 688GB295H (AUS) LANDING GEAR SELECTOR VALVE ACTUATOR HIGH RESISTANCE DUE TO POOR BRUSH CONTACT WITH COMMUTATOR 2 H 7 4 4F 4 F A49EU E6NE 1997020600571 19970206 00571 NE 1997 2 6 AU961104 2 19960730 G 7250 TURBINE BAC 146 146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE 1ST STAGE FAILED W A O OTHER M OVER TEMP TO TAKEOFF 1 AU S LF05903A (AUS) NO2 ENGINE FAILED - TGT INCREASED TO 957 DEGREES - SUSPECT CAUSEDBY 1ST STAGE TURBINE RUB 2 H 7 4 4F 4 F A49EU E6NE 1997020600572 19970206 00572 EU 1997 2 6 AU961105 1 19960720 G 3310 LIGHT AEROSP SA365 SA365C 8680667 EU TMECA ARRIEL ARRIEL1A 60030 NE CREW STA LIGHT S FAULTY W K NONE B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 AU S (AUS) COPILOTS MAP LIGHT WIRING INSULATION WORN AND SHORT CIRCUITING TO GROUND 1 G 7 2 3U 3 U H10EU E19EU 1997020600573 19970206 00573 EA 1997 2 6 AU961106 2 19960808 G 8500 ENGINE CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA MCAULY 1C160 1C160DTM GL ENGINE (RECIPROC ROUGH RUNNING W K NONE E VIBRATION/BUFFET CL CLIMB 1 AU S (AUS) ENGINE RAN ROUGH FOR SEVERAL SECONDS - SUSPECT FUEL PROBLEM - INVESTIGATION COULD FIND NO CAUSE AND THERE WAS NO REPETITION OF THE PROBLEM 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 1997020600574 19970206 00574 1997 2 6 AU961107 1 19960809 G 7110 10191011715 COWLING PWA PT6 PT6A60 52043 NE ENGINE COWL SYS DOOR FAILED W K NONE O D OTHER INFLIGHT SEPARATION CL CLIMB 1 AU S (AUS) LH INBOARD ENGINE COWL DOOR SEPARATED ALONG HINGE LINE - DAMAGE TO ONE WINDOW AND MINOR SCRATCHES AND DENTS TO FU SELAGE 4 T E4EA 1997020600575 19970206 00575 EU 1997 2 6 AU961108 1 19960416 G 2820 FUEL SYSTEM BAC 146 146300A 1500267 EU LYC ALF502 ALF502R5 41580 NE FUEL DISTRBUTION CONTAMINATED W K NONE E X VIBRATION/BUFFET ENGINE FLAMEOUT TO TAKEOFF 1 AU S (AUS) NO1 ENGINE FUEL FEED PIPE CONTAMINATED BY AIR IN LINES - AIRCRAFTHAD BEEN COMPLETELY DEFUELLED THE PREVIOUS NIGHT - THERE IS NO REQUIREMENT FOR BLEEDING OF THE FUEL SYSTEM FOLLOWING COMPLETE DEFUEL 2 H 7 4 4F 4 F RT A49EU E6NE 1997020600576 19970206 00576 EU 1997 2 6 AU961109 1 19960308 G 3230 HTE2501A MOTOR BAC 146 146300A 1500267 EU LYC ALF502 ALF502R5 41580 NE LG EXT-RETRACT S SEIZED W K NONE O OTHER CL CLIMB 1 AU S 11175 1187GB213H (AUS) LANDING GEAR SELECTOR VALVE ACTUATOR FAULTY - INVESTIGATION FOUND INSULATION VARNISH IN THE AIR GAP BETWEEN THE AR MATURE AND FIELD POLES AND POOR BRUSH CONTACT 2 H 7 4 4F 4 F RT A49EU E6NE 1997020600577 19970206 00577 GL 1997 2 6 AU961110 2 19960729 G 7250 6853279 TURBINE WHEEL ALLSN 250C20B ALLSN 250C 250C20B 03013 GL TURBINE SECTION CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 1006 CAT36694 CAE831447 (AUS) FOURTH STAGE TURBINE WHEEL CRACKED THROUGH RIM 3 U E4CE 1997020600578 19970206 00578 GL 1997 2 6 AU961111 2 19960724 G 7250 6886407 TURBINE WHEEL ALLSN 250C20 HUGHES 369 369C 4470704 WP ALLSN 250C 250C20 03013 GL TURBINE SECTION CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S CAT31663 CAE801081BA (AUS) FIRST STAGE TURBINE WHEEL CRACKED - TURBINE LABYRINTH SEAL PICKED UP ON STATIONARY SEAL - SECOND STAGE NGV PNO 687 8426 CRACKED INCURVIC COUPLING 1 G 7 1 3U 3 U H3WE E4CE 1997020600579 19970206 00579 GL 1997 2 6 AU961112 2 19960722 G 7250 6840406 TURBINE BOLT ALLSN 250C30 ALLSN 250C 250C30 03013 GL TURBINE SECTION LOOSE NUT W K NONE O OTHER IN INSP/MAINT 1 AU S CAT98211 CAE895801 (AUS) GAS PRODUCER TURBINE BOLT NUT LOOSE 3 U E1GL 1997020600580 19970206 00580 NE 1997 2 6 AU961113 2 19960810 G 8530 399353CP CYLINDER PWA R985AN14B DHAV DHC2 DHC2EVANS 2801832 EA PWA R985 R985AN14B 52008 NE R ENGINE CYLINDE CRACKED W K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS TO TAKEOFF 1 AU S 4224237 4224237 (AUS) NO8 CYLINDER CRACKED - DURING REMOVAL TOP OF CYLINDER SEPARATED FROM CYLINDER BODY 1 H 7 1 3O 3 R A806 5E1 1997020600581 19970206 00581 EU 1997 2 6 AU961114 1 19960621 G 2133 VFT210700 ACTUATOR AIRBUS 320 A320212 EU PRESS. REGUL/OUT CORRODED W K NONE O OTHER CL CLIMB 1 AU S 20ANSETTS (AUS) AVIONICS VENT SYSTEM SKIN AIR INLET VALVE ACTUATOR INOPERATIVE - SUSPECT CAUSED BY CORROSION BUILDUP ON THE CLOSED POSITION LIMIT MICROSWITCH (S2) 2 L 7 2 4F RT A28NM 1997020600582 19970206 00582 NM 1997 2 6 AU961115 1 19960807 G 2150 7DR1830M5 ACTUATOR UNITEDTECH PACKVALVE DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE CABIN COOLING SY FAULTY W K NONE M J OVER TEMP WARNING INDICATION CL CLIMB 1 AU S 18116 901038 (AUS) CABIN COOLING SYSTEM PACK VALVE ACTUATOR JAMMED IN FULL BYPASS POSITION (BUTTERFLY CLOSED) 2 H 7 2 4T 4 T RT A13NM E20NE 1997020600583 19970206 00583 SW 1997 2 6 AU961116 1 19960810 G 2910 27810321039 PIPE SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE33111U 01514 WP MAIN HYD SYS CORRODED W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S (AUS) HYDRAULIC PIPE LOCATED IN LH WHEEL BAY LEAKING AT 90 DEGREE BEND DUE TO CORROSION PITTING 2 L 7 2 4T 4 T RT A8SW E4WE 1997020600584 19970206 00584 SO 1997 2 6 AU961117 1 19960804 G 3231 VALVE EMB 120 EMB120 3260201 SO PWA 118 PW118A NE LG EXT-RETRACT S FAULTY W K NONE O OTHER NR NOT REPORTED 1 AU S (AUS) LANDING GEAR DOOR SOLENOID VALVE SUSPECT FAULTY 2 L 7 2 4T 4 T RT A31SO E20NE 1997020600585 19970206 00585 SO 1997 2 6 AU961118 1 19960802 G 7100 311591101A HARNESS EMB 120 EMB120 3260201 SO PWA 118 PW118A NE ENG ELEC HARNESS FAULTY W K NONE O OTHER TO TAKEOFF 1 AU S 115662 (AUS) ENGINE ELECTRICAL HARNESS SUSPECT FAULTY 2 L 7 2 4T 4 T RT A31SO E20NE 1997020600586 19970206 00586 CE 1997 2 6 AU961119 1 19960729 G 2432 TERMINAL BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL BATTERY/CHARGER CORRODED W K NONE J H WARNING INDICATION ELECT. POWER LOSS-50 PC CL CLIMB 1 AU S (AUS) BATTERY MONITOR SHUNT TERMINAL CORRODED PREVENTING CORRECT CONTACT 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 1997020600587 19970206 00587 NM 1997 2 6 AU961120 1 19960627 G 3230 SPRING BOEING 747 747438 NM LG EXT-RETRACT S FOULED W K NONE O N OTHER FALSE WARNING CL CLIMB 1 AU S (AUS) BOTH WING LANDING GEAR UPLOCK OVERCENTRE SPRINGS FOULING ON J7 AND J8 JUNCTION BOXES 2 L 7 4 4F RT A20WE 1997020600588 19970206 00588 NM 1997 2 6 AU961121 1 19960530 G 5220 LATCH BOEING 747 747438 NM CABIN EMERG DOOR INCORRECT RIGGED W A K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) FLIGHT DECK ESCAPE HATCH LATCH PINS INCORRECTLY FITTED - SPACERS AND BEARINGS ALSO FOUND TO BE IN WRONG STACKUP CO NFIGURATION 2 L 7 4 4F RT A20WE 1997022000003 19970220 00003 1997 2 20 AU961122 1 19960805 G 7740 COMPUTER RROYCE RB211 RB211535E4 54555 NE ENG INTGRT INSTR CONTAM-WATER W K NONE N FALSE WARNING CL CLIMB 1 AU S (AUS) AREA ABOVE E3 AND E4 ELECTRONICS PACK CONTAMINATED BY WATER DURING HEAVY RAIN STORM - RIGHT EICAS COMPUTER ALSO C ONTAMINATED BY WATER 4 F E12EU 1997020600589 19970206 00589 EU 1997 2 6 AU961123 1 19960811 G 3260 CIRCUIT BOARD BAC 146 146100A 1500260 EU LYC ALF502 ALF502R5 41580 NE LG POSITION IND FAULTY W K NONE O N OTHER FALSE WARNING DE DESCENT 1 AU S (AUS) LANDING GEAR WARNING SYSTEM NOSE LANDING GEAR DOWNLOCK PRINTED CIRCUIT BOARD FAULTY 2 H 7 4 4F 4 F RT A49EU E6NE 1997020600590 19970206 00590 NM 1997 2 6 AU961124 1 19960805 G 2520 908621 FITTING 908622 BOEING 737 737377 NM PASSENGER COMPAR CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FLIGHT ATTENDANT SEAT ROLLER FITTINGS CRACKED - BOTH FITTINGS PNO90862-1 AND PNO 90862-2 CRACKED IN FORWARD SEAT - INBOARD FITTINGPNO 90862-1 CRACKED IN AFT SEAT 2 L 7 2 4F RT A16WE 1997020600591 19970206 00591 NE 1997 2 6 AU961125 2 19960808 G 7261 OIL SYSTEM CFMINT CFM56 CFM565A1 NE TURBINE ENGINE O CONTAM-METAL W K NONE O OTHER IN INSP/MAINT 1 AU S 731140 (AUS) NO1 ENGINE OIL SYSTEM FRONT SCAVENGE MAGNETIC PLUG CONTAMINATED WITH METAL TYPE M50 AND 4340 4 F E29NE 1997020600592 19970206 00592 EA 1997 2 6 AU961127 2 19960806 G 7320 3010466 LEVER 3244834 EMB 110 EMB110P1 3260122 SO PWA PT6 PT6A34 52043 EA HARTZL HCB3T HCB3TN3 GL ENG,FUEL CONTROL BROKEN W K NONE O R OTHER PARTIAL RPM/PWR LOSS CR CRUISE 1 AU S A89271 56681 (AUS) ENGINE FUEL CONTROL UNIT LEVER BROKEN OFF AT BASE - ENGINE RETURNED TO FLIGHT IDLE - SUSPECT PRE-EXISTING CRACK CA USED BY IMPACT 1 L 7 2 4T 4 T A21SO E4EA 6 C P15EA 1997020600593 19970206 00593 CE 1997 2 6 AU961128 1 19960805 G 5730 SKIN CESSNA 404 404CESSNA 2075901 CE MCAULY 3FF32 3FF32C501 GL OUTER WING SYS CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH AND RH LOWER WING SKINS CORRODED IN AREA BETWEEN SKIN, BONDING AGENT AND WAFFLE DOUBLER ON OUTER LEADING EDGE ASSEMBLIES 1 L 7 2 3O A25CE 5 C P45GL 1997020600594 19970206 00594 CE 1997 2 6 AU961129 1 19960811 G 1210 FUEL SYSTEM CESSNA 206 U206C 2073332 CE CONT O520 IO520F 17032 SO MCAULY 3A32C D3A32C90 GL FUEL STORAGE SYS WRONG FUEL W K NONE E Y M VIBRATION/BUFFET ENGINE STOPPAGE OVER TEMP CR CRUISE 1 AU S 566275 (AUS) AIRCRAFT FILLED WITH AVTUR - ENGINE DAMAGED DUE TO DETONATION - METAL CONTAMINATION OF OIL SYSTEM - PERSONNEL/MAI NTENANCE ERROR- UNAPPROVED PART (FUEL) 1 H 7 1 3O 3 O A4CE E5CE 5 C P21EA 1997020600595 19970206 00595 SW 1997 2 6 AU961130 1 19960729 G 5520 442451 BOLT GULSTM 112 114 7630314 SW LYC O540 IO540T4A5 41532 EA HARTZL HCC2Y HCC2YR1 GL ELEVATOR STRUCT CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ELEVATOR HINGE BOLT CORRODED - FOUND DURING ELEVATOR BEARING CHANGE WHEN ELEVATORS REMOVED 1 L 7 1 3O 3 O A12SO 1E4 5 C P920 1997020600596 19970206 00596 CE 1997 2 6 AU961131 1 19960809 G 7120 SPACER CESSNA 172 172P 2072436 CE LYC O320 O320D2J 41508 EA MCAULY 1C160 1C160DTM GL ENGINE MOUNTING MIS INSTALLED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S 61034139A (AUS) ENGINE INCORRECTLY INSTALLED IN ENGINE MOUNTS - LOWER VIBRATION SHOCK MOUNT CONTAINED AN INCORRECT NUMBER OF SPAC ERS - AS ARESULT THE PROPELLER SPINNER BACKING PLATE HAD WORN ON THE LOWER COWL - PERSONNEL/MAINTENANCE ERROR 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 1997020600597 19970206 00597 CE 1997 2 6 AU961132 1 19960806 G 5541 3363000017 SPAR BEECH 33 F33A 1151425 CE CONT O520 IO520B 17032 SO MCAULY 3A32C 3A32C406 GL RUDDER STRUCT SY CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 573470 951740 (AUS) RUDDER SPAR CRACKED - FOUND DURING INSPECTION IAW AD/BEECH33/36 AMDT1 1 L 7 1 3O 3 O 3A15 E5CE 5 C P21EA 1997020600598 19970206 00598 SO 1997 2 6 AU961133 1 19960814 G 5711 SPAR FITTING PIPER REARSPAR PIPER PA28 PA28R200 7102811 SO LYC O360 IO360C1C 41514 EA HARTZL HCC2Y HCC2YK1 GL OUTER WING SYS FAILED RIVETS W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) WING REAR SPAR FITTING ATTACHMENT RIVETS FAILED - HEADS FELL OFF - FOUND DURING INSPECTION IAW AD/PA28/40 1 L 7 1 3O 3 O 2A13 1E10 5 C P920 1997020600599 19970206 00599 CE 1997 2 6 AU961134 1 19960802 G 2810 120040684 VENT CESSNA 210 210N 2073453 CE CONT O520 IO520L 17032 SO MCAULY 3A32C D3A32C88 GL FUEL STORAGE SYS DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RH FUEL TANK VENT LINE DAMAGED DUE TO EXCESSIVE BEND IN LINE - LINE PARTIALLY BLOCKED 1 H 7 1 3O 3 O 3A21 E5CE 5 C P21EA 1997020600600 19970206 00600 EU 1997 2 6 AU961135 1 19960731 G 3213 OLEO SUPPORT NS40D403 BNORM BN2 BN2B26 1520350 EU LYC O540 O540E4C5 41532 EA HARTZL HCC2Y HCC2YK2 GL MAIN GEAR SYS SHEARED RIVET W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH LANDING GEAR OLEO SUPPORT FITTING PNO NS-40-C-075 TO MLG TUBE PNO NS-40-D-403 ATTACHMENT RIVETS SHEARED ALLOWIN G THE MLG WHEEL ASSEMBLY TO TURN RELATIVE TO THE AIRCRAFT CENTRELINE - OCCURRED DURING MINIMUM RADIUS TURN DURING TAXI 1 H 7 2 3O 3 O RT A17EU E295 5 C P920 1997020600601 19970206 00601 EU 1997 2 6 AU961136 1 19960807 G 5511 NB30079 RIB BNORM BN2 BN2B26 1520350 EU LYC O540 O540E4C5 41532 EA HARTZL HCC2Y HCC2YK2 GL HORZ STAB SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH HORIZONTAL STABILISER INNER NOSE RIB CRACKED AT STN 11.40 - SUSPECT CAUSED BY HORIZONTAL STABILISER BEING USED AS AMAINTENANCE STAND IN LIEU OF THE CORRECT ITEM - PERSONNEL/MAINTENANCE ERROR 1 H 7 2 3O 3 O RT A17EU E295 5 C P920 1997020600602 19970206 00602 GL 1997 2 6 AU961137 2 19960809 G 7323 3292 GOVERNOR DRIVE BENDIX PTGOVERNOR BELL 206 206B3 1181506 SW ALLSN 250C 250C20B 03013 GL ENG,FUEL CONTROL FAILED SHAFT W E ENGINE SHUTDOWN O OTHER CL CLIMB 1 AU S 1646 3292 CAE801666BA (AUS) ENGINE POWER TURBINE GOVERNOR DRIVE SHAFT SHEARED DUE TO FAILURE OF DRIVE BEARING SUSPECT DUE TO DETERIORATED AND/ OR LOST GREASE 1 G 7 1 3U 3 U H2SW E4CE 1997020600603 19970206 00603 NM 1997 2 6 AU961138 1 19960722 G 3230 MLG BOEING 737 737476 NM MAIN GEAR SYS FAULTY W K NONE O J OTHER WARNING INDICATION DE DESCENT 1 AU S (AUS) RH MAIN LANDING GEAR FAILED TO LOCK DOWN 2 L 7 2 4F RT A16WE 1997020600604 19970206 00604 NM 1997 2 6 AU961139 1 19960801 G 3246 1864 WHEEL BOEING 737 737376 NM LG WHEEL/BRAKE S CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 1864 (AUS) LH INBOARD MAIN WHEEL CRACKED BETWEEN TIE BOLT HOLE AND OVERINFLATION VALVE ACCESS HOLE - FOUND DURING ROUTINE TY RECHANGE 2 L 7 2 4F RT A16WE 1997020600605 19970206 00605 NM 1997 2 6 AU961140 1 19960731 G 3246 0262 WHEEL BOEING 737 737376 NM LG WHEEL/BRAKE S CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 0262 (AUS) LH INBOARD MAIN WHEEL CRACKED BETWEEN TIE BOLT HOLE AND OVERINFLATION VALVE ACCESS HOLE - FOUND DURING ROUTINE TY RECHANGE 2 L 7 2 4F RT A16WE 1997020600606 19970206 00606 CE 1997 2 6 AU961141 1 19960814 G 3234 SELECTOR BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO HARTZL HCJ3Y PHCJ3YF2 GL LG EXT-RETRACT S FAULTY W K NONE O OTHER TO TAKEOFF 1 AU S (AUS) LANDING GEAR SELECTOR WHEEL LOCKING GRUB SCREW LOOSE 1 L 7 2 3O 3 O 3A16 E5CE 5 C P36EA 1997020600607 19970206 00607 CE 1997 2 6 AU961142 1 19960814 G 5312 24120044 BULKHEAD CESSNA 24120013 CESSNA 172 172RG 2072438 CE LYC O360 O360F1A6 41514 EA MCAULY 2D34C B2D34C220 GL MAIN FRAME SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 0940 (AUS) FUSELAGE BULKHEADS CRACKED IN THE FOLLOWING LOCATIONS: 1. PNO 2412001-3 BULKHEAD LOWER LH STN 108.0 - CRACK LENGTH 27MM (1.06IN) 2. PNO 2412001-4 BULKHEAD LOWER RH STN 108.0 - CRACK LENGTH 30MM (1.18IN) 3. PNO 2412004-4 BULKHEAD L OWER RH STN 124.0 - CRACK LENGTH 22MM (0.866IN) 4. PNO 2412004-5 BULKHEAD LOWER LH STN 124.0 - CRACK LENGTH 9MM (0.354I N) CRACKS EXTEND FROM INBOARD EDGE TOWARDS FUSELAGE SKIN IN BAGGAGE AREA AT FLOOR LEVEL - FORWARD BULKHEADS AT STN 108.0 SHOW SIGNS OF DEFORMATION AND STRUCTURE DISTRESS 1 H 7 1 3O 3 O 3A17 E286 5 C P7EA 1997020600608 19970206 00608 NM 1997 2 6 AU961143 1 19960810 G 5330 SKIN BOEING 767 76733A NM PWA 4056 PW4056 NE EXT PLATES/SKIN CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUSELAGE SKIN CRACKED - CRACK LENGTH 38.1MM (1.5IN) - FURTHER INVESTIGATION OF REAR CARGO FLOOR REVEALED EXFOLIAT ION CORROSION 2 L 7 2 RT 4 F RT A1NM E24NE 1997020600609 19970206 00609 EU 1997 2 6 AU961144 1 19960809 G 3310 LT52A LIGHTING DIMMER BAG JETSTM JETSTM3107 1500215 EU ROTOL R333 R333482F12 GL CREW STA LIGHT S FAULTY W K NONE O B OTHER SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 AU S 6124 (AUS) PILOTS PANEL LIGHT DIMMER FAILED 2 L 7 2 4T RT BA15CAA 6 C P61GL 1997020600610 19970206 00610 CE 1997 2 6 AU961145 1 19960729 G 2520 SEAT BELT CESSNA 182 182F 2072714 CE CONT O470 O470R 17026 SO PASSENGER COMPAR WRONG PART W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) BOTH REAR SEATS FITTED WITH AUTOMOTIVE SEAT BELTS - UNAPPROVED PART - PERSONNEL/MAINTENANCE ERROR 1 H 7 1 3O 3 O NT 3A13 E273 1997020600611 19970206 00611 NM 1997 2 6 AU961146 1 19960721 G 5730 72031 PANEL 654587 BOEING 737 737376 NM OUTER WING SYS MISSING W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH WING NO1 FUEL BOOST PUMP ACCESS PANEL MISSING 2 L 7 2 4F RT A16WE 1997020600612 19970206 00612 EU 1997 2 6 AU961147 1 19960802 G 2910 NAS16126 SEAL AIRBUS 300 A300B4203 3930306 EU GE CF6 CF650C2 30018 NE MAIN HYD SYS DAMAGED W K NONE K FLUID LOSS CR CRUISE 1 AU S (AUS) GREEN HYDRAULIC SYSTEM UNION SEAL LEAKING - SEAL WAS LOCATED AT RH KRUGER FLAP RETURN LINE UNION - LOSS OF HYDRAU LIC FLUID 2 L 7 2 4F 4 F A35EU E23EA 1997022000633 19970220 00633 CE 1997 2 20 AU961148 1 19960815 G 5312 24120521 DOUBLER CESSNA BULKHEAD CESSNA 172 172RG 2072438 CE LYC O360 O360F1A6 41514 EA MCAULY 2D34C B2D34C220 GL MAIN FRAME SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) EMPENAGE TO FUSELAGE ATTACHMENT BULKHEAD CRACKED - SEE ALSO MDR 95/0816 AND MDR 96/1142 FOR SIMILAR DEFECTS 1 H 7 1 3O 3 O 3A17 E286 5 C P7EA 1997022000634 19970220 00634 CE 1997 2 20 AU961149 1 19960812 G 7810 12502642 EXHAUST PIPE CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO MCAULY D3A34 D3A34C404 GL R ENG COLLECTOR WRONG PART W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) RH EXHAUST COLLECTOR NO5 RISER PIPE RUBBING ON NO3 INLET MANIFOLD CAUSING WEAR DAMAGE TO BOTH ITEMS - COLLECTOR AS SEMBLY WAS NOT A GENUINE CESSNA PART AND APPEARS TO HAVE BEEN INCORRECTLY MANUFACTURED - A GENUINE CESSNA PART FITTED CO RRECTLY -PERSONNEL/MAINTENANCE ERROR - UNAPPROVED PART 1 H 7 1 3O 3 O A4CE E5CE 5 C P47GL 1997030300004 19970303 00004 GL 1997 3 3 AU961150 3 19960730 G 6110 PROPELLER PIPER PA60 PA60601 7106010 NM LYC O540 IO540S1A5 41532 EA HARTZL HCC3Y HCC3YR GL PROPELLER ASSY GROUND STRIKE W K NONE C F.O.D. LD LANDING 1 AU S L1935848A CK4187A (AUS) RH ENGINE SUFFERED A PROPELLER STRIKE - ALL THREE BLADES DAMAGED IN AREA APPROXIMATELY 50.8MM (2IN) FROM TIP 1 M 7 2 3O 3 O RT A17WE 1E4 5 C P25EA 1997022000635 19970220 00635 CE 1997 2 20 AU961151 1 19960731 G 2820 10192000016 PIPE BEECH 200 B200C 1152924 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL FUEL DISTRBUTION CHAFED W K NONE K W FLUID LOSS INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) RH MAIN LANDING GEAR TORQUE TUBE PNO 101-810021-3 RUBBING ON INCORRECTLY POSITIONED FUEL LINE BETWEEN THE NACELLE TANK AND THE AUXILIARY TANK WEARING A HOLE IN THE FUEL LINE AND DAMAGING THE TORQUE TUBE - FUEL LEAKING - PERSONNEL/MAI NTENANCE ERROR 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 1997022000636 19970220 00636 GL 1997 2 20 AU961152 3 19960815 G 6111 RETENTION NUT CESSNA 310 310Q 2074242 CE CONT O470 IO470V 17026 SO MCAULY 3AF32C 3AF32C87 GL PROP BLADE LOOSE W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S 722497 (AUS) NO3 PROPELLER BLADE RETENTION NUT LOOSE AND LOCK PLUGS MISSING - SUSPECT RETENTION NUT UNDERTORQUED - PERSONNEL/MA INTENANCE ERROR 1 L 7 2 3O 3 O 3A10 3E1 5 C P22EA 1997022000637 19970220 00637 EA 1997 2 20 AU961153 2 19960614 G 8530 75089 PISTON LYC CYLINDER CESSNA 172 172P 2072436 CE LYC O320 O320D2J 41508 EA MCAULY 1C160 1C160DTM GL R ENGINE CYL DAMAGED W K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CR CRUISE 1 AU S 109153 110560 (AUS) NO3 CYLINDER PISTON DAMAGED AND PISTON RINGS BROKEN - SUSPECT CAUSED BY DETONATION 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 1997022000638 19970220 00638 SW 1997 2 20 AU961154 1 19960508 G 5310 FUSELAGE GULSTM 690TP 690 0141720 SW HARTZL HCB3T HCB3TN5 GL MAIN FRAME SYS BIRD STRIKE W K NONE C F.O.D. LD LANDING 1 AU S (AUS) AIRCRAFT HIT BY SEAGULL DURING LANDING 1 H 7 2 3T 2A4 6 C P15EA 1997022000639 19970220 00639 EA 1997 2 20 AU961155 2 19960809 G 8530 CYLINDER LYC O540 IO540K1C5 41532 EA HARTZL HCA3V HCA3VK2 GL R ENGINE CYL DAMAGED W K NONE E K VIBRATION/BUFFET FLUID LOSS LD LANDING 1 AU S L538248 (AUS) NO3 ENGINE NO6 CYLINDER AND CRANKCASE DAMAGED - AIRCRAFT HAD BEEN IDLE FROM NOVEMBER 1995 UNTIL JUNE 1996 - THE EN GINES HAD NOT BEEN INHIBITED OR REGULARLY GROUND RUN DURING THAT TIME 3 O 1E4 5 C P6EA 1997022000640 19970220 00640 NE 1997 2 20 AU961156 1 19960525 G 2823 SEAL SELECTVALVE SKRSKY S76 S76A 8143006 NE ALLSN 250C 250C30 03013 GL FUEL DIST LEAKING W K NONE E VIBRATION/BUFFET CR CRUISE 1 AU S (AUS) FUEL SELECTOR VALVE SHAFT SEAL LEAKING ALLOWING AIR TO ENTER FUELSYSTEM 1 G 7 2 3U 3 U H1NE E1GL 1997022000641 19970220 00641 NM 1997 2 20 AU961157 1 19960630 G 2130 PRESSURIZATION DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE CABIN PRESS CONT FAULTY W K NONE O OTHER NR NOT REPORTED 1 AU S (AUS) AIRCRAFT DEPRESSURISED - CABIN CREW REPORTED CABIN DOOR MAKING NOISE - GROUND CHECKS CARRIED OUT ON DOOR SEAL AND SYSTEM COULD FIND NO FAULTS 2 H 7 2 4T 4 T RT A13NM E20NE 1997022000642 19970220 00642 CE 1997 2 20 AU961158 1 19960808 G 2510 SEAT BELT CESSNA 172 172B 2072406 CE CONT O300 O300C 17022 SO MCAULY 1C172 1C172EM GL FLT COMPARTMENT WRONG PART W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) SEAT BELT WEBBING AND HARDWARE WAS OF AUTOMOTIVE ORIGIN - UNAPPROVED PART - PERSONNEL/MAINTENANCE ERROR 1 H 7 1 3O 3 O NT 3A12 E253 5 N P910 1997022000643 19970220 00643 CE 1997 2 20 AU961159 1 19960808 G 2510 SEAT BELT BEECH 35 P35BEECH 1151530 CE CONT O470 IO470N 17026 SO MCAULY 2A36C 2A36C23 GL FLT COMPARTMENT WRONG PART W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) SEAT BELT HARDWARE AND WEBBING WAS OF AUTOMOTIVE ORIGIN - UNAPPROVED PART - PERSONNEL/MAINTENANCE ERROR 1 L 7 1 3O 3 O 3A15 3E1 5 C P880 1997022000644 19970220 00644 NM 1997 2 20 AU961160 1 19960620 G 5311 AD461 FRAME ROBSIN R22 R22BETA NM LYC O320 O320B2C 41508 EA MAIN FRAME SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LOWER LH FUSELAGE FRAME CRACKED AT UPPER REAR ATTACHMENT LUG - FOUND DURING NON-DESTRUCTIVE TESTING 1 G 7 1 3O 3 O H10WE E274 1997022000645 19970220 00645 CE 1997 2 20 AU961161 1 19960801 G 3230 MS2451020 CIRCUIT BREAKER BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO MCAULY 3AF34C 3AF34C502 GL LG EXT-RETRACT FAULTY W K NONE O OTHER CL CLIMB 1 AU S (AUS) LANDING GEAR RETRACTION MOTOR CIRCUIT BREAKER FAULTY 1 L 7 2 3O 3 O 3A16 E5CE 5 C P22EA 1997022000646 19970220 00646 CE 1997 2 20 AU961162 1 19960627 G 2434 ALV2006AS BEARING PRESTOLITE ALTERNATOR CESSNA 340 340CESSNA 2076404 CE CONT O520 TSIO520K 17040 SO MCAULY 3AF32C 3AF32C93 GL DC GEN/ALT LOOSE W K NONE O OTHER IN INSP/MAINT 1 AU S 557 A10896 (AUS) ALTERNATOR SLIP RING END BEARING INNER RACE LOOSE ON ROTOR SHAFT 1 L 7 2 3O 3 O 3A25 E8CE 5 C P22EA 1997022000647 19970220 00647 CE 1997 2 20 AU961163 1 19960805 G 5550 07311001415 FITTING 073110015 CESSNA 188 A188B 2073005 CE MCAULY 3A32C D3A32C90 GL VERT STAB STRUCT LOOSE W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) RUDDER LOWER ATTACHMENT FITTING NOT SECURED BY RIVETS ON TOP AND BOTTOM SIDES - SUSPECT MANUFACTURING ERROR 1 L 7 1 3O A9CE 5 C P21EA 1997022000648 19970220 00648 NM 1997 2 20 AU961164 1 19960731 G 3231 400088001 BELLCRANK PIPER PA60 PA60600A 7106002 NM LYC O540 IO540K1J5 41532 EA LG EXT-RETRACT SHEARED W K NONE O OTHER CL CLIMB 1 AU S (AUS) LH MAIN LANDING GEAR DOOR BELLCRANK SHEARED 1 M 7 2 3O 3 O RT A17WE 1E4 1997022000649 19970220 00649 WP 1997 2 20 AU961165 1 19960730 G 5720 40852001 PIN WTHRLY 620 620 9630602 WP PWA R985 R985AN1 52008 NE OUTER WING SYS MISMANUFACTURED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) WING HINGE PINS FAULTY - DEPTH OF THREADED HOLES VARIES BETWEEN 21.463MM AND 21.844MM (0.845IN AND 0.860IN) - MAX IMUM DEPTH OF HOLE IS 21.336MM (0.840IN) - FOUND DURING INSPECTION IAW WEATHERLY SERVICE NOTE NO15 1 L 7 1 3R 3 R A26WE 5E1 1997022000650 19970220 00650 CE 1997 2 20 AU961166 1 19960609 G 3230 PIPE BEECH 23 C24R 1151254 CE LYC O360 IO360A1B6 41514 EA LG EXT-RETRACT CRACKED W K NONE O J K OTHER WARNING INDICATION FLUID LOSS LD LANDING 1 AU S L1799661A (AUS) MAIN LANDING GEAR DOWN LINE CRACKED - NOSE AND RH MLG COLLAPSED ON LANDING 1 L 7 1 3O 3 O A1CE 1E10 1997022000651 19970220 00651 SW 1997 2 20 AU961167 1 19960808 G 3230 LANDING GEAR MTSBSI MU2 MU2B30 5780410 SW HARTZL HCB3T HCB3TN5 GL LG EXT-RETRACT S FAULTY W K NONE O OTHER LD LANDING 1 AU S (AUS) LANDING GEAR WOULD NOT EXTEND IN NORMAL OR EMERGENCY MODES 1 H 7 2 3T A2PC 6 C P15EA 1997022000652 19970220 00652 NE 1997 2 20 AU961168 2 19960813 G 7230 310652101 COMPRESSOR BLADE PWA PT6A42 BEECH 200 B200C 1152924 CE PWA PT6 PT6A42 52043 NE TURB ENG COMP FOD W K NONE O OTHER IN INSP/MAINT 1 AU S 1740 PCE94283 PCE94283 (AUS) RH ENGINE COMPRESSOR FIRST STAGE BLADES DAMAGED BY FOD - AIRCRAFTHAD PREVIOUSLY OPERATED FROM GRAVEL STRIPS 1 L 7 2 4T 4 T A24CE E4EA 1997022000653 19970220 00653 CE 1997 2 20 AU961169 1 19960806 G 5330 1054400005 SKIN BEECH 76 76 1153005 CE EXT PLATES/SKIN CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) REAR FUSELAGE SKIN CRACKED IN SIX PLACES IN AREA AROUND TWO RIVETS AT STN 210 BULKHEAD AND NEAR STRINGER PNO 105- 440000-11 - CRACK LENGTHS 6MM (0.236IN) - SUSPECT CAUSED BY OIL CANNING OF THE SKIN - STRINGER IS NOT CONNECTED TO THE B ULKHEAD AT THIS POINT 1 L 7 2 3O A29CE 1997022000654 19970220 00654 CE 1997 2 20 AU961170 1 19960806 G 5330 1054400006 SKIN BEECH 76 76 1153005 CE EXT PLATES/SKIN CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) REAR FUSELAGE SKIN CRACKED IN FIVE PLACES AROUND TWO RIVETS AT STN 210 BULKHEAD AND NEAR STRINGER PNO HSJ 5893 - C RACK LENGTHSAPPROXIMATELY 10MM (0.393IN) - SUSPECT CAUSED BY OIL CANNING OF THE SKIN - STRINGER IS NOT ATTACHED TO THE BULKHEAD AT THIS POINT 1 L 7 2 3O A29CE 1997030300005 19970303 00005 SO 1997 3 3 AU961171 1 19960819 G 5711 SPAR PIPER LHWING PIPER PA32 PA32300 7103212 SO LYC O540 IO540K1A5 41532 EA HARTZL HCC2Y HCC2YK1 GL OUTER WING SYS MISSING RIVET W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH WING MAIN SPAR TOP CAP REAR FLANGE INBOARD MISSING RIVETS - NEW MAIN SPAR AND TOP REAR WING SKIN FITTED IN JUNE 1977 FOLLOWING HEAVY LANDING REPAIRS - PERSONNEL/MAINTENANCE ERROR 1 L 7 1 3O 3 O A3SO 1E4 5 C P920 1997022000655 19970220 00655 SO 1997 2 20 AU961172 1 19960530 G 5312 6244403 BULKHEAD PIPER PA32 PA32300 7103212 SO LYC O540 IO540K1A5 41532 EA HARTZL HCC2Y HCC2YK1 GL MAIN FRAME SYS CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FIN FORWARD SPAR ATTACHMENT BRACKET AND FUSELAGE BULKHEAD LOCATED AT FS 228 CORRODED 1 L 7 1 3O 3 O A3SO 1E4 5 C P920 1997022000656 19970220 00656 SO 1997 2 20 AU961173 1 19960530 G 5340 6241300 FITTING PIPER PA32 PA32300 7103212 SO LYC O540 IO540K1A5 41532 EA HARTZL HCC2Y HCC2YK1 GL ATTACH FITTING CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) STABILATOR ATTACHMENT FITTINGS, FUSELAGE STRINGERS AND SKIN CORRODED - FOUND DURING INSPECTION IAW AD/PA32/75 1 L 7 1 3O 3 O A3SO 1E4 5 C P920 1997022000657 19970220 00657 EU 1997 2 20 AU961174 1 19960327 G 5330 SKIN FOKKER F27 F27MK50 EU EXT PLATES/SKIN CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) REAR FUSELAGE SKIN CRACKED IN ZONE 300 IN AREA APPROXIMATELY 177.8MM (7IN) BELOW LH AND RH HORIZONTAL STABILISER A T FS 21580 -1. FS 21580 LH CRACKED IN TWO AREAS - CRACK LENGTHS 88.9MM AND114.3MM (3.5IN AND 4.5IN) - IN ADDITION INTERN AL VERTICAL FRAME CRACKED IN SEVERAL AREAS WITH SMALL SECTIONS BROKEN AWAY2. FS 21580 RH - CRACK LENGTH 63.5MM (2.5IN) 2 H 7 2 4T RT A817 1997022000658 19970220 00658 NE 1997 2 20 AU961175 2 19960810 G 7240 ATOMIZER BOEING 727 727277 138408S NM PWA JT8 JT8D15 52051 NE ENG,FUEL DIST SY HOLED W K NONE O OTHER IN INSP/MAINT 1 AU S 687608 (AUS) NO3 ENGINE COMBUSTION CHAMBER NO4 ATOMISER HOLED - FOUND DURING BORESCOPE INSPECTION IAW PWJ-72-40-72 2 L 7 3 4F 4 F RT A3WE E2EA 1997022000659 19970220 00659 NM 1997 2 20 AU961176 1 19960712 G 2130 7638102 CONTROLLER BOEING 737 73733A 1384673 NM GE CFM56 CFM563B1 13802 NE CABIN PRESSURE FAULTY W K NONE O OTHER DE DESCENT 1 AU S 13022 BG1542ANSET (AUS) CABIN PRESSURE CONTROLLER SUSPECT FAULTY - CONTROLLER CHANGED - WORKSHOP INSPECTION COULD FIND NO FAULTS BUT PRES SURISATIONSYSTEM NOW OPERATES NORMALLY 2 L 7 2 4F 4 F RT A16WE E2GL 1997030300006 19970303 00006 EU 1997 3 3 AU961177 1 19960816 G 3260 INDICATOR HWKSLY DH104 DH104* EU HWKSLY PD143 PD143312 EU LG POSITION IND SEIZED W K NONE O N OTHER FALSE WARNING LD LANDING 1 AU S (AUS) RH MAIN LANDING GEAR MECHANICAL FLAG INDICATION SYSTEM SEIZED IN THE `UP' INDICATION POSITION 1 L 7 2 3I A807 5 C P916 1997022000660 19970220 00660 SO 1997 2 20 AU961178 1 19960709 G 3230 604ENI6 SWITCH EMB 110 EMB110P1 3260122 SO PWA PT6 PT6A34 52043 EA HARTZL HCB3T HCB3TN3 GL LG EXT-RETRACT FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH MAIN LANDING GEAR DOWNLOCK MICROSWITCH FAULTY - FOUND DURING INSPECTION IAW AD/EMB110/42 1 L 7 2 4T 4 T A21SO E4EA 6 C P15EA 1997022000661 19970220 00661 SO 1997 2 20 AU961179 1 19960709 G 2730 4A321404 TORQUE TUBE EMB 110 EMB110P1 3260122 SO PWA PT6 PT6A34 52043 EA HARTZL HCB3T HCB3TN3 GL ELEVATOR STRUCT CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH ELEVATOR TORQUE TUBE CRACKED FROM TAPER PLUG HOLES - FOUND DURING INSPECTION IAW SB110-027-0079 1 L 7 2 4T 4 T A21SO E4EA 6 C P15EA 1997022000662 19970220 00662 NM 1997 2 20 AU961180 1 19960712 G 5241 65C340689 HINGE BOEING 737 737377 NM SERVICE DOOR SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FORWARD GALLEY SERVICE DOOR LOWER GATE HINGE CRACKED - FOUND DURING INSPECTION IAW AD/B737/97 2 L 7 2 4F RT A16WE 1997022000663 19970220 00663 NM 1997 2 20 AU961181 1 19960720 G 5241 65C340689 HINGE BOEING 737 73733A 1384673 NM GE CFM56 CFM563B1 13802 NE SERVICE DOOR SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FORWARD GALLEY SERVICE DOOR LOWER GATE HINGE CRACKED - FOUND DURING INSPECTION IAW AD/B737/97 2 L 7 2 4F 4 F RT A16WE E2GL 1997022000664 19970220 00664 NM 1997 2 20 AU961182 1 19960709 G 5241 65C340689 HINGE BOEING 737 737377 NM SERVICE DOOR SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FORWARD GALLEY SERVICE DOOR LOWER GATE HINGE CRACKED - FOUND DURING INSPECTION IAW AD/B737/97 2 L 7 2 4F RT A16WE 1997022000665 19970220 00665 NM 1997 2 20 AU961183 1 19960715 G 5241 65C340689 HINGE BOEING 737 737377 NM SERVICE DOOR SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FORWARD GALLEY SERVICE DOOR LOWER GATE HINGE CRACKED - FOUND DURING INSPECTION IAW AD/B737/97 2 L 7 2 4F RT A16WE 1997022000666 19970220 00666 CE 1997 2 20 AU961184 1 19960806 G 3297 MS252531 WIRE CESSNA 310R CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO LG POSITION IND LOOSE W O OTHER N FALSE WARNING LD LANDING 1 AU S 0531 (AUS) LANDING GEAR WARNING SYSTEM FAULTY - FAULT TRACED TO TERMINAL WIRE G7C20 DISCONNECTED FROM FLAP 1 L 7 2 3O 3 O 3A10 E5CE 1997022000667 19970220 00667 SO 1997 2 20 AU961185 1 19960807 G 2510 SHAFT PACIFICSCIEN SEATBELT PIPER PA28 PA28161 7102803 SO LYC O320 O320D3G 41508 EA SNSNCH 74D 74DM EA FLT COMPARTMENT WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) PILOTS SHOULDER BELT INERTIA REEL CENTRE SHAFT BROKEN - INVESTIGATION FOUND THAT THE STAINLESS STEEL BELT GUIDE H AD WORN THROUGH THE CENTRE SHAFT 1 L 7 1 3O 3 O 2A13 E274 5 N P88614 1997022000668 19970220 00668 CE 1997 2 20 AU961186 1 19960612 G 5720 07214003 ANGLE CESSNA 210 2105 2073404 CE CONT O470 IO470S 17026 SO MCAULY 2A34C D2A34C58 GL OUTER WING SYS CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) DURING INSPECTION OF LH AND RH WINGS MISSING RIVET HEADS WERE FOUND ON THE WING UPPER SKIN THROUGH THE MAIN SPAR INBOARD TOP CAP - FOLLOWING REMOVAL AND DISASSEMBLY OF THE WINGS THE SEVERE EXFOLIATION CORROSION WAS FOUND ON THE FOLL OWING ANGLES ANDPLATES:- 1. LH WING PNO 0721400-3, PNO 0523315, PNO 071402-1 AND PNO 071402-3 2. RH WING PNO 0721400-4, PNO 0523315-1, PNO 071402-23. RH WING LOWER TENSION ANGLE PNO 0721402-4 AT THE WING STRUTATTACHMENT POINT SHOWED SIGNS OF STRESS CORROSION BELOW THE STRUT BOLT HOLE FAILURE OF WHICH WOULD BE CATASTROPHIC AIRCRAFT IS APPROXIMATELY 34 YEAR S OLD 1 H 7 1 3O 3 O 3A21 3E1 5 C P3EA 1997022000669 19970220 00669 CE 1997 2 20 AU961187 1 19960523 G 5730 10140451 SKIN BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A42 52043 NE CENTRE WING SYS DELAMINATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) WING SKIN DELAMINATED - FOUND DURING INSPECTION IAW AD/BEECH200/43 AMDT5 (BEECH SB 2040 REV 3) 1 L 7 2 4T 4 T A24CE E4EA 1997022000670 19970220 00670 CE 1997 2 20 AU961188 1 19960728 G 2730 COLLAR CESSNA 441 441 2076020 CE HARTZL HCB3T HCB3TN5 GL ELEVATOR STRUCT CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RH ELEVATOR TORQUE TUBE COLLAR CRACKED 1 L 7 2 3T RT A28CE 6 C P15EA 1997022000671 19970220 00671 NM 1997 2 20 AU961189 1 19960820 G 3213 765155V TORQUE LINK PIPER PA60 PA60600 7106001 NM LYC O540 IO540K1J5 41532 EA MAIN GEAR SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MAIN LANDING GEAR TORQUE LINKS CRACKED - FOUND DURING FLUORESCENT DYE PENETRANT CHECK 1 M 7 2 3O 3 O RT A17WE 1E4 1997022000672 19970220 00672 CE 1997 2 20 AU961190 1 19960801 G 5312 0713608 BULKHEAD CESSNA 182 182M 2072728 CE CONT O470 O470R 17026 SO MCAULY 2A34C 2A34C203 GL MAIN FRAME SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RH FORWARD DOORPOST BULKHEAD CRACKED IN BEND RELIEF NOTCH - FOUND DURING INSPECTION IAW AD/CESSNA180/75 1 H 7 1 3O 3 O NT 3A13 E273 5 C P3EA 1997022000673 19970220 00673 NM 1997 2 20 AU961191 1 19960816 G 2820 FUEL SYSTEM BOEING 757 757200 1384950 NM FUEL DISTRBUTION FAULTY W K NONE O OTHER CL CLIMB 1 AU S (AUS) RH ENGINE RECEIVED FUEL FROM RH TANK ONLY, CAUSING OUT OF BALANCE CONDITION - INVESTIGATION COULD FIND NO FAULTS WITH THE FUEL SYSTEM 2 L 7 2 4F RT A2NM 1997022000674 19970220 00674 NM 1997 2 20 AU961192 1 19960818 G 2430 BSK122H30PE CONNECTOR BOEING 757 757200 1384950 NM DC GENERATING SY BROKEN W K NONE H ELECT. POWER LOSS-50 PC TO TAKEOFF 1 AU S (AUS) LH ENGINE PYLON ELECTRICAL CONNECTOR D1014P HAD BROKEN WIRE TO PIN 12 2 L 7 2 4F RT A2NM 1997022000675 19970220 00675 EA 1997 2 20 AU961193 2 19960820 G 8520 LW15452 CRANKCASE LYC LTIO540J2BD PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA HARTZL HCE3Y HCE3YR2 GL R ENG POWER SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 1639 L51768A L51768A (AUS) RH ENGINE RH CRANKCASE HALF CRACKED IN AREA OF NO1 CYLINDER LOWER AFT THROUGH BOLT 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 1997022000676 19970220 00676 EU 1997 2 20 AU961194 1 19960721 G 5210 AE4014Z003 SPRING AMD FALC50 FALCON900 2700160 EU CREW-PASS DOOR S DELAMINATED W K NONE O OTHER IN INSP/MAINT 1 AU S 338284 (AUS) PASSENGER DOOR COMPENSATING CYLINDER DOOR ACTUATOR SPRING DELAMINATED AND CRACKED - THIS DEFECT WAS RECEIVED FROM NO34 SQUADRON RAAF AND IS FOR INFORMATION ONLY 2 L 7 3 4F RT A46EU 1997022000677 19970220 00677 CE 1997 2 20 AU961195 1 19960731 G 5210 AN35 BOLT CESSNA 441 441 2076020 CE HARTZL HCB3T HCB3TN5 GL CREW-PASS DOOR S SHEARED W K NONE O OTHER CL CLIMB 1 AU S (AUS) PASSENGER MAIN ENTRANCE DOOR DRIVE CAPSTAN CABLE CLAMP BOLT SHEARED ALLOWING THE DOOR TO INDICATE `LOCKED' WHEN T HE LOWERLOCK PINS WERE ONLY PARTIALLY LOCKED 1 L 7 2 3T RT A28CE 6 C P15EA 1997022000678 19970220 00678 CE 1997 2 20 AU961196 1 19960822 G 7930 1200106247 PIPE CESSNA 210 210N 2073453 CE CONT O520 IO520L 17032 SO MCAULY 3A32C D3A32C88 GL ENG OIL IND SYS WORN W O OTHER K FLUID LOSS CR CRUISE 1 AU S (AUS) ENGINE OIL PRESSURE PIPE LOCATED BETWEEN FIREWALL AND OIL PRESSURE GAUGE WORN THROUGH AND LEAKING DUE TO CHAFING BY SCAT HOSE 1 H 7 1 3O 3 O 3A21 E5CE 5 C P21EA 1997022000679 19970220 00679 SO 1997 2 20 AU961197 1 19960826 G 5310 TUBE PIPER PA22 PA22150 7102210 SO LYC O320 O320A2B 41508 EA SNSNCH 74DM M74DM EA MAIN FRAME SYS CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUSELAGE STRUCTURE LH REAR LONGITUDINAL TUBE LOCATED TO THE REAR OF THE LH PASSENGER DOOR CORRODED THROUGH IN THRE E PLACES IN A 152.4MM (6IN) LENGTH 1 H 7 1 3O 3 O 1A6 E274 5 N P88614 1997022000680 19970220 00680 GL 1997 2 20 AU961198 3 19960826 G 6114 C87 HUB MCAULY C87 CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY FAULTY W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S 1594 752980 752980 (AUS) PROPELLER HUB BLADE NUT EXPANSION LOCK PLUG INCORRECTLY DRILLED - PERSONNEL/MAINTENANCE ERROR 1 L 7 2 3O 3 O 3A10 E5CE 5 C P22EA 1997022000681 19970220 00681 NM 1997 2 20 AU961199 1 19960819 G 3220 BOLT DHAV DHC8 DHC8103 1386005 NM PWA PW121 PW121 52124 NE NOSE-TAIL GEAR JAMMED GEAR W A K NONE O OTHER LD LANDING 1 AU S (AUS) NOSE LANDING GEAR WOULD NOT EXTEND - AIRCRAFT LANDED WITH NLG RETRACTED - INVESTIGATION FOUND THAT A NEW NLG WAS RECEIVEDWITHOUT THE TOP SECTION OF THE PROXIMITY SENSOR PROTECTIVE COVER - A NEW ONE WAS MANUFACTURED AND FITTED WITH HE XAGON HEADED BOLTSINSTEAD OF THE CORRECT COUNTERSUNK ITEMS REQUIRED BY THE MANUFACTURER - INTERNAL SPACERS WERE ALSO USE D TO OBTAIN THE CORRECT INTERNAL CLEARANCE BETWEEN THE COVER AND THE PROXIMITY SENSORS - THE USE OF THE HEXAGON BOLTS AN D SPACERS RESULTED IN THE BOLTS CONTACTING THE UPPER DRAG BRACE DURING NLG RETRACTION PREVENTING NLG EXTENSION - DAMAGE CAUSED TO THE UNDERSIDE OF THE AIRCRAFT - PERSONNEL/MAINTENANCE ERROR - UNAPPROVED PART 2 H 7 2 4T 4 T RT A13NM E20NE 1997022000682 19970220 00682 WP 1997 2 20 AU961200 2 19960806 G 7200 ENGINE FRCHLD SA227 SA227DC 3377521 SW GARRTT TPE331 TPE33112UA 01514 WP MCAULY 4HFR34 4HFR34C652 NE ENGINE TURBINE SEIZED W K NONE O OTHER NR NOT REPORTED 1 AU S P70210 (AUS) ENGINE SEIZED - ENGINE HUNG DURING START AND WAS HARD TO PULL THROUGH WITH PROPELLER 2 L 7 2 4T 4 T RT A18SW E4WE 6 C 3PNE 1997030300007 19970303 00007 EU 1997 3 3 AU961201 1 19960510 G 6120 665031886326REVT MOTOR WOODWARD GOVERNOR SAAB SF340 340B 7860101 EU GE CT7TP CT79B 30030 NE ROTOL R375 R3754123F21 NE HMU CNTRL SYS LOOSE W K NONE E K VIBRATION/BUFFET FLUID LOSS TO TAKEOFF 1 AU S 374 WYG54779 785499 (AUS) RH ENGINE HYDROMECHANICAL UNIT (HMU) TORQUE MOTOR RETAINING BOLTS(3OFF) LOOSE AND RETURN FLOW `O' RING DAMAGED - S USPECT INCORRECTLY TORQUED DURING LAST SHOP VISIT 2 L 7 2 4T 4 T RT A52EU E8NE 6 C P17NE 1997022000683 19970220 00683 CE 1997 2 20 AU961202 1 19960812 G 5312 M20470AD5 RIVET CESSNA 320 320D 2074512 CE CONT O520 TSIO520B 17040 SO MAIN FRAME SYS DETERIORATED W K NONE O OTHER IN INSP/MAINT 1 AU S NA (AUS) RH AND LH AFT CANTED BULKHEAD RIVETS DETERIORATED - RIVET HEADS MISSING 1 L 7 2 3O 3 O 3A25 E8CE 1997022000684 19970220 00684 EA 1997 2 20 AU961203 2 19960815 G 7414 M3004 SUPPORT SLICK 4251 CESSNA 172 172RG 2072438 CE LYC O360 O360F1A6 41514 EA MCAULY 2D34C B2D34C220 GL DISTRIBUTOR GEAR DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S 973 2010068R L2813136A (AUS) MAGNETO DISTRIBUTOR GEAR BEARING SUPPORT DAMAGED - FOUND DURING INSPECTION IAW AD/ELEC/46 - INTERNAL DAMAGE TO MA GNETO 1 H 7 1 3O 3 O 3A17 E286 5 C P7EA 1997030300008 19970303 00008 EU 1997 3 3 AU961204 1 19960807 G 3260 7232206581 PLATE UPLOCKHOOK SAAB SF340 340B 7860101 EU GE CT7TP CT79B 30030 NE ROTOL R375 R3754123F21 NE LG POSITION IND LOOSE W K NONE O N OTHER FALSE WARNING CL CLIMB 1 AU S (AUS) NOSE LANDING GEAR UPLOCK HOOK STRIKER PLATE BOLT MISSING (1OFF2) 2 L 7 2 4T 4 T RT A52EU E8NE 6 C P17NE 1997022000685 19970220 00685 WP 1997 2 20 AU961205 2 19960729 G 7210 RING FRCHLD SA227 SA227DC 3377521 SW GARRTT TPE331 TPE33112UA 01514 WP MCAULY 4HFR34 4HFR34C652 NE TURBINE ENG. RED FAULTY W K NONE R PARTIAL RPM/PWR LOSS TO TAKEOFF 1 AU S P70145 940909 (AUS) ENGINE TORQUE RING FAULTY 2 L 7 2 4T 4 T RT A18SW E4WE 6 C 3PNE 1997022000686 19970220 00686 SW 1997 2 20 AU961206 1 19960220 G 3243 HP1431031 ROD MASTERCYL FRCHLD SA227 SA227DC 3377521 SW GARRTT TPE331 TPE33112UA 01514 WP MCAULY 4HFR34 4HFR34C652 NE LG WHEEL/BRAKE FAILED W K NONE O OTHER NR NOT REPORTED 1 AU S 2756 (AUS) LH TOE BRAKE MASTER CYLINDER PISTON ROD FAILED AT BOTTOM THREAD OF EYE END 2 L 7 2 4T 4 T RT A18SW E4WE 6 C 3PNE 1997030300009 19970303 00009 NE 1997 3 3 AU961207 2 19960119 G 7230 6058T86G01 COMPRESSOR GE CT79B SAAB SF340 340B 7860101 EU GE CT7TP CT79B 30030 NE ROTOL R375 R3754123F21 NE TURBINE ENGINE FOD W E C ENGINE SHUTDOWN ABORTED TAKEOFF R PARTIAL RPM/PWR LOSS CR CRUISE 1 AU S 1176 785487 785487 (AUS) LH ENGINE COMPRESSOR DAMAGED DUE TO FOD - INSPECTION FOUND ONE 1ST STAGE BLADE BENT FORWARD AND SEVERAL OTHER BLAD ES DAMAGED -SUSPECT DUE TO ICE INGESTION - MID FRAME DESWIRL CONE RING ALSO CRACKED AND DAMAGED 2 L 7 2 4T 4 T RT A52EU E8NE 6 C P17NE 1997022000687 19970220 00687 SW 1997 2 20 AU961208 1 19960602 G 3220 STRUT FRCHLD SA227 SA227DC 3377521 SW GARRTT TPE331 TPE33112UA 01514 WP MCAULY 4HFR34 4HFR34C652 NE NOSE-TAIL GEAR FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NOSE LANDING GEAR STRUT CONTAMINATED BY AIR - STRUT SEALS HAD BEEN REPLACED ON THE 1ST JUNE 1996 AND THE HYDRAULI C SIDE HAD NOTBEEN FULLY BLED (CONTAINED AND AIRLOCK) 2 L 7 2 4T 4 T RT A18SW E4WE 6 C 3PNE 1997022000688 19970220 00688 SW 1997 2 20 AU961209 1 19960822 G 2460 LOOM FRCHLD SA227 SA227DC 3377521 SW GARRTT TPE331 TPE33112UA 01514 WP MCAULY 4HFR34 4HFR34C652 NE DC POWER DISTRIB WORN W K NONE O OTHER CR CRUISE 1 AU S (AUS) AFT AVIONICS WIRING LOOM PARTIALLY CUT THROUGH BY AIRCONDITIONER ANTIVIBRATION BASE MOUNT - LOOM IS ROUTED THROUGH THE GAP BETWEENTHE MOUNT AND A STRUCTURAL RIB AND PROVIDES POWER FOR THE CVR, ELT, FDR AND AIRCONDITIONING SYSTEM 2 L 7 2 4T 4 T RT A18SW E4WE 6 C 3PNE 1997022000689 19970220 00689 GL 1997 2 20 AU961210 3 19960823 G 6114 TCM6958 HUB MCAULY 1A103TCM CESSNA 150 A152 2071836 CE MCAULY 1A103 1A103TCM GL PROPELLER ASSY CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 300 R775268 (AUS) PROPELLER HUB CRACKED ADJACENT TO BOLT HOLES AS INDICATED IN MCCAULEY SB 219 1 H 7 1 3O 3A19 5 N P50GL 1997022000690 19970220 00690 SO 1997 2 20 AU961211 1 19960823 G 7120 3802000 FRAME PIPER PA32 PA32R300 7103213 SO LYC O540 IO540K1G5 41532 EA HARTZL HCC2Y HCC2YK1 GL ENGINE MOUNTING CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE MOUNT FRAME CRACKED IN CLUSTER WELD ADJACENT TO THE RH DRAG BRACE BUSHING - CRACK LENGTH 20MM (0.787IN) 1 L 7 1 3O 3 O A3SO 1E4 5 C P920 1997022000691 19970220 00691 1997 2 20 AU961212 4 19960827 G 2562 SWITCH ELT CESSNA 172 172D 2072410 CE CONT O300 O300C 17022 SO MCAULY 1C172 1C172EM GL EMERGENCY LOCATO FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ELT `G' SWITCH FAULTY 1 H 7 1 3O 3 O NT 3A12 E253 5 N P910 1997022000692 19970220 00692 CE 1997 2 20 AU961213 1 19960826 G 5511 2719 SPAR CESSNA 172 CESSNA 172 R172K 2072431 CE CONT O360 IO360K 17025 SO MCAULY 2A34C 2A34C203 GL HORZ STAB SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 2719 (AUS) HORIZONTAL STABILISER FRONT SPAR AND DOUBLER CRACKED - FOUND DURING INSPECTION IAW AD/C170/59 - AIRCRAFT IS USED F OR CATTLE MUSTERING 1 H 7 1 3O 3 O 3A17 E1CE 5 C P3EA 1997022000693 19970220 00693 NE 1997 2 20 AU961214 2 19960820 G 7210 GEAR BOX SKRSKY S76 S76A 8143006 NE TMECA ARRIEL ARRIEL1S 60030 NE TURBINE ENG. RED MAKING METAL W K NONE J WARNING INDICATION CR CRUISE 1 AU S 2076 15077 (AUS) NO1 ENGINE REDUCTION GEARBOX MAGNETIC PLUG CONTAMINATED WITH TYPE3 METAL PARTICLES - SOME TYPE 1 AND TYPE 2 PARTIC LES ALSO ON GEARBOX MAGNETIC PLUGS 1 G 7 2 3U 3 U H1NE E19EU 1996022300415 19960223 00415 SO 1996 2 23 BTVR11996 1 19960119 G 5610 1159SCB31024 WINDSHIELD PPG GULSTM G1159 GIV 3980115 SO RT SIDE CRACKED B BTVR K NONE O OTHER IN INSP/MAINT 1 GL 23 41CP 91282H9190 1179 OUTER LAYER OF GLASS FOUND TO HAVE MULTIPLE CRACKS OVER THE ENTIRE SURFACE. ALL GLASS WAS FOUND TO HAVE STAYED INTACT. THE CRACKS APPEAR TO HAVE ORIGINATED AT THE LOWER CENTER AREAS OF THE GLASS ADJACENT TO THE FRAME. (X) 2 L 7 2 4F RT A12EA 1996080600001 19960806 00001 EU 1996 8 6 CA960103002 1 19960102 G 3320 S2806102 SOCKET BAG BAE146 BAE146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE SIDEWALL LIGHT BURNT W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA LF05465A (CAN)SMOKE COMING FROM SIDEWALL LIGHTING ROW 16 DEF. SOCKET FOR LIGHT BAR FOUND BURNED FROM ELECTRICAL ARCING. LAMP HOLD ER REPLACED. 2 H 7 4 4F 4 F RT A49EU E6NE 1996082900084 19960829 00084 GL 1996 8 29 CA960110005 3 19960102 G 6114 C5480 HUB MCAULY 2A34C 2A34C66 GL NR1 SOCKET CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 1591 741 733444 (CAN)PROPELLER RECEIVED FOR CALENDAR TIME OVERHAUL. AS PER SERVICE BULLETIN 205B EDDY CURRENT CRACK DETECTION WAS PERFOR MED ON PROPELLER HUB THREADED SOCKETS. CRACK DETECTED ON #1 SOCKET. 5 C P3EA 1996090500243 19960905 00243 EU 1996 9 5 CA960111013 1 19960103 G 3230 PUSH PULL ROD GROB 103CAT G103TWNASTIR 1660202 EU MLG ACTUATOR BEARING FAILED W K NONE O OTHER LD LANDING 1 CA (CAN)UNDERCARRIAGE COLLAPSED FOLLOWING TOUCHDOWN. INSPECTION OF THE SYSTEM REVEALED THE ROD END BEARING, AT THE END OF T HE ACTUATOR PUSH/PULL ROD WHERE IT ATTACHES TO THE SECONDARY ACTUATOR ARM HAD COME OUT OF THE ROD END BEARING RETAINING RING. THE ROD THREADED PORTION OF THE ROD END WAS BENT, AS WAS THE ACTUATOR ARM TO WHICH IT WAS ATTACHED. THE LEFT GEAR DOOR WAS WORN THROUGH, REAR HINGE POINT ON THE DOOR WAS TORN AND FRONT HINGE BENT. THE BRAKE ACTUATOR ARM WAS BENT IN. 1 K 0 0 G39EU 1996091600007 19960916 00007 NM 1996 9 16 CA960111016 1 19960110 G 2917 FLOW REGULATOR BOEING 727 727171C 1384057 NM LT WELL HYD LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN)HYDRAULIC FLOW REGULATOR IN LH WHEEL WELL LEAKING. REPLACED. STRIP REPORT INDICATES THAT THE INTERNAL SEALS WERE AT FAULT. 2 L 7 3 4F A3WE 1996090500260 19960905 00260 NM 1996 9 5 CA960115010 1 19960109 G 2435 03600923 BEARING LUCAS 23088002A DHAV DHC8 DHC8* NM STARTER/GEN FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 1451 420 (CAN)STARTER GENERATOR FAILURE CAUSED MINOR DAMAGE TO GENERATOR. 2 H 7 2 4T RT A13NM 1996090500270 19960905 00270 NE 1996 9 5 CA960115020 2 19960103 G 7230 BEARING PWA JT15 JT15D1 52060 NE COMP SHAFT NR 1 DISTRESSED W E ENGINE SHUTDOWN E VIBRATION/BUFFET DE DESCENT 1 CA 4721 1844 77326 (CAN)DURING DESCENT THE CREW REPORTED HEAVY VIBRATION AND NOISE FROM #1 ENGINE. THE ENGINE WAS SHUTDOWN. ENGINE TEARDOWN INDICATES MAJOR DISTRESS TO THE #1 BEARING. 4 F E1NE 1996090500273 19960905 00273 CE 1996 9 5 CA960115101 1 19960111 G 2730 0510105291 CONTROL CABLE CESSNA 0510105291 CESSNA 172 172M 2072418 CE ELEV AFT PULLEY FRAYED W K NONE O OTHER IN INSP/MAINT 1 CA 4458 (CAN)DURING THE PREFLIGHT INSPECTION THE PILOT MOVED THE ELEVATOR AND HEARD A RUBBING NOISE AGAINST THE SKIN. INSPECTION REVEALED THE UPPER ELEVATOR CABLE WAS SEVERELY FRAYED AT THE AFT PULLEY LOCATION. TH E PULLEY WAS FOUND TO MOVE FREELY BUT HAD A SLIGHT GROOVE. A TIMELY AND THOROUGH PREFLIGHT MAY HAVE PREVENTED AN ACCIDENT. 1 H 7 1 3O NT 3A12 1996090500276 19960905 00276 1996 9 5 CA960116002 4 19960108 G 2562 2016 BATTERY POINTER C4000 AT EXIT HOLE CHAFED WIRE W K NONE O OTHER IN INSP/MAINT 1 CA (CAN)DURING ANNUAL RECERTIFICATION OF ELT, 3 OF THE BATTERY PACKS WERE NOTED WITH WIRES CHAFED AT THE EXIT HOLE ON TOP O F BATTERY. 1996090500279 19960905 00279 EA 1996 9 5 CA960116007 1 19960111 G 3213 PINS AND BEARING ROTOL 6008508071 CNDAIR CL600 CL6001A11 1900302 EA MLG CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 5537 (CAN)MAIN LANDING GEAR SHOCK STRUT ATTACH PINS AND BEARINGS CORRODED AND SOME WEAR PROBLEMS AS WELL. 2 L 7 2 4F RT A21EA 1996090500291 19960905 00291 1996 9 5 CA960122005 1 19960111 G 2913 3065476 DRIVE GEAR EASTERN 1213HBG310 OIL PUMP MIS INSTALLED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA OM30651 (CAN)SUBMITTER STATES THAT THE DRIVE GEAR WAS INSTALLED BACKWARDS RESULTING IN FAILURE AND MAJOR DAMAGE TO THE PUMP. 1996090500296 19960905 00296 SO 1996 9 5 CA960122011 1 19960106 G 5344 4810100 FLOOR RIB PIPER PA31T PA31T 7103124 SO DOOR HINGE AREA CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 6067 (CAN)FUSELAGE FLOOR RIB CRACKED AT STN 222.19 WHERE THE CABIN DOOR HINGE IS ATTACHED. A 1/2 IN CRACK IS LOCATED IN THE CORNER WHERE THE PLATE FOR THE CABIN DOOR HINGE IS BOLTED. SUBMITTER STATES THAT THIS LOCATION IS HARD TO SEE WITHOUT RE MOVING THE PLATE FIRST. SEE ALSO SDR 960122012, CRACK AT STN 224.9. 1 L 7 2 3T A8EA 1996090500297 19960905 00297 SO 1996 9 5 CA960122012 1 19960106 G 5344 4522402 FLOOR RIB PIPER PA31T PA31T 7103124 SO PWA DOOR HINGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 6069 (CAN)FUSELAGE FLOOR RIB FOUND CRACKED AT STN 224.9 IN THE UPPER CORNER WHERE THE CABIN DOOR HINGE IS RIVETED. SEE ALSO S DR 960122011 FOR A CRACK OF THE SAME DESCRIPTION AT STN.22.19 1 L 7 2 3T A8EA 1996090500318 19960905 00318 1996 9 5 CA960123012 1 19960112 G 2435 03601018 BEARING LUCAS 23079005 START/GENERATOR FAILED W K NONE O OTHER NR NOT REPORTED 1 CA 787 5427 (CAN)STARTER GENERATOR BEARING FAILED AT THE ANTI-DRIVE END. 1996121200498 19961212 00498 EA 1996 12 12 CA960123022 2 19960116 G 8530 VALVE CESSNA 172 172L 2072432 CE LYC O320 O320E2D 41508 EA MCAULY 1C160 1C160CTM GL #4 CYLINDER JAMMED W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA 3189 649 L4004427A 720159 (CAN) NON FERROUS METAL IN THE MAIN AND SUCTION OIL SCREENS. ZERO COMPRESSION ON #4 CYLINDER, SUSPECT A JAMMED VALVE. #4 CYLINDER REMOVED AND SENT FOR REPAIR. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 1996091200850 19960912 00850 EU 1996 9 12 CA960123027 2 19960102 G 7200 ENGINE RROYCE SPEY SPEY55515P 54521 EU TAIL PIPE MAKING METAL W E ENGINE SHUTDOWN E VIBRATION/BUFFET CR CRUISE 1 CA 9796 (CAN)VIBRATIONS FELT AT FL250. POWER REDUCED FROM 94 PERCENT TO 91 PERCENT & VIBRATIONS INCREASED. ENGINE WAS SHUTDOWN & FLIGHT DIVERTED. POST FLIGHT INSPECTION FOUND METAL IN TAILPIPE & DAMAGE TO BOTH THE LP & HP SYSTEMS. FURTHER DETAILS W ILL FOLLOW ENGINE TEARDOWN. 4 F E2EU 1996091900543 19960919 00543 NM 1996 9 19 CA960126025 1 19960119 G 2435 03600923 BEARINGS LUCAS 23088002A DHAV DHC8 DHC8* NM STARTER ROTOR FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 1447 353 (CAN)BOTH STARTER GENERATOR BEARINGS ON THE ROTOR FAILED. FOUND ON THE BENCH. 2 H 7 2 4T RT A13NM 1996091900549 19960919 00549 SW 1996 9 19 CA960126032 1 19960111 G 5320 TUBE STRUCTURE MOONEY M20 M20J 5870219 SW VENT WINDOW CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 2575 (CAN)CORROSION FOUND ON AIRCRAFT TUBULAR STRUCTURE IN AREAS OF PILOTS VENT WINDOWS AND BELOW BOTH AIR VENTS ON THE SIDES OF THE AIRCRAFT. CORROSION ALSO FOUND ON THE OVERHEAD TUBE BY THE AIR VENT. 1 L 7 1 3O 2A3 1996091900551 19960919 00551 CE 1996 9 19 CA960126034 1 19960112 G 2730 05130631 BRACKET CESSNA 05130631 CESSNA 172 172F 2072414 CE CONT O300 O300D 17022 SO ELEV BELLCRANK CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 5948 29320D4D (CAN)AT THE ANNUAL INSPECTION OF THIS AIRCRAFT THE FORWARD ELEVATOR BELLCRANK SUPPORT BRACKET WAS FOUND CRACKED. THE LOC ATION IS AT THE LEFT FORWARD ATTACHMENT ANGLE UNDER THE CABIN FLOOR AFT OF THE FUEL S ELECTOR. THE TOP BAR SUPPORTING TH E BELLCRANK CENTRE BOLT WAS ALSO FOUND BROKEN. THE PART WAS NOT REPAIRABLE AND THEREFORE WAS REPLACED WITH NEW P/N 05130 63-1. SUBMITTER NOTES THAT THE REPLACEMENT PART WAS FOUND TO BE MORE ROBUST THAN THE ORIGINAL. 1 H 7 1 3O 3 O NT 3A12 E253 1997011600064 19970116 00064 CE 1997 1 16 CA960126036 1 19960115 G 2913 99120624 PUMP CESSNA 500 560CESSNA 2076750 CE LT ENG HYD CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 921 921 (CAN) DURING A VISUAL INSPECTION ON PHASE 4, FOUND OUTBOARD UPPER HOUSING ATTACH BOLT HOLE AREA CRACKED ON L/H ENGINE DR IVEN HYDRAULIC PUMP. 2 L 7 2 4F RT A22CE 1996091900570 19960919 00570 CE 1996 9 19 CA960129013 1 19960116 G 2910 249A4TB CHECK VALVE CESSNA 441 441 2076020 CE HYD SYS LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 5389 (CAN)HYDRAULIC CHECK VALVE UNDER #2 PASSENGER SEAT LEAKED AND CONTAMINATED BOTH THE INSTRUMENT AIR PRESSURE LINES AND TH E WATER SEPARATOR. UPON DISASSEMBLY OF THE VALVE, THE 'O' RINGS WERE FOUND DEFECTIVE. 1 L 7 2 3T RT A28CE 1996100300803 19961003 00803 EA 1996 10 3 CA960131001 1 19960125 G 5310 STRUCTURE DHAV DHAV DHC2 DHC2EVANS 2801832 EA FORWARD FRAME CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN)IN REFERENCE TO SB 2/49 FORWARD FUSELAGE FRAME TUBULAR STRUCTURE FOUND CORRODED USING RADIOGRAPHY TECHNIQUE.SUBMITE R NOTES THAT ULTR ASONIC TECHNIQUE WAS INITIALLY USED BUT 'NO R EADING' LED TO FRAME REJECTION. WHEN RADIOGRAPHY WAS US ED PITTING CORROSION WAS FOUND. THUS THEY FEEL THAT A RADIOGRAPH INSPECTION WILL PROVIDE A MORE POSITIVE RESULT AS WELL L AS PROVIDING A PERMANENT RECORD. 1 H 7 1 3O A806 1997011600067 19970116 00067 CE 1997 1 16 CA960131012 1 19960120 G 2920 551701084 HYDRAULIC LINE CESSNA 500 560CESSNA 2076750 CE AUX.HYD. SYSTEM CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA 929 (CAN) FOLLOWING A TENSION CHECK OF AILERON CABLES TO CLEAR A REPORTED DEFECT, THE AREA AT AILERON SECTOR (PANEL NO.271AT C) WAS INSPECTED FOR CLEANLINESS AND THE AUXILIARY HYDRAULIC LINE SHOWED CHAFING MARKS PRESUMABLY CAUSED BY CONTACT WITH THE AILERON SECTOR. THIS HYDRAULIC LINE WAS PROBABLY MOVED DURING A PREVIOUS ACCESS TO THIS AREA WHICH CANNOT BE DETERM INED. 2 L 7 2 4F RT A22CE 1996101000416 19961010 00416 SW 1996 10 10 CA960131014 1 19960123 G 6510 2060403389 HANGER ASSEMBLY BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL LUG AREA WORN W K NONE O OTHER IN INSP/MAINT 1 CA CAE802381 (CAN)WHEN CARRYING OUT ASB 206-95-86 REV.B, INSPECTION OF TAIL ROTOR DRIVESHAFT HANGER ASSEMBLY AND SPRING. A VISIBLE WE AR STEP IN THE FILLET RADIUS OF THE HANGER LUG WAS FOUND. 1 G 7 1 3U 3 U H2SW E4CE 1996101000417 19961010 00417 CE 1996 10 10 CA960131201 1 19960106 G 3240 0500106194 LINE CESSNA 0500106194 CESSNA 172 172E 2072412 CE CONT O300 O300D 17022 SO BRAKE ABRAIDED W K NONE O OTHER IN INSP/MAINT 1 CA 4381 28272D3D (CAN)UPPER ELEVATOR CABLE ABRAIDED THE ALUMINUM BRAKE LINE. REPAIRED AND AIRCRAFT RETURNED TO SERVICE. 1 H 7 1 3O 3 O NT 3A12 E253 1996101000419 19961010 00419 EA 1996 10 10 CA960202002 1 19960115 G 3010 15323C VALVE BENDIX DHAV DHC6 DHC6300 EA PWA PT6 PT6A27 52043 EA DEICE CORRODED W O OTHER L NO TEST TX TAXI/GRND HDL 1 CA 244461U PCE42076 (CAN)DURING PREFLIGHT THE DEICE SYSTEM TESTED AND RH DEICE BOOT WOULD NOT INFLATE. RH DISTRIBUTOR VALVE REPLACED. VALVE CORRODED INTERNALLY. 1 H 7 2 3T 4 T A9EA E4EA 1996101000420 19961010 00420 EA 1996 10 10 CA960202003 1 19960115 G 2822 2532310102 PUMP DHAV DHC6 DHC6300 EA PWA PT6 PT6A27 52043 EA FUEL LOW PRESSURE W K NONE O OTHER IN INSP/MAINT 1 CA 528 2210 PCE42076 (CAN)DURING MAINTENANCE TO FIND START PROBLEM, FUEL PUMP OUTPUT PRESSURE FOUND TOO LOW 1 H 7 2 3T 4 T A9EA E4EA 1996101000422 19961010 00422 NM 1996 10 10 CA960202007 1 19960126 G 2435 03600923 BEARING LUCAS 23088002A DHAV DHC8 DHC8* NM PWA 120 PW120 NE GEN DRIVE END FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 1021 1284 120896 (CAN)DRIVE END BEARING FAILED ON STARTER GENERATOR. 2 H 7 2 4T 4 T RT A13NM E20NE 1996101000423 19961010 00423 EU 1996 10 10 CA960202008 1 19960122 G 8200 2220FG TANK UNIT BRAERO 748 HS7482A 4231001 EU RROYCE DART DART5342 EU MENTHENOL INTERMITTENT W K NONE O OTHER IN INSP/MAINT 1 CA 14902 (CAN)WATER MENTHENOL TANK DOES NOT INDICATE CONTENTS OF TANK IN THE 20-27 RANGE. 2 L 7 2 3T 4 T A24EU A196 1996101000433 19961010 00433 1996 10 10 CA960202019 4 19960119 G 2360 211SC1 STATIC WICK CHELTON EMB 120 EMB120RT SO PWA 118 PW118 NE HAMSTD 14RF 14RF9 NE WINGS & ELEV CORRODED W K NONE O OTHER DE DESCENT 1 CA PCE115667 880130 (CAN)ON DESCENT IN LIGHT RAIN, AIRCRAFT HAD RADIO RECEPTION FAILURE, BUT COMMUNICATION TRANSMISSION WAS NORMAL. 8 STATIC WICKS HAD TO BE REPLACED. 2 ON EACH WING AND 2 ON EACH ELEVATOR. RESISTANCE CHECKS T O BE INCREASED TO 1200 HOURS FROM 4000. 2 L 7 2 4T 4 T RT A31SO E20NE 6 C P11NE 1996101000439 19961010 00439 NE 1996 10 10 CA960202025 2 19960109 G 7322 FCU DHAV DHC8 DHC8* NM PWA PW120 PW123 NE #1 ENGINE FAULTY W E ENGINE SHUTDOWN O OTHER CL CLIMB 1 CA 4139 123223 (CAN)IN CLIMB #1 ENGINE PARAMETERS DECREASED AND PILOT SHUT THE ENGINE DOWN. THE #1 ENGINE MAIN FUEL CONTROL UNIT (MFCU) WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. 2 H 7 2 4T 4 T RT A13NM E20NE 1996102300007 19961023 00007 NE 1996 10 23 CA960202026 2 19960125 G 7310 "O" RING PACKING PWA PW120 PW126A NE FUEL MANIFOLD DAMAGED W E ENGINE SHUTDOWN A FLAME/FIRE CL CLIMB 1 CA 4578 458 124535 (CAN)DURING A LANDING ROLL THERE WAS A FIRE ON #1 ENGINE. POST FLIGHT THE FIRE WAS CONFIRMED TO ORIGINATE FROM A DAMAGED FUEL MANIFOLD PACKING THAT WAS REPLACED THE PREVIOUS DAY AFTER A FUEL LEAK WAS DETEC TED. 4 T E2ONE 1996101000443 19961010 00443 EA 1996 10 10 CA960205006 2 19960115 G 7230 310082903 VALVE COMP BLEED DHAV DHC6 DHC6300 EA PWA PT6 PT6A27 52043 EA DOWEL STICKING W E ENGINE SHUTDOWN O OTHER IN INSP/MAINT 1 CA 5133 PCE42076 (CAN)FOLLOWING CORRECTION OF A STARTING SNAG THE ENGINE WOULD NOT RESPOND TO THE THROTTLE BUT WOULD STAGNATE AND TEMPERA TURES WOULD CLIMB UNTIL THE FUEL WAS SHUTOFF. INVESTIGATION FOUND THAT DUE TO EXTREMECOLD WEATHER THE LUBRICANT ON THE G UIDE DOWEL OF THE COMPRESSOR SURGE BLEED VALVE WOULD NOT PERMIT IT TO OPEN AND RELIEVE THE COMPRESSOR TO PERMIT ACCELERA TION. THE EXISTING LUBRICANT WAS CLEANED FROM THE DOWEL AND FRESH LUBRICANT WAS APPLIED AND THE ENGINE OPERATED NORMALLY AFTERWARD. 1 H 7 2 3T 4 T A9EA E4EA 1996101000886 19961010 00886 EU 1996 10 10 CA960208102 1 19960129 G 5244 A5247504000600 HANDLE AIRBUS A52475000008 AIRBUS 310 A310304 EU LOWER AC DOOR WORN W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN)ON CLIMB AT 8,000 FEET DOOR WARNING OCCURRED FOR LOWER ACCESS DOORS. AS THIS WAS FIRST FLIGHT AFTER A "C" CHECK, TH E CREW ELECTED TO RETURN TO BASE. MAINTENANCE CHECK REVEALED DOOR HANDLE FOR LOWER AC CESS DOOR WAS FOUND RELEASED. AIRB US SB A310-52-2040 CORRECTS THIS PROBLEM OF INADVERTENT RELEASE. 2 L 7 2 4F RT A35EU 1996101000906 19961010 00906 EU 1996 10 10 CA960212029 1 19960202 G 2910 RELIEF VALVE AIRBUS 320 A320212 EU GE CFM56 CFM565A 13802 NE YELLOW SYS HYD LEAKING W A UNSCHED LANDING K FLUID LOSS CL CLIMB 1 CA 731350 (CAN)DURING FLIGHT, YELLOW HYDRAULIC SYSTEM LOW PRESSURE INDICATION. AIRCRAFT RETURNED TO BASE FOR MAINTENANCE. INVESTIG ATION REVEALED PRESSURE RELIEF VALVE LEAKING DUE TO DETERIORATION OF SEALS. HYDRAULIC SEALS REPLACED AND LEAK CHECKED CA RRIED OUT IN ACCORDANCE WITH MM 05-51-11. 2 L 7 2 4F 4 F RT A28NM E29NE 1999081200318 19990812 00318 EA 1999 8 12 CA960212031 2 19960202 G 8520 ROD PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA CRANKCASE BROKEN W A UNSCHED LANDING E Y J VIBRATION/BUFFET ENGINE STOPPAGE WARNING INDICATION CR CRUISE 1 CA (CAN) A CONNECTING ROD BROKE AND DAMAGED THE CRANKCASE. THE PROPELLER WAS IN FEATHER, THEREFORE,THE ROD HIT THE INSIDE OF THE ENGINE A FEW MOMENTS BEFORE THE ENGINE STOPPED TURNING. 1 L 7 2 3O 3 O A20SO E14EA 1997011600068 19970116 00068 CE 1997 1 16 CA960212032 1 19960131 G 3340 D758520 LANDING LIGHT CESSNA 500 560CESSNA 2076750 CE R/H MAIN GEAR LOW CLEARANCE W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHILE DOING DAILY INSPECTION, THE R/H OLEO EXTENSION WAS LOW AND THERE WAS VERY LITTLE CLEARANCE BETWEEN TIRE AND LIGHT. IF OLEO HAD BOTTOMED OUT, THE LIGHT WOULD HAVE PRESSED INTO THE TIRE ABOUT 1/8". THE TIRE WAS NOT NEW. THE LIGHT WAS ADJUSTED TO PROVIDE CLEARANCE FOR THE TIRE. THE LIGHTS WERE ORIGINALLY INSTALLED IN ACCORDANCE WITH SB 560-33-12. 2 L 7 2 4F RT A22CE 1996121200504 19961212 00504 NE 1996 12 12 CA960212037 2 19960205 G 7322 FCU PWA PT6 PT6A25 52043 NE DRIVE BEARING DAMAGED W A E UNSCHED LANDING ENGINE SHUTDOWN J WARNING INDICATION CR CRUISE 1 CA 2700 52110 (CAN) DURING A FLIGHT, ENGINE PARAMETERS SUDDENLY INCREASED WHILE IN CRUISE. THE ENGINE DID NOT RESPOND TO POWER LEVER I NPUTS. THE PILOT DIVERTED FLIGHT TO THE POINT OF ORIGIN AND SECURED THE ENGINE BEFORE DESCENDING. INSPECTION REVEALED A DAMAGED FUEL CONTROL UNIT GOVERNOR DRIVE BEARING. THE FUEL PUMP WAS REMOVED AND THE FCU WAS SENT FOR REPAIR. 3 T E4EA 1996121200505 19961212 00505 NE 1996 12 12 CA960212038 2 19960207 G 7250 BLADE PWA 120 PW120A NE LP TURBINE FRACTURED W K NONE B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA 120057 (CAN) IN CRUISE, THE WASHROOM SMOKE DETECTOR ALARM SOUNDED AND A SLIGHT ODOUR OF OIL IN THE CABIN WAS NOTICED. POST FLIG HT INSPECTION REVEALED A VIBRATION IN THE CONTROLS DURING ENGINE START. UPON ENGINE REMOVAL, TWO LP TURBINE BLADES WERE FOUND TO BE FRACTURED AT MID-SPAN. 4 T E20NE 1996101000915 19961010 00915 1996 10 10 CA960214008 4 19960209 G 3442 RT1401B400083101 RT UNIT BENDIX RT1401B40008 MOD BOARD BURNT W K NONE O OTHER IN INSP/MAINT 1 CA 1439 (CAN)REPAIR TO CIRCUIT BOARD FOUND TO BE LESS THAN SATISFACTORY CAUSING A SHORT AND BURN OUT IN THE MODULATOR BOARD. 1998041000454 19980410 00454 1998 4 10 CA960214009 4 19960202 G 3418 9002EN3 SWITCH BRAERO DH125 BAE125800A 1500285 EU CASE INTERNAL SHORTED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) SIGNAL SUMMING UNIT (SSU) FAIL LIGHT COMES ON INDICATING A FAULT IN THE STALL PROTECTION SYSTEM. SUBMITTER STATES THEY HAVE REPLACED THREE UNITS WITHIN THE LAST 200 HOURS. 2 L 7 2 4F RT A3EU 1996101000918 19961010 00918 1996 10 10 CA960214012 4 19960208 G 3422 6225812001 FLUX VALVE COLLINS 6225812001 BEECH 90 C90A 1152911 CE COMPASS SYS OIL SOAKED W K NONE O OTHER IN INSP/MAINT 1 CA 7551 (CAN)AIRCRAFT COMPASS SYSTEM REPORTED UNRELIABLE. EXAMINATION OF COMPASS COMPONENTS AND WIRING REVEALED THAT THE FLUX VA LVE WAS SATURATED WITH INSTRUMENT OIL. COLLINS CONFIRMED THAT THE LOSS OF OIL COULD R ESULT IN FAILURE OF THE COMPONENT. FLUX VALVE WAS REPLACED. 1 L 7 2 3T RT 3A20 1996101000924 19961010 00924 EU 1996 10 10 CA960214018 1 19960124 G 5210 FE12700002 DOOR STRIKER AIRBUS 320 A320212 EU DOOR 1R SEIZED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN)DURING INSPECTION OF THE PASSENGER DOORS ACTUATOR STRIKER MECHANISM,DOOR 1R FOUND JAMMED WITHOUT CORROSION. REF AOT 52-12. MAINTENANCE ACTION INVOLVED CLEANING AND LUBRICATION STRIKER MECHANISM. STRIKER MECHANISM FUNCTIONALLY CHECKED S EVERAL TIMES, OPERATED SATISFACTORILY. 2 L 7 2 4F RT A28NM 1996101000926 19961010 00926 SO 1996 10 10 CA960214020 1 19960205 G 2140 B3040 HEAD GASKET JANITROL B3040 PIPER PA31T PA31T 7103124 SO HEATER LEAKING W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 168 1128883 (CAN)HEATER FAILED PRESSURE DECAY TEST. INVESTIGATION FOUND THE HEAD GASKET TO BE LEAKING. REPLACED THE HEAD GASKET AND APPLIED PERMATEX #1372 AS PER JANITROL OVERHAUL MANUAL. SUBMITTER SUSPECTS THE PERMATEX SEALANT WAS LEFT OUT DURING THE LAST OVERHAUL. 1 L 7 2 3T A8EA 1996101000929 19961010 00929 CE 1996 10 10 CA960221201 1 19960102 G 2913 10138800519 MOTOR AIRIGHT 10138800519 BEECH 300 300BEECH 1152930 CE POWER PACK WEAK W A A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA 17 271 (CAN)THE AIRCRAFT WAS IN CRUISE FLIGHT WHEN THE LANDING GEAR HANDLE RED LIGHT CAME ON AND THE PILOTS OBSERVED THE GEAR B EGIN TO LOWER. INSPECTION REVEALED THAT THE HYDRAULIC POWER PACK HAD FAILED AND WAS A LLOWING THE GEAR TO DROP AS THIS A IRCRAFT DOES NOT HAVE UPLOCKS. THE 60 AMP POWER PACK BREAKER WAS RESET AND THE GEAR WAS CYCLED. THE MOTOR OF THE POWER P ACK OPERATED SLOWER THAN NORMAL AND EVENTUALLY THE 60 AMP BREAKER POPPED AGAIN. THE POWER PACK WAS REPLACED AND THE AIRC RAFT RETURNED TO SERVICE. 2 L 7 2 4T A24CE 1996102400387 19961024 00387 EU 1996 10 24 CA960222001 1 19960213 G 2432 052000 TERMINAL NUTS BRAERO DH125 HS125700A 4230170 EU GARRTT BATTERY LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA (CAN)TERMINAL NUTS ON BATTERY WERE FOUND LOOSE AFTER 20 HOURS INSTALLATION. NUTS WERE TORQUE CHECKED AND WITNESS MARKED. CHECKED NUTS AGAIN AND WERE FOUND LOOSE AGAIN. NEW NUTS WERE ORDERED AND WHEN RECEIV ED, WERE OF A DIFFERENT TYPE. 2 L 7 2 4F A3EU 1997011600075 19970116 00075 EA 1997 1 16 CA960222009 2 19960122 G 8520 9645200 BREATHER LYC O360 IO360C1E6 41514 EA ENG OIL BLOCKED W A B E UNSCHED LANDING EMER. DESCENT ENGINE SHUTDOWN K Y FLUID LOSS ENGINE STOPPAGE CL CLIMB 1 CA L1215751A (CAN) AFTER TAKEOFF, THE PILOT NOTICED THE OIL PRESSURE DROPPING ON THE RIGHT ENGINE. AS IT APPROACHED THE CAUTION ARC O N THE GAUGE, HE ELECTED TO SHUT DOWN ENGINE AND RETURN TO AIRPORT.HE THEN NOTICED LEFT ENGINE PRESSURE DROPPING AND DECL ARED AN EMERGENCY. ENGINE SEIZED AND A WHEELS UP LANDING WAS MADE SHORT OF THE RUNWAY. MAINTENANCE STAFF DETERMINED THE PROBLEM TO BE LOSS OF OIL DUE TO FROZEN ENGINE BREATHERS. 3 O 1E10 1996102400396 19961024 00396 CE 1996 10 24 CA960222017 1 19960124 G 5521 07346013 SPAR CESSNA 07346013 CESSNA 180 180 2072602 CE ELEV OUTB HINGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 3890 (CAN)THE ELEVATOR SPAR WAS FOUND CRACKED DURING THE ANNUAL 100 HOUR INSPECTION. SUBMITTER REPORTS THAT AN UNAPPROVED REP AIR WAS ALSO FOUND DURING THE REPAIR. 1 H 7 1 3O NC 5A6 1996102400397 19961024 00397 SO 1996 10 24 CA960222018 1 19960212 G 5310 225387 TUBING PIPER PA22150 PIPER PA22 PA22150 7102210 SO STRUCTURE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 2566 225387 25734 (CAN) AIRCRAFT WAS INSPECTED AND FOUND TO HAVE SEVERAL CRACKS AND CORROSION IN STRUCTURAL TUBING, AS PER SKETCH, THAT AP PEARS TO BE THE RESULT OF WATER FREEZING. SUBMITTER REPORTS THAT THE INSPECTION WOULD NOT HAVE SHOWN THESE DEFECTS WITH OUT HAVING LIFTED THE FLOOR PANELS. 1 H 7 1 3O 1A6 1996102400398 19961024 00398 NM 1996 10 24 CA960222019 1 19960208 G 3097 WIRE HARNESS DHAV DHC8 DHC8102 2809003 NM INTAKE HEAT BURNED W A UNSCHED LANDING Y ENGINE STOPPAGE CR CRUISE 1 CA (CAN)DURING FLIGHT WHEN ENTERING ICING CONDITIONS, CREW SELECTED ENGINE INTAKE BYPASS DOOR OPEN. LEFT HAND EMERGENCY FUE L SHUTOFF VALVE CLOSED AND ENGINE SHUTDOWN. INSPECTION INDICATED THAT 115 VOLT AC INTAKE HEAT WIRE HAD SHORTED ON A HARN ESS SUPPORT TRAY UNDER THE FLOOR AT PASSENGER SEAT, ROW 3. THE SHORTED WIRE HAD CAUSED A WIRE BUNDLE TO BURN. 2 H 7 2 4T RT A13NM 1996102400399 19961024 00399 1996 10 24 CA960222020 4 19960208 G 2562 11513241 SCREWS RESCU406 ELT FRAME LOOSE W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN)LOOSE SCREWS FOUND INSIDE ELT. FRAME USED DURING CONSTRUCTION HAD HELICOILS MOUNTED OFF CENTRE CAUSING INSUFFICIENT THREAD ENGAGEMENT FOR SCREWS SECURING PC BOARD. FIVE UNITS FROM AFFECTED BATCH S/N'S107 THROUGH 263 RETURNED IN THIS CO NDITION. SIL BEING RAISED TO ADDRESS ISSUE. 1996102400400 19961024 00400 1996 10 24 CA960222021 4 19960214 G 2210 82210010001 CONTROL CABLE DHAV DHC8 DHC8311 1386006 EA AUTO PILOT MISINSTALLED W A O OTHER F W FLT CONT AFFECTED INADEQUATE Q C CR CRUISE 1 CA 1864 (CAN)IN CRUISE,AT FL250,WITH AUTO PILOT ON, AIRCRAFT OSCILLATING ABOUT LATERAL AXIS,APPROX. 60 TO 80 FEET.INSPECTION FOU ND NO TENSION ON THE AUTOPILOT SERVO CABLE WHICH SHOULD BE 15 TO 20 LBS.LH ELEVATOR CONTROL CABLE TENSION WITH SERVO DIS CONNECTED WAS FOUND TO BE 35 LBS & SHOULD BE 70,PLUS OR MINUS 7 LBS.SERVO CONTROL RH CABUCKLE ATTACH TO ELEVATOR CONTROL CABLE, INCORRECTLY INSTALLED.CABUCKLE YOKE WAS FITTED TO ELEVATOR CONTROL CABLE 180 DEGREES OUT CAUSING SERVO CABLE TO BE INTERTWINED WITH ELEVATOR CONTROL CABLE.LH ELEVATOR & RH CABLE TURNBUCKLE INCORRECTLY ADJUSTED.FORWARD CABLE ATTACH T O TURNBUCKLE & AFT CABLE ATTACH TO TURNBUCKLE WERE STILL IN SAFETY BUT MISALIGNED CAUSING TWISTING OF THE AFT CABLE.AIRC 2 H 7 2 4T RT A13NM 1996102400403 19961024 00403 1996 10 24 CA960222027 4 19960209 G 2562 MN1300 BATTERY ACK E01 AMTR RWEXEC ROTORWAYEXEC GL ELT DEFECTIVE W K NONE O OTHER IN INSP/MAINT 1 CA 40 014332 (CAN)DURING ELT RECERTIFICATION CHECK A POWDERED DUST NOTICED ON CASE. UNIT FAILED TO ACTIVATE WHEN TURNED ON OR IN ARME D POSITION. ALL BATTERIES FOUND CHAFED, TWO WERE CORRODED, AND SEVERAL HAD LOW VOLTAG E. SUBMITTER SUGGESTS CAUSE IS RES ULT OF USE IN HELICOPTER WITH HIGHER VIBRATIONS. BATTERIES WERE MANUFACTURED BY DURACELL. 1 G 7 1 3O EXPA1G71 1996102400404 19961024 00404 NM 1996 10 24 CA960222028 1 19960214 G 2710 532DB PANEL DHAV DHAV DHC8 DHC8102 2809003 NM RH AND LH GOUGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN)FOUND AS A RESULT OF SD ALERT AL-95-06 BOTH LEFT HAND (P/N 532DB) AND RIGHT HAND (P/N 632DB) PANELS GOUGED FROM LOW ER JAM-SWITCH CABLE CLAMPS. 2 H 7 2 4T RT A13NM 1996102400405 19961024 00405 EA 1996 10 24 CA960222029 1 19960214 G 2710 532DB PANEL DHAV DHAV DHC8 DHC8311 1386006 EA RH AND LH GOUGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN)FOUND AS A RESULT OF SD ALERT AL-95-06, BOTH LEFT (P/N 532DB) AND RIGHT (P/N 632DB) PANEL GOUGED FROM LOWER JAM-SWI TCH CABLE CLAMPS. 2 H 7 2 4T RT A13NM 1996102400406 19961024 00406 EA 1996 10 24 CA960222030 1 19960214 G 2710 532DB PANELS DHAV DHAV DHC8 DHC8311 1386006 EA RH AND LH GOUGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN)FOUND AS A RESULT OF SD ALERT AL-95-06, BOTH LEFT (P/N 532DB) AND RIGHT (P/N 632DB) PANELS GOUGED FROM LOWER JAM-SW ITCH CABLE CLAMPS. 2 H 7 2 4T RT A13NM 1996102400407 19961024 00407 EA 1996 10 24 CA960222031 1 19960214 G 2710 632DB PANEL DHAV DHAV DHC8 DHC8311 1386006 EA RIGHT HAND GOUGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN)FOUND AS A RESULT OF SD ALERT AL-95-06 RIGHT HAND PANEL GOUGED FROM LOWER JAM-SWITCH CABLE CLAMPS. 2 H 7 2 4T RT A13NM 1996102400408 19961024 00408 EA 1996 10 24 CA960222032 1 19960214 G 2710 532DB PANELS DHAV DHAV DHC8 DHC8311 1386006 EA LH AND RH GOUGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN)FOUND AS A RESULT OF SD ALERT AL-95-06 BOTH LEFT HAND (P/N 532DB) AND RIGHT HAND (P/N 632DB) PANELS GOUDED FROM LOW ER JAM-SWITCH CABLE CLAMPS. 2 H 7 2 4T RT A13NM 1996102400409 19961024 00409 EA 1996 10 24 CA960222033 1 19960214 G 2710 532DB PANELS DHAV DHAV DHC8 DHC8311 1386006 EA RH AND LH GOUGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN)FOUND AS A RESULT OF SD ALERT AL-95-06 BOTH LEFT HAND (P/N 532DB) AND RIGHT HAND (P/N 632DB) PANELS GOUGED FROM LOW ER JAM-SWITCH CABLE CLAMPS. 2 H 7 2 4T RT A13NM 1996102400410 19961024 00410 EA 1996 10 24 CA960222034 1 19960214 G 2710 632DB PANEL DHAV DHAV DHC8 DHC8311 1386006 EA RIGHT HAND GOUGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN)FOUND AS A RESULT OF SD ALERT AL-95-06 RIGHT HAND PANEL GOUGED FROM LOWER JAM-SWITCH CABLE CLAMP. 2 H 7 2 4T RT A13NM 1996102400411 19961024 00411 EA 1996 10 24 CA960222035 1 19960214 G 2710 532DB PANELS DHAV DHAV DHC8 DHC8311 1386006 EA RH AND LH GOUGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN)FOUND AS A RESULT OF SD ALERT AL-95-06 BOTH LEFT HAND (P/N 532DB) AND RIGHT HAND (P/N 632DB) PANELS GOUGED FROM LOW ER JAM-SWITCH CABLE CLAMPS. 2 H 7 2 4T RT A13NM 1996102400412 19961024 00412 EA 1996 10 24 CA960222036 1 19960214 G 2710 632DB PANEL DHAV DHAV DHC8 DHC8311 1386006 EA RIGHT HAND GOUGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN)FOUND AS A RESULT OF SD ALERT AL-95-06 RIGHT HAND PANEL GOUGED FROM LOWER JAM-SWITCH CABLE CLAMP. 2 H 7 2 4T RT A13NM 1996102400413 19961024 00413 EA 1996 10 24 CA960222037 1 19960214 G 2710 632DB PANEL DHAV DHAV DHC8 DHC8311 1386006 EA RIGHT HAND GOUGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN)FOUND AS A RESULT OF SD ALERT AL-95-O6 RIGHT HAND PANEL GOUGED FROM LOWER JAM-SWITCH CABLE CLAMP. 2 H 7 2 4T RT A13NM 1996102400414 19961024 00414 EA 1996 10 24 CA960222038 1 19960214 G 2710 532DB PANELS DHAV DHAV DHC8 DHC8311 1386006 EA RH AND LH GOUGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN)FOUND AS A RESULT OF SD ALERT AL-95-06 BOTH LEFT HAND (P/N 532DB) AND RIGHT HAND (P/N 632DB) PANELS GOUGED FROM LOW ER JAM-SWITCH CLAMPS. 2 H 7 2 4T RT A13NM 1997011600077 19970116 00077 SO 1997 1 16 CA960222201 2 19960329 G 8520 MAIN BEARING CESSNA 340 340A 2076405 CE CONT O520 TSIO520N 17040 SO MCAULY 3AF32C 3AF32C93 GL #2 BEARING FRETTED W A UNSCHED LANDING E Y VIBRATION/BUFFET ENGINE STOPPAGE CR CRUISE 1 CA 228430R 890661 (CAN) DURING CRUISE ENGINE STARTED TO VIBRATE AND THEN STOPPED. AIRCRAFT RETURNED TO ORIGIN AND LANDED SAFELY. IT WAS DI SCOVERED THAT ENGINE HAD STOPPED DUE TO #2 MAIN BEARING FAILURE. TEARDOWN REVEALED THAT THE #2 BEARING HAD TURNED IN THE CRANKCASE STOPPING THE OIL FROM FLOWING TO THE NUMBER 2 CONNECTING ROD. THE CONNECTING ROD THEN FAILED AND DAMAGED THE CRANKCASE, CAMSHAFT AND CYLINDERS. THIS CAUSED THE ENGINE TO QUIT RUNNING. 1 L 7 2 3O 3 O 3A25 E8CE 5 C P22EA 1996102400418 19961024 00418 1996 10 24 CA960223003 4 19960201 G 2312 TH4502NNNB COM CONTROL HUGHES 500N 500N 3027374 SW COCKPIT FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 1825 (CAN)TAC/COM CONTROL HEAD HAD BEEN CHECKED TWICE FOR COMPLAINTS, BUT NO FAULT FOUND. SNAGS INCLUDED INTERMITTENT RESPONS E TO MOMENTARY SWITCHES OF 'CHANNEL SELECT' AND 'RADIO NEXT', AND ALSO UNIT WOULD IND ICATE RECEPTION WHEN NO AUDIO COUL D BE HEARD. BOTH SNAGS VERIFIED IN A HELICOPTER WITH AN IFR 2000 COMM ANALYZER. BOTH SNAGS VERIFIED WITH AT LEAST ONE RH IN SCAN MODE. SUBMITTER SUGGESTS A DEFICIENCY IN MANUFACTURE TEST PROCEDURES. UNIT RETURNED TO MANUFACTURER. 1 G 7 1 3U NC H3WE 1996102400419 19961024 00419 NM 1996 10 24 CA960223004 1 19960216 G 2435 03600923 BEARING LUCAS 23088002A DHAV DHC8 DHC8* NM START/GEN FAILED W K NONE O OTHER NR NOT REPORTED 1 CA 1447 353 (CAN)BEARING FAILURE ON STARTER-GENERATOR CAUSED DAMAGE TO ROTOR, STATOR, SPEED P/U AND FAN. 2 H 7 2 4T RT A13NM 1997011600079 19970116 00079 CE 1997 1 16 CA960223009 1 19960215 G 7120 160128 MOUNT CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL ENG BULKHEAD CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 4071 (CAN) CORROSION WAS DETECTED ON BOTH ENGINE MOUNTS AND BOTH ENGINES WERE REMOVED TO EFFECT APPROVED REPAIR UNDER RDA AUT HORITY. DURING RE-RIVETING OF ASSEMBLY, IT BROKE IN TWO DUE TO THE CORROSION. IT WAS STATED THAT OVER 50 PERCENT OF THE STRUCTURE INTEGRITY HAD BEEN COMPROMISED. AFTER FURTHER INVESTIGATION, IT WAS DISCOVERED THAT AD 75-23-08R5 HAD NOT BEEN FULLY COMPLIED WITH. 1 L 7 2 3O RT A7CE 5 C P22EA 1997011600080 19970116 00080 EA 1997 1 16 CA960223012 2 19960216 G 8540 72245 SUPPORT ASSEMBLY PIPER PA32 PA32300 7103212 SO LYC O540 IO540K1A5 41532 EA RING GEAR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 1206 L1001548 (CAN) RING GEAR SUPPORT ASSEMBLY HAD A CIRCUMFERENTIAL CRACK APPROXIMATELY 16" LONG. 1 L 7 1 3O 3 O A3SO 1E4 1997011600081 19970116 00081 1997 1 16 CA960223016 4 19960215 G 2210 AUTO TRIM SYS CESSNA 500 560CESSNA 2076750 CE AUTO PILOT FAULTY W H DEACTIVATE SYST/CIRCUITS F FLT CONT AFFECTED CR CRUISE 1 CA (CAN) WHILE FLYING WITH AUTO PILOT ENGAGED, THE AUTO-TRIM SYSTEM (MISS-TRIM) LIGHT COMES ON AND THE SYSTEM IS UNABLE TO CORRECT THIS SITUATION THUS DISENGAGES THE AUTOPILOT AFTER A SHORT PERIOD OF TIME. CESSNA HAS BEEN MADE AWARE OF THE PRO BLEM AND STATES THERE SHOULD BE A FIX AVAILABLE SOON. THIS PROBLEM ONLY HAPENS AT HIGH SPEED CRUISE AND/OR AT THE TOP EN D OF A CLIMB. 2 L 7 2 4F RT A22CE 1997011600087 19970116 00087 EU 1997 1 16 CA960227009 1 19960103 G 3213 AXLE BARREL BRAERO DH125 BAE125800A 1500285 EU R/H MAIN GEAR CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 2466 (CAN) DURING A SEAL REPLACEMENT, IT WAS DISCOVERED THAT THERE WAS CORROSION BEYOND LIMITS ON THE UPPER MATING SURFACE. I T IS LOCATED AT THE AREA WHERE THE OLEO STRUT SLIPS INTO THE AXLE BARREL AND CONTACTS IN TWO LOCATIONS. THIS IS SEALED A T THE FACTORY AND WOULD NOT HAVE BEEN DISCOVERED UNTIL THE 4500 HOUR INTERVAL FOR OVERHAUL. 2 L 7 2 4F RT A3EU 1997011600091 19970116 00091 WP 1997 1 16 CA960227014 2 19960213 G 7261 OIL SYSTEM GARRTT TFE731 TFE7313 01518 WP LT ENG DEPLETED W E A ENGINE SHUTDOWN UNSCHED LANDING J K WARNING INDICATION FLUID LOSS CR CRUISE 1 CA 5076 P90279 (CAN) L/H OIL PRESSURE DROPPED AND L/H LOW OIL PRESSURE LIGHT CAME ON. ENGINE SHUT DOWN, AND AIRCRAFT LANDED. FOUND LOW ER COWL AND ENGINE SOAKED WITH OIL AND OIL TANK EMPTY. NO EVIDENCE OF OIL IN JET PIPE OR BYPASS DUCT. ENGINE AND COWL WA SHED DOWN, AND OIL TANK TOPPED UP. AIR/OIL BREATHER REPLACED, ENGINE RUN-UP AND TEST FLIGHT CARRIED OUT WITH NO FAULT FO UND, OIL CONSUMPTION NORMAL. 4 F E6WE 1997011600093 19970116 00093 SO 1997 1 16 CA960227024 1 19960220 G 2150 643368 BALL BEARING PIPER PA46 PA46310P 7104605 SO CONT O520 TSIO520BE 17040 SO IDLER PULLEY DISINTEGRATED W A K NONE O OTHER IN INSP/MAINT 1 CA 2471 2471 273625R (CAN) WHILE PERFORMING ENGINE MAINTENANCE, IT WAS NOTICED THAT THE AIR CONDITIONING IDLER SHEAVE (PULLEY) WAS NOT ALIGNE D WITH THE COMPRESSOR PUMP SHEAVE AS IS NORMALLY THE CASE. FURTHER INVESTIGATION WARRANTED DISASSEMBLY, AND IT WAS FOUND THAT THE IDLER SHEAVE BEARING HAD COMPLETELY DISINTEGRATED. SUBSEQUENT LOADS IMPOSED ON THE SHEAVE RESULTED IN WEAR ON THE ASSOCIATED PARTS AND HARDWARE REQUIRING THEIR REPLACEMENT. 1 L 7 1 3O 3 O A25SO E8CE 1996110100003 19961101 00003 SO 1996 11 1 CA960229202 1 19960218 G 3220 NLG SCISSORS PIPER PA34 PA34200T 7103406 SO CONT NOSE GEAR UNFASTENED W A UNSCHED LANDING O OTHER LD LANDING 1 CA (CAN)THE NOSE GEAR WOULD NOT EXTEND WHEN SELECTED. AIRCRAFT MADE A NOSE GEAR UP LANDING. INVESTIGATION FOUND THAT THE NO SE GEAR WAS UNFASTENED TO FACILITATE EASIER GROUND HANDLING AND THE BOLT WAS REPLACED INCORRECTLY THUS ALLOWING THE NOSE WHEEL TO TWIST AND PROBABLY JAM IN THE WHEEL WELL. 1 L 7 2 3O A7SO 1997012200002 19970122 00002 EA 1997 1 22 CA960304004 1 19960213 G 2810 FUEL FLEET 80 FLEET80 EA CONT C85 C8512F 17008 SO FUEL TANK/CARB CONTAMINATED W K NONE E R Y VIBRATION/BUFFET PARTIAL RPM/PWR LOSS ENGINE STOPPAGE AP APPROACH 1 CA 23500612 (CAN) DURING FINAL APPROACH, ENGINE STARTED TO RUN ROUGH, BUT WORKING THROTTLES SEEMED TO FIX PROBLEM. ON SHORT FINAL, E NGINE QUIT AND THEN PROPELLER STOPPED. GLIDE INITIATED BUT LANDED SHORT IN A SHED. INVESTIGATION REVEALED THAT FUEL LINE FROM STRAINER HAD BROKEN ON IMPACT, AND WATER AND CONTAMINATIONS WERE FOUND IN REMAINING 1.5 GALLONS OF FUEL. ENGINE ST OPPAGE MAY HAVE BEEN DUE TO CARB ICE AND FUEL STARVATION. 1 H 7 1 3O 3 O 788 E233 1997011600100 19970116 00100 NE 1997 1 16 CA960304005 1 19960210 G 2913 66WA400 PUMP SKRSKY S64 S64E 8142604 NE 1ST STG HYD PUMP MAKING METAL W A O UNSCHED LANDING OTHER F FLT CONT AFFECTED EX EXTERNAL LOAD 1 CA 52 (CAN) DURING HOVER AFTER 18 MINUTES OF FLIGHT, THIS LOGGING HELICOPTER DEVELOPED A STIFFNESS OF CYCLIC AND THEN COLLECTI VE PITCH. SLINGING WAS ABORTED AND PRECAUTIONARY LANDING WAS CARRIED OUT. AFTER FURTHER INVESTIGATION, IT WAS DISCOVERED THAT THERE WAS METALLIC MATERIAL IN THE FIRST STAGE HYDRAULIC PUMP AND SUBSEQUENT DOWNLINE SYSTEM INCLUDING AFT SERVO B ANK. CONSEQUENTLY, AFCS SERVO AND ALL COMPONENTS OF THE FIRST STAGE HYDRAULIC SYSTEM WERE REPLACED. THE AIRCRAFT WAS THE N GROUND AND FLIGHT TESTED. 2 G 7 2 4U H4EA 1997011600104 19970116 00104 CE 1997 1 16 CA960304011 1 19960213 G 3040 DEICE TANK CESSNA 414 414 2075908 CE CONT O520 TSIO520J 17040 SO MCAULY 3AF32C 3AF32C93 GL VENT LINE WELD CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 503204 871603 (CAN) 1 INCH CRACK AT WELDMENT OF VENT LINE AND LOWER SECTION TANK SKIN. AREA APPEARS CORRODED AND VENT LINE SECTION BEL OW TANK APPEARS TO HAVE HAD AN IMPACT. 1 L 7 2 3O 3 O RT A7CE E8CE 5 C P22EA 1996110100006 19961101 00006 SO 1996 11 1 CA960304012 1 19960217 G 3243 MASTER CYLINDER PIPER PIPER PA31T PA31T 7103124 SO PWA BRAKE FROZEN WATER W K NONE O OTHER TX TAXI/GRND HDL 1 CA 546 (CAN) BRAKE REPORTED TO NOT BE CAPABLE OF HOLDING THE AIRCRAFT. INVESTIGATION FOUND THAT THE AIRCRAFT HAD BEEN STORED OU TSIDE DURING FREEZING TEMPS AND THAT AN AMOUNT OF WATER HAD FROZEN IN THE MASTER CYLINDER THUS DEGRADING BRAKING PERFORM ANCE. THE MASTER CYLINDER AND BRAKES WERE BLED AND THE AIRCRAFT RETURNED TO SERVICE. 1 L 7 2 3T A8EA 1997011600105 19970116 00105 SO 1997 1 16 CA960305201 1 19960229 G 7810 646463181 EXHAUST TEE PIPER PA46 PA46310P 7104605 SO CONT O520 TSIO520B 17040 SO MOUNT BOSS AREA CRACKED W A UNSCHED LANDING O OTHER CR CRUISE 1 CA 252 802510 (CAN) EXTENSIVE CRACKING OF THIS EXHAUST COMPONENT CAUSED A LOSS OF MANIFOLD PRESSURE DUE TO TURBOCHARGER INACTIVITY. TH E LEFT REAR ENGINE ISOLATOR RECEIVED HEAT DAMAGE AS WELL. INITIAL METALURGICAL TESTS INDICATE STRESS CRACKING LIKELY CAU SED BY INSTALLATION PRELOAD. 1 L 7 1 3O 3 O A25SO E8CE 1996110100013 19961101 00013 NM 1996 11 1 CA960306014 1 19960228 G 5755 532DB PANEL DHAV DHAV DHC8 DHC8* NM SPOILER QUADRANT CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN)INSPECTION AS A RESULT OF SERVICE DIFFICULTY ALERT AL-95-06 FOUND ROLL SPOILER PANELS BOTH LEFT HAND AND RIGHT HAND (632DB) GROOVED FROM THE WIRE BUNDLE ON THE ROLL SPOILER QUADRANT. NO CONTROL PROBLE MS FOUND. SB 8-27-80V IS BEING USE D TO REPAIR. SB STILL UNDER REVIEW. 2 H 7 2 4T RT A13NM 1996110100015 19961101 00015 CE 1996 11 1 CA960306016 1 19960223 G 3246 AN770A BOLT EDO 249A2870 CESSNA 180 180G 2072616 CE MCAULY FLOATS CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 619620 (CAN) AFTER ROUTINE CHANGE OVER FROM FLOATS TO SKIS, A FLOAT BOLT WAS CHECKED FOR ITS CONDITION. IT WAS FOUND TO BE CORR ODED TO THE POINT WHERE REPLACEMENT WAS DEEMED TO BE NECESSARY. FUTHER INVESTIGATION FOUND SPREADER BAR BOLTS AND LOWER LIFT STRUT BOLTS CORRODED BEYOND ACCEPTABLE LIMITS. ALL WERE REPLACED WITH NEW HARDWARE. 1 H 7 1 3O 5A6 1996110100021 19961101 00021 EA 1996 11 1 CA960311008 1 19960229 G 7600 C6CEM14323 QUADRANT DHAV DHAV DHC6 DHC6 2802606 EA COCKPIT WARPED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN)NEW QUADRANT BEING INSTALLED TO SATISFY CF-73-06R2. AT INSTALLATION IT WAS FOUND DISTORTED AT THE LOWER FORWARD END . NO INTERFERENCE NOTED, BUT QUADRANT WAS NOT USED. MARKS ON QUADRANT. MELT 950556 AND 12215/0. 1 H 7 2 3T RT A9EA 1996110100024 19961101 00024 EA 1996 11 1 CA960311011 1 19960303 G 7830 22850201481 TORQUE BOX CNDAIR CL600 CL6002B19 EA LH NACELLE TR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 5217 (CAN)FORWARD FRAME INBOARD FLANGE OF TORQUE BOX FOUND CRACKED AT RADIUS AND A PIECE IS MISSING. CAUSE UNKNOWN. 2 L 7 2 4F RT A21EA 1996110100033 19961101 00033 CE 1996 11 1 CA960311022 1 19960301 G 3242 16404700 BRAKE DISC CLEVELAND 4074A CESSNA 206 TU206G 2073357 CE CONT O520 TSIO520M 17040 SO BOLT HOLES CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 713 520066 (CAN)WHILE CARRYING OUT AN INSPECTION ON A FLOAT AIRCRAFT, WHEEL REMOVED. AXLE REMOVED TO SERVICE BEARINGS AND REPLACE B RAKE DISC AND THEN FOUND CRACKS ALONG THE BOLT HOLES. ALL THREE HOLE WERE FOUND CRACK ED. 1 H 7 1 3O 3 O A4CE E8CE 1997011600121 19970116 00121 EA 1997 1 16 CA960311034 1 19960301 G 7930 601600143 TUBE ASSEMBLY CNDAIR CL600 CL6002B16 1900305 EA RT ENG LOOSE W A E UNSCHED LANDING ENGINE SHUTDOWN J K WARNING INDICATION FLUID LOSS CR CRUISE 1 CA 2113 (CAN) AFTER 5 MINUTES IN CRUISE AT FL350, R/H ENGINE OIL PRESSURE SLOWLY DECREASED FROM 85 TO 25 PSI. WHEN RED WARNING L IGHT BLINKED, ENGINE SHUT DOWN. CHECKED AND SECURED OIL TUBE BETWEEN OIL PRESSURE TRANSMITTER AND 'B' SUMP SYSTEM. HIGH POWER RUN CARRIED OUT, NO LEAK FOUND, RESERVOIR TOPPED UP. 2 L 7 2 4F RT A21EA 1997011600122 19970116 00122 NE 1997 1 16 CA960311035 2 19960224 G 7200 ENGINE LKHEED 1011 10113851 5265010 WP RROYCE RB211 RB21122B02 54555 NE NR 2 MAKING METAL W A E ENGINE SHUTDOWN J WARNING INDICATION CL CLIMB 1 CA 39223 2262 10256 (CAN) DURING CLIMB, VIBRATION INCREASED STEADILY. ENGINE SHUT DOWN AND AIRCRAFT RETURNED TO AIRPORT. FOUND HEAVY METAL C ONTAMINATION FROM LOCATION BEARINGS (MAGNETIC CHIP DETECTOR). #2 ENGINE REPLACED AND CHECKED SERVICEABLE. 2 L 7 3 4F 4 F A23WE E12EU 1997011600126 19970116 00126 EU 1997 1 16 CA960312021 1 19960208 G 4950 B-NUT SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1B 6OO30 NE APU GAS GEN VENT LOOSE W A D UNSCHED LANDING RETURN TO BLOCK E O VIBRATION/BUFFET OTHER CL CLIMB 1 CA 875 (CAN) APPROXIMATELY 1 MINUTE AFTER TAKEOFF, A POP WAS HEARD. AIRCRAFT LANDED BACK AT STAGING AREA. INVESTIGATION REVEALE D GAS GENERATOR VENT LINE HAD COME UNDONE AT THE 'B' NUT. NUT WAS RE-INSTALLED AND TORQUED. GROUND RUN SUCCESSFULLY. AIR CRAFT RETURNED TO SERVICE. 1 G 7 1 3U 3 U NC H9EU E19EU 1996110100384 19961101 00384 EU 1996 11 1 CA960313009 1 19960302 G 2910 201042056 LINE AIRBUS 320 A320212 EU GE LH ANTI SKID HY RUPTURED W H DEACTIVATE SYST/CIRCUITS K FLUID LOSS LD LANDING 1 CA (CAN)LOSS OF GREEN HYDRAULIC SYSTM DURING FLIGHT. LOSS WAS CAUSED BY RUPTURED HYDRAULIC LINE ON LEFT ANTI-SKID MODULE. D EFECTIVE LINE REPLACED AND SYSTEM CHECKED FOR LEAKS. 2 L 7 2 4F RT A28NM 1996110100386 19961101 00386 EU 1996 11 1 CA960313011 1 19960222 G 3246 AGA1481 HUB DUNLOP AHA1489 BAG BAE146 BAE146200A 1500266 EU MLG WHEEL CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 5242 KJ217 (CAN)2 CRACKS APPROXIMATELY 1 INCH LONG FOUND ORIGINATING FROM LIGHTENING HOLES. 2 H 7 4 4F RT A49EU 1996110100405 19961101 00405 SO 1996 11 1 CA960315021 1 19960305 G 3220 8361802 TRUNNION PIPER PA46 PA46310P 7104605 SO CONT LEFT HAND FORK CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 2471 (CAN)A FULL PENETRATION CRACK, 5 CM IN LENGTH, WAS FOUND ON THE NOSE TRUNNION AS INDICATED. REPLACEMENT PART WAS P/N 836 06-07 AND TRUNNION KIT P/N 766-211. 1 L 7 1 3O A25SO 1996110100411 19961101 00411 SW 1996 11 1 CA960320001 1 19960215 G 5740 BOLT BLANCA BBAVIA 7 7GCBC 1220601 SW LYC WING ATTACH CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 3175 (CAN)DURING SPAR REPLACEMENT ON THE WING, ALL BOLTS WERE FOUND TO BE CORRODING WHERE THEY CONTACT THE WOOD. THE HEAD AND THREAD OF THE BOLTS WAS FOUND TO BE CLEAN AND BRIGHT BUT THE SHANK OF THE BOLT IN TH E WOOD SHOWS SERIOUS CORROSION. 1 H 7 1 3O NC A759 1996110100413 19961101 00413 SW 1996 11 1 CA960320003 1 19960215 G 5711 SPAR BLANCA 7GCBC BBAVIA 7 7GCBC 1220601 SW LYC L/H WING CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 3175 (CAN)SUBJECT SPAR INDICATED IRREGULAR LINES ACROSS THE GRAIN AT 14 INCHES AND 92 INCHES FROM THE ROOT END, BOTH FORE AND AFT FACES. REFERENCE MATERIAL ENCYCLOPEDIA OF WOOD CHAPTER 4, FIG.4-32 AND FIG.4-8A.SUBMITTER EXPLAINS HE HAS SEEN THIS BEFORE AND HAS SUBMITTED ANOTHER SDR #951027007, 19 OCTOBER 1995. 1 H 7 1 3O NC A759 1996110100418 19961101 00418 SO 1996 11 1 CA960320013 1 19960314 G 3230 67189000 LINE PIPER 67189000 PIPER PA28 PA28R200 7102811 SO LYC GEAR DOWN CORRODED/FAILED W O OTHER K FLUID LOSS LD LANDING 1 CA 3700 (CAN)PILOT HAD TO ACTIVATE THE EMERGENCY EXTENSION SINCE THE NORMAL GEAR DOWN SELECTION WAS INOPERATIVE. INVESTIGATION R EVEALED THAT THE HYDRAULIC LINE HAD FAILED. THE LOCATION OF THE FAILED LINE IS UNDER THE RIGHT CORNER OF THE WINDSHIELD AND CORROSION FOLLOWED BY FAILURE ON THE LINE WAS CAUSED BY TRAPPED MOISTURE IN THE INSULATION. SUBMITTER STATES THAT T HIS PROBLEM HAS BEEN SEEN BEFORE. 1 L 7 1 3O 2A13 1996110100422 19961101 00422 WP 1996 11 1 CA960320019 1 19960306 G 3260 24085571018 LEVER CVAC 440 440 2422902 WP NLG DOWNLOCK CRACKED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN)AFTER TAKEOFF THE NOSE LANDING GEAR REFUSED TO RETRACT. CONFIRMED BY TOWER AND AIRCRAFT LANDED. BROKEN DOWNLOCK LEV ER DUE TO MISADJUSTED DOWN LOCK MICROSWITCH. LEVER REPLACED AND SWITCH ADJUSTED. 2 L 7 2 4R 6A6 1996110100428 19961101 00428 SO 1996 11 1 CA960320026 1 19960314 G 3230 6714600 UPPER DRAG LINK PIPER PIPER PA28 PA28R200 7102811 SO LYC MOUNT ATTACHMENT WORN W K NONE J N W WARNING INDICATION FALSE WARNING INADEQUATE Q C IN INSP/MAINT 1 CA 3700 (CAN) IT WAS NOTED THAT THE NOSE GEAR LIGHT WAS EITHER SLOW TO ACTIVATE OR WOULD NOT ACTIVATE AT ALL. INVESTIGATION FOUN D THAT THERE WAS SO MUCH PLAY IN THE UPPER BEARING AREA OF THE DRAG LINK THAT THE NOSE GEAR LIMIT SWITCH COULD BE ACTIVA TED/DEACTIVATED JUST BY MOVING THE NOSE GEAR BY HAND. INSPECTION FOUND THAT THE BOLTS WASHERS AND BUSHINGS HAD BEEN INST ALLED INCORRECTLY AND THE BEARING WAS NOT THE CORRECT PART NUMBER. THIS COMBINATION OF PROBLEMS CAUSED THE HOLE TO ELONG ATE AND THE DRAG LINK TO BE SCRAPPED. 1 L 7 1 3O 2A13 1996110700230 19961107 00230 EA 1996 11 7 CA960325003 1 19960312 G 3213 17135 CAP END ROTOL 601R8500151 CNDAIR CL600 CL6002B19 EA LH MLG STRUT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 2485 0241B1C (CAN)SHOCK STRUT UPPER AND LOWER ATTACHMENT LUGS PIN PISTON CAP ENDS CRACKED AND EARS TORN OFF. ON DISASSEMBLY LOWER PIN PISTON WAS FOUND CRACKED. 2 L 7 2 4F RT A21EA 1996110700254 19961107 00254 EU 1996 11 7 CA960327016 1 19960305 G 3230 TARGETS AIRBUS 320 A320212 EU NOSE LDG WELL LOOSE W O OTHER J O WARNING INDICATION OTHER CL CLIMB 1 CA (CAN)LANDING GEAR SELECTED UP ON CLIMB DEPARTURE, ECAM MESSAGE WARNING INDICATED NOSE GEAR NOT UPLOCKED, NOSE LDG REMAIN ED EXTENDED. LANDING GEAR SELECTED DOWN, BOTH MAIN LANDING GEAR REMAINED RETRACTED. L ANDING GEAR THEN SELECTED UP AND N ORMAL OPERATION OCCURRED. THE FOLLOWING MAINTENANCE ACTION TOOK PLACE, NOSE LANDING GEAR SENSORS INSPECTED SATISFACTORIL Y, TARGETS (GAPS) CHECKED: 24GA ADJUSTED AND TARGETS 36GA AND 38GA FOUND LOOSE AND WERE SECURED. 2 L 7 2 4F RT A28NM 1997011600139 19970116 00139 1997 1 16 CA960328001 4 19960318 G 3416 152734 SUPPORT RING BRAERO DH125 HS125700A 4230170 EU LOCATING SLOT MODIFIED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) SUPPORT RING HAD BEEN MODIFIED AS DESCRIBED IN SERVICE ALERT AV-93-07R1 14 OCTOBER 1993. 2 L 7 2 4F A3EU 1996110700261 19961107 00261 NM 1996 11 7 CA960328006 1 19960318 G 3240 MS2125006008 BOLT DHAV DHC8 DHC8* NM BRAKE OUT OF SPEC W K NONE O OTHER IN INSP/MAINT 1 CA (CAN)DURING ASSEMBLY OF DHC8 BRAKE UNIT BOLTS P/N MS21250-06008 WERE REPLACED WITH NEW STOCK. ON TORQUING BOLTS TO CORRE CT SPEC. IN ACCORDANCE WITH BF GOODRICH MAINTENANCE MANUAL.BOLTS WERE NOTED TO BE STRETCHING. BOLTS HAD STRETCHED .024 I NCHES AND DEFINITE NECKING OF THE THREADED SECTION HAD OCCURRED. BOLTS ALL FROM ONE BATCH. ALL THESE BOLTS REMOVED FROM STOCK FOR A TOTAL OF 50. 2 H 7 2 4T RT A13NM 1996111400264 19961114 00264 EA 1996 11 14 CA960409024 2 19960208 G 7261 3022375 SEAL DHAV DHC6 DHC6300 EA PWA PT6 PT6A27 52043 EA R/H ENGINE LEAKING W E A ENGINE SHUTDOWN UNSCHED LANDING K FLUID LOSS CL CLIMB 1 CA 261 PCE42076 (CAN) DURING CLIMB, THE R/H ENGINE OIL PRESSURE WAS NOTED TO BEGIN FLUCTUATING. THE ENGINE TORQUE STARTED TO FLUCTUATE A ND AS A RESULT, THE CREW SHUT DOWN THE ENGINE AND RETURNED TO AIRPORT. MAINTENANCE FOUND THAT THE OIL WAS LEAVING THE EN GINE FROM THE ENGINE DRIVEN FUEL PUMP DRIVE SEAL. WHEN THE SEAL CARRIER WAS REMOVED, THE SEAL WAS FOUND TO HAVE MIGRATED FROM THE CARRIER. A NEW SEAL WAS INSTALLED IN THE CARRIER AND THE ENGINE AND AIRCRAFT WERE RETURNED TO SERVICE. 1 H 7 2 3T 4 T A9EA E4EA 1996111400265 19961114 00265 NM 1996 11 14 CA960409025 1 19960321 G 3240 65179783 VALVE SWIVEL BOEING 727 727171C 1384057 NM BRAKE RT MLG LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 904 (CAN)RH MAIN GEAR BRAKE SWIVEL VALVE LEAKING UNDER PRESSURE. REPLACED. 2 L 7 3 4F A3WE 1997031100005 19970311 00005 GL 1997 3 11 CA960412006 2 19960402 G 7250 23031938 NOZZLE ALLSN 250C 250C20 03013 GL TURB 2ND STAGE CRACKED W A B E UNSCHED LANDING EMER. DESCENT ENGINE SHUTDOWN J Y WARNING INDICATION ENGINE STOPPAGE HO HOVERING 1 CA 3302 CAT15239 (CAN) FORCED LANDING DUE TO ENGINE FAILURE. TEARDOWN REVEALED 2ND STAGE TURBINE NOZZLE CRACKED AROUND THE INSIDE CIRCUMF ERENCE. SPECIFICALLY THEY WERE IN THE BEND RADIUS OF THE 2ND STAGE NOZZLE DIAPHRAGM. THESE NOZZLES HAVE BEEN SENT TO COM PANY FOR ANALYSIS. 3 U E4CE 1996111400280 19961114 00280 EU 1996 11 14 CA960412017 1 19960402 G 5320 15S53572604204 STRAP AEROSP AEROSP ATR42 ATR42300 8680920 EU PWA 120 PW120 NE LH MLG WELL CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 17306 (CAN)DURING AIRCRAFT BLOCK CHECK THE STRAP USED TO REINFORCE THE MAIN LANDING GEAR WHEEL WELL WAS FOUND CRACKED. THIS ON E ON THE LEFT SIDE. OPERATOR NOTES THAT THEY HAVE SSEN THIS BEFORE. 2 H 7 2 4T 4 T RT A53EU E20NE 1996111400292 19961114 00292 EA 1996 11 14 CA960415008 2 19960411 G 7414 1051324 IMPULSE SPRING BENDIX D4LN2021 CESSNA 177 177RG 2073709 CE LYC O360 IO360A1B6 41514 EA DUAL MAG BROKEN W A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CL CLIMB 1 CA 2295 758 3437 L13680 (CAN)ON CLIMBOUT, ENGINE RPM DROPPED TO IDLE. EXAMINATION REVEALED THE DUAL MAGNETO IMPULSE SPRING BROKEN. AWD 78-09-07 NOT COMPLIED WITH. 1 H 7 1 3O 3 O A20CE 1E10 1996111400297 19961114 00297 1996 11 14 CA960415017 4 19960415 G 3416 804710DH STOPS AEROMECH 804710DH ALTIMETER MISRIGGED W K NONE L NO TEST IN INSP/MAINT 1 CA 8388 (CAN) ALTIMETER FAILED BENCH TEST AS PER SERVICE DIFFICULTY ADVISORY AV-93-07R1, NO STOPS ON BAROMETRIC KNOBVERY LITTLE RESISTANCE FELT AT 30 90 & DID NOT STOP AND WENT PAST 31 50 IT DID THE SAME ON THE BOTTOM END GOING PAST 28.10. 1996121200533 19961212 00533 CE 1996 12 12 CA960418010 1 19960305 G 7603 5052456849 CONTROL LEVER BEECH 5052456849 BEECH 100 100BEECH 1152916 CE PWA PT6 PT6A28 EA AT PEDESTAL GROOVED W K NONE O OTHER IN INSP/MAINT 1 CA 12050 PCE52489 (CAN) WHILE INSPECTING OF THE THROTTLE LEVER PEDESTAL A GROOVE WAS FOUND TO HAVE BEEN WORN BY RUBBING THE CATCH PLATE. S IMILAR CONDITION FOUND ON BOTH THE RIGHT AND LEFT CONTROL LEVERS. SUBMITTER STATES THAT BEECH NOW MAKES THE PLATES OF A SOFTER MATERIAL AND RECOMMENDS INSPECTING THIS AREA CLOSELY. 1 L 7 2 3T 4 T A14CE E4EA 1996111400621 19961114 00621 NE 1996 11 14 CA960418016 2 19960325 G 7250 214112605 SCREW LYC 214105720 LYC ALF502 ALF502R5 41580 NE HEAT SHIELD LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA A457 (CAN)ON REMOVAL OF THE 4TH ROTOR, A SCREW WAS FOUND LOOSE AND PROTRUDING APPROXIMATELY 3/16 INCH FROM THE REAR HEAT SHIE LD WITH ASSOCIATED DAMAGE IN THE AREA OF THE BLADE ROOTS. RIVET HEADS WORN DOWN AND L IGHTLY RUBBING ON ROTOR DISC. MANU FACTURER SUGGESTED A REVISED TORQUE VALUE FOR THE SCREW. 4 F E6NE 1996111400622 19961114 00622 SO 1996 11 14 CA960418201 2 19960402 G 8540 MOUNTING PAD CONT CESSNA 310 T310R 2074246 CE CONT O520 TSIO520BB 17040 SO ALTERNATOR PAD MISMACHINED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 674 236988R (CAN)MOUNTING HOLE AND PAD FOR ALTERNATOR MACHINED APPROXIMATELY .080 INCH TOO FAR FORWARD CAUSING ALTERNATOR DRIVE GEAR NOT MESHING PROPERLY. 1 L 7 2 3O 3 O 3A10 E8CE 1996111400624 19961114 00624 NM 1996 11 14 CA960419002 1 19960408 G 3010 153212A VALVE BENDIX DHAV DHC8 DHC8* NM DEICE SYSTEM SEIZED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA RF3377 (CAN)DEICE DISTRIBUTION CONTROL VALVE SEIZED DUE TO CORROSION. DRAIN HOLES FOUND OBSTRUCTED BY POTTING COMPOUND CAUSING ACCUMULATION OF MOISTURE AND SUBSEQUENT FAILURE. 2 H 7 2 4T RT A13NM 1996111400637 19961114 00637 NM 1996 11 14 CA960422006 1 19960219 G 2620 A805586 CUTTER KNIFE A80680026 BOEING 727 727 1384001 NM FIRE EXTINGUISH MISMATCH W A O OTHER W INADEQUATE Q C IN INSP/MAINT 1 CA B3431 (CAN)SUBJECT EXTINGUISHER IS A SHOCK WAVE TYPE OF FIRE EXTINGUISHER. ITEM WAS RECEIVED FOR OVERHAUL WITH A CUTTER KNIFE TYPE OUTLET P/N A805586 INSTALLED. FIRE EXTINGUISHER WAS NONFUNCTIONAL IN THE CONFIGURATION RECEIVED AND WOULD NOT HAVE FUNCTIONED IN AN EMERGENCY SITUATION. CORRECT P/N OF SHOCK WAVE TYPE OUTLET REQUIRED ON THIS FIRE EXTINGUISHER IS A80680 3-1. MSB ISSUED TO PRECLUDE THIS TYPE OF MISCONFIGURATION. 2 L 7 3 4F A3WE 1996112100164 19961121 00164 GL 1996 11 21 CA960424018 3 19960423 G 6110 BU10602 PISTON SEAL HARTZL DHAV DHC6 DHC6300 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL PROP LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 1159 BU10602 PCE42076 BU10602 (CAN)SLIGHT OIL TRACE AFT OF PROP SPINNER . PISTON SEAL REPLACED 1 H 7 2 3T 4 T A9EA E4EA 6 C P15EA 1996121200535 19961212 00535 CE 1996 12 12 CA960424021 1 19960409 G 3231 ART5CR ROD END C3500A CESSNA 206 U206F 2073333 CE CONT O520 IO520F 17032 SO MCAULY 2A34C D2A34C58 GL NLG BROKEN W K NONE J WARNING INDICATION CR CRUISE 1 CA 1132 564221 763171 (CAN) BOW WHEEL FAILED TO RETRACT, FOUND ROD END HAD BEEN BROKEN NEXT TO THE CENTRE BALL ALLOWING THE ROD END TO PULL AW AY FROM THE BALL END. SUSPECT INCORRECT RIGGING DUE TO THE 1/4 INCH DISTANCE OF THE ROD END FROM THE GEAR WITH THE GEAR MANUALLY RETRACTED UP AND THE ACTUATOR IS FULLY RETRACTED. 1 H 7 1 3O 3 O A4CE E5CE 5 C P3EA 1996121200536 19961212 00536 SO 1996 12 12 CA960424022 1 19960326 G 3211 2082900 STUD PIPER PIPER PA24 PA24250 7102404 SO LYC O540 O540A1A 41532 EA MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 3155 L392640 (CAN) INSPECTION OF STUDS AS PER AWD 95-20-07 REVEALED FINE LINEAR CRACK INDICATIONS AT THE RADIUS UNDER THE BOLT HEAD. THE BOLTS WERE REJECTED. 1 L 7 1 3O 3 O 1A15 E295 1996121200537 19961212 00537 CE 1996 12 12 CA960424023 1 19960330 G 5312 BULKHEAD CESSNA 210 210G 2073430 CE CONT O520 IO520A 17032 SO MCAULY 3A32C D3A32C88 GL STA 230.1 CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 1106394A 72066 (CAN) DURING A 100 HOUR ANNUAL INSPECTION A CRACK WAS FOUND ON THE AFT BULKHEAD AT STA. 230.1. THE BULKHEAD IS AN ATTACH FOR THE VERTICAL FIN. THE CRACK IS LOCATED ON THE RIGHT HAND SIDE FROM THE CUT OUT FOR THE RUDDER CABLES AND MIGRATES T OWARD THE LOWER RIGHT HAND BOLT. 1 H 7 1 3O 3 O 3A21 E5CE 5 C P21EA 1996121200538 19961212 00538 CE 1996 12 12 CA960424024 1 19960330 G 5330 SKIN CESSNA 210 210G 2073430 CE CONT O520 IO520A 17032 SO MCAULY 3A32C D3A32C88 GL STA 59.7 CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 1106394A 72066 (CAN) SKIN AT STATION 59.7 FOUND CRACKED ON BOTH SIDES FROM THE LANDING GEAR CUTOUT TOWARDS THE DOOR FRAME. THE SUBMITTE R STATES THAT THE CRACK APPEARS TO EXTEND THROUGH AT LEAST TWO SKINS ABOUT 1.5 INCHES LONG. 1 H 7 1 3O 3 O 3A21 E5CE 5 C P21EA 1996112100173 19961121 00173 WP 1996 11 21 CA960429001 2 19960411 G 8530 35175 MOUNTING BOLT DHAV GM10103 DHAV DHC1 DHC1B2 2801736 GL DHAVXX GIPSY GIPSYMAJOR1 20004 WP VALVE RKR BOX LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA 254 DHC120 (CAN)PILOT FOUND #3 ROCKER BOX LOOSE AND TWO NUTS INSIDE LOWER COWLING. MAINTENANCE FOUND #3 ROCKER BOX MOUNTING BOLTS H AD BACKED OFF AND FALLEN INTO BOX COVER. ALSO, THE MOUNTING BOLTS ON ALL THREE REMAINING ROCKER BOXES HAD LOST THEIR TOR QUE LEADING TO BELIEVE THAT INCORRECT TORQUE WAS APPLIED AT LAST OVERHAUL 15 YEAR PREVIOUS. 1 L 7 1 3O 3 I EXPA1L71 A8EU 1996121200541 19961212 00541 SO 1996 12 12 CA960429008 1 19960404 G 3213 78033 TORQUE LINKS PIPER 78033 PIPER PA28 PA28140 7102802 SO LYC O320 O320E2A 41508 EA SNSNCH 74DM M74DM EA MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 3031 L2232127A K13495 (CAN) TORQUE LINKS INSPECTED AS PER AWD AND FOUND CRACKED IN THE LOCATION SHOWN IN THE SERVICE MANUAL. CRACKS WERE DYE P ENETRANT CHECKED BUT SUBMITTER STATES THAT THE CRACKS WERE VISIBLE WITH A 10X MAGNIFYING GLASS. 1 L 7 1 3O 3 O 2A13 E274 5 N P88614 1996112100179 19961121 00179 NE 1996 11 21 CA960429009 2 19960411 G 7250 123022 TURBINE CASE PWA PW123 DHAV DHC8 DHC8301 NM PWA PW120 PW123 NE NR 2 ENG PUNCTURED W A A E UNSCHED LANDING ENGINE SHUTDOWN E A T VIBRATION/BUFFET FLAME/FIRE ENGINE CASE PENETRATION CL CLIMB 1 CA 5857 123022 123022 (CAN)AFTER TAKEOFF, VIBRATION FROM #2 ENGINE FOLLOWED BY ENGINE FIRE. AFM PROCEDURES CARRIED OUT, BOTH BOTTLES DISCHARG ED. FIRE EXTINGUISHED BUT LATER REIGNITED AFTER LANDING, AIRPORT FIRE CREW EXTINGUISHED FIRE. A LARGE QUANTITY OF RESID UAL OIL NOTED IN THE NACELLE AREA WHICH COULD BE THE SOURCE OF SECOND FIRE. HOLE IN THE FRONT OF THE TURBINE SUPPORT CAS E AT THE 8 O'CLOCK POSITION WITH BLADE AND SHROUD SEGMENT DEBRIS IN THE NACELLE. 2 H 7 2 4T 4 T RT A13NM E20NE 1996112100188 19961121 00188 SO 1996 11 21 CA960502049 2 19960415 G 8530 PISTON PIN CESSNA 337 337G 2075730 CE CONT O360 IO360G 17025 SO MCAULY 2AF34C D2AF34C306 GL REAR ENG FRACTURED W A E UNSCHED LANDING ENGINE SHUTDOWN J R WARNING INDICATION PARTIAL RPM/PWR LOSS CL CLIMB 1 CA 130 352477 793546 (CAN) CLIMBING THROUGH 5,200 FEET, REAR ENGINE RPM STARTED FLUCTUATING 200-300 RPM. OIL PRESSURE DROPPED TO ZERO, ENGINE FEATHERED. ENGINE TEARDOWN REVEALED BROKEN PISTON PIN. SUPERIOR AIR PART. 1 H 7 2 3O 3 O A6CE E1CE 5 C P5EA 1996112100189 19961121 00189 EU 1996 11 21 CA960502051 1 19960422 G 3297 3425144 WIRE BAG BAE146 BAE146200A 1500266 EU LT MLG DWNLK DEFECTIVE W A A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 CA (CAN)GEAR SELECTED UP,BUT LH MLG CONTINUED TO INDICATE DOWN & LOCKED.GEAR CYCYLED BUT STILL NO GOOD.INSPECTION FOUND WIR E #34-25-144 WAS CAUSING A LOW RESISTANCE AT PIN 18 OF LEFT GEAR DOWNLOCK CARD,CAUSIN G A CONSTANT DOWNLOCK INDICATION.F URTHER INVESTIGATION FOUND RELAY 3425-K10 OF THE WINDSHEAR SYSTEM DID NOT HAVE POWER APPLIED TO PIN #7.ALSO WIRE IN POSI TION WA6Y IN CB PANEL 131-12-00 HAD BEEN STOWED AS PART OF SB 34-143-50016E.THIS WAS TO ENABLE THE STEEP APPROACH ADAPTO R INSTALLED AS PER SB TO WORK.IT WAS THEN FOUND THAT WIRE 3425-143 HAD BEEN SPLICED TO WIRE WH100.THIS WIRE WAS THEN REM OVED BY SB 34-143-50016E.WIRE 3425-143 WAS THEN REMOVED FROM SPLICE AND TERMINATED INTO PIN WA6Y IN CB PANEL. 2 H 7 4 4F RT A49EU 1996121900777 19961219 00777 SO 1996 12 19 CA960502054 1 19960422 G 7110 65202800 COWLING LATCH PIPER PA32 PA32260 7103206 SO RT FWD CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ON PREPARATION FOR PAINTING, THE FOUR COWLING LATCHES REMOVED. FORWARD R.H. LATCH CRACKED ACROSS THE ATTACH HOLES. 1 L 7 1 3O A3SO 1997030600665 19970306 00665 SW 1997 3 6 CA960502057 1 19960328 G 5610 36004311SS WINDSHIELD GULSTM 690TP 695A 7630519 SW ROTOL R306 R306382F7 GL LEFT SIDE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 66070820823 (CAN) LEFT HAND WINDSHIELD FOUND CRACKED. 1 H 7 2 4T 2A4 6 C P8EU 1997030600666 19970306 00666 CE 1997 3 6 CA960502061 1 19960418 G 2730 CONTROL CESSNA 414 414A 2075907 CE CONT O520 TSIO520NB 17040 SO MCAULY 3AF32C 3AF32C505 GL ELEVATOR OBSTRUCTED W K NONE F W FLT CONT AFFECTED INADEQUATE Q C IN INSP/MAINT 1 CA 290847R 950199 (CAN) ELEVATOR CONTROL OBSTRUCTED BY INSTALLATION OF GPS ANNUNCIATOR UNIT. ELEVATOR CONTROL STRIKING BACK OF INSTALLED U NIT NOT PERMITTING FULL ELEVATOR UP TRAVEL. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 1996112100196 19961121 00196 1996 11 21 CA960507003 4 19960208 G 3422 6225812001 FLUX VALVE COLLINS 6225812001 BEECH 90 C90A 1152911 CE PWA PT6 PT6A21 52043 EA COMPASS SYS OIL SOAKED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 7111 PCE25675 (CAN)AIRCRAFT COMPASS SYSTEM REPORTED UNRELIABLE. EXAMINATION OF COMPASS COMPONENTS AND WIRING REVEALED THAT THE FLUX VA LVE WAS SATURATED WITH INSTRUMENT OIL. COLLINS CONFIRMED THAT THE LOSS OF OIL COULD R ESULT IN FAILURE OF THE COMPONENT. FLUX VALVE REPLACED. 1 L 7 2 3T 4 T RT 3A20 E4EA 1996121000001 19961210 00001 NE 1996 12 10 CA960507010 2 19960409 G 7261 LA153 PUMP LYC 218324001 CNDAIR CL600 CL600* EA LYC ALF502 ALF502L2 41580 NE PIN HOLE IN CASE LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA LA153 LF030363S (CAN)OIL FOUND IN COWLING AND ON GROUND . OIL PUMP HAD A PINHOLE IN THE CASING, VERIFIED BY EDDY CURRENT INSPECTION 2 L 7 2 4F 4 F RT A21EA E6NE 1996112700002 19961127 00002 NM 1996 11 27 CA960507013 1 19960423 G 2435 WIRE LUCAS 23088002A DHAV DHC8 DHC8* NM LT - RT GEN CHAFED W L ABORTED APPROACH H I J ELECT. POWER LOSS-50 PC FLT. ATTITUDE INST. WARNING INDICATION AP APPROACH 1 CA (CAN)ON APPROACH, AND DURING GEAR SELECTION, BOTH #1 AND #2 DC GENERATOR ANNUNCIATORS FLASHED FOLLOWED BY AUXILIARY INVE RTER, RUDDER FULL PRESSURE, GPWS #1 STALL WARN WITH HORN, AND THE MASTER WARNING AND CAUTION LIGHTS FLICKERING. OFF FLA GS ALSO CYCLING ON PILOTS INSTRUMENTS. INSPECTION FOUND GENERATOR FIELD WIRES ON BOTH LEFT AND RIGHT SIDES CHAFING ON EN GINE STRUTS. 2 H 7 2 4T RT A13NM 1996121900788 19961219 00788 GL 1996 12 19 CA960508004 2 19960517 G 7261 LINES LKHEED 382 382G 526414U SO ALLSN 501D 501D22A 03006 GL NR 3 ENG BLOCKED W E ENGINE SHUTDOWN K FLUID LOSS CL CLIMB 1 CA (CAN) DURING CLIMBOUT, THERE WAS AN OIL LOSS INDICTION FOR NR 4 ENGINE. IN-FLIGHT SHUTDOWN WAS CARRIED OUT AND A 3 ENGI NE LANDING CONDUCTED WITHOUT INCIDENT. REAR COMPRESSOR, FRONT TURBINE BEARING SCAVENGE LINES WERE FOUND BLOCKED WITH CA RBON. LINES WERE BLOWN OUT WITH COMPRESSED AIR, FILTERS CHANGED AND AIRCRAFT RETURNED TO SERVICE. 