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 2003111300042 20031113 00042 CE 2003 11 13 001020 1 20001020 G 3230 1153800025 MOTOR BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA MLG SLOW B R3R2 K NONE O OTHER IN INSP/MAINT 1 SW 01 7166P UPON INSTALLATION OF THIS NEWLY OVERHAULED LANDING GEAR RETACT MOTOR THE LANDING GEAR WOULD CYCLE AT ABOUT HALF NORMAL S PEED. ALL MECHANICAL AND ELECTRICAL SYSTEMS CHECKED GOOD. INSTALLED A NEW RETRACT MOTOR AND ALL SYSTEMS OPERATED NORM ALLY. 1 L 7 2 4T 4 T A24CE E4EA 2000121500182 20001215 00182 CE 2000 12 15 010304 1 20001204 G 5730 MS24694C51 SCREW CESSNA 500 550 2076604 CE BOTH WINGS OVERSIZED B R8RR K NONE O OTHER IN INSP/MAINT 1 WP 07 6775C 5500677 LEFT WING AND RIGHT WING LEADING EDGE SKIN HAS BEEN CHAFED BY THE UPPER SCREW OF THE OUTBOARD ROW OF SCREWS ATTACHING TH E HEATED LEADING EDGE TO THE WING. THE SCREWS INSTALLED WERE TOO LONG, ALTHOUGH THEY WERE THE ONES CALLED FOR IN THE PA RTS CATALOG. THEY CHAFED INTO THE WING LEADING EDGE SKIN ABOUT 0.024 INCH DEEP INTO THE LEFT WING AND 0.018 INCH INTO T HE RIGHT WING. THE SKIN IS 0.040 INCH ALUMINUM. CESSNA HAS APPROVED A SHORTER SCREW TO BE INSTALLED AND IS CURRENTLY W ORKING ON A PERMANENT REPAIR. (X) 1 L 7 2 4F A22CE 2000040400458 20000404 00458 EA 2000 4 4 20000328SH001 2 20000321 G 8500 ENGINE CESSNA 172 172R 2072401 CE LYC IO360 IO360L2A EA NOSE MALFUNCTIONED H O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION DE DESCENT 1 SW 99 9559D 724 17280488 L2757151A ENGINE RAN ROUGH AND ALMOST SHUT DOWN DURING DESCENT. (X) 1 H 7 1 3O 3 O NT 3A12 1E10 2000042600035 20000426 00035 EA 2000 4 26 20000328SH002 1 20000222 G 5720 219672 SUPPORT BRACKET AC DHAV DHC2 DHC2* 2800108 EA WING CRACKED H K NONE O OTHER IN INSP/MAINT 1 WP 27 BRAND NEW TANK SUPPORTS HAVE BEEN FOUND TO BE CRACKED ALONG THE BEND RADIUS WHERE THE ALUMINUM HAS BEEN COLD-FORMED, CLO SE TO THE TANK STRAP CLEVIS PEN HOLES. THIS PROBLEM HAS ALSO BEEN FOUND ON PARTS WITH TIME IN SERVICE, AND THE CRACKS P ROGRESS WITH USE. (X) 1 H 7 1 3R A806 2000040400459 20000404 00459 CE 2000 4 4 20000328SH003 1 20000131 G 2750 12957Y CONTROL CABLE BEECH 60 B60 1153605 CE TE FLAP FAILED B O OTHER O OTHER NR NOT REPORTED 1 WP 19 341D 794 P397 CABLE WITH A TWIST TEST OF THE CABLE END SIMILAR TO THE DUKES CABLES ON THE PIPER PA31 FLAP SYSTEMS. (X) 1 L 7 2 3O A12CE 2000042500033 20000425 00033 CE 2000 4 25 20000328SH004 1 20000302 G 3250 S18233 ROD END CESSNA 172 172R 2072401 CE STEERING COLLAR SHEARED G DJXS O OTHER O OTHER NR NOT REPORTED 1 GL 23 922TA 1013 17280249 BEARING ROD END THAT ATTACHES STEERING BUNGEE TO STEERING COLLAR SHEARED AT PREVIOUS CRACK AT THE FIRST THREAD. SUBMITT ER STATED MAY HAVE HAPPENED AS A RESULT OF ACCIDENT RATHER THAN CAUSE. (X) 1 H 7 1 3O NT 3A12 2000032800004 20000328 00004 SO 2000 3 28 20000328SH005 1 20000303 G 2750 573801 VALVE GULSTM G1159 GIV 3980115 SO TE FLAP LOOSE B O OTHER O OTHER NR NOT REPORTED 1 EA 25 250VC 3648 1231 FLAP ACTUATION SLUGGISH WITH ENGINE RUNNING. WOULD NOT OPERATE USING AUXILIARY SYSTEM. FOUND FLAP SELECTOR VALVE INTER NAL SPOOL ACCESS CAP HAD NEVER BEEN SAFETIED (NO SAFETY WIRE MARKS ON UNIT) AND HAD BACKED OUT 3 TURNS. REPLACED SELECT OR VALVE (REPLACEMENT UNIT WAS SAFETIED WITH LEAD SEAL). OPERATION NORMAL. (X) 2 L 7 2 4F RT A12EA 2000042500034 20000425 00034 CE 2000 4 25 20000328SH006 1 20000224 G 2422 2C25001ECM1203 INVERTER CESSNA 208 208B 2073701 CE ELECTRICAL FAILED B QY5R D RETURN TO BLOCK B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 NE 01 9820F 208B0410 WHILE ON A DATA GATHERING NIGHT FLIGHT. THE EQUIPMENT POWERED BY THE INVERTER LOST POWER. WHILE REACHING FOR THE POWER DISCONNECT SWITCH, A FLASH WAS NOTICED IN THE AREA IN WHICH THE INVERTER WAS INSTALLED. POWER TO THE INVERTER WAS CUT OFF AND THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. (X) 1 H 7 1 3T A37CE 2000040400460 20000404 00460 CE 2000 4 4 20000328SH007 1 20000228 G 2510 05142251 SEAT CESSNA 172 172R 2072401 CE COCKPIT CRACKED H K NONE O OTHER IN INSP/MAINT 1 SW 99 405ER 2285 17280285 REFERENCE DRAWING 0514222 (SEAT BACK ASSY, AFT BENCH 172) VIEWING THE -1 SEAT BACK ASSY. AT THE LOWER RIGHT HAND CORNER OF THE SEAT BACK THRE IS A -11 FRAME END THAT WELDS TO THE -4 FRAME UPPER. THE WELD IS APPROXIMATELY 7.30 INCHES UP FR OM THE BOTTOM OF THE -11 FRAME END. APPROXIMATELY .75 INCH BELOW THIS WELD JOINT THE SEAT BACK HAS BROKE IN HALF. (X) 1 H 7 1 3O NT 3A12 2000032800007 20000328 00007 EU 2000 3 28 20000328SH011 1 20000115 G 5610 4AS3430000501 WINDSHIELD ISRAEL GALAXY GALAXY 4500307 EU COCKPIT FAILED B O OTHER O OTHER NR NOT REPORTED 1 SW 07 505GA 654 005 THE PILOT''S WINDSHIELD (INNER PANE) SHATTERED AT FL 430. AT THIS TIME THERE IS NO POSSIBLE CAUSE. THE WINDSHIELD IS B EING SHIPPED TO THE MANUFACTURER TO DETERMINE CAUSE. (X) 2 L 7 2 4F RT A53NM 2000040400463 20000404 00463 WP 2000 4 4 20000328SH012 2 20000120 G 7200 30755141 SEAL GARRTT TFE731 TFE7315R 01518 WP ENGINE LEAKING B U02R K NONE K FLUID LOSS IN INSP/MAINT 1 GL 19 1946 P91165 ENGINE EXPERIENCED IN-FLIGHT SHUT DOWN BY HIGH GEARBOX PRESSURE WHICH EXPANDED OIL TANK AND CREATED HOLE IN OIL TANK AT A SPOT WELD DUE TO HIGH GEARBOX PRESSURE. ENGINE LOST OIL PRESSURE AND WAS SHUT DOWN BY PILOT. (X) 4 F E6WE 2000040400464 20000404 00464 SW 2000 4 4 20000328SH013 1 20000203 G 3230 AN423A BOLT GULSTM 112 114ARKWELL 7630315 SW MLG CRACKED D O OTHER O OTHER LD LANDING 1 SW 99 5923N 14540 UPON LANDING AIRCRAFT, PILOT NOTED RT MAIN LANDING GEAR FELT MUSHY. VISUAL INSPECTION OF PARKED AIRCRAFT YIELDED THE RT MAIN LANDING GEAR FORWARD TRUNNION BOLT WASHER AND NUT WERE MISSING DUE TO THE BOLT SHEARING. AS A PREVENTATIVE MEASUR E, THE LT SIDE BOLT WAS REMOVED AND FOUND SIGNS OF EXTREME WEAR, AND WAS REPLACED. CURRENTLY, THERE ARE NO AIRWORTHINES S DIRECTIVES OR SERVICE BULLETINS ADDRESSING THIS BOLT. SUBMITTER STATED THIS BOLT SHOULD BE A TIME REPLACEMENT PART OF 3-5 YEARS OF 500 LANDINGS. (X) 1 L 7 1 3O A12SO 2000040400465 20000404 00465 NE 2000 4 4 20000328SH014 2 20000201 G 7200 30756441 SEAL GARRTT TFE731 TFE73121C NE ENGINE LEAKING B K NONE K FLUID LOSS IN INSP/MAINT 1 GL 19 P73466 ENGINE EXPERIENCED HIGH GEARBOX PRESSURE AT TEST CELL AFTER ENGINE CORE REPAIR WITH NEW NR 4 AND NR NR 5 SEALS AND RUNNE RS. (X) 4 F E6WE 2000040400466 20000404 00466 NE 2000 4 4 20000328SH015 2 20000201 G 7200 30756392 SEAL GARRTT TFE731 TFE73121C NE ENGINE LEAKING B UO2R K NONE K FLUID LOSS IN INSP/MAINT 1 GL 19 P73466 ENGINE EXPERIENCED HIGH GEARBOX PRESSURE AT TEST CELL AFTER ENGINE CORE REPAIR WITH NEW NR 4 AND AND NEW NR 5 SEALS AND RUNNERS. (X) 4 F E6WE 2000040400467 20000404 00467 NE 2000 4 4 20000328SH016 2 20000201 G 7200 30756332 SEAL GARRTT TFE731 TFE73121C NE ENGINE LEAKING B UO2R K NONE K FLUID LOSS IN INSP/MAINT 1 GL 19 P73466 ENGINE EXPERIENCED HIGH GEARBOX PRESSURE AT TEST CELL AFTER ENGINE CORE REPAIR WITH NEW NR 4 AND NR 5 SEALS AND RUNNERS. (X) 4 F E6WE 2000040400468 20000404 00468 NE 2000 4 4 20000328SH017 2 20000201 G 7200 30756451 SEAL GARRTT TFE731 TFE73121C NE ENGINE LEAKING B UO2R K NONE K FLUID LOSS IN INSP/MAINT 1 GL 19 P73466 ENGINE EXPERIENCED HIGH GEARBOX PRESSURE AT TEST CELL AFTER ENGINE CORE REPAIR WITH NEW NR 4 AND NEW NR 5 SEALS AND RUNN ERS. (X) 4 F E6WE 2000040400470 20000404 00470 EA 2000 4 4 20000328SH020 2 20000208 G 8530 65007 RETAINER SEAL MOONEY M20 M20J 5870219 SW LYC O360 IO360A3B6 41514 EA NR 1 CYLINDER DAMAGED B K NONE O OTHER IN INSP/MAINT 1 SO 05 3935H 2006 240982 DURING ANNUAL INSPECTION, DISCOVERED NR 1 CYLINDER EXHAUST PUSH ROD TUBE SEAL AREA AT CASE HALF RETAINER PROTRUDING AT A N ANGLE. REMOVED NR 1 EXHAUST PUSH ROD, FOUND LIFTER BODY CRACKED, AND BROKEN. LIFTER WILL NOT COME OUT. SUBMITTER SU SPECTED CAUSE WAS STUCK EXHAUST VALVE AT SOME TIME. ENGINE IS AT TBO AND WILL BE REPLACED. (X) 1 L 7 1 3O 3 O 2A3 1E10 2000032900439 20000329 00439 CE 2000 3 29 20000329SH001 1 20000211 G 2731 JACKSCREW LEAR 35 35A 5170602 CE STABILIZER GALLED H O OTHER E VIBRATION/BUFFET DE DESCENT 1 NM 09 573LP 501 171 658 CREW BEGAN TO DESCEND OUT OF CRUISE, AIRCRAFT BECAME NOSE HEAVY. THE CREW COULD NOT TRIM AIRCRAFT STABILIZER AS BOTH PR IMARY AND SECONDARY PORTIONS OF THE STAB ACTUATOR FUNCTIONALLY FAILED. THIS UNIT HAD APPROXIMATELY 500 HOURS ON IT SINC E ITS 12,000 HOUR INSPECTION. POSSIBLE CAUSE WOULD BE FAILURE OF A STAB ACTUATOR COMPONENT COMMON TO BOTH PRIMARY AND S ECONDARY MOTORS, POSSIBLY A GALLED JACK SCREW ASSEMBLY. TEAR DOWN REPORT CONFIRMED A GALLED JACK SCREW ASSEMBLY. SUBMI TTER RECOMMENDED CHANGE IN JACK SCREW DESIGN TO INCREASE SURFACE AREA OF SCREW ASSEMBLY THEREBY REDUCING THE CONTACT SUR FACE LOADING ON THE SCREW ASSEMBLY. (X) 2 L 7 2 4F A10CE 2000040400471 20000404 00471 CE 2000 4 4 20000329SH002 1 20000217 G 5347 1210520 SEAT TRACK CESSNA 210 210L 2073448 CE FUSELAGE MISINSTALLED B R2JR K NONE O OTHER IN INSP/MAINT 1 EA 21 5035V 21060823 DURING AIRCRAFT INSPECTION, FOUND SEAT TRACKS NOT FASTENED TO AIRCRAFT STRUCTURE BELOW FLOOR AND IMPROPER FASTENERS SECU RING SEAT TRACKS. CONTACTED CESSNA TECH SUPPORT TO OBTAIN PROPER INSTALLATION INSTRUCTIONS AND REINSTALLED SEAT TRACKS PROPERLY. SEAT TRACKS ARE MAJOR STRUCTURE AND NEED TO BE INSTALLED PROPERLY FOR CRUSHWORTHINESS. (X) 1 H 7 1 3O 3A21 2000040400472 20000404 00472 CE 2000 4 4 20000329SH003 1 20000209 G 2750 503801531 JACKSCREW BEECH 99 99 1154002 CE TE FLAP WRONG PART B TIMR O OTHER W INADEQUATE Q C NR NOT REPORTED 1 NM 07 199GL 825B98 U15 DURING REPLACEMENT OF FLAP ACTUATORS, LEFT INBOARD FLAP MOVED IN THE OPPOSITE DIRECTION OF FLAP SELECTOR POSITION. REMO VED FLAP ACTUATOR AND DETERMINED THAT DRIVE ASSEMBLY WAS INCORRECT FOR INBOARD ACTUATOR. (X) 1 L 7 2 3T A14CE 2000040400473 20000404 00473 EA 2000 4 4 20000329SH004 2 20000214 G 7322 55018010 CARBURETOR CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA AIRBOX CONTAMINATED D A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION NR NOT REPORTED 1 WP 27 5259R 3706 17263473 A ROUGH RUNNING ENGINE, AND A LOSS OF ENGINE POWER (MAXIMUM RPM 2200) CAUSED PILOT TO MAKE A PRECAUTIONARY LANDING. TE CHNICIAN INSPECTED THE INDUCTION SYSTEM AND FOUND THE CARBURETOR HEAT AIR VALVE SEAL MATERIAL HAD SEPARATED AND WAS INGE STED BECOMING LODGED ACROSS THE CARBURETOR VENTURI. THIS DISRUPTION OF AIR FLOW THROUGH THE VENTURI CAUSED IMPROPER FUE L/AIR MIXTURE AND FUEL SCHEDULING RESULTING IN A LOSS OF POWER. THIS PART HAD NOT BEEN CHANGED SINCE MANUFACTURE OF AIR CRAFT 25 YEARS AGO. TOTAL TIME ON AIRCRAFT 3,706.0 HOURS. RECOMMENDATION: MORE FREQUENT INSPECTIONS OF CARBURETOR AIR BOX ASSEMBLY FOR WEAR AND DETERIORATION AND TOTAL TIME IN SERVICE. (X) 1 H 7 1 3O 3 O NT 3A12 E274 2000040400474 20000404 00474 EA 2000 4 4 20000329SH005 2 20000217 G 7421 SPARK PLUG CESSNA 172 172R 2072401 CE LYC IO360 IO360L2A EA ENGINE DIRTY H O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION NR NOT REPORTED 1 SW 99 477ER 1062 17280622 L2803951A DURING FLIGHT, THE PILOT REPORTED ROUGH ENGINE OPERATION FOR SEVERAL SECONDS. THE SPARK PLUGS WERE SERVICED. (X) 1 H 7 1 3O 3 O NT 3A12 1E10 2000040400475 20000404 00475 EA 2000 4 4 20000329SH006 2 20000217 G 7421 SPARK PLUG CESSNA 172 172R 2072401 CE LYC IO360 IO360L2A EA ENGINE DIRTY H O OTHER R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 SW 99 417ER 1903 17280305 L2727851A DURING FLIGHT, PILOT REPORTED ROUGH ENGINE OPERATION FOR A FEW SECONDS. THE INJECTOR NOZZLES WERE CLEANED, THE SPARK PL UGS WERE SERVICED, AND THE ELECTRIC BOOST PUMP WAS REPLACED. (X) 1 H 7 1 3O 3 O NT 3A12 1E10 2000040400476 20000404 00476 EA 2000 4 4 20000329SH007 2 20000217 G 7320 FLOW DIVIDER CESSNA 172 172R 2072401 CE LYC IO360 IO360L2A EA ENGINE MALFUNCTIONED H O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION NR NOT REPORTED 1 SW 99 460ER 17280668 L2786851A DURING FLIGHT, THE PILOT REPORTED ROUGH ENGINE OPERATION FOR A FEW SECONDS. THE FUEL FLOW DIVIDER WAS REPLACED AND THE NR 1 NOZZLE WAS REPLACED. (X) 1 H 7 1 3O 3 O NT 3A12 1E10 2000040400477 20000404 00477 NE 2000 4 4 20000329SH008 3 20000207 G 6111 C63371 SEAL BEECH 1900 1900D 1154162 CE HARTZL HCE4A HCE4A3A NE PROPELLER BLADE DETERIORATED B LU4R O OTHER O OTHER NR NOT REPORTED 1 SO 17 5151 673 HJ55 NEW STYLE SEAL APPEARS TO HAVE DETERIORATED AFTER 672.4 HOURS OF SERVICE. RETURNED PARTS TO FACTORY FOR EVALUATION. (X) 2 L 7 2 4T RT A24CE 5 C P10NE 2000040400480 20000404 00480 NE 2000 4 4 20000329SH034 3 20000309 G 6111 C60661 PLATE HARTZL HDE6C HDE6C3B NE PROPELLER BLADE CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 05 5018 HL2747 DURING ROUTINE INSPECTION, FOUR OF THE SIX PRELOAD PLATES WERE FOUND CRACKED. CRACKS STARTED AT THE PITCH CHANGE BRACKE T CUT-OUT AREA AND RAN ACROSS THE FACE OF THE PLATE AND DOWN THE OUTSIDE DIAMETER. (X) 6 C P34NE 2000040400483 20000404 00483 SO 2000 4 4 20000329SH038 2 20000214 G 7414 1051324 SPRING CONT O470 O470* 17026 SO IMPULSE COUPLING DAMAGED B QKKR K NONE W INADEQUATE Q C IN INSP/MAINT 1 CE 01 NEW PARTS HAVE FINGER PRINTS ON THEM. PARTS ARE NEW, NOT REMOVED FROM MANUFACTURER''''S BAG SINCE TIME OF BAGGING AT SU PPLY CENTER. SUBMITTER STATED PROBLEM IS SPRING STEEL WITH SWEAT FROM THE PERSONS WORKING ON THE PART. 3 O E273 2000040300012 20000403 00012 CE 2000 4 3 20000329SH039 1 20000302 G 2612 WARNING LIGHT LEAR 25 25D 5170514 CE COCKPIT ILLUMINATED H A UNSCHED LANDING N FALSE WARNING NR NOT REPORTED 1 SO 11 969SS 317 EN ROUTE, RIGHT ENGINE FIRE WARNING LIGHT ILLUMINATED BRIEFLY. DIVERTED FLIGHT. FALSE ENGINE FIRE WARNING, CHAFED WIRE . (X) 2 L 7 2 4J A10CE 2000040400484 20000404 00484 WP 2000 4 4 20000329SH040 1 20000227 G 3244 26088911 TIRE GOODYEARAERO DOUG DC9 DC983 3022083 WP MLG FAILED B A3L2 O OTHER O OTHER NR NOT REPORTED 1 SW 09 72930255 DEFECT: THROWN TREAD FROM CARCASS. CAUSE: UNDETERMINED. TIRE SENT TO MANUFACTURER FOR ANALYSIS. PREVENTIVE ACTION: PENDING COMPLETE INVESTIGATION (INTERIM) ONLY USING NEW TIRES. (X) 2 L 7 2 4F RT A6WE 2000040400485 20000404 00485 CE 2000 4 4 20000329SH041 1 20000220 G 2820 050011874 FUEL LINE CESSNA 172 172M 2072418 CE FUSELAGE CHAFED D K NONE O OTHER IN INSP/MAINT 1 GL 23 73366 2428 17267405 AIRCRAFT ACQUIRED FOR USE IN A FLIGHT SCHOOL. DURING ITS INITIAL INSP (ANNUAL), A FUEL LINE WAS FOUND CHAFING HARD AGAI NST THE STEERING ROD. THIS FUEL LINE IS LOCATED BETWEEN FUEL SELECTOR VALVE AND FUEL STRAINER AND PASSES UNDER COPILOT' 'S RUDDER PEDALS. EVERY TIME RUDDER PEDALS WERE MOVED, THE STEERING ROD (CONNECTED TO NOSE WHEEL) RUBBED AGAINST THE FU EL LINE AT A BEND. FUEL LINE WAS CHAFED TO THE POINT WHERE INTERIOR WALL WAS BENT INWARD AND SO THIN THAT FAILURE WAS I MMINENT. IT APPEARED TO HAVE BEEN CHAFING SINCE ACFT WAS BUILT. NEW FUEL LINE CONTACTED STEERING ROD IN SAME MANNER. CORRECTED BY BENDING LINE AWAY FROM STEERING ROD. 1 H 7 1 3O NT 3A12 2000040400487 20000404 00487 SO 2000 4 4 20000329SH043 1 20000211 G 7110 65202800 LATCH PIPER PA32 PA32260 7103206 SO COWL CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 25 3369W 321054 CRACKS FORM AT THE BEND RADIUS OF THE LATCH ASSEMBLY WITHIN A FEW HOURS OF NORMAL OPERATION. SEVERAL ASSEMBLIES (6) HAV E FAILED IN THE SAME MANNER. THIS ASSY IS FORMED WITH A MUCH SMALLER BEND RADIUS AS COMPARED TO AN OLDER STYLE PIPER OE M LATCH ASSY. 1 L 7 1 3O A3SO 2000040400488 20000404 00488 EA 2000 4 4 20000329SH044 2 20000302 G 8530 05K21123 CYLINDER CESSNA 150 152 2071835 CE LYC O235 O235N2C 41505 EA ENGINE DAMAGED B WIWR K NONE O OTHER IN INSP/MAINT 1 WP 07 95512 466 15285911 RL897015 WHILE PERFORMING ANNUAL INSP, ALUMINUM SHAVINGS WERE FOUND IN THE OIL FILTER. FILTER SENT TO LYC FOR ANALYSIS AND DETER MINED TO BE PISTON PIN PLUG MATERIAL. UPON REMOVAL OF ALL 4 CYLINDERS, SEVERE PITTING FOUND AT BOTTOM OF EACH CYL WALL AT THE POINT WHERE PISTON TOUCHES ITS LOWEST TRAVEL. ALL 4 CYL''S REJECTED AND FACTORY NEW INSTALLED. FACTORY STATES T HIS IS RESULT OF ENG NOT REACHING PROPER OPERATING TEMP. ACFT IS OPERATED IN PHOENIZ, AZ, OIL TEMP GAUGE IS ACCURATE. 1 H 7 1 3O 3 O NT 3A19 E223 2000040400489 20000404 00489 EA 2000 4 4 20000329SH045 2 20000302 G 8530 05K21123 CYLINDER CESSNA 150 152 2071835 CE LYC O235 O235N2C 41505 EA ENGINE DAMAGED B WIWR K NONE O OTHER IN INSP/MAINT 1 WP 07 757NZ 681 15279885 L2507515 WHILE PERFORMING ANNUAL INSP, SMALL ALUMINUM PARTICLES WERE FOUND IN THE OIL FILTER. A BORESCOPE INSP REVEALED WEAR ON CYLINDER WALLS AND PITTING AT THE BASE OF EACH CYL (INSIDE) AT THE POINT OF THE PISTON''S FARTHEST TRAVEL DOWNWARDS. TW O OF THE CYL''S WERE FACTORY NEW WITH 681 HRS SINCE NEW. THE OTHER TWO WERE REPAIRED 1,176.7 HRS AGO AT FACTORY''S REQU EST BY A FACTORY APPROVED REPAIR FACILITY UNDER WARRANTY. THIS IS 3RD OCCURRENCE IN 1,859.5 HRS SMOH BY LYC. THE 1ST O CCURANCE RESULTED IN ALL OF THE ABOVE AND BELOW ACCEPTABLE COMPRESSIONS ON ALL 4 CYL''S. FACTORY STATES ENGINE IS RUNNI NG TOO COLD IN PHX, AZ. 1 H 7 1 3O 3 O NT 3A19 E223 2000040400490 20000404 00490 GL 2000 4 4 20000329SH046 3 20000322 G 6110 CLAMP HARTZL HCA3V EHCA3VF2 GL PROPELLER BLADE DAMAGED G K NONE O OTHER IN INSP/MAINT 1 SO 05 THE PILOT OF A BEECH BARON DISCOVERED A BROKEN BOLT WITHIN THE PROP ASSEMBLY DURING A CAREFUL PRE-FLIGHT INSPECTION. BO TH PROPELLERS HAD RECENTLY UNDERGONE MAINTENANCE AT A PROPELLER REPAIR STATION. EVIDENCE SUGGESTED THE PROPELLER BLADE CLAMP, PN C-3-51 (WHICH HOLDS THE PROP BLADE IN PROP HUB), WAS MAKING CONTACT AND EXERTING FORCE ON THE LATCH BRACKET CA USING BOLTS SECURING BRACKET TO FAIL. THE CONTACT BETWEEN THE BLADE CLAMP AND BRACKET WAS A FUNCTION OF THE BLADE ANGLE SELECTED BY THE PILOT. IT IS UNCLEAR WHY CLEARANCE BETWEEN BLADE CLAMP AND LATCH BRACKET HAD DETERIORATED. HARTZELL C ONTACTED AND IS INVESTIGATING. 5 C P6EA 2000040400491 20000404 00491 CE 2000 4 4 20000329SH047 1 20000224 G 2910 631700348 TUBE CESSNA 525 525 2076601 CE HYD SYSTEM CRACKED H O OTHER K J FLUID LOSS WARNING INDICATION TX TAXI/GRND HDL 1 SW 99 49CJ 2467 5250049 AFTER LANDING GEAR RETRACTION, BOTH HYDRAULIC FLOW AND LOW PRESSURE ANNUNCIATOR LIGHTS ILLUMINATED. FLIGHT WAS ABORTED AND DIVERTED BACK TO PHF (ORIGINATING AIRPORT). LANDING GEAR WAS EXTENDED BY THE EMERGENCY EXTENSION SYSTEM WITH NO FUR THER ABNORMALTIES. MAIN SYSTEM HYDRAULIC FAILURE AS A RESULT OF CRACKED PRESSURE SUPPLY TUBE, PN 6317003-48, TO LOADING VALVE (BYPASS VALVE). FAILED TUBES REPLACED WITH FACTORY-NEW PARTS. LANDINGS: 3,710. 1 L 7 2 4F RT A1WI 2000040400492 20000404 00492 CE 2000 4 4 20000329SH048 1 20000316 G 2822 5100003 PUMP CESSNA 172 172R 2072401 CE LYC IO360 IO360L2A EA FUEL BOOST INOPERATIVE H O OTHER O OTHER NR NOT REPORTED 1 SW 99 416ER 443 17280281 L2732651A THE CREW REPORTED THE ELECTRIC BOOST PUMP INOPERABLE. THE PUMP WAS REPLACED. THIS PUMP ROUTINELY FAILS IN THIS FLEET O F 172R AIRCRAFT, AND IN MOST CASES, PRODUCES METAL THAT CONTAMINATED THE FUEL INJECTION COMPONENTS. (X) 1 H 7 1 3O 3 O NT 3A12 1E10 2000040400509 20000404 00509 GL 2000 4 4 20000330SH001 1 20000131 G 2720 14D01 PEDAL AMTR KITFOX KITFOXIV 05620EP GL RUDDER CONTROL BROKEN H O OTHER O OTHER NR NOT REPORTED 1 SW 99 423GB 194 JCU106 RIGHT RUDDER PEDAL SEPARATED FROM TORQUE TUBE. THE AREA WHERE THE TORQUE TUBE AND RUDDER PEDAL ARE ATTACHED CRACKED BEL OW THE WELD. THIS WAS CRACKED PRIOR TO THE INCIDENT. WHEN HARD RIGHT RUDDER PEDAL WAS APPLIED, IT BROKE AND SPLIT TOR QUE TUBE LOOSING CONTROL OF AIRCRAFT. (X) 1 H 7 1 3I NC EXPA 2000040400510 20000404 00510 EA 2000 4 4 20000330SH002 2 20000306 G 8500 CASE MOONEY M20 M20E 5870212 SW LYC O360 IO360A1A 41514 EA ENGINE CRACKED H K NONE K FLUID LOSS IN INSP/MAINT 1 SW 99 3419X 3270 1250 1118 L230151A PILOT NOTED OIL LEAK. DURING INSPECTION FOR OIL LEAK, ENGINE CASE WAS FOUND CRACKED BELOW NR 1 CYLINDER BASE PAD. CRAC K IS APPROXIMATELY 4.5 INCHES PARALLEL TO CYLINDER PAD. ALSO FOUND NR 1 INTAKE TUBE LOOSE. 1 L 7 1 3O 3 O 2A3 1E10 2000040400511 20000404 00511 SO 2000 4 4 20000330SH003 1 20000306 G 3230 762554 ROD END WIEBEL 21151 PIPER PA31 PA31350 7103110 SO MLG FAILED D A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 GL 23 628HA 11364 WTC2949 317952085 RIGHT MAIN LANDING GEAR FAILED TO RETRACT AFTER TAKEOFF. AFTER NUMEROUS ATTEMPTS AND AFTER PERFORMING A MANUAL EXTENSIO N OF GEAR, A GREEN LIGHT COULD NOT BE OBTAINED ON THE RIGHT GEAR. AFTER A GROUND VISUAL CHECK, IT APPEARED GEAR WAS DOW N. A LANDING WAS PERFORMED, AND AFTER ROLL-OUT, RIGHT LANDING GEAR COLLAPSED. AIRCRAFT RECEIVED MINOR DAMAGE. UPON IN SPECTION, DISCOVERED THE ROD END HAD BROKE OUT ON THE RT MAIN GEAR ACTUATOR. ROD END FAILED JUST AFTER UNLOCKING THE RT GEAR AT A POINT IN WHICH GEAR WOULD NOT FALL BACK INTO A LOCK POSITION. (X) 1 L 7 2 3O A20SO 2000040300015 20000403 00015 CE 2000 4 3 20000330SH004 1 20000201 G 7810 HS783820041 CLAMP RAYTHN DH125 HAWKER800XP CE TAIL PIPE CHAFED B G1FR O OTHER O OTHER NR NOT REPORTED 1 GL 13 139M 258330 CHAFE DAMAGE OCCURRED TO BOTH ENGINE TAILPIPE V-CLAMPS PN 234-559-9019 (IPC REF 78-10-01, FIG 1, ITEM 15) AND INNER CORE COWL CHAFE BRACKET PN HS7838200-41 (IPC REF 78-30-05A, ITEM 245). EACH ENG CONTAINS 8 BRACKETS AND 1 V-CLAMP. DAMAGE HAS OCCURRED AT SOME OR ALL BRACKET MOUNT LOCATIONS WITH APPROX .020 INCH TO .090 INCH DEPTH WITH TOTAL EDGE SPAN OF 0.3 75 INCH ON THE BRACKETS AND APPROX .010 INCH TO .025 INCH DEPTH AT CONTACT LOCATIONS ON V-CLAMP. THIS DAMAGE DISCOVERE D DURING UNSCHEDULED DISASSEMBLY AND REMOVAL OF ENGINES. REPLACE V-CLAMP AND DRESS FWD EDGE OF CHAFE PAD BRACKETS TO AL LOW CLEARANCES OF .050 INCH MIN. 2 L 7 2 4F RT A3EU 2000040400512 20000404 00512 EU 2000 4 4 20000330SH005 1 20000308 G 2460 TB2061238001 SWITCH SOCATA TB20 TB21 8680697 EU ELECTRICAL FAILED H K NONE O OTHER IN INSP/MAINT 1 EA 07 30582 45 1618 INTERNAL ELECTRICAL FAILURE OF PRESSURE SWITCH AT 44.8 HOURS. THIS IS THE 7TH SWITCH INSTALLED IN THIS AIRCRAFT. SWITC H FAILURE IS A MIXTURE OF ELECTRICAL AND MECHANICAL (LEAKAGE). 1 L 7 1 3O RT A51EU 2000040400513 20000404 00513 EA 2000 4 4 20000330SH006 2 20000322 G 8550 LW14729 DIPSTICK PIPER PA32 PA32RT300T 7103216 SO LYC O540 TIO540C1A 41532 EA OIL CAP SEPARATED H O OTHER K J FLUID LOSS WARNING INDICATION TX TAXI/GRND HDL 1 SW 99 9452C 206 32R7887006 L527061A PILOT REPORTED TO REPAIR SHOP, THAT AFTER LANDING, HE HAD AN OIL LEAK IN THE ENGINE AREA. AFTER INSPECTION, FOUND THAT DIP ROD IN THE OIL CAP WAS NOT INSTALLED IN THE CAP AND HAD FALLEN DOWN INTO THE OIL FILL TUBE OF THE ENGINE. UNDER INS PECTION WITH A MAGNIFYING GLASS, NO SIGNS THE ROLL PIN THAT SHOULD HAVE BEEN INSTALLED TO HOLD THE ROD INTO THE CAP HAD EVER BEEN INSTALLED. THIS ENGINE HAD BEEN OVERHAULED BY THE LYCOMING FACTORY, AND WAS NOT AN AFTER MARKET OVERHAUL. 1 L 7 1 3O 3 O A3SO E14EA 2000040400514 20000404 00514 NE 2000 4 4 20000330SH007 2 20000211 G 7250 2A227401 BEARING IAE V2528 V2528D5 NE NR 4 DAMAGED A WA2D K NONE O OTHER IN INSP/MAINT 1 NE 03 1320 V20006 ENGINE RECEIVED FOR THIRD LPT BLADE DAMAGE. DISASSEMBLY INSPECTION REVEALED FLOODED NR 4 BEARING AREA/POSSIBLE FIRE AND CONTACT BETWEEN T2 DISK AND 1-2 AIR SEAL. (X) 4 F E40NE 2000040400515 20000404 00515 NE 2000 4 4 20000330SH008 2 20000211 G 7250 2A227401 BEARING IAE V2528 V2528D5 NE NR 4 DAMAGED B WA2D K NONE O OTHER IN INSP/MAINT 1 NE 03 1320 V20006 ENGINE RECEIVED FOR 3RD LPT BLADE DAMAGE. DISASSEMBLY INSPECTION REVEALED FLOODED NR 4 BEARING AREA/POSSIBLE FIRE AND C ONTACT BETWEEN T2 DISK AND 1-2 AIR SEAL. (X) 4 F E40NE 2000040400516 20000404 00516 CE 2000 4 4 20000330SH009 1 20000330 G 3230 204101738 PLUNGER CESSNA 177 177RG 2073709 CE LT MLG SOLENOID MALFUNCTIONED D O OTHER O OTHER NR NOT REPORTED 1 SW 03 1873Q 177RG0273 WHEN THE GEAR WAS RETRACTED, THE SOLENOID PLUNGER EXTENSION WAS NOT PULLING THE DOWNLOCK MECHANISM COMPLETELY OPEN. WHE N THE GEAR WAS THEN EXTENDED AND THE GEAR HIT THE DOWNLOCK MECHANISM, IT WOULD DRIVE IT OVERCENTER BACKWARDS. REPLACING WORN PARTS FIXED THE PROBLEM. (X) 1 H 7 1 3O A20CE 2000040400517 20000404 00517 SO 2000 4 4 20000330SH010 1 20000308 G 2710 CONTROL CABLE AMRGEN AA5 AA5A 3960106 SO PULLEY CLUSTER DAMAGED D K NONE O OTHER IN INSP/MAINT 1 GL 15 26086 3500 AA5A0326 DURING ANNUAL INSPECTION, FOUND CABLES DETERIORATED AND FRAYED AS WOULD BE FOUND IF INSPECTING SERIES AS AN AA1, AS SPEC IFIED IN AD 72-6-2. AS THE REST OF THE GRUMMAN SINGLE ENGINE FLEET HAS SIMILAR CABLE RUNS AS THE AA1 SERIES AND THE EAR LY AA5''''S WITH EARLIER S/N''''S, AD 72-06-02 SHOULD BE AMENDED TO INCLUDE ALL TYPE SERIES THAT EMPLOY THE SIMILAR PULL EY CLUSTER JUST AHEAD OF THE FRONT SPAR IN THE CABIN. WEAR APPEARS TO BE FROM NORMAL OPERATIONS/AGE OF CABLES. NORMAL ACCUMULATIONS OF DEBRIS AND DIRT IN AREA OF PULLEYS AND THE PULLEYS WERE NOT FROZEN. DUE TO THIS INSTALLATIONS DESIGN. 1 L 7 1 3O A16EA 2000040400518 20000404 00518 SO 2000 4 4 20000330SH011 2 20000215 G 8520 630826 BEARING CESSNA 210 210L 2073448 CE CONT O520 IO520* 17032 SO CRANKSHAFT CRAZED H K NONE O OTHER IN INSP/MAINT 1 SW 99 4667Q 21059567 DURING ENGINE TEAR DOWN DUE TO SUDDEN STOPPAGE. INSPECTION OF THE BEARINGS FOUND 7 OUT OF 12 BEARING HALVES FOUND WITH EXCESSIVE CRAZING ON THE SURFACE. ENGINE WAS ASSEMBLED 12-28-99 AND PUT INTO SERVICE ON 1-29-00 AND WAS DISASSEMBLED 2- 25-00. SUBMITTER STATED CAUSE AND PREVENTION UNKNOWN. (X) 1 H 7 1 3O 3 O 3A21 E5CE 2000040400519 20000404 00519 SO 2000 4 4 20000330SH012 2 20000215 G 8520 653547 BEARING CESSNA 210 210L 2073448 CE CONT O520 IO520L 17032 SO CRANKSHAFT DAMAGED H K NONE O OTHER IN INSP/MAINT 1 SW 99 4667Q 45 21059567 295047R DURING ENGINE TEAR DOWN DUE TO SUDDEN STOPPAGE, INSPECTION OF THE BEARINGS FOUND 4 OUT OF 10 BEARING HALVES WERE FOUND W ITH EXCESSIVE CRACKING ON THE SURFACE. ENGINE WAS ASSEMBLED 12-28-99, AND PUT INTO SERVICE ON 1-29-00, AND WAS DISASSEM BLED 2-25-00. CAUSE AND PREVENTION UNKNOWN. (X) 1 H 7 1 3O 3 O 3A21 E5CE 2000040400520 20000404 00520 CE 2000 4 4 20000330SH013 1 20000313 G 2731 C419175 LINK CESSNA 500 550 2076604 CE PEDESTAL BENT G O OTHER F FLT CONT AFFECTED NR NOT REPORTED 1 GL 15 7ZU 6135 5500433 AIRCRAFT''S PITCH TRIM JAMMED IN-FLIGHT AND A SUCCESSFUL LANDING WAS MADE. UPON INSPECTION, MECHANICS FOUND THE SAFETY CLIP THAT HOLDS TH MASTER LINK TOGETHER CAME OFF AND THEN BENT THE MASTER LINK. THE MASTER LINK IS PART OF A CHAIN ASSY LOCATED IN THE PEDESTAL OF THE COCKPIT TRANSFERRING THE MOTION OF THE ELEVATOR TRIM WHEEL TO TEH CABLE SYSTEM. THE CHA IN ASSY WAS REPLACED AND SYSTEM WORKED FINE. SUBMITTER STATED SPECIAL ATTENTION SHOULD BE ADDRESSED TO THE MASTER LINK ON PHASE 5 INSPECTIONS. 1 L 7 2 4F A22CE 2000040400522 20000404 00522 WP 2000 4 4 20000330SH015 2 20000117 G 7230 30756451 CARBON SEAL LEAR 35 36A 5170603 CE GARRTT TFE731 TFE73122B 01518 WP ENGINE FAILED B IY2R O OTHER X J ENGINE FLAMEOUT WARNING INDICATION NR NOT REPORTED 1 SW 15 32AJ 231 36A048 P89174 ENGINE EXPERIENCED IN-FLIGHT SHUTDOWN 230.5 HRS FOLLOWING CZI (COMPRESSOR ZONE INSP) AND INSTALL OF NEW STYLE CARBON SEA LS PER SB 72-3596 REV 7. ENG TEARDOWN REVEALED FAILURE OF PLANETARY GEAR BEARINGS, PLANETARY GEARS, SUN GEAR, AND RING GEAR. FAILURE CAUSED BY OIL STARVATION TO PLANETARY ASSY DUE TO BLOCKAGES OF PLANETARY OIL MANIFOLDS OIL JET STRAINER, PN 894764-3. THE HAT SHAPED STRAINER WAS PACKED WITH CARBON WHICH REDUCED OIL FLOW TO PLANETARY GEAR AREA. ENG TOTALLY DISASSEMBLED TO ACCOMPLISH LUBRICATION CONTAMINATION INSP AND DETERMINE WHICH COMP GENERATED CARBON PARTICLES. PARTICL ES TRACED TO NEW NR 5 CARBON SEAL PN 3075645-1, SN 9919366801122. (X) 2 L 7 2 4F 4 F A10CE E6WE 2000040400523 20000404 00523 NM 2000 4 4 20000330SH016 1 20000204 G 3242 BRAKE BOEING 747 747212B 1384886 NM MLG OVERHEATED B GK4Y O OTHER A J FLAME/FIRE WARNING INDICATION TX TAXI/GRND HDL 1 WP 03 482EV 20713 ON ARRIVAL, LT WING AND BODY GEAR WHEEL BRAKES OVERHEATED. NR 4 WHEEL ASSY IGNITED, BUT WAS IMMEDIATELY EXTINGUISHED. NR 6 AND NR 7 WHEEL ASSY THERMAL FUSE PLUGS RELIEVED AND WHEELS DEFLATED. INSP OF GEAR AREAS CARRIED OUT OK AND MAIN WH EELS REPLACED (4, 6, AND 7). (X) 2 L 7 4 4F A20WE 2000040300016 20000403 00016 NE 2000 4 3 20000330SH017 2 20000128 G 7230 BLADE BOEING 747 747121 1384871 NM PWA JT9 JT9D7A 52054 NE NR 1 ENGINE BENT B K NONE O OTHER IN INSP/MAINT 1 WP 03 480EV 20348 DURING WALKAROUND INSPECTION, SEVEN N1 FAN BLADES WERE FOUND BENT BEYOND LIMITS ON NR 1 ENGINE. AIRCRAFT WAS GROUNDED N AN. FAN BLADES WERE REPLACED AND TEST RUN CARRIED OUT BY EVERGREEN. (X) 2 L 7 4 4F 4 F A20WE E20EA 2000040400524 20000404 00524 WP 2000 4 4 20000330SH018 2 20000229 G 7314 31080261 PUMP GARRTT TPE331 TPE331* 01514 WP DRIVE GEAR FROZEN B UO2R O OTHER O OTHER NR NOT REPORTED 1 GL 19 13285 P66294 PUMP FROZE DURING FLIGHT STRIPING DRIVE GEAR. (X) 3 T E2WE 2000040400525 20000404 00525 SO 2000 4 4 20000331SH001 1 20000313 G 3242 1331096 STATOR BFGOODRICH EMB 120 EMB120 3260201 SO BRAKE ASSY BROKEN B O OTHER O OTHER NR NOT REPORTED 1 SO 19 0207 BRAKE ASSY, PN 2-1585, FAILED PREMATURELY. NR 1 STATOR BROKEN AND BINDING IN TORQUE TUBE KEY SLOTS. THIS IS A CONTINUA L DISCREPANCY. BRAKE ASSY SHOULD LAST 2,500 CYCLES. NOTE: OEM PARTS INSTALLED IN BRAKE ASSY AND THE MOST RECENT BRAK E CONFIGURATION, PN 2-1585. (X) 2 L 7 2 4T RT A31SO 2000040600061 20000406 00061 WP 2000 4 6 20000331SH002 2 20000301 G 7250 30720705 DISK GARRTT TFE731 TFE731* 01518 WP LP TURBINE NICKED B K NONE O OTHER IN INSP/MAINT 1 GL 19 NEW PART RECEIVED FROM HONEYWELL WITH TWO SMALL NICKS IN WEB AREA FORWARD SIDE AND DAMAGE IN POST FIR TREE AREA ON BOTH SIDES. (X) 4 F E6WE 2000040600062 20000406 00062 2000 4 6 20000331SH003 4 20000225 G 2561 LIFE VEST EAAEROMARINE CABIN FAILED B CHIR K NONE L NO TEST IN INSP/MAINT 1 NM 09 88682 WHILE ATTEMPTING TO INFLATE THIS DUAL CELL ADULT LIFE PRESERVER, BOTH TOGGLES WERE PULLED SIMULTANEOUSLY. THE BACK CELL INFLATED CORRECTLY, THE FRONT CELL FAILED TO INFLATE DUE TO THE ACTUATING LEVER PULLING OUT OF INFLATOR ASSEMBLY HOUSIN G ALLOWING INFLATOR PIN AND SPRING TO FALL OUT OF ASSEMBLY WITHOUT BREAKING SEAL ON CO2 CARTRIDGE. DISASSEMBLY OF BOTH THE GOOD AND FAILED INFLATOR ASSEMBLIES AND COMPARISON OF THE 2 ACTUATING ARM RETAINER PINS SHOWED THE FAILED ASSEMBLY P IN WAS APPROX 0.092 INCH SHORTER THAN THE RETAINER PIN OUT OF THE GOOD ASSY. NOTE THAT BOTH OF THESE PINS ARE STEEL. T HIS VEST IS NOT AFFECTED BY EAM SB SBV-25-2 BY DATE OF MFG AND HAVING STEEL PINS. (X) 2000040400526 20000404 00526 EU 2000 4 4 20000331SH004 1 20000315 G 3260 SP3982 UPLOCK SWITCH AMD FALCON FALCON20 2730103 EU MLG FAILED D O OTHER O OTHER NR NOT REPORTED 1 GL 11 120TF 1 213 384 TWO NEW SWITCHES WERE INSTALLED IN THE LT MAIN GEAR DOOR UPLATCH. (BOTH ARE SAME P/N AND DATE OF MFG). ONE SWITCH CONT ROLS THE RED DOOR UNLOCK LIGHT, AND THE OTHER CONTROLS DOOR AND GEAR SEQUENCING. THE GEAR WAS CYCLED SUCCESSFULLY NUMER OUS TIMES WITH THE ACFT ON JACKS, WHEN THE CREW ATTEMPTED TO EXTEND THE GEAR ON THE SECOND FLIGHT, BOTH NEW SWITCHES FAI LED. THIS CAUSED 2 PROBLEMS. THERE WAS NO INDICATION IN THE COCKPIT THAT THE LT MAIN DOOR OPENED. (NO RED LIGHT). TH E CREW WAS ABLE TO SEE THE LT GEAR DID EXTEND FROM THE COCKPIT PROVING THE DOOR HAD OPENED. AFTER LANDING, THE CREW THE N NOTICED THE LT DOOR HAD REMAINED IN THE OPEN POSITION. THIS WAS CAUSED BY THE FAILURE OF THE SECOND SWITCH. (X) 2 L 7 2 4F RT A7EU 2000040600065 20000406 00065 CE 2000 4 6 20000331SH007 1 20000304 G 2140 AHE85D421 SHUTOFF VALVE CESSNA 414 414A 2075907 CE HEATER FAILED B MI2R O OTHER O OTHER NR NOT REPORTED 1 CE 07 119SK 10 2008052 414A0660 VALVE WILL NOT SHUT OFF THE FUEL TO THE HEATER AND CAUSED HEATER TO OVERHEAT. (X) 1 L 7 2 3O A7CE 2000040600066 20000406 00066 WP 2000 4 6 20000331SH009 2 20000307 G 7250 30723515 DISK GARRTT TFE731 TFE731* 01518 WP LP TURBINE DAMAGED B K NONE O OTHER IN INSP/MAINT 1 GL 19 NEW PART RECEIVED FROM HONEYWELL WITH DAMAGE IN POST-FIR TREE AREA. (X) 4 F E6WE 2000040600068 20000406 00068 CE 2000 4 6 20000331SH010 2 20000310 G 7414 PLATE SLICK MOONEY M20 M20K 5870220 SW CONT O360 TSIO360MB 17025 CE MAGNETO MOUNT MISMANUFACTURED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 NE 03 252BA 631 95030022 251122 317134 WHEN LT AND RT MAGNETOS WERE BEING INSTALLED ON ENGINE AFTER INTERNAL INSPECTION OF MAGNETOS, NOTED MAGNETO HOLD-DOWN PL ATES FROM ENGINE STUD TO MAGNETO MOUNTING FLANGE ONLY ENGAGED FLANGE BY APPROXIMATELY .0625 INCH IF MOUNTED EVEN, OR ONL Y ONE CORNER OF PLATE IF COCKED TO ONE SIDE. SUBMITTER STATED MOUNTING PLATES ARE TYPE NORMALLY SENT WITH NEW MAGNETOS. ORDERED 4 EACH TCM, PN 630535, MOUNT PLATES AND INSTALLED, FIT GOOD. (X) 1 L 7 1 3O 3 O 2A3 E9CE 2000040600069 20000406 00069 CE 2000 4 6 20000331SH011 2 20000310 G 7414 PLATE SLICK MOONEY M20 M20K 5870220 SW CONT O360 TSIO360MB 17025 CE MAGNETO MOUNT MISMANUFACTURED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 NE 03 252BA 97030194 251122 317134 WHEN LT AND RT MAGNETOS WERE BEING INSTALLED ON ENGINE AFTER INTERNAL INSPECTION OF MAGS, NOTED MAGNETO HOLD-DOWN PLATES FROM ENGINE STUD TO MAGNETO MOUNTING FLANGE ONLY ENGAGED FLANGE BY APROXIMATELY .0625 INCH IF MOUNTED EVEN, OR ONLY ONE CORNER OF PLATE IS COCKED TO ONE SIDE. SUBMITTER STATED MOUNTING PLATES ARE TYPE NORMALLY SENT WITH NEW MAGNETOS. ORD ERED 4 EACH TCM PN 630535 MOUNT PLATES AND INSTALLED, FIT GOOD. (X) 1 L 7 1 3O 3 O 2A3 E9CE 2000040400540 20000404 00540 2000 4 4 20000331SH012 4 20000301 G 3416 060030620000 ALTIMETER BEECH 1900 1900D 1154162 CE COCKPIT MALFUNCTIONED B GLBR O OTHER O OTHER NR NOT REPORTED 1 CE 01 220GL 148 UE220 PILOT WRITE UP WAS ''STICKS SEVERAL THOUSAND FEET'', CALIBRATION WAS OUT AT -1,000 AND ZERO FEET AND 500 FEET, ENCODER F UNCTIONS PROPERLY, COULD NOT VERIFY OR DUPLICATE STICKING. ALTIMETER WAS 40 FEET LOW AT -1,000 FEET AND PROGRESSIVELY G OT BETER. AT +1,000 FEET WAS ZERO ERROR AND WITHIN LIMITS FOR REST OF TEST. (X) 2 L 7 2 4T RT A24CE 2000040400541 20000404 00541 2000 4 4 20000331SH013 4 20000223 G 3422 6226136002 GYRO BEECH 1900 1900D 1154162 CE COCKPIT INOPERATIVE B GLBR O OTHER O OTHER NR NOT REPORTED 1 CE 01 245GL 682 UE245 CAPTAIN''S DIRECTIONAL GYRO INOPERATIVE. NR 1 GYRO LOCKED UP. (X) 2 L 7 2 4T RT A24CE 2000040600070 20000406 00070 CE 2000 4 6 20000331SH014 1 20000315 G 3233 993880081 ACTUATOR BEECH 99 C99 1154006 CE MLG CRACKED B O OTHER K FLUID LOSS NR NOT REPORTED 1 NM 11 216CS 72 U216 HYDRAULIC FLUID FOUND IN WHEELWELL DURING POST-FLIGHT INSPECTION. LANDING GEAR RETRACTION PERFORMED, FOUND 2 INCH CRACK AROUND TOP OF ACTUATOR. ACTUATOR OVERHAULED. (X) 1 L 7 2 3T A14CE 2000040400542 20000404 00542 NM 2000 4 4 20000331SH015 1 20000306 G 3244 26066712 TIRE BOEING 737 737* NM MLG FAILED H O OTHER O OTHER NR NOT REPORTED 1 SW 09 TIRE FAILURE. OVERLOAD DUE TO ADJACENT FAILURE. PENDING COMPLETION OF INVESTIGATION. (X) 2 L 7 2 4F RT A16WE 2000040400543 20000404 00543 NM 2000 4 4 20000331SH016 1 20000306 G 3244 H405X145 TIRE BOEING 737 737* NM MLG FAILED H O OTHER O OTHER NR NOT REPORTED 1 SW 09 B9125 TIRE FAILURE, THROWN TREAD. (X) 2 L 7 2 4F RT A16WE 2000040400544 20000404 00544 EU 2000 4 4 20000331SH017 1 20000308 G 3213 7216FR964T SEAL JETAIR JETSTM JETSTM4101 1500501 EU MLG FAILED B FWIR O OTHER K FLUID LOSS NR NOT REPORTED 1 NE 03 306UE APB970039 41020 4046 CSN MFG - 4-97. UNIT LEAKING FROM GLAND SEAL (PREMATURE FAILURE). SEAL FOUND ERODED ON OUTBOARD SIDE BETWEEN SEAL SURFACE AND BACK-UP. THIS IS ONE EXAMPLE OF NUMEROUS UNITS RETURNED FOR REPAIR AFTER 3,000 - 5,000 CYLES WHEN THE OVER HAUL CYLINDER IS 12,000 TO 24,000 DEPENDING ON A/C UNITS WERE MFG IN 1997. MFG OF SEAL SAID RAMRODS WERE AT FAULT, MFG OF UNIT THOUGHT THE SEAL WAS BAD. NO RESOLUTION TO PROBLEM. CONDITION AS OCCURRED IN BOTH JS41 AND SAAB340B UNITS (AIR 886410-1 AND AIR86414-1). (X) 2 L 7 2 4T RT A41NM 2000040600071 20000406 00071 CE 2000 4 6 20000331SH019 1 20000303 G 7120 H30024 SHOCK MOUNT CESSNA 336 336 2075602 CE CONT O360 IO360A 17025 SO FIREWALL FAILED H O OTHER O OTHER TX TAXI/GRND HDL 1 SW 99 3856U 1841 33610156 DIFFICULT TO INSPECT. PILOT HEARD AND NOTICED COWL RUBBING PROPELER SPINNER DURING SHUT DOWN AT FUEL PIT AT MADERA AIRP ORT. (X) 1 H 7 2 3O 3 O A2CE E1CE 2000040600072 20000406 00072 CE 2000 4 6 20000331SH020 1 20000303 G 3246 4075 WHEEL CESSNA 336 336 2075602 CE MLG DAMAGED H O OTHER O OTHER NR NOT REPORTED 1 SW 99 3856U 1830 3360156 BOLTS BENT WHEEL HOLES ELONGATED DUE TO WEIGHT OF AIRCRAFT AND SHORT FIELD LANDINGS. AIRCRAFT USED FOR SEARCH AND RESCU E PLUS TRAINING IN FRESNO COUNTY SHERIFF''S AIR SQUADRON. NOTE: WHEEL STATIC LOAD 1,800 POUNDS. (X) 1 H 7 2 3O A2CE 2000040600073 20000406 00073 EA 2000 4 6 20000331SH021 2 20000312 G 8500 ENGINE CESSNA 172 172R 2072401 CE LYC IO360 IO360L2A EA NOSE ROUGH H O OTHER E J VIBRATION/BUFFET WARNING INDICATION CR CRUISE 1 SW 99 410ER 17280257 LW2722651A6 THE ENGINE WAS REPORTED ROUGH IN CRUISE. CORRECTIVE ACTION WAS TAKEN AND THE AIRCRAFT WAS RETURNED TO SERVICE. (X) 1 H 7 1 3O 3 O NT 3A12 1E10 2000040400546 20000404 00546 CE 2000 4 4 20000331SH022 1 20000310 G 2133 66001983 VALVE LEAR 35 35A 5170602 CE FLOW CONTROL FAILED B O9IR A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 NM 09 45AE 2704 422 AIRCRAFT CABIN DID NOT PRESSURIZE WHEN DEPARTING. AIRCRAFT RETURNED TO LAS VEGAS FOR REPAIR. CABIN FLOW CONTROL VALVE WAS FOUND DEFECTIVE. AN OVERHAULED CABIN FLOW CONTROL VALVE WAS INSTALLED. GROUND RUNS STILL WERE NOT SATISFACTORY. F URTHER INVEST REVEALED THE K2 RELAY ON THE PCB1 SQUAT SWITCH RELAY PANEL TO BE INTERMITTENT. THIS RELAY WAS ALSO CHANGE D. FUNCTIONAL CHECK OF THE PRESSURIZATION SYSTEM REVEALED NO FURTHER DISCREPANCIES. THE DEFECTIVE COMPONENTS ARE ''ON CONDITION'' ITEMS WITHOUT SCHEUDLE REPLACEMENT OR OVERHAUL. A COMPLETE PRESSURIZATION CHECK WAS COMPLETED AS PART OF TH E LAST C-CHECK (1200 HOUR INSP). NO DEFECTS WERE NOTED AT THAT TIME (5-13-98, ACTT 4,540.7 HRS). ACFT TT 5,360.1 HRS.( 2 L 7 2 4F A10CE 2000040600074 20000406 00074 SO 2000 4 6 20000331SH023 2 20000120 G 8530 STUD BENDIX CESSNA 182 182Q 2072732 CE CONT O470 O470U 17026 SO ENGINE CYLINDER BROKEN H K NONE O OTHER IN INSP/MAINT 1 GL 03 42RH 10 18266776 820036R NEW REBUILT ENGINE PURCHASED FROM CONTINENTAL. 10.6 HOURS AFTER INSTALLATION, NR 4 CYLINDER, NR 2 AND NR 3 CYLINDER MOU NTING STUDS BROKE. NR 5 AND NR 6 MISSING NUTS. (TORQUE WAS CHECKED ON ALL OTHER CYLINDERS AND FOUND OK). SAME ENGINE UPON INSTALLATION REQUIRED THE REPLACMENT OF THE RIGHT MAGNETO AT ZERO HOURS. (X) 1 H 7 1 3O 3 O NT 3A13 E273 2000040600075 20000406 00075 GL 2000 4 6 20000331SH024 3 20000301 G 6111 BLADE CESSNA 210 P210N 2073454 CE MCAULY D3A34 D3A34C402 GL PROPELLER MISOVERHAULED B K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 01 4783K 3607 115 P21000314 797073 PROPELLER VIBRATING AFTER RECENT OVERHAUL. DYNAMIC BALANCING HELPED. FOUND 7 AN 97-3 WASHERS FOR DYNAMIC BALANCE ADDED 6 MORE TO BRING BALANCE TO A 1 IPS. ALSO FOUND 6 STATIC WEIGHTS IN SAME LOCATION. REMOVED PROP FROM AIRCRAFT TO CHECK STATIC BALANCE. COULD NOT. MEASURED BLADES AT 30.25 INCHES, 33.25 INCHES, AND 36.25 INCHES STA. FOUND ALL 3 BLADES U NDER MINIMUM WIDTH AT 30.25 INCHES STA. BLADE NR 1, 5,803, NR 2 5,775, NR 3, 5,820 (MIN AT 30.25 INCHES IS 5.825. (X) 1 H 7 1 3O 3A21 5 C P47GL 2000040600076 20000406 00076 SO 2000 4 6 20000331SH025 2 20000306 G 8530 STUD CESSNA 421 421 2076010 CE CONT O520 GTSIO520N 17032 SO NR 5 CYLINDER FAILED B K NONE O OTHER IN INSP/MAINT 1 GL 13 421CH 628 4210176 277018R DURING INSPECTION OF OIL LEAK, FOUND NR 5 CYLINDER BASE FRONT LOWER MOUNT STUD BROKEN. POSSIBLY, THE STUD WAS HARD AND BROKE UNDER STRESS. (X) 1 L 7 2 3O 3 O RT A7CE E7CE 2000040600077 20000406 00077 CE 2000 4 6 20000403SH001 1 20000114 G 8120 AE366303760274 HOSE CESSNA 206 T206H CE TURBOCHARGER BURNED H O OTHER O OTHER NR NOT REPORTED 1 CE 03 7264H 24 T20608103 SCAVENGE OIL HOSE TO TURBOCHARGER BURNED UP BY EXHAUST PIPE. USED ALTERNATE ROUTE TO BYPASS EXHAUSE PIPE. (X) 1 H 7 1 3O A4CE 2000040600078 20000406 00078 SO 2000 4 6 20000403SH002 2 20000306 G 8530 STUD CESSNA 421 421C 2076016 CE CONT O520 GTSIO520N 17032 SO ENGINE FAILED B AZOR O OTHER K FLUID LOSS NR NOT REPORTED 1 GL 13 421LH 128 421C1207 292129R DURING NORMAL ENGINE OPERATION, NOTICED OIL LEAK ON FRONT OF ENGINE. AFTER CLEANING AND INSPECTION, FOUND THE FRONT THR OUGH-STUD BROKEN. POSSIBLE CAUSE COULD BE IMPROPER HARDENING OF THE BOLT. (X) 1 L 7 2 3O 3 O A7CE E7CE 2000040600080 20000406 00080 SO 2000 4 6 20000403SH006 2 20000225 G 8500 ENGINE BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO RIGHT MAKING METAL B BSYR C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 GL 07 7383R TH502 ATL - RIGHT ENGINE PROPELLER WENT INTO FEATHER ON TAKEOFF. FOUND ALUMINUM PLUGGING PROPELLER SCREEN. REMOVED AND REPLA CED ENGINE. SUBMITTER STATED CAUSE UNKNOWN AT THIS TIME. (X) 1 L 7 2 3O 3 O 3A16 E5CE 2000040500006 20000405 00006 WP 2000 4 5 20000403SH007 2 20000229 G 7200 30756842 RETAINER AMD FALC50 FALCON900 2700160 EU GARRTT TFE731 TFE7315BR WP ENGINE BROKEN B UO2R K NONE O OTHER IN INSP/MAINT 1 GL 19 75V 697 13 P95151 DISASSEMBLED ENGINE BECAUSE OF BAD S.O.A.P. SAMPLE. FOUND NR 3 SEAL RUNNER RETAINER BROKEN. (X) 2 L 7 3 4F 4 F RT A46EU E6WE 2000040500007 20000405 00007 EU 2000 4 5 20000403SH008 1 20000306 G 3710 25VF3323309 LINE BRAERO DH125 BAE125800A 1500285 EU VACUUM SYSTEM CUT H O OTHER O OTHER NR NOT REPORTED 1 GL 09 89NC 4211 258102 VACUUM LINE FOR THE PRESSURIZATION SYSTEM LINE, PN 25VF3323-309, RUNS UNDER THE AILERON CABLE. THIS LINE IS .3750 INCH OUTSIDE DIAMETER HAD A CUT IN IT FROM CABLE .1875 INCH DEEP. CUSTOMER REPORTED HAVING PROBLEMS REGULATING PRESSURIZATIO N SYSTEM IN THE NORMAL OR EMERGENCY SYSTEM. (X) 2 L 7 2 4F RT A3EU 2000040600083 20000406 00083 SO 2000 4 6 20000404SH001 2 20000308 G 8530 652956 EXHAUST VALVE BLANCA 17 1730A 1220433 GL CONT O520 IO520K 17032 SO NR 1 CYLINDER WORN B CRJR K NONE O OTHER IN INSP/MAINT 1 CE 01 9606E 145 7630819 224130R EXCESSIVE WEAR FOUND DURING COMPRESSION TEST. EXHAUST VALVE WAS LEAKING. EX GUIDE MEASURED .4384 INCH AT THE TOP AND . 4624 INCH AT THE BOTTOM. EX VALVE MEASURED .4337 INCH AT THE TOP OF THE STEM AND .4263 INCH AT APPROX 2 INCHES FROM THE BOTTOM OF THE VALVE. CLEARANCE BETWEEN VALVE AND GUIDE IS .0361 INCH. SERVICEABLE LIMIT IS .006 INCH. NO METAL WAS F OUND IN THE OIL SCREEN. ENGINE IS NOT EQUIPPED WITH A SPIN ON FILTER. ALL OTHER CYLINDERS'' COMPRESSIONS TESTED OK. E NGINE WAS INSTALLED AFTER FACTORY REMAN IN JAN 98. M OR D SUBMITTED BY HAP''S AIR SERVICE AMES, IA. (X) 1 L 7 1 3O 3 O A18CE E5CE 2000040600084 20000406 00084 SO 2000 4 6 20000404SH002 2 20000308 G 8530 643767 GUIDE BLANCA 17 1730A 1220433 GL CONT O520 IO520K 17032 SO NR 1 CYLINDER WORN B CRJR K NONE O OTHER IN INSP/MAINT 1 CE 01 9606E 145 7630819 224130R EXCESSIVE WEAR FOUND DURING COMPRESSION TEST. EXHAUST VALVE WAS LEAKING. EX GUIDE MEASURED .4384 INCH AT THE TOP AND . 4624 INCH AT THE BOTTOM. EX VALVE MEASURED .4337 INCH AT THE TOP OF THE STEM AND .4263 INCH AT APPROX 2 INCHES FROM THE BOTTOM OF THE VALVE. CLEARANCE BETWEEN VALVE AND GUIDE IS .0361 INCH. SERVICEABLE LIMIT IS .006 INCH. NO METAL WAS F OUND IN THE OIL SCREEN. ENGINE IS NOT EQUIPPED WITH A SPIN ON FILTER. ALL OTHER CYLINDERS'' COMRPESSIONS TESTED OK. E NGINE WAS INSTALLED AFTER FACTORY REMAN IN JAN 98. M OR D SUBMITTED BY HAP''S AIR SERVICE, AMES, IA. (X) 1 L 7 1 3O 3 O A18CE E5CE 2000040600085 20000406 00085 CE 2000 4 6 20000404SH003 2 20000227 G 7320 RSA5AD SERVO PIPER PA34 PA34220T 7103420 SO CONT O360 TSIO360RB 17025 CE FUEL INJECTOR FAILED G O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION LD LANDING 1 WP 07 9299E 16 3449043 819256R ON BASE LEG TO GOODYEAR AIRPORT, THE LEFT ENGINE LAGGED POWER TO LANDING. A SAFE LANDING WAS MADE AND THE AIRCRAFT WAS TAKEN TO MAINTENANCE FOR INSP OF THE LEFT ENGINE. ON GROUND RUN-UP, FOUND THE LEFT ENGINE WAS RUNNING RICH AT LOW POWER SETTINGS. THE LEFT FUEL SERVO WAS REMOVED AND SENT TO TCM FOR WARRANTY. A NEW FUEL SERVO WAS INSTALLED FROM STOCK AND TRIM RUN COMPLETED, THE AIRCRAFT RETURNED TO SERVICE. (X) 1 L 7 2 3O 3 O A7SO E9CE 2000040500023 20000405 00023 EA 2000 4 5 20000404SH005 1 20000225 G 3240 7010FS9545708 SEAL CNDAIR CL600 CL6002B19 EA BRAKE ASSY LEAKING B XC4R K NONE K FLUID LOSS IN INSP/MAINT 1 SO 19 1451 BRAKE ASSY, PN 5010520-1, FAILED PREMATURELY. ONE EACH PISTON LEAKING FROM INSULATOR AREA. PISTON INTERNALLY FILLED WI TH FLUID. EVIDENCE OF T-SEAL FAILURE. THIS IS A CONTINUAL DISCREPANCY. FACTORY NEW BRAKE ASSY. NOTE: OEM PARTS INSTA LLED IN BRAKE ASSY AND THE MOST RECENT BRAKE CONFIGURATION, PN 5010520-1. (X) 2 L 7 2 4F RT A21EA 2000040600086 20000406 00086 CE 2000 4 6 20000404SH011 1 20000225 G 7602 S29991 BALL JOINT CESSNA 414 414A 2075907 CE MIXTURE CONTROL FAILED B AK6R O OTHER O OTHER NR NOT REPORTED 1 SW 19 692WT 100 414A0094 THIS BALL JOINT IS THE CONNECTION BETWEEN THE MIXTURE CABLE AND THE THROTTLE ASSY. WHEN THIS JOINT FAILS THERE IS NO MI XTURE CONTROL. SUBMITTER STATED THIS IS SECOND NEW BALL JOINT SEEN FAIL WITH VERY FEW HRS ON THE PART. SUBMITTER SUSPE CTED NEW PART USED TO REPLACE THIS DEFECTIVE ONE WILL FAIL PREMATURELY ALSO. THIS COULD BE A SERIOUS PROBLEM. (X) 1 L 7 2 3O A7CE 2000040600087 20000406 00087 CE 2000 4 6 20000404SH012 1 20000104 G 2510 08127358 CASTING CESSNA CESSNA 414 414A 2075907 CE COCKPIT SEAT FAILED D D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 SW 05 254TM 5500 414A0254 THE CAPTAIN HAD BOTH ENGINES RUNNING AT THE FBO WITH PARKING BRAKE SET. HE LEANED BACK IN HIS SEAT TO GET READY TO DEPA RT AND THE CASTING BROKE LANDING HIM FLAT ON HIS BACK, STRAPPED INTO THE SEAT WITH HIS PASSENGER IN THE CABIN. HE WAS U NABLE TO REACH THE PEDALS, YOKE, THROTTLES, WHEN PURCHASING A NEW PART AT THE CESSNA DISTRIBUTOR, THEY INDICATED THEY RE CENTLY WENT THROUGH 5 OF THESE. THE PART IS CAST AND CONTAINED A FLAW/POROSITY NOTED BY DISCOLORING INSIDE THE CASTING. (X) 1 L 7 2 3O A7CE 2000040500029 20000405 00029 CE 2000 4 5 20000404SH013 1 20000208 G 7500 66003353 GASKET LEAR 35 35LEAR 5170600 CE NR 1 ENGINE ERODED H A UNSCHED LANDING N FALSE WARNING CR CRUISE 1 SW 99 90WR 35022 DURING CRUISE FLIGHT, THE NR 1 ENGINE FIRE WARNING LIGHT ILLUMINATED. THE PILOT RETARDED POWER, AND LIGHT EXTINGUISHED. ADVANCING POWER AGAIN CAUSED THE LIGHT TO ILLUMINATE AGAIN, RETARDING POWER AGAIN CAUSED IT TO EXTINGUISH. AN UNEVENT FUL LANDING WAS MADE. UPON INVEST, MAINTENANCE FOUND THE BLEED AIR GASKET, PN 6600335-3, ERODED. THIS GASKET IS INSTAL LED BETWEEN THE BLEED AIR DUCT ASSY, PN 2655100-72, AND BLEED AIR FITTING ASSY, PN 2652083-25, ON THE RIGHT HAND SIDE OF THE ENGINE. THIS ALLOWED BLEED AIR TO ESCAPE WITH THE HOT GASSES HEATING UP THE NEARBY FIRE LOOP. GASKET REPLACED AND ACFT RETURNED TO SERVICE. (X) 2 L 7 2 4F A10CE 2000040500031 20000405 00031 NE 2000 4 5 20000404SH015 2 20000119 G 7310 MANIFOLD BOEING 777 777* UTILUSE NM PWA 4090 PW4090 52119 NE FUEL SYSTEM LEAKING H WA2D F C ACTIVATE FIRE EXT. ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 NE 03 EICRT 968 P222110 FIRE WARNING ON TAKEOFF, BOTTLES DISCHARGED, AIR TURN BACK. DISASSEMBLY INSPECTION REVEALED MANIFOLD NUT BACKED OFF, NO T SAFETY WIRED. PRATT & WHITNEY ENG/MFG REVIEWING. SUSPECT ASSEMBLY ERROR. (X) 2 L 7 2 4F 4 F RT T00001SE E46NE 2000040500033 20000405 00033 NM 2000 4 5 20000404SH017 1 20000118 G 5711 SPAR BOEING 737 737* NM WING CRACKED B K NONE O OTHER IN INSP/MAINT 1 SW 15 ONE EACH CRACK EXISTS ON THE UPPER AFT T-SPAR MEASURING 1.5 INCHES LONG, LOCATED AT THE INBOARD END OF THE OUTBOARD MID- FLAP. (X) 2 L 7 2 4F RT A16WE 2000040500032 20000405 00032 NM 2000 4 5 20000404SH018 1 20000118 G 5711 SPAR BOEING 737 737* NM WING CRACKED B K NONE O OTHER IN INSP/MAINT 1 SW 15 ONE EACH CRACK EXISTED ON THE UPPER AFT T-SPAR MEASURING 5.0 INCHES LONG, LOCATED AT THE INBOARD END OF THE OUTBOARD MID FLAP. (X) 2 L 7 2 4F RT A16WE 2000040600092 20000406 00092 CE 2000 4 6 20000404SH023 1 20000121 G 5510 04320016 STRUCTURE CESSNA 150 152 2071835 CE HORIZONTAL STAB DAMAGED D K NONE O OTHER IN INSP/MAINT 1 SW 15 OBTAINED ONE RT HORIZ STAB L/E RT ASSY FROM CESSNA FOR REPAIR OF A DAMAGED STAB. THE NUTPLATE ON THE RIB MUST BE USED T O PROPERLY ORIENT THE RIB TO THE FUSELAGE STRUCTURE BEFORE RIVET HOLES ARE DRILLED TO ATTACH THE RIB TO THE STAB SPAR AN D LEADING EDGE SKID. THE NEW RIB WAS FOUND CURVED EXCESSIVELY ALONG ITS LONGITUDINAL AXIS CAUSING THE TRAILING EDGE OF THE RIB TO BE IMPOSSIBLE TO INSTALL WITH PROPER RIVET EDGE DISTANCE. OBTAINED 2 MORE RIBS FROM CESSNA TO COMPLETE THIS REPAIR. BOTH HAVE THE SAME DEFECT. THIS DEFECT IS MOST APPARENT WHEN RIBS ARE LAID ON THEIR SIDE ON A FLAT SURFACE AND COMPARED TO A PROPERLY FORMED RIB. (X) 1 H 7 1 3O NT 3A19 2000040600093 20000406 00093 GL 2000 4 6 20000404SH025 3 20000207 G 6114 HUB MCAULY CESSNA 401 401A 207590D CE MCAULY 3AF32C 3AF32C87 GL BLADE SOCKET CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 359 776009 PROPELLER HUB CRACKED IN THE BLADE SOCKET AREA. 1 L 7 2 3O A7CE 5 C P22EA 2000041100099 20000411 00099 CE 2000 4 11 20000405SH001 1 20000210 G 7921 3506210 LINE CESSNA 172 172H 2072424 CE OIL COOLER LEAKING B FM6R O OTHER O OTHER NR NOT REPORTED 1 NM 09 1413F 294 17254908 LEAKING OIL PRESSURE LINE TO THE OIL COOLER. PREMATURE HOSE FAILURE STARTED OUT AS AN OILY SPOT INSIDE THE COWL ON THE RIGHT SIDE AND PROGRESSED TO A STREAK OF OIL DOWN THE BELLY WITH OIL WEEPING OUT THE SIDE WALL OF THE HOSE THE FULL LENG TH. (X) 1 H 7 1 3O NT 3A12 2000040600106 20000406 00106 SW 2000 4 6 20000405SH002 1 20000211 G 5510 407023001101 SLAT BELL 407 407 SW HORIZONTAL STAB DAMAGED B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 10EW 865 53262 SLATS REPLACED WITH NEW. C/W BELL ASB 407-99-32. (X) 1 G 7 1 3U O H2SW 2000040600107 20000406 00107 SW 2000 4 6 20000405SH003 1 20000211 G 5510 407023002117 SLAT BELL 407 407 SW HORIZONTAL STAB DAMAGED B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 175P 276 53316 SLATS REPLACED WITH NEW. C/W BELL ASB 407-99-32. (X) 1 G 7 1 3U O H2SW 2000040600108 20000406 00108 SW 2000 4 6 20000405SH004 1 20000211 G 6500 407340339103 BEARING BELL 407 407 SW TAIL ROTOR DRIVE DAMAGED B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 10EW 674 53262 BEARINGS REPLACED WITH NEW. C/W BELL AD 2000-02-12. (X) 1 G 7 1 3U O H2SW 2000040600109 20000406 00109 CE 2000 4 6 20000405SH005 1 20000201 G 5720 817841432 BOLT BEECH 90 E90 1152914 CE WING CRACKED H K NONE O OTHER IN INSP/MAINT 1 SW 99 16NM 8087 LW62 DURING INSPECTION OF WING SPARS IAW AD 89-25-10 AND BEECH SIRM MANUAL, THE LEFT LOWER FORWARD WING BOLT WAS FOUND CRACKE D USING DYE PENETRANT. (X) 1 L 7 2 3T 3A20 2000040600110 20000406 00110 NM 2000 4 6 20000405SH006 1 20000203 G 5751 SR37P28L02 BEARING ALIDSG BOEING 727 727* NM AILERON FAILED B I6UR O OTHER O OTHER NR NOT REPORTED 1 NM 01 1102145 BEARINGS (76) SHATTER WHEN SUBMITTED TO HIGH TORQUE LOADS. THE BEARING FAILURE CAUSES UNIT TO BIND AND BECOME INOPERATI VE. SUBMITTER SUGGESTED LOAD RATING OF THE BEARING IS TOO LOW. (X) 2 L 7 3 4F RT A3WE 2000040600111 20000406 00111 2000 4 6 20000405SH007 4 20000204 G 2562 DMQ181A ANTENNA CESSNA 500 550 2076604 CE ELT MISINSTALLED H O OTHER W INADEQUATE Q C NR NOT REPORTED 1 SW 99 2GG 2941 5500286 ELT ANTENNA FOUND BROKEN OFF. DISCOVERED THAT AN ANTENNA DESIGNED FOR UNDER 250 MPH WAS INSTALLED. WHEN INSTALLLING AN TENNAS CARE MUST BE TAKEN TO ENSURE THE CORRECT SPEED CAPABILITIES ARE MAINTAINED. THIS ANTENNA WAS MOUNTED AFT OF THE ENGINE INLET SO NO ADDITIONAL DAMAGE WAS SUSTAINED. (X) 1 L 7 2 4F A22CE 2000040600112 20000406 00112 SW 2000 4 6 20000405SH008 1 20000125 G 6420 206011809109 STUD BELL 206 206L3 1182108 SW T/R PITCH HORN LOOSE B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 358AL 51460 TAIL ROTOR PITCH HORNS, PITCH CHANGE LINK STUDS LOOSE. REPLACED PART. (X) 1 G 7 1 3U H2SW 2000040600113 20000406 00113 EA 2000 4 6 20000405SH009 2 20000215 G 7324 FLOW DIVIDER CESSNA 172 172R 2072401 CE LYC IO360 IO360L2A EA FUEL SYSTEM MALFUNCTIONED H O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 SW 99 403ER 6011 140 17280245 L2786651A ENGINE HAD MOMENTARY ROUGHNESS WHILE IN CRUISE FLIGHT. REPLACED FUEL FLOW DIVIDER, FUEL SERVO, AND ELECTRIC BOOST PUMP. (X) 1 H 7 1 3O 3 O NT 3A12 1E10 2000040600114 20000406 00114 EA 2000 4 6 20000405SH010 2 20000215 G 7313 NOZZLE CESSNA 172 172R 2072401 CE LYC IO360 IO360L2A EA FUEL SYSTEM DIRTY H O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 SW 99 403ER 6014 144 17280245 L2786651A ENGINE HAD MOMENTARY ROUGHNESS WHILE IN CRUISE FLIGHT. CLEANED ALL FUEL NOZZLES. (X) 1 H 7 1 3O 3 O NT 3A12 1E10 2000040600115 20000406 00115 EA 2000 4 6 20000405SH011 2 20000215 G 7313 NOZZLE CESSNA 172 172R 2072401 CE LYC IO360 IO360L2A EA NR 2 CYLINDER MALFUNCTIONED H O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 SW 99 445ER 1360 17280662 L2785651A ENGINE HAD MOMENTARY ROUGNESS WHILE IN CRUISE FLIGHT. REPLACED NR 2 CYLINDER INJECTOR NOZZLE. (X) 1 H 7 1 3O 3 O NT 3A12 1E10 2000040600116 20000406 00116 EA 2000 4 6 20000405SH012 2 20000215 G 7421 SPARK PLUG CESSNA 172 172R 2072401 CE LYC IO360 IO360L2A EA ENGINE MALFUNCTIONED H O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 SW 99 445ER 1406 17280662 L2785651A ENGINE HAD MOMENTARY ROUGHNESS DURING CRUISE. CHANGED ONE SPARK PLUG. (X) 1 H 7 1 3O 3 O NT 3A12 1E10 2000040600117 20000406 00117 EA 2000 4 6 20000405SH013 2 20000215 G 7421 SPARK PLUG CESSNA 172 172R 2072401 CE LYC IO360 IO360L2A EA ENGINE FAILED H O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 SW 99 434ER 1275 17280655 L2784651A ENGINE HAD MOMENTARY ROUGHNESS WHILE IN CRUISE FLIGHT. REPLACED ALL SPARK PLUGS. (X) 1 H 7 1 3O 3 O NT 3A12 1E10 2000040600118 20000406 00118 EA 2000 4 6 20000405SH014 2 20000215 G 7310 MANIFOLD CESSNA 172 172R 2072401 CE LYC IO360 IO360L2A EA FUEL SYSTEM MALFUNCTIONED H O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 SW 99 434ER 1303 17280655 L2784651A ENGINE HAD MOMENTARY ROUGHNESS DURING CRUISE. REPLACED FUEL MANIFOLD. (X) 1 H 7 1 3O 3 O NT 3A12 1E10 2000040600119 20000406 00119 EA 2000 4 6 20000405SH015 2 20000215 G 7421 SPARK PLUG CESSNA 172 172R 2072401 CE LYC IO360 IO360L2A EA ENGINE FAILED H O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 SW 99 443ER 348 17280661 L2719151A DURING NORMAL CRUISE, ENGINE RAN ROUGH FOR SEVERAL SECONDS. THE SPARK PLUGS WERE SERVICED. (X) 1 H 7 1 3O 3 O NT 3A12 1E10 2000040600120 20000406 00120 EA 2000 4 6 20000405SH016 2 20000215 G 7313 NOZZLE CESSNA 172 172R 2072401 CE LYC IO360 IO360L2A EA NR 3 CYLINDER FAILED H O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 SW 99 460ER 1290 17280668 L2786851A ENGINE HAD MOMENTARY ROUGHNESS WHILE IN CRUISE FLIGHT. REPLACED NR 3 CYLINDER NOZZLE. (X) 1 H 7 1 3O 3 O NT 3A12 1E10 2000040600121 20000406 00121 EA 2000 4 6 20000405SH017 2 20000215 G 7421 SPARK PLUG CESSNA 172 172R 2072401 CE LYC IO360 IO360L2A EA ENGINE FAILED H O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 SW 99 478ER 1179 17280623 L2779151A ENGINE HAD MOMENTARY ROUGHNESS DURING CRUISE. CHANGED ONE SPARK PLUG. INSTALLED NEW SPARK PLUGS. (X) 1 H 7 1 3O 3 O NT 3A12 1E10 2000040600123 20000406 00123 EU 2000 4 6 20000405SH019 1 20000405 G 2450 MS25244255072251 CIRCUIT BREAKER AMD FALCON FALCON20 2730103 EU COCKPIT FAILED B JGVR K NONE O OTHER IN INSP/MAINT 1 CE 09 47LP 457 WHILE CHECKING CIRCUIT BREAKERS FOR AD 70-22-04, FOUND THIS BREAKER WITH MFG DATE OF 9-72 NEARLY JAMMED PER BOEING SB 24 -1019 INSPECTION. BREAKER DID NOT HAVE FALCON JET IDENTIFIER STICKER ''431L2'' ON IT, SO APPARENTLY IT HAS BEEN INSTALL ED AFTER AIRCRAFT LEFT THE FACTORY (AW DATE 9-25-81). BREAKER IS FOR RT LANDING LIGHT. BREAKER FOR LT LANDING LIGHT AP PEARS ORIGINAL, AND IS MADE BY MECHANICAL PRODUCTS. (X) 2 L 7 2 4F RT A7EU 2000040600125 20000406 00125 NE 2000 4 6 20000405SH022 1 20000216 G 6510 SB1111004 BEARING SKRSKY SKRSKY S64 S64E 8142604 NE TAIL ROTOR MAKING METAL B JYDR O OTHER O OTHER TX TAXI/GRND HDL 1 NM 09 6962R 1 EAC10444 64058 AFTER A HALF-HOUR GROUND RUN AND 0.5 FLIGHT, FOUND A LARGE VOLUME OF DISCOLORED (PURPLE IN APPEARANCE) AND METAL CONTAMI NATED GREASE HAD EXTRUDED PAST THE BEARING SEAL AND WAS FOUND ON THE A/C DECK UNDER THE BEARING. THE BEARING WAS NOT HO T TO THE TOUCH AT THAT TIME. ESTIMATED GREASE LOSS WAS 5 CC''S. THE BEARING IS BEING RETURNED TO THE AIRCRAFT MANUFACT URER FOR THEIR INVESTIGATION. (X) 2 G 7 2 4U H4EA 2000040600126 20000406 00126 SO 2000 4 6 20000405SH023 1 20000203 G 3230 2108000 TUBE PIPER PA24 PA24250 7102404 SO MLG DAMAGED B K NONE O OTHER IN INSP/MAINT 1 SW 99 6960P 4595 242098 UPON INVEST FOLLOWING LANDING GEAR COLLAPSE DURING TOUCH DOWN, FOUND LINKS CONNECTING L/G MOTOR RELEASE ARM TO MOTOR REL EASE TUBE BENT TO THEIR OTBD SIDES. INVESTIGATION SUGGESTS AN ATTEMPT WAS MADE TO MANUALLY RAISE GEAR USING EMERGENCY E XTEND LEVER THAT COULD CAUSE RELEASE TUBE TO DROP. (X) 1 L 7 1 3O 1A15 2000040600127 20000406 00127 NM 2000 4 6 20000405SH024 1 20000201 G 5412 FIREWALL DOUG 600N 600N 3027377 NM ENGINE BAY CHAFED H K NONE O OTHER IN INSP/MAINT 1 SW 01 611BP RN041 AFTER REMOVING THE ENGINE FOR FOD, NOTICED THERE WERE TWO RUBBED INDENTATIONS TO THE UPPER LEFT PORTION OF THE FIREWALL. UPON FURTHER INVESTIGATION, NOTED THE BLEED VALVE BOLT HEADS WERE WORN CONSIDERABLY. THIS WAS THE ORIGINAL FACTORY IN STALLATION. (X) 1 G 7 1 3U NC H3WE 2000040700024 20000407 00024 CE 2000 4 7 20000405SH025 1 20000129 G 2810 FUEL TANK CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA LEFT CONTAMINATED D K NONE O OTHER IN INSP/MAINT 1 SO 13 714VA 7679 2107 15279456 L2000615 ENGINE FAILURE AFTER TAKEOFF. OUTSIDE AIR TEMPERATURE BELOW FREEZING FOR APPROX 2 WEEKS BEFORE FLIGHT. SNOW/SLEET IN A REA SEVERAL DAYS PRIOR TO FLIGHT. POSSIBLE CAUSE WAS WATER CONTAMINATED FUEL OR CARBURETOR ICING. DRAINED FUEL TANKS, WATER FOUND IN LT FUEL TANK. FLUSHED FUEL SYSTEM. CHANGED FUEL CAP TO HELP PREVENT RECURRENCE. (X) 1 H 7 1 3O 3 O NT 3A19 E223 2000040600130 20000406 00130 GL 2000 4 6 20000405SH028 2 20000203 G 7240 6870992 COMBUSTION LINER ALLSN BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL TURBINE SECTION CRACKED D O OTHER J WARNING INDICATION HO HOVERING 1 EA 21 777CP 199 33573 3429 CAE830498 DURING HOVERING ON A TRAINING FLIGHT, THE PILOT NOTICED THAT TOT TEMPERATURE WAS HIGHER THAN NORMAL. AFTER TROUBLESHOOT ING WHICH INCLUDED CHANGING BLEED VALVE AND CHECKING ANTI-ICE FOR PROPER CLOSING, THERE WAS NO CHANGE. POWER CHECK ON E NGINE INDICATED SUBSTANTIAL POWER LOSS. THIS WAS A RENTAL ENGINE SO THE AMOC WHICH OWNED THE ENGINE WAS NOTIFED. THEY CAME AND REMOVED THE ENGINE. UPON REMOVAL, A CRACK WAS NOTICED ON THE BACK OF THE COMBUSTION CASE NEXT TO THE FUEL NOZZ LE ABOUT 3 INCHES LONG. ENGINE RETURNED TO AMOC FOR REPAIR. (X) 1 G 7 1 3U 3 U H2SW E4CE 2000040600131 20000406 00131 CE 2000 4 6 20000405SH029 1 20000128 G 2720 CONTROL CABLE BEECH 36 A36 1151604 CE RUDDER MISROUTED B K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 99 898DM E3216 DURING AIRCRAFT''S FIRST ANNUAL INSPECTION (SINCE NEW), FOUND RUDDER CABLE PN R-106-524051-5 INCORRECTLY ROUTED (WRONG B ULKHEAD LIGHTNING HOLE) THROUGH AREA UNDER LANDING GEAR ACTUATOR. PART WAS NOT DAMAGED, SIMPLE RE-ROUTING THROUGH CORRE CT HOLE CORRECTED ISSUE. ACTT: 69.1 HOURS. (X) 1 L 7 1 3O 3A15 2000040600132 20000406 00132 CE 2000 4 6 20000405SH030 1 20000128 G 3246 13889 BEARING BEECH 2000 2000 1152000 CE MLG WHEEL DISINTEGRATED B O OTHER O OTHER NR NOT REPORTED 1 SW 99 8283S OCT89116 NC41 PILOT NOTICED RIGHT MAIN LANDING GEAR INBOARD WHEEL ASSEMBLY TILTED AND HUB CAP BULGED. UPON INSPECTION, FOUND INBOARD BEARING (HUBCAP SIDE) HAD FAILED CAUSING DAMAGE TO WHEEL AND BRAKE ASSY. NO APPARENT FAULT IN WORKMANSHIP FOUND. (X) 1 L 7 2 4T RT A38ACE 2000040600133 20000406 00133 SO 2000 4 6 20000405SH031 1 20000125 G 2840 548671 FLOAT PIPER PA28 PA28181 7102807 SO LT WING TANK BLOCKED D K NONE O OTHER IN INSP/MAINT 1 GL 13 8276V 4122 1818190056 288190056 PILOT REPORTED FUEL QUANTITY INDICATION ALWAYS ON ''E'' FOR LEFT TANK. FOUND THE FLOAT BLOCK WAS DETACHED FROM THE FLOA T SWING ARM. THE FLOAT BLOCK WAS SO BADLY WORN IT SLIPPED OVER THE RETAINING WASHER ON THE SWING ARM. POSSIBLE CAUSE, TOO SOFT OF A MATERIAL USED IN FLOAT BLOCK, AND NO INSERT TO PREVENT BLOCK FROM WEARING THROUGH. REF: IPC SECT VIII FU EL FIGURE 47. (X) 1 L 7 1 3O 2A13 2000040600140 20000406 00140 SO 2000 4 6 20000406SH001 1 20000114 G 5410 12003851002 FRAME EMB 120 EMB120RT SO RT NACELLE CRACKED B WVER K NONE O OTHER IN INSP/MAINT 1 EA 09 273AS 120222 RIGHT NACELLE FRAME 1 CRACKED OUTBOARD OF TORQUE MOUNT. ENGINE VIBRATION/TORSION. SB 120-54-0036 IS BEING INCORPORATED . (X) 2 L 7 2 4T RT A31SO 2000040600141 20000406 00141 SO 2000 4 6 20000406SH002 1 20000114 G 5410 12003851001 FRAME EMB 120 EMB120RT SO LT NACELLE CRACKED B WVER K NONE O OTHER IN INSP/MAINT 1 EA 09 273AS 120222 LEFT NACELLE FRAME 1 CRACKED OUTBOARD OF TORQUE MOUNT. ENGINE VIBRATION/TORSION. SB 120-54-0036 IS BEING INCORPORATED. (X) 2 L 7 2 4T RT A31SO 2000041100102 20000411 00102 NM 2000 4 11 20000406SH003 1 20000131 G 2740 69778551 SPRING BOEING BOEING 737 737* NM HORIZONTAL STAB FAILED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 19059 KEO1657 SPRINGS, PN 69-77855-1, BROKEN IN THE AUXILIARY BRAKE SYSTEM. IMPROPER HEAT-TREATING, AUSTENITE, FATIGUE AND INCREASED SPRING COIL STRESSES. SPRINGS, PN 69-77855-1, ARE TO BE REPLACED WITH P/N 69-77855-2 SPRINGS ON ACTUATOR ASSEMBLIES MAN UFACTURED PRIOR TO S/N KE01730 PER BOEING SL 737-SL-27-090-B. (X) 2 L 7 2 4F RT A16WE 2000040600142 20000406 00142 NM 2000 4 6 20000406SH004 1 20000126 G 2761 120611 PISTON BOEING BOEING 737 737* NM SPOILER ACTUATOR CRACKED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 2760 530 PISTON IS CRACKED IN THE KEYWAY. FATIGUE/OVERSTRESSED. (X) 2 L 7 2 4F RT A16WE 2000040600143 20000406 00143 NM 2000 4 6 20000406SH005 1 20000126 G 2761 116511 PISTON BOEING BOEING 737 737* NM SPOILER ACTUATOR CRACKED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 2760 8138 PISTON IS CRACKED NI THE KEYWAY. (X) 2 L 7 2 4F RT A16WE 2000040600144 20000406 00144 EU 2000 4 6 20000406SH006 1 20000128 G 7170 0174078010 DRAIN VALVE AEROSP SA365 SA365N1 8680668 EU TMECA ARRIEL ARRIEL1C 60030 NE START DRAIN LEAKING B TI1R K NONE K FLUID LOSS IN INSP/MAINT 1 EA 07 94MD 2008 6317 5069 VALVE LEAKING AROUND SPLIT LINE OF CASING. (X) 1 G 7 2 3U 3 U H10EU E19EU 2000040600145 20000406 00145 NM 2000 4 6 20000406SH007 1 20000131 G 2742 69778551 SPRING BOEING BOEING 737 737* NM TRIM ACTUATOR CRACKED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 50559 18889 00602 SPRINGS, PN 69-77855-1, ARE BROKEN IN THE AUXILIARY BRAKE SYSTEM. IMPROPER HEAT-TREATING, AUSTENITE, FATIGUE AND INCREA SED SPRING COIL STRESSES. SPRINGS, PN 69-77855-1, ARE TO BE REPLACED WITH PN 69-77855-2 SPRINGS ON ACTUATOR ASSEMBLIES MANUFACTURED PRIOR TO S/N KEO1730 PER BOEING SL 737-SL-27-090-B. (X) 2 L 7 2 4F RT A16WE 2000040600147 20000406 00147 EU 2000 4 6 20000406SH009 1 20000106 G 3340 G62504 LIGHT BOLKMS 117 BK117B1 5626012 EU FUSELAGE INOPERATIVE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 460H 7142 SEARCH LIGHT WILL NOT RETRACT. REMOVED AND REPLACED. (X) 1 G 7 2 3U H13EU 2000040600157 20000406 00157 SW 2000 4 6 20000406SH021 1 20000107 G 7714 222375022105 INDICATOR BELL 222 222 1182122 SW GAS PRODUCER FLUCTUATES B TI1R O OTHER O OTHER NR NOT REPORTED 1 SW 05 911LW 47520 INDICATOR SLOW TO COME UP. FLUCTUATES AT 90 PERCENT. REMOVED AND REPLACED. (X) 1 G 7 2 3U H9SW 2000040600160 20000406 00160 NE 2000 4 6 20000406SH025 2 20000104 G 7321 4302022307 FUEL CONTROL BELL 222 222 1182122 SW LYC LTS101 LTS101650C 41560 NE ENGINE FAILED B TI1R O OTHER O OTHER NR NOT REPORTED 1 SW 05 911MK 47515 FUEL CONTROL FAILED UPON INSTALLATION. REMOVED AND REPLACED. (X) 1 G 7 2 3U 3 U H9SW E5NE 2000041100132 20000411 00132 SW 2000 4 11 20000406SH052 1 20000202 G 2742 047414300 BEARING BENDIX MOONEY M20 M20M 5870222 SW PITCH TRIM SERVO DAMAGED H O OTHER O OTHER NR NOT REPORTED 1 SW 99 9149Y 270112 LUBRICANT IN ROLLER BEARING AT FORWARD END OF PITCH TRIM TUBE BECAME GUMMED UP AND HARDENED TO THE POINT THAT NEITHER EL ECTRIC OR HAND WHEEL ACTUATION OF PITCH TRIM WAS POSSIBLE. MALFUNTION WAS CORRECTED BY REPLACING BEARING. THERE IS NO PROVISION FOR PERIODIC LUBRICATION. AIRCRAFT WAS MANUFACTURED IN 1991. (X) 1 L 7 1 3O RT 2A3 2000041100133 20000411 00133 EU 2000 4 11 20000406SH053 1 20000107 G 6220 COUNTERWEIGHT SNIAS 350 AS350BA 8680817 EU VIBRATION DAMPER GALLED H K NONE O OTHER IN INSP/MAINT 1 WP 19 92MH 3022 2898 LEAD METAL FLAKING DISCOVERED AT SPHERICAL BEARING INSIDE OF FREQUENCY ADAPTERS. FURTHER INSP REVEALED BROKEN BOLT INSI DE OF ANTI-VIBRATOR SPRING HOUSING. UPON REMOVAL AND DISASSEMBLY OF ANTI-VIBRATOR ASSY, THE LEAD WEIGHTS WERE FOUND SEV ERELY GALLED DUE TO THE LOSS OF TORQUE AND EVENTUAL FAILURE OF THE ATTACHMENT BOLT THAT SECURES THE SMALLER LEADWEIGHT T O THE INNER SHAFT OF THE ASSY. THE ALUM LOCATING PIN HAD ALSO FAILED. RECOMMEND DURING 500-HR ''T'' INSPECTIONS, THE L IFTING EYE PLUG BE REMOVED FROM THE TIP OF THE ANTI-VIBRATOR ASSY, AND A TORQUE CHECK BE PERFORMED ON THE LEAD WEIGHT BO LT. (X) 1 G 7 1 3U NC H9EU 2000041300363 20000413 00363 SW 2000 4 13 20000406SH055 1 20000209 G 5302 407023001101 SLAT BELL 407 407 SW TAIL BOOM DAMAGED B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 98VG 53171 SLATS REJECTED. REPLACED WITH NEW. C/W BELL ASB 407-99-32. (X) 1 G 7 1 3U O H2SW 2000041100135 20000411 00135 2000 4 11 20000406SH056 4 20000131 G 2561 KS9P0101 LIFE VEST CABIN FAILED B KQ1R K NONE L NO TEST IN INSP/MAINT 1 EA 07 LIFE VEST FAILED MANUFACTURER''S RECOMMENDED 2 PSI TEST IAW 25-60-1. ITEM DOM: SEPT 1981. (X) 2000041100136 20000411 00136 NE 2000 4 11 20000406SH057 2 20000209 G 7421 CH34682 IGNITOR PWA 305 PW305 NE ENGINE FAILED B R14R K NONE O OTHER IN INSP/MAINT 1 EA 17 RECEIVED 3 EACH IGNITORS FROM SUPPLY. THE 4TH IGNITOR OPS CHECKED OK. BATCH NUMBER UNKNOWN. THE IGNITOR USED NORMALLY IS INSTALLED ON P&W 305 SERIES ENGINES. P/N 34682. (X) 4 F E35NE 2000041100137 20000411 00137 2000 4 11 20000406SH058 4 20000205 G 2561 AV8AS2100 LIFE VEST CABIN FAILED B KQ1R K NONE L NO TEST IN INSP/MAINT 1 EA 07 INDIVIDUAL FLOTATION DEVICE FAILED MANUFACTURER''S RECOMMENDED 2 PSI TEST IAW 25-60-33. DOM: FEB 1986. (X) 2000041100138 20000411 00138 2000 4 11 20000406SH059 4 20000204 G 2561 HA5 LIFE VEST CABIN FAILED B KQ1R K NONE L NO TEST IN INSP/MAINT 1 EA 07 LIFE VEST FAILED MANUFACTURER''S RECOMMENDED 2 PSI TEST. DOM: JAN 1983. (X) 2000041200076 20000412 00076 2000 4 12 20000406SH060 4 20000106 G 2565 SWD230300201 SLIDE BFGOODRICH DOUG DC10 DC1030 3023501 WP GIRT ASSY MISMANUFACTURED B K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 19 GIRT ASSEMBLY WAS FABRICATED FROM AN UNKNOWN FABRIC AND IDENTIFIED WITH THE MANUFACTURER''S (BFG) P/N AND WITHOUT THE MA NUFACTURER''S INSPECTION STAMP AND INSPECTION DATE. THIS PART IS BEING CONSIDERED AS A SUSPECTED UNAPPROVED PART SINCE IT DOES NOT MEET THE MFG DRAWINGS. NOTE: THIS UNIT WAS LAST OVERHAULED 6-96. (X) 2 L 7 3 4F A22WE 2000041100140 20000411 00140 SO 2000 4 11 20000407SH001 2 20000221 G 8530 654960A1 CYLINDER CESSNA 182 182P 2075816 CE CONT O470 O470U 17026 SO NR 3 WORN D K NONE O OTHER IN INSP/MAINT 1 GL 23 952CC 765 18263638 470757 DURING A ROUTINE COMPRESSION CHECK, THE NR 3 CYLINDER WAS FOUND TO HAVE EXCESSIVE LEAKAGE 53/80 PAST THE PISTON RINGS. THE REMOVED CYLINDER WAS FOUND WORN OUT AT THE TOP OF THE CYLINDER. (X) 1 H 7 1 3O 3 O NT TA13 E273 2000041100141 20000411 00141 SO 2000 4 11 20000407SH002 2 20000221 G 8520 653877 LIFTER CESSNA 182 182P 2075816 CE CONT O470 O470U 17026 SO NR 3 CYLINDER DAMAGED D K NONE O OTHER IN INSP/MAINT 1 GL 23 952CC 1230 18263638 470757 DURING THE REMOVAL OF THE NR 3 CYLINDER, THE EXHAUST VALVE LIFTER WAS INSPECTED AND FOUND TO HAVE CHIPS OF MATERIAL MISS ING FROM THE CORNERS NEAR THE LOWER FACE. THE FACE OF THE LIFTER AND CAM LOBE WERE NOT FOUND TO HAVE ANY DEFECTS. (X) 1 H 7 1 3O 3 O NT TA13 E273 2000041100142 20000411 00142 CE 2000 4 11 20000407SH003 1 20000215 G 5510 115620020 SUPPORT FITTING BEECH 99 B99 1154004 CE HORIZONTAL STAB WORN E K NONE O OTHER IN INSP/MAINT 1 NM 07 950AA U159 ROUTINE INSPECTION REVEALED HORIZONTAL STABILIZER LOOSE AT PIVOT SUPPORTS. REPLACED BOTH LEFT AND RIGHT PIVOT SUPPORT B RACKETS AND BEARINGS AND HARDWARE. PROBLEM DETERMINED TO BE DUE TO NORMAL WEAR AND POSSIBLE LACK OF LUBRICATION. (X) 1 L 7 2 3T A14CE 2000041200078 20000412 00078 CE 2000 4 12 20000407SH004 1 20000127 G 3230 BRAKE ASSY CESSNA 421 421B 2076014 CE MLG DAMAGED H O OTHER O OTHER LD LANDING 1 EA 21 13HB 421B0582 ON LANDING, RT SCISSOR ASSY SEPARATED WHEN BRAKE HOSE CLAMP BROKE, BUSHING AND BOLT PULLED THROUGH SCISSOR ASSY. RE-ASS EMBLED SCISSOR ASSY WITH NEW BUSHING AND HOSE CLAMP, INSTALLED WASHERS ON BOLT AND NUT SIDE OF SCISSORS TO PREVENT THIS PROBLEM. THE WASHER ON THE NUT, HOSE CLAMP SIDE OF SCISSORS NOT INSTALLED. (X) 1 L 7 2 3O A7CE 2000041200079 20000412 00079 NE 2000 4 12 20000407SH005 1 20000226 G 6410 S101521203 BLADE SKRSKY S55 S55 8141602 NE TAIL ROTOR CRACKED H K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 19 17754 648 98 BC48 V55398T ITEM CRACKED AT ROOT ATTACH POINT OF TAIL ROTOR BLADE. REMOVED TAIL ROTOR BLADE FROM ASSY AND DISCOVERED TAIL ROTOR BLA DE ATTACH BOLTS WERE NOT TORQUED TO MANUFACTURER SPECIFICATIONS. (X) 1 G 7 1 3R 1H4 2000041700133 20000417 00133 CE 2000 4 17 20000407SH010 1 20000220 G 2700 KS271C SERVO CESSNA 182 182S 2072701 CE RT WING WORN B K NONE O OTHER IN INSP/MAINT 1 NE 05 116ZX 18280042 WHILE PERFORMING A SERVICE BULLETIN ON A PRIMARY SERVO (SB KS271C-5 ALERT) NOTED THE SERVO GEAR TEETH TO HAVE EXCESSIVE WEAR. GEAR BEARING APPEARS TO BE MAKING METAL. MEAL POWDER RESIN VISIBLE UNDER THE GEAR. GEAR ROTATION IS NOT SMOOTH AND MAKES A SLIGHT GRINDING SOUND. ACFT TOTAL TIME: 390 HOURS. PITCH AND TRIM SERVOS OK. (X) 1 H 7 1 3O NT 3A13 2000041100143 20000411 00143 NM 2000 4 11 20000407SH011 1 20000219 G 2430 RCCB DOUG MD11 MD11 3023602 NM GE CF6 CF680C2D1F 30025 NE E/E BAY FAILED H K NONE O OTHER IN INSP/MAINT 1 SW 99 150EV 48544 LAX/TPE - RIGHT EMER AC BUS'' OFF MESSAGE DURING FLIGHT. DIVERTED TO CTS WITH LIMITED INSTRUMENT. ''REAC SENS RELAY/IN TFC'' CURRENT FAULT FOUND ON CFDS, BUT PERFORM EPU R-T-S TEST PASS AND CHECK ALL FUNCTIONAL NORMAL. FOR MAINTENANCE PREV ENTION, REPLACED RCCB B1-138 IAW MM 24-25-0, AND PERFORM OPERATIONAL TEST, FUNCTION NORMAL. (X) 2 L 7 3 4F 4 F RT A22WE E31N3 2000041100144 20000411 00144 CE 2000 4 11 20000407SH012 1 20000131 G 3230 081330031 TORQUE TUBE CESSNA 310 310 2074202 CE MLG BROKEN G K NONE O OTHER IN INSP/MAINT 1 NM 13 2640C 3220 35040 PART FAILED AT GEAR RETRACTION AFTER TAKEOFF, NOSE GEAR COLLAPSED AT LANDING. COMPONENT WAS REDESIGNED STARTING WITH A/ C SN 35042. SUBMITTER SUGGESTED ADDED EMPHASIS INSPECTION THIS AREA ON EARLY CE-310 A/C. (X) 1 L 7 2 3O RT 3A10 2000041100147 20000411 00147 CE 2000 4 11 20000407SH015 1 20000221 G 8120 640321 SUPPORT BRACKET BEECH 58 58TC 1152746 CE CONT O520 TSIO520L 17040 SO RT ENGINE CRACKED D K NONE O OTHER IN INSP/MAINT 1 NM 03 227BR 3304 TK31 2419489 DURING ANNUAL INSPECTION, FOUND RT ENGINE TURBO MOUNT BRACKET CRACKED UNDER AND NEAR END OF LOWER STIFFENER BEND. CRACK IS APPROXIMATELY ONE INCH LONG AND EXTENDING TOWARD BUT NOT TO LOWER LIGHTING HOLE. NO EVIDENCE OF CAUSE FOR CRACK. ( X) 1 L 7 2 3O 3 O A23CE E8CE 2000041100148 20000411 00148 SO 2000 4 11 20000407SH016 1 20000221 G 3211 40294006 TRUNNION PIPER PA42 PA421000 7104225 SO MLG WW CRACKED D SO5R K NONE O OTHER IN INSP/MAINT 1 NE 03 325KW 4102 425527025 PART IS MAIN LANDING GEAR REAR SIDE BRACE TRUNNION. A SMALL CRACK WAS FOUND IN THE WEB NEXT TO THE INBOARD LOWER BOLT H OLE ON BOTH RT AND LT MAIN GEAR. CRACK WAS DETECTED BY PREVIOUS EXPERIENCE. CRACK WAS VERIFIED BY DYE PENETRANT. (X) 1 L 7 2 4T RT A23SO 2000041100149 20000411 00149 2000 4 11 20000407SH017 4 20000228 G 6122 D20594 SHAFT MCAULY CESSNA 404 404 2075901 CE CONT O520 GTSIO520M 17032 SO PROP GOVERNOR CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 6764D 801100 4040693C CRACK INDICATION. (X) 1 L 7 2 3O 3 O RT A25CE E7CE 2000041100150 20000411 00150 NE 2000 4 11 20000407SH018 3 20000228 G 6110 2202 BEARING PIPER PA60 PA60601P 7106012 NM HARTZL HCC3Y HCC3YR2 NE PROPELLER CRACKED B K NONE O OTHER IN INSP/MAINT 1 SO 17 90370 2724 1134 61P0234034 CK923 CRACK INDICATION. (X) 1 M 7 2 3O RT A17WE 5 C P25EA 2000041100152 20000411 00152 SO 2000 4 11 20000407SH020 1 20000221 G 3211 40294006 TRUNNION PIPER PA42 PA421000 7104225 SO MLG WW CRACKED D SO5R K NONE O OTHER IN INSP/MAINT 1 NE 03 38AF 4881 425527029 PART IS MAIN LANDING GEAR REAR SIDE BRACE TRUNNION. A SMALL CRACK WAS FOUND IN THE WEB NEAR TO THE INBOARD LOWER BOLT H OLE ON BOTH RT AND LT MAIN GEAR. CRACK DETECTED FROM PREVIOUS EXPERIENCE. CRACK WAS VERIFIED BY DYE PENETRANT. (X) 1 L 7 2 4T RT A23SO 2000041100153 20000411 00153 CE 2000 4 11 20000407SH021 1 20000301 G 2780 KS271C SERVO CESSNA 182 182S 2072701 CE LE FLAP WORN B K NONE O OTHER IN INSP/MAINT 1 NE 05 351BR 18280045 WHILE PERFORMING A SERVICE BULLETIN ON PRIMARY SERVO (SB KS271C-5 ALERT NOTED THE SERVO GEAR TEETH TO HAVE EXCESSIVE WEA R. GEAR BEARING APPEARS TO BE MAKING METAL. THERE WAS A BLACKISH METAL POWDER RESIDUE UNDER THE GEAR. WHEN THE GEAR I S TURNED BY HAND IT DOES NOT ROTATE SMOOTHLY AND MAKES A SLIGHT GRINDING NOISE. ACFT TOTAL TIME: 325 HOURS. (TIM AND PITCH SERVOS NORMAL). (X) 1 H 7 1 3O NT 3A13 2000041100165 20000411 00165 SO 2000 4 11 20000407SH024 1 20000217 G 2434 7396509 BELT PIPER PA28 PA28R200 7102811 SO ALTERNATOR DISINTEGRATED H O OTHER O OTHER NR NOT REPORTED 1 SO 13 32891 28R7535098 ALTERNATAOR BELT CAME APART. ALTERNATOR QUIT WORKING. BATTERY DRY OF ACID. BATTERY DEAD. AIRCRAFT LANDED. LANDING G EAR NOT DOWN AND LOCKED. RIGHT GEAR WAS NOT LOCKED. (X) 1 L 7 1 3O 2A13 2000041300364 20000413 00364 SO 2000 4 13 20000407SH025 1 20000407 G 3210 20829 STUD PIPER PA28 PA28R180 7102809 SO MLG WORN D K NONE O OTHER IN INSP/MAINT 1 SW 99 4669J 28R30569 ON ANNUAL INSPECTION (AD 97-01-01R1), FOUND BOTH MAIN LANDING GEARS SIDEBRACE STUDS WORN, RT 0.624 INCH AND THE LT, 0.52 4 INCH AND SIDEBRACE BUSHING WORN. REPLACED BOTH SIDE BRACE STUDS WITH .6250 INCH, P/N 78717-002, AND REAMED EXISTING B USHING TO 0.624 INCH PER AD 97-01-01R1. (X) 1 L 7 1 3O 2A13 2000041100166 20000411 00166 2000 4 11 20000407SH026 4 20000309 G 3416 03753302 ENCODER PIPER PA28 PA28181 7102807 SO COCKPIT LEAKING H K NONE K FLUID LOSS IN INSP/MAINT 1 SW 99 4145A 1087 2843150 INTERNAL LEAK IN ALTITUDE ENCODER GREATER THAN THE ALLOWED 100 FEET/MINUTE IN NON-PRESSURIZED AIRCRAFT. THESE ENCODERS ARE NORMALLY VERY RELIABLE, YET THIS UNIT IS ONLY TWO YEARS OLD AND PROBLEM WAS DISCOVERED ON AIRCRAFT''S FIRST RECERTIF ICATION SINCE PIPER AIRCRAFT INSTALLATION. POSSIBLE NARCO MFG DEFECT IN ASSEMBLY OF PRESSURE SENSOR. LEAKS AROUND GLUE JOINT IN SENSOR. (X) 1 L 7 1 3O 2A13 2000041100167 20000411 00167 2000 4 11 20000407SH027 4 20000309 G 3416 AR850 ENCODER PIPER PA28 PA28181 7102807 SO COCKPIT LEAKING H K NONE K FLUID LOSS IN INSP/MAINT 1 SW 99 4145X 1177 2843152 INTERNAL LEAK IN ALTITUDE ENCODER GREATER THAN THE ALLOWED 100 FEET/MINUTE NON- PRESSURIZED AIRCRAFT. THESE ENCODERS AR E NORMALLY VERY REALIABLE, YET RECERTIFICATION SINCE PIPER AIRCRAFT INSTALLATION. POSSIBLE NARCO MANUFACTURE DEFECT IN ASSEMBLY OF PRESSURE SENSOR. LEAKS AROUND GLUE JOINT IN SENSOR. (X) 1 L 7 1 3O 2A13 2000041100168 20000411 00168 2000 4 11 20000407SH028 4 20000309 G 3416 AR850 ENCODER PIPER PA28 PA28181 7102807 SO COCKPIT LEAKING H K NONE K FLUID LOSS IN INSP/MAINT 1 SW 99 4145G 1078 2843151 INTERNAL LEAK IN ALTITUDE ENCODER GREATER THAN THE ALLOWED 100 FEET/MINUTE IN NON-PRESSURIZED AIRCRAFT. THESE ENCODERS ARE NORMALLY VERY REALIABLE, YET THIS UNIT IS ONLY TWO YEARS OLD AND PROBLEM WAS DISCOVERED ON AIRCRAFT''S FIRST RECERTI FICATION SINCE PIPER AIRCRAFT INSTALLATION. POSSIBLE NARCO MANUFACTURE DEFECT IN ASSEMBLY OF PRESSURE SENSOR. LEAKS AR OUND GLUE JOINT IN SENSOR. (X) 1 L 7 1 3O 2A13 2000041100169 20000411 00169 EA 2000 4 11 20000407SH029 2 20000306 G 8500 ENGINE CESSNA 172 172R 2072401 CE LYC IO360 IO360L2A EA NOSE MALFUNCTIONED H O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION AP APPROACH 1 SW 99 445ER 1503 17280662 L2785651A DURING FINAL APPROACH, THE ENGINE STUMBLED AND RAN ROUGH. (X) 1 H 7 1 3O 3 O NT 3A12 1E10 2000041100170 20000411 00170 EA 2000 4 11 20000407SH030 2 20000307 G 8500 ENGINE CESSNA 172 172R 2072401 CE LYC IO360 IO360L2A EA NOSE MALFUNCTIONED H A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION NR NOT REPORTED 1 SW 99 476ER 1402 17280638 L2778251A WHILE IN THE PATTERN ON A DUAL FLIGHT, THE ENGINE BEGAN TO RUN ROUGH ON THE CROSS-WIND LEG. IT CONTINUED DOING SO ON DO WN-WIND. AN EMERGENCY WAS DECLARED AND A SUCCESSFUL LANDING WAS MADE. (X) 1 H 7 1 3O 3 O NT 3A12 1E10 2000041100172 20000411 00172 SO 2000 4 11 20000407SH032 1 20000221 G 3211 40294006 TRUNNION PIPER PA42 PA421000 7104225 SO MLG WW DAMAGED D SO5R K NONE O OTHER IN INSP/MAINT 1 NE 03 531MC 3439 425527007 PART IS MAIN LANDING GEAR REAR SIDE BRACE TRUNNION. A SMALL ERODE WAS FOUND IN THE WEB NEXT TO THE INBOARD LOWER BOLT H OLE ON BOTH RT AND LT MAIN GEAR. CRACK WAS DETECTED BY SMALL CRACK IN PAINT. CRACK WAS VERIFIED BY DYE PENETRANT. (X) 1 L 7 2 4T RT A23SO 2000041100173 20000411 00173 SO 2000 4 11 20000407SH033 2 20000306 G 8520 11577L CRANKCASE CESSNA 414 414 2075908 CE CONT O520 TSIO520NB 17040 SO ENGINE CRACKED E K NONE O OTHER IN INSP/MAINT 1 CE 09 661CE 881 4140943 L514353 CRANKCASE CRACKED FROM BASE OF NR 4 CYLINDER ACROSS THE TOP OF THE BACKBONE TO THE BASE OF NR 3 CYLINDER. CAUSE UNKNOWN AT THIS TIME. (X) 1 L 7 2 3O 3 O RT A7CE E8CE 2000041100174 20000411 00174 SO 2000 4 11 20000407SH034 1 20000223 G 3211 C4503 FORK PIPER PA31 PA31350 7103110 SO HARTZL HCC4Y HCC4YR2 GL MLG CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 585HV 2528 1479 317552041 FH452 CRACK INDICATION .75 INCH LONG IN SLOT 3. (X) 1 L 7 2 3O A20SO 5 C P52GL 2000041700064 20000417 00064 SO 2000 4 17 20000412SH001 1 20000221 G 3230 40294006 TRUNNION PIPER PA42 PA421000 7104225 SO MLG WW DAMAGED D SO5R K NONE O OTHER IN INSP/MAINT 1 NE 03 248DJ 3938 425527021 PART IS MAIN LANDING GEAR REAR SIDE BRACE TRUNNION. A SMALL CRACK WAS FOUND IN THE WEB NEXT TO THE INBOARD LOWER BOLT HOLE ON BOTH RT AND LT MAIN GEAR. CRACK WAS DETECTED BY SMALL CRACK IN PAINT AND VERIFIED BY DYE PENETRANT. (X) 1 L 7 2 4T RT A23SO 2000041300392 20000413 00392 NE 2000 4 13 20000412SH003 3 20000223 G 6114 660714255 HUB ROTOL ROTOL R390 R3904123F27 NE PROPELLER ASSY CRACKED B MS1R K NONE O OTHER IN INSP/MAINT 1 EA 27 7429 DAP0085 PROPELLER RECEIVED AT DOWTY AEROSPACE PROPELLERS FOR ROUTINE OVERHAUL. NOTED AT TEAR DOWN OF PROPELLER, 2 CRACKS AT HUB SPLIT LINE IN HUB REAR HALF AT NR 1 AND NR 2 BLADE PORT. HEAVY CHAPPING FOUND ON BOTH FRONT AND REAR HUB MATING FACES. (SPLIT LINE). HUB REJECTED FROM FURTHER SERVICE. (X) 6 C P31NE 2000041700156 20000417 00156 SO 2000 4 17 20000412SH005 1 20000303 G 2752 573801 VALVE GULSTM G1159 GIV 3980115 SO FLAP ACTUATOR LOOSE B O OTHER O OTHER NR NOT REPORTED 1 EA 25 250VC 3648 1231 FLAP ACTUATION SLUGGISH WITH ENGINE RUNNING. WOULD NOT OPERATE USING AUXILIARY SYSTEM. FOUND FLAP SELECTOR VALVE INTER NAL SPOOL ACCESS CAP HAD NEVER BEEN SAFETIED (NO SAFETY WIRE MARKS ON UNIT) AND HAD BACKED OUT 3 TURNS. REPLACED SELECT OR VALVE (REPLACEMENT UNIT WAS SAFETIED WITH LEAD SEAL). OPERATION NORMAL. (X) 2 L 7 2 4F RT A12EA 2000041700157 20000417 00157 SO 2000 4 17 20000412SH006 1 20000222 G 5410 FRAME EMB 120 EMB120RT SO RT NACELLE CRACKED B WVER K NONE O OTHER IN INSP/MAINT 1 EA 09 283UE 22739 120139 RIGHT NACELLE NR 1 FRAME CRACKED AT THE ENGINE TORQUE TUBE MOUNT AREA. ENGINE VIBRATION IS A POSSIBLE CAUSE. FRAME IS BEING REPLACED WITH 4 EACH NEW FRAMES, P/N 120-540036-004, WHICH HAS A ''BEEFED'' UP WEB AREA AT THE MOUNTING POINT. (X) 2 L 7 2 4T RT A31SO 2000041300406 20000413 00406 CE 2000 4 13 20000412SH007 1 20000412 G 2460 BUSS CESSNA 340 340A 2076405 CE COCKPIT FAILED H O OTHER H J ELECT. POWER LOSS-50 PC WARNING INDICATION NR NOT REPORTED 1 NE 01 2696P 2700 340A0779 AIRCRAFT LOST AVIONICS POWER, EMERGENCY AVIONICS ALSO INOPERABLE. VFR FLIGHT OUTSIDE OF CLASS B OR CLASS C AIRSPACE. C AUSED BY THE BUS BAR CHAFING THROUGH AT CHAFE STRP ON A/C STRUCTURE AND SHORTING OUT. BUS BAR WAS .25 INCH LONGER THAN ADJACENT BARS CAUSING IT TO BEAR AGAINST THE STRUCTURE. BUS BAR WAS TRIMMED FOR ADDITIONAL CLEARANCE AND NEW CHAFE MATE RIAL INSTALLED. (X) 1 L 7 2 3O 3A25 2000041300407 20000413 00407 GL 2000 4 13 20000412SH008 1 20000210 G 2421 ALY8402 WIRE BLANCA 17 1730A 1220433 GL CONT O520 IO520K 17032 SO ALTERNATOR ARCED G A UNSCHED LANDING O OTHER CR CRUISE 1 WP 17 8843V 30367 209105K71 OPERATOR REPORTED DISCHARGE FROM ALTERNATOR IN CRUISE FLIGHT. MASTER SWITCH WAS TURNED OFF. AIRCRAFT LANDED WITHOUT IN CIDENT. MAINTENANCE DISCOVERED ONE BRUSH WIRE BROKEN AND THE RETAINER SPRING WELDED TO THE HOLDER. (X) 1 L 7 1 3O 3 O A18CE E5CE 2000041700158 20000417 00158 CE 2000 4 17 20000412SH009 1 20000312 G 2430 363800611 BATTERY BEECH 36 A36TC 1151603 CE E/E BAY SHORTED D O OTHER B H SMOKE/FUMES/ODORS/SPARKS ELECT. POWER LOSS-50 PC NR NOT REPORTED 1 SW 03 3683D EA112 WHILE PILOT WAS COMPLETING THE BEFORE TAKEOFF CHECK LIST, A COMPLETE ELECTRICAL SYSTEM FAILURE WAS EXPERIENCED. INITIAL INVESTIGATION REVEALED NO CIRCUIT BREAKERS, FUSES, OR CURRENT LIMITERS HAD FAILED TO OPEN. THE BATTERY WAS FOUND SMOKI NG. UPON REMOVING THE BATTERY CELL CAPS, ALL CELLS WERE FOUND ALMOST COMPLETELY DRY. SOURCE OF ELEC SHORT FOUND TO BE THE THROTTLE CONTROL CABLE, PN 36-380061-1, HAD CHAFED AGAINST THE POSITIVE BATTERY CABLE INSULATION UNTIL THE 2 CABLES SHORTED TOGETHER. THE BATTERY, POSITIVE BATTERY CABLE, AND THROTTLE CONTROL CABLE ALL HAD TO BE REPLACED TO RETURN THE AIRCRAFT TO SERVICE. (X) 1 L 7 1 3O 3A15 2000041700159 20000417 00159 NM 2000 4 17 20000412SH010 1 20000217 G 3240 BRAKE DOUG MD11 MD11 3023602 NM MLG DAMAGED H K NONE O OTHER IN INSP/MAINT 1 SW 99 272WA 6984 48437 BRAKE ASSY WAS RECEIVED FROM AIR CARRIER FOR AN OVERHAUL SERVICE. UPON DISASSEMBLY, IT WAS IDENTIFIED THE AFFECTED BRAK E SUFFERED AN EXTREME CARBON OXIDATION BREAK-DOWN ON THE INNER DIAMETER OF THE HEAT SINK. SUBMITTER SUGGESTED AN ANALYS IS OR REVIEW OF THE CARBON COMPOSITE MANUFACTURING PROCESSES. (X) 2 L 7 3 4F RT A22WE 2000041300410 20000413 00410 WP 2000 4 13 20000412SH011 2 20000309 G 7250 30723515 DISK GARRTT TFE731 TFE731* 01518 WP LP TURBINE DAMAGED H K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 19 NEW PART RECEIVED FROM HONEYWELL WITH DAMAGE ON FORWARD SIDE IN WEB AREA AND AFT SIDE IN POST FIR TREE AREA. REF: LOT NUMBER 00P040. (X) 4 F E6WE 2000041300411 20000413 00411 WP 2000 4 13 20000412SH012 2 20000309 G 7230 30723163 DISK GARRTT TFE731 TFE731* 01518 WP HP TURBINE DAMAGED H K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 99 NEW PART RECEIVED FROM HONEYWELL WITH DAMAGE ON FORWARD SIDE IN POST FIR TREE AREA. REF: LOT NUMBER 99P243. (X) 4 F E6WE 2000041300412 20000413 00412 WP 2000 4 13 20000412SH013 2 20000316 G 7250 30747522 DISK GARRTT TFE731 TFE731* 01518 WP LP TURBINE DAMAGED H K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 99 NEW PART RECEIVED FROM HONEYWELL WITH DAMAGE IN POST FIR TREE AREA ON BOTH FORWARD AND AFT SIDES. REF: LOT NUMBER 99P2 78 4 F E6WE 2000041300413 20000413 00413 WP 2000 4 13 20000412SH014 2 20000309 G 7250 30723515 DISK GARRTT TFE731 TFE731* 01518 WP LP TURBINE DAMAGED H K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 99 NEW PART RECEIVED FROM HONEYWELL WITH DAMAGE ON FORWARD SIDE IN POST FIR TREE AREA. REF: LOT NUMBER 99P341. (X) 4 F E6WE 2000041300414 20000413 00414 WP 2000 4 13 20000412SH015 2 20000310 G 7250 30723515 DISK GARRTT TFE731 TFE731* 01518 WP LP TURBINE DAMAGED H K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 99 NEW PART RECEIVED FROM HONEYWELL WITH GRIND MARKS THROUGHOUT FIR TREE AREA. REF: LOT NUMBER: 00P040. (X) 4 F E6WE 2000041700160 20000417 00160 SO 2000 4 17 20000412SH016 1 20000307 G 3213 65319004 HOUSING PIPER PA28 PA28161 7102803 SO LT MLG STRUT CRACKED B C85R K NONE O OTHER IN INSP/MAINT 1 NE 01 2159H 11250 287916192 MAIN GEAR STRUT HOUSING HAS ATTACH EARS ON IT WHERE UPPER END OF TORQUE LINK ATTACHES. STUDENT REPORTED SHIMMEY AND VIB RATION AFTER LANDING. WHEN ACFT WAS CHECKED, ONE OF TWO EARS ON THE STRUT HOUSING WAS FOUND BROKEN OFF. PART THOUGHT TO BE ORIGINAL. ACFT HAS 11,250.0 HRS SINCE NEW IN 1979. UNKNOWN IF FATIGUE PROBLEM OR STUDENT LANDED IN A GROSS-WIND AND SIDE-LOADED GEAR, OR A COMBINATION OF BOTH. (X) 1 L 7 1 3O 2A13 2000041700161 20000417 00161 EU 2000 4 17 20000412SH017 1 20000202 G 6720 AC66375 HOUSING DUNLOP SNIAS 350 AS350B2 8680813 EU TAIL ROTOR SERVO DAMAGED H K NONE O OTHER IN INSP/MAINT 1 NM 11 911LR 5791 1852 GD346 2404 FAILED EDDY CURRENT TESTING. CRACK DETECTED AT HOLE PLUG (CYLINDER) ON LOWER END OF SERVO BODY. POSSIBLE CAUSE, DURING MANUFACTURING, HOLE PLUG EITHER TOO LARGE OR HOLE PLUG INSTALLED INCORRECTLY. (X) 1 G 7 1 3U H9EU 2000041300418 20000413 00418 WP 2000 4 13 20000412SH018 1 20000109 G 6420 369021800501 SWASHPLATE HUGHES 369 369D 4470706 WP TAIL ROTOR LACK OF LUBE B EOOR K NONE O OTHER IN INSP/MAINT 1 AL 03 5074R 1709 1151D DURING INSPECTION, THE TAIL ROTOR SWASHPLATE WAS FOUND LOW ON GREASE. FURTHER INSPECTION REVEALED NO DEFECTS AND UNIT W AS RE-GREASED AND RETURNED TO SERVICE. (X) 1 G 7 1 3U H3WE 2000041300419 20000413 00419 GL 2000 4 13 20000412SH019 2 20000128 G 7420 6870855 IGNITION LEAD HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL ENGINE CHAFED B EOOR K NONE O OTHER IN INSP/MAINT 1 AL 03 5074R 1151D CAE832750 DURING POST-FLIGHT, IGNITION LEAD WAS FOUND CHAFING ON THE LOWER B-NUT OF THE PC AIR REFERENCE LINE ON THE GOVERNOR. FU RTHER INSPECTION REVEALED THE ADEL CLAMPS FOR THE LEAD AND LINE, AT THAT POINT, WERE MISSING. REPLACED MISSING CLAMPS. (X) 1 G 7 1 3U 3 U H3WE E4CE 2000041300428 20000413 00428 WP 2000 4 13 20000412SH020 1 20000104 G 6520 369D254225 SEAL HUGHES 369 369D 4470706 WP T/R TRANSMISSION LEAKING B EOOR K NONE O OTHER IN INSP/MAINT 1 AL 03 5074R 2136 1151D DURING INSPECTION, FOUND THE TAIL ROTOR OUTPUT SEAL LEAKING. REPLACED SEAL. (X) 1 G 7 1 3U H3WE 2000041300429 20000413 00429 GL 2000 4 13 20000412SH021 2 20000104 G 7310 AN8378D FITTING HUGHES 369 369D 4470706 WP ALLSN 250C 250C* GL FUEL SYSTEM LOOSE B EOOR K NONE O OTHER IN INSP/MAINT 1 AL 03 5074R 1151D DURING INSPECTION, DISCOVERED THE FIREWALL FUEL FITTING (BULKHEAD FITTING) WAS LOOSE IN THE FIREWALL. RE-TORQUED JAM NU T. (X) 1 G 7 1 3U 3 U H3WE E4CE 2000041300439 20000413 00439 WP 2000 4 13 20000412SH023 1 20000110 G 3110 CLAMP HUGHES 369 369D 4470706 WP TOT HARNESS WRONG PART B EOOR K NONE W INADEQUATE Q C IN INSP/MAINT 1 AL 03 5074R 1151D DURING INSPECTION, THE ADEL CLAMP ON THE TOT LEAD AT THE EXHAUST CLAMP WAS FOUND TO BE THE WRONG PART NUMBER AND SUBSEQU ENTLY THE CUSHION WAS UNABLE TO SURVIVE THE TEMPERATURES. REPLACED WITH PROPER PART NUMBER CLAMP. (X) 1 G 7 1 3U H3WE 2000041300440 20000413 00440 SW 2000 4 13 20000412SH024 1 20000309 G 6310 206040118001 COUPLING BELL 206 206B 1181511 SW M/R DRIVE CHIPPED B K NONE O OTHER IN INSP/MAINT 1 AL 03 304MH 1742 DURING NORMAL 600-HOUR/12-MONTH INSPECTION AND REPACK OF MAIN ROTOR DRIVESHAFT, DISCOVERED A GEAR TOOTH (ON THE END) OF THE OUTER COUPLING WAS CHIPPED. SUBMITTER SIFTED THROUGH THE GREASE, BUT COULD NOT FIND ANY EVIDENCE OF THIRD CHIP. P ART WAS RED-TAGGED AND DESTROYED. A NEW OUTER COUPLING OF SAME PART NUMBER INSTALLED AND AIRCRAFT RETURNED TO SERVICE. (X) 1 G 7 1 3U H2SW 2000041700162 20000417 00162 GL 2000 4 17 20000412SH025 1 20000314 G 3213 2082100701 AXLE DIAMON DA20 DA20A1 GL RT MLG WHEEL CRACKED B K NONE O OTHER IN INSP/MAINT 1 SO 17 125MF 3030 10016 DURING WALK-AROUND, INSTRUCTOR NOTICED CRACK ON TOP OF AXLE FLANGE BOLT THROUGH-HOLE. SUSPECT CRACK FORMED BY STRESS CO RROSION. SUBMITTER RECOMMENDED AXLE BE REPLACED AT 2,000-HR OR REPLACE ANODIZED ALUMINUM WITH ONE MADE OF STEEL JUST LI KE THE MATING SURFACE OF GEAR LEG. (X) 1 L 7 1 3O NT TA4CH 2000041300441 20000413 00441 CE 2000 4 13 20000412SH026 1 20000207 G 2731 C419175 CHAIN CESSNA 500 550 2076604 CE ELEVATOR SEPARATED E A UNSCHED LANDING F FLT CONT AFFECTED DE DESCENT 1 CE 01 7ZU 225 5500433 UPON DESCENT INTO FCM, PILOT REPORTED ELECTRIC ELEVATOR TRIM WAS UNRESPONSIVE. PILOT ATTEMPTED TO HAND TRIM THE AIRCRAF T AND FOUND MANUAL TRIM WHEEL FREE TO TURN WITH NO RESISTANCE. CREW FOUND ELEVATOR CONTROL HEAVY AND HARD TO MOVE. THE PILOTS ELECTED TO DIVERT INTO MSP. INVESTIGATION INTO THE CAUSE REVEALED THE TRIM CABLE FORWARD ATTACH CHAIN MASTER LI NK HAD BECOME DISCONNECTED AND WAS FOUND IN THE BELLY OF THE AIRCRAFT ALONG WITH THE ATTACHING HARDWARE AND THE TRIM CAB LES. NO OTHER DISCREPANCIES WERE FOUND WITH THE SYSTEM. (X) 1 L 7 2 4F A22CE 2000041700163 20000417 00163 EA 2000 4 17 20000412SH027 2 20000318 G 7322 LW10540 CARBURETOR PIPER PA32 PA32260 7103206 SO LYC O540 O540E4B5 41532 EA ENGINE SEPARATED D O OTHER O OTHER NR NOT REPORTED 1 SO 33 6YB 1800 321179 L669940 CARBURETOR SEPARATED AT PARTING SURFACE CAUSING BOTTOM HALF OF CARBURETOR TO ALMOST FALL OFF. LOCKING TABS WERE LOCKED, BOLTS WERE LOOSE. SUBMITTER STATED THIS IS THE 3RD CARBURETOR TO HAVE THIS TYPE FAULT. (X) 1 L 7 1 3O 3 O A3SO E295 2000041300487 20000413 00487 WP 2000 4 13 20000412SH028 1 20000307 G 7720 PROBE HUGHES 369 369HS 4470728 WP ALLSN 250C 250C20 03013 GL ENGINE DAMAGED B H8OR O OTHER O OTHER NR NOT REPORTED 1 NM 07 9094F 1000 1110352S CEA82310 THE NYLON INSERT IN THE TEMPERATURE PROBE LET GO RESULTING IN FLUCTUATION AND DROPPING OIL PRESSURE AND A LOSS OF OIL. THE ENGINE HAD TO BE TORN DOWN FOR INSPECTION. MAIN DAMAGE SEEMS TO BE THE ENGINE''S NR 8 BEARING WHICH WAS DESTROYED. (X) 1 G 7 1 3U 3 U H3WE E4CE 2000041300488 20000413 00488 CE 2000 4 13 20000412SH029 1 20000316 G 3230 554110313 UPLOCK CESSNA 500 550 2076604 CE LT MLG DAMAGED B O OTHER O OTHER NR NOT REPORTED 1 SW 15 CCDGA 657 CUSTOMER STATED HE REPLACED LT MLG UPLOCK HOOK DUE TO EXCESS PLAY AT ATTACH BOLT/SPACER AREA. MAINT FACILITY CONDUCTED PHASE-5 INSP AND ADD''L WORK. DURING L/G EXTEND/RETRACT TEST NOTED DURING EXT CYCLE, NOSE AND RT MLG EXTENDED NORMALLY, BUT LT FREE FELL. AFTER T/S, FOUND PRESS TO UPLOCK CYL, BUT NO PRESS AT OUTSIDE WHICH GOES TO DOWN SIDE OF MLG ACTUATO R. FOUND IF CLEVIS PIN WAS REMOVED FROM LINKAGE, THAT CONNECTS UPLOCK ACT TO HOOK, LT GEAR ACT EXTENDED NORMALLY. NOTI FIED CESSNA UPLOCK HOOK WAS CONTACTING RADIUS OF SUPPORT BRACKET. CESSNA BELIEVED CAUSE WAS A RADIUS CUT WAS ELIMINATED DURING MFG. SUPPORT HAD GOUGE WHERE HOOK CONTACTED IT AND CESSNA REQUESTED BOTH HOOK AND SUPPORT BE REPLACED. (X) 1 L 7 2 4F A22CE 2000041300489 20000413 00489 NE 2000 4 13 20000412SH030 2 20000320 G 7310 30718321 MANIFOLD ISRAEL 1124 1124 4500102 EU GARRTT TFE731 TFE73131G 29003 NE FUEL SYSTEM LEAKING H K NONE K FLUID LOSS IN INSP/MAINT 1 SW 99 727AT 6382 284 P76205 DURING ROUTINE 300-HR ENG INSP, FUEL DISCOVERED PUDDLED INSIDE THE LEFT ENGINE LOWER COWLING. A LEAK CHECK CONFIRMED FU EL LEAKING FROM BOTTOM RIB DUCT WHERE THE PRIMARY AND SECONDARY FUEL MANIFOLD LINES ENTER THE 6 O''CLOCK STRUT. LEAK WA S PINPOINTED TO A CRACKED INNER FUEL MANIFOLD FITTING INSIDE STRUT. INNER MANIFOLD HAD CRACKED AT SECONDARY MANIFOLD FI TTING WHERE IT IS BRAZED ONTO INNER MANIFOLD. (X) 2 M 7 2 4F 4 F A2SW E6WE 2000041300497 20000413 00497 SW 2000 4 13 20000412SH033 1 20000114 G 7722 BUMPER BLOCK AMETEK SEL019DS1 BELL 206 206L1 1182107 SW COCKPIT DAMAGED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 XATKU 217AB 45697 DURING START, POINTER STOP ARM STUCK TO LATEX BUMPER. REPLACED LATEX BUMPER WITH NON-STICKING MATERIAL. (X) 1 G 7 1 3U H2SW 2000041300506 20000413 00506 SW 2000 4 13 20000412SH034 1 20000224 G 7722 BUMPER BLOCK AMETEK SEL019DS1 BELL 206 206L1 1182107 SW COCKPIT DAMAGED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 5740L 300BA 45459 DURING START, POINTER STOP ARM STUCK TO LATEX BUMPER. REPLACED LATEX BUMPER WITH NON-STICKING MATERIAL. (X) 1 G 7 1 3U H2SW 2000041300507 20000413 00507 SW 2000 4 13 20000412SH035 1 20000305 G 6510 407340339103 BEARING BELL BELL 407 407 SW TAIL ROTOR DRIVE ROUGH B ALGR O OTHER O OTHER NR NOT REPORTED 1 SW 03 437AL 329 AF8906 53141 BEARINGS NOISEY AND ROUGH. REMOVED AND REPLACED 2 EACH BEARINGS. (X) 1 G 7 1 3U O H2SW 2000041300508 20000413 00508 SW 2000 4 13 20000412SH036 1 20000305 G 6510 407340339103 BEARING BELL BELL 407 407 SW TAIL ROTOR DRIVE ROUGH B ALGR O OTHER O OTHER NR NOT REPORTED 1 SW 03 437AL 5329 AF8906 53141 BEARINGS NOISEY AND ROUGH. REMOVED AND REPLACED 2 EACH BEARINGS. (X) 1 G 7 1 3U O H2SW 2000041700165 20000417 00165 SO 2000 4 17 20000412SH039 1 20000223 G 7922 53E19600 VERNATHERM PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA OIL TEMP REGULAT DAMAGED B FGQR A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION NR NOT REPORTED 1 SO 01 137JH 318252025 L247468A PILOTS REPORTED ENGINE NOT MAKING FULL POWER AND OIL PRESSURE LOW. MAINTENANCE FOUND A PIECE OF CLIP UNDER THE OIL PRES SURE RELIEF VALVE. THE RETAINING CLIP FOR THE VERNATHERM VALVE FOUND TO BE THE SOURCE. FOUR NEW VERNOTHERM VALVES INST ALLED. (X) 1 L 7 2 3O 3 O A20SO E14EA 2000041700166 20000417 00166 CE 2000 4 17 20000412SH040 1 20000222 G 7810 1099500001 EXHAUST PIPE BEECH 90 C90A 1152911 CE PWA PT6 PT6A21 52043 EA ENGINE CRACKED B BQVR K NONE O OTHER IN INSP/MAINT 1 EA 01 600FL 282 LJ1540 CRACKED EXHAUST STACK. 2.75 INCH CRACK WAS FOUND AROUND CIRCUMFERENCE AT WELD ATTACH POINT OF NACELLE INLET DE-ICE TUB E. SUBMITTER STATED THIS IS THE 5TH OCCURRENCE OF SAME PROBLEM ON SAME AIRCRAFT. A RAYTHEON REP HAS BEEN CONTACTED AND A FUTURE SERVICE BULLETIN IS PENDING RELEASE. (X) 1 L 7 2 3T 4 T RT 3A20 E4EA 2000042500114 20000425 00114 EU 2000 4 25 20000413SH001 1 20000222 G 5210 1172428112 CATCHER BOLKMS BK117 BK117C1 5626025 EU DOOR WORN B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 317MC 7505 CATCHER WORN. REMOVED AND REPLACED. (X) 1 G 7 2 3U NC H13EU 2000042500115 20000425 00115 EU 2000 4 25 20000413SH002 1 20000222 G 5210 1172428212 CATCHER BOLKMS BK117 BK117C1 5626025 EU RT DOOR WORN B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 317MC 7505 RIGHT CATCHER WORN. REMOVED AND REPLACED. (X) 1 G 7 2 3U NC H13EU 2000041700170 20000417 00170 EU 2000 4 17 20000413SH004 1 20000222 G 5210 1172427302 GUIDE BOLKMS BK117 BK117C1 5626025 EU CREW DOOR WORN B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 317MC 7505 RIGHT GUIDE WORN. REMOVED AND REPLACED. (X) 1 G 7 2 3U NC H13EU 2000041700171 20000417 00171 EU 2000 4 17 20000413SH005 1 20000222 G 6330 L633M2001105 MOUNT UROCOP EC135 EC135P1 8680990 EU TRANSMISSION LEAKING B TI1R K NONE K FLUID LOSS IN INSP/MAINT 1 SW 05 911SV 391 0070 LEAKING FLUID. REMOVED AND REPLACED. (X) 1 G 7 2 3U O H88EU 2000041700173 20000417 00173 SW 2000 4 17 20000413SH007 1 20000115 G 6322 230365001101 BLOWER BELL 230 230 1182149 SW OIL COOLER VIBRATION B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 4UV 2135 23019 OIL COOLER BLOWER HAD HIGH VIBRATION, .4 IPS. REMOVED AND REPLACED. (X) 1 G 7 2 3U NC H9SW 2000041700174 20000417 00174 2000 4 17 20000413SH008 4 20000302 G 3425 066304605 INDICATOR BOLKMS 105 BO105S 5626006 EU COCKPIT HSI MALFUNCTIONED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 4572R S663 NEEDLE DOES NOT FULLY DEFLECT. REMOVED AND REPLACED. (X) 1 G 7 2 3U H3EU 2000041700175 20000417 00175 SW 2000 4 17 20000413SH009 1 20000209 G 6410 222016001131 BLADE BELL 230 230 1182149 SW TAIL ROTOR CRACKED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 4UV 1257 23019 PITCH CHANGE BEARINGS CRACKED. REMOVED AND REPLACED. (X) 1 G 7 2 3U NC H9SW 2000041700176 20000417 00176 SW 2000 4 17 20000413SH010 1 20000209 G 6410 222016001123 BLADE BELL 230 230 1182149 SW TAIL ROTOR CRACKED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 4UV 2465 23019 PITCH CHANGE BEARINGS CRACKED. REMOVED AND REPLACED. (X) 1 G 7 2 3U NC H9SW 2000041700177 20000417 00177 EU 2000 4 17 20000413SH011 1 20000224 G 5320 1176625501 FIREWALL BOLKMS BK117 BK117C1 5626025 EU ENGINE BAY CRACKED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 317MC 7505 FIRE WALL ASSEMBLY CRACKED. REMOVED AND REPLACED. (X) 1 G 7 2 3U NC H13EU 2000041700178 20000417 00178 EU 2000 4 17 20000413SH012 1 20000215 G 7712 10594575 TRANSMITTER BOLKMS 105 BO105LSA3 5626020 EU ENGINE TORQUE READS HIGH B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 8118Y 342 2017 TORQUE TRANSMITTER OUT OF CALIBRATION. READING HIGH SETTING OF LIGHT. REMOVED AND REPLACED. (X) 1 G 7 2 3U H3AU 2000041700179 20000417 00179 EU 2000 4 17 20000413SH013 1 20000301 G 7714 1179405303 INDICATOR BOLKMS 117 BK117A4 5626017 EU TRIPLE TACH FAILED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 117NG 7083 NR 2 NEEDLE WENT TO ZERO IN-FLIGHT. REMOVED AND REPLACED. (X) 1 G 7 2 3U H13EU 2000041700180 20000417 00180 NE 2000 4 17 20000413SH014 2 20000125 G 7313 0283317500 INJECTOR BOLKMS BK117 BK117C1 5626025 EU TMECA ARRIEL ARRIEL1 60030 NE ENGINE CLOGGED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 317MC 7505 INJECTOR CLOGGED. REMOVED AND REPLACED. (X) 1 G 7 2 3U 3 U NC H13EU E19EU 2000041700181 20000417 00181 NE 2000 4 17 20000413SH015 2 20000125 G 7313 0283317500 INJECTOR BOLKMS BK117 BK117C1 5626025 EU TMECA ARRIEL ARRIEL1 60030 NE ENGINE CLOGGED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 317MC 7505 INJECTOR CLOGGED. REMOVED AND REPLACED. (X) 1 G 7 2 3U 3 U NC H13EU E19EU 2000041700183 20000417 00183 EU 2000 4 17 20000413SH016 1 20000119 G 6340 1179403605 INDICATOR BOLKMS BK117 BK117C1 5626025 EU TRANSMISSION OIL INOPERATIVE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 117NC 7509 TRANS OIL INDICATION LIGHT INOPERATIVE. REMOVED AND REPLACED. (X) 1 G 7 2 3U NC H13EU 2000041700184 20000417 00184 2000 4 17 20000413SH017 4 20000202 G 2397 CIX100XVHGK66P WIRE BOLKMS 105 BO105S 5626006 EU COMM DAMAGED B K NONE O OTHER IN INSP/MAINT 1 SW 05 4572R S663 UPON INITIAL INSTALLATION, CORD SQUEALS AS SOON AS HOOKED UP. REMOVED AND REPLACED. (X) 1 G 7 2 3U H3EU 2000041700185 20000417 00185 EU 2000 4 17 20000413SH018 1 20000203 G 2913 40165 PUMP BOLKMS 117 BK117A1 5626010 EU HYD SYSTEM WORN B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 117M S7023 SPLINES ON HYDRAULIC PUMP WORN. REMOVED AND REPLACED. (X) 1 G 7 2 3U H13EU 2000041700188 20000417 00188 2000 4 17 20000413SH020 4 20000224 G 2311 TFM500G TRANSCEIVER SNIAS 350 AS350B2 8680813 EU UHF COMM INTERMITTENT B TI1R O OTHER O OTHER NR NOT REPORTED 1 SW 05 40751 221 3154 TRANSCEIVER TRANSMITS INTERMITTENTLY ON UHF FREQUENCIES. REMOVED AND REPLACED. (X) 1 G 7 1 3U H9EU 2000041700189 20000417 00189 SW 2000 4 17 20000413SH021 1 20000118 G 3340 900601 LANDING LIGHT BELL 230 230 1182149 SW FUSELAGE INOPERATIVE B TI1R O OTHER O OTHER NR NOT REPORTED 1 SW 05 4UV 23019 LANDING LIGHT HAD NO POWER AT LIGHT. LIGHT WILL NOT COME ON. REMOVED AND REPLACED. (X) 1 G 7 2 3U NC H9SW 2000041700190 20000417 00190 EU 2000 4 17 20000413SH022 1 20000211 G 3310 1179203103 CONTROLLER BOLKMS 117 BK117A3 5626015 EU COCKPIT INOPERATIVE B TI1R O OTHER O OTHER NR NOT REPORTED 1 SW 05 1140H 3 7078 COPILOT''S LIGHTING INOPERABLE. NO OUTPUT FROM UNIT. WORKED 2.7 HOURS AFTER INSTALLATION. REMOVED AND REPLACED. (X) 1 G 7 2 3U H13EU 2000041700191 20000417 00191 EU 2000 4 17 20000413SH023 1 20000209 G 3310 1179203103 CONTROLLER BOLKMS 117 BK117A3 5626015 EU COCKPIT INOPERATIVE B TI1R O OTHER O OTHER NR NOT REPORTED 1 SW 05 1140H 7078 CONTROL LUNIT WILL NOT ILLUMINATE LIGHT. REMOVED AND REPLACED. (X) 1 G 7 2 3U H13EU 2000041700195 20000417 00195 EU 2000 4 17 20000413SH024 1 20000214 G 6520 350A33215300 BEARING SNIAS 350 AS350B2 8680813 EU TAIL ROTOR DELAMINATED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 350AZ 512 3127 BEARING CRACKED ON OUTER CENTER OF LAMINATION. REMOVED AND REPLACED. (X) 1 G 7 1 3U H9EU 2000041700197 20000417 00197 2000 4 17 20000413SH026 4 20000115 G 3425 066304605 INDICATOR BOLKMS 117 BK117A4 5626017 EU COCKPIT HSI INOPERATIVE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 117NG 7083 KI525A INTERNAL LIGHT INOPERATIVE. REMOVED AND REPLACED. (X) 1 G 7 2 3U H13EU 2000041700198 20000417 00198 EU 2000 4 17 20000413SH027 1 20000124 G 6210 117151321 BLADE BOLKMS 117 BK117B1 5626012 EU MAIN ROTOR DEBONDED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 170MC 193 7217 LEADING EDGEOF MAIN ROTOR BLADE DEBONDING (INBOARD JOINT). 193.4 HOURS SINCE REPAIR/OVERHAUL. REMOVED AND REPLACED. (X) 1 G 7 2 3U H13EU 2000041700205 20000417 00205 2000 4 17 20000413SH028 4 20000131 G 3421 5040017926 GYRO BOLKMS 117 BK117B1 5626012 EU COCKPIT FAILED B TI1R O OTHER O OTHER NR NOT REPORTED 1 SW 05 170MC 7217 ATTITUDE GYRO WILL NOT CAGE. TECHNICIAN STATED UNIT ONLY WORKED FOR ONE WEEK AFTER INSTALLATION. REMOVED AND REPLACED. (X) 1 G 7 2 3U H13EU 2000041700233 20000417 00233 SW 2000 4 17 20000413SH036 1 20000106 G 6300 222044006109A SHAFT BELL 230 230 1182149 SW ALLSN 250C 250C30 03013 GL MAIN ROTOR WILL NOT BALANCE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 4UV 1246 23019 ENGINE SIDE OF SHAFT WILL NOT BALANCE. REMOVED AND REPLACED. (X) 1 G 7 2 3U 3 U NC H9SW E1GL 2000041700236 20000417 00236 2000 4 17 20000413SH039 4 20000124 G 3416 1042011968E ENCODER BOLKMS 117 BK117B2 5626013 EU COCKPIT MALFUNCTIONED B TI1R O OTHER O OTHER NR NOT REPORTED 1 SW 05 117MK 7196 ALTIMETER OUT OF CALIBRATION. DOES NOT AGREE WITH COPILOT''S ALTIMETER OR TEST BOX. OFF AT 3,000 FEET. REMOVED AND RE PLACED. (X) 1 G 7 2 3U NC H13EU 2000041700237 20000417 00237 EU 2000 4 17 20000413SH040 1 20000113 G 7714 1179405603 INDICATOR BOLKMS 117 BK117A3 5626015 EU COCKPIT FLUCTUATES B TI1R O OTHER O OTHER NR NOT REPORTED 1 SW 05 527MB 7103 INDICATOR FLUCTUATES UNDER POWER. REMOVED AND REPLACED. (X) 1 G 7 2 3U H13EU 2000041700238 20000417 00238 EU 2000 4 17 20000413SH041 1 20000112 G 7714 1179405603 INDICATOR BOLKMS 117 BK117A3 5626015 EU COCKPIT DAMAGED B TI1R O OTHER O OTHER NR NOT REPORTED 1 SW 05 527MB 7103 NG INDICATOR TRIPPED CIRCUIT BREAKER WHEN INSTALLED AFTER REPAIR. REMOVED AND REPLACED. (X) 1 G 7 2 3U H13EU 2000041700242 20000417 00242 EU 2000 4 17 20000413SH042 1 20000115 G 7714 1179405303 INDICATOR BOLKMS 117 BK117A4 5626017 EU TRIPLE TACH INACCURATE B TI1R O OTHER O OTHER NR NOT REPORTED 1 SW 05 171MU 7138 TRIPLE TACHOMETER, NR 2 NEEDLE READS IMPROPER. REMOVED AND REPLACED. (X) 1 G 7 2 3U H13EU 2000042500152 20000425 00152 CE 2000 4 25 20000413SH044 1 20000222 G 7810 1099500001 EXHAUST PIPE BEECH 90 C90A 1152911 CE ENGINE CRACKED B BQVR K NONE O OTHER IN INSP/MAINT 1 SW 05 600FL 21 LJ1540 CRACKED EXHAUST STACK. SUBMITTER STATED THIS IS THE 6TH OCCURRENCE OF SAME PROBLEM ON SAME AIRCRAFT. 1.5 INCH CRACK WAS FOUND AROUND CIRCUMFERENCE AT WELD ATTACH POINT OF NACELLE INLET DE-ICE TUBE. A RAYTHEON REP HAS BEEN CONTACTED AND A FUTURE SERVICE BULLETIN IS PENDING RELEASE. (X) 1 L 7 2 3T RT 3A20 2000041900263 20000419 00263 EA 2000 4 19 20000413SH045 2 20000102 G 8520 SHAFT PIPER PA18 PA18150 7101828 SO LYC O320 O320A2B 41508 EA IDLER GEAR DAMAGED H K NONE O OTHER IN INSP/MAINT 1 NM 05 5986Z 1591 188242 L4842427A 1,590.6 HRS SINCE FACTORY NEW ENGINE INSTALLED. CRANKSHAFT APPEARED TO BE BINDING WITH SPARK PLUGS REMOVED. METAL (STEE L & ALUM) IN SCREENS. UPON REMOVAL OF MAGNETOS, OBSERVED LT IDLER GEAR COCKING BEFORE IT TURNED, WHILE MOVING CRANKSHAF T FLANGE BACK AND FORTH APPROX 30 DEGREES. UPON REMOVAL OF ACCESSORY CASE, FOUND LT IDLER SHAFT LOOSE AT CRANKCASE ATTA CH. DAMAGE NOTED TO IDLER SHAFT AND CRANKCASE BOSS, RT IDLER SHAFT ATTACH BOLT, LOWER BOLT FND FINGER TIGHT, UPPER, BO LT FND PROPERLY TORQUED. BOTH STILL SAFETY WIRED. ENGINE DISMANTLED FOR COMPLETE O/H. (X) 1 H 7 1 3O 3 O 1A2 E274 2000041900264 20000419 00264 CE 2000 4 19 20000413SH046 1 20000413 G 3241 99123056 CONTROL BOX HYTROL7K3427 CESSNA 500 560CESSNA 2076750 CE ANTI-SKID SYSTEM FAILED H D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 SW 05 560MM 2545 5600235 DURING TAH, PRIOR TO TAKEOFF, FOOT BRAKES APPLIED, NO BRAKING ACTION TOOK PLACE. BRAKE SYS PRE-SELECTED TO THE ATTACHED MODE. INVEST REVEALED WITH ANTI-SKID SELECTED THE FAULT LIGHT WAS OUT WITH BRAKES APPLIED. INITIALLY, BRAKES WENT ON, BUT RELEASED AND STAYED RELEASED. APPEARS ANTI-SKID CONTROL BOX FAILED WITH BRAKE VALVES IN OPEN POSITION. BRAKE ANTI -SKID CONTROL BOX, PN 9912305-6, SN 847, WAS REMOVED. RECORDS SHOWS ORIG INSTALL 12-93, ACFT BUILD DATE. A TEST OF IND ICATION SYS FOR ANTI-SKID SHOWED SWITCH ON-LIGHT OUT, BUT ON REPLACEMENT PART, SWITCH ON-LIGHT OUT-LIGHT ON-LIGHT OUT. (X) 2 L 7 2 4F RT A22CE 2000041900266 20000419 00266 CE 2000 4 19 20000413SH048 1 20000218 G 2820 17160081 SEAL CESSNA 206 206H 2073301 CE FUEL SYSTEM LEAKING D K NONE K FLUID LOSS IN INSP/MAINT 1 SW 99 7264D 97 20608062 DURING INITIAL 100-HOUR INSPECTION ON A NEW CESSNA 206H, FUEL WS FOUND LEAKING FROM THE RIGHT SIDE FUEL SENDER SCREWS. INSPECTION REVEALED LEAK EMANATING FROM IMPROPERLY SEALED NUT RING. AFTER REMOVAL, INSPECTION REVEALED TWO VOIDS BETWEE N NUT RING AND RIB. EXAMINATION OF AREA REVEALED AN UNKNOWN WHITE POWDERY SUBSTANCE IN THE VOID WHERE SEALANT WAS OMITT ED. POSSIBLE CAUSE WAS IMPROPER SEALING TECHNIQUES DURING THE AIRCRAFT''S MANUFACTURING PROCESS. (X) 1 H 7 1 3O RT A4CE 2000042500156 20000425 00156 EU 2000 4 25 20000413SH049 2 20000211 G 7320 CASE504 REGULATOR GULSTM G1159 GIV 3980115 SO RROYCE TAY TAY6118 EU RT ENGINE FAULTY B BTVR O OTHER J WARNING INDICATION DE DESCENT 1 GL 23 7800 3445 1098 16135 ON DESCENT FROM HIGH ALTITUDE WITH AUTO-THROTTLES DISCONNECTED, THE RT ENGINE WOULD NOT DECREASE TO AN IDLE SETTING WITH THE THROTTLES PHYSICALLY IN THE HARD IDLE POSITION. ENGINE FINALLY RETARDED TO IDLE WHEN DESCENDING BELOW 10,000 FEET, SLOWING BELOW 260 KNOTS AND TURNING ON ENGINE AND WING ANTI-ICE. AIRCRAFT WAS BEING FLOWN ON A MAINTENANCE TEST FLIGHT DUE TO A DOUBLE ENGINE CHANGE. AIRCRAFT LANDED SAFELY. (X) 2 L 7 2 4F 4 F RT A12EA E25NE 2000041700004 20000417 00004 EU 2000 4 17 20000413SH051 1 20000215 G 6240 10594564 INDICATOR BOLKMS 105 BO105LSA3 5626020 EU M/R MAST READS HIGH B TI1R O OTHER O OTHER NR NOT REPORTED 1 SW 05 8118Y 342 2017 MAST INDICATOR OUT OF CALIBRATION. READING HIGH SETTING OF LIGHT. REMOVED AND REPLACED. (X) 1 G 7 2 3U H3AU 2000041900270 20000419 00270 CE 2000 4 19 20000413SH052 1 20000303 G 2120 SMOKE LEAR 35 35A 5170602 CE CABIN DETECTED B O OTHER B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 SW 99 77NR 503 CARPET EDGE CAME INTO CONTACT WITH WING HEAT DUCT. WING HEAT WAS USED LONGER THAN NORMAL DUE TO WEATHER CONDITIONS. TH E CARPET EDGE WAS HEATED UNTIL IT STARTED SMOKING. THE AIRCRAFT DIVERTED FOR PRECAUTION. THE CARPET WAS TRIMMED BACK A ND ADDITIONAL INSULATION WAS INSTALLED TO PREVENT RECURRENCE. (X) 2 L 7 2 4F A10CE 2000041900271 20000419 00271 SO 2000 4 19 20000413SH053 1 20000208 G 3222 67037004 STRUT PIPER PA44 PA44180 7104402 SO LT MLG BROKEN B A UNSCHED LANDING D INFLIGHT SEPARATION CL CLIMB 1 GL 21 851ND 5737 4495005 AFTER THROTTLE ADVANCEMENT ON A TOUCH AND GO LANDING, THE LEFT MAIN GEAR STRUT BROKE INSIDE THE FORK CASTING. THE MAIN WHEEL ASSY AND FORK REMAINED ATTACHED TO THE AIRCRAFT BY THE BRAKE HOSE AND WAS WEDGED UNDER THE LEFT NACELLE AND FLAP. PROPELLER ON LEFT SIDE CONTACTED RUNWAY. RESEARCH OF MAINTENANCE RECORDS REVEALED STRUT HAD NEVER BEEN REPLACED. (X) 1 L 7 2 3O A19S0 2000041900272 20000419 00272 EA 2000 4 19 20000413SH054 2 20000228 G 8530 LW12416 CYLINDER CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA NR 4 DAMAGED H A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION NR NOT REPORTED 1 SW 99 9621V 832 17264401 L3469527A PILOT REPORTED ROUGH RUNNING ENGINE AND LOW RPM. MAINTENANCE FOUND NR 4 CYLINDER HAD EXHAUST VALVE STUCK OPEN, NR 4 CYL INDER PUSH ROD AND HOUSING WERE BENT WITH NO OIL LEAKAGE. THE PISTON WAS NOT DAMAGED AND NO METAL FOUND IN THE ENGINE O IL FILTER. (X) 1 H 7 1 3O 3 O NT 3A12 E274 2000041900279 20000419 00279 GL 2000 4 19 20000413SH055 3 20000328 G 6114 B4426 SNAP RING CESSNA 182 182Q 2072732 CE CONT O470 O470U 17026 SO MCAULY 2A34C C2A34C204 GL HUB SEPARATED D O OTHER E VIBRATION/BUFFET NR NOT REPORTED 1 WP 03 735HK 18265435 813259R 767951 INSTALLED OVERHAULED PROPELLER. FLIGHT TEST PERFORMED, ABOUT 20 MINUTES LATER, FELT SLIGHT VIBRATION. LANDED FOR CAUSE AND FOUND SNAP RING AND SHIMS OUT OF HUB ON BLADE SHANK. PROPELLER TSO: .4 HOUR. (X) 1 H 7 1 3O 3 O NT 3A13 E273 5 C P3EA 2000042000112 20000420 00112 NE 2000 4 20 20000413SH056 3 20000404 G 6111 C60661 BLADE DORNER DO32 DO328100 2996000 NM PWA 119 PW119B NE HARTZL HDE6C HDE6C3B NE PROPELLER CRACKED H K NONE O OTHER IN INSP/MAINT 1 SW 99 HL274 DURING SEARCH INSPECTION, 4 EACH C-6066-1 PRELOAD PLATES WERE FOUND CRACKED. (X) 2 H 7 2 4T 4 T RT A45NM E20NE 6 C P34NE 2000042000113 20000420 00113 NE 2000 4 20 20000413SH057 3 20000405 G 6114 A4959 BUSHING DORNER DO32 DO328100 2996000 NM PWA 119 PW119B NE HARTZL HDE6C HDE6C3B NE HUB BROKEN H K NONE O OTHER IN INSP/MAINT 1 SW 99 HL274 DURING SEARCH INSPECTION, FOUND THE A-4659 VESPEL BUSHING WAS MISSING FROM THE HUB PITCH CHANGE ROD BORE. FRAGMENTS OF THE BUSHING WERE FOUND IN THE HUB ASSEMBLY. (X) 2 H 7 2 4T 4 T RT A45NM E20NE 6 C P34NE 2000042000114 20000420 00114 NE 2000 4 20 20000413SH058 3 20000404 G 6111 C60661 PLATE DORNER DO32 DO328100 2996000 NM PWA 119 PW119B NE HARTZL HDE6C HDE6C3B NE PROPELLER BLADE CRACKED H K NONE O OTHER IN INSP/MAINT 1 SW 99 426JS 2161 3038 HL221 DURING SEARCH INSPECTION, 4 EACH C-6066-1 PRELOAD PLATES WERE FOUND CRACKED. ONE EACH PRELOAD PLATE WAS CRACKED IN SUCH A MANNER THAT IT BROKE DURING INSPECTION. TIME SINCE LAST INSPECTION: 2,160:30 HOURS. (X) 2 H 7 2 4T 4 T RT A45NM E20NE 6 C P34NE 2000042000115 20000420 00115 CE 2000 4 20 20000413SH059 1 20000404 G 3242 353800657 VALVE BEECH 76 76 1153005 CE PARKING BRAKE FAILED C K NONE O OTHER IN INSP/MAINT 1 SW 99 822ER ME293 DURING ENGINE-OUT TRAINING, IF THE PILOT''S RT RUDDER IS FULLY DEPRESSED AND THE PILOT''S FOOT IS HIGH AND RT ON THE RUD DER PEDAL, THE PILOT''S RT FOOT CAN INADVERTENTLY PULL BACK ON THE PARKING BRAKE VALVE ACTUATOR ARM AND SET THE BRAKES. IF NOT CAUGHT PRIOR TO LANDING, BLOWN TIRES WILL RESULT WITH POSSIBLE LOSS OF DIRECTIONAL CONTROL. BEECHCRAFT (RAYTHEO N) HAS BEEN NOTIFIED. HAVE REQUESTED THEIR HELP IN POSSIBLE RELOCATION OF THE VALVE. (X) 1 L 7 2 3O A29CE 2000042000117 20000420 00117 EA 2000 4 20 20000413SH060 2 20000329 G 7322 30766 FLOAT FACET CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA CARBURETOR STUCK D O OTHER R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 SW 15 757NJ 75027003 15279870 L167571 ENGINE LOST POWER. POSSIBLE CAUSE WAS LACK OF FUEL CAUSED BY STICKING FLOAT. REMOVED CARBURETOR AND DISASSEMBLED. COUL D FIND NO CAUSE FOR FLOAT TO STICK. SUBMITTER SUGGESTED TO PREVENT RECURRENCE, USE NEW STYLE FLOAT AT OVERHAUL. (X) 1 H 7 1 3O 3 O NT 3A19 E223 2000042000118 20000420 00118 SO 2000 4 20 20000413SH061 1 20000324 G 3200 LANDING GEAR PIPER PA24 PA24250 7102404 SO FUSELAGE COLLAPSED H O OTHER O OTHER TX TAXI/GRND HDL 1 SW 99 6404P 241514 GEAR COLLAPSED ON ROLL-OUT. PILOT AND PASSENGER OBSERVED GREEN LIGHT ON FINAL. PIPER SL 782B DESCRIBES SIMILAR SCENERI O. (X) 1 L 7 1 3O 1A15 2000042500082 20000425 00082 2000 4 25 20000413SH062 4 20000327 G 2210 065001790100 ROLL SERVO CESSNA 182 182S 2072701 CE AUTOPILOT INOPERATIVE B HI1R K NONE O OTHER IN INSP/MAINT 1 NE 05 23383 143 18280406 FOUND AUTOPILOT ROLL SERVO IDLER GEAR ATTACH NUT BACKED OFF SCREW AND OUTPUT GEAR BEARINGS DEFECTIVE DURING COMPLIANCE W ITH SB KS271C-5 ALERT DATED FEB 1, 2000. SUBMITTER STATED FAILURE COULD CAUSE SERVO TO REMAIN ENGAGED EVEN WHEN AUTOPIL OT IS DISENGAGED. (X) 1 H 7 1 3O NT 3A13 2000042500109 20000425 00109 2000 4 25 20000413SH063 4 20000324 G 6122 B41832 FLYWEIGHT HARTZL PIPER PA31 PA31P350 7103111 SO PROP GOVERNOR CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 9238Y 1585 A41J 31P8414023 CRACK INDICATION AT DRIVE END OF BASE. (X) 1 L 7 2 3O RT A8EA 2000042500084 20000425 00084 EA 2000 4 25 20000413SH064 2 20000209 G 8500 NR5 BEARING PIPER PA46 PA46350P SO LYC O540 TIO540AE2A 41532 EA ENGINE MAKING METAL B AJVR K NONE O OTHER IN INSP/MAINT 1 GL 11 997MA 337 4636126 L984061A DURING AN ANNUAL INSPECTION, FOUND METAL IN OIL SCREEN. REMOVED ENGINE AND SENT TO LYCOMING FOR REPAIRS. (X) 1 L 7 1 3O 3 O RT A25SO E14EA 2000041700128 20000417 00128 EA 2000 4 17 20000414SH001 2 20000209 G 8550 NR5 BEARING PIPER PA46 PA46350P SO LYC O540 TIO540AE2A 41532 EA ENGINE MAKING METAL B AJVR K NONE O OTHER IN INSP/MAINT 1 GL 11 9299P 336 4636123 L984961A DURING AN ANNUAL INSPECTION, FOUND METAL SHAVINGS IN OIL SCREEN. REMOVED ENGINE AND SENT TO LYCOMING FOR REPAIRS. (X) 1 L 7 1 3O 3 O RT A25SO E14EA 2000041700167 20000417 00167 EA 2000 4 17 20000414SH002 2 20000209 G 8550 NR5 BEARING PIPER PA46 PA46350P SO LYC O540 TIO540A2A 41532 EA ENGINE MAKING METAL B K NONE O OTHER IN INSP/MAINT 1 GL 11 229MA 215 4636129 L985961A DURING AN ANNUAL INSPECTION, FOUND METAL SHAVINGS IN OIL SCREEN. REMOVED ENGINE AND SENT TO LYCOMING FOR REPAIRS. (X) 1 L 7 1 3O 3 O RT A25SO E14EA 2000041700096 20000417 00096 CE 2000 4 17 20000414SH003 1 20000320 G 3246 95439914 WHEEL LEAR 35 35A 5170602 CE MLG DAMAGED E O OTHER O OTHER TX TAXI/GRND HDL 1 SW 99 18ST 87 316 WHEN AIRCRAFT ROLLED UP TO GATE, NOTICED PART OF THE NR 4 OUTER WHEEL HALF WAS MISSING. APPROXIMATELY ONE-HALF OF THE WHEEL BEND WAS GONE AND TIRE DESTROYED. NO DAMAGE WAS FOUND AT NR 3 TIRE OR WHEEL. (X) 2 L 7 2 4F A10CE 2000042500036 20000425 00036 EA 2000 4 25 20000414SH004 2 20000321 G 7322 A44PA FUEL BOWL PIPER PA28 PA28151 7102805 SO LYC O320 O320E3D 41508 EA CARBURETOR LOOSE B K NONE O OTHER IN INSP/MAINT 1 EA 21 44542 287415662 WHEN ENGINE WAS UNCOWLED, FOUND CARBURETOR BOWL LOOSE. THE BOLTS HAD LOCK WASHERS WITH THE TABS BENT UP. THE BOWL GASK ET WAS IN PLACE. THE PRECISION MANUAL CALLS FOR A TORQUE OF 35-45 INCH/POUNDS ON THESE BOLTS. SUBMITTER STATED UNABLE TO VERIFY THIS. (X) 1 L 7 1 3O 3 O 2A13 E274 2000041700153 20000417 00153 2000 4 17 20000414SH006 4 20000310 G 3416 066306200 ENCODER BEECH 1900 1900C 1154161 CE COCKPIT MALFUNCTIONED B O OTHER O OTHER NR NOT REPORTED 1 CE 01 123UE 1486 UC123 PILOT REPORTED THAT ALTIMETER FLAGGED. COULD NOT DUPLICATE PROBLEM ON TEST BENCH. RE-CERTIFIED ALTIMETER AND RETURNED TO SERVICE. (X) 2 L 7 2 4T RT A24CE 2000041700154 20000417 00154 EA 2000 4 17 20000414SH007 2 20000315 G 8520 STD847 BOLT PIPER PA28 PA28180 7102808 SO LYC O320 O320* 41508 EA CRANKSHAFT MISSING D K NONE O OTHER IN INSP/MAINT 1 SW 99 8804J 282754 L864836A FOUND CRANKSHAFT DRIVE GEAR ATTACHING BOLT MISSING AFTER REMOVAL OF REAR HOUSING FOR OIL PUMP GEAR REPLACEMENT. REPLACE D GEAR, DOWEL PILOT, BOLT AND LOCKPLATE. (X) 1 L 7 1 3O 3 O 2A13 E274 2000042500055 20000425 00055 CE 2000 4 25 20000417SH001 1 20000225 G 2510 08127821 BRACKET CESSNA CESSNA 414 414A 2075907 CE UPPER EAR BROKEN H K NONE O OTHER IN INSP/MAINT 1 WP 19 414RM 170 414A0306 PILOT SEAT - RIGHT HAND BRACKET BROKE. PILOT BARELY LEANED BACK IN SEAT AND THIS BRACKET BROKE. THIS IS THE SECOND BRA CKET THAT BROKE IN THE SAME EXACT PLACE AND UNDER THE SAME CIRCUMSTANCES. SUBMITTER SUSPECTED IT WAS POSSIBLE THAT IT I S A CASTING FLAW. TIME SINCE NEW ON PART: 170.0 HOURS - TSN. (X) 1 L 7 2 3O A7CE 2000042500056 20000425 00056 CE 2000 4 25 20000417SH002 1 20000317 G 3230 VTB0816 BEARING LEAR 35 36A 5170603 CE MLG TRUNNION CRACKED B WTXR K NONE O OTHER IN INSP/MAINT 1 NM 01 432JW 11866 043 DURING REMOVAL OF BOTH LEFT AND RIGHT LANDING GEAR FORWARD TRUNNION BEARINGS, FOUND THE OUTER HOUSING WAS CRACKED COMPLE TELY THROUGH. OLD BEARINGS WERE BEING REMOVED BECAUSE OF LOOSE BALLS. INSTALLED NEW BEARINGS. LANDINGS: 6,201. (X) 2 L 7 2 4F A10CE 2000042500151 20000425 00151 CE 2000 4 25 20000417SH003 1 20000229 G 2434 DOFF10300J ALTERNATOR CESSNA 172 172M 2072418 CE ENGINE FAILED B PE4R O OTHER B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 SO 13 9723V 17264489 SMOKE IN COCKPIT. TROUBLESHOT SYSTEM, FOUND ALTERNATOR BEARING FROZE. REPLACED ALTERNATOR WITH OVERHAUL UNIT, PN DOFF1 0300J, SN A-100167. (X) 1 H 7 1 3O NT 3A12 2000042500057 20000425 00057 SO 2000 4 25 20000417SH004 1 20000221 G 2420 464656 CIRCUIT BREAKER PIPER PA24 PA24250 7102404 SO COCKPIT FAILED D O OTHER O OTHER NR NOT REPORTED 1 CE 09 7404P 2652 242589 CIRCUIT BREAKER P/N 464-656 5 AMP TO LANDING GEAR SOLENOID FAILED INTERNALLY WHILE GEAR WAS IN TRANSIT STOPPING GEAR PAR TIALLY EXTENDED. (X) 1 L 7 1 3O 1A15 2000042500058 20000425 00058 SW 2000 4 25 20000417SH005 1 20000204 G 3260 1SE13 SWITCH GERDES GULSTM 112 112 0144701 SW NLG FAILED D O OTHER O OTHER NR NOT REPORTED 1 NE 01 76QR 232 PILOT REPORTED NLG DOWN LIGHT INTERMITTENT. INVEST SHOWED HYD ACTUATED NLG DOWN SWITCH ROLLER PN 1JE5 HANGING UP AT BOT TOM OF HOLE AT DNLK ASSY. RE-RIGGED SWITCH. WHILE TESTING NLG ACT PN 48805-1 LEAKED. RESEALED ACT. WHILE TESTING HYD POWER PACK PN 795000-1 FAILED. AFTER O/H OF POWER PACK NLG DOWN LIGHT STILL WOULD NOT ILLUMINATE. FND NLG HYD DOWN SWI TCH PN 1SE1-3 WITH HIGH RESISTANCE ON CONTACT THAT OPERATES HYD POWER PACK TO SHUT DOWN WITH ACT APROX .1250 INCH FROM C OMPLETE EXTENSION OF NLG. REPLACED SWITCH. SYS OPERATED NORMALLY EXCEPT AT EMERG EXT, NLG LIGHT FAILED. SHORTED ACT R OD END 1/2 TURN. SYS OPERATES NORMALLY. (X) 1 L 7 1 3O A12SO 2000042500059 20000425 00059 SO 2000 4 25 20000417SH007 1 20000302 G 3213 6703706 STRUT PIPER PA32 PA32R301 7103218 SO MLG CRACKED D K NONE O OTHER IN INSP/MAINT 1 NE 01 8159B 3351 32R8013061 DURING AN ANNUAL INSPECTION, CRACKS WERE FOUND IN BOTH MLG STRUT ASSEMBLIES NEAR THE AXLE BOLT HOLES (BOTH TOP) NEAR BOL T HEADS. THE CRACKS ARE IN THE OUTSIDE WALLS WHERE THE METAL IS THE THINNEST. THIS AIRCRAFT HAS NO ACCIDENT HISTORY OR ANY HARD LANDINGS. PAINT REMOVED AND A 10X MAGNIFYING GLASS WERE REQUIRED. (X) 1 L 7 1 3O A3SO 2000042500121 20000425 00121 SO 2000 4 25 20000417SH008 1 20000417 G 2750 CONTROL CABLE PIPER PA28 PA28R200 7102811 SO TE FLAP WORN H K NONE O OTHER IN INSP/MAINT 1 NE 01 3021R 28R35652 DURING 100-HR INSPECTION, FLAP CABLE WAS FOUND LODGED IN THE TRIM PULLEYS AND WORN 3/4 THROUGH THE RIGHT PULLEY AND NUME ROUS STRANDS OF THE CABLE BROKEN. THIS CONDITION WAS DUPLICATED ON SIMULATING A STICKING FLAP WHEN THE HANDLE IS RELEAS ED AND THE FLAP RETRACTS RAPIDLY, THE LOOSE CABLE JUMPS AND HOOKS INTO THE TRIM PULLEYS. INSTALLED A 90 DEGREE ALUM ANG LE ON THE TOP CLOSE OUT PLATE NEXT TO THE TRIM PULLEYS TO BLOCK THE CABLE FROM HITTING THE PULLEYS AND CHECKING FLAP HIN GE BEARINGS. FOR FREEDOM OF MOVEMENT AND LUBRICATION, CABLE AND ONE PULLEY REPLACED. (X) 1 L 7 1 3O 2A13 2000060500148 20000605 00148 CE 2000 6 5 20000417SH009 1 20000228 G 2910 1118 HOSE CESSNA 207 207A 2073604 CE HYD SYSTEM DAMAGED D K NONE O OTHER IN INSP/MAINT 1 NE 01 END OF HOSE WAS CUT OFF WITH A CUT-OFF WHEEL AND HOSE INTERIOR WAS FOUND COLLAPSED. ANOTHER 1.50 INCH WAS CUT OFF AND T HE SAME CONDITION WAS FOUND. NOTE: SECTION OF HOSE SUBMITTED REPORT FORWARDED TO AEG NE-FSDO-07. (X) 1 H 7 1 3O A16CE 2000042500122 20000425 00122 CE 2000 4 25 20000417SH010 1 20000321 G 5330 SKIN CESSNA 337 337G 2075730 CE FUSELAGE CORRODED D K NONE O OTHER IN INSP/MAINT 1 NE 01 53522 33701680 DURING A 100-HOUR INSPECTION, A SECTION OF MATERIAL USED FOR DAMPING ''OIL CANNING'' WAS REMOVED FROM THE INTERIOR FUSEL AGE SKIN BELOW THE AFT SIDE WINDOW. HEAVY CORROSION WAS FOUND ACROSS THE ENTIRE AREA COVERED BY THE MATERIAL. THIS MAT ERIAL IS USED EXTENSIVELY THROUGHOUT THE AIRFRAME AT MANUFACTURE. (X) 1 H 7 2 3O A6CE 2000042500123 20000425 00123 EA 2000 4 25 20000417SH011 2 20000316 G 7314 LW15472 PUMP PIPER PA28 PA28161 7102803 SO LYC O320 O320D3G 41508 EA FUEL SYSTEM UNSERVICEABLE B DINR O OTHER O OTHER NR NOT REPORTED 1 EA 13 8269E 93 288116039 L1334539A NOTED THE FUEL PRESSURE WOULD DROP OFF AS ALTITUDE INCREASE, FROM 5 PSI AT GROUND LEVEL, TO ABOUT 1-1/2 PSI AT 10,000 FE ET. TURNING ON BOOST PUMP WOULD RESTORE 5 PSI. INSTALLED ANOTHER NEW PUMP AND IT CURED THE PROBLEM. FAILED PUMP, SN 15 4723199. GOOD PUMP, SN 154720200. (X) 1 L 7 1 3O 3 O 2A13 E274 2000042500134 20000425 00134 NE 2000 4 25 20000417SH012 2 20000214 G 8530 PUSHROD AIRTRC AT300 AT301 0390103 SW PWA R1340 R1340AN1 52016 NE ENGINE MISINSTALLED G LSVG K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 09 23043 3010352 19074 ENGINE VALVE PUSH RODS AND ROCKER ARMS WERE REVERSED DURING INSTALLATION ON THE NR 5 CYLINDER. SINCE THE INTAKE ROD IS LONGER AND ENGINE HAS SOLID TAPPETS, THE PUSH ROD ON THE EXHAUST SIDE BENT, AND THE ROCKER ARM BROKE RESULTING IN ENGINE FAILURE. ENGINE OPERATED NORMALLY FOR AT LEAST SEVERAL HOURS BEFORE FAILURE LEADING TO SPECULATION THAT IT DID NOT FAI L UNTIL THE ROCKER ARM BROKE PREVENTING THE EXHAUST VALVE FROM OPENING. (X) 1 L 7 1 3R 3 R A9SW 5E2 2000042500149 20000425 00149 CE 2000 4 25 20000417SH014 1 20000310 G 2434 E3FF10300AAPX ALTERNATOR CESSNA 206 TU206G 2073357 CE ENGINE FAILED B QY5R O OTHER H J ELECT. POWER LOSS-50 PC WARNING INDICATION NR NOT REPORTED 1 NE 01 232MT 29 U20606200 ALTERNATOR FAILED DURING FLIGHT. TROUBLESHOOTING WITH ALTERNATOR TEST BOX SHOWED NO OUTPUT. CHECKING FIELD WINDING RES ISTANCE PER CESSNA MM SHOWED EXCESSIVELY HIGH RESISTANCE. ALTERNATOR REPLACED. (X) 1 H 7 1 3O A4CE 2000042500145 20000425 00145 CE 2000 4 25 20000417SH016 1 20000313 G 3230 12434262 LINK CESSNA 210 T210L 2073449 CE NOSE GEAR CRACKED D DFQR K NONE O OTHER IN INSP/MAINT 1 CE 03 6864C 7716 21061317 DURING ROUTINE INSPECTION, FOUND UPPER TORQUE LINK CRACKED. SUBMITTER STATED THIS PART NUMBER LINK WAS FOUND CRACKED ON ANOTHER T210L IN THE SAME FLEET. (X) 1 H 7 1 3O 3A21 2000042500146 20000425 00146 SO 2000 4 25 20000417SH017 2 20000229 G 8550 LW13094 GASKET LYC PIPER PA32 PA32R300 7103213 SO LYC 0540 IO540K1G5D 41532 SO ENGINE OIL FAILED B EKIR O OTHER K J FLUID LOSS WARNING INDICATION NR NOT REPORTED 1 WP 01 6925J 4377 653 32R7680388 L2012548A ENGINE LOST OIL ON START-UP DUE TO EXCESSIVE OIL PRESSURE WHICH BENT PLATE ON OIL FILLER KIT CAUSING GASKET TO BLOW OUT. (X) 1 L 7 1 3O 3 O A3SO 1E4 2000051800008 20000518 00008 SO 2000 5 18 20000417SH018 2 20000317 G 8530 639614 ROCKER BBAVIA 7 7AC 2110102 SW CONT A65 A658 17003 SO NR 4 CYLINDER BROKEN D O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION NR NOT REPORTED 1 SO 13 84729 500 7AC3445 PILOT REPORTED A REDUCTION IN POWER. AFTER INVESTIGATING, THE ROCKER ARM HAD BROKEN AT THE CENTER. THIS IS THE OLD TYP E WHICH DOES NOT HAVE AS MUCH MATERIAL AS THE NEW TYPE. (X) 1 H 7 1 3O 3 O A759 E205 2000042500150 20000425 00150 NE 2000 4 25 20000417SH020 3 20000318 G 6114 D61681 HUB HARTZL HDE6C HDE6C3B NE PROPELLER CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 05 5942 1941 HL155 DURING PENETRANT INSPECTION, CRACKS WERE FOUND IN THE BLADE SEAL GROOVES OF BLADE SOCKETS 3 AND 4. THE HUB WAS DISPOSIT IONED TO HARTZEL ENGINEERING FOR FURTHER EVALUATION. (X) 6 C P34NE 2000042500272 20000425 00272 NM 2000 4 25 20000417SH021 1 20000221 G 3240 BRAKE DOUG MD11 MD11 3023602 NM MLG FAILED H K NONE O OTHER IN INSP/MAINT 1 SW 99 583FE 2671 48421 BRAKE ASSY WAS RECEIVED FROM AIR CARRIER ON 2-21-00 FOR REPAIR AND OVERHAUL SERVICE. UPON DIS-ASSEMBLY, IT WAS IDENTIFI ED THE AFFECTED BRAKE SUFFERED AN EXTREME CARBON OXIDATION BREAKDOWN ON THE INNER DIAMETER OF THE HEAT SINK. SUBMITTER RECOMMENDATION WOULD BE AN ANALYSIS OR REVIEW OF CARBON COMPOSITE MANUFACTURING PROCESSES. (X) 2 L 7 3 4F RT A22WE 2000042500295 20000425 00295 CE 2000 4 25 20000424SH001 1 20000304 G 2820 FUEL LINE CESSNA 185 185F 2072820 CE CONT O550 IO550D 17042 SO ENGINE FAILED D K NONE O OTHER IN INSP/MAINT 1 SW 07 CGZTT 2300 18503490 284122R RDM/RNO - EN ROUTE 55 MILES NORTH OF LMT, PILOT SENSED A STRONG FUEL ODOR. BRIEF TROUBLESHOOTING CONFIRMED A FUEL LINE FAILURE WITH SYMPTOMS. FUEL FLOW INDICATING ZERO. HIGHER THAN NORMAL EGT'S AND CHT'S (ACFT EQUIPPED WITH A 12-POINT ENG ANALYZER. STRONG AND DANGEROUS FUEL ODOR. PILOT CORRECTLY ASSESSED THE SITUATION AND LEFT POWER SETTING UNTOUCHED AND MIXTURE RICH. PILOT SET UP ON A HIGH APPROACH TO SOUTH RUNWAY AT LMT. ENGINE FAILED WHEN THROTTLE RETARDED. POST-FLIG HT INSPECTION REVEALED FUEL PRESSURE LINE FROM AFT OF ENGINE BAFFLE TO FIREWALL FAILED. LINE SEVERED ONE INCH AFT OF EN GINE BAFFLE. (X) 1 H 7 1 3O 3 O 3A24 E3SO 2000051800043 20000518 00043 CE 2000 5 18 20000424SH008 1 20000229 G 2820 KS271C0650017903 SERVO CESSNA 172 172S 2072439 CE FUEL SYSTEM LOOSE B EHHR K NONE O OTHER IN INSP/MAINT 1 EA 17 642SP 160 172S08050 FOUND LOOSE FREE SPINNING NUT WHILE C/W HONEYWELL SB SK 271-C5, ALERT KS 271C PRIMARY SERVO. RETURNED UNIT TO MANUFACTU RER FOR REPAIR. (X) 1 H 7 1 3O NT 3A12 2000051800044 20000518 00044 SO 2000 5 18 20000424SH009 1 20000318 G 2140 A23D0475 REGULATOR PIPER PA31 PA31350 7103110 SO HEATER LEAKING I WVBA K NONE K FLUID LOSS IN INSP/MAINT 1 AL 01 4082T 560 318152089 DURING ROUTINE INSPECTION, REGULATOR WAS FOUND LEAKING AT PARTING SURFACES. (X) 1 L 7 2 3O A20SO 2000051800046 20000518 00046 CE 2000 5 18 20000424SH012 1 20000310 G 2434 ROTOR COIL FORD BEECH 23 C24R 1151254 CE ALTERNATOR FAILED D O OTHER O OTHER NR NOT REPORTED 1 SO 07 18993 52 9020493 MC550 ALTERNATOR FAILED WHILE ACFT WAS IMC, VFR CONDITIONS ENCOUNTERED. AIRCRAFT LANDED WITHOUT INCIDENT. INVESTIGATION REVE ALED ROTATING FIELD WAS ELECTRICALLY OPEN DOWN. STREAM OF SUD RINGS. PART TSO WAS ONLY 52 HOURS SINCE OVERHAULED. (X) 1 L 7 1 3O A1CE 2000051800047 20000518 00047 GL 2000 5 18 20000424SH013 1 20000316 G 3213 2032100701 AXLE DIAMON DA20 DA20A1 GL RT MLG CORRODED H K NONE O OTHER IN INSP/MAINT 1 SW 99 126MF 3112 10017 DURING TIRE CHANGE, FOUND RT WHEEL AXEL FLANGE EXFOLIATING. SUBMITTER SUSPECTED EXFOLIATION CAUSED BY STRESS CORROSION. RECOMMEND REPLACING ANODIZED ALUMINUM ALLOY PART WITH PART MADE OF STEEL. (X) 1 L 7 1 3O NT TA4CH 2000051800048 20000518 00048 CE 2000 5 18 20000424SH014 1 20000403 G 2820 AN816620 FUEL LINE CESSNA 421 421B 2076014 CE CONT O520 GTSIO520* 17032 SO RT FUEL CELL CORRODED D K NONE O OTHER IN INSP/MAINT 1 NM 05 421SE 421B0393 DURING ANNUAL INSP, RT WING AUXILIARY TRANSFER PUMP PRESS SWITCH THAT OPERATES RT AUX PUMP ANNUNCIATOR LIGHT, WAS FOUND TO HAVE LIGHT FUEL STAINING AROUND BASE OF MICROSWITCH. AFTER REMOVING PRESS SWITCH ASSY (DUE TO CONDITION OF LEFT ONE) , FOUND PIPE THREAD PORTION OF AN 816-6-20 VISIBLE, EXPOSING SEVERE CORROSION TO THE POINT OF ALMOST HALF DIAMETER BEIN G ERODED AWAY. (X) 1 L 7 2 3O 3 O A7CE E7CE 2000051800050 20000518 00050 NM 2000 5 18 20000424SH017 1 20000213 G 5320 900R1103001113 BEAM DOUG MD900 MD900 3027375 NM FUSELAGE DELAMINATED A K NONE O OTHER IN INSP/MAINT 1 NM 07 901CF 90000012 DELAMINATION ALONG TRAILING EDGE IN Y-AREA. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U NC H19NM 2000051800051 20000518 00051 NM 2000 5 18 20000424SH018 1 20000213 G 5320 900R1103001113 BEAM DOUG MD900 MD900 3027375 NM FUSELAGE DELAMINATED A K NONE O OTHER IN INSP/MAINT 1 NM 07 901CF 884 90000012 DELAMINATION ALONG TRAILING EDGE IN Y-AREA. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U NC H19NM 2000042500302 20000425 00302 SW 2000 4 25 20000424SH019 1 20000308 G 6220 6887772D BEARING ALLSN BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL GEARBOX MAKING METAL D K NONE O OTHER IN INSP/MAINT 1 NM 11 37488 38410 2188 823399 METAL FLAKES DETECTED ON MAGNETIC PICK-UP IN LOWER GEARBOX AND OIL PUMP MAGNETIC PICK-UP. DISASSEMBLED GEARBOX FOR INSP ECTION. BEARING INNER AND OUTER RACES BOTH HAD AREAS THAT HAD FLAKED OFF METAL. (X) 1 G 7 1 3U 3 U H2SW E4CE 2000042500303 20000425 00303 GL 2000 4 25 20000424SH021 3 20000316 G 6110 PROPELLER CESSNA 210 210B 2073410 CE HARTZL HCA2X HCA2XF1 GL BLADE BORE MISOVERHAULED B W59R K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 07 9561X 2192 21057861 2714 PROPELLER WAS ASSEMBLED USING U 8833 N-4 BLADES THAT ARE NOT ELIGIBLE FOR INSTALLATION ON HCA2XF-1 HUB. STEEL HUB TUBES CAUSED EXTREME WEAR ON THE INTERNAL BLADE BORE BECAUSE THE INSTALLING AGENCY REMOVED THE BLADE BOXINGS AND BEARINGS TO FACILITATE INSTALLATION OF BLADES ON HUB (X) 1 H 7 1 3O 3A21 5 C P908 2000042500304 20000425 00304 CE 2000 4 25 20000424SH022 1 20000309 G 5751 99130000605 SKIN BEECH 99 99 1154002 CE ALIERON CRACKED E TIMA K NONE O OTHER IN INSP/MAINT 1 NM 07 199GL U15 PRE-FLIGHT INSPECTION REVEALED A SMALL PORTION OF THE AILERON SKIN CRACKED AT THE INBOARD SECTION, TOP SKIN, TRAILING ED GE ADJACENT TO THE MOVABLE TRIM. FURTHER INSPECTION REVEALED EXTENSIVE CORROSION RELATED CRACKING MOSTLY ALONG THE TRAI LING EDGE. REMOVED STATIC WICKS AND FOUND FURTHER UNSERVICEABLE CONDITIONS. WHEN INSPECTING OLDER CONTROL SURFACES, AN D/OR CONTROL SURFACES HAVING CRACKS IN THE PAINT, FURTHER INSPECTION WOULD BE MANDATED TO CHECK FOR CRACKS. (X) 1 L 7 2 3T A14CE 2000042500305 20000425 00305 CE 2000 4 25 20000424SH023 1 20000309 G 3230 508103237 SCISSORS BEECH 99 99A 1154003 CE LANDING GEAR CRACKED A TIMA K NONE O OTHER IN INSP/MAINT 1 NM 07 955AA U128 DURING DETAILED LANDING GEAR INSPECTION, THE SCISSORS ON THE RT MAIN GEAR WERE FOUND CRACKED. THE CRACKS ARE LOCATED NE AR THE MACHINED RADIUS WHERE THE TWO SCISSORS CONNECT. IT WAS DETERMINED THE CRACKS WERE, OR COULD HAVE BEEN CAUSED BY THE TORQUE KNEE BOLT/HARDWARE BEING LOOSE. THE LT GEAR ASSY SCISSORS WERE FOUND TO BE SLOPPY AND THE SUBSEQUENT INSPECT ION REVEALED WORN BUSHINGS. (X) 1 L 7 2 3T A14CE 2000050500076 20000505 00076 NE 2000 5 5 20000425SH031 2 20000201 G 7320 3026983 NUT CESSNA 500 500CESSNA 2076602 CE PWA JFTD12 JFTD12A4A 52047 NE FCU LOOSE H K NONE O OTHER IN INSP/MAINT 1 CE 05 97DD 5000159 P76506 UPON BORESCOPE OF FUEL CONTROL SHUT OFF MECHANISM, NOTED CLEVIS LANYARD THROUGH-BOLT HAD BACKED OFF FROM CLEVIS ON END O F BOLT. (THROUGH-BOLT LOOSE). NUT HAD BACKED OFF. (X) 1 L 7 2 4F 4 U A22CE E15EA 2000050500077 20000505 00077 NE 2000 5 5 20000425SH032 2 20000201 G 7320 311707802 BOLT CESSNA 500 500CESSNA 2076602 CE PWA JT15 JT15D1 52060 NE NR 4 BEARING LOOSE B K NONE O OTHER IN INSP/MAINT 1 CE 05 97DD 5000159 P76506 UPON BORESCOPE OF FUEL CONTROL SHUT OFF MECHANISM, NOTED CLEVIS LANYARD THROUGH-BOLT HAD BACKED OFF FROM CLEVIS ON END O F BOLT. (THROUGH-BOLT LOOSE). NUT HAD BACKED OFF. (X) 1 L 7 2 4F 4 F A22CE E1NE 2000050500078 20000505 00078 WP 2000 5 5 20000425SH033 2 20000322 G 7250 30723515 DISK GARRTT TFE731 TFE731* 01518 WP NR 1 LPT DAMAGED H K NONE O OTHER IN INSP/MAINT 1 SW 99 NEW PART RECEIVED FROM HONEYWELL WITH DAMAGE IN POST FIR TREE AREA. (X) 4 F E6WE 2000050500079 20000505 00079 WP 2000 5 5 20000425SH034 2 20000322 G 7250 300723515 DISK GARRTT TFE731 TFE731* 01518 WP NR 1 LPT DAMAGED H K NONE O OTHER IN INSP/MAINT 1 SW 99 NEW PART RECEIVED FROM HONEYWELL WITH DAMAGE IN POST FIR TREE AREA. (X) 4 F E6WE 2000051800053 20000518 00053 WP 2000 5 18 20000425SH035 2 20000322 G 7250 30725422 DISK GARRTT TFE731 TFE731* 01518 WP NR 2 LPT DAMAGED B K NONE O OTHER IN INSP/MAINT 1 SW 99 NEW PART RECEIVED FROM HONEYWELL WITH DAMAGE IN POST FIR TREE AREA. (X) 4 F E6WE 2000050500080 20000505 00080 2000 5 5 20000425SH036 4 20000310 G 3422 6226136002 GYRO BEECH 1900 1900D 1154162 CE COCKPIT DG FAILED B GLBR O OTHER O OTHER NR NOT REPORTED 1 CE 01 179GL 10225 UE179 PILOT REPORTED THAT ''GYRO FREEZES UP''. NR 1 DIRECTIONAL GYRO REMOVED AND SENT TO TEST FACILITY. 2 L 7 2 4T RT A24CE 2000050500081 20000505 00081 CE 2000 5 5 20000425SH037 1 20000403 G 2820 S14956 FUEL LINE CESSNA 172 172N 2072434 CE LYC O320 O320E2D 41508 EA WING ROOT LEAKING H K NONE K FLUID LOSS IN INSP/MAINT 1 SW 99 5444J 5430 17273798 RL96576T DURING REPLACEMENT OF CABIN INTERIOR, FOUND ONE EACH HOSE LEAKING. REPLACED ALL 6 HOSES IN FUEL VENT SYSTEM. CONDITION OF THESE HOSES THE SAME. AGE OF HOSES, 19 YEARS. (X) 1 H 7 1 3O 3 O NT 3A12 E274 2000050500082 20000505 00082 GL 2000 5 5 20000425SH038 3 20000403 G 6114 D4883C55 HUB BEECH 95 95B55 1152729 CE MCAULY 2AF34C 2AF34C55 GL PROPELLER CRACKED H K NONE O OTHER IN INSP/MAINT 1 SW 99 6853Q TC675 715408 CRACK IN HUB WAS FOUND WITH EDDY CURRENT INSPECTION. (X) 1 L 7 2 3O RT 3A16 5 C P5EA 2000050500083 20000505 00083 SO 2000 5 5 20000425SH039 2 20000403 G 8520 629588 DRIVE GEAR PIPER PA28 PA28R201T 7102813 SO CONT O360 TSIO360FB 17025 SO CAMSHAFT BROKEN H A UNSCHED LANDING Y J ENGINE STOPPAGE WARNING INDICATION NR NOT REPORTED 1 SW 99 47445 1618 28R7703379 237331R PILOT WAS IN-FLIGHT WHEN ENGINE FAILED. PILOT PERFORMED EMERGENCY PROCEDURES AND RETURNED TO AIRPORT. INSPECTION REVEA LED THE GOVERNOR DRIVE GEAR HAD FAILED. GOVERNOR DRIVE GEAR ALSO DRIVES THE ENGINE DRIVEN FUEL PUMP WHICH, WHEN GEAR FA ILED, TOOK THE ENGINE DRIVEN FUEL PUMP OFF-LINE. GOVERNOR DRIVE GEAR APPEARS TO HAVE BEEN CRACKED BEORE FAILURE. (X) 1 L 7 1 3O 3 O 2A13 E9CE 2000050500086 20000505 00086 SO 2000 5 5 20000425SH042 1 20000331 G 5510 6356000 SKIN PIPER PA28 PA28160 7102806 SO STABILATOR CORRODED H K NONE O OTHER IN INSP/MAINT 1 SW 00 5542W 28633 SEVERE CORROSION FOUND ON FORWARD INBOARD STABILATOR SPAR AND INBOARD RIB JUNCTION. FOUND AFTER REMOVING TOP SKIN TO RE PLACE. (X) 1 L 7 1 3O 2A13 2000050500091 20000505 00091 2000 5 5 20000426SH003 4 20000322 G 6122 C20908 FLYWEIGHT MCAULY CESSNA 402 402B 207590P CE PROP GOVERNOR CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 641374A RELEVANT INDICATION ON FLAT BETWEEN TOWERS. EXTENDS AROUND CORNER. (X) 1 L 7 2 3O A7CE 2000050500092 20000505 00092 CE 2000 5 5 20000426SH004 1 20000308 G 2820 154729606 PUMP CESSNA 177 177 2073704 CE FUEL SYSTEM FAILED D K NONE O OTHER IN INSP/MAINT 1 WP 27 2954X 17700354 NEW FUEL PUMP DOES NOT ATTAIN RATED FUEL PRESSURE/FUEL FLOW. THE HIGHEST PRESSURE ATTAINED WAS LESS THAN 2 PSIG AT IDLE AND DROPPED TO NEAR ZERO AS RPM INCREASED. AFTER EXTENSIVE TROUBLESHOOTING OF AIRCRAFT FUEL SYSTEMS, CAME TO THE CONCLU SION THE PUMP MUST BE FAULTY. INSTALLED ANOTHER NEW PUMP AND OPERATIONAL CHECK WAS SATISFACTORY. SUBMITTER SUGGESTED T HAT ALL LYCOMING/AC PUMPS OF THIS BATCH (DATE CODE 9606) SHOULD BE CHECKED FOR PROPER OPERATION. (X) 1 H 7 1 3O NT A13CE 2000050500093 20000505 00093 NE 2000 5 5 20000426SH005 2 20000330 G 7421 CPW3039828 IGNITOR PWA JT15 JT15* 52060 NE ENGINE DAMAGED B K NONE O OTHER IN INSP/MAINT 1 GL 03 DURING NORMAL MAINTENANCE, FOUND IGNITERS ON TWO SEPARATE AIRCRAFT (BOTH BATCH NR 1H99), CENTER ELECTRODES AND CERAMIC I NSULATORS RECESSED APPROXIMATELY .75 INCH. UPON FURTHER INVESTIGATION, FOUND ELECTRODE ASSY WAS LOOSE AND FREE TO FLOAT WITHIN IGNITER. BOTH IGNITERS WERE INOPERABLE UPON REMOVAL. (X) 4 T E1NE 2000050500094 20000505 00094 NE 2000 5 5 20000426SH006 2 20000330 G 7421 CPW3039828 IGNITOR PWA JT15 JT15* 52060 NE ENGINE DAMAGED B K NONE O OTHER IN INSP/MAINT 1 GL 03 DURING NORMAL MAINTENANCE, FOUND IGNITERS ON TWO SEPARATE AIRCRAFT (BOTH BATCH NR 1H99), CENTER ELECTRODES AND CERAMIC I NSULATORS RECESSED APPROXIMATELY .75 INCH. UPON FURTHER INVESTIGATION, FOUND ELECTRODE ASSY WAS LOOSE AND FREE TO FLOAT WITHIN IGNITER. BOTH IGNITERS WERE INOPERABLE UPON REMOVAL. (X) 4 T E1NE 2000050500095 20000505 00095 NM 2000 5 5 20000426SH007 1 20000403 G 3210 9543536 RETAINER DOUG DC10 DC10 N/A-SDR NM RING DAMAGED B INWR K NONE O OTHER IN INSP/MAINT 1 SO 19 3240 VISUAL INSPECTION SHOWED RING RETAINER AREA DAMAGED BEYOND LIMITS AND HEAVY CORROSION AT BOLT HOLE AREAS. (X) 2 L 7 3 4F RT A22WE 2000050500096 20000505 00096 GL 2000 5 5 20000426SH008 3 20000327 G 6114 D7015C87 HUB MCAULY 3AF32C 3AF32C87 GL PROPELLER CRACKED B ME4D K NONE O OTHER IN INSP/MAINT 1 SO 15 771150 DURING INSPECTION, HUB WAS FOUND CRACKED IN NR 3 THREAD OF NR 3 SOCKET. HUB HAS BEEN SCRAPPED. (X) 5 C P22EA 2000050500097 20000505 00097 NE 2000 5 5 20000426SH009 3 20000320 G 6111 D5133 EROSION SHIELD HARTZL HARTZL HCE4A HCE4A3A NE PROPELLER CRACKED B GLBR K NONE O OTHER IN INSP/MAINT 1 CE 01 1588 HJ628 CRACKED AND DEBONDED EROSION SHIELDS. PRELOAD LOOSE. DISASSEMBLED AND CLEANED PROPELLER. REPLACED EROSION SHIELDS BLA DE NR 1 SN 1588. BLADE NR 2 SN 1590. SET PRELOADS. REASSEMBLED PROP, SET BLADE ANGLES. REV AT 14.5 INCHES, FEATHER AT 79.0 INCHES, L.P. AT 18.6 INCHES, STATIC BALANCED PROP IAW HARTZELL CMM. (X) 5 C P10NE 2000050500098 20000505 00098 NE 2000 5 5 20000426SH010 3 20000320 G 6111 D5133 EROSION SHIELD HARTZL HARTZL HCE4A HCE4A3A NE PROPELLER CRACKED B GLBR K NONE O OTHER IN INSP/MAINT 1 CE 01 1590 HJ628 CRACKED AND DEBONDED EROSION SHIELDS. PRELOAD LOOSE. DISASSEMBLED AND CLEANED PROPELLER. REPLACED EROSION SHIELDS BLA DE NR 1 SN 1588. BLADE NR 2 SN 1590. SET PRELOADS. REASSEMBLED PROP, SET BLADE ANGLES. REV AT 14.5 INCHES, FEATHER AT 79.0 INCHES, L.P. AT 18.6 INCHES, STATIC BALANCED PROP IAW HARTZELL CMM. (X) 5 C P10NE 2000050500099 20000505 00099 NE 2000 5 5 20000426SH011 3 20000216 G 6111 D5133 EROSION SHIELD HARTZL HARTZL HCE4A HCE4A3A NE PROPELLER CRACKED B GLBR K NONE O OTHER IN INSP/MAINT 1 CE 01 1497 HJ395 EROSION SHIELD DEBONDED AND CRACKED BLADE NR 2. REMOVED AND REPLACED EROSION SHIELD WITH NEW, STATIC BALANCED PROPELLER IAW PROCEDURE 001 AND HARTZELL CMM. NR 2 BLADE SN 1497, BOOT SN 0255. HYSOL BATCH NR AS9163016 AND 9228-1 (X) 5 C P10NE 2000050500101 20000505 00101 GL 2000 5 5 20000426SH013 3 20000407 G 6114 D653012 HUB HARTZL HARTZL HCC2Y HCC2YF2 GL PROPELLER STRIPPED H K NONE O OTHER IN INSP/MAINT 1 SW 99 AN7323B PROPELLER WAS RETURNED FOR LOOSE MOUNTING STUD. AFTER REMOVAL OF THE STUD, FOUND STUD ATTACHMENT THREADS IN THE HUB WER E STRIPPED. (X) 5 C P920 2000050500106 20000505 00106 GL 2000 5 5 20000426SH018 3 20000323 G 6114 HUB PIPER PA23 PA23250 7102308 SO HARTZL HCC2Y HCC2YR2 GL PROPELLER DAMAGED B SD4R K NONE O OTHER IN INSP/MAINT 1 SO 17 111QT 272849 715 DURING INSPECTION, NOTICED THE PRELOAD SHELF WAS ROLLED. EVIDENCE SHOWS HUB ENDURED EXCESSIVE FORCES. HUB WAS RETIRED FROM SERVICE. (X) 1 L 7 2 3O 1A10 5 C P920 2000050500107 20000505 00107 GL 2000 5 5 20000426SH019 3 20000323 G 6114 HUB PIPER PA23 PA23250 7102308 SO HARTZL HCE2Y HCE2YR2 GL PROPELLER DAMAGED B SD4R K NONE O OTHER IN INSP/MAINT 1 SO 17 111QT 272849 BP5674 DURING INSPECTION, NOTICED THE PRELOAD SHELF WAS ROLLED. EVIDENCE SHOWS HUB ENDURED EXCESSIVE FORCES. HUB WAS RETIRED F ROM SERVICE. (X) 1 L 7 2 3O 1A10 5 C P9EA 2000050500108 20000505 00108 GL 2000 5 5 20000426SH020 3 20000323 G 6111 B67536 BLADE PIPER PA23 PA23250 7102308 SO HARTZL HCE2Y HCE2YR2 GL PITCH KNOB CRACKED B SD4R K NONE O OTHER IN INSP/MAINT 1 SO 17 111QT 272849 BP5674 UPON INSPECTION OF THE PROPELLER BLADE DURING OVERHAUL, THE PITCH KNOB ON THE BUTT OF THE BLADE WAS FOUND CRACKED. BLAD E WAS RETIRED FROM SERVICE. (X) 1 L 7 2 3O 1A10 5 C P9EA 2000050500109 20000505 00109 SW 2000 5 5 20000426SH021 1 20000322 G 6710 206001330001 SUPPORT BRACKET BELL 206 206B 1181511 SW M/R CYCLIC CORRODED D K NONE O OTHER IN INSP/MAINT 1 SW 09 167H 2968 DURING THE ANNUAL INSPECTION, THE PIVOT SUPPORT ASSEMBLY WAS FOUND CORRODED. REPLACED SUPPORT ASSEMBLY WITH NEW PART. SUBMITTER RECOMMENDED SPRAYING A CORROSION PREVENTATIVE COMPOUND IN THE AREA OF THE SUPPORT ASSEMBLY. (X) 1 G 7 1 3U H2SW 2000050500110 20000505 00110 SW 2000 5 5 20000426SH022 1 20000322 G 2822 1C274 PUMP BELL 206 206B 1181511 SW FUEL BOOST FAILED D O OTHER O OTHER NR NOT REPORTED 1 SW 09 198H 253 3647 AFT BOOST PUMP INOPERATIVE. INSPECTED AIRFRAME FUEL FILTER AND FOUND FILTER WAS COATED WITH A BLACK CARBON LIKE MATERIA L THAT WAS SUSPECTED TO BE RESIDUE FROM THE MAGNETS SURROUNDING THE BOOST PUMP CORE. (X) 1 G 7 1 3U H2SW 2000050800066 20000508 00066 EA 2000 5 8 20000426SH025 2 20000328 G 7414 10382681 CAPACITOR BENDIX PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA MAGNETO FAILED D O OTHER O OTHER NR NOT REPORTED 1 EA 03 27329 317752150 NUMEROUS MAGNETO PROBLEMS. UNUSUAL DROP OFF, COMPLETELY DEAD MAG, AND NO HARD STARTING WERE ATTRIBUTED TO CAPACITORS IN THE DUAL MAG SYSTEM. AFTER THE FACT, TCM NOTIFIED AND STATED CAPACITORS CODED PRIOR TO 9946 WERE TO BE PULLED OUT OF S ERVICE. REF TCM CSB NR 662A NEWER CODED CAPACITORS WERE INSTALLED AND MAG OPERATION HAS BEEN SATISFACTORY. (X) 1 L 7 2 3O 3 O A20SO E14EA 2000050800067 20000508 00067 SO 2000 5 8 20000426SH026 1 20000324 G 3213 6792617 TRUNNION PIPER PIPER PA32 PA32R301 7103218 SO RT & LT MLG CRACKED B PRIR K NONE O OTHER IN INSP/MAINT 1 GL 03 29AM 1845 32R8113057 ON PRE-FLIGHT, PILOT NOTICED FLUID FROM MIDDLE OF STRUT. AFTER CLEANING, FLUID RE-APPEARED. AFTER INSP, FOUND STRUT HO USING CRACKED BELOW AFT WEB ON STRUT HOUSING (CASTING). REMOVED AND REPLACED STRUT HOUSING ASSY WITH NEW. INSPECTED OT HER GEAR HOUSING AND DISCOVERED CRACKED, BUT NOT LEAKING AT THIS TIME. REPLACED LT SIDE HOUSING. NEW PARTS FROM PIPER HA VE NEW DESIGN WHERE WEB IS SUPPORTED THE ENTIRE LENGTH OF CASTING AND HAS NEW P/N. SUBMITTER STATED THESE HOUSINGS ARE NOT COVERED IN ANY AD OR SB. (X) 1 L 7 1 3O A3SO 2000050800069 20000508 00069 CE 2000 5 8 20000426SH030 1 20000331 G 3246 26066712 BOLT CESSNA 337 T337G 2075726 CE MLG WHEEL BROKEN H A3L2 K NONE O OTHER IN INSP/MAINT 1 SW 09 357 P3370242 TIE BOLT FAILURE, 3 EACH. UNDETERMINED WHEEL SENT TO MFG FOR ANALYSIS. BOLT HARD TIME IMPLEMENTED, AND TIE NUT CYCLE P LAN INPLEMENTED. (X) 1 H 7 2 3O A6CE 2000050800071 20000508 00071 SO 2000 5 8 20000426SH032 2 20000324 G 7320 0850250189 CONDUIT CESSNA 310 310C 2074210 CE CONT O470 IO470D 17026 SO ENGINE NACELLE FAILED D K NONE O OTHER IN INSP/MAINT 1 NM 11 3311H 35835 10512670R MIXTURE CONTROL CONDUIT IN ENGINE NACELLE BETWEEN MIXTURE CONTROL AND WING ROOT. CONDUIT THAT HOUSES CABLE FATIGUED AND BROKE CAUSING HOUSING TO MOVE AND MIXTURE TO REMAIN IN IDLE CUT-OFF WHICH CAUSED AIRCRAFT TO MAKE AN OFF-AIRPORT LANDIN G. THE ENGINE WAS NOT ABLE TO RE-START. (X) 1 L 7 2 3O 3 O 3A10 3E1 2000050800084 20000508 00084 SW 2000 5 8 20000427SH002 1 20000327 G 2841 INDICATOR BELL 206 206B 1181511 SW FUEL QUANTITY MALFUNCTIONED D O OTHER O OTHER NR NOT REPORTED 1 SW 09 57499 3086 PILOT REPORTED FLUCTUATIONS IN THE FUEL QUANTITY INDICATOR. FLUCTUATED FROM ZERO TO KNOWN QUANTITY. SOLDERED WIRE CONN ECTION AT ZERO ADJUST RESISTOR, WAS CORRODED AND LOOSE. RE-SOLDERED AND RECALIBRATED FUEL QUANTITY SYSTEM. SUBMITTER R ECOMMENDED THAT HEAT SHRINK COVER OVER SOLDER CONNECTION IS INSTALLED. (X) 1 G 7 1 3U H2SW 2000042700101 20000427 00101 SW 2000 4 27 20000427SH003 1 20000314 G 6510 S3532EC1 PULLEY BELL 407 407 SW T/R DRIVE LOOSE B ULXR K NONE O OTHER IN INSP/MAINT 1 WP 01 58236 2920 AFS1229 53069 DURING AIRCRAFT RUN-UP FOLLOWING UNRELATED MAINTENANCE, MECHANIC NOTED AIR CONDITIONING COMP STOPPED TURNING WHEN AIR CO NDITIONER SYSTEM WAS ACTIVATED. ACFT WAS SHUT DOWN AND MECH FOUND AIR COND DRIVE PULLEY LOOSE ON OIL COOLER BLOWER SHAF T. POSSIBLE CAUSE FOR THIS CONDITION WAS LOSS OF TORQUE BETWEEN DRIVE PULLEY FWD OIL COOLER BLOWER BEARING. DRIVE RING LOCK WAS TIGHT AND SAFTIED. SUBMITTER RECOMMENDED A POSSIBLE INCREASE IN TORQUE VALUE AND/OR AT THE VERY LEAST, A TORQ UE CHECK REQUIREMENT OF 1 TO 5 HOURS AFTER INSTALLATION. (X) 1 G 7 1 3U O H2SW 2000052500046 20000525 00046 CE 2000 5 25 20000427SH004 1 20000427 G 5320 04120101 PLATE CESSNA 150 150L 2071826 CE FUSELAGE MISMANUFACTURED B YBUR K NONE W INADEQUATE Q C IN INSP/MAINT 1 EA 03 6556G 15072056 RECEIVED 2 EACH NEW PLATES, P/N 0412010-1. ONE PLATE HAS CASING LINE ACROSS FLAT SURFACE THROUGH TWO MOUNTING HOLES. T HESE TWO PLATES ARE VERY IMPORTANT AND HARD TO INSPECT FOR CRACKS AFTER INSTALLATION. SUBMITTER STATED PART APPEARED TO HAVE BEEN BURNISHED. (X) 1 H 7 1 3O 3A19 2000050800089 20000508 00089 CE 2000 5 8 20000427SH014 1 20000225 G 2400 S337711 SWITCH CESSNA 172 172R 2072401 CE AVIONICS MASTER FAILED D O OTHER O OTHER NR NOT REPORTED 1 GL 03 718EH 17280061 ONE-HALF OF SPLIT AVIONICS MASTER BUS SWITCH FAILED. DEFECTIVE HALF OF SWITCH WILL NOT TURN OFF LEAVING SOME AVIONICS S YSTEMS POWER CONTROLLED BY A/C MASTER SWITCH. SWITCH FAILED UNDER NORMAL OPERATING PARAMETERS. POSSIBLE CAUSE OF FAILU RE IS DUE TO POOR SWITCH DESIGN AND SUBMITTER STATED NEEDS TO BE RE-DESIGNED. (X) 1 H 7 1 3O NT 3A12 2000050800090 20000508 00090 SO 2000 5 8 20000427SH015 1 20000321 G 3230 6792616 TRUNNION PIPER PA28 PA28R201 7102816 SO LEFT MLG CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 21 803ND 9165 2837003 DURING SCHEDULED INSPECTION, HYDRAULIC FLUID WAS DISCOVERED ON AFT WEB OF THE LT MAIN LANDING GEAR TRUNNION. UPON FURTH ER INSPECTION, FOUND IT TO BE CRACKED WHERE THE WEB JOINS THE TRUNNION TUBE ALLOWING FLUID TO LEAK. SUBMITTER STATED PO SSIBLE CAUSE COULD BE HIGH TIME IN USE IN A TRAINING ENVIRONMENT. (X) 1 L 7 1 3O 2A13 2000050800091 20000508 00091 CE 2000 5 8 20000427SH016 1 20000404 G 3240 353800657 VALVE BEECH 76 76 1153005 CE PARKING BRAKE FAILED H O OTHER O OTHER NR NOT REPORTED 1 SW 99 822ER ME293 DURING ENGINE-OUT TRAINING, IF PILOT''S RT RUDDER IS FULLY DEPRESSED AND THE PILOT''S FOOT IS HIGH AND RIGHT ON THE RUDD ER PEDAL, THE PILOT''S RT FOOT CAN INADVERTENTLY PULL BACK ON THE PARKING BRAKE VALVE ACTUATOR ARM AND SET THE BRAKES. IF NOT CAUGHT PRIOR TO LANDING, BLOWN TIRES WILL RESULT WITH POSSIBLE LOSS OF DIRECTIONAL CONTROL. RAYTHEON HAS BEEN NO TIFIED. (X) 1 L 7 2 3O A29CE 2000050800094 20000508 00094 2000 5 8 20000427SH019 4 20000330 G 2562 300011 ELT CESSNA 172 172R 2072401 CE CABIN FAILED D K NONE L NO TEST IN INSP/MAINT 1 SW 15 9543P 17280644 DURING 100-HOUR INSPECTION, ELT SYSTEM WAS TESTED FOR OPERATION. UPON ACTIVATING PANEL MOUNTED REMOTE CABIN SWITCH, PN 2019-10, ELT WOULD NOT TRANSMIT. AFTER REPEATED ATTEMPTS, ELT WOULD SOMETIMES TRANSMIT. ELT WAS REPLACED WITH A SERVIC EABLE UNIT, PN 3000-11, S/N 326702, AND REMOTE SWITCH WAS REPLACED WITH NEW SWITCH. (X) 1 H 7 1 3O NT 3A12 2000050800097 20000508 00097 CE 2000 5 8 20000427SH022 1 20000407 G 7120 0851559 LOCK CESSNA 182 182N 2072730 CE ENGINE MOUNT MISSING H K NONE O OTHER IN INSP/MAINT 1 WP 23 9020G 18260560 WHILE PERFORMING THE APRIL, 2000 ANNUAL, FOUND THE MOUNT SAFETY LOCKS, PN 0851559, WERE MISSING ON ALL FOUR ENGINE MOUNT S, PN J6545-1. INSTEAD, THERE WAS AN EXTRA WASHER TO TAKE UP THE BOLT LENGTH. THE MOUNTS WERE INSTALLED 5-19-98. (X) 1 H 7 1 3O NT 3A13 2000050800102 20000508 00102 CE 2000 5 8 20000427SH027 1 20000317 G 5711 SPAR CESSNA 421 421C 2076016 CE LT WING CRACKED B BXSR K NONE O OTHER IN INSP/MAINT 1 EA 09 60RR 6547 421C0885 A CRACK INDICATION WAS NOTED IN THE LT FORWARD UPPER WING SPAR. THE CRACK INDICATION IS ABOVE THE OUTBOARD HI-LOK AND RUNS SPANWISE. THE INDICATION IS .765 INCH PLUS/MINUS LONG AND IS .3401 PLUS/MINUS ABOVE THE HI-LOK. INSPECTION WAS PE RFORMED PER AD 91-25-08R1. (X) 1 L 7 2 3O A7CE 2000050800103 20000508 00103 CE 2000 5 8 20000427SH028 1 20000315 G 3240 1338932 STATOR BFGOODRICH CESSNA 500 500CESSNA 2076602 CE BRAKE CRACKED E K NONE O OTHER IN INSP/MAINT 1 SW 99 161CC 393 0159R 5000161 WHILE PERFORMING CESSNA SB 500-32-47 AND GOODRICH BULLETIN 2-1530-32-2, FOUND 2 EACH STATORS ON LEFT BRAKE ASSEMBLY CRAC KED IN MULTIPLE PLACES. CRACKS RANGED IN LENGTH FROM .1850 INCH TO .50 INCH WITH TOTAL FAILURE LENGTH OF .6250 INCH. A CCORDING TO GOODRICH, IMPROPER MACHINING CAUSED THIS PROBLEM. (X) 1 L 7 2 4F A22CE 2000050800104 20000508 00104 SO 2000 5 8 20000427SH029 1 20000304 G 3230 3503002 ROD PIPER PA23 PA23250 7102308 SO LT MLG CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 21 2471M 277954065 DURING ANNUAL INSPECTION, FUNCTIONAL TEST OF THE MAIN LANDING GEAR REVEALED THE LT MLG WAS NOT GOING ALL THE WAY UP INTO THE WELL LEAVING A 1.50 INCH CRACK BETWEEN THE MLG DOORS. DURING TROUBLESHOOTING, THE SUBJECT PART ACTUATING ROD WAS F OUND TO HAVE A PIECE CRACKED OUT OF THE THREADED END OF THE ROD. THE END CAP WAS ALSO FOUND TO BE BADLY DAMAGED FROM A PREVIOUS MAINTENANCE ACTION. CYLINDER WAS REPLACED, ADJUSTED IAW MM AND A SUCCESSFUL FUNCTIONAL CHECK OF THE GEAR PER FORMED. POSSIBLE CAUSE IS IMPROPER ADJUSTMENT OF THE CYLINDER FOLLOWING REPACK. (X) 1 L 7 2 3O 1A10 2000050800105 20000508 00105 GL 2000 5 8 20000427SH030 3 20000321 G 6114 D32517 HUB CESSNA 310 T310Q 2074244 CE HARTZL HCJ3Y PHCJ3YF2 GL PROPELLER CRACKED H K NONE O OTHER IN INSP/MAINT 1 SW 15 7542Q 3112 919 310Q0042 EB3817A RAM A/C ENGINE AND PROPELLER MODIFICATIONS PER STC NR SA 4011SW. (X) 1 L 7 2 3O 3A10 5 C P36EA 2000050800106 20000508 00106 GL 2000 5 8 20000427SH031 3 20000321 G 6114 D32517 HUB CESSNA 310 T310Q 2074244 CE HARTZL HCC3Y PHCC3YF2 GL PROPELLER CRACKED H F3PR K NONE O OTHER IN INSP/MAINT 1 SW 15 7542Q 3112 919 310Q0042 EB3817A PART CRACKED FROM GREASE FITTING HOLE ACROSS BACK OF HUB TO OPPOSITE SIDE. SENT TO HARTZEL PROPELLER FOR EVALUATION. ( X) 1 L 7 2 3O 3A10 5 C P25EA 2000050800107 20000508 00107 NE 2000 5 8 20000427SH032 2 20000313 G 7230 1703A38G02 SHAFT GE CF6 CF650* 30018 NE ENGINE SPOOL DAMAGED B KRDY K NONE O OTHER IN INSP/MAINT 1 EA 31 530197 AFTER SHOP MAINTENANCE AND RETURN TO SERVICE, ENGINE SUSTAINED TRANSPORT DAMAGE TO FAN SECTION. THE ENGINE WAS RETURNED TO THE SHOP FOR REPAIR AND TEST RUN. DURING TEST RUN, OIL LEAKAGE OCCURRED FORCING A DISASSEMBLY OF THE ENGINE. AFTER DISASSEMBLY, NOTED THE 11/14 SPOOL SHAFT HAD A CRACK IN THE THREADED AREA WHERE THE AIR DUCT CONNECTS. THIS PART IS UN DER INVESTIGATION BY GE AND KLM. PART LIFE LIMIT: 10,000 HOURS. (X) 4 F E23EA 2000050800108 20000508 00108 SO 2000 5 8 20000427SH033 1 20000329 G 8011 MHB4014 LEAD PRESTOLITE PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA STARTER SEPARATED H K NONE O OTHER IN INSP/MAINT 1 SW 99 27471 1071 317852018 L100268A RIGHT ENGINE FAILED TO START. INVESTIGATION REVEALED BOTH FIELD BRUSH LEADS WERE SEPARATED FROM THEIR RESPECTIVE BRUSHE S. ONE BRUSH SHOWED NO INDICATION OF ARCING IN THE LEAD ATTACH HOLE IN THE BRUSH, WHILE THE OTHER DID. IT APPEARED ONE BRUSH LEAD SEPARATED AND PLACED THE ENTIRE START LOAD ON THE OTHER BRUSH CAUSING IT TO FAIL AT THE LEAD ATTACH POINT. THE STARTER''S OVERALL CONDITION WAS EXCELLENT. THE INSIDE WAS CLEAN AND BRIGHT. FAILURE APPARENTLY WAS DUE TO A POORL Y CONSTRUCTED BRUSH/LEAD ASSY THAT LEAD TO PREMATURE FAILURE. WHEN THE OLD BRUSHES WERE COMPARED TO NEW BRUSHES, THE WE AR WAS NEGLIGIBLE. (X) 1 L 7 2 3O 3 O A20SO E14EA 2000050800022 20000508 00022 EA 2000 5 8 20000501SH001 1 20000220 G 2810 2421143 SHUTOFF VALVE CNDAIR CL600 CL6002B19 EA LT FUEL TANK FAILED B SH5R K NONE O OTHER IN INSP/MAINT 1 NE 03 5100X 3899 7008 TRANSFER SHUTOFF VALVE IS BYPASSING FUEL THROUGH ELECTRICAL CONDUIT. TOP OF SOV BYPASSES FUEL THROUGH ''POTTING'' AND I S FOUND DOWNSTREAM OF ELECTRICAL CONDUIT WITNESS HOLES. SUBMITTER STATED THIS IS THE THIRD LEFT FUEL TRANSFER SOV TO BE REPLACED. FIRST, NOV 1994, SECOND, APR 1995). (X) 2 L 7 2 4F RT A21EA 2000050800023 20000508 00023 EA 2000 5 8 20000501SH002 1 20000329 G 3240 7010FS9545708 SEAL CNDAIR CL600 CL6002B19 EA BRAKE ASSY LEAKING B XC4R K NONE K FLUID LOSS IN INSP/MAINT 1 SO 19 1282 JUN981372 BRAKE ASSY, PN 50105201, FAILED PREMATURELY. TWO EACH, PISTONS LEAKING FROM INSULATOR AREA. PISTONS INTERNALLY FILLED WITH FLUID. SUBMITTER STATED THIS IS A CONTINUAL DISCREPANCY. NOTE: OEM PARTS INSTALLED IN BRAKE ASSY. (X) 2 L 7 2 4F RT A21EA 2000050800024 20000508 00024 EA 2000 5 8 20000501SH003 1 20000330 G 3240 7010FS9545708 SEAL CNDAIR CL600 CL6002B19 EA BRAKE ASSY LEAKING B XC4R K NONE K FLUID LOSS IN INSP/MAINT 1 SO 19 805 MAY991715 BRAKE ASSY, PN 5010520-1, FAILED PREMATURELY. ONE EACH PISTON LEAKING FROM INSULATOR AREA. PISTON INTERNALLY FILLED WI TH FLUID. SUBMITTER STATED THIS IS A CONTINUAL DISCREPANCY. FACTORY NEW BRAKE ASSY. NOTE: OEM PARTS INSTALLED IN BRA KE ASSY. (X) 2 L 7 2 4F RT A21EA 2000050800025 20000508 00025 SO 2000 5 8 20000501SH004 1 20000110 G 2823 A23D047524561731 SHUTOFF VALVE PIPER PA31 PA31350 7103110 SO FUEL SYSTEM LEAKING D K NONE K FLUID LOSS IN INSP/MAINT 1 EA 13 41148 50 318352038 REPLACED HEATER FUEL SHUTOFF/REGULATOR VALVE DUE TO LEAK AT SEAL. REPLACEMENT PART (HEAD) FAILED AT 50 HOURS TT. SAME PROBLEM LEAKING FUEL AT SEAL/DIAPHRAGM. (X) 1 L 7 2 3O A20SO 2000050800026 20000508 00026 CE 2000 5 8 20000501SH005 1 20000326 G 2780 04602171 BELLCRANK CESSNA 150 152 2071835 CE TE FLAP BENT H O OTHER O OTHER NR NOT REPORTED 1 AL 03 922AK 2294 15281807 FLAPS WERE LOWERED TO 30 DEGREES DURING LANDING. AS FLAPS WERE RAISED, A POP SOUND WAS HEARD AND FLAPS WOULD NOT EXTEND . INVESTIGATED AND FOUND BENT BELLCRANK. SUSPECT BELLCRANK FAILED DUE TO WEAR ON CAM PORTION AND WORN SPACERS. NEW PA RT ON ORDER AND FLAP RIGGING TO BE ACCOMPLISHED. (X) 1 H 7 1 3O NT 3A19 2000050800027 20000508 00027 CE 2000 5 8 20000501SH006 1 20000404 G 5400 1225700025 SUPPORT BRACKET BEECH 2000 2000 1152000 CE ENGINE NACELLE CRACKED B MZ4R K NONE O OTHER IN INSP/MAINT 1 SO 17 638LD NC18 THE SUPPORT ASSY (MOUNTING BRACKET) FOR BOTH THE LEFT AND RIGHT ENGINE FIRE EXTINGUISHER BOTTLES WAS FOUND CRACKED. THI S MOUNTING BRACKET HAS BEEN FOUND CRACKED ON SEVERAL OTHER MODEL 2000 AIRCRAFT. SUBMITTER STATED THEIR EXPERIENCE HAS B EEN THAT A REPLACEMENT BRACKET OF THE SAME PART NUMBER WILL ALSO CRACK AFTER A VERY SHORT TIME IN SERVICE. PRESENTLY, S UBMITTER STATED THEIR CORRECTIVE ACTION HAS BEEN TO MANUFACTURE A REPLACEMENT BRACKET USING A D.E.R. DRAWING. THIS MANU FACTURED BRACKET AS OF YET HAS NO SIGNS OF CRACKING. RAYTHEON AIRCRAFT HAS BEEN ADVISED OF THE PROBLEM AND SUBMITTER''S CORRECTIVE ACTION. (X) 1 L 7 2 4T RT A38ACE 2000050800028 20000508 00028 GL 2000 5 8 20000501SH007 3 20000329 G 6110 2202 BEARING BEECH 58 58 1152740 CE HARTZL HCJ3Y PHCJ3YF2 GL PROPELLER CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 C6PTS 1700 ED1808 RELEVENT INDICATION OF CRACKS ON BOTH SIDES OF BEARING. (X) 1 L 7 2 3O 3A16 5 C P36EA 2000050800029 20000508 00029 GL 2000 5 8 20000501SH008 3 20000329 G 6110 3252 FORK BEECH 58 58 1152740 CE HARTZL HCJ3Y PHCJ3YF2 GL PROPELLER CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 C6PTS 1700 ED1808 CRACK IN BLOCK RETENTION AREA. (X) 1 L 7 2 3O 3A16 5 C P36EA 2000050800030 20000508 00030 SW 2000 5 8 20000501SH009 1 20000313 G 2910 1114 HOSE GULSTM 112 112 0144701 SW MLG ACTUATOR DETERIORATED G K NONE O OTHER IN INSP/MAINT 1 EA 31 700 STRATOFLEX HOSE NR 111-4, CURE DATE 3Q92, FULLY DETERIORATED WHILE INSTALLED ON BELGIAN REGISTERED AIRCRAFT. NO OTHER C ASES FOUND WITH INSTALLED HOSES. THIS PART WAS BOUGHT THROUGH GILL AVIATION, VIA AVIALL. HOSE INSTALLED ON A ROCKWELL 112, WITH LYC IO-360-C1D6. TT EST. 700 HOURS. RECOMMEND THAT OPERATERS WITH LIKE HOSE INSPECT FOR CURE DATE AND NOTE C ONDITION OF HOSE ASSY. (X) 1 L 7 1 3O A12SO 2000050800031 20000508 00031 CE 2000 5 8 20000501SH010 1 20000302 G 3233 S34832326H5 SEAL CESSNA CESSNA 500 500CESSNA 2076602 CE MLG ACTUATOR WRONG PART B JGVR K NONE W INADEQUATE Q C IN INSP/MAINT 1 CE 09 CESSNA KITS RECEIVED WITH WRONG PART NUMBER SEAL RING (T-SEAL). MANUAL 32-32-11 (TEIJIN SEIKI) CALLS FOR S34692-326H1. KITS HAVE S34832-326H5 ENG ASSY MLG ACTUATOR, CESSNA P/N 9912053-17. TEIJIN SEIKI, P/N 1523100-1. RE: CESSNA 500 SE RIES. (X) 1 L 7 2 4F A22CE 2000050800034 20000508 00034 CE 2000 5 8 20000501SH013 1 20000329 G 3240 5003541 DISK CESSNA 500 550 2076604 CE RT BRAKE DAMAGED D K NONE O OTHER IN INSP/MAINT 1 WP 19 10EG 157 DEC7266 5500055 DURING MAINTENANCE ON RT MLG WHEEL, MECH NOTICED 2 OF 3 BRAKE STATIONARY DISCS DID NOT MOVE WHEN THE WHEEL ASSY WAS REMO VED. INVEST REVEALED 2 STATIONARY DISCS FURTHEST FROM THE PISTON AND PRESSURE PLATE ASSY OF THE BRAKE WERE WARPED AND D ISTORTED. THE DISTORTION WAS TO THE POINT THE 2 DISCS WERE MAKING CONTACT WITH INNER WHEEL HALF SS HEATSHIELD, PN 50038 43. THE DISTORTION, WITH DISCS ''GROWING'' IN RADIAL DIRECTION, HAS POTENTIAL TO ''LOCK-UP'' THE WHEEL AND CAUSE LOSS O F CONTROL OF ACFT DURING GROUND OPERATIONS. A ''BRAKE WEAR CHECK'' WAS PERFORMED. CLEARANCE LESS THAN 0.54 INCH ''REMO VE FOR OVERHAUL'' WEAR DIMENSION. BRAKES TSO: 157.1 HRS, 148 LANDINGS. (X) 1 L 7 2 4F A22CE 2000050800035 20000508 00035 GL 2000 5 8 20000501SH014 3 20000302 G 6114 HUB CESSNA 150 152 2071835 CE MCAULY 1A103 1A103TCM GL PROPELLER CRACKED D K NONE O OTHER IN INSP/MAINT 1 WP 25 89629 7042 1359 15282807 R775560 FOUND CRACK IN HUB AROUND BOLT HOLE EXTENDING TO EDGE OF HUB WHILE INSPECTING FOR AD 97-06-16 PAR(A)(1)(II). LAST INSPE CTION 209 HOURS AND TEN MONTHS AGO, SHOWED NO CRACKS. (X) 1 H 7 1 3O NT 3A19 5 N P50GL 2000051000162 20000510 00162 NE 2000 5 10 20000502SH008 1 20000328 G 3222 1944E9A BEARING CLEVELANDPNU 1944 SKRSKY S76 S76A 8143006 NE NLG FAILED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 709AL AL3988 760278 DURING RETRACTION TEST OF LANDING GEAR, NOSE STRUT PISTON WOULD NOT EXTEND COMPLETELY WITH AIRCRAFT ON JACKS. WHEEL WOU LD CENTER 180 DEGREES FROM NORMAL CENTER. (WHEEL AND FORK ASSY WOULD CENTER BACKWARDS). LOWER BEARING, PN 1944E9A, MOU NTING FLANGE BOLT HOLES DRILLED 180 DEGREES OUT OF INDEX WITH BEARING CENTERING CAM LOBE. (X) 1 G 7 2 3U H1NE 2000051000163 20000510 00163 SW 2000 5 10 20000502SH009 1 20000201 G 6220 406010107105 ADAPTER BELL 407 BELL 407 407 SW MAIN ROTOR CORRODED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 567AL 2468 A266 53246 DURING DISASSEMBLY FOR 2,500 HOUR OVERHAUL, FOUND ADAPTER CORRODED DUE TO PRIMER NOT COMPATIBLE. (X) 1 G 7 1 3U O H2SW 2000051000164 20000510 00164 SW 2000 5 10 20000502SH010 1 20000201 G 6220 407010103101 PITCH HORN BELL 407 BELL 407 407 SW MAIN ROTOR CORRODED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 567AL 2468 A266 53246 DURING DISASSEMBLY FOR 2,500 HOUR OVERHAUL, FOUND PITCH HORN CORRODED DUE TO ADHESIVE NOT COMPATIBLE. (X) 1 G 7 1 3U O H2SW 2000051000165 20000510 00165 SW 2000 5 10 20000502SH011 1 20000201 G 6220 407010103101 PITCH HORN BELL 407 BELL 407 407 SW MAIN ROTOR CORRODED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 567AL 2468 A266 53246 DURING DISASSEMBLY FOR 2,500 HOUR OVERHAUL, FOUND PITCH HORN CORRODED DUE TO ADHESIVE NOT COMPATIBLE. (X) 1 G 7 1 3U O H2SW 2000051000166 20000510 00166 SW 2000 5 10 20000502SH012 1 20000205 G 6320 E6893673 GEAR ALLSN BELL 407 407 SW GEARBOX GALLED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 937AL 234 CAG47125 53383 UPON VISUAL INSPECTION, INSPECTED CHIP DETECTOR PLUGS AND FOUND METAL ON PLUGS. SPALLING AND GALLING ON TM GEAR TEETH, POSSIBLE DUE TO IMPROPER MESHING OF GEAR TEETH. (X) 1 G 7 1 3U O H2SW 2000051000167 20000510 00167 SW 2000 5 10 20000502SH013 1 20000205 G 6320 6893672 PINION GEAR ALLSN BELL 407 407 1182206 SW GEARBOX GALLED H K NONE O OTHER IN INSP/MAINT 1 SW 03 937AL 234 CAG47125 53383 UPON VISUAL INSPECTION, INSPECTED CHIP DETECTOR PLUGS AND FOUND METAL ON PLUGS. SPALLING AND GALLING IN PINION GEAR TEET H, POSSIBLE DUE TO IMPROPER MESHING OF GEAR TEETH. (X) 1 G 7 1 3U O H2SW 2000051000168 20000510 00168 NE 2000 5 10 20000502SH014 1 20000302 G 6210 7615009000046 BLADE SKRSKY SKRSKY S76 S76A 8143006 NE MAIN ROTOR DEBONDED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 712AL 18628 440 760280 DURING 500-HOUR INSPECTION, FOUND TIP PLATE COMPLETELY DEBONDED. (X) 1 G 7 2 3U H1NE 2000051000174 20000510 00174 EU 2000 5 10 20000502SH020 1 20000404 G 6220 1098110163 SCISSORS AGUSTA A109 A109A2 0260120 EU MAIN ROTOR CRACKED D K NONE O OTHER IN INSP/MAINT 1 NM 01 55NW 4933 7267 DURING INSPECTION OVERHAUL, THE END OF THE LEVER ASSY (ROTATING SCISSORS ASSY) WAS FOUND TO HAVE A CRACK AT THE BUSHING BOSS END APPROXIMATELY 1 INCH LONG. MATERIAL IS 2 INCHES THICK. (X) 1 G 7 2 3U H7EU 2000051000175 20000510 00175 WP 2000 5 10 20000503SH001 2 20000410 G 7250 30720705 DISK GARRTT TFE731 TFE731* 01518 WP LP TURBINE DAMAGED H K NONE O OTHER IN INSP/MAINT 1 GL 19 NEW PART RECEIVED FROM HONEYWELL WITH DAMAGE IN CURVIC AREA AND POST FIR TREE AREA. LOT NR: 00P081. (X) 4 F E6WE 2000051000176 20000510 00176 WP 2000 5 10 20000503SH002 2 20000404 G 7250 30740962 DISK GARRTT TFE731 TFE731* 01518 WP LP TURBINE DAMAGED H K NONE O OTHER IN INSP/MAINT 1 SW 99 NEW PART RECEIVED FROM HONEYWELL WITH DAMAGE IN POST FIR TREE AREA. LOT NR: 99P350. (X) 4 F E6WE 2000051000225 20000510 00225 GL 2000 5 10 20000504SH002 1 20000402 G 2840 SENSOR AMTR TITAN TITANTORNADO GL FUEL CELL MISINSTALLED G B A EMER. DESCENT UNSCHED LANDING W Y J INADEQUATE Q C ENGINE STOPPAGE WARNING INDICATION NR NOT REPORTED 1 GL 15 196KW SILICONE WAS USED TO INSTALL A FUEL SENSING UNIT INSIDE THE FUEL TANK. THE SILICONE DISSOLVED AND SUBSEQUENTLY CLOGGED THE FUEL FILTER CAUSING THE ENGINE TO FAIL. AN OFF AIRPORT LANDING WAS MADE CAUSING SUBSTANTIAL DAMAGE TO AIRCRAFT. AC FT S/N D96618SOKH0204. (X) 1 H 7 1 3I NT EXPA1H71 2000051000227 20000510 00227 2000 5 10 20000504SH004 4 20000309 G 3416 SENSOR NARCO PIPER PA28 PA28181 7102807 SO ALTIMETER SYS LEAKING B UC2R O OTHER O OTHER NR NOT REPORTED 1 GL 19 4145X 1177 15103 2843152 STATIC SYSTEM LEAK GREATER THAN 100 FEET/MINUTE TRACED TO THIS UNIT. AR850 ONLY TWO YEARS IN SERVICE SINCE AIRCRAFT WAS NEW. AR850''S ARE NOT KNOWN TO BE FAULTY IN THIS MANNER. SUBMITTER STATED POSSIBLE NARCO FACTORY DEFECT IN ASSEMBLY O F SENSOR. (X) 1 L 7 1 3O 2A13 2000051000228 20000510 00228 SO 2000 5 10 20000504SH005 1 20000331 G 8011 MHB2399S ARMATURE ELECTROSYS PIPER PA28 PA28181 7102807 SO LYC O360 O360A4M 41514 EA STARTER MISMANUFACTURED B UC2R K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 19 4149G 839 8050831 2843191 L3632336A SUBMITTER STATED THEY HAVE FOUND 6 ARMATURES TO HAVE SEEMINGLY SOFT METAL ON THE DRIVE END SPLINES. THEY HAVE BEEN FOUN D WITH THE SPLINES COMPLETELY GROUND OR STRIPPED AWAY LEAVING SHARDS OF STEEL IN THE GEAR CASING THAT CONTAMINATE THE RO LLER BEARINGS. THE BENDIX DRIVE GEAR IS NOT DAMAGED AND THE SHEAR PIN DOES NOT SHEAR. THE ARMATURE DRIVE END MAY NOT B E PROPERLY HEAT TREATED OR MAYBE THE SHEAR PIN IS TOO HARD. (X) 1 L 7 1 3O 3 O 2A13 E286 2000051000231 20000510 00231 NM 2000 5 10 20000504SH008 1 20000404 G 5280 6521636185 DOOR BOEING 727 727* NM MLG WRONG PART H K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 19 DOOR HAS BEEN IDENTIFIED AS A DASH 185. DOOR IS NOT A DASH 185, BUT A DASH 1. DOOR HAS NOT BEEN MODIFIED PER SB 32-318 WHICH ALLOWS USE OF LARGER DIAMETER DRAG STRUT FOR MLG. THIS DOOR WAS BINDING WITH DRAG STRUT WHICH MAY HAVE CAUSED DI FFICULTY EXTENDING THE LANDING GEAR. (X) 2 L 7 3 4F RT A3WE 2000051000232 20000510 00232 CE 2000 5 10 20000504SH009 1 20000504 G 3230 TORQUE LINK BEECH 90 C90 1152913 CE MLG MISMARKED G K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 04 90LF LJ852 REF: RAYTHEON SB 32-3116. SOME TORQUE KNEES IDENTIFIED AS MLG P/N''S 50-810032-12 AND 50-810295-25 WERE MACHINED TO BE NOSE GEAR COMPONENTS. IF INSTALLED, THESE TORQUE KNEES WILL ALLOW MAIN GEAR TO OVER EXTEND AND DAMAGE FORWARD PORTION OF WHEELWELL UPON RETRACTION. (X) 1 L 7 2 3T 3A20 2000051000233 20000510 00233 CE 2000 5 10 20000504SH010 1 20000415 G 2731 CONTROL CABLE CESSNA 182 182S 2072701 CE ELEVATOR TRIM OUT OF RIG B K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 07 789LM 105 18280043 WHILE CHECKING FOR ELEVATOR TRIM OPERATOR AFTER C/W SB 00-22-01A ON KAP-104 AUTOPILOT SERVO, NOTED THE ELEVATOR TRIM WOU LD NOT GO FULL TRAVEL. AFTER INVESTIGATING, NOTED THE SERVO TRIM CABLE SWEDGED BALL WAS OUTSIDE THE SERVO DRUM, THE AUT OPILOT CABLE WAS NOT PROPERLY CENTERED IN REFERENCE TO ELEV TRIM NEUTRAL. RIGGED SYSTEM TO CESSNA MM WITH NO RIGGING PR OBLEMS. SUBMITTER STATED IT WAS OBVIOUS TRIM WAS NOT RIGGED PROPERLY AT FACTORY. POSSIBILITY OF OTHERS HAVING SIMILAR PROBLEM. PROBLEM WOULD NOT BE OBVIOUS UNTIL ELEVATOR TRIM IS RUN TO ITS LIMIT ALLOWING THE SWEDGE BALL TO COME OFF THE DRUM. (X) 1 H 7 1 3O NT 3A13 2000051000235 20000510 00235 SO 2000 5 10 20000504SH012 1 20000405 G 3213 6531904 CLEVIS PIPER PIPER PA28 PA28151 7102805 SO MLG STRUT FAILED H A UNSCHED LANDING D INFLIGHT SEPARATION CL CLIMB 1 SW 99 41539 287415259 THE UPPER TORQUE LINK ATTACH CASTING CLEVIS BROKE WHILE DOING TOUCH AND GO''S. THE STRUT PISTON AND WHEEL ASSY SEPARATE D FROM AIRCRAFT HELD ONLY BY BRAKE LINE. FAILURE CAUSED BY CRACK IN TORQUE LINK ATTACH CLEVIS ON STRUT. (X) 1 L 7 1 3O 2A13 2000051000236 20000510 00236 CE 2000 5 10 20000504SH013 1 20000406 G 3220 5042000224 TRUNNION CESSNA 340 340CESSNA 2076404 CE NLG FAILED H O OTHER O OTHER NR NOT REPORTED 1 GL 21 123KK 5957 3400251 NOSE GEAR TRUNNION FAILED. (X) 1 L 7 2 3O 3A25 2000051000237 20000510 00237 CE 2000 5 10 20000504SH014 1 20000328 G 3230 51232530 CIRCUIT BREAKER CESSNA 337 337H 2075732 CE MLG PUMP FAILED B LX5R O OTHER O OTHER NR NOT REPORTED 1 GL 19 12445 5306 33701892 THE CIRCUIT BREAKER FAILED TO THE OPEN POSITION PREVENTING A NORMAL EXTENSION OF THE AIRCRAFT LANDING GEAR. (X) 1 H 7 2 3O A6CE 2000051000239 20000510 00239 CE 2000 5 10 20000504SH016 1 20000504 G 3060 MS21919WCF6 CLAMP CESSNA 340 340A 2076405 CE PROP DEICE SYS BROKEN B O OTHER O OTHER NR NOT REPORTED 1 GL 11 550S 340A0086 PILOT COMPLAINED OF ''POP'' WHEN LANDING GEAR WAS EXTENDED. LANDING MADE WITHOUT INCIDENT. UPON INVESTIGATION COULD FI ND NO PROBLEMS WITH GEAR RETRACTION SYSTEM. FURTHER INVESTIGATION REVEALED LEFT PROPELLER NR 3 BLADE DEICE WIRE HARNESS CLAMP HAD BROKEN OFF AND HIT THE LEFT SIDE OF FUSELAGE CAUSING THE ''POP'' THE PILOT HEARD. REPLACED BROKEN CLAMP AND REPAIRED HARNESS. (X) 1 L 7 2 3O 3A25 2000051000241 20000510 00241 SO 2000 5 10 20000504SH018 1 20000314 G 3230 WTC21351 POWERPACK PIPER PA31 PA31350 7103110 SO LT MLG FAILED A BSYA A UNSCHED LANDING J WARNING INDICATION LD LANDING 1 GL 07 4UE 318152061 DTW - AIRCRAFT DID NOT HAVE LEFT GEAR DOWN AND LOCK INDICATION. FLEW AIRCRAFT BACK TO CMH. MAINTENANCE REMOVED AND REP LACED HYDRAULIC POWER PACK. OPS CHECKED GOOD. (X) 1 L 7 2 3O A20SO 2000051000242 20000510 00242 WP 2000 5 10 20000504SH019 2 20000309 G 7320 66001983 VALVE LEAR 35 35A 5170602 CE GARRTT TFE731 TFE73122B 01518 WP FLOW CONTROL FAILED A BSYA O OTHER J WARNING INDICATION NR NOT REPORTED 1 GL 07 56JA 342 P74242C DEN - LOST PRESSURIZATION AFTER TAKEOFF OUT OF DENVER. FOUND FLOW CONTROL VALVE STUCK CLOSED. REMOVED AND REPLACED FLO W CONTROL VALVE. OPS CHECKED GOOD. (X) 2 L 7 2 4F 4 F A10CE E6WE 2000051800055 20000518 00055 SO 2000 5 18 20000504SH020 1 20000314 G 3260 BULB PIPER PA31 PA31350 7103110 SO COCKPIT FAILED A BSYA O OTHER N FALSE WARNING NR NOT REPORTED 1 GL 07 4079Y 318152079 DTW - HAD NO RIGHT GEAR DOWN AND LOCK LIGHT. SWAPPED BULBS BETWEEN NOSE AND RIGHT MAIN. INSTALLED NEW BULB. OPS CHEC KED GOOD. (X) 1 L 7 2 3O A20SO 2000051800056 20000518 00056 EU 2000 5 18 20000504SH021 1 20000331 G 7921 5711012394 COOLER PILATS PC12 PC1245 EU OIL SYSTEM CRACKED B K NONE O OTHER IN INSP/MAINT 1 WP 07 308NA 226 FOUND OIL COOLER VANE CRACKED WITH 3 POPPED RIVETS. REMOVED AND REPLACED OIL COOLER VANE IAW MANUFACTURER''S SB 71-001. NO RECOMMENDATIONS TO PREVENT RECURRENCE SINCE SB 71-001 HAD BEEN PREVIOSULY C/W. (X) 1 L 7 1 3T RT A78EU 2000051800057 20000518 00057 GL 2000 5 18 20000504SH022 3 20000413 G 6110 57C2295 BULKHEAD HARTZL HCC2Y HCC2YF1 GL BLADE SLOTS CRACKED H K NONE O OTHER IN INSP/MAINT 1 SW 99 AM2897 MULTIPLE CRACKS AT BLADE SLOTS. (X) 5 C P920 2000051800060 20000518 00060 SO 2000 5 18 20000504SH025 2 20000309 G 8520 520 CRANKSHAFT CESSNA 340 340CESSNA 2076404 CE CONT O520 TSIO520NB 17040 SO ENGINE FAILED B VAIR O OTHER Y J ENGINE STOPPAGE WARNING INDICATION NR NOT REPORTED 1 SW 19 69520 485 3400353 514988 ENGINE IN-FLIGHT FAILURE DUE TO BROKEN CRANKSHAFT. THIS CRANKSHAFT INSTALLED AS NEW ON MAY 4, 1999 TO REPLACE PREVIOUS NEW CRANKSHAFT AFFECTED BY AD 99-19-01. THIS S/N CRANCKSHAFT, SN B129901N, IS NOT IN AD. CRNAKSHAFT S/N''S IN AD GO T HROUGH 12-1998. (X) 1 L 7 2 3O 3 O 3A25 E8CE 2000051800061 20000518 00061 NM 2000 5 18 20000504SH026 1 20000411 G 2840 600N4004503 CONNECTOR DOUG 600N 600N 3027377 NM FUEL INDICATOR CONTAMINATED D O OTHER N FALSE WARNING NR NOT REPORTED 1 SW 99 611BP 500 RN041 PILOT RECEIVED ERRONEOUS FUEL QUANTITY INDICATIONS. UPON REMOVING ELECTRICAL CONNECTOR AT AFT FUEL BLADDER COVER, NOTED THAT FUEL WAS LEAKING INTO PIN AREA. THIS WAS THE SECOND INSTANCE. FIRST WAS AT BORDER PATROL AIR OPERATIONS IN LARED O, TX. THESE HARNESSES APPARENTLY HAD A SEALING PROBLEM. (X) 1 G 7 1 3U NC H3WE 2000051800062 20000518 00062 NM 2000 5 18 20000504SH027 1 20000413 G 5311 65C353502 FRAME BOEING 727 72721 1384003 NM FUSELAGE CRACKED B K NONE O OTHER IN INSP/MAINT 1 SO 19 727LA 19260 RIGHT FRAME AT STA 870 BETWEEN STR 9R - STR 10R HAS CRACK ON FORWARD OUTBOARD FLANGE UNDER SPLICE PLATE. FOUND WITH ULT RASOUND INSPECTION. (X) 2 L 7 3 4F A3WE 2000062100001 20000621 00001 SO 2000 6 21 20000504SH030 1 20000322 G 3233 MS3877 O-RING GARKENYON PIPER PA32 PA32RT300 7103215 SO NLG ACTUATOR FAILED H A UNSCHED LANDING J K WARNING INDICATION FLUID LOSS CR CRUISE 1 GL 17 800TM 4343 32R7985088 AFTER TAKEOFF, THE NOSE GEAR FAILED TO FULLY RETRACT AND WOULD NOT EXTEND TO DOWN AND LOCKED POSITION. THE PILOT PERFOR MED VAROIUS MANEUVERS AND GEAR FINALLY EXTENDED DURING A POWER OFF STALL. AFTER LANDING INSPECTION, FOUND THE SHAFT O-R ING ON THE NOSE GEAR ACTUATOR BADLY DETERIORATED CAUSING LOSS OF ALL SYSTEM FLUID. ACTUATORS SHOULD BE INSPECTED CLOSEL Y AND ANY SIGNS OF LEAKAGE SHOULD BE REPORTED. (X) 1 L 7 1 3O A3SO 2000051800065 20000518 00065 WP 2000 5 18 20000504SH031 1 20000406 G 6710 369A70099 CONTROL ROD HUGHES 369 369E 4470707 WP COLLECTIVE LOOSE H K NONE O OTHER IN INSP/MAINT 1 WP 09 9204Y 1688 0532E DURING INSPECTION, THE ROD END ON TOP OF THE COLLECTIVE MIXER CONTROL ROD WAS FOUND MOVING. THE JAM NUT ON THE ROD END WAS TIGHT. FURTHER INSPECTION REVEALED THE THREADED INSERT THE ROD END SCREWS INTO WAS LOOSE IN THE CONTROL ROD ITSELF. AFTER REMOVAL OF THE CONTROL ROD FROM THE AIRCRAFT FOR REPLACEMENT, IT WAS FOUND TO CONTAIN WATER THAT HAD APPARENTLY CENTERED THE TUBE AROUND THE LOOSE INSERT. THIS IS THE SECOND INCIDENCE OF FINDING A LOOSE INSERT IN A COLLECTIVE MIXER CONTROL ROD. (X) 1 G 7 1 3U H3WE 2000051000283 20000510 00283 SO 2000 5 10 20000505SH005 2 20000405 G 8530 538304P030 PUSHROD BEECH 55 95A55 1152704 CE CONT O520 IO520CB 17032 SO NR 6 CYLINDER BENT B K NONE O OTHER IN INSP/MAINT 1 GL 03 5115 190 244255R NR 6 EXHAUST PUSHROD BENT, BROKEN AND WORN HALFWAY THRU FROM RUBBING ON INSIDE OF THE PUSHROD HOUSING. NR 6 INTAKE PUSH ROD BROKEN IN TWO. CYL HAS 190 HRS SINCE NEW AND BOTH VALVES MOVED FREELY IN GUIDES. NR 6 CONNECTING ROD FOUND VISIBLY BENT. INTAKE MANIFOLD DRAINS DID NOT DRAIN WHEN TESTED. POSSIBLE CAUSE, HYD LOCK, TCM SB96-11. NR 6 CYL ON THIS INST ALL (RT ENG OF BEECH BARON) IS FRONT INBD CYL. CANT OF ENG WOULD MAKE THIS A LOW SPOT IN INTAKE WHERE FUEL WOULD ACCUMU LATE. WITH FUEL DRAIN INOP, IT WOULD NOT DRAIN OUT. RECOMMENDATION IS TO INCLUDE A TEST OF MANIFOLD DRAINS AT 100-HR ANNUAL INSPECTION. (X) 1 L 7 2 3O 3 O 3A16 E5CE 2000051000285 20000510 00285 NE 2000 5 10 20000505SH007 2 20000404 G 7250 304418301 BLADE PWA PT6 PT6A67D NE POWER TURBINE DAMAGED B MASR K NONE O OTHER IN INSP/MAINT 1 SW 07 PART WAS REMOVED FROM STOCK NEW. BLADE PLATFORM ON ONE BLADE WAS FOUND TO BE TAPERED AND VERY THIN. P&WC WAS NOTIFIED AND WERE ADVISED TO REMOVE BLADE FROM STOCK AND SHIP BAD BLADE BACK TO P&WC. PART WAS NEVER PUT INTO SERVICE. (X) 4 T E26NE 2000051000286 20000510 00286 WP 2000 5 10 20000505SH011 2 20000414 G 7250 30723163 DISK GARRTT TFE731 TFE731* 01518 WP HP TURBINE DAMAGED H K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 99 NEW PART RECEIVED FROM HONEYWELL WITH DAMAGE IN POST FIR TREE AREA. LOT NR 00P054. (X) 4 F E6WE 2000051000287 20000510 00287 WP 2000 5 10 20000505SH012 2 20000412 G 7250 30723163 DISK GARRTT TFE731 TFE731* 01518 WP HP TURBINE DAMAGED H K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 99 NEW PART RECEIVED FROM HONEYWELL WITH 3 DENTS IN POST FIR TREE AREA AFT SIDE. LOT NR 00P054. (X) 4 F E6WE 2000051000288 20000510 00288 WP 2000 5 10 20000505SH013 2 20000414 G 7250 30723163 DISK GARRTT TFE731 TFE731* 01518 WP HP TURBINE DAMAGED H K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 99 NEW PART RECEIVED FRON HONEYWELL WITH DAMAGE IN POST FIR TREE AREA. LOT NR 00P054. (X) 4 F E6WE 2000052300005 20000523 00005 WP 2000 5 23 20000505SH014 2 20000410 G 7230 30720705 DISK GARRTT TFE731 TFE731* 01518 WP LP TURBINE DAMAGED H K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 99 NEW PART RECEIVED FROM HONEYWELL WITH DAMAGE IN POST FIR TREE AREA. LOT NR 99P189. (X) 4 F E6WE 2000062200050 20000622 00050 2000 6 22 20000505SH016 4 20000406 G 3418 861CAU2 VANE FAILED B K NONE O OTHER IN INSP/MAINT 1 GL 19 ANGLE OF ATTACK VANE FAILS ''''ZERO VOLT TEST''''. AT A VANE ANGLE OF 19 DEGREES, VOLTAGE SHOULD BE 5.988 TO 6.012. TH IS VANE READS 6.4 VOLTS. THIS VANE WOULD CAUSE AN EARLY STALL WARNING AND/OR SLAT EXTENSION. (X) 2000061300352 20000613 00352 CE 2000 6 13 20000505SH018 1 20000329 G 7820 075016128 MUFFLER CESSNA 182 182G 2072716 CE CONT O470 O470R 17026 SO EXHAUST SEPARATED D O OTHER O OTHER NR NOT REPORTED 1 NE 05 2354R 18255454 1301794R DURING ANNUAL INSPECTION, THE LT INTERNAL BAFFLE WAS FOUND TO HAVE SEPARATED AND WAS PARTIALLY BLOCKING THE EXHAUST PORT IN THE MUFFLER. UPON REMOVAL, THE RT EXHAUST STACK WAS FOUND BADLY DETERIORATED WITH SEVERAL PIECES MISSING. ONLY MI NOR EXHAUST LEAK WAS NOTED FROM UNDER CLAMP. TIME IN SERVICE OF THESE PARTS IS NOT KNOWN. (X) 1 H 7 1 3O 3 O NT 3A13 E273 2000061400119 20000614 00119 CE 2000 6 14 20000505SH019 1 20000329 G 7820 075016131 MUFFLER CESSNA 182 182G 2072716 CE CONT O470 O470R 17026 SO INTERNAL CONNECT DETERIORATED D K NONE O OTHER IN INSP/MAINT 1 NE 05 2354R 18255454 1301794R DURING ANNUAL INSPECTION, THE LT INTERNAL BAFFLE WAS FOUND TO HAVE SEPARATED AND WAS PARTIALLY BLOCKING THE EXHAUST PORT IN THE MUFFLER. UPON REMOVAL, THE RT EXHAUST STACK WAS FOUND BADLY DETERIORATED WITH SEVERAL PIECES MISSING. ONLY MI NOR EXHAUST LEAK WASNOTED FROM UNDER CLAMP. TIME IN SERVICE OF THESE PARTS IS NOT KNOWN. (X) 1 H 7 1 3O 3 O NT 3A13 E273 2000061600326 20000616 00326 EU 2000 6 16 20000505SH024 1 20000331 G 7921 5711012394 COOLER PILATS PC12 PC1245 EU NOSE CRACKED B K NONE O OTHER IN INSP/MAINT 1 WP 07 317NA 1368 223 FOUND OIL COOLER VANE CRACK WITH 3 POPPED RIVETS. REMOVED AND REPLACED OIL COOLER VANE IAW MANUFACTURER''''S SB 71-001 KIT. NO RECOMMENDATIONS TO PREVENT RECURRENCE SINCE SB 71-001 HAD PREVIOUSLY BEEN C/W. (X) 1 L 7 1 3T RT A78EU 2000061400120 20000614 00120 EA 2000 6 14 20000505SH025 2 20000407 G 8530 AEL6510241 CYLINDER PIPER PA28 PA28161 7102803 SO LYC O320 O320D3G 41508 EA HEAD CRACKED B MW2R K NONE O OTHER IN INSP/MAINT 1 GL 17 4381L 878 288516016 L1341139A FOUND ZERO COMPRESSION ON ROUGH RUNNING ENGINE. FOUND CRACK FROM TOP SPARK PLUG AROUND OUTSIDE OF EXHAUST SEAT TO BOTTO M SPARK PLUG. (X) 1 L 7 1 3O 3 O 2A13 E274 2000061400121 20000614 00121 EA 2000 6 14 20000505SH026 2 20000407 G 8530 AEL6510241 CYLINDER PIPER PA28 PA28161 7102803 SO LYC O320 O320D3G 41508 EA CYLINDER CRACKED B MW2R K NONE R PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 GL 17 4381L 878 288516016 L1341139A FOUND ZERO COMPRESSION ON ROUGH RUNNING ENGINE. FOUND CRACK FROM TOP SPARK PLUG AROUND OUTSIDE OF EXHAUST SEAT TO BOTTO M SPARK PLUG. (X) 1 L 7 1 3O 3 O 2A13 E274 2000061600327 20000616 00327 EA 2000 6 16 20000505SH027 2 20000407 G 8530 AEL6510212 CYLINDER PIPER PA28 PA28181 7102807 SO LYC O360 O360A4M 41514 EA EXHAUST VALVE BROKEN B MW2R K NONE O OTHER AP APPROACH 1 GL 17 4350G 586 288490058 L2749236A EXHAUST VALVE BROKE ON FINAL APPROACH. (X) 1 L 7 1 3O 3 O 2A13 E286 2000061400126 20000614 00126 2000 6 14 20000505SH028 4 20000309 G 3415 SENSOR NARCO PIPER PA28 PA28181 7102807 SO LEAKING B UC2R K NONE O OTHER IN INSP/MAINT 1 GL 19 4145A 1086 15091 2843150 *STATIC SYSTEM LEAK GREATER THAN 100 FEET/MINUTE TRACED TO THIS UNIT. AR850 ONLY TWO YEARS IN SERVICE SINCE AIRCRAFT WA S NEW. AR850''''''''S ARE NOT KNOWN TO BE FAULTY IN THIS MANNER. SUBMITER STATED POSSIBLE NARCO FACTORY DEFECT IN ASS EMBLY OF SENSOR. THIRD FAILURE KNOWN TO SUBMITTER. (X) 1 L 7 1 3O 2A13 2000061400127 20000614 00127 2000 6 14 20000505SH029 4 20000309 G 3416 SENSOR NARCO PIPER PA28 PA28181 7102807 SO LEAKING B UC2R K NONE O OTHER IN INSP/MAINT 1 GL 19 4145G 1078 15090 2843151 STATIC SYSTEM LEAK GREATER THAN 100 FEET/MINUTE TRACKED TO THIS UNIT. AR850 ONLY TWO YEARS IN SERVICE SINCE AIRCRAFT WA S NEW. AR850''S ARE NOT KNOWN TO BE FAULTY IN THIS MANNER. SUBMITTER STATED POSSIBLE NARCO FACTORY DEFECT IN ASSEMBLY OF SENSOR. SECOND FAILURE KNOWN TO THIS SOURCE. (X) 1 L 7 1 3O 2A13 2000052500060 20000525 00060 GL 2000 5 25 20000505SH030 1 20000418 G 6520 28135000 GEAR ENSTRM F28 280C 3300505 GL T/R GEARBOX BROKEN B FSPR K NONE O OTHER IN INSP/MAINT 1 NE 05 5691W 1176 PILOT REPORTED NOT BEING ABLE TO SEE OIL LEVEL IN SIGHT GLASS. WHEN SIGHT GLASS REMOVED, A PIECE OF GEAR SET (TOOTH) AB OUT .4375 INCH LONG WAS FOUND INSIDE. ACFT HAD RETURNED FROM FLYING, AND THERE WAS NO VIBS OF NOISE. WEAR MARKS ON BR OKEN PART GAVE APPEARANCE OF HAVING BEEN BROKEN FOR QUITE SOME TIME. INSP OF CHIP PLUG SHOWED NO METAL FLAKES OR CHIPS . SUBMITTER RECOMMENDED PULLING SIGHT GLASS AND LOOKING INSIDE TAIL GEARBOX AT EACH 100-HR OIL CHANGE/AD 90-01-06 INSPE CTING IT FOR METAL FLAKES. (X) 1 G 7 1 3O H1CE 2000061400131 20000614 00131 EA 2000 6 14 20000505SH031 2 20000505 G 7414 4150 MAGNETO BBAVIA 8 8KCAB 2110612 CE LYC O320 AEIO320E1B 41508 EA CONTAMINATED D K NONE R PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 EA 23 50395 A9379 L567955A OWNER COMPLAINED OF ROUGH RUNNING/MISSING WHEN ENGINE HOT WHILE AT LOW POWER SETTINGS. RT MAG (4150) REMOVED. EXCESS P LAY IN DIST END BEARING (APPROX PLAY, .030 INCH) SN 9010274. LT MAG REMOVED (4151) SN 9010270. FOUND ENTIRE INTERIOR O F MAG CONTAMINATED BY GREASE FROM DRIVE END BEARING. THESE MAGS (4100 SERIES) ARE NOT REBUILDABLE AND SLICK SB RECOMMEND S REPLACEMENT AND TIS TO BE NOT IN EXCESS OF 800 HRS. ENGINE TT: 494 HRS SINCE NEW. 1 H 7 1 3O 3 O A21CE 1E12 2000061400132 20000614 00132 EA 2000 6 14 20000505SH032 2 20000505 G 7414 4151 MAGNETO BBAVIA 8 8KCAB 2110612 CE LYC O320 AEIO320E1B 41508 EA CONTAMINATED B K NONE R PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 EA 23 50395 A9379 L567955A OWNER COMPLAINED OF ROUGH RUNNING/MISSING WHEN ENGINE HOT WHILE AT LOW POWER SETTINGS. RT MAG (4150) REMOVED. EXCESS P LAY IN DIST END BEARING (APPROX PLAY, .030 INCH) SN 9010274. LT MAG REMOVED (4151) SN 9010270. FOUND ENTIRE INTERIOR O F MAG CONTAMINATED BY GREASE FROM DRIVE END BEARING. THESE MAGS (4100 SERIES) ARE NOT REBUILDABLE AND SLICK SB RECOMMEND S REPLACEMENT AND TIS TO BE NOT IN EXCESS OF 800 HRS. ENGINE TT: 494 HRS SINCE NEW. (X) 1 H 7 1 3O 3 O A21CE 1E12 2000061400133 20000614 00133 2000 6 14 20000505SH033 4 20000413 G 6113 08550301719 SPINNER CESSNA 310 310K 2074228 CE LEFT CRACKED A K NONE O OTHER IN INSP/MAINT 1 EA 21 6942L 120 310K0042 BRAND NEW CESSNA SPINNER DOME INSTALLED ON 4-30-99. LAST INSPECTION ANNUAL ON 7/16/99. APRIL12, 2000, 100-HOUR INSPECT ION REVEALS ONE INCH CRACK AT ONE MOST FORWARD SCREW. TWO SCREW HOLES ARE OVAL, NOT ROUND. TOTAL PART TIME PLUS/MINUS 120 HOURS. (X) 1 L 7 2 3O 3A10 2000052500061 20000525 00061 WP 2000 5 25 20000505SH034 1 20000329 G 6720 269A6050S SWASHPLATE HUGHES 269 269C 4470504 WP TAIL ROTOR BINDING B O OTHER O OTHER NR NOT REPORTED 1 WP 15 61447 2428 0007 INTERMITTENT T/R PEDAL BINDING. (X) 1 G 7 1 3O 4H12 2000052500062 20000525 00062 SW 2000 5 25 20000505SH035 1 20000120 G 6340 209A425013 TACHOMETER HUGHES 269 269C1 8059504 SW MAIN ROTOR INOPERATIVE B CAXR O OTHER O OTHER NR NOT REPORTED 1 WP 15 6147Q 1393 0068 ROTOR TACHOMETER INOPERABLE. (X) 1 G 7 1 3O O 4H12 2000061400201 20000614 00201 NE 2000 6 14 20000508SH003 1 20000414 G 7120 LA4180 MOUNT CONAER LA4 LA4 5110302 NE RT LOWER ATTACH CRACKED B UM9R K NONE O OTHER IN INSP/MAINT 1 NM 13 6653L 757 416 RIGHT LOWER ENGINE ATTACH POINT CRACKED TO RIGHT STRUT ATTACH POINT. (RADIALLY THROUGH MOUNT TUBE). DETECTED DURING AN NUAL INSPECTION VISUALLY AND VERIFIED BY DIE/PENETRANT. (X) 1 H 7 1 3O 1A13 2000061400202 20000614 00202 EA 2000 6 14 20000508SH005 2 20000324 G 8530 LW15318 ROCKER BOSS LYC CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA FAILED D K NONE O OTHER IN INSP/MAINT 1 SW 15 75958 85 17268069 RL81676 VALVE ROCKER RETAINING STUD, PN 31-16, SHEARED FLUSH WITH THE CYL HEAD SURFACE. THIS CAUSED PARTS TO MOVE AROUND AT RAN DOM IN THE HEAD. IT IS SUSPECTED THESE LOOSE PARTS INTERFERRED WITH OPER OF INTAKE VALVE MECHANISM CAUSING THE INTAKE P USH ROD TO BEND, CREATING AN OIL LEAK AT THE PUSH ROD HOUSING. SAME PROBLEM OCCURRED 65.7 HRS EARLIER WITH NR 1 CYL, 1 9.2 HRS SINCE O/H. INSP OF ENG REVEALED EXH ROTATOR CAP DISLODGED, LAYING IN BOTTOM OF VALVE COVER ON NR 2 CYL. SUSPEC TED EXH VALVES MAY BE STICKING IN OPEN POSITION ALLOWING ROTATOR CAP TO FALL OUT OF POSITION. THE EXCESSIVE CLEARANCE T HEN CREATED BETWEEN ROCKER ARM AND EXH VALVE STEM COULD POSSIBLY CAUSE ABNORMAL STRESS TO ROCKER ARM RETAINING STUD. 1 H 7 1 3O 3 O NT 3A12 E274 2000061300360 20000613 00360 2000 6 13 20000508SH007 4 20000417 G 2300 LIGHT CESSNA 172 172R 2072401 CE WIRING BUNDLE CHAFED D K NONE O OTHER IN INSP/MAINT 1 SW 15 869CP 953 17280641 PILOT REPORTED THE RADIO LIGHTS WERE FLICKERING WHILE ENGINE WAS RUNNING. UPON INSPECTION, WIRING BUNDLE THAT RUNS HORI ZONTALLY ACROSS BOTTOM OF INSTRUMENT PANEL WAS FOUND CHAFING ON ''''RADIO INSTRUMENT LIGHT POTENTIOMETER'''' PN S2091-9 (REF: R1002 I CESSNA WIRING DIAGRAM 33-10-01). THE CHAFING HAD DAMAGED AND CREATED BARE SPOTS ON THREE WIRES THAT WER E TRACED TO THE AVIONICS LIGHTING BUS'''' CREATING A SHORT AND CAUSING THE FLICKERING OF LIGHTS. THE WIRES WERE REPAIRE D AND WIRING BUNDLE WAS SECURED AND REPOSITIONED IN A WAY TO PREVENT FURTHER CHAFING ON POTENTIOMETER. (X) 1 H 7 1 3O NT 3A12 2000061400203 20000614 00203 CE 2000 6 14 20000508SH009 1 20000402 G 3213 J199744G16 BEARING CESSNA 172 172RG 2072438 CE TRUNNION ASSY N/ LACK OF LUBE D K NONE O OTHER TO TAKEOFF 1 NE 05 9717B 1770 172RG0987 AIRCRAFT WOULD NOT STEER ON TAKEOFF ROLL. BRAKES INEFFECTIVE TO TURN. DISASSEMBLED NOSE GEAR TRUNNION AND FOUND UPPER AND LOWER NACELLE BEARINGS RUSTED AND FROZEN. NO PROVISIONS FOR LUBRICATION AT THESE POINTS. AIRCRAFT MANUFACTURED 198 2. 1 H 7 1 3O 3A17 2000061600332 20000616 00332 CE 2000 6 16 20000508SH010 1 20000402 G 3213 J199740G12 BEARING CESSNA 172 172RG 2072438 CE TRUNNION ASSY FROZEN D K NONE O OTHER TO TAKEOFF 1 NE 05 9717B 1770 172RG0987 AIRCRAFT WOULD NOT STEER ON TAKEOFF ROLL. BRAKES INEFFECTIVE TO TURN. DISASSEMBLED NOSE GEAR TRUNNION AND FOUND UPPER A NDFROZEN. NO PROVISIONS FOR LUBRICATION AT THESE POINTS. AIRCRAFT MANUFACTURED 1982. 1 H 7 1 3O 3A17 2000061400205 20000614 00205 CE 2000 6 14 20000508SH012 1 20000329 G 7120 909100141 MOUNT BEECH 100 B100 1152919 CE WORN B WD4R K NONE O OTHER IN INSP/MAINT 1 SO 17 818PA 5807 BE18 WHILE DOING A HOT SECTION INSPECTION ON THE RIGHT ENGINE AFTER REMOVAL FROM THE AIRCRAFT, NOTICED DAMAGE TO THE TUBULAR ENGINE MOUNT CROSS-MEMBER. AFTER FURTHER INVESTIGATION, FOUND AN ENGINE MOUNT BRACKET RUBBING AGAINST THE TUBULAR CROSS -MEMBER. (X) 1 L 7 2 4T A14CE 2000061300514 20000613 00514 CE 2000 6 13 20000508SH016 1 20000411 G 5753 122101015 FLAP TRACK CESSNA 182 182P 2075816 CE LT WING CRACKED D K NONE O OTHER IN INSP/MAINT 1 NM 01 1298M 18264280 SHEARED RIVETS AT FORWARD LOWER END OF FLAP TRACK AND CRACKED FLAP TRACKMOUNTING ANGLE LOWER END FORWARD. WING FLAP WAS DAMAGED WHEN FLAPS WERE RETRACTED AND CONTACT WAS MADE WITH BRACKET IN FLAP WELL. POSSIBLE CAUSE, OPERATING FLAPS AT HIGHER THAN NORMAL SPEEDS. (X) 1 H 7 1 3O NT TA13 2000060900521 20000609 00521 2000 6 9 20000508SH017 4 20000418 G 3416 212070238007 ALTIMETER BELL 412 412EP 1182205 SW COCKPIT OUT OF ADJ B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 6400J 20 36243 ALTIMETER FAILED CALIBRATION. REPLACED WITH NEW ALTIMETER FROM BELL HELICOPTER. (X) 1 G 7 2 4U H4SW 2000060900522 20000609 00522 2000 6 9 20000508SH018 4 20000418 G 3416 212070238 ALTIMETER BELL 412 412EP 1182205 SW COCKPIT OUT OF ADJ B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 6400J 20 36243 ALTIMETER FAILED CALIBRATION. REPLACED WITH NEW ALTIMETER FROM BELL HELICOPTER. (X) 1 G 7 2 4U H4SW 2000061400206 20000614 00206 EA 2000 6 14 20000508SH019 2 20000414 G 8540 GEAR BNORM BN2 BN2A26 1520226 EU LYC O540 O540E4C5 41532 EA CRANKSHAFT BROKEN D A UNSCHED LANDING Y ENGINE STOPPAGE CR CRUISE 1 SO 21 678TA 6418 2106 77 L1395540 ON CRUISE FLIGHT, LEFT ENGINE QUIT. PILOT LANDED, INVESTIGATION REVEALED BROKEN CRANKSHAFT GEAR. ENGINE RETIRED FROM S ERVICE AND AND OVERHAULED ENGINE INSTALLED ON AIRCRAFT. (X) 1 H 7 2 3O 3 O A17EU E295 2000061400207 20000614 00207 SO 2000 6 14 20000508SH020 2 20000310 G 7421 SPARK PLUG CONT CESSNA 207 207A 2073604 CE CONT O520 IO520* 17032 SO NR 2 CYLINDER FAILED A FMAA A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CR CRUISE 1 AL 01 75703 20700639 814764R PISTON TOP BEGAN TO DISINTEGRATE CAUSING SEVERAL SPARK PLUG FAILURES AND ENOUGH POWER LOSS TO CAUSE A FORCED LANDING. ( X) 1 H 7 1 3O 3 O A16CE E5CE 2000061400208 20000614 00208 NE 2000 6 14 20000508SH021 3 20000404 G 6111 2202 BEARING HARTZL PIPER PA60 PA60601P 7106012 NM HARTZL HCC3Y HCC3YR2 NE CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 LU4R 61P0395135 CK4084A CRACK INDICATION ON BOTH SIDES OF BEARING. (X) 1 M 7 2 3O RT A17WE 5 C P25EA 2000062000009 20000620 00009 2000 6 20 20000508SH022 4 20000411 G 6122 A3181 COUPLER HARTZL CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 3487T RELEVENT CRACK INDICATION OF THE DRIVE SPLINE OF THE DRIVE COUPLER. (X) 2000062000010 20000620 00010 2000 6 20 20000508SH023 4 20000404 G 6122 B41832 FLYWEIGHT HARTZL PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 100RN D2691T 318152080 RELEVENT CRACK INDICATION ON FLYWEIGHT BASE. (X) 1 L 7 2 3O 3 O A20SO E14EA 2000062000011 20000620 00011 2000 6 20 20000508SH024 4 20000405 G 6122 B20908 FLYWEIGHT MCAULY CESSNA 402 402C 207590R CE CONT O520 IO520* 17032 SO CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 860296 RELEVANT CRACK INDICATION ON BASE OF FLYWEIGHT DISC. (X) 1 L 7 2 3O 3 O A7CE E5CE 2000062000012 20000620 00012 CE 2000 6 20 20000508SH025 1 20000412 G 3230 07106082 ANGLE CESSNA 182 182E 2072712 CE GEARBOX RUSTED D K NONE O OTHER IN INSP/MAINT 1 GL 11 9212X 3811 18253612 DURING ANNUAL INSPECTION, DISCOVERED PN 0710608-2 ANGLE HEAVILY RUSTED. AIRCRAFT ANNUAL INSPECTION COMPLETED 12 MONTHS PRIOR TO THIS INSPECTION, AND THE AIRCRAFT WAS DELIVERED FOR INSIDE STORAGE. INSPECTION DISCOVERED DRIED MUD AND DEBRIS IN THE BELLY. AIRCRAFT WAS PREVIOUSLY OPERATED ON A GRASS AND DIRT STRIP. ALL BELLY DRAIN HOLES WERE PLUGGED WITH MUD AND DEBRIS, AND ALLOWED WATER TO COLLECT. SUBMITTER STATED DURING FUTURE ANNUALS, INSPECT BELLY OF AIRCRAFT THOROUGHL Y. (X) 1 H 7 1 3O NT 3A13 2000062000013 20000620 00013 2000 6 20 20000508SH026 4 20000329 G 2215 SERVO BENDIX BEECH 58 58 1152740 CE FAILED B XA12 O OTHER O OTHER CR CRUISE 1 SW 05 3033B 149 TH1869 PILOT REPORTED AUTOPILOT PITCH AXIS FAILED AFTER FLYING THROUGH TURBULENCE. PITCH SERVO REMAINED ENGAGED, BUT IT WOULD NOT FOLLOW FLIGHT DIRECTOR COMMANDS. COMPLAINT WAS CONFIRMED ON GROUND TEST. UPON REMOVAL OF PITCH SERVO, AND ROTATING IT SIDE TO SIDE, IT WAS DETERMINED THAT NUMEROUS UNKNOWN INTERNAL COMPONENTS HAD BECOME DETACHED. (X) 1 L 7 2 3O 3A16 2000062100002 20000621 00002 SO 2000 6 21 20000508SH030 1 20000508 G 3710 SVS0133 SHUTTLE VALVE PIPER PA32 PA32300 7103212 SO VACUUM SYSTEM WORN B K NONE O OTHER IN INSP/MAINT 1 NE 01 2391U 1013 327940253 DURING ANNUAL INSP, VACUUM PUMP DRIVE FOUND SHEARED. OWNER/PILOT DID NOT KNOW PUMP INOP DURING DELIVERY FLIGHT OR AT A NY OTHER TIME. INSP FOUND ACFT TO HAVE PRECISE FLIGHT STANDBY VACUUM SYS INSTALLED, TAE SVS-133 WHICH HAD AN AUTOMATIC FLAPPER/SHUTTLE VALVE WHICH DELIVERS VACUUM FROM ENG INDUCTION SYS, SYS HAS NO INDICATION IN THE COCKPIT TO ALERT PILO T PRIMARY PUMP HAS FAILED. VALVE HAD ALUM RIVET WHICH WAS BADLY WORN AND MEASUREMENT OF SIDE CLEARANCE EXCESSIVE. AD 9 9-24-10 DATED 1-14-00 RECURRING 12/24 MONTHS INSP OF PRECISE FLIGHT STANDBY VACUUM SYS DOES NOT APPLY TO THIS INSTALL. THIS SYS IS STILL LEGAL AND INSTALLED IN ACFT APPROX 1983. NO PUMP FAILURE INDICATION. IMPENDING VALVE FAILURE. (X) 1 L 7 1 3O A3SO 2000062100003 20000621 00003 SW 2000 6 21 20000508SH031 1 20000328 G 7810 40821089 EXHAUST PIPE LYC MOONEY M20 M20M 5870222 SW LYC 0540 TIO540AF1B 41532 EA CONNECTS CYL 2 CRACKED B FE6R O OTHER O OTHER CR CRUISE 1 NM 11 139WT 45 270283 L1036461A PILOT REPORTED NEW CO2 INDICATOR TURNS BLACK EACH FLIGHT. FLT WITH DIGITAL CO2 INDICATING INSTRUMENT INDICATES 200 RPM. MAINT LOCATED 1.75 INCH CRACK AT BASE OF NR 2 CYL RISER, FLG MATING TO CYL NR 1 - 5. (LYC PN''S 40B19822 AND 40B1982 5) FOUND WARPED APPROX .020 INCH. EXH PIPE COUPLING FLG FOR CYL NR 4 (LYC PN 40B19824) FND DISTORTED WITH GASKET (PN 78 084) JOINING IT TO CYL NR 6 BADLY DAMAGED, OUT OF PLACE. ALL CRACKED AND DISTORTED COMPONENTS REPLACED WITH FACTORY NEW . FLG MATING TO CYL 1- 5 ARE DRESSED ON A SURFACE PLATE. (X) 1 L 7 1 3O 3 O RT 2A3 E14EA 2000062200087 20000622 00087 NE 2000 6 22 20000509SH001 2 20000421 G 8550 30506353 ROTOR CFE CFE73811B NE OIL PUMP MISALIGNED H K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 99 IT WAS FOUND THAT THE SEAL ROTOR, PN 3120524-2, WAS INSTALLED BACKWARDS. (X) 4 F E44NE 2000073100001 20000731 00001 NE 2000 7 31 20000509SH002 2 20000417 G 7261 30506353 PUMP CFE CFE73811B NE SEAL ROTOR MISINSTALLED B K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 99 IT WAS FOUND THAT THE SEAL ROTOR, PN 3120524-2,WAS INSTALLED BACKWARDS. (X) 4 F E44NE 2000073100002 20000731 00002 SO 2000 7 31 20000509SH003 1 20000422 G 3240 RFS2010 STATOR BFGOODRICH EMB 120 EMB120 3260201 SO NR 1 POSITION DEFECTIVE B XC4R K NONE O OTHER IN INSP/MAINT 1 SO 19 189 0291A BRAKE ASSEMBLY, PN 2-1585R, FAILED PREMATURELY. NR 1 STATOR CRACKED AT 2 RELIEF HOLES. SUBMITTER STATED THIS IS A CONT INUAL DISCREPANCY. NOTE: RAPCO FLEET SUPPORT PARTS INSTALLED IN BRAKE ASSY. (X) 2 L 7 2 4T RT A31SO 2000073100003 20000731 00003 SO 2000 7 31 20000509SH004 1 20000424 G 3240 RFS2010 STATOR BFGOODRICH EMB 120 EMB120 3260201 SO NR 1 & 2 DEFECTIVE B XC4R K NONE O OTHER IN INSP/MAINT 1 SO 19 1351 1058A BRAKE ASSEMBLY, PN 2-1585-R, FAILED PREMATURELY. NR 1 AND NR 2 STATORS CRACKED AT RELIEF HOLES. SUBMITTER STATED THIS IS A CONTINUAL DISCREPANCY. NOTE: RAPCO FLEET SUPPORT PARTS INSTALLED IN BRAKE ASSEMBLY. (X) 2 L 7 2 4T RT A31SO 2001012900141 20010129 00141 NE 2001 1 29 20000509SH006 2 20000411 G 7230 2A2833 SEAL IAE V2500 V2500A1 NE NR 4 BEARING CRACKED B KB1R K NONE O OTHER IN INSP/MAINT 1 NE 03 FLUORESCENT PENETRANT INSPECTION IAW I.A.E. V2500 PSEM, REV 42, SECTION 70-23-01, INSPECTION CHECK-01, TASK 70-23-01-230 -501). PART REJECTED AT F.P.I. DUE TO A CRACK ON THE TOP SURFACE, 0.180 INCH LONG (AS MARKED). (X) 4 F E311NE 2000062200105 20000622 00105 NE 2000 6 22 20000509SH007 2 20000418 G 7230 2A0003 BEARING IAE IAE V2500 V2500A1 NE NR 4 OUTER RACE SCORED B RA1R O OTHER O OTHER IN INSP/MAINT 1 SW 05 2299 P421091 V10491 ENGINE WAS REMOVED FOR ''NR 4 BEARING INSPECTION/REPAIR''. THE NR 4 BEARING EXHIBITED AXIAL SCORING OF THE ROLLERS AND OUTER RACE. . (X) 4 F E311NE 2001012900005 20010129 00005 WP 2001 1 29 20000509SH017 2 20000417 G 7230 30723524 DISK GARRTT TFE731 TFE731* 01518 WP POST FIR TREE SCRATCHED H K NONE O OTHER IN INSP/MAINT 1 SW 99 NEW PART RECEIVED FROM HONEYWELL WITH NUMEROUS SCRATCHES AROUND DISK IN THE POST FIR TREE AREA. LOT NR: 00P048. (X) 4 F E6WE 2001012900118 20010129 00118 NE 2001 1 29 20000509SH042 2 20000419 G 7230 2A0851 SEAL IAE V2500 V2500A1 NE TOP SURFACE CRACKED C KB1R K NONE O OTHER IN INSP/MAINT 1 NE 03 PART RECEIVED FROM WESTFIELD GAGE FOR FPI IAW V2500 MANUAL REVISION 42, SECTION 70-23-01, INSPECTION CHECK-01, TASK 70-2 3-01-230-501. PART REJECTED AT FPI DUE TO A CRACK (ONE PLACE ON TOP SURFACE, 0.200 INCH LONG). NOTE: SUBMITTER STATE D SECOND TIME THIS SERIAL NUMBER REJECTED. 4 F E311NE 2001012900119 20010129 00119 SO 2001 1 29 20000509SH043 1 20000426 G 3242 RFS2010 STATOR BFGOODRICH EMB 120 EMB120 3260201 SO NR 1 & NR 2 POSI CRACKED B XC4R K NONE O OTHER IN INSP/MAINT 1 SO 19 1214 0097A BRAKE ASSEMBLY, PN 2-15-85-R, FAILED PREMATURELY. NR 2 STATOR CRACKED AT MULTIPLE RELIEF HOLES. SUBMITTER STATED THIS IS A CONTINUAL DISCREPANCY. NOTE: RAPCO FLEET SUPPORT PARTS INSTALLED IN BRAKE ASSEMBLY. (X) 2 L 7 2 4T RT A31SO 2000073100004 20000731 00004 SO 2000 7 31 20000509SH044 1 20000426 G 3240 RFS2010 STATOR BFGOODRICH EMB 120 EMB120 3260201 SO NR 1 & 2 DEFECTIVE B XC4R K NONE O OTHER IN INSP/MAINT 1 SO 19 975 0661A BRAKE ASSY, P/N 2-1585-R, FAILED PREMATURELY. NR 1 AND NR 2 STATORS CRACKED AT MULTIPLE RELIEF HOLES. SUBMITTER STATED THIS IS A CONTINUAL DISCREPANCY. NOTE: RAPCO FLEET SUPPORT PARTS INSTALLED IN BRAKE ASSEMBLY. (X) 2 L 7 2 4T RT A31SO 2000061300370 20000613 00370 SW 2000 6 13 20000510SH001 1 20000302 G 5311 206031308015 FRAME BELL 206 206B 1181511 SW FUSELAGE CRACKED H O OTHER O OTHER NR NOT REPORTED 1 SW 99 67882 2378 5222 FRAME CRACKED AT TOP RIGHT HAND POSITION, (1:00 O''CLOCK). (X) 1 G 7 1 3U H2SW 2000062100007 20000621 00007 CE 2000 6 21 20000510SH002 1 20000510 G 2820 1200406248 LINE CESSNA 206 206H 2073301 CE LEFT HEADER TANK DEFECTIVE E K NONE K FLUID LOSS IN INSP/MAINT 1 AL 05 7273Q 191 20608045 DURING A 100-HOUR INSPECTION, THE FUEL LINE BETWEEN THE LEFT HEADER TANK AND THE FUEL SELECTOR WAS FOUND LEAKING AT THE FITTING. UPON REMOVAL, IT WAS DETERMINED THE FLARE WAS DEFECTIVE. (X) 1 H 7 1 3O RT A4CE 2000062100008 20000621 00008 EA 2000 6 21 20000510SH003 2 20000407 G 7310 MS21044N3 NUT CESSNA 206 206H 2073301 CE LYC O540 O540* 41532 EA FUEL INJECTION DEFECTIVE E K NONE O OTHER IN INSP/MAINT 1 AL 05 7273Q 191 20608045 DURING A 100-HOUR INSPECTION, THE FUEL INJECTION LINE CLAMPS WERE FOUND SECURED WITH FIBER LOCK NUTS, OF WHICH THE FIBER LOCK WAS MELTED FROM THE HEAT OF THE ENGINE DURING OPERATION. ALL NUTS WERE REPLACED WITH ALL-STEEL LOCK NUTS, P/N MS2 1045. (X) 1 H 7 1 3O 3 O RT A4CE E295 2001011100560 20010111 00560 GL 2001 1 11 20000510SH004 3 20000408 G 6110 B3D36C432B PROPELLER CESSNA 206 206H 2073301 CE MCAULY 3DF36C B3DF36C432B GL ENGINE LEAKING C K NONE O OTHER IN INSP/MAINT 1 AL 05 2312V 298 2608046 991143 DURING A PRE-FLIGHT INSPECTION OF THE AIRCRAFT IN A HANGAR, THE PILOT FOUND A LARGE POOL OF RED OIL ON THE FLOOR BENEATH THE PROPELLER. UPON REMOVAL OF THE SPINNER, DETERMINED THE FLUID WAS LEAKING FROM UNDER A PROPELLER BLADE ROOT. THE P ROP WAS REMOVED AND SENT OUT FOR REPAIR. (X) 1 H 7 1 3O RT A4CE 5 C 2000062600001 20000626 00001 NE 2000 6 26 20000510SH005 2 20000405 G 7261 MS9388019 O-RING CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE ENGINE OIL CUT E K NONE K FLUID LOSS IN INSP/MAINT 1 AL 05 1275N 161 208B0756 PCEPO0686 DURING A POST-FLIGHT INSPECTION, THE PILOT NOTED EXCESSIVE OIL ON THE LOWER COWL AND DOWN THE LEFT SIDE OF THE AIRCRAFT. UPON FURTHER INSPECTION, DETERMINED A NR 2 BEARING OIL SCAVENGETUBE COUPLING O-RING LOCATED AT C-FLANGE WAS LEAKING. UPON REMOVAL OF THE O-RING, IT WAS FOUND TO BE 75 PERCENT CUT IN HALF. THE O-RING WAS REPLACED. (X) 1 H 7 1 3T 3 T A37CE E4EA 2000062100011 20000621 00011 CE 2000 6 21 20000510SH006 1 20000407 G 2810 1200406242 LINE CESSNA 206 206H 2073301 CE HEADER TANK DEFECTIVE E K NONE K FLUID LOSS IN INSP/MAINT 1 AL 05 7273Q 191 20608045 DURING A 100-HOUR INSPECTION, THE FUEL LINE BETWEEN THE RIGHT HEADER TANK AND THE FUEL SELECTOR WAS FOUND LEAKING AT THE FITTING. UPON REMOVAL, DETERMINED THE FLARE WAS DEFECTIVE. (X) 1 H 7 1 3O RT A4CE 2000062100012 20000621 00012 CE 2000 6 21 20000510SH008 1 20000310 G 7120 9691001061 ENGINE BEECH 58 58 1152740 CE CONT O520 IO520CB 17032 SO UPPER CROSS-OVER CRACKED D K NONE K FLUID LOSS IN INSP/MAINT 1 EA 23 37SF 10525 2344 TH627 244230 DURING A SCHEDULED INSPECTION, A CRACK WAS DISCOVERED IN THE LEFT ENGINE MOUNT AT THE UPPER CROSSOVER TUBE NEAR THE WELD AT THE UPPER INBOARD ENGINE ATTACH POINT (CUSHION MOUNT). AD 91-15-20 A3 AND C HAD BEEN PREVIOUSLY C/W 2,344.4 HOURS A GO. THE MOUNT WAS REMOVED AND REPAIRED BY REPLACING THE DAMAGED TUBE. A RECORD CHECK SHOWS SUDDEN ENGINE STOPPAGE 1,16 0.8 HOURS PRIOR TO THIS DISCOVERY, AT WHICH TIME THE ENGINE WAS OVERHAULED AND THE MOUNT WAS INSPECTED FOR DAMAGE. IT I S BELIEVED THAT IN LIGHT OF THE PAST HISTORY, THE SUDDEN STOPPAGE FATIGUED THE MOUNT AT THIS POINT AND NORMAL ENGINE VIB RATION ALLOWED THE CRACK TO DEVELOP. (X) 1 L 7 2 3O 3 O 3A16 E5CE 2000061600448 20000616 00448 SW 2000 6 16 20000510SH015 1 20000415 G 5320 407030801105 BEARING BELL BELL 407 407 SW ALLSN 250C 250C47B GL TAIL ROTOR G/B FRETTED C K NONE O OTHER IN INSP/MAINT 1 SO 11 407DD 634 AFS979 53328 CAE847380 WHILE PERFORMING SCHEDULED LUBRICATION OF TAIL ROTOR HANGER BEARINGS, MECHANIC NOTICED METALLIC FRETTING DUST AROUND TAI L ROTOR GEARBOX MOUNTING AREA. FURTHER INVESTIGATION REVEALED MOVEMENT BETWEEN TAIL ROTOR GEARBOX AND TAILBOOM. THIS MA LFUNCTION IS UNDER INVESTIGATION BY MANUFACTURER AND SUBMITTER IS AWAITING RESULTS OF THIS INVESTIGATION. (X) 1 G 7 1 3U 3 U O H2SW E1GL 2000062200133 20000622 00133 SW 2000 6 22 20000510SH019 1 20000302 G 5346 212030015101P FITTING BELL 412 412 1182202 SW ENGINE MOUNT CRACKED C ULXR K NONE O OTHER IN INSP/MAINT 1 WP 23 302FD 1659 33200 DURING ENGINEDECK REPLACEMENT, FOUND FUSELAGE FITTING AT LEFT FORWARD ENGINE MOUNT ATTACHMENT CRACKED. CRACKS EMANATE F ROM INISDE REAR BOLT HOLE. POSSIBLE CAUSE IS HOLES NOT PROPERLY DEBURRED. SUBMITTER STATED TO PREVENT RECURRENCE, HOL ES SHOULD BE DEBURRED OR CHAMFERED ENOUGH TO REMOVE SHARP EDGES. (X) 1 G 7 2 4U H4SW 2000062100014 20000621 00014 EU 2000 6 21 20000510SH021 1 20000428 G 7930 0235237790 CHIP DETECTOR SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D NE ENGINE DEFECTIVE H O OTHER J WARNING INDICATION CR CRUISE 1 WP 13 451H 352 3231 9643 WHILE PILOT FLYING ON TOUR FLIGHT, NOTICED AN ENGINECHIP LIGHT ILLUMINATED. PILOT IMMEDIATELY MADE PRECAUTIONARY LANDIN G. INSPECTED AIRCRAFT AND FOUND THAT ENGINE CHIP PLUG HAD A DEFECT. CLEANED CHIP PLUGS AND C/W OPERATIONAL CHECK AND FUNCTIONALLY CHECKED GOOD. AIRCRAFT RETURNED TO SERVICE. (X) 1 G 7 1 3U 3 U H9EU E19EU 2000062200134 20000622 00134 SW 2000 6 22 20000510SH024 1 20000113 G 2913 MS2467813C SCREW ABEX BELL 206 206L3 1182108 SW SCREW HEAD PORT BROKEN b XJ2R O OTHER O OTHER IN INSP/MAINT 1 WP 01 41AZ 261 AU1804433 51087 P/N MS24678-13C - SCREWS FOUND WITH HEAD BROKEN OFF, LOCKWIRE STILL ATTACHED TO SCREW HEAD DURING ACFT INSP ON HYD PUMP. HYD PUMP HAS 2 SCREWS OF THIS P/N WHICH RETAIN PORT CAP AND 2 SCREWS WITH DIFFERENT P/N. THE 2 DIFFERENT P/N SCREWS W ERE THE ONLY ONES RETAINING PORT CAP ON THE PUMP, BOTH 2 EACH MS28678-13C HEADS FAILED. 2 FAILED SCREWS TESTED, SEVERE HYDROGEN EMBRITTLEMENT. HYD PUMP O/H 6-23-99, INSTALLED 8-12-99, REMOVED 12-10-99, TSO 260.7 HRS. 2 FAILED SCREWS RE PLACED AT O/H WITH NEW, TRACEABLE BY LOT 000062775 MFG 99660-1. ON SIDE OF SCREW HEAD, MFG IDENTIFIED WITH ''CBS''. HY D PUMP WITH FAILED SCREWS REPLACED WITH NEW, RETURNED TO SERVICE. FAILED SCREWS, LOT 000062775, CUSTOMERS TO BE NOTIFIE 1 G 7 1 3U H2SW 2000062200135 20000622 00135 EU 2000 6 22 20000510SH025 1 20000510 G 8010 410CC01Y1 RELAY SNIAS 350 AS350B2 8680813 EU MASTER ELEC BOX WRONG PART B K NONE O OTHER IN INSP/MAINT 1 SW 03 5204Y 464 3101 AIRCRAFT STOPPED AT REMOTE LOCATION FOR FUEL. UPON ATTEMPTING TO RE-START, WHEN STARTER BUTTON PRESSED, THE IGNITERS P OPPED, BUT THE STARTER/GENERATOR WAS DEAD. DURING T/S, DISCOVERED THE K3 START RELAY WAS THE WRONG PART NUMBER. IT IS SUPPOSED TO BE P/N 411CC01Y1. THE RELAY THAT WAS REMOVED, P/N 410CC1Y1, IS SUPPOSED TO BE USED IN THE K4 THRU K7 POSITIO NS. IN THE MASTER ELECTRICAL BOX THERE IS 1 EACH 411CC01Y1 RELAY AND 4 EACH 410CC01Y1 RELAYS ALL LOCATED TOGETHER ON T HE SAME BUSS BAR. AT INITIAL INSTALL, SUSPECT INSTALLER INADVERTENTLY INSTALLED THEM ALL THE SAME. SUBMITTER RECOMMENDS CHECKING OTHER LIKE AIRCRAFT FOR THIS DISCREPANCY, IF NO MAINTENANCE HAS BEEN PREVIOUSLY PERFORMED IN THIS AREA. (X) 1 G 7 1 3U H9EU 2000080800001 20000808 00001 NM 2000 8 8 20000510SH028 1 20000330 G 2910 F2MA751505214A2 LINE AMD FALC50 FALCON2000 2730170 NM RT PYLON LOOSE B O OTHER O OTHER NR NOT REPORTED 1 SW 09 790L 15 RIGHT ENGINE NR 2 SYSTEM HYDRAULIC PRESSURE LINE BECAME UN-SWAGED AT OUTBOARD END CAUSING COMPLETE DRAINAGE OF NR 1 HYDR AULIC SYSTEM. THIS OCCURRED IN-FLIGHT. FURTHER INVESTIGATION REVEALED IMPROPER SWAGING. TUBE WAS INSTALLED APPROXIMATE LY 1 WEEK PRIOR TO INCIDENT. (X) 2 K 7 3 4F RT A50NM 2000062300047 20000623 00047 SW 2000 6 23 20000510SH030 1 20000420 G 6300 406340102101 SEAL BELL 407 407 SW M/R DRIVE LEAKING B GS1R O OTHER O OTHER IN INSP/MAINT 1 EA 03 7ZB 159 53329 SEAL LEAKING ON FREEWHEELING UNIT OUT, BETWEEN ENGINE AND TRANSMISSION. REPLACED WITH NEW SEAL FROM BELL HELICOPTER. ( X) 1 G 7 1 3U O H2SW 2000071100001 20000711 00001 EU 2000 7 11 20000511SH001 1 20000320 G 6720 350A33214501 PITCH LINK SNIAS 350 AS350B2 8680813 EU TAIL ROTOR WORN A XSFA O OTHER O OTHER IN INSP/MAINT 1 WP 13 964SA 4858 2931 TAIL ROTOR PITCH CHANGE ROD REMOVED DUE TO WEAR ON SPHERICAL BEARING IAW AD 98-4-35. REMOVED 2 EACH. (X) 1 G 7 1 3U H9EU 2000071200107 20000712 00107 EU 2000 7 12 20000511SH004 1 20000328 G 7603 704A34130052 CONTROL CABLE SNIAS 350 AS350B2 8680813 EU FUEL CONTROL ROUGH A K NONE O OTHER IN INSP/MAINT 1 WP 13 963SA 3755 2855 FUEL CONTROL CABLE ROUGH AND DIFFICULT TO MOVE. (X) 1 G 7 1 3U H9EU 2000071100002 20000711 00002 EU 2000 7 11 20000511SH005 1 20000328 G 6230 EMRL8RSP3C ROD END SNIAS 350 AS350B2 8680813 EU MAIN ROTOR WORN A XSFA K NONE O OTHER IN INSP/MAINT 1 WP 13 963SA 3755 2855 FORE AND AFT SERVO TOP ROD ENDS AND RIGHT LATERAL SERVO LOWER ROD END HAD WORN BEARINGS. (X) 1 G 7 1 3U H9EU 2000073100005 20000731 00005 CE 2000 7 31 20000511SH006 1 20000207 G 3211 671305210 TRUNNION CESSNA 750 750 2076810 CE NLG CRACKED H K NONE O OTHER IN INSP/MAINT 1 GL 07 9090S 3234 7500009 NOSE GEAR TRUNNION MOUNT PLATES CRACKED. THIS IS THE THIRD OCCURRENCE OF THIS TYPE IN A FLEET OF APPROXIMATELY 25 AIRCR AFT. (X) 2 L 7 2 4J RT T00007WI 2000073100006 20000731 00006 CE 2000 7 31 20000511SH007 1 20000207 G 3211 671305210 TRUNNION CESSNA 750 750 2076810 CE NLG CRACKED H K NONE O OTHER IN INSP/MAINT 1 GL 07 926QS 2629 7500026 NOSE GEAR TRUNNION MOUNT PLATES CRACKED OR MISSING FASTENERS. SUBMITTER STATED THIS IS THE THIRD OCCURRENCE OF THIS TYP E IN A FLEET OF APPROXIMATELY 25 AIRCRAFT. (X) 2 L 7 2 4J RT T00007WI 2000073100007 20000731 00007 CE 2000 7 31 20000511SH008 1 20000207 G 3211 671305210 TRUNNION CESSNA 750 750 2076810 CE NLG LOOSE B K NONE O OTHER IN INSP/MAINT 1 GL 07 947QS 1700 7500047 LEFT NOSE LANDING GEAR TRUNNION LOOSE. THIS IS THE THIRD OCCURRENCE IN A FLEET OF APPROXIMATELY 25 AIRCRAFT. (X) 2 L 7 2 4J RT T00007WI 2000071100005 20000711 00005 SW 2000 7 11 20000511SH013 1 20000420 G 6510 407340339103 BEARING BELL 407 407 SW TAIL BOOM ROUGH B GS1R K NONE O OTHER IN INSP/MAINT 1 SO 19 10EW 674 53262 BEARING ON TAIL ROTOR DRIVESHAFT ON TAILBOOM REJECTED. REPLACED WITH NEW BEARINGS FROM BELL HELICOPTER. THESE WERE NOT INSTALLED ON THE OIL COOLER HANGARS. AD 2000-02-12 IS NOT APPLICABLE DUE TO INSTALLED LOCATION. (X) 1 G 7 1 3U O H2SW 2000071100006 20000711 00006 SW 2000 7 11 20000511SH014 1 20000420 G 6510 407340339103 BEARING BELL 407 407 SW TAIL BOOM ROUGH B GS1R K NONE O OTHER IN INSP/MAINT 1 SO 19 10EW 674 53262 BEARING ON TAIL ROTOR DRIVESHAFT ON TAILBOOM REJECTED. REPLACED WITH NEW BEARINGS FROM BELL HELICOPTER. THESE WERE NOT INSTALLED ON THE OIL COOLER HANGERS. AD 2000-02-12 IS NOT APPLICABLE DUE TO INSTALLED LOCATION. (X) 1 G 7 1 3U O H2SW 2000062600024 20000626 00024 EA 2000 6 26 20000511SH015 2 20000501 G 8550 LW13383 BAFFLE PIPER PA46 PA46350P SO LYC O540 TIO540AE2A 41532 EA OIL SUMP MISALIGNED B BJ3R K NONE O OTHER IN INSP/MAINT 1 WP 15 117NJ 118 4636138 RL1041561A TWO EACH AN470AD RIVET HEADS FOUND IN OIL SUCTION SCREEN. REMOVED SUMP, FOUND BAFFLE HAD 2 RIVETS WITH HEADS MISSING. FURTHER EXAMINATION SHOWED RIVET HOLES COUNTERSUNK ON THE HEAD SIDE. THIS BAFFLE WAS THE NEW STYLE WITH 5 EACH AN470-4-4 AD RIVETS ON EACH BAFFLE PIECE, NOT THE OLDER 3 RIVETS AS PICTURED IN LYC SB 489A. (X) 1 L 7 1 3O 3 O RT A25SO E14EA 2000062600025 20000626 00025 EA 2000 6 26 20000511SH016 2 20000501 G 8550 61298 GEAR PIPER PA46 PA46350P SO LYC O540 TIO540AE2A 41532 EA TEETH WORN B BJ3R K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 15 117NJ 119 4636138 RL10415612A ON REMOVAL OF OIL PUMP, WEAR WAS NOTED ON ALUMINUM GEAR TEETH FACES. IT LOOKED LIKE IMPROPER HARDENING. WEAR ALSO ON T EETH EDGES. DATE CODE: 36/99. (X) 1 L 7 1 3O 3 O RT A25SO E14EA 2000071200256 20000712 00256 NE 2000 7 12 20000511SH040 1 20000424 G 6320 643520411102 PLANETARY GEAR SKRSKY SKRSKY S64 S64F NE MAIN GEARBOX FRACTURED B JYDR K NONE O OTHER IN INSP/MAINT 1 NM 09 158AC 698 A6161 64081 1ST STAGE PLANETARY PINION GEAR, PN 6435-20411-102, SN 1477, HAVING AN UNKNOWN TT, FAILED IN MAIN GEARBOX, PN 6435-20500 -048, SN A6-161. INSP REVEALED TWO-THIRDS OF A 1ST STAGE PLANETARY PINION GEAR TOOTH FRACTURED CAUSING REPLACMENT OF TH E FOLLOWING ITEMS DUE TO SECONDARY DAMAGE: 18 EACH 2ND STAGE PLANETARY PINION GEARS, PN 6435-20057-012, RING GEAR, PN 6 435-20165-012, 1ST STAGE SUN GEAR, PN 6435-20412-102, 2ND STAGE SUN GEAR, PN 6435-20414-101, AND 6 EACH 1ST STAGE PLANET ARY PINION GEARS REPLACED. (X) 2 G 7 2 4U H6EA 2000062600027 20000626 00027 2000 6 26 20000512SH001 4 20000303 G 6113 C6178 BULKHEAD MCAULY CESSNA 414 414A 2075907 CE LEFT PROPELLER CRACKED B VA1R O OTHER O OTHER IN INSP/MAINT 1 SW 19 446W 500 891776 414A0613 BULKHEAD REPLACED IN THE FIELD AND RETURNED FOR WARRANTY CLAIM. BULKHEAD IS CRACKED FROM CENTER HOLE OUTWARD AT APPROXI MATELY 45 DEGREES FOR 4 INCHES. CRACK STARTS .5 INCH TO THE SIDE OF MOUNT HOLE FOR ATTACHMENT TO PROP HUB. BULKHEAD I S .075 INCH ALUMINUM, SINGLE LAYER SUPPORTING 18 INCHES DIAMETER SPINNER. SUBMITTER SUSPECTS BULKHEAD NEEDS DOUBLER. H AVE SEEN CRACKS ON OTHER BULKHEADS INSTALLED ON CESSNA 414A MODIFIED PER STC SA7633SW. (X) 1 L 7 2 3O A7CE 2000062600028 20000626 00028 NE 2000 6 26 20000512SH002 3 20000310 G 6114 660714259 HUB ROTOL ROTOL R390 R3904123F27 NE REAR HALF INSERT CRACKED B MS1R K NONE O OTHER IN INSP/MAINT 1 EA 27 14655 7448 DRG400690 PROPELLER RECEIVED FOR ROUTINE OVERHAUL. DURING NDT INSPECTION, A CRACK WAS FOUND AT NR 1 MOUNTING INSERT IN HUB REAR H ALF. APPROXIMATELY 1.5 INCH LONG HUB ASSY REJECTED FROM FURTHER SERVICE. (X) 6 C P31NE 2000121500001 20001215 00001 CE 2000 12 15 20000512SH019 1 20000323 G 5751 NOSE RIB CESSNA CESSNA 206 T206H CE BEND RELIEF HOLE CRACKED B LN3R K NONE O OTHER IN INSP/MAINT 1 WP 07 2371H 100 T20608060 DURING ACFT''S FIRST 100-HR INSP, A .25 INCH LONG CRACK WAS FOUND IN A NOSE RIB OF THE LT AILERON. NOSE RIB IS AT THE AILERON''S CUT-OUT IN THE LEADING EDGE FOR THE INBD HINGE ATTACH POINT, ON THE OTBD SIDE. THE CRACK IS AT THE UPPER FWD CORNER OF THE NOSE RIB, AT A RELIEF RADIUS FOR THE BEND OF THE ATTACH FLANGES. THE CRACK IS AT THE UPPER FWD CORNER OF THE NOSE RIB, AT A RELIEF RADIUS FOR THE BEND OF THE ATTACH FLANGES. THE CRACK IS BEST VIEWED THROUGH THE EXISTING .75 INCH ACCESS HOLE IN AILERON''S BOTTOM SKIN. INSP, REVEALED ANOTHER CRACK IN THE RT AILERON, SAME LOCATION: INBD HINGE POINT, OTBD NOSE RIB. BOTH AILERONS RETURNED TO CESSNA. TWO NEW AILERONS WERE INSTALLED. CAUSE OF CRACKS UNKNOWN. ( 1 H 7 1 3O A4CE 2000121500002 20001215 00002 CE 2000 12 15 20000512SH020 1 20000323 G 5751 NOSE RIB CESSNA CESSNA 206 T206H CE BEND RELIEF HOLE CRACKED B LN3R K NONE O OTHER IN INSP/MAINT 1 WP 07 2371H 100 T20608060 DURING ACFT''S FIRST 100-HR INSP, A .25 INCH LONG CRACK WAS FOUND IN A NOSE RIB OF THE LT AILERON. NOSE RIB IS AT THE AILERON''S CUT-OUT IN THE LEADING EDGE FOR THE INBD HINGE ATTACH POINT, ON THE OTBD SIDE. THE CRACK IS AT THE UPPER FWD CORNER OF THE NOSE RIB, AT A RELIEF RADIUS FOR THE BEND OF THE ATTACH FLANGES. THE CRACK IS AT THE UPPER FWD CORNER OF THE NOSE RIB, AT A RELIEF RADIUS FOR THE BEND OF THE ATTACH FLANGES. THE CRACK IS BEST VIEWED THROUGH THE EXISTING .75 INCH ACCESS HOLE IN AILERON''S BOTTOM SKIN. INSP, REVEALED ANOTHER CRACK IN THE RT AILERON, SAME LOCATION: INBD HINGE POINT, OTBD NOSE RIB. BOTH AILERONS RETURNED TO CESSNA. TWO NEW AILERONS WERE INSTALLED. CAUSE OF CRACKS UNKNOWN. (X 1 H 7 1 3O A4CE 2000121500003 20001215 00003 SO 2000 12 15 20000512SH021 1 20000101 G 2721 D1 CONTROL CABLE MAULE M7 M7235B 5460109 SO NR 57 FRAYED B K NONE O OTHER IN INSP/MAINT 1 AL 03 1002H 518 23038C BOTH RUDDER TRIM CABLES FRAYED AT RUDDER AS IT COMES OUT OF FLEX HOUSING. (X) 1 H 7 1 3O NC 3A23 2000121500004 20001215 00004 SO 2000 12 15 20000512SH022 1 20000414 G 2720 D7 CONTROL CABLE MAULE M7 M7235B 5460109 SO NR 29 FRAYED B K NONE O OTHER IN INSP/MAINT 1 AL 03 1002H 518 23038C RIGHT RUDDER CABLE FRAYED AT PULLEY AT AFT END OF BAGGAGE COMPARTMENT. (X) 1 H 7 1 3O NC 3A23 2001012900148 20010129 00148 NE 2001 1 29 20000512SH023 2 20000413 G 7230 2A0851 SEAL IAE V2500 V2500A1 NE ENGINE CRACKED B KB1R K NONE O OTHER IN INSP/MAINT 1 NE 03 PART RECEIVED FROM WESTFIELD GAGE CO., FOR FLUORESCENT PENETRANT INSPECTION IAW IAE V2500 PROPULSION SYS ENG MANUAL, REV 42, SECTION 70-23-01, INSPECTION CHECK-01, TASK 70-23-01-230-501. PART REJECTED AT F.P.I. DUE TO A CRACK ONE PLACE ON TOP SURFACE, 0.200 INCH LONG. PARK SENT BACK TO WESTFIELD GAGE WITH REJECT TAG ATTACHED TO IT. (X) 4 F E311NE 2001011100926 20010111 00926 EU 2001 1 11 20000515SH001 1 20000301 G 6720 AC66375 HOUSING DUNLOP SNIAS 350 AS350B2 8680813 EU SERVO ACTUATOR UNDERSIZE H K NONE O OTHER IN INSP/MAINT 1 NM 11 BX109 CRACK DETECTED ON LOWER END OF BODY AT PLUGGED PORT HOLE. UNIT NOT ASSIGNED TO ANY AIRCRAFT, VENDOR SURPLUS/EXCHANGE UN IT. POSSIBLE CAUSE: PLUG BORE UNDERSIZED TOO MUCH. CRACK OCCURRING IN PLUGGED AREA. RECURRENCE PREVENTION RECOMMENDA TION: WIDEN PLUG BORE. (X) 1 G 7 1 3U H9EU 2001012900149 20010129 00149 NE 2001 1 29 20000515SH004 3 20000412 G 6114 60714255 HUB ROTOL R390 R3904123F27 NE HUB ASSY CRACKED B MS1R K NONE O OTHER IN INSP/MAINT 1 EA 27 6856 DAP01013 HUB ASSEMBLY RECEIVED FOR ROUTINE OVERHAUL. DURING INSPECTION, A CRACK WAS FOUND AT NR 1 BLADE PORT IN INNER SEAL LIP A T HUB SPLIT LINE (BOTH HUB HALVES). HUB REJECTED FROM SERVICE. (X) 6 C P31NE 2000051800067 20000518 00067 NE 2000 5 18 20000515SH005 3 20000417 G 6111 6607132886 BLADE PROPELLER ROTOL R389 R3894123F25 NE PROPELLER CRACKED B MS1R K NONE O OTHER IN INSP/MAINT 1 EA 27 19014 5017 BLADE RECEIVED FROM CUSTOMER WITH A CRACK AROUND BLADE ROOT OUTER SLEEVE. BLADE REJECTED FROM FURTHER SERVICE. (X) 6 C P30NE 2000051600129 20000516 00129 SW 2000 5 16 20000515SH006 1 20000420 G 2435 230650001 BEARING GULSTM 690TP 690 0141720 SW STARTER/GEN DESTROYED B IC2R K NONE O OTHER IN INSP/MAINT 1 SW 15 UNIT RECEIVED FROM DTA FOR EVALUATION. INSP DETERMINED UNIT DESTROYED FROM FAILURE OF DRIVE END BEARING. BEARINGS WERE OF LUCAS P/N. SHAFT SHEARED, ARMATURE DESTROYED FROM DRAGGING ON FIELD POLE SHOES. FIELD DRUG OUT, DRIVE END BELL DES TROYED. UNIT HAD OVERHAUL TAG FROM AMR-COMBS. NO TT OF TIME SOH DETERMINED. BEARING MFG THOUGHT TO BE 1997. IMPOSSIB LE TO DETERMINE BALANCE CONDITION OF ARMATURE. RECOMMEND WORK ORDER INFO BE SOUGHT ON BALANCE RECORD OF ARMATURE AT O/H . SUBMITTER STATED BEARINGS DO NOT FAIL UNLESS OUT OF BALANCE CAUSES EXCESSIVE RADIAL LOAD TO BE IMPOSED. 1 H 7 2 3T 2A4 2000051600130 20000516 00130 EA 2000 5 16 20000515SH007 2 20000515 G 7322 30800 FLOAT PRECISION HA6 LYC O360 O360F1A6 41514 EA CARBURETOR DAMAGED B K NONE O OTHER IN INSP/MAINT 1 SO 09 75062805 100CC FUEL LEAKED INTO THE CHAMBER CLOSEST TO THE FULCRUM OF THE FLOAT ASSEMBLY DUE TO THE COMPROMISED INTEGRITY OF THE PLASTIC WELDED SEAM. (X) 3 O E286 2000051600131 20000516 00131 EA 2000 5 16 20000515SH008 2 20000425 G 8530 LW14995 SPRING LYC O540 O540* 41532 EA PUSH ROD BROKEN H K NONE O OTHER IN INSP/MAINT 1 WP 23 280 PUSH ROD RETAINER SPRING, PN LW-14995, BROKEN. PART INSTALLED FROM KIT MFG AFTER DATES LISTED IN LYC SB 519. (X) 3 O E295 2001012900150 20010129 00150 SO 2001 1 29 20000515SH009 2 20000420 G 8540 654720 GEAR CONT O360 TSIO360EB 17025 SO OIL PUMP MISMANUFACTURED D K NONE O OTHER IN INSP/MAINT 1 NE 03 NEW OIL PUMP DRIVEN GEAR DOES NOT HAVE THE CHAMFER ON THE INSIDE OF THE TWO DRIVE SLOTS. THIS IS A MFG''S DEFECT. WHEN T HE DRIVE IMPELLER NR 653814 IS INSTALLED, AND TACH NUT TORQUED, THE NR 654720 GEAR BOTTOMS ON THE 2 RADIUSES OF THE DRIV E DOGS THAT ENGAGE THE SHOTS. A .0015 INCH FEELER GAUGE CAN BE INSERTED UNDER THE GEAR SHAFT WHEN ASSEMBLED. THIS CAUS ES STRESS ON THE RADIUSES OF THE NR 653814 IMPELLERS AND CAN CAUSE A FAILURE OF THE OIL PUMP SYSTEM IF IT WEARS OR CRACK S IN THAT AREA BECAUSE THE TACH NUT WILL LOOSE ITS TORQUE AND THE WHOLE OIL PUMP DRIVE SYSTEM WILL LOOSEN. REF: TCM SB 96-4. (X) 3 O E9CE 2001012900018 20010129 00018 NE 2001 1 29 20000515SH010 2 20000515 G 7230 1B7306 BLADE PWA PWA 2037 PW2037 NE COMPRESSOR SECT FRACTURED B WA2D K NONE O OTHER IN INSP/MAINT 1 NE 03 B27203 P727203 DISASSEMBLY INSPECTION REVEALED ONE EACH 6TH STAGE COMPRESSOR BLADE PN IB7306 HAD FRACTURED AT THE BLADE ROOT. THE FAIL ED BLADE HAS BEEN FORWARDED TO PRATT & WHITNEY EAST HARTFORD CT (T.C. HOLDER) FOR INVESTIGATION. (CUSTOMER: TRANS WORL D AIRLINES, TWAA). (X) 4 F E17NE 2001012900019 20010129 00019 CE 2001 1 29 20000515SH011 1 20000515 G 7921 SA625303 GASKET CESSNA 182 182P 2075816 CE CONT O470 O470S 17026 SO OIL COOLER DAMAGED D A UNSCHED LANDING K FLUID LOSS CR CRUISE 1 WP 01 1197M 19 18264241 269041R DURING CRUISE, THE PILOT OBSERVED OIL COMING UP THE WINDSHIELD AND BOTH SIDE WINDOWS. HE DECLARED AN EMERGENCY AND MADE A SAFE AIRPORT LANDING. THE ENGINE HAD APPROXIMATELY 3 QUARTS OF OIL REMAINING. THE OIL LEAK WAS CAUSED BY A SPLIT IN P/N 5A625303 GASKET BETWEEN THE CASE AND P/N 625016 OIL COOLER ADAPTER PLATE. THE GASKET MATERIAL USED BY SUPERIOR AIR PARTS APPEARS TO BE TOO SOFT AS COMPARED TO THE OEM 625303 GASKET AND SHOULD BE REPLACED. (X) 1 H 7 1 3O 3 O NT TA13 E273 2000051600142 20000516 00142 CE 2000 5 16 20000515SH013 1 20000407 G 5320 085112132 BEAM CESSNA 340 340A 2076405 CE CONT O520 TSIO520NB 17040 SO ENGINE CORRODED B BXSR K NONE O OTHER IN INSP/MAINT 1 EA 09 269PC 3679 340A0785 ENGINE BEAM FOUND EXFOLIATED/CRACKED ON THE TOP OUTBOARD ANGLE, JUST FORWARD AND INBOARD OF THE TAILPIPE. AD 2000-01-16 PAR(D) HAD BEEN C/W 64 HOURS AND 10 WEEKS PREVIOUSLY. (X) 1 L 7 2 3O 3 O 3A25 E8CE 2000051600224 20000516 00224 CE 2000 5 16 20000515SH014 1 20000414 G 5751 50210025 BRACKET CESSNA 340 340A 2076405 CE RT AILERON SHEARED B BXSR K NONE O OTHER IN INSP/MAINT 1 EA 09 269PC 340A0785 FOUND 2 OF 6 RIVETS THAT HOLD THE OUTBOARD AILERON HINGE TO THE WING SPAR SHEARED OFF. (X) 1 L 7 2 3O 3A25 2000051600146 20000516 00146 CE 2000 5 16 20000515SH018 1 20000515 G 3230 HMXL6FG ROD END RAYTHN BEECH 33 35C33A 1151410 CE AUTO RETRACT BROKEN G O OTHER O OTHER NR NOT REPORTED 1 GL 25 7694 CE71 FROM THE PILOT IN COMMAND. UPON RETURNING TO AKR FOR LANDING, WHEN THE LANDING GEAR WAS EXTENDED, HEARD A LOUD BANG AND FELT A SENSATION IN THE FLOORBOARDS. SUBSEQUENTLY, THERE WAS NO NOSE GEAR EXTENDED INDICATION. AIRCRAFT RECEIVED MINO R DAMAGE UPON LANDING WHEN THE NOSE GEAR COLLAPSED. MAINTENANCE FOUND THE ROD END OF THE NOSE GEAR RETRACT ROD AT THE A CTUATOR ARM BROKEN IN THE THREADED AREA OF THE TORN RUT. (X) 1 L 7 1 3O 3A15 2000051600147 20000516 00147 SO 2000 5 16 20000515SH019 1 20000405 G 7603 487925 SWITCH PIPER PA44 PA44180 7104402 SO THROTTLE BROKEN D O OTHER O OTHER NR NOT REPORTED 1 WP 07 3048R 6562 447995242 THE LOW POWER GEAR UP WARNING SWITCH ON THE THROTTLE QUADRANT WAS FOUND BROKEN INTERNALLY. WHEN THE THROTTLES WERE ADV ANCED THE SWITCH WOULD OPEN AND SHORT TO GROUND CAUSING THE LANDING GEAR CONTROL CIRCUIT BREAKER TO OPEN. WHEN THE THRO TTLES WERE PULLED BACK TO THE STOP, THE SWITCH WOULD CLOSE AND THE LANDING GEAR SYSTEM WOULD FUNCTION NORMALLY. SUBMITT ER STATED THE AGE OF THE SWITCH, NUMBER OF CYCLES, IS POSSIBLY THE CAUSE OF FAILURE. (X) 1 L 7 2 3O A19S0 2000051600148 20000516 00148 EA 2000 5 16 20000515SH020 2 20000320 G 7322 A105219 FLOAT HA6 AMRGEN AA5 AA5B 3960105 SO LYC O360 O360A4K 41514 EA CARBURETOR DAMAGED B HO1R O OTHER O OTHER NR NOT REPORTED 1 EA 21 4553C 225 AA5B1202 12504236A ENGINE WOULD NOT RUN UNLESS MIXTURE WAS LEANED ALMOST TO IDLE CUT OFF. IT WAS VERY RICH AND WOULD NOT RUN ABOVE 1,500 RPM. FOUND PLASTIC FLOAT TO BE FILLED WITH AVGAS TWO OF THREE CHAMBERS. FLOAT, P/N 30-800, CARBURETOR ASSY DATE, 9-97. (X) 1 L 7 1 3O 3 O A16EA E286 2000051600035 20000516 00035 SO 2000 5 16 20000515SH021 1 20000310 G 3250 63300008 HORN PIPER PA28 PA28140 7102802 SO LYC O320 O320E3D 41508 EA NLG STEERING BROKEN C O OTHER O OTHER LD LANDING 1 SW 99 7615F 5644 287725090 L4656327A WHILE LANDING, EXPERIENCED EXTREME SHIMMY IN NOSE GEAR. NOSE GEAR STEERING HORN, PN 63300-008, FOUND BROKEN AT WELD. P ART TT: 5,633.43 HRS. (X) 1 L 7 1 3O 3 O 2A13 E274 2000051600149 20000516 00149 SO 2000 5 16 20000515SH022 1 20000308 G 2731 CONTROL CABLE PIPER PA34 PA34200T 7103406 SO ELEVATOR TRIM BROKEN A K NONE O OTHER IN INSP/MAINT 1 AL 05 7333L 700 347670099 CABLE BROKE UPON REMOVAL OF ELEVATOR FOR REPAIR. (X) 1 L 7 2 3O A7SO 2000051600150 20000516 00150 CE 2000 5 16 20000515SH023 1 20000423 G 5753 FLAP TRACK CESSNA 182 R182 2072734 CE RT TE FLAP SEPARATED H K NONE O OTHER IN INSP/MAINT 1 WP 03 736WX 5325 R18200783 FOUND RT INBD FLAP TRACK SEPARATED FROM FWD MOUNT POINT DUE TO SHEARED RIVET. RIVET MAY HAVE BECOME WORK HARDENED. LT INBD FLAP TRACK ALSO FOUND LOOSE AT SAME LOCATION. THIS COULD POSSIBLY APPLY TO ALL CESSNA 182''S. THERE WERE NO OCCUR RENCES OF FLAP OVERSPEEDING THAT ARE KNOWN. THIS COULD BE THE RESULT OF NORMAL WEAR AND TEAR UNDER NORMAL OPERATIONS. SUBMITTER SUGGESTED ADDING A CHECK FOR FLAP TRACK SECURITY ON PRE-FLIGHT FOR CESSNA 182''S. (X) 1 H 7 1 3O RT 3A13 2000051600151 20000516 00151 SO 2000 5 16 20000515SH024 1 20000218 G 5711 SPAR PIPER PA30 PA39 7103902 SO RT WING CRACKED D O OTHER E VIBRATION/BUFFET NR NOT REPORTED 1 GL 13 8898Y 3376 3933 PILOT REPORTED VIBRATION FELT IN THE ACFT AND RT WING TIP TANK TRAILING END COULD BE SEEN ''FLUTTERING'' APPROX 1 INCH I N-FLIGHT. INSP FOUND A CRACK EXTENDING THROUGH THE LOWER SPAR CAP AND UP APPROX 1 INCH INTO FACE OF THE AFT WING SPAR A T STA 132. SEVERAL SOLID RIVETS ATTACHING UPPER WING SKIN TO THE AFT SPAR AND SOLID RIVETS ATTACHING THE UPPER WING SKI N TO AFT SPAR AND RIB AROUND STA 132 HAD BEEN REPLACED BY ''CHERRY TYPE'' RIVETS AT ONE TIME INDICATING THERE MAY HAVE B EEN PROBLEMS IN THAT AREA BEFORE. ALSO, RT MAIN GEAR REPLACED AND AFT TAIL BULKHEAD REPAIRED DUE TO A HARD LANDING 10-9 8. REPAIRS TO DAMAGED WING SPAR WERE MADE USING DER APPROVED DATA. 1 L 7 2 3O A1EA 2000051600152 20000516 00152 2000 5 16 20000515SH025 4 20000426 G 2562 ELT1104 ELT PIPER PA32 PA32301T 7103209 SO TAIL DAMAGED D K NONE L NO TEST IN INSP/MAINT 1 WP 15 9288X 475 3257027 REMOVED ELT UNIT FOR FAR 91-207 CHECK. ACTIVATED. WOULD NOT TURN OFF. REMOVED BATTERY, VERY WET. CHECKED TRANSMITTER , WET. SENT TO FACTORY FOR OVERHAUL. (X) 1 L 7 1 3O A3SO 2001012900020 20010129 00020 WP 2001 1 29 20000515SH026 2 20000426 G 7230 30752272 DISK GARRTT TFE731 TFE731* 01518 WP FIRTREE DAMAGED H K NONE O OTHER IN INSP/MAINT 1 SW 99 NEW PART RECEIVED WITH DAMAGE IN POST FIRTREE AREA AND NUMEROUS MANUFACTURING FLAWS IN POST FIRTREE AREA. RE: LOT NR 00P102. (X) 4 F E6WE 2001012900021 20010129 00021 WP 2001 1 29 20000515SH027 2 20000515 G 7230 30752272 WEB GARRTT TFE731 TFE731* 01518 WP HPT DISK SCRATCHED H K NONE O OTHER IN INSP/MAINT 1 GL 19 NEW PART RECEIVED WITH A SCRATCH IN THE WEB AREA ON THE AFT SIDE. RE: LOT NR 00P098. (X) 4 F E6WE 2001012900022 20010129 00022 WP 2001 1 29 20000515SH028 2 20000503 G 7230 31014051 BEARING GARRTT TPE331 TPE3316 01514 WP GEARBOX FAILED H K NONE O OTHER NR NOT REPORTED 1 GL 19 6118 15 P20246 P20246 COMPRESSOR BEARING FAILED 14.7 HOURS AFTER OVERHAUL CAUSING MAJOR FAILURE DAMAGE TO ENGINE. (X) 4 T E4WE 2001012900023 20010129 00023 WP 2001 1 29 20000515SH029 1 20000427 G 3242 1542522 BRAKE ASSY DOUG DC8 DC8* WP MLG OVERHEATED H K NONE O OTHER IN INSP/MAINT 1 SO 19 TEAR DOWN INSPECTION SHOWS ASSY B.E.R., NO SALVAGEABLE PARTS. OVERHEATED BRAKES. (X) 2 L 7 4 4J F 4A25 2001012900024 20010129 00024 WP 2001 1 29 20000515SH030 1 20000427 G 3242 1542522 BRAKE ASSY DOUG DC8 DC8* WP MLG OVERHEATED H K NONE O OTHER IN INSP/MAINT 1 SO 19 TEAR DOWN INSPECTION SHOWS ASSY B.E.R. NO SALVAGEABLE PARTS. OVERHEATED BRAKES. (X) 2 L 7 4 4J F 4A25 2001012900025 20010129 00025 WP 2001 1 29 20000515SH031 1 20000427 G 3242 1542522 BRAKE ASSY DOUG DC8 DC8* WP MLG OVERHEATED H K NONE O OTHER IN INSP/MAINT 1 SO 19 TEAR DOWN INSPECTION SHOWS ASSY B.E.R. NO SALVAGEABLE PARTS. OVERHEATED BRAKE. (X) 2 L 7 4 4J F 4A25 2001012900026 20010129 00026 WP 2001 1 29 20000515SH032 1 20000503 G 3246 152059 WHEEL BENDIX DOUG DC8 DC8* WP MLG UNSERVICEABLE B K NONE O OTHER NR NOT REPORTED 1 SO 19 B7153 ****NO TEXT**** ***I''''M DOING TEXT****INBOARD HALF OF MAIN WHEEL ASSY AT SPOKE AREA UNSERVICEABLE. OUTBOARD HALF OF MAIN WHEEL ASSY, SN B6029. (X) 2 L 7 4 4J F 4A25 2000080300003 20000803 00003 EU 2000 8 3 20000515SH033 1 20000424 G 5350 355A5805420414 COWLING AEROSP AS355 AS355F2 8680812 EU MAIN GEARBOX DEPARTED C N38A K NONE D INFLIGHT SEPARATION CR CRUISE 1 EA 05 596SJ 3381 5135 RIGHT HAND MAIN GEARBOX COWLING CAME OFF OF AIRCRAFT DURING FLIGHT. NO DAMAGE TO AIRCRAFT OTHER THAN MGB COWL ITSELF. NO PERSONAL OR PROPERY DAMAGE OCCURRED. (X) 1 G 7 2 3U H11EU 2000051600306 20000516 00306 SW 2000 5 16 20000516SH001 1 20000421 G 5751 2250000364 CHANNEL GULSTM 690TP 690B 7630516 SW AILERON CRACKED D K NONE O OTHER IN INSP/MAINT 1 GL 19 81703 4616 11438 AFTER REMOVAL OF BOTH RT AND LT AILERON INBOARD HINGE ASSEMBLIES, FOUND BOTH AILERON ''U'' CHANNELS HAD CRACKS IN THE WE B AROUND THE LOWER HINGE ATTACH BOLTS. SUBMITTER RECOMMENDED INSTALLING A REINFORCING PLATE ON AFT SIDE OF WEB IAW AC 4 3.131B PAR 4-58, 4-59. (X) 1 H 7 2 3T 2A4 2000051600307 20000516 00307 SW 2000 5 16 20000516SH002 1 20000421 G 5751 250000373 CHANNEL GULSTM 690TP 690B 7630516 SW AILERON CRACKED D K NONE O OTHER IN INSP/MAINT 1 GL 19 81703 4616 11438 AFTER REMOVAL OF BOTH RT AND LT AILERON INBOARD HINGE ASSEMBLIES, FOUND BOTH AILERON ''U'' CHANNELS HAD CRACKS IN THE WE B AROUND THE LOWER HINGE ATTACH BOLTS. SUBMITTER RECOMMENDED INSTALLING A REINFORCING PLATE ON AFT SIDE OF WEB IAW AC 4 3.131B PAR 4-58, 4-59. (X) 1 H 7 2 3T 2A4 2000102500001 20001025 00001 EA 2000 10 25 20000516SH003 2 20000302 G 8530 05K21123 PLUG CESSNA 150 152 2071835 CE LYC O235 O235H2C 41505 EA CYL INSIDE WALLS MAKING METAL B WIWR K NONE O OTHER IN INSP/MAINT 1 WP 07 95512 15285911 RL897015 WHILE PERFORMING ANNUAL INSP, ALUMINUM SHAVINGS FOUND IN OIL FILTER. FILTER WAS SENT TO LYC FOR ANALYSIS AND DETERMINE D TO BE PISTON PIN PLUG MATERIALS. UPON REMOVAL OF ALL 4 CYL, SEVERE PITTING FOUND AT BOTTOM OF EACH CYL WHICH AT POINT WHERE PISTON REACHES ITS LOWEST TRAVEL. ALL 4 CYL REJECTED AND FACTORY NEW INSTALLED. FACTORY STATES THIS IS A RESULT OF ENG NOT REACHING PROPER OPERATING TEMP. ACFT IS OPERTED IN PHOENIX, AZ, OIL TEMP GAUGE IS ACCURATE. ACFT HAS HISTO RY AS DO ALL ACFT IN PHX OF RUNNING ABOVE 180 DEGREES WHICH IS THE PROPER (MIN) OIL TEMP FOR OPERATION. (X) 1 H 7 1 3O 3 O NT 3A19 E223 2000102500002 20001025 00002 EA 2000 10 25 20000516SH004 2 20000302 G 8530 05K21123 PISTON CESSNA 150 152 2071835 CE LYC O235 O235N2C 41505 EA CYLINDER WALLS MAKING METAL C WIWR K NONE O OTHER IN INSP/MAINT 1 WP 07 757NZ 15279885 L2507515 WHILE PERFORMING ANNUAL INSP, SMALL ALUMINUM PARTICLES FOUND IN OIL FILTER. BORESCOPE INSP REVEALED WEAR ON CYL WALLS AN D PITTING AT BASE OF EACH CYL (INSIDE) AT THE POINT OF THE PISTONS FARTHEST TRAVEL DOWNWARD. TWO OF THE CYL WERE FACTOR Y NEW WITH 618 HRS SINCE NEW. THE OTHER TWO REPAIRED 1,176.76 HRS AGO AT FACTORY'S REQUEST BY FACTORY APPOINTED REPAIR FACILITY UNDER WARRANTY. THIS IS 3RD OCCURRENCE OF THIS PROBLEM IN 1,859.5 HRS SMOH BY LYC. 1ST OCCURRENCE RESULTED IN ALL OF THE ABOVE AND BELOW ACCEPTABLE COMPRESSIONS ON ALL 4 CYL. FACTORY STATED ENGINE IS RUNNING TOO COLD IN PHX, AZ. (X) 1 H 7 1 3O 3 O NT 3A19 E223 2000102500003 20001025 00003 EA 2000 10 25 20000516SH005 2 20000322 G 8530 LW11633 CYLINDER LYC CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA CYLINDER WALLS MAKING METAL B WIWR K NONE O OTHER IN INSP/MAINT 1 WP 07 69186 460 15282536 L2389615 DURING 100-HR INSP, ALUMINIM SHAVING FOUND IN OIL FILTER. (THIS IS THE 4TH TIME THIS SHOP HAS HAD THIS PROBLEM IN LAST 18-24 MOS). ALUM IS FROM PISTON PIN PLUGS RUBBING AGAINST LOWER PART OF CYL WHICH, AFTER 4-500 HRS, DEVELOPS SEVERE PI TTING THEN CREATES A WEAR STEP IN CYL WALLS. ONE ENG LOST COMPRESSION IN ALL 4 CYL BELOW ACCCEPTABLE LIMITS. SUBMITTER STATED MECH SHOULD BORESCOPE ALL O-235-L2C ENGINES AT EACH 50-HR AND ORDER REPLACEMENT CYL AT FIRST SIGNS OF PITTING AT LOWEST POINT OF CYL WALL WITH THE PISTON AT B.O.C. CYL NEED TO BE REPLACED AT FIRST SIGN OF METAL CONTAMINATION, WHICH WILL OCCUR VERY RAPIDLY. ONE 50-HR THERE WILL BE NO METAL, THE NEXT THERE WILL BE SIGNIFICANT CONTAMINATION. (X) 1 H 7 1 3O 3 O NT 3A19 E223 2000102500004 20001025 00004 NM 2000 10 25 20000516SH006 1 20000427 G 5551 BRACKET UNIVAR 108 108 9230402 NM HORIZ STABILIZER CRACKED B AW4R K NONE O OTHER IN INSP/MAINT 1 WP 11 97142 108142 DURING ANNUAL INSPECTION, FOUND RT FORWARD HORIZONTAL STABILIZER ATTACH BRACKET CRACKED. CRACK APPROXIMATELY .3750 INCH LONG. CRACK EXTENDED THROUGH UPPER ATTACH POINT BOLT HOLE. (X) 1 H 7 1 3O A767 2000102500005 20001025 00005 CE 2000 10 25 20000516SH009 1 20000428 G 6120 WIRE BEECH 90 F90 1152909 CE WS 39.7 WING CTR CHAFED D K NONE O OTHER IN INSP/MAINT 1 NE 01 152WE 5025 LA152 SEVERAL WIRES IN A WIRE BUNDLE WERE FOUND CHAFED THROUGH TO GROUND ON A LEADING EDGE RIB. WIRES GOING TO INTERMITTENT GROUND INCLUDE RT AUTOFEATHER WIRE, ELECTRIC HEAT WIRE, BATTERY CHARGE SHUNT-TO-MODULE WIRES. BUNDLE WAS INSULATED AND SECURED AWAY FROM RIB AFTER REPAIR OF WIRING. FOUND DURING MFG'S PHASE-4 INSPECTION. (X) 1 L 7 2 4T A31CE 2001020500042 20010205 00042 SW 2001 2 5 20000516SH010 1 20000501 G 3220 041200002L BUCKLE MOONEY M20 M20F 5870214 SW LYC O360 O360A1A 41514 EA NLG DAMAGED H K NONE O OTHER IN INSP/MAINT 1 CE 07 7191V 221189 1333451A NOSE GEAR BUCKLE OFF AT UPPER TRUSS. POSSIBLY WEAKENED BY OVERTURNING WITH TOW TRACTOR. SUBMITTER SUGGESTED HEAVIER ME TAL, BETTER SUPERVISION AND TRAINING. (X) 1 L 7 1 3O 3 O 2A3 E286 2000122000001 20001220 00001 EA 2000 12 20 20000516SH011 2 20000419 G 8530 74230 GUIDE CESSNA 182 182S 2072701 CE LYC O540 IO540AB1A5 EA NR5, 1,6 & 4 CYL FAILED B WXHR K NONE O OTHER IN INSP/MAINT 1 NM 01 7267H 351 18280591 L2695148A EXHAUST VALVE STUCK, BENDING PUSH ROD AND HOUSING. SEE LYC SI 1425H, 1485. SB388B. FOUND 3 OTHER CYLINDERS WITH STUC K VALVES. SUBMITTER SUGGESTED AD BE ISSUED. (X) 1 H 7 1 3O 3 O NT 3A13 1E4 2000051600353 20000516 00353 CE 2000 5 16 20000516SH013 1 20000428 G 3210 MC815AS1 RELAY BEECH 200 200BEECH 1152920 CE MLG INOPERATIVE B CTUA O OTHER J WARNING INDICATION NR NOT REPORTED 1 GL 21 553R 2082 BB589 PILOT SELECTED GEAR DOWN, NO RESPONSE. PERFORMED MANUAL GEAR EXTENSION AND LANDED AIRCRAFT. TROUBLESHOT GEAR DOWN CIRC UIT, FOUND ATTACHING SCREENS FOR GEAR DOWN RELAY IN LANDING. GEAR CONTROL BOX HAD COME LOOSE. RE-SECURED RELAY AND PE RFORMED GEAR RETRACTION, CHECK OK. GEAR MOTOR CONTROL BOX WAS REPLACED 12-7-93, ACFT TT: 6,446.4 HRS WITH OVERHAULED U NIT. (X) 1 L 7 2 4T A24CE 2001020500043 20010205 00043 SO 2001 2 5 20000516SH015 2 20000427 G 8520 6461401 STUD CESSNA 210 T210M 2073451 CE CONT O520 TSIO520R 17040 SO CYLINDER BROKEN D K NONE O OTHER IN INSP/MAINT 1 SW 01 730P 894 21062910 512874 BOTH FORWARD AND AFT STUDS BROKEN HALF WAY OUT THROUGH .4375 INCH - 20 INCH THREADS. (X) 1 H 7 1 3O 3 O 3A21 E8CE 2000121500007 20001215 00007 EA 2000 12 15 20000516SH016 2 20000420 G 7414 10163048 BUSHING BENDIX LYC O360 O360A1G 41514 EA DRIVE END OVERSIZED B K NONE O OTHER IN INSP/MAINT 1 GL 03 9125334 A MAGNETO NEWLY OVERHAULED, WOULD NOT SEAT ON THE ENGINE. FOUND THE BUSHING WHICH CAME INSTALLED ON THE MAGNETO WAS TOO LARGE IN DIAMETER TO CENTER THE BORE OF THE DRIVE GEAR. COMPARED TO ANOTHER BUSHING .827 INCH, IT WAS .829 INCH. THE LYC TABLE OF LIMITS SPECIFIES .0015 INCH - .0035 INCH LOOSE FIT. SUBMITTER STATED USE OF THESE BUSHINGS AND THE RESULTI NG IMPROPER FIT COULD RESULT IN MAGNETO MALFUNCTION. (X) 3 O E286 2000080300004 20000803 00004 SW 2000 8 3 20000516SH022 1 20000131 G 6320 406040021101 BEVEL GEAR BELL BELL 206 206L4 1182110 SW TRANSMISSION CRACKED B GJQR O OTHER J WARNING INDICATION CR CRUISE 1 NM 01 404W 3185 A199 52055 TRANSMISSION LOWER CHIP LIGHT ILLUMINATED IN-FLIGHT. AFTER LANDING, INSPECTION FOUND FAIRLY LARGE FERROUS CHIP THAT AP PEARED LIKE PIECE OF GEAR TOOTH. TEAR-DOWN INSPECTION REVEALED INPUT SPIRAL BEVEL GEAR CRACKED 360 DEGREES THROUGH THE RING. THE CRACK PATH TRAVELED THROUGH A BOLT HOLE. RING GEAR REPLACEMENT IN PROGRESS AND CRACKED RING GEAR SENT TO BEL L HELICOPTER PRODUCT SUPPORT ENG FOR EVALUATION AND ANALYSIS. (X) 1 G 7 1 3U NC H2SW 2001013000001 20010130 00001 SO 2001 1 30 20000516SH029 1 20000413 G 5730 6531904 SKIN PIPER PA28 PA28161 7102803 SO LT AND RT WING CORRODED B AHRR K NONE O OTHER IN INSP/MAINT 1 GL 11 9258 CRACKS WERE FOUND USING DYE PENETRANT METHOD, ALL OF THE ABOVE AIRCRAFT WERE DURING ROUTINE MAINTENANCE TO REPAIR FUEL L EAK FROM OVERWING FAIRING ASSY, REMOVED LEFT OVERWING FAIRING AND DISCOVERED EXTREME CASE OF EXFOLIATION CORROSION THAT CAUSED A HOLE THROUGH UPPER WING SKIN. AFTER FINDING CORROSION ON LEFT SIDE, DECIDED TO PULL OFF RIGHT OVERWING FAIRING AND DISCOVERED MORE PITTING CORROSION, BUT NOT AS SEVERE AS LEFT SIDE. POSSIBLE CAUSES ARE MOISTURE UNDER OVERWING FAI RINGS. RECOMMEND CONSCIENTIOUSLY PERFORMED INSPECTION OF THE OVERWING FAIRING AREA. (X) 1 L 7 1 3O 2A13 2001013000002 20010130 00002 SO 2001 1 30 20000516SH030 1 20000413 G 5730 6531904 SKIN PIPER PA28 PA28161 7102803 SO LT AND RT WING CORRODED B AHRR K NONE O OTHER IN INSP/MAINT 1 GL 11 9351 DURING ROUTINE MAINTENANCE TO REPAIR FUEL LEAK FROM OVERWING FAIRING ASSY, REMOVED LEFT OVERWING FAIRING AND DISCOVERED EXTREME CASE OF EXFOLIATION CORROSION THAT CAUSED A HOLE THROUGH UPPER WING SKIN. AFTER FINDING CORROSION ON LEFT SIDE, DECIDED TO PULL OFF RIGHT OVERWING FAIRING AND DISCOVERED MORE PITTING CORROSION, BUT NOT AS SEVERE AS LEFT SIDE. POSS IBLE CAUSES ARE MOISTURE UNDER OVERWING FAIRINGS. RECOMMEND CONSCIENTIOUSLY PERFORMED INSPECTION OF THE OVERWING FAIRIN G AREA. (X) 1 L 7 1 3O 2A13 2001020500152 20010205 00152 SO 2001 2 5 20000516SH031 1 20000413 G 5730 SKIN PIPER PA28 PA28161 7102803 SO LT AND RT WING CORRODED B AHRR K NONE O OTHER IN INSP/MAINT 1 GL 11 6327 DURING ROUTINE MAINTENANCE TO REPAIR FUEL LEAK FROM OVERWING FAIRING ASSY, REMOVED LEFT OVERWING FAIRING AND DISCOVERED EXTREME CASE OF EXFOLIATION CORROSION THAT CAUSED A HOLE THROUGH UPPER WING SKIN. AFTER FINDING CORROSION ON LEFT SIDE, DECIDED TO PULL OFF RIGHT OVERWING FAIRING AND DISCOVERED MORE PITTING CORROSION, BUT NOT AS SEVERE AS LEFT SIDE. POSS IBLE CAUSES ARE MOISTURE UNDER OVERWING FAIRINGS. RECOMMEND CONSCIENTIOUSLY PERFORMED INSPECTION OF THE OVERWING FAIRIN G AREA. (X) 1 L 7 1 3O 2A13 2001020500153 20010205 00153 SO 2001 2 5 20000516SH032 1 20000413 G 5730 SKIN PIPER PA28 PA28181 7102807 SO LT AND RT WING CORRODED B AHRR K NONE O OTHER IN INSP/MAINT 1 GL 11 6522 DURING ROUTINE MAINTENANCE TO REPAIR FUEL LEAK FROM OVERWING FAIRING ASSY, REMOVED LEFT OVERWING FAIRING AND DISCOVERED EXTREME CASE OF EXFOLIATION CORROSION THAT CAUSED A HOLE THROUGH UPPER WING SKIN. AFTER FINDING CORROSION ON LEFT SIDE, DECIDED TO PULL OFF RIGHT OVERWING FAIRING AND DISCOVERED MORE PITTING CORROSION, BUT NOT AS SEVERE AS LEFT SIDE. POSS IBLE CAUSES ARE MOISTURE UNDER OVERWING FAIRINGS. RECOMMEND CONSCIENTIOUSLY PERFORMED INSPECTION OF THE OVERWING FAIRIN G AREA. (X) 1 L 7 1 3O 2A13 2001020500046 20010205 00046 SO 2001 2 5 20000516SH033 1 20000413 G 5730 SKIN PIPER PA28 PA28181 7102807 SO LT AND RT WING CORRODED B AHRR K NONE O OTHER IN INSP/MAINT 1 GL 11 6613 DURING ROUTINE MAINTENANCE TO REPAIR FUEL LEAK FROM OVERWING FAIRING ASSY, REMOVED LEFT OVERWING FAIRING AND DISCOVERED EXTREME CASE OF EXFOLIATION CORROSION THAT CAUSED A HOLE THROUGH UPPER WING SKIN. AFTER FINDING CORROSION ON LEFT SIDE, DECIDED TO PULL OFF RIGHT OVERWING FAIRING AND DISCOVERED MORE PITTING CORROSION, BUT NOT AS SEVERE AS LEFT SIDE. POSS IBLE CAUSES ARE MOISTURE UNDER OVERWING FAIRINGS. RECOMMEND CONSCIENTIOUSLY PERFORMED INSPECTION OF THE OVERWING FAIRIN G AREA. (X) 1 L 7 1 3O 2A13 2001020500047 20010205 00047 SO 2001 2 5 20000516SH034 1 20000413 G 5730 SKIN PIPER PA28 PA28161 7102803 SO LT AND RT WING CORRODED B AHRR K NONE O OTHER IN INSP/MAINT 1 GL 11 8724 DURING ROUTINE MAINTENANCE TO REPAIR FUEL LEAK FROM OVERWING FAIRING ASSY, REMOVED LEFT OVERWING FAIRING AND DISCOVERED EXTREME CASE OF EXFOLIATION CORROSION THAT CAUSED A HOLE THROUGH UPPER WING SKIN. AFTER FINDING CORROSION ON LEFT SIDE, DECIDED TO PULL OFF RIGHT OVERWING FAIRING AND DISCOVERED MORE PITTING CORROSION, BUT NOT AS SEVERE AS LEFT SIDE. POSS IBLE CAUSES ARE MOISTURE UNDER OVERWING FAIRINGS. RECOMMEND CONSCIENTIOUSLY PERFORMED INSPECTION OF THE OVERWING FAIRIN G AREA. (X) 1 L 7 1 3O 2A13 2000062900037 20000629 00037 NE 2000 6 29 20000517SH003 2 20000428 G 7230 2A0003 BEARING IAE IAE V2500 V2500A1 NE NR 4 OUTER RACE SPALLED B RA1R K NONE O OTHER IN INSP/MAINT 1 SW 05 2703 V0106 ENGINE REMOVED FOR ''''PERFORMANCE DETERIORATION''''. THE NR 4 BEARING EXHIBITED AXIAL SCORING OF THE ROLLERS AND OUTER RACE. MINOR FATIGUE SPALLING WAS PRESENT AT THE DAMAGE SITES ON BOTH THE RACE AND ROLLERS. INVESTIGATION IS IN PROGRE SS AT GE ENGINE SERVICES - DALLAS. (X) 4 F E311NE 2000062900038 20000629 00038 NE 2000 6 29 20000517SH004 2 20000428 G 7230 2A0003 BEARING IAE IAE V2500 V2500A1 NE NR 4 OUTER RACE MAKING METAL B K NONE O OTHER IN INSP/MAINT 1 SW 05 4369 V0340 ENGINE WAS REMOVED FOR ''''''''METAL IN NR 4 MCD''''''''. THE NR 4 BEARING EXHIBITED A REGION OF FATIGUE BREAK-UP ON TH E OUTER RACE. INVESTIGATION IS IN PROGRESS AT GE ENGINE SERVICES - DALLAS. (X) 4 F E311NE 2000070600128 20000706 00128 CE 2000 7 6 20000517SH009 1 20000424 G 2740 505244631 SPRING BEECH 99 C99 1154006 CE ATTACH POINT WORN D K NONE O OTHER IN INSP/MAINT 1 NM 11 239AL 15731 U239 SPRINGS TO HORIZONTAL STABILIZER WORN AT BOTH ENDS WHERE THE SPRINGS ATTACH TO THE STRAPS. (X) 1 L 7 2 3T A14CE 2000062900039 20000629 00039 CE 2000 6 29 20000517SH010 1 20000424 G 2740 99524118 STRAP BEECH 99 C99 1154006 CE ATTACH POINT WORN D K NONE O OTHER IN INSP/MAINT 1 NM 11 239AL 15731 U239 STRAPS WORN WHERE THEY ATTACH TO THE HORIZONTAL SPRINGS. (X) 1 L 7 2 3T A14CE 2000062900040 20000629 00040 CE 2000 6 29 20000517SH011 1 20000424 G 2740 995240501 STRAP BEECH 99 C99 1154006 CE ATTACH POINT WORN D K NONE O OTHER IN INSP/MAINT 1 NM 11 239AL 15731 U239 STRAPS WORN WHERE THEY ATTACH TO HORIZONTAL STABILIZER SPRINGS. (X) 1 L 7 2 3T A14CE 2000062900041 20000629 00041 CE 2000 6 29 20000517SH013 1 20000505 G 5712 57222061 CANOPY CESSNA 441 441 2076020 CE CRACKED B WTXR K NONE O OTHER IN INSP/MAINT 1 NM 01 555GD 4170 4410094 DURING A PHASE INSPECTION, FOUND A CRACK IN THE RT WING CANTED RIB TOP CAP. CRACK STARTS AT AFT SIDE OF FORWARD WING SP AR AND RUNS AFT PARALLEL TO THE BEND LINE 1 INCH LONG. STOP DRILLED PER CESSNA INSTRUCTIONS. (X) 1 L 7 2 3T RT A28CE 2000062900042 20000629 00042 EA 2000 6 29 20000517SH017 2 20000425 G 7414 BUSHING SLICK BNORM BN2 BN2A26 1520226 EU LYC O540 O540E4C5 41532 EA DISTRIBUTOR BOX WORN D FYOA K NONE O OTHER IN INSP/MAINT 1 AL 05 999SA 45 97121325 897 L1966540A PILOT REPORTED LEFT ENGINE WAS HARD TO START. REMOVED LEFT MAGNETO INSPECTION AND NOTED ''POINT'' MARKS USED FOR FACTOR Y SEALING STILL IN PLACE INDICATING MAGNETO INTERNAL INSPECTION REVEALED OILITE BUSHING IN DISTRIBUTOR BLOCK EXCESSIVELY WORN PRODUCING A METALLIC DUST COVERING INTERNAL COMPONENTS OF MAGNETO. BUSHING WAS .023 INCH LARGER THAN SHAFT OF ROT OR GEAR AND APPEARED TO HAVE NOT BEEN PROPERLY OILED AT FACTORY. (X) 1 H 7 2 3O 3 O A17EU E295 2000062900043 20000629 00043 2000 6 29 20000517SH018 4 20000424 G 6122 B3124 SHAFT HARTZL PIPER PA24 PA24260 7102406 SO LYC O540 IO540A1A5 41532 EA FAILED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 9051P 1532 665U 244516 RELEVANT INDICATION ON CONTROL SHAFT AT THE SPEED ADJUSTMENT SHAFT. (X) 1 L 7 1 3O 3 O 1A15 1E4 2000062900044 20000629 00044 2000 6 29 20000517SH019 4 20000424 G 6122 A20107 GEAR MCAULY CESSNA 180 180 2072602 CE CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 94003 RELEVANT INDICATION IN TEETH AREA OF IDLER GEAR. (X) 1 H 7 1 3O NC 5A6 2000062900045 20000629 00045 2000 6 29 20000517SH020 4 20000424 G 6122 A20609 LEVER MCAULY CESSNA 180 180 2072602 CE FAILED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 94003 RELEVANT INDICATION AT CLAMP RETENTION AREA OF CONTROL LEVER. (X) 1 H 7 1 3O NC 5A6 2000062900046 20000629 00046 2000 6 29 20000517SH021 4 20000425 G 6122 B3124 SHAFT HARTZL FAILED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 1696U RELEVANT INDICATION ON RETENTION AREA OF CONTROL SHAFT. (X) 2000062900047 20000629 00047 GL 2000 6 29 20000517SH022 3 20000501 G 6114 920012 HUB CESSNA 206 U206C 2073332 CE MCAULY 3A32C D3A32C90 GL CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 29150 88 U2061120 920012 CRACK STARTING FROM O-RING GROOVE EXTENDING ACROSS FLANGE AREA. (X) 1 H 7 1 3O A4CE 5 C P21EA 2000062900048 20000629 00048 2000 6 29 20000517SH023 4 20000412 G 6122 210316 FLYWEIGHT WOODWARD CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 1296292K RELEVANT INDICATION ON FLYWEIGHT BASE. (X) 2000070600135 20000706 00135 EA 2000 7 6 20000517SH024 2 20000320 G 7322 30800 FLOAT PRECISION AMRGEN AA5 AA5B 3960105 SO LYC O360 O360A4K 41514 EA DAMAGED B HO1R O OTHER R PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 EA 21 4553C 225 DL41123 AA5B1202 12504236A ENGINE WOULD NOT RUN UNLESS MIXTURE WAS LEANED ALMOST TO IDLE CUT-OFF, IT WAS VERY RICH AND WOULD NOT RUN ABOVE 1,500 RP M. FOUND PLASTIC FLOAT FILLED 100 II AVGAS TWO OF THREE CHAMBERS, FLOAT PN 30-800 CARBURETOR ASSY, DATE 9-97. (X) 1 L 7 1 3O 3 O A16EA E286 2000062900049 20000629 00049 CE 2000 6 29 20000517SH025 1 20000502 G 7920 MILH60003Q98 HOSE CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA OIL BREATHER LIN BLOCKED D A UNSCHED LANDING K B FLUID LOSS SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 GL 17 64448 17265235 L4200827A DURING ANNUAL INSP, ORIG OIL BREATHER LINE FOUND WEATHER CHECKED AND DETERMINED UNAIRWORTHY. NEW LINE WAS CUT OFF OF BU LK LENGTH STOCK AND REPLACED ORIG LINE IAW STD PRACTICES, AFTER LINE REPLACED, ACFT TEST RUN, ENG RUN-UP ON GROUND AT TA KEOFF POWER, CRUISE POWER, AND POST-MAINT CHK IAW CESSNA MM, CESSNA 172M. PILOTS OPER HANDBOOK WITH NO DISCREPANCIES OR OIL LEAKS NOTED, ACFT RELEASED FROM MAINT. FIVE MINUTES AFTER TAKEOFF, PILOT NOTED OIL SMOKE ENTERING COCKPIT, DECLAR ED EMERG, RETURNED TO AIRPORT. DURING RETURN, FRONT CRANKSHAFT SEAL BLEW OUT CAUSING LOSS OF OIL PRESS, DUMPING OIL OUT OF FRONT SEAL. ACFT LANDED SAFELY. INSP FND NEW BREATHER LINE BLOCKED. PLASTIC CAP SHOVED 4 INCHES UP INSIDE HOSE. 1 H 7 1 3O 3 O NT 3A12 E274 2000081400001 20000814 00001 SW 2000 8 14 20000518SH002 1 20000417 G 6510 407340340101 DISC PACK BELL BELL 407 407 SW T/R DRIVE CRACKED A ALGA O OTHER O OTHER IN INSP/MAINT 1 NM 07 627AL 813 A1178 53284 DURING 25-HOUR AD INSPECTION, FOUND NR 5 COUPLING CRACKED THROUGH ONE LAMINATE ON AFT FACING SIDE OF COUPLING, POSSIBLE CAUSE UNKNOWN. (X) 1 G 7 1 3U O H2SW 2000081400002 20000814 00002 SW 2000 8 14 20000518SH003 1 20000426 G 6510 407340339103 BEARING BELL 407 407 SW T/R DRIVE SHAFT DAMAGED B ALGR K NONE O OTHER IN INSP/MAINT 1 NM 07 687AL 1155 AFS1027 53366 DURING RECURRING 25-HOUR INSPECTION AND BEARING LUBRICATION (PER ASB 407-00-35/AD 2000-02-12), ACCUMULATED GREASE EXPELL ED FROM AROUND THE SEAL IS BLACK DETERMINING BEARING IS DAMAGED. (X) 1 G 7 1 3U O H2SW 2000081400003 20000814 00003 SW 2000 8 14 20000518SH004 1 20000426 G 6510 407340339103 BEARING BELL BELL 407 407 SW SHAFT HANGER DAMAGED B ALGR O OTHER O OTHER IN INSP/MAINT 1 NM 07 687AL A1729 53366 DURING RECURRING 25-HOUR INSPECTION AND BEARING LUBRICATION (PER ASB 407-00-35/AD 2000-02-01), DURING LUBRICATION, ACCUM ULATED GREASE EXPELLED FROM AROUND THE SEAL IS BLACK DETERMINING BEARING IS DAMAGED. (X) 1 G 7 1 3U O H2SW 2000081800001 20000818 00001 SW 2000 8 18 20000518SH005 1 20000426 G 6510 407340339103 BEARING BELL BELL 407 407 SW SHAFT HANGER LEAKING B ALGR O OTHER O OTHER IN INSP/MAINT 1 SW 03 687AL 53366 DURING RECURRING 25-HOUR INSPECTION AND BEARING LUBRICATION (PER ASB 407-00-35/AD 2000-02-12), DURING LUBRICATION, ACCU MULATED GREASE EXPELLED FROM AROUND THE SEAL IS BLACK DETERMINING BEARING IS DAMAGED. (X) 1 G 7 1 3U O H2SW 2000062100091 20000621 00091 SW 2000 6 21 20000518SH006 1 20000426 G 6510 407340339103 BEARING BELL BELL 407 407 SW T/R DRIVE SHAFT LEAKING B ALGR O OTHER K FLUID LOSS IN INSP/MAINT 1 SW 03 687AL 1155 AFS1027 53366 DURING RECURRING 25-HOUR INSPECTION AND BEARING LUBRICATION (PER ASB 407-00-35/AD 2000-02-12), ACCUMULATED GREASE EXPELL ED FROM AROUND THE SEAL IS BLACK DETERMINING BEARING IS DAMAGED. (X) 1 G 7 1 3U O H2SW 2000081800002 20000818 00002 SW 2000 8 18 20000518SH007 1 20000503 G 6730 206076062101 SERVO KAISER BELL 206 206L4 1182110 SW FLIGHT CONTROLS BENT B XJ2R O OTHER O OTHER IN INSP/MAINT 1 WP 01 108W 3595 52034 SERVO, PN 206-076-062-101, SN''S RH4417A, RH4418A, WERE REMOVED FROM AIRCRAFT FOR OVERHAUL. BOTH SERVO EXTENSION ASSEMB LIES WERE BENT TO ONE SIDE, .250 INCH. PART NUMBER OF EXTENSION ASSY, C42642-69. THIS SERVO IS THE SAME DESIGN AS THE ONE USED ON THE BELL 206L1, L3, EXCEPT THE P/N IS 206-076-062-003. THE OPERATING PRESSURE IS 600 PSI ON THE 206L1, L3, AND THE OPERATING PRESSURE ON THE 206L4 IS 1,000 PSI WHICH THE BENT EXTENSIONS CAME OFF. (X) 1 G 7 1 3U NC H2SW 2000081800003 20000818 00003 SW 2000 8 18 20000518SH008 1 20000503 G 6710 206076062101 SERVO KAISER BELL 206 206L4 1182110 SW FLIGHT CONTROLS BENT B XJ2R O OTHER O OTHER IN INSP/MAINT 1 WP 01 108W 3595 52034 SERVO, PN 206-076-062-101, SN''S RH4417A, RH4418A, WERE REMOVED FROM AIRCRAFT FOR OVERHAUL. BOTH SERVO EXTENSION ASSEMB LIES WERE BENT TO ONE SIDE, .250 INCH. PART NUMBER OF EXTENSION ASSY, C42642-69. THIS SERVO IS THE SAME DESIGN AS THE ONE USED ON THE BELL 206L1, L3, EXCEPT THE P/N IS 206-076-062-003. THE OPERATING PRESSURE IS 600 PSI ON THE 206L1, L3, AND THE OPERATING PRESSURE ON THE 206L4 IS 1,000 PSI WHICH THE BENT EXTENSIONS CAME OFF. (X) 1 G 7 1 3U NC H2SW 2001013000003 20010130 00003 GL 2001 1 30 20000518SH010 3 20000310 G 6114 HUB AMTR FISHER FISHERCELITY 05626AZ GL MCAULY 1B90 1B90CM GL HUB ASSY CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 13 8205H AVI001 34090 CRACK IN HUB RADIATING AWAY FROM CENTER PILOT HOLE TOWARD MOUNTING BOLT HOLE. CRACK FOUND USING DYE PENETRANT. PROPELL ER TAKEN OUT OF SERVICE. (X) 1 Q 7 1 3O NC EXPA1Q71 5 N P842 2001013000004 20010130 00004 NE 2001 1 30 20000518SH011 2 20000308 G 7260 4T0170 BEARING DOUG MD90 MD9030 3023690 NM IAE V2500 V2500A1 NE MAIN GRBX ASSY FAILED H WA2D K NONE O OTHER IN INSP/MAINT 1 NE 03 F69703 V20004 GEARBOX REMOVED FOR METAL IN CHIP COLLECTOR AND STRAINER. DISASSEMBLY, INSPECTION DISCLOSED BEARING (CAGE) FAILURE. MA TERIAL FORWARDED TO IAE ENGINEERING FOR REVIEW. (X) 2 L 7 2 4F 4 F RT A6WE E311NE 2001013000005 20010130 00005 SO 2001 1 30 20000518SH012 1 20000314 G 7820 5327F32 MUFFLER MAULE MX7 MX7180B 5460188 SO RT EXHAUST CRACKED D O OTHER B SMOKE/FUMES/ODORS/SPARKS TO TAKEOFF 1 SW 07 410TX 223 22007C PILOT REPORTED SMELL IN COCKPIT. NEXT TAKEOFF, HEARD LOUD RATTLE, LANDED. FOUND RT OUTER MUFFLER SHROUD LOOSE, THEN FO UND MUFFLER CRACKED AT 100.3 HRS. LT MUFFLER CHANGED. FACTORY ADVISED MATERIAL OF MUFFLER HAD BEEN CHANGED; SO, THAT 5 00 HRS SEEMED TO BE THE LIFE OF THESE UNITS AND STATED PROBLEM WAS POSSIBLE DUE TO SHORT HEADER STACKS AND WHEN PILOT PU LLED THROTTLE BACK FAST, CAUSED BACKFIRING IN MUFFLER AND DAMAGE. (X) 1 H 7 1 3O NC 3A23 2001011601197 20010116 01197 2001 1 16 20000518SH013 4 20000215 G 2210 1610128050A7 CIRCUIT BREAKER CESSNA 206 206H 2073301 CE LYC O540 IO540AC1A5 EA AUTOPILOT SYS FAILED E FGHA K NONE O OTHER IN INSP/MAINT 1 AL 05 7273Q 120 20608045 L2694348A DURING TROUBLESHOOTING OF KING KAP-140 AUTOPILOT SYSTEM, FOUND AUTOPILOT CIRCUIT BREAKER TO BE THE ''NON-PULLABLE'' TYPE CONTRARY TO THE PILOT OPERATING HANDBOOK EMERGENCY PROCEDURES FOR AUTOPILOT RUNAWAY **TONY, ISAAC PUT ENG IN SYS**TRIM INDICATION. UPON FLEET INSPECTION OF AIRCRAFT OF SAME MODEL, FOUND SAME SITUATION WITH THE INCORRECT AUTOPILOT CIRCUIT BREAKER INSTALLED IN S/N 20608046 AND S/N 20608048. (X) 1 H 7 1 3O 3 O RT A4CE 1E4 2001011601264 20010116 01264 EA 2001 1 16 20000518SH014 2 20000201 G 8530 LW18944 SHROUD CESSNA 206 206H 2073301 CE LYC O540 IO540AC1A5 EA NR 5 CYLINDER CRACKED E FGHA K NONE O OTHER IN INSP/MAINT 1 AL 05 7281M 48 20608048 L2697448A DISCOVERED OIL LEAK IN ENGINE COMPARTMENT COMING FROM RIGHT SIDE PUSH ROD TUBE SHROUD ON NR 5 CYLINDER ASSEMBLY. ON FUR THER INSPECTION, TUBE WAS FOUND CRACKED APPROXIMATELY ONE INCH DIAGONALLY THEN EXTENDING AROUND THE CIRCUMFERENCE OF THE TUBE (APPROX HALF WAY AROUND). CRACK WAS LOCATED DIRECTLY ADJACENT TO THE SPARK PLUG AND HAD BEEN PAINTED OVER WITH FA CTORY PAINT. NOTE: ENGINE HAD 47.7 HOURS SINCE NEW. AIRCRAFT HAD 47.7 HOURS SINCE NEW. (X) 1 H 7 1 3O 3 O RT A4CE 1E4 2001011601265 20010116 01265 EA 2001 1 16 20000518SH015 2 20000211 G 7497 WIRE CESSNA 206 206H 2073301 CE LYC O540 IO540AC1A5 EA IGNITION SWITCH SHORTED E K NONE O OTHER IN INSP/MAINT 1 AL 05 2312V 62 20608046 L2695848A PILOT REPORTED SPARKS COMING FROM UNDER THE INSTRUMENT PANEL UPON ENERGIZING THE IGNITION SWITCH. UPON FURTHER INVESTIG ATION, FOUND THE WIRE BUNDLE FOR THE CIRCUIT BREAKERS ADJACENT TO THE IGNITION SWITCH WAS TOO LONG AND A WIRE IN THE BUN DLE HAD CHAFED ON AN IGNTION SWITCH POLE EVENTUALLY ARCING. WIRE BUNDLE WAS RE-SECURED. OTHER FLEET AIRCRAFT OF SAME M ODEL REVEALED ONE OTHER AIRCRAFT WITH THE IDENTICAL PROBLEM, WHICH HAD NOT CHAFED THROUGH. (X) 1 H 7 1 3O 3 O RT A4CE 1E4 2000091800004 20000918 00004 SO 2000 9 18 20000522SH001 2 20000425 G 8540 21208A2 HOUSING BEECH 58 58 1152740 CE CONT O520 IO520* 17032 SO HOUSING CRACKED A FPIA K NONE O OTHER IN INSP/MAINT 1 SO 15 329H TH219 TACHOMETER DRIVE HOUSING CRACKED AT OIL PRESSURE BOSS. BOSS ON DRIVE HOUSING NEEDS TO BE BEEFED UP. CRACKS DUE TO WEAK CASTING. (X) 1 L 7 2 3O 3 O 3A16 E5CE 2000091800005 20000918 00005 NM 2000 9 18 20000522SH002 2 20000420 G 7322 8970552L LINE GULSTM 690TP 690B 7630516 SW GARRTT TPE331 TPE3315251K NM FUEL CONT BROKEN H O OTHER O OTHER IN INSP/MAINT 1 SW 15 690SC 11476 P06926 RIGHT ENGINE WOULD NOT START. FOUND PY LINE BROKEN JUST AFT OF LINE FITTING. REPLACED LINE. (X) 1 H 7 2 3T 4 T 2A4 E2WE 2000091800006 20000918 00006 CE 2000 9 18 20000522SH003 1 20000406 G 2720 0411526 BAR CESSNA 150 150M 2071830 CE BROKEN H O OTHER O OTHER NR NOT REPORTED 1 SO 17 9440U 7952 15078388 UNABLE TO GET NORMAL NOSE WHEEL STEERING DUE TO BREAK IN TUBE ALLOWING PEDAL MOVEMENT WITHOUT MOVING LINKAGE TO STEERIN G OR RUDDER. (X) 1 H 7 1 3O 3A19 2001030100001 20010301 00001 2001 3 1 20000522SH006 4 20000427 G 2564 FR46 LIFE RAFT SAFETY EQUIPMENT FAILED B K NONE L NO TEST IN INSP/MAINT 1 SO 19 DURING SCHEDULED MAINTENANCE, LIFE RAFT FUNCTIONALLY TESTED. THE INFLATABLE TUBE NR 1 FAILED TO INFLATE PROPERLY. FURT HER INVEST, REVEALED THE ASPIRATOR''S AIRFLOW BECAME BLOCKED WITH ITS OWN ANTI-CHAFING COATING FOR THE OUTLET. THIS COA TING IS NORMALLY APPLIED DURING MFG OR ACCOMPLISHMENT OF MFG''S SB. SUSPECT THE COAT SEPARATED DUE TO ITS EXCESSIVE LEN GTH (2.1250 INCHES) WHICH COVERS AN AREA OF FASTER AIRFLOW AND IS DIFFERENT FROM MFG''S SPEC LENGTH OF .50 TO .75 INCH. THE CONDITION IS NOT NORMALLY INSPECTED DURING SCHEDULED MAINT UNLESS RAFT FAILS FUNCTIONAL TEST. REF: HOOVER INDUSTRI ES SB 4600-25-01. (X) 2000062600091 20000626 00091 SO 2000 6 26 20000522SH007 1 20000522 G 3222 6705403 TRUNNION PIPER PA28 PA28RT201 7102818 SO SHIMMY DAMPER BROKEN H YBLS O OTHER W INADEQUATE Q C IN INSP/MAINT 1 WP 25 2895D 28R7918204 DURING ANNUAL INSPECTION, NOSE GEAR HAD TO BE TURNED. WHEN IT WAS TURNED TO THE STOP ON THE TRUNNION, A PORTION OF THE CASTING BROKE OFF. THIS PORTION OF THE TRUNNION ANCHORS THE SHIMMY DAMPER. UPON CLOSER INSP, FOUND CASTING HAD THREE AR EAS THAT HAD OPEN POCKETS IN THE CASTING. THERE WERE ALSO AREAS JUST BELOW THIS AREA THAT SHOWED POROSITY. THE TRUNNION WAS INSTALLED AT TIME OF MFG. TT AIRCRAFT: 6,984.4 HOURS. (X) 1 L 7 1 3O 2A13 2000062600092 20000626 00092 SO 2000 6 26 20000522SH010 1 20000522 G 3213 7873802 TRUNNION PIPER PA28 PA28161 7102803 SO TORQUE LINK LUG CRACKED H K NONE O OTHER IN INSP/MAINT 1 GL 11 510PU 8724 287916061 RIGHT GEAR OLEO PISTON ASSY TORQUE LINK LUGS CRACKED. EARLY DETECTION CAN ONLY BE DETECTED BY DYE PENETRANT OR OTHER ND T INSPECTION. AIRCRAFT USED FOR TRAINING 90 PERCENT OF ITS TOTAL TIME. (X) 1 L 7 1 3O 2A13 2000062600093 20000626 00093 SO 2000 6 26 20000522SH011 1 20000522 G 3213 6531904 TRUNNION PIPER PA28 PA28161 7102803 SO RT MAIN GEAR CRACKED H K NONE O OTHER IN INSP/MAINT 1 GL 11 9258 287816587 RIGHT GEAR HOUSING (CYLINDER) CRACKED AT LUG. EARLY DETECTION CAN ONLY BE ACCOMPLISHED BY DYE PENETRANT OR OTHER NDT INS PECTION. AIRCRAFT USED FOR TRAINING 90 PERCENT OF ITS TOTAL TIME. (X) 1 L 7 1 3O 2A13 2000091800007 20000918 00007 SO 2000 9 18 20000522SH012 1 20000522 G 3213 6531904 HOUSING PIPER PA28 PA28161 7102803 SO MAIN GEAR CRACKED H K NONE O OTHER IN INSP/MAINT 1 GL 11 31862 9351 287816587 LEFT GEAR HOUSING (CYLINDER) CRACKED AT LUG. EARLY DETECTION CAN ONLY BE ACCOMPLISHED BY DYE PENETRANT OR OTHER NDT INS PECTION. AIRCRAFT USED FOR TRAINING 90 PERCENT OF ITS TOTAL TIME. (X) 1 L 7 1 3O 2A13 2000103100027 20001031 00027 SO 2000 10 31 20000522SH013 1 20000522 G 3213 6531904 HOUSING PIPER PA28 PA28161 7102803 SO MAIN GEAR CRACKED H K NONE O OTHER IN INSP/MAINT 1 GL 11 6148H 6327 287816230 RIGHT GEAR HOUSING (CYLINDER) CRACKED AT LUG. EARLY DETECTION CAN ONLY BE ACCOMPLISHED BY DYE PENETRANT, OR OTHER NDT I NSPECTION. AIRCRAFT USED FOR TRAINING 90 PERCENT OF ITS TOTAL TIME. (X) 1 L 7 1 3O 2A13 2000103100028 20001031 00028 SO 2000 10 31 20000522SH014 1 20000522 G 3213 6531904 HOUSING PIPER PA28 PA28181 7102807 SO MAIN GEAR CRACKED H K NONE O OTHER IN INSP/MAINT 1 GL 11 8203D 6522 288290120 LEFT GEAR HOUSING (CYLINDER) CRACKED AT LUG. EARLY DETECTION CAN ONLY BE ACCOMPLISHED BY DYE PENETRANT OR OTHER NDT INS PECTION. AIRCRAFT USED FOR TRAINING 90 PERCENT OF ITS TOTAL TIME. (X) 1 L 7 1 3O 2A13 2000091800008 20000918 00008 SO 2000 9 18 20000522SH015 1 20000522 G 3213 6531904 HOUSING PIPER PA28 PA28181 7102807 SO MAIN GEAR CRACKED H K NONE O OTHER IN INSP/MAINT 1 GL 11 8203D 6613 288290120 RIGHT GEAR HOUSING (CYLINDER) CRACKED AT LUG. EARLY DETECTION CAN ONLY BE ACCOMPLISHED BY DYE PENETRANT OR OTHER NDT IN SPECTION. AIRCRAFT USED FOR TRAINING 90 PERCENT OF ITS TOTAL TIME. (X) 1 L 7 1 3O 2A13 2000091800009 20000918 00009 CE 2000 9 18 20000522SH016 1 20000515 G 7810 K1250860100 RISER CESSNA 210 T210L 2073449 CE CONT O520 TSIO520H 17040 SO NR 4 CYLINDER CRACKED B K NONE O OTHER IN INSP/MAINT 1 SW 03 732JF 1300 21061543 293581R MAINTENANCE LOOKED AT ACFT BEFORE FLIGHT. COWLING WAS REMOVED AND EXHAUST SOOT WAS SEEN AROUND LOWER SIDE OF NR 4 CYLIN DER. FURTHER INVESTIGATION REVEALED A CRACK AROUND THE EXHAUST RISER THAT WAS ABOUT 270 DEGREES AROUND THE PIPE. HEAT EXCHANGER PORTION OF THE EXHAUST HAD BEEN REPLACED DURING THE PREVIOUS 100-HR INSP ACCOMPLISHED 30 HRS PREVIOUSLY. THER E WAS NO PROBLEM IN ALIGNMENT DURING RE-ASSY OF EXHAUST SYS. SUBMITTER STATED THIS IS THE FIRST CRACKED RISER WITH THIS STC'D SYSTEM. OTHER AREAS THAT CRACKED WERE RE-DESIGNED BY MFG AND HAVE NOT HAD ANY OTHER PROBLEMS. (X) 1 H 7 1 3O 3 O 3A21 E8CE 2000080700004 20000807 00004 EU 2000 8 7 20000523SH001 1 20000114 G 3251 2878371 CONTROL BOX AMD FALC50 FALCON900 2700160 EU NLG STEERING OUT OF ADJ B AMCR K NONE O OTHER IN INSP/MAINT 1 GL 09 256DV 20 AFTER RECEIVING A REPLACEMENT STEERING CONTROL UNIT, INCOMING INSPECTION REVEALED THE UNIT MIS-ADJUSTED. WHEN PRESSING DOWN ON THE CONTROL WHEEL, SWITCHES MAKE TO ARM THE NG STEERING. THE SWITCH WAS ADJUSTED SUCH THAT WHEN THE CONTROL WHE EL IS TURNED, SLIGHT UP PRESSURE WOULD DISARM THE STEERING. THREE REPLACEMENT UNITS WERE CONFIRMED TO BE MIS-ADJUSTED. THE VENDOR AND OVERHAUL FACILITY WERE NOTIFIED OF PROBLEM. (X) 2 L 7 3 4F RT A46EU 2000081800004 20000818 00004 EU 2000 8 18 20000523SH003 1 20000222 G 6220 1051410110 BOLT BOLKMS BK117 BK117C1 5626025 EU MAIN ROTOR WORN B TI1R O OTHER O OTHER IN INSP/MAINT 1 SW 05 317MC 7505 PRIMARY BLADE REMOVED FOR WEAR. REMOVED AND REPLACED. (X) 1 G 7 2 3U NC H13EU 2000081800005 20000818 00005 EU 2000 8 18 20000523SH004 1 20000222 G 6230 1051011305 BELLOWS BOLKMS BK117 BK117C1 5626025 EU M/R MAST WORN B TI1R O OTHER O OTHER IN INSP/MAINT 1 SW 05 317MC 7505 BELLOWS REMOVED FOR WEAR. REMOVED AND REPLACED. (X) 1 G 7 2 3U NC H13EU 2000081800006 20000818 00006 EU 2000 8 18 20000523SH005 1 20000222 G 6210 10514101111 BOLT BOLKMS BK117 BK117C1 5626025 EU MAIN ROTOR WORN B TI1R O OTHER O OTHER IN INSP/MAINT 1 SW 05 317MC 7505 SECONDARY BLADE REMOVED FOR WEAR. REMOVED AND REPLACED. (X) 1 G 7 2 3U NC H13EU 2001011601295 20010116 01295 EU 2001 1 16 20000523SH008 1 20000203 G 2822 568127500000 ROTOR AIRBUS 320 A320212 EU FUEL PUMP WILL NOT TEST B IU6R K NONE L NO TEST IN INSP/MAINT 1 NM 01 117 UPON INCOMING FUNCTIONAL TEST OF THE UNIT, THE UNIT COULD NOT ACHIEVE THE REQUIRED PRESSURES OR FLOW RATES PER THE OHM. ON FURTHER INSPECTION, THE ROTOR WAS DETERMINED TO BE THE CAUSE OF TEST FAILURE. (X) 2 L 7 2 4F RT A28NM 2001011601297 20010116 01297 EU 2001 1 16 20000523SH010 1 20000203 G 2822 568127500000 ROTOR AIRBUS 320 A320212 EU FUEL PUMP WILL NOT TEST B IU6R K NONE L NO TEST IN INSP/MAINT 1 NM 01 584 UPON INCOMING FUNCTIONAL TEST OF THE UNIT, THE UNIT COULD NOT ACHIEVE THE REQUIRED PRESSURES OR FLOW RATES PER THE OHM. ON FURTHER INSPECTION, THE ROTOR WAS DETERMINED TO BE THE CAUSE OF TEST FAILURE. (X) 2 L 7 2 4F RT A28NM 2001011601298 20010116 01298 EU 2001 1 16 20000523SH011 1 20000302 G 2822 568127500000 ROTOR AIRBUS 320 A320212 EU FUEL PUMP WILL NOT TEST B IU6R K NONE L NO TEST IN INSP/MAINT 1 NM 01 613 UPON INCOMING FUNCTIONAL TEST OF THE UNIT, THE UNIT COULD NOT ACHIEVE THE REQUIRED PRESSURES OR FLOW RATES PER THE OHM. ON FURTHER INSPECTION, THE ROTOR WAS DETERMINED TO BE THE CAUSE OF TEST FAILURE. (X) 2 L 7 2 4F RT A28NM 2001011601299 20010116 01299 EU 2001 1 16 20000523SH012 1 20000203 G 2822 568127500000 ROTOR AIRBUS 320 A320212 EU FUEL PUMP WILL NOT TEST B IU6R K NONE L NO TEST IN INSP/MAINT 1 NM 01 772 UPON INCOMING FUNCTIONAL TEST OF THE UNIT, THE UNIT COULD NOT ACHIEVE THE REQUIRED PRESSURES OR FLOW RATES PER THE OHM. ON FURTHER INSPECTION, THE ROTOR WAS DETERMINED TO BE THE CAUSE OF TEST FAILURE. (X) 2 L 7 2 4F RT A28NM 2001011601494 20010116 01494 EU 2001 1 16 20000523SH013 1 20000203 G 2822 568127500000 ROTOR AIRBUS 320 A320212 EU FUEL PUMP WILL NOT TEST B IU6R K NONE L NO TEST IN INSP/MAINT 1 NM 01 758 UPON INCOMING FUNCTIONAL TEST OF THE UNIT, THE UNIT COULD NOT ACHIEVE THE REQUIRED PRESSURES OR FLOW RATES PER THE OHM. ON FURTHER INSPECTION, THE ROTOR WAS DETERMINED TO BE THE CAUSE OF TEST FAILURE. (X) 2 L 7 2 4F RT A28NM 2001011601223 20010116 01223 EU 2001 1 16 20000523SH014 1 20000203 G 2822 568127500000 ROTOR AIRBUS 320 A320212 EU FUEL PUMP WILL NOT TEST B IU6R K NONE L NO TEST IN INSP/MAINT 1 NM 01 2498 UPON INCOMING FUNCTIONAL TEST OF THE UNIT, THE UNIT COULD NOT ACHIEVE THE REQUIRED PRESSURES OR FLOW RATES PER THE OHM. ON FURTHER INSPECTION, THE ROTOR WAS DETERMINED TO BE THE CAUSE OF TEST FAILURE. (X) 2 L 7 2 4F RT A28NM 2001011601224 20010116 01224 EU 2001 1 16 20000523SH016 1 20000203 G 2822 568127500000 ROTOR AIRBUS 320 A320212 EU FUEL PUMP WILL NOT TEST B IU6R K NONE L NO TEST IN INSP/MAINT 1 NM 01 2983 UPON INCOMING FUNCTIONAL TEST OF THE UNIT, THE UNIT COULD NOT ACHIEVE THE REQUIRED PRESSURES OR FLOW RATES PER THE OHM. ON FURTHER INSPECTION, THE ROTOR WAS DETERMINED TO BE THE CAUSE OF TEST FAILURE. (X) 2 L 7 2 4F RT A28NM 2000091800012 20000918 00012 EA 2000 9 18 20000523SH019 2 20000427 G 7420 IGNITION LEAD CHAMPION PIPER PA28 PA28181 7102807 SO LYC O360 O360A4M 41514 EA SHIELDING FAILED B SL5R O OTHER O OTHER NR NOT REPORTED 1 NE 03 4198F 16 287790006 L2207836A IGNITION NOISE IN RADIO REPORTED BY OWNER. TRACED PROBLEM TO FOUR IGNITION LEADS WITH UNGROUNDED WIRE SHIELDING. SUBMI TTER SUSPECTED POOR QUALITY CONTROL/FINAL INSPECTION BY MANUFACTURER. (X) 1 L 7 1 3O 3 O 2A13 E286 2000091800013 20000918 00013 CE 2000 9 18 20000523SH020 1 20000404 G 3397 WIRE BEECH 36 A36 1151604 CE NAV LIGHT CHAFED B K NONE O OTHER NR NOT REPORTED 1 EA 23 6923R 2980 E2149 FOUND NAVIGATION LIGHT BREAKER TRIPPED. FOUND WIRING IN LEFT WING NOT PROPERLY SECURED AND CHAFED WHERE CROSSING THROUG H RIB; THUS, SHORTING CIRCUIT. SUBMITTER STATED THAT IT LOOKS LIKE IT WAS INSTALLED THIS WAY BY FACTORY, NO SIGNS OF CL AMPS. (X) 1 L 7 1 3O 3A15 2000091800014 20000918 00014 CE 2000 9 18 20000523SH021 1 20000413 G 3230 08411121 LINK CESSNA 421 421A 2076012 CE RT MAIN LANDING SEPARATED G O OTHER O OTHER LD LANDING 1 SO 15 2989Q 421A0089 THE LINK SEPARATED IN THE THREADED AREA WHERE IT ENTERS THE ROD-END IN THE LINK ASSY. THIS IS PART OF BELLCRANK 5041001 -2. THE FAILURE CAUSED THE RIGHT MAIN GEAR TO COME OUT OF OVERCENTER IN THE DOWN POSITION AND THEN COLLAPSE. (X) 1 L 7 2 3O A7CE 2001013000010 20010130 00010 CE 2001 1 30 20000523SH022 1 20000523 G 5410 BEAM CESSNA 402 402B 207590P CE LT AND RT ENGINE DAMAGED B X07R K NONE O OTHER IN INSP/MAINT 1 CE 07 306 402B0435 LT AND RT ENGINE BEAMS (INBD AND OTBD) BUCKLING AND HEAT DAMAGE. GENERAL CORROSION BEHIND ENGINES. LT AND RT ENGINES C ANTED BULKHEADS. CORROSION AND HEAT DAMAGE. LT AND RT WING LOWER SPAR CAPS, OVERSIZED HOLES WITH RIVNUTS INSTALLED. L T AND RT ENGINE NACELLE STIFFENERS BEHIND FWD SPAR HAVE BEEN CUT. RT ELEVATOR HAS SLOP IN TORQUE TUBE. SERVICE KIT 40 2-46 WING FRONT SPAR LOWER CAP MODIFICATION AND ACCESS PANEL INSTALLATION IN WORK. (X) 1 L 7 2 3O A7CE 2000091800015 20000918 00015 CE 2000 9 18 20000523SH024 1 20000508 G 3246 AN535A BOLT BEECH 95 95B55 1152729 CE THREADS BROKEN H K NONE O OTHER IN INSP/MAINT 1 GL 03 2189L TC1993 BOLTS BROKE AT BASE OF THREADS. MOST LIKELY CAUSED BY OVERTORQUING. THE BOLTS ARE WHEEL THROUGH BOLTS ON THE MAIN TIRE S. (X) 1 L 7 2 3O RT 3A16 2000091800016 20000918 00016 SW 2000 9 18 20000523SH025 1 20000523 G 1100 PLACARD MOONEY M20 M20R 5870225 SW PILOT SIDE PANEL INCORRECT B EWGR K NONE O OTHER IN INSP/MAINT 1 SO 05 535C 290146 THE OPERATION LIMITATIONS PLACARD DOES NOT MATCH THE TYPE CERTIFICATE DATA SHEET. THE MANEUVERING SPEED IS DIFFERENT. (X) 1 L 7 1 3O RT 2A3 2000091800017 20000918 00017 NE 2000 9 18 20000523SH026 1 20000414 G 5740 2161110 BEAM LAKEAC LAKE 250LAKE 5110321 NE REAR WING SPAR CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 25 14032 1900 36 CRACK SEEMS TO ORIGINATE FROM A PUNCHED THROUGH .1250 INCH JIG HOLE, 2.50 INCHES OUT FROM REAR SPAR ATTACH BOLT. CAN BE SEEN FROM GEAR WALL .3750 INCH LONG CRACK. (X) 1 H 7 1 3O NC 1A13 2000091800018 20000918 00018 NE 2000 9 18 20000523SH027 1 20000414 G 2730 3225529 BRACKET LAKEAC LAKEAC LAKE 250LAKE 5110321 NE ELEVATOR CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 25 14032 1900 36 ANNUAL INSPECTION FOUND ELEVATOR HORN ATTTACH BRACKETS, UPPER EAR OF BOTH BRACKETS WERE FOUND CRACKED OFF. (X) 1 H 7 1 3O NC 1A13 2000091800019 20000918 00019 CE 2000 9 18 20000523SH028 1 20000516 G 2710 355211524 TORQUE TUBE BEECH 36 A36 1151604 CE ROD END FAILED H K NONE O OTHER IN INSP/MAINT 1 SO 14 422MM 201 E3217 UPON ANNUAL INSPECTION, FOUND LT AILERON WITH EXCESSIVE PLAY. REMOVED TORQUE TUBE AND FOUND THREADED PORTION OF TUBE NO T THREADED TO THE TOP OF TUBE. TUBE REMOVED FROM SERVICE AND INSTALLED NEW TUBE. THE ROD ENDS WERE ALSO REPLACED WITH NEW. (X) 1 L 7 1 3O 3A15 2000061300376 20000613 00376 EU 2000 6 13 20000523SH030 1 20000503 G 2400 B3651M0250 RELAY AMD FALC10 FALCON10 2730101 EU AIRFRAME FAILED B G1FR K NONE O OTHER IN INSP/MAINT 1 GL 13 147G 214 DURING AIRFRAME INSPECTION, THE REVERSE CURRENT RELAY WAS REMOVED FOR INSPECTION AND RECERTIFICATION. THE RELAY, WHICH W AS FUNCTIONING NORMALLY WHEN REMOVED, WAS ROUTED TO A RATED REPAIR STATION FOR CHECK AND RECERTIFICATION. UPON RETURN F ROM VENDOR, UNIT WAS RE-INSTALLED AND OPER CHKS PER MM. AFTER ELEC POWER APPLIED, EXTENSIVE DAMAGE OCCURRED TO WIRING F ROM MAIN POWER JUNCTION BOX TO OVERHEAD PANEL START SWITCHES. REVERSE CURRENT RELAY, PN B3651M0-250, SN 2324, WAS DETER MINED DEFECTIVE AND REPLACED. RELAY REPLACED WITH NEW UNIT PN B3651M0-250 AND DAMAGED WIRING REPLACED FROM MAIN POWER J UNCTION BOX TO OVERHEAD PANEL START SWITCHES. SUBSEQUENT OPER CHECKS WITH ENG RUNS REVEALED NO FURTHER DEFECTS. (X) 2 L 7 2 4F A33EU 2000091800021 20000918 00021 CE 2000 9 18 20000523SH031 1 20000517 G 3246 95440253 WHEEL GOODYEARAERO LEAR 24 24D 5170311 CE FLANGE CRACKED B GPER K NONE O OTHER IN INSP/MAINT 1 SW 05 281FP SEP72516 281 PART TSO: 172 LANDINGS. SINCE EDDY CURRENT INSPECTION, FOUND BY MAINTENANCE AFTER A FLIGHT, NO EVIDENCE THE WHEEL HAD B EEN STRUCK. (X) 2 L 7 2 4J A10CE 2001013000012 20010130 00012 NE 2001 1 30 20000524SH002 2 20000501 G 7230 2A0851 SEAL IAE V2500 V2500A1 NE NR 4 BEARING CRACKED B KB1R K NONE O OTHER IN INSP/MAINT 1 NE 03 PART RECEIVED FROM WESTFIELD GAGE (WNFR711K) FOR PENETRANT INSPECTION PER V2500 ENGINE MANUAL SECTION 70-23-01, TASK 70- 23-01-230-501, INSPECTION CHECK-01. PART REJECTED AT PENETRANT INSPECTION DUE TO A CRACK ON OUTSIDE TOP OF PART APPROX IMATELY .250 INCH LONG. (X) 4 F E311NE 2001013000015 20010130 00015 NE 2001 1 30 20000524SH008 2 20000505 G 7230 2A0851 SEAL IAE V2500 V2500A1 NE NR 4 BEARING CRACKED B KB1R K NONE O OTHER IN INSP/MAINT 1 NE 03 PART RECEIVED FROM WESTFIELD GAGE (WNFR711K) FOR FPI PER V2500 ENGINE MANUAL REV 42, SECTION 70-23-01, INSPECTION CHECK- 01, TASK 70-23-01-230-501). PART REJECTED AT FPI DUE TO A CRACK, 0.180 INCH ON TOP SURFACE, 4 F E311NE 2001013000016 20010130 00016 NE 2001 1 30 20000524SH009 2 20000505 G 7230 2A0851 SEAL IAE V2500 V2500A1 NE NR 4 BEARING CRACKED B KB1R K NONE O OTHER IN INSP/MAINT 1 NE 03 PART RECEIVED FROM WESTFIELD GAGE (WNFR711K) FOR FPI PER V2500 ENGINE MANUAL REV 42, SECTIO 70-23-01, INSPECTION CHECK-0 1, TASK 70-23-01-230-501). PART REJECTEDAT FPI DUE TO A CRACK 0.325 INCH ON TOP SURFACE. (X) 4 F E311NE 2001013000017 20010130 00017 EA 2001 1 30 20000524SH010 2 20000428 G 7414 10382807 CAPACITOR D4LN3200 ENSTRM F28 F28F 3300412 GL LYC O360 HIO360F1AD 41514 EA RIGHT MAGNETO FAILED B NQ2R O OTHER O OTHER NR NOT REPORTED 1 WP 05 110PD 13 H269108G 768 L2537651A SUBJECT CAPACITOR WAS INSTALLED NEW IN AUGUST, 1999. MAGNETO WAS PART OF SPARE ENGINE NOT INSTALLED UNTIL THIS MONTHV. THE CAPACITOR HAD VERY FEW HOURS (13.3 HRS) WHEN IT CAUSED HEAVY POINT RACING WHICH MELTED THE NYLON FOLLOWER. WHEN TH IS HAPPENED, THE POINTS QUIT OPENING AND THE RIGHT HALF OF THE MAG WENT DEAD. CAPACITOR FAILS THE SEALEY RESISTANCE TES T ON THE BENCH AND HAS .4 OHM RESISTANCE FROM P-LEAD END TO DIGITAL. DATE CODE IS 9835 WICH MAKES IT SUBJECT TO TCM BUL LETIN NR CSB662A, BUT OWNER WAS NOT AWARE OF BULLETIN. ALSO, BULLETIN ALLOWS 50 HOUR TIME IN SERVICE. SUBMITTER STATED THIS ONE HAD FAR LESS. (X) 1 G 7 1 3O 3 O H1CE 1E10 2000120700001 20001207 00001 CE 2000 12 7 20000524SH012 1 20000515 G 5312 00244002391 BULKHEAD BEECH 55 E55 1152732 CE CRACKED B NT2R K NONE O OTHER IN INSP/MAINT 1 CE 07 3085W 2206 TE954 DURING ANNUAL INSPECTION, FOUND CRACK .75 INCH LONG (LEFT) AND .3750 INCH LONG (RIGHT) ON BULKHEAD, PN 002-440023-91 AT BS 257.6. CRACKS ARE ADDRESSED IN BEECH SI 0990R2, FIGURE 1. INSTALLED REPAIR KIT AS DIRECTED BY SI 0990R2. (X) 1 L 7 2 3O 3A16 2001010300001 20010103 00001 SW 2001 1 3 20000524SH013 1 20000511 G 2720 500012263 CONTROL CABLE GULSTM 690TP 690B 7630516 SW BS 99.00 BROKEN B K NONE O OTHER IN INSP/MAINT 1 SW 15 690JH 5313 11529 LEFT AND RIGHT FORWARD RUDDER CABLES HAD BROKEN WIRE STRANDS AT LEFT AND RIGHT PULLEY AT BS 99.00. FOUND DURING 100-HOU R INSPECTION. ROTATED CABLES 10 DEGREES FROM PULLEY TO SEE BROKEN WIRE STRANDS. CAUSE, DETERIORATION DUE TO TIME. AIR CRAFT TT: 5,313 HOURS. REPLACED CABLE ASSY. (LEFT FROM RUDDER PEDAL AFT TO TURNBARREL AT STA 335.00) AND (RIGHT FROM RUDDER PEDAL AFT TO TURNBARREL AT STA 353.00). 