2 H 7 4 4T 4 T A1SO E282 1996112700010 19961127 00010 EA 1996 11 27 CA960509201 2 19960425 G 7320 76772 HOSE PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA #3 & #1 CYLINDER DETERIORATED W O OTHER E VIBRATION/BUFFET CR CRUISE 1 CA 489 L673261A (CAN)PILOT REPORTED ROUGH RUNNING ENGINE ACCOMPANIED BY BLACK EXHAUST. PIECES OF INJECTOR AIR BLEED HOSE FOUND INSIDE TH E NOZZLE ASSEMBLES. 1 L 7 2 3O 3 O A20SO E14EA 1996121900789 19961219 00789 CE 1996 12 19 CA960509202 1 19960308 G 5712 RIBS BEECH 95 95 1153402 CE LYC O360 O360A1A 41514 EA WS 94.864 BENT W K NONE O OTHER IN INSP/MAINT 1 CA L2413536A (CAN) RIGHT WING RIBS AT W.S. 94.864, 108.281 AND 122.500 FOUND BENT AND BUCKLED UNDER THE UPPER WING SKIN. POSSIBLY CAU SED BY OVERPRESSURE OF FUEL IN AUXILIARY TANK (THERMAL EXPANSION ). 1 L 7 2 3O 3 O 3A16 E286 1996112700011 19961127 00011 EU 1996 11 27 CA960510101 1 19960430 G 2400 7308228 UPLOCK AIRBUS 310 A310304 EU RAM AIR TURB LOCK FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 14947 14947 (CAN)DURING WALK AROUND/DAILY CHECK ON AIRCRAFT, RAM AIR TURBINE (R.A.T.) WAS FOUND DEPLOYED. BOTH DEPLOY HANDLES IN THE COCKPIT WERE FOUND WITNESSED WIRED IN THE STOWED POSITION. MAINTENANCE CHECK FOUND TH E UPLOCK MECHANISM INOPERATIVE. U PLOCK REPLACED AND SYSTEM CHECKED SERVICEABLE. 2 L 7 2 4F RT A35EU 1996112700012 19961127 00012 EU 1996 11 27 CA960510102 1 19960421 G 2722 81681 ACTUATOR AIRBUS 310 A310304 EU RUDDER JAMMED W A A UNSCHED LANDING J F WARNING INDICATION FLT CONT AFFECTED CL CLIMB 1 CA 9937 9937 (CAN)ON CLIMB OUT, RUDDER TRAVEL #1 AND #2 FAILED QUICKLY IN SEQUENCE, UNABLE TO RESET. MAINTENANCE ACTION INVOLVED CHAN GING RUDDER VARIABLE STOP ACTUATOR. 2 L 7 2 4F RT A35EU 1996112700014 19961127 00014 NE 1996 11 27 CA960513001 2 19960408 G 7250 120111 TURBINE DISC PWA PW120A DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE FIRTREE FRACTURED W A A UNSCHED LANDING X M ENGINE FLAMEOUT OVER TEMP CL CLIMB 1 CA 3683 120111 120111 (CAN)DURING CLIMB, LOUD BANG FOLLOWED BY HIGH ITT ABOVE 950 DEGREES AND ENGINE FLAME OUT MOLTEN DEBRIS IN THE EXHAUST W ITH ALL THREE #6/7 OIL TUBES FRACTURED ENGINE TEARDOWN HAS REVEALED FRACTURE OF TWO LP TURBINE DISC FIRTREE WITH RELEA SE OF THREE LPT BLADES. THE DISC/BLADE ASSEMBLY TO BE RETURNED TO P&WC FOR INVESTIGATION. 2 H 7 2 4T 4 T RT A13NM E20NE 1996112700015 19961127 00015 NE 1996 11 27 CA960513002 2 19960403 G 7250 TURBINE DISC DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE FIRTREE FRACTURED W A A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CL CLIMB 1 CA 9988 5395 120050 (CAN)CLIMBING THROUGH 2,800 FEET, A LOUD SOUND WAS HEARD FROM PORT ENGINE. THE ENGINE WAS SECURED AND RETURNED TO BASE. DISASSEMBLY AT P&WC REVEALED ON LPT DISC FIRTREE HAD FRACTURED BELOW THE FIRST SERRAT ION AND RELEASED TWO BLADES. 2 H 7 2 4T 4 T RT A13NM E20NE 1996112700016 19961127 00016 NE 1996 11 27 CA960513003 2 19960319 G 7310 FUEL LINE MAIN DHAV DHC8 DHC8102 2809003 NM PWA PW121 PW121 52124 NE FLOW DIVIDER LOOSE W A UNSCHED LANDING Y K ENGINE STOPPAGE FLUID LOSS TO TAKEOFF 1 CA 11162 6155 120312 (CAN)ON TAKEOFF, THE ENGINE SPOOLED DOWN AND THE AIRCRAFT RETURNED TO THE GATE. POST FLIGHT INSPECTION FOUND FUEL SPILL ON THE COWLINGS. THE NUT FROM THE MAIN FUEL LINE TO THE FLOW DIVIDER HAD LOOSENED. 2 H 7 2 4T 4 T RT A13NM E20NE 1996112700017 19961127 00017 NE 1996 11 27 CA960513004 2 19960324 G 7321 FUEL CONTRL UNIT STBROS SD3 SD360 8100606 EU PWA PT6 PT6A65AR 52043 NE ENG FAILED W A K NONE O OTHER IN INSP/MAINT 1 CA 10118 4481 97351 (CAN)OVER THE PAST SEVERAL DAYS, THE ENGINE HAD EXPERIENCED REPEATED SURGES. AFTER A LENGTHY TROUBLESHOOTING, THE PROBLE M WAS RESOLVED BY CHANGING THE FCU. THIS PARTICULAR UNIT HAD BEEN INSTALLED ONLY THRE E DAYS PRIOR TO THE ONSET OF THE S URGING. 2 H 7 2 4T 4 T A41EU E4EA 1996112700018 19961127 00018 EA 1996 11 27 CA960513005 2 19960403 G 7250 BLADE BEECH 200 B200 1152922 CE PWA PT6 PT6A41 52043 EA COMP TURBINE FRACTURED W A UNSCHED LANDING Y ENGINE STOPPAGE CR CRUISE 1 CA 4629 1742 81501 (CAN)ENGINE SHUTDOWN FOLLOWING AN INCREASE IN ITT. AS THE POWER LEVER WAS BEING RETARDED, DRBRIS WAS SEEN TO BE COMING F ROM THE EXHAUST. INITIAL REPORT INDICATE THIS TO BE A COMPRESSOR TURBINE BLADE FRACTU RE. 1 L 7 2 4T 4 T A24CE E4EA 1996121000002 19961210 00002 1996 12 10 CA960513006 1 19960321 G 7712 TRANSDUCER PWA PT6 PT6A6 52043 EA ENG TORQUE FAILED W C D ABORTED TAKEOFF RETURN TO BLOCK R PARTIAL RPM/PWR LOSS TO TAKEOFF 1 CA 1681 103172 (CAN)ON TAKEOFF, TORQUE INDICATION DECAYED THROUGH 60 PSI FROM 68 PSI. POWER REDUCTION WAS ALSO AUDIBLE. THE ELECTRONIC LIMITER UNIT WARNING LIGHT ILLUMINATED AND THE CREW ISOLATED THE ELECTRONIC LIMITER S YSTEM. POST EVENT DOWNLOAD OF THE ELU REVEALED A FAULT CODE RELATING TO TORQUE PRESSURE. TORQUE TRANSDUCER REPLACED. 3 T E4EA 1996121000003 19961210 00003 1996 12 10 CA960513007 1 19960320 G 7714 TRANSDUCER PWA PT6 PT6A6 52043 EA ENG TORQUE FAILED W O OTHER J WARNING INDICATION AP APPROACH 1 CA 2045 130140 (CAN)ON APPROACH, THERE WAS A COCKPIT WARNING AND INDICATION OF LOSS OF TORQUE, APPARENTLY WITHOUT A DROP IN ENGINE POWE R. TORQUE TRANSDUCER DEFECTIVE. 3 T E4EA 1998041700397 19980417 00397 CE 1998 4 17 CA960513015 1 19960509 G 2820 560010939 FUEL LINE CESSNA 414 414A 2075907 CE SPAR WEB CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA 3336 (CAN) FUEL LINE CHAFED ON EDGE OF THE HOLE WHERE IT PASSES THROUGH THE MAIN WING SPAR LT SIDE. LINE INSPECTED AND FOUND WITHIN CHAFE LIMITS OF CESSNA SB MEB 87-7. LINE REPOSITIONED TO PROVIDE CLEARANCE. MANUFACTURER INSTALLED SPIRAL CHAF E STRIP TO PROVIDE PROTECTION. EXAMINATION OF RT SIDE DID NOT INDICATE CHAFING, HOWEVER, LINE WAS VERY CLOSE IN PROXIMI TY TO EDGE OF HOLE (.015 INCH). MANY FUEL LINES PASS THROUGH THE WING SPAR IN THIS AREA LEFT AND RIGHT AND ALL HAVE THE POTENTIAL TO CHAFE. 1 L 7 2 3O A7CE 1998041700399 19980417 00399 EU 1998 4 17 CA960514001 1 19960506 G 7830 0330132 ROD ASSEMBLY AMD FALC20 FALCON200 2730150 EU GARRTT ATF3 ATF36A4 29002 WP RH THRUST REVRSR DISCONNECTED W K NONE J WARNING INDICATION LD LANDING 1 CA P20110 (CAN) PILOTS REPORTED RT THRUST REVERSER TRANSIT LIGHT SLOW TO EXTINGUISH DURING STOW CYCLE. HAD TO CYCLE A FEW TIMES B EFORE LIGHT WOULD EXTINGUISH. INSPECTION PANELS REMOVED AND FOUND INBOARD LOWER END OF SCREWJACK TRANSMISSION ROD ASSY WAS NOT IN SAFETY AND BECAME DISCONNECTED. SECURING BOLT WAS INSTALLED IN YOKE AND TAB WASHER BENT OVER TO SECURE BOLT. THRUST REVERSER CHECK COMPLETED AND AIRCRAFT RETURNED TO SERVICE. THE AIRCRAFT HAD COMPLETED 222.5 HOURS SINCE LAST W ORK PERFORMED IN THIS AREA. 2 L 7 2 4F 4 F RT A7EU E7WE 1996121900793 19961219 00793 CE 1996 12 19 CA960515003 1 19960111 G 3411 58031 STATIC SENSOR NARCO AR850 CESSNA 185 A185F 2072821 CE MCAULY 2A34C D2A34C58 GL HOUSING LEAKING W K NONE O OTHER IN INSP/MAINT 1 CA 58031 788769 (CAN) PIEZO STATIC SENSOR HOUSING ASSEMBLY LEAKING IN EXCESS OF LIMITS 1 H 7 1 3O 3A24 5 C P3EA 1996121900794 19961219 00794 CE 1996 12 19 CA960515004 1 19960507 G 3411 20186 STATIC SENSOR NARCO AR850 CESSNA 210 2105 2073404 CE CONT O470 IO470S 17026 SO MCAULY 2A34C D2A34C58 GL HOUSING ASSEMBLY LEAKING W K NONE O OTHER IN INSP/MAINT 1 CA 20186 1090767SR 950428 (CAN) PIEZO STATIC SENSOR HOUSING LEAKING IN EXCESS OF LIMITS 1 H 7 1 3O 3 O 3A21 3E1 5 C P3EA 1996121900795 19961219 00795 SO 1996 12 19 CA960515005 1 19960326 G 3411 12644 STATIC SENSOR NARCO AR850 PIPER PA31T PA31T2 7103127 SO PWA PT6 PT6A135 52043 NE HOUSING ASSEMBLY LEAKING W K NONE O OTHER IN INSP/MAINT 1 CA 12644 PCE92402 (CAN) PIEZO STATIC SENSOR HOUSING LEAKING IN EXCESS OF LIMITS 1 L 7 2 3T 4 T RT A8EA E4EA 1996121900799 19961219 00799 CE 1996 12 19 CA960517103 1 19960501 G 5312 823400109 BULKHEAD CESSNA CESSNA 340 340A 2076405 CE CONT O520 TSIO520NB 17040 SO LT AFT INB FLNGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 2999 519328 (CAN) BULKHEAD ASSEMBLY BUCKLED AND CRACKED FROM LIGHTENING HOLE THROUGH TO INBOARD FLANGE. 1 L 7 2 3O 3 O 3A25 E8CE 1996112700045 19961127 00045 NE 1996 11 27 CA960521002 2 19960511 G 7313 FUEL NOZZLES PWA PWA120 PW125B NE NR 1 ENG LEAKING SEAL W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 8123 125093 (CAN)PRIOR TO DEPARTURE, FUEL LEAKAGE WAS DETECTED FROM FUEL NOZZLES ON #1 ENGINE. TWO FUEL NOZZLES AND THE FLOW DIVIDER REPLACED. AFTER NEXT FLIGHT, FUEL WAS AGAIN LEAKING. ONE MORE FUEL NOZZLE REPLACED. 4 T E20NE 1996112700046 19961127 00046 NE 1996 11 27 CA960521003 2 19960515 G 7261 TRANSFER TUBE DHAV DHC8 DHC8101 2809002 NM PWA 120 PW120A NE #6 & #7 BEARINGS FRACTURED W A A E UNSCHED LANDING ENGINE SHUTDOWN K FLUID LOSS CR CRUISE 1 CA 17989 13194 120399 (CAN)IN CRUISE AT 9K, #1 ENGINE LOW OIL PRESSURE LIGHT ILLUMINATED. ENGINE SHUT DOWN. INSPECTION REVEALED THE OIL TRANSF ER TUBE FEEDING THE #6 & #7 BEARINGS WAS FRACTURED. A TEMPORARY OIL LINE WAS FITTED A ND A DRY MOTORING RUN WAS ATTEMPTE D PRODUCING LOUD NOISE FROM THE ENGINE. FURTHER INSPECTION SHOWED LARGE QUANTITY OF METAL ON THE CHIP DETECTOR. 2 H 7 2 4T 4 T RT A13NM E20NE 1996112700047 19961127 00047 EA 1996 11 27 CA960521004 2 19960515 G 7210 86256 RED GEARBOX PWA DHAV DHC7 DHC7* EA PWA PT6 PT6A50 52043 EA NR 1 ENG FAILED W A D RETURN TO BLOCK Y ENGINE STOPPAGE TX TAXI/GRND HDL 1 CA 28674 3513 86256 PS86256 (CAN)WHILE TAXIING IN PREPARATION FOR TAKEOFF, #1 ENGINE OIL PRESSURE DECAYED AND THE PROPELLER WENT INTO AN UNCOMMANDED FEATHER POSITION ENGINE SECURED AND RETURNED TO GATE. LARGE AMOUNT OF METAL FOUND ON THE REDUCTION GEAR BOX CHIP DETEC TOR. ENGINE INSTALLED 3 DAYS PREVIOUSLY. 2 H 7 4 4T 4 T RT A20EA E4EA 1996112700048 19961127 00048 EA 1996 11 27 CA960521005 2 19960510 G 7230 BLADES BEECH 90 C90 1152913 CE PWA PT6 PT6A20 52043 EA COMPRESSOR TURB FRACTURED W A E UNSCHED LANDING ENGINE SHUTDOWN R PARTIAL RPM/PWR LOSS CR CRUISE 1 CA 9601 2729 22325 (CAN)IN CRUISE, #2 ENGINE PARAMETERS DROPPING. ENGINE SECURED AND RETURN TO POINT OF DEPARTURE. INVESTIGATION REVEALED T HE COMPRESSOR TURBINE BLADES FRACTURED NEAR THE ROOT PLATFORM. 1 L 7 2 3T 3 T 3A20 E4EA 1996112700049 19961127 00049 NE 1996 11 27 CA960521006 2 19960510 G 7230 COMPRESSOR PWA PT6 PT6A60A 52043 NE NR 1 ENG DAMAGED W A E UNSCHED LANDING ENGINE SHUTDOWN R B PARTIAL RPM/PWR LOSS SMOKE/FUMES/ODORS/SPARKS DE DESCENT 1 CA 1805 95083 (CAN)DURING DESCENT, LARGE TORQUE FLUCTUATIONS ON #1 ENGINE ACCOMPANIED BY FLAMES FROM THE EXHAUST AND SMOKE IN THE CABI N. ENGINE SECURED AND LANDED OK. LARGE AMOUNT OF OIL IN THE EXHAUST AREA AND SIGNIFIC ANT DAMAGE IN THE COMPRESSOR AREA. 4 T E4EA 1996112700050 19961127 00050 EA 1996 11 27 CA960521007 2 19960510 G 7250 BLADES PWA AIRTRC AT500 AT502A 0390306 SW PWA PT6 PT6A45R 52043 EA TURBINE FRACTURED W B A EMER. DESCENT UNSCHED LANDING R PARTIAL RPM/PWR LOSS CL CLIMB 1 CA 22581 11122 84131 (CAN)SHORTLY AFTER TAKEOFF, A LOUD BANG WAS HEARD ACCOMPANIED BY A LOSS OF POWER. AIRCRAFT LANDED IN A PLOWED FIELD, NO DAMAGE. INSPECTION REVEALED PERFORATIONS OF THE EXHAUST STUBS AND DUCT, SEVERAL POWERTURBINE BLADES FRACTURED AT MID SPA N. 1 L 7 1 3T 4 T NC A17SW E4EA 1996112700051 19961127 00051 EA 1996 11 27 CA960521008 2 19960509 G 7250 GAS GENERATOR BEECH 1900 1900C 1154161 CE PWA PT6 PT6A65B 52043 EA NR 2 ENG SEIZED W A UNSCHED LANDING Y ENGINE STOPPAGE CR CRUISE 1 CA 13571 6197 32481 (CAN)IN CRUISE, #2 ENGINE STOPPED SUDDENLY WITH NO WARNING OF UNUSUAL ENGINE PARAMETERS. RETURNED TO ALBUQUERQUE WITHOUT INCIDENT. INSPECTION REVEALED THE GAS GENERATOR SECTION SEIZED AND METAL CONTAMINATI ON OF THE OIL FILTER. THE POWER TU RBINE ROTATES FREELY. 2 L 7 2 4T 4 T RT A24CE E4EA 1996112700052 19961127 00052 CE 1996 11 27 CA960521009 1 19960508 G 7810 EXHAUST DUCT BEECH 1900 1900C 1154161 CE PWA PT6 PT6A65B 52043 EA NR 1 ENG CRACKED W A UNSCHED LANDING Y ENGINE STOPPAGE CR CRUISE 1 CA 13550 6296 32512 (CAN)DURING CRUISE, A LOUD BANG WAS HEARD AND THE #1 ENGINE AUTOFEATHERED. ENGINE SECURED AND LANDED OK. A 6 INCH CRACK FOUND IN THE BIFURCATED EXHAUST DUCT AT THE 9 O'CLOCK POSITION. 2 L 7 2 4T 4 T RT A24CE E4EA 1996112700053 19961127 00053 NE 1996 11 27 CA960521010 2 19960509 G 7250 BLADE PWA PWA PT6 PT6A25 52043 NE POWER TURBINE FRACTURED W A E UNSCHED LANDING ENGINE SHUTDOWN Y ENGINE STOPPAGE AB AEROBATIC 1 CA 5199 48076 (CAN)FOLLOWING A STALL EXERCISE DURING FLIGHT TRAINING, ON POWER APPLICATION, THERE WAS AN EXPLOSION FROM THE ENGINE. EN GINE WAS SECURED AND A LANDING MADE. AFTER ENGINE SPLIT AT THE "C" FLANGE, A FRACTURE D POWER TURBINE BLADE WAS EVIDENT. 3 T E4EA 1996112700073 19961127 00073 1996 11 27 CA960524013 4 19960516 G 3413 RC201LB INDICATOR BOEING 727 727171C 1384057 NM PWA JT8 JT8D7A 52053 NE RATE OF CLIMB SHORTED W H DEACTIVATE SYST/CIRCUITS O OTHER CR CRUISE 1 CA P653620B (CAN)DURING CRUISE THE LIGHTING CIRCUIT BREAKER FOR THE THIRD CREWMAN'S PANEL TRIPPED, THE CIRCUIT BREAKER WAS RESET AND POPPED AGAIN. SYSTEM NOT RESET. CABIN RATE OF CLIMB INDICATOR HAD SHORTED, REPLACED. 2 L 7 3 4F 4 F A3WE E2EA 1996112700074 19961127 00074 1996 11 27 CA960524014 4 19960516 G 3416 40416410020 DIAPHRAGM 1122343 DHAV DHC6 DHC6300 EA PWA PT6 PT6A27 52043 EA ALTIMETER DEFECTIVE W K NONE I FLT. ATTITUDE INST. TX TAXI/GRND HDL 1 CA EGH2390 PCE42076 (CAN) DURING TAXI AND GROUND OPERATION THE ALTIMETER WOULD SHOW A DISCREPANCY TO AIRPORT ALTITUDE. INSTRUMENT REPLACED A ND SHOP CHECK FOUND FAULT WITH THE DIAPHRAGM. 1 H 7 2 3T 4 T A9EA E4EA 1996112700076 19961127 00076 NM 1996 11 27 CA960524017 1 19960516 G 2435 03600923 BEARING LUCAS 23088002A DHAV DHC8 DHC8* NM START/GEN FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 330 810 (CAN) STARTER GENERATOR HAD A PREMATURE BEARING FAILURE. 2 H 7 2 4T RT A13NM 1996112700077 19961127 00077 1996 11 27 CA960524018 1 19960430 G 3241 AC60742 FLYWHEEL DUNLOP AC60742 BRAKE MAXARET IMPROPER LUBE W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 491 (CAN) WRONG LUBRICATION IN FLYWHEEL SIDE. 1996112700082 19961127 00082 EA 1996 11 27 CA960524023 1 19960507 G 7800 85411358003 HEAT SHIELD DHAV DHAV DHC8 DHC8311 1386006 EA RIGHT HAND EXH SEPARATED W A K NONE D INFLIGHT SEPARATION CR CRUISE 1 CA (CAN) RIGHT HAND HORIZONTAL STABILIZER FOUND DAMAGED ON ARRIVAL. FURTHER INVESTIGATION REVEALED THAT THE RIGHT HAND EXHA UST FLOATING HEAT SHIELD HAD DEPARTED IN FLIGHT AND CONTACTED THE STABILIZER. CREW REPORTED HEARING OR FEELING NOTHING. RH ENGINE EXHAUST HEAT SHIELD WAS PRE MOD 8/1664. LEFT HAND WAS POST MOD. 2 H 7 2 4T RT A13NM 1996112700086 19961127 00086 EA 1996 11 27 CA960527005 2 19960517 G 7414 10391586 DISTRIBUTOR BLOC BENDIX 103492901 PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA ENG MAG WORN BUSHING W K NONE O OTHER IN INSP/MAINT 1 CA 13 1015567 L313361A (CAN)DISTRIBUTOR BUSHING WORN AT A VERY RAPID RATE UNTIL DISTRIBUTOR GEAR ARM BEGAN INTERFERING AGAINST DISTRIBUTOR BLOC K CONTACTS. 1 L 7 2 3O 3 O A20SO E14EA 1996112700087 19961127 00087 SW 1996 11 27 CA960527006 1 19960415 G 5711 SPAR BBAVIA 7 7BCM 2110106 SW CONT C85 C8512F 17008 SO REAR SPAR ROOT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 102725R (CAN)ON INSPECTION THE REAR SPAR WAS FOUND FAILED (CRACKED) AT THE RIGHT HAND REAR SPAR ROOT END BISCUIT. IT WAS NOTED T O HAVE FAILED ACROSS THE TOP AT THE SECTION OF THE SPAR THAT IS MILLED OUT TO ACCOMMODATE THE BISCUIT DOUBLERS. SUBMITTE R STATES THAT THE AIRCRAFT WAS BUILT IN 1947 AND THAT THE SPAR APPEARS TO BE ORIGINAL. 1 H 7 1 3O 3 O A759 E233 1996112700088 19961127 00088 CE 1996 11 27 CA960527007 1 19960501 G 5711 SPAR BLANCA BBAVIA 8 8KCAB 2110612 CE LYC O320 AEIO320E1B 41508 EA O/B OF ROOT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 1648 L547555A (CAN)THE REAR SPAR EXHIBITS SIGNS OF WOOD COMPRESSION FAILURE AT THE 46 INCH LOCATION OUTBOARD FROM THE ROOT. 1 H 7 1 3O 3 O A21CE 1E12 1996121900807 19961219 00807 NM 1996 12 19 CA960527102 1 19960517 G 5751 SKIN STINSON UNIVAR 108 1083 9230408 NM CONT O470 O470R 17026 SO MCAULY 2A34C 2A34C66 GL AIL BAL WGT ATT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 2349 6665366 688039 (CAN) CRACK 3/8 INCH LONG RADIATING FROM 3 HOLES FOR THE ATTACHMENT OF THE STEEL BALANCE WEIGHT ON THE OUTBOARD LEADING EDGE OF RIGHT HAND AILERON. 1 H 7 1 3O 3 O A767 E273 5 C P3EA 1996121900808 19961219 00808 NM 1996 12 19 CA960527103 1 19960518 G 5751 SKIN STINSON UNIVAR 108 1083 9230408 NM CONT O470 O470R 17026 SO MCAULY 2A36C 2A36C29 GL AIL BAL WGHT ATT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 2510 514656R 63447 (CAN) CRACKS 1/4 INCH LONG RADIATING FROM 3 HOLES FOR THE ATTACHMENT OF THE STEEL BALANCE WEIGHT ON THE OUTBOARD LEADING EDGE OF RIGHT HAND AILERON. 1 H 7 1 3O 3 O A767 E273 5 C P880 1996121900809 19961219 00809 SO 1996 12 19 CA960528103 1 19960506 G 2740 69623004 TUBE PIPER PIPER PA28 PA28160 7102806 SO LYC O320 O320B2B 41508 EA STAB WEIGHT END DEFECTIVE W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA L476739 (CAN) PREPARING THE TUBE FOR INSTALLATION, THERE WAS A BLOB OF PAINT IN THE AREA OF MOUNTING OF THE WEIGHT. ON REMOVING THE BLOB OF PAINT, A FOLD IN THE METAL AND A 3 INCH LONGITUDINAL CRACK IN THE TUBE WAS REVEALED. MATERIAL DEFECT. POOR Q UALITY CONTROL. 1 L 7 1 3O 3 O 2A13 E274 1996112700094 19961127 00094 NM 1996 11 27 CA960529002 1 19960522 G 2421 31708001A AC GENERATOR LUCAS DHAV DHC8 DHC8* NM ROTOR MAKING METAL W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) LARGE PIECE OF METAL FOUND ON CHIP DETECTOR. SMALL SECTION OF ROTOR IRON LAMINATION STACK MISSING. ALSO FOUND A PI ECE OF HELI-COIL LOOSE INSIDE OF GENERATOR. 2 H 7 2 4T RT A13NM 1996112700095 19961127 00095 SO 1996 11 27 CA960529003 2 19960515 G 7322 C324391 ICO VALVE MARVELSCHEB 103878 CESSNA 185 A185F 2072821 CE CONT O520 IO520D 17032 SO MCAULY 2A34C D2A34C58 GL MIX CONTROL INCORRECT ASSY W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA C324391 563812 765933 (CAN)MIXTURE CONTROL AND IDLE CUT-OFF INOPERATIVE. UNIT ASSEMBLED INCORRECTLY WITH MIXTURE CONTROL AND I C O VALVE OUT OF THE VALVE BORE 1 H 7 1 3O 3 O 3A24 E5CE 5 C P3EA 1996120500360 19961205 00360 EA 1996 12 5 CA960529007 1 19960524 G 2422 MS250242 RELAY DHAV DHC6 DHC6300 EA PWA PT6 PT6A27 52043 EA #1 INVERTER INTERMITTENT W K NONE J WARNING INDICATION NR NOT REPORTED 1 CA PCE42076 (CAN) #1 INVERTER INDICATED A FAILURE UNTIL THE SELECTOR SWITCH WAS CYCLED AND THE PROBLEM CLEARED. MAINTENANCE CHANGED THE INVERTER SELECTOR RELAY. 1 H 7 2 3T 4 T A9EA E4EA 1996120500361 19961205 00361 EA 1996 12 5 CA960529008 1 19960528 G 7500 DAS10011 TUBE DEVORE DHAV DHC6 DHC6300 EA PWA PT6 PT6A27 52043 EA BLEED AIR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA PCE42076 (CAN) DURING INSPECTION REQUIRED BY MANUFACTURERS INSPECTION PROGRAM THE BLEED AIR DUCTS IN THE WING WERE FOUND TO BE CR ACKED BETWEEN THE INNER AND OUTER TUBE ON BOTH THE LEFT AND RIGHT SIDE. SB 6/355, USED TO REPAIR AND MOD 6/1614 INSTALLE D IMPROVED TUBES. 1 H 7 2 3T 4 T A9EA E4EA 1996120500362 19961205 00362 NM 1996 12 5 CA960529009 1 19960524 G 3150 D203W3 SWITCH GRIMES 75003821 BOEING 727 727171C 1384057 NM PWA JT8 JT8D7A 52053 NE ANNUN PANEL SHORTED W K NONE J WARNING INDICATION CR CRUISE 1 CA 428 P653620B (CAN)DURING FLIGHT THE FLIGHT ENGINEERS DOOR ANNUNCIATOR PANEL TEST SWITCH FAILED AND RESULTED IN ALL LIGHTS ILLUMINATIN G. THE PANEL WAS REPLACED. 2 L 7 3 4F 4 F A3WE E2EA 1996121900812 19961219 00812 CE 1996 12 19 CA960529010 1 19960522 G 2721 17670667 SCREW ACTUATOR CESSNA 177 177B 2073708 CE MCAULY 2D34C B2D34C211 GL RUDDER TRIM BROKEN W K NONE O F OTHER FLT CONT AFFECTED LD LANDING 1 CA 5487 797366 (CAN) ON APPROACH IN A FORWARD SLIP, RUDDER TRIM INOPERATIVE. RUDDER TRIM SCREW ACTUATOR SHAFT BROKEN MID SHAFT AT THE S HOULDER OF TRAVERSE THREAD. 1 H 7 1 3O A13CE 5 C P7EA 1996120500366 19961205 00366 CE 1996 12 5 CA960530002 1 19960401 G 2434 PU1605 FAN PRESTOLITE ALE8105A BEECH 23 A2319 1151212 CE LYC O320 O320E2C 41508 EA SNSNCH 74DM M74DM EA ALTERNATOR BROKEN W K NONE H ELECT. POWER LOSS-50 PC CR CRUISE 1 CA 1878 L1759327A K3029 (CAN)PILOT HEARD LOUD BANG FOLLOWED BY AMMETER SHOWING DISCHARGE. ALTERNATOR SEPARATED FROM ENGINE. HOUSING MOUNTING LUG S BROKEN OFF BY VIBRATION DUE TO IMBALANCE FOLLOWING A PORTION OF THE FAN BREAKING OF F. 1 L 7 1 3O 3 O A1CE E274 5 N P88614 1996121900817 19961219 00817 SO 1996 12 19 CA960604001 1 19960512 G 3230 2128600 MOTOR BOSCH M072218A PIPER PA24 PA24 7102402 SO LYC O360 O360A1D 41514 EA GEAR EXTEND BURNT W O OTHER B SMOKE/FUMES/ODORS/SPARKS LD LANDING 1 CA 2824 36461 L363136 (CAN) LANDING GEAR REFUSED TO EXTEND AND LOCK. EMERGENCY EXTEND SUCCESSFUL. ELECTRICAL MOTOR BURNT OUT. 1 L 7 1 3O 3 O 1A15 E286 1996120500367 19961205 00367 EA 1996 12 5 CA960604002 2 19960517 G 7414 9050365 BEARING CAP ASSY SLICK 4250 PIPER PA28 PA28181 7102807 SO LYC O360 O360A4M 41514 EA MAG ROTOR SHAFT FAILED W D RETURN TO BLOCK E VIBRATION/BUFFET TX TAXI/GRND HDL 1 CA 9050365 L2739436A (CAN)ENGINE ROUGH ON RUN UP. MAGNETO SEPARATED FROM ENGINE AND HANGING FROM HARNESS. MAGNETO SEIZED AND MOUNTING FLANGE FRACTURED. ROTOR SHAFT SEIZED DUE TO BEARING FAILURE ENSUING FROM OUTER RACE OF BEARING SPINNING WITHIN THE BEARING CAP ASSEMBLY. BEARING CAP ASSEMBLY LACKED THE "J" MARKING SEPCIFIED IN SB 2-88A ALTHOUGH THIS MAGNETO FALLS INTO THE SERIAL NUMBER RANGE FOR THE SB. 1 L 7 1 3O 3 O 2A13 E286 1996120500368 19961205 00368 SO 1996 12 5 CA960604003 2 19960524 G 8530 CYLINDER CESSNA 337 337G 2075730 CE CONT O360 IO360G 17025 SO MCAULY 2AF34C D2AF34C306 GL ENGINE NOT FIRING W E ENGINE SHUTDOWN R PARTIAL RPM/PWR LOSS CR CRUISE 1 CA 155 352839 793546 (CAN)IN CRUISE AT 9.5K, ENGINE RAN ROUGH AND BACKFIRED, SHUTDOWN. 1 H 7 2 3O 3 O A6CE E1CE 5 C P5EA 1996120500372 19961205 00372 1996 12 5 CA960604007 1 19960418 G 7830 THRUST REVERSER GE CFM56 CFM565A 13802 NE NR 1 ENG SHEARED HYD LINE W L ABORTED APPROACH K FLUID LOSS DE DESCENT 1 CA (CAN)THRUST REVERSER LH LOWER LATCH RETURN LINE #1 ENGINE SHEARED AT MIDPOINT CAUSING LOSS OF HYDRAULIC FLUID GREEN SYST EM. AIRCRAFT USED ALTERNATE GEAR EXTENSION AND LANDED SAFELY. LINE SENT TO NRC FOR AN ALYSIS. 4 F E29NE 1996120500380 19961205 00380 NM 1996 12 5 CA960605002 1 19960524 G 3222 STRUT BOEING 727 72725 1384006 NM NLG LEAKING W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) WHEN GEAR WAS SELECTED UP ON CLIMB OUT THE NOSE GEAR DOOR LIGHT REMAINED ON AND THERE WAS AN UNSAFE LANDING GEAR W ARNING, GEAR EXTENDED AND AIRCRAFT LANDED. 2 L 7 3 4F A3WE 1996120500381 19961205 00381 CE 1996 12 5 CA960605004 1 19960529 G 3213 52435183 FORK BOLT CESSNA 414 414 2075908 CE L/H TORQUE TUBE SHEARED W L O ABORTED APPROACH OTHER J WARNING INDICATION LD LANDING 1 CA 1323 (CAN)PILOT REPORTED L/H GEAR UNSAFE LIGHT. AIRCRAFT LANDED WITHOUT INCIDENT. ON ROLL-OUT, THE L/H GEAR DOWN LIGHT CAME O N. INSPECTION REVEALED THAT THE L/H FORK BOLT WAS SHEARED OFF FLUSH WITH THE TORQUE T UBE. AD #76-13-07 REQUIRES REPLACE MENT OF THESE BOLTS EVERY 2,000 HOURS TIME IN SERVICE. THIS AIRCRAFT WAS IN COMPLIANCE WITH THIS AD, HOWEVER, THE OVERCE NTER TENSION WAS HIGHER THAN THE EQUIPMENT COULD MEASURE. BOTH FORK BOLTS WERE REPLACED, AND OVERCENTER TENSION WAS ADJU STED TO THE SPECIFIED 50 LBS. SUBMITTER SUGGESTS THAT RIGGING OF GEAR SHOULD BE PART OF THE PROCEDURE AT TIME OF BOLT RE PLACEMENT. 1 L 7 2 3O RT A7CE 1999081200319 19990812 00319 EA 1999 8 12 CA960605005 1 19960528 G 5312 C2FS533 BULKHEAD DHAV DHC2 DHC2MK3 2800107 EA PWA PT6 PT6A27 52043 EA BS 228 CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 12503 PCE40557 (CAN) AFT FULL BULKHEAD AT STA 228 FOUND CRACKED ON BOTH LEFT AND RIGHT SIDES WHERE RUDDER CONTROL RODS PASS THROUGH THE BULKHEAD. CRACKS RADIATE FROM HOLES .0937 INCH TO .50 INCH TOWARDS THE VERTICAL STABILIZER ATTACHMENT. ANOTHER .50 IN CH CRACK WAS FOUND AT THE TOP OF THE BULKHEAD BETWEEN THE VERTICAL STABILIZER TWO ATTACH POINTS FROM THE BEND RELIEF CUT -OUT. SUBMITTER STATED TWO OTHER DHC-2 MKIII AIRCRAFT WERE INSPECTED AND THE SAME CRACKS WERE FOUND AT THE CONTROL ROD PASS THROUGH AFT FULL BULKHEADS REPLACED WITH NEW UNITS. 1 H 7 1 3T 4 T A806 E4EA 1996120500384 19961205 00384 SO 1996 12 5 CA960606002 2 19960527 G 8520 639292 SPLIT PIN CONT 646321 MAULE M5 M5210C 5460134 SO CONT O360 IO360D 17025 SO MCAULY 2A34C D2A34C67 GL #5 CONROD DETACHED W K NONE O OTHER IN INSP/MAINT 1 CA 320 351203 752647 (CAN)ON ANNUAL INSPECTION, ONE SPLIT PIN FOUND IN THE SUCTION OIL SCREEN. OIL PAN REMOVED FOR INTERNAL INSPECTION. #5 CO NROD BEARING CAP MISSING ONE COTTER PIN, REPLACED. 1 H 7 1 3O 3 O 3A23 E1CE 5 C P3EA 1996120500386 19961205 00386 SO 1996 12 5 CA960606004 2 19960517 G 8530 VALVE GUIDE CONT CESSNA 182 182 2072702 CE CONT O470 O470L 17026 SO MCAULY 2A34C 2A34C50 GL EXHAUST VALVE LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA 513 693105LR 731568 (CAN)ON 100 HOUR INSPECTION, LOW COMPRESSION IN CYLINDER. EXHAUST VALVE GUIDE LOOSE IN CYLINDER HEAD. 1 H 7 1 3O 3 O NT 3A13 E273 5 C P3EA 1996121900827 19961219 00827 SO 1996 12 19 CA960610001 1 19960516 G 5412 5048 FIREWALL MAULE M4210C MAULE M4 M4210C 5460112 SO CONT O360 IO360A 17025 SO MCAULY 2A34C D2A34C67 GL R/H CORNER CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 1070C 10557 681071 (CAN) DURING AN ENGINE CHANGE, FIREWALL WAS FOUND TO BE CORRODED EXCESSIVELY. FIREWALL WAS REPLACED AS PER MAINTENANCE M ANUAL. SUBMITTER NOTES THAT THE MATERIAL OF THE FIREWALL IS GALVANIZED STEEL. 1 H 7 1 3O 3 O 3A23 E1CE 5 C P3EA 1996120500390 19961205 00390 SW 1996 12 5 CA960610004 1 19960520 G 7120 162301 RUBBER BUSHING LORD BBAVIA 8 8GCBC 1220803 SW LYC O360 O360C2E 41514 EA ENG MOUNT DETERIORATED W K NONE O OTHER IN INSP/MAINT 1 CA 474 L1967536A (CAN)ON ANNUAL INSPECTION, THE LOWER RIGHT ENGINE MOUNT RUBBER BUSHING FOUND SEVERELY DETERIORATED. THIS MOUNT IS DIRECT LY BELOW THE OIL FILLER TUBE AND IS SUSCEPTIBLE TO OIL SPILLAGE. 1 H 7 1 3O 3 O A21CE E286 1996121900829 19961219 00829 CE 1996 12 19 CA960610009 1 19960618 G 5511 07326116 RIB CESSNA CESSNA 185 A185E 2072818 CE MCAULY 2A34C D2A34C58 GL HORIZ STAB CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 5596 744927 (CAN) DURING A 100 HOUR INSPECTION, HORIZONTAL STABILIZER RIB P/N 0732611 WAS FOUND CRACKED. WITH THE STABILIZER REMOVED FOR REPAIR, EIGHT (8) NOSE RIBS WERE FOUND CRACKED OR CRUSHED. SUBMITTER STATES THAT THIS AREA IS DIFFICULT TO INSPECT WITH THE STABILIZER INSTALLED. 1 H 7 1 3O 3A24 5 C P3EA 1996120500394 19961205 00394 1996 12 5 CA960610010 4 19960531 G 2562 168 'G' SWITCH CESSNA 500 560CESSNA 2076750 CE ELT TRANSMITTER FAILED TEST W K NONE O OTHER IN INSP/MAINT 1 CA 1144 (CAN)'G' SWITCH FAILED DURING ANNUAL CERTIFICATION TEST IN ACCORDANCE WITH AIRWORTHINESS REGULATIONS. 'G' SWITCH REPLACE D AND RE-CERTIFIED FOR RETURN TO SERVICE. 2 L 7 2 4F RT A22CE 1998041700401 19980417 00401 CE 1998 4 17 CA960610011 1 19960531 G 3242 215295 BRAKE ASSY CESSNA 500 560CESSNA 2076750 CE PLATE WORN W K NONE O OTHER IN INSP/MAINT 1 CA 1132 (CAN) DURING ROUTINE INSPECTION, FOUND WEAR PLATE EXCESSIVELY WORN EVEN WITH 0.150 INCH REMAINING ON THE WEAR INDICATOR (NORMALLY BRAKE SHOULD BE REMOVED WHEN THE INDICATOR IS FLUSH WITH THE BRAKE HOUSING). UPON DIS-ASSEMBLY OF THE BRAKE U NIT, WEAR ON PLATE WAS 0.048 INCH WHERE ACTUAL ALLOWABLE IS 0.070 INCH. ROTOR MINIMUM LIMIT IS 0.300 INCH, AND ACTUAL W AS 0.268 INCH. SAME CONDITION WAS FOUND ON OTHER SIDE OF AIRCRAFT. PART TC: 909. 2 L 7 2 4F RT A22CE 1996120500397 19961205 00397 NM 1996 12 5 CA960611001 1 19960520 G 7120 STRUT LORD 87110016011 DHAV DHC8 DHC8102 2809003 NM NR 1 ENG AFT BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 13905 (CAN)#1 ENGINE REAR OUTBOARD ENGINE MOUNT VERTICAL STRUT FOUND BROKEN. 2 H 7 2 4T RT A13NM 1996120500401 19961205 00401 SO 1996 12 5 CA960611006 2 19960517 G 8530 ROCKER SHAFT CONT 641917 CESSNA 150 150L 2071826 CE CONT O200 O200A 17020 SO NR 4 CYL BROKEN BOSS W C D ABORTED TAKEOFF RETURN TO BLOCK E VIBRATION/BUFFET TO TAKEOFF 1 CA 811 626372AR (CAN)ON TAKEOFF, AT FULL POWER, ABORTED DUE TO SEVERE ENGINE VIBRATION. #4 CYLINDER VALVE ROCKER SHAFT BOSSES BROKEN ACR OSS BOTH VALVES. 1 H 7 1 3O 3 O 3A19 E252 1996121900836 19961219 00836 NE 1996 12 19 CA960612005 1 19960606 G 5302 6120762651 PYLON SKRSKY S61 S61N 8142104 NE 90 DEG FITTING CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) 90 DEGREE GEARBOX FITTING CRACKED AT THE ATTACHMENT AREA OF THE WEB AND BOTH SIDE SKINS. 2 G 7 2 4U 1H15 1996121900837 19961219 00837 1996 12 19 CA960612013 1 19960605 G 2830 15D024A066 BEARING WELDON 70D10 PUMP MOTOR WRONG PART W K NONE W INADEQUATE Q C NR NOT REPORTED 1 CA 03561 (CAN) BEARING REMOVED WAS NOT AS RECOMMENDED BY COMPONENT MANUFACTURER. 1996121900838 19961219 00838 1996 12 19 CA960612014 1 19960605 G 2823 102549E BEARING ITT AV16B1667D FUEL SOV WRONG PART W K NONE W INADEQUATE Q C NR NOT REPORTED 1 CA R124286 (CAN) BEARING REMOVED WAS NOT AS RECOMMENDED BY COMPONENT MANUFACTURER. 1996121900839 19961219 00839 CE 1996 12 19 CA960612018 1 19960606 G 2913 OAS29401 HYDPOWER PACK OZONE OAS29401 CESSNA 210 210E 2073416 CE CONT O520 IO520A 17032 SO MCAULY 2A34C E2A34C73 GL HYD SYS CONTAMINATED W K NONE O OTHER IN INSP/MAINT 1 CA 296 112324R 726919 (CAN) THE HYDRAULIC RESERVOIR WAS FOUND TO BE CONTAMINATED WITH A FILM OF SLUDGE. FURTHER INVESTIGATION FOUND TEFLON TAP E ON THE VARIOUS FITTINGS AND TEFLON CONTAMINATION THROUGHOUT THE UNIT. 1 H 7 1 3O 3 O 3A21 E5CE 5 C P3EA9 1996121200208 19961212 00208 1996 12 12 CA960612023 4 19960527 G 6122 210628G OVERSPEED GOV DHAV DHC2 DHC2EVANS 2801832 EA PROP FAILED W D RETURN TO BLOCK R PARTIAL RPM/PWR LOSS CL CLIMB 1 CA 601 (CAN)PILOT DID OVERSPEED TEST BEFORE TAKEOFF. PROP SPEED, HOWEVER NOTED TO BE LOW. SOLENOID FOR TEST HAD FAILED AND OVER SPEED GOVERNOR NEEDED TO BE REPLACED. 1 H 7 1 3O A806 1996121200211 19961212 00211 NE 1996 12 12 CA960612026 2 19960118 G 7210 310703301 BEARING AEROSP ATR42 ATR42* 8680900 EU PWA 120 PW120 NE RGB NR 15 BRG SPALLED W A K NONE O OTHER IN INSP/MAINT 1 CA 10431 121018 (CAN)METAL ON THE RGB CHIP DETECTOR. #15 BEARING SPALLED SEVERELY. SMALL AMOUNT OF RESIDUAL MAGNETISM DETECTED ON PROPEL LER SHAFT AND #18 AND #19 BEARING RACES. 2 H 7 2 4T 4 T RT A53EU E20NE 1996121200212 19961212 00212 NE 1996 12 12 CA960612027 2 19960118 G 7210 310120201 BEARING EMB 120 EMB120 3260201 SO PWA 118 PW118A NE RGB NR 14 BRG SPALLED W K NONE O OTHER IN INSP/MAINT 1 CA 11758 115521 (CAN)METAL ON RGB CHIP DETECTOR. #14 BEARING OUTER RACE SPALLED, ROLLERS FLAKING AND CAGE CRACKED. 2 L 7 2 4T 4 T RT A31SO E20NE 1996121200213 19961212 00213 NE 1996 12 12 CA960612028 2 19960130 G 7210 310406201 BEARING AEROSP ATR42 ATR42* 8680900 EU PWA PW121 PW121 52124 NE RGB NR 18 BRG SPALLED W A K NONE O OTHER IN INSP/MAINT 1 CA 12880 1125 120460 (CAN)METAL ON THE RGB CHIP DETECTOR. #18 BEARING BALLS SPALLED. ELECTRICAL PITTING FOUND ON #15 AND #19 BEARINGS ON IDLE R DRIVE, THEREFORE THE SPALLING ON THE #18 BEARING IS LIKELY DUE TO ELECTRICAL DISCHA RGE FROM AN EXTERNAL AIRCRAFT SOUR CE. 2 H 7 2 4T 4 T RT A53EU E20NE 1996121200216 19961212 00216 NE 1996 12 12 CA960612031 2 19960108 G 7230 311362301 BEARING EMB 120 EMB120 3260201 SO PWA 118 PW118 NE NR 5 BRG CAGE FRACTURED W A K NONE E VIBRATION/BUFFET IN INSP/MAINT 1 CA 13630 2994 115309 (CAN)ENGINE REPORTED MAKING "GRUMBLING" NOISES. METAL CONTAMINATION OF THE OIL FILTER AND METAL FLAKES ON THE TURBOMACH INE CHIP DETECTOR. #5 BEARING FAILED DUE TO FAILURE OF ONE SEPARATOR OF THE BEARING CA GE ALLOWING ONE ROLLER TO MOVE O UT OF POSITION AND SKIDDING OF THAT ROLLER. NO OBVIOUS REASON FOR THE CAGE FAILURE. THIS BEARING HAD BEEN REPLACED 299 4 HOURS PREVIOUS FOLLOWING A HP STUBSHAFT BOLT FAILURE. 2 L 7 2 4T 4 T RT A31SO E20NE 1996121900842 19961219 00842 CE 1996 12 19 CA960614007 1 19960606 G 2620 RETAINING CLIP RAYTHN 1015700215 BEECH 90 C90A 1152911 CE PWA PT6 PT6A21 52043 EA FIRE EXT SWITCH FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 2290 PCE25648 (CAN) ON INSPECITON OF THE ENGINE FIRE EXTINGUISHER ELECTRICAL SYSTEM, IT WAS NOTED THAT THE FIRE EXTINGUISHER MICROSWIT CH ON THE PANEL ACTIVATING BUTTON HAD COME OFF THE HOLDING CLIP RENDERING THE BUTTON INOPERATIVE. THE SWITCH MANUFACTURE R - RAYTHEON - INDICATES A REPLACEMENT SWITCH IS BEING PRODUCED. 1 L 7 2 3T 4 T RT 3A20 E4EA 1996121900843 19961219 00843 CE 1996 12 19 CA960614010 1 19960605 G 5720 052356529 WING TIP CESSNA CESSNA 150 152 2071835 CE LT WING CRACKED W C ABORTED TAKEOFF O OTHER LD LANDING 1 CA 3462 (CAN) STUDENT ATTEMPTING TO LAND DRAGGED LEFT WING TIP ON RUNWAY. WING TIP CRACKED, NO OTHER DAMAGE. 1 H 7 1 3O NT 3A19 1996121200244 19961212 00244 NE 1996 12 12 CA960614015 2 19960401 G 7210 310924401 BEARING PWA AEROSP ATR42 ATR42* 8680900 EU PWA 120 PW120 NE RGB NR 15 BR SPALLED W A K NONE O OTHER IN INSP/MAINT 1 CA 14134 5708 120661 120661 (CAN)REDUCTION GEAR BOX REPORTED MAKING METAL. #15 BEARING HAD SEVERE SPALLING ON THE ROLLERS AND OUTER RACE. 2 H 7 2 4T 4 T RT A53EU E20NE 1996121200245 19961212 00245 NE 1996 12 12 CA960614016 2 19960404 G 7210 310703301 BEARING PWA AEROSP ATR42 ATR42* 8680900 EU PWA PW121 PW121 52124 NE RGB NR 15 BRG SPALLED W A K NONE O OTHER IN INSP/MAINT 1 CA 6812 121140 121140 (CAN)METAL ON THE REDUCTION GEAR BOX CHIP DETECTOR. #15 BEARING INNER RACE SPALLED. ELECTRICAL DISCHARGE PITTING ON #15 ROLLERS AND #18 BEARING LIKELY FROM STRAY ELECTRICAL DISCHARGE FROM SOME AIRCRAFT COM PONENT. 2 H 7 2 4T 4 T RT A53EU E20NE 1996121200246 19961212 00246 NE 1996 12 12 CA960614017 2 19960409 G 7210 310119101 BEARING PWA DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE RGB NR 10 BRG SPALLED W A K NONE O OTHER IN INSP/MAINT 1 CA 17032 120417 120417 (CAN)REDUCTION GEAR BOX MAKING METAL. LEFT HAND #10 BEARING, ONE BALL SPALLED. REMAINING OIL IN THE GEARBOX WAS VERY DIR TY AND FOUND TO CONTAIN HIGH LEVELS OF PHOSPHORUS AND VANADIUM. SEVERAL OTHER BEARING S HAD PITS AND DISCOLORATION SIMIL AR TO CORROSION THAT MAY BE RELATED TO THE CONTAMINATED OIL. 2 H 7 2 4T 4 T RT A13NM E20NE 1996121200247 19961212 00247 NE 1996 12 12 CA960614018 2 19960503 G 7260 311196801 TOWERSHAFT AEROSP ATR42 ATR42* 8680900 EU PWA PW121 PW121 52124 NE UPPER SHOULDER FRACTURED W A A UNSCHED LANDING Y ENGINE STOPPAGE CR CRUISE 1 CA 10813 120956 (CAN)IN CRUISE, LOSS OF OIL PRESSURE AND ENGINE STOPPED. THE TOWERSHAFT FRACTURED IMMEDIATELY BELOW THE UPPER BEVEL GEAR AND BEARING. THIS RESULTED IN LOSS OF DRIVE TO BOTH THE FUEL PUMP AND THE OIL PUMP, THUS SHUTTING DOWN THE ENGINE. REA SON FOR THE FAILURE COULD NOT BE ASCERTAINED. 2 H 7 2 4T 4 T RT A53EU E20NE 1996121200248 19961212 00248 NE 1996 12 12 CA960614019 2 19960530 G 7210 310709001 BEARING PWA EMB 120 EMB120 3260201 SO PWA 118 PW118 NE RGB NR 19 BRG CRACKED W A K NONE O OTHER IN INSP/MAINT 1 CA 14724 8138 115151 115151 (CAN)REDUCTION GEAR BOX CONTAMINATED WITH METAL. #19 BEARING INNER RACE CRACKED. 2 L 7 2 4T 4 T RT A31SO E20NE 1996121200249 19961212 00249 NE 1996 12 12 CA960614020 2 19960205 G 7210 310703301 BEARING PWA DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE RGB NR 15 BRG SPALLED W A K NONE O OTHER IN INSP/MAINT 1 CA 9266 121064 121064 (CAN)REDUCTION GEARBOX METAL CONTAMINATION. #15 BEARING HAD A LARGE SPALL OVER 60 DEGREES OF THE OUTER RACE. SEVERAL STE EL COMPONENTS WERE HEAVILY MAGNETISED AND #18 AND #19 BEARINGS SHOWING SIGNS OF ELECT RICAL PITTING LEADING TO BELIEVE T HAT LIGHTNING STRIKE IS LIKELY THE CAUSE OF THE BEARING FAILURE. 2 H 7 2 4T 4 T RT A13NM E20NE 1996121200250 19961212 00250 NE 1996 12 12 CA960614021 2 19960308 G 7210 310924401 BEARING PWA AEROSP ATR42 ATR42* 8680900 EU PWA 120 PW120 NE RGB NR 15 BRG SPALLED W A K NONE O OTHER IN INSP/MAINT 1 CA 7573 121172 121172 (CAN)REDUCTION GEARBOX METAL CONTAMINATION. #15 BEARING SUFFERED A MAJOR FAILURE WITH SPALLING ON THE ROLLERS AND THE OU TER RACE. NOTE: ENGINE LOGS INDICATE THAT M50 BEARING MATERIAL PLATELETS WERE DISCOVE RED IN THE RGB 2 MONTHS BEFORE THI S FAILURE BUT NO FURTHER METAL WAS FOUND IN A SAMPLE TAKEN 10 DAYS LATER. 2 H 7 2 4T 4 T RT A53EU E20NE 1996121200251 19961212 00251 NE 1996 12 12 CA960614022 2 19960319 G 7250 MS969611 BOLTS EMB 120 EMB120 3260201 SO PWA 118 PW118 NE INTERSTAGE FLANG BROKEN W A K NONE O OTHER IN INSP/MAINT 1 CA 13584 115244 (CAN)BOLT FOUND LODGED IN POWER TURBINE BLADE ON ROUTINE BORESCOPE INSPECTION. 2 BROKEN BOLTS ON THE INTERSTAGE CASE FLA NGE. SEVERE CORROSION AT ALL BOLT POSITIONS OF THE INTERSTAGE CASE REAR FLANGE. THIS ENGINE WAS PRE SB 21175. 2 L 7 2 4T 4 T RT A31SO E20NE 1996121200252 19961212 00252 NE 1996 12 12 CA960614023 2 19960403 G 7230 311267601 CUP WASHER EMB 120 EMB120 3260201 SO PWA 118 PW118 NE #4 BEARNING UNIT WRONG PART W A K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 13693 115440 (CAN)OPERATOR REPORTED THE ENGINE MAKING A GROWLING NOISE. #4 BEARING FAILED DUE TO THE INSTALLATION OF THE WRONG PART N UMBER RETAINING NUT CUP WASHER. THE CUP WASHER INSTALLED, P/N 3112676-01 IS NOT APPLI CABLE TO THE PW118 AND IS TOO LARG E TO LOCK PROPERLY ON THE IMPELLER ASSEMBLY. 2 L 7 2 4T 4 T RT A31SO E20NE 1996121200253 19961212 00253 NE 1996 12 12 CA960614024 2 19960605 G 7210 311192701 BEARING PWA EMB 120 EMB120 3260201 SO PWA 118 PW118 NE RGB NR 8 BRG SPALLED W A K NONE O OTHER IN INSP/MAINT 1 CA 13400 3480 115307 115307 (CAN)REPORTED METAL ON THE CHIP DETECTOR. NOS.8, 9 & 15 BEARINGS SPALLED WITH #8 SHOWING THE MOST DAMAGE. THE CAGE OF #8 BEARING WAS BROKEN IN 2 PLACES AND HAD SECTIONS MISSING, SEVERAL ROLLERS WERE SEVERELY WORN. #15 BEARING HAD ELECTRICAL DISCHARGE PITTING WHICH APPEARS DUE TO LIGHTNING STRIKE. 2 L 7 2 4T 4 T RT A31SO E20NE 1996121200261 19961212 00261 SO 1996 12 12 CA960619031 2 19960610 G 8520 633976 COUNTERWEIGHT PL CONT MOONEY M20 M20K 5870220 SW CONT O360 IO360G 17025 SO CRANKSHAFT BROKEN W A UNSCHED LANDING E VIBRATION/BUFFET CR CRUISE 1 CA 875 A574M2 309568 (CAN) THE ENGINE DEVELOPED A SLIGHT VIBRATION INFLIGHT. THE ENGINE OIL PRESSURE & VACUUM SUCTION DROPPED TO ZERO. THE ST ANDBY VACUUM RESTORED SUCTION. THE ENGINE OPERATING TEMPERATURE INCREASED BUT STAYED IN THE GREEN. THE MANIFOLD PRESSURE WAS NORMAL. POST FLIGHT INSPECTION REVEALED THAT A CRANKSHAFT COUNTERWEIGHT PIN RETAINER PLATE HAD FAILED ALLOWING THE PIN TO FALL INTO THE CRANKCASE, THE LOOSE PIN FRACTURED AN INTAKE VALVE PUSH ROD CREATING A REDUCTION IN OIL PRESSURE. T HE VACUUM PUMP SHAFT SHEAR BUSHING ALSO FAILED. NO OBVIOUS CAUSE FOR THE RETAINER PLATE WAS DETERMINED. 1 L 7 1 3O 3 O 2A3 E1CE 1998041700402 19980417 00402 GL 1998 4 17 CA960619033 2 19960522 G 7250 23031938 NOZZLE ALLSN 250C 250C20R2 GL 2ND STAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 3121 CAT15310 (CAN) CRACKS FOUND IN THE BEND RADIUS OF THE SECOND STAGE NOZZLE DIAPHRAGM. NOZZLES SENT TO MANUFACTURER. PART TC: 4,2 14. 3 U E4CE 1998041700403 19980417 00403 GL 1998 4 17 CA960619034 2 19960522 G 7250 23031938 NOZZLE ALLSN 250C 250C20R2 GL 2ND STAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 3026 (CAN) CRACKS FOUND IN THE BEND RADIUS OF THE SECOND STAGE NOZZLE DIAPHRAGM. NOZZLES SENT TO MANUFACTURER. PART TC: 3, 694. 3 U E4CE 1998041700404 19980417 00404 GL 1998 4 17 CA960619035 2 19960522 G 7250 23031938 NOZZLE ALLSN 250C 250C20R2 GL 2ND STAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 2669 (CAN) CRACKS FOUND IN THE BEND RADIUS OF THE SECOND STAGE NOZZLE DIAPHRAGM. NOZZLES SENT TO MANUFACTURER. PART TC: 3,3 68. 3 U E4CE 1998041700405 19980417 00405 GL 1998 4 17 CA960619036 2 19960522 G 7250 23031938 NOZZLE ALLSN 250C 250C20R2 GL 2ND STAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 3499 (CAN) CRACKS FOUND IN THE BEND RADIUS OF THE SECOND STAGE NOZZLE DIAPHRAGM. NOZZLES SENT TO MANUFACTURER. PART TC: 3, 030. 3 U E4CE 1998041700406 19980417 00406 GL 1998 4 17 CA960619037 2 19960522 G 7250 23031938 NOZZLE ALLSN 250C 250C20R2 GL 2ND STAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 2498 (CAN) CRACKS FOUND IN THE BEND RADIUS OF THE SECOND STAGE NOZZLE DIAPHRAGM. NOZZLES SENT TO MANUFACTURER. TWO INCH LON G CRACK WITH CRAZE CRACKS OVER 50 PERCENT OF CIRCUMFERENCE. PART TC: 3,527. 3 U E4CE 1996122600537 19961226 00537 CE 1996 12 26 CA960620002 1 19960611 G 2436 REGULATOR CESSNA 172 172M 2072418 CE ALTERNATOR SYS MALFUNCTION W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING RUN-UP FOR OIL CHANGE THE ALTERNATOR SWITCH WAS CYCLED AND THE AMMETER SHOWED A FULL CHARGE. IN THE 'ON' PO SITION A NORMAL RATE OF CHARGE WAS NOTED. WITH THE MASTER IN THE 'OFF' POSITION THE PANEL LIGHTS BECAME VERY BRIGHT. THE AUTOMOTIVE VOLTAGE REGULATOR WAS REPLACED AND THE SYSTEM FUNCTIONED PROPERLY. 1 H 7 1 3O NT 3A12 1996121200269 19961212 00269 SO 1996 12 12 CA960620009 2 19960531 G 7314 3512 GASKET CONT 6381541 CESSNA 206 P206B 2073309 CE CONT O520 IO520A 17032 SO MCAULY 3A32C D3A32C88 GL FUEL PUMP LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 3167 3512 1107924A 711498 (CAN) SLIGHT LEAK AT FUEL PUMP BODY GASKET REPLACED 1 H 7 1 3O 3 O A4CE E5CE 5 C P21EA 1996122600551 19961226 00551 CE 1996 12 26 CA960620026 1 19960513 G 7910 AS9413117 O-RING LEAR 35 35A 5170602 CE GARRTT TFE731 TFE73122B 01518 WP L/H OIL CAP CUT W A E UNSCHED LANDING ENGINE SHUTDOWN K FLUID LOSS CR CRUISE 1 CA 2010 2010 P89737 (CAN) 'O' RING P/N AS9413-117 WAS DAMAGED WHEN OIL CAP WAS INSTALLED. CONDITION CAUSED OIL TO LEAK FROM ENGINE IN FLIGHT AND DUE TO LOW OIL PRESSURE, AN IN-FLIGHT SHUTDOWN WAS CARRIED OUT. AIRCRAFT LANDED WITH NO FURTHER INCIDENT. 'O' RING WAS REPLACED AND ENGINE SERVICED WITH OIL AND RETURNED TO SERVICE. 2 L 7 2 4F 4 F A10CE E6WE 1996121200276 19961212 00276 NE 1996 12 12 CA960620029 2 19960605 G 7260 310137101 BEARING EMB 120 EMB120 3260201 SO PWA 118 PW118 NE FUEL PUMP DRIVE SPALLED W A K NONE O OTHER IN INSP/MAINT 1 CA 18800 9823 115070 (CAN) ENGINE METAL CONTAMINATION. FUEL PUMP DRIVE BEARING HEAVILY SPALLED. 2 L 7 2 4T 4 T RT A31SO E20NE 1996121200278 19961212 00278 EA 1996 12 12 CA960620201 2 19960519 G 7414 1052945 ROTATING SHAFT BENDIX 105136029 PIPER PA28 PA28180 7102808 SO LYC O360 O360A3A 41514 EA WOODRUFF KEY SHEARED W K NONE O OTHER TX TAXI/GRND HDL 1 CA 803 L967436A (CAN) PILOT NOTICED A 250 RPM DROP ON THE RIGHT MAGNETO DURING RUN-UP, AS WELL AS SIGNIFICANT ROUGH RUNNING WHEN ONLY TH E RIGHT MAGNETO WAS SELECTED. AFTER SHUTDOWN THE RIGHT MAGNETO WAS REMOVED AND DISASSEMBLED. INSPECTION OF THE MAGNETO R EVEALED A SHEARED MAGNET SHAFT AT THE WOODRUFF KEY LOCATION. 1 L 7 1 3O 3 O 2A13 E286 1996122600556 19961226 00556 SO 1996 12 26 CA960625012 1 19960521 G 2701 62839000 SPROCKET PIPER PA28 PA28151 7102805 SO LYC O320 O320E3D 41508 EA CONTROL YOKE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 3977 L3284927A (CAN) ON ANNUAL INSPECTION, FOUND CONTROL YOKE SPROCKET CRACKED AT WELD. STOP PIN LOOSE BUT STILL IN PLACE. 1 L 7 1 3O 3 O 2A13 E274 1996121200289 19961212 00289 SO 1996 12 12 CA960625201 2 19960620 G 7414 103493542 FLYWEIGHTS BENDIX 103493501 BEECH 35 V35B 1151548 CE CONT O520 IO520BA 17032 SO MCAULY 3A32C 3A32C406 GL MAGNETO DESTROYED W D RETURN TO BLOCK E VIBRATION/BUFFET IN INSP/MAINT 1 CA A72932 22233373BA 922052 (CAN) FLYWEIGHTS JAMMED ON STOP PIN, WHICH SHEARED PIN. PIN AND FLYWEIGHTS WERE FOUND IN THE ENGINE OIL SUMP. THE ENGINE GEAR TRAIN WAS DAMAGED. THE FAILURE WAS DUE TO EXCESSIVE WEAR ON FLYWEIGHTS AND FLYWEIGHT AXLE. 1 L 7 1 3O 3 O 3A15 E5CE 5 C P21EA 1996122600561 19961226 00561 EU 1996 12 26 CA960703003 1 19960620 G 5510 G102 HORIZONTAL STAB GROB ASTIR G102STDAST3 EU ELEVATOR HINGE DELAMINATED W K NONE E VIBRATION/BUFFET CR CRUISE 1 CA 1101 (CAN) MOMENTARY CONTROL FLUTTER IN FLIGHT. UPON LANDING AN INSPECTION REVEALED THE MYLAR STRIP WHICH IS TAPED TO THE UPP ER SKIN AND EXTENDS OVER THE ELEVATOR CONTROL SURFACE WAS MISSING. THE UPPER SKIN LAMINATE DIRECTLY OVER THE TWO CENTRE HINGES FOR THE ELEVATOR HAD DELAMINATED FROM HINGE TAB. 1 K 0 0 0 0 G33EU 1996122600564 19961226 00564 1996 12 26 CA960703007 4 19960618 G 3422 5223874 AMPLIFIER BOEING 727 727 1384001 NM INST AMP LOOSE W A UNSCHED LANDING I FLT. ATTITUDE INST. CL CLIMB 1 CA (CAN) CAPTAINS GYRO FAILED ON ROTATION. AUXILIARY POSITON SELECTED, NO FIX. AIRCRAFT RETURNED. MAINTENANCE FOUND INSTRUM ENT AMP LOOSE IN ITS MOUNTING BRACKET. AMP HAD BEEN INSTALLED 2 MONTHS EARLIER. 2 L 7 3 4F A3WE 1996121200298 19961212 00298 EA 1996 12 12 CA960703013 1 19960528 G 5312 C2FS533 BULKHEAD DHAV DHAV DHC2 DHC2MK3 2800107 EA PWA PT6 PT6A27 52043 EA AFT FS 228 CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 11071 PCE42145 (CAN) AFT FULL BULKHEAD AT STA. 228 FOUND CRACKED ON BOTH LEFT AND RIGHT SIDES WHERE RUDDER CONTROL RODS PASS THROUGH TH E BULKHEAD. CRACKS RADIATE FROM HOLES 3/32" TO 1/2" TOWARDS THE VERTICAL STAB ATTACHMENT. TWO OTHER AIRCRAFT WERE FOUND WITH SAME CRACKS. 1 H 7 1 3T 4 T A806 E4EA 1996121200304 19961212 00304 EA 1996 12 12 CA960703019 1 19960717 G 2421 721428 ID GENERATOR SUNSTRAND CNDAIR CL600 CL6001A11 1900302 EA ENGINE GEARBOX DEFECTIVE W K NONE J WARNING INDICATION DE DESCENT 1 CA 305232 (CAN) GENERATOR TRIPPPING OFF LINE. METAL IN SCAVENGE FILTER AND ON CHIP DETECTOR. COMPONENT CAUSING TROUBLE WILL HAVE T O BE DETERMINED ON TEARDOWN. 2 L 7 2 4F RT A21EA 1999052800001 19990528 00001 1999 5 28 CA960703022 1 19960619 G 7810 CLIP ALLSN 501D 501D13D 03004 GL NR 1 ENGINE FAILED W E ENGINE SHUTDOWN J WARNING INDICATION NR NOT REPORTED 1 CA 124 501261 (CAN) POSSIBLE RUPTURE AND LOSS IN-FLIGHT OF ATTACHING BAND/CLIP ON THE EXHAUST PIPE OF NR 1 ENGINE CAUSING A FIRE ALARM IN THE EXHAUST PIPE ZONE. EMERGENCY PROCEDURES CARRIED OUT, ENGINE STOPPED AND PROPELLER FEATHERED. PRECAUTIONARY LA NDING MADE. 4 T E282 1996122600572 19961226 00572 NM 1996 12 26 CA960703033 1 19960613 G 2923 AO293 SEAL 65W01025 BOEING 720 720023B 1383841 NM PWA JT3D JT3D3B 52039 NE AUX PUMP BLOWN W K NONE K FLUID LOSS TX TAXI/GRND HDL 1 CA AO293 645267 (CAN) AFTER LANDING THE F E NOTICED AN ACCUMULATION OF HYDRAULIC FLUID IN AREA OF L/H WHEEL. FUNCTION CHECK CARRIED OUT AND FLUID WAS LEAKING FROM BETWEEN HEAD AND MAIN BODY OF AUXILIARY PUMP WHICH WAS REPLACED 2 L 7 4 4F 4 F 4A28 1E8 1996122600575 19961226 00575 CE 1996 12 26 CA960708001 1 19960616 G 2571 BATTERY BOX TUBE CESSNA 182 182Q 2072732 CE MCAULY 2A34C C2A34C204 GL BOX DRAIN BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 5160 773867 (CAN) BATTERY BOX DRAIN TUBE FOUND BROKEN AND HAD ALLOWED VAPOURS TO ENTER THE AREA UNDER THE BATTERY BOX AND CORRODE TH E STRUCTURE. 1 H 7 1 3O NT 3A13 5 C P3EA 1996121200319 19961212 00319 NE 1996 12 12 CA960708007 2 19960626 G 7210 310709001 BEARING PWA PWA 118 PW118 NE RGB NR 19 BRG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 115256 (CAN) THE REDUCTION GEARBOX (RGB) WAS SENT FOR INVESTIGATION AND REPAIR BECAUSE THE RGB WAS MAKING METAL. THE CAUSE OF T HE RGB MAKING METAL WAS AN AXIAL CRACK ON THE INNER RACE OF THE #19 BEARING AND THE SPALLING OF THE #18 BEARING INNER RI NG PLAIN HALF. 4 T E20NE 1996122600577 19961226 00577 NE 1996 12 26 CA960709001 2 19960626 G 7260 4002T00G09 DRIVE SPLINE SKRSKY S61 S61N 8142104 NE GE CT58 CT581101 30011 NE STARTER DRIVE DAMAGED W O OTHER O OTHER TX TAXI/GRND HDL 1 CA (CAN) DURING AN ATTEMPTED START, THE STARTER MOTOR WOULD NOT ENGAGE. ON REMOVING STARTER, ENGINE SIDE OF ENGAGE DRIVE BE CAME UNATTACHED. 2 G 7 2 4U 4 U 1H15 1E3 1996122600579 19961226 00579 GL 1996 12 26 CA960711002 2 19960702 G 7250 6898663 TURBINE BLADES SKRSKY S76 S76A 8143006 NE ALLSN 250C 250C30S 03013 GL 3 AND 4 STAGE DAMAGED W A UNSCHED LANDING Y ENGINE STOPPAGE CR CRUISE 1 CA (CAN) A #2 ENGINE ICP CHECK WAS BEING CONDUCTED WHEN #1 ENGINE WAS OBSERVED STARTING TO DECELERATE ACCOMPANIED BY A FUEL PRESSURE CAUTION LIGHT. WHILE TROUBLESHOOTING #1 ENGINE PROBLEM ENG FAILED. UPON SHUT DOWN AND INVESTIGATION, A POWER T URBINE FAILURE WAS OBSERVED. 1 G 7 2 3U 3 U H1NE E1GL 1996122600583 19961226 00583 SW 1996 12 26 CA960711011 1 19960618 G 5551 22123 BRACKET BLANCA 22123 BBAVIA 8 8GCBC 1220803 SW LYC O360 O360C2E 41514 EA MID LWR BRACKET CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 2797 4374 L188836A (CAN) CRACKS FROUND IN LEFT AND RIGHT ARM OF THE LOWER AFT STAB BRACKET. THIS PART HAS BEEN FOUND CRACKED BEFORE AND REP AIRED BY WELDING. THESE LATEST CRACKS WERE FOUND THROUGH OR NEXT TO THE PREVIOUS REPAIRS. WELD REPAIRS WERE ONCE AGAIN C ARRIED OUT. 1 H 7 1 3O 3 O A21CE E286 1996121200333 19961212 00333 EA 1996 12 12 CA960711012 2 19960703 G 8500 ENGINE BBAVIA 8 8GCBC 1220803 SW LYC O360 O360C2E 41514 EA POWER SECT VIBRATIONS W O OTHER E VIBRATION/BUFFET TX TAXI/GRND HDL 1 CA 530 L2155736A (CAN) PILOT REPORTED AN ENGINE VIBRATION THAT WAS MOST NOTABLE AT 1000-1200 RPM. PROP HAS BEEN OVERHAULED AND BALANCED, SWAPPED FROM A SISTER AIRCRAFT AND TRACKED CHECKED. CARBURETOR HAS BEEN CHECKED, VIBRATION WAS SEVERE ENOUGH TO LOOSEN T HE THROUGH BOLTS ON THE ALTERNATOR. DYNAMIC BALANCING IS GOING TO BE CARRIED OUT. 1 H 7 1 3O 3 O A21CE E286 1996121200334 19961212 00334 1996 12 12 CA960711013 1 19960708 G 2432 CBC182166 VENT CAP CONCORDEBATT CB35 BATTERY TOO SMALL W O OTHER K FLUID LOSS IN INSP/MAINT 1 CA 250 CBC182166 (CAN) BATTERY VENT CAPS WILL NOT REMAIN TIGHT DUE TO CAP THREADS POORLY MADE. THE THREADS SEEM TO BE TOO SMALL AND WOUL D NOT ENGAGE THE CELL COVERS ENOUGH TO STAY TIGHTSEVERAL OTHER AIRCRAFT CHECKED WITH SAME BATTERY MAKE AND HAVE THE SAME PROBLEM. EACH CAP HAS RUBBER CAP CONNECTED TO A VENT MANIFOLD THAT VENTS OVERBOARD. WHEN THE BATTERY CAP COMES LOOSE IN THE THREADS IN THE BATTERY, FLUID CAN SPILL OUT. 1996122600584 19961226 00584 CE 1996 12 26 CA960711014 1 19960709 G 7920 56001093 LINE ASSEMBLY CESSNA 414 414A 2075907 CE CONT O520 TSIO520NB 17040 SO WASTE GATE CHAFED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 278434R (CAN) WASTE GATE OIL SUPPLY LINE FOUND CHAFED ON ENGINE MOUNT BEAM FLANGE. P/N MS21919WCH4 CLAMP AND ASSOCIATED MOUNT BO LT, SPACER, WASHER AND NUT ALSO MISSING WHICH ALLOWED LINE TO DROP DOWN ONTO MOUNT BEAM FLANGE. SUBMITTER STATES AREA IS INCONVENIENT TO INSPECT AND THE DEFECT WAS ONLY FOUND DURING ENGINE CHANGE PROCESS. 1 L 7 2 3O 3 O A7CE E8CE 1996122600585 19961226 00585 CE 1996 12 26 CA960711015 1 19960606 G 2620 RETAINING CLIP RAYTHN 1015700215 BEECH 90 C90A 1152911 CE PWA PT6 PT6A21 52043 EA FIRE EXT SWITCH FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 2295 PCE25637 (CAN) ON INSPECTION OF THE ENGINE FIRE EXTINGUISHER ELECTRICAL SYSTEM, IT WAS NOTED THAT THE FIRE EXTINGUISHER MICROSWIT CH ON THE PANEL ACTIVATING BUTTON HAD COME OFF THE HOLDING CLIP, RENDERING THE BUTTON INOPERATIVE. THE SWITCH MANUFACTUR ER - RAYTHEON - INDICATES THAT A REPLACEMENT SWITCH IS BEING PRODUCED. 1 L 7 2 3T 4 T RT 3A20 E4EA 1996122600587 19961226 00587 SO 1996 12 26 CA960711201 1 19960618 G 2435 603871 FLANGE AUXILEC 8013C PIPER PA31T PA31T2 7103127 SO PWA PT6 PT6A135 52043 NE START/GEN BROKEN LEGS W K NONE O OTHER IN INSP/MAINT 1 CA 954 PCE92560 (CAN) THE STARTER/GENERATOR QUICK ATTACH-DETACH FLANGE WAS FOUND TO HAVE BROKEN LEGS DURING AN INSPECTION. THE PILOT NOT ED A DIFFERENT NOISE WHILE STARTING THE AIRCRAFT. 1 L 7 2 3T 4 T RT A8EA E4EA 1996121200337 19961212 00337 1996 12 12 CA960712103 4 19960702 G 3445 TRANSPONDER AIRBUS 310 A310300 EU TCAS SYS MALFUNCTION W K NONE N FALSE WARNING CR CRUISE 1 CA (CAN) WHILE VMC AT FL350 IN LEVEL FLIGHT NEAR THE AUTUN VOR, AIRCRAFT EXPERIENCED AT FULL TCAS ADVISORY & RESOLUTION. FI RST A TARGET DISPLAYED ON THE IVSI AT THE 2-3 O'CLOCK POSITION AT 2-3 NM RANGE AT THE SAME ALTITUDE, ACCOMPANIED BY AN A URAL WARNING. APPROXIMATELY 2 SECONDS LATER THE IVSI/TCAS LIT UP RED DIRECTING A CLIMB ACCOMPANIED WITH AN AURAL CLIMB C OMMAND. VISUAL CONFIRMATION COMBINED WITH UNREALISTIC SPEED OF THE WARNING SEQUENCE LED CREW TO SUSPECT VALIDITY OF WARN ING. THIS INCIDENT OCCURRED IN IMC CONDITIONS & WAS BELIEVED AT THE TIME TO BE A NEAR MISS. THE TCAS AND TRANSPONDER COM PUTERS WERE REPLACED AND ARE BEING EVALUATED. 2 L 7 2 4F RT A35EU 1998050100204 19980501 00204 CE 1998 5 1 CA960715004 1 19960717 G 2710 55653813 QUADRANT CESSNA 501 501 2076603 CE LT AILERON CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 15055 (CAN) DURING ROUTINE INSPECTION, THE LT AILERON QUADRANT WAS SUSPECTED TO BE CRACKED. AS A PRECAUTION, THE RT QUADRANT WAS INSPECTED AS WELL. THE LT QUADRANT WAS REPLACED AND RT WAS CHECKED BY EDDY CURRENT AND FOUND TO BE SERVICEABLE. P ART TC: 18,996. 1 L 7 2 4F A27CE 1996122600596 19961226 00596 1996 12 26 CA960715201 4 19960709 G 2562 0025004 BATTERY MARTECH EB2BCD MOONEY M20 M20E 5870212 SW LYC O360 IO360A1A 41514 EA ELT LEAKING W K NONE O OTHER IN INSP/MAINT 1 CA 8546 L41751 (CAN) ON ROUTINE INSPECTION OF THE ELT CORROSION WAS NOTED ON THE LOWER END OF THE CASE. INVESTIGATION FOUND THE BATTERY HAD LEAKED AND CORRODED THE INSIDE OF THE CASE AND BOTTOM OF THE PC BOARD. 1 L 7 1 3O 3 O 2A3 1E10 1996122600603 19961226 00603 NM 1996 12 26 CA960716009 1 19960618 G 3320 BA080061 BALLAST BRUCE DHAV DHC8 DHC8101 2809002 NM SEAT ROW 7 BURNT W K NONE B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA (CAN) SMOKE IN CABIN COMING FROM BUFFET CEILING. OVERHEAD PANELS REMOVED AND MAINTENANCE FOUND INOPERATIVE LIGHTS AT SEA T ROW 7. TWO BALLASTS WERE FOUND FAULTY. BOTH UNITS WERE AT MOD 'D' STATUS. MOD 'G' INTRODUCED DESIGN CHANGES TO PREVENT THESE OCCURRENCES. 2 H 7 2 4T RT A13NM 1996121200343 19961212 00343 EA 1996 12 12 CA960722001 2 19960711 G 8530 VALVE SEAT PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA #6 CYLINDER DISLODGED W K NONE O OTHER TX TAXI/GRND HDL 1 CA 660 L1449868A (CAN) AFTER LANDING THE PILOT NOTICED THE NR 2 ENGINE WAS RUNNING ROUGH AT IDLE. INVESTIGATION FOUND THERE WAS NO COMPRE SSION ON #6 CYLINDER. AFTER THE CYLINDER WAS REMOVED IT WAS REVEALED THE EXHAUST VALVE SEAT WAS DISLODGED FROM THE CYLIN DER AND HOLDING THE VALVE PARTLY OPEN. 1 L 7 2 3O 3 O A20SO E14EA 1996122600617 19961226 00617 SW 1996 12 26 CA960722008 1 19960711 G 2730 31072 CONTROL CABLE 31072 BBAVIA 8 8GCBC 1220803 SW LYC O360 O360C2A 41514 EA ELEV AFT PULLY FRAYED W K NONE O OTHER IN INSP/MAINT 1 CA L1868036A (CAN) ON INSPECTION THE ELEVATOR CABLE WAS FOUND FRAYED WHERE IT PASSES OVER THE UPPER REAR PULLEY. 1 H 7 1 3O 3 O A21CE E286 1998050100206 19980501 00206 GL 1998 5 1 CA960723016 2 19960626 G 7260 6894171 BEARING ALLSN 250C 250C20B 03013 GL GEARBOX MAKING METAL W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA 4430 CAE835686 (CAN) NR 2 ENGINE MAGNETIC PLUG WARNING LIGHT CAME ON IN-FLIGHT. PILOT REDUCED POWER TO IDLE ON NR 2 ENGINE AND RETURNE D TO RAMP. LOWER MAGNETIC PLUG HAD HEAVY ACCUMULATION OF FINE METAL PARTICLES. FURTHER INVESTIGATION REVEALED THAT NR 2 1/2 BEARING WAS THE SOURCE OF METAL AND THE SPUR ADAPTER GEAR SHAFT WHERE NR 2 1/2 BEARING RIDES HAS DAMAGE FROM THE B EARING. 3 U E4CE 1997010200219 19970102 00219 EA 1997 1 2 CA960723557 1 19960709 G 2432 160458005 FIN STOCK 237BC1011C CNDAIR CL600 CL6002B16 1900305 EA BATTERY CHARGER LOOSE W K NONE B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 CA 9 262 (CAN) CONVOLUTED FIN STOCK IS BONDED INTO PLACE AS A 'HEAT SINK' IN THE BATTERY CHARGER. THE STOCK CAME LOOSE AND AS THE TECHNICIAN WAS CHECKING SOME COMPONENTS IT CAME IN TOUCH WITH A POWERED TRANSISTOR CAUSING A SHORT. ARCING OCCURRED. SE VEN OTHER UNITS WERE FOUND WITH THE SAME PROBLEM OF A LOOSE FIN STOCK. 2 L 7 2 4F RT A21EA 1998050100207 19980501 00207 1998 5 1 CA960724402 4 19960621 G 3460 13442RE DATA BASE CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE FLT MANAGMNT SYS ERROR W K NONE O OTHER AP APPROACH 1 CA (CAN) WHEN DOING A FLIGHT MANAGEMENT SYSTEM APPROACH, FMS DISENGAGED AND STEERING COMMANDS WENT OFF THE SCREEN. PILOT U NABLE TO RE-ENGAGE APPROACH. AIRCRAFT PERFORMED CORRECTLY ON NORMAL APPROACH (ILS). WHILE UNDER INVESTIGATION, MANUFAC TURER CONTACTED AND THEY INFORMED SUBMITTER THAT THE DATABASE WAS IN ERROR AND UPDATED DISKS WERE SENT TO INSTALL NEW UP DATED DATABASE. 1 L 7 2 4F 4 F A22CE E1NE 1997010200224 19970102 00224 SO 1997 1 2 CA960724403 2 19960726 G 8520 40644 MAIN BEARING TMPSON NAVION NAVIONA 6150104 SW CONT E225 E2254 17015 SO CRANKCASE SEIZED W K NONE O OTHER IN INSP/MAINT 1 CA 770 30025D34 (CAN) CRANKCASE ASSEMBLY RECEIVED FOR INSPECTION AFTER REPORTS OF HIGH OIL TEMPERATURE, LOW OIL PRESSURE AND STIFFNESS O F PROP ROTATION. CRANKCASE DISMANTLED, CLEANED AND INSPECTED. INSPECTION FOUND THE #5 MAIN BEARING SEIZED. FAILURE TYPIC AL OF OIL STARVATION, FURTHER INSPECTION REVEALED A LARGE AMOUNT OF RUBBER DEBRIS IN THE SUCTION TUBE, CHOKING THE SUCTI ON SCREEN. CRANKCASE OVERHAULED. 1 L 7 1 3O 3 O A782 E267 1998050100208 19980501 00208 WP 1998 5 1 CA960729001 1 19960716 G 7921 315341 ACTUATOR CVAC 340 340CVAC 242270A WP OIL COOLER DOOR FAILED W A E UNSCHED LANDING ENGINE SHUTDOWN M OVER TEMP CL CLIMB 1 CA 879 (CAN) FLIGHT CREW ON CLIMB-OUT NOTICED NR 2 ENGINE OIL TEMP HIGH AT APPROX 85 DEGREES CELSIUS. OIL COOLER DOOR WAS MANU ALLY SELECTED OPEN TO COOL OIL. DID NOT RECTIFY PROBLEM. POWER LEVEL RETARDED TO 1,000 H.P., NO CHANGE. OIL TEMP CONT INUED TO RISE AND WAS E-HANDLED AT 100 DEGREES CELSIUS. REPLACED OIL COOLER AND AIRCRAFT DEPARTED WITH NO FURTHER PROBL EMS. AIRCRAFT TT: 20,551 HOURS. 2 L 7 2 4R 6A6 1997121800386 19971218 00386 CE 1997 12 18 CA960729006 1 19960722 G 3230 99810022 PLATE 5081033513 BEECH 100 A100 1152915 CE DRAG BRACE BENT W O OTHER J WARNING INDICATION LD LANDING 1 CA 1310 XL95206 (CAN) RIGHT HAND DOWN LOCK PLATE BENT ON LANDING GIVING UNSAFE GEAR. 1 L 7 2 3T A14CE 1997121800387 19971218 00387 CE 1997 12 18 CA960729007 1 19960717 G 2752 505211516 PISTON 505212224 BEECH 90 C90A 1152911 CE PWA PT6 PT6A21 52043 EA RT FLAP ACTUATOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 2544 944D91 PCE25636 (CAN) DURING ROUTINE MAINTENANCE IT WAS OBSERVED THAT THE RIGHT HAND INBOARD FLAP ACTUATOR PISTON WAS CRACKED ALONG ITS LENGTH. CRACK ORIGINATED AT THE PLUG HOLE. REFERENCE BEECH IPC 27-50-30, FIG 50-30, ITEM 15. SDR 960807007 PERTAINS TO S AME CONDITION. 1 L 7 2 3T 4 T RT 3A20 E4EA 1997010200233 19970102 00233 SO 1997 1 2 CA960729010 2 19960709 G 8520 MAIN BEARINGS CONT O470 O470K 17026 SO #2 & #3 BEARING SPUN W K NONE O OTHER IN INSP/MAINT 1 CA 1040 486559K (CAN) ENGINE WAS UNABLE TO MAINTAIN MINIMUM OIL PRESSURE IN CRUISE AND PROP CONTROL WAS DIFFICULT. ENGINE WAS DISMANTLED FOR INSPECTION WHICH REVEALED #2 & #3 MAINS HAD SPUN IN THE CRANKCASE. CRANKCASE ASSEMBLY OVERHAULED AND ENGINE WAS RE TURNED TO SERVICE. 3 O E273 1998050100209 19980501 00209 GL 1998 5 1 CA960729014 1 19960522 G 6710 206062721011 ACTUATOR BELL 206 206L 1181522 SW ALLSN 250C 250C20R2 GL ENG GOV FAILURE W E ENGINE SHUTDOWN R PARTIAL RPM/PWR LOSS TX TAXI/GRND HDL 1 CA CAE831288 (CAN) AFTER STARTING THE ENGINE, THE PILOT WAS UNABLE TO RAISE THE ROTOR RPM ABOVE 90 PERCENT NR. THERE WAS NO BEEP TRI M RANGE AVAILABLE AND THE ENGINE WAS SHUT DOWN. ON INSPECTION, FOUND THE INTERNAL STOP OF THE LINEAR ACTUATOR HAD FAILE D AND THE SHAFT WAS OVER EXTENDED PUTTING THE ENGINE GOVERNOR AT FULL DECREASE. THE SHAFT HAD BEEN EXTENDED TO THE POIN T THAT ITS THREADS AND THE THREADS OF THE ACTUATING SCREW HAD SEPARATED MAKING IT UNABLE TO RETRACT. 1 G 7 1 3U 3 U H2SW E4CE 1997010200237 19970102 00237 NE 1997 1 2 CA960729016 2 19960717 G 7210 310709001 BEARING PWA PWA 118 PW118 NE RGB NR 19 SPALLED W K NONE O OTHER IN INSP/MAINT 1 CA 115321 (CAN) THE ENGINE, WHICH WAS MAKING METAL, WAS SENT FOR INVESTIGATION/OVERHAUL. DISASSEMBLY FOUND THE #19 BEARING IN THE REDUCTION GEARBOX SPALLED ON THE INNER RACE. THIS IS THE CAUSE OF THE RGB MAKING METAL. THERE WERE NO CONTRIBUTING FACTO RS FOR THE #19 BEARING SPALLING, THEREFORE THIS IS CONSIDERED TO BE A PRIMARY FAILURE OF THE #19 BEARING. THE BEARING WA S REPLACED. 4 T E20NE 1997121800389 19971218 00389 CE 1997 12 18 CA960729019 1 19960702 G 2730 MS178254 CASTLE NUT 26121191 CESSNA 208 208B 2073701 CE AFT ELEVATOR MISSING W K NONE O OTHER IN INSP/MAINT 1 CA 119 (CAN) AFT TAIL ACCESS PANEL WAS REMOVED AND AFT ELEVATOR BELLCRANK PIVOT WAS FOUND TO BE MISSING THE CASTLE NUT AND COTT ER PIN. INSTALLED AND AIRCRAFT RETURNED TO SERVICE. 1 H 7 1 3T A37CE 1998020500595 19980205 00595 CE 1998 2 5 CA960731001 1 19960713 G 3260 903610373 SWITCH BEECH 90 C90A 1152911 CE PWA PT6 PT6A21 52043 EA LEFT MAIN FAILED W L ABORTED APPROACH N FALSE WARNING AP APPROACH 1 CA PCE25664 (CAN) ON LANDING GEAR DOWN AND LOCKED, PILOT SELECTED FULL FLAPS AND THE RED LIGHT IN THE GEAR HANDLE CAME ON, WITH GEAR WARNING HORN ACTIVATED. AIRCRAFT LANDED OK AFTER TOWER CONFIRMATION OF GEAR DOWN. INVESTIGATION FOUND THE LEFT MAIN DOW N LOCK SWITCH ASSEMBLY HAD FAILED. SWITCH REPLACED, BUT THEN FAILED AGAIN A COUPLE OF DAYS LATER. REPLACED AGAIN AND OK THIS TIME. 1 L 7 2 3T 4 T RT 3A20 E4EA 1997010200255 19970102 00255 EA 1997 1 2 CA960801014 1 19960626 G 2915 6607P96A PRESSURE SWITCH CONSOLCNTRLS DHAV DHC6 DHC6300 EA PWA PT6 PT6A27 52043 EA HYDRAULIC SYSTEM LOW SETTTING W K NONE O OTHER NR NOT REPORTED 1 CA 2757 PCE42076 (CAN) DURING INSPECTION IT WAS FOUND THAT THE HYDRAULIC SYSTEM WAS PRODUCING ONLY 1350 PSI. CORRECT PRESSURE IS 1575. A NEW PRESSURE CUTOUT SWITCH WAS INSTALLED. 1 H 7 2 3T 4 T A9EA E4EA 1997010200256 19970102 00256 EA 1997 1 2 CA960801015 1 19960720 G 7500 BELLOWS C6VE10231C DHAV DHC6 DHC6300 EA PWA PT6 PT6A27 52043 EA RT BLEED AIR CRACKED W H DEACTIVATE SYST/CIRCUITS O OTHER TX TAXI/GRND HDL 1 CA 25822 PCE42076 (CAN) RIGHT HAND BLEED AIR SYSTEM NOT RESPONDING TO SELECTOR SWITCH IN THE COCKPIT. INVESTIGATION FOUND THAT BLEED AIR D UCT BELLOWS HAD FAILED AND WAS ALLOWING AIR TO ESCAPE AT ALL TIMES. 1 H 7 2 3T 4 T A9EA E4EA 1997010200257 19970102 00257 EA 1997 1 2 CA960801016 1 19960720 G 7500 BELLOWS C6VE10081C DHAV DHC6 DHC6300 EA PWA PT6 PT6A27 52043 EA RT ENG BLEED FAILED W H DEACTIVATE SYST/CIRCUITS O OTHER TX TAXI/GRND HDL 1 CA 25844 PCE42076 (CAN) DURING TAKEOFF CHECKS IT WAS NOTED THERE WAS NO CHANGE IN RIGHT HAND ENGINE INDICATION WHEN BLEED AIR WAS SELECTED ON. MAINTENANCE FOUND THE BLEED AIR LINE HAD FAILED AT THE EXPANSION BELLOWS ALLOWING BLEED AIR TO ESCAPE AT ALL TIMES. 1 H 7 2 3T 4 T A9EA E4EA 1998041700408 19980417 00408 GL 1998 4 17 CA960801021 2 19960726 G 7230 6876667 EXDUCER BELL 206 206L 1181522 SW ALLSN 250C 250C20B 03013 GL COMPRESSOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA CAE830970 (CAN) WHILE DOING A TURBINE CHANGE, AME FOUND A CRACK IN THE COMPRESSOR DISCHARGE TUBE. SUSPECT CRACK WAS CAUSED BY ME CHANICAL DAMAGE. 1 G 7 1 3U 3 U H2SW E4CE 1998041700411 19980417 00411 EU 1998 4 17 CA960802004 1 19960726 G 2700 L1340213A402092M CABLES LET L13 L13BLANIK 1360306 EU PULLEYS WORN W K NONE O OTHER IN INSP/MAINT 1 CA 1304 (CAN) WHILE CARRYING OUT AN ITRAN INSPECTION, A MOUSE NEST PROMPTED AN INSPECTION FOR CORROSION UNDER THE COCKPIT FLOOR. CABLES IN THAT AREA WERE FOUND TO HAVE AN UNACCEPTABLE AMOUNT OF BROKEN WIRES IN THE AREA OVER THE PULLEYS. THE PREVI OUS LOGS SHOW THAT THE CABLES WERE REPLACED IN JULY OF 1995. AN AME FAMILIAR WITH THIS AIRCRAFT TOLD THE SUBMITTER THAT THIS AREA HAS HAD PROBLEMS BEFORE. 1 K 0 0 G24EU 1997121800391 19971218 00391 CE 1997 12 18 CA960802007 1 19960726 G 3240 0690190 ANCHOR BOLT CLEVELAND 07517100 CESSNA 208 208B 2073701 CE RH AXLE MISSING NUT W K NONE O OTHER TX TAXI/GRND HDL 1 CA 226 (CAN) THE ANCHOR BOLT IS NORMALLY ATTACHED TO THE AXLE TORQUE PLATE WITH AN FIBER LOCKNUT (P/N AN 365). ON THIS OCCURREN CE THE LOWER ANCHOR BOLT ON THE RH SIDE LOST THE ATTACHMENT NUT WHICH CAUSED THE BOLT TO BACK OUT OF THE TORQUE PLATE AN D COME IN CONTACT WITH THE WHEEL HALF BOLTS. THIS CONDITION CAUSED DAMAGE TO THE TORQUE PLATE, WHEEL HALF BOLTS, ANCHOR BOLT AND BRAKE UNIT. THE LOCKNUTS ON THE OTHER ANCHOR BOLTS WERE CHECKED AND IT WAS FOUND THAT THE GREEN NYLON INSERT WA S SQUEEZED OUT PART WAY, IN SOME CASES, LESS THAN 1/2 A THREAD WAS SHOWING. IT IS RECOMMENDED ADJUSTING THE THICKNESS OF THE WASHERS AND USING A STEEL LOCKNUT. 1 H 7 1 3T A37CE 1997121800395 19971218 00395 CE 1997 12 18 CA960807007 1 19960730 G 2752 505211958 PISTON BEECH 505212234 BEECH 90 C90A 1152911 CE FLAP ACTUATOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 119 847B93 (CAN) DURING OPERATION IN GROUND CHECK THE FLAP WAS NOTED TO BE NOISY. TRACKS LUBED TO NO EFFECT. INVESTIGATION FOUND TH E ACTUATOR PISTON WAS SPLIT ALONG ITS LENGTH, APPROXIMATELY 4.5 INCHES FROM THE END.NEW ACTUATOR INSTALLED AND RIGGING C HECKS COMPLETED. SDR 960729007 PERTAINS TO SAME CONDITION. 1 L 7 2 3T RT 3A20 1997010200272 19970102 00272 NE 1997 1 2 CA960808012 2 19960731 G 7210 310924401 BEARING PWA 120 PW120 NE RGB NR 15 SPALLED W K NONE O OTHER NR NOT REPORTED 1 CA 13930 5772 120481 (CAN) THE REDUCTION GEARBOX (RGB) WAS FOUND BY THE OPERATOR TO HAVE METAL CONTAMINATION. DISASSEMBLY OF THE RGB REVEALED THE SOURCE OF THE METAL CONTAMINATION WAS THE #15 BEARING WHICH HAD SPALLED BADLY ON THE OUTER RACE. SECONDARY DAMAGE F ROM THE CONTAMINATES WAS RESTRICTED TO SEVERAL OTHER BEARINGS AND NO GEARS WERE FOUND DAMAGED SUFFICIENTLY TO REQUIRE RE PLACEMENT. 4 T E20NE 1997010200273 19970102 00273 NE 1997 1 2 CA960808013 2 19960731 G 7250 MS969611 BOLT PWA PW121 PW121 52124 NE INTERSTAGE CASE BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 12457 120870 (CAN) THE ENGINE WAS UNDERGOING ROUTINE INSPECTION AND WAS OBSERVED TO HAVE SUSTAINED CONSIDERABLE POWER TURBINE DAMAGE. DISASSEMBLY FOUND THE ENGINE HAD SUFFERED A FRACTURE OF ONE INTERSTAGE CASE BOLT, WHICH RELEASED THE BOLT HEAD WHICH WA S SUBSEQUENTLY INGESTED BY THE POWER TURBINE CAUSING EXTENSIVE SECONDARY DAMAGE. THE INTERSTAGE CASE REAR FLANGE WAS COR RODED IN THE LOCATION THAT THE BOLT FAILED, WITH THE CORROSION PRODUCTS INCREASING THE LOCAL FLANGE THICKNESS CONSIDERAB LY, RESULTING IN BOLT STRETCH AND FAILURE. 4 T E20NE 1997010200274 19970102 00274 NE 1997 1 2 CA960808014 2 19960729 G 7210 310924401 BEARING PWA 119 PW119B NE RGB NR 15 SPALLED W K NONE O OTHER IN INSP/MAINT 1 CA 5095 116023 (CAN) THE REDUCTION GEARBOX (RGB) WAS FOUND TO HAVE METAL CONTAMINATION. DISASSEMBLY OF THE RGB REVEALED THE SOURCE OF T HE METAL CONTAMINATION WAS THE #15 BEARING WHICH HAD SPALLED BADLY ON THE INNER RACE, AROUND APPROXIMATELY 90 PERCENT OF THE CIRCUMFERENCE. SECONDARY DAMAGE FROM THE CONTAMINATS WAS RESTRICTED TO THREE OTHER SECOND STAGE BEARINGS. 4 T E20NE 1997121800400 19971218 00400 CE 1997 12 18 CA960813005 1 19960807 G 5520 3361000039 FITTING BEECH 33610000609 BEECH 36 A36 1151604 CE CONT O550 IO550B SO LT RT ELEV WORN W K NONE O OTHER IN INSP/MAINT 1 CA 675757 (CAN) ON BOTH LEFT HAND AND RIGHT HAND ELEVATOR THE LOWER BOLT (P/N AN23-10A) COULD BE TURNED BY HAND 1 L 7 1 3O 3 O 3A15 E3SO 1997030600669 19970306 00669 CE 1997 3 6 CA960826018 1 19960809 G 3710 3116D HOSE FITTING CESSNA 182 182A 2072704 CE CONT O470 O470L 17026 SO VAC HOSE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 803709L4 (CAN) DURING INSPECTION OF THE VACUUM HOSE FITTING. THE "B" NUT WAS FOUND CRACKED. SUBMITTER SUSPECTS THAT AN OVERTORQUI NG OF THE NUT TOOK PLACE. 1 H 7 1 3O 3 O NT 3A13 E273 1998111300568 19981113 00568 1998 11 13 CA960826046 1 19960812 G 2822 TF70251 BEARING TRW TF57800 ARMATURE UNAPPROVED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA TF784743W (CAN) OEM USES ONLY N.D. BEARINGS. BEARING REMOVED WAS MANUFACTURED BY FAFNIR. 1998111300569 19981113 00569 1998 11 13 CA960826047 1 19960812 G 2110 CYRB234 BEARING BARBERCOL SYLC9868 ARMATURE UNAPPROVED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 695 (CAN) BEARING REMOVED HAS NO MANUFACTURERS NAME ON IT. OEM USES BEARINGS MADE BY NMB. 1998111300570 19981113 00570 1998 11 13 CA960826048 1 19960812 G 2822 1075256 BEARING DELCO A7535A1 ARMATURE UNAPPROVED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 65439 (CAN) OEM USES ONLY NEW DEPARTURE BEARING. BEARING REMOVED WAS AN MRC. 1998111300571 19981113 00571 1998 11 13 CA960826049 1 19960812 G 2822 5331514 BEARING DELCO A7535A1 ARMATURE UNAPPROVED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 65439 (CAN) OEM USES ONLY N.D. BEARING, REMOVED WAS A SMT. 2000020500767 20000205 00767 2000 2 5 CA960826050 1 19960812 G 7714 X12060 BEARING AG34 TACHOMETER GEN WRONG PART W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 35268 (CAN) OEM USES NMB BEARINGS, BEARING REMOVED WAS NEW DEPARTURE. 1998111300572 19981113 00572 1998 11 13 CA960826051 1 19960812 G 6220 X12061 BEARING SUNDSTRANDEM AG34 MAIN ROTOR UNAPPROVED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 25268 (CAN) OEM USES BEARINGS MANUFACTURED BY NMB. BEARING REMOVED WAS MADE BY NEW DEPARTURE. 1998111300573 19981113 00573 1998 11 13 CA960826052 1 19960812 G 6220 8492071 BEARING LUCAS 32005007 MAIN ROTOR UNAPPROVED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 208114 (CAN) OEM PUTS THEIR PART NUMBER ON THE BEARING. BEARING REMOVED DID NOT HAVE PROPER PART NUMBER ON IT. 1998111300574 19981113 00574 1998 11 13 CA960826053 1 19960812 G 2822 STE48 BEARING INTERTECHNIQ 2070C11 ARMATURE UNAPPROVED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 2035 (CAN) OEM USES BEARING WITH A 'O' FRICTION TYPE SEAL. BEARING REMOVED HAD STANDARD SEAL. 1998111300575 19981113 00575 1998 11 13 CA960826054 1 19960812 G 2822 226603 BEARING 1227232000 ARMATURE UNAPPROVED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA PE2427 (CAN) OEM USES IKS HALF SEALED, HALF SHIELDED BEARING. BEARING REMOVED WAS SEALED ON BOTH SIDES AND MADE BY MRC. 1998111300576 19981113 00576 1998 11 13 CA960826055 1 19960812 G 2822 4045685 BEARING HYDROAIRE 85816 ARMATURE UNAPPROVED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA H208 (CAN) OEM USES SKF BEARING. BEARING REMOVED HAD NO NAME ON IT. 1998111300577 19981113 00577 1998 11 13 CA960826056 1 19960812 G 2822 4045685 BEARING HYDROAIRE 85816 ARMATURE UNAPPROVED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA H922A (CAN) OEM USES BEARING MANUFACTURED BY SKF. BEARING REMOVED WAS MADE BY MRC. 1998111300578 19981113 00578 1998 11 13 CA960826057 1 19960812 G 2822 TF70251 BEARING TRW TF57800 ARMATURE UNAPPROVED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA TF84743W (CAN) OEM USES ONLY N.D. BEARINGS. BEARING REMOVED WAS MANUFACTURED BY FAFNIR. 1998111300579 19981113 00579 1998 11 13 CA960826058 1 19960812 G 2435 07111337 BEARING LUCAS 23064001 ARMATURE UNAPPROVED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 2710 (CAN) OEM USES PART NUMBER STAMPED ON BEARING. BEARING REMOVED WAS MADE BY NORMA AND DID NOT HAVE PROPER NUMBER ON IT. 1998111300580 19981113 00580 1998 11 13 CA960826059 1 19960812 G 2435 07111259 BEARING LUCAS 23064001 ARMATURE UNAPPROVED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 2710 (CAN) OEM USES BEARING MADE BY BARDEN AND HAS THEIR PART NUMBER STAMPED ON IT. BEARING REMOVED WAS MADE BY FAG. 1998111300581 19981113 00581 1998 11 13 CA960826060 1 19960812 G 2822 RD56167 BEARING ROMEC RG52400D ARMATURE UNAPPROVED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA B1969 (CAN) OEM USES SEALED 39PP FAFNIR BEARING. BEARING REMOVED WAS SHIELDED. 1998111300582 19981113 00582 1998 11 13 CA960826061 1 19960812 G 2822 RD561661 BEARING ROMEC RG52400D ARMATURE UNAPPROVED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA B1969 (CAN) OEM USES NMB BEARING WITH 'O' FRICTION MICARTA SEALS. BEARING REMOVED HAD NO MANUFACTURERS NAME ON IT. 1997010200300 19970102 00300 NM 1997 1 2 CA960826068 1 19960628 G 3320 1640513 CONNECTOR DHAV DHC8 DHC8301 NM COCKPIT OVERHEATED W E ENGINE SHUTDOWN B M SMOKE/FUMES/ODORS/SPARKS OVER TEMP TX TAXI/GRND HDL 1 CA (CAN) ON POST ENGINE START CHECK, CREW NOTICED AN ELECTRICAL BURNING SMELL FOLLOWED BY SMOKE FROM BEHIND THE COPILOT'S S EAT. SMOKE COMING FROM THE OVERHEAD BIN CONNECTOR THAT HAD SEVERELY OVERHEATED. 2 H 7 2 4T RT A13NM 1997011600940 19970116 00940 1997 1 16 CA960826070 1 19960809 G 2435 PLUG LUCAS BCO9101 PWA PT6 PT6A50 52043 EA SHAFT STARTR GEN FOD W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 0 86011 (CAN) WHILE CARRYING OUT SERVICE BULLETIN 4182, SPLIT SHAFT INSTALLATION, THE REAR CASE HAD TO BE OPENED. A 3/4" X 1/4" ROUND PLUG THREADED ON ONE END WAS FOUND LYING IN THE BOTTOM OF THE CASE. A PRATT & WHITNEY SERVICE REP WAS ON SITE & ID ENTIFIED THE PLUG AS HAVING CAME FROM THE END OF THE STARTER GENERATOR SHAFT. THE STARTER GENERATOR WAS INSPECTED & THE PLUG WAS FOUND PROPERLY INSTALLED. THERE WAS NO WAY OF DETERMINING WHERE THE PLUG CAME FROM OR HOW LONG IT HAD BEEN IN T HE CASE. IT IS A LUCAS MODIFICATION TO PUT THE PLUG IN THE STARTER GENERATOR SHAFT. TO GET INTO THE CASE THE PLUG WOULD HAVE TO HAVE GONE THROUGH THE AIR OIL SEPARATOR & THEN DROP INTO THE CASE. 4 T E4EA 1997011600943 19970116 00943 EA 1997 1 16 CA960826074 1 19960814 G 2421 0085 SENSE WIRE SUNDSTRAND 722822 CNDAIR CL600 CL6002A12 1900304 EA GEN FIELD OPENED W O OTHER O H OTHER ELECT. POWER LOSS-50 PC DE DESCENT 1 CA 0085 (CAN) ON DESCENT GENERATOR FAILED. TROUBLE SHOOTING FOUND OPEN FIELD SENSE WIRE 2 L 7 2 4F RT A21EA 1997011600944 19970116 00944 EA 1997 1 16 CA960826075 1 19960811 G 3320 BV501258 RECEPTACLE CNDAIR CL600 CL600* EA GALLEY SHORTED W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA (CAN) FLOURESCENT LIGHT ASSEMBLY LOCATED BEHIND COFFEE MAKER HAD A SHORTED RECEPTACLE. A BURNING SMELL NOTED AND SHORTLY AFTER THE GALLEY LIGHT CB POPPED. SUSPECT MOISTURE FROM COFFEE MAKER CAUSED PROBLEM WITH RECEPTACLE. COFFEE MAKER TO BE RELOCATED. 2 L 7 2 4F RT A21EA 1997030600675 19970306 00675 SO 1997 3 6 CA960826076 1 19960815 G 3233 SFA2325 ACTUATOR PIPER PA32 PA32R301 7103218 SO LYC O540 IO540K1G5 41532 EA MLG LEAKING W A UNSCHED LANDING K FLUID LOSS CL CLIMB 1 CA 121 0 (CAN) THE PILOT WAS UNABLE TO RETRACT THE GEAR. AFTER A SAFE LANDING, MAINTENANCE FOUND THE MAIN LANDING ACTUATOR HAD LE AKED ALL OF ITS HYDRAULIC FLUID PAST THE O-RING. 1 L 7 1 3O 3 O A3SO 1E4 1997010200303 19970102 00303 1997 1 2 CA960826104 1 19960710 G 6310 3024680 CLUTCH ASSEMBLY PWA 3024780 PWA PT6T PT6T6 52045 EA #2 ENGINE SIDE DISENGAGED W A UNSCHED LANDING O OTHER EX EXTERNAL LOAD 1 CA 1857 CPGB1591 CPPS72009 (CAN) THE HELICOPTER WAS LIFTING A LOAD, WHEN THE FREEWHEEL CLUTCH INSIDE THE COMBINING GEARBOX DECOUPLED OR DISENGAGED ON THE #2 ENGINE SIDE. THE #2 ENGINE WENT TO FLIGHT IDLE. THE PILOT RELEASED THE LOAD AND LANDED AS SOON AS POSSIBLE. THE COMBINING GEARBOX WAS REMOVED AND SHIPPED TO A REPAIR STATION. 4 U E22EA 1997013000467 19970130 00467 NE 1997 1 30 CA960827019 2 19960801 G 7250 MS969611 CASE BOLTS PWA 120 PW120 NE INTERSTAGE CASE FRACTURED W K NONE O OTHER IN INSP/MAINT 1 CA 120080 (CAN) ROUTINE BOROSCOPE INSPECTION REVEALED THE 1ST STAGE POWER TURBINE BLADES HAD SMALL NOTCHES IN THE LEADING EDGE NEA R THE ROOT AND TIP PLATFORM. TEARDOWN OF THE ENGINE FOUND MULTIPLE FAILURES OF THE INTERSTAGE CASE BOLTS. THIS RELEASED THE INTERSTAGE CASE ASSEMBLY ON THE RIGHT HAND SIDE OF THE ENGINE WHICH THEN MOVED BACK UNTIL THE TRAILING EDGE OF THE I NNER AND OUTER PLATFORMS OF THE PT1 STATOR ASSEMBLY CONTACTED THE LEADING EDGE OF THE PT1 ROTOR BLADES CAUSING THE OBSER VED GROOVE. 4 T E20NE 1997013000470 19970130 00470 SO 1997 1 30 CA960827103 1 19960711 G 2810 TANKS PIPER PIPER PA28 PA28180 7102808 SO LYC O360 O360A3A 41514 EA RT AND LT FUEL LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 3118 0 L604936 (CAN) BOTH FUEL TANKS FOUND TO BE LEAKING FROM VARIOUS POINTS. FUEL LINES ALSO LEAKING. PHOTOS OF THE AIRCRAFT SUGGEST M AINTENANCE NEGLECT. 1 L 7 1 3O 3 O 2A13 E286 1997013000471 19970130 00471 SO 1997 1 30 CA960827104 1 19960711 G 5730 PANEL PIPER PIPER PA28 PA28180 7102808 SO LYC O360 O360A3A 41514 EA RT WING CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 3118 0 L604936 (CAN) TWO CRACKS WERE FOUND ON THE BOTTOM OF THE WING PANEL. THE FIRST CRACK APPROXIMATELY 5 INCHES LONG AND STARTING 3 1/2 INCHES FORWARD OF THE SPAR. THE SECOND CRACK IS APPROXIMATELY 3 1/2 INCHES LONG AND STARTING FROM THE FOURTH RIVET O N THE FORWARD ROW OF THE SPAR RIVETS. SUBMITTER STATES THAT BOTH CRACKS APPEAR TO HAVE BEEN THERE FOR SOME TIME. PHOTOS TAKEN OF THE AIRCRAFT AND SUBMITTED WITH SDR 960827103 SUGGEST A LACK OF MAINTENANCE ON THIS AIRCRAFT. 1 L 7 1 3O 3 O 2A13 E286 1997013000472 19970130 00472 EA 1997 1 30 CA960828001 2 19960712 G 7320 3014216 P3 TUBE PWA PT6 PT6A34 52043 EA FCU SIDE FRACTURED W E ENGINE SHUTDOWN R PARTIAL RPM/PWR LOSS AP APPROACH 1 CA 2975 57311 (CAN) ON APPROACH THE #1 ENGINE ROLLED BACK TO IDLE. THE ENGINE WAS SECURED AND THE AIRCRAFT LANDED WITHOUT INCIDENT. PO ST FLIGHT INSPECTION FOUND A FRACTURED P3 TUBE NEAR THE COUPLING NUT ON THE FCU SIDE. THE TUBE HAD BEEN INSPECTED ON 22 MAY 1996. 4 T E4EA 1997013000473 19970130 00473 NE 1997 1 30 CA960828002 2 19960719 G 7320 3017394 P3 TUBE PWA PT6T PT6T3B 52045 NE FUEL CONTROL FRACTURED W O OTHER R PARTIAL RPM/PWR LOSS CR CRUISE 1 CA 554 63492 (CAN) DURING FLIGHT THE #2 ENGINE BEGAN TO ROLL BACK UNTIL THE ENGINE REACHED MINIMUM FUEL FLOW. THE PILOT SWITCHED TO M ANUAL, THE POWER WAS RESTORED AND THE FLIGHT COMPLETED. POST FLIGHT INSPECTION FOUND THE P3 TUBE WAS FRACTURED AT THE EN D OF THE TUBE. 4 U E22EA 1997013000474 19970130 00474 NE 1997 1 30 CA960828003 2 19960621 G 7250 BLADE PWA 120 PW120A NE LOW PRESS TURBIN FRACTURED W E F A ENGINE SHUTDOWN ACTIVATE FIRE EXT. UNSCHED LANDING M OVER TEMP CL CLIMB 1 CA 12500 120826 (CAN) AT 8000 FEET ON CLIMB OUT THE #1 ENGINE TORQUE FLUCTUATED 7-8 PERCENT. THE ITT THEN INCREASED TO 780 DEGREES CELCI US AND SUBSEQUENTLY THE TORQUE DROPPED TO 50 PERCENT. A GRINDING NOISE WAS HEARD FOLLOWED BY A FIRE WARNING. THE ENGINE WAS SECURED AND THE FIRE BOTTLE WAS DISCHARGED. THE FIRE WARNING EXTINGUISHED AND AN UNEVENTFUL LANDING WAS MADE. POST F LIGHT INSPECTION FOUND ONE LOW PRESSURE TURBINE BLADE LIBERATED FROM THE DISK. 4 T E20NE 1997013000475 19970130 00475 NE 1997 1 30 CA960828004 2 19960704 G 7260 TOWER SHAFT PWA 120 PW120A NE ACCESSORY GEARBX FRACTURED W E ENGINE SHUTDOWN J Y WARNING INDICATION ENGINE STOPPAGE CR CRUISE 1 CA 1513 120371 (CAN) DURING CRUISE THE #2 ENGINE TORQUE DROPPED TO ZERO AND THE LOW OIL PRESSURE LIGHT CAME ON. THE ENGINE WAS SHUTDOWN . POST FLIGHT INSPECTION FOUND LARGE PIECES OF METAL IN THE OIL TANK CHIP DETECTOR. THE METAL CONTAMINATION WAS A RESULT OF THE FRACTURE OF THE BEVEL GEAR OF THE ACCESSORY GEARBOX TOWER SHAFT. 4 T E20NE 1997013000477 19970130 00477 NE 1997 1 30 CA960828006 2 19960717 G 7311 FUEL OIL COOLER PWA PWA120 PW125B NE #2 ENGINE FAILED W A UNSCHED LANDING O OTHER CR CRUISE 1 CA 124247 (CAN) TWO MINUTES AFTER TAKEOFF #2 ENGINE OIL PRESSURE FLUCTUATIONS AND LOW OIL PRESSURE WAS EXPERIENCED. POWER WAS REDU CED AND OIL PRESSURE RECOVERED. TWO ATTEMPTS TO INCREASE POWER CONFIRMED THAT OIL PRESSURE OCCURRED ONLY AT HIGH POWER S ETTINGS. POWER WAS REDUCED AND AIRCRAFT RETURNED TO BASE. GROUND INSPECTION REVEALED HIGH OIL LEVEL WITH FUEL ODOR. FUEL COOLED OIL COOLER REPLACED AND AIRCRAFT RETURNED TO SERVICE. 4 T E20NE 1997013000478 19970130 00478 NE 1997 1 30 CA960828007 2 19960811 G 7324 FLOW DIVIDER PWA PWA120 PW125B NE #1 ENGINE FAULTY W O OTHER X R ENGINE FLAMEOUT PARTIAL RPM/PWR LOSS AP APPROACH 1 CA 125020 (CAN) ON APPROACH #1 ENGINE SUFFERED TORQUE FLUCTUATIONS BEFORE FLAMING OUT. THE FUEL FLOW DIVIDER WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. 4 T E20NE 1997013000479 19970130 00479 NE 1997 1 30 CA960828008 2 19960806 G 7311 FUEL OIL COOLER PWA PWA120 PW125B NE #2 ENGINE INTERNAL LEAK W E A ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA 125027 (CAN) AFTER 30 MINUTES OF LEVEL FLIGHT A LOW OIL PRESSURE LIGHT ILLUMINATED ON #2 ENGINE, FOLLOWED BY A PRESSURE DROP TO ZERO. THE ENGINE WAS SHUTDOWN AND THE AIRCRAFT DIVERTED. POST FLIGHT INSPECTION SHOWED THE OIL SYSTEM WAS CONTAMINATED WITH FUEL. THE CAUSE WAS IDENTIFIED AS INTERNAL LEAKAGE OF THE FUEL COOLED OIL COOLER (FCOC). 4 T E20NE 1997021100003 19970211 00003 NM 1997 2 11 CA960830001 1 19960815 G 5230 655343315 FRAME STOP BOEING 727 727171C 1384057 NM PWA JT8 JT8D7A 52053 NE FWD CARGO DOOR BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA P653620B (CAN) FORWARD CARGO DOOR AFT FRAME STOP CRACKED. REPLACED. 2 L 7 3 4F 4 F A3WE E2EA 1997013000480 19970130 00480 NE 1997 1 30 CA960830002 2 19960802 G 7250 BLADE PWA JT8 JT8D7A 52053 NE SHROUD WORN W K NONE O OTHER IN INSP/MAINT 1 CA 34011 14511 P674612B (CAN) AS A RESULT OF THE FINDINGS OF AN INSPECTION REQUIRED BY PRATT & WHITNEY SERVICE BULLETIN #5913, THE #2 ENGINE WAS TO BE REMOVED DUE TO EXCESSIVE WEAR ON THE TURBINE BLADE SHROUD CROSS NOTCH. THE ENGINE WAS REMOVED FOR REPAIR AND RESU RFACEING OF THE TURBINE BLADES. 4 F E2EA 1997013000484 19970130 00484 NM 1997 1 30 CA960909004 1 19960805 G 2820 384453001 VTO DEVICE SIMMONDS 384453001 BOEING 727 727171C 1384057 NM PWA JT8 JT8D7A 52053 NE FUEL SYS CORROSION W H DEACTIVATE SYST/CIRCUITS N FALSE WARNING TX TAXI/GRND HDL 1 CA 6315AB P653620B (CAN) #3 FUEL TANK WOULD NOT ACCEPT FUEL. COCKPIT INSTRUMENT DISCONNECTED AND FUEL ENTERED TANK. VTO DEVICE REPLACED. REPAIR REPORT INDICATED INTERNAL CORROSION AND GROUND WIRE BROKEN. 2 L 7 3 4F 4 F A3WE E2EA 1997013000485 19970130 00485 EU 1997 1 30 CA960909006 1 19960727 G 6330 350A381018 CROSSBEAM AEROSP AEROSP AS355 AS355F1 8680810 EU ALLSN 250C 250C20F 03013 GL ATTACH LUGS CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA CAE832365 (CAN) CRACKS FOUND IN MGB SUSPENSION CROSSBEAM END LUGS AS DESCRIBED IN TELEX SB 05.00.29 AND AD 96-155-053(B). 1 G 7 2 3U 3 U H11EU E4CE 1997013000491 19970130 00491 NE 1997 1 30 CA960909014 2 19960709 G 7530 216035029 ACTUATOR BLEED LYC ALF502 ALF502R5 41580 NE #3 ENGINE INOPERATIVE W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) MAINTENANCE FOUND THE BLEED BAND OPENING/CLOSING WAS IMPOSSIBLE TO ADJUST ON THE #3 ENGINE, DUE TO THE INCORRECT A SSEMBLY OF THE FCU ADJUSTMENT MECHANISM. THE COMPLETE BLEED BAND ACTUATING MECHANISM WAS REMOVED, THE ACTUATOR WAS CLEAN ED. THE TRIGGER LINE MECHANISM, WHICH WAS INCORRECTLY ASSEMBLED, WAS FITTED WITH A NEW FLARED FITTING. A FLARELESS FITTI NG WAS PREVIOUSLY INSTALLED. THE ENGINE GROUND RUN SERVICEABLE AND THE AIRCRAFT RETURNED TO SERVICE. 4 F E6NE 1997013000494 19970130 00494 NE 1997 1 30 CA960909017 2 19960708 G 7324 34050 FLOW DIVIDER LYC ALF502 ALF502R5 41580 NE #2 ENGINE INOPERATIVE W O OTHER O OTHER IN INSP/MAINT 1 CA (CAN) #2 ENGINE WOULD NOT START AFTER REFUELING STOP. DURING THE START SEQUENCE EXCESSIVE FUEL STARTED DRIPPING FROM THE EXHAUST PIPE. THIS FUEL IGNITED CAUSING SOME TORCHING AT THE EXHAUST STACKS. MAINTENANCE FOUND THE FLOW DIVIDER AND CHE CK VALVE TO BE INCREASING FUEL FLOW. THE VALVE WAS REMOVED AND CLEANED AND CHECKED SERVICEABLE AND THE AIRCRAFT RETURNED TO SERVICE. 4 F E6NE 1997013000498 19970130 00498 NE 1997 1 30 CA960909021 2 19960709 G 7530 216035029 ACTUATOR BLEED LYC ALF502 ALF502R5 41580 NE #1 ENGINE INOPERATIVE W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) MAINTENANCE FOUND #1 ENGINE BLEED BAND ACTUATOR AND THE TRIGGER LINE BLOCKED WITH CARBON. THE BLEED BAND ACTUATOR WOULD NOT CLOSE DURING ENGINE OPERATION. MAINTENANCE CLEANED AND PURGED THE BLEED BAND ACTUATOR PLUS ALL TRIGGER LINES A ND CONTROL MECHANISM OF ALL CARBON PARTICLES. ENGINE GROUND RUN SERVICEABLE AND AIRCRAFT RETURNED TO SERVICE. 4 F E6NE 1997020600069 19970206 00069 CE 1997 2 6 CA960909029 1 19960823 G 2823 0716102 SELECTOR CUP CESSNA 0716102 CESSNA 180 180 2072602 CE FUEL INDICATOR WORN W K NONE O OTHER IN INSP/MAINT 1 CA 4100 (CAN) THE FUEL SELECTOR EXTENSION SHAFT UP THROUGH THE CONSOLE IS SQURE. OVER A PERIOD OF TIME THE SHAFT HAS WORN A FLAT SPOT IN THE BRACKET THAT HOLDS THE FUEL INDICATOR CUP. THIS WAS FOUND TO PREVENT THE PILOT FROM MAKING A QUICK SELECTIO N BETWEEN TANKS. 1 H 7 1 3O NC 5A6 1997020600070 19970206 00070 SW 1997 2 6 CA960909030 1 19960823 G 7160 22142 VALVE BBAVIA 8 8GCBC 1220803 SW LYC O360 O360C2E 41514 EA AIR INTAKE MISSING RIVETS W K NONE O OTHER IN INSP/MAINT 1 CA 421 L2691136A (CAN) TWO RIVETS FOUND MISSING AND ALL OTHERS WERE FOUND TO BE LOOSE, ATTACHING BOTH REINFORCING STRIPS. 1 H 7 1 3O 3 O A21CE E286 1997020600071 19970206 00071 EA 1997 2 6 CA960909032 1 19960821 G 2926 82960010191 TUBE DHAV DHC8 DHC8311 1386006 EA NR 2 HYD RESV CRACKED W O OTHER K FLUID LOSS CR CRUISE 1 CA 2 (CAN) IN FLIGHT DEPLETION OF #2 HYDRAULIC RESERVOIR DUE TO CRACKED PRESSURE TRANSDUCER TUBE. MOD 8/2865 ISSUED TO ADDRES S THIS DEFECT, CHANGED TUBE TO A HOSE. 2 H 7 2 4T RT A13NM 1997020600076 19970206 00076 CE 1997 2 6 CA960909037 1 19960813 G 7120 045100336 MOUNT CESSNA 045100336 CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA LWR OLEO CLAMP CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 3525 L2453615 (CAN) DURING MAINTENANCE A CRACK WAS FOUND AT THE WELD POINT WERE THE TUBE INTERSECTS THE LOWER OLEO STRUT CLAMP. RIGHT HAND TUBE WAS ESTIMATED WITH 50 PERCENT GOOD WELD. 1 H 7 1 3O 3 O NT 3A19 E223 1997020600081 19970206 00081 NE 1997 2 6 CA960909042 2 19960823 G 7260 311196801 GEARSHAFT PWA 120 PW120 NE ACCESSORY GEARBX FRACTURED W E ENGINE SHUTDOWN X ENGINE FLAMEOUT CR CRUISE 1 CA 121229 (CAN) THE OPERATOR REPORTS THAT THE ENGINE EXPERIENCED AN AUTOFEATHER AND SHUTDOWN DURING FLIGHT. THE CAUSE OF THE SHUTD OWN AND AUTOFEATHER WAS LOSS OF OIL PRESSURE, CAUSED BY A LOSS OF ACCESSORY DRIVE TRAIN INTEGRITY WHICH PROVIDES THE POW ER TO THE OIL PUMP. THE ANGLE DRIVE (TOWER SHAFT) WAS FOUND TO HAVE FRACTURED IMMEDIATELY BELOW THE UPPER RETAINING NUT. 4 T E20NE 1997020600082 19970206 00082 NE 1997 2 6 CA960909043 2 19960823 G 7250 MS969611 CASE PWA 118 PW118 NE INTERSTAGE CASE BOLT FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 9609 115294 (CAN) THE ENGINE WAS REMOVED FROM SERVICE AFTER THE OPERATOR NOTED EXTENSIVE POWER TURBINE DAMAGE DURING A ROUTINE WALK AROUND. TEARDOWN OF THE ENGINE REVEALED AN INTERSTAGE CASE BOLT HAD FRACTURED LIBERATING THE BOLT HEAD CAUSING DAMAGE TO THE 1ST STAGE POWER TURBINE BLADES AND POSSIBLY CONTRIBUTING TO THE DAMAGE ON THE 2ND STAGE PT STATOR ASSEMBLY AND 2ND STAGE ROTOR ASSEMBLY. 4 T E20NE 1997020600083 19970206 00083 NE 1997 2 6 CA960909044 2 19960822 G 7210 310703301 BEARING PWA 120 PW120 NE RED GRBOX NR 15 SPALLED W K NONE O OTHER IN INSP/MAINT 1 CA 9176 120626 (CAN) THE REDUCTION GEARBOX WAS FOUND TO HAVE METAL FLAKES OF BEARING MATERIAL ON THE CHIP DETECTOR. THE SOURCE OF THE M ETAL CONTAMINATION WAS FOUND TO BE THE #15 BEARING WHICH HAD SPALLED BADLY ON THE OUTER RACE WITH SUBSTANTIAL MATERIAL L OSS. THIS WAS A RESULT OF ELECTRICAL EROSION PITTING, WHICH WAS ALSO FOUND ON THE #19 BEARING. 4 T E20NE 1997020600084 19970206 00084 NE 1997 2 6 CA960909045 2 19960819 G 7250 311260201 PT BLADE LP PWA 120 PW120 NE TURBINE INTERSTG AIRFOIL FRACTURE W E O ENGINE SHUTDOWN OTHER X ENGINE FLAMEOUT CL CLIMB 1 CA 14706 9142 120656 (CAN) THE AIRCRAFT WAS CLIMBING THROUGH 6,000 FEET WHEN THE PILOT NOTED A DROP IN OIL PRESSURE FOLLOWED BY A LOUD BANG. A FIREBALL WAS OBSERVED AND THE ENGINE SUBSEQUENTLY SHUTDOWN. THE CAUSE OF THE IN-FLIGHT SHUTDOWN WAS THE FAILURE OF THE #4, #5 AND #6 BEARINGS AND THE MASSIVE DAMAGE SUSTAINED TO THE INTERSTAGE AREA. WHILE THE FAILURE SEQUENCE IS NOT ABSOL UTELY CLEAR, IT IS THE OPINION OF THE OVERHAULER THAT THE CATASTROPHIC FAILURE ORIGINATED WITH AN EARLIER LOSS OF A SING LE LOW PRESSURE TURBINE AIRFOIL NEAR THE BLADE PLATFORM DUE TO FATIGUE CRACKING. 4 T E20NE 1997020600085 19970206 00085 NE 1997 2 6 CA960909046 2 19960801 G 7313 NOZZLE TIP PWA 118 PW118 NE FUEL NOZZLE MISSING W K NONE O W OTHER INADEQUATE Q C NR NOT REPORTED 1 CA 8338 2662 115410 (CAN) THE CAUSE OF THE FUEL NOZZLE LIBERATION WAS IMPROPER TORQUING AND/OR LOCKING OF THE FUEL NOZZLE TIP. FOUR OTHER FU EL NOZZLES WERE INADEQUATELY TORQUED OR LOCKED. THERE WAS EXTENSIVE HOT SECTION BURNING DAMAGE FROM THE IRREGULAR SPRAY PATTERN OF THE SEPARATED NOZZLE INCLUDING: BASE METAL BURNING OF BOTH COMBUSTIONS LINERS AND THE SMALL EXIT DUCT, BURNIN G DAMAGE ON 4 HP TURBINE VANE RING SEGMENTS, BURNING ON THE FRONT FLANGE OF THE TURBINE SUPPORT CASE, BURNING AND OVERHE ATING OF ALL THE TURBINE BLADES, BURNING ON SEVERAL SHROUD SEGMENTS, BURN THROUGH ON THE VANES OF EVERY TURBINE STATOR A ND BURN THROUGH ON 1 TURBINE INTERSTAGE CASE STRUT. 4 T E20NE 1997020600116 19970206 00116 NE 1997 2 6 CA960910041 2 19960829 G 7261 030137180 VENT PIPE SNIAS 350 AS350B1 8680811 EU TMECA ARRIEL ARRIEL1D NE ENG AFT BEARING PLUGGED W K NONE B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 CA 1953 7139 (CAN) PILOT REPORTED SMOKE COMING FROM ENGINE REAR BEARING AREA.OIL LEAKAGE AT VENT PIPE ATTACH FLANGE. VENT PIPE REMOVE D AND FOUND PLUGGED WITH CARBON DEPOSITS. CLEANED AND REINSTALLED. 1 G 7 1 3U 3 U H9EU E19EU 1997020600117 19970206 00117 NE 1997 2 6 CA960910042 2 19960828 G 7313 O RINGS PWA PW120 PW123 NE FUEL NOZZLES LEAKING W F ACTIVATE FIRE EXT. O B OTHER SMOKE/FUMES/ODORS/SPARKS LD LANDING 1 CA 4500 123263 (CAN) FOLLOWING LANDING, PRIOR TO SHUTDOWN, FUMES WERE SEEN COMING FROM THE #1 ENGINE NACELLE. THE FIRE EXTINGUISHERS WE RE ACTIVATED. INSPECTION REVEALED FOUR FUEL NOZZLE "O" RINGS DAMAGED. THE "O" RINGS WERE REPLACED AND THE AIRCRAFT RETUR NED TO SERVICE. THE "O" RINGS HAD BEEN REPLACED 24 HOURS PRIOR TO THIS INCIDENT. 4 T E20NE 1997021300500 19970213 00500 EU 1997 2 13 CA960916002 1 19960814 G 6330 350A381018 CROSSBEAM AEROSP AEROSP AS355 AS355F2 8680812 EU ALLSN 250C 250C20F 03013 GL M/R GEARBOX CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA CAE840969 (CAN) CRACKS FOUND IN MGB SUSPENSION CROSSBEAM END LUGS AS DESCRIBED IN TELEX SB 05.00.29 AND AD 96-155-053(B). 1 G 7 2 3U 3 U H11EU E4CE 1997021300501 19970213 00501 EU 1997 2 13 CA960916003 1 19960814 G 6330 350A381018 CROSSBEAM AEROSP AEROSP AS355 AS355F1 8680810 EU ALLSN 250C 250C20F 03013 GL M/R GR BOX CRACKED LUGS W K NONE O OTHER IN INSP/MAINT 1 CA CAE840374 (CAN) CRACKS FOUND IN MGB SUSPENSION CROSSBEAM END LUGS AS DESCRIBED IN TELEX SB 05.00.29 AND AD 96-155-053(B). 1 G 7 2 3U 3 U H11EU E4CE 1997021300506 19970213 00506 EU 1997 2 13 CA960916011 1 19960812 G 6320 4638302024 BEARING 4638001001 BOLKMS 105 BO105CBS 5626008 EU M/R GR BOX PEELING W K NONE O OTHER IN INSP/MAINT 1 CA 2552 1224 (CAN) L/H INPUT BEARING ROLLERS PEELING. 1 G 7 2 3U NC H3EU 1997010200307 19970102 00307 SW 1997 1 2 CA960916018 1 19960905 G 6200 MAIN ROTOR BELL 206 206B 1181511 SW M/R RPM DROOP W B EMER. DESCENT O OTHER AP APPROACH 1 CA (CAN) AIRCRAFT UNDERGOING PRODUCTION FLIGHT TEST. AFTER PERFORMING EVALUATION OF ROTOR FOR VIBRATION, THE PILOT STARTED APPROACH. AS THE PILOT BEGAN TO PULL TORQUE THE ROTOR RPM STARTED TO DROOP. INCIDENT UNDER INVESTIGATION. MORE INFO TO F OLLOW. 1 G 7 1 3U H2SW 1997021300512 19970213 00512 NE 1997 2 13 CA960916022 2 19960820 G 7250 MS969601 BOLTS PWA 120 PW120A NE COOLING BAFFLE FRACTURED W K NONE O OTHER IN INSP/MAINT 1 CA 3286 120864 (CAN) UPON TEARDOWN OF ENGINE IT WAS REVEALED THAT 11 OF THE 26 RETAINING BOLTS FOR THE COOLING BAFFLE WERE FRACTURED. T HIS IS AN ON GOING PROBLEM. THE SUBMITTER STATES THAT PRATT & WHITNEY HAS INTRODUCED A NUMBER OF MODS TO DATE WHICH HAS NOT ADDRESSED THE PROBLEM. 4 T E20NE 1997021300513 19970213 00513 EA 1997 2 13 CA960916023 2 19960830 G 8530 SL16740 VALVE LYC O360 IO360A3B6 41514 EA EXH VALVE SEVERE WEAR W K NONE E VIBRATION/BUFFET NR NOT REPORTED 1 CA 127 L2086051A (CAN) DURING TROUBLESHOOTING TO DETERMINE CAUSE OF ROUGH RUNNING ENGINE OIL FILTER WAS REMOVED AND FERROUS METAL PARTICL ES WERE FOUND. ENGINE WAS DISMANTLED AND #1 AND #3 CYLINDER EXHAUST VALVES WERE FOUND SEVERELY WORN. 3 O 1E10 1997021300514 19970213 00514 SW 1997 2 13 CA960916024 1 19960829 G 2435 23917 CONNECTOR LEARSIEGLER 23032027 BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL START/GEN BURNT W K NONE O OTHER IN INSP/MAINT 1 CA 206 23917 0 (CAN) STARTER-GENERATOR ELECTRIC TERMINAL CONNECTOR BURNT 1 G 7 1 3U 3 U H2SW E4CE 1997030600683 19970306 00683 1997 3 6 CA960923001 4 19960923 G 3416 152734 SUPPORT RING AEROMECH 804710HD LOCATING SLOT MODIFIED W K NONE O OTHER IN INSP/MAINT 1 CA 8691 (CAN) SUPPORT RING HAS LOCATING SLOT MODIFIED AS OUTLINED IN SERVICE DIFFICULTY ALERT AV-93-07R1. 1998050100210 19980501 00210 CE 1998 5 1 CA960923002 1 19960708 G 5210 VALVE CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE DOOR SEAL FAILED W B G I EMER. DESCENT O2 MASK DEPLOYED CABIN DEPRESSURIZATION J WARNING INDICATION CR CRUISE 1 CA 71760 (CAN) AIRCRAFT EN ROUTE WHEN PRESSURE BEGAN DECREASING AT UNCONTROLLABLE RATE. OXYGEN MASKS DEPLOYED AND DONNED, AIRCRA FT LANDED SAFELY AT ALTERNATE SITE. MAINTENANCE FOUND MOISTURE TRAPPED IN DOOR SEAL AIR SUPPLY LINE. PURGED AIR USING LT ENGINE TO SUPPLY BLEED AIR AND MANUALLY ACTIVATING PLUNGER TO ALLOW AIR TO FLOW FREELY THROUGH SEAL. AIRCRAFT TT: 2 ,277 HOURS. 1 L 7 2 4F 4 F A22CE E1NE 1998050100211 19980501 00211 CE 1998 5 1 CA960923003 1 19960904 G 5210 SEAL CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE CABIN DOOR MALFUNCTIONED W K NONE J WARNING INDICATION CR CRUISE 1 CA 71760 (CAN) DURING FLIGHT AT 5,000 FEET ASL, FLIGHT CREW NOTICED A GRADUAL LOSS OF CABIN PRESSURIZATION UNTIL THE AIRCRAFT CAB IN ALTITUDE MATCHED AIRCRAFT ALTITUDE. AIRCRAFT RETURNED TO BASE UNPRESSURIZED. AIRCRAFT PRESSURIZATION SYSTEM GROUND CHECKED WITHOUT FAULTS. DOOR SEAL LINE PURGED AS A PRECAUTION. AIRCRAFT TT: 2,277. 1 L 7 2 4F 4 F A22CE E1NE 1998050100212 19980501 00212 WP 1998 5 1 CA960923010 2 19960911 G 7250 8650821 TIE BOLT NUT SWRNGN SA226 SA226TC 8780404 SW GARRTT TPE331 TPE33110UA 01514 WP NR 2 TURB WHEEL WRONG PART W K NONE O OTHER IN INSP/MAINT 1 CA 22175 6093 P54054C (CAN) ON MORNING WALK-AROUND, ENGINE WAS STIFF TO ROTATE. ENGINE REPLACED. ENGINE WAS DIS-ASSEMBLED BY FIELD REP AND F OUND THAT NR 2 TURBINE WHEEL TIE BOLT NUT WAS NOT THE ONE STATED IN THE LATEST SB (331-72-0592, 9/88). NUT P/N SHOULD H AVE BEEN 3108066-1 NOT 865082-1. PART TC: 31,937. 2 L 7 2 4T 4 T RT A8SW E4WE 1997021300526 19970213 00526 SO 1997 2 13 CA960923012 2 19960715 G 8530 PISTON CESSNA 140 140 2071602 CE CONT C90 C9012F 17009 SO #2 CYLINDER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 1153 418099 (CAN) DURING THE ANNUAL AIRCRAFT INSPECTION THE #2 CYLINDER COMPRESSION CHECK WAS LOW AT 43/80. UPON REMOVAL OF THE CYLI NDER, THE PISTON WAS FOUND CRACKED IN TWO PLACES ON THE WRIST PIN BOSSES. A NEW CYLINDER AND PISTON WILL BE INSTALLED. 1 H 7 1 3O 3 O NC A768 E252 1997021300536 19970213 00536 NE 1997 2 13 CA960923025 2 19960912 G 7210 310709001 BEARING PWA 118 PW118 NE RED GEARBX NR 19 SPALLED W K NONE O OTHER IN INSP/MAINT 1 CA 12944 115511 (CAN) METAL CONTAMINATION IN REDUCTION GEARBOX FROM SPALLED #19 BEARING. 4 T E20NE 1998050100213 19980501 00213 CE 1998 5 1 CA960923026 1 19960619 G 5210 DOOR SEAL CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE CABIN LEAKING W O B OTHER EMER. DESCENT J WARNING INDICATION CR CRUISE 1 CA (CAN) PILOT REQUESTED RAPID DESCENT TO 10,000 FEET AND ADVERSION TO ALTERNATE LANDING SITE. PILOT REPORTED DOOR SEAL LE AKING AND A SLOW DEPRESSURIZATION. RUN-UP RT ENGINE AND WITH DOOR OPENED, DEPRESSED THE PLUNGER FOR THE DOOR SEAL VALVE AND ALLOWED THE SYSTEM TO PURGE OFF WATER WHICH WAS FOUND IN THE SYSTEM. AIRCRAFT TT: 2,198 HOURS. 1 L 7 2 4F 4 F A22CE E1NE 1997022000090 19970220 00090 EA 1997 2 20 CA960924021 1 19960915 G 7931 356677499502 TRANSMITTER DHAV DHC6 DHC6300 EA PWA PT6 PT6A27 52043 EA ENG OIL PRESS INTERMITTENT W E A ENGINE SHUTDOWN UNSCHED LANDING N FALSE WARNING CR CRUISE 1 CA PCE42076 (CAN) DURING FLIGHT THE ENGINE OIL PRESSURE INDICATION DROPPED TO 20 PSI, THERE WAS NO PROPELLER RPM CHANGE AND NO LOW O IL PRESSURE WARNING LIGHT. A PRECAUTIONARY SHUTDOWN WAS CARRIED OUT AND THE AIRCRAFT RETURNED TO BASE. THE OIL PRESSURE WAS CONFRIMED WITH A DIRECT READING GAUGE AND THE OIL PRESSURE TRANSMITTER WAS DETERMINED TO BE THE FAULT. THE UNIT WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. 1 H 7 2 3T 4 T A9EA E4EA 1997041500007 19970415 00007 CE 1997 4 15 CA960924024 1 19960901 G 2434 ALV1012S BRUSHES PRESTOLITE ALT9510R CESSNA 340 340A 2076405 CE CONT O520 TSIO520N 17040 SO MCAULY 3AF32C 3AF32C93 GL ALTERNATOR HIGH RESISTANCE W H DEACTIVATE SYST/CIRCUITS J WARNING INDICATION CR CRUISE 1 CA 50 228430R 890661 (CAN) AIRCRAFT ALTERNATORS WOULD NOT BALANCE. INSPECTION REVEALED A HIGH FIELD RESISTANCE. THE BRUSHES WERE FOUND TO HAV E A RESISTANCE OF 15-30 OHMS. REPLACEMENT BRUSHES SOLVED THE PROBLEM. SUBMITTER STATES THAT THIS IS THE THIRD SUCH OCCUR RENCE. 1 L 7 2 3O 3 O 3A25 E8CE 5 C P22EA 1997121800401 19971218 00401 EA 1997 12 18 CA960924028 2 19960916 G 7310 35040284 FUEL HOSE PIPER PA23 PA23250 7102308 SO LYC O540 IO540C4B5 41532 EA ENGINE CYLINDER RUPTURED W D E RETURN TO BLOCK ENGINE SHUTDOWN A B K FLAME/FIRE SMOKE/FUMES/ODORS/SPARKS FLUID LOSS TX TAXI/GRND HDL 1 CA L608248 (CAN) WHILE TAXIING, PILOT NOTICED FLAMES COMING FROM LEFT ENGINE. THE ENGINE WAS SHUT DONW AND FLAMES WENT OUT. ENGINE COWLING AREA WAS FOAMED AS A PRECAUTIONARY MEASURE WHEN THE COWLS WERE REMOVED A FLEX FUEL LINE FROM THE FUEL DISTRIBUTO R ON THE TOP OF THE ENGINE DOWN BETWEEN #1 ABD #3 CYLINDERS TO THE FUEL SERVO WAS RUPTURED. ALSO THE #3 IGNITION LEAD WA S OFF AND LAYING BY THE SPARK PLUG. A CHECK OF THE OTHER FLEX HOSES IN BOTH ENGINE COMPARTMENTS REVEALED DATE CODES RANG ING FROM 1976 TO 1990 AND THE RUPTURED HOSE DID NOT HAVE ANY IDENTIFICATION TAG. 1 L 7 2 3O 3 O 1A10 1E4 1997022000095 19970220 00095 NE 1997 2 20 CA960924033 2 19960905 G 7260 625926 FLANGE BOEING 747 747128 1384894 NM PWA JT9 JT9D7A 52054 NE ANGLE GEARBOX CRACKED W E ENGINE SHUTDOWN K FLUID LOSS CR CRUISE 1 CA 662439 (CAN) DURING FLIGHT THE #4 ENGINE OIL CONSUMPTION WAS OBSERVED. ENGINE WAS OPERATED AT REDUCED THRUST UNTIL OIL PRESSURE INDICATION WAS OBSERVED AND OIL QUANTITY AT 0.7 GALLONS.PRECAUTIONARY SHUTDOWN WAS CARRIED OUT. POST FLIGHT I NSPECTION FOUND A FLANGE CRACKED AT THE OIL RETURN LINE TO THE ANGLE GEARBOX. THE FLANGE AND "O" RING WERE REPLACED AND THE AIRCR AFT RETURNED TO SERVICE. 2 L 7 4 4F 4 F A20WE E20EA 1997022000099 19970220 00099 SO 1997 2 20 CA960924040 2 19960901 G 7322 103237 CARBURETOR MS3SPA CESSNA 172 172G 2072420 CE CONT O300 O300C 17022 SO FLOAT MIS MODIFIED W A UNSCHED LANDING R Y PARTIAL RPM/PWR LOSS ENGINE STOPPAGE CR CRUISE 1 CA 4011672 21806D3C (CAN) MODIFICATION OF CARBURETOR SINGLE PIECE VENTURI AND METAL FLOAT INSTALLATION WAS DONE IMPROPERLY. THE SPRING WHICH BRINGS DOWN THE NEEDLE WHEN THE FLOAT DROPS AS THE FUEL LEVEL LOWERS WAS INSTALLED TO THE FRONT INSTEAD OF FROM THE LEF T OR RIGHT SIDE. IN THIS CONFIGURATION THE FLOAT IS JAMMED IN THE UP POSITION AND FUEL IS PREVENTED FROM ENTERING THE CA RBURETOR. 1 H 7 1 3O 3 O NT 3A12 E253 1997041500008 19970415 00008 SO 1997 4 15 CA960924041 1 19960916 G 5753 95504000 BRACKET PIPER 95504000 PIPER PA34 PA34200T 7103406 SO FLAP CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 5845 (CAN) WHILE CARRYING OUT AWD 96-10-03, BRACKET 95504-000 WAS FOUND CRACKED AT THE 3 TOP NOTCHES. REPLACED WITH NEW PART. 1 L 7 2 3O A7SO 1997022000100 19970220 00100 EA 1997 2 20 CA960924042 2 19960923 G 7314 PUMP PWA PT6 PT6A27 52043 EA ENG FUEL WORN W O OTHER O OTHER NR NOT REPORTED 1 CA 41774 (CAN) FUEL PUMP AND COUPLING SPLINE WEAR, WITH THE COUPLING SPINNING FREELY. AIRCRAFT RETURNED TO SERVICE AFTER FUEL PUM P REPLACEMENT. 4 T E4EA 1997022000101 19970220 00101 NE 1997 2 20 CA960924043 2 19960916 G 7210 PLUG PWA 119 PW119B NE REDUCTION GEARBX DAMAGED W E ENGINE SHUTDOWN J K WARNING INDICATION FLUID LOSS NR NOT REPORTED 1 CA 4613 116012 (CAN) THE #1 ENGINE WAS SHUTDOWN FOLLOWING THE LOSS OF MAIN OIL PRESSURE, WHICH WAS SUBSEQUENTLY FOUND TO BE CAUSED BY D AMAGED THREADS ON A PLUG ON THE REDUCTION GEARBOX. 4 T E20NE 1997022000107 19970220 00107 1997 2 20 CA960927002 4 19960917 G 3421 25861376 GYRO GULSTM G159 G159 3952202 SO RROYCE DART DART5298X 54507 EU RH HSI FAULTY W K NONE P NO WARNING INDICATION CR CRUISE 1 CA 111 16227 (CAN) IN LEVEL FLIGHT, THE R/H HSI INTERMITENTLY INDICATED 10 DEGREES NOSE DOWN WITH NO FLAGS SHOWING. SHORTLY AFTER THE UNIT WAS INSTALLED, IT TOOK 20 MINUTES TO SPOOL UP ON ONE LEG BUT THE FAULT COULD NOT BE DUPLICATED. THE VERTICAL GYRO WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE. 2 L 7 2 4T 4 T 1A17 E297 1997031300259 19970313 00259 CE 1997 3 13 CA961002006 1 19960829 G 2435 8462751 STARTER CESSNA 185 A185F 2072821 CE COILS SHORTED W O OTHER B H SMOKE/FUMES/ODORS/SPARKS ELECT. POWER LOSS-50 PC TX TAXI/GRND HDL 1 CA 25 20 10009517 (CAN) STARTER FIELD COILS LOOSE ON POLE SHOES RUBBED ON THE THROUGH BOLTS CREATING A DEAD HIGH AMPERAGE SHORT RESULTING IN BOTH MASTER SOLENOID AND STARTER SOLENOID CONTACT PLATES WELDING TO TERMINALS - A VERY DANGEROUS AND FIRE CONDITION - SUSPECT INSUFFICIENT CLEARANCE IN DESIGN AND/OR MANUFACTURE BETWEEN COIL AND THROUGH BOLTS. 1 H 7 1 3O 3A24 1997031300260 19970313 00260 EA 1997 3 13 CA961002007 1 19960918 G 2750 FORK END DHAV C6CW10831 DHAV DHC6 DHC6 2802606 EA FLAP ROD MIS MANUFACTURED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) THE NEW FLAP ROD COULD NOT BE INSTALLED AS THE FORK END WAS TOO NARROW TO ACCEPT THE BEARING OF THE ATTACHING ROD BETWEEN THE FORKS. NO EVIDENCE OF DAMAGE. ROD PURCHASED NEW FROM BRAD. 1 H 7 2 3T RT A9EA 1997031300261 19970313 00261 EA 1997 3 13 CA961002009 1 19960918 G 2750 FORK END DHAV C6CW10831 DHAV DHC6 DHC6 2802606 EA FLAP ROD MIS MANUFACTURED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) NEW FLAP ROD WOULD NOT BE INSTALLED BECAUSE THE FORK END OF THE ROD WAS TOO NARROW TO ACCEPT THE BEARING OF THE AT TACHING ROD. NO DAMAGE FOUND ON ROD. SUBMITTER CONCERNED THAT SOME MAY TRY TO FORCE ROD INTO PLACE. 1 H 7 2 3T RT A9EA 1997031300267 19970313 00267 NE 1997 3 13 CA961002016 2 19960920 G 7210 311657901 PINION GEAR PWA 120 PW120 NE RED GR BOX SPALLED W K NONE O OTHER IN INSP/MAINT 1 CA 8987 121159 (CAN) ROUTINE FILTER AND CHIP DETECTOR CHECKS FOUND THE REDUCTION GEARBOX WAS GENERATING ALLOY STEEL FLAKES. THE ENGINE WAS SENT TO R&O FOR INVESTIGATION. THE SOURCE OF THE METAL FLAKES WAS FOUND TO BE FROM SEVERAL SPALLED AREAS ON THE R/H SECOND STAGE PINION GEAR. 4 T E20NE 1997031800006 19970318 00006 EA 1997 3 18 CA961003011 2 19960926 G 8530 62388 CAP VALVE STEM CESSNA 177 177RG 2073709 CE LYC O360 IO360A1B6 41514 EA MCAULY 2D34C B2D34C207 GL #1 CYLINDER MISSING W K NONE O OTHER IN INSP/MAINT 1 CA 202 L982551A 830489 (CAN) ENGINE WAS OVERHAULED 15 AUGUST 1994. ANNUAL 100 HOUR INSPECTION JULY 1995 FOUND #1 CYLINDER COMPRESSION LOW (50 P SI), CYLINDER WAS REMOVED, REPAIRED AND REINSTALLED UNDER WARRANTY BY OVERHAULER. NEXT 103.3 HOUR ANNUAL INSPECTION FOUN D FOUR (4) ROCKER BOX COVERS LEAKING, #1 CYLINDER INTAKE CAP VALVE STEM MISSING AND METAL CONTAMINATION IN THE OIL FILTE R. 1 H 7 1 3O 3 O A20CE 1E10 5 C P7EA 1998050100215 19980501 00215 NE 1998 5 1 CA961007004 2 19960909 G 7261 6029T27G03 OIL JET SKRSKY S61 S61N 8142104 NE GE CT58 CT581401 30011 NE NR 1 OIL JET OBSTRUCTED W E ENGINE SHUTDOWN O OTHER TX TAXI/GRND HDL 1 CA 1680 295106 (CAN) DURING GROUND RUN FOLLOWING ENGINE INSTALLATION, IT WAS OBSERVED THAT NR 2 ENGINE OIL PRESSURE WAS HIGHER THAN NOR MAL (60 VICE 45 PSI). ENGINE REMOVED AND A PIECE OF O-RING WAS FOUND OBSTRUCTING NR 1 OIL JET. ENGINE INSTALLED AND GR OUND RUN NORMAL. 2 G 7 2 4U 4 U 1H15 1E3 1997031300279 19970313 00279 SO 1997 3 13 CA961007005 2 19960919 G 8520 PISTON ROD CESSNA 310 310 2074202 CE CONT O470 O470B 17026 SO BEARING HOUSING BROKEN W E A ENGINE SHUTDOWN UNSCHED LANDING R K E PARTIAL RPM/PWR LOSS FLUID LOSS VIBRATION/BUFFET CR CRUISE 1 CA 506956BR (CAN) ROD FAILURE AT CRANKSHAFT, ROD BROKE IN HALF. ROD EXITED THROUGH TOP OF CRANKCASE REAR LEFT SIDE. 1 L 7 2 3O 3 O RT 3A10 E273 1999043000062 19990430 00062 CE 1999 4 30 CA961007013 1 19960805 G 6320 8681942 SUN GEAR MTSBSI MU2 MU2B36 5780412 CE TRANSMISSION FRACTURED W E ENGINE SHUTDOWN E J VIBRATION/BUFFET WARNING INDICATION NR NOT REPORTED 1 CA 10490 1635 P20062C (CAN) PILOT NOTED SEVERE VIBRATION WITH NO WARNING. PRIOR TO SHUTDOWN, THE TORQUE WENT TO ZERO. AIRCRAFT RETURNED OK. INSPECTION REVEALED THE PLANETARY PIN P/N 868051-1 WAS CHAFED BY THE PLANETARY GEAR P/N 358268-1 WHICH IN TURN ABNORMAL LY LOADED THE SUN GEAR WHICH SUBSEQUENTLY FAILED. 1 H 7 2 3T RT A10SW 1998020500609 19980205 00609 CE 1998 2 5 CA961007018 1 19961002 G 3252 0543004 ARM CESSNA 182 182 2072702 CE SHIMMY DAMPENER BROKEN W K NONE E VIBRATION/BUFFET LD LANDING 1 CA 4329 (CAN) AFTER LANDING SHIMMY DEVELOPED EITHER CAUSING ARM TO BREAK OR ARM WAS ALREADY BROKEN. STEERING FOUND OK AND FLUID LEVEL IN SHIMMY DAMPENER AND OLEO WAS CORRECT. 1 H 7 1 3O NT 3A13 1997031300287 19970313 00287 NE 1997 3 13 CA961007026 2 19960920 G 7210 310703301 BEARING PWA 120 PW120A NE RED GEARBX NR 15 SPALLED W K NONE O OTHER IN INSP/MAINT 1 CA 21127 17248 10A293 120141 (CAN) THE REDUCTION GEARBOX WAS FOUND TO BE GENERATING METAL ANALYSED TO BE M50. THE PRINCIPAL SOURCE OF THE METAL CONTA MINATION WAS FOUND TO BE #15 BEARING WHICH HAD SPALLED BADLY ON THE OUTER RACE WITH SUBSTANTIAL MATERIAL LOSS. THIS APPE ARED TO BE THE RESULT OF ELECTRICAL EROSION PITTING, WHICH WAS ALSO FOUND ON #19 BEARING. 4 T E20NE 1997031300288 19970313 00288 NE 1997 3 13 CA961007027 2 19960927 G 7210 310703301 BEARING PWA 118 PW118 NE RED GEARBX NR 15 SPALLED W K NONE O OTHER IN INSP/MAINT 1 CA 13843 5639 115472 (CAN) REDUCTION GEARBOX (RGB) SENT FOR INVESTIGATION AND REPAIR AFTER THE OPERATOR REPORTED THE RGB WAS MAKING METAL. TH E CAUSE OF THE REDUCTION GEARBOX MAKING METAL WAS SPALLED OF THE #15 BEARING INNER RACE. 4 T E20NE 1997031300289 19970313 00289 NE 1997 3 13 CA961007028 2 19960926 G 7313 NOZZLE PWA 120 PW120 NE NR 2 ENG NR 9 CRACKED BOSS W O OTHER R PARTIAL RPM/PWR LOSS TO TAKEOFF 1 CA 120058 (CAN) LOSS OF POWER ON #2 ENGINE DURING TAKEOFF. GROUND INSPECTION FOUND THE #9 FUEL NOZZLE BOSS CRACKED AND THE GASKET DISTRESSED. 4 T E20NE 1997031300290 19970313 00290 NE 1997 3 13 CA961007029 2 19960830 G 7322 FUEL CONTRL PWA PW120 PW124B NE #2 ENGINE BROKEN FLYWEIGHT W E ENGINE SHUTDOWN R PARTIAL RPM/PWR LOSS CL CLIMB 1 CA 124108 (CAN) DURING CLIMB THE #2 ENGINE LOST POWER. A RELIGHT ATTEMPT PROVED UNSUCCESSFUL. INVESTIGATION FOUND ONE OF THE MAIN FUEL CONTROL FLYWEIGHTS HAD BROKEN OFF. UNIT IS BEING RETURNED FOR INVESTIGATION. 4 T E2ONE 1997031300291 19970313 00291 NE 1997 3 13 CA961007030 2 19960924 G 7260 SPUR GEAR PWA 118 PW118 NE NR 2 ENG GEARBX FAILED W O OTHER X ENGINE FLAMEOUT CL CLIMB 1 CA 20701 10725 115119 (CAN) JUST PRIOR TO COMPLETION OF AIRCRAFT CLIMBOUT, WITHOUT WARNING THE #2 ENGINE SHUTDOWN. POST FLIGHT INSPECTION CONF IRMED AS ACCESSORY DRIVE SPUR GEAR DISTRESS. 4 T E20NE 1997032000002 19970320 00002 SW 1997 3 20 CA961009010 2 19961002 G 7210 3024780 GEARBOX BELL 212 212 1181420 SW PWA PT6T PT6T3 52045 EA COMB GRBOX MAKING METAL W K NONE O OTHER IN INSP/MAINT 1 CA 16526 236 (CAN) WHILE CONDUCTING A 150 HOUR INSPECTION BRASS PARTICLES WERE FOUND IN THE COMBINING GEARBOX. C-BOX WAS REPLACED. 1 G 7 1 4U 4 U H4SW E22EA 1997032000003 19970320 00003 NE 1997 3 20 CA961009011 2 19960926 G 7210 310600201 INPUT PISTON PWA PW121 PW121 52124 NE RED GR BOX SPALLED W K NONE O OTHER IN INSP/MAINT 1 CA 6995 121043 (CAN) ENGINE SENT FOR ROUTINE OVERHAUL. MAINTENANCE TAG STATED REDUCTION GEARBOX WAS MAKING METAL. THE REDUCTION GEARBOX WAS INSPECTED AND THE PROBLEM WAS CAUSED BY A SPALLED INPUT PISTON. 4 T E20NE 1997032000004 19970320 00004 EA 1997 3 20 CA961011001 2 19961001 G 7261 MS9388017 O-RING PWA 303589 DHAV DHC6 DHC6300 EA PWA PT6 PT6A27 52043 EA #1 ENG OIL XSFR LEAKING W E ENGINE SHUTDOWN K FLUID LOSS CR CRUISE 1 CA 1083 1083 40403 (CAN) LOW OIL PRESSURE ON #1 ENGINE FORCED AN INFLIGHT SHUTDOWN. POST FLIGHT INSPECTION FOUND AN OIL LEAK AT THE OIL PRE SSURE TRANSFER TUBE. THE "O" RING WAS FOUND PINCHED AND LEAKING. 1 H 7 2 3T 4 T A9EA E4EA 1997032000005 19970320 00005 SO 1997 3 20 CA961011002 2 19960927 G 7322 666916KIT FLOAT MARVELSCHEB MA45A1048931 CESSNA 180 180H 2072618 CE CONT O470 O470R 17026 SO MCAULY 2A34C 2A34C66 GL CARBURETOR BADLY WORN W K NONE K FLUID LOSS NR NOT REPORTED 1 CA 750 1918508R 785682 (CAN) PILOT COMPLAINED OF INTERMITTENT FUEL LEAK FROM CARBURETOR. DISASSEMBLY OF CARBURETOR REVEALED FLOAT HINGE BADLY W ORN ALLOWING CONTACT OF FLOAT WITH SIDES OF FLOAT CHAMBER RESULTING IN SEVERE WEAR ON SIDES OF METAL FLOATS. FUEL VALVE RETAINER CLIP WORN INTO FUEL STEM (30 PERCENT). FLOAT LEVEL ADJUSTMENT TAB WORN APPROXIMATELY 50 PERCENT AT POINT OF CON TACT WITH FUEL VALVE RESULTING IN INCREASED FLOAT LEVEL, TO POINT WHERE VALVE NO LONGER CLOSED. WEAR SEEMS EXCESSIVE FOR TIME ON COMPONENT. 1 H 7 1 3O 3 O 5A6 E273 5 C P3EA 1997032000006 19970320 00006 SO 1997 3 20 CA961011003 2 19960930 G 8550 539937 OIL SUMP CESSNA 182 182A 2072704 CE CONT O470 O470L 17026 SO MCAULY 2A36C 2A36C29 GL FLANGE CRACKED W E ENGINE SHUTDOWN K FLUID LOSS TX TAXI/GRND HDL 1 CA 803599L4 621309 (CAN) OIL LEAK AT OIL SUMP. RETORQUE OF SUMP BOLTS MADE LEAK WORSE. REMOVAL OF OIL SUMP REVEALED CRACK AT MOUNTING FLANG E. THE AIRCRAFT IS USED TO TOW GLIDERS OFF GRASS STRIP AND THIS NO DOUBT CONTRIBUTED TO THIS FAILURE. 1 H 7 1 3O 3 O NT 3A13 E273 5 C P880 1997032000008 19970320 00008 SO 1997 3 20 CA961016002 2 19960816 G 8550 530763A1 OIL SUMP CESSNA 172 172 2072402 CE CONT O300 O300A 17022 SO FWD DRAIN PLUG CRACKED W K NONE K O FLUID LOSS OTHER IN INSP/MAINT 1 CA 576 12403D6A (CAN) DURING ANNUAL INSPECTION AN OIL LEAK REPORTED BY THE OWNER LED TO INSPECTION OF THE OIL SUMP. EIGHT SMALL CRACKS W ERE FOUND FROM THE FORWARD DRAIN PLUG, ONLY TWO WERE LEAKING. THE CRACKS HAD ORIGINATED INSIDE THE SUMP AND WERE CAUSED BY CORROSION PITTING. 1 H 7 1 3O 3 O NT 3A12 E253 1999043000063 19990430 00063 EU 1999 4 30 CA961016004 1 19961010 G 3260 42196010201 SPEED SWITCH AMD FALC20 FALCON200 2730150 EU MLG FAILED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) PREMATURE FAILURE OF THIS PART NUMBER SPEED SWITCH HAS HAPPENED A NUMBER OF TIMES. REPORTS SHOW THE COMPONENTS AR E OUT OF CALIBRATION, AND THE CONTACTS ARE DIRTY. 2 L 7 2 4F RT A7EU 1997032000014 19970320 00014 NE 1997 3 20 CA961016011 2 19961004 G 7210 310924401 BEARING PWA 120 PW120 NE RED GEARBX SPALLED W K NONE O OTHER IN INSP/MAINT 1 CA 13967 1538 120324 (CAN) THE REDUCTION GEARBOX WAS FOUND TO BE MAKING METAL WHICH WAS IDENTIFIED TO BE M50. THE REDUCTION GEARBOX WAS DISMA NTLED AND INSPECTED AND THE SOURCE OF THE METAL CONTAMINATION WAS SPALLING OF THE #15 BEARING. 4 T E20NE 1997032000015 19970320 00015 NE 1997 3 20 CA961016012 2 19961007 G 7210 310924401 BEARING PWA PW121 PW121 52124 NE REDUCTION GEARBX SPALLED W K NONE O OTHER IN INSP/MAINT 1 CA 10947 8830 120916 (CAN) THE REDUCTION GEARBOX WAS SENT FOR INVESTIGATION AND REPAIR AFTER M50 METAL WAS FOUND IN A SOAP SAMPLE. INVESTIGAT ION FOUND THE SOURCE OF THE METAL WAS SPALLING OF THE #15 BEARING. 4 T E20NE 1997032000016 19970320 00016 NE 1997 3 20 CA961016013 2 19961004 G 7250 311260201 BLADE PWA 120 PW120 NE LP TURBINE FRACTURED W K NONE O OTHER IN INSP/MAINT 1 CA 17610 6098 120562 (CAN) ROUTINE HOT SECTION INSPECTION (HSI) FOUND THE ENGINE HAD SUFFERED A FRACTURE OF ONE LP PRESSURE TURBINE BLADE. TH E FRACTURE OCCURRED AT 60 PERCENT OF THE BLADE HEIGHT AND CAUSED SECONDARY DAMAGE TO THE BALANCE OF THE LP BLADES AND TO THE OTHER TURBINE COMPONENTS. 4 T E20NE 1997032000017 19970320 00017 EA 1997 3 20 CA961018001 1 19961008 G 5520 C6TEM101529 HINGE FITTING DHAV C6TE100111 DHAV DHC6 DHC6300 EA PWA PT6 PT6A27 52043 EA LT ELEV HOLE ELONGATED W K NONE E VIBRATION/BUFFET NR NOT REPORTED 1 CA (CAN) PILOT INDICATED INTERMITTENT VIBRATION AT LOWER SPEEDS. UPON INSPECTION, THE LEFT ELEVATOR WAS FOUND TO HAVE EXCES SIVE PLAY AT OUTBOARD HINGE. BOTH FITTING AND HINGE ARM WERE REPLACED AS THE BOLT HOLE WAS ELONGATED. 1 H 7 2 3T 4 T A9EA E4EA 1999043000064 19990430 00064 EU 1999 4 30 CA961018003 1 19961009 G 2435 03601018 BEARING LEARSIEGLER 23075008 AMD FALC20 FALCON200 2730150 EU START/GENERATOR FAILED W O OTHER J WARNING INDICATION CR CRUISE 1 CA 48 (CAN) UNITS NOT MEETING MANUFACTURER'S RECOMMENDED TBO'S DUE TO PREMATURE BEARING FAILURE. IN MOST CASES, THE PROBLEM IS AIR CREW SNAG, A RUMBLING FROM THE STARTER/GENERATOR. THIS FOUND ON TWO DIFFERENT GENERATORS. 2 L 7 2 4F RT A7EU 1997010200316 19970102 00316 NM 1997 1 2 CA961018005 1 19960620 G 3320 16405130 CONNECTOR DHAV DHC8 DHC8301 NM OVERHEAD BIN BURNT W E ENGINE SHUTDOWN B M SMOKE/FUMES/ODORS/SPARKS OVER TEMP TX TAXI/GRND HDL 1 CA (CAN) AT START OF POST ENGINE START CHECKS, THE CREW NOTICED AN ELECTRICAL BURNING SMELL, FOLLOWED BY SMOKE FROM BEHIND THE COPILOT SEAT. ONCE THE ENGINES SHUTDOWN, DC POWER REMOVED AND THE PASSENGER DOOR OPENED THE SMOKE SUBSIDED. OVERHEAD BIN CONNECTOR HAD BECOME SEVERELY OVERHEATED (OVER SEAT 1CD). INVESTIGATION UNDERWAY AT DHI AND BRAD. ALSO WIRE P/N 1-6 40523-0. 2 H 7 2 4T RT A13NM 1998020500440 19980205 00440 SO 1998 2 5 CA961018006 1 19961003 G 2730 AN36 BOLT 4030700 PIPER PA31T PA31T 7103124 SO PWA PT6 PT6A28 EA ELEV CABLE WORN W K NONE O OTHER IN INSP/MAINT 1 CA 52694 (CAN) ELEVATOR CABLE ATTACHMENT BOLT FOUND WORN WHERE THE CABLE ATTACHES TO THE ELEVATOR BELLCRANK. BOLT HAD TO BE REMOV ED TO SEE WEAR. 1 L 7 2 3T 4 T A8EA E4EA 1998020500441 19980205 00441 SO 1998 2 5 CA961018007 1 19961003 G 2730 4926502 BEARING 4030700 PIPER PA31T PA31T 7103124 SO PWA PT6 PT6A28 EA PUSHPULL ROD WORN W K NONE O OTHER IN INSP/MAINT 1 CA 969 52694 (CAN) ELEVATOR BELLCRANK FOUND WORN WHERE PUSH/PULL ROD IS ATTACHED. AD HAD BEEN COMPLIED WITH 969 HOURS PREVIOUS WITH N O PROBLEM FOUND. RECOMMEND CHANGE AT 1000 HOURS. 1 L 7 2 3T 4 T A8EA E4EA 1998020500442 19980205 00442 NE 1998 2 5 CA961018008 1 19961018 G 5330 SKIN CONAER LA4 LA4 5110302 NE LYC O360 O360A1A 41514 EA INTERIOR CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 1565 L894236A (CAN) INTERIOR OF FUSELAGE SKIN AND BULKHEADS FOUND CORRODED WHERE GLUE IS USED TO SECURE INSULATION TO COMPONENTS INSID E THE CABIN. 1 H 7 1 3O 3 O 1A13 E286 1998020500443 19980205 00443 SO 1998 2 5 CA961018009 1 19960927 G 5740 6210200 SUPPORT BRACKET PIPER PA28 PA28140 7102802 SO LT RT AIL CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 5190 (CAN) LEFT AND RIGHT AILERON BELLCRANK SUPPORT BRACKETS FOUND CRACKED AT FORWARD ATTACHMENT BOLT HOLES. RIGHT SIDE P/N 6 2102-01. 1 L 7 1 3O 2A13 1997032000027 19970320 00027 NE 1997 3 20 CA961018028 2 19961009 G 7250 310410401 PT BLADE PWA 118 PW118 NE 2ND STAGE FRACTURED W K NONE O OTHER IN INSP/MAINT 1 CA 14861 4107 115241 (CAN) TURBOMACHINE WAS SENT FOR INVESTIGATION AND REPAIR AFTER THE OPERATOR REPORTED 2ND STAGE PT BLADE DAMAGE. DISASSE MBLY FOUND THE CAUSE OF THE PT BLADE DAMAGE ON THE TURBOMACHINE WAS A FRACTURE OF ONE, 2ND STAGE PT BLADE HALF WAY DO WN THE AIRFOIL AND THE RESULTING LOSS OF HALF OF THE AIRFOIL. 4 T E20NE 1999043000068 19990430 00068 GL 1999 4 30 CA961021005 2 19960710 G 7250 6886407 BLADE HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL 1ST STAGE SEPARATED W O OTHER M E OVER TEMP VIBRATION/BUFFET LD LANDING 1 CA 415 CAT33356 CAE833904 (CAN) WHILE COMING IN TO LAND, THE PILOT NOTICED A SUDDEN INCREASE IN TOT AND VIBRATION LEVELS. LANDED IMMEDIATELY, NO PROBLEMS. TURBINE INSPECTION REVEALED ONE 1ST STAGE BLADE HAD SEPARATED FROM THE TURBINE DISC AT APPROXIMATELY .150 INC HES FROM BLADE ROOT. NO VISUAL INDICATION OF TIP RUB, EXCESSIVE TEMPERATURE, OR CORROSION. LAB ANALYSIS INDICATED A SU SPECTED HIGH CYCLE, LOW STRESS FATIGUE FROM A DESIGN CONTOUR CHANGE IN TRAILING EDGE OF BLADES. 1 G 7 1 3U 3 U H3WE E4CE 1997032000119 19970320 00119 SW 1997 3 20 CA961022013 1 19961012 G 3213 54530051 YOKE SWRNGN SWRNGN SA226 SA226* SW MAIN GEAR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA PAL32325 (CAN) ULTRASONIC INSPECTION OF LANDING GEAR YOKES AS PER AD 96-19-05. OF 41 YOKES INSPECTED 12 HAD CRACKS. ALL 12 HAD BE EN FOUND OK ONE YEAR PREVIOUS. ALL ARE FAIRLY HIGH TIME. SUBMITTER SUGGESTS THAT CRACKING NOT ENTIRELY RELATED TO FATIGU E AS SOME NEW YOKES HAVE BEEN RECEIVED WITH CRACKS. 2 L 7 2 4T RT A56W 1997032000122 19970320 00122 SO 1997 3 20 CA961023003 2 19961115 G 8530 SA501867 LOCK TAB CONT O360 IO360D 17025 SO ROCKER STUD NUT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 553135D (CAN) DURING INSPECTION WHILE BENDING THE TAB THAT SECURES THE ROCKER STUD NUT THE TAB CRACKED/BROKE. 3 O E1CE 1998020500445 19980205 00445 CE 1998 2 5 CA961025006 1 19961010 G 2916 511700712 SIGHT TUBE CESSNA 511700728 CESSNA 414 414A 2075907 CE CONT O520 TSIO520NB 17040 SO HYD IND MELTED W A UNSCHED LANDING J K WARNING INDICATION FLUID LOSS CL CLIMB 1 CA 519153 (CAN) THE NOSE GEAR FAILED TO LOCK IN THE UP POSITION AFTER TAKEOFF PREVENTING THE HYDRAULIC SYSTEM FROM CYCLING TO 'OPE N CENTRE' OPERATION. CONTINUED HYDRAULIC PRESSURE RAISED FLUID TEMPERATURE TO MELT PLASTIC RESERVOIR SIGHT TUBE AND SUBS EQUENT LOSS OF HYDRAULIC FLUID. INITIAL FAILURE TO LOCK IN UP POSITION WAS LIKELY CAUSED BY INCORRECT ATTACHMENT OF LECT RO TUG TOWING STRAP, RESULTING IN SLIGHT DEFORMATION OF UPLOCK ARM ON NOSE GEAR STRUT. 1 L 7 2 3O 3 O A7CE E8CE 1998020500446 19980205 00446 CE 1998 2 5 CA961025007 1 19961010 G 3230 249A4TT2 CHECK VALVE CESSNA 414 414A 2075907 CE CONT O520 TSIO520NB 17040 SO MLG FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 3372 519153 (CAN) DURING GROUND RETRACTION TESTS, THE GEAR FAILED TO RETRACT. HYDRAULIC PRESSURE CLIMBED SUFFICIENTLY TO TRIP PNEUMA TIC BLOWDOWN SYSTEM. PROBLEM TRACED TO CHECK VALVE WHICH ALLOWED HYDRAULIC PRESSURE TO BE APPLIED TO GEAR UP, GEAR DOWN AND PNEUMATIC BLOWDOWN SYSTEM SIMULTANEOUSLY. DISASSEMBLY OF VALVE REVEALED CONTAMINATION WHICH APPEARED TO BE A SMALL P IECE OF O-RING MATERIAL. 1 L 7 2 3O 3 O A7CE E8CE 1997032700084 19970327 00084 EA 1997 3 27 CA961028002 1 19961021 G 2750 19501100 BODY SYNCRO SKA1943A DHAV DHC6 DHC6 2802606 EA FLAP SELECTOR MIS MANUFACTUED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) THIRD BATCH (5 EACH) OF FLAP SELECTOR VALVE BODIES REJECTED BECAUSE THE THREADS IN THE PORTS (A) ARE EXCESSIVELY L ONG CAUSING 'O' RINGS TO REST ON THE LAST THREAD RATHER THAN THE SMOOTH WALL OF THE BORE. THIS RESULTS IN EXTERNAL LEAKA GE OF HYDRAULIC FLUID AND CONTAMINATION OF THE COCKPIT AREA ANYTIME SELECTION IS MADE. BRAD NOTIFIED. CORRECTIVE ACTION PENDING. 1 H 7 2 3T RT A9EA 1998020500451 19980205 00451 CE 1998 2 5 CA961105003 1 19961028 G 2820 1009200272 FUEL LINE BEECH 90 C90A 1152911 CE PWA PT6 PT6A21 52043 EA RT WING BLOCKED W A E UNSCHED LANDING ENGINE SHUTDOWN K FLUID LOSS CL CLIMB 1 CA PCE25641 (CAN) DURING CLIMB PILOT REPORTED FUEL LEAK AT THE TRAILING EDGE OF THE RIGHT HAND WING. RH ENGINE SHUT DOWN AND SINGLE ENGINE LANDING CARRIED OUT. EVENTUALLY FOUND THAT WHEN LINE WAS REMOVED FOR OBSTRUCTION TEST, THE LINE WAS FOUND BLOCKED . DURING MANUFACTURING PROCESS THE LINES HAD BEEN WELDED TO ANOTHER LINE WITH NO HOLES FOR THE FUEL FLOW. MANUFACTURER N OTIFIED. THIS IS A MULTIPLE LINE WITH 3 SECTIONS. 1 L 7 2 3T 4 T RT 3A20 E4EA 1997032700104 19970327 00104 EA 1997 3 27 CA961112010 1 19961101 G 3040 SYLZ50157 CONTROLLER BARBERCOL DHAV DHC6 DHC6300 EA PWA PT6 PT6A27 52043 EA LT WINDSHIELD FAILED W H DEACTIVATE SYST/CIRCUITS J WARNING INDICATION CR CRUISE 1 CA 1194B PCE42076 (CAN) DURING FLIGHT THE LEFT HAND WINDSHIELD HEAT SYSTEM CIRCUIT BREAKER POPPED. INSPECTION FOUND THAT THE WINDSHIELD HE AT CONTROLLER FOR THE LEFT SIDE WAS NOT CONTROLLING THE TIME ON AND OFF, THUS THE WINDSHIELD WAS BEING HEATED LONGER THA N RECOMMENDED. 1 H 7 2 3T 4 T A9EA E4EA 1997041500016 19970415 00016 NM 1997 4 15 CA961112011 1 19961106 G 2131 10251831 CONTROLLER ALLIED SIGNA BOEING 727 727171C 1384057 NM PWA JT8 JT8D7A 52053 NE CABIN PRESS FAULTY W K NONE O OTHER DE DESCENT 1 CA 125539 P653620B (CAN) DURING DESCENT THE FLIGHT CREW NOTICED THE PRESSURIZATION WOULD NOT INITIALLY RESPOND TO THE CHANGING ALTITUDE, TH EN IT WOULD CAUSE A RAPID CABIN PRESSURE CHANGE TO CATCH UP WITH THE AIRCRAFT ALTITUDE. POST FLIGHT TROUBLESHOOTING LED TO THE CHANGE OF THE AUTOMATIC PRESSURE CONTROLLER AND THE AIRCRAFT RETURNED TO SERVICE. 2 L 7 3 4F 4 F A3WE E2EA 1998040200021 19980402 00021 EU 1998 4 2 CA961112012 1 19960207 G 4950 011469914 VALVE SUNDSTRAND 011469914 AMD FALC20 FALCON200 2730150 EU APU BLEED FAILED W A B I UNSCHED LANDING EMER. DESCENT CABIN DEPRESSURIZATION G MULTIPLE FAILURE CL CLIMB 1 CA 071 (CAN) CABIN PRESSURE STARTED TO CLIMB AFTER PASSING THROUGH 18,000 FEET. MAINTENANCE TROUBLESHOOTING REVEALED SWITCH ON APU BLEED VALVE (199H) FAILED IN THE OPEN POSITION. TEAR DOWN REPORT REQUESTED FROM FALCON JET FOR DEFECTIVE VALVE. 2 L 7 2 4F RT A7EU 1998041700420 19980417 00420 WP 1998 4 17 CA961112025 2 19961017 G 7314 307085057 FUEL PUMP GARRTT BRAERO DH125 BAE125800A 1500285 EU GARRTT TFE731 TFE7315R 01518 WP NR 1 ENG FAILED W O OTHER X ENGINE FLAMEOUT TX TAXI/GRND HDL 1 CA 4220 P91317 P91317 (CAN) ON START OF NR 1 ENGINE, THE ITT REACHED 600 DEGREES CENTIGRADE AND THE ENGINE AUTOMATICALLY SHUT-DOWN. MAINTENAN CE REVEALED THE CAUSE WAS FAILURE OF THE HIGH PRESSURE PUMP. 2 L 7 2 4F 4 F RT A3EU E6WE 1997040200015 19970402 00015 EA 1997 4 2 CA961112031 1 19961029 G 2435 215T50901010 DUCT INLET 215T5091018 CNDAIR CL215 CL2151A10 EA START/GEN COOL SPLIT W K NONE O OTHER NR NOT REPORTED 1 CA 51 (CAN) WELD AT COOLING DUCT ASSEMBLY HAS NO METAL PENETRATION. SKIN JOINT SPLIT AND IT CHAFED ON THE OIL RETURN LINE WHIC H PASSED BETWEEN THIS DUCT ASSEMBLY, AND THE COMPRESSOR OF THE ENGINE. THE CHAFING WAS DEEP ENOUGH TO HAVE TO REPLACE TH E LINE. VISUAL INSPECTION OF ANOTHER AIRCRAFT SHOWS A SIMILAR PROBLEM WILL OCCUR. CANADAIR HAS BEEN ADVISED. 2 H 7 2 4R A14EA 1997041500018 19970415 00018 1997 4 15 CA961112040 1 19960730 G 7810 115024003 DIFFUSER 113063008 LYC T53 T5313B 41549 NE COMBUSTOR EXH CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA LE07605 (CAN) EXHAUST DIFFUSER RECEIVED FOR INSPECTION, 4" X 1" METAL BREAK-OFF AND 2" CIRCUMFERENTIAL CRACK FOUND ON FORWARD FA CE OF THE INNER CONE. CAUSE OF CRACK AND BREAK IS UNKNOWN. 4 U E17EA 1998020500460 19980205 00460 SO 1998 2 5 CA961115013 1 19961106 G 2720 6342005 PEDAL BAR 6345919 PIPER PA28 PA28140 7102802 SO LYC O320 O320E3D 41508 EA LT HAND CRACKED W A UNSCHED LANDING F FLT CONT AFFECTED CR CRUISE 1 CA 9201 L4764427A (CAN) LEFT RUDDER PEDAL BAR CRACKED IN FLIGHT. AIRCRAFT LANDED FROM RIGHT SEAT. RUDDER AND BRAKES LOST TO LEFT SEAT. PIP ER SERVICE LETTER 671 COVERS THE PROBLEM. 1 L 7 1 3O 3 O 2A13 E274 1997041500046 19970415 00046 EA 1997 4 15 CA961118015 1 19961110 G 2530 AE0405A00 FAN CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE GALLEY EXHAUST OVERLOAD W K NONE J WARNING INDICATION CL CLIMB 1 CA 1122 GEE807385 (CAN) DIRECT CURRENT EMERGENCY BUS CAUTION LIGHT ON AT FL180 ON CLIMB OUT. AT SAME TIME CIRCUIT BREAKER C5 GALLEY FAN PO PPED AND WOULD NOT RESET. CIRCUIT BREAKER R7 POPPED AS A RESULT OF CIRCUIT BREAKER C5 GALLEY EXHAUST FAN FAULT. FAN REPL ACED. 2 L 7 2 4F 4 F RT A21EA E15NE 1997041500048 19970415 00048 EA 1997 4 15 CA961120002 2 19961215 G 8530 OIL RING CESSNA 172 172 2072402 CE LYC O320 O320H2AD 41508 EA #4 CYLINDER FAILED W O OTHER R PARTIAL RPM/PWR LOSS CR CRUISE 1 CA RL489676TA (CAN) LOSS OF ENGINE POWER IN FLIGHT. ENGINE CONTINUED TO OPERATE AND FLIGHT CONTINUED TO DESTINATION. POST FLIGHT INSPE CTION FOUND #4 CYLINDER OIL RING FAILED. 1 H 7 1 3O 3 O NT 3A12 E274 1997042200007 19970422 00007 SW 1997 4 22 CA961120010 1 19960913 G 2821 206005 FUEL FILTER BELL 206 206B 1181511 SW OUTLET PORT UNMODIFIED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) MODIFICATION OF OUTLET BLEED PORT NOT INSTALLED. THIS CONDITION COULD LEAD TO ENGINE FLAME OUT (REF: BELL ASB 206- 86-34). 1 G 7 1 3U H2SW 1997042200009 19970422 00009 NE 1997 4 22 CA961120012 2 19961106 G 7230 310454601 BEARING PWA 120 PW120A NE HP SHAFT NR 4 FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 11372 121127 (CAN) ENGINE SENT FOR INVESTIGATION AND REPAIR AFTER OPERATOR REPORTED HP ROTOR LOCKUP. IT WAS ALSO REPORTED THAT THERE WAS NO FILTER BYPASS AND THE ENGINE HAD BEEN INVOLVED IN A LIGHTNING STRIKE. DISASSEMBLY FOUND THE CAUSE OF THE HP ROT OR LOCKUP WAS A CATASTROPHIC FAILURE OF THE NR 4 BEARING. THE FAILURE OF THE NR 4 BEARING APPEARS TO BE THE RESULT OF E ITHER INSUFFICIENT TORQUING OF THE NR 4 BEARING RETAINING NUT AT THE LAST BUILD, OR THE FAILURE OF THE NR 4 BEARING RETA INING NUT CUPWASHER TO PREVENT THE NR 4 BEARING RETAINING NUT FROM ROTATING. 4 T E20NE 1997042200012 19970422 00012 NM 1997 4 22 CA961125005 1 19961115 G 2720 CONTROL DHAV DHAV DHC8 DHC8102 2809003 NM RUDDER LOCKED W A A UNSCHED LANDING F FLT CONT AFFECTED TO TAKEOFF 1 CA (CAN) AT V1 SPEED #1 ALTERNATOR FELL OFF LINE, AFTER ROTATION, SELECTED GEAR UP, DURING RETRACTION, RUDDER CONTROL LOCKE D UP, (BOTH RUDDER AND PEDALS). AT 100 FEET, AIRSPEED 120 TO 130 KNOTS, EMERGENCY DECLARED AND GEAR SELECTED DOWN. DURI NG EXTENSION RUDDER CONTROL WAS RESTORED. ALL OTHER INDICATIONS NORMAL. WEATHER REPORTED AS LOW TEMP WITH RAIN DRIZZLE. OPERATOR PROVIDED TROUBLESHOOTING INFO BY MANUFACTURER. COMPLETE RUDDER SYSTEM FROM FRONT TO BACK OF AIRCRAFT WAS INSPEC TED WITH NOTHING FOUND. MOISTURE MAY HAVE CAUSED FREEZING PROBLEMS. TO LOCK RUDDER SYSTEM AS REPORTED, RUDDER QUADRANT(S ) AND/OR RUDDER PEDALS NEED TO BE JAMMED. EVEN WITH HYDRAULIC PROBLEM, RUDDER PEDALS WOULD STILL BE MOVEABLE. 2 H 7 2 4T RT A13NM 1997042200016 19970422 00016 WP 1997 4 22 CA961125009 1 19961112 G 2530 CA167072 ELECT RECEPTACLE DOUG DC9 DC932 3022066 WP PWA JT8 JT8D7A 52053 NE GALLEY OVEN SHORTED W K NONE B SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 CA P657239D (CAN) FLIGHT ATTENDANT REPORT SMOKE & SPARKS COMING FROM GALLEY OVEN AT POSITION #19. MAINTENANCE ACTION INVOLVED INSTAL LING NEW RECEPTACLE AND OVEN CHECKED SERVICEABLE. 2 L 7 2 4F 4 F A6WE E2EA 1997042200017 19970422 00017 EA 1997 4 22 CA961125010 1 19961107 G 2760 270003 PCU CNDAIR CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE LT HAND SPOILER FAILED W K NONE F FLT CONT AFFECTED NR NOT REPORTED 1 CA 1048 GEE807389 (CAN) FLIGHT SPOILER FAULT MESSAGE. CIRCUIT BREAKER RESET, MESSAGE STILL ON. LEFT HAND FLIGHT SPOILER REMAINED WHITE AFT ER GROUND LIFT DUMP TEST. REQUIRED MAINTENANCE ACTION (27-60-421) CARRIED OUT. LEFT HAND SPOILER RE-RIGGED DUE TO ASYMME TRY FAULT AND LEFT HAND INBOARD FLIGHT SPOILER POWER CONTROL UNIT (PCU) CHANGED. 2 L 7 2 4F 4 F RT A21EA E15NE 1997042200018 19970422 00018 EA 1997 4 22 CA961125012 1 19961113 G 2750 855D1005 BPSU CNDAIR CNDAIR CL600 CL6002B19 EA GE CF34 CF343A 30015 NE RIGHT HAND FLAP FAILED W K NONE F J FLT CONT AFFECTED WARNING INDICATION TO TAKEOFF 1 CA 4267 807317 (CAN) ON TAKEOFF THE CREW REPORTED FLAP FAIL AMBER CAUTION MESSAGE. RIGHT HAND BRAKE AND POSITION SENSOR UNIT CHANGED AS PER MM 27-51-10. SB'S 601R-27-043 (WATER INGRESS) AND -045 HARNESS REPLACEMENT, MAY APPLY. ALSO SB 601R-27-056 REPLACEM ENT OF -5 BPSU WITH A -7 APPLIES. 2 L 7 2 4F 4 F RT A21EA E15NE 1997042200019 19970422 00019 SW 1997 4 22 CA961125015 1 19961013 G 8010 MS25089C5 SWITCH BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL STARTER SWITCH INTERMITTENT W K NONE O OTHER IN INSP/MAINT 1 CA CAE800419BA (CAN) SWITCH WOULD NOT ENGAGE STARTER WHEN DEPRESSED. STARTER BUTTON ENGAGED WHEN MOVED FROM SIDE TO SIDE. 1 G 7 1 3U 3 U H2SW E4CE 1997042200020 19970422 00020 CE 1997 4 22 CA961126002 1 19961118 G 7120 12510104 BRACKET CESSNA 207 207 2073602 CE CONT O520 IO520F 17032 SO MCAULY D3A34 D3A34C404 GL ENGINE MT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 9067 286169R 792737 (CAN) CRACK WAS FOUND DURING A VISUAL INSPECTION OF THE ENGINE COMPARTMENT WHILE PERFORMING AN ENGINE CHANGE. 1 H 7 1 3O 3 O A16CE E5CE 5 C P47GL 1997042200021 19970422 00021 EU 1997 4 22 CA961126003 1 19961118 G 5414 SKIN BNORM BNORM BN2 BN2A26 1520226 EU LYC O540 O540E4C5 41532 EA NACELLE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA RL815340 (CAN) SKIN ON THE NACELLE AFT CLOSURE FOUND CRACKED AT AREA DIRECTLY ABOVE THE LANDING GEAR FAIRING. THE REAR NACELLE BU LKHEAD PASSES THROUGH THE CRACKED PLATE. 1 H 7 2 3O 3 O A17EU E295 1997042200022 19970422 00022 EU 1997 4 22 CA961126004 1 19961118 G 5522 NB31233 ELEVATOR BNORM BNORM BN2 BN2A26 1520226 EU LYC O540 O540E4C5 41532 EA RIGHT SIDE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA RL815340 (CAN) RIGHT SIDE ELEVATOR AT 44 INCHES INBOARD OF TIP SMOKING RIVETS NOTED WHICH LED TO DISCOVERY OF A CRACK. FURTHER IN VESTIGATION NOTED THAT PILOTS HAD BEEN VERBALLY REPORTING SOME VIBRATION. 1 H 7 2 3O 3 O A17EU E295 1997042200023 19970422 00023 NM 1997 4 22 CA961128001 1 19961120 G 7931 APT761000100DW TRANSMITTER DHAV DHC8 DHC8301 NM PWA PW120 PW123 NE OIL SYSTEM FAULTY W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) #2 ENGINE OIL PRESSURE DROPPED TO ZERO ON CLIMBOUT. THERE WAS NO WARNING LIGHT INDICATION. AIRCRAFT RETURNED TO BA SE. POST FLIGHT INSPECTION FOUND THE OIL PRESSURE TRANSMITTER FAULTY. THE OIL PRESSURE TRANSMITTER WAS REPLACED. 2 H 7 2 4T 4 T RT A13NM E20NE 1997042200024 19970422 00024 NM 1997 4 22 CA961128002 1 19961120 G 3060 7826891 BRUSH BLOCK HAMSTD DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE NR2 PROPELLER BURNT W H DEACTIVATE SYST/CIRCUITS J WARNING INDICATION CR CRUISE 1 CA 900742 120226 881010 (CAN) RIGHT HAND TRANSFORMER RECTIFIER UNIT (TRU) FAILED. CIRCUIT BREAKER WOULD NOT RESET. POST FLIGHT INSPECTION FOUND THE #2 PROP DE-ICE BRUSH BLOCK BURNT CAUSING THE R/H "B" PHASE CIRCUIT BREAKER TO "POP". BRUSH BLOCK REPLACED. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 1997042200025 19970422 00025 NM 1997 4 22 CA961128003 1 19961114 G 2160 7787272 PACK VALVE DHAV DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE NR 2 BLEED JAMMED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 CA 120854 (CAN) BLEED AIR SMELL IN CABIN AFTER TAKEOFF, FOLLOWED BY LAVATORY SMOKE ALARM AND THE #2 BLEED HOT CAUTION LIGHT IN FUL L HOT POSITION. SMOKE AND SMELL FROM FULL HOT AIR IN THE AIR CONDITIONING SYSTEM. PACK VALVE REPLACED. 2 H 7 2 4T 4 T RT A13NM E20NE 1997042200026 19970422 00026 NM 1997 4 22 CA961128004 1 19961120 G 2910 82970010391 LINE DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE LH MLG AFT DOOR CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 120165 (CAN) HYDRAULIC LEAK NOTED FROM LEFT HAND MAIN LANDING GEAR AFT DOOR HYDRAULIC LINE. 2 H 7 2 4T 4 T RT A13NM E20NE 1997042200027 19970422 00027 NE 1997 4 22 CA961128005 3 19961120 G 6112 86553115 BLADE DHAV DHC8 DHC8311 1386006 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF15 NE BLADE HEATER BURNED HOLE W O OTHER J WARNING INDICATION CR CRUISE 1 CA 123126 901008 (CAN) PROPELLER DE-ICE UNSERVICEABLE. #2 PROPELLER BLADE FOUND WITH A HOLE BURNED IN THE DE-ICE BOOT BY A SHORT CIRCUIT IN THE DE-ICE HEATER. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 1997042200028 19970422 00028 NE 1997 4 22 CA961128006 2 19961120 G 7230 230098401 BEARING CAGE LYC ALF502 ALF502R5 41580 NE #3 BEARING BREAKING APART W K NONE O OTHER IN INSP/MAINT 1 CA LF05629A (CAN) #2 ENGINE OIL FILTER IMPENDING BY-PASS BUTTON EXTENDED. #2 FULL FLOW CHIP DETECTOR FOUND TO BE METAL CONTAMINATED. METAL ANALYSIS FOUND TO BE #3 BEARING CAGE MATERIAL. ON DISASSEMBLY #3 BEARING CAGE WAS FOUND TO BE BREAKING APART. 4 F E6NE 1997042200029 19970422 00029 NM 1997 4 22 CA961128008 1 19961127 G 2420 10014B22 SENSOR WIRE DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE AC GEN CKT BROKEN W H DEACTIVATE SYST/CIRCUITS M J OVER TEMP WARNING INDICATION CR CRUISE 1 CA 120840 (CAN) AC GENERATOR HOT CAUTION LIGHT ILLUMINATED IN FLIGHT. AC GENERATOR CIRCUIT BREAKER PULLED. SNAG FOUND TO BE BROKEN SENSOR WIRE AT PLUG 2421J4, PIN 11. 2 H 7 2 4T 4 T RT A13NM E20NE 1997042200030 19970422 00030 NM 1997 4 22 CA961128012 1 19961120 G 6220 A1551 SPACER ROBSIN R22 R22BETA NM LYC O320 O320B2C 41508 EA SPINDLE ASSEMBLY CORRODED W K NONE E F VIBRATION/BUFFET FLT CONT AFFECTED CR CRUISE 1 CA 837 L1662739A (CAN) PILOT REPORTED A CYCLIC STICK AND MAIN ROTOR VIBRATION. IT WAS FOUND THAT THE SPINDLE BEARINGS WERE ROUGH. AFTER D ISASSEMBLY THE INNER SPACER (P/N A155-1) WAS FOUND TO BE SEVERELY CORRODED AND PITTED. THE PART LOOKED TO HAVE BAD MACHI NING. THE BEARINGS BECAME ROUGH DUE TO THE METAL OFF THE SPACER. 1 G 7 1 3O 3 O H10WE E274 1997042200031 19970422 00031 SO 1997 4 22 CA961128014 1 19961121 G 7712 650086 TORQUEMETER HAMSTD 6850209 LKHEED 382 382G 526414U SO ALLSN 501D 501D22A 03006 GL HAMSTD 54H 54H60117 NE TORQUE PICKUP LOOSE W K NONE O OTHER CR CRUISE 1 CA 3450 650086 550195 235867 (CAN) IN CRUISE NR 3 ENGINE TORQUE INDICATION FAILED. POST FLIGHT MAINTENANCE INSPECTION FOUND THE TORQUE PICKUP TO BE RUBBING ON THE TORQUE SHAFT AND SOME TORQUEMETER ATTACHMENT NUTS MISSING AT THE REDUCTION GEARBOX ATTACH POINT. AIRCRAF T FERRIED FOR ENGINE CHANGE. 2 H 7 4 4T 4 T A1SO E282 6 C P906 1997042200032 19970422 00032 WP 1997 4 22 CA961128024 1 19961122 G 7810 9063239 CLAMP BAND CVAC 340 340CVAC 242270A WP ALLSN 501D 501D13 03004 GL LT EXH WORN W E F ENGINE SHUTDOWN ACTIVATE FIRE EXT. M OVER TEMP CR CRUISE 1 CA 500589 (CAN) LEFT HAND ZONE 1 FIRE WARNING ILLUMINATED. ENGINE SECURED AND FIRE BOTTLES DISCHARGED. AIRCRAFT LANDED SAFELY. MAI NTENANCE CHECK FOUND LEFT HAND EXHAUST PIPE UNIVERSAL COUPLING HAD SEPARATED ALLOWING EXHAUST GASES TO ENTER ENGINE NACE LLE. COUPLING FAILED DUE TO WEAR OF FLANGE AND CLAMP BAND. COUPLING REPLACED. 2 L 7 2 4R 4 T 6A6 E282 1997042200033 19970422 00033 NE 1997 4 22 CA961128026 2 19961121 G 7210 3100662301 BEARING PWA 118 PW118 NE RED GEARBX NR 18 SPALLED W K NONE O OTHER IN INSP/MAINT 1 CA 15250 4993 115219 (CAN) METAL ON THE CHIP DETECTOR CAUSED THE REDUCTION GEARBOX TO BE REMOVED AND SENT FOR INVESTIGATION AND REPAIR. INSPE CTION OF THE RGB FOUND THE #18 BEARING TO HAVE A SEVERELY SPALLED REAR INNER HALF RACE. MATERIAL LOSS EXTENDED AROUND MO ST OF THE CIRCUMFERENCE. SUBSTANTIAL MATERIAL LOSS OCCURRED AND SECONDARY DAMAGE WAS SUSTAINED BY SEVERAL OTHER 2ND STAG E BEARINGS. 4 T E20NE 1997042200034 19970422 00034 EA 1997 4 22 CA961128027 1 19961119 G 3260 SENSOR CNDAIR CL600 CL6002B19 EA GE CF34 CF343A 30015 NE NOSE OUT OF ADJUST W A UNSCHED LANDING O OTHER CL CLIMB 1 CA 4391 807195 (CAN) UNABLE TO RETRACT NOSE GEAR. FOUND NOSE GEAR SENSOR OUT OF ADJUST. 2 L 7 2 4F 4 F RT A21EA E15NE 1997042200035 19970422 00035 1997 4 22 CA961128030 4 19961117 G 2350 G699306 ATC CNTRL PANEL DOUG DC9 DC932 3022066 WP PWA JT8 JT8D7A 52053 NE COCKPIT ELECT SHORT W D RETURN TO BLOCK B SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 CA P656860D (CAN) AIRCRAFT RETURNED TO GATE DUE TO AIR TRAFFIC CONTROL PANEL ELECTRICAL SHORT AND CIRCUIT BREAKER ATC-1 POPPED. ATC CONTROL PANEL REPLACED AND SYSTEM CHECKED SERVICEABLE. 2 L 7 2 4F 4 F A6WE E2EA 1997042200036 19970422 00036 WP 1997 4 22 CA961128031 1 19961117 G 2560 375321399 LANYARD BRACKET DOUG DC9 DC932 3022066 WP PWA JT8 JT8D7A 52053 NE GALLEY DOOR BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA P657459D (CAN) GALLEY DOOR CHUTE PACK CAME ADRIFT. UNABLE TO INSTALL DUE TO BROKEN LANYARD ATTACHMENT BRACKET. MAINTENANCE INSTAL LED NEW BRACKET CHECKED SERVICEABLE. 2 L 7 2 4F 4 F A6WE E2EA 1997042200037 19970422 00037 NE 1997 4 22 CA961128032 2 19961102 G 7322 7733333 FUEL CONTRL UNIT HAMSTD PWA JT9 JT9D7R4D 52054 NE #1 ENGINE FAULTY W A UNSCHED LANDING O OTHER CL CLIMB 1 CA 709606 (CAN) 15 MINUTES INTO FLIGHT THERE WAS NO POWER RESPONSE FROM THE LEFT HAND THROTTLE (#1 ENGINE). AIRCRAFT RETURNED TO P OINT OF DEPARTURE. POST FLIGHT INSPECTION FOUND #1 ENGINE FUEL CONTROL UNIT FAULTY. FCU REPLACED. GROUND RUN CARRIED OUT AND CHECKED SERVICEABLE. 4 F E3NE 1997042200038 19970422 00038 EA 1997 4 22 CA961128033 1 19961121 G 3230 BRACKET CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE NOSE MISALIGNED W O OTHER J WARNING INDICATION TO TAKEOFF 1 CA 788 GEE807399 (CAN) GEAR UNSAFE ON RETRACTION. NOSE WHEEL REMAINED DOWN AND WOULD NOT RETRACT. FOUND NOSE GEAR PROXIMITY SENSOR BRACKE T MISALIGNED ON OLEO EXTEND. 2 L 7 2 4F 4 F RT A21EA E15NE 1997042200039 19970422 00039 CE 1997 4 22 CA961203001 1 19961106 G 3260 MS243311 SWITCH MITSUELECT MTSBSI MU2 MU2B35 5780411 CE GARRTT TPE331 TPE3316 01514 WP NLG SWITCH BROKEN WIRE W L ABORTED APPROACH J N WARNING INDICATION FALSE WARNING AP APPROACH 1 CA P20276C (CAN) DURING APPROACH THE PILOT COULD NOT GET AN INDICATION OF THE NOSE GEAR DOWN AND LOCKED. EMERGENCY EXTENSION PERFOR MED AND THE AIRCRAFT LANDED SAFELY. MAINTENANCE FOUND A BROKEN WIRE WHERE THE WIRES ENTER A SEALED SWITCH. THE SWITCH WA S REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. 1 H 7 2 3T 4 T RT A10SW E4WE 1997042200040 19970422 00040 NE 1997 4 22 CA961203003 2 19961104 G 7200 ENGINE BOEING 727 727227 1384078 NM PWA JT8 JT8D9A 52048 NE #2 ENGINE OIL BYPASS LITE W A E UNSCHED LANDING ENGINE SHUTDOWN J WARNING INDICATION CR CRUISE 1 CA 665763 (CAN) DURING CLIMB #2 ENGINE LOW OIL PRESSURE/FILTER BYPASS ILLUMINATED. POST FLIGHT INSPECTION OF THE OIL FILTER FOUND NO FAULT. THE ENGINE WAS GROUND RUN SERVICEABLE. ITEM DEFERRED PER MEL TO NITE STOP FOR FURTHER INVESTIGATION. 2 L 7 3 4F 4 F A3WE E2EA 1997042200041 19970422 00041 SW 1997 4 22 CA961203008 1 19960925 G 6420 204011769001 BEARING RACE BELL 206 206L3 1182108 SW ALLSN 250C 250C30P 03013 GL T/R TRUNNION ROUGH W K NONE O OTHER IN INSP/MAINT 1 CA 289 CAE895063 (CAN) DURING INSPECTION OF TAIL ROTOR, A ROUGH, RATCHETING FEELING WAS NOTICED. FURTHER INSPECTION REVEALED THAT THE INN ER BEARING RACE WAS CRACKED. 1 G 7 1 3U 3 U H2SW E1GL 1997042200042 19970422 00042 SW 1997 4 22 CA961203010 1 19961125 G 6230 206010441001 BEARING BELL 206 206L4 1182110 SW ALLSN 250C 250C30P 03013 GL SWASHPLATE WORN W K NONE O OTHER IN INSP/MAINT 1 CA 3220 CAE895715 (CAN) UNUSUAL PLAY IN SWASHPLATE. INSPECTION FOUND TEFLON ON BEARINGS WORN AWAY. 1 G 7 1 3U 3 U NC H2SW E1GL 1997042200043 19970422 00043 NE 1997 4 22 CA961203012 2 19961125 G 7260 602070009 BEARING DOWTY BRAERO 748 HS7482B 1500248 EU RROYCE DART DART5352 54509 NE ACCESSORY GEARBX FAILED W E ENGINE SHUTDOWN O OTHER AP APPROACH 1 CA 568 DRG106164 7149 (CAN) FORWARD TUNNEL SHAFT BEARING FAILED CAUSING FORWARD END CAP OF SHAFT TO DISCONNECT FROM INPUT SHAFT. SUSPECT BEARI NG FAILURE ATTRIBUTED T OIL STARVATION; PLUGGED JET AND/OR PUMP FAILURE. GEARBOX SHIPPED FOR TEARDOWN. 2 L 7 2 3T 4 T A24EU E297 1997042200044 19970422 00044 SO 1997 4 22 CA961203014 1 19961119 G 3231 RODS EMB EMB 110 EMB110P1 3260122 SO NLG DOORS MIS ADJUSTED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) ON TAKEOFF GEAR SELECTED UP. GEAR INSTRANSIT LIGHT REMAINED ON. INSPECTION FOUND THAT THE NOSE LANDING GEAR DOOR W ERE ADJUSTED TOO TIGHT AND WITH THE AIR LOADS IN FLIGHT WOULD PULL GEAR DOWN ENOUGH TO BREAK THE UP SWITCH GIVING THE IN TRANSIT LIGHT. DOOR RODS ADJUSTED. 1 L 7 2 4T A21SO 1997042200045 19970422 00045 NM 1997 4 22 CA961203015 1 19961116 G 5280 85420056103 HINGE ARM DHAV 85420047001 DHAV DHC8 DHC8301 NM PWA PW120 PW123 NE RIGHT MLG DOOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 16589 123045 (CAN) DURING WALK AROUND, THE FORWARD HINGE ARM ON THE RIGHT HAND MAIN LANDING GEAR FORWARD GEAR DOOR WAS FOUND BROKEN O FF. GEAR DOOR ALSO HAD COMPOSITE DAMAGE. 2 H 7 2 4T 4 T RT A13NM E20NE 1997042200046 19970422 00046 NM 1997 4 22 CA961203016 1 19961118 G 5280 83231046001 BUSHING DHAV 85420014009 DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE MLG DOOR ARM MISSING W K NONE O OTHER AP APPROACH 1 CA 120388 (CAN) ON A WALK AROUND IT WAS NOTICED THAT THE FORWARD GEAR DOOR FOR THE RIGHT HAND MAIN LANDING GEAR WAS JAMMED TIGHT A GAINST THE DRAG STRUT. INSPECTION FOUND THAT THE THREADED BUSHING WHICH SECURES THE FORWARD DOOR ACTUATOR CONNECTING BOL T ROD NAS6204-13H TO FORWARD DOOR REAR HINGE HAD LOOSENED AND FALLEN OFF. DURING FLIGHT THE CONNECTING ROD BOLT HAD MIGR ATED OUT HALFWAY AND WHEN GEAR WAS EXTENDED, THE BOLT CONTACTED AND DAMAGED THE NACELLE STRUCTURE. 2 H 7 2 4T 4 T RT A13NM E20NE 1997042200047 19970422 00047 NM 1997 4 22 CA961203017 1 19961122 G 5280 83231046001 BUSHING DHAV 85420014009 DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE RT MLG DOOR ARM MISSING W A UNSCHED LANDING O OTHER CL CLIMB 1 CA 120817 (CAN) AFTER TAKEOFF CREW NOTICED THAT FORWARD GEAR DOOR FOR THE RIGHT HAND MAIN LANDING GEAR WAS NOT CLOSED, AND WAS FLA PPING AROUND. ALL GEAR INDICATIONS NORMAL. BOLT NAS6204-13H AND THREADED BUSHING WHICH CONNECTS FORWARD DOOR ACTUATOR CO NNECTING ROD WAS MISSING AND FORWARD HINGE ARM WAS FOUND BENT. 2 H 7 2 4T 4 T RT A13NM E20NE 1997042200048 19970422 00048 NE 1997 4 22 CA961203018 2 19961125 G 7314 311169301 SPUR GEAR PWA 118 PW118 NE FUEL PUMP DRIVE DAMAGED TEETH W O OTHER O OTHER CR CRUISE 1 CA 20705 10728 115119 (CAN) ENGINE WAS SENT FOR INVESTIGATION AND REPAIR AFTER THE OPERATOR REPORTED AN INFLIGHT SHUTDOWN. INSPECTION FOUND TH E CAUSE OF THE INFLIGHT SHUTDOWN WAS A FAILURE OF THE MAIN ACCESSORY DRIVE GEAR AND THE FUEL PUMP DRIVE GEAR. THE MAIN A CCESSORY DRIVE (SPUR) GEAR HAD DAMAGE TO ALL ITS TEETH WITH THREE TEETH BROKEN OFF, CAUSING LOSS OF DRIVE TO THE FUEL PU MP RESULTING IN ENGINE FUEL STARVATION AND INFLIGHT SHUTDOWN. 4 T E20NE 1997042200049 19970422 00049 EA 1997 4 22 CA961203019 2 19961112 G 7414 4373 MAGNETO SLICK PARTEN P68 P68C 6780105 EU LYC O360 IO360A1B6 41514 EA LH MAGNETO FAILED W O OTHER O OTHER TX TAXI/GRND HDL 1 CA 391 94110070 L2371751A (CAN) ENGINE SHUTDOWN WITHOUT INCIDENT. ON NEXT START BOTH THE RIGHT HAND AND LEFT HAND MAGNETOS WERE DEAD, NO SPARK. 1 H 7 2 3O 3 O A31EU 1E10 1997042200050 19970422 00050 SW 1997 4 22 CA961203020 1 19961121 G 6230 206010455103 CAP BELL 206 206B 1181511 SW SWASHPLATE WORN W K NONE O OTHER IN INSP/MAINT 1 CA 15266 5363 (CAN) DURING A SWASHPLATE INSPECTION, GREASE WAS FOUND AROUND THE TOP SEAL. COVER REMOVED AND SEAL AND CAP REPLACED. 1 G 7 1 3U H2SW 1997042200051 19970422 00051 SW 1997 4 22 CA961203021 1 19961119 G 6330 206033506101 RESTRAINT BELL 206 206L 1181522 SW UPPER DECK WORN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) RESTRAINT BEARING FELT LOOSE. FOUND SWAGED BEARING LOOSE IN RESTRAINT. 1 G 7 1 3U H2SW 1997042200052 19970422 00052 EA 1997 4 22 CA961205001 2 19961126 G 7310 3011849 TUBE ASSEMBLY BEECH 100 A100 1152915 CE PWA PT6 PT6A28 EA FUEL BYPASS CRACKED W O OTHER K FLUID LOSS AP APPROACH 1 CA PCE50447 (CAN) THE PILOT NOTICED A SUBSTANTIAL INCREASE IN FUEL FLOW PRIOR TO LANDING. POST FLIGHT INSPECTION FOUND THE FUEL SYST EM BYPASS LINE CRACKED AT THE SLEEVE, WHICH IS SILVER SOLDERED ONTO THE END OF THE STAINLESS STEEL LINE. THE SUBMITTER S TATES THIS SAME FAULT HAS OCCURRED THREE OTHER TIMES ON COMPANY AIRCRAFT. THE PILOT DID NOT SHUTDOWN THE ENGINE, BUT STA TED IF THE FAULT HAD OCCURRED ON A LONGER TRIP OR IN CRUISE HE WOULD HAVE HAD TO DO AN INFLIGHT SHUTDOWN. 1 L 7 2 3T 4 T A14CE E4EA 1997042200053 19970422 00053 NM 1997 4 22 CA961205002 1 19961128 G 2770 NAS130431 BOLT DHAV DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE ELEVATOR RUSTED W A K NONE O OTHER IN INSP/MAINT 1 CA 18721 120305 (CAN) BOLTS HOLDING RUBBER BUMPERS ON ELEVATOR GUST LOCKS ARE SEVERELY CORRODED. COULD CAUSE ELEVATOR LOCK UP IF BOLTS S EPARATED. FLEET INSPECTION UNDERWAY. MOD SB 8-55-14 TO BE INCORPORATED AS POSSIBLE FIX. (MORE RESEARCH NEEDS TO BE DONE ON THIS SB AS FIX.) 2 H 7 2 4T 4 T RT A13NM E20NE 1997042200054 19970422 00054 NM 1997 4 22 CA961205003 1 19961129 G 2770 NAS130431 BOLT DHAV DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE ELEVATOR RUSTED W K NONE O OTHER IN INSP/MAINT 1 CA 16218 120226 (CAN) BOLTS HOLDING RUBBER BUMPERS ON ELEVATOR GUST LOCKS ARE SEVERELY CORRODED. COULD CAUSE ELEVATOR LOCK UP IF BOLTS S EPARATED. FLEET INSPECTION SO FAR HAS FOUND 7 AIRCRAFT WITH PROBLEM. SB 8-55-14 BEING INCORPORATED AS POSSIBLE FIX. 2 H 7 2 4T 4 T RT A13NM E20NE 1997042200055 19970422 00055 NM 1997 4 22 CA961205004 1 19961129 G 2770 NAS130431 BOLTS DHAV DHAV DHC8 DHC8101 2809002 NM PWA PW120 PW123 NE ELEVATOR RUSTED W A K NONE O OTHER IN INSP/MAINT 1 CA 25321 123138 (CAN) BOLTS THAT HOLD RUBBER BUMPERS TO ELEVATOR GUST LOCK FOUND SEVERELY CORRODED. COULD CAUSE ELEVATOR LOCK UP IF BOLT SEPARATED. FLEET INSPECTION HAS FOUND 7 OF THESE SO FAR. SB 8-55-14 BEING INCORPORATED AND MAY BE FIX. 2 H 7 2 4T 4 T RT A13NM E20NE 1997042200056 19970422 00056 NM 1997 4 22 CA961205005 1 19961203 G 2770 NAS130431 BOLT DHAV DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE ELEVATOR RUSTED W A K NONE O OTHER IN INSP/MAINT 1 CA 19069 PCE120304 (CAN) BOLTS THAT HOLD ELEVATOR GUST LOCK ASSEMBLY RUBBER BUMPERS FOUND RUSTED 1/2 WAY THROUGH. FAILURE OF THIS BOLT COUL D CAUSE THE SPRING LOADED GUST LOCK PIN TO EXTEND LOCKING THE ELEVATOR. SEVEN RUSTED BOLTS FOUND SO FAR IN FLEET. 2 H 7 2 4T 4 T RT A13NM E20NE 1997042800001 19970428 00001 NM 1997 4 28 CA961205006 1 19961203 G 2770 NAS130431 BOLTS DHAV DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE ELEVATOR RUSTED W K NONE F FLT CONT AFFECTED IN INSP/MAINT 1 CA 16470 120165 (CAN) BOLTS THAT HOLD ELEVATOR GUST LOCK RUBBERS FOUND TO BE SEVERELY RUSTED. FAILURE OF THESE BOLTS COULD CAUSE THE SPR ING LOADED PIN TO EXTEND CAUSING THE ELEVATORS TO LOC UP. OPERATOR HAD FOUND THIS A FEW DAYS PREVIOUS ON ANOTHER AIRCRAF T. FLEET CAMPAIGN HAS FOUND 7 FAILURES SO FAR. 2 H 7 2 4T 4 T RT A13NM E20NE 1997042800002 19970428 00002 NM 1997 4 28 CA961205007 1 19961203 G 2770 NAS130431 BOLTS DHAV DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE ELEVATOR RUSTED W K NONE F FLT CONT AFFECTED IN INSP/MAINT 1 CA 25639 120056 (CAN) BOLTS THAT HOLD GUST LOCK RUBBER BUMPERS FOUND SEVERELY RUSTED. FAILURE OF THIS BOLT COULD CAUSE THE SPRING LOADED GUST LOCK PIN TO EXTEND LOCKING UP THE ELEVATORS. OPERATOR HAD FOUND THIS SAME PROBLEM A FEW DAYS PREVIOUS ON ANOTHER A IRCRAFT. FLEET CHECK HAS FOUND 7 CASES SO FAR. 2 H 7 2 4T 4 T RT A13NM E20NE 1997042800003 19970428 00003 NM 1997 4 28 CA961205008 1 19961203 G 2760 WIRE DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE SPOILER CLUTCH BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 120840 (CAN) TOP LEFT HAND ROLL SPOILER CLUTCH SWITCH WIRE FOUND BROKEN. 2 H 7 2 4T 4 T RT A13NM E20NE 1997042800004 19970428 00004 EA 1997 4 28 CA961205009 1 19961203 G 2760 WIRE DHAV DHC8 DHC8311 1386006 EA PWA PW120 PW123 NE NR 2 SPOILER JAM SHORTED W O OTHER F J FLT CONT AFFECTED WARNING INDICATION CR CRUISE 1 CA 123132 (CAN) PFCS SPLR 2 "PUSH OFF" ILLUMINATED IN FLIGHT. FOUND #2 SPOILER JAM MICRO SWITCH WIRES BROKEN AND SHORTING TO GROUN D. 2 H 7 2 4T 4 T RT A13NM E20NE 1997042800005 19970428 00005 NM 1997 4 28 CA961205010 1 19961203 G 7500 O-RINGS DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE #2 BLEED AIR LEAKING W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA 10508 120083 (CAN) SMOKE IN THE CABIN FROM #2 ENGINE BLEED AIR. FOUND NL O-RINGS LEAKING. 2 H 7 2 4T 4 T RT A13NM E20NE 1997042800006 19970428 00006 CE 1997 4 28 CA961205011 1 19961128 G 3232 AA5C GEAR DOOR MITSUELECT MTSBSI MU2 MU2B35 5780411 CE GARRTT TPE331 TPE3316 01514 WP CLUTCH FROZEN W L ABORTED APPROACH J O WARNING INDICATION OTHER AP APPROACH 1 CA 507 P20276C (CAN) ICE CONTAMINATION IN THE GEAR DOOR ACTUATOR CAUSED THE PILOT ABORT THE APPROACH. SUBSEQUENT CYCLING OF THE GEAR PR ODUCED A GEAR DOWN AND LOCKED CONDITION WHEREBY THE AIRCRAFT LANDED SAFELY. 1 H 7 2 3T 4 T RT A10SW E4WE 1997042800007 19970428 00007 SO 1997 4 28 CA961205012 1 19961130 G 5210 487494 SPRING PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA DOOR LATCH BROKEN W K NONE J O WARNING INDICATION OTHER AP APPROACH 1 CA 13967 L726561A (CAN) DURING APPROACH THE PILOT RECEIVED THE DOOR AJAR WARNING LIGHT. AIRCRAFT LANDED SAFELY AND MAINTENANCE FOUND A BRO KEN SPRING WHERE THE SPRING ATTACHES TO THE DOORS INTERNAL SAFETY LATCH. SPRING WAS REPLACED AND THE DOOR RIGGED AND RET URNED TO SERVICE. 1 L 7 2 3O 3 O A20SO E14EA 1997042800008 19970428 00008 WP 1997 4 28 CA961205014 1 19961129 G 3241 46AB FUSE BODY PNEUDRAULICS 61912 DOUG DC10 DC1030 3023501 WP GE CF6 CF650C2 30018 NE NR 3 HYD SYS CRACKED W H O DEACTIVATE SYST/CIRCUITS OTHER K FLUID LOSS LD LANDING 1 CA 46AB 517762 (CAN) ON LANDING AUTO BRAKE SYSTEM ACTIVATED AND #3 HYDRAULIC SYSTEM LOST FLUID IMMEDIATELY AIRCRAFT TOWED TO GATE MAI NTENANCE FOUND BODY OF HYDRAULIC FUSE CRACKED FUSE REPLACED AND #3 HYDRAULIC SYSTEM SERVICED. 2 L 7 3 4F 4 F A22WE E23EA 1997042800009 19970428 00009 SO 1997 4 28 CA961205015 1 19961106 G 2140 B3040 BURNER CAN JANITROL B3040 PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA HEATER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 1500 L186061A (CAN) WHILE CHECKING AD 82-07-02 A CRACK WAS DETECTED. SUBMITTER INSTALLED A NEW HEATER. 1 L 7 2 3O 3 O A20SO E14EA 1997042800010 19970428 00010 SO 1997 4 28 CA961205016 1 19961203 G 5312 5269400 BULKHEAD PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA LT RT WING FITTN CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 11417 L186061A (CAN) ON INSPECTION A 1.5 INCH CRACK WAS FOUND ON BOTH THE LEFT AND RIGHT SIDE WHERE THE FRONT FITTINGS ATTACH TO THE WI NG. 1 L 7 2 3O 3 O A20SO E14EA 1997042800011 19970428 00011 SO 1997 4 28 CA961205017 1 19961203 G 5751 SPAR PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA AILERON CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 11417 L186061A (CAN) WHILE CARRYING OUT AD 96-21-03 A CRACK WAS FOUND UNDER THE HINGE. SUBMITTER INSTALLED A NEW AILERON SPAR. 1 L 7 2 3O 3 O A20SO E14EA 1997042800012 19970428 00012 SO 1997 4 28 CA961205018 1 19961203 G 5751 2570400 BEARINGS PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA AILERON WORN W K NONE O OTHER IN INSP/MAINT 1 CA 11417 L186061A (CAN) WHILE WORKING ON THE AILERON SYSTEM WEAR WAS NOTED IN THE LEFT AILERON OUTBOARD BEARING. SIMILAR PLAY WAS NOTED ON THE RIGHT SIDE. COMPONENTS REPLACED. 1 L 7 2 3O 3 O A20SO E14EA 1997042800013 19970428 00013 NE 1997 4 28 CA961205020 2 19961122 G 7250 311180101 BLADE PWA 118 PW118 NE HP TURBINE FRACTURED W O OTHER O OTHER CL CLIMB 1 CA 7650 115497 (CAN) ENGINE WAS SENT FOR INVESTIGATION AND REPAIR AFTER THE ENGINE MADE A LOUD BANG AND FEATHERED SOME TIME AFTER TKAEO FF. DISASSEMBLY OF THE ENGINE REVEALED THE CAUSE OF THE INFLIGHT SHUTDOWN WAS A HP TURBINE BLADE WHICH HAD FRACTURED THR OUGH THE FIR TREE ROOT. THIS INITIAL FAILURE CAUSED HEAVY DAMAGE TO THE REMAINING HP TURBINE BLADES. 4 T E20NE 1998020500466 19980205 00466 CE 1998 2 5 CA961216001 1 19961026 G 5740 AN824A BOLT CESSNA 150 150M 2071830 CE CONT O200 O200A 17020 SO LH RH SPAR CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 3325 0 (CAN) AFTER REMOVAL OF THE LEFT AND RIGHT WINGS FOR A DETAILED INSPECTION, PITTING CORROSION WAS FOUND IN BOTH LEFT AND RIGHT FORE AND AFT SPAR WING ATTACH BOLTS. CORROSION WAS ALSO EVIDENT IN THE REAR SPAR ECCENTRIC BUSHINGS P/N 0512123 OF THE INTERNAL BORES. 1 H 7 1 3O 3 O 3A19 E252 1997042800014 19970428 00014 EA 1997 4 28 CA961216003 1 19961023 G 8120 SURPERCHARGER DHAV DHC2 DHC2MK1 2800102 EA PWA R985 R985AN14B 52008 NE IMPELLER SHAFT FAILED BUSHING W E ENGINE SHUTDOWN O OTHER TX TAXI/GRND HDL 1 CA 931 17954 (CAN) ENGINE SUPERCHARGER PRESSURE FLUCTUATING AND MAKING A HIGH PITCH SOUND. NO METAL WAS FOUND IN THE OIL SCREEN. INSP ECTION FOUND THE IMPELLER WITH EXCESSIVE MOVEMENT. ON DISASSEMBLY THE EXCESSIVE IMPELLER MOVEMENT WAS CAUSED BY THE FAIL URE OF THE SUPERCHARGER SHAFT BUSHING, BECAUSE OF AN UNAPPROVED REPAIR TO THE OIL FEED GALLERY PLUG THREADS WITH SOME TY PE OF COMPOUND WITH A FIBEROUS TEXTURE. THIS SAME COMPOUND WAS FOUND CLOGGING THE OIL PORT TO THE BUSHING. WHEN THE BUSH ING SEIZED TO THE SHAFT TWO TEETH WERE SNAPPED OFF THE FLOATING GEAR DRIVE. 1 H 7 1 3R 3 R A806 5E1 1997042800015 19970428 00015 EU 1997 4 28 CA961216004 1 19961120 G 6320 369D2551021 DRIVESHAFT HUGHES 369 369FF EU ALLSN 250C 250C30 03013 GL MGB TEETH MISSING W K NONE O OTHER IN INSP/MAINT 1 CA 3131 CAE900134 (CAN) MAIN DRIVESHAFT INSPECTED DURING 300 HOUR INSPECTION. 7 OUT OF 34 TEETH ON OUTPUT SPLINE TO MAIN TRANSMISSION FOUN D CRACKED. 1 G 7 1 3U 3 U H3WE E1GL 1997042800016 19970428 00016 EU 1997 4 28 CA961216005 1 19961122 G 2432 18826003 BATTERY MARATHON FOKKER F28 F28MK1000 4990808 EU CELLS THERMAL DAMAGE W K NONE J M WARNING INDICATION OVER TEMP TX TAXI/GRND HDL 1 CA 1962 154 (CAN) ON ARRIVAL, CREW NOTED #1 BATTERY HOT LIGHT ON. MAINTENANCE FOUND BATTERY HAD SUFFERED AN APPARENT THERMAL RUNAWAY , RESULTING IN 6 CELLS RUPTURED AND DAMAGE TO 11 OTHERS. BATTERY BOX CONTAINED DAMAGE. BATTERY HAD BEEN DEEP CYCLED 154 HOURS - 66 DAYS PREVIOUS. DISCUSSION WITH AIRLINES INDICATED THAT THE BATTERY IS A 19 CELL TYPE. THERE HAS BEEN AN ONGOI NG PROBLEM OF BATTERIES FOR THE AIRLINE - NOT WITH THERMAL RUNAWAYS BUT AT LEAST WITH ENOUGH DIFFICULTIES THAT THE AIRCR AFT MANUFACTURER WAS CONTACTED TO REPLACE TYPE OF BATTERY. THE AIRCRAFT MANUFACTURER HAS DECLINED TO MOVE TO ANOTHER TYP E BATTERY. ISSUE ONGOING AT THIS TIME FOR AIRLINE. 2 L 7 2 4F RT A20EU 1997042800017 19970428 00017 SO 1997 4 28 CA961216009 2 19961203 G 7314 6467586A2 FUEL PUMP PIPER PA34 PA34220T 7103420 SO CONT O360 TSIO360KB 17025 SO MCAULY 3AF32C 3AF32C508 GL ANEROID SCREW STRIPPED W K NONE E VIBRATION/BUFFET CL CLIMB 1 CA 930 307636 823131 (CAN) ON CLIMB OUT THE PILOT NOTICED THE FUEL FLOW GAUGE READING HIGH (IN THE RED) AND THE ENGINE STARTED TO RUN ROUGH, WITH LOSS OF POWER. THE MIXTURE WAS RETARDED AND THE FUEL FLOW DECREASED AND POWER INCREASED. AIRCRAFT RETURNED TO BASE. POST FLIGHT INSPECTION FOUND THE FUEL PUMP ANEROID ADJUSTING SCREW STRIPPED AND EXTENDED OUT 2". THIS ALLOWED THE FUEL PRESSURE TO INCREASE PAST THE DESIRED SETTING. THE FUEL PUMP WAS REPLACED. 1 L 7 2 3O 3 O A7SO E9CE 5 C P22EA 1998020500467 19980205 00467 1998 2 5 CA961216010 1 19961206 G 2430 51509350 CONTACTOR LUCAS 51509002R DC SYS WRONG PART W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 1155 (CAN) WRONG PART NUMBER LINE CONTACTOR INSTALLED, UNAUTHORIZED CONFIGURATION, UNCERTIFIED FOR FLIGHT. 1997042800018 19970428 00018 EU 1997 4 28 CA961216011 1 19961204 G 6720 3160S8700355 CONTROL TUBE AEROSP SA316 SA316B 8680207 EU TMECA ARTST3 ARTOUSTE3B 60003 EU T/R CONTROL CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA 2439 2447 (CAN) CLAMP ON PITOT STATIC TUBE CHAFED A HOLE IN TAIL ROTOR CONTROL TUBE. 1 G 7 1 4U 3 U H1IN E11N 1997042800019 19970428 00019 EA 1997 4 28 CA961216012 2 19961115 G 7261 3008127 GEARSHAFT BEECH 100 100BEECH 1152916 CE PWA PT6 PT6A28 EA OIL PUMP SHEARED W E ENGINE SHUTDOWN O OTHER CL CLIMB 1 CA 3168 50054 (CAN) ON CLIMBOUT THE #2 ENGINE TORQUE DOPPED. THE ENGINE FEATHERED AND SHUTDOWN. POST FLIGHT INSPECTION FOUND THE OIL P UMP GEARSHAFT HAD SHEARED. 1 L 7 2 3T 4 T A14CE E4EA 1997042800020 19970428 00020 EA 1997 4 28 CA961216013 2 19961203 G 8520 LW17060 CRANKSHAFT LYC O320 O320D2A 41508 EA INSIDE DIAMETER CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 899 L1661939A (CAN) DETAILED INSPECTION OF THE ENGINE CRANKSHAFT CARRIED OUT AS PER LYCOMING SB #505A REVEALED CORROSION AND DEEP PITT ING IN THE INSIDE DIAMETER (I.D.). REMOVAL OF THE CORROSION AND PITTING TO THE MAXIMUM ALLOWABLE I.D. OF 1.910" STILL IN DICATED PITTING IN THE AREA 02.00" LONG INWARD FROM THE EXPANSION PLUG. CAUSE OF THE CORROSION WAS DETERMINED AS EXCESSI VE MOISTURE CONTENT IN THE OIL SYSTEM. SOLUTION TO THE PROBLEM IS UNDER DISCUSSION BETWEEN LYCOMING AND SLINGSBY AVIATIO N. ENGINE WAS REJECTED AND WAS BEING SENT OUT FOR A NEW CRANKSHAFT. 3 O E274 1997042800021 19970428 00021 EA 1997 4 28 CA961216014 2 19961203 G 8520 LW17060 CRANKSHAFT LYC O320 O320D2A 41508 EA INSIDE DIAMETER CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 777 L1584839A (CAN) DETAILED INSPECTION OF THE ENGINE CRANKSHAFT CARRIED OUT AS PER LYCOMING SB #505A REVEALED CORROSION AND DEEP PITT ING IN THE INSIDE DIAMETER (I.D.). REMOVAL OF THE CORROSION AND PITTING TO THE MAXIMUM ALLOWABLE I.D. OF 1.910" STILL IN DICATED PITTING IN THE AREA 02.00" LONG INWARD FROM THE EXPANSION PLUG. CAUSE OF THE CORROSION WAS DETERMINED AS EXCESSI VE MOISTURE CONTENT IN THE OIL SYSTEM. SOLUTION TO THE PROBLEM IS UNDER DISCUSSION BETWEEN LYCOMING AND SLINGSBY AVIATIO N. ENGINE WAS REJECTED AND WAS BEING SENT OUT FOR A NEW CRANKSHAFT. 3 O E274 1997042800022 19970428 00022 EA 1997 4 28 CA961216015 2 19961203 G 8520 LW17060 CRANKSHAFT LYC O320 O320D2A 41508 EA INSIDE DIAMETER CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 1373 L1754739A (CAN) DETAILED INSPECTION OF THE ENGINE CRANKSHAFT CARRIED OUT AS PER LYCOMING SB #505A REVEALED CORROSION AND DEEP PITT ING IN THE INSIDE DIAMETER (I.D.). REMOVAL OF THE CORROSION AND PITTING TO THE MAXIMUM ALLOWABLE I.D. OF 1.910" STILL IN DICATED PITTING IN THE AREA 02.00" LONG INWARD FROM THE EXPANSION PLUG. CAUSE OF THE CORROSION WAS DETERMINED AS EXCESSI VE MOISTURE CONTENT IN THE OIL SYSTEM. SOLUTION TO THE PROBLEM IS UNDER DISCUSSION BETWEEN LYCOMING AND SLINGSBY AVIATIO N. ENGINE WAS REJECTED AND WAS BEING SENT OUT FOR A NEW CRANKSHAFT. 3 O E274 1997042800023 19970428 00023 EA 1997 4 28 CA961216016 2 19961203 G 8520 LW17060 CRANKSHAFT LYC O320 O320D2A 41508 EA INSIDE DIAMETER CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 1327 L1754839A (CAN) DETAILED INSPECTION OF THE ENGINE CRANKSHAFT CARRIED OUT AS PER LYCOMING SB #505A REVEALED CORROSION AND DEEP PITT ING IN THE INSIDE DIAMETER (I.D.). REMOVAL OF THE CORROSION AND PITTING TO THE MAXIMUM ALLOWABLE I.D. OF 1.910" STILL IN DICATED PITTING IN THE AREA 02.00" LONG INWARD FROM THE EXPANSION PLUG. CAUSE OF THE CORROSION WAS DETERMINED AS EXCESSI VE MOISTURE CONTENT IN THE OIL SYSTEM. SOLUTION TO THE PROBLEM IS UNDER DISCUSSION BETWEEN LYCOMING AND SLINGSBY AVIATIO N. ENGINE WAS REJECTED AND WAS BEING SENT OUT FOR A NEW CRANKSHAFT. 3 O E274 1997042800024 19970428 00024 EA 1997 4 28 CA961216017 2 19961203 G 8520 LW17060 CRANKSHAFT LYC O320 O320D2A 41508 EA INSIDE DIAMETER CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 1463 L1756039A (CAN) DETAILED INSPECTION OF THE ENGINE CRANKSHAFT CARRIED OUT AS PER LYCOMING SB #505A REVEALED CORROSION AND DEEP PITT ING IN THE INSIDE DIAMETER (I.D.). REMOVAL OF THE CORROSION AND PITTING TO THE MAXIMUM ALLOWABLE I.D. OF 1.910" STILL IN DICATED PITTING IN THE AREA 02.00" LONG INWARD FROM THE EXPANSION PLUG. CAUSE OF THE CORROSION WAS DETERMINED AS EXCESSI VE MOISTURE CONTENT IN THE OIL SYSTEM. SOLUTION TO THE PROBLEM IS UNDER DISCUSSION BETWEEN LYCOMING AND SLINGSBY AVIATIO N. ENGINE WAS REJECTED AND WAS BEING SENT OUT FOR A NEW CRANKSHAFT. 3 O E274 1997042800025 19970428 00025 EA 1997 4 28 CA961216018 2 19961203 G 8520 LW17060 CRANKSHAFT LYC O320 O320D2A 41508 EA INSIDE DIAMETER CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 1414 L1754539A (CAN) DETAILED INSPECTION OF THE ENGINE CRANKSHAFT CARRIED OUT AS PER LYCOMING SB #505A REVEALED CORROSION AND DEEP PITT ING IN THE INSIDE DIAMETER (I.D.). REMOVAL OF THE CORROSION AND PITTING TO THE MAXIMUM ALLOWABLE I.D. OF 1.910" STILL IN DICATED PITTING IN THE AREA 02.00" LONG INWARD FROM THE EXPANSION PLUG. CAUSE OF THE CORROSION WAS DETERMINED AS EXCESSI VE MOISTURE CONTENT IN THE OIL SYSTEM. SOLUTION TO THE PROBLEM IS UNDER DISCUSSION BETWEEN LYCOMING AND SLINGSBY AVIATIO N. ENGINE WAS REJECTED AND WAS BEING SENT OUT FOR A NEW CRANKSHAFT. 3 O E274 1997042800026 19970428 00026 EA 1997 4 28 CA961216019 2 19961203 G 8520 LW17060 CRANKSHAFT LYC O320 O320D2A 41508 EA INSIDE DIAMETER CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 1312 L1759239A (CAN) DETAILED INSPECTION OF THE ENGINE CRANKSHAFT CARRIED OUT AS PER LYCOMING SB #505A REVEALED CORROSION AND DEEP PITT ING IN THE INSIDE DIAMETER (I.D.). REMOVAL OF THE CORROSION AND PITTING TO THE MAXIMUM ALLOWABLE I.D. OF 1.910" STILL IN DICATED PITTING IN THE AREA 02.00" LONG INWARD FROM THE EXPANSION PLUG. CAUSE OF THE CORROSION WAS DETERMINED AS EXCESSI VE MOISTURE CONTENT IN THE OIL SYSTEM. SOLUTION TO THE PROBLEM IS UNDER DISCUSSION BETWEEN LYCOMING AND SLINGSBY AVIATIO N. ENGINE WAS REJECTED AND WAS BEING SENT OUT FOR A NEW CRANKSHAFT. 3 O E274 1997042800027 19970428 00027 EA 1997 4 28 CA961216020 2 19961203 G 8520 LW17060 CRANKSHAFT LYC O320 O320D2A 41508 EA INSIDE DIAMETER CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 1291 L1490839A (CAN) DETAILED INSPECTION OF THE ENGINE CRANKSHAFT CARRIED OUT AS PER LYCOMING SB #505A REVEALED CORROSION AND DEEP PITT ING IN THE INSIDE DIAMETER (I.D.). REMOVAL OF THE CORROSION AND PITTING TO THE MAXIMUM ALLOWABLE I.D. OF 1.910" STILL IN DICATED PITTING IN THE AREA 02.00" LONG INWARD FROM THE EXPANSION PLUG. CAUSE OF THE CORROSION WAS DETERMINED AS EXCESSI VE MOISTURE CONTENT IN THE OIL SYSTEM. SOLUTION TO THE PROBLEM IS UNDER DISCUSSION BETWEEN LYCOMING AND SLINGSBY AVIAITO N. ENGINE WAS REJECTED AND WAS BEING SENT OUT FOR A NEW CRANKSHAFT. 3 O E274 1997042800028 19970428 00028 EA 1997 4 28 CA961216021 2 19961203 G 8520 LW17060 CRANKSHAFT LYC O320 O320D2A 41508 EA INSIDE DIAMETER CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 1316 L1758239A (CAN) DETAILED INSPECTION OF THE ENGINE CRANKSHAFT CARRIED OUT AS PER LYCOMING SB #505A REVEALED CORROSION AND DEEP PITT ING IN THE INSIDE DIAMETER (I.D.). REMOVAL OF THE CORROSION AND PITTING TO THE MAXIMUM ALLOWABLE I.D. OF 1.910" STILL IN DICATED PITTING IN THE AREA 02.00" LONG INWARD FROM THE EXPANSION PLUG. CAUSE OF THE CORROSION WAS DETERMINED AS EXCESSI VE MOISTURE CONTENT IN THE OIL SYSTEM. SOLUTION TO THE PROBLEM IS UNDER DISCUSSION BETWEEN LYCOMING AND SLINGSBY AVIATIO N. ENGINE WAS REJECTED AND WAS BEING SENT OUT FOR A NEW CRANKSHAFT. 3 O E274 1997042800029 19970428 00029 EA 1997 4 28 CA961216022 2 19961203 G 8520 LW17060 CRANKSHAFT LYC O320 O320D2A 41508 EA INSIDE DIAMETER CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 1366 L1758339A (CAN) DETAILED INSPECTION OF THE ENGINE CRANKSHAFT CARRIED OUT AS PER LYCOMING SB #505A REVEALED CORROSION AND DEEP PITT ING IN THE INSIDE DIAMETER (I.D.). REMOVAL OF THE CORROSION AND PITTING TO THE MAXIMUM ALLOWABLE I.D. OF 1.910" STILL IN DICATED PITTING IN THE AREA 02.00" LONG INWARD FROM THE EXPANSION PLUG. CAUSE OF THE CORROSION WAS DETERMINED AS EXCESSI VE MOISTURE CONTENT IN THE OIL SYSTEM. SOLUTION TO THE PROBLEM IS UNDER DISCUSSION BETWEEN LYCOMING AND SLINGSBY AVIATIO N. ENGINE WAS REJECTED AND WAS BEING SENT OUT FOR A NEW CRANKSHAFT. 3 O E274 1997042800030 19970428 00030 EA 1997 4 28 CA961216023 2 19961203 G 8520 LW17060 CRANKSHAFT LYC O320 O320D2A 41508 EA INSIDE DIAMETER CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 1319 L1758439A3 (CAN) DETAILED INSPECTION OF THE ENGINE CRANKSHAFT CARRIED OUT AS PER LYCOMING SB #505A REVEALED CORROSION AND DEEP PITT ING IN THE INSIDE DIAMETER (I.D.). REMOVAL OF THE CORROSION AND PITTING TO THE MAXIMUM ALLOWABLE I.D. OF 1.910" STILL IN DICATED PITTING IN THE AREA 02.00" LONG INWARD FROM THE EXPANSION PLUG. CAUSE OF THE CORROSION WAS DETERMINED AS EXCESSI VE MOISTURE CONTENT IN THE OIL SYSTEM. SOLUTION TO THE PROBLEM IS UNDER DISCUSSION BETWEEN LYCOMING AND SLINGSBY AVIATIO N. ENGINE WAS REJECTED AND WAS BEING SENT OUT FOR A NEW CRANKSHAFT. 3 O E274 1997042800031 19970428 00031 EA 1997 4 28 CA961216024 2 19961203 G 8520 LW17060 CRANKSHAFT LYC O320 O320D2A 41508 EA INSIDE DIAMETER CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 1275 L1758539A (CAN) DETAILED INSPECTION OF THE ENGINE CRANKSHAFT CARRIED OUT AS PER LYCOMING SB #505A REVEALED CORROSION AND DEEP PITT ING IN THE INSIDE DIAMETER (I.D.). REMOVAL OF THE CORROSION AND PITTING TO THE MAXIMUM ALLOWABLE I.D. OF 1.910" STILL IN DICATED PITTING IN THE AREA 02.00" LONG INWARD FROM THE EXPANSION PLUG. CAUSE OF THE CORROSION WAS DETERMINED AS EXCESSI VE MOISTURE CONTENT IN THE OIL SYSTEM. SOLUTION TO THE PROBLEM IS UNDER DISCUSSION BETWEEN LYCOMING AND SLINGSBY AVIATIO N. ENGINE WAS REJECTED AND WAS BEING SENT OUT FOR A NEW CRANKSHAFT. 3 O E274 1997042800032 19970428 00032 SW 1997 4 28 CA961216025 1 19960928 G 3230 27810321046 TUBE SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE33111U 01514 WP LH GEAR DOWN LEAKING PINHOLE W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 7425 44727 (CAN) DURING DI HYDRAULIC FLUID WAS NOTED SEEPING FROM THE LOWER OUTBOARD AREA OF THE CENTRE SECTION. THE LEFT HAND GEAR DOWN LINE WAS FOUND LEAKING FROM A SMALL PIN HOLE WHEN HYDRAULIC SYSTEM PSI WAS UP TO NORMAL OPERATING PRESSURE. TO FIN D PIN HOLE THE PROTECTIVE PLASTIC HAD TO BE CUT AWAY FROM THE LINE. 2 L 7 2 4T 4 T RT A8SW E4WE 1997042800033 19970428 00033 NM 1997 4 28 CA961216029 1 19961119 G 5610 85C0043011 WINDSHIELD PPG DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE LH OUTER PANE SHATTTERED W A UNSCHED LANDING D INFLIGHT SEPARATION CL CLIMB 1 CA 6700 91103H9110 120360 (CAN) DURING CLIMBOUT A BIRD STRUCK THE CAPTAINS WINDSCREEN. OUTER NON STRUCTURAL PLY SHATTERED. 2 H 7 2 4T 4 T RT A13NM E20NE 1997042800034 19970428 00034 NM 1997 4 28 CA961216030 1 19961202 G 3310 7002537 CONTROL BOX GRIMES 7002537 DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE ADVISORY SYSTEM BURNING SMELL W O OTHER B SMOKE/FUMES/ODORS/SPARKS DE DESCENT 1 CA 3447 0417 120384 (CAN) ON DESCENT AN ELECTRICAL BURNING SMELL WAS NOTICED AND ADVISORY LIGHTS WERE FLICKERING. FLICKERING AND SMELL STOPP ED WHEN ADVISORY LIGHTS SELECTED TO BRIGHT. ADVISORY LIGHT CONTROL BOX REPLACED. 2 H 7 2 4T 4 T RT A13NM E20NE 1997042800035 19970428 00035 NE 1997 4 28 CA961216031 3 19961129 G 6114 97722 BARREL SUPPORT CNDAIR CL215 CL2151A10 EA HAMSTD 43E 43E60 NE PROP CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 1583 N195039 (CAN) PROPELLER WAS IN SHOP FOR AD 81-13-06R2 INSPECTION. BARREL SUPPORT WAS FOUND CRACKED. BARREL SUPPORT WAS REPLACED. PROP BLADES HAD LEADING EDGE SPRAY CUTS FILLED. PROPELLER BARREL BOLTS WERE FOUND CORRODED. THE BOLTS WERE REPLACED. PR OPELLER WAS ALODINED AND BALANCED. 2 H 7 2 4R A14EA 6 C P871 1997042800036 19970428 00036 NE 1997 4 28 CA961216032 3 19961129 G 6114 92368 BOLTS HAMSTD 43E 43E60 NE PROP BARREL CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 1257 N190031 (CAN) PROPELLER WAS IN SHOP FOR COMPLIANCE WITH AD 81-13-06R2 INSPECTION. THE SHANKS OF THE BARREL BOLTS WERE FOUND CORR ODED. THE BOLTS WERE REPLACED. THE LEADING EDGES OF THE BLADES WERE FOUND WITH SPRAY CUTS. THE CUTS WERE FILLED AND THE BLADES ALODINED AND BALANCED. 6 C P871 1997042800037 19970428 00037 EU 1997 4 28 CA961216033 1 19961123 G 3222 23067005 SHOCK ABSORBER MESSIER 23175005 AIRBUS 320 A320212 EU NLG UPPER CYL MISALIGNED W O OTHER J WARNING INDICATION LD LANDING 1 CA (CAN) DURING LANDING FOLLOWING AN AIR TURNBACK DUE TO LANDING GEAR WARNING MESSAGES, BOTH NOSE WHEELS DEFLATED. INVESTIG ATION REVEALED THAT NOSE WHEELS WERE ROTATED 90 DEGREES TO AIRCRAFT CENTRE LINE. FURTHER INVESTIGATION DETERMINED THE CA USE TO BE A MISALIGNED SHOCK ABSORBER CENTERING CAM DURING REASSEMBLY OF THE SHOCK ASBORBER AFTER SEAL REPLACEMENT. AS A RESULT OF THE MISALIGNMENT THE SHOCK ABSORBER WAS INCORRECTLY INDEXED IN THE LANDING GEAR LEG ALLOWING THE NOSE WHEELS TO CASTER UP TO 90 DEGREES IN ONE DIRECTION. 2 L 7 2 4F RT A28NM 1997042800038 19970428 00038 SW 1997 4 28 CA961216034 1 19961203 G 7603 C817225 POWER CABLE SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE33111U 01514 WP ROTOL R321 R321482F8 GL FIREWALL ATTACH SEVERED W K NONE R PARTIAL RPM/PWR LOSS TX TAXI/GRND HDL 1 CA P44542C DRG189188 (CAN) AS THE POWER LEVERS WERE ADVANCED FOR TAXI, THE RIGHT HAND ENGINE DID NOT RESPOND. INVESTIGATION REVEALED THAT THE CABLE ASSEMBLY ATTACHED TO THE PROP PITCH CONTROL HAD DETACHED DUE TO INTERNAL FAILURE AT THE ENGINE FIREWALL. 2 L 7 2 4T 4 T RT A8SW E4WE 6 C P61GL 1997042800039 19970428 00039 EA 1997 4 28 CA961216036 2 19961202 G 7200 ENGINE BEECH 1900 1900C 1154161 CE PWA PT6 PT6A65B 52043 EA #2 ENGINE SEIZED W K NONE O OTHER IN INSP/MAINT 1 CA 90 PCE32567 (CAN) DURING GROUND INSPECTION MAINTENANCE PERSONNEL WERE UNABLE TO TURN THE RIGHT HAND PROPELLER. THE ENGINE WAS REMOVE D FOR INVESTIGATION. 2 L 7 2 4T 4 T RT A24CE E4EA 1997042800040 19970428 00040 EA 1997 4 28 CA961216037 2 19961109 G 8530 LW13447 CYLINDER PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2B 41532 EA ENGINE WRONG RINGS W A UNSCHED LANDING M W OVER TEMP INADEQUATE Q C CL CLIMB 1 CA L447661 (CAN) AFTER TAKEOFF THE CYLINDER AND OIL TEMPERATURES BECAME HIGH AND THE OIL PRESSURE WAS DROPPING, THE PILOT RETURNED TO BASE. TWO CYLINDERS HAD RECENTLY BEEN REPLACED AND INVESTIGATION HAD FOUND THAT THE WRONG PISTON RINGS HAD BEEN INSTA LLED. THE ENGINE WAS REPLACED. 1 L 7 2 3O 3 O A20SO E14EA 1997042800041 19970428 00041 NM 1997 4 28 CA961216038 1 19961130 G 5330 SKIN DHAV DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE ATC XPONDER ANT CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 26000 120367 (CAN) DURING INSPECTION OF THE BOND ANTENNA FOR THE ATC TANSPONDER IT WAS NOTED THAT THE FUSELAGE SKIN WAS CORRODED. THE ANTENNA WAS REMOVED FOR FURTHER INVESTIGATION WHICH DISCLOSED SEVERE CORROSION AND DELAMINATION OF THE SKIN APPROXIMATE LY 4 TO 5 INCHES ON EITHER SIDE OF THE ANTENNA CUT-OUT. THE ANTENNA IS LOCATED ON THE UNDERSIDE OF THE FUSELAGE AT STATI ON 258.5. REPAIRED AS PER RD 8-53-2477. 2 H 7 2 4T 4 T RT A13NM E20NE 1997042800042 19970428 00042 GL 1997 4 28 CA961216039 3 19961204 G 6110 57B1938 VALVE STEM PIPER PA23 PA23250 7102308 SO LYC O540 TIO540C1A 41532 EA HARTZL HCE2Y HCE2YR2 GL PROP ACCUMULATOR DISLODGED W A UNSCHED LANDING K FLUID LOSS CL CLIMB 1 CA 647 L364061A BP3469 (CAN) PILOT REPORTED PROP RPM FLUCTUATIONS ON PREVIOUS FLIGHT. ON NEXT FLIGHT REPORTED NO PROP CONTROL WITH PROP LEVER. PILOT ABORTED FLIGHT. INSPECTION FOUND BOTH VALVE STEM AND DUST COVER LYING INSIDE THE PROP SPINNER DOME COVER, PROPELLE R ACCUMULATOR PRESSURE AND LEAK CHECK CARRIED OUT AT 100 HOUR INSPECTION 40.8 HOURS PRIOR TO THIS OCCURRENCE. NO FAULT W AS FOUND AT THAT TIME. 1 L 7 2 3O 3 O 1A10 E14EA 5 C P9EA 1997042800043 19970428 00043 NE 1997 4 28 CA961216040 2 19961202 G 7250 310510301R2W TURBINE BLADE PWA 118 PW118A NE 1ST STAGE FRACTURED W K NONE O OTHER IN INSP/MAINT 1 CA 14652 3182 115421 (CAN) THE ENGINE WAS SHIPPED FOR INVESTIGATION AND REPAIR AFTER THE OPERATOR FOUND THERE WAS A FRACTURE OF A PT1 TURBINE BLADE. DISASSEMBLY FOUND THE FRACTURED PT BLADE TO BE A WALBAR RECOATED BLADE (P/N 3105103-01-R2W) AND THE FAILURE OCCU RRED APPROXIMATELY 0.25" ABOVE THE PLATFORM. THIS BLADE IS NOT A CURRENTLY ACCEPTABLE BLADE PER THE PWC MANUALS AND ITS INSTALLATION IN THE PT ASSEMBLY AT THE TIME OF THE LAST SHOP VISIT SHOULD NOT HAVE OCCURRED. SUBSTANTIAL EVIDENCE EXISTS THAT RECOATED BLADES ARE FAILURE PRONE, ALTHOUGH IT IS NOT CLEAR WHETHER THE RECOATING PROCESS OR SIMPLY HIGH TIME IS T HE PRIMARY CAUSE OF THE FAILURE. 4 T E20NE 1997042800044 19970428 00044 EU 1997 4 28 CA961217001 1 19961205 G 3230 LANDING GEAR BAG BAE146 BAE146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE UPLOCK ICED UP W A UNSCHED LANDING J WARNING INDICATION TO TAKEOFF 1 CA LF05567A (CAN) LEFT HAND MAIN LANDING GEAR UNSAFE LIGHT REMAINED ON WITH GEAR SELECTED UP. AIRCRAFT RETURNED TO AIRPORT. ICE CLEA NED FROM GEAR UPLCOK AND UPLOCK LUBRICATED. 2 H 7 4 4F 4 F RT A49EU E6NE 1997042800045 19970428 00045 EU 1997 4 28 CA961217002 1 19961212 G 2750 676101258 RESOLVER BRAERO BAG BAE146 BAE146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE WING FLAPS FAILED W K NONE F FLT CONT AFFECTED TX TAXI/GRND HDL 1 CA LF05464A (CAN) WING FLAPS STUCK AT 0 DEGREES. FOUND GREEN MAIN RESOLVER OPEN. RESOLVER REPLACED AND RE-RIGGED. 2 H 7 4 4F 4 F RT A49EU E6NE 1997042800046 19970428 00046 EA 1997 4 28 CA961218002 2 19961008 G 8500 ENGINE DOUG DC3 R4D8 3021474 WP WRIGHT R1820 R182080 67020 EA FAILED W A UNSCHED LANDING Y ENGINE STOPPAGE CL CLIMB 1 CA 820 W507415 (CAN) ENGINE FAILED IN FLIGHT. AIRCRAFT RETURNED TO BASE. ENGINE REMOVED AND SENT FOR REPAIR. FURTHER REPORT TO FOLLOW. 2 L 7 2 4R 4 R 6A2 E259 1997042800047 19970428 00047 CE 1997 4 28 CA961218003 1 19961210 G 3710 442CW12 PUMP RAPCO BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO VAC SYS FAILURE W K NONE J WARNING INDICATION CR CRUISE 1 CA 8 1257547CA (CAN) OVERHAULED VACUUM PUMP INSTALLED AFTER VACUUM PUMP FAILURE. EIGHT HOURS LATER THE VACUUM PUMP SEIZED AND FAILED FO R NO APPARENT REASON. THIS IS THE SECOND "RAPCO" PUMP TO FAIL EARLY. 1 L 7 2 3O 3 O 3A16 E5CE 1997042800048 19970428 00048 CE 1997 4 28 CA961218004 1 19961206 G 2435 23048018 GENERATOR BEECH 90 E90 1152914 CE PWA PT6 PT6A28 EA HARTZL HCB3T HCB3TN3 GL #2 ENGINE FAILED W H DEACTIVATE SYST/CIRCUITS B J SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION DE DESCENT 1 CA 222 P50842 BU6310 (CAN) #2 ENGINE STARTER GENERATOR FAILED IN FLIGHT. THERE WAS A SLIGHT SMELL OF SMOKE IN THE COCKPIT PRIOR TO FAILURE. A FTER THE FAILURE THERE WAS A BRIEF FLICKER OF #2 ENGINE FIRE DETECTION LIGHT. THE RIGHT HAND GENERATOR LIGHT ALSO ILLUMI NATED. DUE TO THE INCREASE IN THE SMELL OF SMOKE THE GENERATOR AND THE RH BLEED AIR WAS TURNED OFF AND THE FLIGHT WAS CO MPLETED WITHOUT FURTHER PROBLEM. 1 L 7 2 3T 4 T 3A20 E4EA 6 C P15EA 1998043000042 19980430 00042 CE 1998 4 30 CA961218006 1 19961206 G 5711 SPAR BEECH 99 99 1154002 CE PWA PT6 PT6A20 52043 EA RIGHT WING FAILED W E O ENGINE SHUTDOWN OTHER F O FLT CONT AFFECTED OTHER LD LANDING 1 CA 30219 (CAN) ON LANDING, THERE WAS A MAJOR FAILURE OF THE RIGHT WING STRUCTURE BETWEEN THE NACELLE AND THE FUSELAGE. TSB INVES TIGATING. PART TC: 22,672. 1 L 7 2 3T 3 T A14CE E4EA 1997042800049 19970428 00049 EA 1997 4 28 CA961218008 2 19961206 G 7200 ENGINE BEECH 100 A100 1152915 CE PWA PT6 PT6A34 52043 EA #1 POSITION FAILED W B E A EMER. DESCENT ENGINE SHUTDOWN UNSCHED LANDING A FLAME/FIRE CR CRUISE 1 CA 11440 7870 PCE56069 (CAN) DURING FLIGHT LOUD BANGS WERE HEARD FROM THE #1 ENGINE WITH FLAMES COMING FROM THE EXHAUST STACKS. AN ENGINE FIRE DRILL WAS CARRIED OUT AND THE ENGINE SHUTDOWN. THE AIRCRAFT RETURNED TO BASE WITHOUT INCIDENT. THE ENGINE WAS REMOVED FO R INVESTIGATION. REPORT TO FOLLOW. 1 L 7 2 3T 4 T A14CE E4EA 1997042800050 19970428 00050 NM 1997 4 28 CA961218011 1 19961119 G 3251 89891 LINK DOWTY 8900111 DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE STEERING BROKEN W D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 CA 120358 (CAN) DURING TAXI THE TECHNICIAN LOST STEERING CONTROL. INVESTIGATION FOUND THAT THE LINK WAS BROKEN AT THE RETAINER GRO OVE AND THE AREA WAS CORRODED. 2 H 7 2 4T 4 T RT A13NM E20NE 1997042800051 19970428 00051 EA 1997 4 28 CA961218016 1 19961211 G 3010 6243843 SENSOR CNDAIR CNDAIR CL600 CL6002B19 EA WING RH INB LE CRACKED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) RIGHT HAND INBOARD LEADING EDGE TEMP SENSOR FOUND CRACKED. THE SENSOR HAD NOT BEEN INSTALLED AS PER THE MAINTENANC E TASK. THE BRACKET SHIELD HAD NOT BEEN INSTALLED OVER THE SENSOR AS SPECIFIED IN THE AMM. THEREFORE THE SENSOR WAS DAMA GED BY TORQUING THE MOUNTING SCREW. 2 L 7 2 4F RT A21EA 1997042800052 19970428 00052 SO 1997 4 28 CA961218017 1 19961212 G 8120 LW12127 TRANSITION ASSY PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA TURBOCHARGER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 7420 L339761A (CAN) TURBOCHARGER TRANSITION ASSEMBLY FOUND CRACKED ON INSPECTION. 1 L 7 2 3O 3 O A20SO E14EA 1997042800053 19970428 00053 WP 1997 4 28 CA961220001 1 19961209 G 5710 WING FITTING DOUG DC6 DC6B 3021712 WP HAMSTD 43E 43E60 NE TANK AREA WS 421 CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 201611 (CAN) DURING MAINTENANCE INSPECTION CORROSION WAS DISCOVERED IN THE #1 AND #4 ALTERNATE FUEL TANK AREAS JUST INBOARD OF WS 421 ON THE BATH TUB FITTINGS. CORRODED AREAS WILL BE CLEANED, REPAIRED AND TREATED. THE DEFINED AREAS WILL BE MONITOR ED FOR CORROSION AND INSPECTED ANNUALLY DURING THE WINTER MAINTENANCE PROGRAM. 2 L 7 4 4R 6A4 6 C P871 1997042800054 19970428 00054 WP 1997 4 28 CA961220002 1 19961206 G 5742 33209801 FITTING DOUG DC6 DC6B 3021712 WP HAMSTD 43E 43E60 NE NACELLE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 201611 (CAN) THE FITTING IDENTIFIED IS MOUNTED AND COVERED PREVENTING IT FROM BEING CLEANED AND INSPECTED OR TREATED FOR CORROS ION. THE FITTING WAS FOUND TO BE CRACKED DURING WINTER MAINTENANCE INSPECTION. ALL AIRCRAFT WILL BE NDT CHECKED USING UL TRASONIC AND EDDY CURRENT TECHNIQUES. AFTER ALL AIRCRAFT INSPECTED LONG TERM MAINTENANCE PROGRAM WILL BE INITIATED. 2 L 7 4 4R 6A4 6 C P871 1997042800055 19970428 00055 EU 1997 4 28 CA961220004 1 19961205 G 2121 FAN AIRBUS 320 A320211 3930320 EU ACM FAN BROKEN BLADE W B EMER. DESCENT J WARNING INDICATION CR CRUISE 1 CA (CAN) SMOKE DETECTED IN CABIN, EMERGENCY DECLARED, AIR PACK REGULATOR FAULT ON UPPER ECAM. ON ARRIVAL WHITE SMOKE NOTED ON OPENING PACK DOOR. MAINTENANCE ACTION INVOLVED CHANGING #2 BYPASS VALVE. ACM FOUND SEIZED AND TURBINE THREW BLADE. FU RTHER INVESTIGATION REVEALED BLADE BROKE FROM FAN AND NOT TURBINE. AFTER ACM AND TURBINE BYPASS VALVE REPLACED, ENGINES RAN AND PACKS OPERATED CHECKS SERVICEABLE. 2 L 7 2 4F RT A28NM 1997042800056 19970428 00056 WP 1997 4 28 CA961220009 1 19961125 G 3610 14J63600 DUCT CLAMP DOUG DC10 DC1030 3023501 WP GE CF6 CF650C2 30018 NE #2 ENGINE BROKEN W C D ABORTED TAKEOFF RETURN TO BLOCK G J MULTIPLE FAILURE WARNING INDICATION TO TAKEOFF 1 CA 517392 (CAN) ON TAKEOFF ROLL PRESSURE REGULATOR DUCT #2 ENGINE FAILED CAUSING EXCESSIVE DAMAGE TO PNEUMATIC DUCTING, SENSING LI NES, OIL SCAVANGE AND OIL DUMP LINES. ALSO THERE WAS DAMAGE TO SUROUNDING STRUCTURE. NACELLE TEMPERATURE ROSE TO 240 DEG REES C AND FOLLOWED THROTTLE. MANIFOLD LIGHT CAME ON. ALL DAMAGED PARTS REMOVED AND REPLACED. 2 L 7 3 4F 4 F A22WE E23EA 1997042800057 19970428 00057 1997 4 28 CA961220010 4 19961220 G 3416 152734 SUPPORT RING AEROMECH 804710DH DHAV DHC8 DHC8* NM ALTIMETER MODIFIED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 8455 (CAN) SUPPORT RING FOUND ILLEGALLY MODIFIED AS OUTLINED IN SERVICE DIFFICULTY ADVISORY AV-93-07R1. 2 H 7 2 4T RT A13NM 1997042800058 19970428 00058 SW 1997 4 28 CA961220011 1 19961129 G 2730 2744026011 TORQUE TUBE SWRNGN SA226 SA226TC 8780404 SW GARRTT TPE331 TPE33110UA 01514 WP ELEVATOR CRACKED W A K NONE O OTHER IN INSP/MAINT 1 CA 27546 P54183 (CAN) AS PART OF 8000 BLOCK INSPECTION THE ELEVATORS ARE REMOVED FOR INSPECTION. THE ELEVATOR TORQUE TUBES ARE NOT SPECI FICALLY IDENTIFIED AS REQUIRING SPECIAL ATTENTION. HOWEVER, INSPECTION FOUND THAT THE LEFT ELEVATOR TORQUE TUBE ASSEMBLY WAS CRACKED AT THE 'FORK END'. THE RIGHT HAND TUBE WAS FOUND TO HAVE A BADLY WORN INBOARD HINGE FITTING. SB 226-27-050, TO INSPECT TUBE FOR INTERNAL CORROSION WAS ACCOMPLISHED SEVERAL YEARS EARLIER, AND FAA AD 96-21-05 WAS RECENTLY COMPLIE D WITH. DETECTION OF CRACKS WAS NOT A REQUIREMENT. RIGHT ELEVATOR WAS REPLACED USING AN UPDATED TORQUE TUBE ASSEMBLY P/N 27-44016-007 AND LEFT TUBE WAS REPAIRED USING SAME NEW P/N. 2 L 7 2 4T 4 T RT A8SW E4WE 1997042800059 19970428 00059 GL 1997 4 28 CA961220012 3 19961207 G 6111 PROPELLER MCAULY 1C160 1C160CTM GL BLADE LE EDGES OUT OF SPECS W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) PROPELLER SENT FOR CORROSION INSPECTION, BLADE ANGLES WERE FOUND OUT OF SPECIFICATIONS. LEADING EDGES TRIMMED TO R EMOVE EROSION DAMAGE. 5 N P910 1997042800060 19970428 00060 NM 1997 4 28 CA961220013 1 19961212 G 2710 8270052001 CONTROL CABLE DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE AILERON FRAYED W K NONE O OTHER IN INSP/MAINT 1 CA 18605 120817 (CAN) LEFT HAND LOWER INBOARD AILERON CABLE FOUND CHAFING ON CLAMP P/N DSC70-40. CLAMP WAS INSTALLED IMPROPERLY SECURING SHROUD P/N DSC213-15, ON TO REFUEL/TRANSFER LINE AT LEFT HAND AFT SPAR STN YW196. 2 H 7 2 4T 4 T RT A13NM E20NE 1997042800061 19970428 00061 EA 1997 4 28 CA961220014 1 19961012 G 2721 C6CFM11771 QUADRANT GEAR DHAV DHAV DHC6 DHC6300 EA RUD SERVO TAB CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 19285 (CAN) DURING INVESTIGATION FOR MINOR RUDDER SERVO TAB FREEPLAY, THE GEARED TAB MECHANISM WAS REMOVED AND DISASSEMBLED FO R WEAR INSPECTION. LEVER P/N C6CFM1409-27 WAS FOUND LOOSELY ATTACHED TO QUAD GEAR. QUAD GEAR HAD TWO CRACKS IN THE KEY R OOT OF THE BOSS AREA. CRACKS WERE NOT VISIBLE UNTIL GEAR REMOVED FROM GEARED MECHANISM DUE TO FELT RING INSTALLATION. ON E CRACK FOUND ON ANOTHER AIRCRAFT. FLEET WIDE CHECK TO BE CARRIED OUT. 1 H 7 2 3T A9EA 1997042800062 19970428 00062 NE 1997 4 28 CA961220015 2 19961211 G 7250 310920201 BLADES PWA 118 PW118 NE LP TURBINE MULTIPLE FAILURE W O OTHER O OTHER TX TAXI/GRND HDL 1 CA 19943 16548 115036 (CAN) THE OPERATOR REPORTED DURING A START ATTEMPT THE PROP DID NOT ROTATE. THE OPERATOR REMOVED THE POWER TURBINE AND F OUND EVIDENCE OF DAMAGE. THE ENGINE WAS SENT FOR INVESTIGATION AND REPAIR. ENGINE DISASSEMBLY FOUND MULTIPLE FAILURES OF THE LP TURBINE BLADES. THE CAUSE OF THE BLADE FAILURES WAS CLEARLY RELATED TO CORROSION ATTACK OF THE CORED PASSAGE THR OUGH THE BLADES. 4 T E20NE 1997042800063 19970428 00063 NE 1997 4 28 CA961220016 2 19961209 G 7250 311362301 BEARING PWA 120 PW120A NE HP ROTOR NR 5 FRACTURED W O OTHER O OTHER TX TAXI/GRND HDL 1 CA 21503 7070 120086 (CAN) THE OPERATOR NOTICED A GRINDING NOISE ON SHUTDOWN AND METAL FILINGS WERE FOUND IN THE MAIN OIL PRESSURE FILTER AND ON THE CHIP DETECTOR. THE ENGINE WAS SENT FOR INVESTIGATION. THE CAUSE OF THE GRINDING NOISE AND METAL IN THE FILTERS WAS FOUND TO BE THE FAILURE OF THE NR 5 BEARING CAGE. 4 T E20NE 1997042800064 19970428 00064 SO 1997 4 28 CA961223001 1 19961216 G 3412 W200043418 WIRE EMB 120 EMB120RT 3260202 SO CB 0304 BURNED W K NONE O OTHER IN INSP/MAINT 1 CA 18571 (CAN) DURING INSPECTION SEVERAL WIRES AND AN INSULATION BLANKET WERE FOUND BURNED. THE WIRES HAD BURNED UP TO 6 INCHES O F WIRE AND HAD ALSO BURNED SEVERAL TYWRAPS INSIDE COCKPIT OVERHEAD CIRCUIT BREAKER PANEL. WIRE WHICH APPEARS TO HAVE CAU SED DAMAGE WAS CONNECTED FROM TAT PROBE INDICATOR CIRCUIT BREAKER (CB0304) TO WINDSHIELD WIPER LEFT CIRCUIT BREAKER (CB0 385). 2 L 7 2 4T RT A31SO 1997042800065 19970428 00065 NM 1997 4 28 CA961223002 1 19961205 G 2421 31708001A GENERATOR DHAV DHC8 DHC8301 NM PWA PW120 PW123 NE NR 2 AC FAILED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 11514 123075 (CAN) THE #2 AC GENERATOR FAILED ON DEPARTURE. AIRCRAFT RETURNED TO AIRPORT. RGB CHIP DETECTOR FAILED. 2 H 7 2 4T 4 T RT A13NM E20NE 1997042800066 19970428 00066 EA 1997 4 28 CA961223003 1 19961206 G 3230 83220001001 NOSE GEAR DHAV DHAV DHC8 DHC8311 1386006 EA PWA PW120 PW123 NE EXT MECH FAILED W O OTHER J WARNING INDICATION AP APPROACH 1 CA 723 123192 (CAN) ON APPROACH NOSE GEAR DID NOT EXTEND. SUCCESSFUL ALTERNATE GEAR EXTENSION CARRIED OUT. GEAR INSPECTED, CLEANED, IN CLUDING DRAG STRUT ASSEMBLY, DRAG STRUT ACTUATOR AND BEARING, GEAR DOOR MECHANISM, AND THE MECHANICAL SEQUENCE VALVE RIG GING CHECKED. NOTHING FOUND. 2 H 7 2 4T 4 T RT A13NM E20NE 1997042800067 19970428 00067 SO 1997 4 28 CA961223004 2 19961203 G 8530 642343CN CYLINDER CESSNA 421 421C 2076016 CE CONT O520 GTSIO520L 17032 SO #1 CYLINDER SEPARATED W A UNSCHED LANDING B E K SMOKE/FUMES/ODORS/SPARKS VIBRATION/BUFFET FLUID LOSS CL CLIMB 1 CA 415 239802R (CAN) DURING CLIMBOUT THE #1 ENGINE HAD A LOSS OF POWER FOLLOWED BY ROUGH RUNNING. ON RETURN TO THE AIRPORT OIL WAS NOTI CED ESCAPING THROUGH THE #1 ENGINE COWLING. POST FLIGHT INSPECTION FOUND THE #1 CYLINDER HEAD LYING IN THE COWLING. THE CYLINDER WAS REMOVED; THE OIL DRAINED; THE ENGINE AND FILTERS WERE CHECKED FOR DAMAGE. A NEW #1 CYLINDER WAS INSTALLED A ND THE AIRCRAFT RETURNED TO SERVICE. 1 L 7 2 3O 3 O A7CE E7CE 1997042800068 19970428 00068 NE 1997 4 28 CA961223006 2 19961216 G 7200 ENGINE BEECH 200 B200C 1152924 CE PWA PT6 PT6A42 52043 NE #2 POSITION MAKING METAL W A E UNSCHED LANDING ENGINE SHUTDOWN E J VIBRATION/BUFFET WARNING INDICATION CR CRUISE 1 CA 13564 6164 PCE93186 (CAN) DURING FLIGHT #2 ENGINE CHIP DETECTOR ILLUMINATED. ENGINE WAS SHUTDOWN AND AIRCRAFT LANDED WITHOUT INCIDENT. ENGIN E WAS REMOVED FOR INVESTIGATION. REPORT TO FOLLOW. 1 L 7 2 4T 4 T A24CE E4EA 1997042800069 19970428 00069 NE 1997 4 28 CA961223008 2 19961213 G 8500 ENGINE DOUG DC3 DC3CS1C3G 3021458 WP PWA R1830 R183092 52020 NE #1 POSITION FAILED W E A ENGINE SHUTDOWN UNSCHED LANDING E VIBRATION/BUFFET CR CRUISE 1 CA 66 457481 (CAN) WHILE IN CRUISE THE #1 ENGINE DEVELOPED A POWER LOSS AND BEGAN TO RUN ROUGH. THE ENGINE WAS SHUTDOWN AND THE AIRCR AFT LANDED WITHOUT INCIDENT. UPON FURTHER INVESTIGATION THE STATUS WILL BE UPDATED. 2 L 7 2 4R 4 R A669 5E4 1997042800070 19970428 00070 EU 1997 4 28 CA961230003 1 19961210 G 2612 8934100450A CONTROL UNIT FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU NR 2 FIRE DET FAULTY W E ENGINE SHUTDOWN N FALSE WARNING CR CRUISE 1 CA 17049 9052 (CAN) #2 ENGINE HAD A FIRE WARNING INDICATION IN FLIGHT. #2 ENGINE WAS SHUTDOWN AND FIRE WARNING WENT OUT, SO FIRE BOTTL ES WERE NOT ACTIVATED. AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE COULD NOT DUPLICATE FAULT ON THE GROUND. AL L SYSTEMS CHECKED NORMAL. PRECAUTIONARY REPLACEMENT OF THE FIRE DETECTOR CONTROL UNIT WAS CARRIED OUT FOR TROUBLESHOOTIN G OF THE INTEGRAL K2 RELAY. 2 L 7 2 4F 4 F RT A20EU E2EU 1997032700112 19970327 00112 NM 1997 3 27 CA961230006 1 19961216 G 3230 LANDING GEAR DHAV DHC8 DHC8102 2809003 NM NOSE & RT MAIN FAILED W O OTHER G O MULTIPLE FAILURE OTHER AP APPROACH 1 CA (CAN) AIRCRAFT LANDED WITH RIGHT MAIN LANDING GEAR AND NOSE LANDING GEAR IN THE RETRACT POSITION. LEFT MAIN WAS DOWN AND LOCKED. 2 H 7 2 4T RT A13NM 1997042800071 19970428 00071 EA 1997 4 28 CA961230008 1 19961211 G 3010 6243843 SENSOR CNDAIR CL600 CL6002B19 EA LT WING INB LE DAMAGED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) LEFT HAND, INBOARD LEADING EDGE WING TEMP SENSOR, NOT INSTALLED AS PER MAINTENANCE TASK. THE BRACKET HAD NOT BEEN INSTALLED OVER THE SENSOR AS SPECIFIED IN THE AMM. THEREFORE, THE SENSOR WAS DAMAGED WHEN THE MOUNTING SCREWS WERE TORQU ED DOWN. 2 L 7 2 4F RT A21EA 1997042800072 19970428 00072 SW 1997 4 28 CA961230009 1 19961202 G 5210 2724147003 HINGE SWRNGN SWRNGN SA226 SA226T 8780122 SW PAX DOOR AFT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CABIN DOOR FOUND WITH EXCESSIVE LATERAL MOVEMENT WHEN MOVED OPEN OR CLOSED. IT WAS ALSO NOTED THAT DOOR GUIDES WOU LD CONTACT THE FUSELAGE FRAME WHEN CLOSING. INSPECTION FOUND THAT THE DOOR HINGE HAD A 2 1/2" CRACK WHICH HAD TRAVELLED ACROSS 3 OF THE ATTACHMENT HOLES AND TERMINATED AT THE FOURTH. 2 L 7 2 4T RT A5SW 1997042800073 19970428 00073 SW 1997 4 28 CA961230010 1 19961217 G 2910 MS21926W16 ELBOW BELL 212 212 1181420 SW PWA PT6T PT6T3 52045 EA FLEX LINE CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA CPPS61075 (CAN) DURING DAILY INSPECTION AME FOUND HYDRAULIC OIL ON FLOOR UNDER AIRCRAFT HELL HOLE. AFTER INVESTIGATION, THE AME FO UND OIL DRIPPING FROM THE INLET ELBOW OF THE #1 HYDRAULIC PUMP. THE FLEX LINE WAS DISCONNECTED AND ELBOW FOUND CRACKED. 1 G 7 1 4U 4 U H4SW E22EA 1997042800074 19970428 00074 NE 1997 4 28 CA961230011 2 19961216 G 7260 311169301 GEAR PWA 118 PW118 NE ACCESSORY DRIVE LOSS OF TEETH W E ENGINE SHUTDOWN Y ENGINE STOPPAGE CR CRUISE 1 CA 21293 13404 115135 (CAN) THE OPERATOR REPORTED THE ENGINE SHUTDOWN (UNCOMMANDED) DURING FLIGHT. THE ENGINE WAS REMOVED FROM SERVICE AND SEN T FOR OVERHAUL. ENGINE DISASSEMBLY REVEALED THE INFLIGHT SHUTDOWN WAS CAUSED BY A LOSS OF DRIVE TO THE FUEL PUMP, WHICH RESULTED IN LOSS OF FUEL AND OIL PRESSURE, SHUTTING THE ENGINE DOWN. THE LOSS OF DRIVE TO THE FUEL PUMP WAS CAUSED BY TH E FAILURE OF THE GEAR TEETH ON THE MAIN ACCESSORY DRIVE GEAR AND THE MATING TEETH OF THE FUEL PUMP DRIVE GEAR. 4 T E20NE 1997042800075 19970428 00075 EA 1997 4 28 CA961230012 1 19961219 G 5200 WEB CNDAIR CNDAIR CL215 CL2151A10 EA ACTUATOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 1313 (CAN) WATER BOMBER DOOR WOULD NOT CLOSE COMPLETELY. INSPECTION SHOWED CRACKS IN THE WEB WHERE WATER BOMBER ACTUATOR ATTA CHES TO FRAME. CRACKS EXTENDED FROM SPIGOTS TO LIGHTNING HOLES IN FRAME. TWO AIRCRAFT IN FLEET WITH SAME PROBLEM. 2 H 7 2 4R A14EA 1997042800076 19970428 00076 EA 1997 4 28 CA961230013 2 19961212 G 7323 25249994 GOVERNOR ALLIED SIGNA BELL 212 212 1181420 SW PWA PT6T PT6T3 52045 EA #1 ENGINE FAULTY W H DEACTIVATE SYST/CIRCUITS O OTHER CR CRUISE 1 CA 3123 A9091 CPPS61495 (CAN) UPON DEPARTURE THE LOW SIDE GOVERNOR FAILED ON THE #1 ENGINE. #1 THROTTLE WAS ROLLED BACK TO IDLE, GOVERNOR SELECT ED TO MANUAL AND THROTTLE ROLLED UP TO 4 PERCENT BELOW #2 ENGINE. THE FLIGHT WAS CONCLUDED WITHOUT FURTHER INCIDENT. 1 G 7 1 4U 4 U H4SW E22EA 1997042800077 19970428 00077 EU 1997 4 28 CA961230014 1 19961204 G 8120 139312 SUPERCHARGER DOWTY 60207009 BRAERO 748 HS7482A 4231001 EU RROYCE DART DART5342 EU #2 ENGINE FAULTY W A E ENGINE SHUTDOWN O J OTHER WARNING INDICATION CR CRUISE 1 CA 2504 DRG14206021 19427 (CAN) DURING CRUISE 30 MINUTES AFTER DEPARTURE THE #2 ENGINE RPM INDICATOR WENT TO ZERO. HYDRUALIC FLOW LIGHT GENERATOR AND ALTERNATOR LIGHTS ILLUMINATED. THE ENGINE WAS SHUTDOWN AND THE AIRCRAFT RETURNED TO BASE. POST FLIGHT INSPECTION OF THE GEARBOX FOUND THE MAIN DRIVE SHAFT SHEARED, THE SUPERCHARGER SEIZED AND GENERATOR QUILL SHAFT SHEARED. ALL AFFECTED PARTS REPLACED. THE AIRCRAFT RETURNED TO SERVICE. 2 L 7 2 3T 4 T A24EU A196 1997042800078 19970428 00078 EA 1997 4 28 CA961230016 1 19961219 G 5200 WEB CNDAIR CNDAIR CL215 CL2151A10 EA ACTUATOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WATER BOMBER DOOR WOULD NOT CLOSE COMPLETELY. INSPECTION SHOWED CRACKS IN THE WEB WHERE WATER BOMBER ACTUATOR ATTA CHES TO FRAME. CRACKS EXTENDED FROM SPIGOTS TO LIGHTNING HOLES IN FRAME. TWO AIRCRAFT IN FLEET WITH SAME PROBLEM. 2 H 7 2 4R A14EA 1997042800079 19970428 00079 NE 1997 4 28 CA961231002 2 19961220 G 7250 3039512 LP TURBINE DHAV DHC8 DHC8301 NM PWA PW120 PW123 NE BALDE TIPS DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 7823 123045 (CAN) DURING BOROSCOPE INSPECTION THE LP TURBINE BLADES WERE FOUND DAMAGED AT THE TIPS. THE ENGINE WAS REPLACED. 2 H 7 2 4T 4 T RT A13NM E20NE 1997042800080 19970428 00080 1997 4 28 CA961231003 1 19961220 G 7500 311269001 VENTURI P3 PWA PW120 PW123 NE BASE OF FITTING CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 14737 123010 (CAN) DURING INSPECTION DUST WAS FOUND AROUND THE INSULATION COVERING THE P3 BLEED VENTURI. REMOVED INSULATION AND FOUND A 2" CRACK IN THE VENTURI TUBE. THE TUBE WAS REPLACED. 4 T E20NE 1998020500477 19980205 00477 CE 1998 2 5 CA961231004 1 19961226 G 5410 58540028 BEAM ASSEMBLY CESSNA 404 404CESSNA 2075901 CE MCAULY 3FF32 3FF32C501 GL NR1 ENG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 10612 76618 (CAN) NR1 FORWARD ENGINE BEAM CRACKS FOUND ON BOTH THE LEFT AND RIGHT ENGINE BEAM INBOARD AND OUTBOARD. CRACKS LOCATED D IRECTLY UNDER THE MOUNT AND/OR ORIGINATING FROM END OF THE BEAM AND IN A CIRCULAR SHAPEOF ANCHOR NUT FORWARD END. CRACKS EXTENDING THROUGH THE BEAM DOUBLER AND FORWARD LEG OF BEAM. 1 L 7 2 3O A25CE 5 C P45GL 1998020500478 19980205 00478 CE 1998 2 5 CA961231005 1 19961226 G 5343 52130409 WEB CESSNA 404 404CESSNA 2075901 CE MCAULY 3FF32 3FF32C501 GL NLG GEAR ATTACH CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 10612 76618 (CAN) FORWARD NOSE GEAR TUNNEL WEB, NOSE GEAR ATTACH AREA, FOUND CRACKED AROUND ATTACHING BOLTS, CRACKS CIRCULAR UNDER N UTS. LEFT P/N 5213040-10 . NOSE GEAR DRAG BRACE ATTACH AREA LEFT, CRACK FOUND IN TUNNEL SKIN AND DOUBLER LEFT SIDE TOP A FT CORNER. 1 L 7 2 3O A25CE 5 C P45GL 1997042800081 19970428 00081 SO 1997 4 28 CA970106001 1 19961210 G 5520 5499402 HINGE PIPER PA31T PA31T 7103124 SO PWA PT6 PT6A28 EA ELEVATOR BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 3063 PCE50170 (CAN) DURING INSPECTION AN ELEVATOR HINGE WAS FOUND BROKEN. 1 L 7 2 3T 4 T A8EA E4EA 1997042800082 19970428 00082 1997 4 28 CA970106002 4 19961018 G 2562 1104 BATTERY PIPER PA32 PA32R301 7103218 SO LYC O540 IO540K1G5 41532 EA ELT LEAKING W K NONE O OTHER IN INSP/MAINT 1 CA L2578248A (CAN) ELT BATTERY LEAKING CAUSING THE CASE MOUNTING PLATE TO CRACK. 1 L 7 1 3O 3 O A3SO 1E4 1997042800083 19970428 00083 NM 1997 4 28 CA970106003 1 19961214 G 3230 54C546349 SEQUENCING VALVE DHAV DHC8 DHC8201 2809001 NM LEFT GEAR DOORS FAILED W A UNSCHED LANDING J O WARNING INDICATION OTHER CL CLIMB 1 CA (CAN) AFTER TAKEOFF, LANDING GEAR SELECTED UP AND GEAR RETRACTED, BUT THE LEFT GEAR DOORS REMAINED OPEN. GEAR SELECTED D OWN AND LEFT GEAR REMAINED UP AND LOCKED. EMERGENCY GEAR EXTENSION CARRIED OUT. THE RONSON SEQUENCING VALVE FOR THE LEFT LANDING GEAR HAD REMAINED ENERGIZED CAUSING THE PROBLEM. 2 H 7 2 4T RT A13NM 1998041700421 19980417 00421 EU 1998 4 17 CA970106004 1 19960929 G 4930 100644200 FUEL MANIFOLD SUNDSTRANDEM T62T40C3 AMD FALC20 FALCON200 2730150 EU APU CRACKED W F ACTIVATE FIRE EXT. A B K FLAME/FIRE SMOKE/FUMES/ODORS/SPARKS FLUID LOSS TX TAXI/GRND HDL 1 CA 851751 (CAN) CRACK DEVELOPED IN FUEL MANIFOLD WHILE APU OPERATING. FUEL COLLECTED IN TAIL CONE AND FIRE STARTED. IGNITION SOUR CE UNKNOWN. APU EXTINGUISHER FIRED AND APU SHUT DOWN. PORTABLE EXTINGUISHER ALSO USED. SUNDSTRAND OPTIONAL SB T-62T-4 9-113 INSTALLS A FATIGUE RESISTANT FUEL MANIFOLD. 2 L 7 2 4F RT A7EU 1997042800084 19970428 00084 GL 1997 4 28 CA970106005 3 19961121 G 6114 57D220117 HUB PIPER PA32 PA32260 7103206 SO LYC O540 O540E4B5 41532 EA HARTZL HCC2Y HCC2YK1 GL NR 2 SOCKET CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 1869 572 L1006040 CH972 (CAN) DURING CALENDAR TIME INSPECTION THE PROPELLER HUB WAS FOUND CORRODED IN THE #2 SOCKET. IN ACCORDANCE WITH HARTZELL MANUAL NO CORROSION IS PERMITTED. 1 L 7 1 3O 3 O A3SO E295 5 C P920 1997042800085 19970428 00085 GL 1997 4 28 CA970106006 1 19961119 G 2701 2027040800 CONTROL STICK DIAMON DA20A1 DA20A1 05626UX GL STICK SUPPORT RUBBING W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) RUBBING BETWEEN P/N 20-2704-08-00 CONTROL STICK SUPPORT AT THE PILOTS LOCATION AND BOLT P/N AN364-428 AT END OF CO NTROL ROD. APPEARS THAT THE NEW PARTS INSTALLED IN AIRCRAFT AT LATER DATES HAD A LARGER "LIGHTENING" HOLE AND THUS NO RU BBING. 1 L 7 1 3O NT TA4CH 1997042800086 19970428 00086 SO 1997 4 28 CA970106007 2 19960930 G 8530 653426 CYLINDER CESSNA 150 150M 2071830 CE CONT O200 O200A 17020 SO AT COOLING FINS CRACKED W A UNSCHED LANDING E VIBRATION/BUFFET CR CRUISE 1 CA 1514 250825SO (CAN) INSPECTION FOUND CYLINDER CRACKED AT COOLING FINS AFTER AIRCRAFT MADE FORCED LANDING IN FIELD. 1 H 7 1 3O 3 O 3A19 E252 1997042800087 19970428 00087 CE 1997 4 28 CA970106008 1 19961121 G 3246 16119A WHEEL HALF CLEVELAND 40135 CESSNA 421 421B 2076014 CE CONT O520 GTSIO520H 17032 SO NLG BEAD FLANGE CRACKED W O OTHER O OTHER LD LANDING 1 CA 5018 235232R (CAN) CREW NOTED WHEEL NOISE ON LANDING. INVESTIGATION REVEALED THE INBOARD WHEEL HALF CRACKED AT THE BEAD FLANGE, APPRO XIMATELY 4 INCHES LONG. 1 L 7 2 3O 3 O A7CE E7CE 1997042800089 19970428 00089 CE 1997 4 28 CA970106010 1 19961223 G 5320 12114223 DOUBLER CESSNA 12114223 CESSNA 210 T210G 2073432 CE CONT O520 TSIO520C 17040 SO BOLT HOLES CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 2644 14040266 (CAN) CRACKS DISCOVERED AROUND BOLT HOLES ON THE OUTBOARD SIDE OF THE DOUBLER. LEFT HAND SIDE OF THE MAIN LANDING GEAR. 1 H 7 1 3O 3 O 3A21 E8CE 1997042800090 19970428 00090 CE 1997 4 28 CA970107001 1 19961231 G 3233 1053840021 ACTUATOR GERDES 1053840021 BEECH 76 76 1153005 CE LT GEAR FAILED W H DEACTIVATE SYST/CIRCUITS O OTHER CR CRUISE 1 CA 0152REVD (CAN) IN LEVEL FLIGHT A LOUD BANG WAS HEARD FROM THE LEFT SIDE OF THE AIRCRAFT. THE GEAR WAS LOWERED AND A SUCCESSFUL LA NDING COMPLETED. THE LEFT HAND ACTUATOR CYLINDER WAS FOUND TO HAVE FAILED AT THE ROD END. 1 L 7 2 3O A29CE 1997042800091 19970428 00091 CE 1997 4 28 CA970107002 1 19961220 G 3240 10558000015 BRAKE LINE BEECH 76 76 1153005 CE WING CUT W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) BRAKE LINE FOUND CUT IN THE WING BY A CONTROL CABLE. REPAIRED AND RETURNED TO SERVICE. 1 L 7 2 3O A29CE 1997042800092 19970428 00092 SO 1997 4 28 CA970107004 1 19961230 G 3230 REDUCING VALVE EMB 110 EMB110P1 3260122 SO MLG OUT OF ADJUST W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) ON TAKEOFF LANDING GEAR SELECTED TO RETRACT. RED IN TRANSIT LIGHT WOULD NOT GO OUT. GEAR LEVER TO EXTEND AND THREE GREEN INDICATED. PRESSURE REDUCING VALVE FOUND TO BE LOW AT 1300 PSI. VALVE ADJUSTED TO 1400+/-50 PSI. 1 L 7 2 4T A21SO 1997042800093 19970428 00093 SO 1997 4 28 CA970107005 1 19961218 G 8120 LW12778 ACTUATOR GATE PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA TURBOCHARGER EXCESS WEAR W C D ABORTED TAKEOFF RETURN TO BLOCK J WARNING INDICATION TO TAKEOFF 1 CA 1781 L124968A (CAN) ABORTED TAKEOFF DUE TO ENGINE OVER BOOST. WASTE GATE FOUND TO BE SOURCE OF THE PROBLEM. THE ENGINE WAS REPLACED. 1 L 7 2 3O 3 O A20SO E14EA 1997042800094 19970428 00094 NE 1997 4 28 CA970107006 2 19961226 G 7314 50087350 FUEL PUMP SUNDSTRAND AIRBUS 320 A320231 3930325 EU IAE V2500 V2500A1 NE LOW STAGE SHEARED SHAFT W C D ABORTED TAKEOFF RETURN TO BLOCK R PARTIAL RPM/PWR LOSS TO TAKEOFF 1 CA 7358 0619 V0349 (CAN) ENGINE DID NOT PRODUCE TAKEOFF POWER AND WAS DIFFICULT TO START. INVESTIGATION FOUND THE TWO STAGE FUEL PUMP WAS N OT DELIVERING THE VOLUME OF FUEL REQUIRED, DUE TO A SHEARED DRIVE. 2 L 7 2 4F 4 F RT A28NM E311NE 1997042800095 19970428 00095 NM 1997 4 28 CA970107009 1 19961218 G 3230 54C546347 VALVE KAISER DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE LANDING GEAR BROKEN W O OTHER K FLUID LOSS CL CLIMB 1 CA 25448 0111 120248 (CAN) AFTER TAKEOFF #2 HYDRAULIC SYSTEM PRESSURE AND QUANTITY INDICATED ZERO. INSPECTION FOUND THE MAIN LANDING GEAR SEQ UENCE VALVE SEPARATED BETWEEN THE VALVE BODY AND THE ELECTRICAL SOLENOID. 2 H 7 2 4T 4 T RT A13NM E20NE 1997042800096 19970428 00096 NE 1997 4 28 CA970107010 2 19961220 G 7250 311330301 PT BLADE PWA 118 PW118 NE POWER TURBINE FRACTURED W K NONE O OTHER IN INSP/MAINT 1 CA 13687 115332 (CAN) OPERATOR NOTICED DAMAGE IN THE POWER TURBINE AND THE ENGINE WAS SHIPPED FOR INVESTIGATION AND OVERHAUL. DISASSEMBL Y FOUND THE ENGINE HAD SUFFERED THE FAILURE OF TWO PT1 BLADES. THEY HAD FAILED A SHORT DISTANCE BELOW THE OUTER PLATFORM . THIS IS AN UNUSUAL FAILURE AND PWC SUGGESTS THAT FROM EXPERIENCE IT COULD BE ASSOCIATED WITH MICROSTRUCTURAL DAMAGE RE SULTING FROM AN OVERTEMPERATURE EXCURSION OR HOT START. 4 T E20NE 1997042800099 19970428 00099 1997 4 28 CA970109003 1 19961213 G 3610 S210T120101 SHUTOFF VALVE HAMSTD GE CF6 CF680C2B6 NE #1 ENGINE AIR FAULTY W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 0216 690255 (CAN) AIR TURNBACK DUE TO "LT ENG HPSOV (HIGH PRESSURE SHUTOFF VALVE)" EICAS MESSAGE ON DURING TAKEOFF AND REMANING ON D URING CLIMB. COULD NOT ERASE MESSAGE. SELECTED #1 ENGINE BLEED AIR OFF. REPLACED #1 HPSOV. 4 F E13NE 1997050100356 19970501 00356 EA 1997 5 1 CA970109018 1 19961217 G 3246 BEARING 32100011 CNDAIR CL600 CL6002B19 EA GE CF34 CF343A 30015 NE NLG LT WHEEL GRINDING W C D ABORTED TAKEOFF RETURN TO BLOCK E VIBRATION/BUFFET TO TAKEOFF 1 CA 3357 807267 (CAN) EXCESSIVE VIBRATION FELT ON TAKEOFF. TAKEOFF REJECTED. SUSPECTED NOSE GEAR TIRE. FOUND LEFT HAND NOSE WHEEL BEARIN G GRINDING. 2 L 7 2 4F 4 F RT A21EA E15NE 1997050100357 19970501 00357 EA 1997 5 1 CA970109019 1 19961209 G 2131 21197645 SELECTOR PANEL CNDAIR CL600 CL6002B19 EA GE CF34 CF343A 30015 NE PRESSURIZATION FAILED W A UNSCHED LANDING O OTHER CR CRUISE 1 CA 3307 807267 (CAN) AIRCRAFT WOULD NOT DEPRESSURIZE. PRESSURIZATION SELECTOR PANEL REPLACED. 2 L 7 2 4F 4 F RT A21EA E15NE 1997050100358 19970501 00358 EA 1997 5 1 CA970109020 1 19961217 G 3260 SENSOR CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE GROUND SHIFT CONTAMINATED W A UNSCHED LANDING G J MULTIPLE FAILURE WARNING INDICATION CL CLIMB 1 CA 1319 GEE807389 (CAN) AFTER TAKEOFF, MULTIPLE EICAS MESSAGES APPEARED. ALSO MEMENTARY PASSENGER DOOR WARNING. GROUND SHIFT PROXIMITY SEN SOR CONTAMINATED WITH ICE AND GREASE. ALSO FOUND PASSENGER EXTERIOR DOOR HANDLE RELEASE LEVER NOT FLUSH WHEN HANDLE CLOS ED. NOSE GEAR PROXIMITY SENSOR AND TARGET CLEANED. PASSENGER DOOR HANDLE RELEASE LEVER LUBRICATED. 2 L 7 2 4F 4 F RT A21EA E15NE 1997050100359 19970501 00359 EU 1997 5 1 CA970109021 1 19961213 G 3230 GEAR LOCK AIRBUS 320 A320211 3930320 EU RH LANDING GEAR FOUND INSTALLED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) AFTER TAKEOFF, UNABLE TO RETRACT LANDING GEAR. GEAR RECYCLED NO CHANGE. LEFT GEAR NOT UPLOCKED INDICATION ON ECAM COMPUTER. AIRCRAFT RETURNED TO BASE. MAINTENANCE CHECK REVEALED RH GEAR LOCK INSTALLED. LOCK REMOVED, NO FAULT ON CFDS ( CENTRALIZED FAULTY DISPLAY SYSTEM). SYSTEM CHECKED SERVICEABLE. 2 L 7 2 4F RT A28NM 1997050100360 19970501 00360 EU 1997 5 1 CA970109022 1 19961215 G 3230 SENSOR BOLT AIRBUS 320 A320211 3930320 EU MLG LOOSE W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 CA (CAN) AFTER TAKEOFF, LANDING GEAR WOULD NOT RETRACT. GEAR RECYCLED, NO CHANGE. AIRCRAFT RETURNED TO BASE. MAINTENANCE TR OUBLESHOOTING FOUND SENSOR TARGET BOLT LOOSE. SENSOR BOLT RETIGHTENED AND GEAR SWING CARRIED OUT AND SYSTEM CHECKED SERV ICEABLE. 2 L 7 2 4F RT A28NM 1997050100361 19970501 00361 WP 1997 5 1 CA970109023 1 19961202 G 3310 53989 LIGHT RHEOSTAT DOUG DC9 DC932 3022066 WP PWA JT8 JT8D7A 52053 NE CAPT MAP LIGHT ELECT SHORT W O OTHER B SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 CA P657716D (CAN) ON TAXIING OUT, SMOKE OBSERVED COMING FROM CAPTAIN'S MAP LIGHT. TROUBLESHOOTING REVEALED WIRES SHORTED ON RHEOSTAT . DEFECTIVE RHEOSTAT CHANGED. 2 L 7 2 4F 4 F A6WE E2EA 1997050100362 19970501 00362 WP 1997 5 1 CA970109024 1 19961214 G 2530 60529042 COOLING FAN DOUG DC9 DC932 3022066 WP PWA JT8 JT8D7A 52053 NE GALLEY INOPERATIVE W O H OTHER DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS DE DESCENT 1 CA P657460D (CAN) ELECTRICAL SMOKE FUMES IN FRONT OF GALLEY AREA DURING DESCENT. GALLEY POWER REMOVED AND SMELL DISSIPATED. MAINTENA NCE TROUBLESHOOTING REVEALED RH COOLING FAN INOPERATIVE POPPING CIRCUIT BREAKER. DEFECTIVE FAN REPLACED AND OPERATIONALL Y CHECKED SERVICEABLE. 2 L 7 2 4F 4 F A6WE E2EA 1997050100363 19970501 00363 WP 1997 5 1 CA970109025 1 19961217 G 2530 CA167072 ELECT SOCKET DOUG DC9 DC932 3022066 WP PWA JT8 JT8D7A 52053 NE GALLEY OVEN BROKEN WIRE W O H OTHER DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS DE DESCENT 1 CA P657239D (CAN) ON DESCENT, STRONG ELECTRICAL SMELL COMING FROM FORWARD GALLEY. GALLEY POWER TURNED OFF. TROUBLESHOOTING REVEALED GALLEY OVEN UNIT PIN #3 ON RECEPTACLE WIRING SHORTED. WIRE REPAIRED AND SOCKET REPLACED. CHECKED SERVICEABLE. 2 L 7 2 4F 4 F A6WE E2EA 1997063000001 19970630 00001 WP 1997 6 30 CA970109026 1 19961212 G 3213 OLEO SEALS DOUG DC9 DC932 3022066 WP PWA JT8 JT8D7A 52053 NE NOSE LDG OLEO LEAKING W A UNSCHED LANDING J K WARNING INDICATION FLUID LOSS CL CLIMB 1 CA P657363D (CAN) AFTER TAKEOFF AND GEAR SELECTED UP, NOSE GEAR UNSAFE LIGHT CAME ON ACCOMPANIED BY A LOUD NOISE COMING FROM NOSE WH EEL WELL AREA. QRH (QUICK REFERENCE HANDBOOK) DRILL CARRIED OUT AND AIRCRAFT LANDED SAFELY. MAINTENANCE TROUBLESHOOTING REVEALED NOSE OLEO FLAT AND LEAKING. NOSE OLEO SEALS REPLACED AND OLEO SERVICED. CHECK SWING CARRIED OUT SERVICEABLE. 2 L 7 2 4F 4 F A6WE E2EA 1997050100365 19970501 00365 NE 1997 5 1 CA970109030 2 19961217 G 7200 HC361H0064000 FLANGE LYC ALF502 ALF502R5 41580 NE AROUND LIP CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA LF05083 (CAN) INSPECTION FOUND CRACK AROUND ENGINE FLANGE LIP. 4 F E6NE 1997050100366 19970501 00366 WP 1997 5 1 CA970109031 1 19961205 G 3234 SELECT LEVER CVAC 340 340CVAC 242270A WP ALLSN 501D 501D13 03004 GL MLG SEIZED W A UNSCHED LANDING O OTHER CL CLIMB 1 CA 501634 (CAN) LH POWER LEVER FROZEN IN CLIMB OUT. ON LANDING THE LANDING GEAR LEVER WOULD NOT RELEASE TO DOWN POSITION AND REQUI RED THE USE OF THE EMERGENCY EXTENSION. ONCE LANDED MAINTENENACE CHECKED THE POWER LEVER AND RETRACTION SYSTEM AND BOTH OPERATED NORMALLY. LH POWER LEVER AND GEAR RETRACTIOIN LINKAGE AND CONTROL SYSTEMS INSPECTED FROM PEDESTAL TO LH FUEL CO NTROL UNIT FOR CORRECT ROUTING AND OPERATION. MOISTURE WAS FOUND ON CABLES AND FUSELAGE PRESSURE SEALS LH SIDE. SUSPECT FROZEN CONTROLS DUE TO SLUSH THROWN INTO WHEEL WELL AND FREEZING CAUSING CONTROLS TO TEMPORARILY SEIZE. CABLES AND LINKA GE CLEANED AND LUBRICATED AS PER MAINTENANCE MANUAL. 2 L 7 2 4R 4 T 6A6 E282 1997050600004 19970506 00004 EU 1997 5 6 CA970110001 1 19961218 G 2760 503243000 PIVOT ARM SZD 24 SZD244A 8221004 EU DIVE BRAKE LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA 306 (CAN) WHILE PERFORMING PZL-BIELSKO SB BA-047/50-3/94, THE R/H WING INBOARD DIVE BRAKE PIVOT ARM BOLT WAS FOUND COMPLETEL Y LOOSENED OFF. THE THREADED PORTION HAD DISENGAGED FROM THE NUTPLATE. ACTIVATION OF DIVE BRAKE CAUSED POSITIVE ROTATION OF THE BOLT. 1 K 0 0 G10EU 1997050100369 19970501 00369 1997 5 1 CA970110004 4 19961231 G 2350 LIGHTING PANEL BEECH 200 B200C 1152924 CE PWA PT6 PT6A42 52043 NE CABIN SAT/COMM SHORTED W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA 163 PCE93184 (CAN) WHILE IN CRUISE FLIGHT SMOKE WAS NOTED COMING FROM THE RIGHT HAND SAT/COMM AUDIO PANEL LOCATED IN THE CABIN. CIRCU IT BREAKERS PULLED AND THE PANEL WAS REPLACED AFTER A SAFE LANDING. 1 L 7 2 4T 4 T A24CE E4EA 1997050100370 19970501 00370 CE 1997 5 1 CA970110005 1 19961213 G 7712 26060113 INDICATOR 26060113 CESSNA 208 208B 2073701 CE ENG TORQUE LEAKING W K NONE O OTHER CR CRUISE 1 CA 98 233 (CAN) TORQUE INDICATOR WAS NOTED TO BE LEAKING AND FILLING WITH OIL. 1 H 7 1 3T A37CE 1997050100371 19970501 00371 NM 1997 5 1 CA970113001 1 19961010 G 2720 NAS755010 BUSHING DHAV DHC8 DHC8301 NM RUDDER HINGE MISSING W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) THIS REPORT FROM CAA INDICATING THAT EXCESSIVE PLAY WAS NOTED IN THE LOWER PORTION OF BOTH THE TOP AND BOTTOM TRAI L-TO-FORE RUDDER HINGE POINTS. IT WAS FOUND THAT A BUSHING WAS MISSING. THE HINGE POINTS HAD BEEN PREVIOUSLY REPAIRED US ING OVERSIZED BUSHES (SB 8-27-48) BUT THAT THE INTERNAL BUSHES HAD BEEN OMITTED. THERE WERE NO FLIGHT PROBLEMS REPORTED NOR ANY DAMAGE DUE TO THE MISSING BUSHINGS. FLEET CHECK INITIATED. 