1 H 7 2 3T 2A4 2001013000018 20010130 00018 SW 2001 1 30 20000524SH014 1 20000511 G 2720 500012265 CONTROL CABLE GULSTM 690TP 690B 7630516 SW RUDDER CONTROL FRAYED B K NONE O OTHER IN INSP/MAINT 1 SW 15 690JH 5313 11529 LEFT AND RIGHT FORWARD RUDDER CABLES HAD BROKEN WIRE STRANDS AT LEFT AND RIGHT PULLEY AT BS 99.00. FOUND DURING 100-HOU R INSPECTION. ROTATED CABLES 10 DEGREES FROM PULLEY TO SEE BROKEN WIRE STRANDS. CAUSE, DETERIORATION DUE TO TIME. AIR CRAFT TT: 5,313 HOURS. REPLACED CABLE ASSY. (LEFT FROM RUDDER PEDAL AFT TO TURNBARREL AT STA 335.00) AND (RIGHT FROM RUDDER PEDAL AFT TO TURNBARREL AT STA 353.00). 1 H 7 2 3T 2A4 2001013000019 20010130 00019 CE 2001 1 30 20000524SH015 1 20000227 G 2810 05235221 STRAP CESSNA 150 152 2071835 CE RT FUEL TANK BROKEN D K NONE K FLUID LOSS IN INSP/MAINT 1 EA 23 95939 15285988 IT WAS NECESSARY TO PULL THE RT WING FUEL TANK TO CONFIRM FUEL LEAK LOCATION. THE AFT OUTBOARD STRAP ASSY WAS FOUND BRO KEN ACROSS THE SCREW HOLE. FURTHER EXAM OF STRAP REVEALED THE GRAIN OF THE ALUMINUM WAS PARALLEL TO THE BREAK AS WELL A S THE BEND. IT IS BELIEVED THAT IF THE GRAIN WERE PERPENDICULAR TO THE BEND RADIUS, THE LIKELIHOOD OF A FAILURE AT THE SCREW HOLE OR BEND WOULD BE GREATLY REDUCED. THE FUEL TANK HAD A PREVIOUS CRACK WHICH WAS WELDED. THE LOSS OF THIS STR AP IS BELIEVED TO HAVE CAUSED THE REPEAT FAILURE OF THE TANK AT THIS SAME LOCATION, WHICH WAS AT THE AFT BOTTOM FUEL OUT PUT (JUST ABOVE IT). THE TANK AND STRAP ASSEMBLIES WERE REPLACED WITH NEW ASSEMBLIES. (X) 1 H 7 1 3O NT 3A19 2001013000020 20010130 00020 EA 2001 1 30 20000524SH016 2 20000428 G 8520 SL75060 ROD BOLT PIPER PA32 PA32R300 7103213 SO LYC O540 IO540K1A5 41532 EA NR 1 PISTON ROD FAILED H A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CE 05 47977 214 32R7880031 L1518048A AIRCRAFT ENGINE OIL TEMPERATURE AT 200 DEGREES. LOSS OF OIL PRESSURE AT NORMAL CRUISE MADE OFF-AIRPORT LANDING. FOUND NR 1 PISTON ROD HAD FAILED. POSSIBLE CAUSE FOR FAILURE, SUPERIOR ROD CAP BOLT FAILED CAUSING ROD TO COME LOOSE, KNOCK H OLE IN ENGINE CASE. (X) 1 L 7 1 3O 3 O A3SO 1E4 2000120700002 20001207 00002 CE 2000 12 7 20000524SH018 1 20000420 G 5700 RIVET BEECH 58 58 1152740 CE LEFT MISINSTALLED B K NONE W INADEQUATE Q C IN INSP/MAINT 1 EA 23 2018T TH954 AIRCRAFT REPAIRED IN 1980 AFTER GEAR UP LANDING. REPAIRS FOUND TO BE UNACCEPTABLE IN 2000 ANNUAL. RIVETS WERE INSTALLE D WITH NO SHOP HEAD, AND RIVET HEADS NOT AGAINST STRUCTURE. LOCATION OF REPAIR IS UPPER FORWARD WING SPAR JUST OUTBOARD OF WING BELT FITTING. ANNUAL SIGNED OFF UNAIRWORTY, AND OWNER FERRIED AIRCRAFT TO HOME BASE. OWNER SAYS HE CANNOT BEL IEVE AIRCRAFT WENT THROUGH 18 ANNUALS AND NO ONE SAW THIS. SUBMITTER SUGGESTED EXTRA LOOK AT PREVIOUS REPAIRS. 1 L 7 2 3O 3A16 2001011601235 20010116 01235 NM 2001 1 16 20000530SH006 1 20000403 G 3231 600050525 ROD PIPER PA60 PA60600 7106001 NM MLG DOOR BENT A BSYA O OTHER J WARNING INDICATION NR NOT REPORTED 1 GL 07 3643D 600835816152 BDL - LANDING GEAR WOULD NOT RETRACT. FOUND GEAR DOOR ROD ASSY BENT. REMOVED AND REPLACED ROD ASY. OPS CHECKED GOOD. (X) 1 M 7 2 3O RT A17WE 2001011601236 20010116 01236 EA 2001 1 16 20000530SH007 2 20000426 G 8520 LW10646 CONNECTING ROD PIPER PA60 PA60600 7106001 NM LYC O540 IO540K1J5 41532 EA NR 5 CYLINDER FAILED A BSYA E ENGINE SHUTDOWN R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 GL 07 6896B 600919816126 L1841648A BDL - RT ENGINE ROUGH, THEN PILOT SHUT ENGINE DOWN. FOUND NR 5 CYLINDER CONNECTING ROD FAILED. CAUSE UNKNOWN AT THIS T IME. REMOVED AND REPLACED ENGINE ASSY. (X) 1 M 7 2 3O 3 O RT A17WE 1E4 2000120700003 20001207 00003 CE 2000 12 7 20000530SH008 1 20000509 G 3340 BEACON MOTOR BEECH 58 58 1152740 CE BURNED A BSYA K NONE O OTHER IN INSP/MAINT 1 GL 07 9044V TH216 BDL - GOT SMOKE IN COCKPIT JUST AFTER TAKEOFF, RETURNED TO BDL. FOUND POWER WIRE TO ROTATING BEACON BURNT. (X) 1 L 7 2 3O 3A16 2001011601237 20010116 01237 CE 2001 1 16 20000530SH009 1 20000505 G 2120 UNKNOWN CESSNA 310 310R 2074245 CE COCKPIT ODOR A BYSA C ABORTED TAKEOFF B SMOKE/FUMES/ODORS/SPARKS TO TAKEOFF 1 GL 07 6122C 310R1290 CMH - PILOT REPORTED BURNING SMELL IN COCKPIT ON TAKEOFF. ABORTED TAKEOFF AND RETURNED TO BASE. MAINTENANCE CHECKED HE ATER, LANDING GEAR, ALL ELECTRICAL COMPARTMENTS, AVIONICS, CHECKED ALL RADIOS. COULD NOT DUPLICATE SMELL. RETURNED TO SERVICE. (X) 1 L 7 2 3O 3A10 2001011601238 20010116 01238 EA 2001 1 16 20000530SH010 2 20000505 G 8530 CYLINDER PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA LT ENGINE NR 2 SEPARATED A BYSA O OTHER D R INFLIGHT SEPARATION PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 GL 07 525AA 318052111 AGC - LEFT ENGINE NR 2 CYLINDER SEPARATED FROM ENGINE. CAUSE UNKNOWN AT THIS TIME. (X) 1 L 7 2 3O 3 O A20SO E14EA 2001013000021 20010130 00021 2001 1 30 20000530SH011 4 20000502 G 6122 4508042 FLYWEIGHT WOODWARD GULSTM 500 500RKWELL 0141102 SW PROP GOVERNOR CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 1450395A RELEVANT CRACK INDICATION IN CORNER OF FLYWEIGHT DISC. (X) 1 H 7 2 3O 6A1 2001013000022 20010130 00022 NE 2001 1 30 20000530SH012 2 20000510 G 7250 UL10323 DISK RROYCE RB211 RB211535E4B3 NE TURBINE SECTION CRACKED B XE5R K NONE O OTHER IN INSP/MAINT 1 SW 21 30494 31009 CRACK INDICATIONS FOUND DURING ACCOMPLISHMENT OF ROLLS-ROYCE SB RB.211-72-C817. (X) 4 F E12EU 2001013000023 20010130 00023 NE 2001 1 30 20000530SH013 2 20000510 G 7250 UL10323 DISK RROYCE RB211 RB211535E4B3 NE TURBINE SECTION CRACKED B XE5R K NONE O OTHER IN INSP/MAINT 1 SW 21 29018 31118 CRACK INDICATIONS FOUND DURING ACCOMPLISHMENT OF ROLLS-ROYCE SB RB.211-72-C817. (X) 4 F E12EU 2001013000024 20010130 00024 NE 2001 1 30 20000530SH014 2 20000510 G 7250 UL27681 DISK RROYCE RB211 RB211535E4B3 NE TURBINE SECTION CRACKED B XE5R K NONE O OTHER IN INSP/MAINT 1 SW 21 29778 31030 CRACK INDICATIONS FOUND DURING ACCOMPLISHMENT OF ROLLS-ROYCE SB RB.211-72-C817. (X) 4 F E12EU 2001013000025 20010130 00025 NE 2001 1 30 20000530SH015 2 20000510 G 7250 UL27681 DISK RROYCE RB211 RB211535E4B3 NE TURBINE SECTION CRACKED B XE5R K NONE O OTHER IN INSP/MAINT 1 SW 21 25399 31091 CRACK INDICATIONS FOUND DURING ACCOMPLISHMENT OF ROLLS-ROYCE SB RB.211-72-C817. (X) 4 F E12EU 2001013000026 20010130 00026 NE 2001 1 30 20000530SH016 2 20000510 G 7250 UL27681 DISK RROYCE RB211 RB211535E4B3 NE TURBINE SECTION CRACKED B XE5R K NONE O OTHER IN INSP/MAINT 1 SW 21 22970 31014 CRACK INDICATIONS FOUND DURING ACCOMPLISHMENT OF ROLLS-ROYCE SB RB.211-72-C817. (X) 4 F E12EU 2001013000027 20010130 00027 NE 2001 1 30 20000530SH017 2 20000510 G 7250 UL27681 DISK RROYCE RB211 RB211535E4B3 NE TURBINE SECTION CRACKED B XE5R K NONE O OTHER IN INSP/MAINT 1 SW 21 17201 31031 CRACK INDICATIONS FOUND DURING ACCOMPLISHMENT OF ROLLS-ROYCE SB RB.211-72-C817. (X) 4 F E12EU 2001013000028 20010130 00028 NE 2001 1 30 20000530SH018 2 20000510 G 7250 UL27681 DISK RROYCE RB211 RB211535E4B3 NE TURBINE SECTION CRACKED B XE5R K NONE O OTHER IN INSP/MAINT 1 SW 21 19544 31178 CRACK INDICATIONS FOUND DURING ACCOMPLISHMENT OF ROLLS-ROYCE SB RB.211-72-C817. (X) 4 F E12EU 2000082200001 20000822 00001 2000 8 22 20000531SH001 4 20000327 G 2562 AK450 ELT PIPER PA28 PA28RT201 7102818 SO FAILED H K NONE O OTHER IN INSP/MAINT 1 NM 01 2241N 28R7918043 ELT FAILED TEST PER FAR 91.207. NO SWEEPS COULD BE HEARD ON 121.5. UNIT WAS NEW 12 MONTHS EARLIER. (X) 1 L 7 1 3O 2A13 2000082200002 20000822 00002 SO 2000 8 22 20000531SH002 1 20000518 G 2751 2282002 SENSOR PIPER PA23 PA23250 7102308 SO FLAP MISINSTALLED H K NONE O OTHER IN INSP/MAINT 1 EA 13 FLAP SENDER POTENTIOMETER INSTALLED BACKWARDS. PART WAS NEW FROM PIPER. OTHER PART NUMBERS ON UNIT, 2283-002, 2282-3, 5276. (X) 1 L 7 2 3O 1A10 2000082200003 20000822 00003 2000 8 22 20000531SH003 4 20000508 G 2562 AK450 ELT CESSNA 177 177RG 2073709 CE FAILED H K NONE O OTHER IN INSP/MAINT 1 NM 01 300ZX 177RG0072 ELT UNIT RECEIVED FROM MANUFACTURER AS AN EXCHANGE UNIT. ELT FAILED TEST AFTER REINSTALLATION. NO SWEEPS COULD BE HEAR D ON 121.5. AN OCCASIONAL SHORT ''CHIRP'' COULD BE HEARD, BUT NO SWEEPS. (X) 1 H 7 1 3O A20CE 2000082200004 20000822 00004 2000 8 22 20000531SH004 4 20000208 G 2562 AK450 ELT CESSNA 177 177RG 2073709 CE FAILED H K NONE O OTHER IN INSP/MAINT 1 NM 01 300ZX 100 177RG0072 ELT FAILED TEST PER FAR 91.207. NO SWEEPS COULD BE HEARD ON 121.5. UNIT WAS REPAIRED FOR SAME PROBLEM 11 MONTHS EARLIE R ON 1-19-99. (X) 1 H 7 1 3O A20CE 2001013000029 20010130 00029 SO 2001 1 30 20000531SH005 2 20000419 G 8520 642133 CASE CESSNA 421 421B 2076014 CE CONT O520 GTSIO520H 17032 SO ENGINE CRACKED B EKIR K NONE O OTHER IN INSP/MAINT 1 WP 07 4050Q 421B0274 218398H CASE CRACKED ON LEFT HALF UPPER AT BACK ABOVE SPLIT, THE 5TH BOLT FROM REAR. (X) 1 L 7 2 3O 3 O A7CE E7CE 2001013000030 20010130 00030 EA 2001 1 30 20000531SH006 2 20000502 G 8540 06A19956 SEAL CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA ACCESSORY SECT FAILED B EKIR O OTHER K J FLUID LOSS WARNING INDICATION AP APPROACH 1 WP 07 502ER 1512 172S8002 L2776151A DURING FINAL APPROACH, PILOT NOTED LOW OIL PRESSURE INDICATION. DURING INVESTIGATION OF OIL LOSS, IT WAS NOTED THAT THE OIL SEAL LIP WAS TURNED OUTWARD AND THE TENSION SPRING WAS MISSING. APPROXIMATELY 1 QUART OF OIL REMAINED IN THE OIL S UMP. SEAL WAS IN LOWER VACUUM PUMP ADAPTER. (X) 1 H 7 1 3O 3 O NT 3A12 1E10 2001013000031 20010130 00031 CE 2001 1 30 20000531SH007 1 20000502 G 3211 24411001 PIVOT CESSNA 172 172RG 2072438 CE LT MLG CRACKED B EKIR K NONE K FLUID LOSS IN INSP/MAINT 1 WP 07 4802R 5872 172RG0035 LEFT BRAKE KEPT BECOMING SOFT AND LOOSING HYDRAULIC FLUID WITH NO EXTERNAL LEAKS FOUND. REMOVAL AND DYE PENETRANT INSPE CTION OF LEFT MAIN GEAR PIVOT REVEALED CRACK IN RADIUS OF SPLINES INTO BRAKE FLUID PASSAGE. (X) 1 H 7 1 3O 3A17 2000122900001 20001229 00001 CE 2000 12 29 20000531SH008 1 20000414 G 5260 50430043619 CHANNEL BEECH 100 B100 1152919 CE CABIN DOOR CORRODED B K NONE O OTHER IN INSP/MAINT 1 EA 17 400AC BE12 CABIN DOOR WAS OPENED FOR ACCESS TO AIRCRAFT. THE CHANNEL, WHICH FORMS THE BOTTOM OF THE DOOR AND ATTACHES TO THE DOOR H INGE, FAILED AT ITS AFT END. UPON INSPECTION, THE CHANNEL WAS FOUND TO HAVE INITIAL CORROSION, (INSIDE THE DOOR STRUCTU RE) DUE TO THE SEALED NATURE OF THE DOOR, NO DRAIN HOLE IS POSSIBLE AT THIS LOW SPOT. (X) 1 L 7 2 4T A14CE 2001013000032 20010130 00032 CE 2001 1 30 20000531SH009 1 20000531 G 5220 08112189 CABLE CESSNA 310 310R 2074245 CE EMERGENCY EXIT BROKEN B K NONE O OTHER IN INSP/MAINT 1 EA 07 4FA 310R0700 THE CABLE WHICH IS INSTALLED IN THE LEFT FRAMEWORK AROUND THE EMERGENCY EXIT WAS FRAYED IN TWO PIECES, ONE OF WHICH WAS BROKEN IN TWO. THERE ARE FIVE PINS THAT ATTACH TO THE CABLE WHICH HOLD THE EMERGENCY WINDOW IN PLACE. ONLY TWO PINS WE RE HOLDING THE WINDOW IN PLACE. TWO PINS WERE BROKEN OFF AND ONE PIN WAS MISSING. THIS ITEM IS NOT USUALLY CHECKED DUR ING ANNUAL INSPECTION. THE TWO PINS THAT WERE STILL INSTALLED ACCIDENTALLY CAME OUT THE WINDOW, CAME OUT IN-FLIGHT. (X ) 1 L 7 2 3O 3A10 2001013000033 20010130 00033 2001 1 30 20000531SH010 4 20000531 G 6122 626737 COLLAR CESSNA 340 340A 2076405 CE CONT O520 TSIO520NB 17040 SO CRANKSHAFT SCORED B JZRR K NONE O OTHER NR NOT REPORTED 1 EA 07 5343J 70 340A0416 504283 PROPELLER FEATHERING AT HIGH RPM''S. OIL TRANSFER COLLAR WAS SCORED CAUSING INSUFFICIENT OIL PRESSURE BETWEEN COLLAR AN D CRANKSHAFT PILOT SHAFT. RECOMMEND DESIGN CHANGE ON TRANSFER COLLAR, OR CRANKCASE MODIFICATION TO ALLOW REPLACEMENT OF LEFT HALF OF COLLAR INSTEAD OF ENGINE DISASSEMBLY. (X) 1 L 7 2 3O 3 O 3A25 E8CE 2001020500058 20010205 00058 CE 2001 2 5 20000531SH012 1 20000512 G 3230 95001260102 HOSE CESSNA 421 421C 2076016 CE LANDING GEAR RUPTURED D A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 EA 21 49TD 421C0025 WHILE AT 13,000 FEET, PILOT NOTICED HYDRAULIC ANNUNCIATOR FLICKERING. WITHIN 2-3 MINUTES, PILOT HAD COMPLETE HYDRAULIC FAILURE. PILOT DEPLOYED LANDING GEAR IMMEDIATELY AND STARTED DESCENT. HE GOT 3 GREEN AND CONTINUED DOWN. LANDED WITH NO MISHAP. UPON INSPECTION, FOUND ACTUATOR UP, HOSE RUPTURED. PART WAS REPLACED WITH NEW PART. (X) 1 L 7 2 3O A7CE 2001020100001 20010201 00001 NE 2001 2 1 20000531SH013 1 20000509 G 6210 7615009100052 BLADE SKRSKY S76 S76B 8143007 NE MAIN ROTOR DELAMINATED B CW1R K NONE O OTHER IN INSP/MAINT 1 EA 11 780P 3615 760359 DURING POST-FLIGHT, TECHNICIAN NOTED A LARGE CRACK OR DELAMINATION OF THE INBOARD ROTOR BLADE STARTING ABOUT 20 INCHES F ROM THE ROOF ON THE TRAILING EDGE, EXTENDING ABOUT 5 INCHES LENGTHWISE, THEN DIAGONALLY TO JUST BEHIND THESPAR AND THEN LENGTHWISE ABOUT 12 INCHES. CAUSE IS UNDER INVESTIGATION. (X) 1 G 7 2 4U H1NE 2000082200005 20000822 00005 SW 2000 8 22 20000531SH014 1 20000502 G 8100 633358 CLAMP MOONEY M20 M20K 5870220 SW CONT O360 TSIO360GB 17025 SO EXHAUST OUTLET BROKEN H K NONE O OTHER IN INSP/MAINT 1 SW 07 231BT 1 TSO0100014 250122 309127 TURBO CLAMP THAT ATTACHES EXHAUST PIPE TO TURBO BROKE. CLAMP WAS SAFTIED AROUND BOLT. BREAK OCCURRED SOMEWHERE ON CLAM P. POSSIBLE SEPARATION WHERE SPOT-WELD HOLDS BOLT IN PLACE. (X) 1 L 7 1 3O 3 O 2A3 E9CE 2000082200006 20000822 00006 GL 2000 8 22 20000531SH015 3 20000508 G 6114 D4883C55 HUB MCAULY BEECH 55 D55 1152730 CE CONT O520 IO520C 17032 SO MCAULY 2AF34C 2AF34C55 GL CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 819MC 360 TE600 740405 RELEVANT ET INDICATION, CRACK OUTER MOST THREAD, BOTH SIDES. (X) 1 L 7 2 3O 3 O 3A16 E5CE 5 C P5EA 2000082200007 20000822 00007 GL 2000 8 22 20000531SH016 3 20000509 G 6110 D3156 COUNTERWEIGHT MCAULY BEECH 55 D55 1152730 CE CONT O520 IO520C 17032 SO MCAULY 2AF34C 2AF34C55 GL CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 11 819MC TE600 740405 CRACK INDICATION BETWEEN BOLT ATTACHING HOLES. (X) 1 L 7 2 3O 3 O 3A16 E5CE 5 C P5EA 2000082200008 20000822 00008 GL 2000 8 22 20000531SH017 3 20000511 G 6114 HUB MCAULY BEECH 35 V35 1151538 CE CONT O520 IO520B 17032 SO MCAULY 2A36C 2A36C23 GL CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 1500 661474 EDDY CURRENT AND PENETRANT TESTING INDICATION IN THREAD AREA. (X) 1 L 7 1 3O 3 O 3A15 E5CE 5 C P880 2000082200009 20000822 00009 GL 2000 8 22 20000531SH018 3 20000511 G 6110 C2463 NUT MCAULY BEECH 35 V35 1151538 CE CONT O520 IO520B 17032 SO MCAULY 2A36C 2A36C23 GL FAILED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 1500 661474 PENETRANT TESTING INDICATION IN O-RING AREA. (X) 1 L 7 1 3O 3 O 3A15 E5CE 5 C P880 2000082200010 20000822 00010 2000 8 22 20000531SH019 4 20000510 G 6122 A20609 LEVER MCAULY GOV CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 763256 RELEVANT CRACK INDICATION AT THE RETENTION AREA. (X) 2000082200011 20000822 00011 SO 2000 8 22 20000531SH020 2 20000504 G 7310 PRIMER LINE BEECH 35 E35 1151512 CE CONT E225 E2258 17015 SO CLAMPING AREA CRACKED B K2YR K NONE K FLUID LOSS IN INSP/MAINT 1 EA 21 7382B 1549 D3845 35681D98R AT CYLINDER REPLACEMENT, FOUND PRIMER LINES NR 1, NR 3 CYLINDERS CRACKED (3/4 AROUND) UNDER ADEL CLAMP AREA. EVIDENCE OF FATIGUE AND CORROSION. (X) 1 L 7 1 3O 3 O A777 E267 2000082200012 20000822 00012 SO 2000 8 22 20000531SH021 2 20000504 G 8530 23509 CYLINDER CESSNA 150 150H 2071818 CE CONT O200 O200A 17020 SO ROCKER ARM BOSSE BROKEN B K2YR A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CR CRUISE 1 EA 21 563G 3246 245 15068275 680677A OWNER STATED ENGINE BEGAN RUNNING ROUGH. DEVIATED TO NEAREST AIRPORT. HAD TO KEEP PUMPING THROTTLE TO MAINTAIN ENGINE RUNNING. MADE PRECAUTIONARY LANDING AT AIRPORT. UPON COLD CYLINDER CHECK, REMOVED CYLINDER ROCKER BOSS COVER. PIN AND BOSSES FELL OUT. NEW AND OLD CRACKS EVIDENT. SUBMITTER STATED AD 94-05-05R1 PERTAINS TO THIS. (X) 1 H 7 1 3O 3 O 3A19 E252 2000062000125 20000620 00125 SO 2000 6 20 20000531SH022 2 20000504 G 8530 536727 CYLINDER BEECH 35 E35 1151512 CE CONT E225 E2258 17015 SO BARREL SEPARATED B K2YR K NONE O OTHER IN INSP/MAINT 1 EA 21 7382B 1548 752 D3845 35681D98R AT ANNUAL INSPECTION, FOUND SIGNS OF SEEPAGE AT BARREL (INDICATIONS OF BARREL SEPARATING FROM HEAD) IN NR 4, NR 5, NR 6 CYLINDERS. POSSIBLE CAUSE IS AGE ON CYLINDERS AND TIME IN SERVICE. (X) 1 L 7 1 3O 3 O A777 E267 2000062000126 20000620 00126 GL 2000 6 20 20000531SH023 3 20000509 G 6110 C5270 BEARING MCAULY CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO MCAULY 3AF32C 3AF32C505 GL GROOVED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 CTEXT 369 931446 RELEVANT INDICATION IN BEARING GROOVE. (X) 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2000062000133 20000620 00133 SW 2000 6 20 20000601SH002 1 20000216 G 5302 206030446001F BULKHEAD BELL BELL 206 206B 1181511 SW TAIL BOOM CRACKED C K NONE O OTHER IN INSP/MAINT 1 SO 19 914HH 8345 2297 PART IN QUESTION IS LOCATED ON THE AFT MOST SECTION ON THE HELICOPTER TAIL BOOM. THE TAIL ROTOR GEARBOX AFT MOUNT STUDS PASS THROUGH THE TOP OF THIS FITTING ON THE LEFT AND RIGHT SIDES. CRACKS DEVELOPED FROM THESE STUD HOLES TO ADJACENT M OUNTING RIVET HOLES. ALSO, CRACKS WERE NOTED ON THE TOP SIDE OF THIS FITING THAT WERE NOT VISIBLE WITH FITTING INSTALLE D. CRACKS WERE FOUND DURING NORMAL 100-HOUR INSPECTION. POSSIBLE CAUSE CAN BE UNDER OR OVER TORQUING OF INSTALLATION H ARDWARE, OR EXCESSIVE TAIL ROTOR VIBRATIONS. (X) 1 G 7 1 3U H2SW 2000062000134 20000620 00134 SO 2000 6 20 20000601SH004 1 20000204 G 7800 HEADER PIPER PA23 PA23250 7102308 SO EXHAUST FAILED H K NONE O OTHER IN INSP/MAINT 1 EA 17 6913A 2000 277954108 DURING POST-FLIGHT INSPECTION FOUND EXHAUST HEADER BLOW-OUT OCCURRED AT HEAT EXCHANGER SHROUD INSIDE SHROUD AT CROSSOVER PIPE DIRECTING EXHAUST AT FUEL HOSE AND CONTROL. (X) 1 L 7 2 3O 1A10 2000062100122 20000621 00122 CE 2000 6 21 20000601SH005 1 20000601 G 3150 ANNUNCIATOR BEECH 90 C90A 1152911 CE CABIN WILL NOT TEST H O OTHER O OTHER NR NOT REPORTED 1 NM 11 2354Y 365 LJ1532 A/P TRIM FAILED, CABIN ALT HIGH, AND CABIN DOOR ANNUNCIATOR LIGHTS INTERMITTENT IN ANNUNCIATOR TEST POSITION. FOUND GRO UNDING WIRE WRAPPED AROUND POSTS, BUT NOT SOLDERED. (X) 1 L 7 2 3T RT 3A20 2000062000135 20000620 00135 SO 2000 6 20 20000601SH006 1 20000509 G 2410 75536 BUSHING LYC PIPER PA31 PA31P 7103120 SO LYC O541 TIGO541E1A 41539 EA FAILED B PAIR O OTHER O OTHER CR CRUISE 1 SO 05 61CG 31P30 L47262 PILOT EXPERIENCED ALTERNATOR FAILURE ON LT ENGINE IN-FLIGHT. UPON INSPECTION AFTER LANDING, FOUND LT SIDE OF AIRCRAFT CO VERED IN OIL AND LT ALTERNATOR LYING INSIDE OF COWLING. SUBMITTER SUSPECTED FAILURE OF GENERATOR ADAPTER ASSY BUSHING PN 75539 CAUSED MISALIGNMENT OF ALT DRIVESHAFT WHICH CAUSED COUPLING PN LW-14464 TO FAIL IN SUCH A MANNER THAT CAUSED AL TERNATOR ADAPTER ASSY PN LW-10259 TO FAIL. (X) 1 L 7 2 3O 3 O A8EA E19EA 2000062000136 20000620 00136 CE 2000 6 20 20000601SH007 1 20000505 G 3221 24130023 ATTACH FITTING CESSNA 172 172RG 2072438 CE NOSE LANDING GEA CRACKED G HO1R K NONE O OTHER IN INSP/MAINT 1 EA 21 4914V 11971 172RG0414 REPAIR STATION DISCOVERED, WHILE INSPECTING THE NOSE LANDING GEAR DURING AN ANNUAL INSPECTION, THE NOSE LANDING GEAR RET RACTION ACTUATOR ATTACH FITTING WAS FOUND CRACKED FROM THE LOWER LEFT INNER BOLT HOLE TO THE OUTER EDGE OF THE FITTING. THE CRACK WAS APPROX ONE INCH IN LENGTH. ALL OF THE LOWER ATTACHING BOLTS WERE FOUND LOOSE. SUBMITTER SUSPECTED THE C RACK RESULTED DUE TO LOOSENING OF THE LOWER ATTACHING BOLTS. THESE BOLTS SHOULD BE INSPECTED FOR PROPER TORQUE EVERY 10 0 HOURS OR ANNUAL INSPECTION. AIRCRAFT TT: 11,971.1 HOURS. (X) 1 H 7 1 3O 3A17 2000082200013 20000822 00013 CE 2000 8 22 20000601SH008 1 20000601 G 5713 STRINGER BEECH 200 B200 1152922 CE TAIL CRACKED B K NONE O OTHER IN INSP/MAINT 1 NE 05 86DD 6865 BB1171 COMPLIED WITH AD 93-25-07 IAW SD 2472. NR 10 STRINGER ON THE LEFT SIDE WAS FOUND CRACKED. TOTAL LANDINGS: 7,189. (X) 1 L 7 2 4T A24CE 2000062000137 20000620 00137 2000 6 20 20000601SH009 4 20000522 G 3120 S17111 PRESSURE SWITCH CESSNA 150 152 2071835 CE CABIN LEAKING D K NONE K FLUID LOSS IN INSP/MAINT 1 SO 05 65468 2158 15281569 DURING ROUTINE MAINTENANCE, OIL WAS FOUND ON RIGHT SIDE INBOARD RUDDER PEDAL. FURTHER INVESTIGATION SHOWED OIL WEEPING FROM AROUND CRIMPED HOUSING OF HOURMETER PRESSURE SWITCH. THIS PROBLEM COULD LEAD TO ERRONEOUS READINGS ON OIL PRESSURE GAUGE AND BURNS TO PASSENGERS FEET AND LEGS IF SWITCH WAS TO RUPTURE. SUBMITTER RECOMMENDED CLOSER INSPECTIONS OF THES E SWITCHES DURING INSPECTIONS AND ROUTINE MAINTENANCE. (X) 1 H 7 1 3O NT 3A19 2001020100002 20010201 00002 WP 2001 2 1 20000601SH010 1 20000517 G 6210 5320003 BLADE HILLER UH12 UH12E 4360122 WP MAIN ROTOR DELAMINATED B KQTR K NONE O OTHER IN INSP/MAINT 1 SW 11 144HA 246 HA3044 BLADE WAS RETURNED TO BLADE SHOP FOR REPAIR OF SKIN TO TRAILING EDGE DISBOND. UPON INSPECTION, APPEARS THAT CLEANING AN D/OR METAL PREP PROCESS FAILED CAUSING SKIN AND TRAILING EDGE TO SEPARATE. SUBMITTER RECOMMENDED INSPECTING ALL BLADES IN METAL PREP BATCH FOR POSSIBLE SKIN SEPARATIONS IN FUTURE. (X) 1 G 7 1 3O 4H11 2001020200002 20010202 00002 SW 2001 2 2 20000601SH012 1 20000322 G 3411 206070895033 STATIC LINE BELL 206 206B 1181511 SW PITOT SYS FAILED D O OTHER O OTHER NR NOT REPORTED 1 SW 09 57499 3086 PILOT REPORTED AIRSPEED INDICATED LOW AT CRUISE. FOUND THAT LANDING LIGHT CHAFED A HOLE IN THE PITOT STATIC LINE (IPC RE F: FIG 95-7, PAGE 28 ITEM 16). REPLACED TUBE AND REPOSITIONED AS NOT TO CHAFE. (X) 1 G 7 1 3U H2SW 2000062000138 20000620 00138 SW 2000 6 20 20000601SH013 1 20000510 G 2711 2709 HINGE BBAVIA 7 7GCAA 21101N8 SW BOTTOM TAB BROKEN D K NONE O OTHER IN INSP/MAINT 1 NE 01 2665Z 1877 35178 DURING WINDS OF APPROX 40 KNOTS, AILERON HINGE THAT ATTACHES TO CONTROL ROD TORE LOOSE FROM INBOARD END OF AILERON. FURT HER INVESTIGATION REVEALED THAT HINGE TABS, TOP AND BOTTOM, THAT ARE RIVETED ONTO SPAR CAPS HAD BROKEN PREVIOUSLY. THIS EVIDENCED BY THE STEEL HINGE BEING RUSTED AT THE BREAK. THIS CONDITION IS NOT READILY NOTICED DURING ROUTINE INSPECT ION DUE TO THE FACT THE HINGE TAPS ARE COVERED WITH FABRIC AND FINISH. (X) 1 H 7 1 3O A759 2000062000139 20000620 00139 GL 2000 6 20 20000601SH017 2 20000503 G 7250 FABT8851 TURBINE GE CF6 CF6* 30020 GL STACKING BOLTS MISINSTALLED B SK33 K NONE O OTHER IN INSP/MAINT 1 GL 03 3124 327 CF6-6 ENGINE 451-327 WAS PULLED FOR OVERHAUL AT GE. FOUND TO BE MISSING THE LOCKWIRES FROM THE STACKING BOLTS TO THE TU RBINE IN EACH OF 8 POSITIONS. SUBMITTER STATED FURTHER INVESTIGATION FOUND STACKING CALCULATION ERROR ON THIS AND 26 OT HER CF6-6 TMF ASSEMBLIES. (X) 4 F E23EA 2000062000140 20000620 00140 CE 2000 6 20 20000601SH018 1 20000425 G 2810 993800007 FUEL CELL BEECH 99 99A 1154003 CE PWA PT6 PT6A27 52043 EA RT NACELLE PUNCTURED A TIMA K NONE K FLUID LOSS IN INSP/MAINT 1 NM 07 99GH 33344 U112 RIGHT NACELLE FUEL CELL FOUND LEAKING FUEL. INSPECTION REVEALED A PUNCTURE IN THE SIDE OF THE CELL CAUSED BY A TANK HAN GER THAT HAD BECOME DISLODGED FROM ITS ORIGINAL LOCATION. THE HANGER PROTRUDING CLIP HAD REPOSITIONED TOWARD THE TANK L INER CAUSING THE TANK TO BE PUNCTURED AS THE FUEL LEVEL INCREASED. DURING INITIAL INSTALL OF FUEL CELL, SUBMITTER STATE D CARE SHOULD BE TAKEN TO VERIFY PROPER SEATING OF THE CELL HANGERS TO PREVENT THIS FROM RECURRING. (CELL DATED 1979 AN D OTHERWISE APPEARED IN GOOD CONDITION). (X) 1 L 7 2 3T 4 T A14CE E4EA 2000062000141 20000620 00141 EA 2000 6 20 20000601SH019 2 20000518 G 7414 M3333 IMPULSE COUPLING SLICK PIPER PA32 PA32300 7103212 SO LYC O540 IO540K1G5 41532 EA PAWL-PLATE RIVET DESTROYED B JM2R O OTHER O OTHER IN INSP/MAINT 1 EA 13 323CA 309 96051744 327740026 L1741148A PAWL-PLATE RIVETS BROKE. IMPULSE HOUSING PAWL STEPS BROKEN OFF. IMPULSE COUPLING FAILED AT START-UP. CAUSE UNKNOWN. (X) 1 L 7 1 3O 3 O A3SO 1E4 2000062000142 20000620 00142 CE 2000 6 20 20000601SH020 1 20000515 G 5720 0001101122 GUSSET BEECH 90 C90 1152913 CE BS 160.00 WS 110 CRACKED B UA2R K NONE O OTHER IN INSP/MAINT 1 SW 15 16 LJ893 RIGHT LOWER OUTBOARD WING HAD CRACK IN DOUBLER AT FORWARD ATTACH POINT AND GUSSET CRACKED AT APPROX BS 160.00 AND WS 110 .11. TWO CRACKS IN WING SKIN RIGHT WING 4 INCHES BEHIND FORWARD SPAR JUST AFT OF FORWARD WING BOLT ON TOP SIDE OF WING. TWO CRACKS IN WING SKIN ON LEFT WING JUST AFT OF FORWARD SPAR BEHIND FORWARD WING BOLT ON TOP SIDE OF WING. (X) 1 L 7 2 3T 3A20 2000062000155 20000620 00155 CE 2000 6 20 20000601SH022 1 20000601 G 5740 50110231 FITTING CESSNA 414 414A 2075907 CE LEFT AFT CORRODED B GN1R K NONE O OTHER IN INSP/MAINT 1 NE 01 6672C 6667 414A0053 ON ANNUAL INSPECTION, LT WING AFT SPAR WING ATTACH FITTINGS, PN''S 5011023-1 AND 5-11024-1, INTERGRANULAR CORROSION FOUN D IN AREAS READILY VISIBLE EACH AREA OF CORROSION APPROXIMATELY 1.50 SQUARE INCH AND APPROXIMATELY .1250 INCH DEEP. NO IDEA ON SPECIFIC CAUSE. NOT IN DIRECT AREA OF EXHAUST. SUBMITTER COMMENDED DETAILED VISUAL INSPECTION TO PREVENT RECU RRANCE. FITTINGS CHANGED WITH NEW PARTS. (X) 1 L 7 2 3O A7CE 2000071200009 20000712 00009 NM 2000 7 12 20000601SH027 1 20000314 G 6710 900C2010214101 LINK ROD DOUG MD900 MD900 3027375 NM M/R CONTROL WORN A R7MA K NONE O OTHER IN INSP/MAINT 1 NM 07 901CF 352 90000012 PITCH LINK ASSEMBLY WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U NC H19NM 2000071200010 20000712 00010 NM 2000 7 12 20000601SH028 1 20000306 G 6322 900D1400526101 BLOWER DOUG MD900 MD900 3027375 NM DRIVE UNIT LEAKING A R7MA K NONE K FLUID LOSS IN INSP/MAINT 1 NM 07 901CF 217 90000012 BLOWER DRIVE ASSEMBLY LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U NC H19NM 2000071200011 20000712 00011 NM 2000 7 12 20000601SH029 1 20000314 G 6230 900C2010183107 SCISSORS DOUG MD900 MD900 3027375 NM MAIN ROTOR LOOSE A R7MA K NONE O OTHER IN INSP/MAINT 1 NM 07 901CF 864 90000012 LINK ASSY, DRIVE, SCISSORS HAD EXCESSIVE PLAY IN JOINT AREA. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U NC H19NM 2001020500061 20010205 00061 SO 2001 2 5 20000602SH002 2 20000512 G 8520 649134 CRANKSHAFT CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO ENGINE UNSERVICEABLE B CY4R K NONE O OTHER IN INSP/MAINT 1 AL 03 2216F 66 U20606504 814988R PER TCM MSB 00-5, CRANKSHAFT WAS REJECTED BY TELEDYNE CONTINENTAL MOTORS. (X) 1 H 7 1 3O 3 O A4CE E5CE 2001020500085 20010205 00085 SO 2001 2 5 20000602SH003 2 20000512 G 8520 649141 CRANKSHAFT CESSNA 180 180A 2072604 CE CONT O470 O470R 17026 SO ENGINE UNSERVICEABLE B CY4R K NONE O OTHER IN INSP/MAINT 1 AL 03 4UA 89 32851 833782R PER TCM MSB 00-5, CRANKSHAFT WAS REJECTED BY TELEDYNE CONTINENTAL MOTORS. (X) 1 H 7 1 3O 3 O 5A6 E273 2001020500086 20010205 00086 SO 2001 2 5 20000602SH004 2 20000508 G 8520 649134 CRANKSHAFT CESSNA 206 U206E 2073350 CE CONT O520 IO520F 17032 SO ENGINE UNSERVICEABLE B CY4R K NONE O OTHER IN INSP/MAINT 1 AL 03 4447Z 193 U2061479 574357 PER TELEDYNE CONTINENTAL MOTORS MSB 00-5, CRANKSHAFT WAS REJECTED BY TELEDYNE CONTINENTAL MOTORS. (X) 1 H 7 1 3O 3 O A4CE E5CE 2000062000156 20000620 00156 SO 2000 6 20 20000602SH005 2 20000508 G 8520 649134 CRANKSHAFT CESSNA 180 180 2072602 CE CONT O470 O470K 17026 SO ENGINE DAMAGED B CY4R K NONE O OTHER IN INSP/MAINT 1 AL 03 9028C 1 31076 049406R PER TCM MSB 00-5, CRANKSHAFT WAS REJECTED BY TELEDYNE CONTINENTAL MOTORS. (X) 1 H 7 1 3O 3 O NC 5A6 E273 2001020500176 20010205 00176 SO 2001 2 5 20000602SH006 2 20000502 G 8520 649134 CRANKSHAFT CESSNA 185 A185F 2072821 CE CONT O520 IO520D 17032 SO ENGINE UNSERVICEABLE B CY4R K NONE O OTHER IN INSP/MAINT 1 AL 03 6688H 136 18503335 1580456D PER TCM MSB 00-5, CRANKSHAFT WAS REJECTED BY TELEDYNE CONTINENTAL MOTORS. (X) 1 H 7 1 3O 3 O 3A24 E5CE 2001020500087 20010205 00087 CE 2001 2 5 20000602SH007 1 20000419 G 2170 MOTOR BEECH 200 B200 1152922 CE CONDENSOR INOPERATIVE B DINR K NONE O OTHER NR NOT REPORTED 1 EA 13 260G 738 BB1525 CONDENSER BLOWER MOTOR NO GOOD. 1 L 7 2 4T A24CE 2001020200003 20010202 00003 SW 2001 2 2 20000602SH009 1 20000523 G 7722 407375001105 INDICATOR BELL 407 407 SW MGT MALFUNCTIONED B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 407SD 510 53330 H.A.S. REPLACED WITH NEW MGT INDICATOR FROM BELL HELICOPTER. (X) 1 G 7 1 3U O H2SW 2001020200004 20010202 00004 SW 2001 2 2 20000602SH010 1 20000523 G 7933 407375004101 INDICATOR BELL 407 407 SW OIL PRESS TEMP MALFUNCTIONED B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 09 407SD 510 53330 H.A.S. REPLACED WITH NEW OIL PRESSURE TEMPERATURE INDICATOR FROM BELL HELICOPTER. (X) 1 G 7 1 3U O H2SW 2001030100002 20010301 00002 SW 2001 3 1 20000602SH011 1 20000519 G 6220 407010150105A FRAHM BELL 407 407 SW MAIN ROTOR HEAD DAMAGED B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 98VG 425 53171 SPRING ROTATED RUBBER BUMPER MISSING FROM MAIN ROTOR HEAD. H.A.S. REPLACED WITH NEW FRAHM FROM BELL HELICOPTER. (X) 1 G 7 1 3U O H2SW 2001020500088 20010205 00088 WP 2001 2 5 20000602SH012 1 20000525 G 3246 152059 WHEEL DOUG DC8 DC8* WP MLG CRACKED B INWR K NONE O OTHER IN INSP/MAINT 1 SO 19 NDT INSPECTION SHOWED CRACK INDICATIONS AT SPOKE AREA. (X) 2 L 7 4 4J F 4A25 2001011601506 20010116 01506 EU 2001 1 16 20000605SH001 1 20000121 G 6510 593404 BEARING SNIAS 350 AS350B3 8680954 EU TAIL ROTOR WORN A R7MA K NONE O OTHER IN INSP/MAINT 1 NM 07 103LN 400 3128 BEARING WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001011601300 20010116 01300 EU 2001 1 16 20000605SH002 1 20000420 G 6410 704A33633171 LAMINATED HINGE SNIAS 350 AS350B3 8680954 EU TAIL ROTOR WORN A R7MA K NONE O OTHER IN INSP/MAINT 1 NM 07 103LN 524 3128 ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001011601301 20010116 01301 EU 2001 1 16 20000605SH003 1 20000420 G 6220 117775P BALL JOINT SNIAS 350 AS350B3 8680954 EU STARFLEX WORN A R7MA K NONE O OTHER IN INSP/MAINT 1 NM 07 103LN 524 3128 TEFLON LINERS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001011601302 20010116 01302 EU 2001 1 16 20000605SH004 1 20000420 G 6720 350A33214501 CONTROL ROD SNIAS 350 AS350B3 8680954 EU T/R PITCH WORN A R7MA K NONE O OTHER IN INSP/MAINT 1 NM 07 47MA 524 3129 PITCH CONTROL ROD WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001011601303 20010116 01303 EU 2001 1 16 20000605SH005 1 20000506 G 7921 1184961 COOLER SNIAS 350 AS350B3 8680954 EU OIL SYSTEM LEAKING A R7MA K NONE K FLUID LOSS IN INSP/MAINT 1 NM 07 104LN 761 3134 OIL COOLER LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001011601304 20010116 01304 EU 2001 1 16 20000605SH006 1 20000205 G 6710 350A33214501 CONTROL ROD SNIAS 350 AS350B3 8680954 EU T/R PITCH WORN A R7MA K NONE O OTHER IN INSP/MAINT 1 NM 07 104LN 33 3134 PITCH CONTROL ROD WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001012900074 20010129 00074 EU 2001 1 29 20000605SH007 1 20000122 G 6720 350A33214501 ROD SNIAS 350 AS350B3 8680954 EU PITCH CONTROL WORN A R7MA K NONE O OTHER IN INSP/MAINT 1 NM 07 104LN 488 3134 PITCH CONTROL ROD WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001012900076 20010129 00076 EU 2001 1 29 20000605SH009 1 20000405 G 6520 350A33215001 BEARING SNIAS 350 AS350B2 8680813 EU T/R ROD END WORN A R7MA K NONE O OTHER IN INSP/MAINT 1 NM 07 101LN 692 3038 ROD END WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001012900077 20010129 00077 EU 2001 1 29 20000605SH010 1 20000330 G 6220 117775P BALL JOINT SNIAS 350 AS350B2 8680813 EU STARFLEX WORN A R7MA K NONE O OTHER IN INSP/MAINT 1 NM 07 101LN 145 3038 STARFLEX BALL JOINT - TEFLON LINERS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001012900078 20010129 00078 EU 2001 1 29 20000605SH011 1 20000226 G 7931 350A67402301AA CONNECTOR SNIAS 350 AS350B2 8680813 EU OIL PRESS IND DAMAGED A R7MA K NONE O OTHER IN INSP/MAINT 1 NM 07 102LN 605 3065 HARNESS INDICATOR, ENGINE OIL PRESSURE HAD INTERNAL SHORT. ENGINE OIL PRESSURE FLUCTUATED. REPLACED WITH NEW UNIT, COR RECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001012900079 20010129 00079 EU 2001 1 29 20000605SH012 1 20000211 G 6520 350A33214501 ROD SNIAS 350 AS350B2 8680813 EU PITCH CONTROL WORN A R7MA K NONE O OTHER IN INSP/MAINT 1 NM 07 102LN 586 3065 PITCH CONTROL ROD WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001012900080 20010129 00080 EU 2001 1 29 20000605SH013 1 20000108 G 6410 704A33633171 LAMINATED HINGE SNIAS 350 AS350B2 8680813 EU TAIL ROTOR WORN A R7MA K NONE O OTHER IN INSP/MAINT 1 NM 07 102LN 543 3065 ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001012900081 20010129 00081 EU 2001 1 29 20000605SH014 1 20000329 G 6520 350A33200406 SPIDER SNIAS 350 AS350D 8680803 EU TAIL ROTOR STUCK A R7MA K NONE O OTHER IN INSP/MAINT 1 NM 07 350RM 48 1024 PITCH CHANGE, SPIDER ASSEMBLY - STICKS ON PEDAL MOUNT. BEARING HAS EXCESS PLAY. REPLACED WITH NEW UNIT, CORRECTED PROB LEM. (X) 1 G 7 1 3U H9EU 2001012900082 20010129 00082 EU 2001 1 29 20000605SH015 1 20000326 G 6410 704A33633171 LAMINATED HINGE SNIAS 350 AS350B 8680801 EU TAIL ROTOR WORN A R7MA K NONE O OTHER IN INSP/MAINT 1 NM 07 5771C 621 1369 LAMINATED HINGE, ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001012900083 20010129 00083 EU 2001 1 29 20000605SH016 1 20000512 G 6410 704A33633116 BEARING SNIAS 350 AS350D1 8680804 EU TAIL ROTOR WORN A R7MA K NONE O OTHER IN INSP/MAINT 1 NM 07 57731 317 1434 LAMINATED TAIL BEARING, ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001012900084 20010129 00084 EU 2001 1 29 20000605SH017 1 20000130 G 6410 704A33633171 LAMINATED HINGE SNIAS 350 AS350B2 8680813 EU TAIL ROTOR WORN A R7MA K NONE O OTHER IN INSP/MAINT 1 NM 07 6099P 599 2818 LAMINATED HINGE, ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001012900085 20010129 00085 EU 2001 1 29 20000605SH018 1 20000301 G 6410 704A33633116 BEARING SNIAS 350 AS350B2 8680813 EU TAIL ROTOR WORN A R7MA K NONE O OTHER IN INSP/MAINT 1 NM 07 96LG 525 2817 LAMINATED TAIL BEARING, ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001012900086 20010129 00086 EU 2001 1 29 20000605SH019 1 20000207 G 6220 117775P BALL JOINT SNIAS 350 AS350B2 8680813 EU STARFLEX WORN A R7MA K NONE O OTHER IN INSP/MAINT 1 NM 07 96LG 817 2817 BALL JOINT, STARFLEX - TEFLON LINERS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001012900087 20010129 00087 EU 2001 1 29 20000605SH020 1 20000207 G 6220 126891P BALL JOINT SNIAS 350 AS350B2 8680813 EU STARFLEX WORN A R7MA K NONE O OTHER IN INSP/MAINT 1 NM 07 96LG 708 2817 BALL JOINT, RIGHT THREAD, WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001012900088 20010129 00088 EU 2001 1 29 20000605SH021 1 20000301 G 6410 704A33633171 LAMINATED HINGE SNIAS 350 AS350B2 8680813 EU TAIL ROTOR WORN A R7MA K NONE O OTHER IN INSP/MAINT 1 NM 07 96LG 725 2817 LAMINATED HINGE, ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001012900057 20010129 00057 EU 2001 1 29 20000605SH022 1 20000130 G 6420 704A33633116 BEARING SNIAS 350 AS350B2 8680813 EU TAIL ROTOR WORN A R7MA K NONE O OTHER IN INSP/MAINT 1 NM 07 93LG 349 2654 LAMINATED TAIL BEARING - ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001012900089 20010129 00089 EU 2001 1 29 20000605SH023 1 20000228 G 6420 704A336333116 BEARING SNIAS 350 AS350B2 8680813 EU TAIL ROTOR WORN A R7MA K NONE O OTHER IN INSP/MAINT 1 NM 07 94LG 647 2728 LAMINATED TAIL BEARING - ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001012900090 20010129 00090 EU 2001 1 29 20000605SH024 1 20000127 G 7714 614764021 TACHOMETER SNIAS 350 AS350B2 8680813 EU COCKPIT INTERMITTENT A R7MA O OTHER O OTHER NR NOT REPORTED 1 NM 07 94LG 158 2728 TACHOMETER INDICATOR INOPERATIVE. NR NEEDLE DROPS OFF TO 250 RPM INTERMITTENTLY. REPLACED WITH NEW UNIT, CORRECTED PRO BLEM. (X) 1 G 7 1 3U H9EU 2000062300050 20000623 00050 EU 2000 6 23 20000605SH025 1 20000228 G 6410 704A33633171 LAMINATED HINGE SNIAS 350 AS350B2 8680813 EU TAIL ROTOR WORN A R7MA O OTHER O OTHER IN INSP/MAINT 1 NM 07 94LG 647 2728 LAMINATED HINGE - ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001012900091 20010129 00091 EU 2001 1 29 20000605SH026 1 20000430 G 6410 704A33633171 LAMINATED HINGE SNIAS 350 AS350B2 8680813 EU TAIL ROTOR WORN A R7MA K NONE O OTHER IN INSP/MAINT 1 NM 07 92LG 427 2575 LAMINATED HINGE, ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2000061600413 20000616 00413 SO 2000 6 16 20000605SH030 1 20000605 G 5102 ENVELOPE BALWKS FIREFY FIREFLY11 1050125 SO FABRIC PNLS DETERIORATED H K NONE O OTHER IN INSP/MAINT 1 WP 07 3288H F11B001 EXCESSIVE AND PREMATURE DETERIORATION OF FABRIC PANELS AT GORE TAPE SEAM. GORE TAPE MATERIAL IS STIFF WITH SHARP EDGES AND CUTS INTO FABRIC PANELS WHERE PANELS OVERLAP TAPE APPROXIMATELY 1 INCH FROM PANEL EDGE. IT APPEARED THE AIRCRAFT MA NUFACTURER HAD CHANGED THE GORE TAPE MATERIAL FROM A SOFTER MORE PLIABLE TAPE TO A STIFF TAPE WITH SHARP EDGES. (X) 1 B 0 0 A14SO 2000061300423 20000613 00423 2000 6 13 20000607SH001 4 20000522 G 6122 B20268 FLYWEIGHT MCAULY GOV CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 74134 RELEVANT CRACK INDICATION ON BASE OF FLYWEIGHT DISC. (X) 2000061300424 20000613 00424 2000 6 13 20000607SH002 4 20000517 G 6122 C20908 FLYWEIGHT MCAULY CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 781399 RELEVANT CRACK INDICATION ON THE BASE OF FLYWEIGHT DISC. (X) 2000061600372 20000616 00372 2000 6 16 20000607SH003 4 20000516 G 6122 213908 FLYWEIGHT MCAULY CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 771223 RELEVANT CRACK INDICATION ON THE BASE OF FLYWEIGHT DISC. (X) 2000061400300 20000614 00300 GL 2000 6 14 20000607SH004 2 20000324 G 7322 FUEL CONTROL AMTR KR2 KR2 GL AMTRVW VW VW2200 99999 GL FAILED G A UNSCHED LANDING O OTHER CR CRUISE 1 WP 07 73BP 3634 FAILURE OF MAIN MIXTURE ADJUSTMENT NEEDLE LOCKING DEVICE DURING FLIGHT CAUSING MIXTURE TO GO RICH DRAMATICALLY INCREASIN G FUEL CONSUMPTION WHICH LED TO FUEL STARVATION AND A FORCED LANDING. (X) 1 L 7 1 3O 3 O EXPA1L71 EXP3O 2000061300425 20000613 00425 SO 2000 6 13 20000607SH005 1 20000525 G 3240 RFS2010 STATOR BFGOODRICH EMB 120 EMB120 3260201 SO NR 1 AND 2 DEFECTIVE B XC4R K NONE O OTHER IN INSP/MAINT 1 SO 19 1271 1477A BRAKE ASSEMBLY, PN 2-1585-R, FAILED PREMATURELY. NR 1 AND NR 2 STATORS CRACKED AT RELIEF HOLES. HEAT STACK WARPED UNEV EN WEAR. SUBMITTER STATED THIS IS A CONTINUAL DISCREPANCY. NOTE: RAPCO FLEET SUPPORT PARTS INSTALLED IN BRAKE ASSE MBLY. (X) 2 L 7 2 4T RT A31SO 2000061300426 20000613 00426 SO 2000 6 13 20000607SH006 1 20000525 G 3240 RFS2010 STATOR BFGOODRICH EMB 120 EMB120 3260201 SO NR 1 DEFECTIVE B XC4R K NONE O OTHER IN INSP/MAINT 1 SO 19 1395 0112A BRAKE ASSEMBLY, PN 2-1585-R, FAILED PREMATURELY. NR 1 STATOR WARPED BEYOND SERVICEABLE LIMITS. SUBMITTER STATED THIS I S A CONTINUAL DISCREPANCY. NOTE: RAPCO FLEET SUPPORT PARTS INSTALLED IN BRAKE ASSY. (X) 2 L 7 2 4T RT A31SO 2000062000220 20000620 00220 EU 2000 6 20 20000607SH009 1 20000516 G 5260 14860011 STEP AEROSP SA365 AS365N2 8680815 EU A/C ENTRANCE INOPERATIVE A O OTHER O OTHER IN INSP/MAINT 1 GL 09 365WM 6429 STEP ACTUATOR INOPERATIVE, INTERMITTENT. REMOVED AND REPLACED. (X) 1 G 7 2 3U RT H10EU 2000062900094 20000629 00094 NE 2000 6 29 20000607SH010 2 20000509 G 7314 9A2045 PUMP UROCOP EC135 EC135P1 8680990 EU PWA PW206 PW206B 0 NE A/C FUEL SYSTEM INTERMITTENT A R7MA K NONE O OTHER IN INSP/MAINT 1 NM 07 135SJ 761 EC1350054 UNIT OPERATES INTERMITTENTLY. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U 3 U O H88EU E42NE 2000062000221 20000620 00221 EU 2000 6 20 20000607SH011 1 20000229 G 6420 1053170023 BEARING BOLKMS BK117 BK117C1 5626025 EU TAIL ROTOR WORN A R7MA K NONE O OTHER IN INSP/MAINT 1 NM 07 117SU 378 7527 BEARING WORN BEYOND SERVICEABLE LIMITS. CORE SCRAPPED LOCALLY BY MECHANIC. REPLACED 2 EACH WITH NEW UNITS, CORRECTED P ROBLEM. (X) 1 G 7 2 3U NC H13EU 2000062000222 20000620 00222 EU 2000 6 20 20000607SH012 1 20000331 G 6420 1053170023 BEARING BOLKMS 117 BK117A4 5626017 EU TAIL ROTOR WORN A R7MA K NONE O OTHER IN INSP/MAINT 1 NM 07 911BY 446 7127 BEARING WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH2 EACH NEW UNITS, CORRECTED PROBLEM. (X) 1 G 7 2 3U H13EU 2000062700130 20000627 00130 EU 2000 6 27 20000607SH013 1 20000214 G 6320 IPT20RT1100080G TRANSMITTER BOLKMS 117 BK117B1 5626012 EU M/R TRANSMISSION FLUCTUATES A R7MA O OTHER O OTHER NR NOT REPORTED 1 NM 07 10UM 312 7231 PRESSURE TRANSMITTER UNIT CAUSES PRESSURE GAUGE TO FLUCTUATE. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U H13EU 2000061300428 20000613 00428 EU 2000 6 13 20000607SH014 1 20000410 G 6410 134616P BUSHING BOLKMS 117 BK117B1 5626012 EU WORN A R7MA K NONE O OTHER IN INSP/MAINT 1 NM 07 117BK 551 7229 BUSHING TEFLON LINERS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 2 EACH NEW UNITS, CORRECTED PROBLEM. (X) 1 G 7 2 3U H13EU 2000062300073 20000623 00073 EU 2000 6 23 20000607SH015 1 20000410 G 6410 134617P BUSHING BOLKMS 117 BK117B1 5626012 EU TAIL ROTOR UNSERVICEABLE A R7MA O OTHER O OTHER IN INSP/MAINT 1 NM 07 117BK 551 7229 BUSHING TEFLON LINERS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 2 EACH NEW UNITS, CORRECTED PROBLEM. (X) 1 G 7 2 3U H13EU 2000062300074 20000623 00074 EU 2000 6 23 20000607SH016 1 20000410 G 6420 1053170023 BEARING BOLKMS 117 BK117B1 5626012 EU TAIL ROTOR UNSERVICEABLE A R7MA O OTHER O OTHER IN INSP/MAINT 1 NM 07 117BK 551 7229 BEARING WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 2 EACH NEW UNITS, CORRECTED PROBLEM. (X) 1 G 7 2 3U H13EU 2000062700131 20000627 00131 EU 2000 6 27 20000608SH024 1 20000601 G 6520 350A33200406 SPIDER SNIAS 350 AS350B 8680801 EU TAIL ROTOR UNDERTORQUED B O OTHER O OTHER IN INSP/MAINT 1 SW 09 147BH 908 M577 1273 AFTER THE LAST FLIGHT OF THE DAY, INSP REVEALED TAIL ROTOR SPIDER ASSY LOSS OF TORQUE AT CASTELLATED NUT SECURING SPIDER ASSY. THIS FINDING PROMPTED REMOVAL AND REPLACEMENT OF SPIDER ASSY WITH SERVICEABLE COMPONENT. SPIDER ASSY P/N 350A33. 2004.06. TT IN SERVICE 186.6 FLYING HRS SINCE -06 MODIFICATION C/W BY AMERICAN EUROCOPTER. POSSIBLE CAUSE OF LOSS OF T ORQUE, UNKNOWN. RECOMMENDATION TO PREVENT RECURRENCE, INCREASE TORQUE VALVE AT CASTELLATION. (X) 1 G 7 1 3U H9EU 2000062700132 20000627 00132 EU 2000 6 27 20000608SH025 1 20000329 G 7712 G555674 TRANSDUCER BOLKMS 117 BK117A3 5626015 EU ENGINE INOPERATIVE A R7MA O OTHER O OTHER IN INSP/MAINT 1 NM 07 625MB 376 7108 PRESSURE TRANSDUCER UNIT INOPERATIVE. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U H13EU 2000062300075 20000623 00075 EU 2000 6 23 20000608SH027 1 20000223 G 6410 134617P BUSHING BOLKMS 117 BK117A3 5626015 EU TAIL ROTOR WORN A R7MA O OTHER O OTHER IN INSP/MAINT 1 NM 07 117MV 464 7089 BUSHING TEFLON LINERS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U H13EU 2000062300076 20000623 00076 EU 2000 6 23 20000608SH028 1 20000223 G 6410 134616P BUSHING BOLKMS 117 BK117A3 5626015 EU TAIRL ROTOR WORN A R7MA O OTHER O OTHER IN INSP/MAINT 1 NM 07 117MV 464 7089 BUSHING TEFLON LINERS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U H13EU 2000062300077 20000623 00077 EU 2000 6 23 20000608SH029 1 20000328 G 6410 134617P BUSHING BOLKMS 117 BK117A4 5626017 EU TAIL ROTOR WORN B R7MA O OTHER O OTHER IN INSP/MAINT 1 NM 07 586BH 107 7129 BUSHING TEFLON LINERS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 2 EACH NEW UNITS, CORRECTED PROBLEM. (X) 1 G 7 2 3U H13EU 2000062300078 20000623 00078 EU 2000 6 23 20000608SH030 1 20000328 G 6410 134616P BUSHING BOLKMS 117 BK117A4 5626017 EU TAILROTOR WORN B R7MA O OTHER O OTHER IN INSP/MAINT 1 NM 07 586BH 107 7129 BUSHING TEFLON LINERS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 2 EACH NEW UNITS, CORRECTED PROBLEM. (X) 1 G 7 2 3U H13EU 2000062600107 20000626 00107 EU 2000 6 26 20000609SH001 1 20000524 G 6410 1053170023 BEARING BOLKMS 117 BK117A4 5626017 EU TAIL ROTOR WORN A R7MA O OTHER O OTHER IN INSP/MAINT 1 NM 07 586BH 95 7129 BEARING WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 2 EACH NEW UNITS, CORRECTED PROBLEM. (X) 1 G 7 2 3U H13EU 2000062600108 20000626 00108 2000 6 26 20000609SH002 4 20000316 G 3423 40205773 COMPASS BOLKMS BK117 BK117C1 5626025 EU COCKPIT DASH INOPERATIVE A R7MA O OTHER O OTHER IN INSP/MAINT 1 NM 07 117SU 414 7527 COMPASS UNIT INOPERATIVE. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U NC H13EU 2000062600109 20000626 00109 EU 2000 6 26 20000609SH003 1 20000229 G 5244 1173084103 HINGE BOLKMS BK117 BK117C1 5626025 EU T/R FAIRING WORN A R7MA O OTHER O OTHER IN INSP/MAINT 1 NM 07 117SU 509 7527 HINGE WORN BEYOND SERVICEABLE LIMITS. CORE SCRAPPED LOCALLY BY MECHANIC. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. ( X) 1 G 7 2 3U NC H13EU 2000062600110 20000626 00110 EU 2000 6 26 20000609SH004 1 20000307 G 2497 117188001 WIRE BOLKMS BK117 BK117C1 5626025 EU DC SYSTEM WORN A O OTHER O OTHER IN INSP/MAINT 1 NM 07 117SU 390 7527 CABLE WORN BEYOND SERVICEABLE LIMITS. CORE SCRAPPED LOCALLY BY MECHANIC. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X ) 1 G 7 2 3U NC H13EU 2000062700133 20000627 00133 EU 2000 6 27 20000609SH006 1 20000317 G 5210 1172461611 FITTING BOLKMS BK117 BK117C1 5626025 EU PILOT DOOR WORN A R7MA O OTHER O OTHER IN INSP/MAINT 1 NM 07 117SU 415 7527 FITTING ASSY (UPPER) WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U NC H13EU 2000061300457 20000613 00457 CE 2000 6 13 20000609SH009 1 20000427 G 2140 51A45 COMBUSTION CHAMB JANITROL BEECH 95 B95 1153404 CE DEACTIVATED A K NONE O OTHER IN INSP/MAINT 1 NM 07 802QD 4600128 TD432 JANITROL COMBUSTION HEAD ASSY, PN 51A45, ON HEATER ASSY, PN D83A28, HAD A ONE INCH DIAMETER RUST HOLE. THIS HOLE WAS CA USED BY AGE, DETERIORATION AND USE. THE HEATER HAD BEEN IN OPERATION SINCE 1960. SUBMITTER RECOMMENDED A RECURRING ADVI SORY DIRECTIVE FOR AGING BEECH BARON MODELS 55, A55, B55, AND B55A, AND BEECH TRAVELAIR MODELS 95, B95, B95A, D95A, AND E95 THAT CORPORATE THE JANITROL 83A28 SERIES COMBUSTION ACFT HEATERS. THERE IS A REGULARLY SCHEDULED MAINTENANCE PROCED URE CALLED OUT IN THE 83A28 SERIES JANITROL OVERHAUL MANUAL. (X) 1 L 7 2 3O 3A16 2000061300458 20000613 00458 CE 2000 6 13 20000609SH010 1 20000518 G 2435 2304818 STARTER GEN BEECH 99 99 1154002 CE INOPERATIVE A TIMA K NONE O OTHER IN INSP/MAINT 1 NM 07 199GL U15 OVERHAULED STARTER/GENERATOR. INSTALLED ON AIRCRAFT, WAS FOUND DEFECTIVE. ITEM WAS REMOVED FROM AIRCRAFT AND RETURNED. (X) 1 L 7 2 3T A14CE 2000061300459 20000613 00459 SO 2000 6 13 20000609SH011 1 20000514 G 2820 37756003 SWITCH ALCO PIPER PA44 PA44180T 7104404 SO LYC O360 TO360E1A6 41514 EA INTERNAL OF SW SHORTED D K NONE O OTHER CR CRUISE 1 NE 03 2913U 1350 448107057 617173 LEFT ENGINE IN-FLIGHT ROUGH AND SMOKE. FOUND ELECTRICAL FUEL PRIMER SOLENOID ACTIVATED AND TIME MASTER SWITCH ON. PUSH TO PRIME SWITCH AT COCKPIT INSTRUMENT PANEL SHORTED TO A CONTINUOUS CLOSED CIRCUIT. REPLACED DEFECTIVE SWITCH WITH SAM E PART NUMBER. PROBLEM REPAIRED. (X) 1 L 7 2 3O 3 O A19SO E26EA 2000061300460 20000613 00460 EU 2000 6 13 20000609SH012 1 20000531 G 2913 S40 DRIVE GEAR SNIAS 350 AS350B2 8680813 EU HYD PUMP DRIVE FAILED A A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 SW 09 350JG 370 90191088 3232 HYDRAULIC PUMP FAILED IN-FLIGHT. PRECAUTIONARY LANDING COMPLETED. INSP REVEALED DRIVE SPLINES AT HYD DRIVE COUPLING (F EMALE SPLINES), AND THE DRIVE SPLINES AT THE HYD PUMP (MALE SPLINES) WERE PREMATURELY WORN. SPLINE ENGAGEMENT INSUFFICI ENT FOR DRIVE DEMAND. HYD PUMP DRIVE SPLINES INSPECTED AND GREASED AT BASIC INSP. 500 FLYING HRS OR 15 MONTHS BY CALEN DER. POSSIBLE CAUSE OF FAILURE UNKNOWN. RECOMMENDED TO PREVENT RECURRENCE, INSPECT HYD DRIVE SPLINES WHEN ACFT IS DELI VERED NEW, AND EACH 100-HOUR AIRFRAME INSP INTERVAL UP TO THE 500-HR INSP FOR A TREND ANALYSIS. ENCOUNTER PREMATURE WEAR ON DRIVE SPLINES, (X) 1 G 7 1 3U H9EU 2000061300461 20000613 00461 NE 2000 6 13 20000609SH013 2 20000504 G 8530 CYLINDER HEAD DHAV DHC3 DHC3 2800202 EA PWA R1340 R134059 52016 NE NUMBER 7 CRACKED D A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CL CLIMB 1 NM 01 357AS 694 357 P5844 UPON CLIMB-OUT AFTER TAKEOFF, PILOT REPORTED ROUGH RUNNING ENGINE AND A LOSS OF POWER. PILOT STARTED TURNING BACK FOR A IRPORT AND DECIDED NOT ENOUGH POWER AND LANDED SAFELY IN A FARMER''S FIELD. DISCOVERED, NR 7 CYLINDER HEAD CRACKED FROM ONE SPARK PLUG HOLE ALL THE WAY TO THE OTHER. MAINTENANCE SUGGESTED ALONG WITH A VISUAL INSPECTION OF CYLINDER AND WHI LE DOING A COMPRESSION CHECK, ALSO DO A SOAP AND WATER CHECK FOR CRACKS WHEN AIR IS PUT TO THE CYLINDER. (X) 1 H 7 1 3R 3 R A815 5E2 2000061300462 20000613 00462 SO 2000 6 13 20000609SH014 1 20000426 G 5730 6208700 SKIN PIPER PA32 PA32300 7103212 SO INBD/OTBD EDGES CRACKED D K NONE O OTHER IN INSP/MAINT 1 NE 01 4114W 3372 3240177 LEFT WING-SKIN ASSY-TOP, INBOARD ROOT HAD NUMEROUS CRACKS AT BOTH ENDS OF BOTH STRINGERS AND FOUND ONE STRINGER INBOARD END CRACKED. THIS SKIN, AFTER REMOVAL, WAS FOUND HAVING NO REINFORCEMENT DOUBLERS AT THE ENDS OF BOTH STRINGERS. THE NE W SKIN HAS THE REINFORCEMENT DOUBLERS AND THIS SHOULD PREVENT CRACKING. SUBMITTER RECOMMENEDED THAT ALL PIPERS WITH SAM E WING DESIGN SHOULD BE CHECKED THAT THE DOUBLERS ARE INSTALLED. (X) 1 L 7 1 3O A3SO 2000061300463 20000613 00463 SO 2000 6 13 20000609SH015 1 20000519 G 2700 CONTROL CABLE PIPER PA46 PA46350P 7104602 SO FLIGHT CONTROL BINDING B K NONE O OTHER IN INSP/MAINT 1 EA 01 41676 18 4636268 PILOT NOTICED FLIGHT CONTROLS GETTING STIFF IN ROLL DIRECTION. INSPECTED ENTIRE SYSTEM FOR PROPER ROUTING OF CABLES AND CORRECT TENSION ON PRIMARILY AND AUTOPILOT CABLES. NO DISCREPANCY NOTED. WENT THROUGH ENTIRE SYSTEM AND LUBED ALL ROT ATIONAL POINTS UNTIL CONTROLS FREED UP. POSSIBLY CAUSED BY LACK OF LUBRICATION OF FACTORY. AIRCRAFT ONLY HAD 18 HOURS SINCE NEW. (X) 1 L 7 1 3O RT A25SO 2000061300516 20000613 00516 SW 2000 6 13 20000609SH017 1 20000515 G 2721 B2085400053 BEARING SUPPORT GULSTM 690TP 695A 7630519 SW RUDDER PEDAL LACK OF LUBE H K NONE O OTHER IN INSP/MAINT 1 SW 15 508AB 5792 96034 RUDDER PEDAL BEARINGS FAILED DUE TO LACK OF LUBRICATION. NO WAY TO LUBE WITHOUT COMPLETE DISASSEMBLY. BEARINGS CUT HAL F WAY THROUGH RUDDER PEDAL TUBES, TUBES ARE ONLY .0625 INCH THICK. FOUND DURING GRAND RENAISSANCE PROGRAM. SUBMITTER S TATED NEED WAY TO LUBE RUDDER PEDAL TUBE BEARINGS DURING 100-HOUR INSPECTION OR AT LEAST EVERY 1,000 HOURS. REPLACED TU BES AND BEARINGS. (X) 1 H 7 2 4T 2A4 2000061300517 20000613 00517 CE 2000 6 13 20000609SH018 1 20000519 G 7120 503403034 MOUNT CESSNA CESSNA 421 421C 2076016 CE LT ENGINE BAY CRACKED B K NONE O OTHER IN INSP/MAINT 1 SW 15 5491G 5233 421C0238 DURING ANNUAL INSPECTION, FOUND ONE INCH CRACK LEFT SIDE, AFT CORNER, LEFT ENGINE BAY, CANTED BULKHEAD TOP CAP. EXHAUS T CORROSION IN THIS AREA WAS NOTED. PER AD 2000-01-16 EXHAUST SYSTEM, FOUND CRACKS ON EXHAUST COMPONENTS ALSO IN THIS A REA THAT MAY HAVE CONTRIBUTED TO THIS FAILURE. (X) 1 L 7 2 3O A7CE 2000061300518 20000613 00518 CE 2000 6 13 20000609SH019 1 20000307 G 2410 AN743A BOLT CESSNA CESSNA 172 172RG 2072438 CE ALTERNATOR MOUNT LOOSE B PP4R K NONE H ELECT. POWER LOSS-50 PC CR CRUISE 1 SO 05 5493R 172RG0064 AIRCRAFT EXPERIENCED AN IN-FLIGHT ELECTRICAL FAILURE. UPON LANDING, ALTERNATOR WAS FOUND HANGING FROM THE BELT TENSION BRACKET. THE PRIMARY MOUNT BOLT, AN7-43A, WAS FOUND IN THE LOWER COWLING. WHEN THE MOUNT BOLT FELL OUT, THE COOLING FA N CONTACTED THE ENGINE CASE AND STOPPED THE ALTERNATOR. WITH THE ENGINE RUNNING AND THE ALTERNATOR LOCKED UP, THE ALTER NATOR BELT BURNED UP ON THE ALTERNATOR PULLEY. ALTERNATOR BELT HAD RECENTLY BEEN TIGHTENED. (X) 1 H 7 1 3O 3A17 2000061600329 20000616 00329 CE 2000 6 16 20000609SH022 1 20000524 G 3244 8293P00727 TIRE MTSBSI MU2 MU2B36A 5780413 CE RIGHT MAIN SEPARATED H O OTHER O OTHER LD LANDING 1 SW 15 61BA 13 729SA THE SUBMITTER STATED, TIRE REPAIRED AND RECAPPED BY AERO WHEEL & BRAKE SERVICE CORP., NR U8SR971J. TIRE WAS INSTALLED ON THIS AIRCRAFT ON 4-15-00 AND HAD 13.2 HRS TT WITH 13 LANDINGS TOTAL. DURING LANDING ROLLOUT, A 2.5 INCH WIDE BAND OF T READ SEPARATED FROM THE CENTER AND FULL CIRCUMFERENCE OF THE TIRE RESULTING IN DAMAGE TO THE AFT MAIN GEAR DOOR WHICH WI LL REQUIRE REPLACEMENT OF THE DOOR AND MINOR AREA OF DAMAGE TO THE LOWER SURFACE OF THE INBOARD WING, APPROXIMATELY 3 IN CHES IN DIAMETER. NOTE: TIRE DID NOT DEFLATE. (X) 1 H 7 2 3T A10SW 2000062700134 20000627 00134 EU 2000 6 27 20000609SH025 1 20000519 G 6220 E1T302301 FREQ ADAPTER SNIAS 350 AS350B2 8680813 EU MAIN ROTOR CRACKED B B3OR O OTHER O OTHER IN INSP/MAINT 1 SW 03 5204Y 483 3101 DURING 500-HOUR INSPECTION, FOUND YELLOW BLADE FREQUENCY ADAPTER CRACKED AT EDGE OF KEVLAR MATING SURFACE. THIS IS FIRS T OCCURRENCE OF THIS TYPE ON THE 3 AIRCRAFT OF SAME TYPE OPERATED A TOTAL OF 1200 HOURS. NO REASON FOUND FOR DEFECT. ( X) 1 G 7 1 3U H9EU 2000061600330 20000616 00330 SO 2000 6 16 20000609SH026 1 20000523 G 3230 4204200 BRACE PIPER PIPER PA31 PA31350 7103110 SO INSIDE RADIUS CRACKED I WVBA K NONE O OTHER IN INSP/MAINT 1 AL 01 59764 15290 317652037 DURING A DETAILED INSPECTION OF THE LANDING GEAR, THIS PART WAS FOUND TO HAVE A SMALL CRACK. THIS PART CONNECTS THE HYD RAULIC ACTUATOR TO THE FORWARD SIDE BRACE WHICH EXTENDS AND RETRACTS THE LANDING GEAR. THE WEIGHT OF THE GEAR AND THE S PEED OF MOVING THE GEAR UP AND DOWN EVENTUALLY FATIGUES PARTS. SUBMITTER STATED RECURRENCE CANNOT BE AVOIDED. (X) 1 L 7 2 3O A20SO 2000061600331 20000616 00331 SO 2000 6 16 20000609SH027 1 20000524 G 8100 LW1009685 CONTROLLER PIPER PA31 PA31350 7103110 SO DEFECTIVE I WVBA O OTHER K FLUID LOSS IN INSP/MAINT 1 AL 01 3582P 268 318052103 ON POST-FLIGHT INSPECTION, PILOT NOTICED OIL ON UNDER SIDE OF ENGINE COWLING AND NOTIFIED MAINTENANCE PERSONNEL. FURTHE R INVESTIGATION REVEALED OIL DRIPPING FROM INDUCTION HOUSING DRAIN AND WAS DETERMINED TO BE COMING FROM THE SENSE LINE O UT OF THE DIFFERENTIAL PRESSURE CONTROLLER. (X) 1 L 7 2 3O A20SO 2000061600334 20000616 00334 CE 2000 6 16 20000609SH028 1 20000422 G 3252 08424008 SHIMMY DAMPENER CESSNA 172 172 2072402 CE NOSE FAILED G O OTHER O OTHER LD LANDING 1 SW 03 6331E 46431 AFTER LANDING, THE PIC WAS TAXIING TO THE RAMP WHEN THE NOSE WHEEL STARTED TO SHIMMY. HE APPLIED BRAKES AND THE AIRCRAF T MADE A HARD RIGHT TURN CAUSING THE AIRCRAFT TO TOP OVER TO THE LEFT/FRONT SIDE AND THE LEFT WING TIP AND PROPELLER MAD E CONTACT WITH THE GROUND. INSPECTIONS OF THE AIRCRAFT REVEALED THE NOSE GEAR SHIMMY DAMPER AND BOTH STEERING RODS WERE BROKEN. (X) 1 H 7 1 3O NT 3A12 2000061600408 20000616 00408 CE 2000 6 16 20000613SH001 1 20000511 G 7820 70120 MUFFLER BEECH 35 V35B 1151548 CE CONT O550 IO550B SO LEFT BULGED B MOGR K NONE O OTHER IN INSP/MAINT 1 GL 25 24161 D10103 297079R DURING A BASIC VISUAL INSPECTION OF THE ENGINE, THE LEFT MUFFLER WAS NOTED AS HAVING SEVERAL BULGES. UPON REMOVAL OF TH E MUFFLER AND HEAT SHIELD, THE MUFFLER HAD SEVERAL LARGE HOLES THAT WERE NOT VISIBLE UNTIL THE HEAT SHIELD WAS REMOVED. CAUSE UNKNOWN. SUBMITTER SUGGESTED HEAT SHIELD BE REMOVED FOR CLOSER INSPECTION OF MUFFLER DURING 100 HOUR/ANNUAL INSP ECTIONS. (X) 1 L 7 1 3O 3 O 3A15 E3SO 2000061600409 20000616 00409 SO 2000 6 16 20000613SH002 1 20000308 G 3250 9652200 SPRING PIPER PIPER PA34 PA34200 7103405 SO NOSE GEAR ASSY BROKEN B PP4R K NONE O OTHER IN INSP/MAINT 1 SO 05 1230T 5163 347250268 DURING A 50-HOUR OIL CHANGE, THE AIRCRAFT WAS JACKED UP IN ORDER TO CHANGE BOTH MLG TIRES. WHILE SPOT-CHECKING NLG TIRE , EXCESSIVE PLAY WAS FOUND IN THE NLG STEERING LINKAGE. CLOSER EXAMINATION REVEALED THE STEERING STOPS WERE DAMAGED AND THE NLG CENTERING SPRING WAS BROKEN. NORMALLY, THE CENTERING SPRING TRAVEL IS GREATER THAN THE STEERING STOPS. SUBMIT TER SUSPECTED THE STEERING STOPS WERE DAMAGED DURING TOWING ALLOWING THE STEERING TRAVEL TO EXCEED THE STOPS AND BREAK T HE CENTERING SPRING. (X) 1 L 7 2 3O A7SO 2000061600410 20000616 00410 SW 2000 6 16 20000613SH003 1 20000515 G 5510 3010610 ATTACH FITTING AIRTRC AT400 AT401 0390204 SW HORIZ STAB STRUT CORRODED H K NONE O OTHER IN INSP/MAINT 1 SW 09 4545W 5253 4010790 INTERNAL CORROSION CAUSED FAILURE OF HORIZONTAL STABILIZER STRUT AT LOWER ATTACH FITTING. SUBMITTER RECOMMENDED LOWER A TTACH POINT DESIGNED SIMILAR TO UPPER FITTING AND LINSEED OIL APPLIED TO INSIDE OF STRUT. (X) 1 L 7 1 3R A17SW 2000071900003 20000719 00003 SO 2000 7 19 20000613SH004 1 20000531 G 3240 1159SC15403 BRAKE AHA2163 GULSTM GV GV SO NR 2 MLG DAMAGED H D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 SW 99 83M 595 557 WHILE REMOVING NR 2 MAIN WHEEL ASSY FOR A TIRE CHANGE, NOTED ON THE BRAKE INSPECTION THAT THE OUTBOARD ROTOR KEYWAY SLOT CLIPS WERE BREAKING AWAY FROM THE ROTOR. WHEEL ASSY HAD SOME DAMAGE FOR LOOSE CLIPS. BRAKE AND WHEEL ASSYS WERE BOTH REPLACED. (X) 2 L 7 2 4F RT A12EA 2000101200142 20001012 00142 SW 2000 10 12 20000613SH006 1 20000523 G 7810 649264 INTAKE PIPE MOONEY M20 M20K 5870220 SW CONT O360 TSIO360SB SO NR 4 CYL ATT CRACKED B DY1R O OTHER O OTHER IN INSP/MAINT 1 EA 13 48LW 434 252021 321763 DISCOVERED HEAVY STAIN AT FLANGE END OF INDUCTION TUBE DURING ROUTINE OIL CHANGE. REMOVED FLANGE RETAINER AND FOUND PIP E CRACKED APPROXIMATELY ONE-HALF DIAMETER. CONTINENTAL HAS RECENTLY ISSUED SB 98-8 WHICH RECOMMENDS REPLACEMENT OF ONE PIECE PIPES FOR CYLINDERS 1 AND 3. THIS PIPE WAS FOR CYLINDER NR 4. SUBMITTER RECOMMENDED REPLACEMENT OF CYLINDERS 2 A ND 4 PIPES WITH 2 PIECE STYLE AS WELL. LENGTH OF PIPE IS TOO MUCH FOR FLANGE STRENGTH. (X) 1 L 7 1 3O 3 O 2A3 E9CE 2000061400301 20000614 00301 EU 2000 6 14 20000613SH007 1 20000510 G 2710 PUSHROD TUBE GROB 103TWN G103ATWINII 1660206 EU 96 INCH OUT BD FAILED B L1MR K NONE O OTHER IN INSP/MAINT 1 WP 11 103MG 7775 33983K216 LEFT WING AILERON PUSH ROD FOUND MISSING PLASTIC BEARING CAUSING RIVETS TO WEAR THROUGH PUSH ROD IN 2 PLACES. (X) 1 K 0 0 3O 0 G39EU 2000061400302 20000614 00302 2000 6 14 20000613SH008 4 20000525 G 6122 B41832 FLYWEIGHT PIPER PA32 PA32300 7103212 SO LYC O540 IO540K1G5 41532 EA CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 2947E E103U 327940222 RELEVANT INDICATION OF CRACK IN FLYWEIGHT ASSY. 1 L 7 1 3O 3 O A3SO 1E4 2000061400303 20000614 00303 CE 2000 6 14 20000613SH011 1 20000613 G 5510 1732010 BRACKET CESSNA CESSNA 177 177RG 2073709 CE BEND RADIUS CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 09 545PZ 5000 177RG1023 THREE OF FOUR BALANCE WEIGHT SUPPORT BRACKETS WERE CRACKED ALONG THE BEND RADIUS. CRACKS WERE 1.25 INCHES, 1.50 INCHES, AND 1.75 INCHES ON EACH. THIS WAS NOTICED DURING STABILIZER BEARING REPLACEMENT WITH THE STABLIZER OFF THE AIRCRAFT. SUBMITTER RECOMMENDED FREQUENT INSPECTIONS. UNKNOWN CAUSE. (X) 1 H 7 1 3O A20CE 2000062000227 20000620 00227 CE 2000 6 20 20000613SH012 1 20000613 G 5510 17320311 BRACKET CESSNA CESSNA 177 177RG 2073709 CE BEND RADIUS CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 09 545PZ 5000 177RG1023 THREE OF FOUR BALANCE WEIGHT SUPPORT BRACKETS WERE CRACKED ALONG THE BEND RADIUS. CRACKS WERE 1.25 INCHES, 1.50 INCHES, AND 1.75 INCHES ON EACH. THIS WAS NOTICED DURING STABILIZER BEARING REPLACEMENT WITH THE STABLIZER OFF THE AIRCRAFT. SUBMITTER RECOMMENDED FREQUENT INSPECTIONS. UNKNOWN CAUSE. (X) 1 H 7 1 3O A20CE 2000061400304 20000614 00304 CE 2000 6 14 20000613SH013 1 20000613 G 5510 17320312 BRACKET CESSNA CESSNA 177 177RG 2073709 CE BEND RADIUS CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 09 545PZ 5000 177RG1023 THREE OF FOUR BALANCE WEIGHT SUPPORT BRACKETS WERE CRACKED ALONG THE BEND RADIUS. CRACKS WERE 1.25 INCHES, 1.50 INCHES, AND 1.75 INCHES ON EACH. THIS WAS NOTICED DURING STABILIZER BEARING REPLACEMENT WITH THE STABLIZER OFF THE AIRCRAFT. SUBMITTER RECOMMENDED FREQUENT INSPECTIONS. UNKNOWN CAUSE. (X) 1 H 7 1 3O A20CE 2000061400305 20000614 00305 CE 2000 6 14 20000613SH014 1 20000525 G 3230 508103437 PIN BEECH 200 B200 1152922 CE MLG DOWNLOCK WORN H K NONE O OTHER IN INSP/MAINT 1 EA 21 529NA BB1091 THE RELEASE LINKS AND PINS IN BOTH MAIN LANDING GEAR DOWNLOCKS WERE REMOVED FROM AIRCRAFT FOR INSPECTION. INSPECTION R EVEALED BOTH PINS WERE WORN APPROX .002 INCH BEYOND LIMITS AND BOTH LINK PIN HOLES HAD CIRCUMFERENTIAL SCRATCHES INDICAT ING THAT PINS HAD AT SOME TIME ROTATED IN LINK. PINS AND LINKS WERE REPLACED. ACFT TIME: 8,933.1 HOURS, 5,559 LANDING S. SUBMITTER SUGGESTED THAT HOOK AND LINK ASSYS BE DISASSEMBLED AND INSPECTED AT EACH 6 YEAR 8,000 LANDING INSPECTION O F DRAG BRAKE ASSY. (X) 1 L 7 2 4T A24CE 2000061400306 20000614 00306 WP 2000 6 14 20000613SH021 2 20000601 G 7250 30747522 DISK GARRTT TFE731 TFE731* 01518 WP POST FIR TREE OUT OF TOLERANCE H K NONE O OTHER IN INSP/MAINT 1 SW 99 NEW PART RECEIVED FROM HONEYWELL WITH DAMAGE IN POST FIR TREE AREA. NICK MORE THAN .001 INCH IN DEPTH ON FORWARD SIDE. LOT NUMBER 00P0130. (X) 4 F E6WE 2000061400307 20000614 00307 2000 6 14 20000613SH023 4 20000525 G 6122 B41832 FLYWEIGHT HARTZL PIPER PA23 PA23250 7102308 SO LYC O540 IO540C4B5 41532 EA CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 A3858T RELEVANT CRACK INDICATION AT BASE OF FLYWEIGHT. (X) 1 L 7 2 3O 3 O 1A10 1E4 2000061400308 20000614 00308 SO 2000 6 14 20000613SH024 1 20000509 G 2410 75536 BUSHING LYC PIPER PA31 PA31P 7103120 SO LYC O541 TIGO541E1A 41539 EA FAILED B PAIR K NONE K FLUID LOSS CR CRUISE 1 SO 05 61CG 31P30 L47262 PILOT EXPERIENCED ALTERNATOR FAILURE ON LT ENGINE IN-FLIGHT. UPON INSPECTION AFTER LANDING, FOUND LT SIDE OF AIRCRAFT C OVER IN OIL AND LT ALTERNATOR LYING INSIDE OF COWLING. SUSPECT FAILURE OF GOVERNOR ADAPTER ASSY. BUSHING, PN 75539, CA USED MIS-ALIGNMENT OF ALT DRIVESHAFT WHICH CAUSED COUPLING, PN LW-14464, TO FAIL IN SUCH A MANNER THAT CAUSED ALTERNATOR ADAPTER ASSY, PN LW-10259, TO FAIL. (X) 1 L 7 2 3O 3 O A8EA E19EA 2000061400309 20000614 00309 CE 2000 6 14 20000613SH025 1 20000525 G 7810 NH10010910 COUPLING CESSNA 414 414 2075908 CE CONT O520 TSIO520NB 17040 SO CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 01 4243C 100 4140539 ***TONY, LAST SENTENCE?????***WASTEGATE ELBOW COUPLING INSTALLED ON RAM SERIES VII C-340 AND 414, IAW STC SA4331SW. FOU ND CRACKED AND REPLACED EACH 50 - 100 HOURS FOR 150 HOURS. (X) 1 L 7 2 3O 3 O RT A7CE E8CE 2000061400310 20000614 00310 CE 2000 6 14 20000613SH026 1 20000525 G 3230 508103961 LINK BEECH 200 B200 1152922 CE OUT OF TOLERANCE H K NONE O OTHER IN INSP/MAINT 1 EA 21 529NA BB1091 THE RELEASE LINKS AND PINS IN BOTH MAIN LANDING GEAR DOWNLOCKS WERE REMOVED FROM AIRCRAFT FOR INSPECTION. INSPECTION R EVEALED BOTH PINS WERE WORN APPROX .002 INCH BEYOND LIMITS AND BOTH LINK PIN HOLES HAD CIRCUMFERENTIAL SCRATCHES INDICAT ING THAT PINS HAD AT SOME TIME ROTATED IN LINK. PINS AND LINKS WERE REPLACED. ACFT TIME: 8,933.1 HOURS, 5,559 LANDING S. SUBMITTER SUGGESTED THAT HOOK AND LINK ASSYS BE DISASSEMBLED AND INSPECTED AT EACH 6 YEAR 8,000 LANDING INSPECTION O F DRAG BRAKE ASSY. (X) 1 L 7 2 4T A24CE 2000061600488 20000616 00488 SO 2000 6 16 20000615SH001 1 20000615 G 5711 62015 SPAR PIPER PA28 PA28160 7102806 SO CORRODED C K NONE O OTHER IN INSP/MAINT 1 CE 07 5158W 28189 FORWARD LOWER EDGE OF MAIN SPAR INBOARD BEHIND FUEL TANK BADLY CORRODED. DEFOLIATED BY ABOUT 50 PERCENT OF THICKNESS. MICE NESTS AND FECAL MATTER FOUND. SUBMITTER RECOMMENDED FUEL TANK REMOVAL FOR INSPECTION AT LEAST EVERY 5 YEARS. ALSO , INSTALL INSPECTION HOLE BEHIND TANKS FOR BETTER INSPECTION ACCESS. (X) 1 L 7 1 3O 2A13 2000072600253 20000726 00253 NE 2000 7 26 20000615SH002 2 20000605 G 7230 UL27681 COMPRESSOR WHEEL RROYCE RB211 RB211535E4 54555 NE COOLING HOLES CRACKED B XE5R K NONE O OTHER IN INSP/MAINT 1 SW 21 16222 31374 CRACK INDICATIONS FOUND DURING ACCOMPLISHMENT OF ROLLS-ROYCE SB RB211-72-C817. (X) 4 F E12EU 2000062600125 20000626 00125 NE 2000 6 26 20000615SH003 1 20000511 G 5302 TAIL BOOM SKRSKY S55 S55 8141602 NE TAIL CONE CRACKED B K NONE O OTHER NR NOT REPORTED 1 WP 19 17754 396 V55398T UPPER TAIL CONE SKIN AT STA 181.9 CRACKED APPROXIMATELY 12 INCHES IN LENGTH. (X) 1 G 7 1 3R 1H4 2000070600229 20000706 00229 WP 2000 7 6 20000615SH005 1 20000602 G 3246 152058 WHEEL 1542511 DOUG DC8 DC8* WP SPOKE AREA OTBD UNSERVICEABLE B INWR K NONE O OTHER IN INSP/MAINT 1 SO 19 NDT INSPECTION SHOWED CRACK INDICATION AT SPOKE AREA. (X) 2 L 7 4 4J F 4A25 2000061900240 20000619 00240 2000 6 19 20000615SH007 4 20000523 G 3424 1394T10054 GEAR PIPER PA38 PA38112 7103812 SO TURN AND BANK INOPERATIVE H K NONE O OTHER IN INSP/MAINT 1 NM 08 4265E 1846 3878A0513 TURN COORDINATOR NOT WORKING, FLAG WAS INDICATING PROPER OPERATION, BUT RATE OF TURN NOT INDICATED. OCCURED UNDER NORMAL CONDITONS. THE CAUSE IS INTERNAL DAMAGE TO GEARINGS OR PART MALFUCTNION. SUBMITTER STATED TO PREVENT, TAXI AROUND AND YAW BACK AND FOURTH AND CHECK FOR PROPER OPERATION. (X) 1 L 7 1 3O A18SO 2000062000228 20000620 00228 EA 2000 6 20 20000615SH008 2 20000605 G 8530 LW12892 PLUG PIPER PA23 PA23250 7102308 SO LYC O540 O540C4B5 41532 EA ROCKER SHAFT DETERIORATED D K NONE O OTHER IN INSP/MAINT 1 GL 13 17WE 277854118 L1811048A FOUND IN BOTH ENGINES DURING ANNUAL WHILE PERFORMING LYC 400-HOUR ROCKER ARM INSP, SEVERAL OF THE ROCKER SHAFT THRUST BU TTONS WERE FOUND DETERIORATING. A COUPLE OF THEM WERE FOUND BROKEN OFF AND OUT OF THE ROCKER SHAFT. THE OIL SCREEN WAS FOUND TO CONTAIN SOME BITS OF PLASTIC. ALL THE THRUST BUTTONS WERE REMOVED AND SEVERAL OF THEM CRUMBLED WHEN SQUEEZED. ENGINES HAD JUST OVER 1,600 HRS SMOH IN 1982. A FEW HRS AFTER INSPECTION, ONE OF THE ENGINES DEVELOPED HIGH OIL PRESS URE PROBLEMS, POSSIBLY DUE TO PLUGGED OIL PASSAGES. ALL OF THE THRUST BUTTONS REPLACED AT INSP, BUT THERE STILL COULD B E PLASTIC BITS IN THE ENGINE WHICH COULD PLUG PASSAGES. (X) 1 L 7 2 3O 3 O 1A10 E295 2000062000229 20000620 00229 EA 2000 6 20 20000615SH009 2 20000605 G 8530 LW12892 PLUG PIPER PA23 PA23250 7102308 SO LYC O540 IO540C4B5 41532 EA ROCKER SHAFT DETERIORATED D K NONE O OTHER IN INSP/MAINT 1 GL 13 17WE 277854118 L1815148A FOUND IN BOTH ENGINES DURING ANNUAL WHILE PERFORMING LYC 400-HOUR ROCKER ARM INSP, SEVERAL OF THE ROCKER SHAFT THRUST BU TTONS WERE FOUND DETERIORATING. A COUPLE OF THEM WERE FOUND BROKEN OFF AND OUT OF THE ROCKER SHAFT. THE OIL SCREEN WAS FOUND TO CONTAIN SOME BITS OF PLASTIC. ALL THE THRUST BUTTONS WERE REMOVED AND SEVERAL OF THEM CRUMBLED WHEN SQUEEZED. ENGINES HAD JUST OVER 1,600 HRS SMOH IN 1982. A FEW HRS AFTER INSPECTION, ONE OF THE ENGINES DEVELOPED HIGH OIL PRESS URE PROBLEMS, POSSIBLY DUE TO PLUGGED OIL PASSAGES. ALL OF THE THRUST BUTTONS REPLACED AT INSP, BUT THERE STILL COULD B E PLASTIC BITS IN THE ENGINE WHICH COULD PLUG PASSAGES. (X) 1 L 7 2 3O 3 O 1A10 1E4 2000061900277 20000619 00277 EA 2000 6 19 20000615SH010 2 20000412 G 7320 3027974 TUBE BEECH 90 C90 1152913 CE PWA PT6 PT6A21 52043 EA FCU BROKEN E AOBA O OTHER O OTHER TO TAKEOFF 1 EA 11 369GA 7845 5 LJ934 PCE24685 WHILE APPLYING POWER FOR TAKEOFF, THE LEFT ENGINE WOULD NOT RESPOND. INSPECTED AND FOUND THE PY LINE CRACKED AT THE FUEL CONTROL UNIT. (X) 1 L 7 2 3T 4 T 3A20 E4EA 2000061900278 20000619 00278 CE 2000 6 19 20000615SH011 1 20000524 G 2510 0514090 SEAT CESSNA CESSNA 172 172M 2072418 CE FAILED H K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 11 64427 60541 17265219 WHEN SEAT CRANK IS TURNED, PIN RUBS ON VERTICAL ADJUST SCREW ASSY. IT CATCHES AT MAX ADJUSTMENT AND PREVENTS FULL SEAT ADJUST PIN ENGAGEMENT. SUBMITTER SUGGESTED A POSSIBLE MANUFACTURER DEFECT. (X) 1 H 7 1 3O NT 3A12 2000071800505 20000718 00505 WP 2000 7 18 20000615SH030 1 20000418 G 5320 991073417 WEB DOUG DC9 DC933F 302207A WP FUSELAGE CRACKED B ERKR K NONE O OTHER IN INSP/MAINT 1 WP 07 945F 47279 DURING C-CHECK, FOUND NUMEROUS CRACKS AND ELONGATED HOLES IN CUSP WEB AT BS 218 TO BS 237, LBL 44.5. CAUSE UNKNOWN. (X) 2 L 7 2 4F A6WE 2000062700135 20000627 00135 SW 2000 6 27 20000619SH004 1 20000428 G 6300 412340102101 BOOT BELL BELL 412 412 1182202 SW RUBBER LOOSE B K NONE O OTHER IN INSP/MAINT 1 SW 99 412FH 93 36027 THE RUBBER PART OF THE BOOT HAD COME LOOSE FROM THE METAL RING THAT HOLDS THE BOOT. NOTE: BOOT MFG DATE, MARCH 1999. (X) 1 G 7 2 4U H4SW 2000062700136 20000627 00136 SW 2000 6 27 20000619SH005 1 20000428 G 6310 212040176101 BOOT BELL 412 412 1182202 SW ENGINE/TRANS TORN B K NONE O OTHER IN INSP/MAINT 1 SW 99 THIS BOOT WAS REMOVED FROM STOCK AND FOUND THE RUBBER IN BAD CONDITION. HAD SEVERAL PLACES WHERE IT COULD TEAR. NOTE: BOOT MFG DATE JULY 21, 1999. (X) 1 G 7 2 4U H4SW 2000062700137 20000627 00137 SW 2000 6 27 20000619SH006 1 20000428 G 6310 212040176101 BOOT BELL BELL 412 412 1182202 SW ENGINE/TRANS TORN B K NONE O OTHER IN INSP/MAINT 1 SW 99 555BA 286 36015 TEAR ON RUBBER PART OF THE BOOT. NOTE: BOOT MFG DATE DECEMBER 11, 1998. (X) 1 G 7 2 4U H4SW 2000062700138 20000627 00138 SW 2000 6 27 20000619SH007 1 20000502 G 6310 212040176101 BOOT BELL 412 412 1182202 SW ENGINE/TRANS TORN B K NONE O OTHER IN INSP/MAINT 1 SW 99 555BA 38 36015 TEAR ON RUBBER PART OF BOOT. NOTE: BOOT MFG DATE JULY 21, 1999. (X) 1 G 7 2 4U H4SW 2000072000007 20000720 00007 NE 2000 7 20 20000619SH019 2 20000609 G 7250 811935 SUPPORT BRACKET PWA JT8 JT8* 52044 NE NR 5 BEARING CRACKED B WNFR K NONE O OTHER IN INSP/MAINT 1 NE 03 PART FAILED FMPI CRACK TEST IN SERVERAL LOCATIONS. (X) 4 F E2EA 2000072000008 20000720 00008 NE 2000 7 20 20000619SH020 2 20000609 G 7250 811935 SUPPORT BRACKET PWA JT8 JT8* 52044 NE NR 5 BEARING CRACKED B O OTHER O OTHER NR NOT REPORTED 1 NE 03 PART FAILED FMPI CRACK TEST IN SEVERAL LOCATIONS. (X) 4 F E2EA 2000062000232 20000620 00232 CE 2000 6 20 20000619SH026 1 20000430 G 2823 520220940625 ROLL PIN BEECH 35 K35 1151524 CE FUEL SEL VALVE MISSING D O OTHER O OTHER CR CRUISE 1 SO 09 3095C 3600 D5774 FUEL STARVATION, OFF AIRPORT LANDING. PILOT REPORTED THAT WHEN HE SWITCHED TANKS HE DID NOT FEEL POSITIVE DETENT. APPR OX 12 MINUTES LATER, ENGINE QUIT. AGAIN ATTEMPTED TO SWITCH TANKS AND SELECTOR HANDLE CAME DETACHED FROM SELECTOR VALVE SHAFT. EMERG LANDING MADE AND ON ROLL-OUT, ACFT STRUCK A FENCE CAUSING NOSE GEAR COLLAPSE, HEAVY DAMAGE TO ACFT. INV EST REVEALED THE ROLL PINS WERE MISSING FROM FUEL SELECTOR VALVE SHAFT, UPPER AND LOWER. SUBMITTER STATED SAFETY WIRING THROUGH ROLL PIN AND SHAFT WOULD HAVE ELIMINATED DEFECT. (X) 1 L 7 1 3O 3A15 2000062000233 20000620 00233 CE 2000 6 20 20000619SH028 1 20000530 G 5510 07122071 ATTACH FITTING CESSNA 182 182A 2072704 CE LT SIDE EMPENNAG CRACKED B PP4R K NONE O OTHER IN INSP/MAINT 1 SO 05 5890B 33890 DURING ANNUAL INSP, LT SIDE HORIZONTAL STABILIZER ATTACH BRACKET WAS FOUND CRACKED NEXT TO A MOUNT BOLT. APPROX ONE YEA R PRIOR, THE HORIZ STAB HAD BEEN REBUILT. THE SPAR, STRINGERS, AND SKIN HAD BEEN REPLACED. VERY FEW OF THE ORIGINAL PA RTS WERE RETURNED TO SERVICE. IT IS BELIEVED THE STABILIZER AND MOUNT BRACKET WERE DAMAGED DURING OR BY GROUND HANDLING THE ACFT BY THE TAIL. THE SMALL CRACK NEXT TO ONE OF THE TWO BOLTS THAT ATTACH IT TO THE ACFT WAS OVERLOOKED. (X) 1 H 7 1 3O NT 3A13 2000062000234 20000620 00234 EA 2000 6 20 20000619SH029 2 20000525 G 7300 ENGINE PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA POWER LOSS A BSYA O OTHER R PARTIAL RPM/PWR LOSS TO TAKEOFF 1 GL 07 35453 318052006 L167861A GRR - RIGHT ENGINE WOULD NOT COME ABOVE 2,000 RPM''S ON TAKEOFF. MAINTENANCE TROUBLESHOT, NO PROBLEM FOUND. GROUND RUN CHECKED GOOD. (X) 1 L 7 2 3O 3 O A20SO E14EA 2000062000235 20000620 00235 SO 2000 6 20 20000620SH001 1 20000519 G 3230 ROD PIPER PA31 PA31350 7103110 SO DOWN AND LOCK BINDING A BSYA O OTHER J WARNING INDICATION NR NOT REPORTED 1 GL 07 35551 318052063 - RT MAIN GEAR NO DOWN AND LOCK INDICATION. FOUND ROD AND BINDING NOT LETTING THE HOOK DROP INTO PLACE. CLEANED AND L UBED, OPS CHECKED GOOD. (X) 1 L 7 2 3O A20SO 2000062000236 20000620 00236 CE 2000 6 20 20000620SH002 1 20000525 G 3230 99100023 MOTOR CESSNA 310 310R 2074245 CE LANDING GEAR FAILED A BSYA O OTHER O OTHER NR NOT REPORTED 1 GL 07 5113J 310R0233 BUR - LANDING GEAR CIRCUIT BREAKER TRIPS WHEN GEAR SELECTED UP. REMOVED AND REPLACED GEAR MOTOR. OPS CHECKED GOOD. (X ) 1 L 7 2 3O 3A10 2000062000237 20000620 00237 SO 2000 6 20 20000620SH003 2 20000525 G 7300 ENGINE CESSNA 310 310R 2074245 CE CONT O520 IO520MB 17032 SO SURGES A BSYA O OTHER R PARTIAL RPM/PWR LOSS AP APPROACH 1 GL 07 5215C 310R1515 277772R CMH - RIGHT ENGINE ON APPROACH STARTED SURGING BETWEEN 2,200 RPM AND 2,600 RPM. CHECKED ENGINE OUT COMPLETELY, COULD NO T DUPLICATE. OPS CHECKED GOOD. (X) 1 L 7 2 3O 3 O 3A10 E5CE 2000062000238 20000620 00238 CE 2000 6 20 20000620SH004 1 20000516 G 5610 WINDSHIELD CESSNA 310 310R 2074245 CE BIRD STRIKE A O OTHER O OTHER CR CRUISE 1 GL 07 6121C 310R1288 OMA - PILOT HEARD LOUD BANG ON APPROACH INTO OMAHA. NOTIFIED OMA TOWER AND LANDED, NO PROBLEM. ON THE GROUND, FOUND TH AT A BIRD HIT TOP OF WINDSHIELD. NO DAMAGE TO AIRCRAFT, RETURNED TO SERVICE. (X) 1 L 7 2 3O 3A10 2000062000239 20000620 00239 EA 2000 6 20 20000620SH005 2 20000505 G 7314 5006050 COUPLER PESCO BEECH 90 65A901 CE PWA PT6 PT6A20 52043 EA CASE TO PUMP SHEARED D O OTHER Y ENGINE STOPPAGE CR CRUISE 1 SW 99 7089Q 516 5489 LM77 21043 EXPERIENCED AN ENGINE FAILURE DURING CRUISE AT 4,500 FEET. AFTER SOME TROUBLESHOOTING ON THE GROUND, FOUND IT TO BE THE HIGH PRESSURE FUEL PUMP, PARTICULARLY THE DRIVE COUPLING. THE SPLINES WERE DAMAGED (SHEARED) ENOUGH THAT IT ALLOWED TO O MUCH PLAY AND THE PUMP QUIT PUMPING. THE POSSIBLE CAUSE COULD HAVE BEEN INSUFFICIENT LUBRICATION TO THE DRIVE COUPLIN G. THE PUMP ITSELF HAS NOT YET BEEN TORN ALL THE WAY DOWN TO SEE IF THERE WERE INTERNAL PROBLEMS THAT MAY HAVE CONTRIBU TED. (X) 1 L 7 2 3T 3 T 3A20 E4EA 2000062800189 20000628 00189 CE 2000 6 28 20000620SH008 1 20000605 G 3230 6046H39B RELAY BEECH 95 95B55 1152729 CE LDG MOTOR FAILED D O OTHER O OTHER LD LANDING 1 SO 01 41TG 2900 TC1581 PILOT REPORTED LANDING GEAR MOTOR CIRCUIT BREAKER WOULD TRIP WHEN SELECTING GEAR DOWN. TRIED EMERG EXTENSION HANDLE AND FOUND TIGHT. AFTER SEVERAL TRIES, PILOT WAS ABLE TO EXTEND L/G GEAR WITH THE EMERG EXTENSION HANDLE AND LANDED WITHOUT PROBLEMS. WHEN MAINTENANCE INSPECTED ACFT, THEY FOUND THE LANDING GEAR TRANSMISSION BINDING. LANDING GEAR APPEARED TO BE IN RIG. FURTHER INVESTIGATION REVEALED THE L/G MOTOR DYNAMIC BRAKE RELAY NOT REVERSING THE CURRENT TO STOP MOTOR AND LANDING GEAR TRANSMISSION WHICH ALLOWED THE MOTOR TO DRIVE THE SECTOR GEAR AGAINST THE INTERNAL TRANS STOP. FOUND SECT OR GEAR BADLY DAMAGED AT ONE END. RE-INSTALLED TRANSMISSION AFTER O/H, INSTALLED NEW RELAY. RE-RIGGED GEAR PER MM. (X) 1 L 7 2 3O RT 3A16 2000062100160 20000621 00160 CE 2000 6 21 20000620SH009 1 20000601 G 2822 5100001RX PUMP CESSNA 182 182S 2072701 CE LEAKING D O OTHER K FLUID LOSS IN INSP/MAINT 1 SO 01 664PB 511 18280156 SEAL BETWEEN PUMP AND MOTOR LEAKING SEVERELY OUT DRAIN TUBE. THE ONLY WAY TO STOP IT FROM LEAKING IS TO TURN THE FUEL S ELECTOR VALVE TO THE OFF POSITION. THE ORIGINAL PUMP WAS REPLACED FOR THE SAME PROBLEM AT 81.9 HOURS. INSTALL OVERHAUL ED PUMP P/N 5100-00-3RX. AIRCRAFT TT, 593.2 HRS. SUBMITTER STATED THEY HAVE EXPERIENCED SAME PROBLEM WITH OTHER CESSNA 182S MODELS. (X) 1 H 7 1 3O NT 3A13 2000062100161 20000621 00161 CE 2000 6 21 20000620SH010 1 20000529 G 3222 1243400200 STRUT CESSNA 210 210B 2073410 CE NOSE BROKEN H O OTHER O OTHER TX TAXI/GRND HDL 1 GL 07 3222 3083 21057842 NOSE FORK ASSY BREAKAGE AT SHOCK STRUT MATING SURFACE. DURING ROLL-OUT AFTER LANDING, A SHIMMY WAS ENCOUNTERED FOLLOWED BY NOSE FORK ASSY BREAKAGE. AD 71-22-02 NOT APPLICABLE TO CESSNA 210 SERIES, BUT REFERENCED DIRECTIVE SL 63-31 INCORPO RATES THIS AIRCRAFT MODEL. REVISE AD TO INCORPORATE SL REFERENCED AIRCRAFT. (X) 1 H 7 1 3O 3A21 2000062100162 20000621 00162 EA 2000 6 21 20000620SH015 2 20000530 G 7250 3013102 BLADE BEECH 99 B99 1154004 CE PWA PT6 PT6A27 52043 EA PT DISK MISSING B TIMA O OTHER E VIBRATION/BUFFET TO TAKEOFF 1 NM 11 99TH U155 PCE40840100 ON TAKEOFF, PILOT FELT AIRCRAFT SHUDDER, RETURNED TO FIELD WITHOUT ANY DAMAGE TO AIRCRAFT. UPON INVESTIGATION ON ENGINE , FOUND 2 INCH SQUARE AREA MISSING FROM EXHAUST. UPON FURTHER INVESTIGATION, FOUND PORTION OF POWER TURBINE BLADE MISSI NG. THIS ENGINE HAD 339.1 HOURS SINCE POWER SECTION WAS DISASSEMBLED FOR POWER TURBINE BLADE INSPECTION. (X) 1 L 7 2 3T 4 T A14CE E4EA 2000062100163 20000621 00163 EA 2000 6 21 20000620SH016 2 20000317 G 7310 125099016 LINE CESSNA 206 206H 2073301 CE LYC O540 IO540AC1A5 EA FUEL PRESS CHAFED D K NONE O OTHER IN INSP/MAINT 1 CE 07 950HP 20608002 L2667948A **ISAAC, NADA, PART NAME, ETC.***FOUND FUEL PRESSURE LINE, PN 1250990-16, AND OIL PRESSURE LINE, PN 1250990-15, RUBBING IN ENGINE COMPARTMENT. THESE LINES RUN FROM FUEL DISTRIBUTOR MANIFOLD TO RT REAR BAFFLE AND RT FRONT OIL PASSAGE TO RT REAR BAFFLE. OIL PRESSURE LINE IS CLAMPED TO PUSH ROD TUBES TWO PLACES. BOTH LINES WERE WORN THROUGH TO THE POINT OF LE AKING AT ANY TIME. THIS IS A NEW AIRCRAFT WITH 450 TOTAL HOURS. LINES NEED TO BE BENT SLIGHTLY AND REPOSITIONED TO PRE VENT THIS PROBLEM. NOTE: THIS COULD HAVE CAUSED A FIRE IN THE ENGINE COMPARTMENT AS SOON AS THE NEXT FLIGHT. (X) 1 H 7 1 3O 3 O RT A4CE 1E4 2000062100164 20000621 00164 SO 2000 6 21 20000620SH017 1 20000530 G 7120 6711957 MOUNT PIPER PA28 PA28R201 7102816 SO RT DRAG BRACE BROKEN B OG5R O OTHER J WARNING INDICATION TO TAKEOFF 1 GL 21 175ND 8696 2837029 PILOT REPORTED GEAR UNLOCKED INDICATION WITH GEAR RETRACTED. INVESTIGATION FOUND ENGINE MOUNT TUBE BROKEN JUST ABOVE RI GHT DRAG BRACE MOUNT. WHEN GEAR WAS RETRACTED, MOUNT FLEXED NOT ALLOWING UPLOCK SWITCH CONTROL. (X) 1 L 7 1 3O 2A13 2000072000138 20000720 00138 SO 2000 7 20 20000620SH018 1 20000508 G 7921 8535311 COOLER PIPER PA31 PA31310 7103103 SO LYC O540 TIO540J2BD 41532 EA RT ENG OIL SYS FAILED D C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CE 07 7436L 4600 120 317400994 L1028561A AS AIRCRAFT ROTATED DURING TAKEOFF, MANIFOLD PRESSURE DROPPED, PILOT FOUND LOW OIL RPESSURE, AND RETURNED TO AIRPORT AND SECURED ENGINE AFTER LANDING. ON INSPECTION, FOUND OIL COOLER BOWED OUTWARD AND INNER COILS BULGED WITH 2.5 INCH SPLIT . OIL COOLER WAS OVERHAULED APPROXIMATELY 120 HRS. NO APPARENT DAMAGE OTHER THAN LISTED FOUND ON COOLER. FOUND NO REA SON FOR COOLER RUPTURE. ON ENGINE GROUND TEST, ALL ENGINE PRESSURES NORMAL. (X) 1 L 7 1 3O 3 O RT A20SO E14EA 2000062900124 20000629 00124 SW 2000 6 29 20000620SH030 1 20000602 G 6200 MS3116FB4S CONNECTOR BELL 407 407 SW ALLSN 250C 250C47B GL M/R TRANSMISSION READS HIGH B CYXR O OTHER O OTHER NR NOT REPORTED 1 CE 01 407LG 635 53143 CAE847161 *****MICKEY****,PART LOCATION: TRANSMISSION OIL PRESSURE MANIFOLD*****PILOT REPORTED A HIGH OIL PRESSURE INDICATION (11 0 PSI) ON THE TRANSMISSION OIL PRESSURE INDICATOR. THIS READING WAS CAUSED BY DIRT/CORROSION INSIDE OF AN ELECTRICAL CO NNECTOR ON THE SYSTEMS PRESSURE TRANSDUCER. CONNECTOR WAS CLEANED AND SYSTEM WAS CHECKED GOOD WITH AN EXTERNAL CALIBRAT ED GAUGE. OPERATOR: ST LUKES HOSPITAL, CEDAR RAPIDS, IOWA. 1 G 7 1 3U 3 U O H2SW E1GL 2000062800190 20000628 00190 2000 6 28 20000620SH031 4 20000607 G 6113 D3291 BULKHEAD BEECH 33 35C33 1151408 CE MCAULY 2A36C 2A36C23 GL CRACKED H K NONE O OTHER IN INSP/MAINT 1 WP 15 6134V 100 CD864 705098 CRACKS FORMED AROUND 4 OF ATTACHING BOLTS IN BULKHEAD IN USE LESS THAN 100 HOURS. ATTACHING FLANGE APPEARS TO BE RUBBIN G AGAINST HUB. FLANGE IS MISFORMED. MANUFACTURING DEFECT. (X) 1 L 7 1 3O 3A15 5 C P880 2000062900125 20000629 00125 NE 2000 6 29 20000621SH002 2 20000223 G 7313 430167601 MANIFOLD BOLKMS 117 BK117B1 5626012 EU LYC LTS101 LTS101750B1 41560 NE FUEL NOZZLE DEFECTIVE A R7MA O OTHER O OTHER IN INSP/MAINT 1 NM 07 911VU 7141 LE45583EFA IMPROPER NOZZLE SPRAY PATTERN. REQUIRED 6000-HOUR INSPECTION. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U 3 U H13EU E5NE10 2000100200014 20001002 00014 NE 2000 10 2 20000621SH005 2 20000201 G 7313 430167601 MANIFOLD BOLKMS 117 BK117B1 5626012 EU LYC LTS101 LTS101750B1 41560 NE NOZZLE IMPROPER A R7MA O OTHER O OTHER IN INSP/MAINT 1 NM 07 117BK 653 7229 LE45753EFA IMPROPER NOZZLE SPRAY PATTERN. REQUIRES 600 HOUR INSPECTION. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U 3 U H13EU E5NE10 2000100200015 20001002 00015 NE 2000 10 2 20000621SH006 2 20000420 G 7412 9550176020 EXCITER SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1B 6OO30 NE HE GENERATOR INOPERATIVE A R7MA O OTHER O OTHER NR NOT REPORTED 1 NM 07 151AC 107 1173 415 HE GENERATOR INOPERATIVE. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U 3 U H9EU E19EU 2000100200016 20001002 00016 EU 2000 10 2 20000621SH007 1 20000414 G 2612 0301037070 HARNESS SNIAS 350 AS350B2 8680813 EU FIRE DETECTION INOPERATIVE A R7MA O OTHER O OTHER IN INSP/MAINT 1 NM 07 93LG 221 2654 T4 HARNESS INOPERATIVE. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2000072600168 20000726 00168 WP 2000 7 26 20000621SH008 2 20000313 G 7250 30747522 DISK GARRTT TFE731 TFE731* 01518 WP POST FIR TREE DAMAGED B K NONE O OTHER IN INSP/MAINT 1 GL 19 NEW PART RECEIVED WITH DAMAGE IN POST FIR TREE AREA ON BOTH FORWARD AND AFT SIDE. RE: LOT NUMBER: OOPO14. (X) 4 F E6WE 2000072600077 20000726 00077 WP 2000 7 26 20000621SH009 2 20000309 G 7250 30720705 DISK GARRTT TFE731 TFE731* 01518 WP POST FIR TREE DAMAGED H K NONE O OTHER IN INSP/MAINT 1 SW 99 NEW PART RECEIVED WITH DAMAGE ON AFT SIDE IN POST FIR TREE AREA. LOT NUMBER: 99P348. (X) 4 F E6WE 2000072400078 20000724 00078 WP 2000 7 24 20000621SH014 1 20000607 G 3246 152058 WHEEL DOUG DC8 DC8* WP MLG CRACKED B K NONE O OTHER IN INSP/MAINT 1 SO 19 NDT INSPECTION SHOWED CRACK INDICATION AT BEAD SEAT AREA. (X) 2 L 7 4 4J F 4A25 2000100200252 20001002 00252 EA 2000 10 2 20000622SH002 1 20000622 G 3230 269A3170 DAMPER SCWZER 269 269D 8059501 EA LANDING GEAR CRACKED H O OTHER O OTHER NR NOT REPORTED 1 SW 99 296RL 1862 0020 BOTH OF THE FORWARD LANDING GEAR DAMPERS WERE FOUND WITH A COMPLETE CRACK ON THE UPPER CAP THE CRACK EXTENDS FROM THE B EARING BORE TO THE TOP OF THE CAP. (X) 1 G 7 1 3U 0 4H12 2000101200165 20001012 00165 SO 2000 10 12 20000622SH011 2 20000606 G 8530 CYLINDER BEECH 35 G35 1151516 CE CONT E225 E2258 17015 SO FAILED B K NONE O OTHER IN INSP/MAINT 1 NE 05 231B 155 D4651 36361D7388R ENGINE WAS REMOVED 3 TIMES FOR LOW OIL PRESSURE, AND IT HAD NEW CYLINDERS AT OVERHAUL. SUBMITTER REMOVED ALL 6 CYLINDER S AT 89.9 TSO FOR LOW COMPRESSION LEAKING BY EXHAUST VALVES, 3 CYLINDERS REMOVED AT 154.3 TSO WHICH IS 64.4 HOURS FROM T HE LAST REMOVAL AND REPAIRED. (X) 1 L 7 1 3O 3 O A777 E267 2000100200245 20001002 00245 GL 2000 10 2 20000622SH012 2 20000201 G 7250 23038229 GEAR SHAFT ALLSN AROFAL OH58 OH58C 1181580 SW ALLSN 250C 250C20C 03013 GL GAS PRODUCER SHEARED B HEFR O OTHER O OTHER IN INSP/MAINT 1 WP 21 38FA 1312 7015448 AE405837 ENGINE WAS REMOVED FROM AIRCRAFT BECAUSE IT WAS GENERATING METAL IN THE OIL. AFTER DISASSEMBLY, IT WAS VIEWED THAT THE GEAR SHAFT IN QUESTION HAD SHEARED. THE SHAFT HAD SHEARED FROM WHERE IT MATES WITH THE MAIN GEAR PORTION OF THE PART. NO PROBLEMS WITH RELATED GEARS, BEARINGS, ETC., WERE FOUND TO SUBSTANTIATE A CAUSE FOR THE FAILURE. PART WAS RETURNED T O ALLISON FOR FAILURE ANALYSIS PER ALLISON REF CN0099F-REH 0200. (X) 1 G 7 1 3U 3 U NC H22NM E4CE 2000101200168 20001012 00168 2000 10 12 20000622SH015 4 20000127 G 2200 KA132 ACCELEROMETER KING PIPER PA31 PA31350 7103110 SO FWD RADIO RACK FAULTY H O OTHER O OTHER NR NOT REPORTED 1 AL 01 3536B 317952205 ACCELERATION SWITCH - WHEN SUBJECTED TO VIBRATION (ENGINE AT HIGH POWER OR IN FLIGHT), SERVOS ENGAGE, BUT WILL NOT DRIVE , COMMAND BARS FUNCTION PROPER. AP LIGHT VARIES FROM FULL BRIGHTNESS TO HALF BRIGHT AT A CONSTANT RATE. REPLACED ACCEL ERATION SWITCH AGAIN WITH NEW. A/P WORKS NORMAL. (X) 1 L 7 2 3O A20SO 2000071800521 20000718 00521 CE 2000 7 18 20000622SH016 1 20000210 G 3230 6070843004 RETAINER BEECH 200 B200 1152922 CE PILOT SUB-PANEL BROKEN H K NONE O OTHER IN INSP/MAINT 1 NM 09 3127K BB1293 LANDING GEAR DOWN AND LOCKED ANNUNCIATOR BULB LOST ELECTRICAL POWER DUE TO WORN ANNUNCIATOR CAP RETAINING PINS ALLOWING CAP TO SEPARATE FROM ANNUNCIATOR ASSEMBLY. REF: B200 WIRING MANUAL 32-61-00, PAGE 2. (X) 1 L 7 2 4T A24CE 2000071800012 20000718 00012 CE 2000 7 18 20000622SH018 2 20000425 G 7322 654353 SERVO PIPER PA34 PA34220T 7103420 SO CONT O360 TSIO360RB 17025 CE TOP ENGINE (AFT) GOUGED H K NONE O OTHER IN INSP/MAINT 1 SW 99 4161D 70196810 3449141 322031 FUEL SERVO GOUGED AT BASE BY SHOCK MOUNT ATTACHED TO ENGINE. SUBMITTED STATED SHOCK MOUNT DOES NOT COVER COMPLETE BASE OF SERVO. (X) 1 L 7 2 3O 3 O A7SO E9CE 2000101200006 20001012 00006 SO 2000 10 12 20000622SH019 1 20000513 G 2823 6965422 ARM PIPER PA32 PA32R301 7103218 SO FUEL SELECTOR ST BENT G A UNSCHED LANDING O OTHER CR CRUISE 1 WP 07 4148R 1800 3246129 DURING FLIGHT, THE STUDENT PILOT INADVERTENTLY SHUT THE FUEL OFF CAUSING AN EMERGENCY LANDING AND DAMAGE TO THE RIGHT WI NG. INVESTIGATION REVEALED THE FUEL SELECTOR COULD BE MOVED TO THE OFF POSITION WITH LITTLE RESISTANCE. THE STOP IS AT TACHED TO THE CENTER PANEL AND ITS SPRING STEEL ARM WAS FOUND BENT ALLOWING THE SELECTOR HANDLE TO BYPASS THE STOP. (X) 1 L 7 1 3O A3SO 2001020200006 20010202 00006 SW 2001 2 2 20000622SH021 1 20000209 G 5510 407023002117 SLAT BELL 407 407 SW HORIZONTAL DAMAGED B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 407WH 369 532027 REPLACED WITH NEW SLATS FROM BELL HELICOPTER. C/W BELL ASJ 407-99-32. (X) 1 G 7 1 3U O H2SW 2001020200007 20010202 00007 SW 2001 2 2 20000622SH022 1 20000209 G 2840 407375016101 SIGNAL COND UNIT BELL 407 407 SW FUEL SYSTEM INTERMITTENT B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 407WH 369 532027 REPLACED WITH NEW FUEL SIGNAL CONDITIONER FROM BELL HELICOPTER. (X) 1 G 7 1 3U O H2SW 2001020200010 20010202 00010 GL 2001 2 2 20000622SH025 2 20000224 G 7320 23072725 FUEL CONTROL BELL 407 407 SW ALLSN 250C 250C47B GL HMU FAILED H K NONE O OTHER IN INSP/MAINT 1 GL 13 407CR 1058 433 53254 START PROBLEMS, I.E., (NON-STARTS, ERRATIC STARTS). CHANGED HMU. OPS NORMAL PER MM (ALLISON). (X) 1 G 7 1 3U 3 U O H2SW E1GL 2001020200011 20010202 00011 SW 2001 2 2 20000622SH026 1 20000317 G 3530 GAUGE BELL 407 407 SW OXYGEN BOTTLE LEAKING H K NONE O OTHER IN INSP/MAINT 1 SW 99 407CR 481 53254 OXYGEN GAUGE LEAKING AT CONNECTION PIPE THREADS. SUBMITTER SUGGESTED INSTALLING FLARED OR BRASS FITTINGS TO SEAL BETTER . (X) 1 G 7 1 3U O H2SW 2000062800192 20000628 00192 CE 2000 6 28 20000622SH027 2 20000518 G 7322 RSA5AD2 SERVO PIPER PA34 PA34220T 7103420 SO CONT O360 TSIO360RB 17025 CE FUEL INJECTOR FAILED B VJ3R O OTHER Y ENGINE STOPPAGE TX TAXI/GRND HDL 1 WP 07 4142N 923 450 3449128 322265LN LEFT ENGINE DIED ON ROLL-OUT AFTER LANDING. THIS SERVO HAS 923 HOURS TT SINCE NEW AND 450 HOURS FROM REPAIR OF MIXTURE PLATE. ENGINE RAN ROUGH AT IDLE AND AT LOW POWER SETTINGS. THE MIXTURE WAS ON THE RICH SIDE AND UNABLE TO ADJUST MIXTU RE. SERVO REMOVED AND A NEW ONE INSTALLED IAW TCM AND PIPER MM. (X) 1 L 7 2 3O 3 O A7SO E9CE 2000062800193 20000628 00193 EA 2000 6 28 20000622SH028 2 20000506 G 8530 SEAT AMRGEN AA5 AA5 0631410 SO LYC O320 O320D3G 41508 EA NR 1 CYLINDER MISALIGNED H K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 11 5437L 92 AA50337 L133339A ANNUAL INSPECTION FOUND NO COMPRESSION ON NR 1 CYLINDER. REMOVED CYLINDER, SENT FOR REPAIR. FOUND INTAKE VALVE SEAT IN STALLED WRONG (AT ANGLE) HAD BENT INTAKE VALVE. ALSO, ENGINE HAD NOT BEEN DE-SLUDGED AT OVERHAUL CAUSING PITS. FOUND A T AD INSPECTION AFTER 20 HOURS. (X) 1 L 7 1 3O 3 O A16EA E274 2000062700140 20000627 00140 SW 2000 6 27 20000622SH031 1 20000609 G 2720 500012265 CONTROL CABLE GULSTM 690TP 690B 7630516 SW RT RUDDER FRAYED B K NONE O OTHER IN INSP/MAINT 1 GL 11 489GA 11530 RIGHT RUDDER CABLES FRAYED. (X) 1 H 7 2 3T 2A4 2000062700142 20000627 00142 2000 6 27 20000622SH034 4 20000622 G 2300 CM35895059825010 SWITCH CESSNA 414 414A 2075907 CE FAILED B QFYR K NONE O OTHER IN INSP/MAINT 1 NE 03 643WM 2480 414A1205 DURING TROUBLESHOOTING, FUEL FLOW INDICATION PROBLEM. TECHNICIAN NOTED THE AVIONICS SWITCH FELT ''ABNORMAL''. DID NOT HAVE ''POSITIVE FEEL''. NEW SWITCH INSTALLED. NOTE: REMOVED SWITCH TOTALLY FAILED DURING OPERATION CHECK AFTER REMOVA L. SWITCH LEVER SEIZED. (X) 1 L 7 2 3O A7CE 2000062700143 20000627 00143 SO 2000 6 27 20000622SH035 1 20000104 G 2432 AN33701 CONTACTOR PIPER PA23 PA23250 7102308 SO BATTERY CORRODED H K NONE O OTHER IN INSP/MAINT 1 EA 25 6913A 1795 277954108 DURING ROUTINE MAINTENANCE FOR 100-HOUR INSPECTION, NOTED CORROSION AFTER FAILURE OCCURRED. DISASSEMBLED AND FOUND UNIT FULL OF RUST AND CORROSION CAUSING TOTAL ELECTRICAL SYSTEM FAILURE. (X) 1 L 7 2 3O 1A10 2000062700144 20000627 00144 EA 2000 6 27 20000622SH036 2 20000404 G 7322 MA4SPA CARBURETOR CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA SEPARATED D O OTHER W R INADEQUATE Q C PARTIAL RPM/PWR LOSS CR CRUISE 1 EA 07 6212G 764 17273579 RL515876T AIRCRAFT ENGINE RAN ROUGH DURING FLIGHT. WAS UNABLE TO SHUT ENGINE DOWN USING MIXTURE CONTROL. FOUND CARBURETOR BOWL SEPARATING FROM CARBURETOR BODY. ALL SCREWS WERE SECURED BY SAFETY TABS AND FACTORY TORQUE SEAL, BUT SCREWS WERE LOOSE. SUBMITTER SUSPECTED IMPROPER TORQUE OF SCREWS DURING OVERHAUL. CARBURETOR REPLACED W ITH OVERHAULED UNIT. FUNCTIONS N ORMAL. (X) 1 H 7 1 3O 3 O NT 3A12 E274 2000062700145 20000627 00145 CE 2000 6 27 20000622SH040 1 20000531 G 8100 LW15550 ROTOR LYC CESSNA 182 TR182 2072735 CE LYC O540 O540L3C5 41532 EA OIL PUMP BROKEN G A UNSCHED LANDING O OTHER CR CRUISE 1 NM 07 738FN 287 R18200921 ENGINE TURBO SCAVENGING PUMP FAILED. THIS ALLOWED THE ENGINE TO PUMP ALL THE ENGINE OIL OVERBOARD THROUGH THE TURBO. E MERGENCY OFF AIRPORT LANDING CAUSED SUBSTANTIAL DAMAGE TO AIRCRAFT. (X) 1 H 7 1 3O 3 O 3A13 E295 2000062700151 20000627 00151 SW 2000 6 27 20000623SH007 1 20000419 G 8120 30503505 MOUNT MOONEY M20 M20K 5870220 SW TURBO CRACKED B DY1R K NONE O OTHER IN INSP/MAINT 1 EA 13 9801Y 882 250526 DURING ANNUAL INSPECTION, FOUND TURBO SUPPORT MOUNT UPPER FOOT CRACKED AND LOWER FOOT AREA WHICH IS CLOSER TO TURBO EXHA UST SCROLL VERY RUSTY. REPLACED WITH NEW MOUNT WHICH HAS IMPROVED PLATING PROCESS. AIRCRAFT HAS BEEN MODIFIED IAW STC SA5691MM AND HAS A TSIO520 SERIES INSTALLED. THE PROXIMITY OF THE TURBOCHARGER TO THE ENGINE MOUNT AND TURBO SUPPORT TU BES REQUIRED CONSTANT INSPECTIONS FOR HEAT DAMAGED COMPONENTS. AD 95-17-06 IS NOT AVAILABLE TO THE TURBO SUPPORT TUBE F OUND CRACKED. SUBMITTER RECOMMENDED EXAMINATION OF THE AREA AROUND THE TURBO EXHAUST WHENEVER THE COWLING IS REMOVED. (X) 1 L 7 1 3O 2A3 2000062800194 20000628 00194 2000 6 28 20000623SH009 4 20000512 G 2370 066011550201 AUDIO PANEL CESSNA 172 172S 2072439 CE INTERMITTENT B ACOR K NONE O OTHER IN INSP/MAINT 1 SO 05 971SP 72 172S8173 COPILOT''S TRANSMISSION INTERMITTENT. KMA26 WAS NEW WHEN INSTALLED ON AIRCRAFT. (X) 1 H 7 1 3O NT 3A12 2000082800001 20000828 00001 NE 2000 8 28 20000623SH010 2 20000623 G 7230 772568QQ BOLT PWA JT8 JT8D7B 52053 NE HEAD FAILED B WG4R O OTHER O OTHER NR NOT REPORTED 1 SO 19 657618 PMA BOLT PN 772568QQ, REPLACEMENT FOR OEM BOLT, PN 772568, FAILED AFTER 1.548.5 HOURS AND 932 CYCLES IN SERVICE. BOLT F RACTURED CAUSING HEAD TO BE INGESTED INTO THE N-2 COMPRESSOR DRIVE TURBINE WHERE EXTENSIVE DAMAGE WAS INFLICTED. BOLT W AS FROM AFFECTED BATCHES AS DESCRIBED IN FLIGHT STANDARDS INFORMATION BULLETIN FOR AW NR FSAW 00-07. (X) 4 F E2EA 2000062700152 20000627 00152 WP 2000 6 27 20000623SH013 2 20000609 G 7230 30752272 DISK GARRTT TFE731 TFE731* 01518 WP CURVIC INADEQUATE H K NONE O OTHER IN INSP/MAINT 1 GL 19 NEW PART RECEIVED WITHOUT HIGH SPOT ON CURVIC BEING MARKED ON EITHER SIDE. LOT NR: 00P159. (X) 4 F E6WE 2000100200053 20001002 00053 EU 2000 10 2 20000623SH014 1 20000608 G 2500 C533C DOOR UROCOP EC120 EC120B 8680987 EU SLIDEUPPER HINGE SEPARATED H K NONE D INFLIGHT SEPARATION CR CRUISE 1 SW 09 182TA 862 1001 DURING PHOTO FLIGHT MISSION, SLIDING DOOR, STD EQUIP (STOWED IN THE AFT LOCKED POSITION BEFORE TAKEOFF), AIRSPEED AT OR BELOW FLIGHT MANUAL LIMITATIONS FOR SLIDING DOOR OPEN, EXITED ACFT. THE AIRSTREAM PULLED THE SLIDING DOOR FROM LOWER LT CORNER AWAY FROM THE SLIDING DOOR RAIL, BENDING UPPER LT HINGE POINT ROLLER OUT OF THE RAIL, HINGING AFT UPPER AND LOWE R HINGE POINTS, SWINGING BACK TO CONTACT THE AIRFRAME STRUCT IMMEDIATELY BEHIND SLIDING DOOR ASSY, FINALLY BREAKING THE UPPER AND LOWER SLIDING ASSYS AWAY FROM FRAME RAILS. SUBMITTER RECOMMENDED TO PREVENT RECURRENCE, CLOSE UP TOLERANCE ON FRAME RAILS AGAINST SLIDING DOOR ROLLERS, AND ENHANCE STOPS AT ENDS OF EACH FR RAIL (4 POINTS). DOOR ASSY RECOVERED. 1 G 7 2 3U NC R0001RD 2000062700153 20000627 00153 SW 2000 6 27 20000623SH015 1 20000520 G 7920 31014284 FITTING MTSBSI MU2 MU2B30 5780410 SW GARRTT TPE331 TPE3316 01514 WP COOLER DETERIORATED C DKBA E ENGINE SHUTDOWN K FLUID LOSS CR CRUISE 1 SO 09 13RR 8000 4000 682 P20478 OIL SUPPLY LINE FOR OIL COOLER, FITTING THREADS IN CASE DETERIORATED ALLOWING FITTING TO BLOW OUT. THIS ALLOWED ENGINE OIL TO PUMP OUT. PILOT SHUT ENGINE DOWN WITHOUT DAMAGE TO ENGINE. (X) 1 H 7 2 3T 4 T A2PC E4WE 2000062700154 20000627 00154 CE 2000 6 27 20000623SH016 1 20000425 G 5620 010A31890 WINDOW MTSBSI MU2 MU2B25 5780409 CE LEFT CABIN SEPARATED B IZ2R A UNSCHED LANDING D INFLIGHT SEPARATION CR CRUISE 1 SW 15 10BK 6477 272 IN-FLIGHT, APPROXIMATELY 18,000 FEET, AIRCRAFT LOST PRESSURIZATION. AFTER LANDING, INSPECTION OF THE AIRCRAFT REVEALED LEFT CABIN WINDOW HAD FAILED. DAMAGE WAS LIMITED TO THE WINDOW, NO OTHER AIRFRAME PARTS WERE DAMAGED. WINDOW HAD BEEN POLISHED 8 MONTHS EARLIER. (X) 1 H 7 2 3T A2PC 2000062700155 20000627 00155 2000 6 27 20000623SH017 4 20000607 G 6122 A20066 GEAR MCAULY MOONEY M20 M20K 5870220 SW CONT O360 TSIO360LB 17025 SO CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 231MS 462 794319 250313 RELEVANT CRACK INDICATION. (X) 1 L 7 1 3O 3 O 2A3 E9CE 2000062800195 20000628 00195 CE 2000 6 28 20000623SH018 1 20000609 G 3222 07421801 BUSHING CESSNA 180 180K 2072624 CE TAIL WHEEL SPRIN ERODED G K NONE O OTHER IN INSP/MAINT 1 NM 09 2879K 8 18053115 RECENTLY INSTALLED TAILSPRING BUSHINGS FOUND EXTRUDED AFTER ONLY 8 HOURS OF OPERATION. SUBMITTER KNOWS OF ONE OTHER LOW TIME FAILURE OF THESE BUSHINGS. (X) 1 H 7 1 3O 5A6 2000082100160 20000821 00160 CE 2000 8 21 20000626SH002 1 20000613 G 5740 08112761 FITTING CESSNA 310 310J 2074226 CE RT REAR SPAR CORRODED D K NONE O OTHER IN INSP/MAINT 1 NM 10 3079L 3000 310J0079 EXFOLIATION CORROSION AT LEAST .01 INCH TO .1250 INCH DEEP AND GROWING. SUBMITTER STATES THAT AIRCRAFT WAS BASED IN SAN FRANCISCO BAY AREA AND SALT AIR MAY HAVE CONDENSED INSIDE THE AIRCRAFT INSULATION AND DRIPPED DOWN ON THE FITTINGS. HO WEVER, SUBMITTER BELIEVED THE ORIGINAL CORROSION MAY HAVE BEEN INTERGRANULAR THAT PROGRESSED. (X) 1 L 7 2 3O 3A10 2000082100165 20000821 00165 CE 2000 8 21 20000626SH003 1 20000613 G 5711 08112763 SPAR CESSNA 310 310J 2074226 CE UPER INSIDE CABI CORRODED D K NONE O OTHER IN INSP/MAINT 1 NM 10 310J 3000 310J0079 EXFOLIATION CORROSION AT LEAST .01 INCH TO .1250 INCH DEEP AND GROWING. SUBMITTER STATES THAT AIRCRAFT WAS BASED IN SAN FRANCISCO BAY AREA AND SALT AIR MAY HAVE CONDENSED INSIDE THE AIRCRAFT INSULATION AND DRIPPED DOWN ON THE FITTINGS. HO WEVER, SUBMITTER BELIEVED THE ORIGINAL CORROSION MAY HAVE BEEN INTERGRANULAR THAT PROGRESSED. (X) 1 L 7 2 3O 3A10 2000082100182 20000821 00182 CE 2000 8 21 20000626SH005 1 20000519 G 5312 24122013 BULKHEAD CESSNA 172 172RG 2072438 CE BS 108.00 LT CRACKED B EBVD K NONE O OTHER IN INSP/MAINT 1 GL 09 5169V 6935 172RG0458 DURING INSPECTION, THE LEFT AND RIGHT BULKHEADS AT BS 108.00 WERE FOUND CRACKED. THE CRACKS EMANATED FROM THE BULKHEAD FLANGE THAT IS RIVETED TO THE HAT RACK SKIN. BOTH BULKHEADS WERE REPLACED WITH NEW. RECOMMEND CLOSE INSPECTION OF THIS AREA. ALL BAGGAGE AREA TRIM MUST BE REMOVED IN ORDER TO INSPECT THIS AREA. SUBMITTER STATED INSPECT ESPECIALLY IF HAT RACK IS USED FREQUENTLY. (X) 1 H 7 1 3O 3A17 2000082100183 20000821 00183 CE 2000 8 21 20000626SH006 1 20000519 G 5312 24120014 BULKHEAD CESSNA 172 172RG 2072438 CE BS 108.00 RT CRACKED B EBVD K NONE O OTHER IN INSP/MAINT 1 GL 09 5169V 6935 172RG0458 DURING INSPECTION, THE LEFT AND RIGHT BULKHEADS AT BS 108.00 WERE FOUND CRACKED. THE CRACKS EMANATED FROM THE BULKHEAD FLANGE THAT IS RIVETED TO THE HAT RACK SKIN. BOTH BULKHEADS WERE REPLACED WITH NEW. RECOMMEND CLOSE INSPECTION OF THIS AREA. ALL BAGGAGE AREA TRIM MUST BE REMOVED IN ORDER TO INSPECT THIS AREA. SUBMITTER STATED INSPECT ESPECIALLY IF HAT RACK IS USED FREQUENTLY. (X) 1 H 7 1 3O 3A17 2000082100184 20000821 00184 CE 2000 8 21 20000626SH008 1 20000523 G 2450 ATC30 FUSE LAMAR CESSNA 172 172S 2072439 CE F2 BROKEN D O OTHER O OTHER IN INSP/MAINT 1 WP 07 508ER 1571 80111810 172S8008 AIRCRAFT LOST POWER TO NR 1 BUSS, TAB, NR 1 COMM, ETC. FOUND F2 PUSH IN TYPE 30-AMP FUSE IN ELECTRICAL DISTRIBUTION BOX INTERMITTANT. FUSE WAS NOT BLOWN, BUT PUSHING ON IT MADE CONTACT WITH A+. TRYING TO REMOVE FUSE, IT BROKE A TAB OFF. THERE WAS ARCING ON THE TAB THAT CAUSED THE INTERMITTANT. (X) 1 H 7 1 3O NT 3A12 2000082800017 20000828 00017 EA 2000 8 28 20000626SH009 2 20000615 G 8520 CRANKSHAFT MOONEY M20 M20C 5870208 SW LYC O360 O360A1D 41514 EA BROKEN D A UNSCHED LANDING R W PARTIAL RPM/PWR LOSS INADEQUATE Q C NR NOT REPORTED 1 EA 05 6715U 908 2447 L942436A AIRCRAFT INVOLVED IN AN ACCIDENT BECAUSE OF AN ENGINE FAILURE. THE ENGINE WAS DISASSEMBLED BY THE MANUFACTURER WITH THE FOLLOWING FINDINGS. THE WRONG PART NUMBER CRANKSHAFT WAS INSTALLED IN THE ENGINE. THE SLUDGE TUBES, P/N 71577, WERE NOT INSTALLED ON THE CRANK PINS. THE SLUDGE TUBES AID IN THE LUBRICATION OF THE CRANKSHAFT AND RODS. IN THE CASE OF TH IS ENGINE, THE NR 2 ROD CAP FAILED CAUSING THE ROD TO BREAK THROUGH THE CASE RESULTING IN THE ENGINE FAILING. (X) 1 L 7 1 3O 3 O 2A3 E286 2000082100186 20000821 00186 SO 2000 8 21 20000626SH010 1 20000523 G 7160 DETAIL4 GASKET MAULE MX7 MX7180 5460185 SO LYC O360 O360C1F 41514 EA HEAT BOX LOOSE D O OTHER R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 EA 25 5661P 11006C L3112036A THE DIAMETER OF HEAT BOX THROAT IS LARGER THAN SEALING SURFACE OF CARBURETOR GASKET ALLOWING CARBURETOR BASKET TO REMAIN LOOSE. COULD BE SUCKED INTO CARBURETOR. NOTED DURING ENGINE CHANGE. (X) 1 H 7 1 3O 3 O NC 3A23 E286 2000082100187 20000821 00187 CE 2000 8 21 20000626SH011 1 20000626 G 2410 A144666 ALTERNATOR CESSNA 210 210M 2073450 CE ENGINE LOOSE D DKBA K NONE O OTHER IN INSP/MAINT 1 SO 09 761PS 800 21062415 FOUND GROUND STUD TO BE LOOSE ON BACK OF ALTERNATOR. (X) 1 H 7 1 3O 3A21 2000082100188 20000821 00188 CE 2000 8 21 20000626SH012 1 20000522 G 2437 WIRE MTSBSI MU2 MU2B26A 5780414 CE CHAFED B IZ2R O OTHER H ELECT. POWER LOSS-50 PC NR NOT REPORTED 1 SW 15 741MA 355SA PILOT REPORTED TO MAINTENANCE THAT THE LEFT AMP GAUGE WENT TO ZERO AMPS, BUT LEFT GENERATOR STAYED ON-LINE. INVESTIGATI ON REVEALED CHAFED WIRE BUNDLE IN LEFT MIB AT GROUND ATTACH POINT E253. REPAIRED 7 CHAFED WIRES AND PROTECTED AS NEEDED . SYSTEM OPS CHECKED SATISFACTORY. (X) 1 H 7 2 3T RT A10SW 2000082100189 20000821 00189 CE 2000 8 21 20000626SH013 1 20000613 G 5510 7321014 BRACKET CESSNA 182 182Q 2072732 CE LT AFT HORIZ STA CRACKED D K NONE O OTHER IN INSP/MAINT 1 NM 03 951CC 13427 18266998 DURING 100-HOUR ANNUAL INSPECTION, THE HORIZONTAL STABILIZER ATTACHMENT POINT REINFORCEMENT ON LEFT SIDE WAS FOUND CRACK ED. SUSPECTED CAUSE WAS PART HIGH TIME. ALTHOUGH THE RIGHT REINFORCEMENT WAS NOT CRACKED, IT WAS REPLACED DUE TO HIGH TIME. (X) 1 H 7 1 3O NT 3A13 2000082200036 20000822 00036 SO 2000 8 22 20000626SH014 2 20000613 G 8530 65465044 CYLINDER CESSNA 182 182Q 2072732 CE CONT O470 O470U 17026 SO NR 6 WORN D K NONE O OTHER IN INSP/MAINT 1 NM 03 951CC 1380 18266998 813325R CYLINDER NR 6 WAS REMOVED BECAUSE THE COMPRESSION WAS 50/80 DUE TO LEAKAGE PAST THE INTAKE VALVE. AFTER INSPECTION OF T HE CYLINDER, THE CYLINDER ASSY WAS REPLACED DUE TO A WEAR STEP AT THE TOP OF THE CYLINDER BARREL. (X) 1 H 7 1 3O 3 O NT 3A13 E273 2000082200037 20000822 00037 CE 2000 8 22 20000626SH015 1 20000613 G 7713 0700099138 LINE CESSNA 182 182Q 2072732 CE MANIFOLD/FIREWAL BROKEN D K NONE O OTHER IN INSP/MAINT 1 NM 03 951CC 13359 18266998 MANIFOLD PRESSURE LINE WAS FOUND BROKEN AFTER PILOT REPORTED GAUGE READING AMBIENT PRESSURE. POSSIBLE CAUSE, HIGH PART TOTAL TIME. (X) 1 H 7 1 3O NT 3A13 2000082200038 20000822 00038 SO 2000 8 22 20000626SH017 2 20000525 G 7322 RSA5AD FUEL CONTROL PIPER PA34 PA34220T 7103420 SO CONT O360 TSIO360KB 17025 SO FAILED H VJ3R O OTHER R PARTIAL RPM/PWR LOSS LD LANDING 1 WP 07 9299E 54 3449043 ENGINE DIED ON LANDING ROLL-OUT. AIRCRAFT WAS TAKEN TO MAINTENANCE AND A GROUND RUN PERFORMED. THE FUEL SERVO ON THIS ENGINE WAS RICH AT IDLE AND UNABLE TO ADJUST MIXTURE. SERVO WAS REMOVED FROM ENGINE AND SENT FOR REPLACEMENT. TOTAL TI ME ON UNIT WAS 54 HOURS. FROM NEW, THIS IS A -5 SERVO. (X) 1 L 7 2 3O 3 O A7SO E9CE 2000062700156 20000627 00156 GL 2000 6 27 20000626SH019 1 20000529 G 3240 Y139APU7 VALVE YAKLEV YAK YAK52 9830220 GL PNEUMATIC BRAKE INOPERATIVE H O OTHER O OTHER TX TAXI/GRND HDL 1 WP 07 208YA 435 8910009 BRAKE SYSTEM FAILED WHILE TAXIING FROM HANGAR TO RAMP. FOUND ''REDUCING VALVE'' DEFECTIVE. (REF: BLK NR 5). (X) 1 L 7 1 3R RT EXPA1L71 2000082200039 20000822 00039 CE 2000 8 22 20000626SH020 1 20000614 G 5312 BULKHEAD BEECH 55 E55 1152732 CE CRACKED B NT2R K NONE O OTHER IN INSP/MAINT 1 CE 07 3085W 2206 TE954 INSTALLED KIT, PN 55-4030-5S, SI 0090 REV II. INSPECTED FOR POSSIBLE CRACKS. FOUND CRACKS ON BOTH LT AND RT SIDES OF B ULKHEAD. CRACK .75 INCH LT SIDE. CRACK .3750 INCH RT SIDE, SAME LOCATION. (X) 1 L 7 2 3O 3A16 2000062800223 20000628 00223 CE 2000 6 28 20000626SH021 1 20000514 G 2430 23AT2T2 SWITCH CESSNA 414 414 2075908 CE STANDBY/MAIN REG FAILED H O OTHER A FLAME/FIRE IN INSP/MAINT 1 SW 99 313RW 4140010 THE STANDBY/MAIN VOLTAGE REGULATOR SWITCH FAILED INTERNALLY CAUSING THE NOISE FILTERS, PN CM221, TO SHORT AND CATCH ON F IRE. (X) 1 L 7 2 3O RT A7CE 2001020500174 20010205 00174 NE 2001 2 5 20000626SH023 2 20000308 G 7230 1A9642 LOCK PWA 2037 F117PW100 NE ENGINE UNSECURE B WA2D K NONE W INADEQUATE Q C IN INSP/MAINT 1 NE 03 2191 P170090 IMPROPER ASSEMBLY. WING BORESCOPE INSPECTION DISCLOSED ONE 7TH STAGE BLADE LOCK NOT CRIMPED. DIS-ASSEMBLY INSPECTION V ERIFIED ON WING FINDINGS. REVIEW OF PAST BUILD AND PROCEDURES BEING PERFORMED TO DETERMINE ROOT CAUSE. LAST BUILD PERF ORMED AT CRS WA2D259L. (X) 4 T E17NE 2000082300003 20000823 00003 GL 2000 8 23 20000626SH026 3 20000406 G 6110 SEAL CESSNA 206 206H 2073301 CE MCAULY 3D36C B3D36C432 GL PROP LEAKING E K NONE K FLUID LOSS IN INSP/MAINT 1 SW 99 2312V 298 20608046 991143 DURING PRE-FLIGHT INSPECTION OF THE AIRCRAFT IN A HANGAR, PILOT FOUND A LARGE POOL OF RED OIL ON THE FLOOR BENEATH THE P ROPELLER. UPON REMOVAL OF THE SPINNER, DETERMINED THE FLUID WAS LEAKING FROM UNDER A PROPELLER BLADE ROOT. THE PROPELL ER WAS REMOVED AND SENT OUT FOR REPAIR. (X) 1 H 7 1 3O RT A4CE 5 C P58GL 2000082300005 20000823 00005 SO 2000 8 23 20000627SH005 1 20000509 G 7120 86212002 MOUNT PIPER PA44 PA44180 7104402 SO LEFT BROKEN H K NONE O OTHER IN INSP/MAINT 1 NM 09 28721 447995296 DURING 100-HOUR INSPECTION, FOUND LT ENGINE MOUNT CRACKED AND BROKEN. FAILURE WAS LOCATED BETWEEN THE UPPER AND LOWER O UTBOARD LORD MOUNT LOCATION. TUBULAR MEMBER WAS FOUND COMPLETELY SEVERED WITH SMALL PIECE OF MATERIAL MISSING. PIPER S B 937 AND SL 719, WHICH DEAL WITH MOUNT REINFORCEMENT HAD NOT BEEN COMPLIED WITH. OVERHAULED MOUNT INCORPORATING BULLET INS WAS INSTALLED. (X) 1 L 7 2 3O A19S0 2000082300006 20000823 00006 CE 2000 8 23 20000627SH006 1 20000619 G 2450 ANL325 CURRENT LIMITER BEECH 200 200BEECH 1152920 CE MAIN BUSS TIE FAILED B DBCR O OTHER H ELECT. POWER LOSS-50 PC NR NOT REPORTED 1 GL 19 204JS 4695 BB842 SBM - UPON LEFT ENGINE START-UP, PILOT NOTED ZERO VOLTS ON RIGHT BUSS. TROUBLESHOT TO FAILED CURRENT LIMITER. REPLACED CURRENT LIMITER, PN ANL-M-325. OPS CHECK OK. (X) 1 L 7 2 4T A24CE 2000082300007 20000823 00007 SO 2000 8 23 20000627SH007 1 20000619 G 7120 3802000 MOUNT PIPER PA32 PA32R300 7103213 SO FRONT LOWER END CRACKED B DECR K NONE O OTHER IN INSP/MAINT 1 GL 19 38911 3366 32R7780488 SUPPORT TUBE AT LOWER CURVED TUBE BEHIND STEERING ARM FOUND CRACKED AT WELD. (X) 1 L 7 1 3O A3SO 2000082300008 20000823 00008 EA 2000 8 23 20000627SH008 2 20000620 G 8520 78027 BOLT LYC CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA ROD CAP NR 4 FAILED D O OTHER O OTHER NR NOT REPORTED 1 WP 23 33LJ 6826 15282023 L1867515 CONNECTING ROD CAP BOLT FAILED RESULTING IN ROD FAILURE WHICH BROKE OUT A 6 INCH BY 4 INCH HOLE IN THE CASE. THIS WAS A N IN-FLIGHT FAILURE. THE AIRCRAFT MADE A SAFE ON AIRPORT LANDING. (X) 1 H 7 1 3O 3 O NT 3A19 E223 2000062900176 20000629 00176 SO 2000 6 29 20000627SH009 1 20000427 G 3230 6390128 HOSE PIPER PA34 PA34200T 7103406 SO CONTAMINATED D O OTHER O OTHER LD LANDING 1 GL 21 47611 7264 347770418 P/N 63901-28 AND P/N 63901-70 HOSES (TT 7,264.3 HRS) CAUSED CONTAMINATION TO BE INJECTED INTO ORFICE FITTING OF NOSE GEA R ACTUATOR CAUSING NOSE TO NOT COME OUT OF WHEELWELL MAKING FOR A NOSE GEAR UP LANDING. (X) 1 L 7 2 3O A7SO 2000082300009 20000823 00009 SO 2000 8 23 20000627SH010 1 20000427 G 3233 6390170 HOSE PIPER PA34 PA34200T 7103406 SO DETERIORATED B O OTHER O OTHER NR NOT REPORTED 1 GL 21 47611 7264 347770418 P/N 63901-28 AND P/N 63901-70 HOSES (TT 7,264.3 HRS) CAUSED CONTAMINATION TO BE INJECTED INTO ORFICE FITTING OF NOSE GEA R ACTUATOR CAUSING NOSE TO NOT COME OUT OF WHEELWELL MAKING FOR A NOSE GEAR UP LANDING. (X) 1 L 7 2 3O A7SO 2000082300011 20000823 00011 SO 2000 8 23 20000627SH011 1 20000616 G 5540 HORN PIPER PA28 PA28140 7102802 SO RUDDER CORRODED D K NONE O OTHER IN INSP/MAINT 1 NM 09 4887T 287225230 RUDDER STEEL CONTROL HORN IS MATED TO THE ALUMINUM CONTROL SURFACE BY RIVETS. THE MATING SURFACES OF THE RUDDER WERE CO RRODED TO THE POINT OF REPLACEMENT OF THE LOWER RIB. THERE WAS NO EXTERIOR EVIDENCE OF POTENTIAL FAILURE EXCEPT THAT 2 OF THE RIVET HEADS COULD BE FLIPPED OFF WITH A FINGER NAIL. CROSS SECTION THE RIVETS SHOWED DETERIORATION CAUSED BY ELE CTROLYSIS. THIS ELECTROLYSIS WAS CAUSED BY DISSIMILAR METALS (STEEL & ALUM) IN PRESENCE OF MOISTURE. UPON DISASSSEMBLY OF RUDDER COMPONENTS, FOUND CORROSION. 1 L 7 1 3O 2A13 2000082400001 20000824 00001 CE 2000 8 24 20000627SH012 1 20000613 G 3230 YZ2RN7T SWITCH CESSNA 210 T210N 2073456 CE PLUNGER MISSING D O OTHER J WARNING INDICATION CL CLIMB 1 SO 16 5515Y 21064233 PILOT REPORTED AFTER TAKEOFF AND NORMAL CLIMB, NOTICED THE GEAR UP AND LOCKED LIGHT WAS NOT ILLUMINATED. THE PUSH TO TE ST FUNCTION OPERATED NORMALLY. UPON LANDING, MAINTENANCE DISCOVERED THE NOSE GEAR UPLIMIT SWITCH HAD FAILED. THE PLUN GER ASSY WAS COMPLETELY MISSING FROM THE SWITCH. DURING RIGGING OF NEW SWITCH IAW CESSNA SM D2057-3-13 PARA 5A-85 AND F IG 51-14, AND MANUALLY RETRACTING THE GEAR, WAS UNABLE TO ACQUIRE THE DIMENSION SHOWN IN FIG 5A-14, BUT ONCE HYD POWER A PPLIED TO GEAR, THE DIMENSION SHOWN WAS RECEIVED. SUSPECT THAT THESE SWITCHES MAY BE IMPROPERLY ADJUSTED IF ONLY ADJUST ED DURING MANUAL OPER AND NOT RE-CHECKED USING HYD PRESSURE. (X) 1 H 7 1 3O 3A21 2000082400002 20000824 00002 CE 2000 8 24 20000627SH013 1 20000617 G 7160 05521641 AIR BOX FACET CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA FLAPPER SEAL MISSING D O OTHER R PARTIAL RPM/PWR LOSS CR CRUISE 1 EA 11 734TB 4925 CK11816 17269091 RL655176T ENGINE DEVELOPED VIBRATION IN-FLIGHT AND LOSS OF POWER. MAINTENANCE REMOVED CARBURETOR AIR BOX AND CARBURETOR. FOUND P IECE OF SEAL FROM AIR BOX FLAPPER VALVE BROKEN OFF AND LODGED IN THE VENTURI. (X) 1 H 7 1 3O 3 O NT 3A12 E274 2000082400003 20000824 00003 CE 2000 8 24 20000628SH002 1 20000616 G 5280 3581501G7 HINGE RAYTHN BEECH 58 58P 1152744 CE REAR ARM FAILED H O OTHER O OTHER AP APPROACH 1 EU 01 79AP 3799 TJ206 REAR HINGE CASTING FAILED HALFWAY ALONG ARM OF RADIUS, PN 35/815016/7 WHILE APPROACH TO LAND: POSSIBLE CAUSE IS WEAR IN THE FRONT HINGE PIVOT BRACKET BOLT HOLES WHICH COULD CAUSE VIBRATION. INSPECT BOTH FRONT AND REAR BOLT HOLES FOR WEAR ALIGNMENT BY DISCONNECTING THE ACTUATING ROD, REPLACE AS NECESSARY. (X) 1 L 7 2 3O A23CE 2000082400004 20000824 00004 EA 2000 8 24 20000628SH003 2 20000615 G 8530 73806 PUSHROD CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA CRACKED H O OTHER O OTHER IN INSP/MAINT 1 SO 14 86SA 948 A1520950 L2146215 AIRCRAFT INSPECTED 33 HRS FOLLOWING ANNUAL (1 MONTH) PRIOR TO PUTTING ON LINE FOR FLIGHT TRAINING. LAST REF TO LYC SI 1 068A VALVE TAPPET CLEARANCE CHK FROM LOGS WAS 552.3 HRS PRIOR (100 HR INSP). FOUND 3 TIGHT VALVES. NR 2 EXH WAS TIGHT, PUSHROD CRACKED .5625 INCH LONGITUDINALLY, VISIBLE ON OTBD END. CRACK CONTINUED 180 DEGREES AROUND CIRCUMFERENTIALLY. PUSHROD END LOOSE. REMOVED ALL PUSHRODS, 7 OUT OF 8 CRACKED. MOST .3750 INCH LONGITUDINALLY ON INBD END. REPLACEMENT PART LYC 15F22200/S673806 IS NOW STEEL. ORIG 73806 WAS ALUM. LYC SI 1068A SUPPLEMENT NR 1 NOW APPLIES FOR STEEL PUSHR ODS. (X) 1 H 7 1 3O 3 O NT 3A19 E223 2000082400005 20000824 00005 CE 2000 8 24 20000628SH005 1 20000613 G 5511 1232105 RIB CESSNA 182 182Q 2072732 CE HORIZ STABILIZER BENT D K NONE O OTHER IN INSP/MAINT 1 NM 03 951CC 13427 18266998 DURING ANNUAL/100 HOUR INSPECTION, THE SECOND RIB OUTBOARD OF CENTER ON THE RT SIDE OF THE HORIZONTAL STABILIZER WAS FOU ND BENT THROUGH THE LIGHTENING HOLES. POSSIBLE CAUSE OF THIS DAMAGE, IMPROPER GROUND HANDLING (SITTING ON STABILIZER TO TURN AIRCRAFT). (X) 1 H 7 1 3O NT 3A13 2000082200035 20000822 00035 SW 2000 8 22 20000628SH006 1 20000624 G 5540 14524401 RUDDER HORN NAVION NAVION L17A 6150106 SW CONT E225 E2254 17015 SO HARTZL HC12V HC12V20* GL RUDDER CORRODED D O OTHER O OTHER IN INSP/MAINT 1 WP 05 8818H 4557 NAV4818 DURING INSPECTION FOR AD 68-20-06, FOUND CORRISION HAD CAUSED DELAMINATION AND SWELLING OF ONE SIDE OF RUDDER HORN, P/N 145-24401. LAST ANNUAL 1992. (I) 1 L 7 1 3O 3 O A782 E267 5 C P46GL 2000083000035 20000830 00035 CE 2000 8 30 20000629SH001 1 20000623 G 2823 1093890027 VALVE BEECH 90 F90 1152909 CE PWA PT6 PT6A135 52043 NE FIREWALL LEAKING E K NONE K FLUID LOSS NR NOT REPORTED 1 SW 15 15 100 LA138 INTERNAL LEAK OF FUEL THROUGH GATE VALVE, WITH SHUT-OFF VALVE IN CLOSED POSITION. (I) 1 L 7 2 4T 4 T A31CE E4EA 2000092100007 20000921 00007 SO 2000 9 21 20000707SH001 2 20000523 G 8530 649264 PIPE MOONEY M20 M20K 5870220 SW CONT O360 TSIO360SB SO ATT FLANGE NR 4 CRACKED B DY1R K NONE O OTHER IN INSP/MAINT 1 EA 13 48LW 434 252021 321763 DISCOVERED HEAVY STAIN AT FLANGE END OF INDUCTION TUBE DURING ROUTINE OIL CHANGE. REMOVED FLANGE RETAINER AND FOUND PIP E CRACKED APPROXIMATELY ONE-HALF DIAMETER. CONTINENTAL HAS RECENTLY ISSUED SB 98-8 WHICH RECOMMENDED REPLACEMENT OF ONE -PIECE PIPES FOR CYLINDERS NR 1 AND NR 3. THIS PIPE WAS FOR CYLINDER NR 4. SUBMITTER RECOMMENDED REPLACEMENT OF CYLIND ERS NR 2 AND NR 4 PIPES WITH 2-PIECE STYLE AS WELL. LENGTH OF PIPE IS TOO MUCH FOR FLANGE STRENGTH. 1 L 7 1 3O 3 O 2A3 E9CE 2001020200014 20010202 00014 EA 2001 2 2 20000707SH002 2 20000620 G 7414 10357586 GEAR CONT BELL 47 47G 1181002 SW FRNKLN 6AV350 6V350A 27043 EA MAGNETO DAMAGED B K NONE O OTHER IN INSP/MAINT 1 NE 05 950B 5 C200014DR 693 E60073 AIRCRAFT LANDED AT REMOTE FIELD LOCATION ON ISLAND. SEVERAL HOURS LATER, AIRCRAFT STARTED. RIGHT MAGNETO COMPLETELY FA ILED. ON RPM MAG CHECK, MAGNETO REMOVED AND TAKEN APART. NYLON DISTRIBUTOR GEAR LOST 3 TEETH. GEAR USED WAS NOT NEW, CHECKED WITH TELEDYNE CONTINENTAL. THEY CONFIRMED DISTRIBUTOR GEARS ARE ROUTINELY REUSED. SINCE THERE IS NO WAY TO ZYG LO OR MAGNAFLUX NYLON DISTRIBUTOR GEARS, SUBMITTER RECOMMENDED ROUTINE REPLACEMENT OF ALL DISTRIBUTOR GEARS AT FACTORY O VERHAUL. (X) 1 G 7 1 3O 3 O H1 E9EA 2000102400180 20001024 00180 SO 2000 10 24 20000707SH003 2 20000623 G 8520 642396 CRANKSHAFT CESSNA 340 340A 2076405 CE CONT O520 TSIO520NB 17040 SO RIGHT ENGINE BROKEN B O OTHER Y ENGINE STOPPAGE CR CRUISE 1 NM 05 1920E 60 340A0669 813713R RIGHT ENGINE CRANKSHAFT BROKE IN CRUISE FLIGHT 15,000 FEET, 2,300 RPM. NR 1 PISTON NOT MOVING WHEN PROPELLER IS TURNED. NR 5 CYLINDER, NO COMPRESSION. METAL FOUND IN OIL FILTER AND GOVERNOR GASKET SCREEN. (X) 1 L 7 2 3O 3 O 3A25 E8CE 2000102400007 20001024 00007 2000 10 24 20000707SH005 4 20000621 G 2561 KS9P0101125 LIFE VEST FLOTATION CELL DEFECTIVE B KQ1R K NONE O OTHER IN INSP/MAINT 1 EA 07 CELL FAILED MFG RECOMMENDED 2 PSI PRESSURE TEST IAW 25-60-1. DATE OF MFG: MAY 1983. (X) 2000102400008 20001024 00008 2000 10 24 20000707SH006 4 20000621 G 2561 KS9P0101125 LIFE VEST FLOTATION CELL DEFECTIVE B KQ1R K NONE O OTHER IN INSP/MAINT 1 EA 07 CELL FAILED MFG RECOMMENDED 2 PSI PRESSURE TEST IAW 25-60-1. DATE OF MFG: FEB 1984. (X) 2000102400013 20001024 00013 SO 2000 10 24 20000707SH007 1 20000614 G 2460 E303 CONNECTOR PIPER PA31 PA31350 7103110 SO OVERHEATED MELTED B R2JR O OTHER B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 EA 21 13FS 3542 318352024 WHILE COMPLETING PIPER MANDATORY SB 1004, FOUND PLUG E303 AND WIRING BADLY BURNT. REPLACED PLUG AND WIRING AND RAN WIR ING PER SB INSTRUCTIONS. CREW HAD REPORTED STRONG BURNING SMELL ON ONE PREVIOUS FLIGHT. PLUG IS LOCATED BEHIND COCKPIT UPHOLSTERY AND COULD HAVE CAUSED FIRE. SUBMITTER SUGGEST MSB 1004 BE MADE AN AD NOTE. (X) 1 L 7 2 3O A20SO 2000102400014 20001024 00014 SO 2000 10 24 20000707SH008 1 20000614 G 2823 492114 SHUTOFF VALVE PIPER PA31 PA31350 7103110 SO INTERNAL FAILURE FAILED B R2JR O OTHER O OTHER IN INSP/MAINT 1 EA 21 13FS 3542 318352024 DURING INSPECTION, FOUND RIGHT FIREWALL SHUT-OFF VALVE FAILED TO RIG PROPERLY. FUEL STILL FLOWED IN AFT POSITION. FOUN D VALVE HAD FAILED INTERNALLY. AD 80-18-10 AND PIPER SB 648A APPLIES TO AIRCRAFT WITH LOWER SERIAL NUMBERS, BUT NOT THI S AIRCRAFT. SUBMITTER SUGGESTED SB AND AD BE APPLIED TO ALL SERIAL NUMBERED AIRCRAFT. NEW VALVE WAS INSTALLED AND SYST EM TESTED PROPERLY. LEFT VALVE WAS ALSO TESTED. (X) 1 L 7 2 3O A20SO 2001011100927 20010111 00927 2001 1 11 20000707SH010 1 20000614 G 2431 BS19747 SWITCH MARATHON OVERHEAT IMPROPER PART B R2JR K NONE O OTHER IN INSP/MAINT 1 EA 21 9702895 BATTERY RECEIVED FOR SERVICE AT THIS STATION WITH P/N BS 19747 FAA-PMA OVERHEAT SWITCH INSTALLED. RESEARCH SHOWED THIS BATTERY IS NOT LISTED ON PMA HOLDERS ELIGIBILITY LIST, ALTHOUGH IT IS LISTED IN THE HOLDERS PRODUCT SUPPORT CATALOG AS T HE PROPER SENSOR FOR THIS SP910D BATTERY. PMA HOLDER WAS NOTIFIED. (AD NOTE REQUIRES SENSOR). 2000102400056 20001024 00056 NE 2000 10 24 20000707SH013 2 20000126 G 7421 CH34682 IGNITER PWA 305 PW305 NE FAILED B R14R K NONE O OTHER IN INSP/MAINT 1 EA 17 RECEIVED 2 EACH IGNITERS. THE THIRD IGNITER OPS CHECKED OK. BATCH NUMBER UNKNOWN. THE IGNITER USED NORMALLY IS INSTAL LED IN PWA 305 SERIES ENGINES. (P/N CH34682). (X) 4 F E35NE 2000102400057 20001024 00057 NE 2000 10 24 20000707SH014 2 20000209 G 7421 CH34682 IGNITER PWA 305 PW305 NE DEFECTIVE B R14R K NONE O OTHER IN INSP/MAINT 1 EA 17 RECEIVED 3 EACH IGNITERS. THE 4TH IGNITER OPS CHECKED OK. BATCH NUMBER UNKNOWN. THE IGNITER USED NORMALLY IS INSTALLE D IN P&W 305 SERIES ENGINES. (PN 34682). (X) 4 F E35NE 2000102400058 20001024 00058 2000 10 24 20000707SH015 4 20000619 G 6122 D20887 DRIVE GEAR MCAULY CONT O520 IO520* 17032 SO GOVERNOR DEFECTIVE C LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 760751 LONG LINEAR INDICATION ON SHAFT, POSSIBLE INCLUSION. (X) 3 O E5CE 2000080200067 20000802 00067 SO 2000 8 2 20000707SH018 1 20000626 G 3240 RFS2010 STATOR BFGOODRICH EMB 120 EMB120 3260201 SO NR 2 POSITION DEFECTIVE B XC4R K NONE O OTHER IN INSP/MAINT 1 SO 19 1019 0072A BRAKE ASSEMBLY, P/N 2-1585, FAILED PREMATURELY. NR 2 STATOR CRACKED AT RELIEF HOLES. HEAT STACK WARPED AND UNEVEN WEAR . SUBMITTER STATED THIS IS A CONTINUAL DISCREPANCY. NOTE: RAPCO FLEET SUPPORT PARTS INSTALLED IN BRAKE ASSY. (X) 2 L 7 2 4T RT A31SO 2000102400020 20001024 00020 GL 2000 10 24 20000710SH006 1 20000429 G 5743 5310006 BULKHEAD AMTR SEAREY SEAREY 05625X5 GL LEFT SIDE BROKEN G O OTHER O OTHER TX TAXI/GRND HDL 1 CE 05 4293S 165 1MK026 DURING TAXI, THE LEFT LANDING GEAR COLLAPSED. INSPECTION REVEALED THE TWO LEFT LG BULKHEAD UPRIGHT SUPPORT TUBES BROKEN AT THE LG ATTACH POINT. IT IS SUSPECTED THE PARTS MAY HAVE BEEN OVERSTRESSED DURING ASSY OF MINIMAL STRENGTH OR THE RE SULT OF FATIGUE CAUSED BY AN UNREPORTED HARD LANDING(S). (X) 1 H 7 1 3I RC 1H71EXPA 2001020200016 20010202 00016 SW 2001 2 2 20000710SH008 1 20000520 G 6420 209040177101 FLANGE BELL 412 412EP 1182205 SW TAIL ROTOR LOOSE B EGRR K NONE O OTHER IN INSP/MAINT 1 EA 17 22PP 469 36219 DISC TO FLANGE INTERFACE FOUND LOOSE DURING ROTOR BRAKE QUILL SEAL CHANGE. REPLACED BOTH DISC AND FLANGE WHICH WERE MEA SURED AND FOUND WORN BEYOND LIMITS. (X) 1 G 7 2 4U H4SW 2001020200017 20010202 00017 SW 2001 2 2 20000710SH009 1 20000520 G 6420 94404911 DISC PACK BELL 412 412EP 1182205 SW TAIL ROTOR LOOSE B EGRR K NONE O OTHER IN INSP/MAINT 1 EA 17 22PP 469 36219 DISC TO FLANGE INTERFACE FOUND LOOSE DURING QUILL SEAL CHANGE. REPLACED BOTH DISC AND FLANGE WHICH WAS MEASURED AND FOU ND BEYOND LIMITS. (X) 1 G 7 2 4U H4SW 2001020200018 20010202 00018 NE 2001 2 2 20000710SH010 1 20000225 G 5330 7620305001123 SKIN SKRSKY S76 S76A 8143006 NE PYLON CORRODED B EGRR K NONE O OTHER IN INSP/MAINT 1 EA 17 22BF 6173 760216 CORROSION. SKIN REMOVED FROM PYLON AND TREATED IAW SA 4047-76-8, CORROSION CONTROL MANUAL. THE CORROSION WAS CLASSIFIE D AS MINOR CORROSION. THE CORROSION APPEARED AS PAINT BLISTERS AROUND SKIN FASTENERS. (X) 1 G 7 2 3U H1NE 2001020200019 20010202 00019 NE 2001 2 2 20000710SH011 1 20000225 G 5312 7620104009 BULKHEAD SKRSKY S76 S76A 8143006 NE FUSELAGE MISDRILLED B EGRR K NONE W INADEQUATE Q C IN INSP/MAINT 1 EA 17 22BF 6173 760216 THE VERTICAL PYLON FORWARD BULKHEAD AT STA 458 HAD DOUBLE DRILLED HOLES AT THE FASTENER AREA. THE BULKHEAD IS BETWEEN T HE UPPER AND LOWER DECKS. THERE WAS A CRACK FOUND AT THE LEFT CORNER OF THE BULKHEAD WEB. (X) 1 G 7 2 3U H1NE 2001020200020 20010202 00020 EU 2001 2 2 20000710SH012 1 20000225 G 7120 365A51103300 MOUNT AEROSP AS365 AS365N2 8680815 EU ENGINE CORRODED B EGRR K NONE O OTHER IN INSP/MAINT 1 EA 17 272NE 3235 6435 AIRFRAME ENGINE MOUNT IS CRACKED IN TWO PLACES BEYOND LIMITS FOR REPAIR IAW MANUFACTURER''S MM. CRACKS OCCURRED AT FAST ENING HOLE AREAS. REPLACED WITH NEW PART. (X) 1 G 7 2 3U RT H10EU 2001020200022 20010202 00022 NE 2001 2 2 20000710SH014 1 20000614 G 5320 7620105002114 ANGLE SKRSKY S76 S76B 8143007 NE FUSELAGE CRACKED B EGRR K NONE O OTHER IN INSP/MAINT 1 EA 17 280TR 3951 36085 CAP ANGLE FOUND CRACKED. PART WILL BE REPLACED WITH NEW ASSY IAW MANUFACTURERS MM AND REPAIR PROCEDURES. (X) 1 G 7 2 4U H1NE 2001020200023 20010202 00023 NE 2001 2 2 20000710SH015 1 20000621 G 5320 7608020041101 PLATE SKRSKY S76 S76B 8143007 NE FUSELAGE CORRODED B EGRR K NONE O OTHER IN INSP/MAINT 1 EA 17 280TR 3951 760344 PLATE CORRODED. CORRODED PART WILL BE REPLACED WITH NEW PART. (X) 1 G 7 2 4U H1NE 2001020200024 20010202 00024 NE 2001 2 2 20000710SH016 1 20000621 G 5320 7608020041103 DOUBLER SKRSKY S76 S76B 8143007 NE FUSELAGE CORRODED B EGRR K NONE O OTHER IN INSP/MAINT 1 EA 17 280TR 3951 760344 DOUBLER SHOWED SIGNS OF CORROSION. CORRODED PART WILL BE REPLACED WITH NEW PART. (X) 1 G 7 2 4U H1NE 2001020200025 20010202 00025 NE 2001 2 2 20000710SH017 1 20000621 G 5320 7608020041102 DOUBLER SKRSKY S76 S76B 8143007 NE FUSELAGE CORRODED B EGRR K NONE O OTHER IN INSP/MAINT 1 EA 17 280TR 3951 36085 DOUBLER CORRODED. THE CORRODED PART WILL BE REPLACED WITH NEW PART. (X) 1 G 7 2 4U H1NE 2001020200026 20010202 00026 NE 2001 2 2 20000710SH018 1 20000619 G 5320 7620204002114 ANGLE SKRSKY S76 S76B 8143007 NE FUSELAGE CORRODED B EGRR K NONE O OTHER IN INSP/MAINT 1 EA 17 280TR 3951 760344 ANGLE FOUND CORRODED. PART WILL BE REPLACED WITH A NEW UNIT. (X) 1 G 7 2 4U H1NE 2001020200027 20010202 00027 NE 2001 2 2 20000710SH019 1 20000619 G 5320 RMLH257780 NUT SKRSKY S76 S76B 8143007 NE FUSELAGE CRACKED B EGRR K NONE O OTHER IN INSP/MAINT 1 EA 17 280TR 3951 760344 BARREL NUT FOUND CRACKED IN SEVERAL PLACES. REPLACED WITH NEW PART. C/W ASB 76-66-30. (X) 1 G 7 2 4U H1NE 2001020200028 20010202 00028 NE 2001 2 2 20000710SH020 1 20000619 G 5320 7620204002107 ANGLE SKRSKY S76 S76B 8143007 NE FUSELAGE CORRODED B EGRR K NONE O OTHER IN INSP/MAINT 1 EA 17 280TR 3951 760344 ANGLE FOUND CORRODED. PART WILL BE REPLACED WITH A NEW UNIT. (X) 1 G 7 2 4U H1NE 2001030200003 20010302 00003 NE 2001 3 2 20000710SH021 1 20000608 G 5321 7620204002117 FLOOR PANEL SKRSKY S76 S76B 8143007 NE CABIN CRACKED B EGRR K NONE O OTHER IN INSP/MAINT 1 EA 17 280TR 3951 760344 DECK CRACKED. 1 G 7 2 4U H1NE 2001020200029 20010202 00029 NE 2001 2 2 20000710SH022 1 20000608 G 5320 7620105002101 WEB SKRSKY S76 S76B 8143007 NE FUSELAGE CRACKED B EGRR K NONE O OTHER IN INSP/MAINT 1 EA 17 280TR 3951 760344 WEB CRACKED. 1 G 7 2 4U H1NE 2001020200030 20010202 00030 NE 2001 2 2 20000710SH023 1 20000608 G 5320 7620105002115 ANGLE SKRSKY S76 S76B 8143007 NE FUSELAGE CRACKED B EGRR K NONE O OTHER IN INSP/MAINT 1 EA 17 280TR 3951 760344 ANGLE CRACKED. 1 G 7 2 4U H1NE 2001020200031 20010202 00031 NE 2001 2 2 20000710SH024 1 20000608 G 5320 7607020532101 STRAP SKRSKY S76 S76B 8143007 NE FUSELAGE CRACKED B EGRR K NONE O OTHER IN INSP/MAINT 1 EA 17 280TR 3951 760344 STRAP CRACKED. 1 G 7 2 4U H1NE 2001020200032 20010202 00032 NE 2001 2 2 20000710SH025 1 20000608 G 5320 7620204002124 ANGLE SKRSKY S76 S76B 8143007 NE FUSELAGE CRACKED B EGRR K NONE O OTHER IN INSP/MAINT 1 EA 17 280TR 3951 760344 ANGLE CRACKED. 1 G 7 2 4U H1NE 2001020200033 20010202 00033 NE 2001 2 2 20000710SH026 1 20000608 G 5320 7620105002117 ANGLE SKRSKY S76 S76B 8143007 NE FUSELAGE CRACKED B EGRR K NONE O OTHER IN INSP/MAINT 1 EA 17 280TR 3951 760344 ANGLE CRACKED. 1 G 7 2 4U H1NE 2001020200034 20010202 00034 EU 2001 2 2 20000711SH001 1 20000611 G 6320 4638001001 TRANSMISSION BOLKMS 105 BO105CBS 5626008 EU ALLSN 250C 250C20B 03013 GL MAIN ROTOR MAKING METAL D O OTHER J WARNING INDICATION NR NOT REPORTED 1 SO 17 5417J 1105 S798 MAIN ROTOR CHIP LIGHT CAME ON IN-FLIGHT AND WOULD NOT PULSE OFF. AFTER REMOVAL OF MAIN ROTOR CHIP DETECTOR AND MAIN ROT OR OIL FILTER, FOUND STEEL SLIVERS AND CHIPS, BRONZE IN THE FILTER, AND OIL DRAINED. TRANSMISSION REMOVED AND SHIPPED T O EUROCOPTER CANADA FOR REPAIR. TBO FOR THIS UNIT IS 3,000 HOURS. PART FAILED AT 1,104.5 HOURS SINCE OVERHAUL. (X) 1 G 7 2 3U 3 U NC H3EU E4CE 2000101600308 20001016 00308 EA 2000 10 16 20000711SH002 2 20000614 G 8520 LW12186 NUT LYC GULSTM 500 500B 0141106 SW LYC O540 IO540E1A5 41532 EA SEPARATED E O OTHER O OTHER CR CRUISE 1 SW 15 524HW 1380 1533191 L210748 LEFT ENGINE LOST OIL PRESSURE. FEATHERED IN-FLIGHT. DISASSEMBLED ENGINE. ROD, P/N 75061, ON NR 4 CYLINDER BROKEN AND IT LOOKS AS IF ONE NUT CAME LOOSE CAUSING THE FAILURE. (X) 1 H 7 2 3O 3 O 6A1 1E4 2000101600309 20001016 00309 SO 2000 10 16 20000711SH004 1 20000605 G 5310 1713444 FRAME PIPER PA23 PA23250 7102308 SO CORRODED D K NONE O OTHER IN INSP/MAINT 1 EU 01 250MC 277305142 FUSLAGE FRAME TUBES FOUND BADLY CORRODED ON ANNUAL INSPECTION. WATER SOAKED INSULATION FOUND IN CONTACT WITH AFFECTED T UBES. SUBMITTER SUSPECTED WATER INGRESS FROM BADLY FITTING CABIN DOOR AND PV WINDOW SEALS. SUBMITTER RECOMMENDED THE UNDER FLOOR AREA BELOW THE CABIN DOOR AND PV WINDOW BE INSPECTED ON ALL AIRCRAFT OF A SIMILAR DESIGN TO THE PA23 FOR WAT ER INGRESS, AND CORROSION. DAMAGED AND WATER SOAKED INSULATION BLANKETS BE REPLACED. EXTRA WATER DRAINS BE INSTALLED T O LOWER FUSELAGE AREA IN ORDER TO MINIMIZE THE RISK OF WATER PUDDLES FORMING. (X) 1 L 7 2 3O 1A10 2000101600311 20001016 00311 SO 2000 10 16 20000711SH006 1 20000603 G 3232 758440 ROD END WIEBEL PIPER PA42 PA421000 7104225 SO RT MAIN GEAR BROKEN B SO5R O OTHER J WARNING INDICATION LD LANDING 1 NE 03 325KW 4083 425527025 RIGHT MAIN LANDING GEAR ACTUATOR ROD END BROKE IN HALF WHERE PIVOT BALL IS RETAINED. NOT SURE WHETHER IT BROKE ON UP OR DOWN CYCLE. AFTER FAILURE, GEAR WOULD NOT COMPLETELY LOCK. BLOW DOWN SYSTEM AND HAND PUMP WERE NOT ABLE TO WORK WITH ROD END BROKEN. GEAR WAS EXTENDED, BUT SLOWLY COLLAPSED UPON LANDING. FAILURE MAY HAVE BEEN CAUSED BY MACHINING MARKS ON ROD END OR BY LACK OF PROVISION FOR A DOWN-CYCLE STOP NUT ON THE ACTUATOR SHAFT. (X) 1 L 7 2 4T RT A23SO 2000101600312 20001016 00312 SO 2000 10 16 20000711SH007 1 20000615 G 2434 ES4032 ALTERNATOR PIPER PA28 PA28181 7102807 SO BROKEN D O OTHER O OTHER IN INSP/MAINT 1 WP 13 354MR 147 2843315 HOLES DISCOVERED IN LOWER AND UPPER ENGINE COWLING ON LEFT SIDE. REMOVED COWL AND FOUND ALTERNATOR COOLING FAN BROKEN C AUSING DAMAGE TO COWL. REPAIRED COWL AND REPLACED FAN ASSY WITH NEW PART. SUBMITTER STATED IT APPEARED THAT THE ''DISH ED'' FRONT PLATE WAS ON BACKWARDS. (X) 1 L 7 1 3O 2A13 2000101600313 20001016 00313 WP 2000 10 16 20000711SH008 1 20000602 G 3240 BRAKE ASSY SUPAC LA LFA 8730208 WP SEIZED G O OTHER O OTHER TX TAXI/GRND HDL 1 NM 11 34783 239 UPON DEPARTURE, PILOT LOST DIRECTIONAL CONTROL DUE TO THE LEFT BRAKE SEIZING. AIRCRAFT RECEIVED SUBSTANTIAL DAMAGE. AT INSPECTION, BROKEN ASSY WAS FOUND DRAGGING, BUT WHEN CHECKED A SECOND TIME, IT ROTATED FREELY. NO CAUSE WAS FOUND. (X ) 1 L 7 1 3O A730 2000101600314 20001016 00314 CE 2000 10 16 20000712SH001 1 20000712 G 2800 112054E VENT LINE BEECH 100 A100 1152915 CE LEFT & RIGHT WIN FAILED D O OTHER O OTHER IN INSP/MAINT 1 SO 16 102FG 150 150 B131 OPERATIONAL CHECKS AT INSPECTION INTERVALS TYPICALLY FIND THE VENT HEATS INOPERATIVE DUE TO THE ELECTRICAL CONNECTION ON THE TUBE ITSELF. USING A PROBE AND INSERTING IN THE HOLE WHERE THE HEATING COIL TERMINATES PRODUCES A SPARK AND THEN T HE COIL WILL HEAT PROPERLY AFTER THE CONNECTION IS MADE. THIS DEFECT IS FOUND NEARLY EVERY INSPECTION ON TWO KING AIRS. SUBMITTER STATED A REDESIGN OF THE TERMINATION WOULD MOST LIKELY CURE THE EXISTING POOR CONNECTION. (X) 1 L 7 2 3T A14CE 2001020200036 20010202 00036 NE 2001 2 2 20000712SH007 1 20000404 G 6510 DRIVE SHAFT SKRSKY S76 S76B 8143007 NE TAIL ROTOR CORRODED B EGRR K NONE O OTHER IN INSP/MAINT 1 EA 17 421MK 5285 760354 SUSPECTED CORROSION ON SHAFT TUBE AREA, BLISTERING. REPLACED SHAFT WITH A NEW UNIT IAW SIKORSKY MM. (X) 1 G 7 2 4U H1NE 2001020200037 20010202 00037 EU 2001 2 2 20000712SH008 1 20000301 G 2910 LINE SNIAS 350 AS350B3 8680954 EU MO4 TO MO5 LEAKING B EGRR K NONE O OTHER IN INSP/MAINT 1 EA 17 5226R 500 3144 THE MO4 TO MO5 FLEX LINE STARTED LEAKING AT 500 HOURS. THE LEAK WAS IN THE AREA OF THE FLEX BRAID AND COULD NOT DETECT ANY EXTREME DAMAGE OF THE FLEX LINE. REPLACED WITH NEW FLEX LINE AND PERFORMED LEAK CHECK OK. (X) 1 G 7 1 3U H9EU 2000101600315 20001016 00315 SO 2000 10 16 20000712SH011 1 20000622 G 5553 AN311 BOLT PIPER PA28 PA28140 7102802 SO STABILATOR DAMAGED D O OTHER F FLT CONT AFFECTED IN INSP/MAINT 1 WP 23 6467R 281655 DURING ANNUAL INSPECTION, THE CONTROL SURFACES WERE FOUND TO HAVE NEVER BEEN RE-BALANCED AFTER THE AIRCRAFT HAD BEEN RE- PAINTED SOMETIME PRIOR. WHEN REMOVING THE STABILATOR, IT WAS FOUND THAT THE MOUNTING BOLTS COULD NOT BE REMOVED WITHOUT BEING CUT OFF. ON CLOSER INSPECTION UPON REMOVAL, THE BOLTS HAD BEEN DEFORMED WITH A JOGGLE/BEND FORMED IN THE SHANK. AFTER REMOVING PAINT FROM THE BOLT HEADS, FOUND THAT AN3 BOLTS WERE INSTALLED INSTEAD OF THE STRONGER NAS1104-17 AS SPE CIFIED IN THE PARTS MANUAL. PRIOR TO REMOVAL, THE BOLTS APPEARED NORMAL AND UNDAMAGED. HIGH LOADS ON THE STABILATOR AN D INCORRECT HARDWARE WERE POSSIBLE CAUSES. (X) 1 L 7 1 3O 2A13 2000100300253 20001003 00253 CE 2000 10 3 20000712SH012 1 20000615 G 2434 DOFF10300J HOUSING CESSNA 206 U206A 2073316 CE CONT O520 IO520F 17032 SO ALT BOLTS LOOSE A WVBA O OTHER H ELECT. POWER LOSS-50 PC TO TAKEOFF 1 AL 01 756DJ 96 U20604005 812407R PILOT REPORTED ALTERNATOR INOPERABLE AT TAKEOFF POWER. AT IDLE, ALTERNATOR APPEARED TO OPERATE NORMALLY. UPON EXAMINA TION, FOUND THE COARSE THREAD INTERNAL WRENCHING BOLTS HOLDING THE ALTERNATOR CASE HALVES WERE LOOSE, WHICH AT HIGH ENGI NE RPM, CAUSED THE CASE TO FLOAT ON THE ARMATURE DRIVING THE ALTERNATOR OFF-LINE. SUBMITTER SUGGESTED MANUFACTURER OR O VERHAUL FACILITY SHOULD CONSIDER A HIGHER TORGUE VALUE ON THESE BOLTS TO CURTAIL FURTHER RROBLEMS. THIS WAS THE SECOND OCCURRENCE ON THIS AIRCRAFT WITHIN A 100-HOUR TIME FRAME. (X) 1 H 7 1 3O 3 O A4CE E5CE 2001020200039 20010202 00039 NE 2001 2 2 20000712SH014 1 20000614 G 5320 RMLH257780 NUT SKRSKY S76 S76B 8143007 NE FUSELAGE CRACKED B EGRR K NONE O OTHER IN INSP/MAINT 1 EA 17 9NJ 347 760345 BARREL NUT IS CRACKED. THE PART HAS BEEN IN SERVICE FOR 346.7 HOURS. ALL BARREL NUTS WILL BE REPLACED WITH NEW UNITS. ALL WORK DONE IAW MFG MM. (X) 1 G 7 2 4U H1NE 2001020200040 20010202 00040 NE 2001 2 2 20000712SH015 1 20000613 G 6320 CASE SKRSKY S76 S76B 8143007 NE TRANSMISSION CRACKED B EGRR K NONE O OTHER IN INSP/MAINT 1 EA 17 9NJ 1013 A23100024 760345 MAIN TRANSMISSION HAS CRACK ON THE UPPER CASE IN THE AREA OF THE RIGHT REAR MOUNT LEG. (X) 1 G 7 2 4U H1NE 2000101800112 20001018 00112 CE 2000 10 18 20000712SH020 1 20000424 G 5711 122210630 SPAR CESSNA 206 U206G 2073356 CE RT WS 126 CRACKED B SMTR K NONE O OTHER IN INSP/MAINT 1 EA 17 783 2750 U20606524 DURING ROUTINE INSP, NOTED THE RT WING AFT SPAR WEB CRACKED IN 5 PLACES AND THE ROLL SERVO ATTACH BRACKET 60931 CRACKED AT THE OTBD SERVO ATTACH HOLE. ALL CRACKS ARE IN VICINITY OF S-TEC ROLL SERVO BRACKET ATTACHMENT BOLTS. S-TEC TWO AXIS AUTOMATIC FLIGHT GUIDANCE SYS, MODEL ST-208-50 INSTALL IS APPROVED VIA S-TEC CORP STC SA5216SW-D AND ELIGIBLE TO BE INS TALLED ON ACFT WHEN MODIFIED PER R/STOL SYS. STC SA1513WE (ROBERTSON STOL) WHICH THIS ACFT HAS BEEN MODIFIED OR STC SA 3634SW, WHICH ACFT HAS NOT BEEN MODIFIED. SPAR REPLACED WITH NEW CESSNA P/N 1222106-30. NEW SPAR INSTALLED AND NOT MOD IFIED WITH ROLL SERVO ATTACHMENT HOLES. S-TEC AUTOPILOT DISABLED IAW FAR REG PART 91.213. TT SINCE STC''S, 1,348.2 HRS 1 H 7 1 3O A4CE 2000101800114 20001018 00114 WP 2000 10 18 20000712SH022 1 20000623 G 3246 152059 WHEEL BENDIX DOUG DC8 DC8* WP SPOKE AREA CRACKED B INWR K NONE O OTHER IN INSP/MAINT 1 SO 19 NDT INSPECTION SHOWED CRACK INDICATION AT SPOKE AREA. 2 L 7 4 4J F 4A25 2000101800115 20001018 00115 CE 2000 10 18 20000712SH023 1 20000620 G 5610 531126111 WINDOW CESSNA 340 340CESSNA 2076404 CE DEPARTED H O OTHER O OTHER CR CRUISE 1 SW 09 69554 3400369 AT FLIGHT LEVEL 11,500 FEET, WINDOW BLEW OUT. DETERMINED THAT CESSNA SB HAD NOT BEEN DONE (SK340-26). (X) 1 L 7 2 3O 3A25 2000101800118 20001018 00118 CE 2000 10 18 20000712SH029 1 20000712 G 7921 1E1337652660 COOLER CESSNA 206 206CESSNA 2073302 CE CONT O520 IO520* 17032 SO OIL TUBE LEAKING B RF3R K NONE K FLUID LOSS IN INSP/MAINT 1 WP 23 COOLER HAD RECEIVED PREVIOUS EPOXY REPAIRS. EPOXY FAILED DURING NORMAL USE. SUBMITTER RECOMMENDED ELIMINATING EPOXY USE IN OIL COOLERS AS EPOXY FAILURE IS COMMON OCCURRENCE WHEN USED TO REPAIR LEAKS IN OIL COOLERS. (X) 1 H 7 1 3O 3 O A4CE E5CE 2000101800074 20001018 00074 CE 2000 10 18 20000712SH033 1 20000621 G 7921 8524295 COOLER CONT CESSNA 182 182 2072702 CE CONT O470 O470L 17026 SO CORE LEAKING B RF3R K NONE K FLUID LOSS IN INSP/MAINT 1 WP 23 PART HAD BEEN REPAIRED USING EPOXY TO STOP A LEAK. DURING NORMAL SERVICE, EPOXY FAILED CAUSING THE OIL COOLER TO LEAK A T POINT OF ORIGINAL REPAIR. SUBMITTER RECOMMENDED ELIMINATING USE OF EPOXY IN OIL COOLERS AS EPOXY FAILURE IS COMMON. (X) 1 H 7 1 3O 3 O NT 3A13 E273 2001020500028 20010205 00028 NE 2001 2 5 20000712SH044 2 20000628 G 7250 BLADE GE GE CF700 CF7002D2 30010 NE ENGINE FRACTURED B EX2R K NONE O OTHER IN INSP/MAINT 1 SW 15 712 299091 TWO EACH STAGE 1 TURBINE BLADES FRACTURED AND LIBERATED THE TOP ONE-THIRD OF THE AIRFOIL CAUSING DAMAGE TO THE 2ND STAGE BLADES AND AFT FAN SECTION. SUBMITTER STATED INSUFFICIENT INSPECTION INFORMATION EXISTS I N THE ENGINE MANUAL TO DETEC T THINNING/NECKING OF THE AIRFOIL SECTION DUE TO CREEP AND/OR OXIDATION AND/OR EROSION. THINNING OF THE BLADE AIRFOIL C ROSS-SECTION RESULTS IN BLADE FRACTURE. (X) 4 F E7EA 2001020500029 20010205 00029 NE 2001 2 5 20000712SH045 2 20000628 G 7250 BLADE GE GE CF700 CF7002D2 30010 NE ENGINE FRACTURED B EX2R K NONE O OTHER IN INSP/MAINT 1 SW 15 712 299091 TWO EACH STAGE 1 TURBINE BLADES FRACTURED AND LIBERATED THE TOP ONE-THIRD OF THE AIRFOIL CAUSING DAMAGE TO THE 2ND STAGE BLADES AND AFT FAN SECTION. SUBMITTER STATED INSUFFICIENT INSPECTION INFORMATION EXISTS I N THE ENGINE MANUAL TO DETEC T THINNING/NECKING OF THE AIRFOIL SECTION DUE TO CREEP AND/OR OXIDATION AND/OR EROSION. THINNING OF THE BLADE AIRFOIL C ROSS-SECTION RESULTS IN BLADE FRACTURE. (X) 4 F E7EA 2000101800044 20001018 00044 2000 10 18 20000712SH047 4 20000622 G 6122 G210569 GOVERNOR WOODWARD BNORM BN2 BN2 1520202 EU LYC O540 IO540* 41532 EA MALFUNCTIONED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 RELEVANT INDICATION ON GOVERNOR BODY. (X) 1 H 7 2 3O 3 O A17EU 1E4 2000101800045 20001018 00045 EA 2000 10 18 20000712SH048 2 20000628 G 8520 LW17060 CRANKSHAFT LYC PIPER PA28 PA28161 7102803 SO LYC O320 O320D3G 41508 EA NR 3 THROW BROKEN G A UNSCHED LANDING R PARTIAL RPM/PWR LOSS TO TAKEOFF 1 SW 99 8189T 5487 1281 288016309 L1330539A DURING TAKEOFF, ENGINE QUIT WHEN AIRCRAFT WAS AT 200 FEET AGL. AIRCRAFT CRASHED INTO A SWAMP. AIRCRAFT WAS DESTROYED, OCCUPANTS RECEIVED MINOR INJURIES. DURING POST-CRASH INVESTIGATION, THE ENGINE CRANKSHAFT WAS FOUND BROKEN AT THE NR 3 ROD BEARING JOURNAL FORWARD THROW AT THE ENTER MAIN BEARING JOURNAL. ENGINE TT IS 5,487 HRS AND TSO IS 1,281 HRS. NOTE D IN THE MAINTENANCE RECORDS FOR THE ENGINE THAT A PROP STRIKE OCCURRED WITH APPROX 1,500 HRS TT. AT THAT TIME, ONLY A FLANGE RUN-OUT CHECK WAS ACCOMPLISHED. SUBMITTER SUGGESTED THAT THE CRANKSHAFT BE REPLACED AFTER ANY SUDDEN STOPPAGE OR PROP STRIKE. (X) 1 L 7 1 3O 3 O 2A13 E274 2000080700097 20000807 00097 NE 2000 8 7 20000713SH001 2 20000711 G 7421 ER400 SPARK PLUG PWA AN1 AYRES S2 S2RRESTD 0970101 SO PWA R1340 R1340AN1 52016 NE HAMSTD 12D 12D40 NE ENGINE BROKEN G KIIG A UNSCHED LANDING Y ENGINE STOPPAGE NR NOT REPORTED 1 GL 15 82494 7P102181 1541R 7P102181 SW2837 SPARK PLUG FAILED INTERNALLY. COMBUSTION GASSES BURNT OFF THE SPARK PLUG LEAD AND VENTED EXTERNALLY, RESULTING IN LOST COMPRESSION AND POWER OUTPUT. (INT) 1 L 7 1 3R 3 R A4SW 5E2 5 C P257 2000101800048 20001018 00048 CE 2000 10 18 20000713SH005 1 20000609 G 2450 CIRCUIT BREAKER CESSNA 172 172M 2072418 CE ALTERNATOR OUTP FAILED G O OTHER H ELECT. POWER LOSS-50 PC CR CRUISE 1 NE 03 12766 4622 17262240 ALTERNATOR OUTPUT BREAKER FAILED IN IFR FLIGHT. BREAKER HAD NO CONTINUITY IN CLOSED (NOT TRIPPED) CONDITION. ORIGINAL CIRCUIT BREAKER FROM DATE OF MFG 9/73. (X) 1 H 7 1 3O NT 3A12 2001030200004 20010302 00004 CE 2001 3 2 20000713SH006 1 20000626 G 7160 PAINT CESSNA 208 208B 2073701 CE INERTIAL SEPARAT LOOSE D K NONE O OTHER IN INSP/MAINT 1 WP 07 1289Y 198 208B0818 DURING THE FIRST PHASE 1 INSPECTION, AN AREA APPROXIMATELY 3 INCHES SQUARE ON THE INSIDE BOTTOM OF THE INERTIAL SEPARATO R HAD LOOSE EPOXY PAINT PEELING LOOSE. 15 GRAMS OF CHIPS REMOVED WITH FINGERNAIL. AN UNKNOWN MOUNT WAS MISSING AND PRE SUMABLY WENT THROUGH THE ENGINE. NO DAMAGE WAS NOTED DURING INSPECTION OF NR 1 COMPRESSOR WHEEL. SUBMITTER RECOMMENDED THAT AFTER THIS PART IS DIP PAINTED, IT BE DRIED IN AN UPRIGHT POSITION TO ALLOW EXCESS PAINT TO DRAIN. (X) 1 H 7 1 3T A37CE 2000120700004 20001207 00004 SO 2000 12 7 20000713SH009 2 20000713 G 8520 CASE BEECH 58 58TC 1152746 CE CONT O520 TSIO520L 17040 SO CRACKED H K NONE O OTHER IN INSP/MAINT 1 SW 99 1865L 1084 764 TK14 227668R CASE FOUND CRACKED AT NR 5 CYLINDER STUD NR 3, NUT ON STD NR 7 LOOSE AND STUD NR 8 PULLED FROM CASE AND RESTING ON CYLIN DER COOLING FINS. (X) 1 L 7 2 3O 3 O A23CE E8CE 2001020500041 20010205 00041 SO 2001 2 5 20000713SH010 2 20000222 G 8520 SA10200A1 CASTING LUSCOM 8 8A 8190104 SO CONT C90 C908F 17009 SO ENGINE LEAKING H K NONE K FLUID LOSS IN INSP/MAINT 1 GL 03 1970B 100 6397 4685098 DURING ANNUAL INSPECTION, OIL WAS FOUND LEAKING NEAR BOTTOM OF ROCKER COVERS. THE LEAK WAS TRACKED TO THE CASTING LINE BETWEEN THE VALVE GUIDES IN THE FIN AREA. LOCATION OF THE PROBLEM IS THE SAME ON ALL 4 CYLINDERS. LEAK SEEMED TO BE CA USED BY POROSITY IN CASTING LINE. (X) 1 H 7 1 3O 3 O A694 E252 2000102600001 20001026 00001 CE 2000 10 26 20000713SH023 1 20000514 G 3230 HEIMHML6 ROD END BEECH 35 J35 1151522 CE N/G RETRACT ROD BROKEN D O OTHER O OTHER TX TAXI/GRND HDL 1 SO 03 263AA D5581 PILOT WAS TAXIING OUT FOR TAKEOFF WHEN NOSE GEAR SUDDENLY RETRACTED CAUSING SUDDEN STOPPAGE OF ENGINE. FOUND ROD END BR OKEN AT AFT END OF NOSE GEAR RETRACT ROD WHERE IT ATTACHES TO GEAR ACTUATOR. SUBMITTER RECOMMENDED CLOSER INSPECTION AT ANNUAL. (X) 1 L 7 1 3O 3A15 2000102600002 20001026 00002 EA 2000 10 26 20000713SH024 2 20000613 G 8530 PLUG PIPER PA23 PA23250 7102308 SO LYC O540 IO540C4B5 41532 EA IN PISTON FAILED E K NONE O OTHER IN INSP/MAINT 1 AL 05 40258 163 277305068 PISTON PIN PLUG FAILED AND FILLED THE ENGINE WITH ALUMINUM. THESE ARE THE SEPARATE PUSH IN LARGE DIAMETER PLUGS. INSTA LLATION DATE: 7/98. (X) 1 L 7 2 3O 3 O 1A10 1E4 2000102600003 20001026 00003 2000 10 26 20000713SH025 4 20000510 G 3416 5932A3 ALTIMETER PIPER PA32 PA32300 7103212 SO INSTR PANEL DEFECTIVE B GCPR K NONE O OTHER IN INSP/MAINT 1 NM 09 4210R 3240575 PERFORMED PITOT/STATIC CERTIFICATION IAW FAR 91.411 AND TRANSPONDER CERTIFICATION IAW FAR 91.413. FOUND DEFECTIVE ALTIM ETER AND REPLACED WITH NEW INSTRUMENT. PERFORMED CORRESPONDENCE TEST IAW FAR PART 43 APP E PARA (C). NO FURTHER PROBLE MS SEEN. (X) 1 L 7 1 3O A3SO 2000102600005 20001026 00005 CE 2000 10 26 20000714SH008 1 20000304 G 2730 053200135 ADAPTER CESSNA 172 172F 2072414 CE RT ELEVATOR FRETTED D K NONE O OTHER IN INSP/MAINT 1 SO 09 5320R 4020 17252844 DURING ANNUAL CONDITION INSP, RT ELEVATOR WAS FOUND LOOSE ON THE TORQUE TUBE. FURTHER INVESTIGATION REVEALED THE RIVETS HOLDING THE TORQUE TUBE ADAPTER (PN 0532001-35) WERE FRETTING AND IT WAS DETERMINED TO BE THE CAUSE OF THE LOOSE CONDIT ION. SUBMITTER STATED THIS IS THIRD CONDITION FOUND ON CESSNA ACFT. POSSIBLY CAUSED BY HIGH WINDS AND/OR VIBRATION CAU SED BY PROP WASH. (X) 1 H 7 1 3O NT 3A12 2000120700005 20001207 00005 GL 2000 12 7 20000714SH024 3 20000616 G 6111 V84334R BLADE HARTZL BEECH 35 S35 1151532 CE CONT O520 IO520BA 17032 SO HARTZL HCA3V PHCA3VF4 GL V-GROOVE SHANK CRACKED B W59R K NONE O OTHER IN INSP/MAINT 1 WP 07 87K D7607 BL137 PROPELLER SUBMITTAL FOR AD 97-18-02 INITIAL INSPECTIONS. S/N A69152 (BLADE NR 1) FOUND CRACKED IN AREA OF A/O?????? USI NG EDDY CURRENT INSPECTION EQUIPMENT. NOTE: A/O??????WAS OVERDUE. SUBMITTER STATED SHOULD HAVE BEEN COMPLETED NO LONG ER THAN SEPT, 1999. (X) 1 L 7 1 3O 3 O 3A15 E5CE 5 C P6EA 2000071800130 20000718 00130 EA 2000 7 18 20000714SH029 2 20000714 G 8530 VALVE SEAT CESSNA 206 T206H CE LYC O540 TIO540AF1A 41532 EA EXHAUST LOOSE B O OTHER R PARTIAL RPM/PWR LOSS CR CRUISE 1 SW 99 2638U T20608061 L1018861A AIRCRAFT HAD ENGINE FAILURE AT 79 FLIGHT HOURS. THE NR 1 CYLINDER EXHAUST VALVE SEAT CAME LOOSE FROM THE CYLINDER AND CA USED SIGNIFICANT DAMAGE TO THE ENGINE. THE OUTSIDE DIAMETER OF THE EXHAUST VALVE SEAT WAS FOUND UNDERSIZED. (X) 1 H 7 1 3O 3 O A4CE E14EA 2000071800131 20000718 00131 NE 2000 7 18 20000714SH030 2 20000627 G 7412 CH346593 IGNITER CESSNA 500 560CESSNA 2076750 CE PWA JT15 JT15D5 52112 NE CENTER ELECTRODE FAILED D K NONE O OTHER IN INSP/MAINT 1 SW 01 37WP 148 5600259 PCE108497 DURING PHASE 2 INSPECTION, LEFT ENGINE INBOARD IGNITER PLUG WAS FOUND TO HAVE APPROXIMATELY .6250 INCH OF THE CENTER ELE CTRODE MISSING ON THE FIRING END. IT APPEARS THE ELECTRODE DEPARTED SHORTLY AFTER IGNITER PLUG INSTALLATION DUE TO VERY SLIGHT WEAR ON THE FIRING END OF PLUG. THE HP TURBINE BLADES BORESCOPED BY PRATT & WHITNEY REP WITH NO DISCREPANCIES N OTED. (X) 2 L 7 2 4F 4 F RT A22CE E25EA 2000071800132 20000718 00132 SW 2000 7 18 20000714SH031 1 20000601 G 2121 19A2501 BLOWER MOTOR BELL 412 412 1182202 SW INOPERATIVE A XSFA K NONE O OTHER IN INSP/MAINT 1 WP 13 412SA 33210 BLOWER MOTOR INOPERATIVE. (X) 1 G 7 2 4U H4SW 2000071800133 20000718 00133 CE 2000 7 18 20000714SH032 1 20000625 G 2820 RSA5AD1 SERVO CESSNA 172 172S 2072439 CE LYC O360 O360* 41514 EA FUEL ENG VAPOR LOCK D O OTHER Y ENGINE STOPPAGE TO TAKEOFF 1 NM 03 567JW 590 172S8187 ACFT WAS ON NIGHT FLIGHT AND COMPLETED 5 LANDINGS. FULL STOP ON RUNWAY, THEN TAKING OFF. ON THE 6TH LANDING WHEN THROT TLE WAS RETARDED OVER THE RUNWAY THRESHOLD, ALTERNATOR LIGHT ILLUMINATED AND ON ROLL-OUT, ENGINE QUIT. ATTEMPTS WERE MA DE TO RESTART, BUT WOULD NOT RESTART. ACFT TOWED TO PARKING. MAINTENANCE INSPECTED AND STARTED ENG WITH NO DIFFICULT IES. ALL OPERATING PERIMETERS NORMAL, IDLE SPEED, AND MIXTURE STRENGTH NORMAL. UPON RETURN HOME, ACFT DIVERTED FOR 1 H R DUE TO THUNDERSTORMS, THEN TOOK OFF, RETURNED HOME. UPON ARRIVAL, ENG IDLE WAS ROUGH, IDLE SPEED ERRATIC. ENG SHUT D OWN, RESTART ATTEMPTED, VAPOR LOCKED. RESTARTED END, NO DIFFICULTIES. FUEL SERVO SENT TO CESSNA FOR EXAMINATION. (X) 1 H 7 1 3O 3 O NT 3A12 E286 2000071800134 20000718 00134 CE 2000 7 18 20000714SH033 1 20000629 G 2600 SWITCH CESSNA CESSNA 208 208B 2073701 CE INST PANEL SHORTED C AWHA A UNSCHED LANDING N FALSE WARNING CR CRUISE 1 WP 17 790FE 208B0288 PILOT REPORTED AFTER REPEATED ACTUATIONS OF FIRE DETECTION WARNING TEST SWITCH, SWITCH BUTTON DETACHED FROM SWITCH BODY CAUSING SWITCH TO SHORT AND ACTIVATE WARNING HORN. PILOT DECLARED AN EMERGENCY AND DIVERTED TO BUR AIRPORT WITHOUT INCI DENT. (X) 1 H 7 1 3T A37CE 2000071800196 20000718 00196 CE 2000 7 18 20000714SH034 1 20000622 G 3250 2609 CLIP MAULE BBAVIA 11 11AC 0191102 CE STEERING SPRING SEPARATED G O OTHER O OTHER TX TAXI/GRND HDL 1 SO 07 85861 11AC284 CONNECTOR CLIP PULLED OPEN ALLOWING STEERING SPRING TO COME LOOSE OF TAIL WHEEL STEERING HORN RESULTING IN A LOSS OF LEF T STEERING CONTROL. (X) 1 H 7 1 3O A761 2000071800002 20000718 00002 CE 2000 7 18 20000717SH007 1 20000627 G 7120 045100336 MOUNT CESSNA 150 152 2071835 CE LOWER BROKEN D K NONE O OTHER IN INSP/MAINT 1 SO 05 89433 6203 15282743 LOWER WELD AT LOWER NLG STRUT SLEEVE BROKEN ON ENGINE MOUNT. SUSPECT FATIGUE OR OVERTORQUING OF LOWER STRUT MOUNT BOLT AS CAUSE OF CRACK. POSSIBLE NOSE HARD LANDING CONTRIBUTED TO PROBLEM. (X) 1 H 7 1 3O NT 3A19 2000071800004 20000718 00004 CE 2000 7 18 20000717SH008 1 20000627 G 7120 05510231 MOUNT CESSNA 172 172N 2072434 CE BROKEN D K NONE O OTHER IN INSP/MAINT 1 SO 05 733VS 3586 17268588 DURING 100-HOUR INSPECTION, FOUND LOWER CROSSOVER TUBE ON ENGINE MOUNT BROKEN ON RT SIDE AND CRACKED ON LT SIDE (BOTH AT WELDS). POSSIBLE CAUSES ARE WORN SHOCK MOUNTS CAUSING EXCESS VIBRATION OR FATIGUE. SUBMITTER RECOMMENDED MAKING SURE MOUNT IS CLEAN TO FACILITATE THOROUGH INSPECTION. (X) 1 H 7 1 3O NT 3A12 2000071800007 20000718 00007 EA 2000 7 18 20000717SH010 2 20000610 G 8520 CRANKSHAFT UNIVAR 108 1082 9230406 NM FRNKLN 6A4165 6A4165B3 27025 EA FAILED G O OTHER Y ENGINE STOPPAGE NR NOT REPORTED 1 EA 21 9830K 1082830 ENGINE BEGAN RUNNING ROUGH AND THEN THE PROPELLER LOCKED IN THE VERTICAL POSITION. POST-INCIDENT INSPECTION OF THE ENGI NE REVEALED THE CRANKSHAFT HAD FAILED. (X) 1 H 7 1 3O 3 O A767 E238 2001020700102 20010207 00102 NE 2001 2 7 20000717SH012 2 20000629 G 7250 BLADE GE GE CJ610 CJ6109 30006 NE ENGINE FRACTURED B EX2R K NONE O OTHER IN INSP/MAINT 1 SW 15 4709 1917 GATWZA0442 222060 TWO EACH, STAGE 1 TURBINE BLADES FRACTURED AND LIBERATED THE TOP ONE-THIRD OF THE AIRFOIL CAUSING DAMAGE TO THE 2ND STAG E BLADES. SUBMITTER STATED INSUFFICIENT INSPECTION INFORMATION EXISTS IN THE ENGINE MANUAL TO DETECT THINNING/NECKING O F THE AIRFOIL SECTION DUE TO CREEP AND/OR OXIDATION AND/OR EROSION. THINNING OF THE BLADE AIRFOIL CROSS-SECTION RESULTS IN BLADE FRACTURE. (X) 4 J 1E16 2001020700114 20010207 00114 NE 2001 2 7 20000717SH013 2 20000628 G 7250 BLADE GE GE CJ610 CJ6109 30006 NE ENGINE FRACTURED B EX2R K NONE O OTHER IN INSP/MAINT 1 SW 15 4709 1917 GATWZA00442 222060 TWO EACH, STAGE 1 TURBINE BLADES FRACTURED AND LIBERATED THE TOP ONE-THIRD OF THE AIRFOIL CAUSING DAMAGE TO THE 2ND STAG E BLADES. SUBMITTER STATED INSUFFICIENT INSPECTION INFORMATION EXISTS IN THE ENGINE MANUAL TO DETECT THINNING/NECKING O F THE AIRFOIL SECTION DUE TO CREEP AND/OR OXIDATION AND/OR EROSION. THINNING OF THE BLADE AIRFOIL CROSS-SECTION RESULTS IN BLADE FRACTURE. (X) 4 J 1E16 2001012900031 20010129 00031 EU 2001 1 29 20000717SH014 1 20000416 G 6320 CONNECTOR SNIAS 350 AS350B2 8680813 EU GEARBOX CORRODED A XSFA K NONE O OTHER IN INSP/MAINT 1 WP 13 964SA 4905 2931 CORRODED PINS AT DIFFERENT CANNON PLUGS AND CORRODED WIRES THROUGHOUT HARNESS. (X) 1 G 7 1 3U H9EU 2001012900032 20010129 00032 EU 2001 1 29 20000717SH015 1 20000419 G 6410 350A332115300 BEARING SNIAS 350 AS350B2 8680813 EU TAIL ROTOR DELAMINATED A XSFA K NONE O OTHER IN INSP/MAINT 1 WP 13 964SA 256 2931 BEARING DELAMINATING. (X) 1 G 7 1 3U H9EU 2001012900033 20010129 00033 EU 2001 1 29 20000717SH016 1 20000517 G 7931 642790041 TRANSMITTER SNIAS 350 AS350B2 8680813 EU ENGINE OIL READS LOW A XSFA K NONE O OTHER IN INSP/MAINT 1 WP 13 964SA 4971 2931 TRANSMITTER READING TOO LOW, NOT ACCURATE. (X) 1 G 7 1 3U H9EU 2001012900034 20010129 00034 EU 2001 1 29 20000717SH018 1 20000606 G 6320 SEAL SNIAS 350 AS350B2 8680813 EU MAIN ROTOR INPUT LEAKING A XSFA K NONE K FLUID LOSS IN INSP/MAINT 1 WP 13 985SA 3111 INPUT SEAL, MAIN ROTOR GEARBOX, LEAKING POST LIP. (X) 1 G 7 1 3U H9EU 2000100300050 20001003 00050 SW 2000 10 3 20000718SH001 1 20000608 G 6510 407340339103 BEARING BELL 407 407 SW FAILED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 917AL 524 A283 53381 DURING IN-SHOP REPAIR, FOUND ROUGH BEARINGS. INSTALLED SELF-CENTERING BEARINGS. (X) 1 G 7 1 3U O H2SW 2001020200050 20010202 00050 SW 2001 2 2 20000718SH002 1 20000608 G 6510 407340339103 BEARING BELL 407 407 SW TAIL ROTOR ROUGH B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 917AL 524 A283 53381 DURING IN-SHOP REPAIR, FOUND ROUGH BEARINGS. INSTALLED SELF-CENTERING BEARINGS. REPLACED 2 EACH. (X) 1 G 7 1 3U O H2SW 2001020200051 20010202 00051 SW 2001 2 2 20000718SH003 1 20000505 G 6420 406312100101 BEARING BELL BELL 407 407 SW T/R YOKE WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 917AL 644 A487 53381 DURING DAILY SERVICE CHECK, FOUND INBOARD FEATHER BEARING WEAR, CAUSING THE OUTER RACE OF FEATHER BEARING TO SHIFT IN YO KE CAUSING BORE TO WEAR BEYOND LIMITS. (X) 1 G 7 1 3U O H2SW 2001020200052 20010202 00052 EU 2001 2 2 20000718SH004 1 20000628 G 7603 961305A57105300 BALL JOINT SNIAS 350 AS350B1 8680811 EU POWER LEVER DETACHED B K NONE O OTHER IN INSP/MAINT 1 WP 23 2127S 2213 DURING STARTING SEQUENCE, PILOT ATTEMPTED TO SHUT DOWN THE ENGINE DUE TO SLOW START. ENG KEPT RUNNING, PILOT WENT TO EM ERG SHUT OFF. UPON INSP, POWER LEVER ''END'' HAD COME OFF OF ''BALL JOINT'' WHICH IS ATTACHED TO FUEL CONTROL. THE SAF ETY PIN THAT SAFTIES THE ''END'' RELEASE WAS IN PLACE. NOTED THE ''END'' WOULD COME OFF THE ''BALL JOINT'' WHEN RELEASE WAS PRESSED INSPITE OF SAFETY PIN BEING IN PLACE. IT IS RECOMMENDED THAT INSP CRITERIA FOR PARTS IN QUESTION (BALL JOI NT AND THE END) BE ADDED TO APPROPRIATE MAINT WORK CARDS AND PROCEDURE BE ADDED AS WELL. COPY OF THIS MDR WILL BE SENT TO AMERICAN EUROCOPTER. (X) 1 G 7 1 3U H9EU 2001020200053 20010202 00053 SW 2001 2 2 20000718SH005 1 20000706 G 6310 206040047001 NUT BELL 206 206L3 1182108 SW INPUT ADAPTER OVERTORQUED B NKVR K NONE O OTHER IN INSP/MAINT 1 NM 09 206DB 608 52127 MECHANIC REPORTED THE M/R TRANSMISSION INPUT SHAFT ADAPTER RETAIING NUT SEEMED TO BE OVERTORQUED ON INSTALL OR PREVIOUS MAINTENANCE. ESTIMATED TORQUE WAS AT LEAST TWICE THE BHT M.M. SPEC FOR THAT PART. ADAPTER AND NUT MAGNAFLUXED FOR DEFE CTS, NONE FOUND. SUBMITTER RECOMMENDED SAME ACTION IF OTHER OPERATORS ENCOUNTED THIS PROBLEM. (X) 1 G 7 1 3U H2SW 2001020200054 20010202 00054 SW 2001 2 2 20000718SH006 1 20000403 G 6210 206015001107 BLADE BELL 206 206L1 1182107 SW MAIN ROTOR CORRODED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 27545 2444 45234 INSPECTION OF AIRCRAFT DURING REFURBISHING, FOUND INTERGRANULAR CORROSION OF LEADING EDGE OF MAIN ROTOR BLADES. (X) 1 G 7 1 3U H2SW 2001020200055 20010202 00055 SW 2001 2 2 20000718SH007 1 20000403 G 6210 206015001107 BLADE BELL 206 206L1 1182107 SW MAIN ROTOR CORRODED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 27545 2699 45234 INSPECTION OF AIRCRAFT DURING REFURBISHING FOUND INTERGRANULAR CORROSION OF LEADING EDGE OF MAIN ROTOR BLADES. (X) 1 G 7 1 3U H2SW 2001012900039 20010129 00039 EU 2001 1 29 20000718SH008 1 20000621 G 6730 SC8032 SERVO AEROSP SA365 SA365N 8680669 EU MAIN ROTOR DAMAGED A ZYWA O OTHER J WARNING INDICATION NR NOT REPORTED 1 GL 09 365SJ 2718 6018 SERVO LIGHT INTERMITTENT. REMOVED AND REPLACED SERVO. (X) 1 G 7 2 3U H10EU 2001012900040 20010129 00040 EU 2001 1 29 20000718SH009 1 20000612 G 5260 14860011 ACTUATOR AEROSP AS365 AS365N2 8680815 EU STOP INOPERATIVE A ZYWA K NONE O OTHER IN INSP/MAINT 1 GL 09 365WM 34 6429 STOP ACTUATOR MOTOR INOPERATIVE. REMOVED AND REPLACED MOTOR. (X) 1 G 7 2 3U RT H10EU 2001012900041 20010129 00041 EU 2001 1 29 20000718SH010 1 20000615 G 6230 365A3118SP02 ADAPTER AEROSP AS365 AS365N2 8680815 EU MAIN ROTOR TORN A ZYWA K NONE O OTHER IN INSP/MAINT 1 GL 09 365WM 6429 ONE EACH ADAPTER TORN AFTER 218.1 HOURS IN SERVICE. REMOVED AND REPLACED FREQUENCY ADAPTERS. REPLACED 2 EACH. (X) 1 G 7 2 3U RT H10EU 2001012900042 20010129 00042 EU 2001 1 29 20000718SH011 1 20000615 G 6230 365A3118SP02 ADAPTER AEROSP AS365 AS365N2 8680815 EU MAIN ROTOR TORN A ZYWA K NONE O OTHER IN INSP/MAINT 1 GL 09 365WM 218 6429 ONE EACH ADAPTER TORN AFTER 218.1 HOURS IN SERVICE. REMOVED AND REPLACED FREQUENCY ADAPTERS. REPLACED 2 EACH. (X) 1 G 7 2 3U RT H10EU 2001012900043 20010129 00043 EU 2001 1 29 20000718SH012 1 20000622 G 6730 SC8031 SERVO AEROSP SA365 SA365N 8680669 EU MAIN ROTOR DAMAGED A ZYWA O OTHER J WARNING INDICATION NR NOT REPORTED 1 GL 09 365SJ 2149 6018 SERVO LIGHT ILLUMINATING. REMOVED AND REPLACED SERVO. (X) 1 G 7 2 3U H10EU 2001020200056 20010202 00056 SW 2001 2 2 20000718SH013 1 20000611 G 6210 206015001107 BLADE BELL 206 206L3 1182108 SW MAIN ROTOR CORRODED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 3174Y 3428 51038 DURING DAILY INSPECTION, FOUND HEAVY INTERGRANULAR CORROSION ON TRAILING EDGE EXTRUSION. (X) 1 G 7 1 3U H2SW 2001012900044 20010129 00044 NE 2001 1 29 20000718SH014 1 20000508 G 3230 CONNECTOR SKRSKY S76 S76A 8143006 NE PROX SWITCH DIRTY A ALGA O OTHER N FALSE WARNING CL CLIMB 1 SW 03 376AL 760002 ON TAKEOFF, LANDING GEAR WOULD NOT RETRACT. FOUND ''UP'' PROXIMITY SWITCH CANNON PLUG ON NOSE GEAR ACTUATOR DIRTY. CLE ANED AND REINSTALLED. (X) 1 G 7 2 3U H1NE 2001020200057 20010202 00057 SW 2001 2 2 20000718SH015 1 20000621 G 6320 407040006107 TRANSMISSION BELL 407 407 SW MAIN ROTOR CORRODED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 577AL 2487 A327 53247 AT DISASSEMBLY FOR TRANSMISSIONS FIRST OVERHAUL, FOUND CORROSION IN BORE OF MOUNTING SPLINDLE. CORROSION IN BORE OF CHI P DETECTOR ASSY. CORROSION ON INPUT FLANGE. (X) 1 G 7 1 3U O H2SW 2001012900045 20010129 00045 SW 2001 1 29 20000718SH016 1 20000614 G 6510 407340340101 DISC PACK BELL BELL 407 407 SW T/R DRIVE CRACKED A ALGA K NONE O OTHER IN INSP/MAINT 1 SW 03 467AL 1209 25 A457 53190 DURING 25-HOUR AD INSPECTION, FOUND THE LAST DISC IN THE COUPLING CRACKED (WITH PACK FACING FORWARD) MID-SPAN. (X) 1 G 7 1 3U O H2SW 2001020200058 20010202 00058 SW 2001 2 2 20000718SH017 1 20000527 G 6220 407310101101 BEARING BELL BELL 407 407 SW MAIN ROTOR HUB DAMAGED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 497AL 3185 690 A190 53172 DURING DAILY SERVICE CHECK, FOUND ELASTOMERIC SEPARATED FROM SPINDLE. (X) 1 G 7 1 3U O H2SW 2001012900046 20010129 00046 EA 2001 1 29 20000718SH018 2 20000622 G 7414 10357424 BEARING ROBSIN R22 R22BETAII 7640110 NM LYC O360 O360J2A 41514 EA DIST BLOCK FAILED A MKWA K NONE O OTHER IN INSP/MAINT 1 GL 03 441MM 95 L049915E 3057 L3727236A LEFT MAGNETO FAILED. UPON DISASSEMBLY AND INSPECTION, FOUND THE BUSHING IN THE DISTRIBUTOR BLOCK WHERE THE DISTRIBUTOR G EARSHAFT RIDES, HAD COME LOOSE. THE LOOSE BUSHING HAD BADLY DAMAGED THE DISTRIBUTOR BLOCK ASSY. (X) 1 G 7 1 3O 3 O H10WE E286 2001013000037 20010130 00037 SW 2001 1 30 20000719SH001 1 20000501 G 6510 407340340101 DISC PACK BELL BELL 407 407 SW TAIL ROTOR CRACKED A ALGA K NONE O OTHER IN INSP/MAINT 1 SW 03 607AL 25 A1128 53264 DURING 25-HOUR AD INSPECTION, TAIL ROTOR DRIVESHAFT FOUND CRACKED. (X) 1 G 7 1 3U O H2SW 2001020200059 20010202 00059 SW 2001 2 2 20000719SH002 1 20000427 G 6510 407340339103 HOUSING BELL 407 407 SW T/R BEARING CRACKED C ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 627AL 331 AFS1204 53284 DURING DAILY INSPECTION AND BEARING LUBRICATION, FOUND HOUSING CRACKED AND BLACK GREASE EXPELLED FROM AROUND THE SEAL D ETERMINING BEARING DAMAGED. (X) 1 G 7 1 3U O H2SW 2001013000038 20010130 00038 SW 2001 1 30 20000719SH003 1 20000427 G 6510 206061 HOUSING BELL 407 407 SW TAIL ROTOR CRACKED A ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 627AL 331 AFS1204 53284 DURING DAILY INSPECTION AND BEARING LUBRICATION, FOUND HOUSING CRACKED AND BLACK GREASE EXPELLED FROM AROUND THE SEAL D ETERMINING BEARING DAMAGED. (X) 1 G 7 1 3U O H2SW 2001020200060 20010202 00060 SW 2001 2 2 20000719SH004 1 20000416 G 6510 407340339103 BEARING BELL BELL 407 407 SW SHAFT HANGER DAMAGED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 687AL 907 A1669 53366 RECURRING 25-HOUR INSPECTION AND BEARING LUBRICATION (PER ASB 407-00-35 AND AD 2000-02-01), FOUND ACCUMULATED GREASE EXP ELLED FROM AROUND THE SEAL IS BLACK DETERMINING BEARING IS DAMAGED. (X) 1 G 7 1 3U O H2SW 2001020200061 20010202 00061 GL 2001 2 2 20000719SH006 2 20000601 G 7260 23007248 GEAR SHAFT ALLSN SKRSKY S76 S76A 8143006 NE ALLSN 250C 250C30S 03013 GL GEAR BOX MISMANUFACTURED B ALGR K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 710AL 113 CAG90802 760279 890266S UPON ASSEMBLY OF GEARBOX WHEN INSTALLING COUPLING , FOUND COUPLING WOULD NOT SIT COMPLETELY, STAYED COCKED. REMOVED CO UPLING AND INSPECTED. FOUND IMPROPER MACHINING OF COUPLING MATING SURFACE TO F/C GEAR WITH PIECES OF ROLLED METAL. FUE L CONTROL GEAR HAD IMPROPER MACHINING AT COUPLING MATING SURFACE. (X) 1 G 7 2 3U 3 U H1NE E1GL 2000103100015 20001031 00015 SO 2000 10 31 20000719SH008 2 20000217 G 8530 SA52000A20P GUIDE CONT O520 IO520* 17032 SO INACCURATE B CY4R K NONE O OTHER IN INSP/MAINT 1 AL 03 INTAKE GUIDE VARIANCE, 0.0020 INCH. (X) 3 O E5CE 2000103100016 20001031 00016 SO 2000 10 31 20000719SH009 2 20000217 G 8530 SA52000A20P GUIDE CONT O520 IO520* 17032 SO INACCURATE B CY4R K NONE O OTHER IN INSP/MAINT 1 AL 03 INTAKE GUIDE VARIANCE, 0.0016 INCH. (X) 3 O E5CE 2000103100017 20001031 00017 SO 2000 10 31 20000719SH010 2 20000217 G 8530 52L9915 GUIDE CONT O520 IO520* 17032 SO INACCURATE B CY4R K NONE O OTHER IN INSP/MAINT 1 AL 03 INTAKE GUIDE VARIANCE, 0.0015 INCH. (X) 3 O E5CE 2000103100023 20001031 00023 SO 2000 10 31 20000719SH011 2 20000217 G 8530 SA52000A20P GUIDE CONT O520 IO520* 17032 SO INACCURATE B CY4R K NONE O OTHER IN INSP/MAINT 1 AL 03 INTAKE GUIDE VARIANCE, 0.0016 INCH. (X) 3 O E5CE 2000110100030 20001101 00030 SO 2000 11 1 20000719SH012 2 20000217 G 8530 SA52000A20P GUIDE CONT O520 IO520* 17032 SO INACCURATE B CY4R K NONE O OTHER IN INSP/MAINT 1 AL 03 INTAKE GUIDE VARIANCE, 0.0018 INCH. (X) 3 O E5CE 2000110100031 20001101 00031 SO 2000 11 1 20000719SH013 2 20000227 G 8530 SA52000A20P GUIDE CONT O520 IO520* 17032 SO INACCURATE B CY4R K NONE O OTHER IN INSP/MAINT 1 AL 03 INTAKE GUIDE VARIANCE, 0.0020 INCH. (X) 3 O E5CE 2000073100207 20000731 00207 SO 2000 7 31 20000719SH014 2 20000519 G 8520 649134 CRANKSHAFT CESSNA 185 A185F 2072821 CE CONT O520 IO520D 17032 SO FAILED B CY4R K NONE O OTHER IN INSP/MAINT 1 AL 03 3469Y 63 18502888 559906 PER TCM MSB 00-5, CRANKSHAFT WAS REJECTED BY TELEDYNE CONTINENTAL MOTORS. (X) 1 H 7 1 3O 3 O 3A24 E5CE 2000091400001 20000914 00001 SO 2000 9 14 20000719SH015 2 20000519 G 8510 649134 CRANKSHAFT CESSNA 180 180A 2072604 CE CONT O470 O470K 17026 SO FAILED B CY4R K NONE O OTHER IN INSP/MAINT 1 AL 03 9728B 19 50026 506161 PER TCM MSB 00-5, CRANKSHAFT WAS REJECTED BY TELEDYNE CONTINENTAL MOTORS. (X) 1 H 7 1 3O 3 O 5A6 E273 2000091400002 20000914 00002 EU 2000 9 14 20000719SH016 1 20000705 G 3230 TB2061238001 PRESSURE SWITCH LANDINGGEAR SOCATA TB20 TB21 8680697 EU HYDRAULIC SYSTEM FAILED H A UNSCHED LANDING O OTHER CL CLIMB 1 EA 07 30582 128 W51148 1618 PILOTS REPORTED LANDING GEAR WOULD NOT RETRACT, CHECKED FUSES, ALL OK. BYPASSED PRESSURE SWITCH. GEAR RETRACTED, INSTA LLED NEW PRESSURE SWITCH, PN TB206138001, SYSTEM CHECKED OK. NOTE: SEVERAL PRESSURE SWITCHES HAVE BEEN REPLACED. PART TT 128.1 HOURS, SWITCH WAS INSTALLED 3-16-00. (X) 1 L 7 1 3O RT A51EU 2000091400003 20000914 00003 EA 2000 9 14 20000719SH017 2 20000621 G 8520 SL74644 ROD BOLT LYC GULSTM 500 500B 0141106 SW LYC O540 IO540E1A5 41532 EA BROKEN E O OTHER O OTHER NR NOT REPORTED 1 SW 15 780SP 1400 1362133 L88148 ROD CAP CAME OFF NR 2 CYLINDER AS A RESULT OF EITHER SL74644 BREAKING OR SL128186 NUT BACKING OFF. (X) 1 H 7 2 3O 3 O 6A1 1E4 2000091400004 20000914 00004 EA 2000 9 14 20000719SH018 2 20000621 G 8530 SL12186 NUT GULSTM 500 500B 0141106 SW LYC O540 IO540E1A5 41532 EA FAILED E K NONE O OTHER IN INSP/MAINT 1 SW 15 780SP 1400 1362133 L88248 INTAKE GUIDE VARIANCE, 0.0020 INCH. (X) 1 H 7 2 3O 3 O 6A1 1E4 2000091400006 20000914 00006 CE 2000 9 14 20000720SH001 1 20000613 G 2711 99130011 TRIM TAB BEECH 99 99 1154002 CE LT AILERON CRACKED A TIMA K NONE O OTHER IN INSP/MAINT 1 NM 07 95WA 35294 U6 THE AILERON TRIM TAB DID NOT PASS A VISUAL SURFACE INSPECTION DURING A CHECK OF THE FREE PLAY DURING A DETAILED INSPECTI ON. REMOVED ENTIRE AILERON ASSY AND INSTALLED A SERVICEABLE AILERON ASSY. THE INSPECTION PROCESS WORKED IN THIS CASE A S DESIGNED SO AN INCREASE IN FREQUENCY IS NOT WARRANTED. THE INSPECTION/CHECK IS FOR FREE-PLAY AND THE DISCREPANCY WAS FOR BOTH FREE-PLAY IN EXCESS OF THE MFG''S RECOMMENDATIONS AND CRACKS IN THE SKIN. CRACKS IN THE SKIN APPEAR TO BE THE RESULT OF IMPROPER GROUND HANDLING. (X) 1 L 7 2 3T A14CE 2000091400007 20000914 00007 CE 2000 9 14 20000720SH002 1 20000613 G 2720 50524327 BELLCRANK BEECH 99 B99 1154004 CE RUDDER CORRODED E TIMA K NONE O OTHER IN INSP/MAINT 1 NM 07 99TH 33111 U155 DURING A ROUTINE INSPECTION, THE RUDDER WAS FOUND TO HAVE SOME FREE-PLAY AT THE TOP PIVOT BEARING SUPPORT. IT WAS NECES SARY TO REMOVE THE RUDDER TO INSPECT FOR HIDDEN DAMAGE. UPON REMOVAL, NOTICED THE RUDDER BELLCRANK CORRODED AT THE BOLT HOLES THAT SECURE THE RUDDER TO THE BELLCRANK. THE DEFECTIVE BELLCRANK WAS REPLACED WITH A SERVICEABLE BELLCRANK. FUT URE INSPECTION TECHNIQUES WILL INCLUDE MINOR DISASSEMBLY IN THIS AREA TO INSPECT FOR CORROSION. (X) 1 L 7 2 3T A14CE 2000091400008 20000914 00008 EA 2000 9 14 20000720SH003 2 20000621 G 8520 SL74644 ROD BOLT LYC GULSTM 500 500B 0141106 SW LYC O540 IO540E1A5 41532 EA BROKEN E O OTHER R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 SW 15 304JT 60 1494175 L13048 NR 5 CYLINDER ROD CAP CAME OFF. BOTH ROD BOLTS WERE BROKEN. THE CYLINDER WAS BROKEN AND SEPARATED FROM CRANKCASE AT IT S FLANGE. (X) 1 H 7 2 3O 3 O 6A1 1E4 2000091400009 20000914 00009 EA 2000 9 14 20000720SH004 2 20000621 G 8520 SL12186 NUT LYC GULSTM 500 500B 0141106 SW LYC O540 IO540E1A5 41532 EA BROKEN E O OTHER O OTHER NR NOT REPORTED 1 SW 15 304JT 60 1494175 L13048 NR 5 CYLINDER ROD CAP CAME OFF. BOTH ROD BOLTS WERE BROKEN. THE CYLINDER WAS BROKEN AND SEPARATED FROM CRANKCASE AT IT S FLANGE. (X) 1 H 7 2 3O 3 O 6A1 1E4 2000091400010 20000914 00010 CE 2000 9 14 20000720SH006 1 20000706 G 5550 50610015 FITTING BEECH 80 65A80 1152808 CE CRACKED B XA1R K NONE O OTHER IN INSP/MAINT 1 SW 09 70348 LD246 FOUND CRACK RUNNING FROM .25 INCH MOUNTING HOLE TO EDGE OF PART. POSSIBLE CAUSE WAS OVERTORQUE OF FITTING TO ELEVATOR B ELLCRANK ATTACH BOLT. FITTING TIES ELEVATOR TORQUE TUBE TO BELLCRANK ASSEMBLY. (X) 1 L 7 2 3O 3A20 2000091400011 20000914 00011 EA 2000 9 14 20000720SH007 2 20000622 G 7414 E0080155 MOUNT PIPER PA28 PA28140 7102802 SO LYC O320 O320E3D 41508 EA LT POSITION CRACKED B BCBR O OTHER K FLUID LOSS NR NOT REPORTED 1 EA 03 3480Q 3841 2464 287725299 L4714327A PILOT REPORTED A SLIGHT ENGINE OIL LEAK. PROBLEM TRACED TO LEFT MAGNETO, PULLED TO REPLACE MOUNTING GASKET AND NOTED MO UNTING FLANGE WAS CRACKED IN RADIUS APPROXIMATELY 2 INCHES AROUND. MAGNETO WAS REPLACED. (X) 1 L 7 1 3O 3 O 2A13 E274 2000091400013 20000914 00013 CE 2000 9 14 20000720SH008 1 20000207 G 3230 08421201 TUBE CESSNA 310 310L 2074230 CE L/G, GEARBOX FAILED G O OTHER O OTHER LD LANDING 1 WP 07 867MF 310L0123 ON APPROACH AFTER LOWERING GEAR, PILOT NOTICED NOSE GEAR NOT DOWN AND LOCKED. PILOT MADE NOSE-UP LANDING. FURTHER IN SPECTION REVEALED EYELET OF TUBE ASSY HAD FAILED. (X) 1 L 7 2 3O 3A10 2000091400014 20000914 00014 CE 2000 9 14 20000720SH009 1 20000207 G 3230 08421211 TUBE CESSNA 310 310L 2074230 CE L/G GEARBOX FAILED G O OTHER O OTHER LD LANDING 1 WP 07 867MF 310L0123 ON APPROACH AFTER LOWERING GEAR, PILOT NOTICED NOSE GEAR NOT DOWN AND LOCKED. PILOT MADE NOSE-UP LANDING. FURTHER IN SPECTION REVEALED EYELET OF TUBE ASSY HAD FAILED. (X) 1 L 7 2 3O 3A10 2000091400015 20000914 00015 SO 2000 9 14 20000720SH010 1 20000703 G 3233 41789000 FORK PIPER PA31 PA31350 7103110 SO BROKEN B O OTHER O OTHER NR NOT REPORTED 1 EA 25 766CF 5998 317305102 BOLT BROKE ON SHAFT. POSSIBLE CORROSION. FORK BOLT BROKE WHERE HYDRAULIC ACTUATOR ATTACHES. IT BROKE WHERE IT APPEARE D TO BE SCRATCHED. SUBMITTER STATED THIS MAY BE FROM INSTALLATION. 1 L 7 2 3O A20SO 2000092100014 20000921 00014 EA 2000 9 21 20000720SH011 2 20000608 G 8530 LW11775 PLUG LYC CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA ALL CYLINDERS WORN H K NONE O OTHER IN INSP/MAINT 1 NM 03 789EP 688 172S8135 PERFORMED LYC SI 1492B. DURING THE PHASE 2 INSPECTION, OIL FILTER REMOVED AND CUT OPEN FOR INSPECTION. AN EXCESSIVE AM OUNT OF ALUMINUM FLAKES WERE DISCOVERED. ALL 4 CYLINDERS REMOVED ENOUGH TO INSPECT AND REPLACED 8 WORN PISTON PIN PLUGS WITH P/N 60828 PLUGS. RE-INSTALLED CYLINDERS WITH NEW CYLINDER BASE SEALS, INTAKE GASKETS, PUSHROD SEALS AND VALVE COV ER GASKETS. PERFORMED OPERATIONAL CHECK, CHECKED SATISFACTORY. (X) 1 H 7 1 3O 3 O NT 3A12 1E10 2000110100009 20001101 00009 SO 2000 11 1 20000720SH012 1 20000712 G 7920 LW13366 GASKET PIPER PA31 PA31350 7103110 SO FILTER CONV PLTE DETERIORATED I WVBA K NONE O OTHER IN INSP/MAINT 1 AL 01 35270 177 317952141 L161068A AFTER REPORT FROM ANOTHER OPER ABOUT OIL FILTER CONVERTER PLATE GASKET POSSIBLY FAILING, TECH WERE INSPECTING THE AREAS AROUND OIL FILTER CONVERTER PLATES FOR SIGNS OF GASKET EXTRUDING PAST PLATE ON ACCY HOUSING OIL FILTER PAD. ON HEAVY IN SP OF ENG, NOTICED A .0312 INCH TO .0625 INCH OF GASKET MATERIAL EXTRUDING PAST CONVERTER PLATE. FOR SAFETY, OLD GASKET REMOVED. NOTED OLD GASKET WIDER, THINNER, AND BRITTLE (COMP TO NEW). DURING REMOVAL, GASKET CAME OUT IN SMALL PIECES. NOTED THE BRAKE AWAY TORQUE WAS IN EXCESS OF 50-60 FEET/POUNDS REQ BY SI 1453. THIS SI IS REFERRED TO IN SSP 493, PC- 315-5 DATED OCT 1991 FOR TIO, LTIO-540 SERIES TEXTRON LYC. (X) 1 L 7 2 3O A20SO 2001013000042 20010130 00042 EU 2001 1 30 20000720SH013 1 20000426 G 5550 1053040212 FITTING BOLKMS 117 BK117A3 5626015 EU VERTICAL FIN CRACKED E R7MA K NONE O OTHER IN INSP/MAINT 1 NM 07 163BK 502 7063 UPON INSPECTION, NOTICED A CRACK BEHIND UPPER LEFT BOLT HOLE EXTENDING TO RIVET HOLE. (X) 1 G 7 2 3U H13EU 2001013000043 20010130 00043 EU 2001 1 30 20000720SH014 1 20000202 G 6210 117150071 BLADE BOLKMS 117 BK117A3 5626015 EU MAIN ROTOR DEBONDED A R7MA K NONE O OTHER IN INSP/MAINT 1 NM 07 163BK 6034 7063 LEADING EDGE SKIN UNDER BONDED PV-FILM IN NOSE AREA TO APPROX BLADE STA 922 (SECTION 1) IS DEBONDING ON TRAILING EDGE, B OTH UPPER/LOWER SURFACES. (X) 1 G 7 2 3U H13EU 2000110100011 20001101 00011 SO 2000 11 1 20000720SH015 2 20000714 G 8520 CRANKSHAFT CESSNA 207 207A 2073604 CE CONT O520 IO520F 17032 SO MCAULY D3A34 D3A34C404 GL FLANGE CRACKED G K NONE O OTHER IN INSP/MAINT 1 AL 05 73100 10 20700559 CRANKSHAFT CRACKED AND FAILED JUST AFT OF FLANGE AND PROPELLER SEPARATED FROM AIRCRAFT WHILE IN-FLIGHT. (X) 1 H 7 1 3O 3 O A16CE E5CE 5 C P47GL 2000110700001 20001107 00001 CE 2000 11 7 20000720SH016 1 20000503 G 2800 FUEL LINE CESSNA 206 206H 2073301 CE LYC O540 IO540AC1A5 EA CONTAMINATED E O OTHER R PARTIAL RPM/PWR LOSS TO TAKEOFF 1 AL 03 7254H 20609036 L2688948A PILOT REPORTED ENGINE SURGING ON TAKEOFF WITH SIGNIFICANT FUEL FLOW FLUCTUATION WHICH WAS CORRECTED WITH A DECREASE IN E NGINE POWER BY ADJUSTMENT OF THE PROP CONTROL AND ACTIVATION OF THE STANDBY ELECTRIC FUEL PUMP. POST-GROUND RUNS COULD NOT DUPLICATE THE PROBLEM. FOLLOW-UP TEST FLIGHT COULD NOT DUPLICATE THE PROBLEM. INSPECTION OF THE AIRCRAFT FUEL SYST EM DID NOT FIND ANY CONTAMINATION, OBSTRUCTIONS, OR LEAKAGE. (X) 1 H 7 1 3O 3 O RT A4CE 1E4 2000110700002 20001107 00002 SO 2000 11 7 20000720SH017 2 20000517 G 7322 CARBURETOR CESSNA 180 180J 2072622 CE CONT O520 IO520F 17032 SO INACCURATE G O OTHER R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 AL 05 4406R 18052670 818812R NOTE: ACFT IS CONFIGURED ON AEROCET FLOATS AND INCORPORATES TEXAS SKYWAYS, INC. STC NR SE09017SC. INSTALL OF CARBURETE D IO520F ENGINE. PILOT REPORTED ENGINE RUNS ROUGH AT ALL POWER SETTINGS. THE STC HOLDER ADVISED ACFT SHOULD BE OPERATE D BY ''''LEANING WITH MIXTURE CONTROL AGGRESSIVELY FOR OPERATION'''' AS THE ENGINE IS CONFIGURED WITH A LARGER JET IN TH E CARBURETOR DESIGNED TO RUN RICH TO ACCOMMODATE COOLING OF THE LARGER ENGINE, AS WELL AS SETTING THE IDLE RPM AT 1000, WELL ABOVE THE NORMAL IDLE OF 575-625 RPM. THE FLIGHT SUPPLEMENT SUPPLIED WITH THE STC DOES NOT ADDRESS THESE OPERTIONA L DEVIATIONS NOR DOES THE STANDARD PILOT''''S OPERATING HANDBOOK, AND COULD POTENTIALLY CAUSE A SAFETY OF FLIGHT ISSUE. 1 H 7 1 3O 3 O 5A6 E5CE 2000092500002 20000925 00002 EA 2000 9 25 20000720SH018 2 20000425 G 8500 ENGINE CESSNA 206 206H 2073301 CE LYC O540 IO540AC1A5 EA FAILED E O OTHER R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 AL 05 7281M 20606048 L2497448A PILOT REPORTED ENGINE SURGING ON TAKEOFF WITH SIGNIFICANT FUEL FLOW FLUCTUATION WHICH WAS CORRECTED WITH A DECREASE IN E NGINE POWER BY ADJUSTMENT OF THE PROP CONTROL AND ACTIVATION OF THE STANDBY ELECTRIC FUEL PUMP. POST-GROUND RUNS COULD NOT DUPLICATE THE PROBLEM. FOLLOW-UP TEST FLIGHT COULD NOT DUPLICATE THE PROBLEM. INSPECTION OF THE AIRCRAFT FUEL SYSTE M DID NOT FIND ANY CONTAMINATION, OBSTRUCTIONS, OR LEAKAGE. (X) 1 H 7 1 3O 3 O RT A4CE 1E4 2000092500003 20000925 00003 EA 2000 9 25 20000720SH019 2 20000605 G 8500 ENGINE CESSNA 206 206H 2073301 CE LYC O540 IO540AC1A5 EA FAILED E O OTHER R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 AL 05 7281M 20608048 L2497448A PILOT REPORTED ENGINE SURGING ON TAKEOFF WITH SIGNIFICANT FUEL FLOW FLUCTUATION WHICH WAS CORRECTED WITH A DECREASE IN E NGINE POWER BY ADJUSTMENT OF THE PROP CONTROL AND ACTIVATION OF THE STANDBY ELECTRIC FUEL PUMP. POST-GROUND RUNS DUPLIC ATED THE PROBLEM, BUT NORMAL SYSTEMS CHECKS SATISFACTORY. THREE FOLLOW-UP TEST FLIGHTS PERFORMED, PROBLEM RECURRED IN O NLY 2 OF THE FLIGHTS, BOTH DURING TAKEOFF ROLL. INSPECTION OF THE AIRCRAFT FUEL SYSTEM DID NOT REVEAL ANY CONTAMINATION , OBSTRUCTIONS, OR LEAKAGE. MANUFACTURER RECOMMENDED SWAPPING FUEL SERVOS WITH ANOTHER SAME AIRCRAFT TO DETERMINE IF TH E PROBLEM FOLLOWED THE SERVO. ACCOMPLISHED RECOMMENDATION, AND PROBLEM DID NOT RECUR IN EITHER AIRCRAFT. (X) 1 H 7 1 3O 3 O RT A4CE 1E4 2000092500004 20000925 00004 CE 2000 9 25 20000720SH020 1 20000516 G 2842 C6680501108 TRANSMITTER CESSNA 208 208B 2073701 CE LEFT WING SHORTED E K NONE O OTHER IN INSP/MAINT 1 AL 05 1275N 3494 208B0756 LEFT FUEL QUANTITY INDICATOR INACCURATE AND ERRATIC. REPLACED DEFECTIVE CENTER OUTBOARD FUEL SENDING UNIT. (X) 1 H 7 1 3T A37CE 2000110700003 20001107 00003 CE 2000 11 7 20000720SH021 1 20000613 G 2782 99105863 ACTUATOR CESSNA 208 208B 2073701 CE CABIN CEILING SHEARED E O OTHER F FLT CONT AFFECTED NR NOT REPORTED 1 AL 05 1275N 349 208B0756 STANDBY FLAP MOTOR INOPERATIVE. ACTUATOR SHAFT ROLL PIN SHEARED. JACKSCREW CONTAMINATED WITH METAL PARTICLES, MOTOR INO PERATIVE. UPON REPLACEMENT OF TRANSMISSION ASSY, ALSO DISCOVERED ELECTRICAL PIN IN PRIMARY FLAP MOTOR POWER CONNECTOR P ARTIALLY DISENGAGED CAUSED BY PIN LOCKING TABS NOT EXTENDED. (X) 1 H 7 1 3T A37CE 2000112800016 20001128 00016 NE 2000 11 28 20000720SH022 2 20000516 G 7532 304903802 BLEED VALVE CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE ENGINE FAILED E K NONE W INADEQUATE Q C IN INSP/MAINT 1 AL 05 1275N 321 208B0756 MANUFACTURER RECALLED THIS SPECIFIC COMPRESSOR BLEED VALVE FOR TESTING OF INTERNAL PACKING FOR DEFECTS. BLEED VALVE SER IAL NUMBER FELL OUTSIDE OF ANY AD OR SB. (X) 1 H 7 1 3T 3 T A37CE E4EA 2000111600001 20001116 00001 CE 2000 11 16 20000720SH024 1 20000707 G 2730 187504 CONTROL ARM BEECH 18 C45H 1151018 CE CNTRLCOLUMN ASSY CRACKED H K NONE O OTHER IN INSP/MAINT 1 WP 17 9532Z 7529 AF448 AIRCRAFT SUBJECTED TO HELICOPTER ROTOR WASH WHILE PARKED. ELEVATOR SUBJECTED TO VIOLENT MOVEMENT STOP TO STOP. AD 77-1 9-07 WAS PERFORMED. INSPECTION REVEALED A CRACK IN ELEVATOR CONTROL ARM. CRACK ORIGINATES ON AFT LEFT TAPER PIN HOLE A ND PROCEEDS OFF LEFT SIDE OF CASTING. (X) 1 L 7 2 3R A765 2000111600002 20001116 00002 CE 2000 11 16 20000720SH026 1 20000705 G 2400 W31X104450 CIRCUIT BREAKER CESSNA 414 414A 2075907 CE AVIONICS SYSTEM BURNED OUT D O OTHER O OTHER IN INSP/MAINT 1 WP 13 4573V 414A0300 AFTER TAKEOFF,THERE WAS A SMELL OF SMOKE IN THE COCKPIT. THE SMELL WAS COMING FROM THE AREA OF AVIONICS MASTER BREAKER/ SWITCH. DISCOVERED THE POTTER & BRUMFIELD BREAKER/SWITCH, PN W31-X1000-50, HAD OVERHEATED AND THE BREAKER POINTS HAD WE LDED SHUT. THIS RENDERED THE SWITCH PORTION OF THE BREAKER/SWITCH INOPERATIVE. THIS BREAKER/SWITCH HAD FAILED BEFORE O N THER AIRCRAFT, BUT NEVER IN FLIGHT. THE FAILURES USUALLY OCCURRED ON THE GROUND DURING GROUND OPERATION OR PRE-FLIGHT. THE AVIONICS SYSTEM IS PROTECTED BY A SECOND CIRCUIT BREAKER, PN 7815-15-50, LOCATED IN THE LEFT WING ROOT FWD OF THE BATTERY BOX WHICH WILL TRIP IF THERE IS AN OVERLOAD. (X) 1 L 7 2 3O A7CE 2000112800150 20001128 00150 CE 2000 11 28 20000720SH027 1 20000707 G 2910 551700863 HYDRAULIC LINE CESSNA 501 551 2076605 CE LEAKING B O OTHER K FLUID LOSS IN INSP/MAINT 1 NM 03 242WT 5510066 THE LT MLG PRESSURE LINE RUNNING JUST OVER THE FLIGHT CONTROL CABLES IN THE TAIL CONE SECTION OF THE A/C WAS BEAT DOWN I NTO THE PATH OF ONE OF THE CABLES. AFTER A LIMITED TIME, THE CABLE WORE THROUGH THE HYDAULIC LINE DUMPED THE RESERVOIR INTO THE TAIL CONE. TO PREVENT RECURRENCE OF THIS INCIDENT, SUBMITTER SUGGESTED THE HYDRAULIC LINE SHOULD BE ROUTED BEL OW THE FLIGHT CONTROL CABLES. (X) 1 L 7 2 4F A27CE 2000112800361 20001128 00361 EA 2000 11 28 20000720SH028 2 20000509 G 7414 M3333 IMPULSE COUPLING PIPER PA32 PA32300 7103212 SO LYC O540 IO540K1A5 41532 EA PINS LACK OF LUBE E LABA K NONE O OTHER IN INSP/MAINT 1 AL 05 3957X 500 327640003 RL137854SA OCCURRED UNDER NORMAL WORKING CONDITIONS - LACK OF LUBRICATION IN CHAMBER IS ONE PROBLEM. 1 L 7 1 3O 3 O A3SO 1E4 2000112800362 20001128 00362 CE 2000 11 28 20000720SH029 1 20000623 G 2750 1216346331 FLEX COUPLING BEECH 36 A36 1151604 CE LT FLAP UNSERVICEABLE H O OTHER F FLT CONT AFFECTED CR CRUISE 1 SO 05 1565X 857 E2853 OWNER REPORTED FLAP SPLIT DURING FLIGHT. INSPECTION REVEALED LT FLAP FLEX CABLE DRIVE SPLINE CRIMP TO BE LOOSE WHICH AL LOWED CABLE CORE TO SLIP. LT FLAP DID NOT EXTEND AS MUCH AS RT FLAP. WHEN FLAPS WERE RETRACTED, LT FLAP CONTACTED UPLI MIT SWITCH; THUS, STOPPING FLAP RETRACTION. RT FLAP WAS STILL EXTENDED 15 DEGREES - 25 DEGREES CAUSING SPLIT. THIS APP EARED TO BE A MANUFACTURING DEFECT. SUBMITTER SUGGESTED RAYTHEON ISSUE AN EMERGENCY SB TO REQUIRE FIELD INSPECTIONS OF FLAP DRIVE SYSTEM. (X) 1 L 7 1 3O 3A15 2000112800363 20001128 00363 CE 2000 11 28 20000720SH030 1 20000623 G 2750 99124238EX CONTROL VALVE CESSNA 525 525 2076601 CE FLAP UNIT DEFECTIVE B EBVR O OTHER W INADEQUATE Q C IN INSP/MAINT 1 GL 09 525KA 5250019 ORDERED AND RECEIVED NEW HYDRAULIC FLAP CONTROL VALVE. INSTALLED VALVE AND RAN AIRCRAFT. FOUND FLAPS WOULD ONLY OPERAT E INTERMITTENTLY. CHECKED ALL ELECTRICAL CIRCUITS, ALL CHECKED GOOD. RE-INSTALLED OLD VALVE AND FLAPS OPERATED NORMALL Y. RE-ORDERED A NEW VALVE. (X) 1 L 7 2 4F RT A1WI 2000112800364 20001128 00364 SO 2000 11 28 20000720SH031 1 20000601 G 2910 B-NUT PIPER PA32 PA32R301 7103218 SO RT GEAR LOOSE B O OTHER K FLUID LOSS LD LANDING 1 SO 13 9236V 3213069 GEAR WOULD NOT EXTEND. CIRCUIT BREAKER TRIPPED. RE-SET, BUT NO HELP. GEAR FREE FALL FAILED TO LOCK ALL GEAR DOWN. RI GHT MAIN COLLAPSED UPON LANDING. FOUND B-NUT ON RIGID LINE BELOW HYDRAULIC POWER PACK LOOSE AND LEAKING HYDRAULIC FLUID . GEAR OPERATED NORMAL AFTER FIXING LEAK AND SERVICING RESERVOIR. (RESISTANCE WAS NOTED IN GEAR SYSTEM WHEN RECOVERY F ROM RUNWAY UNTIL EMERGENCY EXTEND RESET). (X) 1 L 7 1 3O A3SO 2000112800365 20001128 00365 GL 2000 11 28 20000720SH032 1 20000604 G 2822 PUMP AMTR 300 SX300 05675EK GL MISINSTALLED G O OTHER O OTHER NR NOT REPORTED 1 NM 11 2H 984 SA2966 AFTER RUNNING LEFT WING TANK DRY, PILOT SWITCHED TO RIGHT WING TANK. ELECTRIC FUEL PUMP FAILED TO PICK UP FUEL AGAIN. INVESTIGATION REVEALED ELECTRIC PUMP HAD BEEN INSTALLED ON FIREWALL INSTEAD OF IN NOSE WHEELWELL AS PLANS INDICATED. 1 L 7 1 3O RT EXPA1L71 2000112800393 20001128 00393 EA 2000 11 28 20000720SH034 2 20000626 G 8530 LW16475KLIO SPRING LYC BEECH 80 65B80 1152812 CE LYC O720 IO720A1B 41546 EA EXHAUST CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 15 530 EXHAUST VALVE SPRING RETAINING CAP BROKE IN HALF AND BURNED EXHAUST VALVE. (X) 1 L 7 2 3O 3 O 3A20 1E15 2000112800395 20001128 00395 SO 2000 11 28 20000720SH036 2 20000628 G 7414 10349276 CAPACITOR CONT BEECH 35 35BEECH 1151502 CE CONT O520 IO520* 17032 SO MAGNETO FAILED B O OTHER R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 GL 03 8 CUSTOMER REPORTED THE RIGHT MAGNETO FAILED. INVESTIGATION REVEALED THE POINTS WERE NOT OPENING. TCM SB 651 DESCRIBES O NE CAUSE FOR THIS TO BE CAPACITOR FAILURE CAUSING POINTS TO ARC, HEAT UP, AND MELT THE NYLON CAM FOLLOWERS. BECAUSE SHO P HAD JUST REPLACED THE CAPACITOR AND SET THE POINTS, SUBMITER BELIEVES THE NEW CAPACITOR FAILED. (X) 1 L 7 1 3O 3 O A777 E5CE 2000112800396 20001128 00396 CE 2000 11 28 20000720SH037 1 20000619 G 5511 STABILIZER CESSNA 150 150J 2071820 CE INBOARD CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 05 1500 15070260 BOTH STABILIZER SPARS FOUND CRACKED IN THE UPPER BEND RADIUS FOR THE FLANGE AT THE INBOARD PAD ABOUT 2 INCHES FROM THE P ADS. THIS AREA IS CONCEALED UNDER STIFFENER 0432001-15 (ALSO CRACKED). THIS WAS DISCOVERED DURING INSPECTION FOR AD 80 -11-04, ALSO SPAR REINFORCMENT, PN 0432001-15, WAS CRACKED. (X) 1 H 7 1 3O 3A19 2001011103993 20010111 03993 2001 1 11 20000720SH038 2 20000626 G 7414 10349276 CAPACITOR CONT OPEN B NQ2R O OTHER W INADEQUATE Q C IN INSP/MAINT 1 WP 05 OPEN CONDITION TO PRIMARY TERMINAL WHICH WOULD CAUSE MAGNETO TO BE ''HOT'' EVEN THOUGH SWITCH IN OFF POSITION. THIS IS A NEW PART ABOUT TO BE INSTALLED DURING OVERHAUL. DATE CODE ON PART IS 99-43. TCM BUL CSB 641 AND AD 94-06-09 SPEAKS T O THIS PROBLEM, BUT THIS ONE IS OUTSIDE THE 93-40 AND 93-42 DATE CODES CALLED OUT IN THE BULLETIN AND AD. (X) 2000112800397 20001128 00397 SO 2000 11 28 20000720SH039 1 20000518 G 3250 8362507 ARM PIPER PA46 PA46350P SO FRONT OP NOSE ST BENT G O OTHER O OTHER LD LANDING 1 SO 17 9250B 4622161 AFTER TOUCHDOWN, PILOT HAD NO NOSE STEERING. AFTER CONTACT WITH DIRT, NOSE STRUT BROKE AT ENGINE MOUNT HARD POINTS AND COLLAPSED. POSSIBLE CAUSE: NOSE STEERING ARM WAS BROKEN. REASON: UNKNOWN. (X) 1 L 7 1 3O RT A25SO 2001013000044 20010130 00044 NE 2001 1 30 20000720SH040 2 20000604 G 7310 1VN02523 MANIFOLD BOLKMS 117 BK117B1 5626012 EU LYC LTS101 LTS101650B1 41560 NE ENGINE FUEL MALFUNCTIONED A R7MA K NONE O OTHER IN INSP/MAINT 1 NM 07 5194C 593 7169 LE45382EA FUEL MANIFOLD ASSY CAUSES ENGINE TO RUN HOT. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U 3 U H13EU E5NE 2001013000045 20010130 00045 EU 2001 1 30 20000721SH001 1 20000202 G 6210 117150071 BLADE BOLKMS 117 BK117A3 5626015 EU MAIN ROTOR DEBONDED A R7MA K NONE O OTHER IN INSP/MAINT 1 nm 07 163BK 7063 LEADING EDGE SKIN UNDER BONDED PV-FILM IN NOSE AREA TO APPROXIMATELY BLADE STA 922 (SECTION 1) IS DEBONDING ON TRAILING EDGE, BOTH UPPER/LOWER SURFACES. (X) 1 G 7 2 3U H13EU 2001013000046 20010130 00046 EU 2001 1 30 20000721SH002 1 20000202 G 6210 117150071 BLADE BOLKMS 117 BK117A3 5626015 EU MAIN ROTOR DEBONDED A R7MA K NONE O OTHER IN INSP/MAINT 1 NM 07 163BK 7063 LEADING EDGE SKIN UNDER BONDED PV-FILM IN NOSE AREA TO APPROXIMATELY BLADE STA 922 (SECTION 1) IS DEBONDING ON TRAILING EDGE, BOTH UPPER/LOWER SURFACES. (X) 1 G 7 2 3U H13EU 2001013000047 20010130 00047 EU 2001 1 30 20000721SH003 1 20000202 G 6210 117150071 BLADE BOLKMS 117 BK117A3 5626015 EU MAIN ROTOR DEBONDED A R7MA K NONE O OTHER IN INSP/MAINT 1 NM 07 163BK 7063 LEADING EDGE SKIN UNDER BONDED PV-FILM IN NOSE AREA TO APPROXIMATELY BLADE STA 922 (SECTION 1) IS DEBONDING ON TRAILING EDGE, BOTH UPPER/LOWER SURFACES. (X) 1 G 7 2 3U H13EU 2001013000048 20010130 00048 NE 2001 1 30 20000721SH004 2 20000602 G 7310 430167601 MANIFOLD BOLKMS 117 BK117A3 5626015 EU LYC LTS101 LTS101650B1 41560 NE ENGINE FUEL MALFUNCTIONED A R7MA O OTHER O OTHER NR NOT REPORTED 1 NM 07 163BK 573 7063 LE45332EA FUEL MANIFOLD ASSY CAUSES ENGINE TO RUN HOT. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U 3 U H13EU E5NE 2001013000049 20010130 00049 NE 2001 1 30 20000721SH005 2 20000518 G 7310 430163701 MANIFOLD BOLKMS 117 BK117A3 5626015 EU LYC LTS101 LTS101650B1 41560 NE ENGINE FUEL MALFUNCTIONED A R7MA O OTHER O OTHER NR NOT REPORTED 1 NM 07 420MB 119 7077 LE45218EA FUEL MANIFOLD ASSEMBLY CAUSES ENGINE TO RUN HOT. (X) 1 G 7 2 3U 3 U H13EU E5NE 2001013000050 20010130 00050 NE 2001 1 30 20000721SH006 2 20000327 G 7310 430167601 MANIFOLD BOLKMS 117 BK117B1 5626012 EU LYC LTS101 LTS101750B1 41560 NE ENGINE FUEL MALFUNCTIONED A R7MA O OTHER O OTHER NR NOT REPORTED 1 NM 07 10UM 555 7231 LE45806EFA FUEL MANIFOLD ASSY CAUSES ENGINE TO RUN HOT. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U 3 U H13EU E5NE10 2001013000051 20010130 00051 2001 1 30 20000721SH007 4 20000620 G 3457 0110028000 GPS SNIAS 350 AS350B3 8680954 EU COCKPIT MALFUNCTIONED A R7MA O OTHER O OTHER NR NOT REPORTED 1 NM 07 392LG 3252 UNIT INOPERATIVE. CRSR WILL NOT SCROLL PAGES. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001020100005 20010201 00005 2001 2 1 20000721SH009 4 20000525 G 3160 B19030MB01 DISPLAY SNIAS 350 AS350B3 8680954 EU COCKPIT INTERMITTENT A R7MA O OTHER O OTHER NR NOT REPORTED 1 NM 07 104LN 804 3134 VEMD UNIT INOPERATIVE. T4.5 SPLIT BETWEEN FADE AND VEMD CAUSES LFI PAGE TO GO OFF-LINE. INTERMITTENT 20 TO 80 DEGREES. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001013100005 20010131 00005 NE 2001 1 31 20000721SH010 2 20000407 G 7310 430167601 MANIFOLD BOLKMS 117 BK117A1 5626010 EU LYC LTS101 LTS101650B1 41560 NE ENGINE FUEL LEAKING A R7MA K NONE K FLUID LOSS IN INSP/MAINT 1 NM 07 128HH 569 7036 LE4515EA FUEL MANIFOLD ASSY LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED UNIT. (X) 1 G 7 2 3U 3 U H13EU E5NE 2001020700195 20010207 00195 SO 2001 2 7 20000721SH011 1 20000713 G 3242 1331317 STATOR BFGOODRICH EMB 120 EMB120 3260201 SO BRAKE ASSY CRACKED B XC4R K NONE O OTHER IN INSP/MAINT 1 SO 19 1271 1561A BRAKE ASSY, PN 2-1661, FAILED PREMATURELY. NR 1 AND NR 2 STATORS CRACKED AT RELIEF HOLES. HEAT STACK WARPED AND UNEVEN WEAR. SUBMITTER STATED THIS IS A CONTINUAL DISCREPANCY. NOTE: OEM PARTS INSTALLED IN BRAKE ASSY AND THE MOST RECENT BRAKE CONFIGURATION, PN 2-1661. (X) 2 L 7 2 4T RT A31SO 2001022100079 20010221 00079 SO 2001 2 21 20000721SH012 1 20000713 G 3242 RFS2010 STATOR BFGOODRICH EMB 120 EMB120 3260201 SO BRAKE ASSY CRACKED B XC4R K NONE O OTHER IN INSP/MAINT 1 SO 19 1650 1246A BRAKE ASSY, PN 2-1584-T, FAILED PREMATURELY. NR 1 AND NR 2 STATORS CRACKED AT RELIEF HOLES. HEAT STACK WARPED AND UNEV EN WEAR. SUBMITTER STATED THIS IS A CONTINUAL DISCREPANCY. NOTE: RAPCO FLEET SUPPORT PARTS INSTALLED TO BRAKE ASSY. (X) 2 L 7 2 4T RT A31SO 2001020600106 20010206 00106 SW 2001 2 6 20000721SH013 1 20000526 G 2622 RTA600 EXTINGUISHER BELL 407 407 SW CABIN LEAKING B FKFR O OTHER K FLUID LOSS NR NOT REPORTED 1 SO 03 24156 53415 FIRE EXTINGUISHER, BELL P/N 40000, TRADE NAME ''RIGHT-OUT'' TM IS STANDARD EQUIPMENT FROM THE BELL FACTORY. THE NEW OWN ER PICKED UP NEW HELICOPTER AT THE COMPLETION CENTER. ON THE FLIGHT TO HOME BASE, THE FIRE EXTINGUISER SLOWLY DISCHARG ED IN-FLIGHT. ESTIMATE AIRCRAFT TT, 15.0 HOURS. (X) 1 G 7 1 3U O H2SW 2001020600107 20010206 00107 SW 2001 2 6 20000721SH014 1 20000721 G 2622 RTA600 EXTINGUISHER BELL 407 407 SW CABIN LEAKING B FKFR O OTHER K FLUID LOSS NR NOT REPORTED 1 SO 03 98JT 53286 FIRE EXTINGUISHER, BELL PN 40000, TRADE NAME ''RIGHT-OUT'' TM, IS STANDARD EQUIPMENT FROM THE BELL FACTORY. SHIP CAME I N FOR AN ANNUAL INSPECTION. THE FIRE EXTINGUISHER WEIGHT WAS FOUND 56 GRAMS LIGHT AND UNAIRWORTHY. (X) 1 G 7 1 3U O H2SW 2000110600131 20001106 00131 2000 11 6 20000721SH015 4 20000705 G 6113 D6199 SPINNER MOONEY M20 M20M 5870222 SW MCAULY 3D32C B3D32C417 GL CRACKED B FCPR K NONE O OTHER IN INSP/MAINT 1 NM 09 10KG 473 270249 980209 FOUND SPINNER BULKHEAD SEVERELY CRACKED DURING ROUTINE MAINTENANCE. SUBMITTER STATED THIS IS THE SECOND M20M WITH LESS THAN 500 HOURS THAT THE BULKHEAD HAS FAILED. SPINNER BULKHEAD HAS CRACKS AT ATTACHEMNT HOLES AND AT FIRST BEND RADIUS. SEVERAL PIECES MISSING. (X) 1 L 7 1 3O RT 2A3 5 C P58GL 2000110600132 20001106 00132 EA 2000 11 6 20000721SH016 2 20000622 G 8530 73555 PUSHROD PIPER PA32 PA32300 7103212 SO LYC O540 IO540K1A5 41532 EA NR 4 CYLINDER FAILED D K NONE O OTHER IN INSP/MAINT 1 EA 21 120DM 327340122 RL930748 ENGINE USING EXCESSIVE OIL AFTER RECENT OVERHAUL (200 HRS). CYL REMOVED FOR RE-OVERHAUL. UPON RE-INSTALL OF NEWLY O/H CYLINDERS, DISCOVERED NR 4 CYL PUSHROD WAS MODIFIED BY APPARENT ATTEMPT TO SHORTEN LENGTH BY CUTTING AND DOWELING ROD O N ONE END. ROD ESTIMATED TO HAVE AT LEAST 200 HRS TIS. ROD STARTING TO FAIL SHOWING MUSHROOMING. TIP COULD BE PULLED APART BY HAND PRESSURE. NOTE: PN 73555 IS SUPERCEDED TO PN 15F21362-21. THIS IS WRONG P/N FOR ENG MODEL. THE CORRECT PUSHROD PN IS 73455 S/S TO 15F19957-55. (X) 1 L 7 1 3O 3 O A3SO 1E4 2000110600133 20001106 00133 2000 11 6 20000721SH017 4 20000427 G 2562 AK450 ELT CESSNA 180 180H 2072618 CE INOPERATIVE D K NONE O OTHER IN INSP/MAINT 1 SW 03 180PR 18052186 DURING ANNUAL INSPECTION, CHECKED ELT FOR OPERATION AND CONDITION. ELT DID NOT OPERATE. EITHER INERTIA SWITCH OR MANUA L SWITCH. CHANGED BATTERY, AS SUGGESTED BY MFG. NO CHANGE. SENT UNIT TO MFG FOR REPLACEMENT. PART TT: 18 MONTHS. (X) 1 H 7 1 3O 5A6 2000110600134 20001106 00134 SO 2000 11 6 20000721SH018 2 20000609 G 8530 642594CP CYLINDER HEAD BEECH 33 F33A 1151425 CE CONT O520 IO520BA 17032 SO NR 3 POSITION CRACKED B JZRR K NONE O OTHER IN INSP/MAINT 1 EA 07 17825 1698 CE711 562770 CYLINDER NR 3 CRACKED FROM BOTTOM SPARK PLUG HOLE THROUGH EXHAUST PORT EXTENDING INTO EXTERNAL FINDS. FOUND DURING COM PRESSION CHECK FOR ANNUAL INSPECTION. CHANNEL CHROME CYLINDER, EXACT HOURS ON CYLINDER UNKNOWN (CHROME PLATED 9/86). SU BMITTER RECOMMENDED LIFE LIMIT ON CYLINDER HEAD SHOULD NOT EXCEED 1,800 HOURS. (X) 1 L 7 1 3O 3 O 3A15 E5CE 2000110600135 20001106 00135 WP 2000 11 6 20000721SH019 1 20000711 G 3260 820014196 LIGHT CVAC CVAC 440 440 2422902 WP ANNUNCIATOR PNL OPEN C OGCB O OTHER O OTHER AP APPROACH 1 GL 23 161FL 15000 430 CREW EN ROUTE FROM MMCS TO ELP. CREW LOWERED LANDING GEAR AND DID NOT RECEIVE A DOWN/LOCKED LIGHT FOR LT MAIN GEAR (INT RANSIT). LIGHT WAS NOT ILLUMINATED NOR DID THEY RECEIVE GEAR HORN. OPTED TO MAKE FLYBY. TOWER WOULD NOT CONFIRM GEAR DOWN. CREW PERFORMED HIGH ''''G'''' MANEUVER, DID NOT RECEIVE GEAR DOWN LOCKED INDICATION. CREW MADE FLYBY AND TOWER T HEN INDICATED GEAR APPEARED TO BE DOWN AND LOCKED. CREW LANDED PLANE WITHOUT INCIDENT. INSP OF ACFT REVEALED LIGHT ASS Y WAS DEFECTIVE. REPLACED LIGHT. ACFT RETURNED TO SERVICE. (X) 2 L 7 2 4R 6A6 2000110600136 20001106 00136 CE 2000 11 6 20000721SH020 1 20000612 G 3246 3680025 WHEEL RAYTHN BEECH 95 95B55 1152729 CE NOSE GEAR CRACKED C O OTHER O OTHER IN INSP/MAINT 1 GL 23 216RW TC1956 A CRACK APPEARED ON NOSE WHEEL 3 INCHES TO 4 INCHES LONG ON THE OUTER HALF OF THE WHEEL. AS THE WHEEL IS INSTALLED, THE CRACK IS ON THE HORIZONTAL SURFACE BETWEEN THE HUB AND THE WHEEL FLANGE. THE CRACK WAS DISCOVERED BEFORE FAILURE OCCUR RED. THE WHEEL WAS REPLACED WITH CLEVELAND ASSY P/N 40-87D. 1 L 7 2 3O RT 3A16 2000110600140 20001106 00140 EU 2000 11 6 20000721SH021 1 20000622 G 5330 SKIN AMD FALC50 FALCON900 2700160 EU FUSELAGE CORRODED B UO2R K NONE O OTHER IN INSP/MAINT 1 GL 19 26LB2 51 CORROSION OF FUSELAGE SKIN AT TOWER FRAME 10 UNDER FORWARD END OF PANEL 130A. THE DOMED NUTPLATES ARE RETAINING WATER. THIS PANEL IS REMOVED ONLY AT 2C INSPECTION. SUBMITTER RECOMMENDED REMOVAL AT EACH C-INSPECTION TO INSPECT FOR CORROSI ON. ACTT: 4,868.6 HRS. (X) 2 L 7 3 4F RT A46EU 2000110600142 20001106 00142 EU 2000 11 6 20000721SH022 1 20000626 G 5330 SKIN AMD FALC50 FALCON900 2700160 EU FUSE CORRODED B UO2R K NONE O OTHER IN INSP/MAINT 1 GL 19 26LB 51 AIRCRAFT FUSELAGE SKIN AT APU EXHAUST BETWEEN FRAMES 33 AND 34 CORRODED. DAMAGED AREA WAS REMOVED AND SKIN REPLACEMENT REPAIR DONE. (X) 2 L 7 3 4F RT A46EU 2000110600144 20001106 00144 NE 2000 11 6 20000721SH023 2 20000531 G 7310 37E501248P101 MANIFOLD LEAR 25 25B 5170511 CE GE CJ610 CJ6106 30006 NE MAIN FITTING LEAKING B O OTHER K A FLUID LOSS FLAME/FIRE NR NOT REPORTED 1 SW 99 239CA 25B149 251332A FUEL MANIFOLD STARTED TO LEAK AT THE SILVER SOLDER JOINT BY THE LARGE B-NUT. FUEL CAUGHT FIRE AND BURNED ENGINE COWL ON TAKEOFF. (X) 2 L 7 2 4J 4 J A10CE 1E16 2000110600145 20001106 00145 SO 2000 11 6 20000721SH024 1 20000623 G 3230 405452 BOLT PIPER PA23 PA23250 7102308 SO LANDING GEAR SHEARED G O OTHER O OTHER LD LANDING 1 SO 17 35LK 277654059 AFTER LANDING, A BOLT IN THE LEFT LINK (PIPER PARTS CATALOG PG 283, ITEM 52, PARA 405, 452) SHEARED COLLAPSING THE GEAR AND WHEEL ASSY AFT AND RESTING TIRE ON THE FLAP. OWNER OPERATOR RECOMMENDED AT LEAST A 1,000 HOUR INSPECTION. (X) 1 L 7 2 3O 1A10 2001020600115 20010206 00115 SW 2001 2 6 20000721SH028 1 20000705 G 2913 8505261 GEAR BELL 206 206B3 1181506 SW HYD PUMP WORN B K NONE O OTHER IN INSP/MAINT 1 CE 03 50Q 433 BDO113 3419 INTERNAL SPLINES ON HYDRAULIC PUMP WORN EXCESSIVELY CAUSING HYDRAULIC PUMP TO START TO FAIL. PUMP OVERHAULED 432.8 HOUR S PRIOR TO FAILURE. REASON FOR FAST SPLINE WEAR UNKNOWN. (X) 1 G 7 1 3U H2SW 2001020600116 20010206 00116 NE 2001 2 6 20000721SH029 2 20000610 G 8550 ENGINE BOLKMS 117 BK117A3 5626015 EU LYC LTS101 LTS101650B1 41560 NE NR 2 MAKING METAL B TI1R K NONE J WARNING INDICATION IN INSP/MAINT 1 SW 05 527MB 6473 107 7103 LE45157 INSPECTED NR 2 ENGINE CHIP DETECTOR AND FOUND NO SIGN OF CHIPS OR DEBRIS. CLEARED CHIP PLUG AND REINSERTED INTO HOUSING . PILOT PERFORMED A GROUND RUN OF THE NR 2 ENGINE AND THE CHIP LIGHT DID NOT ILLUMINATE. PILOT SHUT ENGINE DOWN, RE-CH ECKED CHIP PLUG AND FOUND NO EVIDENCE OF CHIPS. ADJUSTED NR 2 ENGINE FLOW FENCE ACTUATOR AND PERFORMED AN OPERATIONAL C HECK FLIGHT TO VERIFY ENGINE TORQUE INDICATIONS. TORQUE INDICATIONS WERE DEEMED TO BE WITHIN MBB LIMITS AND ACFT RELEAS ED FOR RETURNED TO SERVICE. (X) 1 G 7 2 3U 3 U H13EU E5NE 2000110600147 20001106 00147 CE 2000 11 6 20000721SH031 1 20000630 G 2730 2213063203 BRACKET CESSNA 182 182S 2072701 CE ELEV CABLE PULLE INADEQUATE B FCPR K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 09 6870L 18280097 ****PART LOC: ELEV CABLE PULLEY BRACKET*****WHILE TRYING TO C/W CESSNA MANDATORY SB 00-27-01, REPLACEMENT OF ELEVATOR C ONTROL CABLE SUPPORT BRACKET, FOUND NEW BRACKET PN 2213063-203 WAS IMPROPERLY MANUFACTURED AND WILL NOT PERFORM ITS INTE NDED FUNCTION. (X) 1 H 7 1 3O NT 3A13 2000110600148 20001106 00148 CE 2000 11 6 20000721SH032 1 20000605 G 3230 51420025 DRAG BRACE CESSNA 402 402C 207590R CE NOSE GEAR CRACKED D O OTHER O OTHER IN INSP/MAINT 1 NE 01 69SC 1737 402C0041 ON PRE-FLIGHT, CREW FOUND SUSPECTED CRACK AT DRAG BRACE TO ACTUATOR ATTACH LUG AREA. MAINTENANCE PERFORMED NDT. FOUND TO BE CRACKED AT SUSPECTED AREA. REMOVED AND REPLACED DRAG BRACE AND ROD END (PN ADNE4JW) WITH NEW AND RETURNED AIRCRAF T TO SERVICE. (X) 1 L 7 2 3O A7CE 2000110600149 20001106 00149 EA 2000 11 6 20000721SH035 2 20000630 G 8530 75413 PISTON PIPER PA28 PA28140 7102802 SO LYC O320 O320E2A 41508 EA NR 1 FAILED G A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CR CRUISE 1 NM 02 6887W 1600 2821043 L1539727A THE AIRCRAFT WAS AT 6,500 FEET MSL, ABOUT 30 MINUTES INTO A FLIGHT. (VFR) RPM STARTED TO DROP. THERE WAS NO WARNING O R UNUSUAL SOUND. AIRCRAFT WAS DESTROYED DURING EMERGENCY LANDING ON A ROAD. (X) 1 L 7 1 3O 3 O 2A13 E274 2000110600150 20001106 00150 EA 2000 11 6 20000721SH036 2 20000626 G 7200 ENGINE BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA MAKING METAL D A UNSCHED LANDING O OTHER CR CRUISE 1 EA 05 79GA BB556 PCE81261 PILOT EXPERIENCED OIL PRESSURE AND TORQUE FLUCTUATION. THIS ENGINE SHUT DOWN IN-FLIGHT. INSPECTION OF OIL FILTER SHOWE D METAL CONTAMINATION. THIS ENGINE HAS BEEN OPERATED FOR 714.9 HOURS ON THE MORE PROGRAM. THE EXACT REASON FOR THIS FA ILURE IS NOT KNOWN AT THIS TIME. (X) 1 L 7 2 4T 4 T A24CE E4EA 2000110600155 20001106 00155 SW 2000 11 6 20000721SH037 1 20000706 G 2900 70053H000A100A HOSE BELL 206 206L3 1182108 SW HYD PUMP LEAKING B LX5R A UNSCHED LANDING K FLUID LOSS IN INSP/MAINT 1 GL 19 721LL 51164 HOSE LEAKED, FLUID EMPTIED. LANDED AT BLOOMINGTON, ILL AIRPORT. (X) 1 G 7 1 3U H2SW 2000110600156 20001106 00156 CE 2000 11 6 20000721SH038 1 20000707 G 3710 442CW12 PUMP BEECH 58 58 1152740 CE FAILED D O OTHER O OTHER CR CRUISE 1 EA 25 7353R 222 TH486 VACUUM PUMP FAILED UNDER NORMAL ENGINE OPERATING CONDITIONS. THE INTERNAL DRIVE COUPLING AND ASSOCIATED INTERNAL SPLINE ASSY SEPARATED FROM THE ROTOR. (NOT TO BE CONFUSED WITH THE NORMAL BREAK AWAY FLEXIBLE COUPLING.) (X) 1 L 7 2 3O 3A16 2001020600118 20010206 00118 SW 2001 2 6 20000721SH039 1 20000721 G 2622 RTA600 EXTINGUISHER BELL 407 407 SW CABIN LEAKING B FKFR O OTHER K FLUID LOSS NR NOT REPORTED 1 SO 03 888DJ 53408 FIRE EXTINGUISHER, BELL PN 40000, TRADE NAME ''RIGHT-OUT''TM IS STANDARD EQUIPMENT FROM THE BELL FACTORY. THIS ONE LEAK ED DOWN ON A FLIGHT TO THE REPAIR STATION. AIRCRAFT TT 38.8 HOURS. THE HELICOPTER WAS DELIVERED IN MAY, 2000, AT 16.0 HRS. HAPPENED DURING NICE HOT SUMMER WEATHER. (X) 1 G 7 1 3U O H2SW 2000110600158 20001106 00158 NE 2000 11 6 20000721SH040 2 20000519 G 7310 S2495880000520 HOSE CESSNA 208 208B 2073701 CE PWA PT6 PT6A114 52043 NE LEAKING A HSYA A UNSCHED LANDING K FLUID LOSS CL CLIMB 1 NM 05 903FE 208B0003 HNL - FLT 8666 - ON CLIMB-OUT, PILOT REPORTED ''FUEL FUMES IN COCKPIT''. AIR TURNBACK TO HNL. FUEL ACCUMULATION IN ENG INE COWL DUE TO LOOSE FUEL LINE CONNECTION AT FIREWALL FUEL FILTER. TIGHTENED THE NOSE FITTING, FLUSHED COWLING WITH SO AP AND WATER. PERFORMED GROUND RUN-UP LEAK CHECK. AIRCRAFT RETURNED TO SERVICE. (X) 1 H 7 1 3T 3 T A37CE E4EA 2000110600186 20001106 00186 CE 2000 11 6 20000724SH004 1 20000624 G 2720 CONTROL CABLE BEECH 36 A36 1151604 CE UNDER AFT FLRBD CHAFED B K NONE O OTHER IN INSP/MAINT 1 EA 23 17EA 465 E3092 DURING ANNUAL INSPECTION, FOUND LT RUDDER CABLE RUBBING ON EDGE OF HOLE WHERE IT PASSES THROUGH BULKHEAD UNDER AFT FLOOR BOARDS. NO DAMAGE TO CABLE. APPEARS TO RUB ONLY WHEN RUDDER IS FULLY DEFLECTED TO EITHER SIDE. SUBMITTER SUGGESTED IN SPECTION OF ALL CABLES WHERE THEY PASS THROUGH HOLES. (X) 1 L 7 1 3O 3A15 2000110600187 20001106 00187 EA 2000 11 6 20000724SH005 2 20000705 G 8530 VALVE CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA EXHAUST SEIZED G O OTHER O OTHER IN INSP/MAINT 1 NM 04 733FF 5635 1200 17268256 L31676T NR 1 CYLINDER EXHAUST VALVE SEIZED IN GUIDE, DESTROYED PISTON. RESULTANT OIL SYSTEM CONTAMINATION HUNG NR 2 CYLINDER IN TAKE LIFTER, BROKE CONNECTIN ROD, AND FAILED CASE. LYC MANDITORY SB NR 388B DATED MAY 13, 1992, ADDRESSES SCHEDULED VAL VE TO GUIDE CLEARANCE INSPECTIONS. C/W THIS INSPECTION MAY PRECLUDE POTENTIAL SIMILAR INCIDENTS. (X) 1 H 7 1 3O 3 O NT 3A12 E274 2000110600188 20001106 00188 SO 2000 11 6 20000724SH007 1 20000714 G 2750 486631 SHAFT DUKES PIPER PA31 PA31350 7103110 SO CABLE END FAILED I FWRA O OTHER O OTHER LD LANDING 1 AL 01 100GW 210 317305046 FLT 178 - AFTER LANDING, PILOT RETRACTED FLAPS. RT FLAP CAME UP, LT DID NOT. A FAILURE OF THE LT FLAP FLEX SHAFT, PN 486-631, THRUST OR RETAINING WASHER AT TRANSMISSION END ALLOWED DRIVE END OF CABLE TO PULL OUT OF TRANSMISSION INSIDE CA BLE HOUSING CAUSING TRANSMISSION NOT TO ACTUATE AND THE LT FLAP NOT TO RETRACT. SPLIT FLAP PROTECTION SYS FAILED DUE TO A FAILURE OF THE TIME DELAY RELAY ALLOWING A 40-DEGREE SPLIT CONDITION. REPLACED LT FLAP FLEX SHAFT. REPLACED TIME DE LAY RELAY WITH SERVICABLE UNIT. MOTOR REPLACED WITH OVERHAULED UNIT. (X) 1 L 7 2 3O A20SO 2001020600119 20010206 00119 NE 2001 2 6 20000724SH008 1 20000710 G 2435 200SGL115QZ STARTER GEN SKRSKY S76 S76C 8143008 NE ENGINE DAMAGED B EGRR O OTHER O OTHER NR NOT REPORTED 1 EA 17 165ML 813 760471 COOLING FANS ON BOTH UNITS ARE LOOSE. (X) 1 G 7 2 3U NC H1NE 2001020600120 20010206 00120 NE 2001 2 6 20000724SH009 1 20000710 G 2435 2000SGL115QZ STARTER GEN SKRSKY S76 S76C 8143008 NE ENGINE DAMAGED B EGRR O OTHER O OTHER NR NOT REPORTED 1 EA 17 165ML 813 760471 COOLING FANS ON BOTH UNITS ARE LOOSE. (X) 1 G 7 2 3U NC H1NE 2000110600190 20001106 00190 GL 2000 11 6 20000724SH010 3 20000707 G 6114 PROPELLER HARTZL PIPER PA36 PA36300 7103612 SO HARTZL HCC2Y HCC2YK1 GL HUB CRACKED B ME4R K NONE O OTHER IN INSP/MAINT 1 SO 19 CCCFR 542 7760020 CH30810A DURING PROPELLER OVERHAUL, HUB, PN D-22-1-17, PROP ASSY, SN CH30810A, FACTORY HUB, PN A20277A, WAS DISCOVERED CRACKED. CRACK IS LOCATED IN BOTTOM HUB HALF, NR 2 BLADE SOCKET, T/E SIDE, CRACKED FROM INSIDE TO OUTSIDE ABOUT 3.5 INCHES AROUND BULKHEAD HUB HALF BOLT HOLE AND OUTER HUB HALF BOLT HOLE. CRACK DOES NOT GO THROUGH BOLT HOLES, CRACK STOPS INBD OF OU TER HUB HALF BOLT HOLE. NOTE: CRACK IS VISIBLE WITHOUT USE OF 10X GLASS. HUB FALLS OUTSIDE S/N RANGE OF AD NOTE 90-02 -23. PROP O/H WITH REPLACEMENT HUB AND RETURNED TO SERVICE 1-12-98. (X) 1 L 7 1 3O A10SO 5 C P920 2000110900001 20001109 00001 CE 2000 11 9 20000724SH011 1 20000630 G 5280 24130832 DOOR CESSNA 172 172RG 2072438 CE NOSE GEAR FAILED H O OTHER O OTHER LD LANDING 1 GL 15 6313R 172RG0161 DURING ATTEMPT OF EXTENSION OF LANDING GEAR, MLG EXTENDED NORMALLY, NLG WOULD NOT EXTEND. REPEATED ATTEMPTS WERE MADE T O EXTEND NOSE GEAR WITH NO SUCCESS. ACFT MADE SUCCESSFUL GEAR UP LANDING IN GRASS. UPON LIFTING ACFT TO EXTEND GEAR, F OUND RT NOSE GEAR DOOR OUTER SKIN WRINKLED AND DISTORTED. PRIED SKIN ON DOOR AWAY FROM AIRFRAME SKIN AND NOSE GEAR FELL OUT OF WELL TO A DOWN AND LOCKED POSITION. INVEST FOUND SPOT WELDS THAT HOLD INNER AND OUTER SKIN TOGETHER ON NOSE GEA R DOOR HAD FAILED CAUSING DOOR SKIN TO BIND ON GEARWELL SKIN. THIS INTERFERENCE WOULD NOT ALLOW GEAR TO EXTEND. (X) 1 H 7 1 3O 3A17 2000080100138 20000801 00138 SO 2000 8 1 20000724SH014 1 20000615 G 3060 BOOT PIPER PA34 PA34220T 7103420 SO MCAULY 3AF34C 3AF34C* GL PROP DE-ICE SEVERED D IPMA K NONE O OTHER IN INSP/MAINT 1 WP 11 224BD 348133186 FOUND ALL 3 DEICE BOOT LEADS SEVERED AT CONNECTOR MOUNT BRACKET. DETERMINED PROPELLER OVERHAUL SHOP INSTALLED INCORRECT LY. RECOMMEND INSTALLATION PROCEDURES OUTLINED IN PIPER MM AND BFG SB 3-84070 DATED OCT 1989 FOR PROPER BOOT INSTALLATI ON. SUBMITTER STATED THIS HAS BEEN A REPETITIVE PROBLEM. (X) 1 L 7 2 3O A7SO 5 C P22EA 2000121800001 20001218 00001 GL 2000 12 18 20000724SH015 1 20000628 G 3222 NG01 STRUT AMTR EUROPA XSTRIGEAR 05607JV GL WELDMENTS FAILED H O OTHER O OTHER LD LANDING 1 SO 15 912EA EA003XS NOSE WHEEL FELL FROM AIRCRAFT DURING TOUCH AND GO''S. AIRCRAFT LANDED ON REMAINDER OF NOSE STRUT. INVESTIGATION SHOWS THAT WELD POINTS ON NOSE LANDING GEAR ASSY ARE POSSIBLY DEFECTIVE. ALL WELD POINTS HAD EITHER CRACKED OR BROKEN ENTIREL Y. LANDINGS, 45. (X) 1 L 7 1 3O NC EXPA1L71 2000073100210 20000731 00210 SO 2000 7 31 20000724SH016 1 20000605 G 3230 2108303 HANDLE PIPER PIPER PA24 PA24260 7102406 SO EMER LANDING GR WORN B AW4R K NONE O OTHER IN INSP/MAINT 1 WP 11 9070P 244538 WHILE PERFORMING EMERG LANDING GEAR EXTENSION CHK DURING ANNUAL INSP, FOUND EMERG RELEASE MECH WOULD NOT DISENGAGE L/G FROM TRANSMISSION ASSY WHEN FLOORBOARDS AND RUGS WERE INSTALLED. THIS PREVENTED LANDING GEAR FROM BEING EXTENDED USING MANUAL/EMERG MODE. RELEASE LANDING GEAR/ARM PN 21083-03 WOULD HIT ON FORWARD EDGE OF ACCESS CUT-OUT IN CABIN FLOORBOARD , PN 22720-00. RELEASE MECH WOULD FUNCTION NORMALLY WITH FLOORBOARD REMOVED. INSP REVEALED EXCESSIVE WEAR AT PIVOT POI NTS FOR P/N 21083-03 RELEASE HANDLE ALLOWING EXCESS PLAY AND LOST MOTION IN RELEASE MECH. THIS REQUIRED RELEASE HANDLE TO HAVE TO BE MOVED FURTHER FWD TO RELEASE LANDING GEAR WITH FLOORBOARD IN PLACE, HANDLE TRAVEL WAS RESTRICTED. 1 L 7 1 3O 1A15 2000073100211 20000731 00211 SO 2000 7 31 20000724SH017 1 20000713 G 2820 FUEL LINE PIPER PA22 PA22150 7102210 SO WING DETERIORATED G K NONE O OTHER IN INSP/MAINT 1 CE 01 5785D 224461 A MECHANIC PERFORMING ANNUAL INSP, REPORTED THE FUEL SYSTEM WOULD NOT FLOW FOR THE FUEL STRAINER TEST AND CLEANING. T/ S FUEL SYS, FOUND BOTH RUBBER FUEL LINES IN BOTH WINGS WHERE THE TANK OUTLET FITTING IS CONNECTED TO THE FUSELAGE ALUMIN UM FUEL LINE HAD DETERIORATED. MECH REMOVED BOTH RUBBER HOSES AND FOUND INTERIOR RUBBER HAD COLLAPSED COMPLETELY STOPPI NG ALL FUEL FLOW. THE MARKING ON BOTH HOSES SHOWED MIL-H-6000 MFG DATE OF 3Q72. ALSO, ACFT HAS BEEN OPERATED UNDER AN STC FOR AUTOFUEL FOR MANY YEARS AND HAD SET IDLE IN HANGAR FOR 2 YRS. IT WAS MECHANIC''S OPINION THAT SOME ADDITIVE IN AUTOFUEL HAD SOFTENED INNER RUBBER LINING ALLOWING IT TO COLLAPSE AND SEAL LINE. 1 H 7 1 3O 1A6 2000073100212 20000731 00212 CE 2000 7 31 20000724SH018 1 20000616 G 2841 GAUGE CESSNA 182 182Q 2072732 CE INTERIOR FAILED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 11 PILOT REPORTED RT FUEL GAUGE STUCK ON APPROX ONE-THIRD FULL, NO MATTER WHAT ACTUAL LEVEL WAS. REMOVED GAUGE AND FOUND P IECE OF FOAM INSULATION THAT IS GLUED TO UNDERSIDE OF GLARE SHIELD HAD BECOME LODGED AROUND NEEDLE, PREVENTING IT FROM M OVING. THIS INSULATION WAS FALLING APART AND COVERING COOLING HOLES IN AVIONICS, ETC. 1 H 7 1 3O NT 3A13 2000073100213 20000731 00213 CE 2000 7 31 20000724SH019 1 20000714 G 7820 075016189 MUFFLER CESSNA 185 A185F 2072821 CE OUTLET PIPE SEPARATED G A UNSCHED LANDING O OTHER TO TAKEOFF 1 AL 03 71R 18503942 MUFFLER OUTLET PIPE FELL OFF AFTER TAKEOFF. AIRCRAFT RETURNED. MUFFLER AND SHROUD WERE REPLACED. AIRCRAFT RELEASED TO SERVICE. (X) 1 H 7 1 3O 3A24 2000073100214 20000731 00214 EA 2000 7 31 20000724SH020 1 20000706 G 5540 RCM334TC10Z HINGE MS2124254K WACO YMF YMF 9600412 EA RUDDER BROKEN H K NONE O OTHER IN INSP/MAINT 1 NE 01 90B 276 F5033 FOUND ON ANNUAL INSPECTION, LOWER RUDDER HINGE BROKEN. CAUSE UNKNOWN. PART TT: 275.9 HOURS. (X) 1 Q 7 1 3R ATC542 2000073100215 20000731 00215 CE 2000 7 31 20000724SH021 1 20000606 G 3250 1243405200 SHAFT CESSNA 210 210C 2073412 CE NOSE GEAR STRUT BROKEN H O OTHER O OTHER LD LANDING 1 EA 23 3681Y 2634 21058181 DURING LANDING, NOSE GEAR BEGAN TO SHAKE AND FORK ASSY BROKE CAUSING A PROP STRIKE AND DAMAGE TO NOSE GEAR DOORS. INVES TIGATION FOUND NOSE GEAR STEERING SHAFT BROKEN, SHAFT FOUND TO BE PREVIOUSLY WELDED BY UNKNOWN PARTIES. (X) 1 H 7 1 3O 3A21 2000073100216 20000731 00216 CE 2000 7 31 20000724SH022 1 20000701 G 3242 3063A BRAKE ASSY CESSNA 182 182E 2072712 CE RT MAIN FAILED B EIPR O OTHER A FLAME/FIRE LD LANDING 1 WP 07 3049Y 18254049 AIRCRAFT BRAKED VERY HARD TO CLEAR RUNWAY FOR AIRLINER ON SHORT FINAL. ON TAXI BACK TO RUNWAY FOR TAKEOFF, PILOT NOTICE D RT WHEEL ASSY ON FIRE. THE FIRE DEPT FOAMED AIRCRAFT. NOTE: AIRCRAFT HAS ''STC'' SPEED FAIRINGS. SUBMITTER BELIEV ED THE DESIGN OF THE SPEED FAIRINGS DID NOT ALLOW HEAT TO ESCAPE. THE EXCESSIVE HEAT CAUSED THE BRAKE CALIPER PACK TO P OP OUT CAUSING A HYDRAULIC LEAK WHICH CAUGHT FIRE. THE BOTTOM SKIN OF CABIN WAS WARPED BY THE FIRE. BRAKE CALIPER WAS NOT FOUND. (X) 1 H 7 1 3O NT 3A13 2000073100217 20000731 00217 2000 7 31 20000724SH023 4 20000531 G 6113 055032110 BULKHEAD CESSNA 172 172S 2072439 CE BROKEN B UKJR K NONE W INADEQUATE Q C IN INSP/MAINT 1 EA 23 538SP 41 172S8395 DURING POST-FLIGHT INSPECTION, FOUND AFT EDGE OF PROPELLER SPINNER NEAR BLADE BENT OUTWARD. FOUND AFT SPINNER BULKHEAD BROKEN AROUND THE FLOATING NUTPLATE. REPLACED BULKHEAD WITH NEW. WITH SUCH LOW TIME SINCE NEW ON THIS AIRCRAFT, IT IS POSSIBLE THIS BULKHEAD WAS IMPROPERLY FABRICATED. THE NEW PART WAS INSPECTED AND POSSIBLY THIS ONE WILL ALSO FAIL DUE T O THE WAY IT WAS FABRICATED AT THE RADIUS. SUBMITTER SUGGESTED THE MFG INSPECT THE BULKHEADS IN THE AREA OF THE RADIUS AND CORRECT THIS PROBLEM. (X) 1 H 7 1 3O NT 3A12 2000073100218 20000731 00218 SO 2000 7 31 20000724SH025 2 20000614 G 8530 SA539467 PISTON PIN BEECH 95 95B55 1152729 CE CONT O470 IO470L 17026 SO CYLINDER/PISTON BROKEN B NJ1R O OTHER O OTHER IN INSP/MAINT 1 EA 23 22BS 140 TC1928 454832 PORTION OF THE NR 6 CYLINDER PISTON PIN PLUG BROKE OFF AND CAUSED THE PISTON TO DISINTEGRATE. THIS CAUSED DAMAGE TO THE CONNECTING ROD ON THE NR 5 CYLINDER AND DAMAGE TO THE CRANKCASE. NO RECOMMENDATION TO PREVENT THIS AT THIS TIME. (X) 1 L 7 2 3O 3 O RT 3A16 3E1 2000073100219 20000731 00219 CE 2000 7 31 20000724SH026 1 20000714 G 7160 165201325 AIR BOX CESSNA CESSNA 182 182P 2075816 CE CONT O470 IO470F 17026 SO HINGE PIN DETACHED H O OTHER R PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 WP 23 6305F 33 18264152 089945R DURING T/S OF ROUGH ENG OPERATION FOLLOWED BY NOTED REDUCTION IN AVAILABLE POWER, THE ALTERNATE-AIR DOOR PN 1652013-25 W AS FOUND LOOSE IN THE INDUCTION BOX. THE HINGE PIN HAD SLID OUT OF THE HINGE ALLOWING THE DOOR TO PARTIALLY OBSTRUCT TH E AIR FLOW TO HE ENGINE. UPON INSP OF THE HINGE, DETERMINED STACKING PROCEDURE DURING MFG WAS INADEQUATE TO RETAIN HI NGE PIN. FURTHER ENG DAMAGE RESULTED FROM INGESTION OF THE HINGE SPRING THAT WAS FND LODGED IN THE EXH MUFFLER BAFFLE. AIR-BOX ASSY, PN 1652013-38 WAS INSTALLED IN CONJUNCTION WITH STC NR SA3825SW IN FACTORY NEW CONDITION; 32.6 HRS BEFORE. 1 H 7 1 3O 3 O NT TA13 3E1 2000073100220 20000731 00220 SO 2000 7 31 20000724SH027 2 20000714 G 7322 666916 FLOAT MARVELSCHEBX CESSNA 182 182K 2072724 CE CONT O470 O470R 17026 SO SEPARATED H K NONE K FLUID LOSS NR NOT REPORTED 1 WP 07 104PM 1000 18258085 FUEL SEEP AT CARBURETOR. FOUND BOTH BELLOWS SEPARATED FROM FLOAT ARM. CONDITION EXISTED FOR SOME TIME AS SOLDER JOINTS WERE WORN SMOOTH. (X) 1 H 7 1 3O 3 O NT 3A13 E273 2000121800002 20001218 00002 CE 2000 12 18 20000728SH001 1 20000727 G 2100 LINE CESSNA 210 T210N 2073456 CE CONDENSATION LEAKING B B30R O OTHER J WARNING INDICATION CR CRUISE 1 SW 03 5515Y 21064233 STC SA01194NY WAS INSTALLED IN THIS AIRCRAFT. THIS IS AN ELECTRIC AIR CONDITIONING SYSTEM. PILOT HAD A NEW DEVICE, A TO XIBEE ELECTRONIC CO DETECTOR. DURING FLIGHT, DETECTOR ALARM ACTUATED INDICATING AN UNSAFE LEVEL OF CO. MAINTENANCE INSPE CTED AIRCRAFT AND FOUND THE CONDENSATION DRAIN LINE RAN THROUGH THE AIRFRAME IN THE MAIN GEAR WHEELWELL. THE LINE WAS AB OUT .50 INCH OD GOING THROUGH A HOLE ABOUT 2 INCHES IN DIAMETER. THE MECHANIC SEALED THE HOLE AROUND DRAIN LINE WITH ALU MINUM TAPE AND RTV AND A TEST FLIGHT WAS PERFORMED WITH NO CO DETECTED. STC MANUFACTURER WAS CONTACTED AND HE SAID HE W OULD PROVIDE REPAIR TO AREA TO MAKE A PERMENANT SEAL. 1 H 7 1 3O 3A21 2000121800003 20001218 00003 CE 2000 12 18 20000728SH002 1 20000727 G 2100 LINE CESSNA 210 T210N 2073456 CE CONDENSATIONS LEAKING B B30R O OTHER J WARNING INDICATION CR CRUISE 1 SW 03 5515Y 21064233 STC SA01194NY WAS INSTALLED IN THIS AIRCRAFT. THIS IS AN ELECTRIC AIR CONDITIONING SYSTEM. PILOT HAD A NEW DEVICE, A TO XIBEE ELECTRONIC CO DETECTOR. DURING FLIGHT THE DETECTOR ALARM ACTUATED INDICATING AN UNSAFE LEVEL OF CO. MAINTENANCE IN SPECTED AIRCRAFT AND FOUND THAT THE CONDENSATION DRAIN LINE RAN THROUGH THE AIRFRAME IN THE MAIN GEAR WHEELWELL. THE LIN E WAS ABOUT .50 INCH OD GOING THROUGH A HOLE ABOUT 2 INCHES IN DIAMETER. THE MECHANIC SEALED THE HOLE AROUND DRAIN LINE WITH ALUMINUM TAPE AND RTV AND A TEST FLIGHT WAS PERFORMED WITH NO CO DETECTED. STC MANUFACTURER WAS CONTACTED AND HE SAID HE WOULD PROVIDE REPAIR TO AREA TO MAKE A PERMENANT SEAL. 1 H 7 1 3O 3A21 2000073100222 20000731 00222 EA 2000 7 31 20000728SH004 2 20000703 G 8520 75458 CRANKSHAFT LYC PIPER PA31 PA31P 7103120 SO LYC O541 TIGO541E1A 41539 EA NR 4 CNTRWEIGHT BROKEN B EKIR O OTHER O OTHER NR NOT REPORTED 1 WP 07 252MA 1095 248 31P33 L25562 NR 4 COUNTERWEIGHT DEPARTED CRANKSHAFT AND PUNCHED HOLE IN TOP OF CASE AFTER TAKEOFF. RETURNED TO PHI AND LANDED SAFELY . SUBMITTER STATED THIS APPEARS TO BE A CONTINUING PROBLEM WITH THIS ENGINE. (X) 1 L 7 2 3O 3 O A8EA E19EA 2000073100223 20000731 00223 SO 2000 7 31 20000728SH010 1 20000608 G 2731 96003000 BUSHING PIPER PA34 PA34220T 7103420 SO TAIL WORN H K NONE O OTHER IN INSP/MAINT 1 NM 11 550ST 2957 348533008 EXCESSIVE PLAY IN ELEVATOR TRIM TABS. HOLES IN UPPER LINK, PN 96003-000, WORN OUT. NEW PARTS HAVE BRASS BUSHINGS INSTA LLED IN THESE HOLES, BUT IT IS NOT CALLED OUT IN THE PARTS MANUAL OR BY A SERVICE BULLETIN. (X) 1 L 7 2 3O A7SO 2000080800170 20000808 00170 CE 2000 8 8 20000728SH011 1 20000710 G 2100 A/C PACK CESSNA 210 T210N 2073456 CE DRAIN LINE MLGWW MISINSTALLED B B3OR O OTHER J W WARNING INDICATION INADEQUATE Q C CR CRUISE 1 SW 03 5515Y 21064233 DURING ROUTINE FLIGHT, PILOTS WERE TRYING OUT A NEW ELECTRONIC CO DETECTOR, TOXIBEE, AND THE UNIT REGISTERED 50 PPM OF C O (MAXIMUM THAT IT WILL REGISTER). THIS AIRCRAFT JUST HAD AN AIR CONDITIONING SYSTEM INSTALLED PER STC SA01194NY. MAINTE NANCE INVESTIGATED THE INSTALLATION AND FOUND THAT CONDENSATION DRAIN LINE EXITED CABIN INTO REAR WHEELWELL AREA THROUGH A LARGE DIAMETER HOLE (NOTE: TUNE OD IS .50 INCH , HOLE IS ABOUT 2 INCHES). THIS HOLE WAS SEALED OFF WITH ALUMINUM TAP E AND RTV AND AIRCRAFT WAS TEST FLOWN WITH NO INDICATION OF CO AT ALL ON THE TOXIBEE. THE AIRCRAFT WILL RETURN TO STC IN STALLER WHO WILL PERFORM PERMANENT REPAIR TO DRAIN EXIT. 1 H 7 1 3O 3A21 2000073100225 20000731 00225 EA 2000 7 31 20000731SH001 2 20000710 G 7414 6351 MAGNETO PIPER PA32 PA32300 7103212 SO LYC O540 IO540K1G5 41532 EA CAM FOLLOWER FAILED A LABA K NONE O OTHER IN INSP/MAINT 1 AL 05 200 DUE TO NOT HAVING AN OIL FELT WIPER, A VERY HIGH NUMBER OF NEW OR OVERHAULED SLICK MAGS ARE HAVING EXCESSIVE WEAR ON POI NTS CAM FOLLOWER, AND POINTS ARE SLOWLY CLOSING. SUBMITTER STATED E-GAP MUST NOT ONLY BE CHECKED EVERY 100-HOURS, BUT IN MOST CASES ADJUSTED. (X) 1 L 7 1 3O 3 O A3SO 1E4 2000110600090 20001106 00090 SW 2000 11 6 20000731SH002 1 20000706 G 3211 19805 BOLT BBAVIA 7 7GCBC 1220601 SW LANDING GEAR BROKEN G O OTHER O OTHER LD LANDING 1 EA 17 33472 LEFT SIDE, LANDING GEAR DEPARTED AIRCRAFT. (X) 1 H 7 1 3O NC A759 2000073100226 20000731 00226 SW 2000 7 31 20000731SH003 1 20000706 G 3211 MS2000532 BOLT BBAVIA 7 7GCBC 1220601 SW LANDING GEAR BROKEN G A UNSCHED LANDING O OTHER NR NOT REPORTED 1 EA 17 10989 33472 LEFT SIDE, LANDING GEAR DEPARTED AIRCRAFT. (X) 1 H 7 1 3O NC A759 2000110600091 20001106 00091 SO 2000 11 6 20000731SH004 1 20000720 G 7920 LW13388 GASKET LYC PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA ACCY HOUSING FAILED H K NONE O OTHER IN INSP/MAINT 1 AL 05 200AK 342 318052180 L79368A OIL FILTER CONVERTER PLATE REMOVED FOR SEAL INSPECTION. SEAL FOUND TO BE SOFT AND EXTRUDED. THIS IS THE SECOND SEAL FO UND TO EXHIBIT THIS CONDITION. ENGINE WAS A FACTORY OVERHAUL WITH OVERHAUL DATE OF 3-27-00. (X) 1 L 7 2 3O 3 O A20SO E14EA 2000110600092 20001106 00092 EA 2000 11 6 20000731SH005 2 20000717 G 8510 AEL36001Y CRANKSHAFT PIPER PA28 PA28181 7102807 SO LYC O360 O360A4M 41514 EA FAILED H A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CR CRUISE 1 WP 25 2265M 243 287890238 L2417636A CRANKSHAFT FAILED IN-FLIGHT, FORWARD CHEEK OF NR 4 CONROD JOURNAL. AIRCRAFT LANDED AT AIRPORT. NO DAMAGE. (X) 1 L 7 1 3O 3 O 2A13 E286 2000110600099 20001106 00099 SO 2000 11 6 20000731SH007 1 20000710 G 7810 403109 EXHAUST PIPE PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA ATTACH FLANGE CRACKED I LABA K NONE O OTHER IN INSP/MAINT 1 AL 05 3523Y 317952115 ATTACH FLANGE (TURBO END) OF NR 2 ENGINE OUTBOARD EXHAUST CRACKED AND PIPE DISCONNECTED FROM TURBO. (X) 1 L 7 2 3O 3 O A20SO E14EA 2000110600101 20001106 00101 SO 2000 11 6 20000731SH008 1 20000719 G 5541 6106200 RUDDER PIPER PA25 PA25 7102502 SO LYC O320 O320A1A 41508 EA RUDDER POST CORRODED D K NONE O OTHER IN INSP/MAINT 1 EA 17 6220Z 5900 25263 L292227 RUDDER TAIL POST CORRODED AND BROKE JUST ABOVE LOWER RUDDER MOUNTING PIN AND FORMING TUBE BROKE OFF AT RUDDER POST. (X ) 1 L 7 1 3O 3 O 2A10 E274 2000110600102 20001106 00102 SO 2000 11 6 20000731SH009 1 20000629 G 2820 GL06049 HOSE BALWKS FIREFY FIREFLY9 1050124 SO CRIMP END/HOSE SPLIT B FJ5R K NONE O OTHER IN INSP/MAINT 1 GL 03 90660 F9037 OUTER COVERING OF FUEL HOSES SPLIT AT CRIMP END FITTING. 10 BAD HOSES. (X) 1 B 0 0 A14SO 2000110600103 20001106 00103 SO 2000 11 6 20000731SH010 1 20000620 G 2810 462056 GASKET PIPER PA28 PA28181 7102807 SO FUEL CAP TORN H K NONE O OTHER IN INSP/MAINT 1 WP 07 926PA 9 2843289 THE FUEL CAP GASKET DETERIORATES AND TEARS AFTER PUTTING THE FUEL CAP ON AND OFF A FEW TIMES. APPROXIMATELY 10 TIMES OF TAKING THE FUEL CAP ON AND OFF. (X) 1 L 7 1 3O 2A13 2000110600104 20001106 00104 EA 2000 11 6 20000731SH011 2 20000712 G 8530 74541 EXHAUST VALVE LYC PIPER PA28 PA28180 7102808 SO LYC O360 O360A3A 41514 EA VALVE FACE BROKEN D O OTHER R PARTIAL RPM/PWR LOSS CR CRUISE 1 SW 99 8914J 1885 282929 PILOT REPORTED DURING CRUISE OPERATION ENGINE BECAME ROUGH AND LOST PARTIAL POWER. PRECAUTIONARY LANDING WAS MADE AT RU SH CITY, MN, REGIONAL AIRPORT. INVESTIGATION DISCLOSED APPROX 50 PERCENT OF NR 2 EXHAUST VALVE FACE MISSING, AND EVIDENC E OF PIECES IMPACTING THE PISTON CYL HEAD AND SPARK PLUGS. UPON REMOVAL OF CYLINDER, 3 PIECES OF THE VALVE WERE RECOVE RED FROM THE EXHAUST SYS. NO DEBRIS OR DAMAGE WAS FOUND INSIDE THE ENG OR OIL FILTER. NO ADVANCE SYMPTOMS REPORTED. A NNUAL INSP 20 HOURS PRIOR. COMPRESSION WAS 32/80 AT THAT TIME. USED CYL INSTALLED FOR FLIGHT TO OVERHAUL SHIP. NORMAL OPERATION REPORTED. (X) 1 L 7 1 3O 3 O 2A13 E286 2000110600105 20001106 00105 SO 2000 11 6 20000731SH012 2 20000731 G 8520 A239610N CRANKSHAFT CESSNA 207 207A 2073604 CE CONT O520 IO520F 17032 SO FLANGE CRACKED G A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CR CRUISE 1 SW 99 73100 10 20700559 818889R CRANKSHAFT CRACKED AND FAILED JUST AFT OF FLANGE AND PROPELLER SEPARATED FROM AIRCRAFT WHILE IN-FLIGHT. (X) 1 H 7 1 3O 3 O A16CE E5CE 2000110600106 20001106 00106 CE 2000 11 6 20000731SH013 1 20000710 G 3222 1243400201 FORK CESSNA 210 210B 2073410 CE NOSE GEAR BROKEN D O OTHER O OTHER TX TAXI/GRND HDL 1 CE 01 9661X 21057961 WHILE TAXIING OFF RUNWAY, NOSE GEAR FORK BROKE OFF AT OLEO. RIGHT FORK SHOWED SIGNS OF OLD SEPARATION OR CRACK. (X) 1 H 7 1 3O 3A21 2000110600107 20001106 00107 EA 2000 11 6 20000731SH014 2 20000710 G 7322 SERVO PIPER PA32 PA32300 7103212 SO LYC O540 IO540K1G5 41532 EA FAILED I LABA O OTHER O OTHER NR NOT REPORTED 1 AL 05 95C 327804118 REBUILT SERVO ON ZERO TIMEOVERHAUL FROM FACTORY (LYC). BOTH RAN LEAN, REPLACEMENT SERVO CORRECTED PROBLEM. (X) 1 L 7 1 3O 3 O A3SO 1E4 2000110600108 20001106 00108 EA 2000 11 6 20000731SH015 2 20000710 G 7322 SERVO PIPER PA32 PA32300 7103212 SO LYC O540 IO540K1G5 41532 EA FAILED I LABA O OTHER O OTHER NR NOT REPORTED 1 AL 05 18C 327640049 REBUILT SERVO ON ZERO TIME OVERHAUL FROM FACTORY (LYC). BOTH RAN LEAN, REPLACMENT SERVO CORRECTED PROBLEM. (X) 1 L 7 1 3O 3 O A3SO 1E4 2000110600109 20001106 00109 GL 2000 11 6 20000731SH016 3 20000713 G 6111 S82NC55 BLADE CESSNA 310 T310R 2074246 CE MCAULY 3AF32C 3AF32C93 GL THREADS SCRATCHED H K NONE O OTHER IN INSP/MAINT 1 SW 99 5466J 310R0264 805686 THE BLADE WAS REJECTED DUE TO SCRATCHES IN THREADS PER MCAULEY SB 150. (X) 1 L 7 2 3O 3A10 5 C P22EA 2000110700004 20001107 00004 GL 2000 11 7 20000731SH017 3 20000713 G 6111 S82NC55 BLADE CESSNA 310 T310R 2074246 CE MCAULY 3AF32C 3AF32C93 GL THREADS SCRATCHED H K NONE O OTHER IN INSP/MAINT 1 SW 99 5466J 310R0264 805686 THE BLADE WAS REJECTED DUE TO SCRATCHES IN THREADS PER MCAULEY SB 150. (X) 1 L 7 2 3O 3A10 5 C P22EA 2000110700005 20001107 00005 GL 2000 11 7 20000731SH018 3 20000713 G 6111 S82NC55 BLADE CESSNA 310 T310R 2074246 CE MCAULY 3AF32C 3AF32C93 GL THREADS SCRATCHED H K NONE O OTHER IN INSP/MAINT 1 SW 99 5466J 310R0264 805686 THE BLADE WAS REJECTED DUE TO SCRATCHES IN THREADS PER MCAULEY SB 150. (X) 1 L 7 2 3O 3A10 5 C P22EA 2000110700006 20001107 00006 GL 2000 11 7 20000731SH019 3 20000713 G 6111 S82NC55 BLADE CESSNA 310 T310R 2074246 CE MCAULY 3AF32C 3AF32C93 GL THREADS SCRATCHED H K NONE O OTHER IN INSP/MAINT 1 SW 99 5466J 310R0264 961060 THE BLADE WAS REJECTED DUE TO SCRATCHES IN THREADS PER MCAULEY SB 150. (X) 1 L 7 2 3O 3A10 5 C P22EA 2000110700007 20001107 00007 GL 2000 11 7 20000731SH020 3 20000713 G 6111 S81NC55 BLADE CESSNA 310 T310R 2074246 CE MCAULY 3AF32C 3AF32C93 GL THREADS SCRATCHED H K NONE O OTHER IN INSP/MAINT 1 SW 99 5466J 310R0264 961060 THE BLADE WAS REJECTED DUE TO SCRATCHES IN THREADS PER MCAULEY SB 150. (X) 1 L 7 2 3O 3A10 5 C P22EA 2000110700008 20001107 00008 GL 2000 11 7 20000731SH021 3 20000713 G 6111 S82NC55 BLADE CESSNA 310 T310R 2074246 CE MCAULY 3AF32C 3AF32C93 GL THREADS SCRATCHED H K NONE O OTHER IN INSP/MAINT 1 SW 99 5466J 310R0264 961060 THE BLADE WAS REJECTED DUE TO SCRATCHES IN THREADS PER MCAULEY SB 150. (X) 1 L 7 2 3O 3A10 5 C P22EA 2000110700009 20001107 00009 CE 2000 11 7 20000731SH024 1 20000731 G 2822 1C712 PUMP CESSNA 500 500CESSNA 2076602 CE INTERNAL SEAL LEAKING H O OTHER O OTHER NR NOT REPORTED 1 SW 17 BOOST PUMP WAS CAUSING CIRCUIT BREAKER TO TRIP. FURTHER INVESTIGATION REVEALED UNIT WOULD PUMP FUEL UP THROUGH THE ELEC TRICAL MOTOR THEN THROUGH THE WIRE PROTECTIVE COVERING FINALLY COMING OUT OF THE BACK OF THE CANNON PLUG AND WOULD SHORT THE WIRES TOGETHER CAUSING THE CIRCUIT BREAKER TO TRIP. (X) 1 L 7 2 4F A22CE 2000110700010 20001107 00010 NM 2000 11 7 20000731SH025 1 20000510 G 5311 FRAME BOEING 727 727232 1384082 NM FUSELAGE CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 33785 20640 DURING A C-CHECK, CORROSION WAS NOTED ON FRAME UPPER FLANGE AT STA 1010, RIGHT. (X) 2 L 7 3 4F A3WE 2001020600122 20010206 00122 SW 2001 2 6 20000731SH027 1 20000616 G 6510 407340339103 BEARING BELL 407 407 SW T/R DRIVESHAFT ROUGH B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 407WH 387 532027 WHILE C/W BELL A3B-407-00-35, FOUND 4 EACH BEARINGS TO BE ROUGH. SUBMITTER STATED THESE WERE NOT THE OIL COOLER BEARING S AS REFERENCED IN AD 2000-02-12. (X) 1 G 7 1 3U O H2SW 2001020600123 20010206 00123 SW 2001 2 6 20000731SH028 1 20000616 G 6510 407340339103 BEARING BELL 407 407 SW T/R DRIVESHAFT ROUGH B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 407WH 387 532027 WHILE C/W BELL A3B-407-00-35, FOUND 4 EACH BEARINGS TO BE ROUGH. SUBMITTER STATED THESE WERE NOT THE OIL COOLER BEARING S AS REFERENCED IN AD 2000-02-12. (X) 1 G 7 1 3U O H2SW 2001020600124 20010206 00124 SW 2001 2 6 20000731SH029 1 20000616 G 6510 407340339103 BEARING BELL 407 407 SW T/R DRIVESHAFT ROUGH B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 407WH 387 532027 WHILE C/W BELL A3B-407-00-35, FOUND 4 EACH BEARINGS TO BE ROUGH. SUBMITTER STATED THESE WERE NOT THE OIL COOLER BEARING S AS REFERENCED IN AD 2000-02-12. (X) 1 G 7 1 3U O H2SW 2001020600125 20010206 00125 SW 2001 2 6 20000731SH030 1 20000616 G 6510 407340339103 BEARING BELL 407 407 SW T/R DRIVESHAFT ROUGH B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 407WH 387 532027 WHILE C/W BELL A3B-407-00-35, FOUND 4 EACH BEARINGS TO BE ROUGH. SUBMITTER STATED THESE WERE NOT THE OIL COOLER BEARING S AS REFERENCED IN AD 2000-02-12. (X) 1 G 7 1 3U O H2SW 2000121800004 20001218 00004 NM 2000 12 18 20000731SH032 1 20000510 G 5330 SKIN BOEING 727 727231 1384079 NM STA 480-500 CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 24343 21630 DURING A C-CHECK, CORROSION WAS NOTED ON SKIN BETWEEN STR 27 - STR 28L OF STA 480 - STA 500. (X) 2 L 7 3 4F A3WE 2000121800005 20001218 00005 NM 2000 12 18 20000731SH033 1 20000510 G 5311 FRAME BOEING 727 727231 1384079 NM STA 970-990 CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 24343 21630 DURING A C-CHECK, CORROSION WAS NOTED ON FRAME AT STA 970 - STA 990, STR 29L. OUTBOARD FLANGE, ALSO NOTED ON STR 29R. (X) 2 L 7 3 4F A3WE 2000121800006 20001218 00006 NM 2000 12 18 20000731SH034 1 20000510 G 2510 SEAT TRACK BOEING 727 727231 1384079 NM STA 1030 - 1110 CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 24343 21630 DURING A C-CHECK, CORROSION WAS NOTED ON SEAT TRACK, INBOARD, LEFT STA 1030 - STA 1110, AND OUTBOARD TRACK. (X) 2 L 7 3 4F A3WE 2000121800007 20001218 00007 NM 2000 12 18 20000731SH035 1 20000510 G 5320 SILL BOEING 727 727231 1384079 NM L-2 DOOR/MOPSILL CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 24343 21630 DURING A C-CHECK, CORROSION WAS NOTED ON L-2 DOOR MOP SILL. (X) 2 L 7 3 4F A3WE 2000121800008 20001218 00008 NM 2000 12 18 20000731SH036 1 20000510 G 5315 FLOOR SUPPORT BOEING 727 727231 1384079 NM STA 400-420 CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 24343 21630 DURING A C-CHECK, CORROSION WAS NOTED ON FLOOR SUPPORT, STA 400 - STA 420, BETWEEN BL ZERO AND RBL 24.75. (X) 2 L 7 3 4F A3WE 2000121800009 20001218 00009 NM 2000 12 18 20000731SH037 1 20000510 G 5315 FLOORBEAM BOEING 727 727231 1384079 NM STA 380 CORRODED B KT3R K NONE O OTHER IN INSP/MAINT 1 WP 07 24343 21630 DURING A C-CHECK, CORROSION WAS NOTED ON FLOORBEAM AT STA 380 FROM RT MOPSILL AND R-1 DOOR TO BL ZERO. (X) 2 L 7 3 4F A3WE 2000101000340 20001010 00340 CE 2000 10 10 20000802SH008 1 20000322 G 5712 07221892 RIB CESSNA CESSNA 206 206H 2073301 CE RT WING CRACKED E K NONE O OTHER IN INSP/MAINT 1 AL 05 2312V 294 20808046 DURING 100-HOUR INSPECTION, DISCOVERED THE RT WING LEADING EDGE NOSE RIB LOCATED AT STA 136.00 CRACKED AT THE LIGHTENING HOLE. SUBMITTER SUSPECTED PART WAS DAMAGED DURING INITIAL INSTALL AT THE FACTORY ASSY LINE. (X) 1 H 7 1 3O RT A4CE 2000101000341 20001010 00341 CE 2000 10 10 20000802SH009 1 20000322 G 2810 121640752 TANK CESSNA CESSNA 206 206H 2073301 CE RT SUBFLOOR LEAKING E K NONE K FLUID LOSS IN INSP/MAINT 1 AL 05 2312V 294 20608046 DURING 100-HOUR INSPECTION, DISCOVERED THE RT AUXILIARY FUEL TANK LEAKING FROM A JOINT WELD LOCATED ON THE TOP LEFT SIDE , AND LEAKING FROM THE AFT SIDE OF THE TANK WHERE THERE WAS EVIDENCE OF THE ELECTRODE TOUCHING THE TANK DURING ITS PRODU CTION, AND BURNING A HOLE THROUGH THE SIDE. NOTE: SUBMITTER STATED THIS HOLE WAS NOT LOCATED ON AN EXISTING WELD OR NE AR A FITTING. (X) 1 H 7 1 3O RT A4CE 2000101000342 20001010 00342 2000 10 10 20000802SH010 4 20000322 G 6122 C1610310121 GOVERNOR CESSNA 206 206H 2073301 CE LYC O540 IO540AC1A5 EA POWERPLANT LEAKING E K NONE K FLUID LOSS IN INSP/MAINT 1 AL 05 2312V 294 20608046 L269848A DURING 100-HOUR INSPECTION, DISCOVERED PROPELLER GOVERNOR LEAKING FROM PLUG LOCATED ON THE TOP OF THE GOVERNOR. (X) 1 H 7 1 3O 3 O RT A4CE 1E4 2000101000343 20001010 00343 CE 2000 10 10 20000802SH011 1 20000313 G 2820 1200406249 LINE CESSNA 206 206H 2073301 CE LYC O540 IO540AC1A5 EA HEADER TANK DAMAGED E K NONE K FLUID LOSS IN INSP/MAINT 1 AL 05 7254H 267 20608036 L2688948A DURING A 100-HOUR INSPECTION, FOUND FUEL LINE FROM FUEL BOOST PUMP TO LT HEADER TANK LEAKING AT THE HEADER TANK FITTING. UPON REMOVAL OF LINE, DISCOVERED DAMAGED FLARE. AIRCRAFT TT 288.7 HOURS. (X) 1 H 7 1 3O 3 O RT A4CE 1E4 2000101000346 20001010 00346 EA 2000 10 10 20000802SH014 2 20000714 G 7324 25765561 FLOW DIVIDER PRECISION CESSNA 206 T206H CE LYC O540 TIO540AJ1A EA FAILED B K NONE K FLUID LOSS IN INSP/MAINT 1 EA 13 2467X 11 70194901 T20608155 L1040461A WHILE C/W TEXTRON-LYC SA 55-550 ENG RECALL, FUEL FOUND IN CRANKSCASE MIXED WITH OIL. TEXTRON CHECKED FUEL SYS, FOUND NO PROBLEMS. TECH REP INSPECTED INSTALL AND FOUND NO PROBLEMS WITH INSTALL, BUT NOTED FUEL DRIPPING FROM FUEL INJECTOR LI NES WITH MIX AND THROTTLE CONTROLS IN FWD POSITION WITH NO FUEL BOOST PUMP ON AND FUEL SEL ON. CONDITION CONSIDERED NOR MAL BY TEXTRON AND SUGGESTED TO SHUT OFF FUEL SEL AT EACH ENG SHUT DOWN. TEXTRON RELAYED FUEL SERVO WAS NOT POSITIVE SH UT-OFF TYPE, FUEL FLOW DIVIDER HAS BLEED HOLE FOR ENG TO BE ABLE TO IDLE AND THIS IS WHY FUEL KEEPS DRIPPING. 1 H 7 1 3O 3 O A4CE E14EA 2000101000347 20001010 00347 EA 2000 10 10 20000802SH015 2 20000717 G 8530 MS139973 KEEPER CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA CYLINDER FAILED B O OTHER O OTHER IN INSP/MAINT 1 GL 03 4822G 17273370 L678276T MAJOR DAMAGE TO THE ENGINE CAUSED AS A RESULT OF THE VALVE KEEPERS BREAKING AND ALLOWING THE EXHAUST VALVE TO FALL INTO THE COMBUSTION CHAMBER FOR CAUSE APPEARS TO BE KEEPERS BROKE WHILE WEARING ON THE VALVE UNTIL RELEASE. THE VALVE BROKE AWAY FROM THE HEAD OF THE VALVE AND WAS DRIVEN THROUGH THE TOP OF THE CYLINDER AND ENDED UP INSIDE THE MUFFLER ALONG WIT H LARGE CHUNKS OF THE PISTON WHICH BROKE OFF AND EXITED THROUGH THE NOW EMPTY EXHAUST PORT. 1 H 7 1 3O 3 O NT 3A12 E274 2000101000348 20001010 00348 EA 2000 10 10 20000802SH016 2 20000717 G 8530 SL54017 VALVE CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA CYLINDER FAILED B O OTHER O OTHER IN INSP/MAINT 1 GL 03 4822G 17273370 L678276T MAJOR DAMAGE TO THE ENGINE CAUSED AS A RESULT OF THE VALVE KEEPERS BREAKING AND ALLOWING THE EXHAUST VALVE TO FALL INTO THE COMBUSTION CHAMBER FOR CAUSE APPEARS TO BE KEEPERS BROKE WHILE WEARING ON THE VALVE UNTIL RELEASE. THE VALVE BROKE AWAY FROM THE HEAD OF THE VALVE AND WAS DRIVEN THROUGH THE TOP OF THE CYLINDER AND ENDED UP INSIDE THE MUFFLER ALONG WIT H LARGE CHUNKS OF THE PISTON WHICH BROKE OFF AND EXITED THROUGH THE NOW EMPTY EXHAUST PORT. 1 H 7 1 3O 3 O NT 3A12 E274 2000110700012 20001107 00012 SO 2000 11 7 20000802SH017 1 20000626 G 2700 82836002 ROD END PIPER PA46 PA46310P 7104605 SO AT BOTTOM TUBE CORRODED B SL5R K NONE O OTHER IN INSP/MAINT 1 NE 03 6910T 3181 468508067 DURING ANNUAL INSPECTION, TUBE WAS FOUND WITH EXTERIOR CORROSION ON BOTTOM AFT SURFACE. FLAKED OFF LOOSE PAINT FOUND A DEEP PIT. ABLE TO PASS THIS TUBE WITH AN AWL. WAS ABLE TO PUSH THROUGH A SECOND AREA OF TUBE THAT DID NOT HAVE SIGNS OF CORROSION EXTERNALLY. POSSIBLY CAUSE IS WATER GETTING INTO THE INSIDE OF ROD ASSY FROM THE FORWARD ROD END. SUBMITT ER RECOMMENDED INSPECTION FOR CORROSION AND SPRAYING A CORROSION PREVENTIVE INSIDE OF TUBE. (X) 1 L 7 1 3O RT A25SO 2000110700013 20001107 00013 EA 2000 11 7 20000802SH018 2 20000628 G 8530 EXHAUST VALVE PIPER PA30 PA30 7103002 SO LYC O320 IO320B1A 41508 EA LEFT, NR 2 CYL SHEARED B K NONE O OTHER IN INSP/MAINT 1 CE 01 8219Y 301347 DURING FLIGHT, PILOT HEARD BANG AND NOTICED DIMINISHED POWER. PILOT LANDED WITH BOTH ENGINES RUNNING. ON GROUND, INSP ECTION FOUND ''O'' COMPRESSION ON LEFT ENGINE, NR 2 CYLINDER. ON FURTHER INSPECTION, TOP OF EXHAUST VALVE WAS SHEARED O FF STEM. STEM WAS STILL IN PLACE, VALVE WAS GONE, CYLINDERS AND PISTONS WERE BADLY GOUGED. (X) 1 L 7 2 3O 3 O A1EA 1E12 2000110900002 20001109 00002 NE 2000 11 9 20000802SH021 2 20000717 G 8530 399359 CYLINDER SCWZER G164 G164B 3952802 EA PWA R1340 R134059 52016 NE SPARK PLUG CRACKED B K NONE O OTHER IN INSP/MAINT 1 NM 08 7502Y 1070 821B 19771 THE NUMBER SEVEN CYLINDER HEAD IS CRACKED STARTING AT THE FORWARD SPARK PLUG BOSS RADIATING UP OVER THE TOP OF THE HEAD AND STOPS AT THE AFT SPARK PLUG BOSS. THE CRACK IS OPEN TO AS MUCH AS .0625 INCH, AND EXHAUST GAS RESIDUE IS PRESENT. TOTAL TIME OF CYLINDER IS UNKNOWN. (X) 1 Q 7 1 3R 3 R 1A16 5E2 2000110700017 20001107 00017 CE 2000 11 7 20000802SH024 1 20000622 G 2711 CONTROL CABLE BEECH 58 58 1152740 CE AILERON CHAFED B K NONE O OTHER IN INSP/MAINT 1 CE 05 581SA 46 TH1942 FOUND ONE OF THE AILERON TRIM CABLES CUTTING INTO A FREON LINE UNDER THE FLOOR ON THE LEFT SIDE OF AIRCRAFT BETWEEN STA 100.00 - STA 118.5, P/N 58-555028-13. LINE NEEDS TO FORM DIFFERENTLY TO PROVIDE CLEARANCE FROM THE CABLES. (X) 1 L 7 2 3O 3A16 2000110700018 20001107 00018 CE 2000 11 7 20000802SH025 1 20000717 G 2820 10192000015 TUBE BEECH 200 200BEECH 1152920 CE LT WHEELWELL CHAFED B T4OR K NONE O OTHER IN INSP/MAINT 1 NE 03 1115F 5981 BB324 SMALL HOLE CHAFED IN TUBE. INSTALLED NEW TUBE, POSITIONED FOR PROPER CLEARANCE. (X) 1 L 7 2 4T A24CE 2000110700020 20001107 00020 SO 2000 11 7 20000802SH027 1 20000720 G 7920 LW13904 PLATE PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA HOUSING SEAL DISTORTED H K NONE O OTHER IN INSP/MAINT 1 AL 01 200AK 342 318052180 L79368A OIL FILTER CONVERER PLATE REMOVED FOR SEAL INSPECTION. SEAL FOUND SOFT AND EXTRUDED. THIS IS THE SECOND SEAL FOUND TO EXHIBIT THIS CONDITION. ENGINE WAS A FACTORY OVERHAUL WITH OVERHAUL DATE OF 3-27-00. (X) 1 L 7 2 3O 3 O A20SO E14EA 2000110700021 20001107 00021 CE 2000 11 7 20000802SH028 1 20000610 G 3233 12810012 ACTUATOR CESSNA 210 T210N 2073456 CE BROKEN BODY BROKEN D O OTHER O OTHER IN INSP/MAINT 1 WP 07 4673Y 11299 21063978 RIGHT MAIN GEAR DID NOT FULLY RETRACT. GEAR WAS EXTENDED AND AIRCRAFT LANDED WITHOUT PROBLEMS. FOUND THE RT MLG ACTUAT OR BODY BROKEN JUST FORWARD OF THE ROLLER BEARING. THIS ALLOWED THE RACK AND PINION GEARS TO ''''JUMP A TOOTH''''. THE ACTUATOR BODY, P/N 128101-2, WAS REPLACED. (X) 1 H 7 1 3O 3A21 2000110700022 20001107 00022 CE 2000 11 7 20000802SH029 1 20000721 G 3221 NAS464P426 BOLT CESSNA 421 421B 2076014 CE RT MLG BROKEN H O OTHER O OTHER IN INSP/MAINT 1 CE 05 5987M 7775 421B0329 HEAD OF BOLT BROKE OFF ALLOWING THE REMAINDER OF THE BOLT TO SLIDE OUT. WHEN THE BOLT SLID OUT AND WAS ONLY ON ONE OF T HE LUGS ON THE MAIN GEAR TRUNNION, THE LUG FAILED. (THERE ARE TWO LUGS ON THE TRUNNION). (X) 1 L 7 2 3O A7CE 2000110700023 20001107 00023 CE 2000 11 7 20000802SH030 1 20000714 G 7603 565549011 THROTTLE CABLE CESSNA 172 172P 2072436 CE INACCURATE B DYCR K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 07 54356 17274961 OWNER REQUESTED THROTTLE CABLE BE CHANGED DUE TO CABLE CREEPING. WHEN CABLE WAS COMPARED TO ORIGINAL CABLE, NEW CABLE W AS FOUND TO HAVE MANY DIFFERENCES: LENGTH WAS LONGER; FIREWALL SLEEVE IN DIFFERENT LOCATION; LARGER DIAMETER; ENGINE MO UNT ATTACHMENT COMPLETELY OFF. CESSNA NOTIFIED. (X) 1 H 7 1 3O NT 3A12 2000080300223 20000803 00223 SW 2000 8 3 20000803SH001 1 20000705 G 7332 407075024103 INDICATOR BELL 407 407 SW FUEL PRES. ERRATIC B GS1R O OTHER O OTHER IN INSP/MAINT 1 EA 03 407WH 389 532027 REPLACED FUEL PRESSURE INDICATOR WITH NEW FROM BELL HELICOPTER. (X) 1 G 7 1 3U O H2SW 2001011104087 20010111 04087 2001 1 11 20000803SH004 1 20000720 G 3350 37815001 BATTERY PACK CELL TAPS/SPOT W FAILED B JGVR K NONE W INADEQUATE Q C IN INSP/MAINT 1 CE 09 CELL TAG SPOT WELDS BROKEN AND TABS DISTORTED AT ELECTRICAL CENTER OF PACK., AND AT ONE ADDITIONAL LOCATION. DAMAGE OCC URRED DURING SHIPPING/HANDLING OF PACK BETWEEN FACTORY AND END USER. POSSIBLE CAUSE IS INADEQUATE ADHESIVE USED DURING MANUFACTURING OF PACK. NOTE: THIS PACK DOES HAVE SMALL AMOUNT OF ADHESIVE BETWEEN PACK HALVES, BUT IS NOT ADEQUATE TO SUPPORT HANDLING STRESSES. SUBMITTER RECOMMENDED MORE EXTENSIVE USE OF ADHESIVE AND PERHAPS APPLICATOR NOZZLES TO REAC H CORE OF PACK AND BETWEEN CELLS. (X) 2001011104088 20010111 04088 2001 1 11 20000803SH005 1 20000719 G 3350 37815001 BATTERY PACK CELL TABS 10&11 FAILED B JGVR K NONE W INADEQUATE Q C IN INSP/MAINT 1 CE 09 CELL TAB SPOT WELDS BROKEN AT ELECTRICAL CENTER OF BATTERY PACKS (BETWEEN CELLS NR 10 AND NR 11). DAMAGE TO TABS/SPOT WELDS IS OCCURRING DURING SHIPPING/HANDLING OF THESE PACKS BETWEEN FACTORY AND END USER. POSSIBLE CAUSE IS LACK OF ADHE SIVE BETWEEN CELLS AND PACK HALVES WHICH ONCE WAS, BUT NO LONGER USED DURING MANUFACTURE OF PACKS. SUBMITTER RECOMMEND ED USE OF ADHESIVE IN ASSEMBLY. (X) 2000112800062 20001128 00062 GL 2000 11 28 20000803SH007 3 20000620 G 6110 6506709 BRUSH BLOCK ALLSN A6441 A6441FN606 GL CRACKED H K NONE O OTHER IN INSP/MAINT 1 NM 01 CRACK IN METAL, PN 6506709, IN BRUSH BLOCK LEAF ASSEMBLY. (X) 6 C P898 2000112800063 20001128 00063 SO 2000 11 28 20000803SH009 1 20000714 G 2410 635796 COUPLING PRESTOLITE PIPER PA34 PA34200T 7103406 SO COUPLES ALT/ENG FAILED B HE4R K NONE O OTHER IN INSP/MAINT 1 SO 11 345HK 380 0070545 347870359 SUBMITTER STATED THIS IS THIRD FAILURE EXPERIENCED, TWO PREVIOUS ON RIGHT ENGINE. BOND BETWEEN RUBBER SLEEVE AND ACCESS ORY DRIVE GEAR AND ALTERNATOR COUPLE FAILED WITH GEAR SLIPPING RELATIVE TO COUPLE, CAUSED ALTERNATOR TO FAIL UNDER LOAD. (X) 1 L 7 2 3O A7SO 2000112800064 20001128 00064 EA 2000 11 28 20000803SH010 2 20000707 G 7250 3032651 VANE PWA BEECH 99 99 1154002 CE PWA PT6 PT6A27 52043 EA VANE T/E REPAIR INACCURATE G K NONE W INADEQUATE Q C IN INSP/MAINT 1 NE 01 24BH 176 10471 U67 PCE51931 A TREND HAS DEVELOPED INDICATING PROCEDURES, TECHNIQUES, OR WORKMANSHIP OF OVERHAULED VANE RINGS IS RESULTING IN PREMATU RE FAILURE OF PN 3032651 WHICH RESULTS IN UNSATISFACTORY ENGINE PERFORMANCE AND POSSIBLE ENGINE FAILURE. (X) 1 L 7 2 3T 4 T A14CE E4EA 2000112800065 20001128 00065 SO 2000 11 28 20000803SH011 1 20000607 G 7920 13388 GASKET LYC PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA ACCESSORY CASE ERODED G O OTHER K FLUID LOSS NR NOT REPORTED 1 AL 01 3536B 734 367 317952205 L54361A GASKET UNDER OIL FILTER CONNECTOR PLATE FAILED RESULTING IN LARGE OIL LEAK AND ENGINE FIRE. UPON REMOVAL, GASKET APPEAR ED TO HAVE UNUSUALLY SOFT CONSISTENCY AND EXTENDED BEYOND NORMAL DIMENSIONS. REPLACED WITH NEW. (X) 1 L 7 2 3O 3 O A20SO E14EA 2000112800067 20001128 00067 SO 2000 11 28 20000803SH013 1 20000717 G 3222 6773500V TRUNNION PIPER PA28 PA28R180 7102809 SO LH WEB AREA CRACKED D K NONE O OTHER IN INSP/MAINT 1 GL 15 3293R 28R31264 DURING ANNUAL INSPECTION, FOUND LEFT MAIN GEAR TRUNNION, P/N 67735-00V, CRACKED THROUGH WEB AREA AND INTO CASTING APPROX .75 INCH. PIPER SL 616 ALLOWS FOR THE EXISTING .191 INCH HOLE TO BE ENLARGED TO .500 INCH IN DIAMETER TO REMOVE CRACKE D AREA, BUT THIS CRACK HAD ALREADY EXTENDED TOO FAR UP INTO THE CASTING. REPLACED WITH A SERVICEABLE, NEW STYLE TRUNNIO N WHICH INCORPORATES A MUCH THICKER WEB. AIRCRAFT TT: 3,352 HOURS. (X) 1 L 7 1 3O 2A13 2000112800068 20001128 00068 SW 2000 11 28 20000803SH014 1 20000719 G 7120 6200421 BRACKET GULSTM 690TP 690A 0141722 SW LEFT ENGINE CRACKED B MV5R K NONE O OTHER IN INSP/MAINT 1 GL 11 690DB 8440 11226 AFT ENGINE MOUNT SUPPORT BRACKET TO LEFT ENGINE CRACKED AT INBOARD WEB. (X) 1 H 7 2 3T 2A4 2001020600078 20010206 00078 SW 2001 2 6 20000804SH001 1 20000517 G 6710 2060103605 PITCH LINK BELL 206 206L3 1182108 SW MAIN ROTOR CRACKED C K NONE O OTHER IN INSP/MAINT 1 SW 05 732H 51607 PC LINK FOUND CRACKED AT LOWER END (CRACK - .250 INCH LONG). FOUND ON DAILY INSPECTION. AIRCRAFT TT, 5,271:10 HOURS. POSSIBLE CAUSE UNKNOWN, PREVIOUS PROBLEMS WITH PART ARE ON RECORD AT BHT. (X) 1 G 7 1 3U H2SW 2001020600001 20010206 00001 WP 2001 2 6 20000804SH003 1 20000804 G 2450 TAB ROBSIN R22 R22ALPHA 7640104 WP CAP BENT D K NONE O OTHER IN INSP/MAINT 1 EA 07 22HF 300 0386 FOUND SEVERAL CAPS WITH BROKEN AND BENT LOCKING TABS. ALSO, CORRODED/STUCK SPRUNG IN CAP - EITHER WILL CAUSE DISRUPTION OF POWER TO CLUTCH MOTOR PREVENTING PROPER ACTUATOR FUNCTION WHICH COULD CAUSE PILOT TO MAKE PRECAUTIONARY LANDING. S UBMITTER RECOMMENDED MAKING THE CAPS OF A MORE DURABLE MATERIAL. (X) 1 G 7 1 3O H10WE 2001020100033 20010201 00033 NE 2001 2 1 20000804SH004 2 20000724 G 7314 02527730007 PUMP BELL 212 212 1181420 SW PWA PT6T PT6T3B 52045 NE NR 2 ENGINE BROKEN A HEAA A UNSCHED LANDING Y J ENGINE STOPPAGE WARNING INDICATION NR NOT REPORTED 1 NM 11 214KA 1570 30827 CPPS60002 NR 2 ENGINE SHUT DOWN IN-FLIGHT. PILOT MADE NORMAL LANDING. INVESTIGATED PROBLEM. PULL FUEL PUMP OFF. FOUND INTERNAL SPLINES OF PUMP GROUND OFF. SPLINES MISSING DUE TO ABNORMAL WEAR ON SPLINES. INSTALLED NEW PUMP. GROUND RAN ENGINE. ENGINE FUNCTIONED PROPERLY. (X) 1 G 7 1 4U 4 U H4SW E22EA 2001020600002 20010206 00002 SW 2001 2 6 20000804SH005 1 20000711 G 6710 251401501299 BEARING GLOBE BELL 206 206B 1181511 SW ENGINE BAY BINDING B IIFR K NONE O OTHER IN INSP/MAINT 1 SW 03 2193X 3506 LINEAR ACTUATAORS, PN 206-062-721-001 AND 721-109 FAILED PREMATURELY DUE TO OVERSTAKING OF BEARING ROD END P/N 251401501 299 CAUSING BEARING TO BE TIGHT AND BINDING WHERE ADJUSTMENTS ARE MADE. ACTUATOR MOTOR IS NOT STRONG ENOUGH TO OVERCOME BEARING STIFFNESS. SUBMITTER SUGGESTED USING BRG WITH LESS BREAK FREE FORCE,THAT IS NOT STAKED SO TIGHT TO ALL FREE MO VEMENT OF BRG AND LINEAR ACTUATOR. 1 G 7 1 3U H2SW 2001020600003 20010206 00003 SW 2001 2 6 20000804SH006 1 20000711 G 6710 251401501299 BEARING GLOBE BELL 206 206L1 1182107 SW ENGINE BAY BINDING B IIFR K NONE O OTHER IN INSP/MAINT 1 SW 03 2150M 45703 LINEAR ACTUATORS, P/N 206-062-721-001, AND 721-109, FAILED PREMATURELY DUE TO OVERSTAKING OF BEARING ROD END P/N 2514015 01299 CAUSING BEARING TO BE TIGHT AND BINDING WHERE ADJUSTMENTS ARE MADE. ACTUATOR MOTOR IS NOT STRONG ENOUGH TO OVERCO ME BEARING STIFFNESS. SUBMITTER SUGGESTED USING BRG WITH LESS BREAK FREE FORCE THAT IS NOT STAKED SO TIGHT TO ALLOW FRE E MOVEMENT OF BRG AND LINEAR ACTUATORS. (X) 1 G 7 1 3U H2SW 2001020600004 20010206 00004 SW 2001 2 6 20000804SH007 1 20000726 G 6510 407340339103 BEARING BELL 407 407 SW TAIL ROTOR ROUGH B IIFR K NONE O OTHER IN INSP/MAINT 1 SW 03 407JR 53245 TAIL ROTOR HANGER BEARINGS, P/N 407-340-339-103, HAVE BEEN FOUND ROUGH AND FAILED PREMATURELY ON MANY OCCASIONS DURING INSPECTIONS. THE GREASE USED TO LUBRICATE THESE BEARINGS IS BEING FORCED OUT BY SUCTION CREATED BY THE OIL COOLERS ROTA TING IMPELLER (FAN). SUBMITTER SUGGESTED THE MFG OF THESE BEARINGS DEVELOP A HIGHER QUALITY OF SEAL MORE DURABLE TO RET AIN GREASE IN BEARING. (X) 1 G 7 1 3U O H2SW 2001020600005 20010206 00005 SW 2001 2 6 20000804SH008 1 20000726 G 6510 407340339103 BEARING BELL BELL 407 407 SW TAIL ROTOR ROUGH B IIFR K NONE O OTHER IN INSP/MAINT 1 SW 03 407AK 53269 TAIL ROTOR HANGER BEARINGS, PN 407-340-339-103, HAVE BEEN FOUND ROUGH AND FAILED PREMATURELY ON MANY OCCASIONS DURING IN SPECTIONS. THE GREASE USED TO LUBRICATE THESE BEARINGS IS BEING FORCED OUT BY SUCTION CREATED BY THE OIL COOLERS ROTATI NG IMPELLER (FAN). SUBMITTER SUGGESTED THE MFG OF THESE BEARINGS DEVELOP A HIGHER QUALITY OF SEAL MORE DURABLE TO RETAI N GREASE IN BEARING. (X) 1 G 7 1 3U O H2SW 2001020600008 20010206 00008 SW 2001 2 6 20000804SH009 1 20000726 G 6510 407340339103 BEARING BELL 407 407 SW TAIL ROTOR ROUGH B IIFR K NONE O OTHER IN INSP/MAINT 1 SW 03 407PR 53232 TAIL ROTOR HANGER BEARINGS, P/N 407-340-339-103, HAVE BEEN FOUND ROUGH AND FAILED PREMATURELY ON MANY OCCASIONS DURING I NSPECTIONS. THE GREASE USED TO LUBRICATE THESE BEARINGS IS BEING FORCED OUT BY SUCTION CREATED BY THE OIL COOLERS ROTAT ING IMPELLER (FAN). SUBMITTER SUGGESTED THE MFG OF THESE BEARINGS DEVELOP A HIGHER QUALITY OF SEAL MORE DURABLE TO RETA IN GREASE IN BEARING. (X) 1 G 7 1 3U O H2SW 2001020600009 20010206 00009 SW 2001 2 6 20000804SH010 1 20000726 G 6510 407340339103 BEARING BELL 407 407 SW TAIL ROTOR ROUGH B IIFR K NONE O OTHER IN INSP/MAINT 1 SW 03 517R 53231 TAIL ROTOR HANGER BEARINGS, PN 407-340-339-103, HAVE BEEN FOUND ROUGH AND FAILED PREMATURELY ON MANY OCCASIONS DURING IN SPECTIONS. THE GREASE USED TO LUBRICATE THESE BEARINGS IS BEING FORCED OUT BY SUCTION CREATED BY THE OIL COOLERS ROTATI NG IMPELLER (FAN). SUBMITTER SUGGESTED THE MFG OF THESE BEARINGS DEVELOP A HIGHER QUALITY OF SEAL MORE DURABLE TO RETAI N GREASE IN BEARING. (X) 1 G 7 1 3U O H2SW 2001020600010 20010206 00010 SW 2001 2 6 20000804SH011 1 20000804 G 5210 2060315723S HINGE BELL 206 206B 1181511 SW CREW DOOR WRONG PART B UK7R K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 03 26EA 2175 HINGES REMOVED BECAUSE OF POOR DOOR FIT. FURTHER INSPECTION AND INVESTIGATION REVEALED NON-COMPLIANCE WITH IPB. PART N UMBER NOT APPLICABLE TO 206B SERIES, POSSIBLY OH58 SERIES. REMOVED FROM SERVICE. 1 G 7 1 3U H2SW 2001020600011 20010206 00011 NE 2001 2 6 20000804SH012 1 20000629 G 2422 SPC75B INVERTER SKRSKY S76 S76A 8143006 NE E/E BAY INOPERATIVE B ALGR O OTHER J B WARNING INDICATION SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 SW 03 164AG 760290 AFTER TAKEOFF, NR 1 INVERTER LIGHT ILLUMINATED. NR 1 INVERTER WAS INOPERATIVE, AND CREW AND PASSENGERS SMELLED SMOKE. (X) 1 G 7 2 3U H1NE 2001020100034 20010201 00034 SW 2001 2 1 20000804SH014 1 20000630 G 6510 407340340101 DISC PACK BELL 407 407 SW TAIL ROTOR CRACKED A ALGA K NONE O OTHER IN INSP/MAINT 1 SW 03 427AL A244 53107 DURING 25-HOUR AD INSPECTION, FOUND DISC PACK CRACKED IN 3 PLACES FACING AFT AND 1 CRACK FORWARD. (X) 1 G 7 1 3U O H2SW 2001020600013 20010206 00013 SW 2001 2 6 20000804SH015 1 20000703 G 6510 FRAME BELL 407 407 SW TRANSMISSION CRACKED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 427AL KC312 53107 DURING DAILY SERVICE CHECK, FOUND TRANSMISSION SIDE OF MDS, FORWARD FLEX FRAME CRACKED FROM ATTACHMENT BOLT TO OUTER EDG E OF FLEX FRAME. (X) 1 G 7 1 3U O H2SW 2001020600014 20010206 00014 SW 2001 2 6 20000804SH016 1 20000614 G 6322 407062021101 DUCT BELL 407 407 SW OIL COOLER CRACKED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 467AL 53190 UPON DAILY INSPECTION, FOUND CRACKS IN CORNERS CAUSED BY INHERENT VIBRATIONS. (X) 1 G 7 1 3U O H2SW 2001020600015 20010206 00015 SW 2001 2 6 20000804SH017 1 20000716 G 6322 407062021101 DUCT BELL 407 407 SW OIL COOLER CRACKED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 467AL 132 53190 UPON DAILY INSPECTION, CRACKED IN CORNERS CAUSED BY INHERENT VIBRATIONS. (X) 1 G 7 1 3U O H2SW 2001020100035 20010201 00035 SW 2001 2 1 20000804SH018 1 20000715 G 6510 407340340101 DISC PACK BELL 407 407 SW TAIL ROTOR CRACKED A ALGA K NONE O OTHER IN INSP/MAINT 1 SW 03 417AL A823 53054 DURING 25-HOUR AD INSPECTION, AFT SEGMENT CRACKED ACROSS THE SPAN. (X) 1 G 7 1 3U O H2SW 2001020600017 20010206 00017 SW 2001 2 6 20000804SH019 1 20000531 G 6322 407062021101 DUCT BELL 407 407 SW OIL COOLER CRACKED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 417AL 53054 UPON DAILY INSPECTION, CRACKS IN CORNERS CAUSED BY IHERENT VIBRATIONS. (X) 1 G 7 1 3U O H2SW 2001020600018 20010206 00018 SW 2001 2 6 20000804SH020 1 20000708 G 6322 407062021101 DUCT BELL 407 407 SW OIL COOLER CRACKED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 487AL 1666 53204 UPON DAILY INSPECTION, CRACKS IN CORNERS CAUSED BY INHERENT VIBRATIONS. (X) 1 G 7 1 3U O H2SW 2001020600019 20010206 00019 SW 2001 2 6 20000804SH021 1 20000713 G 6322 407062021101 DUCT BELL 407 407 SW OIL COOLER CRACKED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 477AL 1244 53203 UPON DAILY INSPECTION, CRACKS IN CORNERS CAUSED BY INHERENT VIBRATIONS. (X) 1 G 7 1 3U O H2SW 2001020600056 20010206 00056 GL 2001 2 6 20000804SH022 2 20000218 G 7210 6893672 PINION GEAR CAG47276 BELL 407 407 SW ALLSN 250C 250C47B GL GEARBOX GALLED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 477AL 1985 CAG47276 53203 CAE847125 PINION GEAR HAS EXCESSIVE GALLING ON GEAR TEETH, POSSIBLY DUE TO EXCESSIVE TORQUE ON ENGINE, GEAR CANNOT SUSTAIN LOAD. (X) 1 G 7 1 3U 3 U O H2SW E1GL 2001020600057 20010206 00057 SW 2001 2 6 20000804SH023 1 20000710 G 6510 407340340101 DISC PACK BELL 407 407 SW NR 6 CRACKED B ALGA K NONE O OTHER IN INSP/MAINT 1 SW 00 437AL A932 53141 DURING PHASE INSPECTION, VISUAL INSPECTION OF TAILROTOR DRIVESHAFT FOUND ONE SEGMENT OF DISC PACK OF NR 6 DRIVESHAFT CRA CKED. FORWARD SEGMENT CRACKED ACROSS THE SPAN. (X) 1 G 7 1 3U O H2SW 2001020600058 20010206 00058 SW 2001 2 6 20000804SH024 1 20000712 G 6510 407340340101 DISC PACK BELL 407 407 SW NR 3 CRACKED B ALGA K NONE O OTHER IN INSP/MAINT 1 SW 03 577AL AFS932 53247 DURING 25-HOUR AD INSPECTION, FORWARD SEGMENT CRACKED ACROSS TWO SPANS. 180 DEGREES OPPOSITE EACH OTHER. (X) 1 G 7 1 3U O H2SW 2001020600072 20010206 00072 SW 2001 2 6 20000804SH025 1 20000717 G 6322 406040320101 SHAFT BELL 407 407 SW OIL COOLER FAILED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 577AL 550 AFS932 53247 ON FINAL APPROACH, PILOT FELT A GRINDING IN THE FLIGHT CONTROLS. POST-FLIGHT INSPECTION REVEALED FORWARD OIL COOLER BLO WER BEARING FAILURE. FORWARD BEARING DISINTEGRATED (FAILED) AND DAMAGED SHAFT. (X) 1 G 7 1 3U O H2SW 2001020600073 20010206 00073 SW 2001 2 6 20000807SH001 1 20000717 G 6322 406040322101 HANGER ASSY BELL 407 407 SW OIL COOLER DAMAGED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 577AL 550 AFS932 53247 ON FINAL APPROACH, PILOT FELT A GRINDING IN THE FLIGHT CONTROLS. POST-FLIGHT INSPECTION REVEALED FORWARD OIL COOLER BLO WER BEARING FAILURE. FORWARD BEARING DISINTEGRATED (FAILED) IN THE HANGER AND THE HANGER WAS DAMAGED. (X) 1 G 7 1 3U O H2SW 2001020600074 20010206 00074 SW 2001 2 6 20000807SH002 1 20000717 G 6322 407340339103 BEARING BELL 407 407 SW COOLER BLOWER FAILED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 577AL 550 AFS932 53247 ON FINAL APPROACH, PILOT FELT A GRINDING IN THE FLIGHT CONTROLS. POST-FLIGHT INSPECTION REVEALED FORWARD OIL COOLER BL OWER BEARING FAILURE. BEARING DISINTEGRATED (FAILED). (X) 1 G 7 1 3U O H2SW 2001020600080 20010206 00080 SW 2001 2 6 20000807SH003 1 20000522 G 6322 407062021101 DUCT BELL 407 407 SW OIL COOLER CRACKED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 587AL 2536 53248 UPON DAILY INSPECTION, CRACKS IN CORNERS CAUSED BY INHERENT VIBRATIONS. (X) 1 G 7 1 3U O H2SW 2001020600082 20010206 00082 SW 2001 2 6 20000807SH005 1 20000707 G 6310 406340102101 SEAL BELL 407 407 SW FREEWHEEL UNIT LEAKING A ALGA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 627AL 621 A4199 53284 DURING DAILY INSPECTION, FORWARD SEAL LEAKING, CARBON PORTION PITTED. (X) 1 G 7 1 3U O H2SW 2001020600083 20010206 00083 SW 2001 2 6 20000807SH006 1 20000520 G 6322 407062021101 DUCT BELL 407 407 SW OIL COOLER CRACKED B ALGA K NONE O OTHER IN INSP/MAINT 1 SW 03 627AL 2274 53284 UPON DAILY INSPECTION, CRACKS IN CORNERS CAUSED BY INHERENT VIBRATION. (X) 1 G 7 1 3U O H2SW 2001020600084 20010206 00084 SW 2001 2 6 20000807SH007 1 20000712 G 6510 407340340101 DISC PACK BELL 407 407 SW TAIL ROTOR CRACKED A ALGA K NONE O OTHER IN INSP/MAINT 1 SW 03 627AL A1199 53284 DURING 25 HOUR AD INSPECTION, FORWARD SEGMENT CRACKED ACROSS THE SPAN. (X) 1 G 7 1 3U O H2SW 2001020600085 20010206 00085 SW 2001 2 6 20000807SH008 1 20000712 G 6510 407340340101 DISC PACK BELL 407 407 SW TAIL ROTOR CRACKED A ALGA K NONE O OTHER IN INSP/MAINT 1 SW 03 627AL 184 A1173 53284 DURING 25-HOUR AD INSPECTION, AFT SEGMENT CRACKED ACROSS THE SPAN. (X) 1 G 7 1 3U O H2SW 2001020600086 20010206 00086 SW 2001 2 6 20000807SH009 1 20000713 G 6710 BUSHING BELL 407 407 SW SWASHPLATE LINK WORN A ALGA K NONE O OTHER IN INSP/MAINT 1 SW 03 627AL AFS1179 53284 DURING REPAIR FOR WORN BUSHINGS AND SPACERS, EXCESSIVE CORROSION AROUND AND UNDER BUSHINGS, P/N 206-010-338-3. (X) 1 G 7 1 3U O H2SW 2001020600105 20010206 00105 SW 2001 2 6 20000807SH010 1 20000707 G 6510 407340340101 DISC PACK BELL 407 407 SW TAIL ROTOR CRACKED A ALGA K NONE O OTHER IN INSP/MAINT 1 SW 03 627AL 153 AFS1027 53284 AFT COUPLING OF NR 2 TAILROTOR DRIVESHAFT HAS A CRACK ACROSS THE SPAN ON THE FORWARD AND AFT SEGMENTS OF THE DISC PACK. (X) 1 G 7 1 3U O H2SW 2001020600088 20010206 00088 SW 2001 2 6 20000807SH011 1 20000623 G 6510 407340340101 DISC PACK BELL 407 407 SW TAIL ROTOR CRACKED A ALGA K NONE O OTHER IN INSP/MAINT 1 SW 03 627AL 87 A1199 53284 DURING 25-HOUR AD INSPECTION, DSIC PACK CRACKED IN TWO PLACES ACROSS THE SPAN OF THE FORWARD SEGMENT. (X) 1 G 7 1 3U O H2SW 2001020600089 20010206 00089 SW 2001 2 6 20000807SH012 1 20000606 G 6510 407340340101 DISC PACK NR5 BELL 407 407 SW TAIL ROTOR CRACKED A ALGA K NONE O OTHER IN INSP/MAINT 1 SW 03 627AL A1178 53284 DURING 25-HOUR AD INSPECTION, AFT SEGMENT CRACKED ACROSS THE SPAN. (X) 1 G 7 1 3U O H2SW 2001020600090 20010206 00090 SW 2001 2 6 20000807SH013 1 20000608 G 6510 407340340101 DISC PACK BELL 407 407 SW TAIL ROTOR CRACKED A ALGA K NONE O OTHER IN INSP/MAINT 1 SW 03 627AL A765 53284 DURING 25-HOUR AD INSPECTION, AFT SEGMENT CRACKED ACROSS SPAN. (X) 1 G 7 1 3U O H2SW 2001020600091 20010206 00091 SW 2001 2 6 20000807SH014 1 20000628 G 6220 407010103101 PITCH HORN BELL 407 407 SW MAIN ROTOR CORRODED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 627AL 2486 A305 53284 AT FIRST OVERHAUL OF MAIN ROTOR HUB ASSEMBLY, CORROSION PITTING UNDER BUMPER PLATES. (X) 1 G 7 1 3U O H2SW 2001020600092 20010206 00092 SW 2001 2 6 20000807SH015 1 20000628 G 6220 407010103101 PITCH HORN BELL 407 407 SW MAIN ROTOR CORRODED A ALGA K NONE O OTHER IN INSP/MAINT 1 SW 03 627AL 2486 A305 53284 AT FIRST OVERHAUL OF MAIN ROTOR HUB ASSEMBLY, CORROSION PITTING UNDER BUMPER PLATES. (X) 1 G 7 1 3U O H2SW 2001020600093 20010206 00093 SW 2001 2 6 20000807SH016 1 20000713 G 6710 BUSHING BELL 407 407 SW SWASHPLATE CORRODED A ALGA K NONE O OTHER IN INSP/MAINT 1 SW 03 627AL AFS1788 53284 DURING REPAIR FOR WORN BUSHINGS AND SPACERS, EXCESSIVE CORROSION AROUND AND UNDER BUSHINGS, PN 206-010-338-3. 1 G 7 1 3U O H2SW 2001020600094 20010206 00094 SW 2001 2 6 20000807SH017 1 20000404 G 6510 407340340101 DISC PACK BELL 407 407 SW TAIL ROTOR CRACKED A ALGA K NONE O OTHER IN INSP/MAINT 1 SW 03 627AL 770 A1199 53284 DURING 25-HOUR AD INSPECTION, ONE LAMINATE IS CRACKED (AFT LAMINATE). (X) 1 G 7 1 3U O H2SW 2001020600095 20010206 00095 SW 2001 2 6 20000807SH018 1 20000628 G 6510 407340339103 BEARING BELL 407 407 SW T/R DRIVESHAFT CRACKED A ALGA K NONE O OTHER IN INSP/MAINT 1 SW 03 687AL 388 A469 53366 DURING REPAIR/REPLACEMENT OF CRACKED HOUSING, BEARINGS ROUGH. (X) 1 G 7 1 3U O H2SW 2001020600096 20010206 00096 SW 2001 2 6 20000807SH019 1 20000628 G 6510 407340339103 BEARING BELL 407 407 SW T/R DRIVESHAFT CRACKED A ALGA K NONE O OTHER IN INSP/MAINT 1 SW 03 687AL 388 A469 53366 DURING REPAIR/REPLACEMENT OF CRACKED HOUSING, BEARINGS ROUGH. (X) 1 G 7 1 3U O H2SW 2001020600097 20010206 00097 SW 2001 2 6 20000807SH020 1 20000619 G 6510 407340340101 DISC PACK BELL 407 407 SW TAIL ROTOR CRACKED A ALGA K NONE O OTHER IN INSP/MAINT 1 SW 03 607AL 53264 DURING 50-HOUR VISUAL INSPECTION, NR 3 TAILROTOR DRIVESHAFT DISC PACK IS CRACKED ON AFT SIDE. (X) 1 G 7 1 3U O H2SW 2000091400113 20000914 00113 CE 2000 9 14 20000808SH001 1 20000801 G 3260 V31 SWITCH CESSNA 401 401 207590C CE NOSE GEAR FAILED E MHJA O OTHER J L N WARNING INDICATION NO TEST FALSE WARNING LD LANDING 1 SW 05 401PW 5010269 THE PILOT REPORTED HE DID NOT HAVE A NOSE GEAR DOWNLOCK INDICATION. THE PILOT DECLARED AN EMERGENCY, AND LANDED WITHOUT INCIDENT. THE CAUSE OF THE PROBLEM WAS A DOWNLOCK MICROSWITCH ON THE NOSE GEAR THAT FAILED AND A BROKEN WIRE ON THE DO WNLOCK GEAR INDICATOR. (X) 1 L 7 2 3O A7CE 2000091400115 20000914 00115 CE 2000 9 14 20000808SH002 1 20000726 G 2434 9522R ALTERNATOR CESSNA 401 401 207590C CE RT ENGINE FAILED E MHJA O OTHER J S O WARNING INDICATION AFFECT SYSTEMS OTHER TX TAXI/GRND HDL 1 SW 05 3208Q 4010008 RIGHT ALTERNATOR WAS INOPERTIVE ON RUN-UP BEFORE DEPARTURE. CAUSE OF PROBLEM WAS A DEFECTIVE ALTERNATOR. REPLACED THE ALTERNATOR AND CHECKED THE CHARGING SYSTEM, OK. 1 L 7 2 3O A7CE 2001020600098 20010206 00098 SW 2001 2 6 20000808SH003 1 20000522 G 6730 41002979103 SLEEVE TEXTRON BELL 407 407 SW BYPASS SPOOL CONTAMINATED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 617AL 1331 HR811 53265 ATTEMPTED TAKEOFF, COLLECTIVE LEVER MOVEMENT WAS RESTRICTED. TAKEOFF ABORTED, COLLECTIVE SERVO REPLACED. SHOP INSPECTI ON REVEALED SERVO BYPASS SPOOL WAS BINDING IN BYPASS SPOOL SLEEVE. THIS CAUSED PRIMARY CONTROL SPOOL HYDRAULIC NULL TO SHIFT LIMITING SERVO ACTUATOR MOVEMENT. SPOOLS AND SLEEVE CONTAMINATED WITH SOME TYPE OF COATING. THIS COATING COULD N OT BE SEEN, BUT WAS WASHED OFF. NORMAL SPOOLS AND SLEEVE OPERATION RESTORED. CAUSE UNKNOWN. (X) 1 G 7 1 3U O H2SW 2001020600099 20010206 00099 SW 2001 2 6 20000808SH004 1 20000608 G 6322 407062021101 DUCT BELL 407 407 SW OIL COOLER CRACKED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 917AL 787 53381 UPON DAILY INSPECTION, CRACKS IN CORNERS CAUSED BY INHERENT VIBRATIONS. (X) 1 G 7 1 3U O H2SW 2001020600100 20010206 00100 SW 2001 2 6 20000808SH005 1 20000703 G 6310 406340102101 SEAL BELL 407 407 SW CAP ASSY LEAKING A ALGA K NONE O OTHER IN INSP/MAINT 1 SW 03 917AL 907 A4747 53381 DURING DAILY INSPECTION, FOUND LEAKING, NO OBVIOUS DEFECTS. (X) 1 G 7 1 3U O H2SW 2001020600101 20010206 00101 SW 2001 2 6 20000808SH006 1 20000705 G 6510 206061432121 HOUSING BELL 407 407 SW T/R DRIVESHAFT CRACKED A ALGA K NONE O OTHER IN INSP/MAINT 1 SW 03 917AL 130 A318 53381 DURING DAILY INSPECTION, HOUSING IS CRACKED AND BEARINGS ARE ROUGH. (X) 1 G 7 1 3U O H2SW 2001020600102 20010206 00102 SW 2001 2 6 20000808SH007 1 20000705 G 6510 407340339103 BEARING BELL 407 407 SW T/R DRIVESHAFT ROUGH A ALGA K NONE O OTHER IN INSP/MAINT 1 SW 03 917AL 130 A318 53381 DURING DAILY INSPECTION, HOUSING IS CRACKED AND BEARINGS ARE ROUGH. (X) 1 G 7 1 3U O H2SW 2001020600103 20010206 00103 SW 2001 2 6 20000808SH008 1 20000703 G 6322 407062021101 DUCT BELL 407 407 SW OIL COOLER CRACKED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 917AL 120 53381 UPON DAILY INSPECTION, CRACKS IN CORNERS CAUSED BY INHERENT VIBRATIONS. (X) 1 G 7 1 3U O H2SW 2000091400125 20000914 00125 CE 2000 9 14 20000808SH010 1 20000611 G 3233 508202085 NUT BEECH 100 100BEECH 1152916 CE NOSE GEAR STRIPPED I VNWA O OTHER O OTHER LD LANDING 1 SO 15 11JJ 1918 B2 THE NET ASSEMBLY, P/N 90-820015-1, INSTALLED IN NOSE LANDING GEAR ACTUATOR, P/N 50-820208-5, WAS FOUND VOID OF THREADS C AUSING THE NOSE GEAR TO FAIL TO EXTEND. REQUIRED OVERHAUL IS 8,000 CYCLES, PART HAD 2,516 CYCLES SINCE OVERHAUL. (X) 1 L 7 2 3T A14CE 2000091400126 20000914 00126 2000 9 14 20000808SH011 4 20000725 G 2300 CM358950 SWITCH AMF CESSNA 441 441 2076020 CE AVIONICS BURNED A VE7A O OTHER B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 WP 07 988AE 441075 SWITCH FAILED INTERNALLY CAUSING SMOKE IN THE COCKPIT. DUE TO THE FACT THE SWITCH WAS AT FAULT, IT DID NOT TRIP AND CON TINUED TO SMOKE UNTIL SHUT OFF BY THE PILOT. (X) 1 L 7 2 3T RT A28CE 2000091400128 20000914 00128 CE 2000 9 14 20000808SH014 1 20000712 G 3242 06900400 PIN PARKERHANFIN CESSNA 402 402C 207590R CE BRAKE SYSTEM DESTROYED D O OTHER O OTHER LD LANDING 1 EA 01 771EA 402C0046 ON LANDING, AFT BRAKE LOCKED UP, AND MAIN WHEEL SEIZED. MAINTENANCE FOUND ONE CALIPER ANCHOR PIN SHEARED. REMOVED AND REPLACED MAIN WHEEL ASSY, BRAKE CALIPER, AND BRAKE BACKPLATE ASSY, THEN RETURNED AIRCRAFT TO SERVICE. AT THIS TIME, ALL ANCHOR PINS ARE BEING CHANGED IN THE OPERATOR''S FLEET. (X) 1 L 7 2 3O A7CE 2000091400129 20000914 00129 CE 2000 9 14 20000808SH015 1 20000727 G 7120 J124532 MOUNT CESSNA 210 210M 2073450 CE LT FORWARD MISSING A FPIA K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 15 7660E 21062692 PART MANUFACTURED DEFECT. MISSING REINFORCEMENT WASHER ON UPPER HALF. (X) 1 H 7 1 3O 3A21 2000092100019 20000921 00019 CE 2000 9 21 20000808SH016 1 20000327 G 2497 WIRE CESSNA 182 182Q 2072732 CE ALT BREAKER SHORTED H A UNSCHED LANDING H B ELECT. POWER LOSS-50 PC SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 WP 05 735MS 1917 18265536 PILOT WAS FORCED TO LAND DUE TO SMOKE IN COCKPIT. INSP REVEALED ALTERNATOR POWER WIRE (WIRE NR PB-10) FROM ALT TO THE A LT OUTPUT CIRCUIT BREAKER TO BE HEAT DAMAGED. WIRE IS AN EIGHT-GAUGE SHIELDED WIRE WITH ALTERNATOR OUTPUT POWER IN THE CENTER CONDUCTOR AND THE SHIELDING GROUNDED TO AIRFRAME GROUND. FOR AN UNKNOWN REASON, SHIELDING CHAFED THROUGH TO POWE R CONDUCTOR AND CAUSED A DIRECT SHORT TO GROUND. APPROX 6 INCHES OF THE WIRE SHOWED DAMAGE, INSULATION MELTED OFF BETWE EN POWER CONDUCTOR AND SHIELDING AND MUCH OF THE SHIELDING MISSING DUE TO ARCING. DAMAGED SECTION OF WIRE REPLACED WITH MIL-W-22759/16-8, AND SHIELDING INSPECTED ADJACENT TO DAMAGED AREA. NO OTHER CHAFING OR DEFECTS NOTED. (X) 1 H 7 1 3O NT 3A13 2000091400135 20000914 00135 CE 2000 9 14 20000808SH017 1 20000724 G 7120 505401033 RIVET CESSNA 421 421C 2076016 CE OUTBOARD FRETTED D K NONE O OTHER IN INSP/MAINT 1 CE 01 942SW 4609 421C1025 DURING ROUTINE INSPECTION, LOOSE RIVETS WERE FOUND IN THE TOP PLATE CURBED AREA AFT OF THE ENGINE IN BOTH MOUNT BEAMS OF LEFT ENGINE. SOME RIVET HEADS HAD FRETTED INTO THE SURFACE OF THE PLATE. THE SUSPECTED CAUSE WOULD BE A VIBRATION IN THIS AREA. AN ENGINEERING APPROVED REPAIR WAS MADE AND AIRCRAFT RETURNED TO SERVICE. (X) 1 L 7 2 3O A7CE 2000091400136 20000914 00136 CE 2000 9 14 20000808SH018 1 20000724 G 7160 515402031 RIVET CESSNA 421 421C 2076016 CE INBOARD FRETTED A K NONE O OTHER IN INSP/MAINT 1 CE 01 942SW 4609 421C1025 DURING ROUTINE INSPECTION, LOOSE RIVETS WERE FOUND IN THE TOP PLATE CURBED AREA AFT OF THE ENGINE IN BOTH MOUNT BEAMS OF LEFT ENGINE. SOME RIVET HEADS HAD FRETTED INTO THE SURFACE OF THE PLATE. THE SUSPECTED CAUSE WOULD BE A VIBRATION IN THIS AREA. AN ENGINEERING APPROVED REPAIR WAS MADE AND AIRCRAFT RETURNED TO SERVICE. (X) 1 L 7 2 3O A7CE 2000092100020 20000921 00020 CE 2000 9 21 20000808SH019 1 20000131 G 3010 1H374 CHECK VALVE CESSNA 310 310R 2074245 CE ENGINE COMPART FAILED B DINR K NONE O OTHER IN INSP/MAINT 1 EA 13 90FC 705 310R1838 DURING ROUTINE MAINTENANCE, DISCOVERED 2 UNSERVICEABLE CHECK VALVES, PN''S 1H37-4, FOR THE PNEUMATIC DEICE SYSTEM. BOTH VALVES HAVE 21 MONTHS AND 705.1 HOURS SINCE NEW. THESE VALVES CALL FOR YEARLY INSPECTIONS STARTING AT 5 YEARS FROM NEW THOUGH 10 YEARS REPLACEMENT. THE MANUFACTURER HAS BEEN NOTIFIED AND ONE VALVE HAS BEEN SENT FOR THEIR EVALUATION. (X) 1 L 7 2 3O 3A10 2001020600104 20010206 00104 SW 2001 2 6 20000808SH020 1 20000718 G 6310 406340102101 SEAL BELL 407 407 SW FREEWHEEL UNIT LEAKING B EH1R K NONE O OTHER IN INSP/MAINT 1 EA 13 175P 106 A4504 53316 REPLACED ORIGINAL SEAL AT 383.1 HOURS SINCE NEW. REPLACED SECOND SEAL AFTER 106.1 HOURS. (X) 1 G 7 1 3U O H2SW 2001020600108 20010206 00108 EU 2001 2 6 20000808SH022 1 20000721 G 3340 G62504 MOTOR SNIAS 350 AS350B3 8680954 EU SEARCH LIGHT INOPERATIVE B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 52281 15 3249 SEARCH LIGHT UNIT INOPERATIVE. FAILED TO EXTEND. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001020600109 20010206 00109 NM 2001 2 6 20000808SH023 1 20000519 G 6230 900R3101001107 BEARING DOUG MD900 MD900 3027375 NM MAIN ROTOR DEBONDED B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 901CF 746 90000012 MAIN ROTOR BEARING ASSY DEBONDING. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U NC H19NM 2001020700207 20010207 00207 NM 2001 2 7 20000808SH024 1 20000519 G 6230 900R3101001107 BEARING DOUG MD900 MD900 3027375 NM MAIN ROTOR DEBONDED B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 901CF 752 90000012 MAIN ROTOR CENTER BEARING ASSEMBLY DEBONDING. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U NC H19NM 2001020700190 20010207 00190 NM 2001 2 7 20000808SH025 1 20000628 G 6230 900C2010183107 LINK DOUG MD900 MD900 3027375 NM DRIVE SCISSORS WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 901CF 283 90000012 HINGE AND SHIMS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U NC H19NM 2001020700208 20010207 00208 EU 2001 2 7 20000808SH026 1 20000623 G 2450 430121402 HARNESS BOLKMS 117 BK117A4 5626017 EU ELECTRICAL SYS SHORTED B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 118LF 512 7137 CABLE, ELECTRICAL, AFT HAD INTERNAL SHORT. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U H13EU 2000091400141 20000914 00141 CE 2000 9 14 20000808SH028 1 20000720 G 7820 14550171 BRACE CESSNA 337 337F 2075725 CE CONT O360 IO360C 17025 SO LOWER TUBE LOOSE D K NONE O OTHER IN INSP/MAINT 1 WP 23 793DS 4294 33701376 60466R DURING INSPECTION, P/N 1455017-1 AND P/N 1455017-2 BRACE ASSYS WERE FOUND CHAFING ON THE PN 629671A2 OIL SUMP. THE P/N 1555001-1 MUFFLER CAN MOVE FWD AND AFT DUE TO ENG VIBRATION AS THERE ARE NO DOWL PINS IN P/N 1555001-1 CLAMPS TO MAINTAI N POSITION OF MUFFLER. SUBMITTER RECOMMENDED UPGRADING MUFFLER SYS TO DUAL MUFFLERS LIKE FRONT ENGINE INSTALL OF THIS A CFT, OR AT LEAST THE INSTALL OF DOWL IN P/N 1555002-1 CLAMPS. THIS IS THE THIRD OCCURRANCE ON THE ACFT IN THE LAST 5 YE ARS. (X) 1 H 7 2 3O 3 O A6CE E1CE 2000091400142 20000914 00142 CE 2000 9 14 20000808SH029 1 20000720 G 7820 14550172 BRACE CESSNA 337 337E 2075721 CE CONT O360 IO360C 17025 SO LOWER TUBE CHAFED B K NONE O OTHER IN INSP/MAINT 1 WP 23 793DS 4294 33701376 60466R DURING INSPECTION, P/N 1455017-1 AND P/N 1455017-2 BRACE ASSYS WERE FOUND CHAFING ON THE PN 629671A2 OIL SUMP. THE P/N 1555001-1 MUFFLER CAN MOVE FWD AND AFT DUE TO ENG VIBRATION AS THERE ARE NO DOWL PINS IN P/N 1555001-1 CLAMPS TO MAINTAI N POSITION OF MUFFLER. SUBMITTER RECOMMENDED UPGRADING MUFFLER SYS TO DUAL MUFFLERS LIKE FRONT ENGINE INSTALL OF THIS A CFT, OR AT LEAST THE INSTALL OF DOWL IN P/N 1555002-1 CLAMPS. THIS IS THE THIRD OCCURRANCE ON THE ACFT IN THE LAST 5 YE ARS. (X) 1 H 7 2 3O 3 O A6CE E1CE 2000091400144 20000914 00144 CE 2000 9 14 20000808SH030 1 20000724 G 2460 70H10A DIODE BEECH 99 C99 1154006 CE ELECTRICAL BUSS SHORTED A TIMA K NONE O OTHER IN INSP/MAINT 1 NM 07 239AL U239 DIODE 70 H10 A - 4 EACH IN A/C ELEC BUSS SYS. 2 EACH LEFT, 2 EACH RIGHT WHICH CONTROL ANNUNCIATOR PANEL AND SOME ENGINE S PLUS LANDING GEAR. FOUND 2 EACH DIODES SHORTED OUT ON RIGHT SIDE, NO SHORTS FOUND IN ELECTRICAL SYSTEM. (X) 1 L 7 2 3T A14CE 2000101000354 20001010 00354 CE 2000 10 10 20000808SH031 1 20000707 G 3220 358250545 ARM BEECH 99 99 1154002 CE BELOW COCKPIT LOOSE A TIMA O OTHER O OTHER NR NOT REPORTED 1 NM 07 24BH 25936 U67 NOSE STEERING REPORTED LOOSE AND INSPECTION REVEALED NOSE STEERING TORQUE ARM HOLE TO ACTUATOR ELONGATED. REPLACED NOSE STEERING TORQUE ARM WITH SERVICEABLE ARM. THE ELONGATION COULD HAVE BEEN PREVENTED WITH THE ADDITION OF SHIMS BETWEEN THE CLEVIS ARM AND THE ROD END OF THE ACTUATING ROD. (X) 1 L 7 2 3T A14CE 2000101000355 20001010 00355 CE 2000 10 10 20000808SH032 1 20000707 G 3220 5052432519 ARM BEECH 99 99 1154002 CE PILOTS RIGHT WORN A TIMA O OTHER O OTHER IN INSP/MAINT 1 NM 07 24BH 25936 U67 NOSE STEERING WAS REPORTED TO BE LOOSE. INSPECTION REVEALED RUDDER PEDAL ARM PIVOT HOLES ELONGATED. REPLACED RUDDER AR M ASSY WITH NEW COMPONENT AND NEW HARDWARE AS NECESSARY. LACK OF LUBRICATION IN THIS AREA POSSIBLY ACCELERATED THE WEAR OF THE PIVOT HOLES. THE BE99 MM DOES NOT SPECIFICALLY REFERENCE THIS PARTICULAR AREA FOR LUBRICATION. (CHAP 12). MAI NT DEPT HAS BEEN USING EITHER LPS 2 OR 3. (X) 1 L 7 2 3T A14CE 2000101000356 20001010 00356 SW 2000 10 10 20000809SH001 1 20000725 G 3230 560028951 BRACKET MOONEY M20 M20J 5870219 SW CRACKED B K NONE O OTHER IN INSP/MAINT 1 EA 23 4182H 2458 240656 DURING ANNUAL INSPECTION, THE LEFT RETRACT (LANDING GEAR) SPRING BRACKET WAS FOUND CRACKED AT THE SPRING ATTACH HOLE. B RACKET WAS REPLACED. (X) 1 L 7 1 3O 2A3 2000101000357 20001010 00357 NE 2000 10 10 20000809SH002 2 20000713 G 8520 10992 ROD AIRTRC AT400 AT401 0390204 SW PWA R1340 R1340AN1 52016 NE MASTER ROD FRACTURED G A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CR CRUISE 1 WP 21 4508Y 447 4010751 ZP102256 DURING AGRICULTURAL SPRAYING OPERATION, NR 7 ROD ASSY FAILED FORCING AIRCRAFT TO EMERGENCY LANDING AND SUBSEQUENT SUBSTA NTIAL AIRCRAFT DAMAGE. REF: ACCIDENT REPORT NR LAX00LA271. (X) 1 L 7 1 3R 3 R A17SW 5E2 2000101000358 20001010 00358 SO 2000 10 10 20000809SH003 1 20000714 G 2810 462056 FUEL CAP PIPER PA28 PA28181 7102807 SO GASKET TORN B FQAS K NONE O OTHER IN INSP/MAINT 1 WP 07 910PA 28 2843300 THESE GASKETS APPEAR NOT TO BE COMPATIBLE WITH 100LL FUEL. ALSO COMPOSITION IS WEAK MATERIAL. SOFT AND BREAKS EASY. S UBMITTER STATED OTHERS ON FLEET HAVE SAME PROBLEM. (X) 1 L 7 1 3O 2A13 2000101000359 20001010 00359 SO 2000 10 10 20000809SH004 2 20000801 G 7414 6324 MAGNETO PIPER PA34 PA34220T 7103420 SO CONT O360 TSIO360E 17025 SO LEFT FAILED B O OTHER R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 CE 07 4128M 645 3449068 321449 TEST RUN SHOWED MAGNETO TO BE DEAD. REMOVED AND DISASSEMBLED MAGNETO. FOUND WIPER TAB FOR DISTRIBUTOR GEAR TO BE SHEAR ED OFF OF GEAR. (X) 1 L 7 2 3O 3 O A7SO E9CE 2000101000360 20001010 00360 SO 2000 10 10 20000809SH005 1 20000709 G 2810 462056 GASKET PIPER PA28 PA28181 7102807 SO LT GAS CAP TORN C FQAS K NONE O OTHER IN INSP/MAINT 1 WP 07 917PA 20 2843306 GASKET TEARS AFTER A SHORT USAGE. TIME, APPROXIMATELY 2 WEEKS USAGE. (X) 1 L 7 1 3O 2A13 2000101000361 20001010 00361 SO 2000 10 10 20000809SH006 1 20000713 G 2810 462056 FUEL CAP PIPER PA28 PA28181 7102807 SO GASKET SWOLLEN C FQAS K NONE O OTHER IN INSP/MAINT 1 WP 07 923PA 21 2843277 THESE GASKETS APPEAR NOT TO BE COMPATIBLE WITH 100LL FUEL. THE MATERIAL USED CONTINUED TO SWELL AND RIP AFTER ONLY A SH ORT PERIOD OF TIME. (X) 1 L 7 1 3O 2A13 2000101000362 20001010 00362 GL 2000 10 10 20000809SH007 1 20000605 G 2900 6658531 LINE NAMER T6 SNJ5 6400418 GL RT L/G WELL FRACTURED H K NONE K FLUID LOSS IN INSP/MAINT 1 GL 23 62724 43724 ALUMINUM LINE FRACTURED (SPLIT) APPROXIMATELY .50 INCH IN LENGTH LONGITUDINALLY NEXT TO UNION. CAUSE UNKNOWN. (X) 1 L 7 1 3R A2575 2000111500001 20001115 00001 SO 2000 11 15 20000809SH008 1 20000711 G 2810 462056 GASKET PIPER PA28 PA28181 7102807 SO RT FUEL CAP TORN C FQAS K NONE K FLUID LOSS IN INSP/MAINT 1 WP 07 926PA 25 284389 AFTER SHORT PERIOD OF USE, GASKET HAD DETERIORATED AND TORN. SUBMITTER STATED HAVING SEEN NUMEROUS CASES OF THIS IN FLE ET OF ARCHER III''S. (X) 1 L 7 1 3O 2A13 2000111500002 20001115 00002 SO 2000 11 15 20000809SH009 1 20000707 G 2810 462056 GASKET PIPER PA28 PA28181 7102807 SO RT FUEL CAP TORN C FQAS K NONE K FLUID LOSS IN INSP/MAINT 1 WP 07 928PA 25 2843298 AFTER SHORT PERIOD OF USE, GASKET HAD DETERIORATED AND TORN. SUBMITTER STATED HAVING SEEN NUMEROUS CASES OF THIS IN FLE ET OF ARCHER III''S. (X) 1 L 7 1 3O 2A13 2000111500003 20001115 00003 SO 2000 11 15 20000809SH010 1 20000610 G 2810 462056 GASKET PIPER PA44 PA44180 7104402 SO FUEL CAP TORN C FQAS K NONE O OTHER IN INSP/MAINT 1 WP 07 971PA 11 4496031 GASKET TEARS AND BREAKS APART AFTER A FEW TIMES OPENING THE GAS CAP. (X) 1 L 7 2 3O A19S0 2000111500004 20001115 00004 EA 2000 11 15 20000809SH011 2 20000613 G 7323 210624V GOVERNOR BEECH 99 B99 1154004 CE PWA PT6 PT6A28 EA HARTZL HCB3T HCB3TN3 GL OVERSPEED LEAKING E TIMA O OTHER K FLUID LOSS IN INSP/MAINT 1 NM 07 99TH 35110 U155 RIGHT ENGINE LEAKING OIL AT FRONT SECTION. PROBLEM DETERMINED TO BE CRACKED HOUSING ON AUTOFEATHER DUMP SOLENOID. REPL ACED ENTIRE OVERSPEED GOVERNOR WITH SERVICEABLE OVERSPEED GOVERNOR. PART POSSIBLY CRACKED AS A RESULT OF MATING TWO UNE VEN SURFACES. (X) 1 L 7 2 3T 4 T A14CE E4EA 6 C P15EA 2000111500005 20001115 00005 SO 2000 11 15 20000809SH012 1 20000616 G 2710 62701123 CONTROL CABLE PIPER PA28 PA28181 7102807 SO FRAYED B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 4122F 2342 2843118 LEFT AILERON BALANCE CABLE FRAYED LOCATED UNDER THE REAR SEATS. (X) 1 L 7 1 3O 2A13 2000111500006 20001115 00006 SO 2000 11 15 20000809SH013 1 20000719 G 2740 62701080 CONTROL CABLE PIPER PA34 PA34220T 7103420 SO FRAYED B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 4128X 1165 3449112 LOWER AFT STABILATOR DOWN CONTROL CABLE FRAYED AT FRAME ASSEMBLY, STA 222.43. (X) 1 L 7 2 3O A7SO 2000111500007 20001115 00007 SO 2000 11 15 20000809SH014 1 20000713 G 2710 62701123 CONTROL CABLE PIPER PA28 PA28181 7102807 SO FRAYED B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 4130W 1345 2843204 RIGHT AILERON BALANCE CABLE FRAYED LOCATED UNDER THE REAR SEATS. (X) 1 L 7 1 3O 2A13 2000111500008 20001115 00008 SO 2000 11 15 20000809SH015 1 20000710 G 2740 62701080 CONTROL CABLE PIPER PA34 PA34220T 7103420 SO FRAYED B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 4142N 990 3449128 LOWER AFT STABILATOR DOWN CONTROL CABLE FRAYED LOCATED AT STA 222.43. (X) 1 L 7 2 3O A7SO 2000111500009 20001115 00009 SO 2000 11 15 20000809SH016 1 20000705 G 2710 62701123 CONTROL CABLE PIPER PA28 PA28181 7102807 SO FRAYED B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 4149Y 1741 2843128 LEFT AILERON BALANCE CABLE FRAYED, LOCATED UNDER THE REAR SEATS. (X) 1 L 7 1 3O 2A13 2000111500010 20001115 00010 SO 2000 11 15 20000809SH017 1 20000705 G 2710 62701123 CONTROL CABLE PIPER PA28 PA28181 7102807 SO FRAYED B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 4161Z 2141 2843129 LEFT AILERON BALANCE CABLE FRAYED. LOCATED UNDER THE REAR SEATS. (X) 1 L 7 1 3O 2A13 2000111500011 20001115 00011 SO 2000 11 15 20000809SH018 1 20000719 G 2710 62701123 CONTROL CABLE PIPER PA28 PA28181 7102807 SO FRAYED B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 4163W 1541 2843127 LEFT AILERON BALANCE CABLE FRAYED, LOCATED UNDER THE REAR SEATS. (X) 1 L 7 1 3O 2A13 2000111500012 20001115 00012 SO 2000 11 15 20000809SH019 1 20000715 G 2740 62701080 CONTROL CABLE PIPER PA34 PA34220T 7103420 SO FRAYED B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 4177R 2193 3449046 LOWER AFT STABILATOR DOWN CONTROL CABLE FRAYED AT FRAME ASSEMBLY, STA 222.43. (X) 1 L 7 2 3O A7SO 2000111500013 20001115 00013 SO 2000 11 15 20000809SH020 1 20000719 G 2710 62701123 CONTROL CABLE PIPER PA28 PA28181 7102807 SO FRAYED B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 9299B 2141 2843116 LEFT AILERON BALANCE CABLE FRAYED, LOCATED UNDER THE REAR SEATS. (X) 1 L 7 1 3O 2A13 2000111500014 20001115 00014 SO 2000 11 15 20000809SH021 1 20000630 G 2740 62701080 CONTROL CABLE PIPER PA34 PA34220T 7103420 SO FRAYED B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 9299E 1942 3449043 LOWER AFT STABILATOR DOWN CONTROL CABLE FRAYED AT FRAME ASSY, STA 222.43. (X) 1 L 7 2 3O A7SO 2000081000141 20000810 00141 SO 2000 8 10 20000809SH022 1 20000725 G 2710 62701123 CONTROL CABLE PIPER PA28 PA28181 7102807 SO UND REAR SEAT FRAYED B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 4132D 1144 2843234 RIGHT AILERON BALANCE CABLE FRAYED. LCOATED UNDER THE REAR SEATS. (X) 1 L 7 1 3O 2A13 2000081000142 20000810 00142 SO 2000 8 10 20000809SH023 1 20000725 G 2710 62701123 CONTROL CABLE PIPER PA28 PA28181 7102807 SO UND REAR SEAT FRAYED B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 4144P 1943 2843121 RIGHT AILERON BALANCE CABLE FRAYED. LOCATED UNDER THE REAR SEATS. (X) 1 L 7 1 3O 2A13 2000081000143 20000810 00143 SO 2000 8 10 20000809SH024 1 20000724 G 2740 62701080 CONTROL CABLE PIPER PA34 PA34220T 7103420 SO LOWER AFT FRAYED B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 4123C 1640 3449042 LOWER AFT STABILATOR DOWN CONTROL CABLE FRAYED. FRAYING OCCURRED AT STA 222.43. (X) 1 L 7 2 3O A7SO 2000081000144 20000810 00144 SO 2000 8 10 20000809SH025 1 20000724 G 2710 62701126 CONTROL CABLE PIPER PA34 PA34220T 7103420 SO WING ROOT PULLY FRAYED B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 4142N 1041 3449128 RIGHT AILERON BALANCE CABLE FRAYED AT WING ROOT PULLEY. (X) 1 L 7 2 3O A7SO 2000111500015 20001115 00015 CE 2000 11 15 20000809SH026 1 20000727 G 2842 S33312 TRANSMITTER CESSNA 172 172S 2072439 CE LT FUEL CELL DEFECTIVE D O OTHER O OTHER IN INSP/MAINT 1 NM 03 789EP 768 172S8135 LEFT FUEL QTY WENT TO EMPTY, LT LOW FUEL ANNUNCIATOR LIGHT ILLUMINATED IN-FLIGHT. MAINT FOUND THE FUEL QTY TRANSMITTER I NOP. WHEN XMITTER REMOVED FROM FUEL CELL, THE FLOAT AND RETAINER WASHER ON OTBD END OF THE FLOAT ARM WERE MISSING. FUE L CELL OPENED AND THE FLOAT AND WASHER RETRIEVED. SUBMITTER STATED FUEL QTY XMITTER MFG INCORRECTLY, WIRE ARM THAT RUNS THRU FLOAT WAS NOT CRIMPED ON EITHER SIDE OF THE FLOAT DURING MFG ALLOWING IT TO FALL OFF THE ARM. FOUND LT AND RT FUE L QTY XMITTERS INSTALLED BACKWARDS IAW CESSNA C-172R/S PM. THE S3331-2 TRANSMITTER IS REQUIRED TO BE INSTALLED IN THE R T FUEL CELL AND THE S3331-1 XMITTER IS REQUIRED TO BE INSTALLED IN THE LT FUEL CELL. BOTH TRANSMITTERS REPLACED. (X) 1 H 7 1 3O NT 3A12 2000111500016 20001115 00016 CE 2000 11 15 20000809SH027 1 20000714 G 2410 31M22045 SUPPORT BRACKET CESSNA 206 206H 2073301 CE LYC O540 IO540AC1A5 EA POWERPLANT INCORRECT H O OTHER W INADEQUATE Q C IN INSP/MAINT 1 AL 05 7254H 498 20608036 L2688948A DURING ROUTINE INSPECTION, FOUND THE ALTERNATOR BELT DRIVE SUPPORT MISALIGNED WITH THE ALTERNATOR PULLEY CAUSING THE BEL T TO SLIP PARTIALLY OFF OF THE ALTERNATOR PULLEY. FURTHER INVESTIGATION DETERMINED THE INCORRECT STARTER RING GEAR SUPP ORT, PN 31M22045, WAS INSTALLED WHICH POSITIONED THE BELT SUPPORT FWD OF THE ALTERNATOR DRIVE PULLEY. SUBMITTER STATED THE INCORRECT PART WAS INSTALLED AT THE FACTORY DURING PRODUCTION. (X) 1 H 7 1 3O 3 O RT A4CE 1E4 2000111500017 20001115 00017 CE 2000 11 15 20000809SH028 1 20000714 G 2914 9148D27 PUMP CESSNA 208 208 2073702 CE EMERGENCY SYS LEAKING H O OTHER K FLUID LOSS NR NOT REPORTED 1 AL 05 1273E 87 20800319 EMERGENCY GEAR HAND PUMP SEEPING HYDRAULIC FLUID. DETERMINED METAL SHAVINGS PRODUCED DURING ACTUATOR PRODUCTION HAD LOD GED UNDER AN O-RING. NO GALLING OR DAMAGE WAS FOUND INSIDE THE ACTUATOR. DEBRIS REMOVED AND NEW SEALS INSTALLED. (X) 1 H 7 1 3T NT A37CE 2000111500018 20001115 00018 CE 2000 11 15 20000809SH029 1 20000801 G 5740 50110231 FITTING CESSNA 414 414A 2075907 CE AFT WING ATTACH CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 05 414FC 5076 414A0039 EXTENSIVE INTERGRANULAR CORROSION FOUND ON THE BOTTOM OF THE UPPER AFT WING ATTACH FITTING ON THE LEFT WING. THE SAME F ITTING ON THE RIGHT WING STUB WAS CORRODED TO A LESSER DEGREE. MOISTURE ENTRAPMENT IS BELIEVED TO CONTRIBUTE. (X) 1 L 7 2 3O A7CE 2000111500019 20001115 00019 SO 2000 11 15 20000809SH030 2 20000718 G 8520 539937 SUMP BEECH 95 95B55 1152729 CE CONT O470 IO470L 17026 SO CRACKED B BXSA K NONE K FLUID LOSS IN INSP/MAINT 1 EA 09 931E 223 TC1009 1553646L FOUND THE SUMP CRACKED, CENTER FORWARD SECTION. CRACK OVERALL LENGTH, 2.75 INCHES. TWO SHORT SPUR CRACKS CAME OFF THE MAIN CRACK. (X) 1 L 7 2 3O 3 O RT 3A16 3E1 2000112900001 20001129 00001 2000 11 29 20000810SH001 4 20000801 G 2562 CIR10 ELT BEECH 60 A60 1153604 CE CABIN INOPERATIVE H K NONE O OTHER IN INSP/MAINT 1 WP 23 811DN P224 ALKALINE BATTERY PACK LEAKED AND CORRODED ELT MONITOR. REPLACED ELT WITH NEW ELT NOT REQUIRING A LITHIUM BATTERY PACK. (X) 1 L 7 2 3O A12CE 2000081800082 20000818 00082 WP 2000 8 18 20000810SH002 1 20000712 G 6410 369D2161531 BLADE HUGHES 369 369E 4470707 WP TAIL ROTOR CRACKED D O OTHER O OTHER IN INSP/MAINT 1 WP 07 504MP 6195 0022220312 O523E PILOT FOUND TAIL ROTOR BLADE ROOT FITTING CRACKED ON A PRE-FLIGHT INSPECTION. THIS IS THE SECOND OCCURRENCE ON THIS AIR CRAFT. THE LAST BLADE, S/N 009999-1489, ONLY TWO SERIAL NUMBERS DIFFERENCE. (X) 1 G 7 1 3U H3WE 2000081800083 20000818 00083 WP 2000 8 18 20000810SH003 1 20000309 G 6410 369D2161531 BLADE HUGHES 369 369E 4470707 WP TAIL ROTOR CRACKED D O OTHER O OTHER IN INSP/MAINT 1 WP 07 504MP 5700 0022220312 O523E CRACKED BLADE WAS FOUND ON POST-FLIGHT AFTER THE PILOT FELT AN IN-FLIGHT VIBRATION. THE TAIL ROTOR BLADE WAS CRACKED FR OM THE INBOARD ROOT FITTING, 1.5 INCHES LONG WITH A 90-DEGREE TURN FOR ANOTHER .5 INCH. (X) 1 G 7 1 3U H3WE 2000112900002 20001129 00002 SO 2000 11 29 20000810SH009 1 20000802 G 3242 RFS2010 STATOR BFGOODRICH EMB 120 EMB120 3260201 SO NR 1 POSITION DEFECTIVE B XC4R K NONE O OTHER IN INSP/MAINT 1 SO 19 1050 0478A BRAKE ASSEMBLY, P/N 2-1585-R, FAILED PREMATURELY. NR 1 STATOR IS EXCESSIVELY WARPED. HEAT STACK WARPED AND UNEVEN WEAR . SUBMITTER STATED THIS IS A CONTINUAL DISCREPANCY. NOTE: RAPCO FLEET SUPPORT PARTS INSTALLED IN BRAKE ASSEMBLY. (X) 2 L 7 2 4T RT A31SO 2000081800087 20000818 00087 NE 2000 8 18 20000810SH014 1 20000731 G 2612 7630607902103 DETECTOR SKRSKY S76 S76C 8143008 NE RT FWD ENG COMPT FAILED A N9WA K NONE N FALSE WARNING AP APPROACH 1 EA 11 986AH 760438 ISP - WHILE ON APPROACH, NR 2 ENGINE FIRE WARNING ACTIVATED FOR APPROXIMATELY 2 SECONDS. WARNING ACTIVATED AGAIN APPROX IMATELY 2 MINUTES LATER, STAYED ON FOR APPROXIMATELY 2 MINUTES AND WENT OUT BY ITSELF. THERE WERE NO CONFIRMING ENGINE INDICATIONS. LANDED NORMALLY. REPLACED RIGHT FORWARD FLAME DETECTOR IAW S-76 MM 26-11-01. OPS CHECKED NORMAL. (X) 1 G 7 2 3U NC H1NE 2000081800088 20000818 00088 NE 2000 8 18 20000810SH015 1 20000713 G 2612 473205 DETECTOR SKRSKY S76 S76C 8143008 NE LT AFT ENG COMPT FAILED A N9WA O OTHER O OTHER IN INSP/MAINT 1 EA 11 986AH 760438 CDW - WHILE ON GROUND FOR APPROXIMATELY 5 TO 7 MINUTES, NR 1 ENGINE FIRE DETECTOR ACTIVATED. REPLACED NR 1 ENGINE AFT F LAME DETECTOR, SYSTEM OPS CHECKED NORMAL. (X) 1 G 7 2 3U NC H1NE 2000112900003 20001129 00003 CE 2000 11 29 20000810SH019 1 20000723 G 2810 3189 ADAPTER CESSNA 182 182Q 2072732 CE WING FUEL CAPS INADEQUATE D K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 08 759HT 18266013 AS SUPPLIED WITH THE STC NR SA2326NM, THE DOCUMENTED INSTRUCTIONS, AND DRAWINGS ARE LIMITED IN SCOPE AND POOR IN DETAILS . THE PART USES A SIMPLE SYSTEM TO SECURE THE ADAPTER TO THE ORIGINAL LARGE SIZE FUEL CAP OPENING WITH THE SELF-LOCKING SINGLE LUG ANCHOR NUTS (SIMILAR TO NAS1025-3). THE SINGLE LUG HAS TWO HOLES IN IT AS MANUFACTURED AND IN APPEARANCE, I T IS EASY TO INSTALL THE CAP ADAPTER ASSEMBLY WITH THE ROLL PINS INSTALLED THROUGH THE INSIDE HOLE OF THIS PLATE. SUBMI TTER STATED IF THIS ERROR IS MADE, THE ADAPTER MAY EASILY BE DISLODGED, AND AIRCRAFT FUEL MAY BE LOST IN-FLIGHT CAUSING ENGINE STOPPAGE. (X) 1 H 7 1 3O NT 3A13 2000112900005 20001129 00005 2000 11 29 20000811SH001 4 20000810 G 6113 SPINNER CESSNA CESSNA 150 150M 2071830 CE CONT O200 O200* 17020 SO CRACKED C O OTHER O OTHER IN INSP/MAINT 1 NM 01 SPINNER BACKING PLATE HAS CRACKS RADIATING FROM THE BOLT HOLE AREAS. AN UNAUTHORIZED REPAIR WAS MADE.THE REPAIR WAS MAD E BY MAKING A CIRCULAR FLAT SHEET METAL SAME THICKNESS AS THE ORIGIANL MATERIAL,THEN RIVETED TO THE BACKING PLATE. BOLT HOLES WERE DRILLED AT THE CORRECT LOCATION. IT WAS NOT CONCENTRICALLY ROUND AND IT WAS NOT CENTERED TO THE BACKING PLA TE. THE PLATE WAS OUT OF BALANCE. AFTER A NEW ONE WAS INSTALLED, THE OWNER REPORTS A MUCH SMOOTHER ENGINE-PROPELLER PE RFORMANCE. PART TIME UNKNOWN. OWNER INDICATES THAT ANOTHER 150 IS FLYING WITH THE SAME REPAIR. 1 H 7 1 3O 3 O 3A19 E252 2000112900006 20001129 00006 SO 2000 11 29 20000811SH002 1 20000809 G 2910 LINE PIPER PA42 PA42720 7104212 SO LEAKING B A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CL CLIMB 1 GL 15 31GA 425501009 AFTER TAKEOFF THE LANDING GEAR WOULD NOT PROPERLY RETRACT AND RED FLUID WAS SEEN EXITING RT ENGINE/WING AREA. CREW RETU RNED TO BASE. HYD LEAK FOUND UNDER THE ENGINE NACELLE TO WING ROOT FAIRING. CAUSED BY AN EXCESSIVELY LONG FAIRING SCRE W WHICH HAD CHAFED AND PENETRATED THE ALUMINUM HYDRAULIC LINE. A NEW LINE WAS FABRICATED, PRESSURE TESTED, INSTALLED, A ND OPERATIONALLY TESTED. LINE WAS REROUTED SLIGHTLY AND CORRECT PANEL SCREWS INSTALLED. AS A PRECAUTION, INSPECTED THE LINES IN THE LEFT WING ROOT AND FOUND TWO CHAFED HYDRAULIC LINES WHICH WERE REPLACED. SUBMITTER RECOMMENDED INBOARD WI NG LEADING EDGE BE REMOVED PERIODICALLY TO INSPECT THE INSTALLATION OF ALL HYDRAULIC, DEICE, AND ELETRICA. 1 L 7 2 4T A23SO 2000112900007 20001129 00007 SO 2000 11 29 20000811SH003 1 20000725 G 7603 MS203651032C NUT PIPER PA46 PA46350P SO LYC O540 TIO540AE2A 41532 EA THROTTLE FAILED B JAVR O OTHER O OTHER IN INSP/MAINT 1 NE 01 526JM 1 1 4622166 RL10599 INSTALLED LYCOMING FACTORY REBUILT ENGINE IAW PIPER PA-46-310/350 MM 71-00-00, PG 19-22(A) (8). SECURED ENGINE CONTROL WITH SELF-LOCKING NUTS PER PIPER PRACTICES. AFTER LANDING, ON FIRST FLIGHT, THROTTLE CONTROL WAS LOST DUE TO LOSS OF HA RDWARE AT THROTTLE TO INJECTOR CONTROL. MS20365-1032C SELF-LOCKING NUT BACKED OFF AND LOST. CASTLE NUT/COTTER KEY AND BOLT INSTALLED ON THROTTLE, MIXTURE AND PROPELLER GOVERNOR. (X) 1 L 7 1 3O 3 O RT A25SO E14EA 2000112900008 20001129 00008 SO 2000 11 29 20000811SH004 1 20000609 G 3221 4032700 TRUNNION PIPER PA31 PA31350 7103110 SO CRACKED B QE5R K NONE O OTHER IN INSP/MAINT 1 NM 07 THE MAIN LANDING GEAR TRUNNION WAS BROUGHT TO THIS STATION FOR INSPECTION AND POSSIBLE REPAIR. THE TRUNNION HAD DEVELOP ED A CRACK ALONG THE BARREL AND NEXT TO THE FORGING SEAM. THE OWNER OF THIS TRUNNION HAD TAKEN IT TO A LOCAL WELDING SH OP AND HAD IT WELDED. WELDING SHOP HAD NO APPROVED DATA TO PERFORM ANY WELDING ON THIS COMPONENT, THEREFORE, THE COMPON ENT WAS REJECTED. IN ADDITION, REPAIRS WERE ACCOMPLISHED BY AN UNAUTHORIZED FACILITY. (X) 1 L 7 2 3O A20SO 2000120700006 20001207 00006 CE 2000 12 7 20000811SH005 1 20000717 G 3222 998201213 GEAR BEECH 99 C99 1154006 CE DRAG BRACE DEFECTIVE A TIMA K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 07 236AL U236 THE PART WAS ORDERED NEW FROM BEECHCRAFT WITH THE TOP HOLES DRILLED INCORRECTLY. THE TOP LEFT HOLE IS SUPPOSED TO BE 1. 75 INCHES AND IT WAS DRILLED ON THIS UNIT 1.50 INCHES. (X) 1 L 7 2 3T A14CE 2000111500021 20001115 00021 SW 2000 11 15 20000811SH006 1 20000811 G 3222 TRUNNION SPARTN 7W 7W 8430302 SW CASTING BROKEN D O OTHER O OTHER LD LANDING 1 GL 25 17613 12 LEFT LANDING GEAR DEPARTED UPON LANDING. STRUT ASSY BROKE FROM TRUNNION, LEFT WING TIP IMPACTED RUNWAY, DIRECTIONAL CON TROL LOST. POROUS CASTING, INADEQUATE. (X) 1 L 7 1 3R TC628 2000111500023 20001115 00023 CE 2000 11 15 20000811SH007 1 20000727 G 7120 J124532 MOUNT CESSNA 210 210L 2073448 CE LT FORWARD DEFECTIVE A FPIA K NONE O OTHER IN INSP/MAINT 1 SO 15 2437S 21061281 PART LABELLED/MANUFACTURED WRONG. NOTICED LT FORWARD ENGINE MOUNT SAGGING. UPON FURTHER INSPECTION, FOUND PART LABELLE D ''TOP FORWARD MTG'', BUT DID NOT HAVE REINFORCEMENT WASHER BUILT IN. CHECKED ALL OTHER P/N J-12453-2 MOUNTS IN STOCK, ALL LABELLED ''TOP FORWARD MOUNTING'' AND HAVE REINFORCEMENT WASHER BUILT IN. (X) 1 H 7 1 3O 3A21 2000111500024 20001115 00024 EA 2000 11 15 20000811SH009 2 20000811 G 7421 PLUG CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA FAILED D O OTHER R PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 NM 08 734QM 17269031 L317676 ENGINE DOES NOT HAVE T-MOD\ WHEN CHANGING VALVE COVERS. FOUND LYC PN LW-LW15316 EXHAUST (GASKETS) VALVE CAP LAYING IN B OTTOM OF VALVE COVER, LIFTER P/N LW-16586, WAS NOT PUMPED UP WITH OIL AND WAS BLED DOWN. THIS MAY HAVE ALLOWED THE CAP TO FALL OUT. ENGINE DID HAVE 3 BROKEN SPARK PLUGS. RHM-40E CERAMIC INSERTS WERE BROKEN LOOSE AND ENGINE RUN ROUGH AT S TART-UP, BUT THEN SMOOTHED UP SOMEWHAT. SUBMITTER DID NOT SUSPECT A LIFTER PROBLEM. (X) 1 H 7 1 3O 3 O NT 3A12 E274 2000111500025 20001115 00025 CE 2000 11 15 20000811SH010 1 20000724 G 3233 ROD END BEECH BEECH 58 58P 1152744 CE RT RETRACT ROD WORN H K NONE O OTHER IN INSP/MAINT 1 NM 11 133Z T367 DURING LANDING GEAR INSPECTION, PORTION OF PHASE INSPECTION, AN AMOUNT OF BRASS SHAVINGS WERE OBSERVED UNDER THE RT MAIN GEAR BRAKE ASSY ROD END WHERE IT ATTACHES TO THE ACTUATOR ASSY. THE ROD END WAS DISCOVERED TO BE SEVERELY WORN. BOTH (ACTUATOR END) ROD ENDS WERE REPLACED AND OPS CHECK GOOD. (X) 1 L 7 2 3O A23CE 2000111500026 20001115 00026 CE 2000 11 15 20000811SH011 1 20000724 G 2410 646655 COUPLING BEECH 58 58P 1152744 CE CONT O520 TSIO520LB 17040 SO RT ENG ALTERNATO SEPARATED H O OTHER H ELECT. POWER LOSS-50 PC IN INSP/MAINT 1 NM 11 120Z 990 TJ426 274308R UPON INVESTIGATION OF AN ALTERNATOR FAILURE, DISCOVERED THE ELASTOMER COUPLING HAD COME APART SENDING A LARGE AMOUNT OF RED RUBBER PARTICLES INTO THE ENGINE CRANKCASE AND OIL SYSTEM. THE OIL FILTER WAS INSPECTED AND FOUND TO BE CONTAMINATE D WITH THIS DEBRIS. THE ALTERNATOR WAS NOT SEIZED. THE ENGINE WAS REMOVED FOR TEAR DOWN, PROP, AND OIL LINES FLUSHES. ENGINE INSTALLED IN 1995. (X) 1 L 7 2 3O 3 O A23CE E8CE 2000111500027 20001115 00027 SO 2000 11 15 20000811SH012 2 20000721 G 7314 35328800 PUMP PIPER PA28 PA28181 7102807 SO CONT O360 TSIO360* 17025 SO FIREWALL DAMAGED B O OTHER O OTHER NR NOT REPORTED 1 GL 19 91075 288690021 PILOT REPORTED WHEN ELECTRIC FUEL WAS TURNED ON, THE ELECTRIC FUEL PUMP AND ALTERNATOR FIELD CIRCUIT BREAKERS TRIPPED. INSPECTED FUEL PUMP AND FOUND LEAD-IN WIRE TO ELECTRIC PUMP HAD PULLED OUT OF HOUSING AND WAS SHORTING TO GROUND. (X) 1 L 7 1 3O 3 O 2A13 E9CE 2000122900002 20001229 00002 EA 2000 12 29 20000811SH013 2 20000724 G 8530 74541 EXHAUST VALVE AMRGEN AA5 AA5B 3960105 SO LYC O360 O360A4K 41514 EA VALVE HEAD CRACKED D O OTHER O OTHER NR NOT REPORTED 1 NE 03 28384 1052 AA5B0583 L2362336A EXHAUST VALVE BROKE ON NR 1 CYLINDER. HALF OF VALVE HEAD CAME OFF CAUSING DAMAGE TO NR 1 CYLINDER AND THEN BROKE INTO 3 PIECES. TWO PIECES LODGED IN THE MUFFLER. ONE SMALL PIECE TRAVELLED THROUGH THE INTAKE SYSTEM TO NR 4 CYLINDER WHERE IT DID DAMAGE TO THE HEAD AND PISTON, ALSO BREAKING THE LOWER SPARK PLUG. TWO SERVICEABLE CYLINDERS WERE INSTALLED ON T HE ENGINE. THE ENGINE WAS RUN FOR 1.5 HOURS WITH ALL GAUGE INDICATIONS NORMAL. A COMPRESSION TEST SHOWED NORMAL READIN GS OF NR 1 - 78, NR 2 - 74, NR 3 - 72, NR 4 - 79 AND THE AIRCRAFT WAS RETURNED TO SERVICE. (X) 1 L 7 1 3O 3 O A16EA E286 2000111500029 20001115 00029 EU 2000 11 15 20000811SH014 1 20000731 G 8100 58B19497 TANK SOCATA TB20 TB21 8680697 EU LYC O540 TIO540AB1A 41533 EA AT WELD CRACKED H K NONE K FLUID LOSS IN INSP/MAINT 1 EA 21 159DM 17 2005 L1041261A FOUND WELD AT TURBO BEND OF OIL DRAIN TANK CRACKED. UPON REMOVAL, TUBE CAME OUT OF TANK. LOOKING AT WELD, IT APPEARED TO BE A BAD WELD. SUBMITTER STATED THAT HAD THIS GONE UNDETECTED, IT COULD HAVE BEEN A DISASTER. (X) 1 L 7 1 3O 3 O RT A51EU E14EA 2000111500030 20001115 00030 2000 11 15 20000811SH016 4 20000627 G 6122 C210569 GOVERNOR WOODWARD DEFECTIVE B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 1481260K REVELVANT INDICATION INSIDE GOVERNOR BODY. (X) 2000111500031 20001115 00031 2000 11 15 20000811SH017 4 20000627 G 6122 210658 MOUNT WOODWARD LEAKING B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 1481058B INDICATION AROUND GOVERNOR BODY FACE. (X) 2000112900009 20001129 00009 2000 11 29 20000811SH018 4 20000622 G 6122 G210659 HOUSING WOODWARD BNORM BN2 BN2 1520202 EU DEFECTIVE B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 RELEVANT INDICATION ON GOVERNOR BODY. (X) 1 H 7 2 3O A17EU 2000112900010 20001129 00010 2000 11 29 20000811SH019 4 20000717 G 6122 4030064 HOUSING WOODWARD DEFECTIVE B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 RELEVANT INDICATION (PT/ET) ON TOP OF GOVERNOR BODY. (X) 2000112900011 20001129 00011 2000 11 29 20000811SH020 4 20000714 G 6122 211952 HOUSING WOODWARD BEECH 55 E55 1152732 CE CONT O520 TSIO520C 17040 SO DEFECTIVE B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 1451415N RELEVANT INDICATION ON SIDE OF GOVERNOR BASE. (X) 1 L 7 2 3O 3 O 3A16 E8CE 2000111500022 20001115 00022 GL 2000 11 15 20000811SH021 1 20000811 G 3230 BOLT AMTR LANCAR LANCAIR235 05626K4 GL NOSE GEAR MISALIGNED G O OTHER O OTHER LD LANDING 1 EA 09 67MW 118 95 NOSE GEAR ALIGNING STRAP BOLT CAUGHT ON NOSE GEAR DOOR PIVOT HINGE ASSEMBLY. RESULTED IN GEAR UP LANDING. (X) 1 L 7 1 3O RT EXPA 2000111500028 20001115 00028 CE 2000 11 15 20000811SH022 1 20000811 G 7160 589100287 DUCT BEECH 58 58 1152740 CE CRACKED C K NONE O OTHER IN INSP/MAINT 1 SO 11 286 TH1881 INLET DUCT, CRACKED OUT AT NUTPLATE AT FORWARD MIDDLE SCREW OF DOOR PN 58-910028-17 THAT IS ATTACHED TO THE INLET DUCT. NOTE: BOTH LEFT AND RIGHT ENGINES INLET DUCTS BROKEN AT THE SAME TIME. THE CAUSE COULD BE VIBRATION INDUCED BY THE AI R STREAM. SUBMITTER RECOMMENDED ADDING A FOURTH SCREW FOR DOOR TO LESSEN VIBRATION. (X) 1 L 7 2 3O 3A16 2000112900012 20001129 00012 2000 11 29 20000814SH001 4 20000714 G 6122 B210710 HOUSING BEECH 55 E55 1152732 CE DEFECTIVE B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 CTEXT RELEVANT INDICATION ON TOP OF GOVERNOR BODY. (X) 1 L 7 2 3O 3A16 2000112900013 20001129 00013 CE 2000 11 29 20000814SH002 1 20000727 G 2842 S33312 TRANSMITTER CESSNA 172 172S 2072439 CE LT FUEL CELL DEFECTIVE B O OTHER J WARNING INDICATION CR CRUISE 1 NM 03 789EP 768 172S8135 LEFT FUEL QUANTITY WENT TO EMPTY AND LT LOW FUEL ANNUNCIATOR LIGHT ILLUMINATED IN-FLIGHT. MAINT FOUND THE FUEL QUANTITY TRANSMITTER INOPERATIVE. WHEN THE XMITTER WAS REMOVED FROM FUEL CELL, THE FLOAT WAS MISSING ALONG WITH THE RETAINER WA SHER ON THE OTBD END OF THE FLOAT ARM. THE FUEL CELL WAS OPENED AND THE FLOAT AND WASHER RETRIEVED. FUEL QTY XMITTER M FG INCORRECTLY, THE WIRE ARM THAT RUNS THROUGH THE FLOAT WAS NOT CRIMPED ON EITHER SIDE OF THE FLOAT DURING MFG ALLOWING IT TO FALL OFF THE ARM. ALSO FOUND LT AND RT FUEL QTY XMITTERS INSTALLED BACKWARDS IAW CESSNA C-172R/S PARTS MANUAL. S331-2 TRANSMITTER IS REQUIRED TO BE INSTALLED IN THE RT FUEL CELL AND S331-1 XMITTER IN LT. REPLACED BOTH XMITTERS. 1 H 7 1 3O NT 3A12 2000112900014 20001129 00014 SO 2000 11 29 20000814SH003 1 20000814 G 7160 GASKET PIPER PA25 PA25235 7102504 SO LYC O540 O540B2B5 41532 EA INADEQUATE D K NONE O OTHER IN INSP/MAINT 1 SO 15 8785L 255471 L628440 THIS AIRCRAFT HAS THE SAME AIR FILTER AND LANDING LIGHT ASSY AS THE PA28140 150-150 WITH BAD GASKETS. SUBMITTER FEELS A D96-10-01-R1 SHOULD APPLY. (X) 1 L 7 1 3O 3 O 2A10 E295 2000112900015 20001129 00015 SO 2000 11 29 20000814SH004 1 20000716 G 5280 HINGE FITTING EMB 120 EMB120RT SO RMLG BROKEN B WVER K NONE O OTHER IN INSP/MAINT 1 EA 09 236AS 120049 RIGHT MAIN LANDING GEAR AFT INBOARD DOOR, AFT HINGE FITTING WAS FOUND BROKEN DURING C-CHECK INSPECTION. POSSIBLE CAUSE: FATIGUE. SUBMITTER RECOMMENDED REPLACING MONITOR AT REGULAR INTERVALS. (X) 2 L 7 2 4T RT A31SO 2000112900016 20001129 00016 SO 2000 11 29 20000814SH005 1 20000727 G 3242 1331317 STATOR BFGOODRICH EMB 120 EMB120 3260201 SO NR 2 POSITION DEFECTIVE B XC4R K NONE O OTHER IN INSP/MAINT 1 SO 19 1477 0185 BRAKE ASSEMBLY, PN 2-1661, FAILED PREMATURELY. NR 2 STATOR CRACKED AT RELIEF HOLES. HEAT STACK WARPED AND UNEVEN WEAR. SUBMITTER STATED THIS IS A CONTINUAL DISCREPANCY. NOTE: OEM PARTS INSTALLED IN BRAKE ASSEMBLY AND THE MOST RECENT B RAKE CONFIGURATION, P/N 2-1661. (X) 2 L 7 2 4T RT A31SO 2000112900017 20001129 00017 CE 2000 11 29 20000814SH006 1 20000727 G 7120 J124532 SHOCK MOUNT CESSNA 210 210 2073402 CE ENGINE MISMANUFACTURED A FPIA K NONE O OTHER IN INSP/MAINT 1 SO 15 PART LABELED/MANUFACTURED WRONG. PART LABELED ''''TOP FORWARD MOUNTING'''', BUT AT INSTALLATION, DID NOT HAVE REQUIRED REINFORCEMENT WASHER PUT IN AT MANUFACTURE. PART CURE DATE: 3/99. (X) 1 H 7 1 3O RT 3A21 2000112000001 20001120 00001 CE 2000 11 20 20000814SH012 1 20000725 G 7920 ENGINE BEECH 100 B100 1152919 CE GARRTT TPE331 TPE3316 01514 WP MAKING METAL H K NONE O OTHER IN INSP/MAINT 1 SW 99 3699B 740 100 BE107 P27219 DURING A PHASE INSPECTION, THE LEFT ENG OIL FILTER WAS FOUND TO HAVE EXCESSIVE METAL IN OIL FILTER. ANALYSIS ON OIL AND FILTER WAS COMPLETED. METAL WAS FOUND TO BE MAGNESIUM. (X) 1 L 7 2 4T 4 T A14CE E4WE 2000112000002 20001120 00002 EA 2000 11 20 20000814SH014 2 20000807 G 7260 3021459 SHAFT BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA ACCESSORY GRBX SHEARED E TVMA O OTHER O OTHER NR NOT REPORTED 1 EA 05 79GA 3715 BB556 PCE81261 FAR 135 OPERATOR HAD TO CONDUCT AN EMERGENCY LANDING DUE TO A LEFT ENGINE FAILURE. THE ENGINE WAS BEING MAINTAINED UNDE R THE MORE PROGRAM STC SE0000EN. THE ENGINE FAILED. TEAR-DOWN REPORT SHOWED THE ACCESSORY GEARBOX INPUT DRIVSHAFT AND DRIVESHAFT BEARINGS FAILED. THIS ENGINE EXCEEDED THE RECOMMENDED OVERHAUL TIME OF 3,000 HOURS BECAUSE IT WAS MAINTAINED UNDER THE MORE STC (3,714.9 HRS). (X) 1 L 7 2 4T 4 T A24CE E4EA 2000112000003 20001120 00003 EA 2000 11 20 20000814SH015 2 20000807 G 7260 3010674 BEARING BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA ACCESSORY GRBX SHEARED E TVMA O OTHER O OTHER NR NOT REPORTED 1 EA 05 79GA 3715 BB556 PCE81261 FAR 135 OPERATOR HAD TO CONDUCT AN EMERGENCY LANDING DUE TO A LEFT ENGINE FAILURE. THE ENGINE WAS BEING MAINTAINED UNDE R THE MORE PROGRAM STC SE0000EN. THE ENGINE FAILED. TEAR-DOWN REPORT SHOWED THE ACCESSORY GEARBOX INPUT DRIVSHAFT AND DRIVESHAFT BEARINGS FAILED. THIS ENGINE EXCEEDED THE RECOMMENDED OVERHAUL TIME OF 3,000 HOURS BECAUSE IT WAS MAINTAINED UNDER THE MORE STC (3,714.9 HRS). (X) 1 L 7 2 4T 4 T A24CE E4EA 2000112000004 20001120 00004 CE 2000 11 20 20000814SH016 1 20000814 G 6100 PROPELLER CESSNA 182 182S 2072701 CE MCAULY 3D36C B3D36C431 GL OIL SERVICE PLUG LEAKING B WIWR O OTHER K FLUID LOSS CR CRUISE 1 WP 07 7267Z 106 18280525 990085 PILOT/OWNER REPORTED OIL ON PROPELLER BLADES, WINDSHIELD. INSPECTION OF PROPELLER HUB FOUND RED DYE LEAKING FROM HUB SE RVICE PLUG. SUBMITTER STATED THIS IS THE SECOND 182S MCCAULEY PROPELLER WITH A LEAK FROM PLUG. ALSO, A CESSNA 206H MCC AULEY PROPELLER WAS NOTED AND REPAIRED. ALL AIRCRAFT HAD LESS THAN 160.0 HOURS SINCE NEW. NO GUIDE LINES HAVE BEEN EST ABLISHED FOR THIS PROP IN REGARDS TO ACCEPTABLE STANDARDS FOR RETURN TO SERIVCE CRITERIA. (X) 1 H 7 1 3O NT 3A13 5 C 2001011104170 20010111 04170 2001 1 11 20000816SH001 1 20000804 G 6410 31038382 BLADE GARRTT TPE331 TPE331* 01514 WP 3RD ROTOR ASSY DAMAGED B K NONE O OTHER IN INSP/MAINT 1 GL 19 NEW PART RECEIVED FROM HONEYWELL WITH DAMAGE ON ONE BLADE. LOT NR: 4,685. (X) 3 T E2WE 2000081800166 20000818 00166 EU 2000 8 18 20000816SH012 1 20000108 G 7720 430150102 THERMOCOUPLE BOLKMS 117 BK117A3 5626015 EU ENGINE SHORTED B R7MR O OTHER O OTHER IN INSP/MAINT 1 NM 07 117MV 7089 INTERNAL SHORT. REPLACED THERMOCOUPLE WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U H13EU 2000081800167 20000818 00167 NE 2000 8 18 20000816SH013 2 20000108 G 7240 430150601 SEAL BOLKMS 117 BK117A3 5626015 EU LYC LTS101 LTS101650B1 41560 NE NR 2 BEARING LEAKING B R7MR O OTHER O OTHER IN INSP/MAINT 1 NM 07 117MV 870 7089 LE45078EA SEAL LEAKING BEYOND SERVCIEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U 3 U H13EU E5NE 2000081800168 20000818 00168 NE 2000 8 18 20000816SH014 2 20000108 G 7240 430144801 SEAL BOLKMS 117 BK117A3 5626015 EU LYC LTS101 LTS101650B1 41560 NE NR 3 BEARING LEAKING B R7MR O OTHER O OTHER IN INSP/MAINT 1 NM 07 117MV 870 7089 LE45078EA SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U 3 U H13EU E5NE 2000081800169 20000818 00169 EU 2000 8 18 20000816SH015 1 20000108 G 7712 TUBE BOLKMS 117 BK117A3 5626015 EU LYC LTS101 LTS101650B1 41560 NE TORQUEMETER LEAKING B R7MR O OTHER O OTHER IN INSP/MAINT 1 NM 07 117MV 870 7089 LE45078EA TORQUEMETER FEED LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U 3 U H13EU E5NE 2000082100218 20000821 00218 NE 2000 8 21 20000816SH018 2 20000108 G 7250 411100720 SHROUD BOLKMS 117 BK117A3 5626015 EU LYC LTS101 LTS101650B1 41560 NE GAS PROD BINDING B R7MR O OTHER O OTHER IN INSP/MAINT 1 NM 07 117MV 7089 LE45078EA EXCESSIVE GP BLADE TIP RUB. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U 3 U H13EU E5NE 2000082100224 20000821 00224 NE 2000 8 21 20000816SH020 2 20000108 G 7240 410106701 RING BOLKMS 117 BK117A3 5626015 EU LYC LTS101 LTS101650B1 41560 NE FIRST TURBINE SH WORN B R7MR O OTHER O OTHER IN INSP/MAINT 1 NM 07 117MV 7089 LE45078EA SEAL RING WORN BEYOND SEVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U 3 U H13EU E5NE 2000082100225 20000821 00225 NE 2000 8 21 20000816SH021 2 20000406 G 7250 411100720 SHROUD BOLKMS 117 BK117A4 5626017 EU LYC LTS101 LTS101650B1 41560 NE GP TURBINE ROTOR BINDING B R7MR O OTHER O OTHER IN INSP/MAINT 1 NM 07 117CW 384 7125 LE45273EA EXCESSIVE GP BLADE TIP RUB. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U 3 U H13EU E5NE 2001020800968 20010208 00968 NE 2001 2 8 20000816SH022 2 20000406 G 7230 410115013 DIFFUSER BOLKMS 117 BK117A4 5626017 EU LYC LTS101 LTS101650B1 41560 NE ENGINE MISMANUFACTURED B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 117CW 7125 LE45273EA OUTER DIAMETER OF VANE SUPPORT RING IS TOO LARGE (10.221 INCHES). IMPROPER MANUFACTURE. REPLACED WITH NEW UNIT, CORREC TED PROBLEM. (X) 1 G 7 2 3U 3 U H13EU E5NE 2000112000005 20001120 00005 SO 2000 11 20 20000816SH023 1 20000807 G 2912 28108 HOUSING PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HYD FILTER CRACKED I WVBA O OTHER K FLUID LOSS IN INSP/MAINT 1 AL 01 27755 317852148 RL826861A PILOT REPORTED GEAR WOULD NOT CYCLE DOWN. GEAR WAS PUMPED DOWN MANUALLY. FLUID WAS OBSERVED LEAKING FROM LEFT HYDRAULI C FILTER HOUSING. HOUSING WAS REMOVED AND IT WAS DISCOVERED THAT THE LAST FEW THREADS ON THE HOUSING SIDE HAD CRACKED T HROUGH. HOUSING AND O-RING WERE REPLACED AND SYSTEM SERVICED AND FUNCTIONALLY TESTED. (X) 1 L 7 2 3O 3 O A20SO E14EA 2000112000006 20001120 00006 SO 2000 11 20 20000816SH025 2 20000725 G 8530 652451 PUSHROD CESSNA 180 180F 2072614 CE CONT O470 O470R 17026 SO PLUGGED D O OTHER W INADEQUATE Q C IN INSP/MAINT 1 NM 11 2163Z 190 18051263 815845R C/W TCM SB MSB00-5B, (REPLACING CRANKSHAFT), FOUND PUSH ROD TUBE FOR NR 6 EXHAUST VALVE PLUGGED. THIS APPARENTLY WAS MI S-MANUFACTURED. FROM THE VALVE END IN APPROXIMATELY .1250 INCH FOR AN ADDITIONAL .3750 INCH. THE TUBE IS SOLID, SO NO OIL MAY PASS THROUGH. THIS CAUSED MATERIAL FROM THE ROCKER ARM BUSHING TO TRANSFER TO THE ROCKER ARM SHAFT FROM LACK OF PROPER LUBRICATION. THIS NECESSITATED REPLACEMENT OF THE PUSH ROD, ROCKER ARM ASSY AND ROCKER ARM SHAFT. IT APPEARS T HAT IN MANUFACTURING, THE TUBE BECAME PLUGGED WHEN THE BALL END WAS INSTALLED. (X) 1 H 7 1 3O 3 O 5A6 E273 2000112000007 20001120 00007 CE 2000 11 20 20000816SH026 1 20000802 G 3210 40172 WHEEL BEECH 99 C99 1154006 CE CRACKED B TIMR K NONE O OTHER IN INSP/MAINT 1 NM 07 239AL U239 WHEEL HALF FOUND CRACKED DURING A ROUTINE INSPECTION. (X) 1 L 7 2 3T A14CE 2000112000008 20001120 00008 GL 2000 11 20 20000816SH027 3 20000731 G 6114 C4716C98 HUB CESSNA 188 188CESSNA 2073002 CE MCAULY 2A34C D2A34C98 GL 2ND & 3RD THREAD CRACKED B PI4R K NONE O OTHER IN INSP/MAINT 1 SO 07 983984 HUB, SN 950456, CRACKED ALL THE WAY THROUGH HUB AT 2ND AND 3RD THREAD IN BLADE SOCKET APPROXIMATELY 3.50 INCHES LONG. R ED DYE LEAKING FROM PROPELLER. CAUSE OF CRACK UNKNOWN. PROPELLER USED IN AG OPERATION. REPLACED HUB WITH SN 983984. (X) 1 L 7 1 3O A9CE 5 C P3EA 2000112000009 20001120 00009 GL 2000 11 20 20000816SH028 3 20000731 G 6114 D5904C90 HUB CESSNA 188 T188 2073011 CE MCAULY 3A32C D3A32C90 GL BLADE SOCKETS CRACKED B PI4R K NONE O OTHER IN INSP/MAINT 1 SO 07 7710026 PROPELLER CAME IN LEAKING RED DYE. ALL THREE BLADE RETENTION NUTS CRACKED AND HUB CRACKED IN NR 2 BLADE SOCKET. BLADE, SN K62431YS, HAD EXCESSIVE CORROSION IN BLADE THREADS (SCRAP). PROPELLER USED IN AG OPERATIONS. TWO GOOD BLADES RETUR NED TO CUSTOMER. EXACT CAUSE OF CRACK UNKNOWN. (X) 1 L 7 1 3O A9CE 5 C P21EA 2001030100003 20010301 00003 GL 2001 3 1 20000816SH029 3 20000731 G 6114 D6447C23 HUB MCAULY 2A36C 2A36C23 GL PROPELLER CORRODED B PI4R K NONE O OTHER IN INSP/MAINT 1 SO 19 821846 HUB, SN 673713, SCRAPPED DUE TO EXCESSIVE CORROSION THROUGHOUT (INSIDE/OUTSIDE) AND IN BLADE THREADS. HUB REPLACED WITH SN 821846. CAUSE OF EXCESSIVE CORROSION POSSIBLY AGE (DEFECTIVE HUB WAS 33 YEARS OLD). (X) 5 C P880 2001030100004 20010301 00004 GL 2001 3 1 20000816SH030 3 20000731 G 6111 BLADE HARTZL HC12X HC12X207 GL PROPELLER CORRODED B PI4R K NONE O OTHER IN INSP/MAINT 1 SO 07 6757N HUB (SN 6757N) AND BOTH BLADES (SN A2545 AND A3412) SCRAP DUE TO CORROSION. SUBMITTER STATED: CAUSE DUE TO NEGLECT OVE R THE LAST 53 YEARS. (X) 5 C P845 2000121800012 20001218 00012 GL 2000 12 18 20000816SH031 3 20000731 G 6114 C5480C66 HUB CESSNA 182 182J 2072722 CE MCAULY 2A34C 2A34C66 GL NR 2 HUB SOCKET CRACKED B PI4R K NONE O OTHER IN INSP/MAINT 1 SO 07 725308 HUB, SN 697045, CRACKED IN NR 2 HUB SOCKET ON BACK SIDE. RED DYE LEAKING FROM PROPELLER. CAUSE OF CRACK UNKNOWN. REPL ACED HUB WITH SN 725308. (X) 1 H 7 1 3O NT 3A13 5 C P3EA 2000121800013 20001218 00013 GL 2000 12 18 20000816SH032 3 20000731 G 6111 90DHA4 BLADE CESSNA 188 188CESSNA 2073002 CE MCAULY 2A34C B2A34C205 GL 2.50 INCHES/BUTT CRACKED B PI4R K NONE O OTHER IN INSP/MAINT 1 SO 07 841770 PROPELLER LEAKING RED DYE. TEAR-DOWN INSPECTION REVEALED BLADE CRACKED ALL THE WAY THROUGH INTO THE WEIGHT HOLE. DYE C OMING FROM BLADE PATCH. CAUSE UNKNOWN. PROPELLER USED IN AG OPERATION. (X) 1 L 7 1 3O A9CE 5 C P3EA 2001020700112 20010207 00112 EU 2001 2 7 20000816SH033 1 20000706 G 6220 365A31185802 ADAPTER AEROSP AS365 AS365N2 8680815 EU MAIN ROTOR TORN B ZYWA K NONE O OTHER IN INSP/MAINT 1 GL 09 365WM 6429 FREQUENCY ADAPTER, SN 17143, TORN. REMOVED AND REPLACED FREQUENCY ADAPTER PAIR. (X) 1 G 7 2 3U RT H10EU 2001020100036 20010201 00036 EU 2001 2 1 20000816SH034 1 20000706 G 6220 365A31185802 ADAPTER AEROSP AS365 AS365N2 8680815 EU MAIN ROTOR TORN A ZYWA K NONE O OTHER IN INSP/MAINT 1 GL 09 365WM 314 6429 FREQUENCY ADAPTER TORN. REMOVED AND REPLACED FREQUENCY ADAPTER PAIR. (X) 1 G 7 2 3U RT H10EU 2000121800014 20001218 00014 CE 2000 12 18 20000816SH035 1 20000726 G 3213 07416321 BUSHING CESSNA 182 182S 2072701 CE LT MLG DEFORMED C WIWR K NONE O OTHER IN INSP/MAINT 1 WP 07 321HW 163 18280264 DURING A ROUTINE INSPECTION OF THE AIRFRAME, THE LEFT MAIN LANDING GEAR BUSHING WAS FOUND DEFORMED. THE INSIDE BUSHING MATERIAL WAS PROTRUDING FROM THE EDGE OF THE BUSHING. THE BUSHING WAS FURTHER INSPECTED AFTER REMOVAL FROM THE AIRCRAFT AND CONTAINED STRESS CRACKS ALONG THE INSIDE OF THE BUSHING. POSSIBLE CAUSE WAS A DEFECTIVE BUSHING PRIOR TO INSTALLAT ION IN THE AIRCRAFT. SUBMITTER SUGGESTED BETTER QUALITY CONTROL AND NEW PARTS PRIOR TO INSTALLATION TO PREVENT RECURREN CE. (X) 1 H 7 1 3O NT 3A13 2000121800015 20001218 00015 CE 2000 12 18 20000817SH003 1 20000630 G 7920 17374 STRAINER CESSNA 414 414A 2075907 CE OIL LINE/WASTEGA RESTRICTED H K NONE O OTHER IN INSP/MAINT 1 WP 09 414P 10 414A0507 OIL STRAINER ELEMENT P/N EK9052V INSTALLED UNDER STC BY RAM WHEN AIRCRAFT WAS MODIFIED TO SERIES VII. ELEMENT PLUGS UP AND HAS NO BYPASS AND LIMITS OIL FLOW TO WASTEGATE AND AIRCRAFT DOES NOT DEVELOP FULL POWER ON TAKEOFF OR AT ALTITUDE. WITH NEW ELEMENT, AIRCRAFT OPERATES NORMAL. ELEMENT LASTS ONLY BETWEEN 5 TO 15 HOURS. (X) 1 L 7 2 3O A7CE 2000121800016 20001218 00016 NE 2000 12 18 20000817SH004 2 20000804 G 8530 116733CP CYLINDER DOUG DC3 DC3C 3021457 WP PWA R1830 R183092 52020 NE NR 1 CRACKED H E ENGINE SHUTDOWN R PARTIAL RPM/PWR LOSS CR CRUISE 1 SW 11 5831B 685 421008822 354578 WHILE EN ROUTE, LEFT ENGINE STARTED TO RUN ROUGH. PILOT FEATHERED PROPELLER AND SECURED ENGINE. AN UNEVENTFUL LANDING WAS MADE. MAINTENANCE FOUND NR 1 CYLINDER CRACKED. CYLINDER REPLACED WITH AN OVERHAULED UNIT. ENGINE GROUND RUN AND R ETURNED TO SERVICE. (X) 2 L 7 2 4R 4 R A669 5E4 2000121800017 20001218 00017 SO 2000 12 18 20000817SH005 2 20000719 G 8530 649168 CYLINDER CESSNA 310 310D 2074212 CE CONT O470 IO470D 17026 SO NR 2/EXH VLV FAILED G A UNSCHED LANDING R PARTIAL RPM/PWR LOSS TO TAKEOFF 1 NM 03 674FT 3668 935 39041 R7914200 LEFT ENGINE WOULD NOT DEVELOP FULL POWER AT TAKEOFF. AIRCRAFT CRASH LANDED DUE TO POOR PERFORMANCE. INSPECTION OF ENGI NE REVEALED THAT NR 2 CYLINDER HAD ''ZERO'' COMPRESSION. FURTHER INSPECTION REVEALED THE EXHAUST VALVE FACE WAS NOT SEA LING ON HALF OR MORE OF THE SURFACE OF THE VALVE SEAT. LAST ANNUAL INSPECTION C/W 11-12-99. COMPRESSION CHECK ALL CYLI NDERS NORMAL. ENGINE TIME SINCE MAJOR OVERHAUL, 934.7 HOURS. VALVE, EXHAUST P/N 646286. INSERT, EXHAUST VALVE SEAT, P /N 35967. (X) 1 L 7 2 3O 3 O 3A10 3E1 2000112900019 20001129 00019 NM 2000 11 29 20000817SH010 1 20000712 G 2730 35274001 HORN CHRIS HUSKY A1 221020X NM TAIL OF FUSELAGE MISALIGNED B AWKR O OTHER O OTHER IN INSP/MAINT 1 WP 25 8XJ 390 1388 P/N 50025 (AN3-5) BOLT AND P/N 53875 (AN 1115-21), CLEVIS ATTACHED TO THE ELEVATOR TRIM HORN LINE, P/N 3-5274-001, CHAFE D ON TAIL STRUCTURE TUBING. THE LINK SHOULD HAVE A JOGGLE BUILT IN TO DEFLECT THE TRIM CABLE INBOARD FOR CLEARANCE. AN TI-CHAFE TAPE WAS APPLIED. SUBMITTER STATED PER PHONE CALL TO AVIAT FACTORY, HORN LINK WAS BENT INWARD TO CLEAR FUSELAG E TUBING. (X) 1 H 7 1 3O NC A22NM 2000112900020 20001129 00020 GL 2000 11 29 20000817SH012 3 20000731 G 6114 HUB CESSNA 310 310J 2074226 CE MCAULY 2AF34C D2AF34C81 GL BLADE SOCKET CRACKED B M71R K NONE K FLUID LOSS IN INSP/MAINT 1 SW 15 3141L 310J0141 787504 HUB CRACKED IN BOTH THREADED BLADE SOCKETS. PROPELLER WAS LEAKING, IN FOR RE-SEAL. (X) 1 L 7 2 3O 3A10 5 C P5EA 2000112900022 20001129 00022 EU 2000 11 29 20000817SH014 1 20000808 G 8100 LW19107 LINK SOCATA TB20 TB21 8680697 EU LYC O540 TIO540AB1A 41533 EA TURBO END BROKEN H K NONE O OTHER IN INSP/MAINT 1 WP 23 678TB 23 1925 L1041161A LINK FOUND BROKEN; ANOTHER LINK FOUND BROKEN ON ANOTHER AIRCRAFT. (X) 1 L 7 1 3O 3 O RT A51EU E14EA 2000112900023 20001129 00023 EU 2000 11 29 20000817SH015 1 20000808 G 8100 LW19107 LINK SOCATA TB20 TB21 8680697 EU LYC O540 TIO540AB1A 41533 EA TURBO END BROKEN H K NONE O OTHER IN INSP/MAINT 1 WP 23 678TB 23 2005 L1041261A DURING 25-HOUR INSPECTION, FOUND BROKEN LINK. (X) 1 L 7 1 3O 3 O RT A51EU E14EA 2000112900024 20001129 00024 SO 2000 11 29 20000817SH016 2 20000817 G 8520 535661 CAMSHAFT CESSNA 206 U206F 2073333 CE CONT O520 IO520F 17032 SO MAKING METAL B CY4R K NONE O OTHER IN INSP/MAINT 1 AL 03 7138Q 1947 213 U20603074 247849R FERROUS MATERIAL FOUND IN OIL FILTER. ENGINE DIS-ASSEMBLED, PROBLEM FOUND TO BE FAILED CAMSHAFT AND LIFTER BODIES. (X) 1 H 7 1 3O 3 O A4CE E5CE 2000112900025 20001129 00025 SO 2000 11 29 20000817SH017 2 20000817 G 8520 535661 CAMSHAFT CESSNA 180 180 2072602 CE CONT O470 O470L 17026 SO MAKING METAL B CY4R K NONE O OTHER IN INSP/MAINT 1 AL 03 9269T 2039 80 50769 808530L4 FERROUS MATERIAL FOUND IN OIL FILTER. ENGINE DIS-ASSEMBLED, PROBLEM FOUND TO BE FAILED CHAMSHAFT AND LIFTER BODIES. (X ) 1 H 7 1 3O 3 O NC 5A6 E273 2000112900026 20001129 00026 2000 11 29 20000817SH018 4 20000801 G 6122 320268 HOUSING MCAULY CONT O520 TSIO520P 17040 SO MCAULY D3A34 D3A34C402 GL DEFLATED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 RELEVANT PT/ET INDICATION ON GOVERNOR BODY. (X) 3 O E8CE 5 C P47GL 2000112900027 20001129 00027 SO 2000 11 29 20000817SH019 1 20000809 G 3213 65319004 CYLINDER PIPER PA28 PA28151 7102805 SO LINK ATTACH, LOW CRACKED B K NONE O OTHER IN INSP/MAINT 1 CE 01 1195X 11100 287515324 DURING OTHER MAINTENANCE TO LANDING GEAR, THE TORQUE LINKS WERE REMOVED AND UPPER STRUT CYLINDER CLEANED. CRACKS WERE F OUND AT THE BOTTOM OF THE MACHINED AREA FOR THE TORQUE LINK ATTACHMENT BOTH SIDES. SUBMITTER SUSPECTED AGE IN HOURS AND NUMBER OF LANDINGS AS CAUSE. (X) 1 L 7 1 3O 2A13 2000112900028 20001129 00028 SO 2000 11 29 20000817SH020 2 20000606 G 8520 646623 CRANKSHAFT CESSNA 206 U206F 2073333 CE CONT O550 IO550* SO INADEQUATE B CY4R K NONE O OTHER IN INSP/MAINT 1 AL 03 61599 126 U20602350 284915 PER TCM MSB 00-5B, CRANKSHAFT WAS REJECTED BY TELEDYNE CONTINENTAL MOTORS. (X) 1 H 7 1 3O 3 O A4CE E3SO 2001011104171 20010111 04171 2001 1 11 20000817SH021 2 20000817 G 7322 HW6106019 CARBURETOR PRECISION SATURATED B FUXR O OTHER O OTHER IN INSP/MAINT 1 SO 09 CHAMBER OF FLOAT NEXT TO FULLRUN POINT IS APPROXIMATELY 75 PERCENT FULL OF AVGAS. THE CARBURETOR WAS SENT FOR OVERHAUL. FLOAT STICKING. SUBMITTER STATED THIS IS A RECURRING PROBLEM WITH THIS FLOAT AS THIS IS THE THIRD SUBMITTED BY THIS R EPAIR STATION. SUBMITTER RECOMMENDED RECALL OF THIS 30-800 FLOAT TO REMEDY THIS PROBLEM. (X) 2000082800180 20000828 00180 SO 2000 8 28 20000817SH022 2 20000817 G 8520 SA535661 CAMSHAFT CESSNA 182 182Q 2072732 CE CONT O470 O470S 17026 SO FAILED B K NONE O OTHER IN INSP/MAINT 1 AL 03 79JP 2142 118 18267081 469049 FERROUS MATERIAL FOUND IN OIL FILTER. ENGINE DISASSEMBLED, PROBLEM FOUND TO BE FAILED CAM AND LIFTER BODIES. (X) 1 H 7 1 3O 3 O NT 3A13 E273 2000082800181 20000828 00181 SO 2000 8 28 20000817SH023 2 20000222 G 7314 6482121 PUMP CESSNA 207 207A 2073604 CE CONT O520 IO520F 17032 SO LEAKING D K NONE K FLUID LOSS IN INSP/MAINT 1 AL 05 207DF 253 20700728 818805R FUEL PUMP FOUND LEAKING FUEL FROM SEAL AT THE DRIVE END OF PUMP HOUSING. (X) 1 H 7 1 3O 3 O A16CE E5CE 2000082800182 20000828 00182 CE 2000 8 28 20000817SH024 1 20000211 G 8011 643259A18 ADAPTER CESSNA 207 207 2073602 CE CONT O520 IO520F 17032 SO STARTER SLIPPED B O OTHER O OTHER NR NOT REPORTED 1 AL 05 207EX 171 20700100 812380R STARTER CLUTCH SLIPS. (X) 1 H 7 1 3O 3 O A16CE E5CE 2000082800183 20000828 00183 SO 2000 8 28 20000817SH025 2 20000712 G 8530 MILLENIUM CYLINDER CESSNA 150 150M 2071830 CE CONT O200 O200A 17020 SO FAILED D K NONE O OTHER IN INSP/MAINT 1 AL 03 45624 200 15076995 253134 DURING A 100-HOUR INSPECTION, FOUND THE MILLININUM CYLINDER ASSY WHICH WAS INSTALLED IN THE NR 3 POSITION WOULD ONLY HOL D A COMPRESSION OF 32 PSI AFTER 200 HOURS OF SERVICE. POSSIBLE CAUSE UNKNOWN AT THIS TIME. (X) 1 H 7 1 3O 3 O 3A19 E252 2000082800184 20000828 00184 SO 2000 8 28 20000817SH026 2 20000615 G 7322 BUSHING CONT CESSNA 207 207 2073602 CE CONT O520 IO520F 17032 SO THROTTLE SHAFT WORN H O OTHER Y ENGINE STOPPAGE TO TAKEOFF 1 AL 03 1581U 310 J179716AR 20700181 812349R AIRCRAFT HAD FUEL FLOW FLUCTUATIONS AND POWER SURGES (2-4 GPH). OCCURRED ON TAKEOFF AND WAS PROGRESSIVELY MORE NOTICEAB LE AS ENGINE WARMED UP. POSSIBLE CAUSE WAS THE BUSHINGS THAT THE THROTTLE SHAFT GOES THROUGH BEING WORN CAUSING PLAY IN THROTTLE TO MIXTURE ADJUSTMENT AND SUBSEQUENT CHANGES IN FUEL/AIR RATIO AND INDUCTION LEAKAGE THROUGH WORN BUSHINGS. ( X) 1 H 7 1 3O 3 O A16CE E5CE 2001020700125 20010207 00125 GL 2001 2 7 20000818SH001 2 20000524 G 7261 369A8010681 LINE HUGHES 369 369E 4470707 WP ALLSN 250C 250C20B 03013 GL PLENUM CHAMBER FAILED B ZR4R A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION NR NOT REPORTED 1 SO 11 91DK 151 0187E 835702 COMPRESSION FITTING PROVIDED WITH PLASTIC LINE FAILED IN ENGINE PLENUM CHAMBER AT FULL POWER DURING FLIGHT CAUSING OIL I NGESTION INTO ENGINE CAUSING TURBINE OUTLET TEMPERATURE AND TORQUE SURGE WHEN OIL IGNITED WITH FUEL AIR MIXTURE IN BURNE R CAN. FOUR QUART OIL SYSTEM, OIL REMAINING IN SYSTEM LESS THAN ONE PINT. PILOT ABLE TO SAFELY LAND MACHINE. STRONGLY SUGGEST METAL LINES IN PLENUM CHAMBER INSTEAD OF PLASTIC. MANUFACTURER IS AWARE OF PREVIOUS PROBLEMS WITH PLASTIC LINE S. (X) 1 G 7 1 3U 3 U H3WE E4CE 2000121800018 20001218 00018 SO 2000 12 18 20000821SH001 2 20000808 G 8530 646678 SEAL PIPER PA34 PA34200T 7103406 SO CONT O360 TSIO360EB 17025 SO INTAKE VALVE WORN H K NONE O OTHER IN INSP/MAINT 1 NM 08 1278H 372 347770118 372 HOURS TOTAL TIME SINCE NEW. RETAINER SPRINGS FELL OFF OF SEAL AND INTO THE OIL SYSTEM. NO DAMAGE CAUSED. THEY WER E CAUGHT IN OIL SCREEN. UPON REMOVAL OF VALVE COVERS AND VALVE SPRINGS, ALL SEALS WERE FOUND WORN AND SPRINGS READY TO WEAR THROUGH. (X) 1 L 7 2 3O 3 O A7SO E9CE 2000121800019 20001218 00019 NE 2000 12 18 20000821SH002 3 20000627 G 6111 6607132886 BLADE ROTOL R389 R3894123F25 NE ROOT END OUTER CRACKED B MS1R K NONE O OTHER IN INSP/MAINT 1 EA 27 25152 3194 DRG179287 PROPELLER RECEIVED FOR REPAIR WITH CUSTOMER COMPLAINT OF EXCESSIVE BLADE TIP MOVEMENT. DISASSEMBLED PROPELLER AND FOUND THAT BLADE, S/N 1193, HAD A CRACK 360 DEGREES AROUND OUTER SLEEVE ON ROOT END. BLADE REJECTED FROM SERVICE. (X) 6 C P30NE 2000082800187 20000828 00187 CE 2000 8 28 20000821SH003 1 20000808 G 5540 07126161 BULKHEAD CESSNA 182 182F 2072714 CE LT RUDDER CABLE CRACKED B K NONE O OTHER IN INSP/MAINT 1 SO 06 3171U 4039 18254571 DURING ANNUAL INSPECTION, CRACK FOUND UPPER PORTION OF LEFT RUDDER CABLE CUT OUT ON TAIL BULKHEAD. AD 72-07-09 CRACKS A ND LOOSE BOLTS RUDDER/FIN LAST C/W 4/94 AT ACFT TOTAL TIME 3,845 HOURS BY DYE PENETRANT AND VISUAL INSPECTION. NO DEFEC TS WERE NOTED AT THAT TIME. BULKHEAD REMOVED ALSO FOUND CRACK AT TIE-DOWN LOOP HOLE. POSSIBLE TAIL STRIKE FROM LANDING AND/OR WIND DAMAGE. (X) 1 H 7 1 3O NT 3A13 2000082800188 20000828 00188 SO 2000 8 28 20000821SH004 1 20000629 G 2434 COOLING FAN ELECTROSYS PIPER PA38 PA38112 7103812 SO BROKEN D K NONE O OTHER IN INSP/MAINT 1 EA 27 958SC 294 9070089 3878A0233 DURING 100-HOUR INSPECTION, NOTED ALL OF THE BLADES OF THE COOLING FAN HAD BROKEN FROM THEIR MOUNTING PLATE AND SEPARATE D FROM THE ALTERNATOR. ALTERNATOR WAS STILL PROPERLY FUNCTIONING. THE COOLING FAN BLADES WERE ATTACHED TO AN ALUMINUM PLATE. THE BLADES HAD BROKEN AT THE POINT THEY WERE WELDED TO THE PLATE. (X) 1 L 7 1 3O A18SO 2000082800189 20000828 00189 CE 2000 8 28 20000821SH005 1 20000628 G 7160 P198281 AIR FILTER CESSNA 172 172R 2072401 CE INDUCTION DETERIORATED D K NONE O OTHER IN INSP/MAINT 1 EA 27 4206K 300 17280751 AIR FILTER IS LISTED AS A 500-HOUR REPLACEMENT ITEM. AT 100-HOUR INSPECTION, MADE AT 300 HOURS, NOTED THE INSPECTION AT 200 HOURS AND THE INSPECTION AT 300 HOURS THE PAPER ELEMENT OF THE FILTER ASSY HAD BADLY ERODED ON APPROXIMATELY 40 PER CENT OF THE FORWARD FACING SURFACE TO A DEPTH THAT PENETRATED THE ACCORDIAN FOLDS OF THE PAPER. WHEN THE FILTER WAS HEL D UP TO THE LIGHT, IT APPEARED THE ELEMENT HAD LOST 40 PERCENT OF ITS FILTERING CAPACITY. THIS AIRCRAFT HAS BEEN USED F OR PRIMARY TRAINING AND RENTAL AND HAD BEEN OPERATED FROM PAVED FIELDS ONLY. SUBMITTER SUGGESTED INSPECTING ON A 50-HO UR INTERVAL. (X) 1 H 7 1 3O NT 3A12 2000082800190 20000828 00190 SO 2000 8 28 20000821SH007 1 20000804 G 3233 65319004 CYLINDER PIPER PA28 PA28151 7102805 SO ATTACH FLANGE ELONGATED B RMMR K NONE O OTHER IN INSP/MAINT 1 CE 01 1195X 11100 287515324 ON SEVERAL OCCASIONS DURING INSPECTIONS, THE LT LANDING GEAR TO WING SPAR CAP LOWER BOLTS WAS FOUND BROKEN, USUALLY ONE BOLT. LESS FREQUENTLY, AN UPPER BOLT COULD BE FOUND BROKEN. THE MOUNT HOLES IN BOTH THE SPAR CAPS AND GEAR CYLINDER WE RE FOUND ELONGATED. AIRCRAFT MANUFACTURER HAD NO AUTHORIZED REPAIR FOR THIS CONDITION. AIRCRAFT WAS REPAIRED BY DER AP PROVAL. FOR SEVERAL YEARS, THIS AIRCRAFT HAD MADE A TIGHT LEFT 180 DEGREE TURN INTO ITS PACKING AREA AS A TRAINING AIRC RAFT. (X) 1 L 7 1 3O 2A13 2000082800191 20000828 00191 SO 2000 8 28 20000821SH008 2 20000811 G 7414 6320 MAGNETO CESSNA 210 T210L 2073449 CE CONT O520 TSIO520R 17040 SO INTERNAL CORRODED B AI4R K NONE O OTHER IN INSP/MAINT 1 WP 09 94203 760 21060537 29358R PRESSURIZED SLICK MAGNETOS ON CESSNA T210L. DURING ANNUAL, INSPECTED MAGS INTERNALLY FOR CONDITION. FOUND SEVERE MOIST URE-CASED CORROSION ALL AROUND INSIDE. MAGNETO MANUAL CALLS FOR INSPECTION OF 6200 SERIES EACH 100 HOURS, NOTHING FOUND FOR INSPECTION OF 6300 SERIES. MANUAL SAYS TO CLEAN CORROSION AND RE-INSTALL. CORROSION SO EXTENSIVE, MAGS REPLACED. SLICK AD 88-25-04 ADDRESSES THIS PROBLEM, BUT THESE MAGS, 6320 SERIES, ARE NOT IN THE APPLICABILITY SECTION. SUBMITTER STATED AD SHOULD BE REVISED TO INCLUDE 6300 SERIES PRESSURIZED MAGNETOS. (X) 1 H 7 1 3O 3 O 3A21 E8CE 2000082800192 20000828 00192 SO 2000 8 28 20000821SH009 2 20000811 G 7414 6320 MAGNETO CESSNA 210 T210L 2073449 CE CONT O520 TSIO520R 17040 SO INTERNAL CORRODED B AI4R K NONE O OTHER IN INSP/MAINT 1 WP 09 94203 760 21060537 PRESSURIZED SLICK MAGNETOS ON CESSNA T210L. DURING ANNUAL, INSPECTED MAGS INTERNALLY FOR CONDITION. FOUND SEVERE MOIST URE-CASED CORROSION ALL AROUND INSIDE. MAGNETO MANUAL CALLS FOR INSPECTION OF 6200 SERIES EACH 100 HOURS, NOTHING FOUND FOR INSPECTION OF 6300 SERIES. MANUAL SAYS TO CLEAN CORROSION AND RE-INSTALL. CORROSION SO EXTENSIVE, MAGS REPLACED. SLICK AD 88-25-04 ADDRESSES THIS PROBLEM, BUT THESE MAGS, 6320 SERIES, ARE NOT IN THE APPLICABILITY SECTION. SUBMITTER STATED AD SHOULD BE REVISED TO INCLUDE 6300 SERIES PRESSURIZED MAGNETOS. (X) 1 H 7 1 3O 3 O 3A21 E8CE 2000082800193 20000828 00193 CE 2000 8 28 20000821SH010 1 20000814 G 2720 S100343A BEARING CESSNA 172 172R 2072401 CE COPILOT LT PEDAL LOOSE B VDNR K NONE O OTHER IN INSP/MAINT 1 SW 09 172GH 17280192 COPILOT''S LEFT RUDDER PEDAL FOUND EXCESSIVLEY LOOSE AT DUAL BRAKE TUBE DURING 100-HOUR INSPECTION. FURTHER INVESTIGATI ON REVEALED BEARING, PN S1003-43A, NOT INSTALLED. INSTALLED NEW BEARING. SUBMITTER SUSPECTED BEARING NOT INSTALLED AT FACTORY. AIRCRAFT TT: 1,398.2 HOURS. SUBMITTER STATED THIS IS THE SECOND TIME THIS CONDITION HAS BEEN NOTED AND REPOR TED. (X) 1 H 7 1 3O NT 3A12 2000082800194 20000828 00194 CE 2000 8 28 20000821SH011 1 20000803 G 5510 AN1767A BOLT BEECH 60 B60 1153605 CE HORIZ STABILIZER RUSTED D K NONE O OTHER IN INSP/MAINT 1 GL 05 7BB 1629 P402 DURING ANNUAL INSPECTION, FOUND THE HORIZONTAL STABILIZERS TO CREAK WHEN FORCED UP OR DOWN. DURING INVESTIGATION, NOTIC ED MOVEMENT IN THE AFT ATTACH FITTING FOR BOTH SIDES. REMOVED THE BOLTS FROM THEIR CLOSE TOLERANCE HOLES TO DISCOVER TH EY WERE TOO SHORT. THE DUKE PARTS CATALOG SHOWED THAT AN AN176-11A SHOULD BE INSTALLED. SUBMITTER VERIFIED THAT TO BE TRUE BASED ON LENGTH OF THE HOLE. PART REMOVED WAS AN AN176-7A AND SUBMITTER STATED THIS PART LOOKED TO BE A FACTORY IN STALLATION. (X) 1 L 7 2 3O A12CE 2000082800195 20000828 00195 SO 2000 8 28 20000821SH013 1 20000821 G 3245 TR67 TUBE PIPER PA28 PA28R200 7102811 SO SCHRADER VALVE LEAKING H K NONE O OTHER IN INSP/MAINT 1 GL 09 2311T 165 28R7135197 FAILURE OF SCHRADER VALVE ASSY ON GOODYEAR TUBE: 500-5 TR67 LY23930A MANUFACTURED SEP 25 1998. THE TUBE LOST PRESSURE - FAILED AT THE T LETTER STAMPING ON THE VALVE STEM ITSELF, THE STAMPING TOO DEEP INTO THE METAL VALVE STEM RESULTING IN COMPLETE AIR PRESSURE LOSS. (X) 1 L 7 1 3O 2A13 2000082800196 20000828 00196 SW 2000 8 28 20000825SH001 1 20000824 G 5320 590000001011 BRACKET MOONEY M20 M20K 5870220 SW LOWER BELLY FRACTURED H K NONE O OTHER IN INSP/MAINT 1 NM 01 1162D 1612 250730 DURING COURSE A OF ANNUAL INSPECTION, FOUND HAT SECTION P/N 590000-001/11 CRACKED. 1 L 7 1 3O 2A3 2000082800197 20000828 00197 SO 2000 8 28 20000825SH002 2 20000824 G 8520 631716 CRANKSHAFT CONT PIPER PA28 PA28150 7102804 SO CONT O520 TSIO520P 17040 SO FAILED G A UNSCHED LANDING Y ENGINE STOPPAGE CR CRUISE 1 EA 01 5256W 3054 1254 28276 513691 ENGINE FAILED AFTER TAKEOFF RESULTING IN FORCED LANDING. INSPECTION OF ENGINE REVEALED CRANKSHAFT FAILED BETWEEN THE NR 2 AND NR 3 JOURNALS. 1 L 7 1 3O 3 O 2A13 E8CE 2001011104195 20010111 04195 2001 1 11 20000825SH003 2 20000811 G 7322 30800 FLOAT PRECISION STUCK B K NONE R PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 SO 09 75059703 CARBURETOR FLOAT DEFECTIVE. THE TWO CHAMBERS CLOSEST TO THE FULCRUM ARE APPROXIMATELY 75 PERCENT FULL OF 100LL FUEL. THIS CREATED A STICKING FLOAT SYNDROME AND CAUSED EXTREMELY RICH CONDIITION. THE POSSIBLE CAUSE IS THE INTEGRITY OF THE WELD/GLUE OR WHATEVER IS BEING USED TO PLACE THE TOP ON THE FLOAT IS COMPROMISED CAUSING THE FUEL TO SEEP INTO THE FLO AT CHAMBERS. (X) 2000121800020 20001218 00020 CE 2000 12 18 20000825SH004 1 20000726 G 5752 58341206 HINGE CESSNA CESSNA 425 425 2076018 CE TRIM TAB AREA CRACKED B QB7R K NONE O OTHER IN INSP/MAINT 1 CE 07 0176 DURING INITIAL INSPECTION OF THE AILERON, A SLIGHT BUCKLING WAS OBSERVED IN THE UPPER HINGE AREA. UPON REMOVAL OF THE U PPER SKIN, A CRACK WAS DISCOVERED IN THE UPPER HINGE BRACKET AREA (P/N 5834120-6). THE CRACK EXTENDED FROM RIBS 5834110 -90 TO 5834110-98, WHICH WAS MEASURED AT 12.25 INCHES LONG. (X) 1 L 7 2 3T RT A7CE 2000121800021 20001218 00021 NM 2000 12 18 20000825SH005 2 20000801 G 7210 3588941 BEARING GULSTM 690TP 690 0141720 SW GARRTT TPE331 TPE3315251K NM TORQUE SENSOR FAILED H K NONE O OTHER IN INSP/MAINT 1 NM 05 CGFPP 2591 P598 11032 P06068 ENGINE DISASSEMBLED, INSPECTED, A BEARING IN THE DIRECT-DRIVE GEAR TRAIN FAILED. BEARING IS INSTALLED IN THE TORQUE SE NSOR ASSY. ALLIED SIGNAL SB 331-72-0360 ADDRESSES THIS BEARING BY OFFERING A BEARING WITH INCREASED FATIGUE LIFE. C/W THIS SB IS LISTED AS OPTIONAL. SB 33172-0555 SPECIFICALLY ADDRESSES THIS ISSUE BY REPLACING THE TORQUE SENSOR ASSY WITH AN IMPROVED UNIT. C/W THIS BULLETIN IS LISTED AS RECOMMENDED. ALLIED SIGNAL NOW REQUIRES ENGINES OPERATING TO THE EXT ENDED 5400 HR TBO, TO INCORPORATE THE MODIFICATIONS. THE FAILED TORQUES SENSOR INSTALLED IN 1989, SEE AD 95-16-08. (X) 1 H 7 2 3T 4 T 2A4 E2WE 2001021600019 20010216 00019 SO 2001 2 16 20000825SH006 1 20000818 G 3242 RFS2010 STATOR BFGOODRICH EMB 120 EMB120 3260201 SO BRAKE ASSY CRACKED B XC4R K NONE O OTHER IN INSP/MAINT 1 SO 19 1663 1405A BRAKE ASSY, P/N 2-1585-R, FAILED PREMATURELY. NR 1 AND NR 2 STATORS CRACKED AT RELIEF HOLES. HEAT STACK WARPED AND UNE VEN WEAR. SUBMITTER STATED THIS IS A CONTINUAL DISCREPANCY. NOTE: RAPCO FLEET SUPPORT PARTS INSTALLED IN BRAKE ASSY. (X) 2 L 7 2 4T RT A31SO 2001021600020 20010216 00020 SO 2001 2 16 20000825SH007 1 20000817 G 3242 RFS2010 STATOR BFGOODRICH EMB 120 EMB120 3260201 SO BRAKE ASSY CRACKED B XC4R K NONE O OTHER IN INSP/MAINT 1 SO 19 1674 0437A BRAKE ASSY, P/N 2-1585-R, FAILED PREMATURELY. NR 1 AND NR 2 STATORS CRACKED AT OUTER RELIEF HOLES. HEAT STACK WARPED A ND UNEVEN WEAR. SUBMITTER STATED THIS IS A CONTINUAL DISCREPANCY. NOTE: RAPCO FLEET SUPPORT PARTS INSTALLED IN BRAKE ASSY. (X) 2 L 7 2 4T RT A31SO 2001021600021 20010216 00021 SO 2001 2 16 20000825SH008 1 20000819 G 3242 RFS2010 STATOR BFGOODRICH EMB 120 EMB120 3260201 SO BRAKE ASSY CRACKED B XC4R K NONE O OTHER IN INSP/MAINT 1 SO 19 131 0393A BRAKE ASSY, P/N 2-1585, FAILED PREMATURELY. NR 1 STATOR CRACKED AT RELIEF HOLES. HEAT STACK WARPED AND UNEVEN WEAR. S UBMITTER STATED THIS IS CONTINUAL DISCREPANCY. NOTE: RAPCO FLEET SUPPORT PARTS INSTALLED IN BRAKE ASSEMBLY. (X) 2 L 7 2 4T RT A31SO 2001021600022 20010216 00022 SO 2001 2 16 20000825SH009 1 20000814 G 3242 RFS2010 STATOR BFGOODRICH EMB 120 EMB120 3260201 SO BRAKE ASSY CRACKED B XC4R K NONE O OTHER IN INSP/MAINT 1 SO 19 1948 0547A BRAKE ASSY, P/N 2-1585, FAILED PREMATURELY. NR 1 AND NR 2 STATORS CRACKED AT RELIEF HOLES. HEAT STACK WARPED AND UNEVE N WEAR. SUBMITTER STATED THIS IS A CONTINUAL DISCREPANCY. NOTE: RAPCO FLEET SUPPORT PARTS INSTALLED IN BRAKE ASSEMBL Y. (X) 2 L 7 2 4T RT A31SO 2001021600023 20010216 00023 SO 2001 2 16 20000825SH010 1 20000814 G 3242 RFS2010 STATOR BFGOODRICH EMB 120 EMB120 3260201 SO BRAKE ASSY CRACKED B XC4R K NONE O OTHER IN INSP/MAINT 1 SO 19 1326 0051A BRAKE ASSEMBLY, P/N 2-1585-R, FAILED PREMATURELY. NR 1 AND NR 2 STATORS CRACKED AT RELIEF HOLES. HEAT STACK WARPED AND UNEVEN WEAR. SUBMITTER STATED THIS IS A CONTINUAL DISCREPANCY. NOTE: RAPCO FLEET SUPPORT PARTS INSTALLED IN BRAKE AS SY. (X) 2 L 7 2 4T RT A31SO 2001021600024 20010216 00024 SO 2001 2 16 20000825SH011 1 20000817 G 3242 1331317 STATOR BFGOODRICH EMB 120 EMB120 3260201 SO BRAKE ASSY CRACKED B XC4R K NONE O OTHER IN INSP/MAINT 1 SO 19 981 1438A BRAKE ASEMBLY, P/N 2-1661, FAILED PREMATURELY. NR 1 AND NR 2 STATORS CRACKED AT RELIEF HOLES. HEAT STACK WARPED AND UN EVEN WEAR. SUBMITTER STATED THIS IS A CONTINUAL DISCREPANCY. NOTE: OEM PARTS INSTALLED IN BRAKE ASSY AND THE MOST REC ENT BRAKE CONFIGURATION, P/N 2-1661. (X) 2 L 7 2 4T RT A31SO 2001011100952 20010111 00952 2001 1 11 20000825SH012 1 20000825 G 2822 SHAFT DUKES LYC O540 IO540D4A5 41532 EA FUEL PUMP SHEARED B K NONE O OTHER IN INSP/MAINT 1 SO 25 5788 L402648 THE ELECTRIC FUEL PUMP WOULD RUN, BUT WOULD NOT PUMP FUEL. DURING DISASSEMBLY, FOUND ONE OF THE FOUR VANES MISSING, THE VANE HOUSING TO SHAFT RETAINING PIN HAD COME OUT, AND THE SHAFT HAD SHEARED. THE CONCERN IS THAT THERE IS NO FILTER OR SCREEN BETWEEN THE ELECTRIC PUMP AND THE ENGINE DRIVEN PUMP TO STOP THE DEBRIS FROM THE FAILED ELECTRIC PUMP CAUSING CAT ASTROPHIC DAMAGE TO THE ENGINE DRIVEN PUMP. SUBMITTER RECOMMENDED THAT CLOSE ATTENTION BE PAID TO THE PRESSURE OUT OF T HE ELECTRIC PUMP AND NOT TRUSTING SOLELY IN THE SOUND OF THE PUMP. ALSO, SOME TYPE OF SAFETY SHOULD BE INSTALLED TO PRE VENT ELECTRIC PUMP DEBRIS FROM MIGRATING TO THE ENGINE DRIVEN PUMP. (X) 3 O 1E4 2000112900029 20001129 00029 GL 2000 11 29 20000828SH002 3 20000727 G 6114 C23 HUB BEECH 45 A45 1152006 CE MCAULY 2A36C 2A36C23 GL CRACKED B FR6R K NONE K FLUID LOSS IN INSP/MAINT 1 NM 03 1500 802034 SUBMITTER STATED AT LAST ASSEMBLE, IMPROPER USE OF SILICONE WAS USED TO SEAL THREADS OF RETENTION NUT TO HUB. HUB SOCKE TS WERE BOTH CRACKED. EARLY CRACK DETECTION FROM ROD DYE OIL LEAKING OUT COULD NOT HAPPEN BECAUSE THREADS WERE FILLED W ITH SILICONE DURING ASSEMBLY. (X) 1 L 7 1 3O 5A3 5 C P880 2000112900030 20001129 00030 SW 2000 11 29 20000828SH018 1 20000812 G 3230 1433316510 BRACE RYAN TMPSON NAVION NAVIONB 6150112 SW LMLG CRACKED H K NONE O OTHER IN INSP/MAINT 1 GL 13 10894 4468 NAV42333B DURING ANNUAL INSPECTION, FOUND RIGHT AND LEFT MAIN GEAR RETRACT SIDEBRACE LINKS CRACKED AT WELD WHERE TUBE ATTACHES TO YOKE. ALL 3 LINKS (INCLUDING NOSE GEAR) WERE REPLACED WITH NEW DESIGN. STRONGER UNITS PURCHASED. (X) 1 L 7 1 3O A782 2000112900031 20001129 00031 SO 2000 11 29 20000828SH020 2 20000804 G 8520 537296 SHROUD BEECH 36 A36 1151604 CE CONT O550 IO550B SO PUSH ROD ENGINE CRACKED B A UNSCHED LANDING K Y FLUID LOSS ENGINE STOPPAGE CR CRUISE 1 SW 01 1830V E3087 682616 PUSHROD SHROUD CRACKED AT INSIDE OF SPRING RETAINING CRIMP, AND ALLOWED THE OIL TO LEAVE ENGINE CAUSING ENGINE TO SEIZE. (X) 1 L 7 1 3O 3 O 3A15 E3SO 2000112900032 20001129 00032 CE 2000 11 29 20000828SH021 1 20000727 G 3230 1153800025 MOTOR BEECH 200 B200 1152922 CE CENTER FUSELAGE FAILED D O OTHER J WARNING INDICATION LD LANDING 1 EA 03 152C 260 BB1132 AGC, AIRCRAFT DEPARTED, UPON RETRACTION, FLIGHT CREW NOTICED GEAR OPERATION SOUNDED SLUGGISH. APPROX HALF WAY UP ON RET RACTION, THE GEAR STOPPED FOR A SECOND OR SO, THEN CONTINUED TO RETRACT. PILOTS NOTICED A RED LIGHT IN THE GEAR HANDLE. CREW SELECTED GEAR DOWN, GOT 3 GREEN LIGHTS AND LANDED ACFT BACK AT AGC. AFTER JACKING ACFT IN HANGAR, RETRACTED GEAR 24 TIMES WITHOUT FAILURE. REPLACED GEAR MOTOR. THERE WAS A SLIGHT DIFFERENCE IN THE SPEED OF THE NEW GEAR MOTOR. NO EVIDENCE OF MECHANICAL BINDING IN SYSTEM. FAILED MOTOR WAS O/H. (X) 1 L 7 2 4T A24CE 2000112900033 20001129 00033 CE 2000 11 29 20000828SH022 1 20000722 G 2100 MS20364624C NUT BEECH 58 58P 1152744 CE FREON COMP BRACK MISSING B FC6R K NONE O OTHER IN INSP/MAINT 1 NM 05 163Z TJ247 WHILE PERFORMING A VISUAL INSPECTION OF LEFT ENGINE, DISCOVERED THE FREON COMPRESSOR BRACKET ASSY MISSING THE NUT THAT R ETAINS THE IDLER SHEAVE ARM RETAINING BOLT. THE SHEAVE ASSY WAS BEING HELD TO THE COMPRESSOR BRACKET BY BELT TENSION ON LY AND EVENTUALLY WOULD HAVE FAILED. BOLT THREADS WERE INSPECTED, A NEW WASHER AND NUT CALLED OUT FOR IN THE ENGINE PAR TS CATALOG WERE INSTALLED AND TORQUED PER THE ENGINE O/M. (X) 1 L 7 2 3O A23CE 2000112900034 20001129 00034 CE 2000 11 29 20000828SH023 1 20000722 G 3710 LINE BEECH 58 58P 1152744 CE CONT O520 TSIO520WB 17040 SO MISALIGNED B FC6R O OTHER R PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 NM 05 163Z TJ247 PILOT WAS UNABLE TO OBTAIN FULL RICH FUEL MIXTURE ON LEFT ENGINE. UPON INSPECTION BY MAINTENANCE, THE MIXTURE CONTROLLE R LINKAGE WAS FOUND OBSTRUCTED FROM REACHING FULL TRAVEL BY THE DRY AIR PUMP PRESSURE AIR LINE. THE PRESSURE AIR LINE W AS CORRECTLY ROUTED SO THAT THE MIXTURE CONTROL HAD COMPLETE FREEDOM OF MOVEMENT. (X) 1 L 7 2 3O 3 O A23CE E8CE 2001011100775 20010111 00775 SO 2001 1 11 20000828SH024 1 20000801 G 3340 AL5112 POWER SUPPLY GULSTM G1159 G1159 3953505 SO UPWASH LIGHT SYS DEFECTIVE B O OTHER B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 EA 03 154C 1735 253 WHILE PERFORMING A ROUTINE POST-FLIGHT INSPECTION, SMOKE WAS FOUND COMING FROM BEHIND THE VALANCE PANEL AREA NEAR FWD LT EMERG EXIT WINDOW. FOUND PROTECTED POWER SUPPLY (PPU) FOR ONE OF THE UPWASH FLUORESCENT LIGHT BULBS HAD BEEN DEFECTIVE . SIMILAR OCCCURRENCE ON 9-99 ON SAME ACFT WITH SAME P/N PPU (AL-5112), SN 2526. (X) 2 L 7 2 4F RT A12EA 2001011100799 20010111 00799 CE 2001 1 11 20000828SH025 1 20000808 G 3221 NAS51736 SCREW CESSNA 500 550 2076604 CE NOSE WW LOOSE B K NONE O OTHER IN INSP/MAINT 1 SW 99 26496 4783 5500607 ON THIS ACFT AND SEVERAL OTHERS (4614N, 26494) THE SCREWS HOLDING THE LT AND RT UPPER NOSE AND TRUNNION IN PLACE HAVE BE EN FOUND LOOSE. THERE IS NO INSPECTION PROCEDURE OR TIME FRAME CALLED OUT IN THE MM. (X) 1 L 7 2 4F A22CE 2000112900035 20001129 00035 EA 2000 11 29 20000828SH026 2 20000815 G 7322 2539559F DIAPHRAGM BENDIX RSA5AD1 AMTR SH2R SH2R 05601P2 GL LYC O360 IO360B1E 41514 EA BUSHINGS WORN B X9PR K NONE O OTHER IN INSP/MAINT 1 SO 13 26PB 1000 239709 585R RL70651A SERVO HAD WORN THROTTLE SHAFT BUSHINGS AND IDLE LINK LEVER HOLES. COMPONENT APPEARED TO HAVE BEEN SUBJECTED TO ABNORMAL VIBRATION INPUT. TIME SINCE LAST OVERHAUL - MAY 1965. ALL INSPECTION DATA IS AVAILABLE ON JWO 2705. (X) 1 L 7 1 3O 3 O RT EXPA1L71 1E10 2001020700189 20010207 00189 EA 2001 2 7 20000828SH027 2 20000808 G 8530 73938 INTAKE VALVE LYC HUGHES 269 269C1 8059504 SW LYC O360 HO360C1A 41514 EA ENGINE GOUGED B O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION NR NOT REPORTED 1 WP 03 2039B 44 0111 L3748136A AIRCRAFT EXPERIENCED A ROUGH RUNNING ENGINE ACCOMPANIED BY A LOSS OF POWER. SUSPECTING A STICKING VALVE, AN EXHAUST VAL VE WIGGLE CHECK WAS PERFORMED IAW LYC SB SB388B. SINCE EXHAUST VALVE CLEARANCES WERE FOUND WITHIN LIMITS, AN INSP OF TH E INTAKE VALVES WAS PERFORMED. INSP OF THE NR 2 CYLINDER INTAKE VALVE REVEALED SEVERE GOUGING AND SCORING ON VALVE STEM . MARKS WERE CONSISTENT WITH TOOL JAWS AND BELIEVED TO BE PRODUCED DURING MFG OR ASSY. CYLINDER WAS REMOVED AND REPLAC ED. (X) 1 G 7 1 3O 3 O O 4H12 E286 2000121800022 20001218 00022 CE 2000 12 18 20000828SH029 1 20000702 G 3220 NUT PIPER CESSNA 206 U206B 2073322 CE YOKE NOSE GEAR DAMAGED G O OTHER O OTHER LD LANDING 1 NM 08 3488L 594 U2060788 DURING LANDING TOUCHDOWN, THE AIRCRAFT''S NOSE WHEEL DEPARTED AIRCRAFT. LOCAL PEOPLE, AT THE SITE, FOUND THE NOSE WHEE L AND ATTACHMENT BOLT ALONG WITH OTHER ATTACHMENT HARDWARE. (THE AN6-58A NOSE WHEEL BOLT REVEALS NO SIGNS TO THREAD DAM AGE. ADDITIONALLY, IN THE HARDWARE FOUND AT THE SITE, IS AN AN363-6 SELF-LOCKING NUT, ALTHOUGH THERE IS NO WAY TO POSIT IVELY IDENTIFY THIS NUT AS THE ACTUAL ONE THAT WAS INSTALLED ON THE NOSE WHEEL BOLT; BUT IT MAY HAVE BEEN. NOTE: THE N UT IS EASILY INSTALLED BY HAND ONTO THE BOLT TO WHERE THE NUT IS FLUSH WITH END OF THE BOLT. (X) 1 H 7 1 3O A4CE 2000121800023 20001218 00023 SO 2000 12 18 20000828SH030 1 20000803 G 5751 3721400 HINGE PIPER PA34 PA34200T 7103406 SO RT AILERON CRACKED A HEBA K NONE O OTHER IN INSP/MAINT 1 SW 03 304CW 347870153 RIGHT AILERON CENTER HINGE CRACKED FROM CORROSION INSIDE THE RIGHT AILERON. (X) 1 L 7 2 3O A7SO 2000121800024 20001218 00024 CE 2000 12 18 20000828SH031 1 20000803 G 3211 AN425A BOLT CESSNA 177 177RG 2073709 CE SHEARED B SMTR K NONE O OTHER IN INSP/MAINT 1 EA 17 33224 177RG0928 LANDING GEAR RIGGING WAS BEING CHECKED. DISCOVERED BOLT SHEARED AT MOUNT ATTACH POINT, MAIN LANDING GEAR SUPPORT ASSEMB LY. REPLACED BOTH BOLTS. AC TT: 6,552.00 HOURS. (X) 1 H 7 1 3O A20CE 2001020700193 20010207 00193 EU 2001 2 7 20000828SH034 1 20000804 G 3340 H102 ADAPTER SNIAS 350 AS350B2 8680813 EU STROBE LIGHT DETACHED H K NONE O OTHER IN INSP/MAINT 1 SW 99 4035W 2373 2912 AFTER A FLIGHT AND ON THE POST-FLIGHT INSPECTION, THE TAIL STROBE BEACON WAS FOUND HANGING ON THE SIDE OF THE VERTICAL F IN. THE CLAMP WAS STILL IN PLACE BUT LOOSE ALLOWING THE STROBE LENS TO WEAR AWAY THE HOLDING ADAPTER FOR THE STROBE. W HEN ENOUGH MATERIAL WAS LOST, THE STROBE BROKE OFF. THIS COULD HAVE BEEN A LOT WORSE IF THE WIRES HAD BROKEN AND ALLOWE D THE STROBE TO CONTACT THE TAIL ROTOR. THIS IS THE SECOND TIME ON TWO AIRCRAFT IN FLEET. BOTH AIRCRAFT HAD ABOUT THE SAME AMOUNT OF TIME. (X) 1 G 7 1 3U H9EU 2000083101064 20000831 01064 NE 2000 8 31 20000829SH001 2 20000719 G 8550 33019 DRIVE GEAR FRCHLD 22 22C7A 3370104 EA PWA R2000 R20007M2 52023 NE NR 2 OIL PUMP FRACTURED B G2OC O OTHER J WARNING INDICATION CR CRUISE 1 AL 03 2225C 240 215 P105274 LOSS OF OIL PRESSURE (ENGINE) IN FLIGHT. FOUND MAIN OIL PUMP, PN 33019, DRIVESHAFT SHEARED JUST BELOW THE SCAVENGE VANE S. THE CAUSE APPEARS TO BE A FATIGUE FRACTURE. THE ENGINE ASSY WILL BE REPLACED DUE TO OIL STARVATION. THE OIL PUMP A SSY WILL BE SENT TO THE OVERHAUL FACILITY FOR TDR. (X) 1 H 7 1 3I 4 R ATC438 5E5 2000083101065 20000831 01065 GL 2000 8 31 20000829SH002 1 20000707 G 2710 ROD END AMTR S300 S300D2 GL AILERON HINGE DESTROYED G A UNSCHED LANDING F FLT CONT AFFECTED CR CRUISE 1 GL 13 112KG 393 22 WHILE PERFORMING AEROBATICS (1/2 SNAP TO LEFT) THE LEFT AILERON DEPARTED AIRCRAFT. INVESTIGATION REVEALED CENTER AILERO N HINGE HAD FAILED. LOW CYCLE FATIGUE. AIRCRAFT DESIGNER TO PERFORM A RE-EVALUATION OF THE HINGE DESIGN. AIRCRAFT IS LICENSED ''EXPERIMENTAL EXHIBITION''. (X) 1 L 7 1 3O NC EXPA1L71 2000083101066 20000831 01066 CE 2000 8 31 20000829SH004 1 20000126 G 2434 5488 ALTERNATOR LAMAR CESSNA 172 172S 2072439 CE JUNCTION BOX INOPERATIVE B BF8R O OTHER H ELECT. POWER LOSS-50 PC CR CRUISE 1 WP 07 508ER 1100 172S8008 ALTERNATOR FAILURE REPORTED BY PILOT DURING FLIGHT. INSPECTION OF CHARGING SYSTEM FOUND HIGH RESISTANCE ACROSS ALTERNAT OR CONTACTOR TERMINALS. POSSIBLE CAUSE, TURNING ON ALTERNATOR WITH HIGH LOAD. SUBMITTER SUGGESTED CHANGING START-UP PR OCEDURE SO ALTERNATOR IS ON DURING STARTING AND INSTALL HEAVY DUTY CONTACTOR. (X) 1 H 7 1 3O NT 3A12 2000083101067 20000831 01067 EA 2000 8 31 20000829SH008 2 20000322 G 8530 LW11633 CYLINDER LYC CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA CYLINDER WALLS UNSERVICEABLE B WIWR K NONE O OTHER IN INSP/MAINT 1 WP 07 69186 460 15282536 L2389615 DURING A 100-HOUR INSPECTION, ALUMINUM SHAVINGS WERE FOUND IN THE OIL FILTER. SUBMITTER STATED THIS 5TH TIME THIS SHOP HAS HAD THIS PROBLEM IN THE LAST 18-24 MONTHS). ALUMINUM IS FROM PISTON PIN PLUGS RUBBING AGAINST THE LOWER PART OF THE CYLINDER WHICH, AFTER 400-500 HOURS, DEVELOPED SEVERE PITTING THEN CREATED A WEAR STOP IN THE CYLINDER WALLS. ONE ENGI NE LOST COMPRESSION IN ALL 4 CYLINDERS BELOW ACCEPTABLE LIMITS. (X) 1 H 7 1 3O 3 O NT 3A19 E223 2000083101068 20000831 01068 CE 2000 8 31 20000829SH009 1 20000715 G 3210 07410094 GEAR CESSNA 182 182 2072702 CE MOUNTING AREA FAILED G O OTHER O OTHER TX TAXI/GRND HDL 1 NM 01 6473A 14306 33273 DURING TAXI, LANDING GEAR SPRING FAILED AT MATING AREA OF P/N 0541121-2 SUPPORT. CAUSED SUBSTANTIAL DAMAGE TO RIGHT CAB IN AFT OF CREW DOOR, RIGHT SIDE OF HORIZONTAL STABILIZER AND ELEVATOR, AND OUTBOARD SECTION OF RIGHT WING. (X) 1 H 7 1 3O NT 3A13 2000083101069 20000831 01069 EA 2000 8 31 20000829SH010 2 20000724 G 8550 GASKET CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA OIL SUMP PAN IMPROPER PART B K NONE O OTHER IN INSP/MAINT 1 GL 25 61541 620 17264626 L4068727A THE LOWER RIGHT ENGINE ISOLATION MOUNT IS BECOMING RUPTURED DUE TO CHAFING CAUSED BY THE PROTRUSION OF THE OIL SUMP PAN GASKET. THIS GASKET, WHEN DRIED OUT DUE TO HEAT, SEEMS TO ACT LIKE A KNIFE AGAINST THE ISOLATION MOUNT. TRIMMING THE G ASKET STOPS THIS. SUBMITTER STATED THIS IS 3RD OCCURRENCE ON 3 DIFFERENT AIRCRAFT. (X) 1 H 7 1 3O 3 O NT 3A12 E274 2000083101070 20000831 01070 SO 2000 8 31 20000829SH011 1 20000714 G 8100 654237 DUCT PIPER PA34 PA34220T 7103420 SO CONT O360 TSIO360KB 17025 SO LEFT ENGINE CRACKED A O OTHER R PARTIAL RPM/PWR LOSS CR CRUISE 1 NM 01 8063L 78 348233067 811371R PILOT REPORTED THOTTLE SPLIT AND UNABLE TO OBTAIN RATED POWER ON LEFT ENGINE. INSPECTION OF LEFT ENGINE REVEALED EXHAUS T V-DUCT ASSY AT TURBOCHARGER CRACKED. THIS PART WAS INSTALLED NEW AS A COMPONENT OF A FACTORY RE-MANUFACTURED ENGINE. TOTAL TIME SINCE INSTALLED WAS 78 HOURS. CAUSE OF CRACKING IS UNDER INVESTIGATION. (X) 1 L 7 2 3O 3 O A7SO E9CE 2000083101071 20000831 01071 CE 2000 8 31 20000829SH012 1 20000810 G 7603 5122218 THROTTLE CESSNA 206 P206C 2073312 CE CONT O520 IO520A 17032 SO CENTRAL ASSY BROKEN A DKBA O OTHER R PARTIAL RPM/PWR LOSS CR CRUISE 1 SO 09 8630Z 126 P2060430 112751R PILOT STARTED TO REDUCE POWER IN ORDER TO LOSE ALTITUDE. AT THIS TIME, THE THROTTLE CABLE BROKE CAUSING A LOSS IN ENGIN E POWER. PILOT MADE SAFE LANDING IN A REMOTE FIELD. UPON INSPECTION, MAINTENANCE PERSONNEL FOUND THROTTLE CABLE BROKEN JUST ABOVE THE CABLE SUPPORT BRACKET. SUBMITTER SUSPECTED CAUSE AS IMPROPER HARDWARE USED ON SUPPORT BRACKET ALLOWING IT TO FLEX AS THROTTLE AND MIXTURE CONTROLS WERE CYCLED. SUBMITTER SUGGESTED TO PREVENT RECURRENCES, CLOSER INSPECTION OF FLIGHT CRITICAL ITEMS SHOULD BE PERFORMED IAW MANUFACTURER''S MM. (X) 1 H 7 1 3O 3 O A4CE E5CE 2000083101072 20000831 01072 EA 2000 8 31 20000829SH013 2 20000811 G 7414 4381 MAGNETO CESSNA 150 152 2071835 CE LYC O235 O235N2C 41505 EA LEFT FAILED B WIWR A UNSCHED LANDING Y ENGINE STOPPAGE CR CRUISE 1 WP 07 95615 2070 15285938 L2391215 HIT/DVT - WHILE EN ROUTE PILOT REPORTED A SEVERE LOSS OF ENGINE POWER. ACFT MADE UNEVENTFUL LANDING IN THE DESERT ON AN UNCHARTED DIRT STRIP. ACFT HAD TO BE TRUCKED BACK TO DVT. FOUND MAGNETOS PARTIALLY FAILED. BOTH COILS SHOWED SIGNS O F OVERHEATING AND WERE OUT OF LIMITS PER MFG SPECS. BOTH SETS OF POINTS WERE FOUND UNSERVICABLE, BOTH DISTRIBUTORS SHOW ED SIGNS OF CARBON TRACKING ONE OF WHICH WAS ARCING/GROUNDING OUT ON THE MOUNTING SCREW THROUGH THE CAP. ONE MAG WAS FO UND WITH LARGE AMOUNTS OF OIL INSIDE CASE. POSSIBLY, EXTREMELY HIGH OUTSIDE AIR TEMPS (BETWEEN 110 DEGREES AND 121 DEGR EES) WERE CAUSE OF COILS OVERHEATING. MAINT RECORDS SHOWED NO EVIDENCE OF 500-HR INSP BEING PERFORMED ON EITHER MAG. 1 H 7 1 3O 3 O NT 3A19 E223 2000083101073 20000831 01073 EA 2000 8 31 20000829SH014 2 20000811 G 7414 4381 MAGNETO CESSNA 150 152 2071835 CE LYC O235 O235N2C 41505 EA RIGHT FAILED B WIWR A UNSCHED LANDING Y ENGINE STOPPAGE CR CRUISE 1 WP 07 95615 2070 15285938 L2391215 HIT/DVT - WHILE EN ROUTE PILOT REPORTED A SEVERE LOSS OF ENGINE POWER. ACFT MADE UNEVENTFUL LANDING IN THE DESERT ON AN UNCHARTED DIRT STRIP. ACFT HAD TO BE TRUCKED BACK TO DVT. FOUND MAGNETOS PARTIALLY FAILED. BOTH COILS SHOWED SIGNS O F OVERHEATING AND WERE OUT OF LIMITS PER MFG SPECS. BOTH SETS OF POINTS WERE FOUND UNSERVICABLE, BOTH DISTRIBUTORS SHOW ED SIGNS OF CARBON TRACKING ONE OF WHICH WAS ARCING/GROUNDING OUT ON THE MOUNTING SCREW THROUGH THE CAP. ONE MAG WAS FO UND WITH LARGE AMOUNTS OF OIL INSIDE CASE. POSSIBLY, EXTREMELY HIGH OUTSIDE AIR TEMPS (BETWEEN 110 DEGREES AND 121 DEGR EES) WERE CAUSE OF COILS OVERHEATING. MAINT RECORDS SHOWED NO EVIDENCE OF 500-HR INSP BEING PERFORMED ON EITHER MAG. 1 H 7 1 3O 3 O NT 3A19 E223 2000083101074 20000831 01074 NM 2000 8 31 20000829SH015 1 20000816 G 2820 1086221101 HOSE UNIVAR 108 1081 9230404 NM FRNKLN 6A4150 6A4145A3 27024 EA FUEL SUMP/CARB RESTRICTED H A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CR CRUISE 1 CE 07 9442K 1082442 30093 AIRCRAFT LOST POWER DUE TO FUEL STARVATION. AIRCRAFT LANDED DOWN WIND ON GRASS STRIP MORE THAN HALF WAY DOWN THE STRIP. AIRCRAFT WAS PUT IN A PARTIAL SKID AT TIME OF IMPACT. RIGHT LANDING GEAR COLLAPSED CAUSING PROPELLER TO HIT GROUND AN D RIGHT WING DAMAGED. PILOT WAS NOT INJURED. FOUND FUEL LINE P/N 108-6221101 HAD SWIVELLED UP FROM LOW PRESSURE MIL H- 6000 3Q85 .50 INCH INNER LINING OF HOSE HAS SWIVELLED UP NEAR THE FITTING CAUSING A RESTRICTION. POSSIBLE CAUSE, AIRCRA FT HAD STC FOR AUTOFUEL. AUTOFUEL USED MOSTLY FOR SEVERAL YEARS. (X) 1 H 7 1 3O 3 O A767 E238 2001020700191 20010207 00191 EU 2001 2 7 20000829SH016 1 20000801 G 6320 350A32030004 GEARBOX SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1B 6OO30 NE MAIN MAKING METAL H A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 WP 13 971H 3137 137 2955 4548 WHILE PILOT WAS FLYING ON TOUR FLIGHT, NOTICED MAIN GEARBOX CHIP LIGHT ILLUMINATED. PILOT MADE PRECAUTIONARY LANDING. INSPECTED MAIN GEARBOX CHIP PLUG, FOUND A SMALL METAL FLAKE. CLEANED CHIP PLUG AND PERFORMED OPERATIONAL CHECK, FUNCTIO NALLY CHECKED GOOD. AIRCRAFT RETURNED TO SERVICE. AIRCRAFT TT: 6,706.2 HOURS. (X) 1 G 7 1 3U 3 U NC H9EU E19EU 2001020700192 20010207 00192 SW 2001 2 7 20000829SH017 1 20000731 G 6220 12NH8EB080 NUT BELL BELL 222 222U 1182140 SW M/R PTICH HORN UNSERVICEABLE G K NONE O OTHER IN INSP/MAINT 1 SW 99 911ED 506 A44 45771 NUT P/N 12NH-8 AND P/N EB080. LOOSE TORQUE IF INSTALLED IAW ASB 222U-98-54, ASB HAS NO WASHER INSTALLED UNDER THE HEAD OF THE NUT. THE NUT BECOMES DEFORMED AND LOSES TORQUE. CORRECTED ASB 222U-98-54 TO SHOW A WASHER P/N 140-007-33-28=3, AND NEW NUT P/N 7594S820. (X) 1 G 7 2 3U H9SW 2000112900036 20001129 00036 WP 2000 11 29 20000830SH001 2 20000821 G 7230 30723961 DISK HONEYWELL GARRTT TFE731 TFE7313D WP FWD RIM DV TAIL CRACKED B UO2R K NONE O OTHER IN INSP/MAINT 1 GL 19 7526 6255 P76227 C/W NDT INSPECTION AND FOUND FORWARD RIM CRACKED IN 7 EACH PLACES AND 1 EACH DOVE TAIL CRACKED. (X) 4 F E6WE 2000112900038 20001129 00038 CE 2000 11 29 20000830SH025 1 20000821 G 3230 1068100111 CONTROL CABLE BEECH 58 58 1152740 CE LT MAIN GEAR FRAYED B K NONE O OTHER IN INSP/MAINT 1 SO 03 1057C 601 TH1777 FOUND LEFT MAIN GEAR DOWNLOCK CABLE FRAYED OVER 50 PERCENT THROUGH AT SWAGED TERMINAL ATTACHING TO LANDING GEAR ACTUATOR . NO EVIDENCE OF BEND OF OTHER DAMAGE TO CABLE. DAMAGE APPEARS TO HAVE OCCURRED DURING MANUFACTURE. INSTALLED AND RIG GED NEW CABLE ASSY. (X) 1 L 7 2 3O 3A16 2001020700209 20010207 00209 SW 2001 2 7 20000830SH026 1 20000815 G 6510 222044006109A COUPLING BELL 222 222U 1182140 SW DRIVE SHAFT CORRODED B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 111DS 85 47554 REPLACED WITH RECONDITIONED LEFT DRIVESHAFT FROM BELL HELICOPTER. (X) 1 G 7 2 3U H9SW 2000112900039 20001129 00039 CE 2000 11 29 20000830SH028 1 20000804 G 3246 50300010133 WHEEL BEECH 90 C90A 1152911 CE LT WHEEL BEARING FAILED B O OTHER O OTHER TX TAXI/GRND HDL 1 SO 09 3220L LJ1420 WHEN AIRCRAFT LANDED, THE RT WHEEL WABBLED ON AXLE. JACKED AIRCRAFT AND REMOVED WHEEL WITHOUT REMOVING NUT. FOUND SMAL L OUTER BEARING FROZEN AND DISSINTEGRATED, AND THE INNER (LARGER) RACE SPUN IN WHEEL. FURTHER INVESTIGATION FOUND ALL W HEEL HALF BOLTS FINGER LOOSE. (X) 1 L 7 2 3T RT 3A20 2000112900040 20001129 00040 SO 2000 11 29 20000830SH029 1 20000721 G 3260 SWITCH PIPER PA31 PA31350 7103110 SO LACK OF LUBE A BSYA O OTHER J WARNING INDICATION LD LANDING 1 GL 07 35453 318052006 CLE - GOING INTO CLEVELAND AIRPORT, RT MAIN GEAR DOWN AND LOCK INOPERABLE. CYCLED GEAR SEVERAL TIMES, LIGHT CAME ON. C LEANED AND LUBED DOWN AND LOCK SWITCH. OPS CHECKED GOOD. (X) 1 L 7 2 3O A20SO 2000112900037 20001129 00037 EA 2000 11 29 20000830SH031 2 20000627 G 8520 LW13212 BEARING LYC PIPER PA46 PA46350P SO LYC O540 TIO540AE2A 41532 EA NR 6 FAILED G B EMER. DESCENT Y ENGINE STOPPAGE CR CRUISE 1 EA 01 92939 106 4636119 L1044361A ENGINE (106.6 HOURS SINCE NEW) FAILED WHILE AT CRUISE RESULTING IN AN EMERGENCY DESCENT AND LANDING AT ALB. RESULTS OF ENGINE SERVICE TEARDOWN INSPECTION AND TECHNICAL REPORTS DATED 7/5/2000 AND 7/27/2000 FROM TEXTRON LYCOMING FOUND THE CR ANKSHAFT ROD JOURNAL AND CONNECTING ROD BROKEN AT NR 6 CRANKPIN WITH NR 6 ROD BEARING EXTRUDED. FACTORY TECHNICAL REPOR T CONCLUDED THAT PRIMARY FAILURE WAS MOST LIKELY DUE TO NR 6 CONNECTING ROD BEARING FAILURE. (THIS WAS THE 3RD FACTORY NEW ENGINE INSTALLED ON THIS AIRFRAME). 1 L 7 1 3O 3 O RT A25SO E14EA 2000112900041 20001129 00041 EA 2000 11 29 20000831SH001 2 20000830 G 7310 FUEL LINE PRECISION BEECH 23 C24R 1151254 CE LYC O360 IO360A1B6 41514 EA FUEL SYSTEM DETERIORATED D O OTHER R PARTIAL RPM/PWR LOSS CR CRUISE 1 GL 11 18981 3320 30 MC545 L1805851A IN CRUISE FLIGHT ENGINE RAN ROUGH, HAD LOW EGT 900DG ON NR 2 CYLINDER. AFTER LANDING AND TROUBLESHOOTING FOUND DEBRIS IN FUEL LINE FROM SERVO TO FLOW DIVIDER. REPLACED RUBBER FUEL LINE WITH TEFLON LINE P/N LW12784-4-172 IAW LYCOMING SI12 74B. SUBMITTER SUGGESTED REPLACING ALL FUEL AND OIL LINES WITH TEFLON TYPE. SUSPECT FUEL LINE HAD 30 HRS SMOH. 1 L 7 1 3O 3 O A1CE 1E10 2000112900042 20001129 00042 SO 2000 11 29 20000831SH002 1 20000718 G 3260 BULB PIPER PA31 PA31350 7103110 SO FAILED A BSYA O OTHER O OTHER LD LANDING 1 GL 07 4079Y 318152079 IND - GOING INTO IND COULD NOT GET THE RIGHT GEAR LIGHT TO COME ON. REMOVED AND REPLACED LIGHTBULB. OPS CHECKED GOOD. (X) 1 L 7 2 3O A20SO 2000112900043 20001129 00043 SO 2000 11 29 20000831SH003 2 20000512 G 8530 INTAKE VALVE LYC PIPER PA32 PA32R300 7103213 SO LYC 0540 IO540K1G5D 41532 SO NR 2 CYLINDER FRACTURED D O OTHER R PARTIAL RPM/PWR LOSS CR CRUISE 1 AL 01 5633V 649 32R7780349 L1648648A DURING FLIGHT, ENGINE BEGAN TO RUN ROUGH. PILOT POWERED BACK AND MADE PRECAUTIONARY LANDING. INSPECTION REVEALED FAILU RE OF THE VALVE STEM ON NR 2 CYLINDER INTAKE VALVE. THE FRACTURE IS LOCATED APPROXIMATELY .6250 INCH FROM THE TOP OF TH E VALVE STEM NEAR THE VALVE KEEPERS. SOME WEAR WAS DETECTED AT THE VALVE GUIDE. (X) 1 L 7 1 3O 3 O A3SO 1E4 2000112900044 20001129 00044 GL 2000 11 29 20000831SH004 1 20000723 G 5540 93004 HINGE AMTR KITFOX KITFOXSPEEDS 05623DZ GL RUDD HINGE BOLTS FAILED D O OTHER F FLT CONT AFFECTED LD LANDING 1 CE 09 525PP 360 JBS009 ALL 4 RUDDER HINGE BOLTS FAILED ON LANDING RESULTING IN LOSS OF CONTROL OF AIRCRAFT ON THE RUNWAY. AIRCRAFT WENT OFF RU NWAY INTO THE GRASS (LEFT SIDE RUNWAY). AIRCRAFT THEN TAXIED TO PARKING WHERE FAILED RUDDER HINGES DISCOVERED. REPAIR ED BROKEN BOLTS. (X) 1 H 7 1 3I NC EXPA1H71 2000112900045 20001129 00045 SO 2000 11 29 20000831SH005 1 20000704 G 2910 B-NUT PIPER PA31 PA31350 7103110 SO LOOSE A BSYA O OTHER K FLUID LOSS LD LANDING 1 GL 07 525AA 318052111 OWB - GOING INTO OWB, COULD NOT GET LANDING GEAR DOWN. PILOT HAND PUMPED GEAR DOWN, LANDED NO PROBLEMS. SERVICED HYDRA ULIC FLUID, TIGHTENED LOOSE B-NUT BACK SIDE OF HYDRAULIC SERV. PORT. (X) 1 L 7 2 3O A20SO 2001020700210 20010207 00210 SW 2001 2 7 20000831SH006 1 20000815 G 6510 214040659005 COUPLING BELL 412 412EP 1182205 SW DRIVESHAFT WORN B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 6379E 117 36247 COUPLING FOUND WORN. REPLACED WITH NEW COUPLING FROM BELL HELICOPTER. (X). 1 G 7 2 4U H4SW 2000112900046 20001129 00046 SO 2000 11 29 20000831SH012 2 20000803 G 7322 PUMP CESSNA 210 2105 2073404 CE CONT O470 IO470S 17026 SO LEAKING D O OTHER K FLUID LOSS IN INSP/MAINT 1 NM 09 8260Z 46 F189902BR 2050249 10242125 DURING POST-FLIGHT SECURING OF ACFT, PILOT NOTICED FUEL DRIPPING FROM LT COWL FLAP OPENING. INVEST REVEALED FUEL COMING FROM ENGINE DRAIN LINE TRACED TO THE FUEL INJECTION PUMP. SELECTING THE OFF POSITION OF THE FUEL SELECTOR VALVE RELIEV ED THE FUEL TANK HEAD PRESSURE FROM THE SYSTEM AS THIS WOULD CAUSE THE LEAK TO STOP. BEFORE REPLACING THE PUMP, A GROUN D RUN WAS PERFORMED TO SEE IF FUEL WAS BEING LOST IN-FLIGHT. NONE WAS OBSERVED. THE PILOT INDICATED THE ENGINE PERFORM ED NORMALLY DURING THE LAST FLIGHT, SO THE QUESTION AS TO WHETHER OR NOT AIR WAS BEING DRAWN INTO THE SYSTEM REMAINED UN ANSWERED. FUEL INJECTION PUMP REPLACED. (X) 1 H 7 1 3O 3 O 3A21 3E1 2000112900047 20001129 00047 SO 2000 11 29 20000831SH015 2 20000831 G 8500 ENGINE PIPER PA32 PA32RT300 7103215 SO LYC 0540 IO540K1G5D 41532 SO FAILED A SX0A A UNSCHED LANDING J Y WARNING INDICATION ENGINE STOPPAGE CR CRUISE 1 SO 33 165R 584 32R7885217 L2500448A AIRCRAFT WAS IN-FLIGHT WHEN ENGINE LOST ALL OIL PRESSURE, AND HAD A CATASTROPHIC FAILURE. AIRCRAFT WAS ABLE TO MAKE A S AFE OFF-FIELD LANDING WITH NO STRUCTURAL DAMAGE. ENGINE WAS OVERHAULED ENGINE FROM LYCOMING. ENGINE SHOPPED TO LYC FOR INSPECTION. (X) 1 L 7 1 3O 3 O A3SO 1E4 2001011104196 20010111 04196 GL 2001 1 11 20000831SH016 1 20000714 G 7920 632072 BRACKET DIAMON DA20 DA20C1 2990001 GL CONT O240 IO240B 17063 SO OIL FILTER CLAMP BROKEN B HBKR O OTHER O OTHER IN INSP/MAINT 1 SW 22 107CT 17 C0107 806184 BRACKET BROKEN AT BAND. CAUSE MAY HAVE BEEN DUE TO MISALIGNMENT WITH MATING STRAP AT LOCATION A. (X) 1 L 7 1 3O 3 O NT TA4CH E7SO 2000112900048 20001129 00048 SO 2000 11 29 20000831SH017 2 20000810 G 8520 631845 CAM BEECH 95 95B55 1152729 CE CONT O520 IO520E 17032 SO INTERNAL GEAR STRIPPED B H8AR O OTHER O OTHER NR NOT REPORTED 1 EA 05 22EW TC1058 556217 ENGINE FAILURE CAUSED BY TEETH BEING STRIPPED OFF OF CAMGEAR. ONE TOOTH APPEARS TO HAVE BEEN FRACTURED AND THE FOLLOWIN G 6 TEETH WERE STRIPPED. GEAR WAS STILL PROPERLY FASTENED TO CAMSHAFT. THE CRANKSHAFT GEAR WAS NOT DAMAGED. NO FOREI GN MATERIALS WERE FOUND IN CRANKCASE. ALSO, NO RECENT WORK PERFORMED IN THIS AREA. CAUSE OF FAILURE NOT DETERMINED. ( X) 1 L 7 2 3O 3 O RT 3A16 E5CE 2000112900049 20001129 00049 EA 2000 11 29 20000831SH018 2 20000816 G 8520 LW13885M06 BEARING PIPER PA32 PA32300 7103212 SO LYC O540 IO540K1G5 41532 EA FWD THRUST MAKING METAL A FWRA O OTHER O OTHER IN INSP/MAINT 1 AL 01 31657 180 327840139 L1800548A FOUND METAL IN OIL FILTER AND SCREEN. FOUND FORWARD THRUST BEARING HALVES OUTER COATING ON THE INSIDE HALVES FLAKING OF F. (FLAKES AND CHUNKS). PART NUMBER ON BOTH HALVES IS LW-13885-M06 1-97. (X) 1 L 7 1 3O 3 O A3SO 1E4 2000112900050 20001129 00050 CE 2000 11 29 20000831SH019 1 20000808 G 8011 643259A40 ADAPTER CESSNA 421 421B 2076014 CE CONT O520 GTSIO520H 17032 SO STARTER SHAFT TE WORN B CSLR O OTHER O OTHER IN INSP/MAINT 1 CE 01 41106 781 421B0589 267421 REMOVED STARTER ADAPTER FROM RIGHT POSITION FOR VISUAL INSPECTION PER TCM CRITICAL SB NR CSB94-4C, PART 3. FOUND UNACCE PTABLE HEAVY WEAR, SPALLING AND PITTING FULL TOOTH WIDTH. (X) 1 L 7 2 3O 3 O A7CE E7CE 2000112900051 20001129 00051 CE 2000 11 29 20000831SH020 1 20000808 G 8011 643259A40 ADAPTER CESSNA 421 421B 2076014 CE CONT O520 GTSIO520H 17032 SO SHAFT GEAR TEETH WORN B CSLR O OTHER O OTHER IN INSP/MAINT 1 CE 01 41106 781 421B0589 267420R REMOVED STARTER ADAPTER FROM LEFT POSITION FOR VISUAL INSPECTION PER TCM CRITICAL SB NR CSB94-4C, PART 3. FOUND UNACCEP TABLE HEAVY WEAR, SPALLING AND PITTING FULL TOOTH WIDTH PER FIGURE 6. (X) 1 L 7 2 3O 3 O A7CE E7CE 2000112900052 20001129 00052 CE 2000 11 29 20000831SH021 1 20000731 G 2820 1118 HOSE AYRES S2 S2R 7630202 CE GARRTT TPE331 TPE331* 01514 WP FUEL SOV TO PUMP RESTRICTED D O OTHER O OTHER IN INSP/MAINT 1 NM 11 4925X 2124R P34014 HOSE INTER RUBBER EXPANDED TO RESTRICT FUEL FLOW AT FUEL SHUT-OFF VALVE. PART TIME IN SERVICE: 281 HOURS. REF: S-2R ILLUSTRATED PARTS CATALOG FIG 2-7, ITEM 15, P/N 111-312-312-8-0070. (X) 1 L 7 1 3R 3 T NC A4SW E2WE 2001011104197 20010111 04197 2001 1 11 20000831SH024 3 20000701 G 6110 AN660 BOLT AMTR VANSAC RV3 05608T7 GL PROPELLER FAILED G O OTHER O OTHER CR CRUISE 1 WP 07 470RV 470 OWNER REPORTED 5 OF 6 AN 6-60 PROPELLER BOLTS FAILED IN-FLIGHT. BOLTS SENT TO MFG, FOUND IN SPEC REASON FOR FAILURE DUE TO BOLTS BEING TOO LONG PREVENTING PROPER CLAMP-UP OF CRUSHPLATE AND SPINNER BULKHEAD TO CAMSHAFT FLANGE EXTENSION. FA ILED BOLTS SHOWED 4 TO 5 THREADS PROTRUDING FROM NUTS WITH 2 WASHERS UNDER EACH NUT. SUBMITTER STATED TO CAUTION MECHAN ICS NOT TO ALLOW MORE THAN 2 THREADS TO SHOW BEYOND THE NUT. (X) 1 L 7 1 3O NC EXPA1L71 2000101200127 20001012 00127 SO 2000 10 12 20000831SH025 1 20000802 G 2810 461698 FUEL CELL PIPER PA44 PA44180 7104402 SO RT WING NACELLE LEAKING B WIWR K NONE K FLUID LOSS IN INSP/MAINT 1 WP 07 4144C 61014 4496020 PILOT REPORTED ON PRE-FLIGHT, FUEL WAS DRIPPING FROM THE RIGHT WING NACELLE BEHIND THE ENGINE. UPON INSPECTION, THE FUE L OUTLET NIPPLE HAD A SMALL HOLE. POSSIBLE CAUSE WAS MAIN FUEL LINE IS NOT SUPPORTED IN THAT AREA AND THE GROMMET USED BY PIPER WAS TOO SMALL WHERE THE FUEL LINE WENT THROUGH A RIB. VIBRATIONS FROM ENGINE POSSIBLY WORKED THE NIPPLE UNTIL IT DEVELOPED A HOLE. FUEL BLADDER WAS REPLACED WITH NEW. (X) 1 L 7 2 3O A19S0 2000101200136 20001012 00136 SO 2000 10 12 20000906SH001 1 20000831 G 2710 6271105 PULLEY PIPER PA28 PA28R201 7102816 SO LYC O360 IO360C1C6 41514 EA MCAULY 2D34C B2D34C213 GL WING ROOT FROZEN B O OTHER F FLT CONT AFFECTED IN INSP/MAINT 1 SO 15 773FT 92 2844030 L2885451A 000220 LEFT REAR AILERON CABLE RUNNING ALONG THE OUTSIDE OF CABLE PULLEY AT WING ROOT. NO WEAR PATTERN APPARENT ON PULLEY SLOT INDICATING THAT THE CABLE WAS NEVER ON THE PULLEY SINCE MANUFACTURE. THE PULLEY WAS ALSO FROZEN. SUBMITTER STATED THEY HAVE FOUR NEW PA28R201 AND ONE PA44-180 ALL WITH LESS THAN 200 HOURS TIME AND ALL HAVING ASSORTED RIGGING PULLEYS THAT WERE FROZEN FROM THE FACTORY. ALL OF WHICH HAVE BEEN REPLACED DURING THE FIRST 100 HOUR INSPECTION. (X) 1 L 7 1 3O 3 O 2A13 1E10 5 C P7EA 2000090800155 20000908 00155 EU 2000 9 8 20000906SH002 1 20000901 G 7830 MS178257 NUT AMD FALC90 FALCON900EX 2730009 EU UPPER RT T/R IMPROPER PART C O OTHER O OTHER IN INSP/MAINT 1 SO 11 404A 300 TRO58SL060 56 UPPER RT T/R DOOR HINGE BOLT, P/N NAS6307U-23D, HAD AN ALTERNATE PART NUMBER NUT INSTALLED, P/N MS17825-7. THIS P/N NUT WAS NOT LISTED IN THE IPC (REF IPC78-30-10-10 ,ITEM 60, F12NE4753-070). ONLY THE UPPER RT T/R HINGE BOLT HAD THE ALTER NATE P/N NUT INSTALLED. DURING THE FIRST ACCESS TO THIS AREA , (REMOVAL OF BOLT FOR LUBRICATION) DAMAGE WAS OBSERVED ON THE AFT BODY SKIN BELLOW SUPPORT ASSEMBLY P/N FGFB583842150D2. DAMAGE APPEARED TO HAVE BEEN CAUSED BY NUT ROTATION DUR ING INSTALLATION. DAMAGED AREA MEASURED .60 INCH IN DIAMETER AND .030 TO .050 INCH IN DEPTH. SUBMITTER SUGGESTED MANUF ACTURER MAY HAVE ALLOWED DAMAGE TO BE BLENDED (REF DASSAULT STRUCTURES PROJECT NR 3557). (X) 2 L 7 3 4F RT A46EU 2001020700194 20010207 00194 SW 2001 2 7 20000907SH008 1 20000815 G 6310 406340102101 SEAL BELL 206 206L4 1182110 SW FREEWHEEL UNIT LEAKING B GS1R K NONE K FLUID LOSS IN INSP/MAINT 1 EA 03 208FC 400 52044 FREEWHEELING UNIT OUTPUT SEAL, BETWEEN ENGINE AND TRANSMISSION, REPLACED WITH NEW SEAL FROM BELL HELICOPTER. (X) 1 G 7 1 3U NC H2SW 2001010200001 20010102 00001 CE 2001 1 2 20000907SH010 1 20000822 G 5551 MOUNT CESSNA 172 172R 2072401 CE HORIZ STAB LOOSE H K NONE O OTHER IN INSP/MAINT 1 GL 03 263RE 923 17280572 DURING ANNUAL INSPECTION, FOUND HORIZONTAL STABILIZER LOOSE AT FORWARD MOUNT BOLTS, PLAY VISIBLY NOTICEABLE AND ACCOMPAN IED BY LOUD CREAKING NOISE. (X) 1 H 7 1 3O NT 3A12 2001020700196 20010207 00196 SW 2001 2 7 20000907SH013 1 20000815 G 6510 407340339103 BEARING BELL 407 407 SW TAILROTOR DRIVE DAMAGED B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 52AZ 161 53380 BEARING REPLACED WITH NEW BEARINGS FROM BELL HELICOPTER. REPLACED IAW ASB 407-00-35, NDT PER AD 2000-02-12. (X) 1 G 7 1 3U O H2SW 2001020700257 20010207 00257 SW 2001 2 7 20000907SH014 1 20000815 G 6510 407340339103 BEARING BELL 407 407 SW TAILROTOR DRIVE DAMAGED B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 52AZ 161 53380 REPLACED WITH NEW BEARINGS FROM BELL HELICOPTER. REPLACED IAW ASB 407-00-35, NDT PER AD 2000-02-12. (X) 1 G 7 1 3U O H2SW 2001020700258 20010207 00258 SW 2001 2 7 20000907SH015 1 20000815 G 6230 214040659005 COUPLING BELL 412 412EP 1182205 SW MAIN DRIVESHAFT WORN B GS1R K NONE O OTHER IN INSP/MAINT 1 EA 03 6379E 117 36247 REPLACED COUPLING WITH NEW FROM BELL HELICOPTER. (X) 1 G 7 2 4U H4SW 2001022000165 20010220 00165 GL 2001 2 20 20000907SH016 3 20000822 G 6110 1A101DCM6948 FLANGE CESSNA 150 150H 2071818 CE MCAULY 1A101 1A101DCM GL PROPELLER DAMAGED B W59R K NONE O OTHER IN INSP/MAINT 1 WP 07 6665S 15067465 G1691 PROPELLER SUBMITTER FOR REPAIR. DURING INSPECTION, DISCOVERED THE PROPELLER MOUNTING SURFACE WAS NOT FLAT AND APPEARED TO HAVE BEEN NOT SEATING PROPERLY ON THE ENGINE CRANKSHAFT. SUBMITTER STATED IT APPEARED THE PROPELLER FLANGE HAD BEEN HEAVILY GROUND OR SANDED DURING PREVIOUS MAINTENANCE. (X) 1 H 7 1 3O 3A19 5 N P918 2001020700259 20010207 00259 GL 2001 2 7 20000907SH017 2 20000829 G 7510 23064620 LINE BELL 206 206L3 1182108 SW ALLSN 250C 250C30P 03013 GL ENGINE ANTI-ICE BROKEN B HY1R K NONE O OTHER IN INSP/MAINT 1 EA 23 739NM 7879 51124 CAE895175 WHEN TROUBLESHOOTING THE ENGINE ANTI-ICE SYSTEM, FOUND THE AIR LINE BETWEEN THE SOLENOID VALVE AND AIR VALVE HAD A BROKE N FLARE AT THE AIR VALVE END. THE BROKEN PIECE OF THE FLARE CAME OFF WHEN THE AIR LINE B-NUT WAS REMOVED. 7,879.4 HOUR S ACTT. (X) 1 G 7 1 3U 3 U H2SW E1GL 2001010200002 20010102 00002 SO 2001 1 2 20000907SH018 1 20000808 G 2100 134A COMPRESSOR PIPER PA31 PA31310 7103103 SO A/C CABIN FAILED D A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CE 01 9007Y 3661 1976 5300610200 3111 PILOT DEPARTED RUNWAY AND DURING CLIMB-OUT HAD SMOKE ENTERING CABIN. HE RETURNED TO AIRPORT AND MADE A SAFE LANDING. A FTER INVESTIGATION, FOUND AIR CONDITIONER BELT BURNED AND WAS A CAUSE OF THE COMPRESSOR LOCKING UP. SERVICED WITH FREON , OPS CHECKED, TEST FLOWN, CHECKED OK. A NEW BELT, PN ES200333, WAS ALSO INSTALLED. ALL TIMES ARE AIRCRAFT HOURS NOT A CTUAL TIME ON COMPONENT. (X) 1 L 7 1 3O RT A20SO 2001010200003 20010102 00003 GL 2001 1 2 20000907SH022 1 20000717 G 7910 632072 BRACKET DIAMON DA20 DA20C1 2990001 GL CONT O240 IO240B 17063 SO OIL FILTER TUBE BROKEN B HBKR K NONE O OTHER IN INSP/MAINT 1 SW 11 996CT 16 C0096 806163 BRACKET/CLAMP BROKEN AT BOND. SUBMITTER STATED MAY HAVE BEEN DUE TO MISALIGNMENT AT JOINT. (X) 1 L 7 1 3O 3 O NT TA4CH E7SO 2001010200004 20010102 00004 CE 2001 1 2 20000907SH023 1 20000802 G 7120 50910279 MOUNT BEECH 99 B99 1154004 CE LT/RT ENGINE WORN E TIMA K NONE O OTHER IN INSP/MAINT 1 NM 07 99CA 33953 U127 DURING ENGINE CHANGES, BOTH ENGINE TUBE FRAME MOUNTS WERE FOUND TO HAVE WEAR ON TORSION BARS BEYOND LIMITS. THIS IS OCC URRING DUE TO THE AFT LOWER STAINLESS FIRE SHIELD RESTING ON THE MOUNT. THE LOCATION IS CONCEALED DUE TO THE RUBBER SEC TION OF THE FIRE SHIELD IN THIS AREA. SUBMITTER STATED, NORMALLY, THERE IS ADEQUATE CLEARANCE BETWEEN THE FIRE SHIELD AN D THE TORSION TUBE, BUT IF THE FIRE SHIELD IS BENT FORWARD SUCH AS DURING AN ENGINE INSTALLATION, THEN SUCH A CONDITION IS LIKELY TO RESULT IN CHAFING. (X) 1 L 7 2 3T A14CE 2001010200005 20010102 00005 GL 2001 1 2 20000907SH024 1 20000714 G 7910 632072 BRACKET DIAMON DA20 DA20C1 2990001 GL OIL FILLER BRKT BROKEN B HBKR K NONE O OTHER IN INSP/MAINT 1 SW 11 904CT 17 C0104 BRACKET BROKEN AT BAND. SUBMITTER STATED CAUSE MAY HAVE BEEN DUE TO MISALIGNMENT WITH MATING STRAP. (X) 1 L 7 1 3O NT TA4CH 2001010200006 20010102 00006 GL 2001 1 2 20000907SH025 3 20000802 G 6111 B3204 SCREW HARTZL BEECH 200 200BEECH 1152920 CE HARTZL HCD4N3 HCD4N3A GL SET SCREW FAILED B EK2D O OTHER O OTHER IN INSP/MAINT 1 SW 09 81WU BB576 FY2131 BLADE PRELOAD ADJUSTMENT SCREW FAILED AT JAM NUT ALLOWING THE NUT TO FLOAT FREELY WITHIN THE HUB. PILOT REPORTED OCCASI ONAL STICKING OF THE PROPELLER. THE CONDITION WAS CAUSED BY THE JAM NUT HANGING BETWEEN THE HUB AND THE BETA PICK-UP PL ATE. THE RESULTING DAMAGE TO THE HUB WAS CAUSE FOR RETIREMENT OF THE HUB. (X) 1 L 7 2 4T A24CE 5 C STC 2001010200007 20010102 00007 SO 2001 1 2 20000907SH026 1 20000815 G 2421 3656624 ALTERNATOR PIPER PA28 PA28R201 7102816 SO FAILED D O OTHER H ELECT. POWER LOSS-50 PC NR NOT REPORTED 1 WP 05 5145W 28R7837098 NO ELECTRICAL OUTPUT. ALTERNATOR END BELL CRACKED COMPLETELY THROUGH ONE SIDE. ONE DIODE COPPER LEAD BROKEN IN TWO. R OTOR RUBBING. ALTERNATOR OVERHAULED 3-26-90. TOTAL TIME SINCE O/H: 920 HOURS. (X) 1 L 7 1 3O 2A13 2000122000002 20001220 00002 CE 2000 12 20 20000907SH033 1 20000524 G 2822 476411 TRANSFER PUMP CESSNA 402 402B 207590P CE TIP TANK INOPERATIVE E MHJA K NONE O OTHER IN INSP/MAINT 1 SW 05 402PJ 159 402B0591 SUBMITTER STATED THIS MODEL NUMBERED TRANSFER PUMP IS CONSISTENTLY FAILING AT 300 HOURS OR LESS CAUSING A DANGEROUS COND ITION FOR PILOTS. INSTALLED ON 4-5-00. FAILED ON 5-24-00. (X) 1 L 7 2 3O A7CE 2000122000003 20001220 00003 CE 2000 12 20 20000907SH034 1 20000417 G 2822 476411 TRANSFER PUMP CESSNA 401 401 207590C CE TIP TANK FAILED E MHJA K NONE O OTHER IN INSP/MAINT 1 SW 05 3208Q 368 4010008 SUBMITTER STATED THIS IS ONLY ONE OF MANY INCIDENTS. THESE PUMPS ARE REPEATEDLY FAILING AROUND 300 OR LESS HOURS. INST ALLED ON 11-15-99. FAILED ON 4-17-00. (X) 1 L 7 2 3O A7CE 2000122000004 20001220 00004 CE 2000 12 20 20000907SH035 1 20000810 G 2822 476411 TRANSFER PUMP CESSNA 401 401 207590C CE TIP TANK INOPERATIVE E MHJA K NONE O OTHER IN INSP/MAINT 1 SW 05 3208Q 211 4010008 SUBMITTER STATED THIS MODEL NUMBERED TRANSFER PUMP IS CONSISTENLY FAILING AT 300 HOURS OR LESS CAUSING A DANGEROUS CONDI TION FOR PILOTS AND INCREASED MAINTENANCE. INSTALLED ON 5-19-00. FAILED ON 8-10-00. (X) 1 L 7 2 3O A7CE 2000122000005 20001220 00005 CE 2000 12 20 20000907SH036 1 20000803 G 2822 476411 TRANSFER PUMP CESSNA 402 402B 207590P CE TIP TANK INOPERATIVE E MHJA K NONE O OTHER IN INSP/MAINT 1 SW 03 402PJ 76 402B0591 SUBMITTER STATED THIS MODEL NUMBERED TRANSFER PUMP IS CONSISTENTLY FAILING AT 300 HOURS OR LESS CAUSING A DANGEROUS COND ITION FOR PILOTS AND INCREASED MAINTENANCE. INSTALLED ON 5-22-00. FAILED ON 6-3-00. (X) 1 L 7 2 3O A7CE 2000122000006 20001220 00006 SO 2000 12 20 20000907SH037 1 20000817 G 2720 6345100 SUPPORT BRACKET PIPER PA28 PA28140 7102802 SO CROSSBAR CRACKED B JZRR K NONE O OTHER IN INSP/MAINT 1 EA 07 1692T 5960 287125009 BRACKET ATTACHMENT HOLES CRACKED IN SEVERAL DIRECTIONS (4 HOLES TOTAL). FOUND RUDDER PEDAL CROSSBAR MOVEMENT DURING ANN UAL. METAL FATIGUE AND LIGHT WEIGHT STEEL (.035 INCH) MAY BE CAUSE OF FAILURE. SUBMITTER RECOMMENDED GUSSETS WELDED AT HOLES OF PART CONSTRUCTED FROM THICKER MATERIAL. (X) 1 L 7 1 3O 2A13 2000122000007 20001220 00007 2000 12 20 20000907SH038 4 20000512 G 6122 BEARING MCAULY CESSNA 402 402C 207590R CE INSIDE GOVERNOR DESTROYED D A UNSCHED LANDING R PARTIAL RPM/PWR LOSS TO TAKEOFF 1 EA 07 548GA 1299 791519 402C0653 PILOT REPORTED LOSS OF POWER ON TAKEOFF. MAINTENANCE FOUND PROPELLER GOVERNOR LEAKING OIL AND CONFIRMED POWER LOSS. CH ANGED GOVERNOR AND RETURNED AIRCRAFT TO SERVICE. TEAR DOWN OF GOVERNOR REVEALED INTERNAL FAILURE CAUSED BY BEARING FAIL URE. (X) 1 L 7 2 3O A7CE 2001010200008 20010102 00008 CE 2001 1 2 20000907SH039 1 20000814 G 3244 650108PLY TIRE CESSNA 402 402C 207590R CE LEFT MAIN UNSERVICEABLE D O OTHER O OTHER TX TAXI/GRND HDL 1 EA 07 4652N 99 62140615 402C0011 CREW REPORTED UNUSUAL NOISE ON TAXI. FOUND CHUNK OF AFT TIRE MISSING. MAINTENANCE DISPATCHED TO CHANGE TIRE. FOUND LA RGE PORTION OF RECAP HAD SEPARATED FROM CORE TIRE. MAINTENANCE REMOVED AND REPLACED TIRE AND RELEASED AIRCRAFT BACK INT O SERVICE. (X) 1 L 7 2 3O A7CE 2001022000260 20010220 00260 2001 2 20 20000907SH040 4 20000810 G 6122 D20591 DRIVE GEAR MCAULY CESSNA 180 180 2072602 CE PROP GOVERNOR CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 70634 RELEVANT MT INDICATION AROUND GEAR TEETH. (X) 1 H 7 1 3O NC 5A6 2000101200003 20001012 00003 SO 2000 10 12 20000908SH001 1 20000907 G 2842 SENSOR PIPER PA28 PA28161 7102803 SO MISINSTALLED H OG5S K NONE W INADEQUATE Q C CR CRUISE 1 GL 21 275ND 2842097 PILOT REPORTED FUEL SELECTOR DRAW WAS FROM OPPOSITE TANK SELECTED. TROUBLESHOOTING BY MAINTENANCE FOUND THE WIRES FROM THE FUEL TANK SENDER WERE SWAPPED AT THE INDICATORS. WIRES WERE REMOVED AND REINSTALLED PER THE MANUFACTURER''S WIRE DI AGRAM. SYSTEM FUNCTIONED NORMALLY. (SUBMITTED BY FAR-FSDO FROM FORM 8010-4 SUPPLIED BY OPERATOR). (X) 1 L 7 1 3O 2A13 2000101900117 20001019 00117 SO 2000 10 19 20000908SH002 1 20000907 G 7603 554528 THROTTLE CABLE PIPER PA44 PA44180 7104402 SO RIGHT SEPARATED B OG5S D RETURN TO BLOCK R PARTIAL RPM/PWR LOSS CL CLIMB 1 GL 21 292ND 1311 4496023 AFTER TAKEOFF DURING POWER REDUCTION, RIGHT THROTTLE WOULD NOT DECREASE BELOW 20 INCHES MANIFOLD PRESSURE. AIRCRAFT RETU RNED TO BASE UNEVENTFULLY. INSPECTION REVEALED THROTTLE CABLE SEIZED AT ENGINE SIDE WHERE CABLE EMERGES FROM OUTER SHEA TH. THE OUTER SHEATH HAD SEPARATED AT FLEXIBLE SWEDGE THAT ALLOWED INCREASE OF THROTTLE POSTION BUT LIMTED RETARDING TO 20 INCHES MANIFOLD PRESSURE. CABLE REPLACED AND AIRCRAFT RETURNED TO SERVICE. (SUBMITTED BY FAR-FSDO FROM INFORMATION O N FORM 8010-4 SUPPLIED BY OPERATOR). (X) 1 L 7 2 3O A19S0 2000122000008 20001220 00008 EA 2000 12 20 20000908SH003 2 20000817 G 8530 LW11625 PLUG LYC CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA CYLINDER MAKING METAL D K NONE O OTHER IN INSP/MAINT 1 WP 19 67719 728 15281981 L2438215 AN EXCESSIVE AMOUNT OF ALUMINUM WAS FOUND IN THE OIL SCREEN DURING A 50-HOUR INSPECTION. THE METAL WAS SENT TO LYCOMING FOR EVALUATION AND IT WAS DETERMINED TO BE FROM THE PISTON PIN PLUGS. ALL CYLINDERS WERE REMOVED AND ALL PLUGS SHOW EX CESSIVE WEAR TO VARYING DEGREES. SUBMITTER SUGGESTED POSSIBLE CAUSE AS A DEFECT IN THE METAL USED TO FABRICATE THE END PLUGS. (X) 1 H 7 1 3O 3 O NT 3A19 E223 2000122000009 20001220 00009 SO 2000 12 20 20000908SH004 1 20000908 G 8100 AM52192037 CLAMP PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA VOSS CLP THREADS STRIPPED E K NONE O OTHER IN INSP/MAINT 1 NM 08 84859 1500 317305043 CLAMP AND NUT THREADS SEPARATED CAUSING CLAMP TO SPRING OPEN. THUS, HIGH PRESSURE TURBO AIR LEAKED OVERBOARD CAUSING MA NIFOLD PRESSURE TO DROP TO 25 POUNDS (NATURALLY ASPIRATED). (X) 1 L 7 2 3O 3 O A20SO E14EA 2000122000010 20001220 00010 CE 2000 12 20 20000908SH005 1 20000802 G 2410 S159660L CIRCUIT BREAKER CESSNA 172 172M 2072418 CE BREAKER PANEL INOPERATIVE D A UNSCHED LANDING B H SMOKE/FUMES/ODORS/SPARKS ELECT. POWER LOSS-50 PC NR NOT REPORTED 1 NM 11 9912Q 5673 17265856 PILOT DEPARTED BOISE, NOTICED SMOKE IN THE COCKPIT AND RETURNED FOR LANDING. ALTERNATOR CIRCUIT BREAKER FAILED (DUE TO AGE). NO OTHER DAMAGE FOUND. (X) 1 H 7 1 3O NT 3A12 2000122000011 20001220 00011 CE 2000 12 20 20000908SH006 1 20000814 G 2750 0510105122 CONTROL CABLE CESSNA 185 A185F 2072821 CE TE FLAPS SEPARATED D O OTHER O OTHER NR NOT REPORTED 1 NM 11 4892E 2500 18503897 CABLE PARTED .25 INCH AFT OF MS20668-3 SWAGED TERMINAL EYE END FITTING, IN AN AREA VERY DIFFICULT TO INSPECT VISUALLY, C AUSING SUDDEN FLAP RETRACTION. SUBMITTER RECOMMENDED PERIODIC INSPECTION EVEN IF IT REQUIRES REMOVAL OF THE CABLE. SUB MITTER STATED DESIGN OF INSTALLATION MAY CAUSE BEND IN CABLE IMMEDIATELY ADJACENT TO RIGID END FITTING. (X) 1 H 7 1 3O 3A24 2000122000012 20001220 00012 SO 2000 12 20 20000908SH008 2 20000815 G 7414 TCM10382584 POINTS CESSNA 206 U206 2073306 CE CONT O520 IO520A 17032 SO FAILED B K NONE O OTHER IN INSP/MAINT 1 GL 15 527NR 184 U2060278 DURING PRE-INSPECTION RUN-UP BY MECHANIC, FOUND UNUSUAL MAG DROP ON RIGHT MAGNETO REMOVED FOR TROUBLESHOOTING. FOUND TH E POINT ASSY CONTACT LOOSE AND FALLING OUT OF SPRING ARM. REPLACED CONTACT ASSY. OPS CHECKED GOOD. THIS MAG HAD 184 H OURS SINCE A TCM OVERHAUL. THE MAGNETOS CAME ON A RECENTLY OVERHAULED TCM IO520 ENGINE. (X) 1 H 7 1 3O 3 O A4CE E5CE 2000122000013 20001220 00013 CE 2000 12 20 20000908SH009 1 20000827 G 2810 FUEL CAP BEECH 18 D18S 1151004 CE GARRTT TPE331 TPE33110 01514 WP LEAKING E KKFA K NONE O OTHER IN INSP/MAINT 1 GL 23 502CK 14825 12165 A366 P93049C RIGHT ENGINE SLOWLY ROLLED BACK AND SHUT-DOWN. REMOVED WATER CONTAMINATION FROM FUEL SYSTEM AND TANKS. REPLACED ENGINE FUEL FILTER WITH NEW. REPLACED RIGHT MAIN TANK FUEL CAP WITH NEW. PEFORMED GROUND RUN, LEAK AND PERFORMANCE CHECK IAW GARRETT RUN-UP FORM TTF-0052. (X) 1 L 7 2 3R 4 T A765 E4WE 2000122000014 20001220 00014 2000 12 20 20000908SH010 4 20000815 G 6122 B20908 FLYWEIGHT MCAULY CONT O520 IO520* 17032 SO FAILED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 790153 RELEVANT INDICATION ACROSS FLYWEIGHT BODY. (X) 3 O E5CE 2001010200009 20010102 00009 SO 2001 1 2 20000908SH011 2 20000731 G 7414 1052948 ROTOR S6RN201 CESSNA 182 182D 2072710 CE CONT O470 O470L 17026 SO ROTOR BEARINGS OVERHEATED D K NONE O OTHER IN INSP/MAINT 1 NM 10 9103X 467 K279618ER 18253503 819441L4 MAGNETO DISASSEMBLED FOR 500-HOUR MAINTENANCE, BALL BEARINGS, PN 1081806 AND PN 2202, FROM ROTATING MAGNET ASSY WERE OBS ERVED TO HAVE A SMOKY-BLUE CAST. ROTOR WAS RE-ASSEMBLED IN CASE HALVES TO FACILITATE SHAFT END PLAY CHECK WITH DIAL IND ICATOR. PER SERVICE MANUAL, 30 POUNDS OF FORCE WAS EXERTED ON ROTOR SHAFT IN EACH DIRECTION - NO PERCEPTIBLE NEEDLE REF LECTION RESULTED. SM SPECIFIES INITIAL ROTOR SHAFT END PLAY SHOULD BE FROM 0.0005 INCH TO 0.0015 INCH LOOSE TO OBTAIN P ROPER BEARING PRELOAD. BY REMOVING SHIMS AND RE-CHECKING END PLAY, IT WAS DETERMINED ROTOR BEARINGS WERE UNDER A COMPRE SSION LOAD OF APPROXIMATELY 0.003 INCHES. (X) 1 H 7 1 3O 3 O NT 3A13 E273 2001011104203 20010111 04203 2001 1 11 20000908SH012 1 20000821 G 2560 EAMT46 LIFE RAFT MISMANUFACTURED B K NONE W INADEQUATE Q C IN INSP/MAINT 1 EU 01 OCVYD TEMPORARY PACKING TIE HAD BEEN LEFT ON THE PACKED LIFE RAFT. SUBMITTER STATED THIS WOULD HAVE PREVENTED DEPLOYMENT. DI SCOVERED WHEN RAFT WAS RECEIVED FOR OVERHAUL. THE MANUFACTURE DATE WAS NOVEMBER, 1998, 2001020700260 20010207 00260 EU 2001 2 7 20000908SH013 1 20000831 G 6710 BUSHING SNIAS 350 AS350B3 8680954 EU MAIN ROTOR SEIZED G K NONE O OTHER IN INSP/MAINT 1 NM 11 392LG 3252 FOUND BUSHINGS LOCKED UP CAUSING DAMAGE TO THE SCISSORS HOUSING, PN 350A37-1126-02. FOUR NEW PARTS DID THE SAME THING. PARTS FROM ANOTHER AIRCRAFT WORKED OK. THE NEW PARTS WERE DAMAGED IN 2-5 HOURS. POSSIBLE CAUSE IS BUSHINGS IN THE NEW PARTS MAY HAVE BEEN MISALIGNED. (X) 1 G 7 1 3U H9EU 2001020700262 20010207 00262 SW 2001 2 7 20000911SH003 1 20000619 G 6320 206040221003 SHAFT BELL 206 206B3 1181506 SW FREEWHEEL UNIT WORN B GJQR K NONE O OTHER IN INSP/MAINT 1 NM 01 GPGH 2976 4022 DURING OVERHAUL INSPECTION, DISCOVERED BEARING OUTBRACE HAD ROTATED IN HOUSING. EXCESSIVE WEAR IN HOUSING INSIDE DIAMET ER. WILL C/W BELL TECH BULLETIN 206-95-155 THAT INSTALLS SLOTTED OUTER SHAFT WITH KEYED BEARING WHICH IS TO CORRECT THE BEARING ROTATION PROBLEM. (X) 1 G 7 1 3U H2SW 2001030100005 20010301 00005 EA 2001 3 1 20000911SH004 2 20000821 G 7414 4271 MAGNETO LYC O320 O320B2B 41508 EA ENGINE INOPERATIVE B K NONE O OTHER IN INSP/MAINT 1 SW 09 590 L345027 ENGINE WOULD NOT START NORMALLY. COIL IN MAGNETO SHOWING OPEN. THIS LEFT MAG OPENED AND REPLACED, FAULTY COIL (NUMBER ON COIL, M3525 0310). 3 O E274 2001030100006 20010301 00006 EA 2001 3 1 20000911SH005 2 20000821 G 7414 4270 MAGNETO LYC O320 O320B2B 41508 EA ENGINE MALFUNCTIONED B K NONE O OTHER IN INSP/MAINT 1 SW 09 590 L345027 ENGINE RAN OKAY. MAGNETO DISASSEMBLED AS PRECAUTIONARY. FOUND COIL OUT OF LIMITS WITH VERY HIGH RESISTANCE ON SECONDAR Y CIRCUIT. (COIL NR 5, M3525 011989). (X) 3 O E274 2001030100007 20010301 00007 EA 2001 3 1 20000911SH010 2 20000828 G 8500 C4170 GEAR HARTZL LYC O540 IO540* 41532 EA IDLER CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 6100 E244U RELEVANT MAG PARTICLE INDICATION ON GEAR TEETH. (X) 3 O 1E4 2001030100008 20010301 00008 EA 2001 3 1 20000911SH011 2 20000828 G 8500 C4170 GEAR HARTZL LYC O540 IO540* 41532 EA IDLER CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 B440U RELEVANT MAG PARTICLE INDICATION ON IDLER GEAR TEETH. (X) 3 O 1E4 2001030100009 20010301 00009 EA 2001 3 1 20000911SH012 2 20000828 G 8500 B41832 FLYWEIGHT HARTZL LYC O540 IO540* 41532 EA GOVERNOR CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 B4401U RELEVANT MAG PARTICLE INDICATION ON FLYWEIGHT TOE. (X) 3 O 1E4 2001020700263 20010207 00263 SW 2001 2 7 20000911SH013 1 20000809 G 5302 206033412121A BRACKET BELL 206 206L1 1182107 SW TAIL BOOM DAMAGED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 WHILE FITTING NEW BEARING SUPPORT BRACKET ON TAILBOOM, DISCOVERED CONTOUR WAS NOT CORRECT, TABS WERE OVER BENT AND UNDER BENT. (X) 1 G 7 1 3U H2SW 2001020700264 20010207 00264 SW 2001 2 7 20000911SH014 1 20000809 G 5302 206033412119A BRACKET BELL 206 206L1 1182107 SW TAIL BOOM DAMAGED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 DURING FITTING NEW BEARING SUPPORT BRACKET ON TAILBOOM, DISCOVERED CONTOUR WAS NOT CORRECT, THE TABS WERE OVER BENT AND UNDER BENT. (X) 1 G 7 1 3U H2SW 2001020700265 20010207 00265 SW 2001 2 7 20000911SH015 1 20000809 G 5302 206033412001A BRACKET BELL 206 206L1 1182107 SW TAIL BOOM DAMAGED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 DURING FITTING BEARING SUPPORT BRACKET ON TAILBOOM, DISCOVERED CONTOUR WAS NOT CORRECT, THE TABS WERE OVER BENT AND UNDE R BENT. (X) 1 G 7 1 3U H2SW 2001030100010 20010301 00010 GL 2001 3 1 20000911SH017 3 20000823 G 6111 HUB MCAULY MCAULY 2A34C D2A34C98 GL PROPELLER DAMAGED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 738532 RELEVANT ET INDICATION, 4TH THREAD UP. (X) 5 C P3EA 2000120600002 20001206 00002 SO 2000 12 6 20000911SH018 1 20000829 G 3244 175X625610P TIRE PIPER PA42 PA42 7104202 SO NOSE SHEARED B O OTHER O OTHER LD LANDING 1 SO 11 112BC 82 428001027 TIRE SHREADED ON LANDING. (X) 1 L 7 2 4T A23SO 2000120600003 20001206 00003 EA 2000 12 6 20000911SH019 2 20000816 G 8500 ENGINE PIPER PA46 PA46350P SO LYC O540 TIO540AE2A 41532 EA MAKING METAL B AMYR K NONE O OTHER IN INSP/MAINT 1 CE 05 12KW 139 4636255 L1040961A DURING OIL CHANGE AND OIL FILTER INSPECTION, FOUND METAL IN THE OIL FILTER AND METAL WAS FOUND IN THE SUCTION SCREEN. 5 0 TO 60 PIECES WERE FOUND IN OIL FILTER AND TWO FLAKES WERE FOUND IN THE SUCTION SCREEN. (X) 1 L 7 1 3O 3 O RT A25SO E14EA 2000120600004 20001206 00004 NE 2000 12 6 20000911SH020 2 20000821 G 7220 3018018 RIVET PWA CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE LT ENGINE INLET MISSING A UG8A K NONE O OTHER IN INSP/MAINT 1 GL 23 225J 5500283 PCE70878 RIVET MISSING IN LEFT ENGINE INLET AND ONE FAN BLADE HAD SMALL CURL AT LEADING EDGE TIP. REPLACED MISSING RIVET, INSPEC TED AND REPAIRED FAN ASSEMBLY. (X) 1 L 7 2 4F 4 F A22CE E1NE 2000120600005 20001206 00005 SO 2000 12 6 20000911SH021 1 20000826 G 2400 A002581 SWITCH PIPER PA38 PA38112 7103812 SO UNDER RT VNT PNL SHORTED C K NONE O OTHER IN INSP/MAINT 1 WP 17 2408L 3879A0696 DURING LEVEL FLIGHT WITH NORMAL ELECTRICAL LOAD, ALTERNATOR INOP SWITCH INTERNALLY SHORTED. THE UNIT WAS SEALED. CAUSE IS MOST LIKELY THE AGE OF PART AND NORMAL DEGRADATION OF INTERNAL CIRCUITRY. (X) 1 L 7 1 3O A18SO 2000120600006 20001206 00006 SO 2000 12 6 20000911SH022 1 20000823 G 3230 2075209 HOUSING PIPER PA30 PA30 7103002 SO RT GEAR BROKEN B O OTHER O OTHER LD LANDING 1 CE 07 282P 30508 AFT SUPPORTING PORTION OF THE RIGHT GEAR HOUSING BROKE AND ALLOWED THE POSITION TO SHIFT WHICH CAUSED IT TO HANG UP IN T HE WHEELWELL. AIRCRAFT LANDED GEAR UP BECAUSE GEAR COULD NOT BE EXTENDED USING ELECTRIC MOTOR OR MANUAL LEVER. HAD TO PRY GEAR OUT OF WHEELWELL DURING RECOVERY. (X) 1 L 7 2 3O A1EA 2000120600008 20001206 00008 SO 2000 12 6 20000911SH024 1 20000812 G 7921 20006A OIL COOLER PIPER PA32 PA32R300 7103213 SO LYC 0540 IO540K1G5D 41532 SO LEAKING D K NONE K A FLUID LOSS FLAME/FIRE CR CRUISE 1 GL 23 38984 32R7780495 L1688448A PILOT DEPARTED AIRPORT. DURING CLIMB APPROXIMATELY 2 MINUTES INTO FLIGHT, NOTICED NO OIL PRESSURE INDICATION. QUICKLY RETURNED TO DEPARTURE AIRPORT. ENGINE FAILED ON FINAL DUE TO OIL STARVATION. A SAFE LANDING WAS MADE. ENGINE SEIZED A ND THREW PARTS THROUGH CRANKCASE. UPON INVESTIGATION, OIL COOLER WAS FOUND TO HAVE PIN-HOLE IN BOTTOM. THIS COOLER WAS NEW 1 YEAR AND 117 HOURS PRIOR. INSTALLED IAW LO-PRESTI COWLING MODIFICATION. (X) 1 L 7 1 3O 3 O A3SO 1E4 2000120600009 20001206 00009 CE 2000 12 6 20000911SH025 2 20000813 G 7322 RSA5AD2 SERVO PIPER PA34 PA34220T 7103420 SO CONT O360 TSIO360RB 17025 CE FAILED B VJ3R O OTHER R PARTIAL RPM/PWR LOSS LD LANDING 1 WP 07 4128X 3449112 819255R ON LANDING , LEFT ENGINE LAGGED POWER TO LANDING. THE RPM DROPPED FROM 2,400 TO 1,800. THROTTLE POWER TO 22 INCHES. ( X) 1 L 7 2 3O 3 O A7SO E9CE 2000120600010 20001206 00010 SO 2000 12 6 20000911SH026 1 20000815 G 2710 62701123 CONTROL CABLE PIPER PA28 PA28181 7102807 SO FRAYED B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 VJ3R 1341 2843207 AILERON BALANCE CABLE FRAYED. LOCATED UNDER THE REAR SEATS. (X) 1 L 7 1 3O 2A13 2000120600011 20001206 00011 SO 2000 12 6 20000911SH027 1 20000821 G 2710 62701123 CONTROL CABLE PIPER PA28 PA28181 7102807 SO AILERON FRAYED B K NONE O OTHER IN INSP/MAINT 1 WP 07 4139A 2142 2843115 AILERON BALANCE CABLE FRAYED. LOCATED UNDER THE REAR SEATS. (X) 1 L 7 1 3O 2A13 2000120600012 20001206 00012 SO 2000 12 6 20000911SH028 1 20000821 G 2740 62701113 CONTROL CABLE PIPER PA28 PA28181 7102807 SO FRAYED B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 4139A 5142 2843115 STABILATOR CONTROL CABLE FRAYED. (X) 1 L 7 1 3O 2A13 2000120600013 20001206 00013 SO 2000 12 6 20000911SH029 1 20000824 G 2710 62701125 CONTROL CABLE PIPER PA34 PA34220T 7103420 SO FRAYED B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 4177R 2297 3449046 LEFT HAND BALANCE CABLE FRAYED, NEW CABLE INSTALLED. (X) 1 L 7 2 3O A7SO 2000120600014 20001206 00014 SO 2000 12 6 20000911SH030 1 20000823 G 2750 87765041 CONTROL CABLE PIPER PA34 PA34220T 7103420 SO TE FLAPS FRAYED B K NONE O OTHER IN INSP/MAINT 1 WP 07 4177R 2292 3449046 FLAP SELECTOR CABLE FRAYED WHERE THE CABLE GOES AROUND THE PULLYS AT THE FLAP SELECTOR. (X) 1 L 7 2 3O A7SO 2000120600015 20001206 00015 SO 2000 12 6 20000911SH031 1 20000823 G 2740 62701047 CONTROL CABLE PIPER PA28 PA28181 7102807 SO FRAYED B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 4166H 2843119 AFT STABILATOR TRIM CABLE FRAYED. (X) 1 L 7 1 3O 2A13 2000120600016 20001206 00016 SO 2000 12 6 20000911SH032 1 20000821 G 2700 6270147 CONTROL CABLE PIPER PA28 PA28181 7102807 SO FRAYED B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 4144P 1990 2843121 TRIM CABLE FRAYED AT REAR DRUM. (X) 1 L 7 1 3O 2A13 2000120600017 20001206 00017 SO 2000 12 6 20000911SH033 2 20000821 G 7322 RSA5AD2 SERVO PIPER PA34 PA34220T 7103420 SO CONT O360 LTSIO360RB SO FAULTY B VJ3R O OTHER O OTHER IN INSP/MAINT 1 WP 07 4142N 41 3449128 322021RN ENGINE RUNNING RICH AND BLOWING BLACK SMOKE. UNABLE TO ADJUST MIXTURE. REMOVED AND SENT BACK TO TCM. (X) 1 L 7 2 3O 3 O A7SO E9CE 2000120600018 20001206 00018 CE 2000 12 6 20000911SH034 2 20000727 G 7322 RSA3AD2 SERVO PIPER PA34 PA34220T 7103420 SO CONT O360 TSIO360RB 17025 CE FAULTY B VJ3R O OTHER R PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 WP 07 4128X 158 3449112 819255R WILL NOT IDLE UNLESS BOOST PUMP IS ON, MIXTURE TOO LEAN. SERVO REMOVED AND SENT BACK TO TCM. (X) 1 L 7 2 3O 3 O A7SO E9CE 2000120600019 20001206 00019 SO 2000 12 6 20000911SH035 1 20000825 G 2740 62701104 CONTROL CABLE PIPER PA28 PA28181 7102807 SO STAB TRIM FRAYED B K NONE O OTHER IN INSP/MAINT 1 WP 07 4132D 1242 2843234 TRIM CABLE FRAYED (FRONT CABLE AT TRIM WHEEL). (X) 1 L 7 1 3O 2A13 2000120600020 20001206 00020 SO 2000 12 6 20000911SH036 1 20000725 G 2710 62701123 CONTROL CABLE PIPER PA28 PA28181 7102807 SO FRAYED B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 4132D 1144 2843234 RIGHT HAND AILERON BALANCE CABLE FRAYED. LOCATED UNDER THE REAR SEATS. (X) 1 L 7 1 3O 2A13 2000120600021 20001206 00021 SO 2000 12 6 20000911SH037 1 20000815 G 2710 62701127 CONTROL CABLE PIPER PA34 PA34220T 7103420 SO FRAYED B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 4123C 1694 3449042 RIGHT HAND AILERON BALANCE CABLE FRAYED AT WING ROOT PULLEY. (X) 1 L 7 2 3O A7SO 2000120600022 20001206 00022 SO 2000 12 6 20000911SH038 1 20000815 G 2710 62701127 CONTROL CABLE PIPER PA34 PA34220T 7103420 SO FRAYED B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 4123C 1694 3449042 LEFT HAND AILERON BALANCE CABLE FRAYED AT WING ROOT PULLEY. (X) 1 L 7 2 3O A7SO 2000120600023 20001206 00023 SO 2000 12 6 20000911SH039 1 20000815 G 2750 8776541 CONTROL CABLE PIPER PA34 PA34220T 7103420 SO SELECTOR FLAP FRAYED B K NONE O OTHER IN INSP/MAINT 1 WP 07 4123C 1694 3449042 FLAP SELECTOR CABLE FRAYED WHERE THE CABLE GOES AROUND THE PULLEYS AT THE FLAP SELECTOR. (X) 1 L 7 2 3O A7SO 2000120600024 20001206 00024 CE 2000 12 6 20000911SH040 2 20000821 G 7322 RSA5AD2 SERVO PIPER PA34 PA34220T 7103420 SO CONT O360 TSIO360RB 17025 CE FAULTY B VJ3R O OTHER R PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 WP 07 4123C 3449042 819258R UNABLE TO ADJUST FUEL FLOW AT IDLE. (X) 1 L 7 2 3O 3 O A7SO E9CE 2000120600001 20001206 00001 SO 2000 12 6 20000911SH041 2 20000828 G 8540 35016 GEAR TELEDYNECNTL PIPER PA18 PA18 7101802 SO CONT C90 C908F 17009 SO CRANK SHAFT FRACTURED G B A EMER. DESCENT UNSCHED LANDING Y Z ENGINE STOPPAGE SIGNIFICANT FAILURE REPORT IN INSP/MAINT 1 EA 01 3357A 3418 25 183004 4065788 AIRCRAFT MADE AN EMERGENCY LANDING FOLLOWING SUDDEN ENGINE FAILURE DURING CRUISE FLIGHT. UPON INSPECTION, THE CRANKSHAF T GEAR HAD 5 OR 6 TEETH MISSING AND THE REMAINING TEETH WERE ROUNDED AND EXHIBITED GALLING-LIKE DAMAGE SIMILAR TO THAT F OUND ON THE MAGNETO DRIVE GEARS. ALSO THERE WAS SOME GOUGING IN THE REAR HOUSING AREA, ADJACENT TO THE CRANKSHAFT GEAR. AN ENGINE OVERHAUL WAS COMPLETED DURING THE LAST ANNUAL INSPECTION ON 2/5/2000, AND SINCE HAD ACCUMULATED ONLY 25.3 HO URS. (X) 1 H 7 1 3O 3 O 1A2 E252 2000120600025 20001206 00025 2000 12 6 20000911SH042 4 20000824 G 6122 A153A2 FLYWEIGHT HARTZL LYC O540 IO540* 41532 EA DEFECTIVE B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 B2405U RELEVANT MAG PARTICLE INSPECTION INDICATION AT BOTTOM OF FLYWEIGHT BASE. (X) 3 O 1E4 2000120600026 20001206 00026 EA 2000 12 6 20000911SH044 2 20000816 G 8520 LW13383 BAFFLE PIPER PA46 PA46350P SO LYC O540 TIO540AE2A 41532 EA FWD VERT DEFLECT MISALIGNED B AMYR O OTHER K FLUID LOSS IN INSP/MAINT 1 CE 05 4170K 26 4636297 L1056061A ENGINE OIL QUICK DRAIN WOULD NOT SHUT OFF DUE TO ONE SHEARED OFF RIVET HEAD, MS 20470-4, BLOCKING HOLE IN DRAIN VALVE. REF LYC SB 489A. OIL SUMP BAFFLE ASSY HAD THE VERTICAL DEFLECTOR FLANGE MISALIGNED TO BAFFLE PLATE AND THE TENSION LOAD POPPED THE RIVET HEAD OFF. RIVET LOCATED AT AFT END OF FORWARD VERTICAL DEFLECTOR. (X) 1 L 7 1 3O 3 O RT A25SO E14EA 2001011104205 20010111 04205 CE 2001 1 11 20000911SH045 1 20000821 G 3411 10220001812 ALTIMETER CESSNA 185 A185F 2072821 CE CONT O550 IO550* SO INSTRUMENT PANEL STUCK D O OTHER O OTHER NR NOT REPORTED 1 WP 23 4805 18504432 ALTIMETER STICKING EXCESSIVELY 500-600 FEET. THIS AIRCRAFT WAS PITOT STATIC TESTED THE DAY BEFORE THE FLIGHT FROM PLAC ERVILLE CA TO WHITEMAN AIRPARK. THIS ALTIMETER HAS AN INTERNAL ENCODER. THE PITOT STATIC CASE WAS ORDERED TO BE C/W PR IOR TO CLOSURE OF THE SALE OF THIS ACFT. THE ANNUAL WAS SIGNED OFF WITH NO PITOT STATIC TEST C/W. (X) 1 H 7 1 3O 3 O 3A24 E3SO 2000120600027 20001206 00027 CE 2000 12 6 20000911SH046 1 20000831 G 3250 051010552 CONTROL CABLE CESSNA 185 185F 2072820 CE TAIL WHEEL STEER WRONG PART D K NONE O OTHER IN INSP/MAINT 1 WP 23 4805 18504432 AIRCRAFT WAS SOLD WITH TWO DIFFERENT SIZED TAILWHEEL STEERING CABLES (LEFT CABLE WAS 60 INCHES LONG AND THE RIGHT CABLE WAS 58.50 INCHES LONG), AND THE .1250 INCH CABLE STAYS WERE REPLACED WITH .0625 INCH DIAMETER SOFT COTTER KEYS WHICH CAU SED EXCESSIVE TAIL WHEEL SHIMMY UPON THE FIRST LANDING OF THIS AIRCRAFT BY THE NEW OWNER. THIS AIRCRAFT WAS SOLD WITH A NEW ANNUAL. (X) 1 H 7 1 3O 3A24 2000100300046 20001003 00046 CE 2000 10 3 20000912SH001 1 20000731 G 3230 S217840096 HOSE CESSNA 182 R182 2072734 CE NOSE GEAR SEPARATED D A UNSCHED LANDING K FLUID LOSS CR CRUISE 1 GL 09 4629S R18201361 HOSE SEPARATED AT SWAGED END CAUSING LOSS OF FLUID AND NOSE GEAR TO FALL INTO AIRSTREAM. CESSNA INSPECTION CHECKLIST CA LLS OUT FOR THIS HOSE ALONG WITH REST OF LANDING GEAR HOSES TO BE REPLACED ON CONDITION FOR THIS AIRCRAFT. SUBMITTER RE COMMENDED CHANGING REQUIREMENT TO 5 TO 8 YEAR LIFE ON THESE HOSES. (X) 1 H 7 1 3O RT 3A13 2001020100044 20010201 00044 SW 2001 2 1 20000912SH002 1 20000614 G 6510 407340339103 BEARING BELL 407 407 SW T/R DRIVESHAFT ROUGH A ALGA K NONE O OTHER IN INSP/MAINT 1 SW 03 467AL 126 A263 53190 TAIL ROTOR DRIVESHAFT IN FOR REPAIR OF RIVET MISSING FROM OIL COOLER BLOWER HOUSING. FOUND BEARING ROUGH. (X) 1 G 7 1 3U O H2SW 2001020100045 20010201 00045 SW 2001 2 1 20000912SH003 1 20000614 G 6510 407340339103 BEARING BELL 407 407 SW T/R DRIVESHAFT ROUGH A ALGA K NONE O OTHER IN INSP/MAINT 1 SW 03 467AL 126 A263 53190 TAIL ROTOR DRIVESHAFT IN FOR REPAIR OF RIVET MISSING FROM OIL COOLER BLOWER HOUSING. FOUND BEARING ROUGH. (X) 1 G 7 1 3U O H2SW 2001020100046 20010201 00046 SW 2001 2 1 20000912SH004 1 20000729 G 5302 STRUCTURE BELL 407 407 SW TAIL BOOM CRACKED A ALGA K NONE O OTHER IN INSP/MAINT 1 SW 03 497AL 2747 1406 53207 53172 DURING DAILY SERVICE CHECK AND AD 2000-06-10/ASB 407-99-29 REVISION A, FOUND CRACK IN TAILBOOM SKIN FROM UNDER THE HORIZ ONTAL STABILIZER SUPPORT TO THE FIRST RIVET ABOVE THE SUPPORT. LOCATION LEFT AFT OF THE HORIZONTAL STABILIZER AT THE FO RMER BOOM STA 120.75. (X) 1 G 7 1 3U O H2SW 2001020700266 20010207 00266 SW 2001 2 7 20000912SH005 1 20000721 G 2810 206362002103 FUEL CAP BELL 407 407 SW FUEL CELL LEAKING B ALGR K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 427AL 4309 53107 DURING DAILY INSPECTION, FOUND FUEL CAP LEAKING, CRACKED AT LOCKING MECHANISM. (X) 1 G 7 1 3U O H2SW 2001020700267 20010207 00267 SW 2001 2 7 20000912SH006 1 20000808 G 6322 407062021101 DUCT BELL 407 407 SW OIL COOLER CRACKED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 587AL 272 53248 DURING DAILY INSPECTION, FOUND A CRACK IN THE CORNER. (X) 1 G 7 1 3U O H2SW 2001020100047 20010201 00047 EU 2001 2 1 20000912SH007 1 20000806 G 2612 WIRE BOLKMS 105 BO105C 5626005 EU ALLSN 250C 250C20B 03013 GL NR 1 ENGINE BROKEN A ALGA O OTHER N FALSE WARNING CR CRUISE 1 SW 03 501AL S58 IN CRUISE FLIGHT, NR 1 ENGINE FIRE LIGHT ILLUMINATED. FOUND AND REPAIRED BROKEN WIRE. (X) 1 G 7 2 3U 3 U H3EU E4CE 2001020100048 20010201 00048 NE 2001 2 1 20000912SH008 1 20000815 G 3260 WARNING LIGHT SKRSKY S76 S76A 8143006 NE MLG ILLUMINATED A ALGA O OTHER N FALSE WARNING NR NOT REPORTED 1 SW 03 519AL 760058 BEFORE LANDING, UNSAFE GEAR INDICATION, (LEFT MAIN, NO GREEN, RED STAYED ON). RECYCLED GEAR AND ALL GREEN LIGHTS ILLUMI NATED. VISUALLY CHECKED GEAR AND SWITCHES. NO DEFECTS WERE NOTED. (X) 1 G 7 2 3U H1NE 2001021600036 20010216 00036 SO 2001 2 16 20000912SH009 2 20000824 G 8520 631716 CRANKSHAFT CESSNA 210 P210N 2073454 CE CONT O520 TSIO520P 17040 SO ENGINE FAILED G A UNSCHED LANDING Y ENGINE STOPPAGE CL CLIMB 1 EA 01 5256W 3054 1254 P21000664 51391 ENGINE FAILED AFTER TAKEOFF RESULTING IN FORCED LANDING. INSPECTION OF ENGINE REVEALED CRANKSHAFT FAILED BETWEEN THE NR 2 AND NR 3 JOURNALS. (X) 1 H 7 1 3O 3 O 3A21 E8CE 2001021600037 20010216 00037 SO 2001 2 16 20000912SH010 1 20000828 G 2910 3152700 HYDRAULIC LINE PIPER PA23 PA23250 7102308 SO LT OF PILOT SEAT CHAFED B HI1R K NONE O OTHER IN INSP/MAINT 1 NE 05 500KW 277405264 UPON INSP, FOUND THE LEFT RUDDER CABLE CHAFING ON HYD LINE ATTACHED TO THE LEFT LANDING GEAR SEQ VALVE . THE CABLE HAD CHAFED THRU APPROX 50 PERCENT OF THE HYD LINE OVER A 2 INCH AREA. LOCATION OF AREA IS BEHIND THE PANEL ON THE LEFT SIDE OF THE PILOT SEAT. THE LINE IS ON THE BOTTOM OF A GROUP OF LINES WHICH ARE SECURED TOGETHER BY STAND-OFF LACING. RUDD ER CABLE IS ROUTED SLIGHTLY DIAGONALLY BELOW HYD LINE. 1 L 7 2 3O 1A10 2001020100049 20010201 00049 SW 2001 2 1 20000912SH011 1 20000720 G 6510 407340340101 DISC PACK BELL 407 407 SW TAIL ROTOR CRACKED A ALGA K NONE O OTHER IN INSP/MAINT 1 SW 03 687AL 396 A1729 53366 DURING 25-HOUR AD INSPECTION, FOUND AFT SEGMENT CRACKED IN 3 PLACES ACROSS THE SPAN. (X) 1 G 7 1 3U O H2SW 2001020700268 20010207 00268 SW 2001 2 7 20000912SH012 1 20000802 G 6510 407340340101 DISC PACK BELL 407 407 SW TAIL ROTOR CRACKED A ALGA K NONE O OTHER IN INSP/MAINT 1 SW 03 687AL A1673 53366 DURING 25-HOUR AD INSPECTION, FOUND AFT SEGMENT CRACKED ACROSS THE SPAN. (X) 1 G 7 1 3U O H2SW 2001020700269 20010207 00269 SW 2001 2 7 20000912SH013 1 20000809 G 6320 406040029101 SUN GEAR BELL 407 407 SW TRANSMISSION MAKING METAL B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 607AL 2158 A273 53264 TRANSMISSION ASSEMBLY MAKING METAL. SUN GEAR UPPER TEETH PITTED (BREAKING DOWN). SUN GEAR SCRAPPED. (X) 1 G 7 1 3U O H2SW 2001020100050 20010201 00050 SW 2001 2 1 20000912SH014 1 20000806 G 6510 407340340101 DISC PACK BELL 407 407 SW TAIL ROTOR CRACKED A ALGA K NONE O OTHER IN INSP/MAINT 1 SW 03 627AL 124 A1176 53284 DURING 25-HOUR AD INSPECTION, FOUND AFT SEGMENT IS CRACKED ACROSS THE SPAN IN TWO PLACES 180 DEGREES APART. (X) 1 G 7 1 3U O H2SW 2001020100051 20010201 00051 SW 2001 2 1 20000912SH015 1 20000722 G 5754 407023801133 BRACKET BELL 407 407 SW SLATS CRACKED A ALGA O OTHER D INFLIGHT SEPARATION NR NOT REPORTED 1 SW 03 647AL 554 53357 PILOT NOTICED THE LEFT CENTER SLAT MISSING AFTER LANDING AND SHUT-DOWN AT OFFSHORE PLATFORM MC268. MOUNTING BRACKETS FO R THE LEFT CENTER SLAT WERE CRACKED AND BROKEN ALLOWING SLAT TO DEPART THE AIRCRAFT. LEFT VERTICAL FINLET WAS DAMAGED B Y THE MISSING SLAT. (X) 1 G 7 1 3U O H2SW 2001020100052 20010201 00052 SW 2001 2 1 20000912SH016 1 20000722 G 5754 407023801131 BRACKET BELL BELL 407 407 SW SLATS CRACKED A ALGA O OTHER D INFLIGHT SEPARATION NR NOT REPORTED 1 SW 03 647AL 554 53357 AFTER LANDING AND SHUT-DOWN AT OFFSHORE PLATFORM MC268. MOUNTING BRACKETS FOR THE LEFT CENTER SLAT WERE CRACKED AND BRO KEN ALLOWING SLAT TO DEPART THE AIRCRAFT. LEFT VERTICAL FINLET WAS DAMAGED BY THE MISSING SLAT. (X) 1 G 7 1 3U O H2SW 2001021600038 20010216 00038 CE 2001 2 16 20000912SH017 1 20000822 G 2822 DO299038R PUMP BEECH 33 F33A 1151425 CE CONT O520 IO520BB 17032 SO ENGINE LEAKING B VJ3R K NONE K FLUID LOSS IN INSP/MAINT 1 WP 07 6311Z 1036 CE997 813765R WHEN HOT, THERE WAS NO PRESSURE, AND FUEL LEAKED OUT OF DRAIN. (X) 1 L 7 1 3O 3 O 3A15 E5CE 2001020800969 20010208 00969 SW 2001 2 8 20000912SH018 1 20000731 G 6730 41002979103 SLEEVE TEXTRON BELL 407 407 SW BYPASS SPOOL BINDING B ALGR O OTHER O OTHER NR NOT REPORTED 1 SW 03 587AL 2780 HR763 53248 PILOT REPORTED AN INTERMITTENT BIND. INTERMITTENT BIND IN SERVO ACTUATOR. (X) 1 G 7 1 3U O H2SW 2001010200010 20010102 00010 EA 2001 1 2 20000912SH019 2 20000912 G 7414 10382807F CAPACITOR BENDIX CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA MAGNETO COVER OPEN D K NONE O OTHER IN INSP/MAINT 1 SW 99 734HZ 691 I029912GR 17268878 L141676 OPEN ''P'' LEAD CIRCUIT. (X) 1 H 7 1 3O 3 O NT 3A12 E274 2001010200011 20010102 00011 CE 2001 1 2 20000912SH020 1 20000726 G 2821 07560052 STRAINER CESSNA 172 172N 2072434 CE FUEL STRAINER MALFUNCTIONED B DINR K NONE O OTHER IN INSP/MAINT 1 EA 13 734JS 2824 17268895 BOTH AD2000-06-01 AND SEB97-9 DID NOT APPLY TO THIS AIRCRAFT. (STRAINER HAD NOT BEEN SWAPPED OUT). DURING ROUTINE MAIN TENANCE, SHOP INSPECTS THE STANDPIPE OF THESE STRAINERS SINCE IT IS A VERY EASY PROCEDURE. DURING MAINTENANCE OF THE FU EL STRAINER, FOUND THE STANDPIPE WAS EXTENDED TOO FAR AND ACTUALLY PULLED OUT OF THE TOP ASSY WITH FINGER PRESSURE ONLY. STRAINER WAS REPLACED WITH SERVICEABLE UNIT. (X) 1 H 7 1 3O NT 3A12 2001010200012 20010102 00012 CE 2001 1 2 20000912SH021 1 20000625 G 3230 S20496FG ROD END CESSNA 177 177RG 2073709 CE FAILED B O OTHER O OTHER LD LANDING 1 EA 17 7520V 4580 177RG0817 WHEN PILOT SELECTED GEAR DOWN, HE HEARD A POP/BANG UNDER THE FLOOR AND THE MAIN GEAR FAILED TO EXTEND. ACFT WAS LANDED GEAR UP WITH MINIMAL AIRFRAME DAMAGE. INVEST REVEALED MAIN GEAR ACTUATOR ROD END BEARING PN S2049-6FG HAD FAILED AND SP LIT APART AT THE SPHERICAL END. FAILURE APPEARS TO HAVE STARTED AT THE HOLE IN THE ROD END USED FOR GREASING. AREA INS P APPROX 8 HRS PRIOR, DURING ANNUAL, WITH NO VISUAL DEFECTS. FOUND OLD CESSNA SI LETTER SE79-37 RECOMMENDING ROD END RE PLACEMENT WITH PN S2426-6, WHICH IS NOW SUPERCEDED TO PN S3469-1. NEW P/N IS A SEALED UNIT WITH NO GREASER HOLE. SUBMI TTER RECOMMENDED CESSNA RE-ADDRESS THIS AS A SERVICE BULLETIN WITH HIGHER PRIORITY. (X) 1 H 7 1 3O A20CE 2001020800970 20010208 00970 NE 2001 2 8 20000912SH022 1 20000811 G 7603 7630101015001 ROLLER SKRSKY S76 S76B 8143007 NE THROTTLE DETACHED H K NONE O OTHER IN INSP/MAINT 1 EA 01 780P 3680 760359 THE PIN THAT HOLDS THE ROLLER FOR POSITIVE THROTTLE DETENTS FAILED COMPLETELY AND THE ROLLER AND PIN ASSEMBLY FELL INTO THE THROTTLE QUADRENT. SINCE THE QUADRENT IS IN AN OVERHEAD POSITION, THERE WAS NO THROTTLE RESTRICTION WITH THIS FAILU RE. (X) 1 G 7 2 4U H1NE 2001020800971 20010208 00971 SW 2001 2 8 20000912SH023 1 20000710 G 6510 407040320101 SHAFT BELL BELL 407 407 SW NR 2 WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 847AL 1146 A166 53150 DURING PHASE INSPECTION, FOUND SPLINES WORN BEYOND LIMITS. (X) 1 G 7 1 3U O H2SW 2000092100501 20000921 00501 CE 2000 9 21 20000912SH024 1 20000825 G 3213 5141001212 TRUNNION CESSNA 310 310Q 2074242 CE BELLCRANK ATTACH FAILED D O OTHER O OTHER TX TAXI/GRND HDL 1 GL 15 8403F 5123 310Q0640 AFTER LANDING AND WHILE TURNING LEFT OFF OF RUNWAY ONTO TAXIWAY, RIGHT GEAR COLLAPSED. FOUND RIGHT GEAR TRUNNION UPPER BARREL TO BELLCRANK CASTING FAILED AND THE LOWER SIDE LINK SEPARATED AT ADJUSTMENT BOLT. POSSIBLE CAUSE: LOWER SIDE LI NK ADJUSTMENT BOLT SEPARATED AS GEAR COLLAPSED AS EVIDENT BY BEND IN BOLT. EXACT CAUSE OF FAILURE IS NOT KNOWN, POSSIBL Y THE UPPER BARREL FITTING FAILED. (X) 1 L 7 2 3O 3A10 2000092100502 20000921 00502 SO 2000 9 21 20000912SH025 2 20000824 G 7314 654351A1 PUMP PIPER PA34 PA34220T 7103420 SO CONT O360 LTSIO360RB SO FAILED B VJ3R O OTHER O OTHER IN INSP/MAINT 1 WP 07 9299E 86 3449043 819507R WITH TOP END FUEL PRESSURE SET IAW SPEC, AT IDLE, THE PUMP PRESSURE DROPS TO LOW. LESS THAN 25 PSI TO OPERATE FUEL SERV O AT IDLE. (X) 1 L 7 2 3O 3 O A7SO E9CE 2000092100503 20000921 00503 SO 2000 9 21 20000912SH026 2 20000725 G 7314 F2899168R PUMP PIPER PA34 PA34220T 7103420 SO CONT O360 LTSIO360RB SO FAILED B VJ3R O OTHER O OTHER IN INSP/MAINT 1 WP 07 9299E 3449043 819507R IDLE PRESSURE WAS LOW AND UNABLE TO ADJUST HIGHER. PRESSURE WAS ALSO ERRATIC. (X) 1 L 7 2 3O 3 O A7SO E9CE 2000092100504 20000921 00504 SO 2000 9 21 20000912SH027 1 20000823 G 2710 62701126 CONTROL CABLE PIPER PA34 PA34220T 7103420 SO WING ROOT FRAYED B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 9299E 2091 3449043 RIGHT HAND AILERON BALANCE CABLE FRAYED AT WING ROOT PULLEY. (X) 1 L 7 2 3O A7SO 2000092100505 20000921 00505 CE 2000 9 21 20000912SH028 1 20000426 G 2730 50934032 TAPER PIN CESSNA 421 421C 2076016 CE TORQ TUBE COLLAR LOOSE B GICA K NONE O OTHER IN INSP/MAINT 1 NM 01 88EQ 421C0821 ELEVATORS IN ACFT ARE ATTACHED TO A FLANGED COLLAR WITH TAPER PIN, PN 5035017-1. TAPER PIN WORKED LOOSE WHICH OVALED OU T THE HOLES IN THE COLLAR AND TORQUE TUBE. AT INSP, COULD HOLD ONE ELEV RIGID, MOVE OTHER ELEV APPROX 1 INCH ON BOTH SI DES. CESSNA TECH REPS ACKNOWLEDGED THIS HAS BEEN A PROBLEM ON THE 421. THE ONLY APPROVED CESSNA REPAIR IS TO REPLACE C OLLAR WITH NEW STYLE COLLAR TWICE AS LONG, ALLOWS A HOLE TO BE DRILLED THRU TORQUE TUBE OTBD. NEW COLLAR INSTALLED ON ACFT DURING PREV REPAIR OF SAME CONDITION. ONLY APPROVED REPAIR TO 2ND OCCURRENCE IS TO INSTALL A NEW TORQUE TUBE ASSY THAT COMES WITH SHORTER COLLAR. ALLOWS CYCLE TO BEGIN AGAIN INSTEAD OF A FIX. (CANNOT PURCHASE SHORT COLLAR SEPARATE). 1 L 7 2 3O A7CE 2000092100506 20000921 00506 CE 2000 9 21 20000912SH029 1 20000202 G 7931 1013890233 TRANSDUCER BEECH 90 C90A 1152911 CE PWA PT6 PT6A21 52043 EA ENG COMPARTMENT FAILED B UGIR A UNSCHED LANDING N Y FALSE WARNING ENGINE STOPPAGE CR CRUISE 1 SW 03 68TW 4790 LJ1200 PCE25424 RIGHT ENGINE OIL PRESSURE INDICATION FAILED IN-FLIGHT. ENGINE SHUT DOWN. UNEVENTFUL LANDING. (X) 1 L 7 2 3T 4 T RT 3A20 E4EA 2000092100507 20000921 00507 EA 2000 9 21 20000912SH030 2 20000531 G 8520 72877 LIFTER CESSNA 185 A185E 2072818 CE LYC O540 TIO540J2BD 41532 EA NR 2 EXH LIFTER FAILED B YB3R A UNSCHED LANDING Y ENGINE STOPPAGE CR CRUISE 1 WP 07 694BK 1851582 L474361A THE FAILURE OCCURRED IN-FLIGHT RESULTING IN A FORCED LANDING. POSSIBLE CAUSE FROM FRACTURE OF LIFTER BODY. (X) 1 H 7 1 3O 3 O 3A24 E14EA 2001011105093 20010111 05093 CE 2001 1 11 20000912SH031 1 20000830 G 2800 FUEL LINE PREAIR BEECH 23 C24R 1151254 CE LYC O360 IO360A1B6 41514 EA FUEL SYSTEM DETERIORATED D O OTHER R PARTIAL RPM/PWR LOSS CR CRUISE 1 GL 11 18981 3320 30 MC545 L1805851A IN CRUISE FLIGHT, ENGINE RAN ROUGH HAD LOW EGT 900 DEGREES. ON NR 2 CYLINDER. AFTER LANDING AND TROUBLESHOOTING, FOUND DEBRIS IN FUEL LINE FROM SERVO TO FLOW DIVIDER. REPLACED RUBBER FUEL LINE WITH TEFLON LINE P/N LW12784-4-172 IAW LYCOMI NG SI 1274B. SUBMITTER SUGGESTED REPLACING ALL FUEL AND OIL LINES WITH TEFLON TYPE LINES. TT ON RUBBER FUEL LINE 30 HO URS. (X) 1 L 7 1 3O 3 O A1CE 1E10 2001011101150 20010111 01150 CE 2001 1 11 20000912SH032 1 20000830 G 2810 FUEL LINE PREAIR BEECH 23 C24R 1151254 CE LYC O360 IO360A1B6 41514 EA FUEL SYSTEM DETERIORATED D O OTHER R PARTIAL RPM/PWR LOSS CR CRUISE 1 GL 11 18981 3320 30 MC545 L1805851A IN CRUISE FLIGHT, ENGINE RAN ROUGH HAD LOW EGT 900 DEGREES. ON NR 2 CYLINDER.AFTER LANDING AND TROUBLESHOOTING, FOUND D EBRIS IN FUEL LINE FROM SERVO TO FLOW DIVIDER. REPLACED RUBBER FUEL LINE WITH TEFLON LINE P/N LW12784-4-172 IAW LYCOMIN G SI 1274B. SUGGESTED SUGGESTED REPLACING ALL FUEL AND OIL LINES WITH TEFLON TYPE LINES. TT ON RUBBER FUEL LINE 30 HOU RS. (X) 1 L 7 1 3O 3 O A1CE 1E10 2001010200014 20010102 00014 CE 2001 1 2 20000913SH007 1 20000829 G 2822 6467682A1 PUMP CESSNA 206 TU206F 2073353 CE CONT O520 TSIO520C 17040 SO LEAKING H K NONE K FLUID LOSS IN INSP/MAINT 1 NM 08 1953U 55 U20602306 178573R REPLACEMENT (FOR REBUILT) BRAND NEW FUEL PUMP FOUND LEAKING FUEL FROM PORT SIDE ENGINE COWL BEFORE FLIGHT. POSSIBLE CAU SE, BROKEN DIAPHRAGM. (X) 1 H 7 1 3O 3 O A4CE E8CE 2001010200015 20010102 00015 CE 2001 1 2 20000913SH008 1 20000829 G 2822 6467682A1 PUMP CESSNA 206 TU206F 2073353 CE LEAKING H K NONE K FLUID LOSS IN INSP/MAINT 1 NM 08 1953U 96 U20602306 FUEL CONTINUOUSLY LEAKING FROM PORT SIDE ENGINE COWL. FOUND AT END OF FLIGHT. POSSIBLE CAUSE, BROKEN DIAPHRAGM. (X) 1 H 7 1 3O A4CE 2001010300002 20010103 00002 SO 2001 1 3 20000913SH009 2 20000830 G 8530 CYLINDER HEAD BEECH 33 F33A 1151425 CE CONT O520 IO520BA 17032 SO CYLINDER ASSY DEPARTED E XGNA O OTHER R PARTIAL RPM/PWR LOSS CR CRUISE 1 SW 05 1096W 1033 CE436 249271A CYLINDER HEAD DEPARTED BARREL WHILE AIRCRAFT IN-FLIGHT. (X) 1 L 7 1 3O 3 O 3A15 E5CE 2001010300003 20010103 00003 EU 2001 1 3 20000913SH011 1 20000828 G 5740 D22200361 FITTING WSK M18A M18A EU RIGHT WING CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 11 2297L 5155 01730 AIRCRAFT WAS INSPECTED IAW SPECIAL AIRWORTHINESS INFO BULLETIN NR CE-00-27, DATED ULY 11, 2000. MAG PARTICAL INSPECTION REVEALED CRACK IN RIGHT BOTTOM FITTING, BACK SIDE. (X) 1 L 7 1 3O NC A47EU 2001010300004 20010103 00004 EU 2001 1 3 20000913SH012 1 20000828 G 5740 D22200241 BRACKET WSK M18A M18A EU RIGHT WING CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 11 2297L 5155 1Z01730 AIRCRAFT WAS INSPECTED IAW SPECIAL AIRWORTHINESS INFO BULLETIN NR CE-00-27 DATED JULY 11, 2000. VISUAL INSPECTION REVEA LED CRACKS IN UPPER AND LOWER CUT-OUT SLAT. (X) 1 L 7 1 3O NC A47EU 2001010300006 20010103 00006 CE 2001 1 3 20000913SH014 1 20000821 G 3220 98600661 LOCK CESSNA 185 185F 2072820 CE CABIN/TAIL WHEEL MISSING D K NONE O OTHER IN INSP/MAINT 1 WP 23 4805 18504432 TAIL WHEEL LOCK ASSEMBLY MISSING EVERYTHING BUT THE LOCK ITSELF WHICH IS MOUNTED ON THE TAIL WHEEL. NR 337 SHOWING REMO VAL OF THESE PARTS. AIRCRAFT WAS ORIGINALLY MOUNTED ON FLOATS. AIRCRAFT WAS SOLD WITH WHEEL GEAR INSTALLED AND ANNUALE D IN THIS CONDITION. SALES PEOPLE CONVINCED THE NEW OWNER THAT THE TAIL LOCK ASSY WAS NOT NECESSARY ON THIS AIRCRAFT. TAIL WHEEL LOCK LEVER ALSO MISSING. (X) 1 H 7 1 3O 3A24 2001010200016 20010102 00016 CE 2001 1 2 20000913SH015 1 20000827 G 2741 12606041 INDICATOR CESSNA 206 206H 2073301 CE ELEV TRIM IND MALFUNCTIONED B FTKR K NONE O OTHER IN INSP/MAINT 1 GL 19 631AF 206 20608070 PILOT REPORTED CONTINUOUS TRIM INDICATOR MALFUNCTION. AFTER NUMEROUS ATTEMPTS TO RESET INDICATOR, A NEW PART WAS RECEIV ED. THE TANG WHICH RIDES IN THE TRIM WHEEL WAS FOUND TO BE SHORT BY 50 PERCENT. NEW INDICATOR INSTALLED WITH NO FURTHE R PROBLEMS. (X) 1 H 7 1 3O RT A4CE 2001010300007 20010103 00007 CE 2001 1 3 20000913SH016 1 20000821 G 2822 120040663 LINE CESSNA 210 T210F 2073422 CE LINE TO AUX PUMP LEAKING B FTKR A UNSCHED LANDING K Y FLUID LOSS ENGINE STOPPAGE CR CRUISE 1 GL 19 6777R 2205 T2100177 PILOT REPORTED ENGINE STARTED SURGING THEN CUTTING OUT PRIOR TO COMPLETING THE APPROACH TO LANDING. THE PILOT WAS FORCE D TO LAND SHORT OF THE AIRPORT RESULTING IN DAMAGE TO THE AIRCRAFT. INVESTIGATION RESULTED AN IN-FLIGHT FUEL LEAK FROM THE RIGHT MAIN TANK. ADDITIONALLY, EVIDENCE THAT FUEL WAS BEING LOST IN THE WHEELWELL. THE OUTLET LINE FROM THE AUXILI ARY FUEL PUMP WAS FOUND BARELY SNUG AND EVIDENCE OF FUEL STAINING ON AND AROUND THE FITTING AREA. SUBMITTER SUPPOSED FU EL EXHAUSTION TO ENGINE TO BE CAUSE OF INCIDENT. SUBMITTER SUGGESTED SOME TYPE OF SAFETY/LOCKING DEVICE FOR THOSE LINES THAT COULD BE MOUNTING VIBRATION. (X) 1 H 7 1 3O 3A21 2001010300008 20010103 00008 SO 2001 1 3 20000913SH017 1 20000713 G 3242 1690010 DRUM PIPER PA22 PA22150 7102210 SO BRAKE DRUM WARPED H O OTHER O OTHER IN INSP/MAINT 1 NM 08 1940P 3092 222691 INNER WHEEL HALF ASSEMBLY CAUSING BRAKE DRUMS TO WARP. FOUND EXCESSIVE BRAKE DRAGGING WHEN PERFORMING ANNUAL INSPECTION . SINCE NO SPECIFIC KEY POSITION, ASSEMBLY CAN BE TAKEN OFF AND RE-ASSEMBLED IN DIFFERENT POSITIONS. WHEN TORQUING, WA RPING CAN OCCUR IN BRAKE ASSEMBLY. CAUSE IS DUE TO INACCURACY OF CASTING AT ALL CONTACT POINTS. SUBMITTER SUGGESTED ST AMPING ON THE INNER HALF OF WHEEL AND BRAKE ASSY AS REFERENCE MARK CAN HELP PREVENT WARPING. (X) 1 H 7 1 3O 1A6 2001010300009 20010103 00009 EA 2001 1 3 20000913SH018 1 20000831 G 3244 275K221 TIRE DHAV DHC2 DHC2MK1 2800102 EA RETREAD LEVEL 5 SEPARATED H A3L2 K NONE O OTHER IN INSP/MAINT 1 SW 09 715 1517 NOSE TIRE TREAD SEPARATION FROM CARCASS. SUBMITTER SUSPECTED FOD. (X) 1 H 7 1 3R A806 2001010300010 20010103 00010 CE 2001 1 3 20000913SH019 1 20000721 G 5210 SWITCH BEECH 200 200BEECH 1152920 CE MISRIGGED D O OTHER P NO WARNING INDICATION CR CRUISE 1 WP 23 113GW 6887 BB541 CABIN DOOR WAS NOT COMPLETELY LOCKED BEFORE FLIGHT. DOOR BLEW OPEN DURING PRESSURIZED FLIGHT AT 12,500 FEET. CABIN DOO R WARNING LIGHT MICROSWITCH WAS MISRIGGED TO ALLOW THE WARNING LIGHT TO BE OUT, BUT THE DOOR NOT COMPLETELY LOCKED. SUB MITTER RECOMMENDED TO CLOSELY INSPECT THE DOOR LATCHING RIGGING DURING PHASE 3 INSPECTION TO INSURE THE MICROSWITCH DOES NOT CLOSE BEFORE THE DOOR HANDLE GOES OVERCENTER TO THE LOCKED POSITION. (X) 1 L 7 2 4T A24CE 2001022000123 20010220 00123 SO 2001 2 20 20000913SH021 1 20000802 G 2823 11383004 SELECTOR KNOB PIPER PA22 PA22108 7102204 SO LT CABIN WALL WORN D K NONE O OTHER IN INSP/MAINT 1 NM 11 4689Z 228227 FUEL SELECTOR VALVE IS HARD TO SET IN THE DESIRED POSITION WITHOUT LOOKING AT IT. THE DETENTS ARE NOT POSITIVE ENOUGH A ND THE SELECTORS GET STIFF IF NOT USED ENOUGH. (X) 1 H 7 1 3O 1A6 2001022000124 20010220 00124 SO 2001 2 20 20000913SH022 1 20000802 G 2823 492014 SELECTOR KNOB PIPER PA22 PA22108 7102204 SO LT CABIN WALL WORN D K NONE O OTHER IN INSP/MAINT 1 NM 11 4689Z 228227 FUEL SELECTOR VALVE IS HARD TO SET IN THE DESIRED POSITION WITHOUT LOOKING AT IT. THE DETENTS ARE NOT POSITIVE ENOUGH A ND THE SELECTORS GET STIFF IF NOT USED ENOUGH. (X) 1 H 7 1 3O 1A6 2001030100011 20010301 00011 SW 2001 3 1 20000913SH027 1 20000830 G 7160 88021719 PLENUM GULSTM 690TP 690A 0141722 SW INLET CRACKED B MV5R K NONE O OTHER IN INSP/MAINT 1 GL 11 500TS 5174 11209 INLET PORTION OF PLENUM ASSEMBLY CRACKED AT WELD AREA. (X) 1 H 7 2 3T 2A4 2001022100041 20010221 00041 CE 2001 2 21 20000913SH028 1 20000913 G 7160 16991007721 ALT AIR DOOR BEECH 23 C24R 1151254 CE LYC O360 IO360A1B6 41514 EA ENGINE BROKEN D A UNSCHED LANDING Y ENGINE STOPPAGE CR CRUISE 1 WP 07 397RC 30008 MC631 DURING A FLIGHT LESSON, ENGINE LOST POWER AND AN EMERGENCY LANDING WAS MADE, NO INJURIES OR DAMAGE. DURING INSPECTION A FTER LANDING, ENGINE DEVELOPED POWER WHEN COLD. REMOVED AIR FILTER ELEMENT, DISCOVERED HEAT DAMAGE TO FILTER ELEMENT AN D FOUND ALT AIR DOOR HAD BROKEN AWAY FROM ITS HINGE AND HAD BECOME LODGED IN THE INTAKE OF THE FUEL SERVO. AIRCRAFT INS PECTED 81 HOURS PREVIOUSLY WITH NO DEFECTS NOTED. SUBMITTER RECOMMENDED PAYING CLOSE ATTENTION TO THE ALT AIR DOOR DURI NG INSPECTION, INSTALLING A SCREEN TO PREVENT A TOTAL BLOCKING OF THE INTAKE IF DOOR FAILS, AND INSTALLING A DOUBLER OVE R THE DOOR WHERE IT ATTACHES TO THE HINGE. (X) 1 L 7 1 3O 3 O A1CE 1E10 2001022100058 20010221 00058 SO 2001 2 21 20000913SH029 1 20000831 G 2731 62701104 CONTROL CABLE PIPER PA28 PA28181 7102807 SO STABILATOR TRIM FRAYED B K NONE O OTHER IN INSP/MAINT 1 WP 07 4181M 2041 2843120 TRIM CABLE FRAYED (FRONT CABLE AT TRIM WHEEL). (X) 1 L 7 1 3O 2A13 2001022100059 20010221 00059 SO 2001 2 21 20000913SH030 2 20000830 G 7322 RSA5AD SERVO PIPER PA34 PA34220T 7103420 SO CONT O360 LTSIO360RB SO FUEL INJECTOR INOPERATIVE B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 4138X 3449112 321749R UNABLE TO ADJUST FUEL FLOW AND IDLE MIXTURE. NEW SERVO. (X) 1 L 7 2 3O 3 O A7SO E9CE 2001022100061 20010221 00061 SO 2001 2 21 20000913SH031 2 20000830 G 7322 RSA5AD SERVO PIPER PA34 PA34220T 7103420 SO CONT O360 LTSIO360RB SO FUEL INJECTOR MALFUNCTIONED B VJ3R E ENGINE SHUTDOWN O OTHER CR CRUISE 1 WP 07 4128X 3449112 32179R FUEL FLOW RIGHT ENGINE DROP 3 GALLONS PER HOUR. IN-FLIGHT, CHT AND TIT TEMP WENT HIGHER THAN THE OTHER ENGINE. ENGINE STARTED TO RUN ROUGH. ENGINE WAS SHUT DOWN IN-FLIGHT AND A SAFE LANDING ON ONE ENGINE WAS MADE. INSPECTION OF ENGINE F OUND THE RIGHT FUEL SERVO WAS LEAN AT ALL POWER SETTINGS. SERVO REPLACED. (X) 1 L 7 2 3O 3 O A7SO E9CE 2001022100062 20010221 00062 SO 2001 2 21 20000913SH032 1 20000828 G 2710 62701127 CONTROL CABLE PIPER PA34 PA34220T 7103420 SO LT AILERON FRAYED B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 4128X 1340 3449112 LEFT AILERON FORWARD CABLE FRAYED. (X) 1 L 7 2 3O A7SO 2001022100063 20010221 00063 SO 2001 2 21 20000913SH033 1 20000828 G 2710 62701124 CONTROL CABLE PIPER PA28 PA28181 7102807 SO RT AILERON FRAYED B XJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 4133D 2241 2843117 CABLE FRAYED AT FUSELAGE. RIGHT AILERON BALANCE CABLE. (X) 1 L 7 1 3O 2A13 2001022100066 20010221 00066 SO 2001 2 21 20000913SH034 1 20000828 G 2730 6270113 CONTROL CABLE PIPER PA28 PA28181 7102807 SO LT STABILATOR FRAYED B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 4133D 2241 2843117 LEFT FORWARD STABILATOR CONTROL CABLE FRAYED. (X) 1 L 7 1 3O 2A13 2001022100067 20010221 00067 SO 2001 2 21 20000913SH035 1 20000828 G 2731 62701104 CONTROL CABLE PIPER PA28 PA28181 7102807 SO STABILATOR TRIM FRAYED B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 4133D 2241 2843117 TRIM CABLE FRAYED (FORWARD TRIM CABLE). (X) 1 L 7 1 3O 2A13 2001030100012 20010301 00012 NE 2001 3 1 20000914SH004 2 20000818 G 8550 59500347 FITTING CESSNA 208 208B 2073701 CE PWA PT6 PT6A114 52043 NE ENGINE LEAKING B K NONE K FLUID LOSS IN INSP/MAINT 1 SW 99 1295G 208B0841 AIRCRAFT ARRIVED WITH OIL LEAK. ACFT LOST 1/2 QUART OF OIL DURING A 3.5 HOUR FLIGHT. T/S REVEALED OIL LEAKING FROM THE TOP OF THE TORQUE LINE ADAPTER, PN 5950034-7, MOUNTED AT THE FRONT OF THE ENG. INSP REVEALED FITTING, PN 5950034-7, HA D DRILLED TO ALLOW A .1250 INCH PIPE THREAD FITTING TO BE INSTALLED. HOLE DRILLED, BUT THE .1250 INCH PIPE THREADS WERE NOT CUT. THE .1250 INCH PIPE THREAD FITTING WAS INSTALLED, TORQUED AT THE FACTORY. FITTING ASSY LEAKED ONLY WHEN ENG WAS RUN AT HIGH POWER SETTINGS. AT HIGH POWER SETTINGS, TORQUE FITING HAD PRESS IN RANGE OF 30/60 PSI. TECH REMOVED TH E FITTING, CUT .1250 INCH PIPE THREADS AND REINSTALLED ASSY. ENG TAKEOFF POWER RUNS, LEAK CHECKS OK. HOBBS: 22.0. (X) 1 H 7 1 3T 3 T A37CE E4EA 2001022100072 20010221 00072 2001 2 21 20000914SH005 4 20000829 G 3416 AK350 ENCODER CESSNA 172 172M 2072418 CE INSTRUMENT PNL FAILED B K NONE O OTHER IN INSP/MAINT 1 SW 99 20466 1460 17261310 ENCODER SHOWED PROPER PRESSURE ALTITUDE FOR APPROXIMATELY 25 MINUTES. AFTER THAT TIME, ENCODER STARTED TO REPORT (PLUS) 100 FOOT ERROR EVERY 2 MINUTES UNTIL THE ERROR BECAME ABOUT 600 FEET. AFTER THAT, THE ENCODER WANDERED UP AND DOWN ABO UT 200 FEET. UNIT WAS REPLACED WITH NEW ENCODER. (X) 1 H 7 1 3O NT 3A12 2001022100073 20010221 00073 SO 2001 2 21 20000914SH006 1 20000823 G 2810 2722100 FUEL CAP PIPER PA30 PA30 7103002 SO FUEL TANKS LEAKING B AW4R K NONE O OTHER IN INSP/MAINT 1 WP 11 3JM 30144 DURING TROUBLESHOOTING FOR FUEL CONTAMINATION PROBLEMS, NOTED WATER LEAKING FROM FUEL CAP. UPON DISASSEMBLY OF CAPS, FO UND EVIDENCE OF MOISTURE INSIDE CAPS. CAPS ARE TYPICAL, OLDER PIPER ''THREADS BOTTLE'' CAPS. DESIGN ALLOWS WATER TO EN TER INTERIOR OF CAP THROUGH LOCKING LEVER SHAFT. IF BOTTOM METAL PORTION OF CAP IS DISTORTED OR ATTACH HARDWARE IS CORR ODED, WATER CAN DIRECTLY ENTER TANK, ESPECIALLY IF TANK FILLER SCUPPER DRAINS ARE PLUGGED. TIME SINCE LAST INSPECTION, 25 HOURS. AIRCRAFT TOTAL TIME APPROXIMATELY 4,800 HOURS. (X) 1 L 7 2 3O A1EA 2001022100074 20010221 00074 SW 2001 2 21 20000914SH007 1 20000815 G 3210 71461R GEAR BBAVIA 8 8GCBC 1220803 SW RT MLG BROKEN B AW4R K NONE O OTHER LD LANDING 1 WP 11 8638V 4900 16275 UPON LANDING, RT GEAR LEG, PN 7-1461-R, FAILED AT AREA OF U-BOLT ATTACH CLAMP. FAILURE RESULTED IN DAMAGE TO RT WING, P ROPELLER, ENGINE AND COWLING. AIRCRAFT IS USED FOR GLIDER TOWING FROM AN UNPAVED RUNWAY AND AVERAGES 3-5 TAKEOFFS AND L ANDINGS PER HOUR. TOTAL CYCLES ON GEAR LEG ARE ESTIMATED TO BE BETWEEN 15,000 TO 20,000. CRACK APPEARS TO BE FATIGUE R ELATED AND IS BEING INVESTIGATED BY THE NTSB LABORATORIES. SUBMITTER RECOMMENDED A LIFE-LIMIT BE ESTABLISHED FOR THESE GEAR LEGS. TIME SINCE LAST INSPECTION IS APPROXIMATELY 170 HOURS. (X) 1 H 7 1 3O A21CE 2001022100075 20010221 00075 EA 2001 2 21 20000914SH008 2 20000823 G 7414 106B2016 GEAR CESSNA 182 TR182 2072735 CE LYC O540 O540J3C5 41532 EA MAGNETO BROKEN B AW4R K NONE O OTHER IN INSP/MAINT 1 WP 11 63BD 170 B119801GR R18201067 PILOT REPORTED RT PORTION OF MAGNETO INOPERATIVE (TCM DOUBLE MAG). INVESTIGATION REVEALED SEVERAL TEETH BROKEN FROM RT DISTRIBUTOR GEAR (PN 10-682016) ALLOWING GEAR NOT TO ROTATE. INSPECTION OF LT GEAR SHOWED ONE TOOTH BROKEN, HOWEVER, GE AR WAS STILL ABLE TO TURN. CAUSE OF FAILURE UNKNOWN, IT IS SUSPECTED THAT GEAR TOOTH FAILURE OF ONE GEAR CAUSED FAILURE OF THE OTHER GEAR DUE TO FAILED PART JAMMING OTHER GEAR. (X) 1 H 7 1 3O 3 O 3A13 E295 2001022100099 20010221 00099 CE 2001 2 21 20000914SH009 1 20000908 G 7810 AN3C15 BOLT BEECH 58 58 1152740 CE TAIL PIPE MISSING B VG4R K NONE O OTHER IN INSP/MAINT 1 SO 35 3MU TH1864 AIRCRAFT IN FOR MAINTENANCE WITH MISSING FLANGE BOLTS, BOLTS NOT OF STAINLESS STEEL INSTALLED CAUSING FLANGE BOLT HOLES TO ELONGATE AND POSSIBLE PIPE SEPARATION. NEW AIRCRAFT RECEIVED WITH STANDARD BOLTS INSTALLED. NO INSTALL INSTRUCTION S IN MM. (X) 1 L 7 2 3O 3A16 2001022100076 20010221 00076 EA 2001 2 21 20000914SH010 2 20000719 G 7314 AE40296C PUMP PARTEN P68 P68C 6780105 EU LYC O360 IO360A1B6 41514 EA ENGINE FAILED B GETA O OTHER Y ENGINE STOPPAGE CR CRUISE 1 NM 09 3832Q 13 274 L2310651A 53 MINTUES AFTER TAKEOFF, AT A FLIGHT ALTITUDE 1,500 MSL, 5 MILES WEST OF EVERETT, WA, LEFT ENGINE QUIT. RESTARTED WITH AUXILIARY FUEL PUMP AND LANDED. REPLACED ENGINE DRIVEN PUMP WITH OVERHAULED PUMP FROM LYC. PUMP HAD BEEN NEWLY OVERHA ULED. REPAIR STATION YV4R88M PMI WAS NOTIFIED. (X) 1 H 7 2 3O 3 O A31EU 1E10 2001022100077 20010221 00077 CE 2001 2 21 20000914SH011 1 20000828 G 2120 0570331 DIFFUSER CESSNA 172 172N 2072434 CE RT RADIO RACK OUT OF POSITION B K NONE O OTHER IN INSP/MAINT 1 NM 09 734KU 17268921 PILOT COMPLAINED THE ELEV CONTROL WAS JAMMED, RESTRICTING UP ELEV TRAVEL. INSP FOUND THE RT SIDE RADIO COOLING DIFFUSER CESSNA PN 057033-1 HAD FALLEN AND WAS PINNED BETWEEN THE YOKE TUNNEL AND THE RADIO STACK. WHEN UP ELEV ATTEMPTED, COPI LOT''S YOKE AILERON SPROCKET PINNED THE DIFFUSER AGAINST THE FWD SIDE OF INSTRUMENT PANEL. SINCE THE DIFFUSER WAS DOUBL E-WALLED ALUMINUM AND THE SPACE BETWEEN THE RADIO STACK AND THE YOKE TUNNEL WAS ONLY A FEW INCHES, PILOT WAS NOT ABLE T O OVERCOME THE RESISTANCE. THE DIFFUSER SHOULD BE HELD IN PLACE BY 4 SPRINGS, CESSNA PN 1470221-2, WHICH ATTACH IT TO A N IDENTICAL DIFFUSER ON THE LT SIDE OF THE RADIO STACK. LT DIFFUSER HAD BEEN PREVIOUSLY REMOVED. ONLY 1 SPRING INTACT. 1 H 7 1 3O NT 3A12 2001022100081 20010221 00081 GL 2001 2 21 20000914SH012 3 20000824 G 6110 D4991 MOUNT HARTZL HCD4N3 HCD4N3A GL HUB CRACKED B F3PR K NONE O OTHER IN INSP/MAINT 1 SW 15 2729 1800 FY1049 DURING OVERHAUL INSPECTION, VISUAL CRACK IN BOTTOM OF MOUNTING HOLE DETECTED. CONFIRMED WITH ZYGLO INSPECTION, EDDY CUR RENT DEFLECTION DETECTED. (X) 5 C STC 2001022100100 20010221 00100 CE 2001 2 21 20000914SH013 1 20000814 G 3231 DOOR BEECH 200 B200 1152922 CE LT MLG OUT OF RIG B EBVR K NONE O OTHER CR CRUISE 1 GL 09 55FJ 5434 BB1297 WHILE CONDUCTING A TRAINING EXERCISE, CREW SIMULATED AN ENGINE OUT WITH THE LANDING GEAR DOWN. DURING COURSE OF THE SCE NARIO, THE GEAR WAS RETRACTED. THE CREW NOTED THE HYDRAULIC PUMP STAYED ON UNUSUALLY LONG. THE GEAR WAS PUT BACK DOWN AND AIRCRAFT SOON AFTER LANDED. UPON INSP, LT INBOARD GEAR DOOR EDGE WAS FOUND BENT UP. SUBSEQUENT INSP FOUND THE OVER CENTER CONDITION OF THE GEAR DOOR RIGGING WAS NOT RIGGED PROPERLY AND THE YAW CONDITION DURING GEAR UP OPS CAUSED THE WH EEL TO CATCH THE DOOR. ACFT GEAR DOOR RIGGING HAD JUST BEEN DONE AT RECENT INSPECTION. (X) 1 L 7 2 4T A24CE 2001022100078 20010221 00078 EA 2001 2 21 20000914SH014 2 20000914 G 7322 MA3A NEEDLE SEAT PIPER PA38 PA38112 7103812 SO LYC O235 O235L2C 41505 EA CARBURETOR OBSTRUCTED G A UNSCHED LANDING C R F.O.D. PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 GL 09 2545N 400 3879A0908 LOSS OF POWER AND SUBSEQUENT OFF-AIRPORT LANDING OCCURRED AFTER DARK. REMOVABLE ''''TANG'''' FROM A HELICOIL WAS FOUND IN THE FINGER SCREEN CAVITY STUCK IN THE HOLE OF THE SEAT (OF THE NEEDLE AND SEAT) STOPPING FUEL FLOW TO THE FLOAT BOWL. (X) 1 L 7 1 3O 3 O A18SO E223 2001022100082 20010221 00082 CE 2001 2 21 20000914SH016 1 20000824 G 2121 09040022 FAN BLADE CESSNA 425 425 2076018 CE CABIN BROKEN B EBVR O OTHER B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 GL 09 5PP 294 4250198 DURING FLIGHT, CREW SMELLED BURNING PLASTIC. UPON INVESTIGATION BY MAINTENANCE, FOUND THAT ALL OF THE FAN BLADES HAD BR OKEN OFF AND WERE LAYING IN THE AUXILIARY HEATER ASSY. ONE BLADE MADE IT INTO THE HEATER COILS AND WAS BEING MELTED. I NSTALLED NEW FAN BLADE ASSY. POST OPS CHECK WAS NORMAL. NO REASON OR CAUSE FOR BLADES COMING OFF WAS FOUND. (X) 1 L 7 2 3T RT A7CE 2001022100101 20010221 00101 CE 2001 2 21 20000914SH017 1 20000907 G 2720 5038017027 CHECK VALVE BEECH 200 200BEECH 1152920 CE RUDDER BOOST INOPERATIVE B K NONE O OTHER IN INSP/MAINT 1 GL 03 551JL 4885 BB788 LEFT RUDDER BOOST INOPERATIVE. FOUND RIGHT RUDDER BOOST CHECK VALVE NOT CHECKING-FLOWING BOTH DIRECTIONS CAUSING LEFT E NGINE BLEED PRESSURE TO BE FELT ON BOTH SIDES OF RUDDER BOOST DIFFERENTIAL PRESSURE SWITCH CAUSING NO PRESSURE DIFFERENC E TO BE FELT CAUSING LT RUDDER BOOST TO FAIL. (X) 1 L 7 2 4T A24CE 2001022100088 20010221 00088 GL 2001 2 21 20000914SH018 3 20000903 G 6111 SEAL CESSNA 182 182S 2072701 CE MCAULY 3D36C B3D36C431 GL PROPELLER LEAKING B K NONE K FLUID LOSS IN INSP/MAINT 1 WP 07 913CT 166 18280391 982654 PROPELLER OIL LEAKING FROM SERVICE PLUG, AND BLADE SEALS. NO INSTRUCTIONS PROVIDED FOR APPROVAL FOR RETURN TO SERVICE. (X) 1 H 7 1 3O NT 3A13 5 C 2001020800972 20010208 00972 EU 2001 2 8 20000918SH001 1 20000825 G 2913 SHAFT SNIAS 350 AS350BA 8680817 EU HYD PUMP ASSY WORN H O OTHER J WARNING INDICATION NR NOT REPORTED 1 WP 13 4064F 3087 HYDRAULIC PUMP SHAFT SPLINE WORN MAKING HYDRAULIC SYSTEM INOPERATIVE. THIS HAPPENED ON A FERRY FLIGHT. INSPECTION REQU IREMENTS ARE EVERY 500 HOURS. THE LAST INSPECTION ON THIS UNIT WAS ABOUT 390.2 HOURS AGO. 1 G 7 1 3U NC H9EU 2001020800973 20010208 00973 EU 2001 2 8 20000918SH005 1 20000206 G 7714 430106202 PICKUP BOLKMS 117 BK117B1 5626012 EU LYC LTS101 LTS101750B1 41560 NE NG SPEED ERRATIC B R7MR O OTHER O OTHER NR NOT REPORTED 1 NM 07 117BK 109 7229 LE45753EFA NGP ERRATIC. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U 3 U H13EU E5NE10 2001020800974 20010208 00974 NE 2001 2 8 20000918SH006 2 20000628 G 7420 430111202 IGNITION LEAD BOLKMS 117 BK117A3 5626015 EU LYC LTS101 LTS101650B1 41560 NE ENGINE SHORTED B R7MR O OTHER O OTHER NR NOT REPORTED 1 NM 07 163BK 543 7063 LE45144EA IGNITION HAD INTERNAL SHORT. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U 3 U H13EU E5NE 2001020800975 20010208 00975 NE 2001 2 8 20000918SH007 2 20000412 G 7420 430111202 IGNITION LEAD BOLKMS 117 BK117A3 5626015 EU LYC LTS101 LTS101650B1 41560 NE ENGINE SHORTED B R7MR O OTHER O OTHER NR NOT REPORTED 1 NM 07 158BK 998 7058 LE45291EA488 IGNITION HAD INTERNAL SHORT. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U 3 U H13EU E5NE 2001020800976 20010208 00976 NE 2001 2 8 20000918SH008 2 20000412 G 7420 430111202 IGNITION LEAD BOLKMS 117 BK117A3 5626015 EU LYC LTS101 LTS101650B1 41560 NE ENGINE SHORTED B R7MR O OTHER O OTHER NR NOT REPORTED 1 NM 07 158BK 998 7058 LE45291EA INTERNAL SHORT. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U 3 U H13EU E5NE 2001020800977 20010208 00977 EU 2001 2 8 20000918SH009 1 20000611 G 6210 L621M1010054 BLADE UROCOP EC135 EC135P1 8680990 EU MAIN ROTOR DEBONDED B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 135SJ 1260 0054 PROTECTION PLATE DEBONDING. REPLACED WITH NEW UNITS, CORRECTED PROBLEM. DAMPERS REMOVED: LK0888, LK0894. (X) 1 G 7 2 3U O H88EU 2001020800978 20010208 00978 EU 2001 2 8 20000918SH010 1 20000611 G 6210 L621M1010054 BLADE UROCOP EC135 EC135P1 8680990 EU MAIN ROTOR DEBONDED B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 135SJ 1260 0054 PROTECTION PLATE DEBONDING. REPLACED WITH NEW UNITS, CORRECTED PROBLEM. DAMPERS REMOVED: LK0670, LK0771. (X) 1 G 7 2 3U O H88EU 2001020800979 20010208 00979 2001 2 8 20000918SH011 4 20000802 G 3421 066030460007 INDICATOR SNIAS 350 AS350B3 8680954 EU COCKPIT INOPERATIVE B R7MR O OTHER O OTHER NR NOT REPORTED 1 NM 07 103LN 653 3128 HSI - EXCESSIVE DEVIATION, LOOSE FACE PLATE. UNIT INOPERATIVE. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001020800980 20010208 00980 2001 2 8 20000918SH012 4 20000805 G 3160 B19030MB01 DISPLAY SNIAS 350 AS350B3 8680954 EU COCKPIT INOPERATIVE B R7MR O OTHER O OTHER NR NOT REPORTED 1 NM 07 104LN 147 3134 UNIT INOPERATIVE. NR 1 LANE FAILED. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001020800981 20010208 00981 EU 2001 2 8 20000918SH013 1 20000717 G 2110 SD505 COMPRESSOR SNIAS 350 AS350B2 8680813 EU AIR CONDITIONING LEAKING B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 102LN 3065 LEAKING OIL FROM FRONT SEAL. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001020800982 20010208 00982 EU 2001 2 8 20000918SH014 1 20000611 G 6210 L621M1010054 BLADE UROCOP EC135 EC135P1 8680990 EU MAIN ROTOR DEBONDED B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 135SJ 1260 0054 PROTECTION PLATE DEBONDING. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. DAMPERS REMOVED: LK0911, LK0878. (X) 1 G 7 2 3U O H88EU 2001030100013 20010301 00013 EU 2001 3 1 20000918SH015 1 20000901 G 6710 1174120101 JACKSHAFT BOLKMS 117 BK117A1 5626010 EU M/R CONTROLS CORRODED B TI1R K NONE O OTHER IN INSP/MAINT 1 NM 07 117LF 7928 7013 DURING INSPECTION, FOUND MASSIVE AMOUNTS OF CORROSION INSIDE CYCLIC JACKSHAFT. SAME LOCATION AS FOUND AND REPORTED PREV IOUSLY ON ANOTHER AIRCRAFT 12-8-99. MANUFACTURER ALLOWS .4 MM ALMOST IMPOSSIBLE TO MEASURE. IT APPEARS LITTLE OR NO PA INT TREATMENT ON INTERIOR OF STEEL TUBE. THE TUBE HAS CASTINGS ON EACH END ANGLED UP AT 45 DEGREES WHICH INCREASES CHAN CE OF GETTING FLUIDS INSIDE. THERE ARE NO PROVISIONS FOR DRAINAGE. SUBMITTER SUGGESTED MFG TREAT INTERIOR AND PROVIDE DRAINAGE. THE LAST TIME THIS OCCURRED IT TOOK 3 MONTHS FOR THIS FLIGHT CRITICAL PART OF AN AIRCRAFT STILL IN PRODUCTION TO BE DELIVERED. (X) 1 G 7 2 3U H13EU 2001020800983 20010208 00983 NE 2001 2 8 20000918SH017 2 20000617 G 7323 430121204 GOVERNOR BOLKMS 117 BK117B1 5626012 EU LYC LTS101 LTS101750B1 41560 NE ENGINE ERRATIC B TI1R O OTHER O OTHER NR NOT REPORTED 1 SW 05 214AE 1106 7206 LE45714 GOVERNOR CAUSED ERRATIC POWER OUTPUT RESULTING IN LOSS OF POWER AND SHUT DOWN. REPLACED GOVERNOR. (X) 1 G 7 2 3U 3 U H13EU E5NE10 2001020800984 20010208 00984 2001 2 8 20000918SH019 4 20000810 G 2311 TFM500G TRANSCEIVER SNIAS 350 AS350B3 8680954 EU COCKPIT MALFUNCTIONED B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 392LG 212 3252 UHF 155 TX FEEDBACK TO CREW. NEED M5 REVISION. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001020800985 20010208 00985 EU 2001 2 8 20000918SH021 1 20000808 G 7712 TRANSMITTER SNIAS 350 AS350B3 8680954 EU TMECA ARRIEL ARRIEL2B NE ENGINE TORQUE DAMAGED B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 106LN 283 3251 22097 TORQUE TRANSMITTER LOST ROLL PIN. REPLACED 2 AND 3 MODULES DUE TO TURBINE RUB. REPLACED WITH NEW UNIT, CORRECTED PROBL EM. (X) 1 G 7 1 3U 3 U H9EU E00054EN 2001020800986 20010208 00986 EU 2001 2 8 20000918SH022 1 20000717 G 6230 350A37112602 SCISSORS SNIAS 350 AS350B3 8680954 EU M/R SWASHPLATE DAMAGED B K NONE O OTHER IN INSP/MAINT 1 NM 03 392LG 92 3252 BUSHINGS LOCKED UP CAUSING DAMAGE TO SCISSOR HOUSING. FOUR NEW PARTS DID SAME THING. INSTALLED PART FROM ANOTHER AC AN D WORKED FINE. NEW PARTS DAMAGED IN 2.5 HOURS. SUBMITTER SUSPECTED BUSHINGS IN NEW PARTS TO BE MISALIGNED. (X) 1 G 7 1 3U H9EU 2001022100109 20010221 00109 SW 2001 2 21 20000918SH023 1 20000901 G 2510 49205503 SEAT GULSTM 112 114 7630314 SW PILOT SEAT BROKEN D K NONE O OTHER IN INSP/MAINT 1 NE 03 5879N 1990 14424 SEAT FRAME TUBE FAILED AT LOCATIONS RESULTING IN SEAT BACK GOING TO A FULL RECLINE POSITION. SEAT FRAME HAD BEEN MODIFI ED PER SB 114-21A, REF AD 85-03-04R2. (X) 1 L 7 1 3O A12SO 2001020800987 20010208 00987 EU 2001 2 8 20000918SH028 1 20000119 G 7714 430106202 PICKUP BOLKMS 117 BK117B2 5626013 EU LYC LTS101 LTS101750B1 41560 NE NG SPEED INOPERATIVE B R7MR O OTHER O OTHER NR NOT REPORTED 1 NM 07 7059N 536 7154 LE45755EFA UNIT INOPERATIVE. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U 3 U NC H13EU E5NE10 2001020800988 20010208 00988 NE 2001 2 8 20000918SH030 2 20000811 G 7321 0164248850 FUEL CONTROL SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D NE ENGINE LEAKING B R7MR K NONE K FLUID LOSS IN INSP/MAINT 1 NM 07 96LG 29 2817 9362 FUEL CONTROL ASSY LEAKING FUEL BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U 3 U H9EU E19EU 2001020800989 20010208 00989 EU 2001 2 8 20000918SH031 1 20000127 G 7714 430106202 PICKUP BOLKMS 117 BK117B1 5626012 EU NG SPEED INOPERATIVE B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 911VU 80 7141 UNIT INOPERATIVE. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U H13EU 2001020800990 20010208 00990 2001 2 8 20000919SH001 4 20000731 G 3160 900A3720002111 DISPLAY DOUG MD900 MD900 3027375 NM COCKPIT INOPERATIVE C R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 901CF 313 90000012 UNIT INOPERATIVE. PARTS OF DIGITAL READOUTS AND FUEL QUANTITY BARS INTERMITTENTLY DISAPPEAR. (X) 1 G 7 2 3U NC H19NM 2001020800991 20010208 00991 NM 2001 2 8 20000919SH002 1 20000525 G 6720 900F2421545105 BEARING DOUG MD900 MD900 3027375 NM NOTAR THRUSTER WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 901CF 246 90000012 DIVITS RESULTING FROM BEARING WEAR BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U NC H19NM 2001020800992 20010208 00992 NE 2001 2 8 20000919SH004 2 20000229 G 7260 230307203 SEAL BOLKMS 117 BK117A4 5626017 EU LYC LTS101 LTS101650B1 41560 NE CSD LEAKING B R7MR K NONE K FLUID LOSS IN INSP/MAINT 1 NM 07 911BY 604 7127 LE45385EA LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U 3 U H13EU E5NE 2001020800993 20010208 00993 NE 2001 2 8 20000919SH006 2 20000229 G 7250 410106701 SEAL BOLKMS 117 BK117A4 5626017 EU LYC LTS101 LTS101650B1 41560 NE 1ST TURBINE WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 911BY 604 7127 LE45385EA SEAL WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U 3 U H13EU E5NE 2001020800994 20010208 00994 NE 2001 2 8 20000919SH007 2 20000229 G 7250 410106802 SEAL BOLKMS 117 BK117A4 5626017 EU LYC LTS101 LTS101650B1 41560 NE WORN WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 911BY 604 7127 LE45385EA WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U 3 U H13EU E5NE 2001020800995 20010208 00995 EA 2001 2 8 20000919SH008 2 20000229 G 7230 410115013 DIFFUSER BOLKMS 117 BK117A4 5626017 EU LYC O540 LTIO540* 41533 EA ENGINE CRACKED B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 911BY 604 7127 DIFFUSER ASSY CRACKED BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U 3 O H13EU E14EA 2001020800996 20010208 00996 NE 2001 2 8 20000919SH009 2 20000229 G 7250 411100720 SHROUD BOLKMS 117 BK117A4 5626017 EU LYC LTS101 LTS101650B1 41560 NE GAS PRODUCER DAMAGED B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 911BY 604 7127 LE45385EA EXCESSIVE GP BLADE TIP RUB. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U 3 U H13EU E5NE 2001020800997 20010208 00997 NE 2001 2 8 20000919SH010 2 20000229 G 7240 413102002 CURL BOLKMS 117 BK117A4 5626017 EU LYC LTS101 LTS101650B1 41560 NE COMBUSTION CHAMB BURNED B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 911BY 604 7127 LE45385EA EXCESSIVE BURN IN SOME AREAS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U 3 U H13EU E5NE 2001020800998 20010208 00998 NE 2001 2 8 20000919SH011 2 20000229 G 7250 430144801 SEAL BOLKMS 117 BK117A4 5626017 EU LYC LTS101 LTS101650B1 41560 NE NR 3 BEARING LEAKING B R7MR K NONE K FLUID LOSS IN INSP/MAINT 1 NM 07 911BY 604 7127 LE45385EA LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U 3 U H13EU E5NE 2001020800999 20010208 00999 NE 2001 2 8 20000919SH012 2 20000229 G 7250 430150601 SEAL BOLKMS 117 BK117A4 5626017 EU LYC LTS101 LTS101650B1 41560 NE NR 2 BEARING LEAKING B R7MR K NONE K FLUID LOSS IN INSP/MAINT 1 NM 07 911BY 604 7127 LE45385EA LEAKING BYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U 3 U H13EU E5NE 2001020801000 20010208 01000 EU 2001 2 8 20000919SH014 1 20000329 G 7714 430106202 PICKUP BOLKMS 117 BK117B1 5626012 EU LYC LTS101 LTS101750B1 41560 NE NGP SPEED ERRATIC B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 911VU 136 7141 LE45583EFA NGP SPEED ERRATIC. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U 3 U H13EU E5NE10 2001020100053 20010201 00053 EU 2001 2 1 20000919SH016 1 20000829 G 2435 WIRE UROCOP EC135 EC135P1 8680990 EU PWA PW206 PW206B 0 NE STARTER GEN SHORTED A K NONE O OTHER IN INSP/MAINT 1 SW 03 911KB 96288 0013 BB0017 BRUSH WIRE CONTACTED HOUSING AFTER A BRUSH INSPECTION. EXTREME CARE SHOULD BE TAKEN DURING RE-ASSEMBLY AFTER INSPECTION . (X) 1 G 7 2 3U 3 U O H88EU E42NE 2001030200006 20010302 00006 CE 2001 3 2 20000919SH019 1 20000721 G 7333 99121942 SWITCH CESSNA 441 441 2076020 CE FUEL SYSTEM INTERMITTENT B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 8970N 4410092 FLOW SWITCH UNIT INOPERATIVE. BENCH CHECKED AND FOUND UNIT TO OPERATE INTERMITTENTLY. REPLACED WITH NEW UNIT, CORRECTE D PROBLEM. (X) 1 L 7 2 3T RT A28CE 2001022100169 20010221 00169 SO 2001 2 21 20000919SH020 2 20000808 G 7314 F289916BR PUMP PIPER PA34 PA34220T 7103420 SO CONT O360 LTSIO360RB SO ENGINE INOPERATIVE B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 4177R 841 3449046 819506R IDLE PRESSURE WAS LOW AND UNABLE TO ADJUST HIGHER. (X) 1 L 7 2 3O 3 O A7SO E9CE 2001022100170 20010221 00170 CE 2001 2 21 20000919SH021 2 20000808 G 7314 G189916BR PUMP PIPER PA34 PA34220T 7103420 SO CONT O360 TSIO360RB 17025 CE ENGINE INOPERATIVE B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 VJ3R 841 3449046 819257R IDLE PRESSURE WAS LOW AND UNABLE TO ADJUST HIGHER. (X) 1 L 7 2 3O 3 O A7SO E9CE 2001022100171 20010221 00171 SO 2001 2 21 20000919SH022 2 20000727 G 7314 F289912BR PUMP PIPER PA34 PA34220T 7103420 SO CONT O360 LTSIO360RB SO ENGINE INOPERATIVE B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 4128X 158 3449112 321749 IDLE PRESSURE WAS LOW AND UNABLE TO ADJUST HIGHER. (X) 1 L 7 2 3O 3 O A7SO E9CE 2001022100172 20010221 00172 EA 2001 2 21 20000919SH023 2 20000804 G 8550 LYL10 GASKET AVIAT A1 A1B GL LYC O360 O360* 41514 EA FILTER ADAPTER MISSING B V2AR K NONE K FLUID LOSS IN INSP/MAINT 1 AL 03 58TD 192 2017 FILTER ADAPTER WAS MISSING PN MS28773-08 GASKET. (X) 1 H 7 1 3O 3 O NC A22NM E286 2001022100173 20010221 00173 EA 2001 2 21 20000919SH024 2 20000804 G 8550 LYC10 GASKET AVIAT A1 A1B GL LYC O360 O360* 41514 EA FILTER ADAPTER MISSING B V2AR K NONE K FLUID LOSS IN INSP/MAINT 1 AL 03 475MA 49 2074 FILTER ADAPTER WAS MISSING PN MS28773-08 GASKET. AN6289-8D. NUT WAS NOT TORQUED. OIL FILTER ADAPTER WAS LEAKING. (X ) 1 H 7 1 3O 3 O NC A22NM E286 2001022100174 20010221 00174 SO 2001 2 21 20000919SH025 1 20000919 G 2731 6841403 CONTROLLER PIPER PA32 PA32R300 7103213 SO ELEV TRIM CNTRL WORN B PP4R K NONE O OTHER IN INSP/MAINT 1 SO 05 10WW 2441 32R7680319 DATE OF OCCURRENCE: 12-11-90PILOT REPORTED THAT ATTEMPT TO MANUALLY ADJUST STABILATOR TRIM FAILED. EXAMINATION REVEALE D THAT PLASTIC TRIM CONTROL WHEEL WAS WORN IN AREA OF DETENT RECEPTACLE THAT ENGAGES BALL SWAGED ON CONTROL CABLE. CONT ROL WHEEL WAS REPLACED WITH NEW AND TRIM CONTROL WAS RIGGED PER PIPER PA-32 SERIES SERVICE MANUAL. SUBMITTER SUSPECTED THAT DUE TO RELATIVELY LOW TIME OF PART/AIRCRAFT, DAMAGE POSSIBLY OCCURRED DUE TO ATTEMPT TO OVERRIDE FAILED OR LOCKED U P ELECTRIC TRIM SYSTEM BY APPLYING EXCESSIVE FORCE TO CONTROL. (X) 1 L 7 1 3O A3SO 2001022100175 20010221 00175 NE 2001 2 21 20000919SH026 2 20000602 G 7260 30727841 CARBON SEAL HONEYWELL AMD FALC50 FALCON50MYST 2730106 EU GARRTT TFE731 TFE73131C 01518 NE ACCESSORY GRBX LEAKING B BICR K NONE K FLUID LOSS IN INSP/MAINT 1 NM 11 55AS 214 P76785 ENGINE NEW ON 6-5-90 WITH SB TFE731-72-3124 AND TFE731-72-3289 INCORPORATED. ENGINE HAS HAD SEAL REPLACED ON THE FOLLOW ING DATES AND ENGINE TIMES: TSN 2603.9, 4/5/96;TSN 2720.1, 7-8-96; TSN 2978.6, 1-24-97; TSN 3725.9, 6/26/98; TSN 3962.3 , 12/1/98; TSN 3983.0, 12/21/98; TSN 3992.2, 1/4/99; TSN 4000.5, 1/9/99. (X) 2 L 7 3 4F 4 F A46EU E6WE 2001022100176 20010221 00176 NE 2001 2 21 20000919SH027 2 20000602 G 7260 30727841 CARBON SEAL HONEYWELL AMD FALC50 FALCON50MYST 2730106 EU GARRTT TFE731 TFE73131C 01518 NE ACCESSORY GRBX LEAKING B BICR K NONE K FLUID LOSS IN INSP/MAINT 1 NM 11 55AS 214 P76787 ENGINE NEW ON 7/16/90 WITH SB TFE731-72-3124 AND TFE731-72-3289 INCORPORATED. ENGINE HAS HAD SEAL REPLACED ON THE FOLLO WING DATES AND ENGINE TIMES: TSN 1718.6, 10/24/94; TSN 2815.8, 10/24/96; TSN 3646.4, 6/25/98; TSN 4004.7, 11/12/98; TSN 4126.4, 6/25/99; TSN 4279.5, 10/27/99; TSN 4373.0, 1/3/00. (X) 2 L 7 3 4F 4 F A46EU E6WE 2001022100177 20010221 00177 NE 2001 2 21 20000919SH028 2 20000620 G 7260 30727841 CARBON SEAL HONEYWELL AMD FALC50 FALCON50MYST 2730106 EU GARRTT TFE731 TFE73131C 01518 NE ACCESSORY GRBX LEAKING B BICR K NONE K FLUID LOSS IN INSP/MAINT 1 NM 11 250AS 182 P76628 ENGINE NEW ON 8/83 WITH SB TFE731-72-3124 AND TFE731-72-3289 INCORPORATED. ENGINE HAS HAD SEAL REPLACED ON THE FOLLOWIN G DATES AND ENGINE TIMES: TSN 2219.8, 12/11/92; TSN 3666.5, 5/31/96; TSN 4819.8, 10-30-98, TSN 5574.4, 4/10/00. (X) 2 L 7 3 4F 4 F A46EU E6WE 2001022100006 20010221 00006 CE 2001 2 21 20000920SH001 1 20000714 G 2810 VENT LINE BEECH 77 77 1153007 CE RT WING BENT H K NONE O OTHER CR CRUISE 1 NM 11 3809Y 3997 WA212 INITIAL FLIGHT INFORMATION REVEALED RIGHT FUEL TANK WOULD RUN DRY LONG BEFORE LEFT. AFTER MANY LEAK TESTS, THE FUEL VEN TS WERE SET TO FACTORY SPECS. NEXT FLIGHT INDICATED THE REVERSE OF TANKS. THE FOLLOWING FLIGHTS AND ADJUSTMENTS OF FUE L VENTS LEFT AND RIGHT HAD PRODUCED FAIRLY EVEN FUEL TANK FLOW. (X) 1 L 7 1 3O A30CE 2001022100007 20010221 00007 CE 2001 2 21 20000920SH002 1 20000731 G 2434 649304A1 ALTERNATOR BEECH 58 58 1152740 CE ENGINE MALFUNCTIONED B AWKR K NONE O OTHER IN INSP/MAINT 1 WP 25 458JG 60 TH1908 ALTERNATOR DROPS OFF LINE. (X) 1 L 7 2 3O 3A16 2001022100008 20010221 00008 CE 2001 2 21 20000920SH003 1 20000609 G 2434 649304 ALTERNATOR BEECH 58 58 1152740 CE ENGINE INOPERATIVE B ZWKR K NONE L NO TEST IN INSP/MAINT 1 WP 25 3196W 173 TH1913 ALTERNATOR INOPERATIVE. (X) 1 L 7 2 3O 3A16 2001022100009 20010221 00009 CE 2001 2 21 20000920SH004 1 20000831 G 2434 649305A1 ALTERNATOR BEECH 58 58 1152740 CE ENGINE FAILED B AWKR K NONE L NO TEST IN INSP/MAINT 1 WP 25 3196W 313 TH1913 ALTERNATOR HAD NO OUTPUT. (X) 1 L 7 2 3O 3A16 2001022100010 20010221 00010 CE 2001 2 21 20000920SH005 1 20000920 G 7810 BOLT BEECH 100 B100 1152919 CE EXHAUST CORRODED H K NONE O OTHER IN INSP/MAINT 1 SO 15 120MG BE70 DURING ROUTINE INSPECTION, FOUND THE RETAINING HARDWARE FOR THE EXHAUST DUCT WITHIN BOTH ENGINE COWLINGS WAS CORRODED BE YOND SERVICEABLE LIMITS. BOLTS AN4-4A AND NUTS MS21042L4. THIS INSPECTION TOOK PLACE AT 310.5 HOURS FROM OVERHAUL OF B OTH ENGINES. (X) 1 L 7 2 4T A14CE 2001022100011 20010221 00011 CE 2001 2 21 20000920SH006 1 20000831 G 8011 DRIVE SHAFT BEECH 100 B100 1152919 CE GARRTT TPE331 TPE3316 01514 WP LT ENG STARTER WORN H K NONE O OTHER IN INSP/MAINT 1 SO 15 120MG 311 BE70 P27142 DURING ROUTINE INSPECTION, STARTER DRIVESHAFT WAS FOUND WORN BEYOND SERVICEABLE LIMITS AT 310.5 HOURS AFTER ENGINE OVER HAUL. (X) 1 L 7 2 4T 4 T A14CE E4WE 2001022100016 20010221 00016 CE 2001 2 21 20000920SH007 1 20000908 G 5751 HINGE BEECH 58 58P 1152744 CE AILERON MISINSTALLED B K NONE O OTHER IN INSP/MAINT 1 SW 09 249CR TJ249 OUTER HINGE ATTACHMENT SCREWS ON THE LOWER SIDE WERE HOT. INSTALLED THROUGH THE HINGE ASSEMBLY, BUT THROUGH THE SKIN ON LY. SCREWS WERE HELD IN BY THE SKIN AND BACKSIDE OF COCKED HINGE. PROBLEM WAS DISCOVERED FROM RESPONSE TO BEECH MAINTE NANCE ALERT MA00-03, DATED 8-31-00. (X) 1 L 7 2 3O A23CE 2001020801001 20010208 01001 SW 2001 2 8 20000920SH008 1 20000829 G 5320 206031314037 CHANNEL BELL BELL 206 206L4 1182110 SW FUSELAGE CRACKED H K NONE O OTHER IN INSP/MAINT 1 SO 19 406MP 4700 52086 FOUND .8750 INCH CRACK ON LEFT UPPER TAILBOOM ATTACHMENT CHANNEL DURING A ROUTINE 100 HOUR INSPECTION. THE CRACK WAS ON LY VISIBLE WITH REMOVAL OF THE TAILBOOM ACCESS PANEL AND THE USE OF AN INSPECTION MIRROR. THE CAUSE OF THE CRACK IS NOT YET DETERMINED. (X) 1 G 7 1 3U NC H2SW 2001022100182 20010221 00182 CE 2001 2 21 20000920SH009 1 20000912 G 2434 DOFF10300B ALTERNATOR CESSNA 182 TR182 2072735 CE ENGINE FAULTY H K NONE O OTHER IN INSP/MAINT 1 WP 19 4928S R18201467 ALTERNATOR 60-AMP CIRCUIT BREAKER TRIPPED. JUMP STARTED AIRCRAFT. ENGINE GROUND RUN. ALTERNATOR CHARGED BATTERY WITH RADIO MASTER SWITCH ON. AS LANDING TAXI LIGHTS WERE TURNED ON, 60-AMP CIRCUIT BREAKER TRIPPED. INSTALLED TROUBLESHOOTI NG EQUIPMENT, INDICATIONS OF INTERNAL ALTERNATOR FAULT. REMOVED AND REPLACED ALTERNATOR. (X) 1 H 7 1 3O 3A13 2001022100183 20010221 00183 SO 2001 2 21 20000920SH010 2 20000512 G 8530 INTAKE VALVE LYC PIPER PA32 PA32R300 7103213 SO LYC 0540 IO540K1G5D 41532 SO NR 2 CYLINDER FRACTURED D A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CR CRUISE 1 AL 01 5633V 649 32R7780349 L1648648A DURING FLIGHT, ENGINE BEGAN TO RUN ROUGH. PILOT POWERED BACK AND MADE PRECAUTIONARY LANDING. INSPECTION REVEALED FAILU RE OF THE VALVE STEM ON NR 2 CYLINDER INTAKE VALVE. THE FRACTURE IS LOCATED APPROXIMATELY .6250 INCH FROM THE TOP OF TH E VALVE STEM NEAR THE VALVE KEEPERS. SOME WEAR WAS DETECTED AT THE VALVE GUIDE. (X) 1 L 7 1 3O 3 O A3SO 1E4 2001022100184 20010221 00184 SO 2001 2 21 20000920SH011 1 20000603 G 3700 GASKET AMRGEN AA1 AA1A 0630710 SO LYC O235 O235C2C 41505 EA VACUUM/PUMP LEAKING H K NONE K FLUID LOSS IN INSP/MAINT 1 EA 11 7C AA1A0345 L1080415 REPLACED VAC/PUMP OIL SEAL STD-208 AND GASKET SL-61183 (2 TIMES SL-61183). OIL WOULD LEAK OUT IN GREAT AMOUNT. SEAL/GA SKET DOES NOT HOLD OIL PRESSURE. THE ALUM/BODY HAD A SHAFT AND GEAR DRIVING THE VAC/PUMP. THERE IS A BORED/HOLE TO FEE D OIL UNDER PRESSURE TO THE SHAFT. (X) 1 L 7 1 3O 3 O A11EA E223 2001022100185 20010221 00185 GL 2001 2 21 20000920SH012 1 20000905 G 2821 2228215100 GASCOLATOR DIAMON DA20 DA20C1 2990001 GL FUEL TANK LEAKING B HBKR K NONE K FLUID LOSS IN INSP/MAINT 1 SW 05 899CT 110 C0099 GASCOLATOR BOWL CANNOT BE SECURED TO PREVENT LEAKING AT BOWL GASKET AREA. ANY SIDE LOAD CAUSES EXCESSIVE LEAKING. LEAK S AT JOINT OF HOUSING AND BOWL. (X) 1 L 7 1 3O NT TA4CH 2001022100190 20010221 00190 CE 2001 2 21 20000920SH015 1 20000830 G 3710 HP006 HOSE CESSNA 182 182R 2072731 CE AIR FILTER DETERIORATED H K NONE O OTHER IN INSP/MAINT 1 SO 03 9386X 1608 18268508 FOUND HOSE MADE BY IMPERIAL EASTMAN HYTYON YP006 250 PSI W.P. FOUND OUTSIDE OF HOSE CRACKED AND COMING APART. FOUND IN SIDE OF HOSE RED IN COLOR VERY BRITTLE, CRACKING. HOSE USED FOR INSTRUMENT VACUUM SERVICE. HOSE ROUTED FROM INSTRUMENT AIR FILTER TO ARTIFICIAL HORIZON. NOTE: OTHER CESSNA AIRCRAFT HAVE HAD THIS TYPE HOSE PROBLEM WITH SAME TOTAL TIMES. TACK 1,667.5 HOURS. TTAC 1,607.5 HOURS. (X) 1 L 7 1 3O NT 3A13 2001022100191 20010221 00191 CE 2001 2 21 20000920SH016 1 20000901 G 2571 07120591 SUPPORT BRACKET CESSNA 182 182R 2072731 CE BATTERY BOX CRACKED H K NONE O OTHER IN INSP/MAINT 1 SO 03 9386X 1608 18268508 ON INSPECTION OF AIRCRAFT, FOUND LEFT AND RIGHT BATTERY BOX SUPPORTS CRACKED IN BEND RADIUS, P/N 0712059-1. 24V BATTER Y LOCATED IN TAIL SECTION OF AIRCRAFT. NOTE: THIS PROBLEM HAS BEEN FOUND IN OTHER 182R''S. (X) 1 L 7 1 3O NT 3A13 2001022600001 20010226 00001 EA 2001 2 26 20000920SH017 2 20000905 G 8530 05K22756 TUBE PIPER PA32 PA32301T 7103209 SO LYC O540 TIO540* 41532 EA INTAKE SYSTEM DISCONNECTED D K NONE O OTHER IN INSP/MAINT 1 WP 15 9288X 215 3257027 L9908861A C/W PIPER SB 1030A AIR INLET TUBE REPLACEMENT AND DRAIN IMPROVEMENT AND LYC SB 538A AIR INLET TUBE. REPLACEMENT ON 10-2 6-99 PER PIPER AND LYC SB''''S AND NOW, 215 HOUR LATER, THE INLET DRAIN SNIFFLE VALVE FALLS OUT. (X) 1 L 7 1 3O 3 O A3SO E14EA 2001011101151 20010111 01151 NM 2001 1 11 20000920SH018 1 20000920 G 5300 693535214 STRINGER CLIP BOEING 737 7372B7 1384560 NM FUSELAGE CRACKED B D8LR K NONE O OTHER IN INSP/MAINT 1 SW 99 PARTS PURCHASED NEW FROM BOEING STOCK, FOUND CRACKED IN OUTSIDE RADII OF CLIP IN EXTERNAL LAMINATE. (X) 2 L 7 2 4F A16WE 2001020801002 20010208 01002 SW 2001 2 8 20000920SH026 1 20000831 G 6520 47645205 SHAFT BELL 47 47G2 1181008 SW T/R GEARGOX SHEARED G K NONE O OTHER IN INSP/MAINT 1 GL 15 67083 2280 PILOT HAD JUST ARRIVED AT A FIELD TO SPRAY AND WAS DOING A 180 DEGREE TURN WHEN HE LOST TAIL ROTOR FUNCTION. SHAFT FAIL ED IN TAIL ROTOR GEARBOX. (X) 1 G 7 1 3O H1 2001011101152 20010111 01152 GL 2001 1 11 20000921SH001 3 20000911 G 6114 HUB HARTZL PIPER PA44 PA44180 7104402 SO HARTZL HCC2Y HCC2YR2 GL PROPELLER ASSY CRACKED B K NONE K FLUID LOSS IN INSP/MAINT 1 SO 11 325CD 4441 10 447995243 AU1734 DURING PREFLIGHT, PILOT NOTICED GREASE ON BLADES. MECHANIC REMOVED SPINNER AND FOUND HUB CRACKED ON RADIUS OF HUB. THE CRACK STARTS WHERE THE CYLINDER ATTACHES TO HUB, GOES THROUGH ZERK FITTING HOLE TO MATING SURFACE OF HUB. THE CRACK IS THROUGH THE ENTIRE HUB. (X) 1 L 7 2 3O A19S0 5 C P920 2001030100014 20010301 00014 2001 3 1 20000925SH004 4 20000911 G 2330 22840302 POWER SUPPLY VIDEO UNIT DAMAGED H K NONE O OTHER IN INSP/MAINT 1 WP 23 POWER SUPPLY RETURNED FOR REPAIR AFTER REPORTED THAT UNIT WAS SMOKING DURING FLIGHT SEGMENT. DURING TEAR-DOWN, FOUND '' SCORCHED & MELTED'' CAPACITORS AND COMPONENTS WITHIN POWER SUPPLY. INVESTIGATION OF ROOT CAUSE STILL ONGOING. A NIC MF G CAPACITOR IS SUSPECTED. FINAL FIX STILL BEING WORKED. AS A PRECAUTION, NIC CAPACITORS HAVE BEEN PURGED FROM REPAIR S TATION STOCK AND COORDINATED PRODUCTION. AIRLINE AND BOEING COORDINATION ONGOING. (X) 2001030100015 20010301 00015 2001 3 1 20000925SH005 4 20000911 G 2330 22840303 POWER SUPPLY VIDEO UNIT DAMAGED H K NONE O OTHER IN INSP/MAINT 1 WP 23 POWER SUPPLY RETURNED FOR REPAIR AFTER REPORTED THAT UNIT WAS SMOKING DURING FLIGHT SEGMENT. DURING TEAR-DOWN, FOUND '' SCORCHED & MELTED'' CAPACITORS AND COMPONENTS WITHIN POWER SUPPLY. INVESTIGATION OF ROOT CAUSE STILL ONGOING. A NIC MF G CAPACITOR IS SUSPECTED. FINAL FIX STILL BEING WORKED. AS A PRECAUTION, NIC CAPACITORS HAVE BEEN PURGED FROM REPAIR S TATION STOCK AND COORDINATED PRODUCTION. AIRLINE AND BOEING COORDINATION ONGOING. (X) 2001030100016 20010301 00016 2001 3 1 20000925SH006 4 20000911 G 2330 232840304 POWER SUPPLY VIDEO UNIT DAMAGED H K NONE O OTHER IN INSP/MAINT 1 WP 23 POWER SUPPLY RETURNED FOR REPAIR AFTER REPORTED THAT UNIT WAS SMOKING DURING FLIGHT SEGMENT. DURING TEAR-DOWN, FOUND '' SCORCHED & MELTED'' CAPACITORS AND COMPONENTS WITHIN POWER SUPPLY. LABORATORY INVESTIGATION OF ROOT CAUSE STILL ONGOING . A NIC MFG CAPACITOR IS SUSPECTED. FINAL FIX STILL BEING WORKED. AS A PRECAUTION, NIC CAPACITORS HAVE BEEN PURGED FR OM REPAIR STATION STOCK AND COORDINATED PRODUCTION. AIRLINE AND BOEING COORDINATION ONGOING. (X) 2001030100017 20010301 00017 NM 2001 3 1 20000925SH007 1 20000908 G 6720 500N53673 PITCH SLIDER DOUG 600N 600N 3027377 NM NOTAR FAN CORRODED C K NONE O OTHER IN INSP/MAINT 1 SW 17 603BP 601 RN029 DURING REMOVAL OF NO TAIL ROTOR (NOTAR) FAN BEARING, DISCOVERED THE FAN PITCH SLIDER, P/N 500N5367-3, AND FAN SUPPORT SH AFT, P/N 500N5357-11, HAD PITTING CORROSION. A NEW SUPPORT SHAFT AND SLIDER WERE INSTALLED. WITH NEW PARTS INSTALLED, A CONDITION OF EXCESSIVE BINDING OF THE FAN PITCH SLIDER EXISTED. IN CONJUNCTION WITH MD HELICOPTERS TECH REPS, DETERMI NED THE TORQUE APPLIED TO THE PITCH SUPPORT SHAFT LOCKNUT P/N NAS1493-6F (60 TO 70 FEET/POUNDS AS SPECIFICIED IN THE HAN DBOOK OF MAINTENANCE INSTRUCTIONS) WAS EXCESSIVE AND WAS THE MAJOR CONTRIBUTING FACTOR OF THE BINDING OF THE PITCH SLIDE R. (X) 1 G 7 1 3U NC H3WE 2001022200179 20010222 00179 CE 2001 2 22 20000925SH008 1 20000925 G 3710 LINE CESSNA 182 182R 2072731 CE INSTRUMENT PNL DETERIORATED H K NONE O OTHER IN INSP/MAINT 1 CE 07 6545E 18268373 WHILE CERTIFYING THE STATIC SYSTEM, DISCOVERED THE VACUUM LINES WERE DETERIORATING. AFTER FURTHER INVESTIGATION, FOUND THE VACUUM LINES WERE THE LINES THAT HAD AD ISSUED AGAINST THEM. REMOVED ALL VACUUM LINES AND REPLACED WITH NEW HOSES. POSSIBLE CAUSE FOR THE PROBLEM IS FAULTY ENGINEERING AND AGE OF THE HOSE. SUBMITTER RECOMMENDED ACTION WOULD BE TO REP LACE ALL EASTMAN HOSES FOUND ON CESSNAS. SEB96-10. (X) 1 L 7 1 3O NT 3A13 2001022200001 20010222 00001 CE 2001 2 22 20000925SH009 1 20000811 G 7602 5038901021 CONTROL CABLE BEECH 95 95B55 1152729 CE RT ENG BROKEN B AIHR A UNSCHED LANDING O OTHER CL CLIMB 1 GL 11 18273 TC2065 PILOT REPORTED THAT ON CLIMB, RIGHT ENGINE WOULD NOT LEAN OUT. PILOT THEN TURNED BACK TO AIRPORT AND AN UNEVENTFUL LAND ING WAS MADE. PILOT THEN DISCOVERED RIGHT ENGINE WOULD NOT SHUT DOWN WHEN MIXTURE CONTROL WAS PULLED BACK TO IDLE CUT-O FF. UPON INSPECTION BY MAINTENANCE, RIGHT ENGINE MIXTURE CABLE WAS FOUND WITH END PULLED OUT OF SWAGE AT FUEL CONTROL E ND. (X) 1 L 7 2 3O RT 3A16 2001022200167 20010222 00167 2001 2 22 20000925SH012 4 20000907 G 3452 RT359A TRANSPONDER ARC CESSNA 182 182R 2072731 CE COCKPIT INOPERATIVE H K NONE L NO TEST IN INSP/MAINT 1 GL 05 9910H 82 28853 18268106 TRANSPONDER REPORTED INOPERATIVE. BENCH TEST REVEALED CAVITY TRANSMITTING AT 2,012 MEGAHERTZ AND IT COULD NOT BE ADJUST ED INTO TOLERANCE. FOUND TUBE INSTALLED WAS PC2080A, DATE CODE 99-13. INSTALLED BY FAA CRS AJVR135C, PRESENT MANUFACTU RER (SIGMA-TEK) DOES NOT AUTHORIZE THE USE OF THE PC2080A IN THE TRANSPONDER. (X) 1 L 7 1 3O NT 3A13 2001022200168 20010222 00168 EA 2001 2 22 20000925SH014 2 20000911 G 8550 77808 RELIEF VALVE PIPER PA46 PA46350P SO LYC O540 TIO540AE2A 41532 EA ENGINE CRANKCASE DIRTY B AW4R A UNSCHED LANDING O OTHER CL CLIMB 1 WP 11 193PM 4622143 FOLLOWING TAKEOFF, PILOT NOTED DECREASE IN OIL PRESSURE. PILOT ELECTED TO RETURN TO AIRPORT. UPON LANDING AND TAXI BAC K TO RAMP, PILOT KEPT RPM AT APPROX 1,500 RPM TO KEEP OIL PRESS ABOVE READING (LOW END). DUE TO TAXIING AT HIGH RPM, BR AKES WERE OVERHEATED WITH THE RT BRAKE CATCHING FIRE BY THE TIME ACFT RETURNED TO RAMP. FIRE EXTINGUISHED. DAMAGE CONF INED TO BRAKE AND TIRE. INVEST REVEALED SEVERAL SMALL PIECES OF WHAT APPEARED TO BE DIRT OR SAND ON RELIEF VALVE SEAT A LLOWING OIL TO BYPASS THRUST THE RELIEF VALVE RESULTING IN LOWERED PRESSURE. (X) 1 L 7 1 3O 3 O RT A25SO E14EA 2001020500189 20010205 00189 CE 2001 2 5 20000925SH018 1 20000831 G 5311 994400201 FRAME BEECH 99 99A 1154003 CE FUSELAGE CRACKED A HSYA K NONE O OTHER IN INSP/MAINT 1 NM 05 199CA 24624 U96 CPR - FUSELAGE FRAME CRACKED .75 INCH IN LENGTH AT STA 409 JUST RIGHT OF CENTER BELLY OF AIRCRAFT. SUBMITTER SUSPECTED CAUSED BY FOD. PERFORMED DOUBLER REPAIR; STOP DRILLED THE CRACK, FABRICATED DOUBLER WITH .032 INCH 2024T3 ALUMINUM AND INSTALLED WITH MS20470AD4 RIVETS. COMPLETED FAA FORM 337. (X) 1 L 7 2 3T A14CE 2001022200169 20010222 00169 NE 2001 2 22 20000925SH021 2 20000925 G 7322 P13773 SCREW BENDIX WTHRLY 620 620B 9630605 CE PWA R985 R985AN1 52008 NE CARBURETOR LOOSE D K NONE O OTHER IN INSP/MAINT 1 CE 07 90303 1641 CARBURETOR FLOAT FULCRUM SCREW WAS FOUND LOOSE ON ANNUAL INSPECTION. BRASS THREADS WERE FOUND WORN. REPLACED FULCRUM S CREW, PROPERLY INSTALLED NEW SCREW AND SAFTIED. BELIEVE SCREW WAS NOT PROPERLY INSTALLED BY MANUFACTURER. SUBMITTER RE COMMENDED AN AD OR SA1B BE ISSUED TO INSPECT FULCRUM SCREW FOR PROPER INSTALLATION. (X) 1 L 7 1 3R 3 R NC A26WE 5E1 2001022200173 20010222 00173 EA 2001 2 22 20000925SH024 2 20000828 G 8520 STUD CESSNA 172 172M 2072418 CE LYC O360 O360A4M 41514 EA NR 1 CYLINDER BROKEN D K NONE O OTHER IN INSP/MAINT 1 EA 01 12970 416 17262415 RL2202336A LYC WORK ORDER NR LB 1027207 FACTORY ZERO TIME ASSEMBLED 11-10-92 INSTALLED 12-28-92 IAW PEN YAN STC. 18 HOURS SINCE L AST ANNUAL. FOUND NR 1 CYLINDER TOP RIGHT .50 INCH THROUGH STUD BROKEN FLUSH WITH CASE. ALL OTHER STUDS ON NR 1 OK. R ESEARCH SEEMS TO INDICATE A FATIGUE FAILURE. (X) 1 H 7 1 3O 3 O NT 3A12 E286 2000100200271 20001002 00271 CE 2000 10 2 20000925SH029 2 20000813 G 7322 RSA5AD2 SERVO PIPER PA34 PA34220T 7103420 SO CONT O360 TSIO360RB 17025 CE FAILED B VJ3R O OTHER R PARTIAL RPM/PWR LOSS LD LANDING 1 WP 07 4128X 3449112 819255R ON LANDING AT GOODYEAR AIRPORT IN AZ, THE LEFT ENGINE LAGGED POWER TO LANDING. THE RPM DROPPED FROM 2,400 TO 1,800. TH ROTTLE POWER TO 22 INCHES. (X) 1 L 7 2 3O 3 O A7SO E9CE 2000100200001 20001002 00001 SO 2000 10 2 20000925SH030 1 20000815 G 2710 62701127 CONTROL CABLE PIPER PA34 PA34220T 7103420 SO FRAYED B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 4123C 1694 3449042 RIGHT HAND AILERON BALANCE CABLE FRAYED AT WING ROOT PULLEY. (X) 1 L 7 2 3O A7SO 2000100200003 20001002 00003 SO 2000 10 2 20000925SH031 1 20000815 G 2710 62701127 CONTROL CABLE PIPER PA34 PA34220T 7103420 SO FRAYED B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 4123C 1694 3449042 LEFT HAND AILERON BALANCE CABLE FRAYED AT WING ROOT PULLEY. (X) 1 L 7 2 3O A7SO 2000101300107 20001013 00107 SO 2000 10 13 20000925SH032 2 20000817 G 7322 RSA5AD SERVO PIPER PA34 PA34220T 7103420 SO CONT O360 LTSIO360RB SO FAILED B VJ3R O OTHER O OTHER IN INSP/MAINT 1 WP 07 4123C 323 3449042 321676R THROTTLE HARD TO MOVE IN FLIGHT, SERVO REMOVED AND A NEW ONE INSTALLED. OVER FOUR POUNDS TO MOVE CONTROL. (X) 1 L 7 2 3O 3 O A7SO E9CE 2000100200007 20001002 00007 SO 2000 10 2 20000925SH033 2 20000817 G 8530 649262 TUBE PIPER PA34 PA34220T 7103420 SO CONT O360 LTSIO360RB SO INTAKE NR2 CRACKED B XC4R K NONE O OTHER IN INSP/MAINT 1 WP 07 4177R 800 3449046 819506R NR 2 INTAKE TUBE ON RIGHT ENGINE CRACKED AT THE FLANGE WHERE IT MOUNTS TO THE CYLINDER . INTAKE TUBE WAS REPLACED AND T CM HAS BEEN INFORMED. (X) 1 L 7 2 3O 3 O A7SO E9CE 2000100200008 20001002 00008 SO 2000 10 2 20000925SH034 2 20000817 G 8530 649262 TUBE PIPER PA34 PA34220T 7103420 SO CONT O360 LTSIO360RB SO INTAKE CRACKED B XC4R K NONE O OTHER IN INSP/MAINT 1 WP 07 4177R 800 3449046 819506R NR 6 INTAKE TUBE ON RIGHT ENGINE CRACKED AT THE FLANGE WHERE IT MOUNTS TO THE CYLINDER. INTAKE TUBE WAS REPLACED AND TC M HAS BEEN INFORMED. (X) 1 L 7 2 3O 3 O A7SO E9CE 2000100200009 20001002 00009 CE 2000 10 2 20000925SH035 2 20000816 G 7322 RSA5AD SERVO PIPER PA34 PA34220T 7103420 SO CONT O360 TSIO360RB 17025 CE FAILED B XC4R K NONE O OTHER IN INSP/MAINT 1 WP 07 4177R 3449046 819256R THROTTLE END PLAY ON SHAFT. NEW FROM TCM. (X) 1 L 7 2 3O 3 O A7SO E9CE 2000100200050 20001002 00050 SO 2000 10 2 20000925SH036 2 20000816 G 7322 RSA5AD SERVO PIPER PA34 PA34220T 7103420 SO CONT O360 LTSIO360RB SO FAILED B XC4R K NONE O OTHER IN INSP/MAINT 1 WP 07 4177R 90 3449046 819506R STIFF THROTTLE ARM, OVER 4 POUNDS TO MOVE CONTROL. (X) 1 L 7 2 3O 3 O A7SO E9CE 2000100200051 20001002 00051 CE 2000 10 2 20000925SH037 2 20000817 G 7322 RSA5AD SERVO PIPER PA34 PA34220T 7103420 SO CONT O360 TSIO360RB 17025 CE FAILED B XC4R K NONE O OTHER IN INSP/MAINT 1 WP 07 4177R 442 3449046 819257R THROTTLE HARD TO MOVE IN FLIGHT, SERVO REMOVED AND A NEW ONE INSTALLED. OVER FOUR POUNDS TO MOVE CONTROL. (X) 1 L 7 2 3O 3 O A7SO E9CE 2000100200052 20001002 00052 SO 2000 10 2 20000925SH038 1 20000815 G 2710 62701123 CONTROL CABLE PIPER PA28 PA28181 7102807 SO AILERON FRAYED B K NONE O OTHER IN INSP/MAINT 1 WP 07 4142Q 1341 2843207 AILERON BALANCE CABLE FRAYED. LOCATED UNDER THE REAR SEATS. (X) 1 L 7 1 3O 2A13 2000100200267 20001002 00267 SO 2000 10 2 20000925SH039 2 20000817 G 8530 649264 TUBE PIPER PA34 PA34220T 7103420 SO CONT O360 LTSIO360RB SO INTAKE CRACKED B VJ3R A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CR CRUISE 1 WP 07 4142N 1195 3449128 322021R THE PILOT REPORTED THE RIGHT ENGINE RUNNING ROUGH AND VIBRATION. THE ENGINE WAS SHUT DOWN AND A SAFE LANDING WAS MADE. AIRCRAFT WAS TAKEN TO MAINTENANCE AND INSPECTION WAS DONE ON THE ENGINE, NR 4 INTAKE TUBE WAS FOUND CRACKED AT THE FLAN GE OF TUBE WHERE IT MOUNTS TO THE CYLINDER. NEW INTAKE TUBE INSTALLED. (X) 1 L 7 2 3O 3 O A7SO E9CE 2000100200268 20001002 00268 SO 2000 10 2 20000925SH040 2 20000817 G 7322 RSA5AD225765405 SERVO PIPER PA34 PA34220T 7103420 SO CONT O360 LTSIO360RB SO FAILED B VJ3R O OTHER O OTHER NR NOT REPORTED 1 WP 07 9299E 11 3449043 819507R WHEN BOOST PUMP IS TURNED ON, FUEL FLOW DROPS, ENGINE RUNS ON THE LEAN SIDE. REPLACED SERVO. (X) 1 L 7 2 3O 3 O A7SO E9CE 2000100200231 20001002 00231 SO 2000 10 2 20000927SH001 1 20000926 G 5312 9512103 BULKHEAD PIPER PIPER PA34 PA34200T 7103406 SO BS 49.5 CRACKED B C ABORTED TAKEOFF O OTHER TO TAKEOFF 1 CA 2900S 4480 7970344 7970344 STA 49.5 BULKHEAD CRACKED AT UPPER NOSE GEAR ATTACH AREA - ALSO WINDSHIELD BRACE BUCKLED AT LOWER ATTACH AREA - NOTE: BR ACE INSTALLED AS PART OF STC SA 1434AT. (X) 1 L 7 2 3O A7SO 2000120600028 20001206 00028 CE 2000 12 6 20000927SH002 1 20000908 G 6123 1D41701 COUNTERWEIGHT MCAULY BEECH 58 58 1152740 CE CONT O520 IO520CB 17032 SO MCAULY 2A34C D2AF34C30 GL DEPARTED E VLGA C ABORTED TAKEOFF E VIBRATION/BUFFET TO TAKEOFF 1 GL 15 830Q 828 TH368 298938 725050 DURING THE TAKEOFF ROLL, THE PILOT EXPERIENCED A SEVERE VIBRATION. THE PILOT ABORTED THE TAKEOFF AND SHUT DOWN THE ENGI NES. AN INSPECTION OF THE AIRCRAFT REVEALED THAT A FEATHERING COUNTERWEIGHT ON THE LEFT PROPELLER HAD FAILED, DEPARTING THE AIRCRAFT AND DAMAGED THE SPINNER AND OPPOSITE BLADE. THE SEARCH FOR THE COUNTERWEIGHT IN THE SURROUNDING AREA HAS BEEN UNSUCCESSFUL (X). 1 L 7 2 3O 3 O 3A16 E5CE 5 C P5EA 2000100200058 20001002 00058 CE 2000 10 2 20000927SH003 1 20000926 G 2710 12601121 PULLEY CESSNA CESSNA 182 182S 2072701 CE QUADRANT BURRED B K NONE O OTHER IN INSP/MAINT 1 SW 11 543MC 79 18280548 WHILE PERFORMING SB 00-27-02, DATED AUGUST 14, 2000, TO INSPECT FOR PROPER RADIUS WHERE INTERCONNECT CABLE IS ATTACHED T O QUADRANT, AILERON CABLE 0510105-328 WAS FOUND SEVERELY WORN. CABLE WEAR WAS WHERE CABLE CONTACTED PULLEY GROOVE (OUTE R SECTION OF 1260112-1 PULLEY) OVER HOLE DRILLED FOR NAS561-6-32 PIN (INNER SECTION OF PULLEY) WHICH ATTACHES PULLEY TO AILERON CONTROL TUBE ASSEMBLY, FORWARD OF YOKE.(DIGITAL PICTURES AVAILABLE ON REQUEST). REF: OPER CONTROL NR 200002. (X) 1 H 7 1 3O NT 3A13 2001011101153 20010111 01153 SO 2001 1 11 20001010SH001 2 20000929 G 8550 SUMP CESSNA 150 150L 2071826 CE CONT O200 O200A 17020 SO ENGINE LOOSE C K NONE K FLUID LOSS IN INSP/MAINT 1 SO 13 18640 15074008 ON PREFLIGHT, PILOT NOTICED OILY RESIDUE ON OIL SUMP. DURING A SCHEDULED OIL CHANGE, OWNER/PILOT DISCOVERED ONE OF THE FOUR BRACES THAT EXTEND FROM THE SOIL SUMP FLANGE TO THE SUMP BODY HAD CRACKED PLACING ADDITIONAL STRESS ON THE REMAININ G BRACES. THIS FAILURE INCREASED STRESS ON THE OTHER OIL SUMP BRACES AND CREATED A CRACK IN THE OIL TANK ADJACENT TO TH E OVER STRESSED MEMBER. SUMP WAS REMOVED, OVERHAULED AND RETURNED TO SERVICE. (X) 1 H 7 1 3O 3 O 3A19 E252 2000113000038 20001130 00038 EA 2000 11 30 20001011SH001 2 20000703 G 8500 CAMSHAFT LYC O360 IO360A1B6 41514 EA HARTZL HCC2Y HCC2YK1 GL MAKING METAL W K NONE O OTHER IN INSP/MAINT 1 SW 99 HBKDO 1400 51A CH31018A DURING 50-HOUR INSPECTION, FOUND A FEW CHIPS IN OIL FILTER. 10 HOURS LATER, NO CHIPS FOUND. DURING 100-HOUR INSPECTION, AGAIN, SOME CHIPS. ENGINE CONTROLLED WITH A MORE DETAILED INSPECTION. FOUND CAMSHAFT CYLINDERS 3 AND 4 WORN OUT EXTRE MELY. AIRPLANE WAS USED FREQUENTLY FOR GLIDER TOWING. (X) 3 O 1E10 5 C P920 2000101800087 20001018 00087 2000 10 18 20001011SH002 4 20001006 G 6122 GOVERNOR ALIDSG CESSNA 441 441 2076020 CE GARRTT TPE331 TPE3318 01514 WP MALFUNCTIONED B O OTHER K FLUID LOSS TX TAXI/GRND HDL 1 SO 15 84LJ P337C 4410084 P31437C PILOT REPORTED THAT AFTER ENGINE SHUT-DOWN OF A NORMAL FLIGHT, OIL WAS NOTICED LEAKING PROFUSELY FROM THE RIGHT COWLING. FURTHER INVESTIGATION REVEALED THE OIL LEAK WAS ORIGINATING FROM THE PROP GOVERNOR BASE FLANGE SEAM. IT WAS VERIFIE D BY A MECHANIC THAT THE FLANGE GASKET WAS NOT THE SOURCE OF THE LEAK, BUT THE SEAM ON THE GOVERNOR WAS. GOVERNOR TIME IN SERVICE: 17.8 HOURS. (X) 1 L 7 2 3T 4 T RT A28CE E4WE 2000101800085 20001018 00085 2000 10 18 20001011SH003 4 20001006 G 6122 GOVERNOR ALIDSG CESSNA 441 441 2076020 CE GARRTT TPE331 TPE3318 01514 WP MALFUNCTIONED B E ENGINE SHUTDOWN K FLUID LOSS IN INSP/MAINT 1 SO 15 84LJ P1482 4410084 P31437C A MECHANIC INSTALLED A NEW PROP GOVERNOR, P/N 897160-9, ON THE RIGHT ENGINE OF A CESSNA 441. WHILE PERFORMING ROUTINE GR OUND RUNS AND LEAK CHECKS IT WAS NOTED THAT OIL WAS LEAKING FROM THE TORQUE MOTOR, SPECIFICALLY THE EXIT POINT FOR THE W IRES. GOVERNOR TIME IN SERVICE 0.0 HOURS SINCE NEW, GROUND RUN TIME ONLY. THIS PART NUMBER GOVERNOR HAS HAD A HISTORY OF VARIOUS OUT-OF-BOX FAILURES THROUGHOUT THE CESSNA 441 INDUSTRY. SUBMITTER SUGGESTED THAT WHEN THESE GOVERNORS ARE BE ING BENCH CHECKED AFTER ASSEMBLY, THE MANUFACTURER AND/OR OVERHAUL FACILITY SHOULD USE PREHEATED OIL ON THE TEST BENCH A ND OPERATE THE GOVERNORS FOR A LENGTH OF TIME. (X) 1 L 7 2 3T 4 T RT A28CE E4WE 2000101800086 20001018 00086 CE 2000 10 18 20001011SH004 1 20001004 G 3233 99810057604 ACTUATOR BEECH 200 B200 1152922 CE LT MAIN GEAR SHEARED B K NONE J WARNING INDICATION IN INSP/MAINT 1 SO 13 27LJ 5164 984 BB1040 UNSAFE GEAR INDICATION. INSPECTION REVEALED LT MAIN GEAR ACTUATOR JACKSCREW FAILURE INVOLVING SEPARATION OF SPLINES INT ERNALLY. FAILURE REPORTED TO FSDO-13 OF COLUMBIA, SC. FAA INSPECTOR PRESENT DURING ARRIVAL AND LANDING. AIRCRAFT LAN DED WITHOUT INCIDENT. (X) 1 L 7 2 4T A24CE 2000101800168 20001018 00168 CE 2000 10 18 20001011SH005 1 20001007 G 2822 476411 PUMP CESSNA 310 310Q 2074242 CE POWER LEAD FAILED C O OTHER O OTHER CR CRUISE 1 GL 25 69572 100 310Q0790 DURING FLIGHT, PILOT NOTICED LEFT LANDING LIGHT CIRCUIT BREAKER OPEN. AFTER LANDING, INSP FOUND LEFT TIP TANK FUEL TRAN SFER PUMP P/N 476411 FAILED ELECTRICALLY. PUMP SHOWED SIGNS OF HEAT AND ARCING ON OUTSIDE OF CASE FROM INTERNAL FAILURE . THIS PUMP IS WIRED BY MFG THROUGH LANDING LIGHT CIRCUIT. SUBMITTER STATED THESE PUMPS HAVE HAD A HIGH FAILURE RATE. THE PUMP ON THIS ACFT IS THE FIFTH ONE INSTALLED IN 14 MONTHS. TIME BETWEEN FAILURES HAS BEEN 64 HRS, 21.4 HRS, 15.2 H RS, 100.8 HRS. PUMP IS REQUIRED EQUIPMENT FOR AD NOTE MANDATED EQUIPMENT ON ALL SUCH INSTALLATIONS AND IS REQUIRED FOR FLIGHT OPERATIONS. ELECTRICAL FAILURE OF FUEL PUMPS CONSTITUTES A SIGNIFICANT FIRE/EXPLOSION HAZARD. (X) 1 L 7 2 3O 3A10 2000101800169 20001018 00169 CE 2000 10 18 20001011SH006 1 20001007 G 2822 476411 PUMP CESSNA 310 T310R 2074246 CE POWER LEAD FAILED C O OTHER O OTHER CR CRUISE 1 GL 25 310BA 95 310R0065 DURING FLIGHT, PILOT NOTICED RIGHT LANDING LIGHT CIRCUIT BREAKER OPEN. AFTER LANDING, INSP FOUND LEFT TIP TANK FUEL TRA NSFER PUMP P/N 476411 FAILED ELECTRICALLY. PUMP SHOWED SIGNS OF HEAT AND ARCING ON OUTSIDE OF CASE FROM INTERNAL FAILUR E. THIS PUMP IS WIRED BY MFG THROUGH LANDING LIGHT CIRCUIT. SUBMITTER STATED THESE PUMPS HAVE HAD A HIGH FAILURE RATE . THE PUMP ON THIS AIRCRAFT IS THE THIRD ONE INSTALLED IN 10 MONTHS. TIME BETWEEN FAILURES HAS BEEN 48 HRS, 10.3 HRS, 95 .7 HRS. PUMP IS REQUIRED EQUIPMENT FOR AD NOTE MANDATED EQUIPMENT ON ALL SUCH INSTALLATIONS AND IS REQUIRED FOR FLIGHT OPERATIONS. ELECTRICAL FAILURE OF FUEL PUMPS CONSTITUTES A SIGNIFICANT FIRE/EXPLOSION HAZARD. (X) 1 L 7 2 3O 3A10 2000101800096 20001018 00096 NE 2000 10 18 20001012SH004 3 20000821 G 6114 660714214 HUB ROTOL R390 R3904123F27 NE REAR FACE CRACKED B MS1R K NONE O OTHER IN INSP/MAINT 1 EA 21 11794 4321 DAP0009 CRACK FOUND IN HUB REAR HALF AT NR 4 THREADED, MOUNTING INSERT. CRACK IS APPROXIMATELY 3.5 INCHES LONG TRAVELING TOWARD NR 2 BLADE PORT OPENING. HUB REJECTED FROM SERVICE. (X) 6 C P31NE 2000101900285 20001019 00285 CE 2000 10 19 20001012SH005 2 20000901 G 8500 BEARING CONT IO360 IO360* 17025 CE ENGINE MAKING METAL B EDER K NONE O OTHER IN INSP/MAINT 1 SO 35 FOUND METAL IN FILTER. SENT SAMPLE OF FILTER TO LYCOMING. THEY SAID IT WAS BEARING MATERIAL AND RECOMMENDED TAKING OUT OF SERVICE. (X) 3 O E1CE 2000101800097 20001018 00097 CE 2000 10 18 20001012SH006 1 20001012 G 5521 033422013 SPAR CESSNA 195 195A 2073110 CE OUTBOARD TIP CRACKED D K NONE O OTHER IN INSP/MAINT 1 CE 03 1010D 7618 BOTH ELEVATOR SPARS CRACKED VERTICALLY INITIATING IN BEND RADIUS OF FLANGE TO MOUNT TIP RIB. THIS APPEARS TO BE FROM TO RSIONAL FLEXING DUE TO THE HEAVY COUNTERWEIGHT OPPOSING AIR LOADS. (X) 1 H 7 1 3R A790 2000101800098 20001018 00098 CE 2000 10 18 20001012SH007 1 20001012 G 5751 0322709 HINGE BRACKET CESSNA 190 190 2072902 CE LT & RT INBOARD CRACKED D K NONE O OTHER IN INSP/MAINT 1 CE 03 4339V 7245 FOUND BOTH INBOARD AILERON HINGE BRACKETS CRACKED COMPLETELY THROUGH THE BEARING BOSS. THESE BRACKETS WERE MADE FROM MA GNESIUM AND SUFFER CORROSION PROBLEMS. APPROXIMATELY 40 POUNDS OF PRESSURE SEPARATED THE AILERON FROM ITS HINGE/ATTACH ON THE INBOARD END. (X) 1 H 7 1 3R NC A790 2000101800099 20001018 00099 CE 2000 10 18 20001012SH008 1 20001012 G 5751 03227091 HINGE BRACKET CESSNA 190 190 2072902 CE LT & RT AILERON CRACKED D K NONE O OTHER IN INSP/MAINT 1 CE 03 4339V 7245 FOUND BOTH INBOARD AILERON HINGE BRACKETS CRACKED COMPLETELY THROUGH THE BEARING BOSS. THESE BRACKETS WERE MADE FROM MA GNESIUM AND SUFFER CORROSION PROBLEMS. APPROXIMATELY 40 POUNDS OF PRESSURE SEPARATED THE AILERON FROM ITS HINGE/ATTACH ON THE INBOARD END. (X) 1 H 7 1 3R NC A790 2000101800100 20001018 00100 CE 2000 10 18 20001012SH009 1 20000925 G 2781 HORN CESSNA 421 421C 2076016 CE MALFUNCTIONED G IBUA O OTHER N FALSE WARNING LD LANDING 1 WP 07 6793V 421C1022 LANDING GEAR WARNING HORN SOUNDED WITH GEAR EXTENDED WHEN FLAPS WERE MOVED FROM 15 DEGREES TO 30 DEGREES. AFTER CYCLING GEAR AND FLAPS 2-3 TIMES, SYSTEM FUNCTIONED PROPERLY. AIRCRAFT LANDED WITHOUT INCIDENT. FLAP SWITCH, THROTTLE SWITCH, AND WIRING WERE INSPECTED WITH NO FAULTS NOTED. PERFORMED FUNCTIONAL CHECK OF SYSTEM IAW CESSNA SERVICE MANUAL. SYSTE M FUNCTION NORMAL. (X) 1 L 7 2 3O A7CE 2000101800101 20001018 00101 CE 2000 10 18 20001012SH010 1 20000922 G 5540 07126161 BULKHEAD CESSNA 182 182E 2072712 CE BS 230.187 CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 01 NEW PART AS RECEIVED FROM CESSNA. RE-INSTALLATION INSPECTION FOUND THE .3750 INCH DIAMETER BOLT HOLES ELONGATED AND OVE RSIZED, EXCEEDING THE ACCEPTABLE LIMITS FOR BOLT HOLES LISTED IN AD 7207-09 PARA C)2)B) AND CESSNA SL SE 72-3. DETERMIN ED THE FINISHING PROCESS USED IN AREA OF RUDDER CABLE CUT-OUTS WOULD BE HIGHLY CONDUCIVE TO CRACKING. THIS INCLUDED SCO RING, GOUGING IN THE CORNER RADII, AND THINNING OF THE MATERIAL THICKNESS, AT ONE POINT PRODUCING A KNIFE EDGE. THESE D EFECTS WERE MADE WITH A SANDER OR SIMILAR TOOL. RUDDER CABLE CUT-OUTS ARE WITHIN THE CRITICAL AREAS FOR POTENTIAL CRACK ING AND INSPECTION REFERRED TO IN AD 72-07-09 AND CESSNA SL SE72-3 AND SE27-29. (X) 1 H 7 1 3O NT 3A13 2000101800102 20001018 00102 CE 2000 10 18 20001012SH011 1 20001012 G 5540 07126161 BULKHEAD CESSNA 182 182P 2075816 CE BS 230.187 CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 01 21268 18261528 NEW PART AS RECEIVED FROM CESSNA. RE-INSTALLATION INSPECTION FOUND THE .3750 INCH DIAMETER BOLT HOLES ELONGATED AND OVE RSIZED, EXCEEDING THE ACCEPTABLE LIMITS FOR BOLT HOLES LISTED IN AD 7207-09 PARA C)2)B) AND CESSNA SL SE 72-3. DETERMIN ED THE FINISHING PROCESS USED IN AREA OF RUDDER CABLE CUT-OUTS WOULD BE HIGHLY CONDUCIVE TO CRACKING. THIS INCLUDED SCO RING, GOUGING IN THE CORNER RADII, AND THINNING OF THE MATERIAL THICKNESS, AT ONE POINT PRODUCING A KNIFE EDGE. THESE D EFECTS WERE MADE WITH A SANDER OR SIMILAR TOOL. RUDDER CABLE CUT-OUTS ARE WITHIN THE CRITICAL AREAS FOR POTENTIAL CRACK ING AND INSPECTION REFERRED TO IN AD 72-07-09 AND CESSNA SL SE72-3 AND SE27-29. (X) 1 H 7 1 3O NT TA13 2000101800103 20001018 00103 CE 2000 10 18 20001012SH012 1 20000922 G 5540 07126161 BULKHEAD CESSNA 182 182J 2072722 CE BS 230.187 CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 01 3120F 3186 18257220 AFT BULKHEAD AT BS 230.187 WAS FOUND CRACKED DURING VISUAL INSPECTION IN THE AREA OF THE LEFT RUDDER CABLE CUT-OUT RADIU S AND THE BULKHEAD FLANGE. THESE CRACKS CAN BE VERY FINE AND HARD TO SEE. THEY USUALLY CAN BE VERIFIED BY VIEWING THE BULKHEAD FROM THE FRONT AND BACK. A COMMON AREA FOR CRACKS IS THE LOWER END OF THE OUTSIDE UPPER RADIUS. THIS IS ONE O F THE CRITICAL AREAS LISTED FOR INSPECTION IN AD 72-07-09 AND CESSNA SL SE72-3. REF: ALERTS 215 JUNE 1996 AND ALERTS 2 28 JULY 1997. (X) 1 H 7 1 3O NT 3A13 2001022200015 20010222 00015 SO 2001 2 22 20001012SH013 1 20000914 G 3242 1331317 STATOR EMB 120 EMB120 3260201 SO BRAKE ASSY CRACKED B XC4R K NONE O OTHER IN INSP/MAINT 1 SO 19 1681 0205 BRAKE ASSY, P/N 2-1661, FAILED PREMATURELY. NR 1 AND NR 2 STATORS CRACKED AT RELIEF HOLES. HEAT STACK WARPED AND UNEVE N WEAR. SUBMITTER STATED THIS IS A CONTINUAL DISCREPANCY. NOTE: OEM PARTS INSTALLED IN BRAKE ASSY AND THE MOST RECENT BRAKE CONFIGURATION, P/N 2-1661. (X) 2 L 7 2 4T RT A31SO 2001011101170 20010111 01170 SO 2001 1 11 20001012SH014 1 20000909 G 3240 1331317 STATOR EMB 120 EMB120 3260201 SO NR 1 & NR 2 DEFECTIVE B XC4R K NONE O OTHER IN INSP/MAINT 1 SO 19 1555 1253A BRAKE ASSY, P/N 2-1661, FAILED PREMATURELY. NR 1 AND NR 2 STATORS CRACKED AT RELIEF HOLES. HEAT STACK WARPED AND UNEVE N WEAR. SUBMITTER STATED THIS IS A CONTINUAL DISCREPANCY. NOTE: OEM PARTS INSTALLED IN BRAKE ASSY AND THE MOST RECENT BRAKE CONFIGURATION, P/N 2-1661. (X) 2 L 7 2 4T RT A31SO 2001011101171 20010111 01171 SO 2001 1 11 20001012SH015 1 20000914 G 3240 1331317 STATOR EMB 120 EMB120 3260201 SO NR 1 & NR 2 POS DEFECTIVE B XC4R K NONE O OTHER IN INSP/MAINT 1 SO 19 1689 1179A BRAKE ASSY, P/N 2-1661, FAILED PREMATURELY. NR 1 AND NR 2 STATORS CRACKED AT RELIEF HOLES. HEAT STACK WARPED AND UNEVE N WEAR. SUBMITTER STATED THIS IS A CONTINUAL DISCREPANCY. NOTE: OEM PARTS INSTALLED IN BRAKE ASSY, AND THE MOST RECEN T BRAKE CONFIGURATION, P/N 2-1661. (X) 2 L 7 2 4T RT A31SO 2001022200016 20010222 00016 SO 2001 2 22 20001012SH016 1 20000911 G 3242 1331317 STATOR EMB 120 EMB120 3260201 SO BRAKE ASSY CRACKED B XC4R K NONE O OTHER IN INSP/MAINT 1 SO 19 1600 0096 BRAKE ASSY, P/N 2-1661, FAILED PREMATURELY. NR 1 AND NR 2 STATORS CRACKED AT RELIEF HOLES. HEAT STACK WARPED AND UNEVE N WEAR. SUBMITTER STATED THIS IS A CONTINUAL DISCREPANCY. NOTE: OEM PARTS INSTALLED IN BRAKE ASSY, AND THE MOST RECEN T BRAKE CONFIGURATION, P/N 2-1661. (X) 2 L 7 2 4T RT A31SO 2001022200017 20010222 00017 SO 2001 2 22 20001012SH017 1 20000921 G 3242 1331317 STATOR EMB 120 EMB120 3260201 SO BRAKE ASSY CRACKED B XC4R K NONE O OTHER IN INSP/MAINT 1 SO 19 1785 1560A BRAKE ASSY, P/N 2-1661, FAILED PREMATURELY. NR 1 AND NR 2 STATORS CRACKED AT RELIEF HOLES. HEAT STACK WARPED AND UNEVE N WEAR. SUBMITTER STATED THIS IS A CONTINUAL DISCREPANCY. NOTE: OEM PARTS INSTALLED IN BRAKE ASSY, AND THE MOST RECEN T BRAKE CONFIGURATION, P/N 2-1661. (X) 2 L 7 2 4T RT A31SO 2001011101172 20010111 01172 2001 1 11 20001012SH018 4 20000915 G 6122 B20908 FLYWEIGHT MCAULY GOVERNOR CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 770751 RELEVANT MAGNETIC PARTICLE INDICATION IN CORNER OF FLYWEIGHT HEAD. (X) 2001011101173 20010111 01173 NE 2001 1 11 20001012SH019 1 20000718 G 6320 STRUCTURE SKRSKY SKRSKY S64 S64E 8142604 NE M/R GEARBOX CRACKED B JYDR K NONE O OTHER IN INSP/MAINT 1 NM 09 194AC 3402 1560 A6084 64017 DURING TEARDOWN, MGB, PN 6435-20400-063, SN 16-084, FOR O/H, 5 CRACKS VISUALLY NOTICED IN 5 OF 9 LIGHTENING HOLES IN LOW ER PLATE OF 2ND STAGE PLANETARY PLATE ASSY, P/N 6435-20231-014, SN EAC 3691. FLUORESCENT MAGNETIC PARTICLE INSPECT(FMPI ) REVEALED 8 CRACKS. LONGEST, 3.500 INCHES WHICH EXTENDS INTO THE .500 INCH RADIUS OF CENTER HUB. 7 OF 8 CRACKS BEGAN O N INBD SIDE OF LIGHTENING HOLES EXTENDING AT A 45 DEGREE ANGLE TOWARDS TO .500 INCH RADIUS. 1 CRACK BEGAN AT OTBD SIDE OF LIGHTENING HOLE, BUT DID NOT EXTEND OVER EDGE RADIUS OF THE HOLE. THIS IS THE SAME LIGHTENING HOLE CONTAINING 3.500 INCH CRACK. 2ND STAGE PLANETARY ASSY, PN 6435-20231-014, SN EAC 3681, TT 1936.9 HRS. PERFORMED 62.8 FLT HRS PREVIOUS. 2 G 7 2 4U H4EA 2001022200018 20010222 00018 CE 2001 2 22 20001012SH021 1 20000818 G 2612 47790008 CONTROL BOX CESSNA 208 208 2073702 CE PWA PT6 PT6A114A 52043 NE FIRE DETECTION FAILED E K NONE L NO TEST IN INSP/MAINT 1 SW 99 1273E 175 20800319 PCEPO0759 FIRE ALARM PUSH-TO-TEST FAILED TO ACTIVATE AUDIBLE HORN. DETERMINED THE FIRE DETECTION CONTROL BOX HAD FAILED. (X) 1 H 7 1 3T 3 T NT A37CE E4EA 2001030100018 20010301 00018 CE 2001 3 1 20001012SH022 1 20000728 G 7110 2652026200 ANGLE CESSNA 208 208B 2073701 CE NOSE CAP CRACKED E K NONE O OTHER IN INSP/MAINT 1 SW 99 12813 403 208B0808 FORWARD ANGLE ON LEFT NOSE CAP FOR INDUCTION AIR PLENUM ATTACHMENT CRACKED. (X) 1 H 7 1 3T A37CE 2001030100019 20010301 00019 CE 2001 3 1 20001012SH023 1 20000801 G 7110 2652026200 ANGLE CESSNA 208 208B 2073701 CE NOSE CAP CRACKED E K NONE O OTHER IN INSP/MAINT 1 SW 99 1275N 593 208B0756 FORWARD ANGLE ON LEFT NOSE CAP FOR INDUCTION AIR PLENUM ATTACHMENT CRACKED. (X) 1 H 7 1 3T A37CE 2001030100020 20010301 00020 SO 2001 3 1 20001012SH025 2 20000822 G 8530 PISTON BEECH 58 58 1152740 CE CONT O550 IO550C SO NR 3 CYLINDER STUCK B E ENGINE SHUTDOWN J WARNING INDICATION IN INSP/MAINT 1 EA 21 1015E 17 TH1776 815431 ENGINE LOST OIL PRESSURE, STARTED RUNNING ROUGH, AND OWNER SHUT ENGINE DOWN AND FEATHERED IT. AFTER FURTHER EVALUATION, NR 3 CYLINDER PISTON WAS NOT MOVING IN CYLINDER. ENGINE REMOVED AND SENT TO TCM FOR TEAR DOWN. NO DAMAGED SUSTAINED T O AIRCRAFT, PILOT LANDED WITH NO INCIDENT. (X) 1 L 7 2 3O 3 O 3A16 E3SO 2000120700106 20001207 00106 EU 2000 12 7 20001012SH026 1 20000814 G 7800 PC02596RH HEAT SHIELD RHNFLU EXT300 EA300L 70218DG EU FAILED B UV4R K NONE O OTHER IN INSP/MAINT 1 SO 15 13PR 5 115 EXHAUST HEAT SHIELD FAILED ITS CLAMP ATTACH TABS. SUBMITTER STATED THIS CONDITION COULD BE CONSIDERED SERIOUS IN THE EV ENT A PART FAILS AND BECOMES LOOSE IN THE ENGINE COMPARTMENT. (X) 1 M 7 1 3O NC EA67U 2000120700107 20001207 00107 EU 2000 12 7 20001012SH027 1 20000925 G 2730 PC00423 GRIP RHNFLU EXT300 EA300L 70218DG EU BALL GRIP ELEV DISLODGED B UV4R O OTHER F FLT CONT AFFECTED CR CRUISE 1 SO 15 13PR 28 115 ELEVATOR TRIM BALL GRIP CAME OFF IN-FLIGHT. OWNER COMMENTED HE NOTICED RED MARKS ON HIS RIGHT PANTS LEG JUST ABOVE THE KNEE ON SEVERAL OCCASIONS. SUBMITTER SUGGESTED ALL EXTRA OWNERS CHECK THEIR TRIM KNOBS FOR LOOSENESS AS THIS IS A POTEN TIALLY LIFE THREATENING DEFECT. (X) 1 M 7 1 3O NC EA67U 2000101800128 20001018 00128 CE 2000 10 18 20001012SH028 1 20000915 G 2810 051600918 RESERVOIR CESSNA 172 172R 2072401 CE LOWER, L/E CRACKED B DYCR K NONE K FLUID LOSS IN INSP/MAINT 1 GL 07 172QS 17280440 PILOT REPORTED FUEL DRIPPING FROM UNDER ACFT. MECH DETERMINED IT WAS DRAIN VALVE. DRAIN VALVE REPLACED. FUEL CONTINUE D TO DRIP FROM THE VALVE. INVEST SHOWED THE LEAK WAS COMING FROM THE LOWER LEADING EDGE SEAM OF THE RESERVOIR TANK. AF TER REMOVAL, 2 INCH CRACK IN THE WELD WAS VISIBLE UPON INSP. NO OBVIOUS CAUSE OF THE FRACTURE WAS VISIBLE. POSSIBLE CA USE MAY BE FROM RESERVOIR TANK FLEXING FROM BUILT-UP VENT PRESSURE AND THE WEIGHT OF THE FUEL. INSP OF THIS ITEM ON A S CHEDULED BASIS SHOULD BE ACCOMPLISHED TO DETERMINE CONDITION. SUBMITTER STATED IF SEAM WOULD FAIL DURING FLIGHT, ALL FU EL ONBOARD WOULD BE LOST AND ENGINE WOULD STARVE FOR FUEL. (X) 1 H 7 1 3O NT 3A12 2000101800129 20001018 00129 CE 2000 10 18 20001012SH029 1 20000918 G 7130 0553006209 FIREWALL CESSNA 172 172P 2072436 CE LOWER CRACKED B IKBR K NONE O OTHER IN INSP/MAINT 1 GL 07 100SU 17275001 FIREWALL CRACKS WHERE ENGINE COWLING SHOCK MOUNTS ARE ATTACHED TO THE LOWER FIREWALL AND FIREWALL REINFORCEMENTS. CRACK S APPEAR TO BE DUE TO THE AGE OF THE AIRCRAFT. AIRCRAFT TT, 12,705 HOURS. REPAIRS WERE MADE IAW CESSNA STRUCTURAL REPA IR MANUAL. THIS IS A WELL MAINTAINED AIRCRAFT AND IS USED IN A FLIGHT TRAINING ENVIRONMENT. (X) 1 H 7 1 3O NT 3A12 2000101800009 20001018 00009 CE 2000 10 18 20001012SH030 1 20000904 G 2730 50934042 TUBE CESSNA 402 402C 207590R CE CONT O520 TSIO520UB 17040 SO INSIDE TUBE RUSTED D K NONE O OTHER IN INSP/MAINT 1 GL 01 1361G 402C0270 REMOVED RIGHT ELEVATOR FROM AIRCRAFT TO REPLACE HINGE BEARINGS. CLEANED INSIDE TUBE AND NOTICED 3 RUSTED HOLES THROUGH TUBE. REPLACED TUBE WITH NEW AND LUBED INSIDE TUBE. (X) 1 L 7 2 3O 3 O A7CE E8CE 2000101800109 20001018 00109 SO 2000 10 18 20001013SH001 1 20000914 G 2810 6399816 FUEL TANK PIPER PA28 PA28235 7102810 SO CTR LT WING TANK CONTAMINATED D K NONE O OTHER IN INSP/MAINT 1 GL 09 15219 287310024 DURING ANNUAL INSPECTION, THE MAIN FUEL SUMP SCREEN WAS FOUND ALMOST COMPLETELY BLOCKED WITH A REDDISH/BROWN MATTER. TH E FUEL TANKS'' INTERIOR WAS INSPECTED AND FOUND TO HAVE BEEN SLUSHED AT UNKNOWN DATE AND TIME. THE SLUSHING COMPOUND W AS DISINTEGRATING AND FLAKING OFF. THE TANKS WERE DRAINED AND SENT TO A REPAIR FACILITY FOR REMOVAL OF THE SLUSHING COM POUND AND RESEALED WITH STC APPROVED FFCS-100. NOTE: AIRCRAFT IS BEING USED WITH AUTO FUEL AND IS STC''D FOR AUTO FUEL USE. (X) 1 L 7 1 3O 2A13 2000101800110 20001018 00110 SO 2000 10 18 20001013SH002 1 20000914 G 2810 6399817 FUEL TANK PIPER PA28 PA28235 7102810 SO CTR RT WING TANK CONTAMINATED D K NONE O OTHER IN INSP/MAINT 1 GL 09 15219 287310024 DURING ANNUAL INSPECTION, THE MAIN FUEL SUMP SCREEN WAS FOUND ALMOST COMPLETELY BLOCKED WITH A REDDISH/BROWN MATTER. TH E FUEL TANKS'' INTERIOR WAS INSPECTED AND FOUND TO HAVE BEEN SLUSHED AT UNKNOWN DATE AND TIME. THE SLUSHING COMPOUND W AS DISINTEGRATING AND FLAKING OFF. THE TANKS WERE DRAINED AND SENT TO A REPAIR FACILITY FOR REMOVAL OF THE SLUSHING COM POUND AND RESEALED WITH STC APPROVED FFCS-100. NOTE: AIRCRAFT IS BEING USED WITH AUTO FUEL AND IS STC''D FOR AUTO FUEL USE. (X) 1 L 7 1 3O 2A13 2000101800108 20001018 00108 SO 2000 10 18 20001013SH003 1 20001010 G 2740 6270197 CONTROL CABLE PIPER PA34 PA34200T 7103406 SO AFT FUSELAGE BROKEN C A UNSCHED LANDING F FLT CONT AFFECTED CR CRUISE 1 WP 07 810JP 4415 347670088 STABILATOR TRIM CABLE (P/N 62701-97) BROKE AT THE ELECTRIC TRIM DRIVE WHEEL ASSEMBLY WHILE DOING STEEP TURNS IN PT FOR C OMML (ME). AIRCRAFT PITCHED UP 10-20 DEGREES BUT WAS CONTROLLABLE BY SLOWING AND LOWERING FLAPS TO FIRST NOTCH FOR SLOW RETURN AND LANDING WITHOUT FURTHER PROBLEM. ABOVE PART WAS REPLACED. SUSPECT OVER-STRESS OF TRIM CABLE (P/N 62701-73) A ND THAT WAS ALSO REPLACED. ALL CONTROL/TRIM FUNCTIONS RESTORED TO NORMAL. FORM 337 ISSUED 11 OCT AND MAILED TO SCOTTSD ALE FSDO. (X) 1 L 7 2 3O A7SO 2000101800111 20001018 00111 CE 2000 10 18 20001013SH004 1 20000930 G 7932 633233W CAP BEECH 35 V35B 1151548 CE CONT O520 IO520BA 17032 SO BROKEN D K NONE O OTHER IN INSP/MAINT 1 EA 17 18287 D10032 562885 AFTER CHECKING THE ENGINE OIL QUANTITY, THE ROD-OIL-GAUGE CAP FAILED TO SECURELY LOCK IN PLACE WHEN IT WAS REINSTALLED. UPON INVESTIGATION, FOUND ONE OF THE TWO LOCKING TABS HAD BENT 90 INCHES UP INTO THE FILLER CAP''S ROD-PLATE SPRING COM PARTMENT. OVER TIME, THE TAB HAD WORN VERY THIN FROM REPEATED USE. WHILE ON THE BENCH FOR INSPECTION, THIS BENT LOCKIN G TAB DID BREAK OFF. THE LOCKING TAB COULD HAVE FALLEN INTO THE CRANKCASE. SUBMITTER RECOMMENDED CLOSE VISUAL INSPECTI ON OF THIS ROD-OIL-GAUGE CAP ASSY EACH TIME THE ENGINE OIL QUANTITY IS CHECKED. IMPROVED ROD-OIL-GAUGE, TCM P/N 652171- 1, WAS INSTALLED. (X) 1 L 7 1 3O 3 O 3A15 E5CE 2000101800140 20001018 00140 CE 2000 10 18 20001013SH005 1 20000921 G 2510 201101510 SEAT TRACK CESSNA 177 177RG 2073709 CE CORRODED B X0FR K NONE O OTHER IN INSP/MAINT 1 WP 07 1597H 177RG0771 INTERGRANULAR CORROSION FOUND ON VERTICAL LEG OF SEAT TRACK STARTING AT LAST SEAT ADJUSTMENT PIN HOLE (APPROX 20.25 INCH ES FROM MOST FORWARD HOLE). CORROSION STARTED AT AFT EDGE OF HOLE AND PROGRESSED AFT ONE INCH. SURFACE METAL ON RIGHT SIDE OF VERTICAL LEG WAS FOUND EXFOLIATING APPROXIMATELY 2.5 PERCENT OF TOTAL THICKNESS. POSSIBLE CAUSE IS EXPLAINED IN AC 43.13-1B, PAGES 6-17 AND 6-18, PROPER PERIODIC INSPECTIONS. (X) 1 H 7 1 3O A20CE 2000101800141 20001018 00141 SO 2000 10 18 20001013SH006 1 20000901 G 3230 105476 MOTOR PIPER PA28 PA28R200 7102811 SO EMPENNAGE FAILED H O OTHER O OTHER NR NOT REPORTED 1 GL 11 1334T 62 28R7235263 LANDING GEAR MOTOR WOULD NOT OPERATE IN THE DOWN POSITION. ON JACKS, THE GEAR MOTOR IS GETTING VOLTAGE, TAPPING MOTOR W ITH HAMMER WILL CAUSE MOTOR TO OPERATE. (X) 1 L 7 1 3O 2A13 2000101800142 20001018 00142 SW 2000 10 18 20001013SH007 1 20000912 G 5280 LINK GULSTM 690TP 690A 0141722 SW MAIN GEAR CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 11 690SM 7077 11337 LINK ARM ASSY LOCATED ON RIGHT MAIN GEAR TO DOOR LINK FOUND CRACKED AT LINK TO ARM ATTACH AREA. (X) 1 H 7 2 3T 2A4 2000101800144 20001018 00144 CE 2000 10 18 20001013SH008 1 20000921 G 5530 04310093 FITTING CESSNA CESSNA 150 152 2071835 CE CRACKED D K NONE O OTHER IN INSP/MAINT 1 GL 11 4713B 5099 15283593 TEE SHAPED FITTING ON THE TRAILING EDGE OF THE FIN WAS CRACKED ON THE RIGHT SIDE IN THE RADIUS. (X) 1 H 7 1 3O NT 3A19 2000101800088 20001018 00088 EA 2000 10 18 20001013SH009 2 20000918 G 8520 LW13521 CONNECTING ROD PIPER PA23 PA23250 7102308 SO LYC O540 IO540C4B5 41532 EA BEARING FACE FLAKING D K NONE O OTHER IN INSP/MAINT 1 GL 11 2589Z 764 278154006 RL1888548A DURING ROUTINE OIL CHANGE, FOUND ABUNDANT METAL PARTICLES IN OIL FILTER AND FINGER SCREEN. AFTER CONFERRING WITH LYCOMI NG, ALL CYLINDERS WERE PULLED TO CHECK PILOTED PISTON PIN PLUGS, NO ABNORMAL WEAR WAS NOTED. SENT OIL FILTER AND FINGER SCREEN METAL TO LYCOMING FOR ANALYSIS, FOUND ALL METAL WAS BEARING INSERT MATERIAL. OVERHAUL SHOP NOTED THAT CONNECTIN G ROD BEARING INSERT WAS FLAKING APART. TOTAL TIME ON FACTORY REMANUFACTURED, 763 HOURS, DATE COMPLETED 10-25-96, POSSI BLE CAUSE: UNKNOWN. (X) 1 L 7 2 3O 3 O 1A10 1E4 2001011101174 20010111 01174 EU 2001 1 11 20001013SH010 1 20000802 G 6710 SC5083 SERVO SNIAS 350 AS350B2 8680813 EU LT/RT CONTROL LEAKING B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 102LN 755 3065 SERVO LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001020801003 20010208 01003 EU 2001 2 8 20001013SH011 1 20000805 G 6710 SC5083 SERVO SNIAS 350 AS350B3 8680954 EU MAIN ROTOR LEAKING B R7MR K NONE K FLUID LOSS IN INSP/MAINT 1 NM 07 104LN 954 3134 SERVO LEAKING BEYOND SERVICEABLE LIMITS. REPALCED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001011101175 20010111 01175 EU 2001 1 11 20001013SH012 1 20000801 G 7931 DK040 TRANSMITTER BOLKMS 105 BO105CBS 5626008 EU ENGINE OIL INOPERATIVE B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 105LC S789 PRESSURE TRANSMITTER UNIT INOPERATIVE. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U NC H3EU 2001011101176 20010111 01176 EU 2001 1 11 20001013SH013 1 20000513 G 7931 DK040 TRANSMITTER BOLKMS 105 BO105CBS 5626008 EU ENGINE OIL INOPERATIVE B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 105LC 47 S789 TRANSMITTER UNIT INOPERATIVE. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U NC H3EU 2001011101177 20010111 01177 EU 2001 1 11 20001013SH014 1 20000523 G 7931 DK042M0D01 TRANSMITTER BOLKMS 105 BO105CBS 5626008 EU OIL PRESSURE INOPERATIVE B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 105LC 665 S789 TRANSMMITTER UNIT INOPERATIVE. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U NC H3EU 2001011101178 20010111 01178 EU 2001 1 11 20001013SH015 1 20000629 G 6230 1051011305 BELLOWS BOLKMS 117 BK117B1 5626012 EU MAIN ROTOR TORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 117BK 751 7229 BELLOWS IS TORN AROUND CLAMP AND FOLD AREAS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U H13EU 2000101600452 20001016 00452 CE 2000 10 16 20001013SH017 1 20000913 G 2820 560010631 FUEL LINE CESSNA 340 340CESSNA 2076404 CE NACELLE/FIREWALL WORN D O OTHER O OTHER IN INSP/MAINT 1 SW 99 10MF 6300 3400198 DURING INSTALLATION OF FUEL LINE CROSSFEED KIT NR SK340-31-6, REMOVAL OF THE OLD LINES REVEALED THAT TWO LINES HAD NEARL Y BEEN WORN THROUGH DUE TO CONTACT WITH INSPECTION PANEL SCREWS. THE ORIGINAL TUBING WAS PROTECTED BY THE ABRASION CUSH IONS, BUT THE EXTENT OF DAMAGE WAS NOT EVIDENT UNTIL THE CUSHION WAS PEELED OFF. VERY LITTLE CLEARANCE IS AVAILABLE AT THIS POINT, AND NEARLY IMPOSSIBLE TO DETECT ANY DAMAGE DURING INSPECTIONS. IF THIS CONDITION GOES UNDETECTED, THE NEW T UBING WILL ALSO BE DAMAGED. NUTPLATE/SCREW CLEARANCE FROM FUEL TUBING MUST BE VERIFIED. (X) 1 L 7 2 3O 3A25 2000101600453 20001016 00453 CE 2000 10 16 20001013SH019 1 20000914 G 5540 MS289135 BEARING BEECH 200 200BEECH 1152920 CE RUDDER LOOSE B BXSR O OTHER O OTHER IN INSP/MAINT 1 EA 09 200BE 8238 BB832 BEARING FOUND TO HAVE EXCESSIVE RADIAL FREE PLAY. AFTER REMOVAL FROM THE AIRCRAFT, THE BEARING WAS DISASSEMBLED. FOUND THE INTERNALS WERE DRY. THE LUBRICATION WAS HARD. THIS BEARING SHOULD HAVE A LUBRICATION FITTING OR A CALENDAR REPLACE MENT INTERVAL. (X) 1 L 7 2 4T A24CE 2000101600454 20001016 00454 CE 2000 10 16 20001013SH020 1 20001013 G 7130 12536072 FIREWALL CESSNA 206 T206H CE LWR RT DIAG STRP CRACKED H K NONE O OTHER IN INSP/MAINT 1 NM 09 206VW 92 T20608064 DURING FIRST ANNUAL INSPECTION, FOUND CRACK IN DIAGONAL SUPPORT ACROSS LOWER RIGHT FIREWALL. CRACK APPEARS TO BE CAUSED BY A MANUFACTURING DEFECT. (X) 1 H 7 1 3O A4CE 2000101600455 20001016 00455 SW 2000 10 16 20001013SH021 1 20000907 G 6100 D20887 DRIVE GEAR MCAULY MOONEY M20 M20J 5870219 SW LYC O360 IO360A3B6 41514 EA FAILED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 15 201JY 1100 820251 24318 REVELANT MAG PARTICLE INDICATION IN TEETH AREA. (X) 1 L 7 1 3O 3 O 2A3 1E10 2000101600456 20001016 00456 2000 10 16 20001013SH022 4 20000907 G 6122 D20271 GOVERNOR MCAULY MOONEY M20 M20J 5870219 SW LYC O360 IO360A3B6 41514 EA CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 201JY 1100 241318 RELEVANT EDDY CURRENT AND PENETRANT TESTING INDICATION AROUND HEAD OF GOVERNOR BODY. (X) 1 L 7 1 3O 3 O 2A3 1E10 2000101600457 20001016 00457 CE 2000 10 16 20001013SH023 1 20000814 G 3710 216CW PUMP CESSNA 206 206H 2073301 CE LYC O540 IO540AC1A5 EA RIGHT SIDE SHEARED E K NONE O OTHER NR NOT REPORTED 1 SW 99 2312V 50 20608046 L2695848A RIGHT VACUUM PUMP FAILED, DRIVESHAFT SHEARED. (X) 1 H 7 1 3O 3 O RT A4CE 1E4 2000101600458 20001016 00458 CE 2000 10 16 20001013SH024 1 20000908 G 5540 0532104 BUSHING CESSNA 172 172M 2072418 CE RUDDER WORN D K NONE O OTHER IN INSP/MAINT 1 SW 99 20299 4943 17261172 DURING INSPECTION, FOUND THE RUDDER HINGE BUSHINGS SEVERELY WORN. VISUAL INSPECTION OF THE BUSHINGS DID NOT REVEAL ANY NOTICEABLE WEAR. GENTLY PUSHING THE RUDDER AGAINST ITS STOPS WHILE WATCHING THE HINGE ALIGNMENT SHOWED ADDITIONAL MOVEM ENT. THE FULL EXTENT OF WEAR BECAME APPARENT AFTER REMOVAL OF THE RUDDER. CABLE TENSION MUST BE REMOVED TO DETECT WEAR . THE AIRCRAFT WAS RETURNED TO SERVICE WITH NEW BUSHINGS. (X) 1 H 7 1 3O NT 3A12 2000101600459 20001016 00459 CE 2000 10 16 20001013SH026 1 20000809 G 8100 12509981 LANYARD CESSNA 206 T206H CE LYC O540 TIO540AJ1A EA MISSING H K NONE O OTHER IN INSP/MAINT 1 NM 09 206VW 92 T20608064 L1021361A LANYARD AND ALL ATTACHING HARDWARE FOUND MISSING AND NO SIGN OF EVER BEING INSTALLED DURING FIRST ANNUAL INSPECTION. SU BMITTER STATED THIS DEFECT COULD CAUSE AN IN-FLIGHT FIRE. (X) 1 H 7 1 3O 3 O A4CE E14EA 2000101600460 20001016 00460 CE 2000 10 16 20001013SH027 1 20001013 G 3500 OXYGEN BOTTLE CESSNA 206 T206H CE MISINSTALLED H K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 09 206VW 92 T20608064 OXYGEN BOTTLE APPEARS TO BE INSTALLED ON WRONG SIDE OF AIRCRAFT. REF: CESSNA SERVICE MANUAL INSIDE OF AIRCRAFT TAILCON E. (X) 1 H 7 1 3O A4CE 2000101600461 20001016 00461 CE 2000 10 16 20001013SH028 1 20001013 G 7160 BOLT LYC CESSNA 206 T206H CE LYC O540 TIO540AJ1A EA MISSING H K NONE O OTHER IN INSP/MAINT 1 NM 09 206VW 92 T20608064 L1021361A FOUND FORWARD SECURING BOLT MISSING FROM INTAKE PLENUM. SUBMITTER STATED THERE WAS NO SIGN OF EVER BEING INSTALLED. (X ) 1 H 7 1 3O 3 O A4CE E14EA 2001020801004 20010208 01004 EU 2001 2 8 20001016SH001 1 20001004 G 2121 0500846 BLOWER SNIAS 350 AS350BA 8680817 EU COCKPIT FAN FAILED D LBGA A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 WP 13 87EW 126 2116 DURING FLIGHT, SMOKE FILLED INTO THE CABIN. FIRST, TURNED ALL ELEC OFF SWITCH. VENTED THE CABIN BY OPENING THE FRONT V ENT AND WINDOW (PILOT SIDE). AFTER DETERMINING THERE WAS NO DANGER TO THE SAFE OPERATION OF THE AIRCRAFT, CONTINUED TO ALTERNATE AIRPORT, THEN TURNED ON PRIMARY INSTRUMENTS AND LATER THE AIRCRAFT FAN, THEN DETERMINED IT WAS THE AIRCRAFT 7 INCH FAN. BECAUSE OF THE NATURE OF THE FAILURE, RETURNED TO THE PRIMARY A/P WITHOUT INCIDENT. (X) 1 G 7 1 3U NC H9EU 2001022200004 20010222 00004 SO 2001 2 22 20001016SH003 2 20001002 G 7314 6429324 PUMP CONT BEECH 36 36BEECH 1151602 CE CONT O550 IO550B SO ENGINE LEAKING H K NONE K FLUID LOSS IN INSP/MAINT 1 WP 05 7883R 182 E138 297118R AT 80 HRS TT, FWD SEAL VENT LINE STARTED DISCHARGING SMALL AMTS OF OIL IRREG. OIL ON OUTSIDE OF LT COWL SUSPECTED TO BE RESIDUAL OIL VENTING FROM HEAT. NO BLUE FUEL STAINS EVIDENT. THERE WAS A LOW PRESSURE WHEN PRIMING WITH BOOST PUMP, N OT OUT OF NORMAL RANGE. EGT CONFIRMED MIXTURE SO LEAN, IT WOULD DESTROY ENG BEFORE DEVELOPING POWER FOR TAKEOFF. VERIF IED FUEL PUMP LEAKING BY OPERATING BOOST PUMP WITH ENGINE OFF. FUEL FLOWED OUT VENT. (X) 1 L 7 1 3O 3 O 3A15 E3SO 2000120700109 20001207 00109 EU 2000 12 7 20001016SH004 1 20000725 G 7800 PC02596RH HEAT SHIELD RHNFLU EXT300 EA300L 70218DG EU LOOSE H UV4R K NONE O OTHER IN INSP/MAINT 1 SO 15 278SJ 15 113 EXHAUST HEAT SHIELD FAILED ITS CLAMP ATTACH TABS. THIS CONDITION COULD BE CONSIDERED SERIOUS IN THE EVENT A PART FAILS AND BECOMES LOOSE IN THE ENGINE COMPARTMENT. (X) 1 M 7 1 3O NC EA67U 2001022300003 20010223 00003 SO 2001 2 23 20001016SH007 1 20000918 G 3233 484373 SOLENOID PIPER PA32 PA32RT300T 7103216 SO MLG MALFUNCTIONED D O OTHER J WARNING INDICATION AP APPROACH 1 SO 33 21423 32R7887205 ACFT MADE GEAR UP LANDING AFTER ALTERNATE GEAR EXTENSION PROCEDURES FAILED TO EXTEND GEAR. PILOT REPORTED HEARING GEAR HYD PUMP RUNNING AT ALL TIMES. JUST PRIOR TO TOUCHDOWN, PILOT TURNED OFF MASTER POWER, AND GEAR ATTEMPTED TO EXTEND. T WO DC POWER SOLENOIDS CONTROL PUMP DIRECTION (GEAR UP/GEAR DOWN). FOUND ''UP'' SOLENOID HAD ARCED CONTACT, SENDING DC P OWER TO ''UP'' DIRECTION OF HYD PUMP. SUBMITTER SUSPECTED SOLENOID HAD STUCK, KEEPING GEAR RETRACTED. SUBMITTER RECOMM ENDED PERIODIC REPLACEMENT OF SOLENOIDS, PIPER PN 484-373, TO PRECLUDE POSSIBILITY OF GEAR UP LANDINGS. (X) 1 L 7 1 3O A3SO 2000101900286 20001019 00286 CE 2000 10 19 20001016SH012 1 20000914 G 3231 55421029 TORQUE TUBE CESSNA 500 550 2076604 CE AT WELD CRACKED B K NONE O OTHER NR NOT REPORTED 1 GL 03 361DB 187 5500884 OPERATOR REPORTED THE NOSE LANDING GEAR DOORS ARE NOT CLOSED TIGHT. INVESTIGATION FOUND THE NOSE LANDING GEAR DOORS TOR QUE TUBE DAMAGED. THE RIGHT END PLATE ON TORQUE TUBE HAD ONE WELD BROKEN AND THE OTHER WELD CRACKED. REPLACED TORQUE T UBE AND RIGGED NLG DOORS. (X) 1 L 7 2 4F A22CE 2000101900287 20001019 00287 CE 2000 10 19 20001016SH013 1 20001016 G 3230 4582507239 BRACE BEECH 58 58 1152740 CE RT AFT RETRACT CRACKED E FPIA O OTHER O OTHER NR NOT REPORTED 1 SO 15 329H 9694 TH219 FOUND ITEM CRACKED DURING ROUTINE INSPECTION. CRACK LOCATED ON LOWER SIDE OF RIGHT TUBE WHERE RETRACT ROD ATTACH POINT AND BRACE PIVOT POINT ARE WELDED TOGETHER. SECOND INCIDENT IN NINETY DAYS. FIRST INCIDENT PART FAILED AND CAUSED GEAR COLLAPSE ON LANDING. AIRCRAFT N NR 103GA, S/N JH-213. (X) 1 L 7 2 3O 3A16 2000101900288 20001019 00288 CE 2000 10 19 20001016SH014 1 20000830 G 3340 SWITCH BEECH 58 58 1152740 CE TAXI LIGHT SHORTED A BSYA O OTHER B SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 GL 07 33WC TH170 BWI - TAXIING OUT FOR TAKEOFF, SMELLED SMOKE, RETURNED TO BASE. FOUND TAXI LIGHT SWITCH SHORTED TO WIRING HARNESS SUPPO RT CLAMP. REMOVED AND REPLACED TAXI LIGHT SWITCH AND BURNED WIRES. RETURNED AIRCRAFT TO SERVICE. (X) 1 L 7 2 3O 3A16 2000101900289 20001019 00289 CE 2000 10 19 20001016SH015 1 20000913 G 2742 31350012 SCREW LEAR 35 31 5170530 CE THREADS CORRODED B JGVR K NONE O OTHER IN INSP/MAINT 1 CE 09 331N 022 SCREW ASSEMBLY BAD FROM STOCK. SCREW ASSEMBLY, S/N K138L, WAS FOUND CORRODED WHEN REMOVED FROM WRAPPING. (X) 2 L 7 2 4F RT A10CE 2000101900290 20001019 00290 CE 2000 10 19 20001016SH016 1 20000913 G 2742 31355402 SCREW LEAR LEAR 35 31 5170530 CE STAB ACTUATOR NICKED B JGVR O OTHER O OTHER IN INSP/MAINT 1 CE 09 331N 022 SCREW ASSEMBLY BAD FROM STOCK. SCREW ASSEMBLY, S/N K320L, HAD TWO NICKS ON THREAD SURFACE. (X) 2 L 7 2 4F RT A10CE 2000101900291 20001019 00291 CE 2000 10 19 20001016SH017 1 20000911 G 5610 51116052 WINDOW CESSNA 421 421C 2076016 CE EMERGENCY EXIT CRACKED B R2JR K NONE O OTHER IN INSP/MAINT 1 EA 21 3237U 4520 421C0112 WHILE REPLACING PRESSURIZATION SEAL ON EMERGENCY EXIT, UPHOLSTERY WAS REMOVED. FOUND OUTER WINDOW BROKEN BETWEEN FASTEN ER HOLES. PIECES WERE GLUED IN WITH RTV. CAUSE OF FAILURE BELIEVED TO BE IMPROPER INSTALLATION. NEW WINDOW INSTALLED ALONG WITH METAL RETAINER RING REQUIRED BY CESSNA SB MEB 87-4. (X) 1 L 7 2 3O A7CE 2000101900292 20001019 00292 CE 2000 10 19 20001016SH018 1 20000911 G 7120 505403042 BEAM CESSNA 421 421C 2076016 CE CRACKED B R2JR K NONE O OTHER IN INSP/MAINT 1 EA 21 3237U 4520 421C0112 WHILE PERFORMING ANNUAL INSPECTION, FOUND LEFT ENGINE BEAM WITH 1.50 INCH CRACK ON UPPER CAP. CRACK HAD BEEN STOP DRILL ED, BUT THIS IS NOT A LEGAL REPAIR. BEAM MUST BE REPLACED WITH NEW. CESSNA FIELD SERVICE HAD TO ASSIST TO OBTAIN NEW P ARTS THAT WOULD FIT. CAUSE OF CRACK SUSPECTED TO BE IMPROPER FIT AT MANUFACTURE. SUBMITTER SUGGESTED CLOSE VISUAL INSP ECTION OF THESE BEAMS AT REGULAR INTERVALS. (X) 1 L 7 2 3O A7CE 2000101900293 20001019 00293 CE 2000 10 19 20001016SH019 1 20000911 G 2520 MEB003 SEAT CESSNA 421 421C 2076016 CE CABIN MISINSTALLED B R2JR K NONE O OTHER IN INSP/MAINT 1 EA 21 3237U 4520 421C0112 UPON C/W CESSNA MANDATORY SB MEB 00-3, FOUND ALL 4 CABIN SEATS INSTALLED IN WRONG POSITIONS. PLACARDED AND REINSTALLED SEATS FOR SB. SUBMITTER SUGGESTED A RECURRING AD NOTE BE ISSUED TO REQUIRE C/W THIS BULLETIN. IMPROPER INSTALLATION OF FORWARD AND AFT FACING SEATS NEGATE ANY CRASHWORTHINESS DESIGNED IN THE SEAT. (X) 1 L 7 2 3O A7CE 2000101900294 20001019 00294 CE 2000 10 19 20001016SH020 1 20000911 G 3230 5141200 UPLOCK CESSNA 421 421C 2076016 CE WORN B R2JR K NONE O OTHER IN INSP/MAINT 1 EA 21 3237U 4520 421C0112 OPERATOR COMPLAINED OF HYDRAULIC SYSTEM STAYING ON AFTER LANDING GEAR RETRACTION. COULD NOT DUPLICATE ON JACKS. CESSNA FIELD SERVICE SUGGESTED INSTALLING NEW IMPROVED PARTS FOR UPLOCK HOOKS AND SWITCHES PER CESSNA SI LETTER NR M81-2. NEW PARTS WERE MORE SUBSTANTIAL AND HIGHER QUALITY. SOLVED PROBLEM. ORIGINAL PARTS BADLY WORN. SUBMITTER SUGGESTED COMPL IANCE ON ALL EARLY SERIAL NUMBERED AIRCRAFT. (X) 1 L 7 2 3O A7CE 2001022100084 20010221 00084 CE 2001 2 21 20001016SH021 1 20000911 G 5730 SA2872SW SKIN CESSNA 421 421C 2076016 CE WING DAMAGED B R2JR K NONE O OTHER IN INSP/MAINT 1 EA 21 3237U 421C0112 DURING AIRCRAFT INSPECTION, FOUND RT STC''ED BAGGAGE LOCKER 28 GAL - FUEL TANK HOLD-DOWNS PULLING THROUGH UPPER WING SKI N. 337 FORMS FOUND, BUT NO STC CERTIFICATE. FURTHER INSPECTION REVEALED THIS ENTIRE INSTALLATION DOES NOT SEEM TO MEET INDUSTRY STANDARDS. STC UNAVAILABLE AT THIS TIME AND WILL BE REQUIRED TO CONDUCT CONFORMITY INSPECTION BEFORE AIRCRAFT MAY BE APPROVED FOR RETURN TO SERVICE. AWAITING DRAWINGS FROM STC HOLDER. (X) 1 L 7 2 3O A7CE 2000121500008 20001215 00008 CE 2000 12 15 20001016SH022 1 20000911 G 2820 510011075 LINE CESSNA 421 421C 2076016 CE COLLET CRACKED B R2JR K NONE K FLUID LOSS IN INSP/MAINT 1 EA 21 3237U 4520 421C0112 WHILE CHANGING DEFECTIVE FUEL TANK SELECTOR VALVE (LEFT), FOUND MAIN FUEL LINE TO BOOST PUMP HAD A CRACKED COLLET. NEW LINE INSTALLED. SUBMITTER STATED LEAK OR FAILURE OF THIS LINE COULD CAUSE ENGINE FAILURE AND/OR FIRE. CAUSE OF FAILURE UNKNOWN. (X) 1 L 7 2 3O A7CE 2001022300006 20010223 00006 EA 2001 2 23 20001016SH024 2 20001003 G 8520 LW19340 CAMSHAFT PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA ENGINE DAMAGED I WVBA K NONE O OTHER IN INSP/MAINT 1 AL 01 3527U 1786 317952141 L836861A DURING INSPECTION, LOW CYLINDER COMPRESSION WAS DETECTED DURING THE COMPRESSION CHECK. THE CYLINDER WAS REMOVED AND A V ISUAL INSPECTION PEFORMED ON THE CAMSHAFT. DETERMINED BOTH NR 3 AND NR 4 INTAKE LOBES AND TAPPET FACES WERE DAMAGED. S UBMITTER STATED THIS IS THE FOURTEENTH SUCH OCCURRENCE IN APPROXIMATELY 2-1/2 YEARS FOR THIS OPERATOR. (X) 1 L 7 2 3O 3 O A20SO E14EA 2001020500142 20010205 00142 EU 2001 2 5 20001016SH025 1 20000831 G 7332 642100021 TRANSMITTER AEROSP SA365 SA365N 8680669 EU TMECA ARRIEL ARRIEL1C 60030 NE FUEL PRESSURE INTERMITTENT I ZYWA K NONE O OTHER IN INSP/MAINT 1 GL 09 365SJ 6018 2256 FUEL PRESSURE INTERMITTENT. REMOVED AND REPLACED TRANSMITTER. (X) 1 G 7 2 3U 3 U H10EU E19EU 2001030100021 20010301 00021 GL 2001 3 1 20001016SH026 3 20000912 G 6111 V10133 BLADE HELIO H391 H391B 4300106 CE HARTZL HC82V HC82V201 GL PROPELLER DAMAGED B W59R K NONE O OTHER IN INSP/MAINT 1 WP 07 4120D 044 7682N PROPELLER WAS BEING SERVICED DURING AN ANNUAL 100-HOUR INSPECTION. WHILE ATTEMPTING TO GREASE THE PROPELLER, WATER WAS FOUND STREAMING FROM THE BLADE CLAMPS. PROPELLER WAS DISASSEMBLED AND LIGHT RUST AND CORROSION WAS FOUND THROUGHOUT THE PROPELLER ESPECIALLY IN THE BLADE BALANCE HOLES. ALTHOUGH THE CORROSION WAS LIGHT, THE BALANCE HOLES WERE ALREADY WELL OVER THE MAXIMUM INSIDE DIAMETER FOR REPAIR. THE AIRCRAFT HAD NOT FLOWN AT ALL DURING THE PREVIOUS YEAR. (X) 1 H 7 1 3O 1A8 5 C P23EA 2001030100022 20010301 00022 GL 2001 3 1 20001016SH027 3 20000912 G 6111 V10133 BLADE HELIO H391 H391B 4300106 CE HARTZL HC82V HC82V201 GL PROPELLER DAMAGED B W59R K NONE O OTHER IN INSP/MAINT 1 WP 07 4120D 044 7682N PROPELLER WAS BEING SERVICED DURING AN ANNUAL 100-HOUR INSPECTION. WHILE ATTEMPTING TO GREASE THE PROPELLER, WATER WAS FOUND STREAMING FROM THE BLADE CLAMPS. PROPELLER WAS DISASSEMBLED AND LIGHT RUST AND CORROSION WAS FOUND THROUGHOUT THE PROPELLER ESPECIALLY IN THE BLADE BALANCE HOLES. ALTHOUGH THE CORROSION WAS LIGHT, THE BALANCE HOLES WERE ALREADY WELL OVER THE MAXIMUM INSIDE DIAMETER FOR REPAIR. THE AIRCRAFT HAD NOT FLOWN AT ALL DURING THE PREVIOUS YEAR. (X) 1 H 7 1 3O 1A8 5 C P23EA 2001022300007 20010223 00007 EA 2001 2 23 20001017SH001 2 20000921 G 7322 30802 FLOAT PRECISION PIPER PA28 PA28181 7102807 SO LYC O360 O360A2F 41514 EA CARBURETOR LEAKING B KC2R K NONE O OTHER IN INSP/MAINT 1 GL 03 4419F 200 7501826 287790027 CUSTOMER SUBMITTED CARBURETOR FOR REPAIR FOR A ''STUMBLE IN ACCELERATION''. SPLIT CARBURETOR AND FOUND FUEL IN BOTH PON TOONS ON NEW STYLE ADVANCED POLYMER FLOAT. ALSO, FOUND SCREWS LOOSE HOLDING THROTTLE PLATE TO SHAFT. PLATE MOVED FREEL Y IN SHAFT SLOT. (X) 1 L 7 1 3O 3 O 2A13 E286 2001022300008 20010223 00008 SO 2001 2 23 20001017SH002 1 20000914 G 2710 62701123 CONTROL CABLE PIPER PA28 PA28181 7102807 SO AILERON FRAYED B K NONE O OTHER IN INSP/MAINT 1 GL 19 4145X 1472 2843152 DURING A ROUTINE INSPECTION, THE LEFT AILERON BALANCE CABLE WAS FOUND FRAYED BY THE LEFT WING ROOT RIB. (X) 1 L 7 1 3O 2A13 2000101900295 20001019 00295 SO 2000 10 19 20001017SH003 1 20000906 G 2780 829132 PUSHROD TUBE PIPER PA46 PA46350P SO INBD FLAP WELL BINDING B AMYR K NONE W INADEQUATE Q C IN INSP/MAINT 1 CE 05 41518 28 4636302 BOTH FLAPS BINDING IN TRACKS WHILE EXTENDING FROM FULL UP POSITION TO APPROXIMATELY FIVE DEGREES. FOUND PUSH ROD P/N 82 913-2 THE WRONG LENGTH PER MM, CHAPTER 27-509-00 PAGE 8, PARA (69). THIS MEASUREMENT OF 5.26 INCHES WILL NOT ALLOW BOLT TO BE INSTALLED. (X) 1 L 7 1 3O RT A25SO 2000101900296 20001019 00296 SO 2000 10 19 20001017SH004 1 20000831 G 3234 SELECTOR KNOB PIPER PA31 PA31350 7103110 SO MALFUNCTIONED A BSYA O OTHER N FALSE WARNING LD LANDING 1 GL 07 4UE 318152061 GRR - HAD 3 GREEN DOWN AND LOCK LIGHTS, HANDLE WOULD NOT RETURN TO NEUTRAL. HAD MAINTENANCE JACK AIRCRAFT, CYCLE GEAR M ANY TIMES, COULD NOT DUPLICATE. HYDRAULIC RESERVOIR FULL, BOTH PUMPS CHECKED OK. (X) 1 L 7 2 3O A20SO 2000101900297 20001019 00297 SO 2000 10 19 20001017SH005 1 20000810 G 3230 UPLOCK PIPER PA31 PA31350 7103110 SO MALFUNCTIONED A BSYA O OTHER J WARNING INDICATION TO TAKEOFF 1 GL 07 4UE 318152061 CMH - AFTER TAKEOFF, COULD NOT GET GEAR UP AND LOCKED INDICATION, RETURNED TO CMH. JACKED AIRCRAFT CHECKED ALL UPLOCK A DJUSTMENTS AND OPERATION, CLEANED AND LUBED ALL UPLOCK ATACHMENTS, CYCLED GEAR SEVERAL TIMES. OPS CHECKED GOOD. (X) 1 L 7 2 3O A20SO 2000101900298 20001019 00298 SO 2000 10 19 20001017SH006 1 20000808 G 3230 4878621CH214 DOWNLOCK PIPER PA31 PA31350 7103110 SO MAIN GEAR MALADJUSTMENT A BSYA O OTHER J WARNING INDICATION NR NOT REPORTED 1 GL 07 4079Y 318152079 CMH - LEFT GEAR DID NOT INDICATE DOWN AND LOCK. RECYCLED GEAR, THEN CAME ON. MAINTENANCE JACKED AIRCRAFT, REMOVED AND REPLACED LEFT GEAR DOWN AND LOCK SWITCH. OPS CHECKED GOOD. (X) 1 L 7 2 3O A20SO 2000101900299 20001019 00299 SO 2000 10 19 20001017SH007 1 20000906 G 2730 5698102 LINK PIPER PA31 PA31350 7103110 SO SPRING ATTACH WORN D K NONE O OTHER IN INSP/MAINT 1 NE 01 4095L 318152178 C/W AD 98-08-18 (SB626C) ELEVATOR DOWN SPRING REPLACEMENT. SB CALLS FOR REPLACEMENT OF SPRING, PN 71056-03, AND LINK, P /N 71086-03, BUT DOES NOT ADDRESS THE LINK (P/N 56981-02) AT THE OTHER END OF THE SPRING WHICH IS WORN AT THE ATTACH HOL E. (X) 1 L 7 2 3O A20SO 2000101900300 20001019 00300 SO 2000 10 19 20001017SH008 2 20000920 G 7322 63338811 CONTROLLER PIPER PA34 PA34220T 7103420 SO CONT O360 TSIO360KB 17025 SO LINKAGE LOOSE B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 01 4128X 3449112 EXCESS PLAY IN ARM TO LINKAGE. (X) 1 L 7 2 3O 3 O A7SO E9CE 2000101900301 20001019 00301 SO 2000 10 19 20001017SH009 2 20000920 G 7322 63338811 CONTROLLER PIPER PA34 PA34220T 7103420 SO CONT O360 LTSIO360RB SO MALADJUSTMENT B VJ3R O OTHER O OTHER IN INSP/MAINT 1 WP 07 4128X 1428 3449112 321749R THE CONTROLLER PISTON STICK IN. A SPLIT IN POWER SETTING IN-FLIGHT AND ON THE GROUND. CONTROLLER REPLACED. (X) 1 L 7 2 3O 3 O A7SO E9CE 2000101900302 20001019 00302 CE 2000 10 19 20001017SH010 2 20000614 G 7322 63338811 CONTROLLER PIPER PA34 PA34220T 7103420 SO CONT O360 TSIO360RB 17025 CE MALFUNCTIONED B VJ3R O OTHER O OTHER NR NOT REPORTED 1 WP 07 4128X 30 3449112 819255R THE CONTROLLER PISTON STICK IN. A SPLIT IN POWER SETTING IN-FLIGHT AND ON THE GROUND. CONTROLLER REPLACED. (X) 1 L 7 2 3O 3 O A7SO E9CE 2000101900303 20001019 00303 SO 2000 10 19 20001017SH011 1 20000928 G 2700 62701126 CONTROL CABLE PIPER PA34 PA34220T 7103420 SO FRAYED B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 4128X 1448 3449112 RIGHT HAND BALANCE CABLE FRAYED. (X) 1 L 7 2 3O A7SO 2000101900304 20001019 00304 CE 2000 10 19 20001017SH012 2 20000922 G 7322 63338811 CONTROLLER PIPER PA34 PA34220T 7103420 SO CONT O360 TSIO360RB 17025 CE MALFUNCTIONED B XC4R K NONE O OTHER NR NOT REPORTED 1 WP 07 4177R 218 3449046 819257R THE CONTROLLER PISTON STICK IN. A SPLIT IN POWER SETTING IN-FLIGHT AND ON GROUND. CONTROLLER REPLACED. (X) 1 L 7 2 3O 3 O A7SO E9CE 2000101900305 20001019 00305 CE 2000 10 19 20001017SH013 2 20000404 G 7322 63338811 CONTROLLER PIPER PA34 PA34220T 7103420 SO CONT O360 TSIO360RB 17025 CE MALFUNCTIONED B XC4R K NONE O OTHER NR NOT REPORTED 1 WP 07 4177R 181 3449046 819257R THE CONTROLLER PISTON STICK IN. A SPLIT IN POWER SETTING IN-FLIGHT AND ON THE GROUND. CONTROLLER REPLACED. (X) 1 L 7 2 3O 3 O A7SO E9CE 2001020801005 20010208 01005 EU 2001 2 8 20001017SH014 1 20000818 G 2432 RG355 CASE SNIAS 350 AS350B2 8680813 EU BATTERY CRACKED B RC0R K NONE O OTHER IN INSP/MAINT 1 SW 17 4035W 395 2912 DURING 100-HOUR INSPECTION, LEAD ACID BATTERY WAS FOUND WITH A CASE CRACK IN ALL THE LOWER BOX CORNERS. ALL OF THE CRA CKS ARE 1 INCH TO 2 INCHES LONG. BATTERY IS INSTALLED IN THE TAIL BOOM UNDER AN AEC STC. AT APPROX 119.48 STA, THE LEA D ACID BATTERY IS 4 POUNDS AND THE NICAD, IS 38 POUNDS. TIME ON BATTERY 395 HOURS. WITH THE INCREASED WEIGHT OF BATTER Y AND LOCATION, POSSIBLY THE CASE OF THE BATTERY CANNOT STAND UP TO THE VIBRATIONS. ATTACH BRACKET WHERE THE BATTERY CL AMPS DOWN IS SQUARE CUT NOT ROUNDED. SUBMITTER STATED SECOND ACFT IN FLEET AT THIS SITE WITH THIS CONDITION. TO-DATE, SUBMITTER HAS HAD 6 CASES OF BATTERY BOX CASE CRACKING. (X) 1 G 7 1 3U H9EU 2000101900306 20001019 00306 SO 2000 10 19 20001017SH015 1 20000825 G 2740 62701047 CONTROL CABLE PIPER PA28 PA28181 7102807 SO STAB FRAYED B K NONE O OTHER IN INSP/MAINT 1 WP 07 4130W 1592 2843204 TRIM CABLE FRAYED AT THE REAR TRIM DRUM. (X) 1 L 7 1 3O 2A13 2000101900307 20001019 00307 GL 2000 10 19 20001017SH016 3 20000906 G 6114 D2AF34C30NP HUB MCAULY BEECH 58 58 1152740 CE HARTZL HC92Z HC92ZK1 GL BLADE RET THREAD CRACKED B B2PR K NONE O OTHER IN INSP/MAINT 1 SO 17 4183A TH21 PROPELLER RECEIVED TO INVESTIGATE CAUSE OF DYED OIL LEAKING FROM HUB CAVITY. PROPELLER WAS DISASSEMBLED AND UPON INSPEC TION, SEVERAL CRACKS WERE FOUND IN THE BLADE RETENTION THREADS. CRACKS WERE VERIFIED USING EDDY CURRENT INSPECTION. (X ) 1 L 7 2 3O 3A16 5 C P892 2001020900012 20010209 00012 EU 2001 2 9 20001017SH017 1 20000622 G 7110 1172312001 COWLING BOLKMS 117 BK117A3 5626015 EU FUSELAGE WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 420MB 510 7077 CATCHER/CREST COWLING WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U H13EU 2001020900013 20010209 00013 EU 2001 2 9 20001017SH018 1 20000801 G 7930 6607190A SWITCH BOLKMS 105 BO105S 5626006 EU OIL PRESSURE INOPERATIVE B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 485EC 476 S754 OIL PRESSURE WARNING SWITCH UNIT INOPERATIVE. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U H3EU 2001022300009 20010223 00009 SO 2001 2 23 20001017SH019 2 20000908 G 7322 63338811 CONTROLLER PIPER PA34 PA34220T 7103420 SO CONT O360 LTSIO360RB SO FUEL SYSTEM STUCK B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 4142N 393 3449128 322021R THE CONTROLLER PISTON STICK IN. A SPLIT IN POWER SETING IN-FLIGHT AND ON THE GROUND. CONTROLLER REPLACED. (X) 1 L 7 2 3O 3 O A7SO E9CE 2001022300010 20010223 00010 SO 2001 2 23 20001017SH020 2 20000915 G 7322 RSA5AD SERVO PIPER PA34 PA34220T 7103420 SO CONT O360 LTSIO360RB SO FUEL INJECTOR FAILED B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 4142N 716 3449128 322021R ENGINE DIED AT IDLE, UNABLE TO ADJUST MIXTURE. (X) 1 L 7 2 3O 3 O A7SO E9CE 2001030100023 20010301 00023 SO 2001 3 1 20001017SH021 1 20000914 G 2700 67701073 CONTROL CABLE PIPER PA34 PA34220T 7103420 SO FLIGHT CONTROL FRAYED B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 4142N 1290 3449128 REAR TRIM CABLE FRAYED. (X) 1 L 7 2 3O A7SO 2001020900014 20010209 00014 SW 2001 2 9 20001017SH022 1 20000918 G 6710 369H7024 NUT HUGHES HUGHES 500N 500N 3027374 SW UNILOCK LOOSE B O OTHER O OTHER NR NOT REPORTED 1 WP 07 520PM 24 0245985326 LN059 AT ACTT: 23.5 HOURS, THE UNILOCK, PN 369A7010501 SN 024598-5326, WAS INSTALLED IN NEW CONDITION TO REPLACE A LEAKING UN ILOCK. AFTER 23.6 HRS OF OPERATION, PILOT RETURNED STATING THE CYCLIC CONTROL HAD PLAY LONGITUDINALLY. THE GRIP WOULD MOVE SEVERAL INCHES BEFORE THE INPUT WOULD BE SENT TO THE ROTOR SYSTEM. FOUND NUT, PN 269H7024, WAS LOOSE ALLOWING THE INPUT ROD END TO MOVE. IF THE NUT COMPLETELY LOOSENED, THE ROD END MAY SEPARATE FROM THE UNILOCK LEAVING PILOT WITH NO LONGITUDINAL CONTROL. (X) 1 G 7 1 3U NC H3WE 2001022300011 20010223 00011 EA 2001 2 23 20001017SH024 2 20000828 G 8520 SL75060 ROD BOLT PIPER PA34 PA34200 7103405 SO LYC O360 IO360C1E6 41514 EA ENGINE BROKEN B K NONE O OTHER IN INSP/MAINT 1 SO 14 56213 820 347350304 L80367A NR 3 CONNECTING ROD BOLT PN SL-75060 BROKE CAUSING THE CONNECTING ROD CAP TO SEPARATE RESULTING IN COMPLETE ENGINE FAILU RE. AIRCRAFT LANDED WITHOUT INCIDENT. (X) 1 L 7 2 3O 3 O A7SO 1E10 2001020900015 20010209 00015 EU 2001 2 9 20001017SH028 1 20000919 G 6210 10514101111 BOLT BOLKMS 117 BK117B1 5626012 EU M/R BLADE CRACKED B K NONE O OTHER IN INSP/MAINT 1 EA 17 601EH 728 050042 7181 AGC/CJI - DURING POST-FLIGHT FOUND MAIN ROTOR BLADE SECONDARY BOLT PROTRUDING UP 1 INCH OUT OF BOLT HOLE. NUT AND REMAI NING PART OF BOLT MISSING. (COMPLETELY CRACKED IN HALF). POSSIBLE CAUSE: UNDER INVESTIGATION. (X) 1 G 7 2 3U H13EU 2001020900016 20010209 00016 SW 2001 2 9 20001017SH029 1 20000919 G 3213 20505015249 CROSSTUBE BELL 204 UH1H 1181407 SW LANDING GEAR CRACKED B SXHL K NONE O OTHER IN INSP/MAINT 1 NM 13 6257P 6308807 DURING REFUEL, FOUND FORWARD CROSSTUBE AT RIGHT SADDLE CRACKED. POSSIBLE CAUSE, WEAR. (X) 1 G 7 1 4U EXPA1G71 2001020900017 20010209 00017 SW 2001 2 9 20001017SH030 1 20000901 G 5302 2050307121 ANGLE BELL 204 UH1H 1181407 SW TAILBOOM MOUNT CRACKED B SXHL K NONE O OTHER IN INSP/MAINT 1 NM 13 6257P 6308807 FOUND ANGLE CRACKED AT LEFT LOWER TAILBOOM MOUNT. POSSIBLE CAUSE IS STRESS TORQUE OF TAILBOOM TO FUSELAGE. (X) 1 G 7 1 4U EXPA1G71 2001022300013 20010223 00013 CE 2001 2 23 20001017SH031 1 20000904 G 5330 SKIN BEECH 200 200BEECH 1152920 CE FUSELAGE CRACKED B K NONE O OTHER IN INSP/MAINT 1 NM 03 60PD 15615 BB58 DURING EVENT NR 1 INSPECTION AND SPECIAL STRUCTURAL, BELOW FLOORBOARD FROM FORWARD PRESSURE BULKHEAD TO AFT PRESSURE BUL KHEAD, A 1.50 INCH LATERAL CRACK WAS FOUND IN THE LOWER SKIN PANEL AT APPROXIMATE CENTERLINE OF AIRCRAFT ABOUT .50 INCH FORWARD OF BS 167.625. SUBMITTER STATED THIS WILL REQUIRE DOUBLER REPAIR. (X) 1 L 7 2 4T A24CE 2001020900018 20010209 00018 EU 2001 2 9 20001017SH032 1 20000524 G 7712 G555674 TRANSDUCER BOLKMS 117 BK117B1 5626012 EU ENGINE TORQUE INOPERATIVE B R7MR O OTHER O OTHER NR NOT REPORTED 1 NM 07 62LF 380 7163 PRESSURE TRANSDUCER UNIT INOPERATIVE. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U H13EU 2000101900308 20001019 00308 CE 2000 10 19 20001017SH033 1 20000918 G 2436 VR515G REGULATOR CESSNA 210 P210N 2073454 CE SHORTED G O OTHER H ELECT. POWER LOSS-50 PC CR CRUISE 1 EA 13 734JV P21000604 PILOT EXPERIENCED ELECTRICAL POWER FAILURE. NEW ALTERNATOR INSTALLED. PILOT DEPARTED EN ROUTE HOME WHEN ELECTRICAL POW ER WAS LOST AGAIN 9-19-2000. MAINT REPLACED VOLTAGE REGULATOR. THIS IS THE SECOND INCIDENT. IN TWO YEARS, BOTH TIMES THE INDIVIDUAL COMPONENTS WERE REPLACED AT DIFFERENT TIMES. SUBMITTER SUGGESTED ANY ALTERNATOR FAILURE OF THIS SYSTEM, BOTH THE ALTERNATOR AND REGULATOR, SHOULD BE REPLACED TOGETHER. (X) 1 H 7 1 3O 3A21 2000101900309 20001019 00309 2000 10 19 20001017SH034 4 20000906 G 6122 A20107 GEAR MCAULY CESSNA 402 402B 207590P CE DEFECTIVE B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 768WC 1400 740086 402B1066 RELEVANT MAG PARTICLE INDICATION AROUND TEETH AREA. (X) 1 L 7 2 3O A7CE 2000101900310 20001019 00310 CE 2000 10 19 20001017SH035 1 20000819 G 3710 216CW PUMP CESSNA 206 206H 2073301 CE LYC O540 IO540AC1A5 EA RIGHT SIDE SHAFT SHEARED H K NONE O OTHER IN INSP/MAINT 1 SW 99 7273Q 181 20608045 L2694348A RIGHT VACUUM PUMP FAILED, DRIVESHAFT SHEARED. (X) 1 H 7 1 3O 3 O RT A4CE 1E4 2000101900311 20001019 00311 SO 2000 10 19 20001017SH036 1 20000817 G 2823 491497 VALVE PIPER PA28 PA28180 7102808 SO CABIN SIDEWALL BROKEN D O OTHER O OTHER NR NOT REPORTED 1 SW 99 7846W 281864 FUEL SELECTOR WAS FOUND STIFF AND HAD NO DETECTABLE DETENTS. IN ADDITION, WHILE EXERCISING THE SELECTOR, IT WOULD OCCAS IONALLY SEIZE UP IN RANDOM POSITIONS. TEAR DOWN OF VALVE SHOWED THE DETENT RING HAD DEFORMED AND BROKEN IN TWO PIECES. INTERNAL VALVE WEAR WAS MINIMAL. AIRCRAFT RETURNED TO SERVICE WITH A NEW VALVE. (X) 1 L 7 1 3O 2A13 2001020900019 20010209 00019 GL 2001 2 9 20001017SH037 1 20000916 G 7410 MILT7928 TERMINAL AMTR RF2000 RAF2000 13017MN GL AMTR SUBARU EA81 59050 GL IGNITION WIRE BROKEN G A UNSCHED LANDING Y ENGINE STOPPAGE LD LANDING 1 WP 25 86523 1124 H2934104 AIRCRAFT FORCED TO EMERGENCY LAND AFTER ENGINE QUIT DURING LANDING. AIRCRAFT IS AN AMATEUR BUILT GYRO PLANE. THE ENGIN E WAS A SUBURU WITH SINGLE COIL IGNITION SYSTEM. POST-LANDING INSPECTION REVEALED THE COIL WIRE TERMINAL LUG BROKE OFF THE COIL WHICH TERMINATED IGNITION. OPERATOR STATED HE ALWAYS CHECKS THESE CONNECTIONS DURING PRE-FLIGHTS BY GRASPING T HEM FOR SECURITY CHECK. 1 G 7 1 3O 3 O NT EXPA1G71 EXPA 2000101900312 20001019 00312 CE 2000 10 19 20001017SH038 1 20000912 G 7331 910532P INDICATOR BEECH 60 A60 1153604 CE FUEL FLOW MALFUNCTIONED H O OTHER O OTHER IN INSP/MAINT 1 NM 08 81AG P219 INSTALLED SHADIN FUEL FLOW INDICATOR SYSTEM. PROCESSOR LOCKED UP AND WOULD NOT FUNCTION ON SECOND TEST. RETURNED TO FA CTORY FOR SERVICE. (X) 1 L 7 2 3O A12CE 2000101900313 20001019 00313 CE 2000 10 19 20001017SH039 1 20000823 G 7810 PIPE CESSNA 172 172C 2072408 CE CONT O300 O300D 17022 SO MUFFLER ASSY CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 09 8414X 17248914 34410D6D COWL REMOVED FOR ANNUAL INSP, MASSIVE EXHAUST LEAKS APPARENT AT NR''S 2, 3, AND 4 EXHAUST FLANGES. NR 2 WAS MISSING INB D ATTACH NUT, NR''S 2 AND 4 INLET STACKS IMPROPERLY ORIENTED AND CAUSED FAILURE OF FLANGE GASKET, HAIRLINE CRACK IN MUFF LER AT NR 4 INLET. EXH LEAKAGE AT NR 3 CYL ERODED PORT AND MAY HAVE CAUSED WARPED EXH VALVE IN CYL. ENG HAD 11.0 HRS T SO, 31.0 HRS TSI. REMOVAL OF MUFFLERS FOUND INTERNAL BAFFLES IN BOTH MUFFLERS BURNED AWAY. (X) 1 H 7 1 3O 3 O NT 3A12 E253 2000101900314 20001019 00314 SO 2000 10 19 20001017SH040 2 20000914 G 8550 7429322 PUMP BEECH 33 F33A 1151425 CE CONT O520 IO520BB 17032 SO ENGINE LEAKING B VJ3R K NONE K FLUID LOSS IN INSP/MAINT 1 WP 07 8240T 1274 CE1542 813973R OIL LEAKING FROM VENT. (X) 1 L 7 1 3O 3 O 3A15 E5CE 2000101900315 20001019 00315 SO 2000 10 19 20001017SH041 2 20000925 G 8530 CYLINDER HEAD CESSNA 414 414 2075908 CE CONT O520 TSIO520J 17040 SO NR 5 DESTROYED D O OTHER R PARTIAL RPM/PWR LOSS TO TAKEOFF 1 EA 21 8139Q 2756 1356 4140039 218930H OFP - AFTER TAKEOFF IN VFR CONDITIONS, PILOT REPORTED ENGINE FIRE ON RIGHT ENGINE. AFTER SAFE LANDING, AND INSPECTION O F THE ENGINE REVEALED A 1.75 INCH HOLE IN THE SIDE OF NR 5 CYLINDER HEAD EXHAUST CHAMBER. UPON TEAR-DOWN INSPECTION OF THE ENGINE AND ACCESSORIES, NO OTHER DEFECTS WERE NOTED. POSSIBLE CAUSE TO HEAD FAILURE WAS DETERMINED TO BE AGE OF UNI T AND CRACKING IN THIS HIGH STRESS AREA. (X) 1 L 7 2 3O 3 O RT A7CE E8CE 2000101900316 20001019 00316 SO 2000 10 19 20001017SH042 1 20000907 G 2434 4111809 ALTERNATOR PIPER PA28 PA28181 7102807 SO SOLDER TAB LNGTH FAILED D O OTHER H ELECT. POWER LOSS-50 PC CR CRUISE 1 EA 17 8366Z 53 288190206 DURING TRAINING FLIGHT, PILOT NOTICED SEVERAL HIGH AMPERAGE SPIKES FOLLOWED BY A TOTAL LOSS OF ELECTRICAL OUTPUT FROM TH E ALTERNATOR. ALSO DAMAGED ELECTRICALLY WERE THE VOLTAGE REGULATOR AND OVERVOLTAGE RELAY. POSSIBLE CAUSE FOUND DURING A BENCH CHECK OF AFFECTED ALTERNATOR, AN ARCING FROM FIELD TERMINAL LUG TO THE TIP OF THE REAR COOLING FAN. ABRASIONS F OUND ON ALL OF THE COOLING FAN TIPS INDICATED A CONTINUOUS ARCING HAD BEEN OCCURRING. THE MATTER HAS BEEN BROUGHT TO TH E ATTENTION OF THE ELECTROSYSTEMS, INC. (X) 1 L 7 1 3O 2A13 2001020900020 20010209 00020 EU 2001 2 9 20001017SH043 1 20000818 G 2432 RG355 BATTERY SNIAS 350 AS350B2 8680813 EU TAIL BOOM CRACKED B RC0R K NONE O OTHER IN INSP/MAINT 1 SW 17 896WD 441 2926 DURING 100-HR INSP, LEAD ACID BATTERY FOUND WITH A CASE CRACK IN THE LEFT FORWARD LOWER CORNER. CRACK IS APPROX 1 INCH LONG. BATTERY IS INSTALLED IN THE TAIL BOOM UNDER AN AEC STC AT APPROX 119.48 STA. THE LEAD ACID BATTERY IS 41 POUNDS, NICAD IS 38 POUNDS. TIME ON BATTERY IS 440 HOURS. SUBMITTER SUGGESTED INCREASED WEIGHT OF THE BATTERY AND THE LOCATI ON, THAT THE CASE OF THE BATTERY CANNOT STAND UP TO THE VIBRATIONS PUT ON IT IN THIS LOCATION. THE ATTACHMENT BRACKET W HERE THE BATTERY CLAMPS DOWN IS SQUARE CUT, NOT ROUNDED. THIS MAY ALSO PUT UNDUE STRESS ON THE BATTERY BOX IN THE CORNE RS. STC SH5117NM BATT RELOC, STC SR09185RC NICAD LEAD ACID CONV, FIELD APPROVAL, COMBINED BOTH STC''S ON SAME ACFT. (X 1 G 7 1 3U H9EU 2000102500170 20001025 00170 CE 2000 10 25 20001017SH045 1 20000915 G 8011 MZ4222 STARTER CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA FRONT BEARING DEFECTIVE D O OTHER O OTHER IN INSP/MAINT 1 SW 01 9627Q 119 17265711 FRONT BEARING WORKED OUT OF HOUSING IN 199 HOURS TIME IN SERVICE DUE TO INCORRECT BUSHING NOT PROPERLY FITTED IN HOUSING . INCORRECT PART SIZE, INCORRECT INSTALLATION. OHC WOH 467690 6/10/00. (X) 1 H 7 1 3O 3 O NT 3A12 E274 2001022300015 20010223 00015 CE 2001 2 23 20001018SH001 1 20000831 G 3246 EDO688652 FLOAT CESSNA 175 175 2072502 CE RT FRONT STRUT CRACKED C K NONE O OTHER IN INSP/MAINT 1 AL 05 9366B 55166 RIGHT FRONT STRUT FLOATS CRACKED. (X) 1 H 7 1 3O NT 3A17 2001022300016 20010223 00016 CE 2001 2 23 20001018SH003 1 20000827 G 5312 07126261 BULKHEAD CESSNA 182 182E 2072712 CE FUSELAGE CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 01 9327 18253727 VISUAL INSPECTION OF BULKHEAD REVEALED A HAIRLINE CRACK .25 INCH LONG AT THE LEFT RUDDER CABLE CUT-OUT IN THE OUTER RADI US NEAREST THE BULKHEAD FLANGE. AD 72-07-09 AND SL SE 72.3 REQUIRE INSPECTION OF THIS AREA AND BULKHEAD REPLACEMENT IF FOUND CRACKED. SUBMITTER STATED THIS BULKHEAD WAS A REPLACEMENT AND IS THE SECOND ONE INSTALLED ON THIS AIRCRAFT. (X) 1 H 7 1 3O NT 3A13 2001021300001 20010213 00001 SW 2001 2 13 20001018SH005 1 20000822 G 5312 BULKHEAD BELL 206 206B 1181511 SW FUSELAGE CRACKED A HSYA K NONE O OTHER IN INSP/MAINT 1 NM 05 991FE 208B0127 BIL - DISCOVERED RIGHT BULKHEAD AT STA 385.6 CRACKED WHILE PERFORMING OTHER MAINTENANCE. CRACKED APPROXIMATELY 80 PERCE NT THROUGH INBOARD TO OUTBOARD NEAR LOWER ATTACH TO THE LEFT BULKHEAD. REMOVED AND REPLACED THE RIGHT BULKHEAD, PN 2612 052-6, AT STA 385.6 PER THE IPC AND SRM. INITIATED FAA FORM 337. (X) 1 G 7 1 3U H2SW 2001022300018 20010223 00018 CE 2001 2 23 20001018SH006 1 20000821 G 2820 FUEL LINE CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA ENGINE VAPOR LOCK H O OTHER O OTHER IN INSP/MAINT 1 NM 03 948SP 172S8144 L2812651A AFTER 3RD SORTIE OF THE DAY, AIRCRAFT SAT FOR 45 MINUTES BEFORE NEXT FLIGHT. ENGINE START WAS DIFFICULT USING HOT START ING PROCEDURES WITH ENGINE RUNNING RPM WAS INCREASING AND DECREASING 200 RPM AND ENGINE OPERATION WAS ROUGH AND ERRATIC. AN ATTEMPT WAS MADE TO PURGE VAPORS IAW LYC''S PROCEDURE WITH NO EFFECT. WHEN THROTTLE WAS RETURNED TO IDLE, ENGINE Q UIT. MAINTENANCE ATTEMPTED AN ENGINE START APPROX 15 MINUTES LATER AND WITH MIXTURE FULL OPEN AND BOOST PUMP ON, NO FUE L FLOW INDICATED. ENGINE VAPOR LOCKED. RUN-UP NEXT MORNING NORMAL, NO VAPORIZATION PROBLEMS, SUBSEQUENT TEST FLIGHT SA TISFACTORY. MAINT COULD FIND NOTHING DEFECTIVE WHEN ENGINE INSPECTED. (X) 1 H 7 1 3O 3 O NT 3A12 1E10 2000102500171 20001025 00171 SO 2000 10 25 20001018SH007 1 20000914 G 2710 62701125 CONTROL CABLE PIPER PA34 PA34220T 7103420 SO FRAYED B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 9299E 2138 3449043 LEFT AILERON BALANCE CABLE FRAYED AT WING ROOT PULLEY. (X) 1 L 7 2 3O A7SO 2000102500172 20001025 00172 SO 2000 10 25 20001018SH008 1 20000915 G 2700 62701125 CONTROL CABLE PIPER PA34 PA34220T 7103420 SO FRAYED B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 9299E 2138 3449043 REAR TRIM CABLE FRAYED AT REAR DRUM. (X) 1 L 7 2 3O A7SO 2000102500173 20001025 00173 CE 2000 10 25 20001018SH009 2 20000705 G 7322 63338811 CONTROLLER PIPER PA34 PA34220T 7103420 SO CONT O360 TSIO360RB 17025 CE PISTON STUCK B VJ3R O OTHER O OTHER CR CRUISE 1 WP 07 9299E 156 3449043 809256R THE CONTROLLER PISTON STICK IN. A SPLIT IN POWER SETTING IN-FLIGHT AND ON THE GROUND. CONTROLLER REPLACED. (X) 1 L 7 2 3O 3 O A7SO E9CE 2000102500174 20001025 00174 CE 2000 10 25 20001018SH010 2 20000921 G 7322 6493623 CONTROLLER PIPER PA34 PA34220T 7103420 SO CONT O360 TSIO360RB 17025 CE STUCK B VJ3R O OTHER O OTHER CR CRUISE 1 WP 07 9299E 674 3449043 THE CONTROLLER PISTON STICK IN. A SPLIT IN POWER SETTING IN-FLIGHT AND ON THE GROUND. CONTROLLER REPLACED. (X) 1 L 7 2 3O 3 O A7SO E9CE 2000102500175 20001025 00175 CE 2000 10 25 20001018SH011 2 20000510 G 7322 63338811 CONTROLLER PIPER PA34 PA34220T 7103420 SO CONT O360 TSIO360RB 17025 CE PISTON STUCK B VJ3R O OTHER O OTHER CR CRUISE 1 WP 07 9299E 320 3449043 819256R THE CONTROLLER PISTON STICK IN. A SPLIT IN POWER SETTING IN-FLIGHT AND ON THE GROUND. CONTROLLER REPLACED. (X) 1 L 7 2 3O 3 O A7SO E9CE 2000102500176 20001025 00176 SO 2000 10 25 20001018SH012 2 20000915 G 7322 RSA5AD SERVO PIPER PA34 PA34220T 7103420 SO CONT O360 LTSIO360EB 17025 SO FUEL INJECTOR DEFECTIVE B VJ3R O OTHER O OTHER CR CRUISE 1 WP 07 4128X 120 3449112 321749R THROTTLE HARD TO MORE IN-FLIGHT, SERVO REMOVED AND A NEW ONE INSTALLED. OVER FOUR POUNDS TO MOVE CONTROL. (X) 1 L 7 2 3O 3 O A7SO E9CE 2000102500177 20001025 00177 CE 2000 10 25 20001018SH013 2 20000915 G 7322 RSA5AD SERVO PIPER PA34 PA34220T 7103420 SO CONT O360 TSIO360RB 17025 CE FUEL INJECTOR DEFECTIVE B VJ3R O OTHER O OTHER IN INSP/MAINT 1 WP 07 4128X 120 3449112 819255R THROTTLE HARD TO MOVE IN-FLIGHT, SERVO REMOVED AND A NEW ONE INSTALLED. OVER FOUR POUNDS TO MOVE CONTROL. (X) 1 L 7 2 3O 3 O A7SO E9CE 2001020900021 20010209 00021 EU 2001 2 9 20001018SH014 1 20000726 G 6340 IPT20RT1100080G TRANSMITTER BOLKMS 117 BK117B1 5626012 EU MAIN ROTOR FLUCTUATES B R7MR O OTHER J WARNING INDICATION NR NOT REPORTED 1 NM 07 911VU 280 7141 PRESSURE TRANSMITTER UNIT CAUSED PRESSURE GAUGE TO FLUCTUATE. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U H13EU 2001020900022 20010209 00022 EU 2001 2 9 20001018SH015 1 20000727 G 3340 2LA00162500 LIGHT BOLKMS 117 BK117A4 5626017 EU TAIL WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 911BY 512 7127 CLEAR TAIL LIGHT WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U H13EU 2001020900023 20010209 00023 EU 2001 2 9 20001018SH016 1 20000606 G 7931 DK042M0D01 TRANSMITTER BOLKMS 105 BO105CBS 5626008 EU OIL PRESSURE INOPERATIVE B R7MR O OTHER O OTHER NR NOT REPORTED 1 NM 07 911BH 117 685 OIL PRESSURE TRANSMITTER UNIT INOPERATIVE. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U NC H3EU 2001022300019 20010223 00019 SO 2001 2 23 20001018SH017 1 20000828 G 7120 6711957 MOUNT PIPER PA28 PA28R201 7102816 SO ENGINE CRACKED D K NONE O OTHER IN INSP/MAINT 1 NE 01 941NZ 7673 28R7737172 ENGINE MOUNT CRACKED LOWER LEFT SIDE OF CENTER CROSS TUBE. REQUIRED ENGINE REMOVAL. VISUALLY SEEN DURING ANNUAL INSPEC TION. PAINT WAS STRIPPED IN THE CRACKED AREA AND A DYE CHECK WAS DONE TO CONFIRM THE CRACK. (X) 1 L 7 1 3O 2A13 2001030200008 20010302 00008 2001 3 2 20001018SH024 4 20000926 G 6122 20609 LEVER MCAULY GOVERNOR CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 810290 RELEVANT MAGNETIC PARTICLE INDICATION ON LEVER ARM. (X) 2001022300021 20010223 00021 2001 2 23 20001018SH025 4 20000928 G 6122 4030145 GOVERNOR BNORM BN2 BN2 1520202 EU LYC O540 O540* 41532 EA PROPELLER CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 RELEVANT PENETRANT INDICATION ON TOP OF GOVERNOR BODY. RETIRED FROM SERVICE, UNAIRWORTHY. (X) 1 H 7 2 3O 3 O A17EU E295 2001022300022 20010223 00022 GL 2001 2 23 20001018SH026 3 20000921 G 6111 82NC55 BLADE CESSNA 401 401A 207590D CE MCAULY 3AF32C 3AF32C87 GL PROPELLER CORRODED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 401PC 401A0088 783251 PROPELLER BLADE CORRODED. (X) 1 L 7 2 3O A7CE 5 C P22EA 2001022300023 20010223 00023 GL 2001 2 23 20001018SH027 3 20000921 G 6111 82NC55 BLADE CESSNA 401 401A 207590D CE MCAULY 3AF32C 3AF32C87 GL PROPELLER CORRODED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 401PC 401A0088 952511 PROPELLER BLADE CORRODED. (X) 1 L 7 2 3O A7CE 5 C P22EA 2001030100025 20010301 00025 GL 2001 3 1 20001018SH028 3 20000925 G 6111 D7067 COUNTERWEIGHT CESSNA 401 401A 207590D CE MCAULY 3AF32C 3AF32C87 GL PROPELLER CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 401PC 401A0088 952511 RELEVANT MAGNETIC PARTICLE INDICATION. (X) 1 L 7 2 3O A7CE 5 C P22EA 2001020900024 20010209 00024 NE 2001 2 9 20001018SH029 1 20000816 G 6320 643520411102 GEAR SKRSKY SKRSKY S64 S64F NE M/R GEARBOX FAILED B JYDR K NONE O OTHER IN INSP/MAINT 1 NM 09 163AC 3109 699 A6165 64093 1ST STAGE PLANETARY PINION GEAR, PN 6435-20411-102, SN 1524, UNKNOWN TT, FAILED IN MAIN GEARBOX, PN 6435-20500-049, SN A 6-165, LEAVING LARGE FRAGMENT OF FERROUS METAL IN SUMP, SUMP SCREEN. TEARDOWN INSP REVEALED ENTIRE TOOTH FRACTURED AT J UNCTION OF CASE TO CORE. SECONDARY DAMAGE FOUND ON 3 EACH 2ND STAGE PLANETARY PINION GEARS, PN 6435-20057-012, RING GEA R, PN 6435-20165-012, AND 1ST STAGE SUN GEAR, PN 6435-20412-102, ALL OF WHICH WERE BLENDED, RETURNED TO SERVICE. DURING OPERATION, CREW HEARD A LOUD NOISE AND EXPERIENCED A VIBRATION PRIOR TO REGISTERING A CHIP LIGHT. A PREVIOUS MDR WAS S UBMITTED 4-20-00, SAME PN GEAR FRACTURED A GEAR TOOTH AT 697.0 HRS ON DIFFERENT GEARBOX. (X) 2 G 7 2 4U H6EA 2001020100054 20010201 00054 EU 2001 2 1 20001018SH030 1 20000830 G 6730 AC67244 SERVO SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D NE MAIN ROTOR BINDING A HLXA K NONE O OTHER IN INSP/MAINT 1 SW 09 126TV 1792 2944 9447 SERVO CONTROL REMOVED DUE TO CYCLIC BINDING. (X) 1 G 7 1 3U 3 U H9EU E19EU 2001022300020 20010223 00020 CE 2001 2 23 20001018SH031 1 20001015 G 7110 J744436 MOUNT CESSNA 172 172R 2072401 CE COWLING TORN H K NONE O OTHER UK UNKNOWN 1 SW 99 869CP 1388 17280641 CONDITION: COWLING MOUNT TORN. CORRECTIVE ACTION: REPLACED WITH NEW. (X) 1 H 7 1 3O NT 3A12 2001022300024 20010223 00024 SO 2001 2 23 20001019SH001 2 20000908 G 7314 7429322 PUMP BEECH 33 F33A 1151425 CE CONT O520 IO520BB 17032 SO ENGINE DEFECTIVE B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 1569P 673 CE1300 820276R UNABLE TO ADJUST FUEL FLOW TOP END AND IDLE MIXTURE. (X) 1 L 7 1 3O 3 O 3A15 E5CE 2001020900025 20010209 00025 EU 2001 2 9 20001019SH002 1 20000925 G 6220 350A37124420 BOLT SNIAS 350 AS350B1 8680811 EU MAIN ROTOR BROKEN D K NONE O OTHER IN INSP/MAINT 1 NM 02 13HF 980 2267 BROKEN BOLT FOUND ON PRE-FLIGHT INSPECTION. HELICOPTER IS USED FOR MULTIPLE ROLES INCLUDING PERSONNEL TRANSPORT, EXTERN AL LOAD, WATER DROPPING, AND RECONNAISSANCE. CAUSE IS UNKNOWN AT THIS TIME, BUT IS BEING DETERMINED. (X) 1 G 7 1 3U H9EU 2001020900026 20010209 00026 SW 2001 2 9 20001019SH003 1 20000720 G 6310 70061G00DX116 LINE BELL 206 206B 1181511 SW FREEWHEEL UNIT LEAKING H K NONE K FLUID LOSS IN INSP/MAINT 1 SW 15 59617 1517 FOUND SEEPAGE ON POST-FLGIHT INSPECTION, VERY HOT DAY. REPLACED HOSE. (X) 1 G 7 1 3U H2SW 2001020900027 20010209 00027 GL 2001 2 9 20001019SH004 2 20000825 G 7200 ENGINE BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL ENG BAY MAKING METAL H O OTHER J WARNING INDICATION NR NOT REPORTED 1 SW 15 1585W 2286 2516 CAE831404 ENGINE PRODUCED CHIP LIGHTS. REMOVED CHIP DETECTOR, CLEANED, RE-INSTALLED. RAN ENGINE 30 MINUTES AND FOUND MORE CHIPS. REMOVED ENGINE AND SENT FOR REPAIR. (X) 1 G 7 1 3U 3 U H2SW E4CE 2001020900028 20010209 00028 2001 2 9 20001019SH006 4 20000922 G 3421 4021541671 GYRO BOLKMS 117 BK117B1 5626012 EU COCKPIT MISREPAIRED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 13 217MC 7195 GYRO HORIZON WAS RETURNED FROM REPAIR STATION WITH 8130-3 TAG INDICATING ''REPAIRED''. AFTER INSTALLATION AND FUNCTIONA L TEST, THE UNIT WAS DETERMINED TO HAVE SAME SYMPTOMS AS ORIGINAL. THE UNIT SHOWED NO EVIDENCE THAT IT WAS EVER REPAIRE D. NO ''DO NOT BREAK SEAL'' STICKER, ETC. (X) 1 G 7 2 3U H13EU 2001022300026 20010223 00026 SO 2001 2 23 20001019SH007 2 20000901 G 8550 LW13388 SEAL PIPER PA32 PA32RT300 7103215 SO LYC 0540 IO540K1G5D 41532 SO OIL FILTER FAILED H O OTHER M Y OVER TEMP ENGINE STOPPAGE NR NOT REPORTED 1 CE 05 28WC 373 32RT7885055 L1574648A SEAL SOFTENED, SWELLED, RUPTURED. NIGHT, PART 135 FLIGHT LOST OIL, ENGINE SEIZED. SEAL MATERIAL NOT OIL PROOF. SUBMIT TER SUGGESTED RETURNING TO ORIGINAL MATERIAL. (X) 1 L 7 1 3O 3 O A3SO 1E4 2001022300028 20010223 00028 CE 2001 2 23 20001019SH009 1 20000922 G 3230 50410011 BOLT CESSNA 402 402B 207590P CE LT MLG BELLCRANK SHEARED E K NONE O OTHER NR NOT REPORTED 1 SW 05 3131K 402B0248 BOLT, P/N NAS464P4, SHEARED CAUSING SIDE LOAD ON THE BELLCRANK BREAKING THE ATTACH POINT AT THE GEAR LIGHT SAFETY SWITCH . (X) 1 L 7 2 3O A7CE 2001022300029 20010223 00029 CE 2001 2 23 20001019SH011 1 20001002 G 3250 50420101 BELLCRANK CESSNA 401 401 207590C CE NLG STEERING CRACKED E K NONE O OTHER IN INSP/MAINT 1 SW 05 3260Q 9000 4010060 DURING 100-HOUR INSPECTION, FOUND CRACK IN THE RADIUS OF THE CENTER ATTACH POINT AT BELLCRANK. CAUSE UNKNOWN. (X) 1 L 7 2 3O A7CE 2001022300030 20010223 00030 GL 2001 2 23 20001019SH012 3 20000927 G 6110 PROPELLER CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA MCAULY 1A170 1A170E GL PROPELLER CRACKED B W59R K NONE O OTHER IN INSP/MAINT 1 WP 07 325SP 944 172S8251 TF047 PROPELLER SUBMITTED FOR SB 233A COMPLIANCE. PROPELLER FOUND CRACKED AS INDICATED IN THE SERVICE BULLETIN, IN THE PILOT BORE, FACE SIDE OF THE PROPELLER. PROPELLER IS TO BE RETURNED TO MANUFACTURER FOR DISPOSITION. (X) 1 H 7 1 3O 3 O NT 3A12 1E10 5 N P857 2001022300031 20010223 00031 EA 2001 2 23 20001019SH013 2 20000711 G 7414 ES10349276 CONDENSER BENDIX CESSNA 177 177B 2073708 CE LYC O360 O360A1F6 41514 EA MAGNETO INOPERATIVE G A UNSCHED LANDING Y ENGINE STOPPAGE NR NOT REPORTED 1 SO 13 34194 1 17701692 L1633536A THE AIRCRAFT MADE AN EMERGENCY LANDING IN A FIELD AFTER A LOSS OF ENGINE POWER. INSPECTION BY A MECHANIC REVEALED THE P OINTS WERE BURNED AND THE CONDENSER WERE PART OF A NEWLY INSTALLED FACTORY REMANUFACTURED MAGNETO. THE POINTS AND CONDE NSER WERE REPLACED, AND THE MAGNETO REINSTALLED AND RETURNED TO ENGINE. ENGINE PERFORMED SATISFACTORILY. (X) 1 H 7 1 3O 3 O A13CE E286 2001022300032 20010223 00032 SO 2001 2 23 20001019SH014 1 20000831 G 3211 CASTING LKHEED 12A 12A 5261402 SO RT WW FAILED G K NONE O OTHER LD LANDING 1 NM 09 33RA 1239 RIGHT FLANGE OR GEAR DRIVE CASTING FAILED UNDER LOAD DURING LANDING. THIS CAUSED THE JACK SCREW TO BEND ALLOWING THE RI GHT MAIN LANDING GEAR TO COLLAPSE. (X) 1 L 7 2 3R TC616 2001022300033 20010223 00033 SO 2001 2 23 20001019SH015 1 20001011 G 2722 480735 ROLL PIN PIPER PA31 PA31350 7103110 SO ACTUATOR BACKED OUT I WVBA K NONE F FLT CONT AFFECTED CR CRUISE 1 AL 01 42WP 318252038 PILOT RETURNED FROM FLIGHT, REPORTED RUDDER TRIM INOPERABLE. FOUND ONE OF THE TWO ROLL PINS THAT SECURE THE ROD END THA T CONNECTS THE ACTUATOR SCREW TO THE TRIM TAB PUSH/PULL TUBE HAD MIGRATED ALMOST COMPLETELY OUT, THE OTHER ROLL PIN WAS MISSING. THIS CAUSED ROD END TO DISCONNECT FROM ACTUATOR SCREW RENDERING THE TRIM INOPERABLE. TWO NEW PINS INSTALLED, SAFTIED WITH .032 INCH WIRE. REF: AC65-9A, PG 145; AC43.13-1B, PG 7-17 (7-104). (X) 1 L 7 2 3O A20SO 2001022300034 20010223 00034 CE 2001 2 23 20001019SH016 2 20000908 G 8530 649264 TUBE PIPER PA34 PA34220T 7103420 SO CONT O360 TSIO360RB 17025 CE INTAKE CRACKED B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 4142N 1241 3449128 322265L INSPECTION OF INTAKE FOUND NR 2 INTAKE TUBE CRACKED AT THE FLANGE. (X) 1 L 7 2 3O 3 O A7SO E9CE 2001022300035 20010223 00035 SO 2001 2 23 20001019SH017 2 20000921 G 7322 RSA5AD SERVO PIPER PA34 PA34220T 7103420 SO CONT O360 LTSIO360RB SO FUEL INJECTOR MALFUNCTIONED B VJ3R K NONE O OTHER CR CRUISE 1 WP 07 4128X 3449112 321749R IN-FLIGHT, WHEN MIXTURE WAS LEANED TO CRUISE SETTING AT ABOUT 9 GALLON/HOUR, THE MIXTURE WENT UP TO 3 GALLONS PER HOUR. SERVO REMOVED AND A NEW ONE INSTALLED IAW PIPER MANUAL. (X) 1 L 7 2 3O 3 O A7SO E9CE 2001022300036 20010223 00036 SO 2001 2 23 20001019SH018 1 20000918 G 2710 62701127 CONTROL CABLE PIPER PA34 PA34220T 7103420 SO AILERON FRAYED B XC4R K NONE O OTHER IN INSP/MAINT 1 WP 07 4177R 2345 3449046 LEFT AILERON BALANCE CABLE FRAYED. (X) 1 L 7 2 3O A7SO 2001022300037 20010223 00037 SO 2001 2 23 20001019SH019 1 20000918 G 2710 62701123 CONTROL CABLE PIPER PA28 PA28181 7102807 SO AILERON FRAYED B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 4175V 2340 2843126 LEFT HAND AILERON BALANCE CABLE FRAYED, LOCATED UNDER THE REAR SEATS. (X) 1 L 7 1 3O 2A13 2001022300038 20010223 00038 SO 2001 2 23 20001019SH020 1 20000918 G 2740 62701113 CONTROL CABLE PIPER PA28 PA28181 7102807 SO STABILATOR FRAYED B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 4134T 1540 2843208 FORWARD STABILATOR CABLE FRAYED. (X) 1 L 7 1 3O 2A13 2001022300039 20010223 00039 SO 2001 2 23 20001019SH021 2 20000908 G 7322 6493623 CONTROLLER PIPER PA34 PA34220T 7103420 SO CONT O360 LTSIO360RB SO FUAL CONTROL STUCK B VJ3R K NONE O OTHER CR CRUISE 1 WP 07 4142N 1241 3449128 322021R THE CONTROLLER PISTON STICK IN. A SPLIT IN POWER SETTING IN-FLIGHT AND ON THE GROUND. CONTROLLER REPLACED. (X) 1 L 7 2 3O 3 O A7SO E9CE 2001022300040 20010223 00040 CE 2001 2 23 20001019SH022 1 20000917 G 3230 NAS5055J BEARING BEECH 95 95B55 1152729 CE LT MLG SEIZED G K NONE O OTHER AP APPROACH 1 EA 21 4464S TC1878 INCIDENT INVESTIGATION AFTER LEFT MAIN GEAR FAILED TO EXTEND (BOTH NORMAL AND EMERGENCY), FOUND UPLOCK ROLLER BEARING SE IZED. WOULD NOT ROTATE. AD 72-22-01 IS NOT APPLICABLE PER SERIAL NUMBER OF AIRCRAFT. THE UPLOCK ROLLER CLEARANCE BETW EEN BEARING (NAS505-5J) AND UPLOCK BLOCK (35-815077-4) WAS FOUND TO BE INSUFFICIENT PER MM SPEC''S. THE (35-815156-4) I CE BOOT WAS FOUND TORN AND WEDGED BETWEEN THE WING SHIM AND UPLOCK ASSY WITH THE GEAR RETRACTED. LAST ANNUAL INSPECTION COMPLETED 11/99. SUBMITTER RECOMMENDED TO CLOSELY FOLLOW MANUFACTURER''S INSPECTION GUIDE TO ENSURE PROPER GEAR RIGGIN G AND LUBRICATION. (X) 1 L 7 2 3O RT 3A16 2001022300041 20010223 00041 CE 2001 2 23 20001019SH023 1 20001004 G 2720 NUT CESSNA 172 172S 2072439 CE RUDDER PEDAL MISINSTALLED H K NONE O OTHER IN INSP/MAINT 1 NM 09 571SP 195 172S8496 DURING A 100-HOUR INSPECTION, THE COPILOT''S LEFT PEDAL LOWER BOLT AND NUT WERE FOUND LOOSE. THE NUT WAS STILL IN NEW C ONDITION AND HAD NEVER BEEN PROPERLY TORQUED. THE PLASTIC SELF-LOCKING FEATURE OF THE NUT HAD NEVER BEEN ENGAGED AND NO TORQUE SEAL HAD BEEN APPLIED. (X) 1 H 7 1 3O NT 3A12 2001022300044 20010223 00044 EA 2001 2 23 20001019SH027 2 20000929 G 8550 LW13388 GASKET BEECH 76 76 1153005 CE LYC O360 LO360A1G6 41514 EA OIL FILTER LEAKING B BF8S K NONE K FLUID LOSS IN INSP/MAINT 1 WP 07 66340 1707 ME241 L29471A DURING ROUTINE MAINTENANCE, FOUND OIL FILTER CONVERTER GASKET LEAKING. AD 2000-18-53 DID NOT APPLY DUE TO INSTALLATION DATE OF GASKET (12-18-97 OVERHAUL DATE). GASKET REPLACED WITH CHAMPION GASKET PN CH48211. RUN AND LEAK CHECK GOOD. OL D GASKET DID NOT APPEAR TO HAVE EXTRUDED. (X) 1 L 7 2 3O 3 O A29CE 1E10 2001022300045 20010223 00045 EA 2001 2 23 20001019SH028 2 20000825 G 8550 PLUG CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA ENGINE SUMP MISSING D O OTHER E Y VIBRATION/BUFFET ENGINE STOPPAGE CR CRUISE 1 SW 15 82149 3953 557 17267692 L132076 AIRCRAFT WAS FLYING FROM TULSA/SILOAM SPRINGS, 8 MILES FROM SILOAM SPRINGS AIRPORT, PILOT REPORTED THE ENGINE OIL PRESSU RE WAS FLUCTUATING FROM ZERO TO 60 PSI. ENGINE THEN STARTED TO VIBRATE SEVERELY BEFORE ENGINE COMPLETELY STOPPED. UPON INSPECTION OF AIRCRAFT, FOUND THE OIL QUICK DRAIN MISSING WHICH OBVIOUSLY CAUSED ENGINE TO LOSE OIL PRESSURE. SUBMITTE R STATED QUICK DRAIN INSTALLED DID NOT HAVE A PROVISION FOR SAFETY WIRE. (X) 1 H 7 1 3O 3 O NT 3A12 E274 2001022300046 20010223 00046 EA 2001 2 23 20001019SH029 2 20000928 G 7230 3013340 CASE BEECH 99 B99 1154004 CE PWA PT6 PT6A28 EA LEFT ENGINE CRACKED B TIMA K NONE O OTHER IN INSP/MAINT 1 NM 07 899CA 34511 U104 DURING PROPELLER CHANGE ON LEFT ENGINE, A SERIES OF CRACKS WERE FOUND ON THE INBOARD EXHAUST FLANGE. THE FLANGE IS A PA RT OF THE POWER SECTION, SO FIELD REPAIR WAS NOT POSSIBLE. THE AFFECTED POWER SECTION WAS REPLACED WITH A SERVICEABLE P OWER SECTION. A POSSIBLE CAUSE FOR THE CRACKED FLANGE MAY HAVE BEEN THE RESULT OF OVERTORQUING THE HARDWARE ATTACHING T HE EXHAUST STACKS TO THE FLANGE. (X) 1 L 7 2 3T 4 T A14CE E4EA 2001022300047 20010223 00047 CE 2001 2 23 20001019SH030 2 20000921 G 7322 RSA5AD2 SERVO PIPER PA34 PA34220T 7103420 SO CONT O360 TSIO360RB 17025 CE FUEL INJECTION FAULTY B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 9299E 130 3449043 819507R THROTTLE HARD TO MOVE, CHECKED FORCE TO MOVE THROTTLE ON THE GROUND AND FOUND OVER SPECS. SERVO REMOVED AND A NEW ONE I NSTALLED IAW PIPER MANUAL. (X) 1 L 7 2 3O 3 O A7SO E9CE 2001020900029 20010209 00029 SW 2001 2 9 20001019SH031 1 20000710 G 6220 204011110005 BEARING BELL 212 212 1181420 SW M/R HUB FAILED H K NONE O OTHER IN INSP/MAINT 1 WP 07 911KW 1929 A60 30592 DURING A POST-FLIGHT INSPECTION, DARK BLACK GREASE WAS FOUND ON THE M/R TRUNNION. REMOVED AND DISASSEMBLED M/R TRUNNION . ONE TRUNNION BEARING HAD TOTALLY FAILED. INNER AND OUTER RACES WERE BROKEN. (X) 1 G 7 1 4U H4SW 2001020900030 20010209 00030 SW 2001 2 9 20001019SH032 1 20000928 G 6220 2040111105 BEARING BELL BELL 212 212 1181420 SW M/R TRUNNION FAILED H K NONE O OTHER IN INSP/MAINT 1 WP 07 911VR 1842 ADA01108 30998 DURING MAINTENANCE CHECKS, WHITE M/R BLADE TRUNNION BEARING GREASE WAS FOUND TO BE DARKER THAN RED BLADE. GRAY/RED IN C OLOR. REMOVED AND REPLACED M/R TRUNNION BEARINGS WITH NEW BEARINGS. WHILE BLADE BEARING SHOWS SIGNS OF ADVANCED BRINNE LLING. SUBMITTER STATED THIS IS THE SECOND OCCURRENCE THIS YEAR ON FLEET, PLUS ONE OTHER FROM ANOTHER OPERATOR. REF: OPER CNTRL NR 20001019SH031. (X) 1 G 7 1 4U H4SW 2001022300048 20010223 00048 SO 2001 2 23 20001023SH001 1 20000828 G 2913 HYC5005 MOTOR PIPER PA28 PA28RT201 7102818 SO POWERPACK FAILED D K NONE O OTHER IN INSP/MAINT 1 NM 10 366LC 208 28R8218005 MOTOR QUIT. 1 L 7 1 3O 2A13 2001022300049 20010223 00049 CE 2001 2 23 20001023SH002 2 20000908 G 8530 649264 TUBE PIPER PA34 PA34220T 7103420 SO CONT O360 TSIO360RB 17025 CE NR 2 INTAKE CRACKED B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 4142N 1282 3449128 322265L INSPECTION OF INTAKE FOUND NR 2 INTAKE TUBE CRACKED AT THE FLANGE. (X) 1 L 7 2 3O 3 O A7SO E9CE 2000102400278 20001024 00278 GL 2000 10 24 20001023SH004 3 20000921 G 6110 B3490 LINK MCAULY CESSNA 402 402CESSNA 207590K CE MCAULY 3AF32C 3AF32C87 GL BLADE & PCR DAMAGED B O OTHER O OTHER IN INSP/MAINT 1 SO 11 803995 DURING PREFLIGHT INSPECTION, OPERATOR FOUND BLADE TO BE LOOSE. THE PROPELLER WAS REMOVED FROM AIRCRAFT AND SENT FOR REP AIR. DURING DISASSEMBLY, THE BLADE LINK SNAP RING WAS NOT INTACTED. THE PROPELLER RECEIVED A COMPLETE OVERHAUL WITH RE PLACEMENT OF ALL UNAIRWORTHY PARTS. (X) 1 L 7 2 3O A7CE 5 C P22EA 2001011101194 20010111 01194 NE 2001 1 11 20001024SH001 2 20000829 G 7320 4050582G02 VALVE SKRSKY S61 S61N 8142104 NE GE CT58 CT581402 30011 NE NR 2 ENGINE BROKEN A ERAA B A E EMER. DESCENT UNSCHED LANDING ENGINE SHUTDOWN K J FLUID LOSS WARNING INDICATION DE DESCENT 1 AL 03 563EH 12474 89 61808 295246 DEPARTED MC822 EN ROUTE TO VENICE. DURING LETDOWN TO VENICE, A SLIGHT FUEL ODOR DETECTED. AS POWER INCREASED TO LEVEL AT 500 FEET, NR 2 ENGINE CAME OFF-LINE. N1 NOTED AT APPROX 60 PERCENT, TORQUE AT 20-30 PERCENT, NF HAD SPLIT FROM NR 1 NF. A STRONG FUEL ODOR NOTED. NR 2 ENGINE SECURED PER EMERGENCY ACTION CHECKLIST. A RUNNING LANDING PERFORMED, ACFT L ANDED WITH NO DAMAGE. SUBSEQUENT PRELIMINARY INSP REVEALED FLOW DIVIDER FAILED CAUSING LOSS OF FUEL TO ENGINE. RECOMME NDATION TO PRECLUDE RECURRENCE: FOLLOW UP 9-19-00. FLOW DIVIDERS ON ALL ENGINES WERE REMOVED AND THE TEMP VALVES NDT I NSPECTED AND RE-ASSEMBLED. NO DEFECTS NOTED, SERVICEABLE UNITS REINSTALLED. (X) 2 G 7 2 4U 4 U 1H15 1E3 2001020900045 20010209 00045 SW 2001 2 9 20001024SH002 1 20000816 G 6510 407340340101 DISC PACK BELL BELL 407 407 SW TAIL ROTOR CRACKED A ALGA K NONE O OTHER IN INSP/MAINT 1 SW 03 417AL 184 A823 53054 DURING 25-HOUR AD INSPECTION, FOUND FORWARD SEGMENT CRACKED ACROSS ONE SPAN. (X) 1 G 7 1 3U O H2SW 2001022600003 20010226 00003 NE 2001 2 26 20001024SH004 2 20000927 G 7230 1711M20P08 SEAL GE GE90 GE9090B NE HP INTERSTAGE CRACKED B QEMY K NONE O OTHER IN INSP/MAINT 1 EA 35 9KAOA 900211 SEAL EXHIBTS TWO SHORT CRACKS, 0.150 INCH LENGTH EACH, IN THE FORWARD ARM OUTSIDE DIAMETER AT THE STAGE 1 BLADE INTERFAC E. THIS PART HAD ACCUMULATED 954 CSN. (X) 4 F E00049EN 2001022300050 20010223 00050 CE 2001 2 23 20001024SH005 1 20000920 G 2810 509215873 GASKET BEECH 200 B200 1152922 CE FUEL GASKET SPLIT H K NONE K FLUID LOSS IN INSP/MAINT 1 SO 14 529 BB1194 GASKET SPLITTING AND FUEL LEAKING FROM NACELLE AND AUXILIARY TANKS INTO ENGINE EXHAUST PATH. AIRCRAFT N NR YV0988CP. (X) 1 L 7 2 4T A24CE 2001022600004 20010226 00004 CE 2001 2 26 20001024SH006 1 20000920 G 2810 509215875 GASKET BEECH 200 B200 1152922 CE FUEL GASKET SPLIT H K NONE K FLUID LOSS IN INSP/MAINT 1 SO 14 529 BB1194 GASKET SPLITTING AND FUEL LEAKING FROM NACELLE AND AUXILIARY TANKS INTO ENGINE EXHAUST PATH. AIRCRAFT N NR YV-988CP. ( X) 1 L 7 2 4T A24CE 2001030200009 20010302 00009 2001 3 2 20001024SH012 4 20001002 G 2562 P3030029010 ELT BFGOODRICH LIFE RAFT FAILED B VW3R K NONE L NO TEST IN INSP/MAINT 1 SO 19 10R437 ELT FAILED, UNABLE TO TRANSMIT SIGNALS. ELT PACKED IAW OEM MANUAL INSTRUCTIONS. ELT MODEL SRB-10. (X) 2001030200010 20010302 00010 2001 3 2 20001024SH013 4 20000902 G 2562 P3030029010 ELT BFGOODRICH LIFE RAFT FAILED B VW3R K NONE L NO TEST IN INSP/MAINT 1 WP 09 10R427 ELT FAILED, UNABLE TO TRANSMIT SIGNALS. ELT PACKED IAW OEM MANUAL INSTRUCTIONS. ELT MODEL SRB-10. (X) 2001030200011 20010302 00011 2001 3 2 20001024SH014 4 20000829 G 2562 P3030029010 ELT BFGOODRICH LIFE RAFT FAILED B VW3R K NONE L NO TEST IN INSP/MAINT 1 WP 09 10R215 ELT FAILED, UNABLE TO TRANSMIT SIGNALS. ELT PACKED IAW OEM MANUAL INSTRUCTIONS. ELT MODEL SRB-10. (X) 2001030200012 20010302 00012 2001 3 2 20001024SH015 4 20000608 G 2562 P3030029010 ELT BFGOODRICH LIFE RAFT FAILED B VW3R K NONE L NO TEST IN INSP/MAINT 1 WP 09 10R210 ELT FAILED, UNABLE TO TRANSMIT SIGNALS. ELT PACKED IAW OEM MANUAL INSTRUCTIONS. ELT MODEL SRB-10. (X) 2001030200020 20010302 00020 2001 3 2 20001024SH023 4 20001018 G 2562 SRB10 ELT BFGOODRICH LIFE RAFT FAILED B VW3R K NONE L NO TEST IN INSP/MAINT 1 WP 09 10R214 DURING THE FUNCTIONAL TESTING OF THE ELT, IT DID NOT TRANSMIT ANY SIGNALS. THE BATTERY WAS REPLACED WITH A BATTERY THAT TESTED OKAY ON OTHER ELT''S, BUT THE ELT WOULD STILL NOT TRANSMIT. (X) 2001030200021 20010302 00021 2001 3 2 20001024SH024 4 20001015 G 2562 SRB10 ELT BFGOODRICH LIFE RAFT FAILED B VW3R K NONE L NO TEST IN INSP/MAINT 1 WP 09 10R211 DURING THE FUNCTIONAL TESTING OF THE ELT, IT DID NOT TRANSMIT ANY SIGNALS. THE BATTERY WAS REPLACED WITH A BATTERY THAT TESTED OKAY ON OTHER ELT''S, BUT THE ELT WOULD STILL NOT TRANSMIT. (X) 2001011101195 20010111 01195 CE 2001 1 11 20001025SH001 1 20001024 G 2721 556544060 ROD CESSNA 500 550 2076604 CE RUDDER TRIM SPLIT B O OTHER O OTHER NR NOT REPORTED 1 EA 23 71GA 5500444 AIRCRAFT STRIPPED FOR PAINT. AFTER P/N 5565440-60 RUDDER TRIM ROD (LOWER) PAINTED, BUBBLES APPEARED UNDER PAINT, PAINT CRACKED, SPLIT ABOUT 2 INCHES LONG IN ROD, VISUALLY SEEN. (X) 1 L 7 2 4F A22CE 2000103100114 20001031 00114 CE 2000 10 31 20001025SH002 1 20000906 G 2810 509215873 GASKET BEECH 90 F90 1152909 CE FUEL GASKET SPLIT H K NONE K FLUID LOSS IN INSP/MAINT 1 SO 14 333WT LA91 GASKET SPLITTING AND FUEL LEAKING FROM NACELLE INTO ENGINE EXHAUST PATH. (X) 1 L 7 2 4T A31CE 2001030100026 20010301 00026 EU 2001 3 1 20001025SH003 1 20000901 G 6710 1174120101 JACKSHAFT BOLKMS 117 BK117A1 5626010 EU M/R CONTROLS CORRODED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 117LF 7928 7013 DURING INSPECTION, FOUND MASSIVE AMOUNTS OF CORROSION INSIDE CYCLIC JACKSHAFT. MANUFACTURER ALLOWS .4MM. IT APPEARS LI TTLE OR NO PAINT TREATMENT ON INTERIOR OF STEEL TUBE. THE TUBE HAS CASTINGS ON EACH END ANGLED UP AT 45 DEGREES WHICH I NCREASES CHANCE OF GETTING FLUIDS INSIDE. THERE ARE NO PROVISIONS FOR DRAINAGE. SUBMITTER SUGGESTED MANUFACTURER TREAT INTERIOR AND PROVIDE DRAINAGE. (X) 1 G 7 2 3U H13EU 2000103100113 20001031 00113 CE 2000 10 31 20001025SH004 1 20000825 G 2810 509215873 GASKET BEECH 90 C90 1152913 CE FUEL SPLIT H K NONE K FLUID LOSS IN INSP/MAINT 1 SO 14 34CE LJ932 GASKET SPLITTING AND FUEL LEAKING FROM NACELLE INTO ENGINE EXHAUST PATH. (X) 1 L 7 2 3T 3A20 2000103100139 20001031 00139 SO 2000 10 31 20001025SH005 1 20001018 G 5280 4752932 HINGE PIPER PA31 PA31350 7103110 SO LT MAIN GEAR BROKEN A WVBA K NONE O OTHER IN INSP/MAINT 1 AL 01 300ED 317852008 PILOT REPORTED GEAR DOOR BROKEN. DISCOVERED FORWARD HINGE ON LEFT MAIN GEAR DOOR BROKEN IN HALF AND GEAR DOOR BENT FROM CONTACT WITH MAIN GEAR WHEEL. A NEW DOOR INSTALLED AND AIRCRAFT RETURNED TO SERVICE. SUBMITTER RECOMMENDED THESE HING ES BE STRIPPED OF PAINT PRIOR TO INSTALLATION TO FACILITATE PROPER INSPECTION OF THE LARGE INNER RADIUS OF THE HINGE FOR CRACKING. NOTE: BROKEN HINGE PN 47529-32 IS CORRECT. PART IAW AD 80-2605. (X) 1 L 7 2 3O A20SO 2000103100025 20001031 00025 CE 2000 10 31 20001025SH006 1 20001005 G 3230 50450101 TORQUE TUBE CESSNA 401 401 207590C CE RT WW SEPARATED C K NONE O OTHER IN INSP/MAINT 1 SW 05 3260Q 4010060 PUSH/PULL ROD PN 5045213-2, PULLED OUT OF TORQUE TUBE ASSY, PN 50450104. CAUSE UNKNOWN. (X) 1 L 7 2 3O A7CE 2000103100026 20001031 00026 EA 2000 10 31 20001025SH007 2 20000921 G 8530 77569 SEAL PIPER PA28 PA28R201 7102816 SO LYC O360 IO360C1C6 41514 EA INTAKE MANIFOLD MISSING D K NONE R PARTIAL RPM/PWR LOSS CR CRUISE 1 NE 05 47985 44 28R7837021 RL2171851A AIRCRAFT OWNER, PILOT, COMPLAINED OF PROGRESSIVELY WORSENING BAD IDLE, ABNORMALLY HIGH MANIFOLD PRESSURE AT REDUCED POWE R SETTINGS AND AFTERFIRING ON THROTTLE REDUCTION AND HIGH EGT READY ON NR 3 CYLINDER. AFTER CHECKING COMPRESSION AND FU EL NOZZLES, THE COWL WAS REMOVED, NR 3 AND NR 1 INTAKE SEALS WERE FOUND PARTIALLY INGESTED. NO PIECES HAD SEPARATED AND WENT INTO THE MANIFOLD. THE SEALS AND GASKETS ON THE FLANGES WERE REPLACED AND THE ENGINE RAN-UP NORMALLY. (X) 1 L 7 1 3O 3 O 2A13 1E10 2000103100102 20001031 00102 CE 2000 10 31 20001025SH008 1 20000901 G 2916 511700712 SIGHT GAUGE CESSNA 402 402C 207590R CE HYDRAULIC TANK FAILED D O OTHER K FLUID LOSS CR CRUISE 1 SW 07 402GR 402C0035 HOLE IN SIGHT GAUGE (TUBE) APPEARS TO BE CAUSED BY HEAT, LOST FLUID. NOSE GEAR DID NOT EXTEND. LANDING WAS MADE WITH N OSE GEAR UP. (X) 1 L 7 2 3O A7CE 2000103100030 20001031 00030 CE 2000 10 31 20001025SH009 1 20001009 G 2810 509215873 GASKET BEECH 90 C90A 1152911 CE SPLIT H K NONE K FLUID LOSS IN INSP/MAINT 1 SO 14 488XJ 753 LJ1527 GASKET SPLITTING AND FUEL LEAKING FROM NACELLE INTO ENGINE EXHAUST PATH. (X) 1 L 7 2 3T RT 3A20 2000103100031 20001031 00031 SO 2000 10 31 20001025SH010 1 20000929 G 2750 8776541 CONTROL CABLE PIPER PA34 PA34220T 7103420 SO FLAP SELECTOR FRAYED B K NONE O OTHER IN INSP/MAINT 1 WP 07 4142N 1392 3449128 FLAP SELECTOR CABLE FRAYED WHERE THE CABLE GOES AROUND THE PULLEYS AT THE FLAP SELECTOR. (X) 1 L 7 2 3O A7SO 2000103100032 20001031 00032 SO 2000 10 31 20001025SH011 1 20000929 G 2710 62701127 CONTROL CABLE PIPER PA34 PA34220T 7103420 SO FRAYED B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 4142N 1392 3449128 RIGHT AILERON CABLE FRAYED. (X) 1 L 7 2 3O A7SO 2000103100033 20001031 00033 SO 2000 10 31 20001025SH012 1 20001003 G 2740 62701104 CONTROL CABLE PIPER PA28 PA28181 7102807 SO STAB TRIM FRAYED B K NONE O OTHER IN INSP/MAINT 1 WP 07 4141U 2440 2843125 TRIM CABLE FRAYED (FORWARD). (X) 1 L 7 1 3O 2A13 2000103100034 20001031 00034 SO 2000 10 31 20001025SH013 1 20001003 G 2740 62701104 CONTROL CABLE PIPER PA28 PA28181 7102807 SO STAB RIM FRAYED B K NONE O OTHER IN INSP/MAINT 1 WP 07 4141U 2440 2843125 TRIM CABLE FRAYED (FORWARD). (X) 1 L 7 1 3O 2A13 2000103100035 20001031 00035 SO 2000 10 31 20001025SH014 1 20000929 G 2750 8776541 CONTROL CABLE PIPER PA34 PA34220T 7103420 SO TE FLAPS FRAYED B K NONE O OTHER IN INSP/MAINT 1 WP 07 4128X 1445 3449112 FLAP SELECTOR CABLE FRAYED WHERE THE CABLE GOES AROUND THE PULLEYS AT THE FLAP SELECTOR. (X) 1 L 7 2 3O A7SO 2000103100024 20001031 00024 SO 2000 10 31 20001025SH015 1 20001003 G 2710 62701125 CONTROL CABLE PIPER PA34 PA34220T 7103420 SO AILERON FRAYED B K NONE O OTHER IN INSP/MAINT 1 WP 07 4128X 1447 3449112 AILERON CONTROL CABLE FRAYED. (X) 1 L 7 2 3O A7SO 2001020900048 20010209 00048 SW 2001 2 9 20001025SH016 1 20000905 G 6510 407340340101 DISC PACK BELL BELL 407 407 SW TAIL ROTOR CRACKED A ALGA K NONE O OTHER IN INSP/MAINT 1 SW 03 577AL 170 A657 53247 DURING 25-HOUR AD INSPECTION, FOUND FORWARD SEGMENT CRACKED ACROSS THE SPAN. (X) 1 G 7 1 3U O H2SW 2001022300051 20010223 00051 CE 2001 2 23 20001025SH019 1 20000909 G 2810 509215873 GASKET BEECH 200 B200 1152922 CE FUEL GASKET SPLIT B VG4R K NONE K FLUID LOSS IN INSP/MAINT 1 SO 35 523GM BB1598 GASKET SPLITTING AND FUEL LEAKING FROM NACELLE AND AUXILIARY TANKS INTO ENGINE EXHAUST PATH. (X) 1 L 7 2 4T A24CE 2001022600005 20010226 00005 SO 2001 2 26 20001025SH020 1 20001013 G 3222 6332906 FORK PIPER PA28 PA28140 7102802 SO NLG CORRODED D K NONE O OTHER IN INSP/MAINT 1 NM 01 5926U 5848 2826739 DURING ANNUAL INSPECTION, DISCOVERED EXFOLIATION CORROSION ON INNER SURFACE OF FORK. AREA OF CORROSION WAS .50 INCH WID E, 3.50 INCHES LONG, AND .10 INCH KEEP. STARTING FROM UPPER ANCHOR NUT ON LT SIDE AND EXTENDING UPWARD AROUND UPPER/INN ER CURVE. REPLACED FORK ASSEMBLY. FORK IS ALUMINUM AND ANCHOR NUT IS STEEL, POSSIBLE DISSIMILAR METAL CORROSION IN ADD ITION TO EXFOLIATION/INTERGRANULAR. (X) 1 L 7 1 3O 2A13 2001022600006 20010226 00006 CE 2001 2 26 20001025SH021 1 20001025 G 2810 LINER RAYTHN BEECH 35 J35 1151522 CE FUEL BLADDER CORRODED D K NONE K FLUID LOSS IN INSP/MAINT 1 WP 07 8233D 6254 D5335 REMOVED BOTH MAIN FUEL BLADDERS DUE TO LEAKAGE. FOUND CORROSION UNDER FUEL BLADDERS. ATTEMPTED TO CLEAN CORROSION USIN G ACID ETCHING, LT BAY LINER HAD EXTENSIVE PITTING AND BLISTERING WHILE WORKING CORROSION WITH ABRASIVE WHEEL. FOUND CO RROSION HAD EATEN THROUGH LINER IN ONE SPOT. TANKS APPEAR TO BE ORIGINALS, BOTH HAD 1957 DATES OF MFG STAMPED ON THEM. WATER APPEARED TO HAVE ENTERED AROUND MAIN FUEL CAP ACCESS PLATE THEN COLLECTED BETWEEN BLADDER AND BAY LINER. AFT WAL L OF MAIN FUEL BAY IS THE WING SPAR. SUBMITTER RECOMMENDED SEALING PANEL WITH SEALING COMPOUND ON INSTALLATION, REMOVIN G BLADDERS AND INSPECTING BAY IF TANKS HAVE NOT BEEN REPLACED. (X) 1 L 7 1 3O 3A15 2001020900052 20010209 00052 SW 2001 2 9 20001026SH001 1 20000602 G 6320 6893673 GEAR ALLSN C47B BELL 407 407 SW ALLSN 250C 250C47B GL GEARBOX BROKEN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 687AL 3100 2958 CAG47017 53366 CAE847018 CHIP LIGHT WAS DETECTED ON AIRCRAFT. CHIP DETECTORS WERE PULLED AND INSPECTED. LARGE PIECE OF GEAR TOOTH WAS FOUND ON PLUG. LARGE PIECE OF GEAR TOOTH BROKE OFF DURING FLIGHT. CAUSE FOR BROKEN GEAR TOOTH WAS DUE TO EXCESSIVE GALLING EXTE NDING UP TO FORWARD END OF SMALL GEAR TEETH. (X) 1 G 7 1 3U 3 U O H2SW E1GL 2001020200063 20010202 00063 SW 2001 2 2 20001026SH002 1 20000824 G 6510 407340340101 DISC PACK BELL 407 407 SW TAIL ROTOR CRACKED A ALGA K NONE O OTHER IN INSP/MAINT 1 SW 03 697AL 534 A1778 53374 DURING 25-HOUR AD INSPECTION, TIME SINCE LAST INSPECTION IS 16.6 HOURS. FORWARD SEGMENT OF THE DISC PACK IS CRACKED ACR OSS THE SPAN. (X) 1 G 7 1 3U O H2SW 2000103100179 20001031 00179 CE 2000 10 31 20001026SH003 1 20000926 G 8000 99103971 RELAY CESSNA 402 402C 207590R CE LEFT STAB WING FAILED D O OTHER O OTHER IN INSP/MAINT 1 NE 01 770CA 402C0432 WHEN AIRCRAFT BATTERY MASTER SWITCH WAS TURNED ON, LEFT ENGINE MOTORED OVER. MAINTENANCE REMOVED AND REPLACED LEFT STAR TER RELAY AND RELEASED THE AIRCRAFT BACK TO SERVICE. (X) 1 L 7 2 3O A7CE 2000103100180 20001031 00180 CE 2000 10 31 20001026SH004 1 20000920 G 2710 12601121 CABLE HOUSING CESSNA 206 206H 2073301 CE AILERON QUADRANT INADEQUATE E K NONE O OTHER IN INSP/MAINT 1 SW 99 7281M 3121 20608048 DURING INITIAL INSPECTION OF THE AILERON INTERCONNECT CABLE QUADRANTS (RT AND LT) IAW CESSNA SB SB00-27-02, IT WAS DETER MINED THE REQUIRED RADIUS AROUND THE EDGE OF THE HOLE WHERE THE INTERCONNECT CABLE PASSES WAS NOT PRESENT. SUBSEQUENT I NSPECTION OF THE INTERCONNECT CABLE FOUND ONLY MINIMAL CHAFING WITH NO STRANDS BROKEN. THE CABLE TENSIONS BEFORE REMOVA L WERE WITHIN LIMITS. THE QUADRANTS WERE MODIFIED AND REINSTALLED PER THE INSTRUCTIONS. (X) 1 H 7 1 3O RT A4CE 2000103100103 20001031 00103 CE 2000 10 31 20001026SH005 1 20000920 G 2710 12601122 CABLE GUARD CESSNA 206 206H 2073301 CE AILERON QUADRANT INADEQUATE E K NONE O OTHER IN INSP/MAINT 1 SW 99 7281M 3121 20608048 DURING INITIAL INSPECTION OF THE AILERON INTERCONNECT CABLE QUADRANTS (RT AND LT) IAW CESSNA SB SB00-27-02, IT WAS DETER MINED THE REQUIRED RADIUS AROUND THE EDGE OF THE HOLE WHERE THE INTERCONNECT CABLE PASSES WAS NOT PRESENT. SUBSEQUENT I NSPECTION OF THE INTERCONNECT CABLE FOUND ONLY MINIMAL CHAFING WITH NO STRANDS BROKEN. THE CABLE TENSIONS BEFORE REMOVA L WERE WITHIN LIMITS. THE QUADRANTS WERE MODIFIED AND REINSTALLED PER THE INSTRUCTIONS. (X) 1 H 7 1 3O RT A4CE 2000103100104 20001031 00104 CE 2000 10 31 20001026SH006 1 20000925 G 2710 12601121 CABLE GUARD CESSNA 206 206H 2073301 CE AILERON QUADRANT INADEQUATE E K NONE O OTHER IN INSP/MAINT 1 SW 99 7273Q 405 20608045 DURING INITIAL INSPECTION OF THE AILERON INTERCONNECT CABLE QUADRANTS (RT AND LT) IAW CESSNA SB SB00-27-02, IT WAS DETER MINED THE REQUIRED RADIUS AROUND THE EDGE OF THE HOLE WHERE THE INTERCONNECT CABLE PASSES WAS NOT PRESENT. SUBSEQUENT I NSPECTION OF THE INTERCONNECT CABLE FOUND ONLY MINIMAL CHAFING WITH NO STRANDS BROKEN. THE CABLE TENSIONS BEFORE REMOVA L WERE WITHIN LIMITS. THE QUADRANTS WERE MODIFIED AND REINSTALLED PER THE INSTRUCTIONS. (X) 1 H 7 1 3O RT A4CE 2000103100105 20001031 00105 CE 2000 10 31 20001026SH007 1 20000925 G 2710 12601122 CABLE GUARD CESSNA 206 206H 2073301 CE AILERON QUADRANT INACCURATE E K NONE O OTHER IN INSP/MAINT 1 SW 99 7273Q 406 20608045 DURING THE INITIAL INSPECTION OF THE AILERON INTERCONNECT CABLE QUADRANT (RT AND LT) IAW CESSNA SB SB00-27-02, IT WAS DE TERMINED THE REQUIRED RADIUS AROUND THE EDGE OF THE HOLE WHERE THE INTERCONNECT CABLE PASSES WAS NOT PRESENT. SUBSEQUEN T INSPECTION OF THE INTERCONNECT CABLE FOUND ONLY MINIMAL CHAFING WITH NO STANDS BROKEN. THE CABLE TENSIONS BEFORE REMO VAL WERE WITHIN LIMITS. THE QUADRANTS WERE MODIFIED AND REINSTALLED PER THE INSTRUCTIONS. (X) 1 H 7 1 3O RT A4CE 2000103100116 20001031 00116 SW 2000 10 31 20001026SH008 1 20001002 G 3231 330094505 ARM GULSTM 690TP 690B 7630516 SW CRACKED B MV5R K NONE O OTHER IN INSP/MAINT 1 GL 11 771BA 11429 ARM ASSY CRACKED AT LANDING GEAR DOOR ATTACH AREA. (X) 1 H 7 2 3T 2A4 2001022600007 20010226 00007 EA 2001 2 26 20001026SH010 2 20001026 G 7414 6361 MAGNETO PIPER PA32 PA32R301T 7103220 SO LYC O540 TIO540S1AD 41532 EA ENGINE CONTAMINATED D K NONE O OTHER IN INSP/MAINT 1 WP 07 9299X 440 3257021 OWNER REPORTED ENGINE GETTING HARDER TO START, LAST START TOOK 20 MINUTES, WOULD NOT START AT NEXT FUEL STOP. REMOVED S PARK PLUG LEADS TO CHECK FOR SPARK, NONE NOTED ON EITHER MAGNETO. REMOVED BOTH MAGS AND OPENED FOR INSP. FOUND BOTH MA GS FULL OF MELTED GREASE. GREASE APPEARS TO HAVE COME FROM MAGNETO BEARINGS. RT MAG SHOWED SIGNS OF HIGHER HEAT AS GR EASE WAS MORE LIQUID WHEN COMPARED TO LT MAG. INSTALLED 2 NEW SLICK MAGS OF SAME MODEL NUMBERS. OPER CHECK NORMAL WITH NO DIFFICULT STARTING. (X) 1 L 7 1 3O 3 O A3SO E14EA 2001022600008 20010226 00008 EA 2001 2 26 20001026SH011 2 20001026 G 7414 6360 MAGNETO PIPER PA32 PA32R301T 7103220 SO LYC O540 TIO540S1AD 41532 EA ENGINE CONTAMINATED D K NONE O OTHER IN INSP/MAINT 1 WP 07 9299X 440 3257021 OWNER REPORTED ENGINE GETTING HARDER TO START, LAST START TOOK 20 MINUTES, WOULD NOT START AT NEXT FUEL STOP. REMOVED S PARK PLUG LEADS TO CHECK FOR SPARK, NONE NOTED ON EITHER MAGNETO. REMOVED BOTH MAGS AND OPENED FOR INSP. FOUND BOTH MA GS FULL OF MELTED GREASE. GREASE APPEARS TO HAVE COME FROM MAGNETO BEARINGS. RT MAG SHOWED SIGNS OF HIGHER HEAT AS GR EASE WAS MORE LIQUID WHEN COMPARED TO LT MAG. INSTALLED 2 NEW SLICK MAGS OF SAME MODEL NUMBERS. OPER CHECK NORMAL WITH NO DIFFICULT STARTING. (X) 1 L 7 1 3O 3 O A3SO E14EA 2001022600009 20010226 00009 CE 2001 2 26 20001026SH012 1 20000915 G 5751 SKIN BEECH 90 C90 1152913 CE AILERON CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 01 901JA 8475 LJ694 ON 5-15-00, LEFT AILERON SKIN FOUND CRACKED AT OUTBOARD AFT EDGE UNDERSIDE. UPON FURTHER INSPECTION, FOUND THE SKIN TO BE VERY BRITTLE. ON 9-10-00, FOUND RIGHT AILERON SKIN CRACKED AT SKIN LAP AFT OF CENTER ATTACH POINT BOTH UPPER AND LOW ER. SKIN FOUND TO BE BRITTLE. CRACK WAS DIFFICULT TO IDENTIFY AS IT APPEARED TO BE A NATURAL SEPARATION OF AGING PAINT SEPARATION AT THE LAP JOINT. SUBMITTER SUSPECTED WORKING SURFACES AND/OR DISSIMILAR METAL CORROSION. THERE WERE NO OB VIOUS SIGNS OF A CRACK NOR OF WORKING SURFACES OR CORROSION. (X) 1 L 7 2 3T 3A20 2001022600010 20010226 00010 CE 2001 2 26 20001026SH013 1 20001004 G 2820 FUEL LINE CESSNA 208 208B 2073701 CE FUEL RESERVOIR CHAFED B K NONE O OTHER IN INSP/MAINT 1 SW 15 914FE 7440 208B0014 BOLT HOLDING SEAL TO LONGERON HAD THE END RUBBING AGAINST THE FUEL LINE THAT FEEDS THE RESERVOIR. (X) 1 H 7 1 3T A37CE 2001022600012 20010226 00012 SO 2001 2 26 20001026SH015 1 20001002 G 7602 653657 CONTROL CABLE PIPER PA34 PA34220T 7103420 SO MIXTURE CONTROL BINDING B K NONE O OTHER IN INSP/MAINT 1 WP 07 9299E 2140 3449043 RIGHT HAND MIXTURE CABLE (HARD TO MOVE IN-FLIGHT). (X) 1 L 7 2 3O A7SO 2001020900053 20010209 00053 EU 2001 2 9 20001026SH018 1 20000729 G 3340 356H2802 POWER SUPPLY SNIAS 350 AS350B3 8680954 EU EXTERIOR LIGHTS INOPERATIVE B R7MR K NONE L NO TEST IN INSP/MAINT 1 NM 07 103LN 647 3128 POWER SUPPLY BOX UNIT INOPERATIVE. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001020900054 20010209 00054 2001 2 9 20001026SH019 4 20000726 G 3414 3502001105 INDICATOR SNIAS 350 AS350B3 8680954 EU COCKPIT INOPERATIVE B R7MR O OTHER O OTHER NR NOT REPORTED 1 NM 07 103LN 27 3128 IPC DOES NOT DISTINGUISH BETWEEN LIGHTED AND UNLIGHTED INDICATORS. AIRCRAFT REQUIRES LIGHTED INDICATOR. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001020900055 20010209 00055 EU 2001 2 9 20001026SH020 1 20000421 G 5220 350A25109521 ROD SNIAS 350 AS350B3 8680954 EU JETTISON DOOR WEAK B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 103LN 527 3128 JETTISON DOOR ROD WEAK. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001020900056 20010209 00056 2001 2 9 20001026SH021 4 20000707 G 3413 3502011111 INDICATOR SNIAS 350 AS350B3 8680954 EU VERTICAL SPEED FLUCTUATES B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 103LN 619 3128 VERTICAL SPEED INDICATOR HAD EXCESSIVE NEEDLE FLUCTUATION. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001020900057 20010209 00057 EU 2001 2 9 20001026SH022 1 20000829 G 6720 350A33214501 ROD SNIAS 350 AS350B3 8680954 EU PITCH CONTROL WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 104LN 61 3134 PITCH CONTROL ROD WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001020900058 20010209 00058 EU 2001 2 9 20001026SH023 1 20000726 G 3340 A490ATSCF1428 POWER SUPPLY UROCOP EC135 EC135P1 8680990 EU STROBE LIGHT INOPERATIVE B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 135SJ 372 EC1350054 STROBE POWER SUPPLY UNIT INOPERATIVE. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U O H88EU 2001020900059 20010209 00059 EU 2001 2 9 20001026SH024 1 20000727 G 2822 9A2045 CARTRIDGE UROCOP EC135 EC135P1 8680990 EU FUEL PUMP INOPERATIVE B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 135SJ 137 EC1350054 FUEL PUMP CARTRIDGE INOPERATIVE. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U O H88EU 2001020900060 20010209 00060 EU 2001 2 9 20001026SH025 1 20000718 G 6710 10545371 ROD END BOLKMS BK117 BK117C1 5626025 EU MAIN ROTOR WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 117SU 664 7527 ROD END ASSY WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U NC H13EU 2001020900061 20010209 00061 EU 2001 2 9 20001026SH026 1 20000819 G 7714 117902111 INDICATOR BOLKMS BK117 BK117C1 5626025 EU TRIPLE TACH INOPERATIVE B R7MR O OTHER O OTHER NR NOT REPORTED 1 NM 07 117SU 32 7527 TRIPLE TACH INDICATOR UNIT INOPERATIVE. N2 SPLIT OF 2 PERCENT INDICATED IN ERROR. REPLACED WITH NEW UNIT, CORRECTED PR OBLEM. (X) 1 G 7 2 3U NC H13EU 2001020900062 20010209 00062 EU 2001 2 9 20001026SH027 1 20000807 G 7714 117902111 INDICATOR BOLKMS BK117 BK117C1 5626025 EU TRIPLE TACH INOPERATIVE B R7MR O OTHER O OTHER NR NOT REPORTED 1 NM 07 117SU 713 7527 TRIPLE TACH INDICATOR UNIT INOPERATIVE. NR 1 POINTER INOPERATIVE. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U NC H13EU 2001020900063 20010209 00063 EU 2001 2 9 20001026SH028 1 20000808 G 6320 IPT20RT1100080G TRANSMITTER BOLKMS BK117 BK117C1 5626025 EU TRANS OIL PRESS ERRATIC B R7MR O OTHER O OTHER NR NOT REPORTED 1 NM 07 117SU 713 7527 PRESSURE TRANSMITTER HAD ERRATIC READINGS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U NC H13EU 2001022600019 20010226 00019 CE 2001 2 26 20001030SH014 1 20001013 G 2752 C1452501S MOTOR CESSNA 172 172N 2072434 CE FLAP FAILED B ZKGR K NONE O OTHER IN INSP/MAINT 1 NE 05 737XM 54 17269755 FLAP MOTOR BURNED OUT. SUBMITTER STATED THEY PUT 2 NEW UNITS IN FROM CESSNA, CHECK OF ACTUATOR AND GEARBOX FOUND NO DEF ECTS. TURNS FREELY. CHECKED WIRES, NO DEFECTS. UNKNOWN CAUSE OF FAILURES. DATE OF MANUFACTURE OF MOTOR NR 2 IS 7/99. (X) 1 H 7 1 3O NT 3A12 2001022600020 20010226 00020 CE 2001 2 26 20001030SH015 1 20001013 G 2752 C1452501S MOTOR CESSNA 172 172N 2072434 CE FLAP FAILED B ZKGR K NONE O OTHER IN INSP/MAINT 1 NE 05 737XM 205 17269755 FLAP MOTOR BURNED OUT. SUBMITTER STATED THEY PUT 2 NEW UNITS IN FROM CESSNA, CHECK OF ACTUATOR AND GEARBOX FOUND NO DEF ECTS. TURNS FREELY. CHECKED WIRES, NO DEFECTS. UNKNOWN CAUSE OF FAILURES. DATE OF MANUFACTURE OF MOTOR NR 2 IS 7/99. (X) 1 H 7 1 3O NT 3A12 2001022600021 20010226 00021 SO 2001 2 26 20001030SH016 1 20001013 G 2821 FUEL FILTER PIPER PA34 PA34200T 7103406 SO FUEL SYSTEM CONTAMINATED B ZKGR O OTHER Y ENGINE STOPPAGE CR CRUISE 1 NE 05 4516F 347670340 ACFT FLYING AT 13,000 FEET AROUND ZERO DEGREES FAHRENHEIT, RT ENGINE POWER FLUX AND LOST POWER. ACFT LANDED WITHOUT INC IDENT. INSPECTION OF FUEL SYSTEM AROUND 18 HOURS LATER AND AFTER RUN-UP CHECK ABOUT 1 HR LATER, FOUND WATER DROPLET IN FUEL FILTER BOWL, PILOT HAD HAD ACFT SERVICED WITH FUEL BEFORE FUEL TRUCK RAN OUT OF FUEL IN TANK. WHILE FUELING, RT WI NG, DRAINED FUEL AND FLUSHED TANKS. SUBMITTER STATED PILOT WAS USING ANTI-ICING ADDITIVE FOR FUEL AT THIS TIME TO PREVE NT IT FROM HAPPENING AGAIN WHEN WEATHER CONDUCIVE TO FREEZING. CAUSE OF TROUBLE MAY HAVE BEEN FROZEN WATER IN FUEL STRA INING BOWL. RECHECKED BOWL 5 HRS LATER, NO WATER. (X) 1 L 7 2 3O A7SO 2001020900068 20010209 00068 EU 2001 2 9 20001030SH017 1 20000813 G 3340 A490ATSCF1428 POWER SUPPLY UROCOP EC135 EC135P1 8680990 EU STROBE LIGHT INOPERATIVE B R7MR K NONE L NO TEST IN INSP/MAINT 1 NM 07 135SJ 48 EC1350054 STROBE POWER SUPPLY INOPERATIVE. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U O H88EU 2001020900069 20010209 00069 2001 2 9 20001030SH018 4 20000921 G 3160 B19030MA DISPLAY SNIAS 350 AS350B3 8680954 EU COCKPIT INTERMITTENT B R7MR K NONE L NO TEST IN INSP/MAINT 1 NM 07 392LG 247 3252 UNIT OPERATES INTERMITTENTLY. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001020900070 20010209 00070 EU 2001 2 9 20001030SH019 1 20000802 G 6230 350A37112701 SCISSORS SNIAS 350 AS350B3 8680954 EU MAIN ROTOR LINK WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 392LG 63 3252 BUSHINGS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001020900071 20010209 00071 EU 2001 2 9 20001030SH020 1 20000713 G 6230 704A33640021 SPACER SNIAS 350 AS350B3 8680954 EU SWASHPLATE WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 392LG 13 3252 BUSHINGS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001020900072 20010209 00072 EU 2001 2 9 20001030SH021 1 20000713 G 6230 704A33640021 SPACER SNIAS 350 AS350B3 8680954 EU SWASHPLATE WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 392LG 13 3252 BUSHINGS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001020900073 20010209 00073 EU 2001 2 9 20001030SH022 1 20000713 G 6230 350A37112602 SCISSORS SNIAS 350 AS350B3 8680954 EU MAIN ROTOR LINK WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 00 392LG 8 3252 BUSHINGS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001020900074 20010209 00074 2001 2 9 20001030SH023 4 20000914 G 3160 B19030MB01 DISPLAY SNIAS 350 AS350B3 8680954 EU COCKPIT INOPERATIVE B R7MR K NONE L NO TEST IN INSP/MAINT 1 NM 07 397LG 29 3268 UNIT INOPERATIVE. BRIGHTNESS FAILURE CODE ON NEARLY ALL LIGHTS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001020900075 20010209 00075 EU 2001 2 9 20001030SH024 1 20000826 G 6520 350A33200406 SPIDER SNIAS 350 AS350B3 8680954 EU TAIL ROTOR LOOSE B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 52281 328 3249 EXCESSIVE PLAY ON TR SHAFT ASSY. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001020900076 20010209 00076 EU 2001 2 9 20001030SH025 1 20000826 G 6720 350A33214501 ROD SNIAS 350 AS350B3 8680954 EU PITCH CONTROL WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 52281 328 3249 ROD, PITCH CONTROL WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001020900077 20010209 00077 2001 2 9 20001030SH026 4 20000902 G 3452 KT70 TRANSPONDER SNIAS 350 AS350B3 8680954 EU ATC SHORTED B R7MR O OTHER O OTHER NR NOT REPORTED 1 NM 07 52281 345 3249 TRANSPONDER, KT70 MODE S ATC, HAD INTERNAL SHORT. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001020900078 20010209 00078 EU 2001 2 9 20001030SH027 1 20000817 G 7930 ZRA25500 TRANSMITTER SNIAS 350 AS350B3 8680954 EU OIL PRESSURE INTERMITTENT B R7MR O OTHER O OTHER NR NOT REPORTED 1 NM 07 52285 287 3251 OIL PRESSURE TRANSMITTER UNIT OPERATED INTERMITTENTLY. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001020900079 20010209 00079 EU 2001 2 9 20001030SH029 2 20001030 G 7200 BLADE AEROSP SA316 SA315B 8680615 EU TMECA ARTST2 ARTOUSTE2B1 60002 EU ENGINE MISSING B LH3D K NONE O OTHER IN INSP/MAINT 1 NM 03 65185 7050 2288 400 EXCESSIVE VIBRATION DURING ENGINE RUN-UP. REMOVED ENGINE FOR TEAR-DOWN INSPECTION. FOUND ONE EACH MISSING BLADE AND SE VERAL OTHERS DAMAGED ON 2 INCH STAGE TURBINE WHEEL. CAUSE UNKNOWN AT THIS TIME. (X) 1 G 7 1 4U 3 U H1IN E300 2001020900080 20010209 00080 NM 2001 2 9 20001030SH030 1 20000908 G 6710 900C2010214101 PITCH LINK DOUG MD900 MD900 3027375 NM ROTOR CONTROL WORN B R7MR O OTHER O OTHER NR NOT REPORTED 1 NM 07 901CF 505 90000012 PITCH LINK ASSY, ROTOR CONTROL, WORN BEYOND SERVICEABLE LIMITS. EXCESSIVE WEAR INTO ROD END ASSY. (X) 1 G 7 2 3U NC H19NM 2001022600018 20010226 00018 CE 2001 2 26 20001030SH032 1 20001030 G 2730 RI106 CONTROL BOX CESSNA 501 501 2076603 CE COCKPIT CHAFED B PJYR K NONE O OTHER IN INSP/MAINT 1 GL 15 0075 ELEVATOR TRIM CHAIN IN PEDESTAL CHAFED ON SPERRY RI-106 REMOTE CONTROL BOX. CASE OF CONTROL BOX WAS SEVERLY WORN. IT W AS EVIDENT THIS CONDITION EXISTED FOR SOME TIME. THIS COULD HAVE POSSIBLY LED TO JAMMING OF THE ELEVATOR TRIM SYSTEM. U NIT WAS REMOVED AND AIRCRAFT WAS FERRIED TO A CITATION SERVICE CENTER FOR REPAIR. (X) 1 L 7 2 4F A27CE 2001011101203 20010111 01203 SO 2001 1 11 20001030SH033 2 20001030 G 8530 CYLINDER CONT O520 IO520* 17032 SO ENGINE DELAMINATED C A UNSCHED LANDING Y ENGINE STOPPAGE CL CLIMB 1 SW 17 1831 82 291457R CERMINIL COATING DELAMINATED FROM ONE STEEL CYLINDER BORE AT 82.2 HOURS TSO. POSSIBLE CAUSE, SOME INDIVIDUAL POSSIBLY T OUCHED CYLINDER BORE JUST BEFORE PROCESSING. TOUCHING THE CYLINDER BORE AFTER FINAL CLEANING AND/OR DURING PROCESSING I S STRICTLY PROHIBITED IN SPECIFICATION FOR THE PROCESS BECAUSE CONTAMINATION FROM A PERSON'S HAND CAN CAUSE ADHERENCE P ROBLEMS. THE AUTOMATED PRE-TREAT PROCESS WAS POSSIBLY INTERRUPTED THROUGH SOME ELECTRICAL OR COMPUTER ANOMALY AND THE R EQUIRED PRE-TREATMENTS WERE NOT SATISFACTORLY COMPLETED. THE PLATING PROCESS IS PRIMARILY ACCOMPLISHED THROUGH COMPUTER AND ROBOTIC MANIPULATION. SUBMITTER STATED THE COMPUTER REPORTED PROCESSING PROBLEMS. (X) 3 O E5CE 2001022600024 20010226 00024 SO 2001 2 26 20001031SH003 2 20001005 G 8530 CYLINDER CESSNA 180 180 2072602 CE CONT O470 O470J 17026 SO ENGINE SEPARATED B A UNSCHED LANDING O OTHER TO TAKEOFF 1 GL 15 9248C 31347 4610463 DURING WATER TAKEOFF, EXPERIENCED MODERATE ROUGH RUNNING ENGINE, RETURNED TO LAKE. INSPECTION REVEALED ONE CYLINDER HAD SEPARATED BETWEEN BARREL AND HEAD. THESE 6 CYLINDERS HAD APPROXIMATELY 400 HOURS SINCE BEING CHROMED. OWNER REPLACED ALL CYLINDERS WITH NEW SUPERIOR MILLENIUM SET. (X) 1 H 7 1 3O 3 O NC 5A6 E273 2001022600025 20010226 00025 EA 2001 2 26 20001031SH004 2 20001005 G 7414 MAGNETO PIPER PA23 PA23250 7102308 SO LYC O540 IO540C4B5 41532 EA ENGINE DAMAGED H IK8S K NONE O OTHER IN INSP/MAINT 1 SO 11 6669Y 273986 L95545 MAGNETOS REMOVED FOR OVERHAUL. UPON EXAM OF LT MAG DRIVE GEAR AND ROTATING MAGNET THREAD END, NOTED NUT, PN 10-163178, WAS LOOSE. ALSO, DRIVE BUSHING, PN 10-357193 WAS LOOSE ALLOWING PLATE DRIVE, PN 10-163216 TO SHIFT ALIGNMENT OF DRIVE G EAR WHICH ATE INTO BACK OF ENG CASE. THIS MISALIGNMENT CREATED A LOT OF DAMAGE THAT COULD NOT BE REPAIRED. ALSO DISCOV ERED A WASHER WAS LEFT OUT WHEN MAG O/H''''D. IT GOES BTWN DRIVE NUT PN 10-163178 AND BUSHING PN 10-357193. WITH THIS WASHER, PN 10-116860 OUT, PROPER TORQUE COULD NOT BE OBTAINED. SUBMITTER STATED NO HISTORY AS TO WHEN MAGS O/H''''D, AN D NO HISTORY OF TIME WHEN INSTALLED. (X) 1 L 7 2 3O 3 O 1A10 1E4 2001022600026 20010226 00026 SO 2001 2 26 20001031SH007 1 20000913 G 3211 BOLT PIPER PA28 PA28151 7102805 SO LT MLG MISSING H K NONE O OTHER LD LANDING 1 CE 09 41558 3121 287415270 AIRCRAFT CONTROL LOST ON LANDING. AIRCRAFT BOUNCED AND STRUT FELL OUT. SCISSOR BOLT WAS MISSING. (X) 1 L 7 1 3O 2A13 2001022600027 20010226 00027 CE 2001 2 26 20001031SH008 1 20001010 G 5510 9562001085 CHANNEL BEECH 58 58 1152740 CE HORIZONTAL STAB CRACKED B VY2R K NONE O OTHER IN INSP/MAINT 1 EA 23 3713N 1729 TH1196 FOUND RIGHT STABILIZER, FORWARD SPAR ATTACH CHANNEL CRACKED IN LOWER RADIUS. AREA VERY HARD TO ACCESS WITH MIRROR AND F LASHLIGHT. FOUND A CRACK IN A BARON IN THE SAME LOCATION PREVIOUSLY. CRACK IS FOUND WHERE THE MOUNTING CHANNEL PASSES THROUGH THE FUSELAGE. STABILIZER MUST BE REMOVED TO REPLACE THIS CHANNEL. SUBMITTER SUGGESTED THIS ARM BE INSPECTED RE GULARLY. (X) 1 L 7 2 3O 3A16 2001022600028 20010226 00028 EU 2001 2 26 20001031SH010 1 20000914 G 2752 951D1009 ACTUATOR PILATS PC12 PC12 7090550 EU TE FLAP WORN B K NONE O OTHER IN INSP/MAINT 1 GL 09 171 TWO SHAFT SUPPORT BEARINGS WERE NOT INSTALLED AT THE TIME OF ORIGINAL ASSEMBLY. THE OMISSION OF THESE BEARINGS SA13589- 1 AND SA13588-1 CAUSED PREMATURE WEAR OF THE WORN SHAFT RESULTING IN EXCESSIVE GEAR BACKLASH. (X) 1 L 7 1 3T RT A78EU 2001022100186 20010221 00186 NM 2001 2 21 20001031SH011 1 20001031 G 5753 SPAR BOEING 737 737* NM TE FLAPS CRACKED B K NONE O OTHER IN INSP/MAINT 1 SW 15 BN495 ONE EACH CRACK EXITS ON THE UPPER AFT T-SPAR MEASURING 1.5 INCHES LONG, LOCATED AT THE INBOARD END OF THE OUTBOARD MID-F LAP. (X) 2 L 7 2 4F RT A16WE 2001022100187 20010221 00187 NM 2001 2 21 20001031SH012 1 20001031 G 5753 6540406 SPAR BOEING 737 737300 1384610 NM TE FLAPS CRACKED B K NONE O OTHER IN INSP/MAINT 1 SW 15 737300/737400/737500 WERE FOUND WITH A CRACK IN THE UPPER AFT SPAR T-CAP OF THE OUTBOARD MIDFLAP. CRACK IS LOCATED ON T HE VERTICAL LEG OF THE SPAR NEAR THE EXHAUST GATE HINGE. EACH OF THE LAST FOUR 737 OTBD MIDFLAPS EVALUATED WERE CRACKED IN THE DESCRIBED LOCATION. DETAILS OF THESE 737 OTBD MIDFLAPS ARE: PN 65C263201, SN BN444, 6 INCHES LONG, ON 10-5-99; PN 65C263201, SN BN479, 4.5 INCHES LONG, ON 11-15-99; PN 65C263201, SN BN461, 5 INCHES LONG, ON 1-8-00; PN 65C263203, S N BN495, 1.5 INCHES LONG (W/STOP HOLE), ON 1-11-00. DAMAGE DISCOVERED ON FLAPS DETACHED FROM ACFT DURING EVAL FOR REPAI R/OVERHAUL, POSSIBLE CAUSE CANNOT BE DETERMINED BY SUBMITTER. NOTE: 5TH OTBD MIDFLAP FOUND WITH CRACK SIMILAR LOCAL.(X) 2 L 7 2 4F RT A16WE 2001022100021 20010221 00021 NM 2001 2 21 20001031SH014 1 20001031 G 5753 6540406 SPAR BOEING BOEING 737 737400 NM TE FLAPS CRACKED B K NONE O OTHER IN INSP/MAINT 1 SW 15 737300/737400/737500 WERE FOUND WITH A CRACK IN THE UPPER AFT SPAR T-CAP OF THE OUTBOARD MIDFLAP. CRACK IS LOCATED ON T HE VERTICAL LEG OF THE SPAR NEAR THE EXHAUST GATE HINGE. EACH OF THE LAST FOUR 737 OTBD MIDFLAPS EVALUATED WERE CRACKED IN THE DESCRIBED LOCATION. DETAILS OF THESE 737 OTBD MIDFLAPS ARE: PN 65C263201, SN BN444, 6 INCHES LONG, ON 10-5-99; PN 65C263201, SN BN479, 4.5 INCHES LONG, ON 11-15-99; PN 65C263201, SN BN461, 5 INCHES LONG, ON 1-8-00; PN 65C263203, S N BN495, 1.5 INCHES LONG (W/STOP HOLE), ON 1-11-00. DAMAGE DISCOVERED ON FLAPS DETACHED FROM ACFT DURING EVAL FOR REPAI R/OVERHAUL, POSSIBLE CAUSE CANNOT BE DETERMINED BY SUBMITTER. NOTE: 5TH OTBD MIDFLAP FOUND WITH CRACK SIMILAR LOCAL.(X) 2 L 7 2 4F RT A16WE 2001022100188 20010221 00188 NM 2001 2 21 20001031SH015 1 20001031 G 5753 6540406 SPAR BOEING BOEING 737 737500 NM TE FLAPS CRACKED B K NONE O OTHER IN INSP/MAINT 1 SW 15 737300/737400/737500 WERE FOUND WITH A CRACK IN THE UPPER AFT SPAR T-CAP OF THE OUTBOARD MIDFLAP. CRACK IS LOCATED ON T HE VERTICAL LEG OF THE SPAR NEAR THE EXHAUST GATE HINGE. EACH OF THE LAST FOUR 737 OTBD MIDFLAPS EVALUATED WERE CRACKED IN THE DESCRIBED LOCATION. DETAILS OF THESE 737 OTBD MIDFLAPS ARE: PN 65C263201, SN BN444, 6 INCHES LONG, ON 10-5-99; PN 65C263201, SN BN479, 4.5 INCHES LONG, ON 11-15-99; PN 65C263201, SN BN461, 5 INCHES LONG, ON 1-8-00; PN 65C263203, S N BN495, 1.5 INCHES LONG (W/STOP HOLE), ON 1-11-00. DAMAGE DISCOVERED ON FLAPS DETACHED FROM ACFT DURING EVAL FOR REPAI R/OVERHAUL, POSSIBLE CAUSE CANNOT BE DETERMINED BY SUBMITTER. NOTE: 5TH OTBD MIDFLAP FOUND WITH CRACK SIMILAR LOCAL.(X) 2 L 7 2 4F RT A16WE 2001022600029 20010226 00029 SO 2001 2 26 20001031SH016 2 20000926 G 7314 6467661A1 PUMP BEECH 36 A36 1151604 CE CONT O550 IO550B SO ENGINE FAILED D D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 SO 33 8170D 135 E2600 297181R INTERNAL FAILURE, PUMP STOPPED BEFORE TAKEOFF. (X) 1 L 7 1 3O 3 O 3A15 E3SO 2001030100027 20010301 00027 SO 2001 3 1 20001031SH017 2 20000925 G 8550 SPRING PIPER PA34 PA34200T 7103406 SO CONT O360 LTSIO360EB 17025 SO OIL SYSTEM BROKEN B K NONE O OTHER IN INSP/MAINT 1 GL 21 13AG 1394 347770115 807270R PILOT REPORTED THAT OIL PSI WAS LOW AS HE REDUCED POWER FOR LANDING. THE SPRING BROKE DUE TO RUBBING ON THE INSIDE OF T HE RELIEF VALVE PISTON. (X) 1 L 7 2 3O 3 O A7SO E9CE 2001022600030 20010226 00030 SO 2001 2 26 20001031SH018 2 20000519 G 7313 63274814 INJECTOR BEECH 58 58P 1152744 CE CONT O520 TSIO520WB 17040 SO CYLINDERS LEAKING H O OTHER B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 NM 03 144Z 35 TJ211 274454R WHILE IN-FLIGHT, A FUEL SMELL ENTERED THE CABIN. FUEL WAS LEAKING AT ALL 6 INJECTORS BETWEEN PIPE THREADS AND CYLINDER. ALL INJECTORS WERE SEALED PER CONTINENTAL SM. NEXT FLIGHT STILL LEAKING. INJECTORS RESEALED WITH LOCTITE 569 PER CON TINENTAL. (X) 1 L 7 2 3O 3 O A23CE E8CE 2001030100028 20010301 00028 CE 2001 3 1 20001031SH019 1 20001003 G 2436 DGR72850 REGULATOR CESSNA 310 310H 2074220 CE COPILOT SEAT MISMARKED D K NONE O OTHER IN INSP/MAINT 1 SW 05 1029Q 310H0029 BOTH REGULATORS ARE OF THE PARALLELING TYPE. THE PARALLELING TERMINAL ON THE REGULATOR IS MARKED GRD FOR GROUND, AND SH OULD BE PAR FOR PARALLEL. IF THIS TERMINAL IS GROUNDED TO THE PARALLELING RELAY, THE WIRES WILL SMOKE REPRESENTING A FI RE HAZARD UNDER THE COPILOT''S SEAT. (X) 1 L 7 2 3O 3A10 2001030100029 20010301 00029 CE 2001 3 1 20001031SH020 1 20001003 G 2436 DGR72850 REGULATOR CESSNA 310 310H 2074220 CE COPILOT SEAT MISMARKED D K NONE O OTHER IN INSP/MAINT 1 SW 05 1029Q 310H0029 BOTH REGULATORS ARE OF THE PARALLELING TYPE. THE PARALLELING TERMINAL ON THE REGULATOR IS MARKED GRD FOR GROUND, AND SH OULD BE PAR FOR PARALLEL. IF THIS TERMINAL IS GROUNDED TO THE PARALLELING RELAY, THE WIRES WILL SMOKE REPRESENTING A FI RE HAZARD UNDER THE COPILOT''S SEAT. (X) 1 L 7 2 3O 3A10 2001022600031 20010226 00031 SO 2001 2 26 20001031SH022 2 20001016 G 7322 SHAFT CESSNA 150 150L 2071826 CE CONT O200 O200A 17020 SO CARBURETOR WORN G A UNSCHED LANDING Y ENGINE STOPPAGE NR NOT REPORTED 1 GL 27 18601 15073976 POWER LOSS CAUSED AN OFF AIRPORT LANDING. EXAMINATION OF THE CARBURETOR REVEALED THE THROTTLE SHAFT WAS SEVERELY WORN. ADDITIONALLY, THE ACCELERATOR PUMP SHAFT SEAL WAS ALSO WORN. THE THROTTLE ARM WAS STILL OF THE ORIGINAL TYPE AS IN AD 72-06-05R2. (X) 1 H 7 1 3O 3 O 3A19 E252 2001022600032 20010226 00032 SW 2001 2 26 20001031SH023 1 20000910 G 8120 3AT6EE10J2 TURBOCHARGER MOONEY M20 M20J 5870219 SW LYC O360 IO360A1B6 41514 EA ENGINE SEIZED H A UNSCHED LANDING O OTHER CR CRUISE 1 GL 21 205MN 213 243019 2443351A TURBO LOCKED UP. THE PILOT LANDED THE A/C UNEVENTFULLY. NO DAMAGE TO A/C. TURBOCHARGER P/N 3AT6EE10J2 CF600573-000 0. (X) 1 L 7 1 3O 3 O 2A3 1E10 2001022600033 20010226 00033 SO 2001 2 26 20001031SH024 1 20000816 G 3244 1159SCL20633 TIRE GULSTM G1159 G1159 3953505 SO LT INBD MLG SEPARATED B K NONE O OTHER TO TAKEOFF 1 NE 01 TIRE SHED OUTER TREAD DURING TAKEOFF. TREAD SEPARATED FROM TIRE IN LARGE PIECES AND SHEETS. TIRE CASING REMAINED INTAC T WITH NO LOSS OF AIR PRESSURE. MOUNTED ON LT INBOARD POSITION. TOTAL TIME ON TIRE, 139 HOURS TSN. 123 LANDINGS TSN. (X) 2 L 7 2 4F RT A12EA 2001022600034 20010226 00034 WP 2001 2 26 20001031SH025 1 20001016 G 3246 9550328 WHEEL DOUG DC8 DC8* WP NLG CORRODED B INWR K NONE O OTHER IN INSP/MAINT 1 SO 19 NOSE WHEEL ASSY HEAVILY CORRODED AT BEAD SEAT AREA. ALSO, BOLT HOLES AREA HEAVILY CORRODED. (X) 2 L 7 4 4J F 4A25 2001022600035 20010226 00035 SO 2001 2 26 20001031SH026 1 20001031 G 3230 AN625 BOLT PIPER PA28 PA28R200 7102811 SO DRAG BRACE MISINSTALLED G K NONE O OTHER IN INSP/MAINT 1 GL 25 2781R 28R35272 BOLTS IN UPPER NOSE GEAR DRAG BRACE ASSY, SECURING TO ENGINE MOUNT ARE INSTALLED BACKWARDS. LARGE DIAMETER STEEL WASHER S, TEFLON WASHERS ARE ALSO INSTALLED INCORRECTLY PER PAC DRAWING, IPC, AND SM. (X) 1 L 7 1 3O 2A13 2001022600036 20010226 00036 CE 2001 2 26 20001031SH027 1 20000921 G 3230 504501033 TORQUE TUBE CESSNA 421 421B 2076014 CE LT MLG CRACKED H K NONE O OTHER IN INSP/MAINT 1 EA 23 3372Q 424 421B9256 LEFT MAIN LANDING GEAR WOULD NOT RETRACT. FOUND LARGE CRACK AT LEFT MAIN LANDING GEAR TORQUE TUBE. NOTHING ABNORMAL WI TH GEAR RIGGING, CRACKED FROM STRESS OF CONTINUED USE. REPLACED TORQUE TUBE WITH NEW FROM FACTORY. RECHECKED LANDING G EAR RIGGING PER CESSNA MM. (X) 1 L 7 2 3O A7CE 2001022600037 20010226 00037 CE 2001 2 26 20001031SH028 1 20001018 G 2571 0024000133 DRAIN MAST BEECH 58 58 1152740 CE FWD FUSELAGE BROKEN H K NONE O OTHER IN INSP/MAINT 1 CE 07 4456T 19 TH1946 SUBMITTER STATED BATTERY DRAIN MASTS HAVE BEEN CRACKED OR BROKEN OFF OF A LARGE NUMBER OF NEW B-58 AIRCRAFT. TIME VARIE S FROM 20 HOURS TO SEVERAL HUNDRED HOURS. (X) 1 L 7 2 3O 3A16 2001022600038 20010226 00038 SO 2001 2 26 20001031SH029 1 20001012 G 3230 AN625 BOLT PIPER PIPER PA28 PA28R201T 7102813 SO DRAG BRACE MISINSTALLED G K NONE O OTHER IN INSP/MAINT 1 GL 25 5907V 28R7703165 BOLTS ON UPPER NOSE GEAR DRAG BRACE ASSY, SECURING TO ENGINE MOUNT, ARE INSTALLED BACKWARDS. THE PN 62833-43 LARGE DIA METER STEEL WASHER, TEFLON WASHERS, ARE ALSO INSTALLED INCORRECTLY PER PAC DRAWING, FAC AND SM. (X) 1 L 7 1 3O 2A13 2001022600039 20010226 00039 CE 2001 2 26 20001101SH001 1 20000919 G 2400 S337711 MASTER SWITCH CESSNA 172 172R 2072401 CE INSTRUMENT PANEL MALFUNCTIONED H K NONE O OTHER IN INSP/MAINT 1 GL 03 718EH 1283 17280061 WHEN AVIONICS MASTER SWITCH STARTS TO FAIL, IT WILL ONLY TURN ON THE NR 1 COM. ALL OTHER AVIONIC COMPONENTS ARE CONTROL LED BY THE BATTERY MASTER. (X) 1 H 7 1 3O NT 3A12 2001022600040 20010226 00040 GL 2001 2 26 20001101SH003 3 20000906 G 6111 C32941 BLADE MTSBSI MU2 MU2B35 5780411 CE HARTZL HCB3T HCB3TN5 GL NR 2 ENG PROP BROKEN H E K ENGINE SHUTDOWN NONE E VIBRATION/BUFFET CR CRUISE 1 SW 15 770MA 223 625 BVA7037 AIRCRAFT AT CRUISE, ALT 11,000 FEET, NR 1 PROPELLER BLADE BROKE APPROXIMATELY 10 INCHES FROM HUB ON NR 2 ENGINE. BLADE DID NOT CONTACT AIRCRAFT. DAMAGE TO COWLING, NACELLE, REAR ENGINE MOUNT, OUTBOARD FLAP, WING TRAILING EDGE. ENGINE REM AINED ON WING. CREW MADE NORMAL LANDING. REMAINING PORTION OF BLADE REMOVED FROM PROP HUB AND SENT TO NTSB LAB FOR INS PECTION. (X) 1 H 7 2 3T RT A10SW 6 C P15EA 2000111500244 20001115 00244 SO 2000 11 15 20001101SH004 2 20001002 G 8530 642399 CONNECTING ROD CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO INSIDE ENGINE SEPARATED D A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CL CLIMB 1 NE 01 770CA 518 402C0432 816179 CLIMBING THROUGH 2,000 FEET ON TAKEOFF, LEFT ENGINE QUIT. AIRCRAFT RETURNED TO THE GATE WHERE MAINTENANCE FOUND NR 1 CO NNECTING ROD HAD SEPARATED FROM THE CRANKSHAFT PUNCTURING THE CASE HALVES AND KNOCKING BOTH MAGNETOS AFT OF MOUNTING FLA NGES. MAINTENANCE REMOVED AND REPLACED ENGINE AND RELEASED AIRCRAFT BACK TO SERVICE. (X) 1 L 7 2 3O 3 O A7CE E8CE 2000111500245 20001115 00245 SO 2000 11 15 20001101SH005 2 20001009 G 7414 6310 MAGNETO CESSNA 207 T207 2073612 CE CONT O520 IO520F 17032 SO RIGHT DEFECTIVE D D RETURN TO BLOCK R PARTIAL RPM/PWR LOSS TO TAKEOFF 1 NM 01 7405 534 20700147 818866R ON INITIAL POWER-UP FOR THE FLIGHT''S TAKEOFF ROLL, THE ENGINE LOST SUBSTANTIAL POWER. THE PILOT ROLLED OFF TO A TAXIWA Y AND SHUT DOWN. AFTER TROUBLESHOOTING THE IGNITION SYSTEM, THE RIGHT MAGNETO WAS FOUND DEFECTIVE AND REPLACED WITH NEW . RUN-UP SATISFACTORY. (X) 1 H 7 1 3O 3 O A16CE E5CE 2000111500246 20001115 00246 GL 2000 11 15 20001101SH006 1 20000802 G 8000 SOLENOID BLANCA 17 1730A 1220433 GL CONT O520 IO520K 17032 SO FAILED D O OTHER H B ELECT. POWER LOSS-50 PC SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 CE 01 8223R 30407 20914871K PRIOR TO TAKEOFF ON ENGINE RUN-UP, AIRCRAFT LOST ALL ELECTRICAL POWER, STARTER SOLENOID STAYED ENGAGED. THE ENGINE RAN THE STARTER, CAUSED A REVERSE CURRENT FLOW TO THE BATTERY. BATTERY FAILED, SMOKE FROM UNDER THE COWLING. STARTER SOLEN OID LOCATED ON THE FIRE WALL. SUBMITTER STATED AIRCRAFT IS FABRIC COVERED. THERE WAS NO DAMAGE IN THE ENGINE AREA. (X ) 1 L 7 1 3O 3 O A18CE E5CE 2000111500247 20001115 00247 CE 2000 11 15 20001101SH007 1 20000825 G 7900 VALVE CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA ENG SUMP DRAIN MISSING D A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 SW 15 82149 3953 557 17267692 L132076 THE AIRCRAFT WAS FLYING FROM TULSA TO SILOAM SPRINGS AND 8 MILES FROM SILOAM SPRINGS AIRPORT, PILOT REPORTED THE ENGINE OIL PRESSURE WAS FLUCTUATING FROM ZERO TO 60 PSI. THE ENGINE THEN STARTED TO VIBRATE SEVERELY BEFORE THE ENGINE COMPLET ELY STOPPED. UPON INSPECTION OF AIRCRAFT, FOUND THE OIL QUICK DRAIN WAS MISSING WHICH OBVIOUSLY CAUSED THE ENGINE TO LO SE OIL PRESSURE. THE QUICK DRAIN INSTALLED DID NOT HAVE A PROVISION FOR SAFETY WIRE. SUBMITTER RECOMMENDED TO PREVENT FUTURE PROBLEM WOULD BE TO CHANGE ALL PMA QUICK DRAINS TO BE REQUIRED TO HAVE A SAFETY HOLE IN THE VALVE. (X) 1 H 7 1 3O 3 O NT 3A12 E274 2000111500248 20001115 00248 GL 2000 11 15 20001101SH008 1 20001016 G 7160 19165910 ALT AIR DOOR BLANCA 17 1731A 1220435 GL IND AIR BOX FAILED D A UNSCHED LANDING R PARTIAL RPM/PWR LOSS TO TAKEOFF 1 EA 05 9643E 600 7732169 PILOT REPORTED LOSS OF POWER ON TAKEOFF CLIMB. AFTER RETURNING TO THE AIRPORT, INVESTIGATION REVEALED A FAILED ALTERNAT E AIR DOOR. (X) 1 L 7 1 3O A18CE 2000111500249 20001115 00249 CE 2000 11 15 20001101SH009 1 20000916 G 3230 TUBE CESSNA 310 310H 2074220 CE DRIVE NLG BROKEN G O OTHER O OTHER LD LANDING 1 CE 09 99JT 6167 310H0136 NOSE GEAR WOULD NOT LOCK DOWN AND COLLAPSED ON LANDING. FOUND NOSE GEAR DRIVE TUBE BROKEN. (X) 1 L 7 2 3O 3A10 2000111500250 20001115 00250 EA 2000 11 15 20001101SH010 2 20000818 G 7414 M3158 ROTOR SHAFT PIPER PA28 PA28181 7102807 SO LYC O360 O360A4M 41514 EA ROTOR GEAR SLOT CRACKED D O OTHER R PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 CE 07 9812C 1885 287890445 L2342636A MAGNETO HAD A 250 RPM DROP DURING PRE-FLIGHT RUN UP. A CHECK OF THE TIMING OF MAGNETO TO ENGINE SHOWED IT TO BE APPROX 10 DEGREES RETARDED. MAG WAS NOT FOUND LOOSE AT ITS MOUNT, SO IT WAS REMOVED FOR INSPECTION. UPON DISASSEMBLY, DISCOVE RED A CRACK ON THE ''EAR'' OF THE SLOT IN THE ROTOR SHAFT THAT HOLDS THE CAM FOR OPENING THE POINTS. NO RUST OR OTHER O UTSIDE FACTOR WAS VISIBLE AS A CAUSE FOR THIS FAILURE. (X) 1 L 7 1 3O 3 O 2A13 E286 2000111500251 20001115 00251 EA 2000 11 15 20001101SH011 2 20000928 G 7322 25765362 SERVO CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA FAILED D O OTHER R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 NM 03 948SP 824 172S8144 L2812651A ENGINE RSA-5AD1 FUEL SERVO WILL NOT MEET SPECIFICATIONS. FUEL FLOW BELOW 1700 RPM IS TOO HIGH, AT IDLE RPM IS ERRATIC, AND THE IDLE SPEED AND IDLE MIXTURE CANNOT BE SET TO SPECIFICATION WITH SATISFACTORY ENGINE OPERATION. FUEL SERVO REMOV ED, SENT FOR REPAIR. MAJOR REPAIRS ACCOMPLISHED AND SERVO REFLOWED TO PRECISION FLOW SHEET 30075-02 DATED 1-5-00. REIN STALLED FUEL SERVO, ADJUSTED IAW SPECS, OPERATIONAL CHECKED SATISFACTORY. SUBMITTER RECOMMENDED ANY RSA-5AD1 FUEL SERVO NOT FLOWED TO PRECISION FLOW SHEET 30075-02, BE REMOVED IMMEDIATELY AND SENT TO APPLICABLE REPAIR STATION FOR REPAIR. (X) 1 H 7 1 3O 3 O NT 3A12 1E10 2001020900083 20010209 00083 EU 2001 2 9 20001101SH014 1 20000726 G 6410 704A33633116 BEARING SNIAS 350 AS350B2 8680813 EU TAIL ROTOR WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 97LG 488 2917 ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, FROM 1 EACH KIT P/N 355A09-1036-01, CORRECTED PROB LEM. FOUR HALF SHELLS EQUALS ONE KIT. (X) 1 G 7 1 3U H9EU 2001020900084 20010209 00084 EU 2001 2 9 20001101SH015 1 20000831 G 6410 704A33633171 HINGE SNIAS 350 AS350B2 8680813 EU WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 93LG 2654 ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT FROM 1 EACH KIT P/N 355A33-2153-00 CORRECTED PROBLE M. TWO TEETERING BEARINGS EQUALS ONE KIT. (X) 1 G 7 1 3U H9EU 2001020900085 20010209 00085 EU 2001 2 9 20001101SH016 1 20000914 G 6310 350A35105901 COUPLING SNIAS 350 AS350B3 8680954 EU ENGINE/TRANS BROKEN B K NONE O OTHER IN INSP/MAINT 1 NM 03 5224R 986 2968 COUPLING DISC HAD BROKEN INSERTS. (X) 1 G 7 1 3U H9EU 2001020900086 20010209 00086 EU 2001 2 9 20001101SH017 1 20000901 G 6310 FREEWHEEL UNIT SNIAS SA330 SA330J 8680612 EU M/R GEARBOX FAILED B O OTHER O OTHER NR NOT REPORTED 1 NM 03 330J 1089 1647 MAIN GEARBOX FREEWHEEL FAILURE. (X) 2 G 7 2 4U H4EU 2001020900087 20010209 00087 EU 2001 2 9 20001101SH018 1 20000901 G 6310 330N34400102 FREEWHEEL UNIT SNIAS SA330 SA330J 8680612 EU M/R GEARBOX FAILED B O OTHER O OTHER NR NOT REPORTED 1 NM 03 330J 1647 MAIN GEARBOX FIREEWHEEL FAILURE CAUSING OVERTORQUE TO INTERMEDIATE GEARBOX. (X) 2 G 7 2 4U H4EU 2001020900088 20010209 00088 EU 2001 2 9 20001101SH019 1 20000129 G 6310 330A33000008 FREEWHEEL UNIT SNIAS SA330 SA330J 8680612 EU T/R GEARBOX FAILED B O OTHER O OTHER NR NOT REPORTED 1 NM 03 330J 333 1647 MAIN GEARBOX FREEWHEEL FAILURE CAUSING OVERTORQUE TO TAILROTOR GEARBOX. (X) 2 G 7 2 4U H4EU 2001020900089 20010209 00089 EU 2001 2 9 20001101SH020 1 20000823 G 6720 31605333006001 BEARING AEROSP SA316 SA316B 8680207 EU TAIL ROTOR BRINELLED B K NONE O OTHER IN INSP/MAINT 1 NM 03 31660 326 1981 MAJOR BRINELLING ON INNER AND OUTER RACE. AIRCRAFT WAS REPORTED TO HAVE LOST TAIL ROTOR CONTROL IN-FLIGHT. NO INJURIES OR MAJOR DAMAGE. (X) 1 G 7 1 4U H1IN 2001022600043 20010226 00043 EA 2001 2 26 20001101SH022 2 20001017 G 7314 02532330002 PUMP BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA LT ENGINE BROKEN B AHDR A UNSCHED LANDING X ENGINE FLAMEOUT CR CRUISE 1 EA 13 561SS 873 BB464 PCE80897 LEFT ENGINE FLAMED OUT IN-FLIGHT, RESTART PROCEDURES TRIED, BUT ENGINE WOULD NOT START. EMERGENCY DECLARED, AIRCRAFT LA NDED WITHOUT INCIDENT. TROUBLESHOOTING FOUND DRIVESHAFT FOR HIGH PRESSURE FUEL PUMP BROKEN. ENGINE OIL FILTER CHECKED FOR METAL CONTAMINATION, NONE FOUND. DRAINS FOR FCU CHECKED FOR LEAKAGE, NONE FOUND. CAUSE FOR FAILURE IS STILL UNDER INVESTIGATION. (X) 1 L 7 2 4T 4 T A24CE E4EA 2001022100036 20010221 00036 CE 2001 2 21 20001101SH024 1 20001017 G 2822 64621219A1 PUMP BEECH 58 58 1152740 CE CONT O550 IO550C SO LT FUEL BOOST FAILED B R14R K NONE O OTHER IN INSP/MAINT 1 EA 17 258DM 124 TH1938 684599 PILOT REPORTED LEFT ENGINE EXHIBITING A DROP IN FUEL PRESSURE AT TAKEOFF POWER. PILOT ALSO REPORTED THAT AFTER LANDING, BOTH ENGINES WOULD EXHIBIT AN UNCONTROLLABLE ROLLBACK OF FUEL PRESSURE FOLLOWED BY ENGINE STALL. TROUBLESHOOTING REVEA LED LOW UNMETERED FUEL PRESSURE BEING DELIVERED BY THE ENGINE DRIVEN FUEL PUMPS ON BOTH ENGINES. BOTH FUEL PUMPS WERE R EMOVED AND REPLACED (SUBMITTER STATED THIS IS THE 2ND RAYTHEON MODEL 58 TO BE SERVICED AT THIS FACILITY WITHIN 2 WEEKS F OR THE SAME DISCREPANCY.) (X) 1 L 7 2 3O 3 O 3A16 E3SO 2001022100039 20010221 00039 CE 2001 2 21 20001101SH025 1 20001017 G 2822 64621219A1 PUMP BEECH 58 58 1152740 CE CONT O550 IO550C SO RT FUEL BOOST FAILED B R14R O OTHER O OTHER NR NOT REPORTED 1 EA 17 258DM 124 TH1938 684603 PILOT REPORTED LEFT ENGINE EXHIBITING A DROP IN FUEL PRESSURE AT TAKEOFF POWER. PILOT ALSO REPORTED THAT AFTER LANDING, BOTH ENGINES WOULD EXHIBIT AN UNCONTROLLABLE ROLLBACK OF FUEL PRESSURE FOLLOWED BY ENGINE STALL. TROUBLESHOOTING REVEA LED LOW UNMETERED FUEL PRESSURE BEING DELIVERED BY THE ENGINE DRIVEN FUEL PUMPS ON BOTH ENGINES. BOTH FUEL PUMPS WERE R EMOVED AND REPLACED (SUBMITTER STATED THIS IS THE 2ND RAYTHEON MODEL 58 TO BE SERVICED AT THIS FACILITY WITHIN 2 WEEKS F OR THE SAME DISCREPANCY.) (X) 1 L 7 2 3O 3 O 3A16 E3SO 2001020900090 20010209 00090 SW 2001 2 9 20001101SH026 1 20000914 G 6410 206011809107 PITCH HORN BELL BELL 206 206L3 1182108 SW T/R BLADE LOOSE B C68R K NONE O OTHER IN INSP/MAINT 1 WP 07 288JB 51288 DURING A 100-HOUR INSPECTION, ONE OF THE MECHANICS FOUND THE STUD PN 206-010-744-105 LOOSE IN THE PITCH HORN, PN 206011- 809-107. THE POSSIBLE CAUSE IS UNKNOWN AT THIS TIME. (X) 1 G 7 1 3U H2SW 2001030200022 20010302 00022 NE 2001 3 2 20001101SH028 2 20001016 G 7200 P2A0851 SEAL IAE V2500 V2500A1 NE NR 4 BEARING CRACKED B KB1R K NONE O OTHER IN INSP/MAINT 1 NE 03 PART RECEIVED FOR PENETRANT INSPECTION IAW THE IAE V2500 PROPULSION SYSTEM ENGINE SYSTEM MANUAL, REV 44, SECT 70-23-01, TASK 70-23-01-230-501. PART REJECTED DUE TO CRACKS ON TOP SURFACE. (X) 4 F E311NE 2001020900091 20010209 00091 SW 2001 2 9 20001101SH030 1 20001016 G 6720 407001026101 TUBE BELL 407 407 1182206 SW BELLCRANK DAMAGED B K NONE O OTHER IN INSP/MAINT 1 EA 03 52AZ 290 53380 FOUND DURING SCHEDULED INSPECTION, MECHANICAL DAMAGE FROM AFT BOLTHEAD AT AFT BELLCRANK. REPLACED WITH NEW CONTROL TUBE FROM BELL HELICOPTER. 1 G 7 1 3U O H2SW 2000111500252 20001115 00252 SO 2000 11 15 20001101SH031 2 20001012 G 7322 63338811 CONTROLLER PIPER PA34 PA34220T 7103420 SO CONT O360 TSIO360* 17025 SO STUCK B VJ3R O OTHER O OTHER CR CRUISE 1 WP 07 4123C 244 3449042 THE CONTROLLER PISTON STICK IN. A SPLIT IN POWER SETTING IN-FLIGHT AND ON THE GROUND. CONTROLLER REPLACED. (X) 1 L 7 2 3O 3 O A7SO E9CE 2000111500253 20001115 00253 NE 2000 11 15 20001102SH001 3 20001011 G 6114 660714259 HUB ROTOL R389 R3894123F25 NE MATING FACE CRACKED B MS1R K NONE O OTHER IN INSP/MAINT 1 EA 27 8669 965 DRG876984 HUB ASSEMBLY FOUND CRACKED AT NR 10 AND NR 4 BLADE OPENING AT BEARING ABUTMENT FACE AND SPLIT LINE FACE. HU8 REJECTED F ROM SERVICE. (X) 6 C P30NE 2000112000218 20001120 00218 SO 2000 11 20 20001102SH002 2 20001012 G 7322 63338811 CONTROLLER PIPER PA34 PA34220T 7103420 SO CONT O360 LTSIO360RB SO STUCK B VJ3R O OTHER O OTHER CR CRUISE 1 WP 07 4123C 162 3449042 819505R THE CONTROLLER PISTON STICK IN. A SPLIT IN POWER SETTING IN-FLIGHT AND ON THE GROUND. CONTROLLER REPLACED. (X) 1 L 7 2 3O 3 O A7SO E9CE 2000111500254 20001115 00254 SO 2000 11 15 20001102SH003 2 20001011 G 7322 25765405 SERVO PRECISION PIPER PA34 PA34220T 7103420 SO CONT O360 LTSIO360RB SO FUEL INJECTOR INOPERATIVE B VJ3R O OTHER O OTHER IN INSP/MAINT 1 WP 07 4142N 56 70207608 3449128 322021 UNABLE TO ADJUST MIXTURE AND IDLE WILL NOT STAY SET. (X) 1 L 7 2 3O 3 O A7SO E9CE 2000111500255 20001115 00255 CE 2000 11 15 20001102SH004 2 20001011 G 7322 25765405 SERVO PRECISION PIPER PA34 PA34220T 7103420 SO CONT O360 TSIO360RB 17025 CE FUEL INJECTOR INOPERATIVE B VJ3R O OTHER O OTHER NR NOT REPORTED 1 WP 07 9299E 160 70211310 3449043 819256R UNABLE TO ADJUST MIXTURE AND IDLE. WILL NOT STAY SET. ENGINE QUITS WITH BOOST PUMP ON. (X) 1 L 7 2 3O 3 O A7SO E9CE 2001022100140 20010221 00140 NM 2001 2 21 20001102SH005 1 20000908 G 3240 511531 HOUSING PNEUDRAULICS BOEING 737 737* NM MLG CRACKED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 4005A HOUSING IS CRACKED INSIDE THE MOUNTING HOLE. FATIGUE AND/OR DEFECT IN THE CASTING OF THE HOUSING. (X) 2 L 7 2 4F RT A16WE 2001022100144 20010221 00144 NM 2001 2 21 20001102SH007 1 20000908 G 2782 VALVE BOEING BOEING 737 737* NM SLAT ACTUATOR CRACKED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 123 BLOCKING VALVE ASSY HAD A CRACKED SLEEVE. (X) 2 L 7 2 4F RT A16WE 2001022100145 20010221 00145 NM 2001 2 21 20001102SH008 1 20000914 G 3240 511531 HOUSING PNEUDRAULICS BOEING 737 737* NM MLG CRACKED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 3633 HOUSING IS CRACKED INSIDE THE MOUNTING HOLE. FATIGUE AND/OR DEFECT IN THE CASTING OF THE HOUSING. (X) 2 L 7 2 4F RT A16WE 2001022100056 20010221 00056 NM 2001 2 21 20001102SH009 1 20000914 G 2910 654468311 HOUSING BOEING BOEING 737 737* NM HYD SYSTEM CRACKED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 24699 2030 HOUSING IS CRACKED AT PORT NR 1 CAUSING UNIT TO LEAK WHEN HYDRAULIC PRESSURE IS APPLIED. POSSIBLE CAUSE: FATIGUE. (X) 2 L 7 2 4F RT A16WE 2001022100149 20010221 00149 NM 2001 2 21 20001102SH010 1 20000912 G 2730 401606223 HOUSING MOOG BOEING 727 727* NM CHECK VALVE CORRODED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 596D HOUSING ASSY IS CORRODED ON THE SEAL PLATE SURFACES, BOLT HOLES, AND CHECK VALVE PORTS. HOUSING ASSY IS MADE FROM MAGNE SIUM ALLOY AND IS EXTREMELY SUSCEPTIBLE TO DISSIMILAR METAL CORROSION AND CRACKS. (X) 2 L 7 3 4F RT A3WE 2001022100150 20010221 00150 NM 2001 2 21 20001102SH011 1 20000912 G 2730 401606223 HOUSING MOOG BOEING 727 727* NM CHECK VALVE CORRODED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 07 675R HOUSING ASSY CORRODED ON THE SEAL PLATE SURFACES, BOLT HOLES, AND CHECK VALVE PORTS. HOUSING ASSY IS MADE FROM MAGNESIU M ALLOY AND IS EXTREMELY SUSCEPTIBLE TO DISSIMILAR METAL CORROSION AND CRACKS. (X) 2 L 7 3 4F RT A3WE 2001022100151 20010221 00151 NM 2001 2 21 20001102SH012 1 20000829 G 3240 511531 HOUSING PNEUDRAULICS BOEING 737 737* NM MLG CRACKED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 603 HOUSING HAD A CRACKED MOUNT BOLT HOLE. OVERTORQUING OF MOUNT BOLT IN INSTALLATION. FLAW IN CASTING OF THE HOUSING. (X ) 2 L 7 2 4F RT A16WE 2001022100152 20010221 00152 NM 2001 2 21 20001102SH013 1 20000823 G 2782 108010 HOUSING ROTOL BOEING 727 727* NM SLAT ACTUATOR CRACKED B K NONE O OTHER IN INSP/MAINT 1 NM 01 4390ADEK BODY HAD CRACKS IN BOTH THE EXTEND AND RETRACT PORTS. STRESS AND FATIGUE, TIME IN SERVICE UNKNOWN. (X) 2 L 7 3 4F RT A3WE 2001022100153 20010221 00153 NM 2001 2 21 20001102SH014 1 20000828 G 2782 69358521 SLEEVE BOEING BOEING 737 737* NM SLAT ACTUATOR CRACKED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 360 BLOCKING VALVE SLEEVES ITEMS 31 AND 32 ARE CRACKED. SUBMITTER STATED APPEARED CRACKS OCCURRING UNDER NORMAL USE. (X) 2 L 7 2 4F RT A16WE 2001022100154 20010221 00154 NM 2001 2 21 20001102SH015 1 20000828 G 2782 69358791 SLEEVE BOEING BOEING 737 737* NM SLAT ACTUATOR CRACKED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 360 BLOCKING VALVE SLEEVES ITEMS 31 AND 32 ARE CRACKED. SUBMITTER STATED APPEARED CRACKS OCCURRING UNDER NORMAL USE. (X) 2 L 7 2 4F RT A16WE 2001022100155 20010221 00155 NM 2001 2 21 20001102SH016 1 20000828 G 2782 69358521 SLEEVE BOEING BOEING 737 737* NM SLAT ACTUATOR CRACKED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 384 BLOCKING VALVE SLEEVES ITEMS 31 AND 32 ARE CRACKED. SUBMITTER STATED APPEARED CRACKS WERE OCCURRING UNDER NORMAL USE. (X) 2 L 7 2 4F RT A16WE 2001022100156 20010221 00156 NM 2001 2 21 20001102SH017 1 20000828 G 2782 69358791 SLEEVE BOEING BOEING 737 737* NM SLAT ACTUATOR CRACKED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 384 BLOCKING VALVE SLEEVES ITEMS 31 AND 32 ARE CRACKED. SUBMITTER STATED APPEARED CRACKS WERE OCCURRING UNDER NORMAL USE. (X) 2 L 7 2 4F RT A16WE 2001022100157 20010221 00157 NM 2001 2 21 20001102SH018 1 20000908 G 7830 65445329 HOUSING BOEING BOEING 737 737* NM CONTROL VALVE ERODED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 146593 PORT ''D'' HAD EROSION. POSSIBLE CAUSE: ANGLE OF PORT ''D'' IN THE HOUSING IS APPROXIMATELY 90 DEGREES. (X) 2 L 7 2 4F RT A16WE 2001022100158 20010221 00158 NM 2001 2 21 20001102SH019 1 20000926 G 2782 65447582 STUD BOEING BOEING 737 737* NM SLAT ACTUATOR CHIPPED B K NONE O OTHER IN INSP/MAINT 1 NM 01 0048 LOCKING STUD IS CHIPPING WHERE LOCKING SEGMENTS CONTACT. (X) 2 L 7 2 4F RT A16WE 2001022100159 20010221 00159 NM 2001 2 21 20001102SH020 1 20000926 G 7830 122510 HOUSING ROTOL BOEING 737 737* NM SOLENOID VALVE CRACKED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 7581 2017 BODY IS CRACKED NEXT TO PORT NR 3. (X) 2 L 7 2 4F RT A16WE 2001022100160 20010221 00160 NM 2001 2 21 20001102SH021 1 20000926 G 3240 511531 HOUSING PNEUDRAULICS BOEING 737 737* NM SHUTTLE VAVLE CRACKED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 4224 HOUSING IS CRACKED INSIDE THE THREADED AREA OF THE PLUG HOLE. FATIGUE AND/OR DEFECT IN THE CASTING OF THE HOUSING. (X) 2 L 7 2 4F RT A16WE 2001022100161 20010221 00161 NM 2001 2 21 20001102SH022 1 20000921 G 5513 69778551 SPRING BOEING BOEING 737 737* NM HORIZONTAL STAB CRACKED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 KEO0893 SPRINGS, PN 69-77855-1, ARE BROKEN IN THE AUXILIARY BRAKE SYSTEM CAUSING THE UNIT TO BOND AND JAM. IMPROPER HEAT-TREATI NG, AUSTENITE, FATIGUE AND INCREASED SPRING COIL STRESSES. SUBMITTER STATED SPRINGS PN 69-77855-1 ARE TO BE REPLACED WI TH PN 69-77855-2 SPRINGS ON ACTUATOR ASSEMBLIES MFG PRIOR TO S/N KEO1730 PER BOEING SL 737-SL-27-090-B. (X) 2 L 7 2 4F RT A16WE 2001022100102 20010221 00102 NM 2001 2 21 20001102SH023 1 20001010 G 2923 654468311 HOUSING BOEING BOEING 737 737* NM HYD SYSTEM CRACKED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 16065 2013 HOUSING ASSY HAD MULTIPLE CRACKS IN THE AREA OF PORT NR 1. WEAK POINT OF HOUSING, POSSIBLE OVERTORQUING OF FITTING UPON INSTALLATION. (X) 2 L 7 2 4F RT A16WE 2001022100103 20010221 00103 NM 2001 2 21 20001102SH024 1 20001010 G 2782 65447417 SLEEVE BOEING BOEING 737 737* NM SLAT ACTUATOR CRACKED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 1756T SLEEVE (145) OF THE BLOCKING VALVE ASSY WAS FOUND CRACKED DURING NDI. REMOVED AND REPLACD SLEEVE (145). (X) 2 L 7 2 4F RT A16WE 2001022100104 20010221 00104 NM 2001 2 21 20001102SH025 1 20000928 G 3240 511531 HOUSING PNEUDRAULICS BOEING 737 737* NM SHUTTLE VALVE CRACKED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 8731 3867 HOUSING CRACKED INSIDE THE MOUNTING HOLE. FATIGUE AND/OR DEFECT IN THE CASTING OF THE HOUSING. (X) 2 L 7 2 4F RT A16WE 2001022100105 20010221 00105 NM 2001 2 21 20001102SH026 1 20001011 G 3210 65446925 HOUSING BOEING BOEING 737 737* NM MLG SYSTEM CRACKED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 56579 1033 HOUSING CRACKED IN THE ''D'' PRIORITY AND ''U'' RESTRICTOR PORTS. POSSIBLE CAUSE: FATIGUE, HIGH TSO. (X) 2 L 7 2 4F RT A16WE 2001030200023 20010302 00023 2001 3 2 20001102SH027 4 20001003 G 2561 CELL LIFE VEST FAILED B KQ1R K NONE L NO TEST IN INSP/MAINT 1 EA 07 ONE CELL FAILED THE MFG RECOMMENDED 2 PSI TEST IAW MANUAL 25-60-12. DATE OF MFG: OCT 1986. (X) 2001030200024 20010302 00024 2001 3 2 20001102SH028 4 20001003 G 2561 CELL LIFE VEST FAILED B KQ1R K NONE L NO TEST IN INSP/MAINT 1 EA 07 ONE CELL FAILED THE MFG RECOMMENDED 2 PSI TEST IAW MANUAL 25-60-12. DATE OF MFG OCT 1986. (X) 2001020900092 20010209 00092 EA 2001 2 9 20001102SH029 2 20001016 G 7322 RETAINER ROBSIN R22 R22BETA NM LYC O320 O320B2C 41508 EA GASCOLATOR BROKEN D K NONE O OTHER IN INSP/MAINT 1 WP 23 1118N 3873 1874 1780 DURING A 100-HOUR INSPECTION, THE GASCOLATOR BOWL RETAINING WIRE BROKE WHILE BEING ASSEMBLED. THE BREAK OCCURRED AT THE FLATTENED PART UNDER THE SCREW. IF THE BREAK HAD OCCURRED DURING FLIGHT, IT WOULD HAVE CAUSED A MASSIVE FUEL LEAK. (X ) 1 G 7 1 3O 3 O H10WE E274 2001022600046 20010226 00046 CE 2001 2 26 20001102SH030 1 20001102 G 2752 505211958 ACTUATOR RAYTHN BEECH B300 B300 1159232 CE LT FLAP CRACKED B CGOR K NONE O OTHER IN INSP/MAINT 1 GL 03 CGC5L 1426 378E92 FL87 NOTED DURING REMOVAL OF ACTUATOR FOR ROUTINE 1,200-HOUR LUBE THAT ACTUATOR PISTON WAS CRACKED FOR ENTIRE LENGTH IN AN AP PROXIMATELY STRAIGHT LINE. A NEW P/N''D ACTUATOR AND ACTUATOR SHAFT WAS INCORPORATED ON AIRCRAFT, SN R-129, AND UP. R EPLACED ACTUATOR WITH SUPERSEDING P/N 129-521050-1. DAMAGE MAY HAVE OCCURRED FROM FREEZING OF TRAPPED WATER EXPANDING P ISTON INTERNALLY, OR, BRITTLE METAL CONDITION. (X) 2 L 7 2 4T RT A24CE 2001030100031 20010301 00031 EU 2001 3 1 20001102SH031 1 20001002 G 3246 BOLT BRAERO 1000 BAE1251000A 1500104 EU WHEEL ASSY FAILED B VG4R K NONE O OTHER IN INSP/MAINT 1 SO 35 204R 259017 DUNLOP WHEEL CMM TIE BOLT RUNNING TORQUE CHECK DOES NOT CHECK FULL LENGTH OF THE THREADS. THE TIE BOLTS APPEAR TO BE ST RETCHING FARTHER TOWARD THE SHANK OF THE BOLT. WHEN RUNNING TORQUE WAS CHECKED OVER, THE FULL LENGTH OF THE THREAD, 5 B OLTS FAILED. (X) 2 L 7 2 4F RT A3EU 2001022600047 20010226 00047 NE 2001 2 26 20001102SH032 2 20000806 G 7250 TURBINE AIRTRC AT300 AT301 0390103 SW PWA R1340 R1340AN1 52016 NE ENGINE DAMAGED H K NONE O OTHER IN INSP/MAINT 1 SW 99 5079S 3010116 2P103762 ENGINE DISASSEMBLED 10/4/00. EXTENSIVE DAMAGE TO POWER SECTION OF ENGINE DUE TO ENGINE OPERATION AFTER FIRST KNOWLEDGE OF MALFUNCTION. POSSIBLE CAUSE, LINK ROD BROKE AT LINK PIN AND DUE TO METAL FATIGUE. (X) 1 L 7 1 3R 3 R A9SW 5E2 2001020900093 20010209 00093 SW 2001 2 9 20001102SH033 1 20001013 G 6230 MAST HUGHES 500N 500N 3027374 SW MAIN ROTOR DAMAGED D K NONE O OTHER IN INSP/MAINT 1 WP 07 521FB 9553 0022221970 LN001 FOUND PAINT SEALANT INSIDE MAIN ROTOR MAST TUBE BLISTERED AND FALLING INTO M/R TRANSMISSION GEARBOX. APPEARED THAT M/R TRANSMISSION OIL MOBILE SHC 626 IS NOT COMPATIBLE WITH SEALANT PAINT ON INSIDE OF M/R MAST. 1 G 7 1 3U NC H3WE 2001021300005 20010213 00005 SW 2001 2 13 20001102SH034 1 20001013 G 6230 MAST HUGHES 500N 500N 3027374 SW MAIN ROTOR DAMAGED D K NONE O OTHER IN INSP/MAINT 1 WP 07 523FB 8355 0022221992 LN003 FOUND PAINT SEALANT INSIDE M/R MAST TUBE BLISTERED AND FALLING INTO M/R TRANSMISSION GEARBOX. APPEARED THAT M/R TRANSMI SSION OIL MOBILE SHC 626 IS NOT COMPATIBLE WITH SEALANT PAINT ON INSIDE OF M/R MAST. 1 G 7 1 3U NC H3WE 2001021300006 20010213 00006 SW 2001 2 13 20001102SH035 1 20001013 G 6230 MAST HUGHES 500N 500N 3027374 SW MAIN ROTOR DAMAGED D K NONE O OTHER IN INSP/MAINT 1 WP 07 524FB 8397 0022221999 LN004 FOUND PAINT SEALANT INSIDE MAIN ROTOR MAST TUBE BLISTERED AND FALLING INTO M/R TRANSMISSION GEARBOX. APPEARED THAT M/R TRANSMISSION OIL MOBILE SHC 626 IS NOT COMPATIBLE WITH SEALANT PAINT ON INSIDE OF M/R MAST. 1 G 7 1 3U NC H3WE 2001021300007 20010213 00007 SW 2001 2 13 20001102SH036 1 20001013 G 6230 MAST HUGHES 500N 500N 3027374 SW MAIN ROTOR DAMAGED D K NONE O OTHER IN INSP/MAINT 1 WP 07 525FB 7947 0022222004 LN005 FOUND PAINT SEALANT INSIDE MAIN ROTOR MAST TUBE BLISTERED AND FALLING INTO M/R TRANSMISSION GEARBOX. APPEARED THAT M/R TRANSMISSION OIL MOBIL SHC 626 IS NOT COMPATIBLE WITH SEALANT PAINT ON INSIDE OF M/R MAST. 1 G 7 1 3U NC H3WE 2001021300008 20010213 00008 SW 2001 2 13 20001102SH037 1 20001013 G 6230 MAST HUGHES 500N 500N 3027374 SW MAIN ROTOR DAMAGED D K NONE O OTHER IN INSP/MAINT 1 WP 07 526FB 8121 0022221998 LN006 FOUND PAINT SEALANT INSIDE MAIN ROTOR MAST TUBE BLISTERED AND FALLING INTO M/R TRANSMISSION GEARBOX. APPEARED THAT M/R TRANSMISSION OIL MOBILE SHC 626 IS NOT COMPATIBLE WITH SEALANT PAINT ON INSIDE OF M/R MAST. 1 G 7 1 3U NC H3WE 2001021300009 20010213 00009 SW 2001 2 13 20001102SH038 1 20001013 G 6230 MAST HUGHES 500N 500N 3027374 SW MAIN ROTOR DAMAGED D K NONE O OTHER IN INSP/MAINT 1 WP 07 527FB 7576 0022222003 LN007 FOUND PAINT SEALANT INSIDE MAST TUBE BLISTERED AND FALLING INTO M/R TRANSMISSION GEARBOX. APPEARED THAT M/R TRANSMISSIO N OIL MOBILE SHC 626 IS NOT COMPATIBLE WITH SEALANT PAINT ON INSIDE OF M/R MAST. 1 G 7 1 3U NC H3WE 2001021300010 20010213 00010 SW 2001 2 13 20001103SH001 1 20001013 G 6230 MAST HUGHES 500N 500N 3027374 SW MAIN ROTOR DAMAGED D K NONE O OTHER IN INSP/MAINT 1 WP 07 522FB 8505 0022221949 LN002 FOUND PAINT SEALANT INSIDE MAIN ROTOR MAST TUBE BLISTERED AND FALLING INTO MAIN ROTOR TRANSMISSION GEARBOX. APPEARED TH AT MAIN ROTOR TRANSMISSION OIL MOBILE SHC 626 IS NOT COMPATIBLE WITH SEALANT PAINT ON INSIDE OF MAIN ROTOR MAST. 1 G 7 1 3U NC H3WE 2001022600048 20010226 00048 CE 2001 2 26 20001103SH005 1 20000925 G 5711 SPAR BEECH 23 C23 1151242 CE LT AND RT WING CORRODED B T9ZR K NONE O OTHER IN INSP/MAINT 1 NM 09 7694R 2924 M1294 INSPECTION OF LEFT AND RIGHT WINGS DUE TO ACCIDENT. EXFOLIATION CORROSION IN LOWER SPAR CAP WAS FOUND IN THE SAME AREA ON LEFT AND RIGHT WING SPARS. CORROSION IS LOCATED JUST OUTBOARD OF SPAR SPLICE CONTINUING ON TO WING TIP OR SPAR END. DAMAGE IS EXTREMELY VISIBLE AND SHOULD BE FOUND DURING ROUTINE INSPECTION. WING LEADING EDGE IS FACTORY GLUED TO SPAR IN THIS LOCATION. WING SPAR JUNK. (X) 1 L 7 1 3O A1CE 2001022600050 20010226 00050 2001 2 26 20001103SH008 4 20001016 G 3422 102620422 GYRO CESSNA 172 172R 2072401 CE LYC IO360 IO360L2A EA INSTRUMENT PNL FLUCTUATES D K NONE O OTHER CR CRUISE 1 GL 19 9550Q 916 17280517 L2758651A DIRECTIONAL GYRO PRECESSES ABOUT 5 DEGREES EVERY 10 MINUTES IN-FLIGHT. WITH VACUUM SYSTEM TEST KIT INSTALLED, DG PRECES SES ABOUT ONE-HALF DEGREE EVERY 15 MINUTES. ON THE NEW CESSNA AIRCRAFT, THE INSTRUMENTS AS WELL AS THE INSTRUMENT PANEL ARE HARD MOUNTED TO THE AIRFRAME. SUBMITTER SUSPECTED THE VIBRATIONS CAUSED BY THE RUNNING ENGINE ARE TRANSMITTED DIRE CTLY TO THE INSTRUMENTS AND ARE THE CAUSE OF THE PROBLEM. (X) 1 H 7 1 3O 3 O NT 3A12 1E10 2001022600054 20010226 00054 SW 2001 2 26 20001106SH084 1 20001017 G 3710 PUMP MOONEY M20 M20J 5870219 SW VACUUM PUMP FAILED B K NONE O OTHER IN INSP/MAINT 1 GL 23 CGPKE 240071 PUMP FAILED, 170.5 HOURS. X) 1 L 7 1 3O 2A3 2001021400004 20010214 00004 SW 2001 2 14 20001106SH085 1 20001015 G 6720 CONTROL ROD HUGHES 500N 500N 3027374 SW TAIL ROTOR CHAFED H O OTHER O OTHER NR NOT REPORTED 1 WP 05 954SD 3103 LN079 PILOT REPORTED, DURING THROTTLE ADVANCE ON RUN-UP, A LOUD RUMBLING NOISE AND SEVERE VIBRATION STARTED ABRUPTLY AS TORQUE APPROACHED 40 PERCENT TORQUE. INSP OF ALL SYS BY MECH FOUND NO PROBLEM AREA. TWO SUBSEQUENT RUNS PRODUCED NO REPEAT O F PROBLEM THIRD RUN, SHIP START VIBRATION AGAIN, VERY SEVERE, LOUD NOISE. AFTER SHUT DOWN, TEAR DOWN OF DRIVETRAIN AND CONTROLS, DISCOVERED FAN AFT CONTROL TUBE FOR ANTI-TORQUE CONTROL HAD RUBBED IN 2 PLACES. RUB FND ON FWD PART OF ROD TH AT PASSES THRU FAN GRBX, OUTPUT GEARSHFT ID, REAR CNTRL TUBE, MINOR RUB CENTER OF CNTRL TUBE. SUBMITTER FOUND NO CAUSE FOR THIS CONDITION. MD HELICOPTERS INFORMED. (X) 1 G 7 1 3U NC H3WE 2001022600055 20010226 00055 CE 2001 2 26 20001106SH086 1 20001012 G 5753 052390114 SUPPORT FITTING CESSNA 172 172R 2072401 CE RT FLAP GROOVED B EBVD K NONE O OTHER IN INSP/MAINT 1 GL 09 992CP 842 17280284 DURING INSPECTION, FOUND RT FLAP, INBOARD HINGE, INBOARD FLAP SUPPORT ARM WAS GROOVED BY THE AFT BEARING CHAFING ON IT. REPLACED BOTH THE INBOARD AND OUTBOARD SUPPORT A;RMS. SEB 95-3 ADDRESSES INSPECTING THESE AREAS. (X) 1 H 7 1 3O NT 3A12 2001022600056 20010226 00056 CE 2001 2 26 20001106SH087 1 20001012 G 5753 052390113 SUPPORT FITTING CESSNA 172 172R 2072401 CE RT FLAP GROOVED B EBVD K NONE O OTHER IN INSP/MAINT 1 GL 09 992CP 842 17280284 DURING INSPECTION, FOUND RT FLAP, INBOARD HINGE, INBOARD FLAP SUPPORT ARM WAS GROOVED BY THE AFT BEARING CHAFING ON IT. SUBMITTER STATED THIS CONDITION IS USUALLY FOUND AT THE FORWARD BEARING AREA. FIRST TIME THIS FACILITY HAS SEEN IT IN THE AFT BEARING AREA. REPLACED BOTH THE INBOARD AND OUTBOARD SUPPORT ARMS. SEB 95-3 ADDRESSES INSPECTING THESE AREAS. (X) 1 H 7 1 3O NT 3A12 2001021400005 20010214 00005 NE 2001 2 14 20001107SH001 2 20000525 G 7313 430167601 NOZZLE BOLKMS 117 BK117B1 5626012 EU LYC LTS101 LTS101750B1 41560 NE FUEL MANIFOLD MALFUNCTIONED B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 61LF 507 7230 LE45988EFA IMPROPER NOZZLE SPRAY PATTERN. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U 3 U H13EU E5NE10 2001021400006 20010214 00006 NE 2001 2 14 20001107SH002 2 20001005 G 7250 414129011 TURBINE WHEEL BOLKMS 117 BK117B1 5626012 EU LYC LTS101 LTS101750B1 41560 NE PT SECTION DAMAGED B R7MR O OTHER R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 NM 07 62LF 7163 LE45753EFA LOSS OF TORQUE RETENTION. REPLACED WITH NEW ROTOR, CORRECTED PROBLEM. ROTOR ASSY, INSERTABLE BLADED, POWER TURBINE. ( X) 1 G 7 2 3U 3 U H13EU E5NE10 2001021400007 20010214 00007 NE 2001 2 14 20001107SH003 2 20000720 G 7313 430167601 NOZZLE BOLKMS 117 BK117B1 5626012 EU LYC LTS101 LTS101750B1 41560 NE FUEL MANIFOLD MALFUNCTIONED B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 62LF 651 7163 LE45508EFA IMPROPER NOZZLE SPRAY PATTERN. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U 3 U H13EU E5NE10 2001021400008 20010214 00008 2001 2 14 20001107SH004 4 20000920 G 3457 069010250025 GPS SNIAS 350 AS350B3 8680954 EU COCKPIT OUT OF TOLERANCE B R7MR O OTHER O OTHER NR NOT REPORTED 1 NM 07 103LN 708 3128 VHF COMMUNCIATION TRANSCEIVER/NAVIGATION RECEIVER; GPS OFF COURSE, SOMETIMES BY AS MUCH AS 15 DEGREES. REPLACED WITH NE W UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001021400009 20010214 00009 EU 2001 2 14 20001107SH005 1 20001021 G 2450 45023500 CONTROL BOX UROCOP EC135 EC135P1 8680990 EU ELECTRICAL SYS INOPERATIVE B R7MR O OTHER O OTHER NR NOT REPORTED 1 NM 07 135N 2 EC1350086 ELECTRICAL MASTER BOX, RT FULL OPT, UNIT INOPERATIVE. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U O H88EU 2001021400010 20010214 00010 EU 2001 2 14 20001107SH006 1 20001009 G 3340 02471131 LIGHT SNIAS 350 AS350B3 8680954 EU SEARCH LIGHT SHORTED B R7MR O OTHER O OTHER NR NOT REPORTED 1 NM 07 397LG 71 3268 SEARCH LIGHT ASSEMBLY (SX-5) HAD INTERNAL SHORT. WILL NOT LIGHT. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001021400011 20010214 00011 NE 2001 2 14 20001107SH007 2 20000603 G 7320 TUBE BOLKMS 117 BK117A3 5626015 EU LYC LTS101 LTS101650B1 41560 NE FUEL MANIFOLD WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 158BK 702 7058 LE45291EA TUBE-START ASSIST TO MANIFOLD FEED WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U 3 U H13EU E5NE 2001021400012 20010214 00012 NE 2001 2 14 20001107SH008 2 20000603 G 7230 430124203 BEARING BOLKMS 117 BK117A3 5626015 EU LYC LTS101 LTS101650B1 41560 NE COMPRESSOR CORRODED B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 158BK 702 7058 LE45291EA BEARING - ANNULAR BALL, COMPRESSOR, EXCESSIVE PITTING REPLACED WITH NEW UNIT, CORRECTED. PROBLEM. (X) 1 G 7 2 3U 3 U H13EU E5NE 2001021400013 20010214 00013 NE 2001 2 14 20001107SH009 2 20000603 G 7250 410106701 SEAL BOLKMS 117 BK117A3 5626015 EU LYC LTS101 LTS101650B1 41560 NE 1ST TURB SHROUD WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 158BK 702 7058 LE45291EA SEAL RING - FIRST TURBINE SHROUD, WORN BEYOND SERVICEABLE LIMITS. REPLACED 2 EACH WITH NEW UNITS, CORRECTED PROBLEM. ( X) 1 G 7 2 3U 3 U H13EU E5NE 2001021400014 20010214 00014 NE 2001 2 14 20001107SH010 2 20000603 G 7250 410106802 SPRING BOLKMS 117 BK117A3 5626015 EU LYC LTS101 LTS101650B1 41560 NE SEAL RING WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 158BK 702 7058 LE45291EA SPRING - SEAL RING EXPANDER, WORN BEYOND SERVICEABLE LIMITS. REPLACED 2 EACH WITH NEW UNITS, CORRECTED PROBLEM. (X) 1 G 7 2 3U 3 U H13EU E5NE 2001021400015 20010214 00015 NE 2001 2 14 20001107SH011 2 20000603 G 7230 430151801 BEARING BOLKMS 117 BK117A3 5626015 EU LYC LTS101 LTS101650B1 41560 NE ENGINE WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 158BK 702 7058 LE45291EA BEARING - CYLINDER ROLLER NR 2, WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U 3 U H13EU E5NE 2001021400016 20010214 00016 NE 2001 2 14 20001107SH012 2 20000603 G 7240 413102002 CURL BOLKMS 117 BK117A3 5626015 EU LYC LTS101 LTS101650B1 41560 NE COMBUST CHAMBER DAMAGED B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 158BK 702 7058 LE45291EA CURL ASSY - COMBUSTION CHAMBER, EXCESSIVE BURN IN SOME AREAS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U 3 U H13EU E5NE 2001021400017 20010214 00017 NE 2001 2 14 20001107SH013 2 20000603 G 7250 430144801 SEAL BOLKMS 117 BK117A3 5626015 EU LYC LTS101 LTS101650B1 41560 NE NR 3 BEARING LEAKING B R7MR K NONE K FLUID LOSS IN INSP/MAINT 1 NM 07 158BK 702 7058 LE45291EA SEAL - NR 3 BEARING, LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U 3 U H13EU E5NE 2001021400018 20010214 00018 EU 2001 2 14 20001107SH014 1 20000603 G 7720 430150102 THERMOCOUPLE BOLKMS 117 BK117A3 5626015 EU ENGINE SHORTED B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 158BK 702 7058 THERMOCOUPLE HAD INTERNAL SHORT. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U H13EU 2001021400019 20010214 00019 EU 2001 2 14 20001107SH015 1 20000603 G 7720 430150102 THERMOCOUPLE BOLKMS 117 BK117A3 5626015 EU ENGINE SHORTED B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 158BK 702 7058 THERMOCOUPLE HAD INTERNAL SHORT. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U H13EU 2001021400020 20010214 00020 NM 2001 2 14 20001107SH016 1 20001001 G 6220 900R3101001107 BEARING DOUG MD900 MD900 3027375 NM MAIN ROTOR DEBONDED B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 901CF 33 90000012 CENTER BEARING ASSY, MAIN ROTOR, DEBONDING. (X) 1 G 7 2 3U NC H19NM 2001021400021 20010214 00021 NM 2001 2 14 20001107SH017 1 20001016 G 6220 900R3101001107 BEARING DOUG MD900 MD900 3027375 NM MAIN ROTOR DEBONDED B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 901CF 39 90000012 CENTERING BEARING ASSY, MAIN ROTOR, DEBONDING. (X) 1 G 7 2 3U NC H19NM 2001021400022 20010214 00022 2001 2 14 20001107SH020 4 20000809 G 3160 764B04 BATTERY DOUG MD900 MD900 3027375 NM DISPLAY FAULTY B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 901CF 10 90000012 BMS FAULTS 2 AND 4 TRIGGERED REGULARLY. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U NC H19NM 2001021400023 20010214 00023 NM 2001 2 14 20001107SH021 1 20000911 G 7810 900P2630115102 EXHAUST PIPE DOUG MD900 MD900 3027375 NM ENGINE CRACKED B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 901CF 321 90000012 RIGHT PRIMARY EXHAUST NOZZLE CRACKED BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U NC H19NM 2001021400024 20010214 00024 NM 2001 2 14 20001107SH022 1 20000908 G 6710 900C2010214101 PITCH LINK DOUG MD900 MD900 3027375 NM ROTOR CONTROL WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 901CF 505 90000012 PITCH LINK ASSY, ROTOR CONTROL, WORN BEYOND SERVICEABLE LIMITS. REPLACED 5 EACH WITH NEW UNITS, CORRECTED PROBLEM. (X) 1 G 7 2 3U NC H19NM 2001021400025 20010214 00025 NM 2001 2 14 20001107SH023 1 20000912 G 6720 900F2421545105 BEARING DOUG MD900 MD900 3027375 NM THRUSTER WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 901CF 308 90000012 BEARING RACE, THRUSTER, WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U NC H19NM 2001021400026 20010214 00026 NM 2001 2 14 20001107SH024 1 20000912 G 6720 900R2441017101 SLEEVE DOUG MD900 MD900 3027375 NM NOTAR FAN HUB WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 901CF 584 90000012 SLEEVE, NOTAR FAN HUB, WORN BEYOND SERVICEABLE LIMITS. REPLACED 13 EACH WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U NC H19NM 2001021400027 20010214 00027 NM 2001 2 14 20001107SH025 1 20000916 G 6710 900C3010002105 FRICTION RING DOUG MD900 MD900 3027375 NM COLLECTIVE WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 901CF 2650 90000012 COLLECTIVE FRICTION UNIT LOST FRICTION CONTROL. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U NC H19NM 2001021400028 20010214 00028 NM 2001 2 14 20001107SH026 1 20000309 G 6321 431373 BOLT DOUG MD900 MD900 3027375 NM ROTOR BRAKE WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 901CF 625 90000012 BOLT - ROTOR BRAKE, WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U NC H19NM 2001021400029 20010214 00029 NM 2001 2 14 20001107SH027 1 20000809 G 6321 900D3403006101 LINER DOUG MD900 MD900 3027375 NM ROTOR BRAKE WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 901CF 625 90000012 ROTOR BRAKE LINING WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEMS. (X) 1 G 7 2 3U NC H19NM 2001021400030 20010214 00030 NE 2001 2 14 20001107SH028 2 20000610 G 7250 410106802 SPRING BOLKMS 117 BK117A3 5626015 EU LYC LTS101 LTS101650B1 41560 NE SEAL RING WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 163BK 389 7063 LE45115EA SPRING - SEAL RING EXPANDER, WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U 3 U H13EU E5NE 2001021400031 20010214 00031 NE 2001 2 14 20001107SH029 2 20000610 G 7250 410106701 SEAL BOLKMS 117 BK117A3 5626015 EU LYC LTS101 LTS101650B1 41560 NE 1ST TURB SHROUD WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 163BK 389 7063 LE45115EA SEAL RING - FIRST TURBINE SHROUD, WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U 3 U H13EU E5NE 2001021400032 20010214 00032 NE 2001 2 14 20001107SH030 2 20000907 G 7313 430167601 NOZZLE BOLKMS 117 BK117A3 5626015 EU LYC LTS101 LTS101650B1 41560 NE FUEL MANIFOLD MALFUNCTIONED B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 951AM 7017 LE45111EA FUEL MANIFOLD ASSY HAD IMPROPER NOZZLE SPRAY PATTERN. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U 3 U H13EU E5NE 2001021400033 20010214 00033 NM 2001 2 14 20001108SH002 1 20000813 G 6220 900R3101001107 BEARING DOUG MD900 MD900 3027375 NM MAIN ROTOR DEBONDED B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 901CF 687 90000012 MAIN ROTOR CENTER BEARING ASSEMBLY IS DEBONDING. (X) 1 G 7 2 3U NC H19NM 2001011101205 20010111 01205 2001 1 11 20001108SH003 4 20001016 G 6122 B20908 FLYWEIGHT MCAULY CONT O520 IO520* 17032 SO GOVERNOR DAMAGED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 781836 RELEVANT MAGNETIC PARTICLE INDICATION IN ALL FOUR CORNERS OF FLYWEIGHT DISC. REF: CESSNA. (X) 3 O E5CE 2000120700117 20001207 00117 CE 2000 12 7 20001108SH019 1 20001027 G 3213 07416301 SPRING CESSNA 182 182P 2075816 CE STEP BRACKET CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 21 1933M 18264487 THREE YEARS AFTER REPAIR OF CRACKS IN MAIN LANDING GEAR LEG FAIRING USING A RIVETED PATCH, FOUND THAT HEADS OF RIVETS HA D WORN 7 HOLES (DEPRESSIONS) ABOUT .010 INCH DEEP IN GEAR LEG. CONSULTED CESSNA TECH SERVICE WHO STATED LEG MUST BE REP AIRED OR REPLACED DUE TO DAMAGE THROUGH SHOT PEENED LAYER. REPAIR IMPOSSIBLE LOCALLY BECAUSE NO FACILITY TO SHOT PEEN A REA THAT HAD TO BE GROUND AND POLISHED OUT. SUBMITTER RECOMMENDED THAT ANY PATCHING OF FAIRING BE COVERED WITH ANTI-ABR ASION TAPE. ALSO A GOOD IDEA TO REMOVE FAIRING PERIODICALLY TO EXAMINE GEAR LEG FOR WEAR AND TO RENEW ANTI-ABRASION TAP E. (X) 1 H 7 1 3O NT TA13 2000120700118 20001207 00118 SW 2000 12 7 20001108SH020 1 20001023 G 5753 210104 HINGE MOONEY MOONEY M20 M20J 5870219 SW RT WING INBD HNG BROKEN B K NONE O OTHER IN INSP/MAINT 1 SO 16 191ER 9255 243252 DURING A PRE-FLIGHT INSPECTION, AN INSTRUCTOR NOTICED THE RIGHT FLAP HAD PLAY OR EXCESSIVE TRAVEL WITH FLAPS DOWN. UPON INSPECTION, THE HINGE, P/N 210104-000, WAS FOUND BROKEN JUST BELOW THE AFT HINGE (BOLT). THE BREAK APPEARED TO BE A FR ESH BREAK. (X) 1 L 7 1 3O 2A3 2000120700119 20001207 00119 EA 2000 12 7 20001108SH021 2 20001010 G 8520 LW19341 CAMSHAFT PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA NR 1&2 CAMSHAFTS FAILED H K NONE O OTHER IN INSP/MAINT 1 AL 01 200AK 535 318052180 L79368A STEEL WAS FOUND IN BOTH SPIN-ON FILTER AND OIL SUCTION SCREENS. CAMSHAFT SUSPECTED FAILING, AND PROVEN WITH VISUAL INSP ECTION AND CHECKING THE LIFT OF ALL OF THE LOBES. NR 1 AND NR 2 LOBES WERE ONLY GIVING HALF THE LIFT FROM THE OTHER LOB ES. (X) 1 L 7 2 3O 3 O A20SO E14EA 2000120700120 20001207 00120 SW 2000 12 7 20001108SH022 1 20001018 G 3710 PUMP MOONEY M20 M20J 5870219 SW VACUUM PUMP FAILED B L9PR K NONE O OTHER IN INSP/MAINT 1 GL 23 201DB 58 240026 VACUUM PUMP (215CC) FAILED, 58.1 HOURS. (X) 1 L 7 1 3O 2A3 2000120700121 20001207 00121 SW 2000 12 7 20001108SH023 1 20001015 G 3710 PUMP MOONEY M20 M20J 5870219 SW VACUUM PUMP FAILED B L9PR K NONE O OTHER IN INSP/MAINT 1 GL 23 201DB 39 240026 PUMP (215CC) FAILED AFTER 39 HOURS. (X) 1 L 7 1 3O 2A3 2000120700122 20001207 00122 CE 2000 12 7 20001108SH026 1 20001010 G 7430 C2925010109 IGNITION SWITCH CESSNA 172 172S 2072439 CE STUCK B BF8R O OTHER O OTHER IN INSP/MAINT 1 WP 07 508ER 1843 172S8008 PILOT SQUAWK: IGNITION KEY STICKS IN OFF POSITION. MAINTENANCE REMOVED IGNITION SWITCH AND FOUND BURNED CONTACTS. THI S IS THE SAME SWITCH COVERED BY AD 83-05-06. HOWEVER, THE 172S MODEL IS NOT INCLUDED IN THE AD LIST. SUBMITTER STATED THE 172R''''S MODEL AIRCRAFT SHOULD BE INCLUDED IN AD. ACS KIT NR A3600 INSTALLED. OPERATIONAL CHECK GOOD. AIRCRAFT R ELEASED. (X) 1 H 7 1 3O NT 3A12 2001021400034 20010214 00034 SW 2001 2 14 20001108SH027 1 20001013 G 6320 369D25100507 GEAR HUGHES 500N 500N 3027374 SW M/R TRANSMISSION SPALLED D O OTHER J WARNING INDICATION NR NOT REPORTED 1 WP 07 526FB 4603 1935 2N006 MAIN ROTOR CHIP DETECTORS PICKING UP MAJOR METAL. OPENED GEARBOX AND INSPECTED. FOUND SPALLING OF ALL GEARS. SUBMITTE R SUGGESTED OIL NOT LUBRICATING UNDER LOADS. USING MOBIL SHC 626 PER MDHC NOTICE NL.001.1. (X) 1 G 7 1 3U NC H3WE 2000120700123 20001207 00123 GL 2000 12 7 20001108SH028 3 20001016 G 6110 PROPELLER PIPER PA24 PA24180 7102402 CE MCAULY 3D36C B3D36C424 GL PROP ASSEMBLY VIBRATION B PC7R O OTHER E VIBRATION/BUFFET NR NOT REPORTED 1 WP 09 5785P 24864 000624 NEW MCAULEY STC PROPELLER KIT INSTALLED, ACFT FLOWN FOR BRIEF FLIGHT. AIRCRAFT HAD SUCH VIOLENT VIBRATION, PILOT NO LON GER WILLING TO FLY IT. INSPECTION OF BLADE ANGLES WITH PROP ON ACFT, SHOWED ANGLES WERE NOT IN COMPLIANCE WITH MFG SPEC S BETWEEN BLADES AND COULD CAUSE VIBRATION. MCAULEY REPLACEMENT PROPELLER CHECKED, WHILE NOT PERFECT, WAS INSTALLED. S TILL THERE WAS VIBRATION. BOTH 3-BLADED PROPS WERE DYNAMICALLY BALANCED TO REDUCE VIBRATION. NEW MOTOR MOUNTS INSTALLE D. TEST FLOWN, STILL VIBRATION. FINAL EFFORT, ORIG 2-BLADED HARTZL PROP RE-INSTALLED AND FLOWN TO ITS DESTINATION. SU BMITTER STATED STC NR SA360CH DOES NOT INDICATE RESTRICTIONS ON ACFT MODEL OR SERIAL NUMBER. (X) 1 L 7 1 3O NT 1A15 5 C P58GL 2000120700124 20001207 00124 GL 2000 12 7 20001108SH029 3 20001016 G 6110 PROPELLER PIPER PA24 PA24180 7102402 CE MCAULY 3D36C B3D36C424 GL PROP ASSY VIBRATION B PC7R O OTHER E VIBRATION/BUFFET NR NOT REPORTED 1 WP 09 5785P 24864 000624 NEW MCAULY STC PROPELLER KIT INSTALLED, ACFT FLOWN FOR BRIEF FLIGHT. AIRCRAFT HAD SUCH VIOLENT VIBRATION, PILOT NO LONG ER WILLING TO FLY IT. INSPECTION OF BLADE ANGLES WITH PROP ON ACFT, SHOWED ANGLES WERE NOT IN COMPLIANCE WITH MFG SPECS BETWEEN BLADES AND COULD CAUSE VIBRATION. MCAULEY REPLACEMENT PROPELLER CHECKED, WHILE NOT PERFECT, WAS INSTALLED. ST ILL THERE WAS VIBRATION. BOTH 3-BLADED PROPS WERE DYNAMICALLY BALANCED TO REDUCE VIBRATION. NEW MOTOR MOUNTS INSTALLED . TEST FLOWN, STILL VIBRATION. FINAL EFFORT, ORIG 2-BLADED HARTZL PROP RE-INSTALLED AND FLOWN TO ITS DESTINATION. SUB MITTER STATED STC NR SA360CH DOES NOT INDICATE RESTRICTIONS ON ACFT MODEL OR SERIAL NUMBER. (X) 1 L 7 1 3O NT 1A15 5 C P58GL 2001020200067 20010202 00067 NE 2001 2 2 20001108SH030 2 20001013 G 7200 70BM031070 ENGINE SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1B 6OO30 NE ENGINE BAY STALLED E HWVA O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION NR NOT REPORTED 1 WP 13 8103 2015 4463 PILOT COMPLAINT WAS SMALL COMPRESSOR STALLS ''POPPING SOUND'' OCCURRING WHEN THEY WOULD DROP COLLECTIVE. THIS WAS AN IN FREQUENT OCCURRENCE THAT WAS HAPPENING OVER A PERIOD OF DAYS PRIOR TO INSPECTION OF THE TURBINE SECTION. FULL INSPECTIO N OF THE COMPRESSOR, BLEED VALVE, AND RELATED SYSTEM WERE CONDUCTED, WITHOUT SUCCESS. INSPECTION OF THE HOT END WAS CON DUCTED AND DISCOVERY OF BROKEN TURBINE BLADES WAS DISCOVERED. ENGINE WAS REMOVED AND SHIPPED TO ACRO FOR INSPECTION. ( X) 1 G 7 1 3U 3 U NC H9EU E19EU 2001022600058 20010226 00058 CE 2001 2 26 20001108SH031 1 20000816 G 2820 FUEL LINE CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA FUEL DISTRIBUTE VAPOR LOCK D A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CL CLIMB 1 NM 07 567JW 662 172S8187 L2822651A PILOT REPORTED AT 2,400 RPM, NO CLIMB POWER. TRIED ADJUSTING MIXTURE SETTINGS, NOTHING WORKED. ENGINE COUGHED ON DOWN WIND, ACFT WOULD NOT CLIMB. MAINT ATTEMPTED ENGINE START AFTER PARKING ACFT. ENGINE WAS VAPOR LOCKED, WITH ELEC BOOST PUMP ON AND MIXTURE IN FULL RICH, NO FUEL FLOW COULD BE ATTAINED, NO FUEL WOULD FLOW FROM DRAIN. AFTER ENG COOLED, APPR OX 1 HOUR, ENGINE WAS STARTED, OIL TEMP INDICATED 150 DEGREES FAHRENHEIT. ENGINE OPERATION WAS NORMAL, FULL POWER COULD BE DEVELOPED, AND MAGNETO CHECK NORMAL. ADJ MADE TO THE IDLE MIXTURE TO ENRICH IT, AND THE IDLE SPEED RE-ADJUSTED. AI RCRAFT TEST FLOWN, RELEASED FOR FLIGHT WITH NO ABNORMALTIES NOTED. ENGINE FUEL SERVO REPLACED IN JULY, SAME PROBLEM.(X) 1 H 7 1 3O 3 O NT 3A12 1E10 2000120700125 20001207 00125 CE 2000 12 7 20001108SH032 1 20001023 G 3213 12414231 SADDLE CESSNA 210 T210F 2073422 CE CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 01 6780R 1548 T2100180 DURING ANNUAL INSPECTION AND C/W AD 76-14-07, R2 VISUAL INSPECTION AND DYE PENETRANT INSPECTION OF THE APPROVED P/N 1241 423-1 AND P/N 1241423-2, LANDING GEAR SADDLES SHOWED CRACKS IN THE FORWARD INBOARD RADIUS OF EACH SADDLE. TOTAL TIME O N EACH PART 1,547.89 HOURS IN 23 YEARS OF SERVICE. REPLACED SADDLES WITH NEW P/N 1294151-1 AND P/N 1294151-2 SADDLES. (X) 1 H 7 1 3O 3A21 2000120700126 20001207 00126 CE 2000 12 7 20001108SH033 1 20001023 G 3213 12414232 SADDLE CESSNA 210 T210F 2073422 CE CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 01 6780R 1548 T2100180 DURING ANNUAL INSPECTION AND C/W AD 76-14-07, R2 VISUAL INSPECTION AND DYE PENETRANT INSPECTION OF THE APPROVED P/N 1241 423-1 AND P/N 1241423-2, LANDING GEAR SADDLES SHOWED CRACKS IN THE FORWARD INBOARD RADIUS OF EACH SADDLE. TOTAL TIME O N EACH PART 1,547.89 HOURS IN 23 YEARS OF SERVICE. REPLACED SADDLES WITH NEW P/N 1294151-1 AND P/N 1294151-2 SADDLES. (X) 1 H 7 1 3O 3A21 2000120700127 20001207 00127 CE 2000 12 7 20001108SH034 1 20000913 G 2750 052390138 FLAP CESSNA 172 R172E 2072413 CE RT INBOARD DESTROYED D O OTHER O OTHER NR NOT REPORTED 1 NM 03 7899N 13495 R1720290 AIR LOADS MOVED THE RIGHT FLAP OUTBOARD SO THAT, WHEN RETRACTED, THE INBOARD RIB ASSY - FLAP SUPPORT ARM LEFT, P/N 05239 01-8, WAS BLOCKED BY THE FLAP TRACK SUPPORT STRUCTURE. BOTH FLAP SUPPORT ARMS WERE BENT BACKWARD BY THE FORCE OF THE FL AP MOTOR, FINALLY JAMMING AT ABOUT FIVE DEGREES DOWN. SUBMITTER RECOMMENDED INSTALLATION OF CESSNA SERVICE KIT SK180-44 -1. (X) 1 H 7 1 3O 3A17 2001021400035 20010214 00035 EU 2001 2 14 20001108SH035 1 20001004 G 5302 350A23101920 BULKHEAD SNIAS 350 AS350B2 8680813 EU TAILBOOM CRACKED B RC0R K NONE O OTHER IN INSP/MAINT 1 SW 17 6103X 3262 2723 DURING SCHEDULED INSPECTION WITH HORIZONTAL STABILIZER REMOVED, NOTICED 2 LOOSE RIVETS THAT ATTACH RT AFT GUSSET OF BATT ERY SHELF TO BULKHEAD LOCATED AT BOOM STATION 119.0. THIS IS AN STC RELOCATING THE BATTERY TO THE TAILBOOM. STC NR SH5 117NM, HELD AND INSTALLED BY AMERICAN EUROCOPTER PRIOR TO DELIVERY. RIVET TYPE: CR3212-4. ON ANOTHER OCCASION, 2 OF T HESE 3 ATTACH RIVETS WERE FOUND SHEARED. BELIEVE VIBRATION COULD BE SOURCE OF PROBLEM AS BATTERY IS HELD DOWN BY FWD AN D AFT HOLD-DOWN BRACKETS AT BASE OF BATTERY. NO FEATURE TO HOLD BATTERY DOWN FROM TOP. ALTHOUGH BATTERY FELT SECURE PR IOR TO REMOVAL, FRETTING WAS NOTICED ON THE RT UNDERSIDE AFT HOLD-DOWN BRACKET. (X) 1 G 7 1 3U H9EU 2001022600060 20010226 00060 CE 2001 2 26 20001108SH037 1 20001008 G 3211 2082900 STUD PIPER PA24 PA24180 7102402 CE LANDING GEAR CRACKED B K NONE O OTHER IN INSP/MAINT 1 SW 01 8170P 453 243426 LANDING GEAR STUD IS TO BE INSPECTED EVERY 1,000 HOURS PER AD 97-01-01. CRACKED STUD IN QUESTION HAD ONLY 453 HOURS SIN CE LAST MAGNAFLUX INSPECTION. (X) 1 L 7 1 3O NT 1A15 2001020900094 20010209 00094 CE 2001 2 9 20001108SH038 1 20000918 G 5347 PIN CESSNA 208 208B 2073701 CE CARGO TIE DOWN SHEARED E T0DA K NONE O OTHER UK UNKNOWN 1 CE 03 806BF 208B0806 THE ROLL PIN THAT HOLDS THE LOCK MECHANISM FOR THE CARGO TIE-DOWN FITTING, PN 22555-71, SHEARED CAUSING THE CARGO STRAP TO COME LOOSE AND THE LOAD TO SHIFT. THE LOAD SHIFT CAUSED THE AIRCRAFT IN QUESTION TO FALL ONTO THE TAIL TIE-DOWN AFTE R THE ENGINE WAS SHUT DOWN. (X) 1 H 7 1 3T A37CE 2001030100032 20010301 00032 SO 2001 3 1 20001108SH039 2 20001005 G 8530 CYLINDER CESSNA 180 180 2072602 CE CONT O470 O470J 17026 SO ENGINE SEPARATED B AW0R A UNSCHED LANDING O OTHER TO TAKEOFF 1 GL 15 9248C 31347 461046J DURING WATER TAKEOFF, EXPERIENCED MODERATE ROUGH RUNNING ENGINE, RETURNED TO LAKE. INSPECTION REVEALED ONE CYLINDER HAD SEPARATED BETWEEN BARREL AND HEAD. THESE 6 CYLINDERS HAD APPROX 400 HOURS SINCE BEING CHROMED. OWNER REPLACED ALL CYL INDERS WITH NEW SUPERIOR MILLLENIUM SET. (X) 1 H 7 1 3O 3 O NC 5A6 E273 2001021400036 20010214 00036 GL 2001 2 14 20001108SH040 2 20000922 G 7250 TURBINE WHEEL BELL 407 407 SW ALLSN 250C 250C47B GL NR 1 DAMAGED B O OTHER J WARNING INDICATION IN INSP/MAINT 1 WP 07 905MC 2242 378 53214 CAE847242 DURING APPROACH TO LAND, PILOT EXPERIENCED A LOUD CONTINUOUS NOISE COMING FROM THE ENGINE. ALL ENGINE INSTRUMENTS WERE NORMAL. ENGINE WAS INSPECTED BY MAINT, NO OBVIOUS MALFUNCTIONS WERE NOTED. DURING ENGINE RUN-UP TO ISOLATE ENGINE NOIS E, THE ENGINE CHIP DETECTOR CAUTION LIGHT ILLUMINATED. CHROME SLIVERS WERE FOUND ON BOTTOM PLUG. TEAR-DOWN INSPECTION, FOUND NR 1 TURBINE WHEEL BLADE MISSING AND OTHER BLADES DAMAGED. (X) 1 G 7 1 3U 3 U O H2SW E1GL 2001021400037 20010214 00037 SW 2001 2 14 20001108SH041 1 20001018 G 8000 M835366025M RELAY BELL 407 407 SW STARTER FAILED B K NONE O OTHER IN INSP/MAINT 1 WP 23 911FS 312 53424 START DELAY FAILED/INTERMITTENT. DURING START SEQUENCE, REPLACED PART PER BHT TECH REP. (X) 1 G 7 1 3U O H2SW 2000120700116 20001207 00116 SO 2000 12 7 20001108SH042 1 20001027 G 7120 6711949 MOUNT PIPER PA28 PA28R200 7102811 SO ENGINE MOUNT BROKEN G O OTHER P NO WARNING INDICATION IN INSP/MAINT 1 EA 23 9392N 28R35102 DURING THE COURSE OF A 100 HR INSPECTION, MAINTENANCE DISCOVERED THE ENGINE MOUNT, P/N 67119-49, COMPLETELY BROKEN AT TH E TOP RIGHT HAND SIDE OF THE COMPONENT. THIS WAS NOT SIMPLY A CRACK, BUT RATHER, THE TUBE WAS COMPLETELY BROKEN THROUGH. THIS FAILURE IS THE SUBJECT OF PIPER SERVICE LETTER 568. THE NATURE OF THIS FAILURE IS SUCH THAT IT COULD LEAD TO SEP ARATION OF THE ENGINE AND SUBSEQUENT LOSS OF CONTROL OF THE AIRCAFT. A SEARCH OF THE SDR DATABASE REVEALED THAT SEVEN O THER FAILURES ARE ON RECORD FOR THIS SAME PART NUMBER. SUBMITTER RECOMMENDS THESE MOUNTS BE CLOSELY INSPECTED AT EACH 1 00 HOURS AS STIPULATED BY THE SERVICE LETTER. FOR A COPY OF THIS SERVICE LETTER, CONTACT THE NEW PIPER AIRCRAFT. (X) 1 L 7 1 3O 2A13 2001011101225 20010111 01225 SO 2001 1 11 20001108SH043 1 20001108 G 7120 6711949 MOUNT PIPER PA28 PA28R200 7102811 SO ENGINE CRACKED G K NONE O OTHER IN INSP/MAINT 1 EA 23 9330N 28R35030 DURING THE COURSE OF A 100 HR INSPECTION, MAINTENANCE DISCOVERED THE ENGINE MOUNT P/N 67119-49, WAS CRACKED AT THE TOP L EFT SIDE OF THE COMPONENT. THIS FAILURE IS THE SUBJECT OF PIPER SERVICE LETTER 568. THE NATURE OF THIS FAILURE IS SUCH T HAT IT COULD LEAD TO SEPARATION OF THE ENGINE AND SUBSEQUENT LOSS OF CONTROL OF THE AIRCRAFT. A SEARCH OF THE SDR DATAB ASE REVEALED THAT SEVERAL OTHER SIMILAR FAILURES ON ENGINE MOUNTS HAVE OCCURRED. IN FACT, THE OPERATOR OF THIS AIRCRAFT EXPERIENCED THE SAME FAILURE ON ANOTHER PIPER ARROW JUST WEEKS EARLIER. THE TWO AIRCRAFT ARE ONLY SEVERAL SERIAL NUMBER S APART. SUBMITTER RECOMMENDS THAT THESE ENGINE MOUNTS BE CLOSELY INSPECTED EVERY 100 HRS AS STIPULATED IN PIPER SM.(X) 1 L 7 1 3O 2A13 2001011104470 20010111 04470 2001 1 11 20001109SH004 1 20001017 G 7922 639305 VERNATHERM CONT O520 TSIO520CE 17040 SO OIL TEMP VALVE BROKEN H K NONE O OTHER IN INSP/MAINT 1 GL 03 335 268574R THE VERNATHERM SHAFT WAS BENT AND UPON INVESTIGATION, FOUND BROKEN AT THE ROLL PIN HOLE. ONLY A COUPLE THREADS OF THE S HAFT INTO THE RETAINING NUT WAS HOLDING THE UNIT TOGETHER. ENGINE REBUILT ON 10-17-97. (X) 3 O E8CE 2001011104471 20010111 04471 2001 1 11 20001109SH005 1 20001006 G 7920 F07K311 OIL FILTER FILTER BASE CRACKED G K NONE K FLUID LOSS IN INSP/MAINT 1 EA 21 DURING AN INCOMING MATERIAL INSPECTION, A REPAIR STATION NOTED WHAT APPEARED TO BE A MANUFACTURING INDUCED CRACK ON THE INSIDE PORTION OF THE FILTER BASE RING WHICH RETAINS THE RUBBER GASKET. THIS CRACK IS APPROXIMATELY .0625 INCH IN LENGT H AND APPEARED TO HAVE BEEN FORMED WHEN THE RING WAS CRIMPED TO THE BASE. THE REPAIR STATION CHECKED THEIR STOCK OF FIL TERS AND FOUND NO FURTHER INSTANCES OF THIS CONDITION. (X) 2000111600179 20001116 00179 CE 2000 11 16 20001109SH006 1 20001101 G 3240 5100106159 LINE CESSNA 421 421C 2076016 CE UNDER RT CREW ST LEAKING H K NONE K FLUID LOSS IN INSP/MAINT 1 WP 07 748CA 421C0905 RIGHT BRAKE INOPERATIVE. BRAKES WERE SERVICED AND BLED, THEN MECHANIC FOUND HYDRAULIC FLUID LEAKING FROM BOTTOM OF AIRC RAFT. ON FURTHER INSPECTION, LINE PN 5100106-159 WAS FOUND TO HAVE PIN HOLES IN IT. SUBMITTER RECOMMENDED: INSPECT TH IS LINE IN MORE DETAIL DURING 100-HOUR INSPECTION. (X) 1 L 7 2 3O A7CE 2000111600180 20001116 00180 CE 2000 11 16 20001109SH007 1 20001026 G 5510 16962000165 STABILATOR BEECH 23 B24R 1151253 CE AFT CRACKED A BIKA K NONE O OTHER IN INSP/MAINT 1 EA 21 1991L 2000 MC431 DURING INSPECTIONS OF UNDERSIDES OF STABILATORS ON BEECH SIERRAS, SUNDOWNERS, HAVE FOUND DEFECTS RANGING FROM WORKING RI VETS TO CRACKS IN LOWER SKINS. PROBLEM IS CENTERED APPROX 6 INCHES OUT FROM FUSELAGE ON BOTH SIDES. MECHANICS HAVE INS TALLED OVERSIZED RIVETS, ADDITIONAL RIVETS, PATCHES. BEECH ADDRESSES THIS PROBLEM IN SI 1167, OFFERS A P/N FOR IMPROVED AFT CENTER SPAR CALLING FOR NEW SPAR TO BE BONDED TO SKINS. REPLACED AFT CENTER SPARS, AFT LOWER SKINS ON 2 SIERRAS, I N ONE, SPARS CRACKED WEAKENED BY 0.250 INCH CHERRY MAX RIVETS AND TRIPPLING OF RIVETS. ORIG SPAR DOES NOT OFFER ENOUGH SUPPORT TO CONTROL OIL CANNING EVEN THOUGH EXISTING SPAR MAY NOT BE CRACKED, WORKING, OR OVERSIZED. (X) 1 L 7 1 3O A1CE 2000111600181 20001116 00181 CE 2000 11 16 20001109SH008 1 20001026 G 5510 16962000165 STABILATOR BEECH 23 C24R 1151254 CE AFT CRACKED A BIKA K NONE O OTHER IN INSP/MAINT 1 EA 21 6710D 2000 MC709 DURING INSPECTIONS OF UNDERSIDES OF STABILATORS ON BEECH SIERRAS, SUNDOWNERS, HAVE FOUND DEFECTS RANGING FROM WORKING RI VETS TO CRACKS IN LOWER SKINS. PROBLEM IS CENTERED APPROX 6 INCHES OUT FROM FUSELAGE ON BOTH SIDES. MECHANICS HAVE INS TALLED OVERSIZED RIVETS, ADDITIONAL RIVETS, PATCHES. BEECH ADDRESSES THIS PROBLEM IN SI 1167, OFFERS A P/N FOR IMPROVED AFT CENTER SPAR CALLING FOR NEW SPAR TO BE BONDED TO SKINS. REPLACED AFT CENTER SPARS, AFT LOWER SKINS ON 2 SIERRAS, I N ONE, SPARS CRACKED WEAKENED BY 0.250 INCH CHERRY MAX RIVETS AND TRIPPLING OF RIVETS. ORIG SPAR DOES NOT OFFER ENOUGH SUPPORT TO CONTROL OIL CANNING EVEN THOUGH EXISTING SPAR MAY NOT BE CRACKED, WORKING, OR OVERSIZED. (X) 1 L 7 1 3O A1CE 2000111600183 20001116 00183 GL 2000 11 16 20001109SH010 3 20000904 G 6110 C4451 FERRULE MCAULY CESSNA 206 U206F 2073333 CE MCAULY 3A32C D3A32C90 GL BLADE CRACKED B MFNY K NONE O OTHER IN INSP/MAINT 1 EA 33 OONRJ 318 CA318YS 3579 860281 PROPELLER SENT FOR REPAIR OF OIL LEAK. AFTER INVESTIGATION OF THE PROPELLER AND DISASSEMBLY, FOUND THE OIL LEAK OCCURRE D BECAUSE ONE BLADE FERRULE HAD BEEN CRACKED IN THE BEARING AREA. (X) 1 H 7 1 3O A4CE 5 C P21EA 2000111600184 20001116 00184 CE 2000 11 16 20001109SH011 1 20001030 G 5712 57222082 RIB CESSNA 441 441 2076020 CE LT WING CRACKED B WTXR K NONE O OTHER IN INSP/MAINT 1 NM 07 185GA 4375 4410066 DURING A PHASE INSPECTION, FOUND A 1.1 INCH CRACK IN LEFT WING CANTED RIB. CRACK STARTING AFT OF THE FORWARD SPAR AND E XTENDED AFT ALONG THE RIB RADIUS. SUBMITTER STATED CESSNA NO LONGER WILL ALLOW STOP DRILLING OF THIS CRACK, SO THE RIB WAS REPLACED. (X) 1 L 7 2 3T RT A28CE 2000111600185 20001116 00185 CE 2000 11 16 20001109SH012 1 20001020 G 5712 57222061 RIB CESSNA 441 441 2076020 CE RT WING CRACKED B WTXR K NONE O OTHER IN INSP/MAINT 1 NM 07 185GA 4375 4410066 DURING A PHASE INSPECTION, FOUND A .9 INCH CRACK IN RIGHT WING CANTED RIB TOP CAP. CRACK STARTS AFT OF FORWARD SPAR AND EXTENDS AFT. FOR MANY YEARS, CESSNA HAS ALLOWED THESE CRACKS TO BE STOP DRILLED, BUT NO LONGER WILL ACCEPT THIS REPAIR . NO PARTS ARE AVAILABLE TO REPLACE THIS RIB. STOP DRILLED CRACK IAW 8110-3 DATED 10-19-00 WHICH WILL ALLOW 100 HOURS BEFORE PERMANENT REPAIR. (X) 1 L 7 2 3T RT A28CE 2000111600186 20001116 00186 SO 2000 11 16 20001109SH013 2 20001006 G 8530 HOSE CESSNA 150 150L 2071826 CE CONT O200 O200A 17020 SO MISINSTALLED H K NONE R PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 SW 99 11955 15075733 251631 INTAKE BOOT SLID OFF INTAKE TUBE, MOST LIKELY CAUSED BY IMPROPER POSITIONING OF WORM GEAR HOSE CLAMP. THIS CAUSED EXCES SIVE LEAN MIXTURE. THE RESULT WAS PISTON FAILURE, WRIST PIN FAILURE, AND CYLINDER FAILURE. (X) 1 H 7 1 3O 3 O 3A19 E252 2000111600187 20001116 00187 EA 2000 11 16 20001109SH014 2 20001030 G 8530 SL3600WA20P CYLINDER CESSNA 177 177B 2073708 CE LYC O360 O360A1F6 41514 EA NR 2 BROKEN D O OTHER O OTHER NR NOT REPORTED 1 WP 19 13472 17702425 L2112736A THE PUSH ROD TUBE RETAINER CLIPS, SL 14995, IN NR 2, NR 3, AND NR 4 VALVE COVERS WERE BROKEN OFF AT THE BOLT HEADS. DET ECTION WAS DUE TO A DENT IN THE VALVE COVER OF NR 2 CYLINDER. SUBMITTER STATED IT APPEARED TO BE A MATERIAL DEFECT. (X ) 1 H 7 1 3O 3 O A13CE E286 2000111600188 20001116 00188 EA 2000 11 16 20001109SH015 2 20001030 G 8530 SL3600WR20P CYLINDER CESSNA 177 177B 2073708 CE LYC O360 O360A1F6 41514 EA NR 3 BROKEN D O OTHER O OTHER NR NOT REPORTED 1 WP 19 13472 283 17702425 L2112736A THE PUSH ROD TUBE RETAINER CLIPS, PN SL14995, IN NR 2, NR 3, AND NR 4 VALVE COVERS WERE BROKEN OFF AT THE BOLT HEADS. D ETECTION WAS DUE TO A DENT IN THE VALVE COVER OF NR 2 CYLINDER. SUBMITTER STATED IT APPEARED TO BE A MATERIAL DEFECT. (X) 1 H 7 1 3O 3 O A13CE E286 2000111600189 20001116 00189 EA 2000 11 16 20001109SH016 2 20001030 G 8530 SL3600WA20P CYLINDER CESSNA 177 177B 2073708 CE LYC O360 O360A1F6 41514 EA NR 4 BROKEN D O OTHER O OTHER NR NOT REPORTED 1 WP 19 13472 283 17702425 L2112736A THE PUSH ROD TUBE RETAINER CLIPS, PN SL14995, IN NR 2, NR 3, AND NR 4 VALVE COVERS WERE BROKEN OFF AT THE BOLT HEADS. D ETECTION WAS DUE TO A DENT IN THE VALVE COVER OF NR 2 CYLINDER. SUBMITTER STATED IT APPEARED TO BE A MATERIAL DEFECT. (X) 1 H 7 1 3O 3 O A13CE E286 2000111600190 20001116 00190 CE 2000 11 16 20001109SH020 1 20001019 G 5300 STRINGER CESSNA 500 550 2076604 CE AILERON BELLCK CORRODED B WTXR K NONE O OTHER IN INSP/MAINT 1 NM 07 387SC 7566 5500142 WHILE INVESTIGATING A PROBLEM OF FUEL IN THE CABIN, AN AREA OF SEVERE CORROSION WAS FOUND. THE CORROSION WAS LOCATED IN A STRINGER UNDER THE AILERON BELLCRANK UNDER THE AFT CABIN FLOOR. THE CORRODED STRINGER IS IN THE SAME LOCATION OF A S IMILARLY CORRODED STRINGER FOUND ON AN S550 AIRCRAFT, 5500024. SUBMITTER STATED IT SHOULD BE NOTED THE AREA IN QUESTION IS NOT EASILY SEEN. (X) 1 L 7 2 4F A22CE 2000111600191 20001116 00191 CE 2000 11 16 20001109SH024 1 20001020 G 5712 57222061 RIB CESSNA 441 441 2076020 CE RT WING CRACKED B WTXR K NONE O OTHER IN INSP/MAINT 1 NM 07 445AE 8990 4410043 DURING A PHASE INSPECTION, FOUND THE CRACK IN THE RIGHT CANTED RIB HAD PROGRESSED BEYOND THE PREVIOUSLY INSTALLED STOP D RILLS. AIRCRAFT WAS RETURNED TO THE OPERATOR WITH A ''FERRY PERMIT'' FOR REPAIR. (X) 1 L 7 2 3T RT A28CE 2000111600192 20001116 00192 SW 2000 11 16 20001109SH025 1 20001017 G 7922 639305 VERNATHERM MOONEY M20 M20K 5870220 SW CONT O360 TSIO360MB 17025 CE OIL TEMP VALVE BENT H K NONE O OTHER IN INSP/MAINT 1 GL 03 252DX 1088 250580 279249R RETAINING NUT ROLL PIN TO SECURE THE NUT. THE SHAFT ON WHICH THE NUT IS INSTALLED WAS BENT JUST BEHIND THE NUT. SUBMIT TER HAS SEEN SEVERAL NOW WITH THIS CONDITION AND THEY ARE ALL FROM FACTORY REMAINS OR NEW ENGINES FROM RECENT YEARS. TH IS ONE REBUILT 2-8-95. THE BEND IS IN THE DIRECTION OF THE ROLL PIN. IT COULD BE CAUSED AT MANUFACTURE WHEN THE PIN IS INSTALLED. IT APPEARED THE END OF THE BRASS SHAFT WAS MACHINED. IT COULD OCCUR AT THAT TIME, IF SHAFT IS NOT SUPPORTE D. SUBMITTER HAS ADVISED TCM. (X) 1 L 7 1 3O 3 O 2A3 E9CE 2000111600193 20001116 00193 CE 2000 11 16 20001109SH026 1 20001017 G 6100 NUT CESSNA 337 337 2075702 CE MCAULY 2AF34C D2AF34C61 GL PROPELLER LOOSE B W59R K NONE K FLUID LOSS IN INSP/MAINT 1 WP 07 2181X 3370081 760428 THE REAR PROPELLER WAS SUBMITTED FOR REPAIR OF A LOOSE BLADE FOUND DURING AN ANNUAL INSPECTION. UPON DISASSEMBLY, FOUND THE RED DYE OIL REQUIRED BY AD 91-15-04 HAD BEEN REMOVED AND THE PROPELLER WAS HAND PACKED WITH GREASE. THE LOOSE BLAD E CONTAINED A CRACKED BLADE RETENTION NUT, AND THE BLADE BEARING HAD FAILED ALLOWING THE STEEL ROLLERS END BEARING SPACE R TO ROLL LOOSE IN THE HUB. (X) 1 H 7 2 3O A6CE 5 C P5EA 2000111600194 20001116 00194 SO 2000 11 16 20001109SH027 1 20001014 G 8120 46C19836D BEARING PIPER PA32 PA32R301T 7103220 SO LYC O540 TIO540A1A 41532 EA FAILED H K NONE O OTHER IN INSP/MAINT 1 SW 99 289JG 641 3257030 L992261A THE TURBO WAS HUNG UP ON THE BEARINGS AND COULD NOT ROTATE UNTIL FORCE WAS APPLIED TO THE COMPRESSOR. THEN THERE WAS DR AGGING ON THE BEARINGS AND TURBINE AGAINST THE HOUSING. THERE WAS A LOT OF END-PLAY IN THE TURBINE SHAFT. (X) 1 L 7 1 3O 3 O A3SO E14EA 2000111600195 20001116 00195 EA 2000 11 16 20001109SH028 2 20001017 G 8520 11754 CAMSHAFT PIPER PA28 PA28R201 7102816 SO LYC O360 IO360C1C6 41514 EA ONE LOBE WORN H K NONE O OTHER IN INSP/MAINT 1 GL 09 3327M 580 28R7837112 L1839751A AFTER FINDING FINE FERROUS METAL IN OIL FILTER , FURTHER INVESTIGATION LED TO THE FAILED CAMSHAFT AND TAPPETS. BOTH TAP PETS RIDE ON THE SAME LOBE. SUBMITTER STATED THESE WERE RECONDITIONED PARTS. (X) 1 L 7 1 3O 3 O 2A13 1E10 2001011104473 20010111 04473 2001 1 11 20001109SH029 2 20001017 G 8520 72877 LIFTER PIPER PA28 PA28R201 7102816 SO FACES WORN H K NONE O OTHER IN INSP/MAINT 1 GL 03 3327M 580 28R7837112 AFTER FINDING FINE FERROUS METAL IN OIL FILTER , FURTHER INVESTIGATION LED TO THE FAILED CAMSHAFT AND TAPPETS. BOTH TAP PETS RIDE ON THE SAME LOBE. SUBMITTER STATED THESE WERE RECONDITIONED PARTS. (X) 1 L 7 1 3O 2A13 2001022600061 20010226 00061 CE 2001 2 26 20001109SH032 1 20001012 G 7160 145720210 VALVE CESSNA 172 R172G 2072421 CE CONT O360 IO360DB 17025 SO INDUCT AIR BOX BROKEN D K NONE O OTHER IN INSP/MAINT 1 WP 25 7751L R1720427 ON ENGINE TBO CHANGE BEFORE INSTALLING THE INDUCTION AIR BOX, DISCOVERED THAT ONE HALF OF THE FLASHBACK VALVE HAD BROKEN AND WAS BACK IN THE AIR BOX. BOTH HALVES AND SPRING WERE REPLACED. (X) 1 H 7 1 3O 3 O 3A17 E1CE 2001022700001 20010227 00001 NM 2001 2 27 20001109SH033 2 20001017 G 7321 254911842 FUEL CONTROL GULSTM 690TP 690A 0141722 SW GARRTT TPE331 TPE3315251K NM LT ENGINE FLUCTUATES B K NONE O OTHER IN INSP/MAINT 1 SO 03 81446 1521 11327 P79653 DURING THE RUN AND ADJUSTMENT AFTER THE INSTALLATION OF THE FUEL CONTROL, WHEN THE POWER LEVER WAS ADVANCED ABOVE THE FL IGHT IDLE GATE WITH THE CONDITION LEVER IN THE HIGH POSITION, THE ENGINE GOES TO FULL POWER WITHIN A .50 INCH ABOVE THE FLIGHT GATE. WHEN THE MAX POWER SCREW WAS ADJUSTED OUT, THE POWER LEVER RESPONSE WAS STILL TOO QUICK AND ENGINE FAILED TO MAKE MORE THAN 650 SHP. THIS ENGINE ALSO SURGED WHEN THE POWER LEVER WAS RETARDED TO GROUND IDLE. (X) 1 H 7 2 3T 4 T 2A4 E2WE 2001022600062 20010226 00062 SO 2001 2 26 20001109SH034 1 20001002 G 8120 LW16858 WASTEGATE VALVE PIPER PA32 PA32301T 7103209 SO LYC O540 TIO540S1AD 41532 EA TURBOCHARGER MISSING D O OTHER R PARTIAL RPM/PWR LOSS CR CRUISE 1 WP 09 81573 328024004 L837961A PILOT REPORTED UNABLE TO DEVELOP NORMAL POWER AT ALTITUDE. INSPECTION REVEALED 30 PERCENT - 40 PERCENT OF WASTEGATE BUT TERFLY VALVE MISSING. UNIT REMOVED, REPAIRED AND REINSTALLED. ENGINE HAD APPROX 730 HOURS SINCE FACTORY OVERHAUL. BUT TERFLY WAS NORMAL AT THAT TIME. AIRFRAME TT, APPROX 3,600 HOURS. UNABLE TO DETERMINE IF WASTEGATE ASSY HAD BEEN REPAIR ED OR REPLACED PREVIOUSLY. NO DAMAGE WAS DONE TO TURBINE, SO POSSIBLY BUTTERFLY MUST HAVE DISINTEGRATED SLOWLY OVER A P ERIOD OF TIME. (X) 1 L 7 1 3O 3 O A3SO E14EA 2001022600063 20010226 00063 CE 2001 2 26 20001109SH036 1 20001009 G 3230 MS244615 BEARING CESSNA 414 414 2075908 CE N/G DRAG BRACE LOOSE D K NONE O OTHER IN INSP/MAINT 1 EA 23 8HM 4140620 FOUND NOSE GEAR DRAG BRACE BEARINGS LOOSE. NOTE: MOST NEEDLE BEARINGS WERE MISSING. DRAG BRACE P/N 5042020-3. (X) 1 L 7 2 3O RT A7CE 2001022600064 20010226 00064 CE 2001 2 26 20001109SH037 1 20001010 G 3250 12430714 TUBE CESSNA 210 210 2073402 CE NLG BROKEN D K NONE O OTHER LD LANDING 1 SO 09 9660T 2342 57460 THE TUBE WELDED ASSY WHICH STEERS NOSE GEAR, ARM BROKE THE WELD ON THE TUBE WHICH ALOWED THE NOSE WHEEL TO SWIVEL AND CO LLAPSED THE NOSE WHEEL ON LANDING. (X) 1 H 7 1 3O RT 3A21 2001020900096 20010209 00096 CE 2001 2 9 20001109SH038 1 20001022 G 5330 26110002 SKIN CESSNA 208 208B 2073701 CE FUSELAGE CORRODED A HSYA K NONE O OTHER IN INSP/MAINT 1 NM 05 904FE 6433 208B0004 HNL - MAINTENANCE FOUND FUSELAGE SKIN PANEL, UPPER CENTER FORWARD, CORRODED. PANEL CORRODED BEYOND LIMITS FOR 2024T3, . 032 INCH THICK. REMOVED AND REPLACED PANEL ASSEMBLY IAW C208 SRM 53-10-10 AND SRM 51-40-00. (X) 1 H 7 1 3T A37CE 2001022600065 20010226 00065 CE 2001 2 26 20001109SH039 1 20001024 G 5513 115610010231 SKIN BEECH 99 99A 1154003 CE LT STABILATOR CRACKED B TIMR K NONE O OTHER IN INSP/MAINT 1 NM 07 955AA 30472 U128 DURING ROUTINE INSPECTION, A CRACK WAS FOUND ON THE LEFT STABILATOR LOWER SKIN. (X) 1 L 7 2 3T A14CE 2001022600067 20010226 00067 EA 2001 2 26 20001113SH002 2 20000930 G 7322 CF30766 FLOAT PIPER PA28 PA28161 7102803 SO LYC O320 O320B2B 41508 EA CARBURETOR MISALIGNED G A UNSCHED LANDING Y ENGINE STOPPAGE NR NOT REPORTED 1 WP 23 9372C 55 75065519 287816467 COMPLETE ENGINE FAILURE WITH FORCED LANDING. DISCOVERED CARBURETOR FLOODING ENGINE. UPON DISASSEMBLY OF CARBURETOR WIT H FAA REP, FOUND FLOAT HANGING UP SIDE OF BOWL. FLOAT APPEARS TO BE MISALIGNED DURING ASSSEMBLY AND SOLDERING OF FLOAT. (X) 1 L 7 1 3O 3 O 2A13 E274 2001021400038 20010214 00038 WP 2001 2 14 20001113SH006 1 20001027 G 6220 5143711 HUB HILLER UH12 UH12E 4360122 WP MAIN ROTOR CRACKED B K NONE O OTHER IN INSP/MAINT 1 NM 09 1451 PRIOR TO THE INSTALLATION OF MAIN ROTOR HEAD ASSY, SN 493, AD 73-20-03 WAS ACCOMPLISHED. THE MAIN ROTOR HUB, SN 493, WA S FOUND CRACKED INSIDE THE HUB IN THE AREA OF THE CONTROL ROTOR STUDS. METHOD OF INSPECTION WAS DYE PENETRANT. THE ASS Y RECORDS INDICATE THE ASSY HAD ZERO HOURS SINCE OVERHAUL. (X) 1 G 7 1 3O 4H11 2001021400039 20010214 00039 GL 2001 2 14 20001113SH007 2 20001024 G 7310 B-NUT BELL 206 206L4 1182110 SW ALLSN 250C 250C30P 03013 GL FUEL CONTROL LOOSE G A UNSCHED LANDING R Y J PARTIAL RPM/PWR LOSS ENGINE STOPPAGE WARNING INDICATION NR NOT REPORTED 1 SW 03 58SN 52119 AIRCRAFT WAS LEVEL FLIGHT WHEN ENGINE DECELERATED AND QUIT. PRELIMINARY INSPECTION FOUND PC LINE B-NUT AT FUEL CONTROL LOOSE. LINE WAS REMOVED, INSPECTED, AND RE-INSTALLED. ENGINE GROUND RUN. (X) 1 G 7 1 3U 3 U NC H2SW E1GL 2001020200068 20010202 00068 SW 2001 2 2 20001113SH008 1 20001009 G 7910 206061505109 DRAIN LINE BELL 206 206L1 1182107 SW ENGINE OIL TANK CRACKED E TUSA O OTHER O OTHER NR NOT REPORTED 1 SO 09 911SA 6964 45383 OIL TANK DRAIN VALVE DISCOVERED WET DURING 100-HR INSP. NO STATIC LEAKS NOTED AFTER CAREFUL INSP, ALTHOUGH A SMALL SEEP WAS FOUND DURING ACFT RUN-UP. SMALL STRESS CRACKS FOUND WITH 10X MAGNIFYING GLASS WITHIN THE RADIUS BETWEEN DRAIN FITT ING AND TANK BOTTOM SHEET METAL ADJACENT TO WELDED AREA. SUBSEQUENT PRESS TEST ON THIS TANK SHOWED THE LEAK WOULD OCCUR WITH LESS THAN 3 POUNDS OF PRESSURE. THESE STRESS CRACKS POSSIBLY WERE CAUSED BY 20 YEARS OF OIL CHANGES, AND THE CLOS E PROXIMITY OF SCAVENGE OIL FILTER TO THE DRAIN VALVE. SUBMITTER RECOMMENDED VERYIFYING OIL TANK DRAIN HOSE DOES NOT CO ME IN CONTACT WITH SCAVENGE FILTER HOUSING, AND CARE USED DURING REMOVAL OF AIRFRAME MOUNTED SCAVENGE FILTER. (X) 1 G 7 1 3U H2SW 2001021400040 20010214 00040 GL 2001 2 14 20001113SH010 2 20000819 G 7210 6893672 PINION GEAR ALLSN BELL 407 407 SW ALLSN 250C 250C47B GL GEARBOX MAKING METAL B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 417AL 591 CAG47188 53054 CAE847188 DISASSEMBLED GEARBOX DUE TO METAL IN OIL. CLEANED AND INSPECTED, FOUND EXCESSIVE GALLING ON PINION GEAR AND TORQUEMETER GEAR TEETH. PINION GEAR HAD EXCESSIVE GALLING ON GEAR TEETH DUE TO IMPROPER MESHING OF T/M AND PINION GEARS. SECONDAR Y DAMAGE: T/M GEAR PN 23071895, SN NN146407, TT 591.3 HOURS, SPALLING AND GALLING ON GEAR TEETH. (X) 1 G 7 1 3U 3 U O H2SW E1GL 2001021400041 20010214 00041 SW 2001 2 14 20001113SH011 1 20000830 G 7920 206061432121 HOUSING BELL BELL 407 407 SW T/R DRIVESHAFT CRACKED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 427AL 810 A382 53107 DURING DAILY INSPECTION, FOUND HOUSING CRACKED AND RIVETS MISSING DUE TO HIGH VIBRATION, HOUSING SCRAPPED. (X) 1 G 7 1 3U O H2SW 2001020200069 20010202 00069 NE 2001 2 2 20001113SH012 1 20000831 G 6700 7640701106102 SUPPORT BRACKET SKRSKY S76 S76A 8143006 NE PILOTS CYCLIC BROKEN E ALGA K NONE O OTHER IN INSP/MAINT 1 SW 03 519AL 760058 DURING COMPLIANCE OF ASB 76-67-44, FOUND CYCLIC SUPPORT NOT TO BE THE CORRECT CONFIGURATION. (X) 1 G 7 2 3U H1NE 2001021400042 20010214 00042 NE 2001 2 14 20001113SH013 1 20000120 G 3233 SS49MC90J420R RESTRICTOR VALVE CLEVELANDPNU 1944 SKRSKY S76 S76A 8143006 NE NLG ACTUATOR FAILED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 PTHOR 6607 CPC0118ADER 760003 LANDING GEAR ACTUATOR WOULD NOT LOCK IN DOWN POSITION. ACTUATOR RESTRICTOR ASSEMBLY FILTER AND ORIFICE DISPLACED FROM RESTRICTOR AND FORCED INTO ACTUATOR TERMINAL. THIS PREVENTED DOWNLOCK KEEPER FROM MOVING INTO LOCKED POSITION. (X) 1 G 7 2 3U H1NE 2000120400195 20001204 00195 CE 2000 12 4 20001114SH027 1 20001114 G 5520 NAS464P4A23 BOLT BEECH 200 200BEECH 1152920 CE RT ELEV HINGE BROKEN B K NONE O OTHER IN INSP/MAINT 1 EA 09 200BE 8225 BB832 RIGHT ELEVATOR CENTER HINGE BOLT WAS FOUND BROKEN DURING A ROUTINE AIRCRAFT INSPECTION. IT LOOKED INTACT, BUT UPON A TO RQUE CHECK, IT WAS FOUND THAT THE BOLT WAS BROKEN. THERE IS NO HISTORY OF UNUSUAL STRESSES ON THIS PART. (X) 1 L 7 2 4T A24CE 2001021400043 20010214 00043 EU 2001 2 14 20001117SH003 1 20001117 G 6500 593404 BEARING SNIAS 350 AS350B2 8680813 EU T/R DRIVE SEIZED B E A ENGINE SHUTDOWN UNSCHED LANDING B E SMOKE/FUMES/ODORS/SPARKS VIBRATION/BUFFET NR NOT REPORTED 1 WP 01 6095U 941 2699 SMOKE IN COCKPIT, TAIL VIBRATION. REF: OPERATOR CONTROL NR 010270. (X) 1 G 7 1 3U H9EU 2000120700199 20001207 00199 EA 2000 12 7 20001117SH004 2 20001017 G 7414 103571651 COIL GULSTM 500 500B 0141106 SW LYC O540 IO540E1B5 41532 EA OPEN D K NONE O OTHER NR NOT REPORTED 1 SW 15 917GT 93 G270012ER 500113777 L1456548 PILOT REPORTED LEFT MAGNETO, LEFT ENGINE, INOPERATIVE. ON PREFLIGHT MAGNETO CHECK, REVEALED COIL WIRE BROKEN AT SPADED CONNECTOR TO MAIN CONTACTS. FACTORY OVERHAULED MAGNETO. (X) 1 H 7 2 3O 3 O 6A1 1E4 2000120700200 20001207 00200 CE 2000 12 7 20001120SH001 1 20001119 G 8011 PM240131B22207 STARTER CESSNA 172 172S 2072439 CE POWERPLANT OPEN C K NONE O OTHER IN INSP/MAINT 1 SO 05 916CP 226 172S8336 STARTER FAILED, FAULT TRACED POWER THROUGH CONTACTOR, POWER AT STARTER LUG, NO CURRENT DRAW. NO REASON FOR FAULT COULD BE DETERMINED AS DISASSEMBLY WAS NOT AVAILABLE. NO RECOMMENDATIONS AVAILABLE TO PREVENT RECURRENCE. (X) 1 H 7 1 3O NT 3A12 2000120700201 20001207 00201 SO 2000 12 7 20001120SH003 2 20001015 G 8530 652956 VALVE CESSNA 210 T210N 2073456 CE CONT O520 TSIO520R 17040 SO CYLINDER ASSY WORN D K NONE O OTHER IN INSP/MAINT 1 NM 03 967CC 253 21064534 294133R CYLINDER NR 4 REMOVED FOR LOW COMPRESSION DUE TO LEAKAGE PAST THE EXHAUST VALVE. THE REPAIR STATION THAT REPAIRED THE C YLINDER ASSY REPLACED THE INTAKE AND EXHAUST VALVES, EXHAUST VALVE GUIDE, AND ASSOCIATED PARTS. THE INTAKE VALVE''S FAC E WAS CUPPED, EXHAUST VALVE WAS STRETCHED, AND THE EXHAUST VALVE GUIDE WAS WORN PAST SERVICEABLE LIMITS. (X) 1 H 7 1 3O 3 O 3A21 E8CE 2000120700202 20001207 00202 SO 2000 12 7 20001120SH004 2 20000920 G 8530 646283 VALVE CESSNA 210 T210N 2073456 CE CONT O520 TSIO520R 17040 SO CYLINDER ASSY WORN D K NONE O OTHER IN INSP/MAINT 1 NM 03 967CC 404 21064534 294133R CYLINDER NR 2 REMOVED FOR LOW COMPRESSION DUE TO LEAKAGE PAST THE INTAKE VALVE. THE REPAIR STATION THAT REPAIRED THE CY LINDER ASSEMBLY REPLACED THE INTAKE AND EXHAUST VALVES, EXHAUST GUIDE, AND ASSOCIATED PARTS. THE INTAKE VALVE''S FACE W AS CUPPED, EXHAUST VALVE WAS STRETCHED .0045 INCH, AND THE EXHAUST VALVE GUIDE WAS WORN OVERSIZED. (X). 1 H 7 1 3O 3 O 3A21 E8CE 2000120700203 20001207 00203 CE 2000 12 7 20001120SH005 1 20000913 G 2750 50000084 CONTROL CABLE CESSNA 402 402B 207590P CE FLAP SYSTEM BROKEN C O OTHER F FLT CONT AFFECTED LD LANDING 1 SW 11 5040Q 10 402B0347 CPS/LIT - WHILE ON FINAL, THE FLAP SYSTEM FAILED. IT WAS DETERMINED THE UPPER FLAP EXTEND CABLE ON THE RIGHT SIDE HAD B ROKEN APPROXIMATELY A FOOT OUTBOARD OF THE ACTUATOR CHAIN ATTACH POINT. THE CABLE COULD HAVE BEEN INCORRECTLY ROUTED/RI GGED AND/OR THE CABLE TENSION COULD HAVE BEEN INCORRECTLY SET. THE CABLE WAS REPLACED ABOUT 10 HOURS PRIOR TO FAILURE. (X) 1 L 7 2 3O A7CE 2000120700204 20001207 00204 EA 2000 12 7 20001120SH006 2 20001025 G 7414 10349276G CAPACITOR CONT GULSTM 500 500B 0141106 SW LYC O540 IO540E1B5 41532 EA WIRE CONN END BROKEN D O OTHER R PARTIAL RPM/PWR LOSS CR CRUISE 1 SW 15 524HW 245 B010004ER 1533191 L2076548 PILOT COMPLAINT, SEVERE MAG DROP ON PRE-FLIGHT RUN UP. REPLACED MAGNETO AND PROBLEM WAS FIXED. INSPECTION OF OLD MAGNE TO REVEALED BROKEN WIRE ON CAPACITORS AND POINTS BURNT. (X) 1 H 7 2 3O 3 O 6A1 1E4 2001022600068 20010226 00068 NE 2001 2 26 20001120SH007 3 20001016 G 6111 6607132886 BLADE ROTOL R389 R3894123F26 NE PROPELLER CRACKED B MS1R K NONE O OTHER IN INSP/MAINT 1 EA 21 25625 24951 DRG202388 PROPELLER RECEIVED FOR REPAIR OF SLINGING GREASE AND LIGHT BLADE DAMAGE. BLADE, SN 784, WAS FOUND TO HAVE A CRACK RUNNI NG FROM PTFE FACE TO BLADE BEARING FACE ON OUTER SLEEVE AT ROOT END. BLADE REJECTED FROM SERVICE. (X) 6 C P30NE 2001022600069 20010226 00069 NE 2001 2 26 20001120SH008 3 20001016 G 6111 6607132896 BLADE ROTOL R389 R3894123F26 NE PROPELLER CRACKED B MS1R K NONE O OTHER IN INSP/MAINT 1 EA 27 20288 7428 DRG728486 PROPELLER RECEIVED FOR ROUTINE OVERHAUL. AT DISASSEMBLY FOR OVERHAUL, NOTED BLADE, SN SC340-132/2239 WAS CRACKED IN OUT ER SLEEVE AT ROOT END. BLADE REJECTED FROM FURTHER SERVICE. (X) 6 C P30NE 2001022600071 20010226 00071 2001 2 26 20001120SH011 4 20001024 G 6122 210100 SHAFT WOODWARD BEECH 55 E55 1152732 CE CONT O520 IO520C 17032 SO PROP GOVERNOR CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 102GA 1445291S TE771 RELEVANT MAGNETIC PARTICLE INDICATION ON GEAR TOE. (X) 1 L 7 2 3O 3 O 3A16 E5CE 2001022600073 20010226 00073 SW 2001 2 26 20001120SH022 1 20001106 G 2913 POWERPACK POINTER GULSTM 112 112 0144701 SW HYDRAULIC SYSTEM MALFUNCTIONED H K NONE O OTHER IN INSP/MAINT 1 GL 03 1169J 169 LANDING GEAR HYDRAULIC POWER PACK BUILDS UP 16 PSI. (AFTER GEAR EXTENSION) IN THE ''UP'' SIDE OF HYDRAULIC CIRCUIT CONT RARY TO COMMANDER 112 SM. POWER PACK VENDOR STATES THE OVERHAUL IS IAW COMMANDER SPECS AND COMMANDER STATES PROBLEM IS WITH POWER PACK VENDOR. SUBMITTER STATED, NO RESOLUTION. (X) 1 L 7 1 3O A12SO 2001011101198 20010111 01198 CE 2001 1 11 20001120SH023 1 20000607 G 3230 101810000651 DRAG BRACE BEECH 200 A200 1152921 CE MLG MISOVERHAULED B K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 21 1547 BC50 MAIN GEAR ASSEMBLY RECEIVED IN OVERHAULED CONDITION. DURING INSTALLATION PROCESS, NOTED AND VERIFIED THE DRAG LINK ATTA CHMENT LUG SLEEVE WAS APPROXIMATELY .010 INCH OVERSIZE FROM SPECS CALLED OUT IN THE RAYTHEON BEECHCRAFT COMPONENT MM. R EF: FAA FORM 8130-3. (X) 1 L 7 2 4T A24CE 2001021400044 20010214 00044 EU 2001 2 14 20001120SH025 1 20001106 G 3246 1090500163 WHEEL AGUSTA A109 A109 0260109 EU LT MLG CRACKED B K NONE O OTHER IN INSP/MAINT 1 SO 19 168BH 4367 7256 THE LEFT MAIN TIRE WAS LOW, AS THE MECHANIC WAS GOING TO SERVICE THE TIRE, NOTED A CRACK PROPAGATING FROM A BOLT HOLE OU TWARD. (X) 1 G 7 2 3U H7EU 2001022600074 20010226 00074 SW 2001 2 26 20001120SH026 1 20000925 G 3710 PUMP MOONEY M20 M20K 5870220 SW CONT O360 TSIO360GB 17025 SO VACUUM SYSTEM FAILED H K NONE O OTHER IN INSP/MAINT 1 EA 25 231MY 250152 309262 THIS AIRCRAFT HAD A 211 CC VACUUM PUMP FROM 7/93 UNTIL 5/99. WHEN THE PART FAILED, IT WAS REPLACED WITH A 215 CC, SN 5A R2833. THIS LASTED 4 MONTHS (19 HOURS) AND WAS REPLACED WITH A 215 CC, SN 11AP4226. THIS LASTED 6 MONTHS (57 HOURS) AN D WAS REPLACED IN 5/00 WITH A 215 CC, SN S-2AT1103. THIS FAILED IN 8/00 AFTER 3 MONTHS, AND 64 HOURS AND WAS REPLACED W ITH 215 CC, SN 4AR2358. THIS LASTED ONE MONTH AND 22 HOURS AND FAILED 9/19/00. SUBMITTER THINKS THERE IS A PROBLEM WIT H THIS PUMP TYPE. (X) 1 L 7 1 3O 3 O 2A3 E9CE 2001022600075 20010226 00075 CE 2001 2 26 20001120SH027 1 20001106 G 7112 35910067635 BAFFLE BEECH 36 B36TC 1151609 CE ENGINE CRACKED H K NONE O OTHER IN INSP/MAINT 1 CE 07 376RH 202 EA612 BAFFLE ABOVE OIL COOLER CRACKED OUT FROM PRESS FILTER HOLE. (X) 1 L 7 1 3O 3A15 2001022600076 20010226 00076 CE 2001 2 26 20001120SH028 1 20001110 G 8120 643816 BRACKET BEECH 36 B36TC 1151609 CE CONT O520 TSIO520UB 17040 SO TURBOCHARGER BROKEN H K NONE O OTHER IN INSP/MAINT 1 CE 07 376RH 202 EA612 527393 TURBO CONTROLLER SUPPORT BRACKET BROKEN AT CASE ATTACHMENT POINT. (X) 1 L 7 1 3O 3 O 3A15 E8CE 2001022600077 20010226 00077 SO 2001 2 26 20001120SH029 1 20001103 G 3211 452575 BEARING PIPER PA44 PA44180T 7104404 SO STRUT HOUSING WRONG PART B DPOR K NONE O OTHER IN INSP/MAINT 1 NM 07 227ST 2000 448107042 DURING COMPLIANCE WITH AD 94-13-11 AMDT 79-8952, STRUT HOUSING CHANGE. BEARING HAD NARROW GROOVE AND NO HOLE FOR GREASE TO ENTER THE BEARING (MFG DEFECT). (X) 1 L 7 2 3O A19SO 2001020200081 20010202 00081 EU 2001 2 2 20001120SH032 1 20001102 G 6420 704A33640046 ADAPTER AEROSP AS365 AS365N2 8680815 EU TAIL ROTOR TORN E ZYWA K NONE O OTHER IN INSP/MAINT 1 GL 09 365WM 167 6429 FREQUENCY ADAPTER, SN 18495, TORN. REMOVED AND REPLACED MATCHED PAIR FREQUENCY ADAPTERS. (X) 1 G 7 2 3U RT H10EU 2001020200082 20010202 00082 EU 2001 2 2 20001120SH033 1 20001102 G 6420 704A33640046 ADAPTER AEROSP AS365 AS365N2 8680815 EU TAIL ROTOR TORN E ZYWA K NONE O OTHER IN INSP/MAINT 1 GL 09 365WM 167 6429 FREQUENCY ADAPTER, SN 18495, TORN. REMOVED AND REPLACED MATCHED PAIR FREQUENCY ADAPTERS. (X) 1 G 7 2 3U RT H10EU 2001021300013 20010213 00013 EU 2001 2 13 20001120SH034 1 20001026 G 2911 08233901102 ACCUMULATOR AEROSP AS365 AS365N2 8680815 EU HYD SYSTEM FAILED E ZYWA K NONE O OTHER NR NOT REPORTED 1 GL 09 365WM 7198 6429 ACCUMULATOR FAILED TO HOLD CHARGE, SLOWLY DROPPED PRESSURE. REMOVED AND REPLACED ACCUMULATOR. (X) 1 G 7 2 3U RT H10EU 2001020200083 20010202 00083 EU 2001 2 2 20001120SH035 1 20001018 G 2844 81071370010 TRANSMITTER AEROSP AS365 AS365N2 8680815 EU FUEL PRESSURE FLUCTUATES E ZYWA K NONE O OTHER NR NOT REPORTED 1 GL 09 365WM 1815 6429 PRESSURE TRANSMITTER IS FLUCTUATING. (X) 1 G 7 2 3U RT H10EU 2001022600078 20010226 00078 SO 2001 2 26 20001120SH036 1 20001031 G 2140 A23D04 REGULATOR PIPER PA31 PA31350 7103110 SO HEATER LEAKING H K NONE K FLUID LOSS IN INSP/MAINT 1 AL 01 4112K 318353006 FUEL REGULATOR ON JANITROL HEATING SYSTEM (FORWARD) LEAKED AT CASE PARTING SURFACES. (X) 1 L 7 2 3O A20SO 2001022600079 20010226 00079 SO 2001 2 26 20001120SH037 1 20000911 G 8011 MHB23995 ARMATURE ELECTROSYS PIPER PA28 PA28181 7102807 SO LYC O360 O360A4M 41514 EA STARTER DEFECTIVE B UC2R K NONE O OTHER IN INSP/MAINT 1 GL 19 4147K 8031187 2843169 L3623336A THE ARMATURE DRIVE SPLINE WAS FOUND ALMOST COMPLETELY STRIPPED AWAY LEAVING SHARDS OF STEEL IN THE GEAR HOUSING THAT CON TAMINATED THE BEARINGS. THE BENDIX DRIVE END WAS UNDAMAGED AND THE SHEAR PIN DID NOT SHEAR. THE ARMATURE DRIVE END MA Y NOT BE PROPERLY HEAT TREATED OR SHEAR PIN MAY BE TOO HARD. SUBMITTER STATED THIS IS THE SEVENTH ARMATURE FOUND IN THI S CONDITION. (X) 1 L 7 1 3O 3 O 2A13 E286 2001020200084 20010202 00084 SO 2001 2 2 20001120SH038 1 20001115 G 2140 A23D0475 VALVE JANITROL PIPER PA31 PA31350 7103110 SO FUEL REGULATOR LEAKING A FFSA K NONE O OTHER IN INSP/MAINT 1 AL 01 4501B 164 5954723 318052168 FUEL WAS OBSERVED LEAKING FROM DRAIN TUBE. INVESTIGATION REVEALED VALVE TO BE LEAKING FROM DIAPHRAGM PARTING SURFACE. VALVE BODY SCREWS WERE FOUND TO HAVE LOOSENED OVER TIME. SUBMITTER SUGGESTED SELECTION OF ALTERNATE LOCKING DEVICE TO P REVENT RECURRENCE. (X) 1 L 7 2 3O A20SO 2001022600080 20010226 00080 CE 2001 2 26 20001120SH039 1 20001105 G 5220 52111302 ESCAPE HATCH CESSNA 402 402B 207590P CE FUSELAGE DEPARTED B O OTHER D INFLIGHT SEPARATION CR CRUISE 1 EA 13 4537Q 10771 402B0343 ESCAPE HATCH DEPARTED AIRCRAFT AT 2,200 FEET, SIX MILES WEST OF LANCASTER AIRPORT. NO DAMAGE WAS FOUND ON THE AIRCRAFT. INSPECTION OF THE FRAME, OF THE ESCAPE HATCH OPENING, FOUND NOTHING BROKEN IN THE RETAINING SYSTEM. IT APPEARED THE R ETAINING PINS VIBRATED OUT ENOUGH TO ALLOW THE HATCH TO BE PULLED OUT BY THE WIND. (X) 1 L 7 2 3O A7CE 2001030100034 20010301 00034 CE 2001 3 1 20001120SH040 1 20000717 G 8010 643259A DRIVE SHAFT CESSNA 185 A185F 2072821 CE ENGINE DEFECTIVE E K NONE O OTHER IN INSP/MAINT 1 AL 05 6JV 989 18502397 STARTER DRIVE STARTED MAKING NOISE WHEN CRANKING ENGINE. WHEN STARTER WAS REMOVED, LOWER FLANGE OF STARTER DRIVE WAS FO UND TO BE BROKEN. WHEN ''STARTER DRIVE'' SHAFT WAS TURNED AFTER REMOVAL FROM ENGINE, IT WAS VERY NOISY LIKE A VERY BAD BEARING OR SOMETHING. THE ABOVE IS NOT PART OF THE STARTER. (X) 1 H 7 1 3O 3A24 2001021400046 20010214 00046 EU 2001 2 14 20001120SH051 1 20001104 G 2435 150SG122Q STARTER GEN SNIAS 350 AS350BA 8680817 EU ENGINE INOPERATIVE E KBMA K NONE O OTHER IN INSP/MAINT 1 WP 19 1188P 906 2347 STARTER/GENERATOR INOPERABLE. (X) 1 G 7 1 3U NC H9EU 2001021400047 20010214 00047 EU 2001 2 14 20001120SH052 1 20001030 G 7712 305731366 INDICATOR SNIAS 350 AS350BA 8680817 EU TORQUE ERRATIC E KBMA K NONE O OTHER IN INSP/MAINT 1 WP 19 180EH 2337 TORQUE INDICATOR ERRATIC. (X) 1 G 7 1 3U NC H9EU 2001021400048 20010214 00048 EU 2001 2 14 20001120SH053 1 20001105 G 7714 0177555170 TACHOMETER SNIAS 350 AS350BA 8680817 EU ENGINE INOPERATIVE E KBMA K NONE O OTHER IN INSP/MAINT 1 WP 19 270SH 1864 TACHOMETER BOX INOPERABLE. BLEED VALVE WILL NOT CLOSE. (X) 1 G 7 1 3U NC H9EU 2001021500001 20010215 00001 EU 2001 2 15 20001120SH055 1 20001023 G 7332 704A37643000 INDICATOR SNIAS 350 AS350BA 8680817 EU FUEL PRESSURE INOPERATIVE E KBMA K NONE O OTHER IN INSP/MAINT 1 WP 19 37SH 2300 FUEL PRESSURE INDICATOR IS INOPERATIVE. (X) 1 G 7 1 3U NC H9EU 2001021500002 20010215 00002 SW 2001 2 15 20001120SH056 1 20001025 G 7722 12444412 GAUGE BELL 206 206B 1181511 SW TOT FLUCTUATES E KBMA K NONE O OTHER IN INSP/MAINT 1 WP 19 667JM 3444 TOT GAUGE FLUCTUATES IN-FLIGHT. SPIKES FROM 0 - 800 THEN NORMAL OPS. (X) 1 G 7 1 3U H2SW 2001021500003 20010215 00003 2001 2 15 20001120SH057 4 20001025 G 3422 206075606103 GYRO BELL 206 206B 1181511 SW COCKPIT INOPERATIVE E KBMA K NONE O OTHER IN INSP/MAINT 1 WP 19 73DP 2513 DIRECTIONAL GYRO INOPERABLE. (X) 1 G 7 1 3U H2SW 2001022600081 20010226 00081 EA 2001 2 26 20001120SH058 2 20000802 G 8530 60828 PLUG AMRGEN AA5 AA5 0631410 SO LYC O320 O320E2G 41508 EA CYLINDER NR 2 FAILED D K NONE O OTHER IN INSP/MAINT 1 AL 05 6084L 800 AA50184 L3216327A PISTON PIN PLUG IN CYLINDER NR 2 FAILED CATASTROPHICALLY ENLARGING PISTON BOSS AND WEARING INTO LOWER RING. ENGINE WAS 800 SMOH, CYLINDERS .010 INCH OS (PLAIN STEEL). SCREEN LAST CHECKED 48 HOURS PREVIOUSLY. PRESSURE SCREEN BECAME PLUGGE D WITH ALUMINUM FLAKES, OIL PRESSURE DROPPED AND PILOT NOTICED CHANGE. ALL OTHER CYLINDERS REMOVED. TWO OTHER PLUGS WO RN BEYOND LIMITS. REPLACED ALL PISTON PIN PLUGS WITH LYC PN 72198. (X) 1 L 7 1 3O 3 O A16EA E274 2001022600082 20010226 00082 SW 2001 2 26 20001120SH059 1 20001101 G 5414 SKIN GULSTM 690TP 690A 0141722 SW LT/RT NACELLE CORRODED B K NONE O OTHER IN INSP/MAINT 1 SW 05 62366 4042 11141 DURING 100-HOUR INSPECTION, AIRCRAFT NACELLE AREA FOUND THE UPPER ENGINE MOUNT ATTACH STRUCTURE STEEL STRAPS HEAVILY COR RODED. UPON REMOVAL OF THE UPPER NACELLES ON THE LEFT AND RIGHT SIDES OF THE AIRCRAFT, FOUND HEAVY PITTING AND WIDE SPR EAD CORROSION OVER THE TOP SURFACE OF THE WING AS WELL AS CORROSION AND PITTING EXTENDING UNDER THE STEEL STRAPS. (X) 1 H 7 2 3T 2A4 2001022700002 20010227 00002 SO 2001 2 27 20001120SH060 1 20001027 G 3230 AN643 BOLT PIPER PA23 PA23250 7102308 SO NOSE GEAR BROKEN D K NONE O OTHER IN INSP/MAINT 1 SO 03 6855Y 273891 FOUND UPPER BOLT (AN6-43) IN NOSE GEAR DRAG LINK BROKEN WHERE DRAG LINK ATTACHES TO AIRFRAME STRUCTURE. AIRCRAFT HAD 8, 600 HOURS TOTAL TIME. TOTAL TIME IN SERVICE OF BOLT UNKNOWN. AIRCRAFT OPERATED FROM TURF AND PAVED RUNWAYS. (X) 1 L 7 2 3O 1A10 2001022700003 20010227 00003 EA 2001 2 27 20001120SH062 2 20001025 G 8530 ROCKER BOSS PIPER PA18 PA18150 7101828 SO LYC O320 O320A2B 41508 EA CYLINDER OUT OF POSITION D K NONE O OTHER IN INSP/MAINT 1 SW 13 83296 187609068 L4503827A CYLINDER HAD LOW COMPRESSION. WHEN ROCKER BOSS COVER WAS REMOVED, THE EXHAUST SIDE OF ROCKER SHAFT BOSS WAS FOUND IN BO TTOM OF COMPARTMENT. CHROME CYLINDER WAS OVERHAULED 226 HOURS PRIOR. (X) 1 H 7 1 3O 3 O 1A2 E274 2001022700004 20010227 00004 EA 2001 2 27 20001120SH063 2 20000922 G 8550 PLUG CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA ENGINE SUMP MISSING D O OTHER E M Y VIBRATION/BUFFET OVER TEMP ENGINE STOPPAGE IN INSP/MAINT 1 SW 15 82149 3953 557 17267692 L132076 AIRCRAFT WAS FLYING FROM TULSA TO SILOAM SPRINGS, 8 MILES FROM SILOAM SPRINGS AIRPORT, PILOT REPORTED THE ENGINE OIL PRE SSURE WAS FLUCTUATING FROM ZERO TO 60 PSI. THE ENGINE THEN STARTED TO VIBRATE SEVERELY BEFORE THE ENGINE COMPLETELY STO PPED. UPON INSPECTION OF THE AIRCRAFT, FOUND THE OIL QUICK DRAIN WAS MISSING WHICH OBVIOUSLY CAUSED THE ENGINE TO LOSE OIL PRESSURE. THE QUICK DRAIN INSTALLED DID NOT HAVE A PROVISION FOR SAFETY WIRE. (X) 1 H 7 1 3O 3 O NT 3A12 E274 2001030100035 20010301 00035 SO 2001 3 1 20001121SH001 1 20001108 G 3110 770052 DISPLAY PIPER PA32 PA32301T 7103209 SO INSTRUMENT PANEL FAILED D K NONE O OTHER IN INSP/MAINT 1 WP 15 9288X 223 3257027 CODE ONE FAILURE MODE; SECOND TIME IN THIS AIRCRAFT. SUBMITTER STATED FAX''''S TO PIPER, THEIR TECH REPS SAY THAT IT HA S THE ONLY AMPS AND VOLT READINGS ON THIS INSTRUMENT, SO IT IS REQUIRED. (X) 1 L 7 1 3O A3SO 2001030100036 20010301 00036 SO 2001 3 1 20001121SH002 1 20001108 G 3110 770052 DISPLAY PIPER PA32 PA32301T 7103209 SO LYC O540 TIO540A1A 41532 EA INSTRUMENT PANEL FAILED D K NONE O OTHER IN INSP/MAINT 1 WP 15 9288X 128 3257027 L990861A CODE ONE FAILURE MODE; THIRD TIME IN THIS AIRCRAFT. SUBMITTER STATED FAX''S TO PIPER, THEIR TECH REPS SAY THAT IT HAS T HE ONLY AMPS AND VOLT READINGS ON THIS INSTRUMENT, SO IT IS REQUIRED. (X) 1 L 7 1 3O 3 O A3SO E14EA 2001022700007 20010227 00007 CE 2001 2 27 20001121SH004 1 20001017 G 5412 05530313 FIREWALL CESSNA 172 172S 2072439 CE FUSELAGE CRACKED D K NONE O OTHER IN INSP/MAINT 1 NM 11 74GW 559 172S8143 FIREWALL HAD CRACK APPROXIMATELY .75 INCH STARTING AT LOWER LEFT COWL MOUNT TOWARDS BATTERY BOX MOUNT. CESSNA SB 98-53- 02. PERTAINS TO THIS SITUATION, BUT IS ONLY ON 172R MODEL. (X) 1 H 7 1 3O NT 3A12 2001022700008 20010227 00008 CE 2001 2 27 20001121SH005 1 20001017 G 3340 1212010791 CONNECTOR CESSNA 182 182S 2072701 CE TAILCONE CORRODED D K NONE O OTHER IN INSP/MAINT 1 NM 08 23735 407 18280458 AT 100-HOUR INSPECTION, REMOVED TAILCONE AND FOUND IT FILLED WITH APPROXIMATELY 1.50 INCHES OF WATER. WATER HAD CORRODE D CONNECTOR FOR TAIL NAVIGATION LIGHT. CONNECTOR WAS REPLACED AND LOWER ATTACH SCREW FOR TAILCONE WAS NOT RE-INSTALLED TO ALLOW FOR FUTURE WATER DRAIN. TAILCONE HAD SUFFICIENT SCREWS (14) TO RETAIN IT SAFELY WITH LOWER SCREW OMITTED. (X) 1 H 7 1 3O NT 3A13 2001021500004 20010215 00004 2001 2 15 20001127SH001 4 20001110 G 3422 5050010902 GYRO SNIAS 350 AS350B1 8680811 EU COCKPIT INOPERATIVE E KBMA K NONE O OTHER IN INSP/MAINT 1 WP 19 53SH 2009 DIRECTIONAL GYRO INOPERATIVE. (X) 1 G 7 1 3U H9EU 2001021500005 20010215 00005 2001 2 15 20001127SH004 4 20001109 G 3422 103002201 GYRO SNIAS 350 AS350BA 8680817 EU COCKPIT OUT OF TOLERANCE E KBMA K NONE O OTHER IN INSP/MAINT 1 WP 19 350SH 2957 DIRECTIONAL GYRO, FLAG OUT OF CALIBRATION, POSSIBLY DUE TO ROTOR BEARINGS STARTING TO FAIL. SENT FOR OVERHAUL. (X) 1 G 7 1 3U NC H9EU 2001021500006 20010215 00006 NE 2001 2 15 20001127SH006 2 20000614 G 7250 410106701 SEAL BOLKMS 117 BK117A3 5626015 EU LYC LTS101 LTS101650B1 41560 NE TURBINE SHROUD WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 420MB 423 7077 LE45218EA FIRST TURBINE SHROUD, SEAL RING WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U 3 U H13EU E5NE 2001021500007 20010215 00007 NE 2001 2 15 20001127SH007 2 20000614 G 7250 410106802 SPRING BOLKMS 117 BK117A3 5626015 EU LYC LTS101 LTS101650B1 41560 NE SEAL RING EXPAND WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 420MB 523 7077 LE45218EA SEAL RING EXPANDER - SPRING WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U 3 U H13EU E5NE 2001030200027 20010302 00027 2001 3 2 20001127SH008 4 20001109 G 2561 KS9P0101 LIFE VEST CABIN FAILED B KQ1R K NONE L NO TEST IN INSP/MAINT 1 EA 07 A LIFE VEST FAILED MFGS TWO PSI INFLATION TESTS IAW 25-60-1. LIFE VEST DATE OF MFG, JUNE 1980. FAIR WEAR AND TEAR. (X) 2001022700010 20010227 00010 CE 2001 2 27 20001127SH010 1 20000811 G 5341 0512122 FITTING CESSNA 172 172M 2072418 CE WING ATTACH CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 21 137FS 57980 17266030 CRACK FOUND DURING AN ANNUAL INSPECTION. (X) 1 H 7 1 3O NT 3A12 2001022700011 20010227 00011 SO 2001 2 27 20001127SH011 1 20001108 G 7430 IO3572001 IGNITION SWITCH PIPER PA28 PA28236 7102815 SO LYC O540 O540J3A5 41532 EA COCKPIT FAILED B K NONE O OTHER IN INSP/MAINT 1 WP 07 2234Z 1200 287911160 AD 76-07-12 DOES NOT APPLY TO THIS IGNITION SWITCH BY MANUFACTURE CODE DATE (8408), HOWEVER, SWITCH FAILED THE ''OFF CHE CK'' SPECIFIED IN THE AD. INSTALLATION OF CONTACT KIT P/N 10-357510, WAS REQUIRED. (X) 1 L 7 1 3O 3 O 2A13 E295 2001022700012 20010227 00012 CE 2001 2 27 20001127SH012 1 20001027 G 3221 16981001127 HOUSING BEECH 23 C23 1151242 CE NLG BROKEN G K NONE O OTHER TO TAKEOFF 1 EA 07 450BA 500 M2342 NOSE GEAR ASSEMBLY FELL OFF THE AIRCRAFT ON TAKEOFF. FOUND THE HOUSING HAD CRACKED OUT WHERE THE STEERING ASSY ATTACHES . THIS AREA SHOWED SIGNS OF BEING CRACKED FOR SOME TIME. (X) 1 L 7 1 3O A1CE 2001011101201 20010111 01201 CE 2001 1 11 20001127SH013 1 20001101 G 5520 50610000546 BRACKET BEECH 90 C90 1152913 CE ELEVATOR DAMAGED B WTXR K NONE O OTHER IN INSP/MAINT 1 NM 07 6732V 1745 LJ0899 WHILE RE-INSTALLING THE RIGHT ELEVATOR, THE MECHANIC NOTICED THE BOLT THAT HOLDS THE ELEVATOR OUTBOARD BRACKET TO THE HO RIZONTAL BEARING BRACKET PN 50-620001-69 WAS SLOPPY. AFTER REMOVING BOLT, FOUND IT SEVERELY WORN AND BRACKET 50-61000-5 46 HAD SEVERELY ELONGATED HOLES WHERE THE BOLT PASSES THROUGH IT. SUBMITTER STATED PREVIOUS BOLT WAS INSTALLED WITH THI N WASHERS AND THE NUT WAS SHANKED OUT LEAVING THE BOLT LOOSE TO RATTLE IN THE BRACKET. INSTALLED NEW BRACKET AND PROPER SIZE WASHERS ON NEW BOLT. (X) 1 L 7 2 3T 3A20 2001022700013 20010227 00013 SO 2001 2 27 20001127SH015 1 20001127 G 5341 RIVET PIPER PA24 PA24250 7102404 SO WING ATTACH SHEARED H K NONE O OTHER IN INSP/MAINT 1 NM 09 7456P 242646 DURING ANNUAL INSPECTION, FOUND SHEARED RIVETS AT BOTH REAR WING ATTACH FITTINGS AS FOLLOWS: BS 136 RT SIDE, ALL RIVETS SHEARED THRU PLATE PN 23662-00, FITTING ASSY P/N 23663-00, DOUBLER P/N 23664-02. EXTENSIVE MOVEMENT BETWEEN PLATE AND FITTING ASSY CAUSED ANGLE P/N 20554-16 TO SHEAR IN TWO. LT SIDE MUCH THE SAME EXCEPT 2 RIVETS REMAINING, ANGLE HAS NOT COMPLETELY SHEARED THROUGH. AIRFRAME TT 6,342 HRS. (X) 1 L 7 1 3O 1A15 2001022700014 20010227 00014 SO 2001 2 27 20001127SH017 1 20001110 G 3030 587954 SWITCH PIPER PA34 PA34200T 7103406 SO INSTRUMENT PANEL CORRODED D K NONE O OTHER IN INSP/MAINT 1 NM 08 8514C 347670147 PILOT REPORTED AIRCRAFTS PITOT HEAT SYSTEM TO BE INOPERATIVE. INSPECTION REVEALED THE SWITCH ASSY TO HAVE CORROSION IN THE CONTACTS. THE CORROSION APPEARED TO BE CAUSED BY MOISTURE SUCH AS RAIN WATER. (X) 1 L 7 2 3O A7SO 2001022700015 20010227 00015 EA 2001 2 27 20001127SH018 2 20001014 G 8500 ENGINE PIPER PA24 PA24260 7102406 SO LYC O540 O540E4A5 41532 EA ENGINE FAILED H A UNSCHED LANDING Y ENGINE STOPPAGE CR CRUISE 1 SO 17 9005P 2035 35 244466 L2414040A ENGINE FAILED CATASTROPHICALLY IN-FLIGHT AND SUBSEQUENTLY AIRCRAFT LANDED GEAR UP NEXT TO CANAL. INITIAL INSPECTION IND ICATED ROD BEARING OR ROD CAP FAILURES. MANUFACTURER''S INSPECTION RESULTS ARE PENDING. (X) 1 L 7 1 3O 3 O 1A15 E295 2001030100038 20010301 00038 CE 2001 3 1 20001128SH001 1 20001102 G 5510 1694400173 HINGE BEECH 23 A24R 1151252 CE HORIZONTAL STAB CORRODED D K NONE O OTHER IN INSP/MAINT 1 WP 07 8022R MC14 THE PAINT WAS CRACKED AROUND THE HINGE PLATE ON THE RT SIDE. A FINGERNAIL WOULD GO UNDER A COUPLE OF THE RIVETS. WHEN THE RIVETS WERE DRILLED OUT, SEVERAL SPUN AND BROKE BEFORE THE BIT WENT THROUGH. THE BACK SIDE OF THE HINGE PLATES WAS RUSTED AND BLACK GALLING APPEARED ON THE ALUMINUM UNDERNEATH INDICATING MOVEMENT. SUBMITTER STATED THIS IS A 25-HOUR A D INSPECTION THAT IS DIFFICULT TO ASSESS UNTIL REMOVED. (X) 1 L 7 1 3O A1CE 2001011101202 20010111 01202 SO 2001 1 11 20001129SH001 1 20001128 G 2822 LW5473 PUMP PIPER PA32 PA32300 7103212 SO ENGINE FUEL FAILED E FPXA C ABORTED TAKEOFF R J PARTIAL RPM/PWR LOSS WARNING INDICATION TO TAKEOFF 1 SO 25 2835W 1522 327940148 L1330348A DURING TAKEOFF, THE ENGINE MOMENTARILY LOST POWER WHEN FUEL BOOST PUMP WAS SHUT OFF. FUEL FLOW REDUCED BY 8 GPH. AFTER A COUPLE OF SECONDS, THE FUEL FLOW RETURNED TO NORMAL AND THE ENGINE RECOVERED POWER. THE AIRCRAFT LANDED WITHOUT INCIDEN T. GROUND TESTING REVEALED THE ENGINE DRIVEN PUMP WAS SUPPLYING PROPER PRESSURE DURING ALL OPERATIONS EXCEPT FOR FULL PO WER AFTER ELECTRIC PUMP SHUT DOWN. INTERUPTION OF FUEL FLOW WAS ONLY MOMENTARY AND DID NOT OCCUR AT LOWER POWER SETTING S. ENGINE DRIVEN PUMP WAS REPLACED AND ENGINE OPERATES NORMALLY. (X) 1 L 7 1 3O A3SO 2001030200029 20010302 00029 NE 2001 3 2 20001129SH003 2 20001030 G 7200 P2A0851 SEAL IAE V2500 V2500A1 NE NR 4 BEARING CRACKED B KB1R K NONE O OTHER IN INSP/MAINT 1 NE 03 PART RECEIVED FOR FLUORESCENT PENETRANT INSPECTION IAW IAE V2500 PROPULSION SYSTEM ENGINE MANUAL, REV 44, SECTION 70-23- 01, INSPECTION CHECK-01, TASK 70-23-01-230-501. PART REJECTED AT FPI DUE TO TWO CRACKS ON OUTSIDE DIAMETER OF PART (ARE AS MARKED ON PART). (X) 4 F E311NE 2001011101229 20010111 01229 2001 1 11 20001129SH007 4 20001102 G 6122 B4169 IDLER GEAR HARTZL LYC O360 LO360A1G6 41514 EA GOVERNOR DAMAGED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 1384S RELEVANT MAGNETIC PARTICLE INDICATION AROUND GEAR TEETH AREA. (X) 3 O 1E10 2001020900101 20010209 00101 EU 2001 2 9 20001129SH008 1 20001108 G 3246 AHA1236 WHEEL STBROS SD3 SD360 8100606 EU LT MLG FAILED E DATA K NONE O OTHER LD LANDING 1 GL 13 151CA 272 SH3653 UPON LANDING IN MLI, THE LEFT MAIN WHEEL BLEW OUT. THE MLI MECHANIC REMOVED AND REPLACED THE LT MAIN WHEEL ASSY. THERE WAS NO DAMAGE TO THE BRAKE AND STRUT. OPS CHECKED GOOD. (X) 2 H 7 2 4T A41EU 2001022700021 20010227 00021 SO 2001 2 27 20001129SH014 2 20001115 G 7314 634053 PUMP BEECH 95 95B55 1152729 CE CONT O470 IO470L 17026 SO ENGINE DAMAGED H K NONE K FLUID LOSS IN INSP/MAINT 1 EA 07 222MB TC654 297985R ALT BRACKET CONTACTING FUEL INLET FITTING DUE TO FITTING ''CLOCKING'' AND BRACKET LOCATION. FACTORY ZERO TIMED ENGINE. BOTH COMPONENTS FACTORY INSTALLED CAUSED LOSS OF FUEL IN-FLIGHT. ENGINE PUMP REPLACED WITH CONTINENTAL SUPPLIED O/H UN IT AND FOUND NEW PUMP FITTING TO CONTACTING ARM AS WELL. MODIFY ALT BRACKET PER CONTINENTAL REPS REQUEST. ALSO, FOUND FITTING MILL SHAVINGS IN FITTING BLOCKING FLOW ON NEW PUMP. (X) 1 L 7 2 3O 3 O RT 3A16 3E1 2001022700022 20010227 00022 SO 2001 2 27 20001129SH016 1 20001017 G 2730 400053AN36 BOLT PIPER PA31T PA31T 7103124 SO ELEVATOR CABLE WORN H K NONE O OTHER IN INSP/MAINT 1 GL 11 47SF 31T8020031 UPPER AND LOWER BOLTS THAT ATTACH BOTH THE MAIN ELEVATOR CABLES AND AUTOPILOT BRIDLE CABLES. (X) 1 L 7 2 3T A8EA 2001022700023 20010227 00023 2001 2 27 20001129SH017 4 20001017 G 2200 400056AN311 BOLT PIPER PA31T PA31T 7103124 SO AUTO PILOT CABLE WORN H K NONE O OTHER IN INSP/MAINT 1 GL 11 47JF 31T8020031 UPPER AND LOWER BOLTS THAT ATTACH BOTH THE MAIN ELEVATOR CABLES AND AUTOPILOT BRIDLE CABLES. (X) 1 L 7 2 3T A8EA 2001022700024 20010227 00024 SO 2001 2 27 20001129SH018 1 20001114 G 3213 2075212 STRUT PIPER PA24 PA24260 7102406 SO LT MLG CRACKED D K NONE K FLUID LOSS IN INSP/MAINT 1 WP 27 4960 6763 244025 INSPECTION OF LEFT MAIN LANDING GEAR FOUND STRUT JAMMED. HOUSING CRACKED AND LEAKING FLUID. AIRCRAFT TT, 6,763.2 HOURS . (X) 1 L 7 1 3O 1A15 2001022700025 20010227 00025 SO 2001 2 27 20001129SH019 1 20001013 G 7820 MUFFLER MAULE M7 M7235B 5460109 SO LEFT EXHAUST CRACKED B UM9R K NONE O OTHER IN INSP/MAINT 1 NM 13 4279L 151 23058C DURING ANNUAL INSPECTION, NOTED THE LEFT MUFFLER WAS CRACKED AT THE END PLATE WHERE IT HAD BEEN WELDED DURING ASSY. THE CRACKS RAN PARALLEL TO WELDS AND SHOWED EVIDENCE OF EXHAUST LEAKAGE. (X) 1 H 7 1 3O NC 3A23 2001022700026 20010227 00026 SO 2001 2 27 20001129SH020 1 20001013 G 7810 TAILPIPE MAULE M7 M7235B 5460109 SO LT EXHAUST CRACKED B UM9R K NONE O OTHER IN INSP/MAINT 1 NM 13 4279L 151 23058C DURING ANNUAL INSPECTION, NOTED THE LEFT TAILPIPE CRACKED AT THE MOUNTING SUPPORT TAB APPROXIMATELY 95 PERCENT OF PIPE D IAMETER. CRACK HAD ORIGINATED FROM WELD ON TAB. PART FAILED ON REMOVAL. (X) 1 H 7 1 3O NC 3A23 2001030200030 20010302 00030 CE 2001 3 2 20001129SH022 1 20000927 G 3150 LIGHT CESSNA 206 206H 2073301 CE INSTRUMENT PANEL INOPERATIVE B IC1R K NONE L NO TEST IN INSP/MAINT 1 EA 23 7266Y 188 1808 20608059 OIL PRESSURE LIGHT IN ANNUNCIATOR PANEL IS OUT. SUBMITTER SUSPECTED BAD BULB. REMOVED AND REPLACED ANNUNCIATOR PANEL I AW CESSNA MM. OPERATIONAL TEST GOOD. (X) 1 H 7 1 3O RT A4CE 2001030200031 20010302 00031 CE 2001 3 2 20001129SH023 1 20000915 G 7933 S23351 TERMINAL CESSNA 206 206H 2073301 CE OIL TEMP BULB BROKEN B IC1R K NONE O OTHER IN INSP/MAINT 1 EA 23 7266Y 188 20608059 OIL TEMPERATURE BULB CENTER WIRE TERMINAL POST SPINS IN HOUSING. SUBMITTER SUSPECTED FAULTY UNIT. REPLACED WITH SERVIC EABLE UNIT FROM CESSNA, GROUND RAN ENGINE. OPERATION AND LEAK CHECKS GOOD. (X) 1 H 7 1 3O RT A4CE 2001030200032 20010302 00032 EA 2001 3 2 20001129SH024 2 20001031 G 7414 10349276REVG WIRE GULSTM 500 500B 0141106 SW LYC O540 IO540E1A5 41532 EA CAPACITOR BROKEN H K NONE R PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 SW 99 780SP 315 BF210007ER 1362133 L853948 PRE-FLIGHT RUNUP SHOWED SEVERE MAGNETO DROP. POST-REPLACEMENT INSPECTION SHOWED BURNED CONTACTS AND CAPACITOR WIRE BROK EN. (X) 1 H 7 2 3O 3 O 6A1 1E4 2001011101230 20010111 01230 2001 1 11 20001129SH027 4 20000928 G 8300 67542 BEARING BNORM BN2 BN2A26 1520226 EU LYC O540 O540E4C5 41532 EA ACCESSORY SECT BROKEN B K NONE O OTHER IN INSP/MAINT 1 SO 21 904VL 8806 1012 3014 L1807440A DURING ROUTINE INSPECTION, REMOVED OIL FILTER AND FOUND EXCESSIVE PARTICLES ON OIL SCREEN. REMOVED ENGINE FOR SENDING T O OVERHAUL. PRELIMINARY VIEW FOUND LEFT MAGNETO CASE BEARING DISINTEGRATED AND CASE GEAR WEAR. (X) 1 H 7 2 3O 3 O A17EU E295 2001030200033 20010302 00033 SW 2001 3 2 20001129SH028 1 20001103 G 2432 413S34LN2 CIRCUIT BREAKER MOONEY M20 M20J 5870219 SW LYC O360 IO360A3B6 41514 EA INSTRUMENT PANEL SHORTED D K NONE O OTHER IN INSP/MAINT 1 NM 08 9140X 243245 L2568451A WHILE INSTALLING NEW J. P. INSTRUMENT, REMOVAL OF CIRCUIT BREAKER PANEL REVEALED THE BATTERY BREAKER LINE LEAD WAS CONTA CTING THE INSTRUMENT PANEL SUPPORT STRUCTURE AND HAD BURNED A PENCIL SIZED HOLE IN STRUCTURE. IT APPEARED THIS WAS FACT ORY INSTALLED. RELIEVED PANEL STRUCTURE AND INSTALLED SMALLER DIMENSION BREAKER, AND PLASTIC SHIELD. (X) 1 L 7 1 3O 3 O 2A3 1E10 2001030200034 20010302 00034 SO 2001 3 2 20001130SH001 2 20001013 G 7414 6310 MAGNETO CESSNA 180 180J 2072622 CE CONT O470 O470R 17026 SO ENGINE FAILED B UM9R K NONE O OTHER IN INSP/MAINT 1 NM 13 9912N 5 18052567 MAGNETO FAILED TO OPERATE. AFTER 4.5 HOURS OF OPERATION. DISASSEMBLY REVEALED THAT DISTRIBUTOR BLOCK TAB NEXT TO COIL HAD BURNED AND MELTED CAUSING MAGNETO TO BECOME INOPERATIVE. DEFECT WAS REPORTED TO SLICK TECHNICAL SERVICES DEPARTMENT . SUBMITTER SUSPECTED COIL WAS CRACKED OR LEAKING AND CAUSED THIS FAILURE. (X) 1 H 7 1 3O 3 O 5A6 E273 2001030200035 20010302 00035 SW 2001 3 2 20001130SH003 1 20001109 G 5347 SEAT TRACK GULSTM 690TP 690B 7630516 SW PILOT SEAT CORRODED B MV5R K NONE O OTHER IN INSP/MAINT 1 GL 11 9LV 6088 11550 PILOT INBOARD SEAT RAIL LOCATED AT THE FLOOR ATTACHMENT HAD EVIDENCE OF CORROSION AT THE AFT ATTACHMENT SCREWS. (X) 1 H 7 2 3T 2A4 2001030200036 20010302 00036 CE 2001 3 2 20001130SH004 1 20001101 G 3240 AN313A BOLT CESSNA 172 172S 2072439 CE PARK BRAKE BACKED OUT D K NONE S AFFECT SYSTEMS IN INSP/MAINT 1 NM 03 949SP 823 172S8145 DURING PHASE 2 INSPECTION, PARKING BRAKE CROSSOVER CABLE, BELLCRANK BOLT WAS BACKED OUT AND RESTRICTING PILOT''S R-RUDDE R PEDAL, FWD TRAVEL. WITH THE BOLT BACKED OUT OF THE BELLCRANK, PARKING BRAKE INOP. THE FIBERLOCK NUT WAS FOUND DOWN U NDER THE RUDDER PEDALS AND THE BOLT WAS BENT SLIGHTLY. NO PREVIOUS WORK ACCOMPLISHED ON PARKING BRAKE OR RUDDER PEDALS. IT IS ASSUMED THE NUT WAS NOT TIGHTENED ON INSTALL. THE ONLY WRITE-UP ON ACFT ENTERING PHASE INSPECT WAS PARKING BRA KE INOP. SUBMITTER RECOMMENDED THE AN3-13A BOLT SECURING THE PARKING BRAKE CROSSOVER CABLE BELLCRANK PN 0713070-9 BE IN STALLED FROM RT TO LT INSTEAD OF PRESENT INSTALL LT TO RT. (X) 1 H 7 1 3O NT 3A12 2001011101231 20010111 01231 SO 2001 1 11 20001204SH001 1 20001018 G 7160 3808016 ALT AIR DOOR PIPER PA32 PA32300 7103212 SO LYC O540 IO540K1G5 41532 EA ENGINE BROKEN E FPXA C ABORTED TAKEOFF R PARTIAL RPM/PWR LOSS TO TAKEOFF 1 SO 25 2891U 8056 57 327940184 IMMEDIATELY AFTER THROTTLE UP FOR TAKEOFF, ENGINE LOST SIGNIFICANT POWER. PILOT TRIED TO RETARD THROTTLE TO ABORT, BUT LEVER WOULD ONLY GO ABOUT HALF WAY BACK. HE THEN SLIGHTLY ADVANCED THROTTLE AND THEN WAS ABLE TO PULL THROTTLE ALL THE WAY BACK TO IDLE POSITION. THE ENGINE DEVELOPED SUFFICIANT POWER TO TAXI BACK TO THE RAMP, BUT WAS RUNNING VERY ROUGH. INSPECTION OF THE INDUCTION SYSTEM REVEALED THAT BOTH ALTERNATE AIR DOOR DISCS HAD BROKEN AND LARGE PIECES INGESTED INT O THE ENGINE. ONE HAD LODGED IN THE FUEL SERVO RESTRICTING THE MOVEMENT OF THE AIR VALVE. SEVERAL PIECES MADE IT INTO THE CYLINDERS AND MELTED OVER THE BOTTOM SPARK PLUGS. THE DEBRIS WAS REMOVED, THE INDUCTION SYSTEM CLEANED. 1 L 7 1 3O 3 O A3SO 1E4 2000121800227 20001218 00227 EA 2000 12 18 20001204SH010 2 20001115 G 7310 LINE PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA NR 6 CYLINDER BROKEN E A UNSCHED LANDING Y ENGINE STOPPAGE CR CRUISE 1 WP 19 600EE 317952158 L464861A THE NR 1 ENGINE QUIT EN ROUTE. THE PILOT ATTEMPTED TO RESTART THE DEAD ENGINE WITH NO SUCCESS. A FORCED LANDING WAS SU CCESSFULLY MADE. THE LEFT ENGINE WAS LATER REMOVED FROM THE AIRCRAFT AND INSTALLED ON A TEST STAND. THE NR 6 CYLINDER MANIFOLD TO NOZZLE, TUBE ASSY WAS FOUND BROKEN. A SERVICEABLE TUBE ASSY WAS INSTALLED FOR A TEST RUN. THE ENGINE START ED AND RAN WITH NO APPARENT PROBLEM. THE BROKEN FUEL LINE WAS APPARENTLY THE REASON THE ENGINE QUIT, AND WHY THE PILOT COULD NOT GET IT RE-STARTED. AS 93-02-05 WAS C/W 23.7 HOURS PRIOR TO THE ENGINE FAILURE. (X) 1 L 7 2 3O 3 O A20SO E14EA 2000121800228 20001218 00228 SO 2000 12 18 20001204SH011 1 20001128 G 2140 A23D0475 REGULATOR VALVE PIPER PA31 PA31350 7103110 SO FWD HEATER LEAKING H O OTHER K FLUID LOSS IN INSP/MAINT 1 SW 99 4501B 17 318052168 FUEL OBSERVED DRIPPING FROM DRAIN LINE AFTER GROUND RUN OF ENGINE WITHOUT HEATER BEING USED. VALVE WAS REMOVED FROM AIR CRAFT AND 30 PSI SHOP AIR WAS APPLIED TO INLET WITHOUT POWER TO OPEN VALVE. LEAK CHECK FLUID WAS APPLIED TO VALVE BODY AND LEAK WAS FOUND TO BE COMING FROM UNUSED MOUNTING HOLE ON VALVE BODY. (X) 1 L 7 2 3O A20SO 2000121800229 20001218 00229 SO 2000 12 18 20001204SH012 1 20001128 G 2140 AD23D0475 REGULATOR VALVE PIPER PA31 PA31350 7103110 SO FWD HEATER LEAKING H O OTHER K FLUID LOSS IN INSP/MAINT 1 SW 99 4501B 318052168 INSTALLED NEW FUEL REGULATOR SHUT-OFF VALVE. AFTER SEVERAL MINUTES OF OPERATION, VALVE BEGAN LEAKING AT BODY HALF. REM OVAL AND INSPECTION REVEALED ALL FOUR SCREWS THAT HOLD BODY VALVE TOGETHER TO BE LOOSE WITH TORQUE SEAL IN PLACE. TIGHT ENED SCREWS AND RETESTED. VALVE STILL LEAKED. REPLACED VALVE WITH NEW UNIT. SUBMITTER SUSPECTED IMPROPER TORQUE USED AS ASSEMBLY. (X) 1 L 7 2 3O A20SO 2000121800230 20001218 00230 SO 2000 12 18 20001204SH013 1 20001018 G 7810 2109217 STACK PIPER PA24 PA24 7102402 SO LYC O360 O360A1D 41514 EA INSIDE HEAT MUFF BROKEN G K NONE O OTHER IN INSP/MAINT 1 GL 11 7644P 242858 L494536 THE PIPER COMANCHE BROKE THE RT REAR EXHAUST STACK INSIDE THE CARBURETOR HEAT MUFF. THE PIPE BROKE INSIDE THE CUFF THAT IS WELDED TO THE STACK FOR THE MUFF TO ATTACH TO CAUSING THE STACK TO DROP AND ERODE ITS WAY THROUGH THE MUFF. THE HEA T BEING DIRECTED INSIDE THE ENGINE COWLING CAUSED THE INSULATION ON THE MAG P-LEAD WIRES TO MELT AND GROUND TO THE METAL HOUSING OF THE TACH CABLE THEY WERE SECURED TO, GROUNDING OUT THE MAGS AND SHUTTING DOWN THE ENGINE. AN UNEVENTFUL OFF AIRPORT LANDING OCCURRED WITH NO OTHER DAMAGE. (X) 1 L 7 1 3O 3 O 1A15 E286 2000121800231 20001218 00231 CE 2000 12 18 20001204SH014 1 20001115 G 2510 07140594 SEAT CESSNA CESSNA 182 R182 2072734 CE REAR POINT BROKEN B YEBR K NONE O OTHER IN INSP/MAINT 1 CE 05 11130 6272 R18201940 REAR ATTACH POINT ON LOWER SEAT WHERE IT ATTACHES TO THE PEDESTAL ASSEMBLY. ONE SIDE BROKEN OFF THE OTHER SIDE IS CRACK ED. BROKE AT CUT-OUT FOR SEAT PIVOT BRACKET PN 0514060-5. (X) 1 H 7 1 3O RT 3A13 2000121800232 20001218 00232 CE 2000 12 18 20001204SH015 1 20001018 G 2140 26405 SEAL CESSNA 402 402C 207590R CE RT SUB WING LEAKING D O OTHER K FLUID LOSS IN INSP/MAINT 1 NE 01 2611X 295 402C0072 AFTER DEPARTURE, CREW SMELLED FUEL AND RETURNED TO LAND, LANDING WITHOUT INCIDENT. MAINTENANCE FOUND HEATER FUEL FILTER S LEAKING. REMOVED AND REPLACED GASKET. OPS AND LEAK CHECKED OK. AIRCRAFT RELEASED FOR RETURN TO SERVICE. (X) 1 L 7 2 3O A7CE 2000121800233 20001218 00233 CE 2000 12 18 20001204SH016 1 20001019 G 3230 51420025 DRAG BRACE CESSNA 402 402C 207590R CE NOSE GEAR CRACKED D K NONE O OTHER IN INSP/MAINT 1 NE 01 6837Y 932 402C0467 UPON ROUTINE INSPECTION OF THE NOSE GEAR AREA, MAINTENANCE DETERMINED THE NOSE GEAR DRAG WAS CRACKED AT THE AREA JUST AF T OF THE ACTUATOR ATTACH LUG. MAINTENANCE REMOVED AND REPLACED THE DRAG BRACE AND RELEASED AIRCRAFT BACK TO SERVICE. ( X) 1 L 7 2 3O A7CE 2000121800234 20001218 00234 EA 2000 12 18 20001204SH018 2 20001120 G 7414 16171 CASE BENDIX CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA THREADED HOLES CORRODED D K NONE O OTHER IN INSP/MAINT 1 WP 23 739GQ 3660 500 16171 17270535 L352776 ABOVE 2,100 RPM, ENGINE WOULD HAVE ROUGHNESS. LEFT MAG WOULD CHECK GOOD, BUT RIGHT WOULD RUN ROUGH AND CAUSE AFTERFIRIN G, SOMETIMES VERY LOUDLY. BELOW 2,100 RPM, MAG CHECKS WERE NORMAL. PROBLEM TRACED TO POOR CONTACT ASSY GROUND CAUSED B Y CORROSION IN MAGNESIUM CASE THREADS WHERE DIST BLOCK RETAINING SCREWS (PN 10-35937-20) GROUND CONTACTORS. THREADS WER E BLACK IN COLOR, BUT RESTORED TO BRIGHT METAL BY RUNNING A TAP IN. OHMMETER TESTS RESULTED IN 3 TO 10 OHMS RESISTANCE BEFORETHREADS WERE CLEANED. (X) 1 H 7 1 3O 3 O NT 3A12 E274 2000121800235 20001218 00235 CE 2000 12 18 20001204SH019 1 20001114 G 5210 05170392 HANDLE CESSNA 185 A185F 2072821 CE CABIN INTERIOR FAILED D K NONE O OTHER IN INSP/MAINT 1 SW 03 61301 100 18504144 THE HANDLE SPLINE BUSHING STRIPED CAUSING HANDLE FAILURE. (X) 1 H 7 1 3O 3A24 2000121900203 20001219 00203 CE 2000 12 19 20001205SH009 1 20001103 G 5210 52113492 PIN CESSNA 402 402C 207590R CE LATCH UP CABN DR BROKEN D A UNSCHED LANDING O OTHER CR CRUISE 1 NE 01 548GA 402C0653 DURING FLIGHT, UPPER CABIN DOOR OPENED. AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND FORWARD LATCH PIN BROKEN A T BELLCRANK ATTACH POINT. REPLACED LATCH PIN AND ASSIST SPRINGS AND RELEASED THE AIRCRAFT BACK TO SERVICE. (X) 1 L 7 2 3O A7CE 2000121900204 20001219 00204 EA 2000 12 19 20001205SH010 2 20001107 G 8530 60828 PLUG AMTR MSTG2 MUSTANG2 GL LYC O320 O320E2D 41508 EA NR 1 CYLINDER ERODED D K NONE O OTHER IN INSP/MAINT 1 SO 13 54JL 1700 1776 RL04219027A NOTED LOW COMPRESSION. REMOVED NR 1 CYLINDER, NOTED 1 EACH PISTON PIN PLUG MISSING. OTHER PISTON PIN PLUGS WORN TO TAP ERED SIZE. PISTON PIN HOLE IN PISTON SEVERELY ELONGATED AND MELTED. ALUMINUM NUGGETS FOUND INSIDE OF PISTON PIN. OIL FILTER CONTAINED LARGE AMOUNTS OF METAL. SUCTION SCREEN HAD METAL. OTHER CYLINDER PISTON PIN PLUGS SHOWED SIMILAR WEAR . OPERATOR USING PHILLIPS 20/50 OIL AND 89 OCTANE AUTOGAS AND 100LL AVGAS. (X) 1 L 7 1 3O 3 O EXPA1L71 E274 2000121900206 20001219 00206 CE 2000 12 19 20001205SH012 1 20001006 G 3245 40135 WHEEL CESSNA 414 414A 2075907 CE LT OTBD RIM CRACKED H K NONE O OTHER IN INSP/MAINT 1 GL 25 414SF 414A0488 UPON AN ANNUAL INSPECTION, THE LEFT MAIN WHEEL WAS REMOVED AND CLEANED. AFTER CLEANING, A 4 INCH CRACK WAS NOTICED NEXT TO RIM ON THE OUTBOARD WHEEL. AIR WAS REMOVED AND WHEEL DISASSEMBLED. THE CRACK WAS ALL THE WAY THROUGH. ALSO, THE O NE BRAKE PAD WAS MISSING. NO OTHER DAMAGE FOUND. SUBMITTER SUSPECTED HARDER THAN NORMAL LANDING. (X) 1 L 7 2 3O A7CE 2000121900207 20001219 00207 SO 2000 12 19 20001205SH013 1 20001110 G 3030 587954 PIVOT PIPER PA34 PA34200T 7103406 SO PILOTS CNTRL PNL CORRODED E GAYA O OTHER O OTHER NR NOT REPORTED 1 NM 07 8514C 347670147 PILOT REPORTED THE AIRCRAFT''S PITOT HEAT SYSTEM TO BE INOPERATIVE. INSPECTION REVEALED THE SWITCH ASSY TO HAVE CORROSI ON IN THE CONTACTS. THE CORROSION APPEARED TO BE CAUSED BY MOISTURE SUCH AS RAINWATER. (X) 1 L 7 2 3O A7SO 2001021500021 20010215 00021 EU 2001 2 15 20001205SH027 1 20001117 G 8012 VALVE SNIAS 350 AS350BA 8680817 EU START DRAIN LEAKING E KBMA K NONE K FLUID LOSS IN INSP/MAINT 1 WP 19 270SH 1864 START DRAIN VALVE LEAKING. REPLACED. (X) 1 G 7 1 3U NC H9EU 2001021500022 20010215 00022 EU 2001 2 15 20001205SH028 1 20001115 G 8012 0174078010 VALVE SNIAS 350 AS350B 8680801 EU START DRAIN LEAKING E KBMA K NONE K FLUID LOSS IN INSP/MAINT 1 WP 19 37SH 2300 START DRAIN VALVE LEAKING. (X) 1 G 7 1 3U H9EU 2001021500023 20010215 00023 EU 2001 2 15 20001205SH029 1 20001115 G 7722 56265220 INDICATOR SNIAS 350 AS350B 8680801 EU ENGINE T-4 DAMAGED E KBMA K NONE O OTHER IN INSP/MAINT 1 WP 19 37SH 2300 T-4 GAUGE UNSERVICEABLE. (X) 1 G 7 1 3U H9EU 2001011101256 20010111 01256 NE 2001 1 11 20001206SH001 1 20000926 G 6210 7615009100041A BLADE SKRSKY S76 S76A 8143006 NE MAIN ROTOR DEBONDED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 712AL 10072 264 760280 DISCOVERED DURING POST-FLIGHT INSPECTION (VIBRATION WAS FELT DURING FLIGHT). EXTENSIVE UPPER SURFACE SKIN DISBOND. (X) 1 G 7 2 3U H1NE 2001011101257 20010111 01257 SW 2001 1 11 20001206SH002 1 20000724 G 7810 407062021101 DUCT BELL 407 407 SW EXHAUST CRACKED B ALGA K NONE O OTHER IN INSP/MAINT 1 SW 03 527AL 53211 DURING DAILY INSPECTION FOUND DUCT ASSY CRACKED IN CORNERS. (X) 1 G 7 1 3U O H2SW 2001011101258 20010111 01258 SW 2001 1 11 20001206SH003 1 20000922 G 6310 406040516101 SHAFT BELL 407 407 SW FREEWHEEL UNIT WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 557AL 1389 A4013 53243 DURING SEAL REPAIR, FOUND WORN SPLINES. (X) 1 G 7 1 3U O H2SW 2001011101259 20010111 01259 NE 2001 1 11 20001206SH004 1 20001013 G 3212 7625100702042 EXPLOSIVE LINK SKRSKY S76 S76A 8143006 NE RT MLG DOOR DISCHARGED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 712AL 760280 AIRCRAFT FLOATS WERE INADVERTENTLY DISCHARGED. MALFUNCTION WAS DISCOVERED DURING REMOVAL OF RT MAIN GEAR DOOR. EXPLOSI VE CHARGE DISCHARGED WHEN FLOATS TRIPPED, BUT LINK DID NOT SEPARATE. (X) 1 G 7 2 3U H1NE 2001011101260 20010111 01260 GL 2001 1 11 20001206SH005 2 20001113 G 7240 23062752 NOZZLE RROYCE C47 BELL 407 407 SW ALLSN 250C 250C47B GL 1ST STAGE BROKEN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 487AL 1890 CAT44414 53204 TURBINE RECEIVED IN SHOP TO PERFORM 2000 HOUR OVERHAUL. UPON REMOVAL OF OUTER COMBUSTION CASE AND COMBUSTION LINER, FOU ND A HOLE IN DOME OF 1ST STAGE SHIELD. ALSO, FOUND THE BROKEN PIECE LODGED ON 1ST STAGE NOZZLE VANE. POSSIBLE IMPROPER METAL USED TO MAKE DOME. PART WAS SCRAPPED, UNABLE TO REPAIR. (X) 1 G 7 1 3U 3 U O H2SW E1GL 2001011101261 20010111 01261 SW 2001 1 11 20001206SH006 1 20001025 G 7921 407062021101 DUCT BELL 407 407 SW ALLSN 250C 250C47B GL OIL COOLER CRACKED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 427AL 53107 DURING DAILY INSPECTION, FOUND OIL COOLER BLOWER CRACKED. (X) 1 G 7 1 3U 3 U O H2SW E1GL 2001021500024 20010215 00024 SW 2001 2 15 20001206SH007 1 20000808 G 6510 206061432121 HOUSING BELL 407 407 SW TAIL ROTOR CRACKED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 587AL 603 AFS1204 53248 DURING DAILY INSPECTION, FOUND OCB HOUSING CRACKED DUE TO VIBRATION. (X) 1 G 7 1 3U O H2SW 2001021500025 20010215 00025 SW 2001 2 15 20001206SH008 1 20001029 G 6510 206340300105 DRIVE SHAFT BELL 407 407 SW ALLSN 250C 250C47B GL TRANSMISSION FAILED B ALGR A UNSCHED LANDING O OTHER NR NOT REPORTED 1 SW 03 687AL 1806 53366 IN-FLIGHT, PILOT HEARD A LOUD POP. LANDED AT THE NEAREST PLATFORM AND AFTER SHUT DOWN, FOUND FORWARD FLEXURE ON INPUT D RIVESHAFT HAD FAILED. ONE OF THE FORWARD FLEXURES FAILED AT THE BOLT HOLE AND A PORTION OF THE FLEXURE WENT THROUGH THE TRANSMISSION DECK/CABIN ROOF. (X) 1 G 7 1 3U 3 U O H2SW E1GL 2001021500026 20010215 00026 EU 2001 2 15 20001206SH009 1 20001107 G 6510 350A34021006 DRIVE SHAFT SNIAS 350 AS350B2 8680813 EU TAIL ROTOR DAMAGED B B3OR K NONE O OTHER IN INSP/MAINT 1 SW 03 5204J 486 3118 DURING 500-HOUR INSPECTION, FOUND INNER SLEEVE OF AFT MOST BEARING SLIPPING ON T/R DRIVESHAFT. IT APPEARED TO HAVE BEEN SPINNING FOR SOME TIME AND RUBBER HAD ACTUALLY TRANSFERRED FROM SLEEVE TO SHAFT. SHAFT ITSELF WAS NOT DAMAGED. REPLAC ED ENTIRE SHAFT ASSEMBLY DUE TO WARRANTY AND REPAIR DIFFICULTY. (X) 1 G 7 1 3U H9EU 2001021500027 20010215 00027 EU 2001 2 15 20001206SH010 1 20001107 G 6220 350A31185421 BOLT SNIAS 350 AS350B2 8680813 EU MAIN ROTOR CORRODED B B3OR K NONE O OTHER IN INSP/MAINT 1 SW 03 5204J 486 3118 DURING 500-HOUR INSPECTION, FOUND CORROSION ON SLEEVE ATTACHING BOLTS. NOTED MASTINOX WAS NOT USED AT THE TIME OF ASSEM BLY. REF: S/NS 6327, 6329, 6339, 6343, 6370, AND 6380. (X) 1 G 7 1 3U H9EU 2001021500028 20010215 00028 EU 2001 2 15 20001206SH011 1 20001107 G 6220 350A31185003 FLANGE SNIAS 350 AS350B2 8680813 EU MAIN ROTOR CORRODED B B3OR K NONE O OTHER IN INSP/MAINT 1 SW 03 5204J 486 3118 DURING 500-HOUR INSPECTION, FOUND CORROSION ON UPPER SLEEVE FLANGE HOLES. NOTED MASTINOX WAS NOT USED AT THE TIME OF AS SEMBLY. (X) 1 G 7 1 3U H9EU 2001021500029 20010215 00029 EU 2001 2 15 20001206SH012 1 20001107 G 6220 350A31185002 FLANGE SNIAS 350 AS350B2 8680813 EU MAIN ROTOR CORRODED B B3OR K NONE O OTHER IN INSP/MAINT 1 SW 03 5204J 486 3118 DURING 500-HOUR INSPECTION, FOUND CORROSION ON LOWER SLEEVE FLANGE. NOTED MASTINOX WAS NOT USED AT THE TIME OF ASSEMBLY . REF: S/N M4413, M4415, M4417. (X) 1 G 7 1 3U H9EU 2001021500030 20010215 00030 EU 2001 2 15 20001206SH013 1 20001107 G 6220 704A33640046 ADAPTER SNIAS 350 AS350B2 8680813 EU MAIN ROTOR CORRODED B B3OR K NONE O OTHER IN INSP/MAINT 1 SW 03 5204J 486 3118 DURING 500-HOUR INSPECTION, FOUND CORROSION IN BOLT HOLES OF FREQUENCY ADAPTER. NOTED MASTINOX WAS NOT USED AT THE TIME OF ASSEMBLY. (X) 1 G 7 1 3U H9EU 2001021500031 20010215 00031 EU 2001 2 15 20001206SH014 1 20001107 G 6220 704A33633208 BEARING SNIAS 350 AS350B2 8680813 EU MAIN ROTOR CORRODED B B3OR K NONE O OTHER IN INSP/MAINT 1 SW 03 5204J 486 3118 DURING 500-HOUR INSPECTION, FOUND CORROSION ON THE SPHERICAL THRUST BEARING HOLES. NOTED MASTINOX WAS NOT USED AT THE T IME OF ASSEMBLY. REF: S/N''S LK3520, LK3544, LK3678. (X) 1 G 7 1 3U H9EU 2001021500032 20010215 00032 SW 2001 2 15 20001206SH018 1 20001116 G 6510 407340339103 BEARING BELL 407 407 SW T/R DRIVE ROUGH E R6LA K NONE O OTHER IN INSP/MAINT 1 SW 19 1116H 53046 C/W THE INTENT OF AD 2000-02-12 BY INSPECTING OIL COOLER BLOWER DRIVESHAFT BEARINGS. AFT BEARING FOUND ROUGH RUNNING. (X) 1 G 7 1 3U O H2SW 2001030200038 20010302 00038 CE 2001 3 2 20001206SH019 1 20001201 G 5523 9661000668 ATTACH FITTING BEECH 55 E55 1152732 CE ELEV TRIM TAB CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 25 1025T 3475 TE950 STEEL HORN WITH BRAZED BUSHING CRACK ON HORN ONLY, NOT INTO BUSHING. CAUSE UNKNOWN. (X) 1 L 7 2 3O 3A16 2001030200039 20010302 00039 CE 2001 3 2 20001206SH020 1 20001118 G 3233 35380094 MOTOR BEECH 35 V35B 1151548 CE MLG FAILED D K NONE L NO TEST IN INSP/MAINT 1 SO 15 1825L D9877 DURING RETRACT TEST, LANDING GEAR MOTOR TRIPPED CIRCUIT BREAKER. TROUBLESHOOTING REVEALED EMERGENCY DOWN CRANK IMPOSSIB LE TO TURN. REPLACEMENT OF MOTOR RESOLVED PROBLEM. CONCERN THAT FAILED GEAR MOTOR COULD RENDER EMERGENCY CRANK INOPERA TIVE RESULTING IN A WHEELS UP LANDING. (X) 1 L 7 1 3O 3A15 2001030200040 20010302 00040 SO 2001 3 2 20001206SH022 2 20001114 G 8520 652832 CRANKSHAFT CESSNA 421 421C 2076016 CE CONT O520 GTSIO520L 17032 SO ENGINE BROKEN B K NONE O OTHER IN INSP/MAINT 1 SW 07 11NP 1570 421C0093 272362R CRANKSHAFT BROKEN AFT ON NR 2 ROD JOURNAL AT NR 2 MAIN BEARING. ENGINE HAD 401.0 HOURS SINCE RE-MANUFACTURE. (X) 1 L 7 2 3O 3 O A7CE E7CE 2001021500033 20010215 00033 2001 2 15 20001206SH024 4 20001127 G 3416 D120P2T ENCODER SNIAS 350 AS350BA 8680817 EU ALTIMETER INOPERATIVE E KBMA K NONE O OTHER IN INSP/MAINT 1 WP 19 180EH 2337 ENCODER IS BAD. (X) 1 G 7 1 3U NC H9EU 2001021500034 20010215 00034 SW 2001 2 15 20001206SH025 1 20000814 G 6220 222011114103 SUPPORT BRACKET BELL 222 222U 1182140 SW M/R HEAD FRACTURED E STRA A UNSCHED LANDING E F VIBRATION/BUFFET FLT CONT AFFECTED CR CRUISE 1 WP 27 222UT 3058 47559 PILOT EXPERIENCED A MAIN ROTOR VIBRATION WHICH SUBSEQUENTLY BECAME SEVERE DURING CRUISE FLIGHT. PILOT MADE A LANDING AT NEAREST AIRPORT, DURING SHUT DOWN OF ENGINES, VIBRATION WENT AWAY. INVESTIGATION OF MAIN ROTOR SYS NOTED THE LOWER PEN DULUM OF ONE OF THE BLADES WAS MISSING. FURTHER INSP REVEALED A SLIGHT NICK TO THE T/E OF THE M/R BLADE. UPON EXAMINAT ION OF THE PENDULUM AFTER REMOVAL, SHOWED THE TANGS HAD FRACTURED AND THERE WERE SIGNS OF A PREVIOUS CRACK. PART SENT T O BHT FOR EVALUATION. (X) 1 G 7 2 3U H9SW 2000121500186 20001215 00186 EA 2000 12 15 20001206SH026 2 20001030 G 8520 CRANKSHAFT CESSNA 172 172R 2072401 CE LYC IO360 IO360L2A EA PROP/BUSHING FAILED B QRQR K NONE O OTHER IN INSP/MAINT 1 SW 05 2269S 7 17280955 L2911051A THIS ACFT RECEIVED NEW FROM CESSNA FACTORY. UPON REMOVAL OF PROPELLER TO FACILITATE INSTALL OF AFTERMARKET AIR CONDITIO NERS, NOTED THAT 2 OF THE 4 PROPELLER ALIGNMENT BUSHINGS THAT ARE PRESSED INTO THE CRANKSHAFT FLANGE WERE EXTRUDED FROM THE BACKSIDE OF THE FLANGE APPROX .375 INCH. THE APPARENT CAUSE OF THIS DEFECT WAS THE IMPROPER CLOCKING OF THE PROP TO THE CRANKSHAFT. (X) 1 H 7 1 3O 3 O NT 3A12 1E10 2001030200041 20010302 00041 CE 2001 3 2 20001206SH027 1 20001117 G 2810 SEALANT CESSNA 140 140 2071602 CE LT MAIN FUEL TNK FAILED G K NONE O OTHER IN INSP/MAINT 1 EA 13 279W 7980 556 9976 LARGE PARTICLES OF SLOSHING TYPE FUEL TANK SEALANT WERE FOUND ON THE FUEL TANK FINGER SCREEN DURING A POST-ACCIDENT INSP ECTION. THE SUBJECT ACFT HAD AN AUTOFUEL STC WHICH MAY NOT HAVE BEEN COMPATIBLE WITH THE SEALANT WHICH WAS APPLIED IN 1 957. (X) 1 H 7 1 3O NC A768 2001030200042 20010302 00042 2001 3 2 20001206SH028 4 20001117 G 3416 WIRE CESSNA 320 320D 2074512 CE ALTIMETER CHAFED D K NONE O OTHER IN INSP/MAINT 1 EA 17 254KB 320D0103 A/F TOTAL TIME, 11,510.2 HOURS. INTERMITTENT ERRONEOUS ALTITUDE MODE C INDICATION. FOUND CHAFED WIRE FROM ENCODING ALT IMETER TO TRANSPONDER. REPAIRED WIRING AND SECURE. (X) 1 L 7 2 3O 3A25 2001030200043 20010302 00043 EA 2001 3 2 20001206SH029 2 20001023 G 7322 CARBURETOR PIPER PA23 PA23150 7102303 CE LYC O320 O320* 41508 EA ENGINE ICED C A UNSCHED LANDING Y ENGINE STOPPAGE NR NOT REPORTED 1 NM 01 3127P 231050 ENGINE FAILURE DUE TO CARBURETOR ICE. FAILURE OCCURRED WITHIN 15 SECONDS OF SELECTING FUEL TRANSFER. ASSUMPTION THAT P ROBLEM WAS WITH FUEL TRANSFER DELAYED APPLICATION OF CARBURETOR HEAT. (X) 1 L 7 2 3O 3 O RT 1A10 E274 2001030200044 20010302 00044 CE 2001 3 2 20001206SH030 1 20001114 G 7930 LINE CESSNA 206 TU206A 2073318 CE INSTRUMENT PANEL CORRODED B IC1R K NONE K FLUID LOSS IN INSP/MAINT 1 EA 23 4801F 4258 U2060501 LINE SHOWS SIGNS OF INTERGRANULAR CORROSION. OIL LINE IN COCKPIT BEHIND INSTRUMENT PANEL SUPPLYING OIL PRESSURE GAUGE R UPTURED CAUSING APPROXIMATELY 3 QUARTS OF OIL TO ENTER CABIN PRIOR TO AIRCRAFT LANDING. REPLACED LINE ASSEMBLY, NO LEAK S NOTED. (X) 1 H 7 1 3O A4CE 2001020900103 20010209 00103 SO 2001 2 9 20001206SH031 2 20001116 G 8520 CONNECTING ROD CESSNA 421 421C 2076016 CE CONT O520 GTSIO520H 17032 SO NR 5 CYLINDER FAILED E P6VA O OTHER K J FLUID LOSS WARNING INDICATION CL CLIMB 1 EA 07 410AJ 1216 421C1093 610473 AIRCRAFT WAS CLIMBING AFTER TAKEOFF, LOUD NOISE HEARD BY PILOT, OIL PRESSURE STARTED TO DROP, ENGINE FEATHERED. AIRCRAF T LANDED WITHOUT INCIDENT. FOUND NR 5 CYLINDER CONNECTING ROD FAILED, KNOCKED HOLE IN UPPER CRANKCASE. ENGINE TOTAL T IME 2,768.7 HOURS, 1,215.7 HOURS SMOH. (X) 1 L 7 2 3O 3 O A7CE E7CE 2001020900104 20010209 00104 CE 2001 2 9 20001206SH032 1 20001120 G 8120 MILH60004 LINE CESSNA 421 421C 2076016 CE CONT O520 GTSIO520N 17032 SO LT ENGINE LOOSE E DYVA O OTHER Y ENGINE STOPPAGE CR CRUISE 1 NM 07 4119M 421C1029 277163R THE LEFT ENGINE TURBOCHARGER COMPRESSOR DISCHARGE REFERENCE LINE CAME OFF AT CRUISE POWER AT 15,500 FEET CAUSING THE ENG INE TO DIE WITH AN EXCESSIVELY RICH MIXTURE. THE PILOT DID NOT ATTEMPT LEANING DURING TROUBLESHOOTING AND FEATHERED THE ENGINE, LANDED SAFELY WITH NO FURTHER INCIDENT. THE REFERENCE LINE WAS SECURED AND ENGINE OPERATION CHECKED NORMAL. ( X) 1 L 7 2 3O 3 O A7CE E7CE 2001011101264 20010111 01264 CE 2001 1 11 20001207SH001 1 20001205 G 5730 MS24694C51 SCREW CESSNA CESSNA 500 550 2076604 CE WING SKIN IMPROPER PART C K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 99 1200N 5500681 UPON INSPECTION OF AREA UNDER HEATED LEADING EDGE (TOP FORWARD SCREW), IT WAS FOUND THAT THE SCREW HAD CONTACTED THE SKI N SURFACE. THE SCREW HAD PENETRATED PART OF A RIVET HEAD ON THE LEFT WING AND EXTENDED INTO THE SKIN APPROXIMATELY 0.03 2” INCH. THE SCREW ON THE RIGHT WING HAD NOT CONTACTED A RIVET HEAD BUT HAD PENETRATED THE SKIN BY APPROXIMATELY 0.028 INCH”. THE CORRECT HARDWARE WAS USED PER THE AIRCRAFT MANUFACTURER’S PARTS CATALOGUE. REPAIR OR REPLACEMENT OF THE WING SKIN OVERLAYING THE FUEL CELL WILL BE REQUIRED TO RETURN THE AIRCRAFT TO SERVICE. (X) 1 L 7 2 4F A22CE 2001011101265 20010111 01265 CE 2001 1 11 20001207SH002 1 20001205 G 5730 MS24694C51 SCREW CESSNA CESSNA 500 550 2076604 CE WING SKIN IMPROPER PART C K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 99 4614N 5500659 UPON INSPECTION OF AREA UNDER HEATED LEADING EDGE (TOP FORWARD SCREW), IT WAS FOUND THAT THE SCREW HAD CONTACTED THE SKI N SURFACE. THE SCREW HAD PENETRATED PART OF A RIVET HEAD ON THE LEFT WING AND EXTENDED INTO THE SKIN APPROXIMATELY 0.05 0” INCH (POSSIBLY A COMBINATION OF PENETRATION AND DIMPLING). THE SCREW ON THE RIGHT WING HAD CONTACTED A RIVET HEAD DE AD CENTER AND PENETRATED THE RIVET APPROXIMATELY 0.030 INCH”. THE CORRECT HARDWARE WAS USED PER THE AIRCRAFT MANUFACTUR ER’S PARTS CATALOGUE. THE LEFT WING WILL REQUIRE REPAIR OR REPLACEMENT OF THE WING SKIN OVERLAYING THE FUEL CELL, THE R IGHT WING WILL REQUIRE REPLACEMENT OF THE RIVET IN THE FUEL CELL IN ORDER TO RETURN THE AIRCRAFT TO SERVICE. (X) 1 L 7 2 4F A22CE 2001020900105 20010209 00105 SO 2001 2 9 20001207SH003 1 20001115 G 2140 A23D0475 REGULATOR JANITROL PIPER PA31 PA31350 7103110 SO HEATER LEAKING A FFSA O OTHER K FLUID LOSS IN INSP/MAINT 1 AL 01 4501B 164 5954723 318052168 FUEL WAS OBSERVED LEAKING FROM DRAIN TUBE. INVESTIGATION REGVEALED VALVE TO BE LEAKING FORM DIAPHRAGM PARTING SURFACE. VALVE BODY SCREWS WERE FOUND LOOSENED OVER TIME. SUGGESTED SELECTION OF ALTERNATE LOCKING DEVICE TO PREVENT RECURRENCE . (X) 1 L 7 2 3O A20SO 2001021500035 20010215 00035 SW 2001 2 15 20001207SH004 1 20001116 G 6510 407340339103 BEARING BELL 407 407 SW T/R DRIVE ROUGH E R6LA K NONE O OTHER IN INSP/MAINT 1 SW 19 58236 53069 C/W THE INTENT OF HD 2000-02-12 BY INSPECTING OIL COOLER BLOWER D/S BEARINGS. AFT BEARING FOUND ROUGH RUNNING. (X) 1 G 7 1 3U O H2SW 2001030200045 20010302 00045 CE 2001 3 2 20001207SH005 1 20001114 G 2436 DGR3 REGULATOR CESSNA 172 172P 2072436 CE ALTERNATOR FAILED B IC1R K NONE B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 EA 23 65003 17275666 ALTERNATOR CONTROL UNIT FAILED INTERNALLY EMITTING SMOKE ODOR. REPLACED ACU AND INSPECTED CHARGING SYSTEM FOR OPERATION IAW CESSNA MM. (NO DEFECTS NOTED). (X) 1 H 7 1 3O NT 3A12 2001030200046 20010302 00046 CE 2001 3 2 20001207SH006 1 20001024 G 2751 45AS61015021 SWITCH BEECH MU300 400A 1155402 CE LT FLAP OUT OF ADJ B K NONE J WARNING INDICATION LD LANDING 1 GL 23 695BK 577 RK235 FLAP ASYMMETRY LIGHT ILLUMINATED DURING LANDING. ADJUSTED LEFT FLAP FOLLOW-UP SWITCH OUTPUT VOLTAGE TO ASYMMETRY DETECT OR IAW WITH THE RAYTHEON 400/400A MM. OPERATIONAL CHECK GOOD. (X) 2 H 7 2 4F RT A16SW 2001030200047 20010302 00047 EA 2001 3 2 20001207SH007 2 20001127 G 7322 105193 CARBURETOR PRECISION CESSNA 172 172P 2072436 CE LYC O360 O360A4M 41514 EA ENGINE CRACKED B AQ2R K NONE K FLUID LOSS IN INSP/MAINT 1 EA 07 65516 651 75056408 17275769 L3557336A FOUND CRACKS IN FLOAT BOWL ON LOWER THROUGH-BOLT BOSS. APPEARED TO BE A FORGING PROBLEM. (X) 1 H 7 1 3O 3 O NT 3A12 E286 2001030200048 20010302 00048 EA 2001 3 2 20001207SH008 2 20001109 G 7414 10349276H WIRE GULSTM 500 500B 0141106 SW LYC O540 IO540E1B5 41532 EA CAPACITOR BROKEN D K NONE R PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 CE 07 724LH 182 F070005ER 1613211 RL112048 PILOT REPORT MAGNETO INOPERATIVE. POST-REPLACEMENT INSPECTION REVEALED POINTS BURNT, CAPACITOR WIRE BROKEN AT CAPACITOR END. (X) 1 H 7 2 3O 3 O 6A1 1E4 2000121500191 20001215 00191 CE 2000 12 15 20001207SH009 1 20001101 G 7603 63255535 THROTTLE ARM BEECH 58 58 1152740 CE RIGHT FAILED D K NONE O OTHER IN INSP/MAINT 1 SO 01 7279R TH587 RIGHT THROTTLE ARM, PN 632555-35, FAILED PER DRAWING. THIS IS AT LEAST 10 TIMES ON 10 DIFFERENT AIRPLANES IN PAST 8 YEA RS THIS PART OR SAME P/N MIXTURE ARM HAD FAILED. NEEDS SB OR AD. (X) 1 L 7 2 3O 3A16 2001030200049 20010302 00049 CE 2001 3 2 20001207SH010 1 20001127 G 2823 SELECTOR VALVE CESSNA 172 172B 2072406 CE COCKPIT INOPERATIVE D K NONE O OTHER IN INSP/MAINT 1 SO 13 7752X 4035 17248252 DURING ANNUAL INSPECTION, NOTED THE FUEL SELECTOR VALVE WOULD NOT SHUT OFF FUEL. THIS COULD BE A HAZARD IF AN IN-FLIGHT FIRE OCCURRED. (X) 1 H 7 1 3O NT 3A12 2001030200050 20010302 00050 2001 3 2 20001207SH011 4 20001127 G 2562 7A1132 ELT CESSNA 172 172B 2072406 CE TAIL FAILED D K NONE O OTHER IN INSP/MAINT 1 SW 13 7752X 17248252 DURING ANNUAL INSPECTION, ELT WAS FOUND NOT TO MEET FAR 91.207(D). IT FAILED G-TEST AND WAS MOUNTED IMPROPERLY IN AIRCR AFT. IT WAS MOUNTED WITH VELCRO AND A DETERIORATED STRAP. (X) 1 H 7 1 3O NT 3A12 2001030200051 20010302 00051 CE 2001 3 2 20001207SH012 1 20001127 G 7920 HOSE CESSNA 172 172B 2072406 CE OIL PRESSURE BROKEN D K NONE K FLUID LOSS IN INSP/MAINT 1 SO 13 7752X 17248252 DURING ANNUAL INSPECTION, OIL PRESSURE HOSE WAS FOUND WET WITH OIL. AFTER REMOVING HOSE, HOSE CRACKED AND BROKE WHEN TW ISTED. FUEL HOSE WAS CHECKED AND WAS IN THE NEAR SAME CONDITION. NO LOG ENTRY FOUND AS TO WHEN AND IF THESE HOSES HAD BEEN REPLACED. (X) 1 H 7 1 3O NT 3A12 2001030200052 20010302 00052 CE 2001 3 2 20001207SH013 1 20001102 G 5712 RIB CESSNA 172 172K 2072430 CE LT WING DAMAGED B A5OR K NONE O OTHER IN INSP/MAINT 1 SO 09 7122G 1457 17258822 DURING A HIDDEN DAMAGE INSP, LT WING ASSY PN 0523005-83 FOUND LIGHT DAMAGE TO MID L/E SKIN AND 1 NOSE RIB, UNAPPROVED RE PAIR FOUND TO AFT INBD SPAR ASSY. ALMOST ALL NOSE RIBS IN WING FOUND DAMGED, 10 IN ALL. A T/E RIB WAS CUT BY A FLAP CO NTROL CABLE. 4 SKINS FOUND DAMAGED, OTBD L/E SKIN. RECORDS CHK BY OWNER SHOWED ACFT WING WAS REPAIRED AND RETURNED TO SERVICE. THE SPAR SPLICE WAS NOT DONE IAW CESSNA SM. RT WING INSP, FOUND RT WING WITH 7 DAMAGED NOSE RIBS 2 EACH L/E S KINS DAMAGED, AFT SPAR SPLICED, DAMAGE TO SEVEN OTHER SKINS. (X) 1 H 7 1 3O NT 3A12 2001030200053 20010302 00053 CE 2001 3 2 20001207SH014 1 20001024 G 8011 TAB CESSNA 210 210 2073402 CE SOLENOID BROKEN D K NONE O OTHER IN INSP/MAINT 1 WP 09 7431E 247 57131 MOUNTING TABS BROKE OFF ON BOTH SIDES OF THE STARTER SOLENOID BREAKING GROUND CONNECTION SO STARTER WAS INOP. SOLENOID IS MOUNTED DIRECTLY ON THE STARTER. MOUNTING BRACKET IS SPOT WELDED TO SOLENOID HOUSING. FAILURE POSSIBLY DUE TO VIBRA TION. REPLACED SOLENOID. (X) 1 H 7 1 3O RT 3A21 2001030200054 20010302 00054 GL 2001 3 2 20001207SH015 3 20001127 G 6110 83037L LOCK GULSTM 690TP 690C 7630517 SW HARTZL HCB3T HCB3TN5 GL PROPELLER BROKEN B V5SR K NONE O OTHER IN INSP/MAINT 1 SW 15 840V 117 11727 BUA22884 START-LOCK BROKE AND PIN FELL OUT BECAUSE RETAINING COTTER PIN WAS TOO WEAK. (X) 1 H 7 2 3T 2A4 6 C P15EA 2001030200055 20010302 00055 CE 2001 3 2 20001207SH016 1 20001121 G 3230 504501019 TORQUE TUBE CESSNA 310 310Q 2074242 CE LT MLG CRACKED H A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 EA 03 8TC 310Q0264 AFTER TAKEOFF, PILOT ADVISED BY GROUND OBSERVERS, LT MLG STILL DOWN. GEAR CYCLED SEVERAL TIMES, GROUND OBSERVERS REPORT ED LT MAIN GEAR STILL DOWN. GEAR SELECTED DOWN, SAFE LANDING. INSP SHOWED LT M/G TORQUE TUBE, PN 5045010-19, CRACKED, FAILED. CRACK APPEARED TO ORIG BTWN THREADED BOSS WHERE FORK BOLT PN 5141052-1 LATCHES, AND AFT FLANGE OF AFT PIVOT BOL T MOUNTING BRACKET. AREA OF BOSS, CRACK RUSTED FOR APPROX 1.5 INCHES INDICATING PRE-EXISTING CONDITION. CRACK EXTENDS AXIALLY AFT FOR 2 INCHES, THEN EXTENDS RADIALLY FWD OF BOSS FOR APPROX 5 INCHES TO 6 INCHES SPIRALLING AROUND TUBE. INS P OF INTERIOR OF TORQUE TUBE SHOWED NUMEROUS SPOTS OF CORROSION WITH A CONCENTRATION OF RUST AT THREADS BOSS. (X) 1 L 7 2 3O 3A10 2001030200056 20010302 00056 SW 2001 3 2 20001207SH017 1 20001120 G 3230 ES12404 DRAG BRACE GULSTM 690TP 690B 7630516 SW MLG CRACKED B MV5R K NONE O OTHER IN INSP/MAINT 1 GL 11 9LV 6088 11550 UPPER PORTION OF DRAG BRACE CRACKED. CRACK EXTENDED APPROXIMATELY .50 INCH. (X) 1 H 7 2 3T 2A4 2001030100044 20010301 00044 SW 2001 3 1 20001208SH010 1 20001208 G 5330 SKIN MOONEY M20 M20J 5870219 SW FUSELAGE CRACKED B EBVR K NONE O OTHER IN INSP/MAINT 1 GL 09 58135 698 241567 DURING INSPECTION, A CRACK WAS FOUND AT THE LEFT LOWER FUSELAGE SKIN AT BS -5.375 WHERE THE FUSELAGE SKIN ENDS AT THE FI REWALL AREA. THE CRACK EMANATED FROM THE EDGE OF THE SKIN, EXTENDED THROUGH A RIVET HOLE AND BACK OUT, ANGLING BACK TOW ARDS THE SKIN EDGE AGAIN. THE CRACK WAS APPROXIMATELY 1.5 INCHES LONG WHEN DISCOVERED. A PROPER SKIN REPAIR WAS ACCOMP LISHED. RECOMMEND A CLOSE LOOK IN THIS AREA DURING SCHEDULED INSPECTIONS. NO DEFINITE CAUSE WAS FOUND TO HAVE CAUSED THIS PARTICULAR DEFECT. (X) 1 L 7 1 3O 2A3 2001030100051 20010301 00051 NE 2001 3 1 20001212SH010 2 20001113 G 7250 2A0851 SEAL IAE V2500 V2500A1 NE NR 4 BEARING CRACKED B KB1R K NONE O OTHER IN INSP/MAINT 1 NE 03 PART RECEIVED FOR FPI IAW IAE V2500 PROPULSION SYSTEM ENGINE MANUAL, REV 45, SECTION 70-23-01, INSPECTION CHECK-01, TASK 70-23-01-230-501. PART REJECTED AT FPI DUE TO CRACKS IN TWO AREAS ON OUTSIDE DIAMETER OF PART. (X) 4 F E311NE 2001030100052 20010301 00052 NE 2001 3 1 20001212SH011 2 20001109 G 7250 2A0851 SEAL IAE V2500 V2500A1 NE NR 4 BEARING CRACKED B KB1R K NONE O OTHER IN INSP/MAINT 1 NE 03 PART RECEIVED FOR FPI IAW IAE V2500 PROPULSION SYSTEM ENGINE MANUAL, REV 45, SECTION 70-23-01, INSPECTION CHECK-01, TASK 70-23-01-230-501. PART REJECTED AT FPI FOR CRACKS IN TWO AREAS ON OUTSIDE OF PART. (X) 4 F E311NE 2001030100049 20010301 00049 CE 2001 3 1 20001214SH001 1 20001212 G 2400 HARNESS BEECH 200 B200 1152922 CE PWA PT6 PT6A42 52043 NE FUSELAGE BURNED C K NONE O OTHER IN INSP/MAINT 1 NM 11 773TP 183 BB1722 WIRE BUNDLE SPIRAL WRAP MELTED AND CHAFING AGAINST THE BRAKE DE-ICE HEAT LINE WHERE IT MAKES THE TURN TO COME INTO THE F ORWARD INBOARD PART OF WHEELWELL AT WS 85, ACCESS PANEL NR 13 AS SEEN ON CHAP 12-20-00 PAGE 249, FIG. 205 OF MM. (X) 1 L 7 2 4T 4 T A24CE E4EA 2000121800237 20001218 00237 CE 2000 12 18 20001214SH006 1 20001030 G 5531 16962000161 SPAR CAP BEECH BEECH 23 C23 1151242 CE INTERNAL CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 21 6717K 7191 M2266 DURING ANNUAL INSPECTION, ''CREAKING'' WAS HEARD WHEN FORCE WAS APPLIED TO STABILATOR TIP TO CHECK FOR BEARING PLAY. SO URCE OF SOUND WAS FOUND TO BE WORKING RIVETS AND CRACKED SPAR CAP INSIDE CENTER SPAR BOX ASSY IN THE LOOSE RIVETS OR CRA CK COULD BE SEEN BY EXTERIOR INSPECTION OF THE STABILATOR ONLY. THE BALANCE WEIGHT TUBE HAD TO BE REMOVED TO INSPECT TH E INTERIOR OF THE SPAR BOX. WHEN CHECKED AGAIN THE NEXT MORNING, AFTER COOLING OFF ALL NIGHT, THE CREAKING COULD NOT BE DUPLICATED. SUBMITTER RECOMMENDED PERIODIC INSPECTION OF THE SPAR BOX INTERIOR BY REMOVAL OF THE BALANCE WEIGHT TUBE A NNUALLY AND AT SOME INTERVAL. (X) 1 L 7 1 3O A1CE 2000121800240 20001218 00240 EA 2000 12 18 20001214SH010 2 20001122 G 8530 EC75362EC101 CYLINDER PIPER PA23 PA23250 7102308 SO LYC O540 IO540C4B5 41532 EA NR 5 BURNED D K NONE O OTHER IN INSP/MAINT 1 CE 01 900TS 975 277405429 L634048 AIRCRAFT ON 135 FLIGHT, PILOT NOTICED BLUE FLAME IN COWLING, RIGHT ENGINE. LANDED AT COLUMBIA, MO ON A SCHEDULED STOP. FOUND NR 5 CYLINDER HAD EXHAUST HOLE BURNED THROUGH CYLINDER FORWARD SIDE, .25 INCH BY 1 INCH. HOLE STARTED ON INSIDE EXHAUST PART BY EXHAUST SEAT AND WORKED OR BURNED FORWARD FRONT OF ENGINE. CRACKS WERE NOTED FROM BOTH SPARKPLUG HOLES TO BURNED HOLE. THE CYLINDERS WERE NEW, ECI INSTALLED 2-18-99 AND HAD 974.6 HOURS ON CYLINDER, OCCURRED 11-20-00. (X) 1 L 7 2 3O 3 O 1A10 1E4 2000121800242 20001218 00242 CE 2000 12 18 20001214SH016 1 20001129 G 3233 99810057652 ACTUATOR BEECH 100 100BEECH 1152916 CE FAILED H O OTHER O OTHER LD LANDING 1 SO 23 153JW 2744 B53 LEFT LANDING GEAR FAILED TO EXTEND FOR LANDING. PILOT UNSUCCESSFULLY ATTEMPTED TO LOWER LANDING GEAR (WHILE IN CONTACT WITH MAINTENANCE) SEVERAL TIMES. PILOT LANDED AIRCRAFT WITH GEAR RETRACTED. AIRCRAFT SUSTAINED DAMAGE TO THE LOWER FUS ELAGE, LOWER RIGHT NACELLE AND PROPELLERS. INITIAL INSPECTION REVEALED LEFT TORQUE SHAFT SHEARED INBOARD OF LANDING GEA R ACTUATOR ATTACH POINT DUE TO LEFT LANDING GEAR ACTUATOR INTERNAL FAILURE. NO DISASSEMBLY OF ACTUATOR PERFORMED. CAUS E OF FAILURE UNDETERMINED. (X) 1 L 7 2 3T A14CE 2000121800243 20001218 00243 CE 2000 12 18 20001214SH017 1 20001122 G 3250 05430221 BUNGEE CYLINDER CESSNA 172 172R 2072401 CE NOSE GEAR WEAK B O OTHER O OTHER TX TAXI/GRND HDL 1 CE 07 24468 440 17280863 PILOT EXPERIENCED POOR STEERING, RAN OFF RUNWAY IN CROSSWIND CONDITION. FOUND LEFT AND RIGHT STEERING BUNGEES WEAK. PU LLED TESTED BOTH ORIGINAL BUNGEES, ACTUATOR STARTED ABOUT 20 - 25 POUNDS PULL. NEW BUNGEES PULL TESTED 60 - 65 POUNDS P ULL. (X) 1 H 7 1 3O NT 3A12 2000121800244 20001218 00244 CE 2000 12 18 20001214SH018 1 20001204 G 3250 05430222 BUNGEE CYLINDER CESSNA 172 172R 2072401 CE NOSE GEAR WEAK B O OTHER O OTHER TX TAXI/GRND HDL 1 CE 07 24468 440 17280873 PILOT EXPERIENCED POOR STEERING, RAN OFF RUNWAY IN CROSSWIND CONDITION. FOUND LEFT AND RIGHT STEERING BUNGEES WEAK. PU LLED TESTED BOTH ORIGINAL BUNGEES, ACTUATOR STARTED ABOUT 20 - 25 POUNDS PULL. NEW BUNGEES PULL TESTED 60 - 65 POUNDS P ULL. (X) 1 H 7 1 3O NT 3A12 2000121800245 20001218 00245 CE 2000 12 18 20001214SH019 1 20001121 G 7500 C1B0021 HOSE BEECH 200 200BEECH 1152920 CE INSIDE ENG NAC WORN H AKGR K NONE O OTHER IN INSP/MAINT 1 WP 07 280SC 139 BB664 HOSES ARE WEARING ON COWLING LATCHES. THIS CAUSES DAMAGE TO HOSES AND TO THE LATCHES. HOSES ARE TOO LARGE, OR INSTALLE D AT THIS WRONG ANGLE. HOSES WERE INSTALLED UNDER STC SA 8986SW. (X) 1 L 7 2 4T A24CE 2000121800246 20001218 00246 CE 2000 12 18 20001214SH020 1 20001121 G 7500 C1B0022 HOSE BEECH 200 200BEECH 1152920 CE INSIDE ENG NAC WORN H AKGR K NONE O OTHER IN INSP/MAINT 1 WP 07 280SC 139 BB664 HOSES ARE WEARING ON COWLING LATCHES. THIS CAUSES DAMAGE TO HOSES AND TO THE LATCHES. HOSES ARE TOO LARGE, OR INSTALLE D AT THIS WRONG ANGLE. HOSES WERE INSTALLED UNDER STC SA 8986SW. (X) 1 L 7 2 4T A24CE 2000121800247 20001218 00247 CE 2000 12 18 20001214SH021 1 20001201 G 5600 10138402521 WINDSHIELD BEECH 200 200BEECH 1152920 CE PILOT CRACKED B JEMR K NONE O OTHER IN INSP/MAINT 1 CE 01 300HB BB566 WINDSCREEN SPIDER WEB CRACKED IN-FLIGHT. (X) 1 L 7 2 4T A24CE 2000121800248 20001218 00248 SO 2000 12 18 20001214SH022 2 20001101 G 8530 EXHAUST VALVE BEECH 36 B36TC 1151609 CE CONT O520 TSIO520UB 17040 SO NR 1 CYLINDER GROOVED D K NONE O OTHER IN INSP/MAINT 1 NM 05 36TU 264 EA273 248926R DUE TO LOW COMPRESSION READING, CYLINDER WAS BORESECOPED. EXTREME OVERHEATING OF EXHAUST VALVE WAS NOTED. WEAR GROOVE WAS CUT INTO VALVE FACE BY SEAT. REMOVED CYLINDER. UPON INSPECTION, UNUSUAL WEAR WAS DUE TO MISALIGNMENT OF VALVE GUID E OR VALVE SEAT. CYLINDER SENT FOR INSP. LOWER END OF GUIDE WAS BELL MOUNTED. VALVE SEAT CHECKED WITH MASTER SEAT GAU GE AND FOUND TO SHOW HEAVIER CONTACT ON OTBD SIDE, LESS ON INBD SIDE. CAUSE NOT OFFICIALLY DETERMINED. SUBMITTER BELIE VED CAUSE ORIGINATED DURING MFG. PART CAME FROM FACTORY MISALIGNED. (X) 1 L 7 1 3O 3 O 3A15 E8CE 2000121800249 20001218 00249 CE 2000 12 18 20001214SH025 1 20001120 G 5510 C12326242 BRACKET CESSNA 210 T210N 2073456 CE HORIZ STABILIZER CRACKED D K NONE O OTHER IN INSP/MAINT 1 NM 09 6509N 21063113 DURING ANNUAL INSPECTION, MECHANIC FOUND REINFORCEMENT BRACKET LOCATED CENTER AFT ON HORIZONTAL STABILIZER WAS CRACKED. POSSIBLE CAUSE, MOVING AIRCRAFT VIA HORIZONTAL STABILIZER AND NOT WITH TOW POINTS. INSTALLED NEW AND IMPROVED BRACKETS PER SEB00-10. (X) 1 H 7 1 3O 3A21 2000121800250 20001218 00250 SW 2000 12 18 20001214SH027 1 20001005 G 3220 540015001 LINK MOONEY M20 M20L 5870221 SW NOSE GEAR CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 99 78MP 816 260010 DURING ANNUAL INSP, NOTICED PAINT ON OUTSIDE OF THE SHOCK LINK SHOWED SIGNS OF METAL UNDERNEATH CRACKING. PAINT REMOVED , PART VISUALLY AND DYE PENETRANT INSPECTED. NO CRACKS FOUND. NOTICED SHOCK DISCS COMPRESSED OUT OF LIMITS. UPON REMOV AL, NOTICED SHOCK LINK CRACKED ON INSIDE. IN JUNE, 2000 A MOONEY M20K HAD AN ACCIDENT UPON LANDING. N/G COLLAPSED ON T OUCHDOWN RESULTING IN PROP STRIKE, LOSS OF DIRECTIONAL CONTROL OF ACFT. UPON INVEST, FOUND SHOCK LINK ON N/G HAD CRACK ED, SLOWLY WOBBLED OUT THE INSIDE OF SHAFT. M20K AND M20L HAVE SAME PART NUMBER FOR SHOCK LINK. PART IS INSTALLED IN N /G, USED TO COMPRESS, HOLD RUBBER SHOCK DISCS. IF PART BREAKS, UPON LANDING, PUSHES ITSELF INTO N/G WELL. (X) 1 L 7 1 3O RT 2A3 2000121800251 20001218 00251 CE 2000 12 18 20001214SH028 1 20001125 G 2820 RG34720A PUMP BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA ENG ACCY CASE LEAKING E O OTHER K FLUID LOSS CR CRUISE 1 GL 15 847BA 2019 BB847 PCE85099 DURING FLIGHT, THE FUEL FLOW DROPPED OFF UNTIL THE ENGINE TORQUE DROPPED ENOUGH TO FEATHER THE PROPELLER. THE CREW THEN SHUT THE ENGINE OFF WITH THE FUEL CONDITION LEVER. MAINTENANCE FOUND THE 4 SCREWS (THAT WERE SAFTIED) HOLDING THE PRES SURE RELIEF ADJUSTMENT PLATE ONTO THE LOW PRESSURE FUEL PUMP LOOSE, AND FUEL LEAKING, SUSPECT AIR WAS BEING INTRODUCED I NTO THE FUEL SYSTEM HERE AND CAVITATED THE HIGH PRESSURE PUMP CAUSING LOSS OF FUEL TO FCU. (X) 1 L 7 2 4T 4 T A24CE E4EA 2001021500037 20010215 00037 EU 2001 2 15 20001214SH029 1 20001130 G 8012 B666B VALVE SNIAS 350 AS350B2 8680813 EU START DRAIN LEAKING E KBMA K NONE K FLUID LOSS IN INSP/MAINT 1 WP 09 53SH 2009 START DRAIN VALVE LEAKING INTERNALLY. (X) 1 G 7 1 3U H9EU 2001021500038 20010215 00038 EU 2001 2 15 20001214SH030 1 20001201 G 3110 704A47270101 INDICATOR SNIAS 350 AS350BA 8680817 EU TEMPERATURE INOPERATIVE E KBMA K NONE O OTHER IN INSP/MAINT 1 WP 19 270SH 1864 TEMPERATURE GAUGE INOPERATIVE. (X) 1 G 7 1 3U NC H9EU 2001021500039 20010215 00039 NE 2001 2 15 20001214SH031 2 20001130 G 7321 BB56B FUEL CONTROL SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1 60030 NE ENGINE LEAKING E KBMA K NONE K FLUID LOSS IN INSP/MAINT 1 WP 19 2273A 2273 DECELERATION UNIT ON FCU LEAKING. (X) 1 G 7 1 3U 3 U NC H9EU E19EU 2001021500041 20010215 00041 EU 2001 2 15 20001214SH035 1 20000901 G 6240 614764021 INDICATOR SNIAS 350 AS350B2 8680813 EU TACHOMETER INOPERATIVE B R7MR O OTHER O OTHER NR NOT REPORTED 1 NM 07 101LN 406 3038 TACHOMETER UNIT INOPERATIVE. NTL NEEDLE VIBRATED EXCESSIVELY. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001021500042 20010215 00042 NE 2001 2 15 20001214SH037 2 20000406 G 7250 410106701 SEAL BOLKMS 117 BK117A3 5626015 EU LYC LTS101 LTS101650B1 41560 NE TURBINE SHROUD WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 117MA 449 7107 LE45266EA FIRST TURBINE SHROUD SEAL RING WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U 3 U H13EU E5NE 2001021500043 20010215 00043 NE 2001 2 15 20001214SH038 2 20000912 G 7250 414129011 TURBINE WHEEL BOLKMS 117 BK117B1 5626012 EU LYC LTS101 LTS101750B1 41560 NE POWER TURBINE WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 10UM 2308 1319 7231 LE45610EFA ROTOR ASSY, INSERTABLE BLADED, POWER TURBINE RETENTION PLUG WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, COR RECTED PROBLEM. (X) 1 G 7 2 3U 3 U H13EU E5NE10 2001021500044 20010215 00044 EU 2001 2 15 20001214SH039 1 20001002 G 2913 704A34310006 PUMP SNIAS 350 AS350B3 8680954 EU HYDRAULIC SYS WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 103LN 721 3128 HYDRAULIC PUMP HAD EXCESSIVE SPLINE WEAR. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001021500045 20010215 00045 EU 2001 2 15 20001214SH040 1 20001106 G 2841 9550171990 SWITCH SNIAS 350 AS350B3 8680954 EU TMECA ARRIEL ARRIEL2B NE LOW FUEL INOPERATIVE B R7MR O OTHER O OTHER NR NOT REPORTED 1 NM 07 103LN 3128 22032 LOW FUEL SWITCH UNIT INOPERATIVE. MASTER CAUTION LIGHT GOES OUT PERMANENTLY BEFORE ENGINE START. REPLACED WITH NEW UNI T, CORRECTED PROBLEM. (X) 1 G 7 1 3U 3 U H9EU E00054EN 2001021500046 20010215 00046 EU 2001 2 15 20001214SH041 1 20001122 G 2822 9A2045 CARTRIDGE UROCOP EC135 EC135P1 8680990 EU FUEL PUMP INOPERATIVE B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 135N 3 EC1350086 FUEL PUMP CARTRIDGE UNIT INOPERATIVE. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U O H88EU 2001021500047 20010215 00047 EU 2001 2 15 20001214SH042 1 20001122 G 2822 9A2045 CARTRIDGE UROCOP EC135 EC135P1 8680990 EU FUEL PUMP INOPERATIVE A R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 135N 3 EC1350086 FUEL PUMP CARTRIDGE UNIT INOPERATIVE. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U O H88EU 2001021500048 20010215 00048 EU 2001 2 15 20001214SH043 1 20000922 G 6410 704A33633116 BEARING SNIAS 350 AS350B3 8680954 EU TAIL ROTOR DELAMINATED B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 104LN 705 3134 ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT FROM ONE EACH KIT, P/N 355A09-1036-01, CORRECTED PR OBLEM. 4 HALF SHELLS EQUALS 1 KIT. (X) 1 G 7 1 3U H9EU 2001021500049 20010215 00049 EU 2001 2 15 20001214SH044 1 20001008 G 3340 356H2802 POWER SUPPLY SNIAS 350 AS350B3 8680954 EU EXTERIOR LIGHTS INOPERATIVE B R7MR K NONE L NO TEST IN INSP/MAINT 1 NM 07 104LN 1053 3134 POWER SUPPLY BOX UNIT INOPERATIVE. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001021500050 20010215 00050 2001 2 15 20001214SH045 4 20000805 G 3454 071010520000 TRANSMITTER SNIAS 350 AS350B3 8680954 EU VOR SYSTEM INOPERATIVE B R7MR O OTHER O OTHER NR NOT REPORTED 1 NM 07 104LN 534 3134 MAGNETIC AZIMUTH TRANSMITTER UNIT INOPERATIVE. 5 TO 60 DEGREE DEVIATION WHILE ON SAME HEADING IN SLAVE MODE. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001021500051 20010215 00051 NE 2001 2 15 20001214SH046 2 20000706 G 7260 230093304 BEARING BOLKMS 117 BK117A3 5626015 EU LYC LTS101 LTS101650B1 41560 NE ENGINE WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 127HH 901 7060 LE45083EA ANNULAR BALL BEARING WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U 3 U H13EU E5NE 2001021500052 20010215 00052 NE 2001 2 15 20001214SH047 2 20000706 G 7250 430150601 SEAL BOLKMS 117 BK117A3 5626015 EU LYC LTS101 LTS101650B1 41560 NE NR 2 BEARING LEAKING B R7MR K NONE K FLUID LOSS IN INSP/MAINT 1 NM 07 127HH 901 7060 LE45083EA NR 2 BEARING SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U 3 U H13EU E5NE 2001021500053 20010215 00053 NE 2001 2 15 20001214SH048 2 20000706 G 7250 430144801 SEAL BOLKMS 117 BK117A3 5626015 EU LYC LTS101 LTS101650B1 41560 NE NR 3 BEARING LEAKING B R7MR K NONE K FLUID LOSS IN INSP/MAINT 1 NM 07 127HH 901 7060 LE45083EA NR 3 BEARING SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U 3 U H13EU E5NE 2001021500054 20010215 00054 EU 2001 2 15 20001214SH049 1 20000706 G 8011 GEAR HONEYWELL BOLKMS 117 BK117A3 5626015 EU LYC LTS101 LTS101650B1 41560 NE STARTER WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 127HH 901 A342 7060 LE45083EA STARTER, GEAR ASSY, EXCESSIVE SPLINE WEAR. REPLACED WTIH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U 3 U H13EU E5NE 2001021500055 20010215 00055 EU 2001 2 15 20001215SH001 1 20001008 G 2822 9A2045 CARTRIDGE UROCOP EC135 EC135P1 8680990 EU FUEL PUMP INOPERATIVE B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 135SJ 127 EC1350054 FUEL PUMP CARTRIDGE UNIT INOPERATIVE. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U O H88EU 2001021500056 20010215 00056 NE 2001 2 15 20001215SH002 2 20000326 G 7310 L717M1009801 TUBE UROCOP EC135 EC135P1 8680990 EU PWA PW206 PW206B 0 NE FUEL CONTROL WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 135SJ 1444 EC1350054 TUBE ASSY WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U 3 U O H88EU E42NE 2001021500057 20010215 00057 EU 2001 2 15 20001215SH003 1 20001106 G 3340 02471131 LIGHT BOLKMS BK117 BK117C1 5626025 EU SEARCHLIGHT INOPERATIVE B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 117SU 921 7527 SERACHLIGHT UNIT INOPERATIVE. PIN B-D ONLY 20 VAC, SHOULD BE 48 VAC. (X) 1 G 7 2 3U NC H13EU 2001021500058 20010215 00058 EU 2001 2 15 20001215SH004 1 20001031 G 3030 PR6123 ELEMENT BOLKMS BK117 BK117C1 5626025 EU PITOT HEAT INOPERATIVE B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 117SU 622 7527 PITOT TUBE HAD INOPERATIVE HEATING ELEMENT. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U NC H13EU 2001021500059 20010215 00059 EU 2001 2 15 20001215SH005 1 20001025 G 2913 40165 PUMP BOLKMS BK117 BK117C1 5626025 EU HYDRAULIC SYSTEM DAMAGED B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 117SU 902 7527 DRIVESHAFT WAS TORQUED TOO TIGHTLY IN PLACE AT THE FACTORY. WHILE MECHANIC WAS REMOVING THE PUMP FOR INSPECTION, THE SH AFT PULLED LOOSE. REPLACED WITH USED UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U NC H13EU 2001021500060 20010215 00060 EU 2001 2 15 20001215SH006 1 20000627 G 6710 10513141 ROD END BOLKMS BK117 BK117C1 5626025 EU MAIN ROTOR WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 117SU 617 7527 ROD END ASSY WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U NC H13EU 2001021500061 20010215 00061 EU 2001 2 15 20001215SH007 1 20000627 G 6710 10513142 ROD END BOLKMS BK117 BK117C1 5626025 EU MAIN ROTOR WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 117SU 617 7527 ROD END ASSY WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U NC H13EU 2001021500062 20010215 00062 EU 2001 2 15 20001215SH008 1 20000822 G 6320 4639302037 SEAL BOLKMS BK117 BK117C1 5626025 EU M/R TRANSMISSION LEAKING B R7MR K NONE K FLUID LOSS IN INSP/MAINT 1 NM 07 117SU 751 7527 SEALING RING LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U NC H13EU 2001021500063 20010215 00063 NE 2001 2 15 20001215SH009 2 20000326 G 7250 430144801 SEAL BOLKMS 117 BK117B1 5626012 EU LYC LTS101 LTS101750B1 41560 NE NR 3 BEARING LEAKING B R7MR K NONE K FLUID LOSS IN INSP/MAINT 1 NM 07 7060G 490 7173 LE45756EFA NR 3 BEARING SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U 3 U H13EU E5NE10 2001021500064 20010215 00064 NE 2001 2 15 20001215SH010 2 20000826 G 7250 430150602 SEAL BOLKMS 117 BK117B1 5626012 EU LYC LTS101 LTS101750B1 41560 NE NR 2 BEARING LEAKING B R7MR K NONE K FLUID LOSS IN INSP/MAINT 1 NM 07 7060G 490 7173 NR 2 BEARING SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U 3 U H13EU E5NE10 2001021500065 20010215 00065 NE 2001 2 15 20001215SH011 2 20000826 G 7230 430404701 SEAL BOLKMS 117 BK117B1 5626012 EU LYC LTS101 LTS101750B1 41560 NE NR 1 BEARING LEAKING B R7MR K NONE K FLUID LOSS IN INSP/MAINT 1 NM 07 7060G 490 7173 LE45756EFA NR 1 BEARING SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U 3 U H13EU E5NE10 2001021500066 20010215 00066 EU 2001 2 15 20001215SH012 1 20001101 G 2435 524031 STARTER GEN SNIAS 350 AS350B3 8680954 EU ENGINE INOPERATIVE B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 397LG 3268 STARTER/GENERATOR UNIT INOPERATIVE. BRUSH SPRING BROKE RESULTING IN FAN DAMAGE. REPLACED WITH NEW UNIT, CORRECTED PROB LEM. (X) 1 G 7 1 3U H9EU 2001021500067 20010215 00067 NE 2001 2 15 20001215SH013 2 20001101 G 7261 350A54113800 VENT LINE SNIAS 350 AS350B3 8680954 EU TMECA ARRIEL ARRIEL1B 6OO30 NE OIL SYSTEM CRACKED B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 397LG 102 3268 TUBE, AIR VENT - OIL, CRACKED BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U 3 U H9EU E19EU 2001021500068 20010215 00068 EU 2001 2 15 20001215SH014 1 20001030 G 6321 350A32501000 SUPPORT BRACKET SNIAS 350 AS350B3 8680954 EU ROTOR BRAKE WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 397LG 102 3268 BRAKE LINING SUPPORT WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001021500069 20010215 00069 NE 2001 2 15 20001215SH015 2 20001101 G 7310 350A54113720 COUPLING SNIAS 350 AS350B3 8680954 EU TMECA ARRIEL ARRIEL1B 6OO30 NE P2 LINE WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 397LG 102 3268 P2 UNION WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U 3 U H9EU E19EU 2001021500070 20010215 00070 NE 2001 2 15 20001215SH016 2 20001101 G 7310 9996660 LINE SNIAS 350 AS350B3 8680954 EU TMECA ARRIEL ARRIEL1B 6OO30 NE P2 WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 397LG 102 3268 P2 HOSE WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U 3 U H9EU E19EU 2001021500071 20010215 00071 EU 2001 2 15 20001215SH017 1 20001107 G 2432 RG355 BATTERY SNIAS 350 AS350D 8680803 EU BATTERY BOX DISCHARGED B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 350RM 356 1024 LEAD ACID BATTERY WILL NOT HOLD CHARGE. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001021500072 20010215 00072 EU 2001 2 15 20001215SH018 1 20000810 G 6420 35A33214501 CONTROL ROD SNIAS 350 AS350B3 8680954 EU TAIL ROTOR WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 52285 283 3251 PITCH CONTROL ROD WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001021500073 20010215 00073 EU 2001 2 15 20001215SH019 1 20000731 G 3340 025453 RESISTOR SNIAS 350 AS350B3 8680954 EU LIGHT BALLAST BROKEN B R7MR K NONE L NO TEST IN INSP/MAINT 1 NM 07 52285 3251 BALLAST RESISTOR ASSEMBLY BROKEN AND WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001021500074 20010215 00074 EU 2001 2 15 20001215SH020 1 20000613 G 7933 RP26800 PROBE SNIAS 350 AS350B3 8680954 EU TMECA ARRIEL ARRIEL1B 6OO30 NE OIL TEMPERATURE INOPERATIVE B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 52285 170 3251 TEMPERATURE PROBE UNIT INOPERATIVE. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U 3 U H9EU E19EU 2001021500075 20010215 00075 EU 2001 2 15 20001215SH021 1 20001031 G 2432 350A62250120 BATTERY SNIAS 350 AS350B3 8680954 EU BATTERY BAY CRACKED B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 52285 427 3251 BATTERY FIXING 350B3, CRACKED BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001021500076 20010215 00076 EU 2001 2 15 20001215SH022 1 20001103 G 6720 704A34240015 ACCUMULATOR SNIAS 350 AS350B3 8680954 EU T/R CONTROL LEAKING B R7MR K NONE K FLUID LOSS IN INSP/MAINT 1 NM 07 52285 3251 ACCUMULATOR LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001021500077 20010215 00077 EU 2001 2 15 20001215SH023 1 20001020 G 6410 704A33633116 BEARING SNIAS 350 AS350B 8680801 EU TAIL ROTOR DELAMINATED B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 58045 1602 ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT FROM 1 EACH KIT P/N 355A09-1036-01, CORRECTED PROBL EM. 4 HALF SHELLS EQUALS 1 KIT. (X) 1 G 7 1 3U H9EU 2001021500078 20010215 00078 EU 2001 2 15 20001215SH024 1 20001025 G 6410 704A33633171 HINGE SNIAS 350 AS350B 8680801 EU TAIL ROTOR WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 58045 437 1602 ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT FROM 1 EACH KIT P/N 355A33-2153-00, CORRECTED PROBL EM. TWO TEETERING BEARINGS EQUALS 1 KIT. (X) 1 G 7 1 3U H9EU 2001021500079 20010215 00079 EU 2001 2 15 20001215SH025 1 20001012 G 6410 704A33633116 BEARING SNIAS 350 AS350B3 8680954 EU TAIL ROTOR WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 52281 432 3249 ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT FROM 1 EACH KIT P/N 355A09-1036-01, CORRECTED PROBL EM. FOUR HALF SHELLS EQUALS 1 KIT. (X) 1 G 7 1 3U H9EU 2001021500080 20010215 00080 EU 2001 2 15 20001215SH026 1 20001008 G 3340 025453 RESISTOR SNIAS 350 AS350B3 8680954 EU LIGHT BALLAST BROKEN B R7MR K NONE L NO TEST IN INSP/MAINT 1 NM 07 52281 430 3249 BALLAST RESISTOR ASSEMBLY BROKEN AND WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001021500081 20010215 00081 2001 2 15 20001215SH027 4 20001009 G 3454 071010520000 TRANSMITTER SNIAS 350 AS350B 8680801 EU VOR SYSTEM INOPERATIVE B R7MR K NONE L NO TEST IN INSP/MAINT 1 NM 07 5771C 845 1369 MAGNETIC AZIMUTH TRANSMITTER UNIT INOPERATIVE. 10 TO 15 DEGREE DEVIATION FROM EAST TO WEST. REPLACED WITH NEW UNIT, CO RRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001021500082 20010215 00082 2001 2 15 20001215SH028 4 20001110 G 2211 7004206901 COMPUTER BOLKMS 117 BK117B1 5626012 EU CSAS INOPERATIVE B R7MR K NONE L NO TEST IN INSP/MAINT 1 NM 07 62LF 42 7163 CSAS-COMPUTER PITCH INOPERATIVE. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U H13EU 2001021500083 20010215 00083 NM 2001 2 15 20001215SH029 1 20001107 G 6710 900C3010002105 FRICTION RING DOUG MD900 MD900 3027375 NM COLLECTIVE ROUGH B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 901CF 129 90000012 COLLECTIVE FRICTION UNIT ROUGH AND RATCHETY. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U NC H19NM 2001021500084 20010215 00084 NM 2001 2 15 20001215SH030 1 20001013 G 6220 900R3101001107 BEARING DOUG MD900 MD900 3027375 NM MAIN ROTOR DELAMINATED B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 901CF 29 90000012 MAIN ROTOR ENTERING BEARING ASSY, DELAMINATION. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U NC H19NM 2001021500085 20010215 00085 NM 2001 2 15 20001215SH031 1 20001117 G 6220 900R3101001107 BEARING DOUG MD900 MD900 3027375 NM MAIN ROTOR DELAMINATED B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 901CF 684 90000012 MAIN ROTOR CENTERING BEARIN ASSY , DELAMINATION. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U NC H19NM 2001021500086 20010215 00086 NE 2001 2 15 20001215SH032 2 20001028 G 7261 900P3650108103 BREATHER TUBE DOUG MD900 MD900 3027375 NM PWA PW206 PW206A NE ENGINE OIL DAMAGED B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 901CF 4225 90000012 PCE206042 HOSE, ENGINE OIL BREATHER, INSIDE OF HOSE IS BUBBLED. REPLACED WITH NEW UNIT, CORRECTED UNIT. (X) 1 G 7 2 3U 3 U NC H19NM E42NE 2001021500087 20010215 00087 2001 2 15 20001215SH033 4 20001027 G 3160 900A3720002111 DISPLAY DOUG MD900 MD900 3027375 NM COCKPIT MALFUNCTIONED B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 901CF 259 90000012 INTEGRATED INSTRUMENT DISPLAY SYSTEM ASSEMBLY, MRB BALANCE DISPLAY ONLY SHOWS PARTIAL CHARACTERS. INCORRECT CALCULATION S. (X) 1 G 7 2 3U NC H19NM 2001021500088 20010215 00088 EU 2001 2 15 20001215SH034 1 20000919 G 6410 704A33633171 HINGE SNIAS 350 AS350B2 8680813 EU TAIL ROTOR WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 96LG 474 2817 ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT FROM 1 EACH KIT P/N 355A33-2153-00, CORRECTED PROBL EM. TWO TEETERING BEARINGS EQUALS 1 KIT. (X) 1 G 7 1 3U H9EU 2001021500089 20010215 00089 EU 2001 2 15 20001215SH035 1 20000919 G 6410 704A33633116 BEARING SNIAS 350 AS350B2 8680813 EU TAIL ROTOR WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 96LG 474 2817 ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT FROM 1 EACH KIT P/N 355A09-1036-01, CORRECTED PROBL EM. FOUR HALF SHELLS EQUALS 1 KIT. (X) 1 G 7 1 3U H9EU 2001021500090 20010215 00090 EU 2001 2 15 20001215SH036 1 20000809 G 6720 350A33214501 ROD SNIAS 350 AS350B2 8680813 EU PITCH CONTROL WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 92LG 284 2575 PITCH CONTROL ROD WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001021500091 20010215 00091 2001 2 15 20001215SH037 4 20000719 G 3454 071010520000 TRANSMITTER SNIAS 350 AS350B2 8680813 EU VOR SYSTEM INOPERATIVE B R7MR K NONE L NO TEST IN INSP/MAINT 1 NM 07 92LG 380 2575 MAGNETIC AZIMUTH TRANSMITTER UNIT INOPERATIVE. 12 DEGREE NORTH HEADING DEVIATION. REPLACED WITH NEW UNIT, CORRECTED PR OBLEM. (X) 1 G 7 1 3U H9EU 2001021500092 20010215 00092 EU 2001 2 15 20001215SH038 1 20001108 G 6410 704A33633116 BEARING SNIAS 350 AS350B2 8680813 EU TAIL ROTOR WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 93LG 385 2654 ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT FROM 1 EACH KIT P/N 355A09-1036-01, CORRECTED PROBL EM. 4 HALF SHELLS EQUALS 1 KIT. (X) 1 G 7 1 3U H9EU 2001021500093 20010215 00093 EU 2001 2 15 20001215SH039 1 20000914 G 6720 350A33214501 ROD SNIAS 350 AS350B2 8680813 EU PITCH CONTROL WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 93LG 295 2654 PITCH CONTROL ROD WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 1 3U H9EU 2001021500094 20010215 00094 NE 2001 2 15 20001215SH040 1 20001013 G 3212 7625100702042 LINK SKRSKY S76 S76A 8143006 NE MLG FLOATS FAILED E ALGA K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 712AL 10392 760280 FLOATS WERE INADVERTENTLY INFLATED. LINK DID NOT SEPARATE AT SHEAR POINT. (X) 1 G 7 2 3U H1NE 2001021500095 20010215 00095 NE 2001 2 15 20001215SH041 1 20001030 G 6230 7635109030044 MAST SKRSKY SKRSKY S76 S76A 8143006 NE MAIN ROTOR CRACKED E ALGA K NONE K FLUID LOSS IN INSP/MAINT 1 NM 07 717AL 477 A08100240 760221 WHILE INVESTIGATING AN OIL LEAK AND SUBSEQUENT REMOVAL OF THE MAIN GEARBOX, THE MAST WAS FOUND CRACKED ALMOST HALFWAY AR OUND ITS CIRCUMFERENCE. THE CRACK IS LOCATED BELOW THE LOWER MAIN ROTOR HUB MOUNTING FLANGE. THE CRACK MEASURES ALMOST HALFWAY AROUND THE MAST. THE MAJORITY OF THE CRACK WAS HIDDEN BY THE SWASHPLATE GUIDE SHIELD RUBBER SEAL. MAIN GEARBO X SENT FOR EVALUATION. (X) 1 G 7 2 3U H1NE 2001021500096 20010215 00096 NE 2001 2 15 20001218SH001 1 20000721 G 6210 641520201049 BLADE SKRSKY S64 S64E 8142604 NE MAIN ROTOR CRACKED B JYDR K NONE O OTHER IN INSP/MAINT 1 NM 09 176AC 5881 64003 THE TOP SIDE OF THE TRAILING EDGE RETENTION BLOCK SCREW HOLE HAD A CRACK WHICH EXTENDED APPROXIMATELY .360 INCH AT A 7 O ''CLOCK POSITION (AS VIEWED FROM THE TOPSIDE LOOKING DOWN). THIS CRACK WAS DISCOVERED DURING A VISUAL INSPECTION PERFOR MED IN THE FIELD. (X) 2 G 7 2 4U H4EA 2001021500097 20010215 00097 NE 2001 2 15 20001218SH002 1 20000710 G 3213 646550152103 HOUSING SKRSKY S64 S64E 8142604 NE MLG CRACKED B JYDR K NONE O OTHER IN INSP/MAINT 1 NM 09 218AC 64033 MAIN LANDING GEAR PN 6425-50100-013, -014 WAS REMOVED FOR OVERHAUL. DURING THE FLUORESCENT MAGNETIC PARTICLE INSPECTIO N PROCESS, 15 LINEAR INDICATIONS, NOT VISIBLE TO THE NAKED EYE, WERE REVEALED ON THE UPPER COLLAR HOUSING WITH MEASUREME NTS OF .093 INCH TO .036 INCH IN LENGTH. THE INDICATIONS ARE LOCATED AT THE LIGHTENING HOLES WITH SOME BREAKING THE EDG E OF THE HOLE. A SECOND MLG WAS ALSO INSPECTED AND 7 LINEAR INDICATIONS NOT VISIBLE TO THE NAKED EYE WITH MEASUREMENTS OF .171 INCH TO .531 INCH IN LENGTH WERE FOUND ON THE LOWER COLLAR HOUSING. (X) 2 G 7 2 4U H4EA 2001021500098 20010215 00098 NE 2001 2 15 20001218SH003 1 20000710 G 3213 646550152101 HOUSING SKRSKY S64 S64E 8142604 NE MLG CRACKED B JYDR K NONE O OTHER IN INSP/MAINT 1 NM 09 218AC 64033 MAIN LANDING GEAR PN 6425-50100-013, -014 WAS REMOVED FOR OVERHAUL. DURING THE FLUORESCENT MAGNETIC PARTICLE INSPECTIO N PROCESS, 15 LINEAR INDICATIONS, NOT VISIBLE TO THE NAKED EYE, WERE REVEALED ON THE UPPER COLLAR HOUSING WITH MEASUREME NTS OF .093 INCH TO .036 INCH IN LENGTH. THE INDICATIONS ARE LOCATED AT THE LIGHTENING HOLES WITH SOME BREAKING THE EDG E OF THE HOLE. A SECOND MLG WAS ALSO INSPECTED AND 7 LINEAR INDICATIONS NOT VISIBLE TO THE NAKED EYE WITH MEASUREMENTS OF .171 INCH TO .531 INCH IN LENGTH WERE FOUND ON THE LOWER COLLAR HOUSING. (X) 2 G 7 2 4U H4EA 2001021500099 20010215 00099 WP 2001 2 15 20001218SH004 1 20000707 G 6220 369A10045 PIN HUGHES 369 369D 4470706 WP MAIN ROTOR HUB BROKEN B CHIR K NONE O OTHER IN INSP/MAINT 1 NM 09 502CH 5885 180252D VISUAL INSPECTION REVEALED BROKEN PIN. (X) 1 G 7 1 3U H3WE 2001021500100 20010215 00100 SW 2001 2 15 20001218SH005 1 20000613 G 2822 P49389 RELIEF VALVE AIRBORNE BELL 407 407 SW ALLSN 250C 250C47B GL FUEL BOOST PUMP FAILED B CHIR K NONE O OTHER IN INSP/MAINT 1 NM 09 407AR 197 2AR27 53363 CAE847397 DURING ANNUAL INSPECTION, HARDWARE WAS FOUND IN AIRFRAME ANTI-ICE FUEL FILTER. AFTER CONSULATION WITH BELL PRODUCT SUPP ORT, IT WAS THOUGH TO HAVE COME FROM THE FILTER BOWL. INSPECTION OF THE FILTER BOWL AND FILTER HEAD FOUND NO DISCREPANC IES. INSPECTED AFT FUEL BOOST PUMP ASSY, FOUND LEFT THERMAL RELIEF VALVE HAD COME APART SENDING A NUT AND ANOTHER PIECE INTO THE FILTER. FURTHER INSPECTION FOUND A SPRING IN THE FUEL LINE TO THE FILTER AND ANOTHER PIECE IN THE CANNISTER W ITH SOME ALUMINUM SHAVINGS. THE LEFT VALVE THREADS WERE ALSO PARTIALLY STRIPPED. THE BOOST PUMP ASSY WAS INSPECTED WIT H NO DISCREPANCIES FOUND. (X) 1 G 7 1 3U 3 U O H2SW E1GL 2001021500101 20010215 00101 NE 2001 2 15 20001218SH006 1 20000629 G 6420 6511207101041 ARM SKRSKY SKRSKY S64 S64E 8142604 NE TAIL ROTOR CRACKED B JYDR K NONE O OTHER IN INSP/MAINT 1 NM 09 164AC 1432 A9028 64034D ARM ASSEMBLY HAD CRACK INDICATION ON OUTBOARD MOUNTING LUG EXTENDING FROM .256 INCH/.252 INCH DIAMETER THROUGH HOLE TO . 34 INCH RADIUS. CIRCUMSTANCES UNDER WHICH CRACKING OCCURRED ARE UNKNOWN. POSSIBLE CAUSE IS FROM FRETTING MOVEMENT BETW EEN SLEEVE MOUNTING EARS, AND ARM ASSY MOUNTING LUGS. ALL THROUGH HOLES OF BOTH SLEEVE AND ARM ASSY MET BLUEPRINT REQUI REMENTS .256 INCH/.252 INCH DIAMETER. (X) 2 G 7 2 4U H4EA 2001011104198 20010111 04198 SO 2001 1 11 20001218SH007 2 20001030 G 8530 CLASS71 CYLINDER CONT O520 IO520* 17032 SO ENGINE DELAMINATED B AG2R A UNSCHED LANDING Y ENGINE STOPPAGE CL CLIMB 1 SW 17 1831 82 291457R CERMINIL COATING DELAMINATED FROM ONE STEEL CYL BORE AT 82.2 HRS TSO. POSSIBLE CAUSE, SOME INDIVIDUAL POSSIBLY TOUCHED CYL BORE JUST BEFORE PROCESSING. TOUCHING CYL BORE AFTER FINAL CLEANING AND/OR DURING PROCESSING IS STRICTLY PROHIBITED IN SPECS FOR PROCESS BECAUSE CONTAMINATION FROM PERSON'S HAND CAN CAUSE ADHERENCE PROBLEMS. THE AUTOMATED PRE-TREAT PR OCESS WAS POSSIBLY INTERRUPTED THROUGH SOME ELECTRIC OR COMPUTER ANOMALY AND REQUIRED PRE-TREATMENTS WERE NOT COMPLETED. PLATING PROCESS ACCOMPLISHED THROUGH COMPUTER, ROBOTIC MANIPULATION. COMPUTER REPORTS PROCESSING PROBLEMS, BUT THERE WERE NO REPORTS ASSOCIATED WITH THIS PARTICULAR CYLINDER. (X) 3 O E5CE 2001021400056 20010214 00056 CE 2001 2 14 20001218SH011 1 20001004 G 5510 12326241 BRACKET CESSNA 210 T210N 2073456 CE HORIZ STABILIZER CRACKED B VT3R K NONE O OTHER IN INSP/MAINT 1 WP 09 1766U 5541 21064741 DURING PRE-FLIGHT INSPECTION, PILOT NOTED LEFT STABILIZER BRACKET BROKEN. SUBMITTER RECOMMENDED CLOSE INSPECTION OF THI S AREA DURING PRE-FLIGHT, 100-HOUR, ANNUAL INSPECTIONS, AND TO C/W CESSNA SE 84-17. (X) 1 H 7 1 3O 3A21 2001021400057 20010214 00057 NE 2001 2 14 20001218SH012 1 20001204 G 2612 7630607902103 FIRE DETECTOR SKRSKY S76 S76B 8143007 NE NR 1 ENG MALFUNCTIONED D K NONE N FALSE WARNING CR CRUISE 1 EA 25 22CP 3132 760425 AN ERRONEOUS NR 1 ENGINE FIRE INDICATION (FIRE LIGHT) CAME ON IN-FLIGHT WITH NO OTHER SUPPORTING INDICATIONS OF A FIRE. REPLACED NR 1 FORWARD ENGINE FLAME DETECTOR WITH A NEW SERVICEABLE PART AS DETERMINED BY TROUBLESHOOTING OF FIRE DETECT ION SYSTEM. CHECKED OUT SYSTEM, OK. SUBSEQUENT FLIGHTS, SYSTEM NORMAL. (X) 1 G 7 2 4U H1NE 2001010200131 20010102 00131 SO 2001 1 2 20001218SH015 2 20001110 G 8530 654961A7BP CYLINDER BEECH 36 B36TC 1151609 CE CONT O520 TSIO520UB 17040 SO FAILED B K NONE O OTHER IN INSP/MAINT 1 WP 23 3181U 368 EA563 CYLINDER HAD LOW COMPRESSION. (X) 1 L 7 1 3O 3 O 3A15 E8CE 2001010200146 20010102 00146 CE 2001 1 2 20001218SH017 1 20001115 G 3230 08411103 LINK CESSNA 401 401A 207590D CE ADJUSTING SCREW WORN B AK6R K NONE O OTHER IN INSP/MAINT 1 SW 19 6296Q 6799 401A0096 UPON C/W AD 76-13-07, REPLACEMENT OF FORK BOLTS, PLAY WAS NOTICED AT ADJUSTING SCREW/DOWNLOCK SWITCH LOCK LINK. UPON FU RTHER INSPECTION, THREADS WERE SHOWN TO BE WORN AND PART WAS ALLOWED ABOUT 5 THOUSANDS OF AN INCH IN PLAY. THIS IS THE SECOND REPORT FILED ON THIS PART NUMBER AND SECOND RECOMMENDATION OF MANDATORY AD OF 2,500-HOUR REPLACEMENT. THIS IS TH E ONLY DOWNLOCK LOAD ON THE GEAR SIDE BRACE AND UPON FAILIURE, IS GUARANTEED GEAR FAILURE/COLLAPSE. (X) 1 L 7 2 3O A7CE 2001021400061 20010214 00061 CE 2001 2 14 20001218SH018 1 20001129 G 2434 649304 ALTERNATOR CESSNA 310 310R 2074245 CE ENGINE SHORTED D K NONE O OTHER IN INSP/MAINT 1 GL 21 6832Y 310R2121 FOUND WORN BRUSH IN ALTERNATOR CAUSING SPRING OF BRUSH TO COME OUT OF POSITION TO SHORT ALTERNATOR FIELD. (X) 1 L 7 2 3O 3A10 2001021500102 20010215 00102 NE 2001 2 15 20001218SH019 1 20001201 G 6510 7630807952105 BLOWER SKRSKY S76 S76B 8143007 NE OIL COOLER INTERMITTENT D K NONE O OTHER IN INSP/MAINT 1 EA 25 61CP 760427 DURING A HELICOPTER GROUND RUN, MECHANIC WAS MOVING AND SHAKING THE WIRE BUNDLE LEADING FROM THE HELICOPTER MAIN GEARBOX NR SENSOR ROUTED ALONG LEFT SIDE OF NR 1 ENG OIL COOLER BLOWER BASE, TRYING TO STIMULATE COCKPITS INTERMITTENT INDICATI ON. ENGINES OIL COOLER BLOWERS ARE ACTIVE WHEN MAIN ROTORS ARE TURNING. MECHANIC LOST THE TIPS OF TWO FINGERS OF LEFT HAND BY RUNNING HIS HAND PAST BASE OF ENG OIL COOLER BLOWER CONTACTING THE AIR INLET IMPELLER. 1 G 7 2 4U H1NE 2001021500103 20010215 00103 NM 2001 2 15 20001218SH020 1 20001127 G 5320 STIFFENER DOUG 600N 600N 3027377 NM FUSELAGE CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 17 609BP 903 RN038 DURING AN INSPECTION OF THE AIRCRAFT, A STIFFENER WAS FOUND CRACKED, P/N 369D23022-5. THE CRACK IS LOCATED ON THE INBOA RD SIDE WHERE THE TWO RIVETS THAT HOLD THE STIFFENER TO THE UPPER MAST DECK. (X) 1 G 7 1 3U NC H3WE 2001021500104 20010215 00104 NM 2001 2 15 20001218SH021 1 20001127 G 5320 STIFFENER DOUG 600N 600N 3027377 NM FUSELAGE CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 17 609BP 903 RN038 DURING AN INSPECTION, A STIFFENER WAS FOUND CRACKED, P/N 369D23022-6. THE CRACK IS LOCATED ON THE INBOARD SIDE WHERE TH E TWO RIVETS THAT HOLD THE STIFFENER TO THE UPPER MAST DECK. (X) 1 G 7 1 3U NC H3WE 2001021500105 20010215 00105 NM 2001 2 15 20001218SH022 1 20001127 G 5320 STIFFENER DOUG 600N 600N 3027377 NM FUSELAGE CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 17 610BP 1002 RN040 DURING AN INSPECTION, A STIFFENER WAS FOUND CRACKED, PN 369D23022-5. THE CRACK IS LOCATED ON THE INBOARD SIDE WHERE THE TWO RIVETS THAT HOLD THE STIFFENER TO THE UPPER MAST DECK. (X) 1 G 7 1 3U NC H3WE 2001021500106 20010215 00106 NM 2001 2 15 20001218SH023 1 20001127 G 5320 STIFFENER DOUG 600N 600N 3027377 NM FUSELAGE CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 17 610BP 1002 RN040 DURING AN INSPECTION, A STIFFENER WAS FOUND CRACKED, P/N 369D23022-6. THE CRACK IS LOCATED ON THE INBOARD SIDE WHERE TH E TWO RIVETS THAT HOLD THE STIFFENER TO THE UPPER MAST DECK. (X) 1 G 7 1 3U NC H3WE 2000122800396 20001228 00396 CE 2000 12 28 20001218SH026 1 20000830 G 3233 11581002917 NUT RAYTHN BEECH 200 200BEECH 1152920 CE LT LDG ACTUATOR SEPARATED H O OTHER O OTHER NR NOT REPORTED 1 SO 17 80WM 512G81 BB863 THREADED INSERT SEPARATED FROM LANDING GEAR ACTUATOR ROD CAUSING AN UNSAFE LANDING GEAR INDICATION IN COCKPIT. THE ACT UATOR NUT WAS INSTALLED NEW IN THE LANDING GEAR ACTUATOR. POSSIBLE CAUSE: MANUFACTURING DEFECT. (X) 1 L 7 2 4T A24CE 2000122800397 20001228 00397 CE 2000 12 28 20001218SH029 2 20001205 G 7414 K3823 DISTRIBUTOR SLICK PIPER PA34 PA34220T 7103420 SO CONT O360 TSIO360RB 17025 CE GRSHFT HSNG BASE WORN B RMMR K NONE O OTHER IN INSP/MAINT 1 CE 01 9284R 587 97101129 3449005 321440 DURING SCHEDULED 500-HOUR INSPECTION OF MAGNETO, FOUND DISTRIBUTOR GEARSHAFT AND BLOCK BEARINGS WORN. THIS WEAR HAD ALL OWED BRUSH TO WEAR WHICH CAUSED METAL CONTACT AND WEARING OF THE COIL, THE MAGNETO WAS REPLACED. GEAR AND BLOCK ASSY, PN K-3823. (X) 1 L 7 2 3O 3 O A7SO E9CE 2001022300052 20010223 00052 GL 2001 2 23 20001218SH030 3 20001205 G 6112 755379 LEAD PIPER PA34 PA34220T 7103420 SO HARTZL HCC2Y BHCC2YF2 GL PROPELLER HUB SEVERED B RMMR K NONE O OTHER IN INSP/MAINT 1 CE 01 9284R 823 3449005 DURING SCHEDULED INSPECTION, FOUND 2 PROPELLER BULKHEADS TO SLIP, RING LEADS SEVERED DUE TO CONTACT WITH THE ENGINE COWL . THREE FAULTS WERE FOUND WHICH POSSIBLY CONTRIBUTED TO THIS. ENGINE VIBRATION, MOUNTS WERE SAGGED. MFG RECOMMENDED R EPLACEMENT AT APPROX ENGINE MID-OVERHAUL. FORWARD TY WRAP HOLDING LEAD TO HUB HAD SHIFTED AFT. SPINNER BULKHEAD GROMME TS WERE DETERIORATED (ONE MISSING). PARTS REPLACED, CONTRIBUTING FACTORS REPLACED. GROUND TEST SATISFACTORY. (X) 1 L 7 2 3O A7SO 5 C P920 2001022300053 20010223 00053 SO 2001 2 23 20001218SH031 1 20001204 G 2140 75775694E423 SWITCH PIPER PA34 PA34220T 7103420 SO COCKPIT MALFUNCTIONED B RMMR K NONE L NO TEST IN INSP/MAINT 1 CE 01 928AR 368 A96070023 3449005 DURING SCHEDULED INSPECTION WHEN HEATER SWITCH SELECTED ON, HEATER DID NOT IGNITE. FUEL WAS DRAINING FROM DRAIN. TROUB LESHOOTING DETERMINED NO COMBUSTION AIR FLOW AND CONTINUITY BETWEEN THE TERMINALS OF P/N 94E42-3, (PIPER P/N 757-756) CO MBUSTION AIR SENSE SWITCH. COMBUSTION AIR BLOWER MOTOR BRUSHES WERE SHORT, AND WERE REPLACED. COMBUSTION AIR SWITCH WA S REPLACED WITH NEW. GROUND OPERATIONAL TEST WAS SATISFACTORY. (X) 1 L 7 2 3O A7SO 2001022300054 20010223 00054 CE 2001 2 23 20001218SH032 2 20001205 G 7414 K3823 DISTRIBUTOR SLICK PIPER PA34 PA34220T 7103420 SO CONT O360 TSIO360RB 17025 CE MAGNETO WORN B RMMR K NONE O OTHER IN INSP/MAINT 1 CE 01 9284R 587 97101123 3449005 321440 DURING SCHEDULED 500-HOUR INSPECTION OF MAGNETO, FOUND DISTRIBUTOR GEARSHAFT AND BLOCK BEARINGS WORN. PARTS WERE REPLAC ED. P/N M3828 GEAR REPLACED AND MAGNETO INSTALLED AND TIMED. (X) 1 L 7 2 3O 3 O A7SO E9CE 2001022300055 20010223 00055 2001 2 23 20001218SH033 4 20001004 G 3422 S33302 GYRO CESSNA 172 172R 2072401 CE COCKPIT INOPERATIVE B VT3R K NONE O OTHER IN INSP/MAINT 1 WP 09 9513R 32 17280619 DIRECTIONAL GYRO REPORTED INOPERATIVE BY PILOT. DURING REPLACEMENT OF DG, NOTED THE CASE UNDER THE DATA PLATE WAS DENTE D IN. SUSPECT THAT THE SERIAL NUMBER WAS STAMPED ON DATA PLATE RESULTING IN DENTED CASE. (X) 1 H 7 1 3O NT 3A12 2001022300056 20010223 00056 CE 2001 2 23 20001218SH034 1 20001110 G 8120 63272913 TURBOCHARGER BEECH 36 B36TC 1151609 CE ENGINE LEAKING B K NONE K FLUID LOSS IN INSP/MAINT 1 WP 25 978JG 149 EA637 TURBOCHARGER LEAKING OIL. (X) 1 L 7 1 3O 3A15 2001022300057 20010223 00057 CE 2001 2 23 20001218SH035 1 20000619 G 3221 07421802 BUSHING CESSNA 185 A185F 2072821 CE TAILWHEEL WORN D K NONE O OTHER IN INSP/MAINT 1 NM 09 93055 267 18503173 TAILWHEEL TO AFT BULKHEAD SUPPORT BUSHINGS FOUND SEVERELY WORN. SUBMITTER STATED NEW PARTS OBTAINED FROM CESSNA APPEAR TO BE MADE FROM INFERIOR MATERIALS. (X) 1 H 7 1 3O 3A24 2001022300058 20010223 00058 CE 2001 2 23 20001218SH036 1 20000624 G 3221 07421802 BUSHING CESSNA 185 A185F 2072821 CE TAILWHEEL CRACKED D K NONE O OTHER IN INSP/MAINT 1 NM 09 93055 40 18503173 ON INSPECTION OF TAILWHEEL SUPPORT BUSHINGS, FOUND NEWLY INSTALLED BUSHINGS SEVERELY WORN, EXTRUDED AND CRACKED. THESE BUSHINGS, OBTAINED FROM CESSNA, ARE MADE OF INFERIOR MATERIALS. (X) 1 H 7 1 3O 3A24 2001021400066 20010214 00066 CE 2001 2 14 20001219SH011 1 20001201 G 5523 9661000668 ATTACH FITTING BEECH 55 E55 1152732 CE ELEV TRIM TAB CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 25 1025T 3475 TE950 STEEL HORN WITH BRAZED IN BUSHING CRACK ON HORN ONLY NOT INTO BUSHING. CAUSE UNKNOWN. (X) 1 L 7 2 3O 3A16 2001022300059 20010223 00059 SO 2001 2 23 20001219SH013 1 20001128 G 2140 AD23D0475 REGULATOR JANITROL PIPER PA31 PA31350 7103110 SO FWD HEATER LEAKING H K NONE K FLUID LOSS IN INSP/MAINT 1 AL 01 4501B 318052168 INSTALLED NEW FUEL REGULATOR SHUT-OFF VALVE. AFTER SEVERAL MINUTES OF OPERATION, VALVE BEGAN LEAKING AT BODY HALF. REM OVAL AND INSPECTION REVEALED ALL FOUR SCREWS THAT HOLD BODY HALF TOGETHER TO BE LOOSE WITH TORQUE SEAL IN PLACE. TIGHTE NED SCREWS AND RE-TESTED. VALVE STILL LEAKED. REPLACED VALVE WITH NEW UNIT. SUBMITTER SUSPECTED IMPROPER TORQUE USED AT ASSEMBLY. (X) 1 L 7 2 3O A20SO 2001021400068 20010214 00068 SO 2001 2 14 20001219SH014 1 20001128 G 2140 A23D0475 REGULATOR PIPER PA31 PA31350 7103110 SO HEATER LEAKING H K NONE O OTHER IN INSP/MAINT 1 AL 01 4501B 17 318052168 FUEL OBSERVED DRIPPING FROM DRAIN LINE. AFTER GROUND RUN OF ENGINE WITHOUT HEATER BEING USED. VALVE WAS REMOVED FROM A IRCRAFT AND 30 PSI SHOP AIR WAS APPLIED TO INLET WITHOUT POWER TO OPEN VALVE. LEAK CHECK FLUID WAS APPLIED TO VALVE BOD Y AND LEAK WAS FOUND COMING FROM UNUSED MOUNTING HOLE ON VALVE BODY. (X) 1 L 7 2 3O A20SO 2001021400069 20010214 00069 NE 2001 2 14 20001219SH015 2 20001204 G 7323 430121204 GOVERNOR BOLKMS 117 BK117B1 5626012 EU LYC LTS101 LTS101750B1 41560 NE NR 1 ENGINE FAILED G RMXA O OTHER R PARTIAL RPM/PWR LOSS CR CRUISE 1 SW 05 460H 1815 7142 LE45700 IN CRUISE FLIGHT, NR 2 ENGINE TORQUE DROPPED TO 20 PERCENT, N1 STABILIZED AT 82 PERCENT. BEEPED NR 2 ENGINE UP, CONTINU ED FLIGHT, LANDED WITHOUT INCIDENT. FOUND THE NR 1 ENGINE HIGH SIDE GOVERNOR HAD FAILED. (X) 1 G 7 2 3U 3 U H13EU E5NE10 2001021400070 20010214 00070 CE 2001 2 14 20001219SH016 1 20001207 G 2720 24670013 TORQUE TUBE CESSNA 172 172RG 2072438 CE LT PEDAL UPRIGHT BROKEN B K NONE O OTHER IN INSP/MAINT 1 WP 07 4802R 6237 172RG0035 PILOT''S LEFT RUDDER PEDAL REPORTED AS ''NOT WORKING''. FOUND RUDDER PEDAL SUPPPORT POST BROKEN OFF RUDDER PEDAL TORQUE TUBE. MAINTENANCE REMOVED AND REPLACED ENTIRE TORQUE TUBE ASSEMBLY, LINKAGES, BEARING BLOCKS, AND HARDWARE (BOTH SIDES ). (X) 1 H 7 1 3O 3A17 2001021500107 20010215 00107 NE 2001 2 15 20001219SH019 1 20000629 G 6420 6511207101041 ARM SKRSKY SKRSKY S64 S64E 8142604 NE TAIL ROTOR HEAD CRACKED B JYDR K NONE O OTHER IN INSP/MAINT 1 NM 09 164AC 1432 A9028 64034D ARM ASSEMBLY HAD CRACK INDICATION ON OUTBOARD MOUNTING LUG EXTENDING FROM .256 INCH/.252 INCH DIAMETER THROUGH-HOLE TO . 34 INCH RADIUS. CIRCUMSTANCES UNDER WHICH CRACKING OCCURRED ARE UNKNOWN. POSSIBLE CAUSE IS FROM FRETTING MOVEMENT BETW EEN SLEEVE MOUNTING EARS, AND ARM ASSEMBLY MOUNTING LUGS. ALL THROUGH-HOLES OF BOTH SLEEVE AND ARM ASSEMBLY MEET BLUEPR INT REQUIREMENTS OF .256 INCH/.252 INCH DIAMETER. (X) 2 G 7 2 4U H4EA 2001021500108 20010215 00108 NE 2001 2 15 20001219SH020 1 20000721 G 6210 641520201049 BLADE SKRSKY S64 S64E 8142604 NE MAIN ROTOR CRACKED B JYDR K NONE O OTHER IN INSP/MAINT 1 NM 09 176AC 5881 64003 THE TOP SIDE OF THE TRAILING EDGE RETENTION BLOCK SCREW HOLE HAD A CRACK WHICH EXTENDED APPROXIMATELY 360 DEGREES AT A 7 O CLOCK POSITION (AS VIEWED FROM THE TOPSIDE LOOKING DOWN). THIS CRACK WAS DISCOVERED DURING A VISUAL INSPECTION PERFO RMED IN THE FIELD. (X) 2 G 7 2 4U H4EA 2001021500109 20010215 00109 NE 2001 2 15 20001219SH021 1 20000710 G 3213 646550152103 HOUSING SKRSKY SKRSKY S64 S64E 8142604 NE MLG CRACKED B JYDR K NONE O OTHER IN INSP/MAINT 1 NM 09 218AC 64033 MAIN LANDING GEAR, PN 6425-50100-013, -014, WAS REMOVED FOR OVERHAUL. DURING THE FLUORESCENT MAGNETIC PARTICLE INSPECTI ON PROCESS, 15 LINEAR INDICATIONS, NOT VISIBLE TO THE NAKED EYE, WERE REVEALED ON THE UPPER COLLAR HOUSING WITH MEASUREM ENTS OF .093 INCH TO .360 INCH IN LENGTH. THE INDICATIONS ARE LOCATED AT THE LIGHTENING HOLES WITH SOME BREAKING THE ED GE OF THE HOLE. A SECOND MLG WAS ALSO INSPECTED AND 7 LINEAR INDICATIONS NOT VISIBLE TO THE NAKED EYE WITH MEASUREMENTS OF .171 INCH TO .531 INCH IN LENGTH, WERE FOUND ON THE LOWER COLLAR HOUSING. (X) 2 G 7 2 4U H4EA 2001021400072 20010214 00072 2001 2 14 20001219SH023 4 20001010 G 2211 7004206901 COMPUTER BOLKMS 117 BK117B1 5626012 EU CSAS MALFUNCTIONED B R7MR K NONE O OTHER CR CRUISE 1 NM 07 62LF 129 7163 COMPUTER GOES OFF-LINE DURING FLIGHT. PILOT IS ABLE TO RESET. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X) 1 G 7 2 3U H13EU 2001021400073 20010214 00073 SW 2001 2 14 20001219SH024 1 20001116 G 6310 406040516101 SHAFT BELL 407 407 SW FWU WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 607AL 2492 A4230 53264 DURING 2,500 HOUR OVERHAUL, SPLINES WERE WORN BELOW LIMITS. (X) 1 G 7 1 3U O H2SW 2001021500110 20010215 00110 SW 2001 2 15 20001220SH001 1 20001204 G 6510 206040320015 SHAFT BELL 206 206L3 1182108 SW COOLER BLOWER DAMAGED B C68R K NONE O OTHER IN INSP/MAINT 1 WP 07 288JB 51288 PILOT REPORTED AIRCRAFT MAKING UNUSUAL NOISE. ON INSPECTION, FOUND FORWARD BEARING RETAINING NUT ON OIL COOLER BLOWER S HAFT HAD LOST TORQUE. LOCKING WASHER WAS FULLY ENGAGED AND INTACT, ON DISASSEMBLY, FOUND AFT FACE OF BEARING INNER RACE GROOVED AND DAMAGED BEYOND LIMITS. BOARING INNER RACE HAD ROTATED ON SHAFT CAUSING WEAR ON SHAFT JOURNAL IN EXCESS OF LIMITS. REPLACED SHAFT, BEARING, NUT AND LOCKING WASHER. (X) 1 G 7 1 3U H2SW 2001021400076 20010214 00076 EA 2001 2 14 20001220SH005 2 20000923 G 7414 6351 GEAR SLICK GULSTM 114 114B O145001 SW LYC O540 IO540T4B5 41532 EA MAGNETO WORN G HUNR K NONE O OTHER IN INSP/MAINT 1 NM 01 664H 595 14664 NYLON DRIVE GEAR WORN AND DECOMPOSED DUE TO WATERY CHEMICAL WITHIN MAGNETO CASE. COULD HAVE BEEN CAUSED BY A PRESSURE W ASHER AFTER AN OIL CHANGE OR OTHER SERVICE OR MAINTENANCE. (X) 1 L 7 1 3O 3 O RT A12SO 1E4 2001020900121 20010209 00121 CE 2001 2 9 20001220SH006 1 20001130 G 2400 604H193 RELAY CESSNA 310 310R 2074245 CE BATTERY BOX FAILED E BGJA K NONE H ELECT. POWER LOSS-50 PC DE DESCENT 1 GL 27 6832Y 310R2121 UPON DESCENT, A HEAVY LOAD WAS APPLIED TO THE ELECTRICAL SYSTEM CAUSING THE MASTER RELAY TO FAIL. SUBSEQUENT PARTIAL PO WER LOSS TO THE CABIN RESULTED. THIS REPORT IS FOR C/W FAR 135.415 AND AFS OPS MANUAL 5.9. 1 L 7 2 3O 3A10 2001021400077 20010214 00077 CE 2001 2 14 20001220SH007 1 20001214 G 5330 SKIN CESSNA 206 TU206A 2073318 CE FUSLEAGE CORRODED B RC0R K NONE O OTHER IN INSP/MAINT 1 SW 17 81608 U2060652 DURING AVIONICS RETROFIT, CORROSION NOTICED IN THE HORIZONTAL STABILIZER. FURTHER INSPECTION FOUND 85 PERCENT OF THE RU DDER ASSY WITH MAJOR CORROSION AND CABIN ROOF AREA AND MAIN WING SPAR ATTACHMENT POINTS. THIS AIRCRAFT SPENT MOST OF ITS LIFE IN FLORIDA AND PUERTO RICO. NO PROVISION IS MADE BY MANUFACTURER TO INSPECT MANY OF THESE AREAS. SUBMITTER SUGGE STED SMALL INSPECTION HOLES BE MADE AND BORESCOPED. (X) 1 H 7 1 3O A4CE 2001021500111 20010215 00111 GL 2001 2 15 20001220SH008 2 20001201 G 7323 355A57247221 SPRING AEROSP AS355 AS355F1 8680810 EU ALLSN 250C 250C20F 03013 GL GOV RETENTION BROKEN B SZTR A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION NR NOT REPORTED 1 WP 07 911NW 5082 CAE840415 DURING ROUTINE FLIGHT, PILOT EXPERIENCED A RAPID YAW TO THE RIGHT. NR 2 ENGINE, SN CAE-840415, SPOOLED DOWN TO FLIGHT I DLE AS THE RESULT OF THE NR 2 ENGINE GOVERNOR RETENTION SPRING FAILURE. GOVERNOR RETENTIONS SPRING WAS REPLACED. AIRCR AFT RETURNED TO SERIVCE. (X) 1 G 7 2 3U 3 U H11EU E4CE 2001021300017 20010213 00017 EA 2001 2 13 20001222SH001 2 20001107 G 7322 666943 FLOAT LYC O540 O540J3C5 41532 EA CARBURETOR DAMAGED B K NONE O OTHER IN INSP/MAINT 1 EA 11 142 75058101 L2121140A CARBURETOR FLOAT FILLED UP PART WAY WITH AVIATION FUEL CAUSING VERY RICH FUEL MIXTURE REDUCING ENGINE POWER. (X) 3 O E295 2001021300018 20010213 00018 SW 2001 2 13 20001222SH005 1 20001211 G 2910 FITTING GULSTM 112 112TCA 7630307 SW RT MLG BROKEN B K NONE K FLUID LOSS IN INSP/MAINT 1 GL 15 4590W 13180 RIGHT MAIN GEAR INBOARD HYDRAULIC FITTING BROKE. COMPLETE LOSS OF HYDRAULIC FLUID, FITTING WAS RUBBING ON WING SPAR SUP PORT BRACKET. THIS FAILURE HAPPENED AT 20 INCHES BELOW AIR TEMP. (X) 1 L 7 1 3O A12SO 2001021300019 20010213 00019 2001 2 13 20001222SH006 4 20001206 G 6122 B20107 GEAR MCAULY PROP GOVERNOR CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 RELEVANT MAGNETIC PARTICLE INDICATION ON TEETH AREA OF IDLER GEAR. (X) 2001021300020 20010213 00020 CE 2001 2 13 20001222SH007 1 20001214 G 2110 SEAL GODFREY BEECH 90 B90 1152912 CE PWA PT6 PT6A20 52043 EA SUPERCHARGER LEAKING E IJAA C ABORTED TAKEOFF B K SMOKE/FUMES/ODORS/SPARKS FLUID LOSS TX TAXI/GRND HDL 1 CE 07 777KU 1884 35493 LJ377 PCE21609 PILOT ABORTED FLIGHT DUE TO SMELL OF SMOKE IN CABIN. FOUND SUPERCHARGER SEAL LEAKING OIL INTO AIRCRAFT SILENCER. THIS MIXTURE OF OIL AND BLEED AIR CAUSED SMOKE TO ENTER CABIN. (X) 1 L 7 2 3T 3 T 3A20 E4EA 2001021300021 20010213 00021 GL 2001 2 13 20001222SH008 3 20001110 G 6114 B32811 SPRING PIPER PA23 PA23250 7102308 SO HARTZL HCE2Y HCE2YR2 GL PROPELLER HUB CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 09 13916 600 274551 901 PROPELLER WAS LEAKING GREASE. DURING TEAR DOWN FOUND WATER IN HUB. WATER HAD CORRODED SPRING. SPRING SUBSEQUENTLY BROK E INTO FOUR PIECES. ALSO, FOUND BOTH BLADE SHANKS SERIOUSLY CORRODED IN AREA ADDRESSED BY AD 77-12-06. LAST DOCUMENTED OVERHAUL ON PROP WAS 10/85. (X) 1 L 7 2 3O 1A10 5 C P9EA 2001021300022 20010213 00022 NE 2001 2 13 20001222SH009 2 20000912 G 8530 287177 CYLINDER CVAC 340 34032 2422706 WP PWA R2800 R280083A 52026 NE NR 5 CRACKED H O OTHER R PARTIAL RPM/PWR LOSS DE DESCENT 1 SW 17 3427 257 90 30890 PILOT NOTED DROP IN BMEP AND ROUGHNESS ON DESCENT. INSPECTION DISCOVERED NR 5 CYLINDER CRACKED 1.50 INCHES FROM SPARK PLUG BOSS OUTWARD TOWARD CENTER OF HEAD. (X) 2 L 7 2 4R 4 R 6A6 5E8 2001021300023 20010213 00023 NE 2001 2 13 20001222SH010 2 20001205 G 8530 11876 PUSHROD TUBE SCWZER G164 G164B 3952802 EA PWA R1340 R1340AN1 52016 NE NR 3 CYL EXH BROKEN B MU2R E ENGINE SHUTDOWN R PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 CE 09 3629D 5187 182 743B 17718 AIRCRAFT WAS BEING TEST RUN FOLLOWING ENGINE FAILURE. UPON RUN-UP, ENGINE STARTING MISSING AND WOULD NOT HOLD RPM OVER 600. AIRCRAFT WAS SHUT DOWN. ALL ROCKER BOX COVERS WERE PULLED AND INSPECTION REVEALED THE NR 3 CYLINDER EXHAUST ROCKE R PLAY WOULD GO FROM .010 INCH TO APPROXIMATELY .125 INCH AND A RATTLE WAS ALSO HEARD. UPON REMOVAL OF THE PUSH ROD TUB E, FOUND THE TOP END OF THE ASSY HAD BROKEN IN THE AREA WHERE THE TUBE SLIDES INTO THE END FITTING CAUSING THE ENGINE TO MALFUNCTION. (X) 1 Q 7 1 3R 3 R 1A16 5E2 2001021300024 20010213 00024 SO 2001 2 13 20001222SH011 1 20001220 G 3230 105476 POWERPACK PIPER PA28 PA28R200 7102811 SO EMPENAGE FAILED D O OTHER O OTHER CL CLIMB 1 SO 01 4875T 399 28R7235129 GEAR WOULD NOT RETRACT IN AIR, AND WOULD NOT GO DOWN AND LOCKED. PUT AIRCRAFT ON JACKS, AND GEAR WOULD NOT CYCLE. FOUN D CIRCUIT BREAKER TRIPPED. RESET BREAKER, GEAR COULD COME UNLOCKED, BUT WOULD NOT GO UP, AND GEAR WOULD NOT LOCK DOWN. PUMP DID NOT HAVE PRESSURES IAW PIPER MANUAL. REMOVED POWER PACK FOR OVERHAUL, REINSTALLED AFTER OVERHAUL, GEAR CYCLED NORMAL. (X) 1 L 7 1 3O 2A13 2001020900122 20010209 00122 EA 2001 2 9 20001222SH012 2 20001222 G 8520 13S19648 GEAR LYC CESSNA 206 206H 2073301 CE LYC O540 IO540AC1A5 EA CRANKSHAFT SPALLED A K NONE O OTHER IN INSP/MAINT 1 SW 99 7273Q 438 20608045 L2694348A DURING INSP C/W AD 91-14-22 AND LYC SB 475 REV A, NO DAMAGE FOUND TO CRANKSHAFT COUNTERBORE RECESS, ALIGNMENT DOWEL, RET AINING BOLTS AND THREADS. UPON INSP OF CRANKSHAFT GEAR TEETH, SEVERAL WERE FOUND TO HAVE LINEAR PTTING WHICH APPEARED T O BE CAUSED BY PLATING BREAKDOWN DEFECTS RESEMBLING FRETTING/SPALLING. NO CRITERIA EXISTED IN BODY OF AD, MFG O/H MANUA L, OR SB TO IDENTIFY SERVICEABLE LIMITS FOR DAMAGE FOUND ON TEETH, SO GEAR REPLACED. IT NOTE: THIS ENGINE MAINTAINED U SING 50-HR OIL CHANGES/SAMPLE INTERVALS WITH NO EVIDENCE OF INTERNAL PROBLEMS TO THIS POINT. RECOMMEND ADDITIONAL CRIT ERIA BE ADDED TO SUPPORT PARA (A) OF AD, SO A/W OF GEAR, SHOULD ANY DAMAGE BE FOUND, CAN BE DETERMINED. (X) 1 H 7 1 3O 3 O RT A4CE 1E4 2001021300015 20010213 00015 CE 2001 2 13 20001227SH001 1 20001222 G 3221 TRUNNION CESSNA 425 425 2076018 CE NLG GROOVED B EBVR K NONE O OTHER IN INSP/MAINT 1 GL 09 111SU 2791 4250205 FOUND TWO SMALL GROOVES WORN INTO THE NOSE GEAR UPPER TRUNNION WHERE THE DRAG BRACE ATTACH LINK CONNECTS TO THE UPPER TR UNNION. THE FORWARD END OF THE ATTACH LINK WAS MAKING CONTACT WITH THE UPPER TRUNNION DURING NORMAL OPERATION. FOUND B EARING IN ATTACH LINK WAS GOOD. NO PLAY WAS EVIDENT. REMOVED NOSE GEAR. REMOVED UPPER TRUNNION AND PERFORMED NDT INSP ECTION OF AFFECTED AREA. NO DEFECTS WERE NOTED. BLENDED OUT SMALL GROOVES, TREATED AND PRIMED AREA. RECOMMEND INSPEC TING THIS AREA ANYTIME THE DRAG BRACE IS DISCONNECTED FROM THE UPPER TRUNNION. (X) 1 L 7 2 3T RT A7CE 2001021300016 20010213 00016 SW 2001 2 13 20001227SH002 1 20001222 G 8120 4078109001 TURBOCHARGER MOONEY M20 M20K 5870220 SW ENGINE FAILED B EBVR B A EMER. DESCENT UNSCHED LANDING R K PARTIAL RPM/PWR LOSS FLUID LOSS CR CRUISE 1 GL 09 5269R 251188 OPERATOR WAS CRUISING AT FL 210 WHEN A LOUD NOISE OCCURED FOLLOWED BY AN IMMEDIATE PARTIAL REDUCTION IN POWER. THE OPER ATOR BEGAN IMMEDIATE DESCENT AND VECTORED TO NEAREST AIRPORT FOR LANDING. UPON INVESTIGATING PROBLEM, THE TURBO SHAFT W AS FOUND TO HAVE FAILED AND THE TURBO IMPELLER MOVED AGAINST THE HOUSING AND SHEARED SEVERAL BLADES. MOST OF THE AIRCRA FT''''S OIL WAS LOST OVERBOARD. FOUND METAL IN THE INTERCOOLERS AND FILTER ASSEMBLY. TURBO ASSEMBLY WAS REMOVED AND SE NT TO OEM. ENGINE WAS REMOVED AND SENT OUT FOR INSPECTION. NO DEFINITE CAUSE FOR THE FAILURE HAS BEEN DETERMINED AT TH IS WRITING. (X) 1 L 7 1 3O 2A3 2001011101324 20010111 01324 CE 2001 1 11 20001227SH003 1 20001222 G 2571 0553022 RACK CESSNA 172 172S 2072439 CE BATTERY CRACKED B EIPR K NONE O OTHER IN INSP/MAINT 1 WP 07 428SA 194 49 172S8547 THE BATTERY MOUNT RACK WAS FOUND CRACKED AND BROKEN AT ITS LOWER, OUTBOARD ATTACH POINT WHERE IT IS SECURED TO THE FIREW ALL. THE CRACK OCCURRED AT THE BEND RADIUS OF THE LOWER SINGLE FLANGE OR TAB. SUBMITTER SUGGESTED CAUSE FOR THE CRACK IS THE FIREWALL IS NOT REINFORCED IN THAT AREA. THERE IS A STIFFENER ANGLE ON THE AFT SIDE OF THE FIREWALL THAT RUNS DIAGONALLY FROM THE LOWER, INBOARD TO UPPER, OUTBOARD OF THE BATTERY RACK ATTACHMENT AREA, AND THE UPPER, INBOARD, FORWA RD CORNER OF THE BATTERY RACK IS SUPPORTED BY THE ENGINE MOUNT TUBE WITH AN ADEL CLAMP, BUT THERE IS NOTHING TO HELP THE OUTBOARD LOWER RACK ATTACH AREA SUPPORT THE LOAD DURING LANDING OR TURBULENCE. THE BATTERY RACK WAS REPLACED. (X) 1 H 7 1 3O NT 3A12 2001021300026 20010213 00026 EA 2001 2 13 20001227SH007 2 20001119 G 8530 EXHAUST VALVE PIPER PA28 PA28140 7102802 SO LYC O320 O320E2A 41508 EA NR 4 CYLINDER FAILED D A UNSCHED LANDING R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 GL 27 6772W 601 2820899 L1514627A STUDENT PILOT SOLD X-C - ENGINE FAILURE. LANDED SAFELY IN FIELD. NR 4 CYLINDER EXHAUST VALVE STEM FOUND BROKEN NEXT TO VALVE FACE. PISTON PIN PLUG ALSO FOUND WORN APPROXIMATELY .050 INCH. (X) 1 L 7 1 3O 3 O 2A13 E274 2001021300027 20010213 00027 CE 2001 2 13 20001227SH008 1 20000801 G 3230 1693800573 UPLOCK BEECH 23 C24R 1151254 CE LT MLG CORRODED H O OTHER O OTHER DE DESCENT 1 SO 15 1831N 2323 MC763 PILOT ATTEMPTED EXTENDING THE LANDING GEAR AFTER A NORMAL FLIGHT; WHEN THE LT MAIN LANDING GEAR WOULD NOT EXTEND, PILOT MADE SEVERAL ATTEMPTS WITH BOTH THE NORMAL AND THE EMERGENCY SYSTEMS TO BRING DOWN THE GEAR. THE PILOT MADE A GEAR UP L ANDING. AFTER LIFTING THE AIRCRAFT FROM THE RUNWAY, FOUND THE LT GEAR UPLOCK WOULD NOT RELEASE. PRYING THE UPLOCK ARM AWAY FROM THE GEAR ALLOWED THE GEAR TO FREEFALL INTO THE GEAR DOWN AND LOCKED POSITION. A GEAR DOWN OF THE UPLOCK WAS P ERFORMED. SHAFT WAS FOUND RUSTED AND CYL HEAD, WHICH THE SHAFT RUNS THROUGH, TO BE CORRODED CAUSING THE UPLOCK CYLINDER TO SEIZE. (X) 1 L 7 1 3O A1CE 2001022000128 20010220 00128 EA 2001 2 20 20001227SH010 2 20001206 G 7414 1052947 MAGNETO GULSTM 500 500B 0141106 SW LYC O540 IO540* 41532 EA ENGINE FAILED D E ENGINE SHUTDOWN R PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 SW 15 127KH 16 F280010ER 500B102738 L20548 PRE-FLIGHT RUN UP MAGNET CHECK REVEALED MAGNETO DEAD. POST-REPLACEMENT INSPECTION REVEALED EXCESSIVE. RADIAL AND END P LAY ON ROTATING MAGNET SHAFT POINTS WOULD NOT OPEN. (X) 1 H 7 2 3O 3 O 6A1 1E4 2001021300029 20010213 00029 EA 2001 2 13 20001227SH011 2 20001205 G 7414 10349276REVG CAPACITOR GULSTM 500 500B 0141106 SW LYC O540 IO540E1A5 41532 EA MAGNETO INOPERATIVE D K NONE O OTHER IN INSP/MAINT 1 SW 15 1153C 372 B12004ER 1474169 RL32948 PRE-FLIGHT RUN UP REVEALED EXCESS RPM DROP ON MAG CHECK. POST-REPLACEMENT INSPECTION REVEALED POINTS BURNED AND CAPACIT OR WIRE BROKEN AT CONNECTOR END. (X) 1 H 7 2 3O 3 O 6A1 1E4 2001021300030 20010213 00030 CE 2001 2 13 20001227SH012 1 20001207 G 2810 070009977 VENT LINE CESSNA 182 182B 2072706 CE CABIN CORRODED D K NONE O OTHER IN INSP/MAINT 1 SW 99 2711G 3776 52011 DURING AN ANNUAL INSPECTION, THE FUEL TANK VENT CARRY-THROUGH WAS FOUND CORRODED THROUGH AT SEVERAL POINTS ALONG THE TUB INGS LENGTH. FUEL STAINS WERE ALSO VISIBLE. THE VENT LINE WAS HIDDEN BEHIND A LAYER OF FIBERGLASS INSULATION. THIS PA RT CAN ONLY BE INSPECTED BY REMOVAL OF THE HEADLINER AND ANY INSULATION AT THIS LOCATION. 12 1 H 7 1 3O NT 3A13 2001021300038 20010213 00038 GL 2001 2 13 20001227SH030 1 20000929 G 5540 AN43B BOLT AMTR AEROCP COMPMONST145 05602RF GL RUDDER HINGE CORRODED B K NONE O OTHER IN INSP/MAINT 1 CE 09 6162A 206 96107 HINGE BOLTS WERE FOUND LOOSE DURING ANNUAL INSPECTION. REMOVED RUDDER AND HINGE BOLTS, ROTATED. CALLED COMP AIR PER PR OCEDURE TO TIGHTEN TORQUE ETC. CUT HOLES IN RUDDER TO ACCESS NUTS. FOUND RUST AND CORROSION. REMOVED NUTS AND AN43B H INGE BOLTS. TOP BOLT MINIMAL RUST AND CORROSION, CENTER AND LOWER, FOUND SEVERE RUST AND CORROSION ON SHANKS AND NUTS. (X) 1 H 7 1 30 NC EXPA1H71 2001021300040 20010213 00040 GL 2001 2 13 20001227SH032 1 20000902 G 3213 AXLE AMTR F2SPEC F2SPECIAL 05604C5 GL LT WHEEL FAILED H K NONE O OTHER LD LANDING 1 EA 17 521S 47 002GM ON LANDING, LEFT AXLE FAILED CAUSING AIRCRAFT STRUT TO DIG INTO GRASS FIELD. AIRCRAFT FLIPPED ON ITS BACK CAUSING SUBST ANTIAL DAMAGE. PRELIMINARY INSPECTION INDICATED A FAILED WELD ON THE AXLE TO STRUT BRACKET. (X) 1 H 7 1 EXPA1H71 2001021300041 20010213 00041 SW 2001 2 13 20001227SH033 1 20001211 G 7920 HOSE MOONEY M20 M20A 5870204 SW OIL COOLER LEAKING H K NONE K FLUID LOSS IN INSP/MAINT 1 SO 13 6099X 300 1700A OPERATOR REQUESTED MECHANIC TO TRY AND LOCATE AN OIL LEAK IN ENGINE COMPARTMENT. AFTER INVESTIGATING, THE OIL COOLER HO SE WAS FOUND TO HAVE A SMALL HOLE IN THE EXTERIOR AROUND MIDWAY OF THE HOSE. (X) 1 L 7 1 3O 2A3 2001021300042 20010213 00042 EA 2001 2 13 20001227SH034 2 20001211 G 8520 CAMSHAFT AMRGEN AA5 AA5A 3960106 SO LYC O320 O320E2G 41508 EA ENGINE DAMAGED H K NONE O OTHER IN INSP/MAINT 1 SO 13 26993 1317 AA5A0866 L4876327A CYLINDERS 2 AND 4 REMOVED DUE TO LOW COMPRESSION. AT THIS TIME, THE CAMSHAFT WAS FOUND SEVERELY PITTED, ONE LOBE WAS FL AT. LIFTER BODIES WERE ALSO PITTED. 1,317.0 HOURS, TOTAL TIME. (X) 1 L 7 1 3O 3 O A16EA E274 2001021300043 20010213 00043 SO 2001 2 13 20001228SH001 1 20001211 G 7820 MUFFLER AMRGEN AA5 AA5A 3960106 SO EXHAUST DETERIORATED H K NONE O OTHER IN INSP/MAINT 1 SO 13 26993 1317 AA5A0866 DURING AN ANNUAL INSPECTION, THE MUFFLER ASSY WAS FOUND TO HAVE ITS WALLS SEVERELY DETERIORATED AND THE BAFFLES LOOSE. (X) 1 L 7 1 3O A16EA 2001021300044 20010213 00044 SO 2001 2 13 20001228SH002 2 20001211 G 7310 HOSE CESSNA 140 140 2071602 CE CONT C85 C8512 17008 SO CARBURETOR LEAKING H K NONE K FLUID LOSS IN INSP/MAINT 1 SO 13 1888V 14068 DURING ANNUAL INSPECTION, THE FLEXIBLE FUEL HOSE WAS FOUND WET WITH FUEL NEAR ONE OF THE FITTINGS. THE HOSE WAS NOT THA T OLD AND WAS MADE IN THE FIELD. (X) 1 H 7 1 3O 3 O NC A768 E233 2001021300045 20010213 00045 2001 2 13 20001229SH001 4 20001214 G 2561 AV8AS2100 LIFE VEST CABIN FAILED B KQ1R K NONE O OTHER IN INSP/MAINT 1 EA 07 INDIVIDUAL FLOTATION DEVICE FAILED THE MANUFACTURER''S RECOMMENDED 2 PSI CELL TEST IAW 25-60-33. ITEM DATE OF MFG: AUG 1987. FAIR WEAR AND TEAR. (X) 2001021300046 20010213 00046 2001 2 13 20001229SH002 4 20001214 G 2561 AV8AS2100 LIFE VEST CABIN FAILED B KQ1R K NONE O OTHER IN INSP/MAINT 1 EA 07 INDIVIDUAL FLOTATION DEVICE FAILED MANUFACTURER''S RECOMMENDED TWO PSI CELL TEST IAW 25-60-33. ITEM DATE OF MFG: AUG 1 987. FAIR WEAR AND TEAR. (X) 2001021300047 20010213 00047 GL 2001 2 13 20001229SH003 3 20001201 G 6111 BLADE MULTEC D16 D16A 9230604 WP HARTZL HC82 HC82VL2 GL PROPELLER CRACKED B FR6R K NONE O OTHER IN INSP/MAINT 1 NM 03 708T TTN77 K1428N DISASSEMBLY OF PROPELLER FOR O/H AND AD COMPLIANCE REVEALED BLADE, SN 106993, IS SCRAP BECAUSE BALANCE HOLE TOO DEEP. M AX DEPTH IS 6.5 INCHES. BLADE, SN A27681, IS SCRAP BECAUSE IT IS CRACKED IN THE SHANK. BREAKAWAY TEST PERFORMED TO PUS H THE TUBE BACK IN THE HUB. TEST ONLY NEEDED 2200 PSI TO BREAK IT AWAY. 6000 PSI IS THE MIN PRESSURE REQUIRED FOR THE TEST AND IF TUBE MOVES, IT MUST BE REMOVED AND NEW TUBE INSTALLED. BLADE THRUST BEARINGS PN A14B THAT WERE INSTALLED FO R THE BLADES HAD WRONG RETAINERS PN A159. S/B REPLACED WITH PN A969. COULD HAVE CAUSED BLADE SEPARATION. RETAINER PN A159 S/B REPLACED WITH A159N PER AD 59-01-03. (X) 1 L 7 2 3O 2A1 5 C P23EA 2001021300048 20010213 00048 GL 2001 2 13 20001229SH004 3 20001201 G 6111 BLADE MULTEC D16 D16A 9230604 WP HARTZL HC82 HC82VL2 GL PROPELLER CRACKED B FR6R K NONE O OTHER IN INSP/MAINT 1 NM 03 708T TTN77 K2013N PROPELLERS REMOVED FOR OVERHAUL AND AD COMPLIANCE. BLADE SN 93464 IS SCRAP BECAUSE IT IS CRACKED IN THE SHANK. ONE OF THE BLADE THRUST BEARINGS PN A14B INSTALLED FOR THE BLADES HAD WRONG RETAINERS PN A159. S/B REPLACED WITH PN A969. COU LD CAUSE BLADE SEPARATION. THE OTHER BLADE THRUST BEARING IS PN A14A WHICH IS STILL GOOD. SHOULD HAVE HAD RETAINER PN A159N INSTALLED. THRUST BEARINGS A14A AND A14B BOTH SERVICEABLE BEARINGS, BUT SHOULD BE ALL THE SAME IN PROP ASSY (RETA INER PN A159 SHOULD HAVE BEEN REPLACED WITH A159N PER AD 59-01-03). (X) 1 L 7 2 3O 2A1 5 C P23EA 2001021300049 20010213 00049 SO 2001 2 13 20001229SH005 1 20001207 G 3211 6704204 TRUNNION PIPER PA34 PA34200 7103405 SO LT MLG BROKEN D K NONE O OTHER TX TAXI/GRND HDL 1 SO 09 1390T 347250274 NO LOG BOOKS WITH A/C. RT TACH: 1,993.5 HRS. HM-2,232.1 HRS. LEFT MAIN GEAR SEPARATED FROM A/C WHILE BEING TAXIED AF TER LANDING. FAILURE BELIEVED TO BE CAUSED BY REAR TRUNNION ASSY WITH CRACKS/BREAKS AT 3 OF 4 ATTACH AREAS. WHEN FINAL ATTACH AREA FAILED, THIS ALLOWED GEAR TO DAMAGE FORWARD ATTACH AND GEAR TO SEPARATE A/C. RECOMMEND FORWARD AND AFT TRU NNIONS BE INSPECTED AS MM REQUIRES DURING INSPECTION. (X) 1 L 7 2 3O A7SO 2001021300050 20010213 00050 EA 2001 2 13 20001229SH006 2 20001220 G 7230 COMPRESSOR BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA RT ENGINE FAILED D A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 CE 01 366EA 4421 925 BB841 PCE85097 JUST AFTER TAKEOFF, COPILOT REPORTED SPARKS COMING FROM RT ENGINE INBOARD AND OUTBOARD EXHAUST STACKS. POWER WAS REDUCE D AND AIRCRAFT RETURNED TO AIRPORT WITHOUT INCIDENT. INSPECTION THROUGH THE HIGH AND LOW BLEED VALVE OPENINGS REVEALED MASSIVE COMPRESSOR FAILURE. ENGINE REMOVED AND SENT FOR REPAIR. (X) 1 L 7 2 4T 4 T A24CE E4EA 2001021300052 20010213 00052 SO 2001 2 13 20001229SH008 2 20001218 G 8520 630826 BEARING BEECH 55 95A55 1152704 CE CONT O470 IO470L 17026 SO CONNECTING ROD DELAMINATED H K NONE O OTHER IN INSP/MAINT 1 SW 99 349Y 8 TC389 297805RCS ENGINE WAS DISASSEMBLED FOR PROPELLER STRIKE INSPECTION, FOUND NR 6 ROD BEARING SURFACE MATERIAL DELAMINATING FROM BEARI NG EXPOSING BABBITT MATERIAL AND REMAINING BEARINGS SHOWING SIGNS OF THIS CONDITION FORMING ON THEM. ALL BEARINGS WERE SENT TO TELEDYNE CONTINENTAL MOTORS FOR ANALYTICAL INSPECTION. THESE BEARINGS WERE REMOVED FROM A TELEDYNE CONTINENTAL MOTORS FACTORY REMANUFACTURED WITH 8.3 TOTAL HOURS AND 12 MONTHS FROM INSTALLATION DATE. (X) 1 L 7 2 3O 3 O 3A16 3E1 2001030600018 20010306 00018 CE 2001 3 6 20001229SH010 1 20001229 G 3230 12810331 ACCUMULATOR CESSNA 210 210L 2073448 CE MLG CRACKED B K NONE K FLUID LOSS IN INSP/MAINT 1 CE 01 60617 21060595 FOUND ACCUMULATOR LEAKING. CLEANED AND CYCLED GEAR. FOUND ACCUMULATOR LEAKING FROM CRACK IN MACHINED CASTING SEAM. CR ACK IS ONLY VISIBLE WITH 10X MAGNIFICATION. CAUSE - POSSIBLE CASTING FLAW. (X) 1 H 7 1 3O 3A21 2001030600019 20010306 00019 EA 2001 3 6 20001229SH011 2 20001214 G 7322 30766 FLOAT BBAVIA 7 7ECA 21101NN SW LYC O235 O235C1 41505 EA CARBURETOR DAMAGED D K NONE O OTHER IN INSP/MAINT 1 NM 13 9699S 472 Y202371 430 L890015 CARBURETOR WAS OVERFILLING. UPON DISASSEMBLY, FOUND CARBURETOR GASKET, PN 16-B85, SAGGING AND THE METAL FLOAT, WHERE TH E NEEDLE SEAT RUBS, WORN EXCESSIVELY AT THE FLOAT LEVER ADJUSTMENT TAB. (X) 1 H 7 1 3O 3 O A759 E223 2001030600020 20010306 00020 CE 2001 3 6 20001229SH012 1 20000925 G 3213 2500404511 STRUT HELIO H295 H295 4300802 CE RT MLG BROKEN D O OTHER O OTHER LD LANDING 1 SW 03 993PT 1451 UPON LANDING, THE AIRCRAFT EXPERIENCED SOME VIBRATION AND SHORTLY AFTER, THE RIGHT MAIN LANDING GEAR STRUT BROKE. THE F AILURE OCCURRED HALF WAY DOWN THE LEG, A 2.25 INCH SQUARE CONSTRUCTED OF 0.132/4130 STEEL. THE LANDING GEAR IS BEING EV ALUATED. (X) 1 H 7 1 3O 1A8 2001021500112 20010215 00112 SW 2001 2 15 20001229SH014 1 20001206 G 6410 406016100119 BLADE BELL BELL 407 407 SW TAIL ROTOR CRACKED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 407AL 2778 A95 53044 DURING DAILY INSPECTION, BLADE CRACKED AT WEEP HOLE, ON THE INBOARD LEADING EDGE. CRACK EXTENDED AFT FOR ABOUT 1.50 INC HES. (X) 1 G 7 1 3U O H2SW 2001021500113 20010215 00113 SW 2001 2 15 20001229SH015 1 20001205 G 6410 406016100119 BLADE BELL 407 407 SW TAIL ROTOR CRACKED E ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 497AL 2720 278 53172 DURING DAILY INSPECTION, BLADE CRACKED AT WEEP HOLE, ON THE INBOARD LEADING EDGE. CRACK EXTENDED AFT FOR ABOUT 1.25 INC HES. (X) 1 G 7 1 3U O H2SW 2001021500116 20010215 00116 EU 2001 2 15 20001229SH019 1 20001214 G 2432 BRACKET SNIAS 350 AS350B2 8680813 EU BATTERY BOX WORN H K NONE O OTHER IN INSP/MAINT 1 SW 99 4035W 441 2912 DURING A 100-HOUR INSPECTION, FOUND THE FORWARD BATTERY HOLD-DOWN BRACKET PN G10110 AND THE AFT BATTERY HOLD-DOWN BRACKE T PN G10115 WERE BADLY WORN AT THE SLOTS THAT HOLD THE BATTERY IN PLACE. THERE ARE 3 AIRCRAFT WITH THE SAME STC INSTALL ING THE BATTERY IN THE TAIL BOOM AND ALL SHOW THE SAME PROBLEM WITH THE BRACKET WEAR. WHEN ORDERING REPLACEMENT BRACKET S, THE HOLES DO NOT MATCH THE ATTACH POINTS IN THE AIRCRAFT. EVEN THROUGH ALL AIRCRAFT HAVE THE SAME STC, AEC SAYS THER E ARE AT LEAST 2 CHANGES TO THE DRAWINGS AND THAT THEY ARE WORKING ON THE PROBLEM OF HOW TO FIGURE OUT WHAT PART GOES TO WHAT CHANGE IN AIRCRAFT. TT: 2,571.3 HOURS. (X) 1 G 7 1 3U H9EU 2000011500646 20000115 00646 EA 2000 1 15 2000ZZZX117 2 20000113 G 7322 ID PLATE DONALDSON P107172 MAULE M4 M4220 SO FRNKLN 6AV350 6A350C1 27043 EA CARBURETOR LOOSE B A O OTHER C F.O.D. NR NOT REPORTED 1 WP 25 11EN C2945100301 2037 IDENTIFICATION STICKER CAME LOOSE AND LODGED AGAINST CARBURETOR VENTURI. STICKER WAS STUCK IN CARBURETOR HEAT BOX AND W AS NOT SEEN WHEN NEW FILTER WAS INSTALLED. SUBMITTER RECOMMENDED THAT IDENTIFICATION OF FILTER BE STAMPED ON OR ETCHED. 1 H 7 1 3O 3 O 3A23 E9EA 2000011500661 20000115 00661 EA 2000 1 15 2000ZZZX132 2 20000103 G 7310 LW127844274 MANIFOLD PIPER PA23 PA23250 7102308 SO LYC O540 IO540C4B5 41532 EA FUEL INJECTION LOOSE H K NONE K FLUID LOSS IN INSP/MAINT 1 SW 99 14268 274828 L612148 FOUND FUEL LINE FITTING ON FUEL INJECTOR LOSE CAUSING FUEL STARVATION TO FUEL MANIFOLD. TIGHTENED FITTING AND RETURNED TO SERVICE. 1 L 7 2 3O 3 O 1A10 1E4 2000011500666 20000115 00666 CE 2000 1 15 2000ZZZX137 1 20000114 G 2434 649304 ALTERNATOR BEECH 36 A36 1151604 CE ENGINE FAILED B W45R O OTHER B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 WP 07 3222B 143 E3222 ALTERNATOR BOUND UP AND CAUSED THE DRIVE COUPLING TO SEIZE. STRONG SMELL OF BURNED ELECTRICAL. 1 L 7 1 3O 3A15 2000012200355 20000122 00355 CE 2000 1 22 2000ZZZX172 1 20000106 G 3230 24411091 PIVOT ASSY CESSNA 172 172RG 2072438 CE LT MLG FAILED H O OTHER O OTHER NR NOT REPORTED 1 SW 99 5284V 7365 172RG0494 A 1 1/4 ALUMINUM SHAFT THT ATTACHES THE ACTUATOR TO THE LEFT MAIN GEAR STRUT FAILED UPON RETRACTION. THIS RESULTED IN A CONDITION IN WHICH THE GEAR WAS HANGING OUT AND COULD NOT BE RETRACTED OR EXTENDED. THE INSTRUCTOR HAD STUDENT HANG OU T THE DOOR OF THE AIRCRAFT AND PULL THE GEAR FORWARD UNTIL IT LOCKED IN THE DOWN POSITION. THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. THE ENDS OF THE BROKEN PART APPEAR TO HAVE FAILED IN FATIGUE. THOUGH I AM NO METALURGIST, I THINK I SEE BEACH MARKS ON THE BROKEN SURFACE. 1 H 7 1 3O 3A17 2000012200384 20000122 00384 SW 2000 1 22 2000ZZZX200 1 20000103 G 2432 BATTERY GILLBATT MTSBSI MU2 MU2B 5780404 SW BATTERY BAY DISCHARGED B R2JR K NONE O OTHER IN INSP/MAINT 1 EA 21 36G 035 WHILE PERFORMING PERIODIC INSPECTION, FOUND MAIN BATTERIES HAD CASE DAMAGE CAUSED BY OVERHEATING. ALSO, ELECTROLYTE MOS TLY BOILED OUT. AIRCRAFT ELECTRICAL SYSTEM TESTED OK. BATTERIES SERVICED AND CHECKED 97 HRS PREVIOUSLY, OK PER MANUAL. FAILURE POSSIBLY DUE TO AGE. SUBMITTER SUGGESTED TIME CHANGE REQUIREMENTS BE REQUIRED OR MORE DETAILED IN-SERVICE INSP ECTION CRITERIA BE REQUIRED (I.E., LOAD TEST) IN ORDER TO DETECT PENDING FAILURES. 1 H 7 2 3T A2PC 2000012200385 20000122 00385 NM 2000 1 22 2000ZZZX201 1 20000104 G 3242 2445902 CARRIER BFGOODRICH 21565 DHAV DHC8 DHC8* NM BRAKE BROKEN B XC4R K NONE O OTHER IN INSP/MAINT 1 SO 19 1012 BRAKE ASSY P/N 2-1565 FAILED PREMATURELY. NR 1 CARRIER AND LINING ASSY BROKEN IN HALF. THIS IS A CONTINUAL DISCREPANCY . OEM PARTS INSTALLED IN BRAKE ASSY AND THE MOST RECENT BRAKE CONFIGURATION P/N 2-1565. 2 H 7 2 4T RT A13NM 2000012200394 20000122 00394 2000 1 22 2000ZZZX210 4 20000103 G 2215 40005238501 SERVO MTSBSI MU2 MU2B 5780404 SW AUTOPILOT FAILED B R2JR K NONE O OTHER IN INSP/MAINT 1 EA 21 36G 5463 035 AFTER REINSTALLING BENDIX AUTOPILOT SERVOS AFTER FACTORY OVERHAUL BY ALLIED SIGNAL CRS, ROLL CHANNEL INOPERABLE. TROUBL ESHOOTING REVEALED BAD SERVO. TEAR DOWN SHOWED CLUTCHES CROSS-WIRES; THEREFORE, SERVO RAN THE OPPOSITE DIRECTION IT WAS SUPPOSED TO. 1 H 7 2 3T A2PC 2000012200396 20000122 00396 CE 2000 1 22 2000ZZZX212 1 20000103 G 7830 L2020001A LUG CESSNA 500 550 2076604 CE THRUST REVERSER BROKEN B R2JR O OTHER O OTHER NR NOT REPORTED 1 EA 21 24E 2927 5500651 ON PRE-FLIGHT, CREW FOUND LEFT LOWER THRUST REVERSER DOOR HANGING DOWN. MAINTENANCE FOUND LUGS BROKEN ON BLOCKER DOOR ' BIRDCAGE' ASSEMBLY. FAILURE DUE TO IMPROPER BOLT ANTI-ROTATION DEVICE INSTALLATION PREVIOUSLY C/W. BLOCKER DOOR POSSIB LY WOULD HAVE LEFT AIRCRAFT ON NEXT FLIGHT. THRUST REVERSER ASSY CHANGED. 1 L 7 2 4F A22CE 2000012200397 20000122 00397 WP 2000 1 22 2000ZZZX213 2 20000103 G 7250 30720141 TURBINE BLADE 30720152 AMD FALC10 FALCON10 2730101 EU GARRTT TFE731 TFE7312 01518 WP ENGINE FAILED B IY2R O OTHER O OTHER NR NOT REPORTED 1 SW 15 CGRIS 10452 LOT159 002 P73114 ONE EACH, THIRD STAGE LOW PRESSURE TURBINE BLADE FAILED DUE TO STRESS RUPTURE. AIRCRAFT LANDED SAFELY. POSSIBLE CAUSE WAS THE OPERATION OF BLADE IN EXCESS OF RECOMMENDED HOURS AS SET IN ALLIED SB 72-3494. RECOMMEND ENGINE MFG INCLUDE TUR BINE BLADES IN SB 72-300, 'SERVICE LIFE LIMITED OF CRITICAL LIFE LIMITED COMPONENTS' AS THIS BULLETIN IS THE ONLY MANDAT ORY SB LISTED IN ENGINE TYPE CERTIFICATE DATA SHEET. 2 L 7 2 4F 4 F A33EU E6WE 2000012900233 20000129 00233 2000 1 29 2000ZZZX219 1 20000106 G 3242 7010FS9545708 SEAL 50105201 BRAKE LEAKING B XC4R K NONE K FLUID LOSS IN INSP/MAINT 1 SO 19 1704 APR981278 BRAKE ASSEMBLY P/N 5010520-1 FAILED PREMATURELY. THREE EACH PISTONS LEAKING FROM INSULATOR AREA. PISTONS INTERNALLY FI LLED WITH FLUID. EVIDENCE OF T-SEAL FAILURE. THIS IS A CONTINUAL DISCREPANCY. NOTE: OEM PARTS INSTALLED IN BRAKE ASS EMBLY AND THE MOST RECENT BRAKE CONFIGURATION P/N 5010520-1. 2000012900235 20000129 00235 GL 2000 1 29 2000ZZZX221 3 20000104 G 6110 B36634 COUNTERWEIGHT WSK M18A M18A EU HARTZL HCB3T HCB3TN5 GL PROPELLER CRACKED B S M3PR K NONE O OTHER IN INSP/MAINT 1 SW 11 2296Y 2000 1201827 BVA6450 FOUND DURING ROUTINE INSPECTION, CRACKED COUNTERWEIGHT. 1 L 7 1 3O NC A47EU 6 C P15EA 2000012900237 20000129 00237 GL 2000 1 29 2000ZZZX223 3 20000104 G 6110 B36634 COUNTERWEIGHT WSK M18 M18DROMADER 9810102 EU HARTZL HCB3T HCB3TN5 GL PROPELLER CRACKED B S M3PR K NONE O OTHER IN INSP/MAINT 1 SW 11 5168J 1345 1200719 BVA6452 FOUND DURING MAINTENANCE INSPECTION, CRACKED COUNTERWEIGHT. 1 L 7 1 3O A47EU 6 C P15EA 2000012900244 20000129 00244 CE 2000 1 29 2000ZZZX230 1 20000125 G 2434 649304 ALTERNATOR BEECH 36 A36 1151604 CE ENGINE FAILED B W45R O OTHER H B ELECT. POWER LOSS-50 PC SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 WP 07 4486X 10 E3286 ELECTRICAL FAILURE DUE TO INTERNAL ALTERNATOR FAILURE WITH STRONG SMELL OF ELECTRICAL. 1 L 7 1 3O 3A15 2000012900250 20000129 00250 2000 1 29 2000ZZZX236 1 20000111 G 3240 7010FS9545708 SEAL 50105201 BRAKE LEAKING B XC4R K NONE K FLUID LOSS IN INSP/MAINT 1 SO 19 1030 JUN981391 BRAKE ASSEMBLY, P/N 5010520-1, FAILED PREMATURELY. ONE EACH PISTON LEAKING FROM INSULATOR AREA. PISTON INTERNALLY FILL ED WITH FLUID. EVIDENCE OF T-SEAL FAILURE. THIS IS A CONTINUAL DISCREPANCY. NOTE: OEM PARTS INSTALLED IN BRAKE ASSEM BLY AND THE MOST RECENT BRAKE CONFIGURATION, P/N 5010520-1. 2000012900251 20000129 00251 2000 1 29 2000ZZZX237 1 20000104 G 3240 7010FS9545708 SEAL 50105201 BRAKE LEAKING B XC4R K NONE K FLUID LOSS IN INSP/MAINT 1 SO 19 1701 AUG971057 BRAKE ASSEMBLY, P/N 5020520-1, FAILED PREMATURELY, FIVE EACH PISTONS LEAKING FROM INSULATOR AREA. PISTONS INTERNALLY F ILLED WITH FLUID. EVIDENCE OF T-SEAL FAILURE. SUBMITTER STATED THIS IS A CONTINUAL DISCREPANCY. NOTE: OEM PARTS INST ALLED IN BRAKE ASSEMBLY AND THE MOST RECENT BRAKE CONFIGURATION, P/N 5010520-1. 2000012900252 20000129 00252 2000 1 29 2000ZZZX238 1 20000108 G 3240 7010FS9545708 SEAL 50105201 BRAKE LEAKING B XC4R K NONE K FLUID LOSS IN INSP/MAINT 1 SO 19 2174 JAN981176 BRAKE ASSEMBLY, P/N 5010520-1 FAILED PREMATURELY. ONE EACH PISTON LEAKING FROM INSULATOR AREA. EVIDENCE OF T-SEAL FAIL URE. SUBMITTER STATED THIS IS A CONTINUAL DISCREPANCY. NOTE: OEM PARTS INSTALLED IN BRAKE ASSEMBLY AND THE MOST RECEN T BRAKE CONFIGURATION, P/N 5010520-1. 2000012900253 20000129 00253 2000 1 29 2000ZZZX239 1 20000110 G 3240 7010FS9545708 SEAL 50105201 BRAKE LEAKING B XC4R K NONE K FLUID LOSS IN INSP/MAINT 1 SO 19 1652 APR981293 BRAKE ASSEMBLY, P/N 5010520-1, FAILED PREMATURELY. TWO EACH PISTONS LEAKING FROM INSULATOR AREA. PISTONS INTERNALLY FI LLED WITH FLUID. EVIDENCE OF T-SEAL FAILURE. SUBMITTER STATED THIS IS A CONTINUAL DISCREPANCY. FACTORY NEW BRAKE ASSE MBLY. 2000012900254 20000129 00254 2000 1 29 2000ZZZX240 1 20000107 G 3240 7010FS9545708 SEAL 50105201 BRAKE LEAKING B XC4R K NONE O OTHER IN INSP/MAINT 1 SO 19 1953 JUN971000 BRAKE ASSEMBLY, P/N 5010520-1, FAILED PREMATURELY. THREE EACH PISTONS LEAKING FROM INSULATOR AREA. PISTONS INTERNALLY FILLED WITH FLUID. EVIDENCE OF T-SEAL FAILURE. SUBMITTER STATED THIS IS A CONTINUAL DISCREPANCY. NOTE: OEM PARTS INS TALLED IN BRAKE ASSEMBLY AND THE MOST RECENT BRAKE CONFIGURATION, P/N 5010520-1. 2000012900260 20000129 00260 SW 2000 1 29 2000ZZZX246 1 20000107 G 6420 406312103101 PITCH LINK BELL 407 407 SW TAIL ROTOR WORN B UNFR K NONE O OTHER IN INSP/MAINT 1 SW 19 751 NHF03257 BEARINGS WORN BEYOND LIMITS. 1 G 7 1 3U O H2SW 2000012900261 20000129 00261 SW 2000 1 29 2000ZZZX247 1 20000107 G 6420 406312103101 PITCH LINK BELL 407 407 SW TAIL ROTOR WORN B UNFR K NONE O OTHER IN INSP/MAINT 1 SW 19 751 NHF03235 BEARINGS WORN BEYOND LIMITS. 1 G 7 1 3U O H2SW 2000020500923 20000205 00923 CE 2000 2 5 2000ZZZX258 1 20000202 G 5320 CM35753 SEAL CESSNA 500 560CESSNA 2076750 CE CABIN DAMAGED B JSNR K NONE O OTHER IN INSP/MAINT 1 NM 09 208PC 600 5605005 DURING A SCHEDULED INSPECTION, THE TWO AFT MOISTURE DRAINS/SEALS, P/N CM3575-3, WERE FOUND DAMAGED AND TORN AND NOT DOIN G A PROPER JOB DURING PRESSURIZATION. FIRST TIME THE DRAIN SEALS HAD BEEN INSPECTED. SEALS AND RETAINERS WERE REPLACED . 2 L 7 2 4F RT A22CE 2000020500924 20000205 00924 CE 2000 2 5 2000ZZZX259 1 20000202 G 2621 661420027 TUBE CESSNA 500 560CESSNA 2076750 CE FIRE EXTINGUISH LOOSE B P JSNR K NONE O OTHER IN INSP/MAINT 1 NM 09 207PC 573 5605008 DURING SCHEDULED INSPECTION, B-NUT ON P/N 6614200-27 TUBE ASSY WAS BACKED OFF WITH ONLY ONE THREAD ENGAGED. THIS IS THE FIRE EXTINGUISING TUBE FOR THE RIGHT ENGINE. THIS IS FIRST INSPECTION SINCE AIRCRAFT LEFT FACTORY. B-NUT RETORQUED. 2 L 7 2 4F RT A22CE 2000020500930 20000205 00930 EA 2000 2 5 2000ZZZX265 2 20000114 G 8530 SL36000 CYLINDER LYC O360 O360A4K 41514 EA ENGINE MISMANUFACTURED H K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 99 PORT DOES NOT ALIGN WITH EXHAUST GASKET. ON RECEIPT OF CYLINDERS, THEY ARE CHECKED FOR CONFORMITY. ONE OF THE CHECKS I S PLACING A GASKET ON THE EXHAUST STUDS TO CHECK FOR CONCENTRICITY WITH THE PORT. ANOTHER CHECK IS TO SEE IF THE CYLINDE R HEAD TEMPERATURE DRILLING IS CENTERED IN ITS BOSS. IF THE DRILLING IS OFF, THEN THE EXHAUST PORT WILL BE ALSO. THIS HAS BEEN LEARNED THROUGH TRIAL AND ERROR. IT APPEARS THAT SUPERIOR IS USING A SLIGHTLY LARGER EXHAUST PORT DIMENSION TH AN LYCOMING WHICH GIVES LESS TOELRANCE TO GASKET PLACEMENT. 3 O E286 2000020500943 20000205 00943 CE 2000 2 5 2000ZZZX274 1 20000103 G 5320 991503553 STIFFENER CESSNA 500 560CESSNA 2076750 CE BS 440 DAMAGED B JSNR K NONE O OTHER IN INSP/MAINT 1 NM 09 207PC 573 5605008 DURING A SCHEDULED INSPECTION, NOTED THAT P/N 9915035-53, EXTRUDED STIFFENER, HAD A RIVET CIRCLED IN RED FROM THE MANUFA CTURER. THE RIVET WAS NOT BUCKED. THE HOLE WAS EGGSHAPED WHEN RIVET WAS REMOVED. AN OVERSIZED RIVET WAS USED TO 'COMP LETE' THE JOB. 2 L 7 2 4F RT A22CE 2000020500944 20000205 00944 2000 2 5 2000ZZZX275 4 20000103 G 2562 4523050 ELT TRAY ARTEX 1104 CESSNA 500 560CESSNA 2076750 CE TAIL MISMANUFACTURED B P JSNR K NONE O OTHER IN INSP/MAINT 1 NM 09 207PC 573 5605008 DURING SCHEDULED MAINTENANCE INSPECTION FOR FUNCTIONAL CHECK OF ARTEX ELT 110-4, SEVERAL DISCREPANCIES WERE NOTED. AIRF RAME MANUFACTURER DID NOT PROVIDE ANY CHAFE PROTECTION FOR WIRES AND ANTENNA CABLE COMING THROUGH HOLE IN UPPER FUSELAGE SKIN IN FRONT OF THE ELT TRANSMITTER. THE WIRING WAS SHOWING SIGNS OF CHAFING. THE ELT MOUNTING TRAY ASSY, P/N 452-30 50, RETAINING CAP HAD ONLY ONE OF TWO SCREWS ENGAGED. IT WAS IMPOSSIBLE TO FASTEN THE SECOND SCREW. ON EXAMINATION, TH E INNER TAG OF THE SOUTHCO SCREW CLIP WOULD NOT ENGAGE THE HOLE IN THE MOUNTING TRAY DUE TO THE HOLE CENTER DRILLED TOO LOW ON THE TRAY FOR THE SCREW CLIP. 2 L 7 2 4F RT A22CE 2000021200252 20000212 00252 WP 2000 2 12 2000ZZZX277 1 20000207 G 5311 FRAME DOUG DC9 DC932F 3022067 WP BS 695 CORRODED B ERKR K NONE O OTHER IN INSP/MAINT 1 WP 07 935F 47220 MAIN CARGO COMPARTMENT STA 695 AT CENTER LINE LONGITUDINAL FRAME HAS AN AREA WITH SEVERE INTERGRANULAR CORROSION. REPAI RED BY FABRICATING AND INSTALLING BRACKETS AND INSTALLING A REPAIR DOUBLER. DER APPROVED ON FAA FORM 8110-3 DATED 99-12 -15 ECRA 935-53-055-2. 2 L 7 2 4F A6WE 2000021200253 20000212 00253 WP 2000 2 12 2000ZZZX278 1 20000207 G 5330 SKIN DOUG DC9 DC932F 3022067 WP BS 996-1019 DENTED B ERKR K NONE O OTHER IN INSP/MAINT 1 WP 07 935F 47220 TWO LARGE DENTS IN SKIN AT STA 996 - STA 1019, L3-L5, RIGHT. REPLACED INTERCOSTAL WEBS AND BY SHIMMING THE SMALLER GAP DER APPROVED ON FAA FORM 8110-3 DATED 99-12-02. 2 L 7 2 4F A6WE 2000021200254 20000212 00254 WP 2000 2 12 2000ZZZX279 1 20000207 G 5520 FASTENER DOUG DC9 DC932F 3022067 WP ELEVATOR DAMAGED B ERKR K NONE O OTHER IN INSP/MAINT 1 WP 07 935F 47220 FASTENER HEAD COMING OFF/BENDING BACK, LOWER SIDE OF RIGHT ELEVATOR 23.50 INCHES INBOARD OF OUTBOARD TIP. REPAIRED PER SRM 53-03, FIG 14. DER APPROVED ON FORM 8110-3 DATED 99-11-18. ECRA 935-55-047-2. 2 L 7 2 4F A6WE 2000021200255 20000212 00255 WP 2000 2 12 2000ZZZX280 1 20000207 G 5532 SKIN DOUG DC9 DC932F 3022067 WP VERTICAL STAB DAMAGED B ERKR K NONE O OTHER IN INSP/MAINT 1 WP 07 935F 47220 SCREW HOLE COUNTERSUNK SURFACE AREA DRILLED THROUGH NUMEROUS TIMES ON UPPER LEFT SIDE OF VERTICAL STABILIZER LEADING EDG E PANEL. REPAIRED WITH REPAIR BUSHINGS. DER APPROVED ON FORM 8110-3 DATED 9-11-23 ECRA 935-55-050-2. 2 L 7 2 4F A6WE 2000021200256 20000212 00256 WP 2000 2 12 2000ZZZX281 1 20000207 G 5330 SKIN DOUG DC9 DC932F 3022067 WP BS 47 AND 53 DENTED B ERKR K NONE O OTHER IN INSP/MAINT 1 WP 07 935F 47220 DENT IN SKIN PLATING RIGHT SIDE OF FUSELAGE NOSE SECTION AT BS 47 AND BS 53. REPAIRED BY FABRICATING 2 EACH FRAMES PER DRAWING AND INSTALLING FILLER AND FINGER AND INTERNAL DOUBLER DER APPROVED ON FAA FORM 8110-3 DATED 99-12-07 ECRA 935-53 -045-2. 2 L 7 2 4F A6WE 2000021200257 20000212 00257 WP 2000 2 12 2000ZZZX282 1 20000207 G 5330 SKIN DOUG DC9 DC932F 3022067 WP BS 133.425 MISREPAIRED B ERKR K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 07 935F 47220 PREVIOUS FUSELAGE SKIN PANEL REPAIR AT FS 133.425 NOT PER SRM 53-04, FIG 12B, SHEET 2. REPAIR ASLO HAS NUMEROUS GOUGES IN REPAIR. REPAIRED PER SRM 53-04 FIG 12B DER APPROVED ON FORM 8110-3 DATED 99-11-19, ECRA 935-53-048-2. 2 L 7 2 4F A6WE 2000021200258 20000212 00258 WP 2000 2 12 2000ZZZX283 1 20000207 G 5330 SKIN DOUG DC9 DC932F 3022067 WP FUSELAGE MISREPAIRED B ERKR K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 07 935F 47220 FORWARD LOWER CARGO DOOR FORWARD LOWER CORNERS SKIN REPAIR NOT TO DRAWING. SRO9530117 PER EO 53-DC9-905-98 REV A. REPA IRED BY EXPANDING AND INSTALLING FILLER, DOUBLER, AND TRIPLER. DER APPROVED ON FAA FORM 8110-3 DATED 99-11-29 AND FAA L ETTER DATED DEC 12, 1999, ECRA 935-53-046-2. 2 L 7 2 4F A6WE 2000021200259 20000212 00259 WP 2000 2 12 2000ZZZX284 1 20000207 G 5711 SPAR DOUG DC9 DC933F 302207A WP WS 267 CORRODED B ERKR K NONE O OTHER IN INSP/MAINT 1 WP 07 941F 47193 RIGHT WING REAR SPAR VERTICAL LEG AT STA 267.0 HAS HEAVY CORROSION. REPAIRED BY TRIMMING UPPER CAP BETWEEN XRS 180.1 AN D XRS 319.5. NEW SECTION SPLICED IN PER SB 57-179 AND ECRA 941-57-015-2. 2 L 7 2 4F A6WE 2000021200260 20000212 00260 WP 2000 2 12 2000ZZZX285 1 20000207 G 5320 WEB DOUG DC9 DC932F 3022067 WP BS 370 AND 427 CORRODED B ERKR K NONE O OTHER IN INSP/MAINT 1 WP 07 935F 47220 FORWARD PIT, RIGHT FLOOR WEB BETWEEN BS 370 AND BS 427 ABOVE PIT DOOR HAS SURFACE CORROSION AT FLOOR BEAM. REPAIRED BY INSTALLING NEW CUSP WEB AT STA 313 TO STA STA 389 AND STA 389 TO STA 503. DER APPROVED ON FAA FORM 8110-3 DATED 99-11-1 9, ECRA 935-53-C43-2. 