2 H 7 2 4T RT A13NM 1997050100373 19970501 00373 EA 1997 5 1 CA970114003 2 19961212 G 8550 NBSIG575 BREATHER TUBE BNORM BN2 BN2A26 1520226 EU LYC O540 O540E4C5 41532 EA CRANKCASE FROZEN W E ENGINE SHUTDOWN K FLUID LOSS CR CRUISE 1 CA 12284 RL1327440 (CAN) CRANKCASE BREATHER LINE FROZE. CRANKCASE PRESURIZED AND OIL DIP STICK WAS BLOWN OUT OF SECURE POSITION. OIL WAS ES CAPING, PILOT NOTICED OIL ON ENGINE NACELLE AND SHUTDOWN ENGINE. NO SECONDARY HOLE IN BREATHER LINE FOUND. 1 H 7 2 3O 3 O A17EU E295 1997050100374 19970501 00374 NM 1997 5 1 CA970114007 1 19961219 G 2910 0-RING 2403001001 DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE SPOILER TRUNNION LEAKING W O OTHER J K WARNING INDICATION FLUID LOSS CR CRUISE 1 CA 20440 1061 120275 (CAN) ON CLIMB OUT CREW NOTICED #1 HYDRAULIC QUANTITY WAS DECREASING. FLAPLESS LANDING CARRIED OUT. MAINTENANCE FOUND TH AT THE FLIGHT SPOILER UNLOADING VALVE WAS LEAKING AT THE LOWER TRUNNION. 2 H 7 2 4T 4 T RT A13NM E20NE 1997050100375 19970501 00375 EA 1997 5 1 CA970114008 1 19961220 G 7922 37031 THERMOSTAT ACT DHAV DHC7 DHC7103 2802710 EA PWA PT6 PT6A50 52043 EA HAMSTD 24PF 24PF305 GL OIL COOLER FAULTY W A E UNSCHED LANDING ENGINE SHUTDOWN J K WARNING INDICATION FLUID LOSS CL CLIMB 1 CA 12516 PCE86394 237121 (CAN) FIFTEEN MINUTES IN CLIMB THE #2 ENGINE BEGAN TO LOSE OIL PRESSURE. THE CREW ELECTED TO SHUT THE ENGINE DOWN. POST FLIGHT INSPECTION FOUND THE OIL COOLER VERNATHERM THERMOSTATIC ACTUATOR WAS LEAKING CAUSING A GRADUAL LOSS OF OIL PRESSU RE. FURTHER INSPECTION FOUND THE "O" RING HAD BECOME FLATTENED AND HARDENED OVER TIME. THE "O" RING WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. 2 H 7 4 4T 4 T A20EA E4EA 6 C P1NE 1997050100376 19970501 00376 EU 1997 5 1 CA970114009 2 19961230 G 7311 KB35782A OIL COOLER BRAERO 748 HS7482A 4231001 EU RROYCE DART DART5342 EU #1 ENGINE CRACKED CORE W D E RETURN TO BLOCK ENGINE SHUTDOWN J K WARNING INDICATION FLUID LOSS TX TAXI/GRND HDL 1 CA 24411 4191 19181 (CAN) AIRCRAFT DEPARTED RAMP WHEN PILOT RECEIVED A LOW OIL PRESSURE WARNING FROM THE #1 ENGINE. AIRCRAFT RETURNED TO RAM P. INSPECTION FOUND THE OIL COOLER HAD FAILED RESULTING IN LOST OF OIL AND SUBSEQUENT LOW OIL PRESSURE WARNING. 2 L 7 2 3T 4 T A24EU A196 1997050100377 19970501 00377 SO 1997 5 1 CA970114010 2 19961229 G 8530 CH73ER CYLINDER CESSNA 421 421C 2076016 CE CONT O520 GTSIO520L 17032 SO MCAULY 3FF32 3FF32C501 GL #5 POSITION SEPARATED W A UNSCHED LANDING E VIBRATION/BUFFET CL CLIMB 1 CA 1024 L276323R 931863 (CAN) #1 ENGINE RUNNING ROUGH ON TAKEOFF. AIRCRAFT RETURNED TO BASE. POST FLIGHT INSPECTION FOUND #5 CYLINDER HEAD SEPAR ATED FROM THE BARREL, WITH A THREE INCH CRACK FROM THE INTAKE VALVE TO THE INTAKE PORT. 1 L 7 2 3O 3 O A7CE E7CE 5 C P45GL 1997050100378 19970501 00378 CE 1997 5 1 CA970114011 1 19961227 G 2140 CAS40121 HEATER SOUTHWIND 8472C CESSNA 414 414 2075908 CE CONT O520 TSIO520NB 17040 SO CABIN PUMP FAILED W K NONE O OTHER CR CRUISE 1 CA 156 5436 L519205 (CAN) THE HEATER FAILED IN CRUISE FLIGHT AND COULD NOT BE RESTARTED. MAINTENANCE FOUND THE IGNITION COIL SWOLLEN AND LEA KING OIL AND THE FUEL PUMP ALSO LEAKING. UNITS REPLACED AND AIRCRAFT RETURNED TO SERVICE. 1 L 7 2 3O 3 O RT A7CE E8CE 1998040200027 19980402 00027 CE 1998 4 2 CA970114012 1 19961231 G 3240 BRAKE CESSNA 500 500CESSNA 2076602 CE RT MAIN FROZEN W K NONE O OTHER LD LANDING 1 CA (CAN) THE AIRCRAFT LANDED AND THE RT MAIN WHEEL SKIDDED AND EVENTUALLY BLEW. INVESTIGATION REVEALED THAT THE RT BRAKE H AD ICED UP AND SUBSEQUENTLY FROZE UP. THE AIRPORT OF DEPARTURE HAD SOME SNOW ON THE RUNWAY AND CAUSED THE ICING. AIRCR AFT MOVED TO HANGAR FOR WARMING AND BRAKE FREELY ROTATED. 1 L 7 2 4F A22CE 1997050100379 19970501 00379 CE 1997 5 1 CA970114013 1 19960912 G 2720 07600129 RUDDER BAR CESSNA 07600129 CESSNA 185 A185F 2072821 CE MCAULY 2A34C D2A34C58 GL RUDDER PEDAL LT BROKEN W K NONE O OTHER TX TAXI/GRND HDL 1 CA 3992 748323 (CAN) WHILE TAXIING THE RUDDER BAR BROKE AT THE OUTBOARD PEDAL ATTACH REINFORCEMENT. SE 72-36 MOD. FOUND AND INCORPORATE D. 1 H 7 1 3O 3A24 5 C P3EA 1998040200028 19980402 00028 CE 1998 4 2 CA970114015 1 19961220 G 3230 AN8336D ELBOW LEAR 35 31A 5170531 CE RETRACT ACTUATOR LOOSE W K NONE K W FLUID LOSS INADEQUATE Q C IN INSP/MAINT 1 CA 420 (CAN) DURING A WALK AROUND, HYDRAULIC FLUID WAS NOTICED LEAKING FROM THE NOSE GEAR AREA. GEAR AREA CLEANED UP AND GEAR SWING CARRIED OUT. FLUID NOTICED LEAKING FROM AROUND THE RETRACT LINE OF THE NOSE GEAR ACTUATOR. FITTING FOUND TO BE L OOSE. FITTING TIGHTENED AND LEAK CHECK CARRIED OUT. PART TC: 279. 2 L 7 2 4F RT A10CE 1997050100380 19970501 00380 NE 1997 5 1 CA970114016 1 19961221 G 7921 481141029 OIL COOLER AEROSP ATR42 ATR42300 8680920 EU PWA 120 PW120 NE HAMSTD 14SF 14SF5 NE NR1 ENG CRACKED CORE W C D ABORTED TAKEOFF RETURN TO BLOCK J K WARNING INDICATION FLUID LOSS TO TAKEOFF 1 CA 9655 4286 AC10141 120721 880920 (CAN) ON TAKEOFF ROLL, THE CREW NOTED A LOW OIL PRESSURE ON #1 ENGINE. AIRCRAFT RETURNED TO BLOCKS. OIL COOLER CORE FOUN D CRACKED AND LEAKING. 2 H 7 2 4T 4 T RT A53EU E20NE 6 C P7NE 1997050100381 19970501 00381 EU 1997 5 1 CA970114018 1 19961223 G 2430 10200311 GCU AUXILEC AEROSP ATR42 ATR42300 8680920 EU PWA 120 PW120 NE HAMSTD 14SF 14SF5 NE #1 ENG FAILED W D RETURN TO BLOCK J WARNING INDICATION TX TAXI/GRND HDL 1 CA 13835 512734 120905 880501 (CAN) AFTER STARTING #1 ENGINE DURING TAXI, THE CREW OBSERVED A DC GENERATOR FAULT. THE AIRCRAFT WAS RETURNED TO THE BLO CKS. #1 GCU REPLACED. 2 H 7 2 4T 4 T RT A53EU E20NE 6 C P7NE 1997050100383 19970501 00383 EA 1997 5 1 CA970114020 1 19961226 G 3260 SENSOR CNDAIR CL600 CL6002B19 EA GE CF34 CF343A 30015 NE NLG OUT OF ADJUST W K NONE O OTHER NR NOT REPORTED 1 CA 4369 807213 (CAN) NOSE GEAR WOULD NOT RETRACT. NOSE GEAR SENSOR FOUND OUT OF ADJUSTMENT. RIGGED AS PER MAINTENANCE MANUAL. 2 L 7 2 4F 4 F RT A21EA E15NE 1997050100384 19970501 00384 WP 1997 5 1 CA970114022 1 19961226 G 3231 GEARDOOR DOUG DC9 DC932 3022066 WP PWA JT8 JT8D7A 52053 NE RH MAIN LDG NO EXTENSION W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA P656860D (CAN) ON RETRACTION RH LANDING GEAR UNSAFE LIGHT REMAINED ON WITH GEAR DOOR OPEN LIGHT. RECYCLED GEAR AND DOWN LOCK INDI CATION NORMAL. GEAR RETRACTED GIVING SAME RESULTS. AIRCRAFT RETURNED TO BASE. INSPECTION REVEALED SOME DAMAGE TO RH LAND ING GEAR CUT OUT AREA OF FUSELAGE. SUSPECT RH MAIN LANDING DOOR DID NOT EXTEND ON RETRACTION, CAUSING DAMAGE TO FALSE WO RK AFT OF RH MAIN LANDING GEAR. BOTH MAIN LANDING GEAR OLEOS SERVICED AND FALSE WORK REPAIRED. SEVERAL LANDING GEAR CHEC K SWINGS CARRIED OUT SERVICEABLE. 2 L 7 2 4F 4 F A6WE E2EA 1997050100385 19970501 00385 EA 1997 5 1 CA970114023 1 19961230 G 5210 H34149 DOOR HANDLE CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE PAX DOOR FAILED W B I EMER. DESCENT CABIN DEPRESSURIZATION J WARNING INDICATION CL CLIMB 1 CA 1537 GEE807365 (CAN) CLIMBING THROUGH 14,000 FEET, THE CREW GOT A DOOR HANDLE WARNING FOLLOWED BY A PASSENGER DOOR WARNING. THE FLIGHT THEN DESCENDED THROUGH 13,000 FEET AND DEPRESSURIZED. THE WARNING LIGHT WENT OUT. OUTER DOOR HANDLE REPLACED AND DOOR ME CHANISM RIGGED AS PER MAINTENANCE MANUAL. 2 L 7 2 4F 4 F RT A21EA E15NE 1997050100386 19970501 00386 EA 1997 5 1 CA970114024 1 19961227 G 3260 SENSOR CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE NLG S23 ICED UP W K NONE O OTHER NR NOT REPORTED 1 CA 3637 807165 (CAN) UNABLE TO RAISE NOSE LANDING GEAR. FOUND ICE ON SENSOR #S23 AND TARGET. SENSOR AND TARGET CLEANED. 2 L 7 2 4F 4 F RT A21EA E15NE 1997050100391 19970501 00391 CE 1997 5 1 CA970115001 1 19961230 G 3211 1091200281 DRAG LEG BEECH 90 F90 1152909 CE PWA PT6 PT6A135 52043 NE LT MLG CRACKED W K NONE O OTHER LD LANDING 1 CA 3581 PCE92278 (CAN) AIRCRAFT LANDED ON ICY RUNWAY WITH FROZEN BRAKES AND CAME TO A JARRING STOP WHEN CLEAR RUNWAY WAS ENCOUNTERED. INS PECTION FOUND THE RADII OF THE LEFT HAND DRAG LEG CRACKED. 1 L 7 2 4T 4 T A31CE E4EA 1997050600005 19970506 00005 NE 1997 5 6 CA970115004 2 19961223 G 7200 ENGINE BRAERO 748 HS7482B 1500248 EU RROYCE DART DART5352 54509 NE POWER SECT MAKING METAL W E ENGINE SHUTDOWN J WARNING INDICATION AP APPROACH 1 CA 3957 7149 (CAN) ENGINE WAS SHUTDOWN DURING APPROACH DUE TO ILLUMINATED OIL PRESSURE WARNING LIGHT. POST FLIGHT INSPECTION FOUND ME TAL IN THE OIL FILTER. THE ENGINE WAS REMOVED. 2 L 7 2 3T 4 T A24EU E297 1997050100394 19970501 00394 EU 1997 5 1 CA970115007 1 19961017 G 6330 350A38101832 CROSSBEAM SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1B 6OO30 NE XMSN MOUNT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 257 (CAN) DGACD AD 96-156-071(B) CARRIED OUT, CRACK IN RADIUS OF THIN ATTACHMENT LUG FOUND. 1 G 7 1 3U 3 U H9EU E19EU 1997050800725 19970508 00725 SO 1997 5 8 CA970124002 2 19961216 G 8520 TRANSFER TUBE CESSNA 207 207 2073602 CE CONT O520 IO520F 17032 SO MCAULY D3A34 D3A34C404 GL CRANKSHAFT LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA 1740 286169R 792737 (CAN) DURING TEARDOWN OF A TIME EXPIRED ENGINE IT WAS DISCOVERED THE OIL TRANSFER TUBE IN THE CRANKSHAFT TO THE #6 CONNE CTING ROD HAD WORKED LOOSE AND BEGAN WEARING INTO THE CONNECTING ROD BEARING. THIS TUBE IS FIXED AT MANUFACTURE. THE CRA NKSHAFT WAS SCRAPPED. 1 H 7 1 3O 3 O A16CE E5CE 5 C P47GL 1997051300022 19970513 00022 CE 1997 5 13 CA970124003 1 19961004 G 6120 993800075 CONTROL CABLE BEECH 100 100BEECH 1152916 CE PWA PT6 PT6A28 EA HARTZL HCD4N3 HCD4N3A GL RT PROP BROKEN W D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 CA 12677 PCE52489 FY952 (CAN) CABLE BROKE WHERE IT ATTACHES TO THE BELLCRANK ASSEMBLY UNDER THE PEDESTAL. CABLE BROKE AT THE SWAGE INSIDE THE TE LESCOPING TUBES. SUBMITTER STATES CABLE INSPECTION IS DIFFICULT AT THIS LOCATION. PILOTS REPORTED ROUGHNESS IN THE CONTR OL FOLLOWED BY THE FAILURE WHEN FORCE APPLIED. NEW PART INSTALLED. 1 L 7 2 3T 4 T A14CE E4EA 5 C STC 1997050800737 19970508 00737 WP 1997 5 8 CA970129008 1 19961123 G 2910 7927177799 HYDRAULIC LINE DOUG DC9 DC932 3022066 WP PWA JT8 JT8D7A 52053 NE RT HYD SYS LEAKING W O OTHER K FLUID LOSS CR CRUISE 1 CA P654119D (CAN) DURING TEST FLIGHT, RIGHT HYDRAULIC FLUID LOST. HYDRAULIC BRAKE PRESSURE READ 3400 P.S.I. PRIOR TO PRESSURE LOSS. NEW HYDRAULIC LINE FABRICATED AND INSTALLED AND LEAK CHECKED SERVICEABLE. 2 L 7 2 4F 4 F A6WE E2EA 1997050800738 19970508 00738 WP 1997 5 8 CA970129009 1 19961124 G 2120 9267531 DUCT DOUG DC9 DC932 3022066 WP PWA JT8 JT8D7A 52053 NE LH AIRCONDITION DAMAGED W B EMER. DESCENT J WARNING INDICATION CR CRUISE 1 CA P656844D (CAN) AT FLIGHT LEVEL 350 PRESSURIZATION UNCONTROLLABLE FLOW LIGHT CAME ON. EMERGENCY DESCENT CARRIED OUT. MAINTENANCE T ROUBLESHOOTING FOUND DUCTING ON LEFT HAND AIR CYCLING MACHINE DETACHED AND DUCTING ON RH PACK CRACKED AND FLEX CONNECTOR BROKEN. DUCTING ON LH AIR CONDITIONING AIR CYCLING MACHINE CONNECTED AND SECURED. DUCTING AND CONNECTOR ON RH AIR CYCLI NG MACHINE REPLACED AND OPERATIONAL LEAK CHECK CARRIED OUT SERVICEABLE. 2 L 7 2 4F 4 F A6WE E2EA 1997050800739 19970508 00739 WP 1997 5 8 CA970129011 1 19961124 G 2780 59225321 SLAT DOUG DC9 DC932 3022066 WP PWA JT8 JT8D7 52053 NE #2 L/H EXT BRKT DAMAGED W O OTHER F FLT CONT AFFECTED CR CRUISE 1 CA P654059D (CAN) NO SLAT EXTEND LIGHT ON AND SLAT DISAGREE LIGHT ON. LOUD BANG HEARD AT FLAPS 40 DEGREES. TROUBLESHOOTING FOUND SLA T L/H #1 IDLER EXTEND BRACKET BROKEN. MAINTENANCE REPLACED #2 L/H SLAT AND NEW L/H #1 IDLER BRACKET INSTALLED. OPERATION AL CHECK CARRIED OUT SERVICEABLE. 2 L 7 2 4F 4 F A6WE E2EA 1997050800740 19970508 00740 WP 1997 5 8 CA970129012 1 19961129 G 3244 JT8D7B TIRE DOUG DC9 DC932 3022066 WP PWA JT8 JT8D7A 52053 NE #4 TIRE BLOWN W C ABORTED TAKEOFF B SMOKE/FUMES/ODORS/SPARKS TO TAKEOFF 1 CA P657716D (CAN) DURING TAKEOFF ROLL, AIRCRAFT MADE A LURCH TO THE RIGHT ACCOMPANIED BY COMPRESSOR POP AND BLIP IN RIGHT ENGINE PRE SSURE RATIO AND FOLLOWED BY A BURNING RUBBER SMELL. ALL INDICATIONS SUBSEQUENTLY RETURNED TO NORMAL. MAINTENANCE INVESTI GATION REVEALED #4 TIRE HAD BLOWN AND PIECES WERE INGRESSED INTO RH ENGINE, SOME COMPRESSOR FAN BLADES WERE FOUND DAMAGE D. RH ENGINE CHANGED. 2 L 7 2 4F 4 F A6WE E2EA 1997050800741 19970508 00741 EU 1997 5 8 CA970129013 1 19961121 G 5610 STA320261 WINDSHIELD AIRBUS 320 A320211 3930320 EU FORWARD POSITION SHATTERED W A B UNSCHED LANDING EMER. DESCENT O OTHER CR CRUISE 1 CA (CAN) AT FLIGHT LEVEL 390 FIRST OFFICERS WINDSHIELD SHATTERED. THERE WAS NO FORWARD VISIBILITY THROUGH WINDSHIELD. FLIGH T DESCENDED TO FLIGHT LEVEL 230. AIRCRAFT REQUIRED TO LAND AT ALTERNATE BASE. UPON ARRIVAL MAINTENANCE INSTALLED NEW WIN DSHIELD. 2 L 7 2 4F RT A28NM 1997050800742 19970508 00742 EA 1997 5 8 CA970129014 1 19961125 G 2750 860D10018ABC FECU CNDAIR CNDAIR CL600 CL6002B19 EA GE CF34 CF343A 30015 NE FLAPS FAILED W A UNSCHED LANDING O OTHER CL CLIMB 1 CA 3026 807267 (CAN) FLAPS FAILED AFTER TAKEOFF. CIRCUIT BREAKER RESET - NO GOOD. FLAPS STUCK AT 8 DEGREES. REPLACED FLAP ELECTRONIC CO NTROL UNIT AND ALSO BRAKE POSITION SENSING UNIT. 2 L 7 2 4F 4 F RT A21EA E15NE 1997050800743 19970508 00743 EA 1997 5 8 CA970129015 1 19961119 G 3230 PROXIMITY SWITCH CNDAIR CL600 CL6002B19 EA GE CF34 CF343A 30015 NE NOSE GEAR OUT OF ADJUST W A UNSCHED LANDING O OTHER CL CLIMB 1 CA 5036 807157 (CAN) NOSE GEAR WOULD NOT RETRACT. LANDING GEAR EXTEND AND RETRACT CENTRE PROXIMITY SWITCH ADJUSTED. 2 L 7 2 4F 4 F RT A21EA E15NE 1997050800744 19970508 00744 NE 1997 5 8 CA970129016 2 19961227 G 7220 FAN BLADES PWA 4056 PW4056 NE #2 ENGINE DAMAGED W O OTHER E VIBRATION/BUFFET TO TAKEOFF 1 CA P724414 (CAN) HIGH VIBRATION ON #2 ENGINE WITH FAN BLADE SHINGLING. INSPECTION FOUND ALL FAN BLADES SHINGLED, MANY BLADES DAMAGE D AT MID SPAN SHROUD AREA, TWO BLADES ARE BENT OR TWISTED, MANY BLADES WTIH CONTACT SURFACES "B" AND "A" DAMAGED. THE EN GINE PICKED UP HEAVY SNOW (OR SLUSH) DURING TAKEOFF. ALL FAN BLADES REMOVED. STAGE 2 FAN EXIT VANES AND EXHAUST CHECKED SERVICEABLE. FAN BLADE SET WAS REPLACED. ENGINE GROUND RUN AND VIBRATION SURVEY CARRIED OUT SERVICEABLE. 4 F E24NE 1997050800747 19970508 00747 1997 5 8 CA970130003 4 19961119 G 2210 169 AMPLIFIER COLLINS 5222852001 CVAC 340 340CVAC 242270A WP ALLSN 501D 501D13D 03004 GL AUTO PILOT FAILED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA 169 501421 (CAN) AUTO PILOT CAME OFF LINE AND COCKPIT FILLED WITH SMOKE. TROUBLESHOOTING OF PROBLEM REVEALED AUTO PILOT AMP WAS DE FECTIVE. AMP REMOVED AND SYSTEM DEACTIVATED, ALSO WIRING IN THE AREA WAS INSPECTED NO OTHER FAULT FOUND. 2 L 7 2 4R 4 T 6A6 E282 1997050800748 19970508 00748 CE 1997 5 8 CA970130004 1 19961105 G 3260 MS243311 SWITCH MITSUELECT MTSBSI MU2 MU2B35 5780411 CE GARRTT TPE331 TPE3316 01514 WP NLG WIRE BROKEN W L ABORTED APPROACH J N WARNING INDICATION FALSE WARNING AP APPROACH 1 CA P20276C (CAN) ON APPROACH THE CREW WERE UNABLE TO GET A GREEN LIGHT ON THE NOSE GEAR. THE SYSTEM WAS CYCLED AND A SUCCESSFUL LAN DING WAS MADE. INVESTIGATION REVEALED A BROKEN WIRE AT THE ENTRY TO THE SWITCH LOCATION. THE SWITCH WAS REPLACED AND GEA R SWINGS CHECKED OUT. 1 H 7 2 3T 4 T RT A10SW E4WE 1998040200035 19980402 00035 GL 1998 4 2 CA970131001 2 19960930 G 7250 6871505 BEARING ALLSN 250C 250C20B 03013 GL TURBINE NR 5 FAILED W E ENGINE SHUTDOWN J WARNING INDICATION TX TAXI/GRND HDL 1 CA CAE831949 (CAN) DURING GROUND RUN PROCEDURE, THE MAGNETIC CHIP DETECTOR LIGHT CAME ON. ENGINE SHUT DOWN IN NORMAL CONDITION. MET ALLIC PARTICLES WERE FOUND ON THE BOTTOM OF THE CHIP DETECTOR. TURBINE REMOVED AND DISMANTLED. NR 5 BEARING BALL RETAI NER FOUND BROKEN. FURTHER INSPECTION FOUND NO OTHER FAULT WITH ENGINE. TURBINE REBUILT. 3 U E4CE 1997050800763 19970508 00763 EA 1997 5 8 CA970203009 2 19961126 G 8520 11F20022D3 CRANKCASE PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA #6 CYL FLANGE CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 1588 L51968A (CAN) PILOT REPORTED AN OIL LEAK, INSPECTION FOUND THE CRANKCASE WAS CRACKED ALONG THE #6 CYLINDER FLANGE. 1 L 7 2 3O 3 O A20SO E14EA 1997051500279 19970515 00279 EU 1997 5 15 CA970203016 1 19961215 G 2721 1415502297 BRACKET BAG JETSTM JETSTM4112 EU RUD TRIM WORN W K NONE F FLT CONT AFFECTED CR CRUISE 1 CA 4312 (CAN) PRONOUNCED FLUTTER IN FLIGHT FROM RUDDER. RUDDER TRIM UPPER BEARING ASSEMBLY REPLACED. 1 L 7 2 4T RT A196 1997051500289 19970515 00289 CE 1997 5 15 CA970206010 1 19961218 G 7810 EXHAUST DUCT BEECH 100 100BEECH 1152916 CE PWA PT6 PT6A28 EA SKI JUMP CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA P50702 (CAN) PIECE OF SKI JUMP BROKE OFF AND CAME IN CONTACT WITH THE POWER TURBINE. DEFECT FOUND DURING A ROUTINE NOZZLE CHANG E. POWER SECTION SENT FOR REPAIR, THE EXHAUST DUCT WAS FOUND WITH A FAILED SKI JUMP AND INNER SECTION. THE FAILED MATERI AL FROM THE EXHAUST DUCT MOVED UP INTO THE PATH OF THE POWER TURBINE. THIS MATERIAL IMPACTED AND RUBBED ALL THE POWER TU RBINE BLADES AND CAUSED THE INSULATION BLANKET TO BE TORN APART. FAILURE OF THE SKI JUMP AREA OF THE EXHAUST DUCT MAY BE DUE TO THE PROPAGATION OF A CRACK IN THIS SECTION OR ROTATION OF THE #3 BEARING COVER INSIDE THE INNER CONE AREA OF THE EXHAUST DUCT. SB 1430 WAS EMBODIED WHICH INCORPORATES AN INTEGRAL #3 BEARING COVER WITH THE INNER SECTION OF THE EXHAUS 1 L 7 2 3T 4 T A14CE E4EA 1997061900515 19970619 00515 SO 1997 6 19 CA970206012 1 19961212 G 2436 WIRE PIPER PA31T PA31T 7103124 SO PWA PT6 PT6A28 EA VOLTAGE REGULATR MISINSTALLED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 1213 PCE51676 (CAN) SUBMITTER SUSPECTS INCORRECT WIRING OF SYSTEM PERFORMED. VARIOUS FAULTS WITH VOLTAGE REGULATOR AND GENERATOR SYSTE MS. 1 L 7 2 3T 4 T A8EA E4EA 1997051500297 19970515 00297 EA 1997 5 15 CA970210007 2 19961107 G 7314 0532310103 FUEL PUMP DHAV DHC6 DHC6300 EA PWA PT6 PT6A27 52043 EA #2 ENGINE FAULTY W O OTHER O OTHER AP APPROACH 1 CA 5503 PCE40068 (CAN) ON APPROACH IT WAS NOTICED THE FUEL FLOW FLUCTUATED WHEN THE POWER WAS RETARDED ON THE #2 ENGINE. ALL OTHER #2 ENG INE PARAMETERS WERE NORMAL. AFTER LANDING AND PASSENGERS DEPLANING AN ENGINE GROUND RUN WAS CARRIED OUT. WHEN THE POWER LEVER WAS ADVANCED BEYOND FLIGHT IDLE THE FUEL FLOW WOULD FLUCTUATE AND A POPPING SOUND COULD BE HEARD FROM THE #2 ENGIN E. THE #2 ENGINE FUEL CONTROL UNIT AND THE ENGINE FUEL PUMP WERE REPLACED AND THE ENGINE GROUND RUN SERVICEABLE. THE FCU AND FUEL PUMP WERE SENT FOR INSPECTION AND INVESTIGATION. 1 H 7 2 3T 4 T A9EA E4EA 1997051500298 19970515 00298 EA 1997 5 15 CA970210008 2 19961112 G 7414 4370 MAGNETO SLICK PARTEN P68 P68C 6780105 EU LYC O360 IO360A1B6 41514 EA LH MAGNETO FAULTY W O OTHER O OTHER TX TAXI/GRND HDL 1 CA 391 94080245 L2371751A (CAN) ENGINE SHUTDOWN WITHOUT INCIDENT. ON NEXT START BOTH THE RIGHT HAND AND LEFT HAND MAGNETOS WERE DEAD, NO SPARK. 1 H 7 2 3O 3 O A31EU 1E10 1997051500311 19970515 00311 NE 1997 5 15 CA970217002 2 19960203 G 7322 FUEL CONTROL BOEING 727 727225 1384077 NM PWA JT8 JT8D7B 52053 NE #3 ENGINE FAULTY W A F UNSCHED LANDING ACTIVATE FIRE EXT. O OTHER CL CLIMB 1 CA 653874 (CAN) ON DEPARTURE THE CREW NOTICED EXCESSIVE DUCT PRESSURE AND A DROP OF E.P.R. ON #3 ENGINE, THE AIRCRAFT DIVERTED. PO ST FLIGHT MAINTENANCE TROUBLE SHOOTING REPLACED THE FUEL CONTROL UNIT; PRESSURE RATIO BLEED CONTROL VALVE AND THE START BLEED CONTROL VALVE. A BOROSCOPE INSPECTION WAS CARRIED OUT AND THE AIRCRAFT RETURNED TO SERVICE. 2 L 7 3 4F 4 F A3WE E2EA 1997051500312 19970515 00312 NE 1997 5 15 CA970217003 2 19960205 G 7230 766933001 COMPRESSOR CASE BOEING 727 727225 1384077 NM PWA JT8 JT8D7B 52053 NE #3 ENGINE FAILED W A UNSCHED LANDING O OTHER CL CLIMB 1 CA 2058 UAL332 653874 (CAN) ON DEPARTURE THE CREW OBSERVED HIGH N2, HIGH FUEL FLOW AND HIGH EGT AND AN ABNORMALLY HIGH ACCELERATION RATE ON #3 ENGINE. THE AIRCRAFT DIVERTED. POST FLIGHT INSPECTION FOUND THE 12 O'CLOCK POSITION 8TH STAGE BLEED VALVE HAD SEPARATED FROM THE COMPRESSOR CASE ALONG THE WELD SEAM OF THE MOUNTING PAD FOR THE VALVE. THE VALVE ASSEMBLY WAS FOUND IN THE AFT PORTION OF THE ENGINE, LODGED AGAINST THE MIXER ASSEMBLY. 2 L 7 3 4F 4 F A3WE E2EA 1997052900238 19970529 00238 EA 1997 5 29 CA970226004 2 19961016 G 7230 3015956 SPACER BELL 212 212 1181420 SW PWA PT6T PT6T3 52045 EA 2ND STAGE COMP DAMAGED W O OTHER O OTHER TX TAXI/GRND HDL 1 CA 9349 3398 CPPS60514 (CAN) DURING A START ATTEMPT OF #1 ENGINE THE PILOT WAS UNABLE TO OBTAIN ANY N1 ROTATION. WHEN A SECOND START WAS ATTEMP TED AN AUDIBLE "CLUNK" WAS HEARD. THE STARTER GENERATOR AND TACHOMETER WERE REMOVED TO ATTEMPT TO MANUALLY ROTATE N1 DRI VE. NO ROTATION WAS POSSIBLE. THE POWER SECTION WAS REMOVED AND DISASSEMBLY FOUND DAMAGE TO THE COMPRESSOR BLADES, STATO R, SPACER AND AIR SEAL. 1 G 7 1 4U 4 U H4SW E22EA 1997060500759 19970605 00759 NE 1997 6 5 CA970305001 2 19960429 G 7240 726560 COMBUSTION CASE BOEING 727 72725C 138400H NM PWA JT8 JT8D7B 52053 NE INNER COMB CASE LIBERATED W A K NONE O OTHER CR CRUISE 1 CA 848940 (CAN) THE ENGINE WAS REMOVED AND SENT FOR INVESTIGATION DUE TO HIGH EGT AND TREND ANALYSIS THAT INDICATED HOT SECTION DI STRESS. INVESTIGATION FOUND THE INNER COMBUSTION CASE HAD LIBERATED FROM THE FORWARD FLANGE. IT APPEARED TO SUFFER FROM METAL FATIGUE. ALL THE HARDWARE ATTACHED TO THE INNER COMBUSTION CASE SHIFTED AFT CAUSING STATIONARY PARTS TO RUB ON THE 1ST STAGE TURBINE. THE INNER HEAT SHIELDS REMAINED INTACT PREVENTING A FIRE. THE REPORT SUGGESTS THAT CATASTROPHIC FAIL URE WAS IMMINENT. 2 L 7 3 4F 4 F A3WE E2EA 1997060500771 19970605 00771 SW 1997 6 5 CA970311016 1 19960906 G 7712 32447065 TORQUE CONTROL BELL 212 212 1181420 SW PWA PT6T PT6T3 52045 EA #1 ENGINE FAULTY W A UNSCHED LANDING J WARNING INDICATION HO HOVERING 1 CA 3658 963 CPPS60963 (CAN) 25 PERCENT TORQUE SPLIT. #1 ENGINE 3-4 PERCENT LOW N1, 50-70 DG LOW. 1 G 7 1 4U 4 U H4SW E22EA 1999081200320 19990812 00320 SW 1999 8 12 CA970311062 1 19961121 G 5313 206031314023 LONGERON BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL ENGINE BAY MISREPAIRED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA CAE800471BA (CAN) AN UNAPPROVED REPAIR WAS INCORPORATED ON THE ENGINE LONGERON. THE STRUCTURAL REPAIR MANUAL DOES NOT ALLOW REPAIR OF THIS ASSY. 1 G 7 1 3U 3 U H2SW E4CE 1999081200321 19990812 00321 SW 1999 8 12 CA970311072 1 19961125 G 5320 206031314049 CHANNEL BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL FUSELAGE MISREPAIRED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA CAE821443 (CAN) UNAPPROVED REPAIR INCORPORATED. NO REPAIRS ALLOWED IN THIS AREA PER STRUCTURES REPAIR MANUAL. 1 G 7 1 3U 3 U H2SW E4CE 2000020500771 20000205 00771 SO 2000 2 5 CA970312003 1 19961228 G 5280 4752932 HINGE PIPER PA31T PA31T 7103124 SO PWA PT6 PT6A28 EA HARTZL HCB3T HCB3TN3 GL MLG DOOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA PCE41649 BU5276 (CAN) RIGHT INBOARD GEAR DOOR CRACKED. APPROXIMATELY .250 INCH DEEP AND ORIGINATING AT INSIDE RADIUS OF CURVE. REPAI RED. 1 L 7 2 3T 4 T A8EA E4EA 6 C P15EA 1998040200059 19980402 00059 1998 4 2 CA970326005 1 19961112 G 6320 4638305024 BEARING LT INPUT MGB PEELING W K NONE J WARNING INDICATION CR CRUISE 1 CA 2517 (CAN) LEFT HAND INPUT BEARING,ON MAIN TRANSMISSION, PEELING. 1997061200852 19970612 00852 CE 1997 6 12 CA970326007 1 19961120 G 5610 LP345 WINDSHIELD CESSNA 172 172M 2072418 CE CORNERS DISTORTED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) NEW WINDSHIELD ORDERED. WINDSHIELD FOUND UNACCEPTABLE BY CUSTOMER. DISTORTION PREVENTED CLEAR VIEW. A SECOND WIND SHIELD ORDERED WAS ALSO FOUND UNACCEPTABLE DUE TO DISTORTION P/N 0513230-12. 1 H 7 1 3O NT 3A12 1999081200322 19990812 00322 SW 1999 8 12 CA970327011 1 19961114 G 2913 41000455 BOLT BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL HYDRAULIC SERVO MISINSTALLED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 1136 CAE8223126 (CAN) SERVO SENT FOR REPAIR. PER AD CF96-11R2 AND BELL SB 206-67A-01, A BOLT WAS FOUND SUSPECT. UNIT REPAIRED, BOLT RE PLACED. 1 G 7 1 3U 3 U H2SW E4CE 1997071700397 19970717 00397 CE 1997 7 17 CA970421022 1 19961204 G 5730 SKIN CESSNA 340 340A 2076405 CE CONT O520 TSIO520NB 17040 SO MCAULY 3AF32C 3AF32C93 GL WS 63.45 CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 4050 4050 290440R 890661 (CAN) WING SKIN CRACKED, APPROXIMATELY 3 INCHES LONG, DEVELOPED ON TOP SKIN AT STATION 63.45 RUNNING FORE AND AFT BETWEE N BULKHEAD AND MAIN GEAR SIDE BRACE UPPER ATTACH POINT REINFORCEMENT. SUBMITTER STATES THAT THEY ARE DIFFICULT TO DETECT PRIOR TO BECOMING 3 INCHES IN LENGTH, DUE TO CARPET AND OTHER ITEMS. THEY REPORT HAVING REPAIRED 3 SIMILAR CRACKS IN C4 01 AND C402 AIRCRAFT. 1 L 7 2 3O 3 O 3A25 E8CE 5 C P22EA 1998041700529 19980417 00529 WP 1998 4 17 CA970422023 1 19960416 G 6300 COO75 FANSHAFT ROBSIN R44 R44 7640120 WP LYC O540 O540F1B5 41532 EA TAPERED SHAFT FRETTING W K NONE O OTHER IN INSP/MAINT 1 CA 400 L2486340A (CAN) FANWHEEL REMOVED FOR OTHER MAINTENANCE. FRETTING AND METAL TRANSFER NOTICED BETWEEN THE FANSHAFT AND FANWHEEL. 1 G 7 1 3O 3 O H11NM E295 1997070300309 19970703 00309 EA 1997 7 3 CA970508001 2 19960727 G 8500 ENGINE PIPER PA28 PA28160 7102806 SO LYC O320 O320D2A 41508 EA OIL SCREEN MAKING METAL W K NONE O OTHER IN INSP/MAINT 1 CA L488439 (CAN) DURING ANNUAL INSPECTION METAL FILINGS WERE FOUND IN THE ENGINE OIL SCREENS. THE AIRCRAFT REMAINS GROUNDED PENDING ENGINE TEARDOWN. 1 L 7 1 3O 3 O 2A13 E274 1998041700555 19980417 00555 SW 1998 4 17 CA970513007 1 19960430 G 3213 206033108001 SADDLE BELL 206 206L4 1182110 SW CROSSTUBE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) SKID GEAR SHIFTED LATERALLY ALLOWING SADDLE TO WEAR ON LUG ON SKID CROSS TUBE. 1 G 7 1 3U NC H2SW 1997072500029 19970725 00029 GL 1997 7 25 CA970527012 3 19960522 G 6111 S82NC2 BLADE CESSNA 206 U206F 2073333 CE CONT O520 IO520F 17032 SO MCAULY 3A32C D3A32C* GL PROPELLER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 630 279872R 860568 (CAN) PROPELLER RECEIVED FOR OVERHAUL. PROPELLER BLADE WAS FOUND WITH CRACKED THREADS. PROPELLER WAS NEW IN 1986, CORROS ION INSPECTION CARRIED OUT IN 1992. THIS WAS THE FIRST OVERHAUL, NOT REQUIRED BY CARS, BUT DONE AT CUSTOMERS REQUEST. TH E PROPELLER WAS SCRAPPED AND REPLACED WITH A NEW HARTZELL. 1 H 7 1 3O 3 O A4CE E5CE 5 C P21EA 1997110600629 19971106 00629 NE 1997 11 6 CA970820010 3 19961106 G 6111 7756722 BLADE PIN HAMSTD SFA13M10A HAMSTD 14SF 14SF7 NE PROP BLADE WRONG PART W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 6881 852797 (CAN) INCORRECT BLADE PIN WAS FOUND INSTALLED. NO PART NUMBER ON THE PIN. HAMILTON STANDARD HAVE SIMILAR LOOKING PARTS, THE DIFFERENCES ARE DASH NUMBER AND LENGTH. 775672-1 LENGTH 2.48", 775672-2 LENGTH 2.58". SB 14SF-61-A43 WAS ISSUED TO A DDRESS THIS PROBLEM. THE SUBMITTER STATES THIS IS THE SECOND TIME HE HAS CAME ACROSS THIS PROBLEM. 6 C P7NE 1999043000071 19990430 00071 WP 1999 4 30 CA971128007 2 19960709 G 7210 3583605 BEARING MTSBSI MU2 MU2B60 5780460 CE GARRTT TPE331 TPE33110 01514 WP HARTZL HCB4T HCB4TN5 GL PROPELLER SHAFT CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 466 CDA3110 (CAN) AFT PROPELLER SHAFT BEARING FOUND CORRODED. 1 H 7 2 3T 4 T RT A10SW E4WE 6 C P40E 1998111800012 19981118 00012 EA 1998 11 18 CA980915004 2 19960621 G 7414 4353 MAGNETO LYC O360 AEIO360A1E 41514 EA ENGINE FAILED W K NONE O OTHER NR NOT REPORTED 1 CA 396 L2662551A (CAN) DURING FLIGHT, THERE WAS AN EXCESSIVE DROP ON RIGHT HAND MAGNETO. AIRCRAFT LANDED. DURING GROUND RUN BY MAINTENA NCE THE RT MAG FAILED. RT MAG SIMULTANEOUSLY FIRING ON ALL 4 PLUGS. RT MAG REPLACED WITH NEW UNIT. 3 O 1E10 1996040500073 19960405 00073 WP 1996 4 5 CHI1515 1 19960205 G 6410 369D2161531 BLADE HUGHES 369 369E 4470707 WP T/R CRACKED B CHIR K NONE O OTHER IN INSP/MAINT 1 NM 09 1611W 3394 0022221331 0319E TAIL ROTOR BLADE, PN 369A1619-17, WAS FOUND CRACKED AT ONE OF THE MOUNTING RIVET HOLES. THE CRACK EXTENDED FROM THE RIV ET TO THE OUTBOARD EDGE OF FITTING. (X) 1 G 7 1 3U H3WE 1996042400001 19960424 00001 CE 1996 4 24 CHI1542 1 19960104 G 2910 51001198 HYD LINE CESSNA 414 414A 2075907 CE RT WING CORROSION PIT B CHIR O OTHER J K WARNING INDICATION FLUID LOSS CR CRUISE 1 NM 09 2712V 2377 414A0610 DURING FLIGHT TO 'RUN IN' NEW CYLINDER NR 5 RIGHT ENGINE, 40 MINUTES INTO FLIGHT HYDRAULIC FLOW LIGHTS STARTED TO FLICKE R ON AND OFF. WITHIN 10 MINUTES BOTH LIGHTS FLICKERING STAYING ON LONGER. DECIDED TO SLOW AIRCRAFT AND EXTEND GEAR. W HEN ACTUATED ONLY MAINS CAME DOWN AND LOCKED, PUT GEAR DOWN WITH EMERGENCY SYSTEM PER P.O.H., NOSE GEAR LOCKED DOWN, LAN DED AIRCRAFT. (X) 1 L 7 2 3O A7CE 1996072500275 19960725 00275 SW 1996 7 25 CHI1543 1 19960430 G 6410 206016201103 BLADE 2060118103 BELL 206 206B 1181511 SW T/R DELAMINATED B CHIR K NONE O OTHER IN INSP/MAINT 1 NM 09 10ED 1516 TAH2183 1960 BOTH BLADES WERE FOUND DELAMINATED ON THE DOUBLERS AT THE BUTT END. NOTE: THE BLADES WERE REPAINTED IN 1991 - 353.7 HO URS AGO. REFERENCE: OPERATOR CONTROL NR 96ZZZX3668. (X) 1 G 7 1 3U H2SW 1996101700261 19961017 00261 WP 1996 10 17 CHI1593 1 19960916 G 3213 369D292115 SKID TUBE HUGHES 369 369D 4470706 WP LEFT CRACKED B CHIR K NONE O OTHER IN INSP/MAINT 1 NM 09 501CH 170050D LEFT GEAR SKID TUBE CRACKED ON BOTH SIDES UNDER FORWARD GEAR LEG SADDLE. CRACKS ORIGINATE FROM NUTPLATE ACCESS HOLE ON BOTTOM SIDE UNDER ABRASION STRIP AND PROGRESS UPWARD ON BOTH SIDES THROUGH ENTER HOLES (UNUSED) AND STOP APPROXIMATELY 2 .25 INCHES FROM EACH OTHER. REPLACED SKID TUBE WITH NEW PART. SOR MSG NR 056845 SENT TO MDHC. CRACKED SECTION OF TUBE BEING SENT TO MDHC FOR FURTHER INVESTIGATION. (X) 1 G 7 1 3U H3WE 1996110700279 19961107 00279 WP 1996 11 7 CHI1595 1 19960904 G 6210 369A10045 BLADE PIN HUGHES 369 369D 4470706 WP M/R BLADE FAILED B A CHIR K NONE O OTHER IN INSP/MAINT 1 NM 09 502CH 0098846097 180252D DURING THE 100-HOUR INSPECTION WHILE BLADES WERE BEING REMOVED FOR INSPECTION, THE MAIN ROTOR BLADE PIN S/N 09884-6097 F ELL APART. THE BLADE PIN SHANK BROKE AT THE POINT WHERE THE THREADS START. PART TT: 4667.2. PART HAS A LIFE LIMIT OF 7600 HRS. (X) 1 G 7 1 3U H3WE 1997021300228 19970213 00228 WP 1997 2 13 CHIR823C 1 19961231 G 6420 369D2170721 BEARING 369D21610503 HUGHES 369 369E 4470707 WP T/R YOKE DISBOND B CHIR K NONE O OTHER IN INSP/MAINT 1 NM 09 1611W 1155 W39420862 0319E DURING 300-HOUR INSPECTION, ONE OF THE OUTBOARD ELASTOMERIC BEARINGS FELL OUT WHEN THE T/R ASSY WAS DISASSEMBLED. THE G LUE BOND HAD FAILED. THERE SEEMED TO BE ONLY A SMALL AMOUNT OF GLUE. SOR SENT TO MDHC 12-30-96 ON THIS PART/PROBLEM. (X) 1 G 7 1 3U H3WE 1999040200485 19990402 00485 SW 1999 4 2 CZMA061341 1 19960112 G 6710 4061300 SWITCH BELL 412 412 1182202 SW CYCLIC STUCK E CZMA K NONE O OTHER IN INSP/MAINT 1 SO 03 911BE 2471 36018 PILOT'S CYCLIC TRIGGER SWITCH STICKING IN THE ICS POSITION. REPLACED DEFECTIVE SWITCH. 1 G 7 2 4U H4SW 1999040200486 19990402 00486 SW 1999 4 2 CZMA061343 1 19960919 G 6220 212060823105 BAFFLE BELL 412 412 1182202 SW DEBRIS SCREEN DEFECTIVE E CZMA K NONE O OTHER IN INSP/MAINT 1 SO 03 911BE 3015 36018 CREDIT FOR REPLACEMENT PART REPLACED PART WITH NEW FROM BHT. 1 G 7 2 4U H4SW 1996030100231 19960301 00231 NM 1996 3 1 DP2R5836 1 19960117 G 5330 AIRFRAME CROWN BOEING 727 72723 1384004 NM BS 751-950 DELAMINATED B DP2R K NONE O OTHER IN INSP/MAINT 1 SW 05 1985 72148 18441 AD 90-20-18. AIRFRAME CROWN DELAMINATION NOTED AS FOLLOWS: BS 950, STR 1. BS 950, STR 2R. BS 950, STR 3R. BS 751, S TR 8-10 LT AND RT. BS 775, STR 8-10 LT AND RT. BS 825, STR 8-10 LT AND RT. BS 850, STR 8-10, LT AND RT. (X) 2 L 7 3 4F A3WE 1996022300728 19960223 00728 EU 1996 2 23 DP2R5889 1 19960117 G 5313 STRINGER BAC 111 111203AE 1480208 EU GS 236 STR 23R CRACKS B DP2R K NONE O OTHER IN INSP/MAINT 1 SW 05 1543 017 AD 83-15-08 R1 FOUND STRINGER CRACKED. BS 236 STR 23R, .080 INCH LINEAR INDICATION. BS 500, STR 23R, 2 EACH LINEAR IND ICATIONS, EACH .300 INCH LENGTH. (X) 2 L 7 2 4F A5EU 1997112600255 19971126 00255 GL 1997 11 26 EY2R9600001 3 19960101 G 6114 C4206C55 HUB BEECH 55 9555 1152702 CE MCAULY 2AF34C 2AF34C55 GL THREAD AREA CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 722170 PROP CRACKED IN HUB THREAD AREA 1 L 7 2 3O 3A16 5 C P5EA 1997112600256 19971126 00256 GL 1997 11 26 EY2R9600002 3 19960101 G 6114 C5480C66 HUB CESSNA 180 180 2072602 CE MCAULY 3AF34C 3AF34C* GL NR 2 SOCKET CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 727893 HUB CRACKED IN NR2 BLADE SOCKET 1 H 7 1 3O NC 5A6 5 C P22EA 1997112600257 19971126 00257 GL 1997 11 26 EY2R9600003 3 19960101 G 6114 D7027C87 HUB CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROP CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 780071 PROP HUB CRACKED 1 L 7 2 3O 3A10 5 C P22EA 1997112600258 19971126 00258 GL 1997 11 26 EY2R9600004 3 19960101 G 6114 C3475 NUT CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL HUB CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 760917 PROP HUB NUT CRACKED 1 L 7 2 3O RT 3A10 5 C P22EA 1997112600259 19971126 00259 GL 1997 11 26 EY2R9600005 3 19960101 G 6114 D7015C87 HUB CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL NR 3 SOCKET CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 784126 PROP HUB CRACKED NR3 SOCKET 1 L 7 2 3O 3A10 5 C P22EA 1997112600260 19971126 00260 GL 1997 11 26 EY2R9600006 3 19960101 G 6114 C4451 FERRULE CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL HUB CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 782680 PROP CRACKED IN FERULE BEARING AREA 1 L 7 2 3O RT A7CE 5 C P22EA 1997112600261 19971126 00261 GL 1997 11 26 EY2R9600007 3 19960101 G 6110 C5304 SPRING HOUSING CESSNA 208 208B 2073701 CE MCAULY 3AF34C 3GFR34C703 GL PROP ASSY CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3797 840997 SPRING HOUSING CRACKED 1 H 7 1 3T A37CE 5 C P60GL 1997112600262 19971126 00262 GL 1997 11 26 EY2R9600008 3 19960101 G 6114 C4716C98 HUB CESSNA 188 188CESSNA 2073002 CE MCAULY 2A34C D2A34C98 GL NR 2 SOCKET CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 747975 NR 2 BLADE SOCKET CRACKED 1 L 7 1 3O A9CE 5 C P3EA 1997112600263 19971126 00263 GL 1997 11 26 EY2R9600009 3 19960101 G 6111 S82NC2 BLADE CESSNA 310 310Q 2074242 CE MCAULY 3AF32C D3AF32C80 GL THREAD AREA CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BLADE SN K66887YS, CRACKED IN THREAD AREA 1 L 7 2 3O 3A10 5 C P22EA 1997112600264 19971126 00264 GL 1997 11 26 EY2R9600010 3 19960101 G 6111 13019S CLAMP SWRNGN SA226 SA226AT 8780405 SW HARTZL HCB3T HCB3TN5 GL BLADE CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 668 BV2031 CLAMP CRACKED IN THE INBOARD RADIUS 2 L 7 2 4T RT A5SW 6 C P15EA 1997112600265 19971126 00265 GL 1997 11 26 EY2R9600011 3 19960101 G 6110 1851T BEARING MTSBSI MU2 MU2* SW HARTZL HCB3T HCB3TN5 GL PROP CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BV1423 PROP ASSY BEARING CRACKED 1 H 7 2 3T A2PC 6 C P15EA 1997112600266 19971126 00266 GL 1997 11 26 EY2R9600012 3 19960101 G 6110 1851T BEARING BEECH 18 18* CE HARTZL HCB3T HCB3TN5 GL PROP CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BV811 PROP ASSY BEARING CRACKED 1 L 7 2 3R A765 6 C P15EA 1997112600267 19971126 00267 GL 1997 11 26 EY2R9600013 3 19960101 G 6111 15941 FEATHER SPRING BEECH 95 95B55 1152729 CE HARTZL HCC2Y HCC2YF2 GL PROP CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 AN263 PROP ASSY FEATHERING SPRING CRACKED 1 L 7 2 3O RT 3A16 5 C P920 1997112600268 19971126 00268 GL 1997 11 26 EY2R9600014 3 19960101 G 6111 FJC7666A BLADE PIPER PA34 PA34200 7103405 SO HARTZL HCC2Y HCC2YK2 GL BUTT AREA CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 AU3182 BLADE SN C43336, CRACKED IN BUTT AREA 1 L 7 2 3O A7SO 5 C P920 1997112600269 19971126 00269 GL 1997 11 26 EY2R9600015 3 19960201 G 6110 FIX PITCH CESSNA 150 152 2071835 CE MCAULY 1A103 1A103TCM GL NR 1 MT HOLE CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 RP773425 NR 1 MOUNTING HOLE 1 H 7 1 3O NT 3A19 5 N P50GL 1997112600270 19971126 00270 GL 1997 11 26 EY2R9600016 3 19960201 G 6114 D7015C87 HUB CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL ROD HOLE CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 687544 HUB PISTON ROD HOLE CRACKED 1 L 7 2 3O RT 3A10 5 C P22EA 1997112600271 19971126 00271 GL 1997 11 26 EY2R9600017 3 19960201 G 6114 D7015C87 HUB CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL NR 1 SOCKET CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 791237 HUB HAS CRACKED IN NR1 & 3 SOCKETS 1 L 7 2 3O RT 3A10 5 C P22EA 1997120300014 19971203 00014 GL 1997 12 3 EY2R9600018 3 19960201 G 6114 D7015C87 HUB CESSNA 340 340CESSNA 2076404 CE MCAULY 3AF32C 3AF32C87 GL THREADS CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 773157 HUB CRACKED IN THREADS 1 L 7 2 3O 3A25 5 C P22EA 1997112600272 19971126 00272 1997 11 26 EY2R9600019 4 19960201 G 6113 22835 BULKHEAD BEECH 95 95B55 1152729 CE HARTZL HCC2Y BHCC2YF2 GL HUB CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3932 AN3034 BULKHEAD CRACKED IN HUB BOLT HOLES 1 L 7 2 3O RT 3A16 5 C P920 1997112600273 19971126 00273 GL 1997 11 26 EY2R9600020 3 19960201 G 6114 C4716C98 HUB CESSNA 188 188CESSNA 2073002 CE MCAULY 2A34C D2A34C98 GL PROP CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 780880 PROP HUB CRACKED 1 L 7 1 3O A9CE 5 C P3EA 1997120400064 19971204 00064 1997 12 4 EY2R9600021 4 19960201 G 6113 3064 BULKHEAD BEECH 100 100BEECH 1152916 CE HARTZL HCB3T HCB3TN3 GL PROP CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1322 BU2699 INSPECTION FOUND THE PROP BULKHEAD CRACKED 1 L 7 2 3T A14CE 6 C P15EA 1997120400065 19971204 00065 GL 1997 12 4 EY2R9600022 3 19960201 G 6114 5976 CUP BEECH 100 100BEECH 1152916 CE HARTZL HCB3T HCB3TN3 GL SPRING RETAINER CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1322 BU2699 INSP FOUND PROP SPRING RETAINER CUP CRACKED 1 L 7 2 3T A14CE 6 C P15EA 1997120400066 19971204 00066 GL 1997 12 4 EY2R9600023 3 19960201 G 6114 5976 CUP BEECH 100 100BEECH 1152916 CE HARTZL HCB3T HCB3TN3 GL SPRING RETAINER CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2053 BU4223 INSP FOUND PROP SPRING RETAINER CUP CRACKED 1 L 7 2 3T A14CE 6 C P15EA 1997120400067 19971204 00067 GL 1997 12 4 EY2R9600024 3 19960201 G 6114 18912A PILOT TUBE PIPER PA31T PA31T 7103124 SO HARTZL HCB3T HCB3TN3 GL PROP CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BU3995 INSP FOUND PROP PILOT TUBE CRACKED 1 L 7 2 3T A8EA 6 C P15EA 1997120400068 19971204 00068 GL 1997 12 4 EY2R9600025 3 19960201 G 6114 18916 PILOT TUBE PIPER PA31T PA31T 7103124 SO HARTZL HCB3T HCB3TN3 GL PROP CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BU3996 INSP FOUND PROP PILOT TUBE CRACKED 1 L 7 2 3T A8EA 6 C P15EA 1997120400069 19971204 00069 GL 1997 12 4 EY2R9600026 3 19960201 G 6111 13019S CLAMP MTSBSI MU2 MU2* SW HARTZL HCB3T HCB3TN5 GL PROP CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BU2089 INSP FOUND PROP CLAMP CRACKED 1 H 7 2 3T A2PC 6 C P15EA 1997120400070 19971204 00070 GL 1997 12 4 EY2R9600027 3 19960201 G 6114 1891 PILOT TUBE MTSBSI MU2 MU2* SW HARTZL HCB3T HCB3TN5 GL PROP CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BU2089 PILOT TUBE HAS LONGITUDINAL CRACKS 1 H 7 2 3T A2PC 6 C P15EA 1997120400071 19971204 00071 GL 1997 12 4 EY2R9600028 3 19960201 G 6110 1901 LINK ARM MTSBSI MU2 MU2* SW HARTZL HCB3T HCB3TN5 GL PROP CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BU2089 INSP FOUND PROP LINK ARM CRACKED 1 H 7 2 3T A2PC 6 C P15EA 1997120400072 19971204 00072 GL 1997 12 4 EY2R9600029 3 19960201 G 6110 30283 BRACKET MTSBSI MU2 MU2* SW HARTZL HCB3T HCB3TN5 GL PROP HIGH STOP CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BU2120 INSP FOUND HIGH STOP BRACKET CRACKED 1 H 7 2 3T A2PC 6 C P15EA 1997120400073 19971204 00073 GL 1997 12 4 EY2R9600030 3 19960201 G 6110 3252 FORK GULSTM 500 500S 0141107 SW HARTZL HCC3Y HCC3YR GL PITCH CONTROL CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 CK1256 PC FORK CRACKED IN RADIUS WHERE BLOCK SEATS 1 H 7 2 3O 6A1 5 C P25EA 1997120400074 19971204 00074 GL 1997 12 4 EY2R9600031 3 19960301 G 6114 C6447C23 HUB BEECH 35 V35 1151538 CE MCAULY 2A36C 2A36C23 GL PROP CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 644421 HUB CRACKED IN THREAD AREA 1 L 7 1 3O 3A15 5 C P880 1997120400075 19971204 00075 GL 1997 12 4 EY2R9600032 3 19960301 G 6114 D7015C87 HUB CESSNA 402 402CESSNA 207590K CE MCAULY 3AF32C 3AF32C87 GL PROP CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 804599 HUB OUTER SURFACE CRACKED 1 L 7 2 3O A7CE 5 C P22EA 1997120400076 19971204 00076 GL 1997 12 4 EY2R9600033 3 19960301 G 6114 D7015C93 HUB CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROP CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 737636 PILOT BORE FOR CRANKSHAFT CRACKED 1 L 7 2 3O RT A7CE 5 C P22EA 1997120400077 19971204 00077 GL 1997 12 4 EY2R9600034 3 19960301 G 6114 D5970C58 HUB CESSNA 182 182E 2072712 CE MCAULY 2A34C D2A34C58 GL NR 1 SOCKET CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 780308 HUB CRACKED IN NR 1 SOCKET 1 H 7 1 3O NT 3A13 5 C P3EA 1997120400078 19971204 00078 GL 1997 12 4 EY2R9600035 3 19960301 G 6114 C4716C98 HUB CESSNA 188 188CESSNA 2073002 CE MCAULY 2A34C D2A34C98 GL NR 1 SOCKET CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 734660 HUB CRACKED IN NR1 SOCKET 1 L 7 1 3O A9CE 5 C P3EA 1997120400079 19971204 00079 GL 1997 12 4 EY2R9600036 3 19960301 G 6114 C4716C98 HUB CESSNA 188 188CESSNA 2073002 CE MCAULY 2A34C D2A34C98 GL NR 1 SOCKET CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 754218 HUB CRACKED IN NR 1 SOCKET 1 L 7 1 3O A9CE 5 C P3EA 1997120400080 19971204 00080 GL 1997 12 4 EY2R9600037 3 19960301 G 6114 C4716C98 HUB CESSNA 188 188CESSNA 2073002 CE MCAULY 2A34C D2A34C98 GL NR 1 SOCKET CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 803791 HUB CRACKED IN NR 1 SOCKET 1 L 7 1 3O A9CE 5 C P3EA 1997120400081 19971204 00081 GL 1997 12 4 EY2R9600038 3 19960301 G 6114 C4716C98 HUB CESSNA 188 188CESSNA 2073002 CE MCAULY 2A34C D2A34C98 GL NR 2 SOCKET CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 821935 HUB CRACKED IN NR2 SOCKET, 7 O'CLOCK POSITION 1 L 7 1 3O A9CE 5 C P3EA 1997120400082 19971204 00082 GL 1997 12 4 EY2R9600039 3 19960301 G 6114 D5904C90 HUB CESSNA 206 206CESSNA 2073302 CE MCAULY 3A32C D3A32C90 GL PROP CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 870996 INSP FOUND HUB CRACKED 1 H 7 1 3O A4CE 5 C P21EA 1997120400083 19971204 00083 GL 1997 12 4 EY2R9600040 3 19960301 G 6114 D7037C80 HUB MCAULY 3AF32C D3AF32C80 GL PROP CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 681261 HUB SOCKET CRACKED 5 C P22EA 1997120400084 19971204 00084 GL 1997 12 4 EY2R9600041 3 19960301 G 6114 D7037C80 HUB CESSNA 210 210K 2073446 CE MCAULY 3AF32C D3AF32C80 GL BLADE SOCKET CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 681261 HUB CRACKED IN BLADE SOCKET 1 H 7 1 3O 3A21 5 C P22EA 1997120400085 19971204 00085 GL 1997 12 4 EY2R9600042 3 19960301 G 6114 D5347C73 HUB CESSNA 210 210K 2073446 CE MCAULY 2A34C E2A34C73 GL NR 1 SOCKET CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 764788 HUB CRACKED IN NR 1 SOCKET 1 H 7 1 3O 3A21 5 C P3EA9 1997120400086 19971204 00086 GL 1997 12 4 EY2R9600043 3 19960301 G 6111 8433A4 BLADE GULSTM 500 500RKWELL 0141102 SW HARTZL HCA3V HCA3VK2 GL SHOULDER AREA CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BLADE SN B29226, CRACKED IN SHOULDER AREA 1 H 7 2 3O 6A1 5 C P6EA 1997120400087 19971204 00087 GL 1997 12 4 EY2R9600044 3 19960401 G 6114 C2835C23 HUB BEECH 36 36BEECH 1151602 CE MCAULY 2A36C 2A36C23 GL PROP CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 735725 INSP FOUND HUB CRACKED 1 L 7 1 3O 3A15 5 C P880 1997120400088 19971204 00088 GL 1997 12 4 EY2R9600045 3 19960401 G 6114 C6447C23 HUB BEECH 35 V35 1151538 CE MCAULY 2A36C 2A36C23 GL PROP CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 760424 INSP FOUND HUB CRACKED 1 L 7 1 3O 3A15 5 C P880 1997120400089 19971204 00089 GL 1997 12 4 EY2R9600046 3 19960401 G 6114 D4883C55 HUB BEECH 95 95B55 1152729 CE MCAULY 2AF34C 2AF34C55 GL NR 2 SOCKET CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 695706 HUB CRACKED IN NR 2 SOCKET 1 L 7 2 3O RT 3A16 5 C P5EA 1997120400090 19971204 00090 GL 1997 12 4 EY2R9600047 3 19960401 G 6114 D4883C55 HUB BEECH 95 95B55 1152729 CE MCAULY 2AF34C 2AF34C55 GL NR 2 SOCKET CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 785046 HUB CRACKED IN NR 2 SOCKET 1 L 7 2 3O RT 3A16 5 C P5EA 1997120400091 19971204 00091 GL 1997 12 4 EY2R9600048 3 19960401 G 6114 D7015C87 HUB CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROP CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 712253 INSP FOUND HUB CRACKED 1 L 7 2 3O 3A10 5 C P22EA 1997120400092 19971204 00092 GL 1997 12 4 EY2R9600049 3 19960401 G 6110 C3475 NUT CESSNA 402 402CESSNA 207590K CE MCAULY 3AF32C 3AF32C87 GL PROP CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 PROP ASSY NUT CRACKED IN THREAD AREA 1 L 7 2 3O A7CE 5 C P22EA 1997120400093 19971204 00093 GL 1997 12 4 EY2R9600050 3 19960401 G 6114 D7019C92 HUB CESSNA 421 421B 2076014 CE MCAULY 3AF34C 3AF34C92 GL PROP CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 694040 INSP FOUND PROP HUB CRACKED 1 L 7 2 3O A7CE 5 C P22EA 1997121100133 19971211 00133 GL 1997 12 11 EY2R9600051 3 19960401 G 6110 2202 SPLIT BEARING PIPER PA23 PA23250 7102308 SO HARTZL HCE2Y HCE2YR2 GL PROP ASSY CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BP9080 PROP ASSY HAS A CRACKED SPLIT BEARING 1 L 7 2 3O 1A10 5 C P9EA 1997121100134 19971211 00134 GL 1997 12 11 EY2R9600052 3 19960401 G 6110 15921 SPRING RETAINER BEECH 58 58P 1152744 CE HARTZL HCJ3Y PHCJ3YF2 GL PROP ASSY CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 ED796 PROP ASSY HAS A CRACKED SPRING RETAINER 1 L 7 2 3O A23CE 5 C P36EA 1997121100135 19971211 00135 GL 1997 12 11 EY2R9600053 3 19960401 G 6110 32532 PITCH CHANGE BLK BEECH 58 58P 1152744 CE HARTZL HCJ3Y PHCJ3YF2 GL PROP ASSY CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 4833 1698 ED2833 PROP ASSY HAS A PITCH CHANGE BLOCK CRACKED 1 L 7 2 3O A23CE 5 C P36EA 1997121100136 19971211 00136 GL 1997 12 11 EY2R9600054 3 19960501 G 6114 C4211C76 HUB BEECH 35 35BEECH 1151502 CE MCAULY 3A32C 3A32C76 GL SOCKET CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 752887 HUB BLADE SOCKET CRACKED 1 L 7 1 3O A777 5 C P21EA 1997121100137 19971211 00137 GL 1997 12 11 EY2R9600055 3 19960501 G 6114 D7015C87 HUB CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL THREAD AREA CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 721934 HUB CRACKED IN THREAD AREA 1 L 7 2 3O RT 3A10 5 C P22EA 1997121100138 19971211 00138 GL 1997 12 11 EY2R9600056 3 19960501 G 6111 S82NC55 BLADE CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL THREADS CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BLADE SN F651YS, THREADS CRACKED 1 L 7 2 3O RT 3A10 5 C P22EA 1997121100139 19971211 00139 GL 1997 12 11 EY2R9600057 3 19960501 G 6114 D7015C87 HUB CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL NR 1 SOCKET CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 799116 HUB CRACKED IN NR1 SOCKET 1 L 7 2 3O RT 3A10 5 C P22EA 1997121100140 19971211 00140 GL 1997 12 11 EY2R9600058 3 19960501 G 6111 S82NC55 BLADE CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROP ASSY CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 790630 BLADE SN K92082YS CRACKED 1 L 7 2 3O RT A7CE 5 C P22EA 1997121100141 19971211 00141 GL 1997 12 11 EY2R9600059 3 19960501 G 6111 C4451 FERRULE CESSNA 414 414A 2075907 CE MCAULY 3AF32C 3AF32C93 GL PROP ASSY CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 794518 PROP ASSY BLADE FERRULE CRACKED 1 L 7 2 3O A7CE 5 C P22EA 1997121100142 19971211 00142 GL 1997 12 11 EY2R9600060 3 19960501 G 6114 D5894C92 HUB CESSNA 421 421 2076010 CE MCAULY 3AF34C 3AF34C92 GL RETAIN THREADS CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 739542 HUB CRACKED IN RETENTION THREADS 1 L 7 2 3O RT A7CE 5 C P22EA 1997121100143 19971211 00143 GL 1997 12 11 EY2R9600061 3 19960501 G 6114 D5894C92 HUB CESSNA 421 421 2076010 CE MCAULY 3AF34C 3AF34C92 GL RETAIN THREADS CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 751875 HUB CRACKED IN RETENTION THREADS 1 L 7 2 3O RT A7CE 5 C P22EA 1997121100144 19971211 00144 GL 1997 12 11 EY2R9600062 3 19960501 G 6114 C4716C203 HUB CESSNA 188 188CESSNA 2073002 CE MCAULY 2A34C D2A34C98 GL NR 2 SOCKET CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 762755 HUB CRACKED IN NR2 SOCKET 1 L 7 1 3O A9CE 5 C P3EA 1997121100145 19971211 00145 GL 1997 12 11 EY2R9600063 3 19960501 G 6111 C4902 NUT CESSNA 188 188CESSNA 2073002 CE MCAULY 2A34C D2A34C98 GL BLADE CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 762755 BLADE NUT CRACKED 1 L 7 1 3O A9CE 5 C P3EA 1997121100146 19971211 00146 GL 1997 12 11 EY2R9600064 3 19960501 G 6114 D4887C81 HUB CESSNA 310 310J 2074226 CE MCAULY 2AF34C D2AF34C81 GL PROP ASSY CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 663578 PROP ASSY HUB CRACKED 1 L 7 2 3O 3A10 5 C P5EA 1997121100147 19971211 00147 GL 1997 12 11 EY2R9600065 3 19960501 G 6114 D7037C80 HUB CESSNA 310 310Q 2074242 CE MCAULY 3AF32C D3AF32C80 GL NR 1 SOCKET CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 681261 HUB CRACKED IN NR 1 SOCKET 1 L 7 2 3O 3A10 5 C P22EA 1997122900009 19971229 00009 GL 1997 12 29 EY2R9600066 3 19960501 G 6110 1977P CLAMP DHAV DHC2 DHC2* 2800108 EA HARTZL HCB3R HCB3R302 GL PROP ASSY CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2037 1065N PROP ASSY CLAMP CRACKED 1 H 7 1 3R A806 5 C P28EA 1997122900010 19971229 00010 GL 1997 12 29 EY2R9600067 3 19960501 G 6110 5244 PROPELLER BEECH 58 58P 1152744 CE HARTZL HCCA3A PHCA3VF5 GL HUB ASSY CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 DH20 PROP ASSY P/N 5244 IS CRACKED 1 L 7 2 3O A23CE 5 C P6EA 1997122900011 19971229 00011 GL 1997 12 29 EY2R9600068 3 19960501 G 6110 5244 PROPELLER BEECH 58 58P 1152744 CE HARTZL HCCA3A PHCA3VF5 GL HUB ASSY CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 DH21 PROPELLER ASSY P/N 5244 IS CRACKED 1 L 7 2 3O A23CE 5 C P6EA 1997121100148 19971211 00148 GL 1997 12 11 EY2R9600069 3 19960601 G 6114 D7015C87 HUB CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL SOCKETS CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 774447 HUB ASSY HAS ALL THREE SOCKETS CRACKED 1 L 7 2 3O RT 3A10 5 C P22EA 1997121100149 19971211 00149 GL 1997 12 11 EY2R9600070 3 19960601 G 6114 C3550 FEATHER CYLINDER CESSNA 340 340CESSNA 2076404 CE MCAULY 3AF32C 3AF32C93 GL HUB CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 755780 FEATHER CYLINDER SCREW HOLES CRACKED 1 L 7 2 3O 3A25 5 C P22EA 1997121100150 19971211 00150 GL 1997 12 11 EY2R9600071 3 19960601 G 6114 D7019C92 HUB CESSNA 421 421 2076010 CE MCAULY 3AF34C 3AF34C92 GL PROPELLER CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1642 805941 HUB ASSY CRACKED 1 L 7 2 3O RT A7CE 5 C P22EA 1997121100151 19971211 00151 GL 1997 12 11 EY2R9600072 3 19960601 G 6114 C4716C98 HUB CESSNA 188 188B 2073007 CE MCAULY 2A34C D2A34C98 GL THREAD AREA CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2666 1333 890754 HUB CRACKED IN THREAD AREA 1 L 7 1 3O A9CE 5 C P3EA 1997121100152 19971211 00152 GL 1997 12 11 EY2R9600073 3 19960601 G 6114 D5347C73 HUB BELL 206 206B 1181511 SW MCAULY 2A34C E2A34C73 GL PROPELLER CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1187 850614 HUB ASSY CRACKED 1 G 7 1 3U H2SW 5 C P3EA9 1997121100153 19971211 00153 GL 1997 12 11 EY2R9600074 3 19960601 G 6111 13019S CLAMP DHAV DHC3 DHC3 2800202 EA HARTZL HCB3T HCB3TN3 GL PROP ASSY CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 11412 PROP ASSY BLADE CLAMP CRACKED 1 H 7 1 3R A815 6 C P15EA 1997121100154 19971211 00154 GL 1997 12 11 EY2R9600075 3 19960601 G 6110 18912A PILOT TUBE BEECH 100 100BEECH 1152916 CE HARTZL HCB3T HCB3TN3 GL PROPELLER CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2018 BU13373 PROPELLER ASSY PILOT TUBE CRACKED 1 L 7 2 3T A14CE 6 C P15EA 1997121100431 19971211 00431 GL 1997 12 11 EY2R9600076 3 19960601 G 6110 18912A PILOT TUBE DHAV DHC3 DHC3 2800202 EA HARTZL HCB3T HCB3TN3 GL PROP CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BU8685 PROP PILOT TUBE HAS 3" CRACK 1 H 7 1 3R A815 6 C P15EA 1997121100432 19971211 00432 GL 1997 12 11 EY2R9600077 3 19960601 G 6110 18916A PILOT TUBE DHAV DHC3 DHC3 2800202 EA HARTZL HCB3T HCB3TN3 GL PROP CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BU8685 PROP PILOT TUBE CRACKED 1 H 7 1 3R A815 6 C P15EA 1997121100433 19971211 00433 GL 1997 12 11 EY2R9600078 3 19960601 G 6111 T101731 BLADE DHAV DHC3 DHC3 2800202 EA HARTZL HCB3T HCB3TN3 GL SHANK CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BU8685 PROP BLADE SHANK SN 636978, IS CRACKED 1 H 7 1 3R A815 6 C P15EA 1997121100434 19971211 00434 GL 1997 12 11 EY2R9600079 3 19960601 G 6111 T10282H BLADE DHAV DHC6 DHC6300 EA HARTZL HCB3T HCB3TN3 GL PROP LE CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 6770 896 BU13800 HARD ALLOY BLADES CRACKED IN L.E. 1 H 7 2 3T A9EA 6 C P15EA 1997121100435 19971211 00435 GL 1997 12 11 EY2R9600080 3 19960601 G 6111 T10282H BLADE DHAV DHC6 DHC6300 EA HARTZL HCB3T HCB3TN3 GL PROP CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 6770 896 BU13800 BLADE CRACKED. REWORKED, SN C69741 1 H 7 2 3T A9EA 6 C P15EA 1997121100436 19971211 00436 GL 1997 12 11 EY2R9600081 3 19960601 G 6111 T10282H BLADE DHAV DHC6 DHC6300 EA HARTZL HCB3T HCB3TN3 GL PROP CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 6770 896 BU13800 PROP BLADE CRACKED. REWORKED, SN C69640 1 H 7 2 3T A9EA 6 C P15EA 1997121100437 19971211 00437 GL 1997 12 11 EY2R9600082 3 19960601 G 6111 T10282H BLADE DHAV DHC6 DHC6300 EA HARTZL HCB3T HCB3TN3 GL PROP CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 6770 896 BU13800 PROP BLADE CRACKED. REWORKED, SN C55993 1 H 7 2 3T A9EA 6 C P15EA 1997121100438 19971211 00438 GL 1997 12 11 EY2R9600083 3 19960601 G 6114 3493 STOP MTSBSI MU2 MU2* SW HARTZL HCB4T HCB4TN3 GL HIGH PITCH CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 100 HUB HIGH PITCH STOP BROKEN 1 H 7 2 3T A2PC 6 C P40EA 1997121100439 19971211 00439 GL 1997 12 11 EY2R9600084 3 19960601 G 6111 F8475D4 BLADE PIPER PA32 PA32300 7103212 SO HARTZL HCC2Y HCC2YK1 GL PROP CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 456 CH7205 BLADE SN D11148, FLANGES CRACKED 1 L 7 1 3O A3SO 5 C P920 1997121100440 19971211 00440 GL 1997 12 11 EY2R9600085 3 19960601 G 6111 F8475D4 BLADE PIPER PA32 PA32300 7103212 SO HARTZL HCC2Y HCC2YK1 GL PROP CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 456 CH7205 BLADE SN D3698, FLANGES CRACKED 1 L 7 1 3O A3SO 5 C P920 1997121100441 19971211 00441 GL 1997 12 11 EY2R9600086 3 19960601 G 6110 24182 PISTON ROD PIPER PA24 PA24400 7102408 SO HARTZL HCC2Y HCC2YK1 GL PROP CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 4550 CH2967 PROP PISTON ROD CRACKED 1 L 7 1 3O 1A15 5 C P920 1997121100442 19971211 00442 GL 1997 12 11 EY2R9600087 3 19960601 G 6114 24573 FORK PIPER PA24 PA24400 7102408 SO HARTZL HCC2Y HCC2YK1 GL PITCH CHANGE CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 CH2967 PROP PITCH CHANGE FORK CRACKED 1 L 7 1 3O 1A15 5 C P920 1997121100443 19971211 00443 GL 1997 12 11 EY2R9600088 3 19960601 G 6111 F7666A2 BLADE PIPER PA28 PA28R200 7102811 SO HARTZL HCC2Y HCC2YK1 GL PROP CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 CH11897 BLADE SN H60744, FLANGE CRACKED 1 L 7 1 3O 2A13 5 C P920 1997121100444 19971211 00444 GL 1997 12 11 EY2R9600089 3 19960701 G 6114 C4239C23 HUB BEECH 35 V35 1151538 CE MCAULY 2A36C 2A36C23 GL THREAD AREA CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 711435 HUB CRACKED IN THREAD AREA 1 L 7 1 3O 3A15 5 C P880 1997121100445 19971211 00445 GL 1997 12 11 EY2R9600090 3 19960701 G 6114 C4239C23 HUB BEECH 33 3533 1151402 CE MCAULY 2A36C 2A36C23 GL PROP CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 744502 HUB CRACKED 1 L 7 1 3O 3A15 5 C P880 1997121100446 19971211 00446 GL 1997 12 11 EY2R9600091 3 19960701 G 6114 C4239C23 HUB BEECH 33 3533 1151402 CE MCAULY 2A36C 2A36C23 GL PROP CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 774507 HUB CRACKED IN THREAD AREA 1 L 7 1 3O 3A15 5 C P880 1997121100447 19971211 00447 GL 1997 12 11 EY2R9600092 3 19960701 G 6114 C4206C55 HUB BEECH 58 58 1152740 CE MCAULY 2AF34C 2AF34C55 GL SOCKET CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 723821 HUB CRACKED IN BOTH BLADE SOCKETS 1 L 7 2 3O 3A16 5 C P5EA 1997121100448 19971211 00448 GL 1997 12 11 EY2R9600093 3 19960701 G 6114 D5892C75 HUB BEECH 55 9555 1152702 CE MCAULY 3AF32C 3AF32C75 GL THREAD AREA CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 696160 HUB CRACKED IN THREAD AREA 1 L 7 2 3O 3A16 5 C P22EA 1997122900019 19971229 00019 GL 1997 12 29 EY2R9600094 3 19960701 G 6114 D7015C75 HUB BEECH 55 9555 1152702 CE MCAULY 3AF32C 3AF32C75 GL PROP CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 696160 HUB CRACKED 1 L 7 2 3O 3A16 5 C P22EA 1997121100449 19971211 00449 GL 1997 12 11 EY2R9600095 3 19960701 G 6114 D7015C87 HUB CESSNA 401 401 207590C CE MCAULY 3AF32C 3AF32C87 GL THREAD AREA CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 7911101 HUB CRACKED IN THREAD AREA 1 L 7 2 3O A7CE 5 C P22EA 1997121100450 19971211 00450 GL 1997 12 11 EY2R9600096 3 19960701 G 6114 D5892C87 HUB CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROP CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3348 573 733241 HUB CRACKED 1 L 7 2 3O 3A10 5 C P22EA 1997121100451 19971211 00451 GL 1997 12 11 EY2R9600097 3 19960701 G 6114 D5892C87 HUB CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROP CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3348 573 743081 HUB CRACKED 1 L 7 2 3O 3A10 5 C P22EA 1997121100452 19971211 00452 GL 1997 12 11 EY2R9600098 3 19960701 G 6114 D7015C87 HUB CESSNA 401 401 207590C CE MCAULY 3AF32C 3AF32C87 GL NR 2 SOCKET CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 900221 HUB CRACKED IN NR 2 SOCKET 1 L 7 2 3O A7CE 5 C P22EA 1997121100453 19971211 00453 GL 1997 12 11 EY2R9600099 3 19960701 G 6114 C65HUB CESSNA 310 310 2074202 CE MCAULY 2A34C D2A34C* GL THREAD AREA CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 724508 HUB CRACKED IN THREAD AREA 1 L 7 2 3O RT 3A10 5 C P3EA 1997121100454 19971211 00454 GL 1997 12 11 EY2R9600100 3 19960701 G 6114 D4237C65 HUB CESSNA 310 310 2074202 CE MCAULY 2AF34C D2AF34C65 GL NR 2 SOCKET CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 730063 HUB CRACKED IN NR2 SOCKET 1 L 7 2 3O RT 3A10 5 C P5EA 1997121100455 19971211 00455 GL 1997 12 11 EY2R9600101 3 19960701 G 6110 3496 FEATHER SPRING BEECH 1900 1900C 1154161 CE HARTZL HCB4M HCB4MP3 GL PROP CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 18952 3058 FW264 PROP FEATHERING SPRING CRACKED 2 L 7 2 4T RT A24CE 6 C P56GL 1997121100456 19971211 00456 GL 1997 12 11 EY2R9600102 3 19960801 G 6110 C3112 RETAIN RING ADAMS A50S A55 0050103 SO MCAULY 2AF34C 2AF34C55 GL RPOP CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 695613 PROP RETAIN RING CRACKED 1 B 0 0 A15SO 5 C P5EA 1997121100457 19971211 00457 GL 1997 12 11 EY2R9600103 3 19960801 G 6114 D7015C93 HUB CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL NR 1 SOCKET CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 776628 HUB CRACKED IN NR1 SOCKET 1 L 7 2 3O RT A7CE 5 C P22EA 1997121100458 19971211 00458 GL 1997 12 11 EY2R9600104 3 19960801 G 6110 3496 FEATHER SPRING BEECH 1900 1900C 1154161 CE HARTZL HCB4M HCB4MP3 GL PROP CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 17663 4081 FW868 FEATHER SPRING CRACKED, 5 PCS., SPIRAL MARK ON FLAT EDGE 2 L 7 2 4T RT A24CE 6 C P56GL 1997121100459 19971211 00459 GL 1997 12 11 EY2R9600105 3 19960801 G 6111 FJC7666A BLADE PIPER PA34 PA34200 7103405 SO HARTZL HCC2Y HCC2YK2 GL PROP CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 157 AU7121 BLADE SN H69746, TIP BROKE OFF 12" 1 L 7 2 3O A7SO 5 C P920 1997121100460 19971211 00460 GL 1997 12 11 EY2R9600106 3 19960901 G 6114 C5480C66 HUB CESSNA 182 182P 2075816 CE MCAULY 2A34C 2A34C66 GL THREAD AREA CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 7911125 HUB CRACKED IN THREAD AREA 1 H 7 1 3O NT TA13 5 C P3EA 1997121100461 19971211 00461 GL 1997 12 11 EY2R9600107 3 19960901 G 6114 D6602C76 HUB BEECH 35 V35A 1151544 CE MCAULY 3A32C 3A32C76 GL THREAD AREA CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 676269 HUB CRACKED IN THREAD AREA 1 L 7 1 3O 3A15 5 C P21EA 1997121100462 19971211 00462 GL 1997 12 11 EY2R9600108 3 19960901 G 6114 D7027C87 HUB CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL THREAD AREA CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 798862 HUB CRACKED IN THREAD AREA 1 L 7 2 3O 3A10 5 C P22EA 1997121100463 19971211 00463 NE 1997 12 11 EY2R9600109 3 19960901 G 6111 5133 BLADE BEECH 1900 1900D 1154162 CE HARTZL HCE4A HCE4A3A NE PROP LE CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 HJ117A PROP BLADE LEADING EDGE CRACKED 2 L 7 2 4T RT A24CE 5 C P10NE 1997121100464 19971211 00464 GL 1997 12 11 EY2R9600110 3 19960901 G 6114 32517 HUB CESSNA 340 340A 2076405 CE HARTZL HCC3Y PHCC3YF2 GL PROP CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 EB2248 PROP HUB CRACKED 1 L 7 2 3O 3A25 5 C P25EA 1997121100465 19971211 00465 GL 1997 12 11 EY2R9600111 3 19960901 G 6114 FC84686R BLADE PIPER PA31 PA31 7103102 SO HARTZL HCE2Y HCE2YK2 GL PROP CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BLADE SN D70235 CRACKED 1 L 7 2 3O A20SO 5 C P9EA 1997121100466 19971211 00466 GL 1997 12 11 EY2R9600112 3 19960901 G 6114 FC84686R BLADE PIPER PA31 PA31 7103102 SO HARTZL HCE2Y HCE2YK2 GL PROP CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BLADE SN D73964 CRACKED 1 L 7 2 3O A20SO 5 C P9EA 1997121100467 19971211 00467 GL 1997 12 11 EY2R9600113 3 19960901 G 6111 FC84686R BLADE PIPER PA31 PA31 7103102 SO HARTZL HCE2Y HCE2YK2 GL PROP CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BLADE SN E45280 CRACKED 1 L 7 2 3O A20SO 5 C P9EA 1997121100468 19971211 00468 GL 1997 12 11 EY2R9600114 3 19961001 G 6110 PROPELLER CESSNA 150 152 2071835 CE MCAULY 1A103 1A103TCM GL LE BOLT HOLES CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 K771825 2 CRACKS IN LEAD EDGE BOLT HOLES 1 H 7 1 3O NT 3A19 5 N P50GL 1997121100469 19971211 00469 GL 1997 12 11 EY2R9600115 3 19961001 G 6114 D6602C76 HUB BEECH 35 V35 1151538 CE MCAULY 3A32C 3A32C76 GL THREAD AREA CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 800310 HUB CRACKED IN THREAD AREA 1 L 7 1 3O 3A15 5 C P21EA 1997122900020 19971229 00020 GL 1997 12 29 EY2R9600116 3 19961001 G 6114 D7015C87 HUB CESSNA 402 402CESSNA 207590K CE MCAULY 3AF32C 3AF32C87 GL THREAD AREA CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 687084 HUB CRACKED IN THREAD AREA 1 L 7 2 3O A7CE 5 C P22EA 1997121100470 19971211 00470 GL 1997 12 11 EY2R9600117 3 19961001 G 6111 S82NC4 BLADE CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL NR 1 SOCKET CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 789172 BLADE NR1 SOCKET CRACKED 1 L 7 2 3O RT 3A10 5 C P22EA 1997121100471 19971211 00471 GL 1997 12 11 EY2R9600118 3 19961001 G 6114 D7015C93 HUB CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL NR 1 SOCKET CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 790274 NR 1 BLADE SOCKET UNDER WELCH PLUG CRACKED 1 L 7 2 3O RT A7CE 5 C P22EA 1997122900021 19971229 00021 GL 1997 12 29 EY2R9600119 3 19961001 G 6114 C4716C58 HUB CESSNA 188 188CESSNA 2073002 CE MCAULY 2A34C D2A34C58 GL THREAD AREA CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 735820 HUB CRACKED IN THREAD AREA 1 L 7 1 3O A9CE 5 C P3EA 1997122900022 19971229 00022 GL 1997 12 29 EY2R9600120 3 19961001 G 6114 C4716C98 HUB CESSNA 188 188CESSNA 2073002 CE MCAULY 2A34C D2A34C98 GL PROP CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 902390 PROP HUB CRACKED 1 L 7 1 3O A9CE 5 C P3EA 1997121100472 19971211 00472 GL 1997 12 11 EY2R9600121 3 19961001 G 6110 1851T BEARING BEECH 90 B90 1152912 CE HARTZL HCB3T HCB3TN3 GL PROP CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BU1332 PROP ASSY BEARING CRACKED 1 L 7 2 3T 3A20 6 C P15EA 1997121100473 19971211 00473 GL 1997 12 11 EY2R9600122 3 19961001 G 6110 1891 PILOT TUBE BEECH 90 B90 1152912 CE HARTZL HCB3T HCB3TN3 GL PROP ASSY CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BU1332 PROP ASSY IS CRACKED . ALL 3 PILOT TUBES 1 L 7 2 3T 3A20 6 C P15EA 1997121100474 19971211 00474 GL 1997 12 11 EY2R9600123 3 19961001 G 6110 30283 STOP BRACKET GULSTM 690TP 690 0141720 SW HARTZL HCB3T HCB3TN5 GL PROP HIGH STOP CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BV3133 HIGH STOP BRACKET CRACKED. ALL 3 CRACKED AT PIN 1 H 7 2 3T 2A4 6 C P15EA 1997121100475 19971211 00475 GL 1997 12 11 EY2R9600124 3 19961001 G 6110 30283 STOP BRACKET GULSTM 690TP 690 0141720 SW HARTZL HCB3T HCB3TN5 GL PROP HIGH STOP CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BV3155 PROP HIGH STOP BRACKETCRACKED. ALL 3 CRACKED AT PIN 1 H 7 2 3T 2A4 6 C P15EA 1997121100476 19971211 00476 GL 1997 12 11 EY2R9600125 3 19961001 G 6110 2202 SPLIT BEARING PIPER PA32 PA32R300 7103213 SO HARTZL HCC2Y HCC2YK1 GL PROP ASSY CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3320 CH1108 PROP SPLIT BEARING CRACKED 1 L 7 1 3O A3SO 5 C P920 1997121100477 19971211 00477 GL 1997 12 11 EY2R9600126 3 19960901 G 6114 D7015C87 HUB CESSNA 340 340CESSNA 2076404 CE MCAULY 3AF32C 3AF32C87 GL PROP ASSY CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 764989 PROP HUB ASSY IS CRACKED 1 L 7 2 3O 3A25 5 C P22EA 1997121100478 19971211 00478 GL 1997 12 11 EY2R9600127 3 19960901 G 6110 2202 SPLIT BEARING PIPER PA23 PA23150 7102303 CE HARTZL HCC2Y HCC2YK2 GL PROP ASSY CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BC157 PROP ASSY SPLIT BEARING CRACKED 1 L 7 2 3O RT 1A10 5 C P920 1997122900023 19971229 00023 NE 1997 12 29 EY2R9600128 3 19961001 G 6111 AG1002 BLADE RING CVAC 240 600240D 2422660 WP HAMSTD 12D 12D40 NE PROP ASSY CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1710882 PROP SN 778365, BROKEN BLADE RING 1 L 7 2 4T RT 2L72 5 C P257 1997122900024 19971229 00024 GL 1997 12 29 EY2R9600129 3 19961001 G 6110 PFA12D19B SHEATH DHAV DHC7 DHC7* EA HAMSTD 24PF 24PF305 GL PROP ASSY CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 18628 4803 237492 PROP ASSY HAS 3 SHEATHS CRACKED 2 H 7 4 4T RT A20EA 6 C P1NE 1997121100479 19971211 00479 GL 1997 12 11 EY2R9600130 3 19961001 G 6114 C1579C18 HUB CESSNA 180 180 2072602 CE MCAULY 2A34C 2A34C* GL THREAD AREA CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 55080 HUB CRACKED IN THREADS AREA 1 H 7 1 3O NC 5A6 5 C P3EA 1997121100480 19971211 00480 GL 1997 12 11 EY2R9600131 3 19961001 G 6114 C5480C66 HUB CESSNA 180 180A 2072604 CE MCAULY 2A34C 2A34C66 GL MT FLANGE CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 791490 HUB CRACKED IN MOUNTING FLANGE 1 H 7 1 3O 5A6 5 C P3EA 1997121100481 19971211 00481 GL 1997 12 11 EY2R9600132 3 19961001 G 6114 C5480C66 HUB CESSNA 188 188CESSNA 2073002 CE MCAULY 2A34C 2A34C66 GL THREAD AREA CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 800085 HUB CRACKED IN THREADS 1 L 7 1 3O A9CE 5 C P3EA 1997121100482 19971211 00482 GL 1997 12 11 EY2R9600133 3 19961001 G 6111 C2463 NUT BEECH 36 36BEECH 1151602 CE MCAULY 2A36C 2A36C23 GL BLADE RETAIN CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 641006 BLADE RETAIN NUT CRACKED 1 L 7 1 3O 3A15 5 C P880 1997121100483 19971211 00483 GL 1997 12 11 EY2R9600134 3 19961001 G 6111 S90M8 BLADE CESSNA 182 182 2072702 CE MCAULY 2A36C 2A36C29 GL THREAD AREA CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BLADE SN A4420YS, THREAD AREA CRACKED 1 H 7 1 3O NT 3A13 5 C P880 1997121100484 19971211 00484 GL 1997 12 11 EY2R9600135 3 19961001 G 6114 C4526C29 HUB CESSNA 180 180G 2072616 CE MCAULY 2A36C 2A36C29 GL PROP ASSY CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 601681 PROP HUB ASSY CRACKED 1 H 7 1 3O 5A6 5 C P880 1997121100485 19971211 00485 GL 1997 12 11 EY2R9600136 3 19961001 G 6114 D7015C87 HUB CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL BLADE SOCKET CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 747043 HUB CRACKED IN BLADE SOCKET 1 L 7 2 3O RT 3A10 5 C P22EA 1997121100486 19971211 00486 GL 1997 12 11 EY2R9600137 3 19961001 G 6114 D5892C87 HUB CESSNA 402 402A 207590M CE MCAULY 3AF32C 3AF32C87 GL PROP ASSY CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 795594 PROP HUB ASSY CRACKED 1 L 7 2 3O A7CE 5 C P22EA 1997121100487 19971211 00487 GL 1997 12 11 EY2R9600138 3 19961001 G 6114 D7015C87 HUB CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL THREAD AREA CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 776015 HUB CRACKED IN THREADS 1 L 7 2 3O 3A10 5 C P22EA 1997121100488 19971211 00488 GL 1997 12 11 EY2R9600139 3 19961001 G 6114 D7015C87 HUB CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL NR 1 SOCKET CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 791322 HUB CRACKED IN NR1 SOCKET 1 L 7 2 3O 3A10 5 C P22EA 1997121100489 19971211 00489 GL 1997 12 11 EY2R9600140 3 19961001 G 6114 D7015C93 HUB CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL BLADE SOCKET CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 771316 HUB CRACKED IN BLADE SOCKET 1 L 7 2 3O RT A7CE 5 C P22EA 1997121100490 19971211 00490 GL 1997 12 11 EY2R9600141 3 19961001 G 6114 D7015C93 HUB CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL NR 3 SOCKET CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 795375 HUB CRACKED IN NR3 SOCKET 1 L 7 2 3O 3A25 5 C P22EA 1997121100491 19971211 00491 GL 1997 12 11 EY2R9600142 3 19961001 G 6114 C4716C58 HUB CESSNA 182 182 2072702 CE MCAULY 2A34C D2A34C58 GL PROP ASSY CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 831190 PROP ASSY HUB CRACKED 1 H 7 1 3O NT 3A13 5 C P3EA 1997121100492 19971211 00492 GL 1997 12 11 EY2R9600143 3 19961001 G 6114 C4716C58 HUB CESSNA 188 188CESSNA 2073002 CE MCAULY 2A34C D2A34C58 GL NR 2 SOCKET CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 697479 HUB CRACKED IN NR2 SOCKET 1 L 7 1 3O A9CE 5 C P3EA 1997121100493 19971211 00493 GL 1997 12 11 EY2R9600144 3 19961001 G 6114 C4716C98 HUB CESSNA 188 188CESSNA 2073002 CE MCAULY 2A34C D2A34C98 GL PROP ASSY CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 756845 RED DYE LEAK. HUB CRACKED 1 L 7 1 3O A9CE 5 C P3EA 1997121100494 19971211 00494 GL 1997 12 11 EY2R9600145 3 19961001 G 6110 C4902 NUT CESSNA 188 188CESSNA 2073002 CE MCAULY 2A34C D2A34C98 GL PROP HUB CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 756845 NUT CRACKED WITH HUB 1 L 7 1 3O A9CE 5 C P3EA 1997121100666 19971211 00666 GL 1997 12 11 EY2R9600146 3 19961001 G 6110 C1976 RETAIN NUT CESSNA 210 210 2073402 CE MCAULY 2A36C D2A36C33 GL PROP ASSY CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 61811 PROP ASSY RETAIN NUT CRACKED 1 H 7 1 3O RT 3A21 5 C P880 1997121100667 19971211 00667 GL 1997 12 11 EY2R9600147 3 19961001 G 6114 C2715C33 HUB CESSNA 210 210 2073402 CE MCAULY 2A36C D2A36C33 GL NR 1 SOCKET CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 61811 HUB CRACKED IN NR1 SOCKET 1 H 7 1 3O RT 3A21 5 C P880 1997122900032 19971229 00032 GL 1997 12 29 EY2R9600148 3 19961001 G 6114 D5904C58 HUB CESSNA 185 A185F 2072821 CE MCAULY 3A32C D3A32C90 GL THREAD AREA CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 795820 HUB CRACKED IN THREAD AREA 1 H 7 1 3O 3A24 5 C P21EA 1997122900033 19971229 00033 GL 1997 12 29 EY2R9600149 3 19961001 G 6114 SPIDER DHAV DHC2 DHC2* 2800108 EA HARTZL HCB3R HCB3R304 GL PROP HUB CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 SPIDERS CRACKED IN SPLINES OF HUB 1 H 7 1 3R A806 5 C P28EA 1997121100668 19971211 00668 GL 1997 12 11 EY2R9600150 3 19961001 G 6110 3064 BULKHEAD BEECH 100 B100 1152919 CE HARTZL HCB3T HCB3TN3 GL PROP ASSY CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 9815 1746 BU5621 PROP ASSY CRACKED BULKHEAD 1 L 7 2 4T A14CE 6 C P15EA 1997121100669 19971211 00669 GL 1997 12 11 EY2R9600151 3 19961001 G 6110 3496 FEATHER SPRING STBROS SD3 SD360 8100606 EU HARTZL HCB5M HCB5MP3 GL PROP ASSY CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 15791 4473 EV711 PROP ASSY FEATHERING SPRING BROKEN 2 H 7 2 4T A41EU 6 C P44GL 1997121100670 19971211 00670 GL 1997 12 11 EY2R9600152 3 19961001 G 6111 FL7666A2 BLADE CONAER LA4 LA4200 5110310 NE HARTZL HCC2Y HCC2YK1 GL SHANK CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BLADE SN D66432, CRACKED NEAR SHANK IN LIP 1 H 7 1 3O 1A13 5 C P920 1997121100671 19971211 00671 GL 1997 12 11 EY2R9600153 3 19961001 G 6110 2202 SPLIT BEARING PIPER PA44 PA44180T 7104404 SO HARTZL HCC2Y HCC2YK2 GL PROP ASSY CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 AU2583 PROP ASSY SPLIT BEARING CRACKED AT TOP OF RACE 1 L 7 2 3O A19SO 5 C P920 1997122900034 19971229 00034 GL 1997 12 29 EY2R9600154 3 19961001 G 6111 F8468A8R BLADE CESSNA 206 206CESSNA 2073302 CE HARTZL HCC3Y HCC3YF1 GL SHANK CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 EC117A BLADE SN H58903, CRACKED NEAR SHANK IN LIP 1 H 7 1 3O A4CE 5 C P25EA 1997121100672 19971211 00672 GL 1997 12 11 EY2R9600155 3 19961001 G 6110 2202 SPLIT BEARING PIPER PA23 PA23250 7102308 SO HARTZL HCE2Y HCE2YR2 GL PROP ASSY CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BP7307 PROP ASSY SPLIT BEARING CRACKED 1 L 7 2 3O 1A10 5 C P9EA 1997121100673 19971211 00673 NE 1997 12 11 EY2R9600156 3 19961001 G 6111 5133 BLADE BEECH 1900 1900D 1154162 CE HARTZL HCE4A HCE4A3A NE PROP LE CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 5420 HJ297 BLADE CRACKED LEADING EDGE 2 L 7 2 4T RT A24CE 5 C P10NE 1997121100674 19971211 00674 CE 1997 12 11 EY2R9600157 3 19961101 G 6111 2153192 BEARING BEECH 35 D35 1151510 CE BEECH 215 215* CE BLADE CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 4959 BLADE BEARING RACE CRACKED 1 L 7 1 3O A777 5 C P873 1997121100675 19971211 00675 GL 1997 12 11 EY2R9600158 3 19961101 G 6114 D5892C87 HUB CESSNA 402 402B 207590P CE MCAULY 3AF32C 3AF32C87 GL PROP ASSY CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 702046 PROP HUB ASSY CRACKED 1 L 7 2 3O A7CE 5 C P22EA 1997121100676 19971211 00676 GL 1997 12 11 EY2R9600159 3 19961101 G 6114 D5892C93 HUB CESSNA 402 402C 207590R CE MCAULY 3AF32C 3AF32C93 GL PROP ASSY CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 4020 1379 796457 PROP HUB ASSY CRACKED 1 L 7 2 3O A7CE 5 C P22EA 1997121100677 19971211 00677 NE 1997 12 11 EY2R9600160 3 19961101 G 6110 C5291 COUNTERWEIGHT SWRNGN SA227 SA227AC 8780603 SW MCAULY 4HFR34 4HFR34C652 NE PROP ASSY CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2584 911019 PROP ASSY COUNTERWEIGHT CRACKED 2 L 7 2 4T RT A8SW 6 C 3PNE 1997121100678 19971211 00678 NE 1997 12 11 EY2R9600161 3 19961101 G 6111 5133 BLADE BEECH 1900 1900D 1154162 CE HARTZL HCE4A HCE4A3A NE LEADING EDGE CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 5150 539 HJ272 BLADE ASSY LE SHEATH CRACKED 2 L 7 2 4T RT A24CE 5 C P10NE 1997121100679 19971211 00679 NE 1997 12 11 EY2R9600162 3 19961101 G 6111 5133 BLADE BEECH 1900 1900D 1154162 CE HARTZL HCE4A HCE4A3A NE LE SHEATH CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 4652 HJ310 BLADE LEADING EDGE SHEATH CRACKED 2 L 7 2 4T RT A24CE 5 C P10NE 1997121100680 19971211 00680 NE 1997 12 11 EY2R9600163 3 19961101 G 6111 5133 BLADE BEECH 1900 1900D 1154162 CE HARTZL HCE4A HCE4A3A NE LE SHEATH CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 7846 1350 HJ583 BLADE LEADING EDGE SHEATH CRACKED 2 L 7 2 4T RT A24CE 5 C P10NE 1997121100681 19971211 00681 GL 1997 12 11 EY2R9600164 3 19961201 G 6114 C2835C23 HUB BEECH 33 35B33 1151406 CE MCAULY 2A36C 2A36C23 GL NR 2 SOCKET CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 238 671575 HUB NR2 SOCKET, HAS CRACK 12" LONG 1 L 7 1 3O 3A15 5 C P880 1997122900035 19971229 00035 GL 1997 12 29 EY2R9600165 3 19961201 G 6114 D5892C87 HUB CESSNA 402 402CESSNA 207590K CE MCAULY 3AF32C 3AF32C87 GL THREAD AREAS CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 792390 THREAD AREAS OF HUB ARE CRACKED 1 L 7 2 3O A7CE 5 C P22EA 1997121100682 19971211 00682 GL 1997 12 11 EY2R9600166 3 19961201 G 6110 C4451 FERRULE CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROP ASSY CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1223 741352 5 HOLES IN BLADE PIN HOLE, DIMPLED AND FERRULE CRACKED 1 L 7 2 3O 3A10 5 C P22EA 1997121100683 19971211 00683 GL 1997 12 11 EY2R9600167 3 19961201 G 6114 C4716C98 HUB LKHEED 188 188A 5262602 WP MCAULY 2A34C D2A34C98 GL NR 1 SOCKET CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 789111 NR1 SOCKET, NR 1&2 THREADS CRACKED, 12" LONG 2 L 7 4 4T RT 4A22 5 C P3EA 1997121100684 19971211 00684 GL 1997 12 11 EY2R9600168 3 19961201 G 6114 D4887C81 HUB CESSNA 310 310J 2074226 CE MCAULY 2AF34C D2AF34C81 GL THREAD AREA CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 714258 PROP HUB ASSY CRACKED IN THREAD AREA 1 L 7 2 3O 3A10 5 C P5EA 1997121100685 19971211 00685 GL 1997 12 11 EY2R9600169 3 19961201 G 6114 D3944C88 HUB CESSNA 206 P206C 2073312 CE MCAULY 3A32C D3A32C88 GL NR 2 SOCKET CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 512 692219 HUB ASSY NR2 SOCKET, NR5 THREAD CRACKED, 2" LONG 1 H 7 1 3O A4CE 5 C P21EA 1997121100686 19971211 00686 GL 1997 12 11 EY2R9600170 3 19961201 G 6111 C4451 FERRULE CESSNA 206 P206C 2073312 CE MCAULY 3A32C D3A32C88 GL BLADE CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 512 692219 BLADE PIN HOLE DIMPLED, CAUSED FERRULE CRACK 1 H 7 1 3O A4CE 5 C P21EA 1997121100687 19971211 00687 GL 1997 12 11 EY2R9600171 3 19961201 G 6114 C5347C73 HUB CESSNA 182 182 2072702 CE MCAULY 2A34C E2A34C73 GL THREAD CRACKED CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 900797 THREAD AREAS OF HUB CRACKED 1 H 7 1 3O NT 3A13 5 C P3EA9 1997121100688 19971211 00688 GL 1997 12 11 EY2R9600172 3 19961201 G 6111 F7666A BLADE MAULE M5 M5200 SO HARTZL HCE2Y HCE2YR1BF GL PROP ASSY CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 CH15008 BLADE SN H77743 IS CRACKED 1 H 7 1 3O 3A23 5 C P9EA 1997121100689 19971211 00689 GL 1997 12 11 EY2R9600173 3 19961201 G 6110 3252 FORK BEECH 55 9555 1152702 CE HARTZL HCC3Y PHCC3YF2 GL PITCH CHANGE CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 EB798 PROP ASSY PITCH CHANGE FORK IS CRACKED 1 L 7 2 3O 3A16 5 C P25EA 1997122900036 19971229 00036 GL 1997 12 29 EY2R9600174 3 19961201 G 6110 2202 BEARING PIPER PA23 PA23250 7102308 SO HARTZL HCE2Y HCE2YR2 GL PROP ASSY CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 6195 BP239 PROP ASSY BEARING IS CRACKED 1 L 7 2 3O 1A10 5 C P9EA 1997122900037 19971229 00037 GL 1997 12 29 EY2R9600175 3 19961201 G 6110 24914S ROD PIPER PA23 PA23250 7102308 SO HARTZL HCE2Y HCE2YR2 GL PROP ASSY CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 6195 BP8909 PROP ASSY ROD CRACKED 1 L 7 2 3O 1A10 5 C P9EA 1997121100690 19971211 00690 GL 1997 12 11 EY2R9600176 3 19961201 G 6114 D7027C87 HUB CESSNA 310 310P 2074238 CE MCAULY 3AF32C 3AF32C87 GL THREAD AREA CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1627 692141 HUB ASSY CRACKED THREADS 1 L 7 2 3O 3A10 5 C P22EA 1997121100691 19971211 00691 GL 1997 12 11 EY2R9600177 3 19961201 G 6114 D7027C87 HUB CESSNA 310 310P 2074238 CE MCAULY 3AF32C 3AF32C87 GL THREAD AREA CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 693472 HUB ASSY THREAD CRACKED 1 L 7 2 3O 3A10 5 C P22EA 1997121100692 19971211 00692 GL 1997 12 11 EY2R9600178 3 19961201 G 6111 S90AT8 BLADE MCAULY 2A34C E2A34C73 GL THREADS CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 400 900797 BLADE SN JH105YS, CRACKED THREADS 5 C P3EA9 1997121100693 19971211 00693 GL 1997 12 11 EY2R9600179 3 19961201 G 6114 C6447C23 HUB BEECH 36 36BEECH 1151602 CE MCAULY 2A36C 2A36C23 GL BOLT SOCKETS CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 66085 HUB ASSY CRACKED IN BOLT SOCKETS 1 L 7 1 3O 3A15 5 C P880 1997121100694 19971211 00694 GL 1997 12 11 EY2R9600180 3 19961201 G 6110 C3092 RETAIN NUT CESSNA 210 210 2073402 CE MCAULY 2A34C E2A34C73 GL PROP ASSY CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 774298 PROP ASSY RETAIN NUT CRACKED THREADS 1 H 7 1 3O RT 3A21 5 C P3EA9 1997121100695 19971211 00695 GL 1997 12 11 EY2R9600181 3 19961201 G 6114 D6608C205 HUB CESSNA 188 188CESSNA 2073002 CE MCAULY 2A34C B2A34C205 GL THREAD AREA CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 830312 HUB ASSY CRACKED THREADS 1 L 7 1 3O A9CE 5 C P3EA 1997121100696 19971211 00696 GL 1997 12 11 EY2R9600182 3 19961201 G 6114 D6608C205 HUB CESSNA 188 188CESSNA 2073002 CE MCAULY 2A34C B2A34C205 GL THREAD AREA CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 850679 HUB ASSY CRACKED THREADS 1 L 7 1 3O A9CE 5 C P3EA 1997121100697 19971211 00697 GL 1997 12 11 EY2R9600183 3 19961201 G 6110 40191 BETA COLLAR STBROS SD3 SD360 8100606 EU HARTZL HCB5M HCB5MP3 GL PROP ASSY CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 13167 4311 EV712 PROP ASSY BETA COLLAR CRACKED 2 H 7 2 4T A41EU 6 C P44GL 1997121100698 19971211 00698 NE 1997 12 11 EY2R9600184 3 19961201 G 6111 E10950K BLADE BEECH 1900 1900D 1154162 CE HARTZL HCE4A HCE4A3A NE STA 18 INCH CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 4539 HJ241 BLADE IS CRACKED AT 18" STATION 2 L 7 2 4T RT A24CE 5 C P10NE 1997121100699 19971211 00699 GL 1997 12 11 EY2R9600185 3 19961201 G 6114 D4344C93 HUB CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL NR 3 SOCKET CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 794515 HUB ASSY CRACKED IN NR3 SOCKET, NR3 THREAD 1 L 7 2 3O RT A7CE 5 C P22EA 1997121100700 19971211 00700 GL 1997 12 11 EY2R9600186 3 19961201 G 6114 C4716C58 HUB MCAULY 2A34C D2A34C58 GL PROP ASSY CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1438 701466 MDR ISSUED ON HUB ASSY CRACKED 5 C P3EA 1997121100701 19971211 00701 GL 1997 12 11 EY2R9600187 3 19961201 G 6114 C4716C58 HUB CESSNA 210 210 2073402 CE MCAULY 2A34C D2A34C58 GL NR 1 SOCKET CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 666825 HUB ASSY CRACKED IN NR1 SOCKET 1 H 7 1 3O RT 3A21 5 C P3EA 1997122900038 19971229 00038 GL 1997 12 29 EY2R9600188 3 19961201 G 6114 C4883C55 HUB BEECH 95 95B55 1152729 CE MCAULY 2AF34C 2AF34C55 GL BLADE SOCKETS CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 676027 HUB ASSY CRACKED IN BOTH BLADE SOCKETS 1 L 7 2 3O RT 3A16 5 C P5EA 1997122900039 19971229 00039 GL 1997 12 29 EY2R9600189 3 19961201 G 6111 C3112 BLADE NUTS BEECH 95 95B55 1152729 CE MCAULY 2AF34C 2AF34C55 GL PROP ASSY CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 676027 PROP ASSY BLADE NUTS CRACKED 1 L 7 2 3O RT 3A16 5 C P5EA 1997121100702 19971211 00702 GL 1997 12 11 EY2R9600190 3 19961201 G 6114 D7015C87 HUB CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROP ASSY CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 693311 PROP ASSY HUB CRACKED 1 L 7 2 3O 3A10 5 C P22EA 1997121100703 19971211 00703 GL 1997 12 11 EY2R9600191 3 19961201 G 6110 2202 BEARING BBAVIA 8 8GCBC 1220803 SW HARTZL HCC2Y HCC2YF1 GL PROP ASSY CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 03 CH21278 PROP ASSY BEARING CRACKED 1 H 7 1 3O A21CE 5 C P920 1997121100704 19971211 00704 GL 1997 12 11 EY2R9600192 3 19960101 G 6110 PROPELLER CESSNA 150 152 2071835 CE MCAULY 1A103 1A103TCM GL HUB ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 RDA013 FIXED PITCH PROP ASSY IS CORRODED 1 H 7 1 3O NT 3A19 5 N P50GL 1997121100705 19971211 00705 GL 1997 12 11 EY2R9600193 3 19960101 G 6110 B3414 PISTON ROD PIN CESSNA 182 182P 2075816 CE MCAULY 2A34C 2A34C201 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2617 723706 PROP ASSY PISTON ROD PIN ASSY CORRODED 1 H 7 1 3O NT TA13 5 C P3EA 1997121100706 19971211 00706 GL 1997 12 11 EY2R9600194 3 19960101 G 6110 C3903 SPLIT RETAINER CESSNA 182 182P 2075816 CE MCAULY 2A34C 2A34C201 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2617 723706 PROP ASSY SPLIT RETAINER CRACKED 1 H 7 1 3O NT TA13 5 C P3EA 1997121100707 19971211 00707 GL 1997 12 11 EY2R9600195 3 19960101 G 6110 C5263 CYLINDER CESSNA 182 182P 2075816 CE MCAULY 2A34C 2A34C201 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2617 723706 PROP ASSY CYLINDER CORRODED 1 H 7 1 3O NT TA13 5 C P3EA 1997121100708 19971211 00708 GL 1997 12 11 EY2R9600196 3 19960101 G 6110 C5270 RETAIN BEARING CESSNA 182 182P 2075816 CE MCAULY 2A34C 2A34C201 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2617 723706 PROP ASSY RETAIN BEARING CORRODED 1 H 7 1 3O NT TA13 5 C P3EA 1997121100709 19971211 00709 GL 1997 12 11 EY2R9600197 3 19960101 G 6111 90DA8 BLADE CESSNA 182 182 2072702 CE MCAULY 2A34C 2A34C201 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 693743 BLADE ASSY SN C78439 IS CORRODED 1 H 7 1 3O NT 3A13 5 C P3EA 1997121100710 19971211 00710 GL 1997 12 11 EY2R9600198 3 19960101 G 6111 90DA8 BLADE CESSNA 182 182 2072702 CE MCAULY 2A34C 2A34C201 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 693743 BLADE ASSY SN B39063 IS CORRODED 1 H 7 1 3O NT 3A13 5 C P3EA 1997121100711 19971211 00711 GL 1997 12 11 EY2R9600199 3 19960101 G 6110 PROPELLER CESSNA 182 182Q 2072732 CE MCAULY 2A34C 2A34C203 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 158 765426 PROP ASSY IS CORRODED 1 H 7 1 3O NT 3A13 5 C P3EA 1997121100712 19971211 00712 GL 1997 12 11 EY2R9600200 3 19960101 G 6111 90AT8 BLADE CESSNA 182 182J 2072722 CE MCAULY 2A34C 2A34C66 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 810720 BLADE ASSY SN C37703 IS CORRODED 1 H 7 1 3O NT 3A13 5 C P3EA 1997121100713 19971211 00713 GL 1997 12 11 EY2R9600201 3 19960101 G 6111 90M8 BLADE UNIVAR 108 1082 9230406 NM MCAULY 2A36C 2A36C29 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 641271 BLADE ASSY SN K31785YS IS CORRODED 1 H 7 1 3O A767 5 C P880 1997121100714 19971211 00714 GL 1997 12 11 EY2R9600202 3 19960101 G 6111 90M8 BLADE UNIVAR 108 1082 9230406 NM MCAULY 2A36C 2A36C29 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 641271 BLADE ASSY SN C45338YS IS CORRODED 1 H 7 1 3O A767 5 C P880 1997121100715 19971211 00715 GL 1997 12 11 EY2R9600203 3 19960101 G 6114 C2343C29 HUB UNIVAR 108 1082 9230406 NM MCAULY 2A36C 2A36C29 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 641271 PROP ASSY HUB IS CORRODED 1 H 7 1 3O A767 5 C P880 1997122900040 19971229 00040 GL 1997 12 29 EY2R9600204 3 19960101 G 6111 78FF0 BLADE BEECH 95 95B55 1152729 CE MCAULY 2AF34C 2AF34C55 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 842577 BLADE ASSY SN K99201 IS CORRODED 1 L 7 2 3O RT 3A16 5 C P5EA 1997122900041 19971229 00041 GL 1997 12 29 EY2R9600205 3 19960101 G 6111 78FF0 BLADE BEECH 95 95B55 1152729 CE MCAULY 2AF34C 2AF34C55 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 842577 BLADE ASSY SN K99210 IS CORRODED 1 L 7 2 3O RT 3A16 5 C P5EA 1997122900042 19971229 00042 GL 1997 12 29 EY2R9600206 3 19960101 G 6110 A1896 CYLINDER PIN BEECH 95 95B55 1152729 CE MCAULY 2AF34C 2AF34C55 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 842577 PROP ASSY CYLINDER PIN IS CORRODED 1 L 7 2 3O RT 3A16 5 C P5EA 1997122900043 19971229 00043 GL 1997 12 29 EY2R9600207 3 19960101 G 6110 A4001 DOWEL BEECH 95 95B55 1152729 CE MCAULY 2AF34C 2AF34C55 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 842577 PROP ASSY DOWEL IS CORRODED 1 L 7 2 3O RT 3A16 5 C P5EA 1997122900044 19971229 00044 GL 1997 12 29 EY2R9600208 3 19960101 G 6110 B4458 ACTUATING PIN BEECH 95 95B55 1152729 CE MCAULY 2AF34C 2AF34C55 GL BLADE CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 842577 PROP ASSY BLADE ACTUATING PIN CORRODED 1 L 7 2 3O RT 3A16 5 C P5EA 1997121100716 19971211 00716 GL 1997 12 11 EY2R9600209 3 19960101 G 6114 D6602C76 HUB BEECH 35 V35 1151538 CE MCAULY 3A32C 3A32C76 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 701254 PROP HUB ASSY IS CORRODED 1 L 7 1 3O 3A15 5 C P21EA 1997121100717 19971211 00717 GL 1997 12 11 EY2R9600210 3 19960101 G 6110 A4001 DOWEL BEECH 35 35BEECH 1151502 CE MCAULY 3A32C 3A32C76 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 803085 PROP ASSY DOWEL IS CORRODED 1 L 7 1 3O A777 5 C P21EA 1997121100718 19971211 00718 GL 1997 12 11 EY2R9600211 3 19960101 G 6110 B4460 ACTUATING PIN BEECH 35 35BEECH 1151502 CE MCAULY 3A32C 3A32C76 GL BLADE CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 803085 BLADE ACTUATING PIN IS CORRODED 1 L 7 1 3O A777 5 C P21EA 1997121100719 19971211 00719 GL 1997 12 11 EY2R9600212 3 19960101 G 6110 C2987 RETAIN BEARING BEECH 35 35BEECH 1151502 CE MCAULY 3A32C 3A32C76 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 803085 PROP ASSY RETAIN BEARING CORRODED 1 L 7 1 3O A777 5 C P21EA 1997121100720 19971211 00720 GL 1997 12 11 EY2R9600213 3 19960101 G 6110 C4904 NUT BEECH 35 35BEECH 1151502 CE MCAULY 3A32C 3A32C76 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 803085 PROP ASSY NUT IS CORRODED 1 L 7 1 3O A777 5 C P21EA 1997121100721 19971211 00721 GL 1997 12 11 EY2R9600214 3 19960101 G 6111 S82NC2 BLADE BEECH 35 35BEECH 1151502 CE MCAULY 3A32C 3A32C76 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 803085 BLADE SN K103846YS IS CORRODED 1 L 7 1 3O A777 5 C P21EA 1997121100722 19971211 00722 GL 1997 12 11 EY2R9600215 3 19960101 G 6111 S82NC2 BLADE BEECH 35 35BEECH 1151502 CE MCAULY 3A32C 3A32C76 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 803085 BLADE SN K103399YS IS CORRODED 1 L 7 1 3O A777 5 C P21EA 1997121100723 19971211 00723 GL 1997 12 11 EY2R9600216 3 19960101 G 6110 C5270 RETAIN BEARING CESSNA 303 T303 2073820 CE MCAULY 3AF32C 3AF32C506 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2184 816016 PROP ASSY RETAIN BEARING IS CORRODED 1 L 7 2 3O A34CE 5 C P57GL 1997121100724 19971211 00724 GL 1997 12 11 EY2R9600217 3 19960101 G 6110 C2987 RETAIN BEARING MCAULY 3AF32C 3AF32C75 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 700159 PROP ASSY RETAIN BEARING IS CORRODED 5 C P22EA 1997121100725 19971211 00725 GL 1997 12 11 EY2R9600218 3 19960101 G 6110 A3550 FEATHER CYLINDER CESSNA 402 402B 207590P CE MCAULY 3AF32C 3AF32C87 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 769624 PROP ASSY FEATHER CYLINDER IS CORRODED 1 L 7 2 3O A7CE 5 C P22EA 1997121100726 19971211 00726 GL 1997 12 11 EY2R9600219 3 19960101 G 6110 C2987 RETAIN BEARING CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 711915 PROP ASSY RETAIN BEARING CORRODED 1 L 7 2 3O 3A10 5 C P22EA 1997121100727 19971211 00727 GL 1997 12 11 EY2R9600220 3 19960101 G 6110 C2987 RET. BEARING CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 723586 PROP ASSY RETAIN BEARING IS CORRODED 1 L 7 2 3O RT 3A10 5 C P22EA 1997121100728 19971211 00728 GL 1997 12 11 EY2R9600221 3 19960101 G 6110 C2987 RETAIN BEARING CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 756523 PROP ASSY RETAIN BEARING CORRODED 1 L 7 2 3O 3A10 5 C P22EA 1997121100729 19971211 00729 GL 1997 12 11 EY2R9600222 3 19960101 G 6110 C2987 RETAIN BEARING CESSNA 402 402B 207590P CE MCAULY 3AF32C 3AF32C87 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 769624 PROP ASSY RETAIN BEARING IS CORRODED 1 L 7 2 3O A7CE 5 C P22EA 1997121100730 19971211 00730 GL 1997 12 11 EY2R9600223 3 19960101 G 6110 C2987 RETAIN BEARING CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 780978 PROP ASSY RETAIN BEARING IS CORRODED 1 L 7 2 3O 3A10 5 C P22EA 1997121100731 19971211 00731 GL 1997 12 11 EY2R9600224 3 19960101 G 6110 C2987 RETAIN BEARING CESSNA 402 402B 207590P CE MCAULY 3AF32C 3AF32C87 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 7710826 PROP ASSY RETAIN BEARING IS CORRODED 1 L 7 2 3O A7CE 5 C P22EA 1997121100732 19971211 00732 GL 1997 12 11 EY2R9600225 3 19960101 G 6110 C3475 NUT CESSNA 402 402B 207590P CE MCAULY 3AF32C 3AF32C87 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 769624 PROP ASSY NUT IS CORRODED 1 L 7 2 3O A7CE 5 C P22EA 1997121100733 19971211 00733 GL 1997 12 11 EY2R9600226 3 19960101 G 6110 C3550 FEATHER CYLINDER CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 723586 PROP ASSY FEATHER CYLINDER IS CORRODED 1 L 7 2 3O RT 3A10 5 C P22EA 1997121100734 19971211 00734 GL 1997 12 11 EY2R9600227 3 19960101 G 6110 C3550 FEATHER CYLINDER CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 724316 PROP FEATHER CYLINDER IS CORRODED 1 L 7 2 3O 3A10 5 C P22EA 1997121100735 19971211 00735 GL 1997 12 11 EY2R9600228 3 19960101 G 6110 C3550 FEATHER CYLINDER CESSNA 402 402B 207590P CE MCAULY 3AF32C 3AF32C87 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 7710826 PROP ASSY FEATHER CYLINDER IS CORRODED 1 L 7 2 3O A7CE 5 C P22EA 1997121100736 19971211 00736 GL 1997 12 11 EY2R9600229 3 19960101 G 6114 D7015C87 HUB CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 780978 PROP HUB ASSY CORRODED 1 L 7 2 3O 3A10 5 C P22EA 1997121100737 19971211 00737 GL 1997 12 11 EY2R9600230 3 19960101 G 6111 S82NC4 BLADE CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 711915 BLADE SN F40097YS IS CORRODED 1 L 7 2 3O 3A10 5 C P22EA 1997121100738 19971211 00738 GL 1997 12 11 EY2R9600231 3 19960101 G 6111 82NC55 BLADE CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 746949 BLADE SN K62721YS IS CORRODED 1 L 7 2 3O RT 3A10 5 C P22EA 1997121100739 19971211 00739 GL 1997 12 11 EY2R9600232 3 19960101 G 6111 82NC55 BLADE CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 746949 BLADE SN K62780YS IS CORRODED 1 L 7 2 3O RT 3A10 5 C P22EA 1997121100740 19971211 00740 GL 1997 12 11 EY2R9600233 3 19960101 G 6111 82NC55 BLADE CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 746949 BLADE SN K62754YS IS CORRODED 1 L 7 2 3O RT 3A10 5 C P22EA 1997121100741 19971211 00741 GL 1997 12 11 EY2R9600234 3 19960101 G 6110 B4459 ACTUATING PIN CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL BLADE CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 760917 BLADE ACTUATING PIN IS CORRODED 1 L 7 2 3O RT 3A10 5 C P22EA 1997121100742 19971211 00742 GL 1997 12 11 EY2R9600235 3 19960101 G 6110 C2987 RETAIN BEARING CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 760917 PROP ASSY RETAIN BEARING CORRODED 1 L 7 2 3O RT 3A10 5 C P22EA 1997121100743 19971211 00743 GL 1997 12 11 EY2R9600236 3 19960101 G 6114 D7015C87 HUB CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 760917 PROP ASSY HUB IS CORRODED 1 L 7 2 3O RT 3A10 5 C P22EA 1997121100744 19971211 00744 GL 1997 12 11 EY2R9600237 3 19960101 G 6111 S82NC55 BLADE CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 760917 BLADE SN K62727YS IS CORRODED 1 L 7 2 3O RT 3A10 5 C P22EA 1997121100745 19971211 00745 GL 1997 12 11 EY2R9600238 3 19960101 G 6111 82NC2 BLADE CESSNA 206 U206F 2073333 CE MCAULY 3AF32C 3AF32C* GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 4513 771226 BLADE SN KK041YSI CORRODED 1 H 7 1 3O A4CE 5 C P22EA 1997121100746 19971211 00746 GL 1997 12 11 EY2R9600239 3 19960101 G 6110 C2987 RETAIN BEARING CESSNA 206 U206F 2073333 CE MCAULY 3AF32C 3AF32C* GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 4513 771226 PROP ASSY RETAIN BEARING IS CORRODED 1 H 7 1 3O A4CE 5 C P22EA 1997121100747 19971211 00747 GL 1997 12 11 EY2R9600240 3 19960101 G 6110 C4451 FERRULE CESSNA 206 U206F 2073333 CE MCAULY 3AF32C 3AF32C* GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 4513 771226 PROP ASSY FERRULE IS CORRODED 1 H 7 1 3O A4CE 5 C P22EA 1997121100748 19971211 00748 GL 1997 12 11 EY2R9600241 3 19960101 G 6110 C4451 FERRULE CESSNA 206 U206F 2073333 CE MCAULY 3AF32C 3AF32C* GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 902458 PROP ASSY FERRULE IS CORRODED 1 H 7 1 3O A4CE 5 C P22EA 1997121100749 19971211 00749 GL 1997 12 11 EY2R9600242 3 19960101 G 6110 C4902 NUT CESSNA 206 U206F 2073333 CE MCAULY 3AF32C 3AF32C* GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 4513 771226 PROP ASSY NUT IS CORRODED 1 H 7 1 3O A4CE 5 C P22EA 1997121100750 19971211 00750 GL 1997 12 11 EY2R9600243 3 19960101 G 6114 D5904C90 HUB CESSNA 206 U206F 2073333 CE MCAULY 3AF32C 3AF32C* GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 4513 771226 PROP ASSY HUB IS CORRODED 1 H 7 1 3O A4CE 5 C P22EA 1997121100751 19971211 00751 GL 1997 12 11 EY2R9600244 3 19960101 G 6110 C1896 CYLINDER PIN CESSNA 340 340CESSNA 2076404 CE MCAULY 3AF32C 3AF32C* GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 940191 PROP ASSY CYLINDER PIN IS CORRODED 1 L 7 2 3O 3A25 5 C P22EA 1997121100752 19971211 00752 GL 1997 12 11 EY2R9600245 3 19960101 G 6111 82NC55 BLADE CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 782680 BLADE SN K76547 IS CORRODED 1 L 7 2 3O RT A7CE 5 C P22EA 1997121800684 19971218 00684 GL 1997 12 18 EY2R9600246 3 19960101 G 6111 82NC55 BLADE CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 782680 PROP BLADE SN K77092 IS CORRODED 1 L 7 2 3O RT A7CE 5 C P22EA 1997121800685 19971218 00685 GL 1997 12 18 EY2R9600247 3 19960101 G 6110 C3550 FEATHER CYLINDER CESSNA 340 340CESSNA 2076404 CE MCAULY 3AF32C 3AF32C93 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 733547 PROP FEATHER CYLINDER IS CORRODED 1 L 7 2 3O 3A25 5 C P22EA 1997121800686 19971218 00686 GL 1997 12 18 EY2R9600248 3 19960101 G 6110 C3550 FEATHER CYLINDER CESSNA 340 340CESSNA 2076404 CE MCAULY 3AF32C 3AF32C93 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 800011 PROP FEATHER CYLINDER IS CORRODED 1 L 7 2 3O 3A25 5 C P22EA 1997121800687 19971218 00687 GL 1997 12 18 EY2R9600249 3 19960101 G 6111 S82NC55 BLADE CESSNA 340 340CESSNA 2076404 CE MCAULY 3AF32C 3AF32C93 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 733547 PROP BLADE SN F39058YS IS CORRODED 1 L 7 2 3O 3A25 5 C P22EA 1997121800688 19971218 00688 GL 1997 12 18 EY2R9600250 3 19960101 G 6110 C2987 BEARING CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROP RETAIN CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 741001 PROP ASSY RETAINING BEARING IS CORRODED 1 L 7 2 3O RT A7CE 5 C P22EA 1997121800689 19971218 00689 GL 1997 12 18 EY2R9600251 3 19960101 G 6111 S82NC4 BLADE CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 PROP BLADE SN F48474YS IS CORRODED 1 L 7 2 3O RT A7CE 5 C P22EA 1997121800690 19971218 00690 GL 1997 12 18 EY2R9600252 3 19960101 G 6110 B3490 PISTON ROD PIN CESSNA 340 340CESSNA 2076404 CE MCAULY 3AF32C 3AF32C93 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 779469 PROP ASSY PISTON ROD PIN IS CORRODED 1 L 7 2 3O 3A25 5 C P22EA 1997121800691 19971218 00691 GL 1997 12 18 EY2R9600253 3 19960101 G 6110 C1896 CYLINDER PIN CESSNA 340 340CESSNA 2076404 CE MCAULY 3AF32C 3AF32C93 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 779469 PROP ASSY CYLINDER PIN IS CORRODED 1 L 7 2 3O 3A25 5 C P22EA 1997121800692 19971218 00692 GL 1997 12 18 EY2R9600254 3 19960101 G 6110 C4191 DOWEL CESSNA 340 340CESSNA 2076404 CE MCAULY 3AF32C 3AF32C93 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 779469 PROP ASSY DOWEL IS CORRODED 1 L 7 2 3O 3A25 5 C P22EA 1997121800693 19971218 00693 GL 1997 12 18 EY2R9600255 3 19960101 G 6110 C1896 CYLINDER PIN CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 780708 PROP ASSY CYLINDER PIN IS CORRODED 1 L 7 2 3O RT A7CE 5 C P22EA 1997121800694 19971218 00694 GL 1997 12 18 EY2R9600256 3 19960101 G 6110 C2987 RETAIN BEARING CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 780708 PROP ASSY RETAINING BEARING IS CORRODED 1 L 7 2 3O RT A7CE 5 C P22EA 1997121800695 19971218 00695 GL 1997 12 18 EY2R9600257 3 19960101 G 6110 B3490 PISTON ROD PIN CESSNA 340 340CESSNA 2076404 CE MCAULY 3AF32C 3AF32C93 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 940191 PROP ASSY PISTON ROD PIN IS CORRODED 1 L 7 2 3O 3A25 5 C P22EA 1997121800696 19971218 00696 GL 1997 12 18 EY2R9600258 3 19960101 G 6114 B4459 BLADE ACT PIN CESSNA 340 340CESSNA 2076404 CE MCAULY 3AF32C 3AF32C93 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 940191 PROP ASSY BLADE ACTUATING PIN IS CORRODED 1 L 7 2 3O 3A25 5 C P22EA 1997121800697 19971218 00697 GL 1997 12 18 EY2R9600259 3 19960101 G 6110 C2987 RETAIN BEARING CESSNA 340 340CESSNA 2076404 CE MCAULY 3AF32C 3AF32C93 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 940191 PROP ASSY RETAINING BEARING IS CORRODED 1 L 7 2 3O 3A25 5 C P22EA 1997121800698 19971218 00698 GL 1997 12 18 EY2R9600260 3 19960101 G 6110 C3550 FEATHER CYLINDER CESSNA 340 340CESSNA 2076404 CE MCAULY 3AF32C 3AF32C93 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 779469 PROP ASSY FEATHER CYLINDER IS CORRODED 1 L 7 2 3O 3A25 5 C P22EA 1997121800699 19971218 00699 GL 1997 12 18 EY2R9600261 3 19960101 G 6110 C4191 DOWEL CESSNA 340 340CESSNA 2076404 CE MCAULY 3AF32C 3AF32C93 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 940191 PROP ASSY DOWEL IS CORRODED 1 L 7 2 3O 3A25 5 C P22EA 1997121800700 19971218 00700 GL 1997 12 18 EY2R9600262 3 19960101 G 6110 C7036 NUT CESSNA 340 340CESSNA 2076404 CE MCAULY 3AF32C 3AF32C93 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 940191 PROP ASSY NUT C7036 IS CORRODED 1 L 7 2 3O 3A25 5 C P22EA 1997121800701 19971218 00701 GL 1997 12 18 EY2R9600263 3 19960101 G 6114 D7015C93 HUB CESSNA 340 340CESSNA 2076404 CE MCAULY 3AF32C 3AF32C93 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 779122 PROP ASSY HUB IS CORRODED 1 L 7 2 3O 3A25 5 C P22EA 1997121800702 19971218 00702 GL 1997 12 18 EY2R9600264 3 19960101 G 6110 C3550 FEATHER CYLINDER CESSNA 421 421B 2076014 CE MCAULY 3AF34C 3AF34C92 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 725977 PROP ASSY FEATHER CYLINDER IS CORRODED 1 L 7 2 3O A7CE 5 C P22EA 1997121800703 19971218 00703 GL 1997 12 18 EY2R9600265 3 19960101 G 6114 D7019C92 HUB CESSNA 421 421 2076010 CE MCAULY 3AF34C 3AF34C92 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 716065 PROP HUB ASSY IS CORRODED 1 L 7 2 3O RT A7CE 5 C P22EA 1997121800704 19971218 00704 GL 1997 12 18 EY2R9600266 3 19960101 G 6110 C5270 RETAIN BEARING CESSNA 340 340CESSNA 2076404 CE MCAULY 3AF32C 3AF32C505 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 840801 PROP ASSY RETAINING BEARING IS CORRODED 1 L 7 2 3O 3A25 5 C P22EA 1997121800705 19971218 00705 GL 1997 12 18 EY2R9600267 3 19960101 G 6110 C5270 RETAIN BEARING CESSNA 208 208B 2073701 CE MCAULY 3AF34C 3GFR34C703 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3797 840997 PROP ASSY RETAINING BEARING IS CORRODED 1 H 7 1 3T A37CE 5 C P60GL 1997121800706 19971218 00706 GL 1997 12 18 EY2R9600268 3 19960101 G 6110 D5010 CYLINDER CESSNA 208 208B 2073701 CE MCAULY 3AF34C 3GFR34C703 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3797 840997 PROP ASSY CYLINDER IS CORRODED 1 H 7 1 3T A37CE 5 C P60GL 1997121800707 19971218 00707 GL 1997 12 18 EY2R9600269 3 19960101 G 6114 C4326C214 HUB CESSNA 182 R182 2072734 CE MCAULY 2D34C B2D34C214 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 788787 PROP HUB ASSY IS CORRODED 1 H 7 1 3O RT 3A13 5 C P7EA 1997121800708 19971218 00708 GL 1997 12 18 EY2R9600270 3 19960101 G 6110 C4326C218 HUB CESSNA 182 R182 2072734 CE MCAULY 2D34C B2D34C218 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 821459 PROP HUB ASSY IS CORRODED 1 H 7 1 3O RT 3A13 5 C P7EA 1997121800709 19971218 00709 GL 1997 12 18 EY2R9600271 3 19960101 G 6110 C5270 RETAIN BEARING CESSNA 182 R182 2072734 CE MCAULY 2D34C B2D34C218 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 821459 PROP ASSY RETAINING BEARING 1 H 7 1 3O RT 3A13 5 C P7EA 1997121800710 19971218 00710 GL 1997 12 18 EY2R9600272 3 19960101 G 6111 G90DHB8 BLADE CESSNA 182 R182 2072734 CE MCAULY 2D34C B2D34C218 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 821459 BLADE SN CA325 IS CORRODED 1 H 7 1 3O RT 3A13 5 C P7EA 1997121800711 19971218 00711 GL 1997 12 18 EY2R9600273 3 19960101 G 6111 G90DHB8 BLADE CESSNA 182 R182 2072734 CE MCAULY 2D34C B2D34C218 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 821459 BLADE SN CA337IS CORRODED 1 H 7 1 3O RT 3A13 5 C P7EA 1997121800712 19971218 00712 GL 1997 12 18 EY2R9600274 3 19960101 G 6114 2201 HUB PIPER PA34 PA34200T 7103406 SO HARTZL HCC2Y BHCC2YF2 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 AN4181 PROP HUB ASSY IS CORRODED 1 L 7 2 3O A7SO 5 C P920 1997121800713 19971218 00713 GL 1997 12 18 EY2R9600275 3 19960101 G 6110 C3903 SPLIT RETAINER CESSNA 336 336 2075602 CE MCAULY 2AF34C D2AF34C302 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 728673 PROP ASSY SPLIT RETAINER IS CORRODED 1 H 7 2 3O A2CE 5 C P5EA 1997121800714 19971218 00714 GL 1997 12 18 EY2R9600276 3 19960101 G 6110 C2987 RETAIN BEARING CESSNA 210 210L 2073448 CE MCAULY 3A32C D3A32C88 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2953 1371 710981 PROP ASSY RETAINING BEARING IS CORRODED 1 H 7 1 3O 3A21 5 C P21EA 1997121800715 19971218 00715 GL 1997 12 18 EY2R9600277 3 19960101 G 6110 C4902 NUT CESSNA 210 210L 2073448 CE MCAULY 3A32C D3A32C88 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2953 1371 710981 PROP ASSY NUT PN C4902 IS CORRODED 1 H 7 1 3O 3A21 5 C P21EA 1997121800716 19971218 00716 GL 1997 12 18 EY2R9600278 3 19960101 G 6110 C5262 CYLINDER CESSNA 210 210L 2073448 CE MCAULY 3A32C D3A32C88 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2953 1371 710981 PROP ASSY CYLINDER IS CORRODED 1 H 7 1 3O 3A21 5 C P21EA 1997121800717 19971218 00717 GL 1997 12 18 EY2R9600279 3 19960101 G 6110 C5262 CYLINDER CESSNA 206 P206B 2073309 CE MCAULY 3A32C D3A32C88 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 714263 PROP ASSY CYLINDER IS CORRODED 1 H 7 1 3O A4CE 5 C P21EA 1997121800718 19971218 00718 GL 1997 12 18 EY2R9600280 3 19960101 G 6111 S82NC2 BLADE CESSNA 210 210L 2073448 CE MCAULY 3A32C D3A32C88 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2953 1371 710981 BLADE SN K95680YS IS CORRODED 1 H 7 1 3O 3A21 5 C P21EA 1997121800719 19971218 00719 GL 1997 12 18 EY2R9600281 3 19960101 G 6111 S82NC2 BLADE CESSNA 210 210L 2073448 CE MCAULY 3A32C D3A32C88 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2953 1371 710981 BLADE SN K94806YS IS CORRODED 1 H 7 1 3O 3A21 5 C P21EA 1997121800720 19971218 00720 GL 1997 12 18 EY2R9600282 3 19960101 G 6111 S82NC2 BLADE CESSNA 210 210L 2073448 CE MCAULY 3A32C D3A32C88 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2953 1371 710981 BLADE SN K95331YS IS CORRODED 1 H 7 1 3O 3A21 5 C P21EA 1997121800721 19971218 00721 GL 1997 12 18 EY2R9600283 3 19960101 G 6110 C4451 FERRULE CESSNA 206 TU206D 2073344 CE MCAULY 3A32C D3A32C90 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 850716 PROP ASSY FERRULE IS CORRODED 1 H 7 1 3O A4CE 5 C P21EA 1997121800722 19971218 00722 GL 1997 12 18 EY2R9600284 3 19960101 G 6110 C5262 CYLINDER CESSNA 210 T210N 2073456 CE MCAULY D3A34 D3A34C402 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 786048 PROP ASSY CYLINDER IS CORRODED 1 H 7 1 3O 3A21 5 C P47GL 1997121800723 19971218 00723 GL 1997 12 18 EY2R9600285 3 19960101 G 6110 31A CLAMP PIPER PA24 PA24250 7102404 SO HARTZL HCA2V HCA2V* GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 F3197 PROP ASSY CLAMP IS CORRODED 1 L 7 1 3O 1A15 5 C P24EA 1997121800724 19971218 00724 GL 1997 12 18 EY2R9600286 3 19960101 G 6110 31A CLAMP PIPER PA24 PA24250 7102404 SO HARTZL HCA2V HCA2V* GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 F3207 PROP ASSY CLAMP IS CORRODED 1 L 7 1 3O 1A15 5 C P24EA 1997121800725 19971218 00725 GL 1997 12 18 EY2R9600287 3 19960101 G 6110 8268 PROP ASSY PIPER PA24 PA24250 7102404 SO HARTZL HCA2V HCA2V* GL PROP CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 811 J1161 PROP ASSY PART(PN 8268) IS CPRRODED 1 L 7 1 3O 1A15 5 C P24EA 1997121800726 19971218 00726 GL 1997 12 18 EY2R9600288 3 19960101 G 6110 971 SPLIT BEARING PIPER PA24 PA24250 7102404 SO HARTZL HCA2V HCA2V* GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 811 J1161 PROP ASSY SPLIT BEARING IS CORRODED 1 L 7 1 3O 1A15 5 C P24EA 1998010500015 19980105 00015 GL 1998 1 5 EY2R9600289 3 19960101 G 6110 1851 BEARING BEECH 18 D18S 1151004 CE HARTZL HCB3P HCB3P302 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 5358 1355 923N PROP ASSY BEARING IS CORRODED 1 L 7 2 3R A765 5 C P29EA 1998010500016 19980105 00016 GL 1998 1 5 EY2R9600290 3 19960101 G 6110 1851 BEARING BEECH 18 D18S 1151004 CE HARTZL HCB3R HCB3R302 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 5358 1355 694N PROP ASSY BEARING IS CORRODED 1 L 7 2 3R A765 5 C P28EA 1998010500017 19980105 00017 GL 1998 1 5 EY2R9600291 3 19960101 G 6110 130195 CLAMP EMB 110 EMB110* SO HARTZL HCB3T HCB3TN3 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 8331 2830 BU3847 PROP ASSY CLAMP IS CORRODED 1 L 7 2 4T RT A21SO 6 C P15EA 1998010500018 19980105 00018 GL 1998 1 5 EY2R9600292 3 19960101 G 6110 1851T BEARING EMB 110 EMB110* SO HARTZL HCB3T HCB3TN3 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 8331 2830 BU3847 PROP ASSY BEARING IS CORRODED 1 L 7 2 4T RT A21SO 6 C P15EA 1998010500019 19980105 00019 GL 1998 1 5 EY2R9600293 3 19960101 G 6110 790100018 STEEL BALL EMB 110 EMB110* SO HARTZL HCB3T HCB3TN3 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 8331 2830 BU3847 PROP ASSY STEEL BALL IS CORRODED 1 L 7 2 4T RT A21SO 6 C P15EA 1997121800727 19971218 00727 GL 1997 12 18 EY2R9600294 3 19960101 G 6110 790100018 STEEL BALL MTSBSI MU2 MU2* SW HARTZL HCB4T HCB4TN5 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3027 1196 CD1153M1 PROP ASSY STEEL BALL IS CORRODED 1 H 7 2 3T A2PC 6 C P40EA 1997121800728 19971218 00728 GL 1997 12 18 EY2R9600295 3 19960101 G 6110 790100018 STEEL BALL MTSBSI MU2 MU2* SW HARTZL HCB4T HCB4TN5 GL PROP ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3027 1196 CD1159M1 PROP ASSY STEEL BALL IS CORRODED 1 H 7 2 3T A2PC 6 C P40EA 1997123100234 19971231 00234 GL 1997 12 31 EY2R9600296 3 19960101 G 6110 790100016 STEEL BALL GULSTM 112 114 7630314 SW HARTZL HCC2Y HCC2YR1 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1344 543 CH20680 STEEL BALL CORRODED. 