2 L 7 2 4F A6WE 2000021200261 20000212 00261 WP 2000 2 12 2000ZZZX286 1 20000207 G 5230 PAN DOUG DC9 DC933F 302207A WP CARGO DOOR CRACKED B ERKR K NONE O OTHER IN INSP/MAINT 1 WP 07 941F 47193 CRACK DAMAGE ON THE LOWER AFT CARGO DOOR INNER AND OUTER PAN. REPAIRED LOWER AFT CARGO DOOR INNER AND OUTER PAN PER EIA ECRA 941-52-102-2. 2 L 7 2 4F A6WE 2000021200262 20000212 00262 WP 2000 2 12 2000ZZZX287 1 20000207 G 5330 SKIN DOUG DC9 DC933F 302207A WP BS 58.75 DAMAGED B ERKR K NONE O OTHER IN INSP/MAINT 1 WP 07 941F 47193 APPROVAL FOR AN EXISTING REPAIR ON THE FUSELAGE SKIN AT STA 58.750 L19L. REPAIR REMOVED A CRACK COMMON TO THE SKIN AT T HE STA 58.750 FRAME. REPAIRED FUSELAGE SKIN EXTERNAL DOUBLER AT STA 58.750 L18L TO L19L PER EIA ECRA 941-53-005-2. 2 L 7 2 4F A6WE 2000021200263 20000212 00263 WP 2000 2 12 2000ZZZX288 1 20000207 G 5330 SKIN DOUG DC9 DC933F 302207A WP BS 320 DENTED B ERKR K NONE O OTHER IN INSP/MAINT 1 WP 07 941F 47193 DENT DAMAGE FOUND BELOW THE MAIN DECK CARGO DOOR, FORWARD AND ABOVE THE PRESSURE RELIEF VALVES. REPAIRED FUSELAGE SKIN DENT AT STA 320 BETWEEN L18L TO L19L PER EIA ECRA 941-53-014-2 REV A. 2 L 7 2 4F A6WE 2000021200264 20000212 00264 WP 2000 2 12 2000ZZZX289 1 20000207 G 5320 WEB DOUG DC9 DC933F 302207A WP BS 452-455 PUNCTURED B ERKR K NONE O OTHER IN INSP/MAINT 1 WP 07 941F 47193 PUNCTURE DAMAGE COMMON TO THE CUSP MEMBRANE BETWEEN STA 452 TO ST 455. REPAIRED RT FUSELAGE CUSP MEMBRANE/WEB PUNTURE B ETWEEN STA 452 TO STA 456 PER EIA ECRA 541-53-012-2. 2 L 7 2 4F A6WE 2000021200265 20000212 00265 WP 2000 2 12 2000ZZZX290 1 20000207 G 5230 FITTING DOUG DC9 DC933F 302207A WP CARGO DOOR DAMAGED B ERKR K NONE O OTHER IN INSP/MAINT 1 WP 07 941F 47193 ELONGATED HOLE IN MAIN DECK CARGO DOOR TORQUE TUBE FITTING. REPAIRED UPPER CARGO DOOR TORQUE TUBE AT STA 380 BETWEEN L4 L TO L5L PER EIA ECRA 941-53-072-2. 2 L 7 2 4F A6WE 2000021200266 20000212 00266 WP 2000 2 12 2000ZZZX291 1 20000207 G 5244 DOOR DOUG DC9 DC933F 302207A WP RT WING DAMAGED B ERKR K NONE O OTHER IN INSP/MAINT 1 WP 07 941F 47193 DAMAGE ON THE RIGHT WING NR 4 LEADING EDGE SLAT DOOR AT WS X0S 240.081. REPAIRED DAMAGE ON THE RT WING NR 4 L/E SLAT DO OR AT WS X05 240.081 PER DIA ECRA 941-57-089-2. 2 L 7 2 4F A6WE 2000021200267 20000212 00267 WP 2000 2 12 2000ZZZX292 1 20000207 G 5730 SKIN DOUG DC9 DC933F 302207A WP WS 575.5 DAMAGED B ERKR K NONE O OTHER IN INSP/MAINT 1 WP 07 941F 47193 REPAIRED THE PREVIOUS REPAIR ON THE LT WING LEADING EDGE AT XFS 575.5. REPAIRED PREVIOUS FLUSH REPAIR ON THE LT WING LE ADING EDGE AT XFS 575.5 PER EIA ECRA 941-57-009-2 REV A. 2 L 7 2 4F A6WE 2000021200268 20000212 00268 WP 2000 2 12 2000ZZZX293 1 20000207 G 5220 STRUCTURE DOUG DC9 DC933F 302207A WP EMERGENCY DOOR DAMAGED B ERKR K NONE O OTHER IN INSP/MAINT 1 WP 07 941F 47193 PREVIOUSLY PLUGGED HOLE WITH SHORT EDGE DISTANCE AND GOUGE ON THE RT FORWARD EMERGENCY EXIT DOOR. REPAIRED PREVIOUSLY P LUGGED HOLE WITH SHORT EDGE DISTANCE AND GOUGE ON THE RT FORWARD EMERGENCY EXIT DOOR PER EIA ECRA 941-52-058-2. 2 L 7 2 4F A6WE 2000021200269 20000212 00269 WP 2000 2 12 2000ZZZX294 1 20000207 G 5320 RIVETS DOUG DC9 DC933F 302207A WP BS 256-945 MISINSTALLED B ERKR K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 07 941F 47193 OVERLAPPING RIVETS ON THE INTERCOSTALS AT VARIOUS LOCATIONS. REPAIRED OVERLAPPING RIVETS ON THE INTERCOSTALS AT LT STA' S 617, 465, 945, 927, 908, 889, 851, 832, 813, 794 775, 756, 737, 718, 699, 639, 560, 541, AND 256 L6L. RT STA'S 639, 6 17, 313, 699, 484, 465, 256, 541, 560, 237, 408, 756, 775, 794, 813, 832, 851, 927, AND 945 L6R PER EIA ECRA 941-53-018- 2. 2 L 7 2 4F A6WE 2000021200270 20000212 00270 WP 2000 2 12 2000ZZZX295 1 20000207 G 5311 FRAME DOUG DC9 DC933F 302207A WP BS 908 MISDRILLED B ERKR K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 07 941F 47193 MISDRILLED HOLE AT RT FRAME STA 908.00 L6R. REPAIRED MISDRILLED HOLE AT RT FRAME STA 908 L6R PER EIA ECRA 941-53-039-2. 2 L 7 2 4F A6WE 2000021200271 20000212 00271 WP 2000 2 12 2000ZZZX296 1 20000207 G 5311 FRAME DOUG DC9 DC933F 302207A WP BS 332 MISDRILLED B ERKR K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 07 941F 47193 MISDRILLED HOLE AT RIGHT FRAME STA 332.00 L6R. REPAIRED MISDRILLED HOLE AT RT FRAME STA 332 L6R PER EIA ECRA 941-53-064 -2. 2 L 7 2 4F A6WE 2000021200272 20000212 00272 WP 2000 2 12 2000ZZZX297 1 20000208 G 5311 FRAME DOUG DC9 DC933F 302207A WP BS 718 MISDRILLED B ERKR K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 07 941F 47193 MISDRILLED HOLE AT RIGHT FRAME STA 718, L6R. REPAIRED MISDRILLED HOLE AT RIGHT FRAME STA 718, L6R PER EIA ECRA 941-53-0 23-2. 2 L 7 2 4F A6WE 2000021200273 20000212 00273 WP 2000 2 12 2000ZZZX298 1 20000208 G 5347 CARGO RACK DOUG DC9 DC933F 302207A WP BS 522 PUNCTURED B ERKR K NONE O OTHER IN INSP/MAINT 1 WP 07 941F 47193 PUNCTURE IN THE DUAL CARGO TRACK AT LEFT STA 522.00, LBL 24.00. REPAIRED A PUNCTURE IN THE DUAL CARGO TRACK AT STA 522, LBL 24 PER EIA ECRA 941-53-048-2. 2 L 7 2 4F A6WE 2000021200274 20000212 00274 WP 2000 2 12 2000ZZZX299 1 20000208 G 5320 WEB DOUG DC9 DC933F 302207A WP BS 343.6 CRACKED B ERKR K NONE O OTHER IN INSP/MAINT 1 WP 07 941F 47193 CRACK IN THE FASTENER HOLE ON THE CUSP WEB AT RIGHT STA 343.60, RBL 42. REPAIRED FASTENER HOLE ON CUSP WEB AT RIGHT STA 343.60, RBL 42 PER ECRA 941-53-057-2. 2 L 7 2 4F A6WE 2000010800177 20000108 00177 2000 1 8 2000ZZZX30 4 20000104 G 3444 031002220008 SWITCH CESSNA 500 550 2076604 CE COCKPIT FAILED B CNQ6 O OTHER O OTHER NR NOT REPORTED 1 EA 25 814CB 5500824 BOTH TRANSPONDERS OPERATE SIMULTANEOUSLY. OPERATOR HAD SELECTED NR 1 TRANSPONDER AND PUT NR 1 IN STANDBY WITH 7700 CODE SELECTED. BOTH MODE A CODES SEEN BY RADAR. POSSIBLE CAUSE WAS TRANSPONDER SELECT SWITCH NOT FALLING IN UP POSITION. S ITUATION CAN BE MOST LIKELY TO OCCUR IF THERE IS NOT ENOUGH CLEARANCE BETWEEN SWITCH AND OVERLAY PANEL CAUSING BINDING O F SWITCH MOVEMENT. SWITCH SHOULD BE REPLACED WITH A 'BREAK BEFORE MAKE' TYPE SWITCH. ALSO, ENLARGE HOLE IS OVERLAY PAN EL IF REQUIRED. 1 L 7 2 4F A22CE 2000021200275 20000212 00275 WP 2000 2 12 2000ZZZX300 1 20000208 G 5311 DOOR FRAME DOUG DC9 DC933F 302207A WP FUSELAGE CRACKED B ERKR K NONE O OTHER IN INSP/MAINT 1 WP 07 941F 47193 A 0.5 INCH CRACK WAS FOUND IN THE RADIUS OF THE SERVICE DOOR FRAME. DURING REPAIR, A FASTENER WAS FOUND WITH A 0.15 INC H EDGE MARGIN MEASURED FROM THE CENTER OF THE FASTENER HOLE TO THE EDGE OF THE FITTING. REPAIRED FORWARD GALLEY SERVICE DOOR NR 2 HORIZONTAL BEAM FORWARD UPPER CORNER PER EIA ECRA 941-52-076-2. 2 L 7 2 4F A6WE 2000021200276 20000212 00276 WP 2000 2 12 2000ZZZX301 1 20000208 G 5312 BULKHEAD DOUG DC9 DC933F 302207A WP BS 996 CRACKED B ERKR K NONE O OTHER IN INSP/MAINT 1 WP 07 941F 47193 ELONGATED FASTENER HOLES, GOUGE AND CRACK DAMAGE ASSOCIATED WITH THE AFT PRESSURE BULKHEAD TEE CHORD SPLICE AT L6L TO L8 L. REQUIRED AFT PRESSURE BULKHEAD TEE CHORD AT STA 996 BETWEEN L6L TO L8L PER EIA ECRA 941-53-077-2 REV A. 2 L 7 2 4F A6WE 2000021200277 20000212 00277 WP 2000 2 12 2000ZZZX302 1 20000208 G 5311 FRAME DOUG DC9 DC933F 302207A WP BS 870 MISDRILLED B ERKR K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 07 941F 47193 MISDRILLED HOLE AT RT FRAME STA 870.00 L6R. REPAIRED MISDRILLED HOLE AT RIGHT FRAME STA 870 L6R PER EIA ECRA 941-53-01 9-2. 2 L 7 2 4F A6WE 2000021200278 20000212 00278 WP 2000 2 12 2000ZZZX303 1 20000208 G 5311 FRAME DOUG DC9 DC933F 302207A WP BS 870 MISDRILLED B ERKR K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 07 941F 47193 MISDRILLED HOLE AT LEFT FRAME STA 870.00 L6L. REPAIRED MISDRILLED HOLE AT LEFT FRAME STA 870, L6L PER EIA ECRA 941-53- 020-2. 2 L 7 2 4F A6WE 2000021200279 20000212 00279 WP 2000 2 12 2000ZZZX304 1 20000208 G 3210 FITTING DOUG DC9 DC933F 302207A WP LT AND RT MLG CORRODED B ERKR K NONE O OTHER IN INSP/MAINT 1 WP 07 941F 47193 CORROSION DAMAGE FOUND IN 5 BOLT HOLES COMMON TO THE LT AND RT MAIN LANDING GEAR FITTINGS. REPAIRED LT AND RT MAIN LAND ING GEAR FITTINGS PER EIA ECRA 941-57-065-2 REV A. 2 L 7 2 4F A6WE 2000021200280 20000212 00280 WP 2000 2 12 2000ZZZX305 1 20000208 G 5511 RIB DOUG DC9 DC933F 302207A WP HORIZ STABILIZER CRACKED B ERKR K NONE O OTHER IN INSP/MAINT 1 WP 07 941F 47193 DAMAGE TO THE XHS 86.00 RIB IN THE RT HORIZONTAL STABILIZER FORWARD UPPER END WHILE GAINING ACCESS TO AN UNCONFIRMED CRA CK. CRACK WAS LATER FOUND TO BE AN ANOMALIE ONLY. REPAIRED RT HORIZONTAL STABILIZER RIB DAMAGE AT XHS 86 PER EIA ECRA 941-55-013-2 REV A. 2 L 7 2 4F A6WE 2000021200281 20000212 00281 WP 2000 2 12 2000ZZZX306 1 20000208 G 5330 SKIN DOUG DC9 DC933F 302207A WP BS 927-936 MISREPAIRED B ERKR K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 07 941F 47193 NON-DOCUMENTED DOUBLERS AT FUSELAGE RIGHT STA 927 AND STA 936. REPAIRED RT FUSELAGE SKIN AT STA 927 AND STA 936, BETWEE N L14R AND L15R PER EIA ECRA 941-53-083-2 REV B. 2 L 7 2 4F A6WE 2000021200282 20000212 00282 WP 2000 2 12 2000ZZZX307 1 20000208 G 5511 STRINGER DOUG DC9 DC933F 302207A WP HORIZ STABILIZER MISREPAIRED B ERKR K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 07 941F 47193 TWO EXISTING UNAPPROVED REPAIR CHANNELS ON THE LT HORIZONTAL STABILIZER UPPER PANEL AT STR 6 AT XHS 25 AND XHS 37. REPA IRED LT HORIZONTAL STABILIZER UPPER PANEL STRINGER AT XHS 25 AND XHS 37, L6 PER EIA ECRA 941-55-059-2. 2 L 7 2 4F A6WE 2000021200283 20000212 00283 WP 2000 2 12 2000ZZZX308 1 20000208 G 5320 INTERCOSTAL DOUG DC9 DC933F 302207A WP FUSELAGE CORRODED B ERKR K NONE O OTHER IN INSP/MAINT 1 WP 07 941F 47193 FORWARD ENTRY DOOR LOWER SILL 9957838-3 INTERCOSTAL FOUND CORRODED AT THE NUTPLATE LOCATIONS. WHILE GAINING ACCESS THR OUGH THE UPPER CUSP ANGLE, THE LOWER CUSP ANGLE WAS DAMAGED. REPAIRED FORWARD ENTRY DOOR LOWER SILL UPPER AND LOWER CUS P ANGLES PER EIA ECRA 941-53-075-2. 2 L 7 2 4F A6WE 2000021200284 20000212 00284 WP 2000 2 12 2000ZZZX309 1 20000208 G 5320 WEB DOUG DC9 DC933F 302207A WP BS 579 CRACKED B ERKR K NONE O OTHER IN INSP/MAINT 1 WP 07 941F 47193 CRACK DAMAGE ON THE CUSP WEB AT LEFT AFT STA 579, LBL 54.00. REPAIRED LEFT AFT CUSP WEB AT STA 579, LBL 54, PER EIA ECR A 941-53-052-2 REV A. 2 L 7 2 4F A6WE 2000021200285 20000212 00285 WP 2000 2 12 2000ZZZX310 1 20000208 G 5530 FRAME DOUG DC9 DC933F 302207A WP VERTICAL STAB MISDRILLED B ERKR K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 07 941F 47193 DOUBLE-DRILLED HOLE TO THE VERTICAL STABILIZER FRAME AT STA YV 247.750, ZV 140.825. REPAIRED DOUBLE-DRILLED HOLE ON VER TICAL STABILIZER FRAME AT STA YV 247.750, ZV 140.825 PER EIA ECRA 941-52-053-2 REV A. 2 L 7 2 4F A6WE 2000021200286 20000212 00286 WP 2000 2 12 2000ZZZX311 1 20000208 G 3210 FITTING DOUG DC9 DC933F 302207A WP RT MLG DAMAGED B ERKR K NONE O OTHER IN INSP/MAINT 1 WP 07 941F 47193 THREE OVERSIZED HOLES IN THE RT MAIN LANDING GEAR FITTING. REPAIRED RIGHT MAIN LANDING GEAR FITTING OVERSIZED HOLES PER EIA ECRA 941-57-055-2. 2 L 7 2 4F A6WE 2000021200287 20000212 00287 WP 2000 2 12 2000ZZZX312 1 20000208 G 5311 FRAME DOUG DC9 DC933F 302207A WP BS 1037 CRACKED B ERKR K NONE O OTHER IN INSP/MAINT 1 WP 07 941F 47193 CRACK IN THE LEFT FRAME AT STA 1037. REPAIRED FUSELGE FRAME AT STA 1037 BETWEEN L12L TO L13L PER EIA ECRA 941-53-053-2. 2 L 7 2 4F A6WE 2000021200288 20000212 00288 WP 2000 2 12 2000ZZZX313 1 20000208 G 5330 SKIN DOUG DC9 DC933F 302207A WP BS 1810 CRACKED B ERKR K NONE O OTHER IN INSP/MAINT 1 WP 07 941F 47193 CRACKED AREA OF FUSELAGE SKIN NEAR STA 1810, L23L. REPAIRED FUSELAGE SKIN DOUBLER AT STA 1018, L23L PER EIA ECRA 941-53 -062-2 REV A. 2 L 7 2 4F A6WE 2000021200289 20000212 00289 WP 2000 2 12 2000ZZZX314 1 20000208 G 5320 INTERCOSTAL DOUG DC9 DC933F 302207A WP BS 180 GOUGED B ERKR K NONE O OTHER IN INSP/MAINT 1 WP 07 941F 47193 GOUGE IN INTERCOSTAL AT STA 180.00, RBL 21. REPAIRED INTERCOSTAL GOUGE AT STA 180, RBL 21 PER EIA ECRA 941-53-079-2. 2 L 7 2 4F A6WE 2000021200290 20000212 00290 WP 2000 2 12 2000ZZZX315 1 20000208 G 5330 SKIN DOUG DC9 DC933F 302207A WP BS 160-200 GOUGED B ERKR K NONE O OTHER IN INSP/MAINT 1 WP 07 941F 47193 GOUGES ON THE FUSELAGE SKIN BELOW THE AIRSTAIR DOOR. REPAIRED LEFT FUSELAGE EXTERNAL SKIN AT STA 160 TO STA 200 UNDER T HE AIRSTAIR DOOR PER EIA ECRA 941-53-078-2. 2 L 7 2 4F A6WE 2000021200291 20000212 00291 WP 2000 2 12 2000ZZZX316 1 20000208 G 5320 WEB DOUG DC9 DC933F 302207A WP BS 427 DENTED B ERKR K NONE O OTHER IN INSP/MAINT 1 WP 07 941F 47193 TRIMMED OUT DENT ON FORWARD CARGO COMPARTMENT WEB AT STA 427.00 BETWEEN L24R TO L26R. REPAIRED FORWARD CARGO COMPARTMEN T WEB AT STA 427 BETWEEN L24R TO L26R PER EIA ECRA 941-53-080-2. 2 L 7 2 4F A6WE 2000021200292 20000212 00292 WP 2000 2 12 2000ZZZX317 1 20000208 G 5244 DOOR DOUG DC9 DC933F 302207A WP WS 294 DAMAGED B ERKR K NONE O OTHER IN INSP/MAINT 1 WP 07 941F 47193 EXISTING EXTRA JOINT IN THE RIGHT WING BUTTE DOOR AT XRS 294. REPAIRED RT WING BUTTE DOOR HINGE AT XRS 294 PER EIA ECRA 941-57-082-2. 2 L 7 2 4F A6WE 2000021200293 20000212 00293 WP 2000 2 12 2000ZZZX318 1 20000208 G 5320 CHORD DOUG DC9 DC933F 302207A WP BS 319 GOUGED B ERKR K NONE O OTHER IN INSP/MAINT 1 WP 07 941F 47193 TEE CHORD AT STA 319, L19L HAS A GOUGE AND DENT DAMAGE. REPAIRED GOUGED TEE CHORD AT STA 319, L19L PER EIA ECRA 941-53- 093-2. 2 L 7 2 4F A6WE 2000021200294 20000212 00294 WP 2000 2 12 2000ZZZX319 1 20000208 G 5320 WEB DOUG DC9 DC933F 302207A WP BS 313 AND 323 DAMAGED B ERKR K NONE O OTHER IN INSP/MAINT 1 WP 07 941F 47193 DAMAGE ON THE CUSP WEB BETWEEN RT STA 313 AND STA 323 AT RBL 54. REPAIRED DAMAGED CUSP WEB BETWEEN RT STA 313 TO STA 32 3 AT RBL 54 PER EIA ECRA 941-53-087-2. 2 L 7 2 4F A6WE 2000021200295 20000212 00295 WP 2000 2 12 2000ZZZX320 1 20000208 G 5330 SKIN DOUG DC9 DC933F 302207A WP BS 996 MISREPAIRED B ERKR K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 07 941F 47193 CLASS 2 SKIN REPAIR AT RT STA 996, L28R AND L29R. REPAIRED EXISTING CLASS 2 SKIN REPAIR AT RIGHT STA 996, L28R AND L29R TO A CLASS 1 REPAIR PER EIA ECRA 941-53-051-2. 2 L 7 2 4F A6WE 2000021200296 20000212 00296 WP 2000 2 12 2000ZZZX321 1 20000208 G 5330 SKIN DOUG DC9 DC933F 302207A WP BS 168.750 MISREPAIRED B ERKR K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 07 941F 47193 FUSELAGE SKIN REPAIR ON RIGHT OF FUSELAGE AT FS 168.750 OVERLAPPING SKIN PANEL BUTT JOINT ON LONGERON 26 NEEDS TO BE CHA NGED FROM A CLASS 2 REPAIR TO A CLASS 1 REPAIR. REPAIRED PER ECRA 941-53-081-2. 2 L 7 2 4F A6WE 2000021200297 20000212 00297 WP 2000 2 12 2000ZZZX322 1 20000208 G 5330 SKIN DOUG DC9 DC933F 302207A WP BS 229-588 MISDRILLED B ERKR K NONE O OTHER IN INSP/MAINT 1 WP 07 941F 47193 RIGHT SKIN AT STA 229 - STA 588 HAS A LOT OF DAMAGE AND INTERNAL DOUBLER HAS A HOLE FROM PREVIOUS REPAIR. REMOVED AND R EPLACED SKINS AND INTERNAL DOUBLER PER ECRA 94-53-0003-3. 2 L 7 2 4F A6WE 2000021200298 20000212 00298 WP 2000 2 12 2000ZZZX323 1 20000208 G 5320 SPLICE DOUG DC9 DC933F 302207A WP BS 718 CORRODED B ERKR K NONE O OTHER IN INSP/MAINT 1 WP 07 941F 47193 FUSELAGE STA 715 RIGHT BUTT LINE 58. CORROSION ON WEB. CORROSION ON FORWARD, LOWER SURFACE OF FRAME 718, SPLICE UNDER CABIN FLOOR. REPLACED FRAME STA 781, REPLACED WEB PER SB 53-131 REV 4 AND SRM 53-2, 51-30-5. 2 L 7 2 4F A6WE 2000021200299 20000212 00299 WP 2000 2 12 2000ZZZX324 1 20000208 G 5311 FRAME DOUG DC9 DC933F 302207A WP BS 699 CRACKED B ERKR K NONE O OTHER IN INSP/MAINT 1 WP 07 941F 47193 FUSELAGE STATION 699 RIGHT AFT SIDE OF FRAME IN MID-POCKET. FRAME HAS THREE CRACKS LOCATED BENEATH FLOOR. REPLACED FRA ME PER SB 53-131 REV 4. 2 L 7 2 4F A6WE 2000021200300 20000212 00300 WP 2000 2 12 2000ZZZX325 1 20000208 G 5522 SKIN DOUG DC9 DC933F 302207A WP ELEVATOR DAMAGED B ERKR K NONE O OTHER IN INSP/MAINT 1 WP 07 941F 47193 RIGHT ELEVATOR LOWER SURFACE OUTBOARD END HAS A HOLE. REPLACED SKIN PER DOUGLAS DRAWING ECRA 942-55-083-2 REV A AND DC9 SRM. 2 L 7 2 4F A6WE 2000021200301 20000212 00301 WP 2000 2 12 2000ZZZX326 1 20000208 G 5311 FRAME DOUG DC9 DC933F 302207A WP BS 718 CRACKED B ERKR K NONE O OTHER IN INSP/MAINT 1 WP 07 941F 47193 FRAME 718 RIGHT CRACKED ON FORWARD SIDE OF INTERMEDIATE POCKET, LOWER AFT RADIUS FROM FASTENER HOLE TO FASTENER HOLE UND ER CABIN FLOOR. REPLACED FRAME 718 RIGHT SIDE PER SB 53-131 AND ECRA 941-53-067-2. 2 L 7 2 4F A6WE 2000021200302 20000212 00302 WP 2000 2 12 2000ZZZX327 1 20000208 G 5311 FRAME DOUG DC9 DC933F 302207A WP BS 185.0 GOUGED B ERKR K NONE O OTHER IN INSP/MAINT 1 WP 07 941F 47193 INSIDE L-2 DOOR STA 185.0 LBL 44.5, TEE CHORD HAS .50 INCH LONG DEEP GOUGE ON TOP SIDE. REPAIR PER ECRA 941-53-088-2. 2 L 7 2 4F A6WE 2000021200303 20000212 00303 WP 2000 2 12 2000ZZZX328 1 20000208 G 5330 SKIN DOUG DC9 DC933F 302207A WP BS 737 DAMAGED B ERKR K NONE O OTHER IN INSP/MAINT 1 WP 07 941F 47193 REMOVED EXISTING REPAIR DOUBLER AT STA 737 BETWEEN L17-L18 RT SIDE FOR INSPECTION AND MEASURING BLENDED AREA PER ENGINEE RING. REPAIRED PER ECRA 941-53-061-2. 2 L 7 2 4F A6WE 2000021200304 20000212 00304 WP 2000 2 12 2000ZZZX329 1 20000208 G 5320 DOOR JAMB DOUG DC9 DC933F 302207A WP FUSELAGE CRACKED B ERKR K NONE O OTHER IN INSP/MAINT 1 WP 07 941F 47193 CRACK FOUND ON AFT LOWER CORNER OF THE FORWARD SERVICE DOOR. DOOR JAMB CRACK COMING OUT OF AFT UPPER SCREW HOLE FOR SCU FF PLATE AND CORROSION UNDER SCUFF PLATE. REPAIRED PER ECRA 941-53-098-2 REV A. 2 L 7 2 4F A6WE 2000021200305 20000212 00305 WP 2000 2 12 2000ZZZX330 1 20000208 G 5230 SKIN DOUG DC9 DC933F 302207A WP CARGO DOOR GOUGED B ERKR K NONE O OTHER IN INSP/MAINT 1 WP 07 941F 47193 FORWARD PIT DOOR, DOOR EDGE, LOWER AFT, AND UPPER END FORWARD, HAS A GOUGE. INSTALLED REPAIR PER SRM 52-01 FIG 01 AND E CRA 941-52-091-2. 2 L 7 2 4F A6WE 2000021200306 20000212 00306 WP 2000 2 12 2000ZZZX331 1 20000208 G 5315 FLOORBEAM DOUG DC9 DC933F 302207A WP BS 917 CHAFED B ERKR K NONE O OTHER IN INSP/MAINT 1 WP 07 941F 47193 AFT CARGO PIT STA 917 BL ZERO FLOORBEAM CHAFED. REPAIRED PER ECRA NR 941-53-094-2. 2 L 7 2 4F A6WE 2000021900078 20000219 00078 SO 2000 2 19 2000ZZZX361 1 20000117 G 7603 554051 CONTROL CABLE 6932403 PIPER PA32 PA32R301 7103218 SO ENGINE BAY BENT G A K NONE O OTHER IN INSP/MAINT 1 GL 23 8024A 4687 32R83103008 NOSE GEAR FAILED TO EXTEND. FOUND THE ALTERNATE AIR CABLE (PIPER P/N 554051) NOT ROUTED CORRECTLY IN ENGINE COMPARTMENT AND TY WRAP BROKEN WHICH ALLOWED ALTERNATE AIR CABLE TO BECOME ENTANGLED TO THE NOSE GEAR LOWER DRAG LINK (PIPER P/N 38 040-02) AND BOLT (PIPER P/N 402938). RECOMMENDED SOLUTION THAT PIPER REVIEW MANUAL AND IPC CLARIFING ROUTING AND CLAMPI NG OF ALTERNATE AIR CABLE AND OWNERS THEN ARE PROVIDED WITH THAT, TO PREVENT RECURRENCE. 1 L 7 1 3O A3SO 2000021900079 20000219 00079 WP 2000 2 19 2000ZZZX362 1 20000210 G 5330 DOUBLER DOUG DC9 DC933F 302207A WP BS 376 TEMPORARY B ERKR K NONE O OTHER IN INSP/MAINT 1 WP 07 941F 47193 REMOVED THE EXISTING CLASS 2 REPAIR AND INSTALLED A CLASS 1 REPAIR AT LT STA 376.00 BETWEEN L22L AND L24L. REMOVED CLAS S 2 REPAIRS AND INSTALLED CLASS 1 REPAIRS FROM LT STA 376.00 TO STA 395.00 BETWEEN L22L TO L24L PER EIA ECRA 941-53-090- 2. 2 L 7 2 4F A6WE 2000021900080 20000219 00080 WP 2000 2 19 2000ZZZX363 1 20000110 G 5330 DOUBLER DOUG DC9 DC933F 302207A WP FUSELAGE TEMPORARY B ERKR K NONE O OTHER IN INSP/MAINT 1 WP 07 941F 47193 REPLACED A TEMPORARY REPAIR WITH A PERMANENT REPAIR. TEMPORARY REPAIR IS FOR DENT AND CRACK DAMAGE AT THE LOWER AFT COR NER OF THE MAIN DECK CARGO DOOR. REPAIRED MAIN DECK CARGO DOOR AFT LOWER CORNER DAMAGE PER EIA ECRA 941-52-046-2. 2 L 7 2 4F A6WE 2000021900083 20000219 00083 CE 2000 2 19 2000ZZZX366 1 20000121 G 3310 C6130010101 INVERTER CESSNA 310 T310R 2074246 CE COCKPIT FAILED C O OTHER B SMOKE/FUMES/ODORS/SPARKS AP APPROACH 1 SW 01 828P 243 9817 310R0681 DURING FINAL FOR ARTESIA, NM (ATS) PILOT REPORTED SMOKE IN COCKPIT. ON INSPECTION, FOUND ENGINE SWITCH AND PANEL LIGHTS CIRCUIT BREAKER TRIPPED. TROUBLESHOT SYSTEM AND FOUND 28VDC TO 115VAC INVERTER BURNED OUT AND SEALANT DRIPPING. INVER TER WAS REPLACED 8-25-98. AFTT: 1,982 HOURS. FOUND BREAK IN INSULATION ON WIRE NR L329K20 (28VDC IN) THAT WAS SHORTIN G TO GROUND AND CAUSED THE INVERTER FAILURE. REPAIRED WIRE AND REPLACED INVERTER PACK WITH NEW P/N C613001-0101. 1 L 7 2 3O 3A10 2000021900086 20000219 00086 EA 2000 2 19 2000ZZZX369 2 20000103 G 7314 02532310102 PUMP BEECH 90 C90 1152913 CE PWA PT6 PT6A21 52043 EA LT ENGINE DEFECTIVE C O OTHER O OTHER NR NOT REPORTED 1 CE 07 982FA LJ1000 PCE24449 SERIAL NUMBERS ARE THE UNITS THAT REPLACED THE DEFECTIVE UNITS. S/N 7848. SHAFT IN ENGINE FUEL CONTORL SHEARED CAUSING ENGINE TO SHUT DOWN. 1 L 7 2 3T 4 T 3A20 E4EA 2000021900087 20000219 00087 EA 2000 2 19 2000ZZZX370 2 20000103 G 7321 82447452 FCU BEECH 90 C90 1152913 CE PWA PT6 PT6A21 52043 EA LT ENGINE DEFECTIVE C O OTHER O OTHER NR NOT REPORTED 1 CE 07 982FA LJ1000 PCE24449 SERIAL NUMBERS ARE THE UNITS THAT REPLACED THE DEFECTIVE UNITS. S/N 72779. SHAFT IN ENGINE FUEL CONTROL SHEARED CAUSIN G ENGINE TO SHUT DOWN. 1 L 7 2 3T 4 T 3A20 E4EA 2000021900088 20000219 00088 CE 2000 2 19 2000ZZZX371 1 20000113 G 2810 BAFFLE BBAVIA 8 8KCAB 2110612 CE FUEL CELL LOOSE B A OG5R O OTHER O OTHER NR NOT REPORTED 1 GL 21 68ND 2564 66892 AIRCRAFT WAS WRITTEN UP FOR HAVING A ROLL TENDENCY. INVESTIGATION BY MAINTENANCE FOUND INTERNAL BAFFLING ON LEFT FUEL T ANK HAD COME LOOSE CAUSING TANK HAD COME LOOSE CAUSING TANK TO BUDGE INCREASING THE CAMBER ON THAT WING. FURTHER INSPEC TION OF RT TANK FOUND ONE INTERNAL BAFFLE COMPLETELY SEPARATED AND LOOSE IN THE TANK. BOTH TANKS ARE BEING REPLACED. R T TANK P/N 71537-2. LT TANK P/N 715371. 1 H 7 1 3O A21CE 2000021900092 20000219 00092 CE 2000 2 19 2000ZZZX373 1 20000120 G 7830 ROD END LEAR 35 35A 5170602 CE THRUST REVERSER WORN H K NONE O OTHER IN INSP/MAINT 1 SW 11 10AH 657 DURING A 1,200 HOUR T/R INSPECTION, FOUND WORN ACTUATOR ROD END BUSHING BRACKET. THE BRACKETS ARE ACTUALLY PART OF THE THRUST REVERSER DOOR. THEY ARE CAST INTO THE DOOR. 2 L 7 2 4F A10CE 2000021900093 20000219 00093 EA 2000 2 19 2000ZZZX374 2 20000103 G 8550 LINE AMRGEN AA5 AA5A 3960106 SO LYC O320 O320E2G 41508 EA OIL BREATHER FROZE D K NONE O OTHER IN INSP/MAINT 1 NM 03 26456 AA5A0600 ENGINE AIR BREATHER PINCH HOLE HAD B EEN ELIMINATED BY PARTIES UNKNOWN. BREATHER LINE FROZE SHUT AT 15,000 FEET. EXCES SIVE CRANKCASE PRESSURE CAUSED THE CRANKSHAFT OIL SEAL TO LEAK OIL. BREATHER LINE WAS REPOSITIONED AND A PINCH HOLE WAS DRILLED. 1 L 7 1 3O 3 O A16EA E274 2000021900096 20000219 00096 SW 2000 2 19 2000ZZZX377 1 20000107 G 6310 2060401561 SEAL BELL 407 407 SW TRANSMISSION LEAKING B UNFR K NONE K FLUID LOSS IN INSP/MAINT 1 SW 19 147CF 757 53281 SEAL LEAKING IN TRANSMISSION. 1 G 7 1 3U O H2SW 2000021900098 20000219 00098 CE 2000 2 19 2000ZZZX379 1 20000111 G 6120 68668 SPRING BEECH 95 95 1153402 CE RELIEF VALVE BROKEN D O OTHER O OTHER NR NOT REPORTED 1 NM 09 2051C 1475 TD238 LOW OIL PRESSURE DURING FLIGHT CAUSING PROPELLER TO GO TO LOW PITCH AND EVENTUALLY FEATHER. AIRCRAFT LANDED SAFELY AND AFTER TROUBLESHOOTING PROBLEM, FOUND BROKEN SPRING IN OIL PRESSURE RELIEF VALVE. INSTALLED NEW SPRING, ADJUSTED OIL PRE SSURE AND RETURNED TO SERVICE. 1 L 7 2 3O 3A16 2000021900102 20000219 00102 2000 2 19 2000ZZZX383 4 20000107 G 2561 KS9P0101 LIFE VEST EAAEROMARINE CABIN FAILED B KQ1R K NONE L NO TEST IN INSP/MAINT 1 EA 07 B40352 LIFE VEST FAILED MFG RECOMMENDED 2 PSI TEST IAW MANUAL 25-60-1. ITEM DATE OF MFG JUNE 1980. 2000021900103 20000219 00103 2000 2 19 2000ZZZX384 1 20000115 G 3240 7010FS9545708 SEAL 501052001 BRAKE SYSTEM LEAKING B XC4R K NONE K FLUID LOSS IN INSP/MAINT 1 SO 19 2377 SEP971104 BRAKE ASSEMBLY, P/N 5010520-1, FAILED PREMATURELY. TWO EACH PISTONS LEAKING FROM INSULATOR AREA. PISTONS INTERNALLY FI LLED WITH FLUID. EVIDENCE OF T-SEAL FAILURE. THIS IS A CONTINUAL DISCREPANCY. NOTE: OEM PARTS INSTALLED IN BRAKE ASS EMBLY AND THE MOST RECENT BRAKE CONFIGURATION, P/N 5010520-1. 2000021900104 20000219 00104 2000 2 19 2000ZZZX385 1 20000111 G 3240 7010FS9545708 SEAL 50105201 BRAKE SYSTEM LEAKING B XC4R K NONE K FLUID LOSS IN INSP/MAINT 1 SO 19 1990 APR981288 BRAKE ASSEMBLY, P/N 5010520-1, FAILED PREMATURELY. ONE EACH PISTON LEAKING FROM INSULATOR AREA. PISTON INTERNALLY FILL ED WITH FLUID. EVIDENCE OF T-SEAL FAILURE. THIS IS A CONTINUAL DISCREPANCY. NOTE: OEM PARTS INSTALLED IN BRAKE ASSY AND THE MOST RECENT BRAKE CONFIGURATION, P/N 5010520-1. 2000021900105 20000219 00105 2000 2 19 2000ZZZX386 1 20000117 G 3240 7010FS9545708 SEAL 50105201 BRAKE SYSTEM LEAKING B XC4R K NONE O OTHER IN INSP/MAINT 1 SO 19 1540 DEC981557 BRAKE ASSEMBLY, P/N 5010520-1, FAILED PREMATURELY. TWO EACH PISTONS LEAKING FROM INSULATOR AREA. PISTONS INTERNALLY FI LLED WITH FLUID. EVIDENCE OF T-SEAL FAILURE. THIS IS A CONTINUAL DISCREPANCY. FACTORY NEW BRAKE ASSEMBLY. NOTE: OEM PARTS INSTALLED IN BRAKE ASSY AND THE MOST RECENT BRAKE CONFIGURATION, P/N 5010520-1. 2000021900106 20000219 00106 2000 2 19 2000ZZZX387 1 20000118 G 3240 7010FS9545708 SEAL 50105201 BRAKE SYSTEM LEAKING B XC4R K NONE K FLUID LOSS IN INSP/MAINT 1 SO 19 1330 FEB991604 BRAKE ASSEMBLY, P/N 5010520-1, FAILED PREMATURELY. THREE EACH PISTONS LEAKING FROM INSULATOR AREA. PISTONS INTERNALLY FILLED WITH FLUID. EVIDENCE OF T-SEAL FAILURE. THIS IS A CONTINUAL DISCREPANCY. FACTORY NEW BRAKE ASSY. NOTE: OEM P ARTS INSTALLED IN BRAKE ASSY AND THE MOST RECENT BRAKE CONFIGURATION P/N 5010520-1. 2000021900107 20000219 00107 2000 2 19 2000ZZZX388 1 20000112 G 3240 7010FS9545708 SEAL 50105201 BRAKE SYSTEM LEAKING B XC4R K NONE K FLUID LOSS IN INSP/MAINT 1 SO 19 1049 AUG981445 BRAKE ASSY, P/N 5010520-1, FAILED PREMATURELY. THREE EACH PISTONS LEAKING FROM INSULATOR AREA. PISTONS INTERNALLY FILL ED WITH FLUID. EVIDENCE OF T-SEAL FAILURE. THIS IS A CONTINUAL DISCREPANCY. NOTE: OEM PARTS INSTALLED IN BRAKE ASSEM BLY AND THE MOST RECENT BRAKE CONFIGURATION, P/N 5010520-1. 2000021900108 20000219 00108 2000 2 19 2000ZZZX389 1 20000113 G 3240 7010FS9545708 SEAL 50105201 BRAKE SYSTEM LEAKING B XC4R K NONE K FLUID LOSS IN INSP/MAINT 1 SO 19 1615 OCT981541 BRAKE ASSEMBLY, P/N 5010520-1, FAILED PREMATURELY. ONE EACH PISTON LEAKING FROM INSULATOR AREA. PISTON INTERNALLY FILL ED WITH FLUID. EVIDENCE OF T-SEAL FAILURE. THIS IS A CONTINUAL DISCREPANCY. FACTORY NEW BRAKE ASSEMBLY. NOTE: OEM P ARTS INSTALLE DIN BRAKE ASSY AND THE MOST RECENT BRAKE CONFIGURATION, P/N 5010520-1. 2000021900109 20000219 00109 2000 2 19 2000ZZZX390 1 20000121 G 3240 7010FS9545708 SEAL 50105201 BRAKE SYSTEM LEAKING B XC4R K NONE K FLUID LOSS IN INSP/MAINT 1 SO 19 1977 OCT981543 BRAKE ASSY, P/N 5010520-1, FAILED PREMATURELY. TWO EACH PISTONS LEAKING FROM INSULATOR AREA. PISTONS INTERNALLY FILLED WITH FLUID. EVIDENCE OF T-SEAL FAILURE. THIS IS A CONTINUAL DISCREPANCY. FACTORY NEW BRAKE ASSY. NOTE: OEM PARTS I NSTALLED IN BRAKE ASSEMBLY AND THE MOST RECENT BRAKE CONFIGURATION, P/N 5010520-1. 2000021900110 20000219 00110 2000 2 19 2000ZZZX391 1 20000118 G 3240 7010FS9545708 SEAL 50105201 BRAKE SYSTEM LEAKING B XC4R K NONE K FLUID LOSS IN INSP/MAINT 1 SO 19 1712 APR981290 BRAKE ASSEMBLY, P/N 5010520-1, FAILED PREMATURELY. THREE EACH PISTONS LEAKING FROM INSULATOR AREA. PISTONS INTERNALLY FILLED WITH FLUID. EVIDENCE OF T-SEAL FAILURE. THIS IS A CONTINUAL DISCREPANCY. FACTORY NEW BRAKE ASSY. NOTE: OEM P ARTS INSTALLED IN BRAKE ASSY AND THE MOST RECENT BRAKE CONFIGURATION, P/N 5010520-1. 2000021900111 20000219 00111 2000 2 19 2000ZZZX392 1 20000120 G 3240 7010FS9545708 SEAL 50105201 BRAKE SYSTEM LEAKING B XC4R K NONE K FLUID LOSS IN INSP/MAINT 1 SO 19 1269 MAY981314 BRAKE ASSEMBLY, P/N 5010520-1, FAILED PREMATURELY. TWO EACH PISTONS LEAKING FROM INSULATOR AREA. PISTONS INTERNALLY FI LLED WITH FLUID. EVIDENCE OF T-SEAL FAILURE. THIS IS A CONTINUAL DISCREPANCY. FACTORY NEW BRAKE ASSEMBLY. NOTE: OEM PARTS INSTALLED IN BRAKE ASSY AND THE MOST RECENT BRAKE CONFIGURATION, P/N 5010520-1. 2000021900113 20000219 00113 2000 2 19 2000ZZZX394 1 20000124 G 3240 7010FS9545708 SEAL 50105201 BRAKE SYSTEM LEAKING B XC4R K NONE K FLUID LOSS IN INSP/MAINT 1 SO 19 1292 APR991673 BRAKE ASSEMBLY, P/N 5010520-1, FAILED PREMATURELY. TWO EACH PISTONS LEAKING FROM INSULATOR AREA. PISTONS INTERNALLY FI LLED WITH FLUID. EVIDENCE OF T-SEAL FAILURE. THIS IS A CONTINUAL DISCREPANCY. FACTORY NEW BRAKE ASSEMBLY. NOTE: OEM PARTS INSTALLED IN BRAKE ASSEMBLY AND THE MOST RECENT BRAKE CONFIGURATION, P/N 5010520-1. 2000021900114 20000219 00114 NE 2000 2 19 2000ZZZX395 3 20000126 G 6114 BEARING HARTZL HCC3Y HCC3YR2 NE HUB CORRODED B ZN1R K NONE O OTHER IN INSP/MAINT 1 SW 13 1916 CK2830 HAD EXCESSIVE RUST IN BEARING RACES AND ON BALLS. SOME CORROSION O INSIDE OF HUB. 5 C P25EA 2000021900115 20000219 00115 EU 2000 2 19 2000ZZZX396 1 20000124 G 7931 11346AA TRANSMITTER AMD FALC20 FALCON 2720302 EU ENGINE FAILED D E ENGINE SHUTDOWN N FALSE WARNING NR NOT REPORTED 1 SW 99 213LS 1140 107 OIL PRESSURE INDICATOR IN RIGHT ENGINE FLUCTUATED THEN INDICATED ZERO. SECURED ENGINE FOR PRECAUTION. DECLARED PRECAUT IONARY EMERGENCY WITH ATC AND RETURNED TO HOME BASE (SBN). TRANSMITTER REPLACED WITH OVERHAULED UNIT. OPS/MAINT CHECKE D GOOD. RETURNED AIRCRAFT TO SERVICE. 2 L 7 2 4F A7EU 2000021900118 20000219 00118 CE 2000 2 19 2000ZZZX399 1 20000107 G 3221 504100081 TRUNNION CESSNA 310 310P 2074238 CE LT MLG DAMAGED B L QE5R O OTHER O OTHER NR NOT REPORTED 1 NM 07 5768M 3315 310P0068 COMPONENT SENT TO REPAIR STATION FOR EVALUATION AS TO WHETHER IT WAS REPAIRABLE. ACFT HAD EXPERIENCED A NLG FAILURE AND IT WAS THOUGHT THE NLG FAILURE MAY HAVE CAUSED THE DAMAGE TO LT MLG ASSY. UPON INSP AND REFERENCING MM SECTIONS, THE M LG ASSY IS NON-REPAIRABLE. THE REPAIR WAS ACCOMPLISHED BY DRILLING OUT AND INSERTING A BUSHING. LUG DRILLED TO AN APP ROX SIZE OF .750 INCHES. A BUSHING WITH A .500 ID BY .750 OD WAS INSTALLED. RE MM, BUSHINGS ARE NOT USED AT THIS LOCAT ION AND A CLOSE TOLERANCE PIN, .500 INCH DIA, REF PAGE 2-178 OF MM, SECURE ASSY. DUE TO EXCESSIVE REMOVAL OF BASE MATER IAL, IT IS OPINION OF THIS REPAIR STATION THIS COMPONENT WOULD NOT BE AIRWORTHY; NO REPAIR SHALL BE ATTEMPTED. 1 L 7 2 3O 3A10 2000021900119 20000219 00119 SO 2000 2 19 2000ZZZX400 1 20000103 G 3220 400910 CLEVIS BOLT PIPER PA34 PA34200T 7103406 SO NLG CHAFED G A O OTHER O OTHER AP APPROACH 1 GL 25 47686 456 347770427 NOSE GEAR FAILED TO EXTEND ON APPROACH TO CAK, AIRCRAFT LANDED WITH NOSE GEAR RETRACTED RESULTING IN DAMAGE THE AIRCRAFT . SUBSEQUENT INVESTIGATION REVEALED THE NOSE GEAR CENTERING ATTACH BOLT (PIPER P/N 400-910), HAD COME IN CONTACT WITH N OSE GEAR DOOR ACTUATION-AFT TUBE ASSY, (PIPER P/N 95771-0), PREVENTING EXTENSION OF THE GEAR. SUBMITTER STATED BASED ON THE MARKS CONTAINED ON THE TUBE ASSY, IT APPEARED THAT CONDITION HAD EXISTED FOR A PERIOD OF TIME PRIOR TO THIS OCCURRE NCE. 1 L 7 2 3O A7SO 2000021900123 20000219 00123 CE 2000 2 19 2000ZZZX405 1 20000104 G 2710 PULLEY CESSNA 172 172N 2072434 CE ALERON SEPARATED H A K NONE O OTHER IN INSP/MAINT 1 NM 01 75803 5400 17267962 WHILE REPLACING AILERON PUSH/PULL ROD, SLACKNESS IN AILERON CABLE LED TO DISCOVERY THAT AILERON PULLEY, P/N S378-4 (LOCA TED UPPER STARBOARD POSITION IN REAR DOORPOST BULKHEAD ASSY), WAS NO LONGER BOLTED IN POSITION. NUT HAD WORKED OFF BOLT , BOLT HAD BACKED OUT OF PULLEY, AND PULLEY HAD FALLEN OUT OF POSITION. INSTALLED PULLEY BOLT WAS DISCOVERED TO BE AN4- 14A RATHER THAN SPECIFIED AN4-15A. SUBMITTER SUSPECTED BOLT FACTORY INSTALLED. 1 H 7 1 3O NT 3A12 2000021900124 20000219 00124 CE 2000 2 19 2000ZZZX406 1 20000128 G 7800 SLIP JOINT ZINAIR CH2000 CH2000 9950100 CE EXHAUST LEAKING H P A O OTHER K B FLUID LOSS SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 SW 99 32ZA 375 PILOT REPORTED EXHAUST SMELL IN THE COCKPIT. UPON INVEST, FOUND A SLIP JOINT ABOVE AND FWD OF HEATER MUFF ALLOWING EXH AUST TO ENTER HEAT MUFF. AREA HAD EXCESSIVE EXHAUST STAINS AND SCAT HOSE ON INTAKE SIDE OF THE MUFF WAS BRITTLE AND HE AT DAMAGED. FACTORY INFORMED THERE IS A LOWER PRESSURE IN THE COWLING THAN IN THE HEAT MUFF AND EXHAUST SHOULD NOT ENT ER THE MUFF. THIS THEORY DOES NOT HOLD UP IN THE FIELD. THE OPERATION OF CABIN VENTS, SLOW FLIGHT, FAST FLIGHT, AND CR UISE MAY CHANGE THESE PRESSURES. FACTORY STATED THEY HAVE A NEW DESIGN EXHAUST SYSTEM WITH DIFFERENT STYLE JOINTS AND C LAMPS. SUBMITTER SUGGESTED FACTORY MAKE ALL OWNERS AWARE OF POTENTIAL PROBLEM AND OFFER NEW STYLE EXHAUST. 1 L 7 1 3O NT TA5CH 2000021900125 20000219 00125 WP 2000 2 19 2000ZZZX407 1 20000120 G 3246 26088851 WHEEL 26088911 DOUG DC9 DC9* WP MLG BROKEN B A3L2 K NONE O OTHER IN INSP/MAINT 1 SW 09 B1161 BROKEN HUB. UNDER INVESTIGATION. 2 L 7 2 4F A6WE 2000021900126 20000219 00126 NM 2000 2 19 2000ZZZX408 1 20000120 G 3246 2609811 TIE BOLT DOUG MD11 MD11 3023602 NM WHEEL BROKEN B A3L2 K NONE O OTHER IN INSP/MAINT 1 SW 09 BROKEN TIE BOLT. UNDER INVESTIGATION. 2 L 7 3 4F RT A22WE 2000021900128 20000219 00128 SO 2000 2 19 2000ZZZX410 1 20000103 G 7120 6299173 CLAMP GULSTM G1159 GIV 3980115 SO ENGINE CRACKED B EC3R K NONE O OTHER IN INSP/MAINT 1 WP 05 71RP BN75458 1222 AEROQUIP VEE BAND CLAMP CRACKED STRAP BENEATH 'TEE' BOLT. CLAMP SECURED 12TH STAGE DUCT BLANKING PLATE. CRACK ALLOWED CLAMP TO FLEX THEN FAIL. CLAMP AND PLATE EXITED EXHAUST THROUGH BYPASS SECTION. DAMAGE TO BYPASS CASE OUTBOARD OF 12TH STAGE. 2 L 7 2 4F RT A12EA 2000021900129 20000219 00129 CE 2000 2 19 2000ZZZX411 1 20000120 G 8097 31B22207 WIRE CESSNA 172 172S 2072439 CE STARTER FAILED D O OTHER O OTHER IN INSP/MAINT 1 SW 99 498SP 435 85009816 172S8039 FIFTH FLIGHT OF THE DAY, ENGINE WOULD NOT START. MAINTENANCE FOUND STARTER WOULD NOT MOTOR. REMOVED STARTER AND REMOVE D END CAP, FOUND TWO BRUSH LEADS MELTED WHERE THEY ATTACH TO THE BRUSHES. REPLACED STARTER, OPERATIONAL CHECKED SATISFA CTORY. 1 H 7 1 3O NT 3A12 2000021900130 20000219 00130 WP 2000 2 19 2000ZZZX412 1 20000120 G 3246 26088851 WHEEL 26088911 DOUG DC9 DC983 3022083 WP MLG BROKEN B A3L2 K NONE O OTHER IN INSP/MAINT 1 SW 09 598AA B0172 53288 BROKEN HUB. UNDER INVESTIGATION. 2 L 7 2 4F RT A6WE 2000021900131 20000219 00131 NM 2000 2 19 2000ZZZX413 1 20000120 G 3244 TIRE BOEING 737 737* NM MLG FAILED B A3L2 O OTHER O OTHER NR NOT REPORTED 1 SW 09 PARTIAL SEPARATION OF TIRE TREAD FROM THE CAUCUS. UNDER INVESTIGATION. 2 L 7 2 4F RT A16WE 2000021900132 20000219 00132 CE 2000 2 19 2000ZZZX414 1 20000120 G 7810 HS783820041 BRACKET RAYTHN DH125 HAWKER800XP CE ENG TAILPIPE CHAFED B S G1FR O OTHER O OTHER NR NOT REPORTED 1 GL 13 501F 258286 CHAFE DAMAGE OCCURRED TO BOTH ENGINE TAILPIPE V-CLAMPS, P/N 234-559-9019 (IPC REF 78-10-01, FIG 1, ITEM 15) AND INNER CO RE COWL CHAFE BRACKET, P/N HS7838200-41 (IPC REF 78-30-05-05A, ITEM 245). EACH ENGINE CONTAINS 8 BRACKETS AND 1 V-CLAMP . DAMAGE HAS OCCURRED AT SOME OR ALL BRACKET MOUNT LOCATIONS WITH APPROXIMATE .020 INCH TO .090 INCH DEPTH WITH TOTAL EDGE SPAN OF 0.375 INCH ON THE BRACKETS AND APPROXIMATE .010 INCH TO .025 INCH DEPTH AT CONTACT LOCATIONS ON V-CLAMP. T HIS DAMAGE DISCOVERED DURING DISASSEMBLY AND REMOVAL OF ENGINE FOR 2100 HOUR HOT SECTION INSPECTION. ACFT TT: 2,003.3 HRS. LANDINGS: 1,146. LT ENG, SN 107124 TTSN 1,803.5 HRS, CSN 1,045. RT ENG SN 107125 TTSN 2,003.3 HRS, CSN 1,161. 2 L 7 2 4F RT A3EU 2000021900135 20000219 00135 CE 2000 2 19 2000ZZZX417 1 20000121 G 3222 CPS6502 SEAL CESSNA 650 650 2076802 CE NLG STRUT LEAKING A CNQ3 C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 GL 13 97AL 259 6500155 UPON TAKEOFF, LANDING GEAR WOULD NOT RETRACT BECAUSE SQUAT SWITCH WAS NOT MADE FOR AIR MODE. ADDITIONALLY, NOSE WHEEL W AS DEFLECTED TO THE LEFT. CAUSE WAS DETERMINED TO BE OLEO STRUT NOT EXTENDING COMPLETELY WHICH PREVENTED THE NOSE WHEEL FROM CENTERING, THEREBY, NOT ALLOWING THE SQUAT SWITCH TO MAKE FOR AIR MODE. FOUND OLEO SEALS LEAKING BETWEEN AIR AND FLUID CHAMBERS. REPACKED STRUT WITH NEW SEALS, AIRCRAFT FLIGHT CHECKED GOOD. 2 L 7 2 4F A9NM 2000021900136 20000219 00136 WP 2000 2 19 2000ZZZX418 1 20000129 G 3244 TIRE DOUG DC9 DC982 3022082 WP MLG DAMAGED B A3L2 K NONE O OTHER IN INSP/MAINT 1 SW 09 SEPARATION OF TIRE TREAD FROM TIRE CAUCUS. UNDER INVESTIGATION. 2 L 7 2 4F A6WE 2000021900137 20000219 00137 WP 2000 2 19 2000ZZZX419 1 20000120 G 3240 LINING 26088921 DOUG DC9 DC982 3022082 WP BRAKE ASSY FAILED B A3L2 K NONE O OTHER IN INSP/MAINT 1 SW 09 B0978 BRAKE LININGS FAILURE. CAUSE: UNDETERMINED. 2 L 7 2 4F A6WE 2000030100001 20000301 00001 2000 3 1 2000ZZZX488 1 20000204 G 6123 C6536 COUNTERWEIGHT MCAULY 5JFR C5JFR36C1104 GL PROPELLER CRACKED H K NONE O OTHER IN INSP/MAINT 1 SW 99 11324 5878 COUNTERWEIGHT CRACKED ON LOCATING RIDGE OF PROPELLER. 5 C P15NE 2000030100002 20000301 00002 2000 3 1 2000ZZZX489 1 20000202 G 3240 7010FS9545708 SEAL 50105201 BRAKE ASSY LEAKING B XC4R K NONE K FLUID LOSS IN INSP/MAINT 1 SO 19 2456 1308 MAY981325 BRAKE ASSEMBLY, PN 5010520-1, FAILED PREMATURELY. ONE EACH, PISTON LEAKING FROM INSULATOR AREA. PISTON INTERNALLY FILL ED WITH FLUID. EVIDENCE OF T-SEAL FAILURE. THIS IS A CONTINUAL DISCREPANCY. NOTE: OEM PARTS INSTALLED IN BRAKE ASSEM BLY AND THE MOST RECENT BRAKE CONFIGURATION, P/N 5010520-1. 2000030100003 20000301 00003 2000 3 1 2000ZZZX490 1 20000203 G 3240 7010FS9545708 SEAL 50105201 BRAKE ASSY LEAKING B XC4R K NONE K FLUID LOSS IN INSP/MAINT 1 SO 19 1478 AUG981444 BRAKE ASSEMBLY, PN 5010520-1, FAILED PREMATURELY. ONE EACH, PISTON LEAKING FROM INSULATOR AREA. PISTON INTERNALLY FILL ED WITH FLUID. EVIDENCE OF T-SEAL FAILURE. THIS IS A CONTINUAL DISCREPANCY. NOTE: OEM PARTS INSTALLED IN BRAKE ASSEM BLY AND THE MOST RECENT BRAKE CONFIGURATION, P/N 5010520-1. 2000030100005 20000301 00005 NM 2000 3 1 2000ZZZX492 1 20000129 G 2823 287N33009 CONDUIT BOEING 757 75724APF 1384969 NM NR 2 ENGINE DAMAGED B P HN6R K NONE O OTHER IN INSP/MAINT 1 NM 01 419UP 23906 NR 2 ENGINE FUEL SHUT-OFF VALVE (SOV) CONDUIT IS DAMAGED AT FORWARD END AND WIRING INSULATOR IS PEELED OFF. 2 L 7 2 4F RT A2NM 2000030200002 20000302 00002 2000 3 2 2000ZZZX495 4 20000113 G 2300 C23PU696701 REEL HUGHES C23PB620001 BOEING 767 767 UTILUSE NM PHONE DAMAGED B K NONE O OTHER IN INSP/MAINT 1 SW 19 CTEXT 135910122 339 PHONE REEL MELTED. 2 L 7 2 4F RT A1NM 2000030200005 20000302 00005 SO 2000 3 2 2000ZZZX498 1 20000117 G 5313 LONGERON PIPER PA18 PA18 7101802 SO FUSELAGE CORRODED H K NONE O OTHER IN INSP/MAINT 1 SW 99 DURING LAST 6 AIRCRAFT RECOVERED BY FACILITY, 5 OF THESE AIRCRAFT HAD TO HAVE THE TOP LONGERON REPLACED BECAUSE OF CORRO SION DUE TO WATER BEING TRAPPED UNDER THE SLIDING WINDOW CHANNEL ON THE LEFT SIDE. IN ALL CASES, THE SLIDING CHANNELS I N LONGERON AREA WERE SEVERELY CORRODED BEYOND JUST CLEANING AND HAD TO BE REPAIRED. 1 H 7 1 3O 1A2 2000030300012 20000303 00012 2000 3 3 2000ZZZX499 1 20000202 G 3240 7010FS9545708 SEAL 50105201 BRAKE ASSY LEAKING B XC4R K NONE K FLUID LOSS IN INSP/MAINT 1 SO 19 2339 BRAKE ASSEMBLY, PN 5010520-1, FAILED PREMATURELY. ONE EACH, PISTON LEAKING FROM INSULATOR AREA. PISTON INTERNALLY FILL ED WITH FLUID. EVIDENCE OF T-SEAL FAILURE. THIS IS A CONTINUAL DISCREPANCY. NOTE: OEM PARTS INSTALLED IN BRAKE ASSY A ND THE MOST RECENT BRAKE CONFIGURATION, P/N 5010520-1. 2000030300013 20000303 00013 SO 2000 3 3 2000ZZZX500 1 20000117 G 5320 CHANNEL PIPER PA18 PA18 7101802 SO FUSELAGE CORRODED H K NONE O OTHER IN INSP/MAINT 1 SW 99 DURING RECOVERING OF AIRCRAFT, FOUND THE REAR WINDOW CHANNELS LEFT AND RIGHT WERE CORRODED BEYOND REPAIR AND HAD TO BE R EPLACED. 1 H 7 1 3O 1A2 2000030900064 20000309 00064 GL 2000 3 9 2000ZZZX564 3 20000121 G 6111 BLADE PIPER PA30 PA30 7103002 SO HARTZL HCE2Y HCE2YL2 GL PROPELLER MISOVERHAULED B M71R K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 15 7887Y 3995 219 30973 BG3404 AIRCRAFT WAS IN GEAR UP LANDING IN 1995. PROPELLER WAS OVERHAULED BY KANSAS PROPELLER AND AVIATION. WO NR 1008. SUBMI TTER STATED DAMAGE IN PRELOAD SHOULD HAVE BEEN REJECTED IN 1995. 1 L 7 2 3O A1EA 5 C P9EA 2000030900065 20000309 00065 SO 2000 3 9 2000ZZZX565 1 20000121 G 5720 35770802 WEIGHT ASSY PIPER PA28 PA28R201 7102816 SO WING CORRODED B UC2R K NONE O OTHER IN INSP/MAINT 1 GL 19 9436C 4177 28R7837198 FOUND EXTENSIVE CORROSION ON BOTH STEEL PARTS OF THIS ASSEMBLY DURING 100-HOUR INSPECTION. 1 L 7 1 3O 2A13 2000030900066 20000309 00066 CE 2000 3 9 2000ZZZX566 1 20000306 G 3200 99121033 BOTTLE PACIFICSCIEN 18225901 CESSNA 500 500CESSNA 2076602 CE MLG LEAKING B IBER K NONE K FLUID LOSS IN INSP/MAINT 1 CE 05 4918B 2543 5000102 NEW EMERGENCY BLOW DOWN BOTTLE LEAKING. APPROXIMATELY 500 PSI IN 24-HOUR PERIOD. 1 L 7 2 4F A22CE 2000030900067 20000309 00067 SO 2000 3 9 2000ZZZX567 2 20000111 G 8520 GEAR CESSNA 421 421C 2076016 CE CONT O520 GTSIO520L 17032 SO CRANKSHAFT DAMAGED B TUPR O OTHER Y J ENGINE STOPPAGE WARNING INDICATION TX TAXI/GRND HDL 1 NM 09 421PJ 1229 421C0860 608138 ON ROLL-OUT AFTER LANDING, PILOT OBSERVED THE ENGINE HAD SHUT DOWN. ON ATTEMPTED START, THERE WAS NO PROPELLER MOVEMENT . STARTER WAS CHECKED ON THE BENCH, AND STARTER ADAPTER WAS REMOVED FOR ENGINE TO REVEAL SEVERE GEAR DAMAGE TO THE MAIN CRANKSHAFT GEAR AND STARTER ADAPTER GEAR. OTHER GEARS WERE DAMAGED DUE TO FOD FROM THE CRANK GEAR. INITIAL OBSERVATIO N INDICATED THE STARTER ADAPTER BEARINGS IN THE REAR OF ADAPTER AND THE FORWARD NEEDLE BEARING IN THE CRANKCASE WERE INT ACT AND SECURE. 1 L 7 2 3O 3 O A7CE E7CE 2000030900069 20000309 00069 CE 2000 3 9 2000ZZZX568 1 20000124 G 3240 12801111 SWIVEL CESSNA 182 R182 2072734 CE BRAKE ASSY LEAKING B AMVR O OTHER K FLUID LOSS NR NOT REPORTED 1 CE 05 4135C 8654 R18200326 SWIVEL IS FOR BRAKE LINE AT MAIN GEAR. PILOT SQUAWK OF PEDAL FOR RT BRAKE BLEEDS OFF, BRAKE FLUID ON BELLY. INSPECTION OF SYSTEM UNDER PRESSURE SHOWED LEAK AT SWIVEL. REPLACED SWIVEL. SUBMITTER SUGGESTED CAUSE, AGE. 1 H 7 1 3O RT 3A13 2000030900070 20000309 00070 CE 2000 3 9 2000ZZZX569 1 20000111 G 3230 08411132 ADJUST SCREW CESSNA 340 340CESSNA 2076404 CE RT MLG FAILED B AK6R D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 SW 19 5910M 3622 3400067 UPON TAXI OFF OF THE RUNWAY AFTER AN UNEVENTFUL LANDING, THE PART SPECIFIED (0841113-2) FAILED CAUSING THE RIGHT MAIN GE AR TO FOLD. THE AIRCRAFT ROTATED AROUND CAUSING THE LEFT GEAR TO COLLAPSE. 1 L 7 2 3O 3A25 2000030900071 20000309 00071 SO 2000 3 9 2000ZZZX570 1 20000307 G 5720 2366200 FITTING PIPER PA24 PA24250 7102404 SO WS136 LOOSE D K NONE O OTHER IN INSP/MAINT 1 EA 23 5457P 3017 24513 RIGHT WING ATTACHMENT FITTING STA 136 UNDER AFT BAGGAGE COMPARTMENT FLOOR. PLATE, P/N 23662-00, AND FITTING, P/N 23663- 00, RIVETS GONE. 1 L 7 1 3O 1A15 2000030900073 20000309 00073 GL 2000 3 9 2000ZZZX572 3 20000117 G 6110 LW13335 BEARING LYC LW13081 PIPER PA31 PA31P 7103120 SO HARTZL HCC3Y HCC3YN GL PROPELLER FAILED B EKIR O OTHER K J FLUID LOSS WARNING INDICATION AP APPROACH 1 WP 07 7652L 521 31P730012 D6237 OIL PRESSURE DROPPED TO UPPER YELLOW AREA ON APPROACH TO LANDING. FOUND FERROUS AND NON-FERROUS METAL IN FILTER. ENG INE TORN DOWN, FOUND THRUSTBEARING BEARING BROKEN. SUBMITTER SUSPECTED PIECES WENT THROUGH PROPELLER DRIVE AND DRIVE GE ARS CAUSING DAMAGE TO BOTH GEARS. 1 L 7 2 3O A8EA 5 C P25EA 2000030900074 20000309 00074 NE 2000 3 9 2000ZZZX573 3 20000128 G 6111 D5133 EROSION SHIELD E10950PK HARTZL HCE4A HCE4A3A NE NR 1 PROPELLER DAMAGED B GLBR K NONE O OTHER IN INSP/MAINT 1 CE 01 2540 HJ717 REMOVED EROSION SHIELD PAD BOOT FROM NR 1 BLADE, SN 2540, BECAUSE MISSING .1250 INCH BY .50 INCH PIECE OF EROSION SHIELD . INSTALLED NEW EROSION SHIELD AND DE-ICE BOOT WITH EA9330 LOT NR 9228-1 IAW PROCEDURE 001, AND HARTZELL M 135F 61-13-3 5. BALANCED IAW HARTZELL MM 143A 61-10-16. 5 C P10NE 2000030900075 20000309 00075 NE 2000 3 9 2000ZZZX574 3 20000125 G 6111 D5133 EROSION SHIELD E10950PK HARTZL HCE4A HCE4A3A NE NR 2 PROPELLER CRACKED B GLBR K NONE O OTHER IN INSP/MAINT 1 CE 01 2315 HJ691 REMOVED EROSION SHIELD AND DE-ICE BOOT FROM NR 2 BLADE, S/N 2315, BECAUSE OUT OF LIMITS FOR CRACKS. INSTALLED NEW EROSI ON SHIELD AND DE-ICE BOOT IAW PROCEDURE 001 AND HARTZELL MM 135F 61-13-35 AND BALANCED IAW 143A 61-10-16. USED HYSOL EA 9330 LOT NR 9228-1. 5 C P10NE 2000030900076 20000309 00076 CE 2000 3 9 2000ZZZX575 1 20000111 G 3230 08411011 FITTIN CESSNA 340 340CESSNA 2076404 CE RT MLG FAILED B AK6R O OTHER O OTHER TX TAXI/GRND HDL 1 SW 19 3622 3400067 UPON TAXI OFF OF THE RUNWAY AFTER AN UNEVENTFUL LANDING, THE PART SPECIFIED (0841101-1) FAILED CAUSING THE RIGHT MAIN GE AR TO FOLD. THE AIRCRAFT ROTATED AROUND CAUSING THE LEFT GEAR TO COLLAPSE. 1 L 7 2 3O 3A25 2000030900077 20000309 00077 EA 2000 3 9 2000ZZZX576 2 20000107 G 8530 CYLINDER PIPER PA60 PA60600 7106001 NM LYC O540 IO540K1J5 41532 EA RT ENGINE SEPARATED H O OTHER O OTHER NR NOT REPORTED 1 GL 07 6892R 600887816125 L2082548A BGM - RIGHT ENGINE, NR 2 CYLINDER, SEPARATED. SUBMITTER STATED CAUSE UNKNOWN AT THIS TIME. WILL REMOVE AND REPLACE ENG INE, FLUSH PROPELLER, AND PROPELLER GOVERNOR BEFORE FLIGHT. 1 M 7 2 3O 3 O RT A17WE 1E4 2000030900079 20000309 00079 SW 2000 3 9 2000ZZZX578 1 20000209 G 7714 407375002103 INDICATOR BELL 407 407 SW ENGINE NG MALFUNCTIONED B GS1R O OTHER O OTHER NR NOT REPORTED 1 EA 03 407WH 369 0039 532027 NG INDICATOR MALFUNCTIONED. REPLACED WITH NEW INDICATOR FROM BELL HELICOPTER. 1 G 7 1 3U O H2SW 2000030900080 20000309 00080 SO 2000 3 9 2000ZZZX579 2 20000125 G 8500 ENGINE BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO LEFT MAKING METAL H O OTHER Y ENGINE STOPPAGE NR NOT REPORTED 1 GL 07 58TA TH596 299134R ELM - LEFT ENGINE SHUT DOWN BY ITSELF IN-FLIGHT. ENGINE HAD PLENTY OF OIL, NO EXTERNAL LEAKS OR CRACKS, OIL FILTER FULL OF METAL. SUBMITTER STATED CAUSE UNKNOWN AT THIS TIME. 1 L 7 2 3O 3 O 3A16 E5CE 2000030900081 20000309 00081 SO 2000 3 9 2000ZZZX580 1 20000201 G 2731 PULLEY PIPER PA12 PA12 7101202 SO ELEVATOR WORN D S K NONE O OTHER IN INSP/MAINT 1 NM 08 3168M 3100 121847 FOUND TRIM PULLEY AND SHAFT HAD WORN EXCESSIVELY INTO BRACKETS. WELDED TO AIRCRAFT (THIS IS TRIM CRANK IN COCKPIT) CAUS ED TRIM TO BIND UP. 1 H 7 1 3O A780 2000031700001 20000317 00001 EU 2000 3 17 2000ZZZX581 1 20000211 G 2800 B97E51254 VALVE AMD FALC20 FALCON20F5 2730105 EU RT WING MALFUNCTIONED B UO2R K NONE O OTHER IN INSP/MAINT 1 GL 19 SUAYD 361 RIGHT WING REFUEL VENT VALVE OPERATES INCORRECTLY AFTER OVERHAUL. WHEN POWER IS APPLIED TO THE 'OPEN' CIRCUIT, VALVE RU NS TO THE CLOSED POSITION AND THE VALVE POSITION INDICATOR (MECHANICAL INDICATES CLOSED. ELECTRICALLY, THE VALVE INDICA TES OPEN. 2 L 7 2 4F RT A7EU 2000031700002 20000317 00002 WP 2000 3 17 2000ZZZX582 2 20000103 G 7250 30723515 DISK GARRTT TFE731 TFE7313R1H 29001 WP LP TURBINE FAILED B UO2R K NONE O OTHER IN INSP/MAINT 1 GL 19 2419 2148 103229852 P80131C ENGINE RECEIVED WITH TURBINE DAMAGE. FIELD REPORT REVEALED THIS ENGINE EXPERIENCED AN IN-FLIGHT SHUT DOWN AT FL 350. D URING TEAR DOWN, THE LPT1 ROTOR ASSY HAD ALL BLADES BROKEN OFF JUST ABOVE THE FIR TREE AREA. ONE LPT1 BLADE COULD NOT B E FOUND. DISK GROWTH MEASURED 0.060 INCH. SUBMITTER SUSPECTED BLADE RELEASE. (X) 4 F E6WE 2000031700003 20000317 00003 CE 2000 3 17 2000ZZZX583 1 20000207 G 5320 RIVET LEAR 55 55C 5170706 CE MISINSTALLED B JGVR K NONE O OTHER IN INSP/MAINT 1 CE 09 PTGMN 2261 139 SIX RIVETS MISSING FROM RT FUSELAGE BETWEEN MIDDLE AND AFT WING ATTACH POINTS. BS 401.92 AND BS 410.30. THESE RIVETS D O NOT GO THROUGH THE PRESSURE VESSEL, BUT DO GO THROUGH RT FUSELAGE OVERWING LONGERON. THREE RIVETS MISSING FROM AFT SI DE OF MIDDLE ATTACH FITTING AND THREE RIVETS MISSING FROM AFT SIDE OF AFT ATTACH POINT. (X) 2 L 7 2 4F RT A10CE 2000031700004 20000317 00004 2000 3 17 2000ZZZX584 1 20000223 G 2810 CELL DURACELL PORAPREFI CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 25 FUEL CELLS CRACKING INTERNALLY IF TANKS ARE NOT TOPPED OFF. HAVE RECEIVED 28 OF SUCH CELLS SINCE 11-30-99. CELLS ARE O F FAA APPROVED MATERIAL, ETC. SUBMITTER CONCERNED ABOUT THEIR RELIABILITY IN THE FUTURE IN THAT THERE ARE A LOT OF THES E CELLS OUT THERE. HAVE ADVISED MANUFACTURING INSPECTOR IN ATLANTA, GA OF THE PROBLEM TODAY, 2-24-00, AFTER FINDING RET URNS IN LOG BOOK. (X) 2000031700005 20000317 00005 2000 3 17 2000ZZZX585 1 20000217 G 3240 7010FS9545708 SEAL 50105201 BRAKE ASSY LEAKING B XC4R K NONE K FLUID LOSS IN INSP/MAINT 1 SO 19 1719 DEC981559 BRAKE ASSEMBLY, P/N 5010520-1, FAILED PREMATURELY. TWO EACH, PISTONS LEAKING FROM INSULATOR AREA. PISTONS INTERNALLY F ILLED WITH FLUID. EVIDENCE OF T-SEAL FAILURE. THIS IS A CONTINUAL DISCREPANCY. FACTORY NEW BRAKE ASSEMBLY. NOTE: OE M PARTS INSTALLED IN BRAKE ASSEMBLY AND THE MOST RECENT BRAKE CONFIGURATION, P/N 5010520-1. (X) 2000031700006 20000317 00006 2000 3 17 2000ZZZX586 1 20000224 G 3240 7010FS9545708 SEAL 50105201 BRAKY ASSY LEAKING B XC4R K NONE K FLUID LOSS IN INSP/MAINT 1 SO 19 1292 APR991672 BRAKE ASSEMBLY, P/N 5010520-1, FAILED PREMATURELY. ONE EACH, PISTON LEAKING FROM INSULATOR AREA. PISTON INTERNALLY FIL LED WITH FLUID. EVIDENCE OF T-SEAL FAILURE. THIS IS A CONTINUAL DISCREPANCY. FACTORY NEW BRAKE ASSEMBLY. NOTE: OEM PARTS INSTALLED IN BRAKE ASSEMBLY AND THE MOST RECENT BRAKE CONFIGURATION, P/N 5010520-1. (X) 2000031700007 20000317 00007 2000 3 17 2000ZZZX587 1 20000224 G 3240 7010FS9545708 SEAL 50105201 BRAKE ASSY LEAKING B XC4R K NONE K FLUID LOSS IN INSP/MAINT 1 SO 19 2195 APR981272 BRAKE ASSEMBLY, P/N 5010520-1, FAILED PREMATURELY. FIVE EACH, PISTONS LEAKING FROM INSULATOR AREA. PISTONS INTERNALLY FILLED WITH FLUID. EVIDENCE OF T-SEAL FAILURE. THIS IS A CONTINUAL DISCREPANCY. NOTE: OEM PARTS INSTALLED IN BRAKE A SSEMBLY AND THE MOST RECENT BRAKE CONFIGURATION, P/N 5010520-1. (X) 2000031700008 20000317 00008 WP 2000 3 17 2000ZZZX588 2 20000207 G 7250 30720695 DISK GARRTT TFE731 TFE731* 01518 WP LP TURBINE NICKED B UO2R K NONE O OTHER IN INSP/MAINT 1 GL 19 990322903007 NEW PART RECEIVED FROM HONEYWELL WITH NICKS AND SCRATCHES IN POST FIR TREE AREA, TWO PLACES ON EACH SIDE. (X) 4 F E6WE 2000031700009 20000317 00009 WP 2000 3 17 2000ZZZX589 2 20000204 G 7250 30720695 DISK GARRTT TFE731 TFE731* 01518 WP LP TURBINE NICKED B UO2R K NONE O OTHER IN INSP/MAINT 1 GL 19 990322903661 NEW PART RECEIVED FROM HONEYWELL WITH STEP IN WEB AROUND CURVIC AREA ON FORWARD SIDE OF DISK; ALSO, HAS NICKS IN FIR TRE E AREA ON BOTH SIDES OF DISK. (X) 4 F E6WE 2000031700010 20000317 00010 WP 2000 3 17 2000ZZZX590 2 20000204 G 7250 30720695 DISK GARRTT TPE331 TPE331* 01514 WP LP TURBINE NICKED B UO2R K NONE O OTHER IN INSP/MAINT 1 GL 19 NEW PART RECEIVED FROM HONEYWELL WITH ROUGH SPOTS IN WEB AREA ROUND DISK ON FORWARD SIDE; ALSO, NICKS IN POST FIR TREE A REA ON AFT SIDE. (X) 3 T E2WE 2000031700011 20000317 00011 WP 2000 3 17 2000ZZZX591 2 20000208 G 7250 30720695 DISK GARRTT TFE731 TFE731* 01518 WP LP TURBINE NICKED B UO2R K NONE O OTHER IN INSP/MAINT 1 GL 19 NEW PART RECEIVED FROM HONEYWELL WITH SCRATCHES IN WEB AREA THAT CAN BE FELT WITH AN .080 INCH STYLIST ON FORWARD SIDE; ALSO, ONE NICK IN POST FIR TREE AREA ON FORWARD SIDE. (X) 4 F E6WE 2000031700012 20000317 00012 WP 2000 3 17 2000ZZZX592 2 20000120 G 7261 31032173 SHAFT GARRTT TPE331 TPE33112UA 01514 WP OIL PUMP SHEARED B UO2R O OTHER Y J ENGINE STOPPAGE WARNING INDICATION NR NOT REPORTED 1 GL 19 2568 9714075319 P66184 ENGINE EXPERIENCED AN IN-FLIGHT SHUT DOWN CAUSED BY OIL PUMP SHAFT SHEARED. (X) 4 T E4WE 2000031700013 20000317 00013 WP 2000 3 17 2000ZZZX593 2 20000125 G 7250 30723515 DISK GARRTT TFE731 TFE731* 01518 WP LP TURBINE DAMAGED B UO2R K NONE O OTHER IN INSP/MAINT 1 GL 19 990322902774 NEW PART RECEIVED FROM HONEYWELL WITH DISK WEB DAMAGE. (X) 4 F E6WE 2000031700014 20000317 00014 WP 2000 3 17 2000ZZZX594 2 20000128 G 7250 30723163 DISK GARRTT TPE331 TPE331* 01514 WP HP TURBINE NICKED B UO2R K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 19 990322900255 NEW PART RECEIVED FROM HONEYWELL WITH CURVIC NICKS AT FIR TREE AREA. (X) 3 T E2WE 2000031700015 20000317 00015 WP 2000 3 17 2000ZZZX595 2 20000128 G 7230 30724434 PLENUM GARRTT TPE331 TPE331* 01514 WP COMPRESSOR MISMANUFACTURED B UO2R K NONE W INADEQUATE Q C IN INSP/MAINT 1 GL 19 5991 OP51825 REPAIRED PART FROM HONEYWELL. DIM. C OUT OF LIMITS. (X) 3 T E2WE 2000031700016 20000317 00016 WP 2000 3 17 2000ZZZX596 2 20000209 G 7250 30720695 DISK GARRTT TFE731 TFE731* 01518 WP LP TURBINE NICKED B UO2R K NONE O OTHER IN INSP/MAINT 1 GL 19 990322903684 NEW PART RECEIVED FROM HONEYWELL WITH NICKS IN BORE REGION ON AFT SIDE. (X) 4 F E6WE 2000031700017 20000317 00017 WP 2000 3 17 2000ZZZX597 2 20000125 G 7250 30723515 DISK GARRTT TPE331 TPE331* 01514 WP LP TURBINE NICKED B UO2R K NONE O OTHER IN INSP/MAINT 1 GL 19 NEW PART RECEIVED FROM HONEYWELL WITH CURVIC TEETH DAMAGE, NICKS. (X) 3 T E2WE 2000031700018 20000317 00018 WP 2000 3 17 2000ZZZX598 2 20000125 G 7250 30723515 DISK GARRTT TPE331 TPE331* 01514 WP LP TURBINE NICKED B UO2R K NONE O OTHER IN INSP/MAINT 1 GL 19 990322902797 NEW PART RECEIVED FROM HONEYWELL WITH CURVIC TEETH DAMAGE, NICKS. (X) 3 T E2WE 2000031700019 20000317 00019 WP 2000 3 17 2000ZZZX599 2 20000125 G 7250 30723515 DISK GARRTT TPE331 TPE331* 01514 WP LP TURBINE NICKED B UO2R K NONE O OTHER IN INSP/MAINT 1 GL 19 990322902992 NEW PART RECEIVED FROM HONEYWELL WITH CURVIC TEETH DAMAGE, NICKS. (X) 3 T E2WE 2000031700020 20000317 00020 WP 2000 3 17 2000ZZZX600 2 20000125 G 7250 30723515 DISK GARRTT TPE331 TPE331* 01514 WP LP TURBINE NICKED B UO2R K NONE O OTHER IN INSP/MAINT 1 GL 19 990322902819 NEW PART RECEIVED FROM HONEYWELL WITH CURVIC TEETH DAMAGE, NICKS. (X) 3 T E2WE 2000031700021 20000317 00021 GL 2000 3 17 2000ZZZX601 3 20000207 G 6111 8433 BLADE TEMCO 11A 11A 8890402 CE HARTZL HCD2X HCD2X207 GL V SHANK CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 B68357 AV128 PROPELLER BLADE CRACKED IN V SHANK. (ADP) 1 H 7 1 3O TC804 5 C P917 2000031700022 20000317 00022 2000 3 17 2000ZZZX602 1 20000210 G 3230 23171025 PISTON LEAR MLG MISMANUFACTURED B JGVR K NONE W INADEQUATE Q C IN INSP/MAINT 1 CE 09 RH0249 RECEIVED NEW PISTON INSTALLED BALL HOUSING AND BALLS. INSTALLED PLUNGER, BUT WAS UNABLE TO GET IT INTO LOCKING POSITION . FOUND BALL LOCK GROOVE .015 INCH BELOW FROM THE OLD PISTON. (X) 2000031700023 20000317 00023 SO 2000 3 17 2000ZZZX603 2 20000217 G 7414 6320 MAGNETO SLICK PIPER PA34 PA34220T 7103420 SO CONT O360 TSIO360KB 17025 SO ENGINE FAILED D O OTHER R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 EA 21 198PS 449 97110674 3449051 MAGNETO FAILED IN-FLIGHT. FOUND SEVERE DAMAGE TO DISTRIBUTOR FROM ARCING. ARCING APPEARED TO HAVE STARTED BEWEEN COIL AND REAR BEARING HOUSING. SUBMITTER STATED CAUSE UNKNOWN. (X) 1 L 7 2 3O 3 O A7SO E9CE 2000031700025 20000317 00025 CE 2000 3 17 2000ZZZX605 1 20000217 G 5540 96630000333 RUDDER MAST BEECH 58 58TC 1152746 CE RUDDER DAMAGED B P A R2JR K NONE O OTHER IN INSP/MAINT 1 EA 21 23712 3194 TK67 WHILE INSPECTING AIRCRAFT, FOUND RUDDER WAS LOOSE AT THE ATTACHMENT TO RUDDER CABLE BELLCRANK. REMOVED BOLTS AND FOUND 2 EACH BOLT HOLES ELONGATED. SUBMITTER STATED CAUSE UNKNOWN, BOLTS WERE TIGHT. SUBMITTER SUGGESTED CLOSE INSPECTION OF THIS AREA AT INSPECTION TIME. FREE PLAY WAS SLIGHT AND COULD BE EASILY MISSED, BUT COULD CAUSE FLIGHT CONTROL FLUTTER. (X) 1 L 7 2 3O A23CE 2000031700026 20000317 00026 CE 2000 3 17 2000ZZZX606 1 20000217 G 5540 0025240761 BELLCRANK BEECH 58 58TC 1152746 CE RUDDER DAMAGED B R2JR K NONE O OTHER IN INSP/MAINT 1 EA 21 23712 3194 TK67 WHILE INSPECTING AIRCRAFT, FOUND RUDDER WAS LOOSE AT THE ATTACHMENT TO RUDDER CABLE BELLCRANK. REMOVED BOLTS AND FOUND 2 EACH BOLT HOLES ELONGATED. SUBMITTER STATED CAUSE UNKNOWN, BOLTS WERE TIGHT. SUBMITTER SUGGESTED CLOSE INSPECTION OF THIS AREA AT INSPECTION TIME. FREE PLAY WAS SLIGHT AND COULD BE EASILY MISSED, BUT COULD CAUSE FLIGHT CONTROL FLUTTER. (X) 1 L 7 2 3O A23CE 2000031700027 20000317 00027 SW 2000 3 17 2000ZZZX607 1 20000105 G 3233 BOLT MOONEY M20 M20J 5870219 SW MLG ACTUATOR MISINSTALLED H A O OTHER O OTHER NR NOT REPORTED 1 SO 17 1077V 243160 A SITUATION OCCURRED WHERE THE PILOT NOTICED A HIT IN THE CONTROL SYSTEM WHEN THE LANDING GEAR WAS RETRACTED. IT WAS DE TERMINED THE FORWARD GEAR ACUTATOR BOLT HAD BEEN INSTALLED INCORRECTLY, HAD CONTACTED THE RUDDER INTERCONNECT PIVOT POIN T, AND HAD DEFORMED THE ATTACH POINT THAT WHENEVER THE GEAR WAS RETRACTED IT HIT IT. IT IS RECOMMENDED THAT INSPECTION BE MADE WHENEVER THE ACTUATOR AREA IS ACCESSED TO CONFIRM THE ACTUATOR BOLT IS INSTALLED CORRECTLY. (BOLT HAD FACING LE FT). 1 L 7 1 3O 2A3 2000031700028 20000317 00028 NM 2000 3 17 2000ZZZX608 1 20000124 G 3230 CAM BOEING 767 767332 1382001 NM MLG DAMAGED H P K NONE O OTHER IN INSP/MAINT 1 SW 99 174DN 24802 PARTS WERE RECEIVED AT B. F. GOODRICH AEROSPACE LOCATED IN OPA-LOCKA, FLORIDA. THE INTERNAL PARTS ARE DAMAGED BEYOND RE PAIR. SUBMITTER STATED THE DAMAGES TO UPPER AND LOWER CAMS COULD HAVE BEEN A RESULT OF A DISLODGED SUPPORT PIN LOCATED I THE LOWER CAM. (X) 2 L 7 2 4F RT A1NM 2000031700029 20000317 00029 GL 2000 3 17 2000ZZZX609 3 20000207 G 6114 HUB CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL BLADE SOCKET CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 2744B 188 340A0940 797794 PROPELLER HUB CRACKED IN BLADE SOCKET. (ADP) 1 L 7 2 3O 3A25 5 C P22EA 2000031700030 20000317 00030 GL 2000 3 17 2000ZZZX610 3 20000207 G 6114 C7036 NUT CESSNA 340 340A 2076405 CE MCAULY 3AF32C 3AF32C93 GL PROPELLER HUB CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 2744B 188 349A9849 797794 LOCK NUT CRACKED IN THREADED AREA OF PROPELLER HUB. (X) 1 L 7 2 3O 3A25 5 C P22EA 2000031700031 20000317 00031 2000 3 17 2000ZZZX611 4 20000208 G 3416 KEA346 ALTIMETER BENDIX BEECH 1900 1900D 1154162 CE COCKPIT INOPERATIVE B GLBR K NONE O OTHER IN INSP/MAINT 1 CE 01 254GL 848 2857 UE254 ENCODER INOPERATIVE. (X) 2 L 7 2 4T RT A24CE 2000031700032 20000317 00032 2000 3 17 2000ZZZX612 4 20000208 G 3416 KEA346 ALTIMETER BENDIX BEECH 1900 1900D 1154162 CE COCKPIT INOPERATIVE B GLBR K NONE O OTHER IN INSP/MAINT 1 CE 01 201YQ 790 4510 UE201 ALTIMETER FLAGGED AT 4,200 FEET AND REMAINED INOPERABLE. VERIFIED ON BENCH. (X) 2 L 7 2 4T RT A24CE 2000031700033 20000317 00033 2000 3 17 2000ZZZX613 4 20000208 G 3416 KEA346 ALTIMETER BENDIX BEECH 1900 1900D 1154162 CE COCKPIT READS HIGH B GLBR K NONE O OTHER IN INSP/MAINT 1 CE 01 257GL 107 1381 UE257 ENCODER READS 200 FEET HIGH. PROBLEM VERIFIED ON BENCH. (X) 2 L 7 2 4T RT A24CE 2000031700034 20000317 00034 CE 2000 3 17 2000ZZZX614 1 20000224 G 3252 SHIMMY DAMPENER 17430213 CESSNA 177 177B 2073708 CE MLG BROKEN D O OTHER O OTHER NR NOT REPORTED 1 SW 15 35033 100 177022169 AFTER REPLACING AN OLD SHIMMY DAMPENER WITH A NEW ONE AT APPROXIMATELY 100 HOURS IN SERVICE, THE NEW PART BROKE AT THE O UTER C-CLAMP RING SPLITTING THE OUTER CYLINDER CASE. THIS HAPPENED AS THE AIRCRAFT STOPPED SHIMMING. THE END PLUG, C-C LAMP AND ALL FLUID WERE LOST. NO INJURIES TO OCCUPANTS. THIS IS THE NEW STYLE CYLINDER. SUBMITTER STATEDTHIS CYLINDER MAY NEED MORE END DISTANCE OR THICKNESS. PART TOTAL TIME, 100 HOURS. (X) 1 H 7 1 3O A13CE 2000031700077 20000317 00077 CE 2000 3 17 2000ZZZX615 1 20000204 G 5210 NAS130534H BOLT BEECH MU300 400A 1155402 CE DOOR HINGE LOOSE B QMZR K NONE O OTHER IN INSP/MAINT 1 EA 05 295FA 2660 RK68 AT AN A-INSPECTION, TECHNICAN FOUND DOOR HINGE WASHERS OUT OF ALIGNMENT, AND THEY COULD BE REMOVED BY HAND. GAINED ACCE SS TO HINGE BOLTS. FOUND SAFETY WIRE AND TORQUE SEAL BROKEN ON BOTH BOLTS, AND BOLTS WERE BACKING OUT OF CAPTIVE NUTS. REMOVED BOLTS, INSPECTED, RE-INSTALLED, AND SAFETIED. 2 H 7 2 4F RT A16SW 2000031700078 20000317 00078 EA 2000 3 17 2000ZZZX616 2 20000204 G 8520 LW10545S PISTON PIPER PA31 PA31310 7103103 SO LYC O540 TIO540J2BD 41532 EA ENGINE CORRODED H K NONE O OTHER IN INSP/MAINT 1 NM 08 2336V 31135 RL472661A ENGINE WAS 438 HOURS FROM FACTORY REMANUFACTURE. REMOVED LONER PLUG FROM NR 3 CYLINDER AND FOUND CYLINDER HAD EXCESSIVE OIL IN PLUG. REMOVED CYLINDER AND FOUND THE OIL CONTROL RING LAND AND PISTON PIN HOLE WERE EXCESSIVELY PITTED AND CORR ODED. ENGINE WAS REPORTED AS NEEDING TO 'CLEAR ITS THROAT' BEFORE IT WOULD RUN SMOOTH. 1 L 7 1 3O 3 O RT A20SO E14EA 2000031700079 20000317 00079 CE 2000 3 17 2000ZZZX617 1 20000105 G 3233 1CH16 SWITCH LEAR 35 35A 5170602 CE LT MLG ACTUATOR FAILED H O OTHER J WARNING INDICATION NR NOT REPORTED 1 GL 07 15WH 85 GOING INTO BWI, HAD TO CYCLE GEAR 3 TIMES TO LET LEFT GEAR TO SHOW DOWN AND LOCK INDICATION. FERRIED AIRCRAFT BACK TO C MH. REMOVED AND REPLACED LEFT GEAR ACTUATORS SWITCH. OPS CHECKED GOOD. 2 L 7 2 4F A10CE 2000031700081 20000317 00081 SO 2000 3 17 2000ZZZX619 2 20000210 G 8530 EXHAUST VALVE CESSNA 150 150L 2071826 CE CONT O200 O200A 17020 SO ENGINE STUCK G O OTHER R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 SO 11 11567 738 15075527 2047329A AIRCRAFT LOST POWER WHEN PERFORMING 'TOUGH AND GOES'. AIRCRAFT LANDED APPROXIMATELY 150 FEET FROM THE END OF THE RUNWAY . AN INVESTIGATION HAS DETERMINED THE MOST POSSIBLE CAUSE OF THE ENGINE'S POWER LOSS WAS AN EXHAUST VALVE THAT WAS INTE RMITTENTLY STUCK 'OPEN'. AIRCRAFT WAS SUBSTANTIALLY DAMAGED. 1 H 7 1 3O 3 O 3A19 E252 2000010800520 20000108 00520 EA 2000 1 8 2000ZZZX62 2 20000105 G 7322 1552113 AIRBOX CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA ENGINE MISREPAIRED H K NONE O OTHER IN INSP/MAINT 1 NE 03 13613 17262885 AIRCRAFT LANDED WITH A ROUGH RUNNING ENGINE WITH BLACK SMOKE EXITING FROM THE EXHAUST PIPE. UPON INSPECTION OF THE AIRB OX, NOTED THERE WAS SEAL MATERIAL MISSING FROM THE DIVERTER SEAL AND THAT A NUMBER OF AUTOMOTIVE STYLE POP RIVETS WERE M ISSING FROM A PREVIOUS REPAIR ON THE AIRBOX. THE SEAL WAS ALSO ADJUSTED WRONG SO THERE WAS PARTIAL CARBURETOR HEAT BEIN G APPLIED WHEN THE DASH CONTROL WAS IN THE CLOSED POSITION. THE CESSNA MM WAS USED AS A TROUBLESHOOTING GUIDE AND IT WA S DETERMINED THAT WITH PARTIAL CARBURETOR HEAT, THERE WAS LOW STATIC RPM RUN-UP, 2,050 RPM, MAG TIMING WAS OFF, RT MAG W AS SET FOR 30 - 31 DEGREES BTDC AND THE LT MAG WAS SET FOR 24 DEGREES BTDC, FACTORY SPEC IS 25 BTDC ON BOTH. 1 H 7 1 3O 3 O NT 3A12 E274 2000031700082 20000317 00082 2000 3 17 2000ZZZX620 1 20000203 G 2460 HARNESS FUSELAGE CHAFED B XE5R K NONE O OTHER IN INSP/MAINT 1 SW 21 292 CHAFING OF WIRE BUNDLES IS OCCURRING WHERE BUNDLES PASS THROUGH THE FUME SEALS INTO THE EFC BOX. SB 71-C716 ADDRESSES T HIS ISSUE. 2000031700083 20000317 00083 2000 3 17 2000ZZZX621 4 20000120 G 2562 DURACELLD BATTERY ACK E01 PIPER PA32 PA32RT300T 7103216 SO ELT DAMAGED B K NONE O OTHER IN INSP/MAINT 1 EA 23 2172B 013496 32R7987034 REMOVED ELT TO PERFORM INSPECTION PER FAR 91.2079D0. ELT WAS FOUND INOPERATIVE. DISASSEMBLY FOUND FOUR OF THE EIGHT BA TTERIES SPLIT. REPLACEMENT DATE WAS 3/03. 1 L 7 1 3O A3SO 2000031700084 20000317 00084 CE 2000 3 17 2000ZZZX622 1 20000119 G 5710 5368R STRUT BBAVIA 8 8KCAB 2110612 CE RT WING CORRODED H K NONE O OTHER IN INSP/MAINT 1 SO 05 2962Z 1548 37978 DURING ANNUAL INSPECTION, FOUND RT WING FORWARD LIFT STRUT, LOWER MOUNT AREA (ON STRUT) SEVERELY CORRODED (EXFOLIATION) AND CRACKED APPROXIMATELY 3 INCHES LONG FROM MOUNT BOLT HOLE UPWARD. AREA IS HIDDEN UNDER FAIRING. SPECIFIC CAUSE IS U NKNOWN. REPLACED PART WITH FACTORY NEW ITEM. SUBMITTER RECOMMENDED CLOSE ATTENTION TO COVERED AREAS DURING INSPECTIONS . 1 H 7 1 3O A21CE 2000031700085 20000317 00085 EU 2000 3 17 2000ZZZX623 1 20000201 G 2121 10089782105 COOLING FAN AMD FALC50 FALCON900 2700160 EU E/E BAY FAILED D A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 NM 03 14NA 1902 AFJ813 124 TWO HOURS AFTER TAKEOFF, A HEAVY ELECTRICAL ODOR AND SMELL WAS NOTICED BY THE CREW IN THE CENTER PEDESTAL AREA. A PRECA UTIONARY LANDING WAS EXECUTED. MAINTENANCE FOUND THE SOURCE OF THE SMOKE FROM THE NR 3 IRS COOLING FAN INVERTER. THE D EFECTIVE INVERTER AND FAN WERE REPLACED AND AN OPERATION CHECK OF THE SYSTEM PERFORMED. HONEYWELL TECH NEWSLETTER M23-3 341-011-00 ADDRESSES THIS PROBLEM AND SUGGESTS REPLACING THIS KIT. SUBMITTER STATED THE NEW KIT IS NOT ELIGIBLE FOR INS TALLATION ON THIS MODEL AIRCRAFT. 2 L 7 3 4F RT A46EU 2000031700086 20000317 00086 EU 2000 3 17 2000ZZZX624 1 20000201 G 2121 10089782105 COOLING FAN AMD FALC50 FALCON900 2700160 EU E/E BAY FAILED D A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 NM 03 14NA 1902 AFG863 124 TWO HOURS AFTER TAKEOFF, A HEAVY ELECTRICAL ODOR AND SMELL WAS NOTICED BY THE CREW IN THE CENTER PEDESTAL AREA. A PRECA UTIONARY LANDING WAS EXECUTED. MAINTENANCE FOUND THE SOURCE OF THE SMOKE FROM THE NR 3 IRS COOLING FAN INVERTER. THE D EFECTIVE INVERTER AND FAN WERE REPLACED AND AN OPERATION CHECK OF THE SYSTEM PERFORMED. HONEYWELL TECH NEWSLETTER M23-3 341-011-00 ADDRESSES THIS PROBLEM AND SUGGESTS REPLACING THIS KIT. SUBMITTER STATED THE NEW KIT IS NOT ELIGIBLE FOR INS TALLATION ON THIS MODEL AIRCRAFT. 2 L 7 3 4F RT A46EU 2000031700087 20000317 00087 SO 2000 3 17 2000ZZZX625 2 20000314 G 8520 633945 MANIFOLD CESSNA 421 421 2076010 CE CONT O520 GTSIO520D 17032 SO ENGINE CRACKED B S MI3R K NONE O OTHER IN INSP/MAINT 1 NM 09 3121K 42100102 DURING ANNUAL INSPECTION, A CRACK EXTENDING ABOUT 2 INCHES EACH SIDE OF THE THREADED BOSS. THE BOSS HAD BEEN DRILLED AN D TAPPED FOR A HELICOIL. THREADED BOSS IS FOR ATTACHING THE INTERCOOLER. 1 L 7 2 3O 3 O RT A7CE E7CE 2000031700088 20000317 00088 CE 2000 3 17 2000ZZZX626 1 20000314 G 5410 505403033 BEAM CESSNA 421 421 2076010 CE LT NACELLE CRACKED B MI3R K NONE O OTHER IN INSP/MAINT 1 NM 09 3121K 42100102 THE LEFT ENGINE AFT BEAM ASSEMBLY IS CRACKED. CRACK IS AT THE OUTBOARD BEAM ASSEMBLY (P/N 5054030-13) ATTACHMENT POINT AT THE TOP SIDE, AFT END, EXTENDING 1.1250 INCHES. THE OUTBOARD BEAM ASSEMBLY (5054030-13) ALSO HAD 3 RIVETS WITH HEADS MISSING ON THE INBOARD ROW OF RIVETS. THESE RIVETS ARE THE 7TH, 8TH, AND 9TH RIVETS COUNTING FORWARD FROM THE AFT BEAM ASSEMBLY. 1 L 7 2 3O RT A7CE 2000031700091 20000317 00091 EA 2000 3 17 2000ZZZX629 2 20000208 G 8530 SL14995 RETAINER CUP SLC36100B PIPER PA28 PA28180 7102808 SO LYC O360 O360A4A 41514 EA PUSH ROD HOUSING BROKEN D K NONE O OTHER IN INSP/MAINT 1 EA 07 3659R 346 285762 L1480036A ON ANNUAL INSPECTION, ROCKER COVERS REMOVED FOR GASKET LEAKS. FOUND PUSH ROD RETAINERS ON NR 1 AND NR 2 CYLINDERS BROKE N. THESE WERE SUPERIOR MILLENIUM CYLINDERS WITH 346 HRS SINCE NEW. SUBMITTER STATED PROBLEM IS BELIEVED TO BE INSUFFIC IENT SURFACE AREA FOR THE RETAINER TO SEAT AGAINST. 1 L 7 1 3O 3 O 2A13 E286 2000031700092 20000317 00092 2000 3 17 2000ZZZX630 4 20000208 G 2561 VS357017211 LIFE VEST SWITLIK CABIN FAILED B KQ1R K NONE W INADEQUATE Q C IN INSP/MAINT 1 EA 07 LIFE VEST FAILED MANUFACTURER'S RECOMMENDED 2 PSI TEST. DOM: MAY 1981. 2000031700093 20000317 00093 EA 2000 3 17 2000ZZZX631 1 20000214 G 3240 7010FS9545708 SEAL 50105201 CNDAIR CL600 CL6002B19 EA BRAKE ASSY LEAKING B XC4R K NONE K FLUID LOSS IN INSP/MAINT 1 SO 19 1236 JUN981360 BRAKE ASSEMBLY, P/N 5010520-1, FAILED PREMATURELY. ONE EACH PISTON LEAKING FROM INSULATOR AREA. PISTON INTERNALLY FILL ED WITH FLUID. EVIDENCE OF T-SEAL FAILURE. THIS IS A CONTINUAL DISCREPANCY. FACTORY NEW BRAKE ASSEMBLY. NOTE: OEM P ARTS INSTALLED IN BRAKE ASSEMBLY AND THE MOST RECENT BRAKE CONFIGURATION, P/N 5010520-1. 2 L 7 2 4F RT A21EA 2000031700094 20000317 00094 EA 2000 3 17 2000ZZZX632 1 20000214 G 3240 7010FS9545708 SEAL 50105201 CNDAIR CL600 CL6002B19 EA BRAKE ASSY LEAKING B XC4R K NONE K FLUID LOSS IN INSP/MAINT 1 SO 19 1842 APR981284 BRAKE ASSEMBLY, P/N 5010520-1, FAILED PREMATURELY. TWO EACH, PISTONS LEAKING FROM INSULATOR AREA. PISTONS INTERNALLY FI LLED WITH FLUID. EVIDENCE OF T-SEAL FAILURE. THIS IS A CONTINUAL DISCREPANCY. NOTE: OEM PARTS INSTALLED IN BRAKE ASS EMBLY AND THE MOST RECENT BRAKE CONFIGURATION, P/N 5010520-1. 2 L 7 2 4F RT A21EA 2000031700095 20000317 00095 SO 2000 3 17 2000ZZZX633 1 20000125 G 2140 764340 SHUT OFF VALVE PIPER PA30 PA30 7103002 SO HEATER WORN D O OTHER K FLUID LOSS NR NOT REPORTED 1 EA 23 8486Z 850 30227 VALVE FOUND LEAKING AFTER LANDING. FUEL HAD TRAVELED DOWN FORWARD BULKHEAD IN NOSE SECTION AND FOUND ITS WAY INSIDE AIR CRAFT BETWEEN BELLY SKINS AND GATHERED IN GEAR TRANSMISSION COMPARTMENT. O-RING IS EXPECTED TO HOLD BACK DIRECT FUEL PR ESSURE OF 26 POUNDS WHEN VALVE IS OPEN. VALVE SHOULD BE REPLACED WITH MORE MODERN DESIGN. HAVE FOUND OTHERS WHERE PACK ING NUT WAS NOT DRILLED FOR SAFETY WIRE. PACKING NUT SUBJECT TO ROTATION. 1 L 7 2 3O A1EA 2000031700096 20000317 00096 WP 2000 3 17 2000ZZZX634 1 20000203 G 7120 777111232 BOLT DOUG DC8 DC871F 302199D WP ENGINE MOUNT MISMANUFACTURED B K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 01 828BX 45993 DURING INSTALLATION AND TIGHTENING OF BOLTS THAT SECURE THE FORWARD ENGINE MOUNT TO THE PYLON, ONE BOLT BROKE IN TWO AND ANOTHER BOLT STRIPPED. THIS OCCURRED PRIOR TO THE BOLTS REACHING FINAL TORQUE. THIS IS CURRENTLY BEING INVESTIGATED B Y BOEING AND IS ALSO BEING TRACKED BY GEES SAFETY PRODUCT MANAGEMENT TEAM (SPMT). 2 L 7 4 4F RT 4A25 2000031700097 20000317 00097 SO 2000 3 17 2000ZZZX635 1 20000212 G 7922 53E19600 BYPASS VALVE LYC PIPER PA31 PA31350 7103110 SO OIL COOLER DAMAGED D O OTHER O OTHER NR NOT REPORTED 1 EA 07 202HF 2000 56713 317405437 LYCOMING SB 518C, DATED 5-2-95, STATES THAT THERMOSTATIC BYPASS VALVES (TBV), P/N 53E19600 WITH S/N/S 53788 AND HIGHER A RE NOT SUBJECT TO THE SB INSPECTION. DURING ENGINE REMOVAL, THE TBV (P/N 53E19600, S/N 56713) RETAINING NUT WAS FOUND S EPARATED FROM THE TBV AND LOCATED IN THE OIL COOLER. SUBMITTER RECOMMENDED TO REQUIRE HIGHER SERIAL NUMBERED TBV'S TO T HE INSPECTION REQUIREMENT OF THE SERVICE BULLETIN. 1 L 7 2 3O A20SO 2000031700099 20000317 00099 CE 2000 3 17 2000ZZZX637 1 20000120 G 2820 0700147137 LINE CESSNA 185 A185F 2072821 CE FUEL SYSTEM CRACKED H K NONE K FLUID LOSS IN INSP/MAINT 1 NM 11 714QK 140 18504410 FUEL PRESSURE LINE BROKEN AT FITTING (FIREWALL TO ENGINE). 1 H 7 1 3O 3A24 2000031700100 20000317 00100 CE 2000 3 17 2000ZZZX638 1 20000314 G 3230 508202043 DRAG BRACE BEECH 90 65A90 1152908 CE NLG CRACKED H P K NONE O OTHER IN INSP/MAINT 1 SW 99 615AA LJ298 DURING AN AFTER-FLIGHT INSPECTION OF THE NOSE WHEEL BAY AREA, A CRACK WAS NOTICED EXTENDING FROM THE LUBRICATOR UPON THE NLG BRACE. UPON INSPECTION, NOTED THIS NLG BRACE WAS OF THE OLDER STYLE. 1 L 7 2 3T 3A20 2000031700115 20000317 00115 CE 2000 3 17 2000ZZZX640 1 20000203 G 2140 721526 PUMP CESSNA 310 310R 2074245 CE HEATER FAILED B BXSR O OTHER O OTHER NR NOT REPORTED 1 EA 09 123RA 2 310R0221 PILOT REPORTED THE HEATER WAS INOPERATIVE. TROUBLESHOOTING FOUND THE HEATER FUEL PUMP HAD FAILED, AND THAT IT WAS PUMPI NG FUEL OUT AROUND THE PUMP SHAFT. (X) 1 L 7 2 3O 3A10 2000031700116 20000317 00116 EA 2000 3 17 2000ZZZX641 1 20000208 G 3240 7010FS9545708 SEAT 50105201 CNDAIR CL600 CL6002B19 EA BRAKE ASSY LEAKING B XC4R K NONE K FLUID LOSS IN INSP/MAINT 1 SO 19 821 JUN981357 BRAKE ASSEMBLY, P/N 5010520-1, FAILED PREMATURELY. ONE EACH, PISTON LEAKING FROM INSULATOR AREA. PISTON INTERNALLY FIL LED WITH FLUID. EVIDENCE OF T-SEAL FAILURE. THIS IS A CONTINUAL DISCREPANCY. NOTE: OEM PARTS INSTALLED IN BRAKE ASSE MBLY AND THE MOST RECENT BRAKE CONFIGURATION, P/N 5010520-1. (X) 2 L 7 2 4F RT A21EA 2000031700117 20000317 00117 CE 2000 3 17 2000ZZZX642 1 20000203 G 7820 WO7501612989 MUFFLER CESSNA 185 A185F 2072821 CE EXHAUST DAMAGED D O OTHER O OTHER NR NOT REPORTED 1 SW 99 1164Q 131 18503465 MUFFLER TAILPIPE BROKEN LOSE FROM BODY. DEFECT NOTED TO BE CRACKS IN A VERY UNUSUAL AREA. NOT A WELD OF BODY AND TAILP IPE. SUSPECT MUFFLER SHELL/BODY MATERIAL PROBLEM PART WAS NEW MANUFACTURE WITH 131 HOURS TOTAL TIME. SHOWED NO SIGN OF ADVERSE STRESS. (X) 1 H 7 1 3O 3A24 2000031700118 20000317 00118 CE 2000 3 17 2000ZZZX643 1 20000114 G 5610 10138402516 WINDSHIELD BEECH 200 B200 1152922 CE COCKPIT BROKEN D O OTHER O OTHER NR NOT REPORTED 1 SW 99 63791 1644 94225H2048 BB1100 1-14-00 - FLYING AT 27,000 FEET, THE RIGHT SIDE COPILOT WINDWHIELD BROKE ON THE INSIDE PORTION OF THE WINDOW. THE OUTSI DE PORTION OF THE WINDSHIELD REMAINED INTACT. THE CREW DEPRESSURIZED THE CABIN PER EMERGENCY PROCEDURES AND RETURNED TO PDX. 1-16-00 - AFTER LANDING ON 1-14-00, THE AIRCRAFT REMAINED ON THE GROUND UNTIL TH E WINDSHIELD WAS REPLACED ON 1-1 6-00. (X) 1 L 7 2 4T A24CE 2000031700119 20000317 00119 CE 2000 3 17 2000ZZZX644 1 20000203 G 2820 30J156401 LINE CESSNA 500 550 2076604 CE RT ENGINE LEAKING D K NONE K FLUID LOSS IN INSP/MAINT 1 SO 06 627L 660 5500843 AFTER FLIGHT WHEN PILOT CHECKED RIGHT ENGINE OIL GAUGE. PILOT FOUND FUEL AND SMOKE FUMES IN RIGHT ENGINE BOTTOM COWLING . REMOVED BOTTOM COWLING, FOUND PIN HOLE IN LINE. (X) 1 L 7 2 4F A22CE 2000031700120 20000317 00120 CE 2000 3 17 2000ZZZX645 1 20000202 G 2820 S1236C30350 HOSE CESSNA 206 U206G 2073356 CE ENGINE BAY LEAKING B K NONE K FLUID LOSS IN INSP/MAINT 1 GL 15 68RS U20605503 DURING ANNUAL INSPECTION, FOUND ABOVE MENTIONED HOSE LEAKING PROFUSELY. THE HOSE APPEARED TO BE SUPPORTED PROPERLY. WH EN FUEL PRESSURE WAS APPLIED WITH AIRCRAFT ELECTRIC BOOST PUMP, FUEL BEGAN COMING OUT OF BRAIDED, CRIMPED AREA NEAR THE END OF THE HOSE. AD 71-24-04 DOES NOT APPLY TO THIS MODEL NUMBER AND SERIAL NUMBER OF AIRCRAFT. SE 71-7, SUPPLEMENT 1, DATED 11-3-71, ENCOMPASSES ALL CESSNA SINGLE ENGINE AIRCRAFT. (X) 1 H 7 1 3O A4CE 2000031700122 20000317 00122 EA 2000 3 17 2000ZZZX647 2 20000110 G 7414 10382681 CAPACITOR 66E21576 MAULE M7 M7235 5460170 SO LYC O540 O540J1A5 41532 EA MAGNETO FAILED C K NONE O OTHER IN INSP/MAINT 1 SO 21 783SP 1 G109900C 4101C L2076840A PROBLEM STARTED WITH INSTALLATION OF NEW TCM HARNESS IGNITION SYSTEM. RESULTED IN REPEATED FAILURES IN MAGNETO ON ONE S IDE OR OTHER (I.E., LEFT AND RIGHT). MAGNETOS WERE REMOVED AND CHECKED. POINTS AND CAPACITORS REPLACED. ENGINE AND AIR FRAME ELECTRICS CHECKED OK. CAPACITOR BATCH NR 9920 FOUND DEFECTIVE. REPLACED WITH NR 9948. OK TO-DATE, 1-24-00. (X) 1 H 7 1 3O 3 O NC 3A23 E295 2000031700123 20000317 00123 CE 2000 3 17 2000ZZZX648 1 20000315 G 3230 22411027 PIVOT ASSY CESSNA 182 R182 2072734 CE MLG CRACKED B S A SMTR K NONE O OTHER IN INSP/MAINT 1 EA 17 2394S 5460 R18201336 SUBMITTER STATED FOUND FIVE OTHER PIVOTS WITH THE SAME CRACK. ALL OTHER PIVOTS HAVE 4,500 HOURS TOTAL TIME OR MORE. PO SSIBLE CAUSE UNKNOWN. (X) 1 H 7 1 3O RT 3A13 2000031700124 20000317 00124 CE 2000 3 17 2000ZZZX649 1 20000110 G 2820 0700147137 LINE CESSNA 185 A185F 2072821 CE FUEL SYSTEM BROKEN D K NONE O OTHER IN INSP/MAINT 1 NM 11 714SD 10 18504418 FUEL PRESSURE LINE BETWEEN ENGINE (BAFFLE) AND FFIREWAL BROKEN AT SILVER SOLDER JOINT. (X) 1 H 7 1 3O 3A24 2000031700125 20000317 00125 CE 2000 3 17 2000ZZZX650 1 20000110 G 2820 0700147137 LINE CESSNA 185 A185F 2072821 CE FUEL SYSTEM BROKEN D K NONE O OTHER IN INSP/MAINT 1 NM 11 714SD 300 18504418 FUEL PRESSURE LINE BETWEEN ENGINE AND FIREWALL BROKEN AT SILVER SOLDER JOINT. (X) 1 H 7 1 3O 3A24 2000031700127 20000317 00127 WP 2000 3 17 2000ZZZX652 1 20000211 G 5320 AEA0161 WEB DOUG DC10 DC1010 3022110 WP RT MLG WW CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 99 364FE 46600 DURING MAINTENANCE, 3.0 INCH CRACK WAS FOUND ON RIGHT/CENTER WHEELWELL WEB. CRACK AFFECTED UPPER SPLICE WEB, P/N AEA016 1-1, RT SIDE, AND AEA0501-1. (X) 2 L 7 3 4F A22WE 2000031700128 20000317 00128 WP 2000 3 17 2000ZZZX653 1 20000211 G 5320 AEA0501 WEB DOUG DC10 DC1010 3022110 WP RT MLG WW CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 99 389FE 46623 DURING MAINTENANCE, A 3.75 INCH CRACK WAS FOUND ON RIGHT/CENTER WHEELWELL WEB. CRACK AFFECTED KEEL WEB UPPER SPLICE ONL Y, P/N AEA0501. (X) 2 L 7 3 4F A22WE 2000031700129 20000317 00129 WP 2000 3 17 2000ZZZX654 1 20000211 G 5320 AEA0161 WEB DOUG DC10 DC1010 3022110 WP RT MLG WW CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 99 374FE 46612 DURING MAINTENANCE, THREE 10 INCH CRACKS WERE FOUND ON RIGHT/CENTER WHEELWELL (Y=1386, Z=52) COMMON TO KEEL WEB, WEB DOU BLER, AND UPER WEB SPLICE, P/N'S, AEA0161-3, AEA0161-153, AND AEA0501 RESPECTIVELY. DATA WAS SENT TO BOEING/DOUGLAS 5- 14-99 AND RESENT 7-9-99, WITH NO RESPONSE. (X) 2 L 7 3 4F A22WE 2000031700131 20000317 00131 CE 2000 3 17 2000ZZZX656 1 20000209 G 7931 77041 SWITCH CESSNA 182 182S 2072701 CE ENGINE OIL FAILED D O OTHER O OTHER NR NOT REPORTED 1 CE 01 9539L 1005 18280185 OIL PRESSURE SWITCH FAILED IN-FLIGHT. LOST 7-1/2 QUARTS OF OIL IN 20 MINUTE FLIGHT. HAS 9 QUART SUPPLY. SWITCH FAILED AT PLASTIC HOUSING. SINCE OIL GOES UNDER AND ON BELLY, HAVE NO IDEA OF OIL LEAK IN-FLIGHT. CESSNA SAID IT HAS HAD AT LEAST 4 FAILURES. (X) 1 H 7 1 3O NT 3A13 2000031700135 20000317 00135 2000 3 17 2000ZZZX660 1 20000103 G 3350 POWER SUPPLY AMTR KITFOXSPEEDS CABIN WRONG PART B R2JR K NONE W INADEQUATE Q C IN INSP/MAINT 1 EA 21 193SC SC47101 DURING MAINTENANCE, FOUND MODEL PS823 EMERGENCY POWER SUPPLY INCORRECTLY REPLACED WITH PS835 EMERGENCY POWER SUPPLY. TH OUGH SIMILAR, THESE UNITS ARE NOT DIRECT REPLACEMENTS FOR ONE ANOTHER. WIRING CHANGES ARE REQUIRED PER JET/BF GOODRICH SERVICE DATA. AIRCRAFT ALTERED PER APPROVED DATA. (X) 0 2000032300572 20000323 00572 EA 2000 3 23 2000ZZZX713 2 20000217 G 7313 INJECTOR NOZZLE CESSNA 172 172R 2072401 CE LYC IO360 IO360L2A EA ENGINE FAILED H O OTHER R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 SW 99 498ER 848 17280674 L2786151A PILOT EXPERIENCED A BRIEF ROUGHNESS IN CRUISE. THREE FUEL INJECTOR NOZZLES WERE CHANGED. 1 H 7 1 3O 3 O NT 3A12 1E10 2000032300574 20000323 00574 EA 2000 3 23 2000ZZZX715 2 20000118 G 8550 LW15688 TUBE CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA OIL SUMP DISCONNECTED B O OTHER O OTHER NR NOT REPORTED 1 SO 13 5246B 769 15283815 RL1871015 INDUCTION TUE ATTACHED TO OIL SUMP BECAME LOOSE CAUSING ROUGH RUNNING ENGINE. ENGINE OIL SUMP REPLACED TO CORRECT PROBL EM. SUBMITTER STATED THIS IS SECOND ENGINE FOUND WITH THIS CONDITION ON FACTORY OVERHAULED ENGINE. 1 H 7 1 3O 3 O NT 3A19 E223 2000032300575 20000323 00575 CE 2000 3 23 2000ZZZX716 1 20000223 G 5280 10541000057 CHANNEL BEECH 76 76 1153005 CE NLG DOOR CRACKED H BF8S K NONE O OTHER IN INSP/MAINT 1 WP 07 6632R 9438 ME236 THE CHANNEL AND CHANNEL SUPPORT ARE NOSE GEAR DOOR LINKAGE SUPPORT STRUCTURES. DURING A ROUTINE INSPECTION, THESE ITEMS WERE FOUND TO BE CRACKED AND HAD SHIFTED POSITION WITHIN THE NOSE TUNNEL STRUCTURE. EVEN A SMALL CHANGE IN THE POSITIO N OF THESE PARTS CHANGES THE NOSE GEAR DOOR RIGGING CAUSING THE NOSE GEAR TO LOCK IN THE UP POSITION. FORCE BUILD-UP FR OM THE HYDRAULIC ACTUATOR ATTEMPTING TO LOWER THE NOSE GEAR BROKE THE CHANNEL LOOSE FROM THE NOSE STRUCTURE AND THEN AL LOWED THE NOSE GEAR TO COME DOWN AND LOCK. 1 L 7 2 3O A29CE 2000032300576 20000323 00576 CE 2000 3 23 2000ZZZX717 1 20000223 G 5280 105410000199 SUPPORT BEECH 76 76 1153005 CE NLG DOOR CRACKED H BF8S K NONE O OTHER IN INSP/MAINT 1 WP 07 6632R 9438 ME236 THE CHANNEL AND CHANNEL SUPPORT ARE NOSE GEAR DOOR LINKAGE SUPPORT STRUCTURES. DURING A ROUTINE INSPECTION, THESE ITEMS WERE FOUND TO BE CRACKED AND HAD SHIFTED POSITION WITHIN THE NOSE TUNNEL STRUCTURE. EVEN A SMALL CHANGE IN THE POSITIO N OF THESE PARTS CHANGES THE NOSE GEAR DOOR RIGGING CAUSING THE NOSE GEAR TO LOCK IN THE UP POSITION. FORCE BUILD-UP FR OM THE HYDRAULIC ACTUATOR ATTEMPTING TO LOWER THE NOSE GEAR BROKE THE CHANNEL LOOSE FROM THE NOSE STRUCTURE AND THEN AL LOWED THE NOSE GEAR TO COME DOWN AND LOCK. 1 L 7 2 3O A29CE 2000032300578 20000323 00578 CE 2000 3 23 2000ZZZX719 1 20000210 G 2701 605241603 YOKE BEECH 36 A36 1151604 CE CONTROL COLUMN DAMAGED H P K NONE O OTHER IN INSP/MAINT 1 SW 99 7231Y 2301 E2288 UPON INSP OF CONTROL COLUMNS AND EQUIP, FOUND THE ONLY 4 RIVETS (MS20470AD5) SECURING PILOTS CONTROL COLLAR TO THE YOKE WORKING IN SHEAR CAUSING SLOPPY FEEL IN THE YOKE. SUBMITTER STATED IF RIVETS WERE TO SHEAR, COMPLETE LOSS OF PITCH AND ROLL CONTROL WOULD HAVE OCCURRED. COLUMN AND YOKE REMOVED AND NEW RIVETS THE NEXT DIAMETER UP (MS20470AD6-6) INSTALLED AS A REPAIR UNDER A.C. 43.13 1B, SECT 4-57 PARA 4(B). ACFT MFG NOTIFIED AND IT WAS SUGGESTED TO INSTALL ADDITIONAL RIV ETS IN THIS COLLAR FOR FUTURE REPAIRS. THE CONTROL WHEEL COLLAR IS ATTACHED AT OPPOSITE END WITH 8 RIVETS (MS-20470AD5) . SUBMITTER SUGGESTED AD BE MADE TO ADDRESS THIS ISSUE, ALL BEECH BONANZAS, BARONS WITH DUAL CONTROL COLUM INSTALLS. 1 L 7 1 3O 3A15 2000032300579 20000323 00579 CE 2000 3 23 2000ZZZX720 1 20000216 G 5510 NAS12918 NUT CESSNA 425 425 2076018 CE HORIZ STABILIZER SPLIT H K NONE O OTHER IN INSP/MAINT 1 SW 99 8FR 608 4250095 DURING A PHASE INSPECTION, THE LEFT NUT THAT RETAINS THE HORIZONTAL STABILIZER WAS FOUND SPLIT FROM TOP TO BOTTOM. RECO RDS SHOW THAT SB CQB 85-25 AND AD 85-25-11 WERE C/W IN 1986. THE SB AND AD ADDRESS THIS PROBLEM. THE NUT THAT SPLIT AP PEARS TO HAVE BEEN THE IMPROVED REPLACEMENT CALLED OUT FOR IN THE AD AND SB. 1 L 7 2 3T RT A7CE 2000032300580 20000323 00580 2000 3 23 2000ZZZX721 4 20000207 G 3416 INDICATOR KOLLSMAN 671CK UNIVAR 415 415C 0420302 NM COCKPIT FAILED G O OTHER O OTHER NR NOT REPORTED 1 EA 17 99248 1 67501 1871 DURING FIRST HOUR OF FLIGHT WITH FRESHLY OVERHAULED INSTRUMENT, THE 100 FOOT HAND STOPPED WORKING. AFTER REMOVAL OF THE INSTRUMENT, NOTICED SHAFT FOR THE HAND HAD DISENGAGED INTERNALLY. BY TILTING THE ALTIMETER, THE SHAFT COULD BE RE-ENG AGED WITH THE INTERNAL MECHANISM, BUT WHEN TILTED TO SIMULATE A CLIMB ATTITUDE, IT WOULD ONCE AGAIN DISENGAGE AND BECOME INOPERATIVE. OVERHAULED 8/99. 1 L 7 1 3O A718 2000032300581 20000323 00581 SO 2000 3 23 2000ZZZX722 1 20000214 G 2140 B350091E881EL HEATER PIPER PA34 PA34220T 7103420 SO CABIN FAILED B A FE6R O OTHER W INADEQUATE Q C NR NOT REPORTED 1 NM 11 9265Q 1 A98030046 3449077 THE PILOT ATTEMPTED TO USE THE HEATER ON A NEW AIRCRAFT WITHOUT SUCCESS. THE CIRCUIT BREAKER TRIPPED. REPAIRS WERE MAD E TO OVERHEATED WIRING. HEATER FAILED AGAIN ON NEXT FLIGHT. MAINTENANCE REMOVED THE HEATER FROM THE AIRCRAFT FOR INVES TIGATION, WITH A TOTAL OF .5 HOURS ON THE HEATER HOBBS SINCE NEW. INTERNAL VENT BLOWER FAN (PIPER P/N 753-201) SEPARATE D FROM HUB ARBOR. PRESSURE DIFFERENTIAL SWITCH (JAN AERO P/N 94E42-3). PNEUMATIC FITTING COMPLETELY STRIPPED IN UNIT BO DY. LARGE DRILL SHAVING IN THE FUEL INLET LINE SOLENOID VALVE. 1 L 7 2 3O A7SO 2000032300584 20000323 00584 CE 2000 3 23 2000ZZZX725 1 20000204 G 7810 1099500001 STACK BEECH 90 C90A 1152911 CE EXHAUST CRACKED B BQVR K NONE O OTHER IN INSP/MAINT 1 EA 01 600FL 33 LJ1540 RIGHT ENGINE INBOARD EXHAUST STACK FOUND TO BE CRACKED .75 INCH APPROXIMATELY ONE-THIRD WAY AROUND CIRCUMFERENCE AT WELD ATTACH POINT NACELLE INLET DEICE TUBE. A RAYTHEON REP HAS BEEN CONTACTED AND A FUTURE SERVICE BULLETIN IS PENDING RELE ASE. 1 L 7 2 3T RT 3A20 2000032300585 20000323 00585 CE 2000 3 23 2000ZZZX726 1 20000224 G 7810 1099500001 STACK BEECH 90 C90A 1152911 CE EXHAUST CRACKED B BQVR K NONE O OTHER IN INSP/MAINT 1 EA 01 600FL 206 LJ1540 CRACKED EXHAUST STACK. THREE OTHER M OR D REPORTS SUBMITTED FOR SAME PROBLEM. A RAYTHEON REP HAS BEEN CONTACTED AND A FUTURE SERVICE BULLETIN IS PENDING RELEASE. 1 L 7 2 3T RT 3A20 2000032300586 20000323 00586 GL 2000 3 23 2000ZZZX727 2 20000115 G 7323 23065121 GOVERNOR BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL ENGINE MALFUNCTIONED B L A VBVR A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 SW 09 35WH 1266 21482 2736 CAE836154 IN CRUISE FLIGHT, THE POWER TURBINE ROTOR DROOPED TO 90 PERCENT AND WOULD NOT RECOVER. THE PILOT LOWERED COLLECTIVE, RE COVERED ROTOR SPEED AND DID A POWER ON RECOVERY. 1 G 7 1 3U 3 U H2SW E4CE 2000032300587 20000323 00587 EA 2000 3 23 2000ZZZX728 1 20000207 G 3230 UNIVERSAL ACQCOR F22 F22 8850908 EA RT MLG FAILED G A O OTHER O OTHER NR NOT REPORTED 1 SW 05 92K 383 006 UNIVERSAL JOINT FAILED DURING GEAR RETRACTION PHYSICALLY SEPARATING RIGHT LANDING GEAR SCREW JACK FROM RETRACT SYSTEM. C OULD NOT MANUALLY EXTEND GEAR DUE TO SEPARATION OF ABOVE UNIVERSAL JOINT. UNIVERSAL JOINT HAS 2 PINS PRESSED THROUGH FO RK INTO THE ARTICULATING PORTION OF THE JOINT. NO PROVISION IS MADE FOR RETENTION OF PINS EXCEPT FOR PRESSURE FIT. APP ROXIMATELY 430 CYCLES. 1 H 7 1 3O NC 1A9 2000041700070 20000417 00070 SW 2000 4 17 2000ZZZX803 1 20000223 G 5302 407023800118S SUPPORT BRACKET 407030801101 BELL 407 407 SW TAILBOOM CRACKED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 577AL 3773 53185A 53247 DURING DAILY INSPECTION, FOUND CRACK IN RADIUS. 1 G 7 1 3U O H2SW 2000041300292 20000413 00292 SW 2000 4 13 2000ZZZX804 1 20000220 G 6510 407340339103 BEARING BELL 407 407 SW TAIL ROTOR WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 407AL 979 K980828 53044 DURING DAILY INPSECTION FOUND BEARINGS WORN, AXIAL PLAY. 1 G 7 1 3U O H2SW 2000041300293 20000413 00293 SW 2000 4 13 2000ZZZX805 1 20000220 G 6510 407340339103 BEARING BELL 407 407 SW TAIL ROTOR WORN B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 407AL 979 K980784 53044 DURING DAILY INPSECTION FOUND BEARINGS WORN, AXIAL PLAY. 1 G 7 1 3U O H2SW 2000041700074 20000417 00074 SW 2000 4 17 2000ZZZX808 1 20000209 G 6510 206061432121 HOUSING 407040303105 BELL 407 407 SW BLOWER CRACKED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 627AL AFS1013 53284 DURING DAILY INSPECTION, BLOWER HOUSING FOUND CRACKED. 1 G 7 1 3U O H2SW 2000041300296 20000413 00296 SW 2000 4 13 2000ZZZX809 1 20000203 G 6510 407340339103 BEARING 407040730310 BELL 407 407 SW TAIL ROTOR ROUGH B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 407AL 745 E990600 53044 DURING DAILY INSPECTION BOTH BEARINGS FOUND ROUGH. 1 G 7 1 3U O H2SW 2000041300297 20000413 00297 SW 2000 4 13 2000ZZZX810 1 20000203 G 6510 407340339103 BEARING 407040730310 BELL 407 407 SW TAIL ROTOR ROUGH B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 407AL 745 E990604 53044 DURING DAILY INSPECTION BOTH BEARINGS FOUND ROUGH. 1 G 7 1 3U O H2SW 2000041300298 20000413 00298 SW 2000 4 13 2000ZZZX811 1 20000204 G 6210 206015001107 BLADE BELL 206 206L1 1182107 SW MAIN ROTOR CORRODED B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 3179S 2664 A2472 45781 DURING DAILY INSPECTION, CORROSION AND DEBONDED AT ROOT END GRIP PLATE. 1 G 7 1 3U H2SW 2000041300300 20000413 00300 GL 2000 4 13 2000ZZZX813 2 20000131 G 7261 E23001832 NOZZLE ALLSN 250C 250C30 03013 GL PT OIL MISDRILLED B ALGR K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 CAT98100 HOLES IN UPPER PART OF NOZZLE DRILLED IMPROPERLY, DISCOVERED ON SHELF. PART WAS NEW AND SUBMITTER STATED THIS WAS DONE DURING MANUFACTURING. NOTE: SHOULD HAVE 4 HOLES. 3 U E1GL 2000041300302 20000413 00302 GL 2000 4 13 2000ZZZX815 2 20000131 G 7261 E23001832 NOZZLE ALLSN 250C 250C30 03013 GL PT OIL MISDRILLED B ALGR K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 CAT95221 HOLES IN UPPER PART OF NOZZLE DRILLED IMPROPERLY, DISCOVERED ON SHELF. PART WAS NEW AND SUBMITTER STATED THIS WAS DONE DURING MANUFACTURING. NOTE: SHOULD HAVE 4 HOLES. 3 U E1GL 2000041300303 20000413 00303 GL 2000 4 13 2000ZZZX816 2 20000131 G 7261 E23001832 NOZZLE ALLSN 250C 250C20 03013 GL PT OIL MISDRILLED B ALGR K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 CAT44377 HOLES IN UPPER PART OF NOZZLE DRILLED IMPROPERLY, DISCOVERED ON SHELF. PARTS WAS NEW AND SUBMITTER STATED THIS WAS DONE DURING MANUFACTURING. NOTE: SHOULD HAVE 4 HOLES. 3 U E4CE 2000041300304 20000413 00304 GL 2000 4 13 2000ZZZX817 2 20000131 G 7261 E23001832 NOZZLE ALLSN 250C 250C30 03013 GL PT OIL MISDRILLED B ALGR K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 CAT44316 HOLES IN UPPER PART OF NOZZLE DRILLED IMPROPERLY, DISCOVERED ON SHELF. PART WAS NEW AND SUBMITTER STATED THIS WAS DONE DURING MANUFACTURING. NOTE: SHOULD HAVE 4 HOLES. 3 U E1GL 2000041300305 20000413 00305 GL 2000 4 13 2000ZZZX818 2 20000131 G 7261 E23001832 NOZZLE ALLSN 250C 250C30 03013 GL PT OIL MISDRILLED B ALGR K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 CAT90149 HOLES IN UPPER PART OF NOZZLE DRILLED IMPROPERLY, DISCOVERED ON SHELF. PART WAS NEW AND SUBMITTER STATED THIS WAS DONE DURING MANUFACTURING. NOTE: SHOULD HAVE 4 HOLES. 3 U E1GL 2000041300306 20000413 00306 GL 2000 4 13 2000ZZZX819 2 20000131 G 7261 E23001832 NOZZLE ALLSN 250C 250C30 03013 GL PT OIL MISDRILLED B ALGR K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 CAT95422 HOLES IN UPPER PART OF NOZZLE DRILLED IMPROPERLY, DISCOVERED ON SHELF. PART WAS NEW AND SUBMITTER STATED THIS WAS DONE DURING MANUFACTURING. NOTE: SHOULD HAVE 4 HOLES. 3 U E1GL 2000041300312 20000413 00312 EA 2000 4 13 2000ZZZX827 2 20000308 G 7414 10382681H CAPACITOR BENDIX 66E21576 CESSNA 182 R182 2072734 CE LYC O540 O540L3C5 41532 EA MAGNETO FAILED D K NONE O OTHER IN INSP/MAINT 1 GL 15 4689S 35 F259910G R18200591 L2225140A NEW CAPACITOR INSTALLED TO SATISFY TCM CSB662A FAILED ON FIRST ENGINE RUN AFTER INSTALLATION. DATE CODE ON FAILED CAPAC ITOR IS 00-08. FAILURE WAS INTERMITTENT DURING 15 MINUTE ENGINE RUN-UP. 1 H 7 1 3O 3 O RT 3A13 E295 2000061600335 20000616 00335 WP 2000 6 16 2000ZZZX828 1 20000222 G 6520 369D2512511 PINION GEAR HUGHES 369D25100505 HUGHES 369 369D 4470706 WP TRANSMISSION FAILED H S1EM A UNSCHED LANDING E VIBRATION/BUFFET NR NOT REPORTED 1 WP 09 4575Z 7931 1778 U0215 370094D AIRCRAFT WAS FLYING WHEN A NOISE WAS HEARD. A PRECAUTIONARY LANDING WAS MADE. THE PROBLEM WAS A BROKEN GEAR IN THE MAI N TRANSMISSION. THE BROKEN PART WAS SENT TO THE MANUFACTURER FOR EVALUATION. 1 G 7 1 3U H3WE 2000041300313 20000413 00313 CE 2000 4 13 2000ZZZX829 1 20000219 G 2721 12606323 SPROCKET CESSNA 207 207A 2073604 CE RUDDER TRIM MISMANUFACTURED E K NONE W INADEQUATE Q C IN INSP/MAINT 1 AL 01 7384U 20700431 AFTER INSTALLATION OF PART, OPS CHECK FOUND TRIM CHAIN TO RIDE NORMALLY FOR TWO-THIRDS OF TURN ON SPACER BEFORE RIDING U PON TEETH OF SPROCKET AND JUMPING OFF. INSPECTED SPROCKET AND DETERMINED SOME OF THE TEETH MISS-CUT UPON MANUFACTURE. 1 H 7 1 3O A16CE 2000041300314 20000413 00314 CE 2000 4 13 2000ZZZX830 1 20000327 G 8011 6462751 STARTER CESSNA 207 207A 2073604 CE ENGINE MISREPAIRED B CY4R K NONE W INADEQUATE Q C IN INSP/MAINT 1 AL 03 73503 17 R079210 20700559 UPON DISASSEMBLY OF STARTER, INCORRECT PRESTOLITE BRUSHES, PN MDL-1063B, WERE FOUND INSTALLED. THE STARTER IS TCM, BUT THE BRUSHES ARE PRESTOLITE. TCM BRUSHES ARE .50 INCH LONG. PRESTOLITE BRUSHES ARE .75 INCH LONG. 1 H 7 1 3O A16CE 2000041300315 20000413 00315 SO 2000 4 13 2000ZZZX831 2 20000226 G 7414 M3050 IMPULSE COUPLING SLICK 6310 CESSNA 206 U206F 2073333 CE CONT O520 IO520F 17032 SO MAGNETO FAILED H K NONE O OTHER IN INSP/MAINT 1 SO 15 123TM 91120142 U20601768 247629R THE IMPULSE COUPLING ENGAGES ONLY 1 OUT OF 5 TIMES WHEN PROPELLER IS TURNED BY HAND. THE SPRING WHICH HOLDS THE PAWL OU T TO ENGAGE IMPULSE COUPLING HAS NOT BROKEN BUT HAS TOTALY LOST ITS SPRING EFFECT. 1 H 7 1 3O 3 O A4CE E5CE 2000041300316 20000413 00316 SW 2000 4 13 2000ZZZX832 1 20000124 G 6230 406010418101 SWASHPLATE BELL 407 407 SW MAIN ROTOR DAMAGED B IIFR K NONE O OTHER IN INSP/MAINT 1 SW 03 407JR 1193 A1353 53245 SWASHPLATE SEAL, PN 406-310-407-101, WORE GROOVE IN CAP, P/N 406-010-418-101, CAUSING GREASE FROM BEARINGS BELOW TO ENTE R TOP OF SWASHPLATE OUTER EDGE UNDER BOOT. THIS CAN ALLOW GREASE TO CONTAMINATE TEFLON LINED RACES OF UNIBALL ASSEMBLY RESULTING IN CHANGES OF SWASHPLATE FRICTION SETTING WHICH CAUSES STIFFNESS IN CYCLIC AND COLLECTIVE CONTROL INPUTS. SUB MITTER RECOMMENDED CAP BE MADE OF TOUGHER MATERIAL TO PREVENT DAMAGE FROM SEAL, P/N 406-310-407-101. 1 G 7 1 3U O H2SW 2000041700089 20000417 00089 SW 2000 4 17 2000ZZZX833 1 20000208 G 6321 D01661 PAD BELL 407 407 SW ROTOR BRAKE WORN B IIFR K NONE O OTHER IN INSP/MAINT 1 SW 03 407AK 819 905 53269 DURING REMOVAL OF ROTOR BRAKE CALIPER ASSEMBLIES, FOUND GUIDE HOLES ON PAD ASSY AND GUIDE BOLTS WORN. BOLT, PN D0166-1, WORN IN EXCESS OF 50 PERCENT OF BOLT DIAMETER. PAD ASSY, PN D0163-1, GUIDE HOLES WORN IN EXCESS OF 65 PERCENT OF WALL T HICKNESS. POSSIBLE CAUSE OF PREMATURE WEAR MAY BE FROM EXCESSIVE VIBRATION AND SMALL AREA OF CONTACT AT BOLT AND PAD AS SY GUIDE HOLES. SUBMITTER RECOMMENDED INSPECTION OF BOLTS AND PAD ASSEMBLIES EVERY 600 HOURS. 1 G 7 1 3U O H2SW 2000041700090 20000417 00090 SW 2000 4 17 2000ZZZX834 1 20000208 G 6321 D01661 PAD BELL 407 407 SW ROTOR BRAKE WORN B IIFR K NONE O OTHER IN INSP/MAINT 1 SW 03 407AK 819 907 53269 DURING REMOVAL OF ROTOR BRAKE CALIPER ASSEMBLIES, FOUND GUIDE HOLES ON PAD ASSY AND GUIDE BOLTS WORN. BOLT, PN D0166-1, WORN IN EXCESS OF 50 PERCENT OF BOLT DIAMETER. PAD ASSY, PN D0163-1, GUIDE HOLES WORN IN EXCESS OF 65 PERCENT OF WALL T HICKNESS. POSSIBLE CAUSE OF PREMATURE WEAR MAY BE FROM EXCESSIVE VIBRATION AND SMALL AREA OF CONTACT AT BOLT AND PAD AS SY GUIDE HOLES. SUBMITTER RECOMMENDED INSPECTION OF BOLTS AND PAD ASSEMBLIES EVERY 600 HOURS. 1 G 7 1 3U O H2SW 2000041300317 20000413 00317 EA 2000 4 13 2000ZZZX836 1 20000302 G 5320 MS21905 FITTING CNDAIR CL600 CL6001A11 1900302 EA HYDRAULIC LINE CRACKED C K NONE O OTHER IN INSP/MAINT 1 WP 15 751DB 7950 1075 IN THE LAST 2 MONTHS HAVE FOUND 3 T-FITTINGS CRACKED AND LEAKING. (TWO ON 600 CHALLENGER, ONE ON 601). ONE DID CAUSE AN INTERRUPTION OF A FLIGHT. ALL THREE ARE ALUMINUM FITTINGS THAT HAD NOT BEEN DISTURBED SINCE MANUFACTURE. 2 L 7 2 4F RT A21EA 2000041300318 20000413 00318 EA 2000 4 13 2000ZZZX837 1 20000302 G 5320 MS21905 FITTING CNDAIR CL600 CL6002B16 1900305 EA HYDRAULIC LINE CRACKED C K NONE O OTHER IN INSP/MAINT 1 WP 15 333MG 4290 5035 IN THE LAST 2 MONTHS HAVE FOUND 3 T-FITTINGS CRACKED AND LEAKING. (TWO ON 600 CHALLENGER, ONE ON 601). ONE DID CAUSE AN INTERRUPTION OF A FLIGHT. ALL THREE ARE ALUMINUM FITTINGS THAT HAD NOT BEEN DISTURBED SINCE MANUFACTURE. 2 L 7 2 4F RT A21EA 2000041300319 20000413 00319 2000 4 13 2000ZZZX838 1 20000302 G 5320 MS178264 NUT FUSELAGE MISMANUFACTURED B WTXR K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 07 PURCHASED MS17826-4 SELF-LOCKING CASTELLATED, SHEAR NUT DIRECTLY FROM CESSNA AIRCRAFT PART DEPT. BEFORE INSTALLING ON A FLIGHT CONTROL BOLT, TECHNICIAN NOTICED THE CHAMFER ON THE NUT WAS SO DEEP THERE WAS ONLY ONE GRIPPING THREAD LEFT. AF TER CHECKING THE REST OF THE NUTS IN STOCK, FOUND 37 OUT OF 75 NUTS BAD. 2000041300320 20000413 00320 CE 2000 4 13 2000ZZZX839 1 20000126 G 3230 509400111 TRUNNION CESSNA 340 340CESSNA 2076404 CE MLG DAMAGED G O OTHER O OTHER LD LANDING 1 SO 11 340WD 3400509 DURING THE LANDING PHASE OF THE FLIGHT AFTER TOUCHDOWN, THE AIRCRAFT DIPPED AND VEERED HARD TO THE LEFT. EXAMINATION OF THE AIRCRAFT REVEALED A POSSIBLE CAUSE WAS A FAILURE OF THE BELLCRANK ATTACHMENT POINT OF THE MAIN LANDING GEAR TRUNNIO N ASSEMBLY. 1 L 7 2 3O 3A25 2000041300321 20000413 00321 SO 2000 4 13 2000ZZZX840 1 20000303 G 5320 635012 RIVET PIPER PA34 PA34200T 7103406 SO SKIN MISSING B K NONE O OTHER IN INSP/MAINT 1 NE 05 4516F 6250 347670340 FOUND MISSING AND WORKING RIVETS AND SEPARATION OF SKINS BETWEEN FIN ROOT FITTING AND OUTBOARD SKINS, BOTH SIDES. 1 L 7 2 3O A7SO 2000041300322 20000413 00322 CE 2000 4 13 2000ZZZX841 1 20000214 G 2750 05101056 CONTROL CABLE CESSNA 170 170 2072302 CE TE FLAP FRAYED D K NONE O OTHER IN INSP/MAINT 1 NE 05 3988V 4117 18307 DURING AN ANNUAL INSPECTION, THE OUTBOARD END OF THE RIGHT FLAP CABLE WAS FOUND FRAYED .50 INCH AFT OF THE CLEVIS END. THIS MAY HAVE BEEN CAUSED BY WIND ON THE FLAP FLEXING THE CABLE AT THAT POINT. SUBMITTER SUGGESTED AGE OF THE CABLE WAS POSSIBLY A FACTOR ALSO. 1 H 7 1 3O NT A799 2000041300323 20000413 00323 NE 2000 4 13 2000ZZZX842 3 20000306 G 6111 D5133 SHIELD E10950PK HARTZL HCE4A HCE4A3A NE PROPELLER DEBONDED B GLBR K NONE O OTHER IN INSP/MAINT 1 CE 01 1172 HJ254 EROSION SHIELD DEBOND BLADE NR 3, SN 1172. REMOVED AND REPLACED EROSION SHIELD IAW PROCEDURE 001 AND HARTZELL MM. STAT IC BALANCED PROPELLER IAW HARTZELL CMM. 5 C P10NE 2000041300324 20000413 00324 CE 2000 4 13 2000ZZZX843 1 20000214 G 5320 0512128 BRACKET CESSNA 185 A185F 2072821 CE CONT O520 IO520D 17032 SO BS 65.33 BROKEN H K NONE O OTHER IN INSP/MAINT 1 NM 11 4640E 9884 18503824 293336R RIGHT FLAP RETRACTED AFTER PILOT SELECTED FIRST NOTCH OF FLAPS. FOUND INBOARD MOUNTING EARS BROKEN AWAY FROM PULLEY BRA CKET LOCATED JUST AFT OF FLAP HANDLE. SUBMITTER STATED THIS IS THIRD BRACKET REPLACED IN FLEET OF THREE A185F'S. 1 H 7 1 3O 3 O 3A24 E5CE 2000042500079 20000425 00079 NE 2000 4 25 2000ZZZX844 3 20000327 G 6111 D5133 EROSION SHIELD E10950PB HARTZL HCE4A HCE4A3A NE PROPELLER DEBONDED B GLBR K NONE O OTHER IN INSP/MAINT 1 CE 01 2583 HJ728 DEBOND ON NR 4 BLADE. REMOVED SHIELD TO REPAIR DEBOND AT STA 25 WHICH WAS 1 FOOT BY 1.25 FOOT IN JUST THE TOP LAYER OF G LASS. REPAIRED IAW HARTZELL BSF. INSTALLED NEW EROSION SHIELD AND BOOT IAW PROCEDURE 001 AND HARTZELL MM 135F AND 143A, AND BALANCED. 5 C P10NE 2000041300325 20000413 00325 CE 2000 4 13 2000ZZZX845 1 20000309 G 7120 40044 BRACKET CESSNA 170 170B 2072306 CE ENGINE MOUNT BROKEN D K NONE O OTHER IN INSP/MAINT 1 NM 10 8156A 3624 25008 BRACKET BROKEN AT THE EDGE OF THE STRAIGHT LINE OF BOLT PAD MACHINED SURFACE. SUBMITTER RECOMMENDED VISUAL INSPECTION E VERY 100 HOURS. 1 H 7 1 3O A799 2000010800551 20000108 00551 SW 2000 1 8 2000ZZZX88 1 20000103 G 6420 206011810153 PLUG 206011862101 BELL 206 206B 1181511 SW T/R HUB MISMANUFACTURED H K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 99 5008N 414 A6541 2518 SUSPECT COMPOSIT THRUST PLUGS WERE MISMANUFACTURED OR IMPROPERLY INSTALLED ALLOWING TRUNNION TO SHIFT. THIS CAUSED AN O UT-OF-BALANCE CONDITION. THE TAIL ROTOR HUB AND BLADE ASSEMBLY WAS DYNAMICALLY BALANCED ON SEVERAL OCCASIONS. EACH TIM E THE TAIL ROTOR VIBRATION WOULD RETURN WITHIN A FEW FLIGHT HOURS. THE TAIL ROTOR ASSEMBLY WAS REMOVED FROM SERVICE DIS ASSEMBLED AND THE PROBLEM IDENTIFIED. UPON ASSEMBLY, BELL REQUIRES A .002 TO .004 THOUSANDTHS PINCH FIT. THIS ASSEMBLY LOST ALL PRELOAD AND DUE TO THRUST PLUG WIRE HAD A LOOSE FIT OF .004 THOUSANDTHS. 1 G 7 1 3U H2SW 2001022000302 20010220 00302 EA 2001 2 20 20010123CW008 2 20001220 G 7414 M3548 ROTOR PIPER PA28 PA28181 7102807 SO LYC O360 O360A4M 41514 EA SNSNCH 76E 76EM8 EA MAGNETO CRACKED D K NONE O OTHER IN INSP/MAINT 1 GL 19 4149T 2843192 L3630836A 32543K CRACK FOUND AT ROUTINE 500 HOUR INSPECTION. 1 L 7 1 3O 3 O 2A13 E286 5 N P4EA 2001030600067 20010306 00067 SW 2001 3 6 20010123CW009 1 20001219 G 6220 407310100103 HUB BELL 407 407 SW ALLSN 250C 250C47B GL MAIN ROTOR DEBONDED G K NONE O OTHER IN INSP/MAINT 1 SW 07 407BR 758 53354 RUBBER DEBONDED IN FLIGHT, M/R HUB DAMPER ELASTOMERIC. 1 G 7 1 3U 3 U O H2SW E1GL 2001030600068 20010306 00068 SO 2001 3 6 20010123CW010 1 20001222 G 2730 4084700 TORQUE TUBE PIPER PA31 PA31325 7103105 SO ELEVATOR CORRODED G K NONE O OTHER IN INSP/MAINT 1 GL 15 174BH 317612038 WHILE COMPLYING WITH AD 93-24-02 R1, THE AFT ROD END PN452658 WAS REMOVED. CORROSION WAS DISCOVERED IN THE AFT END OF T HE TUBE IN THE FITTING THAT IS THREADED FOR THE ROD INSTALLATION. 1 L 7 2 3O A20SO 2001040900452 20010409 00452 CE 2001 4 9 20010123CW012 1 20001212 G 5511 503200025 SPAR CESSNA 402 402B 207590P CE HORIZONTAL STAB CORRODED G K NONE O OTHER IN INSP/MAINT 1 SW 99 676MF 402B0106 UPON ANNUAL INSPECTION, FLAKING WAS NOTICED ON CENTER FORWARD SPAR AREA. FURTHER INSPECTION REVEALED THE SPAR WAS CORROD ED 25 PERCENT THROUGH MAIN SURFACE. UNIT WAS REPLACED WITH AN AIRWORTHY ITEM. 1 L 7 2 3O A7CE 2001040900060 20010409 00060 CE 2001 4 9 20010124CW001 1 20001121 G 5210 6211282 ROD END CESSNA 650 650 2076802 CE GARRTT TFE731 TFE731* 01518 WP PAX DOOR BROKEN D K NONE O OTHER IN INSP/MAINT 1 EA 27 50EJ 650148 LOWER DOOR ROD END BROKEN IN TWO PARTS. CAUSE WAS IMPROPER OPERATION BY PEOPLE OPERATING DOOR. 2 L 7 2 4F 4 F A9NM E6WE 2001040900064 20010409 00064 SO 2001 4 9 20010124CW002 1 20001227 G 3232 WTC21141 ACTUATOR PIPER PA31 PA31350 7103110 SO LYC O540 TIO540* 41532 EA RT MLG DOOR LEAKING G K NONE K FLUID LOSS NR NOT REPORTED 1 SO 35 3555B 4455 318052056 PILOT COULD NOT EXTEND LANDING GEAR FULLY WITH EMERGENCY HAND PUMP. FLUID LEAK AT RIGHT MAIN GEAR DOOR ACTUATOR, DEPLET ED FLUID SUPPLY PRIOR TO COMPLETION OF GEAR DOWN CYCLE. 1 L 7 2 3O 3 O A20SO E14EA 2001041000001 20010410 00001 SO 2001 4 10 20010124CW004 1 20001219 G 2750 4009209 BELLCRANK PIPER PA18 PA18 7101802 SO FLAP CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 09 9780D 8000 186849 WHILE COMPLETELY DISASSEMBLING FOR RECOVERY, FOUND BOTH BELLCRANKS CRACKED. ONLY WAY TO SEE IS WITH MIRROR OR COMPLETE DISSASSEMBLE. BOTTOM OF BELLCRANK NOT CRACKED. 1 H 7 1 3O 1A2 2001030700601 20010307 00601 SW 2001 3 7 20010124CW005 1 20001211 G 6320 K974120109 PUMP KAMAN K1200 K1200 05625F6 SW LYC T53 T5317A 41549 NE TRANSMISSION SEIZED D OWVL K NONE O OTHER IN INSP/MAINT 1 sw 99 134KA A940006 LE81002 O.O TIME SINCE OVERHAUL, TRANSMISSION OIL PUMP SEIZED MOMENTARILY, ON FIRST STARTUP AFTER INSTALLATION. DAMAGING TRANSM ISSION INTERNAL OIL PUMP DRIVE GEAR. NO SHEARSHAFT INCORPORATEN IN OIL PUMP ASSEMBLY. TRANSMISSION HAD TO BE CHANGED, SECOND INSTANCE ON THIS AC. REPORTS OF SAME PROBLEM ON OTHER AC. 1 G 7 1 4F 4 U NT TR7BO E17EA 2001041800337 20010418 00337 NE 2001 4 18 20010124CW011 2 20001213 G 7322 2630391 DIAPHRAGM DOUG DC4 C54BDC 3021516 WP PWA R2000 R2000* 52023 NE HAMSTD 23E 23E50 NE ACCELRATOR PUMP CRACKED D K NONE O OTHER IN INSP/MAINT 1 AL 01 44911 250 250 10461 108918 RRE182 DIAPHRAGM STILL SOFT , NOT HARD, BUT CRACKED. 2 L 7 4 4R 4 R A762 5E5 6 C P603 2001050200003 20010502 00003 SO 2001 5 2 20010124CW012 2 20001222 G 8520 642396 CRANKSHAFT CESSNA 414 414A 2075907 CE CONT O520 TSIO520NB 17040 SO ENGINE BROKEN D K NONE O OTHER IN INSP/MAINT 1 SW 99 414WE F344 414A0309 519783 CRANKSHAFT BROKEN IN FRONT OF NR1 ROD JOURNAL. LESS THAN 100 HOURS SINCE OVERHAUL.ATTACHED PICTURES WITH ORIGINAL 1 L 7 2 3O 3 O A7CE E8CE 2001050200004 20010502 00004 EA 2001 5 2 20010125CW001 2 20001208 G 7230 COMPRESSOR BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA ENGINE FAILED G JEMA A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 CE 01 366EA BB841 PCE85097 JUST AFTER T/O COPILOT REPORTED SPARKS COMING FROM RIGHT ENGINE, INBOARD AND OUTBOARD EXHAUST STACKS. POWER WAS REDUCED AND AIRCRAFT RETURNED TO AIRPORT WITHOUT INCIDENT. INSPECTION THROUGH HIGH AND LOW BLEED VALVE OPENINGS REVEALED MASSI VE COMPRESSOR FAILURE. ENGINE REMOVED AND SENT IN FOR REPAIR 1 L 7 2 4T 4 T A24CE E4EA 2001032000103 20010320 00103 SO 2001 3 20 20010125CW005 1 20001117 G 3221 89137041 MOUNT PIPER PA46 PA46350P SO LYC O540 TIO540AE2A 41532 EA ACTUATOR MISMANUFACTURED G K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 99 498MM 387 4636149 L995261A LEFT SIDE OF ACTUATOR ATTACH BOSS NOT WELDED ALL THE WAY AROUND. IF NOT DETECTED THIS COULD HAVE CAUSED NOSE GEAR TO CO LLAPSE. 1 L 7 1 3O 3 O RT A25SO E14EA 2001050200009 20010502 00009 2001 5 2 20010125CW007 4 20001130 G 2210 KS270 SERVO BEECH 36 A36 1151604 CE AUTOPILOT SERVO MISINSTALLED D K NONE O OTHER IN INSP/MAINT 1 SW 99 111LJ 3191 E1822 FOUND PITCH SERVO INOPERATIVE DUE TO WATER CONTAMINATION. FOUND SERVO ON TOP OF MOUNTING BRACKETT AND CLUTCH DRIVE ON T OP OF BRACKETT. SERVO AND CLUTCH DRIVE GEARS WERE ONLY SPLINING ABOUT .0156, AFTER SEVERAL TEST, UNIT WOULD FAIL. INST ALLED NEW SERVO AND CLUTCH DRIVE TOGETHER ON BOTTOM OF MOUNTING BRACKETT. 1 L 7 1 3O 3A15 2001050200010 20010502 00010 SO 2001 5 2 20010125CW008 2 20001218 G 8530 642344 CYLINDER CESSNA 421 421B 2076014 CE CONT O520 GTSIO520H 17032 SO ENGINE CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 99 8004Q 83 421B004 219417 PILOT NOTICED RT ENGINE WAS RUNNING ROUGH. SHUT DOWN ENGINE, DURING INSPECTION FOUND THAT NR5 CYLINDER WAS COLD, WITH COMPRESSION TEST, RESULTS WAS 0/80. FOUND EXHST STUD AND NUT MISSING, ALSO REVEALED BURN MARKS FROM EXHST AND MANY C RACKS AROUND EXHST PORT AND SPK PLUG HOLE. RMVD EXHST SYSTM AND CYL, EXHST VLV WAS SITTING ON TOP OF THE SEAT WITH LO OSE SEAT BECAUSE OF CRACKS THROUGH SEAT AREA. POOR COND. OF CYL PRIOR TO O/H . EXTENT OF RECOND REQUIRED TO REPAIR P REVIOUS DAMAGE EVIDENT BY WELD AROUND SPK PLUG HOLES AND PORTS WAS TO MUCH FOR CYLINDER IN THIS COND. DAMAGE AROUND EXH ST PORT., IMPROPER INSTALL OF STUD OR REPAIR OF HOLES ARE WHERE CRKS STARTED THEN EXHST BURN THRU. 1 L 7 2 3O 3 O A7CE E7CE 2001041800284 20010418 00284 NM 2001 4 18 20010125CW013 1 20001218 G 2742 69778551 SPRING BOEING BOEING 737 737 UTILSYS NM HORIZONTAL STAB BROKEN B K NONE O OTHER IN INSP/MAINT 1 NM 01 KEO0361 SPRINGS ARE BROKEN IN THE AUXILIARY BRAKE SYSTEM, CAUSING THE UNIT TO BIND AND JAM.PROBABLE CAUSE/IMPROPER HEAT-TREATING , AUSTENITE, FATIGUE AND INCREASED SPRING COIL STRESSES. 2 L 7 2 4F RT A16WE 2001041800286 20010418 00286 NM 2001 4 18 20010125CW014 1 20001218 G 3240 511531 HOUSING PNEUDRAULICS 5059 BOEING 737 737 UTILSYS NM SHUTTLE VALVE BROKEN B K NONE O OTHER IN INSP/MAINT 1 NM 01 1522 HOUSING IS BROKEN, SHEARED AT THE PRESSURE POINT. PROBABLE CAUSE WOULD BE FATIGUE AND OR DEFECT IN THE CASTING OF THE H OUSING. 2 L 7 2 4F RT A16WE 2001041800287 20010418 00287 NM 2001 4 18 20010125CW015 1 20001218 G 2761 654494710 HOUSING BOEING BOEING 737 737 UTILSYS NM SPOILER ACTUATOR CRACKED B K NONE O OTHER IN INSP/MAINT 1 NM 01 5440 HOUSING IS CRACKED AT THE EXTERIOR OF THE RETRACT PORT. PROBABLE CAUSE OVERSTRESSED, FATIGUE, AND OR POSSIBLE FLAW I N HOUSING DESIGN. 2 L 7 2 4F RT A16WE 2001041800002 20010418 00002 NM 2001 4 18 20010126CW006 1 20001215 G 2761 654494710 HOUSING BOEING BOEING 767 767 UTILUSE NM SPOILER ACTUATOR CRACKED B K NONE O OTHER IN INSP/MAINT 1 NM 01 5408 HOUSING IS CRACKED BELOW THE RETRACT PORT. PROBABLE CAUSE: STRESS AND OR FATIGUE. 2 L 7 2 4F RT A1NM 2001041800003 20010418 00003 NM 2001 4 18 20010126CW007 1 20001215 G 2761 654494710 HOUSING BOEING BOEING 737 737 UTILSYS NM SPOILER ACTUATOR BROKEN B K NONE O OTHER IN INSP/MAINT 1 NM 01 4139 HOUSING IS BROKEN AT THE BEARING LUG.PROBABLE CAUSE: STRESS, FATIGUE AND OR HIGH TIME ON UNIT. 2 L 7 2 4F RT A16WE 2001041800014 20010418 00014 NM 2001 4 18 20010126CW008 1 20001215 G 2761 654494710 HOUSING BOEING BOEING 737 737 UTILSYS NM SPOILER ACTUATOR BROKEN C K NONE O OTHER IN INSP/MAINT 1 NM 01 4153 HOUSING IS BROKEN AT THE BEARING LUG.PROBABLE CAUSE: STRESS, FATIGUE AND OR HIGH TIME ON UNIT. 2 L 7 2 4F RT A16WE 2001030700570 20010307 00570 NM 2001 3 7 20010126CW009 1 20001215 G 2923 654468311 HOUSING BOEING BOEING 737 737 UTILSYS NM HYDRAULIC SYSTEM CRACKED B K NONE O OTHER IN INSP/MAINT 1 SW 99 3092 HOUSING ASSEMBLY IS CRACKED AT THE NR 1 PORT. 2 L 7 2 4F RT A16WE 2001041800009 20010418 00009 NM 2001 4 18 20010126CW010 1 20001215 G 2782 65447418 SLEEVE BOEING BOEING 737 737 UTILSYS NM SLAT ACTUATOR CRACKED B K NONE O OTHER IN INSP/MAINT 1 NM 01 2501C BLOCKING VALVE ASSEMBLY HAS A CRACKED SLEEVE 145. 2 L 7 2 4F RT A16WE 2001041800215 20010418 00215 CE 2001 4 18 20010126CW011 1 20001228 G 3610 1H1067 VALVE LEAR 60 60LEAR 5170707 CE NR 1 ENGINE FAILED B K NONE O OTHER CR CRUISE 1 SW 05 243F 772 175 AIRCRAFT EXPERIENCED LOSS OF BLEEDAIR INFLIGHT, AFTER LANDING, INVESTIGATION REVEALED UPON OPENING LEFT ENGINE COWLING HAD FOUND VALVE HAD FAILED, SENT TO ENGINEERING FOR INVESTIGATION. 2 L 7 2 4F RT A10CE 2001041800238 20010418 00238 CE 2001 4 18 20010126CW012 1 20001220 G 3240 1013810125 VALVE BEECH 300 300BEECH 1152930 CE PWA PT6 PT6* 52043 EA LT MLG WW STUCK B LX5R K NONE O OTHER IN INSP/MAINT 1 GL 19 981LL 560 FL265 BRAKE DEICE LIGHT WOULD REMAIN ON WHEN ON/OFF SWITCH WAS PLACED IN OFF POSITION. DEICE VALVE STICKING ON. 2 L 7 2 4T 3 T A24CE E2NE 2001022100044 20010221 00044 CE 2001 2 21 20010126CW013 1 20001229 G 6100 3156 COUNTERWEIGHT BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO MCAULY 2A34C D2AF34C30 GL PROPELLER BROKEN B BSYA O OTHER J WARNING INDICATION NR NOT REPORTED 1 GL 07 9189Q TH148 810997RR 702969 MIR / DAL - RIGHT ENGINE SURGING AFTER TAKE OFF, RETURNED TO AIRPORT. FOUND COUNTERWEIGHT COLLAR BROKEN. REMOVED PROP AND SENT TO PROP SHOP FOR INSPECTION, EDDY CURRANT INSPECTION AND REPAIR. RETURNED TO SERVICE REINSTALLED ON AIRCRAFT. 1 L 7 2 3O 3 O 3A16 E5CE 5 C P5EA 2001050200012 20010502 00012 CE 2001 5 2 20010126CW014 1 20001222 G 3230 583800901 MOTOR BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO HARTZL HCJ3Y PHCJ3YF2 GL MLG INOPERATIVE B HE4R K NONE O OTHER AP APPROACH 1 SW 99 1814W TH287 298824R EO1683 MIR BDL HAD NO GEAR DOWN INDICATOR GOING INTO BDL, CRANKED GEAR DOWN AND LANDED WITH NO PROBLEMS. REMOVED AND REPLAC ED LANDING GEAR MOTOR. OPS CHECKS GOOD 1 L 7 2 3O 3 O 3A16 E5CE 5 C P36EA 2001050200013 20010502 00013 2001 5 2 20010129CW001 4 20001215 G 2210 065001782200 SERVO CESSNA 206 T206H CE FUSELAGE INOPERATIVE B HI1R K NONE O OTHER CR CRUISE 1 SW 99 909MA 249 T20608097 THE PILOT INITIALLY COMPLAINED THAT THE AUTOPILOT WOULD NOT MAINTAIN CONSTANT VERTICAL SPEED. THIS ESCALLATED INTO A FU LL NOSE DOWN TRIM RUNAWAY. THE PILOT RECOGNIZED THE PROBLEM AND RECOVERED FROM DIVE. THE PITCH SERVO WAS CHANGED AND T HE PROBLEM DID NOT RECUR. 1 H 7 1 3O A4CE 2001050200014 20010502 00014 GL 2001 5 2 20010129CW002 2 20001130 G 7250 TURBINE ALLSN 250B 250B17F2 GL ENGINE MISDRILLED B YKER K NONE O OTHER IN INSP/MAINT 1 SW 99 CAT81073 CAE881236 DURING REASSEMBLY OF THE TURBINE AFTER REPAIR, THE ANTIROTATION PIN WAS FOUND TO BE LOOSE. UPON REMOVAL, FOUND BURRS AT THE BASE OF THE PIN, CAUSED BY THE PIN BEING PRESSED INTO TOO SMALL A HOLE. MEASUREMENT OF THE PIN HOLE FOUND IT TO BE 0.002 TO 0.003 BELOW THE PRINT LIMIT. 3 T E10CE 2001050200016 20010502 00016 SO 2001 5 2 20010129CW005 1 20001215 G 7160 9904700 AIR BOX PIPER PA28 PA28R201 7102816 SO INTAKE SYSTEM CRACKED B K NONE O OTHER IN INSP/MAINT 1 SW 99 283ND 781 781 2844025 DURING SCHEDULED INSPECTION 2 OF 3 RIVETS HOLDING THE ALTERNATE AIR DOOR HINGE, SHEARED. UPON REMOVAL OF AIR BOX ASSEMB LY, A CRACK WAS FOUND EXTENDING ACROSS THE WELD AND INTO EACH TUBE FORMING THE 90 DEGREE TURN OF THE ASSEMBLY. 1 L 7 1 3O 2A13 2001050200017 20010502 00017 CE 2001 5 2 20010129CW006 1 20001221 G 2434 649304 ALTERNATOR BEECH 58 58 1152740 CE ENGINE INOPERATIVE B K NONE L NO TEST IN INSP/MAINT 1 SW 99 158JG 304 304 TH1900 ALTERNATOR INOPERATIVE. 1 L 7 2 3O 3A16 2001041800347 20010418 00347 CE 2001 4 18 20010129CW007 1 20000801 G 3246 FN22A524 NUT DUNLOP RAYTHN DH125 HAWKER800 7450004 CE MLG WHEEL MISSING B L5NR K NONE O OTHER IN INSP/MAINT 1 GL 25 466CS NN185 NAD446 NUTS CAME OFF IN SERVICE. RECOMMEND NUTS AND BOLTS BE CHANGED AT TIRE CHANGES OR CHANGE TO A NEW TYPE NUT AND BOLT. 2 L 7 2 4F RT A3EU 2001050200018 20010502 00018 2001 5 2 20010129CW009 4 20001213 G 6113 055032110 BULKHEAD CESSNA 172 172S 2072439 CE PROP SPINNER BROKEN B WIWR K NONE O OTHER IN INSP/MAINT 1 SW 99 796WW 143 172S8635 FOLLOWING A ROUTINE TRAINING FLIGHT, THE STUDENT AND INSTRUCTOR RETURNED TO FIND THE SPINNER BULKHEAD BROKEN OFF AROUND THE NUTPLATE AND SPINNER BENT IN THAT AREA.THE PROBABLE CAUSE WAS IMPROPER SPINNER TO BULKHEAD FITTING FROM THE FACTORY, CREATING EXCESSIVE TENSION IN THAT AREA. SUGGEST BETTER QUALITY CONTROL FROM THE MFG WHEN SPINNER IS INSTALLED TO PREV ENT RECURRENCE. 1 H 7 1 3O NT 3A12 2001050200019 20010502 00019 CE 2001 5 2 20010129CW010 1 20001213 G 3230 256566250 FILTER ELEMENT BEECH 90 C90A 1152911 CE SUCTION LINE MISSING B K NONE O OTHER IN INSP/MAINT 1 SW 99 488XJ LJ1527 EMERGENCY LANDING, HAND PUMP SUCTION LINE FILTER ELEMENT NOT INSTALLED FROM BUILD.AIRCRAFT TOTAL TIME 799.8 1 L 7 2 3T RT 3A20 2001050200020 20010502 00020 SO 2001 5 2 20010129CW011 1 20001212 G 3213 AN17413 BOLT PIPER PA23 PA23250 7102308 SO RT MLG BROKEN B K NONE O OTHER LD LANDING 1 SW 99 8VV 3100 7554075 RIGHT M.L.G. TORQUE LINK CENTER BOLT BROKEN DURING LANDING, CAUSING RIGHT WHEEL TO ROTATE 90 DEGREE TO AIRCRAFT TRACK. AIRCRAFT TURNED RIGHT OFF THE RUNWAY BUT WAS NOT DAMAGED. DUE TO M.L.G. DESIGN, THE TORQUE LINK BOLT IS PLACED IN HEAVY TENSION LOAD EACH LANDING. 1 L 7 2 3O 1A10 2001041800349 20010418 00349 CE 2001 4 18 20010129CW012 1 20001220 G 3297 WIRE CESSNA 650 650 2076802 CE GARRTT TFE731 TFE731* 01518 WP PILOT YOKE CHAFED B K NONE O OTHER CR CRUISE 1 GL 23 86VP 4830 6500089 PILOT REPORTED THAT IN FLIGHT, THE NOSE WHEEL STEERING SYSTEM DISARMS WHEN THE YAW DAMPER SYSTEM IS DISENGAGED USING THE AUTOPILOT/ NWS DISCONNECT SWITCH ON THE PILOT OR COPILOTS CONTROL WHEEL. THE TECH FOUND A CHAFFED STEERING SYSTEM WIRE SHORTING TO GROUND IN THE PILOTS CONTROL YOKE, BEHIND THE CONTROL WHEEL.DUE TO LIMITED WIRE HARNESS CLEARANCE IN THE YO KE, THE WIRE PROTECTIVE SLEEV CHAFFED ON YOKE THRU BOLTS AND THE WIRE CHAFFED AND SHORTED TO GROUND. 2 L 7 2 4F 4 F A9NM E6WE 2001050200023 20010502 00023 CE 2001 5 2 20010129CW017 1 20001218 G 2760 LINKAGE MTSBSI MU2 MU2B26A 5780414 CE COCKPIT OBSTRUCTED B A UNSCHED LANDING O OTHER NR NOT REPORTED 1 SW 99 783MA 391 PILOT NOTICED BINDING IN THE SPOILER LINKAGE AND DECLARED AN EMERGENCY. THE AC LANDED WITHOUT INCIDENT. MAINTENANCE IN VESTIGATED AREAS IN THE COCKPIT UNDER THE FLOOR AND FOUND TOOLS AND DEBRIS. SOME HARDWARE WAS FOUND UNDER THE SPOILER C HAIN. ONE OF THE NUTS HAD SIGNS OF DAMAGE ON THE FLATS. SUSPECT THIS NUT HAD LODGED IN THE SPOILER CHAIN, THEN FELL OU T OF MECHANISM. SYSTEM WAS RESTORED AND FLIGHT CHECKED. 1 H 7 2 3T RT A10SW 2001050200024 20010502 00024 EA 2001 5 2 20010129CW019 2 20001215 G 7314 WASHER LYC CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA FUEL PUMP DISINTEGRATED B K NONE O OTHER IN INSP/MAINT 1 SW 99 503ER L2780151A 008003 L2780151A INTERNAL TO THE LW15473 FUEL PUMP, ON THE UPPER END OF THE PULL ROD, SHOWS A WASHER PN6413701 AND PN6413703. WASHER 641 13701 WAS MISSING FROM THE PULL ROD AND BELIEVED TO BE FOUND IN THE SUMP ANDSUMP SCREEN IN PIECES. 1 H 7 1 3O 3 O NT 3A12 1E10 2001050200025 20010502 00025 CE 2001 5 2 20010129CW021 1 20001201 G 2140 CI30021 HOSE BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA RT ENGINE CHAFED B AKGR K NONE O OTHER IN INSP/MAINT 1 WP 07 280SC 138 BB664 PCE81553 HOSE IS RUBBING AGAINST ENGINE COWLING. RT ENGINE OUTBOARD STACK RELOCATE PICK UP TUBE LOCATION, ANGLE TOWARDS ENGINE C ASE. 1 L 7 2 4T 4 T A24CE E4EA 2001050200026 20010502 00026 CE 2001 5 2 20010129CW022 1 20001201 G 2140 CI30022 HOSE BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA RT ENGINE CHAFED B K NONE O OTHER IN INSP/MAINT 1 WP 07 280SC 138 BB664 PCE81553 HOSE IS RUBBING AGAINST ENGINE COWLING. RT ENGINE INBOARD STACK. RELOCATE PICK UP TUBE LOCATION ANGLE TOWARDS ENGINE CA SE. 1 L 7 2 4T 4 T A24CE E4EA 2001050200027 20010502 00027 CE 2001 5 2 20010129CW023 1 20001201 G 2140 CI30021 HOSE BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA LT ENGINE CHAFED B YXUR K NONE O OTHER IN INSP/MAINT 1 SW 99 280SC 138 BB664 PCE81535 HOSE IS RUBBING AGAINST ENGINE COWLING. LEFT ENGINE INBOARD STACK. RELOCATE PICK UP TUBE LOCATION, ANGLE TOWARDS ENGIN E CASE. 1 L 7 2 4T 4 T A24CE E4EA 2001050200028 20010502 00028 CE 2001 5 2 20010129CW024 1 20001201 G 2140 CI30022 HOSE BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA LT ENGINE CHAFED B YXUR K NONE O OTHER IN INSP/MAINT 1 WP 07 280SC 138 BB664 PCE81535 HOSE IS RUBBING AGAINST ENGINE COWLING. LEFT ENGINE OUTBOARD STACK. RELOCATE PICK UP TUBE LOCATION. ANGLE TOWARDS ENGIN E CASE. 1 L 7 2 4T 4 T A24CE E4EA 2001041800178 20010418 00178 NM 2001 4 18 20010129CW026 1 20001130 G 3233 ACTUATOR DOUG MD11 MD11 3023602 NM RT MLG FAILED B A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 WP 03 489GX 48458 AFTER AIRBORNE, RIGHT MAIN LANDING GEAR CAN NOT RETRACT, AIRCRAFT TURNED BACK TO AIRPORT. RIGHT MAIN LANDING GEAR RE TRACT ACTUATOR REPLACED. 2 L 7 3 4F RT A22WE 2001030700589 20010307 00589 SW 2001 3 7 20010130CW003 1 20001203 G 6340 407375001105 INDICATOR BELL 407 407 SW COCKPIT INOPERATIVE B GS1R K NONE O OTHER IN INSP/MAINT 1 sw 99 96JJ 419 53364 H A S REPLACED WITH NEW MGT INDICATOR FROM BELL HELICOPTER. 1 G 7 1 3U O H2SW 2001030700619 20010307 00619 SW 2001 3 7 20010130CW007 1 20001207 G 2820 3017392 FUEL LINE PWA BELL 412 412EP 1182205 SW PWA PT6T PT6T3 52045 EA NR1 INLET CHAFED B K NONE O OTHER IN INSP/MAINT 1 sw 99 63177 165 165 RET60086 36173 RET60086 NR1 INLET COWLING CHAFING FUEL INLET LINE, PN3017392, DUE TO INSTALLATION OF SHADIN FUEL FLOW, STC SE1123GL. 1 G 7 2 4U 4 U H4SW E22EA 2001041000003 20010410 00003 SO 2001 4 10 20010205CW001 2 20001220 G 8530 TCMCC71 CYLINDER BEECH 58 58 1152740 CE CONT O520 IO520CB 17032 SO ENGINE CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 99 922DN T4922 815282R EXHAUST LEAK BY NR 4 CYLINDER EXHAUST GASKET. INSPECTED, FOUND 4 CYLINDER CRACKED BY EXHAUST VALVE AREA, INSTALLED 5-9 -00, CYLINDER OVERHAULED 7-28-98, W/O 4419.CYLINDER HAS TOTAL OF 186.3 HOURS ON IT. INSTALLED OVERHAULD CYLINDER ASSY. 1 L 7 2 3O 3 O 3A16 E5CE 2001032200115 20010322 00115 CE 2001 3 22 20010205CW002 1 20001221 G 3720 1HS1 VALVE CESSNA 320 320C 2074510 CE CONT O470 TSIO470B 17026 SO MANIFOLD FAILED D K NONE O OTHER IN INSP/MAINT 1 EA 17 3055T 6375 320C0055 REPLACED LEFT VACCUUM PUMP. ON OPS CHECK, BOTH RED INDICATORS WERE SUCKED IN(RT ENGINE NOT RUNNING) ADVANCE THROTTLE AND RIGHT SIDE POPPED OUT. TESTED MAN VALVE, VALVED FAILED. CORRECTIVE ACTION: REPLACE VALVE.NOTE: MFG REC 10YR REPLACEME NT BUT DOES NOT HAVE ANY./ONE FOUND 1 L 7 2 3O 3 O 3A25 3E3 2001032200116 20010322 00116 CE 2001 3 22 20010205CW003 1 20001225 G 8010 99103971 RELAY CESSNA 402 402C 207590R CE CONT O520 TSIO520* 17040 SO STARTER SYSTEM FAILED D A UNSCHED LANDING H ELECT. POWER LOSS-50 PC CL CLIMB 1 NM 09 6837Y 402C0467 SHORTLY AFTER TAKEOFF, CREW NOTICED INSTRUMENTS AND RADIOS FLICKERING, FOLLOWED BY TOTAL ELECTRICAL FAILURE. CREW RETUR NED AND LANDED WITHOUT INCIDENT. MECH FOUND RT START RELAY FAILED IN CLOSED POSITION, PERMANENTLY ENGAGING THE STARTER. MECH REMOVED AND REPLACED SART RELAY, STARTER, AND AS PRECAUTIONARY MEASURE, REMOVED AND REPLACED BATTERY AND BATTERY RELAY. AC RETURNED TO SERVICE. 1 L 7 2 3O 3 O A7CE E8CE 2001050200038 20010502 00038 EA 2001 5 2 20010205CW009 2 20001213 G 8530 AL75060 ROD BOLT LYC PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA NR4 CYLINDER BROKEN D O OTHER Y ENGINE STOPPAGE CR CRUISE 1 SW 03 7090B L612061A 317752075 L612061A CONNECTING ROD BOLT BROKEN ON NR4 CYLINDER, LT ENGINE. DURING CRUSE FLIGHT. NR4 CYLINDER WAS PUSHED THRU COWLING AND B ROKE OUT LEFT UPPER CRANKCASE. 1 L 7 2 3O 3 O A20SO E14EA 2001030700574 20010307 00574 SO 2001 3 7 20010205CW017 1 20001212 G 7810 1802716 EXHAUST STACK PIPER PA23 PA23160 7102304 SO NR 3 CYLINDER BROKEN B K NONE O OTHER IN INSP/MAINT 1 EA 21 4048P 231525 DURING REPAIR OF MASSIVE OIL LEAK ON LEFT ENGINE, FOUND EXHAUST STACK MISSING ON NR3 CYLINDER. STACK BROKEN AT FLANGE A ND WAS LYING IN COWL. AIRCRAFT HAD BEEN FLYING THIS WAY FOR SEVERAL HOURS. STACK ON NR2 CYLINDER WAS CRACK MORE THAN 5 0 PERCENT AT FLANGE. OTHER IMPROPER REPAIRS NOTED ON OTHER EXHAUST PIPES. AC HAD JUST PREVIOUSLY BEEN ANNUALED. NEW P ARTS WERE INSTALLED. 1 L 7 2 3O 1A10 2001030700577 20010307 00577 SO 2001 3 7 20010205CW020 1 20001212 G 7120 1713701 TRUSS PIPER PA23 PA23160 7102304 SO RT ENGINE BROKEN B K NONE O OTHER IN INSP/MAINT 1 EA 21 4048P 231525 WHILE PERFORMING OTHER MAINTENANCE ON RT ENGINE, TECH NOTICED BROKEN ENGINE TRUSS. TRUSS MEMBER COMPLETELY BROKEN IN HA LF. CAUSE OF FAILURE BELIEVED TO BE SEVERE CORROSION ON THE INSIDE OF THE STEEL TUBE CONSTRUCTED TRUSS MEMBERS. SUGGES T REPLACING WHOLE LANDING GEAR/ ENGINE TRUSS ASSEMBLY. AC HAD RECIEVED RECENT INSPECTION. 1 L 7 2 3O 1A10 2001030700578 20010307 00578 EA 2001 3 7 20010205CW021 2 20001212 G 8550 0320 TUBE PIPER PA23 PA23160 7102304 SO LYC O320 O320B3B 41508 EA ENGINE MISINSTALLED B K NONE K FLUID LOSS IN INSP/MAINT 1 EA 21 4048P 231525 L150539 AC RETURNED TO AIRPORT DUE TO NOTICEABLE OIL LEAKAGE APPEARING ON LEFT WING AND COWLING. 4 QUARTS OF OIL MISSING WHEN M AINTENANCE CK ENGINE. FOUND OIL DIPSTICK TUBE HAD BEEN IMPROPERLY SAFETIED AND LOOSENED, ALLOWING OIL TO ESCAPE. OTHE R ENGINE TUBE WAS ALSO LOOSE, BUT NOT LEAKING AS BADLY. RESECURED AND SAFETIED BOTH TUBES. AC HAD RECENT INSPECTION. 1 L 7 2 3O 3 O 1A10 E274 2001030700579 20010307 00579 SO 2001 3 7 20010206CW001 1 20001212 G 2820 S220000169 PRIMER LINE PIPER PA23 PA23160 7102304 SO LT ENGINE BROKEN B K NONE O OTHER IN INSP/MAINT 1 EA 13 4048P 231525 WHILE REPAIRING MASSIVE EXHAUST LEAK ON LEFT ENGINE THE CYLINDER PRIMER LINE WAS FOUND BROKEN IN HALF AND ANOTHER FUEL P RIMER LINE FOUND CHAFED. RAW FUEL AND MASSIVE EXHAUST LEAK COULD CAUSE ENGINE FIRE. NEW LINES INSTALLED. AC HAD RECEN T ANNUAL. 1 L 7 2 3O 1A10 2001030700580 20010307 00580 EA 2001 3 7 20010206CW002 2 20001218 G 7200 O320E2D ENGINE CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA ENGINE FAILED B A UNSCHED LANDING O OTHER CL CLIMB 1 EA 21 6802H 17265588 ENGINE HAD LOW OIL PRESSURE AND HIGH OIL TEMPERATURE IN CLIMB. TEMP STABILIZED IN DESCENT BUT OIL PRESSURE STILL LOW. LANDED AIRCRAFT. MAINTENANCE FOUND ALUMINUM ON OIL PRESSURE RELIEF VALVE. OIL PRESSURE SCREEN COVERED WITH ALUMINUM, S TEEL FLAKES. SUSPECT INTERNAL FAILURE. CUSTOMER NOTIFIED, ENGINE REPLACEMENT REQUIRED. CAUSE OF FAILURE UNKNOWN. ENGI NE REPLACED BY CUSTOMER. 1 H 7 1 3O 3 O NT 3A12 E274 2001030700583 20010307 00583 CE 2001 3 7 20010206CW004 1 20001220 G 5347 07106582 SEAT TRACK CESSNA 182 R182 2072734 CE SEAT TRACK MISINSTALLED B K NONE O OTHER IN INSP/MAINT 1 EA 21 4776T 4169 R18201762 DURING COMPLIANCE OF AD, FOUND SEAT TRACKS INSTALLED WITH CHERRY MAX BLIND FASTENERS AND OVERSIZED RIVETS, WHICH DID NOT MEET THE REQUIRED 2D EDGE DISTANCE REQUIREMENT. FLOOR AND TRACKS HAD TO BE REPLACED AND SUB FLOOR REPAIRED. CHERRY MA X RIVETS ANRE NOT APPROVED FOR MAJOR STRUCTURAL USE. SUGGEST CHECKING FASTENERS WHILE COMPLYING WITH AD. CALL CESSNA FO R GUIDANCE. 1 H 7 1 3O RT 3A13 2001041000004 20010410 00004 EU 2001 4 10 20010206CW009 1 20001104 G 6720 AC67032 SERVO DUNLOP AEROSP AS355 AS355F1 8680810 EU TAIL ROTOR CRACKED B K NONE O OTHER IN INSP/MAINT 1 NM 07 1298 CRACK DETECTED ON LOWER END OF SERVO BODY ABOVE END CAP. EDDY CURRENT TESTING. 1 G 7 2 3U H11EU 2001041000006 20010410 00006 SW 2001 4 10 20010206CW013 1 20001027 G 6710 41002413 BEARING TEXTRON BELL 214 214B 1182100 SW SERVO ACTUATOR CRACKED B K NONE O OTHER IN INSP/MAINT 1 NM 07 878 CRACKS DETECTED DURING OVERHAUL. 2 G 7 1 4U H6SW 2001030700616 20010307 00616 EA 2001 3 7 20010207CW003 2 20001212 G 8520 5015P07 STUD PIPER PA23 PA23160 7102304 SO LYC O320 O320B3B 41508 EA ENGINE BROKEN D K NONE O OTHER IN INSP/MAINT 1 EA 21 4048P 231525 L150539 DURING REPAIR OF MAJOR OIL LEAK ON LT ENGINE, FOUND NR1 CYLINDER HAD 3 BROKEN STUDS AND ALL BUT 2 OF THE REMAINING HOLD DOWN NUTS HAD BACKED OFF. CYLINDER ASSEMBLY WOULD HAVE SOON LEFT THE CRANKCASE. 3 STUDS WERE REPLACED AND ALL CLYINDER HOLD DOWNS RE-TORQUED ON BOTH ENGINES ALL FOUND BELOW SPECTS.AC HAD RECENT INSPECTION. NO LOGS AVAILABLE FOR VERIFICAT ION. 1 L 7 2 3O 3 O 1A10 E274 2001030700617 20010307 00617 SO 2001 3 7 20010207CW004 1 20001227 G 3231 6736200 ROD PIPER PA28 PA28R200 7102811 SO NLG DOOR BENT G K NONE O OTHER LD LANDING 1 GL 15 5083S 5169 28R7135082 AIRCRAFT LANDED WITH NOSE GEAR STUCK IN THE WELL. NOSE GEAR DOORS JAMMED SHUT. APPEARS GEAR DOOR OVER TRAVELED DUE TO BENT DOOR LINKAGE. 1 L 7 1 3O 2A13 2001030700614 20010307 00614 SO 2001 3 7 20010209CW001 1 20001214 G 2730 62701113 CONTROL CABLE PIPER PA28 PA28181 7102807 SO ELEVATOR FRAYED G VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 4132D 1541 2843234 LEFT FORWARD ELEVATOR CABLE, FRAYED. 1 L 7 1 3O 2A13 2001030700640 20010307 00640 SO 2001 3 7 20010209CW002 2 20001227 G 7314 64621216A2 PUMP BEECH 33 F33A 1151425 CE CONT O520 IO520BB 17032 SO ENGINE LEAKING G K NONE K FLUID LOSS IN INSP/MAINT 1 WP 07 8268T CE1547 820321R ENGINE DRIVEN FUEL PUMP LEAKING OIL FROM DRAIN. 1 L 7 1 3O 3 O 3A15 E5CE 2001030700641 20010307 00641 SO 2001 3 7 20010209CW003 2 20001226 G 7314 64621216A PUMP BEECH 33 F33A 1151425 CE CONT O520 IO520BB 17032 SO ENGINE LEAKING G K NONE K FLUID LOSS IN INSP/MAINT 1 WP 07 1556A 583 CE1318 820275R ENGINE DRIVEN FUEL PUMP LEAKING OIL FROM DRAIN. 1 L 7 1 3O 3 O 3A15 E5CE 2001030700642 20010307 00642 SO 2001 3 7 20010209CW004 2 20001226 G 7314 64621216A2 PUMP BEECH 33 F33A 1151425 CE CONT O520 IO520BB 17032 SO ENGINE LEAKING G K NONE K FLUID LOSS IN INSP/MAINT 1 WP 07 1570A 707 CE1333 820296R ENGINE DRIVEN FUEL PUMP LEAKING OIL FROM DRAIN. 1 L 7 1 3O 3 O 3A15 E5CE 2001032700193 20010327 00193 CE 2001 3 27 20010209CW005 1 20001130 G 3230 1003810061 DOWNLOCK SWITCH BEECH BE76 BEECH 76 76 1153005 CE LYC O360 O360* 41514 EA LT MLG FAILED G K NONE O OTHER IN INSP/MAINT 1 AL 03 6011U ME101 ME101 THIS IS A TWO WAY SWITCH, ONE HALF IS FOR THE INDICATOR LIGHT WHICH WORKS, THE OTHER HALF IS FOR THE DOWN & LOCK SYSTEM. WHICH SHUTS OFF THE MOTOR WHEN THE GEAR IS DOWN. THE MAINTENANCE MANUAL TROUBLESHOOTING SECTION IS INCORRECT, IT SAY S IF THE MOTOR KEEPS RUNNING, ONE OR MORE SWITCHES ARE OPEN. IN REALITY ONE OR MORE SWITCHES ARE CLOSED. 1 L 7 2 3O 3 O A29CE E286 2001030700625 20010307 00625 CE 2001 3 7 20010209CW006 1 20001212 G 5531 51310002 SPAR CESSNA 402 402B 207590P CE VERTICAL STAB CORRODED D K NONE O OTHER IN INSP/MAINT 1 SW 99 676MF 9676 402B0106 UPON ANNUAL INSPECTION, FLAKING WAS NOTICED ON AFT SPAR AREA. FURTHER INSPECTION REVEALED THE SPAR WAS CORRODED .2500 THROUGH MAIN SURFACE. UNIT WAS REPLACED WITH AN AIRWORTHY ITEM. 1 L 7 2 3O A7CE 2001030700594 20010307 00594 EA 2001 3 7 20010209CW008 2 20001207 G 7414 10382681 CAPACITOR BENDIX PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540* 41533 EA MAGNETO FAILED G K NONE O OTHER IN INSP/MAINT 1 AL 03 38KC 219 L299903 318352033 DURING TROUBLE SHOOTING A RUFF MAG PROBLEM, WE FOUND THAT THE MAG CAPACITOR PN10-382681 WAS COMING APART, SWEGED ON TOP SECTION WAS LOOSE. THIS FAILED CAPCITOR HAS A DATE CODE OF 9948. 1 L 7 2 3O 3 O A20SO E14EA 2001032200122 20010322 00122 EA 2001 3 22 20010212CW004 2 20000921 G 8500 ENGINE CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA MCAULY 1A170 1A170E GL FAILED C O OTHER Y ENGINE STOPPAGE CR CRUISE 1 AL 03 453SP 172S8297 L2852351A TG085 UNEXPECTED ENGINE FAILURE DURING LANDING FLAIR. ON DUAL TRAINING FLIGHT, IP DEMONSTRATING A SHORT-FIELD LANDING , OVER AN OBSTACLE, IN THE LANDING FLAIR, THROTTLE IDLE, ENGINE QUIT, PROP STOPPED TURNING. IP LANDED UNEVENTFULLY AND PULLED OFF RUNWAY. CREW PERFORMED SHUTDOWN CHECKLIST. ALL CONTROLS/SWITCHES WERE IN CORRECT POSITION. CREW PERFORMED ENGINE START CHECKLIST, ENGINE STATED NORMALLY WITH SMOOTH 650RPM IDLE. RUNUP & IDLE CHECKS NORMAL. INSPECTION BY A&P AFTER F LIGHT REVEALED NO ABNORMALITY. IDLE AND RUNUP CHECKS NORMAL. AC RETURNED TO SERVICE. 1 H 7 1 3O 3 O NT 3A12 1E10 5 N P857 2001032200125 20010322 00125 CE 2001 3 22 20010213CW003 1 20001213 G 7920 EK9052V10 OIL FILTER CESSNA 414 414A 2075907 CE LT & RT FILTER RESTRICTED B Q2AR K NONE O OTHER IN INSP/MAINT 1 SW 17 366MC 10 414A1005 OIL FILTER/STRAINER IN EACH ENGINE TURBOCHARGER OIL SUPPLY LINE, THESE FILTERS ARE PREMATURLY CLOGGING WITH CARBON PARTI CLES FROM THE OIL CAUSING LOSS OF MANIFOLD PRESSURE. RAM VERBALLY RECOMMENDS REMOVING THIS STRAINER LELMENT TO PREVENT THIS OCCURANCE, NO WRITTEN NOTICE HAS BEEN PROVIDED 1 L 7 2 3O A7CE 2001032700194 20010327 00194 CE 2001 3 27 20010213CW004 1 20001227 G 3240 S116730085 HOSE CONNECTOR CESSNA 172 172S 2072439 CE LYC O360 O360* 41514 EA BRK CYL/BLKHD LOOSE B K NONE K W FLUID LOSS INADEQUATE Q C IN INSP/MAINT 1 GL 15 499KW 413 172S8430 820296R RIGHT BRAKE INOPERATIVE. FOUND LOOSE B-NUT ON BRAKE HOSE FROM MASTER CYLINDER. APPEARS TO HAVE BEEN LOOSE FROM FACTORY AS THERE IS NO RECORD OF WORK BEING PERFORMED IN THIS AREA, AND UNBROKEN TORQUE SEAL ON FITTINGS. 1 H 7 1 3O 3 O NT 3A12 E286 2001032700195 20010327 00195 SO 2001 3 27 20010213CW006 2 20001226 G 7314 H209901BR PUMP BEECH 33 F33A 1151425 CE CONT O520 IO520BB 17032 SO FUEL PUMP LEAKING B K NONE K FLUID LOSS IN INSP/MAINT 1 WP 07 1570A 707 CE1333 820296R ENGINE DRIVEN FUEL PUMP LEAKING OIL FROM DRAIN. 1 L 7 1 3O 3 O 3A15 E5CE 2001032600155 20010326 00155 CE 2001 3 26 20010215CW008 1 20001211 G 2823 SHUTOFF VALVE BEECH 1900 1900C 1154161 CE PWA PT6 PT6A60A 52043 NE FAILED D PS2R K NONE K FLUID LOSS IN INSP/MAINT 1 CE 07 550CJ UC50 WHILE TROUBLE SHOOTING LEFT FIREWALL FUEL SHUT OFF VALVE TROUBLE, FOUND WIRE CORR. AT CONNECTOR A124P1 SOCKET NR1. THIS IS THE POWER WIRE TO THE SWITCH AT THE T HANDLE, REPAIRED WIRE AT SOCKET BY REPLACEMENT OF SOCKET. NOTE: THE SHUT OFF VALVE GETS POWER FROM HOT BATTERY BUSS AND AC BUSS. BOTH POWERS RUN TO THE ONE LOCATION. IF THIS DOESNT WORK THE VALV E WILL NOT SHUT. CAUSE MAY BE FLUID LEAKING IN THE STORM WINDOW AND RUNNING DOWN THE SIDE WHEN AC IS SITTING ON THE GROU ND. 2 L 7 2 4T 4 T RT A24CE E4EA 2001032600341 20010326 00341 SO 2001 3 26 20010222CW004 2 20001217 G 7314 63815416 PUMP BEECH 35 V35B 1151548 CE CONT O520 IO520* 17032 SO BACK OF ENGINE LEAKING D O OTHER K B FLUID LOSS SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 GL 15 2054N 1500 D10196 SHORTLY AFTER TAKEOFF, PILOT SMELLED SMOKE IN COCKPIT AND RETURNED TO AIRPORT. UPON INSPECTION, FOUND ENGINE DRIVEN FUE L PUMP TO BE LEAKING BETWEEN CASE HALVES. NO HEAT RELATED DAMAGE TO ENGINE AREA WAS NOTED. 1 L 7 1 3O 3 O 3A15 E5CE 2001040900446 20010409 00446 EA 2001 4 9 20010222CW008 2 20001220 G 7414 10106492 HOUSING BENDIX PIPER PA24 PA24180 7102402 CE LYC O360 O360A1D 41514 EA MAGNETO WORN D K NONE O OTHER IN INSP/MAINT 1 EA 03 8040P ESI805608 243286 L2366536A DURING ANNUAL INSPECTION , MAGNETS WERE FOUND TO BE OUT OF TIME TO THE ENGINE. EXAM OF CAM / CONTACT POINT AREA, DISC LOSED OIL AND LG AMTS OF DUST AND ALUMINUM SHAVINGS. DISASSEMBLY OF MAGNETS DISCLOSED BEARING, OUTER RACE / CUP / LOOSE IN THE HOUSING. WEAR HAD REACHED POINT OF PERMITTING MOVEMENT THE ROTARY MAGNET SUFFICIENT CAUSE OIL SEEPAGE PAST OIL SEAL. 1 L 7 1 3O 3 O NT 1A15 E286 2001031400252 20010314 00252 EU 2001 3 14 20010223CW004 1 20001222 G 2742 5435021 ACTUATOR ISRAEL 1124 1124 4500102 EU GARRTT TFE731 TFE731* 01518 WP HORIZONTAL STAB FAILED G K NONE O OTHER IN INSP/MAINT 1 EA 11 62ND 1091 379 NORMAL PITCH SYSTEM INOPERATIVE. AC WAS ON RAMP ALL NIGHT. DISCREPANCY FOUND BEFORE DEPARTURE. COLD AND DAMP WEATHER CONTRIBUTED TO ACTUATOR NOT WORKING. DURING REMOVAL AND INSTALLATION OF AN O/H ACTUATOR IN HANGER SYSTEM WORKED OK. NO TED: GREASE PLUGGING DRAIN HOLE IN ACTUATOR. 2 M 7 2 4F 4 F A2SW E6WE 2001032200201 20010322 00201 SO 2001 3 22 20010227CW003 1 20001220 G 2710 62701124 CONTROL CABLE PIPER PA28 PA28181 7102807 SO LYC O360 O360A4M 41514 EA AILERON FRAYED B K NONE O OTHER IN INSP/MAINT 1 WP 07 4142Q 1740 2843207 L3644336A AILERON BALANCE CABLE FRAYED ABOUT 8 INCHES FROM TURN BUCKLE, NEW CABLE INSTALLED. 1 L 7 1 3O 3 O 2A13 E286 2001040900089 20010409 00089 2001 4 9 20010227CW004 4 20001229 G 3421 RCA26BK9 GYRO BEECH 58 58TC 1152746 CE COCKPIT DEFECTIVE B UKJR O OTHER O OTHER NR NOT REPORTED 1 EA 23 117HS TK21 PILOT REPORTS ELECT STANDBY GYRO HORZ, INOPERATIVE. REMOVED INSTRUMENT, CAN HEAR LOOSE PARTS MOVING AROUND INSIDE INSTR UMENT. REMOVED AND RETURNED TO MFG. 1 L 7 2 3O A23CE 2001050200031 20010502 00031 SO 2001 5 2 20010227SG003 2 20001221 G 7314 6467681A1 PUMP TSIO520M CESSNA 206 U206G 2073356 CE CONT O520 TSIO520M 17040 SO ENGINE LEAKING D K NONE K FLUID LOSS IN INSP/MAINT 1 SW 99 HCBXK 440 818076R U20604404 FUEL LEAK FROM BETWEEN PUMP AND MOUNT 1 H 7 1 3O 3 O A4CE E8CE 2001032100130 20010321 00130 CE 2001 3 21 20010228CW004 1 20001106 G 5520 9661000612 SKIN BEECH 58 58 1152740 CE CONT O550 IO550* SO LWR ELEV SKIN DEBONDED B EWCR K NONE O OTHER IN INSP/MAINT 1 SO 05 587P 194 TH1820 DEBOND ON ALL HONEYCOMB STIFFENERS OF RIGHT ELEVATOR. 1 L 7 2 3O 3 O 3A16 E3SO 2001032100131 20010321 00131 EA 2001 3 21 20010228CW009 2 20000506 G 8530 LW16290 CYLINDER PIPER PA44 PA44180T 7104404 SO LYC O360 TO360E1A6 41514 EA RKR ARM STUD/NUT BROKEN D O OTHER Y ENGINE STOPPAGE CR CRUISE 1 EA 21 8295C 418 448107028 L13973 LEFT ENGINE WAS SHUT DOWN IN CRUISE FLIGHT AFTER A MODERATE VIBARATION WAS NOTED. POST FLIGHT INSPECTION REVEALED THAT NR2 CYLINDER/LT ENGINE/ EXHAUST ROCKER ARM PIVOT STUD HAD BROKEN CAUSING ROCKER ARM TO COME OFF. EXHAUST ROCKER ARM JAM MED THE INTAKE ROCKER ARM CAUSING THE INTAKE PUSH ROD TO BEND. THE HOLD DOWN NUT HAD LOST ITS LOCKING ABILITY. 1 L 7 2 3O 3 O A19SO E26EA 2001040900015 20010409 00015 SO 2001 4 9 20010301CW002 2 20001019 G 8530 RG532451 GASKET BEECH 35 A35 1151504 CE CONT E185 E185* 17014 SO CYLINDER DAMAGED D K NONE O OTHER IN INSP/MAINT 1 WP 23 8595A D2033 399468 A BACKED OUT ROCKER COVER SCREW WAS NOTICED AND A CHECK OF ALL ROCKER SCREWS REVEALED THAT MOST HAD A TOTAL LOSS OF TORQ UE, WITH THE REMAINING HAVING NEARLY A TOTAL LOSS. GASKETS WERE INSTALLED 7 HOURS EARLIER WITH NEW SCREWS, WASHERS AND LOCKWASHERS. GASKETS WERE INSTALLED AT THE TORQUE OF 25 LBS AS PER INSTALLATION INSTRUCTIONS. INSPECTION OF THE GASKET S SHOWED NO VISIBLE DEFECTS. GASKETS MUST HAVE RELAXED DURING THE SHORT TIME IN SERVICE CAUSING A LOSS IN TORQUE. LOCK WASHERS ALONE ARE NOT ADEQUATE. 1 L 7 1 3O 3 O A777 E246 2001032100134 20010321 00134 CE 2001 3 21 20010301CW005 1 20001114 G 2731 065001802700 SERVO CESSNA 182 182C 2072708 CE LYC O540 IO540* 41532 EA TRIM SERVO FAILED C K NONE O OTHER IN INSP/MAINT 1 NM 01 360ME 50 18280849 ELECTRIC TRIM SERVO AT ELEVATOR, FAILED. 1 H 7 1 3O 3 O NT 3A13 1E4 2001030200058 20010302 00058 GL 2001 3 2 20010302AP002 3 20001212 G 6111 1A170E BLADE CESSNA 172 172S 2072439 CE LYC O360 IO360A1A 41514 EA MCAULY 1A170 1A170E GL PROPELLER FAILED G C ABORTED TAKEOFF D INFLIGHT SEPARATION TO TAKEOFF 1 GL 15 582SP 239 172S8509 L2901051A UC143 PROPELLER BLADE FAILED 14 INCHES FROM CENTER OF HUB.PROPELLER WAS FORWARDED TO NTSB LAB FOR FURTHER ANALYSIS. 1 H 7 1 3O 3 O NT 3A12 1E10 5 N P857 2001030500004 20010305 00004 EA 2001 3 5 20010302AP004 2 20001223 G 8500 ENGINE CESSNA 172 172R 2072401 CE LYC IO360 IO360L2A EA ENGINE BAY MALFUNCTIONED P O OTHER R PARTIAL RPM/PWR LOSS CR CRUISE 1 sw 99 23838 I AM A STUDENT PILOT AND WAS AT 3000 FT AT A LEVEL CRUISE AND THE ENGINE SHUTTERED FOR APPROX. 1-3 SECONDS. WE NEVER LO ST POWER AND CONTINUED ON. APPROX. 20 MINUTES LATER AT 2000'''' THE SAME CONDITION OCCURED. MY FLIGHT INSTRUCTOR FELT T HAT WATER HAD PASSED THRU THE FUEL SYSTEM. I HAD PREFLIGHTED THE AIRCRAFT AND SAMPLED FUEL FROM ALL 13 SUMPS, AND FOUND NO EVIDENCE OF WATER OR CONTAMINENTS. 1 H 7 1 3O 3 O NT 3A12 1E10 2001030600021 20010306 00021 SO 2001 3 6 20010302AP006 2 20000907 G 7414 1051324 SPRING BENDIX S6RN1225 CESSNA 206 206CESSNA 2073302 CE CONT O520 TSIO520M 17040 SO MCAULY D3A34 D3A34C402 GL MAGNETO BROKEN D K NONE O OTHER IN INSP/MAINT 1 SW 99 PKMPV 11 11 E189909FR U20605864 818029R 803372 TCM/BENDIX MAGNETO IMPULSE COUPLING SPRING. P/N 10-51324, PART TSN 11.6 HOURS INSTALLED ON: MAGNETO P/N 10-349350-5. S/N E189909FR M/N S6RN-1225 MAGNETO TSN 11.6 HOURS. THIS SPRING BROKE APPROXIMATELY 6 INCHES FROM THE OUTER DIAMETER END. THE MECHANIC REMOVED THE MAG BECAUSE HE HEARD NO COUPLING ENGAGEMENT. I DO NOT KNOW THE RESULTS OF THE MAG DROP TEST, PERHAPS THEY NEVER GOT THAT FAR. I WOULD GUESS IT WAS ROUGH. THE BREAK IN THE SPRING LOOKS LIKE A METALLURGY PROBLEM. IT IS A CLEAN BREAK WITH A BIT OF A FLASHING ON ONE SIDE. 1 H 7 1 3O 3 O A4CE E8CE 5 C P47GL 2001040900250 20010409 00250 CE 2001 4 9 20010302CW002 1 20001114 G 2731 SERVO CESSNA 172 172S 2072439 CE LYC O360 O360* 41514 EA ELEVATOR TRIM FAILED C O OTHER J WARNING INDICATION NR NOT REPORTED 1 NM 01 146ME 288 172S8432 TRIM SERVO FAILURE. UNIT PREVENTS USE OF AUTOPILOT AND ELECTRIC TRIM / ELEVATOR TRIM. 1 H 7 1 3O 3 O NT 3A12 E286 2001040900075 20010409 00075 CE 2001 4 9 20010305CW002 1 20000808 G 3210 3450A LANDING GEAR CESSNA 206 T206H CE MAINS COLLAPSED G O OTHER J WARNING INDICATION NR NOT REPORTED 1 AL 01 7255T 70 70 T20608065 GOT RT GEAR UNSAFE LIGHT, UNABLE TO GET LIGHT TO GO OUT. ON LANDING, ROLL OUT RT MAIN GEAR COLLAPSED, DAMAGING THE RT FLOAT. INSPECTION FOUND RT MAIN GEAR ACTUATING CONTROL SHAFT BROKEN. INSTALLED KIT, REPAIRED RT FLOAT KEEL AND SKINS THAT WERE DAMAGED. 1 H 7 1 3O A4CE 2001040900053 20010409 00053 CE 2001 4 9 20010305CW015 1 20001113 G 2731 065001800400 SERVO CESSNA 172 172S 2072439 CE LYC O360 IO360A1C 41514 EA ELEVATOR TRIM FAILED C O OTHER J WARNING INDICATION NR NOT REPORTED 1 NM 01 350ME 93 172S8585 UNITS TRIM VOLTAGE LOW. CAUSE OF FAILURE UNKNOWN. ELEVATOR TRIM 1 H 7 1 3O 3 O NT 3A12 1E10 2001040500050 20010405 00050 SW 2001 4 5 20010312CW007 1 20001223 G 6210 206010233005 PAD BELL BELL 206 206L1 1182107 SW ROTOR BLADE LOOSE B K NONE O OTHER IN INSP/MAINT 1 CE 03 A1525 GRIP PAD COMES WITH ADHESIVE ON IT. TO APPLY, REMOVE PROTECTIVE TAPE, ROUGH UP PREAPPLIED ADHESIVE WITH SANDPAPER, THEN MIX UP ANOTHER ADHESIVE AND INSTALL GRIP PAD TO BLADE. PROBLEM IS THAT THE PREAPPLIED ADHESIVE LAYER IS TOO THICK, AFT ER INSTALLATION OF GRIP PADS TO BLADE, THE BLADE CANNOT BE INSTALLED INTO ROTOR HEAD. 1 G 7 1 3U H2SW 2001040500115 20010405 00115 NE 2001 4 5 20010314CW005 1 20001202 G 6710 0301037820 HARNESS SKRSKY S76 S76A 8143006 NE ALLSN 250B 250B* GL OVERSPEED GOV DEFECTIVE E EGRA K NONE O OTHER IN INSP/MAINT 1 EA 17 886AH 760153 OVERSPEED SHUTDOWN. THE OVERSPEED HARNESS ASSEMBLY PN0301037820 WAS DISASSEMBLED. THE CONNECTOR ASSEMBLY PN9922020010 HAD WIRES NOT PROPERLY ENGAGED INTO PIN PN9550127410 DURING THE CRIMPING PROCESS.. WIRES PULLED FROM PINS.ACTION: CRIMP ED ON NEW PINS, REASSEMBLED HARNESS ASSEMBLY THEN REINSTALLED IN AIRCRAFT. RUN UP OPERATIONAL CHECK. NORMAL 1 G 7 2 3U 3 T H1NE E10CE 2001040900252 20010409 00252 CE 2001 4 9 20010326CW008 1 20000929 G 5711 052300583 SPAR CESSNA 172 172K 2072430 CE LYC O320 O320* 41508 EA LT WING DAMAGED B A5OR K NONE O OTHER IN INSP/MAINT 1 SO 09 7122G 1457 17258822 DURING HIDDEN DAMAGE INSPECTION SOME LIGHT DABAGE TO MID LEADING EDGE SKIN AND ONE NOSE RIB WAS FOUND. UNAPPROVED REPAI R FOUND TO AFT INBD SPAR ASSY. DAMAGE WAS FOUND ON ALMOST ALL NOSE RIBS IN WING. RECORDS CHECK BY OWNER FOUND WING WAS REPAIRED AND RETURNED TO SERVICE AFTER WING SPAR SPLICE. SPLICE WAS DONE WITH TOO MANY RIVETS, TOO LONG AND BENT OVER. WING SHOWED LT DAMAGE, MID LD EDGE & 1 RIB. IT IS SUSPECT REST OF DAM. WAS PREVIOUS. RECMD SEARCH INSP FOR HIDDEN DAM. BE MADE WITH ANY STRUCTURAL REPAIRS. 1 H 7 1 3O 3 O NT 3A12 E274 2001040900543 20010409 00543 EU 2001 4 9 20010328CW003 1 20001026 G 3246 AN960516 WASHER DUNLOP HAWKER BAE125 BAE125700B 7450007 EU MLG WHEEL WRONG PART B NCQG K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 19 5041376 WHEN THIS PART WAS ADDED TO BOLT, IT MADE THE LENGTH OF BOLT TOO SHORT. RESULTED IN WHEEL DISASSEMBLY. 2 L 7 2 4F RT A3EU 2001040900544 20010409 00544 EU 2001 4 9 20010328CW004 1 20001025 G 3246 MS2125005016 BOLT HAWKER BAE125 BAE125700B 7450007 EU WHEEL ASSY INCORRECT B NCQG K NONE O OTHER IN INSP/MAINT 1 SW 19 THE PART USED WAS TOO SHORT AND CAUSED THE WHEEL HALVES TO SEPARATE. 2 L 7 2 4F RT A3EU 2001040900248 20010409 00248 NM 2001 4 9 20010402CW002 1 20001214 G 3610 1H2410 MANIFOLD PIPER PA60 PA60602P 7106015 NM LT ENGINE MALFUNCTIONED D K NONE O OTHER IN INSP/MAINT 1 WP 01 858CH 2295 608265006 ON LT ENGINE START, RED INDICATOR BUTTON RETRACTED, GAGE DROPPED TO ZERO. PNEUMATIC PUMP SUPPLIED PRESSURE BUT ON PRESS URE WAS GETTING TO GYRO FLIGHT INSTRUMENTS, DOOR SEALS, GYRO PRESSURE REGULATOR OR PRESSURE GAGE. RIGHT ENGINE SHOWED NORMAL INDICATOR AND GAGE INDICATION. LEFT ENGINE SHUT DOWN AND BOTH INDICATOR BUTTONS STAYED RETRACTED. STICKING FLAP PER VALVES IN MANIFOLD CAUSED PROBLEM. THIS WOULD CAUSE A SERIOUS SITUATION AT ALTITUDE. NO PRESSURATION ADN NO GYROS. MANIFOLD IN SERVICE 2295.00 HOURS. 1 M 7 2 3O RT A17WE 2001040900251 20010409 00251 NM 2001 4 9 20010402CW003 1 20000609 G 2510 4000 BUCKLE PIPER PA60 PA60601P 7106012 NM LYC O540 TIO540* 41532 EA SEAT BELT DEFECTIVE D K NONE O OTHER IN INSP/MAINT 1 WP 01 90464 61P0261051 BACK SIDE, OUTER RADIUS FOR BELT CUT OUT. CRACKS AT CORNERS OF SLOT. BUCKLE MADE OF ALUMINUM. 1 M 7 2 3O 3 O RT A17WE E14EA 2001040900255 20010409 00255 NM 2001 4 9 20010402CW004 1 20000609 G 2510 4000 BUCKLE PIPER PA60 PA60602P 7106015 NM LYC O540 IO540* 41532 EA SEAT BELT DEFECTIVE D K NONE O OTHER IN INSP/MAINT 1 WP 01 858CH 608265006 ON BACK SIDE OF ALL SEAT BELT BUCKLES, LATCH PART, CRACKS AT EACH CORNER OF BELT ATTACH SLOT. PROBABLE CAUSE- MANUFACTU RING- JOGGLE TOO SEVERE FOR ALUMINUM BECAUSE CRACKS APPEAR AT EACH JOGGLE. 1 M 7 2 3O 3 O RT A17WE 1E4 2001040900333 20010409 00333 2001 4 9 20010403CW003 4 20000916 G 6113 B2800 SPINNER BLANCA 1413 1413 1201002 EA FRNKLN 6A4150 6A4150* 27024 EA PROP ASSY DESTROYED C A UNSCHED LANDING E VIBRATION/BUFFET CL CLIMB 1 WP 01 74231 375 1344 ON CLIMBOUT A VIBRATION DEVELOPED THAT CONTINUED TO INCREASE IN AMPLITUDE. THE FLIGHT WAS ABORTED. SUBSEQUENT INVESTIG ATION REVEALED THAT THE FORWARD PLASTIC SPINNER BULKHEAD HAD FAILED AROUND ITS PERIPHERY ALLOWING THE SPINNER TO WOBBLE. CONTINUED OPERATION IN THIS CONDITION WOULD HAVE RESULTED IN FAILURE OF THE AFT BULKHEAD AND DEPARTURE OF THE SPINNER FROM THE AIRCRAFT. 1 L 7 1 3O 3 O A773 E238 2001041000274 20010410 00274 NE 2001 4 10 20010409CW015 2 20001009 G 7310 500013201 MANIFOLD PWA JT8 JT8D217 52053 NE FUEL SYSTEM FRACTURED D K NONE O OTHER IN INSP/MAINT 1 SO 19 P708492 RIGHT SECONDARY FUEL MANIFOLD WAS FOUND FRACTURED. REMOVED AND REPLACED ALL FUEL MANIFOLDS. A PRESSURE AND LEAK CHECK WAS CONDUCTED, RESULTED IN NO LEAK FOUND. 4 F E9NE 2001041000276 20010410 00276 EA 2001 4 10 20010409CW017 2 20001212 G 8520 EXHAUST VALVE CESSNA 172 172L 2072432 CE LYC O320 O320E2D 41508 EA NR 2 CYLINDER BROKEN D A UNSCHED LANDING R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 SW 99 3922Q 60022 L3003827A AIRCRAFT ARRIVED WITH A ROUGH ENGINE. OPERATIONAL CHECK OF ENGINE REVEALED DANAGE IN NR 2 CYLINDER. FOUND THAT EXHAUST VALVE HAD BROKEN AND DESTROYED PISTON ALSO. ENGINE HAD 1122.7 TIME SINCE OVERHAUL. PREVIOUS COMPRESSION CHECK SHOU LD HAVE REVEALED ANY PROBLEMS WITH VALVE. ENGINE LOG DID NOT REVEAL ANY COMPRESSION CHECKS. ENGINE OVERHAULED AND RET URNED TO SERVICE. 1 H 7 1 3O 3 O NT 3A12 E274 2001041700225 20010417 00225 SO 2001 4 17 20010410AP018 1 20001204 G 7921 AE7010201K0240 HOSE PIPER PA31T PA31T2 7103127 SO PWA PT6 PT6A135 52043 NE LT ENG OILCOOLER CRACKED G A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 SW 99 410CA 47 31T8166005 PCE92300 DURING CRUSE FLIGHT THE RIGHT ENGINE OIL PRESSURE LOW WARNING ALERT SOUNDED. PILOT SECURED ENGINE AND RETURNED TO THE AI RPORT. TECHNICAN REMOVED ENGINE COWLING AND NOTED ENGINE OIL DRIPPING FROM THE OIL COOLER HOSE FIRE SLEEVE. THE OIL LINE WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE. 1 L 7 2 3T 4 T RT A8EA E4EA 2001042300205 20010423 00205 GL 2001 4 23 20010412CW003 3 20001228 G 6110 B3663 COUNTERWEIGHT HARTZL HCB5M HCB5MP3 GL PROPELLER CRACKED B FQ6R K NONE O OTHER IN INSP/MAINT 1 NM 09 COUNTERWEIGHT SLUG CRACKED. LOW TIME, HAVE SLUG. 6 C P44GL 2001041700074 20010417 00074 GL 2001 4 17 20010412CW004 3 20001211 G 6110 B36632 COUNTERWEIGHT AYRES S2 S2R 7630202 CE HARTZL HCB4T HCB4TN5 GL PROPELLER CRACKED B FQ6R K NONE O OTHER IN INSP/MAINT 1 NM 09 8988Q 1488R CDA3594 COUNTERWEIGHT SLUG CRACKED IN SLOTS. LOW TIME, HAVE SLUG. 1 L 7 1 3R NC A4SW 6 C P40EA 2001042400288 20010424 00288 EA 2001 4 24 20010420CW010 2 20000926 G 8530 RETAINER PIPER PA60 PA60600 7106001 NM LYC O540 IO540K1J5 41532 EA ROCKER PIN LOOSE H K NONE O OTHER IN INSP/MAINT 1 EA 17 5FA 600310115 L2028948A DEFECT OCCURED UNDER NORMAL CIRCUSTANCE ON A FRESH FACTORY OVERHAUL. NR 4 CYL INTAKE ROCKER RETAINER, BONDED TO VALVE C OVER, CAME LOOSE ALLOWING ROCKER PIN TO SLIDE OUT. ROCKER JAMMED AND BY FORCE OF PUSHROD, BROKE ROCKER SHAFT HOUSING, P ART OF CAST ALUMINUM HEAD. ALSO NR 4 INTAKE TAPPET JAMMED IN CASE AND BROKE INTO SEVERAL PIECES. PUSHROD DENTED VALVE COVER ABOUT .3750 INCH DEEP DIMPLE FROM INSIDE. ROCKER RETAINER SHOULD BE WELDED OR RIVETED TO VALVE COVER. 1 M 7 2 3O 3 O RT A17WE 1E4 2001050300109 20010503 00109 CE 2001 5 3 20010424CW009 1 20000928 G 5312 07126161 BULKHEAD CESSNA 182 182M 2072728 CE CONT O470 O470* 17026 SO FUSELAGE CRACKED D K NONE O OTHER IN INSP/MAINT 1 NM 03 182AZ 3938 18259852 WHILE PERFORMING 100 HOUR INSPECTION, FOUND A CRACK IN THE UPPER RADIUS ABOVE THE RIGHT RUDDER STOP BOLT. PROBABLE CAUS E WOULD BE FROM THE RUDDER CONTACTING TOO HARD, POSSIBLE WIND DAMAGE. RECOMMED A SOFT HEADED STOP BOLT. 1 H 7 1 3O 3 O NT 3A13 E273 2001050300154 20010503 00154 SO 2001 5 3 20010426CW006 2 20001204 G 8530 SA52000A20P CYLINDER HEAD CONT O520 IO520* 17032 SO ENGINE CRACKED B CY4R K NONE O OTHER IN INSP/MAINT 1 AL 03 1692 CYLINDER HEADS CRACKED FROM THE OUTSIDE OF THE INTAKE SEAT TO THE SPARK PLUG HOLE. CYLINDER SERIAL NUMBERS: G98/9438, (G98/9439), G98/9440, G98/9441, H98/9469. 3 O E5CE 2001050300155 20010503 00155 SO 2001 5 3 20010426CW007 2 20001204 G 8530 SA52000A20P CYLINDER HEAD CONT O520 IO520* 17032 SO ENGINE CRACKED B CY4R K NONE O OTHER IN INSP/MAINT 1 AL 03 1692 CYLINDER HEADS CRACKED FORM THE OUTSIDE OF THE INTAKE SEAT TO THE SPARK PLUG HOLE. CYLINDER SERIAL NUMBERS: G98/9438, G98/9439, (G98/9440), G98/9441, H98/9469. 3 O E5CE 2001050300156 20010503 00156 SO 2001 5 3 20010426CW008 2 20001204 G 8530 SA52000A20P CYLINDER HEAD CONT O520 IO520* 17032 SO ENGINE CRACKED B CY4R K NONE O OTHER IN INSP/MAINT 1 AL 03 1692 CYLINDER HEADS CRACKED FROM THE OUTSIDE OF THE INTAKE SEAT TO THE SPARK PLUG HOLE. CYLINDER SERIAL NUMBERS: G98/9438, G98/9439, G98/9440, (G98/9441), H98/9469. 3 O E5CE 2001050300157 20010503 00157 SO 2001 5 3 20010426CW009 2 20001204 G 8530 SA52000A20P CYLINDER HEAD CONT O520 IO520* 17032 SO ENGINE CRACKED B CY4R K NONE O OTHER IN INSP/MAINT 1 AL 03 1692 CYLINDER HEADS CRACKED FROM THE OUTSIDE OF THE INTAKE SEAT TO THE SPARK PLUG HOLE. CYLINDER SERIAL NUMBERS: G98/9438, G98/9439, G98/9440, G98/9441, (H98/9469). 3 O E5CE 2001050300242 20010503 00242 CE 2001 5 3 20010502CW004 1 20000719 G 5753 052390133 SKIN CESSNA 182 182Q 2072732 CE CONT O470 O470* 17026 SO MCAULY 2A34C 2A34C203 GL LT WING TE FLAP DAMAGED C AKOM K NONE O OTHER IN INSP/MAINT 1 AL 03 79JP 2400 18267081 469049 891062 DURING A POST FLIGHT INSPECTION, A 10.25 INCH TEAR IN THE LEFT FLAP UPPER SKIN. TRAILING EDGE WAS DISCOVERED. THE UPP ER AND LOWER FLAP SKIN TRAILING EDGES SHOWED EVIDENCE OF NEW CRACKS AROUND THE RIVETS IN THE TRAILING EDGE BEYOND THE DA MAGED SECTION. THE AIRCRAFT HAD BEEN ENGAGED IN GLIDER TOWING OPERATIONS PRIOR TO DAMAGE. PROBABLE CAUSE: PILOT IN CO MMAND, USE OF FLAPS OUTSIDE OF MANUFACTURERS RECOMMENDATIONS. PILOT OPERATING HANDBOOK LIMITATIONS. 1 H 7 1 3O 3 O NT 3A13 E273 5 C P3EA 2001050300324 20010503 00324 SW 2001 5 3 20010503CW003 1 20000508 G 7922 53E19600 VALVE MOONEY M20 M20J 5870219 SW LYC O360 IO360A3D6D 41514 EA OIL TEMP FAILED D O OTHER N FALSE WARNING NR NOT REPORTED 1 NM 01 923DH 679 243368 L2671551A PILOT REPORTS AFTER TAKEOFF OIL TEMPERATURE RED LINED. MADE SUCCESSFUL LANDING. DRAINED OIL SUMP, INSPECTED OIL AND OI L FILTER FOR METAL. FINDING WAS NORMAL. OIL COOLER AND LINES WERE CHECKED FOR OBSTRUCTIONS AND FLOW. FINDINGS WERE NO RMAL. REMOVED VARATHERM AND FIELD TESTED TEMPERATURE FUNCTION, FAILED. NOTED SEATING SUNCTION OF PART THRU WITNESS MA RKS, IT WAS NOT SEATING ON ACC CASE APPROX 70 PERCENT SEATING. NOTED, PLUNGER WAS HANGING UP ON SURCLIP BETWEEN CASE AN D THERMAL SENSOR. INSTALLED SUPERIOR VARATHERM, TESTED AND TEST FLOWN, ALL OPS NORMAL. 1 L 7 1 3O 3 O 2A3 1E10 2001050300214 20010503 00214 EU 2001 5 3 20010503CW006 1 20000727 G 2910 EN63A153 HOSE BAC 111 111419EP 1480280 EU HYDRAULIC SYS RUPTURED D O OTHER K J FLUID LOSS WARNING INDICATION NR NOT REPORTED 1 GL 25 999BW 9150 BAC120 PILOT REPORTED LOW QUANTITY IN NR 1 HYDRAULIC SYSTEM. CAUSE WAS DETERMINED TO BE A RUPTURED HOSE ON THE PRESSURE SIDE O F THE LEFT SPOILER. 2 L 7 2 4F A5EU 2001051500127 20010515 00127 NE 2001 5 15 20010507CW009 1 20000629 G 2140 A14D1175 REGULATOR LAKEAC LAKE 250LAKE 5110321 NE LYC O540 TIO540* 41532 EA HEATER LEAKING B A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 AL 03 8549Z 4 115 DURING A ROUTINE FLIGHT THE PILOT NOTED A FUEL SMELL DURING HEATER OPERATION. HE SHUT OFF THE HEATER AND RETURNED TO MA INTENANCE BASE. THE MECHANICS NOTED THAT THE HEATER FUEL PSI REGULATOR WAS LEAKING FROM DIAPHRAGM SEAL AREA. A NEW VAL VE WAS INSTALLED, BUT FAILED AFTER 2 HRS OF OPERATION. A 2ND NEW VALVE WAS INSTALLED AND WAS FOUND TO LEAK FROM DIAPHR AGM AREA AFTER A FEW HOURS OF OPERATION. THE THIRD VALVE WORKS NORMALLY. NO LEAKS WERE FOUND. 1 H 7 1 3O 3 O NC 1A13 E14EA 2001051600422 20010516 00422 CE 2001 5 16 20010508CW010 1 20001127 G 2820 1560016D0140 LINE CESSNA 182 R182 2072734 CE LYC O540 O540J1A5 41532 EA FUEL SYSTEM LEAKING D K NONE K FLUID LOSS IN INSP/MAINT 1 NE 01 9053C 391 00380 L2000842A STEELE BRADED FUEL LINE FOUND SEVERLY LEAKING AT ANNUAL INSPECTION. NOTICED ENGINE COMPARTMENT VERY WASHED FROM FUEL LE AKING WHILE RUNNING. FUEL LINE WAS PRESSURE LINE FROM ENGINE FUEL PUMP TO CARBURETOR. INSTALLED 2.97 391TT VERY COMMO N PROBLEM. TIME LIMIT NEEDED ON STEELE FUEL LINES. 1 H 7 1 3O 3 O RT 3A13 E295 2001052400001 20010524 00001 CE 2001 5 24 20010509CW008 1 20001020 G 2810 VENT LINE CESSNA 185 185F 2072820 CE CONT O520 IO520* 17032 SO FUEL SYSTEM CHAFED B AKOM K NONE O OTHER IN INSP/MAINT 1 AL 03 61795 871 18504256 572877 DURING AN ANNUAL INSPECTION, THE FLEXIBLE FUEL VAPOR VENT LINE WAS FOUND CHAFED AGAINST THE POSITIVE BATTERY CABLE WHICH SUPPLIES POWER TO THE STARTER CONTACT SOLENOID. UPON REMOVAL, THE FUEL LINE SHOWED EVIDENCE OF ARCHING AND THE STEEL O UTER BRAIDING WAS BURNED AWAY. THE INSULATION ON THE BATTERY CABLE WAS WORN AWAY AND BARE WIRE WAS EXPOSED. PROBABLE C AUSE: IMPROPER FUEL LINE, BATTERY CABLE ROUTING, PROTECTION, AND ENGINE TO FIREWALL CLEARANCE LIMITATIONS. 1 H 7 1 3O 3 O 3A24 E5CE 2001071600049 20010716 00049 CE 2001 7 16 20010614CW001 1 20000501 G 3211 S3461108 BOLT CESSNA 172 172N 2072434 CE RT MLG BROKEN D VT3R K NONE O OTHER LD LANDING 1 WP 09 6360D 9601 17272746 RIGHT GEAR LEG SPRING ROTATED IN MOUNTING (BOLT SHEARED) AFTER AIRCRAFT LOCKED UP WHEEL FROM HARD BRAKING. GEAR ROTATED 180 DEGREES. AIRCRAFT SUFFERED BELLY DAMAGE AND ELEVATOR DAMAGE. 1 H 7 1 3O NT 3A12 2001080100208 20010801 00208 GL 2001 8 1 2001FA0000073 1 20000525 G 5320 81352 ROD AVIAT A1 A1A 2210405 GL TAIL BROKEN D K NONE O OTHER IN INSP/MAINT 1 AL 05 27HU 1359 THIS PART BROKE ON LANDING, I BELIEVE THE AIRCRAFT WAS RENDERED UNCONTROLLABLE. 1 H 7 1 3O NC A22NM 2001092100007 20010921 00007 EA 2001 9 21 2001FA0000321 1 20001122 G 2810 FUEL TANK SCWZER G164 G164B 3952802 EA PWA R985 R985* 52008 NE FUSELAGE CONTAMINATED D K NONE O OTHER IN INSP/MAINT 1 NM 02 SNAYR 700 WATER ACCUMULATING IN FUEL TANKS WITH NO QUICK DRAINS. TT 700 TO 900 HOURSPLUS CORROSION. 1 Q 7 1 3R 3 R 1A16 5E1 2002012400092 20020124 00092 SO 2002 1 24 2002FA0000131 2 20000828 G 8520 630393 PUSHROD PIPER PA34 PA34200T 7103406 SO CONT O360 TSIO360EB 17025 SO MCAULY 3AF34C 3AF34C502 GL LT ENGINE CRACKED P K NONE O OTHER IN INSP/MAINT 1 EA 17 91284 347970111 307800 HUB792007 ON ANNUAL INSPECTION OF THE LEFT ENGINE THREE PUSHRODS WERE NOTED TO BE CRACKED ALONG WHAT LOOKS LIKE THEIR ENTIRE LENGT HS. THE THREE DEFECTIVE PUSHRODS WERE REPLACED WITH NEW ONES, AND THE REMAINDER OF THE PUSHRODS WERE OVERHAULED FOR BOTH ENGINES. CAUSE OF THIS DEFECT IS UNKNOWN. 1 L 7 2 3O 3 O A7SO E9CE 5 C P22EA 2002020800022 20020208 00022 CE 2002 2 8 2002FA0000178 1 20000807 G 5711 STRAP BEECH 90 C90 1152913 CE SPAR DEFECTIVE C K NONE O OTHER IN INSP/MAINT 1 EA 05 575C LJ532 DEFECT IN SK SPAR STRAP SYSTEM. 1 L 7 2 3T 3A20 2002040400066 20020404 00066 SO 2002 4 4 2002FA0000425 1 20000626 G 3213 65313004 HOUSING PIPER PA28 PA28161 7102803 SO MLG STRUT BROKEN B K NONE O OTHER IN INSP/MAINT 1 NE 01 2159H 11437 287916192 ATTACH EAR BROKE OFF AT WHERE THE UPPER END OF THE TORQUE LINK ATTACHES TO THE STRUT HOUSING. NOT ORIGINALLY REMORTED, AS IT WAS THOUGHT TO BE A FLUKE, CAUSED BY A STUDENT CROSS LOADING THE GEAR ON LANDING, THUS CAUSING IT TO BREAK. 1 L 7 1 3O 2A13 2002040400067 20020404 00067 SO 2002 4 4 2002FA0000426 1 20000629 G 3213 65313004 HOUSING PIPER PA28 PA28161 7102803 SO LYC O320 O320* 41508 EA MLG STRUT CRACKED B C85R K NONE O OTHER IN INSP/MAINT 1 NE 01 2496X 7414 288516071 CRACKS IN RADIUS OF SCISSORS EARS. POSSIBLE CAUSE FATIGUE ON HIGH TIME AIRCRAFT. 1 L 7 1 3O 3 O 2A13 E274 2002040400068 20020404 00068 SO 2002 4 4 2002FA0000427 1 20000629 G 3213 65319004 HOUSING PIPER PA28 PA28161 7102803 SO STRUT CRACKED B C85R K NONE O OTHER IN INSP/MAINT 1 NE 01 8234D 7841 288216027 FOUND CRACKED DURING NORMAL MAINTENANCE. NOTED WHILE DYE CHECKING THE AREA INVOLVED, HAVING FOUND 2 PRIOR STRUTS CRACKE D. 1 L 7 1 3O 2A13 2002040400069 20020404 00069 SO 2002 4 4 2002FA0000428 1 20000626 G 3213 65319004 HOUSING PIPER PA28 PA28161 7102803 SO LYC O320 O320* 41508 EA RT MLG CRACKED B C85R K NONE O OTHER IN INSP/MAINT 1 NE 01 2159H 11761 287916192 CRACK WAS FOUND DURING NORMAL 100 HOUR MAINTENANCE, SINCE WE HAD ENCOUNTERED ONE BREAKING OFF EARLIER, WE WERE MORE MIND FUL OF CHECKING THEM CLOSER. DYE CHECK SHOWED THE CRACK IN THE EAR RADIUS AREA. ALL THE STRUTS ARE THOUGHT TO BE ORIGI NAL EQUIPMENT. 1 L 7 1 3O 3 O 2A13 E274 2002112000026 20021120 00026 CE 2002 11 20 2002FA0001302 1 20000126 G 5551 07326015 FITTING CESSNA 210 210J 2073439 CE CONT O520 IO520J 17032 SO HORIZONTAL STAB CRACKED D K NONE O OTHER IN INSP/MAINT 1 NM 08 3366S 21059166 216519R FITTING CRACKED DUE TO FATIGUE & VIBRATION. INSTALL IMPROVED FITTING IN HORIZONTAL STABILIZER. 1 H 7 1 3O 3 O 3A21 E5CE 2003050700156 20030507 00156 CE 2003 5 7 2003FA0000395 1 20000714 G 3230 12416307 BUMPER BLOCK CESSNA 210 P210N 2073454 CE CONT O520 TSIO520* 17040 SO MLG DEBONDED B SMTR O OTHER O OTHER NR NOT REPORTED 1 EA 17 5555S 201 P21000417 LEFT AND RIGHT MAIN LANDING GEAR SHELL BUMPER DEBONDS, THE BUMPER EDGES CURL OVER PREVENTING MAIN GEAR STRUT FROM MAKIN G FULL DOWN TRAVEL. THIS CONDITION PREVENTS MAIN GEAR STRUT FROM CONTACTING DOWNLOCKS AND PROPER DOWNLOCK SWITCH ACTUAT ION, THEREFORE, AN UNSAFE CONDITION. IT APPEARS THAT MFG MAY HAFE CHANGED THE COMPOSITION OF THE SHELL BUMPER MATERIAL WHICH DOES NOT HAVE GOOD BONDING QUALITIES. RECOMMEND CHANGING COMPOSITION OF BUMPER MATERIAL. (PHOTO) 1 H 7 1 3O 3 O 3A21 E8CE 2003111400052 20031114 00052 EA 2003 11 14 2003FA0001090 2 20000101 G 8520 FLANGE PITTS S2B S2B 2210006 SO LYC O540 AEIO540D4A5 41532 EA HARTZL HCC2Y HCC2YR4 GL CRANKSHAFT CRACKED B R6AR O OTHER O OTHER NR NOT REPORTED 1 WP 01 87WY 5111 FOUND CRACKED CRANKSHAFT AT FLANGE RADIUS. SUGGEST INSTALLATION OF 3 BLADE PROP TO REDUCE LOAD ON CRANKSHAFT. 1 Q 7 1 3O 3 O NC A8SO 1E4 5 C P920 2003123000072 20031230 00072 2003 12 30 2003FA0001214 4 20000218 G 8300 07900066 MOUNT CESSNA 185 A185F 2072821 CE CONT O520 IO520* 17032 SO RT GEARBOX CRACKED B FE4R O OTHER O OTHER NR NOT REPORTED 1 AL 03 94204 2995 18503289 DURING AN ANNUAL, FOUND THE RT MAIN GEAR BOX STRUCTURE TO BE CRACKED. ALSO NOTED THAT THE RT GEAR WAS LOOSE IN CASTING. 1 H 7 1 3O 3 O 3A24 E5CE 2001012900064 20010129 00064 NE 2001 1 29 AC2A0000014 1 20000131 G 7160 7630207028060 SCREEN SKRSKY S76 S76 8143010 NE INTAKE DAMAGED A AC2A K NONE O OTHER IN INSP/MAINT 1 SW 03 5402T 891 760140 BROKEN WIRES IN SCREEN. REPLACED SCREEN WITH LIKE ITEM. (X) 1 G 7 2 3U H1NE 2001012900065 20010129 00065 GL 2001 1 29 AC2A0000016 2 20000224 G 7230 6896888 SCROLL SKRSKY S76 S76 8143010 NE ALLSN 250C 250C30S 03013 GL COMPRESSOR CRACKED A AC2A K NONE O OTHER IN INSP/MAINT 1 SW 03 5403C 760141 890850 SCROLL CRACKED AT NORMAL LOCATION. REPLACED SCROLL. (X) 1 G 7 2 3U 3 U H1NE E1GL 2001012900053 20010129 00053 SW 2001 1 29 AC2A0000018 1 20000219 G 6230 222044680101 SLEEVE BELL 430 430 1182150 SW M/R DRIVE SCORED A AC2A K NONE O OTHER IN INSP/MAINT 1 SW 03 430CH 277 49037 SCORING AT THE SEALING SURFACE. REPLACED WITH NEW PART. (X) 1 G 7 2 3U RT H9SW 2001012900037 20010129 00037 SW 2001 1 29 AC2A0000019 1 20000210 G 6410 206310105101 BEARING BELL 206 206L3 1182108 SW TAIL ROTOR GALLED A AC2A K NONE O OTHER IN INSP/MAINT 1 SW 03 17237 932 51478 BEARINGS WERE GALLING AND CAUSING STIFF PETALS AT 100 PERCENT. INSTALLED 4 NEW BEARINGS IN THE BLADES. (X) 1 G 7 1 3U H2SW 2001012900071 20010129 00071 GL 2001 1 29 AC2A0000021 2 20000225 G 7230 6896888 SCROLL SKRSKY S76 S76 8143010 NE ALLSN 250C 250C30 03013 GL COMPRESSOR CRACKED A AC2A K NONE O OTHER IN INSP/MAINT 1 SW 03 5414X 760152 890557 CRACKED SCROLL. INSTALLED NEW SCROLL. (X) 1 G 7 2 3U 3 U H1NE E1GL 2001012900047 20010129 00047 SW 2001 1 29 AC2A0000022 1 20000219 G 5101 430310101105 RETAINER BELL 430 430 1182150 SW FUSELAGE LOOSE A AC2A K NONE O OTHER IN INSP/MAINT 1 SW 03 430CH 1908 49037 SHEAR RESTRAINT CAME LOOSE AT PIN. REPLACED RESTRAINT. (X) 1 G 7 2 3U RT H9SW 2001012900048 20010129 00048 SW 2001 1 29 AC2A0000023 1 20000219 G 6510 430010105105 PLATE BELL 430 430 1182150 SW TAIL ROTOR CHAFED A AC2A K NONE O OTHER IN INSP/MAINT 1 SW 03 430CH 1908 49037 SHEAR RESTRAINT CAME UNBONDED AND WORKED AGAINST CLAMP PLATE. REPLACED CLAMP PLATE ASSY. (X) 1 G 7 2 3U RT H9SW 2001012900049 20010129 00049 2001 1 29 AC2A0000024 4 20000211 G 3425 430375002105 DISPLAY BELL 430 430 1182150 SW EFIS FAILED A AC2A K NONE O OTHER IN INSP/MAINT 1 SW 03 430CH 1690 49037 DISPLAY SLOWLY BECAME DIM, THEN WOULD NOT DISPLAY. REPLACED EFIS DISPLAY. (X) 1 G 7 2 3U RT H9SW 2001012900050 20010129 00050 SW 2001 1 29 AC2A0000026 1 20000229 G 2510 222320828121 SEAT BELT BELL 430 430 1182150 SW COCKPIT FRAYED A AC2A K NONE O OTHER IN INSP/MAINT 1 SW 03 430CH 1710 49037 SHOULDER STRAPS FRAYED AT KEEPER ON TOP OF SEAT. REPLACED RESTRAINT ASSY. SMOOTHED EDGES OF KEEPER. (X) 1 G 7 2 3U RT H9SW 2001012900052 20010129 00052 SW 2001 1 29 AC2A0000029 1 20000224 G 6420 430010433101 BEARING BELL 430 430 1182150 SW ROD END WORN A AC2A K NONE O OTHER IN INSP/MAINT 1 SW 03 430CH 1710 49037 BEARING BEYOND LIMITS. REPLACED ROD END. (X) 1 G 7 2 3U RT H9SW 2001012900058 20010129 00058 SW 2001 1 29 AC2A0000030 1 20000203 G 6720 230312001101 LINK BELL 430 430 1182150 SW TAIL ROTOR PITCH WORN A AC2A K NONE O OTHER IN INSP/MAINT 1 SW 03 430CH 49037 WORN LINKS. REPLACED LINKS. (X) 1 G 7 2 3U RT H9SW 2001012900056 20010129 00056 2001 1 29 AC2A0000035 4 20000226 G 2564 BHLCOMP1822002 LIFE RAFT BELL 430 430 1182150 SW EMERGENCY EQUIP WILL NOT TEST A AC2A K NONE L NO TEST IN INSP/MAINT 1 SW 03 430CH 1710 49037 JETTISONABLE LIFE RAFT WOULD NOT PASS 25 POUND PULL TEST FOR DEPLOYMENT. FOUND TORSION SPRING BHL/COMP.1728-201 INSTALL ED TOO TIGHT AND WASHERS ADDED TO RELEASE HANDLE AT PIVOT POINT WHICH ARE NOT CALLED OUT IN THE PARTS MANUAL OR MM. ADJ USTED SPRING AND REMOVED WASHERS. RAFT RELEASED PER INSPECTION. (X) 1 G 7 2 3U RT H9SW 2001013000040 20010130 00040 SW 2001 1 30 AC2A0000036 1 20000313 G 7810 206064300005 EXHAUST PIPE BELL 206 206L3 1182108 SW ENGINE CRACKED A AC2R K NONE O OTHER IN INSP/MAINT 1 SW 03 7159H 51397 STACK CRACKED. REMOVED AND REPLACED STACK. (X) 1 G 7 1 3U H2SW 2001012900062 20010129 00062 SW 2001 1 29 AC2A0000039 1 20000321 G 3040 222325001027 ARM BELL 430 430 1182150 SW WINDSHIELD WIPER BROKEN A AC2A K NONE O OTHER IN INSP/MAINT 1 SW 03 430CH 1787 49037 WINDSHIELD WIPER GUIDE ARM BROKEN AT ATTACHMENT POINT. REPLACED GUIDE ARM. (X) 1 G 7 2 3U RT H9SW 2001013000036 20010130 00036 SW 2001 1 30 AC2A0000040 1 20000408 G 7810 206064300005 EXHAUST PIPE BELL 206 206L3 1182108 SW ENGINE CRACKED A AC2A K NONE O OTHER IN INSP/MAINT 1 SW 03 6533U 407 51439 EXHAUST ASSEMBLY CRACKED. REMOVED AND REPLACED. (X) 1 G 7 1 3U H2SW 2001012900061 20010129 00061 SW 2001 1 29 AC2A0000042 1 20000108 G 7100 230025203101 TUBE BELL 430 430 1182150 SW ENGINE BAY CHAFED A AC2A K NONE O OTHER IN INSP/MAINT 1 SW 03 430CH 1565 49037 TUBE WAS CHAFED BY ENGINE COWLING. REPLACED TUBE. (X) 1 G 7 2 3U RT H9SW 2001012900067 20010129 00067 NE 2001 1 29 AC2A0000043 1 20000426 G 6700 SA414A BEARING SKRSKY S76 S76 8143010 NE FLIGHT CONTROLS BINDING A AC2A K NONE O OTHER IN INSP/MAINT 1 SW 03 5403C 16609 760141 INTERMITTENT BINDING IN FLIGHT CONTROL WHEN ROLL INPUT IS APPLIED. REPLACED WORN BEARING. (X) 1 G 7 2 3U H1NE 2001012900072 20010129 00072 GL 2001 1 29 AC2A0000044 2 20000531 G 7230 23072848 SCROLL SKRSKY S76 S76 8143010 NE ALLSN 250C 250C30S 03013 GL COMPRESSOR DAMAGED A AC2A K NONE O OTHER IN INSP/MAINT 1 SW 03 5447C 254 760180 890328 ENGINE WOULD NOT PASS LIMITING CHECK AS OUTLINED IN SIKORSKY S76 FLIGHT MANUAL. ENG ALSO REPORTED FOR LOW POWER. ENG R EMOVED. UPON DISASSEMBLY OF TURBINE, 1ST STAGE TURBINE NOZZLE AND 1ST STAGE TURBINE WHEEL WERE FOUND DAMAGED FROM FOREI GN OBJECT PASSING THROUGH TURBINE. BOTH NOZZLE AND WHEEL WERE REJECTED DUE TO THIS DAMAGE. COMPRESSOR DISASSEMBLED, COM P SCROLL, PN 23072848, WAS FOUND WITH ONE PIECE OF TURNING VANE MISSING, AREA BROKEN AWAY IS .50 INCH ACROSS AND ROUGHLY RECTANGULAR AND THIS MISSING PIECE OF TURNING VANE IS OBJECT THAT DAMAGED TURBINE, LEADING TO LOWER POWER. ENG REPLACE D. (X) 1 G 7 2 3U 3 U H1NE E1GL 2001012900073 20010129 00073 NE 2001 1 29 AC2A0000045 1 20000604 G 6320 6893672 PINION GEAR SKRSKY S76 S76 8143010 NE ENGINE GEARBOX SPALLED A AC2A K NONE O OTHER IN INSP/MAINT 1 SW 03 5447C 633 760180 ENGINE REMOVED FOR METAL IN OIL. UPON DISASSEMBLY OF GEARBOX, HELICAL POWER TRAIN PINION GEAR PN 6893672 WAS FOUND TO H AVE SPALLING ON GEAR TEETH. HELICAL TORQUEMETER GEAR ALSO HAD SPALLING ON GEAR TEETH. BOTH PARTS WERE REJECTED DUE TO SPALLING. PINION GEAR FAILED AT LOW TOTAL TIME IN SERVICE. 632.5 HRS. TORQUEMETER GEAR HAD 5,000 PLUS HRS IN SERVICE. ENGINE REPLACED. (X) 1 G 7 2 3U H1NE 2001012900070 20010129 00070 EU 2001 1 29 AC2A0000046 1 20000603 G 6710 10545361 CONTROL ROD BOLKMS 105 BO105S 5626006 EU TAIL ROTOR CRACKED A AC2A K NONE O OTHER IN INSP/MAINT 1 SW 03 5366Y S782 TUBE IS CRACKED AT COLLAR. REPLACED TUBE. (X) 1 G 7 2 3U H3EU 2001012900066 20010129 00066 NE 2001 1 29 AC2A0000047 1 20000520 G 5320 7620202010108 ANGLE SKRSKY S76 S76 8143010 NE FUSELAGE CRACKED A AC2A K NONE O OTHER IN INSP/MAINT 1 SW 03 5403C 760141 T-ANGLE FOUND CRACKED SIX INCHES FORWARD ON PILOTS AFT DOOR POST. REPAIRED PER SRM. (X) 1 G 7 2 3U H1NE 2001020900044 20010209 00044 2001 2 9 AC2A0000048 4 20000617 G 3420 060002600 GYRO BELL 430 430 1182150 SW COCKPIT FAILED A AC2A O OTHER O OTHER NR NOT REPORTED 1 SW 03 430CH 1164 49037 VERTICAL GYRO FAILED AT APPROX 1000 HOURS. PART CAUSED AIRCRAFT AUTOPILOT TO PITCH UP AND ROLL RIGHT WHEN AUTOPILOT ENG AGED. REPLACED VERTICAL GYRO WITH SERVICEABLE VERTICAL GYRO. (X) 1 G 7 2 3U RT H9SW 2001020200065 20010202 00065 SW 2001 2 2 AC2A0000052 1 20000615 G 7810 206064300005 EXHAUST PIPE BELL 206 206L3 1182108 SW ENGINE CRACKED A AC2A K NONE O OTHER IN INSP/MAINT 1 SW 03 7159H 8665 49 51397 STACK IS CRACKED OUT WITH ONLY 48 HOURS. REPLACED PART. (X) 1 G 7 1 3U H2SW 2001020900043 20010209 00043 SW 2001 2 9 AC2A0000053 1 20000617 G 6410 222016001131 BLADE BELL 430 430 1182150 SW TAIL ROTOR SEPARATED A AC2A O OTHER D INFLIGHT SEPARATION NR NOT REPORTED 1 SW 03 430CH 1085 A405 49037 SEPARATION IN THE ROOT CLOSURE. THIS WAS THE ORIGINAL TAIL ROTOR BLADE RECEIVED WITH THIS AIRCRAFT. IT WAS REMOVED THE FIRST TIME AT AIRCRAFT TT: 589.4 HOURS FOR BEARINGS CRACKED. REPLACED TAIL ROTOR BLADE ASSY WITH SERVICEABLE PART. ( X) 1 G 7 2 3U RT H9SW 2001020200064 20010202 00064 GL 2001 2 2 AC2A0000054 2 20000424 G 7230 6896888 SCROLL SKRSKY S76 S76A 8143006 NE ALLSN 250C 250C30S 03013 GL COMPRESSOR CRACKED A AC2A K NONE O OTHER IN INSP/MAINT 1 SW 03 7266F 801 760273 890830 SCROLL ASSEMBLY CRACKED. REPLACED SCROLL. (X) 1 G 7 2 3U 3 U H1NE E1GL 2001020900051 20010209 00051 GL 2001 2 9 AC2A0000055 2 20000622 G 7313 47105 METERING VALVE BELL 206 206L3 1182108 SW ALLSN 250C 250C30P 03013 GL FUEL NOZZLE ERODED A AC2A K NONE O OTHER IN INSP/MAINT 1 SW 03 6533U 531 0571 51439 PART IS ERODED AT THE METER SET CAUSING STREAKING. REPLACED THE METER SET. (X) 1 G 7 1 3U 3 U H2SW E1GL 2001020200062 20010202 00062 GL 2001 2 2 AC2A0000056 2 20000622 G 7313 47105 METER SKRSKY S76 S76 8143010 NE ALLSN 250C 250C30 03013 GL FUEL NOZZLE CORRODED B AC2A K NONE O OTHER IN INSP/MAINT 1 SW 03 5447C 385 AG52992 760180 PART IS ERODED AT THE METER SET CAUSING STREAKING AND VOIDS IN THE SPRAY PATTERN. REPLACED THE METER SET. (X) 1 G 7 2 3U 3 U H1NE E1GL 2001020900047 20010209 00047 GL 2001 2 9 AC2A0000057 2 20000622 G 7313 47105 METERING VALVE SKRSKY S76 S76 8143010 NE ALLSN 250C 250C30 03013 GL FUEL NOZZLE ERODED A AC2A K NONE O OTHER IN INSP/MAINT 1 SW 03 5402T 143 AG55440 760140 PART IS ERODED AT METER SET CAUSING STREAKING AND VOIDS IN THE SPRAY PATTERN. (X) 1 G 7 2 3U 3 U H1NE E1GL 2001020900031 20010209 00031 NE 2001 2 9 AC2A0000063 1 20000511 G 2612 7630607902101 FIRE DETECTOR SKRSKY S76 S76 8143010 NE NR 2 ENGINE MALFUNCTIONED A AC2A A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 SW 03 5447C 16030 760180 AIRCRAFT DEPARTED ICY ON 135 SERVICE FLIGHT AND APPROX 10 MILES SOUTH OF ICY, NR 2 ENGINE FIRE LIGHT ILLUMINATED AND FIR E WARNING HORN SOUNDED. CANCELLED TONE AND IN ABSENCE OF ANY SECONDARY INDICATIONS, RETURNED TO HELIPORT AND MADE A NOR MAL APPROACH. MECHANICS DETERMINED THERE WAS A PROBLEM WITH THE SENSOR SWITCH. REMOVED AND REPLACED FLAME DETECTOR WIT H A SERVICEABLE DETECTOR. SYSTEM CHECKED OK. (X) 1 G 7 2 3U H1NE 2001020100056 20010201 00056 NE 2001 2 1 AC2A0000064 1 20000624 G 7603 7630101910117 CONTROL CABLE SKRSKY S76 S76 8143010 NE ALLSN 250C 250C30 03013 GL THROTTLE DAMAGED A O OTHER J WARNING INDICATION NR NOT REPORTED 1 SW 03 5447C 760180 AFTER LANDING ON SS169C, MOVED ENGINE THROTTLES TO GROUND IDLE WHILE LOADING AND UNLOADING PASSENGERS. WHEN THROTTLES M OVED BACK TO FLY, NR 2 THROTTLE MADE A NOTICEABLE CLICK AT THE FULL OPEN POSITION AND TRAVEL FURTHER FORWARD IN THE QUAD RANT. PULLED THROTTLE BACK SLIGHTLY, RPM RESPONDED. RETURNED THROTTLE TO FULL OPEN. CAREFULLY LIFTED TO A HOVER AND P OWER SEEMED NORMAL. UPON TAKEOFF, NR 2 ENG WOULD NOT PRODUCE MORE THAN 75 PERCENT TORQUE WHILE NR 1 WOULD INCREASE TO 1 00 PERCENT. WHEN COLLECTIVE REDUCED, NR 2 ENG REMAINED AT 75 PERCENT TORQUE. RETURNED TO ICY, MADE A SLOW RUN-ON LANDI NG. WHEN NR 2 ENGINE LEVER RETARDED TO IDLE, WORKED NORMAL, HOWEVER ENGINE RPM WOULD NOT GO BACK TO FLY WHEN ADVANCED. 1 G 7 2 3U 3 U H1NE E1GL 2001020100057 20010201 00057 EU 2001 2 1 AC2A0000065 1 20000622 G 6220 1051410110 BOLT BOLKMS 105 BO105S 5626006 EU MAIN ROTOR HEAD DEFECTIVE A AC2A K NONE O OTHER IN INSP/MAINT 1 SW 03 5366Y 52238 S782 PART IS DEFECTIVE. BOLT HEAD HAS SEVEN SIDES INSTEAD OF THE USUAL SIX. PART TT IS 311.0 HOURS SINCE NEW. REPLACED BOL T. (X) 1 G 7 2 3U H3EU 2001020100058 20010201 00058 NE 2001 2 1 AC2A0000066 1 20000706 G 6220 SS40CT28A140180 HOSE SKRSKY S76 S76A 8143006 NE M/R DAMPER BINDING A AC2A K NONE O OTHER IN INSP/MAINT 1 SW 03 72649 760292 WHILE INSPECTING M/R DAMPERS, THE BLACK DAMPER HOSE WAS FOUND BINDING WHEN THE DAMPER WAS ROTATED. THE INBOARD FERREL W AS ALSO FOUND TURNING WHEN HOSE WAS ROTATED. REPLACED HOSE, THE BAD NOSE WAS FOUND TO BE .50 INCH SOFTER THAN THE NEW H OSE. (X) 1 G 7 2 3U H1NE 2001020100059 20010201 00059 NE 2001 2 1 AC2A0000067 1 20000707 G 6210 7615009100053 BLADE SKRSKY S76 S76A 8143006 NE MAIN ROTOR CORRODED A AC2A K NONE O OTHER IN INSP/MAINT 1 SW 03 5401G 760137 DURING ZONE 1 INSPECTION, CORROSION WAS FOUND THROUGHOUT THE LOWER SURFACE OF THE YELLOW MAIN ROTOR BLADE. THE ALUMINUM WIRE MESH WAS FOUND WITH NUMEROUS SMALL PITS OF CORROSION THROUGHOUT THE LOWER SURFACE OF THE BLADE. REMOVED CORROSION AND SPOT PAINTED PER COMPOSITE REPAIR MANUAL. (X) 1 G 7 2 3U H1NE 2001020100060 20010201 00060 NE 2001 2 1 AC2A0000068 1 20000707 G 6210 7615009100053 BLADE SKRSKY S76 S76A 8143006 NE MAIN ROTOR CORRODED A AC2A K NONE O OTHER IN INSP/MAINT 1 SW 03 5401G 3887 760137 DURING ZONE 1 INSPECTION, CORROSION WAS FOUND THROUGHOUT LOWER SURFACE OF MAIN ROTOR BLADE. THE ALUMINUM WIRE MESH WAS FOUND WITH NUMEROUS CORROSION PITS THROUGHOUT THE LOWER SURFACE OF THE BLADE. REMOVED CORROSION AND SPOT PAINTED PER CO MPOSITE REPAIR MANUAL. (X) 1 G 7 2 3U H1NE 2001020100061 20010201 00061 SW 2001 2 1 AC2A0000072 1 20000712 G 2435 230811150 DRIVE SHAFT BELL 430 430 1182150 SW STARTER GEN DEFECTIVE A AC2A K NONE O OTHER IN INSP/MAINT 1 SW 03 430CH 97101 49037 PART IS DEFECTIVE. SHAFT DIAMETER THAT ENGAGES THE ARMATURE IS TOO LARGE. SUBMITTER STATED THIS IS A MANUFACTURING DEF ECT. REPLACED SHAFT. (X) 1 G 7 2 3U RT H9SW 2001020100063 20010201 00063 SW 2001 2 1 AC2A0000074 1 20000521 G 5210 206033635004 HINGE BELL 206 206L3 1182108 SW CREW DOOR MISMARKED A AC2A K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 7159J 8996 51408 HINGE IS STAMPED WITH LEFT PART NUMBER, BUT IS A RIGHT PART. REMOVED AND REPLACED WITH PROPER PART. (X) 1 G 7 1 3U H2SW 2001020100066 20010201 00066 SW 2001 2 1 AC2A0000077 1 20000709 G 7810 230063301102 EXHAUST PIPE BELL 430 430 1182150 SW ENGINE CRACKED A AC2A K NONE O OTHER IN INSP/MAINT 1 SW 03 430CH 1141 49037 ENGINE EXHAUST DUCT FOUND CRACKED IN THE REAR AREA NEAR CENTER BOTTOM. REPLACED ENGINE EXHAUST DUCT. (X) 1 G 7 2 3U RT H9SW 2001020100067 20010201 00067 SW 2001 2 1 AC2A0000078 1 20000715 G 5210 222031290117 HINGE BELL 430 430 1182150 SW DOOR WINDOW BROKEN A AC2A K NONE O OTHER IN INSP/MAINT 1 SW 03 430CH 2295 49037 COPILOT VENT WINDOW IN COPILOT DOOR WINDOW, HAD BROKEN HINGE. REPLACED VENT WINDOW. (X) 1 G 7 2 3U RT H9SW 2001020100068 20010201 00068 SW 2001 2 1 AC2A0000079 1 20000708 G 3246 430336437101 STRAP BELL 430 430 1182150 SW LANDING SKID DEBONDED A AC2A K NONE O OTHER IN INSP/MAINT 1 SW 03 430CH 2295 49037 RIGHT AFT LANDING GEAR STRAP ASSY HAD RUBBER PAD DEBONDED. REPLACED AFT STRAP ASSY. (X) 1 G 7 2 3U RT H9SW 2001020900032 20010209 00032 SW 2001 2 9 AC2A0000080 1 20000710 G 5210 NAS5623R7A CAM BELL 430 430 1182150 SW CREW DOOR CORRODED A AC2A K NONE O OTHER IN INSP/MAINT 1 SW 03 430CH 49037 CAM FOLLOWERS ON HINGES FOR CABIN DOORS WERE FOUND TO HAVE CORROSION IN BEARINGS CAUSING THE BEARINGS TO SEIZE AND COME APART. THE CAM FOLLOWER IS NOT PROTECTED FROM THE ENVIRONMENT AND MOISTURE CAN EINTER BEARING EASILY. REPLACED CAM FOL LOWERS. (X) 1 G 7 2 3U RT H9SW 2001020900033 20010209 00033 SW 2001 2 9 AC2A0000081 1 20000726 G 7810 206064300005 EXHAUST PIPE BELL 206 206L3 1182108 SW ENGINE CRACKED A AC2R K NONE O OTHER IN INSP/MAINT 1 SW 03 6533U 51439 EXHAUST ASSEMBLY IS CRACKED. REPLACED PART. (X) 1 G 7 1 3U H2SW 2001020900034 20010209 00034 SW 2001 2 9 AC2A0000084 1 20000718 G 7810 206064300005 EXHAUST PIPE BELL 206 206L3 1182108 SW ALLSN 250C 250C30P 03013 GL ENGINE CRACKED A AC2A K NONE O OTHER IN INSP/MAINT 1 SW 03 31079 273 51526 EXHAUST ASSY IS CRACKED. REPLACED WITH NEW PART. (X) 1 G 7 1 3U 3 U H2SW E1GL 2001020900035 20010209 00035 SW 2001 2 9 AC2A0000085 1 20000124 G 7810 206064300005 EXHAUST PIPE BELL 206 206L3 1182108 SW ENGINE CRACKED A AC2A K NONE O OTHER IN INSP/MAINT 1 SW 03 7159J 8682 51408 EXHAUST ASSY CRACKED. REPLACED WITH NEW PART. (X) 1 G 7 1 3U H2SW 2001020900036 20010209 00036 SW 2001 2 9 AC2A0000086 1 20000809 G 7810 206064300005 EXHAUST PIPE BELL 206 206L3 1182108 SW ENGINE CRACKED A AC2A K NONE O OTHER IN INSP/MAINT 1 SW 03 31079 7971 51526 EXHAUST ASSY CRACKED. REMOVED AND REPLACED DUCT. (X) 1 G 7 1 3U H2SW 2001020900037 20010209 00037 NE 2001 2 9 AC2A0000087 1 20000822 G 6711 7640201113101 FITTING SKRSKY S76 S76 8143010 NE COLLECTIVE STICK CRACKED A AC2A K NONE O OTHER IN INSP/MAINT 1 SW 03 5403C 16921 1 760141 FOUND SMALL CRACK IN UNDERSIDE OF FITTING. VERIFIED CRACK WITH NDT. REPLACED FITTING. (X) 1 G 7 2 3U H1NE 2001020900038 20010209 00038 NE 2001 2 9 AC2A0000089 2 20000810 G 7250 23053299 TURBINE WHEEL BELL 430 430 1182150 SW ALLSN 250C 250C40B 03032 NE NR 1 ENGINE CONTAMINATED A AC2A K NONE O OTHER IN INSP/MAINT 1 SW 03 430CH 1524 49037 844017 FIELD MAINT REPORTED NR 1 ENGINE HAD FOREIGN OBJECT DAMAGE TO NR 1 ENG COMPRESSOR. MECH EXAMINED TURBINE FOR DAMAGE PER MAINT INSTRUCTIONS. DAMAGE FOUND ON TURBINE NR 1 WHEEL AND ENG REMOVED AND RETURNED FOR REPAIR. UPON TEARDOWN, FOUND NR 1 TURB WHEEL HAD DAMAGE BEYOND REPAIR ON WHEEL BLADE TIPS DUE TO SULFIDATION CAUSING OTBD L/E OF BLADE TIPS TO ACCUMU LATE DEPOSITS FROM CONTAMINANTS IN ATMOSPHERE, AND POSSIBLY CAUSED BY OTHER CONDITIONS. REF RR 250/C30, CSL 3161. AFFE CTED TURBINE WHEEL REMOVED FROM SERVICE AND REPLACED. TURBINE REPAIRED, RETURNED TO SERVICE. (X) 1 G 7 2 3U 3 U RT H9SW E1GL 2001020900039 20010209 00039 SW 2001 2 9 AC2A0000090 1 20000826 G 7810 206064300005 EXHAUST PIPE BELL 206 206L3 1182108 SW ENGINE CRACKED A AC2A K NONE O OTHER IN INSP/MAINT 1 SW 03 17592 7307 51535 REMOVED AND REPLACED CRACKED EXHAUST DUCT. (X) 1 G 7 1 3U H2SW 2001020900040 20010209 00040 SW 2001 2 9 AC2A0000091 1 20000806 G 6410 206016201131 BLADE BELL 206 206L3 1182108 SW TAIL ROTOR PEELING A AC2A K NONE O OTHER IN INSP/MAINT 1 SW 03 7159J 370 51408 TAIL ROTOR BLADE PAINT PEELING AT 370.2 HOURS SINCE NEW. VISUAL INSPECTED, SANDED PAINT AND REPAINTED. (X) 1 G 7 1 3U H2SW 2001020900041 20010209 00041 SW 2001 2 9 AC2A0000092 1 20000806 G 6410 206016201131 BLADE BELL 206 206L3 1182108 SW TAIL ROTOR PEELING A AC2A K NONE O OTHER IN INSP/MAINT 1 SW 03 7159J 370 51408 TAIL ROTOR BLADE PAINT PEELING AND BEARINGS WORN BEYOND LIMITS. INSPECTED, REPLACED 2 EACH BEARINGS, SANDED THE PAINT A ND REPAINTED. INSTALLED 2 EACH SLEEVES PN 206-010-733-003 PNAV 300549, 2 EACH BEARINGS PN 206-310-105-101 TRACKING NR 3 9858. (X) 1 G 7 1 3U H2SW 2001020200066 20010202 00066 SW 2001 2 2 AC2A0000094 1 20000915 G 7810 206064300005 EXHAUST PIPE BELL 206 206L3 1182108 SW ENGINE CRACKED A AC2A K NONE O OTHER IN INSP/MAINT 1 SW 03 715CC 8380 51380 EXHAUST ASSY CRACKED. REPLACED. (X) 1 G 7 1 3U H2SW 2001020900046 20010209 00046 NE 2001 2 9 AC2A0000095 1 20000926 G 6711 7640201113101 FITTING SKRSKY S76 S76 8143010 NE COLLECTIVE STICK CRACKED A AC2A K NONE O OTHER IN INSP/MAINT 1 SW 03 5402T 760140 FITTING, PILOTS COLLECTIVE STK IS CRACKED. VERIFIED CRACK WITH NDT. REPLACED FITTING. (X) 1 G 7 2 3U H1NE 2000103100106 20001031 00106 NE 2000 10 31 AC2A0000096 1 20000926 G 3210 1945E235 ROD END SKRSKY S76 S76A 8143006 NE MLG CRACKED A AC2A K NONE O OTHER IN INSP/MAINT 1 SW 03 72649 760292 WHILE PERFORMING THE REQUIREMENTS OF ASB 76-32-26, CORROSION INSPECTION OF THE THREADED JOINT, FOUND BEARING CRACKED. R EPLACED POSITIONING ROD END. (X) 1 G 7 2 3U H1NE 2001020900042 20010209 00042 SW 2001 2 9 AC2A000093 1 20000909 G 7810 206064300005 EXHAUST PIPE BELL 206 206L3 1182108 SW ENGINE CRACKED A AC2A K NONE O OTHER IN INSP/MAINT 1 SW 03 53702 51249 EXHAUST ASSEMBLY CRACKED. REPLACED. (X) 1 G 7 1 3U H2SW 2000041300003 20000413 00003 SW 2000 4 13 AC2A066556 1 20000219 G 6410 206310105101 BEARING BELL 206 206L3 1182108 SW TAIL ROTOR DAMAGED H AC2A K NONE O OTHER IN INSP/MAINT 1 SW 03 17237 932 51478 BEARINGS WERE GAULING AND CAUSING STIFF PEDALS AT 100 PERCENT. INSTALLED 4 NEW BEARINGS IN THE BLADES. 1 G 7 1 3U H2SW 2001050700570 20010507 00570 NE 2001 5 7 AC2A072770 1 20001017 G 6700 7640201113101 FITTING SKRSKY S76 S76A 8143006 NE FLIGHT CONTROLS CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 5401G 760137 PART IS CRACKED. REPLACED CRACKED COLLECTIVE SOCKET. 1 G 7 2 3U H1NE 2001050700571 20010507 00571 NE 2001 5 7 AC2A072772 1 20001208 G 6730 7665005801112 SERVO SKRSKY S76 S76A 8143006 NE TAIL ROTOR CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 7266K 13399 760283 CRACKED MOUNTING FLANGE. REPLACED T/R SERVO. 1 G 7 2 3U H1NE 2001051000128 20010510 00128 SW 2001 5 10 AC2A072792 1 20001022 G 7810 206064300005 EXHAUST PIPE BELL 206 206L3 1182108 SW ENGINE CRACKED H AC2A O OTHER O OTHER NR NOT REPORTED 1 FS 01 17238 317 51492 STACK CRACKED AS REAR WELD SEAM. REMOVED AND REMOVED STACK. 1 G 7 1 3U H2SW 2001051000129 20010510 00129 SW 2001 5 10 AC2A072793 1 20001206 G 6300 430010124101 BUSHING BELL 430 430 1182150 SW M/R DRIVE WORN H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CH 589 49037 BUSHINGS WORN BEYOND LIMITS. REPLACED BUSHINGS 1 G 7 2 3U RT H9SW 2001051000130 20010510 00130 SW 2001 5 10 AC2A072794 1 20001206 G 6230 430310450101 DUPLEX BEARING BELL 430 430 1182150 SW SWASHPLATE MAKING METAL H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CH 565 49037 METAL IN SWASHPLATE GREASE. REPLACED DUPLEX BEARING 1 G 7 2 3U RT H9SW 2001051000131 20010510 00131 SW 2001 5 10 AC2A072795 1 20001206 G 6321 5009209 LINER BELL 430 430 1182150 SW ROTOR BRAKE WORN H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CH 964 49037 ROTOR BRAKE WEAK - REPLACED LININGS WITH NEW. 1 G 7 2 3U RT H9SW 2001051000132 20010510 00132 SW 2001 5 10 AC2A072796 1 20001206 G 2432 39563001 BATTERY PACK BELL 430 430 1182150 SW MAIN WEAK H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CH 589 49037 BATTERY FAILED FUNCTIONAL TEST. REPLACED BATTERY. 1 G 7 2 3U RT H9SW 2001051000133 20010510 00133 SW 2001 5 10 AC2A072797 1 20001206 G 7810 230063301102 EXHAUST STACK BELL 430 430 1182150 SW ENGINE CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CH 473 49037 EXHAUST CRACKED. 1 G 7 2 3U RT H9SW 2001051000134 20010510 00134 SW 2001 5 10 AC2A072798 1 20001206 G 7810 206064300005 EXHAUST STACK BELL 206 206L3 1182108 SW ENGINE CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 7159J 634 51408 CRACKED. 1 G 7 1 3U H2SW 2001051000135 20010510 00135 SW 2001 5 10 AC2A072799 1 20001208 G 7810 206064300005 EXHAUST STACK BELL 206 206L3 1182108 SW ENGINE CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 17592 215 51535 CRACKED. 1 G 7 1 3U H2SW 2001051000136 20010510 00136 SW 2001 5 10 AC2A072800 1 20001208 G 2910 70053H000A100A HOSE BELL 206 206L3 1182108 SW HYD PUMP LEAKING H AC2A A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 FS 01 715CC 51380 SMALL PIN HOLE IN HYDRAULIC FLEX LINE CAUSED LOSS OF HYDRAULIC FLUID. FLEX LINE IS LOCATED ON THE PRESSURE OUTLET OF T HE HYDRAULIC PUMP. REPLACED LINE. 1 G 7 1 3U H2SW 2001051000137 20010510 00137 SW 2001 5 10 AC2A072801 1 20001212 G 2910 70053H000A100A HOSE BELL 206 206L3 1182108 SW HYD PUMP LEAKING H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 6533U 8998 51439 PILOT REPORTED GETTING FEEDBACK IN THE FLIGHT CONTROLS UPON SHUTDOWN OF THE AIRCRAFT. AFTER COMPLETING THE SHUTDOWN, HE EXAMINED THE AIRCRAFT AND FOUND HYDRAULIC FLUID IN THE TRANSMISSION DECK. REPLACED HOSE ASSY. 1 G 7 1 3U H2SW 2001051000138 20010510 00138 SW 2001 5 10 AC2A072802 1 20001214 G 2913 222380009105 PUMP BELL 430 430 1182150 SW HYD SYSTEM MALFUNCTIONED H AC2A O OTHER O OTHER NR NOT REPORTED 1 FS 01 430CH 2759 49037 PSI ABOVE 1600 AT 10 DEGS. OAT. REPLACED PUMP 1 G 7 2 3U RT H9SW 2000011500590 20000115 00590 WP 2000 1 15 AGQA065532 1 20000111 G 6510 369A76131 LINK ASSY HUGHES 369 369D 4470706 WP TAIL ROTOR WORN E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 1097J 900801D LINK ASSEMBLY IS WORN EXCESSIVELY. 1 G 7 1 3U H3WE 2000011500591 20000115 00591 WP 2000 1 15 AGQA065533 1 20000106 G 2436 369A4652 VOLT REGULATOR HUGHES 369 369E 4470707 WP BATTERY BOX FAILED E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 8330P 0330E VOLTAGE REGULATOR UNABLE TO POWER UP. 1 G 7 1 3U H3WE 2000011500592 20000115 00592 SW 2000 1 15 AGQA065534 1 20000106 G 2450 MS24171D1 RELAY BELL 206 206B3 1181506 SW MLG BURNED E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 206BX 2872 RELAY IS BURNED. 1 G 7 1 3U H2SW 2000011500593 20000115 00593 SW 2000 1 15 AGQA065535 1 20000106 G 2840 206075189001 INDICATOR BELL 206 206B3 1181506 SW FUEL QUANTITY ERRATIC E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 206BX 2872 FUEL QUANTITY INDICATOR IS ERRATIC. 1 G 7 1 3U H2SW 2000011500594 20000115 00594 2000 1 15 AGQA065536 4 20000106 G 3457 0110005400 GPS HUGHES 369 369D 4470706 WP COCKPIT FAILED E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 1097J 900801D GPS UNABLE TO FIND SATELLITES. 1 G 7 1 3U H3WE 2000011500595 20000115 00595 WP 2000 1 15 AGQA065537 1 20000106 G 6420 369A17255 HUB HUGHES 369 369D 4470706 WP TAIL ROTOR WORN E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 500DC 290456D TAIL ROTOR HUB IS WORN EXCESSIVELY. 1 G 7 1 3U H3WE 2000011500596 20000115 00596 SW 2000 1 15 AGQA065538 1 20000106 G 6240 32005007 TACH GENERATOR BELL 212 212 1181420 SW MAIN ROTOR ERRATIC E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 8530F 30920 TACHOMETER/GENERATOR IS ERRATIC. 1 G 7 1 4U H4SW 2000011500597 20000115 00597 SW 2000 1 15 AGQA065539 1 20000106 G 3240 MS24171D1 RELAY BELL 206 206B3 1181506 SW MLG BURNED E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 49718 1917 RELAY IS BURNED. 1 G 7 1 3U H2SW 2000011500598 20000115 00598 SW 2000 1 15 AGQA065540 1 20000106 G 2430 51509002R CONTROL UNIT BELL 212 212 1181420 SW DC SYSTEM FAILED E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 8530F 30920 DC CONTROL IS UNABLE TO COME ON-LINE. 1 G 7 1 4U H4SW 2000011500599 20000115 00599 WP 2000 1 15 AGQA065541 1 20000106 G 3210 369D26301 DAMPER HUGHES 369 369D 4470706 WP MLG WEAK E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 500DC 290456D MLG DAMPER IS WEAK. 1 G 7 1 3U H3WE 2000011500600 20000115 00600 WP 2000 1 15 AGQA065542 1 20000106 G 3210 369D26301 DAMPER HUGHES 369 369D 4470706 WP MLG WEAK E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 500DC 290456D MLG DAMPER IS WEAK. 1 G 7 1 3U H3WE 2000022300018 20000223 00018 EA 2000 2 23 AGQA065543 2 20000106 G 7412 103815501 EXCITER BELL 212 212 1181420 SW PWA PT6T PT6T3 52045 EA ENGINE FAILED E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 8530F 30920 EXCITER BOX IS INOPERABLE. WILL NOT EXCITE. 1 G 7 1 4U 4 U H4SW E22EA 2000011500601 20000115 00601 2000 1 15 AGQA065544 4 20000106 G 3457 12000301 GPS BELL 212 212 1181420 SW COCKPIT FAILED E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 8530F 30920 GPS UNABLE TO FIND SATELLITES. 1 G 7 1 4U H4SW 2000011500602 20000115 00602 WP 2000 1 15 AGQA065545 1 20000106 G 7714 389A4517 TACH GENERATOR HUGHES 369 369D 4470706 WP ENGINE FAILED E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 5211R 4610 1161D TACHOMETER/GENERATOR MAKES N1 GAUGE HANG AT ZERO.. 1 G 7 1 3U H3WE 2000011500603 20000115 00603 GL 2000 1 15 AGQA065546 2 20000106 G 7532 23053176 BLEED VALVE HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL ENGINE FAILED E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 5027P 611002D CAE822961 BLEED VALVE PRODUCES LOW POWER- HIGH N1 SPEED. 1 G 7 1 3U 3 U H3WE E4CE 2000011500604 20000115 00604 2000 1 15 AGQA065547 4 20000106 G 2300 069102100 RADIO HUGHES 369 369D 4470706 WP COCKPIT INOPERATIVE E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 1097J 900801D RADIO INOPERABLE UPON INSTALLATION. 1 G 7 1 3U H3WE 2000011500605 20000115 00605 WP 2000 1 15 AGQA065548 1 20000106 G 6710 369A717011 MOTOR HUGHES 369 369D 4470706 WP LATERAL TRIM SLOW E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 500DC 290456D HIGH SPEED MOTOR INSTALLED DELAY IN ACTION. 1 G 7 1 3U H3WE 2000011500606 20000115 00606 WP 2000 1 15 AGQA065549 1 20000106 G 2436 369A4652 VOLT REGULATOR HUGHES 369 369D 4470706 WP BATTERY BOX ERRATIC E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 5211R 1161D FIELD VOLTAGE INTERMITTENT, OVERVOLTAGE CONDITION. 1 G 7 1 3U H3WE 2000011500607 20000115 00607 WP 2000 1 15 AGQA065550 1 20000106 G 6220 369A10053 DAMPENER PIN HUGHES 369 369E 4470707 WP M/R HEAD WORN E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 8330P 0330E DAMPENER PIN RIDES UP. 1 G 7 1 3U H3WE 2000011500608 20000115 00608 WP 2000 1 15 AGQA065551 1 20000106 G 6520 369D2172313 BEARING HUGHES 369 369D 4470706 WP TAIL ROTOR WORN E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 5211R 1161D BEARING WORN. 1 G 7 1 3U H3WE 2000011500609 20000115 00609 WP 2000 1 15 AGQA065552 1 20000106 G 6510 369D2172313 LINK ASSY HUGHES 369 369D 4470706 WP TAIL ROTOR WORN E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 1097J 900801D T/R LINK ASSY IS WORN EXCESSIVELY. 1 G 7 1 3U H3WE 2000011500610 20000115 00610 WP 2000 1 15 AGQA065555 1 20000106 G 6710 369A717011 MOTOR HUGHES 369 369D 4470706 WP LATERAL TRIM WEAK E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 1097J 900801D MOTOR IS SLOW AND WEAK. 1 G 7 1 3U H3WE 2000011500611 20000115 00611 SW 2000 1 15 AGQA065556 1 20000106 G 7920 70010G000X116A HOSE BELL 206 206B3 1181506 SW ENGINE OIL LEAKING E AGQA K NONE K FLUID LOSS IN INSP/MAINT 1 EA 13 9907K 2040 HOSE ASSEMBLY LEAKING. 1 G 7 1 3U H2SW 2000011500612 20000115 00612 SW 2000 1 15 AGQA065557 1 20000106 G 7714 32005007 TACH GENERATOR BELL 212 212 1181420 SW ENGINE INTERMITTENT E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 8530F 30920 TACHOMETER/GENERATOR CAUSES N2 GAUGE TO BE INTERMITTENT. 1 G 7 1 4U H4SW 2000011500613 20000115 00613 WP 2000 1 15 AGQA065558 1 20000106 G 6420 369A21800501 SWASHPLATE HUGHES 369 369D 4470706 WP TAIL ROTOR NOISY E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 5027P 611002D SWASHPLATE IS NOISEY, SLIGHT CLICKING NOISE WHEN ROTATING TAIL ROTOR. 1 G 7 1 3U H3WE 2000011500614 20000115 00614 2000 1 15 AGQA065559 4 20000107 G 2320 KY196 RADIO BELL 206 206B3 1181506 SW VHF SYSTEM INOPERATIVE E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 206BY 2871 FREQUENCY WILL NOT CHANGE IN RADIO. 1 G 7 1 3U H2SW 2000011500615 20000115 00615 2000 1 15 AGQA065560 4 20000107 G 3457 0110005400 GPS BELL 206 206B3 1181506 SW COCKPIT FAILED E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 49718 1917 GPS UNABLE TO FIND SATELLITES. 1 G 7 1 3U H2SW 2000011500616 20000115 00616 GL 2000 1 15 AGQA065561 2 20000107 G 7532 23053176 BLEED VALVE HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL COMPRESSOR STICKING E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 369AW 470117D CAE833998 BLEED VALVE STICKING CAUSING COMPRESSOR STALLS. 1 G 7 1 3U 3 U H3WE E4CE 2000011500617 20000115 00617 GL 2000 1 15 AGQA065562 2 20000107 G 7323 23057870 GOVERNOR HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL ENGINE SLOW E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 1097J 900801D CAE833805 GOVERNOR SLOW TO RECOVER. 1 G 7 1 3U 3 U H3WE E4CE 2000011500618 20000115 00618 WP 2000 1 15 AGQA065563 1 20000107 G 7720 369A45217 INDICATOR HUGHES 369 369D 4470706 WP TOT ERRATIC E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 5027P 611002D TOT GAUGE ERRATIC. 1 G 7 1 3U H3WE 2000011500619 20000115 00619 SW 2000 1 15 AGQA065564 1 20000107 G 7714 2090755265 WARINING BOX BELL 212 212 1181420 SW NR 2 ENGINE FAILED E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 8530F 30920 WARNING BOX IS INOPERATIVE. NR 2 ENGINE LIGHT STAYS ON. 1 G 7 1 4U H4SW 2000011500620 20000115 00620 WP 2000 1 15 AGQA065565 1 20000107 G 2400 369H4551 BEARINGS HUGHES 369 369D 4470706 WP TACH GENERATOR DAMAGED E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 5027P 611002D BEARINGS ARE BAD AND WIRES BROKEN. 1 G 7 1 3U H3WE 2000011500621 20000115 00621 SW 2000 1 15 AGQA065566 1 20000107 G 7714 2090753265 WARINING BOX BELL 212 212 1181420 SW NR 2 ENGINE FAILED E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 8530F 30920 NR 2 ENGINE OUT LIGHT INTERMITTENTLY. 1 G 7 1 4U H4SW 2000022300019 20000223 00019 EA 2000 2 23 AGQA065567 2 20000107 G 7321 32447066 CONTROL UNIT BELL 212 212 1181420 SW PWA PT6T PT6T3 52045 EA ENGINE FAILED E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 8530F 30920 CONTROL UNIT WOULD NOT MATCH TORQUES TORQUE SPLIT 1 G 7 1 4U 4 U H4SW E22EA 2000011500622 20000115 00622 SW 2000 1 15 AGQA065568 1 20000107 G 3340 7028511 STROBE BELL 212 212 1181420 SW FUSELAGE INTERMITTENT E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 8530F 30920 STROBE ASSY IS INTERMITTENT. 1 G 7 1 4U H4SW 2000021200036 20000212 00036 WP 2000 2 12 AGQA065668 1 20000124 G 6520 369D21800 PITCH CONTROL HUGHES 369 369D 4470706 WP TAIL ROTOR CHIPPED E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 500DC 290456D SPLINE TEETH ARE BROKEN AND CHIPPED. 1 G 7 1 3U H3WE 2000021200037 20000212 00037 GL 2000 2 12 AGQA065669 2 20000124 G 7532 23053176 BLEED VALVE HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL ENGINE FAILED E AGQA O OTHER O OTHER NR NOT REPORTED 1 EA 13 500DC 290456D CAE831608 BLEED VALVE STALLED IN-FLIGHT. 1 G 7 1 3U 3 U H3WE E4CE 2000021200038 20000212 00038 GL 2000 2 12 AGQA065670 2 20000124 G 7323 252466714 GOVERNOR HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL ENGINE FLUCTUATED E AGQA O OTHER O OTHER NR NOT REPORTED 1 EA 13 1097J 900801D CAE833805 GOVERNOR IS FLUCTUATING IN POWER. 1 G 7 1 3U 3 U H3WE E4CE 2000021200039 20000212 00039 WP 2000 2 12 AGQA065671 1 20000124 G 2430 A700ZG RCR HUGHES 369 369E 4470707 WP GEN CONTROL FAILED E AGQA O OTHER O OTHER NR NOT REPORTED 1 EA 13 8330P 0330E PART IS UNABLE TO COME ON-LINE. 1 G 7 1 3U H3WE 2000021200040 20000212 00040 WP 2000 2 12 AGQA065672 1 20000124 G 7714 369A45167 INDICATOR HUGHES 369 369D 4470706 WP COCKPIT STICKING E AGQA O OTHER O OTHER NR NOT REPORTED 1 EA 13 5027P 611002D TACHOMETER IS STICKING. 1 G 7 1 3U H3WE 2000021200041 20000212 00041 WP 2000 2 12 AGQA065673 1 20000124 G 6520 369D25400 GEARBOX HUGHES 369 369D 4470706 WP TAIL ROTOR WORN E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 500DC 290456D T/R GEARBOX IS WORN EXCESSIVELY. 1 G 7 1 3U H3WE 2000021200042 20000212 00042 GL 2000 2 12 AGQA065674 2 20000128 G 7412 106149501 EXCITER HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL IGNITION SYS FAILED E AGQA O OTHER O OTHER NR NOT REPORTED 1 EA 13 5211R 66 1161D EXCITER IS POWERLESS, WILL NOT EXCITE IGNITER. 1 G 7 1 3U 3 U H3WE E4CE 2000021200043 20000212 00043 GL 2000 2 12 AGQA065675 2 20000128 G 7412 106149501 EXCITER HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL IGNITION SYSTEM FAILED E AGQA O OTHER O OTHER NR NOT REPORTED 1 EA 13 5211R 35 1161D EXCITER IS INOPERABLE, WILL NOT EXCITE. 1 G 7 1 3U 3 U H3WE E4CE 2000021200044 20000212 00044 WP 2000 2 12 AGQA065676 1 20000128 G 3310 369H64255 DIMMER CONTROL HUGHES 369 369D 4470706 WP COCKPIT LIGHTS INOPERATIVE E AGQA O OTHER O OTHER NR NOT REPORTED 1 EA 13 1097J 900801D DIMMER CONTROL IS INOPERABLE, LIGHTS WILL NOT DIM. 1 G 7 1 3U H3WE 2000021200045 20000212 00045 2000 2 12 AGQA065677 4 20000128 G 2312 064101900 TRANSCEIVER BELL 206 206B3 1181506 SW COCKPIT DAMAGED E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 49718 1917 RADIO IS BROKEN, DAMAGED ANTENNA JACK. 1 G 7 1 3U H2SW 2000021200046 20000212 00046 SW 2000 2 12 AGQA065678 1 20000128 G 7714 206075681003 INDICATOR BELL 206 206B3 1181506 SW DUAL TACH INOPERATIVE E AGQA O OTHER O OTHER NR NOT REPORTED 1 EA 13 90322 1736 DUAL TACHOMETER INDICATOR IS INOPERABLE, TURBINE SIDE LOW, INSTALLED AND GROUND RUN. 1 G 7 1 3U H2SW 2000021200047 20000212 00047 SW 2000 2 12 AGQA065679 1 20000128 G 6520 2040406045 COUPLING BELL 204 UH1H 1181407 SW GEARBOX CHIPPED E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 53AG 7221588 COUPLING HAS CHIPPED TOOTH. 1 G 7 1 4U EXPA1G71 2000021200048 20000212 00048 SW 2000 2 12 AGQA065680 1 20000128 G 6510 212311009101 BEARING BELL 212 212 1181420 SW T/R DRIVE SCRATCHED E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 8530F 30920 INNER RACE IS SCRATCHED. 1 G 7 1 4U H4SW 2000021200049 20000212 00049 SW 2000 2 12 AGQA065681 1 20000128 G 6510 212311007101 BEARING BELL 212 212 1181420 SW T/R DRIVE DAMAGED E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 8530F 30920 BEARING IS DAMAGED. 1 G 7 1 4U H4SW 2000021200050 20000212 00050 SW 2000 2 12 AGQA065682 1 20000128 G 6510 212311008101 BEARING BELL 212 212 1181420 SW T/R DRIVE DAMAGED E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 8530F 30920 BEARING IS DAMAGED. 1 G 7 1 4U H4SW 2000021200051 20000212 00051 SW 2000 2 12 AGQA065683 1 20000128 G 6510 212311010101 BEARING BELL 212 212 1181420 SW T/R DRIVE SCORED E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 8530F 30920 INNER RACE IS SCORED. 1 G 7 1 4U H4SW 2000021200052 20000212 00052 SW 2000 2 12 AGQA065684 1 20000128 G 6320 2060401461 GEAR BELL 206 206B3 1181506 SW M/R GEARBOX FLAKING E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 206BX 2872 GEAR IS FLAKING. 1 G 7 1 3U H2SW 2000021200053 20000212 00053 SW 2000 2 12 AGQA065685 1 20000128 G 6320 2060401223 SUN GEAR BELL 206 206B3 1181506 SW M/R GEARBOX FLAKING E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 206BX 2872 SUN GEAR IS FLAKING. 1 G 7 1 3U H2SW 2000021200054 20000212 00054 SW 2000 2 12 AGQA065686 1 20000128 G 6320 2060401461 GEAR BELL 206 206B3 1181506 SW M/R GEARBOX FLAKING E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 206BX 2872 GEAR IS FLAKING. 1 G 7 1 3U H2SW 2000021200055 20000212 00055 SW 2000 2 12 AGQA065687 1 20000128 G 6320 2060401461 GEAR BELL 206 206B3 1181506 SW M/R GEARBOX FLAKING E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 206BX 2872 GEAR IS FLAKING. 1 G 7 1 3U H2SW 2000021200056 20000212 00056 SW 2000 2 12 AGQA065688 1 20000128 G 6320 2060401461 GEAR BELL 206 206B3 1181506 SW M/R GEARBOX FLAKING E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 206BX 2872 GEAR IS FLAKING. 1 G 7 1 3U H2SW 2000021200057 20000212 00057 SW 2000 2 12 AGQA065689 1 20000128 G 5320 2040300611 SUPPORT BELL 204 UH1H 1181407 SW FUSELAGE CRACKED E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 53AG 7221588 SUPPORT IS CRACKED. 1 G 7 1 4U EXPA1G71 2000021200058 20000212 00058 SW 2000 2 12 AGQA065691 1 20000128 G 6300 2040406235 BEARING BELL 204 UH1H 1181407 SW M/R GEARBOX LEAKING E AGQA K NONE K FLUID LOSS IN INSP/MAINT 1 EA 13 53AG 7221588 BEARING IS LEAKING. 1 G 7 1 4U EXPA1G71 2000021200591 20000212 00591 SW 2000 2 12 AGQA065692 1 20000204 G 7920 700096000T302A HOSE BELL 206 206B3 1181506 SW ENGINE OIL SYS LEAKING E AGQA K NONE K FLUID LOSS IN INSP/MAINT 1 EA 13 90322 1736 HOSE IS LEAKING. 1 G 7 1 3U H2SW 2000021200592 20000212 00592 GL 2000 2 12 AGQA065693 2 20000204 G 7412 106149501 EXCITER HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL ENGINE INOPERATIVE E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 1097J 900801D EXCITER INOPERATIVE. 1 G 7 1 3U 3 U H3WE E4CE 2000021200593 20000212 00593 WP 2000 2 12 AGQA065694 1 20000204 G 3252 369D26301131 DAMPER HUGHES 369 369D 4470706 WP MLG DISCHARGED E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 5027P 611002D MAIN LANDING DAMPER IS LOW. 1 G 7 1 3U H3WE 2000021200594 20000212 00594 WP 2000 2 12 AGQA065695 1 20000204 G 3252 369D26301231 DAMPER HUGHES 369 369D 4470706 WP MLG DISCHARGED E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 5027P 611002D MAIN LANDING GEAR DAMPER IS LOW. 1 G 7 1 3U H3WE 2000021200595 20000212 00595 WP 2000 2 12 AGQA065696 1 20000207 G 6720 369D21800501 SWASHPLATE HUGHES 369 369E 4470707 WP TAIL ROTOR WORN E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 8330P 0330E TAIL ROTOR PITCH CONTROL'S INNER BUSHING WORN BEYOND LIMITS. 1 G 7 1 3U H3WE 2000021900074 20000219 00074 WP 2000 2 19 AGQA065932 1 20000208 G 7810 369A8230503 PIPE HUGHES 369 369D 4470706 WP EXHUAST CRACKED E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 369AW 470117D EXHAUST PIPE IS CRACKED APPROXIMATELY 4 INCHES, AFT, INBOARD CENTER. 1 G 7 1 3U H3WE 2000021900075 20000219 00075 2000 2 19 AGQA065933 4 20000209 G 2312 KY195B RADIO HUGHES 369 369D 4470706 WP VHF INOPERATIVE E AGQA O OTHER O OTHER NR NOT REPORTED 1 EA 13 500DC 290456D VHF RADIO IS INOPERATIVE. 1 G 7 1 3U H3WE 2000021900076 20000219 00076 SW 2000 2 19 AGQA065935 1 20000211 G 2436 CSV115212A VOLT REGULATOR BELL 204 UH1H 1181407 SW DC SYSTEM INOPERATIVE E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 53AG 7221588 VOLTAGE REGULATOR INOPERABLE, WILL NOT REGULATE. 1 G 7 1 4U EXPA1G71 2000021900610 20000219 00610 SW 2000 2 19 AGQA065942 1 20000211 G 2436 CSV115212A VOLT REGULATOR BELL 204 UH1H 1181407 SW DC SYSTEM INOPERATIVE E AGQA K NONE O OTHER IN INSP/MAINT 1 EA 13 53AG 7221588 VOLTAGE REGULATOR INOPERABLE. WILL NOT REGULATE. 1 G 7 1 4U EXPA1G71 2000073100024 20000731 00024 EA 2000 7 31 AU000068 2 20000130 G 8540 GEARBOX LYC PIPER PA31 PA31P 7103120 SO LYC O541 TIGO541E1A 41539 EA FAILED W K NONE E VIBRATION/BUFFET CL CLIMB 1 AU S L44162 (AUS) ENGINE GEARBOX SUSPECT FAILURE. 1 L 7 2 3O 3 O A8EA E19EA 2000073100025 20000731 00025 EA 2000 7 31 AU000070 2 20000127 G 8500 ENGINE LYC PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL LEFT MAKING METAL W K NONE O OTHER IN INSP/MAINT 1 AU S L17061A (AUS) LEFT ENGINE OIL FILTER NON-FERROUS METAL CONTAMINATION. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2000073100026 20000731 00026 EA 2000 7 31 AU000074 2 20000205 G 8530 VALVE SEAT PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL NUMBER 5 LOOSE W K NONE O OTHER IN INSP/MAINT 1 AU S 897 L496861A (AUS) LEFT ENGINE NR 5 CYLINDER EXHAUST VALVE SEAT SEPARATED FROM CYLINDER HEAD. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2000073100027 20000731 00027 SO 2000 7 31 AU000081 1 20000207 G 3230 4204200 ARM PIPER PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL LANDING GEAR RET BROKEN W O OTHER O OTHER TO TAKEOFF 1 AU S (AUS) LEFT MAIN LANDING GEAR RETRACTION ARM BROKEN. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2000073100028 20000731 00028 CE 2000 7 31 AU000084 1 20000208 G 2800 FUEL TANK CESSNA 210 210L 2073448 CE CONT O520 IO520L 17032 SO MCAULY 2A34C E2A34C73 GL AIRCRAFT FUEL SY FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) AIRCRAFT FUEL SYSTEM INSPECTED IAW AD/GEN/79, AD/GEN/80 AND AD/GEN/81. 1 H 7 1 3O 3 O 3A21 E5CE 5 C P3EA9 2000073100029 20000731 00029 CE 2000 7 31 AU000086 1 20000112 G 7500 25001 VALVE PARKER 25001 CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE ENGINE BLEED AIR CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) BLEED AIR SOLENOID VALVE OPEN CIRCUITED. MOVING PARTS CORRODED. SUSPECT WATER INGRESS. 1 H 7 1 3T 3 T A37CE E4EA 2000073100030 20000731 00030 EU 2000 7 31 AU000087 1 20000128 G 5730 136 RIVET PARTEN PARTEN P68 P68B EU LYC O360 IO360A1B6 41514 EA HARTZL HCC2Y HCC2YK2 GL WING PLATES/SKIN MISALIGNED W K NONE O OTHER IN INSP/MAINT 1 AU S 136 (AUS) LEFT AND RIGHT WING INBOARD ENGINE COWL RIVETS MISALIGNED. THE RIVETS DID NOT IMPINGE ON THE SPAR. FOUND DURING INSPECTION IAWAD/P68/46. 1 H 7 2 3O 3 O A31EU 1E10 5 C P920 2000073100031 20000731 00031 EA 2000 7 31 AU000090 2 20000120 G 8520 LWI3885MO6 BEARING PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA HARTZL HCE3Y HCE3YR2 GL ENGINE FAILED W K NONE E VIBRATION/BUFFET NR NOT REPORTED 1 AU S RL11668A (AUS) RIGHT ENGINE FRONT BEARING PICKED UP ON CRANKSHAFT. ENGINE SEIZED. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2000073100032 20000731 00032 SO 2000 7 31 AU000091 1 20000201 G 2810 07560106 PLUNGER MAULE M4 M4210 5460108 SO CONT O360 IO360A 17025 SO MCAULY 2A34C D2A34C67 GL FUEL STORAGE DETERIORATED W K NONE O OTHER IN INSP/MAINT 1 AU S 1042444 (AUS) FIREWALL MOUNTED FUEL STRAINER PLUNGER RUBBER NOT COMPATIBLE WITH FUEL PREVENTING FUEL FROM BEING DRAINED FROM STR AINER. PLUNGER WAS PURCHASED AND FITTED IN SEPTEMBER 1999. 1 H 7 1 3O 3 O 3A23 E1CE 5 C P3EA 2000073100033 20000731 00033 SO 2000 7 31 AU000092 1 20000205 G 3260 MS272402 SWITCH EMB 110 EMB110P1 3260122 SO PWA PT6 PT6A34 52043 EA HARTZL HCB3T HCB3TN3 GL LANDING GEAR POS INTERMITTENT W K NONE O N OTHER FALSE WARNING LD LANDING 1 AU S (AUS) RIGHT MAIN LANDING GEAR DOWNLOCK MICROSWITCH INTERMITTENT IN OPERATION. 1 L 7 2 4T 4 T A21SO E4EA 6 C P15EA 2000073100034 20000731 00034 EA 2000 7 31 AU000093 2 20000219 G 8530 LW12427 CYLINDER CESSNA 172 172P 2072436 CE LYC O360 O360A4M 41514 EA MCAULY 1A170 1A170CFA GL NR 4 SPARK PLUG CRACKED W K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CR CRUISE 1 AU S 1239 L3256136A (AUS) NR 4 CYLINDER CRACKED FROM LOWER SPARK PLUG HOLE TO EXHAUST PORT. 1 H 7 1 3O 3 O NT 3A12 E286 5 N P857 2000073100035 20000731 00035 EA 2000 7 31 AU000094 2 20000202 G 7324 254088 DIAPHRAGM BENDIX 25241783 GULSTM 500 500S 0141107 SW LYC O540 IO540E1B5 41532 EA FUEL DIVIDER WORN W K NONE E VIBRATION/BUFFET CL CLIMB 1 AU S AGA631 (AUS) LEFT ENGINE FUEL FLOW DIVIDER DIAPHRAGM FAILED DUE TO CHAFING ON THE VALVE PLATE. 1 H 7 2 3O 3 O 6A1 1E4 2000073100036 20000731 00036 SO 2000 7 31 AU000095 2 20000121 G 8540 534728 STUD CESSNA 404 404CESSNA 2075901 CE CONT O520 GTSIO520M 17032 SO MCAULY 3FF32 3FF32C501 GL IDLER GEAR SHEARED W K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CR CRUISE 1 AU S 1170 276417R 960416 (AUS) IDLER GEAR SUPPORT PIN SECURING STUD SHEARED. 1 L 7 2 3O 3 O A25CE E7CE 5 C P45GL 2000073100037 20000731 00037 CE 2000 7 31 AU000101 1 20000214 G 2800 FUEL TANK CESSNA 150 A152 2071836 CE LYC O235 O235L2C 41505 EA MCAULY 1A103 1A103TCM GL AIRCRAFT FUEL SY CONTAMINATED W K NONE E Y VIBRATION/BUFFET ENGINE STOPPAGE CR CRUISE 1 AU S (AUS) AIRCRAFT FUEL SYSTEM CONTAMINATED WITH WATER. THE FUEL SYSTEM HAD BEEN FLUSHED WITH WATER IAW AD/GEN/80A1 FOLLOWED BY APPROVED PURGING OF THE WATER FROM THE SYSTEM. COMPLETE ENGINE FAILURE OCCURRED IN-FLIGHT. WHEN THE GASCOLATOR WAS DRAINED AFTER LANDING, APPROXIMATELY 100 ML OF WATER WAS RECOVERED FROM THE DRAIN. 1 H 7 1 3O 3 O 3A19 E223 5 N P50GL 2000073100038 20000731 00038 CE 2000 7 31 AU000105 1 20000111 G 7500 25001 VALVE CESSNA 208 208 2073702 CE PWA PT6 PT6A114A 52043 NE ENGINE BLEED AIR FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S 19391 (AUS) BLEED AIR SOLENOID VALVE OPEN CIRCUITED. MOVING PARTS CORRODED. SUSPECT MOISTURE INGRESS. 1 H 7 1 3T 3 T NT A37CE E4EA 2000073100039 20000731 00039 SO 2000 7 31 AU000106 1 20000211 G 2822 421135 PUMP WELDON 421135 PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL FUEL BOOST PUMP FAILED W K NONE J WARNING INDICATION LD LANDING 1 AU S 15 10082 (AUS) RIGHT FUEL BOOST PUMP BLADE RETAINING RING BROKEN. PUMP HAD ONLY JUST BEEN FITTED FOLLOWING OVERHAUL AND HAD ONLY OPERATED FOR APPROXIMATELY FIFTEEN MINUTES. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2000073100040 20000731 00040 CE 2000 7 31 AU000109 1 20000211 G 5520 583410121 DOUBLER 5734100142 CESSNA 441 441 2076020 CE ELEVATOR STRUCTU CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S 0138 (AUS) LEFT AND RIGHT ELEVATOR DOUBLER PLATES CORRODED. 1 L 7 2 3T RT A28CE 2000073100041 20000731 00041 EU 2000 7 31 AU000111 1 20000125 G 7120 68120251 MOUNT PARTEN P68B PARTEN P68 P68B EU LYC O360 IO360A1B6 41514 EA HARTZL HCC2Y HCC2YK2 GL ENGINE MOUNT SEC CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 136 (AUS) LEFT AND RIGHT ENGINE MOUNTS CRACKED AND CORRODED. 1 H 7 2 3O 3 O A31EU 1E10 5 C P920 2000073100042 20000731 00042 SO 2000 7 31 AU000115 1 20000405 G 3211 AN717A BOLT PIPER PA38 PA38112 7103812 SO LYC O235 O235L2C 41505 EA SNSNCH 72C 72CK EA MAIN LANDING GEA CRACKED W O OTHER O OTHER LD LANDING 1 AU S (AUS) LEFT LANDING GEAR INBOARD ATTACHMENT BOLT FAILED. LEFT LANDING GEAR COLLAPSED. 1 L 7 1 3O 3 O A18SO E223 5 N P9045 2000073100043 20000731 00043 NE 2000 7 31 AU000117 2 20000411 G 7313 3017957 NOZZLE PWA BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A42 52043 NE MCAULY 4HFR34 4HFR34C754 NE FUEL INJECTOR NO IMPROPER PART W K NONE O OTHER IN INSP/MAINT 1 AU S AIJ234 (AUS) NR 13 FUEL NOZZLE TIP INCORRECT PART. PART FITTED IS PN 3017957. CORRECT PN 3019424. UNAPPROVED PART. 1 L 7 2 4T 4 T A24CE E4EA 6 C 3PNE 2000081000029 20000810 00029 CE 2000 8 10 AU000120 1 20000413 G 7430 A3600 CONTACTOR LYC CESSNA 172 172R 2072401 CE LYC IO360 IO360L2A EA IGNITION SWITCHI BURNED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) IGNITION SWITCH CONTACTS BURNT/DAMAGED. AIRCRAFT IS NOT SUBJECT TO AD/ELECT/59. 1 H 7 1 3O 3 O NT 3A12 1E10 2000081000030 20000810 00030 CE 2000 8 10 AU000121 1 20000328 G 5522 SKIN BEECH 95 95B55 1152729 CE CONT O470 IO470L 17026 SO MCAULY 2AF34C 2AF34C55 GL ELEVATOR PLATES/ CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 60 (AUS) LT AND RT ELEVATORS PN 96-61005-655 (LT) AND PN 96-61005-656 (RT) HAD CRACKS IN THE TOP AND BOTTOM SKINS. 1 L 7 2 3O 3 O RT 3A16 3E1 5 C P5EA 2000062800216 20000628 00216 SW 2000 6 28 AU000124 1 20000410 G 6230 412010407105 RING BELL BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE MAIN ROTOR MAST CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 1706 RE0160 (AUS) SWASHPLATE OUTER RING CRACKED. 1 G 7 2 4U 4 U H4SW E22EA 2000062800217 20000628 00217 NM 2000 6 28 AU000128 1 20000308 G 6310 A1902 BELT ROBSIN R22 R22BETA NM ENGINE/TRANSMISS FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE TO TRANSMISSION DRIVE BELTS FAILED. LIMITED INFORMATION PROVIDED. 1 G 7 1 3O H10WE 2000021900524 20000219 00524 2000 2 19 AU000128046 4 20000103 G 2562 SWITCH ARTEX 4530150A ELT FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 25271 (AU) INTERNAL G-SWITCH FAILED TO ENABLE INTERMITTENTLY RECERTIFICATION TESTING. 2000021900529 20000219 00529 SO 2000 2 19 AU000128053 2 20000105 G 8500 ENGINE CONT O300A CESSNA 170 170B 2072306 CE CONT O300 O300A 17022 SO MCAULY 1A170 1A170* GL NOSE SEIZED W K NONE O OTHER IN INSP/MAINT 1 CA 479 15335D9AR 15335D9AR M61393 (AU) ENGINE LOST ITS OIL AND SEIZED. OPERATOR SPECIFIED FROZEN BREATHER AS THE CAUSE. 1 H 7 1 3O 3 O A799 E253 5 N P857 2000081000031 20000810 00031 SO 2000 8 10 AU000129 1 20000104 G 3230 DOWNLOCK PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL LANDING GEAR RET LACK OF LUBE W K NONE O J OTHER WARNING INDICATION DE DESCENT 1 AU S (AUS) RIGHT MAIN LANDING GEAR DOWNLOCK PIVOT BOLTS STIFF DUE TO LACK OF LUBRICATION. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2000082800002 20000828 00002 WP 2000 8 28 AU000130 2 20000109 G 7200 ENGINE DHAV DHC2 DHC2* 2800108 EA GARRTT TPE331 TPE3312201A WP HARTZL HCB3T HCB3TN5 GL ENGINE FAILED W O OTHER E R X VIBRATION/BUFFET PARTIAL RPM/PWR LOSS ENGINE FLAMEOUT DE DESCENT 1 AU S 3577 P90202 BVA6348 (AUS) ENGINE FAILED IN-FLIGHT. 1 H 7 1 3R 4 T A806 E3WE 6 C P15EA 2000062800218 20000628 00218 EU 2000 6 28 AU000135 1 20000404 G 7714 0177555170 CONTROL BOX TMECA SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1A 60030 NE ENGINE RPM INDIC FAILED W K NONE E VIBRATION/BUFFET DE DESCENT 1 AU S 903B 4223 (AUS) ENGINE TACHOMETRIC BOX FAILED. SUSPECT CAUSED BY INTERNAL COMPONENT FAILURE. 1 G 7 1 3U 3 U H9EU E19EU 2000062800219 20000628 00219 NM 2000 6 28 AU000136 1 20000310 G 7160 INTAKE DUCT LYC ROBSIN R22 R22BETA NM LYC O320 O320B2C 41508 EA ENGINE AIR INTAK CONTAMINATED W K NONE Y ENGINE STOPPAGE NR NOT REPORTED 1 AU S L1813339A (AUS) AIR INTAKE HOUSING BLOCKED BY WATER FOLLOWING LANDING IN FLOOD WATER. ENGINE FAILURE CAUSED A HARD LANDING WHICH RESULTED IN DAMAGE TO THE LANDING GEAR, ENGINE FRAMES AND BELLY SKIN. 1 G 7 1 3O 3 O H10WE E274 2000082800003 20000828 00003 CE 2000 8 28 AU000137 1 20000316 G 5310 STRUCTURE CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO MCAULY 3AF32C 3AF32C505 GL FUSELAGE MAIN ST FRACTURED W K NONE O OTHER LD LANDING 1 AU S (AUS) NOSE LANDING GEAR NACELLE STRUCTURE FAILED IN THE AREA OF THE UPPER ACTUATOR ATTACHMENT POINT. NLG COLLAPSED DURI NG LANDING CAUSING DAMAGE TO THE SURROUNDING STRUCTURE AND BOTH PROPELLERS. SUSPECT STRUCTURE HAD BEEN DAMAGED FOR SOME TIME BEFORE FINAL FAILURE. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2000082800004 20000828 00004 EU 2000 8 28 AU000142 1 20000125 G 2497 WIRE PILATS PC12 PC12 7090550 EU DC POWER DISTRIB LOOSE W O OTHER H ELECT. POWER LOSS-50 PC NR NOT REPORTED 1 AU S (AUS) GENERATOR GROUND CABLE BOLT LOOSE WITH ARCING AND PITTING OF THE FRAME AND DOUBLER. 1 L 7 1 3T RT A78EU 2000082800005 20000828 00005 SO 2000 8 28 AU000143 2 20000313 G 7310 LINE CONT CESSNA 404 404CESSNA 2075901 CE CONT O520 GTSIO520M 17032 SO MCAULY 3FF32 3FF32C501 GL ENGINE FUEL DIST MISINSTALLED W K NONE E VIBRATION/BUFFET CL CLIMB 1 AU S (AUS) LEFT ENGINE UPPER DECK PRESSURE LINES NOT FITTED TO NR 4 AND NR 6 CYLINDERS. 1 L 7 2 3O 3 O A25CE E7CE 5 C P45GL 2001011105803 20010111 05803 SO 2001 1 11 AU000147 1 20000417 G 5531 4429400 RIB PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL VERTICAL STAB CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) VERTICAL STABILIZER RIB CRACKED. FORWARD SPAR RIVETS LOOSE. DRAG ANGLE PN 71059-06 CRACKED. CRACK LENGTH 20 MM (0.787 INCH). 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2000082800006 20000828 00006 SO 2000 8 28 AU000148 2 20000311 G 8530 ROCKERBOSS CYLINDER CONT CESSNA 182 182P 2075816 CE CONT O470 O470R 17026 SO MCAULY 2A34C 2A34C203 GL ENGINE BROKEN W K NONE E VIBRATION/BUFFET CL CLIMB 1 AU S 438 (AUS) NR 2 CYLINDER EXHAUST VALVE ROCKER BOSS BROKEN. 1 H 7 1 3O 3 O NT TA13 E273 5 C P3EA 2000082800007 20000828 00007 GL 2000 8 28 AU000152 3 20000405 G 6110 PROPELLER HARTZL PILATS PC12 PC12 7090550 EU HARTZL HCE4A HCE4A3D GL PROPELLER ASSY DAMAGED W K NONE C F.O.D. NR NOT REPORTED 1 AU S HJ326 (AUS) PROPELLER STRIKE (KANGAROO). PROPELLER AND ENGINE INSPECTED IAW MAINTENANCE MANUALS WITH NO DEFECTS FOUND. 1 L 7 1 3T RT A78EU 5 C P210NE 2000082800008 20000828 00008 CE 2000 8 28 AU000153 1 20000327 G 5753 3516505084 RIB BEECH 33 F33A 1151425 CE CONT O520 IO520B 17032 SO MCAULY 3A32C 3A32C76 GL TE FLAP STRUCTUR CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT AND RT FLAP RIBS CRACKED. RIBS ARE LOCATED IMMEDIATELY BENEATH THE FLAP ACTUATING BRACKET. 1 L 7 1 3O 3 O 3A15 E5CE 5 C P21EA 2000082800009 20000828 00009 CE 2000 8 28 AU000154 1 20000321 G 5753 3516505084 RIB BEECH 33 F33A 1151425 CE CONT O520 IO520B 17032 SO MCAULY 3A32C 3A32C76 GL TE FLAP STRUCT CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT AND RT FLAP RIBS CRACKED. RIBS ARE LOCATED IMMEDIATELY BENEATH THE FLAP ACTUATING BRACKET. 1 L 7 1 3O 3 O 3A15 E5CE 5 C P21EA 2000082800010 20000828 00010 CE 2000 8 28 AU000156 1 20000217 G 2822 476411 PUMP CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO FUEL BOOST PUMP BURNED OUT W K NONE O OTHER IN INSP/MAINT 1 AU S 277331 (AUS) RIGHT MAIN FUEL TANK TRANSFER PUMP CONNECTOR BURNT AND BLACKENED. 1 L 7 2 3O 3 O 3A10 E5CE 2000082800011 20000828 00011 CE 2000 8 28 AU000157 1 20000228 G 5312 BULKHEAD BEECH 200 B200C 1152924 CE PWA PT6 PT6A42 52043 NE FUSELAGE MAIN BU CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) REAR PRESSURE BULKHEAD LOCATED AT BS 346.75 CRACKED IN TWO PLACES. 1 L 7 2 4T 4 T A24CE E4EA 2000083000070 20000830 00070 CE 2000 8 30 AU000158 1 20000222 G 5311 207 FRAME BEECH 200 B200C 1152924 CE PWA PT6 PT6A42 52043 NE FUSELAGE MAIN FR CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUSELAGE FRAME 207 CRACKED. 1 L 7 2 4T 4 T A24CE E4EA 2000083000071 20000830 00071 CE 2000 8 30 AU000159 1 20000222 G 5311 207 FRAME BEECH 200 B200T 1152929 CE PWA PT6 PT6A42 52043 NE FUSELAGE MAIN FR CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUSELAGE FRAME 207 CRACKED. 1 L 7 2 4T 4 T A24CE E4EA 2000082800012 20000828 00012 CE 2000 8 28 AU000160 1 20000222 G 5311 207 FRAME BEECH 200 B200C 1152924 CE PWA PT6 PT6A42 52043 NE FUSELAGE MAIN FR CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUSELAGE FRAME 207 CRACKED. 1 L 7 2 4T 4 T A24CE E4EA 2000082100071 20000821 00071 EA 2000 8 21 AU000164 2 20000130 G 8540 L44162 GEARBOX PIPER PA31 PA31P 7103120 SO LYC O541 TIGO541E1A 41539 EA ENGINE FAILED W K NONE E VIBRATION/BUFFET CL CLIMB 1 AU S L44162 (AUS) ENGINE SUSPECT GEARBOX FAILURE. 1 L 7 2 3O 3 O A8EA E19EA 2000062800220 20000628 00220 SW 2000 6 28 AU000165 1 20000328 G 5313 47322241173 LONGERON BELL 47G BELL 47 47G5A 1181034 SW LYC O435 VO435B1A 41516 EA FUSELAGE MAIN LO CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUSELAGE LOWER LONGERON CRACKED. FOUND DURING X-RAY INSPECTION IAW AD/BELL47/62 AMDT2. 1 G 7 1 3O 3 O 2H3 E279 2000082100129 20000821 00129 CE 2000 8 21 AU000167 1 20000228 G 5312 10144009811 BULKHEAD BEECH 200 B200C 1152924 CE PWA PT6 PT6A42 52043 NE FUSELAGE MAIN BU CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) REAR PRESSURE BULKHEAD TOP WEB CRACKED IN SEVERAL PLACES. 1 L 7 2 4T 4 T A24CE E4EA 2000082800013 20000828 00013 CE 2000 8 28 AU000168 1 20000210 G 3230 3581507714 UPLOCK ELECTRIC BEECH 33 F33A 1151425 CE CONT O520 IO520B 17032 SO MCAULY 3A32C 3A32C76 GL LANDING GEAR RET CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LANDING GEAR UPLOCK ACTUATING BOLT HOLE CORRODED AND WORN. 1 L 7 1 3O 3 O 3A15 E5CE 5 C P21EA 2000082300002 20000823 00002 WP 2000 8 23 AU000170 2 20000221 G 7322 89711014 FCU CESSNA 441 441 2076020 CE GARRTT TPE331 TPE3318 01514 WP HARTZL HCB3T HCB3TN5 GL FUEL CONTROL/CAR FAULTY W E ENGINE SHUTDOWN E B VIBRATION/BUFFET SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 AU S 271 P31330 (AUS) RT ENGINE FUEL CONTROL UNIT FAULTY. 1 L 7 2 3T 4 T RT A28CE E4WE 6 C P15EA 2000081700020 20000817 00020 CE 2000 8 17 AU000174 1 20000229 G 2460 507250101 CIRCUIT BREAKER BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL DC POWER DISTRIB CORRODED W K NONE J WARNING INDICATION CR CRUISE 1 AU S 8071381011 BU4983BU9782 (AUS) CIRCUIT BREAKER PANEL CORRODED DUE TO WATER INGRESS THROUGH THE COPILOT''S DV WINDOW. 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2000081700021 20000817 00021 CE 2000 8 17 AU000176 1 20000207 G 2430 DGR3 CONTROL PANEL CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO HARTZL HCJ3Y PHCJ3YF1 GL DC GENERATING SY BURNED W K NONE B SMOKE/FUMES/ODORS/SPARKS DE DESCENT 1 AU S 574090 FP1051376 (AUS) ALTERNATOR CONTROL UNIT INTERNAL FAULT. 1 H 7 1 3O 3 O A4CE E5CE 5 C P36EA 2000100300131 20001003 00131 SW 2000 10 3 AU000179 1 20000210 G 3211 AN423A BOLT GULSTM 112 114 7630314 SW LYC O540 IO540T4B5 41532 EA HARTZL HCC2Y HCC2YR1 GL MAIN LANDING GEA BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MAIN LANDING GEAR STRUT TRUNNION PIN RETAINING BOLT CRACKED. TRUNNION PIN ALSO WORN. 1 L 7 1 3O 3 O A12SO 1E4 5 C P920 2000081700022 20000817 00022 CE 2000 8 17 AU000180 1 20000223 G 3230 96820034 SHAFT BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO HARTZL HCJ3Y PHCJ3YF2 GL LANDING GEAR RET FAILED W K NONE O OTHER LD LANDING 1 AU S (AUS) NOSE LANDING GEAR ACTUATING SHAFT SUSPECT ILLEGAL REPAIRS. NLG DOOR APPEARS TO HAVE CLOSED DURING RETRACTION CAUS ING THE NLG TO FOUL. 1 L 7 2 3O 3 O 3A16 E5CE 5 C P36EA 2000081700025 20000817 00025 NE 2000 8 17 AU000182 2 20000220 G 8530 27056 PISTON DHAV DHC2 DHC2* 2800108 EA PWA R985 R985AN14B 52008 NE RING LANDS CRACKED W K NONE E VIBRATION/BUFFET CL CLIMB 1 AU S 521 4219276 (AUS) PISTON CRACKED FROM GUDGEON PIN HOLE, THROUGH THE RING LANDS TO THE CENTRE OF THE PISTON CROWN. 1 H 7 1 3R 3 R A806 5E1 2000081700026 20000817 00026 CE 2000 8 17 AU000183 1 20000217 G 2822 476411 PUMP CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO FUEL BOOST PUMP FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S 277548R (AUS) LEFT MAIN FUEL TANK TRANSFER PUMP FAILED. INSPECTION FOUND BURNT CONNECTOR. 1 L 7 2 3O 3 O 3A10 E5CE 2000081700028 20000817 00028 EA 2000 8 17 AU000188 2 20000216 G 8520 LW16508 CAMSHAFT LYC PIPER PA44 PA44180 7104402 SO LYC O360 O360E1A6 41514 EA ENGINE SPALLED W K NONE O OTHER IN INSP/MAINT 1 AU S L267775 (AUS) CAMSHAFT PN LW16508 LOBE SPALLED. CORRESPONDING TAPPET PN LW16812 ALSO SPALLED. METAL CONTAMINATION OF OIL SYSTEM . 1 L 7 2 3O 3 O A19S0 E286 2000070600234 20000706 00234 GL 2000 7 6 AU000195 2 20000305 G 7260 BEARING BELL 206 206L1 1182107 SW ALLSN 250C 250C30 03013 GL TURBINE ENGINE WORN W K NONE O OTHER NR NOT REPORTED 1 AU S 89007 (AUS) ENGINE ACCESSORY GEARBOX 2.5 BEARING WORN. METAL CONTAMINATION OF OIL SYSTEM. 1 G 7 1 3U 3 U H2SW E1GL 2000081700033 20000817 00033 SO 2000 8 17 AU000202 1 20000314 G 2497 WIRE PIPER PA28 PA28RT201 7102818 SO LYC O360 IO360C1C6 41514 EA MCAULY 2D34C 2D34C215 GL ELECTRICAL POWER FAULTY W O OTHER B SMOKE/FUMES/ODORS/SPARKS DE DESCENT 1 AU S (AUS) ELECTRICAL BURNING SMELL IN COCKPIT. NO EVIDENCE OF FIRE DAMAGE. TEST FLIGHT OK. AIRCRAFT RETURNED TO SERVICE. 1 L 7 1 3O 3 O 2A13 1E10 5 C P7EA 2000081700034 20000817 00034 GL 2000 8 17 AU000203 3 20000420 G 6111 A163634 RETAINER MCAULY REIMS 406 F406 EU PWA PT6 PT6A112 52043 NE MCAULY 3G34C7 3GFR34C701 GL PROPELLER BLADE DAMAGED W K NONE O OTHER LD LANDING 1 AU S PCE12098 881779 (AUS) LEFT PROPELLER FEEDBACK RING RETAINING CIRCLIP DEFORMED. PROPELLER WENT TO UNCOMMANDED FULL REVERSE ON LANDING. 1 L 7 2 3T 3 T RT A54EU E4EA 5 C P60GL 2000082200026 20000822 00026 CE 2000 8 22 AU000208 1 20000301 G 3260 JE3 ACTUATOR ISE13 CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO MCAULY 3AF32C 3AF32C87 GL LANDING GEAR POS BROKEN W K NONE O P OTHER NO WARNING INDICATION LD LANDING 1 AU S (AUS) LEFT MAIN LANDING GEAR DOWN MICROSWITCH ACTUATOR LEAF BROKEN. 1 L 7 2 3O 3 O 3A10 E5CE 5 C P22EA 2000082200027 20000822 00027 SO 2000 8 22 AU000209 1 20000217 G 5310 31420 STRUCTURE PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2B 41532 EA HARTZL HCE3Y HCE3YR2 GL FUSELAGE MAIN ST DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RIGHT FORWARD WING ATTACHMENT FITTING TO FUSELAGE UNDER TENSION. THE FUSELAGE IN THIS AREA BULGING AND CRACKING. INTERNAL STRESS DAMAGE AND CRACKING. CAUSE OF DAMAGE UNKNOWN. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2000082200028 20000822 00028 CE 2000 8 22 AU000210 1 20000317 G 5414 PANEL BEECH 200 B200C 1152924 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL PLATE/SKIN MISSING W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RIGHT NACELLE FUEL DRAIN PANEL NOT REINSTALLED FOLLOWING MAINTENANCE. SAFETY PLUG AND LOCKWIRE ALSO MISSING. 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2000082200029 20000822 00029 SO 2000 8 22 AU000211 1 20000222 G 2731 62701111 CONTROL CABLE PIPER PA28 PA28R201 7102816 SO LYC O360 IO360C1C6 41514 EA MCAULY 2D34C B2D34C213 GL ELEVATOR TAB CON FRAYED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FORWARD TRIM CABLE FRAYED. 1 L 7 1 3O 3 O 2A13 1E10 5 C P7EA 2000072600079 20000726 00079 SO 2000 7 26 AU000214 2 20000307 G 8530 EXHAUST VALVE CONT O200A CESSNA 150 150M 2071830 CE CONT O200 O200A 17020 SO MCAULY 1A102 1A102OCM GL ENGINE SEIZED W K NONE O OTHER IN INSP/MAINT 1 AU S 1340 252651A48 (AUS) NR 4 CYLINDER EXHAUST VALVE SEIZED. 1 H 7 1 3O 3 O 3A19 E252 5 N P918 2000072600087 20000726 00087 SW 2000 7 26 AU000216 1 20000322 G 2810 5630061502 FUEL CELL GULSTM 500 500S 0141107 SW LYC O540 IO540E1B5 41532 EA FUEL STORAGE DETERIORATED W K NONE O K OTHER FLUID LOSS IN INSP/MAINT 1 AU S (AUS) RIGHT FORWARD AND AFT AND LEFT FORWARD INBOARD FUEL CELLS DETERIORATED AND LEAKING. 1 H 7 2 3O 3 O 6A1 1E4 2000072600088 20000726 00088 SW 2000 7 26 AU000217 1 20000322 G 2810 5630080502 FUEL CELL GULSTM 500 500S 0141107 SW LYC O540 IO540E1B5 41532 EA FUEL STORAGE DETERIORATED W K NONE O K OTHER FLUID LOSS IN INSP/MAINT 1 AU S (AUS) RIGHT FORWARD AND AFT AND LT FORWARD INBOARD FUEL CELLS DETERIORATED AND LEAKING. 1 H 7 2 3O 3 O 6A1 1E4 2000072600249 20000726 00249 SW 2000 7 26 AU000218 1 20000322 G 2810 5630060501 FUEL CELL GULSTM 500 500S 0141107 SW LYC O540 IO540E1B5 41532 EA FUEL STORAGE DETERIORATED W K NONE O K OTHER FLUID LOSS IN INSP/MAINT 1 AU S (AUS) RIGHT FORWARD AND AFT AND LEFT FORWARD INBOARD FUEL CELLS DETERIORATED AND LEAKING. 1 H 7 2 3O 3 O 6A1 1E4 2000072600095 20000726 00095 SO 2000 7 26 AU000221 1 20000316 G 2434 762489 STATOR CHRYSLER 4111810 PIPER PA28 PA28151 7102805 SO DC GENERATOR-ALT LOOSE W K NONE H ELECT. POWER LOSS-50 PC NR NOT REPORTED 1 AU S 02317 (AUS) ALTERNATOR STATOR WINDINGS LOOSE CAUSING CHAFING AND SHORT CIRCUIT. 1 L 7 1 3O 2A13 2000072600096 20000726 00096 EA 2000 7 26 AU000226 2 20000327 G 8530 74541 EXHAUST VALVE PIPER PA28 PA28180 7102808 SO LYC O360 O360A3A 41514 EA SNSNCH 76E M76EMM EA ENGINE BROKEN W K NONE E R E VIBRATION/BUFFET PARTIAL RPM/PWR LOSS VIBRATION/BUFFET CR CRUISE 1 AU S L840136A (AUS) NR 2 CYLINDER EXHAUST VALVE FAILED. NR 2 CYLINDER AND SPARK PLUGS DAMAGED. A FRAGMENT OF THE FAILED EXHAUST VALV E WAS INGESTED BY NR 3 CYLINDER CAUSING INTERNAL DAMAGE. 1 L 7 1 3O 3 O 2A13 E286 5 N P4EA4 2000072600097 20000726 00097 NM 2000 7 26 AU000227 1 20000101 G 2820 200072001 PIPE PIPER PA60 PA60602P 7106015 NM LYC O540 IO540AA1A 41532 NE ACFT FUEL DISTRI CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LEFT WING FUEL PIPE CORRODED. 1 M 7 2 3O 3 O RT A17WE 1EA 2000072600252 20000726 00252 CE 2000 7 26 AU000228 1 20000405 G 3230 1454 BUSHING CESSNA 991015403 CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO LANDING GEAR RET CONTAMINATED W K NONE O OTHER LD LANDING 1 AU S (AUS) EMERGENCY LANDING GEAR BLOW DOWN BOTTLE HANDLE WOULD NOT OPERATE. INVESTIGATION FOUND THE TEFLON BUSHING LOCATED BETWEEN THE FIRING PLUNGER AND THE OUTLET LINE BLOCK WAS SWOLLEN AND JAMMED PREVENTING THE BOTTLE FROM FIRING. OIL CONT AMINATION WAS FOUND IN THE BOTTLE HEAD. 1 L 7 2 3O 3 O A7CE E8CE 2000072600254 20000726 00254 CE 2000 7 26 AU000229 1 20000426 G 3233 115380025 MOTOR BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL LANDING GEAR ACT FAULTY W O OTHER O OTHER LD LANDING 1 AU S (AUS) LANDING GEAR MOTOR FAILED TO OPERATE. 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2000072600100 20000726 00100 CE 2000 7 26 AU000236 1 20000311 G 2750 FLAP BEECH 200 200CBEECH 1152926 CE PWA PT6 PT6A42 52043 NE TE FLAP CONTROL FAULTY W K NONE F FLT CONT AFFECTED DE DESCENT 1 AU S (AUS) FLAPS WOULD NOT EXTEND. INVESTIGATION COULD FIND NO FAULT AND THE FLAPS HAVE OPERATED CORRECTLY SINCE. 1 L 7 2 4T 4 T A24CE E4EA 2000072600255 20000726 00255 SO 2000 7 26 AU000237 1 20000402 G 2840 2405105 PIPE PIPER PA30 PA30 7103002 SO LYC O320 IO320* 41508 EA HARTZL HCE2Y HCE2YR2 GL ACFT FUEL INDICA LEAKING W K NONE K FLUID LOSS CL CLIMB 1 AU S (AUS) RIGHT FUEL FLOW LINE LOCATED AT BACK OF INSTRUMENT INADEQUATELY FLARED. FUEL LEAKING. 1 L 7 2 3O 3 O A1EA 1E12 5 C P9EA 2000072600256 20000726 00256 SO 2000 7 26 AU000240 1 20000308 G 2842 550695 TRANSMITTER PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL FUEL QUANTITY SE CORRODED W K NONE O OTHER CR CRUISE 1 AU S (AUS) RIGHT FUEL TANK SENDERS OPEN CIRCUITED AND CORRODED. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2000072600101 20000726 00101 SO 2000 7 26 AU000241 1 20000308 G 2842 550696 TRANSMITTER PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL FUEL QUANTITY SE CORRODED W K NONE O OTHER CR CRUISE 1 AU S (AUS) RIGHT FUEL TANK SENDERS OPEN CIRCUITED AND CORRODED. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2000072600102 20000726 00102 SO 2000 7 26 AU000242 2 20000423 G 7421 RHB32E SPARK PLUG CONT IO520F CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO MCAULY 3A32C D3A32C90 GL SPARK PLUG/IGNIT FAULTY W K NONE E VIBRATION/BUFFET CR CRUISE 1 AU S 286164R (AUS) NR 3 CYLINDER SPARK PLUGS (2 OFF) BRIDGED ACROSS ELECTRODES. 1 H 7 1 3O 3 O A4CE E5CE 5 C P21EA 2000082800014 20000828 00014 SO 2000 8 28 AU000243 1 20000415 G 5101 347350298 STRUCTURE PIPER PA34 PA34200 7103405 SO HARTZL HCC2Y HCC2YK2 GL AIRCRAFT SUB-STA DETERIORATED W K NONE O OTHER IN INSP/MAINT 1 AU S AU2714AU2576 (AUS) AIRCRAFT RECEIVED FOR COFA IN A DETERIORATED CONDITION. COMPASS UNSERVICEABLE LT AND RT ENGINE MIXTURE, THROTTLE AND ALTERNATE AIR CONTROL ROD ENDS UNSERVICEABLE. LT AND RT ENGINE MANIFOLD FUEL DRAINS OPEN TO ATMOSPHERE, RT MLG DOOR CRACKED. RT ENGINE AIR FILTER HOUSING COVER UNSERVICEABLE. LT ENGINE AIR FILTER HOUSING AND COVER UNSERVICEABLE. LT AND RT INDUCTION HOSES COLLAPSED. SCAT HOSES USED IN LIEU OF GENUINE PIPER AIR DUCT. ALL BRAKE LININGS AND DISCS UNSE RVICEABLE. AILERON AND FLAP ROD ENDS WORN BEYOND LIMITS. RT AILERON BALANCE WEIGHT TO AILERON CORRODED. PILOTS CONTRO L WHEEL UNIVERSAL COUPLING UNSERVICEABLE. RT MLG BRAKE HOSE WORN THROUGH. 1 L 7 2 3O A7SO 5 C P920 2000072600257 20000726 00257 SO 2000 7 26 AU000245 2 20000412 G 7414 1050765 CLAMP BENDIX S6LN25T CESSNA 337 337 2075702 CE CONT O360 IO360D 17025 SO MCAULY 2AF34C D2AF34C306 GL MAGNETO/DISTRIBU BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S 338 898959 57083 (AUS) FRONT ENGINE RIGHT MAGNETO COIL ATTACHMENT CLAMPS BROKEN. FOUND DURING INSPECTION IAW AD/ELECT/68. 1 H 7 2 3O 3 O A6CE E1CE 5 C P5EA 2000073100015 20000731 00015 GL 2000 7 31 AU000248 1 20000307 G 8010 RELAY LYC PAC CT4 CT4A 05623UC GL CONT O360 IO360HB 17025 SO HARTZL HCC2Y BHCC2YF1 GL ENGINE CRANKING STUCK W K NONE E VIBRATION/BUFFET CL CLIMB 1 AU S (AUS) ENGINE STARTER SOLENOID RELAY JAMMED IN THE ON POSITION. STARTER MOTOR WOULD NOT DISENGAGE. (X) 1 Q 7 1 3I 3 O RT A9PC E1CE 5 C P920 2000072600120 20000726 00120 EA 2000 7 26 AU000250 2 20000406 G 7310 25243271 VALVE BENDIX RSA5 PIPER PA30 PA30 7103002 SO LYC O320 IO320B1A 41508 EA HARTZL HCE2Y HCE2YL2 GL ENGINE FUEL DIST CONTAMINATED W O OTHER E VIBRATION/BUFFET CR CRUISE 1 AU S L441755A (AUS) RIGHT ENGINE FUEL DISTRIBUTOR VALVE VENT HOLE BLOCKED BY A GREASE TYPE SUBSTANCE APPLIED TO THE DIAPHRAGM SPRING. 1 L 7 2 3O 3 O A1EA 1E12 5 C P9EA 2000072600103 20000726 00103 SO 2000 7 26 AU000252 1 20000209 G 2434 762489 STATOR CHRYSLER 4111810 PIPER PA28 PA28161 7102803 SO LYC O320 O320D3G 41508 EA SNSNCH 74D 74DM EA DC GENERATOR-ALT LOOSE W K NONE H ELECT. POWER LOSS-50 PC CR CRUISE 1 AU S 271 9021856 (AUS) ALTERNATOR STATOR LOOSE. STATOR WINDINGS SHORT CIRCUITED. 1 L 7 1 3O 3 O 2A13 E274 5 N P88614 2000071200112 20000712 00112 SW 2000 7 12 AU000253 1 20000404 G 3230 ES10106 DRAG BRACE GULSTM 500 500S 0141107 SW LYC O540 IO540E1B5 41532 EA HARTZL HCA3V HCA3VK2 GL LANDING GEAR RET FRACTURED W O OTHER C F.O.D. TO TAKEOFF 1 AU S (AUS) NOSE LANDING GEAR DRAG BRACE FAILED AFTER THE AIRCRAFT STRUCK A KANGAROO ON TAKEOFF. THE NLG COLLAPSED DURING LAN DING. 1 H 7 2 3O 3 O 6A1 1E4 5 C P6EA 2000072600104 20000726 00104 SW 2000 7 26 AU000254 1 20000404 G 3230 ES10107 DRAG BRACE GULSTM 500 500S 0141107 SW LYC O540 IO540E1B5 41532 EA HARTZL HCA3V HCA3VK2 GL LANDING GEAR RET FRACTURED W A UNSCHED LANDING C F.O.D. TO TAKEOFF 1 AU S (AUS) NOSE LANDING GEAR DRAG BRACE FAILED WHEN THE AIRCRAFT STRUCK A KANGAROO ON TAKEOFF. NLG COLLAPSED DURING LANDING. 1 H 7 2 3O 3 O 6A1 1E4 5 C P6EA 2000071800156 20000718 00156 WP 2000 7 18 AU000258 1 20000412 G 6310 4474 CLUTCH ROBSIN R22 R22 7640102 WP LYC O320 O320B2C 41508 EA ENGINE/TRANSMISS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 570 (AUS) CLUTCH ASSEMBLY FREE WHEEL UNIT REAR FACE PLATE CRACKED. 1 G 7 1 3O 3 O H10WE E274 2000072600121 20000726 00121 SO 2000 7 26 AU000259 2 20000407 G 8530 PISTON CONT CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO MCAULY 3AF32C 3AF32C505 GL ENGINE FAILED W O OTHER E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CL CLIMB 1 AU S (AUS) NR 2 CYLINDER PISTON HOLED. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2000072700045 20000727 00045 EA 2000 7 27 AU000262 2 20000303 G 8520 CRANKCASE LYC CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA MCAULY 1A103 1A103TCM GL ENGINE CRACKED W K NONE O K OTHER FLUID LOSS IN INSP/MAINT 1 AU S L2161415 (AUS) CRANKCASE CRACKED IN THE AREA BETWEEN NR 2 AND NR 4 CYLINDERS. 1 H 7 1 3O 3 O NT 3A19 E223 5 N P50GL 2000073100016 20000731 00016 SO 2000 7 31 AU000263 1 20000217 G 5310 31420 STRUCTURE PIPER PIPER PA31 PA31310 7103103 SO LYC O540 TIO540A2B 41532 EA HARTZL HCE3Y HCE3YR2 GL FUSELAGE MAIN ST DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUSELAGE SKIN CRACKED IN AREA OF LEFT WING FORWARD ATTACHMENT FITTING. INTERNAL STRUCTURE ALSO DAMAGED IN THE SAME AREA. CENTER SECTION LOWER FUSELAGE FRAMES BUCKLED AND LOWER SKIN DAMAGED. 1 L 7 1 3O 3 O RT A20SO E14EA 5 C P33EA 2000071800161 20000718 00161 NM 2000 7 18 AU000266 1 20000329 G 6310 A1902 BELT ROBSIN R22 R22BETA NM ENGINE/TRANSMISS FAULTY W K NONE O J OTHER WARNING INDICATION IN INSP/MAINT 1 AU S (AUS) DRIVE BELT SET FAULTY. 1 G 7 1 3O H10WE 2000073100017 20000731 00017 SO 2000 7 31 AU000267 1 20000216 G 5730 62061002 SKIN PIPER PA28 PA28181 7102807 SO LYC O360 O360A4M 41514 EA SNSNCH 76E 76EM8 EA WING PLATES/SKIN CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) WING SKIN CRACKED. 1 L 7 1 3O 3 O 2A13 E286 5 N P4EA 2000081000003 20000810 00003 SO 2000 8 10 AU000272 2 20000319 G 7300 FUEL TANK CONT O200A CESSNA 150 A150M 2071831 CE CONT O200 O200A 17020 SO ENGINE FUEL & CO CONTAMINATED W K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS TO TAKEOFF 1 AU S (AUS) ENGINE FUEL SYSTEM CONTAMINATED WITH EDA (ETHYLINE DIAMINE). EVIDENCE OF EDA IN CARBURETOR AND FUEL FILTERS. 1 H 7 1 3O 3 O 3A19 E252 2000081000004 20000810 00004 SO 2000 8 10 AU000279 2 20000209 G 7310 AN78022 FITTING CONT 63135111 PAC CT4 CT4A 05623UC GL CONT O360 IO360HB 17025 SO HARTZL HCC2Y BHCC2YF1 GL ENGINE FUEL DIST DAMAGED W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S 128803CR (AUS) DISTRIBUTOR VALVE TO FUEL INJECTOR LINE FITTING LOOSE. INVESTIGATION FOUND DAMAGED THREADS WHICH ALLOWED THE NUT TO LOOSEN. FUEL LEAKING FROM FITTING. 1 Q 7 1 3I 3 O RT A9PC E1CE 5 C P920 2000082800015 20000828 00015 CE 2000 8 28 AU000281 1 20000114 G 5101 PAINT CESSNA 404 404CESSNA 2075901 CE CONT O520 GTSIO520M 17032 SO MCAULY 3FF32 3FF32C501 GL EXTERIOR COLOUR FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) DURING REPAINTING, THE PRIMER WOULD NOT ADHERE TO THE AIRCRAFT. SUSPECT ONE PART OF THE TWO PART PAINT WAS INCORR ECT. UNAPPROVED PART. 1 L 7 2 3O 3 O A25CE E7CE 5 C P45GL 2000081000005 20000810 00005 SW 2000 8 10 AU000282 1 20000322 G 2810 5630061502 FUEL CELL GULSTM 500 500S 0141107 SW LYC O540 IO540E1B5 41532 EA FUEL STORAGE DETERIORATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RIGHT FORWARD AND AFT AND LEFT FORWARD FUEL CELLS HOLED DUE TO CELL DETERIORATION. FUEL LEAKING FROM CELLS. 1 H 7 2 3O 3 O 6A1 1E4 2000081000006 20000810 00006 SW 2000 8 10 AU000283 1 20000322 G 2810 5630080502 FUEL CELL GULSTM 500 500S 0141107 SW LYC O540 IO540E1B5 41532 EA FUEL STORAGE DETERIORATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RIGHT FORWARD AND AFT AND LEFT FORWARD FUEL CELLS HOLED DUE TO CELL D TERIORATION. FUEL LEAKING FROM CELLS. 1 H 7 2 3O 3 O 6A1 1E4 2000081000007 20000810 00007 SW 2000 8 10 AU000284 1 20000322 G 2810 5360060501 FUEL CELL GULSTM 500 500S 0141107 SW LYC O540 IO540E1B5 41532 EA FUEL STORAGE DETERIORATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RIGHT FORWARD AND AFT AND LEFT FORWARD FUEL CELLS HOLED DUE TO CELL DETERIORATION. FUEL LEAKING FROM CELLS. 1 H 7 2 3O 3 O 6A1 1E4 2000081000008 20000810 00008 EU 2000 8 10 AU000285 1 20000203 G 2800 FUEL TANK NOORDN AT16 AT16HARVARD EU PWA R1340 R1340AN1 52016 NE HAMSTD 12D 12D40 NE AIRCRAFT FUEL SY CONTAMINATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) AIRCRAFT FUEL SYSTEM CONTAMINATED WITH ETHYLENE DIAMINE (EDA). 1 L 7 1 3R 3 R AR11 5E2 5 C P257 2000081000009 20000810 00009 CE 2000 8 10 AU000286 1 20000211 G 2800 FUEL TANK CESSNA 182 R182 2072734 CE LYC O540 O540J3C5 41532 EA AIRCRAFT FUEL SY CONTAMINATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) AIRCRAFT FUEL SYSTEM CONTAMINATED ETHYLENE DIAMINE (EDA). 1 H 7 1 3O 3 O RT 3A13 E295 2000081000010 20000810 00010 SO 2000 8 10 AU000287 1 20000201 G 2800 FUEL TANK PIPER PA32 PA32R300 7103213 SO LYC O540 IO540K1G5 41532 EA HARTZL HCC2Y HCC2YK2 GL AIRCRAFT FUEL SY CONTAMINATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) AIRCRAFT FUEL SYSTEM CONTAMINATED WITH ETHYLENE DIAMINE (EDA). 1 L 7 1 3O 3 O A3SO 1E4 5 C P920 2000081000011 20000810 00011 SO 2000 8 10 AU000288 1 20000207 G 2800 FUEL TANK PIPER PA28 PA28140 7102802 SO LYC O320 O320E2A 41508 EA SNSNCH 74D 74DM EA AIRCRAFT FUEL SY CONTAMINATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) AIRCRAFT FUEL SYSTEM CONTAMINATED WITH ETHYLENE DIAMINE (EDA). 1 L 7 1 3O 3 O 2A13 E274 5 N P88614 2000081000012 20000810 00012 CE 2000 8 10 AU000289 1 20000201 G 2800 FUEL TANK BEECH 33 35B33 1151406 CE CONT O470 IO470K 17026 SO MCAULY 2A36C 2A36C23 GL AIRCRAFT FUEL SY CONTAMINATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) AIRCRAFT FUEL SYSTEM CONTAMINATED WITH ETHYLENE DIAMINE (EDA). 1 L 7 1 3O 3 O 3A15 3E1 5 C P880 2000081000013 20000810 00013 GL 2000 8 10 AU000290 1 20000215 G 2800 FUEL TANK NAMER T6 AT6D 6400416 GL PWA R1340 R1340AN1 52016 NE HAMSTD 12D 12D40 NE AIRCRAFT FUEL SY CONTAMINATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) AIRCRAFT FUEL SYSTEM CONTAMINATED WITH ETHYLENE DIAMINE (EDA). 1 L 7 1 3R 3 R A2575 5E2 5 C P257 2000081000014 20000810 00014 SO 2000 8 10 AU000291 1 20000301 G 2800 FUEL TANK PIPER PA28 PA28235 7102810 SO LYC O540 O540B4B5 41532 EA MCAULY 1A200 1A200FA GL AIRCRAFT FUEL SY CONTAMINATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) AIRCRAFT FUEL SYSTEM CONTAMINATED WITH ETHYLENE DIAMINE (EDA). 1 L 7 1 3O 3 O 2A13 E295 5 N P874 2000081000015 20000810 00015 GL 2000 8 10 AU000293 1 20000203 G 2800 FUEL TANK DHAV DHC1 DCH1CHIPMUNK 2801704 GL AIRCRAFT FUEL SY CONTAMINATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) AIRCRAFT FUEL SYSTEM CONTAMINATED WITH ETHYLENE DIAMINE (EDA). 1 L 7 1 3O EXPA1L71 2000081000016 20000810 00016 CE 2000 8 10 AU000294 1 20000126 G 2800 FUEL TANK CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA SNSNCH 72C 72CK EA AIRCRAFT FUEL SY CONTAMINATED W K NONE O OTHER IN INSP/MAINT 1 AU S L1522915 K6883 (AUS) AIRCRAFT FUEL SYSTEM CONTAMINATED WITH ETHYLENE DIAMINE (EDA). 1 H 7 1 3O 3 O NT 3A19 E223 5 N P9045 2000071200174 20000712 00174 CE 2000 7 12 AU000295 1 20000204 G 2810 FUEL TANK CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA MCAULY 1C160 1C160DTM GL FUEL SYSYTEM CONTAMINATED W K NONE O OTHER IN INSP/MAINT 1 AU S L821276T Q6004 (AUS) AIRCRAFT FUEL SYSTEM CONTAMINATED WITH ETHYLENE DIAMINE (EDA). 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2000081000017 20000810 00017 GL 2000 8 10 AU000296 1 20000203 G 2800 FUEL TANK NAMER T6 SNJ4 6400414 GL PWA R1340 R1340AN1 52016 NE HAMSTD 12D 12D40 NE AIRCRAFT FUEL SY CONTAMINATED W K NONE O OTHER IN INSP/MAINT 1 AU S 15558 80827 (AUS) AIRCRAFT FUEL SYSTEM CONTAMINATED WITH ETHYLENE DIAMINE (EDA). 1 L 7 1 3R 3 R A2575 5E2 5 C P257 2000070300763 20000703 00763 CE 2000 7 3 AU000297 1 20000201 G 2800 FUEL TANK CESSNA 210 210L 2073448 CE CONT O520 IO520L 17032 SO MCAULY 3A32C D3A32C88 GL FUEL SYSTEM CONTAMINATED W K NONE O OTHER IN INSP/MAINT 1 AU S 577217 739868 (AUS) AIRCRAFT FUEL SYSTEM CONTAMINATED WITH ETHYLENE DIAMINE (EDA). 1 H 7 1 3O 3 O 3A21 E5CE 5 C P21EA 2000070300764 20000703 00764 CE 2000 7 3 AU000298 1 20000127 G 2800 FUEL TANK CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA SNSNCH 72C 72CK EA AIRCRAFT FUEL SY CONTAMINATED W K NONE O OTHER IN INSP/MAINT 1 AU S L1543715 K5410 (AUS) AIRCRAFT FUEL SYSTEM CONTAMINATED WITH ETHYLENE DIAMINE (EDA) 1 H 7 1 3O 3 O NT 3A19 E223 5 N P9045 2000071100289 20000711 00289 WP 2000 7 11 AU000299 1 20000209 G 2800 FUEL TANK NANCNG CJ6A CJ6A 056183N WP AIRCRAFT FUEL SY CONTAMINATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) AIRCRAFT FUEL SYSTEM CONTAMINATED WITH ETHYLENE DIAMINE (EDA). 1 L 7 1 3R RT EXPA1L71 2000070300765 20000703 00765 SO 2000 7 3 AU000300 1 20000412 G 3230 451359 BUNGEE CYLINDER PIPER PA30 PA30 7103002 SO LYC O320 IO320B1A 41508 EA HARTZL HCE2Y HCE2YL2 GL LANDING GEAR RET FAULTY W K NONE O J OTHER WARNING INDICATION NR NOT REPORTED 1 AU S (AUS) LANDING GEAR BUNGEE FAULTY. 1 L 7 2 3O 3 O A1EA 1E12 5 C P9EA 2000070300766 20000703 00766 CE 2000 7 3 AU000301 1 20000304 G 5312 DOUBLER CESSNA 441 441 2076020 CE HARTZL HCB3T HCB3TN5 GL FWD PRESS BULKHE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FORWARD PRESSURE BULKHEAD DOUBLER CRACKED. SEALANT DETERIORATED. 1 L 7 2 3T RT A28CE 6 C P15EA 2000081000018 20000810 00018 EA 2000 8 10 AU000305 1 20000215 G 2720 C6CFM12106 PEDAL DHAV DHC6 DHC6100 EA PWA PT6 PT6A20 52043 EA HARTZL HCB3T HCB3TN3 GL RUDDER CONTROL S BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RIGHT RUDDER PEDAL BRAKE CONTROL OPERATING LEVER FAILED. PEDAL WAS FOUND TO BE A PRE-MOD TYPE. 1 H 7 2 3T 3 T A9EA E4EA 6 C P15EA 2000081000019 20000810 00019 SO 2000 8 10 AU000308 1 20000313 G 5320 STRUCTURE EMB 110 EMB110P1 3260122 SO PWA PT6 PT6A34 52043 EA HARTZL HCB3T HCB3TN3 GL FUSELAGE MISREPAIRED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) STRUCTURE AT THE BASE OF THE COPILOT''S CONTROL COLUMN CUT AND GROUND AWAY IN THE AREA OF THE ELEVATOR PUSH-PULL R OD ATTACHMENT. UNAPPROVED MODIFICATION. . 1 L 7 2 4T 4 T A21SO E4EA 6 C P15EA 2000071200194 20000712 00194 SO 2000 7 12 AU000312 1 20000313 G 2710 CONTROL CABLE EMB 110 EMB110P1 3260122 SO PWA PT6 PT6A34 52043 EA HARTZL HCB3T HCB3TN3 GL AILERON CONTROL WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RIGHT WING FORWARD INBOARD AILERON CABLE AND LEFT WING AFT INBOARD AILERON CABLE SEVERELY ERODED IN THE AREA WHERE THEY EXIT THE FUSELAGE. 1 L 7 2 4T 4 T A21SO E4EA 6 C P15EA 2000081000020 20000810 00020 SO 2000 8 10 AU000313 1 20000313 G 5742 FITTING EMB 110 EMB110P1 3260122 SO PWA PT6 PT6A34 52043 EA HARTZL HCB3T HCB3TN3 GL WING, NAC/PYLON CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LEFT INBOARD NACELLE TO FORWARD SPAR ATTACHMENT CASTING UPPER LUG CORRODED IN THE AREA AROUND HI-LOC FASTENER. 1 L 7 2 4T 4 T A21SO E4EA 6 C P15EA 2000081000021 20000810 00021 SO 2000 8 10 AU000314 1 20000313 G 5552 1103216321 FITTING EMB 110 EMB110P1 3260122 SO PWA PT6 PT6A34 52043 EA HARTZL HCB3T HCB3TN3 GL ELEVATOR/TAB ATT WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ELEVATOR TRIM FITTING AND HINGE HAD EXCESSIVE PLAY. FURTHER INVESTIGATION FOUND THE TRIM FITTING CRACKED. 1 L 7 2 4T 4 T A21SO E4EA 6 C P15EA 2000081000022 20000810 00022 SO 2000 8 10 AU000315 1 20000313 G 5347 SEAT TRACK EMB 110 EMB110P1 3260122 SO PWA PT6 PT6A34 52043 EA HARTZL HCB3T HCB3TN3 GL SEAT/CARGO ATTAC CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ALL CABIN SEAT TRACKS SEVERELY CORRODED. 1 L 7 2 4T 4 T A21SO E4EA 6 C P15EA 2001011105985 20010111 05985 SO 2001 1 11 AU000316 1 20000313 G 2520 SEAT EMB 110 EMB110P1 3260122 SO PWA PT6 PT6A34 52043 EA HARTZL HCB3T HCB3TN3 GL CABIN CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) CABIN SEAT LEGS DEFORMED AND CRACKED IN THE AREA OF ATTACHMENT TO THE MAIN SEAT TUBE. 1 L 7 2 4T 4 T A21SO E4EA 6 C P15EA 2001011105986 20010111 05986 SO 2001 1 11 AU000317 1 20000313 G 2730 CONTROL CABLE EMB 110 EMB110P1 3260122 SO PWA PT6 PT6A34 52043 EA HARTZL HCB3T HCB3TN3 GL ELEVATOR CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) AFT ELEVATOR CABLES (4 OFF) AND AFT RUDDER CABLES CORRODED IN THE AREA LOCATED BETWEEN FRAME 19 AND FRAME 21. 1 L 7 2 4T 4 T A21SO E4EA 6 C P15EA 2001011105987 20010111 05987 SO 2001 1 11 AU000318 1 20000413 G 5554 4A3440 HINGE EMB 110 EMB110P1 3260122 SO PWA PT6 PT6A34 52043 EA HARTZL HCB3T HCB3TN3 GL RUDDER CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) CENTER RUDDER HINGE BRACKET CORRODED BEYOND REPAIR. 1 L 7 2 4T 4 T A21SO E4EA 6 C P15EA 2001011105988 20010111 05988 SO 2001 1 11 AU000319 1 20000413 G 5552 HINGE EMB 110 EMB110P1 3260122 SO PWA PT6 PT6A34 52043 EA HARTZL HCB3T HCB3TN3 GL ELEVATOR CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RIGHT ELEVATOR CENTER HINGE CORRODED. 1 L 7 2 4T 4 T A21SO E4EA 6 C P15EA 2001011105989 20010111 05989 SO 2001 1 11 AU000320 1 20000313 G 2730 4A321402 BELLCRANK 4A322402 EMB 110 EMB110P1 3260122 SO PWA PT6 PT6A34 52043 EA HARTZL HCB3T HCB3TN3 GL ELEVATOR CONTROL CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LEFT AND RIGHT ELEVATOR BELLCRANKS PN 4A-3224-02 (LT) AND PN 4A-3214-02 (RT) AND BELLCRANK STOPS PN 110-3010-26 AN D PN 110-3010-27 CORRODED. 1 L 7 2 4T 4 T A21SO E4EA 6 C P15EA 2001011105990 20010111 05990 SO 2001 1 11 AU000321 1 20000313 G 5744 JRA7502 HINGE EMB 110 EMB110P1 3260122 SO PWA PT6 PT6A34 52043 EA HARTZL HCB3T HCB3TN3 GL CONTROL SURFACE CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT AILERON INBOARD HINGE CORRODED. 1 L 7 2 4T 4 T A21SO E4EA 6 C P15EA 2001011105991 20010111 05991 GL 2001 1 11 AU000322 1 20000117 G 2720 MOUNT PAC CT4 CT4A 05623UC GL CONT O360 IO360HB 17025 SO HARTZL HCC2Y BHCC2YF1 GL RUDDER CRACKED W O OTHER O OTHER LD LANDING 1 AU S (AUS) LEFT PILOT SIDE BRAKE CALIPER MOUNT CRACKED. 1 Q 7 1 3I 3 O RT A9PC E1CE 5 C P920 2001011106012 20010111 06012 GL 2001 1 11 AU000323 1 20000124 G 8010 RELAY PAC CT4 CT4A 05623UC GL CONT O360 IO360HB 17025 SO HARTZL HCC2Y BHCC2YF1 GL STARTER STUCK W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 AU S (AUS) STARTER RELAY JAMMED ON. 1 Q 7 1 3I 3 O RT A9PC E1CE 5 C P920 2000081700001 20000817 00001 CE 2000 8 17 AU000325 1 20000426 G 2821 FILTER CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA MCAULY 1C160 1C160DTM GL ACFT FUEL FILTER CONTAMINATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) AIRFRAME FUEL FILTER CONTAMINATED WITH AN UNKNOWN CLEAR GEL TYPE SUBSTANCE. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2000081700002 20000817 00002 SO 2000 8 17 AU000326 1 20000401 G 7160 8734902 RETAINER LYC PIPER PA28 PA28161 7102803 SO LYC O320 O320D3G 41508 EA SNSNCH 74D 74DM EA ENGINE AIR INTAK MISSING W K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CL CLIMB 1 AU S RL1859739A A54041 (AUS) FOAM AIR FILTER ELEMENT INGESTED INTO THE CARBURETTOR.INVESTIGATION FOUND ONLY ONE FILTER RETAINER WAS FITTED INST EAD OF TWO. FURTHER CHECKING FOUND THAT THE IPC MAY BE MISLEADING INTHE NUMBER OF RETAINERS TO BE FITTED. 1 L 7 1 3O 3 O 2A13 E274 5 N P88614 2000081700003 20000817 00003 CE 2000 8 17 AU000328 1 20000504 G 2821 5092004010 FILTER 359242307 BEECH 35 V35 1151538 CE CONT O520 IO520BA 17032 SO MCAULY 2A36C 2A36C23 GL ACFT FUEL FILTER CONTAMINATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) AIRFRAME FUEL FILTER CONTAMINATED BY AN UNKNOWN WHITE SUBSTANCE. 1 L 7 1 3O 3 O 3A15 E5CE 5 C P880 2000081700004 20000817 00004 CE 2000 8 17 AU000329 1 20000331 G 3230 S20495FG ROD END CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO MCAULY 3AF32C 3AF32C87 GL LANDING GEAR RET FAILED W K NONE O OTHER LD LANDING 1 AU S (AUS) LEFT MAIN LANDING GEAR PUSH-PULL ROD END SPLIT. 1 L 7 2 3O 3 O 3A10 E5CE 5 C P22EA 2000081700005 20000817 00005 SO 2000 8 17 AU000330 2 20000131 G 8520 643037 CRANKCASE PIPER PA34 PA34200T 7103406 SO CONT O360 TSIO360E 17025 SO MCAULY 3AF34C 3AF34C502 GL ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 1800 307706 786028L70726 (AUS) CRANKCASE CRACKED IN NUMEROUS PLACES. CRANKCASE HAD BEENPREVIOUSLY WELD REPAIRED. 1 L 7 2 3O 3 O A7SO E9CE 5 C P22EA 2000062800221 20000628 00221 WP 2000 6 28 AU000331 1 20000412 G 6210 269D21100513M BLADE HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL MAIN ROTOR BLADE CRACKED W K NONE F FLT CONT AFFECTED CR CRUISE 1 AU S (AUS) MAIN ROTOR BLADE CRACKED. BUSHING LOOSE. 1 G 7 1 3U 3 U H3WE E4CE 2000081700006 20000817 00006 SO 2000 8 17 AU000334 2 20000427 G 8540 537721 BEARING CESSNA 421 421C 2076016 CE CONT O520 GTSIO520L 17032 SO MCAULY 3FF32 3FF32C501 GL ENGINE DISINTEGRATED W K NONE E VIBRATION/BUFFET TX TAXI/GRND HDL 1 AU S 870 604802 (AUS) STARTER ADAPTER FRONT SUPPORT BEARING DISINTEGRATED. METAL CONTAMINATION OF ENGINE OIL SYSTEM. 1 L 7 2 3O 3 O A7CE E7CE 5 C P45GL 2000062800222 20000628 00222 CE 2000 6 28 AU000335 1 20000408 G 3243 8000016 SEAL CESSNA 50440004 CESSNA 421 421C 2076016 CE CONT O520 GTSIO520L 17032 SO MCAULY 3FF32 3FF32C501 GL MASTER CYL/BRAKE WORN W K NONE O OTHER TX TAXI/GRND HDL 1 AU S (AUS) BRAKE MASTER CYLINDER LOC O SEAL'' FAILED. 1 L 7 2 3O 3 O A7CE E7CE 5 C P45GL 2000081800007 20000818 00007 SO 2000 8 18 AU000340 1 20000420 G 5711 20207T902 SPAR AYRES AYRES S2 S2RG10 SO GARRTT TPE331 TPE33110 01514 WP MCAULY 4HFR34 4HFR34C653 NE WING SPAR STRUCT CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S RE201 P37100C 4HFR34C653G (AUS) RIGHT LOWER SPAR CAP CRACKED. FOUND DURING EDDY CURRENT INSPECTION IAW AD/ACSNOW/24 (1). DEFECT CONFIRMED BY MPI . 1 L 7 1 3T 4 T NC A4SW E4WE 6 C 3PNE 2000081700007 20000817 00007 SO 2000 8 17 AU000341 1 20000505 G 2823 492239 SELECTOR VALVE PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL FUEL SELECTOR/SH CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUEL SELECTOR VALVE SEVERELY CORRODED (RUSTED) INTERNALLY. FOUND APPROXIMATELY 25 HOURS AFTER COMPLIANCE WITH AD/ GEN/81. A SECOND SELECTOR VALVE WAS ALSO FOUND IN THE SAME CONDITION. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2000081700008 20000817 00008 SO 2000 8 17 AU000342 1 20000407 G 2810 FUEL TANK PIPER PA28 PA28R201T 7102813 SO CONT O360 TSIO360F 17025 SO HARTZL HCC2Y BHCC2YF2 GL FUEL STORAGE LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S (AUS) FUEL TANK LEAKING. INSPECTION FOUND FAULTY SEALANT. FOUND FOLLOWING COMPLIANCE WITH AD/GEN/80. 1 L 7 1 3O 3 O 2A13 E9CE 5 C P920 2000081700009 20000817 00009 NM 2000 8 17 AU000343 1 20000407 G 2810 FUEL TANK PIPER PA60 PA60600A 7106002 NM LYC O540 IO540K1J5 41532 EA FUEL STORAGE LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S (AUS) FUEL TANKS LEAKING. FOUND FOLLOWING COMPLIANCE WITH AD/GEN/81 .LEAKS WERE NOT PRESENT PRIOR TO INTRODUCTION OF W ATER OR IPA. 1 M 7 2 3O 3 O RT A17WE 1E4 2000081700010 20000817 00010 SO 2000 8 17 AU000344 1 20000217 G 2810 FUEL TANK PIPER PA28 PA28180 7102808 SO LYC O360 O360* 41514 EA FUEL STORAGE LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S (AUS) FUEL TANKS LEAKING. FOUND FOLLOWING COMPLIANCE WITH AD/GEN/80. 1 L 7 1 3O 3 O 2A13 E286 2000082200014 20000822 00014 SO 2000 8 22 AU000345 1 20000407 G 2810 FUEL TANK PIPER PA32 PA32300 7103212 SO LYC O540 IO540K1B5 41532 EA HARTZL HCC2Y HCC2YK2 GL FUEL STORAGE LEAKING W K NONE O K OTHER FLUID LOSS IN INSP/MAINT 1 AU S (AUS) FUEL TANKS LEAKING. FOUND FOLLOWING COMPLIANCE WITH AD/GEN/80. 1 L 7 1 3O 3 O A3SO 1E4 5 C P920 2000082200015 20000822 00015 WP 2000 8 22 AU000346 1 20000214 G 2800 FUEL TANK FUJI FA200 FA200180 WP LYC O360 IO360B1B 41514 EA MCAULY 2D34C 2D34C53 GL AIRCRAFT FUEL SY CONTAMINATED W K NONE O OTHER IN INSP/MAINT 1 AU S L555451A (AUS) AIRCRAFT FUEL SYSTEM CONTAMINATED WITH ETHYLENE DIAMINE (EDA) 1 L 7 1 3O 3 O A4PC 1E10 5 C P7EA 2000082200016 20000822 00016 CE 2000 8 22 AU000352 1 20000508 G 5730 SKIN CESSNA 402 402B 207590P CE CONT O520 TSIO520E 17040 SO MCAULY 3AF32C 3AF32C87 GL WING PLATES/SKIN CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LEFT WING UPPER SKIN CRACKED IN AREA OF MLG WHEELWELL CENTER RIB. AIRCRAFT HAS A FACTORY INSTALLED RIB REINFORCEM ENT FITTED AND IS ALSO OUTSIDE OF THE SERIAL NUMBER RANGE AS REFERENCED IN AD/CESSNA400/105 AND SERVICE LETTER MEB 76-2. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2000082200017 20000822 00017 SO 2000 8 22 AU000353 1 20000416 G 2800 FUEL TANK PIPER PA28 PA28180 7102808 SO LYC O360 O360A3A 41514 EA SNSNCH 76E M76EMM EA AIRCRAFT FUEL SY CONTAMINATED W K NONE O OTHER IN INSP/MAINT 1 AU S L569936 38002K (AUS) FUEL SYSTEM CONTAMINATED WITH ETHYLENE DIAMINE (EDA). FOLLOWING DECONTAMINATION WASH, WATER WOULD NOT DRAIN FROM THE TANKS. A PROBE INSERTED VIA THE WATER DRAIN PORT RESULTED IN A DIAPHRAGM BEING FELT. THE DIAPHRAGM WAS PUNCTURED T O DRAIN THE WATER. THIS WAS CARRIED OUT NUMEROUS TIMES BEFORE THE TANKS WERE FULLY DRAINED. DURING THE DRAIN A GREEN TR ANSLUCENT GEL APPEARED. A SAMPLE WAS TAKEN BUT APPAREENTLY EVAPORATED OVER A THREE DAY PERIOD. ABOUT THREE TO FOUR D AYS LATER A TREACALY BROWN SUBSTANCE WAS FOUND ON THE BOTTOM OF THE TANKS. 1 L 7 1 3O 3 O 2A13 E286 5 N P4EA4 2000082200018 20000822 00018 SO 2000 8 22 AU000354 2 20000510 G 8520 652541 NUT CONT IO520M CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO MCAULY 3AF32C 3AF32C87 GL ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 1059 560460 560460 (AUS) RIGHT ENGINE NR 6 CYLINDER HOLDDOWN NUT CRACKED. LOSS OF TENSION ON THROUGH BOLT. 1 L 7 2 3O 3 O 3A10 E5CE 5 C P22EA 2000082200019 20000822 00019 SW 2000 8 22 AU000355 1 20000504 G 5311 1044841 TUBE AIRTRC AT500 AT502B 0390307 SW PWA PT6 PT6A15AG 52043 NE HARTZL HCB3T HCB3TN3 GL FUSELAGE MAIN FR CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUSELAGE VERTICAL TUBE CRACKED AT WING ANGLE ATTACHMENT POINT. 1 L 7 1 3T 4 T NC A17SW E4EA 6 C P15EA 2000082200020 20000822 00020 CE 2000 8 22 AU000356 1 20000401 G 5312 BULKHEAD CESSNA 206 U206F 2073333 CE CONT O520 IO520F 17032 SO MCAULY 2A34C D2A34C58 GL FUSELAGE MAIN BU CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FORWARD DOORPOST BULKHEAD CRACKED IN RELIEF HOLE. CRACK LENGTH 12.7 MM (0.5 INCH). FOUND DURING INSPECTION IAW A D/C206/48. 1 H 7 1 3O 3 O A4CE E5CE 5 C P3EA 2000082100130 20000821 00130 EU 2000 8 21 AU000357 1 20000401 G 5753 LINK PARTEN P68 P68B EU LYC O360 IO360A1B6 41514 EA HARTZL HCC2Y HCC2YK2 GL TE FLAP STRUCTUR CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LEFT AND RIGHT INBOARD FLAP HANGERS CORRODED IN AREA OF BONDING WIRE ATTACHMENT. FOUND DURING INSPECTION IAW AD/P 68/40. 1 H 7 2 3O 3 O A31EU 1E10 5 C P920 2000082100131 20000821 00131 SO 2000 8 21 AU000358 1 20000428 G 5730 62061002 SKIN PIPER PA28 PA28181 7102807 SO WING PLATES/SKIN CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) WING SKIN CRACKED. 1 L 7 1 3O 2A13 2000082100132 20000821 00132 EA 2000 8 21 AU000361 2 20000501 G 7250 BEARING BEECH 200 B200C 1152924 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL TURBINE SECTION FAILED W K NONE E VIBRATION/BUFFET CR CRUISE 1 AU S PCE81516 (AUS) ENGINE POWER SECTION FAILED. SUSPECT CAUSED BY NR 3 BEARING FAILURE. 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2000082100133 20000821 00133 SO 2000 8 21 AU000364 1 20000515 G 5311 77467009 FRAME PIPER PA38 PA38112 7103812 SO LYC O235 O235L2C 41505 EA SNSNCH 74D 74DM EA FUSELAGE MAIN FR DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUSELAGE FRAME REINFORCEMENT CHANNEL DISTORTED AND CRACKED ON FLANGES. FUSELAGE FRAME DISTORTED WITH A SMALL CRAC K WHERE ARIVET HAD PULLED OUT AT THE LOWER OUTBOARD ATTACHMENT TO THEFUSELAGE SKIN. FOUND DURING INSPECTION IAW AD/PA38 /25. 1 L 7 1 3O 3 O A18SO E223 5 N P88614 2000082100134 20000821 00134 SO 2000 8 21 AU000365 1 20000505 G 2710 1430028 CONTROL CABLE PIPER PA18 PA18150 7101828 SO LYC O320 O320A2B 41508 EA SNSNCH 74DM M74DM EA AILERON CONTROL WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RIGHT AILERON CONTROL CABLES WORN BEYOND LIMITS IN THE AREA OF THE OUTER GUIDES. 1 H 7 1 3O 3 O 1A2 E274 5 N P88614 2000082100135 20000821 00135 SW 2000 8 21 AU000366 1 20000412 G 3213 ED12526 FITTING GULSTM 710015 GULSTM 500 500S 0141107 SW LYC O540 IO540E1B5 41532 EA MAIN LANDING GEA CRACKED W K NONE O OTHER LD LANDING 1 AU S 2205 (AUS) RH MAIN LANDING GEAR ACTUATOR ATTACHMENT CLEVIS FITTING CRACKED. 1 H 7 2 3O 3 O 6A1 1E4 2000062900173 20000629 00173 SW 2000 6 29 AU000375 1 20000213 G 6720 222012724103 SPACER BELL BELL 222 222U 1182140 SW LYC LTS101 LTS101750C1 41560 NE TAIL ROTOR CONTR CORRODED W K NONE O OTHER TO TAKEOFF 1 AU S (AUS) TAIL ROTOR PITCH CHANGE MECHANISM SPACER SEVERELY CORRODED. A PIECE OF THE SPACER HAD FLAKED OFF AND JAMMED THE S PLINE PLATE PN 222-012-725-001 ON THE OUTPUT SHAFT SPLINES. 1 G 7 2 3U 3 U H9SW E5NE 2000081700015 20000817 00015 GL 2000 8 17 AU000383 3 20000515 G 6111 BLADE MCAULY CESSNA 210 210L 2073448 CE CONT O520 IO520L 17032 SO MCAULY 3A32C D3A32C88 GL PROPELLER BLADE LOOSE W K NONE O OTHER IN INSP/MAINT 1 AU S 830133 (AUS) PROPELLER BLADES LOOSE ON FERRULE ASSEMBLIES. LOW TORQUE. 1 H 7 1 3O 3 O 3A21 E5CE 5 C P21EA 2000071100293 20000711 00293 SW 2000 7 11 AU000384 1 20000515 G 6220 206011147007 STRAP BELL 206011100145 BELL 206 206B3 1181506 SW ALLSN 250C 250C20B 03013 GL MAIN ROTOR HEAD DETERIORATED W K NONE O OTHER IN INSP/MAINT 1 AU S AAB51059 CAE832194 (AUS) TENSION-TORSION (TT) STRAPS DETERIORATED. THE STRAPS WERE DISTORTED AND THE URETHANE COATING ADJACENT TO THE LATC H BOLT BUSHINGS WAS SPLIT REVEALING THE INTERNAL WINDINGS. (X) 1 G 7 1 3U 3 U H2SW E4CE 2000081700016 20000817 00016 GL 2000 8 17 AU000385 3 20000515 G 6114 D32513R HUB HARTZL CESSNA 207 207 2073602 CE CONT O520 IO520F 17032 SO HARTZL HCC3Y HCC3YF1 GL PROPELLER HUB SE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S EC1567A (AUS) PROPELLER HUB CRACKED IN TWO PLACES FROM CRANKSHAFT BORE RADIALLY TO TWO STUD HOLES. 1 H 7 1 3O 3 O A16CE E5CE 5 C P25EA 2000081700023 20000817 00023 GL 2000 8 17 AU000390 3 20000419 G 6112 4E13113 BRUSH BLOCK CESSNA 441 441 2076020 CE HARTZL HCB3T HCB3TN5 GL PROPELLER DE-ICE MISINSTALLED W K NONE O B OTHER SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 AU S (AUS) RIGHT ENGINE DE-ICE SYSTEM CENTER BRUSH BLOCK TERMINAL INCORRECTLY INSTALLED. PROPELLER AMMETER IN LINE TERMINALS MELTED. 1 L 7 2 3T RT A28CE 6 C P15EA 2000070600231 20000706 00231 NM 2000 7 6 AU000391 1 20000224 G 5511 A0441 SPAR ROBSIN ROBSIN R22 R22BETA NM LYC O320 O320B2C 41508 EA HORIZ STABILIZER CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 2072 (AUS) HORIZONTAL STABILIZER SPAR CRACKED THROUGH ATTACHMENT BOLT HOLES (4 OFF). FOUND FOLLOWING TAIL ROTOR STRIKE INSPE CTION ALTHOUGH IT IS SUSPECTED THAT THE CRACKS WERE ALREADY PRESENT. 1 G 7 1 3O 3 O H10WE E274 2000070600232 20000706 00232 EU 2000 7 6 AU000392 1 20000512 G 6210 1178016602 BRACKET 11780166 BOLKMS 117 BK117B1 5626012 EU LYC LTS101 LTS101750B1 41560 NE MAIN ROTOR BLADE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MAIN ROTOR BLADE VIBRATION ABSORBER LOWER BRACKET CRACKED. 1 G 7 2 3U 3 U H13EU E5NE10 2000070600233 20000706 00233 GL 2000 7 6 AU000393 2 20000420 G 7250 23062750 HEAT SHIELD BELL 206 206B3 1181506 SW ALLSN 250C 250C20B 03013 GL TURBINE SECTION CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S CAT36613 CAE832257 (AUS) FIRST STAGE TURBINE NOZZLE HEAT SHIELD CRACKED. FOUND DURING INSPECTION IAW ROLLS ROYCE CEBA-1370. 1 G 7 1 3U 3 U H2SW E4CE 2000081700024 20000817 00024 CE 2000 8 17 AU000394 1 20000519 G 5753 3516505084 RIB BEECH 58 58 1152740 CE MCAULY 3AF32C 3AF32C512 GL TE FLAP CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LEFT FLAP RIB LOCATED BENEATH FLAP ACTUATING BRACKET CRACKED. 1 L 7 2 3O 3A16 5 C P22EA 2000062900174 20000629 00174 EU 2000 6 29 AU000397 1 20000427 G 6510 593404 BEARING AEROSP 350A34011004 AEROSP AS355 AS355F 8680806 EU ALLSN 250C 250C20F 03013 GL TAIL ROTOR DRIVE FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) TAIL ROTOR DRIVESHAFT BEARING SPINNING ON THE DRIVESHAFT WEARING A GROOVE INTO THE SHAFT. 1 G 7 2 3U 3 U H11EU E4CE 2000081700027 20000817 00027 SO 2000 8 17 AU000401 2 20000523 G 7414 10349276TCM CAPACITOR CESSNA 185 A185F 2072821 CE CONT O520 IO520D 17032 SO MCAULY 2A34C D2A34C98 GL MAGNETO/DISTRIBU FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RIGHT MAGNETO CAPACITOR FAULTY. CAPACITOR WAS A NEWLY FITTED ITEM. 1 H 7 1 3O 3 O 3A24 E5CE 5 C P3EA 2000081700029 20000817 00029 CE 2000 8 17 AU000403 1 20000525 G 2497 WIRE CESSNA 206 U206F 2073333 CE MCAULY D3A34 D3A34C404 GL COLLECTOR TANK SHORTED W K NONE O OTHER IN INSP/MAINT 1 AU S 564231 (AUS) FIRE UNDER FUSELAGE FLOOR IN RT FUEL COLLECTOR TANK COMPARTMENT. EXTENSIVE DAMAGE CAUSED TO WIRING LOOM LOCATED B ETWEEN THE COLLECTOR TANK AND THE FLOOR PANEL. SUSPECT CAUSED BY SPARKS FROM THE RIGHT EXHAUST TAILPIPE IGNITING LEAKIN G BOOST PUMP FUEL AND LEAKING ENGINE OIL. 1 H 7 1 3O A4CE 5 C P47GL 2000081700030 20000817 00030 SO 2000 8 17 AU000404 1 20000517 G 3234 LEVER PIPER PA30 PA30 7103002 SO LYC O320 IO320B1A 41508 EA HARTZL HCE2Y HCE2YL2 GL LANDING GEAR SEL FOULED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LANDING GEAR MANUAL EXTENSION SYSTEM LEVER OBSTRUCTED BY THE SEAT MOUNTED PORTABLE FIRE EXTINGUISHER IN SOME SEAT POSITIONS. 1 L 7 2 3O 3 O A1EA 1E12 5 C P9EA 2000081700031 20000817 00031 SO 2000 8 17 AU000408 1 20000510 G 2434 ALH212851 ROTOR ALX842ILS PIPER PA30 PA30 7103002 SO LYC O320 IO320B1A 41508 EA HARTZL HCE2Y HCE2YL2 GL DC GENERATOR-ALT SHORTED W K NONE H ELECT. POWER LOSS-50 PC CR CRUISE 1 AU S 406116 L97455AL8085 BG45824634 (AUS) LEFT ALTERNATOR SHORT CIRCUITED. COMPLETE ELECTRICAL FAILURE. A PROBLEM LOWERING THE LANDING GEAR RESULTED IN A GEAR UP LANDING CAUSING DAMAGE TO THE AIRCRAFT. SEE SDR AU000404 FOR ADDITIONAL INFORMATION. 1 L 7 2 3O 3 O A1EA 1E12 5 C P9EA 2000082100029 20000821 00029 CE 2000 8 21 AU000410 1 20000306 G 2822 PUMP CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO FUEL BOOST PUMP FAULTY W O OTHER O OTHER CR CRUISE 1 AU S 277602R (AUS) LEFT FUEL TRANSFER PUMP FAILED. INVESTIGATION FOUND THAT THE PUMP POSITIVE WIRE HAD BURNED OFF AT THE HOUSING. L EFT LANDING LIGHT CIRCUIT BREAKER TRIPPED. (X) 1 L 7 2 3O 3 O 3A10 E5CE 2000082100030 20000821 00030 CE 2000 8 21 AU000411 1 20000427 G 2822 PUMP CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO FUEL BOOST PUMP FAULTY W K NONE O OTHER CR CRUISE 1 AU S 277564R (AUS) LEFT FUEL TRANSFER PUMP FAILED. INVESTIGATION FOUND THAT THE PUMP POSITIVE WIRE HAD BURNED OFF AT THE HOUSING. L EFT LANDING LIGHT CIRCUIT BREAKER TRIPPED. 1 L 7 2 3O 3 O 3A10 E5CE 2000082100056 20000821 00056 CE 2000 8 21 AU000412 1 20000419 G 2822 PUMP CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO FUEL BOOST PUMP FAULTY W O OTHER O OTHER CR CRUISE 1 AU S 277331R (AUS) RIGHT FUEL TRANSFER PUMP FAILED. INVESTIGATION FOUND THAT THE PUMP POSITIVE WIRE HAD BURNED OFF AT THE HOUSING. RIGHT LANDING LIGHT CIRCUIT BREAKER TRIPPED. 1 L 7 2 3O 3 O 3A10 E5CE 2000082100031 20000821 00031 CE 2000 8 21 AU000414 1 20000525 G 3230 50452134 ROD END 504501025 CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO MCAULY 3AF32C 3AF32C87 GL LANDING GEAR RET FAILED W K NONE O N OTHER FALSE WARNING LD LANDING 1 AU S (AUS) LEFT MAIN LANDING GEAR TORQUE TUBE ROD END FAILED. 1 L 7 2 3O 3 O 3A10 E5CE 5 C P22EA 2001011100337 20010111 00337 NM 2001 1 11 AU000415 1 20000516 G 2750 7455 WIRE ROPE DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE TE FLAP CONTROL WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FLAP SECONDARY DRIVE OUTER CABLE SWAGED COUPLING FLANGE WORNEXCESSIVELY. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2000071800016 20000718 00016 NM 2000 7 18 AU000416 1 20000521 G 6310 A1681 RETAINER ROBSIN ROBSIN R22 R22BETA NM LYC O320 O320B2C 41508 EA ENGINE/TRANSMISS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 409 4430 (AUS) CLUTCH SEAL PLATE CRACKED. 1 G 7 1 3O 3 O H10WE E274 2000071800017 20000718 00017 NM 2000 7 18 AU000417 1 20000510 G 7820 A1696 MUFFLER LYC ROBSIN R22 R22BETA NM LYC O320 O320B2C 41508 EA ENGINE NOISE SUP FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) EXHAUST MUFFLER SPLIT. MUFFLER WAS A NEW ITEM. 1 G 7 1 3O 3 O H10WE E274 2000082100032 20000821 00032 EA 2000 8 21 AU000419 2 20000529 G 8550 LW13388 SEAL LYC PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA HARTZL HCE3Y HCE3YR2 GL ENGINE FAILED W K NONE E K VIBRATION/BUFFET FLUID LOSS LD LANDING 1 AU S L142368A L142368A (AUS) LEFT ENGINE OIL FILTER ADAPTER PLATE SEAL PROTRUDING FROM PLATE. SEAL APPEARED TO BE SEVERED. ENGINE NEEDED 9 LI TRES OF OIL. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2000082100057 20000821 00057 SO 2000 8 21 AU000420 2 20000529 G 8520 652541 NUT CONT CESSNA 182 182P 2075816 CE CONT O470 O470S 17026 SO MCAULY 2A34C 2A34C203 GL ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NR 5 CYLINDER THROUGH BOLT NUT SPLIT. 1 H 7 1 3O 3 O NT TA13 E273 5 C P3EA 2000082100033 20000821 00033 EA 2000 8 21 AU000421 2 20000524 G 8530 CYLINDER LYC GULSTM 500 500S 0141107 SW LYC O540 IO540E1B5 41532 EA HARTZL HCA3V HCA3VK2 GL ENGINE FAILED W O OTHER E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CR CRUISE 1 AU S L1528448 (AUS) LEFT ENGINE NR 6 CYLINDER FAILED AND SEPARATED. CRANKCASE HOLED IN AREA OF NR 6 CYLINDER. 1 H 7 2 3O 3 O 6A1 1E4 5 C P6EA 2000071900172 20000719 00172 EU 2000 7 19 AU000422 1 20000526 G 6230 704A3364021 BUSHING AEROSP SCISSORLINK SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1B 6OO30 NE MAIN ROTOR MAST BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MAIN ROTOR SWASHPLATE TOP SCISSOR LINK BUSHING BROKEN. THE BROKEN BUSHING WORE INTO THE SCISSOR LINK. 1 G 7 1 3U 3 U H9EU E19EU 2000082100038 20000821 00038 CE 2000 8 21 AU000423 1 20000531 G 5523 12346281 TRIM TAB CESSNA 206 U206F 2073333 CE CONT O520 IO520F 17032 SO MCAULY D3A34 D3A34C404 GL ELEVATOR TAB STR DISTORTED W K NONE E F VIBRATION/BUFFET FLT CONT AFFECTED IN INSP/MAINT 1 AU S (AUS) RIGHT ELEVATOR TRIM TAB DISTORTED, SPLIT AND BULGED. INVESTIGATION FOUND THAT THE CORE HAD BEEN FILLED WITH EXPA NDABLE FOAM WHICH HAD CONTINUED TO EXPAND AFTER FILLING THE AVAILABLE SPACE. UNAPPROVED PART. 1 H 7 1 3O 3 O A4CE E5CE 5 C P47GL 2000082100039 20000821 00039 SW 2000 8 21 AU000424 1 20000530 G 7921 8526250 COOLER LYC GULSTM 680 680FL 0141608 SW LYC O720 IO720B1B 41546 EA HARTZL HCB3Z HCB3Z302 GL ENG OIL COOLER CRACKED W K NONE E K VIBRATION/BUFFET FLUID LOSS CR CRUISE 1 AU S L92454A (AUS) RIGHT ENGINE OIL COOLER LEAKING FROM PREVIOUS WELD REPAIR. 1 H 7 2 3O 3 O 2A4 1E15 5 C P907 2000072000016 20000720 00016 SW 2000 7 20 AU000425 1 20000601 G 6220 MAIN ROTOR BELL TRUNNION BELL 206 206B3 1181506 SW ALLSN 250C 250C20B 03013 GL SPLIT CONE HALF DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S 304 (AUS) MAIN ROTOR SPLIT CONE HALF INSTALLED UPSIDE DOWN. MAIN ROTOR TRUNNION CHAMFER DAMAGED BY SHARP EDGE OF CONE. MAS T SPLIT CONE SEAT FRETTING. 1 G 7 1 3U 3 U H2SW E4CE 2000082100040 20000821 00040 CE 2000 8 21 AU000426 1 20000523 G 2810 FUEL TANK CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO MCAULY 3AF32C 3AF32C505 GL FUEL STORAGE FOD W K NONE O K OTHER FLUID LOSS IN INSP/MAINT 1 AU S (AUS) RIGHT WING FUEL TANK FOD. ON REMOVAL OF THE RIGHT WING FUEL TANK ACCESS PANEL, A PIECE OF RAG MEASURING APPROXIMA TELY 300 MM BY 300 MM (11.8 INCHES BY 11.8 INCHES) WAS FOUND IN THE BOTTOM OF THE TANK COVERING ONE FUEL TANK FLOW VALVE AND THE MAIN FUEL SUCTION PORT. THE PANEL WAS REMOVED DUE TO A LARGE FUEL STAIN ON THE TOP SURFACE OF THE WING. IT W AS NOTED THAT THE PANEL HAD BEEN INCORRECTLY INSTALLED AND NO SEALANT HAD BEEN USED. FOD. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2000082400006 20000824 00006 SO 2000 8 24 AU000427 1 20000524 G 2910 9515348 PIPE PIPER PA34 PA34200 7103405 SO LYC O360 IO360C1E6 41514 EA HARTZL HCC2Y HCC2YK2 GL HYDRAULIC, MAIN CORRODED W K NONE O J OTHER WARNING INDICATION LD LANDING 1 AU S (AUS) LANDING GEAR ''UP'' PIPE CORRODED AND LEAKING. LOSS OF HYDRAULIC FLUID. LEFT MLG DOWNLOCK STIFF TO OPERATE. AI RCRAFT OPERATES IN A SALT LADEN ENVIRONMENT. 1 L 7 2 3O 3 O A7SO 1E10 5 C P920 2000082400007 20000824 00007 EA 2000 8 24 AU000428 2 20000214 G 8550 LW13388 SEAL LYC PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA HARTZL HCE3Y HCE3YR2 GL ENGINE FAILED W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S RL11668A (AUS) OIL FILTER BASE PLATE GASKET LEAKING AND PROTRUDING PAST THE PLATE. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2000071900173 20000719 00173 WP 2000 7 19 AU000429 1 20000508 G 6420 B1151 BEARING ROBSIN R22 R22ALPHA 7640104 WP LYC O320 O320B2C 41508 EA TAIL ROTOR HEAD WORN W K NONE O OTHER IN INSP/MAINT 1 AU S DN (AUS) TAIL ROTOR TEETER BEARINGS WEARING PREMATURELY. 1 G 7 1 3O 3 O H10WE E274 2000082400008 20000824 00008 2000 8 24 AU000430 4 20000322 G 2211 BZX5111 DIODE CENTURY IC151 PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL AUTOPILOT COMPUT INCORRECT W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S S205B (AUS) ROLL AMPLIFIER POWER SUPPLY ZENER DIODE INCORRECT PART. DIODE CAUSED DRIVER TRANSISTOR TO FAIL. UNAPPROVED PART. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001011106062 20010111 06062 NM 2001 1 11 AU000431 1 20000414 G 7120 MOUNT DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE ENGINE MISINSTALLED W K NONE O OTHER IN INSP/MAINT 1 AU S 120153 (AUS) NR 2 ENGINE INBOARD AND OUTBOARD FORWARD MOUNTS INCORRECTLY INSTALLED (BACK TO FRONT). FURTHER INVESTIGATION FOUND THE TOP FORWARD MOUNT TO BE UNUSUALLY COMPRESSED AND THE RIVETS IN THE TOP SKIN OF THE HORSE COLLAR IN THE AREA OF THE TOP FORWARD MOUNT TO BE PULLING IN A FORWARD DIRECTION. THE ENGINE CONTROL QUADRANT SPRING STRUT FORK END APPEARS BENT A ND THE AFT TOP ENGINE MOUNT STRUTS ARE ANGLED SLIGHTLY FORWARD. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001011106063 20010111 06063 SW 2001 1 11 AU000432 1 20000530 G 5210 2724127077 LOCK FRCHLD SA227 SA227DC 3377521 SW MCAULY 4HFR34 4HFR34C652 NE PAX DOOR JAMMED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) PASSENGER DOOR HANDLE SAFETY LOCK FAULTY. INVESTIGATION FOUND THE PIVOT BOLT BETWEEN THE ACTUATING ARM AND THE PLU NGER WAS TOOTIGHT CAUSING THE MECHANISM TO JAM. 2 L 7 2 4T RT A18SW 6 C 3PNE 2001011106064 20010111 06064 2001 1 11 AU000433 4 20000528 G 3414 640608901 INDICATOR SAAB SF340 340B 7860101 EU GE CT7TP CT79B 30030 NE ROTOL R375 R3754123F21 NE AIRSPEED FAULTY W O OTHER O OTHER DE DESCENT 1 AU S 10109 (AUS) RT AIRSPEED INDICATOR AND STANDBY AIRSPEED INDICATORS LOSTINDICATION. SUSPECT CAUSED BY ICING. 2 L 7 2 4T 4 T RT A52EU E8NE 6 C P17NE 2001011106065 20010111 06065 WP 2001 1 11 AU000434 2 20000527 G 7313 31032359 NOZZLE SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE33111U 01514 WP FUEL INJECTOR FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S 74 31032359 (AUS) FUEL INJECTOR NOZZLE INLET SHEARED IN THREADED AREA. 2 L 7 2 4T 4 T RT A8SW E4WE 2001011106066 20010111 06066 EU 2001 1 11 AU000435 1 20000528 G 3251 104273007 VALVE ROTOL 200876004 BAG BAE146 BAE146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE STEERING UNIT LEAKING W O OTHER J WARNING INDICATION LD LANDING 1 AU S (AUS) NOSE LANDING GEAR STEERING VALVE INTERNAL LEAK. 2 H 7 4 4F 4 F RT A49EU E6NE 2000082400009 20000824 00009 CE 2000 8 24 AU000436 1 20000605 G 2752 261114467 BRACKET CESSNA 208B CESSNA 208 208B 2073701 CE FUSELAGE MISC FAILED W O OTHER O OTHER DE DESCENT 1 AU S B0428 (AUS) STANDBY FLAP MOTOR SUPPORT BRACKETS PN 2611144-6 AND PN 2611144-7 FAILED. 1 H 7 1 3T A37CE 2000082400010 20000824 00010 NE 2000 8 24 AU000437 2 20000527 G 7532 310334701 BLEED VALVE PWA CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE COMPRESSOR BLEED FAULTY W K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS TO TAKEOFF 1 AU S 390 19308 (AUS) ENGINE BLEED VALVE DIAPHRAGM HOLED AND SEAT BADLY WORN DUE TO CHATTERING. 1 H 7 1 3T 3 T A37CE E4EA 2001011106067 20010111 06067 NM 2001 1 11 AU000438 1 20000603 G 5542 85540012101 SKIN DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE RUDDER CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FORE RUDDER SKIN CRACKED IN TOP LH CORNER. INSPECTION FOUND THAT THE LAST (REARMOST) RIVET ON THE STIFFENER PNO 85 540025-101 WAS INCORRECTLY FITTED. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001011106068 20010111 06068 EU 2001 1 11 AU000439 1 20000528 G 3234 HTE96811 SELECTOR VALVE BAG BAE146 BAE146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE MLG LEAKING W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 AU S (AUS) LANDING GEAR SELECTOR VALVE INTERNAL LEAK. 2 H 7 4 4F 4 F RT A49EU E6NE 2001011106069 20010111 06069 EU 2001 1 11 AU000440 1 20000531 G 2750 CONTROLLER BAC 146 146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE TE FLAP FAULTY W A UNSCHED LANDING F J FLT CONT AFFECTED WARNING INDICATION CL CLIMB 1 AU S (AUS) FLAPS FAULTY. FLAPS CHECKED ON GROUND AND OPERATED WITHOUT FAULT. 2 H 7 4 4F 4 F A49EU E6NE 2001011106070 20010111 06070 EU 2001 1 11 AU000441 1 20000206 G 3230 HTE2501 MOTOR BAG BAE146 BAE146300A 1500267 EU LYC ALF502 ALF502R5 41580 NE CONTROL VALVE FAULTY W O OTHER O OTHER NR NOT REPORTED 1 AU S (AUS) LANDING GEAR CONTROL VALVE ACTUATOR MOTOR FAULTY. 2 H 7 4 4F 4 F RT A49EU E6NE 2001011106071 20010111 06071 NM 2001 1 11 AU000442 1 20000519 G 5310 STRUCTURE BOEING 767 767204 NM GE CF6 CF680A 30025 NE FUSELAGE DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NOSE LANDING GEAR INADVERTANTLY RETRACTED DURING OVERNIGHT MAINTENANCE. EXTENSIVE DAMAGE WAS CAUSED TO THE FUSELAG ESTRUCTURE IN THE NOSE 2 L 7 2 4F 4 F RT A1NM E13NE 2000082400011 20000824 00011 CE 2000 8 24 AU000443 1 20000605 G 2910 520010785 PIPE CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO MCAULY 3AF32C 3AF32C93 GL HYDRAULIC, MAIN CRACKED W K NONE K FLUID LOSS NR NOT REPORTED 1 AU S (AUS) LEFT HYDRAULIC FILTER HOUSING PRESSURE PIPE SPLIT AT OUTBOARD RADIUS OF BEND. LOSS OF HYDRAULIC FLUID. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2000082400012 20000824 00012 CE 2000 8 24 AU000444 1 20000414 G 2910 520010786 PIPE CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO MCAULY 3AF32C 3AF32C93 GL HYDRAULIC, MAIN CRACKED W K NONE O K OTHER FLUID LOSS IN INSP/MAINT 1 AU S (AUS) RIGHT HYDRAULIC FILTER PRESSURE PIPE SPLIT AND LEAKING AT OUTBOARD RADIUS. LOSS OF HYDRAULIC FLUID. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2001011106081 20010111 06081 NM 2001 1 11 AU000445 1 20000528 G 6123 6121K5 RELAY DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE PROPELLER FAULTY W C ABORTED TAKEOFF O OTHER TO TAKEOFF 1 AU S (AUS) AUTO-FEATHER RELAY 6121K5 FAULTY. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2000082400013 20000824 00013 EA 2000 8 24 AU000446 2 20000320 G 8520 CRANKSHAFT LYC GULSTM 500 500S 0141107 SW LYC O540 IO540E1B5 41532 EA ENGINE BROKEN W A UNSCHED LANDING E Y VIBRATION/BUFFET ENGINE STOPPAGE CL CLIMB 1 AU S RL805748C (AUS) ENGINE FAILURE. SUSPECT BROKEN CRANKSHAFT. 1 H 7 2 3O 3 O 6A1 1E4 2000082400014 20000824 00014 CE 2000 8 24 AU000447 1 20000603 G 2435 03601018 BEARING LEARSIEGLER 230790021 CESSNA 441 441 2076020 CE HARTZL HCB3T HCB3TN5 GL STARTER/GEN FAILED W K NONE H ELECT. POWER LOSS-50 PC DE DESCENT 1 AU S 269 (AUS) LEFT ENGINE STARTER/GENERATOR REAR BEARING FAILED. LEFT ELECTRICAL BUS CURRENT LIMITER ALSO FAILED. 1 L 7 2 3T RT A28CE 6 C P15EA 2001011106082 20010111 06082 2001 1 11 AU000448 4 20000606 G 3414 WL604AMA26 INDICATOR BAG BAE146 BAE146200A 1500266 EU LYC ALF502 ALF502R3A 41580 NE AIRSPEED FAULTY W C ABORTED TAKEOFF N FALSE WARNING TO TAKEOFF 1 AU S (AUS) CAPTAINS AIRSPEED INDICATOR (ASI) FAULTY. 2 H 7 4 4F 4 F RT A49EU E6NE 2000071200161 20000712 00161 CE 2000 7 12 AU000449 1 20000605 G 5320 26111446 BRACKET CESSNA CESSNA 208 208B 2073701 CE FUSELAGE FAILED W O OTHER F FLT CONT AFFECTED DE DESCENT 1 AU S B0428 (AUS) FLAP MOTOR SUPPORT BRACKETS PN 2611144-6 AND PN 2611144-7 TORN FROM FUSELAGE STRUCTURE. 1 H 7 1 3T A37CE 2000100300073 20001003 00073 NM 2000 10 3 AU000450 1 20000520 G 2822 50081761 HOUSING SUNDSTRANDEM 5006003C BOEING 767 767277 NM GE CF6 CF680A 30025 NE FUEL BOOST PUMP ERODED W K NONE K FLUID LOSS TX TAXI/GRND HDL 1 AU S 337 (AUS) MAIN FORWARD FUEL TANK LEFT BOOST PUMP FAILED. INVESTIGATION FOUND PIECES OF METAL SEPARATED FROM THE HOUSING INL ET STRUTS JAMMING THE CHECK VALVE PARTIALLY OPEN. 2 L 7 2 4F 4 F RT A1NM E13NE 2001011100632 20010111 00632 NM 2001 1 11 AU000451 1 20000603 G 5610 91142H2369 WINDSHIELD BOEING 737 73733A 1384673 NM COCKPIT CRACKED W O OTHER O OTHER DE DESCENT 1 AU S (AUS) FIRST OFFICERS NO1 WINDOW OUTER PANE CRACKED. 2 L 7 2 4F RT A16WE 2001011100633 20010111 00633 NM 2001 1 11 AU000452 1 20000526 G 5320 WEB BOEING 747 747338 NM FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NOSE LANDING GEAR WHEEL WELL TORQUE BOX VERTICAL WEB CRACKED ANDFRAME DISTORTED. 2 L 7 2 4F RT A20WE 2001011100634 20010111 00634 NE 2001 1 11 AU000453 2 20000527 G 7230 13065 BLADE BOEING 747 747438 NM RROYCE RB211 RB211524G19 NE COMPRESSOR FAILED W O OTHER E J VIBRATION/BUFFET WARNING INDICATION NR NOT REPORTED 1 AU S 41574 13065 (AUS) NO2 ENGINE HIGH PRESSURE COMPRESSOR BLADE FAILED. 2 L 7 4 4F 4 F RT A20WE E30NE 2001011100635 20010111 00635 NM 2001 1 11 AU000454 1 20000523 G 2752 FITTING BOEING 747 747338 NM TE FLAP ACTUATOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) OUTBOARD RT AFT TRAILING EDGE FLAP DRIVE MECHANISM OUTBOARD FITTING CRACKED AND BOLT BADLY CORRODED. BOLT HEAD MIS SING ANDBOLT PROTRUDING. 2 L 7 2 4F RT A20WE 2001011100636 20010111 00636 2001 1 11 AU000455 4 20000523 G 2565 G126 PIN BOEING 767 767338 1385151 NM GE CF6 CF680C2* GL ESCAPE SLIDE MISINSTALLED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) ESCAPE SLIDERAFT INFLATION BOTTLE SAFETY PIN STILL FITTED. SLIDEWOULD NOT HAVE OPERATED WHEN REQUIRED. PERSONNEL / MAINTENANCE ERROR. 2 L 7 2 4F 4 F RT A1NM E23EA 2000082800019 20000828 00019 CE 2000 8 28 AU000456 1 20000601 G 7160 HOSE LYC CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA MCAULY 1C160 1C160DTM GL ENG AIR INTAKE LOOSE W K NONE E VIBRATION/BUFFET CR CRUISE 1 AU S L266776 731692 (AUS) ENGINE CARBURETOR HEAT SCAT HOSE CLAMP MISSING. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2001011100666 20010111 00666 EU 2001 1 11 AU000457 1 20000610 G 7600 CONTROL UNIT SAAB SF340 SF340A 7850100 EU GE CT7TP CT75A2 30030 NE ROTOL R354 R3544123F13 NE ENGINE MALFUNCTIONED W C ABORTED TAKEOFF E VIBRATION/BUFFET TO TAKEOFF 1 AU S 367175 (AUS) RT ENGINE CTOT WOULD NOT ENABLE. DURING FAULT FINDING ENGINEOPERATED OK UNTIL TORQUE MOTOR LOCKOUT WAS SELECTED. S USPECTTORQUE MOTOR LOCKED OUT DURING OPERATION. 2 L 7 2 4T 4 T RT A52EU E8NE6 6 C P61GL 2001011100667 20010111 00667 EU 2001 1 11 AU000458 1 20000609 G 7712 7239060503 PANEL SAAB SF340 340B 7860101 EU GE CT7TP CT79B 30030 NE ROTOL R390 R3904123F27 NE TORQUE PANEL FAULTY W C ABORTED TAKEOFF N FALSE WARNING TO TAKEOFF 1 AU S 5780 785153 (AUS) CONSTANT TORQUE ON TAKEOFF (CTOT) PANEL FAULTY. 2 L 7 2 4T 4 T RT A52EU E8NE 6 C P31NE 2001011100668 20010111 00668 SO 2001 1 11 AU000459 1 20000607 G 5610 SEAL EMB 120 EMB120 3260201 SO PWA 118 PW118A NE COCKPIT WINDOW FAULTY W A UNSCHED LANDING O OTHER CL CLIMB 1 AU S (AUS) COPILOTS SIDE WINDOW SEAL OUT OF POSITION AND LEAKING. 2 L 7 2 4T 4 T RT A31SO E20NE 2000082800020 20000828 00020 EA 2000 8 28 AU000460 2 20000529 G 7210 GEARBOX PWA BEECH 200 B200C 1152924 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL ENGINE CONTAMINATED W K NONE E J VIBRATION/BUFFET WARNING INDICATION CR CRUISE 1 AU S PCE81186 (AUS) PROPELLER REDUCTION GEARBOX METAL CONTAMINATION. 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2000082800021 20000828 00021 2000 8 28 AU000461 4 20000609 G 3422 258719343 GYRO BAG JETSTM JETSTM3201 1500217 EU DIRECTIONAL GYRO FAULTY W K NONE O OTHER NR NOT REPORTED 1 AU S 92071948 (AUS) NR 2 DIRECTIONAL GYRO INTERNAL FAULT. 2 L 7 2 4T RT A56EU 2000082800022 20000828 00022 WP 2000 8 28 AU000462 2 20000607 G 7230 P31075 SEAL GARRTT CESSNA 441 441 2076020 CE GARRTT TPE331 TPE3318 01514 WP HARTZL HCB3T HCB3TN5 GL ENGINE LEAKING W K NONE B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 AU S (AUS) LEFT ENGINE CARBON SEAL ALLOWING OIL TO LEAK INTO THE BLEED AIR SYSTEM AND CONTAMINATE THE COALESCER BAG IN THE AI R CYCLE MACHINE. SMOKE IN THE CABIN. 1 L 7 2 3T 4 T RT A28CE E4WE 6 C P15EA 2000082800023 20000828 00023 SO 2000 8 28 AU000463 1 20000613 G 3234 12038594001 CONTROL BOX EMB 120 EMB120 3260201 SO PWA 118 PW118A NE LANDING GEAR SEL FAULTY W K NONE O N OTHER FALSE WARNING TO TAKEOFF 1 AU S J120046R (AUS) LANDING GEAR CONTROL BOX FAULTY. 2 L 7 2 4T 4 T RT A31SO E20NE 2000082800024 20000828 00024 WP 2000 8 28 AU000464 1 20000607 G 5743 BRACKET DOUG DC3 DC3CS1C3G 3021458 WP PWA R1830 R183092 52020 NE HAMSTD 23E 23E50 NE WING, L/G WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LANDING GEAR REAR STRUT ATTACHMENT ''Y'' BRACKETS HAD MOUNTING HOLES DRILLED OVERSIZE. FOUND DURING INSPECTION IA W AD/DC3/31 AMDT2. 2 L 7 2 4R 4 R A669 5E4 6 C P603 2001011100669 20010111 00669 WP 2001 1 11 AU000465 1 20000607 G 5330 SKIN DOUG DC3 DC3CS1C3G 3021458 WP PWA R1830 R183092 52020 NE HAMSTD 23E 23E50 NE FUSELAGE CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) CENTER SECTION UPPER CORRUGATED SKIN CRACKED AND CORRODED IN AN AREA LOCATED NEAR THE AIRCRAFT CENTRELINE INBOARD OF STN 7.5 BETWEEN THE CENTRE AND REAR SPARS. 2 L 7 2 4R 4 R A669 5E4 6 C P603 2000082800025 20000828 00025 EA 2000 8 28 AU000466 2 20000616 G 7210 GEARBOX PWA BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL ENGINE CONTAMINATED W K NONE E J VIBRATION/BUFFET WARNING INDICATION CL CLIMB 1 AU S PCE80767 (AUS) PROPELLER REDUCTION GEARBOX METAL CONTAMINATION. 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2000072000030 20000720 00030 EU 2000 7 20 AU000468 1 20000428 G 6220 350A31190703 STARFLEX AEROSP AS355 AS355F1 8680810 EU ALLSN 250C 250C20F 03013 GL MAIN ROTOR HEAD CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S M3308 CAE840630627 (AUS) MAIN ROTOR STARFLEX HEAD ASSEMBLY CRACKED. 1 G 7 2 3U 3 U H11EU E4CE 2000082800026 20000828 00026 EA 2000 8 28 AU000469 2 20000502 G 8530 05K21114KIT CYLINDER LYC CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA MCAULY 1A103 1A103TCM GL ENGINE CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S L1939415 LL034 (AUS) ENGINE SEIZED. CYLINDERS AND PISTON RINGS RUSTED. SURFACE CORROSION EVIDENT ON CAM FOLLOWERS AND CONNECTING RODS . AIRCRAFT HAD RECENTLY UNDERGONE FUEL DECONTAMINATION. (X) 1 H 7 1 3O 3 O NT 3A19 E223 5 N P50GL 2001011104166 20010111 04166 2001 1 11 AU000470 1 20000513 G 3500 80366201 CONTROL BOX OXYGEN SYSTEM WRONG PART W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) OXYGEN FLOW CONTROL UNITS (2 OFF) HAD UNAPPROVED SEALANT (TAPE AND PLASTICINE) APPLIED TO THE FIRST STAGE PRESSURE RELIEF PORTS. UNAPPROVED PART. 2001011100670 20010111 00670 EU 2001 1 11 AU000471 1 20000613 G 7712 SWITCH SAAB SF340 340B 7860101 EU GE CT7TP CT79B 30030 NE ROTOL R375 R3754123F21 NE FUSELAGE MALFUNCTIONED W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 AU S 785512785402 (AUS) CONSTANT TORQUE ON TAKEOFF (CTOT) SWITCH LEFT IN INCORRECT POSITION. LT AND RT ENGINE OVERTEMPERATURE OCCURRED. 2 L 7 2 4T 4 T RT A52EU E8NE 6 C P17NE 2000082800027 20000828 00027 SO 2000 8 28 AU000472 1 20000614 G 5711 SPAR CAP PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA HARTZL HCE3Y HCE3YR2 GL WING SPAR STRUCT CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LOWER SPAR CAP CORRODED IN WING ROOT AREA. FOUND FOLLOWING REMOVAL OF ANTI-CHAFING TAPE. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001011100671 20010111 00671 2001 1 11 AU000473 4 20000313 G 2565 7A124836 SLIDE BOEING 747 747SP38 NM PAX DOOR MALFUNCTIONED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT UPPER DECK ESCAPE SLIDE FAILED TO CORRECTLY DEPLOY. 2 L 7 4 4F RT A20WE 2000082800028 20000828 00028 CE 2000 8 28 AU000474 1 20000614 G 2820 52001063 PIPE CESSNA 402 402CESSNA 207590K CE CONT O520 TSIO520E 17040 SO MCAULY 3AF32C 3AF32C87 GL ACFT FUEL DISTRI CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUEL CROSSFEED PIPE CORRODED AND LEAKING. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2000082800029 20000828 00029 CE 2000 8 28 AU000475 1 20000614 G 2820 510010877 PIPE CESSNA 402 402CESSNA 207590K CE CONT O520 TSIO520E 17040 SO MCAULY 3AF32C 3AF32C87 GL ACFT FUEL DIST WORN W K NONE O OTHER IN INSP/MAINT 1 AU S 183445 (AUS) FUEL CROSSFEED PIPE WORN BY SPAR ANGLE. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2001011100672 20010111 00672 SW 2001 1 11 AU000476 1 20000614 G 2435 03601018 BEARING SWRNGN SA226 SA226TC 8780404 SW HARTZL HCB3T HCB3TN5 GL STARTER GEN FAILED W A UNSCHED LANDING H ELECT. POWER LOSS-50 PC CL CLIMB 1 AU S (AUS) LT STARTER-GENERATOR REAR BEARING FAILED AND SHAFT SHEARED. 2 L 7 2 4T RT A8SW 6 C P15EA 2001011100673 20010111 00673 EU 2001 1 11 AU000477 1 20000609 G 2530 38512 CONNECTOR SAAB SF340 SF340A 7850100 EU GE CT7TP CT75A2 30030 NE ROTOL R354 R3544123F13 NE GALLEY BROKEN W O OTHER B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 AU S (AUS) GALLEY COFFEEMAKER PLUG BROKEN CAUSING OVERHEATING. RT EADI HOT. 2 L 7 2 4T 4 T RT A52EU E8NE6 6 C P61GL 2001011100674 20010111 00674 EU 2001 1 11 AU000478 1 20000609 G 2910 137311D1576 PIPE BAG JETSTM JETSTM3201 1500217 EU ROTOL R333 R333482F12 GL HYDRAULIC SYS RUPTURED W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S (AUS) RT HYDRAULIC BRAKE PIPE LOCATED IN THE LANDING GEAR BAY FAILED. LOSS OF HYDRAULIC FLUID. 2 L 7 2 4T RT A56EU 6 C P61GL 2000082800030 20000828 00030 SO 2000 8 28 AU000479 2 20000607 G 8530 SA625393 SEAT CONT CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO MCAULY 3A32C D3A32C90 GL ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 291324R (AUS) INLET VALVE SPRING SEATS ON ALL CYLINDERS CRACKED. FURTHER INVESTIGATION FOUND THAT THE INLET VALVE GUIDES WERE N OT FULLY SEATED IN THE CYLINDER HEAD. 1 H 7 1 3O 3 O A4CE E5CE 5 C P21EA 2001011100675 20010111 00675 SO 2001 1 11 AU000480 1 20000621 G 3234 12043270501 RELAY EMB 120 EMB120 3260201 SO PWA 118 PW118A NE MLG INTERMITTENT W O OTHER N FALSE WARNING LD LANDING 1 AU S (AUS) LANDING GEAR RELAY BOX INTERMITTENT IN OPERATION. 2 L 7 2 4T 4 T RT A31SO E20NE 2001011100676 20010111 00676 SO 2001 1 11 AU000481 1 20000622 G 3231 12032943001 VALVE EMB 120 EMB120 3260201 SO PWA 118 PW118A NE MLG STUCK W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 AU S (AUS) RT NOSE LANDING GEAR DOOR SEQUENCE VALVE STICKING. LANDING GEAR DOOR SOLENOID VALVE PNO SV14H1100-4 SUSPECT INTERN AL LEAK. 2 L 7 2 4T 4 T RT A31SO E20NE 2000071900174 20000719 00174 SW 2000 7 19 AU000482 1 20000601 G 6220 206011113103 TRUNNION BELL BELL 206 206B3 1181506 SW ALLSN 250C 250C20B 03013 GL MAIN ROTOR HEAD DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S 304 (AUS) MAIN ROTOR TRUNNION FAULTY. MAST AND SPLIT CONES ALSO REPLACED. 1 G 7 1 3U 3 U H2SW E4CE 2000071900175 20000719 00175 EU 2000 7 19 AU000483 1 20000526 G 2435 150SG10095 BRUSH BLOCK 150SG1RZQ SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1B 6OO30 NE STARTER/GEN BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S 5461 (AUS) STARTER/GENERATOR BRUSHES BROKEN. 1 G 7 1 3U 3 U H9EU E19EU 2000082800031 20000828 00031 EA 2000 8 28 AU000484 2 20000602 G 8530 68761 PIPE LYC BNORM BN2 BN2A20 1520220 EU LYC O540 IO540K1B5 41532 EA HARTZL HCC2Y HCC2YK2 GL ENGINE CORRODED W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S L1327648A (AUS) RIGHT ENGINE NR 5 CYLINDER ROCKER COVER OIL DRAIN PIPE HOLED DUE TO CORROSION. LOSS OF ENGINE OIL. 1 H 7 2 3O 3 O A17EU 1E4 5 C P920 2000082800032 20000828 00032 CE 2000 8 28 AU000485 1 20000612 G 2913 98807101 PRESSURE SWITCH 12808461 CESSNA 210 210L 2073448 CE CONT O520 IO520L 17032 SO MCAULY 3A32C D3A32C88 GL HYDRAULIC PUMP FAULTY W K NONE O OTHER TO TAKEOFF 1 AU S 1000 (AUS) LANDING GEAR POWER PACK PRESSURE SWITCH FAULTY. 1 H 7 1 3O 3 O 3A21 E5CE 5 C P21EA 2000082800033 20000828 00033 GL 2000 8 28 AU000486 1 20000414 G 3233 10258162 FITTING 106580270 AMTR MSTG2 MUSTANG2 GL PCKARD V1650 V16507 49001 SO HAMSTD 24D 24D50 NE LANDING GEAR ACT DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S 33 97277468 V303101 ADH9196 (AUS) RIGHT MAIN LANDING GEAR RETRACTION RAM FITTING FAILED. INVESTIGATION FOUND THAT THE END FITTING FROM A FLAP RAM HAD BEEN FITTED INSTEAD OF THE CORRECT PART. UNAPPROVED PART. 1 L 7 1 3O 4 V EXPA1L71 EXP4V 6 C P784 2000082800034 20000828 00034 WP 2000 8 28 AU000487 2 20000612 G 8530 EXHAUST VALVE DHAVXX GIPSYMAJOR10 DHAVXX DH82 DH82AROBRTSN 2801002 WP DHAVXX GIPSY GIPSYMAJOR1 20004 WP ENGINE FAILED W K NONE E VIBRATION/BUFFET NR NOT REPORTED 1 AU S 816 10114 (AUS) NR 1 CYLINDER EXHAUST VALVE HEAD SEPARATED FROM VALVE STEM. VALVE HEAD PUNCTURED PISTON AND EXITED THE ENGINE VIA THE TOP RIGHT SIDE OF THE CRANKCASE. 1 Q 7 1 3I 3 I A8EU A8EU 2000082800035 20000828 00035 CE 2000 8 28 AU000488 1 20000616 G 3230 508102101 MOTOR BEECH 80 70 1152807 CE LYC O480 IGSO480A1E6 41529 EA HARTZL HCB3Z HCB3Z302 GL LANDING GEAR ACT FAILED W K NONE O OTHER LD LANDING 1 AU S (AUS) LANDING GEAR MOTOR DRIVESHAFT AND GEAR TEETH STRIPPED. 1 L 7 2 3O 3 O 3A20 E284 5 C P907 2000083000029 20000830 00029 SO 2000 8 30 AU000490 1 20000503 G 3220 GEAR PIPER PA23 PA23250 7102308 SO LYC O540 IO540C4B5 41532 EA HARTZL HCE2Y HCE2YR2 GL NOSE COLLAPSED W O OTHER O OTHER LD LANDING 1 AU S (AUS) NOSE LANDING GEAR COLLAPSED ON LANDING. 1 L 7 2 3O 3 O 1A10 1E4 5 C P9EA 2000081000032 20000810 00032 CE 2000 8 10 AU000491 1 20000623 G 3231 504500110 BELLCRANK CESSNA 310R CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO L/G DOOR BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S 1681 (AUS) RIGHT MAIN LANDING GEAR DOOR BELLCRANK BROKEN. 1 L 7 2 3O 3 O 3A10 E5CE 2001011100708 20010111 00708 EU 2001 1 11 AU000492 1 20000604 G 2751 D150175 TRANSDUCER FOKKER F27 F27MK50 EU TE FLAP POSITION INTERMITTENT W O OTHER F FLT CONT AFFECTED CL CLIMB 1 AU S (AUS) FLAP POSITION TRANSDUCER CONNECTOR LOOSE. 2 H 7 2 4T RT A817 2001011100709 20010111 00709 EU 2001 1 11 AU000493 1 20000618 G 5210 F5106043425 SEAL FOKKER F27 F27MK50 EU PAX DOOR CONTAMINATED W O OTHER O OTHER CR CRUISE 1 AU S (AUS) CABIN DOOR SEAL CONTAMINATED WITH WATER. SUSPECT WATER FROZE AT ALTITUDE CAUSING LOSS OF PRESSURISATION. 2 H 7 2 4T RT A817 2001011100711 20010111 00711 EU 2001 1 11 AU000494 1 20000616 G 7722 321EDP32 INDICATOR BAG BAE146 BAE146200A 1500266 EU LYC ALF502 ALF502R3A 41580 NE ENGINE EGT/TIT FLUCTUATES W C ABORTED TAKEOFF E VIBRATION/BUFFET TO TAKEOFF 1 AU S (AUS) NR 1 ENGINE TGT SYSTEM TERMINAL LOOSE AT FORWARD PYLON BREAK. 2 H 7 4 4F 4 F RT A49EU E6NE 2001011100712 20010111 00712 NE 2001 1 11 AU000496 2 20000623 G 7320 1103P2671 SWITCH SAAB SF340 SF340A 7850100 EU GE CT7TP CT75A2 30030 NE ROTOL R354 R3544123F13 NE FUEL CONTROL DAMAGED W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 AU S (AUS) LT ENGINE AUTO COARSEN P3 SWITCH HAD HIGH RESISTANCE ACROSS THE CONTACTS. 2 L 7 2 4T 4 T RT A52EU E8NE6 6 C P61GL 2001011100713 20010111 00713 EA 2001 1 11 AU000497 1 20000626 G 5610 WINDSHIELD CNDAIR CL600 CL6002B19 EA COCKPIT CRACKED W A UNSCHED LANDING O OTHER CR CRUISE 1 AU S (AUS) LH FORWARD WINDSHIELD CRACKED. 2 L 7 2 4F RT A21EA 2001011100719 20010111 00719 SO 2001 1 11 AU000498 1 20000618 G 3260 12041127001 PROXIMITY SENSOR EMB 120 EMB120 3260201 SO PWA 118 PW118A NE MLG INTERMITTENT W O OTHER N FALSE WARNING CL CLIMB 1 AU S (AUS) RT MAIN LANDING GEAR POSITION PROXIMITY SENSOR INTERMITTENT INOPERATION. 2 L 7 2 4T 4 T RT A31SO E20NE 2000081000033 20000810 00033 CE 2000 8 10 AU000499 1 20000617 G 3260 ICHI6 SWITCH CESSNA 441 441 2076020 CE MCAULY 3G34C6 3GFR34C601 GL LANDING GEAR POS INTERMITTENT W K NONE E VIBRATION/BUFFET NR NOT REPORTED 1 AU S (AUS) LEFT MAIN LANDING GEAR SQUAT SWITCH INTERMITTENT IN OPERATION. 1 L 7 2 3T RT A28CE 6 C P54GL 2000071900176 20000719 00176 WP 2000 7 19 AU000500 1 20000621 G 6220 36124 CUFF HILLER HILLER UH12 UH12E 4360122 WP ALLSN 250C 250C20 03013 GL MAIN ROTOR HEAD CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 527 10580 (AUS) MAIN ROTOR CUFF CRACKED FROM BOLT HOLE. CRACK LENGTH 10MM (0.393IN). FOUND DURING DYE PENETRANT INSPECTION IAW AD/ HIL12/17(SB 36-1). 1 G 7 1 3O 3 U 4H11 E4CE 2000071900177 20000719 00177 SW 2000 7 19 AU000501 1 20000624 G 3397 WIRE BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE PASSENGER COMPT BROKEN W O OTHER B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 AU S (AUS) CABIN DOME LIGHT DIMMER POTENTIOMETER WIRE BROKEN AND SHORT CIRCUITING. 1 G 7 2 4U 4 U H4SW E22EA 2000112800091 20001128 00091 2000 11 28 AU000502 4 20000628 G 6122 B20897 COVER MCAULY VARIOUS PROP GOVERNOR FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) CSU COVER FAULTY. THE COVER IS OVAL SHAPED AND THE BORE IS OVERSIZE BY 0.0762 MM (0.003 INCH). SUBMITTER STATED TH E ITEM IS FAULTY AS RECEIVED FROM THE MANUFACTURER. (X) 2001011100745 20010111 00745 EU 2001 1 11 AU000503 1 20000616 G 2823 9401037 VALVE FOKKER F28 F28MK0100 4990807 EU FUEL SELECTOR SEIZED W C ABORTED TAKEOFF E J VIBRATION/BUFFET WARNING INDICATION TO TAKEOFF 1 AU S (AUS) RT FIRE/FUEL SHUTOFF VALVE MOTOR SEIZED APPROXIMATELY 75 PERCENT CLOSED. 2 L 7 2 4F RT 2001011100747 20010111 00747 WP 2001 1 11 AU000504 2 20000619 G 7322 897780 FUEL CONTROL BAG JETSTM JETSTM3201 1500217 EU GARRTT TPE331 TPE33112UHR WP ROTOL R333 R333482F12 GL LT ENGINE FAULTY W A UNSCHED LANDING E J VIBRATION/BUFFET WARNING INDICATION CR CRUISE 1 AU S 2176 P66363 (AUS) LT ENGINE FUEL CONTROL UNIT FAULTY. 2 L 7 2 4T 4 T RT A56EU E4WE 6 C P61GL 2001011100748 20010111 00748 EU 2001 1 11 AU000505 1 20000628 G 2841 INDICATOR BAG JETSTM JETSTM3201 1500217 EU GARRTT TPE331 TPE33112UA 01514 WP MCAULY 4HFR34 4HFR34C653 NE FUEL QUANTITY OUT OF TOLERANCE W O OTHER O OTHER CL CLIMB 1 AU S (AUS) FUEL QUANTITY SYSTEM OUT OF CALIBRATION. 2 L 7 2 4T 4 T RT A56EU E4WE 6 C 3PNE 2001011100749 20010111 00749 EU 2001 1 11 AU000506 1 20000618 G 3412 522707 INDICATOR FOKKER F27 F27MK50 EU TAT FAULTY W O OTHER B SMOKE/FUMES/ODORS/SPARKS LD LANDING 1 AU S 0870032 (AUS) TOTAL AIR TEMPERATURE (TAT) INDICATOR INTERNAL FAULT. 2 H 7 2 4T RT A817 2000082100099 20000821 00099 EA 2000 8 21 AU000507 1 20000628 G 2820 PIPE DHAV DHC6 DHC6 2802606 EA ACFT FUEL DIST FOD W K NONE K FLUID LOSS CR CRUISE 1 AU S (AUS) FORWARD FUEL TANK TRANSFER PIPE BLOCKED BY BLANKING PLUG. FOD. (X) 1 H 7 2 3T RT A9EA 2000082100100 20000821 00100 CE 2000 8 21 AU000508 1 20000623 G 2823 5425662046 CONTROL CABLE BEECH 58 58 1152740 CE CONT O520 IO520* 17032 SO FUEL SELECTOR SEIZED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RIGHT FUEL SELECTOR TELEFLEX CABLE FITTING BINDING AT SELECTOR END. (X) 1 L 7 2 3O 3 O 3A16 E5CE 2000082100101 20000821 00101 CE 2000 8 21 AU000509 1 20000623 G 7810 2437241 MANIFOLD BEECH 58 58 1152740 CE CONT O520 IO520* 17032 SO ENGINE COLLECTOR FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S 2437241 (AUS) LEFT ENGINE EXHAUST MANIFOLDS TRANSPOSED. (X) 1 L 7 2 3O 3 O 3A16 E5CE 2000082100102 20000821 00102 SO 2000 8 21 AU000511 2 20000629 G 8520 646277 LIFTER CESSNA 182 182P 2075816 CE CONT O470 O470R 17026 SO MCAULY 2A34C 2A34C203 GL ENGINE WORN W K NONE O OTHER IN INSP/MAINT 1 AU S 459310 739670 (AUS) HYDRAULIC VALVE LIFTERS (TAPPETS) WORN AND PITTED. EVIDENCE OF PITTING ON THE CAMSHAFT. (X) 1 H 7 1 3O 3 O NT TA13 E273 5 C P3EA 2000082100103 20000821 00103 EA 2000 8 21 AU000512 2 20000426 G 8500 ENGINE LYC PIPER PA24 PA24400 7102408 SO LYC O720 IO720A1A 41546 EA HARTZL HCA3V HCA3VK4 GL ENGINE DETERIORATED W K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS TO TAKEOFF 1 AU S 218654C (AUS) ENGINE IN A DETERIORATED AND POOR CONDITION. SOME UNAPPROVED PARTS FITTED. (X) 1 L 7 1 3O 3 O 1A15 1E15 5 C P6EA 2000082100104 20000821 00104 CE 2000 8 21 AU000513 1 20000703 G 2710 AN443A BOLT CESSNA CESSNA 150 150M 2071830 CE CONT O200 O200A 17020 SO MCAULY 1A102 1A102OCM GL AILERON CONTROL LOOSE W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S 15079333 (AUS) AILERON PULLEY PN S378-4 TO CENTER CONSOLE ATTACHMENT BOLT HAD THE NUT MISSING AND THE INCORRECT WASHER SPACING UN DER THE PULLEY GUARDS. (X) 1 H 7 1 3O 3 O 3A19 E252 5 N P918 2000082100105 20000821 00105 SO 2000 8 21 AU000514 1 20000621 G 3213 4550406 AXLE PIPER PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL MLG CRACKED W K NONE O OTHER LD LANDING 1 AU S 317305064 (AUS) MAIN LANDING GEAR STRUT AXLE CRACKED. (X) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001011100561 20010111 00561 NM 2001 1 11 AU000515 1 20000613 G 2761 654494710 HOUSING BOEING 65448517 BOEING 737 737377 NM DRAG CONTROL ACT CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S 4392A303103S (AUS) LT INBOARD GROUND SPOILER OUTBOARD ACTUATOR HOUSING CRACKED. 2 L 7 2 4F RT A16WE 2001011100588 20010111 00588 NM 2001 1 11 AU000516 1 20000604 G 2760 285T0012116 CONTROLLER BOEING 767 767277 NM GE CF6 CF680A 30025 NE DRAG CONTROL SYS FAULTY W O OTHER F FLT CONT AFFECTED NR NOT REPORTED 1 AU S (AUS) LT WING NR 3 SPOILER VIBRATING UP TO 52.8MM (2IN) FROM THE SELECTED POSITION. WORKSHOP INVESTIGATION FOUND THE SPO ILER CONTROL MODULE FAULTY. 2 L 7 2 4F 4 F RT A1NM E13NE 2001011100594 20010111 00594 NM 2001 1 11 AU000517 1 20000527 G 5320 253T31164 WEB BOEING 767 767277 NM GE CF6 CF680A 30025 NE FUSELAGE CRACKED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) PARK BRAKE INPUT CRANK ASSEMBLY SUPPORT WEB CRACKED. SUSPECTPARKING BRAKE MECHANISM INCORRECTLY RIGGED CAUSING FLE XING OF THE WEB. 2 L 7 2 4F 4 F RT A1NM E13NE 2001011100631 20010111 00631 2001 1 11 AU000518 4 20000616 G 2565 SLIDE BOEING 747 747438 NM PAX DOOR FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NR 1 LT SLIDERAFT MOORING LINE TANGLED WITH ASPIRATOR. 2 L 7 4 4F RT A20WE 2001011100282 20010111 00282 NM 2001 1 11 AU000519 1 20000618 G 3397 WIRE BOEING 747 747338 NM CABIN BURNED W O OTHER B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 AU S (AUS) SIDEWALL LIGHTING SYSTEM TOMBSTONE AT POSITION 40A SMOKING FROM POWER WIRE. 2 L 7 2 4F RT A20WE 2001011106203 20010111 06203 2001 1 11 AU000520 4 20000618 G 2565 7A146914 SLIDE BOEING 747 747438 NM PAX DOOR FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) DOOR 5 RT ESCAPE SLIDE INFLATED WITH DOOR CLOSED AND LOCKED. SAFETY PIN STILL IN POSITION. 2 L 7 4 4F RT A20WE 2001011106204 20010111 06204 NE 2001 1 11 AU000521 2 20000528 G 7510 2351A000 VALVE LYC ALF502R5 BAC 146 146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE ENGINE ANTI-ICE FAULTY W A UNSCHED LANDING E J VIBRATION/BUFFET WARNING INDICATION CR CRUISE 1 AU S 17783 A8713381 (AUS) NR 2 ENGINE ANTI-ICE VALVE FAULTY. 2 H 7 4 4F 4 F A49EU E6NE 2000080700169 20000807 00169 SW 2000 8 7 AU000523 1 20000619 G 6220 2060111221 BOLT BELL 206011100021 BELL 206 206B3 1181506 SW ALLSN 250C 250C20B 03013 GL MAIN ROTOR HEAD WRONG PART W K NONE O OTHER IN INSP/MAINT 1 AU S 1309 JILM1679 (AUS) MAIN ROTOR HUB LATCH BOLTS HAD UNKNOWN HISTORY AND WERE REPLACED. THE LATCH BOLTS WERE SERIAL NUMBERED FOR USE ON BELL 206L TYPE AIRCRAFT AND HAVE A 1200 HOUR LIFE. (X) 1 G 7 1 3U 3 U H2SW E4CE 2001011100283 20010111 00283 EU 2001 1 11 AU000524 1 20000630 G 2612 2HK163 FIRE LOOP BAG BAE146 BAE146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE FIRE DETECTION WORN W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 AU S (AUS) NR 2 ENGINE FIRE WIRE CHAFED. 2 H 7 4 4F 4 F RT A49EU E6NE 2000082100001 20000821 00001 CE 2000 8 21 AU000525 1 20000701 G 3233 99101399 ACTUATOR CESSNA 441 441 2076020 CE HARTZL HCB3T HCB3TN5 GL LANDING GEAR ACT FAULTY W K NONE O OTHER CR CRUISE 1 AU S 994 (AUS) NOSE LANDING GEAR ACTUATOR FAULTY. SUSPECT WORN DOWNLATCH PINS. (X) 1 L 7 2 3T RT A28CE 6 C P15EA 2001011100342 20010111 00342 NE 2001 1 11 AU000526 3 20000704 G 6197 WIRE STBROS SD3 SD360 8100606 EU PWA PT6 PT6A67R 52043 NE HARTZL HCA6A HCA6A3 NE PROP INDICATOR BROKEN W C ABORTED TAKEOFF N FALSE WARNING TO TAKEOFF 1 AU S PLE106132 GP148 (AUS) LT PROPELLER INDICATION SYSTEM WIRE BROKEN. 2 H 7 2 4T 4 T A41EU E26NE 6 C P14NE 2001011106205 20010111 06205 EU 2001 1 11 AU000527 1 20000704 G 3260 A7872200 SPRING FOKKER F28 F28MK0100 4990807 EU MLG BROKEN W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 AU S (AUS) LT MAIN LANDING GEAR DOOR FORWARD UPLOCK PROXIMITY SENSOR RETURNSPRING BROKEN. 2 L 7 2 4F RT 2001011106206 20010111 06206 WP 2001 1 11 AU000528 2 20000630 G 7210 3583605 BOLT BAG JETSTM JETSTM3201 1500217 EU GARRTT TPE331 TPE33112UHR WP MCAULY 4HFR34 4HFR34C653 NE RT ENGINE MISSING W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S 1036 P66277 (AUS) RT ENGINE PROPELLER SHAFT AFT ROLLER BEARING OUTER RACE FLANGED JOURNAL RETAINING BOLT FELL OUT AND WAS FOUND AT T HE BOTTOM OFTHE ACCESSORY GEARBOX. THE OTHER TWO RETAINING BOLTS WERE FOUND TO BE FINGER TIGHT ONLY. 2 L 7 2 4T 4 T RT A56EU E4WE 6 C 3PNE 2000082100002 20000821 00002 EA 2000 8 21 AU000529 2 20000521 G 8520 74309 BEARING PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA ENGINE FAILED W K NONE E K VIBRATION/BUFFET FLUID LOSS CR CRUISE 1 AU S 835 L80576AA (AUS) ENGINE NR 1 CONNECTING ROD BEARING SPINNING. METAL CONTAMINATION OF ENGINE OIL SYSTEM. (X) 1 L 7 2 3O 3 O A20SO E14EA 2000082100158 20000821 00158 CE 2000 8 21 AU000530 1 20000709 G 5311 FRAME BEECH 200 B200C 1152924 CE PWA PT6 PT6A42 52043 NE FUSELAGE MAIN FR CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUSELAGE FRAME NR 207 CRACKED ON LEFT SIDE. (X) 1 L 7 2 4T 4 T A24CE E4EA 2000082100003 20000821 00003 SO 2000 8 21 AU000531 1 20000407 G 5230 SEAL GULSTM G1159 GIV 3980115 SO RROYCE TAY TAY6118 EU CARGO/BAGGAGE DR LEAKING W O OTHER O OTHER CR CRUISE 1 AU S (AUS) REAR BAGGAGE DOOR SEAL LEAKING. INVESTIGATION COULD FIND NO FAULT ALTHOUGH MOISTURE WAS FOUND IN THE SEAL INFLATI ON SYSTEM. SUSPECT MOISTURE IN DOOR SEAL AIR SUPPLY LINES FROZE AT ALTITUDE. (X) 2 L 7 2 4F 4 F RT A12EA E25NE 2000081700072 20000817 00072 CE 2000 8 17 AU000532 1 20000711 G 5311 10112002117 FRAME BEECH 200 B200C 1152924 CE PWA PT6 PT6A42 52043 NE FUSELAGE MAIN FR CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LEFT FUSELAGE FRAME NR 207 CRACKED. LEFT AND RIGHT STIFFENER PN 101-120021-17 AND PN 101-120021-18 ALSO CRACKED. (X) 1 L 7 2 4T 4 T A24CE E4EA 2000081700073 20000817 00073 CE 2000 8 17 AU000533 1 20000612 G 3213 MS20392IC53 PIN 76 BEECH 76 76 1153005 CE MLG SHEARED W K NONE O OTHER LD LANDING 1 AU S (AUS) LEFT MAIN LANDING GEAR FORK CLEVIS PIN SHEARED. (X) 1 L 7 2 3O A29CE 2000081700074 20000817 00074 SO 2000 8 17 AU000534 1 20000710 G 5743 95299 STUD PIPER PA28 PA28R201T 7102813 SO CONT O360 TSIO360F 17025 SO HARTZL HCC2Y BHCC2YF2 GL WING, LANDING GR CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LEFT AND RIGHT MAIN LANDING GEAR SIDE BRACE STUDS CRACKED. FOUND DURING MAGNETIC PARTICLE INSPECTION IAW AD/PA28/ 91. (X) 1 L 7 1 3O 3 O 2A13 E9CE 5 C P920 2001011106208 20010111 06208 SO 2001 1 11 AU000535 1 20000709 G 3260 12041127001 PROXIMITY SWITCH EMB 120 EMB120 3260201 SO PWA 118 PW118A NE MLG FAULTY W C ABORTED TAKEOFF N FALSE WARNING TO TAKEOFF 1 AU S (AUS) LANDING GEAR POSITION PROXIMITY SWITCH SUSPECT FAULTY. 2 L 7 2 4T 4 T RT A31SO E20NE 2001011106209 20010111 06209 EU 2001 1 11 AU000536 2 20000619 G 7260 DRG152866 BEARING FOKKER F27 F27MK600 4990706 EU RROYCE DART DART5327 54509 EU ROTOL R4304 R1934304 EU ENGINE GEARBOX FAILED W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 AU S 12888 (AUS) RT ENGINE ACCESSORY GEARBOX INPUT BEARING FAILED ALLOWING OIL TOLEAK OUT OF CASE. 2 H 7 2 4T 4 T A817 E297 6 C P899 2000080700170 20000807 00170 GL 2000 8 7 AU000537 2 20000630 G 7250 23062750 HEAT SHIELD ALLSN HUGHES 369 369E 4470707 WP ALLSN 25OC 250C20R GL TURBINE SECTION CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S CAE295280 (AUS) ENGINE FIRST STAGE NOZZLE HEAT SHIELD CRACKED. FOUND DURING INSPECTION IAW ALERT BULLETIN CEBA-72-4075. (X) 1 G 7 1 3U 3 U H3WE E4CE 2000080700171 20000807 00171 NE 2000 8 7 AU000539 1 20000521 G 6210 7615009000045 SPAR SKRSKY 7615009000 SKRSKY S76 S76A 8143006 NE ALLSN 250C 250C30 03013 GL MAIN ROTOR BLADE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S A08600119 (AUS) MAIN ROTOR BLADE SPAR CRACKED FROM OUTBOARD LOWER FORWARD BLADE ATTACHMENT BOLT HOLE. LENGTH OF VISIBLE PORTION O F CRACK APPROXIMATELY 44.45 MM (1.75 INCHES). FOUND DURING INSPECTION IAW AD/S76/16 AMDT2. 1 G 7 2 3U 3 U H1NE E1GL 2000081700075 20000817 00075 CE 2000 8 17 AU000540 1 20000711 G 5342 04311481 BRACKET CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA MCAULY 1A103 1A103TCM GL STABILIZER ATTAC CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FIN ATTACHMENT BRACKET CRACKED. (X) 1 H 7 1 3O 3 O NT 3A19 E223 5 N P50GL 2001011106210 20010111 06210 NM 2001 1 11 AU000541 1 20000713 G 2760 MOUNT BOEING 727 72777C 1380420 NM PWA JT8 JT8D7A 52053 NE DRAG CONTROL FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NR 2 SPOILER ACTUATOR MOUNT ASSEMBLY INBOARD LOWER MOUNT BOLT HOLE LUG CRACKED AND OUTBOARD LOWER MOUNT BOLT HOLE LUG BROKEN.INBOARD LOWER MOUNT BOLT SHEARED. 2 L 7 3 4F 4 F A3WE E2EA 2000081700076 20000817 00076 SO 2000 8 17 AU000542 1 20000714 G 2434 A3985T HOUSING CHRYSLER 00638 PIPER PA28 PA28161 7102803 SO DC GENERATOR-ALT CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 6110120 (AUS) ALTENATOR REAR HOUSING CRACKED AT ATTACHMENT POINTS. 1 L 7 1 3O 2A13 2000081700077 20000817 00077 EU 2000 8 17 AU000543 1 20000709 G 5742 RIVET PARTEN P68 P68B EU LYC O360 IO360A1B6 41514 EA HARTZL HCC2Y HCC2YK2 GL WING, NAC/PYLON MISALIGNED W K NONE O OTHER IN INSP/MAINT 1 AU S 1L1819751A2L (AUS) LEFT OUTBOARD ENGINE NACELLE COWL RIVET MISALIGNED TO SPAR CAP RIVETS BY APPROXIMATELY 3.175 MM (0.125 INCH). FOU ND DURING INSPECTION IAW AD/P68/46. (X) 1 H 7 2 3O 3 O A31EU 1E10 5 C P920 2000081700078 20000817 00078 CE 2000 8 17 AU000544 1 20000612 G 3213 MS20392IC53 PIN BEECH BEECH 76 76 1153005 CE MLG SHEARED W K NONE O OTHER LD LANDING 1 AU S (AUS) LEFT MAIN LANDING GEAR SHOCK ABSORBER PN 105-384001-3 TO FORK PN 105-810021-9 ATTACHMENT PIN PN 105-810026-1 CLEVI S PIN SHEARED ALLOWING ATTACHMENT PIN TO MIGRATE OUT. (X) 1 L 7 2 3O A29CE 2001011106212 20010111 06212 WP 2001 1 11 AU000545 2 20000630 G 7260 31028823 HOUSING SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE33111U 01514 WP ROTOL R321 R321482F8 GL ENGINE GEARBOX CRACKED W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 AU S P44207C (AUS) ENGINE GEARBOX HOUSING CRACKED. 2 L 7 2 4T 4 T RT A8SW E4WE 6 C P61GL 2001011106213 20010111 06213 NM 2001 1 11 AU000546 1 20000419 G 5312 BULKHEAD BOEING 737 737377 NM FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUSELAGE FORWARD PRESSURE BULKHEAD WEB CRACKED AT RIGHT BUTTOCK LINE 5.7 AND WATERLINE 8.3. FOUND DURING EDDY CURR ENT INSPECTION. 2 L 7 2 4F RT A16WE 2001011106224 20010111 06224 NM 2001 1 11 AU000547 1 20000512 G 5730 SKIN BOEING 737 737377 NM LT WING CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT WING LOWER SKIN CONTAINED INTERGRANNULAR CORROSION IN AN AREAADJACENT TO ACCESS PANEL 7204L. CORROSION EXTENDED FROM THE EDGEOF THE PANEL CUTOUT IN TWO LOCATIONS FOR APPROXIMATELY 25MM (1IN). 2 L 7 2 4F RT A16WE 2001011106226 20010111 06226 NM 2001 1 11 AU000548 1 20000717 G 2910 S271T12161883 HEAT EXCHANGER BOEING 767 767338 1385151 NM GE CF6 CF680C2* GL HYD SYSTEM FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT HYDRAULIC SYSTEM HEAT EXCHANGER CORE FAILED ALLOWING THE CONTENTS OF THE RT HYDRAULIC SYSTEM TO DRAIN INTO THE RT FUEL TANK. 2 L 7 2 4F 4 F RT A1NM E23EA 2001011106227 20010111 06227 NM 2001 1 11 AU000549 1 20000710 G 2710 PIN BOEING 767 767238 NM PWA JT9 JT9D7R4E 52054 NE AILERON CONTROL MISSING W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT INBOARD AILERON LOWER HALF PCA SUMMING LEVER/INPUT ROD PIVOT LINK PIN MISSING. 2 L 7 2 4F 4 F RT A1NM E3NE 2001011106229 20010111 06229 NM 2001 1 11 AU000550 1 20000711 G 5714 DRAIN LINE BOEING 747 747438 NM WING CENTER BOX BLOCKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) WING CENTRE SECTION CAVITY DRAIN BLOCKED BY WAX BUILDUP. LARGEAMOUNTS OF DEBRIS FOUND IN AREA. FOUND DURING INSPEC TION IAWAD/B747/71. 2 L 7 4 4F RT A20WE 2001011106231 20010111 06231 NM 2001 1 11 AU000551 1 20000711 G 3040 205319EO39LL4TL POWER CABLE BOEING 737 737476 NM CFMINT CFM56 CFM563C 13802 EU WINDSHIELD BROKEN W O OTHER B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 AU S (AUS) WINDOW R2 POWER CABLE BROKEN. 2 L 7 2 4F 4 F RT A16WE E21EU 2001011106233 20010111 06233 NM 2001 1 11 AU000552 1 20000706 G 2450 CIRCUIT BREAKER BOEING 737 737376 NM CFMINT CFM56 CFM563C 13802 EU AC POWER DIST DIRTY W O OTHER B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 AU S (AUS) P6-3 CIRCUIT BREAKER PANEL FOD. INSPECTION FOUND TWO SPRING WASHERS ADHERING TO A LABEL BETWEEN TWO CIRCUIT BREAKE RS CAUSINGTHE CIRCUIT BREAKERS TO POP. 2 L 7 2 4F 4 F RT A16WE E21EU 2001011106234 20010111 06234 NM 2001 1 11 AU000553 1 20000705 G 5753 6SB1754011 FITTING BOEING 747 747338 NM TE FLAP BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) TRAILING EDGE FOREFLAP ATTACHMENT FITTING LOCATED AT NR 5 SEQUENCE CARRIAGE BROKEN THROUGH THE LOWER BEARING LUG A LLOWING FOREFLAP TO SEPARATE FROM THE SEQUENCE CARRIAGE. DAMAGE TO FOREFLAP TRACKS, MIDFLAP OUTBOARD UPPER LEADING EDGE FIBREGLASS PANEL, INBOARD UPPER TRAILING EDGE PANEL STAY ROD AND UPPER AND LOWER ATTACHMENT POINTS OF THAT STAY ROD. 2 L 7 2 4F RT A20WE 2001011106235 20010111 06235 NM 2001 1 11 AU000554 1 20000703 G 3242 26056623316B PAD BOEING 747 747338 NM BRAKE LOOSE W O OTHER O OTHER LD LANDING 1 AU S (AUS) NR 9 MAINWHEEL BRAKE PAD ADRIFT AND JAMMING ROTORS CAUSING THE BRAKE TO SEIZE. NR 9 MAINWHEEL TYRE BLOWN. 2 L 7 2 4F RT A20WE 2000081700079 20000817 00079 SW 2000 8 17 AU000555 1 20000229 G 3230 AN415 BOLT GULSTM 112 114 7630314 SW LYC O540 IO540T4B5 41532 EA HARTZL HCC2Y HCC2YR1 GL LANDING GEAR RET SEPARATED W K NONE O OTHER TO TAKEOFF 1 AU S (AUS) NOSE LANDING GEAR RETRACTION RAM TO NOSE LANDING GEAR STRUT SEPARATED DUE TO BOLT, NUT, WASHER AND SPLIT PIN SECUR ING THE TWO ITEMS COMING LOOSE. 1 L 7 1 3O 3 O A12SO 1E4 5 C P920 2001011106244 20010111 06244 SO 2001 1 11 AU000556 1 20000713 G 5343 4A112222 BRACKET EMB 110 EMB110P1 3260122 SO PWA PT6 PT6A34 52043 EA HARTZL HCB3T HCB3TN3 GL NLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NOSE LANDING GEAR ACTUATOR SUPPORT BRACKET CRACKED. CRACK LENGTH28.5MM (1.125IN). FOUND DURING INSPECTION IAW SB 1 10-53-0027. CRACK COULD BE SEEN VISUALLY. 1 L 7 2 4T 4 T A21SO E4EA 6 C P15EA 2000081700080 20000817 00080 EA 2000 8 17 AU000557 1 20000707 G 5720 C6WM140031 STRUT DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A20 52043 EA HARTZL HCB3T HCB3TN3 GL WING MISC CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LEFT WING STRUT CORRODED IN AN AREA LOCATED APPROXIMATELY 355.6 MM (14 INCHES) OUTBOARD FROM THE LOWER ATTACHMENT FITTING ON THE AFT WEB. FOUND DURING INSPECTION IAW AD/DHC6/58 AND SB 6-474. (X) 1 H 7 2 3T 3 T RT A9EA E4EA 6 C P15EA 2001011106246 20010111 06246 WP 2001 1 11 AU000558 2 20000701 G 7250 P90018 SHAFT STBROS SC7 SC7SERIES3 8100512 EU GARRTT TPE331 TPE3312201A WP HARTZL HCB3T HCB3TN5 GL TURBINE FAILED W E ENGINE SHUTDOWN E J VIBRATION/BUFFET WARNING INDICATION DE DESCENT 1 AU S P90018 (AUS) RT ENGINE TURBINE SHAFT FAILED. SECOND STAGE AND THIRD STAGETURBINE WHEELS, REAR BEARING SUPPORT AND SCAVENGE PUMP MISSING. 1 H 7 2 3T 4 T NT A15EU E3WE 6 C P15EA 2000082100016 20000821 00016 EU 2000 8 21 AU000559 1 20000704 G 7120 MOUNT PWA REIMS 406 F406 EU PWA PT6 PT6A112 52043 NE MCAULY 3G34C7 3GFR34C701 GL ENGINE MOUNT SEC CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LEFT ENGINE MOUNT CRACKED. FOUND DURING MAGNETIC PARTICLE INSPECTION. 1 L 7 2 3T 3 T RT A54EU E4EA 5 C P60GL 2001011106247 20010111 06247 EA 2001 1 11 AU000560 1 20000505 G 2720 CF3985A PIN DHAV DHC3 DHC3 2800202 EA RUDDER CONTROL S BROKEN W D RETURN TO BLOCK F FLT CONT AFFECTED TX TAXI/GRND HDL 1 AU S (AUS) RUDDER CONTROL SYSTEM PIVOT PIN CRACKED AT WELD AND THEN BROKEOFF. 1 H 7 1 3R A815 2000082100022 20000821 00022 CE 2000 8 21 AU000561 1 20000607 G 2750 C3B18 WIRE CESSNA 414 414A 2075907 CE CONT O520 TSIO520N 17040 SO MCAULY 3AF32C 3AF32C505 GL TE FLAP CONTROL BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) TRAILING EDGE FLAP POWER WIRE BROKEN IN AREA APPROXIMATELY 100 MM( 4 INCHES) FROM THE FLAP PRESELECT SWITCHES. WI RE IS ONE IN A BUNDLE OF FIVE WIRES WHICH FLEXES WHEN THE FLAPS MOVE. (X) 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2000082100023 20000821 00023 SO 2000 8 21 AU000562 2 20000617 G 8520 CRANKSHAFT CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO MCAULY D3A34 D3A34C404 GL ENGINE FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S 814840R (AUS) CRANKSHAFT DEFECTIVE. FOUND DURING INSPECTION AND CORE SAMPLING IAW AD/CON/80. 1 H 7 1 3O 3 O A4CE E5CE 5 C P47GL 2000082100024 20000821 00024 EA 2000 8 21 AU000563 1 20000703 G 2612 1734362 FIRE DETECTOR DHAV DHC6 DHC6200 EA PWA PT6 PT6A20 52043 EA HARTZL HCB3T HCB3TN3 GL FIRE DETECTION FAULTY W K NONE B N SMOKE/FUMES/ODORS/SPARKS FALSE WARNING CL CLIMB 1 AU S 8552 (AUS) RIGHT ENGINE GEARBOX FIRE DETECTOR FAULTY. LOW RESISTANCE. 1 H 7 2 3T 3 T A9EA E4EA 6 C P15EA 2000082100025 20000821 00025 EA 2000 8 21 AU000564 1 20000515 G 5413 C6W151248 LONGERON DHAV DHC6 DHC6300 2802606 EA LONGERON/STR CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE NACELLE RIGHT OUTBOARD LONGERON CRACKED IN AN AREA APPROXIMATELY 254 MM (10 INCHES) AFT OF THE ENGINE MOUNT FITTING. CRACK LENGTH APPROXIMATELY 57.15 MM (2.25 INCHES). FOUND DURING INSPECTION IAW AD/DHC6/51.4 (DHC6 SB 6/509). 1 H 7 2 3T RT A9EA 2000080700172 20000807 00172 SW 2000 8 7 AU000565 1 20000701 G 6230 206010451005 RING BELL BELL 206 206L3 1182108 SW MAIN ROTOR MAST CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S RE103 (AUS) MAIN ROTOR SWASHPLATE INNER RING CRACKED ON RIGHT INPUT ARM LOCATED APPROXIMATELY 5 MM (0.2 INCH) BEHIND THE SPHER ICAL BEARING. (X) 1 G 7 1 3U H2SW 2000082100026 20000821 00026 EA 2000 8 21 AU000566 1 20000607 G 3250 7116111 COLLAR HEROUX 713005 DHAV DHC6 DHC6300 2802606 EA LANDING GEAR STE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S H174 (AUS) NOSE LANDING GEAR STEERING COLLAR CRACKED IN ATTACHMENT BLOCK RADIUS. FOUND USING VISUAL INSPECTION AND CONFIRMED USING ULTRASONIC INSPECTION. 1 H 7 2 3T RT A9EA 2000091300010 20000913 00010 CE 2000 9 13 AU000567 1 20000612 G 5740 0411129 FITTING CESSNA 182 182 2072702 CE WING ATTACH FIT CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LEFT ABD RIGHT WING ATTACHMENT BLOCKS CONTAIN EXFOLIATION CORROSION. 1 H 7 1 3O NT 3A13 2000091400037 20000914 00037 EA 2000 9 14 AU000568 2 20000709 G 8500 ENGINE LYC CESSNA 172 172R 2072401 CE LYC IO360 IO360L2A EA ENGIN FAILED W K NONE E Y VIBRATION/BUFFET ENGINE STOPPAGE TO TAKEOFF 1 AU S L2716851A (AUS) ENGINE FAILED ON TAKEOFF RESULTING IN A FORCED LANDING. AIRCRAFT DAMAGED. GROUND RUNS ON ENGINE COULD NOT REPLICAT E FAULT AND ENGINE RAN OK. 1 H 7 1 3O 3 O NT 3A12 1E10 2001011106248 20010111 06248 NM 2001 1 11 AU000569 1 20000713 G 2910 82950010247 PIPE DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE HYD SYSTEM LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S (AUS) HYDRAULIC PIPE CONTAINED A SMALL PIN HOLE LEAK ON THE INSIDE OF THE BEND RADIUS. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2000080700173 20000807 00173 NE 2000 8 7 AU000570 2 20000708 G 7323 430121204 GOVERNOR LYC 430121204 BOLKMS 117 BK117B2 5626013 EU LYC LTS101 LTS101750B1 41560 NE TURBINE GOVERNOR FAILED W O OTHER E VIBRATION/BUFFET CL CLIMB 1 AU S 37422 LE48171 (AUS) RIGHT ENGINE POWER TURBINE GOVERNOR INTERNAL FAILURE. GOVERNOR DRIVE SPLINE SHEARED WITH CORRESPONDING ENGINE OVE RSPEED. (X) 1 G 7 2 3U 3 U NC H13EU E5NE10 2001011106250 20010111 06250 EU 2001 1 11 AU000571 1 20000714 G 7603 POWER LEVER SAAB SF340 340B 7860101 EU GE CT7TP CT79B 30030 NE ROTOL R390 R3904123F27 NE LEFT OUT OF ADJ W C ABORTED TAKEOFF E VIBRATION/BUFFET TO TAKEOFF 1 AU S (AUS) LH POWER LEVER OUT OF ADJUSTMENT AND LAGGING BEHIND THE RH POWERLEVER. 2 L 7 2 4T 4 T RT A52EU E8NE 6 C P31NE 2000080700174 20000807 00174 GL 2000 8 7 AU000572 2 20000708 G 7320 68711461 PIPE ALLSN BELL 206 206B3 1181506 SW ALLSN 250C 250C20B 03013 GL FUEL CONTROLLING LOOSE W K NONE E VIBRATION/BUFFET TO TAKEOFF 1 AU S CAE832194 (AUS) PR FUEL PIPE BETWEEN THE FUEL CONTROL UNIT AND THE POWER TURBINEGOVERNOR HAD A LOOSE B'''' NUT. (X) 1 G 7 1 3U 3 U H2SW E4CE 2001011106253 20010111 06253 SO 2001 1 11 AU000573 1 20000720 G 2731 WHEEL EMB 120 EMB120 3260201 SO PWA 118 PW118A NE HAMSTD 14RF 14RF9 NE ELEVATOR TAB OUT OF ADJ W A UNSCHED LANDING F FLT CONT AFFECTED CR CRUISE 1 AU S (AUS) RT TRIM WHEEL OUT OF ADJUSTMENT. SUSPECT INCORRECT FITMENT. 2 L 7 2 4T 4 T RT A31SO E20NE 6 C P11NE 2001011106254 20010111 06254 NE 2001 1 11 AU000574 2 20000718 G 7260 AS3209241 O-RING DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE ENGINE CUT W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 AU S 50 120427 (AUS) RH ENGINE GENERATOR MOUNT O' RING SEAL CUT AND LEAKING. AC GENERATOR CONTAMINATED BY OIL. SUSPECT O' RING SEAL DAM AGEDDURING INSTALLATION. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001011106269 20010111 06269 EU 2001 1 11 AU000575 1 20000719 G 5610 1379628C402 WINDSHIELD BAG JETSTM JETSTM3201 1500217 EU ROTOL R333 R333482F12 GL COCKPIT CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT WINDSHIELD CRACKED AND DELAMINATING. 2 L 7 2 4T RT A56EU 6 C P61GL 2001011106270 20010111 06270 NE 2001 1 11 AU000576 2 20000719 G 7210 PCE115319 GEARBOX EMB 120 EMB120 3260201 SO PWA 118 PW118A NE ENGINE MAKING METAL W K NONE O OTHER IN INSP/MAINT 1 AU S PCE115319 (AUS) RT ENGINE REDUCTION GEARBOX CHIP DETECTOR AND SCAVENGE FILTER CONTAMINATED WITH METAL. 2 L 7 2 4T 4 T RT A31SO E20NE 2000091400038 20000914 00038 CE 2000 9 14 AU000577 1 20000119 G 5540 12138871 SUPPORT BRACKET CESSNA 207 CESSNA 207 T207A 2073614 CE CONT O520 TSIO520G 17040 SO MCAULY D3A34 D3A34C404 GL FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 00340 570008 920058 (AUS) RUDDER BAR SUPPORT ASSEMBLIES PN 1213887-1 (LEFT) AND PNO1213887-2 (RIGHT) CRACKED THROUGH BOLT HOLES. 1 H 7 1 3O 3 O A16CE E8CE 5 C P47GL 2001011106271 20010111 06271 EU 2001 1 11 AU000578 1 20000630 G 2131 CONTROLLER AIRBUS 320 A320211 3930320 EU CFMINT CFM56 CFM565A1 NE CABIN PRESSURE BLOCKED W O OTHER O OTHER CL CLIMB 1 AU S (AUS) NO2 CABIN PRESSURE CONTROLLER PC PORT HAD A BLANKING CAP FITTED PREVENTING THE CONTROLLER FROM SENSING CORRECT CAB IN PRESSURE.THE BLANKING CAP PNO CD-3 HAD BEEN FITTED TO THE PORT DURINGTROUBLESHOOTING AND HAD NOT BEEN REMOVED. PERSON NEL/MAINTENANCE ERROR. 2 L 7 2 4F 4 F RT A28NM E29NE 2001011106272 20010111 06272 NM 2001 1 11 AU000579 1 20000707 G 3251 3821128101 PIN PARKER 3790037106 BOEING 767 767277 NM GE CF6 CF680A 30025 NE STEERING UNIT SHEARED W D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 AU S 00025ANSSN32 (AUS) NOSE LANDING GEAR STEERING SYSTEM RT METERING VALVE INDEXING PINSHEARED. WORKSHOP FOUND EVIDENCE OF HEAVY CORROSIO N AROUND THEPIN LOCATION HOLE. 2 L 7 2 4F 4 F RT A1NM E13NE 2000091400039 20000914 00039 SO 2000 9 14 AU000580 2 20000721 G 8520 606507 CRANKCASE CONT CESSNA 404 404CESSNA 2075901 CE CONT O520 GTSIO520M 17032 SO MCAULY 3FF32 3FF32C501 GL ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 925 606507 (AUS) ENGINE CRANKCASE CRACKED ADJACENT TO UPPER SPLIT LINE. FURTHER INVESTIGATION FOUND THE CAMSHAFT FORWARD JOURNAL CR ACKED THROUGH THE OIL FEED HOLE TO THE JOURNAL APPEARED BLOCKED. SUBMITTER SUSPECTED HOLE HAD BEEN WELDED CLOSED. 1 L 7 2 3O 3 O A25CE E7CE 5 C P45GL 2000091400040 20000914 00040 EA 2000 9 14 AU000582 2 20000720 G 8550 LW13388 GASKET LYC PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL ENGINE FRACTURED W K NONE E K VIBRATION/BUFFET FLUID LOSS CL CLIMB 1 AU S 924 6540761A DJ11605A (AUS) ENGINE OIL FILTER ADAPTER GASKET LEAKING. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001011106273 20010111 06273 CE 2001 1 11 AU000583 1 20000613 G 2750 FLAP BEECH 1900 1900D 1154162 CE TRAILING EDGE OUT OF ADJ W C ABORTED TAKEOFF F FLT CONT AFFECTED TO TAKEOFF 1 AU S (AUS) FLAPS OUT OF ADJUSTMENT. 2 L 7 2 4T RT A24CE 2001011106274 20010111 06274 NE 2001 1 11 AU000584 3 20000719 G 6110 HJ376 FORK BEECH 1900 1900D 1154162 CE HARTZL HCE4A HCE4A3A NE PITCH CHANGE OUT OF RIG W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S HJ376 (AUS) RT PROPELLER REVERSE STOP INCORRECTLY SET. PITCH CHANGE FORK CRACKED. 2 L 7 2 4T RT A24CE 5 C P10NE 2001011106275 20010111 06275 NM 2001 1 11 AU000585 1 20000616 G 2730 85520271003 STOP DHAV DHC8 DHC8102 2809003 NM ELEVATOR DETERIORATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RH ELEVATOR STOP MISSING DUE TO DETERIORATION OF THE RUBBER.ELEVATOR TRAILING EDGE DAMAGED. AREA OF DAMAGE 100MM B Y 100MM (4IN BY 4IN). 2 H 7 2 4T RT A13NM 2001011106278 20010111 06278 EU 2001 1 11 AU000586 1 20000614 G 2160 342D0200000 THERMOSTAT AIRBUS 320 A320211 3930320 EU ENVIRONMENT FAILED W A UNSCHED LANDING O OTHER CL CLIMB 1 AU S 27930 381 (AUS) DURING CLIMB THE NR 2 BLEED OVERHEATED. SUSEQUENTLY, THE NO1 BLEED ALSO OVERHEATED, CABIN COULD NOT BE PRESSURISE D. STRIP REPORT HIGH LIGHTED THAT THE NR 1 FAN AIR VALVE AND THE NR 2 TEMPERATURE CONTROL THERMOSTAT WERE BOTH FAULTY. 2 L 7 2 4F RT A28NM 2000091400041 20000914 00041 CE 2000 9 14 AU000587 1 20000707 G 7810 BOLT CONT CESSNA 340 340CESSNA 2076404 CE CONT O520 TSIO520K 17040 SO ENGINE COLLECTOR BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S 245704R (AUS) ENGINE EXHAUST BOLTS BROKEN, ALLOWING EXHAUST GASSES TO INITIATE BURNING A HOLE IN THE AIRFRAME. 1 L 7 2 3O 3 O 3A25 E8CE 2000091400042 20000914 00042 SO 2000 9 14 AU000588 2 20000611 G 8500 ENGINE CONT CESSNA 172 172 2072402 CE CONT O300 O300A 17022 SO ENGINE MAKING METAL W K NONE K FLUID LOSS TO TAKEOFF 1 AU S 14296 (AUS) DURING CRUISE, A DROP IN INDICATED OIL PRESSURE AND A RISE IN OIL TEMPERATURE WAS OBSERVED. A POST INSPECTION FOU ND THE OIL FILTER CLOGGED WITH ALUMINIUM AND WHITE BEARING METAL CONTAMINATION. 1 H 7 1 3O 3 O NT 3A12 E253 2000112800059 20001128 00059 NE 2000 11 28 AU000589 2 20000713 G 7230 COMPRESSOR PWA PWA JT9 JT9D7R4E 52054 NE ENGINE CONTAMINATED W K NONE O OTHER IN INSP/MAINT 1 AU S 716931 (AUS) HP COMPRESSOR DISCS (STG 8, 10, 12 AND 14) FOUND WITH SILVER PLATE CONTAMINATION, CAUSED BY USE OF SILVER PLATED N UTS FITTED AT TIE ROD LOCATIONS. 4 F E3NE 2000112800060 20001128 00060 NE 2000 11 28 AU000590 2 20000713 G 7230 716913 COMPRESSOR PWA PWA JT9 JT9D7R4E 52054 NE TURBINE CONTAMINATED W K NONE O OTHER IN INSP/MAINT 1 AU S 716913 (AUS) HP COMPRESSOR DISCS (STG. 8, 10, 12 AND 14) FOUND WITH SILVER PLATE CONTAMINATION CAUSED BY USE OF SILVER PLATED N UTS FITTED AT TIE ROD LOCATIONS. 4 F E3NE 2001011106280 20010111 06280 NM 2001 1 11 AU000591 1 20000712 G 3250 3790037U PIN BOEING 767 767338 1385151 NM GE CF6 CF680C2* GL NLG STEERING SHEARED W D RETURN TO BLOCK J WARNING INDICATION TX TAXI/GRND HDL 1 AU S SY (AUS) DURING AIRCRAFT TAXI (TURNING) INTO BAY, THE NOSE WHEEL STEERINGWENT TO FULL LOCK UNCOMMANDED.INVESTIGATION FOUND THAT THE LOCATOR PIN FOR THE RT STEERING ACTUATOR ON THE RT SWIVEL VALVE HAD SHEARED. 2 L 7 2 4F 4 F RT A1NM E23EA 2001011106300 20010111 06300 NM 2001 1 11 AU000592 1 20000704 G 2821 FILTER DHAV DHC8 DHC8202 2809007 NM FUEL SYSTEM CONTAMINATED W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 AU S (AUS) AT CRUISE THE NR 1 FUEL BYPASS LIGHT ILLUMINATED. DURING POST INVESTIGATION BOTH HP/LP FUEL FILTERS WERE INSPECTED AND REPLACED - FILTERS INDICATED SOME SLIGHT SIGNS OF FUNGUS. DURING NEXTFLIGHT THE SAME PROBLEM RE-OCCURRED. BOTH FILT ERS WERE CHANGE DONCE AGAIN - AIRCRAFT SERVICEABLE. 2 H 7 2 4T RT A13NM 2000081700081 20000817 00081 SO 2000 8 17 AU000594 1 20000717 G 2823 12444LH12424 SEAL SCOTT 236405 PIPER PA34 PA34200T 7103406 SO FUEL SELECTOR MELTED W K NONE O OTHER IN INSP/MAINT 1 AU S 12444LH12424 (AUS) DURING SCHEDULED MAINTENANCE, THE FUEL COULD NOT BE TURNED OFF FULLY AND FUEL WAS CROSS-FEEDING. THE SELECTOR VAL VES WERE REMOVED AND FOUND THAT THE SEALS HAD DISSOLVED. SUBMITTER SUSPECTED INCORRECT SEALS OR INCORRECT SOLVENT USED IN COMPLYING WITH AD/GEN/81. 1 L 7 2 3O A7SO 2001011100345 20010111 00345 EU 2001 1 11 AU000595 1 20000721 G 3297 S320020APG WIRE BAC 146 146200A 1500266 EU MLG FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FIRST POWER UP, AIRCRAFT WAS INDICATING WEIGHT ON WHEELS SENSORS IN THE 'AIR' MODE.INVESTIGATION FOUND THE LHS INB OARD WEIGHT ON WHEELS PROXIMITY SENSOR AND HARNESS FAULTY. BOTH WERE REPLACED,HOWEVER, THE AIRCRAFT WAS STILL IN 'AIR' MODE. FURTHER INVESTIGATION FOUND THE BLUE WIRE OF GA033 (TRIPLE SHIELD) HAD LEAKAGE TO THE SHIELD CAUSING PROXIMITY SE NSOR GA40 PCB NOT TO OPERATE. 2 H 7 4 4F A49EU 2001011106301 20010111 06301 NM 2001 1 11 AU000596 1 20000227 G 7830 000518ANSSN30 NUT BOEING 737 737377 NM GE CFM56 CFM563B1 13802 NE THRUST REVERSER UNDERTORQUED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) DURING PREFLIGHT INSPECTION, THE NR 4 BLOCKER DOOR WAS FOUND NOT FULLY STOWED ON THE NR 1 ENGINE I/B REVERSER COWL . INVESTIGATION THEN FOUND THE BLOCKER DOORS LOWER HINGE BOLT WAS MISSING ANDTHE UPPER BOLT WAS LOOSE. FURTHER INVESTIG ATION FOUNDTHE NR 2 AND NR 3 BLOCKER DOORS HAD LOOSE NUTS ON THE LOWER HINGE BOLTS AND MISSING NUTS AND WASHERS ON THE UPPER HINGE BOLTS. SUSPECT THE FASTENERS WERE IMPROPERLY TORQUED AT LAST BLOCKER DOOR REPLACEMENT. MAINTENANCE/PERSONNE L ERROR. 2 L 7 2 4F 4 F RT A16WE E2GL 2001011106302 20010111 06302 NM 2001 1 11 AU000597 1 20000401 G 5310 STRUCTURE BOEING 737 737377 NM FUSELAGE CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LEVEL 2 CORROSION FOUND IN THE FUSELAGE STRUCTURE AS A RESULT OFAD/B737/52 AMDT 2. 2 L 7 2 4F RT A16WE 2001011106303 20010111 06303 NM 2001 1 11 AU000598 1 20000401 G 5310 STRUCTURE BOEING 737 737377 NM FUSELAGE CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LEVEL 2 CORROSION FOUND IN FUSELAGE STRUCTURE AS A RESULT OFAD/B737/52 AMDT 2. 2 L 7 2 4F RT A16WE 2001011106304 20010111 06304 2001 1 11 AU000599 4 20000616 G 2565 7A146721 SLIDE BOEING 747 747438 NM PAX DOOR MALFUNCTIONED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) DURING TEST, NR 1 LT SLIDE RAFT MOORING LINE TANGLED WITH THE ASPIRATOR. INVESTIGATION FOUND THAT THE SLIDE MOORIN G LINE WAS NOT ATTACHED TO THE GIRT BAR. PERSONNEL/MAINTENANCE ERROR. 2 L 7 4 4F RT A20WE 2001011106305 20010111 06305 2001 1 11 AU000600 4 20000715 G 2565 101630201 SLIDE BOEING 767 767338 1385151 NM GE CF6 CF680C2* GL PAX DOOR WRONG PART W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ON REMOVAL OF THE LT 'OFF' WING SLIDE, IT WAS DISCOVERED THAT THE SLIDE TYPE SHOULD NOT HAVE BEEN FITTED TO A -300 SERIES AIRCRAFT- A SINGLE LANE SLIDE WAS FITTED IN LIEU OF A DUAL LANE SLIDE. PERSONNEL/MAINTENANCE ERROR. 2 L 7 2 4F 4 F RT A1NM E23EA 2000081700082 20000817 00082 EA 2000 8 17 AU000601 1 20000313 G 5210 B6MA50 DOOR DHAV DHC6 DHC6300 2802606 EA PASSENGER/CREW D MALFUNCTIONED W K NONE O OTHER CR CRUISE 1 AU S B070 (AUS) DURING FLIGHT, THE CABIN AIRSTAIR DOOR OPENED. SUBMITER SUSPECTED REAR SEAT PASSENGER MAY HAVE ACCIDENTLY BUMPED THE DOOR HANDLE WITH KNEE. 1 H 7 2 3T RT A9EA 2000081700083 20000817 00083 EA 2000 8 17 AU000602 1 20000606 G 5413 C6W151248 LONGERON DHAV DHC6 DHC6300 2802606 EA LONGERON/STR CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) A CRACK APPROXIMATELY 44.5 MM (1.75 INCHES) WAS FOUND IN THE RT OUTBOARD ENGINE NACELLE LONGERON, APPROXIMATELY 24 CM (9.5 INCHES) AFT OF THE ENGINE MOUNT FITTING. THE CRACK ORIGINATED FROM BENEATH STRAP P/N C6WM1712-27 WHICH WAS FIT TED IAW DHC MOD 6/1655. 1 H 7 2 3T RT A9EA 2000080700175 20000807 00175 EU 2000 8 7 AU000603 1 20000520 G 6410 355A12003108 BLADE SNIAS 350 AS350BA 8680817 EU TAIL ROTOR BLADE DELAMINATED W K NONE O OTHER IN INSP/MAINT 1 AU S 382 2386 (AUS) AFTER APPROXIMATELY A ONE HOUR FLIGHT IN HEAVY RAIN, THE PILOT DISCOVERED THE DELAMINATION ON ONE TAIL BLADE HAD P ROPAGATED TO APPROXIMATELY 3.5CM (1.37 INCH). PROBLEM WAS INITIALLY FOUND ABOUT 18 HOURS EARLIER, HOWEVER, THE DELAMIN ATION WAS WITHIN LIMITS AND REPAIRED (SEALED) IAW MRR. 1 G 7 1 3U NC H9EU 2000081700084 20000817 00084 CE 2000 8 17 AU000604 1 20000226 G 3230 LANDING GEAR CESSNA 402 402B 207590P CE CONT O520 TSIO520B 17040 SO MLG COLLAPSED W K NONE O OTHER LD LANDING 1 AU S MCCOWEN3AF32 (AUS) PILOT REPORTED THAT THE LANDING GEAR RETRACTED BY ITSELF. POST-RETRACTION/EXTENSION TESTS CARRIED OUT WITHOUT INC IDENT. AS A PRECAUTION, THE LG MOTOR WAS REPLACED. SWITCHES, SETTINGS AND LIGHTS WERE CHECKED - NO DEFECTS FOUND. 1 L 7 2 3O 3 O A7CE E8CE 2000081700085 20000817 00085 GL 2000 8 17 AU000605 3 20000306 G 6111 90DFA10 BLADE CESSNA 206 TU206* CE CONT O520 TSIO520M 17040 SO MCAULY D3A34 D3A34C402 GL PROPELLER BLADE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 1330 861329 (AUS) PROPELLER WOULD NOT RETURN TO FINE PITCH FROM COURSE PITCH AT ENGINE SPEEDS BELOW 2200 RPM AND WOULD REMAIN IN COU RSE PITCH AFTER FINE PITCH SELECTED.DURING PROPELLER DISASSEMBLY, THE NR 3 BLADE WAS FOUND CRACKED AT THE BLADE ROOT ARO UND APPROXIMATELY HALF THE BLADE''S CIRCUMFERENCE. 1 H 7 1 3O 3 O A4CE E8CE 5 C P47GL 2000081700086 20000817 00086 SO 2000 8 17 AU000606 1 20000719 G 5553 NUT PIPER PA32 PA32RT300 7103215 SO VERT STAB ATTACH SPLIT W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ANCHOR NUT FOR RIGHT FORWARD FIN ATTACH BOLT SPLIT. 1 L 7 1 3O A3SO 2000081700087 20000817 00087 GL 2000 8 17 AU000607 1 20000706 G 5720 SPAR AMTR F11 JODELD11 GL WING FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) PORT WING SPAR FAILED IN COMPRESSION AT DIHEDRAL ''CRANK''. REAR UPPER SPAR BOOM FAILED IN BOX SPAR AT TWO POINTS : VERTICAL PLY FACE OF BOX SPAR FAILED AT OUTER FAILURE, AND UPPER PLY FACE FAILED AT NEXT INBOARD RIB. 1 L 7 1 3O EXPA1L71 2001011106307 20010111 06307 EU 2001 1 11 AU000608 1 20000720 G 2730 602EN166B SWITCH FOKKER F28 F28MK4000 4990810 EU ELEVATOR FAULTY W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 AU S (AUS) ON APPLICATION OF TAKE-OFF POWER, THE WARNING HORN SOUNDED AND TAKE-OFF WAS ABORTED. POST INVESTIGATION FOUND THE NR 2 ELEVATOR BYPASS MICROSWITCH WAS OPEN CIRCUIT. 2 L 7 2 4F RT A20EU 2000081700088 20000817 00088 EA 2000 8 17 AU000609 2 20000720 G 8530 BARREL PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL CYL GLAZED W K NONE R PARTIAL RPM/PWR LOSS TO TAKEOFF 1 AU S 202 L280461A DJ10751A (AUS) PILOT REPORTED VIBRATION DURING ROTATION AND CLIMB. GROUND INVESTIGATION FOUND EXCESSIVE OIL IN THE LEFT ENGINE'' S NR 3 CYLINDER. CYLINDER WAS REMOVED AND FOUND WITH SEVERE GLAZING OF THE BORE. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001011106308 20010111 06308 NM 2001 1 11 AU000610 1 20000723 G 5330 SKIN DHAV DHC8 DHC8102 2809003 NM FUSELAGE DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) WIND BLEW CATERING CART INTO AIRCRAFT FUSELAGE, PUNCTURING A HOLE APPROXIMATELY 2CMS IN SIZE. 2 H 7 2 4T RT A13NM 2001011106310 20010111 06310 SW 2001 1 11 AU000611 1 20000710 G 2913 PUMP SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE33111U 01514 WP HYD SYSTEM FAILED W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 AU S P44125C (AUS) PILOT REPORTED LOW HYDRAULIC PRESSURE. INVESTIGATION FOUND THE RT HYDRAULIC PUMP WAS DAMAGED. ON NEXT FLIGHT THE P ILOT REPORTED THAT THE HYDRAULIC PRESSURE HAD INCREASED TO THE 'RED LINE'. THE POWER PACK WAS THEN REMOVED AS A RESULT O F THECONTAMINATION FROM THE FAILED HYDRAULIC PUMP. 2 L 7 2 4T 4 T RT A8SW E4WE 2000112800061 20001128 00061 EU 2000 11 28 AU000612 1 20000720 G 5552 NB310077 BRACKET BNORM BN2 BN2A21 1520221 EU ELEV/TAB ATTACH CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ELEVATOR BRACKET CRACKED ALONG THE BEND RADII OF ONE SIDE. 1 H 7 2 3O A17EU 2001011106330 20010111 06330 NM 2001 1 11 AU000613 1 20000711 G 3246 300653 HUB BFGOODRICH 31448 DHAV DHC8 DHC8102 2809003 NM WHEEL FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S 1933 (AUS) DURING A NOSE WHEEL TIRE CHANGE, FLAWS WERE OBSERVED UP TO A DEPTH OF 1.02MM (0.040IN) IN THE OUTER HUB FLANGE RAD IUS OVER A 17.78CM (7IN) SPAN 2 H 7 2 4T RT A13NM 2001011106331 20010111 06331 EU 2001 1 11 AU000614 1 20000719 G 3020 SM15CXD4 RELAY SAAB SF340 SF340A 7850100 EU INTAKE ANTI ICE BURNED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 AU S (AUS) AFTER TAKE-OFF WHEN ANTI-ICE WAS SELECTED 'ON', THE RH ENGINE INTAKE CAUTION LIGHT ILLUMINATED. GROUND INVESTIGAT ION FOUND THE RELAY WHICH CONTROLS AC POWER TO THE ELECTRICALLY HEATED ENGINE INTAKE DUCT IN A BURNT CONDITION. IN ADDI TION, THE CONTACTS ANDWIRING AT THE RELAY CONNECTOR WERE BURNT AND HAD TO BEREPLACED/REPAIRED. 2 L 7 2 4T RT A52EU 2000100300136 20001003 00136 EA 2000 10 3 AU000615 1 20000901 G 7722 TERMINAL PWA DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A20 52043 EA ENG EGT/TIT IND FAULTY W K NONE O OTHER CR CRUISE 1 AU S (AUS) DURING CRUISE, THE ENGINE T5 INDICATOR FLUCTUATED BETWEEN 500 DEGREES CELSIUS AND 630 DEGREES CELSIUS. INVESTIGAT ION FOUND A DEFECTIVE WIRING JOINT AT THE ENGINE TERMINAL. (X) 1 H 7 2 3T 3 T RT A9EA E4EA 2000100300137 20001003 00137 EA 2000 10 3 AU000616 1 20000901 G 5330 SKIN DHAV DHC6 DHC6300 2802606 EA FUSELAGE MAIN PL WRINKLED W K NONE E C VIBRATION/BUFFET F.O.D. LD LANDING 1 AU S (AUS) NOSE LANDING GEAR IMPACTED TWO EARTH MOUNDS ON LANDING. GROUND INVESTIGATION FOUND SKIN RIPPLES AND LOOSE RIVETS IN THE LOWER FUSELAGE AREA AT STN 60. TWO LOWER STRINGER ANGLES WERE ALSO FOUND TO BE CRACKED. (X) 1 H 7 2 3T RT A9EA 2000100300138 20001003 00138 EA 2000 10 3 AU000617 1 20000901 G 5610 C6SC10624 WINDSHIELD DHAV DHC6 DHC6300 2802606 EA FLIGHT COMPART CRACKED W K NONE C F.O.D. TX TAXI/GRND HDL 1 AU S (AUS) AIRCRAFT WAS PARKED (AWAITING DEPARTURE) BEHIND ANOTHER AIRCRAFT WHEN THE PILOT OF THE LEAD AIRCRAFT PERFORMED AN ENGINE POWER CHECK. STONES WERE THROWN UP AND CRACKED THE RIGHT WINDSHIELD. (X) 1 H 7 2 3T RT A9EA 2000092800094 20000928 00094 WP 2000 9 28 AU000618 1 20000901 G 2435 230322210 END BELL LEARSIEGLER 23032027 HUGHES 369 369E 4470707 WP STARTER/GEN FAILED W K NONE E VIBRATION/BUFFET NR NOT REPORTED 1 AU S 16326 (AUS) ON START-UP, THE ENGINE WOULD NOT ACCELERATE PAST 13 PERCENT AND TOT WAS APPROACHING A HOT START. ON THE SECOND A TTEMPT TO START, A GRUMBLING NOISE WAS HEARD COMING FROM THE ENGINE AREA. INVESTIGATION FOUND THE STARTER/GENERATOR DRI VESHAFT END BELL HAD FAILED. (X) 1 G 7 1 3U H3WE 2001011106332 20010111 06332 SO 2001 1 11 AU000619 1 20000901 G 7312 10718D FUEL HEATER EMB 120 EMB120 3260201 SO PWA 118 PW118A NE HAMSTD 14RF 14RF9 NE ENGINE LEAKING W C ABORTED TAKEOFF K J FLUID LOSS WARNING INDICATION TO TAKEOFF 1 AU S 3296 (AUS) FOLLOWING ABORTED TAKEOFF THE ENGINE OIL WAS FOUND TO BE 1.9 LITRES (TWO QUARTS) BELOW THE LEVEL CHECK ON PRE-FLIG HT INSPECTION. SUSPECT INTERNAL OIL LEAK IN THE FUEL TO OIL HEATER. 2 L 7 2 4T 4 T RT A31SO E20NE 6 C P11NE 2000100300139 20001003 00139 SO 2000 10 3 AU000620 2 20000901 G 8530 646657 CYLINDER CONT IO520F CESSNA 206 U206 2073306 CE CONT O520 IO520F 17032 SO ENGINE SEPARATED W K NONE E F VIBRATION/BUFFET FLT CONT AFFECTED NR NOT REPORTED 1 AU S 496 563758 (AUS) NR 6 CYLINDER HEAD SEPARATED FROM BARREL. (X) 1 H 7 1 3O 3 O A4CE E5CE 2001011106345 20010111 06345 NM 2001 1 11 AU000621 1 20000901 G 3213 TORQUE LINK DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE MLG MISINSTALLED W C ABORTED TAKEOFF N FALSE WARNING TO TAKEOFF 1 AU S (AUS) RT MLG TORQUE LINKS REVERSED AT REINSTALLATION FOLLOWING BUSHING REPLACEMENT. PERSONNEL / MAINTENANCE ERROR. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001011106346 20010111 06346 NM 2001 1 11 AU000622 1 20000901 G 3230 LANDING GEAR DHAV DHC8 DHC8202 2809007 NM NOSE FAILED W C ABORTED TAKEOFF O OTHER TO TAKEOFF 1 AU S (AUS) AFTER TAKEOFF ON THE FIRST FLIGHT OF DAY THE NLG FAILED TO RETRACT AT GEAR UP SELECTION. GROUND CHECKS FOUND THE N OSE GEAR LOCK ENGAGED. PERSONNEL/MAINTENANCE ERROR 2 H 7 2 4T RT A13NM 2001011106348 20010111 06348 SW 2001 1 11 AU000623 1 20000901 G 7603 POWER LEVER FRCHLD SA227 SA227DC 3377521 SW GARRTT TPE331 TPE33112UHR WP MCAULY 4HFR34 4HFR34C652 NE RIGHT DAMAGED W A UNSCHED LANDING F FLT CONT AFFECTED CL CLIMB 1 AU S (AUS) AFTER TAKEOFF ERRATIC ENGINE INDICATIONS WERE OBSERVED ON THE RT ENGINE INSTRUMENTS. ENGINE WAS SHUT DOWN. SUBSEQU ENT INVESTIGATION INCLUDED RIGGING CHECK, SPEED LEVER FRICTION CHECK AND ENGINE GROUND RUNS. FAULT COULD NOT BE DUPLICAT ED. SUSPECT THE SPEED LEVER HAD MOVED AFT FROM THE MAXIMUM RPM POSITION TO THE POINT WHERE THE SRL SYSTEM CRUISE EGT SCH EDULE WAS REACHED. 2 L 7 2 4T 4 T RT A18SW E4WE 6 C 3PNE 2000100300140 20001003 00140 SO 2000 10 3 AU000624 2 20000901 G 8520 STUD CONT PIPER PA34 PA34200T 7103406 SO CONT O360 TSIO360E 17025 SO HARTZL HCC2Y BHCC2YF1 GL ENGINE WRONG PART W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) BOTH PROPELLERS COULD NOT BE FITTED CORRECTLY DURING INSTALLATION TO RECENTLY OVERHAULED ENGINES. SUBSEQUENT INVE STIGATION FOUND THE ATTACHING STUDS WERE TOO LONG (-4 STUDS HAD BEEN FITTED INLIEU OF -3 STUDS). (X) 1 L 7 2 3O 3 O A7SO E9CE 5 C P920 2000100300141 20001003 00141 SO 2000 10 3 AU000625 1 20000901 G 2823 1790001 SELECTOR VALVE PIPER PA46 PA46350P SO LYC O540 TIO540AE2A 41532 EA HARTZL HCC2Y BHCC2YF1 GL FUEL SELECTOR/SH SEIZED W K NONE O OTHER CR CRUISE 1 AU S (AUS) FUEL SELECTOR VALVE SEIZED. INVESTIGATION FOUND WATER CONTAMINATION IN THE VALVE SPOOL CAVITY. SUSPECT WATER FRO ZE AND JAMMED SELECTOR. SUBMITTER STATED FUEL SYSTEM HAD BEEN DECONTAMINATED 28 HOURS EARLIER PER AD/GEN/80 AMDT2. (X ) 1 L 7 1 3O 3 O RT A25SO E14EA 5 C P920 2001011106350 20010111 06350 WP 2001 1 11 AU000626 2 20000901 G 7250 31032794 TURBINE NOZZLE BAG JETSTM JETSTM3201 1500217 EU GARRTT TPE331 TPE33112UA 01514 WP MCAULY 4HFR34 4HFR34C653 NE RT ENGINE SEPARATED W E A ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION NR NOT REPORTED 1 AU S (AUS) RT ENGINE NOZZLE GUIDE VANE SEGMENT SEPARATED. DAMAGE TO FIRST, SECOND AND THIRD STAGE NOZZLE ASSEMBLIES AND TURBI NE WHEELS CAUSED BY FOD. 2 L 7 2 4T 4 T RT A56EU E4WE 6 C 3PNE 2000100300142 20001003 00142 NM 2000 10 3 AU000627 1 20000901 G 5341 22107001 FITTING CHILD S2 S2BPITTS 0110304 NM WING ATTACH FITT CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RIGHT LOWER WING ATTACHMENT FITTING CRACKED PER PITTS SERVICE BULLETIN 25. (X) 1 Q 7 1 3O A8SO 2001011106351 20010111 06351 NM 2001 1 11 AU000628 1 20000901 G 3242 QF56039 STATOR S160T400510 BOEING 767 767338 1385151 NM GE CF6 CF680C2* GL BRAKE DISINTEGRATED W K NONE O OTHER IN INSP/MAINT 1 AU S QF56039 (AUS) NR 2 MAIN WHEEL BRAKE STATOR DISINTEGRATED. 2 L 7 2 4F 4 F RT A1NM E23EA 2001011106352 20010111 06352 NM 2001 1 11 AU000629 1 20000901 G 2720 AV13J5147 VALVE BOEING 737 737376 NM CFMINT CFM56 CFM563C 13802 EU RUDDER CONTROL FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) STANDBY RUDDER SHUTOFF VALVE INOPERATIVE. INVESTIGATION FOUND THE VALVE TO BE QUITE HOT AND THE OVERRIDE LEVER STI FF TO OPERATE. 2 L 7 2 4F 4 F RT A16WE E21EU 2001011106354 20010111 06354 NE 2001 1 11 AU000630 2 20000901 G 7200 ENGINE BAG BAE146 BAE146100A 1500260 EU LYC ALF502 ALF502R5 41580 NE NR 1 VIBRATES W A UNSCHED LANDING E F VIBRATION/BUFFET FLT CONT AFFECTED CR CRUISE 1 AU S (AUS) NO1 ENGINE VIBRATION WITH INDICATION OF 1.5. GROUND CHECKS COULDFIND NO PROBLEMS AND AIRCRAFT RETURNED TO SERVICE. SUSPECT ICING. 2 H 7 4 4F 4 F RT A49EU E6NE 2001011106355 20010111 06355 NE 2001 1 11 AU000631 2 20000901 G 7250 TURBINE NOZZLE BAG BAE146 BAE146100A 1500260 EU LYC ALF502 ALF502R5 41580 NE NR 2 ENGINE FAILED W C ABORTED TAKEOFF X J ENGINE FLAMEOUT WARNING INDICATION TO TAKEOFF 1 AU S (AUS) NR 2 ENGINE FAILED ON TAKEOFF WITH THE TGT EXCEEDING 1000 DEGREESC. SUSPECT CAUSED BY FAILURE OF THE SECOND STAGE HP TURBINE NOZZLE. 2 H 7 4 4F 4 F RT A49EU E6NE 2001011106356 20010111 06356 EU 2001 1 11 AU000632 1 20000901 G 2910 SM601BA40A14 CIRCUIT BREAKER BAC 146 146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE HYD PUMP STUCK W O OTHER O OTHER NR NOT REPORTED 1 AU S (AUS) AC HYDRAULIC PUMP REMOTE CONTROL CIRCUIT BREAKER STUCK IN THE ON' POSITION. 2 H 7 4 4F 4 F A49EU E6NE 2000092800095 20000928 00095 NM 2000 9 28 AU000633 1 20000901 G 6320 A0061 TRANSMISSION ROBSIN A0061 ROBSIN R22 R22BETA NM LYC O320 O320B2C 41508 EA MAIN ROTOR G/B CONTAMINATED W K NONE O OTHER IN INSP/MAINT 1 AU S 659 0766 (AUS) MAIN TRANSMISSION MAKING METAL. CHIP LIGHT DID NOT ILLUMINATE. (X) 1 G 7 1 3O 3 O H10WE E274 2000100300152 20001003 00152 SO 2000 10 3 AU000634 1 20000901 G 2913 ESQ12S BRUSH BLOCK PRESTOLITE 9667102 PIPER PA28 PA28RT201 7102818 SO LYC O360 IO360C1C6 41514 EA MCAULY 2D34C B2D34C213 GL HYDRAULIC PUMP WORN W K NONE O OTHER CR CRUISE 1 AU S (AUS) HYDRAULIC POWER PACK MOTOR BRUSHES WORN. (X) 1 L 7 1 3O 3 O 2A13 1E10 5 C P7EA 2001011106367 20010111 06367 WP 2001 1 11 AU000635 1 20000901 G 5554 BRACKET DOUG DC3 DC3CS1C3G 3021458 WP PWA R1830 R183092 52020 NE HAMSTD 23E 23E50 NE RUDDER CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) UPPER RUDDER HINGE MOUNT BRACKET CRACKED AND CORRODED. 2 L 7 2 4R 4 R A669 5E4 6 C P603 2001011106368 20010111 06368 WP 2001 1 11 AU000636 1 20000901 G 5730 SKIN DOUG DC3 DC3CS1C3G 3021458 WP PWA R1830 R183092 52020 NE HAMSTD 23E 23E50 NE LT & RT WING CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT AND RT WING UPPER CORRUGATED SKIN LOCATED JUST INBOARD OF STN 142 CONTAINED SURFACE CORROSION AND ISOLATED EXFO LIATION CORROSION. 2 L 7 2 4R 4 R A669 5E4 6 C P603 2000100300158 20001003 00158 EA 2000 10 3 AU000637 2 20000901 G 8530 LW12966 CYLINDER LYC PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL RECIPROCATING EN WORN W K NONE O OTHER IN INSP/MAINT 1 AU S L82B361A (AUS) ENGINE EXHAUST VALVE SEATING INCORRECTLY. (X) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001011106369 20010111 06369 WP 2001 1 11 AU000638 2 20000901 G 7322 89778025 FUEL CONTROL BAG JETSTM JETSTM3201 1500217 EU GARRTT TPE331 TPE33112UA 01514 WP MCAULY 4HFR34 4HFR34C653 NE RT ENGINE OUT OF ADJ W C ABORTED TAKEOFF E R J VIBRATION/BUFFET PARTIAL RPM/PWR LOSS WARNING INDICATION TO TAKEOFF 1 AU S 2185 (AUS) RT ENGINE FUEL CONTROL UNIT OUT OF ADJUSTMENT. 2 L 7 2 4T 4 T RT A56EU E4WE 6 C 3PNE 2000100300159 20001003 00159 CE 2000 10 3 AU000639 1 20000901 G 3230 HMXL6G ROD END BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO MCAULY 3AF34C 3AF34C502 GL LANDING GEAR RET BROKEN W K NONE O OTHER LD LANDING 1 AU S (AUS) NOSE LANDING GEAR RETRACTION ROD ROD END FAILED. (X) 1 L 7 2 3O 3 O 3A16 E5CE 5 C P22EA 2001011106370 20010111 06370 NM 2001 1 11 AU000640 1 20000901 G 2520 1108133M061 SEAT BELT DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE PAX SEAT FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) SEAT BELT LIFT UP RELEASE MECHANISM SPLIT DOWN THE CENTRE. THEASSEMBLY IS MANUFACTURED FROM A PLASTIC COMPOUND. A TOTAL OF FIFTEEN ASSEMBLIES HAVE BEEN FOUND DAMAGED. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2000100300160 20001003 00160 EA 2000 10 3 AU000641 2 20000901 G 8530 VALVE GUIDE LYC CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA MCAULY 1C160 1C160DTM GL ENGINE CARBONED W K NONE E VIBRATION/BUFFET CL CLIMB 1 AU S (AUS) NR 4 CYLINDER EXHAUST VALVE STICKING IN VALVE GUIDE DUE TO CARBON BUILD-UP. (X) 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2000100300119 20001003 00119 CE 2000 10 3 AU000642 1 20000901 G 2910 572700223 HOSE CESSNA CESSNA 441 441 2076020 CE HARTZL HCB3T HCB3TN5 GL HYDRAULIC, MAIN FAILED W K NONE K FLUID LOSS DE DESCENT 1 AU S 0159 (AUS) HYDRAULIC HOSE LOCATED IN THE RIGHT WING LEADING EDGE FRACTURED ON THE BOND RADIUS. (X) 1 L 7 2 3T RT A28CE 6 C P15EA 2001011106371 20010111 06371 NM 2001 1 11 AU000643 1 20000901 G 7603 TLA2 CONTROL CABLE PWA JT9D7R4E BOEING 767 767238 NM PWA JT9 JT9D7R4E 52054 NE POWER LEVER WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE THRUST CONTROL CABLES PN TLA2 AND PN TRA2 WORN BEYOND LIMITS. FOUND DURING INSPECTION IAW AD/B767/118. 2 L 7 2 4F 4 F RT A1NM E3NE 2001011106372 20010111 06372 NM 2001 1 11 AU000644 1 20000901 G 3340 BRACKET BOEING 737 737376 NM CFMINT CFM56 CFM563C 13802 EU EXTERIOR LIGHT CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) TAXI LIGHT BRACKET CRACKED. FOUND DURING INSPECTION IAW CASAAD/B737/144 AND FAA AD 2000-08-17 AMDT 39-11703. 2 L 7 2 4F 4 F RT A16WE E21EU 2001011106373 20010111 06373 NM 2001 1 11 AU000645 1 20000901 G 3340 BRACKET BOEING 737 737376 NM CFMINT CFM56 CFM563C 13802 EU EXTERIOR LIGHT CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) TAXI LIGHT BRACKET CRACKED. FOUND DURING INSPECTION IAW CASAAD/B737/144 AND FAA AD 2000-08-17 AMDT 39-11703. 2 L 7 2 4F 4 F RT A16WE E21EU 2001011106374 20010111 06374 NM 2001 1 11 AU000646 1 20000901 G 3340 BRACKET BOEING 737 737376 NM CFMINT CFM56 CFM563C 13802 EU EXTERIOR LIGHT CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) TAXI LIGHT BRACKET CRACKED. FOUND DURING INSPECTION IAW CASAAD/B737/144 AND FAA AD 2000-08-17 AMDT 39-11703. 2 L 7 2 4F 4 F RT A16WE E21EU 2000100300161 20001003 00161 EA 2000 10 3 AU000647 1 20000901 G 2100 DSC360100 SEAL DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL AIR CONDITIONING FAILED W K NONE O OTHER CR CRUISE 1 AU S (AUS) BLEED AIR PIPE CONNECTOR PERISEAL DETERIORATED AND LEAKING. (X) 1 H 7 2 3T 4 T RT A9EA E4EA 6 C P15EA 2000100300162 20001003 00162 CE 2000 10 3 AU000648 1 20000901 G 3260 ISE13 SWITCH CESSNA 402 402B 207590P CE LANDING GEAR POS FAULTY W K NONE O P OTHER NO WARNING INDICATION NR NOT REPORTED 1 AU S (AUS) LEFT MAIN LANDING GEAR DOWNLOCK MICROSWITCH INTERMITTENT IN OPERATION. (X) 1 L 7 2 3O A7CE 2001011106375 20010111 06375 EU 2001 1 11 AU000649 1 20000901 G 7712 310703411 INDICATOR BAG JETSTM JETSTM3201 1500217 EU GARRTT TPE331 TPE33112UHR WP ROTOL R333 R333482F12 GL ENGINE TORQUE FAILED W O OTHER O OTHER CR CRUISE 1 AU S 2105 (AUS) NR 2 ENGINE TORQUE STRAIN GAUGE BRIDGE OPEN CIRCUITED. 2 L 7 2 4T 4 T RT A56EU E4WE 6 C P61GL 2001011106376 20010111 06376 NM 2001 1 11 AU000650 1 20000901 G 3244 DSC429 TIRE DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE NLG DEFLATED W C ABORTED TAKEOFF F FLT CONT AFFECTED TO TAKEOFF 1 AU S 53 (AUS) NOSE WHEEL TYRES DEFLATED. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001011106377 20010111 06377 NE 2001 1 11 AU000651 2 20000901 G 7230 SEAL BAG BAE146 BAE146100A 1500260 EU LYC ALF502 ALF502R5 41580 NE NR 1 BEARING LEAKING W A UNSCHED LANDING K B J FLUID LOSS SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CR CRUISE 1 AU S (AUS) ENGINE NR 1 BEARING SEAL LEAKING. 2 H 7 4 4F 4 F RT A49EU E6NE 2000100300163 20001003 00163 SO 2000 10 3 AU000652 1 20000901 G 5711 6207006 SPAR PIPER PA28 PA28R200 7102811 SO LYC O360 IO360C1C 41514 EA HARTZL HCC2Y HCC2YK1 GL WING SPAR STRUCT CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LEFT WING MAIN SPAR CONTAINED PATCHES OF INTERGRANULAR CORROSION. (X) 1 L 7 1 3O 3 O 2A13 1E10 5 C P920 2001011106378 20010111 06378 EU 2001 1 11 AU000653 1 20000901 G 6120 RELAY SAAB SF340 SF340A 7850100 EU GE CT7TP CT75A2 30030 NE ROTOL R320 R3204123F1 NE PROP CONTROL FAULTY W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 AU S (AUS) AUTO-COARSEN SYSTEM FAILED. INVESTIGATION FOUND AN INTERMITTENT RELAY. 2 L 7 2 4T 4 T RT A52EU E8NE6 6 C P5NE 2001011106401 20010111 06401 2001 1 11 AU000654 4 20000901 G 2312 064102300 TRANSCEIVER KING VHF22A SAAB SF340 340B 7860101 EU GE CT7TP CT79B 30030 NE ROTOL R390 R3904123F27 NE VHF COMMS FAILED W O OTHER O OTHER DE DESCENT 1 AU S UK (AUS) NR 1 VHF TRANSCEIVER FAILED. 2 L 7 2 4T 4 T RT A52EU E8NE 6 C P31NE 2001011106402 20010111 06402 2001 1 11 AU000655 4 20000901 G 3445 WARNING SYSTEM SAAB SF340 340B 7860101 EU GE CT7TP CT79B 30030 NE ROTOL R375 R3754123F21 NE AIR COLLISION FALSE ACTIVATION W O OTHER N FALSE WARNING DE DESCENT 1 AU S (AUS) TRAFFIC ALERT AND COLLISION AVOIDANCE SYSTEM (TCAS) SUSPECT ACTIVATED BY AIRCRAFT ON PARALLEL RUNWAY. 2 L 7 2 4T 4 T RT A52EU E8NE 6 C P17NE 2001011106403 20010111 06403 EU 2001 1 11 AU000656 1 20000901 G 2120 9303688100 DUCT SAAB SF340 340B 7860101 EU GE CT7TP CT79B 30030 NE ROTOL R375 R3754123F21 NE AIR DISTRIBUTION DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) AIR CYCLE MACHINE BLEED AIR SUPPLY DUCT HOLED. 2 L 7 2 4T 4 T RT A52EU E8NE 6 C P17NE 2001011106404 20010111 06404 WP 2001 1 11 AU000658 2 20000901 G 7261 CHIP DETECTOR CASA C212 C212200 2410304 EU GARRTT TPE331 TPE33110 01514 WP ENGINE CONTAMINATED W A UNSCHED LANDING E J VIBRATION/BUFFET WARNING INDICATION CR CRUISE 1 AU S (AUS) LT ENGINE CHIP DETECTOR CONTAMINATED WITH METAL. 2 H 7 2 4T 4 T RT A43EU E4WE 2001021400003 20010214 00003 NM 2001 2 14 AU000659 1 20000901 G 2400 HARNESS RROYCE RB211524G BOEING 747 747438 NM RROYCE RB211 RB211524* NE ENG ELECTRICAL CHAFED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MAIN ENGINE WIRE BUNDLES W6000 AND W6080 BADLY CHAFED IN THE AREA WHERE THEY RUN THROUGH THE NO1 STRUT KNEECAP. TH E BUNDLES HAD BEEN CHAFING ON AN ACCESS PANEL LOCATED BENEATH THE WING LEADINGEDGE AND THE AIR DUCT ASSEMBLY. 2 L 7 4 4F 4 F RT A20WE E12EU 2000100300164 20001003 00164 SO 2000 10 3 AU000660 1 20000901 G 2913 1213HBG310A PUMP LYC TIO540J2BD PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL HYDRAULIC PUMP. FAILED W K NONE K FLUID LOSS NR NOT REPORTED 1 AU S 2 L462561A (AUS) LEFT ENGINE DRIVEN HYDRAULIC PUMP DRIVESHAFT SHEARED. PUMP HAD ONLY COMPLETED 1.7 HOURS TIS SINCE OVERHAUL. (X) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2000100300165 20001003 00165 CE 2000 10 3 AU000661 1 20000901 G 5311 207 FRAME BEECH 200 B200C 1152924 CE PWA PT6 PT6A42 52043 NE FUSELAGE MAIN FR CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUSELAGE FRAME 207 LEFT, CRACKED. (X) 1 L 7 2 4T 4 T A24CE E4EA 2000100300166 20001003 00166 EA 2000 10 3 AU000662 2 20000901 G 8530 4091709001 PISTON RING LYC PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA HARTZL HCE3Y HCE3YR2 GL ENGINE BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RIGHT ENGINE OIL CONTROL PISTON RINGS BROKEN AND STUCK. TURBOCHARGER LEAKING OIL. (X) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2000101200145 20001012 00145 SO 2000 10 12 AU000663 1 20000901 G 8120 4091709001 TURBOCHARGER LYC PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL EXHAUST TURBO LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S 1028 CAN00091 (AUS) LEFT ENGINE EXHAUST TURBOCHARGER LEAKING OIL. (X) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2000101200149 20001012 00149 EA 2000 10 12 AU000664 2 20000901 G 8530 L913161A PISTON RING LYC PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 1045 (AUS) LEFT ENGINE PISTON RINGS CRACKED AND STUCK. PISTON RING GROOVES WORN. (X) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2000101200150 20001012 00150 CE 2000 10 12 AU000665 1 20000901 G 5740 1011100313 FITTING BEECH BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL WING ATTACH FITT SCORED W K NONE O OTHER IN INSP/MAINT 1 AU S 36 (AUS) LEFT UPPER FORWARD WING ATTACHMENT FITTING SCORED IN THE BORE OFTHE BARREL NUT RECESS IN THE BATHTUB FITTING. CAU SED BY THE BARREL NUT INSERT BEING INSERTED 90 DEGREES OUT FROM ITS CORRECT POSITION. SUBMITTER SUSPECTED OCCURRED DURI NG THE PREVIOUS INSPECTION IAW BEECH STRUCTURAL INSPECTION AND REPAIR MANUAL 98-39006P4 SECTION57-17-00. 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2001011106405 20010111 06405 NE 2001 1 11 AU000666 2 20000901 G 7200 ENGINE BAG BAE146 BAE146100A 1500260 EU LYC ALF502 ALF502R3A 41580 NE NR 2 FAILED W C ABORTED TAKEOFF E M J VIBRATION/BUFFET OVER TEMP WARNING INDICATION TO TAKEOFF 1 AU S (AUS) NR 2 ENGINE TGT EXCEEDED 900 DEGREES AND FLAMES CAME FROM THEENGINE. THE ENGINE WAS REMOVED AND SENT FOR INVESTIGA TION AND REPAIR. 2 H 7 4 4F 4 F RT A49EU E6NE 2001011106406 20010111 06406 2001 1 11 AU000667 4 20000901 G 3418 STICK SHAKER DHAV DHC8 DHC8315 2809010 NM COCKPIT FAULTY W D RETURN TO BLOCK F J FLT CONT AFFECTED WARNING INDICATION TX TAXI/GRND HDL 1 AU S (AUS) STICK SHAKER SYSTEM FAILED. LIMITED INFORMATION PROVIDED. 2 H 7 2 4T RT A13NM 2000101200151 20001012 00151 EA 2000 10 12 AU000668 2 20000901 G 7414 6360 MAGNETO LYC PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL MAGNETO/DIST MISINSTALLED W K NONE O OTHER IN INSP/MAINT 1 AU S RL907161A (AUS) LEFT AND RIGHT MAGNETOS INCORRECTLY FITTED. SUBMITTER SUSPECTED THE MAGNETOS WERE TRANSPOSED DURING ENGINE OVERHA UL. (X) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2000101200137 20001012 00137 2000 10 12 AU000669 4 20000901 G 6122 F624Z CSD WOODWARD F6247 PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL PROP GOVERNOR FAULTY W O OTHER O OTHER TO TAKEOFF 1 AU S 1277 E83T (AUS) CONSTANT SPEED UNIT (CSU) FAULTY. FINE PITCH STOP ADJUSTED WITH NO INCREASE IN RPM. (X) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2000101200152 20001012 00152 SO 2000 10 12 AU000670 2 20000901 G 8530 646657CEA7 CYLINDER CONT TSIO520N CESSNA 340 340A 2076405 CE CONT O520 TSIO520N 17040 SO MCAULY 3AF32C 3AF32C93 GL ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LEFT ENGINE NR 2 AND NR 3 CYLINDERS CRACKED BETWEEN FUEL INJECTOR AND SPARK PLUG. FUEL LEAKING EXTERNALLY. (X) 1 L 7 2 3O 3 O 3A25 E8CE 5 C P22EA 2000101200153 20001012 00153 EA 2000 10 12 AU000672 2 20000901 G 8530 CYLINDER LYC PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL ENGINE DAMAGED W K NONE E VIBRATION/BUFFET CR CRUISE 1 AU S (AUS) RIGHT ENGINE N=R 5 CYLINDER SUSPECT DETONATION. DAMAGE TO CYLINDER HEAD, PISTON AND PISTON PIN. TOP PISTON RING BROKEN CAUSING DAMAGE TO THE CYLINDER HEADM VALVES AND TURBOCHARGER TURBINE WHEEL. (X) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001011106410 20010111 06410 EU 2001 1 11 AU000673 1 20000901 G 3246 5009237 WHEEL SAAB SF340 340B 7860101 EU GE CT7TP CT79B 30030 NE ROTOL R375 R3754123F21 NE MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MAIN WHEEL ASSEMBLY CRACKED AT BEAD SEAT RADIUS. CRACK LENGTH APPROXIMATELY 93.345MM (3.675IN). 2 L 7 2 4T 4 T RT A52EU E8NE 6 C P17NE 2000090800104 20000908 00104 SO 2000 9 8 AU000674 2 20000901 G 7414 M3050 IMPULSE COUPLING SLICK 6310 CESSNA 206 U206 2073306 CE CONT O520 IO520A 17032 SO MCAULY 2A34C D2A34C58 GL MAGNETO/DIST FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S 96010133LH96 (AUS) MAGNETO IMPULSE COUPLINGS (2OFF) HAD LOOSE RIVETS IN THE FLYWEIGHT ASSEMBLIES. FOUND DURING INSPECTION IAW SLICK SB 1-86B. (X) 1 H 7 1 3O 3 O A4CE E5CE 5 C P3EA 2000090800107 20000908 00107 EA 2000 9 8 AU000675 2 20000901 G 8520 L1349148 CRANKSHAFT LYC GULSTM 500 500S 0141107 SW LYC O540 IO540E1B5 41532 EA HARTZL HCA3V HCA3VK2 GL ENGINE BROKEN W K NONE E VIBRATION/BUFFET CL CLIMB 1 AU S 1354 (AUS) RIGHT ENGINE CRANKSHAFT BROKEN. (X) 1 H 7 2 3O 3 O 6A1 1E4 5 C P6EA 2000090800108 20000908 00108 SO 2000 9 8 AU000676 2 20000901 G 8540 402711 STUD CONT COVER CONT O520 IO520C 17032 SO MCAULY 3AF34C 3AF34C502 GL ENGINE MISSING W K NONE K E B FLUID LOSS VIBRATION/BUFFET SMOKE/FUMES/ODORS/SPARKS TO TAKEOFF 1 AU S (AUS) LEFT ENGINE TACHOMETER DRIVE COVER STUD MISSING. OIL LEAKING ONTO HOT EXHAUST. (X) 3 O E5CE 5 C P22EA 2001011106412 20010111 06412 NE 2001 1 11 AU000677 2 20000901 G 7250 70BM041020 TURBINE AEROSP SA365 SA365C 8680667 EU TMECA ARRIEL ARRIEL1A 60030 NE NR 2 ENGINE MAKING METAL W A UNSCHED LANDING E J VIBRATION/BUFFET WARNING INDICATION CR CRUISE 1 AU S 74 (AUS) NR 2 ENGINE REAR BEARING MAGNETIC PLUG CONTAIN A SMALL SLIVER OF METAL. THE ENGINE WAS INSPECTED IAW THE MANUFACTU RERS INSTRUCTIONS BEFORE BEING GROUND RUN AND FLIGHT TESTED WITH NOFURTHER PROBLEMS. AIRCRAFT RETURNED TO SERVICE. 1 G 7 2 3U 3 U H10EU E19EU 2000090800109 20000908 00109 SO 2000 9 8 AU000678 2 20000901 G 8540 643109 SPRING CONT STARTADPTR CESSNA 206 U206F 2073333 CE CONT O520 IO520F 17032 SO MCAULY 3A32C D3A32C90 GL ENGINE BROKEN W K NONE E VIBRATION/BUFFET NR NOT REPORTED 1 AU S (AUS) ENGINE STARTER/ ADAPTER CLUTCH SPRING BROKEN EIGHT COILS FROM THE ATTACHMENT POINT TO THE CLUTCH DRUM. (X) 1 H 7 1 3O 3 O A4CE E5CE 5 C P21EA 2000090800110 20000908 00110 NM 2000 9 8 AU000679 1 20000901 G 3230 4000833 BRACE PIPER PA60 PA60601 7106010 NM LYC O540 IO540S1A5 41532 EA LANDING GEAR RET CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LEFT MAIN LANDING GEAR LOWER SIDE BRACE CRACKED. FOUND DURING INSPECTION IAW TSA-SB600-134A. (X) 1 M 7 2 3O 3 O RT A17WE 1E4 2000090800111 20000908 00111 NM 2000 9 8 AU000680 1 20000901 G 3230 4000833 BRACE PIPER PA60 PA60600A 7106002 NM LYC O540 IO540K1J5 41532 EA LANDING GEAR RET CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LEFT MAIN LANDING GEAR LOWER SIDE BRACE CRACKED. FOUND DURING INSPECTION IAW TSA-SB600-134A. (X) 1 M 7 2 3O 3 O RT A17WE 1E4 2001011100002 20010111 00002 NE 2001 1 11 AU000681 2 20000901 G 7250 GAS GENERATOR STBROS SD3 SD360 8100606 EU PWA PT6 PT6A67R 52043 NE HARTZL HCA6A HCA6A3 NE RT ENGINE SEIZED W E A ENGINE SHUTDOWN UNSCHED LANDING E J VIBRATION/BUFFET WARNING INDICATION CR CRUISE 1 AU S (AUS) RT ENGINE GAS GENERATOR MODULE AND POWER SECTION SEIZED. 2 H 7 2 4T 4 T A41EU E26NE 6 C P14NE 2001011100003 20010111 00003 WP 2001 1 11 AU000682 2 20000901 G 7250 310323511 TURBINE NOZZLE BAG JETSTM JETSTM3201 1500217 EU GARRTT TPE331 TFE33112UHR WP ROTOL R333 R333482F12 GL LT ENGINE CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT ENGINE FIRST STAGE NOZZLE AND INNER BAFFLE ASSEMBLY BURNED, CRACKED AND CORRODED. SEAL PLATE WARPED AND CRACKED . FIRST STAGE TURBINE BLADE TIPS ERODED. SUSPECT CAUSED BY SULPHURISATION CORROSION OF THE NOZZLE COMPINED WITH STREAKIN G FUEL INJECTORS. 2 L 7 2 4T 4 T RT A56EU E4WE 6 C P61GL 2000090800112 20000908 00112 CE 2000 9 8 AU000683 1 20000901 G 2720 12604566 RUDDER BAR CESSNA 210 210L 2073448 CE CONT O520 IO520L 17032 SO MCAULY D3A34 D3A34C404 GL RUDDER CONTROL S CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RUDDER PEDAL SEPARATED FROM RUDDER BAR AT WELD JOINT. BRAKES HAD BEEN BLED TWELVE HOURS PREVIOUSLY. (X) 1 H 7 1 3O 3 O 3A21 E5CE 5 C P47GL 2001011100005 20010111 00005 NM 2001 1 11 AU000684 1 20000901 G 2530 HEATER DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE GALLEY WATER OVERHEATED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 AU S (AUS) STRONG ELECTRICAL SMELL EMANATING FROM THE AREA OF THE RT EMERGENCY CUPBOARD. INVESTIGATION COULD FIND NO SIGNS OF SMOKE OR FIRE. NR 2 URN WAS FOUND TO BE EMPTY OF WATER. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2000090800050 20000908 00050 CE 2000 9 8 AU000685 1 20000901 G 7810 MVT68892250 CLAMP CONT CESSNA 340 340CESSNA 2076404 CE CONT O520 TSIO520K 17040 SO MCAULY 3AF32C 3AF32C505 GL ENGINE COLLECTOR INADEQUATE W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE EXHAUST CLAMPS HAD UNKNOWN HOURS IN SERVICE. CLAMPS ARE LIFED AT 500 HOURS. C LAMPS WERE IN POOR CONDITION. (X) 1 L 7 2 3O 3 O 3A25 E8CE 5 C P22EA 2000090800115 20000908 00115 CE 2000 9 8 AU000686 1 20000901 G 2510 SEAT BELT CESSNA 340 340CESSNA 2076404 CE CONT O520 TSIO520K 17040 SO MCAULY 3AF32C 3AF32C505 GL FLIGHT COMPART INADEQUATE W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FORWARD SEAT BELT SHOULDER HARNESSES NOT FITTED. ITEMS HAD NOT BEEN REINSTALLED FOLLOWING INTERIOR REFURBISHMENT. (X) 1 L 7 2 3O 3 O 3A25 E8CE 5 C P22EA 2000090800116 20000908 00116 CE 2000 9 8 AU000687 1 20000901 G 6120 991026915 CONTROL CABLE MCAULY CESSNA 340 340CESSNA 2076404 CE CONT O520 TSIO520K 17040 SO MCAULY 3AF32C 3AF32C505 GL PROP CONTROL FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LEFT AND RIGHT PROPELLER OUTER CONTROL CABLES SEPARATED AT SLIDE JOINT LOCATED AT PROPELLER GOVERNOR END. LEFT CA BLE HAD BEEN REPAIRED BY LOCKWIRING THE ENDS TOGETHER. CABLES P/N 9910269-15 AND P/N 9910269-16. (X) 1 L 7 2 3O 3 O 3A25 E8CE 5 C P22EA 2000090800117 20000908 00117 CE 2000 9 8 AU000688 1 20000901 G 2711 BOLT CESSNA 340 340CESSNA 2076404 CE CONT O520 TSIO520K 17040 SO MCAULY 3AF32C 3AF32C505 GL AILERON TAB CONT MISINSTALLED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LEFT AILERON TRIM ACTUATING ROD ATTACHMENT BOLT AND NUT NOT SPLIT PINNED. (X) 1 L 7 2 3O 3 O 3A25 E8CE 5 C P22EA 2001011106027 20010111 06027 2001 1 11 AU000689 4 20000901 G 3414 WL106AMA7 INDICATOR BAG BAE146 BAE146100A 1500260 EU LYC ALF502 ALF502R5 41580 NE AIRSPEED FAULTY W C ABORTED TAKEOFF N FALSE WARNING TO TAKEOFF 1 AU S (AUS) AIR SPEED INDICATOR FAULTY. 2 H 7 4 4F 4 F RT A49EU E6NE 2001011100006 20010111 00006 EU 2001 1 11 AU000690 1 20000901 G 5711 SPAR BAG BAE146 BAE146100A 1500260 EU LYC ALF502 ALF502R5 41580 NE LT & RT WING CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT AND RT WINGS FORWARD AND REAR SPARS CRACKED IN AREA LOCATED OUTBOARD OF RIB NR 13. 2 H 7 4 4F 4 F RT A49EU E6NE 2000090800119 20000908 00119 EA 2000 9 8 AU000691 2 20000901 G 8550 LW13388 SEAL LYC PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA HARTZL HCE3Y HCE3YR2 GL ENGINE FAILED W K NONE E K VIBRATION/BUFFET FLUID LOSS CL CLIMB 1 AU S RL11668A (AUS) RIGHT ENGINE OIL FILTER ADAPTER PLATE SEAL FAILED. SEAL WAS PROTRUDING FROM PLATE. LOSS OF 9 LITRES OF ENGINE OI L. (X) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2000090800120 20000908 00120 CE 2000 9 8 AU000692 1 20000901 G 5312 BULKHEAD CESSNA 182 182P 2075816 CE CONT O470 O470U 17026 SO MCAULY 2A34C 2A34C203 GL FUSELAGE MAIN BU CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LEFT DOORPOST BULKHEAD CRACKED. FOUND DURING INSPECTION IAW AD/C180/75. (X) 1 H 7 1 3O 3 O NT TA13 E273 5 C P3EA 2000090800121 20000908 00121 2000 9 8 AU000693 4 20000901 G 3416 B43E ALTIMETER AMTR LNCAIR 320LANCAIR 056129G GL LYC O320 O320* 41508 EA ALTIMETER, BAROM FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S 3293 (AUS) ALTIMETER FAULTY. (X) 1 L 7 1 3O 3 O RT EXPA1L71 E274 2001011100007 20010111 00007 NM 2001 1 11 AU000694 1 20000901 G 7603 TLA2 CONTROL CABLE BOEING 767 767238 NM PWA JT9 JT9D7R4E 52054 NE POWER LEVER WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE THRUST CONTROL CABLES TLA-2 AND TRA-2 LOCATED IN THE RHFORWARD CARGO HOLD WERE WORN BEYOND LIMITS. FOUND DU RING INSPECTION IAW AD/B767/118. 2 L 7 2 4F 4 F RT A1NM E3NE 2001011100008 20010111 00008 NM 2001 1 11 AU000695 1 20000901 G 7500 24098350 SEAL BOEING 747 747238B 1384828 NM RROYCE RB211 RB211524D419 54555 NE BLEED AIR SYSTEM FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) BLEED AIR DUCT SEAL DETERIORATED AND BROKEN INTO PIECES. HOTBLEED AIR LEAKING ONTO CENTRE WING AND FUEL TANK. 2 L 7 4 4F 4 F A20WE E12EU 2000090800122 20000908 00122 SW 2000 9 8 AU000696 1 20000901 G 2810 FUEL TANK MOONEY MOONEY M20 M20J 5870219 SW LYC O360 IO360A1B6 41514 EA HARTZL HCC2Y HCC2YK1 GL FUEL STORAGE LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S (AUS) LEFT FUEL TANK LEAKING FROM TOP SEAM. AD/GEN/80 AMDT2 HAD RECENTLY BEEN CARRIED OUT. (X) 1 L 7 1 3O 3 O 2A3 1E10 5 C P920 2000090800123 20000908 00123 CE 2000 9 8 AU000697 1 20000901 G 2810 0029200344 FUEL TANK BEECH 95 95B55 1152729 CE CONT O470 IO470L 17026 SO MCAULY 2AF34C 2AF34C55 GL FUEL STORAGE LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S (AUS) RIGHT INBOARD LEADING EDGE FUEL TANK LEAKING. AIRCRAFT HAD ONLY JUST HAD AD/GEN/82 AMDT2 CARRIED OUT. (X) 1 L 7 2 3O 3 O RT 3A16 3E1 5 C P5EA 2000090800124 20000908 00124 EA 2000 9 8 AU000698 2 20000901 G 8520 L575861A STUD LYC PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL ENGINE FAILED W K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS TO TAKEOFF 1 AU S L575861A (AUS) LEFT ENGINE NR 2 CYLINDER HOLD-DOWN STUDS (4OFF) FAILED. BROKEN STUDS FOUND IN ENGINE COWL. (X) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001011100009 20010111 00009 NM 2001 1 11 AU000699 1 20000901 G 5755 85770068003 LEVER DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE SPOILER CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) OUTBOARD GROUND SPOILER LEVER CRACKED. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2000090800125 20000908 00125 EA 2000 9 8 AU000700 2 20000901 G 7414 M3548 ROTOR SLICK 4370 CESSNA 172 172P 2072436 CE LYC O360 O360A4M 41514 EA MCAULY 1A170 1A170FFA GL MAGNETO/DIST BROKEN W K NONE E VIBRATION/BUFFET CR CRUISE 1 AU S 9600917 (AUS) RIGHT MAGNETO ROTOR SHAFT SHEARED. (X) 1 H 7 1 3O 3 O NT 3A12 E286 5 N P857 2000090800126 20000908 00126 CE 2000 9 8 AU000701 1 20000901 G 2700 571509665 CONTROL CABLE CESSNA 404 404CESSNA 2075901 CE CONT O520 GTSIO520M 17032 SO MCAULY 3FF32 3FF32C501 GL FLIGHT CONTROLS BROKEN W K NONE F FLT CONT AFFECTED CR CRUISE 1 AU S (AUS) CABLE BROKEN. (X) 1 L 7 2 3O 3 O A25CE E7CE 5 C P45GL 2000090800127 20000908 00127 EA 2000 9 8 AU000702 2 20000901 G 7412 103815504 EXCITER PWA BEECH 90 C90 1152913 CE PWA PT6 PT6A20 52043 EA HARTZL HCB3T HCB3TN3 GL EXCITER FAILED W K NONE E VIBRATION/BUFFET NR NOT REPORTED 1 AU S 623 984OR003C (AUS) LEFT ENGINE IGNITION EXCITER FAILED. INVESTIGATION ALSO FOUND THAT AN ATTACHMENT POINT HAD FAILED. (X) 1 L 7 2 3T 3 T 3A20 E4EA 6 C P15EA 2001011100011 20010111 00011 NM 2001 1 11 AU000703 1 20000901 G 5330 SKIN BOEING 737 737377 NM FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT FORWARD SERVICE DOOR AFT LOWER CORNER OUTER SKIN CRACKED. CRACK LENGTH 13MM (0.51IN). FOUND DURING EDDY CURRENT INSPECTION IAW ER B73-53-30-18B. 2 L 7 2 4F RT A16WE 2001011100012 20010111 00012 NM 2001 1 11 AU000704 1 20000901 G 5512 SKIN BOEING 737 737377 NM HORIZONTAL STAB CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT HORIZONTAL STABILISER LOWER SKIN CRACKED IN AREA OF CHEMICALLY MILLED EDGE BETWEEN STN 147.9 AND STN157.1 JUST FORWARD OF THE REAR SPAR. CRACK LENGTH 38.1MM (1.5IN). FOUND DURING EDDY CURRENT INSPECTION. 2 L 7 2 4F RT A16WE 2001011100031 20010111 00031 EU 2001 1 11 AU000705 1 20000901 G 5311 FRAME AIRBUS 320 A320211 3930320 EU CFMINT CFM56 CFM565A1 NE FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUSELAGE FRAME 35 CRACKED IN ALL TWELVE HOLES LOCATED BETWEEN STRINGERS 30 AND 31 ON LT AND RT SIDES. FOUND DURING EDDY CURRENT INSPECTION IAW AD/A320/94. 2 L 7 2 4F 4 F RT A28NM E29NE 2001011100033 20010111 00033 EU 2001 1 11 AU000706 1 20000901 G 2752 JACKSCREW BAC 146 146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE TE FLAP ACTUATOR FAULTY W O OTHER F FLT CONT AFFECTED NR NOT REPORTED 1 AU S (AUS) FLAPS UNABLE TO BE MOVED FROM THE UP' POSITION. SUSPECT FAULTY RT OUTBOARD SCREWJACK. 2 H 7 4 4F 4 F A49EU E6NE 2001011100034 20010111 00034 EU 2001 1 11 AU000707 1 20000901 G 5313 STRINGER AIRBUS 320 A320211 3930320 EU CFMINT CFM56 CFM565A1 NE FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FRONT VERTICAL STRINGER CRACKED AT FRAME 36. FOUND DURING EDDY CURRENT INSPECTION IAW SB A320-57-1017. 2 L 7 2 4F 4 F RT A28NM E29NE 2001011100036 20010111 00036 EU 2001 1 11 AU000708 1 20000901 G 5311 FRAME AIRBUS 320 A320211 3930320 EU CFMINT CFM56 CFM565A1 NE FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUSELAGE FRAME CRACKED IN HOLES (2OFF) LOCATED BETWEEN FRAME 38 AND FRAME 41 AND STRINGER 12 AND STRINGER 21. FOUN D DURING INSPECTION IAW AD/A320/89. 2 L 7 2 4F 4 F RT A28NM E29NE 2001011100037 20010111 00037 EU 2001 1 11 AU000709 1 20000901 G 5311 FRAME AIRBUS 320 A320211 3930320 EU CFMINT CFM56 CFM565A1 NE FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUSELAGE FRAME 53 CRACKED. CRACK LENGTH APPROXIMATELY 2MM (0.078IN). FOUND DURING ULTRASONIC INSPECTION IAW SBA320 -52-1032. 2 L 7 2 4F 4 F RT A28NM E29NE 2000090800128 20000908 00128 EU 2000 9 8 AU000710 1 20000901 G 3213 1095015 PIN GROB G115 G115 EU LYC O235 O235H2C 41505 EA SNSNCH 72C 72CK EA MLG BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MAIN LANDING GEAR AXLE PIN BROKEN BETWEEN WHEEL NUT AND SPAT RETAINER CAP. (X) 1 L 7 1 3O 3 O NT A57EU E223 5 N P9045 2000090800129 20000908 00129 SO 2000 9 8 AU000711 1 20000901 G 5711 4042000 SPAR CAP PIPER PA31 PA31 7103102 SO LYC O540 TIO540A1A 41532 EA HARTZL HCE3Y HCE3YR2 GL WING SPAR STRUCT CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LEFT LOWER SPAR CAP CORRODED IN AREA BETWEEN THE FUSELAGE AND WHERE THE LOWER SKIN BEGINS. THE AREA IS COVERED BY AN ALUMINIUM ADHESIVE TAPE USED AS AN ANTI-CHAFING STRIP AND THE CORROSION WAS FOUND FOLLOWING REMOVAL OF THE TAPE. (X) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2000090800130 20000908 00130 WP 2000 9 8 AU000712 1 20000901 G 6210 A18910 NUT ROBSIN R22 R22 7640102 WP MAIN ROTOR BLADE MISMANUFACTURED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MAIN ROTOR RETENTION BOLT NUT FAULTY. NO LEAD ON THREAD. SUBMITTER STATED NUT WAS A NEW ITEM FROM ROBINSON. (X) 1 G 7 1 3O H10WE 2001011100039 20010111 00039 EU 2001 1 11 AU000713 1 20000901 G 2730 P310450002 DAMPER BAG BAE146 BAE146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE ELEVATOR FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ELEVATOR GUST DAMPER ASSEMBLY FAULTY. 2 H 7 4 4F 4 F RT A49EU E6NE 2000090800131 20000908 00131 EA 2000 9 8 AU000714 2 20000901 G 8520 SEAL LYC PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL ENGINE LOOSE W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RIGHT ENGINE CRANKSHAFT SEAL ADRIFT. (X) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2000090800132 20000908 00132 EA 2000 9 8 AU000715 2 20000901 G 8530 GASKET LYC PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL ENGINE FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RIGHT ENGINE NR 2, NR 4 AND NR 6 INDUCTION SYSTEM GASKETS FAULTY. (X) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2000090800133 20000908 00133 EA 2000 9 8 AU000716 2 20000901 G 8530 SEAL LYC PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL ENGINE LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S (AUS) LEFT ENGINE NR 5 AND NR 6 PUSHROD GUARD TUBE SEALS LEAKING. (X) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2000090800134 20000908 00134 EA 2000 9 8 AU000717 2 20000901 G 8520 SEAL LYC PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL ENGINE LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S (AUS) LH AND RH ENGINE CRANKSHAFT SEALS ADRIFT AND LEAKING OIL. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2000090800135 20000908 00135 EA 2000 9 8 AU000718 1 20000901 G 5540 STIFFENER WACO YMF YMF 9600412 EA JACOBP R755 R755B2 35007 SW RUDDER STRUCTURE BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RUDDER LOWER STIFFENER RUSTED AND SEPARATED FROM LOWER RUDDER BOW. SUBMITTER SUSPECTED CAUSED BY TRAPPED WATER. (X) 1 Q 7 1 3R 3 R ATC542 E237 2001011100040 20010111 00040 EA 2001 1 11 AU000719 1 20000901 G 2742 8396 ACTUATOR CNDAIR CL600 CL6002B19 EA STABILIZER TRIM FAULTY W C ABORTED TAKEOFF F FLT CONT AFFECTED TO TAKEOFF 1 AU S (AUS) STABILISER TRIM ACTUATOR FAULTY. 2 L 7 2 4F RT A21EA 2001011100042 20010111 00042 EA 2001 1 11 AU000720 1 20000901 G 2613 356024310 DETECTOR CNDAIR CL600 CL6002B19 EA RT & LT PYLON MALFUNCTIONED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT AND RT PYLON BLEED LEAK DETECTOR LOOPS FAILED RESISTANCE CHECK. FOUND DURING INSPECTION IAW SB A601R-36-014. 2 L 7 2 4F RT A21EA 2001011100058 20010111 00058 SO 2001 1 11 AU000722 1 20000901 G 3242 1331096 STATOR BFGOODRICH EMB 120 EMB120 3260201 SO PWA 118 PW118A NE HAMSTD 14RF 14RF9 NE BRAKE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 038OR (AUS) RH OUTBOARD BRAKE ASSEMBLY STATOR CRACKED FROM EXPANSION SLOT TOTHE INSIDE DIAMETER AND PARTLY THROUGH ONE OF THE DRIVE LUGS. TWO OTHER SMALL CRACKS FOUND AT TWO OTHER EXPANSION SLOTS. FOUND WHEN BRAKE REMOVED DUE TO WEAR. 2 L 7 2 4T 4 T RT A31SO E20NE 6 C P11NE 2001011100060 20010111 00060 SW 2001 1 11 AU000723 1 20000901 G 5541 2742051037 TORQUE TUBE FRCHLD SA227 SA227DC 3377521 SW MCAULY 4HFR34 4HFR34C652 NE RUDDER WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RUDDER TORQUE TUBE ASSEMBLY WORN BEYOND LIMITS. CHAFING MARKS ARE APPROXIMATELY 0.254MM (0.010IN) DEEP. THE MAXIMU M DEPTH PERMITTED IS 0.0762MM (0.003IN). SUSPECT CAUSE OF WEAR IS MISALIGNMENT OF THE PRESSURISATION SEAL AT INSTALLATIO N ALLOWING IT TO CONTACTTHE TORQUE TUBE. 2 L 7 2 4T RT A18SW 6 C 3PNE 2001011100061 20010111 00061 SW 2001 1 11 AU000724 1 20000901 G 5541 2742051037 TORQUE TUBE FRCHLD SA227 SA227DC 3377521 SW RUDDER WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RUDDER TORQUE TUBE ASSEMBLY WORN BEYOND LIMITS. CHAFING MARKS ARE APPROXIMATELY 0.254MM (0.010IN) DEEP. THE MAXIMU M DEPTH PERMITTED IS 0.0762MM (0.003IN). SUSPECT CAUSE OF WEAR IS MISALIGNMENT OF THE PRESSURISATION SEAL AT INSTALLATIO N ALLOWING IT TO CONTACTTHE TORQUE TUBE. 2 L 7 2 4T RT A18SW 2001011100063 20010111 00063 2001 1 11 AU000725 4 20000901 G 6122 89741016AC GOVERNOR FRCHLD SA227 SA227DC 3377521 SW GARRTT TPE331 TPE33112UA 01514 WP MCAULY 4HFR34 4HFR34C652 NE RT PROPELLER FAULTY W O OTHER O OTHER DE DESCENT 1 AU S 25 (AUS) RT PROPELLER GOVERNOR FAULTY. 2 L 7 2 4T 4 T RT A18SW E4WE 6 C 3PNE 2000090800142 20000908 00142 EA 2000 9 8 AU000726 2 20000901 G 8530 L280461A CYLINDER LYC PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL RECIPROCATING EN GLAZED W K NONE O OTHER IN INSP/MAINT 1 AU S 247 L280461A (AUS) ENGINE SPARK PLUGS CONTAMINATED WITH OIL. INVESTIGATION FOUND NR 2, NR 4, NR 5, AND NR 6 CYLINDER BORES GLAZED WIT H NR 5 AND NR 6 CYLINDERS ALSO CONTAINING CORROSION IN THE BORES. THE ENGINE WAS ONLY 247.9 HOURS OUT OF FACTORY OVERHAU L. SUBMITTER SUSPECTED GLAZING CAUSED BY INCORRECT TEST RUNNING AND CORROSION CAUSED BY INCORRECT INHIBITING FOLLOWING TEST RUNS AT THE FACTORY. (X) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2000090800143 20000908 00143 EA 2000 9 8 AU000727 2 20000901 G 7322 1052061 CARBURETOR LYC BEECH 76 76 1153005 CE LYC O360 O360A1G6D EA FUEL CONTROL/CAR CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S 92 (AUS) CARBURETOR FAULTY. INVESTIGATION FOUND STICKY NEEDLE AND SEAT ASSEMBLY, PLUNGER O''-RING FAULTY AND CORROSION ON THE INSIDE OF THE CARBURETOR COVER. (X) 1 L 7 2 3O 3 O A29CE E286 2001011100065 20010111 00065 EU 2001 1 11 AU000728 1 20000901 G 2910 SA7670006155 HOSE BAC 146 146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE HYD SYSTEM FAILED W D RETURN TO BLOCK K FLUID LOSS TX TAXI/GRND HDL 1 AU S (AUS) NR 2 ENGINE HYDRAULIC PUMP PRESSURE HOSE FAILED. LOSS OF HYDRAULIC FLUID. 2 H 7 4 4F 4 F A49EU E6NE 2001011100067 20010111 00067 EU 2001 1 11 AU000729 1 20000901 G 2711 HC270H0134014 CONTROL CABLE BAC 146 146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE AILERON TAB CORRODED W A UNSCHED LANDING D J INFLIGHT SEPARATION WARNING INDICATION CL CLIMB 1 AU S (AUS) RT UPPER AILERON TRIM CABLE CORRODED AND BROKEN IN AREA OFOUTBOARD PULLEY LOCATED AT WING RIB NR 14. 2 H 7 4 4F 4 F A49EU E6NE 2001011100068 20010111 00068 SW 2001 1 11 AU000730 1 20000901 G 2432 RELAY FRCHLD SA227 SA227DC 3377521 SW MCAULY 4HFR34 4HFR34C652 NE BATTERY CHARGER SHORTED W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 AU S (AUS) BATTERY LOCKOUT RELAY FAULTY. RELAY TERMINAL SHORT CIRCUITING TOGROUND IN THE RT BATTERY BOX. 2 L 7 2 4T RT A18SW 6 C 3PNE 2001011100075 20010111 00075 EU 2001 1 11 AU000731 1 20000901 G 7603 POWER LEVER BAG BAE146 BAE146300A 1500267 EU LYC ALF502 ALF502R5 41580 NE NR 3 ENGINE STUCK W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 AU S (AUS) NR 3 ENGINE THRUST LEVER STUCK AT CRUISE POWER. INVESTIGATIONCOULD FIND NO CAUSE OF DEFECT. 2 H 7 4 4F 4 F RT A49EU E6NE 2001011100076 20010111 00076 NM 2001 1 11 AU000732 1 20000901 G 5330 SKIN BOEING 737 737377 NM FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FORWARD SERVICE DOOR CUTOUT CONTAINED SEVEN CRACKS PROPAGATING FROM RIVET HOLES IN THE FORWARD UPPER CORNER AND SI X OUT OF ROUND HOLES IN THE UPPER AFT CORNER. FOUND DURING EDDY CURRENTINSPECTION. 2 L 7 2 4F RT A16WE 2001011100077 20010111 00077 EU 2001 1 11 AU000733 1 20000901 G 5330 SKIN AIRBUS 320 A320211 3930320 EU CFMINT CFM56 CFM565A1 NE FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUSELAGE SKIN CRACKED IN RIVET HOLES (16OFF). FOUND DURINGINSPECTION IAW SB A320-53-1031. 2 L 7 2 4F 4 F RT A28NM E29NE 2001011100078 20010111 00078 NM 2001 1 11 AU000734 1 20000901 G 5330 SKIN BOEING 767 767277 NM GE CF6 CF680A 30025 NE FUSELAGE CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) AIRCRAFT SKIN CORRODED BENEATH PAINT LOCATED AFT OF STN 287 AND BELOW STRINGER NR 24. AREA OF CORROSION 50MM BY 50 MM (1.968IN BY 1.968IN) AND 2.032MM (0.080IN) DEEP. 2 L 7 2 4F 4 F RT A1NM E13NE 2001011100080 20010111 00080 NM 2001 1 11 AU000735 1 20000901 G 3230 113T11102 HOUSING BOEING 767 767277 NM GE CF6 CF680A 30025 NE MLG CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT MAIN LANDING GEAR SIDE STRUT SWIVEL HOUSING CORRODED IN THEAREA OF THE BUSHING FLANGE. DEPTH OF CORROSION 0.12 7MM (0.005IN). 2 L 7 2 4F 4 F RT A1NM E13NE 2001011104202 20010111 04202 2001 1 11 AU000736 1 20000901 G 3520 11900301 OXYGEN MASK PAX OXYGEN FIRE W O OTHER A FLAME/FIRE IN INSP/MAINT 1 AU S 09238 (AUS) DURING PBE MASK DISCHARGE, THE OXYGEN MASK ACTIVATION MECHANISM SEPARATED FROM OXYGEN GENERATOR UNDER PRESSURE CAU SING THE GENERATOR UNIT TO CATCH FIRE. (X) 2001011100397 20010111 00397 NM 2001 1 11 AU000737 1 20000901 G 2897 WIRE BOEING 737 737376 NM CFMINT CFM56 CFM563C 13802 EU FUEL INDICATOR WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) CENTRE FUL TANK FLOAT SWITCH WIRING CHAFING APPROXIMATELY 100MM (4IN) FROM END. FOLLOWING REMOVAL OF THE WIRE FUEL CONTAMINATIONOF THE FLOAT SWITCH WAS EVIDENT. 2 L 7 2 4F 4 F RT A16WE E21EU 2001011100082 20010111 00082 NM 2001 1 11 AU000738 1 20000901 G 3230 LANDING GEAR DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE NOSE FAULTY W O OTHER O OTHER LD LANDING 1 AU S (AUS) NOSE LANDING GEAR WOULD NOT EXTEND BY NORMAL MEANS (THREE ATTEMPTS). NLG FINALLY EXTENDED USING THE EMERGENCY SYST EM. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2000090800147 20000908 00147 CE 2000 9 8 AU000739 1 20000901 G 5610 531126110 WINDOW CESSNA 340 340CESSNA 2076404 CE CONT O520 TSIO520K 17040 SO MCAULY 3AF32C 3AF32C93 GL FLIGHT COMPART SEPARATED W O OTHER D INFLIGHT SEPARATION CR CRUISE 1 AU S (AUS) COPILOT SIDE WINDOW SEPARATED IN-FLIGHT. (X) 1 L 7 2 3O 3 O 3A25 E8CE 5 C P22EA 2000090800148 20000908 00148 SO 2000 9 8 AU000740 2 20000901 G 8520 NUT CONT CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO MCAULY 3AF32C 3AF32C93 GL ENGINE LOOSE W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) LEFT AND RIGHT ENGINE CYLINDER HOLD-DOWN NUTS LOOSE. SUBMITTER SUSPECTED CAUSED BY INCORRECT ASSEMBLY. ENGINES H AD COMPLETED 210.5 HOURS SINCE BULKSTRIP. (X) 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2000090800149 20000908 00149 CE 2000 9 8 AU000741 1 20000901 G 3246 4075D WHEEL CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO MCAULY 3A32C D3A32C90 GL WHEEL/SKI/FLOAT CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MAIN WHEEL INBOARD HALF CRACKED IN BEAD RADIUS WITH PARTIAL SEPARATION OF FLANGE. CRACK LENGTH 127 MM (5 INCHES). (X) 1 H 7 1 3O 3 O A4CE E5CE 5 C P21EA 2000090800049 20000908 00049 CE 2000 9 8 AU000742 1 20000901 G 2710 CONTROL CABLE CESSNA 207 207A 2073604 CE CONT O520 IO520F 17032 SO MCAULY 3A32C D3A32C90 GL AILERON CONTROL SEPARATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RIGHT AILERON CABLE SEPARATED FROM PULLEY AT RIGHT PULLEY SET LOCATED IMMEDIATELY INBOARD OF THE AILERON BELLCRANK . NO DAMAGE TO PULLEY OR CABLE. (X) 1 H 7 1 3O 3 O A16CE E5CE 5 C P21EA 2000090800150 20000908 00150 CE 2000 9 8 AU000743 1 20000901 G 6120 CONTROL CABLE MCAULY D3A32C90 CESSNA 206 U206F 2073333 CE CONT O520 IO520F 17032 SO MCAULY 3A32C D3A32C90 GL PROP CONTROL SEPARATED W O OTHER O OTHER CR CRUISE 1 AU S (AUS) PROPELLER CONTROL CABLE ROD END NOT CONNECTED TO CSU. BOLT MISSING. (X) 1 H 7 1 3O 3 O A4CE E5CE 5 C P21EA 2001011100083 20010111 00083 EU 2001 1 11 AU000744 1 20000901 G 2910 A71281421 PIPE FOKKER F28 F28MK0100 4990807 EU HYD SYSTEM CRACKED W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CL CLIMB 1 AU S (AUS) NO1 SYSTEM HYDRAULIC FROM PRESSURE REDUCING VALVE CRACKED ATFLARE. LOSS OF HYDRAULIC FLUID. 2 L 7 2 4F RT 2001011100084 20010111 00084 NE 2001 1 11 AU000745 2 20000901 G 7322 78639010 HMU EMB 120 EMB120 3260201 SO PWA 118 PW118A NE LT ENGINE FAULTY W C ABORTED TAKEOFF E R J VIBRATION/BUFFET PARTIAL RPM/PWR LOSS WARNING INDICATION TO TAKEOFF 1 AU S (AUS) LT ENGINE HYDROMECHANICAL METERING UNIT (HMU) FAULTY. 2 L 7 2 4T 4 T RT A31SO E20NE 2000090800152 20000908 00152 SW 2000 9 8 AU000746 1 20000901 G 2910 70053H000A100A HOSE BELL 206 206L3 1182108 SW ALLSN 250C 250C30P 03013 GL HYDRAULIC, MAIN FAILED W O OTHER K F FLUID LOSS FLT CONT AFFECTED CR CRUISE 1 AU S (AUS) HYDRAULIC HOSE LOCATED BETWEEN HYDRAULIC PUMP AND FILTER ASSEMBLY FAILED. (X) 1 G 7 1 3U 3 U H2SW E1GL 2001011100085 20010111 00085 NE 2001 1 11 AU000747 2 20000901 G 7210 3107090 BEARING EMB 120 EMB120 3260201 SO PWA 118 PW118A NE RT ENGINE G/B SPALLED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT ENGINE REDUCTION GEARBOX NR 19 BEARING FAILED. SPALLING OF THEINNER RACE CREATED METAL CONTAMINATION OF NR 18 B EARING CAUSINGLIGHT SPALLING OF THE RACE. METAL CONTAMINATION OF THE ENGINE. 2 L 7 2 4T 4 T RT A31SO E20NE 2000120700090 20001207 00090 NE 2000 12 7 AU000748 2 20000814 G 8520 4224837 LINK ROD PWA DHAV DHC2 DHC2* 2800108 EA PWA R985 R985AN14B 52008 NE ENGINE SEIZED W K NONE E Y VIBRATION/BUFFET ENGINE STOPPAGE TX TAXI/GRND HDL 1 AU S (AUS) ENGINE FAILED. INVESTIGATION FOUND THAT THE NR 7 LINK ROD SEIZED IN THE NR 7 LINK PIN. (X) 1 H 7 1 3R 3 R A806 5E1 2000112200003 20001122 00003 NM 2000 11 22 AU000749 1 20000817 G 6310 A1681 RETAINER ROBSIN ROBSIN R22 R22BETA NM ENGINE/TRANS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) UPPER SHEAVE SEAL PLATE CRACKED. LIMITED INFORMATION PROVIDED. (X) 1 G 7 1 3O H10WE 2000112200004 20001122 00004 SW 2000 11 22 AU000750 1 20000821 G 6320 412040002103 TRANSMISSION BELL BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE M/R GEARBOX FAULTY W K NONE J WARNING INDICATION NR NOT REPORTED 1 AU S 3919 ABW40279 (AUS) MAIN TRANSMISSION CHIP DETECTOR CONTAMINATED WITH METAL. FOLLOWING INSPECTION AND GROUND RUN, THE CHIP DETECTOR A GAIN ILLUMINATED. (X) 1 G 7 2 4U 4 U H4SW E22EA 2001011100086 20010111 00086 NE 2001 1 11 AU000751 2 20000814 G 7230 311358901 BEARING STBROS SD3 SD360 8100606 EU PWA PT6 PT6A67R 52043 NE HARTZL HCA6A HCA6A3 NE ENGINE FAILED W O OTHER E VIBRATION/BUFFET NR NOT REPORTED 1 AU S (AUS) NR 1 BEARING FAULTY. N1 ROTOR SEIZED. 2 H 7 2 4T 4 T A41EU E26NE 6 C P14NE 2001011100108 20010111 00108 EA 2001 1 11 AU000752 1 20000821 G 7540 356024310 INDICATOR CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE BLEED AIR FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT PYLON BLEED AIR LEAK DETECTOR LOOP HAD LOW RESISTANCE. FOUND DURING INSPECTION IAW SBA601R-36-104. 2 L 7 2 4F 4 F RT A21EA E15NE 2001011100109 20010111 00109 SW 2001 1 11 AU000753 1 20000827 G 2421 300SG121Q GCU FRCHLD SA227 SA227DC 3377521 SW MCAULY 4HFR34 4HFR34C652 NE LT GENERATOR FAULTY W C ABORTED TAKEOFF H J ELECT. POWER LOSS-50 PC WARNING INDICATION TO TAKEOFF 1 AU S 113 (AUS) LT GENERATOR CONTROL UNIT FAULTY. 2 L 7 2 4T RT A18SW 6 C 3PNE 2001011100112 20010111 00112 EU 2001 1 11 AU000754 1 20000825 G 5743 7257162514S515S0 FITTING SAAB SF340 SF340A 7850100 EU GE CT7TP CT75A2 30030 NE ROTOL R354 R3544123F13 NE WING CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LANDING GEAR SUPPORT FITTINGS CORRODED IN BEARING BORES AND LINK ATTACHMENT HOLES. DEPTH OF CORROSION BETWEEN 0.15 2MM AND 1.092MM(0.006IN AND 0.043IN). 2 L 7 2 4T 4 T RT A52EU E8NE6 6 C P61GL 2001011100114 20010111 00114 EU 2001 1 11 AU000755 1 20000829 G 7712 INDICATOR BAG JETSTM JETSTM3201 1500217 EU GARRTT TPE331 TPE33112UA 01514 WP MCAULY 4HFR34 4HFR34C653 NE RT ENGINE TORQUE OUT OF ADJ W C ABORTED TAKEOFF E R J VIBRATION/BUFFET PARTIAL RPM/PWR LOSS WARNING INDICATION TO TAKEOFF 1 AU S (AUS) RT ENGINE TORQUE STRAIN GAUGE BRIDGE OUT OF ADJUSTMENT. 2 L 7 2 4T 4 T RT A56EU E4WE 6 C 3PNE 2000120700091 20001207 00091 SO 2000 12 7 AU000756 2 20000829 G 8520 631845 GEAR CONT CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO MCAULY 3A32C D3A32C90 GL ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 570452 (AUS) CAMSHAFT GEAR P/N 631845 CRACKED. FUEL PUMP DRIVE GEAR P/N 535662 CRACKED AND TEETH BADLY WORN. FUEL CONTROL UNI T P/N 629703-2 HAD O-RING SEAL MISSING FROM MIXTURE SHAFT. SUBMITTER SUSPECTED CAUSED BY INCORRECT MESHING OF FUEL PUM P DRIVE GEAR P/N 535662 AND FUEL PUMP GEAR P/N 631684, AND/OR INSUFFICIENT LUBRICATION OF FUEL PUMP GEAR P/N 631684 AND FUEL PUMP LOWER HOUSING INSIDE DIAMETER. (X) 1 H 7 1 3O 3 O A4CE E5CE 5 C P21EA 2000120700092 20001207 00092 EA 2000 12 7 AU000757 2 20000901 G 8520 LW13838 CRANKCASE LYC LYC O540 IO540K1G5 41532 EA ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 220 (AUS) ENGINE CRANKCASE CRACKED IN AREA ADJACENT TO NR 2 CYLINDER TOP FORWARD BASE STUD. FOLLOWING ENGINE BULK STRIP, TH E FOLLOWING DEFECTS WERE ALSO NOTED: CRANKCASES BADLY FRETTED ON MATING FACES . INTERMEDIATE MAIN BEARINGS LOOSE IN M AIN TUNNEL CAUSING WEAR TO TUNNEL. MATERIAL CHIPPED AWAY FROM TUNNEL LOCATING DOWEL HAD DAMAGED BEARING SURFACE. SUBMI TTER SUSPECTED LOCATING DOWEL LOOSE IN CRANKCASE. SIGNIFICANT TANG DAMAGE FROM BEARINGS ROTATING IN CRANKCASES. CSU DR IVE GEARSHAFT IN FRONT OF CRANKCASE NOT SECURED CORRECTLY AND SHAFT SPINNING IN CRANKCASE. SEALANT USED WAS A RED SILIC ON MATERIAL USED MEASURING 0.0035 INCHES THICK WHEN REMOVED. (X) 3 O 1E4 2001011100115 20010111 00115 NM 2001 1 11 AU000758 1 20000831 G 2701 521314 TORQUE TUBE AEROCD 100 100 NM CONT O200 O200A 17020 SO MCAULY 1A105 1A105SCM GL CONTROL COLUMN CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) CONTROL TORQUE TUBE CRACKED IN THREE PLACES IN THE AREA ADJACENT TO THE CONTROL COLUMN PIVOT. 1 L 7 1 3O 3 O NT 1A21 E252 5 N P918 2001011100116 20010111 00116 NM 2001 1 11 AU000759 1 20000831 G 2701 521314 TORQUE TUBE AEROCD 100 100 NM CONT O200 O200A 17020 SO MCAULY 1A105 1A105SCM GL CONTROL COLUMN CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) CONTROL TORQUE TUBE CRACKED. TORQUE TUBE ALSO EXHIBITED A 10 DEGREE TWIST FROM END TO END. 1 L 7 1 3O 3 O NT 1A21 E252 5 N P918 2001011100118 20010111 00118 SO 2001 1 11 AU000760 1 20000828 G 3246 300608 WHEEL EMB 110 EMB110P1 3260122 SO PWA PT6 PT6A34 52043 EA HARTZL HCB3T HCB3TN3 GL MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT MAIN WHEEL INNER HALF CRACKED IN THE TIRE BEAD SEAT AREA RESULTING IN A SECTION BREAKING AWAY AND CAUSING THE T IRE TO DEFLATE. 1 L 7 2 4T 4 T A21SO E4EA 6 C P15EA 2001011100119 20010111 00119 CE 2001 1 11 AU000761 1 20000828 G 3260 SWITCH BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A42 52043 NE MCAULY 4HFR34 4HFR34C754 NE MLG OUT OF ADJ W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 AU S (AUS) RT MAIN LANDING GEAR UP LIMIT MICROSWITCH OUT OF ADJUSTMENT. ABURNING SMELL IN THE CABIN WAS ATTRIBUTED TO A RECEN T COMPRESSOR WASH. 1 L 7 2 4T 4 T A24CE E4EA 6 C 3PNE 2001011100145 20010111 00145 NM 2001 1 11 AU000762 1 20000825 G 2731 697045521 CONTROL CABLE BOEING 737 737377 NM ELEVATOR TAB FRAYED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) HORIZONTAL STABILISER TRIM CABLE HAD AN EXCESSIVE AMOUNT OF BROKEN STRANDS. APPROXIMATELY THIRTY STRANDS BROKEN IN A 609.6MM(24IN) LENGTH LOCATED IN THE EMPENNAGE AREA. 2 L 7 2 4F RT A16WE 2001011100146 20010111 00146 NM 2001 1 11 AU000763 1 20000725 G 2752 MX469871 BEARING VICKERS 569670 BOEING 737 737377 NM TE FLAP ACTUATOR FAILED W O OTHER F FLT CONT AFFECTED DE DESCENT 1 AU S 605 MX469871 (AUS) TRAILING EDGE HYDRAULIC FLAP DRIVE MOTOR DRIVE SHAFT BEARING FAILED. 2 L 7 2 4F RT A16WE 2001011100147 20010111 00147 2001 1 11 AU000764 4 20000829 G 3420 6466350 INDICATOR BAG BAE146 BAE146200A 1500266 EU LYC ALF502 ALF502R3A 41580 NE ATTITUDE FAULTY W A UNSCHED LANDING O OTHER CR CRUISE 1 AU S (AUS) ARTIFICIAL HORIZON FAULTY. A TOTAL OF THREE INDICATORS HAVE FAILED IN A FEW WEEKS. 2 H 7 4 4F 4 F RT A49EU E6NE 2001011100149 20010111 00149 EU 2001 1 11 AU000765 1 20000829 G 2421 GENERATOR BAC 146 146200A 1500266 EU NR 1 FAILED W A UNSCHED LANDING H J ELECT. POWER LOSS-50 PC WARNING INDICATION CL CLIMB 1 AU S (AUS) NR 1 GENERATOR FAILURE. LIMITED INFORMATION PROVIDED. 2 H 7 4 4F A49EU 2001011100543 20010111 00543 2001 1 11 AU000766 4 20000901 G 2397 WIRE CESSNA 340 340CESSNA 2076404 CE CONT O520 TSIO520K 17040 SO MCAULY 2AF34C D2AF34C71 GL PTT SWITCH SHORTED W A UNSCHED LANDING O OTHER CR CRUISE 1 AU S (AUS) PRESS TO TALK (PTT) SWITCH STUCK IN THE TRANSMIT' POSITION. INVESTIGATION FOUND THE THE PVT WIRE LOCATED IN THE C ENTRE PEDESTAL UNDER THE THROTTLE QUADRANT WAS SHORTING OUT. 1 L 7 2 3O 3 O 3A25 E8CE 5 C P5EA 2000120700093 20001207 00093 CE 2000 12 7 AU000767 1 20000830 G 5540 51310103 BEARING CESSNA 414 414A 2075907 CE CONT O520 TSIO520N 17040 SO MCAULY 3AF32C 3AF32C505 GL RUDDER STRUCTURE CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LOWER RUDDER HINGE BEARING PLATE CORRODED. UPON REMOVAL, THE BEARING PLATE WAS FOUND TO HAVE BEEN INSTALLED UPSID E DOWN. THE BEARING PLATE APPEARED TO BE ORIGINAL FITMENT. (X) 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2001011100152 20010111 00152 NM 2001 1 11 AU000768 1 20000714 G 5313 INTERCOSTAL BOEING 737 737377 NM FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUSELAGE INTERCOSTAL / STRINGER LOCATED AT S5L AT BS 303.9 CRACKED BOTH LONGITUDINALLY AND VERTICALLY. 2 L 7 2 4F RT A16WE 2000120700094 20001207 00094 CE 2000 12 7 AU000769 1 20000828 G 5711 SPAR CESSNA 402 402B 207590P CE CONT O520 TSIO520E 17040 SO MCAULY 3AF32C 3AF32C87 GL WING SPAR STRUCT CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LEFT WING REAR SPAR ASSEMBLY UPPER AND LOWER SPAR CAPS CORRODED. FOUND DURING INSPECTION IAW AD/C400/40 AMDT13. (X) 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2000120700095 20001207 00095 CE 2000 12 7 AU000770 1 20000828 G 5711 51220313 SPAR CAP CESSNA 402 402B 207590P CE CONT O520 TSIO520E 17040 SO MCAULY 3AF32C 3AF32C87 GL WING SPAR STRUCT CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LEFT WING LOWER SPAR CAP CORRODED. SPAR CAP EXHIBITS SIGNS OF PREVIOUS UNAPPROVED REPAIRS. FOUND DURING INSPECTIO N IAWAD/C400/40 AMDT13. (X) 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2001011100153 20010111 00153 2001 1 11 AU000772 4 20000826 G 2310 6225272020 TRANSCEIVER BAC 146 AVRO146RJ100 1500096 EU HF COMMS FAULTY W O OTHER N FALSE WARNING NR NOT REPORTED 1 AU S (AUS) HF TRANSCEIVER CAUSES FIRE BELL TO RING WHEN TRANSMITTER KEYED. TRANSCEIVER HAD BEEN FITTED FOLLOWING REPAIR. 2 H 7 4 4F RT A49EU 2001011100154 20010111 00154 NM 2001 1 11 AU000773 1 20000716 G 5330 SKIN BOEING 737 737377 NM FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUSELAGE SKIN CRACKED ON THE LT SIDE JUST AFT OF THE WING LIGHT ASSEMBLY BETWEEN STN 500C AND STN 500D LOCATED ABO VE STRINGER NR 15. CRACK LENGTH APPROXIMATELY 50MM (1.96IN). 2 L 7 2 4F RT A16WE 2000120700096 20001207 00096 EU 2000 12 7 AU000774 1 20000812 G 7931 PIPE LYC PARTEN P68 P68B EU LYC O360 IO360A1B6 41514 EA HARTZL HCC2Y HCC2YK2 GL ENGINE OIL PRESS WORN W K NONE K FLUID LOSS NR NOT REPORTED 1 AU S (AUS) ENGINE OIL PRESSURE LINE LOCATED BEHIND INSTRUMENT PANEL WORN BY OPILOT ASHTRAY. OIL LEAKING. (X) 1 H 7 2 3O 3 O A31EU 1E10 5 C P920 2001011100155 20010111 00155 EU 2001 1 11 AU000775 1 20000903 G 7712 BRIDGE BAG JETSTM JETSTM3201 1500217 EU GARRTT TPE331 TPE33112UA 01514 WP MCAULY 4HFR34 4HFR34C653 NE ENGINE TORQUE FAULTY W C ABORTED TAKEOFF E R J VIBRATION/BUFFET PARTIAL RPM/PWR LOSS WARNING INDICATION TO TAKEOFF 1 AU S (AUS) RT ENGINE TORQUE STRAIN GAUGE NR 1 BRIDGE OUTPUT FAULTY. 2 L 7 2 4T 4 T RT A56EU E4WE 6 C 3PNE 2001011100179 20010111 00179 SO 2001 1 11 AU000776 1 20000831 G 7712 CONNECTOR EMB 120 EMB120 3260201 SO PWA 118 PW118A NE ENGINE TORQUE CORRODED W C ABORTED TAKEOFF E VIBRATION/BUFFET TO TAKEOFF 1 AU S (AUS) LT ENGINE NP PROBE PLUG AND PINS CORRODED. 2 L 7 2 4T 4 T RT A31SO E20NE 2000120700097 20001207 00097 CE 2000 12 7 AU000777 1 20000827 G 5744 FITTING BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL CONTROL SURFACE LOOSE W K NONE O F OTHER FLT CONT AFFECTED IN INSP/MAINT 1 AU S (AUS) RIGHT AILERON FOULING ON UPPER WING SKIN PREVENTING FULL AILERON MOVEMENT. FURTHER INVESTIGATION FOUND THAT THE I NBOARD HINGE ATTACHMENT BRACKET WAS NOT SECURED. THE TWO LOWER ATTACHMENT SCREWS WERE INSTALLED BUT NOT SECURED TO THE A NCHOR NUTS. (X) 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2001011100181 20010111 00181 SW 2001 1 11 AU000778 1 20000901 G 7722 P70141 HARNESS FRCHLD SA227 SA227DC 3377521 SW GARRTT TPE331 TFE33112UHR WP MCAULY 4HFR34 4HFR34C652 NE EGT INDICATOR FAULTY W O OTHER E X VIBRATION/BUFFET ENGINE FLAMEOUT DE DESCENT 1 AU S P70141 (AUS) RT ENGINE EGT FLUCTUATING DUE TO FAULTY WIRING HARNESS. RT ENGINE FLAMED OUT DURING LANDING. FCU AND FUEL PUMP CHA NGED. 2 L 7 2 4T 4 T RT A18SW E4WE 6 C 3PNE 2000120600037 20001206 00037 CE 2000 12 6 AU000779 1 20000828 G 2710 AILERON CESSNA 340 340CESSNA 2076404 CE CONT O520 TSIO520K 17040 SO MCAULY 2AF34C D2AF34C71 GL AILERON CONTROL SEIZED W K NONE F FLT CONT AFFECTED CR CRUISE 1 AU S (AUS) AILERONS JAMMED DURING CRUISE. AILERONS FREED DURING DESCENT. INVESTIGATION COULD FIND NO CAUSE OF JAMMING. SUS PECT ICING. (X) 1 L 7 2 3O 3 O 3A25 E8CE 5 C P5EA 2000120600038 20001206 00038 CE 2000 12 6 AU000780 1 20000904 G 2810 FILLER CESSNA 150 150F 2071814 CE CONT O200 O200A 17020 SO MCAULY 1A100 1A100MCM GL FUEL STORAGE CONTAMINATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUEL TANK FILLER NECK CONTAMINATED WITH WASP NEST. (X) 1 H 7 1 3O 3 O 3A19 E252 5 N P918 2000120600039 20001206 00039 CE 2000 12 6 AU000781 1 20000904 G 2800 FUEL TANK CESSNA 150 150F 2071814 CE CONT O200 O200A 17020 SO MCAULY 1A100 1A100MCM GL AIRCRAFT FUEL SY UNWANTED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MOGAS USED IN AIRCRAFT WITHOUT AN STC. . (X) 1 H 7 1 3O 3 O 3A19 E252 5 N P918 2000120600040 20001206 00040 CE 2000 12 6 AU000782 1 20000904 G 2823 SELECTOR VALVE CESSNA 150 150F 2071814 CE CONT O200 O200A 17020 SO MCAULY 1A100 1A100MCM GL FUEL SELECTOR/SH SEIZED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUEL SELECTOR VALVE SEIZED. (X) 1 H 7 1 3O 3 O 3A19 E252 5 N P918 2000120600041 20001206 00041 GL 2000 12 6 AU000783 3 20000904 G 6111 1AMCM BLADE MCAULY 1A100MCM CESSNA 150 150F 2071814 CE CONT O200 O200A 17020 SO MCAULY 1A100 1A100MCM GL PROPELLER BLADE CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S 2111 (AUS) PROPELLER BLADES CORRODED CAUSING PAINT TO LIFT. (X) 1 H 7 1 3O 3 O 3A19 E252 5 N P918 2000120600042 20001206 00042 2000 12 6 AU000784 4 20000904 G 2300 VHF COMM CESSNA 150 150F 2071814 CE CONT O200 O200A 17020 SO MCAULY 1A100 1A100MCM GL COMMUNICATIONS S INACCURATE W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) AVIONICS FIT NOT RECORDED OR CERTIFIED IN AIRCRAFT LOG BOOK. ITEMS NOT ACCOUNTED FOR: 1. IC-A200 VHF SNO 139702. KT76A ATC TRANSPONDER SNO 117656. 3. AMER-KING ENCODER SNO 35243954. SPA-400 TSO SIGTRONICS CORP INTERCOM SNO 6055958 . (X) 1 H 7 1 3O 3 O 3A19 E252 5 N P918 2000120600043 20001206 00043 CE 2000 12 6 AU000785 1 20000904 G 3411 PITOT LINE CESSNA 150 150F 2071814 CE CONT O200 O200A 17020 SO MCAULY 1A100 1A100MCM GL PITOT/STATIC SYS LEAKING W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) PITOT/STATIC SYSTEM FAILED LEAK TEST. INVESTIGATION FOUND THE PITOT SYSTEM CONNECTOR LOCATED AT THE LEFT WING BRE AK WAS CROSS-THREADED AND ONLY HOLDING BY ONE TURN. THE STATIC SYSTEM HAD BEEN REWORKED TO ACCOMMODATE THE ENCODED. TH E EXISTINGPLUMBING HAD BEEN CUT AND LARGER PLASTIC TUBING SLIPPED OVER IT TO FIT THE BRASS TEE. UNAPPROVED PART. (X) 1 H 7 1 3O 3 O 3A19 E252 5 N P918 2000120600044 20001206 00044 CE 2000 12 6 AU000786 1 20000904 G 7160 HOSE CONT CESSNA 150 150F 2071814 CE CONT O200 O200A 17020 SO MCAULY 1A100 1A100MCM GL ENG AIR INTAKE MISSING W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) CARBURETOR HEAT HOSE LOCATED BETWEEN FORWARD RIGHT ENGINE BAFFLE AND THE RIGHT MUFFLER MISSING. (X) 1 H 7 1 3O 3 O 3A19 E252 5 N P918 2000120600045 20001206 00045 CE 2000 12 6 AU000787 1 20000904 G 2510 SEAT BELT CESSNA 150 150F 2071814 CE CONT O200 O200A 17020 SO MCAULY 1A100 1A100MCM GL FLIGHT COMPARTME MISINSTALLED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LEFT AND RIGHT SEAT BELT OUTBOARD ATTACHMENT POINTS INCORRECT. THE BELTS WERE ATTACHED TO THE FORWARD BAGGAGE FLO OR WITH AN3 BOLTS INSTEAD OF TO THE CORRECT POSITION BELOW THE DOOR CUTOUTS USING 6.35 MM (0.25 INCH) HARDWARE AND BUSHE S. UNAPPROVED PARTS. (X) 1 H 7 1 3O 3 O 3A19 E252 5 N P918 2000120600046 20001206 00046 CE 2000 12 6 AU000789 1 20000904 G 3240 7410 BRAKE ASSY CLEVELAND CFP3063 CESSNA 150 150F 2071814 CE CONT O200 O200A 17020 SO MCAULY 1A100 1A100MCM GL LANDING GEAR BRA CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) BRAKE ASSEMBLY BACK PLATES P/N 74-10 AND PRESSURE PLATES P/N 73-11 BADLY CORRODED. BRAKE LININGS CRACKED. ONE BR AKE BLEEDER SCREW BROKEN AND BOTH BRAKER BLEEDER SEAT HEXAGONALS COMPLETELY ROUNDED. BRAKE SEALS LEAKING. (X) 1 H 7 1 3O 3 O 3A19 E252 5 N P918 2000120600047 20001206 00047 CE 2000 12 6 AU000790 1 20000904 G 3246 15315 SEAL CLEVELAND CFP4097 CESSNA 150 150F 2071814 CE CONT O200 O200A 17020 SO MCAULY 1A100 1A100MCM GL WHEEL/SKI/FLOAT DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) WHEEL BEARING SEALS DAMAGED AND/OR FELT MISSING. WHEEL NUT SPLIT PIN TAILS NOT BENT OVER. (X) 1 H 7 1 3O 3 O 3A19 E252 5 N P918 2000120600048 20001206 00048 CE 2000 12 6 AU000791 1 20000904 G 2810 SEAL CESSNA 150 150F 2071814 CE CONT O200 O200A 17020 SO MCAULY 1A100 1A100MCM GL FUEL STORAGE DETERIORATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUEL STORAGE SYSTEM SEALS AND GASKETS DETERIORATED. SEALS AFFECTED: 1. FUEL TANK GASKETS DETERIORATED. 2. FUEL CAP SEALS DETERIORATED. 3. LEFT AND RIGHT FUEL TANK DRAIN VALVE SEALS DETERIORATED. (X) 1 H 7 1 3O 3 O 3A19 E252 5 N P918 2000120600049 20001206 00049 CE 2000 12 6 AU000792 1 20000904 G 1100 PLATE CONT O200A CESSNA 150 150F 2071814 CE CONT O200 O200A 17020 SO MCAULY 1A100 1A100MCM GL ENGINE (RECIPROC INACCURATE W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE DATA PLATE NOT STAMPED FOR COMPLIANCE WITH AD/CON/75. (X) 1 H 7 1 3O 3 O 3A19 E252 5 N P918 2000120600050 20001206 00050 CE 2000 12 6 AU000793 1 20000904 G 2510 SEAT CESSNA 150 150F 2071814 CE CONT O200 O200A 17020 SO MCAULY 1A100 1A100MCM GL FLIGHT COMPART SEIZED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) PILOT AND COPILOT SEAT ROLLERS SEIZED. COPILOT''S SEAT RELEASE ROD BENT AND FOULING ON THE STRUCTURE BENEATH THE SEAT PREVENTING THE SEAT FROM LOCKING. PILOT''S SEAT LEFT SEAT RAIL CRACKED AT INBOARDFORWARD ATTACHMENT SKIN. (X) 1 H 7 1 3O 3 O 3A19 E252 5 N P918 2000120600051 20001206 00051 2000 12 6 AU000794 4 20000904 G 3420 GAUGE CESSNA 150 150F 2071814 CE CONT O200 O200A 17020 SO MCAULY 1A100 1A100MCM GL ATTITUDE AND DIR UNSERVICEABLE W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ARTIFICIAL HORIZON, DIRECTING GYRO AND CYLINDER HEAD TEMPERATUREGAUGE UNSERVICEABLE. UNSERVICEABLE INSTRUMENTS NO T PLACARDED IAW CAO 20.18.10. S TANDBY COMPASS HAD 23 DEGREES ERROR ON WEST. (X) 1 H 7 1 3O 3 O 3A19 E252 5 N P918 2000120600052 20001206 00052 CE 2000 12 6 AU000795 1 20000904 G 7110 04520026 CAP CONT CESSNA 150 150F 2071814 CE CONT O200 O200A 17020 SO MCAULY 1A100 1A100MCM GL ENGINE COWLING S CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE COWL NOSE CAP CRACKED. CRACK LENGTH 100 M (4 INCHES). NOSE CAP HAD BEEN ILLEGALLY REPAIRED USING A FIRE EX TINGUISHER DATE PLATE, POP RIVETS AND LIQUID NAILS. UNAPPROVED REPAIR. (X) 1 H 7 1 3O 3 O 3A19 E252 5 N P918 2000120600053 20001206 00053 CE 2000 12 6 AU000796 1 20000904 G 3252 DAMPER CESSNA 150 150F 2071814 CE CONT O200 O200A 17020 SO MCAULY 1A100 1A100MCM GL SHIMMY DAMPER FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) SHIMMY DAMPER LOW ON FLUID. ON FURTHER INVESTIGATION THE FOLLOWING COMPONENTS WERE FOUND TO BE DAMAGED: 1. HEAD BEARING P/N 0542102-3. 2. ROLL PIN P/N NAS 561P4-143. RING RETAINER P/N MS16625-1118. DAMPER WAS ATTACHED BY TWO FU LLY THREADED METRIC BOLTS. UNAPPROVED PART. (X) 1 H 7 1 3O 3 O 3A19 E252 5 N P918 2000120600054 20001206 00054 CE 2000 12 6 AU000797 1 20000904 G 5740 FITTING CESSNA 150F CESSNA 150 150F 2071814 CE CONT O200 O200A 17020 SO MCAULY 1A100 1A100MCM GL WING ATTACH FITT OUT OF ADJ W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) AIRCRAFT MAIN PLANE ATTACHMENT FITTING CONCENTRIC BUSHES OUT OF ADJUSTMENT CAUSING AIRCRAFT TO ROLL TO THE LEFT. LEFT WING WAS UNABLE TO BE ADJUSTED AS THE BUSH WAS FOUND TO BE IN THE MAXIMUM POSITION. THE ADJUSTMENT HAD TO BE CARRIE D OUT ON THE RIGHT WING BUSH. (X) 1 H 7 1 3O 3 O 3A19 E252 5 N P918 2001011100182 20010111 00182 NM 2001 1 11 AU000798 1 20000828 G 5610 17180003 WINDOW DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE COCKPIT CRACKED W A UNSCHED LANDING O OTHER CL CLIMB 1 AU S (AUS) LT SIDE COCKPIT WINDOW CRACKED. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2000120700098 20001207 00098 SO 2000 12 7 AU000799 1 20000906 G 2140 461731 REGULATOR JANITROL FR65D793EL PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL HEATING SYSTEM LEAKING W K NONE O OTHER IN INSP/MAINT 1 AU S 7 A92080029 (AUS) CABIN FUEL HEATER REGULATOR LEAKING. SUBMITTER SUSPECTED HOLED DIAPHRAGM. (X) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2000120700099 20001207 00099 SO 2000 12 7 AU000800 2 20000805 G 7414 10106498 HOUSING BENDIX S6RN201 CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO MCAULY 3AF32C 3AF32C87 GL MAGNETO/DIST CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 784 1269595ER (AUS) MAGNETO TOP HOUSING CRACKED AROUND BEARING. (X) 1 L 7 2 3O 3 O 3A10 E5CE 5 C P22EA 2001011100184 20010111 00184 NM 2001 1 11 AU000801 1 20000715 G 2782 256T21205 ACTUATOR BOEING 767 767277 NM GE CF6 CF680A 30025 NE LE FLAP CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S 13773 (AUS) NR 11 LEADING EDGE SLAT INBOARD ROTARY ACTUATOR INTERNALLY CORRODED. RING GEAR SEAL MISSING. 2 L 7 2 4F 4 F RT A1NM E13NE 2000112200005 20001122 00005 EA 2000 11 22 AU000802 2 20000905 G 7414 67542 BEARING LYC ROBSIN R44 R44 7640120 WP LYC O540 O540F1B5 41532 EA MAGNETO/DIST FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MAGNETO ADAPTER BEAR FAULTY. BEARING HAD NO CAGE FITTED. FOUND WHEN MAGNETO WAS REMOVED DUE TO BROKEN DRIVE CUSH IONS P/N LW-13641. (X) 1 G 7 1 3O 3 O H11NM E295 2001011100186 20010111 00186 NM 2001 1 11 AU000803 1 20000731 G 3233 273T63002 ACTUATOR BOEING 767 767277 NM GE CF6 CF680A 30025 NE MLG FAILED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 AU S 00056 (AUS) RT MAIN LANDING GEAR DRAG BRACE ACTUATOR PISTON ROD PN 273T6034-1 FRACTURED IN THREADED END. 2 L 7 2 4F 4 F RT A1NM E13NE 2001011100188 20010111 00188 NM 2001 1 11 AU000804 1 20000621 G 2910 V643602 FUSE BOEING 767 767277 NM GE CF6 CF680A 30025 NE HYD SYSTEM CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S 7641 (AUS) OUTBOARD HYDRAULIC FUSE ON BRAKE MODULE CRACKED IN VALVE BODY. VALVE IS LOCATED AT THE WING TRAILING EDGE OUTBOARD OF THE LT MAIN LANDING GEAR. LOSS OF RT HYDRAULIC SYSTEM FLUID. 2 L 7 2 4F 4 F RT A1NM E13NE 2001011100189 20010111 00189 EU 2001 1 11 AU000805 1 20000601 G 2910 SA7670006155 HOSE BAC 146 146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE HYD SYSTEM WORN W O OTHER K FLUID LOSS NR NOT REPORTED 1 AU S (AUS) NR 2 ENGINE HYDRAULIC PUMP PRESSURE HOSE CHAFED THROUGH BY ADEL CLAMP. LOSS OF YELLOW' SYSTEM HYDRAULIC FLUID. 2 H 7 4 4F 4 F A49EU E6NE 2001011100235 20010111 00235 SO 2001 1 11 AU000806 1 20000907 G 2750 HANDLE EMB 120 EMB120 3260201 SO PWA 118 PW118A NE TE FLAP CONTROL STUCK W O OTHER F FLT CONT AFFECTED LD LANDING 1 AU S (AUS) FLAP SELECTOR HANDLE STICKING. 2 L 7 2 4T 4 T RT A31SO E20NE 2000120700100 20001207 00100 CE 2000 12 7 AU000807 1 20000905 G 7714 041108728 TACHOMETER CESSNA 041108728 CESSNA 172 172 2072402 CE CONT O300 O300A 17022 SO MCAULY 1C172 1C172EM GL ENGINE RPM IND WORN W K NONE E I VIBRATION/BUFFET FLT. ATTITUDE INST. CR CRUISE 1 AU S 13471 (AUS) TACHOMETER FAILED. ITEM HAD BEEN LAST OVERHAULED IN 1972. (X) 1 H 7 1 3O 3 O NT 3A12 E253 5 N P910 2001011100236 20010111 00236 EU 2001 1 11 AU000808 1 20000907 G 3244 404F63T2 TIRE FOKKER F28 F28MK4000 4990810 EU RROYCE SPEY SPEY55515 54521 EU LT MLG SEPARATED W C ABORTED TAKEOFF D INFLIGHT SEPARATION TO TAKEOFF 1 AU S (AUS) LT MAIN LANDING GEAR NR 2 TIRE TREAD SEPARATED. DAMAGE TO LT INBOARD FLAP LEADING EDGE AND FLAP VANE. 2 L 7 2 4F 4 F RT A20EU E2EU 2000120700101 20001207 00101 SO 2000 12 7 AU000809 1 20000828 G 2810 557003 ADAPTER 531035 PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL FUEL STORAGE FAILED W K NONE D INFLIGHT SEPARATION TO TAKEOFF 1 AU S (AUS) RIGHT WING FUEL ADAPTER FAULTY. FUEL CAP CAME LOOSE. (X) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001011100237 20010111 00237 EU 2001 1 11 AU000810 1 20000906 G 2810 FUEL TANK BAC 146 146100A 1500260 EU LYC ALF502 ALF502R5 41580 NE LT WING CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT WING TANK HAD EVIDENCE OF PITTING CORROSION. 2 H 7 4 4F 4 F RT A49EU E6NE 2000120700102 20001207 00102 SO 2000 12 7 AU000811 1 20000829 G 2140 A230048 REGULATOR PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA HARTZL HCE3Y HCE3YR2 GL HEATING SYSTEM LEAKING W K NONE O K OTHER FLUID LOSS IN INSP/MAINT 1 AU S 520 (AUS) CABIN HEATER REGULATOR LEAKING FROM DIAPHRAGM. (X) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2000120700103 20001207 00103 SO 2000 12 7 AU000812 1 20000831 G 2140 A230048 REGULATOR PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL HEATING SYSTEM LEAKING W K NONE O K OTHER FLUID LOSS IN INSP/MAINT 1 AU S (AUS) CABIN HEATER REGULATOR LEAKING FROM DIAPHRAGM. BASE PLATE APPEARS WARPED. (X) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2000120700104 20001207 00104 CE 2000 12 7 AU000813 1 20000912 G 5312 121340710 BULKHEAD CESSNA 206 U206B 2073322 CE CONT O520 IO520A 17032 SO MCAULY D3A34 D3A34C404 GL FUSELAGE MAIN BU CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FORWARD DOORPOST BULKHEAD CRACKED ON LEFT AND RIGHT SIDES. (X) 1 H 7 1 3O 3 O A4CE E5CE 5 C P47GL 2000120700105 20001207 00105 CE 2000 12 7 AU000814 1 20000912 G 5711 07214024 ANGLE CESSNA 206 U206B 2073322 CE CONT O520 IO520A 17032 SO MCAULY D3A34 D3A34C404 GL WING SPAR STRUCT CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RIGHT WING LOWER SPAR CAP ANGLE CONTAINED INTERGRANNULAR CORROSION. (X) 1 H 7 1 3O 3 O A4CE E5CE 5 C P47GL 2000113000025 20001130 00025 CE 2000 11 30 AU000815 1 20000912 G 5711 07214003 ANGLE CESSNA 206 U206B 2073322 CE CONT O520 IO520A 17032 SO MCAULY D3A34 D3A34C404 GL WING SPAR STRUCT CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LEFT WING UPPER SPAR CAP ANGLE CONTAINED EXFOLIATION CORROSION. (X) 1 H 7 1 3O 3 O A4CE E5CE 5 C P47GL 2001011100238 20010111 00238 EU 2001 1 11 AU000816 1 20000907 G 3260 JE5 ACTUATOR BAG JETSTM JETSTM3201 1500217 EU ROTOL R333 R333482F12 GL MLG BROKEN W O OTHER O OTHER CR CRUISE 1 AU S (AUS) LANDING GEAR DOOR SWITCH ACTUATOR BROKEN. 2 L 7 2 4T RT A56EU 6 C P61GL 2000113000026 20001130 00026 CE 2000 11 30 AU000817 1 20000907 G 5341 0512122 FITTING CESSNA 150 150B 2071806 CE CONT O200 O200A 17020 SO MCAULY 1A100 1A100MCM GL WING ATTACH FITT CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LEFT AND RIGHT WING REAR ATTACHMENT FITTINGS CORRODED. (X) 1 H 7 1 3O 3 O 3A19 E252 5 N P918 2000113000027 20001130 00027 CE 2000 11 30 AU000818 1 20000904 G 3260 MS272401 SWITCH CESSNA 441 441 2076020 CE MCAULY 3G34C6 3GFR34C601 GL LANDING GEAR POS FAULTY W K NONE O N OTHER FALSE WARNING CL CLIMB 1 AU S (AUS) RIGHT MAIN LANDING GEAR UPLOCK MICROSWITCH FAILED. LEFT MAIN LANDING GEAR UPLOCK MICROSWITCH INTERMITTENT IN OPER ATION. (X) 1 L 7 2 3T RT A28CE 6 C P54GL 2000113000028 20001130 00028 CE 2000 11 30 AU000819 1 20000907 G 3297 G12C20 WIRE CESSNA 441 441 2076020 CE LANDING GEAR SEL BROKEN W K NONE O OTHER DE DESCENT 1 AU S (AUS) LANDING GEAR HYDRAULIC SELECTOR VALVE WIRE BROKEN AT TERMINAL CONNECTOR. (X) 1 L 7 2 3T RT A28CE 2000113000029 20001130 00029 EU 2000 11 30 AU000820 1 20000911 G 7603 PIN LYC BNORM BN2 BN2A20 1520220 EU LYC O540 IO540K1B5 41532 EA HARTZL HCC2Y HCC2YK2 GL POWER LEVER DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) THROTTLE FRICTION ADJUSTER SHAFT SPLIT PIN DEFORMED AND PARTIALLY SHEARED. (X) 1 H 7 2 3O 3 O A17EU 1E4 5 C P920 2000113000030 20001130 00030 CE 2000 11 30 AU000821 1 20000911 G 5521 12346501 TORQUE TUBE 12340192 CESSNA 206 U206F 2073333 CE CONT O520 IO520F 17032 SO MCAULY 3A32C D3A32C90 GL ELEVATOR SPAR/RI CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ELEVATOR TORQUE TUBE CRACKED ON INBOARD END. DISASSEMBLY FOUND SIGNIFICANT CORROSION BETWEEN THE TORQUE TUBE AND THE SPAR MOUNTING BRACKET. (X) 1 H 7 1 3O 3 O A4CE E5CE 5 C P21EA 2001011100239 20010111 00239 SW 2001 1 11 AU000822 1 20000816 G 3213 2752529003 SHAFT SWRNGN SA227 SA227AC 8780603 SW ROTOL R321 R321482F8 GL MLG BROKEN W O OTHER O OTHER LD LANDING 1 AU S 664 (AUS) LT MAIN LANDING GEAR UPPER TORQUE LINK SHAFT BROKEN. 2 L 7 2 4T RT A8SW 6 C P61GL 2001011100240 20010111 00240 WP 2001 1 11 AU000823 1 20000903 G 2911 5133124 ACCUMULATOR DOUG DC3 DC3CS1C3G 3021458 WP PWA R1830 R183092 52020 NE HAMSTD 23E 23E50 NE HYD SYSTEM FAULTY W O OTHER F FLT CONT AFFECTED LD LANDING 1 AU S 4 3545 (AUS) HYDRAULIC ACCUMULATOR FAULTY. 2 L 7 2 4R 4 R A669 5E4 6 C P603 2000112800106 20001128 00106 WP 2000 11 28 AU000824 1 20000810 G 6320 269A505073 BEARING HUGHES 269 269B 4470502 WP LYC O360 HIO360A1A 41514 EA M/R GEARBOX MISINSTALLED W K NONE O OTHER IN INSP/MAINT 1 AU S 384 (AUS) MAIN ROTOR DRIVE SHAFT THRUST BEARING WAS INCORRECTLY INSTALLED. DISCRPENCY WAS FOUND DURING INSPECTION IAW AD HU2 69/28 AMDT3. (X) 1 G 7 1 3O 3 O 4H12 1E10 2001011100242 20010111 00242 SW 2001 1 11 AU000825 1 20000904 G 2752 2736053003 ACTUATOR FRCHLD SA227 SA227DC 3377521 SW GARRTT TPE331 TPE33112UA 01514 WP MCAULY 4HFR34 4HFR34C652 NE TE FLAP CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT FLAP ACTUATOR BODY CRACKED. LOSS OF HYDRAULIC FLUID. 2 L 7 2 4T 4 T RT A18SW E4WE 6 C 3PNE 2001011100244 20010111 00244 EU 2001 1 11 AU000826 1 20000904 G 3020 CONNECTOR BAC 146 146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE INTAKE ANTI ICE DIRTY W C ABORTED TAKEOFF N FALSE WARNING TO TAKEOFF 1 AU S (AUS) NR 2 ENGINE INTAKE LOW PRESSURE SWITCH CANNON PLUG DIRTY. 2 H 7 4 4F 4 F A49EU E6NE 2001011104403 20010111 04403 2001 1 11 AU000827 1 20000907 G 7732 TRANSDUCER LYC ALF502R5 LYC ALF502 ALF502R5 41580 NE ENGINE VIBRATION FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE VIBRATION TRANSDUCER PLUG BROKEN. PINS MISSING AND BAREWIRES SHOWING. ENGINE HAD BEEN RECEIVED FROM USA. 4 F E6NE 2001011100309 20010111 00309 EU 2001 1 11 AU000828 1 20000905 G 3320 LIGHT BAG BAE146 BAE146100A 1500260 EU LYC ALF502 ALF502R5 41580 NE CABIN FAILED W K NONE B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 AU S (AUS) LAMP HOLDERS LOCATED AT ROW 14 AND ROW 10 ON THE RT SIDE WALLS BURNED OUT. 2 H 7 4 4F 4 F RT A49EU E6NE 2001011100546 20010111 00546 2001 1 11 AU000829 4 20000906 G 2397 WIRE BAG BAE146 BAE146100A 1500260 EU LYC ALF502 ALF502R5 41580 NE INTERPHONE FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) GROUND CALL HORN WIRE FAULTY. 2 H 7 4 4F 4 F RT A49EU E6NE 2001011100363 20010111 00363 EU 2001 1 11 AU000831 1 20000908 G 3320 6524001 BALLAST SAAB SF340 340B 7860101 EU GE CT7TP CT79B 30030 NE ROTOL R375 R3754123F21 NE CABIN FAILED W O OTHER B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 AU S (AUS) CABIN LIGHTING BALLAST LOCATED ABOVE ROW 3 FAILED. 2 L 7 2 4T 4 T RT A52EU E8NE 6 C P17NE 2001011100364 20010111 00364 2001 1 11 AU000832 4 20000906 G 3418 WARNING SYSTEM CNDAIR CL600 CL6002B19 EA STALL WARNING SY FAULTY W C ABORTED TAKEOFF N FALSE WARNING TO TAKEOFF 1 AU S (AUS) STALL WARNING SYSTEM FAULT INDICATION. INVESTIGATION COULD FIND NO FAULT WITH THE SYSTEM. SUSPECT CAUSED BY GUSTIN G CROSSWIND. 2 L 7 2 4F RT A21EA 2001011100365 20010111 00365 SW 2001 1 11 AU000833 1 20000908 G 3260 UPLOCK BRACKET FRCHLD SA227 SA227DC 3377521 SW MCAULY 4HFR34 4HFR34C652 NE MLG STIFF W C ABORTED TAKEOFF N FALSE WARNING TO TAKEOFF 1 AU S (AUS) RT MAIN LANDING GEAR UPLOCK HOOK STIFF IN OPERATION. 2 L 7 2 4T RT A18SW 6 C 3PNE 2001011100366 20010111 00366 EU 2001 1 11 AU000834 1 20000907 G 3260 HARNESS SAAB SF340 SF340A 7850100 EU GE CT7TP CT75A2 30030 NE ROTOL R320 R3204123F1 NE MLG SHORTED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT LANDING GEAR EMERGENCY EXTENSION ELECTRICAL HARNESS OPEN CIRCUITED. INVESTIGATION FOUND A BROKEN WIRE IN THE HA RNESS. 2 L 7 2 4T 4 T RT A52EU E8NE6 6 C P5NE 2001011100367 20010111 00367 EA 2001 1 11 AU000835 1 20000801 G 2910 D97C00614 ACTUATOR CNDAIR CL600 CL6002B19 EA HYD SYSTEM FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT FIREWALL HYDRAULIC SHUT-OFF VALVE ACTUATOR FAULTY. 2 L 7 2 4F RT A21EA 2001011100368 20010111 00368 EU 2001 1 11 AU000836 1 20000904 G 3020 SWITCH BAC 146 146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE INTAKE ANTI ICE CONTAMINATED W C ABORTED TAKEOFF N FALSE WARNING TO TAKEOFF 1 AU S (AUS) NR 2 ENGINE INTAKE LOW PRESSURE WARNING SWITCH PLUG DIRTY. 2 H 7 4 4F 4 F A49EU E6NE 2000113000031 20001130 00031 EU 2000 11 30 AU000837 1 20000828 G 6123 15M3 SWITCH MCAULY REIMS 406 F406 EU PWA PT6 PT6A112 52043 NE MCAULY 3G34C7 3GFR34C701 GL PROP FEATHER FAULTY W K NONE J WARNING INDICATION TO TAKEOFF 1 AU S (AUS) LEFT AUTOFEATHER MICROSWITCH FAULTY. (X) 1 L 7 2 3T 3 T RT A54EU E4EA 5 C P60GL 2001011100369 20010111 00369 NM 2001 1 11 AU000838 1 20000908 G 2730 STOP DHAV DHC8 DHC8202 2809007 NM ELEVATOR FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ELEVATOR BUMPER STOPS FAILED ALLOWING THE ELEVATOR TO CONTACT THE RUDDER. RT ELEVATOR TRIM TAB AND RUDDER TRAILING EDGE DAMAGED. 2 H 7 2 4T RT A13NM 2000113000032 20001130 00032 NE 2000 11 30 AU000839 2 20000814 G 8520 NO7 PIN PWA DHAV DHC2 DHC2* 2800108 EA PWA R985 R985AN14B 52008 NE ENGINE FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S 4224837 (AUS) NO7 LINK PIN DISPLACED. (X) 1 H 7 1 3R 3 R A806 5E1 2000112200006 20001122 00006 SW 2000 11 22 AU000840 1 20000907 G 6320 7001F000X116 HOSE BELL 206 206B3 1181506 SW ALLSN 250C 250C20B 03013 GL MAIN ROTOR GRBOX FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) TRANSMISSION OIL HOSE FAILED. (X) 1 G 7 1 3U 3 U H2SW E4CE 2000112200007 20001122 00007 GL 2000 11 22 AU000841 2 20000825 G 7261 6853464 PIPE ALLSN BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL ENGINE CRACKED W K NONE O E K OTHER VIBRATION/BUFFET FLUID LOSS IN INSP/MAINT 1 AU S 31388 (AUS) ENGINE OIL PIPE LEAKING IN AREA BENEATH P'' CLIPS. (X) 1 G 7 1 3U 3 U H2SW E4CE 2000101100452 20001011 00452 WP 2000 10 11 AU000842 2 20000913 G 7250 TURBINE GARRTT GARRTT TPE331 TPE331* 01514 WP TURBINE SECTION INACCURATE W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) FIRST STAGE TURBINE WHEEL AND THIRD STAGE STATOR SERIAL NUMBERS DID NOT MATCH THE SERIAL NUMBERS IN THE LOGBOOK OR LOG CARDS. (X) 3 T E2WE 2001011100370 20010111 00370 NM 2001 1 11 AU000844 1 20000902 G 3260 PLUG BOEING 737 737376 NM CFMINT CFM56 CFM563C 13802 EU MLG CONTAMINATED W C ABORTED TAKEOFF N FALSE WARNING TO TAKEOFF 1 AU S (AUS) RT GROUND SHIFT PLUGS D4574P AND D4852P CONTAMINATED WITH EXCESS MOISTURE. SUSPECT MOISTURE CONTAMINATED PLUGS FOL LOWING A WHEEL WELL WASH. 2 L 7 2 4F 4 F RT A16WE E21EU 2001011100371 20010111 00371 EU 2001 1 11 AU000845 2 20000902 G 7310 737M28500011 VALVE BOEING 737 737376 NM CFMINT CFM56 CFM563C 13802 EU FUEL DIST FAILED W O OTHER J WARNING INDICATION NR NOT REPORTED 1 AU S (AUS) NR 1 ENGINE FUEL VALVE FAILED TO OPEN DURING ENGINE START. 2 L 7 2 4F 4 F RT A16WE E21EU 2001011100373 20010111 00373 NM 2001 1 11 AU000846 1 20000909 G 2820 VALVE BOEING 737 737476 NM CFMINT CFM56 CFM563C 13802 EU FUEL DIST FAILED W O OTHER J WARNING INDICATION NR NOT REPORTED 1 AU S (AUS) NR 1 SPAR VALVE FAILED. 2 L 7 2 4F 4 F RT A16WE E21EU 2000101100453 20001011 00453 CE 2000 10 11 AU000847 1 20000913 G 5741 05233091 ANGLE 0523309 CESSNA 206 U206B 2073322 CE CONT O520 IO520A 17032 SO MCAULY D3A34 D3A34C404 GL WING, FUSELAGE A CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LEFT AND RIGHT WING FORWARD ATTACHMENT FITTING ANGLES CONTAINED INTERGRANNULAR CORROSION. (X) 1 H 7 1 3O 3 O A4CE E5CE 5 C P47GL 2000101100454 20001011 00454 CE 2000 10 11 AU000848 1 20000907 G 3520 174412030 SOLENOID AEROSPACECMP 44021 BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL PASSENGER OXYGEN OPEN W K NONE O OTHER NR NOT REPORTED 1 AU S 548 027 (AUS) PASSENGER OXYGEN MASKS DID NOT DEPLOY DURING TEST FLIGHT. INVESTIGATION FOUND SOLENOID OPEN CIRCUIT. (X) 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2000101100455 20001011 00455 SO 2000 10 11 AU000849 2 20000423 G 8530 631639 EXHAUST VALVE CONT CESSNA 172 172D 2072410 CE CONT O300 O300A 17022 SO MCAULY 1C172 1C172EM GL ENGINE SEIZED W K NONE E VIBRATION/BUFFET CR CRUISE 1 AU S (AUS) NR 4 CYLINDER EXHAUST VALVE STUCK IN VALVE GUIDE. (X) 1 H 7 1 3O 3 O NT 3A12 E253 5 N P910 2001011100419 20010111 00419 NM 2001 1 11 AU000850 1 20000829 G 3242 NUT BOEING 767 767338 1385151 NM GE CF6 CF680C2* GL BRAKE LOOSE W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NO3 FRONT BRAKE EQUALISER ROD TO BRAKE ATTACHMENT PIN RETENTION NUT BACKED OFF WITH APPROXIMATELY TWO THREADS LEFT BEFORE THE NUT WOULD HAVE FALLEN OFF. 2 L 7 2 4F 4 F RT A1NM E23EA 2001011100421 20010111 00421 NM 2001 1 11 AU000851 1 20000828 G 5210 HANDLE BOEING 767 767338 1385151 NM GE CF6 CF680C2* GL PAX DOOR SEPARATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FORWARD ENTRY DOOR HANDLE HAD EXCESSIVE FREE PLAY. DURING OPERATION THE INTERIOR HANDLE SEPARATED FROM THE SHAFT P REVENTING THE DOOR FROM BEING OPERATED FROM THE INSIDE. 2 L 7 2 4F 4 F RT A1NM E23EA 2001011100422 20010111 00422 NM 2001 1 11 AU000852 1 20000826 G 2710 252T21182 BELLCRANK BOEING 767 767238 NM PWA JT9 JT9D7R4E 52054 NE AILERON CONTROL FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) PCA BELLCRANK SHEAR RIVETS FAILED. FOUND DURING INSPECTION IAW EI 767-027-0112 AND FAA AD 2000 17-05. 2 L 7 2 4F 4 F RT A1NM E3NE 2001011100423 20010111 00423 NM 2001 1 11 AU000853 1 20000825 G 2710 BELLCRANK BOEING 767 767338 1385151 NM AILERON CONTROL FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) PCA BELLCRANK SHEAR RIVETS FAILED. FOUND DURING INSPECTION IAW EI 767-027-0112 AND FAA AD 2000-18-05. 2 L 7 2 4F RT A1NM 2001011100424 20010111 00424 NM 2001 1 11 AU000854 1 20000828 G 3244 161U00011 TIRE BOEING 747 747438 NM MLG SEPARATED W O OTHER D INFLIGHT SEPARATION NR NOT REPORTED 1 AU S (AUS) NR 4 RT TIRE TREAD SEPARATED. DAMAGE TO AIRCRAFT. 2 L 7 4 4F RT A20WE 2001011100425 20010111 00425 NM 2001 1 11 AU000855 1 20000901 G 5314 KEELBEAM BOEING 727 72777C 1380420 NM PWA JT8 JT8D15 52051 NE FUSELAGE CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) KEEL BEAM WEB CORRODED AT STN 950 LOCATED IN THE UPPER AFT CORNER OF THE LT WHEEL WELL. FOUND DURING CORROSION INS PECTION. 2 L 7 3 4F 4 F A3WE E2EA 2001011100426 20010111 00426 NM 2001 1 11 AU000856 1 20000901 G 5720 WEB BOEING 727 72777C 1380420 NM PWA JT8 JT8D15 52051 NE LT WING CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) UPPER WEB LOCATED IN THE LT UPPER WHEEL WELL AT STN 870 BETWEEN WBL 0 AND WBL 24.75 CORRODED. FOUND DURING CORROSI ON INSPECTION. 2 L 7 3 4F 4 F A3WE E2EA 2001011100427 20010111 00427 NM 2001 1 11 AU000857 1 20000901 G 5720 FITTING BOEING 727 72777C 1380420 NM PWA JT8 JT8D15 52051 NE LT WING CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) SPLICE FITTING LOCATED BETWEEN STN 870 FORGING AND HORIZONTAL BEAM LOCATED IN LT WHEEL WELL CORRODED. FOUND DURING CORROSIONINSPECTION. 2 L 7 3 4F 4 F A3WE E2EA 2001011100428 20010111 00428 NM 2001 1 11 AU000858 1 20000901 G 5320 ANGLE BOEING 727 72777C 1380420 NM PWA JT8 JT8D15 52051 NE FUSELAGE CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) BULKHEAD T' ANGLE LOCATED IN RT WHEEL WELL AT STN 950 CORRODED AT KEEL BEAM ATTACHMENT. FOUND DURING CORROSION INS PECTION. 2 L 7 3 4F 4 F A3WE E2EA 2001011100429 20010111 00429 NM 2001 1 11 AU000859 1 20000902 G 5330 SKIN BOEING 727 72777C 1380420 NM PWA JT8 JT8D15 52051 NE FUSELAGE CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LOWER CENTRE LINE FUSELAGE SKIN CORRODED AT STN 360. FOUND DURING CORROSION INSPECTION. 2 L 7 3 4F 4 F A3WE E2EA 2001011100430 20010111 00430 NM 2001 1 11 AU000860 1 20000902 G 5711 SPAR BOEING 727 72777C 1380420 NM PWA JT8 JT8D15 52051 NE WING CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) REAR SPAR UPPER CHORD CORRODED AT UPPER SKIN INTERFACE INBOARD OF NR 4 SPOILER INBOARD HINGE. FOUND DURING CORROSI ON INSPECTION. 2 L 7 3 4F 4 F A3WE E2EA 2001011100476 20010111 00476 NM 2001 1 11 AU000861 1 20000901 G 5711 SPAR CAP BOEING 727 72777C 1380420 NM PWA JT8 JT8D15 52051 NE WING CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) REAR SPAR CAP CORRODED AT UPPER SKIN INTERFACE ADJACENT TOOUTBOARD FLAP OUTBOARD JACKSCREW GEARBOX. FOUND DURING C ORROSIONINSPECTION. 2 L 7 3 4F 4 F A3WE E2EA 2001011100547 20010111 00547 SW 2001 1 11 AU000862 1 20000914 G 2897 WIRE FRCHLD SA227 SA227DC 3377521 SW MCAULY 4HFR34 4HFR34C652 NE BOOST PUMP WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT AUXILIARY BOOST PUMP WIRE WORN. LT MAIN BOOST PUMP WIRE INSULATION WORN. 2 L 7 2 4T RT A18SW 6 C 3PNE 2001011100548 20010111 00548 SW 2001 1 11 AU000863 1 20000913 G 2897 WIRE FRCHLD SA227 SA227DC 3377521 SW GARRTT TPE331 TPE33112UA 01514 WP MCAULY 4HFR34 4HFR34C652 NE BOOST PUMP WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT AND RT AUXILIARY FUEL BOOST PUMP WIRES WORN. 2 L 7 2 4T 4 T RT A18SW E4WE 6 C 3PNE 2001011100549 20010111 00549 SW 2001 1 11 AU000864 1 20000908 G 2897 WIRE SWRNGN 3282030002 FRCHLD SA227 SA227DC 3377521 SW MCAULY 4HFR34 4HFR34C652 NE BOOST PUMP WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT AUXILIARY BOOST PUMP WIRE INSULATION WORN. 2 L 7 2 4T RT A18SW 6 C 3PNE 2001011100550 20010111 00550 SW 2001 1 11 AU000865 1 20000914 G 2897 WIRE SWRNGN 32820391 FRCHLD SA227 SA227DC 3377521 SW GARRTT TPE331 TPE33112UA 01514 WP MCAULY 4HFR34 4HFR34C652 NE BOOST PUMP WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT AUXILIARY FUEL BOOST PUMP AND LT MAIN FUEL BOOST PUMP WIRING DAMAGED. 2 L 7 2 4T 4 T RT A18SW E4WE 6 C 3PNE 2001011100551 20010111 00551 SW 2001 1 11 AU000866 1 20000915 G 2897 WIRE SWRNGN 32820301 FRCHLD SA227 SA227DC 3377521 SW MCAULY 4HFR34 4HFR34C652 NE BOOST PUMP WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT MAIN FUEL BOOST PUMP AND RT AUXILIARY FUEL BOOST PUMP WIRESWORN. 2 L 7 2 4T RT A18SW 6 C 3PNE 2001011100577 20010111 00577 SW 2001 1 11 AU000867 1 20000914 G 2897 WIRE SWRNGN 3282030001 FRCHLD SA227 SA227DC 3377521 SW MCAULY 4HFR34 4HFR34C652 NE BOOST PUMP WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT FUEL BOOST PUMP WIRE INSULATION WORN. 2 L 7 2 4T RT A18SW 6 C 3PNE 2001011101761 20010111 01761 NE 2001 1 11 AU000868 2 20000914 G 7321 70886M60G11 ECU GE CT75A2 SAAB SF340 SF340A 7850100 EU GE CT7TP CT75A2 30030 NE ROTOL R354 R3544123F13 NE FUEL CONTROL FAULTY W C ABORTED TAKEOFF E M J VIBRATION/BUFFET OVER TEMP WARNING INDICATION TO TAKEOFF 1 AU S 367249 (AUS) LT ENGINE ELECTRICAL CONTROL UNIT FAULTY. 2 L 7 2 4T 4 T RT A52EU E8NE6 6 C P61GL 2001011101762 20010111 01762 EA 2001 1 11 AU000869 1 20000721 G 2731 83963 ACTUATOR CNDAIR CL600 CL6002B19 EA ELEVATOR TAB FAULTY W C ABORTED TAKEOFF F FLT CONT AFFECTED TO TAKEOFF 1 AU S (AUS) HORIZONTAL STABILISER TRIM ACTUATOR (HSTA) FAULTY. NR 1 CHANNEL MOTOR FAULTY. 2 L 7 2 4F RT A21EA 2001011101763 20010111 01763 EA 2001 1 11 AU000870 1 20000914 G 2910 D97C00614 ACTUATOR CNDAIR CL600 CL6002B19 EA HYD SYSTEM FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT FIREWALL HYDRAULIC SHUTOFF VALVE ACTUATOR FAULTY. 2 L 7 2 4F RT A21EA 2000101300111 20001013 00111 SO 2000 10 13 AU000871 1 20000915 G 2810 FUEL CELL AMRGEN AA5 AA5A 3960106 SO LYC O360 O360* 41514 EA MCAULY 1A170 1A170FFA GL FUEL STORAGE DETERIORATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUEL TANK ACCESS PANEL BONDED DOUBLER DISBONDED FROM WING SKINDUE TO CORROSION. FUEL LEAKING THROUGH TO OUTSIDE S KIN. FUEL TANK SEALING COMPOUND FOUND TO BE VERY SOFT AND LIFTING OFF IN SOME AREAS. WATER CONTAMINATION OF FUEL CELLS. SUBMITTER SUSPECTED WATER LEFT OVER FROM FUEL CELL DECONTAMINATION IN JANUARY 2000. SUSPECT IPA USED IN THE DECONTAMI NATION PROCESS CAUSED THE DETERIORATION OF THE TANK SEALANT WHICH THEN LED TO THE CORROSION AND FUEL LEAKAGE. (X) 1 L 7 1 3O 3 O A16EA E286 5 N P857 2000101800080 20001018 00080 CE 2000 10 18 AU000873 1 20000821 G 3230 08411068 BELLCRANK CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO MCAULY 3AF32C 3AF32C87 GL LANDING GEAR RET BROKEN W K NONE O OTHER CL CLIMB 1 AU S (AUS) RIGHT MAIN LANDING GEAR IDLER BELLCRANK FAILED. DURING RETRACTION THE MAIN WHEEL DID NOT CLEAR THE INBOARD DOOR R ESULTING IN THE FAILURE OF THE DOWNLOCK BELLCRANK. (X) 1 L 7 2 3O 3 O 3A10 E5CE 5 C P22EA 2000101800002 20001018 00002 CE 2000 10 18 AU000874 1 20000905 G 2434 318 ALTERNATOR CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA MCAULY 1C160 1C160DTM GL DC GENERATOR-ALT FAULTY W K NONE H ELECT. POWER LOSS-50 PC CL CLIMB 1 AU S 8070446 (AUS) ALTERNATOR FAILED. INVESTIGATION COULD FIND NO FAULT. SUBMITTER SUSPECTED CAUSED BY STICKING BRUSH. (X) 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2000101800081 20001018 00081 CE 2000 10 18 AU000875 1 20000908 G 3230 HMXL6G ROD END BEECH 55 D55 1152730 CE CONT O520 IO520C 17032 SO MCAULY 3AF32C 3AF32C75 GL LANDING GEAR RET SEIZED W K NONE O OTHER LD LANDING 1 AU S (AUS) NOSE LANDING GEAR REAR ACTUATING ROD ROD END SEIZED AND FAILED ALLOWING NLG TO COLLAPSE ON LANDING. (X) 1 L 7 2 3O 3 O 3A16 E5CE 5 C P22EA 2000101800082 20001018 00082 CE 2000 10 18 AU000876 1 20000908 G 5312 0024400249 BULKHEAD 44002411 BEECH 58 58 1152740 CE MCAULY 3AF32C 3AF32C512 GL FUSELAGE MAIN BU CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) REAR TAILCONE BULKHEAD LOCATED AT BS 271.92 CRACKED THROUGH WEB IN AREA OF RIGHT LOWER CARRY THROUGH SPAR CUT-OUT. (X) 1 L 7 2 3O 3A16 5 C P22EA 2000101800083 20001018 00083 CE 2000 10 18 AU000877 1 20000913 G 5312 0024400249 BULKHEAD 44002411 BEECH 58 58 1152740 CE CONT O550 IO550C SO MCAULY 3AF32C 3AF32C512 GL FUSELAGE MAIN BU CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) REAR TAILCONE BULKHEAD LOCATED AT BS 271.92 CRACKED THROUGH BULKHEAD AND WEB IN THE AREA OF THE LEFT LOWER CARRY T HROUGH SPAR CUT-OUT. CRACK LENGTH APPROXIMATELY 10.41 MM (0.41 INCH). (X) 1 L 7 2 3O 3 O 3A16 E3SO 5 C P22EA 2001011101764 20010111 01764 NE 2001 1 11 AU000878 2 20000915 G 7261 310573501 RELIEF VALVE EMB 120 EMB120 3260201 SO PWA 118 PW118A NE ENGINE OIL PRESS OUT OF ADJ W C ABORTED TAKEOFF E K J VIBRATION/BUFFET FLUID LOSS WARNING INDICATION TO TAKEOFF 1 AU S (AUS) RT ENGINE OIL PRESSURE REGULATING VALVE OUT OF ADJUSTMENT. 2 L 7 2 4T 4 T RT A31SO E20NE 2000101900280 20001019 00280 CE 2000 10 19 AU000879 1 20000915 G 3520 13240822 DIODE BEECH 300 B300C CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL PASSENGER OXYGEN SHORTED W K NONE O OTHER NR NOT REPORTED 1 AU S (AUS) CABIN OXYGEN CONTROL SOLENOID TRANSIENT VOLTAGE SUPPRESSION DIODE SHORT CIRCUITED. FAILURE OF PASSENGER OXYGEN MA SK AUTOMATIC DEPLOYMENT. (X) 2 L 7 2 4T 4 T RT A24CE E4EA 6 C P15EA 2000113000033 20001130 00033 EU 2000 11 30 AU000880 1 20000912 G 3250 5325012055 FLANGE PILATS PC12 PC12 7090550 EU LANDING GEAR STE LOOSE W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NOSE WHEEL STEERING SYSTEM BEARING RETAINER AND RETAINING BOLTS LOOSE. (X) 1 L 7 1 3T RT A78EU 2000113000034 20001130 00034 EU 2000 11 30 AU000881 1 20000810 G 2620 WIRE REIMS 406 F406 7535723 EU PWA PT6 PT6A112 52043 NE MCAULY 3G34C7 3GFR34C701 GL EXTINGUISHING SY MISINSTALLED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NR 2 FIRE BOTTLE SQUIB WIRING INCORRECTLY WIRED TO THE BOTTLE ARM/FIRING SWITCH. SUBMITTER STATED THIS WOULD HAVE PREVENTED OPERATION OF THE FIRE BOTTLE. SUSPECT MANUFACTURING ERROR. (X) 1 L 7 2 3T 3 T RT A54EU E4EA 5 C P60GL 2000113000035 20001130 00035 EA 2000 11 30 AU000882 2 20000914 G 7322 1041641 CARBURETOR LYC O360A3A PIPER PA28 PA28180 7102808 SO LYC O360 O360A3A 41514 EA SNSNCH 76E 76EM8 EA FUEL CONTROL/CAR FAULTY W K NONE E VIBRATION/BUFFET CR CRUISE 1 AU S 1361 (AUS) CARBURETOR PRIMARY VENTURI DISLODGED. VENTURI WAS A TWO-PIECE ITEM. (X) 1 L 7 1 3O 3 O 2A13 E286 5 N P4EA 2000113000036 20001130 00036 NE 2000 11 30 AU000883 2 20000710 G 7200 T700 ENGINE GE T700SERIES GE TC7TS T700T1C 30029 NE ENGINE WRONG PART W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) GENERAL ELECTRIC T700 GAS TURBINE ENGINES AS USED BY MILITARY HELICOPTERS WERE FOUND TO CONTAIN UNAPPROVED PARTS. GE T700 ENGINE COMES FROM THE SAME FAMILY OF ENGINES AS GE CT7 ENGINE. THIS DEFECT RECEIVED FROM ADF AS WARNING TO CIVIL IAN OPERATORS OF GE CT7SERIES ENGINES. FOLLOWING PARTS AFFECTED: NUT SELF-LOCKING - NSN 5310-01-102-8856 - GE P3031T29 . STUD SHOULDERED - NSN 5307-01-099-2481 - GE P4041T11P02. NUT SELF-LOCKING - NSN 5310-00-129-6126 - GE P/N R1180. ST UD SWIRL PLATE - NSN 53 07-01-235-7902 - GE P4076T45P02. W8 COUNTERBALANCE - NSN 2840-01-143-3372 - GE P/N 4069T98P04. TUBE OIL SUMP - NSN 4710-01-089-4109 - GE P4041T52P01. (X) 4 U E8NE 2001011101766 20010111 01766 EU 2001 1 11 AU000884 1 20000919 G 5610 NF20216246 WINDSHIELD BAG BAE146 BAE146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE COCKPIT CRACKED W O OTHER O OTHER NR NOT REPORTED 1 AU S (AUS) COPILOTS A WINDSHIELD OUTER PANE CRACKED. 2 H 7 4 4F 4 F RT A49EU E6NE 2001011101770 20010111 01770 EU 2001 1 11 AU000885 1 20000527 G 5751 RIB BAC 146 AVRO146RJ70A 1500095 EU AILERON DAMAGED W O OTHER C F.O.D. LD LANDING 1 AU S (AUS) RT AILERON DAMAGED DURING GROUND HANDLING. RIB 20 AND FAIRING DAMAGED. 2 H 7 4 4F RT A49EU 2001011101771 20010111 01771 EU 2001 1 11 AU000886 1 20000424 G 3234 HTE210014 MOTOR BAG BAE146 BAE146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE MLG FAULTY W O OTHER O OTHER NR NOT REPORTED 1 AU S 190GB189H (AUS) LANDING GEAR SELECTOR VALVE MOTOR FAULTY. WORKSHOP INVESTIGATION FOUND THE CLUTCH SLIPPING DUE TO WORN CLUTCH PADS AND INSUFFICIENT SPRING TENSION ON THE CLUTCH. 2 H 7 4 4F 4 F RT A49EU E6NE 2001011101804 20010111 01804 2001 1 11 AU000887 4 20000311 G 2370 9806005076 CVR BOEING 767 767204 NM GE CF6 CF680A 30025 NE COCKPIT FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) COCKPIT VOICE RECORDER (CVR) FAULTY. WORKSHOP INVESTIGATION FOUND INTERMITTENT FAILURE DUE TO TAPE DEPOSIT ON RECO RDING HEADS CAUSING LOW AUDIO ON TRACK 2. 2 L 7 2 4F 4 F RT A1NM E13NE 2001011101810 20010111 01810 EU 2001 1 11 AU000888 1 20000322 G 2450 503CA02F102Y1 CONTACTOR AIRBUS 320 A320211 3930320 EU CFMINT CFM56 CFM565A1 NE AC POWER DISTRIB FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) AC ESSENTIAL BUS FEED SWITCH CONTACTOR 3XC FAULTY. 2 L 7 2 4F 4 F RT A28NM E29NE 2001011101849 20010111 01849 2001 1 11 AU000889 4 20000714 G 3460 B397BAM0513 COMPUTER AIRBUS 320 A320211 3930320 EU CFMINT CFM56 CFM565A1 NE FLIGHT MANAGE FAULTY W O OTHER J WARNING INDICATION NR NOT REPORTED 1 AU S 5454ANSCCN44 (AUS) FLIGHT AUGMENTATION COMPUTER (FAC) SUSPECT FAULTY. WORKSHOP INSPECTION COULD NOT FAULT ITEM. 2 L 7 2 4F 4 F RT A28NM E29NE 2001011101850 20010111 01850 NM 2001 1 11 AU000890 1 20000724 G 2721 658D1003 ACTUATOR BOEING 767 767277 NM GE CF6 CF680A 30025 NE RUDDER TAB FAULTY W O OTHER F FLT CONT AFFECTED DE DESCENT 1 AU S (AUS) RUDDER TRIM ACTUATOR FAULTY. WORKSHOP INVESTIGATION COULD FIND NO FAULTS. 2 L 7 2 4F 4 F RT A1NM E13NE 2001011101983 20010111 01983 NM 2001 1 11 AU000891 1 20000316 G 2422 7077603 INVERTER BOEING 767 767277 NM GE CF6 CF680A 30025 NE AC SYSTEM FAULTY W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 AU S 37726 (AUS) STANDBY STATIC INVERTER FAULTY. WORKSHOP INVESTIGATION FOUND THAT TRANSISTORS Q3 TO Q10 WERE SHORT CIRCUITED OR OP EN CIRCUITED WITH THE BASE BIAS RESISTORS BLOWN OPEN. 2 L 7 2 4F 4 F RT A1NM E13NE 2000112100221 20001121 00221 SO 2000 11 21 AU000892 2 20000831 G 8520 6525396 CRANKCASE CONT CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO MCAULY 3AF32C 3AF32C87 GL ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 2093 565547 (AUS) RT ENGINE CRANKCASE CRACKED IN THE AREA OF NR 1 CYLINDER UPPER FORWARD STUD. NR 1 CYLINDER FORWARD LOWER BASE STU D PN 646140-1 SHEARED. THE CRACK WAS FOUND APPROXIMATELY 60 HOURS PREVIOUSLY DURING ROUTINE MAINTENANCE, BUT WAS WITHIN LIMITS (LESS THAN 50.8 MM OR 2 INCHES). THE CRACK HAS NOW GROWN BY APPROXIMATELY 12.7 MM (0.5 INCH) WITH ADDITIONAL CRA CKS APPROXIMATELY 6.35 MM (0.25 INCH)CROSSING THE END OF THE MAIN CRACK. (X) 1 L 7 2 3O 3 O 3A10 E5CE 5 C P22EA 2000112100222 20001121 00222 EA 2000 11 21 AU000893 2 20000826 G 8520 25015 STUD LYC PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL ENGINE SHEARED W K NONE E K VIBRATION/BUFFET FLUID LOSS IN INSP/MAINT 1 AU S (AUS) LEFT ENGINE NR 2 CYLINDER HOLD-DOWN STUDS SHEARED. THE TWO THROUGH-BOLTS WERE INTACT. (X) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2000112100223 20001121 00223 SO 2000 11 21 AU000894 1 20000921 G 7920 LW13388 GASKET LYC PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL ENGINE DETERIORATED W K NONE E K VIBRATION/BUFFET FLUID LOSS IN INSP/MAINT 1 AU S (AUS) LEFT ENGINE OIL FILTER GASKET DETERIORATED AND LEAKING. ATTACHMENT STUD ALSO LOOSE. (X) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2000112100224 20001121 00224 CE 2000 11 21 AU000895 1 20000917 G 3520 1013840281 SWITCH BEECH 200 B200C 1152924 CE PWA PT6 PT6A42 52043 NE PAX OXYGEN MISINSTALLED W K NONE O OTHER CL CLIMB 1 AU S (AUS) CABIN ALTITUDE SENSE SWITCH INCORRECTLY WIRED. CABIN OXYGEN MASKS FAILED TO CORRECTLY DEPLOY. (X) 1 L 7 2 4T 4 T A24CE E4EA 2000112100225 20001121 00225 EA 2000 11 21 AU000897 2 20000922 G 8500 ENGINE LYC O235L2C CESSNA 150 A152 2071836 CE LYC O235 O235L2C 41505 EA MCAULY 1A103 1A103TCM GL ENGINE POWER LOSS W K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CR CRUISE 1 AU S (AUS) ENGINE LOST POWER. GROUND RUN CARRIED OUT WITH NO FAULT FOUND. (X) 1 H 7 1 3O 3 O 3A19 E223 5 N P50GL 2001011100620 20010111 00620 EU 2001 1 11 AU000898 1 20000903 G 3297 WIRE ROPE FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU NLG STEERING FAILED W D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 AU S (AUS) NOSE WHEEL STEERING CABLE FAILED. 2 L 7 2 4F 4 F RT A20EU E2EU 2001011101985 20010111 01985 EU 2001 1 11 AU000899 1 20000909 G 2910 58137 MOTOR FOKKER F28 F28MK4000 4990810 EU RROYCE SPEY SPEY55515 54521 EU HYD SYSTEM LEAKING W D RETURN TO BLOCK K J FLUID LOSS WARNING INDICATION TX TAXI/GRND HDL 1 AU S 1595 (AUS) FLAP HYDRAULIC MOTOR LEAKING. LOSS OF UTILITY HYDRAULIC SYSTEMFLUID. 2 L 7 2 4F 4 F RT A20EU E2EU 2001011101986 20010111 01986 2001 1 11 AU000900 4 20000912 G 3442 20412170413 TRANSCEIVER FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU WEATHER RADAR FAULTY W D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 AU S 4452 (AUS) WEATHER RADAR TRANSCEIVER FAULTY. 2 L 7 2 4F 4 F RT A20EU E2EU 2001011101987 20010111 01987 EU 2001 1 11 AU000901 1 20000910 G 3610 DUCT FOKKER F28 F28MK4000 4990810 EU RROYCE SPEY SPEY55515 54521 EU PNEUMATIC SYSTEM LEAKING W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) TAIL DUCT ASSEMBLY LEAKING. 2 L 7 2 4F 4 F RT A20EU E2EU 2001011101988 20010111 01988 EU 2001 1 11 AU000902 1 20000910 G 2910 58137 MOTOR FOKKER F28 F28MK4000 4990810 EU RROYCE SPEY SPEY55515 54521 EU HYD SYSTEM LEAKING W D RETURN TO BLOCK K J FLUID LOSS WARNING INDICATION TX TAXI/GRND HDL 1 AU S 1595 (AUS) FLAP HYDRAULIC MOTOR LEAKING. LOSS OF HYDRAULIC FLUID FROMUTILITY SYSTEM. 2 L 7 2 4F 4 F RT A20EU E2EU 2000112800267 20001128 00267 GL 2000 11 28 AU000903 2 20000907 G 7314 PE132 DRIVE SHAFT SUNDSTRANDEM 5000950D BELL 206 206L1 1182107 SW ALLSN 250C 250C30 03013 GL ENGINE FUEL PUMP SHEARED W K NONE E VIBRATION/BUFFET TO TAKEOFF 1 AU S 974 PE132 (AUS) ENGINE DRIVEN FUEL PUMP INPUT DRIVE SHAFT SHEARED. (X) 1 G 7 1 3U 3 U H2SW E1GL 2000112800268 20001128 00268 SW 2000 11 28 AU000904 1 20000812 G 5314 212030169107 PANEL BELL BELL 212 212 1181420 SW PWA PT6T PT6T3B 52045 NE FUSELAGE MAIN KE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 30860 (AUS) MAIN BEAM PANEL CRACKED AT STA 166. CRACK LENGTH 100 MM (4 INCHES). FOUND DURING INSPECTION AND REPLACEMENT OF CR ACKED MAIN BEAM CAP IAW BHT TB 212-88-106. (X) 1 G 7 1 4U 4 U H4SW E22EA 2001011101989 20010111 01989 NM 2001 1 11 AU000905 1 20000920 G 2820 MS29513330 SEAL BOEING 747 747438 NM GE CF6 CF680C2* GL FUEL DIST DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NR 4 ENGINE MAIN FUEL FEED PIPE COUPLING BACKUP WASHER PROTRUDING FROM COUPLING AND O-RING SEAL DAMAGED. FUEL LEAK ING. 2 L 7 4 4F 4 F RT A20WE E23EA 2001011101990 20010111 01990 2001 1 11 AU000906 4 20000918 G 3445 ANTENNA DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE TCAS MISINSTALLED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) TCAS ANTENNA MOUNTED ON THE TOP OF THE FUSELAGE LEAKING AIR THROUGH THE SEALANT. DURING REMOVAL OF THE ANTENNA IT WAS FOUND THAT THE TWO REAR SCREWS HAD LOOSE NUTS AND WASHERS INSTEAD OFANCHOR NUTS. THE RH FRONT SCREW WAS ALSO SPINNIN G IN THE ANCHOR NUT. ON REASSEMBLY OF THE ANTENNA IT WAS FOUND THAT THE REARSCREWS WERE TOO LONG AND BOTTOMED OUT LEAVIN G THE ANTENNA LOOSE ON THE MOUNT PLATE. PERSONNEL/MAINTENANCE ERROR. UNAPPROVED PART. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2000112100226 20001121 00226 GL 2000 11 21 AU000907 1 20000916 G 3260 6409231 CONNECTOR AMTRNC LANCAIR320 AMTR MK1 MK1 05620JY GL LANDING GEAR POS DISCONNECTED W K NONE O P OTHER NO WARNING INDICATION DE DESCENT 1 AU S (AUS) LEFT MAIN LANDING GEAR DOWNLOCK MICROSWITCH WIRE SPADE CONNECTOR DISCONNECTED FROM SWITCH LUG. (X) 1 H 7 1 3O NC EXPA1H71 2000112100227 20001121 00227 NE 2000 11 21 AU000908 2 20000702 G 7260 311178001 DUCT PWA PWA PT6 PT6A34AG 52053 NE HARTZL HCB3T HCB3TN3 GL TURBINE SECTION CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) TURBINE DUCT ASSEMBLY CRACKED LONGITUDINALLY WITH A SECTION BROKEN OUT. SUBMITTER SUSPECTED CAUSED BY VIBRATION DU E TO WORN SPLINE ON PROPELLER REDUCTION GEARBOX HOUSING ASSEMBLY PN 3044254-01. (X) 4 T E4EA 6 C P15EA 2000112100228 20001121 00228 NE 2000 11 21 AU000909 2 20000906 G 7260 311178001 DUCT PWA PWA PT6 PT6A34AG 52053 NE HARTZL HCB3T HCB3TN3 GL TURBINE SECTION CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) TURBINE DUCT ASSEMBLY CRACKED. SAME PROBLEM HAD OCCURRED 21.6 HOURS PREVIOUSLY (REF: AU000908). INVESTIGATION F OUND THE FOLLOWING PROBLEMS: 1. SECOND STAGE SUNGEAR HEAVY WEAR AND SPALLING. 2. SECOND STAGE PLANETARY GEARS (5OFF) HEAVY WEAR AND SPALLING. 3. FRONT REDUCTION GEARBOX CASE NR 5 BEARING JOURNAL WORN (LOOSE BEARING). 4. FIRST STAGE CARRIED OVER LIMITS ON BALANCE. 5. ZERO TORQUE ON NR 5 BEARING RETAINING BOLTS. (X) 4 T E4EA 6 C P15EA 2001011101991 20010111 01991 SW 2001 1 11 AU000910 1 20000924 G 5730 PANEL FRCHLD SA227 SA227DC 3377521 SW MCAULY 4HFR34 4HFR34C652 NE LT WING MISREPAIRED W K NONE W K INADEQUATE Q C FLUID LOSS IN INSP/MAINT 1 AU S (AUS) FUEL TANK PANEL LEAKING. INVESTIGATION FOUND THAT AN UNAPPROVED REPAIR HAD BEEN CARRIED OUT BY SPLICINGINTO WIRING LOOMS ON EACH SIDE OF THE PANEL WITH THE WIRING GOING THROUGH A HOLE IN THE PANEL. THE SPLICES USED WERE UNSEALED CRIMP S USED WITHIN THE FUEL TANK WET AREA. PERSONNEL/MAINTENANCE ERROR. UNAPPROVED REPAIR. UNAPPROVED PART. 2 L 7 2 4T RT A18SW 6 C 3PNE 2001011101992 20010111 01992 NM 2001 1 11 AU000911 1 20000608 G 3244 6442 TIRE BOEING 737 73733A 1384673 NM LT MLG FAILED W O OTHER O OTHER NR NOT REPORTED 1 AU S (AUS) LT MAIN LANDING GEAR NR 2 TIRE FAILED DUE TO FATIGUE AND SEPARATION OF THE SIDEWALL AREA. LT MLG NR 1 TIRE FAILED DUE TO OVERLOAD AS A CONSEQUENCE OF THE FAILURE OF NR 2 TIRE. 2 L 7 2 4F RT A16WE 2000112100229 20001121 00229 EU 2000 11 21 AU000912 1 20000706 G 3222 604201011 STRUT REIMS 406 F406 EU PWA PT6 PT6A112 52043 NE MCAULY 3G34C7 3GFR34C701 GL NOSE/TAIL LDNG FAILED W K NONE O OTHER LD LANDING 1 AU S (AUS) NOSE LANDING GEAR OLEO OVER EXTENDED ALLOWING TORQUE LINKS TO INVERT. CAUSED BY OLEO UPPER BEARING LOOSENING FROM PISTON BARREL. (X) 1 L 7 2 3T 3 T RT A54EU E4EA 5 C P60GL 2001011101993 20010111 01993 EA 2001 1 11 AU000913 1 20000821 G 3250 DCL44299 LEVER CNDAIR CL600 CL6002B19 EA STEERING TILLER STUCK W D RETURN TO BLOCK F FLT CONT AFFECTED TX TAXI/GRND HDL 1 AU S (AUS) NOSE WHEEL STEERING SYSTEM TILLER WOULD NOT RETURN TO THE DETENT POSITION AFTER RELEASE. SUSPECT CAUSED BY EXCESSI VE FRICTION ON TILLER SHAFT. 2 L 7 2 4F RT A21EA 2001011101994 20010111 01994 NE 2001 1 11 AU000914 3 20000921 G 6114 660710325 BOLT SAAB SF340 340B 7860101 EU GE CT7TP CT79B 30030 NE ROTOL R390 R3904123F27 NE PROPELLER HUB UNDERTORQUED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) PROPELLER HUB BOLTS NR 2, NR 3 AND NR 6 UNDERTORQUED. FOUND DURING INSPECTION IAW DOWTY SB SF340-61-96. SUSPECT CA USED BY EXCESSIVE SEALANT BETWEEN HUB HALVES. 2 L 7 2 4T 4 T RT A52EU E8NE 6 C P31NE 2000112100230 20001121 00230 SO 2000 11 21 AU000915 1 20000925 G 2731 4173405 CONTROL CABLE PIPER PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA HARTZL HCE2Y HCE2YK2 GL ELEVATOR TAB CON BROKEN W O OTHER F FLT CONT AFFECTED CL CLIMB 1 AU S (AUS) FORWARD ELEVATOR TRIM CABLE BROKEN AT TRIM SERVO. LOSS OF TENSION CAUSED CABLE ON TRIM CABLE DRUM TO UNWIND AND J AM THE DRUM. INVESTIGATION FOUND THAT THE CABLE HAD BEEN INCORRECTLY INSTALLED CAUSING THE CABLE TO BE SHORT AT THE TUR N BARREL CONNECTION. AN UNAPPROVED SHORT SECTION OF CABLE HAD BEEN INSTALLED TO MAKE UP THE CABLE LENGTH. UNAPPROVED R EPAIR/PART. (X) 1 L 7 2 3O 3 O A20SO E14EA 5 C P9EA 2000112100231 20001121 00231 SO 2000 11 21 AU000916 1 20000927 G 3260 487862 SWITCH PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL LANDING GEAR POS INTERMITTENT W K NONE O P OTHER NO WARNING INDICATION LD LANDING 1 AU S (AUS) NOSE LANDING GEAR MICROSWITCH INTERMITTENT IN OPERATION. (X) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001011101995 20010111 01995 NE 2001 1 11 AU000918 3 20000912 G 6111 66071328710 BLADE SAAB SF340 SF340A 7850100 EU GE CT7TP CT75A2 30030 NE ROTOL R389 R3894123F25 NE PROPELLER SPLIT W K NONE O OTHER IN INSP/MAINT 1 AU S 4679 (AUS) RT PROPELLER NR 1 BLADE TRAILING EDGE SPLIT FROM THE BLADE TIP. LENGTH OF SPLIT 355.6MM (14IN). 2 L 7 2 4T 4 T RT A52EU E8NE6 6 C P30NE 2001011101996 20010111 01996 WP 2001 1 11 AU000919 2 20000926 G 7261 31039081 TUBE FRCHLD SA227 SA227DC 3377521 SW GARRTT TPE331 TPE33112UHR WP MCAULY 4HFR34 4HFR34C652 NE LT PROP GOVERNOR CRACKED W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 AU S 870212 (AUS) LT PROPELLER GOVERNOR RESET TUBE CRACKED AT FLARE. LOSS OFAPPROXIMATELY THREE LITRES OF ENGINE OIL. TUBE IS A PER SBTPE331-A77-0072 ITEM. 2 L 7 2 4T 4 T RT A18SW E4WE 6 C 3PNE 2001011100800 20010111 00800 NE 2001 1 11 AU000920 3 20000922 G 6114 660710325 BOLT SAAB SF340 340B 7860101 EU GE CT7TP CT79B 30030 NE ROTOL R390 R3904123F27 NE PROPELLER HUB MISINSTALLED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) PROPELLER HUB BOLT INCORRECT TORQUE. FOUND DURING INSPECTION IAWDOWTY SB SF340-61-96. SUSPECT CAUSED BY EXCESSIVE SEALANT BETWEEN HUB HALVES. 2 L 7 2 4T 4 T RT A52EU E8NE 6 C P31NE 2001011100802 20010111 00802 EA 2001 1 11 AU000921 1 20000918 G 5230 HANDLE CNDAIR CL600 CL6002B19 EA CARGO DOOR UNLOCKED W D RETURN TO BLOCK W INADEQUATE Q C TX TAXI/GRND HDL 1 AU S (AUS) CARGO DOOR WARNING. ENGINEER FOUND DOOR HANDLE EXTENDED. INVESTIGATION COULD FIND NO FAULT WITH HANDLE OR WARNING SYSTEM. 2 L 7 2 4F RT A21EA 2001011100805 20010111 00805 2001 1 11 AU000922 4 20000918 G 3444 WARNING SYSTEM SAAB SF340 SF340A 7850100 EU GE CT7TP CT75A2 30030 NE ROTOL R354 R3544123F13 NE GROUND PROXIMITY FAULTY W O OTHER N FALSE WARNING DE DESCENT 1 AU S (AUS) GROUND PROXIMITY WARNING SYSTEM (GPWS) FALSE WARNING. INVESTIGATION COULD FIND NO FAULTS. 2 L 7 2 4T 4 T RT A52EU E8NE6 6 C P61GL 2000112100232 20001121 00232 SO 2000 11 21 AU000924 2 20000907 G 8530 630046 PISTON PIN CONT CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO MCAULY 3AF32C 3AF32C93 GL ENGINE CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S 277299R (AUS) LEFT ENGINE, ALL SIX PISTON PINS SEVERELY CORRODED. (X) 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2000112800358 20001128 00358 SW 2000 11 28 AU000925 1 20001001 G 6322 209062502101 BEARING PWA BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE COOLING FAN MISALIGNED W K NONE E VIBRATION/BUFFET CR CRUISE 1 AU S 62338 (AUS) NR 2 ENGINE OIL COOLER BLOWER BEARING WAS MISALIGNED CAUSING THE BLOWER SHAFT TO SHEAR. (X) 1 G 7 2 4U 4 U H4SW E22EA 2000113000069 20001130 00069 SO 2000 11 30 AU000926 2 20000921 G 8520 641250 SEAL CONT O520 IO520* 17032 SO RECIPROCATING EN FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) CRANKSHAFT SEAL INNER LIP DAMAGED. SEAL WAS A NEW ITEM RECEIVED FROM SUPPLIER. (X) 3 O E5CE 2000112100233 20001121 00233 CE 2000 11 21 AU000927 1 20000925 G 2821 07560051 FILTER CESSNA 150 150M 2071830 CE CONT O200 O200A 17020 SO MCAULY 1A102 1A102OCM GL ACFT FUEL FILTER CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUEL FILTER BOWL CONTAMINATED WITH ALUMINIUM HYDROXIDE. FILTER BOWL CORRODED. (X) 1 H 7 1 3O 3 O 3A19 E252 5 N P918 2000112100234 20001121 00234 EU 2000 11 21 AU000928 1 20000927 G 5741 D22200361 FITTING WSK M18A M18A EU WING, FUSELAGE A CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LEFT OUTER WING BOTTOM ATTACHMENT FITTING PITTED. (X) 1 L 7 1 3O NC A47EU 2000112100235 20001121 00235 EU 2000 11 21 AU000929 1 20000927 G 5741 D22200361 FITTING WSK M18A M18A EU WING, FUSELAGE A CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RIGHT OUTER WING BOTTOM ATTACHMENT FITTING CRACKED AND PITTED. (X) 1 L 7 1 3O NC A47EU 2000112100236 20001121 00236 SO 2000 11 21 AU000930 2 20000920 G 7414 103493505 IMPULSE COUPLING CONT CESSNA 207 207 2073602 CE CONT O520 IO520F 17032 SO MCAULY D3A34 D3A34C404 GL MAGNETO/DIST WORN W K NONE O OTHER IN INSP/MAINT 1 AU S 491 (AUS) RIGHT MAGNETO IMPULSE COUPLING WORN EXCESSIVELY. (X) 1 H 7 1 3O 3 O A16CE E5CE 5 C P47GL 2000112100237 20001121 00237 CE 2000 11 21 AU000931 1 20000912 G 2822 1419 PUMP AIRBORNE IC712 CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE FUEL BOOST PUMP FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S 1419 (AUS) FUEL BOOST PUMP WIRES BROKEN AT BULKHEAD CANNON PLUG. (X) 1 L 7 2 4F 4 F A22CE E1NE 2000112100238 20001121 00238 CE 2000 11 21 AU000932 1 20000912 G 2810 5500347 FUEL TANK CESSNA 550 CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE FUEL STORAGE LEAKING W K NONE O K OTHER FLUID LOSS IN INSP/MAINT 1 AU S 5500347 (AUS) LEFT WING INBOARD HEATED LEADING EDGE ANTI-ICE PANEL ATTACHMENT SCREW HOLES LEAKING FUEL FROM TANKS. FUEL TANK AL SO LEAKING IN AREA BEHIND ANTI-ICE PANEL. (X) 1 L 7 2 4F 4 F A22CE E1NE 2000112100239 20001121 00239 SO 2000 11 21 AU000933 2 20000927 G 7322 O-RING CONT 6405632 PAC CT4 CT4A 05623UC GL CONT O360 IO360HB 17025 SO HARTZL HCC2Y BHCC2YF1 GL FUEL CONTROL/CAR WRONG PART W K NONE O OTHER IN INSP/MAINT 1 AU S 175 G269601NZ (AUS) THROTTLE METERING PLATE O RING SEAL NOT USED IN THIS LOCATION. NO REFERENCE TO THIS O RING IN THE PARTS CATALOGUE . UNAPPROVED PART. (X) 1 Q 7 1 3I 3 O RT A9PC E1CE 5 C P920 2001011100807 20010111 00807 EU 2001 1 11 AU000934 1 20000919 G 5610 NF20216246 WINDSHIELD BAG BAE146 BAE146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE COCKPIT CRACKED W A UNSCHED LANDING O OTHER CR CRUISE 1 AU S (AUS) WINDSHIELD CRACKED. 2 H 7 4 4F 4 F RT A49EU E6NE 2001011100841 20010111 00841 2001 1 11 AU000935 4 20000916 G 3460 1796001020012 CDU BAG BAE146 BAE146100A 1500260 EU LYC ALF502 ALF502R5 41580 NE FLIGHT MANAGE FAULTY W C ABORTED TAKEOFF O OTHER TO TAKEOFF 1 AU S (AUS) GPS CENTRAL DATA UNIT (CDU) LOCKED UP. GPS WOULD NOT TRACK. 2 H 7 4 4F 4 F RT A49EU E6NE 2001011100844 20010111 00844 EU 2001 1 11 AU000936 1 20000716 G 5752 TRIM TAB BAG BAE146 BAE146100A 1500260 EU LYC ALF502 ALF502R5 41580 NE AILERON DAMAGED W O OTHER O OTHER LD LANDING 1 AU S (AUS) LT AILERON TRIM TAB DAMAGED DURING GROUND OPERATION. 2 H 7 4 4F 4 F RT A49EU E6NE 2001011100846 20010111 00846 NE 2001 1 11 AU000937 2 20000929 G 7260 1081 BEARING BOEING 717 717200 1383700 NM RROYCE BR700 BR700715A130 NE ENGINE FAILED W O OTHER K J FLUID LOSS WARNING INDICATION LD LANDING 1 AU S (AUS) LT ENGINE ACCESSORY GEARBOX DEDICATED DRIVE GENERATOR BALLBEARING FAILED. METAL CONTAMINATION OF GEARBOX. 2 L 7 2 4F 4 F TR A6WE E00061EN 2001011100847 20010111 00847 EU 2001 1 11 AU000938 1 20000905 G 7602 82GR03291100888 CONTROL CABLE LYC O360A1F6 GROB G115 G115C 1660303 EU LYC O360 O360A1F6 41514 EA MIXTURE CONTROL FAILED W A UNSCHED LANDING F FLT CONT AFFECTED CR CRUISE 1 AU S (AUS) MIXTURE CONTROL CABLE FAILED AT SWAGED END FITTING. 1 L 7 1 3O 3 O NT A57EU E286 2001011100873 20010111 00873 EU 2001 1 11 AU000939 1 20001001 G 2750 CIRCUIT BREAKER BAG JETSTM JETSTM3201 1500217 EU MCAULY 4HFR34 4HFR34C653 NE TE FLAP CONTROL TRIPPED W C ABORTED TAKEOFF F FLT CONT AFFECTED TO TAKEOFF 1 AU S (AUS) FLAP CONTROL CIRCUIT BREAKER TRIPPED. INVESTIGATION COULD FIND NO FAULT. 2 L 7 2 4T RT A56EU 6 C 3PNE 2001011100874 20010111 00874 NM 2001 1 11 AU000940 1 20000926 G 3260 TARGET DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE RT MLG LOOSE W O OTHER N FALSE WARNING CL CLIMB 1 AU S (AUS) RT MAIN LANDING GEAR PROXIMITY SENSOR TARGET LOOSE. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2000112100240 20001121 00240 SO 2000 11 21 AU000941 1 20001002 G 2434 WIRE PIPER PA30 PA39 7103902 SO LYC O320 IO320B1A 41508 EA HARTZL HCE2Y HCE2YL2 GL DC GENERATOR-ALT CRACKED W K NONE H ELECT. POWER LOSS-50 PC CL CLIMB 1 AU S (AUS) RIGHT ALTERNATOR FIELD WIRING CRACKED ALLOWING SHORT CIRCUIT. (X) 1 L 7 2 3O 3 O A1EA 1E12 5 C P9EA 2001011100876 20010111 00876 NM 2001 1 11 AU000942 1 20000205 G 2530 DPXAMA2634P PLUG BOEING 737 737377 NM GALLEY BURNED W O OTHER B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 AU S 6322 (AUS) AFT GALLEY NR 3 OVEN TIMER POWER PINS BURNT AT TIMER MODULE PLUG. 2 L 7 2 4F RT A16WE 2001011100878 20010111 00878 EU 2001 1 11 AU000943 1 20000904 G 7722 WL706RSA4 INDICATOR BAG BAE146 BAE146100A 1500260 EU LYC ALF502 ALF502R5 41580 NE NR 2 ENGINE FLUCTUATES W A UNSCHED LANDING E VIBRATION/BUFFET CL CLIMB 1 AU S (AUS) NR 2 ENGINE EGT INDICATOR FLUCTUATING. 2 H 7 4 4F 4 F RT A49EU E6NE 2001011100879 20010111 00879 NM 2001 1 11 AU000944 1 20001002 G 3350 CONNECTOR DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE EMERGENCY LIGHT UNAPPROVED PART W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) INCORRECT CONNECTORS USED FOR EMERGENCY LIGHTS LOCATED AT LT AND RT UNDERWING EXITS. CONNECTORS APPEAR TO BE COMME RCIAL TELEPHONEMODULAR ITEMS. PERSONNEL/MAINTENANCE ERROR. UNAPPROVED PART. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2000112100241 20001121 00241 CE 2000 11 21 AU000945 1 20000928 G 2150 7547511 VALVE CESSNA 441 441 2076020 CE HARTZL HCB3T HCB3TN5 GL CABIN COOLING SY STUCK W K NONE O OTHER CR CRUISE 1 AU S FJ43426 (AUS) AIR CYCLE MACHINE BYPASS VALVE STICKING IN THE ''OPEN'' POSITION. (X) 1 L 7 2 3T RT A28CE 6 C P15EA 2000112100242 20001121 00242 EA 2000 11 21 AU000946 2 20000818 G 8520 5015 STUD LYC PIPER PA31 PA31 7103102 SO LYC O540 TIO540A1A 41532 EA HARTZL HCE3Y HCE3YR2 GL ENGINE SHEARED W K NONE E VIBRATION/BUFFET DE DESCENT 1 AU S L12061 (AUS) NR 4 CYLINDER MOUNT STUDS (3OFF) SHEARED. (X) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2000112100243 20001121 00243 CE 2000 11 21 AU000947 1 20000929 G 5312 BULKHEAD CESSNA 206 U206F 2073333 CE CONT O520 IO520F 17032 SO MCAULY 3A32C D3A32C90 GL FUSEMAIN BULKHD CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FORWARD TAIL BULKHEAD CRACKED IN THE AREA OF THE HORIZONTAL STABILIZER ATTACHMENT POINT. (X) 1 H 7 1 3O 3 O A4CE E5CE 5 C P21EA 2001011100881 20010111 00881 EU 2001 1 11 AU000948 1 20000928 G 2611 7211121100 SMOKE DETECTOR SAAB SF340 SF340A 7850100 EU GE CT7TP CT75A2 30030 NE ROTOL R354 R3544123F13 NE CARGO BAY FAULTY W D RETURN TO BLOCK N FALSE WARNING TX TAXI/GRND HDL 1 AU S (AUS) CARGO SMOKE DETECTOR FAULTY. FIRE BOTTLE ACTIVATED. INVESTIGATION FOUND NO EVIDENCE OF FIRE. 2 L 7 2 4T 4 T RT A52EU E8NE6 6 C P61GL 2001011100883 20010111 00883 EA 2001 1 11 AU000949 1 20000929 G 2740 BEARING CNDAIR CL600 CL6002B19 EA STABILIZER STIFF W A UNSCHED LANDING F FLT CONT AFFECTED CL CLIMB 1 AU S (AUS) HORIZONTAL STABILISER PIVOT BEARINGS BINDING CAUSING FAILURE OF THE STABILISER TRIM ACTUATOR. 2 L 7 2 4F RT A21EA 2001011100904 20010111 00904 NM 2001 1 11 AU000950 1 20000918 G 3244 319K281 TIRE DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE RT MLG LEAKING W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT OUTBOARD WHEEL TIRE LEAKING FROM LOWER SIDEWALL CASING VENTS. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2000113000070 20001130 00070 CE 2000 11 30 AU000951 1 20001002 G 3230 HYDRAULIC SYSTEM CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO MCAULY 3AF32C 3AF32C505 GL L/G RETRACT CONTAMINATED W K NONE O J OTHER WARNING INDICATION LD LANDING 1 AU S (AUS) LANDING GEAR HYDRAULIC SYSTEM CONTAMINATED WITH O RING AND TEFLON SEAL MATERIAL. CONTROL VALVE CONTAMINATED. LEF T DOWNLOCK SWITCH FAILED. NOSE LANDING GEAR ACTUATOR FAULTY. (X) 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2000113000071 20001130 00071 NM 2000 11 30 AU000952 1 20000801 G 3250 450052001 COLLAR PIPER PA60 PA60600 7106001 NM LYC O540 IO540K1J5 41532 EA LANDING GEAR STE WRONG PART W K NONE O OTHER TO TAKEOFF 1 AU S (AUS) NOSE LANDING GEAR STEERING COLLAR FAILED AT ACTUATOR ATTACHMENT POINT. CONNECTING BOLT WAS INCORRECT PART. BOLT SHEARED. UNAPPROVED PART. (X) 1 M 7 2 3O 3 O RT A17WE 1E4 2000113000072 20001130 00072 NE 2000 11 30 AU000953 2 20000905 G 8520 39785C PIN PWA 128502 DHAV DHC2 DHC2* 2800108 EA PWA R985 R985AN14B 52008 NE MASTER ROD FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S 835 (AUS) MASTER ROD LINK PINS (8OFF) ELECTROPLATED USING AN UNAPPROVED PROCESS. NO EVIDENCE OF UNSERVICEABILITY FOUND. U NAPPROVED PART. (X) 1 H 7 1 3R 3 R A806 5E1 2000113000073 20001130 00073 NE 2000 11 30 AU000954 2 20000905 G 8520 39785C PIN PWA 128502 DHAV DHC2 DHC2* 2800108 EA PWA R985 R985AN14B 52008 NE ENGINE FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S 555 RE12449 (AUS) MASTER ROD LINK PINS (8OFF) ELECTROPLATED USING AN UNAPPROVED PROCESS. NO EVIDENCE OF UNSERVICEABILITY FOUND. UN APPROVED PART. (X) 1 H 7 1 3R 3 R A806 5E1 2000113000074 20001130 00074 EA 2000 11 30 AU000955 2 20000824 G 8520 LW16511 CAMSHAFT LYC O320H2AD CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA MCAULY 1C160 1C160DTM GL ENGINE SPALLED W K NONE O OTHER IN INSP/MAINT 1 AU S L258676 (AUS) CAMSHAFT LOBES AND ASSOCIATED LIFTERS SPALLED, PITTED, AND WORN. (X) 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2000113000075 20001130 00075 SO 2000 11 30 AU000956 2 20000907 G 8530 630046 PISTON PIN CONT CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO MCAULY 3AF32C 3AF32C93 GL ENGINE CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S 277299R (AUS) LEFT ENGINE PISTON PINS (6OFF) SEVERELY CORRODED. (X) 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2000112800359 20001128 00359 NM 2000 11 28 AU000957 1 20000930 G 6310 A1902 BELT ROBSIN R22 R22BETA NM ENGINE/TRANS STRETCHED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE TO TRANSMISSION DRIVE BELTS WERE STRETCHED AFTER THIRTEEN HOURS OF OPERATION. BELTS DID NOT COME OFF PULLE YS. (X) 1 G 7 1 3O H10WE 2000113000076 20001130 00076 EA 2000 11 30 AU000958 1 20000923 G 5710 FRAME DHAV DHC2 DHC2* 2800108 EA PWA R985 R985AN14B 52008 NE HAMSTD 2D 2D30 NE WING MAIN FRAME DAMAGED W K NONE O OTHER LD LANDING 1 AU S (AUS) LEFT WING DAMAGED DURING HEAVY LANDING. (X) 1 H 7 1 3R 3 R A806 5E1 5 C P206 2001011100906 20010111 00906 EU 2001 1 11 AU000960 1 20001002 G 3260 387 BULB SAAB SF340 340B 7860101 EU GE CT7TP CT79B 30030 NE ROTOL R375 R3754123F21 NE MLG INDICATOR FAILED W O OTHER L NO TEST LD LANDING 1 AU S (AUS) LT MAIN LANDING GEAR LIGHT BULB BLOWN. 2 L 7 2 4T 4 T RT A52EU E8NE 6 C P17NE 2001011100911 20010111 00911 EU 2001 1 11 AU000962 1 20000929 G 7712 522948 INDICATOR SAAB SF340 SF340A 7850100 EU GE CT7TP CT75A2 30030 NE ROTOL R354 R3544123F13 NE BMEP/TORQUE STUCK W C ABORTED TAKEOFF N FALSE WARNING TO TAKEOFF 1 AU S (AUS) RT ENGINE TORQUE GAUGE FAILED. INVESTIGATION FOUND THAT THE GAUGE WAS STICKING AT APPROXIMATELY 45 PERCENT BEFORE GOING TO FULLSCALE INDICATION. 2 L 7 2 4T 4 T RT A52EU E8NE6 6 C P61GL 2001011100912 20010111 00912 EA 2001 1 11 AU000963 1 20000925 G 2421 755469D IDG CNDAIR CL600 CL6002B19 EA AC GENERATOR FAILED W A UNSCHED LANDING H J ELECT. POWER LOSS-50 PC WARNING INDICATION CR CRUISE 1 AU S 09192961 (AUS) NR 1 INTEGRATED DRIVE GENERATOR (IDG) FAILED. 2 L 7 2 4F RT A21EA 2001011100936 20010111 00936 2001 1 11 AU000964 4 20001004 G 3418 2566A27 VANE FOKKER F28 F28MK0100 4990807 EU STALL WARNING FAULTY W C ABORTED TAKEOFF N FALSE WARNING TO TAKEOFF 1 AU S (AUS) LT STALL VANE FAULTY. 2 L 7 2 4F RT 2000113000077 20001130 00077 CE 2000 11 30 AU000965 1 20000920 G 3230 3682001115 ROD BEECH BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO L/G RETRACT CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NOSE LANDING GEAR RETRACTION ROD CRACKED IN TWO POSITIONS 180 DEGREES APART AND RUNNING LENGTHWISE FROM UNDER THE LOCKNUT. CRACK LENGTH 6.35 MM (0.25 INCH). ITEM WAS ALSO IDENTIFIED AS AN UNAPPROVED PART. (X) 1 L 7 2 3O 3 O 3A16 E5CE 2000113000078 20001130 00078 CE 2000 11 30 AU000966 1 20000905 G 2932 98087 PRESSURE SWITCH BEECH 200 B200C 1152924 CE PWA PT6 PT6A42 52043 NE HYD PRESSURE FAULTY W K NONE O OTHER TO TAKEOFF 1 AU S (AUS) HYDRAULIC PRESSURE SWITCH FAULTY. (X) 1 L 7 2 4T 4 T A24CE E4EA 2000113000079 20001130 00079 GL 2000 11 30 AU000967 3 20001005 G 6110 PROPELLER MCAULY CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO MCAULY 3AF32C 3AF32C505 GL PROPELLER ASSY LEAKING W K NONE K FLUID LOSS NR NOT REPORTED 1 AU S (AUS) PROPELLER SLOW TO FEATHER. BLADE SEALS LEAKING GREASE. (X) 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2001011100938 20010111 00938 NM 2001 1 11 AU000968 1 20000927 G 5753 113T184287SP FAIRING BOEING 767 767338 1385151 NM GE CF6 CF680C2* GL TE FLAP SEPARATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT OUTBOARD FLAP INBOARD TRAILING EDGE FAIRING MISSING. INBOARD FAIRING ATTACHMENT BRACKET MISSING. FASTENERS PULL ED FROM FLAP. 2 L 7 2 4F 4 F RT A1NM E23EA 2001011100939 20010111 00939 NM 2001 1 11 AU000969 1 20000930 G 2830 02891113A VALVE 6072101 BOEING 747 747438 NM FUEL DUMP SEPARATED W K NONE O OTHER IN INSP/MAINT 1 AU S 02891113A (AUS) NR 3 OVER-RIDE JETTISON PUMP INLET CHECK VALVE SEPARATED FROM THE HINGE POINT. INSPECTION OF THE PUMP FOUND THAT T HE IMPELLER WAS LOOSE AND INSECURE. 2 L 7 4 4F RT A20WE 2001011100621 20010111 00621 EU 2001 1 11 AU000970 1 20001003 G 2897 WIRE AEROSP SA365 SA365C 8680667 EU TMECA ARRIEL ARRIEL1A 60030 NE FUEL QTY IND FAULTY W E A ENGINE SHUTDOWN UNSCHED LANDING E J VIBRATION/BUFFET WARNING INDICATION CR CRUISE 1 AU S (AUS) NO2 FUEL TANK QUANTITY GAUGE OVER-READING DUE TO DEFECTIVE WIRING AT NO2 FUEL QUANTITY TRANSMITTER. NO2 ENGINE FAI LED DUE TO FUEL EXHAUSTION. 1 G 7 2 3U 3 U H10EU E19EU 2001011101107 20010111 01107 EA 2001 1 11 AU000973 1 20001001 G 2750 860D10018 FCU CNDAIR CL600 CL6002B19 EA TE FLAP FAULTY W O OTHER F FLT CONT AFFECTED DE DESCENT 1 AU S (AUS) FLAP ELECTRONIC CONTROL UNIT (FECU) FAULTY. FOLLOWING CIRCUIT BREAKER REST THE FAULT COULD NOT BE DUPLICATED. 2 L 7 2 4F RT A21EA 2001011101108 20010111 01108 EA 2001 1 11 AU000974 1 20001005 G 5610 NP1393215 WINDSHIELD CNDAIR CL600 CL6002B19 EA COCKPIT CRACKED W O OTHER O OTHER DE DESCENT 1 AU S (AUS) CAPTAINS WINDSHIELD CRACKED. 2 L 7 2 4F RT A21EA 2001011101063 20010111 01063 NM 2001 1 11 AU000975 1 20000306 G 5400 FRFOE2822PO3 CONNECTOR BOEING 737 737377 NM NR 2 PYLON DAMAGED W O OTHER H J ELECT. POWER LOSS-50 PC WARNING INDICATION CR CRUISE 1 AU S (AUS) NR 2 PYLON HARNESS FIREWALL CONNECTOR DAMAGED DUE TO ARCING. 2 L 7 2 4F RT A16WE 2000112800374 20001128 00374 SW 2000 11 28 AU000976 1 20001006 G 2560 206706211103 FLOATATION BELL 206 206B3 1181506 SW ALLSN 250C 250C20B 03013 GL EMERG QUIPMENT FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) EMERGENCY FLOATS INFLATED OVERNIGHT WITH NO REASON OR CAUSE BEING FOUND. INVESTIGATION OF THE FLOAT SYSTEM FOUND THAT THE SQUIB HAD BEEN FIRED ELECTRICALLY AND THAT THE SYSTEM HAD OPERATED NORMALLY. (X) 1 G 7 1 3U 3 U H2SW E4CE 2000112800375 20001128 00375 SW 2000 11 28 AU000977 1 20000106 G 6310 206040015103 DRIVE SHAFT BELL 206 206B3 1181506 SW ALLSN 250C 250C20B 03013 GL ENGINE/TRANS FAILED W K E NONE ENGINE SHUTDOWN O OTHER NR NOT REPORTED 1 AU S 599 (AUS) ENGINE TO TRANSMISSION DRIVE SHAFT FAILED AND SEPARATED AT THE TRANSMISSION END. SUSPECT ATTACHMENT NUTS PN MS210 43-4 HAD NOT BEEN CORRECTLY RETORQUED (LEFT FINGER TIGHT) FOLLOWING SERVICING AND GREASING OF THE SHAFT APPROXIMATELY ON E HOUR PREVIOUSLY. TWO OF THE NUTS WERE FOUND ON THE TRANSMISSION DECK. (X) 1 G 7 1 3U 3 U H2SW E4CE 2001011101085 20010111 01085 NE 2001 1 11 AU000978 2 20001010 G 7261 115175 ENGINE EMB 120 EMB120 3260201 SO PWA 118 PW118A NE NR 1 MALFUNCTIONED W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 AU S (AUS) NR 1 ENGINE OIL PRESSURE LOW. 2 L 7 2 4T 4 T RT A31SO E20NE 2000113000080 20001130 00080 SO 2000 11 30 AU000979 2 20000928 G 8540 631847 SHAFT CONT CESSNA 404 404CESSNA 2075901 CE CONT O520 GTSIO520M 17032 SO MCAULY 3FF32 3FF32C501 GL ENGINE STRIPPED W K NONE E VIBRATION/BUFFET NR NOT REPORTED 1 AU S 810608R (AUS) RH ENGINE STARTER GEAR TEETH STRIPPED. 1 L 7 2 3O 3 O A25CE E7CE 5 C P45GL 2000113000081 20001130 00081 SO 2000 11 30 AU000980 2 20001005 G 8540 276157R SLEEVE CONT CESSNA 404 404CESSNA 2075901 CE CONT O520 GTSIO520M 17032 SO MCAULY 3FF32 3FF32C501 GL ENGINE FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S 276157R (AUS) LEFT ENGINE STARTER DRIVE NEEDLE ROLLER BEARING SLEEVE FAILED. METAL CONTAMINATION OF OIL SYSTEM. THE SLEEVE IS NOT AC ONTINENTAL PART. UNAPPROVED PART. (X). 1 L 7 2 3O 3 O A25CE E7CE 5 C P45GL 2001011101086 20010111 01086 NM 2001 1 11 AU000981 1 20001001 G 2120 UNKNOWN BOEING 767 767338 1385151 NM GE CF6 CF680C2* GL CABIN ODOR W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 AU S (AUS) ACRID OILY ODOR EVIDENT IN AIRCRAFT WITH A VISIBLE MIST OBSERVED ON THE FLIGHTDECK. ON DESCENT THE FUMES DISSIPATE D. 2 L 7 2 4F 4 F RT A1NM E23EA 2001011101088 20010111 01088 NM 2001 1 11 AU000982 1 20000924 G 4930 FUEL CONTROL BOEING 767 767338 1385151 NM APU LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S (AUS) APU FUEL CONTROL UNIT LEAKING. INVESTIGATION COULD FIND NO LEAKS. SUSPECT LEAK WAS RESIDUAL FUEL FROM COMBUSTION C ASE DRAIN VALVE. 2 L 7 2 4F RT A1NM 2001011101089 20010111 01089 NM 2001 1 11 AU000983 1 20000917 G 3150 0881031006 STRUCTURE BOEING 737 737476 NM CFMINT CFM56 CFM563C 13802 EU COCKPIT ARCED W D RETURN TO BLOCK B SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 AU S (AUS) LT MASTER CAUTION RESET BASE ASSEMBLY ARCING. LIMITED INFORMATION PROVIDED. 2 L 7 2 4F 4 F RT A16WE E21EU 2000113000082 20001130 00082 WP 2000 11 30 AU000984 2 20000821 G 7250 TURBINE GARRTT CESSNA 441 441 2076020 CE GARRTT TPE331 TPE3318 01514 WP HARTZL HCB3T HCB3TN5 GL TURBINE SECTION OVERHEATED W K NONE E R M VIBRATION/BUFFET PARTIAL RPM/PWR LOSS OVER TEMP CL CLIMB 1 AU S (AUS) LEFT ENGINE UNCOMMANDED TORQUE REDUCTION COUPLED WITH HIGH EGT INDICATION. HOT SECTION OVERTEMP DAMAGE. (X) 1 L 7 2 3T 4 T RT A28CE E4WE 6 C P15EA 2001011101155 20010111 01155 SW 2001 1 11 AU000985 1 20000907 G 2822 3282030001 HARNESS SWRNGN SB28003 SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE33111U 01514 WP ROTOL R321 R321482F8 GL BOOST PUMP WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT FUEL BOOST PUMP HARNESSES (2OFF) AND LT OUTBOARD BOOST PUMP HARNESS CHAFED. 2 L 7 2 4T 4 T RT A8SW E4WE 6 C P61GL 2001011101156 20010111 01156 EU 2001 1 11 AU000986 1 20001007 G 2435 524031 STARTER GEN AEROSP SA365 SA365C 8680667 EU TMECA ARRIEL ARRIEL1A 60030 NE NR 1 ENGINE FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S 206 (AUS) NR 1 ENGINE STARTER-GENERATOR SHAFT HAD EXCESSIVE PLAY CAUSING HIGH VIBRATION LEVEL. IGNITER BRACKET CRACKED AS A RESULT. 1 G 7 2 3U 3 U H10EU E19EU 2001011101157 20010111 01157 NM 2001 1 11 AU000987 1 20000310 G 3320 285T00976 CIRCUIT BOARD BOEING 767 767277 NM GE CF6 CF680A 30025 NE LIGHTING SYSTEM BURNED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 AU S (AUS) MASTER DIM AND TEST PRINTED CIRCUIT BOARD M2 IN PANEL P29 BURNED. 2 L 7 2 4F 4 F RT A1NM E13NE 2001011101180 20010111 01180 EU 2001 1 11 AU000988 1 20001002 G 2701 TORQUE BOX GROB G115 G115 EU LYC O235 O235C1B 41505 EA MCAULY 1C90 1C90LM GL CONTROL COLUMN CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) CONTROL COLUMN TORQUE BOX CONTAINED TWO CRACKS ON THE LOWER SURFACE EMANATING FROM THE EDGES OF THE CONTROL COLUMN CUT-OUT. ONE OF THE CRACKS HAD BEEN STOP DRILLED AND REINFORCED WITH A SMALL DOUBLER PATCH. LOG BOOK ENTRY SHOWED THA T THE CRACK HAD BEEN REPAIRED ON 29 APRIL 1989 AT 2,523 HOURS. THIS REPAIR IS AN ILLEGAL REPAIR. AD/VAT/42 WAS LAST CAR RIED OUT AT 3,399 HOURS. UNAPPROVED REPAIR. (X) 1 L 7 1 3O 3 O NT A57EU E223 5 N P842 2000113000083 20001130 00083 SO 2000 11 30 AU000989 2 20000927 G 8597 530830 PISTON PIN CONT CESSNA 150 150G 2071816 CE CONT O200 O200A 17020 SO MCAULY 1A102 1A102OCM GL ENGINE FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S 1147 669177A (AUS) PISTON PIN FAULTY. LIMITED INFORMATION PROVIDED. (X) 1 H 7 1 3O 3 O 3A19 E252 5 N P918 2001011101183 20010111 01183 WP 2001 1 11 AU000990 2 20001009 G 7261 31080281 SHAFT 31080261 FRCHLD SA227 SA227DC 3377521 SW GARRTT TPE331 TPE33112UHR WP MCAULY 4HFR34 4HFR34C652 NE RT ENGINE SEIZED W O OTHER E K VIBRATION/BUFFET FLUID LOSS LD LANDING 1 AU S (AUS) RT ENGINE TURBINE BEARING SCAVENGE PUMP GEARSHAFT SEIZED IN THE PUMP HOUSING CAUSING THE PUMP DRIVESHAFT GEARS TO STRIP. METAL CONTAMINATION OF THE SCAVENGE PUMP AND REAR TURBINE BEARING. 2 L 7 2 4T 4 T RT A18SW E4WE 6 C 3PNE 2000113000084 20001130 00084 CE 2000 11 30 AU000991 1 20001012 G 7120 539914 MOUNT CONT CESSNA 182 182Q 2072732 CE CONT O470 O470U 17026 SO MCAULY 2A34C 2A34C203 GL ENGINE MOUNT SEC BROKEN W K NONE C F.O.D. NR NOT REPORTED 1 AU S (AUS) RIGHT SIDE ENGINE MOUNTS BROKEN. AIRCRAFT WAS BEING HAND STARTED AND RAN AWAY FROM THE PILOT BEFORE HITTING A FEN CE. THE PROPELLER HIT THE FENCE AND STALLED THE ENGINE. (X) 1 H 7 1 3O 3 O NT 3A13 E273 5 C P3EA 2001011101184 20010111 01184 NM 2001 1 11 AU000993 1 20001005 G 3244 H31X9751312PLY TIRE DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE MLG SPLIT W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MAIN LANDING GEAR TIRE DAMAGED ON OUTBOARD LOWER SIDEWALL BY SHARP STONE. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2000113000085 20001130 00085 CE 2000 11 30 AU000994 1 20001011 G 2150 AN737TW98 CLAMP HAMSTD H573844315 CESSNA 441 441 2076020 CE HARTZL HCB3T HCB3TN5 GL CABIN COOLING SY LOOSE W K NONE O OTHER CR CRUISE 1 AU S 50794 (AUS) AIR CYCLE MACHINE TO WATER SEPARATOR DUCT CLAMP LOOSE. INVESTIGATION FOUND THE CLAMP WAS THE INCORRECT SIZE. COR RECT CLAMP PN AN737TW-91. UNAPPROVED PART. (X) 1 L 7 2 3T RT A28CE 6 C P15EA 2000113000086 20001130 00086 CE 2000 11 30 AU000995 1 20000928 G 5312 POST CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO MCAULY 2A34C D2A34C58 GL FUSELAGE MAIN BU CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUSELAGE RIGHT FORWARD LOWER DOOR POST BULKHEAD CRACKED AT RELIEF HOLE PER AD/CESSNA206/48 AMDT1. CRACK LENGTH 8. 2 MM (0.325 INCH). AD/CESSNA206/48 AMDT1 WAS NOT DUE FOR ANOTHER 120 HOURS. (X) 1 H 7 1 3O 3 O A4CE E5CE 5 C P3EA 2001011101185 20010111 01185 NM 2001 1 11 AU000996 1 20001016 G 3260 SENSOR DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE MLG OUT OF ADJ W C ABORTED TAKEOFF N FALSE WARNING TO TAKEOFF 1 AU S (AUS) LT MAIN LANDING GEAR DOOR WARNING LIGHT SENSOR OUT OF ADJUSTMENT. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001011101206 20010111 01206 NE 2001 1 11 AU000997 2 20001011 G 7322 78639010 HMU PWA PW118A EMB 120 EMB120 3260201 SO PWA 118 PW118A NE FUEL CONTROL FAULTY W A UNSCHED LANDING E R J VIBRATION/BUFFET PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 AU S 6743 F324B (AUS) LT ENGINE HYDRO MECHANICAL UNIT (HMU) FAULTY. 2 L 7 2 4T 4 T RT A31SO E20NE 2001011101207 20010111 01207 EU 2001 1 11 AU000998 1 20001017 G 2421 TERMINAL BAG BAE146 BAE146300A 1500267 EU LYC ALF502 ALF502R5 41580 NE AC GENERATOR LOOSE W O OTHER H J ELECT. POWER LOSS-50 PC WARNING INDICATION NR NOT REPORTED 1 AU S (AUS) NR 1 GENERATOR PHASE TERMINAL LOOSE. DURING TROUBLE SHOOTING FAULTS WERE ALSO FOUND IN THE BUS TRANSFER SYSTEM. 2 H 7 4 4F 4 F RT A49EU E6NE 2001011100623 20010111 00623 EU 2001 1 11 AU000999 1 20000612 G 2730 27930288 WIRE AIRBUS 320 A320211 3930320 EU CFMINT CFM56 CFM565A1 NE RT ELEVATOR DAMAGED W O OTHER N FALSE WARNING NR NOT REPORTED 1 AU S (AUS) RT INBOARD ELEVATOR SERVO POSITION FEEDBACK TRANSDUCER WIRE PNO 2793-0288 HAD INSULATION DAMAGE. SUSPECT DAMAGE CA USED BY FOD. 2 L 7 2 4F 4 F RT A28NM E29NE 2001011101211 20010111 01211 NM 2001 1 11 AU001000 1 20000823 G 2425 119191N7 SWITCH BOEING 737 737377 NM AC POWER FAULTY W K NONE B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 AU S (AUS) AC POWER SELECTOR SWITCH (S3) ARCING INTERNALLY. 2 L 7 2 4F RT A16WE 2001011101238 20010111 01238 EU 2001 1 11 AU001001 1 20001019 G 3020 6124100 DUCT SAAB SF340 340B 7860101 EU GE CT7TP CT79B 30030 NE ROTOL R390 R3904123F27 NE INTAKE ANTI ICE FAULTY W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 AU S (AUS) LT ENGINE INTAKE LOWER ANTI-ICE DUCT FAULTY. 2 L 7 2 4T 4 T RT A52EU E8NE 6 C P31NE 2001030200025 20010302 00025 EU 2001 3 2 AU001002 1 20001017 G 2497 55T802024029 WIRE SAAB SF340 SF340A 7850100 EU GE CT7TP CT75A2 30030 NE ROTOL R354 R3544123F13 NE FUSELAGE WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) DURING INSPECTION FOR AD/SF340/73 (SB 92-027) TWO WIRES WEREFOUND CHAFED THROUGH TO THE CONDUCTOR IN THE HOLE LOCA TED IN FRAME 272. 2 L 7 2 4T 4 T RT A52EU E8NE6 6 C P61GL 2000113000087 20001130 00087 CE 2000 11 30 AU001003 1 20001019 G 2130 1013800133 VALVE 10138001319 BEECH 200 B200C 1152924 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL CABIN PRESSURE C FAULTY W K NONE O OTHER CR CRUISE 1 AU S 648184R (AUS) CABIN PRESSURIZATION SYSTEM FAULTY RESULTING IN AUTO DEPLOYMENT OF THE OXYGEN MASKS. INVESTIGATION FOUND THE RIGH T FLOW PACK PN 101-380013-19 UNSERVICEABLE AND THE LEFT PNEUMOSTAT PN 101-380013-3 STICKING. (X) 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2001011101239 20010111 01239 NM 2001 1 11 AU001004 1 20000826 G 5280 113T820176A DOOR BOEING 767 76733A 1385209 NM PWA 4060 PW4060 52119 NE LANDING GEAR SEPARATED W O OTHER D INFLIGHT SEPARATION AP APPROACH 1 AU S (AUS) RT MAIN LANDING GEAR STRUT AND TRUNNION DOORS MISSING.INVESTIGATION FOUND OTHER DAMAGE INCLUDING RH BRAKE LINES AN D BOGIE TILT ACTUATOR HYDRAULIC LINES. IMPACT DAMAGE OCCURRED TOTHE WING TO BODY FAIRING (PANEL 196KR) AND UNDERWING PAN EL 615SB. THE RH HORIZONTAL STABILISER LEADING EDGE WAS DENTED AND THREEFAN BLADES ON THE RH ENGINE HAD MINOR TIP CURL. SCUFF MARKS ONTHE RH FUSELAGE AND FORWARD OF THE RH MAIN WHEEL WELL SEEMS TOINDICATE THAT THE DAMAGE WAS CAUSED BY RUBBE R DEBRIS THROWN UPDURING TAKEOFF. INSPECTION OF THE AIRCRAFT TYRES FOUND NO RUBBERMISSING WHICH INDICATES THAT THE RUBBE R IS FROM ANOTHER AIRCRAFT. 2 L 7 2 4F 4 F RT A1NM E24NE 2000113000088 20001130 00088 CE 2000 11 30 AU001005 1 20001009 G 2820 FITTING BEECH 36 A36 1151604 CE CONT O520 IO520B 17032 SO MCAULY 3A32C 3A32C76 GL ACFT FUEL DIST RUSTED W K NONE E VIBRATION/BUFFET CR CRUISE 1 AU S (AUS) ENGINE DRIVEN FUEL PUMP CONTAMINATED. INVESTIGATION FOUND CONTAMINATION WAS RUST FROM THE INTERNAL BORES OF THE S TEEL END FITTINGS OF THE FLEXIBLE HOSES AND FIREWALL FITTINGS IN THE FUEL SUPPLY SYSTEM PLUMBING. SUBMITTER SUSPECTED R UST PROBLEM IS ASSOCIATED WITH THE DECONTAMINATION OF THE FUEL SYSTEM WITH WATER FOLLOWING THE MOBIL FUEL CONTAMINATION PROBLEM. (X) 1 L 7 1 3O 3 O 3A15 E5CE 5 C P21EA 2000113000089 20001130 00089 SO 2000 11 30 AU001006 2 20000929 G 8540 653882 SHAFT CONT ADAPTER CESSNA 404 404CESSNA 2075901 CE CONT O520 GTSIO520M 17032 SO MCAULY 3FF32 3FF32C501 GL ENGINE STRIPPED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE STARTER SHAFT GEAR TEETH STRIPPED. CRANKSHAFT GEAR DAMAGED. (X) 1 L 7 2 3O 3 O A25CE E7CE 5 C P45GL 2000113000090 20001130 00090 SO 2000 11 30 AU001007 2 20001016 G 7310 641558 PIPE CONT CESSNA 404 404CESSNA 2075901 CE CONT O520 GTSIO520M 17032 SO MCAULY 3FF32 3FF32C501 GL ENGINE FUEL DIST DISCONNECTED W K NONE E VIBRATION/BUFFET CL CLIMB 1 AU S 276276R (AUS) LEFT ENGINE DECK PRESSURE LINE DISCONNECTED. (X) 1 L 7 2 3O 3 O A25CE E7CE 5 C P45GL 2000113000091 20001130 00091 SO 2000 11 30 AU001008 2 20001004 G 7314 PUMP CONT BEECH 36 A36 1151604 CE CONT O520 IO520B 17032 SO MCAULY 3A32C 3A32C76 GL ENGINE FUEL PUMP CONTAMINATED W K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CL CLIMB 1 AU S (AUS) ENGINE DRIVEN FUEL PUMP VAPOR SEPARATOR CHAMBER CONTAINED A SMALL PIECE OF UNIDENTIFIABLE CONTAMINANT. REF: OPE R CNTRL NR AU001005 FOR SUSPECTED ORIGIN OF CONTAMINATION. (X) 1 L 7 1 3O 3 O 3A15 E5CE 5 C P21EA 2001011101241 20010111 01241 CE 2001 1 11 AU001009 1 20001020 G 3213 5081032017 SOCKET BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE HARTZL HCE4A HCE4A3A NE MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT MAIN LANDING GEAR TORQUE LINK ATTACHMENT LUG LOCATED ON THE SOCKET ASSEMBLY CRACKED. FOUND DURING UNSCHEDULED D OUBLE BRAKE UNIT CHANGE. AIRCRAFT HAD SUFFERED A WALLABY STRIKE ON LANDING ON THE PREVIOUS DAY. 2 L 7 2 4T 4 T RT A24CE E26NE 5 C P10NE 2001011101266 20010111 01266 NE 2001 1 11 AU001010 2 20001020 G 7260 39705500 BEARING BOEING 717 717200 1383700 NM RROYCE BR700 BR700715A130 NE RT ENGINE DISINTEGRATED W O OTHER E J VIBRATION/BUFFET WARNING INDICATION LD LANDING 1 AU S (AUS) RT ENGINE ACCESSORY DRIVE GEARBOX ENGINE ELECTRONIC CONTROL (EEC) DEDICATED DRIVE GENERATOR (DDG) LINE 12 BEARING FAILED. 2 L 7 2 4F 4 F TR A6WE E00061EN 2000113000092 20001130 00092 CE 2000 11 30 AU001011 1 20001019 G 2460 7277210 CIRCUIT BREAKER BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO MCAULY 3AF34C 3AF34C502 GL DC POWER DISTRIB FAULTY W K NONE H ELECT. POWER LOSS-50 PC CR CRUISE 1 AU S (AUS) ALTERNATOR FIELD CIRCUIT POWER CIRCUIT BREAKER FAILED. (X) 1 L 7 2 3O 3 O 3A16 E5CE 5 C P22EA 2000112800406 20001128 00406 WP 2000 11 28 AU001012 1 20001024 G 6310 A1882 CLUTCH ROBSIN CLUTCH ROBSIN R22 R22 7640102 WP LYC O320 O320B2C 41508 EA ENGINE/TRANSMISS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 4112 (AUS) ENGINE TO TRANSMISSION CLUTCH SHEAVE CRACKED FROM OUTER RETAINING BOLT. SEAL RETAINING PLATES ALSO CRACKED. 1 G 7 1 3O 3 O H10WE E274 2001011101268 20010111 01268 EU 2001 1 11 AU001013 1 20001018 G 3233 AE7064584 HOSE SAAB SF340 340B 7860101 EU GE CT7TP CT79B 30030 NE ROTOL R390 R3904123F27 NE MLG ACTUATOR FAILED W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S (AUS) NOSE LANDING GEAR RETRACTION ACTUATOR HYDRAULIC HOSE FAILED. 2 L 7 2 4T 4 T RT A52EU E8NE 6 C P31NE 2001011101270 20010111 01270 EA 2001 1 11 AU001014 2 20001018 G 8520 LW11750 CONNECTING ROD GROB G115 G115C 1660303 EU LYC O360 O360A1F6 41514 EA HARTZL HCF2Y HCF2YR1 GL ENGINE MISMANUFACTURED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) CONNECTING ROD BIGEND BOLT HOLES INCORRECTLY DRILLED. BOLT HOLESWERE DRILLED APPROXIMATELY TWO DEGREES OF CENTRE L INE RESULTING IN A TAPERING GAP OF 0.889MM (0.035IN). MANUFACTURING ERROR. 1 L 7 1 3O 3 O NT A57EU E286 5 C P27EA 2001011101273 20010111 01273 EU 2001 1 11 AU001015 1 20001010 G 3020 HE69822 CONTROL UNIT SAAB SF340 SF340A 7850100 EU GE CT7TP CT75A2 30030 NE ROTOL R354 R3544123F13 NE INTAKE ANTI ICE MALFUNCTIONED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 AU S (AUS) RT ENGINE AIR INTAKE ANTI-ICE CONTROL SYSTEM THERMISTOR HAD HIGH RESISTANCE. 2 L 7 2 4T 4 T RT A52EU E8NE6 6 C P61GL 2000112800407 20001128 00407 SW 2000 11 28 AU001016 1 20001009 G 6410 406016100119 BLADE BELL BELL 407 407 SW TAIL ROTOR BLADE FOD W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) TAIL ROTOR BLADE DAMAGED BY DZUS FASTENER WHICH SEPARATED FROM THE TAIL ROTOR GEARBOX COWLING. FOD. (X) 1 G 7 1 3U O H2SW 2001011101277 20010111 01277 NE 2001 1 11 AU001018 2 20000916 G 7532 BLEED BAND BAC 146 146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE COMPRESSOR OUT OF ADJ W A UNSCHED LANDING E R J VIBRATION/BUFFET PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 AU S (AUS) NR 2 ENGINE BLEED BAND OUT OF ADJUSTMENT. 2 H 7 4 4F 4 F A49EU E6NE 2001011101301 20010111 01301 EU 2001 1 11 AU001019 1 20000908 G 5610 NP1701022 WINDSHIELD BAG BAE146 BAE146300A 1500267 EU LYC ALF502 ALF502R5 41580 NE COCKPIT CRACKED W A UNSCHED LANDING O OTHER CL CLIMB 1 AU S 16880 (AUS) FIRST OFFICERS B WINDSHIELD OUTER PANE SHATTERED. CRACKING HAD INITIATED FROM A LOCALISED HOT SPOT ALONG THE LOWE R EDGE OF THE WINDSHIELD ADJACENT TO THE BUS BAR AREA. 2 H 7 4 4F 4 F RT A49EU E6NE 2001011101303 20010111 01303 NM 2001 1 11 AU001020 1 20000922 G 5512 SKIN BOEING 737 73733A 1384673 NM HORIZONTAL STAB CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT HORIZONTAL STABILISER LOWER SKIN CRACKED IN AREA BETWEEN STN 125 AND STN 127. CRACK LENGTH 44.45MM (1.75IN). 2 L 7 2 4F RT A16WE 2001011101304 20010111 01304 NM 2001 1 11 AU001021 1 20000823 G 5512 SKIN BOEING 737 737377 NM HORIZONTAL STAB CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT HORIZONTAL STABILISER LOWER SKIN CRACKED AT THE CHEMICALLY MILLED EDGE BETWEEN STN 156.00 AND STN 158.00. CRACK LENGTH 50.8MM(2IN). 2 L 7 2 4F RT A16WE 2001011101305 20010111 01305 NM 2001 1 11 AU001022 1 20000728 G 5280 655051425 BRACKET BOEING 737 737377 NM MLG DOOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT NOSE LANDING GEAR DOOR FORWARD HINGE BRACKET CRACKED ACROSS WEB. CRACK LENGTH 23MM (0.905IN). 2 L 7 2 4F RT A16WE 2001011101306 20010111 01306 NM 2001 1 11 AU001023 1 20000920 G 2612 WARNING SYSTEM BOEING 767 767277 NM GE CF6 CF680A 30025 NE FIRE DETECTION FAULTY W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 AU S (AUS) LT ENGINE FIRE WARNING. A THOROUGH INVESTIGATION OF THE FIRE WARNING SYSTEM COULD FIND NO FAULTS AND THE SYSTEM HA S OPERATED CORRECTLY SINCE. DEFECT NOT CONFIRMED. 2 L 7 2 4F 4 F RT A1NM E13NE 2000113000093 20001130 00093 CE 2000 11 30 AU001024 1 20001025 G 2751 SWITCH BEECH 200 B200C 1152924 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL TE FLAP POSITION STUCK W K NONE O N OTHER FALSE WARNING CL CLIMB 1 AU S (AUS) FLAP WARNING SYSTEM MICROSWITCH STUCK. (X) 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2000113000094 20001130 00094 CE 2000 11 30 AU001025 1 20001017 G 2731 12600741 ACTUATOR CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA MCAULY 1C160 1C160DTM GL ELEVATOR TAB CON CORRODED W K NONE F FLT CONT AFFECTED TO TAKEOFF 1 AU S (AUS) ELEVATOR TRIM ACTUATOR CORRODED INTERNALLY WITH THE LUBRICANT DRIED OUT. AIRCRAFT HAD BEEN STRIPPED AND RE-SPRAYE D APPROXIMATELY SIX WEEKS PREVIOUSLY WHICH MAY HAVE CONTRIBUTED TO THE PROBLEM. (X) 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2001011101307 20010111 01307 2001 1 11 AU001026 4 20001008 G 3418 EASPE8801402 CONTROL BOX FOKKER F28 F28MK0100 4990807 EU STALL WARNING FAULTY W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 AU S 440 (AUS) STALL PROTECTION ENHANCEMENT BOX FAULTY. 2 L 7 2 4F RT 2001011101308 20010111 01308 EU 2001 1 11 AU001027 1 20001024 G 3230 SELECTOR SWITCH FOKKER F28 F28MK0100 4990807 EU MLG MALFUNCTIONED W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 AU S (AUS) LANDING GEAR TEST SELECTOR LEFT IN GROUND ONLY' (TEST) POSITION FOLLOWING MAINTENANCE. PERSONNEL/MAINTENANCE ERRO R. 2 L 7 2 4F RT 2000121200300 20001212 00300 CE 2000 12 12 AU001028 1 20001010 G 2434 646655A1 HUB CONT CB12C BEECH 36 A36 1151604 CE CONT O520 IO520B 17032 SO MCAULY 3A32C 3A32C76 GL DC GENERATOR-ALT FAILED W K NONE H ELECT. POWER LOSS-50 PC CR CRUISE 1 AU S 98 B512914 (AUS) ALTERNATOR FLEXIBLE DRIVE COUPLING FAILED. (X) 1 L 7 1 3O 3 O 3A15 E5CE 5 C P21EA 2001011101309 20010111 01309 EU 2001 1 11 AU001029 1 20001023 G 2420 GENERATOR BAG BAE146 BAE146100A 1500260 EU LYC ALF502 ALF502R5 41580 NE NR 1 FAULTY W O OTHER H J ELECT. POWER LOSS-50 PC WARNING INDICATION LD LANDING 1 AU S (AUS) NR 1 GENERATOR WENT OFF LINE. GENERATOR CONTROL UNIT AND LINE CONTACTOR CHANGED AND WIRING INSPECTED WITH NIL FAUL TS FOUND. INVESTIGATION CONTINUING. 2 H 7 4 4F 4 F RT A49EU E6NE 2000121200301 20001212 00301 CE 2000 12 12 AU001030 1 20001018 G 3230 1313782520CL LINK 131378252889 BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL LANDING GEAR RET SEPARATED W K NONE O OTHER CR CRUISE 1 AU S (AUS) NOSE LANDING GEAR DRIVE CHAIN LINK ASSEMBLY SEPARATED DUE TO FAILURE OF THE RETAINING CLIP. INSPECTION OF THE RET AINING CLIP UNDER A 10X MAGNIFYING GLASS FOUND INDICATIONS OF FATIGUE AND CORROSION. (X) 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2001011101310 20010111 01310 2001 1 11 AU001031 4 20000901 G 2210 1311000 RELAY BAC 146 AVRO146RJ70A 1500095 EU AUTOPILOT SYSTEM MISINSTALLED W O OTHER F FLT CONT AFFECTED LD LANDING 1 AU S (AUS) NAVIGATION RELAY BOX WIRES CR101 AND CR102 (HSI COURSE ERROR TO AUTOPILOT) NOT CONNECTED. 2 H 7 4 4F RT A49EU 2000121200302 20001212 00302 GL 2000 12 12 AU001032 3 20001022 G 6111 BLADE HARTZL BEECH 95 D95A 1153408 CE LYC O360 IO360B1B 41514 EA HARTZL HC92W HC92WK2 GL PROPELLER BLADE SEPARATED W K NONE F FLT CONT AFFECTED CR CRUISE 1 AU S (AUS) LEFT PROPELLER BLADE SECTION SEPARATED APPROXIMATELY 200 MM (7.87 INCHES) FROM THE BLADE TIP. FAILURE ORIGINATED FROM A PREVIOUS STONE STRIKE THAT HAD NOT BEEN ADEQUATELY BLENDED OUT. (X) 1 L 7 2 3O 3 O 3A16 1E10 5 C P16EA 2000121200303 20001212 00303 EA 2000 12 12 AU001033 2 20000925 G 8550 LW13388 GASKET LYC PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL ENGINE FAULTY W K NONE E VIBRATION/BUFFET CL CLIMB 1 AU S (AUS) ENGINE OIL FILTER CONVERTER PLATE GASKET FAULTY. GASKET WAS SWOLLEN AND SPONGY IN APPEARANCE. (X) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001011101311 20010111 01311 EU 2001 1 11 AU001034 1 20001023 G 2613 CONNECTOR SAAB SF340 SF340A 7850100 EU GE CT7TP CT75A2 30030 NE ROTOL R354 R3544123F13 NE OVERHEAT DETECT SHORTED W A UNSCHED LANDING E B J VIBRATION/BUFFET SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CL CLIMB 1 AU S (AUS) TAILPIPE OVERHEAT DETECTOR SHORT CIRCUITING AT CONNECTOR DUE TO CONTAMINATION. 2 L 7 2 4T 4 T RT A52EU E8NE6 6 C P61GL 2001011101331 20010111 01331 EU 2001 1 11 AU001035 1 20001025 G 2840 946432 INDICATOR SAAB SF340 SF340A 7850100 EU GE CT7TP CT75A2 30030 NE ROTOL R354 R3544123F13 NE FUEL FLOW FAULTY W C ABORTED TAKEOFF O OTHER TO TAKEOFF 1 AU S (AUS) RT FUEL FLOW INDICATION SYSTEM SUSPECT FAULTY (INDICATOR WENT TOFULL SCALE DEFLECTION). INVESTIGATION COULD FIND N O FAULT WITH THE SYSTEM. 2 L 7 2 4T 4 T RT A52EU E8NE6 6 C P61GL 2000121200304 20001212 00304 CE 2000 12 12 AU001036 1 20001024 G 5313 STRINGER BEECH 200 B200C 1152924 CE PWA PT6 PT6A42 52043 NE FUSELAGE MAIN LO CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) STRINGER NR 10 RT LOCATED AT FRAME 207 CRACKED. NEW FRAME 207 AND SKIN HAD BEEN FITTED. (X) 1 L 7 2 4T 4 T A24CE E4EA 2000121200305 20001212 00305 SO 2000 12 12 AU001037 2 20001022 G 7314 MS9021016 O-RING CONT 6381572 PAC CT4 CT4A 05623UC GL CONT O360 IO360HB 17025 SO HARTZL HCC2Y BHCC2YF1 GL ENGINE FUEL PUMP DAMAGED W K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS DE DESCENT 1 AU S 960 L177307 (AUS) ENGINE DRIVEN FUEL PUMP O-G SEAL DAMAGED. A PORTION OF THE SEAL BLOCKED THE METERING ORIFICE AT THE FCU ALLOWING THROUGH ONLY ENOUGH FUEL FOR IDLE POWER. SUSPECT SEAL DAMAGED DURING PUMP ASSEMBLY AT OVERHAUL. (X) 1 Q 7 1 3I 3 O RT A9PC E1CE 5 C P920 2000121200306 20001212 00306 CE 2000 12 12 AU001038 1 20001020 G 7810 EXHAUST PIPE CONT CESSNA 402 402A 207590M CE CONT O520 TSIO520E 17040 SO MCAULY 3AF32C 3AF32C87 GL ENGINE COLLECTOR FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) EXHAUST SLIP JOINT BURNT THROUGH ENGINE BEARER CAUSING EXTENSIVE DAMAGE TO BEARER AND WIRING. FIRE DETECTION SYST EM DID NOT INDICATE FAULT. (X) 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2001011101332 20010111 01332 SW 2001 1 11 AU001039 1 20000928 G 6230 206010332017 MAST BELL 206 206B3 1181506 SW ALLSN 250C 250C20B 03013 GL MAIN ROTOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 2906 (AUS) MAIN ROTOR MAST CRACKED AT TOP BEARING JOURNAL. FOUND DURING MAGNETIC PARTICLE INSPECTION. (X) 1 G 7 1 3U 3 U H2SW E4CE 2001011101333 20010111 01333 NE 2001 1 11 AU001040 3 20001011 G 6114 660710325 BOLT SAAB SF340 340B 7860101 EU GE CT7TP CT79B 30030 NE ROTOL R390 R3904123F27 NE PROPELLER HUB DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) PROPELLER HUB BOLTS NR 1, NR 2, NR 3, NR 6, NR 7 AND NR 8 DID NOT MAKETHE 0.381MM (0.015IN) STRETCH LIMIT AS PER D OWTY SB SF340-61-96.SUSPECT CAUSED BY EXCESSIVE SEALANT BETWEEN HUB HALVES. 2 L 7 2 4T 4 T RT A52EU E8NE 6 C P31NE 2001011101124 20010111 01124 EU 2001 1 11 AU001041 1 20001026 G 5610 D20543406 WINDSHIELD FOKKER F28 F28MK0100 4990807 EU COCKPIT DELAMINATED W O OTHER O OTHER CR CRUISE 1 AU S (AUS) RT WINDSHIELD DELAMINATED AND OUTER PANE CRACKED. 2 L 7 2 4F RT 2000121200307 20001212 00307 EA 2000 12 12 AU001042 1 20001028 G 5520 ELEVATOR DHAV DHC2 DHC2* 2800108 EA PWA R985 R985AN14B 52008 NE ELEVATOR STRUCTU FOD W K NONE O C OTHER F.O.D. IN INSP/MAINT 1 AU S (AUS) RIGHT ELEVATOR DAMAGED BY YACHT. TRIM TAB DAMAGED. AIRCRAFT IS A FLOAT PLANE AND WAS MOORED AT THE TIME. (X) 1 H 7 1 3R 3 R A806 5E1 2001011101125 20010111 01125 SW 2001 1 11 AU001043 1 20001030 G 2752 2736053003 ACTUATOR FRCHLD SA227 SA227DC 3377521 SW MCAULY 4HFR34 4HFR34C652 NE TE FLAP CRACKED W O OTHER K J FLUID LOSS WARNING INDICATION LD LANDING 1 AU S 7594 (AUS) FLAP ACTUATOR HOUSING CRACKED. LOSS OF HYDRAULIC FLUID. 2 L 7 2 4T RT A18SW 6 C 3PNE 2000121200308 20001212 00308 SW 2000 12 12 AU001044 1 20000731 G 2822 A8164A PUMP MOONEY M20 M20J 5870219 SW LYC O360 IO360A3B6 41514 EA MCAULY 2D34C B2D34C212 GL FITTING WRONG PART W K NONE O OTHER IN INSP/MAINT 1 AU S 63229 (AUS) INCORRECT FUEL PUMP FITTED. PUMP DEVELOPS ONLY 6 PSI WHEN THE REQUIREMENT IS FOR 14 PSI. PUMP SERIAL NUMBER ALSO INCORRECTLY RECORDED. UNAPPROVED PART. (X) 1 L 7 1 3O 3 O 2A3 1E10 5 C P7EA 2001011101126 20010111 01126 EU 2001 1 11 AU001046 1 20001031 G 7931 CONNECTOR BAG JETSTM JETSTM3201 1500217 EU GARRTT TPE331 TPE33112UHR WP ROTOL R333 R333482F12 GL OIL PRESS IND FAULTY W D RETURN TO BLOCK K N FLUID LOSS FALSE WARNING TX TAXI/GRND HDL 1 AU S (AUS) NR 2 ENGINE OIL PRESSURE TRANSMITTER CONNECTOR CONTAINED A BROKENDRY SOLDER JOINT. 2 L 7 2 4T 4 T RT A56EU E4WE 6 C P61GL 2001011101127 20010111 01127 NM 2001 1 11 AU001047 1 20001103 G 3150 SWITCH DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE CENTRAL WARNING OUT OF ADJ W C ABORTED TAKEOFF N FALSE WARNING TO TAKEOFF 1 AU S (AUS) TAKEOFF WARNING SYSTEM MICROSWITCH OUT OF ADJUSTMENT. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2000121200309 20001212 00309 EU 2000 12 12 AU001049 1 20001106 G 5711 68140053 SPAR PARTEN P68B PARTEN P68 P68B EU LYC O360 IO360A1B6 41514 EA HARTZL HCC2Y HCC2YK2 GL WING SPAR STRUCT CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LEFT AND RIGHT WING REAR SPAR WEBS CRACKED AT RELIEF HOLE FOR NR 3 FLAP HINGE BRACKET. (X) 1 H 7 2 3O 3 O A31EU 1E10 5 C P920 2000121200310 20001212 00310 CE 2000 12 12 AU001050 1 20001101 G 3260 1SE13 SWITCH 3500A CESSNA 206 U206F 2073333 CE CONT O520 IO520F 17032 SO MCAULY 3A32C D3A32C90 GL LANDING GEAR POS FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S 4950 (AUS) LANDING GEAR LIMIT MICROSWITCHES PN 1SE1-3 FAILED. THE RUBBER INSERT HOLDING THE PLUNGER AND SEALING THE SWITCH HA D EXPANDED AND DISINTEGRATED APPROXIMATELY EIGHT TO TWELVE HOURS AFTER LUBRICATION WITH LPS1 LUBRICANT AS SPECIFIED IN T HE 3500A FLOAT SERVICE MANUAL. A TEST WITH LPS2 LUBRICANT HAD A SIMILAR RESULT. SUSPECT RUBBER USED IN THE MICROSWITCH IS INCOMPATIBLE WITH THE RECOMMENDED LUBRICANT. THE AIRCRAFT IS FITTED WITH PK DEVOIE3500A TYPE FLOATS. MICROSWITCH P N 1SE1-3 IS USED IN NUMEROUS AIRCRAFT TYPES. (X) 1 H 7 1 3O 3 O A4CE E5CE 5 C P21EA 2000121200311 20001212 00311 CE 2000 12 12 AU001051 1 20001023 G 3260 DIODE CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO MCAULY 3AF32C 3AF32C93 GL LANDING GEAR POS FAILED W K NONE O OTHER LD LANDING 1 AU S (AUS) LANDING GEAR ANNUNCIATOR LOGIC BOARD DIODE FAILED. (X) 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2001011101128 20010111 01128 EA 2001 1 11 AU001052 1 20001101 G 3231 400019000001 VALVE CNDAIR CL600 CL6002B19 EA NLG DOOR STUCK W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NOSE LANDING GEAR MANUAL RELEASE SYSTEM NOT FULLY STOWED. INVESTIGATION FOUND THAT THE RH NOSE GEAR DOOR BYPASS VA LVE WAS JAMMED. 2 L 7 2 4F RT A21EA 2000121200312 20001212 00312 CE 2000 12 12 AU001053 1 20001031 G 2430 08504691 RELAY CESSNA 340 340CESSNA 2076404 CE CONT O520 TSIO520K 17040 SO MCAULY 3AF32C 3AF32C87 GL DC GENERATING SY CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) BATTERY RELAY COIL OPEN CIRCUITED DUE TO CORROSION CAUSED BY MOISTURE INGRESS. (X) 1 L 7 2 3O 3 O 3A25 E8CE 5 C P22EA 2000121200313 20001212 00313 CE 2000 12 12 AU001054 1 20001107 G 2822 476411 PUMP CESSNA 340 340CESSNA 2076404 CE CONT O520 TSIO520K 17040 SO MCAULY 3AF32C 3AF32C87 GL FUEL BOOST PUMP SHORTED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUEL TRANSFER PUMP FAILED AFTER 287.8 HOURS OPERATION SINCE NEW. PREVIOUS FUEL PUMP AND FUEL TANKS HAD BEEN CONTA MINATED WITH EDA. (X) 1 L 7 2 3O 3 O 3A25 E8CE 5 C P22EA 2000121200314 20001212 00314 NE 2000 12 12 AU001056 2 20001024 G 8530 40698 PISTON PWA WTHRLY 620 620B 9630605 CE PWA R985 R985AN14B 52008 NE ENGINE WRONG PART W K NONE O OTHER IN INSP/MAINT 1 AU S 147 JP205253 (AUS) INCORRECT PISTONS FITTED TO NR 4 AND NR 7 CYLINDERS. THE PISTONS WERE UNDRILLED AND ARE ONLY USED IN NR 5 AND NR 6 CYLINDERS. THE ENGINE HAD BEEN OVERHAULED IN THEUSA. UNAPPROVED PART. (X) 1 L 7 1 3R 3 R NC A26WE 5E1 2000121200315 20001212 00315 CE 2000 12 12 AU001058 1 20001019 G 2130 1013800133 VALVE 10138001319 BEECH 200 B200C 1152924 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL CABIN PRESSURE C FAULTY W K NONE O OTHER CL CLIMB 1 AU S 648184R (AUS) RIGHT FLOW PACK PN 101-380013-19 FAULTY AND LT PNEUMOSTAT PN 101-380013-3 STICKING. (X) 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2000121200316 20001212 00316 EA 2000 12 12 AU001059 2 20000930 G 7310 LW120980240 LINE LYC IO720A1B NEWZE FU24 FU24954 WP LYC O720 IO720A1B 41546 EA ENGINE FUEL DIST BROKEN W K NONE K FLUID LOSS CR CRUISE 1 AU S 944 L163554A (AUS) NR 2 AND NR 4 CYLINDER FUEL INJECTOR LINES PN LW-12098-0-170 AND PN LW-12098-0-240 BROKEN AT OR NEAR NIPPLE ON NOZ ZLE END OF LINE. (X) 1 L 7 1 3O 3 O A9PC 1E15 2001011104402 20010111 04402 2001 1 11 AU001060 1 20001108 G 8120 4066109020 TURBOCHARGER LYC LYC O540 TIO540A2C 41532 EA EXH TURBOCHARGER FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S L436661A (AUS) TURBOCHARGER IMPELLER RUBBING ON HOUSING. TURBOCHARGER WAS A NEWLY OVERHAULED ITEM UNDERGOING A PREFITMENT INSPECT ION. (X) 3 O E14EA 2001011101129 20010111 01129 SW 2001 1 11 AU001061 1 20001101 G 2910 2781032776 PIPE FRCHLD SA227 SA227DC 3377521 SW MCAULY 4HFR34 4HFR34C652 NE HYD SYSTEM CRACKED W O OTHER K FLUID LOSS NR NOT REPORTED 1 AU S (AUS) HYDRAULIC PIPE LOCATED IN RT ENGINE BAY LEAKING FROM CRACKED FLARE. 2 L 7 2 4T RT A18SW 6 C 3PNE 2001011101130 20010111 01130 EA 2001 1 11 AU001062 1 20001006 G 3213 170571 WASHER CNDAIR CL600 CL6002B19 EA MLG MISSING W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MAIN LANDING GEAR NR 2 WHEEL BEARING ANTI-ROTATION WASHER MISSING. WASHER WAS FOUND IN THE WHEEL CLEANUP BASKET DU RING CLEANING OF THE WHEEL PRIOR TO A TIRE CHANGE. THE WHEEL HAD BEEN REMOVED TWO DAYS BEFORE AND THIS PROMPTED AN INVES TIGATION DURING WHICH THE NEWLY FITTED WHEEL WAS REMOVED AND THE LACK OF WASHER DISCOVERED. THE WHEEL, AXLE AND BRAKE WE RE INSPECTED FOR DAMAGE WITH NO FAULT FOUND. PERSONNEL/MAINTENANCE ERROR. 2 L 7 2 4F RT A21EA 2000121200317 20001212 00317 EA 2000 12 12 AU001063 2 20001103 G 7414 M3548 ROTOR SLICK 4370 PIPER PA28 PA28161 7102803 SO LYC O320 O320D3G 41508 EA MAGNETO/DIST BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S 96030014 (AUS) RIGHT MAGNETO ROTOR SHAFT BROKEN AT THE MAGNET. DURING DISASSEMBLY IT WAS NOTICED THAT THE TORQUE ON THE ROTOR SH AFT NUT WAS VERY HIGH. (X) 1 L 7 1 3O 3 O 2A13 E274 2001011101334 20010111 01334 EU 2001 1 11 AU001064 1 20000915 G 5720 STIFFENER AIRBUS 320 A320211 3930320 EU CFMINT CFM56 CFM565A1 NE WING CENTER BOX CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) WING CENTRE SECTION VERTICAL STIFFENERS CRACKED IN HOLES. FOUND DURING INSPECTION IAW SB A320-57-1017. 2 L 7 2 4F 4 F RT A28NM E29NE 2001011101335 20010111 01335 NM 2001 1 11 AU001065 1 20001016 G 2420 BACC63CD28A22P CONNECTOR BOEING 737 737377 NM AC GENERATION DAMAGED W A UNSCHED LANDING H J ELECT. POWER LOSS-50 PC WARNING INDICATION CL CLIMB 1 AU S (AUS) NR 1 GENERATOR HARNESS CONNECTOR D5124J AND WIRES W142-001-6,W142-002-6 AND W142-003-6 LOCATED AT WING DISCONNECT BURNT ANDDAMAGED DUE TO ARCING. SUSPECT CAUSED BY LOOSE CONTACTS DUE TOFAULTY MANUFACTURE AND POOR RELIABILITY OF CONNEC TORS. 2 L 7 2 4F RT A16WE 2001011101336 20010111 01336 NM 2001 1 11 AU001066 1 20000907 G 5415 311T31021 PIN BOEING 767 767277 NM GE CF6 CF680A 30025 NE LT PYLON CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT ENGINE PYLON MIDSPAR INBOARD FUSE PIN CRACKED. CRACK LENGTH APPROXIMATELY 14MM (0.55IN). FOUND DURING EDDY CURR ENT INSPECTION. 2 L 7 2 4F 4 F RT A1NM E13NE 2001011101337 20010111 01337 2001 1 11 AU001067 4 20000817 G 2565 60070102 SLIDE AIRBUS 320 A320211 3930320 EU OVERWING EXIT LEAKING W K NONE O OTHER IN INSP/MAINT 1 AU S 9072 (AUS) RT OFFWING SLIDE RAMP LEAKING IN VARIOUS LOCATIONS. DURING INVESTIGATION A SEAM OPENED UP FOR APPROXIMATELY 152.4M M (6IN). 2 L 7 2 4F RT A28NM 2001011101338 20010111 01338 2001 1 11 AU001068 4 20000817 G 2565 60070101 SLIDE AIRBUS 320 A320211 3930320 EU OVERWING EXIT LEAKING W K NONE O OTHER IN INSP/MAINT 1 AU S 9491 (AUS) LT OFFWING ESCAPE SLIDE RAMP SEAMS LEAKING IN VARIOUS AREAS. DURING INVESTIGATION A SEAM ON THE UPPER INBOARD RAIL TUBE OPENED UP FOR APPROXIMATELY 406.4MM (16IN). 2 L 7 2 4F RT A28NM 2000121200318 20001212 00318 CE 2000 12 12 AU001069 1 20000831 G 5321 PANEL CESSNA 441 441 2076020 CE HARTZL HCB3T HCB3TN5 GL FLOOR PANELS FAILED W K NONE O OTHER CL CLIMB 1 AU S (AUS) METAL FLOOR PANELS INTERMITTENTLY OIL CANNING DURING PHASES OF PRESSURIZATION. (X) 1 L 7 2 3T RT A28CE 6 C P15EA 2001011101339 20010111 01339 EU 2001 1 11 AU001070 1 20001102 G 2150 17983211 HEAT EXCHANGER FOKKER F28 F28MK4000 4990810 EU RROYCE SPEY SPEY55515 54521 EU CABIN COOLING FAULTY W A UNSCHED LANDING B J SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CR CRUISE 1 AU S (AUS) NR 1 AIRCONDITIONING PACK FAILED. LT COOLING TURBINE AND HEAT EXCHANGER REPLACED. 2 L 7 2 4F 4 F RT A20EU E2EU 2000121200319 20001212 00319 SO 2000 12 12 AU001071 2 20001108 G 8500 ENGINE CONT CESSNA 206 U206F 2073333 CE CONT O520 IO520F 17032 SO MCAULY D3A34 D3A34C404 GL ENGINE OVERSPEED W K NONE E VIBRATION/BUFFET TO TAKEOFF 1 AU S (AUS) ENGINE OVERSPED IN EXCESS OF 3,300 RPM. (X) 1 H 7 1 3O 3 O A4CE E5CE 5 C P47GL 2001011101340 20010111 01340 NE 2001 1 11 AU001072 2 20001106 G 7320 3029267 FILTER BELL 212 212 1181420 SW PWA PT6T PT6T3B 52045 NE FUEL CONTROL CONTAMINATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NR 2 ENGINE P3 FILTER PARTIALLY BLOCKED. AIRCRAFT IS OPERATING IN EAST TIMOR. (X) 1 G 7 1 4U 4 U H4SW E22EA 2001011101341 20010111 01341 NM 2001 1 11 AU001073 1 20000916 G 3246 BEARING BOEING 767 767277 NM GE CF6 CF680A 30025 NE COLLAPSED W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 AU S (AUS) NR 7 MAIN WHEEL INNER BEARING COLLAPSED. INVESTIGATION FOUND THAT DURING THE LAST WHEEL CHANGE, THE INBOARD WHEEL SPACER WAS NOTREFITTED TO THE AXLE DUE TO THE SPACER COMING OFF WITH THE WHEEL. PERSONNEL/MAINTENANCE ERROR. 2 L 7 2 4F 4 F RT A1NM E13NE 2001011101342 20010111 01342 NM 2001 1 11 AU001074 1 20001025 G 3242 BRAKE BOEING 737 737377 NM NR 2 CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NR 2 BRAKE ATTACHMENT FLANGE BOLT HOLES CORRODED. PITTING CORROSION ALSO FOUND IN THE BOLT HOLE AT THE 10 O CLOCK POSITION. FOUND DURING INSPECTION IAW AD/B737/140. 2 L 7 2 4F RT A16WE 2001011101350 20010111 01350 NM 2001 1 11 AU001075 1 20001102 G 3242 BRAKE BOEING 737 73733A 1384673 NM NR 1 CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NR 1 BRAKE MOUNT HOLE LOCATED AT THE 2 O CLOCK POSITION, NR 2 BRAKE MOUNT FLANGE HOLE LOCATED AT THE 11 O CLOCK PO SITION AND NO4BRAKE MOUNT FLANGE HOLE LOCATED AT THE 10 O CLOCK POSITION ALLCONTAINED FRETTING CORROSION. FOUND DURING I NSPECTION IAW AD/B737/140. 2 L 7 2 4F RT A16WE 2001011101351 20010111 01351 WP 2001 1 11 AU001076 1 20001106 G 5711 RHTOPWING SPAR DHAVXX DH82 DH82AROBRTSN 2801002 WP DHAVXX GIPSY GIPSYMAJOR1 20004 WP RT WING CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT UPPER WING FORWARD SPAR CRACKED FROM SLAT CABLE HOLE LOCATED OUTBOARD OF THE FORWARD INTERPLANE STRUT. FOUND DU RING INSPECTION IAW AD/DH82/11 AMDT1. 1 Q 7 1 3I 3 I A8EU A8EU 2001011101352 20010111 01352 SW 2001 1 11 AU001077 1 20001107 G 2752 2736053003 ACTUATOR FRCHLD SA227 SA227DC 3377521 SW GARRTT TPE331 TPE33112UA 01514 WP MCAULY 4HFR34 4HFR34C652 NE TE FLAP ACTUATOR CRACKED W O OTHER K J FLUID LOSS WARNING INDICATION NR NOT REPORTED 1 AU S (AUS) RT FLAP ACTUATOR BODY CRACKED AND LEAKING. CRACK LENGTH 40MM(1.57IN). MANUFACTURER STATES THAT THIS ITEM IS ONE OF A BATCH OF ACTUATORS WITH SUSPECT INCORRECT MACHINING OF THE ACTUATOR BODY BORE. 2 L 7 2 4T 4 T RT A18SW E4WE 6 C 3PNE 2001011101353 20010111 01353 SW 2001 1 11 AU001078 1 20001110 G 6320 206040150 CASE BELL 206B BELL 206 206B3 1181506 SW ALLSN 250C 250C20B 03013 GL M/R GEARBOX CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 2455 BKW11302 (AUS) MAIN ROTOR TRANSMISSION LOWER CASE CONTAINED NUMEROUS CRACKS AND WAS LEAKING IN AREA BELOW MOUNT FOR PIN ASSEMBLY PN 206-031-633-101. (X) 1 G 7 1 3U 3 U H2SW E4CE 2000121200320 20001212 00320 CE 2000 12 12 AU001079 1 20001108 G 5711 051212443 SPAR CESSNA 172 172F 2072414 CE CONT O300 O300C 17022 SO MCAULY 1C172 1C172EM GL WING SPAR STRUCT CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) WING CENTER SECTION SPAR TO PN 0512124-35 AND PN 0512124-36 LT AND RT DOOR POST CHANNELS HAD ATTACHMENT RIVETS COR RODED WITH RIVET HEADS MISSING. (X) 1 H 7 1 3O 3 O NT 3A12 E253 5 N P910 2000121200321 20001212 00321 GL 2000 12 12 AU001080 1 20001112 G 2823 AN40043 SELECTOR VALVE NAMER T6 AT6D 6400416 GL PWA R1340 R1340AN1 52016 NE HAMSTD 12D 12D40 NE FUEL SELECTOR/SH CONTAMINATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUEL SELECTOR STIFF IN OPERATION. SUSPECT CAUSED BY CONTAMINATED FUEL. (X) 1 L 7 1 3R 3 R A2575 5E2 5 C P257 2000121200322 20001212 00322 CE 2000 12 12 AU001081 1 20001108 G 2432 7007 CONNECTOR CONCORDEBATT RG380E BEECH MU300 400A 1155402 CE PWA JT15 JT15D5 52112 NE BATTERY/CHARGER BURNED W K NONE O OTHER IN INSP/MAINT 1 AU S CBC368276 (AUS) BATTERY AIRCRAFT SIDE CONNECTOR POSITIVE TERMINALS BURNT AND MELTED. (X) 2 H 7 2 4F 4 F RT A16SW E25EA 2001011104404 20010111 04404 2001 1 11 AU001082 1 20001116 G 3230 LANDING GEAR 146300 LANDING GEAR RET FAULTY W K NONE O OTHER LD LANDING 1 AU S (AUS) LANDING GEAR FAILED TO EXTEND. GEAR SELECTOR HANDLE RECYCLED WITH THE LANDING GEAR EXTENDING APPROXIMATELY 15 SECO NDS AFTER THE DOWN' SELECTION. 2000121200323 20001212 00323 CE 2000 12 12 AU001083 1 20000922 G 8010 S24432 SOLENOID CESSNA 207 207A 2073604 CE CONT O520 IO520F 17032 SO MCAULY D3A34 D3A34C404 GL STARTER FAULTY W O OTHER E VIBRATION/BUFFET NR NOT REPORTED 1 AU S (AUS) STARTER SOLENOID DID NOT RELEASE ON START-UP. (X) 1 H 7 1 3O 3 O A16CE E5CE 5 C P47GL 2000121200324 20001212 00324 CE 2000 12 12 AU001084 1 20001030 G 3230 24670036 BUNGEE CYLINDER CESSNA 172 172RG 2072438 CE LYC O360 O360F1A6 41514 EA MCAULY 2D34C B2D34C220 GL LANDING GEAR RET FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) BUNGEE ASSEMBLY INTERNAL LEFT ADJUSTMENT THREAD BROKEN. (X) 1 H 7 1 3O 3 O 3A17 E286 5 C P7EA 2000121200325 20001212 00325 CE 2000 12 12 AU001085 1 20001109 G 5523 12346131 TRIM TAB CESSNA 206 U206A 2073316 CE CONT O520 IO520F 17032 SO HARTZL HCC3Y HCC3YF1 GL ELEVATOR TAB STR CRACKED W K NONE F FLT CONT AFFECTED DE DESCENT 1 AU S (AUS) ELEVATOR TRIM TAB CRACKED AND FAILED IN THE AREA AROUND THE HORN. (X) 1 H 7 1 3O 3 O A4CE E5CE 5 C P25EA 2001011101354 20010111 01354 NM 2001 1 11 AU001086 1 20000901 G 5310 STRUCTURE BOEING 737 737377 NM FUSELAGE CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LEVEL 2 CORROSION INSPECTION CARRIED OUT IAW AD/B737/52 AMDT2. 2 L 7 2 4F RT A16WE 2000121200326 20001212 00326 CE 2000 12 12 AU001087 1 20001121 G 5312 BULKHEAD CESSNA 182 182Q 2072732 CE CONT O470 O470U 17026 SO MAIN BULKHEAD CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LEFT AND RIGHT FORWARD DOORPOST BULKHEADS CRACKED. FOUND DURING INSPECTION IAW AD/CESSNA 180/75. (X) 1 H 7 1 3O 3 O NT 3A13 E273 2000121200327 20001212 00327 SO 2000 12 12 AU001088 1 20001116 G 5521 40075021 SPAR PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL ELEVATOR SPAR/RI CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ELEVATOR SPAR CRACKED. FOUND DURING INSPECTION IAW AD/PA31/126AMDT3. (X) 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001011101355 20010111 01355 WP 2001 1 11 AU001089 1 20001113 G 2911 5133124 ACCUMULATOR DOUG DC3 DC3CS1C3G 3021458 WP PWA R1830 R183092 52020 NE HAMSTD 23E 23E50 NE HYD SYSTEM LEAKING W O OTHER O OTHER DE DESCENT 1 AU S 14 (AUS) HYDRAULIC ACCUMULATOR DIAPHRAGM LEAKING FLUID. 2 L 7 2 4R 4 R A669 5E4 6 C P603 2001011101356 20010111 01356 WP 2001 1 11 AU001091 2 20001103 G 7250 3103783931038971 BLADE FRCHLD SA227 SA227DC 3377521 SW GARRTT TPE331 TPE33112UA 01514 WP MCAULY 4HFR34 4HFR34C652 NE TURBINE SECTION DAMAGED W C ABORTED TAKEOFF M J OVER TEMP WARNING INDICATION TO TAKEOFF 1 AU S (AUS) LT ENGINE FIRST STAGE TURBINE BLADES AND SECOND STAGE TURBINE NOZZLE HEAT DAMAGED. 2 L 7 2 4T 4 T RT A18SW E4WE 6 C 3PNE 2001011101357 20010111 01357 EA 2001 1 11 AU001092 1 20001115 G 2751 601R930303 TRANSMITTER CNDAIR CL600 CL6002B19 EA TE FLAP POSITION INTERMITTENT W A UNSCHED LANDING F N FLT CONT AFFECTED FALSE WARNING CL CLIMB 1 AU S (AUS) FLAP POSITION TRANSMITTER INTERMITTENT IN OPERATION. INVESTIGATION FOUND THAT THE TRANSMITTER CONNECTOR WERE CONTA MINATED WITH MOISTURE DUE TO HEAVY RAIN. 2 L 7 2 4F RT A21EA 2001011101358 20010111 01358 WP 2001 1 11 AU001094 2 20001108 G 7200 P70066 ENGINE FRCHLD SA227 SA227DC 3377521 SW GARRTT TPE331 TPE33112UHR WP MCAULY 4HFR34 4HFR34C652 NE LEFT MALFUNCTIONED W C ABORTED TAKEOFF E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS TO TAKEOFF 1 AU S 2364 (AUS) LT ENGINE LOW POWER. GROUND RUN CONFIRMED THE ENGINE TO BE 3 PERCENT BELOW TARGET TORQUE. 2 L 7 2 4T 4 T RT A18SW E4WE 6 C 3PNE 2001011101359 20010111 01359 EU 2001 1 11 AU001095 1 20001110 G 2611 72111211000 SMOKE DETECTOR SAAB SF340 340B 7860101 EU GE CT7TP CT79B 30030 NE ROTOL R390 R3904123F27 NE CARGO BAY INTERMITTENT W F A ACTIVATE FIRE EXT. UNSCHED LANDING N FALSE WARNING CR CRUISE 1 AU S (AUS) CARGO SMOKE DETECTOR GAVE INTERMITTENT WARNINGS. FIRE EXTINGUISHER DISCHARGED. NO EVIDENCE OF SMOKE OR FIRE. 2 L 7 2 4T 4 T RT A52EU E8NE 6 C P31NE 2000121200328 20001212 00328 CE 2000 12 12 AU001096 1 20001102 G 2510 46884689 HOOK CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO MCAULY D3A34 D3A34C404 GL COCKPIT CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) SEAT BELT HARNESS SNAP HOOK SPRING AND PIVOT PINS CORRODED. THE HOOK IS CHROME PLATED, BUT THE HOOK SPRINGS AND PI VOT PINS ARE NOT. THE CORRODED (RUSTY) COMPONENTS PREVENT CORRECT OPERATION OF THE HOOKS. (X) 1 H 7 1 3O 3 O A4CE E5CE 5 C P47GL 2000121200329 20001212 00329 EU 2000 12 12 AU001097 1 20001122 G 7603 PIN BNORM BN2 BN2B20 1520302 EU LYC O540 IO540K1B5 41532 EA HARTZL HCC2Y HCC2YK2 GL POWER LEVER SHEARED W K NONE O OTHER IN INSP/MAINT 1 AU S 236 (AUS) THROTTLE FRICTION ADJUSTMENT SHAFT SPLIT PIN SHEARED DURING FRICTION ADJUSTMENT. FOUND DURING INVESTIGATION OF EX CESSIVETHROTTLE FRICTION AND AD/BN-2/69. (X) 1 H 7 2 3O 3 O A17EU 1E4 5 C P920 2000121200330 20001212 00330 SO 2000 12 12 AU001098 2 20001121 G 8540 GEAR CONT CESSNA 337 337G 2075730 CE CONT O360 IO360G 17025 SO MCAULY 2AF34C D2AF34C306 GL ENGINE FAILED W K NONE E VIBRATION/BUFFET CR CRUISE 1 AU S 80 (AUS) VACUUM PUMP DRIVE GEAR FAILED. (X) 1 H 7 2 3O 3 O A6CE E1CE 5 C P5EA 2001011101360 20010111 01360 EU 2001 1 11 AU001099 2 20001013 G 7250 CFM563C1 ENGINE BOEING 737 737476 NM CFMINT CFM56 CFM563C 13802 EU TURBINE SECTION DAMAGED W A UNSCHED LANDING E X J VIBRATION/BUFFET ENGINE FLAMEOUT WARNING INDICATION CL CLIMB 1 AU S 28817 (AUS) LT ENGINE FAILED. GROUND INSPECTION FOUND MAJOR DAMAGE IN THE TURBINE AREA AND ALSO ON FOUR AREAS ON THE LEFT LOWE R FUSELAGE. 2 L 7 2 4F 4 F RT A16WE E21EU 2001011101376 20010111 01376 2001 1 11 AU001100 4 20001016 G 2565 130104223 CYLINDER BOEING 767 767338 1385151 NM GE CF6 CF680C2* GL ESCAPE SLIDE UNAPPROVED PART W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) LH OVERWING SLIDE INFLATION CYLINDER INCORRECT PART. THE INCORRECT PNO 130104-223 INFLATION CYLINDER HAS A 750 CU BIC INCHCAPACITY BOTTLE WHILE THE CORRECT INFLATION CYLINDER HAS A 900 CUBIC INCH CAPACITY BOTTLE. UNAPPROVED PART. 2 L 7 2 4F 4 F RT A1NM E23EA 2001011101377 20010111 01377 2001 1 11 AU001102 4 20001122 G 3445 6228973001 ANTENNA BAG BAE146 BAE146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE FUSELAGE SPLIT W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) UPPER TCAS ANTENNA SPLIT. FOUND DURING REMOVAL FOR AIRFRAME CORROSION INSPECTION. ANTENNA HAD BEEN ATTACHED USING PRC1422. 2 H 7 4 4F 4 F RT A49EU E6NE 2001011101378 20010111 01378 NM 2001 1 11 AU001103 1 20001110 G 3242 215152 BRAKE BOEING 747 747438 NM NR 10 FIRE W D RETURN TO BLOCK A FLAME/FIRE TX TAXI/GRND HDL 1 AU S 12047 (AUS) NR 10 BRAKE UNIT FIRE. SUSPECT CAUSED BY EXCESS USE OF GREASE. 2 L 7 4 4F RT A20WE 2000121200331 20001212 00331 CE 2000 12 12 AU001104 1 20001103 G 2750 51152242 CONTROL CABLE CESSNA 402 402B 207590P CE CONT O520 TSIO520E 17040 SO MCAULY 3AF32C 3AF32C87 GL TE FLAP CONTROL FAILED W K NONE F FLT CONT AFFECTED LD LANDING 1 AU S (AUS) FLAP FOLLOW-UP CABLE DAMAGED. UPLIMIT SWITCH OUT OF ADJUSTMENT. SECONDARY DAMAGE CAUSED BY FLAP OVER-RUN DUE TO THE UPLIMIT SWITCH INCORRECT ADJUSTMENT. (X) 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2000121200332 20001212 00332 CE 2000 12 12 AU001105 1 20001121 G 2760 C4A20 WIRE G41A20 CESSNA 404 404CESSNA 2075901 CE CONT O520 GTSIO520M 17032 SO MCAULY 3FF32 3FF32C501 GL ELEC WIRING SHORTED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FLAPS UP WIRE C4A-20 SHORT CIRCUITED TO LANDING GEAR UP WIRE G41A-20 WITHIN THE WIRING LOOM LOCATED ADJACENT TO TH E PILOTS LEFT FOOT AREA. SUSPECT CAUSED BY WATER INGRESS AND A CRACK IN WIRE C4A-20. (X) 1 L 7 2 3O 3 O A25CE E7CE 5 C P45GL 2001011101379 20010111 01379 NE 2001 1 11 AU001106 2 20001117 G 7200 ENGINE FOKKER F28 F28MK0100 4990807 EU RROYCE TAY TAY65015 54557 NE NR 1 VIBRATES W O OTHER E J VIBRATION/BUFFET WARNING INDICATION DE DESCENT 1 AU S (AUS) NR 1 ENGINE VIBRATION. INSPECTION COULD FIND NO CAUSE OR DAMAGE AND IT IS SUSPECTED THAT ICE FORMATION ON THE FAN BLADES WAS THE CAUSE OF THE PROBLEM. 2 L 7 2 4F 4 F RT E25NE 2001011101380 20010111 01380 EU 2001 1 11 AU001107 1 20001118 G 3244 TIRE STBROS SD3 SD360 8100606 EU PWA PT6 PT6A67R 52043 NE HARTZL HCA6A HCA6A3 NE LT MLG FAILED W O OTHER O OTHER LD LANDING 1 AU S (AUS) LT MAIN LANDING GEAR TIRE BURST FOLLOWING A PRACTICE SINGLE ENGINE APPROACH AND LANDING. 2 H 7 2 4T 4 T A41EU E26NE 6 C P14NE 2000121200333 20001212 00333 SW 2000 12 12 AU001108 1 20001121 G 5347 410A HOOK BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE NONSTD EQUIP MISMANUFACTURED W A K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S 047 (AUS) RESCUE HOIST HOOK ASSEMBLY THREADED ATTACHMENT SPINDLE APPROXIMATELY 0.482 MM (0.019 INCHES) UNDER SPECIFICATION S IZE ALLOWING THE NUT TO HAVE EXCESSIVE MOVEMENT ON THE THREAD. (X) 1 G 7 2 4U 4 U H4SW E22EA 2001011101381 20010111 01381 EU 2001 1 11 AU001109 1 20001118 G 2612 51224133 FIRE LOOP STBROS SD3 SD360 8100606 EU PWA PT6 PT6A67R 52043 NE HARTZL HCA6A HCA6A3 NE RT ENGINE CONTAMINATED W O OTHER E B N VIBRATION/BUFFET SMOKE/FUMES/ODORS/SPARKS FALSE WARNING LD LANDING 1 AU S (AUS) RT ENGINE FIRE WARNING. NIL EVIDENCE OF FIRE OR HOT AIR LEAKS FOUND. SUSPECT WATER CONTAMINATION OF FIRE WIRE CONN ECTOR. AIRCRAFT HAD FLOWN THROUGH RAIN PRIOR TO FIRE WARNING. 2 H 7 2 4T 4 T A41EU E26NE 6 C P14NE 2000121200334 20001212 00334 NE 2000 12 12 AU001110 2 20001118 G 7320 3028325 LINE PWA BELL 212 212 1181420 SW PWA PT6T PT6T3B 52045 NE FUEL CONTROLLING FRACTURED W K NONE K FLUID LOSS NR NOT REPORTED 1 AU S 60723 (AUS) ENGINE P3 LINE FRACTURED AT THE FLANGE WHERE THE LINE IS SWAGED TO THE FILTER BOWL. (X) 1 G 7 1 4U 4 U H4SW E22EA 2000121200335 20001212 00335 CE 2000 12 12 AU001111 1 20001114 G 5522 96610006618 SKIN BEECH 58 58 1152740 CE MCAULY 3AF32C 3AF32C512 GL ELEVATOR PLATES CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RIGHT ELEVATOR LOWER SKIN CRACKED AND DISBONDED IN AREA OF STIFFENERS. CRACK LENGTHS 31.75 (1.25 INCHES). ELEVAT ORS ARE FROM THE PERIOD SPECIFIED IN SB 27-3396 REV 1. (X) 1 L 7 2 3O 3A16 5 C P22EA 2000121200336 20001212 00336 EU 2000 12 12 AU001112 1 20001122 G 2800 FUEL CELL HWKSLY DH104 DH104* EU RROYCE GIPSY GIPSY70MK2 20007 EU HWKSLY PD143 PD143312 EU FUEL SYS CONTAMINATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) AIRCRAFT FUEL SYSTEM CONTAMINATED WITH EDA (ETHYLENE DIAMINE). (X) 1 L 7 2 3I 3 I A807 E310 5 C P916 2001011101382 20010111 01382 WP 2001 1 11 AU001113 2 20001115 G 7261 P1070 FILTER FRCHLD SA227 SA227DC 3377521 SW GARRTT TPE331 TPE33112UHR WP MCAULY 4HFR34 4HFR34C652 NE LT ENGINE OIL BROKEN W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S (AUS) LT ENGINE OIL FILTER END CAP BROKEN AWAY AT RECESS. 2 L 7 2 4T 4 T RT A18SW E4WE 6 C 3PNE 2001011101383 20010111 01383 EU 2001 1 11 AU001114 1 20001025 G 3260 ZOON7143022038 CONNECTOR SOCATA TB20 TB20TRINIDAD 8680695 EU LYC O540 IO540C4D5 41532 EA HARTZL HCC2Y HCC2YK1 GL MLG DOWNLOCK BROKEN W O OTHER N FALSE WARNING LD LANDING 1 AU S (AUS) RT DOWNLOCK SWITCH CONNECTOR BROKEN AT THE BOTTOM OF THE ATTACHMENT NUT. 1 L 7 1 3O 3 O RT A51EU 1E4 5 C P920 2000121200337 20001212 00337 SW 2000 12 12 AU001115 1 20001123 G 5711 204311 SPAR CAP AIRTRC AIRTRC AT500 AT502 0390303 SW PWA PT6 PT6A15AG 52043 NE HARTZL HCB3T HCB3TN3 GL WING SPAR STRUCT CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 5020055 (AUS) LEFT SPAR CAP CRACKED IN AREA OF THE HOLE LOCATED 3 MM (0.118 INCHES) FORWARD ALONG THE BOTTOM FACE AND 8 MM (0.31 4 INCHES) UP THE HOLE. FOUND DURING MAGNETIC PARTICLE INSPECTION IAW AT/20 SL 197. (X) 1 L 7 1 3T 4 T NC A9SW E4EA 6 C P15EA 2001011101384 20010111 01384 NM 2001 1 11 AU001117 1 20001111 G 2820 SEAL BOEING 747 747438 NM GE CF6 CF680C2* GL FUEL DIST MISINSTALLED W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S (AUS) NR 4 PYLON FUEL LINE WIGGINS COUPLING LEAKING. INVESTIGATION FOUND THAT THE SEALS HAD BEEN INCORRECTLY FITTED. 2 L 7 4 4F 4 F RT A20WE E23EA 2001011101385 20010111 01385 NM 2001 1 11 AU001118 1 20001120 G 2510 CLAMP BOEING 747 747438 NM COCKPIT FAULTY W A UNSCHED LANDING O OTHER CL CLIMB 1 AU S (AUS) FIRST OFFICERS FLIGHT LIBRARY BOX BROKE FREE FROM THE RESTRAINT AND SLID BACK UNDER THE FIRST OBSERVERS TABLE. INV ESTIGATION FOUND THAT THE BOX BROKE FREE DUE TO INADEQUATE GRIP ON THE RETAINING STRAP BY THE FORWARD LOCKING CLAMP. 2 L 7 4 4F RT A20WE 2001011101386 20010111 01386 NM 2001 1 11 AU001119 1 20001115 G 2750 65C3084618 BELLCRANK BOEING 737 737476 NM CFMINT CFM56 CFM563C 13802 EU TE FLAP CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT OUTBOARD AFT FLAP INBOARD BELLCRANK CRACKED. THE CRACK RAN FOR ALMOST THE ENTIRE LENGTH OF THE SMALLER CRANK AR M. 2 L 7 2 4F 4 F RT A16WE E21EU 2001011101387 20010111 01387 NM 2001 1 11 AU001120 1 20001031 G 3810 S417T2006 SUPPORT BRACKET BOEING 767 767338 1385151 NM GE CF6 CF680C2* GL POTABLE WATER FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT MAIN POTABLE WATER TANK SUPPORT RODS (3OFF) BROKEN ALLOWINGTHE TANK TO COLLAPSE ONTO THE TOILET FAN AND RUPTURE . 2 L 7 2 4F 4 F RT A1NM E23EA 2001011101390 20010111 01390 NM 2001 1 11 AU001121 1 20001105 G 2520 908356G SEAT BOEING 737 737400 NM CFMINT CFM56 CFM563C 13802 EU CABIN SEPARATED W K NONE O OTHER NR NOT REPORTED 1 AU S (AUS) FLIGHT ATTENDANTS FORWARD DOUBLE SEAT SEPARATED FROM WALL. 2 L 7 2 4F 4 F RT A16WE E21EU 2001011101391 20010111 01391 NM 2001 1 11 AU001122 1 20001027 G 2731 AR7077M3 ACTUATOR BOEING 737 737476 NM CFMINT CFM56 CFM563C 13802 EU ELEVATOR TAB CON FAILED W O OTHER F FLT CONT AFFECTED CR CRUISE 1 AU S 18131 Y0504 (AUS) HORIZONTAL STABILISER TRIM ACTUATOR FAILED. 2 L 7 2 4F 4 F RT A16WE E21EU 2000121200338 20001212 00338 CE 2000 12 12 AU001123 1 20001122 G 2434 649304 ALTERNATOR CESSNA 404 404CESSNA 2075901 CE CONT O520 GTSIO520M 17032 SO MCAULY 3FF32 3FF32C501 GL DC GENERATOR-ALT FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ALTERNATOR FAILED. WINDINGS AND DIODES BURNT. ALTERNATOR HAD ONLY RECENTLY BEEN OVERHAULED. (X) 1 L 7 2 3O 3 O A25CE E7CE 5 C P45GL 2000121200339 20001212 00339 CE 2000 12 12 AU001125 1 20001108 G 3260 661011 PLUG CESSNA 404 404CESSNA 2075901 CE CONT O520 GTSIO520M 17032 SO MCAULY 3FF32 3FF32C501 GL LANDING GEAR POS BURNED OUT W K NONE J WARNING INDICATION DE DESCENT 1 AU S (AUS) PILOT REPORTED LG MALFUNCTION PRIOR TO LANDING - THREE GREEN INDICATIONS AND AN INTERMITTENT RED LIGHT. ON TOUCH DOWN, THE NLG COLLAPSED. INVESTIGATION FOUND THE BULKHEAD PLUG PN 66101-1 ON THE FORWARD CABIN FIREWALL HAD AN INTERNAL MELT DOWN AND FUSED SOME PINS TOGETHER. (X) 1 L 7 2 3O 3 O A25CE E7CE 5 C P45GL 2001011101392 20010111 01392 EU 2001 1 11 AU001126 1 20001106 G 3610 9303688100 DUCT SAAB SF340 340B 7860101 EU PNEUMATIC SYSTEM LEAKING W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) DURING AN ENGINE GROUND RUN THE LH 'BLEED LEAK' LIGHT ILLUMINATED. A SYSTEM CHECK DETECTED LEAKAGE FROM THE FLEXIB LEDUCT AT THE WIND ROOT.FURTHER INVESTIGATION FOUND A STAINLESS STEEL INSERT HAD DISBONDED FROM THE SILICON FLEXIBLE DUC T. 2 L 7 2 4T RT A52EU 2001011101393 20010111 01393 EU 2001 1 11 AU001127 1 20001122 G 2844 8346 PRESSURE SWITCH SAAB SF340 SF340A 7850100 EU PRESSURE IND LEAKING W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) DURING PRE-FLIGHT INSPECTION FUEL DEPOSITS WERE OBSERVED ON THE RT ENGINE AND NACELLE. FUEL LEAKAGE WAS TRACED TO A CRACKED SOLDER JOINT IN THE DIFFERENTIAL PRESSURE SWITCH FITTING. 2 L 7 2 4T RT A52EU 2001011101394 20010111 01394 EU 2001 1 11 AU001128 1 20001121 G 3610 7275031506 DUCT SAAB SF340 SF340A 7850100 EU PNEUMATIC SYSTEM CRACKED W O OTHER O OTHER CR CRUISE 1 AU S J94051 (AUS) DURING CRUISE THE CREW NOTICED THE ITT DELTA T WAS 20 DEGREES HIGHER ON THE LT ENGINE COMPARED TO PREVIOUS FLIGHT. INVESTIGATION FOUND A CRACK AROUND THE HIGH PRESSURE BLEED DUCT EXTENDING FOR APPROXIMATELY 180 DEGREES ADJACENT TO THE FLANGE COUPLING TO THE ENGINE. 2 L 7 2 4T RT A52EU 2001011101395 20010111 01395 EU 2001 1 11 AU001129 1 20001118 G 3610 9303688100 DUCT SAAB SF340 340B 7860101 EU PNEUMATIC SYSTEM LEAKING W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) DURING A SCHEDULED INSPECTION, EVIDENCE OF BLEED AIR LEAKAGE AT THE LT WING ROOT FLEXIBLE DUCT WAS FOUND. FURTHER INVESTIGATIONFOUND A STAINLESS STEEL INSERT HAD DISBONDED FOR THE SILICONDUCT. 2 L 7 2 4T RT A52EU 2001011101396 20010111 01396 NM 2001 1 11 AU001130 1 20000814 G 2750 TORQUE TUBE DHAV DHC8 DHC8106 NM TE FLAP MISINSTALLED W O OTHER J WARNING INDICATION LD LANDING 1 AU S (AUS) DURING LANDING THE FLAPS WERE APPLIED TO 35 DEGREES AND FLAP DRIVE CAUTION LIGHT ILLUMINATED. INSPECTION OF THE FL AP DRIVE SYSTEM FOUND THAT THE RT INBOARD PRIMARY DRIVE TORQUE TUBE WAS INCORRECTLY FITTED. 2 H 7 2 4T RT A13NM 2001011101397 20010111 01397 NM 2001 1 11 AU001131 1 20001021 G 5280 NUT BOEING 747 747438 NM MLG DOOR LOOSE W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT WING LANDING GEAR DOOR PANEL 743AB HAD EXCESSIVE PLAY. INSPECTION FOUND THE DOOR TO GEAR STRUT CONNECTING ROD N UT AND BOLT LOOSE. NUT WAS ATTACHED BY TWO THREADS ONLY. . 2 L 7 4 4F RT A20WE 2001011101398 20010111 01398 CE 2001 1 11 AU001132 1 20001125 G 5312 BULKHEAD BEECH 200 B200C 1152924 CE PWA PT6 PT6A42 52043 NE FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) REAR PRESSURE BULKHEAD CRACKED. FOUND DURING INSPECTION IAW AD/200/67. 1 L 7 2 4T 4 T A24CE E4EA 2001011101399 20010111 01399 EA 2001 1 11 AU001133 3 20001102 G 6110 72CK56 BLADE PIPER PA38 PA38112 7103812 SO LYC O235 O235L2A 41505 EA SNSNCH 72C 72CK EA PROPELLER MISMANUFACTURED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) PROPELLER TIP EXFOLIATING. SUSPECT MANUFACTURING DEFECT/FLAW. 1 L 7 1 3O 3 O A18SO E223 5 N P9045 2001011101400 20010111 01400 SO 2001 1 11 AU001134 2 20001024 G 8520 653580 ADAPTER CESSNA 404 404CESSNA 2075901 CE CONT O520 GTSIO520M 17032 SO MCAULY 3FF32 3FF32C501 GL STARTER WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT ENGINE CRANKSHAFT STARTER ADAPTER GEAR TEETH HAD ABNORMAL WEAR INDICATIONS. 1 L 7 2 3O 3 O A25CE E7CE 5 C P45GL 2001011101401 20010111 01401 SO 2001 1 11 AU001135 2 20001127 G 8540 631847 SHAFT CESSNA 404 404CESSNA 2075901 CE CONT O520 GTSIO520M 17032 SO MCAULY 3FF32 3FF32C501 GL STARTER ADAPTER FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S 39 (AUS) LT ENGINE STARTER ADAPTER GEAR SHAFT SHEARED IN AN AREA 16MM(0.629IN) FROM THE PILOT BEARING END OF THE SHAFT. 1 L 7 2 3O 3 O A25CE E7CE 5 C P45GL 2001011101413 20010111 01413 NE 2001 1 11 AU001136 2 20001129 G 7200 CT79B ENGINE SAAB SF340 340B 7860101 EU GE CT7TP CT79B 30030 NE ROTOL R375 R3754123F21 NE RIGHT MAKING METAL W A UNSCHED LANDING E J VIBRATION/BUFFET WARNING INDICATION CR CRUISE 1 AU S 12835 (AUS) RH ENGINE CHIP DETECTOR CONTAMINATED WITH A LARGE AMOUNT OF BEARING MATERIAL. 2 L 7 2 4T 4 T RT A52EU E8NE 6 C P17NE 2001011101414 20010111 01414 EA 2001 1 11 AU001137 3 20000802 G 6110 M74DM51 PROPELLER PIPER PA18 PA18150 7101828 SO LYC O320 O320A2B 41508 EA SNSNCH 74DM M74DM EA FWD UNAPPROVED PART W A K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S 1322 (AUS) INCORRECT PROPELLER FITTED TO AIRCRAFT. PERSONNEL/MAINTENANCE ERROR. UNAPPROVED PART. 1 H 7 1 3O 3 O 1A2 E274 5 N P88614 2001011101415 20010111 01415 CE 2001 1 11 AU001138 1 20001130 G 2435 1013690145 COVER BEECH 200 B200C 1152924 CE PWA PT6 PT6A42 52043 NE STARTER-GEN SEPARATED W O OTHER E VIBRATION/BUFFET LD LANDING 1 AU S (AUS) STARTER COVER CAME OFF AND JAMMED BETWEEN THE COWL AND THE ENGINE FCU CONTROL ROD. 1 L 7 2 4T 4 T A24CE E4EA 2001011101416 20010111 01416 CE 2001 1 11 AU001139 1 20001129 G 2910 AE1003785G0250 HOSE CESSNA 421 421C 2076016 CE CONT O520 GTSIO520L 17032 SO MCAULY 3FF32 3FF32C501 GL HYD SYSTEM FAILED W O OTHER K J FLUID LOSS WARNING INDICATION LD LANDING 1 AU S (AUS) LT ENGINE DRIVEN HYDRAULIC PUMP PRESSURE HOSE FAILED. SUSPECT HOSE WAS HEAT STRESSED. 1 L 7 2 3O 3 O A7CE E7CE 5 C P45GL 2001011101417 20010111 01417 SO 2001 1 11 AU001140 1 20001122 G 3520 OXYGEN MASK EMB 120 EMB120 3260201 SO PWA 118 PW118A NE HAMSTD 14RF 14RF9 NE O2 SYSTEM FAILED W O OTHER O OTHER DE DESCENT 1 AU S (AUS) PASSENGER OXYGEN MASKS FAILED TO DEPLOY AT 14,000 FEET. SUSPECT CAUSED BY DRY AND STIFF HINGES ON THE OXYGEN MASK DOORS DUE TOINFREQUENT USE AND SOLVENTS USED IN REPAINTING HAVING WASHED ANYLUBRICANT FROM THE HINGES. THE TOILET OXYGEN MASK DOOR ELECTRIC LATCH WAS ALSO DEFECTIVE. 2 L 7 2 4T 4 T RT A31SO E20NE 6 C P11NE 2001011101418 20010111 01418 EU 2001 1 11 AU001141 1 20001127 G 5730 SKIN BAG BAE146 BAE146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE WING DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) WING TOP SKIN PANELS CONTAINED NUMEROUS DRILL MARKED AREAS. FOUND DURING INSPECTION IAW AD/BAE146/66 AND ANSETT EN GINEERING RELEASE BA6-57-10-9C. NO CORROSION WAS FOUND. 2 H 7 4 4F 4 F RT A49EU E6NE 2001011101419 20010111 01419 2001 1 11 AU001142 4 20001201 G 3457 TNG2101 GPS BAG JETSTM JETSTM3107 1500215 EU ROTOL R333 R333482F12 GL COCKPIT FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S 6021318 (AUS) GPS SYSTEM FAULTY. RECEIVER INDICATES SPACE VEHICLES USED FOR NAVIGATION ARE BELOW THE HORIZON. 2 L 7 2 4T RT BA15CAA 6 C P61GL 2001011101420 20010111 01420 CE 2001 1 11 AU001143 1 20001128 G 3221 5842000211 PIN CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO MCAULY 3AF32C 3AF32C505 GL NLG TRUNNION CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NOSE LANDING GEAR TRUNNION PINS CRACKED. FOUND DURING INSPECTIONIAW CESSNA SB 88-5R2. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2001011101421 20010111 01421 SW 2001 1 11 AU001144 1 20001128 G 3213 27515010 STRUT SWRNGN 27515003BC FRCHLD SA227 SA227DC 3377521 SW MCAULY 4HFR34 4HFR34C652 NE MLG LEAKING W O OTHER O OTHER NR NOT REPORTED 1 AU S 120TD (AUS) LT MAIN LANDING GEAR STRUT CYLINDER GLAND SEAL RETAINING RING GROOVE LOWER LAND SHEARED RELEASING THE RETAINING RI NG AND ALLOWING THE GLAND TO SLIP DOWN THE PISTON CAUSING LOSS OF FLUID FROM THE STRUT. 2 L 7 2 4T RT A18SW 6 C 3PNE 2001011101422 20010111 01422 EU 2001 1 11 AU001145 1 20001126 G 7722 522861 INDICATOR SAAB SF340 SF340A 7850100 EU GE CT7TP CT75A2 30030 NE ROTOL R354 R3544123F13 NE EGT/TIT IND FAILED W A UNSCHED LANDING P NO WARNING INDICATION CR CRUISE 1 AU S (AUS) LT ENGINE TURBINE TEMPERATURE INDICATOR FAILED. ANALOGUE AND DIGITAL INDICATIONS WERE LOST. 2 L 7 2 4T 4 T RT A52EU E8NE6 6 C P61GL 2001011101423 20010111 01423 EU 2001 1 11 AU001146 1 20001130 G 7712 CONTROL PANEL SAAB SF340 340B 7860101 EU GE CT7TP CT79B 30030 NE ROTOL R390 R3904123F27 NE LT ENG CTOT FAULTY W C ABORTED TAKEOFF E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS TO TAKEOFF 1 AU S (AUS) LT ENGINE CONSTANT TORQUE ON TAKEOFF (CTOT) CONTROL PANEL SUSPECT FAULTY OR ENGINE CONTROLS SLIGHTLY MISRIGGED PRE VENTING CTOT FROM CAPTURING THE ENGINE. 2 L 7 2 4T 4 T RT A52EU E8NE 6 C P31NE 2001011101424 20010111 01424 SW 2001 1 11 AU001148 1 20001108 G 2910 2781006 PIPE SWRNGN SA226 SA226TC 8780404 SW GARRTT TPE331 TPE3313UW 01514 WP HARTZL HCB3T HCB3TN5 GL HYD SYSTEM LEAKING W O OTHER K FLUID LOSS NR NOT REPORTED 1 AU S (AUS) HYDRAULIC POWER PACK PIPE LOCATED IN LT ENGINE NACELLE LEAKING. 2 L 7 2 4T 4 T RT A8SW E4WE 6 C P15EA 2001011101438 20010111 01438 NE 2001 1 11 AU001149 2 20001204 G 7250 PCE115413 ENGINE EMB 120 EMB120 3260201 SO PWA 118 PW118A NE TURBINE SECTION MAKING METAL W O OTHER E J VIBRATION/BUFFET WARNING INDICATION NR NOT REPORTED 1 AU S (AUS) LH ENGINE CHIP DETECTOR METAL CONTAMINATION. FOURTH STAGE TURBINE DAMAGED. 2 L 7 2 4T 4 T RT A31SO E20NE 2001011101439 20010111 01439 NM 2001 1 11 AU001150 1 20001115 G 2913 3508806 PUMP BOEING 767 767216 1385121 NM GE CF6 CF680A 30025 NE HYD SYSTEM CRACKED W O OTHER F K FLT CONT AFFECTED FLUID LOSS CR CRUISE 1 AU S 10278 (AUS) RT ENGINE DRIVEN HYDRAULIC PUMP CASING CRACKED. PUMP DRIVESHAFT FAILED AT SHEAR POINT. SEVERE INTERNAL DAMAGE TO P UMP. SUSPECTPISTON AND SHOE SUBASSEMBLY FAILED FIRST. LOSS OF HYDRAULIC FLUID. 2 L 7 2 4F 4 F RT A2NM E13NE 2001011101440 20010111 01440 WP 2001 1 11 AU001151 1 20001205 G 6220 5143711 HUB HILLER UH12 UH12E 4360122 WP LYC O540 VO540C2A 41532 EA MAIN ROTOR CRACKED W A C ABORTED TAKEOFF F FLT CONT AFFECTED TO TAKEOFF 1 AU S 304 (AUS) MAIN ROTOR HUB SEVERELY CRACKED IN AN AREA NOT KNOWN FOR CRACKING. FOLLOWING TAKEOFF CONTROL WAS ALMOST IMPOSSIBLE AND THE MASSIVE VIBRATION CAUSED THE FORE/AFT ENGINE MOUNT TO BE TORN FROM ITS HOUSING AND THE SHAFT TO CRACK. THE CRAC K WAS OPENINGUP UNDER LOAD AND CAUSING A MASSIVE OUT OF BALANCE VIBRATION. THE SEPARATION OF THE MAIN ROTOR BLADE WAS C ONSIDERED IMMINENT. 1 G 7 1 3O 3 O 4H11 E304 2001011101441 20010111 01441 NM 2001 1 11 AU001152 1 20001115 G 2611 30326E1 AMPLIFIER DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE SMOKE DETECTOR FAULTY W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 AU S (AUS) BAGGAGE COMPARTMENT SMOKE DETECTOR AMPLIFIED FAULTY. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001011101442 20010111 01442 EU 2001 1 11 AU001154 1 20001201 G 2910 F8553048401 HOSE FOKKER F27 F27MK50 EU HYD SYSTEM FAILED W A UNSCHED LANDING K FLUID LOSS CR CRUISE 1 AU S (AUS) LT MAIN LANDING GEAR RETRACTION HOSE BURST. LOSS OF HYDRAULIC FLUID. 2 H 7 2 4T RT A817 2001011101443 20010111 01443 CE 2001 1 11 AU001155 1 20001211 G 3510 51001063 PIPE CESSNA 421 421C 2076016 CE CONT O520 GTSIO520N 17032 SO MCAULY 3FF32 3FF32C501 GL OXYGEN SYSTEM CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) OXYGEN PIPE CORRODED AND LEAKING IN AREA BEHIND PILOTS SEAT SIDELINING. PIPE CONTAINED PIN HOLE CORROSION IN THE A REAS TOUCHING THE SCAT HOSE. 1 L 7 2 3O 3 O A7CE E7CE 5 C P45GL 2001011101444 20010111 01444 SO 2001 1 11 AU001156 2 20001205 G 8550 PUMP PAC CT4 CT4B GL CONT O360 IO360HB 17025 SO HARTZL HCC2Y BHCC2YF1 GL ENGINE OIL FOD W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 AU S 292 (AUS) FOREIGN OBJECT DAMAGE TO ENGINE OIL PUMP. INSPECTION FOUND THAT A SMALL LOOP OF SPRING LIKE STEEL HAD ENTERED THE OIL PUMP ANDJAMMED TO PUMP GEARS CAUSING THE DRIVESHAFT TO SHEAR. INSPECTIONOF THE FOREIGN MATERIAL HAS DETERMINED THAT IT IS NOT FROM ACOMPONENT WITHIN THE ENGINE. 1 L 7 1 3O 3 O RT A9PC E1CE 5 C P920 2001011101445 20010111 01445 NM 2001 1 11 AU001157 1 20001129 G 7920 R14 FILTER ROBSIN R22 R22BETA NM LYC O320 O320B2C 41508 EA ENGINE OIL DISTORTED W O OTHER B SMOKE/FUMES/ODORS/SPARKS LD LANDING 1 AU S (AUS) EXTERNAL ENGINE OIL FILTER MOUNT FACE WARPED AND LEAKING OIL. 1 G 7 1 3O 3 O H10WE E274 2001011101446 20010111 01446 EU 2001 1 11 AU001158 1 20001208 G 7120 BRACKET BNORM BN2 BN2A20 1520220 EU LYC O540 IO540K1B5 41532 EA HARTZL HCC2Y HCC2YK2 GL ENGINE MOUNT CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE MOUNT BRACKETS CRACKED ON SPAR ATTACHMENT FLANGE. FORWARD SPAR CRACKED. 1 H 7 2 3O 3 O A17EU 1E4 5 C P920 2001011101447 20010111 01447 CE 2001 1 11 AU001159 1 20001207 G 2460 CM358940 CIRCUIT BREAKER CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO MCAULY 3AF32C 3AF32C93 GL DC POWER FAILED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 AU S (AUS) AVIONICS CIRCUIT BREAKER/SWITCH INTERNAL FAILURE. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2001011101448 20010111 01448 CE 2001 1 11 AU001160 1 20001130 G 2810 FUEL CELL CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO MCAULY 3AF32C 3AF32C93 GL MAIN CONTAMINATED W A UNSCHED LANDING E VIBRATION/BUFFET CL CLIMB 1 AU S (AUS) FUEL SYSTEM WATER CONTAMINATION. SUSPECT LEAKING FUEL TANK CAPSEALS. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2001011101449 20010111 01449 EA 2001 1 11 AU001161 2 20001130 G 8550 LW13388 GASKET PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA HARTZL HCE3Y HCE3YR2 GL ENGINE DETERIORATED W A UNSCHED LANDING E K J VIBRATION/BUFFET FLUID LOSS WARNING INDICATION CL CLIMB 1 AU S (AUS) ENGINE OIL FILTER CONVERTER PLATE GASKET DETERIORATED AND EXTRUDED. ENGINE OIL LEAKING. FOUND DURING INSPECTION IA W AD/LYC/105. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001011101464 20010111 01464 NM 2001 1 11 AU001162 1 20001120 G 2824 405742 ACTUATOR BOEING 737 737376 NM CFMINT CFM56 CFM563C 13802 EU FUEL TRANSFER FAULTY W A UNSCHED LANDING K FLUID LOSS CR CRUISE 1 AU S 9853 (AUS) FUEL CROSSFEED VALVE ACTUATOR FAULTY. 2 L 7 2 4F 4 F RT A16WE E21EU 2001011101465 20010111 01465 NM 2001 1 11 AU001163 1 20001204 G 5414 196CR PANEL BOEING 767 767238 NM PWA JT9 JT9D7R4E 52054 NE RT PYLON SEPARATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT STRUT TRUNNION ACCESS PANEL SEPARATED FROM AIRCRAFT. THE PANEL CAUSED IMPACT DAMAGE TO THE RT HORIZONTAL STABIL ISER LEADING EDGE AND TOP SKIN. FOLLOWING REMOVAL OF THE REMAINS OF THE DEPARTEDPANEL THE HOLDING TORQUE ON THE ANCHOR N UTS WAS CHECKED WITH FOUR ANCHOR NUTS FAILING THE TORQUE CHECK. 2 L 7 2 4F 4 F RT A1NM E3NE 2001011101466 20010111 01466 NM 2001 1 11 AU001164 1 20001123 G 2520 18DEF SEAT BOEING 737 737400 NM CFMINT CFM56 CFM563C 13802 EU CABIN LOOSE W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) PASSENGER SEAT 18DEF LOOSE DUE TO THE AISLE LEG BEING OUT OF THE TRACK. 2 L 7 2 4F 4 F RT A16WE E21EU 2001011101467 20010111 01467 2001 1 11 AU001165 4 20001117 G 2561 LIFE VEST BOEING 737 737376 NM CFMINT CFM56 CFM563C 13802 EU CABIN MISSING W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) AIRCRAFT HAD A SHORTAGE OF LIFE JACKETS ON BOARD. 2 L 7 2 4F 4 F RT A16WE E21EU 2001011101468 20010111 01468 NM 2001 1 11 AU001166 1 20001112 G 7830 DOOR RROYCE RB211524G BOEING 747 747438 NM RROYCE RB211 RB211524G19 NE THRUST REVERSER SEPARATED W O OTHER E D VIBRATION/BUFFET INFLIGHT SEPARATION LD LANDING 1 AU S (AUS) NR 3 ENGINE THRUST REVERSER BLOCKER DOOR SEPARATED. 2 L 7 4 4F 4 F RT A20WE E30NE 2001011101469 20010111 01469 SW 2001 1 11 AU001167 1 20000918 G 5310 2700 STRUCTURE MOONEY M20 M20C 5870208 SW LYC O360 O360A1D 41514 EA HARTZL HCC2Y HCC2YK1 GL FUSELAGE CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) AIRCRAFT EXTENSIVELY CORRODED IN BOTH WINGS AND FUSELAGE IN NORMALLY INACCESSIBLE AREAS. AIRCRAFT HAD NO CORROSION PROTECTION AT MANUFACTURE. 1 L 7 1 3O 3 O 2A3 E286 5 C P920 2001011101470 20010111 01470 SO 2001 1 11 AU001168 2 20000901 G 8520 CONNECTING ROD PAC CT4 CT4B GL CONT O360 IO360HB 17025 SO HARTZL HCC2Y BHCC2YF1 GL NR 1 CYLINDER FAILED W A UNSCHED LANDING E VIBRATION/BUFFET NR NOT REPORTED 1 AU S (AUS) NR 1 CYLINDER CONNECTING ROD LITTLE END FAILED RESULTING IN CATASTROPHIC ENGINE FAILURE. INVESTIGATION FOUND THAT THE LITTLE END BUSH WAS CRACKED CAUSING THE FAILURE. SUSPECT CRACKING CAUSED BY ENGINE OVERSPEED. 1 L 7 1 3O 3 O RT A9PC E1CE 5 C P920 2001011101471 20010111 01471 CE 2001 1 11 AU001169 1 20001025 G 2731 12600741 ACTUATOR CESSNA 182 182P 2075816 CE CONT O470 O470U 17026 SO MCAULY 2A34C 2A34C203 GL ELEVATOR FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ELEVATOR TRIM ACTUATOR HAD EXCESSIVE PLAY IN THE SHAFT/INTERNAL SCREW COMBINATION RESULTING IN EXCESSIVE TRIM TAB FREEPLAY. THE UNIT HAD ONLY 62.2 HOURS SINCE NEW. 1 H 7 1 3O 3 O NT TA13 E273 5 C P3EA 2001011101472 20010111 01472 EA 2001 1 11 AU001170 2 20001208 G 8530 MS139973 KEY HUGHES 269 269C 4470504 WP LYC O360 HIO360D1A 41514 EA ENGINE DISINTEGRATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NO3 CYLINDER EXHAUST VALVE SPRING LOCKING KEYS SHATTERED BUT WERE STILL HOLDING THE SPRINGS IN PLACE. CAP PNO MS13 998-3 ALSO HADSEVERAL CHIPS MISSING. THE VALVE SEAT WAS DAMAGED BEYOND LIMITS.FOUND DURING INSPECTION IAW LYCOMING SB 38 8B. NO EVIDENCE OFMETAL IN THE OIL FILTERS. 1 G 7 1 3O 3 O 4H12 1E10 2001011101473 20010111 01473 EA 2001 1 11 AU001171 1 20001211 G 3260 864807 PSEU CNDAIR CL600 CL6002B19 EA MLG FAULTY W O OTHER J WARNING INDICATION LD LANDING 1 AU S (AUS) PROXIMITY SENSOR ELECTRONIC UNIT (PSEU) FAULTY. 2 L 7 2 4F RT A21EA 2001011101474 20010111 01474 NM 2001 1 11 AU001172 1 20001214 G 6310 A1161 SHAFT ROBSIN R22 R22BETA NM LYC O320 O320B2C 41508 EA ENGINE CLUTCH SHEARED W K NONE O OTHER IN INSP/MAINT 1 AU S 100 (AUS) CLUTCH SHAFT SHEARED AND CLUTCH DISINTEGRATED. 1 G 7 1 3O 3 O H10WE E274 2001011101475 20010111 01475 NM 2001 1 11 AU001173 1 20000922 G 2133 OUTFLOW VALVE BOEING 737 737476 NM CFMINT CFM56 CFM563C 13802 EU CABIN PRESSURE FAILED W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 AU S (AUS) CABIN PRESSURISATION SYSTEM OUTFLOW VALVE FAULTY. 2 L 7 2 4F 4 F RT A16WE E21EU 2001011101492 20010111 01492 NM 2001 1 11 AU001174 1 20000924 G 4930 FUEL CONTROL BOEING 767 767330 NM APU LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S (AUS) APU FUEL CONTROL UNIT LEAKING FUEL. 2 L 7 2 4F RT A1NM 2001011101493 20010111 01493 NM 2001 1 11 AU001175 1 20000922 G 2133 OUTFLOW VALVE BOEING 737 737400 NM CFMINT CFM56 CFM563C 13802 EU CABIN PRESSURE FAILED W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 AU S (AUS) CABIN PRESSURISATION SYSTEM OUTFLOW VALVE FAILED. 2 L 7 2 4F 4 F RT A16WE E21EU 2001011101494 20010111 01494 EU 2001 1 11 AU001176 1 20000908 G 5311 FRAME AIRBUS 320 A320211 3930320 EU CFMINT CFM56 CFM565A1 NE FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUSELAGE FRAME 35 CRACKED IN AREA BETWEEN STRINGER NO30 AND STRINGER NO31. 2 L 7 2 4F 4 F RT A28NM E29NE 2001011101495 20010111 01495 2001 1 11 AU001177 4 20000702 G 2370 93A10030 CVR BAC 146 146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE COCKPIT FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) COCKPIT VOICE RECORDER FAILED STEPS NR1 1 AND NR 12 OF AMM23-71-00-501. 2 H 7 4 4F 4 F A49EU E6NE 2001011101496 20010111 01496 SO 2001 1 11 AU001178 1 20001118 G 5521 40075016 SPAR PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL ELEVATOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT ELEVATOR SPAR CRACKED AT OUTBOARD END. FOUND DURING INSPECTION IAW AD/PA31/126 AMDT3. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001011101497 20010111 01497 EU 2001 1 11 AU001179 1 20001204 G 2750 9450202201 DRIVE SHAFT PILATS PC12 PC12 7090550 EU TE FLAP CONTROL DAMAGED W O OTHER F FLT CONT AFFECTED NR NOT REPORTED 1 AU S (AUS) RT FLAP INBOARD DRIVESHAFT DAMAGED. 1 L 7 1 3T RT A78EU 2001011101498 20010111 01498 EU 2001 1 11 AU001180 1 20001208 G 6320 332A32100701P TRANSMISSION SNIAS AS332 AS332L 8680809 EU TMECA MAKILA MAKILA1A 60040 EU MAIN ROTOR G/B MAKING METAL W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 AU S 2423 (AUS) MAIN TRANSMISSION MAGNETIC PLUG AND OIL FILTER CONTAMINATED WITHMETAL. 2 G 7 2 4U 4 U H4EU E12NE 2001011101499 20010111 01499 EU 2001 1 11 AU001181 1 20001209 G 3260 WARNING SYSTEM SNIAS AS332 AS332L 8680809 EU TMECA MAKILA MAKILA1A 60040 EU MLG FAULTY W O OTHER N FALSE WARNING LD LANDING 1 AU S (AUS) LANDING GEAR WARNING LIGHTS ILLUMINATED DURING DESCENT. THE LANDING GEAR WAS CONFIRMED DOWN. INVESTIGATION OF THE WARNING SYSTEM COULD FIND NO FAULTS. AIRCRAFT RETURNED TO SERVICE. 2 G 7 2 4U 4 U H4EU E12NE 2001011101500 20010111 01500 EU 2001 1 11 AU001182 1 20001209 G 3230 LANDING GEAR SNIAS AS332 AS332L 8680809 EU TMECA MAKILA MAKILA1A 60040 EU MAINS FAILED W O OTHER J WARNING INDICATION DE DESCENT 1 AU S (AUS) LANDING GEAR WOULD NOT EXTEND. THE GEAR WAS EXTENDED USING THEEMERGENCY SYSTEM. INVESTIGATION COULD FIND NO FAULTS BUT THELANDING GEAR CONTROL PRINTED CIRCUIT BOARD WAS CHANGED AS A PRECAUTION. 2 G 7 2 4U 4 U H4EU E12NE 2001011101501 20010111 01501 EU 2001 1 11 AU001183 1 20001215 G 3320 SMOKE DETECTOR SAAB SF340 340B 7860101 EU GE CT7TP CT79B 30030 NE ROTOL R375 R3754123F21 NE LAVATORY FALSE ACTIVATION W A UNSCHED LANDING N FALSE WARNING CR CRUISE 1 AU S (AUS) LAVATORY SMOKE DETECTOR OPERATED. INVESTIGATION FOUND NO EVIDENCE OF FIRE. 2 L 7 2 4T 4 T RT A52EU E8NE 6 C P17NE 2001011101502 20010111 01502 2001 1 11 AU001184 4 20001206 G 3417 02702MOD6 ADC EMB 120 EMB120 3260201 SO PWA 118 PW118A NE COCKPIT FAULTY W O OTHER J WARNING INDICATION DE DESCENT 1 AU S 0285960 (AUS) AIR DATA COMPUTER (ADC) FAULTY. 2 L 7 2 4T 4 T RT A31SO E20NE 2001011101503 20010111 01503 NM 2001 1 11 AU001185 1 20001203 G 4920 APU DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE APU BAY SHUTDOWN W A UNSCHED LANDING H J ELECT. POWER LOSS-50 PC WARNING INDICATION NR NOT REPORTED 1 AU S (AUS) APU AUTO SHUTDOWN AND OVERHEAT WARNING. INVESTIGATION COULD FINDNO FAULTS. AIRCRAFT RETURNED TO SERVICE. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001011101518 20010111 01518 SO 2001 1 11 AU001186 1 20001210 G 2752 11595CC2127 ACTUATOR GULSTM G1159 GIV 3980115 SO RROYCE TAY TAY6118 EU TE FLAP FAULTY W O OTHER J WARNING INDICATION LD LANDING 1 AU S (AUS) LT OUTBOARD FLAP JACK SCREW ACTUATOR CLUTCH WEAK PREVENTING CORRECT FLAP OPERATION. 2 L 7 2 4F 4 F RT A12EA E25NE 2001011101519 20010111 01519 EA 2001 1 11 AU001188 1 20001203 G 2910 S3250AND PIPE DHAV DHC3 DHC3 2800202 EA HYD SYSTEM BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT MAIN LANDING GEAR BRAKE LINE BROKEN. SUSPECT CAUSED BY PROPELLER WASH DEBRIS. 1 H 7 1 3R A815 2001011101520 20010111 01520 CE 2001 1 11 AU001189 1 20001210 G 3213 508103207 SOCKET BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE LT MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT MAIN LANDING GEAR STRUT SOCKET ASSEMBLY CRACKED IN THE AREA OF ATTACHMENT LUGS. CRACK LENGTHS INBOARD 13.2MM (0 .52IN) ANDOUTBOARD 12.7MM (0.5IN). 2 L 7 2 4T 4 T RT A24CE E26NE 2001011101521 20010111 01521 CE 2001 1 11 AU001190 1 20001210 G 3213 5081032017 SOCKET BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE LT & RT MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT AND RT MAIN LANDING GEAR STRUT SOCKET ASSEMBLIES CRACKED INTHE AREA OF ATTACHMENT LUGS. 2 L 7 2 4T 4 T RT A24CE E26NE 2001011101522 20010111 01522 EA 2001 1 11 AU001193 1 20001208 G 2701 600591567 CAPSTAN CNDAIR CL600 CL6002B19 EA CONTROL COLUMN SLIPPED W O OTHER O OTHER NR NOT REPORTED 1 AU S (AUS) STICK PUSHER CAPSTAN SLIPPING WHEN THE ACTUATOR REACHED FULL TRAVEL ALLOWING THE CONTROL COLUMN TO RETURN FROM ITS FULL TRAVEL STOP AN TO BE DRIVEN TO THE STOP AGAIN. DURING REPLACEMENT OF THE CAPSTAN ONE OF THE CONTROL CABLES RUNNING TO THE STICK PUSH ACTUATOR WAS FOUND TO BE SEPARATED FROM THE SWAGED TERMINAL. 2 L 7 2 4F RT A21EA 2001011101523 20010111 01523 SW 2001 1 11 AU001194 1 20001129 G 2913 PVB04426 PUMP SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE33111U 01514 WP HYD SYSTEM LEAKING W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 AU S 276 (AUS) RT ENGINE DRIVEN HYDRAULIC PUMP LEAKING FLUID FROM BETWEEN PARTING FACES. INVESTIGATION FOUND THAT A CHECK VALVE I N THE RT HYDRAULIC PUMP BYPASS LINE WAS BLOCKED BY DEBRIS FROM PREVIOUS PUMP FAILURES CAUSING A BUILDUP OF PRESSURE ACRO SS THE PUMP WHICH COULD NOT BE BYPASSED THERE FORE CAUSING THE PUMP TO OPEN UP AT APARTING FACE AND ALLOW HYDRAULIC FLUI D TO BE LOST. 2 L 7 2 4T 4 T RT A8SW E4WE 2001011101524 20010111 01524 NE 2001 1 11 AU001195 2 20001213 G 7230 COMPRESSOR BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A42 52043 NE MCAULY 4HFR34 4HFR34C754 NE ENGINE DAMAGED W O OTHER E VIBRATION/BUFFET NR NOT REPORTED 1 AU S (AUS) ENGINE SURGING ABOVE 1400 FTLBS OF TORQUE. BLEED VALVE CHECKEDOK. FIRST STAGE COMPRESSOR BLADES HAD SOME LEADING E DGE ROUGHNESS. RECOVERY WASH CARRIED OUT. STALL/SURGE AT 900 FT LBS ACCOMPANIED BY A LOUD SQUEAL FROM THE ENGINE. SUSPEC T COMPRESSOR SECTION DISTRESS / FAILURE. 1 L 7 2 4T 4 T A24CE E4EA 6 C 3PNE 2001011101525 20010111 01525 EU 2001 1 11 AU001196 1 20001217 G 5510 2712001052901 SKIN FOKKER F27 F27MK500 4990629 EU ROTOL R4304 R1934304 EU HORIZONTAL STAB DELAMINATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT HORIZONTAL STABILISER LEADING EDGE (LAMINATED TIMBER CONSTRUCTION) BADLY DELAMINATED , THE TIMBER SECTION ROTTE D AND THE BONDED SECTION FULL OF WATER. RUBBER BOOT DISBONDED AND INFLATION CELLS PERISHED ON THE TOP SURFACE. 2 H 7 2 4T A817 6 C P899 2001011101526 20010111 01526 EU 2001 1 11 AU001197 1 20001215 G 5342 TB2034021003 BRACKET SOCATA TB10 TB10TOBAGO 8680696 EU LYC O360 O360A1A 41514 EA HARTZL HCC2Y HCC2YK1 GL STABILIZER CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) STABILISER ATTACHMENT BRACKET CONTAINED EXFOLIATION CORROSION INTHE OUTBOARD VERTICAL FACE. 1 L 7 1 3O 3 O RT A51EU E286 5 C P920 2001011101527 20010111 01527 WP 2001 1 11 AU001201 1 20001220 G 6220 A2035 YOKE ROBSIN R22 R22ALPHA 7640104 WP LYC O320 O320B2C 41508 EA MAIN ROTOR HEAD CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MAIN ROTOR YOKE CRACKED IN THE AREA DESCRIBED IN AD/R22/49. 1 G 7 1 3O 3 O H10WE E274 2001011101528 20010111 01528 CE 2001 1 11 AU001202 1 20001212 G 2710 08111481 BRACKET CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO MCAULY 3AF32C 3AF32C87 GL AILERON CONTROL WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) UPPER AILERON BELLCRANK BRACKET WORN ON THE LOWER SIDE. THE WEAR WAS CAUSED BY THE BELLCRANK/CABLE ATTACHMENT CLEV IS PINS RUBBING. 1 L 7 2 3O 3 O 3A10 E5CE 5 C P22EA 2001011101529 20010111 01529 EU 2001 1 11 AU001203 1 20001220 G 2750 CONTACTOR PILATS PC12 PC12 7090550 EU TE FLAP CONTROL FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FLAP MOTOR CONTACTOR SUSPECT FAULTY. 1 L 7 1 3T RT A78EU 2001011101563 20010111 01563 CE 2001 1 11 AU001204 1 20001220 G 2710 CONTROL CABLE CESSNA 172 172A 2072404 CE CONT O300 O300C 17022 SO MCAULY 1C172 1C172EM GL RT AILERON MISINSTALLED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FORWARD LH FLAP RETRACTION CABLE AND RH AILERON CABLES CROSSEDOVER EACH OTHER UNDER THE FLOOR BEHIND THE LANDING G EAR BULKHEAD. FLAP AND AILERON CABLES INCORRECTLY FITTED TO BOTH LOWER OUTERAND LH AND RH PULLEYS BEHIND THE CABIN DOORS . AILERON CABLE STRANDS WORN. PERSONNEL/MAINTENANCE ERROR. 1 H 7 1 3O 3 O 3A12 E253 5 N P910 2001011101564 20010111 01564 CE 2001 1 11 AU001205 1 20001205 G 3213 5081032011 STRUT BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE HARTZL HCE4A HCE4A3A NE MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT MAIN LANDING GEAR STRUCK BY A KANGAROO. INSPECTION FOUND THE LT MAIN LANDING GEAR AXLE AND TORQUE KNEE SOCKET C RACKED AT THE LOWER END OF THE TORQUE KNEE ATTACHMENT LUGS. CRACK LENGTH11.43MM (0.45IN). 2 L 7 2 4T 4 T RT A24CE E26NE 5 C P10NE 2001040200308 20010402 00308 NM 2001 4 2 AU001206 1 20001211 G 3240 215152 HEAT SHIELD BOEING 747 747438 NM RROYCE RB211 RB211524G19 NE MLG DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NR 12 BRAKE HEAT SHIELD DISTORTED AND CUT A GROOVE INTO THE WHEELHUB. THE HEAT SHIELD APPEARS TO HAVE BEEN DAMAGED BY IMPACT SOMETIME PREVIOUSLY. 2 L 7 4 4F 4 F RT A20WE E30NE 2001040200309 20010402 00309 NM 2001 4 2 AU001207 1 20001225 G 3244 6558256281 TIRE BOEING 737 737476 NM CFMINT CFM56 CFM563C 13802 EU LT NLG FAILED W C ABORTED TAKEOFF E VIBRATION/BUFFET TO TAKEOFF 1 AU S 211 (AUS) LT NOSE WHEEL TYRE SHREDDED. THE TIRE WAS STILL INFLATED. 2 L 7 2 4F 4 F RT A16WE E21EU 2001040200310 20010402 00310 NM 2001 4 2 AU001208 1 20001220 G 3510 HOSE BOEING 737 737376 NM CFMINT CFM56 CFM563C 13802 EU CREW OXYGEN LEAKING W O OTHER O OTHER NR NOT REPORTED 1 AU S (AUS) CREW OXYGEN SYSTEM HOSE LEAKING. HOSE IS LOCATED IN AN AREA BELOW THE FIRST OFFICERS OXYGEN MASK BOX. 2 L 7 2 4F 4 F RT A16WE E21EU 2001040200311 20010402 00311 EA 2001 4 2 AU001209 2 20001026 G 7240 PCE22284 BRACKET PIPER PA36 PA36375 7103620 SO PWA PT6 PT6A20 52043 EA HARTZL HCB3T HCB3TN3 GL ENGINE CASE FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE GAS GENERATOR OUTER CASE BRACKET BROKE OF THE CASE LEAVING TWO HOLES OF APPROXIMATELY 9.525MM (0.375IN) IN THE CASE. THE BRACKET IS WELDED TO THE GAS GENERATOR CASE AND IS USED TOSUPPORT THE FORWARD FIRESEAL BULKHEAD ASSEMBLY. 1 L 7 1 3O 3 T A10SO E4EA 6 C P15EA 2001040200312 20010402 00312 CE 2001 4 2 AU001210 1 20001219 G 3221 6042001 TRUNNION CESSNA 402 402A 207590M CE CONT O520 TSIO520E 17040 SO MCAULY 3AF32C 3AF32C87 GL NLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NOSE LANDING GEAR TRUNNION CRACKED AROUND THE TRUNNION PINS. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2001040200313 20010402 00313 NE 2001 4 2 AU001211 3 20001220 G 6114 7823011 BEARING HAMSTD 7827015 DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE PROP HUB GALLED W K NONE O OTHER IN INSP/MAINT 1 AU S 8000 860628 (AUS) PROPELLER HUB BLADE RETAINING BEARING OUTER RACE GALLED. FOUND DURING SCHEDULED BLADE CHANGE. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001040200314 20010402 00314 CE 2001 4 2 AU001212 1 20001219 G 3221 6042001 TRUNNION CESSNA 402 402B 207590P CE CONT O520 TSIO520E 17040 SO MCAULY 3AF32C 3AF32C87 GL NLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NOSE LANDING GEAR TRUNNION CRACKED IN AREA AROUND TRUNNION PINS. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2001040200315 20010402 00315 NE 2001 4 2 AU001213 2 20001226 G 7310 218376002 LINE LYC ALF502R5 BAC 146 146100A 1500260 EU LYC ALF502 ALF502R5 41580 NE FUEL DIST FAILED W O OTHER E B J VIBRATION/BUFFET SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CR CRUISE 1 AU S (AUS) NR 3 ENGINE FUEL LINE LOCATED BETWEEN THE FLOW DIVIDER AND FUELMANIFOLD FRACTURED AND LEAKING FUEL. FUEL IGNITED C AUSING DAMAGETO THE WIRING HARNESS AND TGT HARNESS. 2 H 7 4 4F 4 F RT A49EU E6NE 2001040200316 20010402 00316 NM 2001 4 2 AU001214 1 20001218 G 7110 2242301513 COWLING BOEING 767 767338 1385151 NM GE CF6 CF680C2* GL ENGINE MISSING W K NONE O OTHER IN INSP/MAINT 1 AU S 38787 (AUS) RT ENGINE LT CORE COWL MISSING A SECTION APPROXIMATELY 254MM BY 304.8MM (10IN BY 12IN) WHICH INCLUDED THE SUPPORT FRAME. THEENGINE MOUNT WAS EXPOSED. 2 L 7 2 4F 4 F RT A1NM E23EA 2001040200317 20010402 00317 NM 2001 4 2 AU001215 1 20001027 G 2742 AR7077M3 ACTUATOR BOEING 737 737476 NM CFMINT CFM56 CFM563C 13802 EU STABILIZER FAULTY W O OTHER F FLT CONT AFFECTED CR CRUISE 1 AU S 18131 (AUS) HORIZONTAL STABILISER TRIM MOTOR FAULTY. 2 L 7 2 4F 4 F RT A16WE E21EU 2001040200318 20010402 00318 NM 2001 4 2 AU001216 1 20001105 G 2520 908356G SEAT BOEING 737 737400 NM CFMINT CFM56 CFM563C 13802 EU CABIN SEPARATED W D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 AU S 2281 (AUS) FLIGHT ATTENDANT FORWARD DOUBLE SEAT SEPARATED FROM WALL. 2 L 7 2 4F 4 F RT A16WE E21EU 2001040200013 20010402 00013 NM 2001 4 2 AU001217 1 20001031 G 3810 S417T2006 TANK SNO0506 BOEING 767 767338 1385151 NM GE CF6 CF680C2* GL POTABLE WATER RUPTURED W D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 AU S 0506 (AUS) RT MAIN POTABLE WATER TANK SUPPORTING RODS (3OFF) BROKEN ALLOWING THE TANK TO COLLAPSE ONTO THE TOILET FAN AND RUP TURE. 2 L 7 2 4F 4 F RT A1NM E23EA 2001040200014 20010402 00014 NM 2001 4 2 AU001218 1 20001211 G 2761 69B841881 BOLT BOEING 747 747400 NM GE CF6 CF680C2* GL DRAG CONTROL MISSING W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NT 4 SPOILER ACTUATOR ROD END BOLT / NUT / BUSHING MISSING. 2 L 7 4 4F 4 F RT A20WE E23EA 2001040200015 20010402 00015 2001 4 2 AU001219 4 20001211 G 3460 6224717003 CONTROL PANEL BOEING 767 767338 1385151 NM GE CF6 CF680C2* GL FLIGHT COMPUTER FAULTY W O OTHER B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 AU S (AUS) MODE CONTROL PANEL FAULTY. 2 L 7 2 4F 4 F RT A1NM E23EA 2001040200016 20010402 00016 NM 2001 4 2 AU001220 1 20001017 G 2810 BACB30US12K56 BOLT BOEING 747 747338 NM RROYCE RB211 RB211524D419 54555 NE FUEL STORAGE BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) REAR SPAR LOWER LT SPLICE PLATE / CENTER WING TANK BOLT BROKEN. THE BOLT SHANK WAS COMPLETELY SEVERED AND THE BOLT HEAD WAS PROTRUDING APPROXIMATELY 19.05MM (0.75IN) INTO THE CENTER WING TANK WITH SURROUNDING SEALANT DAMAGE EVIDENT. F OUND DURING INSPECTION IAW 747-028-0019. 2 L 7 2 4F 4 F RT A20WE E12EU 2001040200017 20010402 00017 NM 2001 4 2 AU001221 1 20001016 G 5414 PANEL BOEING 737 737476 NM CFMINT CFM56 CFM563C 13802 EU LT PYLON CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT PYLON PANEL 5727L REPAIR DOUBLER CRACKED. DOUBLER WAS FITTED IAW SB 7737-54-1035. 2 L 7 2 4F 4 F RT A16WE E21EU 2001040200018 20010402 00018 NM 2001 4 2 AU001222 1 20001016 G 7110 401B1613000059 COWLING BOEING 767 767338 1385151 NM GE CF6 CF680C2* GL ENGINE SEPARATED W O OTHER D INFLIGHT SEPARATION CR CRUISE 1 AU S (AUS) RT ENGINE INBOARD TRANSLATING COWL INNER SKIN SECTION SEPARATED. SIZE OF SEPARATED SECTION APPROXIMATELY 304.8MM B Y 609.6MM (12INBY 24IN). 2 L 7 2 4F 4 F RT A1NM E23EA 2001040200019 20010402 00019 WP 2001 4 2 AU001223 1 20001222 G 5540 3115125 BRACKET DOUG DC3 DC3CS1C3G 3021458 WP PWA R1830 R183092 52020 NE HAMSTD 23E 23E50 NE RUDDER CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S 142 (AUS) RUDDER HINGE BRACKETS CORRODED. 2 L 7 2 4R 4 R A669 5E4 6 C P603 2001040200020 20010402 00020 EU 2001 4 2 AU001225 1 20001219 G 5246 LATCH BAG BAE146 BAE146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE FUEL PANEL OPEN W O OTHER W J INADEQUATE Q C WARNING INDICATION CL CLIMB 1 AU S (AUS) REFUEL PANEL LATCH LOCATED ADJACENT TO DOOR WARNING MICROSWITCH WAS UNLATCHED. 2 H 7 4 4F 4 F RT A49EU E6NE 2001040200021 20010402 00021 EU 2001 4 2 AU001226 1 20001222 G 2810 N382602 CAP BAG BAE146 BAE146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE FUEL CELL MISSING W O OTHER D K J INFLIGHT SEPARATION FLUID LOSS WARNING INDICATION CL CLIMB 1 AU S (AUS) LT OVERWING FUEL CAP MISSING. LOSS OF APPROXIMATELY 230KG OF FUEL. 2 H 7 4 4F 4 F RT A49EU E6NE 2001040200022 20010402 00022 NM 2001 4 2 AU001227 1 20001212 G 5350 195CL FAIRING BOEING 767 767338 1385151 NM GE CF6 CF680C2* GL WING TO BODY MISSING W O OTHER O OTHER NR NOT REPORTED 1 AU S (AUS) LT WING TO BODY FAIRING PANEL 195CL MISSING. 2 L 7 2 4F 4 F RT A1NM E23EA 2001040300011 20010403 00011 NE 2001 4 3 AU001228 2 20001226 G 7320 6055T19P14 HYDROMECH UNIT SAAB SF340 SF340A 7850100 EU GE CT7TP CT75A2 30030 NE ROTOL R354 R3544123F13 NE FUEL CONTROL FAULTY W C ABORTED TAKEOFF R J PARTIAL RPM/PWR LOSS WARNING INDICATION TO TAKEOFF 1 AU S 12938 (AUS) LT ENGINE COMPRESSOR STALL (SURGE). OPERATING LIMITS EXCEEDED. SUSPECT CAUSED BY FAULTY HYDROMECHANICAL UNIT (HMU) . 2 L 7 2 4T 4 T RT A52EU E8NE6 6 C P61GL 2001040200023 20010402 00023 EU 2001 4 2 AU001229 1 20001204 G 2433 TRANSFORMER BAG BAE146 BAE146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE RECTIFIER FAULTY W O OTHER H J ELECT. POWER LOSS-50 PC WARNING INDICATION CR CRUISE 1 AU S (AUS) SUSPECT NR 1 AND NR 2 TRANSFORMER RECTIFIER UNITS (TRU) HAD INTERMITTENT FAULTS CAUSING CIRCUIT BREAKERS TO TRIP. SUSPECT ALSO THAT CONTACTORS XD4 AND XD5 WERE INTERMITTENT IN OPERATION. 2 H 7 4 4F 4 F RT A49EU E6NE 2001040200024 20010402 00024 EU 2001 4 2 AU001230 1 20001218 G 7931 1241013 TRANSMITTER BAG JETSTM JETSTM3201 1500217 EU GARRTT TPE331 TPE33112UA 01514 WP MCAULY 4HFR34 4HFR34C653 NE OIL PRESSURE FAULTY W O OTHER N FALSE WARNING CR CRUISE 1 AU S (AUS) RT ENGINE OIL PRESSURE TRANSMITTER FAULTY. 2 L 7 2 4T 4 T RT A56EU E4WE 6 C 3PNE 2001040200025 20010402 00025 EU 2001 4 2 AU001231 1 20001224 G 2910 NAS16126 O-RING FOKKER F28 F28MK0100 4990807 EU RROYCE TAY TAY62015 04564 NE HYDRAULIC SYS SPLIT W O OTHER K FLUID LOSS CR CRUISE 1 AU S (AUS) NR 1 HYDRAULIC SYSTEM PRESSURE SWITCH O-RING SEAL SPLIT. 2 L 7 2 4F 4 F RT E25NE 2001040200026 20010402 00026 2001 4 2 AU001232 4 20001217 G 3418 EASPC850340 COMPUTER FOKKER F28 F28MK0100 4990807 EU RROYCE TAY TAY62015 04564 NE STALL WARNING FAULTY W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 AU S 932 (AUS) STALL PROTECTION COMPUTER FAULTY. 2 L 7 2 4F 4 F RT E25NE 2001040200027 20010402 00027 CE 2001 4 2 AU001233 1 20001229 G 3222 35820115 BEARING BEECH 33 E33 1151422 CE CONT O470 IO470K 17026 SO MCAULY 2A36C 2A36C23 GL NLG WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NOSE LANDING GEAR BEARING WORN EXCESSIVELY. THE THICKNESS OF THEBEARING SURFACE WAS 1.143MM (0.045IN). WHEN NEW TH E THICKNESS IS1.57MM (0.0625IN). TO COMPENSATE FOR WEAR A BRONZE SPACER RING2.74MM (0.108IN) WAS FITTED BETWEEN THE WORN BEARING AND THEBARREL RESULTING IN MISALIGNMENT OF THE SHIMMY DAMPER AND BENDING OF THE ACTUATING ROD. PERSONNEL/MAINTE NANCE ERROR. UNAPPROVED PART. 1 L 7 1 3O 3 O 3A15 3E1 5 C P880 2001040200028 20010402 00028 CE 2001 4 2 AU001234 1 20001229 G 7800 61199 GASKET CESSNA 150 150F 2071814 CE CONT O200 O200A 17020 SO SNSNCH 69CK M69CK EA EXHAUST SYS MISINSTALLED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) NR 3 CYLINDER EXHAUST GASKET INCORRECTLY FITTED ON ONLY ONE STUD.DURING TIGHTENING OF THE EXHAUST THE FLANGE CRACK ED AS WELL ASTHE WELD BETWEEN THE FLANGE AND THE PIPE. LT MUFFLER BAFFLE PIPEALSO ERODED. 1 H 7 1 3O 3 O 3A19 E252 5 N P9045 2001040200029 20010402 00029 SO 2001 4 2 AU001235 2 20001229 G 8530 662200 PISTON CESSNA 150 150F 2071814 CE CONT O200 O200A 17020 SO SNSNCH 69CK M69CK EA CYLINDER CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NR 1, NR 2 AND NR 4 CYLINDER PISTONS CRACKED BETWEEN OIL HOLES. THEPISTONS ARE MANUFACTURED BY WELLWORTH CASTING NUMBER A470102 AND ARE DIFFERENT TO THE CONTINENTAL MANUFACTURED PISTON IN HAVINGTEN OIL HOLES UNDER THE OIL RING WHERE CONTINENTAL PISTONS HAVE EIGHT HOLES BELOW THE OIL RING. LOG BOOK INDICATES THAT NO3 PISTON WAS PREVIOUSLY CRACKED AND H AD BEEN REPLACE BY A CONTINENTAL PNO 530348. 1 H 7 1 3O 3 O 3A19 E252 5 N P9045 2001040200030 20010402 00030 SO 2001 4 2 AU001236 1 20001219 G 2140 A98040136 VALVE PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL HEATER MISSING W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) CABIN HEATER FITTED WITHOUT USING PIPER KIT 764-005 SL 894. NO DUCTING OR AIR SHUTOFF VALVE FITTED BETWEEN AIR SCO OP AND HEATER. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001040200031 20010402 00031 NE 2001 4 2 AU001237 2 20001227 G 7200 ENGINE BAC 146 146300A 1500267 EU LYC ALF502 ALF502R5 41580 NE NR 1 FAILED W O OTHER E M VIBRATION/BUFFET OVER TEMP NR NOT REPORTED 1 AU S (AUS) NR 1 ENGINE FAILED. A LOUD BANG WAS HEARD FROM THE ENGINE WITH THE TGT INCREASING TO 1000 DEGREES BEFORE SHUTDOWN. 2 H 7 4 4F 4 F RT A49EU E6NE 2001040200032 20010402 00032 NM 2001 4 2 AU001239 1 20001230 G 2910 82950010269 LINE DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE HYDRAULIC SYS SPLIT W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S (AUS) HYDRAULIC LINE SPLIT AND LEAKING. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001040200033 20010402 00033 CE 2001 4 2 AU001240 1 20001229 G 7120 S7510088 MOUNT CESSNA 441 441 2076020 CE GARRTT TPE331 TPE3318 01514 WP HARTZL HCB3T HCB3TN5 GL RT ENGINE BROKEN W O OTHER O OTHER NR NOT REPORTED 1 AU S (AUS) RT ENGINE INBOARD MOUNT BROKEN. ENGINE HAD DROPPED APPROXIMATELY38.1MM (1.5IN). 1 L 7 2 3T 4 T RT A28CE E4WE 6 C P15EA 2001040200034 20010402 00034 SW 2001 4 2 AU001241 1 20001204 G 7722 CONNECTOR SWRNGN SA227 SA227* SW GARRTT TPE331 TPE33112UHR WP EGT/TIT INDICATO CORRODED W O OTHER E VIBRATION/BUFFET CL CLIMB 1 AU S (AUS) LT ENGINE EGT SYSTEM CONNECTOR PLUG CORRODED. 2 L 7 2 4T 4 T RT A5SW E4WE 2001040200206 20010402 00206 SW 2001 4 2 AU001242 1 20001206 G 7712 SIGNAL COND UNIT SWRNGN SA227 SA227* SW GARRTT TPE331 TPE33112UHR WP BMEP/TORQ IND OUT OF ADJ W O OTHER N FALSE WARNING CL CLIMB 1 AU S (AUS) RT ENGINE TORQUE SIGNAL CONDITIONER OUT OF ADJUSTMENT. 2 L 7 2 4T 4 T RT A5SW E4WE 2001040200035 20010402 00035 SW 2001 4 2 AU001244 1 20001226 G 2752 GEAR AIRTRC AT802 AT802 0390305 SW PWA PT6 PT6A65R 52043 EA TE FLAP ACTUATOR WORN W O OTHER O OTHER NR NOT REPORTED 1 AU S (AUS) FLAP ACTUATOR FAULTY. INVESTIGATION FOUND THE WORM GEAR AND DRIVE GEAR WORN. 1 L 7 1 3T 4 T NC A19SW E4EA 2001040200036 20010402 00036 EU 2001 4 2 AU001245 1 20001228 G 2611 FR2212 SMOKE DETECTOR SNIAS AS332 AS332L 8680809 EU TMECA MAKILA MAKILA1A 60040 EU CARGO BAY FAULTY W O OTHER N FALSE WARNING CR CRUISE 1 AU S 377 (AUS) BAGGAGE BAY SMOKE DETECTOR FAULTY. HEATER HOT AIR VALVE STUCK INOPEN'' POSITION. 2 G 7 2 4U 4 U H4EU E12NE 2001040200037 20010402 00037 CE 2001 4 2 AU001246 1 20001230 G 5511 553200048 SPAR CESSNA 500 S550 2076607 CE PWA JT15 JT15D1 52060 NE HORIZONTAL STAB CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) HORIZONTAL STABILISER REAR SPAR AND UPPER SPAR CAP CORRODED.FOUND DURING REMOVAL OF THE UPPER RH SKIN DUE TO DELAM INATION. 1 L 7 2 4F 4 F RT A22CE E1NE 2001040200038 20010402 00038 CE 2001 4 2 AU001247 1 20001003 G 5610 10138402515 WINDSHIELD BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A42 52043 NE COCKPIT CRACKED W O OTHER O OTHER CL CLIMB 1 AU S (AUS) LT WINDSHIELD OUTER PANE CRACKED. 1 L 7 2 4T 4 T A24CE E4EA 2001040200039 20010402 00039 CE 2001 4 2 AU001249 1 20001219 G 2731 ACTUATOR CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO MCAULY 3AF32C 3AF32C93 GL ELEVATOR TRIM FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S 162 (AUS) ELEVATOR TRIM ACTUATOR HAD EXCESSIVE END PLAY RESULTING INEXCESSIVE ELEVATOR TAB FREE PLAY. ACTUATOR HAD BEEN OVER HAULED162 HOURS PREVIOUSLY. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2001040200040 20010402 00040 EA 2001 4 2 AU001250 1 20001018 G 2823 DIAPHRAGM DHAV DHC2 DHC2MK1 2800102 EA PWA R985 R985AN14B 52008 NE HAMSTD 2D 2D30 NE FUEL SELECTOR SPLIT W O OTHER O OTHER NR NOT REPORTED 1 AU S (AUS) FUEL SELECTOR VALVE DIAPHRAGM / SEAL SPLIT. SELECTOR STIFF TO OPERATE. 1 H 7 1 3R 3 R A806 5E1 5 C P206 2001040200041 20010402 00041 SO 2001 4 2 AU001251 1 20001213 G 2434 23080013 GENERATOR EMB 120 EMB120 3260201 SO PWA 118 PW118A NE HAMSTD 14SF 14SF9 NE NR 2 FAILED W C ABORTED TAKEOFF H J ELECT. POWER LOSS-50 PC WARNING INDICATION TO TAKEOFF 1 AU S 1320 (AUS) NR 2 (RT) MAIN GENERATOR FAILED. 2 L 7 2 4T 4 T RT A31SO E20NE 6 N P11NE 2001040200042 20010402 00042 NM 2001 4 2 AU001252 1 20001230 G 7603 38925085 CONTROL BOX BOEING 747 747238B 1384828 NM RROYCE RB211 RB211524D419 54555 NE POWER LEVER DAMAGED W C ABORTED TAKEOFF R J PARTIAL RPM/PWR LOSS WARNING INDICATION TO TAKEOFF 1 AU S (AUS) NR 1 ENGINE FFR THROTTLE CONTROL BOX RACK DAMAGED. 2 L 7 4 4F 4 F A20WE E12EU 2001040200043 20010402 00043 2001 4 2 AU001253 4 20001225 G 2565 20131 BATTERY 20121 BOEING 767 767332 1382001 NM GE CF6 CF680C2* GL ESCAPE SLIDE FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT AND RT ESCAPE SLIDE BATTERY PACK AND CHARGER ASSEMBLIES FAULTY. 2 L 7 2 4F 4 F RT A1NM E23EA 2001040200044 20010402 00044 NM 2001 4 2 AU001254 1 20001230 G 2497 WIRE BOEING 767 767338 1385151 NM GE CF6 CF680C2* GL ELECTRICAL POWER DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) GROUND SERVICE FEEDER WIRING BURNT AND DAMAGED. 2 L 7 2 4F 4 F RT A1NM E23EA 2001040200045 20010402 00045 NM 2001 4 2 AU001255 1 20001229 G 2410 735511A RELIEF VALVE BOEING 737 737376 NM CFMINT CFM56 CFM563C 13802 EU ALTERNATOR FAILED W O OTHER J WARNING INDICATION CR CRUISE 1 AU S 1558 (AUS) NR 2 ENGINE CONSTANT SPEED DRIVE (CSD) INTERNAL FAILURE. INVESTIGATION FOUND THAT THE OIL PRESSURE RELIEF VALVE HA D BLOWNOUT AND THE ATTACHMENT BOLTS HAD SHEARED. OIL LOSS THEN CAUSED CSD FAILURE. 2 L 7 2 4F 4 F RT A16WE E21EU 2001040200046 20010402 00046 NM 2001 4 2 AU001256 1 20001217 G 5320 EO180401 COVER BOEING 767 767238 NM PWA JT9 JT9D7R4E 52054 NE FUSELAGE MISSING W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) BULK CARGO VENT COVER MISSING. AD/B767/65 AND FAA AD FAD 92-02-12 REQUIRE THE COVER TO BE FITTED FOLLOWING REMOVAL OF THE BULK CARGO VENTILATION VALVE IAW BOEING SB 767-21A0098. 2 L 7 2 4F 4 F RT A1NM E3NE 2001040200047 20010402 00047 NM 2001 4 2 AU001257 1 20001228 G 5260 STRUCTURE DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE AIRSTAIR DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) AIRSTAIR COMPONENTS BROKEN AND BADLY WORN. MAIN CABIN DOOR COULD NOT BE OPENED. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001040200207 20010402 00207 CE 2001 4 2 AU001258 1 20001220 G 2731 0861100164 WHEEL CESSNA 441 441 2076020 CE GARRTT TPE331 TPE3318 01514 WP HARTZL HCB3T HCB3TN5 GL ELEVATOR TRIM BROKEN W C ABORTED TAKEOFF F FLT CONT AFFECTED TO TAKEOFF 1 AU S (AUS) ELEVATOR TRIM WHEEL POINTER GROOVE BROKEN. 1 L 7 2 3T 4 T RT A28CE E4WE 6 C P15EA 2001040200048 20010402 00048 EU 2001 4 2 AU001259 1 20001222 G 7603 CABLE LYC ALF502R5 BAG BAE146 BAE146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE POWER LEVER CONTAMINATED W O OTHER O OTHER DE DESCENT 1 AU S (AUS) NR 4 ENGINE THROTTLE CABLE CONTAMINATED WITH DIRT AND STIFF IN OPERATION. 2 H 7 4 4F 4 F RT A49EU E6NE 2001040200049 20010402 00049 EU 2001 4 2 AU001260 1 20000409 G 2752 JACKSCREW BAC 146 146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE TE FLAP ACTUATOR FAULTY W O OTHER F FLT CONT AFFECTED AP APPROACH 1 AU S (AUS) RT OUTBOARD FLAP JACKSCREW SUSPECT FAULTY. INVESTIGATION COULD NOT CONFIRM THE DEFECT ALTHOUGH THE JACKSCREW WAS N OTCHY IN OPERATION. 2 H 7 4 4F 4 F A49EU E6NE 2001040200050 20010402 00050 GL 2001 4 2 AU001261 2 20001201 G 7230 23057142 CASE AEROSP AS355 AS355F1 8680810 EU ALLSN 250C 250C20F 03013 GL COMPRESSOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NR 2 ENGINE LOWER COMPRESSOR CASE HALF HAD DEBONDING OF THEPLASTIC BAND SECTION BETWEEN NR 3 AND NR 4 STAGES. EXCE SSIVE SPOOL RUB EVIDENT ON THE PLASTIC SECTIONS CAUSING EXCESSIVE CRACKING. CIRCUMFERENTIAL CRACKING WAS FOUND ACROSS TH E ENTIRE SECTION OF THE THIRD AND FOURTH STAGE BAND PLASTIC SECTION. SUSPECT CAUSED BY CORROSION. 1 G 7 2 3U 3 U H11EU E4CE 2001040200051 20010402 00051 NM 2001 4 2 AU001262 1 20001211 G 2751 TRANSMITTER BOEING 737 737377 NM GE CFM56 CFM563B1 13802 NE TE FLAP POSITION OUT OF ADJ W O OTHER F FLT CONT AFFECTED DE DESCENT 1 AU S (AUS) LT TRAILING EDGE FLAP TRANSMITTER OUT OF ADJUSTMENT. 2 L 7 2 4F 4 F RT A16WE E2GL 2001040200052 20010402 00052 CE 2001 4 2 AU001263 1 20001202 G 2133 903800003 REGULATOR BEECH 200 B200C 1152924 CE PWA PT6 PT6A41 52043 EA P3 AIR LEAKING W K NONE O OTHER IN INSP/MAINT 1 AU S 11965 (AUS) PRESSURE REGULATOR LEAKING P3 AIR INTO CABIN. INTERNAL INSPECTION FOUND ALL SEALS WORN AND THE REGULATOR WORN AND LEAKING. 1 L 7 2 4T 4 T A24CE E4EA 2001040200066 20010402 00066 EA 2001 4 2 AU001264 2 20001201 G 8530 75838 VALVE GUIDE PIPER PA32 PA32RT300T 7103216 SO LYC O540 TIO540S1AD 41532 EA HARTZL HCE2Y HCE2YR1 GL ENGINE FAILED W O OTHER E VIBRATION/BUFFET TO TAKEOFF 1 AU S (AUS) NR 5 CYLINDER EXHAUST VALVE GUIDE BROKEN UP. PIECES OF THE VALVE GUIDE EXITED THE CYLINDER AND JAMMED AND DAMAGED THE TURBOCHARGER TURBINE. NR 5 CYLINDER EXHAUST VALVE NECKED AND COLLETTS WORN. 1 L 7 1 3O 3 O A3SO E14EA 5 C P9EA 2001040200067 20010402 00067 NM 2001 4 2 AU001265 1 20001231 G 5330 SKIN BOEING 727 727277 138408S NM PWA JT8 JT8D15 52051 NE FUSELAGE CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S 47862 (AUS) RT SIDE FUSELAGE SKIN CONTAINED LEVEL 2 CORROSION AT STN 1420 INAREA ABOVE NR 2 ENGINE. SKIN BULGED AND FASTENERS SHEARED. FOUND DURING CORROSION PREVENTION AND CONTROL PROGRAM. 2 L 7 3 4F 4 F RT A3WE E2EA 2001040200068 20010402 00068 CE 2001 4 2 AU001266 1 20001031 G 2750 SWITCH CESSNA 402 402B 207590P CE CONT O520 TSIO520E 17040 SO MCAULY 3AF32C 3AF32C87 GL TE FLAP CONTROL OUT OF ADJ W O OTHER F FLT CONT AFFECTED LD LANDING 1 AU S (AUS) FLAP SELECTOR SWITCHES OUT OF ADJUSTMENT. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2001040200069 20010402 00069 NM 2001 4 2 AU001267 1 20001227 G 2520 91012 SEAT DHAV DHC8 DHC8103 1386005 NM PWA 120 PW123D 52152 NE HAMSTD 14SF 14SF23 NE CABIN LOOSE W O OTHER O OTHER DE DESCENT 1 AU S (AUS) SEAT SEPARATED FROM SEAT TRACK DURING TURBULENCE. SUSPECT SEATINCORRECTLY LOCKED IN TRACK DURING FITMENT. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001040200070 20010402 00070 NE 2001 4 2 AU001268 2 20001209 G 7250 INLET GUIDE VANE BELL 212 212 1181420 SW PWA PT6T PT6T3B 52045 NE NR 1 ENGINE DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NR 1 ENGINE EXPERIENCED CONTINUOUS HIGH TEMPERATURES. INVESTIGATION FOUND THE FOLLOWING DEFECTS: HOLE BURNED IN IN LET GUIDE VANE. FIRST STAGE NOZZLE BURNED WITH A PIECE MISSING. T5 HARNESS THERMOCOUPLE END BURNED OFF. POWER TURBINE VA NE RING CRACKED BETWEEN ADJACENT BLADES. 1 G 7 1 4U 4 U H4SW E22EA 2001040200071 20010402 00071 SO 2001 4 2 AU001269 2 20001127 G 8520 6419311075 BOLT CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO CRANKCASE BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LOWER THOUGH BOLT BETWEEN NR 2 AND NR 3 CYLINDERS BROKEN 35MM (1.5IN) FROM THE LEFT END OF THE BOLT IN THE O'' RIN G SEAL GROOVE. 1 L 7 2 3O 3 O A7CE E8CE 2001040200072 20010402 00072 SO 2001 4 2 AU001270 2 20001025 G 8520 6419311075 BOLT CESSNA 206 TU206G 2073357 CE CONT O520 TSIO520M 17040 SO ENGINE BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) UPPER THROUGH BOLT LOCATED BETWEEN NR 2 AND NR 3 CYLINDERS BROKEN.FAILURE OCCURRED APPROXIMATELY 76.2MM (3IN) FROM THE LEFT END OF THE BOLT. 1 H 7 1 3O 3 O A4CE E8CE 2001040200073 20010402 00073 CE 2001 4 2 AU001271 1 20000504 G 3213 51411036 STRUT CESSNA 402 402C 207590R CE RT MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT MAIN LANDING GEAR UPPER BARREL ASSEMBLY CRACKED ON THE INNER RADIUS OF THE TORQUE LINK COLLAR LUG. FOUND DURING FLUORESCENT MAGNETIC PARTICLE INSPECTION (MAGNAFLUX) IAW MEB89-2 R1. 1 L 7 2 3O A7CE 2001040200074 20010402 00074 CE 2001 4 2 AU001272 1 20000504 G 3211 51227202 TRUNNION CESSNA 402 402C 207590R CE RT MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT MAIN LANDING GEAR FORWARD TRUNNION CRACKED ON THE TOP WEB ADJACENT TO THE GEAR ATTACHMENT BEARING. FOUND DURING FLUORESCENT DYE PENETRANT INSPECTION IAW MEB85-11 R4. 1 L 7 2 3O A7CE 2001040200075 20010402 00075 CE 2001 4 2 AU001273 1 20001012 G 3230 51420023 DRAG BRACE CESSNA 402 402C 207590R CE NLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NOSE LANDING GEAR DRAG BRACE CRACKED IN THE RADIUS OF THE ACTUATOR ATTACHMENT POINT. FOUND USING DYE PENETRANT INS PECTION IAW MEB91-11 AND CESSNA CAP 32-20-00. 1 L 7 2 3O A7CE 2001040200076 20010402 00076 CE 2001 4 2 AU001274 1 20000504 G 3211 51227201 TRUNNION CESSNA 402 402C 207590R CE MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MAIN LANDING GEAR FORWARD TRUNNION CRACKED IN THE TOP WEB ADJACENT TO THE GEAR ATTACHMENT BEARING. FOUND DURING FL UORESCENT DYE PENETRANT INSPECTION IAW MEB85-11 R4. 1 L 7 2 3O A7CE 2001040200077 20010402 00077 EU 2001 4 2 AU001275 1 20001025 G 5711 SPAR BAG BAE146 BAE146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE RT WING CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT AND RT WING FORWARD AND AFT SPARS CONTAINED PITTING CORROSION IN AREA BETWEEN RIB NR 13 AND RIB NR 18. 2 H 7 4 4F 4 F RT A49EU E6NE 2001040200078 20010402 00078 EU 2001 4 2 AU001276 1 20001215 G 5711 SPAR BAC 146 146100A 1500260 EU LYC ALF502 ALF502R5 41580 NE RT & LT WING CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT AND RT WING FORWARD AND AFT SPARS CONTAINED SUSPECT INTERGRANNULAR CORROSION IN AREAS LOCATED OUTBOARD OF RIB N R 13. 2 H 7 4 4F 4 F RT A49EU E6NE 2001040200080 20010402 00080 SO 2001 4 2 AU001278 1 20001116 G 3260 1204112500 PROXIMITY SWITCH EMB 120 EMB120 3260201 SO PWA 118 PW118A NE HAMSTD 14SF 14SF9 NE NLG FAULTY W C ABORTED TAKEOFF N FALSE WARNING TO TAKEOFF 1 AU S (AUS) NOSE LANDING GEAR SYSTEM B PROXIMITY SWITCH AND HARNESS SUSPECT FAULTY. 2 L 7 2 4T 4 T RT A31SO E20NE 6 N P11NE 2001040200208 20010402 00208 2001 4 2 AU001280 4 20001228 G 2565 C0118 CABLE AIRCRUISERS 60592101 AIRBUS 320 A320211 3930320 EU CFMINT CFM56 CFM565A1 NE ESCAPE SLIDE DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S C0118 (AUS) ESCAPE SLIDE RESERVOIR ASSEMBLY WIRE CONTROL INTERNAL CABLE DAMAGED (KINKED) AT THE END AND AT THE ROD TO CABLE SW AGE. DAMAGE ALSO TO THE END FITTING. FOUND DURING TESTING IAW WR 25-60/119. 2 L 7 2 4F 4 F RT A28NM E29NE 2001040200209 20010402 00209 EU 2001 4 2 AU001281 1 20001229 G 3510 MF100511 OXYGEN MASK AIRBUS 320 A320211 3930320 EU CFMINT CFM56 CFM565A1 NE CREW OXYGEN LEAKING W O OTHER O OTHER CR CRUISE 1 AU S 58538 (AUS) FIRST OFFICERS OXYGEN MASK LEAKING. 2 L 7 2 4F 4 F RT A28NM E29NE 2001040200210 20010402 00210 EU 2001 4 2 AU001282 1 20001214 G 5610 WP1701011 WINDSHIELD BAC 146 146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE COCKPIT CRACKED W O OTHER O OTHER CR CRUISE 1 AU S (AUS) LT WINDSHIELD OUTER LAYER CRACKED. ARCING OCCURRED IN THE TOP RH CORNER OF THE SCREEN. 2 H 7 4 4F 4 F A49EU E6NE 2001040200211 20010402 00211 NM 2001 4 2 AU001283 1 20000615 G 2897 WIRE BOEING 737 737377 NM GE CFM56 CFM563B1 13802 NE FUEL SYSTEM DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) KAPTON WIRES LOCATED IN REFUEL PANEL HAVE DAMAGED INSULATION ALLOWING THE WIRES TO BE EXPOSED. 2 L 7 2 4F 4 F RT A16WE E2GL 2001040200212 20010402 00212 NM 2001 4 2 AU001284 1 20001125 G 2897 WIRE BOEING 737 737377 NM GE CFM56 CFM563B1 13802 NE FUEL SYSTEM DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) KAPTON WIRES LOCATED IN REFUEL PANEL HAVE DAMAGED INSULATION ALLOWING THE WIRES TO BE EXPOSED. 2 L 7 2 4F 4 F RT A16WE E2GL 2001040200213 20010402 00213 NM 2001 4 2 AU001287 1 20001117 G 2910 BACH8A06NN0336T HOSE BOEING 737 737377 NM GE CFM56 CFM563B1 13802 NE HYDRAULIC SYSTEM LEAKING W O OTHER K J FLUID LOSS WARNING INDICATION LD LANDING 1 AU S (AUS) NOSE LANDING GEAR RETRACTION ACTUATOR DOWN LINE HYDRAULIC HOSE RUPTURED. LOSS OF SYSTEM A'' HYDRAULIC FLUID. 2 L 7 2 4F 4 F RT A16WE E2GL 2001040300094 20010403 00094 NM 2001 4 3 AU001288 1 20001230 G 5754 114T310024 SLAT BOEING 767 767338 1385151 NM GE CF6 CF680C2* GL RT WING SLAT DEBONDED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT WING NR 7 LEADING EDGE SLAT TRAILING EDGE WEDGE DISBONDING ON UPPER AND LOWER SURFACES. 2 L 7 2 4F 4 F RT A1NM E23EA 2001040200214 20010402 00214 EU 2001 4 2 AU001289 1 20000309 G 7830 VALVE PWA PW4152 AIRBUS 310 A310324 3930206 EU PWA 4152 PW4152 NE THRUST REVERSER FAULTY W C ABORTED TAKEOFF E J VIBRATION/BUFFET WARNING INDICATION TO TAKEOFF 1 AU S (AUS) NR 2 THRUST REVERSER PRESSURE REGULATING AND SHUTOFF VALVE (PRSOV) FAULTY. 2 L 7 2 4F RT A35EU E24NE 2001040300095 20010403 00095 EU 2001 4 3 AU001290 1 20000302 G 7830 DRIVE SHAFT PWA PW4152 AIRBUS 310 A310324 3930206 EU PWA 4152 PW4152 NE THRUST REVERSER FAULTY W C ABORTED TAKEOFF E J VIBRATION/BUFFET WARNING INDICATION TO TAKEOFF 1 AU S (AUS) NR 2 THRUST REVERSER PNEUMATIC DRIVE UNIT FAULTY. 2 L 7 2 4F RT A35EU E24NE 2001040200215 20010402 00215 2001 4 2 AU001292 4 20000819 G 2300 602TR4183 RADIO FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU COMMUNICATIONS CONTAMINATED W O OTHER O OTHER DE DESCENT 1 AU S (AUS) FIRST OFFICERS RADIO SYSTEM CONTAMINATED WITH WATER. WINDOW HAD BEEN LEFT OPEN THE PREVIOUS NIGHT AND RAIN ENTERED THE COCKPIT. 2 L 7 2 4F 4 F RT A20EU E2EU 2001040200216 20010402 00216 EU 2001 4 2 AU001293 1 20001230 G 3230 BDM30003 LANDING GEAR AIRBUS 310 A310324 3930206 EU PWA 4152 PW4152 NE MLG FAULTY W O OTHER J WARNING INDICATION CL CLIMB 1 AU S 92 (AUS) LANDING GEAR WOULD NOT RETRACT WITH SYSTEM 1 SELECTION. OK USING SYSTEM 2. 2 L 7 2 4F RT A35EU E24NE 2001040200217 20010402 00217 EU 2001 4 2 AU001294 1 20001110 G 2750 CIRCUIT BREAKER AIRBUS 310 A310324 3930206 EU PWA 4152 PW4152 NE TE FLAPS FAULTY W O OTHER F FLT CONT AFFECTED NR NOT REPORTED 1 AU S (AUS) FLAPS WOULD NOT OPERATE. CIRCUIT BREAKERS CYCLED AND FAULT CLEARED. 2 L 7 2 4F RT A35EU E24NE 2001040200218 20010402 00218 EU 2001 4 2 AU001295 2 20000823 G 7321 612ECU1 FUEL CONTROL FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU NR 1 ENGINE FAULTY W O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 AU S (AUS) NR 1 ENGINE THRUST AND N2 FLUCTUATING. TGT WARNING ILLUMINATED. 2 L 7 2 4F 4 F RT A20EU E2EU 2001040200219 20010402 00219 2001 4 2 AU001297 4 20000415 G 3444 9650476088 COMPUTER FOKKER F28 F28MK4000 4990810 EU RROYCE SPEY SPEY55515 54521 EU GROUND PROXIMITY FAULTY W O OTHER J WARNING INDICATION DE DESCENT 1 AU S (AUS) GROUND PROXIMITY WARNING SYSTEM (GPWS) COMPUTER FAULTY. 2 L 7 2 4F 4 F RT A20EU E2EU 2001040200220 20010402 00220 2001 4 2 AU001299 4 20000206 G 2210 COMPUTER DHAV DHC8 DHC8* NM PWA 120 PW123D 52152 NE AUTOPILOT SYSTEM FAULTY W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 AU S (AUS) AUTOFLIGHT CONTROL SYSTEM (AFCS) COMPUTER FAULTY. 2 H 7 2 4T 4 T RT A13NM E20NE 2001040200221 20010402 00221 EU 2001 4 2 AU001303 1 20001211 G 3260 SPRING FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU MLG BROKEN W O OTHER N FALSE WARNING LD LANDING 1 AU S (AUS) RT MAIN LANDING GEAR DOOR UPLOCK MICROSWITCH SPRING BROKEN. 2 L 7 2 4F 4 F RT A20EU E2EU 2001040200222 20010402 00222 EU 2001 4 2 AU001304 1 20001210 G 2432 23531 BATTERY FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU BATTERY BAY OVERHEATED W A UNSCHED LANDING M J OVER TEMP WARNING INDICATION CR CRUISE 1 AU S (AUS) AIRCRAFT BATTERY OVER TEMPERATURED. 2 L 7 2 4F 4 F RT A20EU E2EU 2001040200223 20010402 00223 EU 2001 4 2 AU001305 1 20001208 G 2432 23531 BATTERY FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU BATTERY BAY OVERHEATED W O OTHER J M WARNING INDICATION OVER TEMP NR NOT REPORTED 1 AU S (AUS) FORWARD BATTERY OVER TEMPERATURED. 2 L 7 2 4F 4 F RT A20EU E2EU 2001040200224 20010402 00224 NM 2001 4 2 AU001306 1 20001116 G 3260 SENSOR DHAV DHC8 DHC8* NM PWA 120 PW123D 52152 NE MLG DOOR DAMAGED W O OTHER N FALSE WARNING CR CRUISE 1 AU S (AUS) LANDING GEAR DOOR WIRING OPEN CIRCUITED AT FILTER / INDUCTOR L4 (LT FORWARD DOOR SENSOR INPUT TO PSEU). 2 H 7 2 4T 4 T RT A13NM E20NE 2001040200225 20010402 00225 EU 2001 4 2 AU001307 1 20001029 G 2130 A/C PACK FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU CABIN PRESSURE FAULTY W O OTHER O OTHER NR NOT REPORTED 1 AU S (AUS) PRESSURISATION SYSTEM LEAKING. 2 L 7 2 4F 4 F RT A20EU E2EU 2001040200226 20010402 00226 EU 2001 4 2 AU001308 1 20001023 G 3610 DUCT FOKKER F28 F28MK4000 4990810 EU RROYCE SPEY SPEY55515 54521 EU PNEUMATIC SYS LEAKING W O OTHER J WARNING INDICATION NR NOT REPORTED 1 AU S (AUS) DUCTING FROM APU TO CROSS DUCT AND GROUND AIR SUPPLY DUCT LEAKING. 2 L 7 2 4F 4 F RT A20EU E2EU 2001040200227 20010402 00227 EU 2001 4 2 AU001309 1 20001022 G 3230 A78712001 SPRING FOKKER F28 F28MK4000 4990810 EU RROYCE SPEY SPEY55515 54521 EU MLG DOOR BROKEN W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 AU S (AUS) RT MAIN LANDING GEAR DOOR AFT UPLOCK HOOK SPRING BROKEN. 2 L 7 2 4F 4 F RT A20EU E2EU 2001040200228 20010402 00228 EU 2001 4 2 AU001310 1 20001022 G 2432 23531 BATTERY FOKKER F28 F28MK4000 4990810 EU RROYCE SPEY SPEY55515 54521 EU BATTERY BAY OVERHEATED W O OTHER M J OVER TEMP WARNING INDICATION NR NOT REPORTED 1 AU S (AUS) MAIN BATTERIES HAD OVERTEMPERATURE. 2 L 7 2 4F 4 F RT A20EU E2EU 2001040200229 20010402 00229 EU 2001 4 2 AU001311 2 20001017 G 7261 EU18394A FILTER FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU ENGINE OIL LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S (AUS) NR 2 ENGINE OIL FILTER DRAIN OUTLET LEAKING. 2 L 7 2 4F 4 F RT A20EU E2EU 2001040200230 20010402 00230 EU 2001 4 2 AU001312 1 20001015 G 3150 WARNING SYSTEM FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU COCKPIT FALSE ACTIVATION W O OTHER N FALSE WARNING CL CLIMB 1 AU S (AUS) NR 1 BAY OVERHEAT LIGHT ILLUMINATED. AIR LEAK CHECK CARRIED OUTWITH NO LEAKS EVIDENT. 2 L 7 2 4F 4 F RT A20EU E2EU 2001040200231 20010402 00231 EU 2001 4 2 AU001313 2 20001013 G 7321 CASC211 REGULATOR FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU NR 2 ENGINE FUEL FAULTY W C ABORTED TAKEOFF R J PARTIAL RPM/PWR LOSS WARNING INDICATION TO TAKEOFF 1 AU S (AUS) NR 2 ENGINE FUEL FLOW REGULATOR (FFR) FAULTY. 2 L 7 2 4F 4 F RT A20EU E2EU 2001040200232 20010402 00232 EU 2001 4 2 AU001314 1 20001006 G 3234 HANDLE FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU MLG STUCK W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 AU S (AUS) LANDING GEAR SELECTOR HANDLE STUCK IN THE DOWN POSITION. 2 L 7 2 4F 4 F RT A20EU E2EU 2001040200233 20010402 00233 2001 4 2 AU001315 4 20001004 G 3416 23932004 ALTIMETER FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU COCKPIT OUT OF ADJ W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FIRST OFFICERS ALTIMETER OUT OF CALIBRATION. FOUND DURING COMPLIANCE WITH AD/RAD/68 AMDT2. 2 L 7 2 4F 4 F RT A20EU E2EU 2001040200234 20010402 00234 EU 2001 4 2 AU001316 1 20000927 G 2722 1101025 ACTUATOR FOKKER F28 F28MK4000 4990810 EU RROYCE SPEY SPEY55515 54521 EU RUDDER FAULTY W A UNSCHED LANDING F J FLT CONT AFFECTED WARNING INDICATION CL CLIMB 1 AU S FAS920821 (AUS) RUDDER ACTUATOR ASSEMBLY FAULTY. 2 L 7 2 4F 4 F RT A20EU E2EU 2001040200235 20010402 00235 2001 4 2 AU001317 4 20000912 G 3442 20412170413 TRANSCEIVER FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU WEATHER RADAR FAULTY W D RETURN TO BLOCK J WARNING INDICATION TX TAXI/GRND HDL 1 AU S (AUS) WEATHER RADAR TRANSCEIVER FAULTY. 2 L 7 2 4F 4 F RT A20EU E2EU 2001040200236 20010402 00236 EU 2001 4 2 AU001318 1 20000910 G 2752 58137 ACTUATOR FOKKER F28 F28MK4000 4990810 EU RROYCE SPEY SPEY55515 54521 EU TE FLAP LEAKING W D RETURN TO BLOCK K J FLUID LOSS WARNING INDICATION TX TAXI/GRND HDL 1 AU S (AUS) FLAP HYDRAULIC MOTOR LEAKING. LOSS OF SYSTEM 1 HYDRAULIC FLUID. 2 L 7 2 4F 4 F RT A20EU E2EU 2001040200237 20010402 00237 EU 2001 4 2 AU001319 1 20000910 G 3610 DUCT FOKKER F28 F28MK4000 4990810 EU RROYCE SPEY SPEY55515 54521 EU PNEUMATIC SYSTEM LEAKING W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 AU S (AUS) TAIL DUCT ASSEMBLY LOCATED AFT OF THE REAR PRESSURE BULKHEADLEAKING. 2 L 7 2 4F 4 F RT A20EU E2EU 2001040200238 20010402 00238 EU 2001 4 2 AU001320 1 20000909 G 2752 58137 ACTUATOR FOKKER F28 F28MK4000 4990810 EU RROYCE SPEY SPEY55515 54521 EU TE FLAP LEAKING W D RETURN TO BLOCK K J FLUID LOSS WARNING INDICATION TX TAXI/GRND HDL 1 AU S (AUS) FLAP HYDRAULIC MOTOR LEAKING. LOSS OF UTILITY HYDRAULIC SYSTEM FLUID (SYSTEM 1). 2 L 7 2 4F 4 F RT A20EU E2EU 2001040200239 20010402 00239 EU 2001 4 2 AU001321 1 20000903 G 3250 CONTROL CABLE FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU NLG STEERING BROKEN W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 AU S (AUS) NOSE WHEEL STEERING CABLE BROKEN. 2 L 7 2 4F 4 F RT A20EU E2EU 2001040200240 20010402 00240 EU 2001 4 2 AU001322 1 20000830 G 2421 914F5696 GENERATOR FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU NR 2 AC SYSTEM FAILED W O OTHER H J ELECT. POWER LOSS-50 PC WARNING INDICATION NR NOT REPORTED 1 AU S (AUS) NR 2 GENERATOR DROPPED OFF LINE. 2 L 7 2 4F 4 F RT A20EU E2EU 2001040200241 20010402 00241 EU 2001 4 2 AU001323 1 20001213 G 5740 114001021RH FITTING AVIONS R2160 R2160 0960101 EU LYC O320 O320D2A 41508 EA SNSNCH 74D 74DM EA RT WING CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT WING REAR SPAR INBOARD ATTACHMENT BRACKET CRACKED. CRACKSAPPEAR TO INITIATE FROM THE ACCESS PANEL ON THE LOWER WING SKIN PANELS ARE NONSTANDARD ACCESS PANELS. 1 L 7 1 3O 3 O RT A48EU E274 5 N P88614 2001040200242 20010402 00242 EU 2001 4 2 AU001324 1 20001213 G 5740 114001011LH FITTING AVIONS R2160 R2160 0960101 EU LYC O320 O320D2A 41508 EA SNSNCH 74D 74DM EA LT WING CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT WING REAR SPAR INBOARD ATTACHMENT BRACKET CRACKED. CRACKSAPPEAR TO INITIATE FROM THE ACCESS PANEL ON THE LOWER WING SKIN PANELS ARE NON STANDARD ACCESS PANELS. 1 L 7 1 3O 3 O RT A48EU E274 5 N P88614 2001040200243 20010402 00243 NM 2001 4 2 AU001325 1 20000928 G 2910 AN9388 FITTING DHAV DHC8 DHC8* NM HYDRAULIC SYS CRACKED W O OTHER K B FLUID LOSS SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 AU S (AUS) HYDRAULIC PIPE FITTING LOCATED IN LH NACELLE AREA CRACKED AND LEAKING. LOSS OF NR 1 SYSTEM HYDRAULIC FLUID. 2 H 7 2 4T RT A13NM 2001040200244 20010402 00244 EA 2001 4 2 AU001326 2 20001009 G 7250 PCE41063 VANE DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL TURBINE SECTION DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT ENGINE POWER TURBINE VANE ASSEMBLY BROKEN AND POWER TURBINEDISC DISLODGED. 1 H 7 2 3T 4 T RT A9EA E4EA 6 C P15EA 2001040200245 20010402 00245 NE 2001 4 2 AU001327 2 20001015 G 7261 ENGINE DHAV DHC8 DHC8* NM PWA 120 PW120A NE NR 1 LACK OF LUBE W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CL CLIMB 1 AU S (AUS) NR 1 ENGINE OIL LEVEL LOW. 2 H 7 2 4T 4 T RT A13NM E20NE 2001040200246 20010402 00246 NE 2001 4 2 AU001328 3 20001020 G 6111 SFA13M1ROAD BLADE DHAV DHC8 DHC8* NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE LT PROPELLER DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT PROPELLER BLADE HOLED. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001040200247 20010402 00247 NE 2001 4 2 AU001329 2 20001209 G 7313 NOZZLE BELL 212 212 1181420 SW PWA PT6T PT6T3B 52045 NE NR 1 ENGINE BURNED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NR 1 ENGINE CONTINUOUS HIGH TEMPERATURE. STRIP INSPECTION FOUNDTHE FOLLOWING DEFECTS: HOLE BURNT IN INLET GUIDE VA NE. FIRST STAGE NOZZLE BURNED AND PIECE MISSING . T5 HARNESS THERMOCOUPLE END BURNED OFF. POWER TURBINE VANE RING CRACKE DBETWEEN ADJACENT BLADES 1 G 7 1 4U 4 U H4SW E22EA 2001040200268 20010402 00268 NM 2001 4 2 AU001331 1 20001207 G 2510 8120727 SEAT BACK BOEING 767 767204 NM GE CF6 CF680A 30025 NE COCKPIT CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) CAPTAINS SEAT BACK VERTICAL ADJUSTMENT TRACKS PNO 812072-7 ANDPNO 812072-8 CRACKED FROM THE UPPER EDGE OF THE AFT TRACK FLANGE. CRACK LENGTH 30MM (1.18IN). 2 L 7 2 4F 4 F RT A1NM E13NE 2000021900503 20000219 00503 CE 2000 2 19 AU991229075 1 20000204 G 2820 1118 HOSE STRATOFLEX CESSNA 207 207A 2073604 CE FUEL SYSTEM MISMANUFACTURED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA (AU) WHILE ASSEMBLING HOSE, FOUND THE END FITTING WOULD NOT INSTALL WITHOUT DAMAGING THE INNER HOSE LINER. THE HOSE WA S MEASURED AND FOUND TO BE AT THE BOTTOM RANGE OF THE MIL-H-8974 HOSE DIMENSIONAL LIMITS. 1 H 7 1 3O A16CE 2000101800004 20001018 00004 CE 2000 10 18 B30R200000004 1 20001002 G 2840 AN9245D SWITCH CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE WING ROOT MISSING B B3OR O OTHER S AFFECT SYSTEMS IN INSP/MAINT 1 SW 03 6637G 3890 5500670 DURING A PHASE INSPECTION OF THE FUEL LOW LEVEL SWITCH, THE SWITCH WAS FOUND FAULTY. DURING REPLACEMENT, IT WAS NOTICED THERE WAS ONLY ONE NUT HOLDING THE SWITCH IN PLACE. (NO JAM NUT). THE IPC CHAPTER 28-40-01 FIG 1 ITEM 6 SHOWS TWO NUTS . TWO OTHER AIRCRAFT, S/N'S 550-663 AND 550-666, WERE ALSO FOUND TO BE IN THE SAME CONDITION. SUBMITTER STATED THERE IS NO WAY TO SAFETY JUST ONE NUT. THE SITUATION COULD POSSIBLY CAUSE A FUEL LEAK. (X) 1 L 7 2 4F 4 F A22CE E1NE 2000073100224 20000731 00224 CE 2000 7 31 B3OR200000002 1 20000726 G 5330 12112871 SKIN PANEL CESSNA 210 T210L 2073449 CE AFT CABIN LOOSE B B3OR O OTHER J WARNING INDICATION CR CRUISE 1 SW 03 732JF 21061543 AIRCRAFT WAS TEST FLOWN DUE TO HIGH CO LEVEL DISCOVERED IN ANOTHER 210 SERIES FLEET AIRCRAFT. PILOTS FOUND UNACCEPTABLE LEVEL OF CO IN CABIN USING TOXIBEE CO DETECTOR. MAINTENANCE FOUND EXHAUST GASES ENTERING TAILCONE THROUGH VENT HOLE FOR STC SA71RM AIR CONDITIONING SYSTEM. THIS VENT IS LOCATED ON THE BOTTOM OF THE AIRCRAFT IN THE EXHAUST STREAM. ADDITIONAL LY, IT WAS FOUND THAT AFT BAGGAGE WALL HAD MISSING FASTENERS AND A POOR REPAIR CAUSING LEAKAGE, AND THERE WERE GAPS AROU ND WIRE BUNDLES ENTERING THE AFT AVIONICS AREA. THE WALL WAS REPLACED WITH A NEW PART AND ALL GAPS WERE SEALED. TEST FLI GHT REVEALED NO CO INTRUSION AT ALL INTO CABIN. 1 H 7 1 3O 3A21 2001011103004 20010111 03004 CE 2001 1 11 B3OR200000003 1 20000915 G 2841 L15H3 SWITCH CESSNA 500 550 2076604 CE LT WING TANK INACCURATE B B3OR K NONE O OTHER IN INSP/MAINT 1 SW 03 6637G 550670 PERFORMED FUNCTIONAL TEST OF FUEL LOW LEVEL WARNING SYSTEM, IT FAILED ON ONE SIDE, ILLUMINATING WARNING CAPSULE AT 100 P OUNDS INSTEAD OF 200 POUNDS OF FUEL. REPLACED FUEL LOW LEVEL WARNING FLOAT SWITCH. SYSTEM FAILED AGAIN, DISCOVERED THA T NEW PART WAS INTERMITTENT. THIS SWITCH HAS BEEN A PROBLEM IN FLEET FOR YEARS, IT SEEMS EACH TIME WE DO THE FUNCTIONAL TEST ON THE WARNING SYSTEM WE FIND A SWITCH THAT IS BAD. AS A SIDE NOTE, WE FOUND ONLY ONE NUT SECURING EACH SWITCH IN THE TANK WHEN THE PARTS CATALOG SPECIFIES TWO NUTS USED TO JAM-LOCK EACH OTHER. (X) 1 L 7 2 4F A22CE 2001011103012 20010111 03012 EA 2001 1 11 B3OR200000005 2 20001102 G 7300 3019288 TUBE BEECH 200 A200 1152921 CE PWA PT6 PT6A41 52043 EA FUEL CONTROL CRACKED B B3OR C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 SW 03 7074G BC17 PCE85295 PILOTS COMPLETED PRE-TAKEOFF ENGINE RUNS AND RETURNED ENGINES TO IDLE. WHEN POWER LEVERS WERE ADVANCED FOR TAXI TO ACTI VE, NR 1 ENGINE DID NOT RESPOND TO INPUT. AIRCRAFT WAS RETURNED TO RAMP WHERE IT WAS DISCOVERED THAT P3 SENSE LINE TO F CU WAS CRACKED NEAR B-NUT AT FCU CONNECTION. THE PRESSURE LEAKAGE PREVENTED FCU FROM SCHEDULING REQUIRED FUEL FOR ENGIN E SPOOL-UP. SUBMITTER STATED THIS IS THE SECOND P3 LINE THEY HAVE HAD CRACK THIS YEAR ON 200 SERIES AIRCRAFT. (X) 1 L 7 2 4T 4 T A24CE E4EA 2001011103013 20010111 03013 CE 2001 1 11 B3OR200000007 1 20001130 G 5730 652210223 SKIN CESSNA 500 550 2076604 CE WING DAMAGED B B3OR K NONE O OTHER IN INSP/MAINT 1 SW 03 5314J 3270 5500663 WHILE REPLACING A WING DEICE BOOT, DISCOVERED ONE OF THE HEATED LEADING EDGE RETAINING SCREWS HAD MADE CONTACT WITH THE WING SKIN AT WS 60. THE DAMAGE IS FAR BEYOND NORMAL LIMITS OF 10 PERCENT OF SKIN THICKNESS. INVESTIGATION REVEALED PRO PER P/N AND LENGTH OF SCREWS WERE INSTALLED PER CESSNA PARTS CATALOG, AND THIS SCREW DOES INDEED CONTACT LEADING EDGE SK IN WHEN INSTALLED. FOUND SIMILAR DAMAGE TO OTHER WING. CHECKED OTHER AIRCRAFT ON RAMP, FOUND SAME DAMAGE. SO FAR, 5 O THER FLEET AIRCRAFT HAVE BEEN DISCOVERED TO HAVE CONTACT DAMAGE. (X) 1 L 7 2 4F A22CE 2001040900071 20010409 00071 CE 2001 4 9 B3OR200000008 1 20001204 G 5730 652210223 SKIN CESSNA 500 550 2076604 CE WING DAMAGED B B3OR K NONE O OTHER IN INSP/MAINT 1 SW 03 5408G 3722 5500666 INSPECTED THIS AC FOR LING LEADING EDGE SKIN CONTACT DAMAGE FROM HEATED LEADING EDGE RETAINING SCREWS DUE TO CONTACT DAM AGE BEING FOUND IN SISTER SHIP. DAMAGE WAS FOUND TO WING LEADING EDGE UNDER HEATED LEADING EDGE ASSY EVEN THOUGH PROPER SCREWS WERE USED . THIS DAMAGE COULD POSSIBLY CAUSE FUEL LEAKAGE INTO THE AREA COVERED BY THE HEATED LEADING EDGE ASSY , CREATING A POTENTIAL FIRE HAZARD. THERE IS NO ALLOWABLE FUEL LEAKAGE IN THIS AREA. 1 L 7 2 4F A22CE 2001011103014 20010111 03014 EU 2001 1 11 B3OR200000009 1 20001229 G 6700 CN6MEGR BEARING SNIAS 350 AS350B2 8680813 EU ROD END BINDING B B3OR C ABORTED TAKEOFF O OTHER HO HOVERING 1 SW 03 4059W 1240 2933 PILOT LIFTED AIRCRAFT INTO A HOVER AND FELT SOME BINDING IN THE FORE AND AFT DIRECTION OF HIS CYCLIC CONTROL. AFTER SHUT DOWN, MAINTENANCE PERSONNEL INSPECTED CONTROL SYSTEM. BINDING WAS DUPLICATED AFTER DISCONNECTING SERVO INPUTS. INVESTIGA TION REVEALED A FROZEN BEARING IN THE LOWER ROD END OF THE PITCH SERVO ACTUATOR INPUT ROD. REPLACEMENT OF THIS BEARING E NDED THE BINDING AS VERIFIED BY TEST RUN. 1 G 7 1 3U H9EU 2001011104226 20010111 04226 CE 2001 1 11 B3OR20010001 1 20001206 G 7800 121136012 BOOT ASSEMBLY CESSNA CESSNA 210 T210N 2073456 CE CONT O520 TSIO520R 17040 SO UNDER FLOOR SMALL CUTS B B3OR O OTHER J WARNING INDICATION CR CRUISE 1 SW 03 9403Y 21064498 This aircraft has an electronic carbon monoxide detector. In cruise flight, the detector registered a reading of 98 ppm CO. OSHA limits exposure to 50 ppm in normal circustances, avation sources suggest a much more conservative 10 to 20 ppm due to the elevated enviroment. The CO level dropped rapidly when air vents were opened. Investigation found that the a ccordian style seal boots on the main landing gear downlock actuators (under cabin floor) had several cuts in them. Main tenance sealed these with holes with RTV sealant and test flight revealed a maximan reading of 7 ppm in the cabin and 17 ppm in the baggage area. 1 H 7 1 3O 3 O 3A21 E8CE 2000121500181 20001215 00181 CE 2000 12 15 B8RR010301 1 20001205 G 5730 MS24694C51 SCREW CESSNA 500 550 2076604 CE BOTH WINGS OVERSIZED B R8RR K NONE O OTHER IN INSP/MAINT 1 WP 07 1254X 5500494 LEFT WING AND RIGHT WING LEADING EDGE SKIN HAS BEEN CHAFED BY THE UPPER SCREW OF THE OUTBOARD ROW OF SCREWS ATTACHING TH E HEATED LEADING EDGE TO THE WING. THE SCREWS INSTALLED WERE TOO LONG, ALTHOUGH THEY WERE THE ONES CALLED FOR IN THE PA RTS CATALOG. THEY CHAFED INTO THE WING LEADING EDGE SKIN ABOUT 0.020 INCH DEEP INTO THE LEFT WING AND 0.01 INCH INTO TH E RIGHT WING. THE SKIN IS 0.040 INCH ALUMINUM. CESSNA HAS APPROVED A SHORTER SCREW TO BE INSTALLED AND IS CURRENTLY WO RKING ON A PERMANENT REPAIR. (X) 1 L 7 2 4F A22CE 2000061300292 20000613 00292 EA 2000 6 13 BJ3RE000001 2 20000427 G 8550 AN470 RIVET PIPER PA46 PA46350P SO LYC O540 TIO540AE2A 41532 EA BAFFLE BROKEN G BJ3R K NONE O OTHER IN INSP/MAINT 1 WP 15 117NJ 118 4636168 LW13383 DURING AN OIL CHANGE, TWO RIVET HEADS (AN470) WERE FOUND IN THE OIL SUCTION SCREEN. THE ENGINE WAS REMOVED AND THE OIL SUMP PULLED OFF. TWO RIVET HEADS WERE MISSING FROM THE OIL SUMP BAFFLE. THESE ARE MS20470AD4-4 RIVETS. THE HOLES ON T HE DRIVEN SIDE APPEARED TO BE COUNTERSUNK OR EXCESSIVELY DEBURRED, WHICH GAVE LITTLE BEARING SURFACE FOR THE RIVET HEAD. LYCOMING SB489B REFERS TO THESE RIVETS AND THEIR REPLACEMENT. 1 L 7 1 3O 3 O RT A25SO E14EA 2000061300293 20000613 00293 EA 2000 6 13 BJ3RE000002 2 20000427 G 8550 61298 GEAR PIPER PA46 PA46350P SO LYC O540 TIO540AE2A 41532 EA TEETH WORN G BJ3R K NONE O OTHER IN INSP/MAINT 1 WP 15 117NJ 118 4636138 RL1041561A UPON REMOVAL OF THE OIL PUMP, TO CHECK FOR POSSIBLE DAMAGE DUE TO TWO RIVET HEADS FOUND IN THE OIL SUCTION SCREEN, IT WA S NOTED THAT THE ALUMINUM OIL PUMP GEAR HAD EXCESSIVE WEAR ON THE DRIVEN SIDE OF EACH TOOTH, AND CHIPS MISSING ON THE OU TER EDGE OF SEVERAL TEETH. IT ALMOST APPEARS THAT THE HARDNESS OF THE ALUMINUM GEAR WAS NOT CORRECT. THE STEEL DRIVING GEAR 61297 WAS ALSO DAMAGED, POSSIBLY DUE TO THE ALUMINUM GEAR. 1 L 7 1 3O 3 O RT A25SO E14EA 2000091800001 20000918 00001 EA 2000 9 18 BJ3RE000003 2 20000502 G 8550 LW13383 BAFFLE PIPER PA46 PA46350P SO LYC O540 TIO540AE2A 41532 EA RIVET HOLES DEFECTIVE G BJ3R K NONE O OTHER IN INSP/MAINT 1 WP 15 117N 4636168 RL1041561A ON RECEIPT OF A NEW BAFFLE, IT WAS DERIVETED TO CHECK FOR DEFECTIVE HOLES, LIKE THE ONE REMOVED DUE TO FAILED RIVETS. T HIS IS ONE OF THE NEW DESIGN WITH 5 RIVETS PER SIDE, INSTEAD OF THE EARLIER 3 RIVET UNIT. RIVET HOLES 1, 3, AND 5 ON EA CH SIDE HAVE EITHER BEEN HEAVILY DEBURRED OR COUNTERSUNK, WHICH LEAVES INSUFFICIENT BEARING SURFACE FOR THE RIVET HEADS. SB 489B SAYS THAT MS20470AD4-4 RIVETS ARE TO BE USED. (X) 1 L 7 1 3O 3 O RT A25SO E14EA 2000091800002 20000918 00002 EA 2000 9 18 BJ3RE000004 2 20000508 G 8550 LW13383 BAFFLE PIPER PA46 PA46350P SO LYC O540 TIO540AE2A 41532 EA RIVET HOLES ELONGATED G BJ3R K NONE O OTHER IN INSP/MAINT 1 WP 15 117NJ 4636168 RL1041561A ON RECEIPT OF A SECOND NEW BAFFLE, IT WAS DERIVETED TO CHECK FOR DEFECTIVE HOLES LIKE THE ORIGINAL UNIT AND ITS REPLACEM ENT. SUBMITTER STATED THIS IS THE SECOND NEW DESIGN (5 RIVETS PER SIDE) BAFFLE RECEIVED. THE HOLES ARE ELONGATED, OVER SIZED OR FIGURE 8 SHAPED AND ARE NO LONGER SUITABLE FOR THE MS20470AD4-4 RIVETS THAT ARE SUPPOSED TO BE INSTALLED. ONE OF THE WASHERS ON THE BUCKED SIDE OF THE RIVET WAS MISSING ON ARRIVAL. 1 L 7 1 3O 3 O RT A25SO E14EA 2000091800003 20000918 00003 EA 2000 9 18 BJ3RE000005 2 20000517 G 8550 LW13383 BAFFLE PIPER PA46 PA46350P SO LYC O540 TIO540AE2A 41532 EA RIVET HOLES ELONGATED G BJ3R K NONE O OTHER IN INSP/MAINT 1 WP 15 117NJ 4636168 RL1041561A ON RECEIPT OF A THIRD NEW BAFFLE, IT WAS DERIVETED TO CHECK FOR DEFECTIVE HOLES LIKE THE PREVIOUS UNITS. THIS IS ALSO O F THE NEW (5 RIVETS PER SIDE) DESIGN. SUBMITTER STATED THE HOLES ARE ELONGATED, OVERSIZED, AND NO LONGER SUITABLE FOR T HE MS20470AD4-4 RIVETS CALLED FOR. (X) 1 L 7 1 3O 3 O RT A25SO E14EA 2000110600192 20001106 00192 SO 2000 11 6 BJ3RE000006 1 20000720 G 7920 LW13383 BAFFLE PIPER PA46 PA46350P SO LYC O540 TIO540AE2A 41532 EA RIVETED JOINT BROKEN B BJ3R K NONE O OTHER IN INSP/MAINT 1 WP 15 600CR 1288 4622060 L902361A RIVET HEAD FOUND IN OIL SUCTION SCREEN ON OIL CHANGE. HEAD IS OF THE TYPE USED TO INSTALL THE VERTICAL BAFFLE ON THE OI L SUMP BAFFLE. REFERENCE LYC. SB489A. SUBMITTER STATED AFTER RECEIVING 4 NEW DEFECTIVE OIL SUMP BAFFLES FROM LYCOMING OF THIS PART NUMBER, THERE IS CONCERN ABOUT THE MANUFACTURING PROCESS. SEE SDR QC10263/BJ3RE000003,000004, AND 000005. 1 L 7 1 3O 3 O RT A25SO E14EA 2001011103018 20010111 03018 NE 2001 1 11 BTEAS76B001 1 20000908 G 2910 SS482C2C165000 LINE SKRSKY S76 S76B 8143007 NE PWA PT6 PT6B36 52043 EA HYD SYSTEM BURST E BTEA E ENGINE SHUTDOWN K J FLUID LOSS WARNING INDICATION NR NOT REPORTED 1 GL 09 176BA 6682 760317 NR 2 HYDRAULIC PRESSURE LINE FROM HYDRAULIC PUMP TO BULKHEAD FITTING FAILED ON AIRCRAFT START-UP. LINE BURST FROM INSID E WITHOUT WARNING, (NO LEAKS NOTED ON PREFLIGHTS). LINE WAS REPLACED, SYSTEM SERVICED AND AIRCRAFT RETURNED TO SERVICE . (X) 1 G 7 2 4U 4 U H1NE E4EA 2001032800114 20010328 00114 EA 2001 3 28 CA000110066 1 20000104 G 3244 TIRE CNDAIR CL600 CL6002B19 EA LT MLG FAILED W C ABORTED TAKEOFF O OTHER TO TAKEOFF 1 CA (CAN) VIBRATIONS FELT DURING TAKE-OFF, TAKE OFF ABORTED. BOTH TIRES ON LT MLG FOUND BLOWN WITH LIGHT DAMAGE TO MLG DOOR. 2 L 7 2 4F RT A21EA 2001032800115 20010328 00115 EA 2001 3 28 CA000110067 1 20000105 G 5740 WINDOW CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE COCKPIT FAILED W O OTHER O OTHER TX TAXI/GRND HDL 1 CA (CAN) AFTER LANDING, WHILE TAXING, THE A/C WAS CAUGHT IN SEVERE WIND GUST. LT WING WAS LIFTED OFF THE GROUND, RT WING TI P CONTACTED THE RUNWAY, LT COCKPIT SIDE WINDOW SHATTERED. AWAITING CREW REPORT. UPDATEAS INFO COMES AVAILABLE. 2 L 7 2 4F 4 F RT A21EA E15NE 2000020500955 20000205 00955 CE 2000 2 5 CA000118024 1 20000110 G 3246 300257 WHEEL BFGOODRICH 50300010133 BEECH 90 E90 1152914 CE PWA PT6 PT6A28 EA HARTZL HCD4N3 HCD4N3A GL MLG BROKEN W D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 CA 2147 A4262 PCE51688 FY1618 (CAN) INNER WHEEL (BRAKE HALF) CRACKED DURING TAXI AND JAMMED THE BRAKE. FURTHER INVESTIGATION REVEALED CRACKS IN THE O THER MAIN WHEEL HALVES. 1 L 7 2 3T 4 T 3A20 E4EA 5 C STC 2000020500956 20000205 00956 CE 2000 2 5 CA000118025 1 20000110 G 3250 35660311 FITTING BEECH P35 P35 1151530 CE CONT O470 IO470N 17026 SO MCAULY 2A36C 2A36C23 GL MLG STEERING CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA CS955642N 663213 (CAN) DURING 100 HR INSPECTION, THE RT TORQUE FITTING WAS FOUND CRACKED AT THE ROD ATTACH POINT. POSSIBLE CAUSE IS THAT THE NOSE GEAR WAS OVER-STEERED AND THE STEERING STOPS WERE NOT ADJUSTED PROPERLY AND THAT MAY HAVE PUT EXCESSIVE FORCE ON THE FITTING CAUSING IT TO CRACK. DAMAGED PARTS REPLACED. SUBMITTER STATES THAT ENGINEERS SHOULD BE AWARE THAT IF AI RCRAFT HAS BEEN OVER-STEERED, TO CHECK AT THE UPPER YOKE AND STEERING MECHANISM BOLTS FOR DAMAGE DUE TO EXCESSIVE STRESS . 1 L 7 1 3O 3 O RT 3A15 3E1 5 C P880 2001032800267 20010328 00267 EA 2001 3 28 CA000120032 1 20000107 G 7931 PUMP CNDAIR CL604 CL604 EA GE CF34 CF343B1 NE ENGINE FAILED W E ENGINE SHUTDOWN L NO TEST CR CRUISE 1 CA 5 (CAN) PRODUCTION AIRCRAFT EXPERIENCED LT ENGINE OIL PRESSURE WARNING WAS POSTED DURING FLIGHT TEST. 2 L 7 2 4F 4 F RT A21EA E15NE 2001032800288 20010328 00288 NE 2001 3 28 CA000128026 2 20000128 G 7250 310976601 SHAFT PWA PT6 PT6A42 52043 NE TURBINE FRACTURED W K NONE O OTHER IN INSP/MAINT 1 CA 3836 884 (CAN) POWER TURBINE SHAFT BROKEN. RESEARCH OF DETAILS ONGOING. 4 T E4EA 2001032800301 20010328 00301 2001 3 28 CA000128046 4 20000103 G 2562 G SWITCH ARTEX 4530150A ELT UNIT FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 25271 (CAN) INTERNAL G SWITCH FAILED TO ENABLE INTERMITANTLY RECERTIFICATION TESTING. 2001032800308 20010328 00308 SO 2001 3 28 CA000128053 2 20000105 G 8500 ENGINE O300A CESSNA 170 170B 2072306 CE CONT O300 O300A 17022 SO NACELLE SEIZED W K NONE O OTHER IN INSP/MAINT 1 CA 479 (CAN) ENGINE LOST ITS OIL AND SEIZED. OPERATOR SPECIFIED FROZEN BREATHER AS THE CAUSE. 1 H 7 1 3O 3 O A799 E253 2001032800311 20010328 00311 CE 2001 3 28 CA000128056 1 20000108 G 3230 608100823 PIN BEECH 95 95B55 1152729 CE CONT O470 IO470L 17026 SO LT MLG MISSING W A UNSCHED LANDING D INFLIGHT SEPARATION CL CLIMB 1 CA 9350 (CAN) DURING INITIAL RETRACTION WHEN THE GEAR WAS SELECTED UP THE LEFT GEAR STAYED DOWN. WHEN THE GEAR WAS SELECTED DOWN EVERYTHING WAS NORMAL ON THE INDICATOR.INSPECTION REVEALED THAT THE SHEAR PIN ON THE LEFT GEAR WAS MISSING.THE GEARS WE RE LUBRICATED & THE BOTH LT & RT SHEAR PINS REPLACED. 1 L 7 2 3O 3 O RT 3A16 3E1 2001032900011 20010329 00011 EA 2001 3 29 CA000201014 1 20000101 G 2910 82960010209 TUBE DHAV DHC8 DHC8311 1386006 EA PWA PW120 PW123 NE HYD SYSTEM RUPTURED W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CL CLIMB 1 CA 2221 (CAN) ON TAKE OFF, THE AIRCRAFT EXPERIENCED A LOSS OF NR 2 HYD SYSTEM. THE AIRCRAFT RETURNED FOR LANDING AFTER A GETTIN G NR 2 HYD PESS AND RUDDER ISOLATE CAUTION LIGHTS. MAINTENANCE FOUND A RUPTURED HYDRAULIC LINE TO THE RUDDER LIMITER 2 H 7 2 4T 4 T RT A13NM E20NE 2001032600275 20010326 00275 SW 2001 3 26 CA000209005 1 20000127 G 3213 540053 LINK MOONEY M20 M20E 5870212 SW LYC O360 IO360A1A 41514 EA NLG CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 4213 (CAN) WHILE RPLACING THE RUBBER SHOCKS ON THE NOSE GEAR SHOCK ASSEMBLY, IT WAS NOTICED THAT THERE WAS CORROSION ON THE P OST WHERE THE RUBBER DISCS ARE PLACED.IN ORDER TO DETECT CORROSIONIN THIS AREA,THIS ASSEMBLY HAS TO BE REMOVED AND DISSA SEMBLED. 1 L 7 1 3O 3 O 2A3 1E10 2001032600279 20010326 00279 SO 2001 3 26 CA000209009 1 20000128 G 5340 JW2901R FITTING LKHEED 1329 1329 5263102 SO FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 8964 (CAN) PART CRACKED BEYOND LIMITS. 2 L 7 4 4J 2A15 2001032600289 20010326 00289 EA 2001 3 26 CA000209026 1 20000201 G 3411 ST5122DH PITOT TUBE DHAV DHC7 DHC7102 2802708 EA PWA PT6 PT6A50 52043 EA HAMSTD 24PF 24PF305 GL NR 2 STATIC SYS BLOCKED W O OTHER N FALSE WARNING CL CLIMB 1 CA (CAN) DUE TO CLIMATIC CONDITIONS IN FRENCH GUIANA AT THIS TIME OF YEAR, IN EFFORT TO PROTECT THE STATIC SYSTEM FROM WATE R CONTAMINATION, THE PORTS WERE COVERED WITH TAPE WHEN THE AIRCRAFT WAS PARKED. ONE PORT WAS BLOCKED WITH A SMALL PIECE OF TAPE AND THE OTHER WAS BLOCKED BY THE GLUE FROM THE TAPE. THE COMPANY PROCEDURE HAS CHANGED TO ALIMINUM TAPE WITH REM OVE BEFORE FLIGHT FLAG. 2 H 7 4 4T 4 T A20EA E4EA 6 C P1NE 2001022200124 20010222 00124 GL 2001 2 22 CA000215012 2 20000207 G 7240 6878426 NOZZLE ALLSN 6898734 ALLSN 250C 250C20 03013 GL ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 1401 CAT31116P (CAN) THE 2ND STAGE NGV,FIRST STAGE BLADE PATH WAS FOUND CRACKED 50% AROUND THE CIRCUMFERENCE. THE BLADE PATH HAD BEEN R EPLACED AND WAS JOINED AT THE SECOND NOZZLE BY A BRAZED BUT JOINT. THIS IS /WAS A DAR APPROVED REPAIR. SUSPECT NGV ARE R EQUESTED TO BE REMOVED FROM OPERATIONS AS REQUESTED BYALERT NOTICE FROM ORENDA AEROTECH ALERT SERVICE NOTICE DATED 02/23 /00.CORRECTIVE ACTIO N ADRESSING FAA AND CANADIAN OPERATORS UNDER REVIEW. 3 U E4CE 2000081000041 20000810 00041 GL 2000 8 10 CA000215018 3 20000105 G 6110 7998TOR7080 PROPELLER HARTZL HCF3Y HCF3YR2 GL DECAL,TORQUE MISMARKED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 1190 DA1032 (CAN) WRONG PROPELLER INSTALLATION DECAL ATTACHED WHICH INDICATED AN IMPROPER TORQUE VALUE. 5 C P31EA 2000071800165 20000718 00165 SW 2000 7 18 CA000218005 1 20000214 G 7810 222063307141 TAILPIPE BELL 222063307 BELL 222 222U 1182140 SW X-TUBES & BRKTS CRACKED W O OTHER O OTHER IN INSP/MAINT 1 CA (CAN) TAILPIPE FORWARDED FOR FUSION WELD REPAIR TO 4 X-TUBE SUPPORT BRACKETS. EXCESSIVE PLAY WAS NOTED. DETAILED INSPEC TION REVEALED WEAR THROUGH DAMAGE OF BOTH X-TUBES VISIBLE FROM ONLY INSIDE OF THE TAILPIPE WHERE WEAR WAS THEN NOTED IN 3 AREAS. BELL ENGINEERING WAS INFORMED AND THEY WILL CLOSELY MONITOR SUBSEQUENT FIELD REPORTS. 1 G 7 2 3U H9SW 2001011104277 20010111 04277 2001 1 11 CA000222018 4 20000204 G 2564 SA2733 REGULATOR BOEING 767 767233 NM PWA JT9 JT9D7R4D 52054 NE ESCAPE SLIDE FAILED W K NONE L NO TEST IN INSP/MAINT 1 CA (CAN) SLIDE/RAFT DAH A 10 SECOND HUNG TIME ON TEST. CMM INDICATES 6 SEC MAX TIME. REGULATOR REPAIRED IN ACC WITH CMM. 2 L 7 2 4F 4 F RT A1NM E3NE 2001011104278 20010111 04278 2001 1 11 CA000222019 4 20000211 G 2565 SA2733 REGULATOR BOEING 767 767233 NM PWA JT9 JT9D7R4D 52054 NE ESCAPE SLIDE FAILED W K NONE L NO TEST IN INSP/MAINT 1 CA (CAN) SLIDE/RAFT HAD A 10 SECOND HUNG TIME ON TEST. CMM INDICATES 6 SEC MAX TIME DELAY. REGULATER REPAIRED AS PER CMM. 2 L 7 2 4F 4 F RT A1NM E3NE 2001011104364 20010111 04364 SO 2001 1 11 CA000301046 1 20000221 G 2140 10D22 IGNITER PIPER PA31 PA31 7103102 SO LEAD END DEFECTIVE W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) IGNITORS WERE FOUND TO BE MISSING THE CERAMIC COATING WHICH IS REQUIRED TO PREVENT THE INGNITION LEAD SPRING FROM ARCING INSIDE THE LEAD BARREL. (FLASH OVER). AVIALL, AIRCRAFT HEATERS, API AND ELECTRO SYSTEMS ARE AWARE OF THE QA PROBL EM. 1 L 7 2 3O A20SO 2000083000117 20000830 00117 EU 2000 8 30 CA000310003 1 20000222 G 6120 1530650012 SPRING L24278000000 ZLIN 242 Z242L 9970204 EU MUHBR MTV MTV3BC EU UPPER PRT SPRING BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 31900 98471 (CAN) DURING INSPECTION IT WAS NOTICED THAT THE PROPELLER CONTROL FLAT SPRING WAS BROKEN. THIS SPRING IS USED TO KEEP T HE PROP CONTROL TELEFLEX SHEATH RIGID DURING PROP GOVERNOR CONTROL MOVEMENT. THE SUBMITTER SUGGESTS THAT DURING INSTALL ATION THEY SHOULD BE INSTALLED WITH NO STRESS ON THE SPRINGS WHICH COULD BE DETECTED BY SPRING BENDING BETWEEN THE BRACK ET AND THE SUPPORT. (X) 1 L 7 1 3O 0 A76EU 5 C USSR 2000082800036 20000828 00036 CE 2000 8 28 CA000329012 1 20000320 G 3260 1003810061 SWITCH BEECH 100 A100 1152915 CE PWA PT6 PT6A28 EA NOSE FAULTY W H DEACTIVATE SYST/CIRCUITS N FALSE WARNING CL CLIMB 1 CA PCE51107 (CAN) PILOT REPORTED LANDING GEAR UNSAFE LIGHT ON HANDLE WOULD NOT EXTINGUISH. LANDING GEAR POSITION SWITCH ON MOTOR AD JUSTED. PROBLEM RECURRED WITH INDICATION LIGHT NOW BEING INTERMITTANT. DISCOVERED MICROSWITCH INTERNALLY FAULTY. 1 L 7 2 3T 4 T A14CE E4EA 2000082800037 20000828 00037 CE 2000 8 28 CA000329014 1 20000321 G 2131 13034611 CONTROLLER BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA MCAULY 4HFR34 4HFR34C754 NE INTERNAL FAULTY W I CABIN DEPRESSURIZATION O OTHER CR CRUISE 1 CA 88800 PCE81062 300783 (CAN) ON PREPARATION FOR DESCENT, CABIN PRESSURIZATION CONTROLLER RATE WAS ADJUSTED. AFTER ADJUSTMENT WAS MADE CABIN PR ESSURE INCREASED TO MAXIMUM DIFERENTIAL AND WAS UNCONTROLLABLE AND NONRESPONSIVE TO ANY FURTHER ADJUSTMENTS TO THE CONTR OLLER. CONTROLLER REPAIRED. 1 L 7 2 4T 4 T A24CE E4EA 6 C 3PNE 2000083000120 20000830 00120 CE 2000 8 30 CA000329016 1 20000314 G 5740 817861018 BOLT BEECH 100 B100 1152919 CE GARRTT TPE331 TPE3316252B 01514 WP LT WING CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 89900 P27035 (CAN) CF 81-25R5 WAS BEING CARRIED OUT EARLY, 417.2 HRS. FOUND LEFT WING TOP REAR BOLT (P/N 81786-10-18) WAS INSPECTED AND FOUND CRACKED AND REJECTED. NEW BOLT INSTALLED. 1 L 7 2 4T 4 T A14CE E2WE 2000083000125 20000830 00125 SO 2000 8 30 CA000329035 1 20000323 G 3250 401265 BOLT PIPER 4438800 PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA STRUT TOP DAMAGED W O OTHER O OTHER IN INSP/MAINT 1 CA 65200 L586361A (CAN) AT 1,000 HR INSP, 2 BOLTS (P/N 401-265) AND BOLT (P/N 401-268) WERE REMOVED FROM NOSE GEAR STRUT ASSY FOR INSP. O NE 401-265 STARTING TO SHEAR AND OTHER SHOWING STRAIN. LONGERONS 401-268 SHOWED LIGHT BENDING. THESE BOLTS WERE REPLAC ED 651.5 HRS AGO ON APR 20, 1999, AND THEY ARE SHOWING WEAKNESS. SUBMITTER STATED CHIEFTAIN IS HEAVIER TO STEER THAN NA VAJOS USING SAME SYS. LUBRICATING SYS MORE OFTEN HELPS. SUBMITTER SUGGESTED PIPER PUT 500 HR LIFE LIMIT ON THESE BOLTS . SUBMITTER CITED AN INCIDENT WITH AN OPERATOR WHERE COMPLETE STEERING ARM ASSY HAD LEFT A/C AND SUSPECTED CAUSE TO BE OVERSTRESSING THESE THREE BOLTS. 1 L 7 2 3O 3 O A20SO E14EA 2000083000075 20000830 00075 CE 2000 8 30 CA000329041 1 20000317 G 3250 50420101 HORN CESSNA CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO MCAULY 3AF32C 3AF32C87 GL CENTER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 59300 232095R 779115 (CAN) THE STEERING HORN WAS FOUND CRACKED JUST OUTBOARD OF THE CENTER PIVOT ATTACHMENT. THE CRACKS WERE CONFIRMED USING FPI. 1 L 7 2 3O 3 O 3A10 E5CE 5 C P22EA 2000083000126 20000830 00126 SO 2000 8 30 CA000329042 1 20000328 G 2434 ALU8421LS ALTERNATOR PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2B 41532 EA INTERNAL SHORTED W A UNSCHED LANDING H ELECT. POWER LOSS-50 PC CR CRUISE 1 CA 55600 RL77261 (CAN) SHORTLY AFTER TAKEOFF, THE AMMETERS WERE SHOWING A DISCHARGE AND VOLTAGE REGULATOR POPPED. ALTERNATOR FOUND TO B E SHORTED INTERNALLY. 1 L 7 2 3O 3 O A20SO E14EA 2000083000127 20000830 00127 CE 2000 8 30 CA000330003 1 20000131 G 3233 115380025 MOTOR RAYTHN 115811020613 BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA INTERNAL WEAK W O OTHER H R J ELECT. POWER LOSS-50 PC PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 CA 30300 PCE80590 (CAN) DURING CLIMB WHEN THE GEAR WAS SELECTED UP, THE GEAR RETRACTED ONLY HALF WAY AND THE GEAR HANDLE RED LIGHT REMAINE D ILLUMINATED. THE GEAR WAS LEFT IN ITS PARTIALLY RETRACTED POSITION. WHEN ON APPROACH AND THE GEAR SELECTED TO EXTEND , THE GEAR WOULD NOT MOVE. THE GEAR WAS MANUALLY EXTENDED. MAINTENANCE FOUND THE 60 AMP CIRCUIT BREAKER UNDER THE FLOO RBOARD TO HAVE TRIPPED. UPON RECYCLING THE GEAR IT WAS DETERMINED THAT THE MOTOR WAS WEAK AND DRAWING TOO MUCH CURRENT (APPROX. 53 AMPS). BENCH TESTING FOUND EXCESSIVE SPARKING. THE MOTOR WAS REPLACED. THE STRIP DOWN REPORT REVEALED THA T THE 4 BRUSH SPRINGS WERE WORN AND THE FILTER ASSY SHORTED. 1 L 7 2 4T 4 T A24CE E4EA 2000082100136 20000821 00136 CE 2000 8 21 CA000330004 1 20000323 G 5414 631220292 SKIN CESSNA CESSNA 525 525 2076601 CE MID SKIN CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 1665 (CAN) DURING SCHEDULED MAINTENANCE, A CRACK WAS FOUND ON THE LOWER PYLON SKIN. THE CRACKS WERE FOUND ON TWO RIVET ROWS P ARALLEL TO THE C/L OF THE AIRCRAFT. THE CRACKS WERE APPROXIMATELY SIX INCHES LONG. 1 L 7 2 4F RT A1WI 2000082100137 20000821 00137 CE 2000 8 21 CA000330005 1 20000323 G 7830 6354050204 CHANNEL CESSNA CESSNA 525 525 2076601 CE WILINT FJ44 FJ44 66000 GL INBD PIVOT ATTAC CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 1016 1131 (CAN) DURING SCHEDULED MAINTENANCE, CRACKS WERE FOUND ON THE THRUST ATTENUATOR PIVOT SUPORT CHANNELS (UPPER AND LOWER, R IGHT SIDE). THESE CHANNELS HAD BEEN INSTALLED AS PART OF SERVICE BULLETIN 525-78-03. 1 L 7 2 4F 4 F RT A1WI E3GL 2000083000134 20000830 00134 SO 2000 8 30 CA000330006 1 20000323 G 3710 2H2211 SOLENOID AIRBORNE 2H2211 PIPER PA31 PA31 7103102 SO LYC O540 TIO540A1A 41532 EA VALVE STUCK W O OTHER O OTHER TX TAXI/GRND HDL 1 CA 45200 L81561C (CAN) PILOT REPORTED SLUGGISH GYRO OPERATION, FOUND LOW GYRO PRESSURE (3 PSI) ON BOTH ENGINES SELECTED OR SINGLE ENGINE OPERATION. UNABLE TO INCREASE PRESSURE. REMOVED VALVES (P/N 2H22-11) AND BENCH TESTED RESPECTIVE SOLENOIDS. SOLENOID S FOUND TO BE PARTIALLY CLOSED AND NOT ENERGIZING ON POWER AS WELL AS LOSING PRESSURE ON LOW PRESSURE SIDE. BOTH VALVES REPLACED. 1 L 7 2 3O 3 O A20SO E14EA 2000073100018 20000731 00018 EA 2000 7 31 CA000331010 2 20000325 G 7310 3011857 LINE PWA EMB 110 EMB110P1 3260122 SO PWA PT6 PT6A34 52043 EA FCU CRACKED W K NONE B K SMOKE/FUMES/ODORS/SPARKS FLUID LOSS LD LANDING 1 CA 6675 PCE56782 (CAN) FUEL LINE CRACK AT B-NUT FOUND TO BE THE CAUSE OF FUEL ODOR, AT FCU. FEEDBACK. 1 L 7 2 4T 4 T A21SO E4EA 2000082100138 20000821 00138 CE 2000 8 21 CA000331013 1 20000327 G 3240 651710018 RESERVOIR CESSNA 651710018 CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE AFT WELD LINE CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 71721 (CAN) DURING INSPECTION, THE BRAKE FLUID RESERVOIR WAS FOUND LEAKING AT A CRACK ON THE AFT RIGHT CORNER WELD BEAD. 1 L 7 2 4F 4 F A22CE E1NE 2000073100019 20000731 00019 NE 2000 7 31 CA000404001 2 20000321 G 7314 SHAFT PWA DHAV DHC2 DHC2MK1 2800102 EA PWA R985 R985AN1 52008 NE FUEL PUMP BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 320 4221504 (CAN) ENGINE WOULD NOT RUN WITHOUT WOBBLE PUMP OPERATING. ENGINE DRIVEN PUMP REMOVED AND QUILL SHAFT FOUND BROKEN. 1 H 7 1 3R 3 R A806 5E1 2000071800168 20000718 00168 EA 2000 7 18 CA000404002 2 20000324 G 7314 301600 PUMP PWA BELL 212 212 1181420 SW PWA PT6T PT6T3 52045 EA TURB PWR SECTION FAILED W A UNSCHED LANDING E VIBRATION/BUFFET CR CRUISE 1 CA 11441 2916 CPPS60876 (CAN) FUEL PUMP SHAFT WAS ROUGH TO TURN. SENT FOR EVALUATION. 1 G 7 1 4U 4 U H4SW E22EA 2000083000135 20000830 00135 CE 2000 8 30 CA000404005 1 20000229 G 2612 473275 FIRE DETECTOR BEECH 200 B200C 1152924 CE PWA PT6 PT6A41 52043 EA WIRING SHORTED W K NONE N FALSE WARNING CR CRUISE 1 CA (CAN) THE CREW REPORTED THAT DURING FLIGHT THE LEFT ENGINE FIRE WARNING CAME ON INTERMITTENTLY. THE LIGHT INDICATION OC CURS ONLY AFTER PRECIPITATION OR AIRCRAFT WASHING. FOUND FIRE DETECTOR TRIGGER VOLTAGE LEAKING THROUGH WIRE INSULATION WHEN IT IS WET. 1 L 7 2 4T 4 T A24CE E4EA 2000083000136 20000830 00136 CE 2000 8 30 CA000404006 1 20000315 G 3233 993880051 RESTRICTOR VALVE BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA RESTRICTOR VALVE SHEARED W O OTHER K FLUID LOSS CR CRUISE 1 CA PCE80342 (CAN) RESTRICTOR VALVE SHEARED OFF FROM THE LEFT MAIN LANDING GEAR RETRACT/EXTEND ACTUATOR (UP LINE) CAUSING HYDRAULIC F LUID TO BE LOST DURING FLIGHT. RESTRICTOR VALVE REPLACED. 1 L 7 2 4T 4 T A24CE E4EA 2000071800179 20000718 00179 NE 2000 7 18 CA000404015 2 20000404 G 7530 0177556170 TACHOMETER SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1B 6OO30 NE INTERNAL FAILED W O OTHER O OTHER LD LANDING 1 CA 255 2194B 840 (CAN) TACHOMETER BOX FAILED TO SEND SIGNAL TO BLEED VALVE, CAUSING VALVE NOT TO CLOSE. 1 G 7 1 3U 3 U H9EU E19EU 2000082100139 20000821 00139 CE 2000 8 21 CA000404021 1 20000328 G 3340 S21604 SWITCH CESSNA 172 172P 2072436 CE LYC O320 O320D2J 41508 EA TERMINAL LOOSE W D RETURN TO BLOCK B SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 CA L1701539A (CAN) DURING THE RUN-UP, THE PILOT NOTICED SMOKE COMING FROM BEHIND THE INSTRUMENT PANEL. THE AIRCRAFT WAS TAXIED BACK T O THE RAMP AND SHUT DOWN. MAINTENANCE FOUND A LOOSE/OVERHEATED CONNECTOR ON THE BACK OF THE LANDING LIGHT SWITCH. 1 H 7 1 3O 3 O NT 3A12 E274 2001030800128 20010308 00128 GL 2001 3 8 CA000404022 3 20000317 G 6111 S90AT4 BLADE MCAULY D2A34C58 CESSNA 185 A185F 2072821 CE CONT O520 IO520D 17032 SO MCAULY 2A34C D2A34C58 GL THREADED AREA CRACKED W O OTHER O OTHER IN INSP/MAINT 1 CA 477 734108 816532R 734108 (CAN) BLADE THREADS CRACKED S/N K67168YS 1 H 7 1 3O 3 O 3A24 E5CE 5 C P3EA 2000073100020 20000731 00020 SO 2000 7 31 CA000404025 1 20000323 G 6120 B30012 COLLAR HARTZL AYRES S2 S2RT34NORMAL 0970106 SO PWA PT6 PT6A34AG 52053 NE HARTZL HCB3T HCB3TN3 GL INNER SURFACE DAMAGED W O OTHER O OTHER IN INSP/MAINT 1 CA 159 PCE56682 BU10976 (CAN) DAMAGE TO INNER SURFACE OF LOW STOP COLLAR DUE TO IMPROPERLY SECURED LOCK WIRE. 1 L 7 1 3T 4 T A3SW E4EA 6 C P15EA 2000071800183 20000718 00183 EA 2000 7 18 CA000404031 2 20000309 G 7322 HA61030 CARBURETOR HUGHES 269 269C1 8059504 SW LYC O360 HO360C1A 41514 EA ENGINE FAILED W E ENGINE SHUTDOWN R PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 CA 45 75048907 L3486936A (CAN) ENGINE QUIT DURING IDLE , AFTER RESTART, ENGINE WOULD NOT ACCELERATE FROM IDLE TO WARM UP RPM. CARBURETOR REPLACE D. 1 G 7 1 3O 3 O O 4H12 E286 2000083000140 20000830 00140 EA 2000 8 30 CA000404047 2 20000327 G 7414 COIL BOSCH SFLU1410 GRUMAV TBM TBM3AIRTRD 3950308 EA WRIGHT R2600 R260020 67050 EA HAMSTD 23E 23E50 NE AT STUD BURNED OUT W K NONE O OTHER IN INSP/MAINT 1 CA 39000 S9131 172966 P84440 (CAN) DURING ANNUAL INSPECTION IT WAS FOUND THAT THE MAGNETO COULD NOT BE TIMED PROPERLY. FURTHER INVESTIGATION REVEALE D THE COIL TO ROTOR CONTACT STUD WAS BROKEN AND THE COIL BURNED. 1 L 7 1 4R 4 R L82 TC176 6 C P603 2000083000142 20000830 00142 CE 2000 8 30 CA000410008 1 20000329 G 3213 9981002823 TRUNNION BEECH 100 100BEECH 1152916 CE PWA PT6 PT6A28 EA UPR TORQ KNEELUG CRACKED W O OTHER O OTHER IN INSP/MAINT 1 CA PCE50045 (CAN) RIGHT MAIN LANDING GEAR ASSEMBLY WAS FOUND TO BE CRACKED AT THE UPPER TORQUE KNEE HOUSING. BOTH SIDES OF THE LUG WERE CRACKED. 1 L 7 2 3T 4 T A14CE E4EA 2000083000143 20000830 00143 CE 2000 8 30 CA000410009 1 20000331 G 5610 10138402521 WINDSHIELD BEECH STC200BEECH BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA L/H SIDE CRACKED W D RETURN TO BLOCK O OTHER IN INSP/MAINT 1 CA PCE81062 (CAN) WINDSHIELD DELAMINATED 2 MONTHS PRIOR TO CRACK. DELAMINATION WAS WITHIN THE BEECH SERVICE MANUAL LIMITS. WINDSHI ELD CRACKED IN AREA OF DELAMINATION. 1 L 7 2 4T 4 T A24CE E4EA 2000073100021 20000731 00021 SO 2000 7 31 CA000410010 1 20000331 G 8120 LINE CONT PIPER PA31 PA31 7103102 SO LYC O540 TIO540F2BD 41532 EA TURBOCHARGER BROKEN W A E UNSCHED LANDING ENGINE SHUTDOWN E VIBRATION/BUFFET AP APPROACH 1 CA L473961A L473961A (CAN) OIL LINE FAILURE AT FITTING FEEDING TURBOCHARGER SECONDARY DAMAGE TO CONNECTING ROD BEARING CAUSING ROD FAILURE. 1 L 7 2 3O 3 O A20SO E14EA 2001030800055 20010308 00055 EU 2001 3 8 CA000410015 1 20000323 G 3297 9717516500 WIRE PILATS PC12 PC1245 7090551 EU INSIDE NLG PLUG BROKEN W L ABORTED APPROACH J WARNING INDICATION AP APPROACH 1 CA 270 (CAN) ON APPROACH THE PILOT NOTICED THAT THE NOSE GEAR DOWN AND LOCKED LIGHT DID NOT ILLUMINATE AND THAT ALL THREE IN TR ANSIT LIGHTS STAYED ON. LANDING GEAR WAS VERIFIED TO BE DOWN BY CONTROL TOWER PERSONNEL AND THE AIRCRAFT LANDED SAFELY. MAINTENANCE TRACED THE PROBLEM TO A BROKEN WIRE IN THE NOSE GEAR PROXIMITY SENSOR CANNON PLUG (P056, PIN A). 1 L 7 1 3T RT A78EU 2000071100294 20000711 00294 NE 2000 7 11 CA000410036 2 20000305 G 7310 0301007710 LINE TMECA SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1B 6OO30 NE BELOW FLARE CRACKED W O OTHER K FLUID LOSS IN INSP/MAINT 1 CA 866 (CAN) ENGINE FAILED TO START, MAINTENANCE FOUND SPRAY OF FUEL BETWEEN THE LEFT HAND FITTING TO THE START INJECTOR. THE LINE WAS REMOVED AND FOUND CRACKED AT BASE OF THE FLARE. 1 G 7 1 3U 3 U NC H9EU E19EU 2000072000054 20000720 00054 WP 2000 7 20 CA000412001 1 20000303 G 6510 369D25518 DRIVE SHAFT HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL DAMPER BRACKET DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 9502 CAE831949 (CAN) UPON REMOVAL OF TAIL ROTOR GEARBOX AND DRIVESHAFT, EXTENSIVE DAMAGE WAS FOUND ON TAIL ROTOR DRIVESHAFT. INVESTIGAT ION REVEALED THAT THE DAMPER BRACKET WAS BROKEN OFF WHICH ALLOWED THE TAIL ROTOR DRIVESHAFT TO WHIP AND RESULT IN THIS D AMAGE. 1 G 7 1 3U 3 U H3WE E4CE 2000083000149 20000830 00149 CE 2000 8 30 CA000412002 1 20000331 G 3233 1053840001 ACTUATOR 1058200001 BEECH 76 76 1153005 CE LWR PART HOUSING CRACKED W O OTHER R PARTIAL RPM/PWR LOSS LD LANDING 1 CA (CAN) NOSE GEAR FAILED TO RETRACT AFTER DOING NUMEROUS GEAR EXTENSION/RETRACTIONS DURING TRAINING. MAINTENANCE FOUND NO SE LANDING GEAR ACTUATOR HAD A HAIRLINE CRACK IN ITS HOUSING WHICH ALLOWED THE FLUID TO SLOWLY LEAK OUT.ACTUATOR REPLACE D. 1 L 7 2 3O A29CE 2000072600167 20000726 00167 EU 2000 7 26 CA000412003 1 20000403 G 6420 1053172904 BUSHING BOLKMS 1053172901 BOLKMS 105 BO105S 5626006 EU TAIL ROTOR CRACKED W K NONE O OTHER CR CRUISE 1 CA 5651 (CAN) PILOT COMPLAINED THAT EXCESSIVE LEFT PEDAL WAS REQUIRED. TAIL ROTOR ASSEMBLY WAS MEASURED WITH SPRING SCALE AND FO RCES WERE FOUND EXCESSIVE. TAIL ROTOR DISASSEMBLED TO CLEAN INNER SLEEVE BUSHINGS AND TEFLON BUSHINGS. THE OUTBOARD SLE EVE BUSHING WAS FOUND CRACKED. 1 G 7 2 3U H3EU 2000070300767 20000703 00767 NE 2000 7 3 CA000412004 2 20000314 G 7261 0301037180 VENT LINE TMECA ARRIEL1D SNIAS 350 AS350B1 8680811 EU TMECA ARRIEL ARRIEL1D NE REAR BRG VENTL BROKEN W K NONE O OTHER CR CRUISE 1 CA 3084 7026 7026 (CAN) ENGINE REAR BEARING VENT LINE SNAPPED OFF DURING FLIGHT AND WAS LATER DISCOVERED THAT THE VENT LINE WENT INTO THE TAIL ROTOR. THE PREVIOUS DAY THE VENT LINE CLAMP HAD BROKE AND IT WAS THEN NOTED THAT THE VENT LINE HAD CHAFE WEAR MARK S CAUSED BY THIS CLAMP. 1 G 7 1 3U 3 U H9EU E19EU 2000083000150 20000830 00150 SW 2000 8 30 CA000412007 1 20000405 G 3240 332 CONTROL CABLE 3434 BBAVIA 7 7EC 2110120 SW CONT O200 O200A 17020 SO BRAKE SYSTEM FRAYED W K NONE O OTHER IN INSP/MAINT 1 CA 42400 637556A (CAN) DURING INSPECTION, NOTICED THAT THE LT AND RT BRAKE CABLES WERE BADLY FRAYED WHERE THEY PASS THROUGH THE LOWER FAI RLEADS (P/N 1-2259) ON THE AXLE STRUTS. FURTHER INSPECTION, REVEALED FRAYING OF THE CABLE BACK INSIDE THE SHEATHING UN DER THE BOOT COWL. THIS FRAYING COULD ONLY BE DETECTED BY REMOVING THE AFFECTED CABLE ASSEMBLY. BOTH CABLES REPLACED. 1 H 7 1 3O 3 O A759 E252 2000073100022 20000731 00022 CE 2000 7 31 CA000412009 1 20000412 G 2750 262228112 BELLCRANK CESSNA 208 208B 2073701 CE INPUT ARM BROKEN W L ABORTED APPROACH F FLT CONT AFFECTED AP APPROACH 1 CA 2392 (CAN) DURING APPROACH ,THE FLAPS FULLY RETRACTED. MAINTENANCE PERSONNEL FOUND THAT THE RIGHT FLAP BELLCRANK HAD BROKEN AT THE ARM CONNECTED TO THE INPUT DRIVE SHAFT FROM THE FLAP TRANSMISSION. THE BREAK OCCURRED AT THE WELD WHERE THE DOUB LER ENDS. THE BELLCRANK HAD BEEN INSPECTED FOR CRACKS 351 LANDINGS PREVIOUSLY. 1 H 7 1 3T A37CE 2000083000151 20000830 00151 CE 2000 8 30 CA000412010 1 20000410 G 5610 50420051255 WINDSHIELD BEECH STC99 BEECH 99 99 1154002 CE PWA PT6 PT6A28 EA OUTER PANE CRACKED W O OTHER O OTHER CR CRUISE 1 CA U98 PCE41733 (CAN) WHILE EN ROUTE, THE CAPTAIN NOTICED THE WINDSHIELD CRACKED. WINDSHIELD REPLACED. 1 L 7 2 3T 4 T A14CE E4EA 2000071100292 20000711 00292 EU 2000 7 11 CA000412015 1 20000412 G 6320 BABDRR SEAL SNIAS 350 AS350B2 8680813 EU M/R TRANSMISSION LEAKING W K NONE O OTHER IN INSP/MAINT 1 CA 72 (CAN) MAIN ROTOR TRANSMISSION INPUT SEAL LEAKING AT 71.6 HOURS SINCE INSTALLATION. SEAL CHANGED, BUT LEAKING AGAIN AT 101.3 HOURS. INPUT SEAL WAS FOUND TO BE .003 THOUSANDS OF AN INCH LARGER DIAMETER. 1 G 7 1 3U H9EU 2000083000152 20000830 00152 SO 2000 8 30 CA000412016 1 20000405 G 5743 40287KAE ATTACH FITTING PIPER 40288000 PIPER PA31T PA31T 7103124 SO PWA PT6 PT6A28 EA TOP REINFORC RIB CRACKED W O OTHER O OTHER IN INSP/MAINT 1 CA 14172 PCE51966 (CAN) DURING ROUTINE INSPECTION, A CRACK WAS FOUND ON THE LEFT AFT MAIN LANDING GEAR TRUNNION ASSEMBLY. THE CRACKS WERE FOUND TO BE ON THE UPPER REINFORCEMENT RIBS. PART WAS REPLACED. 1 L 7 2 3T 4 T A8EA E4EA 2000073100023 20000731 00023 CE 2000 7 31 CA000414007 1 20000329 G 3397 WIRE CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA MCAULY 1C160 1C160DTM GL CABIN CHAFED W H A DEACTIVATE SYST/CIRCUITS UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 CA RL462776T 728612 (CAN) DURING CLIMB, THE PILOT NOTICED A BURNING SMELL. THE PILOT TURNED OFF ALL ELECTRICS AND RETURNED FOR LANDING. MAI NTENANCE PERSONNEL FOUND THE WIRES TO THE LIGHT DIMMING CIRCUIT WERE SHORTING TO GROUND WHERE THEY HAD CHAFED ON THE CON SOLE STRUCTURE. THE SHORT WAS INTERMITTANT AND DID NOT USE ENOUGH CURRENT TO CAUSE THE CIRCUIT BREAKER TO TRIP. THE WIR E WAS REPAIRED AND A CHAFE STRIP WAS ADDED TO THE STRUCTURE IN THE AREA OF THE WIRE DAMAGE. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2000072000062 20000720 00062 SW 2000 7 20 CA000414009 1 20000411 G 2435 230321380 BRUSH BLOCK LEARSIEGLER 23032018 BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL STARTER GENERATO BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 436 4900 CAE832736 (CAN) POST-FLIGHT INSPECTION REVEALED THAT ONE OF THE BRUSHES WAS WORN DOWN TWICE AS MUCH AS THE OTHER VISIBLE BRUSH. U PON REMOVAL, IT WAS THEN NOTED THAT ONE OTHER BRUSH WAS BROKEN AND/OR BURNT OFF. HOWEVER, THE STARTER/GENERATOR WAS STI LL FUNCTIONING AS IT GAVE NO FAILURE WARNING INDICATION. 1 G 7 1 3U 3 U H2SW E4CE 2000071900178 20000719 00178 NE 2000 7 19 CA000419005 2 20000410 G 7210 103019204 SUN GEAR LYC BELL 205 205A1 1181414 SW LYC T53 T5313B 41549 NE REDUCTION GEARBX BROKEN W O OTHER P NO WARNING INDICATION IN INSP/MAINT 1 CA 72500 LE07187X (CAN) UPON FURTHER INVESTIGATION INTO WHY ENGINE WAS MAKING METAL, IT WAS FOUND THAT TWO TEETH HAD FRAGMENTED OFF THE GE AR. THE TEETH FRAGMENTS WERE .6250 INCH LONG AND WERE FOUND TRAPPED IN THE INTERNAL OIL SCREEN. THE CAUSE FOR THE GEAR FAILURE WAS NOT EVIDENT. AS SPECIFIED BY THE SUBMITTER AND IAW THE ENGINE MANUAL, THIS ENGINE COULD HAVE REMAINED IN S ERVICE. 1 G 7 1 4U 4 U H1SW E17EA 2001011104480 20010111 04480 CE 2001 1 11 CA000419009 1 20000414 G 3246 13889 CONE BEECH 1900 1900C 1154161 CE MLG WHEEL SCORED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) BEARINGS RECEIVED FROM CANADIAN DISTRIBUTOR WITH NEW CERTIFICATION BUT VISUALLY INSPECTED TO BE USED PARTS. ISSUE SENT TO MAINTENANCE AND MANUFACTURING FOR FOLLOW-UP. (X) 2 L 7 2 4T RT A24CE 2000083000157 20000830 00157 SO 2000 8 30 CA000419012 1 20000406 G 3246 751489 CONE PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2B 41532 EA NOSE FAILED W K NONE O OTHER IN INSP/MAINT 1 CA L285161 (CAN) NOSE WHEEL BEARING FAILED ONLY 11.5 HOURS AFTER INSPECTION. THE BEARINGS HAD BEEN CHECKED VISUALLY AFTER THEY WER E CLEANED AND THEN RELUBED. SUBMITTER IS CONCERNED THAT THE VISUAL INSPECTION METHOD IS INADEQUATE TO DETECT POSSIBLE B EARING FAILURE. 1 L 7 2 3O 3 O A20SO E14EA 2000083000159 20000830 00159 EA 2000 8 30 CA000427001 2 20000408 G 7320 RSA10AD1 SERVO PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2B 41532 EA FUEL INJ SERVO FAILED W K NONE L W NO TEST INADEQUATE Q C IN INSP/MAINT 1 CA L58061 (CAN) FCU REQUIRED INTERNAL FUEL FLOW ADJUSTMENTS. 1 L 7 2 3O 3 O A20SO E14EA 2000083000160 20000830 00160 NE 2000 8 30 CA000427002 2 20000403 G 8530 399354 CYLINDER PWA DHAV DHC2 DHC2* 2800108 EA PWA R985 R985AN14B 52008 NE BTWN HEAD&BARREL CRACKED W A UNSCHED LANDING E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CL CLIMB 1 CA 62000 32349 (CAN) CYLINDER FOUND SEPARATED BETWEEN HEAD AND BARREL. AD 78-08-07 COMPLIED WITH AT OVERHAUL 63 HOURS PREVIOUSLY. 1 H 7 1 3R 3 R A806 5E1 2000072000308 20000720 00308 SW 2000 7 20 CA000427003 1 20000329 G 6710 212076151007 TUBE BELL 212 212 1181420 SW PWA PT6T PT6T3 52045 EA CYCLIC LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA CPPS61242 (CAN) DURING INSPECTION, THE RIGHT CYCLIC SERVO INPUT LEVER WAS FOUND IN AN AFT OF CENTER ORIENTATION. SUBSEQUENT OBSER VATION REVEALED BOTH CYCLIC BOOST TUBES HAD LOOSE CLEVIS ASSEMBLIES AT LOWER END. THIS CAUSED THE SERVO TO ROTATE IN AN Y POSITION AND INTERFERE WITH THE PARENT STRUCTURE. NORMALLY, THE CLEVISES MUST BE TIGHT AND LOCKED IN POSITION TO PRE VENT THE SERVO FROM TURNING. THE USE OF SILICONE SEAL WAS USED TO BOND THE THREADED CLEVIS TO TUBE AS PER BELL MAINTENAN CE MANUAL. BELL WAS INFORMED AND STATED THAT THEY ARE MAKING THE CORRECTION TO THE MAINTENANCE MANUAL. 1 G 7 1 4U 4 U H4SW E22EA 2000072000208 20000720 00208 SW 2000 7 20 CA000427004 1 20000411 G 5302 212030447001 BEAM BELL 212030100103 BELL 212 212 1181420 SW PWA PT6T PT6T3 52045 EA LEFT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 11193 ADW04155 CPPS61242 (CAN) DURING PRE-FLIGHT, THE LEFT HAND BEAM CAP ON THE TAILBOOM PYLON WAS FOUND CRACKED (.080 INCH). NOTE: THIS CRACK WAS FOUND IN THE SAME PLACE AS DESCRIBED IN FAA AD 99-18-02 APPLICABLE TO BELL 205 SERIES. 1 G 7 1 4U 4 U H4SW E22EA 2000083000161 20000830 00161 EA 2000 8 30 CA000427005 2 20000410 G 8520 STD1211 PLUG LYC LW17071 CESSNA 172 172P 2072436 CE LYC O320 O320D2J 41508 EA MCAULY 1C160 1C160DTM GL EXPANSION PLUG BACKED OUT W A UNSCHED LANDING K FLUID LOSS CL CLIMB 1 CA 28000 L1232339A BL073 (CAN) EXPANSION PLUG AT FRONT OF CRANKSHAFT HAD COME LOOSE ALLOWING OIL TO LEAK OUT. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2000082100140 20000821 00140 EU 2000 8 21 CA000427010 1 20000413 G 3242 9595601511 BRAKE PILATS PC12 PC1245 EU RT GEAR FROZEN W O OTHER O OTHER LD LANDING 1 CA 13 (CAN) THE RIGHT BRAKE FROZE AND ON LANDING THE TIRE FAILED TO ROTATE AND WORE THROUGH THE CASING. THE TIRE WENT FLAT AND THE AIRCRAFT HAD TO BE TOWED FROM THE RUNWAY. 1 L 7 1 3T RT A78EU 2000083100898 20000831 00898 EU 2000 8 31 CA000427030 2 20000417 G 7414 996538 STATOR ROTAX DIAMON DA20 DA20A1 GL ROTAX 912 ROTAX912 55555 EU R/H COIL BROKEN W K NONE R Y PARTIAL RPM/PWR LOSS ENGINE STOPPAGE IN INSP/MAINT 1 CA 58800 4380752 (CAN) AD 98..SB 912-026R3 PREVIOUSLY COMPLIED WITH. SUBSEQUENT FAILURE OF STATOR PICK-UP COIL FOUND WITH PIECES MISSING AND COPPER WINDINGS SEVERED. COMPONENT HAD 587.7 HOURS. 1 L 7 1 3O 3 I NT TA4CH EXPE3I 2000100300254 20001003 00254 2000 10 3 CA000427035 4 20000418 G 3400 030023490004 CONNECTOR HONEYWELL KNR634066107 ELECT CONNECTOR WRONG PART W O OTHER O OTHER IN INSP/MAINT 1 CA 3607 (CAN) NO TEXT 2000100300255 20001003 00255 NE 2000 10 3 CA000427036 2 20000418 G 7210 311657901 PINION GEAR PWA PWA 120 PW123D 52152 NE 2ND STG PINION SPALLED W K NONE O OTHER IN INSP/MAINT 1 CA 33700 AG0086 (CAN) GEAR TEETH ON THE BULL GEAR AND BOTH SECOND STAGE PINIONS WERE SPALLED AND MISSING MATERIAL. THE WEAR PATTERNS OF THE GEARS SHOWED HEAVY WEAR ON THE FRONT HALVES AND THE SPALLED SECTIONS WERE ALL IN THE FRONT HALF OF THE GEAR TEETH. NO ALIGNMENT ERRORS WERE FOUND NOR LUBRICATION OR RESIDUAL MAGNETISM SEEMED TO BE AT FAULT. THE NR 11 BEARINGS WERE FO UND TO HAVE MISMATCHED SERIAL NUMBERS. SEVEN RGB''S TO DATE WITH SIMILAR PROBLEMS HAVE BEEN REPORTED BY THE SUBMITTOR A ND THE OPI IS AWARE AND REVIEWING THE SERVICE DIFICULTIES EXPERIENCED. 4 T E20NE 2001030900020 20010309 00020 NM 2001 3 9 CA000501001 1 20000113 G 3350 6104799 LIGHT DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE CABIN FAILED W K NONE L NO TEST IN INSP/MAINT 1 CA 120832 860404 (CAN) BASE ASSY 3351-PS2 REPLACED BECAUSE NUMERIOUS EMERGENCY LIGHTS WOULD NOT TURN ON. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001030900024 20010309 00024 EU 2001 3 9 CA000501006 1 20000421 G 2910 HTE9531101 VALVE BAG BAE146 BAE146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE HYD SYSTEM FAILED W K NONE O OTHER IN INSP/MAINT 1 CA LF05461A (CAN) NR 2 HYD PUMP FAILED. INVESTIGATION REVEALED A LEAKING ISOLATION VALVE. 2 H 7 4 4F 4 F RT A49EU E6NE 2001030900025 20010309 00025 EA 2001 3 9 CA000501009 1 20000412 G 6320 23HD12004 TRANSMISSION BOEING 234 234 1385049 EA LYC AL5512 AL5512 41581 NE MAIN ROTOR MAKING METAL W A UNSCHED LANDING J WARNING INDICATION DE DESCENT 1 CA 85110 13770 (CAN) DURING DESCENT, CHIP WARNING LITE ILLUMINATED. MAINTENANCE PERSONNEL THEN CLEANED CHIP PLUG & CHANGED FILTER. SER VICEABILITY CHECK CARRIED OUT AS PER BOEING MAINTENANCE MANUAL SECTION 63-25-00 & 63-23-00 AND TRANSMISSION FOUND SERVIC EABLE. HOWEVER, ROTORCRAFT WAS FERRIED TO AMO FOR PRECAUTIONARY REPLACEMENT OF TRANSMISSION. 2 G 7 2 4U 4 U H9EA E4NE 2001030900028 20010309 00028 EA 2001 3 9 CA000501013 2 20000414 G 7322 LW10098 CONTROLLER LW1009885 PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA FUEL CONTROL FAILED W O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 CA 569 (CAN) PILOT NOTICED PARTIAL POWER LOSS ON CLIMB THROUGH 5-6000 FT. FAULTY DIFFERENTIAL CONTROLLER WAS FOUND. 1 L 7 2 3O 3 O A20SO E14EA 2001030900029 20010309 00029 NE 2001 3 9 CA000501014 3 20000417 G 6114 P7900010030 HUB MORAVN Z142 Z142 EU HAMSTD V500 AVIAV500A NE OIL SEAL GROOVE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 1151 505 12060787 (CAN) PROP WAS SENT FOR NDT AS PER V500A/6A AND A CRACK WAS FOUND IN THE OIL SEALING RING GROVE RUNNING PARALLEL WITH TH E GROOVE.A SECOND CRACK WAS FOUND 180 DEGREES FROM THE FIRST CRACK ON THE WALL OF THE GROOVE. NEITHER OF THESE CRACKS AR E IN THE LOCATION SET OUT IN THE BULLETIN V500A/6A. 1 L 7 1 3O NT A76EU 5 C P11BO 2001030900030 20010309 00030 WP 2001 3 9 CA000501015 1 20000424 G 5711 SPAR DOUG B26 B26C 3200524 WP PWA R2800 R280079 52026 NE LT WING CRACKED W O OTHER O OTHER LD LANDING 1 CA 3559 FPO24759 (CAN) ON TAKEOFF THE PILOT HEARD A LOUD BANG. A VISUAL INSPECTION REVEALED NOTHING UNUSUAL AND HE CONTINUED THE FLIGHT. ON LANDING THE ENGINEER DISCOVERED THE LT REAR SPAR CRACKED COMPLETELY. FLEET NDT CAMPAIGN BEING CARRIED OUT. 2 M 7 2 4R 4 R L34 5E8 2001030900031 20010309 00031 EU 2001 3 9 CA000501017 1 20000411 G 2742 02109703 ACTUATOR AMD FALC10 FALCON10 2730101 EU GARRTT TFE731 TFE7312 01518 WP HORIZONTAL STAB FAILED W O OTHER J WARNING INDICATION CR CRUISE 1 CA 51300 P73113C (CAN) ON DECENT, FOUND HORIZONTAL STAB NORMAL MODE U/S. SELECTED EMERGENCY STAB AND LANDED.FOUND STAB ACTUATOR NORMAL M ODE MOTOR U/S. 2 L 7 2 4F 4 F A33EU E6WE 2001030900032 20010309 00032 NM 2001 3 9 CA000501018 1 20000415 G 2497 L51015915 WIRE BOEING 737 737242C 1384478 NM PWA JT8 JT8D9A 52048 NE CABIN OVERHEATED W H DEACTIVATE SYST/CIRCUITS M B OVER TEMP SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 CA (CAN) PRIOR TO PASS BOARDING WHILE FLIGHT ATTENDANTS PREPARED THE CABIN FOR FLIGHT SMOKE AND ARCING WAS NOTICED COMING F ROM THE REAR OF THE AIRCRAFT GALLEY COFFEE MAKER CB PANEL. ELECTRICAL POWER WAS REMOVER FROM THE AIRCRAFT GALLEY AND THE FIRE EXTINGUISHER FIRED INTO THE COMPARTMENT. NR 2 COFFEEMAKER CB AND ATTACH WIRES HAD BEEN SEVERELY OVERHEATED AND PAR T OF THE HOUSING AND WIRES WERE BURNED. CB AND WIRES REPLACED. 2 L 7 2 4F 4 F A16WE E2EA 2001030900033 20010309 00033 NM 2001 3 9 CA000501019 1 20000411 G 2612 FIRE LOOP BOEING 737 737242C 1384478 NM PWA JT8 JT8D9A 52048 NE RT ENGINE CHAFED W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 CA (CAN) ON CLIMB CREW OBSERVED ON INTERMITTENT NR 2 ENG FIRE WARNING ILLUMINATION. A/C RETURNED. WIRE UNDER RT ENGINE ANTI SLAVE FOUND CHAFED. WIRE REPAIRED. CRUSH WASHERS UNDER FIRE LOOP CONNECTORS MISSING, REPLACED. FIRE LOOP TOUCHING LOWER COWL, REPOSITIONED. SYS SERVICEABLE. 2 L 7 2 4F 4 F A16WE E2EA 2001030900034 20010309 00034 NM 2001 3 9 CA000501020 1 20000411 G 2781 188915 SENSOR BOEING 737 737242C 1384478 NM PWA JT8 JT8D9A 52048 NE LE FLAPS INTERMITTENT W D RETURN TO BLOCK J WARNING INDICATION TX TAXI/GRND HDL 1 CA 648850 (CAN) ON TAXI CREW OBSERVED LE SLAT IN TRANSIT LIGHT STILL ON. NR 4 LE SLAT PROXIMITY SENSOR REPLACED. SYS SERVICEABLE. 2 L 7 2 4F 4 F A16WE E2EA 2001030900035 20010309 00035 2001 3 9 CA000501021 4 20000418 G 3416 1063701696 ALTIMETER PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2B 41532 EA COCKPIT FAILED W O OTHER N FALSE WARNING DE DESCENT 1 CA 33 (CAN) NEEDLES BECAME ERRATIC AND LOOSE AFTER A FEW HOURS. ITEM RETURNED ON WARRANTY AND REPAIRED. RE-INSTALLED. FAIL ED AFTER 32.5 HOURS. INSTRUMENT REPLACED AGAIN. OVERHAULER SAYS THAT THIS INSTRUMENT WAS WORN. 1 L 7 2 3O 3 O A20SO E14EA 2001030900037 20010309 00037 EA 2001 3 9 CA000501025 1 20000409 G 5270 SENSOR CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE PAX DOOR FAILED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 807167 (CAN) EICAS MESSAGE FAILURE OF THE PASSENGER DOOR UNSAFE, AFTER TAKE OFF FLIGHT RETURNED TO ORD. SENSOR FOUND TO BE FAR . CLEANED SENSORS, PERFORMED SELF TEST. 2 L 7 2 4F 4 F RT A21EA E15NE 2001011104983 20010111 04983 NM 2001 1 11 CA000501029 1 20000331 G 5511 SPAR BOEING 767 767333 NM PWA 4060 PW4060 52119 NE RT HORIZ STAB DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA P724313 (CAN) NO TEXT 2 L 7 2 4F 4 F RT A1NM E24NE 2001030900041 20010309 00041 NM 2001 3 9 CA000501030 1 20000404 G 2421 736664F GENERATOR BOEING 767 767233 NM PWA JT9 JT9D7R4D 52054 NE LT ENGINE FAILED W O OTHER H ELECT. POWER LOSS-50 PC CR CRUISE 1 CA P709683 (CAN) LT ENGINE GENERATOR FAULT DURING FLIGHT BUT RUGHT HAND GEN COULD NOT POWER LT BUSS. APU USED TO POWER LT BUSS. L T INTRIGATED DRIVE GEN REPLACED, SYS SERVICEABLE. 2 L 7 2 4F 4 F RT A1NM E3NE 2001030900042 20010309 00042 WP 2001 3 9 CA000501031 1 20000407 G 2450 5256 CONNECTOR DOUG DC9 DC932 3022066 WP PWA JT8 JT8D7 52053 NE EMERGENCY EXIT CONTAMINATED W K NONE B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 CA P653888D (CAN) SMOKE IN CABIN. AC OUTLET ARCING AND SMOKING AT FLOOR LEVEL UNDERNEATH LT OVERWING EMERGENCY EXIT. WATER INFILTRA TION IN CONNECTOR FROM OVERWING EXIT. CONNECTOR REPLACED. (ADP) 2 L 7 2 4F 4 F A6WE E2EA 2001030900043 20010309 00043 NM 2001 3 9 CA000501032 1 20000411 G 3211 113T11113 FITTING BOEING 767 767209 NM PWA JT9 JT9D7R4D 52054 NE LT DRAG STRUT CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA P709688 (CAN) ON HEAVY MAINTENANCE LT DRAG STRUT SIDE BRACE FITTING BUSHING FOR SPINDLE PIN FOUND WITH EVIDENCE OF HAVING ROTATE D, SEALENT CUT AROUND PERIPHERY OF BUSHING FLANGE. DRAG STRUT BUSHING REMOVED AND HEAVY CORROSION FOUND ON BOTH FLANGE S EAT AND BORE SURFACE OF FITTING. FITTING REWORKED TO REMOVE CORROSION AND OVERSIZE BUSHING FABRICATED AND INSTELLED. 2 L 7 2 4F 4 F RT A1NM E3NE 2001030900044 20010309 00044 NM 2001 3 9 CA000501033 1 20000411 G 3211 113T11104 FITTING BOEING 767 767209 NM PWA JT9 JT9D7R4D 52054 NE RT DRAG STRUT CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 55769 P709688 (CAN) ON HEAVY MAINTENANCE L DRAG STRUT SIDE BRACE FITTING BUSHING FOR SPINDLE PIN FOUND WITH EVIDENCE OF HAVING ROTATED , SEALENT CUT AROUND PERIPHERY OF BUSHING FLANGE. DRAG STRUT BUSHING REMOVED AND HEAVY CORROSION FOUND ON BOTH FLANGE SE AT AND BORE SURFACE OF FITTING. FITTING REWORKED TO REMOVE CORROSION AND OVERSIZE BUSHING FABRICATED AND INSTALLED. 2 L 7 2 4F 4 F RT A1NM E3NE 2001030900045 20010309 00045 EA 2001 3 9 CA000501035 1 20000428 G 2720 26S83 STUD CNDAIR CL600 CL6002B19 EA RUDDER FAILED W O OTHER F FLT CONT AFFECTED CR CRUISE 1 CA (CAN) A/C EXPERIENCED RESTRICTED MOVEMENT OF THE RUDDER PEDALS. ONE OF THE STUDS HAD POPPED OUT OF THE RUDDER PEDELS PR ETECTIVE PANEL RESTRICTING THE MOVEMENT IN FLIGHT.STUDS WERE REMOVED AND SENT TO BOMBARDIER FOR INVESTIGATION. 2 L 7 2 4F RT A21EA 2001030900046 20010309 00046 SO 2001 3 9 CA000501036 1 20000414 G 7430 103572101 IGNITION SWITCH PIPER PA28 PA28140 7102802 SO LYC O320 O320E3D 41508 EA INSTRUMENT PANEL FAILED W E C ENGINE SHUTDOWN ABORTED TAKEOFF B J SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION TO TAKEOFF 1 CA 13607 L4652527A (CAN) SMOKE OBSERVED IN COCKPIT WHEN MAGNETO SWITCH SELECTED TO LT MAG POSITION. INSPECTED A/C WIRE BUNDLES AND CONNEC TIONS. REPLACED FAULTY SWITCH. UNSERVICEABLE SWITCH DISASSEMBLED AND STRONG ELECTRICAL BURNING SMELL WAS NOTED AS WELL AS SOME ELECTRICAL ARCING NOTED INSIDE THE SWITCH. 1 L 7 1 3O 3 O 2A13 E274 2001030900047 20010309 00047 NE 2001 3 9 CA000505002 2 20000505 G 7200 6761005 ACTUATOR BAG BAE146 BAE146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE NR 1 ENGINE FAILED W O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA 17394 LF05543A (CAN) NR 1 ENGINE ACTUATOR CYCLING BACK AND FORTH CAUSING N1 AND TGT TO FLUCTUATE BY 2 PERCENT N1 AND 30 DEGREES TGT.TMS ACTUATOR REPLACED. 2 H 7 4 4F 4 F RT A49EU E6NE 2001030900051 20010309 00051 NE 2001 3 9 CA000505006 2 20000412 G 7321 7257256 FUEL CONTROL BOEING 107 1072 9420604 EA GE CT58 CT581401 30011 NE ENGINE MISRIGGED W O OTHER R PARTIAL RPM/PWR LOSS AP APPROACH 1 CA 280319A ENGINE FAILED TO RESPOND TO COLLECTIVE INPUT. A/C COMPLETED TEST FLIGHT TO ISOLATE PROBLEM WITH NO POSITIVE RESULTS. E NGINE CHANGED OUT. REPORT REQUESTED .05, 15, 2000. ENGINE RIGGING SPECIFIED TO BE THE MOST LIKELY CAUSE. 2 G 7 2 4U 4 U 1H16 1E3 2001030900052 20010309 00052 EA 2001 3 9 CA000505008 2 20000426 G 8550 LW13388 SEAL PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA ACCESSORY CASE LEAKING W E ENGINE SHUTDOWN K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA L147768A (CAN) OIL LEAKING FROM FAILED SEAL BETWEEN OIL FILTER ADAPTER AND ACCESSORY CASE. SHUT DOWN ENGINE IN-FLIGHT. AREA CLE ANED AND NEW SEAL INSTALLED. 1 L 7 2 3O 3 O A20SO E14EA 2001030900053 20010309 00053 EU 2001 3 9 CA000505010 1 20000414 G 3260 622800200 SWITCH BAG JETSTM JETSTM3101 1500215 EU ROTOL R333 R333482F12 GL NLG DAMAGED W L ABORTED APPROACH N FALSE WARNING AP APPROACH 1 CA 50800 DRG138781 (CAN) DURING APPROACH THE CREW LOWERED THE LANDING GEAR AND FAILED TO GET A SAFE (GREEN) INDICATION FOR THE NOSE GEAR.TH HE APPROACH WAS ABORTED AND A TOWER FLY BY WAS PERFORMED IN ORDER TO VERFY THE NOSE LANDING GEAR POSITION. ATC PERSONNEL CONFIRMED THAT THE GEAR APPEARED TO BE DOWN AND A SAFE LANDING WAS CARRIED OUT. MAINTENANCE PERSONNEL FOUND TWO BROKEN WIRES ON THE NOSE GEAR DOWNLOCK SWITCH. 2 L 7 2 4T RT A21EU 6 C P61GL 2001030900054 20010309 00054 GL 2001 3 9 CA000505011 2 20000424 G 7240 6890040 SHIELD BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL NOZZLE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 771 CAT38320F (CAN) WHEN COMPLETING CEB A-1370, 1ST STAGE NOZZLE SHIELD INSPECTION, FOUND AREA OF INSPECTION CRACKED. 1 G 7 1 3U 3 U H2SW E4CE 2001030900055 20010309 00055 EU 2001 3 9 CA000505012 1 20000503 G 5270 9733024202 ARM 552301200 PILATS PC12 PC1245 EU CARGO DOOR LATCH BENT W K NONE N FALSE WARNING IN INSP/MAINT 1 CA 207 (CAN) THE CARGO DOOR COULD BE CLOSED NORMALLY AND THE INDICATION WAS CORRECT. DURING A 100-HOUR INSPECTION, MAINTENANCE PERSONNEL FOUND THE MICROSWITCH ARM ON THE LOCKING LEVER (IPC REF. 52-30-00-05 ITEM 195 - 215) BENT. THE BENT SWITCH A RM PREVENTED THE LOCKING LEVER FROM ENGAGING THE CATCH WHILE ALLOWING THE SWITCH TO MAKE CONTACT AND INDICATE THE DOOR T O BE NORMALLY LOCKED. 1 L 7 1 3T RT A78EU 2001030800087 20010308 00087 SO 2001 3 8 CA000505013 2 20000420 G 8520 6492863 CRANKCASE CONT IO360G CESSNA 337 337B 2075706 CE CONT O360 IO360G 17025 SO MCAULY 2AF34C D2AF34C301 GL ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 1362 352669 (CAN) CRANKCASE FOUND TO BE A LIGHT DUTY CASE.ENGINE SHOP DISCARDED CASE AND REPLACED IT WITH A NEW HEAVY CASE. 1 H 7 2 3O 3 O A6CE E1CE 5 C P5EA 2000083100899 20000831 00899 EU 2000 8 31 CA000505014 2 20000426 G 7414 888712 STATOR ROTAX 912A3 DIAMON DA20 DA20A1 GL ROTAX 912 ROTAX912 55555 EU RT PICKUP COIL BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 94100 4412707 4412707 (CAN) AD 98 SB 996-538 ... REMOVE STATOR AND REPLACE WITH NEW. UPON REMOVAL FOUND RT PICK-UP COIL PLASTIC SHROUD DISIN TEGRATING IN PIECES, NO PERIPHERAL DAMAGE AS A RESULT. SEE ALSO SDR 20000427030. REFER AD98-9120026R3. 1 L 7 1 3O 3 I NT TA4CH EXPE3I 2001030900056 20010309 00056 SO 2001 3 9 CA000505015 1 20000426 G 3230 1742002 SUPPORT BRACKET PIPER PA23 PA23250 7102308 SO LYC O540 IO540C4B5 41532 EA AFT MOUNTING CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 30260 (CAN) AT ANNUAL INSPECTION, A CRACK WAS FOUND ON THE RIGHT MAIN GEAR OUTBOARD TUBE ASSEMBLY OF THE DRAG LINK FITTING SUP PORT (ITEM 13 FIG. 25 OF IPC). THE CRACK IS LOCATED NEAR THE LOWER MOUNTING BOLT HOLE OF THE TUBE ASSEMBLY AND IS ABOUT 1 INCH LONG. 1 L 7 2 3O 3 O 1A10 1E4 2001011103988 20010111 03988 2001 1 11 CA000505016 3 20000427 G 6111 78FF0 BLADE ROOT MCAULY 78FF0 BLADE THREADS CORRODED W O OTHER O OTHER IN INSP/MAINT 1 CA C2535Y ****THIS SDR ATA NEEDS PROP MDL*****(CAN) BLADES RECEIVED FOR REWORK - SB81A. HEAVY CORROSION FOUND DURING LPI. 2000083100900 20000831 00900 GL 2000 8 31 CA000505017 3 20000428 G 6114 57A0285 ROLL PIN HARTZL 8382 TMPSON NAVION NAVIONA 6150104 SW CONT E185 E1859 17014 SO HARTZL HCA2V HCA2V204 GL LINK PIN & CWT MISSING W O OTHER O OTHER IN INSP/MAINT 1 CA 71000 41500 K1886 5054D AK1345 (CAN) MAINTENANCE ISSUE. 1 L 7 1 3O 3 O A782 E246 5 C P24EA 2001030900057 20010309 00057 EA 2001 3 9 CA000505021 1 20000417 G 3230 AN62498 CHECK VALVE CNDAIR CL215 CL2151A10 EA PWA R2800 R2800* 52026 NE RIGHT MLG CRACKED W O OTHER K FLUID LOSS DE DESCENT 1 CA 2494 (CAN) PILOT NOTICED A LOSS OF HYD PRESSURE BEFORE LOWERING THE LANDING GEAR. EMERGENCY LANDING GEAR EXTENSION SELECTED. RT CHECK VALVE WAS FOUND CRACKED AND SEPERATED IN TWO PIECES CAUSING FLUID LOSS. S/B 215-466 INCORPARTED. 2 H 7 2 4R 4 R A14EA 5E8 2001030900058 20010309 00058 CE 2001 3 9 CA000505023 1 20000423 G 5610 141T480013 WINDSHIELD CESSNA 182 182P 2075816 CE CONT O470 O470R 17026 SO MCAULY 2A34C 2A34C201 GL COCKPIT FAILED W O OTHER O OTHER CR CRUISE 1 CA 811954R 713018 (CAN) 2 HOURS INTO FLIGHT CAPTAINS WINDSHIELD OUTER PANE SHATTERED. WINDSHIELD REPLACED, HEAT CONTROLLER REPLACED AND SY STEM CHECKS CARRIED OUT SERVICEABLE. 1 H 7 1 3O 3 O NT TA13 E273 5 C P3EA 2001030900062 20010309 00062 EA 2001 3 9 CA000505028 1 20000505 G 2752 854D10012 ACTUATOR CNDAIR CL600 CL6002B19 EA TE FLAPS FAILED W O OTHER F J FLT CONT AFFECTED WARNING INDICATION AP APPROACH 1 CA (CAN) DURING FINAL APPROACH A/C HAD FLAP FAIL AT 17 DEGREES. RT O/B FLAP FOUND TWISTED. FLAP PANEL AND BOTH ACTUATORS R EPLACED. 2 L 7 2 4F RT A21EA 2001030900063 20010309 00063 EA 2001 3 9 CA000505029 1 20000505 G 2750 852D100012 ACTUATOR CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE TE FLAP SEIZED W O OTHER E VIBRATION/BUFFET AP APPROACH 1 CA (CAN) DURING FINAL APPROACH A/C HAD FLAP FAILURE AT 40 DEGREES. 2 L 7 2 4F 4 F RT A21EA E15NE 2001030900064 20010309 00064 NE 2001 3 9 CA000511001 2 20000502 G 7200 ENGINE DHAV DHC8 DHC8311 1386006 EA PWA PW120 PW123 NE NR 2 LEAKING W O OTHER B SMOKE/FUMES/ODORS/SPARKS DE DESCENT 1 CA 123113 (CAN) OIL SMELL NOTICEDTHROUGH OUTAIRCRAGFT.OIL RESIDUE FOUND IN NR 2 ACM OUTLET DUCTS. IT WAS DETERMINED NR 4 BEARING SEAL LEAKING. 2 H 7 2 4T 4 T RT A13NM E20NE 2001030900065 20010309 00065 NE 2001 3 9 CA000511002 2 20000430 G 7230 216035029 ACTUATOR BAG BAE146 BAE146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE BLEED BAND FAILED W O OTHER M OVER TEMP CR CRUISE 1 CA LF05543A (CAN) BLEED BAND ACTUATOR FAILED CAUSING HIGHER THAN NORMAL TEMPRATURES. 2 H 7 4 4F 4 F RT A49EU E6NE 2001031200403 20010312 00403 NE 2001 3 12 CA000511003 2 20000504 G 7532 217114002 BLEED VALVE BAG BAE146 BAE146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE COMPRESSOR MALFUNCTIONED W O OTHER M OVER TEMP CR CRUISE 1 CA LF05543A (CAN) BLEED BAND ACTUATOR FAILED CAUSING HIGHER THAN NORMAL TREMPERATURES. 2 H 7 4 4F 4 F RT A49EU E6NE 2001030900066 20010309 00066 EU 2001 3 9 CA000511004 1 20000501 G 6420 1053172904 BUSHING BOLKMS 105 BO105S 5626006 EU ALLSN 250C 250C20B 03013 GL TAIL ROTOR LOOSE W E C ENGINE SHUTDOWN ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA CAE835542 (CAN) PILOT STARTED AIRCRAFT AND FOUND PEDAL FORCES EXCESSIVE. AIRCRAFT WAS SHUT DOWN. T/R WAS DISASSEMBLED AND IT WAS F OUND THAT ONE OF THE OUTBOARD BUSHING HAD SLID APPROXIMATELY .25 INCH OFF THE INNER SLEEVE AND WAS RUBBING THE OUTBOARD SPACER, LOCATED INSIDE THE BLADE GRIP. 1 G 7 2 3U 3 U H3EU E4CE 2001030900067 20010309 00067 EA 2001 3 9 CA000511005 1 20000416 G 6410 6117030201041 BLADE CARSON S61 S61LSKRSKY EA GE CT58 CT581401 30011 NE TAIL ROTOR TORN W K NONE O OTHER IN INSP/MAINT 1 CA 891 295082 (CAN) POST FLIGHT INSPECTION REVEALED TWO TEARS IN TAIL ROTOR BLADE POCKET (19 & 16 INCH FROM TIP). IT APPEARS THAT LEAD ING EDGE TAPE CAME LOOSE AND FLAPPED AGAINST BLADE CAUSING THE TWO TEARS. 2 G 7 2 4U 4 U H8EA 1E3 2001031200404 20010312 00404 NE 2001 3 12 CA000511007 2 20000408 G 7260 4050T12P01 BEARING BOEING 107 1072 9420604 EA GE CT58 CT581401 30011 NE ACCESSORY DRIVE FAILED W E A ENGINE SHUTDOWN UNSCHED LANDING Y ENGINE STOPPAGE CR CRUISE 1 CA 96 280209A (CAN) ENGINE CHIP PLUG INDICATED CHIPS & THEN PLUG CLEANED & INSPECTED, SHOWING NO SLIVERS, ONLY PASTE. NEXT DAY AFTER 5 0 MINS OF FLT, FLUXS OCCURRED ON FUEL & OIL PRESSURES&NG&THEN ENGINE FLAMED-OUT. SUBSEQUENTLY, SINGLE ENGINE LANDING CAR RIED OUT AT LOGGING WORK SITE. INITIAL INDICATION IS THAT BEARING FAILED AT FRONT FRAME ACCESSORY DRIVE. POST TEARDOWN R PT STATES THAT FFAD BEARING FAILED WHICH CAUSED BEVEL&PINION GEARS TO WEAR&LOSE CONTACT CAUSING ENGINE FLAMEOUT. METAL T HEN CLOGGED OIL FILTER WHICH WENT INTO BYPASS&THEN CONTAMINATED ALL BEARINGS WHICH FAILED INSP. COMPRESSOR SPOOL&CASES W ERE RED-TAGGED BECAUSE OF HOT SPOTS FROM RUBBING WHICH WERE CAUSED BY HIGH VIBRATIONS. 2 G 7 2 4U 4 U 1H16 1E3 2001030900068 20010309 00068 NE 2001 3 9 CA000511008 2 20000420 G 7310 8945682 LINE FRCHLD SA227 SA227CC SW GARRTT TPE331 TPE33114 01514 NE FCU CRACKED W E A ENGINE SHUTDOWN UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 CA 17743 (CAN) FUEL LINE ITEM NR 105 ON IPC 73-10-01 FOUND CRACKED DUE TO VIBRATION AND LACK OF CLAMP AS REQUIRED WITHIN IPC ITEM NR 110 73-10-01 FIG. 2PAGE 2B. 2 L 7 2 4T 4 T RT A18SW E18NE 2001030900069 20010309 00069 NM 2001 3 9 CA000511009 1 20000426 G 3340 5102991 ATTACH FITTING BOEING 737 737281 138448P NM PWA JT8 JT8D17 52049 NE NLG BROKEN W O OTHER D INFLIGHT SEPARATION AP APPROACH 1 CA P649414B (CAN) ON APPROACH WHEN LANDING GEAR LOWERED CREW REPORTED A BANGING NOISE FROM THE AREA OF THE NOSE. INSPECTION AT THE G ATE FOUND THE TAXI LIGHT SUPPORT HAD BROKEN AND THE TAXI LIGHT WAS TRAILING THE GEAR BY THE WIRE HARNESS. REPAIRED. 2 L 7 2 4F 4 F A16WE E2EA 2001030900070 20010309 00070 EU 2001 3 9 CA000511010 1 20000330 G 2510 5000B2 LATCH SNIAS 350 AS350D 8680803 EU LYC LTS101 LTS101600A2 41560 NE SEAT BELT MALFUNCTIONED W K NONE O OTHER IN INSP/MAINT 1 CA 10000 LE43488E (CAN) IT WAS NOTICED THAT 2 OF THE FOUR SEAT BELT LATHCHES DO NO ALWAYS ENGAGE PROPERLY. WHEN THE BUCKLE IS INSERTED ALL THE WAY INTO THE LATCH, IT SOUNDS AN D LOOKS LIKE IT IS LATCHED BUT IF WE PULL THE BELT TO TIGHTEN IT, THE BUCKLE PULLS OUT OF THE LATCH WITH NO RESTRICTION. IT TAKES 4 TO 5 ATTEMPTS BEFORE BUCKLE LATCHES POSITIVELY. PROBLEM HAS NOW BEEN I DENTIFIED AND REPLACEMENT PARTS ARE ON ORDER. 1 G 7 1 3U 3 U H9EU E5NE 2001030900071 20010309 00071 CE 2001 3 9 CA000511012 1 20000428 G 5540 50600016 BELLCRANK BEECH 100 B100 1152919 CE GARRTT TPE331 TPE3316252B 01514 WP RUDDER LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA 6848 P27206 (CAN) PILOT COMPLAINED OF WING ROCKING PROBLEM. INVESTIGATION FOUND 1/4 PLAY AT RUDDER TRAILING EDGE WHILE PEDALS BEING HELD AT FULL DEFLECTION. PLAY FOUND TO ORIGINATE FROM BELLCRANK FITTING (P/N 50-600016) AND LOWER SUPPORT TUBE ATTACHM ENT POINT (RIVETS). DISASSEMBLY FOUND THE RIVETS WORN, THE 3 BOLTS (P/N AN173-12A) CONNECTING THE RUDDER BELLCRANK AND BELLCRANK FITTING SLIGHTLY BENT AND THE HOLES DISTORTED NEW BELLCRANK, BELLCRANK FITTING AND BOLTS INSTALLED. SUBMITT ER SUSPECTS DAMAGE CAUSED FROM WIND GUSTS AND TOWING WITH GUST LOCK ON. 1 L 7 2 4T 4 T A14CE E2WE 2000062800196 20000628 00196 CE 2000 6 28 CA000511013 1 20000305 G 5720 MS24694 SCREW CESSNA 208 208B 2073701 CE WING PLATE MISINSTALLED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 208B0765 208B0765 (CAN) DURING A PHASE 1 INSPECTION, INCORRECT LENGTH SCREWS WERE FOUND INSTALLED AT WING ACCESS PANELS FOR THE AILERON BE LLCRANK. THE SCREWS WERE RUBBING ON THE BELLCRANK AND THE SUBMITTER STATED THAT THE ENDS OF THE SCREWS WERE FOUND WORN O FF. 1 H 7 1 3T A37CE 2000072100922 20000721 00922 SW 2000 7 21 CA000511015 1 20000427 G 6230 206040536101 BEARING BELL 206040014003 BELL 206 206L 1181522 SW M/R MAST MAKING METAL W K NONE J WARNING INDICATION IN INSP/MAINT 1 CA 79800 NJF389A (CAN) TWO TINY MARKS ON BEARING - MAKING METAL. REPLACED WITH NEW MAST BEARING 206-040-536-101, S/N J0394-1 AND 2, NEW SEAL AND COMPLY WITH 1500 HOUR INSPECTION. 1 G 7 1 3U H2SW 2000062800197 20000628 00197 GL 2000 6 28 CA000511016 2 20000504 G 7230 23009609 BEARING BELL 206 206L 1181522 SW ALLSN 250C 250C20R2 GL COMPRESSOR MAKING METAL W K NONE O OTHER IN INSP/MAINT 1 CA 32230 CAE295288 (CAN) NR 1 COMPRESSOR ROLLER BEARING MAKING METAL. 1 G 7 1 3U 3 U H2SW E4CE 2000062800198 20000628 00198 CE 2000 6 28 CA000511018 1 20000510 G 3297 V31001 WIRE BEECH 100 A100 1152915 CE PWA PT6 PT6A28 EA MLG SWITCH LOOSE W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA PCE50717 (CAN) AIRCRAFT RETURNED WITH GEAR IN-TRANSIT LIGHT. AFTER NUMEROUS GEAR SWINGS IT WAS DISCOVERED THAT THE WIRE WAS LOOS E WHERE IT IS ATTACHED TO THE EMERGENCY GEAR EXTENTION MICRO-SWITCH.THIS SWITCH CUTS POWER SO THAT WHEN THE EMERGENCY SY STEM IS USED THERE IS NO POWER. THE INTERMITTANT POWER CAUSED THE GEAR NOT TO FULLY RETRACT AND CAUSE THE IN-TRANSIT LI GHT TO STAY ON. WIRE WAS SECURED. 1 L 7 2 3T 4 T A14CE E4EA 2000083000166 20000830 00166 CE 2000 8 30 CA000511019 1 20000510 G 5510 1154400312 BRACKET RAYTHN BEECH 100 A100 1152915 CE PWA PT6 PT6A28 EA CASTING CRACKED W O OTHER O OTHER IN INSP/MAINT 1 CA B153 PCE41799 (CAN) CRACK FOUND DURING INSPECTION IN WEBBING. SUBMITTER STATED THIS IS A COMMON AREA FOR CRACKING WITH THE UNITS. 1 L 7 2 3T 4 T A14CE E4EA 2001030900072 20010309 00072 GL 2001 3 9 CA000511020 2 20000315 G 7230 23056109 COMPRESSOR BELL 206 206L1 1182107 SW ALLSN 250C 250C28B 03013 GL ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 860787 (CAN) 1.5 INCH CRACK FOUND ON COMPRESSOR SCROLL STARTING ALONG AFT RADIUS OF SCROLL PROGRESSING TOWARD DISCHARGE ELBOW A ND TURNING TO MIDDLE OF OUTSIDE FACE. 1 G 7 1 3U 3 U H2SW E1GL 2001030900076 20010309 00076 EU 2001 3 9 CA000511024 1 20000420 G 3020 5302412003 INTAKE DUCT PILATS PC12 PC1245 EU ENGINE BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 28770 (CAN) DURING INSPECTION, EXHAUST RESIDUE WAS FOUND ON THE INSIDE OF THE LOWER FORWARD ENGINE COWLING. UPON CLOSER INSPE CTION BOTH PIPE ADAPTERS FOR THE EXHAUST INLET AND OUTLET TO THE INTAKE LIP WERE FOUND BROKEN AWAY FROM THE LIP ASSY. 1 L 7 1 3T RT A78EU 2000072400259 20000724 00259 SW 2000 7 24 CA000511026 1 20000217 G 5347 HOOK BELL BELL 206 206L 1181522 SW ALLSN 250C 250C20R2 GL ON THE LANYARD WRONG PART W O OTHER O OTHER CR CRUISE 1 CA 45146 CAE831288 (CAN) ROTORCRAFT WAS CARRYING A SKIDOO ON THE CARGO HOOK WHEN THE PILOT FELT IT RELEASE. RETURNED TO BASE WHERE THE HOO K AND MECHANICAL AND ELECTRICAL RELEASES WERE CHECKED. AS A PRECAUTIONARY MEASURE, THE HOOK WAS REPLACED. THE REMOVED ASSY WAS TESTED AS PER BREEZE EASTERN RECOMMENDATIONS (TWICE) AND NO DEFECTS WERE FOUND. IT IS SUSPECTED THAT THE WRONG SIZE RING WAS USED ON THE LANYARD. 1 G 7 1 3U 3 U H2SW E4CE 2000082200031 20000822 00031 SO 2000 8 22 CA000511027 1 20000502 G 3030 30216003 PITOT TUBE PIPER DWGI6065 PIPER PA23 PA23250 7102308 SO LYC O540 IO540C4B5 41532 EA L/H WING BURNED OUT W O OTHER M P OVER TEMP NO WARNING INDICATION TO TAKEOFF 1 CA 71510 275476 L585248 (CAN) WHEN PITOT HEAT WAS SELECTED, CIRCUIT BREAKER TRIPPED. UPON INVESTIGATION, FOUND HEATER ELEMENT GROUNDING OUT TO PITOT HEAD HOUSING. SUBMITTER SUGGESTED CAUSE TO BE PREVIOUS USER TO SELECT HEAT WHILE ON GROUND BEYOND THE 3 MINUTE T IME LIMIT OR NORMAL WEAR. 1 L 7 2 3O 3 O 1A10 1E4 2000071200059 20000712 00059 EA 2000 7 12 CA000511029 1 20000310 G 7800 T10417 TRUNNION ORENDA OE600A DHAV DHC3 DHC3 2800202 EA EXHAUST ROCKER FAILED W A UNSCHED LANDING E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CR CRUISE 1 CA 63000 OE600A0016 OE600A0016 (CAN) ROCKER TRUNNION FAILED, PART RETURNED FOR INVESTIGATION. 1 H 7 1 3R A815 2000062800199 20000628 00199 CE 2000 6 28 CA000511030 1 20000502 G 5720 082260030 FITTING CESSNA 082260068 CESSNA 402 402B 207590P CE CONT O520 TSIO520E 17040 SO TIP TANKS LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA 11500 502131A (CAN) DURING SCHEDULED INSPECTION, MOVEMENT WAS NOTICED AT THE AFT TIP TANK FITTING AS MAINTENANCE PERSONNEL APPLIED UP AND DOWN FORCES TO THE TIP TANK TRAILING EDGE. THE TWO MOST OUTBOARD RIVETS WHICH ATTACH THE FITTING TO THE OUTBOARD RIB (THROUGH THE REAR SPAR) WERE FOUND SHEARED. THE SUBMITTER STATES THAT THIS IS THE SECOND AIRCRAFT HE HAS FOUND IN THIS CONDITION. 1 L 7 2 3O 3 O A7CE E8CE 2001021400001 20010214 00001 EA 2001 2 14 CA000511031 1 20000506 G 2740 SWITCH CNDAIR CL600 CL6002B19 EA COCKPIT FAILED W O OTHER F J FLT CONT AFFECTED WARNING INDICATION CR CRUISE 1 CA (CAN) DURING CRUISE AN AP PITCH TRIM MESSAGE APPEARED.BOTH FCC,HSTCU AND TRIM SWITCHES REPLACED. 2 L 7 2 4F RT A21EA 2001030900078 20010309 00078 EA 2001 3 9 CA000511032 1 20000506 G 2611 WARNING SYSTEM CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE CARGO BAY FALSE INDICATION W F ACTIVATE FIRE EXT. B SMOKE/FUMES/ODORS/SPARKS AP APPROACH 1 CA 807147 (CAN) CARGO SMOKE MESSAGE ON SHORT FINAL. FOLLOWED QRH AND BLEW BOTTLES. 2 L 7 2 4F 4 F RT A21EA E15NE 2001031200405 20010312 00405 EA 2001 3 12 CA000511033 1 20000506 G 2752 854D10012 ACTUATOR CNDAIR CL600 CL6002B19 EA TE FLAPS FAILED W B EMER. DESCENT F FLT CONT AFFECTED DE DESCENT 1 CA (CAN) FLAPS FAIL AT 17 DEG. FLAP ACTUATOR REPLACED 2 L 7 2 4F RT A21EA 2001030900079 20010309 00079 EA 2001 3 9 CA000511034 1 20000506 G 5210 DOOR CNDAIR CL600 CL6002B19 EA PAX NOT CLOSED W A UNSCHED LANDING W J INADEQUATE Q C WARNING INDICATION CL CLIMB 1 CA (CAN) PAX DOOR HANDLE MESSAGE APPEARED ON EICAS DURING CLIMB. THEY REPORTED THAT THE DOOR WAS NOT SHUT ALL THE WAY. 2 L 7 2 4F RT A21EA 2001031200406 20010312 00406 EA 2001 3 12 CA000511035 1 20000506 G 2760 PANEL CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE COCKPIT FAILED W A UNSCHED LANDING F FLT CONT AFFECTED AP APPROACH 1 CA (CAN) ON SHORT FINAL FLT SPOILER DEPLOYED UNCOMMANDED ABOUT 25 DEG UP ON THE RT WING AND APPROX 10 DEGREES UP ON THE LT WING. SPOILER PANEL, INBOARD PCU AND O/B PCU REPLACED. 2 L 7 2 4F 4 F RT A21EA E15NE 2001031200407 20010312 00407 EA 2001 3 12 CA000511036 1 20000506 G 4990 APU CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE APU BAY OVERSERVICED W B EMER. DESCENT B SMOKE/FUMES/ODORS/SPARKS DE DESCENT 1 CA 807435 (CAN) SMOKE TOILET MESSAGE APPEARED ON EICAS AFTER TRANSFERING PACKS TO APU BLEED AIR. APU FOUND OVERSERVICED BY APPRO X. 1/2 QT. 2 L 7 2 4F 4 F RT A21EA E15NE 2000062800200 20000628 00200 CE 2000 6 28 CA000511038 1 20000504 G 5753 052323113 FLAP TRACK CESSNA CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA TE FLAP CRACKED W O OTHER O OTHER CL CLIMB 1 CA L3234327A (CAN) FOLLOWING A SIMULATED FORCED APPROACH, THE INSTRUCTOR AND STUDENT HEARD A LOUD BANG AS THE FLAPS WERE RETRACTING. THE FLAPS CONTINUED TO RETRACT TO THE FULL UP POSITION AND THE FLIGHT CONTINUED BACK TO BASE AND LANDED UNEVENTFULLY.MA INTENANCE PERSONNEL FOUND THAT THE LEFT INBOARD FLAP TRACK (RIB ASSY) HAS CRACKED. 1 H 7 1 3O 3 O NT 3A12 E274 2000072400260 20000724 00260 SW 2000 7 24 CA000511040 1 20000506 G 5302 206032409001P BOLT BELL 206033004011 BELL 206 206L 1181522 SW TAIL BOOM CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA AOKP00649 (CAN) CRACKED TAILBOOM ATTACHMENT BOLT FITTING. 1 G 7 1 3U H2SW 2001031200408 20010312 00408 SW 2001 3 12 CA000511041 1 20000502 G 2710 KP16B BEARING SWRNGN SA227 SA227AC 8780603 SW ROTOL R321 R321482F8 GL AILERON ROUGH W O OTHER F FLT CONT AFFECTED CR CRUISE 1 CA DRG294783 (CAN) THE FLIGHT CREW REPORTED THAT THE AILERON MOVEMENT WAS ROUGH AND WAS MAKING A ROUGH SOUND. MAINTENANCE FOUND A ROU GH BEARING IN THE AILERON TORQUE TUBE HOUSING SUPPORT. THE BEARINGS WERE REPLACED WITH NEW. 2 L 7 2 4T RT A8SW 6 C P61GL 2000062800201 20000628 00201 2000 6 28 CA000511042 4 20000417 G 2562 E01 SWITCH CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA MCAULY 1C160 1C160DTM GL ELT CONTAMINATED W K NONE O OTHER IN INSP/MAINT 1 CA L3197827A 726767 (CAN) ELT FALSE ALARM - EVIDENCE OF MOISTURE ON REMOTE SWITCH PLUG END. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2000062800202 20000628 00202 SO 2000 6 28 CA000511043 1 20000418 G 7603 554546 CABLE PIPER PA44 PA44180 7104402 SO LYC O360 LO360E1A6 41514 EA PEDESTAL SEPARATED W O OTHER E VIBRATION/BUFFET TO TAKEOFF 1 CA L43472 (CAN) DURING TAKEOFF, THE LEFT ENGINE REMAINED AT MAXIMUM RPM WHEN CLIMB POWER WAS SELECTED FOR BOTH ENGINES. MAINTENAN CE FOUND THE LEFT THROTTLE CABLE BROKEN WITHIN THE PEDESTAL AREA AT THE POINT WHERE THE CABLE ENTERS THE HOUSING. CABLE REPLACED. 1 L 7 2 3O 3 O A19S0 E286 2000062800203 20000628 00203 EA 2000 6 28 CA000511044 2 20000418 G 8530 3116 STUD LYC LW15322 PIPER PA44 PA44180 7104402 SO LYC O360 LO360E1A6 41514 EA NR 3 CYLINDER BROKEN W C ABORTED TAKEOFF E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS TO TAKEOFF 1 CA 94000 20940 L32872T (CAN) INTAKE ROCKER STUD FOUND BROKEN ON #3 CYLINDER. CYLINDER SENT FOR EVALUATION WHERE IT WAS DETERMINED THAT STRESS TO THE THREADED PORTION OF THE STUD WAS THE CAUSE OF ITS FAILURE. 1 L 7 2 3O 3 O A19S0 E286 2000083000168 20000830 00168 CE 2000 8 30 CA000511045 1 20000427 G 5345 08119031 MOUNT BRACKET CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO MCAULY 3AF32C 3AF32C87 GL SUPPORT ASSY CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 59600 310R0927 235587R 779115 (CAN) DURING A 200-HOUR INSPECTION, LOOSENESS WAS FOUND AT THE CABIN STEP ATTACHMENT. THE STEP AND SUPPORT WERE REMOVED FOR RE-BUSHING. THE SUPPORT ASSEMBLY WAS INSPECTED AND FOUND CRACKED. THE CAUSE OF THE LOOSENESS IN THE STEP WAS CORR OSION AND WEAR IN THE STEP MOUNTING HOLES. A NEW SUPPORT ASSEMBLY WAS INSTALLED. 1 L 7 2 3O 3 O 3A10 E5CE 5 C P22EA 2001031200409 20010312 00409 NM 2001 3 12 CA000511046 1 20000503 G 2510 5110013033 SEAT BACK ISRAEL 1125 1125 NM ALIDSG TFE731 TFE7313AR WP CAPTAINS SEAT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 31710 P96208 (CAN) PILOTS SEAT BACK REST FOUND CRACKED. 2 L 7 2 4F 4 F RT A16NM E6WE 2000072400261 20000724 00261 2000 7 24 CA000516001 4 20000510 G 2562 BS2166 BATTERY NARCO ELT10 BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL ELT BATTERY LEAKING W K NONE O OTHER IN INSP/MAINT 1 CA C10317 CAE830913 (CAN) ELT WAS REMOVED FOR ANNUAL INSPECTION AND IT WAS NOTED THAT WHITE POWDER WAS ON OUTSIDE OF BATTERY AND ELT CASE. UPON INSPECTION AFTER BATTERY REMOVAL, A LEAK WAS DETECTED. BATTERY STILL HAD 5 MONTHS LEFT ON ITS LIFE. EXPIRATION, SEPT 2000. BATTERY WAS REPLACED AND ELT WAS TESTED SERVICEABLE. NO INTERNAL DAMAGE OCCURRED. OWNER DID NOT NOTICE LEA KAGE UNTIL ELT WAS REMOVED FROM BRACKET. ELT BATTERY LOT NR 1S 44181. MANUFACTURE DATE IS AUGUST 1998. 1 G 7 1 3U 3 U H2SW E4CE 2000062800204 20000628 00204 2000 6 28 CA000516002 4 20000505 G 2562 0010009 BATTERY NARCO ELT10 CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA MCAULY 1C160 1C160DTM GL ELT DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 71322 3877627A 82493 (CAN) LOOSE BATTERY CELLS IDENTIFIED. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2000062800205 20000628 00205 EA 2000 6 28 CA000516003 2 20000509 G 8550 62817 SCREEN CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA MCAULY 1C160 1C160DTM GL OIL SYSTEM DETERIORATED W K NONE O OTHER IN INSP/MAINT 1 CA L4429127A 732270 (CAN) DURING INSPECTION, THE OIL SCREEN WAS FOUND TO BE DETERIORATING AND BEGINNING TO FRAY IN ONE AREA. THE SUBMITTER SUGGESTS THAT THE SCREEN WAS DETERIORATING DUE TO OLD AGE AND REPEATED CLEANINGS. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2000062800206 20000628 00206 CE 2000 6 28 CA000516005 1 20000504 G 7120 05510171 MOUNT CESSNA 172 172L 2072432 CE LYC O320 O320E2D 41508 EA MCAULY 1C160 1C160DTM GL ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA L4429127A E18147 (CAN) DURING SCHEDULED MAINTENANCE, THE ENGINE MOUNT LOWER HORIZONTAL BRACE WAS FOUND CRACKED AT BOTH ENDS. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2000062800207 20000628 00207 CE 2000 6 28 CA000516006 1 20000403 G 5510 1156100181 SUPPORT FITTING BEECH 100 100BEECH 1152916 CE PWA PT6 PT6A28 EA TORQUE TUBE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 82080 50078 (CAN) ON 1000 HOUR INSPECTION, NDT FOUND CRACK IN TAPER PIN ATTACH HOLE. SUSPECT OVERTORQUING OF PIN. NEW TORQUE ASSY. REPLACED. 1 L 7 2 3T 4 T A14CE E4EA 2000062800208 20000628 00208 EU 2000 6 28 CA000516007 1 20000420 G 3260 9733033111 PROXIMITY SWITCH PILATS PC12 PC1245 EU MLG FAILED W O OTHER J WARNING INDICATION CR CRUISE 1 CA 10490 (CAN) THE CREW RECEIVED A CAWS WARNING LIGHT FOR AIR/GROUND (AIRGND). THE MAINTENANCE CREW DIAGNOSED A FAILED PROXIMITY SWITCH. 1 L 7 1 3T RT A78EU 2000062800209 20000628 00209 EU 2000 6 28 CA000516008 1 20000414 G 2752 951D10011 GEAR PILATS PC12 PC1245 EU FLAP ACTUATOR WORN W K NONE O OTHER IN INSP/MAINT 1 CA 25900 (CAN) DURING SCHEDULED INSPECTION, THE FLAP ACTUATOR WAS FOUND WORN BEYOND SERVICE LIMITS. 1 L 7 1 3T RT A78EU 2000072600060 20000726 00060 EU 2000 7 26 CA000516009 1 20000425 G 3010 9598901035 BOOT PILATS PC12 PC1245 EU L/H STAB UNBONDED W K NONE O OTHER IN INSP/MAINT 1 CA 28400 (CAN) DURING PREFLIGHT INSPECTION, THE PILOT NOTICED THE DE-ICE BOOT HAD BECOME UNGLUED ON THE TOP FOR A DISTANCE OF ABO UT TWO FEET. THE BOOT WAS REPLACED WITH A NEW UNIT . THE SUBMITTER STATES THAT THE OLD BOOT WAS EASILY REMOVED AND DID NOT APPEAR TO BE PROPERLY ADHERING TO THE STABILIZER SURFACE. 1 L 7 1 3T RT A78EU 2000072600061 20000726 00061 EU 2000 7 26 CA000516010 1 20000519 G 2752 951D10011 ACTUATOR PILATS PC12 PC1245 EU WORM GEAR WORN W K NONE O OTHER IN INSP/MAINT 1 CA 17800 (CAN) DURING SCHEDULED INSPECTION OF THE FLAP ACTUATORS, THREE OUT OF FOUR ACTUATORS WERE FOUND WORN BEYOND SERVICE LIMI TS. 1 L 7 1 3T RT A78EU 2000071800135 20000718 00135 GL 2000 7 18 CA000516012 2 20000410 G 7250 6878426 NOZZLE ALLSN BELL 206 206BELL 1181502 SW ALLSN 250C 250C20 03013 GL 1 BLADE PATH CIR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA CAT31780D CAT31780P (CAN) A GROUP OF 2ND STAGE NOZZLES ARE IN THE PROCESS OF RECALL. IT WAS FOUND THAT REPAIRS MADE TO SOME NOZZLES; WHICH WAS AN APPROVED REPAIR , HAVE FAILED TO REACH O/H AND ARE CRACKING WHERE THE FIRST STAGE BLADE PATH WAS JOINED TO THE 2 ND STAGE NOZZLE. TRANSPORT CAW CORRECTIVE ACTION GROUP IS ADRESSSING THIS ISSUE. 1 G 7 1 3U 3 U H2SW E4CE 2001031200411 20010312 00411 GL 2001 3 12 CA000516014 2 20000502 G 7250 689784 ADAPTER ALLSN 250C 250C20B 03013 GL OUTER SPLINE DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 323 (CAN) EXCESSIVE DAMAGE TO SPLINES OF ADAPTER AND INNER SPLINES OF THE COMPRESSOR TO TURBINE COUPLING SHAFT. IN SOME CASE A SPLINE TOOTH IS COMPLETELY SHEARED OFF. 3 U E4CE 2001031200412 20010312 00412 EA 2001 3 12 CA000516016 1 20000508 G 2910 2156401521 LINE CNDAIR CL215 CL2151A10 EA HYD SYSTEM CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) BETWEEN FS 52.00 AND LWS 60.8 WHERE LEFT FUEL TUBE ASSY AND HYD TUBE ASSY GO THROUGH THE WING ROOT. IT WAS FOUND THAT THE HYD PRESSURE TUBE WAS CHAFING AGAINST LT FUEL TUBE ASSY. 2 H 7 2 4R A14EA 2000072600062 20000726 00062 CE 2000 7 26 CA000516017 1 20000505 G 3233 99810057652 ACTUATOR BEECH 99 99 1154002 CE PWA PT6 PT6A20 52043 EA RT MLG INTERNAL SEIZED W O OTHER J WARNING INDICATION LD LANDING 1 CA 24134 (CAN) THE CREW ON A TRAINING FLIGHT NOTICED, AFTER A NUMBER OF TIMES CYCLING THE GEAR, THE GEAR HANDLE RED LIGHT REMAINI NG ON. AS THE AIRCRAFT LANDED, THE RIGHT LANDING GEAR COLLAPSED .MAINTENANCE FOUND THE RIGHT LANDING GEAR ACTUATOR SEI ZED IN THE PARTIALLY RETRACTED POSITION. THE ACTUATOR IS BEING SENT OUT FOR EVALUATION. 1 L 7 2 3T 3 T A14CE E4EA 2001032000002 20010320 00002 SW 2001 3 20 CA000516018 1 20000508 G 6320 269A54979 SHAFT HUGHES 269 269C1 8059504 SW MAIN ROTOR CRACKED W A UNSCHED LANDING E VIBRATION/BUFFET AP APPROACH 1 CA 1286 (CAN) FOLLOWING 1.8 HOUR FLIGHT AND AT BEGINNING OF APPROACH TO AIRFIELD, A BANG WAS HEARD AND A LOW POWER AUTOROTATION WAS CARRIED OUT. ROTORCRAFT WAS LEFT RUNNING FOR ENGINEER TO INSPECT. A VIBRATION WAS FELT THROUGHOUT THE CABIN (MOSTLY IN THE FLOOR) & LOWER PULLEY WAS VIBRATING. INSPECTION AFTER SHUT-DOWN REVEALED A VISUAL CRACK ON THE FORWARD PART OF S HAFT LOCATED UNDER THE BEARING (SHAFT IS STAINLESS). THE CRACK WAS 1.5 INCH LONGITUDINAL AND 2 ING AROUND THE SHAFT CIR CUMFERENCE. 1 G 7 1 3O O 4H12 2001011104172 20010111 04172 WP 2001 1 11 CA000516020 1 20000504 G 2821 66547775940 BOLT PUROLATOR 6815922 CVAC 580 580 WP ALLSN 501D 501D13 03004 GL ALLSN A6441 A6441* GL FILTER ASSY BROKEN W A UNSCHED LANDING K FLUID LOSS CR CRUISE 1 CA 6 501698 HC183 (CAN) CREW OBSERVED A REDUCTION OF HP, FF, TIT AND LOW PRESS FUEL LIGHT ON NR 1 ENGINE. ALSO NOTICED RAPID LOSS OF FUEL IN LEFT WING TANK. ENGINE SHUT DOWN AND FUEL TANK S/O CLOSED. LP FUEL BOWL FAILED DUE TO CENTER BOLT BROKEN AT END OF THREADS. BOLT REPLACED. 2 L 7 2 4T 4 T RT E282 6 C P898 2000072600063 20000726 00063 EA 2000 7 26 CA000516021 2 20000508 G 8520 7380685 PUSHROD CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA AT 1 BALL END DAMAGED W C ABORTED TAKEOFF R PARTIAL RPM/PWR LOSS TO TAKEOFF 1 CA 21960 RL1627815 (CAN) STEEL ENDS OF PUSH RODS DAMAGING ALUMINUM TUBES. LYCOMING SB 453 ADDRESSES ISSUE. LYCOMING HAS SINCE SWITCHED TO ALL STEEL PUSH RODS. 1 H 7 1 3O 3 O NT 3A19 E223 2000072600064 20000726 00064 CE 2000 7 26 CA000516022 1 20000508 G 3222 AN5 BOLT CESSNA 172 172RG 2072438 CE LYC O360 O360F1A6 41514 EA MCAULY 2D34C B2D34C220 GL NLG AXLE BOLT MISSING W O OTHER O OTHER LD LANDING 1 CA 36000 L2827936A 815095 (CAN) AFTER LANDING, THE PILOT EXPERIENCED DIFFICULTY STEERING THE AIRCRAFT. THE AIRCRAFT WAS STOPPED ON THE RUNWAY AND IT WAS NOTICED THAT THE NOSEWHEEL WAS SITTING CROOKED ON THE NOSE GEAR FORK. FURTHER INSPECTION REVEALED THAT THE NOSE W HEEL AXLE BOLTAND ONE AXLE FERRULE WERE MISSING FROM THE NOSE GEAR. THE SUBMITTER SUSPECTS THAT THE NUT MAY HAVE COME OF F THE BOLT OR THE BOLT MAY HAVE BROKEN. 1 H 7 1 3O 3 O 3A17 E286 5 C P7EA 2000072600070 20000726 00070 SO 2000 7 26 CA000516023 1 20000508 G 2120 8124402 TUBE PIPER PA31T PA31T 7103124 SO PWA PT6 PT6A28 EA FWD PRT OF TUBE DISCONNECTED W G B O2 MASK DEPLOYED EMER. DESCENT W INADEQUATE Q C CR CRUISE 1 CA 85000 PCE51623 (CAN) AIRCRAFT MADE AN IN-FLIGHT RAPID DECOMPRESSION. THE FORWARD PART OF THE FRESH AIR DISTRIBUTION TUBE WAS FOUND TO BE DISCONNECTED. THE CLAMPS WERE REMOVED, INSPECTED, REINSTALLED, AND LOC WIRED TO PREVENT SLIPPAGE. THE SUBMITTER S TATES THAT ALTHOUGH LOCKWIRING THE CLAMPS IS NOT IN THE MAINTENANCE MANUAL, LOCKWIRING GIVES BETTER SECURITY. 1 L 7 2 3T 4 T A8EA E4EA 2000072600071 20000726 00071 SO 2000 7 26 CA000516024 1 20000508 G 3243 492152 VALVE PIPER PA42 PA42 7104202 SO PWA PT6 PT6A41 52043 EA PARKING BRAKE FAILED W A UNSCHED LANDING O OTHER CR CRUISE 1 CA 48090 PCE80156 (CAN) PILOTS CHECKED FOR BRAKE PRESSURE DURING CRUISE FLIGHT AT 33,000 FEET. BRAKES WERE VERY SOFT. PARKING BRAKE VALV E FOUND TO HAVE LEAKING O-RINGS. SEALS REPLACED. 1 L 7 2 4T 4 T A23SO E4EA 2000072600072 20000726 00072 EU 2000 7 26 CA000516026 1 20000505 G 3250 Z4242170001 SPRING MORAVN L24242370000 ZLIN 242 Z242L 9970204 EU AFT END BROKEN W K NONE O D OTHER INFLIGHT SEPARATION IN INSP/MAINT 1 CA 36530 (CAN) WHILE HAND TOWING THE AIRCRAFT, A NOISE WAS HEARD WHILE TURNING TO THE RIGHT. INVESTIGATION REVEALED THAT THE LEF T STEERING SPRING HAD BROKEN. THE SPRING WAS REPLACED USING THE MINIMUM DISTANCE SETTINGS ON THE LT AND RT STEERING SPR INGS. SUBMITTER STATED TURNING THE NOSE GEAR SHOULD BE DONE WHILE MOVING AND MONITORING TURN LIMITS DURING HAND TOWING WOULD HELP REDUCE SIMILAR OCCURENCES. 1 L 7 1 3O 0 A76EU 2000072600078 20000726 00078 EU 2000 7 26 CA000516027 1 20000510 G 3010 9598901014 TIMER BFGOODRICH PILATS PC12 PC1245 EU INTERNAL FAILED W H DEACTIVATE SYST/CIRCUITS J WARNING INDICATION AP APPROACH 1 CA 40900 U0058 (CAN) WHILE ON APPROACH, THE PILOT SELECTED DE-ICE ON. AFTER 8 SECONDS, A DE-ICE FAIL WARNING WAS OBSERVED. SELECTING THE DE-ICE OFF DID NOT CANCEL THE WARNING LIGHT SO THE PILOT SECURED THE CIRCUIT BREAKER. MAINTENANCE LATER DETERMINED THAT THE DE-ICE TIMER HAD FAILED AND HAD STUCK IN THE HORIZONTAL STABILIZER POSITION. 1 L 7 1 3T RT A78EU 2000083000169 20000830 00169 EA 2000 8 30 CA000516031 3 20000426 G 6111 1774017060 PROPELLER SNSNCH PIPER PA22 PA22150 7102210 SO LYC O320 O320A2B 41508 EA SNSNCH 74DM M74DM EA FACE AND CAMBER CORRODED W O OTHER O OTHER IN INSP/MAINT 1 CA 31700 L400327 K30334 (CAN) NO TEXT 1 H 7 1 3O 3 O 1A6 E274 5 N P88614 2001031200415 20010312 00415 NE 2001 3 12 CA000516033 2 20000411 G 7270 FAN CNDAIR CL600 CL6001A11 1900302 EA LYC ALF502 ALF502L 41580 NE ENGINE FAILED W A UNSCHED LANDING Y ENGINE STOPPAGE CL CLIMB 1 CA 3068 (CAN) FOLLOWING A/C ROTATIONAT 100AGL THE NUMBER 2 ENGINE AUTOMATICALLY SHUTDOWN WITH AN OVERSPEED INDICATION. N1 FAN WO ULD NOT ROTATE. ENGINE REPLACED. 2 L 7 2 4F 4 F RT A21EA E6NE 2001031200416 20010312 00416 NM 2001 3 12 CA000516034 1 20000501 G 3246 2607047 WHEEL BOEING 737 737242C 1384478 NM PWA JT8 JT8D9A 52048 NE MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 648850 (CAN) WHILE TAXING MAINT NOTED NR 2 MAIN WHEEL ASSY WAS FLAT. FURTHER INVESTIGATION REVEALED 1/3 OF THE OUTBOARD WHEEL H ALF HAD BROKEN OFF AND THE TIRE WAS CUT AT THE WALL EDGE. DAMAGE WAS FOUND ON THE WING BODY FAIRING, LT IB FORE FLAP AND THE LT UPPER WING TRAILING EDGE. ALL EXCEDED SRM LIMITS. NR 2 MAIN WHEEL REPLACED AND A/C FERRIED FOR MAINTENANCE. 2 L 7 2 4F 4 F A16WE E2EA 2000072400263 20000724 00263 NM 2000 7 24 CA000516035 1 20000313 G 6322 A1874 CONE ROBSIN B1741 ROBSIN R22 R22BETA NM LYC O320 O320B2C 41508 EA CIRC OF CONE CHAFED W O OTHER O OTHER IN INSP/MAINT 1 CA L1581339A (CAN) THE LENGTH OF THE SCREW THAT ATTACHES INSPECTION PLATE P/N D229-4 TO SCROLL SET P/N R7156 WAS EXTENDED THROUGH SCR OLL SET TO A DEPTH THAT IT CONTACTED CONE P/N A187-4 CAUSING IT TO CHAFE AS THE FAN WHEEL ROTATED. UNABLE TO DETERMINE AT THIS TIME THE P/N OF THE SCREW THAT WAS INSTALLED. THE CORRECT P/N FROM ROBINSON R2 ILLUSTRATED PARTS CATALOG IS MS3 5206-227. IT IS SUSPECTED THAT AN OVERLY LONG SCREW WAS INSTALLED DURING THE ROTORCRAFT''S OVERHAUL. 1 G 7 1 3O 3 O H10WE E274 2000082200032 20000822 00032 SW 2000 8 22 CA000516036 1 20000509 G 5101 STRUCTURE MOONEY M20 M20C 5870208 SW LYC O360 O360A1D 41514 EA AIRFRAME CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 28440 RL954336A (CAN) SEVERE CORROSION FOUND DURING ANNUAL INSPECTION. EXFOLIATION CORROSION FOUND AT LT FLAP 3 AND 4 HINGE BRACKET. IN TERGRANULAR CORROSION FOUND AT LT MAIN GEAR LINK ATTACHMENT TO MAIN WING SPAR BRACKET. AT THE LT AND RT FUSELAGE TUBING ATTACHMENT TO MAIN WING LOWER SPAR, THE STEEL TUBING IS RUSTED RIGHT THROUGH. ALSO, GENERAL SURFACE CORROSION WAS DIS COVERED IN THE CABIN FLOOR AREA. 1 L 7 1 3O 3 O 2A3 E286 2000081000023 20000810 00023 NE 2000 8 10 CA000518001 2 20000503 G 8530 CONNECTING ROD PWA GRUMAV G21 G21A 3951204 SO PWA R985 R985AN14B 52008 NE CONNECTING ROD BROKEN W A E UNSCHED LANDING ENGINE SHUTDOWN B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA 12430 225627 (CAN) CONNECTING RODS FOR NR 8 AND NR 9 CYLINDERS BROKEN. 1 H 7 2 3R 3 R TC654 5E1 2000062800211 20000628 00211 SW 2000 6 28 CA000518007 1 20000216 G 6320 212040001059 PLANETARY GEAR BELL 212040001059 BELL 212 212 1181420 SW PWA PT6T PT6T3 52045 EA TRANSMISSION CHIPPED W O OTHER J WARNING INDICATION TO TAKEOFF 1 CA 56030 ABW40017 CPPS61014 (CAN) METAL FOUND ON THE PLANETARY CHIP DETECTOR (.040 INCH - .060 INCH). TRANSMISSION WAS REMOVED SHORT OFF AND SENT F OR REPAIR. 1 G 7 1 4U 4 U H4SW E22EA 2000062800213 20000628 00213 NE 2000 6 28 CA000518009 2 20000301 G 7530 0177555170 TACHOMETER TMECA 0177555170 SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1B 6OO30 NE INTERNAL UNSERVICEABLE W O OTHER O OTHER CL CLIMB 1 CA 1338B 290 (CAN) ENGINE BLEED VALVE WHICH IS CONTROLLED BY THE TACHOMETER BOX INADVERTENTLY OPENED TWICE AT 98 PERCENT NG. OPERATO R WAS NOT ABLE TO DUPLICATE. POSSIBLE CAUSE WAS A SHORT IN THE TACHOMETER BOX. 1 G 7 1 3U 3 U H9EU E19EU 2000072600245 20000726 00245 EU 2000 7 26 CA000518010 1 20000301 G 7712 9580113720 TRANSMITTER SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1B 6OO30 NE TORQUE INDECATOR INCORRECT W O OTHER O OTHER CL CLIMB 1 CA 30000 1451 451 (CAN) TORQUE TRANSMITTER WAS INSTALLED THE DAY BEFORE AND SET TO PROPER PRESSURE. CHECKED LATER AND FOUND TO BE OFF BY 3% PERCENT. UNIT RE-ADJUSTED. 1 G 7 1 3U 3 U H9EU E19EU 2000062800214 20000628 00214 EU 2000 6 28 CA000518011 1 20000229 G 7921 RH2125 COOLER RH2125 SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1B 6OO30 NE ENG OIL COOLER LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 457 290 (CAN) EXTERNAL SEAM ON THE OIL COOLER LEAKING PROGRESSIVELY WORSE, UNIT REPLACED. 1 G 7 1 3U 3 U H9EU E19EU 2000062800215 20000628 00215 EU 2000 6 28 CA000518012 1 20000302 G 2140 350A72100509 HEATER 350A72100509 SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1B 6OO30 NE UNION FITTING CORRODED W O OTHER O OTHER IN INSP/MAINT 1 CA 834 (CAN) LINE FOUND TO BE CORRODED AND CRACKED BY THE UNION. 1 G 7 1 3U 3 U H9EU E19EU 2000072600161 20000726 00161 EU 2000 7 26 CA000518013 1 20000411 G 6720 1053178201 PITCH LINK BOLKMS 105 BO105S 5626006 EU ALLSN 250C 250C20B 03013 GL T/R GEAR BOX UNSERVICEABLE W O OTHER O OTHER IN INSP/MAINT 1 CA 512519 CAE836046 (CAN) DURING A TAILROTOR (T/R) GEARBOX CHANGE,THE T/R PITCH CHANGE BELLCRANK WAS FOUND DAMAGED. THE DAMAGE WAS CAUSED F ROM THE SAFETY WIRE CHAFING NEAR THE PIVOT BEARING. SAFETY WIRE IS FASTENED TO PIVOT BEARING STUD FROM THE T/R GEARBOX. 1 G 7 2 3U 3 U H3EU E4CE 2000072600246 20000726 00246 NE 2000 7 26 CA000518014 2 20000329 G 7532 9550158260 BLEED VALVE SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1B 6OO30 NE ENGINE STUCK W O OTHER J WARNING INDICATION LD LANDING 1 CA 13780 347 (CAN) UNIT STICKS CLOSED INTERMITTENTLY. 1 G 7 1 3U 3 U H9EU E19EU 2000081000024 20000810 00024 CE 2000 8 10 CA000518015 1 20000517 G 3260 V3100 SWITCH BEECH 100 A100 1152915 CE PWA PT6 PT6A28 EA WIRE CONNECTION LOOSE W A UNSCHED LANDING J S WARNING INDICATION AFFECT SYSTEMS CL CLIMB 1 CA PCE40975 (CAN) DURING CLIMB, THE GEAR WAS SELECTED UP AND THE GEAR DID NOT RETRACT. THE SELECTION WAS ATTEMPTED SEVERAL TIMES WIT H THE GEAR RETRACTING ON THE LAST SELECTION. MAINTENANCE FOUND A LOOSE WIRE ON THE EMERGENCY EXTENSION MICROSWITCH LOCA TED BY THE GEAR TRANSMISSION. THE CONNECTION WAS RESECURED. 1 L 7 2 3T 4 T A14CE E4EA 2000083000170 20000830 00170 CE 2000 8 30 CA000518016 1 20000511 G 5510 04320049 BRACKET CESSNA 043200159 CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA RH UP NUTPLATE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 80640 L1942015 (CAN) DURING INSPECTION FOR AD 80-11-04, THE STEEL BRACKET THAT THE SUBJECT NUTPLATES ARE ATTACHED TO WAS FOUND TO BE CR ACKED. THE CRACK COMPLETELY ENCIRCLED THE RIGHT UPPER NUTPLATE. 1 H 7 1 3O 3 O NT 3A19 E223 2001031200420 20010312 00420 CE 2001 3 12 CA000518017 1 20000516 G 3297 WIRE LEAR 35 35A 5170602 CE GARRTT TFE731 TFE7312 01518 WP LT MLG CUT W A UNSCHED LANDING N FALSE WARNING AP APPROACH 1 CA (CAN) LT MLG HAD NO LIGHT INDICATION. EMERG GEAR USED. BROKEN WIRE AT CR73 LT EQUIPMENT TRAY. 2 L 7 2 4F 4 F A10CE E6WE 2000081000025 20000810 00025 EA 2000 8 10 CA000519001 1 20000414 G 2710 C2WA159AWD BRACKET DHAV C2WA155A DHAV DHC2 DHC2* 2800108 EA WSK PZL PZL3S 67204 EU WSK US132 US132000A NE REAR VERT TUBE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 9502022CS AO27038 (CAN) WHILE CONDUCTING CF-61-12, AILERON MASS BALANCE WT INSPECTION. A CRACK WAS FOUND IN SUPPORT BRACKET. 1 H 7 1 3R 3 R A806 E18EU 5 C P4NE 2001031200422 20010312 00422 2001 3 12 CA000519004 4 20000505 G 3417 700700975 COMPUTER DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE AIR DATA FAILED W O OTHER O OTHER TX TAXI/GRND HDL 1 CA 57280 52500 120164 910442 (CAN) NR 2 ADC FAILED DURING TAXI.MULTIPLE INSTRUMENTS FAILED. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001031200423 20010312 00423 NE 2001 3 12 CA000519005 2 20000515 G 7200 230371302 BEARING LYC ALF502R5 BAG BAE146 BAE146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE NR 3 FAILED W C ABORTED TAKEOFF B J SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION TO TAKEOFF 1 CA LF05461A LF05461A (CAN) NR 3 ENGINE BEARING SEAL FAILED. 2 H 7 4 4F 4 F RT A49EU E6NE 2000072600247 20000726 00247 EU 2000 7 26 CA000519006 1 20000502 G 7500 1462502034 LINE SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1B 6OO30 NE BLEED AIR BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 69280 841 (CAN) WHEN STARTING, PILOT NOTICED HE HAD TO MOVE POWER LEVER TO ALMOST HALF THROTTLE TO GET ENGINE STARTED. IN-FLIGHT, LACK OF POWER WAS NOT EVIDENT. UPON LANDING, IT WAS DISCOVERED THE BLEED AIR LINE HAD BROKEN COMPLETELY OFF NEAR THE 9 0 DEGREE FITTING WHERE THE LINE WENT INTO THE COMPRESSOR SECTION OF ENGINE. 1 G 7 1 3U 3 U H9EU E19EU 2001031200424 20010312 00424 EU 2001 3 12 CA000519007 1 20000404 G 5302 ATTACH FITTING SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1B 6OO30 NE FUSE TO TAILBOOM CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 9601 303 (CAN) CRACK FOUND ON THE FUSELAGE TO TAILBOOM ATTACHMENT FLANGE. CRACK LOCATED (LOOKING FORWARD) AT 2:30 POSITION ON RI GHT SIDE. CRACK LENGTH WAS APROXIMATELY 3.5 CM LONG AND ABOUT 2 MM FROM EDGE. THE TORQUE ON FUS/TAILBOOM ATTACH BOLTS WERE UNKNOWN AT THE TIME OF TAILBOOM REMOVAL (RE: CF-93-12R1). 1 G 7 1 3U 3 U H9EU E19EU 2000083000171 20000830 00171 CE 2000 8 30 CA000519008 1 20000515 G 2430 S159660 CIRCUIT BREAKER MECHPRODUCTS MP1601 CESSNA 172 172L 2072432 CE LYC O320 O320E2D 41508 EA INTERNAL BURNED W D RETURN TO BLOCK B H SMOKE/FUMES/ODORS/SPARKS ELECT. POWER LOSS-50 PC TX TAXI/GRND HDL 1 CA 10973 L4570027A (CAN) VOLTAGE REGULATOR A WIRE SHORTED TO GROUND. THE 60 AMP ALTERNATOR CIRCUIT BREAKER SMOKED BUT DID NOT TRIP. THE M ANUFACTURING DATE ON THE CIRCUIT BREAKER WAS FEB, 1972. THE CIRCUIT BREAKER WAS REPLACED WITH ONE SUPPLIED IN A CESSNA S ERVICE KIT. INTERNAL EXAMINATION SHOWED HEAVY CONTACT MELTING WHILE STILL EXHIBITING CONTINUITY. 1 H 7 1 3O 3 O NT 3A12 E274 2000083000172 20000830 00172 CE 2000 8 30 CA000519009 1 20000523 G 2821 07560052 STRINGER CESSNA 07560051 CESSNA 182 182P 2075816 CE CONT O470 O470R 17026 SO MCAULY 2A34C 2A34C203 GL TUBE AT FUEL INL MISINSTALLED W O OTHER W INADEQUATE Q C IN INSP/MAINT 1 CA 37980 22292473R 737870 (CAN) AIRCRAFT FUEL STRAINER INSPECTED IAW AD 2000-06-01 EVEN THOUGH THE TECHNICAL RECORDS DID NOT INDICATE THE FUEL STR AINER TOP ASSY HAD BEEN CHANGED DURING THE SPECIFIED TIME PERIOD. THE FUEL STRAINER TUBE WAS FOUND TO BE LONGER THAN TH E SPECIFIED LENGTH, AND WITH A LIGHT PULL THE INLET TUBE WAS PULLED FREE OF THE TOP ASSEMBLY. THE SUBMITTER STATED THAT THE TUBE DID NOT LOOK LIKE AN ORIGINAL PART AND FEELS THAT IT HAD BEEN REPLACED PREVIOUSLY WITH AN UNAPPROVED OR HOME M ADE PART. THE SUBMITTER ALSO CAUTIONS AGAINST REINSTALLING THE TUBE IN THE TOP ASSY BECAUSE INSERTING THE TUBE TOO FAR C OULD RESTRICT OR BLOCK OFF THE FLOW OF FUEL INTO THE FUEL STRAINER. 1 H 7 1 3O 3 O NT TA13 E273 5 C P3EA 2000081000026 20000810 00026 CE 2000 8 10 CA000519010 1 20000523 G 5553 2070702 HINGE PIPER 20730 PIPER PA24 PA24180 7102402 CE LYC O360 O360A1D 41514 EA UP HNG VERT FIN CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 31270 20730 L369136 (CAN) UPON STRIPING OF THE VERTICAL STABILIZER, A CRACK WAS NOTED IN THE UPPER HINGE. THIS AIRCRAFT HAS THE RUDDER BALAN CE WEIGHT INSTALLATION. PIPER KIT NR 760705 INSTALLED MARCH 15, 1973. THIS AIRCRAFT WAS VANDALIZED BUT NO VISIBLE DAMA GE TO CONTROL WAS NOTED. THE CRACK MAY HAVE BEEN A RESULT OF PRE-RUDDER BALANCE FLUTTER OR AN ORIGINAL INSERTION OF THE BEARING, NO INDICATION OF OF NEW BEARING INSTALLED. HINGE REPLACED. 1 L 7 1 3O 3 O NT 1A15 E286 2000081000027 20000810 00027 SO 2000 8 10 CA000519012 1 20000429 G 5312 4475800 BULKHEAD PIPER PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA LWR ATTACH FLANG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 93640 318052048 L236368A (CAN) THE LEFT AND RIGHT FUSELAGE MOUNTED FORWARD WING SUPPORT BULKHEADS WERE INSPECTED AND FOUND TO BE CRACKED ON THEIR LOWER MOUNTING FLANGES. (P/NS 44758-00 AND 44758-01). 1 L 7 2 3O 3 O A20SO E14EA 2000081000028 20000810 00028 SO 2000 8 10 CA000519013 1 20000429 G 5312 4475800 BULKHEAD PIPER PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA LWR ATTACH FLANG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 87070 317752096 L57468A (CAN) THE LEFT AND RIGHT MOUNTED FWD WING SUPPORT BULKHEADS WERE INSPECTED AND FOUND TO BE CRACKED ON THEIR LOWER MOUNTI NG FLANGES. (P/NS 44758-00 L/H & 44758-01 R/H) 1 L 7 2 3O 3 O A20SO E14EA 2001031200425 20010312 00425 EA 2001 3 12 CA000519015 2 20000510 G 7321 324475315 SHAFT PWA PT6A50 DHAV DHC7 DHC7103 2802710 EA PWA PT6 PT6A50 52043 EA HAMSTD 24PF 24PF305 GL FUEL CONTROL SHEARED W E ENGINE SHUTDOWN M OVER TEMP CR CRUISE 1 CA 2505 86194 (CAN) NG AND ITT CLIMED BEYOND MANUFACTURES LIMITS. FCU FOUND TO HAVE SHEARED SHAFT. 2 H 7 4 4T 4 T A20EA E4EA 6 C P1NE 2001031200426 20010312 00426 EA 2001 3 12 CA000519016 1 20000515 G 2742 6009230165 ACTUATOR CNDAIR CL600 CL6002A12 1900304 EA GE CF34 CF341A NE PITCH TRIM FAILED W O OTHER F J FLT CONT AFFECTED WARNING INDICATION TX TAXI/GRND HDL 1 CA 11200 350146 (CAN) WHILE TAXING TO RAMP PILOT MOVED STAB TRIM TO NOSE DOWN POSITION. CHANNEL 1 NOSE DOWN FAIL LIGHT CAME ON AND ACT W OULD NOT MOVE. MAINT CHANGED PITCH TRIM ACTUATOR AND RETURNED A/C TO SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001031200428 20010312 00428 NM 2001 3 12 CA000519018 1 20000503 G 2612 P34797 CONNECTOR GTCP85129 BOEING 737 7372E1 138448F NM PWA JT8 JT8D9A 52048 NE APU FIRE LOOP DAMAGED W A UNSCHED LANDING N FALSE WARNING CR CRUISE 1 CA P34797 674284 (CAN) AT CRUISE APU FIRE HANDLE ILLUMINATED AND AUDIBLE FIRE WARNING BELL. FIRE WARNING DRILL AND FIRE WARNING HANDLE W AS PULLED AND FIRE BOTTLE DISCHARGED.ATC ADVISED AND A/C LANDED SAFELY. APU AREA CLEANED AND INSPECTED. APU DMIDAND FLOW N FOR REPAIRS. APU FIRE BOTLE AND SQUIB REPLACED. FIRE LOOP PLUG FOUND FAULTY. PLUG REPAIRED AND APU GROUND RUN SERVICEA BLE. 2 L 7 2 4F 4 F A16WE E2EA 2001031200429 20010312 00429 EA 2001 3 12 CA000519019 1 20000518 G 2710 BEARING CNDAIR CL600 CL6002B19 EA AILERON STUCK W O OTHER F FLT CONT AFFECTED AP APPROACH 1 CA 37990 (CAN) ON APPROACH, PILOT REPORTED THAT EXCESSIVE FORCE WAS REQUIRED TO MOVE AILERONS WITH AN INTERMITTENT LOSS OF ARTIFI CIAL FEEL. INSPECTION REVEALED THE LEFT REAR QUADRANTS BEARING WAS STIFF. BOTH QUADRANTS REPLACED. 2 L 7 2 4F RT A21EA 2001031200430 20010312 00430 EA 2001 3 12 CA000519020 1 20000518 G 2740 7060883963 CONTROL UNIT CNDAIR CL600 CL6002B19 EA E/E BAY MALFUNCTIONED W B EMER. DESCENT F FLT CONT AFFECTED CR CRUISE 1 CA (CAN) WHILE INTERCEPTING ILS, STAB TRIM FAIL CAUTION MESSAGE APPEARED. THE A/C WAS STABLIZED. A SYSTEM TEST WAS CARRIED OUT, TRIM DID NOT RE-ENGAGE. STAB TRIM WAS IN NOSE DOWN ATTITUDE. WHILE ON APPROACH, EXCESSIVE FORCE WAS REQUIRED TO MAI NTAIN THE A/C FROM PITCHING DOWN. EMERG WAS DECLARED. LANDING NORMAL AT FLAPS 20. HSTCU AND HSTA REPLACED. 2 L 7 2 4F RT A21EA 2001031200431 20010312 00431 EA 2001 3 12 CA000519021 1 20000518 G 2420 M832481910 PACKING CNDAIR CL600 CL6002B19 EA NR 2 IDG CUT W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA (CAN) DURING TAKE OFF ROLL, IDG NR 2 CAUTION MESSAGE POSTED AND WENT AWAY, BUT SEVERAL OTHER CAUTIONS POSTED INCLUDING WINDSHIELD AND WINDOW HEAT. MAINT FOUND OIL LEAK FROM NR 2 IDG OUTPORT CAUSED BY A CUT O-RING. 2 L 7 2 4F RT A21EA 2001031200433 20010312 00433 NM 2001 3 12 CA000530002 1 20000517 G 3097 SFA13M1R0A WIRE DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE PROPELLER HEAT FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 21790 7691 120832 860404 (CAN) LT PHASE B PROP HEAT CB POPPING. BLADE HEAT WIRING BURNED. BLADE REPLACED. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2000072700239 20000727 00239 SW 2000 7 27 CA000530010 1 20000116 G 2810 2120606003E FUEL LINE BELL 212 212 1181420 SW PWA PT6T PT6T3 52045 EA FUEL CELL DELAMINATED W K NONE O OTHER IN INSP/MAINT 1 CA 608 CPPS61552 (CAN) WHEN REPLACING FLEXIBLE LINES INSIDE THE FUEL CELL, IT WAS NOTED THAT THE BOTTOM OF THE FUEL CELL WAS SPONGY. IT WAS THEN DESCOVERED THAT LAYERS OF RUBBER WERE BREAKING DOWN AND SEPARATING. 1 G 7 1 4U 4 U H4SW E22EA 2000072700240 20000727 00240 EU 2000 7 27 CA000530011 1 20000515 G 6720 704A33651003 BEARING 350A332004 SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1B 6OO30 NE TAIL ROTOR ROUGH W K NONE O OTHER IN INSP/MAINT 1 CA 10040 M1652 382 (CAN)WHILE PERFORMING AN INSPECTION OF THE TAIL ROTOR PITCH CHANGE SPIDER BEARINGS FOR ROUGHNESS, DRAG AND TORQUE, (AW D 1999-085-076(A)R2). IT WAS DISCOVERED THAT BEARING WAS VERY ROUGH AND RATCHETY. THE AWD IS A REPETITIVE AWD FOR E VERY 50 HOURS. MANUFACTURES P/N 60102RS1HT33CA. 1 G 7 1 3U 3 U NC H9EU E19EU 2000083000173 20000830 00173 EA 2000 8 30 CA000530012 1 20000515 G 6120 KX5116 BETA SWITCH HARTZL DHAV DHC6 DHC6200 EA PWA PT6 PT6A20 52043 EA HARTZL HCB3T HCB3TN3 GL BETA SWITCH FAILED W K NONE N FALSE WARNING IN INSP/MAINT 1 CA PCE20768 BUA20758 (CAN) NR 2 ENGINE BETA BACK UNSERVICEABLE, PROPELLER REVERSES WITH NO BLUE LIGHT IN TEST MODE. 1 H 7 2 3T 3 T A9EA E4EA 6 C P15EA 2000083000174 20000830 00174 EA 2000 8 30 CA000530013 1 20000602 G 2914 3115818 PUMP DHAV DHC6 DHC6100 EA PWA PT6 PT6A20 52043 EA HYD HAND PUMP JAMMED W K NONE O OTHER IN INSP/MAINT 1 CA 2801 PCE22476 (CAN) HYDRAULIC HAND PUMP JAMMED. 1 H 7 2 3T 3 T A9EA E4EA 2000072800034 20000728 00034 2000 7 28 CA000530014 4 20000530 G 3414 INDICATOR SKRSKY S76 S76 8143010 NE AIRSPEED INDICAT FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) S76 REQUIRES A NON-STANDARD PITOT PRESSURE TO ACHIEVE CALIBRATION OF THE AIRSPEED INDICATOR. SUBJECT INDICATOR WA S FOUND TO BE IN PERFECT CALIBRATION WITH STANDARD PRESSURE APPLIED. WITH THE RECOMMENDED PRESSURE APPLIED, THE AIRSPEE D ERRORS WERE WELL IN EXCESS OF THE ALLOWABLE TOLERANCE. 1 G 7 2 3U H1NE 2000072800035 20000728 00035 NE 2000 7 28 CA000530015 2 20000521 G 7314 P94B12208 PUMP ZENITH SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1B 6OO30 NE ENGINE READS LOW W O OTHER O OTHER IN INSP/MAINT 1 CA 32000 23455 4510 (CAN) PRIOR TO STARTING AIRCRAFT ENGINE, THE FUEL PRESSURE GAUGE WAS OBSERVED TO BE INDICATING ZERO PRESSURE WITH PUMP S WITCHED ON. WHEN LISTENED TO, THE PUMP SEEMED TO BE WORKING, BUT OBVIOUSLY THE ELECTRIC MOTOR WAS NOT ROTATING THE IMPE LLER, AS PROVEN BY DISCONNECTING AN INLINE FUEL LINE AND OBTAINING NO FUEL FLOW. TSO ON THE PUMP HAS ONLY 32.1 HOURS, T HUS EITHER A POOR OVERHAUL OR A FAULTY INTERNAL PART IS SUSPECT. THE PUMP WAS REPLACED WITH A NEWLY OVERHAULED UNIT AND THE AIRCRAFT WAS RETURNED TO SERVICE. 1 G 7 1 3U 3 U NC H9EU E19EU 2000072800036 20000728 00036 NE 2000 7 28 CA000530016 2 20000510 G 7314 O94B12209 PUMP ZENITH SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1B 6OO30 NE ENGINE READS LOW W K NONE J WARNING INDICATION CR CRUISE 1 CA 89600 20617 4510 (CAN) DURING FLIGHT, THE PILOT NOTICED THE FUEL PRESSURE INDICATING ZERO. BEING CLOSE TO THE DESTINATION, THE SHORT FLI GHT WAS COMPLETED WITHOUT INCIDENT. WITH THE ENGINE SHUT DOWN, NOTICED THE PUMP OPERATION SOUNDED CORRECT WITH THE POWE R APPLIED, BUT WAS FOUND TO BE PRODUCING NO PRESSURE AND WAS REMOVED. THE IMPELLER TO MOTOR DRIVE CONNECTION SEEMS TO H AVE FAILED. A REPLACEMENT PUMP WAS INSTALLED AND THE ROTORCRAFT RETURNED TO SERVICE. 1 G 7 1 3U 3 U NC H9EU E19EU 2000080300043 20000803 00043 WP 2000 8 3 CA000530017 1 20000518 G 6310 269A59993 BOOT HUGHES 269 269C 4470504 WP LYC O360 HIO360D1A 41514 EA FAN HOUSING TORN W O OTHER O OTHER IN INSP/MAINT 1 CA S0714 L2660251A (CAN)WHILE PERFORMING A POST-FLIGHT INSPECTION, THE PILOT NOTED GREASE ON THE FAN HOUSING (SCROLL ASSY). INSPECTION SHO WED A TEAR ON BOOT 269A-5473 INSTALLED ON ADAPTER 269A5411. DRIVESHAFT GREASE HAS LEAKED RADIALLY FROM BOOT. BOOT STIL L CONTAINED SUFFICIENT GREASE TO LUBRICATE DRIVESHAFT. 1 G 7 1 3O 3 O 4H12 1E10 2000100300263 20001003 00263 NE 2000 10 3 CA000530018 2 20000522 G 7314 AN4100 PUMP PWA DHAV DHC2 DHC2MK1 2800102 EA PWA R985 R985AN14B 52008 NE SPLINE DRIVESHAF FAILED W E C ENGINE SHUTDOWN ABORTED TAKEOFF J R WARNING INDICATION PARTIAL RPM/PWR LOSS TO TAKEOFF 1 CA 77600 415530 (CAN) LOW FUEL FLOW PRESSURE WARNING LIGHT AND INDICATION. FUEL PUMP REPLACED DUE TO DE-COUPLED SPLINE DRIVESHAFT. 1 H 7 1 3R 3 R A806 5E1 2001032900016 20010329 00016 GL 2001 3 29 CA000530019 2 20000510 G 7321 321881 ROD BENDIX NPNZ HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL FCU STRIPPED W O OTHER E X J VIBRATION/BUFFET ENGINE FLAMEOUT WARNING INDICATION LD LANDING 1 CA 2284 321881 (CAN) THE THREADS BENEATH THE INNER POSITIONING NUT ON THE INTERCONNECT ROD WHICH LINKS THE CUT OF LEVER (QUADRANT POINT ER) TO THE MAIN CONTROL SHAFT HAD FAILED. THIS ALLOWED THE FCU CUTOFF LEVER TO MOVE INTO CUTOFF INITIATING AN UNCOMMANDE D ENGINE SHUTDOWN. 1 G 7 1 3U 3 U H3WE E4CE 2000083000175 20000830 00175 CE 2000 8 30 CA000530021 1 20000503 G 2520 551900922 TUBE CESSNA 551901516 CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE SEAT BASE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 50790 PCE70400 (CAN) DURING DAILY INSPECTION, THE RIGHT AFT SEAT WAS FOUND IN THE RECLINED POSITION. PUSHING THE RETRACT BUTTON DID N OT CAUSE THE SEAT BACK TO RETURN TO THE UPRIGHT POSITION. MAINTENANCE PERSONNEL FOUND THE UPPER SEAT BASE TUBE CRACKED ADJACENT TO THE SEAT BACK PICKUPS. 1 L 7 2 4F 4 F A22CE E1NE 2000081700032 20000817 00032 CE 2000 8 17 CA000530022 1 20000402 G 2121 BRUSH HOLDER ELECTROMECH 903840311 BEECH 90 C90A 1152911 CE PWA PT6 PT6A21 52043 EA NOSE CASE SHORTED W D RETURN TO BLOCK B B SMOKE/FUMES/ODORS/SPARKS SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 CA 38300 1544 PCE25323 (CAN) THE AIRCRAFT HAD BEEN RUNNING FOR 2-3 MINUTES WHEN THE CREW COULD SMELL AND SEE SMOKE. MAINTENANCE FOUND THE SOUR CE OF SMOKE CAME FROM THE VENT BLOWER. FURTHER INVESTIGATION FOUND THE POSITIVE BRUSH HOLD DOWN SPRING TO SHORTING OUT TO THE CASE CAUSING THE SPRING TO WELD ONTO IT. MAINTENANCE ALSO FOUND THE CLEARANCE BETWEEN THE NEGATIVE BRUSH HOLD DO WN SPRING AND THE CASE TO BE MINIMAL. THIS CONCERN WAS FORWARDED TO BEECHCRAFT AND THE MANUFACTURER OF THE VENT BLOWER (ELECTRO MECH). A REPORT WAS ALSO SENT TO TRANSPORT SAFETY BOARD. 1 L 7 2 3T 4 T RT 3A20 E4EA 2000083100901 20000831 00901 EA 2000 8 31 CA000530023 1 20000414 G 2710 C6CW10191 ROD DHAV DHC6 DHC6100 EA PWA PT6 PT6A20 52043 EA FLT CNTRL ROD CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 28137 PCE21168 (CAN) FLIGHT CONTROL ROD FROM BELLCRANK TO AILERON FOUND CRACKED. ROD REPLACED. 1 H 7 2 3T 3 T A9EA E4EA 2000083100902 20000831 00902 CE 2000 8 31 CA000530024 1 20000511 G 2120 551530824 DUCT CESSNA 500 500CESSNA 2076602 CE PRESS DUCT DISCONNECTED W B EMER. DESCENT W INADEQUATE Q C CR CRUISE 1 CA (CAN) WHILE IN CRUISE FLIGHT AT FL 280, THE CABIN PRESSURE STARTED TO DECREASE. SHORTLY THEREAFTER A LOUD BANG WAS HEARD AND THE CABIN PRESSURE BEGAN TO RAPIDLY DECREASE. AN EMERGENCY DECENT WAS CARRIED OUT AND THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. INVESTIGATION REVEALED THAT THE PRESSURIZATION DUCT DOWNSTREAM OF THE WATER SEPARATOR HAD BECOME DISC ONNECTED. 1 L 7 2 4F A22CE 2000083100903 20000831 00903 CE 2000 8 31 CA000530025 1 20000530 G 3230 504501033 TORQUE TUBE CESSNA 402 402B 207590P CE CONT O520 TSIO520EB 17040 SO MCAULY 3AF32C 3AF32C87 GL LT LDG CRACKED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 815023R 722156 (CAN) AFTER TAKEOFF, THE CREW NOTICED THAT THE LEFT MAIN GEAR HAD NOT RETRACTED AND THE CREW RETURNED FOR LANDING. UPON INSPECTION, THE LEFT TORQUE TUBE ASSEMBLY WAS FOUND TO BE CRACKED ALONG ITS LENGTH LIKE AN UNWRAPPED PAPER TOWEL CARDBO ARD TUBE. THE CRACK APPEARED TO ORIGINATE FROM THE WELD AROUND THE HOLE FOR THE MAIN LANDING GEAR FORK BOLT. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2000081700035 20000817 00035 SW 2000 8 17 CA000530027 1 20000411 G 3213 31600 AXLE BBAVIA 7 7GCBC 1220601 SW LYC O320 O320A2D 41508 EA UPPER FWD CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA L4943227A (CAN) CRACK FOUND IN BEND JUST BELOW FORWARD UPPER BOLT HOLE 1 H 7 1 3O 3 O NC A759 E274 2000083100904 20000831 00904 EA 2000 8 31 CA000530028 1 20000516 G 6123 7982132002 ECU HAMSTD DHAV DHC8 DHC8311 1386006 EA PWA PW120 PW123 NE ELECT ENG CNTRL DEFECTIVE W C ABORTED TAKEOFF J R WARNING INDICATION PARTIAL RPM/PWR LOSS TO TAKEOFF 1 CA 15932 88121889 123010 (CAN) AUTO FEATHER ACTIVATED ON TAKEOFF. FDR REMOVED AND ANALYZED POINTING TO DEFECTIVE EEC . 2 H 7 2 4T 4 T RT A13NM E20NE 2000083100905 20000831 00905 CE 2000 8 31 CA000530029 1 20000516 G 2421 DOFF10300F ALTERNATOR CESSNA 150 150M 2071830 CE CONT O200 O200A 17020 SO LOWER CASE HALF CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 32800 21411772A (CAN) LOWER CASE HALF WEBS FOUND CRACKED. 1 H 7 1 3O 3 O 3A19 E252 2001031500144 20010315 00144 NM 2001 3 15 CA000530030 1 20000418 G 3242 BACH30A50 LINE BOEING 727 72727C 138400J NM PWA JT8 JT8D7B 52053 NE BRAKE ASSY RUPTURED W O OTHER A FLAME/FIRE NR NOT REPORTED 1 CA 655816 (CAN) NR 2 MAIN WHEEL BRAKE FOUND ON FIRE FOLLOWING ENGINE SHUT DOWN. HYD BRAKE LINE TO NR 1 BRAKE RUPTURED. LINE AND N R 1 AND 2 BRAKE REPLACED. 2 L 7 3 4F 4 F A3WE E2EA 2000083100906 20000831 00906 SO 2000 8 31 CA000530031 1 20000501 G 3222 67054003 TRUNNION PIPER PA28 PA28RT201T 7102817 SO CONT O360 TSIO360F 17025 SO SHIMMY DAMPNER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 18500 232766R (CAN) DURING A 50-HOUR INSPECTION OF THE LANDING GEAR, THE NOSE GEAR TRUNNION WAS FOUND CRACKED AT SHIMMY DAMPENER ATTAC HMENT POINT. POSSIBLE CAUSE - OVERSTEER. 1 L 7 1 3O 3 O 2A13 E9CE 2000082200021 20000822 00021 GL 2000 8 22 CA000530032 3 20000517 G 6140 503890571 TACH GENERATOR HARTZL BEECH 100 A100 1152915 CE PWA PT6 PT6A28 EA HARTZL HCB4T HCB4TN3 GL DRIVESHAFT FAILED W K NONE O OTHER CR CRUISE 1 CA 14050 PCE50295 EAA1113 (CAN) WHILE IN CRUISE, THE RT PROPELLER INDICATION WENT TO ZERO. NO ACTION WAS TAKEN, AIRCRAFT WAS RETURNING TO BASE. MAINTENANCE REMOVED TACH GENERATOR AND FOUND DRIVESHAFT ROUNDED OFF. NEW TACH GENERATOR INSTALLED. 1 L 7 2 3T 4 T A14CE E4EA 6 C P40EA 2000083100907 20000831 00907 GL 2000 8 31 CA000530033 3 20000517 G 6111 PROPELLER MCAULY 1C160CTM CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA MCAULY 1C160 1C160CTM GL CAMBER FACE CORRODED W O OTHER O OTHER IN INSP/MAINT 1 CA 60960 723879 L4121327A 723879 (CAN) CORROSION ON CAMBER AND FACE OF PROPELLER BLADE. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2000082200022 20000822 00022 SO 2000 8 22 CA000530034 1 20000504 G 3260 327 BULB GE PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA COCKPIT FAILED W O OTHER O OTHER DE DESCENT 1 CA L185661 (CAN) PILOT VERIFIED BURNT RIGHT GEAR BULB USING PRESS-TO-TEST FEATURE. 1 L 7 2 3O 3 O A20SO E14EA 2000083100908 20000831 00908 NE 2000 8 31 CA000530035 2 20000523 G 7261 AS3209018 O-RING PWA 310958701 PILATS PC12 PC1245 EU PWA PT6 PT6A67B 52043 NE FILLER OIL STICK FAILED W A UNSCHED LANDING K FLUID LOSS CR CRUISE 1 CA 70700 PCEPR0130 (CAN) O-RING ON FILLER NECK STICK WAS DISPLACED AND CAUSED OIL EGRESS. REPLACED. 1 L 7 1 3T 4 T RT A78EU E26NE 2000090600001 20000906 00001 CE 2000 9 6 CA000530036 1 20000530 G 2620 873364 CARTRIDGE KIDDE 8980662 CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE SQUIB FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 97688EK 71749 (CAN) AFTER THE FIRE BOTTLE WAS DISCHARGED, THE SQUIB (FIRE BOTTLE CARTRIDGE) WAS FOUND BLOWN APART. THE SUMITTER SUGGE STED THAT PERSONNEL OR ADJACENT EQUIPMENT WAS AT RISK OF DAMAGE OR INJURY DUE TO THE EXTERNAL EXPLOSION OF THE SQUIB. 1 L 7 2 4F 4 F A22CE E1NE 2000083100909 20000831 00909 CE 2000 8 31 CA000530037 1 20000506 G 3310 A343 CONNECTOR CESSNA CESSNA 414 414A 2075907 CE CONT O520 TSIO520NB 17040 SO MCAULY 3AF32C 3AF32C93 GL POST LIGHT BURNED W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA 901223H 728088 (CAN) DURING CRUISE FLIGHT, ONE POST LIGHT CONNECTOR BURNT. IT APPEARED THAT THE CONNECTOR SPRING BROKE AND CAUSED AN ARC, OVERHEATING THE CONNECTOR AND CAUSING SMOKE IN THE COCKPIT. THE LIGHTING SYSTEM WAS DEACTIVATED AND THE AIRCRAFT R ETURNED TO BASE. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2000083100910 20000831 00910 CE 2000 8 31 CA000530038 1 20000504 G 2434 03601018 BEARING LUCAS 2308023 LEAR 35 31A 5170531 CE GARRTT TFE731 TFE7312 01518 WP FRONT BEARING DISINTEGRATED W H DEACTIVATE SYST/CIRCUITS E VIBRATION/BUFFET CR CRUISE 1 CA 34900 15060 95121 P99334 (CAN) LEFT GENERATOR TRIPPED OFF IN-FLIGHT AND WOULD NOT RESET. ON INSPECTION, FOUND GENERATOR FRONT BEARING UNSERVICEA BLE. REMOVED GENERATOR AND REPLACED WITH O/H UNIT. VIBRATIONS FELT THROUGHOUT AIRCRAFT WHEN GEN TRIPPED OFF LINE. 2 L 7 2 4F 4 F RT A10CE E6WE 2000082200023 20000822 00023 CE 2000 8 22 CA000530039 1 20000525 G 3246 21406300 BEARING CLEVELAND 04028900 BEECH 99 99A 1154003 CE PWA PT6 PT6A28 EA CUP SURFACE CORRODED W O OTHER O OTHER IN INSP/MAINT 1 CA 24772 PCE50392 (CAN) INBOARD BEARING CUPS HAVE BEEN PITTING AND SCRATCHING ON A CONSTANT BASIS. THIS IS THE ONLY WHEEL TYPE THAT DOES THIS IN OUR OPERATION AND OCCURS ONLY ON THE INBOARD SIDE OF THE WHEEL ASSY. 1 L 7 2 3T 4 T A14CE E4EA 2000082200024 20000822 00024 CE 2000 8 22 CA000530040 1 20000525 G 3213 50810318605 BOSS 115810000651 BEECH 99 99A 1154003 CE PWA PT6 PT6A28 EA TORQ KNEE BOSS CRACKED W O OTHER O OTHER IN INSP/MAINT 1 CA AMA1135 PCE50392 (CAN) LEFT MAIN GEAR LOWER ASSEMBLY CRACKED AT THE TORQUE KNEE BOSS. 1 L 7 2 3T 4 T A14CE E4EA 2000082200025 20000822 00025 CE 2000 8 22 CA000530041 1 20000525 G 5510 1154400313U BRACKET BEECH 1154400313 BEECH 99 99 1154002 CE PWA PT6 PT6A28 EA WEB HINGE POINT CRACKED W O OTHER O OTHER IN INSP/MAINT 1 CA PCE51808 (CAN) UPON INSPECTION OF THE HORIZONTAL STABILIZER ATTACH BRACKET, IT WAS DISCOVERED THAT THE CASTING WAS CRACKED IN THE WEB BY THE ATTACH HOLES. 1 L 7 2 3T 4 T A14CE E4EA 2000082200030 20000822 00030 CE 2000 8 22 CA000530043 1 20000517 G 3297 V3100 WIRE BEECH 100 A100 1152915 CE PWA PT6 PT6A28 EA WIRE CONNECTION LOOSE W A UNSCHED LANDING J S WARNING INDICATION AFFECT SYSTEMS IN INSP/MAINT 1 CA PCE40975 (CAN) GEAR WAS SELECTED UP AND THE GEAR WOULD NOT RETRACT. THE SELECTION WAS TRIED SEVERAL TIMES AND FINALLY RETRACTED.A LOOSE WIRE WAS FOUND ON THE EMERGENCY EXTENSION MICROSWITCH LOCATED BY THE GEAR TRANSMISSION. THE CONNECTION WAS RESECU RED. 1 L 7 2 3T 4 T A14CE E4EA 2001031500145 20010315 00145 WP 2001 3 15 CA000530044 2 20000525 G 7200 ENGINE SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE33111U 01514 WP MCAULY 4HFR34 4HFR34C652 NE NACELLE MAKING METAL W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA P44121C 881807 (CAN) CHIP DETECTOR WARNING - SMALL SLIVER WAS FOUND. A RECENT ENGINE CHANGE HAD TAKEN PLACE. 2 L 7 2 4T 4 T RT A8SW E4WE 6 C 3PNE 2001031500146 20010315 00146 WP 2001 3 15 CA000530045 2 20000502 G 7260 GEARBOX SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE33111U 01514 WP MCAULY 4HFR34 4HFR34C652 NE ENG ACCESSORY FAILED W E A ENGINE SHUTDOWN UNSCHED LANDING R X J PARTIAL RPM/PWR LOSS ENGINE FLAMEOUT WARNING INDICATION CR CRUISE 1 CA P44727C 881807 (CAN) AIRCRAFT WAS ON TRAINING FLIGHT WHEN THE CAPTAIN NOTICED NO POWER CHANGE WITH LEVER INPUT CHANGE. ALL PARAMETERS WERE NORMAL EXCEPT FOR POWER OUTPUT. ENGINE WAS SHUT DOWN AND RETURNED TO BASE. UPON INVESTIGATION METAL WAS FOUND IN OI L.THE EXACT CAUSE IS STILL NOT FINALIZED. TWO LOCATING PINS AT THE CENTER BORE OF THE AGB HOUSING WERE WORN. THE PIN BOR ES WERE ALSO WORN OBLONG AND THE LOCATING PINS COULD EASILY BE REMOVED BY HAND WITH LITTLE RESISTANCE. IT IS POSSIBLE TH AT THE CONDITION OF THE PINS CAUSED MOVEMENT BETWEEN THE BEARING SUPPORT, BEARING, AGB CASE AND THE IDLER ARM. SUBMITTER SPECIFIED A SUPPLEMENTAL SDR WILL BE FILED ALONG WITH THE TEAR DOWN REPORT. 2 L 7 2 4T 4 T RT A8SW E4WE 6 C 3PNE 2001032900017 20010329 00017 2001 3 29 CA000530047 4 20000519 G 3421 RCA227 GYRO CESSNA 172 172K 2072430 CE LYC O320 O320E2D 41508 EA COCKPIT WRONG PART W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) SUSPECTED UNAPPROVED PART DETECTED DURING IMPORTATION INSPECTION. UNIT INSTALLED: SEPT 10 1999 INVESTIGATION IN PR OGRESS BY NEW OWNER. INVESTIGATION INTO DISCREPANCIES BETWEEN THE INSTALL AND PURCHASE DATES. FOLLOW UP BY PAH-HAM IN PR OGRESS 1 H 7 1 3O 3 O NT 3A12 E274 2001031500147 20010315 00147 CE 2001 3 15 CA000530048 1 20000502 G 3246 13600LA902A1 BEARING BEECH 1900 1900C 1154161 CE PWA PT6 PT6A65B 52043 EA MAIN WHEEL FAILED W L D ABORTED APPROACH RETURN TO BLOCK D INFLIGHT SEPARATION LD LANDING 1 CA PCE32130 (CAN) NR 4 MAIN WHEEL DISLODGED FROM ITS AXLE IN FLIGHT. NO OTHER APPARENT DAMAGE TO GEAR OR AIRFRAME.THE BRAKES AND TI RES ON THIS AXLE WERE REMOVED AND REPLACED JANUARY 06, 2000. NR 4 MAIN WHEEL HAS NOT BEEN LOCATED. SUPPLEMENTAL: RECORD S INDICATE NEW BEARING INSTALLED ONTO NR 4 WHEEL ASSY. TOTAL TIME ON BEARING, 367 CYCLES. FURTHER FOLLOW UP INDICATES T HE FORMER HAVING THE SAME PART NUMBERS INSTALLED ONTO NR 4 WHEEL ASSY. TOTAL TIME ON THIS BEARING WAS 2036 CYCLES FROM F EB 28/97 TO MAY 20/00. ALTHOUGH BOTH BEARINGS ARE THE SAME PART NUMBER, THERE IS NO INDICATION AS TO WHAT POSITION THEY ARE INSTALLED INTO DURING WHEEL ASSY. BUILD UP. 2 L 7 2 4T 4 T RT A24CE E4EA 2000101000336 20001010 00336 EU 2000 10 10 CA000530049 1 20000512 G 3250 5322012276 STOP PILATS PC12 PC1245 EU LEFT SUPPORT ARM CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 79300 (CAN) NOSE GEAR TURN LIMIT STOP INDICATOR FOUND CRACKED ON THE LEFT SUPPORT ARM. 1 L 7 1 3T RT A78EU 2001011104661 20010111 04661 EU 2001 1 11 CA000530050 1 20000512 G 2510 5251512026 COVER PILATS PC12 PC1245 EU SEAT BASE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 79300 (CAN) AFT COVER PLATE ON SEAT BASE WAS FOUND CRACKED AT THE MOUNTING HOLES. 1 L 7 1 3T RT A78EU 2001031500148 20010315 00148 NM 2001 3 15 CA000530051 1 20000517 G 2150 6806404 ACM BOEING 757 75723A 1384967 NM RROYCE RB211 RB211535E4 54555 NE LEFT SEIZED W O OTHER J WARNING INDICATION CR CRUISE 1 CA 30863 (CAN) CREW UNABLE TO CONTROL FLIGHT DECK, LT AIR CYCLE MACHINE SEIZED, SENT TO SHOP FOR REPAIR AND REPORT. 2 L 7 2 4F 4 F RT A2NM E12EU 2001031500149 20010315 00149 WP 2001 3 15 CA000530053 1 20000521 G 2120 958132 CHECK VALVE LKHEED 1011 1011385114 WP RROYCE RB211 RB21122B02 54555 NE AIR DUCTING MISSING W K NONE O OTHER IN INSP/MAINT 1 CA 10217 (CAN) NO FLOW WAS COMING OUT OF NR 3 PACK. WHEN REMOVING NR 3 PACK CONTROL VALVE, FOUND PART OF A CHECK VALVE STUCKED I NSIDE THE PACK VALVE. AFTER INVESTIGATION, FOUND 2 PIE SHAPE SEGMENTS MISSING OF THE APU DISCHARGED CHECK VALVE. PNEUMAT IC SYSTEM DUCTS INSPECTED AT MOST PROBABLE AREAS AND NO PART FOUND. ALL PACK CONTROL VALVES, AIR CLEANERS. APU DISCHARGE VALVE REPLACED AND PNEUMATIC SYSTEM CHECK SERVICEABLE. DUE TO THE FACT THAT ALL SYSTEM OPERATE NORMALLY AND THE MISSING PART WAS UNFINDABLE, SUSPECT THAT THE PART WAS PREVIOUSLY REMOVED FROM THE SYSTEM DURING PREVIOUS MAINTENANCE, AIRCRAFT RETURNED TO SERVICE. 2 L 7 3 4F 4 F A23WE E12EU 2001031500150 20010315 00150 EA 2001 3 15 CA000530055 1 20000524 G 7931 601509197 TRANSDUCER CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE OIL PRESSURE INOPERATIVE W E ENGINE SHUTDOWN N FALSE WARNING AP APPROACH 1 CA (CAN) OIL PRESSURE TRANSDUCER WAS INOPERATIVE, GIVING FALSE LOW PSI READING. NO EICAS SYSTEM WARNING PRESENT. 2 L 7 2 4F 4 F RT A21EA E15NE 2001031500151 20010315 00151 EA 2001 3 15 CA000530056 1 20000530 G 2612 356024310 FIRE LOOP CNDAIR CL600 CL6002B19 EA LT ENGINE FAILED W E A ENGINE SHUTDOWN UNSCHED LANDING N FALSE WARNING CL CLIMB 1 CA (CAN) SHORTLY AFTER T.O. EICAS WARNING 14TH STAGE DUCT APPEARED. LT ENGINE WAS SHUT DOWN IN FLIGHT. A/C RETURNED TO LAND . LT ENG 14TH STAGE HEAT SENSING ELEMENT REPLACED. 2 L 7 2 4F RT A21EA 2001031500152 20010315 00152 EA 2001 3 15 CA000530057 1 20000530 G 2916 RESERVOIR CNDAIR CL600 CL6002B19 EA HYD SYSTEM FAILED W D RETURN TO BLOCK K J FLUID LOSS WARNING INDICATION TX TAXI/GRND HDL 1 CA (CAN) ON RETURN FROM FLIGHT, NR 2 HYD RES SYSTEM WAS OBSERVED AT 20 PERCENT QUANTITY CONTINUED TO DECREASE UNTIL LOW PRE SSURE MESSAGE WAS DISPLAYED. 2 L 7 2 4F RT A21EA 2001031500156 20010315 00156 NM 2001 3 15 CA000530062 1 20000507 G 2910 41010029 POWER UNIT AIRBUS A319 A319114 NM HYD SYSTEM LEAKING W H DEACTIVATE SYST/CIRCUITS K J FLUID LOSS WARNING INDICATION IN INSP/MAINT 1 CA (CAN) LOSS OF YELLOW SYSTEM HYD. SYS FLUID. POWER TRANSFER UNIT DEACTIVATED. INVESTIGATION REVEALED PTU LEAKING AT QUICK DISCONNECT. SEALS REPLACED. 2 L 7 2 4F RT A28NM 2001031500157 20010315 00157 NE 2001 3 15 CA000530063 2 20000501 G 7200 ENGINE CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE LEFT MALFUNCTIONED W K NONE O OTHER IN INSP/MAINT 1 CA 807154 (CAN) NOT ABLE TO DUPLICATE SNAG, NO FAULT FOUND. 2 L 7 2 4F 4 F RT A21EA E15NE 2001031500163 20010315 00163 NM 2001 3 15 CA000530070 1 20000427 G 5610 141T48011 WINDOW BOEING 767 767209 NM PWA JT9 JT9D7R4D 52054 NE COCKPIT FAILED W O OTHER O OTHER CR CRUISE 1 CA P709688 (CAN) DURING CRUISE AT FL 360 FIRST OFFICER WINDOW OUTER PANE FAILED. CREW COMMENTED ARCING ON WINDSCREEN. WINDOW AND CO NTROLLER REPLACED. 2 L 7 2 4F 4 F RT A1NM E3NE 2001031500164 20010315 00164 NM 2001 3 15 CA000530071 1 20000518 G 2572 732591A FAN BOEING 767 767233 NM PWA JT9 JT9D7R4D 52054 NE E/E BAY FAILED W O OTHER B SMOKE/FUMES/ODORS/SPARKS DE DESCENT 1 CA P707531 (CAN) ELECTRICAL BURNING SMELL IN COCKPIT DURING APPROACH, ELECTRICAL COOLING SWITCH SELECTED TO OVERIDE SMELL DISSIPAT ED. NR 1 EQUIPMENT COOLING VAN SOURCE OF SMELL AND GRINDING DURING ROTATION. CHANGED. 2 L 7 2 4F 4 F RT A1NM E3NE 2001031500165 20010315 00165 NM 2001 3 15 CA000530072 1 20000427 G 2933 851307683020 SWITCH BOEING 767 767333 NM PWA 4060 PW4060 52119 NE INDICATOR BURNED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA P724359 (CAN) CENTER HYD PUMP FAILED IN CRUISE ELECTRICAL BURN SMELL IN COCKPIT, SMOKE EVIDENT, PUMP SHUT OFF, SMOKE DISSIPATED. SWAPPED C1 AND C2 DELAY MODULE AND CHANGED C1 LIGHT SWITCH. ON CLIMB THERE WAS A BURNING SMELL, C1 HYD SYSTEM SHUT DOWN A/C DIVERTED. FOUND C1 SWITCH LIGHT AND C2 DELAY MODULES BURNT. NEW TIME DELAY INSTALLED AND C2 POSITION SWAPPED FOR RE CIRC FAN SWITCH. 2 L 7 2 4F 4 F RT A1NM E24NE 2001031500166 20010315 00166 NM 2001 3 15 CA000530073 1 20000517 G 2910 LINE BOEING 767 767233 NM PWA JT9 JT9D7R4D 52054 NE HYDRAULIC SYS RUPTURED W O OTHER J WARNING INDICATION LD LANDING 1 CA P716610 (CAN) ON LANDING CENTER HYD SYSTEM FLUID DROPPED TO ZERO. PRESSURE LINE FROM CENTER HYD SYS PUMP RUPTURED. LINE REPLACED , SYS SERVICED AND LEAK CHECK OK. 2 L 7 2 4F 4 F RT A1NM E3NE 2000073100044 20000731 00044 CE 2000 7 31 CA000530074 1 20000518 G 2750 WIRE CESSNA 500 S550 2076607 CE CENTER CNTR CHAFED W O OTHER F FLT CONT AFFECTED CL CLIMB 1 CA 47260 (CAN) DURING CLIMB, THE FLAP CONTROL CIRCUIT BREAKER TRIPPED AS THE FLAPS WERE BEING RETRACTED. THE BREAKER WAS RESET A ND IT TRIPPED AGAIN. THE FLIGHT WAS CONTINUED WITH THE FLAPS PARTIALLY EXTENDED. MAINTENANCE PERSONNEL FOUND THE FLAP C ONTROL CIRCUIT WIRING WAS CHAFED AND SHORTING WHERE THE WIRES ARE ROUTED THROUGH THE RIGHT HAND WING FAIRING (APPROX WS 100.00, ZONE 612 AND 622). 1 L 7 2 4F RT A22CE 2001031500167 20010315 00167 EA 2001 3 15 CA000530075 1 20000511 G 3246 C3US1563 BOLT DHAV DHC3 DHC3 2800202 EA PWA PT6 PT6A135 52043 NE AT SHEAR POINT BROKEN W A UNSCHED LANDING D INFLIGHT SEPARATION TO TAKEOFF 1 CA 158 (CAN) DURING TAKEOFF RUN, A SOUND WAS HEARD OUTSIDE THE AIRCRAFT. THE PASSENGER IN RIGHT SEAT NOTED RIGHT SKI WAS TIPPE D FORWARD AMD HANGING BY CHECK CABLE. LANDING WAS CARRIED OUT AND RESULTED IN SKI DIGGING IN FRONT AND CUTTING THE REAR GEAR ATTACHMENT STRUT. 1 H 7 1 3R 4 T A815 E4EA 2000082800016 20000828 00016 CE 2000 8 28 CA000606003 1 20000601 G 2824 13341511 VALVE MTSBSI MU2 MU2B36 5780412 CE GARRTT TPE331 TPE3316 01514 WP OPERATOR MOTOR MALFUNCTIONED W A UNSCHED LANDING A FLAME/FIRE CR CRUISE 1 CA 18651 P27223C (CAN) DURING CRUISE, THE CREW STARTED TO TRANSFER TIP FUEL WITH NO PROBLEM. WHEN THE CREW SELECTED TIP TRANSFER OFF, TH E RT TIP TANK CONTINUED TO FLOW UNTIL TIP TANK PRESSURE WAS EXHAUSTED. THIS CAUSED ABOUT A 15 GALLON FUEL IMBALANCE BET WEEN THE TIP TANKS (RT LIGHTER). DURING LANDING AND TAXI WITH A FULL MAIN TANK AND THE LEFT WING LOW DUE TO THE FUEL IM BALANCE, A SMALL AMOUNT OF FUEL PASSED BY THE SNORKLE CHECK VALVE AND ACCUMULATED IN THE VENT SYSTEM, WHICH DRAINED ONTO THE GROUND SLOWLY AFTER THE AIRCRAFT WAS PARKED. THE VALVE WAS REPLACED WITH A SERVICEABLE VALVE AND THE AIRCRAFT RETU RNED TO SERVICE. 1 H 7 2 3T 4 T RT A10SW E4WE 2000073100045 20000731 00045 CE 2000 7 31 CA000606006 1 20000527 G 2730 115610010325 TORQUE TUBE BEECH 100 100BEECH 1152916 CE PWA PT6 PT6A28 EA TAPER PIN HOLES WORN W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 57800 PCE50050 (CAN) AUDITOR INSPECTION OF AIRCRAFT NOTICED LOOSE ELEVATOR TORQUE TUBES. FOUND LEFT ELEVATOR TORQUE TUBE HOLES WORN BE YOND LIMITS. EXAM OF HOLES NOTED HOLES NOT ROUND, APPEARED THAT FACTORY REAMER CHATTERED MAKING LEDGES IN HOLE. ALSO N OTED FACTORY INSTALLED TAPER PINS ALREADY BEYOND LIMITS OF PROTRUSION. RAYTHEON CONTACTED. TORQUE TUBE ASSEMBLY REPLAC ED. 1 L 7 2 3T 4 T A14CE E4EA 2000101000337 20001010 00337 CE 2000 10 10 CA000606007 1 20000520 G 5753 052390113 SUPPORT BRACKET CESSNA 052390138 CESSNA 172 R172K 2072431 CE CONT O360 IO360K 17025 SO MCAULY 2A34C 2A34C203 GL BEHIND BRG ROLLE WORN W K NONE O OTHER IN INSP/MAINT 1 CA 26650 355524 771797 (CAN) WEAR WAS FOUND WHERE ROLLER IS ATTACHED TO THE FLAP SUPPORT RIB. BEARING MUST BE REMOVED TO INSPECT. FOUND WORN OVER 1/3 THROUGH FLAP SUPPORT RIB, IN NICE CIRCLES CAUSED BY BEARING/ROLLER ITSELF. THIS THE 2ND CASE SUBMITTER HAS SEEN . 1 H 7 1 3O 3 O 3A17 E1CE 5 C P3EA 2000071800200 20000718 00200 GL 2000 7 18 CA000606009 2 20000521 G 7260 6890914 BEARING ALLSN 6894171 BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL SUPP ADAPTR GEAR WORN W A UNSCHED LANDING D P INFLIGHT SEPARATION NO WARNING INDICATION CR CRUISE 1 CA 49420 CAG34043 CAE801640BA (CAN) WHILE IN-FLIGHT, THE PILOT COULD HEAR A LOUD METALLIC SCREAMING GRINDING NOISE FROM THE ENGINE. HE LANDED AT A CL EARING AND SHUT DOWN ENGINE. THE ENGINE GEARBOX HAD QUICK DISCONNECT CHIP PLUGS, PULLED THE CHIP DETECTORS AND FOUND FE RROUS METAL ON THE OUTER PERIMETER, BUT NO CHIPS CROSSING ONTO THE CENTER PROBE TO GIVE THE PILOT A CHIP LIGHT ON THE IN STRUMENT PANEL. THE SYSTEM WAS INSPECTED FOR LIGHT INDICATION AND FOUND SERVICEABLE. GEARBOX TSN 11,413.5 HOURS. TIME S INCE LAST MAJOR INSPECTION 4941.9 HOURS. 1 G 7 1 3U 3 U H2SW E4CE 2001031500170 20010315 00170 EU 2001 3 15 CA000606010 1 20000602 G 2742 1TW18 SWITCH FOKKER F28 F28MK1000 4990808 EU STAB ACTUATOR OUT OF RIG W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) PILOTS NOTICED OUTBOUND OF YXE. THAT THE HORIZONTAL STAB TRIM WHEEL WAS UNABLE TO BE ADJUSTED. THE CREW DECIDED TO RETURN AND AT THAT TIME THEY REALIZED THAT THE UTILITY AND FLIGHT CONTROL SYSTEM STAB CAUTION LIGHTS WERE ON - INDICAT ING NO HYDRAULIC POWER TO THE STAB. AS PER THE PILOTS CHECKLIST, THE CREW MANUALLY SELECTED THE STAB SWITCHES OFF AND TH EN PROCEEDED TO USE THE STAB VIA THE ALTERNATE STAB ELECTRIC SWITCH. THE AIRCRAFT RETURNED& LANDED WITHOUT INCIDENT. MAI NTENANCE INSPECTION FOUND THE HORIZONTAL STAB STICKING SWITCH OUT OF RIG. MAINTENANCE RE-RIGGED THE SWITCH & CHECKED IT AS SERVICEABLE. TEST FLIGHT WAS COMPLETED & CHECKED OK. 2 L 7 2 4F RT A20EU 2001031500171 20010315 00171 EU 2001 3 15 CA000606011 1 20000604 G 2612 30262A18A19 SWITCH FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU FIRE DETECTION INTERMITTENT W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 CA 9077 (CAN) PILOTS REPORTED THAT ON HEAD START DEPARTURE OUT OF YVR, THE NR 1 ENGINE FIRE DETECT SYSTEM WOULD NOT TEST. MAINTE NANCE WAS CALLED OUT TO THE AIRCRAFT AND FOUND THAT THE PROBLEM TO BE THE TEST SWITCH. THEY SPRAY CLEANED THE SWITCH & I T TESTED SERVICEABLE. AIRCRAFT RETURNED TO SERVICE HOWEVER ON THE OUTBOARD LEG THE FIRE DETECT SYSTEM WOULD NOT TEST ONC E AIRBORNE. CREW ELECTED TO RETURN TO YVR & LANDED WITHOUT INCIDENT. MAINTENANCE REPLACED THE NR 1 FIRE WARNING TEST SWI TCH, P/N 3026218A9, & TESTED SERVICEABLE. AIRCRAFT RETURNED TO SERVICE WITH NO FURTHER INCIDENTS TO REPORT. 2 L 7 2 4F 4 F RT A20EU E2EU 2000080800016 20000808 00016 GL 2000 8 8 CA000606012 1 20000526 G 7900 ENGINE ROTAX DIAMON DA20 DA20A1 GL ROTAX 912 ROTAX912 55555 EU ENGINE FAULTY W O OTHER J WARNING INDICATION CR CRUISE 1 CA 13380 4412605 (CAN) ENGINE OIL PRESSURE WENT FROM 60 PSI TO 32 PSI AFTER TAKEOFF WHEN THE AIRCRAFT WAS LEVELED OFF FOR CRUISE. PILOT RETURNED AND LANDED SAFELY. ENGINE HAS BEEN GROUND RUN TWICE AND CHECKED. COULD NOT DUPLICATE ON GROUND. AIRCRAFT RET URNED TO SERVICE. NO FURTHER REPORTS. 1 L 7 1 3O 3 I NT TA4CH EXPE3I 2000073100046 20000731 00046 CE 2000 7 31 CA000606013 1 20000531 G 3230 LANDING GEAR BEECH 100 B100 1152919 CE GEAR FAILED W A UNSCHED LANDING J O WARNING INDICATION OTHER TO TAKEOFF 1 CA (CAN) PILOT SELECTED GEAR UP AFTER TAKEOFF WITH NO GEAR RESPONSE. PILOT CHECKED CONTROL AND POWER CIRCUIT BREAKER AND R ECYCLED GEAR, NO RESPONSE. EMERGENCY GEAR EXTENSION AND LANDING C/O-NORMAL. AIRCRAFT PLACED ON JACKS, NO POWER TO GEAR MOTOR. AFTER APPROX. 20 MINUTES, GEAR POWER C/B (60 AMP) RESET AND HEARD TO CLICK GEAR FUNCTION NORMAL. NO FAULT FOUN D - NOTE - PILOT HANDBOOK ELECTRIC LOAD LIMITS LIST GEAR MOTOR AT 140 AMPS. AMP TEST OF AIRCRAFT WHEN GEAR CYCLING. 75 AMPS NOMINAL TO 120 AMPS PEAK. 1 L 7 2 4T A14CE 2000080900004 20000809 00004 EA 2000 8 9 CA000606014 2 20000228 G 8530 CYLINDER LYC CESSNA 172 172P 2072436 CE LYC O320 O320D2J 41508 EA MCAULY 1C160 1C160DTM GL LT FWD NR 2 CYL FAILED W A B UNSCHED LANDING EMER. DESCENT R K PARTIAL RPM/PWR LOSS FLUID LOSS CL CLIMB 1 CA 16000 L909339A 83414 (CAN) AIRCRAFT IN-FLIGHT, OVER LETHBRIDGE CLIMB-OUT. BIG BANG, NR 2 CYLINDER EXITED LEFT COWL, OIL ALL OVER. PILOT LAN DED AIRCRAFT AT LETHBRIDGE. ENGINE MADE ENOUGH POWER TO GET AIRCRAFT TO AIRPORT. CYLINDER NOT FOUND. SMALL PART OF PI STON, RINGS, HYDRAULIC LIFTER, FOUND IN COWL, NO PISTON PIN FOUND. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2001011104700 20010111 04700 EU 2001 1 11 CA000606017 1 20000531 G 7921 5791012038 STRUT PWA PILATS PC12 PC1245 EU PWA PT6 PT6A67B 52043 NE CLEVIS END DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 25950 PCEPR0090 (CAN) THE HOLES IN THE FLAP STRUT ON THE CLEVIS END ARE ELONGATED. THIS STRUT OPENS THE OIL COOLER DOOR WHEN THE GEAR I S EXTENDED. 1 L 7 1 3T 4 T RT A78EU E26NE 2000080900005 20000809 00005 CE 2000 8 9 CA000606018 1 20000531 G 3246 16218000 WHEEL CLEVELAND 40289 BEECH 99 99 1154002 CE PWA PT6 PT6A28 EA BEAD AREA CRACKED W O OTHER O OTHER IN INSP/MAINT 1 CA 24900 14532 PCE40209 (CAN) WHEEL FOUND CRACKED IN THE BEAD AREA ON THE 3RD TIRE CHANGE CYCLE. 1 L 7 2 3T 4 T A14CE E4EA 2000080900006 20000809 00006 CE 2000 8 9 CA000606019 1 20000601 G 3246 04028900A WHEEL CLEVELAND 16118000 BEECH 100 A100C 1152917 CE PWA PT6 PT6A28 EA BEAD AREA CRACKED W O OTHER O OTHER IN INSP/MAINT 1 CA 15142 PCE40919 (CAN) WHEEL HALF FOUND CRACKED IN BEAD AREA DURING LPI. THIS RIM ASSEMBLY WAS ON ITS 23RD TIRE CHANGE. 1 L 7 2 4T 4 T A14CE E4EA 2000080900007 20000809 00007 CE 2000 8 9 CA000606020 1 20000601 G 3260 V31001 SWITCH BEECH 115810052 BEECH 99 B99 1154004 CE PWA PT6 PT6A28 EA TERMINAL LOOSE W O OTHER J S WARNING INDICATION AFFECT SYSTEMS CL CLIMB 1 CA PCE41919 (CAN) LANDING GEAR WOULD NOT RETRACT. THERE WAS NO IN TRANSIT LIGHT ON AND THE THREE GREEN DOWN AND LOCKED POSITION LIG HTS REMAINED ON. A LOOSE WIRE WAS FOUND ON THE EMERGENCY EXTENSION SAFETY SWITCH PREVENTING THE GEAR FROM RETRACTING BY REMOVING ALL POWER TO THE MOTOR. WIRE SECURED AND AIRCRAFT RETURNED TO SERVICE. 1 L 7 2 3T 4 T A14CE E4EA 2000101000338 20001010 00338 EA 2000 10 10 CA000606021 1 20000514 G 2711 C6CW108727 CONTROL ROD DHAV DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA FROM RIVET HOLE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 382 PCE40329 (CAN) DURING INSPECTION THE SERVO TAB LINK FOR THE AILERON WAS FOUND CRACKED AT THE UPPER END. THE CRACK EXTENDED FROM T HE ROD END BEARING RETENTION RIVET HOLE TO THE END OF THE ROD. FOR REFERENCE SEE DEHAVILLAND IPC 27-10-00, FIG. 5 (SHEE T 1 OF 1), ITEM 90. THE ROD WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. 1 H 7 2 3T 4 T RT A9EA E4EA 2000101000339 20001010 00339 EA 2000 10 10 CA000606023 1 20000605 G 3246 AN4424 BOLT DHAV DHC3 DHC3 2800202 EA PWA PT6 PT6A34 52043 EA EYE PORTION CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA PCE40906 (CAN) INSPECTION OF CANOE RACK FOR LOOSENESS FOUND EYE BOLT HEAD SLIGHTLY BENT WITH CRACK ON FORWARD FACE. EYE BOLT REP LACED. 1 H 7 1 3R 4 T A815 E4EA 2001011104701 20010111 04701 EU 2001 1 11 CA000606024 1 20000525 G 7712 5771112105B LINE PILATS PC12 PC1245 EU PWA PT6 PT6A67B 52043 NE TRANSDUCER LOOSE W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CL CLIMB 1 CA 57400 PCEPR0141 (CAN) TORQUE TRANSDUCER AND OIL SUPPLY LINES MEET. DETERMINED THAT LINE 577.11.12.105B AT TQ LIMITER CONNECTION WAS LOO SE. IT SURMISED THAT BY MULTIPLE CONNECT/RE-CONNECT AT 'T', BENDING AND POTENTIAL FOR MOVEMENT OF ENTIRE PLUMBING BUNDL E, LACK OF TORQUE APPLIED AT TQ LIMITER NUT CONNECTION, CAUSED BREACH AND RESULTED IN LEAK. TIGHTENING OF NUT AND SUBSEQ UENT GROUND RUNS AND TEST FLIGHT SHOWED NO FURTHER SIGNS OF OIL LEAKAGE. MORE THOROUGH POST INSP ENGINE GROUND RUN WILL BE INCORPORATED. SUGGESTION : BENDING POTENTIAL IS GREAT, CONSIDERING LINES ARE OF COMBINED RIGID AND FLEXIBLE DESIGN . IT WOULD BE ADVANTAGEOUS TO INCORPORATE TEE FIT ING AND SAFTIED CAP FOR PURPOSE OF ATTACHMENT. 1 L 7 1 3T 4 T RT A78EU E26NE 2001032900018 20010329 00018 GL 2001 3 29 CA000606026 3 20000425 G 6112 9598901035 BOOT PILATS PC12 PC1245 EU HARTZL HCE4A HCE4A3D GL LT STAB SEPARATED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ON PRE-FLIGHT THE PILOT NOTICED THE BOOT HAD BECOME UNGLUED ON THE TOP FOR ABOUT TWO FEET. HE ADVISED THE ENGINEER & BOOT WAS REGLUED UNTIL A NEW BOOT COULD BE ORDERED. WHEN NEW BOOT ARRIVED THE OLD BOOT WAS PEELED OFF AND NEW ONE INS TALLED. THE OLD BOOT WAS NOT STUCK DOWN VERY WELL AND WAS EASY TO PEEL OFF. 1 L 7 1 3T RT A78EU 5 C P210NE 2001032900019 20010329 00019 EU 2001 3 29 CA000606027 1 20000606 G 2752 951D10011 ACTUATOR PILATS PC12 PC1245 EU TE FLAPS WORN W K NONE O OTHER IN INSP/MAINT 1 CA 17800 (CAN) ON INSPECTION OF BACKLASH CHECK UNITS WORN BEYOND LIMITS ON THREE OUT OF FOUR ACTUATORS. THEY ALL HAVE THE SAME CY CLES AND HOURS ON THE UNITS. 1 L 7 1 3T RT A78EU 2001032900020 20010329 00020 EU 2001 3 29 CA000606028 1 20000414 G 5753 951D10011 ACTUATOR PILATS PC12 PC1245 EU TE FLAPS WORN W K NONE O OTHER IN INSP/MAINT 1 CA 26000 (CAN) ON INSPECTION THE BACKLASH WAS BEYOND LIMITS. 1 L 7 1 3T RT A78EU 2001031500175 20010315 00175 GL 2001 3 15 CA000606030 3 20000526 G 6114 A2043 NUT HARTZL HCC2Y HCC2YK1 GL PROPELLER CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA CH20345 (CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. REPLACED 10 OUT OF 10 NUTS. 5 C P920 2000072800037 20000728 00037 EU 2000 7 28 CA000606031 1 20000526 G 2612 B232M FIRE DETECTOR BOLKMS 105 BO105C 5626005 EU ALLSN 250C 250C20B 03013 GL ENGINE LOOSE W O OTHER N FALSE WARNING CR CRUISE 1 CA CAE835650 (CAN) #1 FIRE WARNING LIGHT CAME ON IN CRUISE FLIGHT. PILOT RETARDED THROTTLE TO IDLE & RETURNED TO BASE. AIRCRAFT INSPE CTED LOOSE WIRE ON DETECTOR FOUND, WIRE (MEET) TORQUED SYSTEM CHECKED & FOUND SERVICEABLE, AIRCRAFT RETURNED TO SERVICE. 1 G 7 2 3U 3 U H3EU E4CE 2000080900008 20000809 00008 SO 2000 8 9 CA000606032 1 20000525 G 3213 4028800 TRUNNION PIPER PA31T PA31T2 7103127 SO PWA PT6 PT6A135 52043 NE REINFORCEMNT RIB CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 79530 PCE92353 (CAN) DURING INSPECTION, A CRACK WAS FOUND ON THE AFT RIGHT MAIN LANDING GEAR TRUNNION ASSEMBLY. THE CRACK WAS FOUND TO BE ON THE UPPER REINFORCEMENT RIB. THE PART WAS REPLACED WITH NEW. 1 L 7 2 3T 4 T RT A8EA E4EA 2000080900009 20000809 00009 GL 2000 8 9 CA000606033 3 20000531 G 6111 900CB8 BLADE MCAULY C2A34C204 CESSNA 182 182R 2072731 CE CONT O470 O470U 17026 SO MCAULY 2A34C C2A34C204 GL L/E & FACE DAMAGED W O OTHER O OTHER IN INSP/MAINT 1 CA 87400 831059 470465 831059 (CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. BLADES TRIMMED, ALODINED, PAINTED. 1 L 7 1 3O 3 O NT 3A13 E273 5 C P3EA 2000080900010 20000809 00010 GL 2000 8 9 CA000606034 3 20000606 G 6111 PROPELLER MCAULY CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA MCAULY 1C160 1C160CTM GL LEADING EDGE ERODED W O OTHER O OTHER IN INSP/MAINT 1 CA 11790 L4029827A 724384 (CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2000080900011 20000809 00011 EA 2000 8 9 CA000606035 2 20000515 G 7310 3026779 TUBE PWA BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA AFT B NUT CRACKED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 CA 26060 PCE80073 (CAN) AFTER TAKEOFF, FUEL VAPOR SMELL IN CABIN, SHUT OFF BLEED AIR, SMELL WENT DOWN. AIRCRAFT RETURNED TO YQB. FOUND F UEL PRESSURE TUBE ASSY CRACKED JUST AFT OF B-NUT. 1 L 7 2 4T 4 T A24CE E4EA 2000100300072 20001003 00072 SO 2000 10 3 CA000606036 2 20000526 G 8520 5A10204 EXHAUST VALVE CONT CESSNA 150 150M 2071830 CE CONT O200 O200A 17020 SO STEM BROKEN W A UNSCHED LANDING R E PARTIAL RPM/PWR LOSS VIBRATION/BUFFET CL CLIMB 1 CA 13640 621372AR (CAN) IN-FLIGHT, THE ENGINE WAS RUNNING ROUGH. NR 3 CYLINDER SPARK PLUGS FOUND BROKEN. NR 3 CYLINDER MOVED AND REPLACE D BY OVERHAULED ONE (EXHAUST VALVE FOUND BROKEN). 1 H 7 1 3O 3 O 3A19 E252 2001011104721 20010111 04721 EA 2001 1 11 CA000606037 1 20000530 G 5610 C2F249 STRUCTURE DHAV DHAV DHC3 DHC3 2800202 EA WINDSCREEN SEAT CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 18798 135 (CAN) WINDSCREEN SEAT CLEANED AT REPLACEMENT. INSPECTED PER SB 3/29.CORROSION FOUND AS INDICATED IN SB. 0.250 INCH HOLE S FOUND AT LOWER AREA OF DOOR POST. NEW REPLACEMENTS WILL BE INSTALLED. 1 H 7 1 3R A815 2001031500176 20010315 00176 WP 2001 3 15 CA000614001 1 20000525 G 2434 G3004BM1 GENERATOR GRUMAN TS2 TS2ACALFORST 3951102 WP WRIGHT R1820 982C9HE2 67020 EA HAMSTD 43D 43D51 NE LT ENGINE DESTROYED W H DEACTIVATE SYST/CIRCUITS B J SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CR CRUISE 1 CA 14 PC10164C 196156 (CAN) LT ENGINE GEN FAILURE LIGHT CAME ON & GEN SELECTED OFF. WHEN A/C SLOWED FOR LDG SMOKE OBSERVED IN COCKPIT. ELECT. SYS WERE SHUT OFF & SMOKE DISSIPATED. UPON INVESTIGATION FOUND THAT GENERATOR HAD SHEARED OFF ALL OF MOUNTING STUDS WITH GEN LYING IN BOTTOM OF ENGINE COWLS. GEN REMOVED & RETURNED TO CONAIR, ABBOTSFORD FOR FURTHER INVESTIGATION. GEN SHAFT SHEARED & END-BEARING P/B JH 203-10 FOUND DESTROYED . GEN ELECTRICAL WIRING SECURED & ENGINE GROUND RUN COMPLETED.ENGINE FUNCTION TESTED SATISFACTORILY. ENGINE FILTER CHECKED FOR CONTAMINANTS - NONE FOUND. ELECT. WIRING CHECKED FOR DAMAGE - WIRING REPD/REPL, AS NECESSARY. 2 H 7 2 4R 4 R A25WE E259 6 C P8879 2001031500177 20010315 00177 2001 3 15 CA000614002 4 20000517 G 2565 D31022102 SLIDE AIRBUS 310 A310304 EU OVERWING FAILED W K NONE L NO TEST IN INSP/MAINT 1 CA 30037 2722 (CAN) AIRCRAFT 204, MAY 17/2000, TRENTON, LOG SEQUENCE 0511852. DURING SCHEDULED TEST DEPLOYMENT OF RT OVERWING SLIDE, I T FAILED TO DEPLOY. SLIDE WAS DEPLOYED BY FURTHER ACTUATION OF AUTOMATIC CABLE. SLIDE DID NOT FULLY INFLATE. 2 L 7 2 4F RT A35EU 2001031500178 20010315 00178 NM 2001 3 15 CA000614003 1 20000602 G 3244 26010452 TIRE BOEING 737 7372T2 1384491 NM PWA JT8 JT8D17A 52049 NE MLG SEPARATED W A UNSCHED LANDING O OTHER CL CLIMB 1 CA 9162 324 709382 (CAN) ON ROTATION, STRONG VIBRATION FELT FROM NOSE GEAR. TOWER ADVISED, PIECES OF RUBBER AND METAL FOUND ON RUNWAY AFTER TAKEOFF. RETURNED TO RAMP. REPLACED BOTH NOSE WHEEL ASSEMBLIES DUE LT NOSE WHEEL TIRE TREAD HAD SEPARATED. LT NOSE SKI TO WHEEL SEAL RETAINER MISSING. OFF CANADIAN PART NUMBERS, LT WHEEL & TIRE 7-3241-9-0022 S/N 0315, ON S/N 2169. RT WHEEL & TIRE 7-3241-9-0022 S/N 3687, ON S/N 0203. WHEELS & TIRES REPLACED AS PER WORK CARD 4147. TRIMMED SEAL AND REMAINING S EAL RETAINER. OVERWEIGHT LANDING INSPECTION COMPLETED AS PER WORK CARD 4041. AIRCRAFT OK FOR SERVICE. 2 L 7 2 4F 4 F RT A16WE E2EA 2001031500179 20010315 00179 NM 2001 3 15 CA000614004 1 20000608 G 3230 106122615 SENSOR BOEING 737 737275C NM PWA JT8 JT8D9A 52048 NE MLG OUT OF TOLERANCE W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 687895 (CAN) ON TAKEOFF, LANDING GEARS WOULD NOT RETRACT WITHOUT USING GEAR OVERRIDE. AIRCRAFT RETURNED. LANDING GEAR ACCESSOR Y MODULE REPLACED AS PER WORK CARD 4281. OFF CANADIAN PART 7-326-9-0010 SERIAL 0054, ON SERIAL #0438. FURTHER TROUBLESHO OTING FOUND AIR SENSOR OUT OF TOLERANCE. SENSOR ADJUSTED AS PER MM 32-09-200, PAGES 501. GEAR SWING ACCOMPLISHED AND CHE CKED OK. 2 L 7 2 4F 4 F A16WE E2EA 2000080900003 20000809 00003 CE 2000 8 9 CA000614005 1 20000607 G 7603 016A43298 NUT MTSBSI MU2 MU2B35 5780411 CE GARRTT TPE331 TPE3316252M 01514 NE POWER LEVER LOOSE W O OTHER R PARTIAL RPM/PWR LOSS CR CRUISE 1 CA 11099 P33087C (CAN) INVESTIGATION REVEALED THE P/N 016A-43298 LT-RT THREADED ADJUSTMENT ROD ON THE POWER LEVER ATTACHMENT TO THE ENGI NE, HAD COME LOOSE AND HAD MOVED, CAUSING A POWER LEVER MISMATCH. IT IS ASSUMED THAT THE LOCKNUTS WERE NOT SUFFICIENTLY TORQUED FOLLOWING ADJUSTMENT. NO FURTHER PROBLEM WAS FOUND. THE POWER LEVER WAS RE-RIGGED AND LOCKNUTS TORQUED, ENGINE GROUND RUN OK AND RETURNED TO SERVICE. 1 H 7 2 3T RT A10SW E2WE 2001031500180 20010315 00180 EU 2001 3 15 CA000614007 2 20000515 G 7200 ENGINE FOKKER F27 F27MK400 4990626 EU RROYCE DART DART5327 54509 EU NACELLE FAILED W C E ABORTED TAKEOFF ENGINE SHUTDOWN M R OVER TEMP PARTIAL RPM/PWR LOSS TO TAKEOFF 1 CA 19130 2218 13185 (CAN) AS PILOT APPLIED TAKEOFF POWER THERE WAS A CHANGE IN NOISE PITCH & THEN A DROP IN POWER WAS NOTICED. AFTER POWER R EDUCED & TAKEOFF ABORTED E.G.T. WAS PEGGED. ENGINE SHUTDOWN & E.G.T. STARTED DROPPING. ENGINE HAD JUST BEEN INSTALLED & GROUND TESTED OK. CAUSE OF FAILURE UKN. TC: FOLLOW-UP / TEARDOWN REPORT EXPECTED FROM OPERATOR. 2 H 7 2 4T 4 T A817 E297 2000072800038 20000728 00038 SW 2000 7 28 CA000614008 1 20000520 G 6420 206016201131 BEARING BELL 206011810125 BELL 206 206L1 1182107 SW ALLSN 250C 250C30 03013 GL TAIL ROTOR FAILED W O OTHER O OTHER IN INSP/MAINT 1 CA 58600 A805 CAE895116 (CAN) AIRCRAFT WAS GROUND RUN TO GROUND IDLE. TAIL ROTOR PEDDLES STARTED TO STIFFEN UP. AS THE AIRCRAFT RPM WAS INCRE ASED TO 100 PERCENT NR, TAIL ROTOR PEDDLES STIFFENED TO BEYOND LIMITS APPROXIMATELY 35 POUNDS. FORCE REQUIRED TO MOVE T HE PEDDLES. AT THIS RPM, THE TAIL ROTOR SYSTEM WAS THOROUGHLY INSPECTED AND NO PROBLEMS FOUND. THE TAIL ROTOR BLADES WE RE REMOVED AND THE AIRCRAFT RUN UP TO 100 PERCENT WITH ONLY THE T/R HUB INSTALLED. THE PEDDLES MOVED FREELY WITH NO STI FFNESS. SPHERICAL BEARINGS REPLACED ON BOTH BLADES. AIRCRAFT RUN UP AND PEDDLES MOVED FREELY WITH NO STIFFNESS. BEARI NGS ARE AVAILABLE FOR INSPECTION. 1 G 7 1 3U 3 U H2SW E1GL 2000072800039 20000728 00039 EU 2000 7 28 CA000614009 1 20000522 G 2932 NE15BAT11TFGNOIR SWITCH 350A27055300 SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1B 6OO30 NE COLLECTIVE CRACKED W O OTHER O OTHER IN INSP/MAINT 1 CA 21150 341 (CAN) PILOT REPORTED THAT THE SWITCH WAS INTERMITTENT (HYDRAULIC CUT-OFF SWITCH ON COLLECTIVE STICK). 1 G 7 1 3U 3 U H9EU E19EU 2000080900012 20000809 00012 CE 2000 8 9 CA000614010 1 20000530 G 7603 S122225A THROTTLE CONTROL CESSNA STC207 CESSNA 207 207 2073602 CE CONT O550 IO550F 17042 SO THROTTLE CONTROL DEFECTIVE W K NONE O OTHER IN INSP/MAINT 1 CA 24600 20700228 284748R (CAN) AT SCHEDULED MAINTENANCE FUNCTION, THE THROTTLE CONTROL WAS FOUND TO BE DEFECTIVE. THE OUTER CASING (SHROUD) HAD S EPARATED AT A SWAGED FITTING NEAR THE ENGINE END. 1 H 7 1 3O 3 O A16CE E3SO 2000072800040 20000728 00040 SW 2000 7 28 CA000614011 1 20000427 G 6720 206001020045 PITCH LINK 206B BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL TAIL ROTOR UNSAFETIED W O OTHER W INADEQUATE Q C IN INSP/MAINT 1 CA 11200 3055 CAE270029 (CAN) DURING MAINTENANCE, PERFORMED BELOW THE ENGINE PAN, A TAIL ROTOR FLIGHT CONTROL BOLT WAS FOUND UNFASTENED. T/R AN TI-TORQUE CONTROL TUBE (ITEM NR 21, 206 IPC FIG.67-2) REAR ATTACHMENT BOLT FOUND WITH NUT BACKED OFF, NO COTTER PIN INST ALLED. AIRCRAFT GROUNDED AND ALL FLIGHT CONTROLS WERE INSPECTED FOR SAFETY. ONE MORE BOLT THAT ATTACHES THE T/R PITCH CONTROL ROD TO THE PITCH CONTROL LEVER WAS ALSO FOUND UN-SAFETIED WITHOUT A COTTER PIN SAFETING THE NUT/BOLT. A QUALIT Y CONTROL PROBLEM DURING RECENT A/C REBUILD IS SUSPECTED TO BE A FACTOR IN THE FINDINGS. THE OVERHAUL SHOP HAS BEEN MADE AWARE OF THE FINDINGS. 1 G 7 1 3U 3 U H2SW E4CE 2000080200001 20000802 00001 SW 2000 8 2 CA000614012 1 20000529 G 5320 206001734001101 BOLT BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL UPPER FUS AREA LOOSE W O OTHER W INADEQUATE Q C IN INSP/MAINT 1 CA 18200 CAE270029 (CAN) DURING A ROUTINE CLEANING BEHIND HAT RACK AREA, 2 BOLTS ATTACHING A SUPPORT ASSY (ITEM 34, 206 IPC FIG.67-2) WERE FOUND SIGNIFICANTLY LOOSE. AREA WAS INSPECTED FOR FURTHER DEFECTS, NONE FOUND. BOLTS WERE TIGHTENED PER BELL 206 MAINT ENANCE MANUAL. A QUALITY CONTROL PROBLEM DURING A/C REASSEMBLY FOLLOWING AN A/C ACCIDENT IS SUSPECTED TO BE THE CAUSE. THE OVERHAUL SHOP HAS BEEN MADE AWARE OF THE FINDINGS. 1 G 7 1 3U 3 U H2SW E4CE 2001031500181 20010315 00181 EU 2001 3 15 CA000614014 1 20000602 G 2742 1110043A3 ACTUATOR FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU STABILIZER CONTAMINATED W O OTHER J WARNING INDICATION AP APPROACH 1 CA 23959 (CAN) ON JUN 6/2000 MASTER FLT CAUTION LIGHT ILLUMINATED ALONG WITH BOTH UTILITY & FLT CNTL CHANNEL LIGHTS ON FLT CNTL P ANEL AS REORTED BY CREW INBOUND ALT ELECTRIC SYS POPPED CCT BREAKER TWICE UPON ACTIVATION. CREW THEN PROCEEDED AS PER C HECK LIST WITH JAMMED HORIZ STAB & A/C LANDED W/O INCID.. ENGINEERS INSPECT & PREP A/C FOR FERRY FLT TO YVR. MAINT INSP FOUND WATER CONTAMINATION IN STAB GEARBOX CLUTCHES. FLUID FLUSHED IN ACCORD WITH CRA TECHNICAL INFO BULLETIN F28-27-03R 2, SYS TESTED SEVERAL TIMES WITH HYDRAULIC POWER & STANDBY ELECT. POWER, NO FAULT FOUND. A/C INSP & FOUND SAFE FOR FERRY FLT TO YVR. YVR MAINTENACE REPLACING STAB ACTUATOR. 2 L 7 2 4F 4 F RT A20EU E2EU 2001032900021 20010329 00021 NE 2001 3 29 CA000614015 2 20000531 G 7532 118010502 HOUSING BELL 205 205A1 1181414 SW LYC T53 T5313B 41549 NE ACTUATOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) PART WAS SUSPECTED TO BE CRACKED DURING A DAILY INSPECTION OF THE AIRCRAFT. THE PART WAS MOVED FOR INVESTIGATION A ND THE CRACK FAILED. IF THE PART HAD FAILED IN FLIGHT IT WOULD HAVE CAUSED SEVERE COMPRESSOR STALLING OF THE ENGINE. 1 G 7 1 4U 4 U H1SW E17EA 2000080900019 20000809 00019 CE 2000 8 9 CA000614016 1 20000601 G 2510 04142221 FRAME CESSNA 040011887 CESSNA 150 150J 2071820 CE CONT O200 O200A 17020 SO AFT O/B LUG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 63250 619465A (CAN) DURING 100 HOUR INSPECTION, IT WAS DISCOVERED THAT THERE WERE 2 SMALL CRACKS ON THE FRAME REAR LUG THAT HOUSES THE ADJUSTING CAM FOR THE SEAT BACK. ONE CRACK WAS FOUND ATTHE LUG WELD WHILE THE OTHER WAS FROM THE HOLE FOR THE SHAFT ASS Y (0411105-1).IT WAS ALSO DISCOVERED THAT THE SHAFT ASSY ITSELF WAS CRACKED/SPLIT AT THE ENDS INCLUDING UNDER THE CAM. S EAT FRAME IS TO BE REPAIRED AND THE SHAFT ASSY REPLACED. 1 H 7 1 3O 3 O 3A19 E252 2000080900020 20000809 00020 GL 2000 8 9 CA000614017 3 20000602 G 6114 57B32518R HUB HARTZL CESSNA 206 U206G 2073356 CE HARTZL HCC3Y PHCC3YF1 GL CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 17230 EE2171A (CAN) FIELD MAINTENANCE FOUND SUSPECTED CRACK, N.D.T. CONFIRMED CRACK. HUB REPLACED, PROPELLER RETURNED TO SERVICE. 1 H 7 1 3O A4CE 5 C P25EA 2000071800240 20000718 00240 2000 7 18 CA000614018 4 20000605 G 2562 4000 ELT BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL ELT FAILED W O OTHER O OTHER IN INSP/MAINT 1 CA 406329 CAE834205 (CAN) DURING ANNUAL RECERTIFICATION, THE ELT WAS FOUND TO HAVE NO TRANSMIT POWER OUTPUT. THE UNIT WAS SENT BACK TO FOR REPAIR STATION. 1 G 7 1 3U 3 U H2SW E4CE 2001011105145 20010111 05145 EA 2001 1 11 CA000614019 1 20000606 G 5741 C2FS209 STRUT DHAV DHC2 DHC2MK1 2800102 EA PWA R985 R985AN14B 52008 NE MLG CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA JP211236 (CAN) DURING INSPECTION AS DIRECTED BY CF-98-37R1, THE STRUTS WERE FOUND BEYOND THE LIMIT SET BY THE AD. BOTH LEFT AND RIGHT STRUTS ARE BEING REPLACED. 1 H 7 1 3R 3 R A806 5E1 2000080900021 20000809 00021 CE 2000 8 9 CA000614022 1 20000523 G 7120 265102215 RING ASSEMBLY CESSNA 265102319 CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE RT LWR CORNER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 20800 1032 PCE19415 (CAN) DURING HOT SETION INSP PROCEDURES OF A/C ENGINE. ROUTINE INSP OF ENG MOUNT REVEALED A ONE INCH LONG CRACK IN ENG M OUNT RING LOWER (AFT) CORNER, RT SIDE. CRACKING OF RING SUBJECT OF AWD 90-05-04 AND CESSNA S/B CAB 88-14 INVOLVING A/C S /NS 208B0001 THRU S/N 208B0086, AND IS NOT APPLICABLE TO THIS A/C S/N - HOWEVER, SINCE WE ARE CONSTANTLY FLYING INTO OIL /MINING COMPANY UNIMPROVED STRIPS, COMPANY INTERNAL INSP PROCEDURES INCLUDE REPETITIVE, DETAILED INSPS OF ENGINE MOUNT A ND ACCELERATED OVERHAUL PERIODS FOR NOSE LDG GEAR SHIMMY DAMPER. ENGINE MOUNT RING REMOVED FOR REPAIR AND OVERHAUL. 1 H 7 1 3T 3 T A37CE E4EA 2000082200033 20000822 00033 SO 2000 8 22 CA000614023 1 20000602 G 5311 1220502 CHANNEL PIPER PIPER PA18 PA18150 7101828 SO LYC O320 O320A2B 41508 EA CHANNEL CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 35810 187290 L597427A (CAN) DURING INSPECTION, CRACK WAS FOUND ON ONE VERTICAL MEMBER FROM CHANNEL. WHEN THE RIGHT HAND WING WAS REMOVED TO C ARRY OUT REPAIR, THE WELDS ON THE ADJACENT VERTICAL MEMBER WAS FOUND TO BE CRACKED. ALSO THE WELD AT THE FRONT OF THE UP PER DOOR CHANNEL WAS FOUND CRACKED. CRACKS WERE REPAIRED BY WELDING AND THE AIRCRAFT WAS RETURNED TO SERVICE. 1 H 7 1 3O 3 O 1A2 E274 2000080900022 20000809 00022 CE 2000 8 9 CA000614024 1 20000505 G 5210 12170534 HANDLE CESSNA 206 U206F 2073333 CE CONT O520 IO520F 17032 SO SPLINE OF DOOR DAMAGED W A UNSCHED LANDING D INFLIGHT SEPARATION CL CLIMB 1 CA U20602938 286376R (CAN) PILOT CLOSED DOOR WITH HANDLE SELECTED TO THE CLOSED POSITION, HOWEVER, HANDLE WAS PARTIAL STRIP ON INSIDE GEARIN G, AND DOOR WAS NOT FULLY LOCKED. MAINTENANCE REPLACED DOOR HANDLE WITH SERVICEABLE HANDLE AND RETURNED THE AIRCRAFT TO SERVICE. 1 H 7 1 3O 3 O A4CE E5CE 2000080900023 20000809 00023 SO 2000 8 9 CA000614025 2 20000526 G 8530 TM639272 CYLINDER CESSNA 185 A185F 2072821 CE CONT O520 IO520D 17032 SO MCAULY 2A34C D2A34C58 GL CYLINDER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 221410 781584 (CAN) CRACK BETWEEN SPARK PLUG AND EXHAUST PORT. 1 H 7 1 3O 3 O 3A24 E5CE 5 C P3EA 2000080900024 20000809 00024 EA 2000 8 9 CA000614026 2 20000601 G 7532 310082903 BLEED VALVE PWA PIPER PA31T PA31T 7103124 SO PWA PT6 PT6A28 EA BLEED VALVE FAILED W E ENGINE SHUTDOWN R PARTIAL RPM/PWR LOSS DE DESCENT 1 CA 41900 PCE50216 (CAN) DURING FINAL POWER REDUCTION ON LANDING IN YYC, THE RIGHT ENGINE DEVELOPED SYMPTOMS OF COMPRESSOR STALL . ENGINE W AS SHUTDOWN AND SECURED. AIRCRAFT LANDING UNEVENTFUL. MAINTENANCE DISCOVERED ENGINE VALVE REPLACED WITH SERVICEABLE U NIT. ENGINE GROUND RUN C/O PERFORMANCE SATISFACTORY. 1 L 7 2 3T 4 T A8EA E4EA 2000081000001 20000810 00001 SO 2000 8 10 CA000614027 1 20000602 G 2120 4998903 CLAMP PIPER PA31T PA31T 7103124 SO PWA PT6 PT6A28 EA TUBE CLAMP STRAP IMPROPER PART W B EMER. DESCENT W INADEQUATE Q C CR CRUISE 1 CA P50694 (CAN) AIRCRAFT LOST CABIN PRESSURE WHILE IN CRUISE AT FL 210. PILOT DESCENDED AND RETURNED TO BASE. MAINTENANCE DISCOV ERED AIR DISTRIBUTION TUBE (P/N 46504-00) AND HOSE (P/N 49990-06) CONNECTION HAD COME APART. FURTHER INVESTIGATION DETER MINED THE WRONG SIZE STRAP HAD BEEN INSTALLED UNDER THE CLAMP THAT SECURES THE HOSE/TUBE CONNECTION. THE SUSPECT STRAP I S USED ON THE PARALLEL TUBE ADJACENT TO THE FAILED CONNECTION. THIS PARALLEL TUBE HAD ONE INCORRECT STRAP INSTALLED AS W ELL. STRAPS SWITCHED TO PROPER TUBE/HOSE ASSEMBLIES AND TIGHTENED. NOTE: CAUTION WHEN REMOVING BOTH TUBES AT SAME TIME TO PREVENT INCORRECT STRAP INSTALLATION. 1 L 7 2 3T 4 T A8EA E4EA 2000081700011 20000817 00011 EU 2000 8 17 CA000614030 1 20000604 G 2910 9738114306 PRESSURE SWITCH 5291312004 PILATS PC12 PC1245 EU PRESSURE SWITCH FAILED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN THE HIGH PRESSURE CONDITION COULD NOT BE DUPLICATED IN THE HANGAR. THE PREVIOUS DAYS FLYING WAS A TRIP FROM ST. J OHNS TO GOOSE BAY, 2 HRS AT FL 280 AND -45 DEGREES. SUSPECT THE HYD SYSTEM, UPON BEING SUPER CHILLED AT ALTITUDE, IS C AUSING THE OVER PRESSURE CONDITION. SYSTEM PRESSURE SWITCH AND POWER PAC IS LOCATED IN LEFT WING ROOT. SYSTEM RECHARGE S IN FLIGHT WHEN COMMANDED BY THE SYSTEM PRESSURE SWITCH. WHEN RECHARGING AT THESE TEMPS IT IS SUSPECTED THAT THE PRESS URE SWITCH BECOMES LAZY DUE TO THE TEMPERATURE AND VISCOSITY OF THE HYDRAULIC SYSTEM. THERE IS NO OVER PRESSURE INDICAT ION ON THE FLIGHT DECK. WILL MONITOR THE SYSTEM IN FUTURE TO SEE IF THE OVER PRESSURE CONDITION CAN BE DUPLICATED. 1 L 7 1 3T RT A78EU 2001031500183 20010315 00183 SO 2001 3 15 CA000614031 1 20000602 G 7931 ENGINE LKHEED 382 382G 526414U SO ALLSN 501D 501D22A 03006 GL HAMSTD 54H 54H60117 NE NR 3 MALFUNCTIONED W E A ENGINE SHUTDOWN UNSCHED LANDING N FALSE WARNING CR CRUISE 1 CA 550859 2303445 (CAN) ENROUTE LOUISVILLE KY FROM YGQ DURING MODERATE TURBULENCE THE NR 3 ENGINE HAD LOW ENGINE OIL PRESSURE INDICATION. THE ENGINE WAS SHUT DOWN AND THE AIRCRAFT CONTINUED TO DESTINATION. INVESTIGATION FOUND NO FAULT & GROUND RUN RESULTS WE RE NORMAL. THE AIRCRAFT RETURNED TO YGQ WITH NO FURTHER DIFFICULTY. NO SOURCE FOR THIS ANNOMOLY HAS BEEN DETERMINED. 2 H 7 4 4T 4 T A1SO E282 6 C P906 2001011105147 20010111 05147 EA 2001 1 11 CA000614033 1 20000610 G 2720 C3CF1314 PEDAL DHAV DHC3 DHC3 2800202 EA PWA PT6 PT6A34 52043 EA RUDDER CONTROL BROKEN W D RETURN TO BLOCK F FLT CONT AFFECTED TX TAXI/GRND HDL 1 CA PCE40906 (CAN) WHILE TAXIING ON THE WATER IN STRONG WIND CONDITIONS, PILOT LOST RIGHT RUDDER CONTROL. PART WAS REPLACED. AIRCR AFT WAS RETURNED TO SERVICE. 1 H 7 1 3R 4 T A815 E4EA 2001011105148 20010111 05148 EA 2001 1 11 CA000614034 1 20000611 G 5753 C3WF46 RIB DHAV C3WF527 DHAV DHC3 DHC3 2800202 EA PWA PT6 PT6A27 52043 EA LT WING FAILED W K NONE O OTHER IN INSP/MAINT 1 CA PCE40691 (CAN) WHILE THE AME WAS CARRYING OUT A 100 HOUR INSPECTON OF THE LT WING FLIGHT CONTROLS, NOTICED THERE WAS A SMALL CRAC K ON THE TOP SKIN AND SEVERAL SHEARED RIVETS. THE FLAP WAS REMOVED, DISASSEMBLED AND INSPECTED. IT WAS FOUND THAT THE INTERNAL RIB P/N C3WF46 WAS SHATTERED. THE RIB WAS REPLACED, THE FLAP REASSEMBLED, REPAIRED AND RETURNED TO SERVICE. CO ULD FIND NO APPARENT REASON FOR THE CAUSE OF THIS FAILURE. 1 H 7 1 3R 4 T A815 E4EA 2000081700012 20000817 00012 CE 2000 8 17 CA000614036 1 20000614 G 2740 505244953 WIRE 995240554 BEECH 100 A100 1152915 CE PWA PT6 PT6A28 EA THROUGH DASH BROKEN W A D UNSCHED LANDING RETURN TO BLOCK F FLT CONT AFFECTED CL CLIMB 1 CA PCE41799 (CAN) AIRCRAFT DEPARTED AND SHORTLY AFTER TAKEOFF, THE MAIN STABILIZER TRIM FAILED. AIRCRAFT RETURNED TO BASE. A WIRE W AS FOUND BROKEN ON THE COPILOT''''S SIDE WHERE THE WIRE GOES THROUGH THE DASH. WIRE REPAIRED AND AIRCRAFT RELEASED TO S ERVICE. 1 L 7 2 3T 4 T A14CE E4EA 2001011105021 20010111 05021 NM 2001 1 11 CA000614038 1 20000427 G 5210 85210195001 HANDLE DHAV DHC8102 DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE PAX DOOR FAILED W O OTHER J WARNING INDICATION DE DESCENT 1 CA 052 (CAN) DURING DESCENT AT FLIGHT IDLE THE CABIN DOOR HANDLE MOVED TO THE MID POSITION WHICH IN TURN COLLAPSED THE DOOR SEA L FOLLOWED BY A WHISTLING NOISE AND CABIN DEPRESSURIZATION. WITHOUT CONSULTING WITH THE FLIGHT CREW THE CABIN ATTENDANT PUSHED THE HANDLE TO THE CLOSED POSITION SEAL INFLATED AND CABIN PRESSURE RETURNED TO NORMAL. AIRCRAFT LANDED WITHOUT IN CIDENT. DOOR MECHANISM RIGGING WAS CARRIED OUT AS PER THE AMM. FUNCTIONAL CHECKS DONE. AIRCRAFT RETURNED TO SERVICE. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2000081700013 20000817 00013 CE 2000 8 17 CA000614039 1 20000511 G 2612 99120363 SENSOR MACCHI 99120363 CESSNA 500 500CESSNA 2076602 CE LT ENGINE CHAFED W O OTHER N FALSE WARNING CL CLIMB 1 CA 23350 (CAN) AIRCRAFT WAS RUNNING ON GROUND FOR APPROX 30-40 MINUTES PRIOR TO DEPARTURE. UPON CLIMB OUT, LT ENGINE FIRE LIGHT FLICKERED AND STAYED EXTINGUISHED. AIRCRAFT CONTINUED FLIGHT WITH NO FURTHER OCCURRENCE. ENGINE WAS GROUND RUN TO CHEC K FOR BLEED AIR LEAKS AND NONE WERE FOUND. FIRE WIRE INSPECTED AND FOUND CHAFED NEARLY IN HALF, BEHIND INBOARD BLEED A IR COUPLER. SYSTEM STILL WAS ABLE TO SELF-TEST OK. SUSPECT THE LACK OF MATERIAL ON THE FIRE WIRE CAUSED LIGHT TO ILLUM INATE EARLIER THAT NORMAL. ULTIMATELY THE ENTIRE FIRE WIRE WAS REPLACED. 1 L 7 2 4F A22CE 2000082200034 20000822 00034 EU 2000 8 22 CA000614040 2 20000607 G 7414 996538 STATOR ROTAX DIAMON DA20 DA20A1 GL ROTAX 912 ROTAX912 55555 EU PICK UP COIL FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 48400 4380628 (CAN) DURING MAINTENANCE GROUND RUN, TROUBLESHOOTING COULD NOT CORRECT ROUGH RUNNING ENGINE BY MANUAL (TECH) PROCEDURES. FURTHER INSPECTION SHOWED DETERIORATING STATOR PICKUP COIL AND SHROUD PER PREVIOUS SDR 2000505014 RE:SB 98-9R-026R3. FAILURE OF CONPONENT IN-FLIGHT WILL PREVENT ENGINE RE-STARTING DURING EMERGENCY PROCEDURES. AD 98-912-026R3 REFERS 1 L 7 1 3O 3 I NT TA4CH EXPE3I 2000081700014 20000817 00014 EA 2000 8 17 CA000614041 3 20000602 G 6111 BLADE BEECH 23 C23 1151242 CE SNSNCH 76E 76EM8 EA AT 34.20 STA INACCURATE W O OTHER O OTHER IN INSP/MAINT 1 CA 10600 7625K (CAN) DIMENSIONAL CHECK, FOUND PROPELLER TO BE JUST UNDER MINIMUM ALLOWABLE THICKNESS AT THE 34.20 INCH STATION. PROPEL LER RETIRED FROM SERVICE. 1 L 7 1 3O A1CE 5 N P4EA 2000081700017 20000817 00017 CE 2000 8 17 CA000614045 1 20000526 G 2720 NAS697A3 NUT CESSNA 150 150A 2071804 CE CONT O200 O200A 17020 SO MCAULY 1A100 1A100MCM GL RUD STOP BOLT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 22460 25741A F4459 (CAN) AIRCRAFT WAS INSPECTED AS A RESULT OF SDR AL-2000-04. ANCHOR NUT FOR RUDDER STOP BOLT FOUND CRACKED. 1 H 7 1 3O 3 O 3A19 E252 5 N P918 2000081700018 20000817 00018 EU 2000 8 17 CA000614046 1 20000526 G 2810 PC642031L FUEL TANK RHNFLU EXT300 EA300L 70218DG EU LYC O540 AEIO540L1B5 41532 NE RT SIDE WELD CRACKED W K NONE B K SMOKE/FUMES/ODORS/SPARKS FLUID LOSS IN INSP/MAINT 1 CA 78400 L2594848A (CAN) FUEL TANK CRACKED ALONG SIDE WHERE WELDED. AUTOMATIC FUEL CATCH SHIELD DID NOT WORK AND GAS DRIPPED INTO CABIN NO T OVERBOARD AS SUPPOSED TO. 1 M 7 1 3O 3 O NC EA67U 1E4 2000081700019 20000817 00019 EA 2000 8 17 CA000614047 3 20000608 G 6111 PROPELLER PIPER PA38 PA38112 7103812 SO LYC O235 O235L2C 41505 EA SNSNCH 72C 72CK EA L/E & FACE CORRODED W O OTHER O OTHER IN INSP/MAINT 1 CA 66530 L2240115 K2857 (CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. 1 L 7 1 3O 3 O A18SO E223 5 N P9045 2000083100911 20000831 00911 2000 8 31 CA000614057 4 20000602 G 3422 1426200113 GYRO EDOAIREXXXXX H000B12 PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA INSTRUMENT PANEL FAILED W O OTHER O OTHER CR CRUISE 1 CA 33200 65247 L159368A (CAN) WHEN RE-SETTING COURSE, PILOT HAD LET-GO SETTING KNOB WHICH SNAPPED BACK IN PLACE. LATER DIRECTIONAL GYRO WOULD NOT FOLLOW COURSE CHANGE UNLESS PILOT HELD KNOB PULLED OUT. EVIDENTLY, KNOB SPRING BROKE INSIDE. INSTRUMENT TECHNICIA N STATED KNOB SHOULD NOT BE LET GO TO SNAP IN BUT BE FOLLOWED IN. 1 L 7 2 3O 3 O A20SO E14EA 2000083100912 20000831 00912 SO 2000 8 31 CA000614058 1 20000606 G 2823 400440 BOLT DUKES 3487001 PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA LT WING ROOT JAMMED W O OTHER E VIBRATION/BUFFET TX TAXI/GRND HDL 1 CA 12455 L159368A (CAN) PILOT REPORTED LT FUEL SELECTOR STIFF AND JAMMING ON INBD TANK AT PRE-TAKEOFF CHECK. WITH ENOUGH PRESSURE, SELECT OR COMPLETED TRAVEL, PILOT CHECKED OPER OF ENGINE, INBD, OTBD, POSITIONS AND IN OFF, SEVERAL TIMES PRIOR TO ELECT TO TAK EOFF AND REPORTED SNAG IN LOG AND VERBAL DEBRIEFING AT ARRIVAL. CORRECTIVE ACTIONS TAKEN IMMEDIATELY. ACCESS PANEL OFF , OPER OF SELECTOR SHOWED STIFF AT SOME TRAVEL POINT 2 TIMES OUT OF 3. POSSIBLE JAMMING. FOUND BOLT NR 400-440 (AN3-6A ), AT TIMES, CHAFING ON SELECTOR CASING ASSY SCREW HEAD. FOUND WASHER BETWEEN CABLE TERMINAL NR 44668-000 (MS20668-4) A ND SELECTOR ARM, WORN RENDERING BOLT TOO LONG ON NUT SIDE. ALSO, OTHER 2 WASHERS IN WRONG SEQUENCE. RE-INST NEW HDWE. 1 L 7 2 3O 3 O A20SO E14EA 2001031900067 20010319 00067 CE 2001 3 19 CA000614059 1 20000614 G 3020 1299700321 TUBE BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE DE-ICE SYSTEM CRACKED W O OTHER J WARNING INDICATION CR CRUISE 1 CA 9037 (CAN) RT BLEED AIR FAIL WARNING LIGHT COME ON DURING FLIGHT. AFTER INVESTIGATION WE FOUND THAT LINE P/N 129-970032-1 WAS CRACKED AT WELDING JOINT OF THREADED FITTING. 2 L 7 2 4T 4 T RT A24CE E26NE 2001031900068 20010319 00068 EA 2001 3 19 CA000614060 1 20000530 G 2612 356024310 FIRE LOOP CNDAIR CL600 CL6002B19 EA LT ENGINE FAILED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) SHORTLY AFTER TAKE-OFF EICAS WARNING 14TH STAGE DUCT APPEARED.LT ENGINE WAS SHUTDOWN IN FLIGHT.AIRCRAFT RETURN TO LAND.LT ENGINE 14TH STAGE HEAT SENSING ELEMENT REPLACED.NOTE: LT ENGINE WAS NOT SHUTDOWN IN FLIGHT AS REPORTED. DATE 17 JUNE 2000. 2 L 7 2 4F RT A21EA 2001031900075 20010319 00075 EA 2001 3 19 CA000614061 1 20000611 G 2612 35602310 FIRE LOOP CNDAIR CL600 CL6002B19 EA LT ENGINE FAILED W E A ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) DURING CLIMB, PILOT REPORTED L 14TH DUCT MESSAGE. EMERGENCY PROCEDURES CARRIED OUT AS PER AFM, WARNING PERSISTED. PILOT SHUT DOWN THE ENGINE AS PER AFM & PERFORMED AN UNEVENTFUL SINGLE ENGINE LANDING IN VIE, SINGLE ENGINE FLIGHT LASTE D 15 MINUTES. MECHANICS FOUND A FAILED LOOP WHICH WAS REPLACED. 2 L 7 2 4F RT A21EA 2001031900076 20010319 00076 EA 2001 3 19 CA000614062 1 20000611 G 7900 6018T30P06 CARBON SEAL CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE TURBINE DISK FAILED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA 10423 (CAN) DURING A FLIGHT, THE CREW NOTICED A FUEL/OIL ODOR IN THE COCKPIT. IT WAS ALSO NOTICED IN THE CABIN WHILE ON THE GR OUND. THE NR 1 CARBON SEAL WAS REPLACED. THE FAN DISK ASSEMBLY P/N 6078T57G04, S/N GEE0893 WAS REPLACED (TSN: 10423.9, C NS: 9754). 2 L 7 2 4F 4 F RT A21EA E15NE 2000092100001 20000921 00001 SO 2000 9 21 CA000614063 1 20000607 G 3230 41789000 BOLT PIPER PA31T PA31T1 7103126 SO PWA PT6 PT6A11 52043 NE UPPR DNLK HK ROD SHEARED W O OTHER O OTHER IN INSP/MAINT 1 CA PCE10037 (CAN) UPON MAKING A QUICK/INSPECTION OF THE MAIN GEAR DRAG BRACES AND RODS, FOUND EXCESSIVE PLAY IN THE DOWNLOCK ROD AT THE CLEVIS BOLT. THE RT CLEVIS BOLT P/N 41789-000 WAS FOUND SHEARED; AND THE LT CLEVIS WORN ON ITS WAY TO SHEARING. 1 L 7 2 3T 3 T A8EA E4EA 2000072000235 20000720 00235 NE 2000 7 20 CA000614064 2 20000614 G 7250 M031070 TURBINE SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1B 6OO30 NE FUEL INJECT FAILED W O OTHER O OTHER TO TAKEOFF 1 CA 59300 7984810 786 (CAN) DURING START PROCEDURE STARTER WAS UNABLE TO MOTOR ENGINE. AFTER INSPECTING ENGINE FOR F.O.D. AND REMOVING COMPON ENTS ON THE ACCESSORY GEARBOX,, ENGINE WAS DISMANTLED TO ISOLATE THE LOCK UP. LOCK UP WAS FOUND TO BE IN THE GAS PRODU CER ASSEMBLY (M024M03). ASSEMBLY WAS SENT TO REPAIR CENTER WHERE IT WAS FOUND TO BE FUEL COKING ON THE LABYRINTH SEALS OF THE CENTRIFUGAL INJECTION WHEEL. 1 G 7 1 3U 3 U H9EU E19EU 2001031900079 20010319 00079 NM 2001 3 19 CA000621004 1 20000615 G 7830 SWITCH BOEING 737 737217 1384464 NM PWA JT8 JT8D17 52049 NE THRUST REVERSER FAILED W C ABORTED TAKEOFF O OTHER TO TAKEOFF 1 CA (CAN) ON TAKE, THRUST REVERSER ISOLATION VALVE WARNING LIGHT ILLUMINATED. RETURNED TO YYZ. THRUST REVERSERS OPERATED AS PER WORK CARD 1187, COULD NOT DUPLICATE DISCREPANCY. REPLACED NR 1 AND 2 THRUST REVERSER PRESSURE SWITCHES PER MM 78-31- 16. OVERWEIGHT LANDING CHECK COMPLETED AS PER FLYAWAY MANUAL PAGE 02.01.01, NO FAULTS NOTED. 2 L 7 2 4F 4 F A16WE E2EA 2001032900023 20010329 00023 NM 2001 3 29 CA000621005 1 20000617 G 2420 OIL COOLER BOEING 737 737275 1384485 NM PWA JT8 JT8D9A 52048 NE NR 2 CSD FAILED W E ENGINE SHUTDOWN J WARNING INDICATION CR CRUISE 1 CA 40768 37820 (CAN) A/C 759, , FLT 195, NR 2 CSD DISCONNECTED DUE LOW OIL PRESSURE LIGHT CAME ON. REPLACED NR 2 CSD OIL COOLER DUE CO OLER BLOCKED BY PIECES OF FAN DIFUSER DUCT LINING, THAT HAD BROKEN UP. REPLACED NR 2 ENGINE AS PER WORK CARD 1125-2, 2 L 7 2 4F 4 F A16WE E2EA 2001032900025 20010329 00025 NE 2001 3 29 CA000621008 2 20000607 G 7321 324476810 BEARING BENDIX 324476810 BEECH 200 B200 1152922 CE PWA PT6 PT6A42 52043 NE FUEL CONTROL SEIZED W E A ENGINE SHUTDOWN UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA 2624 A69446 (CAN) DURING CRUISE RT ENGINE FLUXUATES ALL PARAMETERS THAN DROPS TO GROUND IDLE. UNEVENTFUL LANDING. T/S P3,PY ALL SYST EM FOR LEAKS AND OR BLOCKAGE - NONE FOUND. PULLED FCU AND FOUND DRIVE BEARING SEIZED AND DRIVE COUPLER BROKEN. 1 L 7 2 4T 4 T A24CE E4EA 2000092100002 20000921 00002 EA 2000 9 21 CA000621009 1 20000610 G 5740 C6TFM1022 ATTACH FITTING DHAV DHAV DHC6 DHC6200 EA PWA PT6 PT6A20 52043 EA BOTTOM PLATE CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 176 PCE20768 (CAN) LEVEL 3 CORROSION FOUND ON PLATE BETWEEN ATTACH POINTS. 1 H 7 2 3T 3 T A9EA E4EA 2001032900026 20010329 00026 EU 2001 3 29 CA000621010 2 20000601 G 8520 BEARING ROTAX 912F3 DIAMON DA20 DA20A1 GL ROTAX 912 ROTAX912 55555 EU ENGINE MAIN MAKING METAL W K NONE O OTHER IN INSP/MAINT 1 CA 1790 4380740 (CAN) UPON REGULAR 200 HR ON CONDITION INSP, STEEL & ALUMINUM, BABBITT PARTICLES FOUND IN OIL & FILTER. PISTONS & CYLIND ERS PULLED & INSP. NO EVIDENCE OF PART FAILURE: GEARBOX REMOVED, SLIGHT FRETTING OF VALLEYS ON DOGS - ADJUSTED FRICTION. ENGINE RE-ASSEMBLED & FLOWN DUAL LCL ONLY FOR 5 HRS ON ADVICE OF DIRECTOR OF MAINT OF ROTAX CANADA. AFTER 5 HRS FLT A/ C ENGINE INSP METAL. MOSTLY BABBITT & ALUMINUM FOUND IN OIL & OIL FILTER. ENGINE REMVD & SENT TO ROTAX IN VERNON. UPON THEIR INSP CRANKSHAFT MAIN CTR BEARING & CRANKSHAFT MAIN CTR SURFACE WHERE WEARING, EXCEPT FOR METAL. FOUND DURING INS P, ENGINE RAN & TESTED WITHIN ALL SPECIFIED PARAMETERS. OVERHAULED ENGINE WILL BE INSTALLED. 1 L 7 1 3O 3 I NT TA4CH EXPE3I 2001031900080 20010319 00080 EU 2001 3 19 CA000621011 1 20000616 G 3244 5504632 TIRE FOKKER F28 F28MK1000 4990808 EU MLG FAILED W A UNSCHED LANDING D N INFLIGHT SEPARATION FALSE WARNING CL CLIMB 1 CA (CAN) THE PILOT OF CRA A/CRPTED LT INBOARD MAIN WHEEL TIRE ASSY BLEW ON ROTATION OUT OF QUE CITY, QUE &GEAR SAFE IND. LI GHT WENT OUT. MAINT CNTL TROUBLESHOT PROBLEM WITH FLT CREW BUT WERE UNABLE TO GET LEFT MAIN GEA R TO INDICATE DOWN & LOC KED.THE DECISION MADE TO DIVERT A/C TO MONTREAL (YUL) WHERE EMERG LDG CARRIED OUT - AFTER BURNING OFF EXCESS FUEL. A/C L ANDED W/O INCIDENT, PASSENGERS WERE DEPLAINED & TRANSPORTED TO TERMINAL BY BUS. INIT MAINT INSP REVEALED RETREAD ON NR 2 TIRE HAD LET GO, TIRE ASSY STILL AT 100 PSI. MAINT INST THEG EAR PINS, CHANGED NR 1 & 2 TIRES (P/N 9550463-2) & FERRIED A/C TO TORONTO (YYZ). FURTHER INSPECTION IN YYZ REVEALED DAMAGE TO LT SIDE. 2 L 7 2 4F RT A20EU 2001031900081 20010319 00081 SO 2001 3 19 CA000621012 1 20000607 G 2721 63457003 ARM PIPER PA32 PA32300 7103212 SO LYC O540 IO540K1A5 41532 EA RUDDER CONTROL FAILED W D RETURN TO BLOCK F FLT CONT AFFECTED LD LANDING 1 CA 2256 L1253048 (CAN) - PILOT REPORTED POOR LT AUTHORITY ONLANDING, UNABLE TO TRIM. - INSPECTION FOUND THE TAB THAT RUDDER TRIM CONTROL ATTACHES TO AN ARM ASSEMBLY P/N 63457-003, WAS TORN OUT OF THE TUBE. 1 L 7 1 3O 3 O A3SO 1E4 2001031900082 20010319 00082 SO 2001 3 19 CA000621013 1 20000612 G 2913 1213HBG310A PUMP PIPER PA31 PA31 7103102 SO HARTZL HCC4Y HCC4YR2 GL HYD SYSTEM DEFECTIVE W K NONE O OTHER IN INSP/MAINT 1 CA 193 FH271 (CAN) LANDING GEAR SELECTOR HANDLE WOULD NOT RETURN TO NEUTRAL DURING ENGINE SHUTDOWN CHECK. NEW HYDRULIC PUMP INSTALLED AND LANDING GEAR SELECTOR CHECK FUNCTIONED NORMALLY. SUSPECT LOW VOLUME AND/OR PRESSURE OUTPUT FROM REMOVED PUMP. DEFEC TIVE PART RETURNED TO MFR. FOR WARRANTY CONSIDERATION. HYDRAULIC PUMP DISCHARGE FILTER DID NOT SHOW ANY SIGN OF METAL CO NTAMINATION. 1 L 7 2 3O A20SO 5 C P52GL 2001032900027 20010329 00027 CE 2001 3 29 CA000621014 1 20000407 G 7120 05510171 MOUNT CESSNA 172 172L 2072432 CE LYC O320 O320E2D 41508 EA MCAULY 1C160 1C160CTM GL ENGINE BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ON ROUTINE 100 HOUR INSPECTION LT VERTICAL TUBE ON ENGINE MOUNT WAS FOUND BROKEN.FURTHER INVESTIGATION FOUND THAT THIS AIRCRAFT HAD HAD A LONG HISTORY OF NOSE WHEEL SHIMMY. OVERHAULED ENGINE MOUNT AND SERVICING OF SHIMMY DAMPER, FIXED THE PROBLEMS. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2001031900087 20010319 00087 CE 2001 3 19 CA000621015 1 20000324 G 3411 STATIC LINE CESSNA 172 172L 2072432 CE LYC O320 O320E2D 41508 EA MCAULY 1C160 1C160CTM GL PITOT/STATIC SYS KINKED W A UNSCHED LANDING O OTHER CL CLIMB 1 CA L3063527A 710364 (CAN) THE AIRSPEED INDICATOR HAD BEEN REMOVED FOR MAINTENACE, AND RE-INSTALLED. SUPPOSEDLY A PITOT/STATIC TEST WAS CARRI ED OUT, AND SIGNED FOR. AIRCRAFT WHEN ON INITIAL FLIGHT AND AIRSPEED & ALTIMETER DID NOT FUNCTION.THE CAUSE OF THE PROBL EM WAS THAT, THE STATIC LINE TO AIRSPEED WAS TOTALLY KINKED OFF. THE LINE WAS REPAIRED WITH A SATISFACTORY PITOT/STATIC TEST BEING CARRIED OUT. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2001031900088 20010319 00088 CE 2001 3 19 CA000621016 1 20000531 G 7810 991029910 ELBOW CESSNA 340 340A 2076405 CE CONT O520 TSIO520NB 17040 SO EXHAUST CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 1371 521338 (CAN) MINOR HEAT STRESS CRACK ADJACENT TO EXISTING SEAM WELD. 1 L 7 2 3O 3 O 3A25 E8CE 2001031900092 20010319 00092 SO 2001 3 19 CA000621020 1 20000612 G 2620 7395603 SWITCH PIPER PA42 PA42720 7104212 SO PWA PT6 PT6A61 52043 EA EXTINGUISHER FAILED W E F ENGINE SHUTDOWN ACTIVATE FIRE EXT. N FALSE WARNING CR CRUISE 1 CA 5222 PCE99130 (CAN) PILOT EXPERIENCED RIGHT ENGINE FIRE WARNING AND MASTER CAUTION ANNUCIATORS. ENGINE WAS SHUTDOWN BY CHECKLIST AND R E FIRE BOTTLE DISCHARGE SWITCH ACTIVATED. LANDING C/O UNEVENTFUL. MAINTENANCE DETERMINED ENGINE FIRE WARNING WAS FALSE A ND THAT THE FIRE BOTTLE DID NOT DISCHARGE. INSPECTION REVEALED THE CONNECTOR HAD SEPARATED ON THE BACK OF THE FIRE EXTIN GUISHER SWITCH ASSEMBLY. NO CAUSE OF THE FALSE FIRE WARNING COULD BE DETERMINED AS ALL PROBES TESTED IN SPEC. WIRING HAR NESS INSPECTED SERVICEABLE AND GROUND RUNS SATISFACTORY. FIRE EXTINGUISHER SWITCH CONNECTOR ATTACHED AND SECURED. TEST F LIGHT C/O SATISFACTORY, AIRCRAFT RELEASED. 1 L 7 2 4T 4 T A23SO E4EA 2000092100003 20000921 00003 CE 2000 9 21 CA000621021 1 20000610 G 3240 1280506130 LINE CESSNA 207 207A 2073604 CE CONT O520 IO520A 17032 SO R/H BRAKE LINE CHAFED W D RETURN TO BLOCK K FLUID LOSS TX TAXI/GRND HDL 1 CA 112560R (CAN) DURING TAXI, THE PILOT NOTICED THE RT BRAKE HAD LESS PRESSURE THAN THE LT. AIRCRAFT RETURNED TO BLOCKS,. INVESTIG ATION REVEALED THAT THE RT BRAKE LINE HAD BEEN CHAFED BY A FAIRING SCREW AND WAS LEAKING. BRAKE LINE REPLACED, SHORTER SCREWS INSTALLED IN FAIRING. 1 H 7 1 3O 3 O A16CE E5CE 2000092100004 20000921 00004 SO 2000 9 21 CA000621022 1 20000609 G 3250 1505800002 GEAR 1521500001 EMB 110 EMB110P1 3260122 SO PWA PT6 PT6A34 52043 EA SECTOR GEAR FAILED W O OTHER O OTHER LD LANDING 1 CA PCE56711 (CAN) PILOT REPORTED A WOBBLY NOSE GEAR SHIMMY ON LANDING ROLL-OUT WITH LIMITED RT TURNING CAPACITY. MAINTENANCE FOUND TEETH MISSING OFF THE SECTOR GEAR JAMMING ON THE RACK FOR LIMITED TRAVEL WITH A GAP IN THE CENTER CAUSING THE SEVERE SHI MMY. THE GEAR WAS DISMANTLED, CLEANED WITH A SERVICEABLE SECTOR GEAR INSTALLED. REGREASED ASSEMBLED AIRCRAFT TO BE FE RRY FLOWN TO YTH FOR PERMANENT REPAIRS. POSSIBLE CAUSE, TAXIING ONE ENGINE OR TOWING CONNECTED, HOWEVER, NOTHING REPORT ED. 1 L 7 2 4T 4 T A21SO E4EA 2001032900029 20010329 00029 EA 2001 3 29 CA000621024 1 20000621 G 2720 C3CF1314 LEVER DHAV DHC3 DHC3 2800202 EA RUDDER PEDAL CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHILE CARRYING OUT A 100 HOUR INSPECTION ON THE RUDDER PEDALS THE ENGINEER FOUND A CRACK AT THE TOP OF THE RUDDER PEDAL LEVER. THE LEVER WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. 1 H 7 1 3R A815 2001032900030 20010329 00030 GL 2001 3 29 CA000621025 3 20000613 G 6111 S82NB2 BLADE BEECH 33 3533 1151402 CE CONT O520 IO520B 17032 SO MCAULY 3A32C 3A32C76 GL PROPELLER CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 51 (CAN) FOUND CORROSION ON THE BLADE THREADS DURING THE CORROSIION INSPECTION. BLADES REPLACED WITH USED SERVICEABLE. IN A CCORDANCE WITH MCCAULEY MANUAL 720415. 1 L 7 1 3O 3 O 3A15 E5CE 5 C P21EA 2001032900031 20010329 00031 GL 2001 3 29 CA000621026 3 20000621 G 6114 FLANGE MCAULY 1A200 1A200DFA GL PROPELLER DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 281 (CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. 5 N P874 2000092100005 20000921 00005 2000 9 21 CA000621027 4 20000612 G 6122 B4183 FLYWEIGHT HARTZL F624 PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA HARTZL HCE3Y HCE3YR2 GL CUP BROKEN W K NONE O OTHER CL CLIMB 1 CA C549T L199468N DJDJ10707A (CAN) FLYWEIGHT CUP IS SPOT WELDED TO FLYWEIGHT HEAD. SPOT WELD BROKE, HEAD SPUN WITHOUT CUP AND CUT CUP CAUSING FAILUR E. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001032900032 20010329 00032 NM 2001 3 29 CA000621028 1 20000612 G 2120 65405521 MUFFLER BOEING 727 72725 1384006 NM PWA JT8 JT8D7B 52053 NE AIR DISTRIBUTION FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING TROUBLESHOOTING OF AIRCRAFT FOR A PRESSURIZATION DEFECT, IT WAS NOTICED THAT THE RT ACCOUSTIC MUFFLER INTER IOR LINING HAD BECOME DETACHED. THE PIECES WERE FOUND BLOCKING THE PRIMARY HEAT EXCHANGER. THIS WAS DETERMINED TO BE THE CAUSE OF THE PRESSURIZATION DIFFICULTY. THE MUFFLER WAS REPLACED. PARTS WERE REMOVED AND AREA CLEANED. AIRCRAFT RETURNE D TO SERVICE. 2 L 7 3 4F 4 F A3WE E2EA 2000092100006 20000921 00006 SO 2000 9 21 CA000621029 1 20000615 G 2701 6855811 WHEEL PIPER PA28 PA28140 7102802 SO LYC O320 O320E3D 41508 EA L/H O/B TOP BROKEN W D RETURN TO BLOCK F FLT CONT AFFECTED CR CRUISE 1 CA 10677 RL4406027A (CAN) PILOT SIDE OF CONTROL WHEEL BROKE IN-FLIGHT. LEFT SIDE OF WHEEL TOP PORTION AT CENTER OF WHEEL WHERE A HOLE HAD B EEN DRILLED TO ACCEPT WIRE FROM CONTROL SHAFT TO MIKE SWITCH MOUNTED ON TOP LEFT SIDE. 1 L 7 1 3O 3 O 2A13 E274 2001032900033 20010329 00033 NM 2001 3 29 CA000621030 1 20000608 G 3246 4312176 BOLT BOEING 757 757236 NM RROYCE RB211 RB211535E437 54555 NE WHEEL SHEARED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHILE MECHANIC WAS CARRYING OUT HIS INSPECTION HE OBSERVED THAT NR 7 MAIN WHEEL ASSEMBLY TIE BOLTS WERE SHEARED OF F (X3). MAIN WHEEL ASSEMBLY WAS REMOVED & SERVICEABLE ASSEMBLY WAS INSTALLEDI.A.W. M.M. 32-45-01. NO FUTHER PROBLEMS ON SUBSEQUENT FLIGHTS. 2 L 7 2 4F 4 F RT A2NM E12EU 2001032900035 20010329 00035 WP 2001 3 29 CA000621032 1 20000519 G 3260 BULB LKHEED 1011 1011385114 WP RROYCE RB211 RB21122B02 54555 NE LIGHT BURNED OUT W L ABORTED APPROACH N FALSE WARNING AP APPROACH 1 CA (CAN) DURING APPROACH , NO INDICATION DOWN AND LOCK FOR NOSE LANDING GEAR. AIRCRAFT MADE GO AROUND TO VISUALLY VERIFY GE AR DOWN AND LOCK AND FINALLY LAND WITH NO PROBLEM. THE PROBLEM RESULT AT 2 LIGHT BULB BURNT OUT. BULB REPLACED AND AIRCR AFT RETURNED TO SERVICE. 2 L 7 3 4F 4 F A23WE E12EU 2001032900039 20010329 00039 NM 2001 3 29 CA000621037 1 20000603 G 3251 3790037107 VALVE BOEING 767 767333 NM PWA 4060 PW4060 52119 NE NLG STEERING FAILED W D RETURN TO BLOCK J WARNING INDICATION TX TAXI/GRND HDL 1 CA (CAN) DURING TAXI, AIRCRAFT STOPPED RESPONDING TO RIGHT STEERING TILLER OR RIGHT RUDDER PEDAL INPUTS. STEERING WOULD ONL Y RESPOND TO CENTRE TO LEFT POSITIONS. AIRCRAFT RETURNED TO GATE. NOSE WHEEL STEERING METERING VALVE MODULE REPLACED AND SYSTEM CHECKED SERVICEABLE AS PER MAINTENANCE MANUAL 2 L 7 2 4F 4 F RT A1NM E24NE 2001032900041 20010329 00041 WP 2001 3 29 CA000621039 1 20000508 G 2131 20219741 CONTROLLER DOUG DC9 DC932 3022066 WP PWA JT8 JT8D7 52053 NE CABIN PRESSURE FAILED W O OTHER J WARNING INDICATION CL CLIMB 1 CA (CAN) TRANSFER LOCKOUT/STANDBY ON LIGHT ON, QUICK REFERENCE HANDBOOK PROCEDURE CARRIED OUT AND SYSTEM CAUSED SURGE AND L ARGE CABIN RATE CHANGE, USING STANDBY LEVER HUNGTING +/- 2 INCHES. CHANGED NR 2 CABIN PRESSURE CONTROLLER AND OUTFLOW VA LVE ACTUATOR. 2 L 7 2 4F 4 F A6WE E2EA 2001032900044 20010329 00044 NM 2001 3 29 CA000621042 1 20000621 G 5280 NAS6706D26B BOLT BOEING 767 767333 NM PWA 4060 PW4060 52119 NE MLG SHEARED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AFTER A/C ARRIVED AT GATE (YUL) MAINT FOUND ON WALK AROUND CHECK DAMAGE TO RT LOWER WING PANEL , RT LDG GEAR DRAG STRUT, & RIGHT LDG GEAR STRUT DOOR. HEAD OF BOLT ATTACHING RIGHT STRUT DOOR TO LANDING GEAR STRUT FOUND SHEARED OFF. STR UT DOOR THEN ALLOWED TO MOVE AFT&HANG DOWN INTO AIRSTREAM RESULTING IN DAMAGE TO BOTH DOORS & WING PANEL. 2 L 7 2 4F 4 F RT A1NM E24NE 2001032900047 20010329 00047 NE 2001 3 29 CA000621045 2 20000311 G 7260 312137201 SPUR GEAR PWA PW120A DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE ACCESSORY DRIVE WORN W E ENGINE SHUTDOWN O OTHER CR CRUISE 1 CA 15076 PCE120369 (CAN) EXAMINATION OF AGB BREATHER GEAR SHOWED THAT ALL OF DRIVE TEETH FOR FUEL PUMP GEAR HAD FRACTURED FROM ROOT WITH EX CEPTION OF 5 TEETH. THESE 5 TEETH DISPLAYED SEVERE WEAR PATTERN ON TOOTH FLANK, MAINLY BELOW PITCH LINE. IN-FLT SHUT DOW N CAUSED BY LOSS OF FUEL PUMP DRIVE DUE TO AGB BREATHER & FUEL PUMP GEARS TEETH FRACTURE: THE TEETH FRACTURE OF ACCESSOR Y DRIVE BREATHER GEAR OCCURED FROM FATIGUE, WHICH ORIGINATED AT TEETH ROOT RADIUS BELOW TEETH WEAR. HIGH STRESS CONTACT FATIGUE COMBINED WITH HIGH HRS OF OP ON GEARS PROBABLY CAUSED TEETH WEAR AT PITCH LINE. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001031900084 20010319 00084 NM 2001 3 19 CA000706001 1 20000620 G 2420 915F2125 GCU BOEING 737 737217 1384464 NM PWA JT8 JT8D17 52049 NE NR 2 ENGINE FAILED W A UNSCHED LANDING H ELECT. POWER LOSS-50 PC CR CRUISE 1 CA 46203 (CAN) NR 2 ENGINE GENERATOR SYSTEM FAILED, UNABLE TO ESTABLISH APU ON AIRCRAFT BUSS. AIRCRAFT DIVERTED TO YHZ. NR 2 GENE RATOR CONTROL PANEL REPLACED AS PER WORK CARD, SYSTEM CHECKED SERVICEABLE. APU GENERATOR OPERATIONS CHECKED NORMAL WHEN FUNCTIONED GROUND AND FLIGHT MODE. 2 L 7 2 4F 4 F A16WE E2EA 2001031900085 20010319 00085 NM 2001 3 19 CA000706002 1 20000617 G 7120 CSD BOEING 737 737275 1384485 NM PWA JT8 JT8D9A 52048 NE NR 2 ENGINE FAILED W O OTHER O OTHER CR CRUISE 1 CA 40768 37820 707408 (CAN) A/C 759, JUNE 17/2000, FLT 195, LOG SEQUENCE 0300876. NR 2 CSD DISCONNECTED DUE LOW OIL PRESSURE LIGHT CAME ON. RE PLACED NR 2 CSD OIL COOLER DUE COOLER BLOCKED BY PIECES OF FAN DIFFUSER DUCT LINING, THAT HAD BROKEN UP. REPLACED NR 2 E NGINE AS PER WORK CARD 1125-2, OFF CANADIAN PART NUMBER 7-7200-9-0001, ON SERIAL NUMBER 4240. 2 L 7 2 4F 4 F A16WE E2EA 2001031900109 20010319 00109 NM 2001 3 19 CA000706003 1 20000623 G 2910 O-RING BOEING 767 767375 NM HYD SYSTEM LEAKING W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) CREW REPORTED CENTER SYSTEM HYDRAULIC LOW QUANTITY LIGHT ON. TURNED OFF ALL CENTER HYDRAULIC PUMPS. FLIGHT DIVERTE D, DECLARED AN EMERGENCY, LANDED WITHOUT INCIDENT. ON INSPECTION FOUND LEAK AT DELTA P FITTING ON CENTER SYSTEM CASE DRA IN FILTER MODULE. O-RING REPLACED LEAK CHECKED OK. 2 L 7 2 4F RT A1NM 2001031900128 20010319 00128 NM 2001 3 19 CA000706004 1 20000625 G 3244 H40X14519 TIRE BENDIX 26066712 BOEING 737 737242C 1384478 NM PWA JT8 JT8D9A 52048 NE LT MLG MISSING W C ABORTED TAKEOFF O OTHER TO TAKEOFF 1 CA 42747 21210 5095 (CAN) AIRCRAFT ON TAKEOFF, REPORTED TIRE DEBRIS ON RUNWAY. MAINTENANCE ADVISED, UNABLE TO DETERMINE FLT, LANDING, CREW REQUESTED CFR, DUE POTENTIAL TIRE PROBLEMS. FLIGHT LANDED WITHOUT INCIDENT. INSPECTION FOUND TIRE CAP MISSING FROM LEFT INBOARD WHEEL. DAMAGE NOTED ON LT INBOARD AFT FLAP AND TRAILING EDGE PANEL. WHEEL AND TIRE REPLACED, FLAP AND PANEL POST ED FOR REPAIR. 2 L 7 2 4F 4 F A16WE E2EA 2001031900158 20010319 00158 NM 2001 3 19 CA000706006 1 20000629 G 7312 320115 VALVE BOEING 737 737275 1384485 NM PWA JT8 JT8D9A 52048 NE FUEL HEAT FAILED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 39104 9633 (CAN) ON CLIMBOUT FROM MCO, NR 1 FUEL HEAT VALVE FAILED IN OPEN POSITION, CAUSING NR 1 ENGINE HIGH OIL TEMP. RETURNED T O MCO. REPLACED NR 1 ENGINE FUEL HEAT VALVE AS PER MM 73-14-11 PAGE 401, TESTED AS PER MM 73-14-11 PAGE 501. CHECKED OK. 2 L 7 2 4F 4 F A16WE E2EA 2001031200437 20010312 00437 EA 2001 3 12 CA000706014 1 20000705 G 2430 31890 TERMINAL DHAV DHC8 DHC8311 1386006 EA PWA PW120 PW123 NE NR 1 DC GEN FAILED W O OTHER N FALSE WARNING CR CRUISE 1 CA (CAN) THE FLIGHT CREW REPORTED THAT NR 1 D.C. GENERATOR LOAD METER WAS INDICATING A LOAD OF 1.26 CONTINUOUSLY. MAINTENAN CE INVESTIGATION REVEALED A BAD (HIGH RESISTANCE) ON THE R1 TERMINAL CONNECTION OF THE GENERATOR SHUNT LOCATED BEHIND TH E LT LANDING LIGHT. THE TERMINAL LUGS WERE REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. 2 H 7 2 4T 4 T RT A13NM E20NE 2001031200438 20010312 00438 NE 2001 3 12 CA000706015 2 20000705 G 7532 WIRE DHAV DHC8 DHC8301 NM PWA PW120 PW123 NE BLEED VALVE CHAFED W O OTHER J WARNING INDICATION CR CRUISE 1 CA (CAN) THE FLIGHT CREW REPORTED THAT THE NR 1 BLEED SYSTEM CONTROL CIRCUIT BREAKER POPPED. MAINTENANCE INVESTIGATION REVA LED A CHAFED WIRE AT THE NR 1 HGIH PRESSUE BLEED VALVE CONNECTOR PLUG 2121-P9. THE WIRE WAS REPAIRED AND THE AIRCRAFT WA S RETURNED TO SERVICE. 2 H 7 2 4T 4 T RT A13NM E20NE 2001032600221 20010326 00221 EA 2001 3 26 CA000706021 2 20000626 G 7261 LW13904 SEAL PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA OIL FILTER LEAKING W E A ENGINE SHUTDOWN UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA 149 (CAN) PILOT REPORTED OBSRVING WHITE FUMES COMING OUT OF LT ENGINE DURING CRUISE. EMERGENCY FIRE DRILL CARRRIED OUT & FI RE OUT. INVESTESTIGATION ON GROUND CONDUCTED, FOUND FIRE DAMAGE TO HIGH TENSION MAGNETO LEADS, OIL HOSES, HYDRAULIC & FU EL HOSES & ELECTRIC WIRINGS. MAGNETO , FUEL PUMP, HYD PUMP, VACUUM PUMP WIRE AFFECTED. OIL STAINS REMAINING WITHIN AREA BETWEEN FIREWALL & AFT OF CRANKCASE ACCESSORY HOUSING & FIRE CONTAINED WITHIN AREA ONLY ATTEMPTED TO FIND CAUSE OF FIRE, FUEL PUMP TURNED ON, & NO FUEL LEAKAGE EVIDENT FROM PUMP & HOSES, DRY MOTOR RUN ALSO CARRIED OUT, & DISCOVERED FRESH OI L DRIPPING THROUGH PRESSURE FILTER OIL SEAL AS REFERRED ABOVE. 1 L 7 2 3O 3 O A20SO E14EA 2001031200443 20010312 00443 CE 2001 3 12 CA000706023 1 20000613 G 3260 327 BULB BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE NLG INDICATOR FAILED W O OTHER P NO WARNING INDICATION AP APPROACH 1 CA 5560 (CAN) ON APPROACH TO PENTICTION NOSE GEAR LIGHTS DID NOT ILLUMINATE. INTRANSIT LIGHT WAS EXTINGUISHED & NOSE LIGHTS DID NOT ILLUMINATE DURING PRESS TO TEST. PILOT DID FLYBY OF TOWER & ALL LOOKED GOOD. HE THEN ELECTED NOT TO LAND BUT RETURN TOCALGARY WHERE HE DID ANOTHER PASS BY THE TOWER & AS A PRECAUTION. ALSO HAD EMERGENCY SERVICES CALLED OUT. AN UNEVENTFU L LANDING WAS DONE & THE AIRCRAFT BROUGHT TO THE HANGAR WHERE THIS BULBS IN THE ANNUNICATOR WERE REPLACED P/N 327 AND GE AR SWINGS COMPLETED WITH ALL SYSTEMS OPERATING NORMALLY. 2 L 7 2 4T 4 T RT A24CE E26NE 2000092100009 20000921 00009 CE 2000 9 21 CA000706025 1 20000617 G 5751 991300003 AILERON RAYTHN STC100BEECH BEECH 100 100BEECH 1152916 CE PWA PT6 PT6A28 EA UPR/LWR JOINTS CRACKED W O OTHER O OTHER IN INSP/MAINT 1 CA B40 PCE50050 (CAN) DURING REPETITIVE AILERON STRUCTURE INSPECTION, FOUND SKIN CRACKS ALONG FORWARD/AFT UPPER AND LOWER SKIN LAP JOINT S. CRACKS (2 FOUND INITIALLY) RUN LATERALLY ALONG LAP JOINT. ON SKIN REMOVAL, FOUND CORROSION UNDER SKIN AND 5 CRACKS VERYING FROM LESS THAN 1 INCH TO 3 INCHES LONG. 1 L 7 2 3T 4 T A14CE E4EA 2001032600223 20010326 00223 EU 2001 3 26 CA000706026 1 20000618 G 6420 350A33211905 HOUSING AEROSP AS355 AS355F1 8680810 EU ALLSN 250C 250C20F 03013 GL T/R DRIVE SHAFT SHEARED W K NONE O OTHER IN INSP/MAINT 1 CA 898 (CAN) DURING HUB REMOVAL TO C/W SB 65.00.38 (T/R SPYDER BEARING KIT INSTALLATION) THE KEY THAT ALIGNS HUB TO T/R SHAFT W AS FOUND SHEARED & THE HUB HAD SPUN APPROX. 110 DEGREES. THE T/R LONG DRIVE SHAFT P/N 350A34-0110-07 WAS FOUND TO HAVE A N APPROX 60 DEGREES TWIST IN IT. FOLLOWING PARTS WERE REPLACED DUE TO SUSPECT T/R STRIKE. LONG DRIVE SHAFT, T/R HUB, T/ R GEAR BOX, T/R HUB BOLT, T/R BLADES, T/R COUPLE MGBOLTS, EXPANDABLE PIN, SPLIT BUSHINGS, T/R PITCH LINKS. 1 G 7 2 3U 3 U H11EU E4CE 2001032600226 20010326 00226 SW 2001 3 26 CA000706033 1 20000201 G 2820 LINE MOONEY M20 M20D 5870210 SW LYC O360 O360A1D 41514 EA FUEL SYSTEM DAMAGED W A UNSCHED LANDING N B FALSE WARNING SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 CA 6082 (CAN) ON 1 FEB 2000 PILOT REPORTED FLUCTUATING FUEL PRESSURE GAUGE. ALSO IN THE PAST PILOTS FELT IT READ LOW AND SOMETIM ES NOTICED A FUEL SMELL. FOUND: THE SHORT CURVED FUEL LINE (NOT SHOWN IN MANUAL) THAT PASSES THROUGH THE CABIN BETWEEN THE FUEL SELECTOR & THE FUEL STRAINER HAD BEEN RUBBING WHERE IT PASSES THROUGH BULKHEAD. THE HOLE WAS AT THE TOP OF THE BEND AT THE HIGHEST POINT OFTHE FUEL SYSTEM. THEREFORE IT DID NOT LEAK BUT SENT OUT AN ODOR. WHEN RUNNING, AIR WOULD BE INJECTED THROUGH THIS HOLE CAUSING LOW FUEL PRESSURE AND FLUCTUATIONS. A NEW LINE WAS MADE AND FUEL PRESSURE IS NOW NOR MAL. 1 L 7 1 3O 3 O 2A3 E286 2000092100011 20000921 00011 CE 2000 9 21 CA000706034 1 20000327 G 7430 C2925010105 IGNITION SWITCH CESSNA 150 150L 2071826 CE CONT O200 O200A 17020 SO INTERNAL DIRTY W O OTHER Y ENGINE STOPPAGE CL CLIMB 1 CA 24300 20593970A 20593970A (CAN) ON MARCH 27, 2000, PILOT REPORTED ON CLIMB-OUT, ENGINE SUDDENLY RAN ROUGH AND COMPLETE ELECTRICAL FAILURE FOR 5 SE CONDS. CHECKED ALL WIRING AND ENGINE FOR ANY ABNORMAL SIGNS. NONE FOUND. RAN FINE ON GROUND, ETC. OPENED IGNITION SW ITCH AND FOUND A LITTLE DIRTY (BUT DRY). CLEANED CONTACT PLATES AND LUBRICATED WITH ELECTRICAL LUBE AND RE-ASSEMBLED. PERFORMED TEST FLIGHT AND FOUND NOT EVEN A STUTTER. AIRCRAFT WAS FLOWN 150 HRS SINCE THEN WITH NO DIFFICULTY. NOTE: SUBMITTER NOT POSITIVE THAT THE IGNITION SWITCH CAUSED THIS. COULD BE SOMETHING ELSE AND DID NOT THINK THE SWITCH WAS T HAT BAD BUT COULD NOT FIND ANYTHING ELSE. 1 H 7 1 3O 3 O 3A19 E252 2001032600229 20010326 00229 SW 2001 3 26 CA000706035 1 20000504 G 6520 206031446001 CASTING BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL T/R GEARBOX CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 9069 (CAN) CRACK FOUND AT AFT CASTING WHERE TAIL ROTOR GEARBOX MOUNTS IN TAILBOOM ON R/H HOLE. CASTING REMOVED BY OVERHAUL SH OP FOR REPLACEMENT AND CRACK ALSO LOCATED IN LT MOUNTING AREA. CRACK WAS FOUND ON SCHEDULED 100 HOUR INSPECTION OF AIRCR AFT. 1 G 7 1 3U 3 U H2SW E4CE 2000080300219 20000803 00219 SW 2000 8 3 CA000706036 1 20000607 G 6230 206010154003 WASHER BELL 206011100021 BELL 206 206B3 1181506 SW ALLSN 250C 250C20B 03013 GL LWR BLADE BOLT BROKEN W O OTHER O OTHER IN INSP/MAINT 1 CA 71200 AAB54008 CAE832459 (CAN) DEFECT WAS FOUND DURING PREFLIGHT. 1 G 7 1 3U 3 U H2SW E4CE 2001031500099 20010315 00099 EU 2001 3 15 CA000712002 2 20000621 G 7313 VC070 INJECTOR MORAVN Z142 Z142 EU AVIA M337 M337AK EU FUEL SYSTEM MISSING W A UNSCHED LANDING E VIBRATION/BUFFET CL CLIMB 1 CA 1124 9241143 (CAN) DURING A CLIMB, THE ENGINE STARTED VIBRATING, AND RUNNING ROUGH. THE FLIGHT WAS CANCELLED AND THE AIRPLANE RETURNE D SAFELY TO THE AIRPORT. TROUBLESHOOTING FOUND THE PROBLEM TO BE A FUEL INJECTOR IN THE NR 1 CYLINDER. THE NOZZLE OF TH E INJECTOR WAS MISSING. A VISUAL INSPECTION OF THE INTAKE VALVE AND CYLINDER FOUND NO DAMAGE. A COMPRESSION TEST WAS PERFORMED AND WAS NORMAL. THE INJECTOR WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. 1 L 7 1 3O 3 I NT A76EU EXPE3I 2001032600232 20010326 00232 SO 2001 3 26 CA000712009 1 20000611 G 3230 4032700 TRUNNION 4550726 PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA LT MLG CRACKED W O OTHER K FLUID LOSS LD LANDING 1 CA 5638 (CAN) - PIPER AIRCRAFT SETTLED LOWER TO LEFT SIDE ON LANDING. INITIAL INSPECTION REVEALED FLAT LEFT MAIN OLEO & EVIDENC E OF HYDRAULIC FLUID LEAK ON LEFT GEAR AND UNDER LEFT WING. FURTHER INSPECTION REVEALED AN APPROX 6 INCH CRACK ON AFT/ BOTTOM SIDE OFUPPER GEAR TRUNNION. ADDITIONAL INFO: PART AFFECTED HAS 5638 HRS PREVIOUS TAKEOFF. LANDINGS OF THE DAY WE RE REPORTED NORMAL. AIRCRAFT OPERATES WITH INCREASED TAKEOFF WEIGHT OF 7368 LBS IN ACCORDANCE WITH BOUNDARY LAYER RESE ARCH VORTEX GENERATOR KIT STC # SA00192SE, INSTALLED APRIL 1995. 1 L 7 2 3O 3 O A20SO E14EA 2001031200445 20010312 00445 NM 2001 3 12 CA000712011 1 20000619 G 3230 69546002 CYLINDER BOEING 737 737204 1384458 NM PWA JT8 JT8D15 52051 NE MLG CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 688675 (CAN) DURING WALK AROUND, AIRCRAFT HYDRAULIC FLUID WAS NOTICED COMING FROM THE LEFT HAND WHEEL WELL. FURTHER INVESTIGAT ION FOUND THE FLUID WAS LEAKING FROM A CRACK IN THE MAIN LANDING GEAR TRANSFER CYLINDER. THE TRANSFER CYLINDER ASSY WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. 2 L 7 2 4F 4 F A16WE E2EA 2001032600236 20010326 00236 SO 2001 3 26 CA000712012 1 20000606 G 2730 71056003 SPRING PIPER 41963 PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA ELEVATOR BUNGEE BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 774 (CAN) DURING A ROUTINE INSPECTION, MAINTENANCE CREW WERE COMPLYING TO PIPER SB 626C AND FOUND THE ELEVATOR BUNGEE SPRING BROKE AT THE HOOK END. NO COMPLAINTS OR SNAGS WERE REPORTED OR DETECTED BY THE PILOT. IT WAS THEREFORE ASSUMED TO HAVE BROKEN AFTER THE AIRCRAFT LANDED. 1 L 7 2 3O 3 O A20SO E14EA 2001032600237 20010326 00237 SO 2001 3 26 CA000712013 1 20000621 G 2810 531035 RETAINER PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA FUEL CAP SEPARATED W A UNSCHED LANDING D K INFLIGHT SEPARATION FLUID LOSS TO TAKEOFF 1 CA (CAN) WHEN THE AIRCRAFT WAS BEING REFUELED, THE GAS ATTENDANT HAD ROTATED THE GAS CAP TO REMOVE THE CAP. THIS ACTION IN TURN ROTATED THE RETAINER (P/N 531-035), CAUSING IT TO BECOME UNLOCKED FROM THE FILLER NECK. THE CAP WAS THEN PUT BACK ON AND LOCKED DOWN GIVING THE APPEARANCE OF BEING LOCKED. WHEN THE AIRCRAFT ROTATED ON TAKEOFF THE GAS CAP CAME OFF. THE RETAINER IS WHAT THE FUEL CAP LOCKS ONTO AND BECAUSE IT WAS NO LONGER LOCKED ONTO THE FILLER NECK THE CAP JUST FELL OFF . IT WAS LATER FOUND THAT THE LOCKS ON THE RETAINER HAD TO BE BENT DOWN MORE TO PROVIDE A MORE SUITABLE LOCK FOR THE RET AINER. THREE OF THE FUEL CAPS ON THE AIRCRAFT HAD THE SAME PROBLEM. 1 L 7 2 3O 3 O A20SO E14EA 2000100300239 20001003 00239 EA 2000 10 3 CA000712014 1 20000712 G 2750 ROD END DHAV C3CF1057 DHAV DHC3 DHC3 2800202 EA PWA PT6 PT6A34 52043 EA RIVIT LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA PCE40906 (CAN) WHILST CARRYING OUT A 100 HOUR INSPECTION OF THE CONTROL SYSTEM, THE ENGINEER NOTICED THAT THE RT FLAP PUSH/PULL R OD END FITTING APPEARED TO BE LOOSE. THE ROD WAS REMOVED FROM THE AIRCRAFT FOR FURTHER INVESTIGATION. IT WAS FOUND THA T THE RIVETS WHICH SECURE THE END FITTING TO THE FLAP PUSH/PULL ROD WERE LOOSE. THE RIVETS WERE REMOVED, THE END FITTING REMOVED AND A DETAILED INSPECTION CARRIED OUT - NO DAMAGE WAS FOUND TO THE FITTING OR THE ROD. IT WAS RE-ASSEMBLED AN D RE-RIVETED. IT SHOULD BE NOTED THAT FAILURE OF THESE RIVETS WOULD HAVE CAUSED AN ASYMMETRIC FLAP CONDITION. 1 H 7 1 3R 4 T A815 E4EA 2000100300109 20001003 00109 EA 2000 10 3 CA000712015 1 20000621 G 5230 C3FS23843 LOCK DHAV C3FS21925 DHAV DHC3 DHC3 2800202 EA PWA PT6 PT6A135 52043 NE LOCK MALFUNCTIONED W B EMER. DESCENT O OTHER CR CRUISE 1 CA PCE92418 (CAN) DURING FLIGHT IN ROUGH TURBULENCE, THE REAR CARGO DOOR CAME OPEN. THE FLIGHT CREW ADVISED THAT THE LOCKS HAD BEEN SECURED AND LOCKED. THE AIRCRAFT IS HERE UNDERGOING REPAIR. INSPECTED THE LOCKS AND CAN FIND NO PROBLEM WITH THEM AS OF YET. 1 H 7 1 3R 4 T A815 E4EA 2001040200267 20010402 00267 NE 2001 4 2 CA000712016 2 20000621 G 7261 3020290 BREATHER TUBE DHAV DHC3 DHC3 2800202 EA PWA PT6 PT6A135 52043 NE ENGINE LEAKING W B EMER. DESCENT K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) THE AIRPLANE CONSUMED APPROXIMATELY 5 LITERS OF OIL IN 1 HOUR OF FLIGHT. THE CENTRIFUGAL BREATHER WAS REMOVED FOR INSPECTION AND DEEMED UNSERVICEABLE BY THE PRATT & WHITNEY FIELD REP ON HAND. A REPLACEMENT PART WAS INSTALLED. 1 H 7 1 3R 4 T A815 E4EA 2000100300110 20001003 00110 CE 2000 10 3 CA000712017 1 20000703 G 3246 10320400 BOLT PARKERHANFIN 40179 CESSNA 208 208B 2073701 CE PWA PT6 PT6A114 52043 NE BOLT SHEARED W O OTHER O OTHER IN INSP/MAINT 1 CA 02 PCE19192 (CAN) WHILE CARRYING REGULAR MAINT ON A/C, NOTICED ONE NUT WAS MISSING FROM WHEEL HUB BOLTS. UPON FURTHER INVESTIGATION , FOUND THAT BOLT HAD SHEARED AND NUT HAD FALLEN OFF, AT WHICH POINT, BOLT BACKED OUT OF HUB AND HIT BRAKE TORQUE PLATE, BENDING BOLT AND SCORING TORQUE PLATE. WHEEL AND TORQUE PLATE WERE REPLACED. BOLT HAD 173.7 HRS SINCE NEW. IT WAS RE PLACED AT LAST TIRE CHANGE. STANDARD PROCEDURE IS ALL WHEEL HUB BOLTS ARE REPLACED AT TIRE CHANGE AND TORQUED IAW MFGS SPECS. THIS IS SECOND OCCURENCE OF THIS BOLT FALLING IN LAST 2 YRS. BOLT PART NUMBER IS 103-20400, BUT MAY ALSO BE REC OGNIZED UNDER AN5-40A. (X) 1 H 7 1 3T 3 T A37CE E4EA 2000100300111 20001003 00111 EA 2000 10 3 CA000712018 1 20000703 G 2731 C3TE1312 TAB DHAV DHC3 DHC3 2800202 EA SERVO TAB TWISTED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A ROUTINE 100 HOUR INSPECTION OF THE TAIL OF THE TURBO OTTER, THE ENGINEER FOUND THE ELEVATOR SERVO TAB WAS BENT AND TWISTED. FURTHER EXAMINATION FOUND THAT THE SERVO TAB WAS BENT AND TWISTED. SUBMITTER STATED THERE HAVE BEEN NUMEROUS SDRS FILLED OUT ON THE SERVO TAB OF THE TURBO OTTER. 1 H 7 1 3R A815 2000100300112 20001003 00112 EA 2000 10 3 CA000712019 1 20000703 G 2730 C6CF113711 BELLCRANK DHAV C6CF11371 DHAV DHC6 DHC6200 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL CABLE QUADRANT TWISTED W K NONE O OTHER IN INSP/MAINT 1 CA PCEPG0034 BU8721 (CAN) WHILE CARRYING OUT AD CF-72-06R4 PART III, THE ELEVATOR QUADRANT WAS FOUND TO BE RUBBING AGAINST THE SIDE OF THE C ABLE GUARD AS DESCRIBED IN THE AD. THE QUADRANT ASSEMBLY INCLUDING SUPPORT BRACKET WAS REPLACED PRIOR TO FLIGHT. (X) 1 H 7 2 3T 4 T A9EA E4EA 6 C P15EA 2001032600471 20010326 00471 CE 2001 3 26 CA000712021 1 20000704 G 5741 9041101S FITTING BEECH 99 99A 1154003 CE PWA PT6 PT6A28 EA LT WING ROOT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CRACK DISCOVERED DURING LPI OF FITTINGS CALLED UP BY AD. CRACK WAS FOUND AT RADIUS OF WING ROOT ATTACH FLANGE ON F ORWARD SIDE OF FITTING. BY THE SLOT ON THE SIDE. 1 L 7 2 3T 4 T A14CE E4EA 2001032600472 20010326 00472 CE 2001 3 26 CA000712022 1 20000704 G 5741 9041102S FITTING BEECH 99 99A 1154003 CE PWA PT6 PT6A28 EA RT WING ROOT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CRACKED AT RADIUS OF WING ROOT ATTACH FLANGE ON FORWARD SIDE OF FITTING. 1 L 7 2 3T 4 T A14CE E4EA 2001032600473 20010326 00473 CE 2001 3 26 CA000712023 1 20000704 G 5741 9041102S FITTING BEECH 99 99 1154002 CE PWA PT6 PT6A28 EA RT WING CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WING FITTING CRACKED AT RADIUS PORTION OF UPPER SURFACE OF WING FITTING. SLOT AREA. 1 L 7 2 3T 4 T A14CE E4EA 2001032600474 20010326 00474 CE 2001 3 26 CA000712024 1 20000704 G 5741 9041063S FITTING BEECH 100 A100 1152915 CE PWA PT6 PT6A28 EA LT WING ROOT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CRACKED AT RADIUS OF WING ROOT ATTACH FLANGE ON FORWARD SIDE OF FITTING. SLOT AREA. 1 L 7 2 3T 4 T A14CE E4EA 2001031200446 20010312 00446 WP 2001 3 12 CA000712026 2 20000612 G 7321 GEAR SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE33111U 01514 WP MCAULY 4HFR34 4HFR34C652 NE FUEL CONTROL FAILED W E ENGINE SHUTDOWN X J ENGINE FLAMEOUT WARNING INDICATION LD LANDING 1 CA P44717C 911170 (CAN) UPON SHORT FINAL ENGINE FLAMED OUT DUE TO THE DRIVE THAT TURNS THE FUEL PUMP AND FCU STOPPED. CAUSE UNKNOWN AT THI S TIME. AIRCRAFT LANDED WITHOUT INCIDENT AND THE ENGINE WAS REPLACED. AIRCRAFT RETURNED TO SERVICE. TEARDOWN TO BE ACCOM PLISHED THIS WEEK. 2 L 7 2 4T 4 T RT A8SW E4WE 6 C 3PNE 2001032600480 20010326 00480 CE 2001 3 26 CA000712028 1 20000623 G 6123 A15941 SPRING BEECH 95 95B55 1152729 CE CONT O470 IO470L 17026 SO HARTZL HCC3Y HCC3YF2 GL PROP FEATHER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 1342 (CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. FEATHER SPRING FOUND CRACKED. 1 L 7 2 3O 3 O RT 3A16 3E1 5 C P25EA 2001032600081 20010326 00081 CE 2001 3 26 CA000712029 1 20000623 G 6123 B15941 SPRING HARTZL PHCC3YF2FU BEECH 95 95B55 1152729 CE CONT O470 IO470L 17026 SO HARTZL HCC3Y HCC3YF2 GL PROP FEATHER BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 1342 EB1378 (CAN) PROPELLER RECEIVED FOR CORROSION INSPECTON. 1 L 7 2 3O 3 O RT 3A16 3E1 5 C P25EA 2000100300113 20001003 00113 GL 2000 10 3 CA000712030 3 20000622 G 6111 PROPELLER MCAULY 1C160DTM CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA MCAULY 1C160 1C160DTM GL LE & FACE DAMAGED W O OTHER O OTHER IN INSP/MAINT 1 CA 21770 723286 L3643127A 723286 (CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. (X) 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2000100300114 20001003 00114 CE 2000 10 3 CA000712031 1 20000623 G 6121 D22011 HUB HARTZL CESSNA 172 172D 2072410 CE FRNKLN 6AV350 6A350C2 27043 EA HARTZL HCC2Y HCC2YF1 GL C/S SEAL AREA CORRODED W O OTHER O OTHER IN INSP/MAINT 1 CA 14200 610653 AM2505 (CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. (X) 1 H 7 1 3O 3 O NT 3A12 E9EA 5 C P920 2001032600082 20010326 00082 SW 2001 3 26 CA000713002 1 20000120 G 2720 45300655 BRACKET GULSTM 500 500B 0141106 SW LYC O540 IO540E1A5 41532 EA RUDDER PULLEY CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 10569 (CAN) ON INSPECTION BOTH LT AND RT RUDDER PULLEY BRACKETS WERE FOUND CRACKED AT THE TOP PORTION. PULLEY BRACKETS WERE PA TCHED USING THICKER ALUMINUM. FURTHER INSPECTIONS FOUND TWO OTHER PULLEY BRACKETS CRACKED IN THE SAME LOCATION. 1 H 7 2 3O 3 O 6A1 1E4 2001032600083 20010326 00083 CE 2001 3 26 CA000713003 1 20000303 G 3230 MS203921C21 CLEVIS PIN CESSNA 12805043 CESSNA 337 337H 2075732 CE CONT O360 IO360GB 17025 SO DOWNLOCK ACTUATO SHEARED W K NONE O OTHER IN INSP/MAINT 1 CA 10038 (CAN) ON INSPECTION OF LANDING GEAR DOWNLOCK ACTUATOR THE RT CLEVIS PIN HALF WAS MISSING. THE CLEVIS PIN WAS REMOVED AND FOUND TO BE SHEARED. A NEW PIN WAS INSTALLED.ON FURTHER INSPECTIONS TWO OTHERS WERE FOUND SHEARED AND MANY OTHER BENT O N DIFERENT AIRCRAFT. 1 H 7 2 3O 3 O A6CE E1CE 2000080200210 20000802 00210 SW 2000 8 2 CA000713004 1 20000509 G 6230 206010152101 NUT BELL 206011100021 BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL OTBD SHANK RADIU CRACKED W O OTHER O OTHER IN INSP/MAINT 1 CA 69950 (CAN) DURING A SCHEDULED OVERHAUL OF THE ABOVE DESCRIBED MAIN ROTOR HUB ASSEMBLY, A COMPONENT WITHIN THIS ASSEMBLY KNOWN AS THE MAST NUT WAS FOUND TO HAVE A CRACK INDICATION. THIS WAS DETECTED DURING THE MAGNETIC PARTICLE INSPECTION. THIS N UT HAS SINCE BEEN SENT TO BELLL HELICOPTER FOR FURTHER INSPECTION AND TESTING. 1 G 7 1 3U 3 U H2SW E4CE 2001031200447 20010312 00447 NM 2001 3 12 CA000713005 1 20000602 G 3246 31414 WHEEL BOEING 727 72727C 138400J NM PWA JT8 JT8D7B 52053 NE MLG DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) MAIN WHEEL ASSEMBLY FOUND DAMAGED FROM A BRAKE DRIVE KEY COMING LOOSE.BRAKE ASSEMBLY DAMAGED BY WHEEL DRIVE KEY CO MING LOOSE. MAIN WHEELAND BRAKE ASSEMBLY REPLACED AND CHECKS SERVICEABLE. 2 L 7 3 4F 4 F A3WE E2EA 2000091900001 20000919 00001 EA 2000 9 19 CA000713006 1 20000608 G 2710 C2CF1125A CONTROL CABLE DHAV DHC2 DHC2MK1 2800102 EA PWA R985 R985AN14B 52008 NE RT LWR DOOR BKHD FRAYED W K NONE F FLT CONT AFFECTED IN INSP/MAINT 1 CA JP206759 (CAN) DURING DISMANTLING REQUIRED BY AD CF-98-37, ALL CABLES WERE CHANGED AS PRECAUTIONARY MEASURE. HOWEVER, UPON REMOV AL, CABLE WAS FOUND WORN AND FRAYED AT LOWER RT DOOR BULKHEAD PULLEY. AREA IS DIFFICULT TO INSPECT AT ROUTINE INSPECTIO N. (X) 1 H 7 1 3R 3 R A806 5E1 2001021400002 20010214 00002 NE 2001 2 14 CA000713008 2 20000613 G 7420 37C311098P101 IGNITION LEAD GE CF7002D2 AMD FALCON FALCON20 2730103 EU GE CF700 CF7002D2 30010 NE ENGINE SEPARATED W K NONE O OTHER IN INSP/MAINT 1 CA 245VO95 245VO95 (CAN) DURING ROUTINE MAINTENANCE, THE IGNITION LEAD WAS REMOVED FROM THE IGNITOR PLUG TO FACILITATE REPLACEMENT OF THE P LUG. IT WAS NOTED THAT THE LEAD WAS STUCK IN THE PLUG. REMOVAL OF THE LEAD CAUSED THE PIN TO BECOME DETECHED FROM THE AS SEMBLY. THE LEAD WAS REPLACED WITH A NEW SERVICEABLE UNIT, NO FURTHER ACTION TAKEN. 2 L 7 2 4F 4 F RT A7EU E7EA 2000091900002 20000919 00002 EU 2000 9 19 CA000713009 1 20000615 G 2400 AZS5 CIRCUIT BREAKER ZLIN 242 Z242L 9970204 EU C/B PANEL FAILED W O OTHER O OTHER IN INSP/MAINT 1 CA 35440 (CAN) AS PART OF AN INSPECTION OF THE AIRCRAFT WIRING AND PROTECTON DEVICES, IT WAS FOUND THAT (2) CIRCUIT BRAKER SWITCH ES FAILED TO PERFORM THEIR INTENDED FUNCTION. THE BREAKER SWITCHES WERE TESTED AT TWICE THEIR RATED CURRENT FOR A PERIOD OF 3 MINUTES AND THEY WOULD NOT OPEN. THE SWITCHES APPEAR TO BE NON MIL SPEC. THE REMAINING CIRCUIT BREAKERS WORKED A S INTENDED. ALL BREAKER SWITCHES ARE TO BE REPLACED WITH MS 24508-B-X MIL SPEC CIRCUIT BREAKER SWITCHES. NOTE: NORMA LLY CIRCUIT BREAKERS AND SWITCHES ARE ON CONDITION AND ARE NOT TESTED UNDER THESE CIRCUMSTANCES AS PART OF NORMAL MAINTE NANCE PRACTICES. 1 L 7 1 3O 0 A76EU 2001031200449 20010312 00449 EA 2001 3 12 CA000713010 1 20000614 G 5314 SKIN DHAV DHC7 DHC7102 2802708 EA PWA PT6 PT6A50 52043 EA HAMSTD 24PF 24PF305 GL FUSELAGE BULGED W K NONE O OTHER IN INSP/MAINT 1 CA 31460 PCE86483 237795 (CAN) DURING ROUTINE INSPECTION THE AIRCRAFT SKIN WAS FOUND BULGING OUTWARDS & 3 RIVETS WERE PULLED THROUGH THE SKIN. 2 H 7 4 4T 4 T A20EA E4EA 6 C P1NE 2000100200065 20001002 00065 EU 2000 10 2 CA000713011 1 20000617 G 5521 9408308602 BEARING 5552012194 PILATS PC12 PC1245 EU ON CNTRL LEVER LOOSE W O OTHER O OTHER IN INSP/MAINT 1 CA 24260 (CAN) - ON INSPECTION, FOUND BEARING TO BE LOOSE IN ITS BORE. BEARING IS AT ATTACH POINT FOR CONTROL INPUT LEVER/ROD. BEARING RE-BONDED IN BORE PER PILATUS TECH MEMO EF-12-TM-778. 1 L 7 1 3T RT A78EU 2000091900003 20000919 00003 EA 2000 9 19 CA000713012 2 20000619 G 8530 73806 PUSHROD LYC CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA MCAULY 1A103 1A103TCM GL INTAKE BENT W A UNSCHED LANDING R E PARTIAL RPM/PWR LOSS VIBRATION/BUFFET CR CRUISE 1 CA 29640 L2330615 R770128 (CAN) - BENT PUSHROD CAUSING POWER LOSS AND ROUGH RUNNING ENGINE. - REASON FOR BENDING UNKNOWN. 1 H 7 1 3O 3 O NT 3A19 E223 5 N P50GL 2000091900004 20000919 00004 CE 2000 9 19 CA000713013 1 20000619 G 2740 BRACKET CESSNA 180 180H 2072618 CE CONT O470 O470R 17026 SO MCAULY 2A34C 2A34C203 GL LEFT STABILIZER CRACKED W O OTHER O OTHER IN INSP/MAINT 1 CA 69000 9011950H 760187 (CAN) THE ANGLE TAIL CONE REINFORCEMENT WAS CHANGED AS IT WAS CRACKED. P/N 0712048-7 WAS REPLACED WITH NEW PART USING E XISTING RIVET SIZE AND PATTERN. THE BRACKET ON THE LEFT STABILIZER WAS CHANGED AS IT WAS FOUND TO BE CRACKED. P/N 0712 3021 WAS REPLACED WITH NEW PART USING EXISTING RIVET SIZE AND PATTERN. THE REINFORCEMENT STABILIZER HINGE (BOX) ON THE H ORIZONTAL STABILIZER WAS CHANGED. P/N 0732101-4 WAS REPLACED WITH NEW PART USING EXISTING RIVET SIZE AND PATTERN. 1 H 7 1 3O 3 O 5A6 E273 5 C P3EA 2000091900005 20000919 00005 CE 2000 9 19 CA000713014 1 20000626 G 2110 1H953 CHECK VALVE CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE LT PNEU TAILCON FAILED W K NONE L NO TEST IN INSP/MAINT 1 CA 38960 71752 (CAN) DURING THE PHASE 1,2,3 & 4 INSPECTION, AN OPERATIONAL CHECK OF THE INFLATABLE DOOR SEAL WAS CARRIED OUT. THE RESUL TING TEST FOUND THAT PRESSURE WAS ZERO DOWNSTREAM FROM THE REGULATOR MEASURED AT MAIN DOOR SEAL INFLATING FITTING. ALSO NOTICED THE DE-ICING BOOTS WERE NOT INFLATING TO THEIR FULL FIRMNESS. THE AIRCRAFT WAS TAKEN OUT FOR A GROUND RUN WITH RT ENGINE ONLY OPERATING TO SEE IF THE SAME RESULTS WOULD APPEAR. ALL SYSTEMS WERE OPERATING NORMALLY. TROUBLESHOOTIN G THE PNEUMATIC SYSTEM REVEALED THE BLEED AIR CHECK VALVE P/N 1H95-3 FOR THE LEFT HAND ENGINE HAD THE FLAPPER VALVE BROK EN FROM ITS HINGE ASSEMBLY. AIR WAS ESCAPING VIA THE BLEED AIR LINE TO LT ENGINE. 1 L 7 2 4F 4 F A22CE E1NE 2000091900006 20000919 00006 CE 2000 9 19 CA000713015 1 20000703 G 3110 MS24693BB30 SCREW CESSNA 551818694 CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE SCREW INADEQUATE W O OTHER O OTHER IN INSP/MAINT 1 CA 71749 (CAN) DUE TO PREVIOUS SDR (APR/MAR 99), INSPECTION OF GLARESHIELD ATTACHING SCREWS RESULTED IN FINDING SLIGHT CHAFING (D ISCOLORATION) OF WIRE BUNDLE (3 PLACES) THAT RUNS THROUGH INSTRUMENT PANEL SUPPORT ASSEMBLY, INSULATION NOT BROKEN. WIR E BUNDLE SPY WRAPPED, SCREWS SHORTENED TO ONE FULL THREAD PROTRUDING PAST NUTPLATE LOCKING AS PER CAMPAIGN NOTICE 851-01 0 MAR 3/99. 1 L 7 2 4F 4 F A22CE E1NE 2001031200450 20010312 00450 EA 2001 3 12 CA000713016 2 20000624 G 7321 324475316 FUEL CONTROL DHAV DHC7 DHC7102 2802708 EA PWA PT6 PT6A50 52043 EA HAMSTD 24PF 24PF305 GL ENGINE FAILED W E ENGINE SHUTDOWN E VIBRATION/BUFFET CR CRUISE 1 CA 6952 (CAN) FUEL CONTROL UNIT WAS REPLACED. ENGINE RUN CARRIED OUT, TEST OKAY.AIRCRAFT RELEASED TO SERVICE. 2 H 7 4 4T 4 T A20EA E4EA 6 C P1NE 2001031200451 20010312 00451 GL 2001 3 12 CA000713017 1 20000713 G 2710 2057500000 HINGE DIAMON DA20 DA20A1 GL AILERON CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) - CRACKS FOUND ON SEVERAL CONTROL SURFACE HINGE ON AIRCRAFT OPERATED IN THE U.K. - CRACKS VISABLE AS BUBBLED PAI NT EXPOSED ON LOWER SURFACE.- ON REMOVAL OF PAINT, CRACK WAS FOUND RUNNING FROM HINGE PIN HOLE TO SURFACE. - PRESSED H INGE BUSHING WAS REMOVED FROM HINGE AND MINIMAL CORROSION WAS FOUND. - HINGE, REMOVED AND REPLACED WITH NEW. 1 L 7 1 3O NT TA4CH 2001011105115 20010111 05115 EA 2001 1 11 CA000714002 1 20000624 G 3411 INDICATOR CNDAIR CL600 CL6002B19 EA COCKPIT FAILED W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA (CAN) ON TAKE OFF CO-PILOT NOTICED NO AIRSPEED ON PFD2, TAKE OFF WAS ABORTED AND AIRCRAFT RETURNED TO GATE.THEY FOUND TH E CO-PILOT COVER THAT WAS NOT REMOVED PRIOR TO DISPATCHING THE AIRCRAFT. 2 L 7 2 4F RT A21EA 2001031200452 20010312 00452 NE 2001 3 12 CA000714003 2 20000624 G 7230 BLADE CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE COMPRESSOR FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 807040 (CAN) DURING SCHEDULE BORESCOPE INSPECTION SEVERAL STAGE ON COMPRESSOR BLADES ON NR 1 ENGINE, FOUND NICKS. 2 L 7 2 4F 4 F RT A21EA E15NE 2001031200453 20010312 00453 EA 2001 3 12 CA000714004 1 20000624 G 5610 NP1393215 WINDSHIELD CNDAIR CL600 CL6002B19 EA COCKPIT FAILED W O OTHER O OTHER DE DESCENT 1 CA (CAN) ON DESCENT THE CAPTAIN FRONT WINDSHIELD CENTRE PLY SHATTERED. 2 L 7 2 4F RT A21EA 2001031200454 20010312 00454 EA 2001 3 12 CA000714005 1 20000628 G 5210 HANDLE CNDAIR CL600 CL6002B19 EA PAX DOOR FAILED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) FROM CVG TO MKE, THE FLIGHT CREW REPORTED DURING CLIMB OUT THE PAX DR OUT HNDL CAUTION MESSAGE APPEARED ON ED1. TH E FLIGHT CREW INITIATED EMERGENCY DESCENT, FOLLOWING THE QRH PROCEDURE. MAINTENANCE ACTION: COMPLIED WITH OPERAITONAL CH ECK REQUIREMENTS AS PER AMM, FOUND SERVICEABLE. 2 L 7 2 4F RT A21EA 2001011105098 20010111 05098 EA 2001 1 11 CA000714006 1 20000628 G 5240 PANEL CNDAIR CL600 CL6002B19 EA O2 SERVICE OPEN W D RETURN TO BLOCK N FALSE WARNING CL CLIMB 1 CA (CAN) ON CLIMB OUT OF MEMPHIS, THE CREW REPORTED A LOUD NOISE COMING FROM THE R/H FORWARD SECTION ASSOCIATED WITH A STA LL FAIL MESSAGE.MAINTENANCE FOUND THE O2 SERVICING PANEL OPEN. THE PANEL WAS CLOSE AND THE AIRCRAFT RETURNED TO SERVICE. 2 L 7 2 4F RT A21EA 2001031200455 20010312 00455 EA 2001 3 12 CA000714007 1 20000702 G 3251 CONTROL UNIT CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE NLG STEERING FAILED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 807042 (CAN) AFTER TAKE OFF, NOSE GEAR WOULD NOT RETRACT, WITH ASSOCIATED MSG, WOW INPUT, STEERING FAIL ETC. CREW DECLARED AN E MERGENCY AND COMPLETED AN UNEVENTFUL LANDING, RETURNING TO THEIR ORIGINATING BASE. MAINTENANCE REPLACED STEERING HARNESS P/N: DOWTY 17300-233 AND NOSE GEAR RETRACT ACTUATOR P/N: DOWTY 16520-101. 2 L 7 2 4F 4 F RT A21EA E15NE 2001031200456 20010312 00456 EA 2001 3 12 CA000714008 1 20000702 G 2613 WARNING SYSTEM CNDAIR CL600 CL6002B19 EA EICAS FAILED W E A ENGINE SHUTDOWN UNSCHED LANDING N FALSE WARNING CR CRUISE 1 CA (CAN) THE FLIGHT CREW REPORTED DURING CRUISE L 14TH DUCT WARNING MESSAGE APPEARED ON EICAS WITH AURAL BLEED AIR DUCT MES SAGE. THE FLIGHT CREW INITIATED LT ENGINE SHUT-DOWN AND LANDED AT THE NEAREST AVAILABLE AIRPORT. TROUBLESHOOTING CARRIE D OUT AND NOT ABLE TO DUPLICATE DEFECT AT THIS TIME. 2 L 7 2 4F RT A21EA 2001031200457 20010312 00457 NM 2001 3 12 CA000714009 1 20000620 G 2120 214N211512 DUCT BOEING 757 75723A 1384967 NM RROYCE RB211 RB211535E437 54555 NE PAX AIR CRACKED W O OTHER O OTHER CR CRUISE 1 CA A8310 (CAN) IN FLIGHT, LOUD WISHING NOISE FROM CEILING AT ROW 12 AND PASSENGER WERE COMPLAINING ABOUT VERY COLD TEMPERATURE. A FTER INVESTIGATION, MAINTENANCE FOUND A LEAK AT AIR PLENUM AROUND R2/L2 DOOR AREA. LEAK WAS COMING FROM A PREVIOUS REPAI R. PLENUM REPAIRED AND CHECKED SERVICEABLE. 