1 L 7 1 3O A12SO 5 C P920 1997123100235 19971231 00235 GL 1997 12 31 EY2R9600297 3 19960101 G 6110 2067 MTG. STUD PIPER PA31 PA31 7103102 SO HARTZL HCE2Y HCE2YK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1938 232 CJ838 MOUNTING STUD FOUND CORRODED. 1 L 7 2 3O A20SO 5 C P9EA 1997123100236 19971231 00236 GL 1997 12 31 EY2R9600298 3 19960101 G 6110 2202 SPLIT BEARING PIPER PA31 PA31 7103102 SO HARTZL HCE2Y HCE2YK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 4975 1810 CJ344 SPLIT BEARING HAS CORROSION. 1 L 7 2 3O A20SO 5 C P9EA 1997123100237 19971231 00237 GL 1997 12 31 EY2R9600299 3 19960101 G 6110 2202 SPLIT BEARING PIPER PA31 PA31 7103102 SO HARTZL HCE2Y HCE2YK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1938 232 CJ838 SPLIT BEARING HAS CORROSION. 1 L 7 2 3O A20SO 5 C P9EA 1997123100238 19971231 00238 GL 1997 12 31 EY2R9600300 3 19960101 G 6110 24573 PITCH CHG FORK PIPER PA31 PA31 7103102 SO HARTZL HCE2Y HCE2YK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1938 232 CJ838 PITCH CHANGE FORK CORRODED. 1 L 7 2 3O A20SO 5 C P9EA 1997123100239 19971231 00239 GL 1997 12 31 EY2R9600301 3 19960101 G 6114 24772 HUB PIPER PA31 PA31 7103102 SO HARTZL HCE2Y HCE2YK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 4975 1810 CJ344 HUB FOUND CORRODED. 1 L 7 2 3O A20SO 5 C P9EA 1997123100240 19971231 00240 GL 1997 12 31 EY2R9600302 3 19960101 G 6114 24773 HUB PIPER PA23 PA23250 7102308 SO HARTZL HCE2Y HCE2YR2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BP3875 HUB FOUND CORRODED. 1 L 7 2 3O 1A10 5 C P9EA 1997123100241 19971231 00241 GL 1997 12 31 EY2R9600303 3 19960101 G 6114 24773 HUB PIPER PA23 PA23250 7102308 SO HARTZL HCE2Y HCE2YR2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BP6195 HUB FOUND CORRODED. 1 L 7 2 3O 1A10 5 C P9EA 1997123100242 19971231 00242 GL 1997 12 31 EY2R9600304 3 19960201 G 6110 PROPELLER CESSNA 150 152 2071835 CE MCAULY 1A103 1A103TCM GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 R773623 CORROSION FOUND ON FIX-PITCHED PROPELLER. 1 H 7 1 3O NT 3A19 5 N P50GL 1997123100243 19971231 00243 GL 1997 12 31 EY2R9600305 3 19960201 G 6110 C3411 BEARING RACE CESSNA 172 172K 2072430 CE MCAULY 2A34C 2A34C203 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 755593 BEARING RACE FOUND WITH CORROSION. 1 H 7 1 3O NT 3A12 5 C P3EA 1997123100244 19971231 00244 GL 1997 12 31 EY2R9600306 3 19960201 G 6110 C3903 SPLIT RETAINER CESSNA 172 172K 2072430 CE MCAULY 2A34C 2A34C203 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 755593 SPLIT RETAINER FOUND TO BE CORRODED. 1 H 7 1 3O NT 3A12 5 C P3EA 1997123100245 19971231 00245 GL 1997 12 31 EY2R9600307 3 19960201 G 6114 C4239C66 HUB CESSNA 182 182B 2072706 CE MCAULY 2A34C 2A34C66 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 731416 HUB FOUND CORRODED. 1 H 7 1 3O NT 3A13 5 C P3EA 1997123100246 19971231 00246 GL 1997 12 31 EY2R9600308 3 19960201 G 6114 C5480C66 HUB CESSNA 180 180 2072602 CE MCAULY 2A34C 2A34C66 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 783777 HUB FOUND CORRODED. 1 H 7 1 3O NC 5A6 5 C P3EA 1997123100247 19971231 00247 GL 1997 12 31 EY2R9600309 3 19960201 G 6114 C5480C66 HUB CESSNA 180 180 2072602 CE MCAULY 2A34C 2A34C66 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 823120 HUB FOUND CORRODED. 1 H 7 1 3O NC 5A6 5 C P3EA 1997123100248 19971231 00248 GL 1997 12 31 EY2R9600310 3 19960201 G 6110 C2987 RETAIN BEARING BEECH 36 A36 1151604 CE MCAULY 3A32C 3A32C76 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2833 631 781342 RETAIN BEARING FOUND CORRODED. 1 L 7 1 3O 3A15 5 C P21EA 1997123100249 19971231 00249 GL 1997 12 31 EY2R9600311 3 19960201 G 6114 D5880C508 HUB PIPER PA34 PA34220T 7103420 SO MCAULY 3AF32C 3AF32C508 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 851633 HUB FOUND CORRODED. 1 L 7 2 3O A7SO 5 C P22EA 1997123100250 19971231 00250 GL 1997 12 31 EY2R9600312 3 19960201 G 6110 A16349 BALL BEARING BEECH 58 58 1152740 CE MCAULY 3AF32C 3AF32C512 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 832248 CORROSION FOUND ON BALL BEARING. 1 L 7 2 3O 3A16 5 C P22EA 1997123100251 19971231 00251 GL 1997 12 31 EY2R9600313 3 19960201 G 6110 A16349 BALL BEARING BEECH 58 58 1152740 CE MCAULY 3AF32C 3AF32C512 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2200 437 840493 CORROSION FOUND ON BALL BEARING. 1 L 7 2 3O 3A16 5 C P22EA 1997123100252 19971231 00252 GL 1997 12 31 EY2R9600314 3 19960201 G 6110 C2987 RETAIN BEARING CESSNA 402 402B 207590P CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 709 761779 RETAIN BEARING FOUND CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100253 19971231 00253 GL 1997 12 31 EY2R9600315 3 19960201 G 6110 C2987 RETAIN BEARING CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1655 780874 RETAIN BEARING FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100254 19971231 00254 GL 1997 12 31 EY2R9600316 3 19960201 G 6110 C2987 RETAIN BEARING CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1655 790739 RETAIN BEARING FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100255 19971231 00255 GL 1997 12 31 EY2R9600317 3 19960201 G 6110 C2987 RETAIN BEARING CESSNA 310 T310Q 2074244 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 800234 RETAIN BEARING FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100256 19971231 00256 GL 1997 12 31 EY2R9600318 3 19960201 G 6110 C3475 NUT CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1655 790739 NUT FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100257 19971231 00257 GL 1997 12 31 EY2R9600319 3 19960201 G 6110 C3475 NUT CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 800234 NUT FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100258 19971231 00258 GL 1997 12 31 EY2R9600320 3 19960201 G 6110 C3550 FEATHER CYLINDER CESSNA 310 T310Q 2074244 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 739404 FEATHER CYLINDER FOUND WITH CORROSION. 1 L 7 2 3O 3A10 5 C P22EA 1997123100259 19971231 00259 GL 1997 12 31 EY2R9600321 3 19960201 G 6110 C3550 FEATHER CYLINDER CESSNA 402 402B 207590P CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 709 761779 FEATHER CYLINDER FOUND WITH CORROSION. 1 L 7 2 3O A7CE 5 C P22EA 1997123100260 19971231 00260 GL 1997 12 31 EY2R9600322 3 19960201 G 6110 C4451 FERRULE CESSNA 310 T310Q 2074244 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 739404 CORROSION FOUND ON FERRULE. 1 L 7 2 3O 3A10 5 C P22EA 1997123100261 19971231 00261 GL 1997 12 31 EY2R9600323 3 19960201 G 6110 C4451 FERRULE CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1655 780874 CORROSION FOUND ON FERRULE. 1 L 7 2 3O 3A10 5 C P22EA 1997123100262 19971231 00262 GL 1997 12 31 EY2R9600324 3 19960201 G 6110 C4451 FERRULE CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1655 790739 CORROSION FOUND ON FERRULE. 1 L 7 2 3O 3A10 5 C P22EA 1997123100263 19971231 00263 GL 1997 12 31 EY2R9600325 3 19960201 G 6110 C4451 FERRULE CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 800234 CORROSION FOUND ON FERRULE. 1 L 7 2 3O 3A10 5 C P22EA 1997123100264 19971231 00264 GL 1997 12 31 EY2R9600326 3 19960201 G 6114 D7015C87 HUB CESSNA 310 T310Q 2074244 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 739404 HUB FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100265 19971231 00265 GL 1997 12 31 EY2R9600327 3 19960201 G 6114 D7015C87 HUB CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1655 780874 HUB FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100266 19971231 00266 GL 1997 12 31 EY2R9600328 3 19960201 G 6114 D7015C87 HUB CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 790297 HUB FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100267 19971231 00267 GL 1997 12 31 EY2R9600329 3 19960201 G 6114 D7015C87 HUB CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 790628 HUB FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100268 19971231 00268 GL 1997 12 31 EY2R9600330 3 19960201 G 6114 D7015C87 HUB CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 790739 HUB FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100269 19971231 00269 GL 1997 12 31 EY2R9600331 3 19960201 G 6114 D7015C87 HUB CESSNA 310 T310Q 2074244 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 800234 HUB FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100270 19971231 00270 GL 1997 12 31 EY2R9600332 3 19960201 G 6111 S82NC4 BLADE CESSNA 310 T310Q 2074244 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 739404 BLADE, SN F45471YS, FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100271 19971231 00271 GL 1997 12 31 EY2R9600333 3 19960201 G 6111 S82NC4 BLADE CESSNA 310 T310Q 2074244 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 739404 BLADE, SN F45225YS, FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100272 19971231 00272 GL 1997 12 31 EY2R9600334 3 19960201 G 6111 S82NC4 BLADE CESSNA 310 T310Q 2074244 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 739404 BLADE, SN F45244YS, FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100273 19971231 00273 GL 1997 12 31 EY2R9600335 3 19960201 G 6111 S82NC4 BLADE CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 790297 BLADE, SN K92607, FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100274 19971231 00274 GL 1997 12 31 EY2R9600336 3 19960201 G 6111 S82NC4 BLADE CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 790297 BLADE, SN K92081, FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100275 19971231 00275 GL 1997 12 31 EY2R9600337 3 19960201 G 6111 S82NC4 BLADE CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 790297 BLADE, SN K92608, FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100276 19971231 00276 GL 1997 12 31 EY2R9600338 3 19960201 G 6111 S82NC4 BLADE CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 790628 BLADE, SN EB140, FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100277 19971231 00277 GL 1997 12 31 EY2R9600339 3 19960201 G 6111 S82NC4 BLADE CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 790628 BLADE, SN EF120, FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100278 19971231 00278 GL 1997 12 31 EY2R9600340 3 19960201 G 6111 S82NC4 BLADE CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 790628 BLADE, SN EF094, FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100279 19971231 00279 GL 1997 12 31 EY2R9600341 3 19960201 G 6111 S82NC55 BLADE CESSNA 402 402B 207590P CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 709 761779 BLADE, SN K99017YS, FOUND CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100280 19971231 00280 GL 1997 12 31 EY2R9600342 3 19960201 G 6111 S82NC55 BLADE CESSNA 402 402B 207590P CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 709 761779 BLADE, SN K98877YS, FOUND CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100281 19971231 00281 GL 1997 12 31 EY2R9600343 3 19960201 G 6111 S82NC55 BLADE CESSNA 402 402B 207590P CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 709 761779 BLADE, SN K98973YS, FOUND CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100282 19971231 00282 GL 1997 12 31 EY2R9600344 3 19960201 G 6111 S82NC55 BLADE CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1655 780874 BLADE, SN K96093YS, FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100283 19971231 00283 GL 1997 12 31 EY2R9600345 3 19960201 G 6111 S82NC55 BLADE CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1655 780874 BLADE, SN K95783YS, FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100284 19971231 00284 GL 1997 12 31 EY2R9600346 3 19960201 G 6111 S82NC55 BLADE CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1655 780874 BLADE, SN K95918YS, FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100285 19971231 00285 GL 1997 12 31 EY2R9600347 3 19960201 G 6111 S82NC55 BLADE CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 790739 BLADE, SN K96121YS, FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100286 19971231 00286 GL 1997 12 31 EY2R9600348 3 19960201 G 6111 S82NC55 BLADE CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 790739 BLADE, SN K95793YS, FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100287 19971231 00287 GL 1997 12 31 EY2R9600349 3 19960201 G 6111 S82NC55 BLADE CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 790739 BLADE, SN K95795YS, FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100288 19971231 00288 GL 1997 12 31 EY2R9600350 3 19960201 G 6111 S82NC55 BLADE CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 800234 BLADE, SN K86543, FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100289 19971231 00289 GL 1997 12 31 EY2R9600351 3 19960201 G 6111 S82NC55 BLADE CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 800234 BLADE, SN K85795, FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100290 19971231 00290 GL 1997 12 31 EY2R9600352 3 19960201 G 6111 S82NC55 BLADE CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 800234 BLADE, SN K85902, FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100291 19971231 00291 GL 1997 12 31 EY2R9600353 3 19960201 G 6114 D7015C87 HUB CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 794034 HUB CORRODED. 1 L 7 2 3O RT 3A10 5 C P22EA 1997123100292 19971231 00292 GL 1997 12 31 EY2R9600354 3 19960201 G 6111 S82NC55 BLADE CESSNA 340 340CESSNA 2076404 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 773157 BLADE, SN F38706YS, FOUND CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997123100293 19971231 00293 GL 1997 12 31 EY2R9600355 3 19960201 G 6114 D7015C87 HUB CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 710420 HUB FOUND CORRODED. 1 L 7 2 3O RT 3A10 5 C P22EA 1997123100294 19971231 00294 GL 1997 12 31 EY2R9600356 3 19960201 G 6110 C2987 RETAIN BEARING CESSNA 340 340CESSNA 2076404 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 755740 RETAIN BEARING FOUND CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997123100295 19971231 00295 GL 1997 12 31 EY2R9600357 3 19960201 G 6110 A1896 CYLINDER PIN CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 780522 CYLINDER PIN CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100296 19971231 00296 GL 1997 12 31 EY2R9600358 3 19960201 G 6110 A4191 DOWEL CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 780522 DOWELL DISCOVERED TO BE CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100297 19971231 00297 GL 1997 12 31 EY2R9600359 3 19960201 G 6110 A1896 CYLINDER PIN CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 791430 CYLINDER PIN FOUND CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100298 19971231 00298 GL 1997 12 31 EY2R9600360 3 19960201 G 6110 A1896 CYLINDER PIN CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 7810050 CYLINDER PIN FOUND CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100299 19971231 00299 GL 1997 12 31 EY2R9600361 3 19960201 G 6110 A4191 DOWEL CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 791430 DOWEL DISCOVERED TO BE CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100300 19971231 00300 GL 1997 12 31 EY2R9600362 3 19960201 G 6110 A4191 DOWEL CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 7810050 DOWEL FOUND CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100301 19971231 00301 GL 1997 12 31 EY2R9600363 3 19960201 G 6110 C4191 DOWEL CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 780708 DOWEL FOUND CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100302 19971231 00302 GL 1997 12 31 EY2R9600364 3 19960201 G 6110 C7036 NUT CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 791430 NUT CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100303 19971231 00303 GL 1997 12 31 EY2R9600365 3 19960201 G 6110 C7036 NUT CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 7810050 NUT FOUND CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100304 19971231 00304 GL 1997 12 31 EY2R9600366 3 19960201 G 6110 2202 SPLIT BEARING BEECH 55 9555 1152702 CE HARTZL HCC2Y BHCC2YF2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3932 AN3034 FOUND CORROSION IN SPLIT BEARING. 1 L 7 2 3O 3A16 5 C P920 1997123100305 19971231 00305 GL 1997 12 31 EY2R9600367 3 19960201 G 6114 D4887C81 HUB CESSNA 310 310 2074202 CE MCAULY 2AF34C D2AF34C81 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 772913 HUB FOUND CORRODED. 1 L 7 2 3O RT 3A10 5 C P5EA 1997123100306 19971231 00306 GL 1997 12 31 EY2R9600368 3 19960201 G 6110 1303A BEARING PIPER PA24 PA24 7102402 SO HARTZL HC92Z HC92ZK8 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 5489 990L BEARING FOUND CORRODED. 1 L 7 1 3O 1A15 5 C P892 1997123100307 19971231 00307 GL 1997 12 31 EY2R9600369 3 19960201 G 6110 13088 PILOT TUBE PIPER PA24 PA24 7102402 SO HARTZL HC92Z HC92ZK8 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 5489 990L PILOT TUBE FOUND CORRODED. 1 L 7 1 3O 1A15 5 C P892 1997123100308 19971231 00308 GL 1997 12 31 EY2R9600370 3 19960201 G 6110 130195 CLAMP BEECH 90 B90 1152912 CE HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 CORROSION FOUND ON CLAMP. 1 L 7 2 3T 3A20 6 C P15EA 1997123100309 19971231 00309 GL 1997 12 31 EY2R9600371 3 19960201 G 6111 T10173B8 BLADE BEECH 90 B90 1152912 CE HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BLADE, SN 62744, FOUND CORRODED. 1 L 7 2 3T 3A20 6 C P15EA 1997123100310 19971231 00310 GL 1997 12 31 EY2R9600372 3 19960201 G 6110 1851T BEARING BEECH 100 100BEECH 1152916 CE HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BU10928 BEARING FOUND CORRODED. 1 L 7 2 3T A14CE 6 C P15EA 1997123100311 19971231 00311 GL 1997 12 31 EY2R9600373 3 19960201 G 6110 5862 PTCH CHG ROD BEECH 100 100BEECH 1152916 CE HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1322 BU2699 PITCH CHANGE ROD FOUND BENT. 1 L 7 2 3T A14CE 6 C P15EA 1997123100312 19971231 00312 GL 1997 12 31 EY2R9600374 3 19960201 G 6110 1851T BEARING PIPER PA31T PA31T 7103124 SO HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BU3995 BEARING FOUND WITH CORROSION. 1 L 7 2 3T A8EA 6 C P15EA 1997123100313 19971231 00313 GL 1997 12 31 EY2R9600375 3 19960201 G 6110 1851T BEARING MTSBSI MU2 MU2* SW HARTZL HCB3T HCB3TN5 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BU2089 BEARING FOUND WITH CORROSION. 1 H 7 2 3T A2PC 6 C P15EA 1997123100314 19971231 00314 GL 1997 12 31 EY2R9600376 3 19960201 G 6110 1851T BEARING BEECH 35 B35 1151506 CE HARTZL HCB4M HCB4MP3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 FW1010 BEARING FOUND WITH CORROSION. 1 L 7 1 3O A777 6 C P56GL 1997123100315 19971231 00315 GL 1997 12 31 EY2R9600377 3 19960201 G 6114 4993 HUB BEECH 200 200BEECH 1152920 CE HARTZL HCD4N3 HCD4N3A GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 4131 2448 FY35A HUB FOUND CORRODED. 1 L 7 2 4T A24CE 5 C STC 1997123100316 19971231 00316 GL 1997 12 31 EY2R9600378 3 19960201 G 6110 2202 SPLIT BEARING PIPER PA32 PA32* SO HARTZL HCE2Y HCE2YR2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2715 BP715 SPLIT BEARING FOUND CORRODED. 1 L 7 1 3O A3SO 5 C P9EA 1997123100317 19971231 00317 GL 1997 12 31 EY2R9600379 3 19960201 G 6110 2202 SPLIT BEARING PIPER PA23 PA23250 7102308 SO HARTZL HCE2Y HCE2YR2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BP9059 SPLIT BEARING FOUND CORRODED. 1 L 7 2 3O 1A10 5 C P9EA 1997123100318 19971231 00318 GL 1997 12 31 EY2R9600380 3 19960201 G 6110 2431 BOLT BEECH 33 F33 1151423 CE HARTZL HCC3Y PHCC3YF1 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2030 EE1402 CORROSION FOUND ON BOLT. 1 L 7 1 3O 3A15 5 C P25EA 1997123100319 19971231 00319 GL 1997 12 31 EY2R9600381 3 19960201 G 6114 32518R HUB BEECH 33 F33 1151423 CE HARTZL HCC3Y PHCC3YF1 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2030 EE1402 HUB, SN EE1402, FOUND CORRODED. 1 L 7 1 3O 3A15 5 C P25EA 1997123100320 19971231 00320 GL 1997 12 31 EY2R9600382 3 19960301 G 6114 C3910C201 HUB MCAULY 2A34C 2A34C201 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 725913 HUB FOUND CORRODED. 5 C P3EA 1997123100321 19971231 00321 GL 1997 12 31 EY2R9600383 3 19960301 G 6114 C3910C201 HUB CESSNA 180 180 2072602 CE MCAULY 2A34C 2A34C201 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 700261 CORROSION FOUND ON HUB. 1 H 7 1 3O NC 5A6 5 C P3EA 1997123100322 19971231 00322 GL 1997 12 31 EY2R9600384 3 19960301 G 6110 A4001 DOWEL CESSNA 182 182 2072702 CE MCAULY 2A34C 2A34C203 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2804 535 750557 CORROSION FOUND ON DOWEL. 1 H 7 1 3O NT 3A13 5 C P3EA 1997123100323 19971231 00323 GL 1997 12 31 EY2R9600385 3 19960301 G 6114 C5480C66 HUB CESSNA 182 182 2072702 CE MCAULY 2A34C 2A34C66 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 754537 CORROSION FOUND ON HUB. 1 H 7 1 3O NT 3A13 5 C P3EA 1997123100324 19971231 00324 GL 1997 12 31 EY2R9600386 3 19960301 G 6110 C2464 FERRULE CESSNA 182 182 2072702 CE MCAULY 2A36C 2A36C29 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2436 797 61275 FERRULE CORRODED. 1 H 7 1 3O NT 3A13 5 C P880 1997123100325 19971231 00325 GL 1997 12 31 EY2R9600387 3 19960301 G 6111 82NDB2 BLADE BEECH 36 A36 1151604 CE MCAULY 3A32C 3A32C406 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BLADE, SN BF319, FOUND CORRODED. 1 L 7 1 3O 3A15 5 C P21EA 1997123100326 19971231 00326 GL 1997 12 31 EY2R9600388 3 19960301 G 6111 82NDB2 BLADE BEECH 36 A36 1151604 CE MCAULY 3A32C 3A32C406 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BLADE, SN BF307, FOUND CORRODED. 1 L 7 1 3O 3A15 5 C P21EA 1997123100327 19971231 00327 GL 1997 12 31 EY2R9600389 3 19960301 G 6111 82NDB2 BLADE BEECH 36 A36 1151604 CE MCAULY 3A32C 3A32C406 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BLADE, SN BF318, FOUND CORRODED. 1 L 7 1 3O 3A15 5 C P21EA 1997123100328 19971231 00328 GL 1997 12 31 EY2R9600390 3 19960301 G 6110 C4001 DOWEL BEECH 36 A36 1151604 CE MCAULY 3A32C 3A32C76 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 815822 DOWEL FOUND CORRODED. 1 L 7 1 3O 3A15 5 C P21EA 1997123100329 19971231 00329 GL 1997 12 31 EY2R9600391 3 19960301 G 6110 A1896 CYLINDER PIN CESSNA 303 T303 2073820 CE MCAULY 3AF32C 3AF32C506 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 820713 CYLINDER PIN FOUND CORRODED. 1 L 7 2 3O A34CE 5 C P57GL 1997123100330 19971231 00330 GL 1997 12 31 EY2R9600392 3 19960301 G 6110 A4191 DOWEL CESSNA 303 T303 2073820 CE MCAULY 3AF32C 3AF32C506 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 820713 CORROSION FOUND ON DOWEL. 1 L 7 2 3O A34CE 5 C P57GL 1997123100331 19971231 00331 GL 1997 12 31 EY2R9600393 3 19960301 G 6110 A1896 CYLINDER PIN CESSNA 303 T303 2073820 CE MCAULY 3AF32C 3AF32C507 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 820985 CYLINDER PIN CORRODED. 1 L 7 2 3O A34CE 5 C P57GL 1997123100332 19971231 00332 GL 1997 12 31 EY2R9600394 3 19960301 G 6110 A4191 DOWEL CESSNA 303 T303 2073820 CE MCAULY 3AF32C 3AF32C507 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 820985 CORROSION FOUND ON DOWEL. 1 L 7 2 3O A34CE 5 C P57GL 1997123100333 19971231 00333 GL 1997 12 31 EY2R9600395 3 19960301 G 6111 S82N4 BLADE CESSNA 320 320D 2074512 CE MCAULY 3AF32C 3AF32C72 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BLADE, SN C89048YS, FOUND CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997123100334 19971231 00334 GL 1997 12 31 EY2R9600396 3 19960301 G 6111 S82N4 BLADE CESSNA 320 320D 2074512 CE MCAULY 3AF32C 3AF32C72 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BLADE, SN 31160YS, FOUND CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997123100335 19971231 00335 GL 1997 12 31 EY2R9600397 3 19960301 G 6114 D7015C72 HUB CESSNA 320 320D 2074512 CE MCAULY 3AF32C 3AF32C72 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 690905 CORROSION FOUND ON HUB. 1 L 7 2 3O 3A25 5 C P22EA 1997123100336 19971231 00336 GL 1997 12 31 EY2R9600398 3 19960301 G 6114 D7015C87 HUB CESSNA 402 402CESSNA 207590K CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 754662 CORROSION FOUND ON HUB. 1 L 7 2 3O A7CE 5 C P22EA 1997123100337 19971231 00337 GL 1997 12 31 EY2R9600399 3 19960301 G 6110 A1896 CYLINDER PIN CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 753352 CORROSION FOUND ON CYLINDER PIN. 1 L 7 2 3O 3A10 5 C P22EA 1997123100338 19971231 00338 GL 1997 12 31 EY2R9600400 3 19960301 G 6110 A4191 DOWEL CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 753352 DOWEL PIN CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100339 19971231 00339 GL 1997 12 31 EY2R9600401 3 19960301 G 6110 B3490 PISTON ROD PIN CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 753352 CORROSION FOUND ON PISTON ROD PIN. 1 L 7 2 3O 3A10 5 C P22EA 1997123100340 19971231 00340 GL 1997 12 31 EY2R9600402 3 19960301 G 6110 C7036 NUT CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 753352 NUT CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100341 19971231 00341 GL 1997 12 31 EY2R9600403 3 19960301 G 6110 A1896 CYLINDER PIN CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 727522 CORROSION FOUND ON CYLINDER PIN. 1 L 7 2 3O 3A10 5 C P22EA 1997123100342 19971231 00342 GL 1997 12 31 EY2R9600404 3 19960301 G 6110 A1896 CYLINDER PIN CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 7810424 CORROSION FOUND ON CYLINDER PIN. 1 L 7 2 3O 3A10 5 C P22EA 1997123100343 19971231 00343 GL 1997 12 31 EY2R9600405 3 19960301 G 6110 A4191 DOWEL CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 727522 DOWEL CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100344 19971231 00344 GL 1997 12 31 EY2R9600406 3 19960301 G 6110 A4191 DOWEL CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 7810424 DOWEL CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100345 19971231 00345 GL 1997 12 31 EY2R9600407 3 19960301 G 6110 B3490 PISTON ROD PIN CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 7810424 CORROSION FOUND ON PISTON ROD PIN. 1 L 7 2 3O 3A10 5 C P22EA 1997123100346 19971231 00346 GL 1997 12 31 EY2R9600408 3 19960301 G 6110 C7036 NUT CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 727514 NUT CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100347 19971231 00347 GL 1997 12 31 EY2R9600409 3 19960301 G 6110 C7036 NUT CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 727522 NUT CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100348 19971231 00348 GL 1997 12 31 EY2R9600410 3 19960301 G 6114 D7015C87 HUB CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 727514 CORROSION FOUND ON HUB. 1 L 7 2 3O 3A10 5 C P22EA 1997123100349 19971231 00349 GL 1997 12 31 EY2R9600411 3 19960301 G 6114 D7015C87 HUB CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 727522 CORROSION FOUND ON HUB. 1 L 7 2 3O 3A10 5 C P22EA 1997123100350 19971231 00350 GL 1997 12 31 EY2R9600412 3 19960301 G 6110 A1896 CYLINDER PIN CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 765319 CORROSION FOUND ON CYLINDER PIN. 1 L 7 2 3O 3A10 5 C P22EA 1997123100351 19971231 00351 GL 1997 12 31 EY2R9600413 3 19960301 G 6110 A4191 DOWEL CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 765319 DOWEL CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100352 19971231 00352 GL 1997 12 31 EY2R9600414 3 19960301 G 6110 C7036 NUT CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 765319 NUT CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100353 19971231 00353 GL 1997 12 31 EY2R9600415 3 19960301 G 6114 D7015C87 HUB CESSNA 402 402A 207590M CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 791892 CORROSION FOUND ON HUB. 1 L 7 2 3O A7CE 5 C P22EA 1997123100354 19971231 00354 GL 1997 12 31 EY2R9600416 3 19960301 G 6110 C2987 RETAIN BEARING CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 791238 RETAIN BEARING FOUND CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997123100355 19971231 00355 GL 1997 12 31 EY2R9600417 3 19960301 G 6110 A1896 CYLINDER PIN CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3406 1101 779611 CYLINDER PIN CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997123100356 19971231 00356 GL 1997 12 31 EY2R9600418 3 19960301 G 6110 A1896 CYLINDER PIN CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3406 1101 779760 CYLINDER PIN CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997123100357 19971231 00357 GL 1997 12 31 EY2R9600419 3 19960301 G 6110 A4191 DOWEL CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3406 1101 779611 CORROSION ON DOWEL. 1 L 7 2 3O 3A25 5 C P22EA 1997123100358 19971231 00358 GL 1997 12 31 EY2R9600420 3 19960301 G 6110 A4191 DOWEL CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3406 1101 779760 CORROSION ON DOWELL. 1 L 7 2 3O 3A25 5 C P22EA 1997123100359 19971231 00359 GL 1997 12 31 EY2R9600421 3 19960301 G 6110 C2987 RETAIN BEARING CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3406 1101 779760 RETAIN BEARING CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997123100360 19971231 00360 GL 1997 12 31 EY2R9600422 3 19960301 G 6110 C7036 NUT CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3406 1101 779611 CORROSION FOUND ON NUT. 1 L 7 2 3O 3A25 5 C P22EA 1997123100361 19971231 00361 GL 1997 12 31 EY2R9600423 3 19960301 G 6111 S82NC55 BLADE CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3406 1101 779611 BLADE, SN F81396YS, FOUND CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997123100362 19971231 00362 GL 1997 12 31 EY2R9600424 3 19960301 G 6111 S82NC55 BLADE CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3406 1101 779611 BLADE, SN K86826YS, FOUND CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997123100363 19971231 00363 GL 1997 12 31 EY2R9600425 3 19960301 G 6114 D7015C93 HUB CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 782374 CORROSION FOUND ON HUB. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100364 19971231 00364 GL 1997 12 31 EY2R9600426 3 19960301 G 6114 D7015C93 HUB CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 779171 CORROSION FOUND ON HUB. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100365 19971231 00365 GL 1997 12 31 EY2R9600427 3 19960301 G 6111 S82NC55 BLADE CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BLADE, SN F41011YS, FOUND CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100366 19971231 00366 GL 1997 12 31 EY2R9600428 3 19960301 G 6111 S82NC55 BLADE CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 737636 BLADE, SN F40982YS, FOUND CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100367 19971231 00367 GL 1997 12 31 EY2R9600429 3 19960301 G 6111 S82NC55 BLADE CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 737636 BLADE, SN F90645YS, FOUND CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100368 19971231 00368 GL 1997 12 31 EY2R9600430 3 19960301 G 6111 S82NC55 BLADE CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 737636 BLADE, SN F41010YS, FOUND CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100369 19971231 00369 GL 1997 12 31 EY2R9600431 3 19960301 G 6110 A1896 CYLINDER PIN CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 789634 CORROSION FOUND ON CYLINDER PIN. 1 L 7 2 3O 3A25 5 C P22EA 1997123100370 19971231 00370 GL 1997 12 31 EY2R9600432 3 19960301 G 6110 A1896 CYLINDER PIN CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 794049 CORROSION FOUND ON CYLINDER PIN. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100371 19971231 00371 GL 1997 12 31 EY2R9600433 3 19960301 G 6110 A4191 DOWEL CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 789634 CORROSION FOUND ON DOWEL. 1 L 7 2 3O 3A25 5 C P22EA 1997123100372 19971231 00372 GL 1997 12 31 EY2R9600434 3 19960301 G 6110 A4191 DOWEL CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 794049 CORROSION FOUND ON DOWEL. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100373 19971231 00373 GL 1997 12 31 EY2R9600435 3 19960301 G 6110 B4459 BLADE ACT PIN CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 789634 CORROSION FOUND ON BLADE ACT. PIN 1 L 7 2 3O 3A25 5 C P22EA 1997123100374 19971231 00374 GL 1997 12 31 EY2R9600436 3 19960301 G 6110 C2987 RETAIN BEARING CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 789634 RETAIN BEARING FOUND WITH CORROSION. 1 L 7 2 3O 3A25 5 C P22EA 1997123100375 19971231 00375 GL 1997 12 31 EY2R9600437 3 19960301 G 6110 C3550 FEATHER CYLINDER CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 802952 FEATHER CYLINDER FOUND CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997123100376 19971231 00376 GL 1997 12 31 EY2R9600438 3 19960301 G 6110 C7036 NUT CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 794049 CORROSION FOUND ON NUT. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100377 19971231 00377 GL 1997 12 31 EY2R9600439 3 19960301 G 6110 C4450 FERRULE CESSNA 421 421A 2076012 CE MCAULY 3AF34C 3AF34C92 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 727005 CORROSION FOUND ON FERRULE. 1 L 7 2 3O A7CE 5 C P22EA 1997123100378 19971231 00378 GL 1997 12 31 EY2R9600440 3 19960301 G 6110 C7036 NUT CESSNA 421 421A 2076012 CE MCAULY 3AF34C 3AF34C92 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 727005 NUT CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100379 19971231 00379 GL 1997 12 31 EY2R9600441 3 19960301 G 6114 D7019C92 HUB CESSNA 421 421A 2076012 CE MCAULY 3AF34C 3AF34C92 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 727005 CORROSION FOUND ON HUB. 1 L 7 2 3O A7CE 5 C P22EA 1997123100380 19971231 00380 GL 1997 12 31 EY2R9600442 3 19960301 G 6111 S90LF0 BLADE CESSNA 421 421A 2076012 CE MCAULY 3AF34C 3AF34C92 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 727005 BLADE, SN B16100YS, FOUND CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100381 19971231 00381 GL 1997 12 31 EY2R9600443 3 19960301 G 6110 A1896 CYLINDER PIN CESSNA 421 421A 2076012 CE MCAULY 3AF34C 3AF34C92 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 726157 CYLINDER PIN FOUND CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100382 19971231 00382 GL 1997 12 31 EY2R9600444 3 19960301 G 6110 A4191 DOWEL CESSNA 421 421A 2076012 CE MCAULY 3AF34C 3AF34C92 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 726157 DOWEL CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100383 19971231 00383 GL 1997 12 31 EY2R9600445 3 19960301 G 6110 C2987 RETAIN BEARING CESSNA 421 421A 2076012 CE MCAULY 3AF34C 3AF34C92 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 726157 RETAIN BEARING CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100384 19971231 00384 GL 1997 12 31 EY2R9600446 3 19960301 G 6110 C7036 NUT CESSNA 421 421A 2076012 CE MCAULY 3AF34C 3AF34C92 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 726157 NUT CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100385 19971231 00385 GL 1997 12 31 EY2R9600447 3 19960301 G 6114 D7019C92 HUB CESSNA 421 421A 2076012 CE MCAULY 3AF34C 3AF34C92 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 726157 HUB FOUND WITH CORROSION. 1 L 7 2 3O A7CE 5 C P22EA 1997123100386 19971231 00386 GL 1997 12 31 EY2R9600448 3 19960301 G 6110 A3267 ADAPTER CESSNA 310 310R 2074245 CE MCAULY 3AF34C 3AF34C92 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 765319 CORROSION FOUND ON ADAPTER. 1 L 7 2 3O 3A10 5 C P22EA 1997123100387 19971231 00387 GL 1997 12 31 EY2R9600449 3 19960301 G 6110 C4451 FERRULE CESSNA 310 310R 2074245 CE MCAULY 3AF34C 3AF34C92 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 765319 FERRULE CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100388 19971231 00388 GL 1997 12 31 EY2R9600450 3 19960301 G 6114 D7019C92 HUB CESSNA 421 421 2076010 CE MCAULY 3AF34C 3AF34C92 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 739711 CORROSION FOUND ON HUB. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100389 19971231 00389 GL 1997 12 31 EY2R9600451 3 19960301 G 6110 A1896 CYLINDER PIN CESSNA 421 421B 2076014 CE MCAULY 3AF34C 3AF34C92 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 813209 CORROSION FOUND ON CYLINDER PIN. 1 L 7 2 3O A7CE 5 C P22EA 1997123100390 19971231 00390 GL 1997 12 31 EY2R9600452 3 19960301 G 6110 B4459 BLADE ACT PIN CESSNA 421 421B 2076014 CE MCAULY 3AF34C 3AF34C92 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 813209 BLADE ACT PIN CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100391 19971231 00391 GL 1997 12 31 EY2R9600453 3 19960301 G 6110 A1896 CYLINDER PIN CESSNA 421 421C 2076016 CE MCAULY 3FF32 3FF32C501 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3139 1430 812966 CYLINDER PIN CORRODED. 1 L 7 2 3O A7CE 5 C P45GL 1997123100392 19971231 00392 GL 1997 12 31 EY2R9600454 3 19960301 G 6110 A4191 DOWEL CESSNA 421 421C 2076016 CE MCAULY 3FF32 3FF32C501 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3139 1430 812966 DOWEL CORRODED. 1 L 7 2 3O A7CE 5 C P45GL 1997123100393 19971231 00393 GL 1997 12 31 EY2R9600455 3 19960301 G 6110 A1896 CYLINDER PIN CESSNA 421 421C 2076016 CE MCAULY 3FF32 3FF32C501 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2594 702 757208 CYLINDER PIN CORRODED. 1 L 7 2 3O A7CE 5 C P45GL 1997123100394 19971231 00394 GL 1997 12 31 EY2R9600456 3 19960301 G 6110 A1896 CYLINDER PIN CESSNA 421 421C 2076016 CE MCAULY 3FF32 3FF32C501 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2594 702 930080 CYLINDER PIN CORRODED. 1 L 7 2 3O A7CE 5 C P45GL 1997123100395 19971231 00395 GL 1997 12 31 EY2R9600457 3 19960301 G 6110 A4191 DOWEL CESSNA 421 421C 2076016 CE MCAULY 3FF32 3FF32C501 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2594 702 757208 DOWEL CORRODED. 1 L 7 2 3O A7CE 5 C P45GL 1997123100396 19971231 00396 GL 1997 12 31 EY2R9600458 3 19960301 G 6110 A4191 DOWEL CESSNA 421 421C 2076016 CE MCAULY 3FF32 3FF32C501 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2594 702 930080 DOWEL CORRODED. 1 L 7 2 3O A7CE 5 C P45GL 1997123100397 19971231 00397 GL 1997 12 31 EY2R9600459 3 19960301 G 6110 B48201 ACT PIN ASSY CESSNA 421 421C 2076016 CE MCAULY 3FF32 3FF32C501 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2594 702 757208 ACT PIN ASSY CORRODED. 1 L 7 2 3O A7CE 5 C P45GL 1997123100398 19971231 00398 NE 1997 12 31 EY2R9600460 3 19960301 G 6110 D40354 SLIP RING SWRNGN SA227 SA227AC 8780603 SW MCAULY 4HFR34 4HFR34C652 NE PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1956 911610 SLIP RING FOUND CORRODED. 2 L 7 2 4T RT A8SW 6 C 3PNE 1997123100399 19971231 00399 GL 1997 12 31 EY2R9600461 3 19960301 G 6114 C5078C220 HUB CESSNA 172 172RG 2072438 CE MCAULY 2D34C B2D34C220 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 881543 CORROSION FOUND ON HUB. 1 H 7 1 3O 3A17 5 C P7EA 1997123100400 19971231 00400 GL 1997 12 31 EY2R9600462 3 19960301 G 6114 220118 HUB PIPER PA34 PA34220T 7103420 SO HARTZL HCC2Y BHCC2YF2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 AN750 CORROSION FOUND ON HUB. 1 L 7 2 3O A7SO 5 C P920 1997123100401 19971231 00401 GL 1997 12 31 EY2R9600463 3 19960301 G 6114 220118 HUB PIPER PA34 PA34220T 7103420 SO HARTZL HCC2Y BHCC2YF2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 AN3392 CORROSION FOUND ON HUB. 1 L 7 2 3O A7SO 5 C P920 1997123100402 19971231 00402 GL 1997 12 31 EY2R9600464 3 19960301 G 6110 2202 SPLIT BEARING BEECH 55 E55 1152732 CE HARTZL HCJ2Y BHCJ2YF2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 DZ117 CORROSION FOUND ON SPLIT BEARING. 1 L 7 2 3O 3A16 5 C P37EA 1997123100403 19971231 00403 GL 1997 12 31 EY2R9600465 3 19960301 G 6114 D6603C88 HUB CESSNA 206 P206 2073304 CE MCAULY 3A32C D3A32C88 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 740892 HUB CORRODED. 1 H 7 1 3O A4CE 5 C P21EA 1997123100404 19971231 00404 GL 1997 12 31 EY2R9600466 3 19960301 G 6114 D6603C88 HUB CESSNA 206 P206 2073304 CE MCAULY 3A32C D3A32C88 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 805990 HUB CORRODED. 1 H 7 1 3O A4CE 5 C P21EA 1997123100405 19971231 00405 GL 1997 12 31 EY2R9600467 3 19960301 G 6110 A4001 DOWEL TMPSON NAVION NAVIONH 6150122 SW MCAULY 3A32C D3A32C90 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 745434 CORROSION FOUND ON DOWEL. 1 L 7 1 3O A782 5 C P21EA 1997123100406 19971231 00406 GL 1997 12 31 EY2R9600468 3 19960301 G 6114 D5904C90 HUB CESSNA 206 206CESSNA 2073302 CE MCAULY 3A32C D3A32C90 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 739418 HUB CORRODED. 1 H 7 1 3O A4CE 5 C P21EA 1997123100407 19971231 00407 GL 1997 12 31 EY2R9600469 3 19960301 G 6110 14962 PILOT TUBE TMPSON NAVION NAVION* 6150130 SW HARTZL HC82V HC82V* GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 F1961 CORROSION FOUND ON PILOT TUBE. 1 L 7 1 3O A782 5 C P23EA 1997123100408 19971231 00408 GL 1997 12 31 EY2R9600470 3 19960301 G 6110 83810 CLAMP TMPSON NAVION NAVION* 6150130 SW HARTZL HC82V HC82V* GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 F1961 CLAMP CORRODED. 1 L 7 1 3O A782 5 C P23EA 1997123100409 19971231 00409 GL 1997 12 31 EY2R9600471 3 19960301 G 6110 83811 CLAMP PIPER PA23 PA23150 7102303 CE HARTZL HC82 HC82VL2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 K2739N CLAMP CORRODED. 1 L 7 2 3O RT 1A10 5 C P23EA 1997123100410 19971231 00410 GL 1997 12 31 EY2R9600472 3 19960301 G 6110 83811 CLAMP PIPER PA23 PA23150 7102303 CE HARTZL HC82 HC82VL2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 K306 CLAMP CORRODED. 1 L 7 2 3O RT 1A10 5 C P23EA 1997123100411 19971231 00411 GL 1997 12 31 EY2R9600473 3 19960301 G 6110 14B BEARING HARTZL HC82X HC82XF1 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 T349 BEARING CORRODED. 5 C P878 1997123100412 19971231 00412 GL 1997 12 31 EY2R9600474 3 19960301 G 6110 8382 CLAMP HARTZL HC82X HC82XF1 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 T349 CLAMP CORRODED. 5 C P878 1997123100413 19971231 00413 GL 1997 12 31 EY2R9600475 3 19960301 G 6114 84019B HUB HARTZL HC82X HC82XF1 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 T349 CORROSION FOUND ON HUB. 5 C P878 1997123100414 19971231 00414 GL 1997 12 31 EY2R9600476 3 19960301 G 6110 969 SPLIT RING HARTZL HC82X HC82XF1 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 T349 SPLIT RING CORRODED. 5 C P878 1997123100415 19971231 00415 GL 1997 12 31 EY2R9600477 3 19960301 G 6111 V843310 BLADE PIPER PA23 PA23250 7102308 SO HARTZL HCA2X HCA2XK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BLADE, SN 90218, FOUND CORRODED. 1 L 7 2 3O 1A10 5 C P908 1997123100416 19971231 00416 GL 1997 12 31 EY2R9600478 3 19960301 G 6110 1851T BEARING GULSTM G73 G73 3951802 SW HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 14430 2985 BU2127 BEARING CORRODED. 1 H 7 2 3R A783 6 C P15EA 1997123100417 19971231 00417 GL 1997 12 31 EY2R9600479 3 19960301 G 6110 790100018 STEEL BALL GULSTM G73 G73 3951802 SW HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BU1860 STEEL BALL CORRODED. 1 H 7 2 3R A783 6 C P15EA 1997123100418 19971231 00418 GL 1997 12 31 EY2R9600480 3 19960301 G 6110 83867 CLAMP GULSTM G73 G73 3951802 SW HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 14430 2985 BU2127 CLAMP CORRODED. 1 H 7 2 3R A783 6 C P15EA 1997123100419 19971231 00419 GL 1997 12 31 EY2R9600481 3 19960301 G 6114 220117 HUB PIPER PA32 PA32260 7103206 SO HARTZL HCC2Y HCC2YK1 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 CH4094 CORROSION FOUND ON HUB. 1 L 7 1 3O A3SO 5 C P920 1997123100420 19971231 00420 GL 1997 12 31 EY2R9600482 3 19960301 G 6111 F84772 BLADE PIPER PA32 PA32260 7103206 SO HARTZL HCC2Y HCC2YK1 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 CH4094 BLADE, SN D4042, FOUND CORRODED. 1 L 7 1 3O A3SO 5 C P920 1997123100421 19971231 00421 GL 1997 12 31 EY2R9600483 3 19960301 G 6110 2202 SPLIT BEARING CESSNA 182 182 2072702 CE HARTZL HCC3Y HCC3YF1 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1873 168 EC176 CORROSION FOUND ON SPLIT BEARING. 1 H 7 1 3O NT 3A13 5 C P25EA 1997123100422 19971231 00422 GL 1997 12 31 EY2R9600484 3 19960301 G 6114 32511R HUB PIPER PA28 PA28R200 7102811 SO HARTZL HCC3Y HCC3YR GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 DY60 HUB FOUND CORRODED. 1 L 7 1 3O 2A13 5 C P25EA 1997123100423 19971231 00423 GL 1997 12 31 EY2R9600485 3 19960301 G 6114 32511 HUB PIPER PA60 PA60600 7106001 NM HARTZL HCC3Y HCC3YR GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 CK1927 HUB FOUND CORRODED. 1 M 7 2 3O RT A17WE 5 C P25EA 1997123100424 19971231 00424 GL 1997 12 31 EY2R9600486 3 19960301 G 6110 790100016 STEEL BALL PIPER PA23 PA23250 7102308 SO HARTZL HCE2Y HCE2YR2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BP7785 STEEL BALL FOUND CORRODED. 1 L 7 2 3O 1A10 5 C P9EA 1997123100425 19971231 00425 GL 1997 12 31 EY2R9600487 3 19960301 G 6114 32857 HUB BEECH 58 58P 1152744 CE HARTZL HCJ3Y PHCJ3YF2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 ED2589 CORROSION FOUND ON HUB. 1 L 7 2 3O A23CE 5 C P36EA 1998010700007 19980107 00007 GL 1998 1 7 EY2R9600488 3 19960401 G 6114 D7037C80 HUB CESSNA 310 310L 2074230 CE MCAULY 3AF32C 3AF32C* GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 666083 CORROSION FOUND ON HUB. 1 L 7 2 3O 3A10 5 C P22EA 1998010700008 19980107 00008 GL 1998 1 7 EY2R9600489 3 19960401 G 6114 D7037C80 HUB CESSNA 310 310L 2074230 CE MCAULY 3AF32C 3AF32C* GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 769239 CORROSION FOUND ON HUB. 1 L 7 2 3O 3A10 5 C P22EA 1997123100426 19971231 00426 GL 1997 12 31 EY2R9600490 3 19960401 G 6110 C2987 RETAIN BEARING CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 730410 RETAIN BEARING CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100427 19971231 00427 GL 1997 12 31 EY2R9600491 3 19960401 G 6110 C2987 RETAIN BEARING CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 731300 RETAIN BEARING CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100428 19971231 00428 GL 1997 12 31 EY2R9600492 3 19960401 G 6110 C2987 RETAIN BEARING CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 744241 RETAIN BEARING CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100429 19971231 00429 GL 1997 12 31 EY2R9600493 3 19960401 G 6110 C2987 RETAIN BEARING CESSNA 310 310P 2074238 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 766765 RETAIN BEARING CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100430 19971231 00430 GL 1997 12 31 EY2R9600494 3 19960401 G 6110 RETAIN BEARING CESSNA 402 402B 207590P CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 794953 RETAIN BEARING CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100431 19971231 00431 GL 1997 12 31 EY2R9600495 3 19960401 G 6114 D7015C87 HUB CESSNA 402 402CESSNA 207590K CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 673158 CORROSION FOUND ON HUB. 1 L 7 2 3O A7CE 5 C P22EA 1997123100432 19971231 00432 GL 1997 12 31 EY2R9600496 3 19960401 G 6110 A1896 CYLINDER PIN CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2454 1338 721970 CYLINDER PIN CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100433 19971231 00433 GL 1997 12 31 EY2R9600497 3 19960401 G 6110 A1896 CYLINDER PIN CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 784317 CYLINDER PIN CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100434 19971231 00434 GL 1997 12 31 EY2R9600498 3 19960401 G 6110 A1896 CYLINDER PIN CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2454 1338 7810422 CYLINDER PIN CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100435 19971231 00435 GL 1997 12 31 EY2R9600499 3 19960401 G 6110 A1896 CYLINDER PIN CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 733287 CYLINDER PIN CORRODED. 1 L 7 2 3O RT 3A10 5 C P22EA 1997123100436 19971231 00436 GL 1997 12 31 EY2R9600500 3 19960401 G 6110 A4191 DOWEL CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2454 1338 721970 DOWEL FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100437 19971231 00437 GL 1997 12 31 EY2R9600501 3 19960401 G 6110 A4191 DOWEL CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 733287 DOWEL FOUND CORRODED. 1 L 7 2 3O RT 3A10 5 C P22EA 1997123100438 19971231 00438 GL 1997 12 31 EY2R9600502 3 19960401 G 6110 A4191 DOWEL CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 733313 DOWEL FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100439 19971231 00439 GL 1997 12 31 EY2R9600503 3 19960401 G 6110 A4191 DOWEL CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 784317 DOWEL FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100440 19971231 00440 GL 1997 12 31 EY2R9600504 3 19960401 G 6110 A4191 DOWEL CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2454 1338 7810422 DOWEL FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100441 19971231 00441 GL 1997 12 31 EY2R9600505 3 19960401 G 6110 B4459 BLADE ACT PIN CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2454 1338 721970 BLADE ACT PIN FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100442 19971231 00442 GL 1997 12 31 EY2R9600506 3 19960401 G 6110 B4459 BLADE ACT PIN CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 733287 BLADE ACT PIN FOUND CORRODED. 1 L 7 2 3O RT 3A10 5 C P22EA 1997123100443 19971231 00443 GL 1997 12 31 EY2R9600507 3 19960401 G 6110 C2987 RETAIN BEARING CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2454 1338 721970 RETAIN BEARING FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100444 19971231 00444 GL 1997 12 31 EY2R9600508 3 19960401 G 6110 C2987 RETAIN BEARING CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 733287 RETAIN BEARING FOUND CORRODED. 1 L 7 2 3O RT 3A10 5 C P22EA 1997123100445 19971231 00445 GL 1997 12 31 EY2R9600509 3 19960401 G 6110 C2987 RETAIN BEARING CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2454 1338 7810422 RETAIN BEARING FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100446 19971231 00446 GL 1997 12 31 EY2R9600510 3 19960401 G 6110 C3550 FEATHER CYLINDER CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2454 1338 7810422 FEATHER CYLINDER CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100447 19971231 00447 GL 1997 12 31 EY2R9600511 3 19960401 G 6110 C4451 FERRULE CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2454 1338 721970 FERRULE FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100448 19971231 00448 GL 1997 12 31 EY2R9600512 3 19960401 G 6110 C4451 FERRULE CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 733287 FERRULE FOUND CORRODED. 1 L 7 2 3O RT 3A10 5 C P22EA 1997123100449 19971231 00449 GL 1997 12 31 EY2R9600513 3 19960401 G 6110 C4451 FERRULE CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2454 1338 7810422 FERRULE FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100450 19971231 00450 GL 1997 12 31 EY2R9600514 3 19960401 G 6110 C7036 NUT CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2454 1338 721970 CORROSION FOUND ON NUT. 1 L 7 2 3O 3A10 5 C P22EA 1997123100451 19971231 00451 GL 1997 12 31 EY2R9600515 3 19960401 G 6110 C7036 NUT CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 733287 CORROSION FOUND ON NUT. 1 L 7 2 3O RT 3A10 5 C P22EA 1997123100452 19971231 00452 GL 1997 12 31 EY2R9600516 3 19960401 G 6114 D7015C87 HUB CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 733313 HUB FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100453 19971231 00453 GL 1997 12 31 EY2R9600517 3 19960401 G 6110 C2987 RETAIN BEARING CESSNA 320 320E 2074514 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 747347 RETAIN BEARING FOUND CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997123100454 19971231 00454 GL 1997 12 31 EY2R9600518 3 19960401 G 6110 C2987 RETAIN BEARING CESSNA 320 320E 2074514 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 747406 RETAIN BEARING FOUND CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997123100455 19971231 00455 GL 1997 12 31 EY2R9600519 3 19960401 G 6110 C3475 NUT CESSNA 421 421B 2076014 CE MCAULY 3AF34C 3AF34C92 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 724578 NUT FOUND CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100456 19971231 00456 GL 1997 12 31 EY2R9600520 3 19960401 G 6110 C3550 FEATHER CYLINDER CESSNA 421 421B 2076014 CE MCAULY 3AF34C 3AF34C92 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 724578 FEATHER CYLINDER FOUND CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100457 19971231 00457 GL 1997 12 31 EY2R9600521 3 19960401 G 6110 A1896 CYLINDER PIN CESSNA 421 421 2076010 CE MCAULY 3AF34C 3AF34C92 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 775854 CYLINDER PIN CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100458 19971231 00458 GL 1997 12 31 EY2R9600522 3 19960401 G 6110 C7036 NUT CESSNA 421 421 2076010 CE MCAULY 3AF34C 3AF34C92 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 775854 CORROSION FOUND ON NUT. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100459 19971231 00459 GL 1997 12 31 EY2R9600523 3 19960401 G 6111 S90LF0 BLADE CESSNA 421 421 2076010 CE MCAULY 3AF34C 3AF34C92 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 775854 BLADE, SN B24646YS, FOUND CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100460 19971231 00460 GL 1997 12 31 EY2R9600524 3 19960401 G 6110 A1896 CYLINDER PIN CESSNA 421 421 2076010 CE MCAULY 3AF34C 3AF34C92 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 780456 CORROSION FOUND ON CYLINDER PIN. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100461 19971231 00461 GL 1997 12 31 EY2R9600525 3 19960401 G 6110 C5270 RETAIN BEARING CESSNA 172 172RG 2072438 CE MCAULY 2D34C B2D34C220 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1391 715 830266 RETAIN BEARING FOUND WITH CORROSION. 1 H 7 1 3O 3A17 5 C P7EA 1997123100462 19971231 00462 GL 1997 12 31 EY2R9600526 3 19960401 G 6110 2224 PROPELLER PIPER PA28 PA28* SO HARTZL HCC2Y BHCC2YF1 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3196 759 AM1840 PROPELLER ASSY FOUND CORRODED 1 L 7 1 3O 2A13 5 C P920 1997123100463 19971231 00463 GL 1997 12 31 EY2R9600527 3 19960401 G 6110 C2987 RETAIN BEARING CESSNA 185 185 2072802 CE MCAULY 2A34C D2A34C58 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 710952 RETAIN BEARING FOUND CORRODED. 1 H 7 1 3O NC 3A24 5 C P3EA 1997123100464 19971231 00464 GL 1997 12 31 EY2R9600528 3 19960401 G 6114 C2715C33 HUB CESSNA 210 210B 2073410 CE MCAULY 2A36C D2A36C33 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 605 745830 HUB FOUND WITH CORROSION. 1 H 7 1 3O 3A21 5 C P880 1997123100465 19971231 00465 GL 1997 12 31 EY2R9600529 3 19960401 G 6110 C2987 RETAIN BEARING CESSNA 210 210L 2073448 CE MCAULY 3A32C D3A32C88 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3830 921 752306 RETAIN BEARING FOUND CORRODED. 1 H 7 1 3O 3A21 5 C P21EA 1997123100466 19971231 00466 GL 1997 12 31 EY2R9600530 3 19960401 G 6110 A4001 DOWEL CESSNA 210 210 2073402 CE MCAULY D3A34 D3A34C402 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 801364 DOWEL CORRODED. 1 H 7 1 3O RT 3A21 5 C P47GL 1997123100467 19971231 00467 GL 1997 12 31 EY2R9600531 3 19960401 G 6110 B48202 ACT PIN ASSY CESSNA 210 210 2073402 CE MCAULY D3A34 D3A34C402 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 801364 ACT PIN ASSY FOUND CORRODED. 1 H 7 1 3O RT 3A21 5 C P47GL 1997123100468 19971231 00468 GL 1997 12 31 EY2R9600532 3 19960401 G 6110 C3903 SPLIT RETAINER CESSNA 210 210 2073402 CE MCAULY D3A34 D3A34C402 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 801364 CORROSION FOUND ON SPLIT RETAINER. 1 H 7 1 3O RT 3A21 5 C P47GL 1997123100469 19971231 00469 GL 1997 12 31 EY2R9600533 3 19960401 G 6110 14B BEARING CESSNA 180 180 2072602 CE HARTZL HC82V HC82V* GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 T1843N BEARING CORRODED. 1 H 7 1 3O NC 5A6 5 C P23EA 1997123100470 19971231 00470 GL 1997 12 31 EY2R9600534 3 19960401 G 6110 14B BEARING CESSNA 310 310G 2074218 CE HARTZL HC82V HC82V* GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1425 F1739 BEARING CORRODED. 1 L 7 2 3O 3A10 5 C P23EA 1997123100471 19971231 00471 GL 1997 12 31 EY2R9600535 3 19960401 G 6110 14A BEARING CESSNA 310 310A 2074204 CE HARTZL HC82X HC82XF2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 F2202 BEARING CORRODED. 1 L 7 2 3O 3A10 5 C P878 1997123100472 19971231 00472 GL 1997 12 31 EY2R9600536 3 19960401 G 6110 1496 PILOT TUBE PIPER PA24 PA24250 7102404 SO HARTZL HC82X HC82XK1 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 618G PILOT TUBE FOUND WITH CORROSION. 1 L 7 1 3O 1A15 5 C P878 1997123100473 19971231 00473 GL 1997 12 31 EY2R9600537 3 19960401 G 6110 1331 SPLIT RING BEECH 95 B95 1153404 CE HARTZL HC92W HC92WK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 320 1008F CORROSION FOUND ON SPLIT RING. 1 L 7 2 3O 3A16 5 C P16EA 1997123100474 19971231 00474 GL 1997 12 31 EY2R9600538 3 19960401 G 6110 1308 PILOT TUBE PIPER PA24 PA24 7102402 SO HARTZL HC92Z HC92ZK8 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1286L PILOT TUBE FOUND WITH CORROSION. 1 L 7 1 3O 1A15 5 C P892 1997123100475 19971231 00475 GL 1997 12 31 EY2R9600539 3 19960401 G 6110 1301A CLAMP BEECH 50 G50 1152532 CE HARTZL HC93Z HC93Z202 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1548A CLAMP CORRODED. 1 L 7 2 3O 5A4 5 C P891 1997123100476 19971231 00476 GL 1997 12 31 EY2R9600540 3 19960401 G 6110 1303A BEARING BEECH 50 G50 1152532 CE HARTZL HC93Z HC93Z202 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 690A BEARING CORRODED. 1 L 7 2 3O 5A4 5 C P891 1997123100477 19971231 00477 GL 1997 12 31 EY2R9600541 3 19960401 G 6110 1308 PILOT TUBE BEECH 50 G50 1152532 CE HARTZL HC93Z HC93Z202 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1548A PILOT TUBE FOUND WITH CORROSION. 1 L 7 2 3O 5A4 5 C P891 1997123100478 19971231 00478 GL 1997 12 31 EY2R9600542 3 19960401 G 6110 1308 PILOT TUBE BEECH 50 G50 1152532 CE HARTZL HC93Z HC93Z202 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 690A PILOT TUBE FOUND WITH CORROSION. 1 L 7 2 3O 5A4 5 C P891 1997123100479 19971231 00479 GL 1997 12 31 EY2R9600543 3 19960401 G 6110 83810 CLAMP CESSNA 320 320B 2074508 CE HARTZL HCA2V HCA2VF2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 Y2618 CLAMP CORRODED. 1 L 7 2 3O 3A25 5 C P24EA 1997123100480 19971231 00480 GL 1997 12 31 EY2R9600544 3 19960401 G 6110 1851T BEARING BEECH 100 100BEECH 1152916 CE HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BU392 CORROSION FOUND ON BEARING. 1 L 7 2 3T A14CE 6 C P15EA 1997123100481 19971231 00481 GL 1997 12 31 EY2R9600545 3 19960401 G 6110 1891A PILOT TUBE BEECH 100 100BEECH 1152916 CE HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BU392 PILOT TUBE FOUND CORRODED. 1 L 7 2 3T A14CE 6 C P15EA 1997123100482 19971231 00482 GL 1997 12 31 EY2R9600546 3 19960401 G 6114 84060 HUB BEECH 100 100BEECH 1152916 CE HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BU392 CORROSION FOUND ON HUB. 1 L 7 2 3T A14CE 6 C P15EA 1997123100483 19971231 00483 GL 1997 12 31 EY2R9600547 3 19960401 G 6110 83865 CLAMP EMB 110 EMB110* SO HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3669 BU11710 CLAMP CORRODED. 1 L 7 2 4T RT A21SO 6 C P15EA 1997123100484 19971231 00484 GL 1997 12 31 EY2R9600548 3 19960401 G 6110 18912A PILOT TUBE MTSBSI MU2 MU2B 5780404 SW HARTZL HCB3T HCB3TN5 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BV452 PILOT TUBE FOUND WITH CORROSION. 1 H 7 2 3T A2PC 6 C P15EA 1997123100485 19971231 00485 GL 1997 12 31 EY2R9600549 3 19960401 G 6110 1851T BEARING STBROS SD3 SD360 8100606 EU HARTZL HCB5M HCB5MP3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 22514 706 EV134 BEARING CORRODED. 2 H 7 2 4T A41EU 6 C P44GL 1997123100486 19971231 00486 GL 1997 12 31 EY2R9600550 3 19960401 G 6110 2432 BOLT CESSNA 172 172 2072402 CE HARTZL HCC2Y HCC2YK1 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 CH22812 BOLT FOUND CORRODED. 1 H 7 1 3O NT 3A12 5 C P920 1997123100487 19971231 00487 GL 1997 12 31 EY2R9600551 3 19960401 G 6114 220116 HUB PARTEN P68 P68B EU HARTZL HCC2Y HCC2YK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1625 AU4481 HUB FOUND CORRODED. 1 H 7 2 3O A31EU 5 C P920 1997123100488 19971231 00488 GL 1997 12 31 EY2R9600552 3 19960401 G 6111 FC7666A4 BLADE PARTEN P68 P68B EU HARTZL HCC2Y HCC2YK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1625 AU4481 BLADE, SN D11451, FOUND WITH CORROSION. 1 H 7 2 3O A31EU 5 C P920 1997123100489 19971231 00489 GL 1997 12 31 EY2R9600553 3 19960401 G 6111 FC7666A4 BLADE PARTEN P68 P68B EU HARTZL HCC2Y HCC2YK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1625 AU4481 BLADE, SN D11394, FOUND WITH CORROSION. 1 H 7 2 3O A31EU 5 C P920 1997123100490 19971231 00490 GL 1997 12 31 EY2R9600554 3 19960401 G 6110 2202 SPLIT BEARING PIPER PA30 PA30 7103002 SO HARTZL HCE2Y HCE2YL2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3456 960 BG125 CORROSION FOUND ON SPLIT BEARING. 1 L 7 2 3O A1EA 5 C P9EA 1997123100491 19971231 00491 GL 1997 12 31 EY2R9600555 3 19960401 G 6110 2202 SPLIT BEARING PIPER PA30 PA30 7103002 SO HARTZL HCE2Y HCE2YL2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3449 960 BG1600 CORROSION FOUND ON SPLIT BEARING. 1 L 7 2 3O A1EA 5 C P9EA 1997123100492 19971231 00492 GL 1997 12 31 EY2R9600556 3 19960401 G 6110 2202 SPLIT BEARING PIPER PA31 PA31350 7103110 SO HARTZL HCE3Y HCE3YR2A GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 758 DJ1538 CORROSION FOUND ON SPLIT BEARING. 1 L 7 2 3O A20SO 5 C P33EA 1997123100493 19971231 00493 GL 1997 12 31 EY2R9600557 3 19960501 G 6114 C3910C203 HUB CESSNA 182 182 2072702 CE MCAULY 2A34C 2A34C203 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 754900 HUB CORRODED. 1 H 7 1 3O NT 3A13 5 C P3EA 1997123100494 19971231 00494 GL 1997 12 31 EY2R9600558 3 19960501 G 6110 C3411 BEARING RACE CESSNA 172 172K 2072430 CE MCAULY 2A34C 2A34C203 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 800627 BEARING RACE CORRODED. 1 H 7 1 3O NT 3A12 5 C P3EA 1997123100495 19971231 00495 GL 1997 12 31 EY2R9600559 3 19960501 G 6114 C4211C76 HUB BEECH 36 36BEECH 1151602 CE MCAULY 3A32C 3A32C76 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 740263 HUB CORRODED. 1 L 7 1 3O 3A15 5 C P21EA 1997123100496 19971231 00496 GL 1997 12 31 EY2R9600560 3 19960501 G 6114 D6603C88 HUB CESSNA 210 210 2073402 CE MCAULY 3A32C 3A32C* GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 750803 HUB CORRODED. 1 H 7 1 3O RT 3A21 5 C P21EA 1997123100497 19971231 00497 GL 1997 12 31 EY2R9600561 3 19960501 G 6110 C5270 RETAIN BEARING CESSNA 414 414A 2075907 CE MCAULY 3AF32C 3AF32C505 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 821250 RETAIN BEARING FOUND CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100498 19971231 00498 GL 1997 12 31 EY2R9600562 3 19960501 G 6114 D5882C507 HUB CESSNA 303 T303 2073820 CE MCAULY 3AF32C 3AF32C507 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 815927 HUB CORRODED. 1 L 7 2 3O A34CE 5 C P57GL 1997123100499 19971231 00499 GL 1997 12 31 EY2R9600563 3 19960501 G 6111 G82NEB8 BLADE CESSNA 303 T303 2073820 CE MCAULY 3AF32C 3AF32C507 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BLADE, SN BH432, FOUND CORRODED. 1 L 7 2 3O A34CE 5 C P57GL 1997123100500 19971231 00500 GL 1997 12 31 EY2R9600564 3 19960501 G 6111 G82NEB8 BLADE CESSNA 303 T303 2073820 CE MCAULY 3AF32C 3AF32C507 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BLADE, SN BH434, FOUND CORRODED. 1 L 7 2 3O A34CE 5 C P57GL 1997123100501 19971231 00501 GL 1997 12 31 EY2R9600565 3 19960501 G 6111 G82NEB8 BLADE CESSNA 303 T303 2073820 CE MCAULY 3AF32C 3AF32C507 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BLADE, SN BI935, FOUND CORRODED. 1 L 7 2 3O A34CE 5 C P57GL 1997123100502 19971231 00502 GL 1997 12 31 EY2R9600566 3 19960501 G 6111 S82NC4 BLADE CESSNA 320 320F 2074516 CE MCAULY 3AF32C 3AF32C72 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 703825 BLADE, SN 31158YS, FOUND CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997123100503 19971231 00503 GL 1997 12 31 EY2R9600567 3 19960501 G 6111 S82NC4 BLADE CESSNA 320 320F 2074516 CE MCAULY 3AF32C 3AF32C72 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 760336 BLADE, SN C40376YS, FOUND CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997123100504 19971231 00504 GL 1997 12 31 EY2R9600568 3 19960501 G 6111 S82NB6 BLADE BEECH 55 9555 1152702 CE MCAULY 3AF32C 3AF32C75 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 783253 BLADE, SN K101554YS, FOUND CORRODED. 1 L 7 2 3O 3A16 5 C P22EA 1997123100505 19971231 00505 GL 1997 12 31 EY2R9600569 3 19960501 G 6110 C2987 RETAIN BEARING CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 747159 RETAIN BEARING FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100506 19971231 00506 GL 1997 12 31 EY2R9600570 3 19960501 G 6110 C2987 RETAIN BEARING CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 797174 RETAIN BEARING FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100507 19971231 00507 GL 1997 12 31 EY2R9600571 3 19960501 G 6110 C3475 NUT CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 747159 NUT CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100508 19971231 00508 GL 1997 12 31 EY2R9600572 3 19960501 G 6110 C2987 RETAIN BEARING CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 737905 RETAIN BEARING FOUND CORRODED. 1 L 7 2 3O RT 3A10 5 C P22EA 1997123100509 19971231 00509 GL 1997 12 31 EY2R9600573 3 19960501 G 6111 S82NC55 BLADE CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BLADE, SN F629YS, CORRODED. 1 L 7 2 3O RT 3A10 5 C P22EA 1997123100510 19971231 00510 GL 1997 12 31 EY2R9600574 3 19960501 G 6114 D7015C87 HUB CESSNA 401 401 207590C CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 751198 HUB CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100511 19971231 00511 GL 1997 12 31 EY2R9600575 3 19960501 G 6111 S82NC55 BLADE CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 787149 BLADE, SN K88765YS, FOUND CORRODED. 1 L 7 2 3O RT 3A10 5 C P22EA 1997123100512 19971231 00512 GL 1997 12 31 EY2R9600576 3 19960501 G 6110 C2987 RETAIN BEARING CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 726481 RETAIN BEARING FOUND WITH CORROSION. 1 L 7 2 3O RT 3A10 5 C P22EA 1997123100513 19971231 00513 GL 1997 12 31 EY2R9600577 3 19960501 G 6110 C4451 FERRULE CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 726481 FERRULE FOUND WITH CORROSION. 1 L 7 2 3O RT 3A10 5 C P22EA 1997123100514 19971231 00514 GL 1997 12 31 EY2R9600578 3 19960501 G 6110 C7036 NUT CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 726481 NUT CORRODED. 1 L 7 2 3O RT 3A10 5 C P22EA 1997123100515 19971231 00515 GL 1997 12 31 EY2R9600579 3 19960501 G 6110 D3474 PISTON ROD ASSY CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 726481 FOUND CORROSION ON PISTON ROD ASSY. 1 L 7 2 3O RT 3A10 5 C P22EA 1997123100516 19971231 00516 GL 1997 12 31 EY2R9600580 3 19960501 G 6110 B3490 PISTON ROD PIN CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 748132 FOUND CORROSION ON PISTON ROD ASSY. 1 L 7 2 3O 3A10 5 C P22EA 1997123100517 19971231 00517 GL 1997 12 31 EY2R9600581 3 19960501 G 6111 B4459 BLADE ACT PIN CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 747892 BLADE ACT PIN FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100518 19971231 00518 GL 1997 12 31 EY2R9600582 3 19960501 G 6111 B4459 BLADE ACT PIN CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 748132 BLADE ACT PIN FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100519 19971231 00519 GL 1997 12 31 EY2R9600583 3 19960501 G 6110 C3550 FEATHER CYLINDER CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3428 501 723023 FEATHER CYLINDER FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100520 19971231 00520 GL 1997 12 31 EY2R9600584 3 19960501 G 6110 C3550 FEATHER CYLINDER CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3428 501 723458 FEATHER CYLINDER FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100521 19971231 00521 GL 1997 12 31 EY2R9600585 3 19960501 G 6110 C3550 FEATHER CYLINDER CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 747892 FEATHER CYLINDER FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100522 19971231 00522 GL 1997 12 31 EY2R9600586 3 19960501 G 6110 C3550 FEATHER CYLINDER CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 748132 FEATHER CYLINDER FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100523 19971231 00523 GL 1997 12 31 EY2R9600587 3 19960501 G 6110 C7036 NUT CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3428 501 723458 NUT CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100524 19971231 00524 GL 1997 12 31 EY2R9600588 3 19960501 G 6110 C7036 NUT CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 747892 NUT CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100525 19971231 00525 GL 1997 12 31 EY2R9600589 3 19960501 G 6110 C7036 NUT CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 748132 NUT CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100526 19971231 00526 GL 1997 12 31 EY2R9600590 3 19960501 G 6114 D7015C87 HUB CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3428 501 723023 HUB FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100527 19971231 00527 GL 1997 12 31 EY2R9600591 3 19960501 G 6114 D7015C87 HUB CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3428 501 723458 HUB FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100528 19971231 00528 GL 1997 12 31 EY2R9600592 3 19960501 G 6114 D7015C87 HUB CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 747892 HUB FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100529 19971231 00529 GL 1997 12 31 EY2R9600593 3 19960501 G 6114 D7015C87 HUB CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 748132 HUB FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100530 19971231 00530 GL 1997 12 31 EY2R9600594 3 19960501 G 6110 C2987 RETAIN BEARING CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 740286 RETAIN BEARING FOUND CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997123100531 19971231 00531 GL 1997 12 31 EY2R9600595 3 19960501 G 6114 D7015C93 HUB CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 782374 HUB CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100532 19971231 00532 GL 1997 12 31 EY2R9600596 3 19960501 G 6111 S82NC55 BLADE CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 795337 BLADE, SN K96453YS, FOUND CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997123100533 19971231 00533 GL 1997 12 31 EY2R9600597 3 19960501 G 6111 S82NC55 BLADE CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 795337 BLADE, SN K96440YS, FOUND CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997123100534 19971231 00534 GL 1997 12 31 EY2R9600598 3 19960501 G 6111 S82NC55 BLADE CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 795337 BLADE, SN K96436YS, FOUND CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997123100535 19971231 00535 GL 1997 12 31 EY2R9600599 3 19960501 G 6111 S82NC55 BLADE CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 790630 BLADE, SN K92092YS, FOUND CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100536 19971231 00536 GL 1997 12 31 EY2R9600600 3 19960501 G 6111 S82NC55 BLADE CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 790630 BLADE, SN K92062YS, FOUND CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100537 19971231 00537 GL 1997 12 31 EY2R9600601 3 19960501 G 6111 S82NC55 BLADE CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 790819 BLADE, SN K92524YS, FOUND CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100538 19971231 00538 GL 1997 12 31 EY2R9600602 3 19960501 G 6110 A1896 CYLINDER PIN CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 761198 CYLINDER PIN FOUND CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997123100539 19971231 00539 GL 1997 12 31 EY2R9600603 3 19960501 G 6110 A1896 CYLINDER PIN CESSNA 414 414A 2075907 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 794518 CYLINDER PIN FOUND CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100540 19971231 00540 GL 1997 12 31 EY2R9600604 3 19960501 G 6110 A4191 DOWEL CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 761198 DOWEL CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997123100541 19971231 00541 GL 1997 12 31 EY2R9600605 3 19960501 G 6110 A4191 DOWEL CESSNA 414 414A 2075907 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 794518 DOWEL CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100542 19971231 00542 GL 1997 12 31 EY2R9600606 3 19960501 G 6110 C7036 NUT CESSNA 414 414A 2075907 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 794518 NUT CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100543 19971231 00543 GL 1997 12 31 EY2R9600607 3 19960501 G 6114 D7015C93 HUB CESSNA 414 414A 2075907 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 794518 HUB FOUND CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100544 19971231 00544 GL 1997 12 31 EY2R9600608 3 19960501 G 6110 A1896 CYLINDER PIN CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 760862 CYLINDER PIN FOUND CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997123100545 19971231 00545 GL 1997 12 31 EY2R9600609 3 19960501 G 6110 A4191 DOWEL CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 760862 DOWEL FOUND CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997123100546 19971231 00546 GL 1997 12 31 EY2R9600610 3 19960501 G 6110 C4451 FERRULE CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 453 7710747 FERRULE FOUND CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100547 19971231 00547 GL 1997 12 31 EY2R9600611 3 19960501 G 6110 C7036 NUT CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 453 7710747 NUT FOUND CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100548 19971231 00548 GL 1997 12 31 EY2R9600612 3 19960501 G 6110 C2987 RETAIN BEARING CESSNA 421 421 2076010 CE MCAULY 3AF34C 3AF34C92 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 730390 RETAIN BEARING FOUND WITH CORROSION. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100549 19971231 00549 GL 1997 12 31 EY2R9600613 3 19960501 G 6110 C7036 NUT CESSNA 421 421C 2076016 CE MCAULY 3AF34C 3AF34C92 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 694532 NUT FOUND WITH CORROSION. 1 L 7 2 3O A7CE 5 C P22EA 1997123100550 19971231 00550 GL 1997 12 31 EY2R9600614 3 19960501 G 6114 D5894C92 HUB CESSNA 421 421B 2076014 CE MCAULY 3AF34C 3AF34C92 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 748237 HUB FOUND CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100551 19971231 00551 GL 1997 12 31 EY2R9600615 3 19960501 G 6114 D7019C92 HUB CESSNA 421 421B 2076014 CE MCAULY 3AF34C 3AF34C92 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 733129 HUB FOUND CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100552 19971231 00552 GL 1997 12 31 EY2R9600616 3 19960501 G 6110 B48201 ACT PIN ASSY CESSNA 421 421 2076010 CE MCAULY 3FF32 3FF32C501 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 769147 ACT PIN ASSY FOUND CORRODED. 1 L 7 2 3O RT A7CE 5 C P45GL 1997123100553 19971231 00553 GL 1997 12 31 EY2R9600617 3 19960501 G 6110 B48201 ACT PIN ASSY CESSNA 421 421 2076010 CE MCAULY 3FF32 3FF32C501 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 771839 ACT PIN ASSY FOUND CORRODED. 1 L 7 2 3O RT A7CE 5 C P45GL 1997123100554 19971231 00554 GL 1997 12 31 EY2R9600618 3 19960501 G 6110 P501459401 PROPELLER CESSNA 421 421 2076010 CE MCAULY 3FF32 3FF32C501 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 761556 EXCESSIVE INTERNAL DAMAGE & CORR 1 L 7 2 3O RT A7CE 5 C P45GL 1997123100555 19971231 00555 GL 1997 12 31 EY2R9600619 3 19960501 G 6110 C5116 FEEDBACK COLLAR CESSNA 208 208 2073702 CE MCAULY 3AF34C 3GFR34C703 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 902362 FEEDBACK COLLAR CORRODED. 1 H 7 1 3T NT A37CE 5 C P60GL 1997123100556 19971231 00556 GL 1997 12 31 EY2R9600620 3 19960501 G 6110 C5503 BETA ROD CESSNA 208 208 2073702 CE MCAULY 3AF34C 3GFR34C703 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 902362 BETA ROD FOUND CORRODED. 1 H 7 1 3T NT A37CE 5 C P60GL 1997123100557 19971231 00557 GL 1997 12 31 EY2R9600621 3 19960501 G 6110 C5503 BETA ROD CESSNA 208 208 2073702 CE MCAULY 3AF34C 3GFR34C703 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 910691 BETA ROD FOUND CORRODED. 1 H 7 1 3T NT A37CE 5 C P60GL 1997123100558 19971231 00558 GL 1997 12 31 EY2R9600622 3 19960501 G 6110 D5010 CYLINDER CESSNA 208 208 2073702 CE MCAULY 3AF34C 3GFR34C703 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 910691 CYLINDER FOUND CORRODED. 1 H 7 1 3T NT A37CE 5 C P60GL 1997123100559 19971231 00559 NE 1997 12 31 EY2R9600623 3 19960501 G 6114 D6153C652 HUB SWRNGN SA226 SA226AC 8780402 SW MCAULY 4HFR34 4HFR34C652 NE PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 15814 2454 881745 HUB FOUND CORRODED. 2 L 7 2 4T RT A5SW 6 C 3PNE 1997123100560 19971231 00560 GL 1997 12 31 EY2R9600624 3 19960501 G 6110 C3411 BEARING RACE MOONEY M20 M20K 5870220 SW MCAULY 2D34C B2D34C214 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 797211 BEARING RACE CORRODED. 1 L 7 1 3O 2A3 5 C P7EA 1997123100561 19971231 00561 GL 1997 12 31 EY2R9600625 3 19960501 G 6110 C5270 RETAIN BEARING CESSNA 172 172RG 2072438 CE MCAULY 2D34C B2D34C220 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 870599 RETAIN BEARING FOUND WITH CORROSION. 1 H 7 1 3O 3A17 5 C P7EA 1997123100562 19971231 00562 GL 1997 12 31 EY2R9600626 3 19960501 G 6110 B3905 BASE ASSY PIN CESSNA 172 172RG 2072438 CE MCAULY 2D34C B2D34C220 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1202 921377 BASE ASSY PIN. 1 H 7 1 3O 3A17 5 C P7EA 1998010700009 19980107 00009 GL 1998 1 7 EY2R9600627 3 19960501 G 6111 74E0 BLADE MOONEY M20 M20 5870202 SW MCAULY 2D34C B2D34C53 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 701181 BLADE, SN A10840, FOUND CORRODED. 1 L 7 1 3O 2A3 5 C P7AE 1998010700010 19980107 00010 GL 1998 1 7 EY2R9600628 3 19960501 G 6111 74E0 BLADE MOONEY M20 M20 5870202 SW MCAULY 2D34C B2D34C53 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 701181 BLADE, SN A5868, FOUND CORRODED. 1 L 7 1 3O 2A3 5 C P7AE 1997123100563 19971231 00563 GL 1997 12 31 EY2R9600629 3 19960501 G 6110 2202 SPLIT BEARING BEECH 55 E55 1152732 CE HARTZL HCC2Y BHCC2YF2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 AN1446 CORROSION FOUND ON SPLIT BEARING. 1 L 7 2 3O 3A16 5 C P920 1997123100564 19971231 00564 GL 1997 12 31 EY2R9600630 3 19960501 G 6110 24573 PITCH CHGE FORK BEECH 55 E55 1152732 CE HARTZL HCC2Y BHCC2YF2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 AN1446 PITCH CHANGE FORK CORRODED. 1 L 7 2 3O 3A16 5 C P920 1997123100565 19971231 00565 GL 1997 12 31 EY2R9600631 3 19960501 G 6111 FC84756 BLADE BEECH 55 E55 1152732 CE HARTZL HCC2Y BHCC2YF2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 AN1446 BLADE, SN C77820, FOUND CORRODED. 1 L 7 2 3O 3A16 5 C P920 1997123100566 19971231 00566 GL 1997 12 31 EY2R9600632 3 19960501 G 6111 FC84756 BLADE BEECH 55 E55 1152732 CE HARTZL HCC2Y BHCC2YF2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 AN1446 BLADE, SN 64981, FOUND CORRODED. 1 L 7 2 3O 3A16 5 C P920 1997123100567 19971231 00567 GL 1997 12 31 EY2R9600633 3 19960501 G 6110 2202 SPLIT BEARING BEECH 95 95B55 1152729 CE HARTZL HCC2Y BHCC2YF2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 AN2167 SPLIT BEARING HAS CORROSION. 1 L 7 2 3O RT 3A16 5 C P920 1997123100568 19971231 00568 GL 1997 12 31 EY2R9600634 3 19960501 G 6110 2202 SPLIT BEARING BEECH 95 95B55 1152729 CE HARTZL HCC2Y BHCC2YF2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 AN2184 SPLIT BEARING HAS CORROSION. 1 L 7 2 3O RT 3A16 5 C P920 1997123100569 19971231 00569 GL 1997 12 31 EY2R9600635 3 19960501 G 6110 24915 PITCH CHANGE ROD BEECH 55 E55 1152732 CE HARTZL HCJ2Y BHCJ2YF2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 DZ895 PITCH CHANGE ROD FOUND WITH CORROSION. 1 L 7 2 3O 3A16 5 C P37EA 1997123100570 19971231 00570 GL 1997 12 31 EY2R9600636 3 19960501 G 6110 S76C2 BLADE MAULE M5 M5220C 5460133 SO MCAULY 2A34C D2A34C67 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 758280 BLADE, SN B49631YS, FOUND WITH CORROSION. 1 H 7 1 3O 3A23 5 C P3EA 1997123100571 19971231 00571 GL 1997 12 31 EY2R9600637 3 19960501 G 6110 B2345 PISTON TUBE CESSNA 188 188CESSNA 2073002 CE MCAULY 2A34C D2A34C98 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 891351 PISTON TUBE FOUND CORRODED. 1 L 7 1 3O A9CE 5 C P3EA 1997123100572 19971231 00572 GL 1997 12 31 EY2R9600638 3 19960501 G 6110 PL4664 KIT ASSY CESSNA 188 188CESSNA 2073002 CE MCAULY 2A34C D2A34C98 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 891351 PROPELLER KIT ASSY FOUND CORRODED 1 L 7 1 3O A9CE 5 C P3EA 1997123100573 19971231 00573 GL 1997 12 31 EY2R9600639 3 19960501 G 6111 78CBA2 BLADE CESSNA 337 337 2075702 CE MCAULY 2AF34C D2AF34C307 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 736926 BLADE, SN K73867, FOUND CORRODED. 1 H 7 2 3O A6CE 5 C P5EA 1997123100574 19971231 00574 GL 1997 12 31 EY2R9600640 3 19960501 G 6110 C4451 FERRULE CESSNA 210 T210* CE MCAULY 3A32C D3A32C88 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 770656 FERRULE FOUND CORRODED. 1 H 7 1 3O 3A21 5 C P21EA 1997123100575 19971231 00575 GL 1997 12 31 EY2R9600641 3 19960501 G 6110 C5262 CYLINDER CESSNA 210 T210* CE MCAULY 3A32C D3A32C88 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 770656 CYLINDER FOUND WITH CORROSION. 1 H 7 1 3O 3A21 5 C P21EA 1997123100576 19971231 00576 GL 1997 12 31 EY2R9600642 3 19960501 G 6110 A4001 DOWEL CESSNA 210 210M 2073450 CE MCAULY 3A32C D3A32C88 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 785659 DOWEL CORRODED. 1 H 7 1 3O 3A21 5 C P21EA 1997123100577 19971231 00577 GL 1997 12 31 EY2R9600643 3 19960501 G 6114 D5858C402 HUB CESSNA 206 206CESSNA 2073302 CE MCAULY D3A34 D3A34C402 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 861233 HUB FOUND WITH CORROSION. 1 H 7 1 3O A4CE 5 C P47GL 1997123100578 19971231 00578 GL 1997 12 31 EY2R9600644 3 19960501 G 6110 C4001 DOWEL CESSNA 206 U206 2073306 CE MCAULY D3A34 D3A34C404 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2194 410 811646 DOWEL CORRODED. 1 H 7 1 3O A4CE 5 C P47GL 1997123100579 19971231 00579 GL 1997 12 31 EY2R9600645 3 19960501 G 6114 D4190C307 HUB CESSNA 337 337 2075702 CE MCAULY 2AF34C D2AF34C307 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 736926 HUB FOUND CORRODED. 1 H 7 2 3O A6CE 5 C P5EA 1997123100580 19971231 00580 GL 1997 12 31 EY2R9600646 3 19960501 G 6110 1303 BEARING BEECH 95 B95 1153404 CE HARTZL HC92W HC92WK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1798F BEARING CORRODED. 1 L 7 2 3O 3A16 5 C P16EA 1997123100581 19971231 00581 GL 1997 12 31 EY2R9600647 3 19960501 G 6110 1303A BEARING BEECH 95 B95 1153404 CE HARTZL HC92W HC92WK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1544F BEARING CORRODED. 1 L 7 2 3O 3A16 5 C P16EA 1997123100582 19971231 00582 GL 1997 12 31 EY2R9600648 3 19960501 G 6110 1330 PROPELLER BEECH 95 B95 1153404 CE HARTZL HC92W HC92WK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1543F PROP ASSY CORRODED 1 L 7 2 3O 3A16 5 C P16EA 1997123100583 19971231 00583 GL 1997 12 31 EY2R9600649 3 19960501 G 6110 1331 SPLIT RING BEECH 95 B95 1153404 CE HARTZL HC92W HC92WK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1543F CORROSION FOUND ON SPLIT RING. 1 L 7 2 3O 3A16 5 C P16EA 1997123100584 19971231 00584 GL 1997 12 31 EY2R9600650 3 19960501 G 6110 1331 SPLIT RING BEECH 95 B95 1153404 CE HARTZL HC92W HC92WK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1544F CORROSION FOUND ON SPLIT RING. 1 L 7 2 3O 3A16 5 C P16EA 1997123100585 19971231 00585 GL 1997 12 31 EY2R9600651 3 19960501 G 6110 83830 CLAMP BEECH 95 B95 1153404 CE HARTZL HC92W HC92WK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1543F CLAMP CORRODED. 1 L 7 2 3O 3A16 5 C P16EA 1997123100586 19971231 00586 GL 1997 12 31 EY2R9600652 3 19960501 G 6110 83830 CLAMP BEECH 95 B95 1153404 CE HARTZL HC92W HC92WK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1544F CLAMP CORRODED. 1 L 7 2 3O 3A16 5 C P16EA 1997123100587 19971231 00587 GL 1997 12 31 EY2R9600653 3 19960501 G 6110 1301 CLAMP BEECH 95 B95 1153404 CE HARTZL HC92Z HC92ZK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1141F CLAMP CORRODED. 1 L 7 2 3O 3A16 5 C P892 1997123100588 19971231 00588 GL 1997 12 31 EY2R9600654 3 19960501 G 6110 8382 CLAMP BEECH 35 B35 1151506 CE HARTZL HCA2X HCA2X* GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 CLAMP CORRODED. 1 L 7 1 3O A777 5 C P908 1997123100589 19971231 00589 GL 1997 12 31 EY2R9600655 3 19960501 G 6110 83867 CLAMP DHAV DHC6 DHC6300 EA HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 CLAMP CORRODED. 1 H 7 2 3T A9EA 6 C P15EA 1997123100590 19971231 00590 GL 1997 12 31 EY2R9600656 3 19960501 G 6110 83867 CLAMP DHAV DHC6 DHC6300 EA HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 CLAMP CORRODED. 1 H 7 2 3T A9EA 6 C P15EA 1997123100591 19971231 00591 GL 1997 12 31 EY2R9600657 3 19960501 G 6110 1891 PILOT TUBE AYRES S2 S2RT34NORMAL 0970106 SO HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BU17784 PILOT TUBE FOUND WITH CORROSION. 1 L 7 1 3T A3SW 6 C P15EA 1997123100592 19971231 00592 GL 1997 12 31 EY2R9600658 3 19960501 G 6110 1851T BEARING AYRES S2 S2R 7630202 CE HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BU13149 BEARING CORRODED. 1 L 7 1 3R NC A4SW 6 C P15EA 1997123100593 19971231 00593 GL 1997 12 31 EY2R9600659 3 19960501 G 6110 1851T BEARING AIRTRC AT400 AT400 0390202 SW HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BU14660 BEARING CORRODED. 1 L 7 1 3T A9SW 6 C P15EA 1997123100594 19971231 00594 GL 1997 12 31 EY2R9600660 3 19960501 G 6110 1891 PILOT TUBE AYRES S2 S2R 7630202 CE HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BU17706 PILOT TUBE FOUND CORRODED. 1 L 7 1 3R NC A4SW 6 C P15EA 1997123100595 19971231 00595 GL 1997 12 31 EY2R9600661 3 19960501 G 6110 1891 PILOT TUBE AYRES S2 S2R 7630202 CE HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BU17852 PILOT TUBE FOUND CORRODED. 1 L 7 1 3R NC A4SW 6 C P15EA 1997123100596 19971231 00596 GL 1997 12 31 EY2R9600662 3 19960501 G 6110 1891 PILOT TUBE AYRES S2 S2R 7630202 CE HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BU18954 PILOT TUBE FOUND CORRODED. 1 L 7 1 3R NC A4SW 6 C P15EA 1997123100597 19971231 00597 GL 1997 12 31 EY2R9600663 3 19960501 G 6110 1891 PILOT TUBE AIRTRC AT400 AT400 0390202 SW HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BU3882 PILOT TUBE FOUND CORRODED. 1 L 7 1 3T A9SW 6 C P15EA 1997123100598 19971231 00598 GL 1997 12 31 EY2R9600664 3 19960501 G 6110 30215 PISTON UNIT AIRTRC AT400 AT400 0390202 SW HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BU3882 PISTON UNIT FOUND CORRODED. 1 L 7 1 3T A9SW 6 C P15EA 1997123100599 19971231 00599 GL 1997 12 31 EY2R9600665 3 19960501 G 6110 868AS PTCH CHANGE ROD AIRTRC AT400 AT400 0390202 SW HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BU3882 PITCH CHANGE ROD FOUND CORRODED. 1 L 7 1 3T A9SW 6 C P15EA 1997123100600 19971231 00600 GL 1997 12 31 EY2R9600666 3 19960501 G 6110 1851T BEARING BEECH 200 200BEECH 1152920 CE HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 4155 BU13998 BEARING CORRODED. 1 L 7 2 4T A24CE 6 C P15EA 1997123100601 19971231 00601 GL 1997 12 31 EY2R9600667 3 19960501 G 6110 1891 PILOT TUBE AYRES S2 S2R 7630202 CE HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BU12693 PILOT TUBE FOUND CORRODED. 1 L 7 1 3R NC A4SW 6 C P15EA 1997123100602 19971231 00602 GL 1997 12 31 EY2R9600668 3 19960501 G 6111 T10282 BLADE AYRES S2 S2R 7630202 CE HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BU12693 BLADE, SN E85574, FOUND CORRODED. 1 L 7 1 3R NC A4SW 6 C P15EA 1997123100603 19971231 00603 GL 1997 12 31 EY2R9600669 3 19960501 G 6110 1851T BEARING BEECH 100 100BEECH 1152916 CE HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3897 BU16570 BEARING CORRODED. 1 L 7 2 3T A14CE 6 C P15EA 1997123100604 19971231 00604 GL 1997 12 31 EY2R9600670 3 19960501 G 6110 13019S CLAMP AIRTRC AT300 AT301 0390103 SW HARTZL HCB3T HCB3TN5 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BV2014 CLAMP CORRODED. 1 L 7 1 3R A9SW 6 C P15EA 1997123100605 19971231 00605 GL 1997 12 31 EY2R9600671 3 19960501 G 6110 1851T BEARING BEECH 1900 1900C 1154161 CE HARTZL HCB4M HCB4MP3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 FW1151 BEARING CORRODED. 2 L 7 2 4T RT A24CE 6 C P56GL 1997123100606 19971231 00606 GL 1997 12 31 EY2R9600672 3 19960501 G 6110 3475A3 LOW STOP COLLAR BEECH 1900 1900C 1154161 CE HARTZL HCB4M HCB4MP3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 FW1151 LOW STOP COLLAR FOUND CORRODED. 2 L 7 2 4T RT A24CE 6 C P56GL 1997123100607 19971231 00607 GL 1997 12 31 EY2R9600673 3 19960501 G 6110 3475A3 LOW STOP COLLAR BEECH 1900 1900C 1154161 CE HARTZL HCB4M HCB4MP3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 FW1151 LOW STOP COLLAR FOUND CORRODED. 2 L 7 2 4T RT A24CE 6 C P56GL 1997123100608 19971231 00608 GL 1997 12 31 EY2R9600674 3 19960501 G 6111 M10476 BLADE BEECH 1900 1900C 1154161 CE HARTZL HCB4M HCB4MP3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 FW1151 BLADE FOUND CORRODED. 2 L 7 2 4T RT A24CE 6 C P56GL 1997123100609 19971231 00609 GL 1997 12 31 EY2R9600675 3 19960501 G 6110 83867 CLAMP BEECH 100 100BEECH 1152916 CE HARTZL HCB4T HCB4TN5 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 CD402 CLAMP FOUND CORRODED. 1 L 7 2 3T A14CE 6 C P40EA 1997123100610 19971231 00610 GL 1997 12 31 EY2R9600676 3 19960501 G 6114 220117 HUB MOONEY M20 M20E 5870212 SW HARTZL HCC2Y HCC2YK1 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 CH22351 HUB FOUND CORRODED. 1 L 7 1 3O 2A3 5 C P920 1997123100611 19971231 00611 GL 1997 12 31 EY2R9600677 3 19960501 G 6114 220116 HUB GRTLKS 2T1 2T1A1 3910107 NM HARTZL HCC2Y HCC2Y* GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 DN932 HUB FOUND CORRODED. 1 Q 7 1 3O A18EA 5 C P920 1997123100612 19971231 00612 GL 1997 12 31 EY2R9600678 3 19960501 G 6110 24182 PISTON ROD PIPER PA32 PA32260 7103206 SO HARTZL HCC2Y HCC2YR1 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 CH25452 PISTON ROD CORRODED. 1 L 7 1 3O A3SO 5 C P920 1997123100613 19971231 00613 GL 1997 12 31 EY2R9600679 3 19960501 G 6110 2431 BOLT PIPER PA30 PA30 7103002 SO HARTZL HCE2Y HCE2YL2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BG1381 BOLT CORRODED. 1 L 7 2 3O A1EA 5 C P9EA 1997123100614 19971231 00614 GL 1997 12 31 EY2R9600680 3 19960501 G 6110 2431 BOLT PIPER PA30 PA30 7103002 SO HARTZL HCE2Y HCE2YL2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BG3943 BOLT CORRODED. 1 L 7 2 3O A1EA 5 C P9EA 1997123100615 19971231 00615 GL 1997 12 31 EY2R9600681 3 19960501 G 6110 2433 BOLT PIPER PA30 PA30 7103002 SO HARTZL HCE2Y HCE2YL2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BG1381 BOLT CORRODED. 1 L 7 2 3O A1EA 5 C P9EA 1997123100616 19971231 00616 GL 1997 12 31 EY2R9600682 3 19960501 G 6110 2433 BOLT PIPER PA30 PA30 7103002 SO HARTZL HCE2Y HCE2YL2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BG3943 BOLT CORRODED. 1 L 7 2 3O A1EA 5 C P9EA 1997123100617 19971231 00617 GL 1997 12 31 EY2R9600683 3 19960501 G 6110 24914S PITCH CHANGE ROD PIPER PA30 PA39 7103902 SO HARTZL HCE2Y HCE2YL2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BG1716 PITCH CHANGE ROD FOUND CORRODED. 1 L 7 2 3O A1EA 5 C P9EA 1997123100618 19971231 00618 GL 1997 12 31 EY2R9600684 3 19960501 G 6110 F84774 BLADE PIPER PA32 PA32RT300T 7103216 SO HARTZL HCE2Y HCE2YR1BF GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 DK1424 BLADE, SN D961511, FOUND CORRODED. 1 L 7 1 3O A3SO 5 C P9EA 1997123100619 19971231 00619 GL 1997 12 31 EY2R9600685 3 19960501 G 6110 F84774 BLADE PIPER PA32 PA32RT300T 7103216 SO HARTZL HCE2Y HCE2YR1BF GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 DK1424 BLADE, SN D885229, FOUND CORRODED. 1 L 7 1 3O A3SO 5 C P9EA 1997123100620 19971231 00620 GL 1997 12 31 EY2R9600686 3 19960501 G 6110 2202 SPLIT BEARING PIPER PA31 PA31325 7103105 SO HARTZL HCE3Y HCE3YR2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 DJ9058A CORROSION FOUND ON SPLIT BEARING. 1 L 7 2 3O A20SO 5 C P33EA 1997123100621 19971231 00621 GL 1997 12 31 EY2R9600687 3 19960501 G 6111 FC84686R BLADE PIPER PA31 PA31325 7103105 SO HARTZL HCE3Y HCE3YR2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 DJ9058A BLADE, SN H19056, FOUND CORRODED. 1 L 7 2 3O A20SO 5 C P33EA 1997123100622 19971231 00622 GL 1997 12 31 EY2R9600688 3 19960501 G 6110 3475A2 LOW STOP COLLAR BEECH 58 58P 1152744 CE HARTZL HCCA3A PHCA3VF5 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 DH20 CORROSION FOUND ON LOW STOP COLLAR. 1 L 7 2 3O A23CE 5 C P6EA 1997123100623 19971231 00623 GL 1997 12 31 EY2R9600689 3 19960501 G 6110 3475A2 LOW STOP COLLAR BEECH 58 58P 1152744 CE HARTZL HCCA3A PHCA3VF5 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 DH21 CORROSION FOUND ON LOW STOP COLLAR. 1 L 7 2 3O A23CE 5 C P6EA 1997123100624 19971231 00624 GL 1997 12 31 EY2R9600690 3 19960501 G 6110 971 SPLIT BEARING BEECH 58 58P 1152744 CE HARTZL HCCA3A PHCA3VF5 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 DH20 CORROSION FOUND ON SPLIT BEARING. 1 L 7 2 3O A23CE 5 C P6EA 1997123100625 19971231 00625 GL 1997 12 31 EY2R9600691 3 19960501 G 6110 971 SPLIT BEARING BEECH 58 58P 1152744 CE HARTZL HCCA3A PHCA3VF5 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 DH21 CORROSION FOUND ON SPLIT BEARING. 1 L 7 2 3O A23CE 5 C P6EA 1997123100626 19971231 00626 GL 1997 12 31 EY2R9600692 3 19960601 G 6114 C3910C203 HUB CESSNA 182 182 2072702 CE MCAULY 2A34C 2A34C203 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 755185 HUB CORRODED. 1 H 7 1 3O NT 3A13 5 C P3EA 1997123100627 19971231 00627 GL 1997 12 31 EY2R9600693 3 19960601 G 6110 C5270 RETAIN BEARING CESSNA 172 172K 2072430 CE MCAULY 2A34C 2A34C203 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 910336 RETAIN BEARING FOUND CORRODED. 1 H 7 1 3O NT 3A12 5 C P3EA 1997123100628 19971231 00628 GL 1997 12 31 EY2R9600694 3 19960601 G 6110 C5270 RETAIN BEARING CESSNA 172 172K 2072430 CE MCAULY 2A34C 2A34C203 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 910336 RETAIN BEARING FOUND CORRODED. 1 H 7 1 3O NT 3A12 5 C P3EA 1997123100629 19971231 00629 GL 1997 12 31 EY2R9600695 3 19960601 G 6110 C5270 RETAIN BEARING CESSNA 172 172K 2072430 CE MCAULY 2A34C 2A34C203 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 910336 RETAIN BEARING FOUND CORRODED. 1 H 7 1 3O NT 3A12 5 C P3EA 1997123100630 19971231 00630 GL 1997 12 31 EY2R9600696 3 19960601 G 6110 A4001 DOWEL CESSNA 182 182 2072702 CE MCAULY 2A34C 2A34C50 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3854 493 741216 DOWEL CORRODED. 1 H 7 1 3O NT 3A13 5 C P3EA 1997123100631 19971231 00631 GL 1997 12 31 EY2R9600697 3 19960601 G 6111 S90A8 BLADE CESSNA 182 182 2072702 CE MCAULY 2A34C 2A34C50 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3854 493 741216 BLADE FOUND WITH CORROSION. 1 H 7 1 3O NT 3A13 5 C P3EA 1997123100632 19971231 00632 GL 1997 12 31 EY2R9600698 3 19960601 G 6110 A16349 BALL BEARING BEECH 36 A36 1151604 CE MCAULY 3A32C 3A32C406 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 530 911534 BALL BEARING CORRODED. 1 L 7 1 3O 3A15 5 C P21EA 1997123100633 19971231 00633 GL 1997 12 31 EY2R9600699 3 19960601 G 6110 C3903 SPLIT RETAINER CESSNA 320 320 2074502 CE MCAULY 3AF32C 3AF32C* GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 811497 CORROSION FOUND ON SPLIT RETAINER. 1 L 7 2 3O 3A25 5 C P22EA 1997123100634 19971231 00634 GL 1997 12 31 EY2R9600700 3 19960601 G 6110 C3903 SPLIT RETAINER CESSNA 402 402C 207590R CE MCAULY 3AF32C 3AF32C505 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 811285 CORROSION FOUND ON SPLIT RETAINER. 1 L 7 2 3O A7CE 5 C P22EA 1997123100635 19971231 00635 GL 1997 12 31 EY2R9600701 3 19960601 G 6110 C3903 SPLIT RETAINER CESSNA 340 340CESSNA 2076404 CE MCAULY 3AF32C 3AF32C505 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 932390 CORROSION FOUND ON SPLIT RETAINER. 1 L 7 2 3O 3A25 5 C P22EA 1997123100636 19971231 00636 GL 1997 12 31 EY2R9600702 3 19960601 G 6110 A1896 CYLINDER PIN CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C505 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 920046 CYLINDER PIN CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100637 19971231 00637 GL 1997 12 31 EY2R9600703 3 19960601 G 6110 A1896 CYLINDER PIN CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C505 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 920330 CYLINDER PIN CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100638 19971231 00638 GL 1997 12 31 EY2R9600704 3 19960601 G 6110 A4191 DOWEL CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C505 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 920046 DOWEL CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100639 19971231 00639 GL 1997 12 31 EY2R9600705 3 19960601 G 6110 A4191 DOWEL CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C505 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 920330 DOWELL CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100640 19971231 00640 GL 1997 12 31 EY2R9600706 3 19960601 G 6110 C3903 SPLIT RETAINER CESSNA 303 T303 2073820 CE MCAULY 3AF32C 3AF32C506 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 821060 CORROSION FOUND ON SPLIT RETAINER. 1 L 7 2 3O A34CE 5 C P57GL 1997123100641 19971231 00641 GL 1997 12 31 EY2R9600707 3 19960601 G 6114 C4326C206 HUB CESSNA 303 T303 2073820 CE MCAULY 3AF32C 3AF32C506 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 821060 HUB FOUND CORRODED. 1 L 7 2 3O A34CE 5 C P57GL 1997123100642 19971231 00642 GL 1997 12 31 EY2R9600708 3 19960601 G 6110 C5270 RETAIN BEARING CESSNA 303 T303 2073820 CE MCAULY 3AF32C 3AF32C506 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 821060 RETAIN BEARING FOUND CORRODED. 1 L 7 2 3O A34CE 5 C P57GL 1997123100643 19971231 00643 GL 1997 12 31 EY2R9600709 3 19960601 G 6110 C7036 NUT CESSNA 320 320 2074502 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 711484 NUT CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997123100644 19971231 00644 GL 1997 12 31 EY2R9600710 3 19960601 G 6110 C2987 RETAIN BEARING CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 777497 RETAIN BEARING FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100645 19971231 00645 GL 1997 12 31 EY2R9600711 3 19960601 G 6110 C3475 NUT CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 777497 NUT CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100646 19971231 00646 GL 1997 12 31 EY2R9600712 3 19960601 G 6110 C2987 RETAIN BEARING CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 774447 RETAIN BEARING CORRODED. 1 L 7 2 3O RT 3A10 5 C P22EA 1997123100647 19971231 00647 GL 1997 12 31 EY2R9600713 3 19960601 G 6110 C7036 NUT CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 774447 NUT CORRODED. 1 L 7 2 3O RT 3A10 5 C P22EA 1997123100648 19971231 00648 GL 1997 12 31 EY2R9600714 3 19960601 G 6110 C7036 NUT CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 783146 NUT CORRODED. 1 L 7 2 3O RT 3A10 5 C P22EA 1997123100649 19971231 00649 GL 1997 12 31 EY2R9600715 3 19960601 G 6114 D7015C87 HUB CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 682245 HUB FOUND CORRODED. 1 L 7 2 3O RT 3A10 5 C P22EA 1997123100650 19971231 00650 GL 1997 12 31 EY2R9600716 3 19960601 G 6114 D7015C87 HUB CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 682424 HUB FOUND CORRODED. 1 L 7 2 3O RT 3A10 5 C P22EA 1997123100651 19971231 00651 GL 1997 12 31 EY2R9600717 3 19960601 G 6114 D7015C87 HUB CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 4368 1382 726136 HUB FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100652 19971231 00652 GL 1997 12 31 EY2R9600718 3 19960601 G 6114 D7015C87 HUB CESSNA 402 402B 207590P CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 733152 HUB FOUND CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100653 19971231 00653 GL 1997 12 31 EY2R9600719 3 19960601 G 6114 D7015C87 HUB CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 5851 368 756558 HUB FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100654 19971231 00654 GL 1997 12 31 EY2R9600720 3 19960601 G 6114 D7015C87 HUB CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 783146 HUB FOUND CORRODED. 1 L 7 2 3O RT 3A10 5 C P22EA 1997123100655 19971231 00655 GL 1997 12 31 EY2R9600721 3 19960601 G 6114 D7015C87 HUB CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 814168 HUB FOUND CORRODED. 1 L 7 2 3O RT 3A10 5 C P22EA 1997123100656 19971231 00656 GL 1997 12 31 EY2R9600722 3 19960601 G 6114 D7015C87 HUB CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 815998 HUB FOUND CORRODED. 1 L 7 2 3O RT 3A10 5 C P22EA 1997123100657 19971231 00657 GL 1997 12 31 EY2R9600723 3 19960601 G 6111 S82NC4 BLADE CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 814168 BLADE, SN BD1029YS, FOUND CORRODED. 1 L 7 2 3O RT 3A10 5 C P22EA 1997123100658 19971231 00658 GL 1997 12 31 EY2R9600724 3 19960601 G 6111 S82NC4 BLADE CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 814168 BLADE, SN BD1015YS, FOUND CORRODED. 1 L 7 2 3O RT 3A10 5 C P22EA 1997123100659 19971231 00659 GL 1997 12 31 EY2R9600725 3 19960601 G 6111 S82NC4 BLADE CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 814168 BLADE, SN BF119YS, FOUND CORRODED. 1 L 7 2 3O RT 3A10 5 C P22EA 1997123100660 19971231 00660 GL 1997 12 31 EY2R9600726 3 19960601 G 6111 S82NC4 BLADE CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 815998 BLADE, SN BG409YS, FOUND CORRODED. 1 L 7 2 3O RT 3A10 5 C P22EA 1997123100661 19971231 00661 GL 1997 12 31 EY2R9600727 3 19960601 G 6111 S82NC4 BLADE CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 815998 BLADE, SN BG348YS, FOUND CORRODED. 1 L 7 2 3O RT 3A10 5 C P22EA 1997123100662 19971231 00662 GL 1997 12 31 EY2R9600728 3 19960601 G 6111 S82NC55 BLADE CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 774447 BLADE, SN K76165YS, FOUND CORRODED. 1 L 7 2 3O RT 3A10 5 C P22EA 1997123100663 19971231 00663 GL 1997 12 31 EY2R9600729 3 19960601 G 6111 S82NC55 BLADE CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 774447 BLADE, SN K76240YS, FOUND CORRODED. 1 L 7 2 3O RT 3A10 5 C P22EA 1997123100664 19971231 00664 GL 1997 12 31 EY2R9600730 3 19960601 G 6111 S82NC55 BLADE CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 774447 BLADE, SN K76239YS, FOUND CORRODED. 1 L 7 2 3O RT 3A10 5 C P22EA 1997123100665 19971231 00665 GL 1997 12 31 EY2R9600731 3 19960601 G 6111 S82NC55 BLADE CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 783146 BLADE, SN K76877YS, FOUND CORRODED. 1 L 7 2 3O RT 3A10 5 C P22EA 1997123100666 19971231 00666 GL 1997 12 31 EY2R9600732 3 19960601 G 6111 S82NC55 BLADE CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 783146 BLADE, SN F75090YS, FOUND CORRODED. 1 L 7 2 3O RT 3A10 5 C P22EA 1997123100667 19971231 00667 GL 1997 12 31 EY2R9600733 3 19960601 G 6110 C2987 RETAIN BEARING CESSNA 402 402B 207590P CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 799902 RETAIN BEARING FOUND CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100668 19971231 00668 GL 1997 12 31 EY2R9600734 3 19960601 G 6110 A1896 CYLINDER PIN CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 734167 CYLINDER PIN CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100669 19971231 00669 GL 1997 12 31 EY2R9600735 3 19960601 G 6110 A1896 CYLINDER PIN CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 753351 CYLINDER PIN CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100670 19971231 00670 GL 1997 12 31 EY2R9600736 3 19960601 G 6110 A1896 CYLINDER PIN CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 773769 CYLINDER PIN CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100671 19971231 00671 GL 1997 12 31 EY2R9600737 3 19960601 G 6110 A1896 CYLINDER PIN CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 783822 CYLINDER PIN CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100672 19971231 00672 GL 1997 12 31 EY2R9600738 3 19960601 G 6110 A4191 DOWEL CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 734167 DOWEL CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100673 19971231 00673 GL 1997 12 31 EY2R9600739 3 19960601 G 6110 A4191 DOWEL CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 773769 DOWEL CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100674 19971231 00674 GL 1997 12 31 EY2R9600740 3 19960601 G 6110 A4191 DOWEL CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 783822 DOWEL CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100675 19971231 00675 GL 1997 12 31 EY2R9600741 3 19960601 G 6110 C7036 NUT CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 734167 NUT CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100676 19971231 00676 GL 1997 12 31 EY2R9600742 3 19960601 G 6110 C2987 RETAIN BEARING CESSNA 402 402A 207590M CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 737350 RETAIN BEARING CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100677 19971231 00677 GL 1997 12 31 EY2R9600743 3 19960601 G 6111 82NC2 BLADE CESSNA 210 210 2073402 CE MCAULY 3AF32C 3AF32C* GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3096 309 816304 BLADE, SN BJ550YS, FOUND CORRODED. 1 H 7 1 3O RT 3A21 5 C P22EA 1997123100678 19971231 00678 GL 1997 12 31 EY2R9600744 3 19960601 G 6110 C4451 FERRULE CESSNA 210 210 2073402 CE MCAULY 3AF32C 3AF32C* GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3096 309 816304 FERRULE CORRODED. 1 H 7 1 3O RT 3A21 5 C P22EA 1997123100679 19971231 00679 GL 1997 12 31 EY2R9600745 3 19960601 G 6110 C4904 NUT CESSNA 210 210 2073402 CE MCAULY 3AF32C 3AF32C* GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3096 309 816304 NUT CORRODED. 1 H 7 1 3O RT 3A21 5 C P22EA 1997123100680 19971231 00680 GL 1997 12 31 EY2R9600746 3 19960601 G 6110 C5262 CYLINDER CESSNA 210 210 2073402 CE MCAULY 3AF32C 3AF32C* GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3096 309 816304 CYLINDER FOUND CORRODED. 1 H 7 1 3O RT 3A21 5 C P22EA 1997123100681 19971231 00681 GL 1997 12 31 EY2R9600747 3 19960601 G 6110 C7036 NUT CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 755780 NUT CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997123100682 19971231 00682 GL 1997 12 31 EY2R9600748 3 19960601 G 6114 D7015C93 HUB CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1005 783104 HUB FOUND CORRODED. 1 L 7 2 3O RT 3A10 5 C P22EA 1997123100683 19971231 00683 GL 1997 12 31 EY2R9600749 3 19960601 G 6111 90LF0 BLADE CESSNA 421 421 2076010 CE MCAULY 3AF34C 3AF34C92 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1642 743229 BLADE, SN IA029, FOUND CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100684 19971231 00684 GL 1997 12 31 EY2R9600750 3 19960601 G 6111 B4459 BLADE ACT PIN CESSNA 421 421 2076010 CE MCAULY 3AF34C 3AF34C92 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1642 743229 BLADE ACT PIN FOUND CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100685 19971231 00685 GL 1997 12 31 EY2R9600751 3 19960601 G 6110 C4550 FERRULE CESSNA 421 421 2076010 CE MCAULY 3AF34C 3AF34C92 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 944 739301 FERRULE FOUND CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100686 19971231 00686 GL 1997 12 31 EY2R9600752 3 19960601 G 6110 C7036 NUT CESSNA 421 421 2076010 CE MCAULY 3AF34C 3AF34C92 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1642 805941 NUT CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100687 19971231 00687 GL 1997 12 31 EY2R9600753 3 19960601 G 6114 D7019C92 HUB CESSNA 421 421 2076010 CE MCAULY 3AF34C 3AF34C92 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 944 739301 HUB FOUND CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100688 19971231 00688 GL 1997 12 31 EY2R9600754 3 19960601 G 6111 S90LF0 BLADE CESSNA 421 421 2076010 CE MCAULY 3AF34C 3AF34C92 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 711725 BLADE, SN HL080YS, FOUND CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100689 19971231 00689 GL 1997 12 31 EY2R9600755 3 19960601 G 6111 S90LF0 BLADE CESSNA 421 421 2076010 CE MCAULY 3AF34C 3AF34C92 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 711725 BLADE, SN HL062YS, FOUND CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100690 19971231 00690 GL 1997 12 31 EY2R9600756 3 19960601 G 6111 S90LF0 BLADE CESSNA 421 421 2076010 CE MCAULY 3AF34C 3AF34C92 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 711725 BLADE, SN OA037YS, FOUND CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100691 19971231 00691 GL 1997 12 31 EY2R9600757 3 19960601 G 6111 S90LF0 BLADE CESSNA 421 421 2076010 CE MCAULY 3AF34C 3AF34C92 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 944 739301 BLADE FOUND CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100692 19971231 00692 GL 1997 12 31 EY2R9600758 3 19960601 G 6111 90UMB0 BLADE CESSNA 404 404CESSNA 2075901 CE MCAULY 3FF32 3FF32C501 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 830433 BLADE, SN CB356, FOUND CORRODED. 1 L 7 2 3O A25CE 5 C P45GL 1997123100693 19971231 00693 GL 1997 12 31 EY2R9600759 3 19960601 G 6111 90UMB0 BLADE CESSNA 404 404CESSNA 2075901 CE MCAULY 3FF32 3FF32C501 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 830433 BLADE, SN CB258, FOUND CORRODED. 1 L 7 2 3O A25CE 5 C P45GL 1997123100694 19971231 00694 GL 1997 12 31 EY2R9600760 3 19960601 G 6111 90UMB0 BLADE CESSNA 404 404CESSNA 2075901 CE MCAULY 3FF32 3FF32C501 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 830433 BLADE, SN CB257, FOUND CORRODED. 1 L 7 2 3O A25CE 5 C P45GL 1997123100695 19971231 00695 GL 1997 12 31 EY2R9600761 3 19960601 G 6111 90UMB0 BLADE CESSNA 404 404CESSNA 2075901 CE MCAULY 3FF32 3FF32C501 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 830437 BLADE, SN CB179, FOUND CORRODED. 1 L 7 2 3O A25CE 5 C P45GL 1997123100696 19971231 00696 GL 1997 12 31 EY2R9600762 3 19960601 G 6111 90UMB0 BLADE CESSNA 404 404CESSNA 2075901 CE MCAULY 3FF32 3FF32C501 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 830437 BLADE, SN CB433, FOUND CORRODED. 1 L 7 2 3O A25CE 5 C P45GL 1997123100697 19971231 00697 GL 1997 12 31 EY2R9600763 3 19960601 G 6111 90UMB0 BLADE CESSNA 404 404CESSNA 2075901 CE MCAULY 3FF32 3FF32C501 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 830437 BLADE, SN CB178, FOUND CORRODED. 1 L 7 2 3O A25CE 5 C P45GL 1997123100698 19971231 00698 GL 1997 12 31 EY2R9600764 3 19960601 G 6114 D5878C501 HUB CESSNA 404 404CESSNA 2075901 CE MCAULY 3FF32 3FF32C501 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 830433 HUB FOUND CORRODED. 1 L 7 2 3O A25CE 5 C P45GL 1997123100699 19971231 00699 GL 1997 12 31 EY2R9600765 3 19960601 G 6114 D5878C501 HUB CESSNA 404 404CESSNA 2075901 CE MCAULY 3FF32 3FF32C501 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 830437 HUB FOUND CORRODED. 1 L 7 2 3O A25CE 5 C P45GL 1997123100700 19971231 00700 GL 1997 12 31 EY2R9600766 3 19960601 G 6110 A3267 ADAPTER CESSNA 421 421C 2076016 CE MCAULY 3FF32 3FF32C501 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1005 804734 CORROSION FOUND ON ADAPTER. 1 L 7 2 3O A7CE 5 C P45GL 1997123100701 19971231 00701 GL 1997 12 31 EY2R9600767 3 19960601 G 6110 A3267 ADAPTER CESSNA 421 421C 2076016 CE MCAULY 3FF32 3FF32C501 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 250 804734 CORROSION FOUND ON ADAPTER. 1 L 7 2 3O A7CE 5 C P45GL 1997123100702 19971231 00702 GL 1997 12 31 EY2R9600768 3 19960601 G 6110 A1896 CYLINDER PIN CESSNA 421 421C 2076016 CE MCAULY 3FF32 3FF32C501 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 755998 CYLINDER PIN FOUND CORRODED. 1 L 7 2 3O A7CE 5 C P45GL 1997123100703 19971231 00703 GL 1997 12 31 EY2R9600769 3 19960601 G 6110 A1896 CYLINDER PIN CESSNA 421 421C 2076016 CE MCAULY 3FF32 3FF32C501 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 760509 CYLINDER PIN FOUND CORRODED. 1 L 7 2 3O A7CE 5 C P45GL 1997123100704 19971231 00704 GL 1997 12 31 EY2R9600770 3 19960601 G 6110 A4191 DOWEL CESSNA 421 421 2076010 CE MCAULY 3FF32 3FF32C501 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 755998 DOWEL CORRODED. 1 L 7 2 3O RT A7CE 5 C P45GL 1997123100705 19971231 00705 GL 1997 12 31 EY2R9600771 3 19960601 G 6110 A4191 DOWEL CESSNA 421 421C 2076016 CE MCAULY 3FF32 3FF32C501 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 760509 DOWEL CORRODED. 1 L 7 2 3O A7CE 5 C P45GL 1998010700011 19980107 00011 NE 1998 1 7 EY2R9600772 3 19960601 G 6114 D5886C601 HUB CESSNA 441 441 2076020 CE MCAULY 4HFR34 4HFR34C660 NE PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 841350 HUB FOUND CORRODED. 1 L 7 2 3T RT A28CE 5 C 3PNE 1998010700012 19980107 00012 NE 1998 1 7 EY2R9600773 3 19960601 G 6114 D5886C601 HUB CESSNA 441 441 2076020 CE MCAULY 4HFR34 4HFR34C660 NE PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 841830 HUB FOUND CORRODED. 1 L 7 2 3T RT A28CE 5 C 3PNE 1997123100706 19971231 00706 NE 1997 12 31 EY2R9600774 3 19960601 G 6110 B5162 REVERSE STOP SWRNGN SA226 SA226AC 8780402 SW MCAULY 4HFR34 4HFR34C652 NE PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2834 890505 CORROSION FOUND ON REVERSE STOP SCREW. 2 L 7 2 4T RT A5SW 6 C 3PNE 1997123100707 19971231 00707 NE 1997 12 31 EY2R9600775 3 19960601 G 6110 D6174 CYLINDER SWRNGN SA226 SA226AC 8780402 SW MCAULY 4HFR34 4HFR34C652 NE PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2834 890505 CYLINDER FOUND CORRODED. 2 L 7 2 4T RT A5SW 6 C 3PNE 1997123100708 19971231 00708 NE 1997 12 31 EY2R9600776 3 19960601 G 6110 A163919 NUT SWRNGN SA226 SA226AC 8780402 SW MCAULY 4HFR34 4HFR34C652 NE PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2834 890503 NUT FOUND CORRODED. 2 L 7 2 4T RT A5SW 6 C 3PNE 1997123100709 19971231 00709 NE 1997 12 31 EY2R9600777 3 19960601 G 6110 A1896 CYLINDER PIN SWRNGN SA226 SA226AC 8780402 SW MCAULY 4HFR34 4HFR34C652 NE PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 14000 4758 880393 CORROSION FOUND ON CYLINDER. 2 L 7 2 4T RT A5SW 6 C 3PNE 1997123100710 19971231 00710 NE 1997 12 31 EY2R9600778 3 19960601 G 6110 B5162 REVERSE STOP SWRNGN SA226 SA226AC 8780402 SW MCAULY 4HFR34 4HFR34C652 NE PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2834 890503 CORROSION FOUND ON REVERSE STOP SCREW. 2 L 7 2 4T RT A5SW 6 C 3PNE 1997123100711 19971231 00711 NE 1997 12 31 EY2R9600779 3 19960601 G 6110 D6174 CYLINDER SWRNGN SA226 SA226AC 8780402 SW MCAULY 4HFR34 4HFR34C652 NE PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2834 890503 CYLINDER CORRODED. 2 L 7 2 4T RT A5SW 6 C 3PNE 1997123100712 19971231 00712 GL 1997 12 31 EY2R9600780 3 19960601 G 6111 90DHA4 BLADE CESSNA 188 A188B 2073005 CE MCAULY 2A34C B2A34C205 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2804 1202 831317 BLADE, SN GK56, FOUND CORRODED. 1 L 7 1 3O A9CE 5 C P3EA 1997123100713 19971231 00713 GL 1997 12 31 EY2R9600781 3 19960601 G 6111 90DHA4 BLADE CESSNA 188 A188B 2073005 CE MCAULY 2A34C B2A34C205 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2804 1202 831317 BLADE, SN GK05, FOUND CORRODED. 1 L 7 1 3O A9CE 5 C P3EA 1997123100714 19971231 00714 GL 1997 12 31 EY2R9600782 3 19960601 G 6114 C6608C205 HUB CESSNA 188 A188B 2073005 CE MCAULY 2A34C B2A34C205 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2804 1202 831317 CORROSION FOUND ON HUB. 1 L 7 1 3O A9CE 5 C P3EA 1997123100715 19971231 00715 GL 1997 12 31 EY2R9600783 3 19960601 G 6114 D4326C207 HUB CESSNA 177 177 2073704 CE MCAULY 2D34C B2D34C207 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 774490 CORROSION FOUND ON HUB. 1 H 7 1 3O NT A13CE 5 C P7EA 1997123100716 19971231 00716 GL 1997 12 31 EY2R9600784 3 19960601 G 6111 90DHB8 BLADE CESSNA 182 R182 2072734 CE MCAULY 2D34C B2D34C218 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 802969 BLADE, SN BF964, FOUND CORRODED. 1 H 7 1 3O RT 3A13 5 C P7EA 1997123100717 19971231 00717 GL 1997 12 31 EY2R9600785 3 19960601 G 6111 90DHB8 BLADE CESSNA 182 R182 2072734 CE MCAULY 2D34C B2D34C218 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 802969 BLADE, SN CA326, FOUND CORRODED. 1 H 7 1 3O RT 3A13 5 C P7EA 1997123100718 19971231 00718 GL 1997 12 31 EY2R9600786 3 19960601 G 6114 D5045C218 HUB CESSNA 182 R182 2072734 CE MCAULY 2D34C B2D34C218 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 802969 HUB FOUND CORRODED. 1 H 7 1 3O RT 3A13 5 C P7EA 1997123100719 19971231 00719 GL 1997 12 31 EY2R9600787 3 19960601 G 6114 22015 HUB PIPER PA46 PA46310P 7104605 SO HARTZL HCC2Y BHCC2YF1 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1379 AM2728 HUB FOUND CORRODED. 1 L 7 1 3O A25SO 5 C P920 1997123100720 19971231 00720 GL 1997 12 31 EY2R9600788 3 19960601 G 6111 90AT4 BLADE CESSNA 188 A188B 2073005 CE MCAULY 2A34C D2A34C98 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2666 1333 890754 BLADE, SN IJ120YS, FOUND CORRODED. 1 L 7 1 3O A9CE 5 C P3EA 1997123100721 19971231 00721 GL 1997 12 31 EY2R9600789 3 19960601 G 6111 90AT4 BLADE CESSNA 188 A188B 2073005 CE MCAULY 2A34C D2A34C98 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2666 1333 890754 BLADE, SN IJ089YS, FOUND CORRODED. 1 L 7 1 3O A9CE 5 C P3EA 1997123100722 19971231 00722 GL 1997 12 31 EY2R9600790 3 19960601 G 6111 78CAA0 BLADE CESSNA 337 337 2075702 CE MCAULY 2AF34C D2AF34C306 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 821929 BLADE FOUND CORRODED. 1 H 7 2 3O A6CE 5 C P5EA 1997123100723 19971231 00723 GL 1997 12 31 EY2R9600791 3 19960601 G 6114 D4476C306 HUB CESSNA 337 337 2075702 CE MCAULY 2AF34C D2AF34C306 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 821929 HUB FOUND CORRODED. 1 H 7 2 3O A6CE 5 C P5EA 1997123100724 19971231 00724 GL 1997 12 31 EY2R9600792 3 19960601 G 6114 D4190C307 HUB CESSNA 337 337 2075702 CE MCAULY 2AF34C D2AF34C307 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 734246 HUB FOUND CORRODED. 1 H 7 2 3O A6CE 5 C P5EA 1997123100725 19971231 00725 GL 1997 12 31 EY2R9600793 3 19960601 G 6111 L78CBA2 BLADE CESSNA 337 337 2075702 CE MCAULY 2AF34C D2AF34C307 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 734246 BLADE, SN K77066, FOUND CORRODED. 1 H 7 2 3O A6CE 5 C P5EA 1997123100726 19971231 00726 GL 1997 12 31 EY2R9600794 3 19960601 G 6111 L78CBA2 BLADE CESSNA 337 337 2075702 CE MCAULY 2AF34C D2AF34C307 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 734246 BLADE, SN K76674, FOUND CORRODED. 1 H 7 2 3O A6CE 5 C P5EA 1997123100727 19971231 00727 GL 1997 12 31 EY2R9600795 3 19960601 G 6110 C2987 RETAIN BEARING CESSNA 310 310P 2074238 CE MCAULY 2AF34C D2AF34C71 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 788660 RETAIN BEARING FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P5EA 1997123100728 19971231 00728 GL 1997 12 31 EY2R9600796 3 19960601 G 6110 C3475 NUT CESSNA 310 310P 2074238 CE MCAULY 2AF34C D2AF34C71 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 788660 NUT CORRODED. 1 L 7 2 3O 3A10 5 C P5EA 1997123100729 19971231 00729 GL 1997 12 31 EY2R9600797 3 19960601 G 6110 C5270 RETAIN BEARING CESSNA 180 180A 2072604 CE MCAULY 3A32C D3A32C* GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 831717 RETAIN BEARING CORRODED. 1 H 7 1 3O 5A6 5 C P21EA 1997123100730 19971231 00730 GL 1997 12 31 EY2R9600798 3 19960601 G 6114 D6603C88 HUB CESSNA 210 210 2073402 CE MCAULY 3A32C D3A32C88 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 715483 HUB FOUND CORRODED. 1 H 7 1 3O RT 3A21 5 C P21EA 1997123100731 19971231 00731 GL 1997 12 31 EY2R9600799 3 19960601 G 6111 S82NC2 BLADE CESSNA 210 210 2073402 CE MCAULY 3A32C D3A32C88 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 715483 BLADE, SN K65734YS, FOUND CORRODED. 1 H 7 1 3O RT 3A21 5 C P21EA 1997123100732 19971231 00732 GL 1997 12 31 EY2R9600800 3 19960601 G 6111 S82NC2 BLADE CESSNA 210 210 2073402 CE MCAULY 3A32C D3A32C88 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 715483 BLADE, SN K65733YS, FOUND CORRODED. 1 H 7 1 3O RT 3A21 5 C P21EA 1997123100733 19971231 00733 GL 1997 12 31 EY2R9600801 3 19960601 G 6111 S82NC2 BLADE CESSNA 210 210 2073402 CE MCAULY 3A32C D3A32C88 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 715483 BLADE, SN K65732YS, FOUND CORRODED. 1 H 7 1 3O RT 3A21 5 C P21EA 1997123100734 19971231 00734 GL 1997 12 31 EY2R9600802 3 19960601 G 6110 A4001 DOWEL CESSNA 210 P210N 2073454 CE MCAULY D3A34 D3A34C402 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 796954 DOWEL CORRODED. 1 H 7 1 3O 3A21 5 C P47GL 1997123100735 19971231 00735 GL 1997 12 31 EY2R9600803 3 19960601 G 6110 A4001 DOWEL CESSNA 210 210 2073402 CE MCAULY D3A34 D3A34C402 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 796956 DOWEL CORRODED. 1 H 7 1 3O RT 3A21 5 C P47GL 1997123100736 19971231 00736 GL 1997 12 31 EY2R9600804 3 19960601 G 6110 C3411 BEARING RACE CESSNA 210 210N 2073453 CE MCAULY D3A34 D3A34C402 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 801266 BEARING RACE FOUND CORRODED. 1 H 7 1 3O 3A21 5 C P47GL 1997123100737 19971231 00737 GL 1997 12 31 EY2R9600805 3 19960601 G 6110 C3903 SPLIT RETAINER CESSNA 210 210N 2073453 CE MCAULY D3A34 D3A34C402 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 801266 CORROSION FOUND ON SPLIT RETAINER. 1 H 7 1 3O 3A21 5 C P47GL 1997123100738 19971231 00738 GL 1997 12 31 EY2R9600806 3 19960601 G 6110 C3475 NUT CESSNA 310 310N 2074234 CE MCAULY 3AF32C D3AF32C80 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 666649 NUT CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100739 19971231 00739 GL 1997 12 31 EY2R9600807 3 19960601 G 6110 C3550 FEATHER CYLINDER CESSNA 310 310N 2074234 CE MCAULY 3AF32C D3AF32C80 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 666649 FEATHER CYLINDER CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100740 19971231 00740 GL 1997 12 31 EY2R9600808 3 19960601 G 6110 971 SPLIT BEARING BEECH 58 58 1152740 CE HARTZL HCA3V EHCA3VF2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BR571 CORROSION FOUND ON SPLIT BEARING. 1 L 7 2 3O 3A16 5 C P6EA 1997123100741 19971231 00741 GL 1997 12 31 EY2R9600809 3 19960601 G 6110 14B BEARING GULSTM 680 680 0141602 SW HARTZL HC83V HC83V202 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1672 59 D1182N BEARING CORRODED. 1 H 7 2 3O 2A4 5 C P14EA 1997123100742 19971231 00742 GL 1997 12 31 EY2R9600810 3 19960601 G 6110 14B BEARING GULSTM 680 680 0141602 SW HARTZL HC83V HC83V202 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1672 59 D1183N BEARING CORRODED. 1 H 7 2 3O 2A4 5 C P14EA 1997123100743 19971231 00743 GL 1997 12 31 EY2R9600811 3 19960601 G 6110 1301 CLAMP BEECH 95 B95A 1153406 CE HARTZL HC92W HC92WK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1207F CLAMP CORRODED. 1 L 7 2 3O 3A16 5 C P16EA 1997123100744 19971231 00744 GL 1997 12 31 EY2R9600812 3 19960601 G 6110 1301 CLAMP BEECH 95 B95A 1153406 CE HARTZL HC92W HC92WK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1208F CLAMP CORRODED. 1 L 7 2 3O 3A16 5 C P16EA 1997123100745 19971231 00745 GL 1997 12 31 EY2R9600813 3 19960601 G 6110 971 SPLIT BEARING PIPER PA23 PA23 7102302 SO HARTZL HCA2V HCA2VK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 H1049 CORROSION FOUND ON SPLIT BEARING. 1 L 7 2 3O 1A10 5 C P24EA 1997123100746 19971231 00746 GL 1997 12 31 EY2R9600814 3 19960601 G 6111 84334 BLADE GULSTM 500 500RKWELL 0141102 SW HARTZL HCA2X HCA2XK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 H106 BLADE, SN A18604, FOUND CORRODED. 1 H 7 2 3O 6A1 5 C P908 1997123100747 19971231 00747 GL 1997 12 31 EY2R9600815 3 19960601 G 6110 971 SPLIT BEARING GULSTM 500 500RKWELL 0141102 SW HARTZL HCA2X HCA2XK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 H106 CORROSION FOUND ON SPLIT BEARING. 1 H 7 2 3O 6A1 5 C P908 1997123100748 19971231 00748 GL 1997 12 31 EY2R9600816 3 19960601 G 6110 1851T BEARING GULSTM G73 G73 3951802 SW HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3744 2984 BU14300 BEARING CORRODED. 1 H 7 2 3R A783 6 C P15EA 1997123100749 19971231 00749 GL 1997 12 31 EY2R9600817 3 19960601 G 6110 83865 CLAMP GULSTM G73 G73 3951802 SW HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3744 2984 BU14300 CLAMP CORRODED. 1 H 7 2 3R A783 6 C P15EA 1997123100750 19971231 00750 GL 1997 12 31 EY2R9600818 3 19960601 G 6110 84060 HUB GULSTM G73 G73 3951802 SW HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3744 2984 BU14300 PILOT TUBES REMOVED & REPLACED. 1 H 7 2 3R A783 6 C P15EA 1997123100751 19971231 00751 GL 1997 12 31 EY2R9600819 3 19960601 G 6110 1851T BEARING MTSBSI MU2 MU2B30 5780410 SW HARTZL HCB3T HCB3TN5 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3551 1300 BV4246 BEARING CORRODED. 1 H 7 2 3T A2PC 6 C P15EA 1997123100752 19971231 00752 GL 1997 12 31 EY2R9600820 3 19960601 G 6110 3406 CYLINDER BEECH 1900 1900C 1154161 CE HARTZL HCB4M HCB4MP3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 14107 3709 FW633 CORROSION FOUND ON CYLINDER. 2 L 7 2 4T RT A24CE 6 C P56GL 1997123100753 19971231 00753 GL 1997 12 31 EY2R9600821 3 19960601 G 6110 1851T BEARING BEECH 300 300BEECH 1152930 CE HARTZL HCB4M HCB4MP3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 FW297 BEARING CORRODED. 2 L 7 2 4T A24CE 6 C P56GL 1997123100754 19971231 00754 GL 1997 12 31 EY2R9600822 3 19960601 G 6110 1851T BEARING STBROS SD3 SD360 8100606 EU HARTZL HCB5M HCB5MP3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 14395 4470 EV624 CORROSION FOUND ON BEARING. 2 H 7 2 4T A41EU 6 C P44GL 1997123100755 19971231 00755 GL 1997 12 31 EY2R9600823 3 19960601 G 6111 FC7666A2 BLADE BBAVIA 8 8KCAB 2110612 CE HARTZL HCC2Y HCC2YK1 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 348 DN1558 BLADE, SN E84429, FOUND CORRODED. 1 H 7 1 3O A21CE 5 C P920 1997123100756 19971231 00756 GL 1997 12 31 EY2R9600824 3 19960601 G 6111 FC7666A2 BLADE BBAVIA 8 8KCAB 2110612 CE HARTZL HCC2Y HCC2YK1 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 348 DN1558 BLADE, SN E83260, FOUND CORRODED. 1 H 7 1 3O A21CE 5 C P920 1997123100757 19971231 00757 GL 1997 12 31 EY2R9600825 3 19960601 G 6110 2202 SPLIT BEARING BNORM BN2 BN2A 1520204 EU HARTZL HCC2Y HCC2YK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 AU2053 CORROSION FOUND ON SPLIT BEARING. 1 H 7 2 3O A17EU 5 C P920 1997123100758 19971231 00758 GL 1997 12 31 EY2R9600826 3 19960601 G 6110 2202 SPLIT BEARING BNORM BN2 BN2A3 1520215 EU HARTZL HCC2Y HCC2YK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 AU7443 CORROSION FOUND ON SPLIT BEARING. 1 H 7 2 3O A17EU 5 C P920 1997123100759 19971231 00759 GL 1997 12 31 EY2R9600827 3 19960601 G 6110 2202 SPLIT BEARING BEECH 90 B90 1152912 CE HARTZL HCD4N3 HCD4N3A GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1063 FY518 CORROSION FOUND ON SPLIT BEARING. 1 L 7 2 3T 3A20 5 C STC 1997123100760 19971231 00760 GL 1997 12 31 EY2R9600828 3 19960601 G 6114 4993 HUB BEECH 90 B90 1152912 CE HARTZL HCD4N3 HCD4N3A GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1063 FY518 HUB FOUND CORRODED. 1 L 7 2 3T 3A20 5 C STC 1997123100761 19971231 00761 GL 1997 12 31 EY2R9600829 3 19960601 G 6110 60711 PITCH CHG ROD BEECH 90 B90 1152912 CE HARTZL HCD4N3 HCD4N3A GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1063 FY1240 PITCH CHANGE ROD FOUND CORRODED. 1 L 7 2 3T 3A20 5 C STC 1997123100762 19971231 00762 GL 1997 12 31 EY2R9600830 3 19960601 G 6114 24831 HUB PIPER PA30 PA30 7103002 SO HARTZL HCE2Y HCE2YL2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BG712 HUB FOUND CORRODED. 1 L 7 2 3O A1EA 5 C P9EA 1997123100763 19971231 00763 GL 1997 12 31 EY2R9600831 3 19960601 G 6114 24831 HUB PIPER PA30 PA30 7103002 SO HARTZL HCE2Y HCE2YL2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BG714 HUB FOUND CORRODED. 1 L 7 2 3O A1EA 5 C P9EA 1997123100764 19971231 00764 GL 1997 12 31 EY2R9600832 3 19960601 G 6110 2202 SPLIT BEARING PIPER PA30 PA39 7103902 SO HARTZL HCE2Y HCE2YL2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BG317 CORROSION FOUND ON SPLIT BEARING. 1 L 7 2 3O A1EA 5 C P9EA 1997123100765 19971231 00765 GL 1997 12 31 EY2R9600833 3 19960601 G 6110 2202 SPLIT BEARING PIPER PA30 PA39 7103902 SO HARTZL HCE2Y HCE2YL2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1739 CORROSION FOUND ON SPLIT BEARING. 1 L 7 2 3O A1EA 5 C P9EA 1997123100766 19971231 00766 GL 1997 12 31 EY2R9600834 3 19960601 G 6110 2202 SPLIT BEARING PIPER PA23 PA23250 7102308 SO HARTZL HCE2Y HCE2YR2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 634 CORROSION FOUND ON SPLIT BEARING. 1 L 7 2 3O 1A10 5 C P9EA 1997123100767 19971231 00767 GL 1997 12 31 EY2R9600835 3 19960601 G 6110 2202 SPLIT BEARING PIPER PA23 PA23250 7102308 SO HARTZL HCE2Y HCE2YR2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BP3903 CORROSION FOUND ON SPLIT BEARING. 1 L 7 2 3O 1A10 5 C P9EA 1997123100768 19971231 00768 GL 1997 12 31 EY2R9600836 3 19960601 G 6110 2202 SPLIT BEARING PIPER PA31 PA31325 7103105 SO HARTZL HCE3Y HCE3YR2A GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 DJ5094 CORROSION FOUND ON SPLIT BEARING. 1 L 7 2 3O A20SO 5 C P33EA 1997123100769 19971231 00769 GL 1997 12 31 EY2R9600837 3 19960601 G 6110 23813 FEATHERING SPRNG BEECH 60 60 1153602 CE HARTZL HCF3Y HCF3YR2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1479 DA1508 CORROSION FOUND ON FEATHERING SPRING. 1 L 7 2 3O A12CE 5 C P31EA 1997123100770 19971231 00770 GL 1997 12 31 EY2R9600838 3 19960601 G 6110 971 SPLIT BEARING BEECH 58 58 1152740 CE HARTZL HCA3V PHCA3VF2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BR440 CORROSION FOUND ON SPLIT BEARING. 1 L 7 2 3O 3A16 5 C P6EA 1997123100771 19971231 00771 GL 1997 12 31 EY2R9600839 3 19960601 G 6114 84082 HUB BEECH 35 V35 1151538 CE HARTZL HCA3V PHCA3VF4 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 465 BL164 HUB FOUND CORRODED. 1 L 7 1 3O 3A15 5 C P6EA 1997123100772 19971231 00772 GL 1997 12 31 EY2R9600840 3 19960601 G 6110 2202 SPLIT BEARING BEECH 58 58 1152740 CE HARTZL HCJ3Y PHCJ3YF2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2472 ED1215 CORROSION FOUND ON SPLIT BEARING. 1 L 7 2 3O 3A16 5 C P36EA 1997123100773 19971231 00773 GL 1997 12 31 EY2R9600841 3 19960601 G 6110 3237 PISTON UNIT BEECH 58 58 1152740 CE HARTZL HCJ3Y PHCJ3YF2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2472 ED2543 PISTON UNIT CORRODED. 1 L 7 2 3O 3A16 5 C P36EA 1997123100774 19971231 00774 GL 1997 12 31 EY2R9600842 3 19960601 G 6114 32857 HUB BEECH 58 58 1152740 CE HARTZL HCJ3Y PHCJ3YF2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2472 ED1215 HUB FOUND CORRODED. 1 L 7 2 3O 3A16 5 C P36EA 1997123100775 19971231 00775 GL 1997 12 31 EY2R9600843 3 19960601 G 6111 FC76632R BLADE BEECH 58 58 1152740 CE HARTZL HCJ3Y PHCJ3YF2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2472 ED1215 BLADE, SN H36796, FOUND CORRODED. 1 L 7 2 3O 3A16 5 C P36EA 1997123100776 19971231 00776 GL 1997 12 31 EY2R9600844 3 19960601 G 6111 FC76632R BLADE BEECH 58 58 1152740 CE HARTZL HCJ3Y PHCJ3YF2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2472 ED1215 BLADE, SN H36799, FOUND CORRODED. 1 L 7 2 3O 3A16 5 C P36EA 1997123100777 19971231 00777 GL 1997 12 31 EY2R9600845 3 19960601 G 6111 FC76632R BLADE BEECH 58 58 1152740 CE HARTZL HCJ3Y PHCJ3YF2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2472 ED2543 BLADE, SN F98274, FOUND CORRODED. 1 L 7 2 3O 3A16 5 C P36EA 1997123100778 19971231 00778 GL 1997 12 31 EY2R9600846 3 19960601 G 6111 FC76632R BLADE BEECH 58 58 1152740 CE HARTZL HCJ3Y PHCJ3YF2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2472 ED2543 BLADE, SN F98278, FOUND CORRODED. 1 L 7 2 3O 3A16 5 C P36EA 1997123100779 19971231 00779 GL 1997 12 31 EY2R9600847 3 19960701 G 6110 C3411 BEARING RACE CESSNA 177 177B 2073708 CE MCAULY 2D34C 2D34C* GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 779804 BEARING RACE CORRODED. 1 H 7 1 3O A13CE 5 C P7EA 1997123100780 19971231 00780 GL 1997 12 31 EY2R9600848 3 19960701 G 6110 A1896 CYLINDER PIN BEECH 55 D55 1152730 CE MCAULY 3AF32C 3AF32C75 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 796163 CYLINDER PIN CORRODED. 1 L 7 2 3O 3A16 5 C P22EA 1997123100781 19971231 00781 GL 1997 12 31 EY2R9600849 3 19960701 G 6110 A4001 DOWEL BEECH 55 D55 1152730 CE MCAULY 3AF32C 3AF32C75 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 796163 DOWEL FOUND WITH CORROSION. 1 L 7 2 3O 3A16 5 C P22EA 1997123100782 19971231 00782 GL 1997 12 31 EY2R9600850 3 19960701 G 6111 S82NB6 BLADE BEECH 55 D55 1152730 CE MCAULY 3AF32C 3AF32C75 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 796163 BLADE, SN F14967YS, FOUND CORRODED. 1 L 7 2 3O 3A16 5 C P22EA 1997123100783 19971231 00783 GL 1997 12 31 EY2R9600851 3 19960701 G 6110 A1896 CYLINDER PIN BEECH 55 D55 1152730 CE MCAULY 3AF32C 3AF32C75 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 697561 CYLINDER PIN FOUND CORRODED. 1 L 7 2 3O 3A16 5 C P22EA 1997123100784 19971231 00784 GL 1997 12 31 EY2R9600852 3 19960701 G 6110 A4001 DOWEL BEECH 55 D55 1152730 CE MCAULY 3AF32C 3AF32C75 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 697561 DOWEL CORRODED. 1 L 7 2 3O 3A16 5 C P22EA 1997123100785 19971231 00785 GL 1997 12 31 EY2R9600853 3 19960701 G 6111 S82NB6 BLADE BEECH 55 D55 1152730 CE MCAULY 3AF32C 3AF32C75 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 697561 BLADE, SN F11710YS, FOUND CORRODED. 1 L 7 2 3O 3A16 5 C P22EA 1997123100786 19971231 00786 GL 1997 12 31 EY2R9600854 3 19960701 G 6111 S82NB6 BLADE BEECH 55 D55 1152730 CE MCAULY 3AF32C 3AF32C75 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 697561 BLADE, SN F12557YS, FOUND CORRODED. 1 L 7 2 3O 3A16 5 C P22EA 1997123100787 19971231 00787 GL 1997 12 31 EY2R9600855 3 19960701 G 6110 C4451 FERRULE CESSNA 402 402B 207590P CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 697985 FERRULE CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100788 19971231 00788 GL 1997 12 31 EY2R9600856 3 19960701 G 6110 C4451 FERRULE CESSNA 402 402B 207590P CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 779568 FERRULE CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100789 19971231 00789 GL 1997 12 31 EY2R9600857 3 19960701 G 6110 C3550 FERRULE CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 747485 FEATHER CYLINDER CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100790 19971231 00790 GL 1997 12 31 EY2R9600858 3 19960701 G 6110 S82NC7 BLADE CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 747485 BLADE, SN F23333YS, FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100791 19971231 00791 GL 1997 12 31 EY2R9600859 3 19960701 G 6111 S82NC7 BLADE CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 747485 BLADE, SN F19644YS, FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100792 19971231 00792 GL 1997 12 31 EY2R9600860 3 19960701 G 6110 C3550 FEATHER CYLINDER CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 789450 FEATHER CYLINDER CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100793 19971231 00793 GL 1997 12 31 EY2R9600861 3 19960701 G 6110 C7036 NUT CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 789450 NUT CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100794 19971231 00794 GL 1997 12 31 EY2R9600862 3 19960701 G 6110 A1896 CYLINDER PIN CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2573 793864 CYLINDER PIN CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100795 19971231 00795 GL 1997 12 31 EY2R9600863 3 19960701 G 6110 A4191 DOWEL CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2573 793864 DOWEL CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100796 19971231 00796 GL 1997 12 31 EY2R9600864 3 19960701 G 6110 B3490 PISTON ROD PIN CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2573 793864 PISTONR ROD FOUND CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100797 19971231 00797 GL 1997 12 31 EY2R9600865 3 19960701 G 6111 B4459 BLADE ACT PIN CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2573 793864 BLADE ACT PIN CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100798 19971231 00798 GL 1997 12 31 EY2R9600866 3 19960701 G 6110 C2987 RETAIN BEARING CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1190 733315 RETAIN BEARING FOUND CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997123100799 19971231 00799 GL 1997 12 31 EY2R9600867 3 19960701 G 6110 C2987 RETAIN BEARING CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2573 793864 RETAIN BEARING FOUND CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100800 19971231 00800 GL 1997 12 31 EY2R9600868 3 19960701 G 6110 C4451 FERRULE CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2573 793864 FERRULE CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100801 19971231 00801 GL 1997 12 31 EY2R9600869 3 19960701 G 6110 C7036 NUT CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2573 793864 NUT FOUND CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100802 19971231 00802 GL 1997 12 31 EY2R9600870 3 19960701 G 6114 D7015C93 HUB CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2573 793864 CORROSION FOUND ON HUB. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100803 19971231 00803 GL 1997 12 31 EY2R9600871 3 19960701 G 6111 S82NC55 BLADE CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2573 793864 BLADE, SN F28561YS, FOUND CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100804 19971231 00804 GL 1997 12 31 EY2R9600872 3 19960701 G 6110 A1896 CYLINDER PIN CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1496 722254 CYLINDER PIN FOUND CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100805 19971231 00805 GL 1997 12 31 EY2R9600873 3 19960701 G 6110 A4191 DOWEL CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1496 722254 DOWEL PIN CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100806 19971231 00806 GL 1997 12 31 EY2R9600874 3 19960701 G 6110 C3475 NUT CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1190 783577 NUT CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997123100807 19971231 00807 GL 1997 12 31 EY2R9600875 3 19960701 G 6110 C4451 FERRULE CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1496 722254 FERRULE CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100808 19971231 00808 GL 1997 12 31 EY2R9600876 3 19960701 G 6111 S82NC55 BLADE CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1190 783577 BLADE, SN K85709YS, FOUND CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997123100809 19971231 00809 GL 1997 12 31 EY2R9600877 3 19960701 G 6110 A1896 CYLINDER PIN PIPER PA34 PA34200T 7103406 SO MCAULY 3AF34C 3AF34C502 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1580 788537 CYLINDER PIN CORRODED. 1 L 7 2 3O A7SO 5 C P22EA 1997123100810 19971231 00810 GL 1997 12 31 EY2R9600878 3 19960701 G 6110 A4191 DOWEL PIPER PA34 PA34200T 7103406 SO MCAULY 3AF34C 3AF34C502 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1580 788537 DOWEL CORRODED. 1 L 7 2 3O A7SO 5 C P22EA 1997123100811 19971231 00811 GL 1997 12 31 EY2R9600879 3 19960701 G 6114 C4801C204 HUB CESSNA 182 182 2072702 CE MCAULY 2A34C C2A34C204 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 776119 HUB FOUND CORRODED. 1 H 7 1 3O NT 3A13 5 C P3EA 1997123100812 19971231 00812 GL 1997 12 31 EY2R9600880 3 19960701 G 6114 C4810C204 HUB CESSNA 182 182 2072702 CE MCAULY 2A34C C2A34C204 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 781441 HUB FOUND CORRODED. 1 H 7 1 3O NT 3A13 5 C P3EA 1997123100813 19971231 00813 GL 1997 12 31 EY2R9600881 3 19960701 G 6114 D4326C211 HUB CESSNA 177 177 2073704 CE MCAULY 2D34C B2D34C211 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 757500 HUB FOUND CORRODED. 1 H 7 1 3O NT A13CE 5 C P7EA 1997123100814 19971231 00814 GL 1997 12 31 EY2R9600882 3 19960701 G 6110 B48202 ACT PIN ASSY BEECH 33 F33A 1151425 CE MCAULY 3A32C D3A32C* GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1539 467 850989 ACT PIN ASSY FOUND CORRODED. 1 L 7 1 3O 3A15 5 C P21EA 1997123100815 19971231 00815 GL 1997 12 31 EY2R9600883 3 19960701 G 6110 C5264 CYLINDER CESSNA 206 TU206G 2073357 CE MCAULY D3A34 D3A34C402 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 902242 CORROSION FOUND ON CYLINDER. 1 H 7 1 3O A4CE 5 C P47GL 1997123100816 19971231 00816 GL 1997 12 31 EY2R9600884 3 19960701 G 6114 D5858C402 HUB CESSNA 206 TU206G 2073357 CE MCAULY D3A34 D3A34C402 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 902242 HUB FOUND CORRODED. 1 H 7 1 3O A4CE 5 C P47GL 1997123100817 19971231 00817 GL 1997 12 31 EY2R9600885 3 19960701 G 6110 B48202 ACT PIN ASSY CESSNA 210 T210N 2073456 CE MCAULY D3A34 D3A34C402 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 815224 ACT PIN ASSY CORRODED. 1 H 7 1 3O 3A21 5 C P47GL 1997123100818 19971231 00818 GL 1997 12 31 EY2R9600886 3 19960701 G 6110 C3903 SPLIT RETAINER CESSNA 210 T210N 2073456 CE MCAULY D3A34 D3A34C402 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 815224 CORROSION FOUND ON SPLIT RETAINER 1 H 7 1 3O 3A21 5 C P47GL 1997123100819 19971231 00819 GL 1997 12 31 EY2R9600887 3 19960701 G 6110 C5270 RETAIN BEARING CESSNA 210 T210N 2073456 CE MCAULY D3A34 D3A34C402 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 815224 RETAIN BEARING FOUND CORRODED. 1 H 7 1 3O 3A21 5 C P47GL 1997123100820 19971231 00820 GL 1997 12 31 EY2R9600888 3 19960701 G 6110 38B BEARING FRCHLD 24 24R46 3370514 EA HARTZL HC12V HC12V20* GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 P477 BEARING CORRODED. 1 H 7 1 3I A706 5 C P46GL 1997123100821 19971231 00821 GL 1997 12 31 EY2R9600889 3 19960701 G 6110 83888 CLAMP BEECH 200 200BEECH 1152920 CE HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 CLAMP CORRODED. 1 L 7 2 4T A24CE 6 C P15EA 1997123100822 19971231 00822 GL 1997 12 31 EY2R9600890 3 19960701 G 6110 1851T BEARING PIPER PA31T PA31T 7103124 SO HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BU12944 BEARING CORRODED. 1 L 7 2 3T A8EA 6 C P15EA 1997123100823 19971231 00823 GL 1997 12 31 EY2R9600891 3 19960701 G 6110 1851T BEARING BEECH 100 100BEECH 1152916 CE HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BU9021 BEARING CORRODED. 1 L 7 2 3T A14CE 6 C P15EA 1997123100824 19971231 00824 GL 1997 12 31 EY2R9600892 3 19960701 G 6110 3475A2 LOW STOP COLLAR BEECH 100 100BEECH 1152916 CE HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BU9021 CORROSION FOUND ON COLLAR. 1 L 7 2 3T A14CE 6 C P15EA 1997123100825 19971231 00825 GL 1997 12 31 EY2R9600893 3 19960701 G 6110 1851T BEARING DHAV DHC6 DHC6100 EA HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 328 BU1222 BEARING CORRODED. 1 H 7 2 3T A9EA 6 C P15EA 1997123100826 19971231 00826 GL 1997 12 31 EY2R9600894 3 19960701 G 6110 1851T BEARING DHAV DHC6 DHC6100 EA HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 328 BU2305 BEARING CORRODED. 1 H 7 2 3T A9EA 6 C P15EA 1997123100827 19971231 00827 GL 1997 12 31 EY2R9600895 3 19960701 G 6110 18912A PILOT TUBE DHAV DHC6 DHC6100 EA HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 328 BU1222 PILOT TUBE FOUND CORRODED. 1 H 7 2 3T A9EA 6 C P15EA 1997123100828 19971231 00828 GL 1997 12 31 EY2R9600896 3 19960701 G 6110 1851T BEARING DHAV DHC6 DHC6300 EA HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 20791 3036 BU7082 BEARING CORRODED. 1 H 7 2 3T A9EA 6 C P15EA 1997123100829 19971231 00829 GL 1997 12 31 EY2R9600897 3 19960701 G 6111 T102826 BLADE AYRES S2 S2R 7630202 CE HARTZL HCB3T HCB3TN5 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BLADE, SN H13058, FOUND CORRODED. 1 L 7 1 3R NC A4SW 6 C P15EA 1997123100830 19971231 00830 GL 1997 12 31 EY2R9600898 3 19960701 G 6111 T102826 BLADE AYRES S2 S2R 7630202 CE HARTZL HCB3T HCB3TN5 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BLADE, SN H13052, FOUND CORRODED. 1 L 7 1 3R NC A4SW 6 C P15EA 1997123100831 19971231 00831 GL 1997 12 31 EY2R9600899 3 19960701 G 6111 T102826 BLADE AYRES S2 S2R 7630202 CE HARTZL HCB3T HCB3TN5 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BLADE, SN H13053, FOUND CORRODED. 1 L 7 1 3R NC A4SW 6 C P15EA 1997123100832 19971231 00832 GL 1997 12 31 EY2R9600900 3 19960701 G 6110 1851T BEARING BEECH 1900 1900C 1154161 CE HARTZL HCB4M HCB4MP3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 18952 3058 FW253 BEARING CORRODED. 2 L 7 2 4T RT A24CE 6 C P56GL 1997123100833 19971231 00833 GL 1997 12 31 EY2R9600901 3 19960701 G 6110 1851T BEARING BEECH 1900 1900C 1154161 CE HARTZL HCB4M HCB4MP3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 18952 3058 FW264 BEARING CORRODED. 2 L 7 2 4T RT A24CE 6 C P56GL 1997123100834 19971231 00834 GL 1997 12 31 EY2R9600902 3 19960701 G 6110 338614H BOLT BEECH 1900 1900C 1154161 CE HARTZL HCB4M HCB4MP3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 18952 3058 FW253 BOLT CORRODED. 2 L 7 2 4T RT A24CE 6 C P56GL 1997123100835 19971231 00835 GL 1997 12 31 EY2R9600903 3 19960701 G 6110 338614H BOLT BEECH 1900 1900C 1154161 CE HARTZL HCB4M HCB4MP3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 18952 3058 FW264 BOLT CORRODED. 2 L 7 2 4T RT A24CE 6 C P56GL 1997123100836 19971231 00836 GL 1997 12 31 EY2R9600904 3 19960701 G 6114 220116 HUB BNORM BN2 BN2A3 1520215 EU HARTZL HCC2Y HCC2YK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 4002 2002 AU139 HUB FOUND CORRODED. 1 H 7 2 3O A17EU 5 C P920 1997123100837 19971231 00837 GL 1997 12 31 EY2R9600905 3 19960701 G 6110 2202 SPLIT BEARING BNORM BN2 BN2A3 1520215 EU HARTZL HCC2Y HCC2YK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 4002 2002 AU139 CORROSION FOUND ON SPLIT BEARING. 1 H 7 2 3O A17EU 5 C P920 1997123100838 19971231 00838 GL 1997 12 31 EY2R9600906 3 19960701 G 6110 2202 SPLIT BEARING PIPER PA34 PA34200 7103405 SO HARTZL HCC2Y HCC2YR2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 AU1124 CORROSION FOUND ON SPLIT BEARING. 1 L 7 2 3O A7SO 5 C P920 1997123100839 19971231 00839 GL 1997 12 31 EY2R9600907 3 19960701 G 6114 32512 HUB GULSTM 500 500RKWELL 0141102 SW HARTZL HCC3Y HCC3YR GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 CK325 HUB FOUND CORRODED. 1 H 7 2 3O 6A1 5 C P25EA 1997123100840 19971231 00840 GL 1997 12 31 EY2R9600908 3 19960701 G 6114 32512 HUB GULSTM 500 500RKWELL 0141102 SW HARTZL HCC3Y HCC3YR GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 CK325 HUB FOUND CORRODED. 1 H 7 2 3O 6A1 5 C P25EA 1997123100841 19971231 00841 GL 1997 12 31 EY2R9600909 3 19960701 G 6114 32512 HUB GULSTM 500 500RKWELL 0141102 SW HARTZL HCC3Y HCC3YR GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 CK386 HUB FOUND CORRODED. 1 H 7 2 3O 6A1 5 C P25EA 1997123100842 19971231 00842 GL 1997 12 31 EY2R9600910 3 19960701 G 6110 2202 SPLIT BEARING PIPER PA30 PA39 7103902 SO HARTZL HCE2Y HCE2YL2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1889 330 BG1742 CORROSION FOUND ON SPLIT BEARING. 1 L 7 2 3O A1EA 5 C P9EA 1997123100843 19971231 00843 GL 1997 12 31 EY2R9600911 3 19960701 G 6110 2202 SPLIT BEARING PIPER PA30 PA39 7103902 SO HARTZL HCE2Y HCE2YL2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1889 330 BG1748 CORROSIONF OUND ON SPLIT BEARING. 1 L 7 2 3O A1EA 5 C P9EA 1997123100844 19971231 00844 GL 1997 12 31 EY2R9600912 3 19960801 G 6110 C4450 FERRULE BEECH 55 95A55 1152704 CE MCAULY 2AF34C 2AF34C55 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 695613 FERRULE CORRODED. 1 L 7 2 3O 3A16 5 C P5EA 1997123100845 19971231 00845 GL 1997 12 31 EY2R9600913 3 19960801 G 6114 D7015C93 HUB CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1376 799581 HUB FOUND CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997123100846 19971231 00846 GL 1997 12 31 EY2R9600914 3 19960801 G 6110 PROP CESSNA 421 421 2076010 CE MCAULY 3AF34C 3AF34C92 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 683684 PROP ASSY CORRODED 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100847 19971231 00847 GL 1997 12 31 EY2R9600915 3 19960801 G 6110 A1896 CYLINDER PIN CESSNA 421 421B 2076014 CE MCAULY 3AF34C 3AF34C92 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 703948 CYLINDER PIN FOUND CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100848 19971231 00848 GL 1997 12 31 EY2R9600916 3 19960801 G 6110 A1896 CYLINDER PIN CESSNA 421 421B 2076014 CE MCAULY 3AF34C 3AF34C92 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 783928 CYLINDER PIN FOUND CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100849 19971231 00849 GL 1997 12 31 EY2R9600917 3 19960801 G 6110 B5177 SCREW CESSNA 208 208 2073702 CE MCAULY 3AF34C 3GFR34C703 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2790 910789 CORROSION FOUND ON SCREW. 1 H 7 1 3T NT A37CE 5 C P60GL 1997123100850 19971231 00850 GL 1997 12 31 EY2R9600918 3 19960801 G 6110 A4427 RING MOONEY M20 M20 5870202 SW MCAULY 2D34C B2D34C214 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2017 539 779855 CORROSION FOUND ON RING. 1 L 7 1 3O 2A3 5 C P7EA 1997123100851 19971231 00851 GL 1997 12 31 EY2R9600919 3 19960801 G 6110 A4001 DOWEL CESSNA 182 182 2072702 CE MCAULY 2A34C C2A34C204 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 807774 DOWEL CORRODED. 1 H 7 1 3O NT 3A13 5 C P3EA 1997123100852 19971231 00852 GL 1997 12 31 EY2R9600920 3 19960801 G 6110 A1896 CYLINDER PIN CESSNA 337 337H 2075732 CE MCAULY 2AF34C D2AF34C307 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 4785 913 779147 CYLINDER PIN CORRODED. 1 H 7 2 3O A6CE 5 C P5EA 1997123100853 19971231 00853 GL 1997 12 31 EY2R9600921 3 19960801 G 6110 A4001 DOWEL CESSNA 337 337H 2075732 CE MCAULY 2AF34C D2AF34C307 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 4785 913 779147 DOWEL CORRODED. 1 H 7 2 3O A6CE 5 C P5EA 1997123100854 19971231 00854 GL 1997 12 31 EY2R9600922 3 19960801 G 6110 A1896 CYLINDER PIN CESSNA 337 337H 2075732 CE MCAULY 2AF34C D2AF34C310 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 4785 913 780550 CORROSION FOUND CYLINDER PIN. 1 H 7 2 3O A6CE 5 C P5EA 1997123100855 19971231 00855 GL 1997 12 31 EY2R9600923 3 19960801 G 6110 A4001 DOWEL CESSNA 337 337H 2075732 CE MCAULY 2AF34C D2AF34C310 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 4785 913 780550 DOWEL CORRODED. 1 H 7 2 3O A6CE 5 C P5EA 1997123100856 19971231 00856 GL 1997 12 31 EY2R9600924 3 19960801 G 6110 A1896 CYLINDER PIN CESSNA 337 337 2075702 CE MCAULY 2AF34C D2AF34C59 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 704088 CYLINDER PIN CORRODED. 1 H 7 2 3O A6CE 5 C P5EA 1997123100857 19971231 00857 GL 1997 12 31 EY2R9600925 3 19960801 G 6110 A4001 DOWEL CESSNA 337 337 2075702 CE MCAULY 2AF34C D2AF34C59 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 704088 DOWEL CORRODED. 1 H 7 2 3O A6CE 5 C P5EA 1997123100858 19971231 00858 GL 1997 12 31 EY2R9600926 3 19960801 G 6110 14B BEARING PIPER PA23 PA23 7102302 SO HARTZL HC82 HC82VL2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 K1463N BEARING CORRODED. 1 L 7 2 3O 1A10 5 C P23EA 1997123100859 19971231 00859 GL 1997 12 31 EY2R9600927 3 19960801 G 6111 PROPELLER BLADES PIPER PA23 PA23 7102302 SO HARTZL HC82X HC82XL2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 K1252 BLADES, SN'S 91373,01495, FOUND CORRODED 1 L 7 2 3O 1A10 5 C P878 1997123100860 19971231 00860 GL 1997 12 31 EY2R9600928 3 19960801 G 6110 1303A BEARING BEECH 95 B95 1153404 CE HARTZL HC92Z HC92ZK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1682F BEARING CORRODED. 1 L 7 2 3O 3A16 5 C P892 1997123100861 19971231 00861 GL 1997 12 31 EY2R9600929 3 19960801 G 6110 1331 SPLIT RING BEECH 95 B95 1153404 CE HARTZL HC92Z HC92ZK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1682F CORROSION FOUND ON SPLIT RING. 1 L 7 2 3O 3A16 5 C P892 1997123100862 19971231 00862 GL 1997 12 31 EY2R9600930 3 19960801 G 6110 83830 CLAMP BEECH 95 B95 1153404 CE HARTZL HC92Z HC92ZK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1682F CLAMP CORRODED. 1 L 7 2 3O 3A16 5 C P892 1997123100863 19971231 00863 GL 1997 12 31 EY2R9600931 3 19960801 G 6110 853 FEATHERING SPRNG BEECH 95 B95 1153404 CE HARTZL HC92Z HC92ZK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1682F CORROSION FOUND ON FEATHERING SPRING. 1 L 7 2 3O 3A16 5 C P892 1997123100864 19971231 00864 GL 1997 12 31 EY2R9600932 3 19960801 G 6110 84060 PILOT TUBE AIRTRC AT400 AT400A 0390203 SW HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BU18837 CORROSION FOUND ON PILOT TUBES. REPLACED PILOT TUBES. 1 L 7 1 3T A9SW 6 C P15EA 1997123100865 19971231 00865 GL 1997 12 31 EY2R9600933 3 19960801 G 6110 790100016 BALL BEARING AIRTRC AT400 AT400A 0390203 SW HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BU18837 BALL BEARING CORRODED. 1 L 7 1 3T A9SW 6 C P15EA 1997123100866 19971231 00866 GL 1997 12 31 EY2R9600934 3 19960801 G 6114 220117 HUB PIPER PA28 PA28R180 7102809 SO HARTZL HCC2Y HCC2YK1 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1240 770 AW1137 HUB CORRODED. 1 L 7 1 3O 2A13 5 C P920 1997123100867 19971231 00867 GL 1997 12 31 EY2R9600935 3 19960801 G 6110 2202 SPLIT BEARING PIPER PA28 PA28R180 7102809 SO HARTZL HCC2Y HCC2YK1 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1240 770 AW1137 CORROSION FOUND ON SPLIT BEARING. 1 L 7 1 3O 2A13 5 C P920 1997123100868 19971231 00868 GL 1997 12 31 EY2R9600936 3 19960801 G 6111 F7666A BLADE PIPER PA28 PA28R180 7102809 SO HARTZL HCC2Y HCC2YK1 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1240 770 AW1137 BLADE, SN B24230, FOUND CORRODED. 1 L 7 1 3O 2A13 5 C P920 1997123100869 19971231 00869 GL 1997 12 31 EY2R9600937 3 19960801 G 6111 F7666A BLADE PIPER PA28 PA28R180 7102809 SO HARTZL HCC2Y HCC2YK1 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1240 770 AW1137 BLADE, SN C3762, FOUND CORRODED. 1 L 7 1 3O 2A13 5 C P920 1997123100870 19971231 00870 GL 1997 12 31 EY2R9600938 3 19960801 G 6114 220117 HUB CONAER LA4 LA4200 5110310 NE HARTZL HCC2Y HCC2YK1 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 CH1609 HUB CORRODED. 1 H 7 1 3O 1A13 5 C P920 1997123100871 19971231 00871 GL 1997 12 31 EY2R9600939 3 19960801 G 6110 790100018 BALL BEARING BNORM BN2 BN2A3 1520215 EU HARTZL HCC2Y HCC2YK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 AU42 BALL BEARING CORRODED. 1 H 7 2 3O A17EU 5 C P920 1997123100872 19971231 00872 GL 1997 12 31 EY2R9600940 3 19960801 G 6114 24772R HUB PIPER PA23 PA23250 7102308 SO HARTZL HCE2Y HCE2YK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BP2764 HUB CORRODED. 1 L 7 2 3O 1A10 5 C P9EA 1997123100873 19971231 00873 GL 1997 12 31 EY2R9600941 3 19960901 G 6110 130035908 CAP SCREW SWRNGN SA226 SA226TC 8780404 SW ROTOL R321 R321482F8 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 11083 4352 DRG58982 CORROSION FOUND ON CAP SCREW. 2 L 7 2 4T RT A8SW 6 C P61GL 1997123100874 19971231 00874 GL 1997 12 31 EY2R9600942 3 19960901 G 6110 A10210E BOLT SWRNGN SA226 SA226TC 8780404 SW ROTOL R321 R321482F8 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 11083 4352 DRG58982 CORROSION FOUND ON BOLT. 2 L 7 2 4T RT A8SW 6 C P61GL 1997123100875 19971231 00875 GL 1997 12 31 EY2R9600943 3 19960901 G 6114 C3910C201 HUB CESSNA 180 180H 2072618 CE MCAULY 2A34C 2A34C201 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 735447 HUB CORRODED. 1 H 7 1 3O 5A6 5 C P3EA 1997123100876 19971231 00876 GL 1997 12 31 EY2R9600944 3 19960901 G 6114 C3910C203 HUB CESSNA 182 182P 2075816 CE MCAULY 2A34C 2A34C203 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 743 230 752704 HUB CORRODED. 1 H 7 1 3O NT TA13 5 C P3EA 1997123100877 19971231 00877 GL 1997 12 31 EY2R9600945 3 19960901 G 6110 C3411 BEARING RACE CESSNA 404 404CESSNA 2075901 CE MCAULY 3AF32C 3AF32C* GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 797355 BEARING RACE FOUND CORRODED. 1 L 7 2 3O A25CE 5 C P22EA 1997123100878 19971231 00878 GL 1997 12 31 EY2R9600946 3 19960901 G 6110 A16346 BALL BEARING CESSNA 402 402C 207590R CE MCAULY 3AF32C 3AF32C505 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 813310 BALL BEARING CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100879 19971231 00879 GL 1997 12 31 EY2R9600947 3 19960901 G 6110 C5270 RETAIN BEARING CESSNA 402 402C 207590R CE MCAULY 3AF32C 3AF32C505 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3745 674 841466 RETAIN BEARING FOUND CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100880 19971231 00880 GL 1997 12 31 EY2R9600948 3 19960901 G 6110 C5270 RETAIN BEARING CESSNA 402 402C 207590R CE MCAULY 3AF32C 3AF32C505 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3745 674 841467 RETAIN BEARING FOUND CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100881 19971231 00881 GL 1997 12 31 EY2R9600949 3 19960901 G 6110 A16349 BALL BEARING CESSNA 402 402C 207590R CE MCAULY 3AF32C 3AF32C505 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 861371 BALL BEARING FOUND CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100882 19971231 00882 GL 1997 12 31 EY2R9600950 3 19960901 G 6110 A4191 DOWEL CESSNA 303 T303 2073820 CE MCAULY 3AF32C 3AF32C506 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 822089 DOWEL CORRODED. 1 L 7 2 3O A34CE 5 C P57GL 1997123100883 19971231 00883 GL 1997 12 31 EY2R9600951 3 19960901 G 6110 A4191 DOWEL CESSNA 303 T303 2073820 CE MCAULY 3AF32C 3AF32C507 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 822439 DOWEL CORRODED. 1 L 7 2 3O A34CE 5 C P57GL 1997123100884 19971231 00884 GL 1997 12 31 EY2R9600952 3 19960901 G 6110 A1896 CYLINDER PIN PIPER PA34 PA34220T 7103420 SO MCAULY 3AF32C 3AF32C508 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 814783 CYLINDER PIN CORRODED. 1 L 7 2 3O A7SO 5 C P22EA 1997123100885 19971231 00885 GL 1997 12 31 EY2R9600953 3 19960901 G 6110 A4191 DOWEL PIPER PA34 PA34220T 7103420 SO MCAULY 3AF32C 3AF32C508 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 814783 DOWEL CORRODED. 1 L 7 2 3O A7SO 5 C P22EA 1997123100886 19971231 00886 GL 1997 12 31 EY2R9600954 3 19960901 G 6110 A1896 CYLINDER PIN PIPER PA34 PA34220T 7103420 SO MCAULY 3AF32C 3AF32C509 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 814791 CYLINDER PIN CORRODED. 1 L 7 2 3O A7SO 5 C P22EA 1997123100887 19971231 00887 GL 1997 12 31 EY2R9600955 3 19960901 G 6110 C5270 RETAIN BEARING BEECH 58 58 1152740 CE MCAULY 3AF32C 3AF32C512 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 940739 RETAIN BEARING. 1 L 7 2 3O 3A16 5 C P22EA 1997123100888 19971231 00888 GL 1997 12 31 EY2R9600956 3 19960901 G 6110 A1896 CYLINDER PIN CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 782818 CYLINDER PIN CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100889 19971231 00889 GL 1997 12 31 EY2R9600957 3 19960901 G 6110 A4191 DOWEL CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 782818 DOWEL CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100890 19971231 00890 GL 1997 12 31 EY2R9600958 3 19960901 G 6111 S82NC55 BLADE CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 782818 BLADE, SN K85269YS, FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100891 19971231 00891 GL 1997 12 31 EY2R9600959 3 19960901 G 6111 S82NC55 BLADE CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 782818 BLADE, SN K85267YS, FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100892 19971231 00892 GL 1997 12 31 EY2R9600960 3 19960901 G 6110 A1896 CYLINDER PIN CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 804818 CYLINDER PIN FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100893 19971231 00893 GL 1997 12 31 EY2R9600961 3 19960901 G 6110 A4191 DOWEL CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 804818 DOWEL CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100894 19971231 00894 GL 1997 12 31 EY2R9600962 3 19960901 G 6110 A1896 CYLINDER PIN CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 753330 CYLINDER PIN FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100895 19971231 00895 GL 1997 12 31 EY2R9600963 3 19960901 G 6110 A1896 CYLINDER PIN CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 4772 788627 CYLINDER PIN FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100896 19971231 00896 GL 1997 12 31 EY2R9600964 3 19960901 G 6110 A1896 CYLINDER PIN CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 4772 789445 CYLINDER PIN FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100897 19971231 00897 GL 1997 12 31 EY2R9600965 3 19960901 G 6110 A4191 DOWEL CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 753330 DOWEL CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100898 19971231 00898 GL 1997 12 31 EY2R9600966 3 19960901 G 6110 A4191 DOWEL CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 4772 788627 DOWEL CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100899 19971231 00899 GL 1997 12 31 EY2R9600967 3 19960901 G 6110 A4191 DOWEL CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 4772 789445 DOWEL CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100900 19971231 00900 GL 1997 12 31 EY2R9600968 3 19960901 G 6110 B3490 PISTON ROD PIN CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 753330 PISTON ROD PIN FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100901 19971231 00901 GL 1997 12 31 EY2R9600969 3 19960901 G 6110 C2987 RETAIN BEARING CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 753330 RETAIN BEARING FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100902 19971231 00902 GL 1997 12 31 EY2R9600970 3 19960901 G 6110 C7036 NUT CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 753330 CORROSION FOUND ON NUT. 1 L 7 2 3O 3A10 5 C P22EA 1997123100903 19971231 00903 GL 1997 12 31 EY2R9600971 3 19960901 G 6110 A1896 CYLINDER PIN CESSNA 335 335 2075601 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 798440 CYLINDER PIN FOUND CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997123100904 19971231 00904 GL 1997 12 31 EY2R9600972 3 19960901 G 6110 A1896 CYLINDER PIN CESSNA 335 335 2075601 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 798443 CYLINDER PIN FOUND CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997123100905 19971231 00905 GL 1997 12 31 EY2R9600973 3 19960901 G 6110 A4191 DOWEL CESSNA 335 335 2075601 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 798440 DOWEL CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997123100906 19971231 00906 GL 1997 12 31 EY2R9600974 3 19960901 G 6110 A4191 DOWEL CESSNA 335 335 2075601 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 798443 DOWEL CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997123100907 19971231 00907 GL 1997 12 31 EY2R9600975 3 19960901 G 6110 B3490 PISTON ROD PIN CESSNA 335 335 2075601 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 798443 PISTON ROD PIN FOUND CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997123100908 19971231 00908 GL 1997 12 31 EY2R9600976 3 19960901 G 6110 C2987 RETAIN BEARING CESSNA 335 335 2075601 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 798443 RETAIN BEARING FOUND CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997123100909 19971231 00909 GL 1997 12 31 EY2R9600977 3 19960901 G 6110 C7036 NUT CESSNA 335 335 2075601 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 798443 NUT CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997123100910 19971231 00910 GL 1997 12 31 EY2R9600978 3 19960901 G 6110 A1896 CYLINDER PIN CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 911178 CORROSION FOUND ON CYLINDER PIN. 1 L 7 2 3O 3A10 5 C P22EA 1997123100911 19971231 00911 GL 1997 12 31 EY2R9600979 3 19960901 G 6110 A4191 DOWEL CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 911178 DOWEL CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100912 19971231 00912 GL 1997 12 31 EY2R9600980 3 19960901 G 6110 B3490 PISTON ROD PIN CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 911178 PISTON ROD PIN FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100913 19971231 00913 GL 1997 12 31 EY2R9600981 3 19960901 G 6110 C7036 NUT CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 911178 CORROSION FOUND ON NUT. 1 L 7 2 3O 3A10 5 C P22EA 1997123100914 19971231 00914 GL 1997 12 31 EY2R9600982 3 19960901 G 6110 B4460 BLADE ACT PIN CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 940196 BLADE ACT PIN FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100915 19971231 00915 GL 1997 12 31 EY2R9600983 3 19960901 G 6114 D7015C87 HUB CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 745607 HUB CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100916 19971231 00916 GL 1997 12 31 EY2R9600984 3 19960901 G 6114 D7015C87 HUB CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1772 783143 HUB CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1997123100917 19971231 00917 GL 1997 12 31 EY2R9600985 3 19960901 G 6110 A18961 CYLINDER PIN CESSNA 414 414A 2075907 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3436 1174 782013 CYLINDER PIN FOUND CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100918 19971231 00918 GL 1997 12 31 EY2R9600986 3 19960901 G 6110 A4191 DOWEL CESSNA 414 414A 2075907 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3436 1174 782013 DOWEL CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100919 19971231 00919 GL 1997 12 31 EY2R9600987 3 19960901 G 6110 C7036 NUT CESSNA 414 414A 2075907 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3436 1174 782013 NUT CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100920 19971231 00920 GL 1997 12 31 EY2R9600988 3 19960901 G 6110 C3411 BEARING RACE PIPER PA34 PA34200T 7103406 SO MCAULY 3AF34C 3AF34C502 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3021 975 789767 BEARING RACE FOUND CORRODED. 1 L 7 2 3O A7SO 5 C P22EA 1997123100921 19971231 00921 GL 1997 12 31 EY2R9600989 3 19960901 G 6111 S82NC55 BLADE CESSNA 402 402CESSNA 207590K CE MCAULY 3AF34C 3AF34C92 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 803690 BLADE, SN BD1023YS, FOUND CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100922 19971231 00922 GL 1997 12 31 EY2R9600990 3 19960901 G 6110 A1896 CYLINDER PIN CESSNA 421 421C 2076016 CE MCAULY 3FF32 3FF32C501 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 763069 CYLINDER PIN FOUND CORRODED. 1 L 7 2 3O A7CE 5 C P45GL 1997123100923 19971231 00923 GL 1997 12 31 EY2R9600991 3 19960901 G 6110 A4191 DOWEL CESSNA 421 421C 2076016 CE MCAULY 3FF32 3FF32C501 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 763069 DOWEL CORRODED. 1 L 7 2 3O A7CE 5 C P45GL 1997123100924 19971231 00924 GL 1997 12 31 EY2R9600992 3 19960901 G 6110 B5177 SCREW CESSNA 208 208 2073702 CE MCAULY 3AF34C 3GFR34C703 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2848 902582 CORROSION FOUND ON SCREW. 1 H 7 1 3T NT A37CE 5 C P60GL 1997123100925 19971231 00925 GL 1997 12 31 EY2R9600993 3 19960901 G 6111 G78TCA0 BLADE CESSNA 177 177RG 2073709 CE MCAULY 2D34C B2D34C207 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1256 582 832495 BLADE, SN DF067, FOUND CORRODED. 1 H 7 1 3O A20CE 5 C P7EA 1997123100926 19971231 00926 GL 1997 12 31 EY2R9600994 3 19960901 G 6111 G78TCA0 BLADE CESSNA 177 177RG 2073709 CE MCAULY 2D34C B2D34C207 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1256 582 832495 BLADE, SN DF052, FOUND CORRODED. 1 H 7 1 3O A20CE 5 C P7EA 1997123100927 19971231 00927 GL 1997 12 31 EY2R9600995 3 19960901 G 6110 A3124 GUIDE SPRING CESSNA 182 182 2072702 CE MCAULY 2D34C B2D34C214 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3465 1803 783681 GUIDE SPRING FOUND CORRODED. 1 H 7 1 3O NT 3A13 5 C P7EA 1997123100928 19971231 00928 GL 1997 12 31 EY2R9600996 3 19960901 G 6110 C4451 FERRULE CESSNA 206 P206A 2073308 CE MCAULY 3A32C D3A32C90 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 851261 FERRULE CORRODED. 1 H 7 1 3O A4CE 5 C P21EA 1997123100929 19971231 00929 GL 1997 12 31 EY2R9600997 3 19960901 G 6110 14B BEARING HELIO H395 H395A 4300206 CE HARTZL HC82V HC82V201 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 7682N BEARING CORRODED. 1 H 7 1 3O 1A8 5 C P23EA 1997123100930 19971231 00930 GL 1997 12 31 EY2R9600998 3 19960901 G 6110 83810 CLAMP PIPER PA23 PA23 7102302 SO HARTZL HCA2V HCA2VK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 5507 1755 H1062 CORROSION FOUND ON CLAMP. 1 L 7 2 3O 1A10 5 C P24EA 1997123100931 19971231 00931 GL 1997 12 31 EY2R9600999 3 19960901 G 6110 971 SPLIT BEARING PIPER PA23 PA23 7102302 SO HARTZL HCA2V HCA2VK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 5507 1755 H1062 CORROSION FOUND ON SPLIT BEARING. 1 L 7 2 3O 1A10 5 C P24EA 1997123100932 19971231 00932 GL 1997 12 31 EY2R9601000 3 19960901 G 6110 1977 CLAMP DOUG B18 B18A 3020605 WP HARTZL HCB3R HCB3R302 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 CORROSION FOUND ON CLAMP. 2 M 7 2 4R 2577 5 C P28EA 1997123100933 19971231 00933 GL 1997 12 31 EY2R9601001 3 19960901 G 6110 13081 PILOT TUBE BEECH 80 65B80 1152812 CE HARTZL HCB3Z HCB3Z302 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 831J PILOT TUBE FOUND CORRODED. 1 L 7 2 3O 3A20 5 C P907 1997123100934 19971231 00934 GL 1997 12 31 EY2R9601002 3 19960901 G 6110 1851 BEARING BEECH 80 65B80 1152812 CE HARTZL HCB3Z HCB3Z302 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 831J BEARING CORRODED. 1 L 7 2 3O 3A20 5 C P907 1997123100935 19971231 00935 GL 1997 12 31 EY2R9601003 3 19960901 G 6110 1851 BEARING BEECH 80 65B80 1152812 CE HARTZL HCB3Z HCB3Z302 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 865J BEARING CORRODED. 1 L 7 2 3O 3A20 5 C P907 1997123100936 19971231 00936 GL 1997 12 31 EY2R9601004 3 19960901 G 6110 83817 CLAMP BEECH 80 65B80 1152812 CE HARTZL HCB3Z HCB3Z302 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 831J CORROSION FOUND ON CLAMP. 1 L 7 2 3O 3A20 5 C P907 1997123100937 19971231 00937 GL 1997 12 31 EY2R9601005 3 19960901 G 6110 83817 CLAMP BEECH 80 65B80 1152812 CE HARTZL HCB3Z HCB3Z302 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 865J CORROSION FOUND ON CLAMP. 1 L 7 2 3O 3A20 5 C P907 1997123100938 19971231 00938 GL 1997 12 31 EY2R9601006 3 19960901 G 6114 32511R HUB CESSNA 207 207 2073602 CE HARTZL HCC3Y HCC3YR GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 225 DY2050 HUB CORRODED. 1 H 7 1 3O A16CE 5 C P25EA 1997123100939 19971231 00939 NE 1997 12 31 EY2R9601007 3 19960901 G 6114 3932 HUB BEECH 1900 1900D 1154162 CE HARTZL HCE4A HCE4A3A NE PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 HJ117A HUB CORRODED. 2 L 7 2 4T RT A24CE 5 C P10NE 1997123100940 19971231 00940 GL 1997 12 31 EY2R9601008 3 19961001 G 6111 90DA8 BLADE CESSNA 182 182P 2075816 CE MCAULY 2A34C 2A34C201 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 72258 BLADE, SN B12911, FOUND CORRODED. 1 H 7 1 3O NT TA13 5 C P3EA 1997123100941 19971231 00941 GL 1997 12 31 EY2R9601009 3 19961001 G 6111 90DA8 BLADE CESSNA 182 182P 2075816 CE MCAULY 2A34C 2A34C201 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 72258 BLADE, SN B12748, FOUND CORRODED. 1 H 7 1 3O NT TA13 5 C P3EA 1997123100942 19971231 00942 GL 1997 12 31 EY2R9601010 3 19961001 G 6111 90DHB16E BLADE MOONEY M20 M20K 5870220 SW MCAULY 2A34C 2A34C* GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 821428 BLADE, SN H1099, FOUND CORRODED. 1 L 7 1 3O 2A3 5 C P3EA 1997123100943 19971231 00943 GL 1997 12 31 EY2R9601011 3 19961001 G 6111 90DHB16E BLADE MOONEY M20 M20K 5870220 SW MCAULY 2A34C 2A34C* GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 821428 BLADE, SN H1087, FOUND CORRODED. 1 L 7 1 3O 2A3 5 C P3EA 1997123100944 19971231 00944 GL 1997 12 31 EY2R9601012 3 19961001 G 6111 82NEA55 BLADE CESSNA 402 402CESSNA 207590K CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 816080 BLADE, SN BD618, FOUND CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100945 19971231 00945 GL 1997 12 31 EY2R9601013 3 19961001 G 6114 D5888C505 HUB CESSNA 402 402CESSNA 207590K CE MCAULY 3AF32C 3AF32C505 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 815922 HUB CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100946 19971231 00946 GL 1997 12 31 EY2R9601014 3 19961001 G 6111 S82NC4 BLADE CESSNA 320 320D 2074512 CE MCAULY 3AF32C 3AF32C72 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 686532 BLADE, SN C33529YS, FOUND CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997123100947 19971231 00947 GL 1997 12 31 EY2R9601015 3 19961001 G 6114 D7015C87 HUB CESSNA 402 402B 207590P CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 73270 HUB CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100948 19971231 00948 GL 1997 12 31 EY2R9601016 3 19961001 G 6114 D7015C87 HUB CESSNA 402 402B 207590P CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 732094 HUB CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100949 19971231 00949 GL 1997 12 31 EY2R9601017 3 19961001 G 6111 S82NC55 BLADE CESSNA 402 402B 207590P CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 73270 BLADE, SN F35476YS, FOUND CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100950 19971231 00950 GL 1997 12 31 EY2R9601018 3 19961001 G 6111 S82NC55 BLADE CESSNA 402 402B 207590P CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 73270 BLADE, SN F35761YS, FOUND CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100951 19971231 00951 GL 1997 12 31 EY2R9601019 3 19961001 G 6111 S82NC55 BLADE CESSNA 402 402B 207590P CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 73270 BLADE, SN F33462YS, FOUND CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100952 19971231 00952 GL 1997 12 31 EY2R9601020 3 19961001 G 6111 S82NC55 BLADE CESSNA 402 402B 207590P CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 732094 BLADE, SN F35930YS, FOUND CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100953 19971231 00953 GL 1997 12 31 EY2R9601021 3 19961001 G 6111 S82NC55 BLADE CESSNA 402 402B 207590P CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 732094 BLADE, SN F35903YS, FOUND CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100954 19971231 00954 GL 1997 12 31 EY2R9601022 3 19961001 G 6111 S82NC55 BLADE CESSNA 402 402B 207590P CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 732094 BLADE, SN F35778YS, FOUND CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100955 19971231 00955 GL 1997 12 31 EY2R9601023 3 19961001 G 6111 S82NC55 BLADE CESSNA 402 402CESSNA 207590K CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 798951 BLADE, SN F41236YS, FOUND CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100956 19971231 00956 GL 1997 12 31 EY2R9601024 3 19961001 G 6111 S82NC55 BLADE CESSNA 402 402CESSNA 207590K CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 798951 BLADE, SN F41359YS, FOUND CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100957 19971231 00957 GL 1997 12 31 EY2R9601025 3 19961001 G 6111 BLADE CESSNA 402 402C 207590R CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 799131 BLADES, SN'S K100294YS, K100298YS, K100724YS, FOUND CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100958 19971231 00958 GL 1997 12 31 EY2R9601026 3 19961001 G 6110 C3903 SPLIT RETAINER CESSNA 421 421 2076010 CE MCAULY 3FF32 3FF32C501 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 841269 CORROSION FOUND ON SPLIT RETAINER. 1 L 7 2 3O RT A7CE 5 C P45GL 1997123100959 19971231 00959 GL 1997 12 31 EY2R9601027 3 19961001 G 6110 C5270 RETAIN BEARING CESSNA 421 421 2076010 CE MCAULY 3FF32 3FF32C501 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 841269 RETAIN BEARING CORRODED. 1 L 7 2 3O RT A7CE 5 C P45GL 1997123100960 19971231 00960 GL 1997 12 31 EY2R9601028 3 19961001 G 6110 D40099 SLIP RING CESSNA 421 421 2076010 CE MCAULY 3FF32 3FF32C501 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 841269 CORROSION FOUND ON SPLIT RING. 1 L 7 2 3O RT A7CE 5 C P45GL 1997123100961 19971231 00961 GL 1997 12 31 EY2R9601029 3 19961001 G 6114 220118 HUB PIPER PA34 PA34200T 7103406 SO HARTZL HCC2Y BHCC2YF2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 AN5991 HUB CORRODED. 1 L 7 2 3O A7SO 5 C P920 1997123100962 19971231 00962 GL 1997 12 31 EY2R9601030 3 19961001 G 6111 90AT4 BLADE CESSNA 188 188CESSNA 2073002 CE MCAULY 2A34C D2A34C98 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 902390 BLADE, SN KH07445, FOUND CORRODED. 1 L 7 1 3O A9CE 5 C P3EA 1997123100963 19971231 00963 GL 1997 12 31 EY2R9601031 3 19961001 G 6111 90AT4 BLADE CESSNA 188 188CESSNA 2073002 CE MCAULY 2A34C D2A34C98 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 902390 BLADE, SN KH06645, FOUND CORRODED. 1 L 7 1 3O A9CE 5 C P3EA 1997123100964 19971231 00964 GL 1997 12 31 EY2R9601032 3 19961001 G 6111 80GF0 BLADE CESSNA 310 310 2074202 CE MCAULY 2AF34C D2AF34C52 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 751077 BLADE, SN C30806YS, FOUND CORRODED. 1 L 7 2 3O RT 3A10 5 C P5EA 1997123100965 19971231 00965 GL 1997 12 31 EY2R9601033 3 19961001 G 6111 80GF0 BLADE CESSNA 310 310 2074202 CE MCAULY 2AF34C D2AF34C52 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 751077 BLADE, SN B29888YS, FOUND CORRODED. 1 L 7 2 3O RT 3A10 5 C P5EA 1997123100966 19971231 00966 GL 1997 12 31 EY2R9601034 3 19961001 G 6111 90DFA10 BLADE CESSNA 210 210 2073402 CE MCAULY D3A34 D3A34C402 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 788478 BLADE, SN B136412, FOUND CORRODED. 1 H 7 1 3O RT 3A21 5 C P47GL 1997123100967 19971231 00967 GL 1997 12 31 EY2R9601035 3 19961001 G 6111 90DFA10 BLADE CESSNA 210 210 2073402 CE MCAULY D3A34 D3A34C402 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 788478 BLADE, SN B09515, FOUND CORRODED. 1 H 7 1 3O RT 3A21 5 C P47GL 1997123100968 19971231 00968 GL 1997 12 31 EY2R9601036 3 19961001 G 6111 90DFA10 BLADE CESSNA 210 210 2073402 CE MCAULY D3A34 D3A34C402 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 788478 BLADE, SN B98523, FOUND CORRODED. 1 H 7 1 3O RT 3A21 5 C P47GL 1997123100969 19971231 00969 GL 1997 12 31 EY2R9601037 3 19961001 G 6110 C5264 CYLINDER CESSNA 210 210 2073402 CE MCAULY D3A34 D3A34C402 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 788478 CYLINDER CORRODED. 1 H 7 1 3O RT 3A21 5 C P47GL 1997123100970 19971231 00970 GL 1997 12 31 EY2R9601038 3 19961001 G 6114 D5858C402 HUB CESSNA 210 210 2073402 CE MCAULY D3A34 D3A34C402 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 788478 HUB CORRODED. 1 H 7 1 3O RT 3A21 5 C P47GL 1997123100971 19971231 00971 GL 1997 12 31 EY2R9601039 3 19961001 G 6110 971 SPLIT BEARING GULSTM 500 500RKWELL 0141102 SW HARTZL HCA2X HCA2XF2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 H107 CORROSION FOUND ON SPLIT BEARING. 1 H 7 2 3O 6A1 5 C P908 1997123100972 19971231 00972 GL 1997 12 31 EY2R9601040 3 19961001 G 6110 84082 PILOT TUBE BEECH 80 65A80 1152808 CE HARTZL HCA3V HCA3VK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1472 944 BJ468 R & R PILOT TUBES 1 L 7 2 3O 3A20 5 C P6EA 1997123100973 19971231 00973 GL 1997 12 31 EY2R9601041 3 19961001 G 6110 84082 PILOT TUBE BEECH 80 65A80 1152808 CE HARTZL HCA3V HCA3VK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1472 944 BJ481 R & R PILOT TUBES 1 L 7 2 3O 3A20 5 C P6EA 1997123100974 19971231 00974 GL 1997 12 31 EY2R9601042 3 19961001 G 6110 971 SPLIT BEARING BEECH 58 58 1152740 CE HARTZL HCA3V HCA3VK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1472 944 BJ481 CORROSION FOUND ON SPLIT BEARING. 1 L 7 2 3O 3A16 5 C P6EA 1997123100975 19971231 00975 GL 1997 12 31 EY2R9601043 3 19961001 G 6111 V84332R BLADE BEECH 80 65A80 1152808 CE HARTZL HCA3V HCA3VK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1472 944 BJ468 BLADE, SN B69968, FOUND CORRODED. 1 L 7 2 3O 3A20 5 C P6EA 1997123100976 19971231 00976 GL 1997 12 31 EY2R9601044 3 19961001 G 6111 V84332R BLADE BEECH 80 65A80 1152808 CE HARTZL HCA3V HCA3VK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1472 944 BJ468 BLADE, SN A20549, FOUND CORRODED. 1 L 7 2 3O 3A20 5 C P6EA 1997123100977 19971231 00977 GL 1997 12 31 EY2R9601045 3 19961001 G 6111 V84332R BLADE BEECH 80 65A80 1152808 CE HARTZL HCA3V HCA3VK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1472 944 BJ468 BLADE, SN 111092, FOUND CORRODED. 1 L 7 2 3O 3A20 5 C P6EA 1997123100978 19971231 00978 GL 1997 12 31 EY2R9601046 3 19961001 G 6114 24772 HUB PIPER PA23 PA23250 7102308 SO HARTZL HCE2Y HCE2YR2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1998 BP1655 HUB CORRODED. 1 L 7 2 3O 1A10 5 C P9EA 1997123100979 19971231 00979 GL 1997 12 31 EY2R9601047 3 19961001 G 6114 24772 HUB PIPER PA23 PA23250 7102308 SO HARTZL HCE2Y HCE2YR2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1998 BP5731 CORROSION FOUND ON HUB. 1 L 7 2 3O 1A10 5 C P9EA 1997123100980 19971231 00980 GL 1997 12 31 EY2R9601048 3 19960901 G 6110 C5971 COUNTERWEIGHT CESSNA 402 402CESSNA 207590K CE MCAULY 3AF32C 3AF32C505 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1500 921207 COUNTERWEIGHT CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100981 19971231 00981 GL 1997 12 31 EY2R9601049 3 19960901 G 6110 C2987 RETAIN BEARING CESSNA 402 402CESSNA 207590K CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 743983 RETAIN BEARING FOUND CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1997123100982 19971231 00982 GL 1997 12 31 EY2R9601050 3 19960901 G 6110 C2987 RETAIN BEARING CESSNA 340 340CESSNA 2076404 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 764989 RETAIN BEARING FOUND CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997123100983 19971231 00983 GL 1997 12 31 EY2R9601051 3 19960901 G 6110 C2987 RETAIN BEARING CESSNA 340 340CESSNA 2076404 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 801079 RETAIN BEARING FOUND CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997123100984 19971231 00984 GL 1997 12 31 EY2R9601052 3 19960901 G 6110 C3475 NUT CESSNA 320 320 2074502 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 760968 NUT CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997123100985 19971231 00985 GL 1997 12 31 EY2R9601053 3 19960901 G 6110 C3475 NUT CESSNA 320 320 2074502 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 764755 NUT CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997123100986 19971231 00986 GL 1997 12 31 EY2R9601054 3 19960901 G 6110 C3475 NUT CESSNA 340 340CESSNA 2076404 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 801079 NUT CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997123100987 19971231 00987 GL 1997 12 31 EY2R9601055 3 19960901 G 6110 C3550 FEATHER CYLINDER CESSNA 320 320 2074502 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 764755 CORROSION FOUND ON FEATHER CYLINDER. 1 L 7 2 3O 3A25 5 C P22EA 1997123100988 19971231 00988 GL 1997 12 31 EY2R9601056 3 19960901 G 6111 S82NC4 BLADE CESSNA 340 340CESSNA 2076404 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 713447 BLADE, SN F25242YS, FOUND CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1997123100989 19971231 00989 GL 1997 12 31 EY2R9601057 3 19960901 G 6110 C2987 RETAIN BEARING CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 768641 RETAIN BEARING FOUND CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100990 19971231 00990 GL 1997 12 31 EY2R9601058 3 19960901 G 6110 C3475 NUT CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 768641 NUT CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1997123100991 19971231 00991 GL 1997 12 31 EY2R9601059 3 19960901 G 6110 2202 SPLIT BEARING BEECH 55 9555 1152702 CE HARTZL HCJ2Y BHCJ2YF2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 DZ442 CORROSION FOUND ON SPLIT BEARING. 1 L 7 2 3O 3A16 5 C P37EA 1997123100992 19971231 00992 GL 1997 12 31 EY2R9601060 3 19960901 G 6110 A4577 LINK CESSNA 210 210 2073402 CE MCAULY D3A34 D3A34C402 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 840414 CORROSION FOUND ON LINK. 1 H 7 1 3O RT 3A21 5 C P47GL 1997123100993 19971231 00993 GL 1997 12 31 EY2R9601061 3 19960901 G 6110 C4784 PISTON CESSNA 210 210 2073402 CE MCAULY D3A34 D3A34C402 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 840414 PISTON CORRODED. 1 H 7 1 3O RT 3A21 5 C P47GL 1997123100994 19971231 00994 GL 1997 12 31 EY2R9601062 3 19960901 G 6110 C5264 CYLINDER CESSNA 210 210 2073402 CE MCAULY D3A34 D3A34C402 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 840414 CYLINDER CORRODED. 1 H 7 1 3O RT 3A21 5 C P47GL 1997123100995 19971231 00995 GL 1997 12 31 EY2R9601063 3 19960901 G 6110 C2987 RETAIN BEARING CESSNA 310 310 2074202 CE MCAULY 3AF32C D3AF32C80 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 798498 RETAIN BEARING FOUND CORRODED. 1 L 7 2 3O RT 3A10 5 C P22EA 1997123100996 19971231 00996 GL 1997 12 31 EY2R9601064 3 19960901 G 6110 C3475 NUT CESSNA 310 310 2074202 CE MCAULY 3AF32C D3AF32C80 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 798498 NUT CORRODED. 1 L 7 2 3O RT 3A10 5 C P22EA 1997123100997 19971231 00997 GL 1997 12 31 EY2R9601065 3 19960901 G 6110 1303A BEARING CONAER LA4 LA4 5110302 NE HARTZL HC92W HC92W* GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2404Z BEARING CORRODED. 1 H 7 1 3O 1A13 5 C P16EA 1997123100998 19971231 00998 GL 1997 12 31 EY2R9601066 3 19960901 G 6110 2202 SPLIT BEARING BEECH 58 58TC 1152746 CE HARTZL HCJ3Y PHCJ3YF2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 ED952 CORROSION FOUND ON SPLIT BEARING. 1 L 7 2 3O A23CE 5 C P36EA 1998042900132 19980429 00132 GL 1998 4 29 EY2R9601067 3 19961001 G 6114 C3910C201 HUB CESSNA 182 182 2072702 CE MCAULY 2A34C 2A34C201 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 800691 HUB CORRODED. 1 H 7 1 3O NT 3A13 5 C P3EA 1998042900133 19980429 00133 GL 1998 4 29 EY2R9601068 3 19961001 G 6114 C3910C203 HUB CESSNA 182 182 2072702 CE MCAULY 2A34C 2A34C203 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 742514 HUB CORRODED. 1 H 7 1 3O NT 3A13 5 C P3EA 1998042900134 19980429 00134 GL 1998 4 29 EY2R9601069 3 19961001 G 6114 C3910C203 HUB CESSNA 182 182 2072702 CE MCAULY 2A34C 2A34C203 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 756040 HUB CORRODED. 1 H 7 1 3O NT 3A13 5 C P3EA 1998042900135 19980429 00135 GL 1998 4 29 EY2R9601070 3 19961001 G 6110 A4001 DOWEL CESSNA 182 182P 2075816 CE MCAULY 2A34C 2A34C203 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 870628 DOWEL CORRODED. 1 H 7 1 3O NT TA13 5 C P3EA 1998042900136 19980429 00136 GL 1998 4 29 EY2R9601071 3 19961001 G 6111 S90AT8 BLADE CESSNA 188 188CESSNA 2073002 CE MCAULY 2A34C 2A34C66 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BLADE, SN B23171YS, FOUND CORRODED. 1 L 7 1 3O A9CE 5 C P3EA 1998042900137 19980429 00137 GL 1998 4 29 EY2R9601072 3 19961001 G 6111 S90AT8 BLADE CESSNA 188 188CESSNA 2073002 CE MCAULY 2A34C 2A34C66 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BLADE, SN B20147YS, FOUND CORRODED. 1 L 7 1 3O A9CE 5 C P3EA 1998042900138 19980429 00138 GL 1998 4 29 EY2R9601073 3 19961001 G 6114 C4526C29 HUB CESSNA 180 180H 2072618 CE MCAULY 2A36C 2A36C29 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 62347 HUB CORRODED. 1 H 7 1 3O 5A6 5 C P880 1998042900139 19980429 00139 GL 1998 4 29 EY2R9601074 3 19961001 G 6114 C4526C29 HUB CESSNA 180 180G 2072616 CE MCAULY 2A36C 2A36C29 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 591058 HUB CORRODED. 1 H 7 1 3O 5A6 5 C P880 1998042900140 19980429 00140 NE 1998 4 29 EY2R9601075 3 19961001 G 6110 55210 PROPELLER STNSON SM8 SM8A 8630802 GL HAMSTD 2B 2B20 NE PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 101 T20363 CORRODED PROP ASSY 1 H 7 1 3R ATC295 5 C P255 1998042900141 19980429 00141 GL 1998 4 29 EY2R9601076 3 19961001 G 6111 82NB2 BLADE BEECH 36 A36 1151604 CE MCAULY 3A32C 3A32C76 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BLADE, SN C44573YS, FOUND CORRODED. 1 L 7 1 3O 3A15 5 C P21EA 1998042900142 19980429 00142 GL 1998 4 29 EY2R9601077 3 19961001 G 6111 BLADES BEECH 33 F33A 1151425 CE MCAULY 3A32C 3A32C76 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 781601 BLADES, SN'S K91889YS,K92027YS,K91828YS, FOUND CORRODED. 1 L 7 1 3O 3A15 5 C P21EA 1998042900143 19980429 00143 GL 1998 4 29 EY2R9601078 3 19961001 G 6110 A1896 PIN CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C505 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1858 755 851043 CORROSION FOUND ON CYLINDER PIN. 1 L 7 2 3O RT A7CE 5 C P22EA 1998042900144 19980429 00144 GL 1998 4 29 EY2R9601079 3 19961001 G 6110 A4191 DOWEL CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C505 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1858 755 851043 DOWEL CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1998042900145 19980429 00145 GL 1998 4 29 EY2R9601080 3 19961001 G 6110 A16349 BEARING CESSNA 402 402C 207590R CE MCAULY 3AF32C 3AF32C505 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1501 940211 BALL BEARING CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1998042900146 19980429 00146 GL 1998 4 29 EY2R9601081 3 19961001 G 6110 A1896 PIN BEECH 58 58 1152740 CE MCAULY 3AF32C 3AF32C512 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 625 920675 CYLINDER PIN CORRODED. 1 L 7 2 3O 3A16 5 C P22EA 1998042900147 19980429 00147 GL 1998 4 29 EY2R9601082 3 19961001 G 6110 A4191 DOWEL BEECH 58 58 1152740 CE MCAULY 3AF32C 3AF32C512 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 625 920675 DOWEL CORRODED. 1 L 7 2 3O 3A16 5 C P22EA 1998042900148 19980429 00148 GL 1998 4 29 EY2R9601083 3 19961001 G 6114 D6468C8 HUB BEECH 23 A23 1151204 CE MCAULY 3AF32C 3AF32C* GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 686186 HUB CORRODED. 1 L 7 1 3O A1CE 5 C P22EA 1998042900149 19980429 00149 GL 1998 4 29 EY2R9601084 3 19961001 G 6111 S82NC55 BLADE CESSNA 402 402CESSNA 207590K CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BLADE, SN K62383YS, FOUND CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1998042900150 19980429 00150 GL 1998 4 29 EY2R9601085 3 19961001 G 6111 S82NC55 BLADE CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 739707 BLADE FOUND CORRODED. 1 L 7 2 3O RT 3A10 5 C P22EA 1998042900151 19980429 00151 GL 1998 4 29 EY2R9601086 3 19961001 G 6114 D7015C87 HUB CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 684435 HUB FOUND CORRODED. 1 L 7 2 3O RT 3A10 5 C P22EA 1998042900152 19980429 00152 GL 1998 4 29 EY2R9601087 3 19961001 G 6111 S82NC4 BLADE CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 684435 BLADE, SN C41944YS, FOUND CORRODED. 1 L 7 2 3O RT 3A10 5 C P22EA 1998042900153 19980429 00153 GL 1998 4 29 EY2R9601088 3 19961001 G 6110 A1896 CYLINDER PIN CESSNA 310 310P 2074238 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 696 727378 CYLINDER PIN FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1998042900154 19980429 00154 GL 1998 4 29 EY2R9601089 3 19961001 G 6110 A4191 DOWEL CESSNA 310 310P 2074238 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 696 727378 DOWEL CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1998042900155 19980429 00155 GL 1998 4 29 EY2R9601090 3 19961001 G 6110 B3490 PIN CESSNA 310 310P 2074238 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 696 727378 CORROSION FOUND ON PISTON ROD PIN. 1 L 7 2 3O 3A10 5 C P22EA 1998042900156 19980429 00156 GL 1998 4 29 EY2R9601091 3 19961001 G 6110 B4459 BLADE ACT PIN CESSNA 310 310P 2074238 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 696 727378 BLADE ACT PIN FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1998042900157 19980429 00157 GL 1998 4 29 EY2R9601092 3 19961001 G 6110 C3550 CYLINDER CESSNA 310 310P 2074238 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 696 727378 CORROSION FOUND ON FEATHER C YLINDER. 1 L 7 2 3O 3A10 5 C P22EA 1998042900158 19980429 00158 GL 1998 4 29 EY2R9601093 3 19961001 G 6111 S82NC4 BLADE CESSNA 310 310P 2074238 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 696 727378 BLADE, SN BG397YS, FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1998042900159 19980429 00159 GL 1998 4 29 EY2R9601094 3 19961001 G 6110 A1896 PIN CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2780 1480 746034 CYLINDER PIN FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1998042900160 19980429 00160 GL 1998 4 29 EY2R9601095 3 19961001 G 6110 A1896 PIN CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2780 771292 CYLINDER PIN FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1998042900161 19980429 00161 GL 1998 4 29 EY2R9601096 3 19961001 G 6110 A4191 DOWEL CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2780 1480 746034 DOWEL CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1998042900162 19980429 00162 GL 1998 4 29 EY2R9601097 3 19961001 G 6110 A4191 DOWEL CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2780 771292 DOWEL CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1998042900163 19980429 00163 GL 1998 4 29 EY2R9601098 3 19961001 G 6110 C3550 CYLINDER CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2780 1480 746034 CORROSION FOUND ON CYLINDER. 1 L 7 2 3O 3A10 5 C P22EA 1998042900164 19980429 00164 GL 1998 4 29 EY2R9601099 3 19961001 G 6111 S82NC55 BLADE CESSNA 402 402CESSNA 207590K CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BLADE, SN K103232YS, FOUND ON CYLINDER. 1 L 7 2 3O A7CE 5 C P22EA 1998042900165 19980429 00165 GL 1998 4 29 EY2R9601100 3 19961001 G 6110 C4451 FERRULE CESSNA 310 310P 2074238 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1229 673758 FERRULE FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1998042900166 19980429 00166 GL 1998 4 29 EY2R9601101 3 19961001 G 6114 D7015C87 HUB CESSNA 310 310P 2074238 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1229 673758 HUB CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1998042900167 19980429 00167 GL 1998 4 29 EY2R9601102 3 19961001 G 6111 82NC55 BLADE CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 795369 BLADE, SN K82853YS, FOUND CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1998042900168 19980429 00168 GL 1998 4 29 EY2R9601103 3 19961001 G 6111 82NC55 BLADE CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 795369 BLADE, SN K82928YS, FOUND CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1998042900169 19980429 00169 GL 1998 4 29 EY2R9601104 3 19961001 G 6110 A1896 PIN CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 795369 CYLINDER PIN FOUND CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1998042900170 19980429 00170 GL 1998 4 29 EY2R9601105 3 19961001 G 6110 A1896 PIN CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 795375 CYLINDER PIN FOUND CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1998042900171 19980429 00171 GL 1998 4 29 EY2R9601106 3 19961001 G 6110 A4191 DOWEL CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 795369 DOWEL CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1998042900172 19980429 00172 GL 1998 4 29 EY2R9601107 3 19961001 G 6110 A4191 DOWEL CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 795375 DOWEL CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1998042900173 19980429 00173 GL 1998 4 29 EY2R9601108 3 19961001 G 6110 B3490 PISTON ROD PIN CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 795369 PISTON ROD PIN FOUND CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1998042900174 19980429 00174 GL 1998 4 29 EY2R9601109 3 19961001 G 6110 C2987 BEARING CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 795369 RETAIN BEARING FOUND CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1998042900175 19980429 00175 GL 1998 4 29 EY2R9601110 3 19961001 G 6110 C2987 RETAIN BEARING CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 795375 RETAIN BEARING FOUND CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1998042900176 19980429 00176 GL 1998 4 29 EY2R9601111 3 19961001 G 6110 C4451 FERRULE CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 795369 FERRULE FOUND WITH CORROSION. 1 L 7 2 3O 3A25 5 C P22EA 1998042900177 19980429 00177 GL 1998 4 29 EY2R9601112 3 19961001 G 6110 C4451 FERRULE CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 795375 FERRULE FOUND WITH CORROSION. 1 L 7 2 3O 3A25 5 C P22EA 1998042900178 19980429 00178 GL 1998 4 29 EY2R9601113 3 19961001 G 6110 A1896 PIN CESSNA 421 421C 2076016 CE MCAULY 3FF32 3FF32C501 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 768385 CYLINDER PIN FOUND CORRODED. 1 L 7 2 3O A7CE 5 C P45GL 1998042900179 19980429 00179 GL 1998 4 29 EY2R9601114 3 19961001 G 6110 A4191 DOWEL CESSNA 421 421C 2076016 CE MCAULY 3FF32 3FF32C501 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 768385 DOWEL CORRODED. 1 L 7 2 3O A7CE 5 C P45GL 1998042900180 19980429 00180 GL 1998 4 29 EY2R9601115 3 19961001 G 6110 B4426 RETAIN RING CESSNA 421 421C 2076016 CE MCAULY 3FF32 3FF32C501 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 789223 RETAIN RING FOUND CORRODED. 1 L 7 2 3O A7CE 5 C P45GL 1998042900181 19980429 00181 GL 1998 4 29 EY2R9601116 3 19961001 G 6110 B48201 ACT PIN ASSY CESSNA 421 421C 2076016 CE MCAULY 3FF32 3FF32C501 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 789223 ACT PIN ASSY FOUND CORRODED. 1 L 7 2 3O A7CE 5 C P45GL 1998042900182 19980429 00182 GL 1998 4 29 EY2R9601117 3 19961001 G 6110 C5270 BEARING CESSNA 421 421C 2076016 CE MCAULY 3FF32 3FF32C501 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 789223 RETAIN BEARING CORRODED. 1 L 7 2 3O A7CE 5 C P45GL 1998042900183 19980429 00183 GL 1998 4 29 EY2R9601118 3 19961001 G 6110 D3474 ROD CESSNA 421 421C 2076016 CE MCAULY 3FF32 3FF32C501 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 767592 PISTON ROD ASSY FOUND WITH CORROSION. 1 L 7 2 3O A7CE 5 C P45GL 1998042900184 19980429 00184 GL 1998 4 29 EY2R9601119 3 19961001 G 6114 D5878C501 HUB CESSNA 421 421C 2076016 CE MCAULY 3FF32 3FF32C501 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 767592 HUB FOUND CORRODED. 1 L 7 2 3O A7CE 5 C P45GL 1998042900185 19980429 00185 GL 1998 4 29 EY2R9601120 3 19961001 G 6110 B5177 SCREW CESSNA 208 208 2073702 CE MCAULY 3AF34C 3GFR34C703 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2760 900938 SCREW CORRODED. 1 H 7 1 3T NT A37CE 5 C P60GL 1998042900186 19980429 00186 GL 1998 4 29 EY2R9601121 3 19961001 G 6110 B5177 SCREW CESSNA 208 208 2073702 CE MCAULY 3AF34C 3GFR34C703 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2688 910855 SCREW CORRODED. 1 H 7 1 3T NT A37CE 5 C P60GL 1998042900187 19980429 00187 GL 1998 4 29 EY2R9601122 3 19961001 G 6110 D5010 CYLINDER CESSNA 208 208 2073702 CE MCAULY 3AF34C 3GFR34C703 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2760 900938 CYLINDER FOUND CORRODED. 1 H 7 1 3T NT A37CE 5 C P60GL 1998042900188 19980429 00188 GL 1998 4 29 EY2R9601123 3 19961001 G 6114 C208 HUB CESSNA 177 177B 2073708 CE MCAULY 2D34C B2D34C208 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 778236 HUB FOUND CORRODED. 1 H 7 1 3O A13CE 5 C P7EA 1998042900189 19980429 00189 GL 1998 4 29 EY2R9601124 3 19961001 G 6110 B2345 PISTON TUBE CESSNA 182 182R 2072731 CE MCAULY 2D34C B2D34C219 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 7910786 PISTON TUBE FOUND CORRODED. 1 L 7 1 3O NT 3A13 5 C P7EA 1998042900190 19980429 00190 GL 1998 4 29 EY2R9601125 3 19961001 G 6110 C5046 PLATE CESSNA 182 182R 2072731 CE MCAULY 2D34C B2D34C219 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 7910786 PLATE CORRODED. 1 L 7 1 3O NT 3A13 5 C P7EA 1998042900191 19980429 00191 GL 1998 4 29 EY2R9601126 3 19961001 G 6114 C5078C220 HUB CESSNA 172 172RG 2072438 CE MCAULY 2D34C B2D34C220 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 803354 HUB FOUND CORRODED. 1 H 7 1 3O 3A17 5 C P7EA 1998042900192 19980429 00192 GL 1998 4 29 EY2R9601127 3 19961001 G 6110 5002X118 PIN PIPER PA28 PA28R201T 7102813 SO HARTZL HCC2Y BHCC2YF1 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 764 356 AM1751 PIN CORRODED. 1 L 7 1 3O 2A13 5 C P920 1998042900193 19980429 00193 GL 1998 4 29 EY2R9601128 3 19961001 G 6114 C4801C204 HUB CESSNA 182 182 2072702 CE MCAULY 2A34C C2A34C204 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 767053 CORROSION FOUND ON HUB. 1 H 7 1 3O NT 3A13 5 C P3EA 1998042900194 19980429 00194 GL 1998 4 29 EY2R9601129 3 19961001 G 6110 A4001 DOWEL CESSNA 182 182R 2072731 CE MCAULY 2A34C C2A34C204 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3080 1478 901245 DOWEL CORRODED. 1 L 7 1 3O NT 3A13 5 C P3EA 1998042900195 19980429 00195 GL 1998 4 29 EY2R9601130 3 19961001 G 6114 C4716C58 HUB CESSNA 206 206CESSNA 2073302 CE MCAULY 2A34C D2A34C58 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 755346 CORROSION FOUND ON HUB. 1 H 7 1 3O A4CE 5 C P3EA 1998042900196 19980429 00196 GL 1998 4 29 EY2R9601131 3 19961001 G 6110 C3054 FERRULE CESSNA 188 188CESSNA 2073002 CE MCAULY 2A34C D2A34C98 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 777021 FERRULE FOUND CORRODED. 1 L 7 1 3O A9CE 5 C P3EA 1998042900197 19980429 00197 GL 1998 4 29 EY2R9601132 3 19961001 G 6110 A1896 PIN CESSNA 337 337 2075702 CE MCAULY 2AF34C D2AF34C61 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 753558 CYLINDER PIN FOUND CORRODED. 1 H 7 2 3O A6CE 5 C P5EA 1998042900198 19980429 00198 GL 1998 4 29 EY2R9601133 3 19961001 G 6110 A4001 DOWEL CESSNA 337 337 2075702 CE MCAULY 2AF34C D2AF34C61 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 753558 DOWEL CORRODED. 1 H 7 2 3O A6CE 5 C P5EA 1998042900199 19980429 00199 GL 1998 4 29 EY2R9601134 3 19961001 G 6111 G80VA0 BLADE CESSNA 185 185E 2072816 CE MCAULY D3A34 D3A34C403 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 861348 BLADE, SN BK472, FOUND CORRODED. 1 H 7 1 3O 3A24 5 C P47GL 1998042900200 19980429 00200 GL 1998 4 29 EY2R9601135 3 19961001 G 6111 G80VA0 BLADE CESSNA 185 185E 2072816 CE MCAULY D3A34 D3A34C403 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 861348 BLADE, SN BK434, FOUND CORRODED. 1 H 7 1 3O 3A24 5 C P47GL 1998042900201 19980429 00201 GL 1998 4 29 EY2R9601136 3 19961001 G 6111 G80VA0 BLADE CESSNA 185 185E 2072816 CE MCAULY D3A34 D3A34C403 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 861348 BLADE, SN BG318, FOUND CORRODED. 1 H 7 1 3O 3A24 5 C P47GL 1998042900202 19980429 00202 GL 1998 4 29 EY2R9601137 3 19961001 G 6110 A1896 PIN BEECH 58 58 1152740 CE MCAULY 3AF32C D3AF32C35 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 768730 CYLINDER PIN FOUND WITH CORROSION. 1 L 7 2 3O 3A16 5 C P22EA 1998042900203 19980429 00203 GL 1998 4 29 EY2R9601138 3 19961001 G 6110 A4191 DOWEL BEECH 58 58 1152740 CE MCAULY 3AF32C D3AF32C35 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 768730 DOWEL CORRODED. 1 L 7 2 3O 3A16 5 C P22EA 1998042900204 19980429 00204 GL 1998 4 29 EY2R9601139 3 19961001 G 6111 S82NC2 BLADE CESSNA 310 310K 2074228 CE MCAULY 3AF32C D3AF32C80 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BLADE, SN F73319YS, FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1998042900205 19980429 00205 GL 1998 4 29 EY2R9601140 3 19961001 G 6111 S82NC2 BLADE CESSNA 310 310K 2074228 CE MCAULY 3AF32C D3AF32C80 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BLADE, SN F32952YS, FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1998042900206 19980429 00206 GL 1998 4 29 EY2R9601141 3 19961001 G 6111 S82NC2 BLADE CESSNA 310 310K 2074228 CE MCAULY 3AF32C D3AF32C80 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BLADE, SN F32834YS, FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1998042900207 19980429 00207 GL 1998 4 29 EY2R9601142 3 19961001 G 6110 14B BEARING PIPER PA24 PA24250 7102404 SO HARTZL HC82V HC82V* GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 4516 143G BEARING CORRODED. 1 L 7 1 3O 1A15 5 C P23EA 1998042900208 19980429 00208 GL 1998 4 29 EY2R9601143 3 19961001 G 6110 806 CYLINDER PIPER PA24 PA24250 7102404 SO HARTZL HC82V HC82V* GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 4516 143G CYLINDER CORRODED. 1 L 7 1 3O 1A15 5 C P23EA 1998042900209 19980429 00209 GL 1998 4 29 EY2R9601144 3 19961001 G 6110 8382 CLAMP PIPER PA24 PA24250 7102404 SO HARTZL HC82V HC82V* GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 4516 143G CLAMP CORRODED. 1 L 7 1 3O 1A15 5 C P23EA 1998042900210 19980429 00210 GL 1998 4 29 EY2R9601145 3 19961001 G 6110 14962 PILOT TUBE PIPER PA23 PA23 7102302 SO HARTZL HCA2V HCA2VK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1531 H1786 CORROSION FOUND ON PILOT TUBES. REMOVED AND REPLACED PILOT TUBES. 1 L 7 2 3O 1A10 5 C P24EA 1998042900211 19980429 00211 GL 1998 4 29 EY2R9601146 3 19961001 G 6110 14962 PILOT TUBE PIPER PA23 PA23 7102302 SO HARTZL HCA2V HCA2VK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 9880 789 H610 CORROSION FOUND ON PILOT TUBES. REMOVED AND REPLACED PILOT TUBES. 1 L 7 2 3O 1A10 5 C P24EA 1998042900212 19980429 00212 GL 1998 4 29 EY2R9601147 3 19961001 G 6110 83812 CLAMP PIPER PA23 PA23 7102302 SO HARTZL HCA2V HCA2VK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1531 H1786 CLAMP CORRODED. 1 L 7 2 3O 1A10 5 C P24EA 1998042900213 19980429 00213 GL 1998 4 29 EY2R9601148 3 19961001 G 6110 971 BEARING PIPER PA23 PA23 7102302 SO HARTZL HCA2V HCA2VK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1531 H1786 CORROSION FOUND ON SPLIT BEARING. 1 L 7 2 3O 1A10 5 C P24EA 1998042900214 19980429 00214 GL 1998 4 29 EY2R9601149 3 19961001 G 6110 971 BEARING PIPER PA23 PA23 7102302 SO HARTZL HCA2V HCA2VK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 9880 789 H610 CORROSION FOUND ON SPLIT BEARING. 1 L 7 2 3O 1A10 5 C P24EA 1998042900215 19980429 00215 GL 1998 4 29 EY2R9601150 3 19961001 G 6110 13333 BOLT PIPER PA24 PA24250 7102404 SO HARTZL HCA2X HCA2XK1 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 J477 BOLT FOUND CORRODED. 1 L 7 1 3O 1A15 5 C P908 1998042900216 19980429 00216 GL 1998 4 29 EY2R9601151 3 19961001 G 6110 13336 BOLT PIPER PA24 PA24250 7102404 SO HARTZL HCA2X HCA2XK1 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 J477 BOLT FOUND CORRODED. 1 L 7 1 3O 1A15 5 C P908 1998042900217 19980429 00217 GL 1998 4 29 EY2R9601152 3 19961001 G 6110 8382 CLAMP PIPER PA24 PA24250 7102404 SO HARTZL HCA2X HCA2XK1 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 J477 CLAMP FOUND CORRODED. 1 L 7 1 3O 1A15 5 C P908 1998042900218 19980429 00218 GL 1998 4 29 EY2R9601153 3 19961001 G 6110 971 BEARING PIPER PA24 PA24250 7102404 SO HARTZL HCA2X HCA2XK1 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 J477 SPLIT BEARING FOUND CORRODED. 1 L 7 1 3O 1A15 5 C P908 1998042900219 19980429 00219 GL 1998 4 29 EY2R9601154 3 19961001 G 6110 J2016 BEARING PIPER PA24 PA24250 7102404 SO HARTZL HCA2X HCA2XK1 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 J477 BEARING FOUND CORRODED. 1 L 7 1 3O 1A15 5 C P908 1998042900220 19980429 00220 GL 1998 4 29 EY2R9601155 3 19961001 G 6110 971 BEARING BEECH 80 65A80 1152808 CE HARTZL HCA3V HCA3VK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1472 944 BJ468 SPLIT BEARING FOUND CORRODED. 1 L 7 2 3O 3A20 5 C P6EA 1998042900221 19980429 00221 GL 1998 4 29 EY2R9601156 3 19961001 G 6111 T10173B8 BLADE BEECH 200 200BEECH 1152920 CE HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BU16490 BLADE, SN B21030, FOUND CORRODED. 1 L 7 2 4T A24CE 6 C P15EA 1998042900222 19980429 00222 GL 1998 4 29 EY2R9601157 3 19961001 G 6110 3475A2 STOP COLLAR BEECH 100 100BEECH 1152916 CE HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 9815 1746 BU5621 LOW STOP COLLAR FOUND WITH CORROSION. 1 L 7 2 3T A14CE 6 C P15EA 1998042900223 19980429 00223 GL 1998 4 29 EY2R9601158 3 19961001 G 6110 1851T BEARING BEECH 1900 1900C 1154161 CE HARTZL HCB4M HCB4MP3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 10073 2099 FW559 BEARING FOUND CORRODED. 2 L 7 2 4T RT A24CE 6 C P56GL 1998042900224 19980429 00224 GL 1998 4 29 EY2R9601159 3 19961001 G 6111 LT10574FS BLADE DORNER DO228 DO228* EU HARTZL HCB4T HCB4TN5 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 CD1876 BLADE, SN H05668, FOUND CORRODED. 1 H 7 2 4T RT A16EU 6 C P40EA 1998042900225 19980429 00225 GL 1998 4 29 EY2R9601160 3 19961001 G 6111 LT10574FS BLADE DORNER DO228 DO228* EU HARTZL HCB4T HCB4TN5 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 CD1876 BLADE, SN H05667, FOUND CORRODED. 1 H 7 2 4T RT A16EU 6 C P40EA 1998042900226 19980429 00226 GL 1998 4 29 EY2R9601161 3 19961001 G 6111 LT10574FS BLADE DORNER DO228 DO228* EU HARTZL HCB4T HCB4TN5 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 CD1876 BLADE, SN F58721, FOUND CORRODED. 1 H 7 2 4T RT A16EU 6 C P40EA 1998042900227 19980429 00227 GL 1998 4 29 EY2R9601162 3 19961001 G 6110 2421 SOCKET SET SCREW MOONEY M20 M20E 5870212 SW HARTZL HCC2Y HCC2YK1 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 CA132 PROP ASSY SOCKET SCREW CORRODED 1 L 7 1 3O 2A3 5 C P920 1998042900228 19980429 00228 GL 1998 4 29 EY2R9601163 3 19961001 G 6114 220116 HUB BNORM BN2 BN2B20 1520302 EU HARTZL HCC2Y HCC2YK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1999 AU4803 CORROSION FOUND ON HUB. 1 H 7 2 3O A17EU 5 C P920 1998042900229 19980429 00229 GL 1998 4 29 EY2R9601164 3 19961001 G 6110 2202 BEARING BNORM BN2 BN2B20 1520302 EU HARTZL HCC2Y HCC2YK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1999 AU4803 CORROSION FOUND ON SPLIT BEARING. 1 H 7 2 3O A17EU 5 C P920 1998042900230 19980429 00230 GL 1998 4 29 EY2R9601165 3 19961001 G 6111 F7666A BLADE PIPER PA28 PA28R180 7102809 SO HARTZL HCC2Y HCC2YR1 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BLADE, SN H57236, FOUND CORRODED. 1 L 7 1 3O 2A13 5 C P920 1998042900231 19980429 00231 GL 1998 4 29 EY2R9601166 3 19961001 G 6110 3807 BOLT HARTZL HCC2Y HCC2YR4 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 635 AU7576 BOLT FOUND CORRODED. 5 C P920 1998042900232 19980429 00232 GL 1998 4 29 EY2R9601167 3 19961001 G 6110 3807 BOLT HARTZL HCC2Y HCC2YR4 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 616 DN1712 BOLT FOUND CORRODED. 5 C P920 1998042900233 19980429 00233 GL 1998 4 29 EY2R9601168 3 19961001 G 6110 3807 BOLT HARTZL HCC2Y HCC2YR4 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 843 DN1961 BOLT FOUND CORRODED. 5 C P920 1998042900234 19980429 00234 GL 1998 4 29 EY2R9601169 3 19961001 G 6110 3807 BOLT HARTZL HCC2Y HCC2YR4 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 903 DN374 BOLT FOUND CORRODED. 5 C P920 1998042900235 19980429 00235 GL 1998 4 29 EY2R9601170 3 19961001 G 6110 3807 BOLT HARTZL HCC2Y HCC2YR4 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1048 357 DN921 BOLT FOUND CORRODED. 5 C P920 1998042900236 19980429 00236 GL 1998 4 29 EY2R9601171 3 19961001 G 6110 3807 BOLT HARTZL HCC2Y HCC2YR4 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 804 DN942 BOLT FOUND CORRODED. 5 C P920 1998042900237 19980429 00237 NE 1998 4 29 EY2R9601172 3 19961001 G 6110 51171 CLAMP BEECH 1900 1900D 1154162 CE HARTZL HCE4A HCE4A3A NE PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 5420 HJ297 PROP ASSY COUNTERWEIGHT CLAMP FOUND CORRODED. 2 L 7 2 4T RT A24CE 5 C P10NE 1998042900238 19980429 00238 GL 1998 4 29 EY2R9601173 3 19961001 G 6110 15941 SPRING PIPER PA31 PA31P350 7103111 SO HARTZL HCI3Y HCI3YR2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 F5177A CORROSION FOUND ON FEATHERING SPRING. 1 L 7 2 3O RT A8EA 5 C P33EA 1998042900239 19980429 00239 GL 1998 4 29 EY2R9601174 3 19961001 G 6110 971 SPLIT BEARING BEECH 55 95A55 1152704 CE HARTZL HCA3V PHCA3VF2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 307 BR701 CORROSION FOUND ON SPLIT BEARING. 1 L 7 2 3O 3A16 5 C P6EA 1998042900240 19980429 00240 GL 1998 4 29 EY2R9601175 3 19961101 G 6110 130035908 CAP SCREW BAG JETSTM JETSTM3101 1500215 EU ROTOL R333 R333482F12 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 21844 5889 DRG418385 CAP SCREW FOUND CORRODED. 2 L 7 2 4T RT A21EU 6 C P61GL 1998042900241 19980429 00241 GL 1998 4 29 EY2R9601176 3 19961101 G 6110 660706613 SLEEVE BAG JETSTM JETSTM3101 1500215 EU ROTOL R333 R333482F12 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 10721 5750 DRG725489 CORROSION FOUND ON SLEEVE. 2 L 7 2 4T RT A21EU 6 C P61GL 1998042900242 19980429 00242 GL 1998 4 29 EY2R9601177 3 19961101 G 6110 850000058 BALL SET BAG JETSTM JETSTM3101 1500215 EU ROTOL R333 R333482F12 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 10721 5750 DRG725489 CORROSION FOUND ON BALL SET. 2 L 7 2 4T RT A21EU 6 C P61GL 1998042900243 19980429 00243 GL 1998 4 29 EY2R9601178 3 19961101 G 6110 PROPELLER CESSNA 150 150 2071802 CE MCAULY 1A101 1A101HCM GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 G10243 CORROSION FOUND ON FIXED-PITCH PROPELLER. 1 H 7 1 3O NT 3A19 5 N P918 1998042900244 19980429 00244 GL 1998 4 29 EY2R9601179 3 19961101 G 6110 PROPELLER CESSNA 140 140 2071602 CE MCAULY 1B90 1B90CM GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 49746 CORROSION FOUND ON FIXED-PITCH PROPELLER. 1 H 7 1 3O NC A768 5 N P842 1998042900245 19980429 00245 GL 1998 4 29 EY2R9601180 3 19961101 G 6110 PROPELLER CESSNA 140 140 2071602 CE MCAULY 1B90 1B90CM GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 24403 CORROSION FOUND ON FIXED-PITCH PROPELLER. 1 H 7 1 3O NC A768 5 N P842 1998042900246 19980429 00246 GL 1998 4 29 EY2R9601181 3 19961101 G 6110 PROPELLER BBAVIA 7 7AC 2110102 SW MCAULY 1B90 1B90CM GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 33791 CORROSION FOUND ON FIXED-PITCH PROPELLER. 1 H 7 1 3O A759 5 N P842 1998042900247 19980429 00247 GL 1998 4 29 EY2R9601182 3 19961101 G 6110 PROPELLER PIPER J3 PA11 7101102 SO MCAULY 1B90 1B90CM GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 28425 CORROSION FOUND ON FIXED-PITCH PROPELLER. 1 H 7 1 3O A691 5 N P842 1998042900248 19980429 00248 GL 1998 4 29 EY2R9601183 3 19961101 G 6110 PROPELLER GULSTM AA5 AA5 0631410 SO MCAULY 1C172 1C172* GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 P71063 CORROSION FOUND ON FIXED-PITCH PROPELLER. 1 L 7 1 3O A16EA 5 N P910 1998042900249 19980429 00249 CE 1998 4 29 EY2R9601184 3 19961101 G 6114 279100 HUB BEECH 50 50 1152502 CE BEECH 279 279100 CE PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1485 HUB, SN 78, FOUND CORRODED. 1 L 7 2 3O 5A4 5 C P885 1998042900250 19980429 00250 CE 1998 4 29 EY2R9601185 3 19961101 G 6111 27920798 BLADE BEECH 50 50 1152502 CE BEECH 279 279100 CE PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1485 BLADE, SN 81160, FOUND CORRODED. 1 L 7 2 3O 5A4 5 C P885 1998042900251 19980429 00251 CE 1998 4 29 EY2R9601186 3 19961101 G 6111 27920798 BLADE BEECH 50 50 1152502 CE BEECH 279 279100 CE PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1485 BLADE, SN 81164, FOUND CORRODED. 1 L 7 2 3O 5A4 5 C P885 1998042900252 19980429 00252 GL 1998 4 29 EY2R9601187 3 19961101 G 6110 B2417 COVER PLATE BEECH 35 B35 1151506 CE MCAULY 2A36C 2A36C23 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 696231 CORROSION FOUND ON SPLIT COVER PLATE. 1 L 7 1 3O A777 5 C P880 1998042900253 19980429 00253 GL 1998 4 29 EY2R9601188 3 19961101 G 6114 C2835C23 HUB BEECH 35 V35B 1151548 CE MCAULY 2A36C 2A36C23 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 66981 HUB FOUND CORRODED. 1 L 7 1 3O 3A15 5 C P880 1998042900254 19980429 00254 GL 1998 4 29 EY2R9601189 3 19961101 G 6110 C4904 NUT BEECH 35 V35B 1151548 CE MCAULY 3A32C 3A32C76 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 674507 CORROSION FOUND ON NUT. 1 L 7 1 3O 3A15 5 C P21EA 1998042900255 19980429 00255 GL 1998 4 29 EY2R9601190 3 19961101 G 6114 D6602C76 HUB BEECH 35 V35B 1151548 CE MCAULY 3A32C 3A32C76 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 674507 CORROSION FOUND ON HUB. 1 L 7 1 3O 3A15 5 C P21EA 1998042900256 19980429 00256 GL 1998 4 29 EY2R9601191 3 19961101 G 6110 C3411 BEARING CESSNA 303 T303 2073820 CE MCAULY 3AF32C 3AF32C506 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2993 1650 814245 BEARING RACE CORRODED. 1 L 7 2 3O A34CE 5 C P57GL 1998042900257 19980429 00257 GL 1998 4 29 EY2R9601192 3 19961101 G 6110 C3903 RETAINER CESSNA 303 T303 2073820 CE MCAULY 3AF32C 3AF32C506 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2993 1650 814245 SPLIT RETAINER FOUND CORRODED. 1 L 7 2 3O A34CE 5 C P57GL 1998042900258 19980429 00258 GL 1998 4 29 EY2R9601193 3 19961101 G 6110 C2987 BEARING CESSNA 402 402B 207590P CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 702046 RETAIN BEARING FOUND CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1998042900259 19980429 00259 GL 1998 4 29 EY2R9601194 3 19961101 G 6110 C2987 BEARING CESSNA 402 402C 207590R CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 4020 1379 796457 RETAIN BEARING FOUND CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1998042900260 19980429 00260 GL 1998 4 29 EY2R9601195 3 19961101 G 6110 C2987 BEARING CESSNA 402 402C 207590R CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 4020 1379 799790 RETAIN BEARING FOUND CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1998042900261 19980429 00261 GL 1998 4 29 EY2R9601196 3 19961101 G 6114 D5892C93 HUB CESSNA 402 402C 207590R CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 4020 1379 799790 CORROSION FOUND ON HUB. 1 L 7 2 3O A7CE 5 C P22EA 1998042900262 19980429 00262 GL 1998 4 29 EY2R9601197 3 19961101 G 6110 B5177 SCREW CESSNA 208 208 2073702 CE MCAULY 3AF34C 3GFR34C703 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 911090 SCREW CORRODED. 1 H 7 1 3T NT A37CE 5 C P60GL 1998042900263 19980429 00263 GL 1998 4 29 EY2R9601198 3 19961101 G 6110 B5177 SCREW CESSNA 208 208 2073702 CE MCAULY 3AF34C 3GFR34C703 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2490 911608 SCREW CORRODED. 1 H 7 1 3T NT A37CE 5 C P60GL 1998042900264 19980429 00264 GL 1998 4 29 EY2R9601199 3 19961101 G 6110 B5177 SCREW CESSNA 208 208 2073702 CE MCAULY 3AF34C 3GFR34C703 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2791 910787 SCREW CORRODED. 1 H 7 1 3T NT A37CE 5 C P60GL 1998042900265 19980429 00265 GL 1998 4 29 EY2R9601200 3 19961101 G 6110 B5177 SCREW CESSNA 208 208 2073702 CE MCAULY 3AF34C 3GFR34C703 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2995 911606 SCREW CORRODED. 1 H 7 1 3T NT A37CE 5 C P60GL 1998042900266 19980429 00266 NE 1998 4 29 EY2R9601201 3 19961101 G 6110 C5328 FEATHER SPRING SWRNGN SA227 SA227AC 8780603 SW MCAULY 4HFR34 4HFR34C652 NE PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 10750 828 881053 CORROSION FOUND ON FEATHER SPRING. 2 L 7 2 4T RT A8SW 6 C 3PNE 1998042900267 19980429 00267 NE 1998 4 29 EY2R9601202 3 19961101 G 6110 A163563 SCREW SWRNGN SA227 SA227AC 8780603 SW MCAULY 4HFR34 4HFR34C652 NE PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2584 911019 SCREW CORRODED. 2 L 7 2 4T RT A8SW 6 C 3PNE 1998042900268 19980429 00268 NE 1998 4 29 EY2R9601203 3 19961101 G 6110 B5162 REVRS STOP SCREW SWRNGN SA227 SA227AC 8780603 SW MCAULY 4HFR34 4HFR34C652 NE PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2584 911016 CORROSION FOUND ON REVERSE STOP SCREW. 2 L 7 2 4T RT A8SW 6 C 3PNE 1998042900269 19980429 00269 NE 1998 4 29 EY2R9601204 3 19961101 G 6110 D6174 CYLINDER SWRNGN SA227 SA227AC 8780603 SW MCAULY 4HFR34 4HFR34C652 NE PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2584 911016 CYLINDER CORRODED. 2 L 7 2 4T RT A8SW 6 C 3PNE 1998042900270 19980429 00270 NE 1998 4 29 EY2R9601205 3 19961101 G 6110 D6174 CYLINDER SWRNGN SA227 SA227AC 8780603 SW MCAULY 4HFR34 4HFR34C652 NE PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2584 911019 CYLINDER CORRODED. 2 L 7 2 4T RT A8SW 6 C 3PNE 1998042900271 19980429 00271 GL 1998 4 29 EY2R9601206 3 19961101 G 6110 C6263 CYLINDER CESSNA 182 182 2072702 CE MCAULY 2A34C C2A34C204 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1771 767948 CYLINDER CORRODED. 1 H 7 1 3O NT 3A13 5 C P3EA 1998042900272 19980429 00272 GL 1998 4 29 EY2R9601207 3 19961101 G 6110 C3411 BEARING CESSNA 180 180K 2072624 CE MCAULY 2A34C C2A34C204 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 765710 CORROSION FOUND ON BEARING RACE. 1 H 7 1 3O 5A6 5 C P3EA 1998042900273 19980429 00273 GL 1998 4 29 EY2R9601208 3 19961101 G 6110 A16349 BEARING CESSNA 182 182F 2072714 CE MCAULY 3A32C D3A32C* GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 676 910981 BALL BEARING CORRODED. 1 H 7 1 3O NT 3A13 5 C P21EA 1998042900274 19980429 00274 GL 1998 4 29 EY2R9601209 3 19961101 G 6111 90DFA10 BLADE CESSNA 210 T210M 2073451 CE MCAULY D3A34 D3A34C402 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 7911143 BLADE, SN 124558, FOUND CORRODED. 1 H 7 1 3O 3A21 5 C P47GL 1998042900275 19980429 00275 GL 1998 4 29 EY2R9601210 3 19961101 G 6111 90DFA10 BLADE CESSNA 210 T210M 2073451 CE MCAULY D3A34 D3A34C402 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 7911143 BLADE, SN 125221, FOUND CORRODED. 1 H 7 1 3O 3A21 5 C P47GL 1998042900276 19980429 00276 GL 1998 4 29 EY2R9601211 3 19961101 G 6111 90DFA10 BLADE CESSNA 210 T210M 2073451 CE MCAULY D3A34 D3A34C402 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 7911143 BLADE, SN 125242, FOUND CORRODED. 1 H 7 1 3O 3A21 5 C P47GL 1998042900277 19980429 00277 GL 1998 4 29 EY2R9601212 3 19961101 G 6110 A3125 SPRING CESSNA 210 T210M 2073451 CE MCAULY D3A34 D3A34C402 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 7911143 CORROSION FOUND ON PITCH RETURN SPRING 1 H 7 1 3O 3A21 5 C P47GL 1998011500001 19980115 00001 GL 1998 1 15 EY2R9601213 3 19961101 G 6110 A4002 PROPELLER CESSNA 210 T210M 2073451 CE MCAULY D3A34 D3A34C402 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 7911143 PROPELLER ASSY IS CORRODED 1 H 7 1 3O 3A21 5 C P47GL 1998042900278 19980429 00278 GL 1998 4 29 EY2R9601214 3 19961101 G 6110 A4738 PISTON LINK PIN CESSNA 210 T210M 2073451 CE MCAULY D3A34 D3A34C402 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 7911143 CORROSION FOUND ON PISTON LINK PIN. 1 H 7 1 3O 3A21 5 C P47GL 1998042900279 19980429 00279 GL 1998 4 29 EY2R9601215 3 19961101 G 6110 B48202 ACTUATOR PIN CESSNA 210 T210M 2073451 CE MCAULY D3A34 D3A34C402 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 7911143 ACT PIN ASSEMBLY FOUND CORRODED. 1 H 7 1 3O 3A21 5 C P47GL 1998042900280 19980429 00280 GL 1998 4 29 EY2R9601216 3 19961101 G 6110 C3903 RETAINER CESSNA 210 T210M 2073451 CE MCAULY D3A34 D3A34C402 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 7911143 CORROSION FOUND ON SPLIT RETAINER. 1 H 7 1 3O 3A21 5 C P47GL 1998042900281 19980429 00281 GL 1998 4 29 EY2R9601217 3 19961101 G 6110 C4784 PISTON CESSNA 210 T210M 2073451 CE MCAULY D3A34 D3A34C402 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 7911143 PISTON CORRODED. 1 H 7 1 3O 3A21 5 C P47GL 1998042900282 19980429 00282 GL 1998 4 29 EY2R9601218 3 19961101 G 6110 C5264 CYLINDER CESSNA 210 T210M 2073451 CE MCAULY D3A34 D3A34C402 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 7911143 CYLINDER CORRODED. 1 H 7 1 3O 3A21 5 C P47GL 1998042900283 19980429 00283 GL 1998 4 29 EY2R9601219 3 19961101 G 6110 C5270 BEARING CESSNA 210 T210M 2073451 CE MCAULY D3A34 D3A34C402 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 7911143 RETAIN BEARING CORRODED. 1 H 7 1 3O 3A21 5 C P47GL 1998042900284 19980429 00284 GL 1998 4 29 EY2R9601220 3 19961101 G 6110 1303A BEARING BEECH 95 B95 1153404 CE HARTZL HC92W HC92WK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 8435 1391 1680F BEARING CORRODED. 1 L 7 2 3O 3A16 5 C P16EA 1998042900285 19980429 00285 GL 1998 4 29 EY2R9601221 3 19961101 G 6110 1303A BEARING BEECH 95 B95 1153404 CE HARTZL HC92W HC92WK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 8435 1391 1681F BEARING CORRODED. 1 L 7 2 3O 3A16 5 C P16EA 1998042900286 19980429 00286 GL 1998 4 29 EY2R9601222 3 19961101 G 6110 853 SPRING BEECH 95 B95 1153404 CE HARTZL HC92W HC92WK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 8435 1391 1680F CORROSION FOUND ON FEATHERING SPRING. 1 L 7 2 3O 3A16 5 C P16EA 1998042900287 19980429 00287 GL 1998 4 29 EY2R9601223 3 19961101 G 6110 853 SPRING BEECH 95 B95 1153404 CE HARTZL HC92W HC92WK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 8435 1391 1681F CORROSION FOUND ON FEATHERING SPRING. 1 L 7 2 3O 3A16 5 C P16EA 1998042900288 19980429 00288 GL 1998 4 29 EY2R9601224 3 19961101 G 6110 971 BEARING PIPER PA24 PA24250 7102404 SO HARTZL HCA2V HCA2V* GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 430 J1625 CORROSION FOUND ON SPLIT BEARING. 1 L 7 1 3O 1A15 5 C P24EA 1998042900289 19980429 00289 GL 1998 4 29 EY2R9601225 3 19961101 G 6110 971 SPLIT BEARING PIPER PA24 PA24250 7102404 SO HARTZL HCA2V HCA2V* GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 J263 CORROSION FOUND ON SPLIT BEARING. 1 L 7 1 3O 1A15 5 C P24EA 1998042900290 19980429 00290 GL 1998 4 29 EY2R9601226 3 19961101 G 6110 83888 CLAMP BEECH 90 B90 1152912 CE HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 CLAMPS, SN'S EK395, EK359, FOUND CORRODED. 1 L 7 2 3T 3A20 6 C P15EA 1998042900291 19980429 00291 GL 1998 4 29 EY2R9601227 3 19961101 G 6111 T10282N4 BLADE AIRTRC AT400 AT400 0390202 SW HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BLADE, SN H44122, FOUND CORRODED. 1 L 7 1 3T A9SW 6 C P15EA 1998042900292 19980429 00292 GL 1998 4 29 EY2R9601228 3 19961101 G 6110 1851T BEARING DHAV DHC6 DHC6300 EA HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 14123 3404 BU14783 BEARING CORRODED. 1 H 7 2 3T A9EA 6 C P15EA 1998042900293 19980429 00293 GL 1998 4 29 EY2R9601229 3 19961101 G 6110 1851T BEARING DHAV DHC6 DHC6300 EA HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 24237 2961 BU7083 BEARING CORRODED. 1 H 7 2 3T A9EA 6 C P15EA 1998042900294 19980429 00294 GL 1998 4 29 EY2R9601230 3 19961101 G 6110 1851T BEARING ISRAEL 101 ARAVA101 EU HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BU7523 BEARING CORRODED. 1 H 7 2 3T A32EU 6 C P15EA 1998042900295 19980429 00295 GL 1998 4 29 EY2R9601231 3 19961101 G 6110 83867 CLAMP DHAV DHC6 DHC6300 EA HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 24237 2961 BU7083 CLAMPS, SN'S EF2929, EF8442, AND EF9704, FOUND CORRODED. 1 H 7 2 3T A9EA 6 C P15EA 1998042900296 19980429 00296 GL 1998 4 29 EY2R9601232 3 19961101 G 6110 338614H BOLT BEECH 300 300BEECH 1152930 CE HARTZL HCB4M HCB4MP3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3613 815 FW842 BOLT CORRODED. 2 L 7 2 4T A24CE 6 C P56GL 1998042900297 19980429 00297 GL 1998 4 29 EY2R9601233 3 19961101 G 6114 220117 HUB CESSNA 172 172 2072402 CE HARTZL HCC2Y HCC2YK1 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 CH27570 HUB CORRODED. 1 H 7 1 3O NT 3A12 5 C P920 1998042900298 19980429 00298 GL 1998 4 29 EY2R9601234 3 19961101 G 6114 22013 HUB PIPER PA28 PA28* SO HARTZL HCC2Y HCC2YK1 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 CH5946 HUB CORRODED. 1 L 7 1 3O 2A13 5 C P920 1998042900299 19980429 00299 GL 1998 4 29 EY2R9601235 3 19961101 G 6111 F7666A BLADE CESSNA 172 172 2072402 CE HARTZL HCC2Y HCC2YK1 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 CH27570 BLADE, SN F52834, FOUND CORRODED. 1 H 7 1 3O NT 3A12 5 C P920 1998042900300 19980429 00300 GL 1998 4 29 EY2R9601236 3 19961101 G 6111 F7666A BLADE CESSNA 172 172 2072402 CE HARTZL HCC2Y HCC2YK1 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 CH27570 BLADE, SN F52931, FOUND CORRODED. 1 H 7 1 3O NT 3A12 5 C P920 1998042900301 19980429 00301 GL 1998 4 29 EY2R9601237 3 19961101 G 6114 220117 HUB PIPER PA32 PA32301 7103207 SO HARTZL HCC2Y HCC2YK1 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 CH7157 HUB FOUND CORRODED. 1 L 7 1 3O A3SO 5 C P920 1998042900302 19980429 00302 GL 1998 4 29 EY2R9601238 3 19961101 G 6110 2202 BEARING PIPER PA32 PA32301 7103207 SO HARTZL HCC2Y HCC2YK1 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 CH7157 CORROSION FOUND ON SPLIT BEARING. 1 L 7 1 3O A3SO 5 C P920 1998042900303 19980429 00303 GL 1998 4 29 EY2R9601239 3 19961101 G 6110 2202 BEARING BNORM BN2 BN2 1520202 EU HARTZL HCC2Y HCC2YK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 AU5625 CORROSION FOUND ON SPLIT BEARING. 1 H 7 2 3O A17EU 5 C P920 1998042900304 19980429 00304 GL 1998 4 29 EY2R9601240 3 19961101 G 6110 2202 BEARING BNORM BN2 BN2 1520202 EU HARTZL HCC2Y HCC2YK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 AU5967 CORROSION FOUND ON SPLIT BEARING. 1 H 7 2 3O A17EU 5 C P920 1998042900305 19980429 00305 GL 1998 4 29 EY2R9601241 3 19961101 G 6110 2202 BEARING PIPER PA23 PA23250 7102308 SO HARTZL HCE2Y HCE2YK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BP6431 CORROSION FOUND ON SPLIT BEARING. 1 L 7 2 3O 1A10 5 C P9EA 1998042900306 19980429 00306 GL 1998 4 29 EY2R9601242 3 19961201 G 6114 D7015C87 HUB CESSNA 335 335 2075601 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1507 7910597 HUB FOUND CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1998042900307 19980429 00307 GL 1998 4 29 EY2R9601243 3 19961201 G 6110 C7036 LOCKNUT CESSNA 335 335 2075601 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1507 7910597 CORROSION FOUND ON LOCKNUT. 1 L 7 2 3O 3A25 5 C P22EA 1998042900308 19980429 00308 GL 1998 4 29 EY2R9601244 3 19961201 G 6110 B4459 ACT PIN CESSNA 335 335 2075601 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1507 7910597 ACT. PIN RUSTED. 1 L 7 2 3O 3A25 5 C P22EA 1998042900309 19980429 00309 GL 1998 4 29 EY2R9601245 3 19961201 G 6111 S82NC2 BLADE CESSNA 402 402CESSNA 207590K CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 694041 BLADE, SN K56449YS, FOUND CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1998042900310 19980429 00310 GL 1998 4 29 EY2R9601246 3 19961201 G 6111 S82NC2 BLADE CESSNA 402 402CESSNA 207590K CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 694041 BLADE, SN K56826YS, FOUND CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1998042900311 19980429 00311 GL 1998 4 29 EY2R9601247 3 19961201 G 6111 S82NC4 BLADE CESSNA 402 402CESSNA 207590K CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 737982 BLADE, SN F40087YS, FOUND CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1998042900312 19980429 00312 GL 1998 4 29 EY2R9601248 3 19961201 G 6114 D7015C87 HUB CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1223 741352 NR 1 SOCKET FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1998042900313 19980429 00313 GL 1998 4 29 EY2R9601249 3 19961201 G 6110 C2987 RACE CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1223 741352 CORROSION FOUND ON RACE. 1 L 7 2 3O 3A10 5 C P22EA 1998042900314 19980429 00314 GL 1998 4 29 EY2R9601250 3 19961201 G 6110 C40603 PISTON CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 755780 PISTON CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1998042900315 19980429 00315 GL 1998 4 29 EY2R9601251 3 19961201 G 6111 C2987 BEARING CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 746944 BLADE BEARING FOUND CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1998042900316 19980429 00316 GL 1998 4 29 EY2R9601252 3 19961201 G 6110 C4451 FERRULE CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 746944 FERRULE CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1998042900317 19980429 00317 GL 1998 4 29 EY2R9601253 3 19961201 G 6110 C4451 FERRULE CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 746944 FERRULE CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1998042900318 19980429 00318 GL 1998 4 29 EY2R9601254 3 19961201 G 6110 C3475 RETAIN NUT CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 746944 RETAIN NUT FOUND CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1998042900319 19980429 00319 GL 1998 4 29 EY2R9601255 3 19961201 G 6110 C40603 PISTON CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 746953 PISTON CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1998042900320 19980429 00320 GL 1998 4 29 EY2R9601256 3 19961201 G 6110 C3475 RETAIN NUT CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 746953 RETAIN NUT CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1998042900321 19980429 00321 GL 1998 4 29 EY2R9601257 3 19961201 G 6110 C3475 RETAIN NUT CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 746953 RETAIN NUT CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1998042900322 19980429 00322 GL 1998 4 29 EY2R9601258 3 19961201 G 6110 C3475 RETAIN NUT CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 746953 RETAIN NUT CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1998042900323 19980429 00323 GL 1998 4 29 EY2R9601259 3 19961201 G 6111 C2987 BEARING CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 746953 BLADE BEARING FOUND CORRODED. 1 L 7 2 3O 3A25 5 C P22EA 1998042900324 19980429 00324 GL 1998 4 29 EY2R9601260 3 19961201 G 6111 PROPELLER RETAINERS CESSNA 402 402C 207590R CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 785572 BLADES, SN'S F44301YS, F44956YS, AND F44460YS, FOUND CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1998042900325 19980429 00325 GL 1998 4 29 EY2R9601261 3 19961201 G 6111 S90LF0 BLADE CESSNA 421 421 2076010 CE MCAULY 3AF34C 3AF34C92 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 860386 BLADE, SN C31669YS, FOUND CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1998042900326 19980429 00326 GL 1998 4 29 EY2R9601262 3 19961201 G 6110 C4458 ACT PIN CESSNA 337 337A 2075704 CE MCAULY 2AF34C D2AF34C59 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2250 693055 ACT. PIN FOUND RUSTED. 1 H 7 2 3O A6CE 5 C P5EA 1998042900327 19980429 00327 GL 1998 4 29 EY2R9601263 3 19961201 G 6114 D4885 HUB CESSNA 337 337A 2075704 CE MCAULY 2AF34C D2AF34C61 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2250 653785 HUB FOUND CORRODED. 1 H 7 2 3O A6CE 5 C P5EA 1998042900328 19980429 00328 GL 1998 4 29 EY2R9601264 3 19961201 G 6111 L76C0 BLADE CESSNA 337 337A 2075704 CE MCAULY 2AF34C D2AF34C61 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2250 653785 BLADE, SN D2514YS, FOUND CORRODED. 1 H 7 2 3O A6CE 5 C P5EA 1998042900329 19980429 00329 GL 1998 4 29 EY2R9601265 3 19961201 G 6110 C4905 LOCKNUT CESSNA 337 337A 2075704 CE MCAULY 2AF34C D2AF34C61 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2250 653785 LOCKNUT CORRODED. 1 H 7 2 3O A6CE 5 C P5EA 1998042900330 19980429 00330 GL 1998 4 29 EY2R9601266 3 19961201 G 6110 C2987 RACE CESSNA 206 P206C 2073312 CE MCAULY 3A32C D3A32C88 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 512 692219 RACE CORRODED. 1 H 7 1 3O A4CE 5 C P21EA 1998042900331 19980429 00331 GL 1998 4 29 EY2R9601267 3 19961201 G 6114 D5858C404 HUB CESSNA 206 U206 2073306 CE MCAULY D3A34 D3A34C404 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2643 851392 HUB CORRODED. 1 H 7 1 3O A4CE 5 C P47GL 1998042900332 19980429 00332 GL 1998 4 29 EY2R9601268 3 19961201 G 6110 C5270 BEARINGS CESSNA 206 U206 2073306 CE MCAULY D3A34 D3A34C404 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2643 851392 BEARINGS FOUND CORRODED. 1 H 7 1 3O A4CE 5 C P47GL 1998042900333 19980429 00333 GL 1998 4 29 EY2R9601269 3 19961201 G 6110 C3903 RETAINERS CESSNA 206 U206 2073306 CE MCAULY D3A34 D3A34C404 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2643 851392 RETAINERS FOUND CORRODED. 1 H 7 1 3O A4CE 5 C P47GL 1998042900334 19980429 00334 GL 1998 4 29 EY2R9601270 3 19961201 G 6111 T10173E8 BLADE BEECH 200 200BEECH 1152920 CE HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BU2510 BLADE, SN B51837, FOUND CORRODED. 1 L 7 2 4T A24CE 6 C P15EA 1998042900335 19980429 00335 GL 1998 4 29 EY2R9601271 3 19961201 G 6110 2202 BEARING PIPER PA32 PA32300 7103212 SO HARTZL HCC2Y HCC2YR1 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3331 CH12928 BEARING FOUND CORRODED. 1 L 7 1 3O A3SO 5 C P920 1998042900336 19980429 00336 GL 1998 4 29 EY2R9601272 3 19961201 G 6111 F8475D4 BLADE PIPER PA32 PA32300 7103212 SO HARTZL HCC2Y HCC2YR1 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3331 CH12928 SHANK FOUND CORRODED. 1 L 7 1 3O A3SO 5 C P920 1998042900337 19980429 00337 GL 1998 4 29 EY2R9601273 3 19961201 G 6110 C7036 NUT CESSNA 421 421B 2076014 CE MCAULY 3AF34C 3AF34C92 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 6108 753019 NUT CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1998042900338 19980429 00338 GL 1998 4 29 EY2R9601274 3 19961201 G 6111 T10173E8 BLADE BEECH 100 100BEECH 1152916 CE HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BU2510 BLADE, SN B51384, FOUND CORRODED. 1 L 7 2 3T A14CE 6 C P15EA 1998042900339 19980429 00339 GL 1998 4 29 EY2R9601275 3 19961201 G 6111 T10173E8 BLADE BEECH 100 100BEECH 1152916 CE HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BU2510 BLADE, SN B51383, FOUND CORRODED 1 L 7 2 3T A14CE 6 C P15EA 1998042900340 19980429 00340 GL 1998 4 29 EY2R9601276 3 19961201 G 6111 T10173E8 BLADE BEECH 100 100BEECH 1152916 CE HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BU2491 BLADE, SN B51827, FOUND CORRODED 1 L 7 2 3T A14CE 6 C P15EA 1998042900341 19980429 00341 GL 1998 4 29 EY2R9601277 3 19961201 G 6111 T10173E8 BLADE BEECH 100 100BEECH 1152916 CE HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BU2491 BLADE, SN B51441, FOUND CORRODED. 1 L 7 2 3T A14CE 6 C P15EA 1998042900342 19980429 00342 GL 1998 4 29 EY2R9601278 3 19961201 G 6111 T10173E8 BLADE BEECH 100 100BEECH 1152916 CE HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BU2491 BLADE, SN B51073, FOUND CORRODED. 1 L 7 2 3T A14CE 6 C P15EA 1998042900343 19980429 00343 GL 1998 4 29 EY2R9601279 3 19961201 G 6111 90UMB0 BLADE CESSNA 421 421 2076010 CE MCAULY 3FF32 3FF32C501 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 55 776790 BLADE SHANK, SN K76136, FOUND CORRODED. 1 L 7 2 3O RT A7CE 5 C P45GL 1998042900344 19980429 00344 GL 1998 4 29 EY2R9601280 3 19961201 G 6111 90UMB0 BLADE CESSNA 421 421 2076010 CE MCAULY 3FF32 3FF32C501 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 55 776790 BLADE SHANK, SN K76140, FOUND CORRODED. 1 L 7 2 3O RT A7CE 5 C P45GL 1998042900345 19980429 00345 GL 1998 4 29 EY2R9601281 3 19961201 G 6111 90UMB0 BLADE CESSNA 421 421 2076010 CE MCAULY 3FF32 3FF32C501 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 55 776790 BLADE SHANK, SN K76153, FOUND CORRODED. 1 L 7 2 3O RT A7CE 5 C P45GL 1998042900346 19980429 00346 GL 1998 4 29 EY2R9601282 3 19961201 G 6111 90DFA10 BLADE CESSNA 210 210 2073402 CE MCAULY 2A34C D2A34C* GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 815622 BLADE, SN BH469, FOUND CORRODED. 1 H 7 1 3O RT 3A21 5 C P3EA 1998042900347 19980429 00347 GL 1998 4 29 EY2R9601283 3 19961201 G 6111 90DFA10 BLADE CESSNA 210 210 2073402 CE MCAULY 2A34C D2A34C* GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 815622 BLADE, SN BH489, FOUND CORRODED. 1 H 7 1 3O RT 3A21 5 C P3EA 1998042900348 19980429 00348 GL 1998 4 29 EY2R9601284 3 19961201 G 6111 90DFA10 BLADE CESSNA 210 210 2073402 CE MCAULY 2A34C D2A34C* GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 815622 BLADE, SN BH500, FOUND CORRODED. 1 H 7 1 3O RT 3A21 5 C P3EA 1998042900349 19980429 00349 GL 1998 4 29 EY2R9601285 3 19961201 G 6114 D5858C402 HUB CESSNA 210 210 2073402 CE MCAULY 2A34C D2A34C* GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 815622 HUB FOUND CORRODED. 1 H 7 1 3O RT 3A21 5 C P3EA 1998042900350 19980429 00350 GL 1998 4 29 EY2R9601286 3 19961201 G 6114 D5926 HUB BOEING 75 A75N1 1380134 CE MCAULY 41D59 41D5926 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 AC4215977 HUB FOUND CORRODED. 1 Q 7 1 3R A743 5 N 781 1998042900351 19980429 00351 GL 1998 4 29 EY2R9601287 3 19961201 G 6111 MC42 BLADE BOEING 75 A75N1 1380134 CE MCAULY 41D59 41D5926 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 AC4215977 BLADE, SN 424274, FOUND CORRODED. 1 Q 7 1 3R A743 5 N 781 1998042900352 19980429 00352 GL 1998 4 29 EY2R9601288 3 19961201 G 6111 S82NC4 BLADE CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 714662 BLADE, SN F26105YS, FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1998042900353 19980429 00353 GL 1998 4 29 EY2R9601289 3 19961201 G 6111 S82NC4 BLADE CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 714662 BLADE, SN F26088YS, FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1998042900354 19980429 00354 GL 1998 4 29 EY2R9601290 3 19961201 G 6111 S82NC4 BLADE CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 714662 BLADE, SN F26156YS, FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1998042900355 19980429 00355 GL 1998 4 29 EY2R9601291 3 19961201 G 6111 T10282N4 BLADE HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BUA19181 BLADE, SHANK AREA, SN H76638, FOUND CORRODED. 6 C P15EA 1998042900356 19980429 00356 GL 1998 4 29 EY2R9601292 3 19961201 G 6111 T10282N4 BLADE HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BUA19181 BLADE, SHANK AREA, SN H76629, FOUND CORRODED. 6 C P15EA 1998042900357 19980429 00357 GL 1998 4 29 EY2R9601293 3 19961201 G 6111 T10282N4 BLADE HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BUA19181 BLADE, SN H76636, SHANK AREA, FOUND CORRODED. 6 C P15EA 1998042900358 19980429 00358 GL 1998 4 29 EY2R9601294 3 19961201 G 6111 BLADE PIPER PA23 PA23 7102302 SO HARTZL HC82X HC82XL2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 K2314N BLADE, SN'S 103647, 104122, FOUND CORRODED. 1 L 7 2 3O 1A10 5 C P878 1998042900359 19980429 00359 GL 1998 4 29 EY2R9601295 3 19961201 G 6110 C4451 FERRULE CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 5217 1299 696110 FERRULE FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1998042900360 19980429 00360 GL 1998 4 29 EY2R9601296 3 19961201 G 6114 D7015C87 HUB CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 5217 1299 696110 HUB FOUND WITH CORROSION. 1 L 7 2 3O 3A10 5 C P22EA 1998042900361 19980429 00361 GL 1998 4 29 EY2R9601297 3 19961201 G 6110 C4451 FERRULE CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2895 1295 797157 FERRULE FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1998042900362 19980429 00362 GL 1998 4 29 EY2R9601298 3 19961201 G 6111 S82NC55 BLADE CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2895 1295 797157 BLADE, SN F84468YS, FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1998042900363 19980429 00363 GL 1998 4 29 EY2R9601299 3 19961201 G 6111 S82NC55 BLADE CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2895 1295 797157 BLADE, SN F90225YS, FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1998042900364 19980429 00364 GL 1998 4 29 EY2R9601300 3 19961201 G 6111 S82NC55 BLADE CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2895 1295 797157 BLADE, SN K95983YS, FOUND CORRODED. 1 L 7 2 3O 3A10 5 C P22EA 1998010700013 19980107 00013 GL 1998 1 7 EY2R9601301 3 19961201 G 6110 C3550 CYLINDER CESSNA 310 310L 2074230 CE MCAULY D3AF32 D3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1234 436 728522 CYLINDER FOUND WITH CORROSION. 1 L 7 2 3O 3A10 5 C P22EA 1998010700014 19980107 00014 GL 1998 1 7 EY2R9601302 3 19961201 G 6110 C3550 CYLINDER CESSNA 310 310L 2074230 CE MCAULY D3AF32 D3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1234 436 728509 CYLINDER FOUND WITH CORROSION. 1 L 7 2 3O 3A10 5 C P22EA 1998042900365 19980429 00365 GL 1998 4 29 EY2R9601303 3 19961201 G 6110 C5270 BEARING CESSNA 210 T210* CE MCAULY D3A34 D3A34C402 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 7810149 BEARING RACE FOUND CORRODED. 1 H 7 1 3O 3A21 5 C P47GL 1998042900366 19980429 00366 GL 1998 4 29 EY2R9601304 3 19961201 G 6110 B5177 SCREW CESSNA 208 208 2073702 CE MCAULY 3AF34C 3GFR34C703 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2887 911091 SCREW CORRODED. 1 H 7 1 3T NT A37CE 5 C P60GL 1998042900367 19980429 00367 GL 1998 4 29 EY2R9601305 3 19961201 G 6110 D5010 CYLINDER CESSNA 208 208 2073702 CE MCAULY 3AF34C 3GFR34C703 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2887 911091 CYLINDER CORRODED. 1 H 7 1 3T NT A37CE 5 C P60GL 1998042900368 19980429 00368 GL 1998 4 29 EY2R9601306 3 19961201 G 6110 C5270 BEARING BEECH 58 58 1152740 CE MCAULY 3AF32C 3AF32C512 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1872 910156 BEARING CORRODED. 1 L 7 2 3O 3A16 5 C P22EA 1998042900369 19980429 00369 GL 1998 4 29 EY2R9601307 3 19961201 G 6114 D7019C92 HUB CESSNA 421 421 2076010 CE MCAULY 3AF34C 3AF34C92 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3692 1168 738767 HUB FOUND CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1998042900370 19980429 00370 GL 1998 4 29 EY2R9601308 3 19961201 G 6110 C7036 NUT CESSNA 421 421 2076010 CE MCAULY 3AF34C 3AF34C92 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3692 1168 738767 NUT CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1998042900371 19980429 00371 GL 1998 4 29 EY2R9601309 3 19961201 G 6110 1826 SPRING SWRNGN SA226 SA226AT 8780405 SW HARTZL HCB3T HCB3TN5 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BV4526 SPRING CORRODED. 2 L 7 2 4T RT A5SW 6 C P15EA 1998042900372 19980429 00372 GL 1998 4 29 EY2R9601310 3 19961201 G 6110 3498 SPRING SWRNGN SA226 SA226AT 8780405 SW HARTZL HCB3T HCB3TN5 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BV4526 SPRING CORRODED. 2 L 7 2 4T RT A5SW 6 C P15EA 1998042900373 19980429 00373 GL 1998 4 29 EY2R9601311 3 19961201 G 6110 1851T BEARING SWRNGN SA226 SA226AT 8780405 SW HARTZL HCB3T HCB3TN5 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BV4526 BEARING CORRODED. 2 L 7 2 4T RT A5SW 6 C P15EA 1998042900374 19980429 00374 GL 1998 4 29 EY2R9601312 3 19961201 G 6110 83867 CLAMP SWRNGN SA226 SA226AT 8780405 SW HARTZL HCB3T HCB3TN5 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BV4526 CLAMP CORRODED. 2 L 7 2 4T RT A5SW 6 C P15EA 1998042900375 19980429 00375 GL 1998 4 29 EY2R9601313 3 19961201 G 6111 M10876ASK BLADE STBROS SD3 SD360 8100606 EU HARTZL HCB5M HCB5MP3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 13167 4311 EV712 BLADE, SN F91132, FOUND CORRODED. 2 H 7 2 4T A41EU 6 C P44GL 1998042900376 19980429 00376 NE 1998 4 29 EY2R9601314 3 19961201 G 6110 792 BEARING BEECH 1900 1900D 1154162 CE HARTZL HCE4A HCE4A3A NE PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 4539 HJ241 PROP ASSY BEARING CORRODED. 2 L 7 2 4T RT A24CE 5 C P10NE 1998042900377 19980429 00377 GL 1998 4 29 EY2R9601315 3 19961201 G 6110 1851T BEARING SWRNGN SA226 SA226AT 8780405 SW HARTZL HCB3T HCB3TN5 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BV2796 BEARING CORRODED. 2 L 7 2 4T RT A5SW 6 C P15EA 1998042900378 19980429 00378 GL 1998 4 29 EY2R9601316 3 19961201 G 6114 D4344C93 HUB CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 795316 HUB FOUND CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1998042900379 19980429 00379 GL 1998 4 29 EY2R9601317 3 19961201 G 6110 C2987 RACES CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 795316 RACES CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1998042900380 19980429 00380 GL 1998 4 29 EY2R9601318 3 19961201 G 6110 C2987 RACES CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 794515 RACES CORRODED. 1 L 7 2 3O RT A7CE 5 C P22EA 1998042900381 19980429 00381 GL 1998 4 29 EY2R9601319 3 19961201 G 6110 C2987 RACES CESSNA 402 402B 207590P CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 5695 772 795378 RACES CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1998042900382 19980429 00382 GL 1998 4 29 EY2R9601320 3 19961201 G 6110 C3903 KEEPERS CESSNA 303 T303 2073820 CE MCAULY 3AF32C 3AF32C507 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2993 1650 814976 CORROSION FOUND ON KEEPERS. 1 L 7 2 3O A34CE 5 C P57GL 1998042900383 19980429 00383 GL 1998 4 29 EY2R9601321 3 19961201 G 6110 C3411 RACES CESSNA 303 T303 2073820 CE MCAULY 3AF32C 3AF32C507 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2993 1650 814976 RACES CORRODED. 1 L 7 2 3O A34CE 5 C P57GL 1998042900384 19980429 00384 GL 1998 4 29 EY2R9601322 3 19961201 G 6110 C3903 KEEPERS CESSNA 401 401 207590C CE MCAULY 3AF32C 3AF32C* GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 866 820094 CORROSION FOUND ON KEEPERS. 1 L 7 2 3O A7CE 5 C P22EA 1998042900385 19980429 00385 GL 1998 4 29 EY2R9601323 3 19961201 G 6110 C3411 RACES CESSNA 401 401 207590C CE MCAULY 3AF32C 3AF32C* GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 866 820094 RACES CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1998042900386 19980429 00386 GL 1998 4 29 EY2R9601324 3 19961201 G 6110 B3490 RACES CESSNA 401 401 207590C CE MCAULY 3AF32C 3AF32C* GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 866 820094 RACES CORRODED. 1 L 7 2 3O A7CE 5 C P22EA 1998042900387 19980429 00387 GL 1998 4 29 EY2R9601325 3 19961201 G 6110 C5270 RACES BEECH 36 A36 1151604 CE MCAULY 3A32C D3A32C* GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1704 931567 RACES CORRODED. 1 L 7 1 3O 3A15 5 C P21EA 1998042900388 19980429 00388 GL 1998 4 29 EY2R9601326 3 19961201 G 6114 24772R HUB PIPER PA23 PA23250 7102308 SO HARTZL HCE2Y HCE2YK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BP6434 HUB FOUND CORRODED. 1 L 7 2 3O 1A10 5 C P9EA 1998042900389 19980429 00389 GL 1998 4 29 EY2R9601327 3 19961201 G 6110 2202 BEARING PIPER PA23 PA23250 7102308 SO HARTZL HCE2Y HCE2YK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BP6434 BEARING CORRODED. 1 L 7 2 3O 1A10 5 C P9EA 1998042900390 19980429 00390 GL 1998 4 29 EY2R9601328 3 19961201 G 6111 F84657R BLADE PIPER PA23 PA23250 7102308 SO HARTZL HCE2Y HCE2YK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BP6434 BLADE, SN C37674, FOUND CORRODED. 1 L 7 2 3O 1A10 5 C P9EA 1998042900391 19980429 00391 GL 1998 4 29 EY2R9601329 3 19961201 G 6111 F84657R BLADE PIPER PA23 PA23250 7102308 SO HARTZL HCE2Y HCE2YK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BP6434 BLADE, SN C38521, FOUND CORRODED. 1 L 7 2 3O 1A10 5 C P9EA 1998042900392 19980429 00392 GL 1998 4 29 EY2R9601330 3 19961201 G 6110 2202 RACES PIPER PA23 PA23250 7102308 SO HARTZL HCE2Y HCE2YK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BP7417 RACES CORRODED. 1 L 7 2 3O 1A10 5 C P9EA 1998042900393 19980429 00393 GL 1998 4 29 EY2R9601331 3 19961201 G 6111 FC84756 BLADE BEECH 55 E55 1152732 CE HARTZL HCC2Y BHCC2YF2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 147 AN2518 BLADE, SN E50359, FOUND CORRODED. 1 L 7 2 3O 3A16 5 C P920 1998042900394 19980429 00394 GL 1998 4 29 EY2R9601332 3 19961201 G 6111 FC84756 BLADE BEECH 55 E55 1152732 CE HARTZL HCC2Y BHCC2YF2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 147 AN2518 BLADE, SN E50404, FOUND CORRODED. 1 L 7 2 3O 3A16 5 C P920 1998042900395 19980429 00395 GL 1998 4 29 EY2R9601333 3 19961201 G 6110 2202 BEARINGS BEECH 55 E55 1152732 CE HARTZL HCC2Y BHCC2YF2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 147 AN2518 BEARINGS CORRODED. 1 L 7 2 3O 3A16 5 C P920 1998042900396 19980429 00396 GL 1998 4 29 EY2R9601334 3 19961201 G 6110 1851T BEARINGS DHAV DHC6 DHC6300 EA HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2938 BU12633 BEARINGS CORRODED. 1 H 7 2 3T A9EA 6 C P15EA 1998042900397 19980429 00397 GL 1998 4 29 EY2R9601335 3 19961201 G 6110 2202 BEARINGS PIPER PA34 PA34200 7103405 SO HARTZL HCC2Y HCC2YK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 AU1601 BEARINGS CORRODED. 1 L 7 2 3O A7SO 5 C P920 1998042900398 19980429 00398 GL 1998 4 29 EY2R9601336 3 19961201 G 6110 2202 BEARINGS PIPER PA34 PA34200 7103405 SO HARTZL HCC2Y HCC2YK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 AU1577 BEARINGS CORRODED. 1 L 7 2 3O A7SO 5 C P920 1998042900399 19980429 00399 GL 1998 4 29 EY2R9601337 3 19961201 G 6110 1851 BEARING SWRNGN SA226 SA226AT 8780405 SW HARTZL HCB3T HCB3TN5 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BV3013 BEARING CORRODED. 2 L 7 2 4T RT A5SW 6 C P15EA 1998042900400 19980429 00400 GL 1998 4 29 EY2R9601338 3 19961201 G 6114 2201 HUB PIPER PA28 PA28* SO HARTZL HCC2Y HCC2YK1 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 CH19579 CORROSION FOUND ON HUB. 1 L 7 1 3O 2A13 5 C P920 1998042900401 19980429 00401 GL 1998 4 29 EY2R9601339 3 19961201 G 6114 2201 HUB PIPER PA34 PA34* SO HARTZL HCC2Y BHCC2YF2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 AN3046 CORROSION FOUND ON HUB. 1 L 7 2 3O RT A7SO 5 C P920 1998042900402 19980429 00402 GL 1998 4 29 EY2R9601340 3 19961201 G 6114 2201 HUB PIPER PA34 PA34* SO HARTZL HCC2Y BHCC2YF2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 AN2055 CORROSION FOUND ON HUB. 1 L 7 2 3O RT A7SO 5 C P920 1998042900403 19980429 00403 GL 1998 4 29 EY2R9601341 3 19961201 G 6114 C5480C66 HUB CESSNA 182 182 2072702 CE MCAULY 2A34C 2A34C66 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 68889 CORROSION FOUND ON HUB. 1 H 7 1 3O NT 3A13 5 C P3EA 1998042900404 19980429 00404 GL 1998 4 29 EY2R9601342 3 19961201 G 6110 C4450 FERRULES CESSNA 310 310K 2074228 CE MCAULY 2AF34C D2AF34C81 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 751494 FERRULES CORRODED. 1 L 7 2 3O 3A10 5 C P5EA 1998042900405 19980429 00405 GL 1998 4 29 EY2R9601343 3 19961201 G 6110 2202 BEARING PIPER PA34 PA34200 7103405 SO HARTZL HCC2Y BHCC2YF2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 AN4587 BEARING CORRODED. 1 L 7 2 3O A7SO 5 C P920 1998042900406 19980429 00406 GL 1998 4 29 EY2R9601344 3 19961201 G 6110 24913 ROD PIPER PA34 PA34200 7103405 SO HARTZL HCC2Y BHCC2YF2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 AN4587 CORROSION FOUND O PITCH CHANGE ROD. 1 L 7 2 3O A7SO 5 C P920 1998042900407 19980429 00407 GL 1998 4 29 EY2R9601345 3 19961201 G 6110 14B BEARING PIPER PA23 PA23160 7102304 SO HARTZL HC82 HC82VL2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 507R BEARING CORRODED. 1 L 7 2 3O 1A10 5 C P23EA 1998042900408 19980429 00408 GL 1998 4 29 EY2R9601346 3 19961201 G 6110 83811 CLAMP PIPER PA23 PA23160 7102304 SO HARTZL HC82 HC82VL2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 507R CLAMP CORRODED. 1 L 7 2 3O 1A10 5 C P23EA 1998042900409 19980429 00409 GL 1998 4 29 EY2R9601347 3 19961201 G 6110 87 JACK PLATE BLANCA 1419 1419 1220402 GL HARTZL HC12V HC12V20* GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 6234 CORROSION FOUND ON JACK PLATE. 1 L 7 1 3O 1A3 5 C P46GL 1998042900410 19980429 00410 GL 1998 4 29 EY2R9601348 3 19961201 G 6110 14B BEARING BLANCA 1419 1419 1220402 GL HARTZL HC12V HC12V20* GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 6234 BEARING CORRODED. 1 L 7 1 3O 1A3 5 C P46GL 1998042900411 19980429 00411 GL 1998 4 29 EY2R9601349 3 19961201 G 6110 83812 CLAMP BLANCA 1419 1419 1220402 GL HARTZL HC12V HC12V20* GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 6234 CORROSION FOUND ON CLAMP. 1 L 7 1 3O 1A3 5 C P46GL 1998042900412 19980429 00412 GL 1998 4 29 EY2R9601350 3 19961201 G 6114 4214 HUB BEECH 23 B24R 1151253 CE HARTZL HCM2Y HCM2YR GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 EN260 HUB FOUND CORRODED. 1 L 7 1 3O A1CE 5 C P43GL 1998042900413 19980429 00413 GL 1998 4 29 EY2R9601351 3 19961201 G 6110 38 THRUST BEARING HARTZL HC12X HC12X* GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 7751 CORROSION FOUND ON THRUST BEARING. 5 C P845 1998042900414 19980429 00414 GL 1998 4 29 EY2R9601352 3 19961201 G 6111 844712A BLADE BEECH 95 B95 1153404 CE HARTZL HC92W HC92WK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 858F BLADE, SN C1610, SHANK AREA, FOUND CORRODED. 1 L 7 2 3O 3A16 5 C P16EA 1998042900415 19980429 00415 GL 1998 4 29 EY2R9601353 3 19961201 G 6110 1303 BEARING BEECH 95 B95 1153404 CE HARTZL HC92W HC92WK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 858F BEARING CORRODED. 1 L 7 2 3O 3A16 5 C P16EA 1998042900416 19980429 00416 GL 1998 4 29 EY2R9601354 3 19961201 G 6110 1301 CLAMP BEECH 95 B95 1153404 CE HARTZL HC92W HC92WK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 858F PROP SHOULDER CLAMP FOUND CORRODED. 1 L 7 2 3O 3A16 5 C P16EA 1998042900417 19980429 00417 GL 1998 4 29 EY2R9601355 3 19961201 G 6110 855 ROD BEECH 95 B95 1153404 CE HARTZL HC92W HC92WK2 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 858F CORROSION FOUND ON PITCH CHANGE ROD. 1 L 7 2 3O 3A16 5 C P16EA 1998042900418 19980429 00418 GL 1998 4 29 EY2R9601356 3 19961201 G 6110 C4904 RETAIN NUT BEECH 36 A36 1151604 CE MCAULY 3AF32C 3AF32C* GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 801062 RETAIN NUT FOUND CORRODED. 1 L 7 1 3O 3A15 5 C P22EA 1998011500002 19980115 00002 GL 1998 1 15 EY2R9601358 3 19960601 G 6111 M10476 BLADE BEECH 300 300BEECH 1152930 CE HARTZL HCB4M HCB4MP3 GL PROPELLER ASSY CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1787 316 FW854 BLADE, SN H16195, FOUND CORRODED. 2 L 7 2 4T A24CE 6 C P56GL 1998011500003 19980115 00003 GL 1998 1 15 EY2R9601359 3 19960701 G 6110 2202 SPLIT BEARING BEECH 200 200BEECH 1152920 CE HARTZL HCD4N3 HCD4N3A GL PROP ASSY DEFECTIVE B K NONE O OTHER IN INSP/MAINT 1 GL 03 248 FY1155 SPLIT BEARING ONE RACE WOULD NOT DEMAGNETIZE. SUSPECT LIGHTNING. 1 L 7 2 4T A24CE 5 C STC 1998011500004 19980115 00004 GL 1998 1 15 EY2R9601361 3 19960801 G 6110 2202 SPLIT BEARING PIPER PA28 PA28R201T 7102813 SO HARTZL HCC2Y BHCC2YF1 GL PROPELLER ASSY DEFECTIVE B K NONE O OTHER IN INSP/MAINT 1 GL 03 2809 283 AM1784 PROPELLER MAGNETIZED. SUSPECT LIGHTNING 1 L 7 1 3O 2A13 5 C P920 1998011500005 19980115 00005 GL 1998 1 15 EY2R9601362 3 19960901 G 6111 114HCA0 BLADE MCAULY 5JFR B5JFR36C1101 GL PROPELLER ASSY DAMAGED B K NONE O OTHER IN INSP/MAINT 1 GL 03 899 951374 BLADE SN PD017 DAMAGED. SUSPECT LIGHTNING 5 C P15WE 1998011500006 19980115 00006 GL 1998 1 15 EY2R9601366 3 19960101 G 6110 C4451 FERRULE BEECH 95 95B55 1152729 CE MCAULY 2AF34C 2AF34C55 GL PROPELLER ASSY DAMAGED B K NONE O OTHER IN INSP/MAINT 1 GL 03 842577 SNAP RING GROOVE DAMAGED 1 L 7 2 3O RT 3A16 5 C P5EA 1998011500007 19980115 00007 GL 1998 1 15 EY2R9601367 3 19960101 G 6114 C4211C76 HUB BEECH 35 V35 1151538 CE MCAULY 3A32C 3A32C76 GL PROPELLER ASSY MIS DRILLED B K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 03 2165 1016 723315 PROP ASSY HUB DRILLED PAST .152 1 L 7 1 3O 3A15 5 C P21EA 1998011500008 19980115 00008 GL 1998 1 15 EY2R9601368 3 19960101 G 6110 D7015C72 HUB CESSNA 320 320C 2074510 CE MCAULY 3AF32C 3AF32C72 GL PROPELLER ASSY DEFECTIVE B K NONE O OTHER IN INSP/MAINT 1 GL 03 742238 HUB WELCH PLUG HOLES TOO CLOSE 1 L 7 2 3O 3A25 5 C P22EA 1998011500009 19980115 00009 GL 1998 1 15 EY2R9601369 3 19960101 G 6114 D7015C87 HUB CESSNA 402 402B 207590P CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY DEFECTIVE B K NONE O OTHER IN INSP/MAINT 1 GL 03 7710826 PROP ASSY HUB EXPANSION HOLE TOO DEEP 1 L 7 2 3O A7CE 5 C P22EA 1998011500010 19980115 00010 GL 1998 1 15 EY2R9601370 3 19960101 G 6114 D7027C87 HUB CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY DEFECTIVE B K NONE O OTHER IN INSP/MAINT 1 GL 03 756523 PROP ASSY HUB EXPANSION HOLES TOO CLOSE 1 L 7 2 3O 3A10 5 C P22EA 1998011500011 19980115 00011 GL 1998 1 15 EY2R9601373 3 19960101 G 6114 D7015C87 HUB CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY DEFECTIVE B K NONE O OTHER IN INSP/MAINT 1 GL 03 762832 PROP HUB ASSY HAS IMPROPER SAFETY HOLE 1 L 7 2 3O 3A10 5 C P22EA 1998011500012 19980115 00012 GL 1998 1 15 EY2R9601374 3 19960101 G 6110 B4459 ACTUATING PIN CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY BENT B K NONE O OTHER IN INSP/MAINT 1 GL 03 752145 BLADE ACTUATING PIN BENT 1 L 7 2 3O 3A10 5 C P22EA 1998011500013 19980115 00013 GL 1998 1 15 EY2R9601375 3 19960101 G 6114 D7015C93 HUB CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY DEFECTIVE B K NONE O OTHER IN INSP/MAINT 1 GL 03 782680 PROP HUB ASSY DRILLED PAST .152 1 L 7 2 3O RT A7CE 5 C P22EA 1998011500014 19980115 00014 GL 1998 1 15 EY2R9601376 3 19960101 G 6110 C3267 ADAPTER CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY DAMAGED B K NONE O OTHER IN INSP/MAINT 1 GL 03 741001 DAMAGE ON INSIDE BUSHING 1 L 7 2 3O RT A7CE 5 C P22EA 1998011500015 19980115 00015 NE 1998 1 15 EY2R9601379 3 19960101 G 6110 D5170 PISTON ROD SWRNGN SA227 SA227AC 8780603 SW MCAULY 4HFR34 4HFR34C652 NE PROPELLER ASSY BROKEN B K NONE O OTHER IN INSP/MAINT 1 GL 03 80392 HEAD BROKEN LOOSE FROM ROD ASSY. 2 L 7 2 4T RT A8SW 6 C 3PNE 1998011500016 19980115 00016 NE 1998 1 15 EY2R9601380 3 19960101 G 6110 D5170 PISTON ROD SWRNGN SA227 SA227AC 8780603 SW MCAULY 4HFR34 4HFR34C652 NE PROPELLER ASSY BROKEN B K NONE O OTHER IN INSP/MAINT 1 GL 03 81168 HEAD BROKEN LOOSE FROM ROD ASSY. 2 L 7 2 4T RT A8SW 6 C 3PNE 1998011500017 19980115 00017 GL 1998 1 15 EY2R9601382 3 19960101 G 6114 840139 HUB BEECH 100 A100 1152915 CE HARTZL HCB4T HCB4TN3 GL PROPELLER ASSY DEFECTIVE B K NONE O OTHER IN INSP/MAINT 1 GL 03 548 EAA1169 PROP HUB ASSY FAILED S.B. 196A 1 L 7 2 3T A14CE 6 C P40EA 1998011500018 19980115 00018 GL 1998 1 15 EY2R9601387 3 19960101 G 6110 24182 PISTON ROD CESSNA 172 172 2072402 CE HARTZL HCC2Y HCC2YR1 GL PROPELLER ASSY BENT B K NONE O OTHER IN INSP/MAINT 1 GL 03 CH6594 PROP ASSY PISTON ROD BENT 1 H 7 1 3O NT 3A12 5 C P920 1998011500019 19980115 00019 GL 1998 1 15 EY2R9601391 3 19960101 G 6111 FC84754 BLADE PIPER PA31 PA31 7103102 SO HARTZL HCE2Y HCE2YK2 GL PROPELLER ASSY WORN B K NONE O OTHER IN INSP/MAINT 1 GL 03 4975 1810 CJ344 BLADE SN F05216, PIN WORN 1 L 7 2 3O A20SO 5 C P9EA 1998011500020 19980115 00020 GL 1998 1 15 EY2R9601392 3 19960101 G 6111 FC84754 BLADE PIPER PA31 PA31 7103102 SO HARTZL HCE2Y HCE2YK2 GL PROPELLER ASSY WORN B K NONE O OTHER IN INSP/MAINT 1 GL 03 4975 1810 CJ344 BLADE SN F05201, PIN WORN 1 L 7 2 3O A20SO 5 C P9EA 1998011500021 19980115 00021 GL 1998 1 15 EY2R9601393 3 19960101 G 6111 F7673DR BLADE PIPER PA32 PA32301T 7103209 SO HARTZL HCE3Y HCE3YR1 GL PROPELLER ASSY DEFECTIVE B K NONE O OTHER IN INSP/MAINT 1 GL 03 BLADE BEARING BORE OVERSIZE 1 L 7 1 3O A3SO 5 C P33EA 1998011500022 19980115 00022 GL 1998 1 15 EY2R9601396 3 19960101 G 6111 FJC84686R BLADE PIPER PA31 PA31310 7103103 SO HARTZL HCE3Y HCE3YR2A GL PROPELLER ASSY DEFECTIVE B K NONE O OTHER IN INSP/MAINT 1 GL 03 1956 DJ10046A BLADE SN E34407, BORE OVERSIZED 1 L 7 1 3O RT A20SO 5 C P33EA 1998011500023 19980115 00023 GL 1998 1 15 EY2R9601397 3 19960101 G 6111 FJC84686R BLADE PIPER PA31 PA31310 7103103 SO HARTZL HCE3Y HCE3YR2A GL PROPELLER ASSY DEFECTIVE B K NONE O OTHER IN INSP/MAINT 1 GL 03 1956 DJ10046A BLADE SN E35512, BORE OVERSIZED 1 L 7 1 3O RT A20SO 5 C P33EA 1998011500024 19980115 00024 GL 1998 1 15 EY2R9601398 3 19960101 G 6110 24041 LOW PTCH STOP PIPER PA31 PA31350 7103110 SO HARTZL HCE3Y HCE3YR2A GL PROPELLER ASSY STRIPPED B K NONE O OTHER IN INSP/MAINT 1 GL 03 DJ4732 PROP LOW PITCH STOP HAS STRIPPED THREADS 1 L 7 2 3O A20SO 5 C P33EA 1998011500025 19980115 00025 GL 1998 1 15 EY2R9601403 3 19960201 G 6110 PROPELLER FIX PITCH CESSNA 172 172 2072402 CE MCAULY 1C160 1C160DTM GL PROPELLER ASSY DEFECTIVE B K NONE O OTHER IN INSP/MAINT 1 GL 03 KJ005 3 HOLES IN HUB FROM STOP DRILL 1 H 7 1 3O NT 3A12 5 N P910 1998011500026 19980115 00026 GL 1998 1 15 EY2R9601404 3 19960201 G 6110 A16349 BALL BEARING CESSNA 401 401A 207590D CE MCAULY 3AF32C 3AF32C* GL PROPELLER ASSY FRETTED B K NONE O OTHER IN INSP/MAINT 1 GL 03 489 910548 PROP ASSY BALLS FRETTED 1 L 7 2 3O A7CE 5 C P22EA 1998011500027 19980115 00027 GL 1998 1 15 EY2R9601405 3 19960201 G 6110 C5270 RETAIN BEARING CESSNA 401 401A 207590D CE MCAULY 3AF32C 3AF32C* GL PROPELLER ASSY FRETTED B K NONE O OTHER IN INSP/MAINT 1 GL 03 489 910548 PROP ASSY RETAIN BEARING RACES FRETTED 1 L 7 2 3O A7CE 5 C P22EA 1998011500028 19980115 00028 GL 1998 1 15 EY2R9601406 3 19960201 G 6114 D7015C87 HUB CESSNA 402 402B 207590P CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY DEFECTIVE B K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 03 709 761779 PROP ASSY HUB WELCH PLUGS DRILLED WRONG 1 L 7 2 3O A7CE 5 C P22EA 1998011500029 19980115 00029 GL 1998 1 15 EY2R9601407 3 19960201 G 6111 S82NC55 BLADE CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY DAMAGED B K NONE O OTHER IN INSP/MAINT 1 GL 03 687544 BLADE DAMAGED DUE TO DRILL MARK IN BALANCE HOLE 1 L 7 2 3O RT 3A10 5 C P22EA 1998011500030 19980115 00030 GL 1998 1 15 EY2R9601408 3 19960201 G 6114 D7015C87 HUB CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY DEFECTIVE B K NONE O OTHER IN INSP/MAINT 1 GL 03 713768 HUB STAKING PLUG HOLE IN WRONG PLACE 1 L 7 2 3O RT 3A10 5 C P22EA 1998011500031 19980115 00031 GL 1998 1 15 EY2R9601409 3 19960201 G 6111 B4459 ACTUATING PIN CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY DAMAGED B K NONE O OTHER IN INSP/MAINT 1 GL 03 780522 BLADE ACTUATING PIN DAMAGE NO REPAIR 1 L 7 2 3O RT A7CE 5 C P22EA 1998011500032 19980115 00032 GL 1998 1 15 EY2R9601411 3 19960201 G 6111 S82NC55 BLADE CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY DAMAGED B K NONE O OTHER IN INSP/MAINT 1 GL 03 780522 BLADE HAS SCRATCH IN RADIUS OF THREAD 1 L 7 2 3O RT A7CE 5 C P22EA 1998011500033 19980115 00033 NE 1998 1 15 EY2R9601412 3 19960201 G 6110 C5387 ACTUATI PIN CESSNA 425 425 2076018 CE MCAULY 4HFR34 4HFR34C762 NE PROPELLER ASSY DAMAGED B K NONE O OTHER IN INSP/MAINT 1 GL 03 902350 ACTUATING PIN DAMAGED 1 L 7 2 3T RT A7CE 6 C 3PNE 1998011500034 19980115 00034 GL 1998 1 15 EY2R9601413 3 19960201 G 6111 83867 CLAMP BEECH 90 B90 1152912 CE HARTZL HCB3T HCB3TN3 GL PROP ASSY PITTED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BLADE CLAMP HAS PITS IN RADIUS 1 L 7 2 3T 3A20 6 C P15EA 1998011500035 19980115 00035 GL 1998 1 15 EY2R9601414 3 19960201 G 6110 5862 PITCH CHANGE ROD BEECH 100 100BEECH 1152916 CE HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY BENT B K NONE O OTHER IN INSP/MAINT 1 GL 03 2053 BU4223 PITCH CHANGE ROD IS BENT. 1 L 7 2 3T A14CE 6 C P15EA 1998011500036 19980115 00036 GL 1998 1 15 EY2R9601415 3 19960201 G 6110 30012 LOW STOP COLLAR PIPER PA31T PA31T 7103124 SO HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY DEFECTIVE B K NONE O OTHER IN INSP/MAINT 1 GL 03 BU3996 LOW STOP COLLAR IS OUT OF ROUND 1 L 7 2 3T A8EA 6 C P15EA 1998011500037 19980115 00037 GL 1998 1 15 EY2R9601416 3 19960201 G 6110 13019S CLAMP MTSBSI MU2 MU2* SW HARTZL HCB3T HCB3TN5 GL PROPELLER ASSY MIS DRILLED B K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 03 BU2089 CLAMP SCREW HOLES MISDRILLED 1 H 7 2 3T A2PC 6 C P15EA 1998011500038 19980115 00038 GL 1998 1 15 EY2R9601417 3 19960201 G 6110 83867 CLAMP MTSBSI MU2 MU2* SW HARTZL HCB3T HCB3TN5 GL PROPELLER ASSY MIS DRILLED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BU2120 CLAMP SCREW HOLES MISDRILLED 1 H 7 2 3T A2PC 6 C P15EA 1998011500039 19980115 00039 GL 1998 1 15 EY2R9601422 3 19960201 G 6110 4991 HUB BEECH 200 200BEECH 1152920 CE HARTZL HCD4N3 HCD4N3A GL PROPELLER ASSY DAMAGED B K NONE O OTHER IN INSP/MAINT 1 GL 03 FY415A HUB O'RING GROOVE DAMAGE 1 L 7 2 4T A24CE 5 C STC 1998011500040 19980115 00040 GL 1998 1 15 EY2R9601423 3 19960201 G 6114 4991 HUB BEECH 200 200BEECH 1152920 CE HARTZL HCD4N3 HCD4N3A GL PROPELLER ASSY DAMAGED B K NONE O OTHER IN INSP/MAINT 1 GL 03 FY416A THREADS PULLED ON HUB 1 L 7 2 4T A24CE 5 C STC 1998011500041 19980115 00041 GL 1998 1 15 EY2R9601426 3 19960301 G 6114 C5480C66 HUB CESSNA 182 182 2072702 CE MCAULY 2A34C 2A34C66 GL PROPELLER ASSY DEFECTIVE B K NONE O OTHER IN INSP/MAINT 1 GL 03 683275 HUB HAS IMPROPER CYL. MTG. HOLE 1 H 7 1 3O NT 3A13 5 C P3EA 1998011500042 19980115 00042 GL 1998 1 15 EY2R9601427 3 19960301 G 6110 D3474 PISTON ROD ASSY CESSNA 303 T303 2073820 CE MCAULY 3AF32C 3AF32C507 GL PROPELLER ASSY WORN B K NONE O OTHER IN INSP/MAINT 1 GL 03 820985 PROP PISTON ROD ASSY WORN 1 L 7 2 3O A34CE 5 C P57GL 1998011500043 19980115 00043 GL 1998 1 15 EY2R9601430 3 19960301 G 6110 C3474 PISTON ROD ASSY CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY WORN B K NONE O OTHER IN INSP/MAINT 1 GL 03 753352 PROP PISTON ROD ASSY WORN 1 L 7 2 3O 3A10 5 C P22EA 1998011500044 19980115 00044 GL 1998 1 15 EY2R9601431 3 19960301 G 6114 D7015C87 HUB CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY DEFECTIVE B K NONE O OTHER IN INSP/MAINT 1 GL 03 756462 HUB STAKING PIN HOLES TOO CLOSE 1 L 7 2 3O RT 3A10 5 C P22EA 1998011500045 19980115 00045 GL 1998 1 15 EY2R9601434 3 19960301 G 6110 D3474 PISTON ROD ASSY CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY WORN B K NONE O OTHER IN INSP/MAINT 1 GL 03 727514 PROP PISTON ROD ASSY WORN 1 L 7 2 3O 3A10 5 C P22EA 1998011500046 19980115 00046 GL 1998 1 15 EY2R9601437 3 19960301 G 6110 D3474 PISTON ROD ASSY CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY WORN B K NONE O OTHER IN INSP/MAINT 1 GL 03 3406 1101 779611 PROP PISTON ROD ASSY WORN 1 L 7 2 3O 3A25 5 C P22EA 1998011500047 19980115 00047 GL 1998 1 15 EY2R9601438 3 19960301 G 6110 C4451 FERRULE CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY MIS DRILLED B K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 03 789634 PROP FERRULE HOLES DRILLED TOO CLOSE 1 L 7 2 3O 3A25 5 C P22EA 1998011500048 19980115 00048 GL 1998 1 15 EY2R9601440 3 19960301 G 6110 D3474 PISTON ROD ASSY CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY WORN B K NONE O OTHER IN INSP/MAINT 1 GL 03 802952 PROP PISTON ROD ASSY WORN 1 L 7 2 3O 3A25 5 C P22EA 1998011500049 19980115 00049 GL 1998 1 15 EY2R9601441 3 19960301 G 6110 D3474 PISTON ROD ASSY CESSNA 421 421A 2076012 CE MCAULY 3AF34C 3AF34C92 GL PROPELLER WORN B K NONE O OTHER IN INSP/MAINT 1 GL 03 727005 PROP PISTON ROD ASSY WORN 1 L 7 2 3O A7CE 5 C P22EA 1998011500050 19980115 00050 GL 1998 1 15 EY2R9601443 3 19960301 G 6110 D3474 PISTON ROD ASSY CESSNA 421 421A 2076012 CE MCAULY 3AF34C 3AF34C92 GL PROPELLER ASSY WORN B K NONE O OTHER IN INSP/MAINT 1 GL 03 726157 PROP PISTON ROD ASSY WORN 1 L 7 2 3O A7CE 5 C P22EA 1998011500051 19980115 00051 GL 1998 1 15 EY2R9601444 3 19960301 G 6114 D7019C92 HUB CESSNA 421 421 2076010 CE MCAULY 3AF34C 3AF34C92 GL PROPELLER ASSY DEFECTIVE B K NONE O OTHER IN INSP/MAINT 1 GL 03 740705 PROP HUB ALIGNMENT STUD PULLED 1 L 7 2 3O RT A7CE 5 C P22EA 1998011500052 19980115 00052 GL 1998 1 15 EY2R9601445 3 19960301 G 6111 S90LF0 BLADE CESSNA 421 421B 2076014 CE MCAULY 3AF34C 3AF34C92 GL PROPELLER ASSY DAMAGED B K NONE O OTHER IN INSP/MAINT 1 GL 03 781644 BLADE SN B20325YS, THREADS SCRATCHED 1 L 7 2 3O A7CE 5 C P22EA 1998011500053 19980115 00053 GL 1998 1 15 EY2R9601452 3 19960301 G 6114 D5878C501 HUB CESSNA 404 404CESSNA 2075901 CE MCAULY 3FF32 3FF32C501 GL PROPELLER ASSY DAMAGED B K NONE O OTHER IN INSP/MAINT 1 GL 03 781134 HUB BEARING RACE MATING AREA DAMAGED 1 L 7 2 3O A25CE 5 C P45GL 1998011500054 19980115 00054 GL 1998 1 15 EY2R9601453 3 19960301 G 6110 C3474 PISTON ROD ASSY CESSNA 421 421C 2076016 CE MCAULY 3FF32 3FF32C501 GL PROPELLER ASSY WORN B K NONE O OTHER IN INSP/MAINT 1 GL 03 3139 1430 812996 PROP PISTON ROD ASSY WORN 1 L 7 2 3O A7CE 5 C P45GL 1998011500055 19980115 00055 GL 1998 1 15 EY2R9601455 3 19960301 G 6111 S82N4 BLADE CESSNA 182 182E 2072712 CE MCAULY 2A34C D2A34C58 GL PROPELLER ASSY DAMAGED B K NONE O OTHER IN INSP/MAINT 1 GL 03 780308 BLADE SN C89035YS, THREAD DAMAGE 1 H 7 1 3O NT 3A13 5 C P3EA 1998012200001 19980122 00001 GL 1998 1 22 EY2R9601456 3 19960301 G 6114 D4887C81 HUB CESSNA 310 310 2074202 CE MCAULY 2AF34C D2AF34C81 GL PROP ASSY FRETTED B K NONE O OTHER IN INSP/MAINT 1 GL 03 7772913 PROP HUB HAS EXCESSIVE FRETTING. 1 L 7 2 3O RT 3A10 5 C P5EA 1998020500244 19980205 00244 GL 1998 2 5 EY2R9601458 3 19960301 G 6114 D7037C80 HUB MCAULY 3AF32C D3AF32C80 GL PROP ASSY DEFECTIVE B K NONE O OTHER IN INSP/MAINT 1 GL 03 654650 HUB STAKING PIN HOLES TOO CLOSE 5 C P22EA 1998020500245 19980205 00245 GL 1998 2 5 EY2R9601459 3 19960301 G 6114 24772 HUB PIPER PA23 PA23250 7102308 SO HARTZL HCE2Y HCE2YR2 GL PROP ASSY WORN B K NONE O OTHER IN INSP/MAINT 1 GL 03 BP9141 HUB PISTON ROD BORE ABOVE MAXIMUM 1 L 7 2 3O 1A10 5 C P9EA 1998012200002 19980122 00002 GL 1998 1 22 EY2R9601460 3 19960301 G 6110 884 SPRING PIPER PA23 PA23150 7102303 CE HARTZL HC82 HC82VL2 GL PROPELLER ASSY WORN B K NONE O OTHER IN INSP/MAINT 1 GL 03 K2739N PROP ASSY SPRING WORN 1 L 7 2 3O RT 1A10 5 C P23EA 1998012200003 19980122 00003 GL 1998 1 22 EY2R9601461 3 19960301 G 6114 84074 HUB BEECH 18 18S 1150802 CE HARTZL HCB3R HCB3R304 GL PROPELLER ASSY DAMAGED B K NONE O OTHER IN INSP/MAINT 1 GL 03 A6596A HUB HAS DEEP DEEP SCRATCHES BETWEEN SPLINES 1 L 7 2 3R TC710 5 C P28EA 1998012200004 19980122 00004 GL 1998 1 22 EY2R9601462 3 19960301 G 6110 30012 LOW STOP COLLAR BEECH 200 200BEECH 1152920 CE HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY WORN B K NONE O OTHER IN INSP/MAINT 1 GL 03 BU12196 PROP LOW STOP COLLAR IS WORN 1 L 7 2 4T A24CE 6 C P15EA 1998012200005 19980122 00005 GL 1998 1 22 EY2R9601466 3 19960301 G 6114 220117 HUB CESSNA 177 177 2073704 CE HARTZL HCC2Y HCC2YR1 GL PROPELLER ASSY DAMAGED B K NONE O OTHER IN INSP/MAINT 1 GL 03 CH24362 HUB GREASE FITTING HOLE DAMAGED 1 H 7 1 3O NT A13CE 5 C P920 1998012200006 19980122 00006 GL 1998 1 22 EY2R9601467 3 19960301 G 6110 24182 PISTON ROD CESSNA 182 182 2072702 CE HARTZL HCC3Y HCC3YF1 GL PROPELLER ASSY DAMAGED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1873 168 EC176 PROP ASSY PISTON ROD ASSY DAMAGED 1 H 7 1 3O NT 3A13 5 C P25EA 1998020500246 19980205 00246 GL 1998 2 5 EY2R9601473 3 19960401 G 6110 D3474 PISTON ROD ASSY CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROP ASSY WORN B K NONE O OTHER IN INSP/MAINT 1 GL 03 2454 1338 721970 PISTON ROD ASSY WORN 1 L 7 2 3O 3A10 5 C P22EA 1998012200007 19980122 00007 GL 1998 1 22 EY2R9601474 3 19960401 G 6110 D3474 PISTON ROD ASSY CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY WORN B K NONE O OTHER IN INSP/MAINT 1 GL 03 733313 PROP ASSY PISTON ROD ASSY WORN 1 L 7 2 3O 3A10 5 C P22EA 1998012200008 19980122 00008 GL 1998 1 22 EY2R9601475 3 19960401 G 6110 D3474 PISTON ROD CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY WORN B K NONE O OTHER IN INSP/MAINT 1 GL 03 784317 PROP ASSY PISTON ROD ASSY IS WORN 1 L 7 2 3O 3A10 5 C P22EA 1998012200009 19980122 00009 GL 1998 1 22 EY2R9601480 3 19960401 G 6114 D7019C92 HUB CESSNA 421 421 2076010 CE MCAULY 3AF34C 3AF34C92 GL PROPELLER ASSY STRIPPED B K NONE O OTHER IN INSP/MAINT 1 GL 03 743413 PROP ASSY HUB DOWEL PIN HOLE STUD STRIPPED 1 L 7 2 3O RT A7CE 5 C P22EA 1998012200010 19980122 00010 GL 1998 1 22 EY2R9601483 3 19960401 G 6114 D4197C90 HUB CESSNA 206 P206A 2073308 CE MCAULY 3A32C D3A32C90 GL PROPELLER ASSY MIS DRILLED B K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 03 3698 972 754862 PROP HUB WELCH PLUG HOLES DRILLED WRONG 1 H 7 1 3O A4CE 5 C P21EA 1998012200011 19980122 00011 GL 1998 1 22 EY2R9601488 3 19960401 G 6110 2020 BEARING CESSNA 172 172 2072402 CE HARTZL HCC2Y HCC2YK1 GL PROPELLER ASSY WORN B K NONE O OTHER IN INSP/MAINT 1 GL 03 CH22812 PROP ASSY BEARING WORN 1 H 7 1 3O NT 3A12 5 C P920 1998012200012 19980122 00012 GL 1998 1 22 EY2R9601489 3 19960401 G 6114 3276 HUB PIPER PA31 PA31P 7103120 SO HARTZL HCC3Y HCC3YN GL PROPELLER ASSY DAMAGED B K NONE O OTHER IN INSP/MAINT 1 GL 03 DG519 PROP ASSY HUB DAMAGED 1 L 7 2 3O A8EA 5 C P25EA 1998020500247 19980205 00247 GL 1998 2 5 EY2R9601497 3 19960501 G 6110 B4459 BLADE ACT PIN CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL PROP ASSY DAMAGED B K NONE O OTHER IN INSP/MAINT 1 GL 03 3428 501 723023 BLADE ACTUATING PIN DAMAGED 1 L 7 2 3O 3A10 5 C P22EA 1998012200013 19980122 00013 GL 1998 1 22 EY2R9601498 3 19960501 G 6111 B4459 ACTUATING PIN CESSNA 310 310Q 2074242 CE MCAULY 3AF32C 3AF32C87 GL BLADE WORN B K NONE O OTHER IN INSP/MAINT 1 GL 03 3428 501 723458 PROP ASSY BLADE ACTUATING PIN WORN 1 L 7 2 3O 3A10 5 C P22EA 1998012200014 19980122 00014 GL 1998 1 22 EY2R9601501 3 19960501 G 6110 B4650 LINK ASSY CESSNA 414 414 2075908 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER ASSY BENT B K NONE O OTHER IN INSP/MAINT 1 GL 03 453 7710747 PROP LINK ASSY IS BENT 1 L 7 2 3O RT A7CE 5 C P22EA 1998012200015 19980122 00015 GL 1998 1 22 EY2R9601502 3 19960501 G 6110 D3474 PISTON ROD ASSY CESSNA 421 421 2076010 CE MCAULY 3FF32 3FF32C501 GL PROPELLER ASSY WORN B K NONE O OTHER IN INSP/MAINT 1 GL 03 771839 PROP ASSY PISTON ROD ASSY IS WORN 1 L 7 2 3O RT A7CE 5 C P45GL 1998012200016 19980122 00016 GL 1998 1 22 EY2R9601504 3 19960501 G 6110 B3478 RETAIN RING CESSNA 210 210M 2073450 CE MCAULY 3A32C D3A32C88 GL PROPELLER ASSY BENT B K NONE O OTHER IN INSP/MAINT 1 GL 03 785659 PROP ASSY RETAIN RING IS BENT 1 H 7 1 3O 3A21 5 C P21EA 1998012200017 19980122 00017 GL 1998 1 22 EY2R9601507 3 19960501 G 6114 84059 HUB PIPER PA23 PA23150 7102303 CE HARTZL HC82 HC82VL2 GL PROPELLER ASSY DAMAGED B K NONE O OTHER IN INSP/MAINT 1 GL 03 5125 1111 K851N PROP HUB THREADS MISSING 1 L 7 2 3O RT 1A10 5 C P23EA 1998012200018 19980122 00018 GL 1998 1 22 EY2R9601509 3 19960501 G 6110 3475A2 LOW STOP COLLAR BEECH 90 C90 1152913 CE HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY BENT B K NONE O OTHER IN INSP/MAINT 1 GL 03 3181 1979 BU16874 PROP ASSY LOW STOP COLLAR BENT 1 L 7 2 3T 3A20 6 C P15EA 1998012200019 19980122 00019 GL 1998 1 22 EY2R9601513 3 19960501 G 6112 4E26241 SLIP RING BEECH 1900 1900C 1154161 CE HARTZL HCB4M HCB4MP3 GL PROPELLER ASSY DEBONDED B K NONE O OTHER IN INSP/MAINT 1 GL 03 FW984 PROP ASSY SLIP RING DEBONDED, INSULATOR CRACKED 2 L 7 2 4T RT A24CE 6 C P56GL 1998020500248 19980205 00248 GL 1998 2 5 EY2R9601514 3 19960501 G 6110 868AS PITCH CHANGE ROD BEECH 35 B35 1151506 CE HARTZL HCB4M HCB4MP3 GL PROP ASSY DEFECTIVE B K NONE O OTHER IN INSP/MAINT 1 GL 03 FW1117 PITCH CHANGE ROD DEFECTIVE 1 L 7 1 3O A777 6 C P56GL 1998012200020 19980122 00020 GL 1998 1 22 EY2R9601516 3 19960501 G 6110 3494 HIGH PTCH STOP BEECH 100 100BEECH 1152916 CE HARTZL HCB4T HCB4TN5 GL PROPELLER ASSY BENT B K NONE O OTHER IN INSP/MAINT 1 GL 03 CD402 PROPELLER ASSY HIGH PITCH STOP FOUND BENT. 1 L 7 2 3T A14CE 6 C P40EA 1998012200021 19980122 00021 GL 1998 1 22 EY2R9601517 3 19960501 G 6110 83034 HIGH PTCH STOP BEECH 100 100BEECH 1152916 CE HARTZL HCB4T HCB4TN5 GL PROPELLER ASSY BENT B K NONE O OTHER IN INSP/MAINT 1 GL 03 CD402 HIGH PITCH STOP FOUND BENT. 1 L 7 2 3T A14CE 6 C P40EA 1998012200022 19980122 00022 GL 1998 1 22 EY2R9601525 3 19960501 G 6110 24914S PITCH CHANGE ROD PIPER PA30 PA30 7103002 SO HARTZL HCE2Y HCE2YL2 GL PROPELLER ASSY WORN B K NONE O OTHER IN INSP/MAINT 1 GL 03 BG1381 PROP ASSY PITCH CHANGE ROD WORN 1 L 7 2 3O A1EA 5 C P9EA 1998012200023 19980122 00023 GL 1998 1 22 EY2R9601534 3 19960601 G 6110 C3474 PISTON ROD ASSY CESSNA 303 T303 2073820 CE MCAULY 3AF32C 3AF32C506 GL PROPELLER ASSY BENT B K NONE O OTHER IN INSP/MAINT 1 GL 03 821060 PISTON ROD ASSY BENT 1 L 7 2 3O A34CE 5 C P57GL 1998012200024 19980122 00024 GL 1998 1 22 EY2R9601535 3 19960601 G 6110 C4283 CYLINDER CESSNA 303 T303 2073820 CE MCAULY 3AF32C 3AF32C506 GL PROPELLER ASSY DENTED B K NONE O OTHER IN INSP/MAINT 1 GL 03 821060 PROP ASSY CYLINDER DENTED 1 L 7 2 3O A34CE 5 C P57GL 1998012200025 19980122 00025 GL 1998 1 22 EY2R9601540 3 19960601 G 6111 C4459 ACTUATING PIN CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY DAMAGED B K NONE O OTHER IN INSP/MAINT 1 GL 03 783822 PROP ASSY BLADE ACTUATING PIN DAMAGED 1 L 7 2 3O 3A10 5 C P22EA 1998012200026 19980122 00026 GL 1998 1 22 EY2R9601545 3 19960601 G 6110 C3550 FEATHER CYLINDER CESSNA 421 421 2076010 CE MCAULY 3AF34C 3AF34C92 GL PROPELLER ASSY DEFECTIVE B K NONE O OTHER IN INSP/MAINT 1 GL 03 805941 PROP ASSY FEATHER ASSY .067 LARGER THAN NORMAL 1 L 7 2 3O RT A7CE 5 C P22EA 1998020500249 19980205 00249 GL 1998 2 5 EY2R9601550 3 19960601 G 6114 D7019C92 HUB CESSNA 421 421B 2076014 CE MCAULY 3AF34C 3AF34C92 GL PROP ASSY DEFECTIVE B K NONE O OTHER IN INSP/MAINT 1 GL 03 400 768477 PROP HUB HAS PULLED STUD 1 L 7 2 3O A7CE 5 C P22EA 1998012200027 19980122 00027 NE 1998 1 22 EY2R9601551 3 19960601 G 6111 L106LA0 BLADE SWRNGN SA226 SA226AC 8780402 SW MCAULY 4HFR34 4HFR34C652 NE PROPELLER DAMAGED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2834 890503 BLADE SN JC011, RADIUS DAMAGED 2 L 7 2 4T RT A5SW 6 C 3PNE 1998012200028 19980122 00028 GL 1998 1 22 EY2R9601552 3 19960601 G 6110 C3418 PISTON CESSNA 182 182 2072702 CE MCAULY 2D34C B2D34C214 GL PROPELLER ASSY DAMAGED B K NONE O OTHER IN INSP/MAINT 1 GL 03 786792 PROP ASSY PISTON IS DAMAGED 1 H 7 1 3O NT 3A13 5 C P7EA 1998012200029 19980122 00029 GL 1998 1 22 EY2R9601554 3 19960601 G 6110 A31504 ROLL PIN CESSNA 210 210 2073402 CE MCAULY D3A34 D3A34C402 GL PROPELLER ASSY BENT B K NONE O OTHER IN INSP/MAINT 1 GL 03 796954 PROP ASSY ROLL PIN BENT 1 H 7 1 3O RT 3A21 5 C P47GL 1998012200030 19980122 00030 GL 1998 1 22 EY2R9601555 3 19960601 G 6111 S82NC4 BLADE CESSNA 310 310L 2074230 CE MCAULY 3AF32C D3AF32C80 GL PROPELLER ASSY DAMAGED B K NONE O OTHER IN INSP/MAINT 1 GL 03 663778 BLADE SN K77739YS, SCRATCH IN THREADS 1 L 7 2 3O 3A10 5 C P22EA 1998012200031 19980122 00031 GL 1998 1 22 EY2R9601556 3 19960601 G 6111 S90AT8 BLADE CESSNA 206 P206B 2073309 CE MCAULY 2A34C E2A34C73 GL PROPELLER DAMAGED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1187 850614 BLADE SN EJ299YS, THREADS CHIPPED. 1 H 7 1 3O A4CE 5 C P3EA9 1998012200032 19980122 00032 GL 1998 1 22 EY2R9601557 3 19960601 G 6111 S90AT8 BLADE CESSNA 206 P206B 2073309 CE MCAULY 2A34C E2A34C73 GL PROPELLER ASSY STRIPPED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1187 850614 BLADE SN EJ247YS, THREADS CHIPPED 1 H 7 1 3O A4CE 5 C P3EA9 1998020500250 19980205 00250 GL 1998 2 5 EY2R9601558 3 19960601 G 6114 84096 HUB GULSTM 500 500RKWELL 0141102 SW HARTZL HCA2X HCA2XK2 GL PROP ASSY WORN B K NONE O OTHER IN INSP/MAINT 1 GL 03 H2803 HUB PILOT TUBE BORE WORN 1 H 7 2 3O 6A1 5 C P908 1998020500251 19980205 00251 GL 1998 2 5 EY2R9601559 3 19960601 G 6114 84096 HUB GULSTM 500 500RKWELL 0141102 SW HARTZL HCA2X HCA2XK2 GL PROP ASSY DEFECTIVE B K NONE O OTHER IN INSP/MAINT 1 GL 03 H2804 HUB PILOT TUBE BORE DEFECTIVE 1 H 7 2 3O 6A1 5 C P908 1998012200033 19980122 00033 GL 1998 1 22 EY2R9601560 3 19960601 G 6110 13019S CLAMP BEECH 100 100BEECH 1152916 CE HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY MISDRILLED B K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 03 6715 BV5314 PROP ASSY CLAMP HAS MISDRILLED 321 SCREWS. 1 L 7 2 3T A14CE 6 C P15EA 1998012200034 19980122 00034 GL 1998 1 22 EY2R9601561 3 19960601 G 6110 30012 LOW STOP COLLAR BEECH 100 100BEECH 1152916 CE HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY DEFECTIVE B K NONE O OTHER IN INSP/MAINT 1 GL 03 6715 BV5314 LOW STOP COLLAR IS .30 INCH OUT OF ROUND. 1 L 7 2 3T A14CE 6 C P15EA 1998012200035 19980122 00035 GL 1998 1 22 EY2R9601562 3 19960601 G 6197 38012 WIRE BEECH 100 100BEECH 1152916 CE HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY DAMAGED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2018 BU13376 PROP ASSY I.D. WIRE DAMAGE 1 L 7 2 3T A14CE 6 C P15EA 1998012200036 19980122 00036 GL 1998 1 22 EY2R9601564 3 19960601 G 6110 24573 PITCH CHANGE BNORM BN2 BN2A3 1520215 EU HARTZL HCC2Y HCC2YK2 GL PROP ASSY FORK WORN B K NONE O OTHER IN INSP/MAINT 1 GL 03 AU7443 PROP ASSY PITCH CHANGE FORK WORN 1 H 7 2 3O A17EU 5 C P920 1998012200037 19980122 00037 GL 1998 1 22 EY2R9601568 3 19960601 G 6114 32517 HUB BEECH 95 95B55 1152729 CE HARTZL HCC3Y PHCC3YF2 GL PROPELLER ASSY DAMAGED B K NONE O OTHER IN INSP/MAINT 1 GL 03 1545 EB1496 PROP HUB DOWEL PINS ENLARGED 1 L 7 2 3O RT 3A16 5 C P25EA 1998012200038 19980122 00038 GL 1998 1 22 EY2R9601570 3 19960701 G 6114 D7015C75 HUB BEECH 55 D55 1152730 CE MCAULY 3AF32C 3AF32C75 GL PROPELLER ASSY DAMAGED B K NONE O OTHER IN INSP/MAINT 1 GL 03 697561 PROP HUB OUTSIDE DAMAGE 1 L 7 2 3O 3A16 5 C P22EA 1998012200039 19980122 00039 GL 1998 1 22 EY2R9601571 3 19960701 G 6110 C3550 FEATHER CYLINDER CESSNA 402 402B 207590P CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY WORN B K NONE O OTHER IN INSP/MAINT 1 GL 03 697985 PROP FEATHER CYLINDER WORN 1 L 7 2 3O A7CE 5 C P22EA 1998012200040 19980122 00040 GL 1998 1 22 EY2R9601572 3 19960701 G 6110 C3550 FEATHER CYLINDER CESSNA 402 402B 207590P CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY WORN B K NONE O OTHER IN INSP/MAINT 1 GL 03 779568 PROP FEATHER CYLINDER WORN 1 L 7 2 3O A7CE 5 C P22EA 1998012200041 19980122 00041 GL 1998 1 22 EY2R9601573 3 19960701 G 6114 D7015C87 HUB CESSNA 402 402B 207590P CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY DAMAGED B K NONE O OTHER IN INSP/MAINT 1 GL 03 697985 HUB EXPANSION HOLE TOO DEEP 1 L 7 2 3O A7CE 5 C P22EA 1998012200042 19980122 00042 GL 1998 1 22 EY2R9601574 3 19960701 G 6114 D7015C87 HUB CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY MIS DRILLED B K NONE O OTHER IN INSP/MAINT 1 GL 03 698455 NR1 SOCKET, STAKNG PIN DRILLED WRONG 1 L 7 2 3O RT 3A10 5 C P22EA 1998012200043 19980122 00043 GL 1998 1 22 EY2R9601575 3 19960701 G 6114 D7015C87 HUB CESSNA 310 310 2074202 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY DAMAGED B K NONE O OTHER IN INSP/MAINT 1 GL 03 690742 PROP HUB STAKING PIN HOLE TOO DEEP 1 L 7 2 3O RT 3A10 5 C P22EA 1998012200044 19980122 00044 GL 1998 1 22 EY2R9601576 3 19960701 G 6114 D7015C87 HUB CESSNA 340 340CESSNA 2076404 CE MCAULY 3AF32C 3AF32C87 GL PROPELLER ASSY MIS DRILLED B K NONE O OTHER IN INSP/MAINT 1 GL 03 721859 HUB STAKING PIN HOLE DRILLED WRONG 1 L 7 2 3O 3A25 5 C P22EA 1998012200045 19980122 00045 GL 1998 1 22 EY2R9601577 3 19960701 G 6110 C5503 BETA ROD CESSNA 208 208 2073702 CE MCAULY 3AF34C 3GFR34C703 GL PROPELLER ASSY WORN B K NONE O OTHER IN INSP/MAINT 1 GL 03 2566 910058 PROP BETA ROD WORN 1 H 7 1 3T NT A37CE 5 C P60GL 1998012200046 19980122 00046 GL 1998 1 22 EY2R9601578 3 19960701 G 6110 D5010 CYLINDER CESSNA 208 208 2073702 CE MCAULY 3AF34C 3GFR34C703 GL PROPELLER ASSY GROOVED B K NONE O OTHER IN INSP/MAINT 1 GL 03 2566 910058 PROP ASSY CYLINDER GROOVED EXCESSIVELY 1 H 7 1 3T NT A37CE 5 C P60GL 1998012200047 19980122 00047 GL 1998 1 22 EY2R9601579 3 19960701 G 6110 A16349 BALL BEARING CESSNA 172 172RG 2072438 CE MCAULY 2D34C B2D34C220 GL PROPELLER ASSY DEFECTIVE B K NONE O OTHER IN INSP/MAINT 1 GL 03 5633 1131 814657 PROP ASSY BEARINGS FLAT 1 H 7 1 3O 3A17 5 C P7EA 1998012200048 19980122 00048 GL 1998 1 22 EY2R9601580 3 19960701 G 6110 C5264 CYLINDER CESSNA 210 T210N 2073456 CE MCAULY D3A34 D3A34C402 GL PROPELLER ASSY DAMAGED B K NONE O OTHER IN INSP/MAINT 1 GL 03 815224 PROP ASSY CYLINDER DAMAGED 1 H 7 1 3O 3A21 5 C P47GL 1998012200049 19980122 00049 GL 1998 1 22 EY2R9601581 3 19960701 G 6110 127 COVER PLATE FRCHLD 24 24R46 3370514 EA HARTZL HC12V HC12V20* GL PROPELLER ASSY BENT B K NONE O OTHER IN INSP/MAINT 1 GL 03 P477 PROP ASSY COVER PLATE BENT 1 H 7 1 3I A706 5 C P46GL 1998012200050 19980122 00050 GL 1998 1 22 EY2R9601585 3 19960701 G 6110 30012 LOW STOP COLLAR PIPER PA31T PA31T1 7103126 SO HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY DAMAGED B K NONE O OTHER IN INSP/MAINT 1 GL 03 35843 CARBON BLOCK CUT GROOVE IN BETA RING 1 L 7 2 3T A8EA 6 C P15EA 1998020500252 19980205 00252 GL 1998 2 5 EY2R9601588 3 19960701 G 6114 220118 HUB PIPER PA34 PA34200T 7103406 SO HARTZL HCC2Y HCC2YF2 GL PROP ASSY DAMAGED B K NONE O OTHER IN INSP/MAINT 1 GL 03 AN4270 HUB DAMGED IN MOUNTING O'RING AREA 1 L 7 2 3O A7SO 5 C P920 1998020500253 19980205 00253 GL 1998 2 5 EY2R9601589 3 19960701 G 6114 220117 HUB CESSNA 172 172 2072402 CE HARTZL HCC2Y HCC2YK1 GL PROP ASSY DEFECTIVE B K NONE O OTHER IN INSP/MAINT 1 GL 03 CH28614 HUB HAS OVERSIZE QUAD SEAL GROOVE 1 H 7 1 3O NT 3A12 5 C P920 1998020500254 19980205 00254 GL 1998 2 5 EY2R9601592 3 19960701 G 6111 FC74792R BLADE BEECH 60 60 1153602 CE HARTZL HCF3Y HCF3YR2 GL PROP ASSY DAMAGED B K NONE O OTHER IN INSP/MAINT 1 GL 03 BLADE SN D2825, NICKED 1 L 7 2 3O A12CE 5 C P31EA 1998020500255 19980205 00255 GL 1998 2 5 EY2R9601593 3 19960801 G 6111 80VHA35 BLADE CESSNA 172 172RG 2072438 CE MCAULY 2D34C 2D34C* GL PROP ASSY GALLED B K NONE O OTHER IN INSP/MAINT 1 GL 03 4459 7910322 BLADE SN IB026, GALLED BAD 1 H 7 1 3O 3A17 5 C P7EA 1998020500256 19980205 00256 GL 1998 2 5 EY2R9601594 3 19960801 G 6111 80VHA35 BLADE CESSNA 172 172RG 2072438 CE MCAULY 2D34C 2D34C* GL PROP ASSY GALLED B K NONE O OTHER IN INSP/MAINT 1 GL 03 4459 7910322 BLADE SN IB008, GALLED BAD 1 H 7 1 3O 3A17 5 C P7EA 1998020500257 19980205 00257 GL 1998 2 5 EY2R9601595 3 19960801 G 6114 C5078C220 HUB CESSNA 172 172RG 2072438 CE MCAULY 2D34C 2D34C* GL PROP ASSY GALLED B K NONE O OTHER IN INSP/MAINT 1 GL 03 4459 7910322 HUB ASSY GALLED BAD 1 H 7 1 3O 3A17 5 C P7EA 1998020500258 19980205 00258 GL 1998 2 5 EY2R9601597 3 19960801 G 6111 S82NC2 BLADE CESSNA 188 A188B 2073005 CE MCAULY 3A32C D3A32C90 GL PROP ASSY FAILED B K NONE E VIBRATION/BUFFET NR NOT REPORTED 1 GL 03 891793 BLADE SN JE035YS, SLUNG TIP WHILE IN FLT 1 L 7 1 3O A9CE 5 C P21EA 1998020500259 19980205 00259 GL 1998 2 5 EY2R9601606 3 19960901 G 6110 D3474 PISTON ROD ASSY CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROP ASSY WORN B K NONE O OTHER IN INSP/MAINT 1 GL 03 4772 788627 PISTON ROD ASSY WORN 1 L 7 2 3O 3A10 5 C P22EA 1998020500260 19980205 00260 GL 1998 2 5 EY2R9601607 3 19960901 G 6110 D3474 PISTON ROD ASSY CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROP ASSY WORN B K NONE O OTHER IN INSP/MAINT 1 GL 03 4772 789445 PISYON ROD ASSY WORN 1 L 7 2 3O 3A10 5 C P22EA 1998020500261 19980205 00261 GL 1998 2 5 EY2R9601608 3 19960901 G 6110 D3474 PISTON ROD ASSY CESSNA 335 335 2075601 CE MCAULY 3AF32C 3AF32C87 GL PROP ASSY WORN B K NONE O OTHER IN INSP/MAINT 1 GL 03 798440 PISTON ROD ASSY WORN 1 L 7 2 3O 3A25 5 C P22EA 1998020500262 19980205 00262 GL 1998 2 5 EY2R9601609 3 19960901 G 6110 D3474 PISTON ROD ASSY CESSNA 335 335 2075601 CE MCAULY 3AF32C 3AF32C87 GL PROP ASSY WORN B K NONE O OTHER IN INSP/MAINT 1 GL 03 798443 PISTON ROD ASSY WORN 1 L 7 2 3O 3A25 5 C P22EA 1998020500263 19980205 00263 GL 1998 2 5 EY2R9601610 3 19960901 G 6110 C3550 FEATHER CYLINDER CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROP ASSY WORN B K NONE O OTHER IN INSP/MAINT 1 GL 03 940196 FEATHER CYLINDER WORN 1 L 7 2 3O 3A10 5 C P22EA 1998020500264 19980205 00264 GL 1998 2 5 EY2R9601613 3 19960901 G 6110 C5116 FEEDBACK COLLAR CESSNA 208 208 2073702 CE MCAULY 3AF34C 3GFR34C703 GL PROP ASSY DEFECTIVE B K NONE O OTHER IN INSP/MAINT 1 GL 03 233 952165 PROP ASSY FEEDBACK COLLAR OUT OF ROUND 1 H 7 1 3T NT A37CE 5 C P60GL 1998020500265 19980205 00265 GL 1998 2 5 EY2R9601614 3 19960901 G 6110 B2345 PISTON TUBE CESSNA 182 182 2072702 CE MCAULY 2D34C B2D34C214 GL PROP ASSY WORN B K NONE O OTHER IN INSP/MAINT 1 GL 03 3465 1803 783681 PISTON TUBE WORN 1 H 7 1 3O NT 3A13 5 C P7EA 1998020500266 19980205 00266 GL 1998 2 5 EY2R9601615 3 19960901 G 6111 S90AT8 BLADE CESSNA 210 210D 2073414 CE MCAULY 2A34C D2A34C58 GL PROP ASSY DAMAGED B K NONE O OTHER IN INSP/MAINT 1 GL 03 721718 SCRATCH IN THREADS OF BLADE SN K84876YS 1 H 7 1 3O 3A21 5 C P3EA 1998020500267 19980205 00267 GL 1998 2 5 EY2R9601618 3 19961001 G 6111 S78FM0 BLADE BEECH 55 9555 1152702 CE MCAULY 2AF36C 2AF36C89 GL PROP ASSY DAMAGED B K NONE O OTHER IN INSP/MAINT 1 GL 03 THREADS SCRATCHED ON BLADE SN 29825YS 1 L 7 2 3O 3A16 5 C P911 1998020500268 19980205 00268 GL 1998 2 5 EY2R9601619 3 19961001 G 6111 S78FM0 BLADE BEECH 55 9555 1152702 CE MCAULY 2AF36C 2AF36C89 GL PROP ASSY DAMAGED B K NONE O OTHER IN INSP/MAINT 1 GL 03 THREADS SCRATCHED ON BLADE SN 29825YS 1 L 7 2 3O 3A16 5 C P911 1998020500269 19980205 00269 GL 1998 2 5 EY2R9601627 3 19961001 G 6110 7384302 RACE DHAV DHC7 DHC7* EA HAMSTD 24PF 24PF305 GL PROP ASSY DEFECTIVE B K NONE O OTHER IN INSP/MAINT 1 GL 03 18628 4803 237492 PROP ASSY RACES CHATTERED 2 H 7 4 4T RT A20EA 6 C P1NE 1998020500270 19980205 00270 GL 1998 2 5 EY2R9601628 3 19961001 G 6110 B2345 PISTON TUBE CESSNA 182 182P 2075816 CE MCAULY 2A34C 2A34C203 GL PROP ASSY WORN B K NONE O OTHER IN INSP/MAINT 1 GL 03 870628 PROP ASSY PISTON TUBE WORN 1 H 7 1 3O NT TA13 5 C P3EA 1998020500271 19980205 00271 GL 1998 2 5 EY2R9601631 3 19961001 G 6110 D3474 PISTON ROD ASSY CESSNA 310 310R 2074245 CE MCAULY 3AF32C 3AF32C87 GL PROP ASSY WORN B K NONE O OTHER IN INSP/MAINT 1 GL 03 2780 771292 PISTON ROD ASSY WORN 1 L 7 2 3O 3A10 5 C P22EA 1998020500272 19980205 00272 GL 1998 2 5 EY2R9601633 3 19961001 G 6110 D3474 PISTON ROD ASSY CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROP ASSY WORN B K NONE O OTHER IN INSP/MAINT 1 GL 03 795369 PISTON ROD ASSY WORN 1 L 7 2 3O 3A25 5 C P22EA 1998020500273 19980205 00273 GL 1998 2 5 EY2R9601634 3 19961001 G 6110 D3474 PISTON ROD ASSY CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROP ASSY WORN B K NONE O OTHER IN INSP/MAINT 1 GL 03 795375 PISTON ROD ASSY WORN 1 L 7 2 3O 3A25 5 C P22EA 1998020500274 19980205 00274 GL 1998 2 5 EY2R9601635 3 19961001 G 6114 D7015C93 HUB CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROP ASSY WORN B K NONE O OTHER IN INSP/MAINT 1 GL 03 795369 HUB ASSY BUSHING HOLE OVERSIZE 1 L 7 2 3O 3A25 5 C P22EA 1998020500275 19980205 00275 GL 1998 2 5 EY2R9601636 3 19961001 G 6110 D3474 PISTON ROD ASSY CESSNA 421 421C 2076016 CE MCAULY 3FF32 3FF32C501 GL PROP ASSY WORN B K NONE O OTHER IN INSP/MAINT 1 GL 03 768385 PISTON ROD ASSY WORN 1 L 7 2 3O A7CE 5 C P45GL 1998020500276 19980205 00276 GL 1998 2 5 EY2R9601637 3 19961001 G 6110 D3474 PISTON ROD ASSY CESSNA 421 421C 2076016 CE MCAULY 3FF32 3FF32C501 GL PROP ASSY WORN B K NONE O OTHER IN INSP/MAINT 1 GL 03 789223 PISTON ROD ASSY WORN 1 L 7 2 3O A7CE 5 C P45GL 1998020500277 19980205 00277 GL 1998 2 5 EY2R9601639 3 19961001 G 6110 24281 CYLINDER UNIT PIPER PA28 PA28R201T 7102813 SO HARTZL HCC2Y BHCC2YF1 GL PROP ASSY WORN B K NONE O OTHER IN INSP/MAINT 1 GL 03 AM2596 PROP CYLINDER UNIT WORN 1 L 7 1 3O 2A13 5 C P920 1998020500278 19980205 00278 GL 1998 2 5 EY2R9601640 3 19961001 G 6110 A3267 ADAPTER CESSNA 337 337 2075702 CE MCAULY 2AF34C D2AF34C61 GL PROP ASSY WORN B K NONE O OTHER IN INSP/MAINT 1 GL 03 753558 PROP ASSY ADAPTER WORN 1 H 7 2 3O A6CE 5 C P5EA 1998020500279 19980205 00279 GL 1998 2 5 EY2R9601641 3 19961001 G 6110 C3274 FEATHER CYLINDER CESSNA 337 337 2075702 CE MCAULY 2AF34C D2AF34C61 GL PROP ASSY WORN B K NONE O OTHER IN INSP/MAINT 1 GL 03 753558 FEATHER CYLINDER ASSY WORN 1 H 7 2 3O A6CE 5 C P5EA 1998020500280 19980205 00280 GL 1998 2 5 EY2R9601653 3 19961001 G 6110 660709612 CYLINDER BAG JETSTM JETSTM3101 1500215 EU ROTOL R333 R333482F12 GL PROP ASSY WORN B K NONE O OTHER IN INSP/MAINT 1 GL 03 21893 5973 DRG936282 PROP ASSY CYLINDER WORN 2 L 7 2 4T RT A21EU 6 C P61GL 1998020500281 19980205 00281 GL 1998 2 5 EY2R9601654 3 19961001 G 6110 860013002 SPRING BAG JETSTM JETSTM3101 1500215 EU ROTOL R333 R333482F12 GL PROP ASSY WORN B K NONE O OTHER IN INSP/MAINT 1 GL 03 21893 5973 DRG936282 PROP ASSY SPRING WORN 2 L 7 2 4T RT A21EU 6 C P61GL 1998020500282 19980205 00282 GL 1998 2 5 EY2R9601655 3 19961001 G 6110 860014002 SPRING BAG JETSTM JETSTM3101 1500215 EU ROTOL R333 R333482F12 GL PROP ASSY WORN B K NONE O OTHER IN INSP/MAINT 1 GL 03 21893 5973 DRG936282 PROP ASSY SPRING WORN 2 L 7 2 4T RT A21EU 6 C P61GL 1998020500283 19980205 00283 GL 1998 2 5 EY2R9601656 3 19961101 G 6114 660709201 HUB BAG JETSTM JETSTM3101 1500215 EU ROTOL R333 R333482F12 GL PROP ASSY DEFECTIVE B K NONE O OTHER IN INSP/MAINT 1 GL 03 21844 5889 DRG418385 PROP ASSY HUB DEFECTIVE 2 L 7 2 4T RT A21EU 6 C P61GL 1998020500284 19980205 00284 CE 1998 2 5 EY2R9601657 3 19961101 G 6110 B200373 PITCH SCREW BEECH 35 F35 1151514 CE BEECH 215 215108 CE PROP ASSY WORN B K NONE O OTHER IN INSP/MAINT 1 GL 03 662 41714 PROP ASSY PITCH CHANGE SCREW WORN 1 L 7 1 3O A777 5 C P873 1998020500285 19980205 00285 CE 1998 2 5 EY2R9601658 3 19961101 G 6114 215107 HUB BEECH 35 D35 1151510 CE BEECH 215 215* CE PROP ASSY SCORED B K NONE O OTHER IN INSP/MAINT 1 GL 03 4959 HUB SCORED FROM BEARING 1 L 7 1 3O A777 5 C P873 1998020500286 19980205 00286 CE 1998 2 5 EY2R9601659 3 19961101 G 6110 B200373 PITCH SCREW BEECH 35 D35 1151510 CE BEECH 215 215* CE PROP ASSY WORN B K NONE O OTHER IN INSP/MAINT 1 GL 03 4959 PROP ASSY PITCH CHANGE SCREW WORN 1 L 7 1 3O A777 5 C P873 1998020500287 19980205 00287 GL 1998 2 5 EY2R9601662 3 19961101 G 6110 C5503 BETA ROD CESSNA 208 208 2073702 CE MCAULY 3AF34C 3GFR34C703 GL PROP ASSY WORN B K NONE O OTHER IN INSP/MAINT 1 GL 03 2490 911608 PROP ASSY BETA ROD WORN 1 H 7 1 3T NT A37CE 5 C P60GL 1998020500288 19980205 00288 GL 1998 2 5 EY2R9601663 3 19961101 G 6110 D5010 CYLINDER CESSNA 208 208 2073702 CE MCAULY 3AF34C 3GFR34C703 GL PROP ASSY DEFECTIVE B K NONE O OTHER IN INSP/MAINT 1 GL 03 2490 911608 PROP ASSY CYLINDER PLATING BLISTERED 1 H 7 1 3T NT A37CE 5 C P60GL 1998020500289 19980205 00289 NE 1998 2 5 EY2R9601664 3 19961101 G 6114 D6153C652 HUB SWRNGN SA226 SA226AC 8780402 SW MCAULY 4HFR34 4HFR34C652 NE PROP ASSY WORN B K NONE O OTHER IN INSP/MAINT 1 GL 03 10269 3143 890764 PROP HUB ASSY HAS WORN SHIM SET 2 L 7 2 4T RT A5SW 6 C 3PNE 1998020500290 19980205 00290 GL 1998 2 5 EY2R9601665 3 19961101 G 6111 B4163 BASE ASSY PIN CESSNA 337 337E 2075721 CE MCAULY 2AF34C D2AF34C302 GL PROP ASSY OTHERLOOSE B K NONE O OTHER IN INSP/MAINT 1 GL 03 712397 PROPELLER BLADE PIN LOOSE. PREVENTED ACTUATION. 1 H 7 2 3O A6CE 5 C P5EA 1998020500291 19980205 00291 GL 1998 2 5 EY2R9601672 3 19961201 G 6110 C3550 CYLINDER CESSNA 421 421B 2076014 CE MCAULY 3AF34C 3AF34C92 GL PROP ASSY SCORED B K NONE O OTHER IN INSP/MAINT 1 GL 03 6108 832375 PROP ASSY CYLINDER I.D. SCORED 1 L 7 2 3O A7CE 5 C P22EA 1998020500292 19980205 00292 GL 1998 2 5 EY2R9601677 3 19961201 G 6110 24913 ROD BNORM BN2 BN2 1520202 EU HARTZL HCC2Y HCC2YK2 GL PROP ASSY DEFECTIVE B K NONE O OTHER IN INSP/MAINT 1 GL 03 AU5083 PROP ASSY ROD HAS BAD THREADS 1 H 7 2 3O A17EU 5 C P920 1998020500293 19980205 00293 GL 1998 2 5 EY2R9601678 3 19961201 G 6110 24914S ROD PIPER PA23 PA23250 7102308 SO HARTZL HCE2Y HCE2YR2 GL PROP ASSY BENT B K NONE O OTHER IN INSP/MAINT 1 GL 03 BP8008 PROP ASSY ROD BENT 1 L 7 2 3O 1A10 5 C P9EA 1998020500294 19980205 00294 GL 1998 2 5 EY2R9601681 3 19961201 G 6110 C3550 CYLINDER CESSNA 421 421B 2076014 CE MCAULY 3AF34C 3AF34C92 GL PROP ASSY SCORED B K NONE O OTHER IN INSP/MAINT 1 GL 03 6108 753019 PROP ASSY CYLINDER I.D. SCORED 1 L 7 2 3O A7CE 5 C P22EA 1998020500295 19980205 00295 GL 1998 2 5 EY2R9601682 3 19961201 G 6110 24914S ROD BEECH 58 58 1152740 CE HARTZL HCJ2Y BHCJ2YF2 GL PROP ASSY STRIPPED B K NONE O OTHER IN INSP/MAINT 1 GL 03 4600 DZ336 PROP ASSY ROD THREAD STRIPPED 1 L 7 2 3O 3A16 5 C P37EA 1998020500296 19980205 00296 GL 1998 2 5 EY2R9601683 3 19961201 G 6110 24914S ROD PIPER PA23 PA23250 7102308 SO HARTZL HCE2Y HCE2YR2 GL PROP ASSY DEFECTIVE B K NONE O OTHER IN INSP/MAINT 1 GL 03 BP6390 PROP ASSY ROD IS DEFECTIVE 1 L 7 2 3O 1A10 5 C P9EA 1998021100005 19980211 00005 NE 1998 2 11 EY2R9601684 3 19961201 G 6110 6071 ROD SOCATA TBM TBM700 8682000 EU HARTZL HCE4N HCE4N3 NE PROP ASSY DEFECTIVE B K NONE O OTHER IN INSP/MAINT 1 GL 03 HH32 PROP ASSY SN 1321 IS DEFECTIVE 1 L 7 1 3T RT A60EU 5 C P10NE 1998020500297 19980205 00297 GL 1998 2 5 EY2R9601691 3 19961001 G 6111 76634 BLADE PIPER PA30 PA30 7103002 SO HARTZL HCE2Y HCE2YL2 GL PROP ASSY WORN B K NONE O OTHER IN INSP/MAINT 1 GL 03 BG2659 PITCH CHANGE KNOB BELOW MINIMUM 1 L 7 2 3O A1EA 5 C P9EA 1996020200314 19960202 00314 SW 1996 2 2 GCHA9622 1 19960116 G 2810 206063688001 HOSE BELL 206 206L1 1182107 SW FUEL CELL VENT LEAKING I GCHA K NONE B K SMOKE/FUMES/ODORS/SPARKS FLUID LOSS CR CRUISE 1 WP 19 1075S 16439 45366 PILOT REPORTED STRONG FUEL SMELL IN COCKPIT. FOUND THE R/H SIDE FLEX LINE LEAKING APPROX 7" FROM CENTER FITTING. REMOV ED AND REPLACED FORWARD FUEL CELL VENT HOSE ASSY WITH SERVICEABLE PART NUMBER 206-063-688-001 1 G 7 1 3U H2SW 1996112700284 19961127 00284 SW 1996 11 27 GJQR0000097 1 19961022 G 6410 204011702121 BLADE BELL 204 UH1B 1181410 SW T/R DEBONDED B GJQR K NONE O OTHER IN INSP/MAINT 1 NM 01 102FW 226 A20323 621905 C/W ASB 204-96-48 DUE TO POSSIBILITY OF DEBONDING OF THE MAIN SPAR LEADING EDGE DOUBLER. SEE AD 96-12-26. REPLACED WIT H NEW BLADES FROM CSF STOCK. (X) 1 G 7 1 4U EXPA1G71 1996112700283 19961127 00283 SW 1996 11 27 GJQR0000098 1 19961022 G 6410 204011702121 BLADE BELL 204 UH1B 1181410 SW T/R DEBONDED B GJQR K NONE O OTHER IN INSP/MAINT 1 NM 01 102FW 226 A20318 621905 C/W ASB 204-96-48 DUE TO POSSIBILITY OF DEBONDING OF THE MAIN SPAR LEADING EDGE DOUBLER. SEE AD 96-12-26. REPLACED WIT H NEW BLADES FROM CSF STOCK. (X) 1 G 7 1 4U EXPA1G71 1997020600185 19970206 00185 SW 1997 2 6 GJQR9600100 1 19961209 G 6410 206016201131 BLADE BELL 206 206B 1181511 SW T/R DEBONDED B GJQR K NONE O OTHER IN INSP/MAINT 1 NM 01 96NW 264 CS873 4389 BLADE REPLACED DUE TO DEBOND DETECTED DURING POST FLIGHT. BLADE MAKES CLICKING SOUND AND DELAMINATION PRESENT AT BLADE ROOT DOUBLER AREA. (X) 1 G 7 1 3U H2SW 1996121200113 19961212 00113 SW 1996 12 12 GJQR9663 1 19960201 G 5320 206020114131S FAIRING BELL 206 206B3 1181506 SW FUSELAGE MIS MFG H GJQR L ABORTED APPROACH W INADEQUATE Q C IN INSP/MAINT 1 SW 13 53W 3587 THIS FAIRING WAS ORDERED FROM BELL - BUT IT DOESN'T FIT - IT IS ONE-HALF INCH SHORT. 1 G 7 1 3U H2SW 1996062700389 19960627 00389 SW 1996 6 27 GJQR9664 1 19960201 G 6320 206075678107 INDICATOR BELL 206 206L 1181522 SW TRANSMISSION ERRATIC H GJQR K NONE O OTHER NR NOT REPORTED 1 SW 13 108W 1344 52034 INDICATOR IS ERRATIC - WILL NOT READ ABOVE 50 DEGREE - DROPS TO ZERO DURING FLIGHT, UNRELIABLE. REPLACED WITH NEW INDICA TOR FROM BELL. 1 G 7 1 3U H2SW 1996122600464 19961226 00464 SW 1996 12 26 GJQR9675 1 19960528 G 3213 206033108001 FITTING BELL 206 206L 1181522 SW RT CROSSTUBE WORN H K NONE O OTHER IN INSP/MAINT 1 FS 01 108W 1122 52034 FWD CROSS TUBE STRAP ASSY. WORN INTO RIGHT FW.CROSS TUBE FITTING. REPLACED FITTING PER PRODUCT SUPPORT WEAR LIMITS. 1 G 7 1 3U H2SW 1996122600465 19961226 00465 SW 1996 12 26 GJQR9680 1 19960528 G 6410 206310105101 BEARING BELL 206 206L 1181522 SW T/R BLADE DEFECTIVE H K NONE W INADEQUATE Q C IN INSP/MAINT 1 FS 01 108W 863 52034 INSTALLED BEARING IN T/R BLADE TO C/W TB206L-94-172 REV.A PT. I. BLADE ALIGNMENT WOULD NOT MEET THE DIMENSIONAL REQUIR EMENT DUE TO THE AXIAL PLAY IN THE NEW BEARING. REPLACED WITH NEW BEARING FROM CSF STOCK. 1 G 7 1 3U H2SW 1996122600466 19961226 00466 SW 1996 12 26 GJQR9681 1 19960528 G 6410 206010733003 SLEEVE BELL 206 206L 1181522 SW T/R BLADE DEFECTIVE H K NONE W INADEQUATE Q C IN INSP/MAINT 1 FS 01 108W 863 52034 INSTALLED BRG. IN T/R BLADE TO W/C TB206L-94-172 REV.A,PT.I. BLADE ALIGHNMENT WOUD NOT MEET THE DIMENSIONAL REQUIREMENT DUE TO THE AXIAL PAY IN THE NEW BEARING. REPLACED WITH NEW STOCK FROM CSF. 1 G 7 1 3U H2SW 1996011900170 19960119 00170 NE 1996 1 19 GMAL9501021 2 19960102 G 7323 116085025 GOVERNOR KAMAN K1200 K1200 05625F6 SW LYC T53 T5317A 41549 NE ENG OVERSPEED DEFECTIVE H GMAL O OTHER J WARNING INDICATION EX EXTERNAL LOAD 1 NM 09 132KA 410 A940004 PILOT REPORTED GOVERNOR DECAY FROM 104 PERCENT NR DOWN TO 97 PERCENT NR DURING HOVER. PROBLEM INTERMITTENT EVERY 3 TO 4 TURNS DURING LOGGING OPERATIONS. (X) 1 G 7 1 4F 4 U NT TR7BO E17EA 1996020900639 19960209 00639 NE 1996 2 9 GMAL9501022 2 19960102 G 7210 103022903 SEAL HOUSING KAMAN K1200 K1200 05625F6 SW LYC T53 T5317A 41549 NE OUTPUT GEARSHAFT CRACKED H S GMAL K NONE O OTHER IN INSP/MAINT 1 NM 09 132KA 410 940004 CIRCUMFERENCE CRACK OF OUTPUT GEAR SHAFT HOUSING IN STEP-DOWN RADIUS OF HOUSING, LEFT AND RIGHT SIDES 2:00 O'CLOCK TO 5: 00 O'CLOCK AND 7:00 O'CLOCK TO 10:00 O'CLOCK POSITIONS. (X) 1 G 7 1 4F 4 U NT TR7BO E17EA 1996031500401 19960315 00401 SW 1996 3 15 GMAL9501023 1 19960102 G 2121 K986127 FAN KAMAN K1200 K1200 05625F6 SW AIR DIST FAILED H GMAL K NONE O OTHER IN INSP/MAINT 1 NM 09 134KA 411 A940006 FAN MOTOR BEARINGS WORN. FAN WILL NOT ROTATE. FAN WAS INSTALLED AT A/C TT 560.8 HOURS ON 8-10-95. PREVIOUS FAN WAS RE PLACED FOR SAME PROBLEM. TOTAL TIME, AIRCRAFT, 560.8 HOURS. (X) 1 G 7 1 4F NT TR7BO 1996020900640 19960209 00640 NE 1996 2 9 GMAL9501024 2 19960102 G 7210 103022903 SEAL HOUSING KAMAN K1200 K1200 05625F6 SW LYC T53 T5317A 41549 NE OUTPUT GEARSHAFT CRACKED H GMAL K NONE O OTHER IN INSP/MAINT 1 NM 09 134KA 600 940006 CIRCUMFERENCE CRACK OF OUTPUT GEARSHAFT SEAL HOUSING IN STEP-DOWN RADIUS OF HOUSING, LEFT AND RIGHT SIDES. (X) 1 G 7 1 4F 4 U NT TR7BO E17EA 1996020900641 19960209 00641 NE 1996 2 9 GMAL9501025 2 19960102 G 7210 103022903 SEAL HOUSING KAMAN K1200 K1200 05625F6 SW LYC T53 T5317A 41549 NE OUTPUT GEARSHAFT CRACKED H GMAL K NONE O OTHER IN INSP/MAINT 1 NM 09 135KA 719 A940007 LE81004 CIRCUMFERENCE CRACK OF OUTPUT GEARSHAFT SEAL HOUSING IN STEP-DOWN RADIUS OF HOUSING, 2:00 O'CLOCK TO 6:00 O'CLOCK POSITI ONS. THIS SEAL RETAINER WAS REPLACED BY LYCOMING AT TOTAL TIME 583.6 ENGINE HOURS. (X) 1 G 7 1 4F 4 U NT TR7BO E17EA 1998042400255 19980424 00255 SW 1998 4 24 HAI00000067 1 19960307 G 2840 222366621103 FUEL FILTER BELL 206 206L 1181522 SW BYPSSS SWITCH MALFUNCTION H K NONE N FALSE WARNING IN INSP/MAINT 1 FS 01 108W 52034 AIRFRAME FUEL FILTER IMPENDING BYPASS SWITCH MALFUNCTIONING. BYPASS LIGHT COMES ON AND OFF WITH NO CONTAMINATION FOUND IN FILTER. REPLACED WITH NEW FILTER. 1 G 7 1 3U H2SW 1998042400256 19980424 00256 SW 1998 4 24 HAI00000068 1 19960307 G 6310 289051098 SEAL BELL 206 206B 1181511 SW ENG /XMSN WORN H K NONE O OTHER IN INSP/MAINT 1 FS 01 345RR 2107 SEAL IS WORN EXCESSIVELY. CUSTOMER COMPLAINT IS THAT ALL OF THE "2890" SERIES SEALS WITH THE BLACK MATERIAL SEEM TO WE AR DEEPER GROOVES AT A FASTER RATE THAN THE CHICAGO RAWHIDE SEALS WITH THE RED MATERIAL. THIS IS FOR INFORMATION ONLY. 1 G 7 1 3U H2SW 1998042400257 19980424 00257 1998 4 24 HAI00000069 1 19960404 G 2550 206072903101 CABLE ASSY CARGO HOOK FAILED H K NONE O OTHER IN INSP/MAINT 1 FS 01 1421 WHILE FERTILIZING DURING A FUEL STOP ON A NORMAL WALK-AROUND, NOTICED SOMETHING HANGING DOWN BELOW THE CARGO HOOK. FUR THER INVESTIGATION, FOUND THE CARGO HOOK EMERGENCY RELEASE CABLE BROKEN COMPLETELY THROUGH 2 INCHES FROM CONNECTION ON CARGOHOOK. REPLACED WITH NEW CABLE. 1998042400258 19980424 00258 SW 1998 4 24 HAI00000075 1 19960528 G 3213 206033108001 FITTING BELL 206 206L 1181522 SW RT CROSSTUBE WORN H K NONE O OTHER IN INSP/MAINT 1 FS 01 108W 1122 52034 FWD CROSS TUBE STRAP ASSY WORN INTO RIGHT FWD CROSS TUBE FITTING. REPLACED FITTING PER PRODUCT SUPPORT WEAR LIMITS. 1 G 7 1 3U H2SW 1998042400259 19980424 00259 SW 1998 4 24 HAI00000076 1 19960528 G 6320 206040810103 INDICATOR BELL 206 206L 1181522 SW TRANSMISSION DEFECTIVE H K NONE O OTHER IN INSP/MAINT 1 FS 01 108W 1526 52034 DURING 1500 TRANSMISSION SUN GEAR INSPECTION COMPLETED TB206L-95-183 PER BULLETIN. REPLACED WITH NEW PART FROM BHT 1 G 7 1 3U H2SW 1998042400260 19980424 00260 SW 1998 4 24 HAI00000080 1 19960528 G 6410 206310105101 BEARING BELL 206 206L 1181522 SW T/R BLADE DEFECTIVE H K NONE W INADEQUATE Q C IN INSP/MAINT 1 FS 01 108W 863 52034 INSTALLED BEARING IN T/R BLADE TO C/W TB206L-94-172 REV.A PT. I. BLADE ALIGNMENT WOULD NOT MEET THE DIMENSIONAL REQUIR EMENT DUE TO THE AXIAL PLAY IN THE NEW BEARING. REPLACED WITH NEW BEARING FROM CSF STOCK. 1 G 7 1 3U H2SW 1998042400261 19980424 00261 SW 1998 4 24 HAI00000081 1 19960528 G 6410 206010733003 SLEEVE BELL 206 206L 1181522 SW T/R BLADE DEFECTIVE H K NONE O OTHER IN INSP/MAINT 1 FS 01 108W 863 52034 INSTALLED BRG. IN T/R BLADE TO W/C TB206L-94-172 REV.A,PT.I. BLADE ALIGHNMENT WOULD NOT MEET THE DIMENSIONAL REQUIREMEN T DUE TO THE AXIAL PAY IN THE NEW BEARING. REPLACED WITH NEW STOCK FROM CSF. 1 G 7 1 3U H2SW 1998042400262 19980424 00262 1998 4 24 HAI00000084 1 19960627 G 7933 MS280343 TEMP BULB OIL TEMP FAILED H K NONE O OTHER IN INSP/MAINT 1 FS 01 INSTALLED NEW PART FROM CSF STOCK AND IT FAILED. REPLACED WITH NEW PART FROM CSF STOCK. 1998042400263 19980424 00263 GL 1998 4 24 HAI00000088 2 19961018 G 7210 406340104101 SEAL ALLSN 250C 250C30 03013 GL ENG GR BOX TORN H K NONE O OTHER IN INSP/MAINT 1 FS 01 SEAL IS TORN. REPLACED WITH NEW SEAL FROM CSF STOCK. 3 U E1GL 1998042400269 19980424 00269 SW 1998 4 24 HAIGJQR0063 1 19960201 G 5350 206020114131S FAIRING BELL 206 206B3 1181506 SW FUSELAGE MIS MFG H GJQR K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 13 53W 3587 THIS FAIRING WAS ORDERED FROM BELL - BUT IT DOESN'T FIT - IT IS ONE-HALF INCH SHORT. 1 G 7 1 3U H2SW 1998042400270 19980424 00270 SW 1998 4 24 HAIGJQR0064 1 19960201 G 6320 206075678107 INDICATOR BELL 206 206L 1181522 SW XMSN TEMP FAILED H GJQR K NONE O OTHER NR NOT REPORTED 1 SW 13 108W 1344 52034 INDICATOR IS ERRATIC - WILL NOT READ ABOVE 50 DEGREE - DROPS TO ZERO DURING FLIGHT, UNRELIABLE. REPLACED WITH NEW INDICA TOR FROM BELL. 1 G 7 1 3U H2SW 1998042400271 19980424 00271 SW 1998 4 24 HAIGJQR0100 1 19961204 G 6410 206016201131 BLADE BELL 206 206B 1181511 SW T/R DEBONDED H GJQR K NONE O OTHER IN INSP/MAINT 1 SW 13 96NW 264 4389 BLADE REPLACED DUE TO DEBOND DETECTED DURING POST FLIGHT. BLADE MAKES CLICKING SOUND AND DELAMINATION PRESENT AT BLADE ROOT DOUBLER AREA. REPLACED WITH CSF STOCK. 1 G 7 1 3U H2SW 1997041000498 19970410 00498 SW 1997 4 10 HAIW6HR0048 1 19961112 G 3340 G62504 LIGHT 222175302105 BELL 222 222U 1182140 SW STROBE CIRCUIT-GROUNDED E W6HR K NONE O OTHER IN INSP/MAINT 1 WP 21 429MA 116 47523 PART IS CIRCUIT-GROUNDED. LIGHT WILL NOT EXTEND AND POPS CIRCUIT BREAKER. 1 G 7 2 3U H9SW 1997041000499 19970410 00499 SW 1997 4 10 HAIW6HR0049 1 19961112 G 2840 7G547 SWITCH 206061600021 BELL 206 206B1 1181503 SW FUEL SYS DEFECTIVE E A W6HR K NONE O OTHER IN INSP/MAINT 1 WP 21 68TJ 206 1301 FUEL PRESSURE SWITCH IS DEFECTIVE. PART APPEARED TO BE DEFECTIVE UPON INSTALLATION. 2 OTHER SWITCHES PREVIOUSLY INSTAL LED FAILED WITHIN 5 MINS. OF USE.. REPLACED WITH NEW. 1 G 7 1 3U H2SW 1997041000500 19970410 00500 SW 1997 4 10 HAIW6HR0050 1 19961113 G 2913 65132 PUMP 222180004107 BELL 222 222U 1182140 SW #1 POSITION HYD WORN EXCESSIVELY E W6HR K NONE K FLUID LOSS IN INSP/MAINT 1 WP 21 415MA 47568 PUMP IS WORN EXCESSIVELY. PUMP LEAKS AT SHAFT SEAL. PUMP HAS ONLY BEEN INSTALLED 1 MONTH. BHT P/N: 222-380-009-103. . REPLACED WITH SERVICEABLE UNIT. 1 G 7 2 3U H9SW 1997041000501 19970410 00501 SW 1997 4 10 HAIW6HR0054 1 19961212 G 6330 222031662105 BEARING 222031662105 BELL 222 222U 1182140 SW XMSN MT WORN EXCESSIVELY E W6HR K NONE O OTHER IN INSP/MAINT 1 WP 21 429MA 490 0814 47523 PART IS WORN EXCESSIVELY. ELASTOMERIC MATERIAL IS EXTRUDING. PART BEING HELD FOR DISPOSITION. RDM 12-31-96. 1 G 7 2 3U H9SW 1997041000502 19970410 00502 SW 1997 4 10 HAIW6HR0055 1 19961212 G 6330 LB9130251NV FLEXURE 222031601105 BELL 222 222U 1182140 SW NODAL BEAM BROKEN E W6HR K NONE O OTHER IN INSP/MAINT 1 WP 21 415MA 189 47568 PART IS BROKEN. RUBBER IS SEPERATED FROM END FITTINGS. 1 G 7 2 3U H9SW 1997041000503 19970410 00503 SW 1997 4 10 HAIW6HR0056 1 19961212 G 6330 LB9130251NV FLEXURE 222031601106 BELL 222 222U 1182140 SW NODAL BEAM BROKEN E W6HR K NONE O OTHER IN INSP/MAINT 1 WP 21 415MA 189 47568 PART IS BROKEN. RUBBER IS SEPERATED FROM END FITTINGS. RETURNED TO MANU FOR CREDIT ( REQUEST REPLACEMENT PART) 1 G 7 2 3U H9SW 1997041000504 19970410 00504 NE 1997 4 10 HAIW6HR0061 2 19961220 G 7320 222360703101 SOLENOID 222060001103 BELL 222 222U 1182140 SW LYC LTS101 LTS101750C1 41560 NE FUEL CONTROL CIRCUIT-SHORTED E W6HR K NONE M OVER TEMP IN INSP/MAINT 1 WP 21 429MA 2 47523 PART IS CIRCUIT-SHORTED. PART FAILED - PART GOT EXTREMELY HOT. REPLACED WITH NEW PART - WORKS O.K.. 1 G 7 2 3U 3 U H9SW E5NE 1997041000505 19970410 00505 NE 1997 4 10 HAIW6HR0062 2 19961230 G 7320 222360703101 SOLENOID 222060001103 LYC LTS101 LTS101750C1 41560 NE FUEL CONTROL DEFECTIVE E W6HR K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 21 PART IS DEFECTIVE. UPON OPENING PACKAGE DURING "RECEIVING INSPECTION" FOUND LEVER ASSY. 'RETURN SPRING' OUT OF PLACE & U NWOUND. HOLDING UNIT FOR DISPOSITION. 3 U E5NE 1997041000506 19970410 00506 SW 1997 4 10 HAIW6HR0063 1 19961230 G 3340 G62504 LIGHT 222175302105 BELL 222 222U 1182140 SW SEARCH SEIZED E W6HR K NONE O OTHER LD LANDING 1 WP 21 429MA 47523 PART IS SEIZED. ASSY. WILL NOT EXTEND OR RETRACT. ASSY. HAS BEEN IN SERVICE 2 WEEKS SINCE REPAIR. 1 G 7 2 3U H9SW 1996011900254 19960119 00254 GL 1996 1 19 HEEA966329 2 19960102 G 7250 23032345 COUPLING 23033185 BELL 206 206L1 1182107 SW ALLSN 250C 250C28B 03013 GL 3RD STAGE STEP WEAR E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5007Y 453 CAT70022 45192 CAE860583 ENGINE REMOVED DUE TO TURBINE 3RD STAGE WHEEL REPLACEMENT. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: STEP WEAR BEYOND LIMITS ON N1 COUPLING I.D. SPLINES. INSTALLED NEW N1 COUPLING. 1 G 7 1 3U 3 U H2SW E1GL 1996011900255 19960119 00255 GL 1996 1 19 HEEA966330 2 19960102 G 7250 6886407 BLADE 6898735 AEROSP AS355 AS355F1 8680810 EU ALLSN 250C 250C20F 03013 GL 1ST STAGE WHEEL ERROSION E HEEA K NONE R PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 SW 03 5791M 951 CAT25125 5116 CAE840056 ENGINE REMOVED DUE TO LOW POWER AND OIL LEAKING. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: 50% OF 1ST STAG E WHEEL SULFIDATED AND DELAMINATED ON FORWARD SIDE OF BLADES AND EROSION OF ALL LEADING EDGES AND BLADE TIPS. SCRAPPED 1 ST STAGE WHEEL. 1 G 7 2 3U 3 U H11EU E4CE 1996011900256 19960119 00256 GL 1996 1 19 HEEA966331 2 19960102 G 7250 6886407 BLADE 6898735 BOLKMS 105 BO105S 5626006 EU ALLSN 250C 250C20B 03013 GL 1ST STAGE WHEEL DELAMINATED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5421E 725 CAT31716F S806 CAE836341 ENGINE REMOVED DUE TO CYCLED OUT 2ND STAGE WHEEL. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: SULFIDATION OF 1ST STAGE WHEEL BLADES CAUSING DELAMINATION ON AFT SIDE OF LEADING EDGES. SCRAPPED 1ST STAGE WHEEL. 1 G 7 2 3U 3 U H3EU E4CE 1996011900257 19960119 00257 GL 1996 1 19 HEEA966332 2 19960102 G 7250 6886407 BLADE 6898735 BELL 206 206B3 1181506 SW ALLSN 250C 250C20B 03013 GL 1ST STAGE WHEEL DELAMINATED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2285B 1493 CAT40231 3642 CAE836318 ENGINE REMOVED DUE TO CYCLED OUT WHEELS. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: SULFIDATION CAUSING SLI GHT DELAMINATION ON FORWARD SIDE OF ALL 1ST STAGE WHEEL BLADES AND EROSION ON LEADING EDGE. SCRAPPED 1ST STAGE WHEEL. 1 G 7 1 3U 3 U H2SW E4CE 1996011900258 19960119 00258 GL 1996 1 19 HEEA966334 2 19960102 G 7250 6886407 BLADE 6898735 BOLKMS 105 BO105S 5626006 EU ALLSN 250C 250C20B 03013 GL 1ST STAGE WHEEL DELAMINATED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 105WK 832 CAT38001F S812 CAE834578 ENGINE REMOVED DUE TO CYCLED OUT WHEELS. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: SULFIDATION ON ALL 1ST STAGE WHEEL BLADES CAUSING SLIGHT DELAMINATION. SCRAPPED 1ST STAGE WHEEL. 1 G 7 2 3U 3 U H3EU E4CE 1996011900259 19960119 00259 EU 1996 1 19 HEEA966335 1 19960102 G 7712 TORQUEMETER 6898735 BOLKMS 105 BO105S 5626006 EU ALLSN 250C 250C20B 03013 GL ENGINE LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 7170D 798 CAT127943 S840 CAE822237F ENGINE REMOVED DUE TO TORQUE METER LEAKING. 1 G 7 2 3U 3 U H3EU E4CE 1996011900260 19960119 00260 1996 1 19 HEEA966340 4 19960104 G 2370 9806019001 CVR BELL 412 412 1182202 SW COCKPIT INOPERATIVE E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 7128R 3066 36007 CVR INTERMITTENTLY INOPERATIVE. 1 G 7 2 4U H4SW 1996011900261 19960119 00261 1996 1 19 HEEA966341 4 19960104 G 3452 066106200 TRANSCEIVER KT76 BELL 206 206L 1181522 SW COCKPIT ATC FAILED E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 62127 52023 DOES NOT TRANSMIT CODE 0401 OR 1201 NO REPLY. REPLACED DEFECTIVE V101 CAVITY OSCILLATOR. ADJUSTED AS NEEDED AND BENCH C HECK GOOD. 1 G 7 1 3U H2SW 1996011900262 19960119 00262 1996 1 19 HEEA966342 4 19960104 G 2312 40001278500 TRANSCEIVER RT406F BOLKMS 105 BO105S 5626006 EU COCKPIT DEFECTIVE E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 7171A S838 NO MIC GAIN DEVIATION. REPLACED SYNTHESIZER BOARD P/N 300-014140-00 FROM ANOTHER UNIT. REPAIRED PROBLEM. UNIT BENCH CH ECK GOOD. 1 G 7 2 3U H3EU 1996011900263 19960119 00263 SW 1996 1 19 HEEA966343 1 19960104 G 7714 412075010109 INDICATOR BELL 412 412 1182202 SW TRIPLE TACH DEFECTIVE E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 7128R 36007 ALL NEEDLES HAVE EXCESSIVE NEEDLE SPLIT. #1 AND ROTOR NEEDLES STICK. 1 G 7 2 4U H4SW 1996011900264 19960119 00264 SW 1996 1 19 HEEA966344 1 19960104 G 6220 412010179105 CONE 412010100193 BELL 412 412 1182202 SW M/R HUB FRETTING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2298Z 3242 AAD50024 33077 FRETTING FABRIC GALLED OUT. 1 G 7 2 4U H4SW 1996011900265 19960119 00265 SW 1996 1 19 HEEA966345 1 19960104 G 6220 412010124109 BOLT 412010100193 BELL 412 412 1182202 SW M/R FLAKING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2298Z 2234 AAD50024 33077 PLATING FLAKING AT EDGE OF BOLT SHANK. 1 G 7 2 4U H4SW 1996011900266 19960119 00266 SW 1996 1 19 HEEA966346 1 19960104 G 6220 412010124109 BOLT 412010100193 BELL 412 412 1182202 SW M/R FLAKING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2298Z 2234 AAD50024 33077 PLATING FLAKING AT EDGE OF BOLT SHANK. 1 G 7 2 4U H4SW 1996011900267 19960119 00267 SW 1996 1 19 HEEA966347 1 19960104 G 6220 412010124109 BOLT 412010100193 BELL 412 412 1182202 SW M/R FLAKING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2298Z 2234 AAD50024 33077 PLATING FLAKING AT EDGE OF BOLT SHANK. 1 G 7 2 4U H4SW 1996011900268 19960119 00268 SW 1996 1 19 HEEA966348 1 19960104 G 5302 206032308003 FRAME BELL 206 206L1 1182107 SW TAILBOOM CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5007Q 45187 CRACKED IN UPPER L/H CORNER. REPLACED WITH SERVICEABLE FRAME. 1 G 7 1 3U H2SW 1996011900269 19960119 00269 SW 1996 1 19 HEEA966349 1 19960104 G 5302 206032308103S FRAME BELL 206 206L3 1182108 SW TAILBOOM CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 8589X 51487 FRAME CRACKED UPPER R/H BOLT AREA. REPLACED WITH SERVICEABLE FRAME. 1 G 7 1 3U H2SW 1996011900270 19960119 00270 SW 1996 1 19 HEEA966350 1 19960104 G 5302 206032308103 FRAME BELL 206 206L1 1182107 SW TAILBOOM CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2251Z 45756 PART IS CRACKED. L/H UPPER T/B FITTING CRACKED P/N 206-031-329-003. TAILBOOM MOUNT FRAME P/N 206-032-308-103S CRACKED AT UPPER L/H MOUNT HOLE. REPLACED FITTING UPPER L/H SIDE WITH 206-031-329-103S AND REPLACED T/B FRAME WITH P/N 206-032-3 08-103S. 1 G 7 1 3U H2SW 1996011900271 19960119 00271 SW 1996 1 19 HEEA966351 1 19960104 G 5320 206031200076 STRAP BELL 206 206B 1181511 SW AFT CABIN CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2269A 3608 PART IS CRACKED. AFT CABIN OVERHEAD BOX BEAM R/H STRAP P/N 206-031-200-076 CRACKED OUT AT CENTER R/H SUPPORT. INSTALLED NEW STRAP ASSEMBLY. 1 G 7 1 3U H2SW 1996011900272 19960119 00272 1996 1 19 HEEA966352 4 19960104 G 2210 214074303115 AMPLIFIER ASSY BELL 214 214ST 1182106 SW AUTOFLT DEFECTIVE E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 3897N 28106 PITCH WILL NOT ENGAGE. 2 G 7 2 4U H10SW 1996011900273 19960119 00273 NE 1996 1 19 HEEA966353 2 19960104 G 7320 3240864 SCREEN ASSY 324473513 BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE FUEL INLET SPRING FAILED E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 22347 B14461 36005 AIRCRAFT EXPERIENCED 10% TORQUE SPLIT IN FLIGHT WITH TORQUE AT OR ABOVE 90%. UPON CHECK OF SINGLE ENGINE BEEP RANGES NO TED #1 ENGINE FULL INCREASE RPM 2% HIGH. WHEN THROTTLE WAS ROLLED BACK TO IDLE, THE ENGINE WOULD DECEL ONLY TO 74% N1 I NSTEAD OF 61%. ALSO THE THROTTLE WOULD SELF-ADVANCE RAPIDLY TO FULL OPEN POSITION IF IT WASN'T HELD OR FRICTIONED. RE PLACED THE AFCU AND DURING SWAP OF FUEL TUBES FOUND PIECES OF THE FUEL INLET SCREEN ASSEMBLY SPRING IN THE INLET PORT, A ND ADDITIONAL PIECES LODGED IN THE PORT. IT APPEARS THAT THE INLET SCREEN ASSEMBLY MAY HAVE BEEN INSTALLED INCORRECTLY FROM THE MANUFACTURER. REPLACED AFCU. NOTE: THE AFCU WAS OVERHAULED BY PRATT & WHITNEY MAY 1995 1 G 7 2 4U 4 U H4SW E22EA 1996011900274 19960119 00274 SW 1996 1 19 HEEA966354 1 19960104 G 5321 412030324101 PANEL BELL 412 412 1182202 SW RT FLOOR WRONG STUD E HEEA K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 3893N 33010 STUD P/N 120-064-3HN WAS INSTALLED IN WRONG POSITION. HAD TO REMOVE IT TO MAKE REPAIR TO STYROFOAM AND INSTALL PROPER ST UD P/N 120-142-1. REMOVED PANEL AND MADE HOLE IN STYROFOAM. REMOVED STUD AND INSTALLED SERVICEABLE STUD. REPAIRED HOLE AND REINSTALLED PANEL. 1 G 7 2 4U H4SW 1996011900275 19960119 00275 EU 1996 1 19 HEEA966355 1 19960104 G 3242 419210E CALIPER BOLKMS 105 BO105S 5626006 EU ROTOR BRAKE DEFECTIVE E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 624MB S751 PISTON WILL NOT RETRACT. REPLACED WITH SERVICEABLE CALIPER. 1 G 7 2 3U H3EU 1996011900276 19960119 00276 EU 1996 1 19 HEEA966356 1 19960104 G 2810 FTA017522 CELL BOLKMS 105 BO105S 5626006 EU AUX TANK LEAKING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 724MB S756 AFT FUEL CELL LEAKING FUEL. INSTALLED SERVICEABLE FUEL CELL. 1 G 7 2 3U H3EU 1996011900277 19960119 00277 NE 1996 1 19 HEEA966357 1 19960104 G 6210 7615009100041A BLADE SKRSKY S76 S76A 8143006 NE M/R CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2743E 7948 760155 PART IS CRACKED. SPAR CRACK AT THE TIP. THE CRACK STARTED FROM THE OUTER HOLE FOR THE "C" BLOCK BOLT. SCRAPPED M/R BLA DE. 1 G 7 2 3U H1NE 1996011900278 19960119 00278 NE 1996 1 19 HEEA966358 1 19960104 G 6210 7615009100051A BLADE SKRSKY S76 S76A 8143006 NE M/R CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5426U 9252 760167 BLADE IS CRACKED. SPAR CRACKED AT ROOT END. SCRAPPED M/R BLADE. 1 G 7 2 3U H1NE 1996011900279 19960119 00279 NE 1996 1 19 HEEA966359 1 19960104 G 6321 7819712 ARMATURE SKRSKY S76 S76A 8143006 NE ROTOR BRAKE SHORTED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3122G 760232 ARMATURE SHORTED. IT WAS INSTALLED IN ROTOR BRAKE S/N 479. 1 G 7 2 3U H1NE 1996011900280 19960119 00280 1996 1 19 HEEA966360 4 19960104 G 3444 066104800 ALTIMETER KRA405 SKRSKY S76 S76A 8143006 NE COCKPIT RAD ALT ERROR E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 22342 760096 WILL NOT READ OUT CORRECT ALTITUDE. SENT TO THE RADIO SHOP FOR INSPECTION AND REPAIR. 1 G 7 2 3U H1NE 1996011900281 19960119 00281 1996 1 19 HEEA966361 4 19960104 G 3455 066104701 RECEIVER SKRSKY S76 S76A 8143006 NE COCKPIT ADF DEFECTIVE E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 5427S 760168 WILL NOT POINT CORRECTLY IN TEST MODE AND CANNOT ADJUST VOLUME. SENT TO THE RADIO SHOP FOR INSPECTION AND REPAIR. 1 G 7 2 3U H1NE 1996011900282 19960119 00282 1996 1 19 HEEA966362 4 19960105 G 2312 40001278500 TRANSCEIVER RT406 BOLKMS 105 BO105S 5626006 EU COCKPIT VHF DEFECTIVE E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 5418A S800 NO TRANSMIT DEVIATION AND WEAK RECEIVE. 1 G 7 2 3U H3EU 1996011900283 19960119 00283 1996 1 19 HEEA966363 4 19960105 G 3442 MI585202 ANT PEDESTAL BELL 214 214ST 1182106 SW RADAR DEFECTIVE E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 3897N 28106 RADAR DOES NOT PAINT TARGETS. 2 G 7 2 4U H10SW 1996012600208 19960126 00208 1996 1 26 HEEA966364 4 19960105 G 3442 MI5853011 INDICATOR HONEYWELL P500 COCKPIT FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 INDICATOR HAS BLANK DISPLAY. 1996012600209 19960126 00209 SW 1996 1 26 HEEA966365 1 19960105 G 5330 214030325103 DOOR ASSY BELL 214 214ST 1182106 SW TAIL BOOM ACCESS CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3897N 28106 DOOR IS CRACKED. DOOR CRACKED 4.3" FROM EDGE AT AFT L/H BOLT HOLE GOING INBOARD. (THIS DOOR WAS NEW STYLE THICKER DOOR ) REPLACED AS PER ASB 214ST-82-4 DATED 11-19-82 FROM 214-030-325-003 TO 214-030-324-103. COMPLIED WITH TB 214ST-95-144 DATED 3-13-95 AND REPLACED ACCESS DOOR. 2 G 7 2 4U H10SW 1996012600210 19960126 00210 EU 1996 1 26 HEEA966366 1 19960105 G 5210 350A2510842001 HANDLE SNIAS 350 AS350B2 8680813 EU DOOR LATCH ASSY BROKEN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 60951 2771 LOCK PIN HANDLE BROKE OFF. REPLACED LATCH ASSEMBLY. 1 G 7 1 3U H9EU 1996012600211 19960126 00211 1996 1 26 HEEA966367 4 19960105 G 3453 453105004 LORAN ARNAV R501 SKRSKY S76 S76A 8143006 NE COCKPIT DEFECTIVE E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 707AE 760276 ENTER BUTTON INTERMITTENT. SENT TO ARNAV SYSTEMS FOR INSPECTION AND REPAIR. 1 G 7 2 3U H1NE 1996012600212 19960126 00212 SW 1996 1 26 HEEA966368 1 19960105 G 7810 212061201012 EJECTOR ASSY BELL 412 412 1182202 SW RT EXHAUST CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 22608 33075 EJECTOR ASSY EXCESSIVE INTERFERENCE WITH EXHAUST STACK. 1 G 7 2 4U H4SW 1996012600213 19960126 00213 1996 1 26 HEEA966369 4 19960105 G 3457 0110014700 ANTENNA GARMIN BELL 206 206L1 1182107 SW COCKPIT GPS DEFECTIVE E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 5000K 45167 GPS ANTENNA WILL NOT PICK UP SATELLITE. 1 G 7 1 3U H2SW 1996012600214 19960126 00214 1996 1 26 HEEA966370 4 19960105 G 3416 212070238007 INDICATOR BELL 412 412 1182202 SW COCKPIT ERROR E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 3893P 33012 PILOT REPORTED NEEDLE HAS 700 FOOT ERROR 1 G 7 2 4U H4SW 1996012600215 19960126 00215 NE 1996 1 26 HEEA966371 1 19960105 G 6410 7610105101041 BLADE SKRSKY S76 S76A 8143006 NE T/R DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 1546K 9015 760082 HOLE THROUGH THE LEADING EDGE STRIP ON PADDLE "B". 1 G 7 2 3U H1NE 1996012600216 19960126 00216 SW 1996 1 26 HEEA966372 1 19960105 G 6220 412010190103 SPINDLE BELL 412 412 1182202 SW M/R UNBONDED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2148K 5553 36001 BEARING UNBONDED FROM SPINDLE. SENT TO LORD MANUFACTURING FOR INSPECTION AND REPAIR. 1 G 7 2 4U H4SW 1996012600217 19960126 00217 1996 1 26 HEEA966373 4 19960105 G 3452 066106200 TRANSCEIVER KT76 BELL 206 206L3 1182108 SW COCKPIT ATC DEFECTIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6748D 51106 BENCH CHECK NEEDED. INSPECTED UNIT AND FOUND UNIT HAS NO TRANSMIT. FOUND OUTPUT OF MICROPROCESSOR I405 TO BE BAD. REP LACED INTEGRATED CIRCUITS I402 AND I406. REPLACED CAVITY OSCILLATOR V101. REPLACED BROKEN TRANSISTOR Q415 AND INSTALLE D HEATSINKBEHIND TRANSISTOR Q415. REPLACED RESISTOR/CAPACITOR PACK RM401. 1 G 7 1 3U H2SW 1996012600218 19960126 00218 1996 1 26 HEEA966374 4 19960105 G 2312 40001452502 TRANSCEIVER RT138F BOLKMS 117 BK117B2 5626013 EU COCKPIT VHF DEFECTIVE E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 132AE 7238 WEAK TRANSMIT AND RECEIVE. ADJUSTED GUARD RECEIVER CRYSTAL AND ADJUSTED MIC GAIN DEVIATION. REPAIRED PROBLEM. UNIT BEN CH CHECK GOOD. 1 G 7 2 3U NC H13EU 1996012600219 19960126 00219 GL 1996 1 26 HEEA966375 2 19960108 G 7230 23035262 BEARING 23033193 BELL 206 206L3 1182108 SW ALLSN 250C 250C30P 03013 GL COMP NR 1 BRG CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 8589X 364 CAC90854 51487 CAE890024 ENGINE REMOVED DUE TO CRACKED SCROLL. UPON INSPECTION OF COMPRESSOR PARTS NOTED THE FOLLOWING: 2 EACH CRACKS IN SEPERA TOR ON #1 ROLLER BEARING AND WORN TANGS AND TANGSLOTS ON CARBON SEAL ASSEMBLY. NEW PARTS INSTALLED. REFERENCE: AFA#2445 3A. NOTE: SEE MMIR#6376 FOR CARBON SEAL ASSEMBLY. 1 G 7 1 3U 3 U H2SW E1GL 1996012600220 19960126 00220 GL 1996 1 26 HEEA966376 2 19960108 G 7230 23004513 CARBON SEAL 23033193 BELL 206 206L3 1182108 SW ALLSN 250C 250C30P 03013 GL COMPRESSOR WORN TANGS E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 8589X 364 CAC90854 51487 CAE890024 ENGINE REMOVED DUE TO CRACKED SCROLL. UPON INSPECTION OF COMPRESSOR PARTS NOTED THE FOLLOWING: 2 EACH CRACKS IN SEPERA TOR ON #1 ROLLER BEARING AND WORN TANGS AND TANGSLOTS ON CARBON SEAL ASSEMBLY. NEW PARTS INSTALLED.REFERENCE: AFA#24453 A. NOTE: SEE MMIR#6375 FOR #1 ROLLER BEARING. 1 G 7 1 3U 3 U H2SW E1GL 1996012600221 19960126 00221 GL 1996 1 26 HEEA966377 2 19960108 G 7250 6886407 WHEEL 6898735 ALLSN 250C 250C20B 03013 GL 1ST STAGE BLADE DELAM E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 1737 CAT37072 CAE836462 ENGINE REMOVED DUE TO TURBINE OVERHAUL. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: SULFIDATION CAUSING DELA MINATION ON ALL 1ST STAGE WHEEL BLADES AND EROSION OF ALL LEADING EDGES. SCRAPPED 1ST STAGE WHEEL. 3 U E4CE 1996012600222 19960126 00222 1996 1 26 HEEA966378 4 19960109 G 3453 453105004 LORAN ARNAV R501 SKRSKY S76 S76A 8143006 NE COCKPIT DEFECTIVE E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 706AE 760275 LOSES WAYPOINTS WITH POWER OFF AND UNIT UNRELIABLE. 1 G 7 2 3U H1NE 1996012600223 19960126 00223 EU 1996 1 26 HEEA966379 1 19960109 G 6310 4638202007 CLUTCH 4638001004 BOLKMS 105 BO105S 5626006 EU FREEWHEEL DEFECTIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 4294R 177 1328 S860 CLUTCH SLIPPAGE AND SUDDEN ENGAGEMENT. REPLACED WITH SERVICEABLE CLUTCH. 1 G 7 2 3U H3EU 1996012600224 19960126 00224 EU 1996 1 26 HEEA966380 1 19960109 G 3242 AHA1121M0D1234 CALIPER BOLKMS 105 BO105S 5626006 EU CALIPER MALFUNCTION E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 4302G S853 PISTON WILL NOT RETRACT. REPLACED WITH SERVICEABLE CALIPER. 1 G 7 2 3U H3EU 1996012600225 19960126 00225 EU 1996 1 26 HEEA966381 1 19960109 G 6710 SC50811 SERVO CONTROL SNIAS 350 AS350B2 8680813 EU CYCLIC RT/LT BINDING E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 60951 1686 2771 CYCLIC HAS BINDING WHEN THE CYCLIC IS MOVED LEFT AND RIGHT. REPLACED WITH SERVICEABLE SERVO. 1 G 7 1 3U H9EU 1996012600226 19960126 00226 SW 1996 1 26 HEEA966382 1 19960109 G 2432 3055401C BATTERY BELL 206 206L1 1182107 SW DC SYS DEFECTIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2770Y 45291 BATTERY WILL NOT ACCEPT A CHARGE. INSPECTED BY ACCESSORY SHOP AND FOUND THIS BATTERY WAS REMOVED NUMEROUS TIMES FOR BEI NG WEAK. 1 G 7 1 3U H2SW 1996012600227 19960126 00227 NE 1996 1 26 HEEA966383 1 19960109 G 2435 230811011 ARMATURE SKRSKY S76 S76A 8143006 NE START/GEN DEFECTIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 CAUSES UNIT TO DRAW EXCESSIVE AMPS ON SEATER AND ARMATURE SHOWS SIGNS OF MAGNETISM ON GROWLER. . RECEIVED REWOUND ON 10 -20-95. 1 G 7 2 3U H1NE 1996012600228 19960126 00228 SW 1996 1 26 HEEA966384 1 19960109 G 6330 206033506103 RESTRAINT BELL 206 206L 1181522 SW TRANSMISSION BEARING WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 7077B 1439 52037 TRANSMISSION RESTRAINT BEARINGS WORN. 1 G 7 1 3U H2SW 1996012600229 19960126 00229 1996 1 26 HEEA966386 4 19960109 G 3423 C2300DL4B COMPASS MASCO COCKPIT MIS MFG E HEEA K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 BAD FROM STOCK. ONE WIRE IS MISSING. NEEDS TWO WIRES. 1996012600230 19960126 00230 EU 1996 1 26 HEEA966387 1 19960109 G 2434 230321823 STATOR BOLKMS 105 BO105S 5626006 EU DC GEN MIS OHAULED E HEEA K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 STATOR BRUSH LEADS ARE TOO SHORT TO REACH BRUSH BOX SCREWS. RECEIVED REWOUND 3-23-95. 1 G 7 2 3U H3EU 1996012600231 19960126 00231 SW 1996 1 26 HEEA966388 1 19960109 G 7722 35712519129 INDICATOR BELL 206 206L1 1182107 SW COCKPIT TOT READS HIGH E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 10814 45415 INDICATOR READS HIGH AT 700 DEGREES AND ABOVE. 1 G 7 1 3U H2SW 1996012600232 19960126 00232 NE 1996 1 26 HEEA966389 1 19960109 G 2435 230811011 ARMATURE SKRSKY S76 S76A 8143006 NE START/GEN DEFECTIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 INSTALLED ARMATURE IN STARTER GENERATOR AND FOUND ARMATURE CAUSES EXCESSIVE ARCHING. 1 G 7 2 3U H1NE 1996012600233 19960126 00233 1996 1 26 HEEA966390 4 19960109 G 3421 1113034 INDICATOR BELL 412 412 1182202 SW COCKPIT ATTITUDE FLAG STICKS E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 3911L 33023 INDICATOR FLAG STICKS OUT OF VIEW. 1 G 7 2 4U H4SW 1996021300003 19960213 00003 EU 1996 2 13 HEEA966391 1 19960109 G 3340 02471131 SEARCH LIGHT BOLKMS 117 BK117A3 5626015 EU REFLECTOR MIS REPAIRED E HEEA K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 SEARCH LIGHT FOCUS REFLECTOR LOOSE, WILL NOT FOCUS. TIME SINCE REPAIR 0:00. 1 G 7 2 3U H13EU 1996021300004 19960213 00004 1996 2 13 HEEA966392 4 19960109 G 3416 8140BS20LW ALTIMETER COCKPIT MIS REPAIRED E HEEA K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 ENCODING ALTIMETER NEEDLE LOOSE IN CASE WHEN PART RECEIVED FROM REPAIR. 1996012600234 19960126 00234 SW 1996 1 26 HEEA966393 1 19960110 G 2730 214001970107 ACTUATOR ASSY BELL 214 214ST 1182106 SW ELEV SYS FAILED E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 3897N 28106 ACTUATOR ASSY DEFECTIVE. #1 ELEVATOR SYSTEM INOPERATIVE. 2 G 7 2 4U H10SW 1996012600235 19960126 00235 EU 1996 1 26 HEEA966394 1 19960110 G 7712 305731365 INDICATOR SNIAS 350 AS350B2 8680813 EU ENG TORQUE READS LOW E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6097Z 1401 2820 TORQUE IND. READS LOW IN UPPER RANGE. 1 G 7 1 3U H9EU 1996012600236 19960126 00236 SW 1996 1 26 HEEA966395 1 19960110 G 5260 214001426101 BRACKET BELL 214 214ST 1182106 SW STEP ACTUATOR MIS MACHINED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 8045T 28101 BRACKET IS NOT MACHINED PROPERLY. UNABLE TO INSTALL BEARING BETWEEN BRACKET AS REQUIRED. 2 G 7 2 4U H10SW 1996012600237 19960126 00237 1996 1 26 HEEA966396 4 19960110 G 2210 7012409901 PITCH ACTUATOR BOLKMS 117 BK117B1 5626012 EU AUTOPILOT SYS DEFECTIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 117BK 7229 UNIT UNABLE TO TEST AUTO PILOT SYSTEM. 1 G 7 2 3U H13EU 1996012600238 19960126 00238 EU 1996 1 26 HEEA966397 1 19960110 G 7714 1179405603 INDICATOR N1 BOLKMS 117 BK117B1 5626012 EU ENG N1 INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 117BK 7229 N1 INDICATOR INOPERATIVE. NO GAUGE INDICATION ON ENGINE START. 1 G 7 2 3U H13EU 1996012600239 19960126 00239 1996 1 26 HEEA966398 4 19960110 G 3416 10222011886 ALTIMETER BOLKMS 117 BK117B1 5626012 EU COCKPIT INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 117BK 7229 ALTIMETER INOPERATIVE. 1 G 7 2 3U H13EU 1996012600240 19960126 00240 EU 1996 1 26 HEEA966399 1 19960110 G 2432 501122803 BATTERY BOLKMS 117 BK117B1 5626012 EU EMERG POWER INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 117BK 7229 EMERGENCY POWER BATTERY INOPERATIVE. 1 G 7 2 3U H13EU 1996012600241 19960126 00241 EU 1996 1 26 HEEA966400 1 19960110 G 7714 1179405603 INDICATOR BOLKMS 117 BK117B1 5626012 EU ENG N1 INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 117BK 7229 ENGINE N1 INDICATOR INOPERATIVE. 1 G 7 2 3U H13EU 1996012600242 19960126 00242 SW 1996 1 26 HEEA966401 1 19960110 G 6340 214074280107 DETECTOR BELL 412 412 1182202 SW RPM LIMIT DEFECTIVE E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 3893N 54 33010 COULD NOT ADJUST RPM LIMIT DETECTOR. 1 G 7 2 4U H4SW 1996012600243 19960126 00243 SW 1996 1 26 HEEA966402 1 19960110 G 7931 206075677103 INDICATOR BELL 206 206L3 1182108 SW ENGINE OIL READS HIGH E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 8587X 51464 OIL PRESSURE READS TOO HIGH OUT OF TOLERANCE. 1 G 7 1 3U H2SW 1996012600244 19960126 00244 SW 1996 1 26 HEEA966403 1 19960110 G 2840 384178103 SWITCH BELL 412 412 1182202 SW FUEL INDICATION DEFECTIVE E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 22608 33075 SWITCH PIN D NOT GROUNDED TO CASE. CAUSES INDICATOR TO FLUCTUATE. 1 G 7 2 4U H4SW 1996012600245 19960126 00245 NE 1996 1 26 HEEA966404 1 19960110 G 7810 7630507003044 EJECTOR SKRSKY S76 S76A 8143006 NE EXHAUST DEFECTIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 EJECTOR IMPROPER . RETURN TO SERVICE AS PER BATON ROUGE, LA FSDO. 1 G 7 2 3U H1NE 1996012600246 19960126 00246 SW 1996 1 26 HEEA966405 1 19960110 G 2435 230811010 ARMATURE BELL 206 206L1 1182107 SW START/GEN SHORTED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 ARMATURE IS SHORTED AND CAUSING EXCESSIVE ARCHING. RECEIVED REWOUND BY THRUST TECH AVIATION ON 6-7-95. INSTALLED ON AI RCRAFT ON 6-16-95 AND FAILED ON 11-21-95. 1 G 7 1 3U H2SW 1996012600247 19960126 00247 SW 1996 1 26 HEEA966406 1 19960110 G 6710 214001347005 ACTUATOR ROTARY BELL 412 412 1182202 SW CYCLIC DEFECTIVE E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 7128R 36007 ROTARY ACTUATOR CAUSED BINDING IN LATERAL MOVEMENT OF CYCLIC. 1 G 7 2 4U H4SW 1996012600248 19960126 00248 1996 1 26 HEEA966407 4 19960110 G 3421 7660002113103 VERTICAL GYRO SKRSKY S76 S76A 8143006 NE COCKPIT DEFECTIVE E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 1546K 760082 VERT GYRO TUMBLES ADI. 1 G 7 2 3U H1NE 1996012600249 19960126 00249 SW 1996 1 26 HEEA966408 1 19960110 G 7714 412075010109 INDICATOR BELL 412 412 1182202 SW ENG TRIPLE TACH INOPERATIVE E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 2261D 33076 NR1 ENGINE NEEDLE WILL NOT GO TO ZERO; INOPERATIVE. 1 G 7 2 4U H4SW 1996012600250 19960126 00250 SW 1996 1 26 HEEA966409 1 19960110 G 2435 230321827 FIELD ASSY BELL 206 206L1 1182107 SW START/GEN OPEN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 INSTALLED STATOR IN LIMIT. HAD NO VOLTAGE OUTPUT ON TEST. REMOVED AND FOUND STATOR TO HAVE OPEN WINDING, TO SHUNT WIND ING AT A, D & E. 1 G 7 1 3U H2SW 1996012600251 19960126 00251 SW 1996 1 26 HEEA966412 1 19960111 G 3212 214073929105 VALVE BELL 214 214ST 1182106 SW FLOAT LEAKING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 FLOAT VALVE LEAKING OUT OF VENT PORT. 2 G 7 2 4U H10SW 1996012600252 19960126 00252 EU 1996 1 26 HEEA966413 1 19960111 G 5610 706A39821064 SEAL SNIAS 350 AS350B2 8680813 EU SKY WINDOW TORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 60951 2771 SEAL TORN. REPLACED WITH SERVICEABLE SEAL. 1 G 7 1 3U H9EU 1996012600253 19960126 00253 EU 1996 1 26 HEEA966414 1 19960111 G 6720 350A33214501 ROD BEARING SNIAS 350 AS350B2 8680813 EU T/R PITCH WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 60951 2771 BEARING WORN. REPLACED WITH SERVICEABLE T/R P/C LINK. 1 G 7 1 3U H9EU 1996012600254 19960126 00254 EU 1996 1 26 HEEA966415 1 19960111 G 2840 C100U4 SWITCH SNIAS 350 AS350B2 8680813 EU FUEL INDICATING STICKING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 60951 2771 FUEL TANK LIGHT SWITCH STICKS. REPLACED FUEL TANK PUSH BUTTON LIGHT SWITCH DUE TO STICKING. 1 G 7 1 3U H9EU 1996012600255 19960126 00255 EU 1996 1 26 HEEA966416 1 19960111 G 5220 350A25109521 ROD SNIAS 350 AS350B2 8680813 EU JETTISON DOOR DEFECTIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 60951 2771 STRUT WILL NOT HOLD DOOR OPEN. REPLACED DOOR SWITCH. 1 G 7 1 3U H9EU 1996012600256 19960126 00256 EU 1996 1 26 HEEA966417 1 19960111 G 5200 AIR106 HANDLE SNIAS 350 AS350B2 8680813 EU DOOR BROKE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 60951 2771 HANDLE BROKE AND CAME OFF "D" RING. REPLACED WITH SERVICEABLE HANDLE. 1 G 7 1 3U H9EU 1996012600257 19960126 00257 1996 1 26 HEEA966418 4 19960111 G 3422 200DC GYRO COMPASS SNIAS 350 AS350B2 8680813 EU COCKPIT MALFUNCTION E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 6095S 2777 GYRO CYCLES ON/OFF DURING FLIGHT. REPLACED WITH SERVICEABLE GYRO. 1 G 7 1 3U H9EU 1996012600258 19960126 00258 EU 1996 1 26 HEEA966419 1 19960111 G 3340 4580 LAMP SNIAS 350 AS350B2 8680813 EU LANDING LIGHT FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 350BZ 2653 LANDING LIGHT BULB BURNT. REPLACED WITH SERVICEABLE BULB. 1 G 7 1 3U H9EU 1996012600259 19960126 00259 EU 1996 1 26 HEEA966420 1 19960111 G 6520 350A33215300 BEARING 350A33211905 SNIAS 350 AS350B2 8680813 EU T/R HUB WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6100R 236 A21A 2862 LAMINATED HINGE BEARINGS WORN. INSTALLED NEW TAIL ROTOR HUB ASSEMBLY. 1 G 7 1 3U H9EU 1996012600260 19960126 00260 SW 1996 1 26 HEEA966421 1 19960111 G 2840 206063656001 TRANSMITTER BELL 206 206L1 1182107 SW FUEL SYS DEFECTIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 TRANSMITTER HIGH OUT OF TOLERANCE, WILL NOT ADJUST AT FULL SCALE. 1 G 7 1 3U H2SW 1996012600261 19960126 00261 EU 1996 1 26 HEEA966422 1 19960111 G 6720 AC67032 SERVO AEROSP AS355 AS355F1 8680810 EU T/R LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 5797X 1548 5182 LEAKING AT PILOT VALVE AND BOTH ENDS OF CYLINDER ALSO OUT OF TIMING. SENT TO AMERICAN EUROCOPTER CORP. ..THEIR PROPERTY BEING RETURNED. (PHI REQUESTS FOR CREDIT) 1 G 7 2 3U H11EU 1996012600262 19960126 00262 1996 1 26 HEEA966423 4 19960111 G 3420 6220876001 INDICATOR VIR30AGM BEECH 200 200CBEECH 1152926 CE COCKPIT INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 39PH BL3 DEAD NEEDLE; CONTINUOUS FLAG. TIME SINCE REPAIR 4:00. 1 L 7 2 4T A24CE 1996012600263 19960126 00263 EU 1996 1 26 HEEA966424 1 19960111 G 7160 350A54108421 SEAL SNIAS 350 AS350B2 8680813 EU ENG INTAKE TORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 60951 2771 ENGINE AIR INTAKE SEAL TORN. REPLACED WITH SERVICEABLE SEAL. 1 G 7 1 3U H9EU 1996012600264 19960126 00264 SW 1996 1 26 HEEA966427 1 19960112 G 6300 230030535101 ROD END BELL 230 230 1182149 SW M/R BEARING WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 230UN 736 23009 BEARING WORN; TEFLON GONE AND BEARING STARTING TO BECOME GALLED. 1 G 7 2 3U NC H9SW 1996012600265 19960126 00265 SW 1996 1 26 HEEA966428 1 19960112 G 6320 222340057103 CHIP DETECTOR BELL 230 230 1182149 SW TRANSMISSION SHORTED E HEEA K NONE N FALSE WARNING IN INSP/MAINT 1 SW 03 230UN 2588 23009 CHIP PLUG HAS INTERNAL SHORT CAUSING TRANS CHIP LIGHT. 1 G 7 2 3U NC H9SW 1996012600266 19960126 00266 SW 1996 1 26 HEEA966429 1 19960112 G 6710 206062721105 ACTUATOR BELL 230 230 1182149 SW M/R INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 230UN 473 23009 ACTUATOR INTERMITTENTLY INOPERATIVE. 1 G 7 2 3U NC H9SW 1996012600267 19960126 00267 SW 1996 1 26 HEEA966430 1 19960112 G 7600 222060790101 BELLCRANK ASSY BELL 230 230 1182149 SW ENG CONTROL BEARING WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 230UN 2731 23009 BELLCRANK BEARING WORN. 1 G 7 2 3U NC H9SW 1996012600268 19960126 00268 NE 1996 1 26 HEEA966431 1 19960112 G 6210 7615009100051 BLADE SKRSKY S76 S76A 8143006 NE M/R CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 1547D 11742 760077 PART IS CRACKED. BLADE IS DUE FOR TIME EXTENSION AND ALSO HAS SEPARATION ON THE TITANIUM LEADING EDGE STRIP WITH A CHOR DWISE CRACK NEAR THE INBOARD END OF THE NICKEL STRIP. 1 G 7 2 3U H1NE 1996012600269 19960126 00269 1996 1 26 HEEA966432 4 19960112 G 2312 071121525 CONTROL UNIT SKRSKY S76 S76A 8143006 NE COCKPIT DEFECTIVE E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 707AE 760276 CONTROL UNIT HAS CONSTANT STATIC. REPLACED FADED DISPLAY LENS, INTERMITTENT S102 TRANSFER SWITCH. ALSO REPLACED HEADER P201 AND APPLIED HUMISEAL FOR HEADER MODIFICATION. INSPECTED AND UNIT BENCH CHECK GOOD. 1 G 7 2 3U H1NE 1996012600270 19960126 00270 1996 1 26 HEEA966433 4 19960112 G 2312 4000103000 TRANSCEIVER WULFSBERG RT450 COCKPIT INTERMITTENT E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 TRANSMIT POWER INTERMITTENT. TROUBLESHOT AND REPLACED C1 CAPACITOR, C2 CAPACITOR, C7 CAPACITOR, C8 CAPACITOR, CR1 DIODE . REPAIRED INTERMITTENT TRANSMIT PROBLEM. BENCH CHECK GOOD. 1996012600271 19960126 00271 1996 1 26 HEEA966434 4 19960112 G 2312 4000106010 CONTROL UNIT C10 BOLKMS 117 BK117A3 5626015 EU COCKPIT DEFECTIVE E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 911NC 7026 NOT ALL PL TONES MATCH THUMBWHEEL TO DIGITAL READOUT. TROUBLESHOT AND REPLACED 8 EACH CRIMP CONNECTOR SOCKETS. REPAIRED . BENCH CHECK GOOD. 1 G 7 2 3U H13EU 1996012600272 19960126 00272 1996 1 26 HEEA966435 4 19960112 G 3444 066106103 RADAR ALTIMETER BOLKMS 105 BO105S 5626006 EU COCKPIT MALFUNCTION E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 7171A S838 NEEDLE STAYS ABOVE 50 FEET. DOESN'T MOVE AFTER PRESSING BUTTON. SENT TO THE RADIO SHOP FOR INSPECTION AND REPAIR. 1 G 7 2 3U H3EU 1996012600273 19960126 00273 1996 1 26 HEEA966436 4 19960112 G 3453 4530093 RECEIVER ARNAV20 BELL 206 206L3 1182108 SW COCKPIT DEFECTIVE E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 31077 51520 "O" BUTTON DOES NOT ILLUMINATE, "ENT" BUTTON HAS TO BE PRESSED VERY HARD AND SEVERAL TIMES TO FUNCTION. 1 G 7 1 3U H2SW 1996012600274 19960126 00274 SW 1996 1 26 HEEA966437 1 19960112 G 2435 36B510954G2 CLUTCH BELL 214 214ST 1182106 SW START/GEN SLIPPAGE E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 FAILS CLUTCH SLIPPAGE TEST. IT WAS TESTED AS RECEIVED BY ACCESSORY OVERHAUL SHOP AND SLIPPED AT 195 INCH POUNDS. TEST SPECS - 325 TO 375 INCH POUNDS. ALSO END PLAY IS AT MAX .010 TEST-SPECS .004-.010. 2 G 7 2 4U H10SW 1996012600275 19960126 00275 1996 1 26 HEEA966438 4 19960112 G 2370 9806019001 CVR SKRSKY S76 S76A 8143006 NE COCKPIT INOPERATIVE E HEEA K NONE L NO TEST NR NOT REPORTED 1 SW 03 3122H 2633 760233 CVR WILL NOT TEST OR WORK. 1 G 7 2 3U H1NE 1996012600276 19960126 00276 NE 1996 1 26 HEEA966439 1 19960112 G 6210 7615009043051 TIP CAP SKRSKY S76 S76A 8143006 NE M/R MIS REPAIRED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 TIP CAP WAS REPAIRED AT CTI 12-11-95. THE TIP CAP DOES NOT FIT. THE TOP LEADING EDGE HOLE DOES NOT LINE UP AND THE AB RASION STRIP IS NOT STRAIGHT, PREVENTING THE TIP CAP TO FIT PROPERLY, ALSO THERE IS AN EXCESSIVE AMOUNT OF HYSOL EA9309. 3NABETWEEN THE TOP INSIDE DOUBLER AND THE SKIN OF THE TIP CAP. SENT TO COMPOSITE TECHNICS FOR WARRANTY REPAIR. 1 G 7 2 3U H1NE 1996020200323 19960202 00323 NE 1996 2 2 HEEA966440 1 19960115 G 6320 7635109023101 LINER SKRSKY S76 S76A 8143006 NE M/R GR BOX MIS MFG E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 LINER FOUND TO BE OBLONG MIC READING 6.232 AND 6.2155. MISMANUFACTURED - LINER IS OUT OF ROUND. 1 G 7 2 3U H1NE 1996020200324 19960202 00324 EU 1996 2 2 HEEA966441 1 19960115 G 6321 350A32050002 BRAKE ASSY SNIAS 350 AS350B2 8680813 EU ROTOR WORN EXCESSIVELY E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 60951 1525 2771 BRAKE ASSY IS WORN EXCESSIVELY. BRAKE PAD IS WORN. 1 G 7 1 3U H9EU 1996020200325 19960202 00325 EU 1996 2 2 HEEA966442 1 19960115 G 6220 827S115X140X12FP SHAFT SEAL 105141081 BOLKMS 105 BO105S 5626006 EU M/R LEAKING E HEEA K NONE K FLUID LOSS CR CRUISE 1 SW 03 4391S 2 050081 S787 SHAFT SEAL LEAKING IN FLIGHT. NO STATIC LEAK. 1 G 7 2 3U H3EU 1996020200326 19960202 00326 EU 1996 2 2 HEEA966443 1 19960115 G 7160 350A54108004 INTAKE AIR SNIAS 350 AS350B2 8680813 EU ENGINE CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6100R 499 2862 AIR INTAKE IS CRACKED. 1 G 7 1 3U H9EU 1996020200327 19960202 00327 SW 1996 2 2 HEEA966444 1 19960115 G 5302 206031329101 FITTING BELL 206 206L1 1182107 SW TAILBOOM CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2759U 45267 L/H FITTING CRACKED IN THREE PIECES. REPLACED FITTING WITH NEW . 1 G 7 1 3U H2SW 1996020200328 19960202 00328 SW 1996 2 2 HEEA966445 1 19960115 G 5302 206031329101 FITTING BELL 206 206L1 1182107 SW TAILBOOM CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5745N 45489 L/H UPPER FITTING CRACKED AROUND RIVETS. REPLACED WITH SERVICEABLE FITTING. 1 G 7 1 3U H2SW 1996020200329 19960202 00329 SW 1996 2 2 HEEA966446 1 19960115 G 5320 205030710008 FITTING BELL 212 212 1181420 SW FUSELAGE CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 27805 14148 31106 PART IS CRACKED. ANGLE CRACKED IN HALF DUE TO FASTENER HOLES NOT DEBURRED. REMOVED AND REPLACED ANGLE WITH SHIMS NEEDED AND PROPER HARDWARE. DEBURR HOLES AT ALL LOCATIONS OF FASTENERS. 1 G 7 1 4U H4SW 1996020200330 19960202 00330 1996 2 2 HEEA966447 4 19960115 G 3444 066304400 ALTIMETER LIGHT BELL 412 412 1182202 SW RADAR ALT DEFECTIVE E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 3893P 33012 DH LIGHT INOPERATIVE. 1 G 7 2 4U H4SW 1996020200331 19960202 00331 EU 1996 2 2 HEEA966448 1 19960115 G 7400 355A72302300 SENSOR ASSY AEROSP AS355 AS355F1 8680810 EU ALLSN 250C 250C20F 03013 GL AUTO RELIGHT MALFUNCTION E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 5796S 5164 AUTO RELIGHT COMES ON IN FLIGHT. REPLACED WITH SERVICEABLE TRANSDUCER. 1 G 7 2 3U 3 U H11EU E4CE 1996020200332 19960202 00332 NE 1996 2 2 HEEA966449 2 19960115 G 7210 3024780 GEARBOX BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE COMBINING FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2298Z 18020 33077 COMBINING GEAR BOX IS TRANSFERRING OIL TO BOTH ENGINES, 1 QUART OIL PER 4 FLIGH T HOURS. 1 G 7 2 4U 4 U H4SW E22EA 1996020200333 19960202 00333 1996 2 2 HEEA966450 4 19960115 G 3416 54025100034 ALERTER COCKPIT MALFUNCTION E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 ALERT LIGHT ON UNIT AND ON ALL ALTIMETERS, FLASHES ON THEN GOES OUT AT 1000 FEET BEFORE DESIRED ALTITUDE. AT 750 FEET BEFORE DESIRED ALTITUDE LIGHTS COME ON AND FUNCTIONS NORMALLY. UNIT CHECKED AT SEVERAL ALTITUDE SETTINGS IN CLIMB AND DESCENT AND FUNCTIONED THE SAME. 1996020200334 19960202 00334 EU 1996 2 2 HEEA966451 1 19960115 G 2121 420800001 BLOWER SNIAS 350 AS350B2 8680813 EU AIR DIST FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 350BZ 254 2653 BROKEN FAN CAUSED MOTOR TO BURN UP. 1 G 7 1 3U H9EU 1996020200335 19960202 00335 NE 1996 2 2 HEEA966452 2 19960115 G 7320 6038T62P24 HMU BELL 214 214ST 1182106 SW GE CT7TS CT72A 30030 NE THROTTLE MALFUNCTION E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3897N 28106 BINDING THROTTLE NEAR IDLE CUT OFF. 2 G 7 2 4U 4 U H10SW E8NE 1996020200336 19960202 00336 1996 2 2 HEEA966453 4 19960115 G 3444 6223201001 ALTIMETER KING A COCKPIT ERRATIC E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 39PH BL3 RADIO ALTIMETER ERRATIC ALTITUDE READOUT. 1996020200337 19960202 00337 NE 1996 2 2 HEEA966454 1 19960115 G 3610 7650007903102 VALVE SKRSKY S76 S76A 8143006 NE BLEED SOV INOPERATIVE E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 31219 8627 760230 BLEED SOV SOLENOID INOPERATIVE. 1 G 7 2 3U H1NE 1996020200338 19960202 00338 NE 1996 2 2 HEEA966455 1 19960115 G 3230 7665001801103 BOTTLE SKRSKY S76 S76A 8143006 NE GEAR BLOW DOWN LEAKING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 792CH 148 760193 BOTTLE LEAKING THROUGH HEAD VALVE ASSEMBLY. 1 G 7 2 3U H1NE 1996020200339 19960202 00339 SW 1996 2 2 HEEA966456 1 19960115 G 6240 214074280105 DETECTOR BELL 214 214ST 1182106 SW LOW RPM WARN DEFECTIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5748M 539 28102 LOW RPM LIGHT INOPERATIVE. 2 G 7 2 4U H10SW 1996020200340 19960202 00340 SW 1996 2 2 HEEA966457 1 19960115 G 2824 L88010501 VALVE BELL 412 412 1182202 SW FUEL SYS INOPERATIVE E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 2258F 33073 VALVE INOPERATIVE. 1 G 7 2 4U H4SW 1996020200341 19960202 00341 EU 1996 2 2 HEEA966459 1 19960115 G 7110 TL100AXE12L55 FASTENER SNIAS 350 AS350B2 8680813 EU COWL EXCESS WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 60951 2771 FASTENER IS WORN EXCESSIVELY. HINGE WORN AND LATCH HOOK WORN. REPLACED WITH SERVICEABLE LATCH ASSEMBLY. 1 G 7 1 3U H9EU 1996020200342 19960202 00342 EU 1996 2 2 HEEA966460 1 19960115 G 6330 704A33633151 BEARING SNIAS 350 AS350B2 8680813 EU M/R XMSN SEPARATED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 60951 1995 2771 DURING 2000 HOUR INSPECTION FOUND BEARING SEPARATED. REPLACED WITH SERVICEABLE BEARING. 1 G 7 1 3U H9EU 1996020200343 19960202 00343 EU 1996 2 2 HEEA966461 1 19960115 G 3213 350A41104620 SHOE SNIAS 350 AS350B2 8680813 EU RT FWD SKID EXCESS WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 60951 2771 FOUND RIGHT FORWARD SKID SHOE WORN THROUGH. REPLACED WORN SHOE 1 G 7 1 3U H9EU 1996020900089 19960209 00089 SW 1996 2 9 HEEA966464 1 19960115 G 5610 M2063401 WINDSHIELD BELL 206 206L1 1182107 SW COCKPIT LT MIS MFG E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 1077A 45382 WINDSHIELD IS MANUFACTURED TOO SMALL TO PROPERLY FIT WINDSHIELD FRAME. 1 G 7 1 3U H2SW 1996020900090 19960209 00090 SW 1996 2 9 HEEA966465 1 19960116 G 6240 214175233101 SENSOR BELL 230 230 1182149 SW M/R RPM DEFECTIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 230UN 2617 23009 MAIN ROTOR NEEDLE ON TRIPLE TACH IS ERRATIC. 1 G 7 2 3U NC H9SW 1996020900091 19960209 00091 SW 1996 2 9 HEEA966466 1 19960116 G 2150 230325003101 HOSE BELL 230 230 1182149 SW AIR COND TORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 230UN 2582 23009 AIRCONDITION RETURN VENT HOSE TORN AND COLLAPSED. SCRAPPED IN FIELD. 1 G 7 2 3U NC H9SW 1996020900092 19960209 00092 SW 1996 2 9 HEEA966467 1 19960116 G 6420 222012714001 BEARING BELL 230 230 1182149 SW T/R WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 230UN 2588 23009 T/R BEARING RACE WORN. 1 G 7 2 3U NC H9SW 1996020900093 19960209 00093 1996 2 9 HEEA966468 4 19960116 G 2312 069102409 TRANSCEIVER KX155 COCKPIT INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 TRANSCEIVER INOPERATIVE. UNIT BURNT AND SPACER MISSING ON REAR OF CHASSIS AND AUDIO BOARD. 1996020900094 19960209 00094 1996 2 9 HEEA966469 4 19960116 G 2312 064102300 TRANSCIEVER BELL 214 214ST 1182106 SW COCKPIT VHF LOW POWER E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 8045T 28101 TRANSCEIVER LOW OUTPUT POWER. REPLACED TRANSISTORS Q109 AND 110. REPAIRED. INSTALLED MOD 2. REPLACED HEADER J304 AND APPLIED HUMISEAL TO HEADER. REPLACED TRANSMIT HEATSINK DUE TO SCREW BEING BROKEN IN HOLE. FOUND FREQUENCY UNABLE TO AD JUST TO SPECS. REPLACED CRYSTAL Y101.REPAIRED. ADJUSTED C/SQUELCH AND SIDETONE. BENCH CHECK GOOD. 2 G 7 2 4U H10SW 1996020900095 19960209 00095 1996 2 9 HEEA966470 4 19960116 G 3455 066107200 RECEIVER KR87 BELL 206 206L3 1182108 SW COCKPIT ADF DEFECTIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6748D 51106 BENCH CHECK NEEDED. INSPECTED AND TESTED. FOUND HOLE STRIPPED IN HEATSINK. REPLACED HEATSINK. REPAIRED. REPLACED DIS PLAY DUE TO INOPERATIVE SEGMENTS. REPAIRED. APPLIED DOW CORNING #4 COMPOUND TO DISPLAY. BENCH CHECK GOOD. 1 G 7 1 3U H2SW 1996020900096 19960209 00096 1996 2 9 HEEA966471 4 19960116 G 3452 066106200 TRANSCEIVER KT76 BELL 206 206L3 1182108 SW COCKPIT ATC DEFECTIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 32041 51539 2 YEAR INSPECTION DUE. REPLACED WEAK V101 CAVITY OSCILLATOR. ADJUSTED FREQUENCY. BENCH CHECK GOOD. 1 G 7 1 3U H2SW 1996020900097 19960209 00097 1996 2 9 HEEA966472 4 19960116 G 3453 4530103 RECEIVER ARNAV21 BELL 206 206B 1181511 SW COCKPIT LORAN DEFECTIVE E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 2275Q 3625 DISPLAYS "OSCILLATOR ERROR". 1 G 7 1 3U H2SW 1996020900098 19960209 00098 1996 2 9 HEEA966473 4 19960116 G 3421 1113034 INDICATOR BELL 214 214ST 1182106 SW COCKPIT ATTITUDE DEFECTIVE E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 3897N 28106 ATTITUDE GYRO WILL NOT ERECT. 2 G 7 2 4U H10SW 1996020900099 19960209 00099 SW 1996 2 9 HEEA966474 1 19960116 G 7714 412075010109 INDICATOR BELL 412 412 1182202 SW TRIPLE TACH NEEDLE SPLIT E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 22608 33075 #1 AND #2 NEEDLES HAVE A 3% SPLIT. SENT TO AIR DALLAS INSTRUMENTS FOR WARRANTY REPAIR. TIME SINCE REPAIR 17:00. 1 G 7 2 4U H4SW 1996020900100 19960209 00100 SW 1996 2 9 HEEA966476 1 19960116 G 2436 206075447007 REGULATOR BELL 206 206L3 1182108 SW DC SYS DEFECTIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3108E 51498 VOLTAGE REGULATOR WOULD NOT HOLD VOLTAGE SETTING. 1 G 7 1 3U H2SW 1996020900101 19960209 00101 GL 1996 2 9 HEEA966477 2 19960119 G 7230 23031922 SHAFT 6890550 BOLKMS 105 BO105S 5626006 EU ALLSN 250C 250C20B 03013 GL COMPRESSOR FRETTED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 967MB 54 CAC40338 S737 CAE835381 ENGINE REMOVED DUE TO METAL IN OIL. UPON INSPECTION OF COMPRESSOR PARTS NOTED THE FOLLOWING: 1) FRETTING ON SPUR ADPAT ER GEARSHAFT DUE TO RETAINING RING NOT IN SPLINE ADAPTER GROOVE AND GROOVED NR 2 1/2 BEARING INNER RACE O.D. 2) EXCESSI VE WEAR ON SPLINE ADAPTER RETAINING RING GROOVE. 3) SPIRAL LOCK RING BECOMING DISLODGED IN SPLINE ADAPTER AND CAUSING M ETAL IN OIL. 4) GROOVED AND DENTED ROLLERS IN NR 2 1/2 BEARING. NOTE: NR 2 1/2 BEARING INNER RACE REMOVED FROM SPUR AD APTER GEARSHAFT AND SENT WITH OTHER PARTS AND N1 COUPLING BEING SENT FOR INSPECTION AS N1 SHAFTING SET. SEE MMIR'S NR 6 477 THROUGH NR 6481 FOR ADDITIONAL PARTS REPLACED. 1 G 7 2 3U 3 U H3EU E4CE 1996020900102 19960209 00102 GL 1996 2 9 HEEA966478 2 19960119 G 7230 23039791 SPLINE ADAPTER 6890550 BOLKMS 105 BO105S 5626006 EU ALLSN 250C 250C20B 03013 GL COMPRESSOR FRETTING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 967MB 54 CAC40338 S737 CAE835381 ENGINE REMOVED DUE TO METAL IN OIL. UPON INSPECTION OF COMPRESSOR PARTS NOTED THE FOLLOWING: 1) FRETTING ON SPUR ADPAT ER GEARSHAFT DUE TO RETAINING RING NOT IN SPLINE ADAPTER GROOVE AND GROOVED NR 2 1/2 BEARING INNER RACE O.D. 2) EXCESSI VE WEAR ON SPLINE ADAPTER RETAINING RING GROOVE. 3) SPIRAL LOCK RING BECOMING DISLODGED IN SPLINE ADAPTER AND CAUSING M ETAL IN OIL. 4) GROOVED AND DENTED ROLLERS IN NR 2 1/2 BEARING. NOTE: NR 2 1/2 BEARING INNER RACE REMOVED FROM SPUR AD APTER GEARSHAFT AND SENT WITH OTHER PARTS AND N1 COUPLING BEING SENT FOR INSPECTION AS N1 SHAFTING SET. SEE MMIR'S NR 64 77 THROUGH NR 6481 FOR ADDITIONAL PARTS REPLACED. 1 G 7 2 3U 3 U H3EU E4CE 1996020900103 19960209 00103 GL 1996 2 9 HEEA966479 2 19960119 G 7230 672665690 SPIRAL LOCK RING 6890550 BOLKMS 105 BO105S 5626006 EU ALLSN 250C 250C20B 03013 GL COMPRESSOR DISLODGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 967MB 54 CAC40338 S737 CAE835381 ENGINE REMOVED DUE TO METAL IN OIL. UPON INSPECTION OF COMPRESSOR PARTS NOTED THE FOLLOWING: 1) FRETTING ON SPUR ADPAT ER GEARSHAFT DUE TO RETAINING RING NOT IN SPLINE ADAPTER GROOVE AND GROOVED NR 2 1/2 BEARING INNER RACE O.D. 2) EXCESSI VE WEAR ON SPLINE ADAPTER RETAINING RING GROOVE. 3) SPIRAL LOCK RING BECOMING DISLODGED IN SPLINE ADAPTER AND CAUSING M ETAL IN OIL. 4) GROOVED AND DENTED ROLLERS IN NR 2 1/2 BEARING. NOTE: NR 2 1/2 BEARING INNER RACE REMOVED FROM SPUR AD APTER GEARSHAFT AND SENT WITH OTHER PARTS AND N1 COUPLING BEING SENT FOR INSPECTION AS N1 SHAFTING SET. SEE MMIR'S NR 64 77 THROUGH NR 6481 FOR ADDITIONAL PARTS REPLACED. 1 G 7 2 3U 3 U H3EU E4CE 1996020900104 19960209 00104 GL 1996 2 9 HEEA966480 2 19960119 G 7230 23034787 BEARING 6890550 BOLKMS 105 BO105S 5626006 EU ALLSN 250C 250C20B 03013 GL COMPRESSOR 2.5 DEFECTIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 967MB 54 CAC40338 S737 CAE835381 ENGINE REMOVED DUE TO METAL IN OIL. UPON INSPECTION OF COMPRESSOR PARTS NOTED THE FOLLOWING: 1) FRETTING ON SPUR ADPAT ER GEARSHAFT DUE TO RETAINING RING NOT IN SPLINE ADAPTER GROOVE AND GROOVED NR 2 1/2 BEARING INNER RACE O.D. 2) EXCESSI VE WEAR ON SPLINE ADAPTER RETAINING RING GROOVE. 3) SPIRAL LOCK RING BECOMING DISLODGED IN SPLINE ADAPTER AND CAUSING M ETAL IN OIL. 4) GROOVED AND DENTED ROLLERS IN NR 2 1/2 BEARING. NOTE: NR 2 1/2 BEARING INNER RACE REMOVED FROM SPUR AD APTER GEARSHAFT AND SENT WITH OTHER PARTS AND N1 COUPLING BEING SENT FOR INSPECTION AS N1 SHAFTING SET. SEE MMIR'S NR 64 77 THROUGH NR 6481 FOR ADDITIONAL PARTS REPLACED. 1 G 7 2 3U 3 U H3EU E4CE 1996020900105 19960209 00105 GL 1996 2 9 HEEA966481 2 19960119 G 7230 6898977 COUPLING 6898735 BOLKMS 105 BO105S 5626006 EU ALLSN 250C 250C20B 03013 GL COMPRESSOR DEFECTIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 967MB 54 CAT40070 S737 CAE835381 ENGINE REMOVED DUE TO METAL IN OIL. UPON INSPECTION OF COMPRESSOR PARTS NOTED THE FOLLOWING: 1) FRETTING ON SPUR ADPAT ER GEARSHAFT DUE TO RETAINING RING NOT IN SPLINE ADAPTER GROOVE AND GROOVED NR 2 1/2 BEARING INNER RACE O.D. 2) EXCESSI VE WEAR ON SPLINE ADAPTER RETAINING RING GROOVE. 3) SPIRAL LOCK RING BECOMING DISLODGED IN SPLINE ADAPTER AND CAUSING M ETAL IN OIL. 4) GROOVED AND DENTED ROLLERS IN NR 2 1/2 BEARING. NOTE: NR 2 1/2 BEARING INNER RACE REMOVED FROM SPUR AD APTER GEARSHAFT AND SENT WITH OTHER PARTS AND N1 COUPLING BEING SENT FOR INSPECTION AS N1 SHAFTING SET. SEE MMIR'S NR 64 77 THROUGH NR 6481 FOR ADDITIONAL PARTS REPLACED. 1 G 7 2 3U 3 U H3EU E4CE 1996020900106 19960209 00106 GL 1996 2 9 HEEA966482 2 19960119 G 7210 6876925A TUBE ASSY 6894171 BOLKMS 105 BO105S 5626006 EU ALLSN 250C 250C20B 03013 GL ENG GR BOX LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 5421E 7173 CAG39055 S806 CAE270055 ENGINE REMOVED DUE TO OIL LEAKING AT GEARBOX SPLIT LINE. UPON INSPECTION OF GEARBOX PARTS NOTED THE FOLLOWING: OIL TRA NSFER TUBE FAILED DIMENSIONAL CHECK IN ACCORDANCE WITH CEB1307. INSTALLED A NEW OIL TUBE ASSY. 1 G 7 2 3U 3 U H3EU E4CE 1996020900107 19960209 00107 SW 1996 2 9 HEEA966483 1 19960119 G 5302 206031329003 FITTING BELL 206 206L1 1182107 SW TAILBOOM CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 1076T 45373 UPPER L/H TAILBOOM FITTING CRACKED. 1 G 7 1 3U H2SW 1996020900108 19960209 00108 EU 1996 2 9 HEEA966484 1 19960119 G 6320 1171261201 BEARING 1171200501 BOLKMS 117 BK117B1 5626012 EU M/R GR BOX SPALLED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2313 KA0474 BEARING INNER RACE, ROLLERS AND OUTER RACE SPALLING EXCESSIVELY. 1 G 7 2 3U H13EU 1996020900109 19960209 00109 SW 1996 2 9 HEEA966485 1 19960119 G 6240 206075681105 INDICATOR BELL 206 206L3 1182108 SW DUAL TACH DEFECTIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 363BH 51345 INDICATOR GLASS FOGGED UP. 1 G 7 1 3U H2SW 1996020900110 19960209 00110 1996 2 9 HEEA966486 4 19960119 G 3454 066107810 RECEIVER KNR634A SKRSKY S76 S76A 8143006 NE COCKPIT NAV DEFECTIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 89H 205 760406 NAV RECEIVER BAD FROM STOCK. BLUE LIGHT STAYS ON MARKER BEACON INDICATOR. TIME SINCE REPAIR 0:00. 1 G 7 2 3U H1NE 1996020900111 19960209 00111 EU 1996 2 9 HEEA966487 1 19960119 G 6520 350A33200403 SPIDER SNIAS 350 AS350B2 8680813 EU T/R BOOT LOOSE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 60951 1248 2771 DUST BOOT P/N 350A33-2069-20 COMING LOOSE FROM SPIDER ASSY AND SLIDING ON SHAFT. 1 G 7 1 3U H9EU 1996020900112 19960209 00112 EU 1996 2 9 HEEA966488 1 19960119 G 2610 0301037070 HARNESS SNIAS 350 AS350B2 8680813 EU FIRE DETECTOR B NUT LOOSE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 60951 2771 B-NUT UNBONDED FROM HARNESS. 1 G 7 1 3U H9EU 1996020900113 19960209 00113 1996 2 9 HEEA966489 4 19960119 G 2210 7690001802106 ACTUATOR SKRSKY S76 S76A 8143006 NE AFCS DEFECTIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 31219 2607 760230 #1 ROLL CHATTERS. INSPECTED BY ACCESSORY OVERHAUL SHOP AND FOUND TEST POINT E.4 OUT OF CALIBRATION. 1 G 7 2 3U H1NE 1996020900114 19960209 00114 GL 1996 2 9 HEEA966490 2 19960119 G 7314 D10731812A PUMP ALLSN 250C 250C20B 03013 GL STATOR DEFECTIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 STATOR INSULATION COVERING WINDINGS HANGS OVER LIP OF HOUSING AND CANNOT BE ASSEMBLED ON PUMP. 3 U E4CE 1996020900115 19960209 00115 SW 1996 2 9 HEEA966491 1 19960119 G 5320 206033100261 SHELL ASSY BELL 206 206L1 1182107 SW FUSELAGE MIS MFG E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 10814 45415 TRANSITION AREA ALONG AFT EDGE MISALIGNED. RECESS FOR FUEL CROSS OVER LINE NOT CENTERED ON SHELL ASSY. 1 G 7 1 3U H2SW 1996020900116 19960209 00116 NE 1996 2 9 HEEA966492 1 19960119 G 6210 7615009043050 TIP CAP SKRSKY S76 S76A 8143006 NE M/R CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 1545K 760047 TIP CAP HAS INTERNAL DOUBLER SEPARATED BEYOND LIMITS AND LEADING EDGE ABRASION STRIP CRACKED AND SEPARATED. 1 G 7 2 3U H1NE 1996020900117 19960209 00117 EU 1996 2 9 HEEA966493 1 19960119 G 6240 10594564 INDICATOR BOLKMS 105 BO105S 5626006 EU MAST MOMENT INOPERATIVE E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 6607K S841 MAST MOMENT SYSTEM INOPERATIVE. BLOWS FUSES. 1 G 7 2 3U H3EU 1996020900118 19960209 00118 EU 1996 2 9 HEEA966494 1 19960119 G 6240 10594575 TRANSMITTER BOLKMS 105 BO105S 5626006 EU MAST MOMENT DEFECTIVE E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 6607K S841 MAST MOMENT SYSTEM INOPERATIVE. BLOWS FUSES. 1 G 7 2 3U H3EU 1996020900119 19960209 00119 SW 1996 2 9 HEEA966495 1 19960119 G 7712 412075008111 INDICATOR BELL 412 412 1182202 SW COCKPIT TORQUE DEFECTIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3893P 33012 #2 NEEDLE INTERMITTENTLY STICKS AT 0 AND 38%. 1 G 7 2 4U H4SW 1996020900120 19960209 00120 SW 1996 2 9 HEEA966496 1 19960119 G 6220 412010124109 BOLT 412010100151 BELL 412 412 1182202 SW M/R FLAKING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 108X 1183 AAD00032 33115 TUNGSTEN CARBIDE COATING FLAKING OFF. 1 G 7 2 4U H4SW 1996020900121 19960209 00121 SW 1996 2 9 HEEA966497 1 19960119 G 6220 412010124109 BOLT 412010100151 BELL 412 412 1182202 SW M/R COAT FLAKE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 108X 1183 AAD00032 33115 BOLT TUNGSTEN CARBIDE COATING FLAKING OFF. S/N A732, A50 AND A716 1 G 7 2 4U H4SW 1996020900122 19960209 00122 SW 1996 2 9 HEEA966498 1 19960119 G 6220 412010124109 BOLT 412010100151 BELL 412 412 1182202 SW M/R FLAKING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 108X 1183 AAD00032 33115 BOLT TUNGSTEN CARBIDE COATING FLAKING OFF. S/N A726 & A750 1 G 7 2 4U H4SW 1996020900123 19960209 00123 SW 1996 2 9 HEEA966499 1 19960119 G 6420 214011801117 HUB BELL 214 214ST 1182106 SW T/R WONT BALANCE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 8045T 431 28101 INSPECT AND REPAIR DUE TO UNABLE TO BALANCE. 2 G 7 2 4U H10SW 1996020900124 19960209 00124 SW 1996 2 9 HEEA966500 1 19960123 G 3340 214175127103 POWER SUPPLY BELL 214 214ST 1182106 SW DC SYS INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5748M 28102 POWER SUPPLY INOPERATIVE. 2 G 7 2 4U H10SW 1996020900125 19960209 00125 SW 1996 2 9 HEEA966501 1 19960123 G 7120 230322452 PLATE BELL 206 206L1 1182107 SW MOUNT CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 10814 45415 MOUNTING PLATE CORRODED. (CORROSION ON CLAMP FLANGE) REPLACED WITH SERVICEABLE MOUNTING PLATE. 1 G 7 1 3U H2SW 1996020900126 19960209 00126 1996 2 9 HEEA966502 4 19960123 G 3452 066106200 TRANSCEIVER KT76 BELL 206 206B 1181511 SW COCKPIT ATC WEAK E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 2277A 3630 NO RECEPTION BY TOWER. REPLACED WEAK V101 CAVITY OSCILLATOR. ADJUSTED FREQUENCY. BENCH CHECK GOOD. 1 G 7 1 3U H2SW 1996020900590 19960209 00590 1996 2 9 HEEA966503 4 19960123 G 3444 066104800 ALTIMETER KRA405 BELL 214 214ST 1182106 SW COCKPIT RAD ALT INOPERATIVE E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 3897N 28106 RADAR ALTIMETER INOPERATIVE. PERFORMED COMPLETE CALIBRATION AND ALIGNMENT. REPLACED RESISTORS R518, R519, R534 AND R260 TO INCORPORATE MOD 10. BENCH CHECK GOOD. 2 G 7 2 4U H10SW 1996020900591 19960209 00591 1996 2 9 HEEA966504 4 19960123 G 3444 066104800 ALTIMETER KRA405 BELL 412 412 1182202 SW COCKPIT RAD ALT DEFECTIVE E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 2149S 36002 GIVES INCORRECT ALTITUDE. PERFORMED COMPLETE CALIBRATION AND ALIGNMENT. REPAIRED. REPLACED RESISTORS R518,R519,R534 AN D R260 TO INCORPORATE MOD 10. BENCH CHECK GOOD. 1 G 7 2 4U H4SW 1996020900592 19960209 00592 1996 2 9 HEEA966505 4 19960123 G 3452 066106200 TRANSCEIVER KT76 BELL 206 206L1 1182107 SW COCKPIT ATC MALFUNCTION E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 50046 45173 TRANSCEIVER MUST BE RECYCLED ON FIRST FLIGHT TO SEND SIGNAL, WORKS FINE THE REST OF THE DAY. REPLACED PHOTOCELL V301 DUE TO WEAK REPLY LIGHT. REPAIRED. ALIGNED RECEIVER. ADJUSTED POWER OUT AND FREQUENCY TO SPECS. BENCH CHECK GOOD. 1 G 7 1 3U H2SW 1996020900593 19960209 00593 1996 2 9 HEEA966506 4 19960123 G 3442 MI585200 RT UNIT BELL 412 412 1182202 SW COCKPIT RADAR DEFECTIVE E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 3893P 33012 RADAR R/T HAS BAD MODULATOR; WILL NOT SHOW ANY TARGETS. 1 G 7 2 4U H4SW 1996020900594 19960209 00594 1996 2 9 HEEA966507 4 19960123 G 3453 25410038 7000 CDU BELL 412 412 1182202 SW COCKPIT LORAN DEFECTIVE E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 3893P 33012 CDU HAS LIGHT SEGMENTS OUT. 1 G 7 2 4U H4SW 1996020900595 19960209 00595 1996 2 9 HEEA966508 4 19960123 G 3444 066106103 ALTIMETER BOLKMS 105 BO105S 5626006 EU COCKPIT RADAR MALFUNCTION E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 911BR S719 RADAR ALTIMETER PEGS OUT AFTER 15 MINUTES. SENT TO THE RADIO SHOP FOR INSPECTION AND REPAIR. 1 G 7 2 3U H3EU 1996020900596 19960209 00596 EU 1996 2 9 HEEA966509 1 19960123 G 2435 230321825 STATOR 23032027 BOLKMS 105 BO105S 5626006 EU START/GEN DEFECTIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 352TT 24480 S59 STARTER GENERATOR WOULD NOT PUT OUT ANY VOLTAGE WITH THIS STATOR INSTALLED. 1 G 7 2 3U H3EU 1996020900597 19960209 00597 1996 2 9 HEEA966510 4 19960123 G 3422 5050010902 GYRO 200 SNIAS 350 AS350B2 8680813 EU COCKPIT PRECESSES E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 6097Z 2820 DIRECTIONAL GYRO PRECESSES EXCESSIVELY. REPLACED WITH SERVICEABLE GYRO. 1 G 7 1 3U H9EU 1996020900598 19960209 00598 1996 2 9 HEEA966511 4 19960123 G 3422 5050010902 GYRO 200 SNIAS 350 AS350B2 8680813 EU COCKPIT INTERMITTENT E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 60951 2771 GYRO UNRELIABLE AND WORKS INTERMITTENTLY. REPLACED WITH SERVICEABLE GYRO. 1 G 7 1 3U H9EU 1996020900599 19960209 00599 EU 1996 2 9 HEEA966512 1 19960123 G 3340 356H2802 POWER SUPPLY SNIAS 350 AS350B2 8680813 EU ANTI COLL BEACON INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 60951 2771 ANTI-COLLISION LIGHT INOPERATIVE. REPLACED WITH SERVICEABLE POWER SUPPLY. 1 G 7 1 3U H9EU 1996020900600 19960209 00600 1996 2 9 HEEA966513 4 19960123 G 3422 5050002904 GYRO SNIAS 350 AS350B2 8680813 EU COCKPIT DG INTERMITTENT E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 60951 2771 DG OPERATES INTERMITTENTLY. REPLACED WITH SERVICEABLE DIRECTIONAL GYRO. 1 G 7 1 3U H9EU 1996020900601 19960209 00601 1996 2 9 HEEA966514 4 19960123 G 3457 0110010600 RECEIVER GPS165 BRAERO DH125 HS125700A 4230170 EU COCKPIT GPS FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 125CS NA0212 GPS NOT PICKING UP SATELLITES AND LOCKS UP WHEN ENTERING A WAYPOINT. 2 L 7 2 4F A3EU 1996020900602 19960209 00602 SW 1996 2 9 HEEA966515 1 19960123 G 3212 212050207104 FLOAT BAG VALVE BELL 212 212 1181420 SW RT FLOAT FWD UNBONDED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 FWD FLOAT BAG HAS UNBONDED INLET VALVE. 1 G 7 1 4U H4SW 1996020900603 19960209 00603 SW 1996 2 9 HEEA966516 1 19960123 G 3212 212050207011 FLOAT BAG VALVE BELL 212 212 1181420 SW LT FLOAT FWD UNBONDED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 FWD FLOAT BAG HAS UNBONDED INLET VALVE. 1 G 7 1 4U H4SW 1996020900604 19960209 00604 1996 2 9 HEEA966517 4 19960123 G 2312 064102300 TRANSCIEVER BOLKMS 117 BK117B1 5626012 EU COCKPIT VHF FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 117BK 7229 TRANSCEIVER RECEIVES OK, BUT DOES NOT TRANSMIT FROM EITHER STATION. 1 G 7 2 3U H13EU 1996020900605 19960209 00605 NE 1996 2 9 HEEA966518 2 19960123 G 7321 0164248700 FUEL CONTROL SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1B 6OO30 NE ENGINE DEFECTIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 350BZ 1056 2653 ENGINE SLOW AND HANG STARTS ON FIRST START OF DAY. 1 G 7 1 3U 3 U H9EU E19EU 1996020900606 19960209 00606 SW 1996 2 9 HEEA966519 1 19960123 G 6320 212070116009 INDICATOR BELL 412 412 1182202 SW XMSN OIL TEMP STICKING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2258F 33073 INDICATOR STICKING AT 50 DEGREES, METER MOVEMENT BROKEN ON TEMP SIDE. 1 G 7 2 4U H4SW 1996020900607 19960209 00607 SW 1996 2 9 HEEA966520 1 19960125 G 5320 206031314083S CHANNEL BELL 206 206L3 1182108 SW FUSELAGE MIS MFG E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 41128 51134 FWD UPPER FLANGE HAS NO EDGE DISTANCE FOR RIVET INSTALLATION. 1 G 7 1 3U H2SW 1996020900608 19960209 00608 1996 2 9 HEEA966522 4 19960126 G 2312 021003800 OSC SNIAS 350 AS350B2 8680813 EU COCKPIT COMM DEFECTIVE E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 350BZ 2653 WEAK POWER AND OFF FREQUENCY. 1 G 7 1 3U H9EU 1996020900609 19960209 00609 SW 1996 2 9 HEEA966523 1 19960126 G 6730 206076062003 CYLINDER BELL 206 206L1 1182107 SW M/R DEFECTIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5017G 13550 45228 CYLINDER LEAKING INTERNALLY AND LOOSE BEARING. 1 G 7 1 3U H2SW 1996020900610 19960209 00610 1996 2 9 HEEA966524 4 19960126 G 3414 8000B12 INDICATOR BELL 206 206L1 1182107 SW COCKPIT AIR SPD READS LOW E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 2246Q 45752 INDICATOR UNIT INDICATES 20 MPH LOW, OUT OF TOLERANCE. 1 G 7 1 3U H2SW 1996020900611 19960209 00611 EU 1996 2 9 HEEA966525 1 19960126 G 3150 WARNING BOX KDW02 BOLKMS 105 BO105S 5626006 EU COCKPIT DEFECTIVE E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 4391S S787 WARNING BOX WARNING HORN STAYS ON BELOW 75%. SENT 1 G 7 2 3U H3EU 1996020900612 19960209 00612 NE 1996 2 9 HEEA966526 2 19960126 G 7323 25249994 GOVERNOR BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE ENGINE DEFECTIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 22347 36005 TROUBLESHOT OSCILLATION 1% N1. GOVERNOR SHAFT ROUGH. UNIT RECEIVED INSTALLED ON CPGB-1333. 1 G 7 2 4U 4 U H4SW E22EA 1996020900613 19960209 00613 NE 1996 2 9 HEEA966527 2 19960126 G 7323 25249994 GOVERNOR BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE ENGINE DEFECTIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 22347 36005 TORQUE SPLIT, TORQUE OSCILLATION. UNIT RECEIVED INSTALLED ON CPGB-1333. 1 G 7 2 4U 4 U H4SW E22EA 1996020900614 19960209 00614 SW 1996 2 9 HEEA966528 1 19960126 G 7810 212061201012 EJECTOR ASSY BELL 412 412 1182202 SW RT EXH CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 22608 33075 EJECTOR IS CRACKED AND HAS BROKEN RIVETS. 1 G 7 2 4U H4SW 1996020900615 19960209 00615 SW 1996 2 9 HEEA966529 1 19960126 G 7714 412075010109 INDICATOR BELL 412 412 1182202 SW TRIPLE TACH STICKS E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 22608 33075 TRIPLE TACH NEEDLE STICKS AND EXCESSIVE NEEDLE SPLIT. 1 G 7 2 4U H4SW 1996020900616 19960209 00616 1996 2 9 HEEA966530 4 19960126 G 2562 ELT NARCO ELT910 SKRSKY S76 S76A 8143006 NE COCKPIT DEFECTIVE E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 31219 760230 ELT STAYS ACTIVATED. 1 G 7 2 3U H1NE 1996020900617 19960209 00617 1996 2 9 HEEA966531 4 19960126 G 2562 ELT NARCO ELT910 BELL 412 412 1182202 SW COCKPIT MALFUNCTION E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 2258F 2776 33073 ELT UNIT ACTIVATES BY ITSELF IN ARMED POSITION INTERMITTENTLY. 1 G 7 2 4U H4SW 1996020900618 19960209 00618 EU 1996 2 9 HEEA966532 1 19960126 G 2810 FTA017521 TANK BOLKMS 105 BO105S 5626006 EU MAIN FUEL PEELING E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 86CH S557 MAIN FUEL TANK,PEELING INSIDE. 1 G 7 2 3U H3EU 1996020900619 19960209 00619 1996 2 9 HEEA966533 4 19960126 G 3416 5035P2P42 ALTIMETER UNITEDINST BELL 412 412 1182202 SW COCKPIT READS HIGH E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 22608 33075 ALTIMETER READS 500 FEET HIGH. 1 G 7 2 4U H4SW 1996020900620 19960209 00620 SW 1996 2 9 HEEA966534 1 19960126 G 2436 206075447007 REGULATOR BELL 206 206L1 1182107 SW DC SYS MALFUNCTION E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 5012V 45200 GENERATOR TURNING AS A MOTOR AT 15-20% N1 AFTER SHUTDOWN. REGULATOR MALFUNCTION. 1 G 7 1 3U H2SW 1996020900621 19960209 00621 NE 1996 2 9 HEEA966535 1 19960126 G 7333 PC820101 SIGNAL CONDITION SKRSKY S76 S76A 8143006 NE ALLSN 250C 250C30S 03013 GL FUEL FLOW MALFUNCTION E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 4253S 171 760035 FUEL FLOW IND. NEEDLE PEGS OUT. SIGNAL GENERATOR MALFUNCTION. 1 G 7 2 3U 3 U H1NE E1GL 1996020900622 19960209 00622 SW 1996 2 9 HEEA966536 1 19960126 G 2432 39563001 BATTERY BELL 412 412 1182202 SW DC SYS DEFECTIVE E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 2149S 992 36002 BATTERY FAILED CAPACITY TEST. 1 G 7 2 4U H4SW 1996020900623 19960209 00623 EU 1996 2 9 HEEA966537 1 19960126 G 7712 G555674 TRANSDUCER BOLKMS 117 BK117B1 5626012 EU NR 2 ENG TORQUE DEFECTIVE E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 117BK 7229 #2 ENGINE TORQUE READS INTERMITTENT. TRANSDUCER DEFECTIVE 1 G 7 2 3U H13EU 1996020900624 19960209 00624 EU 1996 2 9 HEEA966538 1 19960126 G 3340 356H2802 POWER SUPPLY SNIAS 350 AS350B2 8680813 EU BEACON DEFECTIVE E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 6100U 389 2863 BEACON FLASHES VERY SLOWLY AND DIMMLY. 1 G 7 1 3U H9EU 1996082900327 19960829 00327 GL 1996 8 29 HEEA967686 2 19960822 G 7230 23033439 DAMPER SEGMENT 23038126 ALLSN 250C 250C20B 03013 GL ENG COMP BELOW SPECS E HEEA K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 CAC15233 CAE830070 RECEIVING INSPECTION REVEALED DAMPER SEGMENT LENGTH .0335 BELOW BLUE PRINT SPECS OF .542 - .544. REPLACED DISCREPANT PAR T WITH NO CHARGE REPLACEMENT RECEIVED FROM ALLISON. 3 U E4CE 1996091200220 19960912 00220 1996 9 12 HEEA967701 1 19960829 G 7722 206375007103 INDICATOR MASCO COCKPIT TOT MIS MARKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 INDICATOR UNIT HAS WRONG RANGE MARKS ON FACEPLATE. (RANGE MARKS REFLECT P/N 206-375-005-101) TIME SINCE REPAIR 0:00. 1996091200225 19960912 00225 1996 9 12 HEEA967706 1 19960829 G 7722 206375006101 INDICATOR COCKPIT TOT MALFUNCTION E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 WHEN POWER IS APPLIED WITH AN INPUT OF 29.14 M.V. (OR 700 DEGREES) NEEDLE REMAINS AT ZERO AND OVERTEMP LIGHT ILLUMINATES . TIME SINCE REPAIR 0:00. 1996091900289 19960919 00289 1996 9 19 HEEA967765 4 19960903 G 2312 4000098000 TRANSCEIVER RT3 COCKPIT VHF DEFECTIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 RECEIVER INTERMITTENT AND TRANSMITS OFF FREQUENCY. SENT TO ALLIED SIGNAL AVIONICS FOR INSPECTION AND REPAIR. 1996091900303 19960919 00303 GL 1996 9 19 HEEA967779 2 19960904 G 7250 23008054 NOZZLE ALLSN 250C 250C28 03013 GL NR 1 OUT OF SPECS E HEEA K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 RECEIVING INSPECTION REVEALED: MEASUREMENT ON #1 NOZZLE DIMENSION (A) .019 BELOW CEB72-2103R-6 SPECS, (B) .005 BELOW BL UEPRINT SPECS, (C) .012 BELOW BLUEPRINT SPECS. 3 U E1GL 1996091900308 19960919 00308 GL 1996 9 19 HEEA967786 2 19960906 G 7230 23056634 GEAR 23033193 ALLSN 250C 250C30P 03013 GL SPUR ADAPTER DEFECTIVE E HEEA K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 CAC91370 CAE895336 RECEIVING INSPECTION REVEALED: SERIAL NUMBER ON SPUR GEAR DOES NOT MATCH NUMBER ON BOX. REPLACED DISCREPANT PART. 3 U E1GL 1996101000777 19961010 00777 1996 10 10 HEEA967813 1 19960910 G 7720 206075187001 INDICATOR COCKPIT DUAL IND CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 INDICATOR IS CRACKED. (GLASS IS CRACKED) 1996101000779 19961010 00779 1996 10 10 HEEA967815 4 19960910 G 2312 071121524 CONTROL KING KFS598 COCKPIT FAILED E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 UNIT DEFAULTS TO 120.00 MHZ WHEN TURNED OFF AND ON. 1996101700448 19961017 00448 1996 10 17 HEEA968006 1 19961003 G 2140 BH1411840 PROBE JET CAL HEATER FAILED E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 FAILED IN OPEATION. PROBE ASSEMBLY WON'T HEAT. 1996101700470 19961017 00470 1996 10 17 HEEA968028 1 19961003 G 7930 90321003 INDICATOR COCKPIT DEFECTIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 INDICATOR HAS RATTLE INSIDE UNIT. 1996101700475 19961017 00475 1996 10 17 HEEA968033 4 19961003 G 3452 6224527015 TRANSPONDER COCKPIT DEFECTIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 ATC XPONDER UNIT DOES NOT MEET MANUFACTURE AND AIRWORTHINESS STANDARDS. NUMBERS DON'T SEQUENCE CORRECTLY. IDENT SWITCH LIGHT DOES NOT COME ON AND GOES OFF INTERMITTENTLY . TEST SWITCH DOESN'T WORK AT ALL. TIME SINCE REPAIR 0:00. 1996101700481 19961017 00481 1996 10 17 HEEA968041 4 19961003 G 3452 066106200 TRANSCEIVER ATC XPONDR INOPERATIVE E HEEA K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 INOPERATIVE FROM STOCK. REPLACED DEFECTIVE Q415 TRANSISTOR. REPAIRED PROBLEM. INSPECTED AND BENCH CHECK GOOD. 1996101700814 19961017 00814 1996 10 17 HEEA968085 4 19961003 G 2312 064105430 TRANSCEIVER COCKPIT DEFECTIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 ALL 8' ON STANDBY FREQUENCY , FOUND 2 BURNT SURFACES MOUNT DEVICES ON BOTTOM SIDE OF BOARD. 1996101700831 19961017 00831 1996 10 17 HEEA968102 1 19961003 G 6320 212070116009 INDICATOR MASCO XMSN OIL STICKS E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 PRESS NEEDLE STICKS 50 TO 80%. 1996102400075 19961024 00075 1996 10 24 HEEA968178 4 19961010 G 3444 066304400 ALTIMETER. KRA405 RADAR ALT FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 PRECISION EQUIPMENT OUTPUT VOLTAGE BAD. VOLTAGE FLUCTUATES IN SELF-TEST MODE USING KRA405 SWAPPED KNI416. SENT TO HELIC OPTER SUPPORT, INC. FOR OVERHAUL. 1996102400298 19961024 00298 1996 10 24 HEEA968195 4 19961010 G 3457 13824120234 RECEIVER TRMNAV COCKPIT GPS INTERMITTENT E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 GPS RECEIVER VERY INTERMITTENT OPERATION DISPLAY VERY DIM. WOULD NOT COMPLETE A CYCLE. 1996102400306 19961024 00306 1996 10 24 HEEA968204 4 19961010 G 3442 MI5853013 INDICATOR P500 COCKPIT DEFECTIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 AZIMUTH LINE NOT CENTERED AND DISPLAY HAS GLITCHES EVERY 2-5 MINUTES AFTER WARM UP. TIME SINCE REPAIR 0:00. 1996103000007 19961030 00007 GL 1996 10 30 HEEA968220 2 19961011 G 7230 23039791 SPLINE ADAPTER ALLSN 250C 250C20 03013 GL ENGINE BELOW LIMITS E HEEA K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 RECEIVING INSPECTION REVEALED: MEASURED .0034 BELOW MINIMUM LIMITS OF .8994 ON COUPLING'S EXTERNAL SPLINES. SERIAL NUMB ER 65243 AND S/N 65246 9-17-96 AND SERIAL NUMBER 64938 3 U E4CE 1996102400329 19961024 00329 GL 1996 10 24 HEEA968228 2 19961011 G 7250 6892828 SHIELD ALLSN 250C 250C20 03013 GL NR 1 NOZZLE DEFECTIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 RECEIVING INSPECTION REVEALED: .050 OUT OF FLATNESS BETWEEN #1 NOZZLE SHIELD OUTER BAND AND INNER BAND. 3 U E4CE 1996102400359 19961024 00359 1996 10 24 HEEA968259 4 19961011 G 3451 DMED35B INDICATOR COCKPIT INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 INDICATOR INOPERATIVE UNIT. TIME SINCE REPAIR 0:00. 1996112100306 19961121 00306 1996 11 21 HEEA968427 4 19961104 G 2312 064105430 TRANSCEIVER COCKPIT INOP E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 TRANSCEIVER NO DISPLAY. 1996112100311 19961121 00311 1996 11 21 HEEA968432 4 19961104 G 2312 071121524 CONTROL KFS598 COCKPIT FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 CONTROL HAS NO DISPLAY. TIME SINCE REPAIR 0:00. 1996120500224 19961205 00224 GL 1996 12 5 HEEA968536 2 19961121 G 7230 6851574 SCROLL ASSY ALLSN 250C 250C20B 03013 GL ENGINE MIS REPAIRED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 RECEIVING INSPECTION REVEALED: REPAIR TO SCROLL ASSEMBLY ANTI-ICE PORT NOT FULLY WELDED AS MARKED AND DIMENSION FROM AN TI-ICE PORT TO SPLIT LINE MEASURES .080 ABOVE BLUE PRINT SPECS (2.225) 3 U E4CE 1996121200467 19961212 00467 GL 1996 12 12 HEEA968616 2 19961206 G 7260 23033437 GEARBOX COVER ALLSN 250C 250C20B 03013 GL STUD HELICOIL DEFECTIVE E HEEA K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 UPON INSTALLATION OF STUD NOTED: 12:00 HELICOIL INSTALLED AT AN ANGLE ON GEARBOX COVER. TIME SINCE REPAIR 0:00. 3 U E4CE 1996121900388 19961219 00388 1996 12 19 HEEA968671 4 19961211 G 3442 MI5853013 INDICATOR HONEYWELL P500 COCKPIT DEFECTIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 SEC SCAN SWITCH INTERMITTENT. THIS IS THE THIRD TIME THIS UNIT IS BEING RETURNED FOR REPAIR. 1997010900070 19970109 00070 1997 1 9 HEEA968792 4 19961230 G 3444 066304400 INDICATOR RADAR ALT FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 CHECKING INDICATOR WITH KRA405 ON SECTION 5.5.1.8 OVERALL PERFORMANCE TEST OF KRA405 MANUAL, THE PRECISION EQUIPMENT OUT PUT VOLTAGES ARE BAD. SWAPPING INDICATORS CURED PROBLEM. TIME SINCE REPAIR 0:00. 1996031500184 19960315 00184 NE 1996 3 15 JYER960111 1 19960111 G 6420 S6110334061 SPINDLE SKRSKY S61 S61A 814210C NE T/R HEAD CRACKED B S JYER K NONE O OTHER IN INSP/MAINT 1 NM 09 1043T 7030 1747 61083 AT OVERHAUL, TAIL ROTOR SPINDLE WAS FOUND CRACKED IN AREA OF FIRST THREAD. SIKORSKY AIRCRAFT HAS BEEN NOTIFED AND THE S PINDLE SENT TO THEM. (X) 2 G 7 2 4U H2EA 1996082900374 19960829 00374 WP 1996 8 29 JZBR12924 2 19960801 G 7530 30717781 MANIFOLD ALIDSIGNAL AMD FALC10 FALCON10 2730101 EU GARRTT TFE731 TFE7312 01518 WP AIR LEAK CRACKED B JZBR K NONE R PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 EA 25 500FF 6550 99193A P73246 P73246 CREW REPORTED RT ENGINE CANNOT MAKE TAKEOFF POWER DUE TO TEMP INDICATION. TROUBLESHOT SYSTEM AND FOUND NO TEMPERATURE D IFFERENCE BETWEEN NORMAL AND MANUAL MODE INDICATIONS. BLEED VALVE OPEN AT ALL TIMES. REPLACED BLEED VALVE, PROBLEM STI LL EXISTED. CHECKED HARNESS, SOLENOIDS, COMPUTER, AND BLEED VALVE SOLENOID MANIFOLD. ALL CHECKED GOOD. PERFORMED A FU NCTIONAL CHECK OF THE BLEED VALVE ON THE ENGINE AND DISCOVERED A LARGE AIR LEAK IN THE MANIFOLD CAUSING THE BLEED VALVE TO REMAIN OPEN. REPLACED THE MANIFOLD. ACCOMPLISHED AN ENGINE RUN, PERFORMED ALL OPERATIONAL AND LEAK CHECKS IAW MM WI TH NO DISCREPANCIES. THE AIRCRAFT/ENGINE WERE RETURNED TO SERVICE. (X) 2 L 7 2 4F 4 F A33EU E6WE 1996102400001 19961024 00001 SO 1996 10 24 JZBR13138 1 19960828 G 5210 159AMM100771 LATCH HANDLE GULSTM G1159 G1159 3953505 SO CABIN ENTRY BROKE B A JZBR K NONE O OTHER IN INSP/MAINT 1 EA 25 720JW 178 WHILE OPENING THE DOOR FROM THE INSIDE, THE SECONDARY LATCH HANDLE BROKE AT THE LATCH SLOT AND THE RIVETS BETWEEN THE HA NDLE-LATCH PLATE AND THE BELLCRANK WERE SHEARED. THERE IS NO PROCEDURE IN THE MM FOR REPLACEMENT OR RIGGING OF THIS HAN DLE. SUBMITTER STATED THE MM SHOULD BE UPDATED TO INCLUDE THE REQUIRED INSTRUCTIONS. 2 L 7 2 4F RT A12EA 1996122600420 19961226 00420 SO 1996 12 26 JZBR13247 1 19961212 G 3240 50109331 BRAKE UNIT GULSTM G1159 G1159A 3970109 SO MLG WRONG PART B JZBR K NONE W INADEQUATE Q C IN INSP/MAINT 1 EA 25 166WC 413 DURING A NORMAL BRAKE CHANGE, A PROBLEM WAS ENCOUNTERED. A SEARCH FOR REPLACEMENT BRAKES WAS INDICATED USING THE ABS P/ N. DURING THE COURSE OF THE SEARCH, A GULFSTREAM P/N WAS GENERATED. IT WAS ONLY AFTER THE FACT DISCOVERED THE GULFSTRE AM P/N WAS INCORRECT. THIS RESULTED IN THE INSTALLATION OF A 15 DEGREE SLOTTED BRAKE WITH A ZERO DEGREE KEYED WHEEL. D AMAGE TO THE BRAKES HAS OCCURRED AND POSSIBLY THE WHEELS. ALL FOUR WHEELS AND BRAKES WILL BE CHANGED W ITH SERVICEABLE UNITS. CAUSE: INCORRECT P/N BRAKES INSTALLED DUE TO WRONG P/N BEING REQUESTED. (X) 2 L 7 2 4F A12EA 1996122600411 19961226 00411 EA 1996 12 26 JZBR13659 2 19961108 G 8520 CRANKCASE PIPER PA60 PA60600 7106001 NM LYC O540 IO540K1J5 41532 EA NR 1 CYL BROKEN B JZBR K NONE K FLUID LOSS NR NOT REPORTED 1 EA 25 6896B 1540 600919816126 L2121748A ENGINE LOST MOST OF ITS OIL DUE TO A HOLE IN THE TOP OF THE CRANKCASE ABOVE THE CAMSHAFT LOBE FOR NR 1 CYLINDER. SUSPEC T CAMSHAFT FOLLOWER FAILURE WHICH WEDGED ITSELF BETWEEN THE CASE AND CAMSHAFT CAUSING CASE FAILURE. (X) 1 M 7 2 3O 3 O RT A17WE 1E4 1996122600528 19961226 00528 SO 1996 12 26 JZBR13820 1 19961212 G 2740 1159SCC21365 TORQUE TUBE GULSTM G1159 G1159 3953505 SO HORIZ STAB CHAFED B JZBR K NONE O OTHER IN INSP/MAINT 1 EA 25 711RL 25 WHILE INVESTIGATING A TOILET DUMP ITEM, NOTICED THE DUMP CHUTE CHAFING ON THE HORIZONTAL STABILIZER TORQUE TUBE SHAFT LO CATED UNDER THE LAVATORY FLOOR. REMOVED THE SHAFT AND FOUND DAMAGE TO BE OUT OF LIMITS. REPLACED THE TORQUE TUBE SHAFT WITH A NEW UNIT AND REPOSITIONED THE LAVATORY DUMP CHUTE FOR PROPER CLEARANCE. OPERATIONAL CHECK OF SYSTEM ACCOMPLISHE D. ALL WORK DONE IAW THE MM. AIRCRAFT RELEASED TO SERVICE. (X) 2 L 7 2 4F RT A12EA 1997011600849 19970116 00849 1997 1 16 KQ1R279K 4 19961216 G 2561 S2100AV8A VEST SWITLIK CELL LEAK B KQ1R K NONE O OTHER IN INSP/MAINT 1 EA 07 81310 CELL LEAK DISCOVERED DURING ROUTINE ANNUAL VEST INSPECTION. INSP IAW MANUAL 25-60-33. (X) 1999092400132 19990924 00132 1999 9 24 MVH0064095 4 19960907 G 2312 4000103000 TRANSCEIVER AEROSP SA365 SA365N 8680669 EU COCKPIT MISREPAIRED H BAQA K NONE W INADEQUATE Q C IN INSP/MAINT 1 EA 03 63CF 6068 RECEIVED REPAIRED RT-450 SN 530. RETURNING LOANER RT-450 SN 465. NOT SERVICABLE DUE TO INTERMITTENT TRANSMIT. REMOVED RT-450 SN 465. RETURNED TO INSTALLED REPAIRED UNIT RT-450 SN 530. OP CHECK GOOD. 1 G 7 2 3U H10EU 1999092400133 19990924 00133 EU 1999 9 24 MVH0064096 1 19960729 G 7712 9580113720 TRANSMITTER AEROSP SA365 SA365N 8680669 EU TMECA ARRIEL ARRIEL1C 60030 NE TORQUE READS LOW H BAQA K NONE O OTHER IN INSP/MAINT 1 EA 03 63CF 2380 6068 2046 TORQUE TRANSMITTER READS LOW. 1 G 7 2 3U 3 U H10EU E19EU 1999092400134 19990924 00134 EU 1999 9 24 MVH0064097 1 19960729 G 7714 645383081 INDICATOR AEROSP SA365 SA365N 8680669 EU NG TACH STICKING H BAQA K NONE O OTHER IN INSP/MAINT 1 EA 03 63CF 5180 6068 TACHOMETER GAUGE STICKS. 1 G 7 2 3U H10EU 1999092400135 19990924 00135 EU 1999 9 24 MVH0064099 1 19960730 G 7712 9580113720 TRANSMITTER AEROSP SA365 SA365N 8680669 EU TMECA ARRIEL ARRIEL1C 60030 NE TORQUE FAILED H BAQA K NONE O OTHER IN INSP/MAINT 1 EA 03 63CF 525 6068 2046 TORQUE TRANSMITTER SHORTED INTERNALLY. 1 G 7 2 3U 3 U H10EU E19EU 1999092400136 19990924 00136 EU 1999 9 24 MVH0064100 1 19960730 G 6210 365A11005003 BLADE AEROSP SA365 SA365N 8680669 EU MAIN ROTOR DAMAGED H BAQA K NONE O OTHER IN INSP/MAINT 1 EA 03 63CF 5246 6068 MAIN ROTOR REMOVED FOR DAMAGE TO INBOARD LEADING EDGE. 1 G 7 2 3U H10EU 1999092400137 19990924 00137 EU 1999 9 24 MVH0064101 1 19960730 G 3213 1801510001 STRUT AEROSP SA365 SA365N 8680669 EU MLG RATCHETS H BAQA K NONE O OTHER IN INSP/MAINT 1 EA 03 63CF 5266 6068 STRUT DOES NOT EXTEND SMOOTHLY. RATCHETS DOWN AND SOME TIMES WILL NOT EXTEND. 1 G 7 2 3U H10EU 1999092400138 19990924 00138 EU 1999 9 24 MVH0064102 1 19960730 G 6210 365A11005003 BLADE AEROSP SA365 SA365N 8680669 EU MAIN ROTOR DAMAGED H BAQA K NONE O OTHER IN INSP/MAINT 1 EA 03 63CF 5246 6068 MAIN ROTOR REMOVED FOR DAMAGE TO INBOARD LEADING EDGE. 1 G 7 2 3U H10EU 1999092400139 19990924 00139 EU 1999 9 24 MVH0064103 1 19960730 G 7931 53408A TRANSMITTER AEROSP SA365 SA365N 8680669 EU ENG OIL PRESS ERRATIC H BAQA K NONE O OTHER IN INSP/MAINT 1 EA 03 63CF 6068 TRANSMITTER INDICATION ERRATIC. REMOVED. 1 G 7 2 3U H10EU 1999092400140 19990924 00140 EU 1999 9 24 MVH0064104 1 19960730 G 2150 M4582AE BLOWER AEROSP SA365 SA365N 8680669 EU AIR DISTRIBUTION INOPERATIVE H BAQA K NONE O OTHER IN INSP/MAINT 1 EA 03 63CF 2060 6068 BLOWER INOPERABLE. 1 G 7 2 3U H10EU 1999092400141 19990924 00141 1999 9 24 MVH0064105 4 19960730 G 3421 H140JAM GYRO AEROSP SA365 SA365N 8680669 EU COCKPIT MALFUNCTIONED H BAQA K NONE O OTHER IN INSP/MAINT 1 EA 03 63CF 80 6068 GYRO WILL NOT STAY. 1 G 7 2 3U H10EU 1999092400142 19990924 00142 1999 9 24 MVH0064106 4 19960730 G 2312 4000103000 TRANSCEIVER AEROSP SA365 SA365N 8680669 EU COCKPIT FAILED H BAQA K NONE O OTHER IN INSP/MAINT 1 EA 03 63CF 6068 RT 450 WILL NOT TURN ON. 1 G 7 2 3U H10EU 1999092400143 19990924 00143 1999 9 24 MVH0064109 4 19960730 G 3416 396005241 ENCODER AEROSP SA365 SA365N 8680669 EU ALTIMETER INACCURATE H BAQA K NONE O OTHER IN INSP/MAINT 1 EA 03 63CF 6068 ENCODER INDICATES INACCURATELY. 1 G 7 2 3U H10EU 1999092400144 19990924 00144 1999 9 24 MVH0064110 4 19960731 G 2312 6221879001 TRANSCEIVER AEROSP SA365 SA365N 8680669 EU COCKPIT FAILED H BAQA K NONE O OTHER IN INSP/MAINT 1 EA 03 63CF 6068 VHF TRANSCEIVER WILL NOT COME ON. 1 G 7 2 3U H10EU 1999092400145 19990924 00145 1999 9 24 MVH0064111 4 19960731 G 2312 4000103000 TRANSCEIVER AEROSP SA365 SA365N 8680669 EU COCKPIT FAILED H BAQA K NONE O OTHER IN INSP/MAINT 1 EA 03 63CF 6068 TRANSCEIVER WILL NOT TRANSMIT. 1 G 7 2 3U H10EU 1999092400146 19990924 00146 EU 1999 9 24 MVH0064112 1 19960731 G 2612 C33 DETECTOR AEROSP SA365 SA365N 8680669 EU CABIN MALFUNCTIONED H BAQA K NONE O OTHER IN INSP/MAINT 1 EA 03 63CF 6068 DETECTOR ILLUMINATES WHEN BATTERY TURNED ON. REPLACED AND SCRAPPED LOCALLY. 1 G 7 2 3U H10EU 1999092400147 19990924 00147 1999 9 24 MVH0064117 4 19960830 G 2312 4000103000 TRANSCEIVER AEROSP SA365 SA365N 8680669 EU COCKPIT MALFUNCTIONED H BAQA K NONE O OTHER IN INSP/MAINT 1 EA 03 63CF 6068 LOANER RT-450 IS STATIC IN TRANSMIT. BLEEDING OVER ONTO OTHER RADIOS. PROBLEM IS CONSTANT WITH INTERMITTENT BREAKS IN TRANSMIT. REMOVED LOANER RT 450 SN 652. INSTALLED LOANER SN 465. OPS CHECK GOOD. 1 G 7 2 3U H10EU 1999092400148 19990924 00148 NE 1999 9 24 MVH0064119 2 19960913 G 7210 0235237600 CHIP DETECTOR AEROSP SA365 SA365N 8680669 EU TMECA ARRIEL ARRIEL1C 60030 NE ENGINE LEAKING H BAQA K NONE K FLUID LOSS IN INSP/MAINT 1 EA 03 63CF 6068 2203 CHIP PLUG LEAKS THROUGH BODY AND ELECTRODE IS LOOSE. 1 G 7 2 3U 3 U H10EU E19EU 1999092400149 19990924 00149 1999 9 24 MVH0064120 4 19960925 G 2312 4000103000 TRANSCEIVER AEROSP SA365 SA365N 8680669 EU COCKPIT INTERMITTENT H BAQA K NONE O OTHER IN INSP/MAINT 1 EA 03 63CF 6068 RT 450 SN 530 REMOVED DUE TO INTERMITTENT TRANSMIT. REMOVED RT 450 SN 530. INSTALLED RT 450 LOANER FROM CORPORATE JET S PN 400-0103-00 SN 464. TRANSMITS AND RECEIVES GOOD. 1 G 7 2 3U H10EU 1999092400150 19990924 00150 1999 9 24 MVH0064123 4 19961013 G 2312 4000103000 TRANSCEIVER AEROSP SA365 SA365N 8680669 EU COCKPIT INTERMITTENT H BAQA K NONE O OTHER IN INSP/MAINT 1 EA 03 63CF 6068 RT 450 LOANER SN 652 IS INTERMITTENT IN TRANSMIT. REMOVED LOANER RT 450 SN 652. REINSTALLED LOANER RT 450 SN 464. OP CHECKS GOOD. 1 G 7 2 3U H10EU 1999092400151 19990924 00151 1999 9 24 MVH0064124 4 19961018 G 2312 4000103000 TRANSCEIVER AEROSP SA365 SA365N 8680669 EU COCKPIT INTERMITTENT H BAQA K NONE O OTHER IN INSP/MAINT 1 EA 03 63CF 6068 RT 450 LOANER SN 652 IS INTERMITTENT IN TRANSMIT. REMOVED LOANER RT 450 SN 652 AND REINSTALLED RT 450 SN 530. OP CHECK S GOOD. 1 G 7 2 3U H10EU 1999092400152 19990924 00152 EU 1999 9 24 MVH0064126 1 19961023 G 6730 SC4161 SERVO AEROSP SA365 SA365N 8680669 EU TAIL ROTOR LEAKING H BAQA K NONE K FLUID LOSS IN INSP/MAINT 1 EA 03 63CF 509 6068 TAIL ROTOR SERVO LEAKS AT INPUT AND OUTPUT, SERVO INPUT LEVER WORN. 1 G 7 2 3U H10EU 1999092400153 19990924 00153 1999 9 24 MVH0064127 4 19961024 G 2312 CH45202G CONTROL UNIT AEROSP SA365 SA365N 8680669 EU COMMUNICATIONS INTERMITTENT H BAQA K NONE O OTHER IN INSP/MAINT 1 EA 03 63CF 3596 6068 RT 450 HAS INTERMITTIENT TRANSMIT LANE RT2. 1 G 7 2 3U H10EU 1999092400154 19990924 00154 1999 9 24 MVH0064129 4 19961024 G 2211 CDV85 COMPUTER AEROSP SA365 SA365N 8680669 EU AUTO PILOT MALFUNCTIONED H BAQA K NONE O OTHER IN INSP/MAINT 1 EA 03 63CF 5573 6068 AUTOPILOT DECOUPLES, INTERMITTENT, HAS PROBLEMS HOLDING TRACK. 1 G 7 2 3U H10EU 1999092400155 19990924 00155 EU 1999 9 24 MVH0064140 1 19961113 G 2435 524031B BRUSHES AEROSP SA365 SA365N 8680669 EU STARTER/GEN WORN H BAQA K NONE O OTHER IN INSP/MAINT 1 EA 03 63CF 3790 6068 GENERATOR BRUSHES WORN. OVERHAULED, CHANGED BEARINGS, AND NEW BRUSHES. 1 G 7 2 3U H10EU 1999092400156 19990924 00156 NE 1999 9 24 MVH0064141 2 19961116 G 7260 9560115450 MAGNETIC SEAL AEROSP SA365 SA365N 8680669 EU TMECA ARRIEL ARRIEL1C 60030 NE STARTER DRIVE LEAKING H BAQA K NONE K FLUID LOSS IN INSP/MAINT 1 EA 03 63CF 202 6068 2203 MAG SEAL REMOVED FOR LEAKING. 1 G 7 2 3U 3 U H10EU E19EU 1999092400157 19990924 00157 EU 1999 9 24 MVH0064143 1 19961118 G 7920 0210145040 CHECK VALVE ARRIEL1 AEROSP SA365 SA365N 8680669 EU TMECA ARRIEL ARRIEL1C 60030 NE ENGINE OIL LEAKING H BAQA K NONE K FLUID LOSS IN INSP/MAINT 1 EA 03 63CF 2106 6068 2203 REPLACED VALVE FOR EXTERNAL LEAKING SN P171B. REMOVED VALVE SN P171B AND INSTALLED SERVICABLE VALVE , SN K575B. 1 G 7 2 3U 3 U H10EU E19EU 1999092400158 19990924 00158 1999 9 24 MVH0064144 4 19961120 G 2312 4000103000 TRANSCEIVER AEROSP SA365 SA365N 8680669 EU COCKPIT FAILED H BAQA K NONE O OTHER IN INSP/MAINT 1 EA 03 63CF 6068 LOANER RT 450 SN 652 WILL NOT TRANSMIT. REPLACED WITH LOANER RT 450 SN 465. 1 G 7 2 3U H10EU 1999092400187 19990924 00187 EU 1999 9 24 MVH0064211 1 19960730 G 3230 894TS05NY SWITCH AEROSP SA365 SA365N 8680669 EU MLG MALFUNCTIONED H BAQA K NONE O OTHER IN INSP/MAINT 1 EA 03 63CF 136 6068 LANDING GEAR SWITCH INTERMITTENT, WILL NOT EXTEND OCCASIONALLY . 1 G 7 2 3U H10EU 1999092400188 19990924 00188 EU 1999 9 24 MVH0064212 1 19960730 G 3270 160PS01A5A BUTTON AEROSP SA365 SA365N 8680669 EU AUX MLG MALFUNCTIONED H BAQA K NONE O OTHER IN INSP/MAINT 1 EA 03 63CF 5266 6068 BUTTON IS INTERMITTENT, GEAR WILL NOT EXTEND OCCASIONALLY. 1 G 7 2 3U H10EU 1999092400189 19990924 00189 EU 1999 9 24 MVH0064216 1 19960730 G 6220 126892P ROD END AEROSP SA365 SA365N 8680669 EU MAIN ROTOR WORN H BAQA K NONE O OTHER IN INSP/MAINT 1 EA 03 63CF 6068 PART WORN EXCESSIVELY. 1 G 7 2 3U H10EU 1999092400190 19990924 00190 1999 9 24 MVH0064217 4 19960730 G 2312 A21815869808 SWITCH AEROSP SA365 SA365N 8680669 EU TRIGGER INTERMITTENT H BAQA K NONE O OTHER IN INSP/MAINT 1 EA 03 63CF 259 6068 SWITCH INOPERATIVE, INTERMITTENT ACTIVATION. 1 G 7 2 3U H10EU 1999092400191 19990924 00191 1999 9 24 MVH0064218 4 19960730 G 2312 4000103000 TRANSCEIVER AEROSP SA365 SA365N 8680669 EU COCKPIT FAILED H BAQA K NONE O OTHER IN INSP/MAINT 1 EA 03 63CF 6068 TRANSCEIVER WILL NOT TRANSMIT. 1 G 7 2 3U H10EU 1999092400192 19990924 00192 EU 1999 9 24 MVH0064219 1 19960731 G 6320 365A32600100ME BRUSH AEROSP SA365 SA365N 8680669 EU M/R GEARBOX DEBONDED H BAQA K NONE O OTHER IN INSP/MAINT 1 EA 03 63CF 1848 6068 GIMBLE RING BUSHINGS DEBONDED AND WORN. 1 G 7 2 3U H10EU 1999092400193 19990924 00193 EU 1999 9 24 MVH0064221 1 19960814 G 5260 14860011 ACTUATOR AEROSP SA365 SA365N 8680669 EU STEP INOPERATIVE H BAQA K NONE O OTHER IN INSP/MAINT 1 EA 03 63CF 316 6068 ACTUATOR INOPERATIVE. 1 G 7 2 3U H10EU 1999092400194 19990924 00194 EU 1999 9 24 MVH0064233 1 19961111 G 6720 360A33107001 LOBE AEROSP SA365 SA365N 8680669 EU PITCH CONTROL WORN H BAQA K NONE O OTHER IN INSP/MAINT 1 EA 03 63CF 6068 LOBES WORN ON TAIL ROTOR PITCH. 1 G 7 2 3U H10EU 1996080200316 19960802 00316 1996 8 2 RU3A96003 4 19960627 G 3451 TRANSISTOR SIERRA 890100011 BEECH 300 300BEECH 1152930 CE TACAN SYSTEM SHORTED A RU3A A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 SW 21 70 FF5 ELECTRICAL FUMES INSIDE AIRCRAFT, MADE PRECAUTIONARY LANDING. (M) 2 L 7 2 4T A24CE 1996080200317 19960802 00317 CE 1996 8 2 RU3A96004 1 19960705 G 2121 SR1406 BLOWER MOTOR BEECH 300 300BEECH 1152930 CE AUX AIR COND FAILED A RU3A A H UNSCHED LANDING DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 SW 21 81 OKC115019 FF16 THE CREW REPORTED AN ELECTRICAL BURNING SMELL IN THE CABIN SHORTLY AFTER DEPARTING THE PEORIA, ILL AIRPORT. THEY IMMEDI ATELY RECEIVED CLEARANCE TO THE AIRPORT AND LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE AVIONICS EQUIPMENT CABINET A UX AIR CONDITIONING EVAPORATOR BLOWER MOTOR WAS INOP AND SMELL OVERHEATED. THE BLOWER MOTOR WAS REPLACED AND THE AIRCRA FT WAS RETURNED TO SERVICE. (M) 2 L 7 2 4T A24CE 1996020900087 19960209 00087 NM 1996 2 9 TWRA9603 1 19960111 G 3350 3004185 LIGHT BOEING 747 747212B 1384886 NM L5 DOOR INOPERATIVE A TWRA K NONE L NO TEST IN INSP/MAINT 1 EA 15 6186 21439 DURING DAILY INSPECTION, L5 MAIN ENTRY DOOR EMERGENCY LIGHT WAS FOUND INOPERATIVE. EVAC L5 EMERGENCY DOOR LIGHT WAS REP LACED. OPS CHECK OK. MM REF 33-51-00. (X) 2 L 7 4 4F A20WE 1996082900753 19960829 00753 NM 1996 8 29 TWRA96208 1 19960724 G 3350 S1356B37 LIGHT BOEING 747 747212B 1384886 NM CABIN INOPERATIVE A TWRA K NONE L NO TEST IN INSP/MAINT 1 EA 15 6186 16336 21439 DURING DAILY CHECK, FOUND SILL LIGHT L5 DOOR FORWARD INOP. REMOVED AND REPLACED SILL LIGHT. OPS CHECK NORMAL PER MM 33 -51-00. (M) 2 L 7 4 4F A20WE 1996082900754 19960829 00754 NM 1996 8 29 TWRA96209 1 19960724 G 3350 ML7715 BULB BOEING 747 747212B 1384886 NM CABIN FAILED A TWRA K NONE L NO TEST IN INSP/MAINT 1 EA 15 6186 21439 DURING DAILY CHECK, FOUND SEAT 56, 57 ABC EVAC LIGHTS INOP. RELAMPED, OPS CHECK OK PER MM 33-51-00. (M) 2 L 7 4 4F A20WE 1996082900755 19960829 00755 NM 1996 8 29 TWRA96210 1 19960724 G 3350 276001 FUSE BOEING 747 747212B 1384886 NM CABIN INOPERATIVE A TWRA K NONE L NO TEST IN INSP/MAINT 1 EA 15 6186 21439 DURING DAILY CHECK, FOUND E-ZONE E-PATH BATTERY PACK DISCONNECTED DUE TO LIGHT STAYING ON ALL TIMES. REPLACED FUSE ALL E-ZONE E-PATH LIGHTS. OPS CHECK OK PER MM 33-51-00. (M) 2 L 7 4 4F A20WE 1996090500537 19960905 00537 NM 1996 9 5 TWRA96242 1 19960727 G 3350 ML7715 BULB BOEING 747 747212B 1384886 NM CABIN FAILED A TWRA K NONE L NO TEST IN INSP/MAINT 1 EA 15 6186 21439 DURING DAILY CHECK, FOUND EVAC LIGHT AT SEAT 40ABC INOP. REPAIRED BROKEN WIRE AND RELAMPED. OPS CHECKED OK PER MM 33-5 1-00 PG 501. (M) 2 L 7 4 4F A20WE 1996082900773 19960829 00773 NM 1996 8 29 TWRA96256 1 19960731 G 3350 ML7715 BULB BOEING 747 747212B 1384886 NM CABIN FAILED A TWRA K NONE L NO TEST IN INSP/MAINT 1 EA 15 6186 21439 DURING DAILY CHECK, FOUND EMERGENCY LIGHT INOP AT SEAT 45C. REPLACED LAMP AND LENS ASSY. OPS CHECKED GOOD PER MM 33-51 -00 PG 501. (M) 2 L 7 4 4F A20WE 1996091900846 19960919 00846 NM 1996 9 19 TWRA96297 1 19960824 G 3350 776005 FUSE BOEING 747 747212B 1384886 NM CABIN BLOWN A TWRA K NONE L NO TEST IN INSP/MAINT 1 EA 15 6186 21439 DURING DAILY CHECK, FOUND D-ZONE ENTIRE LEFT SIDE EVAC LIGHTS INOP BETWEEN ROWS 35ABC-45ABC. REMOVED AND REPLACED BATTE RY PACK FUSE PER MM 33-51-00. OPS CHECKED NORMAL. (M) 2 L 7 4 4F A20WE 1996100300608 19961003 00608 NM 1996 10 3 TWRA96303 1 19960829 G 3350 776005 FUSE BOEING 747 747212B 1384886 NM CABIN BLOWN A TWRA K NONE L NO TEST IN INSP/MAINT 1 EA 15 6186 21439 DURING DAILY CHECK, FOUND D-ZONE LEFT SIDE EVAC LIGHT INOP. REMOVED AND REPLACED BATTERY PACK FUSE. OPS CHECK NORMAL P ER MM 33-51-00, PAE 501. (M) 2 L 7 4 4F A20WE 1996100300609 19961003 00609 NM 1996 10 3 TWRA96304 1 19960829 G 3350 086861 SOCKET BOEING 747 747212B 1384886 NM CABIN INOP A TWRA K NONE L NO TEST IN INSP/MAINT 1 EA 15 6186 21439 DURING DAILY CHECK, FOUND SEAT 21C EVAC LIGHT INOP. REPLACED SOCKET AND RELAMPED. OPS CHECKED NORMAL AS PER MM 33-51-0 0. (M) 2 L 7 4 4F A20WE 1996110700715 19961107 00715 SW 1996 11 7 UNKN0000089 1 19961010 G 6410 204011702121 BLADE BELL 204 UH1B 1181410 SW T/R CORRODED B GJQR K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 01 102FW A21429 621905 PART IS CORRODED. REPLACED WITH BLADE FROM BHT. (X) 1 G 7 1 4U EXPA1G71 1996110700714 19961107 00714 SW 1996 11 7 UNKN0000090 1 19961010 G 6410 204011702121 BLADE BELL 204 UH1B 1181410 SW T/R CORRODED B GJQR K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 01 102FW A21279 621905 PART IS CORRODED. RECEIVED FROM BHT AS IS - REORDERED 2ND SET FROM BHT. (X) 1 G 7 1 4U EXPA1G71 1996110700713 19961107 00713 SW 1996 11 7 UNKN0000091 1 19961010 G 6410 204011702121 BLADE BELL 204 UH1B 1181410 SW T/R CORRODED B GJQR K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 01 102FW A21068 621905 PART IS CORRODED. 2ND SET RECEIVED FORM BHT - REORDERED 3RD SET FROM BHT. (X) 1 G 7 1 4U EXPA1G71 1996110700712 19961107 00712 SW 1996 11 7 UNKN0000092 1 19961010 G 6410 204011702121 BLADE BELL 204 UH1B 1181410 SW T/R CORRODED B GJQR K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 01 102FW A21063 621905 PART IS CORRODED. 2ND SET FROM BHT - REORDERED 3RD SET FROM BHT. (X) 1 G 7 1 4U EXPA1G71 1996110700711 19961107 00711 SW 1996 11 7 UNKN0000093 1 19961016 G 6410 204011702121 BLADE BELL 204 UH1B 1181410 SW T/R CORRODED B GJQR K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 01 102FW A21336 621905 PART IS CORRODED. 3RD SET FROM BHT - REORDERED 4TH SET FROM BHT. 1 G 7 1 4U EXPA1G71 1996110700710 19961107 00710 SW 1996 11 7 UNKN0000094 1 19961016 G 6410 204011702121 BLADE BELL 204 UH1B 1181410 SW T/R CORRODED B GJQR K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 01 102FW A21337 621905 PART IS CORRODED. 3RD SET FROM BHT - REORDERED 4TH SET FROM BHT. (X) 1 G 7 1 4U EXPA1G71 1996110700708 19961107 00708 SW 1996 11 7 UNKN0000095 1 19961017 G 6410 204011702121 BLADE BELL 204 UH1B 1181410 SW T/R CORRODED B GJQR K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 01 102FW A21233 621905 PART IS CORRODED. 4TH SET FROM BHT - REORDERED 5TH SET FROM BHT. 1 G 7 1 4U EXPA1G71 1996110700709 19961107 00709 SW 1996 11 7 UNKN0000096 1 19961017 G 6410 204011702121 BLADE BELL 204 UH1B 1181410 SW T/R CORRODED B GJQR K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 01 102FW A21236 621905 PART IS CORRODED. 4TH SET FROM BHT - REORDERED 5TH SET FROM BHT. 1 G 7 1 4U EXPA1G71 1996082900791 19960829 00791 NM 1996 8 29 USVA69601 1 19960806 G 5320 STIFFENER BOEING 737 737247 138448D NM BS 540 CRACKED A USVA K NONE O OTHER IN INSP/MAINT 1 SO 11 309VA 19614 VERTICAL STIFFENER FORWARD FACE OF CENTER FUEL TANK IS CRACKED AT UPPER FLOOR FRAME ATTACH CUP BS 540. REPAIRED IAW MHA 2020 REV 'N/C' DATED 6-26-96 APPROVED DATA FAA FORM 8110-3. (M) 2 L 7 2 4F A16WE 1996082900792 19960829 00792 NM 1996 8 29 USVA96602 1 19960806 G 5311 FRAME BOEING 737 737247 138448D NM BS 578 CRACKED A USVA K NONE O OTHER IN INSP/MAINT 1 SO 11 309VA 19614 CIRCUMFERENTIAL FRAME BS 578 RIGHT SIDE, 4 INCHES ABOVE CREASE BEAM, HAS CRACK EMANATING FROM HOLE FOR RECEPTACLE, WHICH SIDE WALL PANEL MOUNTS FROM INBOARD FACE OF FRAME RADIUS INTO WEB AREA 1 INCH CRACK. REPAIRED IAW MHA2021 REV 'N/C' DA TED 6-26-96 APPROVED DATA FAA FORM 8110-3. (M) 2 L 7 2 4F A16WE 1996082900793 19960829 00793 NM 1996 8 29 USVA96603 1 19960806 G 5320 652179962 FITTING BOEING 737 737247 138448D NM BS 578 CRACKED A USVA K NONE O OTHER IN INSP/MAINT 1 SO 11 309VA 19614 MAIN CABIN FLOOR BEAM RIGHT SIDE BS 578 ATTACH ANGLE TO WEB HAS A 3.75 INCH CRACK AT WL 208 AND BBR 70.85. INSTALLED NE W FITTING ATTACH ANGLE, AND ALL FASTENERS IAW WITH SRM 51-30-2. (M) 2 L 7 2 4F A16WE 1997013000002 19970130 00002 WP 1997 1 30 VJ1R96003 2 19961215 G 7260 30719082 PLUG BRAERO DH125 HS125700A 4230170 EU GARRTT TFE731 TFE7313 01518 WP OIL JET CLEAN DETACHED B VJ1R K NONE K FLUID LOSS IN INSP/MAINT 1 SW 05 300BS 6932 NA0241 P76434C ENGINE COWLING WAS OPENED TO INVESTIGATE LOSS OF OIL. 'FOUND THE TRANSFER GEARBOX OIL JET CLEAN OUT PLUG (CHAPTER 72-60 -03, FIG 1, ITEM 25) UNSEATED AND HANGING ON ITS MOUNTING STUD'. LUBE OIL WAS VENTED OVERBOARD ONCE THE PLUG WAS UNSEAT ED. (X) 2 L 7 2 4F 4 F A3EU E6WE 1996102400363 19961024 00363 SW 1996 10 24 W6HR9640 1 19960930 G 6330 222331617101 ISOLATION MT 222031602107 BELL 222 222U 1182140 SW M/R XMSN WORN EXCESS E W6HR K NONE O OTHER IN INSP/MAINT 1 WP 21 416MA 47526 ISOLATION MOUNTIS WORN EXCESSIVELY. ELASTOMERIC MATERIAL IS SEPERATED FROM INNER THREADED BOSS WHERE ROD END IS THREADED INTO. 1 G 7 2 3U H9SW 1997032700276 19970327 00276 SW 1997 3 27 W6HR9644 1 19961106 G 6330 222331617101 ISOLATION MOUNT BELL 222 222U 1182140 SW M/R XMSN DEFECTIVE E W6HR K NONE O OTHER IN INSP/MAINT 1 WP 21 416MA 59 47526 MOUNT IS DEFECTIVE. MOUNT APPEARS TO BE "WEAK". A/C HAD A "GROUND BOUNCE". POSSIBLE DELAMINATION OF ELASTROMIC MATERI AL IS APPARENT. REPLACING THIS MOUNT WI TH "NEW" REMOVED THE GROUND BOUNCE. 1 G 7 2 3U H9SW 1996102400754 19961024 00754 CE 1996 10 24 WG1R583K 1 19961001 G 2421 835563 ALTERNATOR CESSNA 650 650 2076802 CE NR 1 ENG AC BEARING FAILED B L WG1R O OTHER E J VIBRATION/BUFFET WARNING INDICATION NR NOT REPORTED 1 SW 19 874G 7406 1623 650137 PILOT REPORTED VIBRATION COMING FROM NR 1 ENG WHICH VARIED WITH THROTTLE ALONG WITH A VOLTAGE SPIKE ON AC VOLTMETER. AF TER EXTENSIVE TROUBLESHOOTING, FOUND ALTERNATOR BEARINGS HAD FAILED, SHORTING OUT ALTERNATOR CONTROL UNIT, AC VOLT METER AND HORIZ STAB ANTI-ICE CONTROL UNIT. ALTERNATOR ON NR 2 ENGINE FAILED 5 HRS LATER SHORTING OUT ALTERNATOR CONTROL UNI T ALSO. ALTERNATOR BEARINGS HAVE A SERVCIE LIFE OF 2,000 HRS. FIRST ONE FAILED AT 1,618 HRS AND SECOND AT 1623 HRS SIN CE OVERHAUL. (X) 2 L 7 2 4F A9NM 1996061300067 19960613 00067 EU 1996 6 13 XC4R9620651 1 19960305 G 2435 P6048233 ARMATURE AUXILEC 8260121 AEROSP ATR72 ATR72 EU START/GEN NR 2 DEFECTIVE B XC4R K NONE O OTHER IN INSP/MAINT 1 SO 19 425 1146 ARMATURE COMMUTATOR TOTAL INDICATED RUN-OUT VARIES PLUS OR MINUS 0.005 INCH. INCONSISTENCY OF COMMUTATOR WEAR CAUSED EX CESSIVE BRUSH WEAR. (X) 2 H 7 2 4T RT