2 L 7 2 4F 4 F RT A2NM E12EU 2001031200459 20010312 00459 NE 2001 3 12 CA000714011 2 20000622 G 7200 ENGINE RROYCE RB21122B02 LKHEED 1011 1011385114 WP RROYCE RB211 RB21122B02 54555 NE NR 1 OVERHEATED W O OTHER M J OVER TEMP WARNING INDICATION TO TAKEOFF 1 CA 10164 10164 (CAN) DURING TAKE OFF OUT OF LAS VEGAS, TGT ON NR 1 ENGINE WENT UP TO 740 DEG FOR 2 SEC. E.P.R. BROUGHT BACK IMMEDIATELY TO MAINTAIN 728 DEG. WHEN SAFELY AIRBORNE, E.P.R. REDUCED TO .462 MAINTAIN 725 DEG. BECAUSE OF PREVIOUS PROBLEM WITH TH IS ENGINE, YYZ MAINTENANCE REDUCE N2 BY 5 CLICKS AND AIRPLANE FLEW BACK TO YMX WITH NO PAX FOR ENGINE CHANGE. WAITING F OR SHOP REPORT. 2 L 7 3 4F 4 F A23WE E12EU 2001031200461 20010312 00461 2001 3 12 CA000714013 4 20000630 G 2565 416N21133 RETAINER BOEING 757 757236 NM RROYCE RB211 RB211535E437 54555 NE GIRT BAR CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 30732 (CAN) DURING SLIDE/RAFT REPLACEMENT, THE GIRT BAR RETAINER PLATE FOUND SPLIT IN HALF DUE TO EXCESSIVE CORROSION. PLATE R EPLACED AND FLEET CAMPAIGN WILL BE DONE TO VERIFIED THE CONDITION OF THE PLATE AS PER SPECIAL INSPECTION 3-25-30 REV-0. 2 L 7 2 4F 4 F RT A2NM E12EU 2001031200465 20010312 00465 WP 2001 3 12 CA000714017 1 20000606 G 7830 CABLE DOUG DC9 DC932 3022066 WP PWA JT8 JT8D7 52053 NE THRUST REVERSER OUT OF RIG W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA P657715D (CAN) REJECTED TAKEOFF DUE LEFT HAND ENGINE REVERSER UNLOCK AMBER LIGHT ON. QUICK REFERENCE HANDBOOK PROCEDURE CARRIED O UT. REDUCING POWER RESULTED IN LIGHT GOING OUT. REVERSER RETRACTED. RE-RIGGED UNLOCK LATCH CABLE. OPERATION CHECKED NORM AL. 2 L 7 2 4F 4 F A6WE E2EA 2001031200469 20010312 00469 EA 2001 3 12 CA000714021 1 20000610 G 3260 UPLOCK TARGET CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE MLG LOOSE W O OTHER N FALSE WARNING CL CLIMB 1 CA 807264 (CAN) EICAS (ENGINE INDICATION AND CREW ALERT SYSTEM) MESSAGE FOR DISAGREEMENT FOR LANDING GEAR RETRACTION, (FOR UP LOCK ) AIRCRAFT RETURNED TO LAND IN PHILADELPHIA AFTER QRH PROCEDURE APPLIED.AFTER INSPECTION, FOUND THE UP LOCK TARGET TO BE LOOSE. RE-TIGHTENED THE TARGET, GEAR SWING COMPLETED, LANDING GEAR CHECKED SERVICEABLE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001031200470 20010312 00470 WP 2001 3 12 CA000714022 1 20000613 G 2720 5616068501 BRACKET DOUG DC9 DC932 3022066 WP PWA JT8 JT8D7 52053 NE RT ATTACH LUG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA P657537D (CAN) FIRST OFFICER RUDDER PEDAL ATTACH BRACKET CRACKED AT FORWARD RT ATTACH LUG RADIUS. AD 89-14-02. REPLACED BRACKET. 2 L 7 2 4F 4 F A6WE E2EA 2000091900007 20000919 00007 GL 2000 9 19 CA000714024 3 20000302 G 6114 HUB MCAULY MCAULY 3AF34C 3AF34C92 GL PROPELLER HUB FAILED W O OTHER O OTHER IN INSP/MAINT 1 CA 38800 (CAN) HUB MOUNTING DOWEL STUD WAS STRIPPED DUE TO AN EXCESSIVE TORQUE AT INSTALLATION. HUB S/N 733929 REMOVED FROM SERV ICE AND REPLACED BY S/N 775546. (X) 5 C P22EA 2000091900008 20000919 00008 NE 2000 9 19 CA000714025 3 20000412 G 6114 51430 BRACKET HAMSTD DHAV DHC2 DHC2MK1 2800102 EA PWA R985 R985AN14B 52008 NE HAMSTD 2D 2D30 NE BRACKET CRACKED W O OTHER O OTHER IN INSP/MAINT 1 CA 43630 JP211684 T34151 (CAN) BARREL P/N S8462, S/N T34151 FOUND CORRODED BEYOND REPAIRABLE LIMIT IAW BARREL BLADE BORE INSIDE DIAMETER SPECIFIC ATIONS. REPLACED BY BARREL S/N: NO-65520. ONE BRACKET P/N 51430 FOUND CRACKED IN RETENTION TEETH AND WAS REPLACED BY N EW PARTS. 1 H 7 1 3R 3 R A806 5E1 5 C P206 2000091900009 20000919 00009 NE 2000 9 19 CA000714029 2 20000616 G 8500 GASKET ORENDA DHAV DHC3 DHC3 2800202 EA ORENDA OE600A OE600A NE GASKETS BLOWN W A UNSCHED LANDING Y ENGINE STOPPAGE CL CLIMB 1 CA OE600A0016 (CAN) AIRCRAFT CENTER FUEL TANK INADVERTENTLY FUELED WITH JET B IN KANGIRSUK, QUE ALTHOUGH SEALED DRUM CLEARLY MARKED JE T B IT ALSO LABELLED GASOLINE 100 LL NR 19 OF 30 ON M. AIRCRAFT THEN FLEW FROM YAS TO MNR CAMP AT KANGISAVIP LAKE USIN G ONLY FIRST TANK, UNLOADED AND RETURNING TO YAS. JUST PRIOR TO TAKEOFF, PILOT SELECTED CENTER TANK FOR RETURN TRIP. J UST AFTER LIFT OFF, ENGINE BEGAN RUNNING ROUGH AND SUFFERED REDUCTION IN POWER OUTPUT, AN INCREASE IN COOLANT TEMP AND PRESSURE ALSO NOTED. SUCCESSFUL FORCED LANDING CARRIED OUT. AN INTERNAL INSP CARRIED OUT REF. C AR625 APP.G . INSP REV EALED BLOWN HEADGASKET. 1 H 7 1 3R 3 V A815 E0006A 2001031200475 20010312 00475 EA 2001 3 12 CA000714030 2 20000616 G 7322 MA3PA CARBURETOR CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA MCAULY 1A103 1A103TCM GL ENGINE MALFUNCTIONED W A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 CA 2183 L1972515 KC015 (CAN) CARBURETOR REPLACED - MALADJUSTED. 1 H 7 1 3O 3 O NT 3A19 E223 5 N P50GL 2001032600241 20010326 00241 CE 2001 3 26 CA000714031 1 20000621 G 7810 12502632 EXHAUST PIPE CESSNA 206 U206G 2073356 CE CONT O550 IO550F 17042 SO ENGINE BURNED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) EXHAUST COLLECTOR FOUND BURNED AND CRACKED. 1 H 7 1 3O 3 O A4CE E3SO 2001031200476 20010312 00476 CE 2001 3 12 CA000714032 1 20000622 G 5751 991300009 SKIN B100 BEECH 100 B100 1152919 CE GARRTT TPE331 TPE3316252B 01514 WP AILERON CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA BE39 (CAN) CRACK DISCOVERED ON THE TOP OF THE AILERON SKIN.SKIN REPLACED.AILERON REINSTALLED. 1 L 7 2 4T 4 T A14CE E2WE 2000091900010 20000919 00010 GL 2000 9 19 CA000714033 3 20000624 G 6111 FC8475B14 BLADE PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2B 41532 EA HARTZL HCE2Y HCE2YR2 GL LT HUB PROP FAILED W O OTHER O OTHER IN INSP/MAINT 1 CA 69800 37420 L286061A CJ283 (CAN) BLADES REPLACED NEW: 21 OCT 83 - PAGE 2 OF LOG. TSN: 3742.3. LAST COMPLETE OVERHAUL: 15 MAR 99 - PAGE 16 OF LOG. TSO: 6947.93. PROPELLER TIME SINCE NEW - EXCEPT FOR BLADES: 5459.4. GREASE SPLASH DETECTED ON A/C SIDE OF FUSELA GE AND ICE SHIELD. GREASE LEAK FURTHER DETECTED AT ROOT OF NR 1 BLADE. SOME PLAY IN PITCH OF BLADE. PREVIOUS OVERHAU LER INFORMED. PROPELLER RECALLED TO OVERHAUL SHOP. REMOVED AND SHIPPED FOR REPAIRS. A/C AFTT: 8637.2 HRS. ENG TSO: 1 104.6 HRS. 1 L 7 2 3O 3 O A20SO E14EA 5 C P9EA 2000080200211 20000802 00211 EU 2000 8 2 CA000714034 1 20000503 G 5310 145201 CARGO HOOK BREEZE A25LT BOLKMS 105 BO105C 5626005 EU ALLSN 250C 250C20B 03013 GL CABLE END TWISTED W O OTHER O OTHER HO HOVERING 1 CA 54560 3186 CAE835697 (CAN) THE PILOT CAME BACK FROM WORK AND REPORTED HE COULD NOT LATCH LOAD ON CARGO HOOK. A VISUAL INSP ON CARGO HOOK EM ERG RELEASE CABLE SHOWED THERE WAS TOO MUCH STRAIN ON CABLE THAT CAUSED MECHANICAL RELEASE TO MOVE THE INTERNAL HOOK MEC HANISM FROM LATCHED TO UNLATCHED MODE. SHOCK LOAD COULD THEN RELEASE LOAD FROM HOOK. TENSION ON CABLE CAME FROM POOR R OUTING UNDER FUSELAGE COCKPIT T HANDLE. MIN BEND RADIUS NOT DONE WHEN INSTALLING THE CABLE WHICH GAVE TOO MUCH STRAIN T O WHOLE ASSY. PILOT TWISTED SWAGED END OF CABLE BY TRYING TO PUSH T HANDLE ON FLOOR ON FEW OCCASIONS. NEW UPPER RELEAS E CABLE INSTALLED, RE-ROUTED, AND ASSY IS NOW WORKING PROPERLY. 1 G 7 2 3U 3 U H3EU E4CE 2000091900011 20000919 00011 SO 2000 9 19 CA000714036 1 20000604 G 2421 902241 FAN BLADE FORD ALY6421 PIPER PA44 PA44180 7104402 SO LT ALTERNATOR DISINTEGRATED W O OTHER O OTHER IN INSP/MAINT 1 CA 13680 6L000102 (CAN) DURING RUN-UP, LEFT ALTERNATOR WAS REPORTED NOT CHARGING, FLIGHT CANCELLED. AME WALKING UP TO LEFT ENGINE, FOUND TWO METAL SHARDS STICKING OUT OF NOSE BOWL COWLING. INSPECTION REVEALED THAT THE ALTERNATOR COOLING FAN DISINTEGRATED ( ALL BLADES WERE GONE FROM BEHING THE PLATE) AND THE TWO PIECES STUCK IN THE COWLING WERE BLADES. FIELD WIRE FOUND CUT. NO EVIDENCE OF JAMMING (NO DAMAGE TO ALT BODY) OR BELT SLIPPAGE. NEW ALTERNATOR INSTALLED AND FIELD WIRE REPAIRED. 1 L 7 2 3O A19S0 2000100200097 20001002 00097 SO 2000 10 2 CA000714037 1 20000614 G 7160 6367400 SCREW PIPER 6577800 PIPER PA28 PA28140 7102802 SO LYC O320 O320E2A 41508 EA SNSNCH 74D 74DM EA THUMB SCREW WORN W O OTHER O OTHER CR CRUISE 1 CA L4002627A A56007 (CAN) THE RETAINING BOLT FOR THE AIR FILTER HOUSING BACKED OFF FROM THE TORQUED POSITION AND ALLOWED THE HOUSING TO MOVE FORWARD AND STRIKE THE PROPELLER DURING FLIGHT. A VIBRATION WAS FELT BY THE PILOT AND HE RETURNED THE AIRCRAFT TO BASE AND LANDED SAFELY. MAINTENANCE INSPECTION REVEALED THAT THE FIBER LOCK ANCHOR NUT IN THE AIR FILTER HOUSING WAS IN WOR N CONDITION WITH LITTLE OR NO LOCK FEATURE REMAINING. A FLEET CAMPAIGN TO CHECK ALL SIMILAR INSTALLATION IS IN PROGRESS . (ENGINE/PROP REMOVED FOR REPAIR.) 1 L 7 1 3O 3 O 2A13 E274 5 N P88614 2000100200098 20001002 00098 EA 2000 10 2 CA000714038 2 20000525 G 8530 PUSHROD LYC PIPER PA34 PA34200 7103405 SO LYC O360 LIO360C1E6 41515 EA PUSHROD BENT W A E UNSCHED LANDING ENGINE SHUTDOWN E VIBRATION/BUFFET AP APPROACH 1 CA 40000 L32867A (CAN) CREW EXPERIENCED ROUGH RUNNING ENGINE (RT) WHILE ON APPROACH. CREW POWERED BACK, LANDING WITHOUT FURTHER INCIDENT . UPON INVESTIGATION BY MAINTENANCE, IT WAS DISCOVERED THAT 2 NUTS HAD BACKED OFF ON THE COVER PLATE FOR THE ROCKER PIN CAUSING THE PLATE TO FALL OFF. THIS CAUSED THE PIN TO MOVE ITS WAY OUT OF THE CYLINDER CAUSING THE PUSHROD TO BEND AND SUBSEQUENT OIL LEAKAGE. CYLINDER ASSEMBLY WAS REPLACED. AIRCRAFT RELEASED TO SERVICE WITHOUT FURTHER INCIDENT. 1 L 7 2 3O 3 O A7SO 1E10 2000100200099 20001002 00099 EA 2000 10 2 CA000714039 1 20000614 G 2435 30F1611C GENERATOR BENDIX DHAV DHC3 DHC3 2800202 EA PWA R1340 R134059 52016 NE GENERATOR FAILED W O OTHER H ELECT. POWER LOSS-50 PC IN INSP/MAINT 1 CA 27700 R1081M (CAN) GENERATOR NOT SUPPLYING POWER. 1 H 7 1 3R 3 R A815 5E2 2000100200100 20001002 00100 NE 2000 10 2 CA000714040 2 20000618 G 8530 CYLINDER DHAV DHC3 DHC3 2800202 EA PWA R1340 R134059 52016 NE CYLINDER ASSY CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 28600 (CAN) NR 1 CYLINDER HEAD CRACKED. 1 H 7 1 3R 3 R A815 5E2 2000100200242 20001002 00242 EA 2000 10 2 CA000718017 2 20000626 G 8550 LW13904 ADAPTER CONT PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA CONVERTER PLATE FAILED W O OTHER O OTHER CR CRUISE 1 CA 14900 L224168A (CAN) PILOT REPORTED OBSERVING WHITE FUMES COMING OUT OF LEFT ENGINE DURING CRUISE. EMERG FIRE DRILL CARRIED OUT, AND F IRE OUT. JOURNEY LOG NR 653 REFERS. INVEST ON GROUND CONDUCTED, FOUND FIRE DAMAGE TO HIGH TENSION MAGNETO LEADS, OIL H OSES, HYDRAULIC AND FUEL HOSES, ELECTRIC WIRINGS. MAGNETO, FUEL PUMP, HYDRAULIC PUMP, VACUUM PUMP WERE AFFECTED. OIL STAINS REMAINING WITHIN AREA BETWEEN FIREWALL AND AFT OF CRANKCASE ACCESSORY HOUSING, AND FIRE CONTAINED WITHIN THIS ARE A ONLY. ATTEMPTED TO FIND CAUSE OF FIRE: FUEL PUMP TURNED ON, NIL FUEL LEAKAGE EVIDENT FROM PUMP AND HOSES. DRY MOTOR RUN ALSO CARRIED OUT, DISCOVERED FRESH OIL DRIPPING THROUGH PRESSURE OIL FILTER SEAL. 1 L 7 2 3O 3 O A20SO E14EA 2001031300009 20010313 00009 EA 2001 3 13 CA000718018 2 20000705 G 8500 ENGINE GRUMAN TS2 TS2ACALFORST 3951102 WP WRIGHT R1820 982C9HE2 67020 EA HAMSTD 43D 43D51 NE ENGINE BAY MAKING METAL W E A ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION NR NOT REPORTED 1 CA 719 524181 229707 (CAN) DURING FIREFIGHTING OPERATIONS THE PILOT NOTICED AN INCREASE IN OIL TEMPERATURE AND A DECREASE IN OIL PRESSURE. PO WER WAS REDUCED AND THE PROPELLER WAS FEATHERED. THE AIRCRAFT RETURNED TO YKA. THE MAIN OIL SCREEN AND THE HIGH CAPACITY OIL SCREENS WERE REMOVED FOR INSPECTION. BOTH FILTERS HAD STEEL AND ALUMINUM CONTAMINATION. THE ENGINE WAS REMOVED AND A SERVICEABLE ENGINE QCU WAS INSTALLED. THE AIRCRAFT WAS TEST FLOWN AND RETURNED TO SERVICE. 2 H 7 2 4R 4 R A25WE E259 6 C P8879 2000080200212 20000802 00212 SW 2000 8 2 CA000718019 1 20000626 G 6410 212010750105 TAIL ROTOR BELL 212010701029 BELL 205 205A1 1181414 SW LYC T53 T5317A 41549 NE OUTBOARD TIP MISSING W O OTHER O OTHER CR CRUISE 1 CA 26790 A2901262 LEO7669C (CAN) WHILE IN FLIGHT,TAIL ROTOR TIP CLOSURE FROM BLADE S/N A-9612 DEPARTED BLADE. ENSUING, EXTREME VIBRATION, CAUSED PI LOT TO LAND IMMEDIATELY, WITHOUT FURTHER DAMAGE TO A/C. INSPECTION OF T/R SHOWED TIP CLOSURE OF BLADE S/N A-9612 TO BE GONE IN ITS ENTIRETY, LEAVING HONEYCOMB INNER STRUCTURE TOTALLY EXPOSED. BOTH BLADES WERE REMOVED FROM ASSY AND WERE FO RWARDED TO TSB (PICKWICK). T/R HUB ASSY IS BEING HELD IN QUARANTINE AT CONAIR HELICOPTERS TILL FURTHER NOTICE. AS AN ADD ITIONAL PRECAUTION 90 DEGREES T/R GEARBOX HAS BEEN REMOVED FOR OVERHAUL. A/C INSP FOR FURTHER DAMAGE - NONE FOUND. REP LACED 90 DEGREES TAIL ROTOR GEARBOX, TAIL ROTOR ASSY AND PITCH CHANGE ASSY INSTA 1 G 7 1 4U 4 U H1SW E17EA 2000080200213 20000802 00213 SW 2000 8 2 CA000719003 1 20000406 G 5330 2050310778 FASTENER BELL STC212 BELL 212 212 1181420 SW PWA PT6T PT6T3 52045 EA LT DOOR POST CORRODED W O OTHER O OTHER IN INSP/MAINT 1 CA 88740 30877 CPPS61425 (CAN) EXCESSIVE DISSIMILAR METAL CORROSION CAUSED BY SHEET METAL CLECOS BEING LEFT IN SINCE MANUFACTURE. THEY WERE LOCAT ED IN THE LEFT-HAND DOOR POST ON BULKHEAD STATION 63.27. NOTE: THIS AREA IS NOT ACCESSIBLE UNLESS THE SKIN IS REMOVED. IT WAS FOUND DURING A 300. 1 G 7 1 4U 4 U H4SW E22EA 2000080200214 20000802 00214 EU 2000 8 2 CA000719004 1 20000502 G 2435 150SG122Q STARTER GEN SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1B 6OO30 NE ENGINE FAILED W O OTHER O OTHER IN INSP/MAINT 1 CA 32770 5700 4432 4432 (CAN) STARTER/GENERATOR FOUND TO BE CAUSING EXCESSIVE ENGINE VIBRATION. UNIT REPLACED. 1 G 7 1 3U 3 U H9EU E19EU 2001032600377 20010326 00377 EU 2001 3 26 CA000719007 1 20000628 G 2810 1608550 VALVE FOKKER F28 F28MK1000 4990808 EU FUSELAGE STUCK W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA (CAN) ON TAKEOFF OUT OF WINNIPEG, CREW NOTED THAT FUEL WAS VENTING OUT OF LT WING. CREW ELECTED TO RETURN YWG, & LANDED WITH NO FURTHER EVENTS. MAINT INVEST. REVEALED NR 1 TANK OVERFLO W VALVE WAS STUCK IN OPEN POS, CONFIRMED BY GREN IND ON A/C REFUELING PANEL. VALVE WAS CLOSED MANU, & PRESSURE REFUELING SYS WAS ACTIVATED A NO OF TIMES TO C HECK VALVE OPERAI TON, NO FURTHER DISCREPANCIES. A/C WAS RT-SRV. NOTE: OVERFLOW VALVES INDICATE OPEN ON REFUELING PANEL DURING REFUELING. IT IS STANDARD PROC FOR REFUEL ERS TO ADVISE FLT CREW WHEN GREEN LIGHT(S) REMAIN ON ON COMPLETION OF REFUELINGTHIS WAS MISSED ON THIS OCCASION. 2 L 7 2 4F RT A20EU 2000100200254 20001002 00254 CE 2000 10 2 CA000719009 1 20000623 G 2800 120040696 LINE CESSNA 210 210L 2073448 CE CONT O520 IO520L 17032 SO FUEL LINE ASSY ERODED W O OTHER K FLUID LOSS IN INSP/MAINT 1 CA 572188 (CAN) FUEL WAS LEAKING FROM BELLY OF AIRCRAFT WHILE PARKED. FLOOR WAS OPENED AND FUEL LINE BETWEEN FUEL PUMP AND F/W WA S ERODED (PITTED) AND LEAKING FUEL INTO BELLY. LINE WAS REMOVED AND REPLACEMENT LINE INSTALLED. 1 H 7 1 3O 3 O 3A21 E5CE 2001032600385 20010326 00385 CE 2001 3 26 CA000719010 1 20000628 G 5311 FRAME BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA MCAULY 4HFR34 4HFR34C754 NE FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) 0.75 INCH CRACK AT TOP OF SIDE FRAME INSIDE BEND RADIUS. 1 L 7 2 4T 4 T A24CE E4EA 6 C 3PNE 2001032600386 20010326 00386 CE 2001 3 26 CA000719011 1 20000629 G 2500 551900921 SEAT CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE CABIN CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 5137 (CAN) THE LEFT AFT SEAT WAS REMOVED AND INSPECTED FOR CRACKING OF THE SEATBACK MOUNT TUBE. THE TUBE WAS FOUND CRACKED OU TBOARD OF THE OUTBOARD SEAT BACK PICKUP AND A CRACK JUST STARTING OUTBOARD OF THE INBOARD SEATBACK PICKUP. SEAT REPAIRED AND REINSTALLED. 1 L 7 2 4F 4 F A22CE E1NE 2000100200257 20001002 00257 WP 2000 10 2 CA000719012 1 20000708 G 7721 84085A1 CYLINDER PWA CVAC PBY5 PBY5A 2421208 WP PWA R1830 R183092 52020 NE CYLINDER CRACKED W O OTHER R PARTIAL RPM/PWR LOSS CL CLIMB 1 CA 66800 CP316780 CP316780 (CAN) DURING CLIMB OUT , THE RIGHT ENGINE STARTED TO RUN ROUGH. THE PILOT FEATHERED THE ENGINE AND RETURNED TO YELLOWKNI FE .MAINTENANCE FOUND 2 CRACKS AT THE EXHAUST PORT OF NR 7 CYLINDER OF THE RT ENGINE. THESE HAD STARTED TO SPREAD AND L IKELY CAUSED THE EXHAUST VALVE TO MALFUNCTION. MAIN OIL SCREEN CHECKED AND SUMP DRAINED, NO CONTAMINATION FOUND. THE CYLINDER WAS REPLACED, ENGINE GROUND RUN AND RETURNED TO SERVICE. (X) 2 H 7 2 4R 4 R 2548 5E4 2000080300220 20000803 00220 SW 2000 8 3 CA000719013 1 20000630 G 6320 206040151015 CASE BELL 206040002013 BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL TRANSMISSION CRACKED W O OTHER K FLUID LOSS IN INSP/MAINT 1 CA 51500 B1285 CAE820706 (CAN) OIL WAS NOTED LEAKING FROM TRANSMISSION DURING GROUND RUN. REMOVAL OF THE PAINT REVEALED A CRACK ON THE UPPER CAS E STARTING FROM THE SPLIT LINE BETWEEN TWO MOUNTING STUDS AT THE 4:30 POSITION, VIEWED FROM THE TOP. AIRCRAFT WAS GROUN DED, TRANSMISSION REMOVED. 1 G 7 1 3U 3 U H2SW E4CE 2000100200258 20001002 00258 SO 2000 10 2 CA000719014 1 20000620 G 5310 46624 DOUBLER PIPER PIPER PA31T PA31T 7103124 SO PWA PT6 PT6A28 EA BEND RADIUS CRACKED W O OTHER O OTHER IN INSP/MAINT 1 CA 31T7620019 PCE42096 (CAN) DOUBLER CRACKED IN RADIUS. DOUBLER IS A COMPONENT IN STRUCTURE SEWING AIR STAIR DOOR HINGE TO DOOR AND SUBSEQUENT LY THE DOOR TO THE AIRFRAME. 1 L 7 2 3T 4 T A8EA E4EA 2000100200066 20001002 00066 EU 2000 10 2 CA000719016 1 20000707 G 5520 ELEVATOR PILATS PILATS PC12 PC1245 EU RT ELEVATOR FAILED W A UNSCHED LANDING F FLT CONT AFFECTED DE DESCENT 1 CA 193 (CAN) AIRCRAFT WAS STRUCK BY LIGHTNING DURING DESCENT. LIGHTNING STRUCK RT ELEVATOR OUTBOARD TIP. EXIT THROUGH PROPELL ER. SLIGHT BURN/ARC DAMAGE TO ELEVATOR. BURN/ARC DAMAGE ON PROPELLER 5 INCHES FROM TIP ON ONE BLADE. UNKNOWN DAMAGE T O POWER SECTION OF ENGINE DUE TO ARC DAMAGE TO BEARINGS. AIRCRAFT WAS FERRIED TO V. KELNER - THUNDER BAY, ONTARIO FOR P ROP AND ENGINE CHANGE AND REPAIRS TO RT ELEVATOR. 1 L 7 1 3T RT A78EU 2000100200259 20001002 00259 SO 2000 10 2 CA000719017 1 20000702 G 3213 40327000 TRUNNION PIPER PA31 PA31350 7103110 SO LYC T53 T5313B 41549 NE HARTZL HCE3Y HCE3YR2 GL FORGING SEAMLINE CRACKED W O OTHER O OTHER IN INSP/MAINT 1 CA LEO7592 (CAN) DURING OVERHAUL AND LPI NDT, NOTED CRACK ON FORGING SEAM LINE. ATTEMPTS TO DRESS OUT SEAM LINE AND CRACK WERE UNS UCCESSFUL AS CRACK WAS TOO DEEP. THIS PROBLEM WAS NOT VISIBLE TO THE NAKED EYE. 1 L 7 2 3O 4 U A20SO E17EA 5 C P33EA 2000100200260 20001002 00260 EU 2000 10 2 CA000719018 1 20000525 G 5541 NB4513544 BEAM BNORM BNORM BN2 BN2A26 1520226 EU LYC O540 O540E4C5 41532 EA RUDDER BEAM CRACKED W O OTHER O OTHER IN INSP/MAINT 1 CA 2017 RL1609440A (CAN) FLUORESCENT LP EXAMINATION WAS CONDUCTED ON THE AIRCRAFT PILOT, COPILOT LT, RT RUDDER PEDAL TORQUE ARM RADIUS. RE SULTS: COPILOT RUDDER SET REVEALED REJECTABLE CRACK INDICATIONS AS MARKED. IN SERVICE BULLETIN (PRECAUTIONARY EXAMINAT ION) THERE WERE NO REJECTABLE INDICATION IN ACCORDANCE WITH CODE ON THE PILOT SET. 1 H 7 2 3O 3 O A17EU E295 2000100200262 20001002 00262 CE 2000 10 2 CA000719019 1 20000717 G 7603 5038901215 CABLE CONT BEECH 100 100BEECH 1152916 CE CONT O470 IO470L 17026 SO MCAULY 2AF34C 2AF34C55 GL THROTTLE CABLE SEPARATED W E ENGINE SHUTDOWN O OTHER CR CRUISE 1 CA 28850 468033 468033 711344 (CAN) DURING CRUISE FLIGHT, THE RIGHT THROTTLE CABLE FAILED RESULTING IN A FULL THROTTLE CONDITION. THE ENGINE WAS SHUT DOWN AND SECURED AND THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. THE THROTTLE CABLE WAS REPLACED AND THE AIRCRAFT RE TURNED TO SERVICE. 1 L 7 2 3T 3 O A14CE 3E1 5 C P5EA 2000100200263 20001002 00263 SO 2000 10 2 CA000719020 1 20000621 G 5312 416580 BULKHEAD PIPER PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2B 41532 EA FLANGE RADIUS CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 12596 31743 L198561 (CAN) WHILE PERFORMING UNSCHEDULED MAINTENANCE, A BULGE WAS OBSERVED ON FUSELAGE SKIN AROUND THE FORWARD WING SPAR PICKU P FITTING. FURTHER INSPECTION REVEALED BOTH LT AND RT FROST SPAR ATTACHMENT BULKHEADS P/NS 41658-0 AND -1 WERE CRACKED AND ALSO LT AND LT FRONT SPAR ATTACHMENT CHANNEL P/N''S 40603-0 AND -1 WERE CRACKED. ATTACHMENT BULKHEADS WERE REPLACED WITH NEW PIPER P/N''S 52694-0 AND 52694-01. FRONT SPAR ATTACHMENT CHANNELS WERE REPLACED. WITH NEW PIPER P/N''S 40603 -02 AND 40603-03. 1 L 7 2 3O 3 O A20SO E14EA 2000080300221 20000803 00221 SW 2000 8 3 CA000719021 1 20000630 G 6410 206310105101 BEARING BELL 206016201127 BELL 206 206L 1181522 SW TAIL ROTOR BLACE LOOSE W O OTHER O OTHER IN INSP/MAINT 1 CA 63700 CS5021 (CAN) EXCESS BEARING PLAY. BEARING WAS LOOSE IN THE SLEEVE. REPLACED BEARINGS IN ACCORDANCE WITH BHT 206L M&O. 1 G 7 1 3U H2SW 2001031300011 20010313 00011 EA 2001 3 13 CA000719022 1 20000626 G 2612 28506038 DETECTOR CNDAIR CL215 CL2151A10 EA HAMSTD 43E 43E60 NE RT NACELLE FALSE INDICATION W E F ENGINE SHUTDOWN ACTIVATE FIRE EXT. N FALSE WARNING NR NOT REPORTED 1 CA 3274 (CAN) WHILE PICKING UP A WATER LOAD THE GROUND POWER UNIT - 2 FIRE WARNING LIGHT STARTED TO FLICKER AND THEN STAYED ON S TEADY WITH THE WARNING BELL. FOLLOWING PROCEDURES THE CREW SHUT DOWN THE RT ENGINE AND DISCHARGED FIRE BOTTLE INTO THE N ACELLE PROTECTED AREA. AIRCRAFT LANDED WITHOUT INCIDENT. NO SIGN OF FIRE IN GPU-2 AREA. APPEARS TO HAVE BEEN A FALSE IND ICATION. SYSTEM WIRING CHECKED BY MAINTENANCE - UNABLE TO DUPLICATE FIRE WARNING. 2 H 7 2 4R A14EA 6 C P871 2000100200264 20001002 00264 EU 2000 10 2 CA000719023 1 20000705 G 5510 NS03089301 BRACKET TRNSQP TRNSQP KR03A KR03A 1130847 EU HORIZ STAB CRACKED W O OTHER O OTHER IN INSP/MAINT 1 CA 70000 0402 (CAN) WHILE INSPECTING VERTICAL STABILIZER LEADING EDGE IMPACT ON SKIN, A CRACK WAS IDENTIFIED ON THE LEFT HAND HORIZONT AL STABILIZER ATTACH BRACKET. NDT BY EDDY CURRENT METHOD CONFIRMED A .0625 INCH CRACK EMANATING FROM A WELD TERMINATIO N OF A DOUBLER ON BRACKET. NEW BRACKETS INSTALLED ON BOTH LEFT AND RIGHT SIDES AS NEW BRACKETS MADE FROM THICKER, NON-W ELDED MATERIAL. 1 K 0 0 RC G56EU 2000100200147 20001002 00147 CE 2000 10 2 CA000719024 1 20000625 G 2820 50921592 RESTRICTOR VALVE BEECH 90 C90A 1152911 CE PWA PT6 PT6A21 52043 EA DEBONDED BACKED OUT W A UNSCHED LANDING O OTHER CR CRUISE 1 CA 42580 PCE25678 (CAN) PILOTS REPORTED A PROBLEM OF SLOW TO NO FUEL TRANSFER ON PORT SIDE OF FUEL SYSTEM. UPON TROUBLESHOOTING THE SYSTE M, FOUND THE RESTRICTOR FROM THE TEE RESTRICTOR P/N 50-921592 HAD BECOME DEBONDED AND TRAVELLED DOWN STREAM TO THE NEXT TEE FITTING AND BECAME LODGED. THIS RESTRICTED THE LINE AND LIMITED THE FLOW OF FUEL FROM THE TEE FITTING TO THE NACELL E TANK CAUSING THE SLOW FUEL TRANSFER PROBLEM. 1 L 7 2 3T 4 T RT 3A20 E4EA 2001032600019 20010326 00019 CE 2001 3 26 CA000719025 1 20000710 G 2752 505212234 ACTUATOR BEECH 99 99A 1154003 CE PWA PT6 PT6A27 52043 EA TE FLAP CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) PART NUMBER FOR TIME X CONDITION. CENTRE SHAFT LONGITUDINAL CRACKED. CRACK DISCOVERED AFTER REMOVAL. 1 L 7 2 3T 4 T A14CE E4EA 2001032600020 20010326 00020 CE 2001 3 26 CA000719026 1 20000709 G 2750 101380001 SHAFT BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA LT WING TE FLAPS TWISTED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) FLAP JUMPED FLAP LIMIT & SWITCH, WHILE GOING IN TO THE UP POSITION AND CAUSING A FAILURE OF THE FLAP SHAFT LT OUTB OARD TELEFLEX ASSY. RECTIFICATION: REPLACED THE FLAP MOTOR. INSPECTED THE 90 DEGREES DRIVE. INSPECTED THE FLAP TRANSMIS SION AND REPLACED THE FLAP FLEXIBLE DRIVE (SHAFT ASSY). FLAP SYSTEM RIGGED, TESTED AND AIRCRAFT RETURNED TO SERVICE. 1 L 7 2 4T 4 T A24CE E4EA 2001031300012 20010313 00012 EA 2001 3 13 CA000719027 1 20000606 G 2913 SCREW CNDAIR CL215 CL2151A10 EA HAMSTD 43E 43E60 NE LT HYD PUMP BROKEN W K NONE J K WARNING INDICATION FLUID LOSS IN INSP/MAINT 1 CA 570 N184505 (CAN) HYDRAULIC PUMP CAP SCREWS BROKEN ALLOWING HEAD TO SEPARATE FROM BODY. HYDAULIC FLUID DISCHARGED THROUGH SEPARATION IN PUMP. CREW LANDED AIRCRAFT USING EMERGENCY HYDRAULICS. 2 H 7 2 4R A14EA 6 C P871 2001032600025 20010326 00025 GL 2001 3 26 CA000719028 2 20000607 G 7250 23053299 BLADE ALLSN 250C 250C30P 03013 GL 1ST TURB WHEEL FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 1136 (CAN) DURING DISMANTLING OF THE TURBINE, THE 1ST STAGE WHEEL HAD SUFFERED A SINGLE BLADE FAILURE. AFTER THE FAILURE, TH E BLADE DAMAGED THE REMAINING COMPONENTS DOWNSTREAM CRACK ORIGINATION SITE APPEARS TO BE ON LOWER LEADING EDGE OF BLADE. 2ND STAGE EXTEX NOZZLE INSTALLED IN THE TURBINE. 3 U E1GL 2001032600026 20010326 00026 SO 2001 3 26 CA000719029 1 20000621 G 3230 14469 BOLT 14480 EMB 110 EMB110P1 3260122 SO PWA PT6 PT6A34 52043 EA TORQUE LINK ASSY SHEARED W O OTHER O OTHER LD LANDING 1 CA (CAN) A/C ON LANDING ROLLOUT PULLED TO R/H WHEN STOPPED. RT GEAR 90 DEGS TO DIRECTION OF FLT. MAINT HALF OF P/N 16469 CE NTRE TORQUE LINK BOLT STILL IN PLACE. REPLACED BOLT FERRIED A/C TO MAINBASE. INSP CARRIED OUT USING MAINTENANCE MANUAL & 625 APPENDIX G. ABNORMAL OCCURRENCES FOR REFERENCE & INSPECTING AXLES & DRAG BRACES FOR AREAS THAT WOULD BE AFFECTED BY HIGH DRAG LOAD. VISUAL INSP CARRIED OUT ON P/N 14469 ON REMAINING EMBS WITH FLEET WIDE REPLACEMENT TO FOLLOW. TOOLING M ARKS ARE FROM REMOVAL. 1 L 7 2 4T 4 T A21SO E4EA 2000100200148 20001002 00148 CE 2000 10 2 CA000719030 1 20000607 G 2120 131823E4 CLAMP BEECH 100 A100 1152915 CE PWA PT6 PT6A28 EA EVA TUBING CLAMP FAILED W A E UNSCHED LANDING ENGINE SHUTDOWN I FLT. ATTITUDE INST. CR CRUISE 1 CA PCE50661 (CAN) DURING A COMPANY TRAINING FLIGHT, THE LT BLEED AIR FAIL ANNUNCIATOR LIGHT (RED) ILLUMINATED. A S PER PROCEDURES, T HE LT BLEED AIR SWITCH WAS SELECTED TO THE OFF POSITION. A VISUAL MEANS TO ASCERTAIN THE VALVE IS WORKING IS WHEN SELEC TED TO OFF, A SLIGHT RISE IN TQ OCCURS. THE CREW WAS UNCERTAIN THAT THE VALVE WAS OPERATIONAL AND THUS THEY COMPLETED A PRECAUTIONARY ENGINE SHUTDOWN. UPON INSPECTION IN THE HANGAR, NOTED THE EVA TUBING HAD SOMEHOW BECOME DISCONNECTED FROM THE EVA TUBING SUPPLY MANIFOLD, REDUCING PRESS TO ZERO AND ACTIVATING THE ANNUNCIATOR LAMP. THE LINE WAS RE-SECURED. THE BLEED AIR SHUT-OFF VALVE (LT) WAS ALSO TESTED AND FOUND TO BE FUNCTIONING PROPERLY. 1 L 7 2 3T 4 T A14CE E4EA 2000100200149 20001002 00149 EA 2000 10 2 CA000720002 1 20000106 G 5712 C6WF110067768 RIB DHAV C6WF10023 DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA FLAP CNTRE HINGE LOOSE W O OTHER O OTHER IN INSP/MAINT 1 CA 23987 317 PCE40361 (CAN) EXCESSIVE LOOSENESS BETWEEN THE TWO HALVES OF THE FLAP AT THE CENTER HINGE ARM POSITION. THE RIBS ON EITHER SIDE O F THE HINGE ARM ARE ASSEMBLED TO THE ARM BY THE USE OF LONG MS20470AD5 SOLID RIVETS. IT WOULD APPEAR THAT THERE HAS BEE N SOME WORKING BETWEEN THE RIVET HEADS (MANUFACTURES) AND THE OUTBOARD RIB WHICH HAS CAUSED WEARING OF THE RIB AROUND TH E RIVET HOLES. (X) 1 H 7 2 3T 4 T RT A9EA E4EA 2000100200150 20001002 00150 EA 2000 10 2 CA000720003 1 20000709 G 8012 3020958 VALVE SEAT PWA DHAV DHC3 DHC3 2800202 EA PWA PT6 PT6A34 52043 EA VALVE SEAT FAILED W O OTHER O OTHER DE DESCENT 1 CA 41697 (CAN) THE PILOT FLYING ALONG. WHEN REDUCED POWER FOR DESCENT, OIL PRESSURE DROPPED FROM 90 PSI TO 50 PSI. PILOT LANDED IMMEDIATELY AND SHUT DOWN ENGINE. ENGINE INSP, FOUND NON-MAGNETIC PARTICLES IN OIL FILTER. THE CHIP DETECTOR AND REDU CTION GEARBOX AREA WERE CHECKED. NO PARTICLES FOUND. OIL TANK DRAINED AND CHECKED. NO PARTICLES FOUND. REAR ACCESSO RY GEARBOX DRAINED AND CHECKED. FEW SMALL PARTICLES FOUND. PRESSURE RELIEF VALVE REMOVED, DISASSEMBLED. FOUND SMALL P ARTICLE OF NON-MAGNETIC MATERIAL ON VALVE SEAT. PRESSURE RELIEF VALVE RE-ASSEMBLED AND INST OIL SYS FLUSHED, REPLENISHE D. GROUND RUNS AND INSPS WERE CARRIED OUT IAW WITH P&W MM. NO FURTHER METAL GENERATED. 1 H 7 1 3R 4 T A815 E4EA 2000100200219 20001002 00219 EA 2000 10 2 CA000720004 1 20000714 G 2710 C3CF2015 CONTROL CABLE DHAV DHAV DHC3 DHC3 2800202 EA PWA PT6 PT6A27 52043 EA AILERON FRAYED W K NONE O OTHER IN INSP/MAINT 1 CA PCE40691 (CAN) WHILE CARRYING OUT AN 800 HOUR INSPECTION, THE RT AILERON CABLE WAS FOUND TO BE FRAYED. THE DAMAGE TO THE CABLE WAS LOCATED AT THE PULLEY WHERE THE CABLE GOES THROUGH THE COCKPIT FLOOR BY THE COPILOT SEAT. THE 800 HOUR INSPECTION R EQUIRES THAT YOU INSPECT THE CABLE THROUGHOUT ITS ENTIRE LENGTH. IT SHOULD BE NOTED THAT THIS DAMAGE WOULD NOT HAVE BEE N FOUND WITHOUT THE REMOVAL OF THE CABLE WHICH IS STANDARD COMPANY POLICY ON AN 800 HOUR INSPECTION. 1 H 7 1 3R 4 T A815 E4EA 2000100200220 20001002 00220 EA 2000 10 2 CA000720005 1 20000714 G 5523 C3TE1312 TAB DHAV C3TE1111 DHAV DHC3 DHC3 2800202 EA PWA PT6 PT6A135 52043 NE LEVER LOOSE W O OTHER O OTHER IN INSP/MAINT 1 CA PCE92418 (CAN) WHILE CARRYING OUT THE 100 HOUR INSPECTION OF THE SERVO TAB, THE ENGINEER NOTICED THAT THERE WAS EXCESSIVE PLAY IN THE ELEVATOR SERVO TAB OPERATING LEVER. UPON FURTHER INVESTIGATION, FOUND THE SERVO TAB HAD TO BE REPLACED DUE TO WEAR ON THE OPERATING LEVER BOLT HOLE. SUBMITTER STATED IT SHOULD BE NOTED THAT NUMEROUS PROBLEMS HAVE BEEN FOUND IN THIS A REA. WOULD IT NOT BE WISE TO MANDATE A 50 HOUR INSPECTION OF THE SERVO TABS? 1 H 7 1 3R 4 T A815 E4EA 2000100200221 20001002 00221 EA 2000 10 2 CA000720006 1 20000714 G 2720 VALC3UF619 CONTROL CABLE DHAV DHC3 DHC3 2800202 EA PWA PT6 PT6A135 52043 NE WATER RUDDER FRAYED W K NONE O OTHER IN INSP/MAINT 1 CA PCE92418 (CAN) WHILE CARRYING OUT AN INSPECTION OF THE WATER RUDDER CABLES, THE ENGINEER FOUND THE WATER RUDDER STEERING CABLE TH AT ATTACHES TO THE RUDDER BELLCRANK BELOW THE PILOTS FLOOR WAS SEVERELY FRAYED WHERE IT CONTACTS THE FORWARD PULLEY ON T HE BACKSIDE OF THE FIREWALL. THE CABLE WAS REPLACED. 1 H 7 1 3R 4 T A815 E4EA 2000100200067 20001002 00067 EU 2000 10 2 CA000720007 1 20000706 G 2434 HED60CR132903 BRUSH BLOCK 5243212158 PILATS PC12 PC1245 EU BRUSH BLCOK ASSY WORN W O OTHER O OTHER LD LANDING 1 CA 68600 100092 (CAN) UPON LANDING NR 2 GENERATOR WENT OFF LINE RED ANNUNCIATOR GEN 2 OFF ILLUMINATED. PILOT WAS UNABLE TO RESET GENERA TOR. INVESTIGATION OF GENERATOR SYSTEM FOUND NR 2 GENERATOR BRUSHES WERE WORN TO THE EXTENT THE BRUSHES NO LONGER CONTA CTED THE SLIP RINGS. A NEW GENERATOR WAS INSTALLED. GROUND RUN CARRIED OUT AND ALL WAS SATISFACTORY. SUBMITTER STATED THERE IS NO CALL OUT IN THE PILATUS MAINTENANCE MANUALS TO INSPECT CONDITION OF NR 2 GENERATOR BRUSHES FOR CONDITION OR LENGTH. 1 L 7 1 3T RT A78EU 2000072700171 20000727 00171 CE 2000 7 27 CA000720008 1 20000720 G 7100 105217 CARBURETOR LYC O320H2AD CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA MCAULY 1C160 1C160DTM GL MIXTURE CNTRL FAILED W O OTHER O OTHER IN INSP/MAINT 1 CA 85000 L81876T L81876T 79744 (CAN) THE RECENTLY OVERHAULED ENGINE WOULD START (ON PRIMING FUEL) AND THEN QUIT (AS IF THE MIXTURE CONTROL WAS IN IDLE CUTOFF), CARBURETOR REMOVED AND ANOTHER CARB PUT ON ENGINE - RAN NORMAL CARB MIXTURE, CONTROL SEEMS TO BE STUCK ON IDLE CUT-OFF INTERNALLY, ALTHOUGH EXTERNAL CONTROL ARM MOVES FROM LEAN TO RICH - SENT TO OVERHAUL FACILITY FOR REPAIR. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2000072700172 20000727 00172 CE 2000 7 27 CA000720009 1 20000620 G 7100 O-RING CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA CASE/STUD WRONG PART W O OTHER K FLUID LOSS IN INSP/MAINT 1 CA 77500 L623815 (CAN) DURING TROUBLESHOOTING FOR AN ENGINE OIL LEAK, IT WAS DETERMINED THAT OIL WAS SEEPING OUT THE CENTER THROUGH-BOLT STUDS; ENGINE AND CRANKCASE WAS DISASSEMBLED FOR ACCESS TO THE THROUGH-STUD O-RINGS. IT WAS THEN DISCOVERED THAT THE WR ONG O-RINGS WERE INSTALLED ON THE 6 THROUGH-STUDS. THE O-RINGS WERE THICKER THAN THE RECESS WAS GROOVED OUT FOR AND AS A RESULT THE 6 O-RINGS WERE SQUASHED AND STUCK IN THE MATING SURFACES OF THE CRANKCASE HALVES, WHICH RESULTED IN A LOSS OF TORQUE AND FRETTING OF THE CRANKCASE MATING SURFACES. THE CRANKCASE HALVES NEEDED TO BE MILLED AND LINE BORED. 1 H 7 1 3O 3 O NT 3A19 E223 2000072700173 20000727 00173 SO 2000 7 27 CA000720010 1 20000628 G 3260 487862 SWITCH PIPER PA31T PA31T2 7103127 SO PWA PT6 PT6A135 52043 NE NLG OUT OF ADJ W L ABORTED APPROACH J WARNING INDICATION AP APPROACH 1 CA PCE92653 (CAN) - PILOT DID NOT RECEIVE NOSE GEAR DOWN LIGHT INDICATION AFTER CYCLING GEAR DOWN FOR LANDING. MAINTENANCE ADVISE D PILOT TO USE RUDDER PEDALS TO ACTIVATE NOSE GEAR DOWN MICROSWITCH. THIS ACTION GAVE NOSE GEAR DOWN INDICATION TO PILO T. THE AIRCRAFT WAS LANDED WITHOUT ANY INCIDENT. MAINTENANCE JACKED THE AIRCRAFT, CYCLED GEARS AND ADJUSTED THE NOSE GEAR DOWN MICROSWITCH. 1 L 7 2 3T 4 T RT A8EA E4EA 2000080300222 20000803 00222 GL 2000 8 3 CA000720012 2 20000705 G 7240 23031260 COMBUSTION CHAMB ALLSN 6898734 BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL PATCH AREA CRACKED W O OTHER O OTHER IN INSP/MAINT 1 CA 13900 CAT31672 CAE820619 (CAN) A HIGHER THAN NORMAL T.O.T. WAS EXPERIENCED UNDER NORMAL OPERATING TO-QUE SETTINGS. AIRCRAFT ENGINE WAS INSPECTED UPON LANDING TO DETECT A POSSIBLE MALFUNCTION. A CRACK WAS DISCOVERED IN THE COMBUSTION CASE ASSEMBLY IN THE REINFORCE D PATCH AREA OF THE LEFT TUBE INSIDE CURVE AREA. A PREVIOUS AND RECURRING PROBLEM; HENCE, THE REINFORCING PATCH. 1 G 7 1 3U 3 U H2SW E4CE 2001032600034 20010326 00034 2001 3 26 CA000720014 4 20000620 G 2562 BP1020 BATTERY DORNEMARGLN DMELT1411 CNDAIR CL600 CL6002A12 1900304 EA GE CF34 CF343A1 30015 NE ELT WRONG PART W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 2062A (CAN) UPON ELT RECERTIFICATION, A NON TC APPROVED BATTERY WAS FOUND IN THE UNIT.ONLY THE DM U158-1 IS APPROVED BY TC (RE F AWN BO14, EDITION 4) FOR USE IN THIS ELT. CORRECT BATTERY WAS INSTALLED AND ELT RECERTIFIED.SUP 2 L 7 2 4F 4 F RT A21EA E15NE 2000073100208 20000731 00208 SO 2000 7 31 CA000720015 1 20000628 G 3250 AN3H7A BOLT 4531400 PIPER PA31T PA31T2 7103127 SO PWA PT6 PT6A135 52043 NE TOP OF CYL SHEARED W O OTHER O OTHER LD LANDING 1 CA 11272 PCE92427 (CAN) UPON LANDING THE AIRCRAFT, THE PILOTS NOTICED A PULLING TO THE LEFT. AFTER A BRIEF INSPECTION, THE THREE UPPER A N3 BOLTS, WHICH HOLD THE STEERING ARM AND BRACKET TO THE NOSE GEAR CYLINDER, WERE FOUND TO BE SHEARED. 1 L 7 2 3T 4 T RT A8EA E4EA 2000073100209 20000731 00209 SO 2000 7 31 CA000720017 2 20000707 G 8530 646657A2 CYLINDER CESSNA 207 T207A 2073614 CE CONT O520 TSIO520M 17040 SO MCAULY D3A34 D3A34C401 GL EX. VALVE NR 5 CRACKED W O OTHER O OTHER IN INSP/MAINT 1 CA 291516R (CAN) WHEN PERFORMING A CYLINDER DIFFERENTIAL COMPRESSION CHECK, FOUND CYLINDER NR 5 HAD A 60/80 COMPRESSION, AND AIR WA S LEAKING OUTSIDE CYLINDER. AFTER FURTHER INSPECTION, FOUND CRACK COULD BE SEEN JUST INBOARD OF THE EXHAUST PIPE FLANGE . CYLINDER WAS REMOVED FROM SERVICE. NEW OVERHAULED CYLINDER WAS INSTALLED. 1 H 7 1 3O 3 O A16CE E8CE 5 C P47GL 2001031300019 20010313 00019 EU 2001 3 13 CA000721009 1 20000627 G 2120 AIR FILTER AIRBUS 320 A320211 3930320 EU CFMINT CFM56 CFM565A1 NE AIR DISTRIBUTION CONTAMINATED W O OTHER B SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 CA 731248 (CAN) ON GROUND AFTER ENGINE START, SMELL OF EXHAUST (POSSIBLE FUEL VAPORS) IN REAR CABIN, DISSIPATED BEFORE DEPARTURE. ON FINAL APPROACH A STRONG KEROSENE SMELL EMANATED THROUGHOUT FORWARD GALLEY AND J CLASS CABIN AND SMELL DIDNT DISSPATE UNTIL AFTER ENGINES SHUT DOWN.ENGINE GROUND RUN CARRIED OUT WITH INDIVIDUAL ENGINE AND APU BLEEDS ISOLATED. NO FAULT FOU ND. ENGINE FUEL NOZZLES INSPECTED AS PER JOB CARD, NO FAULT FOUND.BOTH CABIN AIR RECALCULATION FILTER REPLACED AND SYSTE M CHECKED SERVICEABLE. 2 L 7 2 4F 4 F RT A28NM E29NE 2001031300021 20010313 00021 EA 2001 3 13 CA000724002 1 20000716 G 2910 LINE CNDAIR CL600 CL6002B19 EA HYDRAULIC SYSTEM LEAKING W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) LOST OF HYDRAULIC PRESSURE SYSTEM NR 1 AND QUANTITY IN CRUISE AT FLIGHT LEVEL 310. NO QUANTITY OR PRESSURE FOR 36 MINUTES BEFORE ENGINE SHUTDOWN AFTER LANDING. THE EDP AND THE LEAKING HYDRAULIC PRESSURE LINE REPLACED. 2 L 7 2 4F RT A21EA 2001031300022 20010313 00022 EA 2001 3 13 CA000724003 1 20000714 G 7540 FIRE LOOP CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE LT ENGINE FAILED W E ENGINE SHUTDOWN N FALSE WARNING CR CRUISE 1 CA (CAN) IN CRUISE ON FLIGHT 5367 FROM CINCINNATI TO MINNEAPOLIS / ST PAUL LT 14TH STAGE DUCT WARN ILLUMINATED. CREW FOLLOW ED THEIR QRH AND SHUT DOWN THE ENGINE. AFTER DECLARING AN EMERGENCY AND DIVERTING TO MADISON THEY COMPLETED AN UNEVENTFU L LANDING. 2 L 7 2 4F 4 F RT A21EA E15NE 2001031300023 20010313 00023 EA 2001 3 13 CA000724004 1 20000711 G 2910 HYDRAULIC LINE CNDAIR CL600 CL6002B19 EA GE CF34 CF341A NE HYDRAULIC SYS LEAKING W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA 807038 (CAN) ON FLIGHT 5692 FROM CINCINNATI (CVG) TO MYRTLE BEACH SC (MYR), HYDRAULIC NR 2 PRESSURE CAUTION MESSAGE IN FLIGHT. CREW DECLARED AN EMERGENCY AND MADE AN UNEVENTFUL LANDING BACK AT CINCINNATI. MAINTENANCE ACTION: MAINTENANCE FOUND AN H YDRAULIC LEAK IN THE AFT FUSE, FOUND TO BE NR 2 ENGINE CASE DRAIN LINE LEAKING, MAINTENANCE REPLACED HYDRAULIC LINE, AIR CRAFT WAS BACK TO SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001031300024 20010313 00024 EA 2001 3 13 CA000724005 1 20000713 G 2916 RESERVOIR CNDAIR CL600 CL6002B19 EA GE CF34 CF341A NE HYD SYSTEM FAILED W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA 807038 (CAN) ON A FLIGHT FROM CVG TO MYR, THE HYDRAULIC NR 2 LOW PRESSURE CAUTION MESSAGE OCCURRED IN FLIGHT. SYSTEM PRESSURE W AS LESS THAN 15 PERCENT. CREW DECLARED AN EMERGENCY AND MADE AN UNEVENTFUL LANDING BACK AT CINCINNATI. THE NR 2 RESERVOI R WAS IDENTIFIED AS BEING THE CAUSE OF THE PROBLEM. 2 L 7 2 4F 4 F RT A21EA E15NE 2001031300025 20010313 00025 EA 2001 3 13 CA000724006 1 20000707 G 5330 SKIN CNDAIR CL600 CL6002B19 EA FUSELAGE CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING C CHECK MAINTENANCE, MAINTENANCE REQUIRED ACCESS TO RIVETS FOUND UNDER THE TRAILING EDGE PYLON ASSEMBLY. A FTER REMOVAL OF THE PYLON TRAILING EDGE ASSEMBLY, LT AND RT, MAINTENANCE NOTED ABRASION DAMAGE TO THE FUSELAGE (CHAFING ). THE DAMAGE WAS LOCATED IN AN UNPRESSURIZED AREA AND IN SOME LOCATION WAS AS MUCH AS .050 DEEP. MAINTENANCE ACTION: RE PAIR ENGINEERING ORDER PROVIDED TO CUSTOMER. 2 L 7 2 4F RT A21EA 2001031300026 20010313 00026 EA 2001 3 13 CA000724007 1 20000709 G 2750 BPSU CNDAIR CL600 CL6002B19 EA RIGHT FAILED W B EMER. DESCENT F FLT CONT AFFECTED CR CRUISE 1 CA (CAN) FLAP FAIL CAUTION MESSAGE ILLUMINATED IN CRUISE AT 25,000 FEET (FLAPS STAYED AT 0 DEGREE). CREW DECLARED AN EMERGE NCY AND MADE AN UNEVENTFUL LANDING. MAINTENANCE REPLACED THE RIGHT BPSU. 2 L 7 2 4F RT A21EA 2001031300027 20010313 00027 NE 2001 3 13 CA000724008 2 20000711 G 7250 TURBINE CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE NR 2 ENGINE FAILED W A UNSCHED LANDING X T J ENGINE FLAMEOUT ENGINE CASE PENETRATION WARNING INDICATION CL CLIMB 1 CA 807084 (CAN) ON CLIMB OUT NR 2 ENGINE N2 EXCEEDED LIMITS, THEN SHUT DOWN. CREW DECLARED AN EMERGENCY AND MADE AN UNEVENTFUL LAN DING. AFTER INVESTIGATION MAINTENANCE REPORT LPT (LOW PRESSURE TURBINE SECTION) CASE PENETRATION (PRIMARILY AT THE 7-8 O CLOCK POSITION). THE ENGINE HAS BEEN CHANGE OUT AND THE AIRCRAFT IS BACK IN SERVICE.ENGINE HISTORY: APPROXIMATELY 14,300 CYCLES ON IT - AND HAD PREVIOUSLY BEEN OFF AT 6000 CYCLES FOR AN HSI.FSR QUERIED ON FOREIGN SDR NO DETAILS AVAILABLE. 2 000,08,09 2 L 7 2 4F 4 F RT A21EA E15NE 2000081700089 20000817 00089 CE 2000 8 17 CA000724010 1 20000628 G 3297 WIRE CESSNA 664164068R CESSNA 560 560XL 2076702 CE LUG END BROKEN W O OTHER O OTHER DE DESCENT 1 CA 103 040 (CAN) ON JUNE 28, 2000, THE AIRCRAFT WAS ON TRAINING PURPOSE WHEN DURING NORMAL PROCEDURE OF DESCENT AND AFTER THE GEAR DOWN WAS SELECTED, THE CREW NOTICE THAT NO INDICATION FOR THE RIGHT GEAR DOWN AND LOCKED BUT LIGHT TESTED OK. THE CREW D ECLARED AN EMERGENCY LANDING AT ST-HUBERT AIRPORT. THE AIRCRAFT MADE AN UNEVENTFUL LANDING.AFTER INSPECTION OF THE LAND ING GEAR SYSTEM, TECHNICIANS FOUND A GROUND WIRE (GR008) BROKEN AT LUG. THE LUG WAS REPLACED, THE SYSTEM CHECKED SERVICE ABLE AND THE AIRCRAFT RETURNED TO SERVICE. 2 L 7 2 4F RT A22CE 2000081700090 20000817 00090 EA 2000 8 17 CA000724011 1 20000707 G 2701 215T9027622 TORQUE TUBE CNDAIR CNDAIR CL215 CL2156B11415 EA PWA PW120 PW123 NE OTBD SHAFT LOOSE W O OTHER O OTHER IN INSP/MAINT 1 CA 588 2023 (CAN) WHEN OPPOSING FORCE BETWEEN LT AND RT ELEVATOR CONTROL COLUMN, MINOR LOOSENESS CAN BE FELT ON LT COLUMN PRODUCED B Y OUTBOARD FASTENERS LOOSENESS ON OUTBOARD LAYSHAFT. S EE K/M/ PSP492,27-31-00, P602 FIG CC OUTBOARD SIDE. NOTE: (ACTI ON) REPAIRED C/O I.A.W. BOMBARDIER R.E.O. 215-27-30-03. 2 H 7 2 4T 4 T RT A14EA E20NE 2001031300029 20010313 00029 NE 2001 3 13 CA000724012 2 20000705 G 7200 ENGINE CNDAIR CL600 CL6001A11 1900302 EA LYC ALF502 ALF502L2 41580 NE RIGHT FAILED W A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) DURING CRUISE AT 41,000 FT THE FLIGHT CREW NOTICED A SMALL SURGE IN POWER ON THE RT ENGINE FOLLOWED ABOUT 10 SECON DS LATER BY A DECREASE IN RPM AND INCREASE IN ITT. THE ENGINE AND AIRCRAFT IMMEDIATELY BEGAN VIBRATING, WITH THE RT ENGI NE VIBE METER INDICATING MAXIMUM. THE CREW SHUTDOWN THE ENGINE BUT A HIGH LEVEL OF VIBRATION CONTINUED AS THE ENGINE WIN DMILLED. THE AIRCRAFT DIVERTED AND HAD AN UNEVENTFUL LANDING APPROXIMATELY ONE HOUR 30 MIN LATER. THE ENGINE WAS REPLACE D, THE ENGINE MOUNTS INSPECTED AND THE AIRCRAFT RETURNED TO SERVICE.DETAILS REGARDNG THE TEARDOWN AND FAILURE INVESTIGAT ION OF THE ENGINE WILL FOLLOW.2000-11-08TC: NO INFORMATION RECEIVED. 2 L 7 2 4F 4 F RT A21EA E6NE 2001031300030 20010313 00030 EA 2001 3 13 CA000724013 2 20000708 G 7250 TURBINE CNDAIR CL600 CL6001A11 1900302 EA LYC ALF502 ALF502* 41580 EA RT ENGINE SEIZED W O OTHER Y ENGINE STOPPAGE LD LANDING 1 CA 3066S (CAN) AFTER LANDING, DURING ROLLOUT, THE CREW DEPLOYED THE THRUST REVERSER AND THE RT ENGINE SHUTDOWN. THE AIRCRAFT CONT INUED TO THE HANGAR AND AN INITIAL EVALUATION OF THE ENGINE REVEALED THAT THE TURBINE WHEEL HAD SEIZED.FURTHER DETAILS O F THE ENGINE INSPECTION AND REPAIR WILL FOLLOW.2000,10,04, - THE NUMBER 2 ENGINE GAS PRODUCER AND COMBUSTOR TURBINE MODU LE (S/N 81H005) WAS REMOVED AND REPLACED ON WING.SUBSEQUENT OVERHAUL REVEALED PLASMA COATING MISSING FROM THE COMPRESSOR , EVIDENCE OF AN IMPELLER RUB AND GROUND UP METAL ON THE DIFFUSER VANES. BLADE MATERIAL TRANSFER RESULTED IN DAMAGE AND SEIZURE OF THE TURBINE ASSEMBLY 2 L 7 2 4F 4 F RT A21EA E6NE 2001031300031 20010313 00031 CE 2001 3 13 CA000724014 1 20000702 G 3234 MS24171D1 RELAY BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE FAILED W A UNSCHED LANDING O OTHER CL CLIMB 1 CA GGMPS0027 (CAN) AFTER TAKEOFF THE PILOT SELECTED THE GEAR UP BUT THEY DIDN'T MOVE. THEY DIVERTED THE FLIGHT TO YQB. AFTER INVESTIG ATION WE FOUND RELAY LANDING GEAR MOTOR P/N MS24171D1 IN LT NACELLE COMPLETELY BURNED. 2 L 7 2 4T 4 T RT A24CE E26NE 2001031300032 20010313 00032 EA 2001 3 13 CA000724015 1 20000706 G 2730 215T9027622 SHAFT CNDAIR CL215 CL2151A10 EA PWA PW120 PW123 NE TORQUE TUBE LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA 5731 (CAN) WHEN OPPOSING FORCE ON LT AND RT CONTROL COLUMN. MINOR LOOSENESS CAN BE FEEL ON LT CONTROL COLUMN PRODUCE BY OUTBO ARD FASTENERS LOOSENESS ON OUTBOARD LAYSHAFT. SEE M.M.492, 27-31-00 P602 FIG. CC OUTBOARD SIDE.NOTE: (ACTION) REPAIRS/OU T I.A.W. BOMBARDIER REO 215-27-30-03. 2 H 7 2 4R 4 T A14EA E20NE 2001031300033 20010313 00033 NE 2001 3 13 CA000724016 2 20000709 G 8550 AN929A4 OIL CAP CNDAIR CL215 CL2151A10 EA PWA R2800 CA3 52026 NE PRE OILING SYS LOOSE W E A ENGINE SHUTDOWN UNSCHED LANDING Y ENGINE STOPPAGE NR NOT REPORTED 1 CA 32875 (CAN) ENGINE HAD TO BE FEATHERED IN FLIGHT DUE TO LOW OIL PRESSURE AND OIL QUANTITY DRIPPING. AFTER LANDING, A TECHNICI AN FOUND THAT THE PRE-OILING PLUG LOOSEN.HE REINSTALLED THE PLUG, FILL THE OIL TANK, PERFORMED AN ENGINE RUN AND RETURN THE AIRCRAFT TO SERVICE. 2 H 7 2 4R 4 R A14EA E231 2000081700091 20000817 00091 SO 2000 8 17 CA000724018 1 20000706 G 3710 441CC7 PUMP AIRBORNE PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA LT ENGINE JAMMED W O OTHER O OTHER IN INSP/MAINT 1 CA 362 85687 L586361A (CAN) PUMP S/N 856871. DETECTED SQUEAKING WHEN TURNING PROPELLER DURING TEARDOWN FOR ENGINE CHANGE. PUMP REMOVED. HA RDLY ABLE TO TURN IT BY HAND. INSTALLED 14 FEB. 2000 AT 12269.2 = 6 MS AND 361.6 HRS. REMOVED 06 JUL.2000 AT 12630 = 6 MS & 361.6 HRS. WHEN INSTALLED, MAN. INSTRUCTIONS FOLLOWED METICULOUSLY CLEAN HOSES, COOLING HOSE AND BAFFLE, R.V. FI LTERS. 133-5-1 FILTERS REPLACED EVERY 100 HOURS. NOTE: POOR DESIGN: PUMP BREATHERS FROM AIR INTAKE UNDER NACELLE NEA R COWL FLAPS AND EXHAUSTS. 1 L 7 2 3O 3 O A20SO E14EA 2000081700092 20000817 00092 SO 2000 8 17 CA000724019 1 20000706 G 3242 07900300 SCREW CLEVELAND 309C PIPER PA18 PA18150 7101828 SO BLEEED VLV/RT BK MISSING W E O ENGINE SHUTDOWN OTHER K R FLUID LOSS PARTIAL RPM/PWR LOSS LD LANDING 1 CA 5738 (CAN) THIS REPORT FOLLOWS LANDING INCIDENT. NO RIGHT BRAKE. AIRCRAFT LANDED AND PILOT CNTLLED A/C ONTO ECHO TAXIWAY . SHUT DOWN AND PUSHED A/C OFF TAXIWAY BY HAND. ON SITE, PRELIMINARY INSP AND TOWED A/C CLEAR OF ALL TRAFFIC AREAS - U NDER AIRPORT MGRS ESCORT. BRAKE BLEEDER ASSY (SEAT PN 08100100, SCREW PN 07900300, CAP PN 18300100) MISSING FROM CYLIND ER P/N 061-03901. IT APPEARED THAT IT ORIGINALLY NOT SCREWED IN VERY DEEP, 2 OR 3 THREADS. 1ST THREADS BURNED FIELD R EPLACED, BLED AND SERVICED. ENTRY IN LOG TO BE REVIEWED AT HOME BASE (REMOVED AND RE-INSP). PILOT AND AMO ADVISED. TA XI-TESTED AND LEAK CHECKED. NOTE: A/C AMPHIBIOUS - FLOATS - LAST TAKEOFF FROM GRAVEL. 1 H 7 1 3O 1A2 2000081700093 20000817 00093 SO 2000 8 17 CA000724020 1 20000627 G 2710 677550100 BELLCRANK PIPER PA28 PA28R200 7102811 SO LYC O360 IO360C1C 41514 EA RIGHT WING CRACKED W O OTHER O OTHER IN INSP/MAINT 1 CA 3023 L772851A (CAN) THE RIGHT AILERON CONTROL BELLCRANK LOWER ANGLE WAS FOUND CRACKED DURING INSPECTION. 1 L 7 1 3O 3 O 2A13 1E10 2000081700094 20000817 00094 SO 2000 8 17 CA000724021 1 20000704 G 3244 50644 TIRE CLEVELAND 4040 PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA NLG BLOWN W O OTHER R PARTIAL RPM/PWR LOSS LD LANDING 1 CA 622 182 L159368A (CAN) THIS REPORT FOLLOWS LANDING INCIDENT, TOWED OFF RUNWAY. RUNWAY INSP, NO DEBRIS. TEAR DOWN OF WHEEL ASSY SHOWED TIRE TREAD OBLIQUE - SKID - FLAT SPOT. POSSIBLY DUE T O CRAB LDG OR TO SKIDDING AFTER BLOWING AT TOUCH DOWN. BALANCE P ATCH 1 OZ INSIDE TIRE FOUND DISINTEGRATED. INSIDE CORD BROKEN, POSSIBLY DUE TO TOWING ACFT OFF RUNWAY. TUBE FOUND PUNC TURED AND CHAFED, BURNED, DISCARDED. BEARINGS AND CUP BURNERS SHOWING LIGHT SIGNS OF HEATING. NO SIGNS OF POSSIBLE FO REIGN OBJECT IN TIRE, NAIL, PIN, STONE ETC. WHEEL AND LANDING GEAR INSP PER ASM. NO DEFECT. REPAIRED WHEEL WITH NEW B EARING RUNNERS, WITH NEW TUBE AND NEW MICHELLIN-AVIATOR TIRE. 1 L 7 2 3O 3 O A20SO E14EA 2000081700095 20000817 00095 CE 2000 8 17 CA000724022 1 20000621 G 3297 WIRE CESSNA 402 402B 207590P CE CONT O520 TSIO520E 17040 SO BROKEN W O OTHER O OTHER DE DESCENT 1 CA 275423R (CAN) UPON ACTIVATION OF THE LANDING GEAR, THE LEFT GREEN DOWN AND LOCKED LIGHT DID NOT ILLUMINATE. AFTER VISUAL CONFI RMATION, THE AIRCRAFT LANDED SAFELY. BROKEN WIRE CAUSED THE PROBLEM. 1 L 7 2 3O 3 O A7CE E8CE 2000081700096 20000817 00096 GL 2000 8 17 CA000724023 3 20000704 G 6114 HUB PIPER PA30 PA30 7103002 SO LYC O320 IO320B1A 41508 EA HARTZL HCE2Y HCE2YL2 GL HUB SHELF DAMAGED W O OTHER O OTHER IN INSP/MAINT 1 CA 1166 L17755 4246 (CAN) DAMAGE BEYOND LIMIT TO HUB SHELF DUE TO A PREVIOUS PROPELLER STRIKE. 1 L 7 2 3O 3 O A1EA 1E12 5 C P9EA 2000081700097 20000817 00097 SO 2000 8 17 CA000724024 1 20000709 G 3243 16748000 MASTER CYLINDER PIPER PA23 PA23250 7102308 SO LYC O540 IO540C4B5 41532 EA RT RUD PEDAL LEAKING W O OTHER K FLUID LOSS IN INSP/MAINT 1 CA 1046 L585248 (CAN) WHILE WORKING ON ANOTHER NEARBY AIRCRAFT IN HANGAR, MECHANIC NOTICED PUDDLE OF HYDRAULIC FLUID UNDER THE AZTEC. MONITORED FOR ONE HOUR, INCREASED IN SIZE OF PUDDLE COMFIRMED LEAK TO BE MAJOR. OIL RAN FROM NOSE NACELLE AREA TO MID-C ENTER SECTION BEFORE DRIPPING DOWN. CHECKED HYDRAULIC SYSTEM. BRAKE RESERVOIR FOUND EMPTY. RIGHT BRAKE MASTER CYLIND ER LEAKING. TOP SEALS. TSO: 1045.7 HR. INSTALLED 17 OCT 91. REPLACED UNIT - BLED AND SERVICED. 1 L 7 2 3O 3 O 1A10 1E4 2000081700098 20000817 00098 EA 2000 8 17 CA000724025 2 20000628 G 7322 25245009 SERVO PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA RT ENGINE FAILED W O OTHER Y Z ENGINE STOPPAGE SIGNIFICANT FAILURE REPORT IN INSP/MAINT 1 CA 379 70698 L159368A (CAN) INSTALLED 20 JAN 2000 BY OVERHAULED ON O/H ENGINE. AT TSO: 119.7 HRS. IDLE MIXTURE RICHENED 3 NOTCHES. AT T SO: 153.3 HRS. IDLE MIXTURE RICHENED 1 NOTCH FROM ONE FLIGHT TO ANOTHER, PILOT REPORTED DIFFICULTIES IN SETTING MIXTU RE, FUEL FLOW AND EGT. SEVERAL VERIFICATIONS OF SYSTEM CARRIED OUT DURING THAT PERIOD, TIMING, INTAKE LEAKS, INJECTOR N OZZLE, SPARK PLUGS ALWAYS TO SHOW NORMAL OPERATION AFTERWARDS. ALTHOUGH INDICATING PARAMETERS GOOD, SOME GAUGES REPLACE D, EXHAUST STACKS INDICATING LEAN EXHAUST. THIS TIME, PILOT ENCOUNTERED HARD TO START AND NO CUTTING OUT WHEN MIXTURE PULLED BACK. UNSTABLE UNIT - REPLACED. 1 L 7 2 3O 3 O A20SO E14EA 2000081700099 20000817 00099 SO 2000 8 17 CA000726002 1 20000623 G 2730 4030700 ELEVATOR PIPER PIPER PA31T PA31T 7103124 SO PWA PT6 PT6A28 EA LOWER BEARING WORN W K NONE F FLT CONT AFFECTED IN INSP/MAINT 1 CA 31T7920008 PCE51839 (CAN) DURING INSPECTION BELLCRANK FOUND TO BE WORN IN BEARING LOCATION WHERE ELEVATOR PUSH-PULL ROD ATTACHES, TO THE POI NT WHERE THE BEARING WAS LOOSE IN BELLCRANK. PROBLEM SEEMED TO BE CAUSED BY BEARING BECOMING SEIZED. 1 L 7 2 3T 4 T A8EA E4EA 2000080800171 20000808 00171 NE 2000 8 8 CA000726003 2 20000628 G 7200 WHEEL TMECA 70BM035240 SNIAS 350 AS350B1 8680811 EU TMECA ARRIEL ARRIEL1D NE GAS GENERATOR COKED W K NONE O OTHER TX TAXI/GRND HDL 1 CA 2999 175 5258 7139 (CAN) THIRD OCCASION THAT THE COMPRESSOR SECTION HAD BECOME DIFFICULT TO TURN DUE TO COKING AROUND LABYRINTH SEAL AT INJ ECTION WHEEL. ONLY SOLUTION IS TO REMOVE ENGINE M.O.2 SECTION SENT TO OVERHAUL FACILITY FOR REPAIR. TURBOMECA IS NOW LO OKING INTO THIS PROBLEM DUE TO OTHER OCCURRENCES OF THIS PROBLEM. 1 G 7 1 3U 3 U H9EU E19EU 2001031300035 20010313 00035 CE 2001 3 13 CA000726004 1 20000619 G 2752 503801537 DRIVE SHAFT BEECH 1295210501 BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE FLAP ACTUATOR WORN W K NONE O OTHER IN INSP/MAINT 1 CA 6669 796B96 PCEPS0104 (CAN) INITY MAINT NOTIFIED THAT WHEN SELECTING FLAPS TO UP POS (ON GROUND) THAT FLAP IND. SHOWING 20 DEGS&THAT FLAPS WE RE NOT ABLE TO RETRACT ANY FURTHER. MAINT FOUND L/H INBOARD FLAP IN APPROX. 25DEGS DOWN POS,&THAT FLAP SPLIT SYS PREVENT ING FURTHER FLAP-MOTOR OP. ALL FLAPS WERE MANU RETRACTED&CONFIRMED LOCKED IN UP POS. A/C DISPATCHED AS PER MEL PROCEDURE FOR FLAP-UP OPS.DURING T TROUBLE-SHOOTING IT FOUND THAT L/H INBOARD FLAP ACTUATOR ASSY FAILING, INTERNALLY. GEAR INTERN ALLY OF DRIVE ASSY, WHICH IS PART OF FLAP ACTUATOR ASSY FOUND WORN WITH SECTION OF GEAR BROKEN OFF.L/H INBOARD FLAP ACTU ATOR REPLACED BEFORE FURTHER FLT. 2 L 7 2 4T 4 T RT A24CE E26NE 2001011105199 20010111 05199 NM 2001 1 11 CA000731008 1 20000722 G 5753 CONTROL UNIT BOEING 767 767375 NM TE FLAPS FAILED W O OTHER O OTHER LD LANDING 1 CA (CAN) A/C 640, JULY 22/2000, FLT 51, YYZ, LOG SEQUENCE 0272985, ON LANDING YYZ, CAPTAIN DECLARED AN EMERGENCY, DUE TRAIL ING EDGE FLAP ASYMMETRY OCCURRED WITH FLAPS BEYOND 20 DEGREES. LANDED WITHOUT INCIDENT. SYSTEM RESET AS PER FAULT ISOLA TION MANUAL 27-51-00 FIG.114C, FOR TRAILING EDGE FLAP SHUTDOWN, NO FAULTS INDICATED. AFTER RESET FLAPS CYCLED SEVERAL TI MES WITH HYDRAULICS AND IN ALTERNATE MODE, UNABLE TO DUPLICATE SNAG. 2 L 7 2 4F RT A1NM 2000081700100 20000817 00100 NM 2000 8 17 CA000731015 1 20000717 G 5530 220015001 FITTING PIPER 220000999 PIPER PA60 PA60600 7106001 NM LYC O540 IO540K1J5 41532 EA FITTING CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 3981 14071 L1600248A (CAN) AN A INSPECTION WAS BEING ACCOMPLISHED ON THE AIRCRAFT. DURING THIS INSPECTION, A CRACK WAS FOUND ON THE AFT VERT ICAL STABILIZER ATTACH FITTING. THE CRACK WAS CONFIRMED USING EDDY CURRENT INSPECTION METHOD. AFTER THE FITTING WAS RE MOVED FROM THE STABILIZER A FURTHER EDDY CURRENT INSPECTION INDICATED A TOTAL OF 5 DIFFERENT CRACKS IN THE FITTING. T HE CRACKS ALL EXTEND GRAIN-WISE BETWEEN FASTENER HOLES ON BOTH FLANGES OF THE FITTING. THE FITTING WAS REPLACED WITH A NE W FITTING. CONAIR WILL BE CONDUCTING A FLEET CAMPAIGN TO INSPECT THE AFT VERTICAL STABILIZER ATTACH FITTING TO DETERMIN E THE EXTENT OF THE PROBLEM AND RECTIFY (I.E. REPLACE) DEFECTIVE FITTINGS. 1 M 7 2 3O 3 O RT A17WE 1E4 2001031400115 20010314 00115 EU 2001 3 14 CA000731016 1 20000719 G 3233 AIR111506 ACTUATOR BRAERO DH125 HS125700B 1500205 EU MLG CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 5059 (CAN) DURING A ROUTINE MAINTENANCE GEAR SWING, A VISUAL CHECK INDICATED FLUID LEAKAGE FROM THE ACTUATOR HEAD. INVESTIGAT ION SHOWED A 2.0 INCH LONG LONGITUDINAL CRACK RUNNING FROM THE BASE THROUGH A SET SCREW HOLE TOWARDS MAIN BUSHING PIVOT BORE IN THE 3.0 INCH LONG JACK CYLINDER HEAD. ASSEMBLY REPLACED WITH OVERHAULED PART. SUGGEST OPERATORS OF ALL A/C SERIE S DETAIL INSPECT ACTUATORS FOR LEAKAGE OR HIDDEN CRACKING UNDER LOOSE PAINT. 2 L 7 2 4F A3EU 2000081400173 20000814 00173 SW 2000 8 14 CA000731018 1 20000627 G 2912 206076022005 PUMP BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL HYD PUMP & RESRV CONTAMINATED W O OTHER O OTHER TX TAXI/GRND HDL 1 CA 12147 4995 CC211858 CAE820296 (CAN) AFTER A DAYS FLYING, IT WAS DISCOVERED THAT THE HYDRAULIC FILTER BYPASS BUTTON HAD POPPED. THE BUTTON WAS DEPRESS ED, AIRCRAFT RUN UP, BUTTON POPPED AGAIN. CONTAMINATES WERE FOUND IN THE FILTER. ALL HYDRAULIC LINES, SERVOS WERE FLUSH ED, A NEW FILTER INSTALLED. THE AIRCRAFT WAS RUN AGAIN FOR 10 MINUTES, FEEDBACK WAS DISCOVERED IN THE CONTROLS. THE FILT ER HAD MORE CONTAMINATES, CONTAMINATES WERE ALSO FOUND IN THE RESERVOIR. THE PUMP AND RESERVOIR ASSEMBLY WERE REPLACED, AS WELL AS A SERVO. CONTAMINATES AND FEEDBACK NO LONGER EXIST. 1 G 7 1 3U 3 U H2SW E4CE 2000101300001 20001013 00001 2000 10 13 CA000731020 4 20000512 G 8300 BP252 GEARBOX KLIMOV TB3117BMA KAMOV KA32 KA32A1 SW ASSY G/B CONTAMINATED W O OTHER O OTHER CR CRUISE 1 CA 971 708789210008 708789210008 (CAN) GEARBOX CHIP LIGHT, METAL CHIPS ON DETECTOR. (X) 1 G 7 2 4U NC 2001032700127 20010327 00127 SW 2001 3 27 CA000731021 1 20000512 G 6220 D26212090 BEARING D262000DB KAMOV KA32 KA32A1 SW MAIN ROTOR HUB FLAKING W A UNSCHED LANDING E VIBRATION/BUFFET CR CRUISE 1 CA 887 920018 (CAN) VIRBATION, METAL FLAKES IN OIL. REDESIGN OF FLAPPING BEARING HUB IN PROGRESS. 1 G 7 2 4U NC 2001031400116 20010314 00116 CE 2001 3 14 CA000731022 1 20000630 G 3610 1143800025 COOLER BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE RT ENG NACELLE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 6199 PCE0S0115 (CAN) AIRCRAFT ARRIVED WITH SMALL OIL LEAK ON RT LOWER ENGINE NACELLE. PRECOOLER HAD CRACKED ALLOWING HOT P3 AIR TO BLOW ONTO OIL COOLER. OIL COOLER FINS MELTED ALLOWING OIL LEAK. OIL COOLER P/N 114-389000-5.THIS IS SECOND INSTANCE FOR THIS DEFECT FOR OUR FLEET IN LAST MONTH.NONE PREVIOUSLY NOTED. 2 L 7 2 4T 4 T RT A24CE E26NE 2001031400117 20010314 00117 CE 2001 3 14 CA000731023 1 20000616 G 3610 1143800025 COOLER BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE RT ENG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 5841 PCEPSO141 (CAN) PILOTS REPORT RT ENGINE RUNNING HOTTER THAN LT. RT PRECOOLER HAD CRACK IN IT, P3 AIR STRIKING OIL COOLER CAUSED LE AK. SMALL AMOUNT OF OIL COMING FROM OIL COOLER, P/N 114-3890005. THIS IS ONE OF TWO INSTANCES OF PRECOOLER BURNING INTO OIL COOLER THIS MONTH. NO PREVIOUS INSTANCES NOTED. 2 L 7 2 4T 4 T RT A24CE E26NE 2001032700128 20010327 00128 SW 2001 3 27 CA000731025 1 20000721 G 3320 4501221 PIVOT BELL 212 212 1181420 SW PWA PT6T PT6T3B 52045 NE CABIN LIGHTS WRONG PART W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) PARTS NOT TO MANUFACTURERS SPECIFICATIONS I.E. BOGUS.ADDITION TO MULTIPLE REPORT PREVIOUSLY RE THE SAME PROBLEM. M ELT DOWN. 1 G 7 1 4U 4 U H4SW E22EA 2000081700101 20000817 00101 CE 2000 8 17 CA000801003 1 20000717 G 5711 5147L SPAR ARONCA 11AC BBAVIA 11 11AC 0191102 CE CONT A65 A658 17003 SO REAR/OTBD END CRACKED W O OTHER O P OTHER NO WARNING INDICATION IN INSP/MAINT 1 CA 1558 11AC257 4699168 (CAN) DURING INSPECTION OF WING FOLLOWING WIND DAMAGE, CRACK FOUND IN UPPER EDGE OF LEFT REAR SPAR, OUTBOARD OF STRUT AT TACH PLY PLATES. SPAR REPLACED. 1 H 7 1 3O 3 O A761 E205 2000080800173 20000808 00173 GL 2000 8 8 CA000801006 2 20000718 G 7240 68709926 CASE ALLSN BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL COMBUSTION CASE CRACKED W O OTHER O OTHER IN INSP/MAINT 1 CA CAE822700 (CAN) DURING A 100 HOUR INSPECTION AND TURBINE CHANGE THE AME NOTICED A CRACK IN THE ARMPIT AREA OF THE OUTER COMBUSTION CASE. INSPECTION C/W PER ALLISON 250-C20 SERIES O&M 10W2, 72-40-00 PARA 2B. 1 G 7 1 3U 3 U H2SW E4CE 2001032700132 20010327 00132 SW 2001 3 27 CA000801009 1 20000719 G 6420 212010782101 BEARING 212010701055 BELL 205 205A1 1181414 SW LYC T53 T5313B 41549 NE T/R HUB FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 294 AFS1486 (CAN) T/R BECAME UNBALANCED. INSPECTED HUB AND FOUND BEARING TEFLON LINER CAME OFF FROM OUTER RACE. 1 G 7 1 4U 4 U H1SW E17EA 2000080800174 20000808 00174 WP 2000 8 8 CA000801012 1 20000722 G 6200 252466715H GOVERNOR BENDIX 252466715 HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL ENGINE MALFUNCTIONED W O OTHER J WARNING INDICATION HO HOVERING 1 CA 567 31160 CAE822593 (CAN) WHILE MAKING POWER CHANGES IN HOVER, THE ROTOR RPM DROPS AND OVERSPEEDS. 152.0 HOURS SINCE REPAIR. 1 G 7 1 3U 3 U H3WE E4CE 2001032700134 20010327 00134 EU 2001 3 27 CA000801013 1 20000719 G 2422 PC250 INVERTER BOLKMS 117 BK117A4 5626017 EU LYC LTS101 LTS101650B1 41560 NE ELECTRICAL SYS FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AFTER CUSTOMER COMPLAINED OF OSCILLATION IN COMPASS CARD OF EHSI, DETERMINED THAT PROBLEM CAUSED BY VOLTAGE FLUX OF NR 1 AC BUS. TROUBLESHOOTING REVEALED THAT VOLTAGE FLUX ONLY PRESENT WHEN INVERTER OPERATED AT APPROXIMATELY 12 TO 20 PERCENT OF FULL LOAD. IT ALSO FOUND THAT BOTH INVERTERS ON A/C PRESENTED SAME PROBLEM. INVERTERS ARE MARATHON POWER TEC HNOLOGIES MODEL PC-250, SER-NO 4343&4346. BOTH INVERTS ARE AT MOD LEVEL C. WHEN INVERTS W/O MOD C WERE INST IN A/C PROBL EM NO LONGER PRESENT. 1 G 7 2 3U 3 U H13EU E5NE 2000081700102 20000817 00102 CE 2000 8 17 CA000801014 1 20000619 G 5510 07123021 BRACKET CESSNA 180 180H 2072618 CE CONT O470 O470R 17026 SO MCAULY 2A34C 2A34C203 GL LT STABILIZER CRACKED W O OTHER O OTHER IN INSP/MAINT 1 CA 6900 9011950H 760187 (CAN) THE BRACKET ON THE LEFT STABILIZER WAS CHANGED AS IT WAS FOUND TO BE CRACKED. P/N 0712302-1 WAS REPLACED WITH NEW PART USING EXISTING RIVET SIZE AND PATTERN. 1 H 7 1 3O 3 O 5A6 E273 5 C P3EA 2000081700103 20000817 00103 CE 2000 8 17 CA000801015 1 20000619 G 2740 07321014 HINGE BRACKET CESSNA 180 180H 2072618 CE CONT O470 O470R 17026 SO MCAULY 2A34C 2A34C203 GL HORIZONTAL STAB FAILED W O OTHER O OTHER IN INSP/MAINT 1 CA 6900 9011950H 760187 (CAN) THE REINFORCEMENT STABILIZER HINGE (BOX) ON THE HORIZONTAL STABILIZER WAS CHANGED. P/N 0732101-4 WAS REPLACED WIT H NEW PART USING EXISTING RIVET SIZE AND PATTERN. 1 H 7 1 3O 3 O 5A6 E273 5 C P3EA 2000112800123 20001128 00123 SW 2000 11 28 CA000801016 1 20000801 G 2910 MS287786 O-RING PU304426 SWRNGN SA226 SA226TC 8780404 SW GARRTT TPE331 TPE33110UA 01514 WP O-RING PINCHED W A UNSCHED LANDING K FLUID LOSS CR CRUISE 1 CA R512341 P52065C (CAN) DURING CRUISE FLIGHT, A TOTAL HYDRAULIC FAILURE WAS ENCOUNTERED, AN EMERGENCY GEAR EXTENSION WAS PERFORMED AND THE AIRCRAFT LANDED WITHOUT INCIDENT. A SUBSEQUENT INSPECTION REVEALED THAT THE HYDRAULIC SYSTEM FLUID LEVEL WAS AT ZERO, CAUSED BY A LEAK AT THE OUTPUT FITTING PIN AN815-65 OF THE LT HYDRAULIC PUMP, FURTHER INSPECTION REVEALED THAT THE O-RIN G FOR THIS FITTING HAD BEEN PINCHED ON INSTALLATION OF THE HYDRAULIC PUMP THE PREVIOUS DAY. THE O-RING WAS REPLACED, THE HYDRAULIC SYSTEM SERVICED AND THE AIRCRAFT RETURNED TO SERVICE. 2 L 7 2 4T 4 T RT A8SW E4WE 2000112800125 20001128 00125 EU 2000 11 28 CA000801021 3 20000405 G 6111 BLADE MUHBR RHNFLU EXT300 EA300L 70218DG EU LYC O540 AEIO540L1B5 41532 NE MUHBR MTV MTV3BC EU PROPELLER BLADES LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA 744 L2594848A 97059 (CAN) LOOSE PROPELLER BLADES. 1 M 7 1 3O 3 O NC EA67U 1E4 5 C USSR 2000112800126 20001128 00126 EU 2000 11 28 CA000801022 1 20000531 G 5412 FIREWALL RHNFLU EXT300 EA300L 70218DG EU LYC O540 AEIO540L1B5 41532 NE FIREWALL LOOSE W O OTHER O OTHER DE DESCENT 1 CA 740 043 L2594848A (CAN) FIRE WALL NEEDS TO BE STIFFENED. 1 M 7 1 3O 3 O NC EA67U 1E4 2000112800127 20001128 00127 EU 2000 11 28 CA000801023 1 20000531 G 7110 COWLING LYC RHNFLU EXT300 EA300L 70218DG EU LYC O540 AEIO540L1B5 41532 NE HOLE ELONGATED W O OTHER O OTHER IN INSP/MAINT 1 CA 743 L2592348A L2592348A (CAN) SAME PROBLEM AS WITH C-GAKN. COWLING IS FALLING OFF DUE TO STRUCTURALLY INADEQUATE FIREWALL. 1 M 7 1 3O 3 O NC EA67U 1E4 2000083101005 20000831 01005 SO 2000 8 31 CA000801027 2 20000720 G 7314 476411 PUMP CONT CESSNA 340 340CESSNA 2076404 CE CONT O520 TSIO520NB 17040 SO MCAULY 3AF32C 3AF32C93 GL WIRE ENTER.PUMP SHORTED W O OTHER O OTHER CR CRUISE 1 CA 56 276649R 7911065 (CAN) THE ELECTRICAL WIRE WHERE IT ENTERS THE PUMP HAS SHORTED. THIS WIRE IS COVERED BY A BRAIDED WIRE. NO DISASSEMBLY HAS BEEN CARRIED OUT, HOWEVER, 24V WAS APPLIED TO PUMP TO CONFIRM SHORT. SUBMITTER STATED THIS IS THE SECOND PUMP REPL ACEMENT ON THIS AIRCRAFT IN THREE MONTHS. 1 L 7 2 3O 3 O 3A25 E8CE 5 C P22EA 2000083101006 20000831 01006 SO 2000 8 31 CA000801028 2 20000704 G 7314 476411 PUMP CESSNA 402 402B 207590P CE CONT O520 TSIO520EB 17040 SO MCAULY 3AF32C 3AF32C87 GL FUEL PUMP INOPERATIVE W O OTHER O OTHER IN INSP/MAINT 1 CA 19 815004R 767565 (CAN) BURNING ODOR WAS NOTICED FROM LT WING TIP AND LT LANDING LIGHT. CIRCUIT BREAKER TRIPPED. (TIP TRANSFER PUMP RECE IVES POWER FROM THIS BREAKER AND PUMP IS RUNNING WHENEVER MASTER SWITCH IS ON). PUMP WAS REMOVED AND APPROXIMATELY 1/2 OF THE PUMP BODY WAS FOUND DISCOLORED BY HEAT. (PROBLEM NOTICED ON WALKAROUND). SUBMITTER STATED THESE PUMPS FAIL ON A REGULAR BASIS (LT PUMP RECENTLY CHANGED WITH 90 HOURS SINCE NEW), HOWEVER, THIS IS THE FIRST ONE FOUND HEAT DISCOLORED . NORMAL FAILURE MODE IS FOR THE PUMP TO SLOWLY STOP RUNNING. NOTE: IN THIS INSTALLATION THE PUMP IS USED TO PUMP FUE L INTERNALLY IN THE TANK TO THE AREA OF THE FUEL OUTLET. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2000083101007 20000831 01007 EA 2000 8 31 CA000801029 2 20000721 G 7322 105062N CARBURETOR CESSNA 172 172L 2072432 CE LYC O320 O320E2D 41508 EA MCAULY 1C160 1C160CTM GL CARBURETOR FAILED W O OTHER R PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 CA BC01025 (CAN) DURING ENGINE START, ENGINE BACKFIRED.AFTER ENGINE START, ENGINE WOULD IDLE, BUT NOT DEVELOP POWER. ENGINE RUNS S MOOTH UNDER 1,000 RPM, OVER 1,000 RPM ENGINE RUNS ROUGH. WILL NOT EXCEED 1200 RPM. REMOVED CARBURETOR AND INSTALLED O VERHAULED UNIT. ENGINE RUNS PERFORMED. ALL PARAMETERS NORMAL. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2000083101008 20000831 01008 CE 2000 8 31 CA000801030 1 20000721 G 7920 AE3663162E0210 HOSE PWA CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE HOSE ASSY LOOSE W E ENGINE SHUTDOWN J K WARNING INDICATION FLUID LOSS CR CRUISE 1 CA PCE70491 (CAN) IN CRUISE AT APPROXIMATELY 31,000 FEET, PILOT NOTICED RT ENGINE OIL PRESSURE SLOWLY DROPPING, PER THE FLIGHT MANU AL, THEN REDUCED POWER AND AS THE PRESSURE APPROACHED 36 PSI THEY PERFORMED A PRECAUTIONARY SHUTDOWN AND LANDED IN CINCI NNATI, OHIO. MAINTENANCE FLEW DOWN AND PERFORMED AN INSPECTION, FOUND OIL PRESSURE LINE TO OIL PRESSURE TRANSDUCER LOOS E, APPROXIMATELY 2 TURNS TO TIGHTEN, LINE TIGHTENED ADDED 5 QUARTS OF AEROSHELL 500 AND PERFORMED FULL POWER RUNS. NO LEAKS OBSERVED. PRESSURE AND TEMPERATURES NORMAL. AIRCRAFT RETURNED TO SERVICE. 1 L 7 2 4F 4 F A22CE E1NE 2000083101009 20000831 01009 CE 2000 8 31 CA000801031 1 20000717 G 7120 05510171 MOUNT CONT CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA LOWER INNER CRACKED W O OTHER O OTHER IN INSP/MAINT 1 CA 1900 L2800027A (CAN) CRACK DISCOVERED. SCHEDULED MAINTENANCE, MOUNT REMOVED - SENT FOR NDT - REPAIR - NDT - PAINT RE-INSTALLED. 1 H 7 1 3O 3 O NT 3A12 E274 2001032700135 20010327 00135 CE 2001 3 27 CA000801033 1 20000717 G 2134 PRESSURE SWITCH LEAR 25 25B 5170511 CE CABIN PRESSURE FAILED W B EMER. DESCENT J WARNING INDICATION CR CRUISE 1 CA (CAN) A/C EXCEDED MAX ALT DUE TO UPDRAFT, A/C PRESSURIZATION SYSTEM ANORIDE SWITCH OPERATED TO SPEC UPON DESCNET SYSTEM OPERATED NORMALLY. I.A.W. L25 MM 21-30-07. 2 L 7 2 4J A10CE 2001031400127 20010314 00127 EA 2001 3 14 CA000802007 1 20000720 G 2742 CONTROL UNIT CNDAIR CL600 CL6002B19 EA STABILIZER FAILED W A UNSCHED LANDING F FLT CONT AFFECTED CL CLIMB 1 CA (CAN) DEPARTING MONTEREY, CA. CLIMBING OUT THRU FL200. EICAS ALERTED US OF AP PITCH TRIM MASTER CAUTION FOLLOWED BY AP PITCH TRIM NOSE DOWN MASTER CAUTION ANNUNCIATOR. WE FOLLOWED CFM PROCS&UPON DISCONNECTING AUTOPILOT HAD TO MAINTAIN ABOU T 2 IN OF NOSE DOWN PRESSURE ON YOKE TO MAINTAIN LEVEL FLT. WOULD NOT TRIM DOWN IT STUCK AT 4 UNITS. IT WOULD TRI M UP B UT NOT DOWN . WE CALLED MIX ON SELCAL THEN TALKED TO DISPATCH & DECIDED TO DIVERT TO FRESNO, CALF. APPROXIMATELY 20 MIN AWAY. WE DECLARED EMERGENCY & LANDED UNEVENTFULLY ON 29 RT, IN FRESNO . 2 L 7 2 4F RT A21EA 2001031400128 20010314 00128 2001 3 14 CA000802008 4 20000709 G 2397 31116062 WIRE LKHEED 1011 1011385115 5265015 WP RROYCE RB211 RB21122B02 54555 NE TRANSCEIVER BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHILE TROUBLE SHOOTING HF PROBLEM, FOUND COAX CABLE BEHIND TRANSCEIVER DAMAGE AT CONNECTOR (SHIELD BROKEN). CABLE REPLACED AND AIRCRAFT RETURNED TO SERVICE. SPECIAL INSPECTION WILL BE IN PLACE SHORTLY TO INSPECT THESE CABLE ON ALL L-1 011. 2 L 7 3 4F 4 F A23WE E12EU 2001031400130 20010314 00130 NM 2001 3 14 CA000802010 1 20000713 G 2820 COUPLING BOEING 757 75728A 1384976 NM RROYCE RB211 RB211535E437 54555 NE FUEL LINE CONTAMINATED W C ABORTED TAKEOFF R J PARTIAL RPM/PWR LOSS WARNING INDICATION TO TAKEOFF 1 CA 30739 (CAN) UNABLE TO ACHIEVE TAKEOFF POWER, WITHOUT RETURNING AT THE DATE, CREW DID A SUCCESSFUL POWER RUN AND A/C DEPARTED. SAME THING HAPPENED ON THE NEXT LEG. AFTER INVESTIGATION, MAINTENANCE FOUND COUPLING BETWEEN ENGINE AND FRAME FFG CABLE CONNECTOR CONTAMINATED WITH CARBON AND DIRT. CLAMP CLEANED AND RETORQUED. A/C RETURNED TO SERVICE. 2 L 7 2 4F 4 F RT A2NM E12EU 2001031400131 20010314 00131 NE 2001 3 14 CA000802011 2 20000722 G 7260 CARBON SEAL CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE LT ENGINE LEAKING W E ENGINE SHUTDOWN K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) PILOT REPORTED LT ENGINE OIL PRESSURE WARNING AND OIL PRESSURE FLUCTUATING BETWEEN 24 & 45 PSI. PILOT SHUT DOWN T HE ENGINE. MAINTENANCE FOUND THAT THE ENGINE REQUIRED 5 LITERS OF OIL. NO EXTERNAL LEAK FOUND. ENGINE RUN CARRIED OUT AN D LEAKAGE FOUND FROM IDG DRIVE PAD CARBON SEAL.CARBON SEAL REPLACED. 2 L 7 2 4F 4 F RT A21EA E15NE 2001031400132 20010314 00132 EA 2001 3 14 CA000802012 1 20000722 G 2612 47259701 FIRE DETECTOR CNDAIR CL600 CL6002B19 EA APU FAILED W E A ENGINE SHUTDOWN UNSCHED LANDING N FALSE WARNING CR CRUISE 1 CA (CAN) DURING CRUISE, FLT APU FIRE WARNING MESSAGE APPEARED ON ED NR 1. QRH FOLLOWED, MESSAGE REMAINED FOLLOWED BY A RT E XAUST PIPE OVERHEATED WARNING MESSAGE. THEN LT ENGINE FIRE WARNING MESSAGE APPEARED ON EDI. QRH FOLLOWED, LEFT ENGINE SH UTDOWN AND AIRCRAFT DIVERTED TO TYS AND A SINGLE ENGINE LANDING. AIRCRAFT WAS EVACUATED.THE FIRE DETECTOR P/N 472597-01 WAS REPLACED. 2 L 7 2 4F RT A21EA 2001031400133 20010314 00133 EA 2001 3 14 CA000802013 1 20000722 G 3222 STRUT CNDAIR CL600 CL6002B19 EA NLG FAILED W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 CA (CAN) AFTER TAKEOFF, WHEN GEAR HANDLE SELECTED UP, GEAR DISAGREE WARNING MESSAGE, WOW INPUT CAUTION MESSAGE, NOSE DOOR O PEN, STEERING INOP MESSAGE. CREW DECLARED AN EMERGENCY AND RETURNED TO CVG, COMPLETING AN UNEVENTFUL LANDING. THE NOSE S TRUT WAS SERVICED AND A/C RETURNED TO SERVICE. 2 L 7 2 4F RT A21EA 2001032700136 20010327 00136 EA 2001 3 27 CA000802014 1 20000722 G 2750 855D1009 BPSU CNDAIR CL600 CL6002B19 EA TE FLAPS FAILED W B EMER. DESCENT F FLT CONT AFFECTED AP APPROACH 1 CA (CAN) REMOVED AND REPLACED THE BPSU. INSTALLED BUT IT FAILED DURING THE TEST AND FIRED THE FBCU (CRITICAL FAILURE). 2 L 7 2 4F RT A21EA 2001032700137 20010327 00137 2001 3 27 CA000802015 4 20000715 G 2562 762357 STRAP NARCO 5480054 PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA ELT SUPPORT WORN W K NONE O OTHER IN INSP/MAINT 1 CA 12649 (CAN) AT ANNUAL INSPECTION REMOVAL OF ELT FOR CERTIFICATION. REMOVED DORSAL FIN ACCESS TO ELT PANEL & FOUND ELT NOT S ECURED PROPERLY IN ITS MANUFACTURERS SUPPORT BASE LATCH ON STRAP HAD COME UNDONE, WHAT APPEARS FROM VIBRATION. IT IS PL AUSIBLE TO THINK THAT IF THE AIRCRAFT IMPACTED FWD & WITH NAGATIVE UPWARDS FORCES, ELT MIGHT NOT COME ON. A PORTION OF T HE SPRING IN THE LATCH WAS WORN, THUS RELEASING WHEN TAPPED OR SLIGHTLY SHAKEN. 1 L 7 2 3O 3 O A20SO E14EA 2000083101010 20000831 01010 SO 2000 8 31 CA000802016 1 20000715 G 3050 597257 ANTENNA PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA RT TOP FUSELAGE MISSING W O OTHER O OTHER IN INSP/MAINT 1 CA 12649 L159368A (CAN) 1) COMING UP THE STEP LADDER TO REPLACE ELT FOR ANNUAL CERTIFICATION AND BATTERY DUE CAR 625 APP. C PARA 11A). ME CHANIC/AME NOTICED ELT ANTENNA MISSING. BROKEN FLUSH AT BASE NUT TO FUSELAGE SKIN AND DOUBLER. REPLACED WITH NEW KIT N R 455-9000 REV D. - 110-324 REV A ANTENNA WHIP W/INDUCTOR - 611-6013-10 REV A COAX CABLE NARCO. 1 L 7 2 3O 3 O A20SO E14EA 2000080700176 20000807 00176 WP 2000 8 7 CA000802017 1 20000718 G 5510 369D2363312 TIP CAP 369D23601 HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL RIGHT STABILIZER CRACKED W O OTHER O OTHER CR CRUISE 1 CA 2695 1571 CAE830428 (CAN) DURING FLIGHT A VIBRATION WAS FELT IN THE FLOOR AND WENT AWAY AS THE AIRCRAFT WAS RETURNING TO THE LANDING SITE. THE ENGINEER INSPECTED THE AIRCRAFT AND FOUND THE TIP PLATE OF THE R/H SIDE OF THE HORIZONTAL STABILIZER WAS MISSING. 1 G 7 1 3U 3 U H3WE E4CE 2000083101011 20000831 01011 NE 2000 8 31 CA000802018 2 20000710 G 8530 CYLINDER DHAV DHC2 DHC2MK1 2800102 EA PWA R985 R985AN14B 52008 NE AROUND HEAD BROKEN W O OTHER O OTHER CR CRUISE 1 CA 12 41557 41557 (CAN) THE CYLINDER HEAD SEPARATED FROM CYLINDER BARREL. 1 H 7 1 3R 3 R A806 5E1 2001032700138 20010327 00138 CE 2001 3 27 CA000802019 1 20000713 G 2121 50041 MOTOR 1013841001 BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA BLOWER FAILED W I G CABIN DEPRESSURIZATION O2 MASK DEPLOYED B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA 400 1709 (CAN) - AIRPLANE HAD SMOKE IN COCKPIT / CABIN. AFTER TROUBLESHOOTING FOUND THAT FORWARD BLOWER MOTOR MAKING GRINDING N OISE AND SMOKE. REPLACED FORWARD BLOWER ASSEMBLY GROUND CHECK SERVICE. 1 L 7 2 4T 4 T A24CE E4EA 2000083101012 20000831 01012 EA 2000 8 31 CA000802020 2 20000714 G 7414 ES10382681 CAPACITOR BENDIX 1068291618 PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA LT MAG-DUAL BURNED W O OTHER O OTHER TO TAKEOFF 1 CA 418 8010918 L159368A (CAN) PRE-TAKEOFF RUN, PILOT CHECKED RT MAG OFF. ENGINE QUIT. PILOT TOLD FUEL NATURE OF DEFECT TO FSS MONT-JOLI WHEN ADVISING THEM WERE RETURNING TO BLOCK. LEFT MAGNETA (DUAL TYPE) CAPACITOR CHECKED. NO CONTINUITY. SIGNS OF BURNS WHE RE WIRE IS SEALED-PITTED INTO CAPACITOR. REPLACED, RUN-UP, LOG ENTRY. NOTE: FAILED CAPACITOR WAS CHECKED ON 18 MARCH 2000 AS N/A BY DATE AND NAME OF MANUFACTURER. AEF: LYC SB 541 (TCM CSB NR 662A AND S.1.2 NR 642). 1 L 7 2 3O 3 O A20SO E14EA 2000083101013 20000831 01013 CE 2000 8 31 CA000802023 1 20000714 G 3230 51577A1 SOLENOID CESSNA 210 T210L 2073449 CE CONT O520 TSIO520H 17040 SO MCAULY 3A32C D3A32C88 GL SOLENOID FAILED W O OTHER O OTHER LD LANDING 1 CA 5024 19879072H 19879072H (CAN) AFTER TAKEOFF AND LANDING SELECTED UP AND LOCKED. LANDING GEAR CIRCUIT BREAKER TRIPPED. (PROBLEM RETURNED INTERM ITTENTLY.) PROBLEM TRACED TO DEFECTIVE LANDING GEAR SOLENOID. SOLENOID REPLACED, PROBLEM SOLVED. 1 H 7 1 3O 3 O 3A21 E8CE 5 C P21EA 2000101000349 20001010 00349 CE 2000 10 10 CA000802024 1 20000714 G 2730 12326241 BRACKET CESSNA 210 T210L 2073449 CE CONT O520 TSIO520H 17040 SO MCAULY 3A32C D3A32C88 GL LT INBD CRACKED W O OTHER O OTHER IN INSP/MAINT 1 CA 4955 19879072H 19879072H (CAN) DURING THE INSPECTION OF THE STABILIZER, A CRACK WAS FOUND ON THE INBOARD LT STABILIZER BRACKET TO ELEVATOR P/N 12 32624-1 ATTACHED TO THE SPAR. PROBLEM WAS REPAIRED. 1 H 7 1 3O 3 O 3A21 E8CE 5 C P21EA 2000101000350 20001010 00350 SO 2000 10 10 CA000803002 2 20000717 G 8530 635448 CYLINDER CONT CESSNA 185 A185F 2072821 CE CONT O520 IO520D 17032 SO MCAULY D3A34 D3A34C403 GL CYLINDER CRACKED W O OTHER O OTHER IN INSP/MAINT 1 CA 580 566472 777484 (CAN) HEAD CRACKED TWO/THIRDS AROUND AT 3RD FIN FROM BOTTOM OF HEAD. HEARD BY MAINTENANCE WHEN AIRCRAFT WAS TAXIING TO DOCK, PILOT REPORTED NO INDICATION OF PROBLEM. NO CAUSE FOUND. CYLINDER REPLACED. 1 H 7 1 3O 3 O 3A24 E5CE 5 C P47GL 2000101000351 20001010 00351 NM 2000 10 10 CA000803003 1 20000712 G 3242 214664 HOUSING DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE PISTON BORE CRACKED W O OTHER O OTHER IN INSP/MAINT 1 CA 10198 1275 1168 (CAN) BRAKE REMOVED FROM AIRCRAFT BECAUSE OF BRAKE BEING WORN TO LIMITS. INSPECTION AT SHOP REVEALED A CRACK IN ONE PIST ON BORE .700 INCH. BRAKE HOUSING SCRAPPED. 2 H 7 2 4T 4 T RT A13NM E20NE 2000101000352 20001010 00352 SO 2000 10 10 CA000803004 1 20000718 G 7797 WIRE PIPER 86749002 PIPER PA44 PA44180 7104402 SO 8 IN FROM SENDER CHAFED W O OTHER O OTHER CR CRUISE 1 CA (CAN) DURING TRAINING, FLT INSTRUCTOR NOTICED LEFT ENGINE TEMP GAUGE PEGGED AT HIGH RED LINE. PREVIOUS SCANS OF INSTRUM ENTS, BY BOTH STUDENT AND INSTRUCTOR HAD NOT INDICATED ANY PROBLEM. LOWER POWER SETTING TRIED BUT DID NOT DECREASE THE TEMP: PILOT MADE DECISION TO SHUT DOWN ENGINE TO AVOID DAMAGE AND HEADED INBOUND TO FIELD (YQM). A/C LANDED WITHOUT FURT HER INCIDENT. ENGINE GROUND RUN SERVICEABLE, BUT DECISION MADE TO INSPECT FURTHER. WIRE FROM INBOARD OF NACELLE, TO TE MP SENDER REMOVED FOR INSP. WIRE FOUND CHAFED 8 INCHES FROM SENDER. IT RUBBING ON ENGINE MOUNT OBSTRUCTED BY TY-RAPS A TTACHING IT. WIRE REPLACED, ISOLATED AND ACFT RETURNED TO SERVICE 1 L 7 2 3O A19S0 2000101000353 20001010 00353 EU 2000 10 10 CA000803005 1 20000707 G 2434 ALK8421 ALTERNATOR PARTEN P68 P68C 6780105 EU LYC O360 IO360A1B6 41514 EA RT ENGINE FAILED W O OTHER O OTHER IN INSP/MAINT 1 CA 283 A121326 L2371751A (CAN)ALTERNATOR NOT CHARGING, POSSIBLY DUE TO INTERNAL PROBLEMS. 1 H 7 2 3O 3 O A31EU 1E10 2000081600336 20000816 00336 SW 2000 8 16 CA000803006 1 20000719 G 7930 B3225C CHIP DETECTOR BELL 2060402703 BELL 206 206L 1181522 SW ALLSN 25OC 250C20R GL FREEWHEEL ASSY MISSING W O OTHER O OTHER IN INSP/MAINT 1 CA BLA05631 CAE295348 (CAN) DURING DAILY INSPECTION, IT WAS NOTICED THAT A PIN WAS NOT IN THE CHIP DETECTOR HOUSING ASSEMBLY. UPON REMOVAL IT WAS FOUND THAT 2 OF THE 3 PINS WHICH HOLD THE CHIP DETECTOR IN PLACE WERE MISSING. PINS COULD NOT BE FOUND. CHIP DETE CTOR ASSEMBLY WAS REPLACED. (X) 1 G 7 1 3U 3 U H2SW E4CE 2001031500106 20010315 00106 NM 2001 3 15 CA000804007 1 20000803 G 2700 841005 PSEU DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE SPOILERS FAILED W C ABORTED TAKEOFF N FALSE WARNING TO TAKEOFF 1 CA 27962 009 120833 860404 (CAN) ROLL SPOILER INBOARD / OUTBOARD GROUND CAUTION LIGHTS ILLUMINATED WHEN POWER LEVERS ADVANCE. DURING GROUND RUNS. F AULT PERSISTED WITH AUTO-FEATHER ON OR OFF. DRIVER FAULT ON PSEU. PSEU REPLACED, MICRO SWITCHES CLEANED AND AIRCRAFT RET URNED TO SERVICE. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2000100200012 20001002 00012 CE 2000 10 2 CA000804011 1 20000723 G 2434 ES4147 STATOR FORD 10300J BEECH P35 P35 1151530 CE CONT O470 IO470N 17026 SO MCAULY 2A36C 2A36C23 GL DIODE PLATE BROKEN W O OTHER H ELECT. POWER LOSS-50 PC CR CRUISE 1 CA 20 CS961508NR 705112 (CAN) TWO LEGS OF STATOR WINDING BROKE AT DIODE PLATE. RESULTS NO ALTERNATOR OUTPUT. (X) 1 L 7 1 3O 3 O RT 3A15 3E1 5 C P880 2000100200027 20001002 00027 2000 10 2 CA000804014 4 20000711 G 3452 414201128 TRANSPONDER CESSNA CESSNA 182 182Q 2072732 CE CONT O470 O470U 17026 SO MCAULY 2A34C C2A34C204 GL INTRNL CIR BOARD MELTED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA 16577 467467 7710865 (CAN) AIRCRAFT HAD BEEN AT CRUISE ALTITUDE FOR ABOUT TWO HOURS WHEN A STRONG BURNING SMELL WAS NOTICED BY ALL ABOARD. A N IMMEDIATE DESCENT WAS INITIATED AND CALGARY ATC DID AN EXCELLENT JOB OF DIVERTING TRAFFIC TO ALLOW A STRAIGHT IN APPRO ACH. PILOT ATTEMPTED TO SHED ALL UNNECESSARY ELECTRICAL LOADS AND AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. (X) 1 H 7 1 3O 3 O NT 3A13 E273 5 C P3EA 2001031500110 20010315 00110 NM 2001 3 15 CA000804015 1 20000722 G 3244 0396772 TIRE BOEING 737 737275 1384485 NM PWA JT8 JT8D9A 52048 NE NLG FAILED W A UNSCHED LANDING E VIBRATION/BUFFET CL CLIMB 1 CA 674569 (CAN) CREW REPORTED LOUD BANG FROM NOSE WHEEL AREA ON TAKEOFF ROLL AND JUST BEFORE ROTATION. THEY ALSO NOTICED SOMEHTING GO PAST THE WINDSCREEN. A FLY PAST THE CONTROL TOWER AND DEBRIS FOUND ON THE RUNWAY CONFIRMED TREAD SEPARATION FROM ONE OF THE NOSE WHEEL TIRES. THE AIRCRAFT FLEW AROUND TO BURN OFF SUFFICIENT FUEL AND LANDED WITHOUT INCIDENT. 2 L 7 2 4F 4 F A16WE E2EA 2001031500111 20010315 00111 NM 2001 3 15 CA000804016 1 20000722 G 2121 215201 MOTOR BOEING 737 737281 138448P NM PWA JT8 JT8D17 52049 NE GASPER FAN SEIZED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 CA 6915 776 P685509B (CAN) DURING THE CLIMB FROM 4XS (SASKATOON) THE CREW BECAME AWARE OF A STRANGE ODOR / SMELL IN THE CABIN. THERE WAS NO S MOKE OBSERVED BUT THE CREW ELECTED TO RETURN TO THE STATION AS A PRECAUTION. ON THE GROUND THE CREW CHECKED AND FOUND TH E GASPER FAN C/B POPPED. WHEN THEY ATTEMPTED TO RESET IT THE ODOR RETURNED TO THE CABIN. THE C/B WAS PULLED AND MEL 21-2 4 WAS APPLIED. THE GASPER FAN WAS REPLACED AT THE NEXT MAINTENANCE OPPORTUNITY. 2 L 7 2 4F 4 F A16WE E2EA 2001031500112 20010315 00112 NM 2001 3 15 CA000804017 1 20000712 G 5754 65555261 TRACK BOEING 737 737297 1384480 NM PWA JT8 JT8D9A 52048 NE SLATS BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA P665885 (CAN) DURING THE WALK AROUND AND INSPECTION FOR AN A CHECK THE MECHANIC NOTICED EXCESSIVE MOVEMENT IN THE NR 6 SLAT. FUR THER INVESTIGATION REVEALED THAT THE CENTER AUX RACK HAD BROKEN AT THE ATTACH POINT TO THE SLAT. THE SLAT ASSEMBLE WAS R EPLACED WITH A SERVICEABLE UNIT. REFERENCE ATTACHED PHOTOGRAPHS. 2 L 7 2 4F 4 F A16WE E2EA 2000100200029 20001002 00029 SO 2000 10 2 CA000804019 1 20000725 G 7714 574AW TACHOMETER CONSOLCNTRLS PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA TACHOMETER FAILED W K NONE O OTHER CR CRUISE 1 CA 187 7124 L91668A (CAN) PILOT REPORTED RIGHT TACHOMETER NEEDLE ERRATIC. TACHOMETER REPLACED WITH SERVICEABLE UNIT. GROUND RUN CARRIED OU T SATISFACTORILY. (X) 1 L 7 2 3O 3 O A20SO E14EA 2001031500114 20010315 00114 GL 2001 3 15 CA000808002 1 20000719 G 2730 SOGC4193000 CONTROL UNIT BOMBDR BD700 BD7001A10 1390006 GL ELEVATORS FAILED W A UNSCHED LANDING L F NO TEST FLT CONT AFFECTED CR CRUISE 1 CA (CAN) DURING PRODUCTION TEST FLIGHT STALL RECOVERY TEST 30 DEG FLAP, GEARDOWN, THE AIRCRAFT EXPERIENCED ABNORMALLY HEAVY PITCH CONTROL FORCES. THE ABNORMALITY WAS CLEARED BY HIGH PILOT EFFORT AT THE CONTROL COLUMN. ALL PRODUCTION FLIGHT TES TING WAS STOPPED AT THAT POINT AND THE AIRCRAFT RTURNED SAFELY TO BASE WITHOUT FURTHER INCIDENT. 2 L 7 2 4F RT T00003NY 2000100200033 20001002 00033 EA 2000 10 2 CA000808004 3 20000707 G 6111 PROPELLER SNSNCH PIPER PA28 PA28140 7102802 SO LYC O320 O320E2A 41508 EA SNSNCH 74D 74DM EA L/E & FACE DAMAGED W O OTHER O OTHER IN INSP/MAINT 1 CA 115 L2254827A A56025 (CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION; TRIMMED, ANODIZED, PAINTED. (X) 1 L 7 1 3O 3 O 2A13 E274 5 N P88614 2000100200034 20001002 00034 EA 2000 10 2 CA000808005 3 20000711 G 6111 BLADE SNSNCH PIPER PA28 PA28140 7102802 SO LYC O320 O320E3D 41508 EA SNSNCH 74D 74DM EA CAMBER SIDE CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA L3331127A K35171 (CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. 1 L 7 1 3O 3 O 2A13 E274 5 N P88614 2000100200035 20001002 00035 EA 2000 10 2 CA000808006 3 20000710 G 6111 PROPELLER SNSNCH PIPER PA28 PA28140 7102802 SO LYC O320 O320E2A 41508 EA SNSNCH 74D 74DM EA FACE CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 903 L1737427A A52179 (CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. REQUIRED OVERHAUL DUE TO CORROSION. (X) 1 L 7 1 3O 3 O 2A13 E274 5 N P88614 2000100200036 20001002 00036 NE 2000 10 2 CA000808008 3 20000726 G 6110 PROPELLER HAMSTD NAMER T6 HARVARDMK4 1922828 GL PWA R1340 R1340AN1 52016 NE HAMSTD 12D 12D40 NE PROPELLER CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 1134 8872CPL 404173 8872CPL (CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. CWT BRACKET WEB WORN BEYOND REPAIR. BLADE MERROR FINISHED WITH DEEP CORROSION. NOTE: MERROR FINISH IS NOT A GOOD THING FOR PROPELLER BLADES, IT DOES NOT OFFER ANY CORROSION PROTECTION. BLADE BEARINGS DRY. (X) 1 L 7 1 3R 3 R EXPA1L71 5E2 5 C P257 2000100200037 20001002 00037 CE 2000 10 2 CA000808009 1 20000801 G 3411 201314217 SELECTOR VALVE CESSNA 208 208B 2073701 CE PWA PT6 PT6A114 52043 NE LEAKING W A UNSCHED LANDING O OTHER CR CRUISE 1 CA PCE19192 (CAN) IN FLIGHT PILOT NOTICED A DISCREPANCY BETWEEN COPILOT AND PILOT AIR SPEED AND ALTIMETER. PILOT RETURNED TO MAINTEN ANCE BASE AND FOUND BODY OF SELECTOR VALVE SPARATED FROM DASH MOUNT PLATE CAUSING LARGE STATIC LEAK. VALVE WAS REMOVED, REASSEMBLED USING ORIGINAL PARTS AND REINSTALLED IN AIRCRAFT. LEAK CHECKED OK AND RETURNED TO SERVICE. 1 H 7 1 3T 3 T A37CE E4EA 2000100200038 20001002 00038 2000 10 2 CA000808010 4 20000720 G 6122 RELIEF VALVE HAMSTD DHAV DHC2 DHC2* 2800108 EA PWA R985 R985AN14B 52008 NE HAMSTD 2D 2D30 NE RELIEF VALVE FAILED W E ENGINE SHUTDOWN O OTHER CR CRUISE 1 CA 167 T16413 JP207431 T16413 (CAN) LOW PITCH STOP NUTS BROKEN, CWT SHAFTS BENT. THIS PROPELLER USES GOVERNOR OIL PRESSURE TO MOVE PROP TO LOW PITCH WITH RELIEF VALVE SET AT 200 PSI WHICH WILL NOT DAMAGE LOW STOPS. RELIEF VALVE HAD TO BE NON-OPERATIONAL DUE TO CONTAM INATION, CORROSION OR TAMPERING TO CAUSE THIS DAMAGE. (X) 1 H 7 1 3R 3 R A806 5E1 5 C P206 2001031500116 20010315 00116 WP 2001 3 15 CA000808012 1 20000728 G 7920 95551655 LINE DOUG DC3 DC3CS1C3G 3021458 WP PWA R1830 R183092 52020 NE LT ENGINE CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 461615 (CAN) HOSE REMOVED DUE ON CONDITION STATUS WHICH IS UNKNOWN. OUTER RUBBER FALLING OFF AND BRAIDING EXPOSED AND RUST CORR OSION ON BRAIDING FULL LENGTH OF HOSE, FROM OIL COOLER TO OIL TANK. 2 L 7 2 4R 4 R A669 5E4 2001031500117 20010315 00117 EA 2001 3 15 CA000808013 1 20000726 G 4950 FILTER CNDAIR CL601 CL6012A12 1900303 EA GE CF34 CF341A NE BLEED AIR LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA 270 350132 (CAN) ON JULY 25, 2000 CREW REPORTED UPON SELECTION OF APU BLEED AIR ASSOCIATED INDICATOR. OF LOAD CONTROL VALVE OPENING HAD FAILED. A/C MAINT ENGINEER OPENED EXTERNAL AIR SOURCE PANEL ONLY TO FIND APU FAULT INDICATOR PANEL HAD MELTED. FU RTHER INVEST. FOUND THAT APUS LOAD CONTROL VALVE FILTER HAD DEPARTED FROM VALVE ASSY & TRAVELLED THROUGH PNEUMATIC PLUMB ING EVENTUALLY JAMMING CHECK VALVE LOCATED AT EXTERNAL AIR SOURCE COUPLING. RESULTANT 10TH STAGE AIR LEAKED INTO ACCESS PANEL AREA & HEATED APU FAULT PANEL TO POINT OF MELTING IT. THE FAULT PANEL WAS ISOLATED, PNEUMATIC SYS INSP & A NEW LOA D CONTROL VALVE INSTALLED, DISCREPANCY RECTIFIED. 2 L 7 2 4F 4 F RT A21AE E15NE 2001032700139 20010327 00139 EA 2001 3 27 CA000808022 1 20000730 G 2730 276003 PCU CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE LT & RT ELEVATOR LEAKING W K NONE L NO TEST IN INSP/MAINT 1 CA (CAN) WHILE PERFORMING FIRST FLIGHT OF THE DAY ELEVATOR SYSTEM CHECK USING NR 2 HYDRAULIC SYSTEM ONLY, ELEVATOR POSITION EICAS READINGS SHOWING SPLIT AS MUCH AS 15-24 DEGREES. LT ELEVATOR PCU NR 2 AND RT ELEVATOR PCU NR 3 REPLACED. 2 L 7 2 4F 4 F RT A21EA E15NE 2001031500124 20010315 00124 NE 2001 3 15 CA000808023 2 20000730 G 7321 FUEL CONTROL CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE LT ENGINE FAILED W E A ENGINE SHUTDOWN UNSCHED LANDING E J VIBRATION/BUFFET WARNING INDICATION CR CRUISE 1 CA (CAN) CAPTAIN BROUGHT THROTTLES BACK TO FLIGHT IDLE AND THE NR 1 ENGINE STAYED AT A CRUISE POWER SETTING. IN FLIGHT SHUT DOWN PERFORMED ON THE LT ENGINE. DECLARED EMERGENCY. MAINTENANCE REPLACED THE LT ENGINE FUEL CONTROL UNIT. ENGINE CHECKE D SERVICEABLE AND AIRCRAFT RETURNED TO SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001031500125 20010315 00125 NE 2001 3 15 CA000808024 2 20000731 G 7261 O-RING CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE LT ENGINE LEAKING W E A ENGINE SHUTDOWN UNSCHED LANDING J K WARNING INDICATION FLUID LOSS CL CLIMB 1 CA (CAN) DURING A FERRY FLIGHT FROM MORLAIX TO CAEN, PILOTS REPORTED A LT ENGINE N2 FLUCTUATION FOLLOWED BY A LOW OIL PRESS URE WARNING MESSAGE. THE ENGINE WAS SHUT DOWN AND THE AIRCRAFT COMPLETED AN UNEVENTFUL LANDING IN MORLAIX. FINDINGS: OIL LEAK WAS FOUND AROUND THE AXIS . A O-RING RETAINER, 5 LITRES OF OIL ADDED. 2 L 7 2 4F 4 F RT A21EA E15NE 2000100200234 20001002 00234 NE 2000 10 2 CA000808025 2 20000808 G 8530 399356 CYLINDER PWA DHAV DHC3 DHC3 2800202 EA PWA R1340 R134059 52016 NE CYLINDER HEAD CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 286 13569 13569 (CAN) NR 4 CYLINDER HEAD FOUND CRACKED WHILE DOING AN UNSCHEDULED VISUAL INSPECTION OF THE ENGINE FORWARD FACE. CRACK W AS NOT DETECTED AT THE LAST INSPECTION 60.3 HOURS BEFORE THIS EVENT. CRACK LOCATED AT EXHAUST PUSH ROD/ROCKER HORN. S ERVICEABLE UNIT INSTALLED AND RETURNED TO SERVICE. (X) 1 H 7 1 3R 3 R A815 5E2 2001032700142 20010327 00142 2001 3 27 CA000809006 4 20000724 G 2312 064105430 TRANSCEIVER PIPER PA60 PA60600 7106001 NM LYC O540 IO540K1J5 41532 EA VHF SYSTEM FAILED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS FF FIRE FIGHTING 1 CA (CAN) DURING FIRE FIGHTING OPERATIONS THE NUMBER 2 POSITION VHF TRANSCEIVER HAD FAILED. THE PILOT SMELLED SMOKE IN THE C OCKPIT AND TURNED OFF THE RADIO. THE AIRCRAFT RETURNED TO YKA. THE SOURCE OF THE SMOKE WAS INVESTIGATED AND FOUND TO BE FROM THE NUMBER 2 VHF RADIO. THE RADIO WAS REPLACED WITH A SERVICEABLE UNIT. 1 M 7 2 3O 3 O RT A17WE 1E4 2000100200049 20001002 00049 WP 2000 10 2 CA000809007 2 20000730 G 7250 31015701 SEAL ALIDSG 310210610 GARRTT TPE331 TPE331* 01514 WP LABYRINTH SEAL FAILED W O OTHER O OTHER IN INSP/MAINT 1 CA 2680 5013455176 (CAN) DURING PRE-INSTALLATION INSPECTION, IT WAS NOTICED THAT THERE WAS EXCESSIVE GAP BETWEEN THE SEAL AND THE ROTOR. G AP WAS MEASURED AT 0.022 INCHES. IRM 72-IR-15 R9 STATES THAT THE GAP SHOULD BE NO LARGER THAN 0.010 INCHES. 3 T E2WE 2001032700144 20010327 00144 CE 2001 3 27 CA000809011 1 20000713 G 3213 998100289 BRACE BEECH 99 99 1154002 CE MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 4060 (CAN) FATIGUE CRACKS LOCATED AT BASE OF TQ KNEE LUG ON UPPER BRACE. CRACKS RANGE IN SIZE FROM 1/4 TO 3/8 INCH LONG AND R UN PARALLEL TO THE TQ KNEE LUG RADIUS. UPPER BRACE REMOVED FROM SERVICE. 1 L 7 2 3T A14CE 2001032700145 20010327 00145 CE 2001 3 27 CA000809012 1 20000724 G 2134 44EVAB4 TUBE BEECH 200 B200C 1152924 CE PWA PT6 PT6A42 52043 NE BLEED AIR SPLIT W B EMER. DESCENT N FALSE WARNING CL CLIMB 1 CA (CAN) DURING CLIMB CREW OBSERVED A RT BLEED AIR LIGHT. WHEN RT BLEED AIR SWITCHED OFF, LT BLEED WOULD NOT HOLD CABIN PRE SSURE. AN EMERGENCY DESCENT WAS CARRIED OUT. AT 7,000 THE AIRCRAFT LEVELED OFF AND RETURNED TO BASE. THE DAMAGED PIECE O F TUBING WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. THIS TUBING IS PRESSURIZED BY THE BLEED AIR SYSTEM. IF IT LE AKS. AS IS THE CASE WITH THIS AIRCRAFT IT WILL GIVE A BLEED AIR INDICATION, AND A FALSE WARNING TO THE FLIGHT CREW. 1 L 7 2 4T 4 T A24CE E4EA 2001032700146 20010327 00146 2001 3 27 CA000809013 4 20000728 G 3418 CONTROL UNIT DHAV DHC7 DHC7* EA STALL WARNING FAILED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 24220 (CAN) ARKIA AIRLINES FLIGHT CREW REPORT RECEIVING A STALL WARN/STICK SHAKER DURING INITIAL CLIMB, APPROXIMATELY 500 FT. IAS 100 KTS/120 KTS AT THE TIME THE INCIDENT OCCURRED. CREW REACTED BY ADVANCING PLA ON ALL ENGINES & REPORT ALL THE ALL STALL WARNINGS LASTED APPROX. 30 SECS. CREW THEN CARRIED OUT AN IMMEDIATE AIR RETURN TO DOV AIRPORT. NO EMERGENCY WAS D ECLARED & AIRCRAFT LANDING WAS UNEVENTFUL DFDR & CVR REMOVED FOR ANALYSIS. 2 H 7 4 4T RT A20EA 2001032700147 20010327 00147 NE 2001 3 27 CA000809014 2 20000728 G 7261 310573507 REGULATOR DHAV DHC8 DHC8311 1386006 EA PWA PW120 PW123 NE OIL PRESSURE LEAKING W E ENGINE SHUTDOWN K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) NR 2 ENGINE OIL PRESSURE WARNING LIGHT ILLUMINATED DURING THE CRUISE PHASE OF FLIGHT. NR 2 OIL PRESSURE DROPPED T O BELOW 40 PSI. ENGINE SHUT DOWN. OIL LEAK FOUND ON NR 2 ENGINE OIL PRESSURE REGULATOR VALVE, HOUSING ASSEMBLY. AT THE TEST POINT, PRESSURE REGULATOR ASSEMBLY REPLACED, GROUND RUNS COMPLETED SATISFACTORY. 2 H 7 2 4T 4 T RT A13NM E20NE 2001032700148 20010327 00148 EA 2001 3 27 CA000810002 1 20000807 G 3230 601R7520615 PRIORITY VALVE CNDAIR CL600 CL6002B19 EA MLG FAILED W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA (CAN) THE FLIGHT CREW REPORTED DURING CRUISE: WHEN FOLLOWING THE QRH PROCEDURES FOR A MLG OVERHEAT FAIL MESSAGE . THE GE AR DISAGREE WARNING MESSAGE ILLUMINATED. THE A/C COULD NOT CONTINUE THE FLIGHT WITH GEAR SELECTED DOWN DUE TO THE MLG OV ERHEAT FAIL MESSAGE & THE ADDITIONAL FUEL REQUIREMENT. AIRCRAFT RETURNED TO THE DEPARTING AIRPORT & DECLARED EMERGENCY. MAINTENANCE REPLACED THE NOSE & MAIN LANDING GEAR PRIORITY VALVE. AIRCRAFT RETURNED TO SERVICE. 2 L 7 2 4F RT A21EA 2001032700149 20010327 00149 EA 2001 3 27 CA000810003 1 20000807 G 3260 PROXIMITY SWITCH CNDAIR CL600 CL6002B19 EA RT MLG LOOSE W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 CA (CAN) THE FLIGHT CREW REPORTED: ON DEPARTUE, THE GEAR DISAGREE WARNING MESSAGE IN ASSOCIATION WITH THE RIGHT GEAR SHOWIN G RED. QRH PROCEDURE FOLLOWED AND AIRCRAFT RETURNED TO THE DEPARTING AIRPORT, EMERGENCY DECLARED, THE LANDING WAS UNEVEN TFUL. MAINTENANCE FOUND LOOSE PROX TARGETON THE RIGHT MLG. TARGET RE-SECURED AND AIRCRAFT RETURNED TO SERVICE AFTER A GE AR SWING. 2 L 7 2 4F RT A21EA 2001032700150 20010327 00150 EA 2001 3 27 CA000810004 1 20000807 G 3220 STRUT CNDAIR CL600 CL6002B19 EA NLG FAILED W A UNSCHED LANDING K FLUID LOSS CL CLIMB 1 CA (CAN) THE FLIGHT CREW REPORTED: GEAR UP DISAGREEMENT (NOSE) ON TAKEOFF. QRH PROCEDURE WERE COMPLIED WITH (PRECAUTIONARY LANDING). AIRCRAFT RETURNED TO DEPARTING AIRPORT. MAINTENANCE FOUND NOSE STRUT IMPROPERLY SERVICED (RE-SERVICED NOSE GEA R STRUT ASSEMBLY) AND GEAR RETRACTION CARRIED OUT. 2 L 7 2 4F RT A21EA 2001032700151 20010327 00151 EA 2001 3 27 CA000810005 1 20000807 G 3320 BR95005 BALLAST CNDAIR CL600 CL6002B19 EA CABIN SHORTED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA (CAN) THE FLIGHT CREW REPORTED: NOTICED BURNING SMELLL IN DURING FLIGHT. AIRCRAFT RETURNED TO DEPARTING AIRPORT.MAINTENA NCE REPLACED BALLAST AT CABIN SEAT LOCATION 3BC. 2 L 7 2 4F RT A21EA 2001032700152 20010327 00152 EA 2001 3 27 CA000810006 1 20000807 G 2910 AE2460210E0164 LINE CNDAIR CL600 CL6002B19 EA HYD SYSTEM DAMAGED W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CL CLIMB 1 CA (CAN) ON INITIAL CLIMB, AFTER SELECTING THE LANDING GEAR UP, THE GEAR DISAGREE WARNING MESSAGE WAS POSTED ON EICAS. SHOR TLY AFTER, HYD 3 LO PRESS CAUTION MESSAGE WAS POSTED. AIRCRAFT RETURNED TO DEPARTING AIRPORT. MAINTENANCE DISCOVERED THA T THE HYDRAULIC HOSE ASSEMBLY CONNECTING TO THE NOSE GEAR SELECTOR VALVE WAS DAMAGE WHICH CAUSED THE FLUID LOSS. HOSE RE PLACED AND AIRCRAFT RETURNED TO SERVICE. 2 L 7 2 4F RT A21EA 2001032700153 20010327 00153 EA 2001 3 27 CA000810007 1 20000807 G 3310 BC10059001 SOCKET CNDAIR CL600 CL6002B19 EA GALLEY SHORTED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 CA (CAN) FLIGHT CREW REPORTED, NOTICED ELECTRIC SMOKE DURING FLIGHT. AIRCRAFT RETURNED TO DEPARTURE AIRPORT, NO EMERGENCY D ECLARED. MAINTENANCE FOUND GALLEY LIGHT SOCKET SHORTED. SOCKET REPLACED AND AIRCRAFT RETURNED TO SERVICE. 2 L 7 2 4F RT A21EA 2001032700154 20010327 00154 EA 2001 3 27 CA000810008 1 20000806 G 3310 BR95005 BALLAST CNDAIR CL600 CL6002B19 EA ROW 3BC SHORTED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA (CAN) THE FLIGHT CREW REPORTED: NOTICED BURNING SMELL IN AIRCRAFT DURING FLIGHT. AIRCRAFT RETURNED TO DEPARTURE AIRPORT , NO EMERGENCY DECLARED. THE MAINTENANCE REPLACED THE BALLAST AT THE CABIN SEAT LOCATION 3BC. 2 L 7 2 4F RT A21EA 2001032700155 20010327 00155 EA 2001 3 27 CA000810009 1 20000806 G 7500 7062814460101 DUCT CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE 14TH STAGE CRACKED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) DURING A PERIOD OF 4 DAYS, THE CREW REPORTED NUMEROUS INDICATION OF RT JET OVHT FAIL, CAUTION MESSAGE AND RT JET P IPE OVHT WARNING MESAGE. WHEN RETARDING THE THRUST AS PER QRH, THE MESSAGES WENT AWAY. THE PROBLEM WAS IDENTIFIED AS A 1 4TH STAGE DUCT LEAK IN THE PYLON. THE DUCT WAS CONFIRMED TO BE CRACKED (APPROX 2 INCHES LONG) ON THE CIRCUMFERENCE AT TH E FLANGE OF ITS JOINT IN THE PYLON. THE DUCT WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001032700156 20010327 00156 EA 2001 3 27 CA000810010 1 20000806 G 2742 70623 CONTROL UNIT CNDAIR CL600 CL6002B19 EA STABILIZER FAILED W O OTHER J WARNING INDICATION CR CRUISE 1 CA (CAN) BRIT AIR HAVE REPORTED A STABILIZER PIVOT BUSHING SEIZED AND BOTH STAB TRIM CHANNELS INOPERATIVE. THE MAINTENANCE REPLACED THE MCU AND THE HSTA. ALSO ONE BUSHING, TWO BUSHINGS AND ONE FITTING WERE REPLACED.AIRCRAFT RETURNED TO SERVI CE. 2 L 7 2 4F RT A21EA 2001032700157 20010327 00157 2001 3 27 CA000810011 4 20000808 G 3414 LINE CNDAIR CL600 CL6002B19 EA P3 LEAKING W C ABORTED TAKEOFF N FALSE WARNING TO TAKEOFF 1 CA (CAN) ABORTED TAKEOFF, NO AIRSPEED ON STANDBY AIRSPEED INDICATOR. MAINTENANCE PURGE P3 LINE AND PERFORMED LEAK TEST IAW AMM TASK 34-11-00-790-803. 2 L 7 2 4F RT A21EA 2001032700159 20010327 00159 SO 2001 3 27 CA000810014 2 20000725 G 8530 SA530830 PISTON PIN CESSNA 150 150L 2071826 CE CONT O200 O200A 17020 SO MCAULY 1A101 1A101HCM GL ENGINE CHIPPED W K NONE O OTHER IN INSP/MAINT 1 CA 1659 1659 (CAN) ALUMINIUM CHIPS FOUND IN OIL FILTER.ALL CYLINDER REMOVED AND PISTON PIN NR 1, 2 AND 3 REPLACED (NR 4 WAS REPLACED AT 1171.4). 1 H 7 1 3O 3 O 3A19 E252 5 N P918 2000081600337 20000816 00337 EU 2000 8 16 CA000810015 1 20000720 G 6220 350A31190703 STARFLEX 360A31000008 SNIAS 350 AS350D 8680803 EU LYC LTS101 LTS101600A 41560 NE M/R HEAD CRACKED W O OTHER O OTHER IN INSP/MAINT 1 CA 1407 M447 LE43520E (CAN) STAR FOUND CRACK IN YELLOW. P STAR FLEX REPLACED. 1 G 7 1 3U 3 U H9EU E5NE 2000090800090 20000908 00090 SO 2000 9 8 CA000810016 1 20000727 G 8120 4066109020 TURBOCHARGER LYC PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2B 41532 EA RT ENGINE SLUGGISH W O OTHER R PARTIAL RPM/PWR LOSS CL CLIMB 1 CA 543 L524661A (CAN) TAKEOFF AT 43 HG - ON LEG RETURN TO HOME BASE. FIRST POWER SETTING TO 40 HG - THROTTLE BACK - DID NOT RESPOND. SECOND POWER SETTING TO 35 HG - PILOT HAD TO PULL THROTTLE QUITE FAR BACK AND THEN FORWARD TO SET POWER. WASTEGATE, TH ROTTLE LINKAGE CHECKED. INSPECTION OF TURBO SHOW HEAVY RESIDUES OF GRAY SUIT ON COMPRESSOR HOUSING AND SOME ON EXHAUST IMPELLER. REPLACED TURBOCHARGER. EVIDENCE OF IMPROPER COOLING AFTER FLIGHT OR RUN-UP .LATELY: DAMP, HEAVY HOT CLIMATE . 1 L 7 2 3O 3 O A20SO E14EA 2000090800096 20000908 00096 EA 2000 9 8 CA000810017 1 20000810 G 2910 LINE CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE HYD LINE BURST W A UNSCHED LANDING J S K WARNING INDICATION AFFECT SYSTEMS FLUID LOSS TO TAKEOFF 1 CA (CAN) DESCRIPTION OF DEFECTS: AIRCRAFT AFTER TAKEOFF AND ON CLAIM RECEIVED HYD 3 PRESS EICAS WARNING MESSAGE. SYSTEM N R 3 HAD NO PRESSURE. AIRCRAFT DECLARED EMERGENCY LANDING AND EMERGENCY GEAR EXTENSION AND RETURN TO FIELD. MAINTENANCE ACTIONS: MAINTENANCE HAS FOUND A HYDRAULIC LINE BURST. LINE WILL BE REPLACED WHEN PART IS GOING TO BE AVAILABLE AND A IRCRAFT WILL BE SENT BACK TO SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2000092800086 20000928 00086 EU 2000 9 28 CA000811003 1 20000714 G 6230 4619305032M MAST 3638001009 BOLKMS 105 BO105C 5626005 EU ALLSN 250C 250C20B 03013 GL MAIN ROTOR FAILED W D RETURN TO BLOCK J WARNING INDICATION TO TAKEOFF 1 CA 6061 671 1024 (CAN) EVENT: DURING PILOT TRAINING OFF-LEVEL LANDING BEING CONDUCTED; A/C LANDED ON SLOPE WITH RT SKID LOW. PILOTS WE RE CHECKING THEIR RESPECTIVE SIDES OF A/C AND A/C MOVED ON SLOPE. PILOT APPLIED CYCLIC INPUT WHEN THE A/C SLIPPED. WHE N A/C LIFTED INTO HOVER,TRAINING PILOT NOTICED MAST MOMENT IND. LIGHT ON STEADY, AND A/C RETURNED TO BASE. MAINT ACTION : MAINT MANUAL CHECKED FOR PROCEDURES WHEN MAST MOMENT LIMITS EXCEEDED. MAIN ROTOR STUDS WERE CHECKED FOR LOSS OF TORQ UE. RESULTS OF TORQUE INSP REVEALED THAT ALL 12 NUTS HAD LESS THAN MIN 140 NEWTON METERS OF TORQUE 4 OF 12 NUTS MOVED A PPROXIMATELY 1/4 OF FLAT TO BRING THEM UP TO TORQUE. 1 G 7 2 3U 3 U H3EU E4CE 2000090800097 20000908 00097 SO 2000 9 8 CA000811004 2 20000720 G 8520 649133 CRANKSHAFT CONT CESSNA 182 182N 2072730 CE CONT O470 IO470D 17026 SO MCAULY 2A34C D2A34C58 GL FWD - NR 1 ROW SEPARATED W B A EMER. DESCENT UNSCHED LANDING E T Y VIBRATION/BUFFET ENGINE CASE PENETRATION ENGINE STOPPAGE CR CRUISE 1 CA 3746 82 791680D (CAN) AIRCRAFT WAS IN A CRUISE ATTITUDE, IN PREPARATION TO DISEMBARK SKYDIVERS, WHEN PILOT NOTICED AN ENGINE VIBRATION FOLLOWED BY A BANG, ENGINE CAME TO A SUDDEN STOP. AIRCRAFT LANDED AT AIRPORT OF DEPARTURE WITHOUT FURTHER INCIDENT. U PON INSPECTION, FOUND CRANKSHAFT HAD FAILED AND PUNCTURED THROUGH THE TOP OF THE CRANKCASE. THIS AIRCRAFT ENGINE HAS BE EN MODIFIED PER STA NR SA95-55 AND SE95-9. 1 H 7 1 3O 3 O NT 3A13 3E1 5 C P3EA 2000090800098 20000908 00098 NM 2000 9 8 CA000824002 1 20000818 G 2910 82970410119 LINE DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE LT NACELLE FAILED W O OTHER K FLUID LOSS IN INSP/MAINT 1 CA (CAN) HYDRAULIC PRESSURE LINE NR 1 SYSTEM WORN THROUGH 1/2 WALL THICK AT LOCATION X124 LT NACELLE ABOVE EXHAUST. LINE WORN BECAUSE ADEL CLAMPS BROKE ALONG SIDE MLG RETRACTION ACTUATOR FITTER LOCATION AND RUBBED AGAINST LINE. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001032700163 20010327 00163 EA 2001 3 27 CA000824006 2 20000815 G 8550 7581378 SEAL LW13904 PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA RT ENGINE RUPTURED W E C ENGINE SHUTDOWN ABORTED TAKEOFF K J FLUID LOSS WARNING INDICATION TO TAKEOFF 1 CA 586 (CAN) RT ENGINE OIL FILTER CONVERTER PLATE SEAL RUPTURED DURING TAKEOFF, CAUSING OIL LOSS ONTO HOT TUBOCHARGER AND EXHAU ST COMPONENTS. THE FLIGHT CREW NOTED DECAYING OIL PRESSURE AND LOSS OF PROPELLER RPM CONTROL, AND INITIATED ENGINE IN-FL IGHT SHUTDOWN. INVESTIGATION REVEALED AN APPARENT BREAK-DOWN OF THE BONDED RUBBER SEAL MATERIAL BETWEEN THE OIL FILTER C ONVERTER-PLATE AND THE ENGINE CASE. THE SWELLED RUBBER INDICATED AN INCOMPATIBILITY WITH THE ENGINE OIL. 1 L 7 2 3O 3 O A20SO E14EA 2000090800099 20000908 00099 CE 2000 9 8 CA000824010 1 20000730 G 7820 04504003 MUFFLER CESSNA 045040021 CESSNA 150 150M 2071830 CE CONT O200 O200A 17020 SO BACK END CRACKED W A UNSCHED LANDING Y ENGINE STOPPAGE CL CLIMB 1 CA 4623 (CAN) AFTER TAKEOFF AND IN CLIMB-OUT, PILOT EXPERIENCED POWER LOSS (90 PERCENT). PILOT RETURNED TO THE AIRPORT AND LAND ED SAFELY. ON ROLL OUT, ENGINE STOPPED COMPLETELY AND COULD NOT BE RESTARTED. INVESTIGATION FOUND THE REAR SECTION OF T HE LEFT HAND EXHAUST MUFF WAS CRACKED LEAVING A HOLE ALLOWING HOT EXHAUST GASES TO ESCAPE INTO THE ENGINE COMPARTMENT. THE HOT GASES MELTED THE MAGNETO P-LEAD WIRES RUNNING ALONG THE FIREWALL. BECAUSE THE P-LEADS WERE SHIELDED, THE OUTER GROUND SHIELDING MELTED AND CONTACTED THE INNER P-LEAD WIRE. THUS GROUNDING OUT THE MAGNETOS CAUSING THE ENGINE TO QUIT. THE MUFFLER WAS INSPECTED PER CF-90-13R2. 1 H 7 1 3O 3 O 3A19 E252 2001031500128 20010315 00128 EU 2001 3 15 CA000824011 1 20000728 G 3230 GEAR HWKSLY DH1254 HS125400F 230145 EU LEVER UNSECURE W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) AFTER MAINTENANCE, AIRCRAFT WAS DELIVERED TO CUSTOMER. ON DEPARTURE DURING INITIAL CLIMB, GEAR WAS SELECTED UP. CR EW STATED GEAR APPEARED TO RETRACT (GREEN LIGHT OUT) BUT A WARNING LIGHT REMAINED ON RT GEAR. ATC REPORTED GEAR WAS NOT FULLY RETRACTED SO THE AIRCRAFT CANCELLED AND RETURNED. SEVERAL GEAR SWINGS WERE PERFORMED AND NOTHING FOUND. PRIOR TO F LIGHT EMERGENCY HYDRAULIC LEVER HAD BEEN LIFTED TO DROP GEAR DOORS FOR WHEEL WELL INSPECTION BY CREW PRIOR TO FLIGHT. WE SUSPECT LEVER WAS NOT FULLY STOWED ALLOWING BYPASS OF HYDRAULIC PRESSURE AND PREVENTING THE FULL RETRACTION OF GEAR. AI RCRAFT DEPARTED AGAIN AND GEAR FUNCTIONED NORMAL. 2 L 7 2 3F RT A3EU 2000100200137 20001002 00137 2000 10 2 CA000824013 4 20000731 G 3460 TH2502FF CONTROL BOX GULSTM 500 500B 0141106 SW LYC O540 IO540E1A5 41532 EA FM CNTRL HEAD BURNED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA 2011 (CAN) PILOT REPORTED SMOKE IN THE COCKPIT AND LANDED. INSPECTION FOUND THAT FM CONTROL HEAD WAS UNSERVICEABLE AND SMELL ED BURNT. SERVICEABLE FM CONTROL HEAD WAS INSTALLED AND TESTED WITHOUT RECURRENCE. 1 H 7 2 3O 3 O 6A1 1E4 2000100200209 20001002 00209 CE 2000 10 2 CA000824021 1 20000604 G 5710 8178512 BOLT BEECH BEECH 100 B100 1152919 CE UPPER FWD WING CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA BE131 BE131 (CAN) UPPER FORWARD WING - BOLT FOUND CRACKED DURING ROUTINE INSPECTION. 1 L 7 2 4T A14CE 2000100200210 20001002 00210 NE 2000 10 2 CA000824022 2 20000618 G 8530 366249 CYLINDER PWA DHAV DHC3 DHC3 2800202 EA PWA R1340 R134059 52016 NE ROCKER EAR CRACKED W O OTHER O OTHER CR CRUISE 1 CA 712 4215119 (CAN) ROCKER EAR SEPARATION AT ROCKER PIN. 1 H 7 1 3R 3 R A815 5E2 2000100200211 20001002 00211 CE 2000 10 2 CA000824023 1 20000623 G 2410 DOFF10300B ALTERNATOR CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO ALTERNATOR FAILED W O OTHER H ELECT. POWER LOSS-50 PC DE DESCENT 1 CA (CAN) UPON DESCENT, PILOT NOTICED AMP METER IN DISCHARGE POSITION. AFTER CHECKING BREAKERS, HE SWITCHED OFF MOST ELECTRI CAL SWITCHES TO CONSERVE BATTERY POWER THROUGH LANDING. INVESTIGATION REVEALED ALTERNATOR AND CONTROLLER NOT FUNCTIONIN G. BOTH PARTS REPLACED AND AIRCRAFT RETURNED TO SERVICE BY AME. 1 H 7 1 3O 3 O A4CE E5CE 2000100200212 20001002 00212 SO 2000 10 2 CA000824024 2 20000629 G 7414 X13964 MAGNETO CONT CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO RT MAGNETO FAILED W O OTHER O OTHER TX TAXI/GRND HDL 1 CA 1686209F (CAN) WHILE TAXIING AFTER LANDING, PILOT TESTED MAG SWITCH TO DISCOVER DEAD RT MAGNETO. INVESTIGATION BY AME DISCOVERED RT MAGNETO NOT WORKING. PART WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE. 1 H 7 1 3O 3 O A4CE E5CE 2000100200213 20001002 00213 CE 2000 10 2 CA000824025 1 20000725 G 8100 12502557 MOUNT BRACKET CESSNA 12502557 CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO RT LWR FIREWALL BROKEN W O OTHER E VIBRATION/BUFFET IN INSP/MAINT 1 CA (CAN) PILOT NOTED SLIGHT ENGINE VIBRATION, ENGINE PARAMETERS NORMAL .INVESTIGATION REVEALED EXHAUST SUPPORT MOUNT P/N 1 250255-7 BROKEN, ALSO DISCOVERED MUFFLER (P/N 1250251-13) HEAT SHIELD MOUNT CRACKED AT WELD. EXHAUST SUPPORT MOUNT AND MUFFLER REPLACED, VIBRATION PROBLEM SOLVED. AIRCRAFT OPERATES ON FLOATS, SUSPECT THAT MOUNT FAILED AND ALLOWING MUFFLE R, TAILPIPE TO RESONATE, CAUSING MUFFLER TO CRACK. 1 H 7 1 3O 3 O A4CE E5CE 2001032700170 20010327 00170 CE 2001 3 27 CA000824026 1 20000705 G 7603 S110113 ROD END CESSNA 210 210 2073402 CE CONT O470 IO470E 17026 SO MCAULY 2A34C D2A34C58 GL THROTTLE SEPARATED W A UNSCHED LANDING O OTHER CR CRUISE 1 CA (CAN) PILOT REPORTED LACK OF THROTTLE RESPONSE. THE AIRCRAFT LANDED SAFELY. MAINTENANCE FOUND THROTTLE ROD END SEPARATED FROM BALL AT THROTTLE ARM ON THE FUEL CONTROL. A NEW ROD END 1 H 7 1 3O 3 O RT 3A21 3E1 5 C P3EA 2001032700171 20010327 00171 CE 2001 3 27 CA000824027 1 20000713 G 2921 MS287001 ACCUMULATOR BEECH 100 B100 1152919 CE GARRTT TPE331 TPE3316252B 01514 WP HYD SYSTEM FAILED W O OTHER J WARNING INDICATION CR CRUISE 1 CA (CAN) 1 HOUR INTO RETURN LEG, MOTOR LIGHT STARTED TO ILLUMINATE MORE OFTEN, FINALLY RUNNING CONTINUOUSLY BEFORE 60 AMP B REAKER IN FLOOR OPENED. PILOT PERFORMED NORMAL GEAR BLOW DOWN AND LANDED. - MAINTENANCE FOUND GEAR SYSTEM ACCUMULATION P RESSURE LOW.- SYSTEM SERVICED AND RUN, RELEASED FOR FLIGHT. AGAIN FOUND SYSTEM LOW AFTER RETURN TO BASE. SYSTEM SERVICED , AGAIN SAME PROBLEM. SWAPPED ACCUMULATOR WITH ANOTHER AIRCRAFT. BOTH ARE RUNNING FINE. HOLDING PRESSURE. 1 L 7 2 4T 4 T A14CE E2WE 2001032700173 20010327 00173 CE 2001 3 27 CA000824029 1 20000720 G 2510 56140593 SEAT CESSNA 414 414A 2075907 CE CONT O520 TSIO520NB 17040 SO MCAULY 3AF32C 3AF32C505 GL COCKPIT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 7058 (CAN) PILOTS SEAT SUPPORT LEFT/RIGHT CHANNELS CRACKED / BROKEN / MISSING PIECES. NEW LEFT / RIGHT SUPPORT CHANNELS FABRI CATED AND INSTALLED. FOUND DURING ROUTINE SCHEDULED INSPECTION. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2000100200032 20001002 00032 SO 2000 10 2 CA000824030 1 20000728 G 3233 GROUND WIRE PIPER PA34 PA34220T 7103420 SO CONT O360 TSIO360KB 17025 SO MCAULY 3AF32C 3AF32C508 GL TERMINAL END BROKEN W O OTHER R PARTIAL RPM/PWR LOSS LD LANDING 1 CA 866 (CAN) THIS AIRCRAFT SUFFERED A PARTIAL GEAR UP LANDING ON JUNE 19, 2000. TEMPORARY REPAIRS WERE MADE AND THE AIRCRAFT WA S FERRIED TO CYEG FOR FURTHER INSPECTION AND REPAIR. NECESSARY REPAIRS WERE MADE. INSPECTION BEFORE FURTHER FLIGHT REV EALED THAT THE STAKON TERMINAL END ON THE HYDRAULIC PUMP ELECTRIC MOTOR GROUND WIRE WAS CRIMPED OVER THE INSULATION WITH ONLY ONE OR TWO STRANDS OF WIRE MAKING CONTACT. GROUND CONTACT COULD BE MADE OR BROKEN SIMPLY BY FLEXING THE WIRE AT T HE STAKON TERMINAL END. HIS COULD HAVE BEEN THE CAUSE OF THE UNDERCARRIAGE MALFUNCTION. IT APPEARS TO BE ORIGINAL FACT ORY INSTALLATION. 1 L 7 2 3O 3 O A7SO E9CE 5 C P22EA 2001032700174 20010327 00174 EA 2001 3 27 CA000824031 1 20000728 G 2400 HOSE DHAV DHC3 DHC3 2800202 EA PWA PT6 PT6A34 52043 EA HEATER BURNED W C ABORTED TAKEOFF B SMOKE/FUMES/ODORS/SPARKS TO TAKEOFF 1 CA (CAN) ON TAKEOFF RUN SMOKE STARTED COMING FROM UNDER INSTRUMENT PANEL. THE TAKEOFF WAS ABORTED PRIOR TO LIFT-OFF THE WAT ER. MAINTENANCE FOUND THAT A SCAT HOSE IN THE HEATER SYSTEM FWD OF THE RT INSTRUMENT PANEL HAD MOVED REARWARD AND CONTAC TED THE HOT BUS SIDE OF THE C/BS. CURRENT FOUND A GROUND THROUGH THE WIRE IN THE SCAT HOSE AND CAUSED ARICH SECTION OF T HE SCAT HOSE TO BURN.THE EFFECT HOSE WAS REMOVED AND C/BS WITH PITTING ON THE HOT TERMINALS WERE REPLACED. ELECTRICAL SY STEM WILL BE PROTECTED FROM ANY POSSIBLE REARWARD MOVEMENT OF SCAT HOSE WHEN HOSE IS REINSTALLED. 1 H 7 1 3R 4 T A815 E4EA 2000100200215 20001002 00215 NE 2000 10 2 CA000828004 2 20000714 G 8530 366249 VALVE PWA DHAV DHC3 DHC3 2800202 EA PWA R1340 S3H1G 52016 NE EXHAUST VALVE FRACTURED W O OTHER R PARTIAL RPM/PWR LOSS LD LANDING 1 CA 1115 P326010 (CAN) UPON REACHING DESTINATION, THE PILOT REDUCED POWER TO LAND. UPON DOING SO, THE ENGINE STARTED TO BACKFIRE AND RUN ROUGH. NORMAL LANDING PROCEDURES WERE CARRIED OUT FOR REDUCED POWER AND AIRCRAFT LANDED WITHOUT INCIDENT. PRIOR TO TH IS, THE ENGINE HAD NOT GIVEN ANY INDICATION OF ANY PROBLEMS. UPON INVESTIGATION OF THE ENGINE, IT WAS NOTED THE EXHAUST VALVE IN THE NR 1 CYLINDER HAD BROKEN OFF AND HAD DAMAGED THE PISTON AND CYLINDER HEAD. PARTS OF THE VALVE WERE ALSO F OUND AT THE NR 5 AND NR 6 CYLINDERS INTAKE TUBES. INTAKES NRS 4, 5, 6, AND 7 WERE CLEANED, ENGINE WAS INSPECTED FOR OTH ER DAMAGE AND NR 1 CYLINDER CHANGED AND AIRCRAFT WAS RETURNED TO SERVICE. 1 H 7 1 3R 3 R A815 E142 2000100200216 20001002 00216 NE 2000 10 2 CA000828005 2 20000727 G 8530 366249 CYLINDER PWA DHAV DHC3 DHC3 2800202 EA PWA R1340 S3H1G 52016 NE BROKEN RINGS WORN W A UNSCHED LANDING K FLUID LOSS CR CRUISE 1 CA 1138 P326010 (CAN) AIRCRAFT DEPARTED, JUST AFTER TAKEOFF, THE PILOT NOTICED OIL ON THE WINDSHIELD. AFTER CHECKING ENGINE INSTRUMENTS , OIL TEMP NORMAL, OIL PRESSURE NORMAL. CYLINDER HEAD TEMP 240 (OAT FOR THE DAY WAS ABOUT 30 DEGREES CELSIUS). PILOT D ECIDED TO CONTINUE THE FLIGHT TO MAIN BASE ABOUT 16 MILES AWAY. ABOUT 8 MILES FROM BASE, THE OIL LEAK STARTED TO WORSEN AND ENGINE STARTED RUNNING ROUGH. PILOT DECIDED TO LAND. THE PLANE LANDED WITHOUT INCIDENT. ON INVESTIGATION OF THE ENGINE, NR 9 PISTON DISCOVERED BROKEN AND MISSING 2 TOP RINGS WHICH CAUSED THE CASE TO PRESSURIZE AND BLOW OIL OUT THE N OSE CASE. NR 9 CYLINDER WAS CHANGED AND ENGINE INSPECTED FOR ANY OTHER DAMAGE. AIRCRAFT WAS RETURNED TO SERVICE. 1 H 7 1 3R 3 R A815 E142 2000100200217 20001002 00217 CE 2000 10 2 CA000828006 1 20000815 G 5300 SKIN BEECH BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA LEFT WING CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 13697 BB14 (CAN) FUSELAGE SKIN CRACK IN PRESSURE VESSEL LOCATED AT WING TO FUSELAGE FILLET MOUNTING SCREW HOLE (ANCHOR NUT) AT LEFT HAND WING LEADING EDGE (APPROX 1.25 INCHES LONG). 1 L 7 2 4T 4 T A24CE E4EA 2001032700176 20010327 00176 CE 2001 3 27 CA000828007 1 20000804 G 7810 GASKET CESSNA 180 180A 2072604 CE CONT O470 O470R 17026 SO MCAULY 2A34C 2A34C66 GL EXHAUST STACK LEAKING W O OTHER B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA (CAN) CARBON MONOXIDE IN CABIN DUE TO LEAKING EXHAUST GASKETS 1 H 7 1 3O 3 O 5A6 E273 5 C P3EA 2000100200218 20001002 00218 SO 2000 10 2 CA000828008 1 20000802 G 3230 452383 ROD END BEARING PIPER 4194902 PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA BEARING SEIZED W O OTHER J R WARNING INDICATION PARTIAL RPM/PWR LOSS AP APPROACH 1 CA (CAN) PILOT REPORTED LEFTMAIN GEAR UNSAFE LIGHT WHEN GEAR WAS SELECTED DOWN. GEAR HANDLE WAS PUT IN THE DOWN POSITION A ND MASTER SWITCH SELECTED OFF TO MAINTAIN HYDRAULIC PRESSURE TO THE ACTUATOR, PREVENTING GEAR COLLAPSE. MAINTENANCE FOU ND THE DOWNLOCK LATCH NOT LOCKED. THE ROD END BEARING ON THE DOWNLOCK ROD WAS SEIZED PREVENTING THE LATCH FROM ENGAGING . BEARING WAS REPLACED, SYSTEM CLEANED, GEAR SWING COMPLETED SUCCESSFULLY. AIRCRAFT RETURNED TO SERVICE. 1 L 7 2 3O 3 O A20SO E14EA 2001032700178 20010327 00178 NM 2001 3 27 CA000829003 1 20000731 G 2910 LINE DHAV DHC8 DHC8101 2809002 NM PWA PW120 PW123 NE HYD SYSTEM FAILED W D RETURN TO BLOCK J WARNING INDICATION TO TAKEOFF 1 CA (CAN) AFTER PUSH BACK, AND AFTER START CHECKS COMPLETED (BOTH ENGINES IN FEATHER). WHEN PARK BRAKE RELEASED, AIRCRAFT MO VED FORWARD DESPITE CAPTAINS & CO-PILOT FOOTBRAKES APPLIED, EMERGENCY/PARK BRAKE APPLIED GENTLY TO STOP AIRCRAFT. AIRCRA FT THEN TOWED BACK TO STAND.ADDITIONAL INFO:ENGINEERS COMPLETED CHECKS & FOUND NO DEFECT WITH SYSTEM, ALL HYDRAULIC LEVE LS CHECKED & FUNCTION OF SYSTEM PROVED SATISFACTORY.ONE WEEK PREVIOUS THE HYDRAULIC ISOLATION MOD WAS COMPLETED WITH VAR IOUS HYDRAULIC PIPES REPLACED. 2 H 7 2 4T 4 T RT A13NM E20NE 2001032700179 20010327 00179 2001 3 27 CA000829004 4 20000731 G 2565 SLIDE DHAV DHC8 DHC8301 NM PWA PW120 PW123 NE LEFT DEPLOYED W O OTHER O OTHER CR CRUISE 1 CA (CAN) CABIN CREW INFORMED. FLIGHT CREW F USUAL NOISE IN VICINITY OF ROW 11, SUSPECT, LEFT HAND DITCHING DAM DEPLYMENT, V ISUALLY CONFIRMED BY THE CABIN CREW. FLIGHT CONTINUED TO DESTINATION AIRPORT AT REDUCED AIRSPEED 190 KTS. 26 MAY 2000 LE FT HAND DITCHING DAM REPLOYED IN FLIGHT. AIRSPEED SLOWED TO 160 KTS & FLIGHT CONTINUED TO MANCHESTER. 2 H 7 2 4T 4 T RT A13NM E20NE 2001032700180 20010327 00180 NM 2001 3 27 CA000829005 1 20000802 G 3260 DOWNLOCK SENSOR DHAV DHC8 DHC8* NM MLG OUT OF RIG W A UNSCHED LANDING N FALSE WARNING AP APPROACH 1 CA (CAN) ON FINAL APPROACH, FLT 650 AT APPROX 1830 HRS, FOLLOWING GEAR DOWN SELECTION, RT MLG UNSAFE INDICATION. GEAR CYCLE D 2 TIMES, RT MLG STILL UNSAFE. ALTERNATE EXTENSION CARRIED OUT WITH SAME INDICATION. ALTERNATE DOWNLOCK INDICATION SHOW ED THREE GREEN AFTER ALL GEAR DOWN SELECTIONS. AT APPOX. 17:15 HRS CET AN EMERGENCY LANDING WAS DECLARED AND THE AIRCRAF T LANDED WITHOUT INCIDENT.NOTE: TROUBLESHOOTING BY TECHNICIANS FOUND PRIMARY DOWNLOCK SENSOR OUT OF RIG. TOO FAR INDICAT ED ON PSEU. SENSOR RE-RIGGER AND PSEU CHECKED SERVICEABLE. CHECK / POSITIONING FLIGHT CARRIED OUT. NO FURTHER INCIDENTS. 2 H 7 2 4T RT A13NM 2001030600056 20010306 00056 NM 2001 3 6 CA000829006 1 20000802 G 2720 82710016003 SHAFT DHAV DHC8 DHC8103 1386005 NM RT RUDDER PEDAL BROKEN W D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 CA (CAN) AFFECTED PART RUDDER PEDAL SHAFT ASSY (WELDED) P/N 8270016-003. DURING BRAKING FOR FULL STOP ON TARMAC, R/H RUDDER PEDAL ASSEMBLY P/N 82710016-003 FAILED ON CAPTAINS PEDALS. INSPECTION REVEALED A BROKEN ARM ON THE RUDDER PEDAL SHAFT A SSY. DETAIL ISPECTION SHOWED THAT A CRACK IN THE WELD HAD PROPAGATED UNTIL TOTAL SEPARATION OF THE ARM FROM THE SHAFT. A PART OF THE WELD INDICATED THAT THIS CRACK STARTED A LONG TIME AGO SINCE HALF OF THE CRACK SURFACE LENGTH HAD EVIDENCE OF RUST. WE HAVE INITIATED A ONE TIME BORESCOPE INSPECTION ON ALL OUR A/C, WHICH WE EXPECT TO COMPLETE WITHIN AUGUST 10 . THIS ALSO IS REPORTED TO THE NORWEGIAN CAA. KARE PEDERSON (DIRECTOR ENG. DEPT.) 2 H 7 2 4T RT A13NM 2001011105313 20010111 05313 NM 2001 1 11 CA000829007 1 20000802 G 2730 MS276434 BEARING DHAV DHC8 DHC8301 NM PWA PW120 PW123 NE RT ELEVATOR WORN W O OTHER O OTHER AP APPROACH 1 CA (CAN) ON APPROACH INTO BRISTOL PILOT REPORTED LOOSE & FLOPPY ELEVATOR CONTROL.NOTE: ELEVATOR TENSION CARRIED OUT AND RIG CHECK. INSPECTION OF ELEVATORS REVEALED INPUT LEVER BEARINGS WORN. BEARINGS REPLACED AND FUNCTIONS COMPLETED SATISFACTO RY. 2 H 7 2 4T 4 T RT A13NM E20NE 2001030600057 20010306 00057 NM 2001 3 6 CA000829008 1 20000802 G 5610 85C0043012 WINDSHIELD DHAV DHC8 DHC8301 NM PWA PW120 PW123 NE COCKPIT FAILED W B EMER. DESCENT O OTHER CL CLIMB 1 CA 963439H4741 (CAN) BW1A AIRCRAFT MSN-489, LANDED WITH THE FIRST OFFICERS WINDSHIELD SHATTERED. INFORMATION FROM JOURNEY LOG: CLIMBING OUT OF 17,500 FT, RIGHT WINDSHIELD (OUTER GLASS) SHATTERED WITH LOUD BANG. AIRCRAFT WAS DESCENDED TO 10,000 PLUS PROCED URES CARRIED OUT. AT TIME OF DAMAGE, WX WAS GOOD, CABIN DIFF.5.O, NO ABNORMAL INDICATIONS. MC VERBALLY REPORTED THAT CRE W DECLARED AN EMERGENCY LANDING.FSR WAS CALLED TO ASSIST IN REPLACEMENT OF WINDSCREEN. THE FIRST OFFICERS WINDSHIELD SHO WS FOD DAMAGE IN THE FORM OF A CHIP IN THE WINDSHIELD. SUSPECT PRESSURIZATION AND W/S CYCLING CAUSED W/S TO SHATTER. 2 H 7 2 4T 4 T RT A13NM E20NE 2001030600058 20010306 00058 NE 2001 3 6 CA000829009 2 20000804 G 7310 3036484 FUEL LINE PWA PWC123 DHAV DHC8 DHC8301 NM PWA PW120 PW123 NE NR 2 ENGINE LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA PCEAR0014 (CAN) FSR WAS CALLED INTO ASSIST. BW1A MAINTENANCE CONTROL ON AOG WITH AIRCRAFT 9Y-WIN, WITH A LEAKING FUEL LINE ON THE NR2 ENGINE. THE AIRCRAFT WAS IN BARBADOS WITH NO PARTS. PRELIMINARY REPORTS WAS THE LINE FROM THE FUEL COOLED OIL COOLER HAS PIN HOLE, LEAKING FUEL ON GROUND. (REFERENCE PWC IPC 72-01-40 FIG 3, PG2 ITEM 80.)REPLACEMENT. LINE WAS LOANED TO B W1A FROM ALM, THE LINE INSTALED AND WIRE HARNESS CORRECTLY RE-INSTALLED, ADEL CLAMPS WERE ADJUSTED BY MAINTENANCE IN BGI .INVESTIGATION BY FSR, SHOWS A PIN HOLE WHICH LOOKS LIKE IT WAS CAUSED BY ARCING OR THE WIRE HARNESS ON THE FUEL LINE EX ITING THE FUEL COOLED OIL COVER TO THE FLOW DIVIDER. CAW:SB BEING DEVELOPED - CF AD PENDING SEPT 2000. 2 H 7 2 4T 4 T RT A13NM E20NE 2001030600059 20010306 00059 NM 2001 3 6 CA000829010 1 20000803 G 5753 6521630188 SKIN BOEING 727 72722C 138400F NM PWA JT8 JT8D7B 52053 NE ALLSN A6441 A6441FN606 GL RT FORE FLAP SEPARATED W K NONE F FLT CONT AFFECTED NR NOT REPORTED 1 CA BN62 (CAN) CREW REPORTED ABNORMAL AILERON CORRECTION REQUIRED AT FLAPS 15 OR GREATER INBOUND TO YQM. ON INSPECTION IT WAS FOU ND THAT THE RIGHT HAND FORWARD INBD FORE FLAP HAD SPLIT OPEN AT THE SPAR. THE FLAP WAS REPLACED AND AIRCRAFT RELEASED. U PON INSPECTION OF FLAP IN SHOP, IT WOULD APPEAR THAT THE AFT HONEYCOMB SECTION HAS SEPARATED FROM THE SPAR DUE TO DISBON DING OF THE JOINT. FURTHER INVESTIGATION REVEALS THAT THE SPAR WAS NOT PROTECTED BY PRIMER AND THE BONDING WAS SPORADIC PERHAPS ONLY 20-30% OF THE WHOLE LENGTH OF THE FLAP. 2 L 7 3 4F 4 F A3WE E2EA 6 C P898 2001030600060 20010306 00060 CE 2001 3 6 CA000829011 1 20000810 G 3230 404188446 DRAG BRACE BEECH 18 E18S9700 1151008 CE PWA R985 R985AN14B 52008 NE LT MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 13781 (CAN) DURING ROUTINE 100 HOUR INSPECTION OF AIRCRAFT THE L/H MAIN GEAR DRAG BRACE WAS FOUND TO BE CRACKED PERPENDICULAR TO THE TUBE JUST ABOVE THE LOWER ATTACH POINT, ACROSS THE WELD. THE DRAG BRACE WAS REMOVED AND A SERVICEABLE UNIT WAS IN STALLED WITH MULTIPLE GEAR SWINGS PERFORMED. SERVICEABLE. 1 L 7 2 3R 3 R A765 5E1 2001030600061 20010306 00061 SW 2001 3 6 CA000829012 1 20000721 G 5753 21583 MOUNT BBAVIA 8GCBC BBAVIA 8 8GCBC 1220803 SW LYC O360 O360C2E 41514 EA LT FLAP CRACKED W K NONE F FLT CONT AFFECTED DE DESCENT 1 CA 2334 27278 (CAN) PILOT REPORTED A TENDENCY FOR A/C TO ROLL TO RIGHT, ON FULL FLAP SELECTION. VISUAL INSPECTION INDICATED L/H INBOAR D FLAP MOUNT HAD CONSIDERABLE VERTICAL MOVEMENT. FURTHER INSPECTION REVEALED THAT INBOARD FLAP MOUNT LOWER ATTACHMENT PO INT HAD BROKEN FREE. 1 H 7 1 3O 3 O A21CE E286 2001011105326 20010111 05326 EA 2001 1 11 CA000829013 1 20000817 G 3244 256K433 TIRE 6008512315R CNDAIR CL601 CL6012A12 1900303 EA MLG BULGED W K NONE O OTHER IN INSP/MAINT 1 CA AVG82470 (CAN) TIRE HAS BULGES ON RADIUS OF TIRE. THE TREAD IS DELAMINATING AND LETTING AIR COLLECT BETWEEN LAYERS CAUSING BULGES AND SOFT SPOTS. 2 L 7 2 4F RT A21AE 2001030100076 20010301 00076 CE 2001 3 1 CA000829014 1 20000808 G 5520 1156200219 HINGE BEECH BEECH 100 100BEECH 1152916 CE PWA PT6 PT6A28 EA ELEVATOR BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 19788 B8 (CAN) DURING PRE-FLIGHT INSPECTION GROUND CREW HEARD A NOISE WHEN ELEVATOR MOVED, INVESTIGATION REVEALED R/H OUTBOARD HI NGE BROKEN AT INSIDE STABILIZER. AIRCRAFT GROUNDED. HINGE REPLACED. 1 L 7 2 3T 4 T A14CE E4EA 2001030600062 20010306 00062 EA 2001 3 6 CA000829015 1 20000817 G 2700 7X19 CONTROL CABLE C3CF1975R DHAV DHC3 DHC3 2800202 EA PWA PT6 PT6A34 52043 EA FLIGHT CONTROLS FRAYED W K NONE O OTHER IN INSP/MAINT 1 CA 302 (CAN) WHILST CARRYING OUT AN 800 HOUR INSPECTION OF THE AIRCRAFT, SEVERAL CABLES WERE FOUND THAT HAD A QUANTITY OF BROKE N STRANDS BEYOND THE ALLOWABLE LIMITS. THIS IS ONE OF TH CABLES THAT WAS FOUND. IT SHOULD BE NOTED THAT THE AIRCRAFT MAN UAL STATES THAT THE CABLES MUST BE INSPECTED THROUGHOUT THEIR ENTIRE LENGTH. IN ORDER FOR THIS TO BE ACCOMPLISHED, THE C ABLES MUST BE REMOVED FROM THE AIRCRAFT. IT SHOULD BE NOTED THAT THESE DEFECTIVE CABLES WOULD NOT HAVE BEEN FOUND BY INS PECTING THE CABLES WHILE STILL INSTALLED ON THE AIRCRAFT. 1 H 7 1 3R 4 T A815 E4EA 2001030600063 20010306 00063 EA 2001 3 6 CA000829016 1 20000817 G 2700 7X19 CONTROL CABLE DHAV DHC3 DHC3 2800202 EA PWA PT6 PT6A34 52043 EA FLIGHT CONTROLS FRAYED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHILST P/N C3CF195-7 AND P/N C3CF199-5. WHILST CARRYING OUT AN 800 HOUR INSPECTION OF THE AIRCRAFT, SEVERAL CABLES WERE FOUND THAT HAD A QUANTITY OF BROKEN STRANDS BEYOND THE ALLOWABLE LIMITS. THESE ARE TWO OF THE CABLES. IT SHOULD BE NOTED THAT THE AIRCRAFT MANUAL STATES THAT THE CABLES MUST BE INSPECTD THROUGHOUT THEIR ENTIRE LENGTH. IN ORDER FOR THI S TO BE ACCOMPLISHED, THE CABLES MUST BE REMOVED FROM THE AIRCRAFT. IT SHOULD BE NOTED THAT THESE DEFECTIVE CABLES WOULD NOT HAVE BEEN FOUND BY INSPECTING THE CABLES WHILE STILL INSTALLED ON THE AIRCRAFT. 1 H 7 1 3R 4 T A815 E4EA 2001030600064 20010306 00064 EA 2001 3 6 CA000829017 1 20000817 G 2700 7X19 CONTROL CABLE C3CF1935 DHAV DHC3 DHC3 2800202 EA PWA PT6 PT6A34 52043 EA FLIGHT CONTROLS FRAYED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHILST CARRYING OUT AN 800 HOUR INSPECTION OF THE AIRCRAFT, SEVERAL CABLES WERE FOUND WHICH HAD A QUANTITY OF BROK EN STRANDS BEYOND THE ALLOWABLE LIMITS. THIS IS ONE OF THE CABLES THAT WAS FOUND. IT SHOULD BE NOTED THAT THE AIRCRAFT M ANUAL STATES THAT THE CABLES MUST BE INSPECTED THROUGHOUT THEIR ENTIRE LENGTH. IN ORDER FOR THIS TO BE ACCOMPLISHED, THE CABLES MUST BE REMOVED FROM THE AIRCRAFT. IT SHOULD BE NOTED THAT THESE DEFECTIVE CABLES WOULD NOT HAVE BEEN FOUND BY I NSPECTING THE CABLES WHILE STILL INSTALLED ON THE AIRCRAFT. 1 H 7 1 3R 4 T A815 E4EA 2001030600065 20010306 00065 EA 2001 3 6 CA000829018 1 20000820 G 2700 SCREW C3TE1213 DHAV DHC3 DHC3 2800202 EA PWA PT6 PT6A135 52043 NE SERVO TAB LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) NOT AN SDR - WHILST CARRYING OUT A 100 HOUR INSPECTION, THE ENGINEER NOTICED THAT THE SCREWS ATTACHING THE COUNTER WEIGHT ARM TO THE SERVO TAB WERE LOOSE. THE TRIM TAB WAS OPENED UP, THE SCREWS WERE TIGHTENED, THE TAB WAS CLOSED UP AND THE AIRCRAFT WAS RETURNED TO SERVICE. 1 H 7 1 3R 4 T A815 E4EA 2001030600066 20010306 00066 EA 2001 3 6 CA000829019 1 20000820 G 2731 ROD END DHAV C3CF4195 DHAV DHC3 DHC3 2800202 EA PWA PT6 PT6A135 52043 NE ELEVATOR TAB WRONG PART W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) WHEN CARRYING OUT A 100 HOUR INSPECTION, THE ENGINEER NOTICED THAT THE ROD END BEARING ON THE ELEVATOR TRIM TAB RO D LOOKED UNUSUAL. UPON FURTHER INVETIGATION, THE ENGINEER NOTED THAT IT WAS UNLIKE ANY OTHER HE HAD EVER SEEN!THE PART O F UNKNOWN ORIGIN WAS REPLACED WITH THE PROPER ROD END - P/N M34-14. 1 H 7 1 3R 4 T A815 E4EA 2001030200062 20010302 00062 WP 2001 3 2 CA000830010 1 20000731 G 3244 32700821 TIRE DOUG DC9 DC932 3022066 WP PWA JT8 JT8D7 52053 NE LT MLG BLOWN W C ABORTED TAKEOFF C Y F.O.D. ENGINE STOPPAGE TO TAKEOFF 1 CA (CAN) AIRCRAFT REJECTED TAKEOFF DUE TO LT ENGINE POWER LOSS (125-130 KNOTS). NR 2 MAIN TIRE BLOWN, TIRE SEPARATION, DEBR IS OF TIRE FLEW INTO LT ENGINE CAUSING DAMAGE, THE DEBRIS ALSO DAMAGED THE LT INBOARD FLAP. REPLACED ALL FOUR MAIN TIRE AND FOUR MAIN BRAKES. REPAIR FLAP AS PER ENGINEERING PRODUCTION PERMIT 7-57-50/351-57-854.REPLACED LT FAN BLADES AND HUB , LEAK AND OPERATIONAL CHECK CARRIED OUT (VIB CHECK, CONDITIONAL CHECKS) ALL CHECKS FOUND SATISFACTORY.NOTE: GOODYEAR WA S ADVISE. 2 L 7 2 4F 4 F A6WE E2EA 2001030700657 20010307 00657 NM 2001 3 7 CA000830011 1 20000716 G 2121 732591A FAN BOEING 767 767233 NM PWA JT9 JT9D7R4D 52054 NE E&E BAY FAILED W K NONE B J SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION IN INSP/MAINT 1 CA (CAN) SMOKE IN COCKPIT IN FLIGHT WHILE EXITING AN INBOUND HOLD. AFTER INVESTIGATION, AN AFTER SMOKE DISSIPATED AN EICAS (ENGINE INDICATION AND CREW ALERT SYSTEM) MESSAGE APPEARED FOR A TRIPPED OFF LINEOF THE FORWARD ELECTRICAL SUPPLY FAN. R EPLACED AIR COOLING FAN AND REPLACED ELECTRICAL/ELECTRONICS EQUIPMENT COOLING SYSTEM 9 INCH DIAMETER AIR CHECK VALVE THA T WAS FOUND BROKEN. FAN SYSTEM OPERATIONAL AND MESSAGE CLEARED. 2 L 7 2 4F 4 F RT A1NM E3NE 2001030700658 20010307 00658 NM 2001 3 7 CA000830012 1 20000727 G 2920 729550014 CAP BOEING 767 767275 1385155 NM PWA JT9 JT9D7R4D 52054 NE RAM AIR TURBINE SHEARED W O OTHER K J FLUID LOSS WARNING INDICATION AP APPROACH 1 CA (CAN) CENTRE HYDRAULIC QUANTITY WENT TO 0 AFTER FLAP SELECTION 1, ON FINAL APPROACH. QRH APPLIED, AIRCRAFT LANDED SAFELY . AFTER INVESTIGATION, FOUND TH RAT CHECK OUT MODULE (RAM AIR TURBINE) CHECK VALVE CAP SHEARED (CAP COMPLETELY SEPARATED FROM THE REST OF THE HOUSING).REPLACED RAT UNIT CHECK OUT MODULE, AS PER BOEING TASK 29-21-11-004-042 OPERATIONAL CHECK CARRIED OUT, FOUND SERVICEABLE. 2 L 7 2 4F 4 F RT A1NM E3NE 2001030700659 20010307 00659 CE 2001 3 7 CA000830015 1 20000804 G 5730 RIVET BEECH 96110005703 BEECH 55 E55 1152732 CE CONT O520 IO520CB 17032 SO WING LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA 8386 TE1197 (CAN) DURING SCHEDULED MAINTENANCE ON THE AIRCRAFT WE HAVE FOUND LOOSE RIVETS ON THE WING SKIN LOWER MAIN PANEL AFT OF T HE SPAR AT WING STA 70-00 TO STA 76-00. AFTER A CONTACT WITH A TECH REP AT BEECH AIRCRAFT, WE HAVE REPLACED THE LOOSE RI VETS WITH STANDARD MS20470AD-5 SOLID RIVETS DIPPED IN WET ZINCHROMATE PRIMER AS REQUIRED IN BEECH REPAIRS MANUAL AND REC OMMENDED BY BEECH TECH REP. 1 L 7 2 3O 3 O 3A16 E5CE 2001030700660 20010307 00660 NM 2001 3 7 CA000830016 1 20000807 G 5230 DOOR SEAL BOEING 757 75728A 1384976 NM RROYCE RB211 RB211535E437 54555 NE CARGO DOOR OBSTRUCTED W A UNSCHED LANDING O OTHER CR CRUISE 1 CA (CAN) AIRCRAFT RETURNED TO BASE AFTER NOT BEING ABLE TO MAINTAIN CABIN PRESSURIZATION ABOVE 23,000 FEET,. DURING GRD PRE SSURIZATION CHECK FOUND HEAVY AIR LEAK FROM L/H PRSOV AND C1 CARGO. C1 CARGO FOUND NET OVER CARGO DOOR SEAL, NET REPOSIT IONED. PRSOV LOCKED IN THE CLOSED POSITION PER MEL 21-31-00. GROUND PRESSURIZATION TEST ACCOMPLISHED IN ACCORDANCE WITH AMM 21-31-00, AIRCRAFT RELEASED. 2 L 7 2 4F 4 F RT A2NM E12EU 2001030700661 20010307 00661 NM 2001 3 7 CA000830017 1 20000805 G 7830 52754031 CABLE RROYCE RB211535E4 BOEING 757 75728A 1384976 NM RROYCE RB211 RB211535E437 54555 NE THRUST REVERSER DAMAGED W K NONE O OTHER LD LANDING 1 CA 30739 (CAN) LOG BOOK DEFECT REPORTED BY FLIGHT CREW ON ARRIVAL . NR2 ENGINE THROTTLE BINDING. FOUND THRUST REVERSER FEEDBACK P USH PULL CABLE DAMAGED CAUSING THE T/R FEEDBACK CAM TO BEND. FORWARD THRUST FEED AND SENSE C/O, NO FAULT FOUND, T/R LOCK ED OUT AS PER MEL. 2 L 7 2 4F 4 F RT A2NM E12EU 2001030200065 20010302 00065 EA 2001 3 2 CA000830018 1 20000801 G 2913 NAS1611008 PACKING VICKERS PV304448 CNDAIR CL600 CL6002B19 EA HYDRAULIC PUMP LEAKING W A UNSCHED LANDING K FLUID LOSS CR CRUISE 1 CA MX590791A (CAN) CREW REPORTED HYDRAULIC LEVEL SYSTEM NR1 AT 30% AT TOP OF CLIMB. DROPPED TO 25% 3 MINUTES LATER. MAINTENANCE FOUND LEAK FROM HYDRAULIC PUMP. THEY REPLACED THE PACKING. 2 L 7 2 4F RT A21EA 2001030200066 20010302 00066 NE 2001 3 2 CA000830019 2 20000815 G 7200 ENGINE GE CF343B1 CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE LT ENGINE MALFUNCTIONED W O OTHER J WARNING INDICATION CL CLIMB 1 CA (CAN) AFTER TAKEOFF, WITH TAKEOFF POWER APPLIED, THE CREW HEARD A LOUD BANG. AFTER THE NOISE, THE LT ENGINE ITT & N2 WEN T INTO THE RED. PILOT SET ENGINE TO IDLE AND OPERATION WAS NORMAL AT IDLE. PILOTS WERE THEN UNABLE TO INCREASE THRUST, E NGINE WOULD NOT RESPOND TO THROTTLE SETTING. THE MDC REVEALED AN ITT OF 1147 DEGREES C FOR 7.4 SECONDS AND N2 OF 102.5% FOR 2.3 SECONDS. THE LT ENGINE HAS BEEN REPLACED. 2 L 7 2 4F 4 F RT A21EA E15NE 2001030700664 20010307 00664 EA 2001 3 7 CA000830020 1 20000815 G 2760 PCU CNDAIR CL600 CL6002B19 EA SPOILER SYSTEM OUT OF RIG W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA (CAN) ABORTED TAKEOFF AT ABOUT 135 KTS DUE TO A CONFIG SPOILER WARNING MESSAGE. ON ALL FOUR BRAKES, NOT MORE THAN 5 UNIT S INDICATED.THE SECU #1 WAS REPLACED AND THE NEXT DAY AFTER THE REOCCURRENCE OF THE SAME PROBLEM, THE R/H INBOARD SPOILE RON PCU WAS RERIGGED. 2 L 7 2 4F RT A21EA 2001030700665 20010307 00665 EA 2001 3 7 CA000830021 1 20000815 G 3234 750006000 SELECTOR VALVE CNDAIR CL600 CL6002B19 EA NLG LEAKING W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CL CLIMB 1 CA 652 (CAN) AFTER TAKEOFF, THE GEAR DID NOT COME UP AFTER SELECTION.NOSE LANDING GEAR SELECTOR VALVE REPLACED DUE OF EVIDENCE OF A LEAK. 2 L 7 2 4F RT A21EA 2001030200067 20010302 00067 EA 2001 3 2 CA000830022 1 20000801 G 4900 APU CNDAIR CL600 CL6002B19 EA APU FAILED W A UNSCHED LANDING B J SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CR CRUISE 1 CA (CAN) THE SMOKE TOILET CAUTION MESSAGE DISPLAYED DURING FLIGHT, ACCOMPANIED WITH SMOKE ODOR AND HAZE IN THE CABIN.INITIA L REPORT FOUND NO DISCREPANCY, SECOND REPORT RESULTED INTO AN APU REPLACEMENT. 2 L 7 2 4F RT A21EA 2001030200068 20010302 00068 EA 2001 3 2 CA000830023 1 20000815 G 4900 38004883 APU CNDAIR CL600 CL6002B19 EA APU BAY FAILED W O OTHER B SMOKE/FUMES/ODORS/SPARKS DE DESCENT 1 CA P177 (CAN) THE FLIGHT CREW REPORTED THE SMOKE JUST PRIOR TO LANDING, SMOKE ODOR DETECTED, WHEN THE AIR CONDITIONING PACKS WER E TRANSFERRED FROM THE ENGINE TO THE APU PROCEEDED TO DESTINATION AIRPORT (CVG) DECLARED EMERGENCY. THE APU WAS REPLACED . 2 L 7 2 4F RT A21EA 2001030700666 20010307 00666 2001 3 7 CA000830024 4 20000801 G 3418 45150340 VANE CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE LT AOA FAILED W C ABORTED TAKEOFF N FALSE WARNING TO TAKEOFF 1 CA (CAN) THE FLIGHT CREW ABORTED THE TAKEOFF WHEN THE STALL FAIL CAUTION MESSAGE APPEARED AT 70 TO 80 KNOTS. (ABORTED T/O). THE LEFT AOA VANE WAS REPLACED AND THE AIRCRAFT RETURNED IN SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001030700667 20010307 00667 EA 2001 3 7 CA000830025 1 20000823 G 5210 HANDLE CNDAIR CL6002B19 CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE PAX DOOR OUT OF RIG W K NONE O OTHER IN INSP/MAINT 1 CA 7127 (CAN) MAIN PAX DOOR HANDLE WAS STUCK. DOOR WILL NOT OPEN FROM INSIDE OR OUTSIDE.PAX DOOR RIGGED AS PER AMM 52-11-02-820- 801 AND SL 52-010. 2 L 7 2 4F 4 F RT A21EA E15NE 2001030200069 20010302 00069 NE 2001 3 2 CA000830026 2 20000821 G 7200 ENGINE CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE RIGHT MALFUNCTIONED W A UNSCHED LANDING O OTHER CL CLIMB 1 CA (CAN) AFTER TAKEOFF, THE RIGHT ENGINE OIL PRESSURE WAS FLUCTUATING RAPIDLY 55-42 PSI. THE PILOT DECLARED EMERGENCY, THE LANDING WAS UNEVENTFUL. MAINTENANCE CONTROL REPLACED THE RT ENGINE (THE EXACT CAUSE IS NOT KNOWN) (S/N OFF: 807100/S/N O N: 807432). 2 L 7 2 4F 4 F RT A21EA E15NE 2001030700668 20010307 00668 EA 2001 3 7 CA000830027 1 20000821 G 3231 555405 SELECTOR VALVE CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE NLG DOOR FAILED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) AFTER TAKEOFF, WHEN SELECTING THE LANDING GEAR UP, THE NOSE DOOR OPEN WARNING APPEARED. MAINTENANCE REPLACED THE N OSE GEAR DOOR SELECTOR VALVE (P/N:55540-5, S/N OFF: 1131/S/N ON: 1197) AND THE PROX. SENSOR P/N: 8-648-07 & P/N: 8-648-0 8. 2 L 7 2 4F 4 F RT A21EA E15NE 2001030200070 20010302 00070 EA 2001 3 2 CA000830028 1 20000820 G 5610 1393216 WINDSHIELD CNDAIR CL600 CL6002B19 EA COCKPIT CRACKED W O OTHER O OTHER CR CRUISE 1 CA 00036H9096 (CAN) DURING FLIGHT THE RT WINDSHIELD MIDDLE PLY CRACKS. THE AIRCRAFT LANDED WITHOUT ANY FURTHER COMPLICATION. 2 L 7 2 4F RT A21EA 2001030200071 20010302 00071 EA 2001 3 2 CA000830029 1 20000820 G 2710 6224404101 AILERON CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE RIGHT JAMMED W O OTHER F FLT CONT AFFECTED CL CLIMB 1 CA 459 (CAN) THE FLIGHT CREW REPORTED AFTER TAKEOFF THE RIGHT AILERON APPEARS TO BE JAMMED. ON DESCENT, THE AILERON CAME UN-JAM MED AND APPEARED TO BE NORMAL.AILERON SERVO REPLACED AS PRE-CAUTIONARY MEASURE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001030700669 20010307 00669 EA 2001 3 7 CA000830030 1 20000811 G 3234 601R509677 CONTROL HANDLE CNDAIR CL600 CL6002B19 EA COCKPIT BROKEN W A UNSCHED LANDING O OTHER CL CLIMB 1 CA 652 0018A (CAN) AFTER TAKEOFF, UPON A GEAR RETRACTION, THE LANDING GEAR HANDLES SHAFT BROKE. AIRCRAFT RETURNED TO BASE AND LANDED SUCCESSFULLY. 2 L 7 2 4F RT A21EA 2000101200172 20001012 00172 SO 2000 10 12 CA000830032 2 20000805 G 8530 TCK654970K CYLINDER CESSNA 172 172 2072402 CE CONT O360 IO360K 17025 SO FRT RT NR 5 POS BROKEN W A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CR CRUISE 1 CA 1030 355597 (CAN) AMERICAN PRIVATE OWNED AIRCRAFT TOURING GASPE REGN. TAKEOFF FROM STE .ANNE DES MONTS. 20 MILES OUT-WEST, ENGINE WENT ROUGH AND RISE IN CHT. DATE: 25 JUL 2000. TIME: 02 HR.25. PILOT PURCHED GPS INDICATING STE.ANNE AS NEAREST AIR PORT AND ADVISED FSSYZV (SERT-ILES) OF PROBLEM. NR 5 CYLINDER HEAD BROKEN OFF AT BOTH ROCKER HOUSING. NOTE: PILOT HAD STOPPED ON WAY IN, AT GRANDFALLS, NB WITH OIL LEAK, ASSUMED TO BE FROM ROCKER COVER. RESEALED. BROKEN PORTION OF CYLIN DER INDICATE PREVIOUS CRACKS. NOTE: A/C HAD LAST MONTH FLOWN WITH COWL PLUGS ON FOR 50 MILES. (X) 1 H 7 1 3O 3 O NT 3A12 E1CE 2001030700671 20010307 00671 SO 2001 3 7 CA000830034 2 20000801 G 8530 633106 LIFTER CONT TSIO360GB MOONEY M20 M20K 5870220 SW CONT O360 TSIO360GB 17025 SO NR 6 CYLINDER DAMAGED W A UNSCHED LANDING O OTHER CR CRUISE 1 CA 1752 309457 (CAN) ENGINE KNOCKING IN FLIGHT. AIRCRAFT LANDED. VALVE ROCKER SHAFT STUDS FOUND BROKEN NR6 EXHAUST. PUSH ROD FOUND DAMA GED ON EXHAUST SIDE. INTAKE PUSH ROD ALSO FOUND DAMAGED. CYLINDER REMOVED FOR INSPECTION & REPAIR. INTAKE LIFTER FOUND D AMAGED BUT COMPLETE. EXHAUST LIFTER FOUND DAMAGED AND MISSING SPRING.CYLINDER REPAIRED BY ENGINE SHOP., PUSH ROD REPLACE D, LIFTERS REPLACED AND RUN-UP CARRIED OUT.CYLINDER NR6 TTSN: 80:55 HOURS; CYLINDER NR6 WAS INSTALLED NEW AT AFTT:1671 H OURS. 1 L 7 1 3O 3 O 2A3 E9CE 2001030700672 20010307 00672 2001 3 7 CA000830035 4 20000608 G 3416 GH3000 ALTIMETER CNDAIR CL601 CL6013A 8070802 EA INSTRUMENT PNL FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) THIS UNIT WAS INSTALLED AS PART OF LSTC Q-LSA-5020. ITEM REPORTED BY OPERATOR, RDAF (DANISH AIRFORCE). NO FURTHER DETAILS SUPPLIED. INFORMATION ON THIS UNSERVICEABILITY WAS RECEIVED ON 8 JUNE 2000 FROM OUR PROGRAMS DIVISION AS A RESUL T OF A WARRANTY CLAIM BY RDAF WITH EQUIPMENT VENDOR. SINCE THE A/C IS REGISTERED AND OPERATED BY A NON-CIVIL OPERATOR (R DAF), WE BELIEVED IT DID NOT REQUIRE AN SDR TO TC UNTIL WE QUESTIONED TC AND WERE ADVISED 4 AUG 2000 THAT IT SHOULD BE R EPORTED.THE EQUIPMENT VENDOR (GOODRICH) ADVISED THEY COULD NOT REPRODUCE FAULT AND THEY BELIEVED A SOFTWARE UPGRADE MAY SOLVE PROBLEM. WE ARE UNAWARE WHAT HAS HAPPENED SINCE. 2 L 7 2 4F RT A21EA 2001030700673 20010307 00673 NM 2001 3 7 CA000830036 1 20000727 G 2910 65468581103 HYDRAULIC LINE BOEING 737 737242C 1384478 NM PWA JT8 JT8D9A 52048 NE RT ENGINE RUPTURED W O OTHER K J FLUID LOSS WARNING INDICATION DE DESCENT 1 CA (CAN) LOSS OF HYDRAULIC FLUID DURING DESCENT AND LANDING. NR2 ENGINE THRUST REVERSER PRESSURE LINE WAS FOUND RUPTURED I N PYLON UNDER A SUPPORT CLAMP.HYDRAULIC PUMP AND FILTER WERE CHECKED FOR CONTAMINATION AND FOUND SERVICEABLE. HYDRAULIC LINE REPLACED AS PER M.M. CAMPAIGN ON FLEET CARRIED OUT AND AN REPETITIVE INSPECTION AT 2B CHECK IS ESTABLISHED. 2 L 7 2 4F 4 F A16WE E2EA 2001030700676 20010307 00676 NM 2001 3 7 CA000830040 1 20000809 G 2410 CONNECTOR BOEING 737 737242C 1384478 NM PWA JT8 JT8D9A 52048 NE CSD CONTAMINATED W D RETURN TO BLOCK N FALSE WARNING TX TAXI/GRND HDL 1 CA (CAN) NR1 CSD IN TEMP ROSE TOWARDS 160 DEGREES WITH POWERED UP TO 80% TAKEOFF. FOUND MAIN CONNECTOR AT RIGHT SIDE OF CS D CONTAMINATED WITH OIL. THE CONNECTOR WAS CLEANED AND ENGINE GROUND RUN CARRIED OUT. SYSTEM CHECK SERVICEABLE. NO FUTHE R ABNORMALITIES REPORTED. 2 L 7 2 4F 4 F A16WE E2EA 2001030200072 20010302 00072 GL 2001 3 2 CA000830042 3 20000724 G 6114 HUB MCAULY D2A34C58 CESSNA 206 U206D 2073342 CE CONT O520 IO520F 17032 SO MCAULY 2A34C D2A34C58 GL PROPELLER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 1269 533 797406 (CAN) CRACK IN RETENTION THREAD. SEE MCCAULEY SB # 205B 1 H 7 1 3O 3 O A4CE E5CE 5 C P3EA 2001030200074 20010302 00074 SW 2001 3 2 CA000830044 1 20000808 G 2911 EA1563 ACCUMULATOR OZONE GULSTM 690TP 695A 7630519 SW GARRTT TPE331 TPE33110 01514 WP ROTOL R306 R306382F7 GL HYDRAULIC SYSTEM FAILED W A D UNSCHED LANDING RETURN TO BLOCK O OTHER DE DESCENT 1 CA 3 041200X (CAN) 1.A/C JUST COMPLETED ROUTINE 100 HR PERIODIC INSP. 2. HYDRAULIC ACCUMULATOR REGULATOR ASSY REPL, DUE TO LEAKING AC CUMULATOR (INTERNAL). IT WOULD NOT STORE FLUID PRESSURE: O HR T.S.O. PART INST FUNCTION TESTS & P OST INSP CHECK FLT CAR RIED OUT NO FAULT FOUND. 3. ON ROUTINE FLT TO BANGOR CREW SELECTED GEAR DOWN, HYDRAULIC SYS PRESSUE DROPPED TO ZERO. GEA R EMERG EXTENSION PROCS WERE APPLIED, GEAR LOCKED DOWN&A/C RETURNED TO BASE (SAINT JOHN). A/CLANDED & TAXIED TO HANGAR. ELECTRO-PUMP - BACKUP WORKED NORMAL FOR BRAKES & STEERING. NO HYD FLOW LIGHTS WERE ON. HYD PUMPS WORKINGOK. NO FLUID L OSS OR EXTERNAL LEAKAGE EVIDENT.4. GROUND TESTS INDICATE FLUID BYPASSING WITHIN ACCUM 1 H 7 2 4T 4 T 2A4 E4WE 6 C P8EU 2001030200077 20010302 00077 NM 2001 3 2 CA000901003 1 20000822 G 6120 3612001 ACTUATOR DHAV DHC8 DHC8301 NM PWA PW120 PW123 NE HAMSTD 14SF 14SF15 NE RT PROPELLER LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 8501 960518 (CAN) TIME SINCE REPAIR 4379. RIGHT PROP LEAKING OIL. RT PROP ACTUATOR REPLACED AND AIRCRAFT RETURNED TO SERVICE. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001030200081 20010302 00081 2001 3 2 CA000901007 4 20000815 G 3425 5222782004 INDICATOR BOEING 737 737275 1384485 NM PWA JT8 JT8D9A 52048 NE COCKPIT FAILED W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA 36822 7730 (CAN) IN CRUISE CAPTAINS HORIZONTAL SITUATION INDICATOR STOPPED TURNING WHEN AIRCRAFT WAS IN A TURN. COMPARATOR LIGHT CA ME ON. RETURNED. CAPTAINS HSI REPLACED. 2 L 7 2 4F 4 F A16WE E2EA 2001030200082 20010302 00082 CE 2001 3 2 CA000901008 1 20000825 G 2820 050011874 FUEL LINE CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA MCAULY 1C160 1C160DTM GL FUEL SYSTEM CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA 5564 (CAN) FUEL LINE LOCATED BETWEEN THE FUEL SELECTOR VALVE AND FUEL STRAINER & PASSES UNDER THE CO-PILOTS RUDDER PEDALS. TH E RUDDER PEDALS MOVE THE STEERING ROD RUBBED AGAINST THE FUEL LINE. THE FUEL LINE WAS RUBBED MORE THAN HALF THROUGH. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2000092100508 20000921 00508 SO 2000 9 21 CA000901012 1 20000802 G 8120 4066109020 TURBOCHARGER HONEYWELL PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2B 41532 EA EXH BLDE LET GO FAILED W E ENGINE SHUTDOWN O OTHER CR CRUISE 1 CA 2B005672 (CAN) CLIMBING THROUGH 16,000 FEET, RIGHT ENGINE SHUTDOWN. GOING THROUGH 10,000 FEET, ENGINE RESTARTED AND PARTIAL POWE R WAS AVAILABLE. (X) 1 L 7 2 3O 3 O A20SO E14EA 2000092100509 20000921 00509 EA 2000 9 21 CA000901013 2 20000714 G 8530 AEL19001 VALVE AEL651024 PIPER PA28 PA28140 7102802 SO LYC O320 O320E2A 41508 EA VALVE TIP FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 102 7558303H (CAN) ENGINE WAS SHOWING SIGNS OF METAL IN OIL FILTER. ENGINE DISMANTLED TO FIND CAUSE OF METAL. ONE EXHAUST VALVE FOU ND TO BE PROTRUDING FROM CYLINDER FARTHER THAN USUAL. EXHAUST VALVE REMOVED AND FOUND TO BE MISSING APPROXIMATELY .1250 INCH MATERIAL WHERE RETANING KEYS HOLD VALVE. (X) 1 L 7 1 3O 3 O 2A13 E274 2000092800113 20000928 00113 NE 2000 9 28 CA000901015 2 20000824 G 7200 ENGINE TMECA ARRIEL1B SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1B 6OO30 NE ENGINE POWER LOSS W A UNSCHED LANDING R PARTIAL RPM/PWR LOSS HO HOVERING 1 CA 4124 (CAN) HELICOPTER WAS IN A HOVER WHEN A POWER LOSS OCCURRED. UNKNOWN AT THIS TIME WHAT THE CAUSE WAS. TC AWAITING FOLLO W-UP REPORT. (X) 1 G 7 1 3U 3 U H9EU E19EU 2000092800114 20000928 00114 EU 2000 9 28 CA000901016 1 20000829 G 2913 S40 COUPLING AEROSP 350A35013004 SNIAS 350 AS350B2 8680813 EU SPLINES WORN W A UNSCHED LANDING F FLT CONT AFFECTED CR CRUISE 1 CA (CAN) THE PILOT WAS IN CRUISE WHEN HE LOST HYDRAULIC BOOST. THE PILOT INITIATED A HYDRAULIC FAILURE PROCEDURE AND LANDED THE HELICOPTER WITHOUT AN ACCIDENT. AN ENGINEER FOUND WORN OUT SPLINES ON THE COUPLING SLEEVE OF THE HYDRAULIC PUMP PU LLEY ASSEMBLY. AS A PRECAUTION, REPLACED THE HYDRAULIC PUMP. THE INSPECTION PERIOD AND REGREASE BY EUROCOPTER IS EVERY 500 HOURS. OUR MAINTENANCE SCHEDULE IS EVERY 100 HOURS. THE RECOMMENDED GREASE BY EUROCOPTER IS G355 (ROYCO 49B) GREA SE. (X) 1 G 7 1 3U H9EU 2000092800115 20000928 00115 SW 2000 9 28 CA000901017 1 20000804 G 6320 BP252 GEARBOX TB3117BMA KAMOV KA32 KA32A1 SW M/R GEARBOX MAKING METAL W A UNSCHED LANDING J WARNING INDICATION HO HOVERING 1 CA 649 364 708789210008 (CAN) DURING LOGGING OPERATION, PILOT REPORTED GEARBOX CHIP WARNING INDICATION AND LANDED IN SERVICE LANDING. INSPECTIO N OF CHIP DEECTORS REVEALED METALLIC FUZZ. DETECTORS CLEANED, AIRCRAFT GROUND RUN AND TEST FLOWN IN ACCORDANCE WITH BP2 52 MAINTENANCE MANUAL 84.10.00 P.103, RETURNED TO SERVICE. PROBLEM RECURRED, METAL DETECTED ON CHIP DETECTORS. GEARBOX REMOVED FROM SERVICE. (X) 1 G 7 2 4U NC 2000092100511 20000921 00511 WP 2000 9 21 CA000905002 2 20000822 G 7261 31012801 TUBE GARRTT MTSBSI MU2 MU2B35 5780411 CE GARRTT TPE331 TPE3316 01514 WP GEARBOX END CRACKED W E ENGINE SHUTDOWN J K WARNING INDICATION FLUID LOSS CR CRUISE 1 CA 2000 P20148C (CAN) THE ENGINE WAS SHUTDOWN IN FLIGHT AS A PRECAUTION DUE TO AN OIL LEAK AND LOW OIL PRESSURE. ONCE ON THE GROUND, THE SOURCE OF THE OIL LEAK COULD NOT POSITIVELY BE LOCATED.THE ENGINE WAS MOUNTED IN THE TEST CELL AND THE OIL LEAK WAS FIN ALLY TRACED TO A CRACKED FLARE ON THE OIL SUPPLY TUBE P/N 3101280-1 UNDER THE FLARE NUT AT THE GEARBOX END. THIS NUT IS LOCATED UNDER THE PROP PITCH CONTROL, AND BEHIND THE PROPELLER GOVERNOR, WHICH COMPLICATED LOCATING THE SOUCE OF THE LEA K IN THE FIELD. THE TUBE WAS REPLACED WITH A SERVICEABLE TUBE, ENGINE RE-ASSEMBLED, AND TESTED IN THE TEST CELL OK. THE ENGINE HAS BEEN FOUND ACCEPTABLE FOR RETURN TO SERVICE. 1 H 7 2 3T 4 T RT A10SW E4WE 2001011105375 20010111 05375 EU 2001 1 11 CA000905004 1 20000616 G 3244 5504632 TIRE FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU MLG FAILED W C ABORTED TAKEOFF D J INFLIGHT SEPARATION WARNING INDICATION TO TAKEOFF 1 CA (CAN) THE PILOT RPTED LT INBOARD MAIN WHEEL TIRE ASSY BLEW ON ROTATION & GEAR SAFE IND. LIGHT WENT OUT. MAINT CNTL TROUB LESHOT PROBLEM WITH FLT CREW BUT WERE UNABLE TO GET LEFT MAIN GEAR TO INDICATE DOWN AND LOCKED. DECISION MADE TO DIVERT WHERE EMERG LDG CARRIED OUT - AFTER BURNING OFF EXCESS FUEL. A/C LANDED W/O INCID., PASSENGERS WERE DEPLANED & TRANSPOR TED TO TERMINAL BY BUS. INIT MAINT INSP REVEALED RETREAD ON NR 2 TIRE HAD LET GO - TIRE ASSY STILL AT 100 PSI. MAINT INS T GEAR PINS, CHANGED #1 & #2 TIRES (P/N 9550462-2)&FERRIED FURTHER INSP REVEALED DAMAGE TO L/H SIDE STAY ASSY (P/N 20049 00 1), LOWER TOGGLE STRIKER SUB-ASSY (P/N 200 2 L 7 2 4F 4 F RT A20EU E2EU 2001011105376 20010111 05376 EU 2001 1 11 CA000905005 1 20000720 G 5280 200642005 STOP FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU MLG DOOR LOOSE W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) SHORTLY AFTER TAKEOFF AIRCRAFT REPORTED THE LEFT MAIN GEAR DOOR WOULD NOT CLOSE AFTER GEAR RETRACTION. THE GEAR WA S CYCLED SEVERAL TIMES WITH THE SAME RESULT. THE CREW ELECTED TO RETURN TO WITH THE GEAR DOWN SELECTION NORMAL - 5 GREEN LIGHTS AND BOTH MAIN GEAR DOORS CLOSED. AIRCRAFT LANDED WITHOUT INCIDENT - CFR WAS CALLED OUT ON STANDBY AS A PRECAUTIO N. AIRCRAFT INSPECTED AND FOUND SAFE FOR FERRY FLIGHT WITH GEAR DOWN AND PINS INSTALLED. MAINTENANCE INSPECTION FOUND TH E LEFT HAND MAIN LANDING GEAR DOOR WOULD NOT LOCK BECAUSE THE DOOR STOP WAS LOOSE. STOP WAS ADJUSTED AND LOCK WIRED - GE AR SWINGS CARRIED OUT AND CHECKED SERVICEABLE.AIRCRAFT RETURNED TO SERVICE WITH NO FURTHER INCIDENTS TO REPORT. 2 L 7 2 4F 4 F RT A20EU E2EU 2001030700651 20010307 00651 EU 2001 3 7 CA000905006 1 20000725 G 5210 A26084005 SEAL FOKKER A26050801 FOKKER F28 F28MK1000 4990808 EU PAX DOOR LOOSE W D RETURN TO BLOCK J WARNING INDICATION CL CLIMB 1 CA 048 (CAN) SHORTLY AFTER TAKEOFF THE CREW REPORTED THE AIRCRAFT WOULD NOT PRESSURIZE BECAUSE THE MAIN CABIN DOOR WAS NOT SEAL ING PROPERLY. AICRAFT RETURNEDAND LANDED WITHOUT INCIDENT. PASSENGERS DEPLANED AND TRANSFERED TO A WAITING AIRCRAFT. MAI NTENANCE TAXIED AIRCRAFT BACK TO THE HANGAR AND INSPECTED THE DOOR AREA. MAINTENANCE FOUND THE MAIN CABIN WOULD NOT SEAT PROPERLY WHEN AIRCRAFT WAS PRESSURIZED TO MAX DIFFERENTIAL.DOOR SEAL WAS RE-ADJUSTED AND AIRCRAFT GROUND PRESSURIZED SE RVICEABLE.AIRCRAFT RETURNED TO SERVICE WITH NO FUTHER INCIDENTS TO REPORT. 2 L 7 2 4F RT A20EU 2001030700652 20010307 00652 EU 2001 3 7 CA000905007 1 20000723 G 2910 LINE FOKKER F28 F28MK1000 4990808 EU HYD SYSTEM RUPTURED W D RETURN TO BLOCK K FLUID LOSS CL CLIMB 1 CA (CAN) AIRCRAFT RETURNED TO BLOCKS BECAUSE THE CREW REPORTED THE NR 2 SYSTEM HYDRAULIC PUMP LIGHTS ILLUMINATED AND THEN T HE NR 2 SYSTEM QUANTITY AND PRESSURE DROPPED QUICKLY. AIRCRAFT RETURNED TO YVR AND LANDED WITHOUT INCIDENT. MAINTENANCE INSPECTION REVEALED A RUPTURED LINE FOUND IN THE STUB WING AFT OF THE NR 2 SHUT OFF VALVE. LINE REPLACED, AREA INSPECTED AND GROUND CHECKED SERVICEABLE - AIRCRAFT RETURNED TO SERVICE WITH NO FURTHER INCIDENTS TO REPORT. 2 L 7 2 4F RT A20EU 2001030700653 20010307 00653 2001 3 7 CA000905008 4 20000722 G 3442 20671570153 RADAR FOKKER F28 F28MK1000 4990808 EU WEATHER FAILED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 9583 (CAN) AIRCRAFT REPORTED THE WEATHER RADAR WAS U/S ON CLIMB OUT. THE CREW DECIDED TO RETURN DUE TO UNFAVORABLE WEATHER CO NDITIONS - AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE SENT AND TESTED THE SYSTEM - TECHNICIAN REPORTED SYSTEM CHECKED SERVICEABLE. DECISION MADE TO REPLACE WEATHER RADAR FOR TROUBLESHOOTING REASONS. R/T REPLACED, S/NON1523, S/N OFF 4972, SYSTEM GROUND CHECKED SERVICEABLE. AIRCRAFT RETURNED TO SERVICE WITH NO FURTHER INCIDENTS TO REPORT. 2 L 7 2 4F RT A20EU 2001010200013 20010102 00013 WP 2001 1 2 CA000905010 2 20000529 G 7320 DIAPHRAGM WOODWARD 89356110 BEECH 100 100BEECH 1152916 CE GARRTT TPE331 TPE3316252B 01514 WP SIDEWALL OF ROLL PIN HOLE W O OTHER O OTHER LD LANDING 1 CA 1705317 (CAN) TORQUE ON LEFT ENGINE WOULD NOT GO BELOW 900 POUND/FEET OF TORQUE AT FLIGHT IDLE, ENGINE SHUT DOWN ON LANDING. FC U DIAPHRAGM FAILED LEAK TEST. FOUND BELLOW/DIAPHRAGM ASSY WITH PIN HOLES. NOTE: FCU HAS 5709 ON, AND TSO DIAPHRAGM IS A 300 HR REPLACEMENT ITEM. SHOULD HAVE BEEN REPLACED AT 3000 HOURS WHEN AIRCRAFT WAS U.S. REGISTERED - TECHNICAL HISTO RY ON ENGINE DOES NOT REFLECT FCU MAINTENANCE. 1 L 7 2 3T 4 T A14CE E2WE 2000092800116 20000928 00116 SW 2000 9 28 CA000905011 1 20000822 G 6510 205040176101 BOOT BELL 205040004101 BELL 205 205A1 1181414 SW LYC T53 T5313B 41549 NE MAIN DRIVE SHAFT TORN W O OTHER K FLUID LOSS NR NOT REPORTED 1 CA 2064 A2011823 (CAN) - LEAKAGE OF GREASE WAS DISCOVERED COMING FROM THE MAIN DRIVE SHAFT AFTER AIRCRAFT WAS SHUT DOWN . FURTHER INVE STIGATION REVEALED THAT THE BOOT WAS TORN THUS ALLOWING LEAKAGE OF GREASE FROM THE DRIVE SHAFT COUPLING.- NO INDICATIO N OF OVERHEATING. 1 G 7 1 4U 4 U H1SW E17EA 2001030700684 20010307 00684 SO 2001 3 7 CA000905012 2 20000823 G 7414 M3050 IMPULSE COUPLING SLICK 6310 CESSNA 210 210L 2073448 CE CONT O520 IO520L 17032 SO MAGNETO FAILED W K NONE R PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 CA 1446 96111161 (CAN) MAGNETO HAD 125 HOURS SINCE LAST 500 HOUR INSPECTION, AT WHICH TIME IMPULSE COUPLING WS WITHIN SPECS AS CALLED OU T IN SLICK MAINTENANCE AND OVERHAUL MANUAL. DURING END RUN FOR 50 HOUR A/C INSPECTION, R/H MAG FOUND DEAD. DURING INSPEC TION, FOUND MAG LYING ON TOP OF ENGINE WITH BUSTED MOUNTING FLANGE. INSPECTION FOUND THAT IMPULSE COUPLING HAD COME APAR T DURING END RUN - SEIZED MAG THUS BUSTING FLANGE. 1 H 7 1 3O 3 O 3A21 E5CE 2000092800117 20000928 00117 GL 2000 9 28 CA000905014 2 20000811 G 7314 6899253 PUMP HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL FUEL CONTROLL FAILED W O OTHER O OTHER HO HOVERING 1 CA 3650 T1271 (CAN) WHILE IN 4 FT HOVER, AN ENGINE FLAMEOUT OCCURRED. UPON INVESTIGATION IT WAS DISCOVER THE THE ENGINE DRIVEN FUEL P UMP TO BE IN BY PASS. FUEL CONTROL AND FUEL PUMP REPLACED. 1 G 7 1 3U 3 U H3WE E4CE 2001030700686 20010307 00686 GL 2001 3 7 CA000905015 2 20000816 G 7323 23065121 GOVERNOR BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL ENGINE MALFUNCTIONED W C ABORTED TAKEOFF R PARTIAL RPM/PWR LOSS TO TAKEOFF 1 CA 203 14151 (CAN) WHILE RUNNING ON THE GROUND AT 100% N2 THE PILOT PULLED COLLECTIVE. AS HE PULLED IN POWER THE ROTOR RPM DROPPED TO 80%, ALL AIR LINES WERE LEAK CHECKED, GOVERNOR REPLACED & THE PROBLEM WENT AWAY. 1 G 7 1 3U 3 U H2SW E4CE 2001030700654 20010307 00654 NM 2001 3 7 CA000905016 1 20000818 G 4990 GTCP85129CKA BLEED VALVE BOEING 737 737281 138448P NM PWA JT8 JT8D17 52049 NE APU FAILED W E F ENGINE SHUTDOWN ACTIVATE FIRE EXT. O OTHER CR CRUISE 1 CA 31440 1440 P35248C (CAN) ON TWO OCCASIONS, THE CREW EXPERIENCED A FIRE INDICATION ON THE APU WHILE THE AIRCRAFT WAS AT CRUISING ALTITUDE. O N BOTH OCCASIONS, THE APU SHUT DOWN AND THROUGH CREW PROCEDURES, THE APU FIRE BOTTLE WAS DISCHARGED. IN BOTH OCCURRENCES , MAINTENANCE INSPECTED THE APU COMPARTMENT AND FOUND NO SIGNS THAT A FIRE HAD OCCURRED AND THE AIRCRAFT CONTINUED IN SE RVICE WITH THE APU ON MEL FOR THE DISCHARGED BOTTLE. FOUND PINS ON BLEED VALVE CORRODED, LOAD CONTROL VALVE AND REGULATO R REPLACED. 2 L 7 2 4F 4 F A16WE E2EA 2000092100512 20000921 00512 SO 2000 9 21 CA000906002 1 20000807 G 3231 1776604 HOSE PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA ADJ TO FITTING LEAKING W A UNSCHED LANDING K FLUID LOSS TO TAKEOFF 1 CA (CAN) WHEN DEPARTING YTH, ON 4 AUG 2000, WITH GEAR SELECTED UP, U/C FAILED TO RETRACT. PILOT LOCKED U/C DOWN BY HAND PU MP AND RETURNED TO YTH. FLY PAST CARRIED TO CONFIRM U/C POS AND UNEVENTFUL LDG MADE .INSP REVEALED THAT HYDRAULIC HOSE TO PORT U/C DOOR ACTUATOR LEAKING AND CAUSED HYDRAULIC SYS FLUID LOSS. NEW HOSE INST AND HYDRAULIC SYS PRIMED, BLED. U /C CYCLED THROUGH SEVERAL RETRACTIONS WITH NO FAULTS. AIRCRA FT RETURNED TO SERVICE. HOSE LEAKING FROM STEEL BRAIDS AT END ADJACENT TO END FITTING CONNECTED TO DOOR ACTUATOR. EXAMINATION OF HOSE SHOWED 2 BROKEN STRANDS IN STEEL OUTER BRA IDING,&VERY SLIGHT DISTORTION OF HOSE IN AREA OF END FITTING. 1 L 7 2 3O 3 O A20SO E14EA 2000092800128 20000928 00128 SW 2000 9 28 CA000906003 1 20000816 G 6730 204076052009 SERVO BELL 204 204B 1181404 SW LYC T53 T5313B 41549 NE ACTUATOR FAILED W O OTHER F FLT CONT AFFECTED CR CRUISE 1 CA 612 62656 (CAN) THE PILOT FELT A FEEDBACK IN THE CYCLIC STICK IN THE FORWARD RIGHT HAND QUADRANT. THIS FEEDBACK WAS NOT SATISFACT ORY TO THE AIRCRAFT TYPE. THE RIGHT HAND SERVO WAS REMOVED AND EXCHANGED WITH THE LEFT HAND CYCLIC SERVO. THE SUSPECT SERVO NOW IN THE LEFT HAND POSITIION CAUSED AN EXCESSIVE FEEDBACK IN THE FORWARD LEFT HAND QUANDRANT. THE SUSPECT SERVO WAS REMOVED AND REPLACED WITH A SERVO (TSO 0:0 HOURS) WHICH ELIMINATED THE CYCLIC STICK FEEDBACK. THE AIRCRAFT WAS FOUN D SATISFACTORY TO TYPE AND SUBSEQUENTLY RELEASED TO SERVICE. (X) 1 G 7 1 4U 4 U H1SW E17EA 2000092100513 20000921 00513 SO 2000 9 21 CA000906005 1 20000821 G 7930 3030359 CHIP DETECTOR PWA PIPER PA42 PA42720 7104212 SO PWA PT6 PT6A61 52043 EA BSE-THRDED AREA BROKEN W E F A ENGINE SHUTDOWN ACTIVATE FIRE EXT. UNSCHED LANDING B K SMOKE/FUMES/ODORS/SPARKS FLUID LOSS CL CLIMB 1 CA PCE99130 (CAN) DURING CLIMB, PILOT NOTICED SMOKE FROM LEFT ENGINE. SUSPECTING FIRE, ENGINE WAS SHUTDOWN AND SECURED AND FIRE BOT TTLE ACTIVATED. UNEVENTFUL LANDING C/O SASKATOON. MAINTENANCE DISCOVERED BROKEN CHIP DETECTOR ALLOWING ENGINE OIL TO L EAK ONTO ENGINE CASE, RESULTING IN SMOKE. OIL REPLENISHED, DETECTOR REPLACED NEW. FIRE BOTTLE REMOVED FOR RECHARGE. CR ACK FOUND AT THE CHIP DETECTORS BASE TO THREADED AREA. (X) 1 L 7 2 4T 4 T A23SO E4EA 2000092100514 20000921 00514 CE 2000 9 21 CA000906006 1 20000817 G 5610 10138402518 WINDSHIELD BEECH 200 B200 1152922 CE PWA PT6 PT6A42 52043 NE RT WINDSHIELD FAILED W I A CABIN DEPRESSURIZATION UNSCHED LANDING S AFFECT SYSTEMS CR CRUISE 1 CA 1374 97058H9808 (CAN) WHILE IN CRUISE AT 28,000 FEET, THE R/H WINDSHIELD FAILED. THE INNER LAMINATION SUSTAINED A FAILURE RESULTING IN A LATTICE LIKE SERIES OF CRACKS. (INSTALLED MAY 1997.) 1 L 7 2 4T 4 T A24CE E4EA 2000092100515 20000921 00515 SO 2000 9 21 CA000906008 2 20000816 G 8520 ENGINE CESSNA 206 U206F 2073333 CE CONT O520 IO520F 17032 SO ENGINE FAILED W A UNSCHED LANDING E VIBRATION/BUFFET CR CRUISE 1 CA (CAN) PILOT REPORTED DURING CRUISE HE HAD BRIEF VIBRATION FOLLOWED BY A LOSS OF OIL PRESSURE AND IMMEDIATE ENGINE FAILUR E. AN UNEVENTFUL FORCED LANDING WAS CONDUCTED ON A LAKE 40 NAUTICAL MILES NORTHWEST OF RANKIN INLET, NUNAVUT. MAINTENA NCE FOUND THE FRONT HALF OF THE ENGINE FREE AND WOULD TURN OVER, HOWEVER, AN ACCESSORY CASE AND REAR OF ENGINE APPEARS S EIZED INDICATING A POSSIBLE CRANK FAILURE. THIS DATE THE A/C IS IN THE PROCESS OF RECEIVING A ZERO TIME ENGINE. THE FAI LED ENGINE IS TO BE RETURNED TO PROGRESSIVE AIR IN KAMLOOPS FOR ANALYSIS. HAVE REQUESTED A FURTHER SDR AND STRIP REPORT . (X) 1 H 7 1 3O 3 O A4CE E5CE 2000092100516 20000921 00516 SO 2000 9 21 CA000906009 1 20000817 G 3246 16107200 WHEEL CLEVELAND 40106 PIPER PA31T PA31T 7103124 SO PWA PT6 PT6A28 EA BEAD FLANGE RADI CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) RECENT LPI NDT TESTS REVEALED WHEEL HALF CRACKING IN THE BEAD FLANGE AREA. CLEVELAND WHEELS ARE DATE MARKED AND N DT SERIALIZED. AFFECTED WHEELS WERE DATED JUNE 1994 AND JUNE 1991. WHEELS REMOVED FROM SERVICE. (X) 1 L 7 2 3T 4 T A8EA E4EA 2000092100517 20000921 00517 EA 2000 9 21 CA000906010 2 20000723 G 7421 RHB32E SPARK PLUG CHAMPION PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2B 41532 EA SPARK PLUG FAILED W A UNSCHED LANDING E VIBRATION/BUFFET CL CLIMB 1 CA L78161 (CAN) SPARK PLUG MISFIRING THROUGH ALTITUDE. TESTED WITH PLUG MACHINE AND FOUND ERRATIC AND YELLOW COLOR SPARK. (X) 1 L 7 2 3O 3 O A20SO E14EA 2000092800103 20000928 00103 SW 2000 9 28 CA000907002 1 20000821 G 6220 206011125001 PIN BELL BELL 206 206L1 1182107 SW ALLSN 250C 250C28B 03013 GL CENTER WORN W K NONE O OTHER IN INSP/MAINT 1 CA 582 A1417 (CAN) DURING MAINTENANCE TEARDOWN, PINS FOUND TO HAVE MECHANICAL WEAR AND REPLACED. (X) 1 G 7 1 3U 3 U H2SW E1GL 2001030700655 20010307 00655 NM 2001 3 7 CA000907003 1 20000823 G 2782 269002910 ACTUATOR BOEING 727 727217 NM PWA JT8 JT8D17 52049 NE SLATS CRACKED W O OTHER K FLUID LOSS DE DESCENT 1 CA 10522 (CAN) LOST " A" SYSTEM HYDRAULICS, PRESSUE AND QUANTITY READ ZERO. TROUBLESHOOTING CARRIED OUT FOUND NR 3 LEADING EDGE S LAT ACTUATOR HOUSING CRACKED. LEADING EDGE SLAT ACTUATOR REPLACED PER MM 27-81-22. 2 L 7 3 4F 4 F RT A3WE E2EA 2000091800022 20000918 00022 SO 2000 9 18 CA000907004 2 20000823 G 7414 M3081 POINTS SLICK 4371 CESSNA 150 150L 2071826 CE CONT O200 O200A 17020 SO CONTACT POINT LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA 651 99020938 (CAN) THE MAGNETO WAS REMOVED FROM SERVICE DUE TO INTERMITTENT FIRING. ON INSPECTION, THE STATIONARY POINT WAS FOUND LO OSE. THE POINT, IS MANUFACTURED WITH A STEM TO BE RIVETED TO THE STEEL FRAME. TOTAL TIME ON NEW POINT SET INSTALLED AT T HE 500 HOUR MAINTENANCE CHECK IS 151.2 HOURS. (X) 1 H 7 1 3O 3 O 3A19 E252 2001030800001 20010308 00001 GL 2001 3 8 CA000907005 3 20000826 G 6111 PFA12D19B BLADE HAMSTD 24PF305 DHAV DHC7 DHC71 2802702 EA PWA PT6 PT6A50 52043 EA HAMSTD 24PF 24PF305 GL PROPELLER MISREPAIRED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 9257 2860 238306 (CAN) . BLADE SER #841280. BLADE RECD FROM OPERATOR WITH FIBREGLASS DAMAGE BEYONG MANUAL LIMITSL. BLADE RETURNED TO MFG FOR REPAIR. BLADE RETURNED FROM MFG AFTER REPAIR ANDFOUND NOT TO COMPLY WITH COMPONENT MAINT MANUAL IN 2 AREAS. CMM61-13 -01.1ST: ALUMINUM PORTION OF BLADE SHANK PAINTED WITH REQD BLACK EROSIION COATING THAT IS CONDUCTIVE. BUT BLADE NOT COA TED WITH REQD CLEAR POLYURATHANE COATING ON TOP OF BLACK EROSION COATING. IS NEW REQMT WHEN MANUAL REVISED TO REVISION 1 0 IN JUN 1999.2ND: BLADE FOUND WITH CORK INST IN TAPER BORE: CORK MUST BE REMVD FROM BLADE AS PART OF DISASSY PROC& T 2 H 7 4 4T 4 T A20EA E4EA 6 C P1NE 2001011105149 20010111 05149 NM 2001 1 11 CA000907006 1 20000825 G 3260 1010153 POSITION SWITCH BOEING 727 727233 138408A NM PWA JT8 JT8D15 52051 NE SPRING ANCHOR FAILED W L ABORTED APPROACH N FALSE WARNING AP APPROACH 1 CA (CAN) FAILED NLG POS IND. SWITCH YIELDED FOLLOWING RESULTS. CURSORY INSP DETECTED INTERNAL RATTLE. WHEN CASE OPENED LOOS E DRIVE SCREW & SLEEVE (THIMBLE) WHICH COMPRISE SWITCH ARM SPRING ANCHOR ASSY WERE FOUND. THE CONTACTOR ASSY APPEARED TO BE IN AS NEW CONDITION. CLOSER EXAMINATION REVEALED DRIVE SCREW WHICH RETAINS SWITCH ARM SPRING ANCHOR THIMBLE APPEARED TO BE INADEQUATE. 2 L 7 3 4F 4 F RT A3WE E2EA 2000091800023 20000918 00023 EU 2000 9 18 CA000907008 1 20000828 G 6120 9717517102 WIRE 975290201 PILATS PC12 PC1245 7090551 EU HARTZL HCE4A HCE4A3D GL PIN BROKEN W O OTHER O OTHER CR CRUISE 1 CA 081 (CAN) CAREW REPORTED APPROXIMATELY 200 RPM PROP INDICATION FLUCTUATION IN-FLIGHT. ALL OTHER ENGINE PARAMETERS WERE OK. SYSTEM INSPECTED AND A PIN IN THE PROP MAGNETIC PICK UP CANNON PLUG WAS FOUND WITH A BROKEN WIRE. WIRE/PIN CONNECTION REPAIRED AND RUN-UP CARRIED OUT SERVICEABLE. (X) 1 L 7 1 3T RT A78EU 5 C P210NE 2000091800024 20000918 00024 EU 2000 9 18 CA000907009 1 20000828 G 7331 9753512602 TRANSMITTER PWA PILATS PC12 PC1245 EU PWA PT6 PT6A67B 52043 NE INTERNAL INACCURATE W K NONE O OTHER CR CRUISE 1 CA 3121 PCEPR0090 (CAN) PILOT REPORTED THAT THE EIS PANEL WAS ONLY READING 50 POUNDS PER HOUR FUEL FLOW. REPLACED FUEL FLOW TRANSMITTER A ND FUEL FLOW CHECKED SERVICEABLE. (X) 1 L 7 1 3T 4 T RT A78EU E26NE 2000091800025 20000918 00025 CE 2000 9 18 CA000907014 1 20000816 G 6100 PROPELLER MCAULY CESSNA 150 150M 2071830 CE CONT O200 O200A 17020 SO MCAULY 1A102 1A102OCM GL L/E & FACE DAMAGED W O OTHER O OTHER IN INSP/MAINT 1 CA 1498 K18663 (CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. (X) 1 H 7 1 3O 3 O 3A19 E252 5 N P918 2000091800026 20000918 00026 SO 2000 9 18 CA000907015 1 20000819 G 5311 4521504 BULKHEAD PIPER PIPER PA31T PA31T 7103124 SO PWA PT6 PT6A28 EA SNUBR UPR BOLT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 14755 31T7920045 (CAN) DOOR FRAME (BULKHEAD) CRACKED AT SNUBBER UPPER ATTACHMENT POINT. (X) 1 L 7 2 3T 4 T A8EA E4EA 2000091800027 20000918 00027 CE 2000 9 18 CA000907016 1 20000824 G 7400 103572001 IGNITION SWITCH CONT CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA LT MAG CONTACTS SHORTED W O OTHER O OTHER IN INSP/MAINT 1 CA 6711 L2620227A (CAN) FLIGHT SCHOOL INSTRUCTOR AND STUDENT PERFORMED POST FLIGHT MAG CHECK BEFORE SHUTDOWN. WHEN SELECTING LT MAG, AIRC RAFT STARTED TO FILL WITH SMOKE FOLLOWED BY THE INSTRUMENT BREAKER TRIPPING. AMES FOUND THE PROBLEM TO ORIGINATE AT THE IGNITION SWITCH GROUNDING OUT. SWITCH WAS REPLACED AND FUNCTION TESTED. SYSTEM FOUND TO BE SERVICEABLE. (X) 1 H 7 1 3O 3 O NT 3A12 E274 2001011105150 20010111 05150 NM 2001 1 11 CA000907018 1 20000801 G 2435 230880026 STARTER GEN DHAV DHC8 DHC8301 NM PWA PW120 PW123 NE NR 1 ENGINE INOPERATIVE W O OTHER O OTHER TX TAXI/GRND HDL 1 CA 1859 (CAN) AIRCRAFT ARRIVED IN GEORGETOWN (GGO) WITH THE " NR 1 DC GEN HOT" CAUTION LIGHT & HEATER CAUTION LIGHT. THE STARTER GENERATOR AND AREA AROUND IT INSPECTED AS PER MEL 24-1, STARTER GENERATOR FUNCTIONED CHECKED. OK.AIRCRAFT ARRIVED LATER AT PORT OF SPAIN (POS), WHEN THE CREW WAS READY TO DEPART AND COMMENCE STARTING OF THE NR 1 ENGINE, IT WOULD NOT START. STARTER GENERATOR REPLACED, SYSTEM OPERATES CORRECTLY. 2 H 7 2 4T 4 T RT A13NM E20NE 2001030800005 20010308 00005 NM 2001 3 8 CA000907019 1 20000815 G 3260 DSC201 HARNESS ELDEC 858601 DHAV DHC8 DHC8201 2809001 NM PWA PW120 PW123 NE MLG DEFECTIVE W C D ABORTED TAKEOFF RETURN TO BLOCK N FALSE WARNING TO TAKEOFF 1 CA (CAN) ON TAKEOFF ROLL AT APPROX. 50 KTS LEFT MAIN GEAR DOOR ADVISORY LIGHT ILLUMINATED ONLY, PILOT ABORTED TAKEOFF AND R ETURNED TO STAND. ON CHECKING PSEU FAULT CODES 06 AND 53 WITH EXPANDED TEST 72 APPARENT LEFT MAIN GEAR DOOR WIL NOT CLOS E. TECHNICIANS - TROUBLESHOOTING REVEALED, CORRECT OPERATION NOTE GEAR & R/H MAIN GEAR (UP & DOWN), LEFT GEAR SEQUENCE V ALVE - NO POWER. FURTHER INVESTIGATION REVEALED A DEFECT WITH THE WOW NR2 WIRING HARNESS, NR2 WOW HARNESS (MLG) ORDERLY AOG - REPLACED HARNESS & CHAFED RELAY WIRE.PSEU REPLACED - AIRCRAFT SERVICEABLE AT 1900 HOURS17 AUGUST 2000. 2 H 7 2 4T 4 T RT A13NM E20NE 2001030800006 20010308 00006 NM 2001 3 8 CA000907020 1 20000821 G 2913 570347 PUMP DHAV DHC8 DHC8301 NM PWA PW120 PW123 NE NR 1 ENGINE MALFUNCTIONED W O OTHER J WARNING INDICATION AP APPROACH 1 CA (CAN) AT 4 MILES FINAL FLAPS SELECTED TO 15 DEGREES NR1 ENGINE HYDRAULIC CAUTION LIGHT ILLUMINATED TOGETHER WITH ROD PRE SSURE NR1 AND ROD HYDRAULIC NR1 AND MASTER CAUTION.STANDBY AND MAIN PRESSURES OBSERVED TO BE 1500 PSI FLAPS CONTINUED TO TRAVEL TO 15 DEGREES. STANDBY AND MAIN PRESSURES 3000 PSI. STANDBY AND MAIN PRESSURES OBSERVED NORMAL, HYDRAULIC QUANTI TIES NORMAL. FLAPS OBSERVED AT 15 DEGREES. NR1 ENGINE HYDRAULIC PUMP CAUTION LIGHT REMAINED ILLUMINATED. UNEVENTFUL LAND ING MADE. NR1 ENGINE DRIVEN PUMP REPLACED. FUNCTIONED SATISFACTORY. 2 H 7 2 4T 4 T RT A13NM E20NE 2001011105151 20010111 05151 NM 2001 1 11 CA000907021 1 20000720 G 3040 8SC0043011 WINDSHIELD DHAV DHC8 DHC8301 NM PWA PW120 PW123 NE COCKPIT FAILED W O OTHER O OTHER CR CRUISE 1 CA 4803 97326H1600 (CAN) DURING A FLIGHT THE CAPTAIN NOTICED A SMELL & SOME SMOKE COMING FROM THE TOP OF HIS WINDSHIELD. WINDSHIELD DE-ICIN G WAS TURNED OFF AND THE SMELL WENT AWAY. AIRCRAFT CONTINUED WITH DE-ICE OFF. MAINTENANCE NOTICED THAT THE STUD FOR THE GROUND AT THE WINDOW WAS VERY DARK AND BURNT. THE STUD WAS REPLACED AND WINDOW HEAT WAS FUNCTIONED. AS SOON AS THE HEAT WAS SELECTED TO NORM THE WINDOW SHATTERED. WINDSHIELD WAS REPLACED. SECOND WINDOW TO SHATTER IN A YEAR. BOTH CASES FINE GLASS SPRAYED IN THE FLIGHT COMPARTMENT. FIRST WINDOW 12,000 HOURS, SECOND WINDOW 4,803HOURS. 2 H 7 2 4T 4 T RT A13NM E20NE 2001030800007 20010308 00007 NM 2001 3 8 CA000907022 1 20000811 G 5270 864202 PROXIMITY SWITCH 85220284003 DHAV DHC8 DHC8301 NM PWA PW120 PW123 NE FWD EMERG EXIT OUT OF ADJ W A UNSCHED LANDING N FALSE WARNING CR CRUISE 1 CA (CAN) DURING THE CRUISE THE FORWARD EMERGENCY EXIT ILLUMINATED EMERGENCY CHECK LIST ENTERED AND AIRCRAFT DIVERTED TO MAN CHESTER, UNEVENTFUL LANDING MADE AT MANCHESTER AIRPORT. ENGINEERS FOUND THAT THE PROXIMITY SENSOR WAS NOT WIRE LOCKED LA RGER THAN NORMAL OPERATING GAP. SWITCH ADJUSTED AS PER MAINTENANCE MANUAL, CHECKED FOUND SATISFACTORY. SWITCH NOW WIRELO CKED. AIRCRAFT RETURNED TO SERVICE. 2 H 7 2 4T 4 T RT A13NM E20NE 2000091800028 20000918 00028 SO 2000 9 18 CA000907024 1 20000806 G 3260 451823 ACTUATOR PIPER 6741108 PIPER PA34 PA34200 7103405 SO LYC O360 IO360C1E6 41514 EA LT MAIN GEAR BROKEN W K NONE J WARNING INDICATION CL CLIMB 1 CA 2720 (CAN) GEAR WOULD NOT RETRACT AFTER TAKEOFF. AT RETURN TO BASE, SQUAT SWITCH ACTUATOR ARM WAS FOUND TO BE BROKEN. NEW A CTUATOR INSTALLED, NORMAL FUNCTION RETURNED. (X) 1 L 7 2 3O 3 O A7SO 1E10 2000091800029 20000918 00029 CE 2000 9 18 CA000907025 1 20000808 G 3233 99124852 ACTUATOR CESSNA 500 550 2076604 CE NOSE GEAR ACT FAILED W O OTHER R D PARTIAL RPM/PWR LOSS INFLIGHT SEPARATION LD LANDING 1 CA 1519 015 (CAN) NOSE GEAR COLLAPSED UPON LANDING, WITH 3 GREEN INDICATIONS. PILOT APPLIED UP ELEVATOR EASING THE WEIGHT ON THE NO SE AND THE NOSE GEAR CAME BACK DOWN AND LOCKED. TAXIED TO FBO OK. MAINTENANCE AND CESSNA REP REMOVED GEAR DOORS AND CO NFIRMED DOWN AND LOCKED. AIRCRAFT FERRIED TO YYZ FROM YHM. NOSE GEAR ACTUATOR REMOVED. SENT TO FAA ACO WICHITA KS FO R TESTING. REPLACED ACTUATOR. GEAR SWINGS CARRIED OUT. CHECKED OK. (X) 1 L 7 2 4F A22CE 2001011105159 20010111 05159 NM 2001 1 11 CA000907027 1 20000822 G 6310 ENGINE BOEING 727 727260 NM PWA JT8 JT8D17 52049 NE NR 2 FAILED W O OTHER O OTHER DE DESCENT 1 CA (CAN) PRIOR TO DESCENT INTO YYC LOW OIL PRESSURE LIGHT ON FOR NR 2 ENGINE OIL PRESSURE DECREASING AND OIL QUANTITY DECR EASING.ENGINE FAILURE AND SHUTDOWN FOLLOWED BY ONE ENGINE INOPERATIVE CHECKLIST CARRIED OUT. DECLARED EMERGENCY LANDING. TROUBLESHOOTING CARRIED OUT, FOUND REQUIRES ENGINE CHANGE. PRESENTLY IN PROCESS OF MAKING ARRANGEMENT TO REPLACE ENGINE IN YYC. 2 L 7 3 4F 4 F RT A3WE E2EA 2001030700662 20010307 00662 WP 2001 3 7 CA000918003 1 20000808 G 2121 5007025211 FAN DOUG DC9 DC932 3022066 WP PWA JT8 JT8D7 52053 NE E/E BAY FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) BURNING SMELL ON PRE-DEPARTURE COMING FROM THE ELECTRICAL EQUIPMENT COMPARTMENT. FOUND THE A/C BUS CONTROL PANEL C IRCUIT BREAKER POPPED, UNABLE TO RESET. REPLACED THE RADIO RACK COOLING FAN AND ALSO THE A/C BUS CONTROL PANEL. 2 L 7 2 4F 4 F A6WE E2EA 2001030800010 20010308 00010 WP 2001 3 8 CA000918006 1 20000817 G 2420 WIRE DOUG DC9 DC932 3022066 WP PWA JT8 JT8D7 52053 NE LT GENERATOR DAMAGED W D RETURN TO BLOCK J WARNING INDICATION TX TAXI/GRND HDL 1 CA (CAN) STALL INDICATION FAILURE LIGHT ON TRAINING FLIGHT, AIRCRAFT RETURNED TO BASE. FOUND LT GENERATOR TRIPPED, ATTEMPTE D RESET, NIL FIX, FOUND DAMAGED WIRING.REPLACED WIRE X4A2N, SYSTEM CHECK SERVICEABLE. 2 L 7 2 4F 4 F A6WE E2EA 2001011105184 20010111 05184 NM 2001 1 11 CA000918010 1 20000807 G 2613 285N002821 CIRCUIT BOARD BOEING 767 767209 NM PWA JT9 JT9D7R4D 52054 NE LOGIC TEST CARD FAILED W K NONE L NO TEST IN INSP/MAINT 1 CA (CAN) REJECTED TAKEOFF AT 80 KNOTS FOR A FIRE/OVERHEAT SYSTEM FAULT. DISPLAYED ON THE (EICAS) ENGINE INDICATION AND CREW ALERT SYSTEM. (CARGO INDICATION) THE A FAULT CARDS WERE SWAPPED, NIL FIX PROBLEM REPEATED. SUSPECT TO BE THE AFT LOGIC TEST CARD. REPLACED THE AFT LOGIC TEST CARD, TEST PERFORMED AND CHECK SERVICEABLE. 2 L 7 2 4F 4 F RT A1NM E3NE 2001030800013 20010308 00013 NM 2001 3 8 CA000918011 1 20000810 G 7700 834802 PROXIMITY SWITCH PWA JT9D7R4D BOEING 767 767209 NM PWA JT9 JT9D7R4D 52054 NE LEFT FAULTY W C ABORTED TAKEOFF N FALSE WARNING TO TAKEOFF 1 CA P709699 (CAN) AIRCRAFT REJECTED TAKEOFF AT 76 KNOTS FOR AN (EICAS) ENGINE INDICATION AND CREW ALERT SYSTEM MESSAGE INDICATION. F OUND LT SLEEVE UNLOCK PROXIMITY SWITCH AT FAULT. REPLACED LT PROXIMITY SWITCH. 2 L 7 2 4F 4 F RT A1NM E3NE 2001030800014 20010308 00014 2001 3 8 CA000919002 4 20000831 G 3418 SENSOR CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE STALL WARNING FAILED W C ABORTED TAKEOFF N FALSE WARNING TO TAKEOFF 1 CA (CAN) FLIGHT NR 5805 FROM CVG TO ISP, THE FLIGHT CREW REPORTED. STALL FAIL MSG AT 80 KTS, ON TAKEOFF ROLL. (ABORTED TAKE OFF BELOW 80 KTS). AIRCRAFT RETURNED TO THE GATE FOR INVESTIGATION. MAINTENANCE CREW REPLACED THE AOA SENSOR AND THE AIR CRAFT RETURNED IN SERVICE 28 AUGUST 2000. 2 L 7 2 4F 4 F RT A21EA E15NE 2001030800015 20010308 00015 EA 2001 3 8 CA000919003 1 20000831 G 7603 GEARBOX CNDAIR CL600 CL6002B19 EA ATR FAILED W B EMER. DESCENT E VIBRATION/BUFFET CR CRUISE 1 CA (CAN) FLIGHT NR 5743 FROM CVG TO CLT, THE FLIGHT CREW REPORTED: IN FLIGHT (DESCENT), NR 2 ENGINE, THE N2 SET AT 82%, DID NOT RESPOND THE THRUST LEVER MOVEMENT. SHUT ENGINE DOWN IN FLIGHT, ECLRED EMERGENCY LANDING WITH NR 1 ENGINE ONLY, LAND ING WAS UNEVENTFUL. T/S IN PROGRESS, APPEARS TO BE ATR GEARBOX. 2 L 7 2 4F RT A21EA 2001030800016 20010308 00016 EA 2001 3 8 CA000919004 1 20000831 G 3250 TORQUE LINK CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE NLG STEERING FAILED W D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 CA (CAN) FLIGHT NR 5122 FROM MSY TO MCO, THE FLIGHT CREW REPORTED: THE NOSE GEAR STEERING DISCONNECTED ON TAXI OUT (SCISSOR S). MAINTENANCE RECONNECTED THE NOSE GEAR STEERING TORQUE LINK (SCISSORS). 2 L 7 2 4F 4 F RT A21EA E15NE 2001011105177 20010111 05177 EA 2001 1 11 CA000919005 1 20000831 G 5270 HANDLE CNDAIR CL6002B19 CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE PAX DOOR FAILED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 7067 (CAN) CREW REPORTED PAX DOOR OUTER HANDLE MSG POSTED AFTER TAKEOFF. A/C RETURNED TO FRESNO, CA. MAINTENANCE CONFIRMED GR OUND CHECKS NORMAL. 2 L 7 2 4F 4 F RT A21EA E15NE 2000113000001 20001130 00001 NE 2000 11 30 CA000919006 2 20000818 G 8530 71167 EXHAUST VALVE PWA DHAV DHC3 DHC3 2800202 EA PWA R1340 S3H1G 52016 NE STEM MEET HEAD BROKEN W A UNSCHED LANDING E B VIBRATION/BUFFET SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA 769 22910 (CAN) THE AIRCRAFT WAS CRUISING AT 4500 ASL WHEN THE ENGINE BEGAN RUNNING ROUGH, SOME SMOKE WAS SEEN, THE ENGINE WAS SH UT DOWN AND A SUCCESSFUL FORCED LANDING WAS CARRIED OUT ON A LAKE 26.5 NM SOUTH OF PUVIRNITUQ, QUEBEC. INVESTIGATION IN TO THE CAUSE FOUND THAT THE VALVE HEAD OF NR 2 CYLINDER EXHAUST HAD SEPARATED AND BEAT ABOUT THE PISTON AND CYLINDER HEA D UNTIL THE CYLINDER HEAD FINALLY CRACKED OPEN. NR 2 CYLINDER AND PISTON ASSEMBLY WERE REPLACED. ENGINE WAS GROUND RUN AND FOUND SERVICEABLE. (X) 1 H 7 1 3R 3 R A815 E142 2001030800017 20010308 00017 EA 2001 3 8 CA000919007 1 20000831 G 2760 4916405 CONTROL UNIT CNDAIR CL600 CL6002B19 EA SPOILER FAILED W C ABORTED TAKEOFF F FLT CONT AFFECTED TO TAKEOFF 1 CA (CAN) THE CREW CARRIE OUT AN AIR TURNBACK AND RETURNED TO MADRID. THE CREW REPORTED: SPOILERONS, FLIGHT SPOILERS AND GRO UND SPOILERS FAULTS ON THE EICAS.MAINTENANCE RPLACED THE SECU NR 2. 2 L 7 2 4F RT A21EA 2001030800018 20010308 00018 EA 2001 3 8 CA000919008 1 20000826 G 2742 83963 ACTUATOR CNDAIR CL600 CL6002B19 EA HORIZONTAL STAB FAILED W C ABORTED TAKEOFF F FLT CONT AFFECTED TO TAKEOFF 1 CA (CAN) PRIOR TO DEPARTURE, HORIZONTAL STABILIZER CHANNEL NR 2 WOULD NOT ENGAGE. FOUND MOTOR NR 2 FAULT. SENT A/C TO HANGA R, REPLACE HSTA AND MCU. DURING REPLACEMENT, FOUND RESTRICTED MOVEMENT OF STAB SURFACE. PIVOT PIN WAS BINDING. SENT AIRC RAFT TO MAINTENANCE FACILITY TO PERFORM STRUCTURAL REPAIRS. 2 L 7 2 4F RT A21EA 2001030800019 20010308 00019 EA 2001 3 8 CA000919009 1 20000827 G 5270 840534 PROXIMITY SWITCH CNDAIR CL600 CL6002B19 EA PAX DOOR FAILED W O OTHER N FALSE WARNING NR NOT REPORTED 1 CA (CAN) FLIGHT CREW REPORTED A PAX DOOR MESSAGE APPEARED IN ASSOCIATION WITH THE STOW HANDLE CAUTION, INTERMITTENTLY. REPL ACED PROXIMITY SENSOR DI-16. 2 L 7 2 4F RT A21EA 2001030800020 20010308 00020 EA 2001 3 8 CA000919010 1 20000827 G 3234 601R509677 HANDLE CNDAIR CL600 CL6002B19 EA COCKPIT BROKEN W O OTHER O OTHER AP APPROACH 1 CA 657 (CAN) UPON GEAR DOWN SELECTION ON APPROACH, THE LANDING GEAR HANDLE BROKE OFF. AN EMERGENCY WAS DECLARED, MANUAL RELEASE OF THE LANDING GEAR WAS PERFORMED AND LANDING WITH NO FURTHER EVENTS.THE HANDLE ASSEMBLY WAS REPLACED, A/C BACK IN SERV ICE.AN AD IS BEING ISSUED TO ADDRESS THIS PROBLEM. 2 L 7 2 4F RT A21EA 2001030800021 20010308 00021 NE 2001 3 8 CA000919011 2 20000831 G 7261 ENGINE CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE RIGHT LEAKING W A UNSCHED LANDING K FLUID LOSS CR CRUISE 1 CA (CAN) FLIGHT NR 5737 FROM CVG TO MSN, THE FLIGHT CREW RPORTED: THE RIGHT ENGINE OIL PRESSURE WARNING ILLUMINTED IN FLIGH T. ENGINE WAS SHUT DOWN AS PER QRH PROCEDURE: DECLARED EMERGENCY LANDING AND RETURNED TO THE DEPARTURE AIRPORT. THE LAND ING WAS UNEVENTFUL. MAINTENANCE REPLENISHED THE OIL SYSTEM. T/S ONGOING. 2 L 7 2 4F 4 F RT A21EA E15NE 2001030800022 20010308 00022 NE 2001 3 8 CA000919012 2 20000824 G 7200 ENGINE CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE LEFT FAILED W E A ENGINE SHUTDOWN UNSCHED LANDING O OTHER CL CLIMB 1 CA (CAN) FLIGHT NR 6047 FROM (LGA) TO (BUF) CLIMBING THROUGH 17,000 FT LEFT ENGINE FAILED. MADE A SINGLE ENGINE LANDING WIT HOUT INCIDENT. CREW DECLARED AN EMERGENCY AND MADE AN UNSCHEDULED LANDING INTO (AVP).SENT MECHANICS, FOUND BLADES MISSIN G ON LPT. STILL INVESTIGATING. 2 L 7 2 4F 4 F RT A21EA E15NE 2001030800023 20010308 00023 2001 3 8 CA000919013 4 20000824 G 3418 601R550221 SENSOR CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE LT/RT AOA FAILED W C ABORTED TAKEOFF N FALSE WARNING TO TAKEOFF 1 CA (CAN) FLIGHT NR 5979 FROM (CVG) TO (GRR), THE FLIGHT CREW REPORTED: DURING TAKEOFF ROLL AT APPROXIMATELY 80 KTS, THE STA LL FAIL MSG ILLUMINATED (TAKEOFF ABORTED)(SECOND ATTEMPT).MAINTENANCE REPLACED LT AND RT AOA SENSORS. 2 L 7 2 4F 4 F RT A21EA E15NE 2001030800024 20010308 00024 EA 2001 3 8 CA000919014 1 20000824 G 5610 NP1393215 WINDSHIELD CNDAIR CL600 CL6002B19 EA COCKPIT CRACKED W O OTHER O OTHER TX TAXI/GRND HDL 1 CA (CAN) DURING DELIVERY FLIGHT OF AIRCRAFT 7419, CIMBER UPON FIRST LANDING IN KEFLAVIK, ICELAND CAPT FWD WINDSHIELD MIDDLE PLY CRAACKED FROM THE USUAL AREA. CIMBER OBTAINED CONCESSION LETTER CO95-1652 TO BRING THE AIRCRAFT TO A REPAIR FACILIT Y.MAINTENANCE REPLACED THE WINDSHIELD. 2 L 7 2 4F RT A21EA 2001030800025 20010308 00025 NE 2001 3 8 CA000919015 2 20000824 G 7261 ENGINE CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE RT & LT FAILED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) IN FLIGHT. ENCOUNTERED EXTREME TURBULENCE, BOTH L/R ENGINE OIL PRESS WARNING MESSAGES APPEAED. IT WAS NEAR IMPOSS IBLE TO CONTROL THE AIRCRAFT. THE LANDING WAS UNEVENTFUL. SEVERE TURBULENCE INSPECTION CARRIED OUT, NO DAMAGE RPORTED (F DR WAS REMOVED FOR READOUT). 2 L 7 2 4F 4 F RT A21EA E15NE 2000113000002 20001130 00002 GL 2000 11 30 CA000920002 3 20000825 G 6114 HUB MCAULY MCAULY 2A34C D2A34C58 GL RETENTION THREAD CRACKED W O OTHER O OTHER IN INSP/MAINT 1 CA 1314 1116 763862 (CAN) CRACK FOUND IN RETENTION THREAD AREA DURING EDDY CURRENT INSPECTION AS SPECIFIED IN MCAULEY SB NR 205B INSTRUCTION S. (X) 5 C P3EA 2000101300109 20001013 00109 GL 2000 10 13 CA000920005 2 20000811 G 7261 23053298 TURBINE ALLSN HUGHES 500N 500N 3027374 SW ALLSN 25OC 250C20R GL OIL STRUT CARBONED W B EMER. DESCENT B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA 8778 2302 CAE295439 (CAN) DURING FLIGHT, A LOSS OF OIL PRESSURE AND TORQUE INDICATION WAS NOTED. AN IMMEDIATE LANDING WAS PERFORMED AND THE ENGINE WAS SECURED. THE ENGINE OIL LEVEL WAS CHECKED AND IT WAS THEN DISCOVERED THAT THE ENGINE OIL TANK WAS ENPT Y. THE PILOT STATED THAT HEAVY SMOKE WAS SEEN COMING FROM THE EXHAUST ON SHUT DOWN. THERE WAS NO DAMAGE TO THE AIRCRA FT. PILOT LANDED WITH POWER ON. (X) 1 G 7 1 3U 3 U NC H3WE E4CE 2000113000003 20001130 00003 CE 2000 11 30 CA000920006 1 20000822 G 3710 PUMP CESSNA 172 172L 2072432 CE LYC O320 O320E2D 41508 EA MCAULY 1C160 1C160CTM GL ENG REAR ACCY FAILED W O OTHER O OTHER CR CRUISE 1 CA 1356 (CAN) PUMP FAILED ABOUT HALF WAY DURING 1.7 HOURS FLIGHT TG3 TO CYXK. ALTERNATOR FAILURE FOLLOWED. ALTHOUGH PUMP TU RNED FREE BY HAND, BROKEN NYLON DRIVE SHOWED SIGNS OF PRE-FAILURE DETERIORATION. PUMP HAD 1356.1 HOURS, WAS INSTALLED NEW 7 APRIL 1977, CHECKED OK AT TSN: 1046.9 HOURS AT ENGINE OVERHAUL ON 21 MAR. 1996. AIRCRAFT FLOWN 309.2 HOURS IN LAS T 4 YEARS AND 5 MONTHS. AVERAGE OF 70.11 HOURS A YEAR. HANGARED 95 PERCENT OF TIME ON GROUND. PRIVATE OWNED. .REPLAC ED PUMP - NEW. REPLACED B3-5-1FILTER - AIR INLET. (X) 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2000113000004 20001130 00004 CE 2000 11 30 CA000920007 1 20000822 G 2497 DOFF103001 WIRE CESSNA 172 172L 2072432 CE LYC O320 O320E2D 41508 EA MCAULY 1C160 1C160CTM GL ALT TERMINAL FAILED W H DEACTIVATE SYST/CIRCUITS H ELECT. POWER LOSS-50 PC CR CRUISE 1 CA 2980 111 (CAN) ALTERNATOR NO CHARGE LIGHT CAME ON ABOUT HALF WAY DURING 1.7 HOUR FLIGHT FROM TG3 TO CYXK, JUST AFTER VACUUM PUMP FAILURE. PILOT SHUT DOWN ELECTRICAL SYSTEMS TO SAVE BATTERY POWER AND WAS ABLE TO PERFORM NECESSARY COMMUNICATIONS WIT H FSS ,AND TERMINATED FLIGHT AS INTENDED. PRELIMINARY INSPECTION DID NOT SHOW TROUBLE AS WIRES TIED IN BUNDLE AT VICIN ITY OF ALTERNATOR. BEGAN TO REMOVE ALTERNATOR. MAIN CABLE TERMINAL LUG FELL OFF THE END OF CABLE. REPLACED LUG. GROU ND RUN OK. (X) 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2000113000005 20001130 00005 EA 2000 11 30 CA000920008 2 20000821 G 7414 ES10382681 CAPACITOR BENDIX 1068218 PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA RT ENGINE SHORTED W A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CR CRUISE 1 CA 8010918 (CAN) AIRCRAFT DEPARTED RIMOUSKI AT 9 + 10, TO MADELEINA ISLANDS (FLIGHT DURATION ESTIMITATED 1.5 HRS), FLYING OFF SHOR E AT CHARLD N.B., RT ENGINE STARTED TO CUT-OUT MOMENTARILY. PILOT ELECTED TO TURN BACK, ENGINE CONTINUED COUGHING EVERY 5 MINUTES AND INDICATED HIGH OIL TEMP. LANDED AT 9 + 50. TOTAL AIR TIME 0176 A/C LOADED - CARGO). FOUND CAPACITOR IN RT MAG HAVING LOOSE SPRING AND WORN P-LEAD TIP. REPAIRED TIP AND REPLACED CAPACITOR RT. NOTE DATE ON CAPACITOR 93-07, HOWEVER, INSTALLED AT OVERHAUL ON 99/12/20. LT CAPACITOR DATED 92-35 WAS PREVIOUSLY REPLACED ON JULY 14, 2000. SUBMITT ER RECOMMENDED: TO MAKE MANDATORY REPLACEMENT OF CAPACITORS AT ENGINE T.B.O. AND O/H. (X) 1 L 7 2 3O 3 O A20SO E14EA 2001011105183 20010111 05183 SO 2001 1 11 CA000920009 1 20000817 G 8120 MS20500624 NUT LYC TIO540A2B PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2B 41532 EA TURBO CHARGER WRONG PART W O OTHER W INADEQUATE Q C NR NOT REPORTED 1 CA L286061A (CAN) NOT AN SDR - SEE PMI1. OVERHAULED TURBO CHARGER WAS INSTALLED AS SUPPLIED BY OVER HAULER, PREVIOUS REPORT, FOR TRO UBLE SHOOTING. 2. NEW MS20500-624 NUTS WERE ORDERED WITH ACCESSORY.3. SHOP SHIPPED MS21045-6 NUTS - HEAT RESISTING.4. WE CALLED OVER HAULER AS TO SIGNAL THAT HE SENT WRONG PARTS. HE APPEARED NOT AWARE OF DIFFERENCE BETWEEN THE TWO TYPES. 5. LYCOMING.P.C. SPECIFIES #MS20500-624.NOTE: MS 20500-624 =HART RESIST 1200 DEGREE F.MS 21045-6 = HEAT RESIST250 DEGREE F. IF WRONG TYPE UTILIZED, DAMAGE CAN BE INDUCED TO STUDS AT REMOVAL, UNSEEN & WHEN REINSTALLED, TURBO COULD EVENTUALLY COME LOOSE ON BASE. 1 L 7 2 3O 3 O A20SO E14EA 2000113000006 20001130 00006 SO 2000 11 30 CA000920010 1 20000811 G 8120 12A19770 BRACKET LYC PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2A 41532 EA LT LWR INBD BROKEN W O OTHER W INADEQUATE Q C IN INSP/MAINT 1 CA 551 L564261A (CAN) AT 246.2 HOURS TSO BOLT LW31S4.10 HAD BEEN FOUND SHEARED AND WAS REPLACED. AT 543.6 HOURS TSO, BOLT FOUND LOOSE . REMOVED. FOUND THAT BUSHING INSTALLED BY OVERHAULER IN THE DYNAFOCAL MOUNT BRACKET HAD PIECE OF FLANGE BROKEN. TEMPO RARY SHIMMED AND NEW BOLT INSTALLED. NEW BRACKET ORDERED. AT 550.6 HOURS: THIS TIME (U.0 HRS FLOWN WITH INSPECTION OF SHIMMED REPAIRED AT EVERY LANDING) (A/C FLOWN TO AVIOINICS SHOP FOR MAINTENANCE). NEW BOLT LW31S4.10, NEW NUT STD1420, AND NEW WASHERS STD 2197) INSTALLED, TORQUED, AND SAFETIED PER LYC S.I. NR 1384 AND A CERTIFIED BRACKET SUPPLIED BY OVE RHAULER INSTALLED. NOTE: SEE SDR - 14-08-00 FOR C-GPXW SIMILAR PROBLEM - SAME OVERHAULER. (X) 1 L 7 2 3O 3 O A20SO E14EA 2000113000007 20001130 00007 SO 2000 11 30 CA000920011 1 20000814 G 8120 LW31S444 BOLT LYC LW18302 PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA LWR OTBD LOOSE W O OTHER O OTHER IN INSP/MAINT 1 CA 481 (CAN) OUTBOARD TURBO MOUNT LOWER BOLT TO ENGINE DYNAFOCAL MOUNT BRACKET WAS FOUND LOOSE (HAND LOOSE) WITH PLAY IN MOUNT . HOWEVER, CUTTER PIN WAS INSTALLED. NO WASHER P/N STD 2197 BETWEEN NUT P/N STD 1420 AND FACE OF BOSS ON MOUNT P/N LW-1 8302 (SUPPORT ASSY) ON BOLT P/N LW-31S4.44. NO TORQUE ON NUT AND BOLT ASSY. CAUGHT IN TIME, NO SIGNIFICANT FRETTTING O N SUPPORT BOSS OR ON DYNAFOCAL MOUNT BRACKET. (X) 1 L 7 2 3O 3 O A20SO E14EA 2000113000008 20001130 00008 EA 2000 11 30 CA000920012 2 20000811 G 7313 25245008R INJECTOR PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA RT ENGINE DIRTY W C D ABORTED TAKEOFF RETURN TO BLOCK R PARTIAL RPM/PWR LOSS TO TAKEOFF 1 CA 481 65298 (CAN) 1. RIGHT ENGINE DEVELOPED ONLY 2300 RPM AT MAX M.P. ON TAKEOFF. COULD NOT DUPLICATE ON GROUND RUN. INVESTIGATED ENGINE AND PROP SYSTEMS. FUEL SERVO FUEL INLET SCREEN SHOWED SMALL PARTICLES. CLEANED. FUEL SYSTEM - AIRCRAFT - MAIN BOWL SCREEN SHOWED SMALL PIN HEAD PARTICLES - NO IMPORTANT QUANTITY. RT FUEL TANKS DRAINED - CLEAR. GROUND RUN AND RE TURNED TO SERVICE. REF: SEE ALSO SDR CA00920014. (X) 1 L 7 2 3O 3 O A20SO E14EA 2000113000009 20001130 00009 EA 2000 11 30 CA000920013 2 20000811 G 7322 SERVO PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA FUEL TANK CAP INTERFERENCE W O OTHER R PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 CA (CAN) RECENTLY REMOVED AS UNSCHEDULED, A FUEL SERVO FROM THE A/C ENGINE FUEL INJECTION SYSTEM, AS MIXTURE WOULD NOT CLO SE PROPERLY. TEAR DOWN INSPECTION: OVERHAULER INFORMED US HE HAD FOUND SMALL PARTICLES OF BLUE THIN PLASTIC-PAPER IN S CREEN AND UNDER MIXTURE INTERNALMACHANISM. IDENTIFIED TO OCTANE RATING DECAL OF PLACARDS, SOLD AT LARGE ON THE AVIATION MARKET. REFUELERS DRAG THE REFUELING NOZZLE OR/AND FUEL CAPS ON DECAL AND TEAR SMALL PIECES THAT GOES INTO THE TANKS; HENCE, INJECTOR PROBLEMS AND FUEL DRAIN COCKS PROBLEMS. REMOVED AND INSTALLED PROPER RECTANGULAR PLACARDS - ABOVE FUEL FILLERS. (X) 1 L 7 2 3O 3 O A20SO E14EA 2000113000010 20001130 00010 EA 2000 11 30 CA000920014 2 20000816 G 7414 1068291018 MAGNETO PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA RT ENGINE MISINSTALLED W A UNSCHED LANDING W R INADEQUATE Q C PARTIAL RPM/PWR LOSS TO TAKEOFF 1 CA 484 8010918 (CAN) FUEL SYSTEM CONTAMINATION. LEAVING GROUND ON TAKEOFF, RT ENGINE AGAIN SURGED, COMMITTED TO CONTINUE TAKEOFF - PI LOT COMPLETED CIIRCUIT BACK TO BASE. NOTE: SINCE LAST REPAIR; CLEANING FUEL, A/C HAD FLOWN TWICE FOR 3-4 HOURS , NO IN CIDENT. AGAIN, FOUND SOME LEFT OVER PARTICLES IN FUEL. AFTER REPAIRS: RUN-UP OK, BUT AMES EXPERIENCED EARS DETECTED SOME PUFFING UNEVEN. MAGNETO TIMING CHECKED: SHOWED (DUAL MAG) 17 - 15 DEGREE BTDC. RETIMER: LT AT 20 DEGREES PER M AN. GIVING RT 18 DEGREES IN LIMITS OF 3 DEGREES. REPLACED LOWER PLUGS. GROUND RUN OK. AIRCRAFT IN-FLIGHT AT THIS TIM E. (X) 1 L 7 2 3O 3 O A20SO E14EA 2000113000011 20001130 00011 EA 2000 11 30 CA000920015 2 20000815 G 8520 75060 BOLT LYC LW10646 BEECH 60 B60 1153605 CE LYC O541 TIO541E1C4 41536 EA SHANK SHEARED W A E UNSCHED LANDING ENGINE SHUTDOWN T E E ENGINE CASE PENETRATION VIBRATION/BUFFET VIBRATION/BUFFET CR CRUISE 1 CA 1993 (CAN) THE NR 3 CYLINDER CONNECTING ROD BOLT FAILED DUE TO FATIGUE, OR DEFECTIVE MATERIAL. 1 L 7 2 3O 3 O A12CE E10EA 2000113000012 20001130 00012 EA 2000 11 30 CA000921002 1 20000625 G 2700 C3CF2179 CABLE DHAV DHC3 DHC3 2800202 EA FLAP CNTRLS CORRODED W O OTHER O OTHER IN INSP/MAINT 1 CA (CAN) AIRCRAFT SUNK IN SALT WATER ON A MOORING IN NAIN LABRADOR. AIRCRAFT SALVAGED AND FLOATED. AIRCRAFT FLUSHED WITH FRESH WATER, INSTRUMENTS CHANGED, ENGINE COMPONENTS CHANGED, AIRCRAFT READIED FOR FERRY FLIGHT USING PROCEDURES IN ACCO RDANCE WITH CARS 625 APP. G. CORROSION FOUND (SEVERE) IN FOLLOWING BELLCRANKS - FLAP CONTROLS, AILERON AND RUDDER CONTR OLS. P/N''''S AFFECTED AND REPLACED BEFORE FLIGHT: (1). C3CF217-9. (2). C3CF217-10. (3). C3CF218-9. (4). C3CF218- 10. (5). C3CF40-116. C3CF77-5 7. C3CF37-5. (X) 1 H 7 1 3R A815 2001030900001 20010309 00001 SO 2001 3 9 CA000921003 1 20000808 G 3246 16200600 WHEEL PIPER PA22 PA22135 7102206 SO LYC O320 O320B2A 41508 EA MLG CRACKED W K NONE D INFLIGHT SEPARATION TX TAXI/GRND HDL 1 CA 2556 (CAN) WHEEL HALF DISCOVERED WITH A PIECE MISSING AND THE WITH TIRE & TUBE BULGING OUT IN THAT AREA. 1 H 7 1 3O 3 O 1A6 E274 2001030800027 20010308 00027 EA 2001 3 8 CA000921004 2 20000808 G 7300 3032125 LINE PWA PT6A65B BEECH 1900 1900C 1154161 CE PWA PT6 PT6A65B 52043 EA P3 CRACKED W A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CL CLIMB 1 CA 5600 PCE32182 (CAN) ENGINE WENT TO FLIGHT IDEL JUST AFTER TAKE OFF ALONG WITH RESULTANT AUTOFEATHER AFTER TORQUE DROPPED BELOW 250 LBS . P3 LINE CRACKED AT FLARE. 2 L 7 2 4T 4 T RT A24CE E4EA 2001030800028 20010308 00028 SW 2001 3 8 CA000921005 1 20000814 G 6510 407340340101 DISC PACK BELL 407 407 SW TAIL ROTOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CRACKS ON FORE AND AFT OUTER DISC SEGMENTS. INSTALLED AT 1202.8 HOURS, DECEMBER 12, 1999. NR 7 BEARING INSTALL ED AT 1060.2 HOURS, SEPTEMBER 17, 1999. NR 3 BEARING (UNDER OIL COOLER). 1 G 7 1 3U O H2SW 2001030800029 20010308 00029 SW 2001 3 8 CA000925002 1 20000605 G 2810 50061530000001 FUEL TANK KAMOV KA32 KA32A1 SW FUSELAGE LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 5311 (CAN) FUEL LEAK.NOTE: TANK P/N 500.6154.000.001 S/N 9106808 WAS REPLACED (CHAFED), ALSO BECAUSE IT IS INTER-CONNECTED T O TANK P/N 500.6153.0000.001. 1 G 7 2 4U NC 2000101600355 20001016 00355 SW 2000 10 16 CA000925003 1 20000512 G 6220 D2B211002 BEARING D2B200000B KAMOV KA32 KA32A1 SW FLAP HINGE BRG FAILED W A UNSCHED LANDING O OTHER CR CRUISE 1 CA 887 920018 (CAN) ROTOR SYSTEM VIBRATION, METAL NOTICED IN OIL AT OIL CHANGE MAINTENANCE. 1 G 7 2 4U NC 2000101600356 20001016 00356 SW 2000 10 16 CA000925004 1 20000512 G 6320 BP252 GEARBOX KAMOV KA32 KA32A1 SW MAIN GEARBOX CONTAMINATED W A UNSCHED LANDING J WARNING INDICATION NR NOT REPORTED 1 CA 971 0703003 (CAN) METAL CONTAMINATION: THREE CONSECUTIVE CHIP LIGHTS, GEARBOX REMOVED. (X) 1 G 7 2 4U NC 2000113000013 20001130 00013 CE 2000 11 30 CA000925005 1 20000731 G 3230 MC815AS1 MOTOR BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA MOTOR CONTROLLER STUCK W A UNSCHED LANDING O OTHER CL CLIMB 1 CA (CAN) LANDING GEAR WOULD NOT RETRACT WHEN SELECTED. (X) 1 L 7 2 4T 4 T A24CE E4EA 2000101600357 20001016 00357 NE 2000 10 16 CA000925006 2 20000809 G 7321 216062022 FUEL CONTROL LYC BELL 214 214B1 1182105 SW LYC T55 T5508D 41555 NE N2 GOVERNOR WORN W K NONE E VIBRATION/BUFFET IN INSP/MAINT 1 CA 5283 1801 (CAN) PERIODIC ENGINE N2 DROOP WITH POWER APPLICATION WITH SLOW RECOVERY WAS REPORTED. DURING SUBSEQUENT TROUBLESHOOTIN G, N2 DROOPED WITH NO NR RECOVERY UNTIL COLLECTIVE WAS CYCLED SEVERAL TIMES. N2 LEVER ON FUEL CONTROL UNIT APPEARS TO B E ROUGH WHEN CYCLED BY HAND. THE NOTED FCU WAS REMOVED AND REPLACED WITH A SERVICEABLE UNIT. (X) 2 G 7 1 4U 4 U H6SW E4NE 2001030800030 20010308 00030 NE 2001 3 8 CA000925007 2 20000815 G 8520 BEARING PWA WASPCB3 DOUG DC6 DC6A 3021706 WP PWA R2800 CB3 52026 NE HAMSTD 43E 43E60 NE MASTER ROD FAILED W D RETURN TO BLOCK Y ENGINE STOPPAGE TO TAKEOFF 1 CA 1038 55249 (CAN) ON TAKEOFF ENGINE AUTO-FEATHERED, AND LOAD OF RETARDANT WAS JETTISONED. AIRCRAFT RETURNEDTO AIRPORT WITH THREE EN GINES OPERATIVE. INSPECTIONS COMPLETED - I.E. NOSE CASE REMOVED AND CHIPPED TEETH FOUND ON COUNTER BALANCE DRIVE GEARS A ND THE SUPPORT BEARING WAS FOUND CRACKED. ENGINE WAS RE-ASSEMBLED FOR THREE ENGINE FERRY. NOSE CASE WAS AGAIN REMOVED TO DETERMINE EXTENT OF DAMAGE. DAMAGE FOUND INDICATED A MASTER ROD BEARING FAILURE WHICH RESULTED IN THE MASTER ROD COMING LOOSE AND DAMAGING THE REAR CYLINDERS. SERVICEABLE ENGINE INSTALLED AND AIRCRAFT DISPATCHED FOR FIRE FIGHTING. 2 L 7 4 4R 4 R 6A3 E264 6 C P871 2001030800031 20010308 00031 WP 2001 3 8 CA000925008 1 20000826 G 2752 5363998403 BRACKET DOUG DC6 DC6A 3021706 WP HAMSTD 43E 43E60 NE ACTUATOR BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHILE COMPLETING THE ROUTNE A INSPECTION THE OUTBOARD FLAP ACTUATOR ATTACHMENT ARMS WERE FOUND BROKEN. THE AIRCRAF T WAS GROUNDED UNTIL THE FLAP WAS REPLACED. PARTS ARE BEING SHIPPED BACK TO CONAIR FOR INSPECTION.ALL ACTIVE AIRCRAFT IN SPECTED AND FOUND SERVICEABLE. 2 L 7 4 4R 6A3 6 C P871 2001030800032 20010308 00032 2001 3 8 CA000925009 4 20000901 G 3414 4039891903 INDICATOR HONEYWELL BOEING 767 7673S1 1385211 NM COCKPIT FAILED W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA 32336 897 89031649 (CAN) FIRST OFFICERS AIRSPEED FAILED AT 60 KNOTS ON TAKEOFF ROLL. REJECTED TAKEOFF AT 100 KNOTS. FIRST OFFICERS AIRSPEED INDICATOR REPLACED . WHEELS AND TIRES INSPECTED AS PER FLYAWAY MANUAL 2.02-05.02, DUE RTO, NO DAMAGE FOUND, BRAKE TEMP INDICATIONS NORMAL. 2 L 7 2 4F RT A1NM 2001030800033 20010308 00033 NM 2001 3 8 CA000925010 1 20000901 G 5280 DOOR BOEING 767375 BOEING 767 767375 NM GE CF6 CF680C2B6 30025 NE RT MLG DOOR DAMAGED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 24083 (CAN) AIRCRAFT DEPARTED, CDL32-12A APPLIED PIOR TO DEPARTURE DUE R/H GEAR TRUNNION DOOR DAMAGE. CDL INDICATED A MINOR AI RCRAFT WEIGHT PENALTY. VMO/MMO SWITCH PLACED IN ALTERNATE POSITION DUE CDL. ON AKEOFF, (APPROX 250 KTS) OVERSPEED AURAL WARNING AND BARBER POLE WARNINGS INDICATED. FLIGHT CREW CONTACTED DISPATCH AND MOC, IT WAS NOTED THAT WITH VMO/MMO SWITC H IN ALTERNATE POSITION SPEED IS LIMITED TO 260 KTS. DECISION WAS MADE TO RETURN, DUE SPEED RESTRICTIONS ON AIRSPEED IN CRUISE. AIRCRAFT LANDED YVR NORMALLY. DOOR REPAIRS COMPLETED AS PER LOG SEQUENCE 0304937. OVERWEIGHT LANDING CHECK COMPL ETED AS PER FLYAWAY MANUAL.. 2 L 7 2 4F 4 F RT A1NM E13NE 2000101600358 20001016 00358 NE 2000 10 16 CA000925011 1 20000816 G 6410 S611730101045 BLADE SKRSKY S61 S61N 8142104 NE GE CT58 CT581401 30011 NE TAIL ROTOR BLADE CRACKED W K NONE P NO WARNING INDICATION IN INSP/MAINT 1 CA 18854 61VR18181785 (CAN) THE T/R SPINDLE INSPECTION WAS BEING C/O AT WHICH TIME A CRACK IN THE SKIN OF THE TAIL ROTOR BLADE WAS DISCOVERED. THE BLADE WAS REMOVED FROM SERVICE AND IMMEDIATELY SENT BACK TO THE MANUFACTURER FOR REPAIR EVALUATION. (X) 2 G 7 2 4U 4 U 1H15 1E3 2000101800126 20001018 00126 NE 2000 10 18 CA000925012 1 20000818 G 6320 S613520670 GEARBOX SKRSKY S61352060004 SKRSKY S61 S61N 8142104 NE GE CT58 CT581401 30011 NE M/R TRANS CRACKED W K NONE K FLUID LOSS NR NOT REPORTED 1 CA 97 A14D2667789 (CAN) OIL LEAK WAS DETECTED ON RIGHT HAND FORWARD SIDE OF MAIN GEARBOX. AFTER FURTHER INVESTIGATION, FOUND THERE WAS A CRACK IN THE LOWER HOUSING ASSY. THE CRACK WAS 2.75 INCHES LONG AND LOCATED APPROXIMATELY 4 INCHES ABOVE AND FORWARD OF THE FORE AND AFT SERVO BRACKET. THE AIRCRAFT WAS THEN GROUNDED AND THE GEARBOX ASSY WAS REMOVED AND SENT FOR REPAIR. (X) 2 G 7 2 4U 4 U 1H15 1E3 2000101900278 20001019 00278 NE 2000 10 19 CA000925024 1 20000905 G 2910 7665104001051 HYDRAULIC LINE SKRSKY S76 S76A 8143006 NE ALLSN 250C 250C30S 03013 GL MAIN HYD SYS LEAKING W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION HO HOVERING 1 CA (CAN) PRIOR TO TAKEOFF, NR 1 SERVO JAM LIGHT CAME ON. NR 1 HYDRAULIC SYSTEM LEVEL HAD DROPPED TO THE REFILL LINE AND A CTIVATED THE LOW LEVEL SWITCH. AFTER REMOVAL OF T/R COWLS, HYD FLUID WAS WIPED UP BUT NO CRACK COULD BE SEEN - FLUID LEV EL WAS TOPPED UP AND A/C WAS GROUND RUN AT 3000 PSI. FLUID WAS LEAKING FROM HYD LINE AT 6 INCHES FROM T/R SERVO. LINE WAS CHANGED AND GROUND RUN CHECKED SERVICEABLE. (PORUS SECTION WHERE LEAK IS, IS NOT VISIBLE TO NAKED EYE). (X) 1 G 7 2 3U 3 U H1NE E1GL 2001011105596 20010111 05596 NM 2001 1 11 CA000925025 1 20000820 G 2750 CONTROL UNIT BOEING 767375 BOEING 767 767375 NM TE FLAPS FAULTY W O OTHER J WARNING INDICATION CR CRUISE 1 CA 25120 (CAN) A/C 641, AUG 20/2000, FLT 30, LOG SEQUENCE 0225444. AT APPROXIMATELY 14,000 FEET, LEADING EDGE SLAT ASYMMETRY WARN ING ILLUMINATED ON EICAS, FLAP POSITION NEEDLE INDICATED BETWEEN 1 UNIT AND UP. RETURNED TO PEK. BITE CHECK COMPLETED ON PSEU, NIL FAULTS INDICATED. SLATS AND FLAPS EXTENSION CHECKED SEVERAL TIMES NO FAULTS FOUND. COCKPIT INDICATION CHECKED OK. 2 L 7 2 4F RT A1NM 2000101900279 20001019 00279 SW 2000 10 19 CA000925028 1 20000818 G 6310 206040106003 SPRING BELL 206040015103 BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL T/R DRIVE SHAFT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 10443 AMN52117 (CAN) 600/YEARLY INSPECTION BEING CARRIED OUT ON MAIN DRIVESHAFT. UPON REMOVAL OF COUPLING CAP, FOUND SPRING BROKEN IN A DOZEN PIECES. THE PIECES DAMAGED THE INNER COUPLING RENDERING IT UNSERVICEABLE. THE CAP, SPRING AND INNER COUPLING WE RE SCRAPED. (X) 1 G 7 1 3U 3 U H2SW E4CE 2000102000042 20001020 00042 SW 2000 10 20 CA000925029 1 20000830 G 6330 212040106103 MOUNT BELL 212 212 1181420 SW PWA PT6T PT6T3 52045 EA M/R TRANSMISSION CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) IN THE PROCESS OF CHANGING WEAK TRANSMISSION LORD MOUNTS, FOUND A CRACKED LIFT LINK (FITTING) MOUNT. THE RIGHT FO RWARD EAR WAS CRACKED. THE FITTING IS ON THE TRANSMISSION. THE DAMPERS WERE WEAK ALSO. (X) 1 G 7 1 4U 4 U H4SW E22EA 2000102700108 20001027 00108 SW 2000 10 27 CA000925030 1 20000911 G 6720 206010793101 PITCH LINK BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL ROD END BRG WALL CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CRACK DISCOVERED DURING DAILY INSPECTION. (X) 1 G 7 1 3U 3 U H2SW E4CE 2000113000014 20001130 00014 CE 2000 11 30 CA000925032 1 20000911 G 2750 0512128 PULLEY BRACKET CESSNA 180 180H 2072618 CE CONT O470 O470R 17026 SO UNDER FLOOR BROKEN W O OTHER F I FLT CONT AFFECTED FLT. ATTITUDE INST. AP APPROACH 1 CA 5742 (CAN) A BROKEN FLAP CONTROL CABLE PULLEY BRACKET CAUSED THE RIGHT FLAP EXTEND CABLE TO GO SLACK, RESULTING IN THE RIGHT FLAP PANEL PARTIALLY RETRACTING. THE AIRCRAFT EXPERIENCED AN UNCOMMANDED ROLL TO THE RIGHT AND THE PILOT HAD TO RETRAC T THE FLAPS TO RECOVER A LEVEL FLIGHT ATTITUDE. THE PILOT THEN CARRIED OUT AN UNEVENTFUL FLAPLESS LANDING. (X) 1 H 7 1 3O 3 O 5A6 E273 2000113000015 20001130 00015 SO 2000 11 30 CA000925033 2 20000823 G 8530 642167A1 CRANKCASE CONT IO470S CESSNA 210 2105 2073404 CE CONT O470 IO470S 17026 SO MCAULY 2A34C D2A34C49 GL LTCRANKCASE CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 1202 CSIO23832S (CAN) OIL LEAK TRACED TO CYLINDER HOLD DOWN AREA OF NR 2 CYLINDER. LARGE CRACK FROM 3 O''CLOCK POSITION. NR 2 CYLINDER UP TO 11 O''CLOCK. (X) 1 H 7 1 3O 3 O 3A21 3E1 5 C P3EA 2000113000016 20001130 00016 NE 2000 11 30 CA000925034 2 20000826 G 7322 P19248 HOUSING A302503 GRUMAV G21 G21A 3951204 SO PWA R985 R985AN14B 52008 NE BLW THRTLE SHAFT CRACKED W K NONE R PARTIAL RPM/PWR LOSS TX TAXI/GRND HDL 1 CA 705 5715901 (CAN) CRACK LINE DEVELOPED AT MIXTURE ADJUSTING LEVER ONE INCH BELOW THE THROTTLE SHAFT AND PROPAGATED IN A HORIZONTAL D IRECTION AROUND THE CIRCUMFERENCE OF THE THROTTLE BODY UNIT. ENGINE DEVELOPED AN IDLING PROBLEM AND ON INSPECTION, CRAC K FAULT WAS DETECTED. SUBMITTER SUSPECTED THE FAULT CAUSE TO BE CASTING FLAW OR MECHANICAL DAMAGE. CARBURETOR RETURNED TO OVERHAUL FACILITY FOR REPAIR AND DAMAGE INVESTIGATION. (X) 1 H 7 2 3R 3 R TC654 5E1 2001030800050 20010308 00050 EU 2001 3 8 CA000926005 1 20000906 G 5270 4HS26 SWITCH FOKKER A33200401 FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU AFT CARGO DOOR MALFUNCTIONED W K NONE N FALSE WARNING CL CLIMB 1 CA (CAN) PILOTS RPTED OUTBOUND THAT CARGO DOOR WARNING LIGHT CAME ON AT 4.4 PSI DIFFERENTIAL. A/C RETURNED & LANDED W/O INC ID..MAINT INSP FOUND WIRING ON REAR CARGO DOOR HANDLE SWITCH CHAFED & GROUNDING OUT ON WARNING CCT. WIRING REPD IN ACCOR D WITH APPLICABLE STANDARDS OF A/W & A/C DEEMED SERVICEABLE FOR TEST FLT. CARGO DOOR LIGHT CONTINUED TO ILLUMINATE ON TE ST FLT - A/C RETURNED TO BASE & LANDED W/O INCID..MAINT REPLD REAR CARGO DOOR HANDLE SWITCH & GROUND PRESSURIZED A/C TO 6.6 PSI DIFFERENTIALWITH NO FAULTS TO RPT. TEST FLT SUCCESSFULLY COMPLETED. A/C RT-SRV WITH NO FURTHER INCID. TO RPT. 2 L 7 2 4F 4 F RT A20EU E2EU 2000113000017 20001130 00017 EU 2000 11 30 CA000926006 1 20000910 G 2752 951D10011 ACTUATOR PILATS PC12 PC1245 EU FLAP ACTUATOR WORN W K NONE O OTHER IN INSP/MAINT 1 CA 302 0186AB (CAN) ON INSPECTION, THE BACKLASH WAS FOUND EXCESSIVE. (X) 1 L 7 1 3T RT A78EU 2001030800051 20010308 00051 EU 2001 3 8 CA000926007 1 20000801 G 3246 AH52689 WHEEL BAG JETSTM JETSTM3101 1500215 EU ROTOL R333 R333482F12 GL MLG DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHEEL DISASSEMBLED FOR TIRE REPLACEMENT NOTED TO HAVE IMPACT DAMAGE 70.032 IN AND GAUGE AROUND WHEEL BEARING BOSS. IMPACT DAMAGE BEYOND LIMITS. WHEEL SCRAPPED. APPEARS TO HAVE BEEN CAUSED BY BRAKE ASSY - NO OBVIOUS DEFECTS. 2 L 7 2 4T RT A21EU 6 C P61GL 2000113000018 20001130 00018 EA 2000 11 30 CA000926008 1 20000820 G 2711 C6CW10861 SLEEVE DHAV DHC6 DHC6 2802606 EA PWA PT6 PT6A20 52043 EA HARTZL HCB3T HCB3T* GL SWAGED AREA MISSING W O OTHER O OTHER IN INSP/MAINT 1 CA (CAN) BOMBARDIER NOT IN COMPLIANCE WITH AIRWORTHINESS DIRECTIVE CF-80-03R. SLEEVE MISSING FROM SWAGED AREA OF ROD ENDS. ROD PURCHASED NEW AS A SPARE PART. (X) 1 H 7 2 3T 3 T RT A9EA E4EA 6 C P15EA 2000112100001 20001121 00001 NE 2000 11 21 CA000926011 2 20000509 G 7320 117024093 REGULATOR BELL 205 205A1 1181414 SW LYC T53 T5313B 41549 NE FUEL REGULATOR FAILED W O OTHER E VIBRATION/BUFFET HO HOVERING 1 CA 702AS9102 (CAN) - BLEED BAND OPENED WITH COLLECTIVE PITCH UP AND TORQUE INDICATOR SPIKED AND N1 SPOOL UP. BLEED BAND WOULD NOT C LOSE. N1 TOPPED UP AND TORQUE STAYS LOW. REPLACED BLEED BAND ACTUATOR WOULD NOT SOLVE PROBLEM. PROBLEM WAS FIXED WITH REPLACEMENT OF FUEL REGULATOR . (X) 1 G 7 1 4U 4 U H1SW E17EA 2000112200001 20001122 00001 SW 2000 11 22 CA000926012 1 20000511 G 7332 8G506 SWITCH BELL 205 205A1 1181414 SW LYC T53 T5313B 41549 NE FUEL PRESS SW FAILED W O OTHER J WARNING INDICATION IN INSP/MAINT 1 CA 6044 (CAN) FUEL PUMP CAUTION LIGHT ILLUMINATED AFTER REPLACING FUEL REGULATOR. REPLACED PRESS SWITCH. CHECKED THIS SWITCH. CIRCUIT WAS CLOSED WITH PRESSURE. (X) 1 G 7 1 4U 4 U H1SW E17EA 2001030800053 20010308 00053 SO 2001 3 8 CA000926013 2 20000626 G 8530 GO300D ENGINE CESSNA 172 P172D 2072202 CE CONT O300 GO300E 17022 SO MCAULY 1B175 1B175* GL ENGINE BAY FAILED W B E EMER. DESCENT ENGINE SHUTDOWN E J VIBRATION/BUFFET WARNING INDICATION CL CLIMB 1 CA 2055 3 (CAN) - ENGINE INSTALLED AFTER OVERHAUL GROUND RUNS COMPLETED, STATIC R.P.M., 0.1 PRESSURE AND OIL TEMPERATURE NORMAL, ENGINE CONTROLS FUNCTIONING NORMAL.- FIRST FLIGHT WAS APPROXIMATELY 12 MINUTES AIR TIME AND SEEMED TO RUNSMOOTHLY. - SE COND FLIGHT WAS CONDUCTED AND AIRCRAFT STARTED TO MAKE NOISES AND VIBRATE DURING THE LEFT TURN OUT FROM THE CIRCUIT. SH OT DOWN WAS COMPLETED AND PILOT WAS ABLE TO LAND AT AIRPORT. - ENGINE INSPECTION FOUND CENTRE CYLINDER ON PASSENGER SI DE, PISTON NOT MOVING. ENGINE REMOVED. 1 H 7 1 3O 3 O 3A17 E298 5 N P857 2000113000019 20001130 00019 CE 2000 11 30 CA000926014 1 20000824 G 2434 991059111 ALTERNATOR CESSNA 172 172R 2072401 CE ALTERNATOR SEIZED W K NONE B H SMOKE/FUMES/ODORS/SPARKS ELECT. POWER LOSS-50 PC CR CRUISE 1 CA 1249 A129346 (CAN) ALTERNATOR SEIZED. BELT PULLEY SHEARED FROM MAIN DRIVESHAFT. (X) 1 H 7 1 3O NT 3A12 2000113000020 20001130 00020 CE 2000 11 30 CA000926015 1 20000906 G 2750 65651203CR CONTROL CABLE CESSNA 500 560CESSNA 2076750 CE TE FLAP BROKEN W O OTHER F J FLT CONT AFFECTED WARNING INDICATION LD LANDING 1 CA 5936 (CAN) ON SELECTING FULL FLAPS, PILOT NOTED THAT HYDRAULIC PRESSURE LIGHT DID NOT EXTINGUISH AFTER FLAPS REACHED FULL POS ITION. DURING TAXI FOLLOWING LANDING, WHEN PILOT SELECTED TAKEOFF AND APPROACH POSITION, FLAP INDICATOR WOULD NOT RESPO ND. AFT FLAP PRE-SELECT CABLE FOUND BROKEN AT ZONE 272. (X) 2 L 7 2 4F RT A22CE 2000113000021 20001130 00021 SO 2000 11 30 CA000926016 1 20000710 G 5313 9947008 SKIN PIPER PIPER PA34 PA34220T 7103420 SO CONT O360 LTSIO360KB 17025 SO MCAULY 3AF32C 3AF32C508 GL INTEGRAL STRINGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 9264 348233048 (CAN) WHILE CARRYING OUT SB 856 (STABILATOR ATTACH FITTING CORROSION INSPECTION), NOTED THAT THE LOWER RIGHT INTEGRAL ST RINGER ON SKIN P/N 99470-08 WAS CRACKED COMPLETELY THROUGH. WHEN THE STABILATOR WAS MOVED FORE AND AFT, THERE WAS CONSI DERABLE MOVEMENT IN THE AREA THAT WAS CRACKED. POSSIBLE CAUSE FOR CRACK - DUE TO THE STEEL BRACKET AND EXTRUDED ANGLE NOT BEING TIED TOGETHER MAKING THE AREA IN BETWEEN WEAK. THIS AREA WAS REPAIRED BY INSTALLING AN .063 INCH ALUMINUM ANG LE TO TIE THE ATTACH FITTING AND THE EXTRUDED ANGLE TOGETHER PER APPROVED ENGINEERING DRAWINGS. NOTE: LT SKIN WAS NOT CRACKED, BUT WAS REPAIRED THE SAME TO PREVENT FURTHER CRACKS. (X) 1 L 7 2 3O 3 O A7SO E9CE 5 C P22EA 2000112200002 20001122 00002 SW 2000 11 22 CA000926017 1 20000914 G 6510 327211 DISC PACK BELL 327211 BELL 206 206BELL 1181502 SW ALLSN 250C 250C20 03013 GL MCAULY D3A34 D3A34C402 GL T/R DRIVE MISINSTALLED W O OTHER W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) WHILE INSPECTING A NEW PART PRIOR TO INSTALLATION, IT WAS NOTED THAT INDIVIDUAL DISCS WERE NOT CORRECTLY STACKED P ER BELL 206 MAINTENANCE MANUAL (FIGURE 65-6, PARAGRAPH 65-19 CAUTION COPY ATTACHED.) THE NOTE ATTACHED TO THE DISC SET S TATES THAT THEY MUST BE INSTALLED AS ONE UNIT EXACTLY AS PACKED. THREE DISC PACKS WERE FOUND MIS-STACKED. (X) 1 G 7 1 3U 3 U H2SW E4CE 5 C P47GL 2000113000023 20001130 00023 CE 2000 11 30 CA000927003 1 20000831 G 3231 08411065 BELLCRANK CESSNA 310 310R 2074245 CE CONT O520 IO520MB 17032 SO MCAULY 3AF32C 3AF32C87 GL ACTUATING ARM BROKEN W O OTHER O OTHER IN INSP/MAINT 1 CA (CAN) AFTER LANDING, PILOT NOTICED THAT THE GEAR DOOR ON THE LEFT MAIN WAS HANGING DOWN. AIRCRAFT WAS PLACED ON JACKS A ND GEAR DOOR BELLCRANK WAS FOUND TO BE BROKEN. PART WAS REMOVED AND NEW PART INSTALLED. GEAR SWING WAS COMPLETED 5 TIM ES AND GEAR DOOR WORKED CORRECTLY. COULD NOT DETERMINE WHY THE PART HAD BROKEN. THERE WAS NO EVIDENCE OF DAMAGE TO THE ASSEMBLY. (X) 1 L 7 2 3O 3 O 3A10 E5CE 5 C P22EA 2000113000024 20001130 00024 NE 2000 11 30 CA000927004 2 20000828 G 7321 324476812 FUEL CONTROL PWA BEECH 200 B200 1152922 CE PWA PT6 PT6A42 52043 NE FUEL CNTRL UNIT FAILED W E ENGINE SHUTDOWN E VIBRATION/BUFFET AP APPROACH 1 CA 2275 PCE94483 (CAN) UPON APPROACH TO YRT, PILOTS DISCOVERED NR 1 ENGINE WOULD NOT RESPOND TO POWER LEVER COMMANDS. AS A RESULT, THE P ILOTS HAD TO SHUT DOWN NR 1 ENGINE TO LAND. FCU WAS REPLACED. ENGINE GROUND TESTED SERVICEABLE. (X) 1 L 7 2 4T 4 T A24CE E4EA 2000120600029 20001206 00029 CE 2000 12 6 CA000927006 1 20000827 G 2750 51152531 SHAFT CESSNA 421 421C 2076016 CE CONT O520 GTSIO520L 17032 SO MCAULY 3FF32 3FF32C501 GL SIDE OF ACTUATOR LOOSE W D RETURN TO BLOCK F FLT CONT AFFECTED TX TAXI/GRND HDL 1 CA (CAN) THE FLAPS WOULD NOT MOVE DURING TAXI. PILOTS WERE ADVISED TO ENSURE THE FLAPS WERE RETRACTED, PULL AND SECURE THE FLAP CIRCUIT BREAKER, AND RETURN TO MAINTENANCE FLAPLESS FOR REPAIRS. MAINTENANCE FOUND THE INPUT ROD OR SHAFT THAT MOV ES THE CAM TO THE UP OR DOWN LIMIT SWITCH WAS LOOSE AND SLIPPING. THIS CAUSED THE FLAPS TO OVER RETRACT, CAUSING PULLEY PIN FAILURE ON THE ACTUATOR CHAIN GEAR, AND A PULLEY BRACKET TO BE DAMAGED. THE NECESSARY REPAIRS WERE MADE TO THE BRA CKET BY REPLACING THE BRACKET. INSPECTION OF FLAP ACTUATOR, FLAP CABLES, AND FLAP LINKS WAS CARRIED OUT. THE FLAPS WER E RERIGGED AND THE AIRCRAFT WAS RETURNED TO SERVICE. (X) 1 L 7 2 3O 3 O A7CE E7CE 5 C P45GL 2001032900049 20010329 00049 CE 2001 3 29 CA000927008 1 20000829 G 5753 FLAP TRACK CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA MCAULY 1C160 1C160CTM GL RT WING CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 5667 (CAN) THE ATTACHING PART BETWEEN THE FLAP TRACK AND LOWER WING SKIN WAS FOUND CRACKED DURING A ROUTINE INSPECTION. UPON INSPECTION OF ANOTHER AIRCRAFT OF THE SAME MODEL IT WAS FOUND THAT REINFORCING PART WERE NOT INSTALLED AT THE FACTORY O N SUBJECT AIRCRAFT. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2001031900163 20010319 00163 SO 2001 3 19 CA000927009 2 20000831 G 7310 LINE CESSNA 414 414 2075908 CE CONT O520 TSIO520NB 17040 SO FUEL SYSTEM CHAFED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) DURING GROUND HANDLING FUEL LEAK ON LT ENGINE WAS OBSERVED. FURTHER INVESTIGATION REVEALED THAT FUEL LINE BETWEEN FCU AND FUEL LIMITER WAS CHAFED THROUGH. TEMPORARY REPAIR TO FLY AIRCRAFT BACK TO HOME BASE. AT HOME BASE FUEL LINE REPL ACED BY NEW AND AIRCRAFT RETURNED TO SERVICE.ASSUMED REASON FOR DAMAGE: DISLOCATION DUE TO BROKEN BRACKET ON FUEL LIMITE R (REPLACED AS WELL), RESULTING IN CHAFING CONTACT WITH AIR BOX. 1 L 7 2 3O 3 O RT A7CE E8CE 2000120600030 20001206 00030 SO 2000 12 6 CA000927011 1 20000902 G 7603 S18193 ROD END PWA CURTIS C46 C46AAIRLIFT SO PWA R2800 R280051 52026 NE THROTTLE LINKAGE WORN W C E ABORTED TAKEOFF ENGINE SHUTDOWN O OTHER TO TAKEOFF 1 CA FPO65143 (CAN) DURING TAKEOFF OUT OF SANDY LAKE, THE PILOT NOTICED NR 1 THROTTLE SETTING LOOSE. HE ABORTED THE TAKEOFF AND SHUT DOWN THE ENGINE. UPON INSPECTION, IT WAS FOUND THAT THE JAM NUT CAME LOOSE, AND WORE THE THREADS OUT OF THE ROD END. (X) 2 L 7 2 4R 4 R 3A2 5E8 2000120600031 20001206 00031 CE 2000 12 6 CA000927012 1 20000903 G 5740 6147514435 WASHER BEECH BEECH 100 A100 1152915 CE PWA PT6 PT6A28 EA PRELD INDIC RING FAILED W K NONE O OTHER IN INSP/MAINT 1 CA B149 (CAN) WHILE REASSEMBLING THE WING FOLLOWING INSPECTION IN ACCORDANCE WITH CF-81-25R5, A NEW PRELOAD INDICATING WASHER AS SY INSTALLED ON THE LT LOWER FORWARD WING BOLT INDICATED THE BOLT WAS TORQUED AT AN ABNORMALLY LOW TORQUE. THE BOLT WAS UNDONE AND THE WASHER KIT FURTHER EXAMINED. THE INNER RING WAS FOUND TO BE THINNER THAN THE INDICATOR RING CAUSING THE INDICATOR RING TO INDICATE THE BOLT WAS TORQUED AS SOON AS THE NUT CONTACTED THE WASHER ASSY, BEFORE ANY TORQUE WAS APPL IED. PART WAS RECEIVED WITH P/N 8130 FORM FROM RAYTHEON AIRCRAFT. (X) 1 L 7 2 3T 4 T A14CE E4EA 2000120600032 20001206 00032 CE 2000 12 6 CA000928002 1 20000901 G 6100 PROPELLER MCAULY CESSNA 150 150L 2071826 CE CONT O200 O200A 17020 SO MCAULY 1A101 1A101HCM GL L. EDGE & FACE DAMAGED W O OTHER O OTHER IN INSP/MAINT 1 CA 5227 G11772 (CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. 1 H 7 1 3O 3 O 3A19 E252 5 N P918 2001032900050 20010329 00050 SW 2001 3 29 CA000928004 1 20000901 G 6320 206075660001 LINE BELL 206 206L 1181522 SW M/R GEARBOX CHAFED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) PILOT LANDED & SHUT DOWN NORMALLY. HE THEN NOTICED FLUID RUNNING DOWN SIDE OF FUSELAGE. INVESTIGATION REVEALED THA T LEAKING OIL WAS COMING FROM THE MGB OIL PRESSURE INDICATING LINE, LOCATED UNDER THE TRANSMISSION RESTRAINT. THE CHAFIN G OF THE FOIL FLEX LINE GOING TO THE FREEWHEELING UNIT LIKELY CAUSED THE OIL PRESSURE INDICATING LINE TO FAIL AND LEAK O IL. THE LINE WAS REPLACED. THE DG CLAMPS ATTACHING THE OIL FLEX LINE TO THE TRANSMISSION RESTRAINT WERE RE-ARRANGED TO G IVE MORE CLEARANCE BETWEEN THE TWO LINES. THE OIL LEVEL WAS ADJUSTED, THE HELICOPTER WASHED, GROUND RUN AND RETURNED TO SERVICE. 1 G 7 1 3U H2SW 2001040300037 20010403 00037 2001 4 3 CA000928005 4 20000906 G 3418 C6SC106027 STALL BAR DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA RIGHT DEBONDED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A SCHEDULED MAINTENANCE CHECK,, THE RT STALL BAR WAS FOUND TO BE PARTIALLY UNGLUED. THE STALL BAR WAS REMOV ED, CLEANED AND REBONDED AS PER DHC MAINTENANCE INSTRUCTIONS. 1 H 7 2 3T 4 T RT A9EA E4EA 2001031900165 20010319 00165 NM 2001 3 19 CA000928008 1 20000911 G 2722 591005013 PCU BOEING 727 727217 NM PWA JT8 JT8D17 52049 NE RUDDER FAILED W O OTHER F FLT CONT AFFECTED TX TAXI/GRND HDL 1 CA 572 (CAN) ON SERVICE CHECK FOUND LOWER RUDDER DEFLECTED TO THE LEFT WITH ZERO INPUT, A SYSTEM PRESSURIZED. FURTHER TROUBLE S HOOTING REVEALED LOWER RUDDER PCU BYPASSING. LOWER RUDDER PCU REPLACED AND INSTALLATION LEAK, FUNCTION INSPECTED SERVICE ABLE IN ACCORDANCE WITH MM 27-20-141. 2 L 7 3 4F 4 F RT A3WE E2EA 2001032900053 20010329 00053 NM 2001 3 29 CA000928009 1 20000920 G 2133 7110033 OUTFLOW VALVE BOEING 727 727221 1384071 NM PWA JT8 JT8D17 52049 NE CABIN PRESSURE INTERMITTENT W O OTHER J WARNING INDICATION CR CRUISE 1 CA 168503 (CAN) AIRCRAFT WOULD NOT PRESSURIZE AFTER TAKEOFF. OUTFLOW VALVE STUCK OPEN. ATTEMPTED STANDBY, ALSO STUCK OPEN. AC MO DE CLOSED OUTFLOW VALVE ONLY AFTER MOVING SWITCH TO OPEN, THEN CLOSE. AUTO APPEARS TO NOT WORK. FOOUND OUTFLOW VALVE INT ERMITTENT IN MANUAL AC/DC. OUTFLOW VALVE REPLACED PER MM 21-31-11. 2 L 7 3 4F 4 F A3WE E2EA 2000120600033 20001206 00033 CE 2000 12 6 CA000928011 1 20000911 G 2913 1240084CR0190 LINE BEECH 9938800213 BEECH 99 99A 1154003 CE PWA PT6 PT6A28 EA 1/2 FROM FITTIN LEAKING W A D UNSCHED LANDING RETURN TO BLOCK J WARNING INDICATION CR CRUISE 1 CA 37 (CAN) HYDRAULIC POWER PACK STARTED TO CYCLE FREQUENTLY AND THE HYDRAULIC LOW LIGHT CAME ON AND STAYED ON. HYDRAULIC CON TROL CIRCUIT BREAKER TRIPPED. PILOT RETURNED TO BASE AND DID A MANUAL EXTENSION AND LANDED AIRCRAFT WITH 3 GREEN. MAIN TENANCE FOUND LINE GOING FROM MAINTENANCE VALVE TO POWER PACK GEAR UP SIDE TO BE LEAKING. LINE REPLACED AND CHECKED SER VICEABLE. (X) 1 L 7 2 3T 4 T A14CE E4EA 2000120600034 20001206 00034 EA 2000 12 6 CA000928012 1 20000910 G 2730 MS206674 FITTING C3CF1935 DHAV DHC3 DHC3 2800202 EA HOLE INACCURATE W O OTHER O OTHER IN INSP/MAINT 1 CA (CAN) WHILE ATTEMPTING TO FIT THE ELEVATOR CONTROL CABLE TO A DHC-3T DURING A 400 HOUR INSPECTION, IT WAS FOUND THAT THE END FITTING ON THE NEW CABLE HAD AN INCORRECTLY SIZED HOLE. THE END FITTING HOLE IN THE ORIGINAL PART WAS 14 INCHES IN DIAMETER, AND THAT IN THE NEW PART SUPPLIED WAS .1875 INCH IN DIAMETER. A NEW CABLE ASSEMBLY WAS REQUESTED. (X) 1 H 7 1 3R A815 2001032900054 20010329 00054 EA 2001 3 29 CA000928013 1 20000911 G 2730 C3TE134 LEVER DHAV DHC3 DHC3 2800202 EA PWA PT6 PT6A135 52043 NE ELEVATOR LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA 100 (CAN) DURING A ROUTINE 400 HOUR INSPECTION OF THE ELEVATOR SERVO TAB, THE ENGINEER FOUND THAT THE RIVETS SECURING THE LE VER TO THE SERVO TABLWERE LOOSE. THE ENGINEER REMOVED THE TAB, AND REPLACED THE LOOSE RIVET WITH NEW RIVETS. THE SERVO T AB WAS REINSTALLED. 1 H 7 1 3R 4 T A815 E4EA 2001032900055 20010329 00055 EA 2001 3 29 CA000928014 1 20000911 G 2730 AGS6052 CLAMP DHAV DHC2 DHC2MK3 2800107 EA PWA PT6 PT6A27 52043 EA ELEVATOR JAMMED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AT THE END OF THE DAY WHEN THE PILOT WAS SECURING THE FLIGHT CONTROLS HE FOUND THAT WHEN HE PULLED THE ELEVATORS T O THE FULL BACK POSITION, THEY WOULD STICK IN THAT POSITION. IT WAS FOUND THAT THE CLAMP THAT SECURES THE COVER TO THE E LEVATOR TRIM JACK WAS GETTING CAUGHT ON THE ELEVATOR CONTROL LEVER. INSPECTION FOUND THAT THE IMPROPER CLAMP WAS INSTALL ED. THE CLAMP WAS REMOVED AND REPLACED WITH THE PROPER PART. THE AIRCRAFT WAS RETURNED TO SERVICE. 1 H 7 1 3T 4 T A806 E4EA 2000120600035 20001206 00035 SO 2000 12 6 CA000928017 2 20000604 G 8530 654651A8 CYLINDER CONT BEECH 45 A45 1152006 CE CONT O520 IO520BA 17032 SO MCAULY 3A32C 3A32C76 GL CYLINDER CRACKED W O OTHER O OTHER CL CLIMB 1 CA 363 562878 (CAN) AFTER TAKEOFF, PILOT HAD VIBRATION IN ENGINE. RETURNED TO AIRPORT, MAINTENANCE FOUND NR 2 CYLINDER CRACKED AT SPA RK PLUG HOLE TO EXHAUST VALVE. CRACK APPROXIMATELY 5 INCHES LONG. CYLINDER REPLACED WITH NEW CONTINENTAL CYCLES AND RE TURN TO SERVICE. (X) 1 L 7 1 3O 3 O 5A3 E5CE 5 C P21EA 2000120600036 20001206 00036 CE 2000 12 6 CA000928019 1 20000830 G 3110 RACK CESSNA 08134551 CESSNA 310 310L 2074230 CE CONT O470 IO470V 17026 SO MCAULY 3AF32C D3AF32C80 GL TOP SUPRT BRCKET CHAFED W O OTHER O OTHER LD LANDING 1 CA 6471 (CAN) UPON PERFORMING FLAIR DURING LANDING, THE PILOTS NOTICED THE ELEVATOR CONTROLS WERE FEELING A LITTLE STIFF. UPON MAINTENANCE INVESTIGATION, FOUND THE RADIO IN THE CENTER INSTRUMENT PANEL (RADIO RACK) WERE SETTING DOWN AND MAKING CONT ACT WITH THE CONTROL YOKE. FORWARD RADIO RACK SUPPORT WAS REPAIRED, RADIO RACK WAS ADJUSTED TO PROVIDE ADEQUATE CLEARAN CE. CONTROLS MOVED TO EXTREMES, NO CONTACT NOTICED. (X) 1 L 7 2 3O 3 O 3A10 3E1 5 C P22EA 2000120700086 20001207 00086 CE 2000 12 7 CA000928020 1 20000711 G 2844 FUEL LINE AEROQUIP AE7013127022 CESSNA 310 310D 2074212 CE CONT O470 IO470D 17026 SO AT THE FLARE BROKEN W O OTHER O OTHER CR CRUISE 1 CA 108 (CAN) BOTH LT AND RT FUEL PRESSURE LINES WERE MADE LOCALLY BY OTHERS OUT OF -2 SOFT COPPER. COPPER MOST LIKELY WORK HAR DENED AND CRACKED. CORRECT P/N HOSES AS ABOVE WILL NOT FIT IN AIRCRAFT AS AIRCRAFT USES -2 FITTING ON BACK OF PUMP AND FIREWALL. ACCORDING TO MIL AERO, THESE HOSE ASSEMBLIES ARE -4 HOSE WITH SPECIAL -3 ENDS. TWO HOSES WERE MADE OF AEROQU IP 306 -2 RUBBER HOSE AND INSTALLED. (X) 1 L 7 2 3O 3 O 3A10 3E1 2001032900058 20010329 00058 CE 2001 3 29 CA000928021 1 20000826 G 2742 NAS56138 ROLL PIN CESSNA 07125002 CESSNA 185 A185F 2072821 CE CONT O520 IO520D 17032 SO TRIM ACTUATOR DISPLACED W D RETURN TO BLOCK J WARNING INDICATION TX TAXI/GRND HDL 1 CA (CAN) ROLL PIN ON LEFT STABILIZER ACTUATOR SLID OUT AND GOT CAUGHT ON THE ACTUATOR HINGE ASSEMBLY. THIS PREVENTED THE ST ABILIZER TRIM FROM MOVING. THE TRIM ACTUATORS WERE REMOVED, THE PIN RE-INSTALLED, AND LOCKWIRED. SUGGEST LOCKWIRING PINS IN ALL ACTUATORS. 1 H 7 1 3O 3 O 3A24 E5CE 2000120700087 20001207 00087 2000 12 7 CA000928022 4 20000816 G 2562 BS2173 BATTERY DORNEMARGLN DMELT6C UNIVAR 415 A2ALON 0540102 NM CONT C90 C9016F 17009 SO BATTERY WRONG PART W O OTHER O OTHER IN INSP/MAINT 1 CA 0006 (CAN) ELT WAS EQUIPPED WITH NON-APPROVED BATTERY MADE BY AVIAL PER B014 AIRWORTHINESS NOTICE. AVIALL BATTERY PACK IS ON LY APPROVED FOR DMELT 6 OR 8. (X) 1 L 7 1 3O 3 O A787 E252 2001032900059 20010329 00059 CE 2001 3 29 CA000928024 1 20000823 G 5347 051100014 SEAT TRACK CESSNA 170 170 2072302 CE CONT C145 C1452 17012 SO MCAULY 1A170 1A170DM GL COCKPIT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 2067 18527 (CAN) DURING THE ANNUAL INSPECTION IT WAS DISCOVERED THAT THE RIGHT SIDE INBOARD SEAT RAIL HAD NUMEROUS CRACKS. SEAT RAI L DID NOT MEET AIRWORTHINESS DIRECTIVE CF 87-15 R2CRITERIA. SEAT RAIL REPLACED WITH NEW CESSNA SEAT RAIL. RAIL SECURED U SING INSTRUCTIONS DETAILED IN CESSNA SERVICE MANUALS AND THE AC 43-13-1B, CHAPTER 2, PARA 99, RIVETING STANDARDS. 1 H 7 1 3O 3 O NT A799 E253 5 N P857 2000120700088 20001207 00088 CE 2000 12 7 CA000928026 1 20000626 G 3600 14953 CHECK VALVE CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE LT PRESS T/CONE BROKEN W O OTHER O OTHER IN INSP/MAINT 1 CA 91 (CAN) DURING TROUBLESHOOTING EXERCISE, OPAL CHECK OF INFLATABLE DOOR SEAL CARRIED OUT. RESULTING TEST FOUND THAT PRESSU RE ZERO DOWNSTREAM FROM REGULATOR MEASURED AT MAIN DOOR SEAL INFLATION FITTING. IT ALSO NOTICED THAT THE DE-ICE BOOTS W ERE NOT INFLATING WHEN SELECTED. WITH PRESSURE STILL APPLIED AT TEST PORT IN TAILCONE, AIR NOISE HEARD FROM LT ENGINE E XHAUST DUCT. DUE TO PREVIOUS SIMILAR PROBLEM (REPORTED ON SDR NR 20000713014) LT PNEUMATIC CHECK VALVE REMOVED FROM A/C AND FLAP PER VALVE HINGE ASSY FOUND BROKEN INSIDE VALVE BODY. ONLY TIME THAT WOULD CAUSE SERIOUS PROBLEM IS WHEN ENGIN E FAILURE WOULD OCCUR AND ALL OR MOST OF BLEED AIR WOULD ESCAPE TO THE FAILED ENGINE AND CHECK VALVE. (X) 1 L 7 2 4F 4 F A22CE E1NE 2001032900062 20010329 00062 NM 2001 3 29 CA000928029 1 20000907 G 2433 10333671 BUSS TIE 1152230 DHAV DHC8 DHC8* NM DC CONTACTOR BOX OVERHEATED W D RETURN TO BLOCK H ELECT. POWER LOSS-50 PC TX TAXI/GRND HDL 1 CA 314 10333 (CAN) IT WAS REPORTED FROM OPERATOR AIRCRAFT RETURNED TO GATE WITH LOSS NR 1 TRU, & ANTI-ICE CAUTION LIGHTS ON. MAINTENA NCE REPORTS, DISCOVERING SOME OVERHEATING OF BUS BAR T4 & K6, THESE PARTS & ASSOCIATED HARDWARE WERE REPLACED & AIRCRAFT RETURNED TO SERVICE. 2 H 7 2 4T RT A13NM 2000120700089 20001207 00089 CE 2000 12 7 CA000928031 1 20000910 G 5240 6610169311 DOOR CESSNA 560 560XL CE BATTERY DOOR DEPARTED W O OTHER O OTHER CR CRUISE 1 CA 130 (CAN) AFTER 45 MINUTES AT CRUISE ALTITUDE 31,000 FEET, CREW HEARD LOUD BANG. UPON LANDING, NOTICED THAT BATTERY DOOR O N LEFT SIDE OF A/C HAD DEPARTED. BATTERY FLOOR LOWER OUTSIDE SKIN CREASED. FWD HYDRAULIC BELLY PANEL HAD MINOR DING, U NILINK COM ANTENNA CUT IN HALF, AND AFT BELLY HYDRAULIC PANEL SCRATCHED. BOTH CREW MEMBERS HAD VISUALLY INSP BATTERY DO OR PRIOR TO DEPARTUE AND VERIFIED THAT ALL 4 LATCHED WERE SECURED AND DOOR LOCKED IN LINE WITH BLACK LOCKED MARK. (X) 2 L 7 2 4F RT A22CE 2001032900063 20010329 00063 NE 2001 3 29 CA000928032 2 20000908 G 7397 302114F202 WIRE DHAV DHC8 DHC8* NM PWA PW120 PW123 NE OIL COOLER CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA 4245 (CAN) DURING A SCHEDULED ENGINE CHANGE, DURING CHANGE REMOVED & PARTS/WIRING WERE TRANSFERRED TO NEW ENGINE. DURING ECU CHANGE THE WIRING TO FUEL OIL COOLER UNIT WAS DISCOVERED CHAGED. WIRE WAS EPAIRED IAW AMM CH20 . 2 H 7 2 4T 4 T RT A13NM E20NE 2000101800016 20001018 00016 SO 2000 10 18 CA000928036 2 20000814 G 8520 LIFTER CONT CESSNA 206 U206D 2073342 CE CONT O520 IO520F 17032 SO MCAULY 2A34C D2A34C58 GL FOLLOWING FACE CHIPPED W K NONE O OTHER IN INSP/MAINT 1 CA 552992 (CAN) A LARGE AMOUNT OF ALUMINUM WAS FOUND IN THE OIL SCREEN. A CYLINDER DIFFERENTIAL COMPRESSION CHECK WAS PERFORMED A ND FOUND TO BE ALL ABOVE 70/80. STARTER DRIVE WAS REMOVED AND INSPECTED, NO DAMAGE FOUND AT THIS TIME (SUSPECTED USING ONLY A BORESCOPE). CYLINDERS 3 AND 1 WERE REMOVED FOR INTERNAL ENGINE INSPECTION. NR 1 CYLINDER INTAKE HYDRAULIC LIFTE R WAS FOUND TO HAVE A .25 INCH BY .25 INCH BY .0625 INCH (APPROX) CHIP OUT OF THE FOLLOWING FACE. AT THIS POINT THE ENG INE WAS REMOVED FOR REPAIR AT AIRCRAFT TECHNICAL CONSULTANTS. 7 A,, B AND C FOUND DURING A 50 HR OIL CHANGE. (X) 1 H 7 1 3O 3 O A4CE E5CE 5 C P3EA 2000101800022 20001018 00022 SO 2000 10 18 CA000928037 2 20000828 G 8520 654149 CRANKCASE CONT CESSNA 206 U206D 2073342 CE CONT O520 IO520F 17032 SO MCAULY 2A34C D2A34C58 GL CRANKCASE FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 720 552992 (CAN) NR 2 MAIN BEARING HAD STARTED TO SPIN IN CRANKCASE CAUSING ALUMINUM IN FILTER. CRANKCASE SENT OUT FOR REPAIR. EN GINE ASSEMBLED WITH NEW CRANKCASE. (X) 1 H 7 1 3O 3 O A4CE E5CE 5 C P3EA 2000101800023 20001018 00023 CE 2000 10 18 CA000928044 1 20000928 G 3211 998100287 BRACE BEECH 100 100BEECH 1152916 CE PWA PT6 PT6A28 EA BRACE CRACKED W O OTHER O OTHER IN INSP/MAINT 1 CA (CAN) CRACKED WAS FOUND THROUGH EDDY CURRENT TESTING. (X) 1 L 7 2 3T 4 T A14CE E4EA 2001032900065 20010329 00065 EA 2001 3 29 CA001002002 1 20000904 G 2740 83963 ACTUATOR CNDAIR CL600 CL6002B19 EA STABILIZER FAILED W A UNSCHED LANDING F J FLT CONT AFFECTED WARNING INDICATION CL CLIMB 1 CA (CAN) BOTH STABILIZER TRIM CHANNEL NR 1 AND 2 AND MACH TRIM DISENGAGED UPON LANDING.EVENT: WOULD NOT REST (LANDING WAS U NEVENTFUL, NO EMERGENCY DECLARATION). ON CLIMB OUT THROUGH 2000 FEET, THE STAB / MACH TRIM CAUTION MESSAGE APPEARED. RE SET SYSTEM TWICE. RETURNED TO DEPARTURE AIRPORT, LANDING WAS UNEVENTFUL. REPLACED THE MACH TRIM / STAB CONTROL PANEL, R EPLACED THE STABILIZER ACTUATOR AND MCU, A/C RETURNED TO SERVICE 2 L 7 2 4F RT A21EA 2001032900066 20010329 00066 EA 2001 3 29 CA001002003 1 20000904 G 5210 SPRING CNDAIR CL6002B19 CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE PAX DOOR ROD FAILED W O OTHER O OTHER NR NOT REPORTED 1 CA 7145 (CAN) FLIGHT CREW REPORTED THE PRESSURIZATION VALVE ON THE MAIN CABIN DOOR WILL NOT CLOSED. MAINTENANCE FOUND THE ROD SP RING WEAK, THEY REPLACED THE ROD ASSY. 2 L 7 2 4F 4 F RT A21EA E15NE 2001032900067 20010329 00067 EA 2001 3 29 CA001002004 1 20000904 G 2910 LINE CNDAIR CL600 CL6002B19 EA HYD SYSTEM FAILED W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) HIGH TEMP CAUTION MSG APPEARED IN FLIGHT FOLLOWED BY AN INTERMITTENT HYDRAULIC NR 2 LOW PRESSURE. MAINTENANCE REPL ACED THE HYDRAULIC LINE TO THE EDP NR 2. 2 L 7 2 4F RT A21EA 2001032900068 20010329 00068 EA 2001 3 29 CA001002005 1 20000904 G 2740 BUSHING CNDAIR CL600 CL6002B19 EA HORIZONTAL STAB DAMAGED W A UNSCHED LANDING F FLT CONT AFFECTED CR CRUISE 1 CA (CAN) AP PITCH TRIM MESSAGE ON EICAS, ELECTRICAL STAB TRIM OPERATED APPROX. 10 PERCENT OF THE TIME AND SOME OF THE TIME IN ONE DIRECTION. HORIZONTAL STAB BUSHING FOUND STIFF. 2 L 7 2 4F RT A21EA 2001032900069 20010329 00069 2001 3 29 CA001002006 4 20000904 G 3418 VANE CNDAIR CL600 CL6002B19 EA AOA DAMAGED W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA (CAN) FLIGHT CREW REPORTED ATERNATE TAKEOFF STALL FAIL ON EICAS ALONG WITH THE SHAKER.MAINTENANCE FOUND NR 2 AOA VANE DA MAGE. THEY REPLACED THE 2 AOA VANES AND THE STALL COMPUTER. 2 L 7 2 4F RT A21EA 2001031900170 20010319 00170 EA 2001 3 19 CA001002007 1 20000904 G 2710 PCU CNDAIR CL600 CL6002B19 EA RT AILERON FAILED W A UNSCHED LANDING F FLT CONT AFFECTED CR CRUISE 1 CA (CAN) FLIGHT CREW REPORTED THE A/C WANT TO ROLL TO THE RIGHT, REQUIRED EXCESSIVE TRIM LWD TO MAINTAIN FLIGHT LEVEL. MAIN TENANCE REPLACED THE R/H AILERON PCU CONNECTING HARDWARE. 2 L 7 2 4F RT A21EA 2001032900070 20010329 00070 2001 3 29 CA001002008 4 20000907 G 3418 TRANSDUCER CNDAIR CL600 CL6002B19 EA STALL SYSTEM FAILED W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA (CAN) DURING TAKEOFF THE STALL FAIL CAUTION MESSAGE APPEARED, FOLLOWED BY THE CONFIG SPOILERS AURAL. THEY DID A REJECTED TAKEOFF. MAINTENANCE REPLACED THE MACH TRANSDUCER. 2 L 7 2 4F RT A21EA 2001031900171 20010319 00171 EA 2001 3 19 CA001002010 1 20000908 G 7932 PROBE CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE LT ENGINE OIL FAILED W A UNSCHED LANDING M J OVER TEMP WARNING INDICATION CL CLIMB 1 CA (CAN) ON CLIMBOUT, ENG OIL WENT RED ON LEFT ENGINE (>165 DEG C). QRH UTILIZED AND TEMP BROUGHT BACK INTO GREEN AT A VERY REDUCED POWER SETTING. ITT NORMAL THROUGHOUT EVOLUTION. PRESSURE WAS LOW BUT IN NORMAL RANGE. MAINTENANCE FOUND OIL REP LENISHMENT SYSTEM CONTINUOUSLY RUNNING OIL INTO LEFT ENGINE. DESERVICED GEARBOX & ENGINE. FOUND 8 QTS IN GEARBOX. REPLAC ED OIL LEVEL PROBE IN OIL REPLENISHMENT SYSTEM AND A/C RETURNED TO SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001032900071 20010329 00071 2001 3 29 CA001002011 4 20000908 G 8300 M832481910 PACKING CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE NR 2 IDG CUT W C ABORTED TAKEOFF K J FLUID LOSS WARNING INDICATION TO TAKEOFF 1 CA (CAN) ABORTED TAKEOFF DUE TO THE IDG 2 CAUTION MESSAGE. MAINTENANCE FOUND AN OIL LEAK FROM THE IDG NR 2 OUT PORT CAUSED BY A CUT O-RING . O-RING REPLACED AND A/C RETURNED TO SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001031900172 20010319 00172 2001 3 19 CA001002012 4 20000909 G 3418 WARNING SYSTEM CNDAIR CL600 CL6002B19 EA COCKPIT FAILED W C ABORTED TAKEOFF N FALSE WARNING TO TAKEOFF 1 CA (CAN) DURING TAKEOFF ACCELERATION, EICAS MESSAGE STALL FAIL APPEARED. CREW ABORTED TAKEOFF AND RETURN TO GATE FOR MAINTE NANCE ACTION. MDC REVEALED NO ANOMALIES. STALL PROTECTION COMPUTER WAS RESET AND THE AIRCRAFT WAS RETURNED TO SERVICE WI TH NO FURTHER ANOMALIES. 2 L 7 2 4F RT A21EA 2001031900173 20010319 00173 EA 2001 3 19 CA001002013 1 20000912 G 2910 AE7120311 LINE CNDAIR CL600 CL6002B19 EA HYDRAULIC SYS CUT W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) CREW REPORTED HYDRAULIC LOW PRESSURE WARNING AND THE ZERO QUANTITY INDICATION ON THE EICAS. MAINTENANCE REPLACED H YDRAULIC ON THE NR 2 ENGINE THAT WAS FOUND CUT. 2 L 7 2 4F RT A21EA 2001031900174 20010319 00174 2001 3 19 CA001002014 4 20000912 G 3418 COMPUTER CNDAIR CL600 CL6002B19 EA STALL WARNING MALFUNCTIONED W C ABORTED TAKEOFF N FALSE WARNING TO TAKEOFF 1 CA (CAN) STALL FAIL CAUTION MESSAGE POSTED ON EICAS UPON TAKEOFF. ABORTED TAKEOFF AND RETURNED TO BLOCKS. RESET STALL COMPU TER. A/C RETURNED TO SERVICE. 2 L 7 2 4F RT A21EA 2001032900072 20010329 00072 EA 2001 3 29 CA001002015 1 20000901 G 2750 855D1009 BPSU CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE LEFT & RIGHT FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) FLAPS FAIL EICAS MESSAGE AFTER SWITCHING NR 2 GENERATOR ON LINE AFTER ENGINE START. FERRIED A/C TO MAIN BASE. REPL ACED LT & RT BRAKE POSITION SENSOR UNIT (BPSU). A/C RETURNED TO SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001032900073 20010329 00073 EA 2001 3 29 CA001003002 1 20000915 G 2740 CONTROL UNIT CNDAIR CL600 CL6002B19 EA HORIZONTAL STAB FAILED W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA (CAN) AT APPROXIMATELY 100 KTS, THE STAB TRIM & MACH TRIM FAILED. THEY ABORTED THE TAKEOFF AND RETURNED TO GATE.THEY REP LACED THE HSTCU AND CARRIED OUT AN ABORTED TAKEOFF INSPECTION. 2 L 7 2 4F RT A21EA 2001032900074 20010329 00074 2001 3 29 CA001003003 4 20000915 G 3418 SENSOR CNDAIR CL600 CL6002B19 EA LT AOA FAILED W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA (CAN) AT APPROXIMATELY 90 KTS, THEY HAD A STALL FAIL, FOLLOWED BY A CONFIG SPOILERS MESSAGE. THEY ABORTED THE TAKEOFF AN D RETURNED TO THE GATE. THE MAINTENANCE REPLACED THE LEFT AOA SENSOR AND CARRIED OUT AN ABORTED TAKEOFF INSPECTION. 2 L 7 2 4F RT A21EA 2001032900075 20010329 00075 EA 2001 3 29 CA001003004 1 20000916 G 3244 TIRE CNDAIR CL600 CL6002B19 EA LT NR 1 & 2 DAMAGED W C ABORTED TAKEOFF O OTHER TO TAKEOFF 1 CA (CAN) DURING THE TAKEOFF, WHILE THE AIRCRAFT WAS ACCELERATING, AN IMORTANT VIBRATION WAS FELT IN THE COCKPIT. THRUST RET ARDED TO IDLE AN AIRCRAFT RETURNED TO THE GATE AFTER THE ABORTED TAKEOFF. MAINTENANCE FOUND BOTH LT MLG TIRES DAMAGED . ALSO DAMAGE WAS FOUND TO THE LEFT INBOARD FLAP (INBOARD SIDE OF TRAILING EDGE), THE WING TRAILING EDGE AROUND WWS 56.177 AND THE LEFT GEAR DOOR. DEEP INSPECTION OF THE AIRCRAFT SYSTEM CARRIED OUT BEFORE RELEASING THE WE ARE WAITING FOR A MO RE COMPLETE REPORT. 2 L 7 2 4F RT A21EA 2001031900177 20010319 00177 2001 3 19 CA001003005 4 20000919 G 3418 COMPUTER CNDAIR CL600 CL6002B19 EA STALL WARNING MALFUNCTIONED W C ABORTED TAKEOFF O OTHER TO TAKEOFF 1 CA (CAN) STALL FAIL MESSAGE POSTED ON THE EICAS ON TAKEOFF. A/C MADE AN AIR RETURN TO THE BASE. STALL COMPUTER RE-RACKED, O PERATIONAL TEST CARRIED OUT, A/C RETURNED TO SERVICE. 2 L 7 2 4F RT A21EA 2001031900178 20010319 00178 2001 3 19 CA001003006 4 20000919 G 3418 COMPUTER CNDAIR CL600 CL6002B19 EA STALL WARNING MALFUNCTIONED W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA (CAN) STALL FAIL MESSAGE POSTED ON THE EICAS ON TAKEOFF.RESET STALL COMPUTER. A/C BACK IN SERVICE. 2 L 7 2 4F RT A21EA 2001031900179 20010319 00179 2001 3 19 CA001003007 4 20000919 G 3418 COMPUTER CNDAIR CL600 CL6002B19 EA STALL WARNING FAILED W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA (CAN) STALL FAIL MESSAGE POSTED ON THE EICAS ON TAKEOFF.RESET STALL COMPUTER, A/C BACK IN SERVICE. 2 L 7 2 4F RT A21EA 2001031900180 20010319 00180 2001 3 19 CA001003008 4 20000919 G 3418 COMPUTER CNDAIR CL600 CL6002B19 EA STALL WARING MALFUNCTIONED W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA (CAN) STALL FAIL MESSAGE POSTED ON THE EICAS ON TAKEOFF.RESET STALL COMPUTER, A/C BACK IN SERVICE. 2 L 7 2 4F RT A21EA 2001032000053 20010320 00053 2001 3 20 CA001003009 4 20000919 G 3418 COMPUTER CNDAIR CL600 CL6002B19 EA STALL WARING MALFUNCTIONED W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA (CAN) STALL FAIL MESSAGE POSTED ON THE EICAS ON TAKEOFF.RESET STALL COMPUTER, A/C BACK IN SERVICE. 2 L 7 2 4F RT A21EA 2001032000054 20010320 00054 2001 3 20 CA001003010 4 20000919 G 3418 COMPUTER CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE STALL WARNING FAILED W C ABORTED TAKEOFF O OTHER TO TAKEOFF 1 CA (CAN) STALL FAIL MESSAGE POSTED ON THE EICAS AFTER TAKEOFF. A/C MADE AN AIR RETURN TO THE BASE. AOA CHECKED, NO CODES FO R SPC IN MDC, PUSHER CHECKED GOOD. STALL COMPUTER RESET. A/C RETURNED TO SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001032000055 20010320 00055 2001 3 20 CA001003011 4 20000919 G 3418 COMPUTER CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE STALL WARNING FAILED W C ABORTED TAKEOFF O OTHER CL CLIMB 1 CA (CAN) STALL FAIL MESSAGE POSTED ON THE EICAS AFTER TAKEOFF. A/C MADE AN AIR RETURN TO THE BASE. REPLACED STALL COMPUTER AND TESTED PER AMM. A/C BACK IN SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001032900076 20010329 00076 EA 2001 3 29 CA001003012 1 20000920 G 2750 BPSU CNDAIR CL600 CL6002B19 EA TE FLAPS FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) FLAPS FAIL MESSAGE APPEARED IN FLIGHT AT 45 DEGREES.MAINTENANCE ACTION : REPLACED THE RIGHT BPSU. A/C RETURNED TO SERVICE. 2 L 7 2 4F RT A21EA 2001032000056 20010320 00056 EA 2001 3 20 CA001003013 1 20000920 G 2740 CONTROL UNIT CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE STAB TRIM FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) STAB TRIM CHANNEL NR 2 MESSAGE ON EICAS POSTED PRIOR TO DEPARTURE.MAINTENANCE REPLACED THE MCU (MOTOR CONTROL UNIT ). A/C RETURNED TO SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001032000057 20010320 00057 2001 3 20 CA001003014 4 20000920 G 3418 COMPUTER CNDAIR CL600 CL6002B19 EA STALL WARNING FAILED W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA (CAN) STALL FAIL MESSAGE POSTED ON EICAS DURING FLIGHT. MAINTENANCE REPLACED THE STALL COMPUTER.A/C BACK IN SERVICE. 2 L 7 2 4F RT A21EA 2001032000058 20010320 00058 EA 2001 3 20 CA001003015 1 20000920 G 2450 CIRCUIT BREAKER CNDAIR CL600 CL6002B19 EA STAB TRIM TRIPPED W O OTHER F FLT CONT AFFECTED DE DESCENT 1 CA (CAN) DURING DESCENT, STAB TRIM CHANNEL NR 1 CAUTION MESSAGE APPEARED ALONG WITH MACH TRIM MESSAGE. MAINTENANCE FOUND CI RCUIT BREAKER TRIPPED.CIRCUIT BREAKER RESET, A/C BACK IN SERVICE. 2 L 7 2 4F RT A21EA 2001032000059 20010320 00059 NE 2001 3 20 CA001003016 2 20000920 G 7220 ENGINE CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE RIGHT DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING MORNING CREW PRE-FLIGHT WALK AROUND, RT ENGINE INTAKE, FAN & GUIDE VANES FOUND DAMAGED.ENGINE CHANGED, A/C BACK IN SERVICE.TC: SUSPECT FOD NO - FURTHER ACTION 2 L 7 2 4F 4 F RT A21EA E15NE 2001032000060 20010320 00060 2001 3 20 CA001003017 4 20000920 G 3418 TRANSDUCER CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE STALL WARNING FAILED W C ABORTED TAKEOFF F J FLT CONT AFFECTED WARNING INDICATION TO TAKEOFF 1 CA (CAN) STALL FAIL CAUTION MESSAGE ON EICAS FOLLOWED BY INBD SPOILERS MESSAGE ON TAKE OFF ROLL. REPLACED AOA NR 1 TRANSDUC ER AND AOA NR 2 TRANSDUCER (STIFF WHEN ROTATING). A/C BACK IN SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001032000061 20010320 00061 2001 3 20 CA001003018 4 20000922 G 3418 COMPUTER CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE STALL WARNING MALFUNCTIONED W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA (CAN) STALL FAIL CAUTION MESSAGE POSTED UPON TAKEOFF. RESET STALL COMPUTER, A/C BACK IN SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001032000062 20010320 00062 2001 3 20 CA001003019 4 20000922 G 3418 COMPUTER CNDAIR CL600 CL6002B19 EA STALL WARING MALFUNCTIONED W C ABORTED TAKEOFF N FALSE WARNING TO TAKEOFF 1 CA (CAN) STALL FAIL CAUTION MESSAGE POSTED UPON TAKEOFF, ASSOCIATED WITH CONFIGURATION SPOILERS AND PAX DOOR OUTER HANDLE. RESET STALL COMPUTER. A/C BACK IN SERVICE. 2 L 7 2 4F RT A21EA 2001032000063 20010320 00063 2001 3 20 CA001003020 4 20000922 G 3418 COMPUTER CNDAIR CL600 CL6002B19 EA STALL WARNING FAILED W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA (CAN) STALL FAIL MESSAGE POSTED ON THE EICAS ON TAKEOFF.A/C RETURNED TO THE BASE.STALL COMPUTER RESET, OPERATIONAL TEST CARRIED OUT. A/C RETURNED TO SERVICE. 2 L 7 2 4F RT A21EA 2001032000064 20010320 00064 EA 2001 3 20 CA001003021 1 20000922 G 3230 601R510087 CONTROL PANEL CNDAIR CL600 CL6002B19 EA COCKPIT FAILED W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA (CAN) AFTER TAKEOFF, THE LANDING GEAR WOULD NOT RETRACT. REPLACED LANDING GEAR CONTROL PANEL, GEAR SWING CARRIED OUT. A/ C BACK IN SERVICE. 2 L 7 2 4F RT A21EA 2001032900077 20010329 00077 EA 2001 3 29 CA001003022 1 20000922 G 2750 855D1009 BPSU CNDAIR CL600 CL6002B19 EA LT TE FLAPS FAILED W O OTHER J WARNING INDICATION CR CRUISE 1 CA (CAN) FLAPS FAIL CAUTION MESSAGE POSTED ON EICAS. REPLACED LEFT BPSU AND ALLL 8 FLAP ACTUATORS. A/C BACK IN SERVICE. 2 L 7 2 4F RT A21EA 2001032900078 20010329 00078 EA 2001 3 29 CA001003023 1 20000922 G 2740 83963 ACTUATOR CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE HORIZONTAL STAB FAILED W D RETURN TO BLOCK J WARNING INDICATION TX TAXI/GRND HDL 1 CA (CAN) STAB TRIM CHANNEL NR 2 WILL NOT ENGAGE & MACH TRIM CATUION MESSAGE AT THE GATE. REPLACED THE HSTA AND THE MCU ON S PEC.NOTE: DURING REPLACEMENT, FOUND THE STABILIZER SURFACE TO BE EXCESSIVELY STIFF TO MOVE. STABILIZER PIVOT LUBRICATED. A/C BACK IN SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001032900079 20010329 00079 EA 2001 3 29 CA001004004 2 20000911 G 8540 13519648 GEAR PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA CRANKSHAFT DESTROYED W O OTHER Y J ENGINE STOPPAGE WARNING INDICATION AP APPROACH 1 CA 1108 (CAN) CRANKSHAFT GEAR FAIL CAUSING DAMAGE TO OTHER ACCESSORY GEARS AND RESULTING IN ENGINE STOPPAGE. 1 L 7 2 3O 3 O A20SO E14EA 2001032900080 20010329 00080 NE 2001 3 29 CA001004006 2 20000814 G 8530 331107 VALVE CNDAIR CL215 CL2151A10 EA PWA R2800 CA3 52026 NE NR 3 CYLINDER BROKEN W A UNSCHED LANDING R Y PARTIAL RPM/PWR LOSS ENGINE STOPPAGE CR CRUISE 1 CA 680 680 (CAN) DURING SCOOP OPERATION, RT ENGINE BEGIN BACKFIRING. THE PILOT IN COMMAND DECIDED TO ABORT THE OPERATION AND TOOK O FF. ONCE THE AIRCRAFT WAS IN CRUISE, THEY PERFORMED A PERFORMANCE TEST ON THE RT ENGINE AND AS THOSE TESTS SHOWED THAT E NGINE COULD NOT MEET ITS SPECIFICATIONS AND PERFORMANCE, HE SHUT DOWN IT AND LAND AT THE CLOSEST AIRPORT. BOTH INTAKE A ND EXHAUST VALVES OF REAR NR 3 CYLINDER WERE DAMAGED. EXHAUST VALVE WAS LOST WHILE THE INTAKE VALVE WAS BENT. HE ALSO F OUND THE UPPER BEARING OF THE MAGNETO ALMOST DESTROYED. 2 H 7 2 4R 4 R A14EA E231 2001032000066 20010320 00066 EA 2001 3 20 CA001004007 1 20000824 G 5244 DOOR CNDAIR CL215 CL2151A10 EA ACCESSORY BAY SEPARATED W E C ENGINE SHUTDOWN ABORTED TAKEOFF D INFLIGHT SEPARATION TO TAKEOFF 1 CA (CAN) THE PILOT COMMAND (PIC) A REPORTED THAT DURING A SCOOPING OPERATION, HE FELT SOMETHING DRAGGING THE AIRCRAFT. THE PIC NOTICED THE WATER SYSTEM INDICATION PANEL ON THE GLARE SHIELD INDICATED THAT THE RT WATER DOOR WAS OPENED. THEN THE PIC PULLED BACK THE THROTTLE AND STOPPED ENGINES. HE LOOKED AT THE WATER DOOR MECHANISM AND SAW BOTH WATER DOOR ACTUATOR S PROTRUDING THROUGH THE WOODEN FLOOR. THE ACA INITIALLY REPORTED THAT BOTH THE WATER DOOR SPIGOTS WERE TORN FROM THE BU LKHEAD AT FS 371.5 AND THE RT WATER DOOR WAS OPENED AND COULD NOT MECHANICALLY BE CLOSED. THE RT WATER DOOR WAS MANUALLY CLOSED AND STRAPED TO PERMIT A TAKE OFF FROM THE SEA AND RETURN TO THE MAINTENANCE BASE. 2 H 7 2 4R A14EA 2001032900082 20010329 00082 NM 2001 3 29 CA001004009 1 20000830 G 2121 731376 FAN BOEING 757 75723A 1384967 NM RROYCE RB211 RB211535E437 54555 NE EQUIPMENT BAY SEIZED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA (CAN) AIRCRAFT WAS DIVERTED DUE TO BURNING ODOR IN COCKPIT AND FWD CABIN, CREW STATED THAT ODOR STOPPED AS SOON AS ALTER NATE FAN SELECTION WAS CARRIED OUT. UPON ARRIVALMAINTENANCE FOUND NR 1 EQUIPMENT COOLING FAN BREAKER POPPED, FAN FOUND S EIZED. AIRCRAFT WAS RELEASED UNDER MEL 21-58-3. 2 L 7 2 4F 4 F RT A2NM E12EU 2001032000067 20010320 00067 SO 2001 3 20 CA001004010 1 20000911 G 3233 2060500005 ROD END EMB 120 EMB120ER 3260203 SO PWA 118 PW118 NE HAMSTD 14RF 14RF9 NE ACTUATOR BROKEN W K NONE J WARNING INDICATION IN INSP/MAINT 1 CA (CAN) WHEN SELECTION GEAR UP, RED LIGHT STAY ON AT THE NOSE SYSTEM INDICATION. INVESTIGATION CUT OUT, A/C ON JACKS, GEAR SELECTED AT UP POSITION, FOUND NLG NOT LOCKED PROPERLY BY THE UPLOCK HOOK. RETRACTION ACTUATOR ADJUSTMENT WAS USSPECTED (P/N 20605-000-05) DECISION WAS MADE TO READJUST THE ROD END OF THE RETRACTION ACTUATOR BEOFORE ANY ADJUSTMENT WAS MADE , FOUND BROKEN LOCK WASHER (P/N 19803). INSIDE TANG WAS MISSING AND ROD END ADJUSTMENT HAD CHANGE (MOVED IN), THE LENGTH OF THE ACTUATOR WAS SHORTER. NEW LOCK WASHER INSTALLED AND ACTUATOR ADJUSTED AS PER M/M 32-32-11 AND SYSTEM CHECKED OK. 2 L 7 2 4T 4 T RT A31SO E20NE 6 C P11NE 2001032000070 20010320 00070 WP 2001 3 20 CA001004015 1 20000825 G 2710 2587788902 SERVO DOUG DC9 DC932 3022066 WP PWA JT8 JT8D7 52053 NE AILERONS FAILED W O OTHER F FLT CONT AFFECTED CR CRUISE 1 CA (CAN) AILERON SERVO WILL NOT DISENGAGE WITH SERVO SWITCHED OFF. UNABLE TO DISENGAGE AUTO PILOT. AILERON SERVO AND NR 1 D IRECTIONAL GYRO CHANGED. 2 L 7 2 4F 4 F A6WE E2EA 2001032900083 20010329 00083 NM 2001 3 29 CA001004016 1 20000815 G 5414 313T3200238 PANEL 767233 BOEING 767 767233 NM PWA JT9 JT9D7R4D 52054 NE NACELLE MISSING W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ON WALKAROUND FOUND PANEL MISSING ON INBOARD SIDE OF RIGHT HAND ENGINE STRUT. NIL PART AVAILABLE, PLACED ON MEL 54 -51-0100. NEW PANEL INSTALLED. 2 L 7 2 4F 4 F RT A1NM E3NE 2001032900084 20010329 00084 WP 2001 3 29 CA001004017 1 20000824 G 2740 95901 MOTOR DOUG DC9 DC932 3022066 WP PWA JT8 JT8D7 52053 NE STAB TRIM FAILED W O OTHER J WARNING INDICATION CR CRUISE 1 CA (CAN) PRIMARY LONGITUDINAL TRIM DID NOT WORK SHORTLY AFTER TAKEOFF. NEITHER SUITCASE HANDLES OR THUMB SWITCHES WORKED. A LTERNATE TRIM WORKED AND SHORTLY THEREAFTER THE PRIMARY TRIM BEGAN TO WORK. PRIMARY STABILIZER TRIM MOTOR REPLACED AS PE R MAINTENANCE MANUAL REF 27-40-01 AND OPERATION CHECKED SERVICEABLE. 2 L 7 2 4F 4 F A6WE E2EA 2001032000071 20010320 00071 NE 2001 3 20 CA001004018 2 20000824 G 7200 ENGINE AIRBUS 320 A320211 3930320 EU CFMINT CFM56 CFM565A1 NE NR 1 FIRE W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) HELICOPTER PILOT REPORTING SEEING FIRE IN BACK OF ONE ENGINE AFTER LANDING. A VISUAL INSPECTION OF BOTH ENGINES WA S COMPLETED WITH NO UNUSUAL FINDINGS. ALSO PILOTS DID NOT SEE ANY ABNORMAL INDICATION IN THE COCKPIT. AIRCRAFT CONSIDERE D SERVICEABLE. 2 L 7 2 4F 4 F RT A28NM E29NE 2001032900085 20010329 00085 NM 2001 3 29 CA001004021 1 20000819 G 2750 CONTROL UNIT BOEING 767 767333 NM PWA 4060 PW4060 52119 NE TE FLAPS FAILED W O OTHER F FLT CONT AFFECTED CR CRUISE 1 CA (CAN) UPON SELECTION OF FLAPS (25 FLAP) ICAS MESSAGE TE FLAP DISAGREE AND STATUS MESSAGE TE FLAP SHUTDOWN ILUMINATED. FL AP INDICATION SHOWED SLIGHTLY ASYMMETRY AT 23 DEGREES. CHENAGED FLAP SLAT ELECTRICAL UNIT (F.S.E.U.) AND TEST CARRIED OU T AS PER FAUALT ISOLATION MANUAL (F.I.M.) 27-50-00 PAGE 160, FIGURE 114C. NR 4 FLAP POSITION TRANSMITTER (M476) ADJUSTED . OPERATIONAL CHECK CARRIED OUT, CHECKED SERVICEABLE, BITE CHECKED FSEU NO FAULTS FOUND. 2 L 7 2 4F 4 F RT A1NM E24NE 2001032900086 20010329 00086 NE 2001 3 29 CA001005003 2 20000811 G 8530 33645 PUSHROD TUBE CNDAIR CL215 CL2151A10 EA PWA R2800 CA3 52026 NE NR 7 CYLINDER CRACKED W E A ENGINE SHUTDOWN UNSCHED LANDING K B FLUID LOSS SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 CA 1145 (CAN) SHORTLY AFTER TAKEOFF, DURING INITIAL CLIMB, TOWER REPORTED SMOKE FROM RT ENGINE.PILOT IN COMMAND ACKNOWLEDGED SIT UATION AND SHUT DOWN THE RT ENGINE AND RETURNED FOR LANDING.SIGNIFICANT OIL QUANTITY WAS LOST AS INDICATED ON OIL QUANTI TY INDICATOR. APPROXIMATELY 7 GALS LOST.UPON INVESTIGATOIN, IT WAS FOUND EXHAUST PUSH ROD HOUSING OF CYLINDER NR 7 CRACK ED. THEN, DURING THE REPLACEMENT, IT WAS FOUND THAT THE PUSH ROD ITSELF WAS SEPARATED AND CRACKED.PUSH ROD AND PUSH ROD HOUSING WERE REPLACED IAW PRATT & WHITNEY AND THE AIRCRAFT WAS RELEASED TO RETURN TO SERVICE. 2 H 7 2 4R 4 R A14EA E231 2001032900087 20010329 00087 EU 2001 3 29 CA001005004 2 20000628 G 7250 AS20625 NUT RROYCE SPEY SPEY5118 54523 EU GUIDE VANE RING DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 6194 608 (CAN) THE NUT AS20625 HOLDING THE OUTLET GUIDE VANE RING BETWEEN THE LOW PRESSURE COMPRESSOR ROTOR AND THE HIGH PRESSURE COMPRESSOR ROTOR WAS UNTORQUE AND ENTERED INTO THE HIGH PRESSURE COMPRESSOR ROTOR DAMAGING THE HP COMPRESSOR BLADES. TH E BOLT K1861114 ATTACHED BY THE NUT AS20625 HAS DAMAGED THE LP COMPRESSOR ROTOR BLADE STAGE 5 AND ALSO THE LP COMPRESSOR ROTOR DRUM. ENGINE REMOVED AFTER A POST FLIGHT INSPECTION BY THE CUSTOMER. ROLLS ROYCE MOD 5270 WHICH CORRECT THIS PROB LEM, WILL BE RE-EMBODY ON ENGINE, AND TORQUE RE-APPLY AS PER SERVICE BULLETIN. SERVICE BULLETIN SB 72-5270 IS THE STANDA RD RE-BUILD FOR SPEY 511-8 AT RRC. 4 F E2EU 2000101800061 20001018 00061 SO 2000 10 18 CA001005005 1 20000906 G 2720 7C1015015 CONTROL CABLE GULSTM GA7 GA7 3960401 SO LYC O320 O320D1D 41508 EA RUDDER CABLES LOOSE W O OTHER F FLT CONT AFFECTED TO TAKEOFF 1 CA (CAN) RUDDER CABLE TENSION NOT WITHIN SPECS - TOO LOOSE - SUSPECT REVERSAL OF RUDDER PEDAL BELLCRANK (7C10302-2) IF CABL E TENSION IS NOT WITHIN SPECS THIS BELLCRANK CAN BE REVERSED AND ARM CAN TRAVEL UNDER SHAFT. SPRING 7C10415-5 KEEPS THI S ARM IN POSITION. (FOUND ONE OF THESE SPRINGS PREVIOUSLY BROKEN CAUSING A SIMILAR OCCURRENCE - GROUND ONLY) RUDDER SYS TEM RIGGED PER S.M. (X) 1 L 7 2 3O 3 O A17SO E274 2000101800062 20001018 00062 2000 10 18 CA001005006 4 20000829 G 2562 0507002 BATTERY LEIGH SHARC7K191 PIPER PA28 PA28140 7102802 SO LYC O320 O320E2A 41508 EA INTEGRATED - ELT UNSERVICEABLE W O OTHER O OTHER IN INSP/MAINT 1 CA 225049 (CAN) AIRCRAFT FLEW FROM 16 APR 1999 TO 16 JUL 1999 (11.7 HRS) TRAINING WITH PILOT-OWNER UNAWARE THAT ELT BATTERY EXPI RED ON APR 1999 DECAL BY R.S. A/C RADIO LTD. ON UNIT SHOWS BATTERY EXPIRED APR 1999, LAST TEST: OCT 5, 1998, NEXT TEST : OCT 5 1999. NO ENTRY OR NOTE, ETC., IN JOURNAL LOG NR 2, P. 1 TO 3 INCLUSIVE. IN AF TECH LOG SECTION 1, LAST REF. T O ELT IS DATED MAY 16/96. IN AF TACH LOG SECT 2, LAST REF TO ELT IS DATED JUN 1986. A/C SOLD TO ACTUAL OWNER AND DELI VERED AT CYXK ON 28 MAR 1999 FEW DAYS PRIOR TO BATTERY DUE. (X) 1 L 7 1 3O 3 O 2A13 E274 2000112200008 20001122 00008 GL 2000 11 22 CA001005009 1 20000808 G 7333 CASC211 REGULATOR RROYCE ENSTRM F28 F28ENSTRM 3300404 GL RROYCE SPEY SPEY55515P 54521 EU FUEL FLOW REG FAILED W O OTHER O OTHER CL CLIMB 1 CA 2562 9786 (CAN) AFTER TAKEOFF, THE FLIGHT CREW WAS UNABLE TO THROTTLE BACK THE ENGINE. THEY SUBSEQUENTLY SHUT THE ENGINE DOWN AND RETURNED TO FIELD. REPLACEMENT OF FUEL FLOW REGULATOR CORRECTED THE PROBLEM. DEFECTIVE FFR UNDER INVESTIGATION AT RRC. (X) 1 G 7 1 3O 4 F H1CE E2EU 2000101800063 20001018 00063 CE 2000 10 18 CA001005010 1 20000409 G 3230 084122510 DOWNLOCK CESSNA 310 310J 2074226 CE CONT O470 IO470U 17026 SO DOWNLOCK ASSY MISALIGNED W O OTHER O OTHER LD LANDING 1 CA 5429 (CAN) - RIGHT GEAR COLLAPSED AFTER LANDING. DOWNLOCK FOUND MISADJUSTED (TOO SHORT). DOWNLOCK BELLCRANK, SIDE BRACE L INK REPLACED. DOWNLOCK READJUSTED. (X) 1 L 7 2 3O 3 O 3A10 3E1 2000101800064 20001018 00064 CE 2000 10 18 CA001005012 1 20000907 G 7920 ENGINE CESSNA 402 402CESSNA 207590K CE CONT O520 TSIO520E 17040 SO MCAULY 3AF32C 3AF32C87 GL ENGINE FAILED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) ENGINE WAS SENT OUT FOR A PROP STRIKE INSPECTION TO AN APPROVED ENGINE OVERHAUL SHOP. AFTER REINSTALLATION PROBLE MS OF FLUCTUATING INTERMITTENT OIL PRESSURE OCCURRED, TROUBLESHOOTING AND INVESTIGATION OF OIL PRESSURE SYSTEM LED TO TH E FINDING OF A PIECE OF MASKING TAPE 23 INCHES LONG IN THE OIL PAN WHICH OBSTRUCTED INTERMITTENTLY THE OIL PRESSURE SCRE EN AND LED TO THE RELATED PROBLEM. AIRCRAFT FLIGHT TESTED SATISFACTORY AND RETURNED TO SERVICE. (X) 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2001032900089 20010329 00089 SO 2001 3 29 CA001005015 1 20000911 G 7713 17766100 HOSE PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2B 41532 EA MANIFOLD DETERIORATED W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA 1207 (CAN) LOW TAKEOFF MANIFOLD PRESSURE. RAPID DIMINUTION OF MANIFOLD PRESSURE DURING CLIMB.ON INSPECTION, HOSE APPEARED BRO WNISH & DRY. DURING MANIPULATION TO CHECK NUMBERS ON/DENT BAND, HOSE BROKE IN TWO PIECES AT 4.5 INCHES FROM DIFF. CONTRO LLER IN VICINITY OF EXHAUST PIPE. 1 L 7 2 3O 3 O A20SO E14EA 2001032900090 20010329 00090 NM 2001 3 29 CA001005017 1 20000907 G 2751 2061141 INDICATOR BOEING 737 7372E1 138448F NM PWA JT8 JT8D9A 52048 NE COCKPIT FAULTY W O OTHER J WARNING INDICATION AP APPROACH 1 CA (CAN) ON APPROACH FLAPS 1 SELECTED & T/E ASYMMETRY OCCURRED. FLAP INDICATING GAUGE FAULTY. GAUGE REPLACED I.A.W. M.M. 27 -58-41 & CHECK SERVICEABLE. NO PROBLEMS FOUND DURING SUBSEQUENT FLIGHT. 2 L 7 2 4F 4 F A16WE E2EA 2000112800081 20001128 00081 SW 2000 11 28 CA001005019 1 20000825 G 5302 206031418007 SUPPORT BRACKET BELL 206033004NA BELL 206 206L 1181522 SW ALLSN 250C 250C20B 03013 GL VERTICAL FIN BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 9918 AOKP02014 (CAN) DURING A DAILY INSPECTION CHECK, TWO BREAKS WERE FOUND IN TH E UPPER MAIN ATTACHMENT POINT FOR THE VERTICAL FIN R EAR SUPPORT. THE BROKEN PIECE IS APPROXIMATELY 1 INCH BY 1 INCH IN SIZE. (X) 1 G 7 1 3U 3 U H2SW E4CE 2000101800066 20001018 00066 EA 2000 10 18 CA001006005 2 20000907 G 7414 4372 MAGNETO PARTEN P68 P68C 6780105 EU LYC O360 IO360A1B6 41514 EA LEFT MAGNETO FAILED W O OTHER O OTHER IN INSP/MAINT 1 CA 485 98060355 (CAN) ENGINE SHUT DOWN NORMAL WENT TO RESTART, NO SPARK LEFT MAGNETO PROBLEM INTERNAL GROUNDING. (X) 1 H 7 2 3O 3 O A31EU 1E10 2000110300059 20001103 00059 CE 2000 11 3 CA001012002 1 20000914 G 5510 04320049 BRACKET CESSNA CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA TOP LT FWD CORNR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 16000 15283403 (CAN) BRACKET CRACKED ALONG WELDED SEAM ALONG LT FRONT TOP OF BRACKET. CRACK RUNS AROUND THE BOLT HOLE OF VERTICAL FIN LT OUTBOARD ATTACH BOLT. (X) 1 H 7 1 3O 3 O NT 3A19 E223 2001032900092 20010329 00092 NE 2001 3 29 CA001012003 1 20000918 G 6320 GEARBOX SKRSKY S61 S61N 8142104 NE GE CT58 CT581401 30011 NE NR 2 ENGINE FAILED W C ABORTED TAKEOFF Y J ENGINE STOPPAGE WARNING INDICATION TO TAKEOFF 1 CA (CAN) TAKEOFF WAS ABORTED WHEN A LOUD BANG WAS HEARD BY FLIGHT CREW. NR 2 ENGINE SHUT DOWN & A/C LANDED BACK ON THE HELI PAD. ON TOUCH DOWN THE TAIL WHEEL MISSED THE PAD & THE AIRCRAFT CAME TO REST ON THE KEEL JUST FORWARD OF THE TAIL WHEEL . ALL PAX WERE UNLOADED & MOVED AWAY FROM THE AIRCRAFT. THE FLIGHT CREW THEN TAXIED THE AIRCRAFT (SINGLE ENGINE) TO THE FAR CORNER OF THE HELIPAD & SHUTDOWN - TSB HAS ALL COMPONENT RECORDS AT THIS TIME. 2 G 7 2 4U 4 U 1H15 1E3 2000110300011 20001103 00011 SO 2000 11 3 CA001012004 1 20000922 G 3230 755956 ROD END PIPER 4204200 PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA FROM ARM BROKEN W A UNSCHED LANDING R PARTIAL RPM/PWR LOSS TO TAKEOFF 1 CA 13223 (CAN) LOG PAGE 665 REFERS. PILOT REPORTED GEAR NOT LOCKED, LIGHT ILLUMINATE AFTER TAKEOFF - RECYCLED 3 TIMES FOR 3 GREE N LIGHT FOR LANDING. MAINTENANCE FOUND LEFT MAIN GEAR RETRACTION ARM BROKEN OFF FROM ROD END. (X) 1 L 7 2 3O 3 O A20SO E14EA 2001032000081 20010320 00081 NM 2001 3 20 CA001012007 1 20000919 G 2782 252T13013 ACTUATOR BOEING 767 767375 NM GE CF6 CF680C2B6 30025 NE NR 5 SPOILER FAILED W O OTHER F J FLT CONT AFFECTED WARNING INDICATION AP APPROACH 1 CA 54992 (CAN) DURING APPROACH , GEAR DOWN, FLAPS 20, AUTOPILOT ON. VIBRATION, FELT LIKE SPOILERS UP. CONTROL WHEEL SHOWED 1/2 TO 3/4 (TOTAL) WHEEL MOVEMENT ROLL TO RIGHT. DISCONNECTED AUTOPILOT & AUTO THROTTLE, A AIRCRAFT, THEN ROLLED HARD TO LEFT, REQUIRED LARGE AMOUNT OF RIGHT WING DOWN TO KEEP A/C LEVEL. LANDED WITH FLAPS AT 25 UNITS, SAME AILERON INPUT REQUIRED TO KEEP WINGS LEVEL, VIBRATIONS DOWN TO & INCLUDING LDG. AILERON & AILERON TRIM CHECKED AS PER MM 27-11-00 P. 501, NO FAULT FOUND. AILERON DROOP CHECK COMPLETED AS PER MM 27-11-00 P. 513, CHECKED OK. FOUND #5 SPOILER VIBRATING HEAVILY WIT H AILERON INPUT. SPOILER ACTUATOR REPLACED AS PER MM 27-61-01 P. 401. TEST FLT COMPLETED, OPERATIONS NORMAL. 2 L 7 2 4F 4 F RT A1NM E13NE 2000110900265 20001109 00265 NE 2000 11 9 CA001012009 1 20000921 G 1230 1368DP CHECK VALVE HP6101002C10 SKRSKY S61 S61N 8142104 NE GE CT58 CT581401 30011 NE CHECK VALVE CRACKED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) DURING REFUELING OF HELICOPTER, A HYDRAULIC LEAK WAS DETECTED. THE FAULT WAS FOUND TO BE A CHECK VALVE/FITTING FO R THE PRIMARY HYDRAULIC MANIFOLD. FITTING WAS REPLACED WITH A LATER P/N STEEL PART. (X) 2 G 7 2 4U 4 U 1H15 1E3 2000112200009 20001122 00009 NE 2000 11 22 CA001012010 1 20000927 G 1230 HOSE SKRSKY S61 S61N 8142104 NE GE CT58 CT581401 30011 NE HYDRAULIC HOSE LEAKING W O OTHER O OTHER CL CLIMB 1 CA (CAN) WHILE IN-FLIGHT, PRIMARY HYDRAULIC PRESSURE DROPPED. AFTER LANDING, FOUND A HYDRAULIC PRESSURE HOSE FROM THE PUMP TO THE MANIFOLD HAD STARTED TO LEAK. HOSE WAS REPLACED AND LEAK CHECKED. AIRCRAFT RETURNED TO SERVICE. (X) 2 G 7 2 4U 4 U 1H15 1E3 2000110300035 20001103 00035 CE 2000 11 3 CA001012011 1 20000929 G 2720 S16751 BEARING SUPPORT CESSNA 172 172R 2072401 CE CENTER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 1077 (CAN) DURING ROUTINE INSPECTION, RUDDER PEDAL TORQUE TUBE SUPPORT BEARING FOUND CRACKED IN HALF AT APPROXIMATELY THE CEN TER OF THE UPPER BEARING HALF. BEARING HALVES WERE BOTH REPLACED. BEARING FAILURE APPEARS TO HAVE OCCURED DUE TO MANUF ACTURING DEFECT. (X) 1 H 7 1 3O NT 3A12 2001033000002 20010330 00002 NE 2001 3 30 CA001012012 1 20000921 G 6310 O-RING SKRSKY S61 S61N 8142104 NE GE CT58 CT581401 30011 NE INPUT COUPLING LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) WE HAVE HAD 5 CASES OF UNACCEPTABLE GREASE LEAKAGE RATES FROM THE INPUT COUPLINGS.WHEN THE COUPLINGS WERE DISASSEM BLED THE O-RING P/N M83248-1-132 WAS FOUND TO BE EITHER FLAT OR DETERIORATED. ACRO (LANGLEY) TOLD ME THAT THEY DID A HAR DNESS TEST ON THEIR BATCH OF O-RINGS AND FOUND THAT THEY FAILED. ATTACHED TO THIS REPORT YOU WIL FIND A COPY OF THE LOT NUMBER OF THE O-RINGS IN QUESTION. 2 G 7 2 4U 4 U 1H15 1E3 2001032900094 20010329 00094 NE 2001 3 29 CA001012013 1 20000918 G 6320 7620903001054 FITTING SKRSKY S76 S76A 8143006 NE TMECA ARRIEL ARRIEL1S1 60030 NE TRANSMISSION CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 10194 (CAN) UPON PURCHASE OF THIS AIRCRAFT AND DISASSEMBLED FOR REFURBISHING. THE RT MAIN TRANSMISSION SUPPORT FITTING WAS FOU ND TO BE CRACKED. DURING INSPECTION. 1 G 7 2 3U 3 U H1NE E19EU 2001032900095 20010329 00095 NE 2001 3 29 CA001012014 1 20000922 G 6710 NAS464P842 BOLT SKRSKY S76 S76A 8143006 NE TMECA ARRIEL ARRIEL1S1 60030 NE M/R PITCH ROD WORN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) UPON PURCHASE OF THIS AIRCRAFT AND DISASSEMBLED FOR INSPECTION AND RE-FURBISHING. THE YELLOW & BLACK M/R PITCH ROD , LOWER ATTACH BOLTS WERE FOUND TO BE EXTREMELY WORN. 1 G 7 2 3U 3 U H1NE E19EU 2001032900096 20010329 00096 EU 2001 3 29 CA001013002 1 20000203 G 6730 AC67246 SERVO SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1B 6OO30 NE ROTOR FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 20 20 EDK277 (CAN) FORE AND AFT SERVO WORKED WELL ON THE INSTALLATION, HOWEVER AFTER 19.7 HOURS IT WAS MOTORING AND CAUSING FEED BACK . UNIT REPLACED. 1 G 7 1 3U 3 U H9EU E19EU 2001032900097 20010329 00097 2001 3 29 CA001013003 4 20000304 G 2562 C4000 ELT BELL 212 212 1181420 SW PWA PT6T PT6T3 52045 EA CABIN FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 403899 (CAN) ELT WAS TESTED AS PER THE 100 HOUR INSPECTION SCHEDULED AND UNIT WOULD NOT ACTIVATE AFTER BEING SHAKEN OR WHEN THE MASTER SWITCH WAS TURNED TO THE ON POSITION. UNIT REPLACED. 1 G 7 1 4U 4 U H4SW E22EA 2001032900098 20010329 00098 EU 2001 3 29 CA001013004 1 20000403 G 2810 SUPPORT BRACKET SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1B 6OO30 NE FUEL CELL CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 6563 (CAN) AFTER THE FUEL CELL WAS REMOVED FOR INSPECTION, CRACKS WERE DETECTED IN THE AREA OF THE UPPER TWO BOLT HOLES FOR THE FUEL CELL SUPPORT SADDLES. CRACKED WERE REPAIRED AS PER MRR 53-10-21-777. 1 G 7 1 3U 3 U H9EU E19EU 2001032900099 20010329 00099 EU 2001 3 29 CA001013005 1 20000403 G 6220 SHIM SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1B 6OO30 NE FREQ ADAPTOR MISSING W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING THE MAIN ROTOR BLADE REMOVAL, NOTICED THAT THE BLADE PINS WERE HARD TO REMOVE. AFTER INSPECTION, FOUND THA T THE SHIMS WERE MISSING FROM THE FREQUENCY ADAPTERS. ONCE THE SHIMS WERE INSTALLED THE BLADE PIN INSTALL WAS NORMAL. 1 G 7 1 3U 3 U H9EU E19EU 2001032900100 20010329 00100 NE 2001 3 29 CA001013006 2 20000405 G 7532 9550158260 BLEED VALVE SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1B 6OO30 NE COMPRESSOR FAILED W O OTHER R PARTIAL RPM/PWR LOSS HO HOVERING 1 CA 1005 (CAN) INTERMITTENT FAILURE TO CLOSE. 1 G 7 1 3U 3 U H9EU E19EU 2001032900102 20010329 00102 EU 2001 3 29 CA001013008 1 20000414 G 6210 350A11001007 BLADE SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1B 6OO30 NE MAIN ROTOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 3398 (CAN) CRACKED AT STATION 570, ALSO LEADING EDGE EROSION. BLADE REPLACED. 1 G 7 1 3U 3 U H9EU E19EU 2000112700052 20001127 00052 NE 2000 11 27 CA001013009 2 20000415 G 7321 0164448380 FUEL CONTROL SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1B 6OO30 NE ENGINE FAILED W O OTHER O OTHER CR CRUISE 1 CA 1758 (CAN) THE ROTOR RPM WAS ADJUSTED SEVERAL TIMES OVER THE COURSE OF A MONTH, AT WHICH TIME THE UNIT FAILED THE CHARACTERI STICS CHECK. UNIT REPLACED. (X) 1 G 7 1 3U 3 U H9EU E19EU 2001032900103 20010329 00103 SW 2001 3 29 CA001013010 1 20000421 G 6220 206031509005 BEARING BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL M/R HEAD LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA 127 (CAN) BEARING FOUND LOOSE IN THE DRAG PIN, POOR STAKING SEEMS TO BE THE CAUSE. 1 G 7 1 3U 3 U H2SW E4CE 2001032900104 20010329 00104 SW 2001 3 29 CA001013011 1 20000425 G 2820 CHECK VALVE BELL 206 206L1 1182107 SW ALLSN 250C 250C30P 03013 GL FUEL SYSTEM FAILED W K NONE X J ENGINE FLAMEOUT WARNING INDICATION IN INSP/MAINT 1 CA (CAN) C-GLMV UNDERGOING AFTER FUEL SYS MAINT CHECK, (2 MIN AT 100 PERCENT NR WITH BOOST PUMPS OFF) WHEN IT FLAMED OUT. A /C HAD BEEN RUNNING FOR APPROX. 10 MIN W/O INCID. PRIOR TO PULLING PUMPS. A/C THEN BLED & RESTARTED & RUN AT 100% FOR 2 0 MIN. BOOST PUMPS WERE TURNED OFF & ENG FLAMED OUT AGAIN. FUEL SYS INVESTIGATED & IT FOUND THAT BOTH OF INLINE CHECK VA LVES WERE STUCK IN OPEN POSITION. ALLOWED ENG DRIVEN PUMP TO DRAW AIR INTO SYS ONCE BOOST PUMPS WERE PULLED OFF LINE. A/ C ONLY HAD 125 LBS OF FUEL ON BOARD SO FWDTANKS WOULD HAVE BEEN EMPTY DURING TEST.AFTER INSP OF CHECK VALVES THEY WERE F OUND TO HAVE SAND IN THEM. INLINE FILTERS WERE ALSO DIRTY 1 G 7 1 3U 3 U H2SW E1GL 2001032900105 20010329 00105 EU 2001 3 29 CA001013012 1 20000427 G 6210 350A11001001 BLADE SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1B 6OO30 NE MAIN ROTOR FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 7207 (CAN) MAIN ROTOR BLADE AFTER BALANCING SEVERAL TIMES WINDS UP FLYING OUT OF TRACK, CAUSING A CYCLIC STICK FEEDBACK WHEN THE HYDRAULICS ARE OFF. 1 G 7 1 3U 3 U H9EU E19EU 2001032900107 20010329 00107 EU 2001 3 29 CA001013014 1 20000519 G 6420 350A33200405 BEARING SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1B 6OO30 NE T/R SPIDER FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 304 ACRO03 (CAN) DURING A 50 HR INSPECTION ON THIS SPIDER, THE BEARING WAS FOUND TO BE ROUGH. NOTE THE BEARING ONLY REACHED 10 PERC ENT OF ITS SERVICE LIFE. 1 G 7 1 3U 3 U NC H9EU E19EU 2001032900110 20010329 00110 EU 2001 3 29 CA001013018 1 20000529 G 6420 350A33200406 BEARING SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1B 6OO30 NE T/R SPIDER FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 678 9 (CAN) EXCESSIVE PLAY FOUND BETWEEN THE BEARING AND SPIDER HOUSING. ALSO FOUND SIGNS OF OVERHEATING WITH LOSS OF GREASE A ND PAINT MELTING. 1 G 7 1 3U 3 U NC H9EU E19EU 2000122900006 20001229 00006 GL 2000 12 29 CA001013019 2 20000531 G 7250 6898734 TURBINE ALLSN BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL ENGINE FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 6893 1248 CAT31125P (CAN) DURING A COMPRESSOR WASH, BRULIN AND WATER MIX WAS COMING OUT OF THE NR 6 AND NR 7 AIR DELIVERY TUBE. UPON FURTHE R INVESTIGATON IT WAS DISCOVERED THAT THE TUBE WAS NOT WELDED TO THE ASSY. (X) 1 G 7 1 3U 3 U H2SW E4CE 2001032900111 20010329 00111 SW 2001 3 29 CA001013020 1 20000613 G 7712 206075185103 GAUGE BELL 206 206L1 1182107 SW ALLSN 250C 250C30P 03013 GL TORQUE FAILED W O OTHER N FALSE WARNING NR NOT REPORTED 1 CA 10 (CAN) THIS GAUGE DID NOT INDICATE PROPERLY FROM THE INITIAL INSTALLATION AND DURING THE REPLACEMENT THE NEEDLE CAME OFF. 1 G 7 1 3U 3 U H2SW E1GL 2001032900112 20010329 00112 GL 2001 3 29 CA001013021 2 20000621 G 7323 23006259 GOVERNOR BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL ENGINE MISINSTALLED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) WHEN CHECKING THE GOVERNOR ON RECEIPT, IT WAS NOTED THAT THE T FITTING WAS INSTALLED IN THE WRONG PORT. FITTING WA S REMOVED AND INSTALLED IN THE CORRECT PORT. 1 G 7 1 3U 3 U H2SW E4CE 2001032900113 20010329 00113 SW 2001 3 29 CA001013022 1 20000628 G 6710 2060627211 ACTUATOR BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL MAIN ROTOR SEIZED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) THE LINEAR ACTUATOR IS SEIZED IN THE MOST FORWARD POSITION. WHEN THE UNIT IS ACTUATED THE MOTOR RUNS AND THEN STOP S RIGHT AWAY. 1 G 7 1 3U 3 U H2SW E4CE 2001032900114 20010329 00114 SW 2001 3 29 CA001013023 1 20000821 G 6230 206010450113 SEAL BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL SWASHPLATE SPINNING W K NONE O OTHER IN INSP/MAINT 1 CA 14328 212 (CAN) THE UPPER SEAL FOUND SPINNING IN THE CAP. 1 G 7 1 3U 3 U H2SW E4CE 2001032900115 20010329 00115 EU 2001 3 29 CA001013024 1 20000920 G 6210 350A11001007 BLADE SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1B 6OO30 NE MAIN ROTOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 3398 7252 (CAN) BLADE CRACKED AT STATION 570, ALSO LEADING EDGE EROSION. 1 G 7 1 3U 3 U H9EU E19EU 2000112000026 20001120 00026 CE 2000 11 20 CA001013025 1 20000831 G 2824 AHE05D92 PUMP CESSNA 401 401 207590C CE CONT O520 TSIO520EB 17040 SO MCAULY 3AF32C 3AF32C87 GL POWER LEAD SHORTED W O OTHER B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA 109 (CAN) THIS PUMP IS LOCATED ON AFT SIDE OF BACK WALL OF TIP TANK. ITS PURPOSE IS TO CIRCULATE FUEL FROM FRONT OF TANK TO CENTER SECTION OF TANK WHERE FUEL PICKUP IS. IT IS CONNECTED TO TEN AMP CCTT BREAKER, SHARED BY THE LDG LIGHT ON THAT SIDE. BREAKER HAD TRIPPED IN-FLIGHT AND PILOT WROTE SNAG UP AS LDG LIGHT PROBLEM. WHEN TROUBLESHOOTING SYS, BREAKER RE SET AND POWER APPLIED TO SYS. ARCING HEARD AND POWER LEAD BEGAN TO SMOKE. BREAKER TRIPPED IMMEDIATELY. IS PMA UNIT A ND HAD BEEN INST IN ACFT ONLY 109.2 HRS BEFORE IT FAILED. WERE NO EXTERNAL SIGNS THAT POWER LEAD CHAFED OR WORN. SHORT APPEARS TO HAVE OCCURRED INSID E CONNECTOR TO FUEL PUMP. (X) 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2000112000027 20001120 00027 CE 2000 11 20 CA001013026 1 20000909 G 3231 08411066 BELLCRANK CESSNA 401 401 207590C CE CONT O520 TSIO520EB 17040 SO MCAULY 3AF32C 3AF32C87 GL ACTUATING LINK BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 6814 (CAN) AFTER LANDING, PILOT NOTICED THE RT MAIN GEAR DOOR WAS NOT CLOSED. MAINTENANCE DISCOVERED THE DOOR ACTUATING BELL CRANK HAD BROKEN HALF WAY BETWEEN THE PIVOT AND THE ACTUATING LINKAGE. HAVE SEEN THIS SAME PART BREAK IN THE SAME PLACE ON AN AIRCRAFT THAT HAD OPERATED IN THE PAST. FROM THE COLOR OF THE METAL AT THE FAILURE, IT APPEARS THAT THE FAILURE D ID NOT OCCUR ALL AT ONCE. ABOUT 70 PERCENT OF THE CROSS SECTION APPEARED TO BE OXIDIZED. BOTH TIMES HAVING SEEN THIS FAILURE, NO OTHER PROBLEMS HAVE RESULTED FROM THE DOOR HANGING OPEN, BUT THERE IS THE POTENTIAL FOR THE GEAR DOOR TO JAM OR OTHERWISE CAUSE PROBLEMS. (X) 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2001033000003 20010330 00003 NM 2001 3 30 CA001013027 1 20001007 G 5302 500N34223 FITTING 500N34215 DOUG 600N 600N 3027377 NM TAIL BOOM CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 1496 (CAN) DURING REMOVAL OF TAILBOOM ASSY TO FACILITATE MAINTENANCE A CRACK WAS DISCOVERED AT THE UPPER RT TAILBOOM ATTACH F ITTING. FURTHER INVESTIGATION IN THE FUSELAGE STRUCTURE REVEALED MORE CRACKING IN THE FUSELAGE TAILBOOM SUPPORT STRUCTUR E. 1 G 7 1 3U NC H3WE 2001032900116 20010329 00116 NM 2001 3 29 CA001013028 1 20001007 G 6210 369D21102523 BLADE DOUG 600N 600N 3027377 NM MAIN ROTOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 1233 099992836 (CAN) CRACK DETECTED IN M/R BLADE ASSY LOWER SKIN APPROX 16 INCHES FROM ROOT FITTING. CRACK APPEARS TO HAVE STARTED IN T HE CENTRE OF THE BLADE SKIN AND PROGRESSED IN A CHORDWISE MANNER TOWARD THE TRAILING EDGE AND THE BLADE SPAR. CRACK WAS DISCOVERED DURING A 100 HOUR INSP OF THE M/R BLADES, AS A PRECAUTION ALL M/R BLADES (6) WERE REPLACED. M/R BLADES REMOVE D HAVE BEEN RETURNED TO THE MANUFACTURER FOR FURTHER EVALUATION AT THEIR REQUEST. 1 G 7 1 3U NC H3WE 2001032900117 20010329 00117 NM 2001 3 29 CA001013029 1 20001007 G 2840 60N810713 INDICATOR DOUG 600N 600N 3027377 NM FUEL QUANTITY FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ERRATIC FUEL QUANTITY INDICATION DISCOVERED DURING REFUELING. FUEL QUANTITY INDICATOR WAS FOUND TO BE INDICATING M ORE FUEL ON BOARD THAN THE AIRCRAFT COULD BE SERVICED WITH. AIRCRAFT WAS DEFUELED AND FUEL SYSTEM WAS RECALIBRATED AND T HE DEFECT APPEARED TO RECTIFIED. PROBLEM OCCURRED AGAIN AND FUEL INDICATOR WAS REPLACED AT AFT 1402.3 HOURS. REPORT IS B EING SUBMITTED BECAUSE THIS IS THE SECOND OCCURRENCE OF THIS PROBLEM. FUEL INDICATOR WAS PREVIOUSLY REPLACED AT AFT 990. 4 HOURS. 1 G 7 1 3U NC H3WE 2000112000028 20001120 00028 SO 2000 11 20 CA001013030 1 20000929 G 2731 41734078 CONTROL CABLE PIPER PA31 PA31 7103102 SO HARTZL HCC4Y HCC4YR2 GL ELEVATOR TRIM FRAYED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) UPON ROUTINE INSPECTION OF ELEVATOR TRIM SYSTEM, AFT TRIM CABLE FOUND FRAYED AND WITH BROKEN STRANDS. DAMAGE TO CABLE BELIEVED TO BE CAUSED BY SHARP BENDS AND HIGH FREQUENCY OF MOVEMENT USING ELECTRIC TRIM SERVO. (X) 1 L 7 2 3O A20SO 5 C P52GL 2001032900118 20010329 00118 SW 2001 3 29 CA001013032 1 20000913 G 6710 212010403005 LEVER BELL 205 205A1 1181414 SW LYC T53 T5313B 41549 NE COLLECTIVE FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) PIN PRESSED INTO ASSEMBLY CAME LOOSE. FOUND WHEN SWASHPLATE ASSY CHANGE. 1 G 7 1 4U 4 U H1SW E17EA 2001032900119 20010329 00119 SW 2001 3 29 CA001013033 1 20000929 G 2910 212076372001 LINE BELL 205 205A1 1181414 SW LYC T53 T5313B 41549 NE HYD SYSTEM CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA 293 (CAN) NR 1 HYDRAULIC SYSTEM RETURN LINE WAS CHAFED WITH NR 2 PUMP PRESSURE LINE, REPLACED. THIS TUBE ASSEMBLY WAS INSTA LLED 293.1 HOURS BEFORE.FOUND PRESSURE LINE WAS ROUTED OTHER SIDE OF NR 2 PUMP. 1 G 7 1 4U 4 U H1SW E17EA 2001032900120 20010329 00120 WP 2001 3 29 CA001013034 1 20000928 G 2435 150SG1052B BEARING HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL STARTER GEN LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA 433 (CAN) STARTER-GENERATOR WAS REMOVED TO INVESTIGATE AN ENGINE VIBRATION. AME FOUND THE DRIVE END BEARING WAS VERY LOOSE, WITH RADIAL PLAY. SENT UNIT TO AMO. AMO DISASSEMBLED & FOUND D.E. BALL BEARING HAD CONSIDERABLE PLAY IN BOTH RADIAL (.01 0) X AXIAL (.025) DIRECTIONS. NO OTHER FAULTS FOUND.NEW BEARING INSTALLED & UNIT TESTED AND RETURNED RO SERVICE.U/S BEAR ING SENT TO OEM FOR WARRANTY ASSESSMENT. 1 G 7 1 3U 3 U H3WE E4CE 2000112700053 20001127 00053 WP 2000 11 27 CA001016002 1 20000920 G 2435 6054424 STARTER HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL STARTER SEAL FAILED W O OTHER O OTHER CR CRUISE 1 CA 22 (CAN) PILOT NOTICED SPRAY OUT OF ENGINE BAY AREA AND WHEN HE CHECKED INSTRUMENT PANEL, TORQUE GAUGE WAS FLUCTUATING AND OIL PRESSURE WAS DROPPING BELOW 30 PSI. AIRCRAFT WAS LANDED AND LARGE AMOUNT OF OIL NOTICED COMING OUT OF STARTER AREA. STARTER WAS REMOVED AND SEAL WAS FOUND TO HAVE COME OUT OF HOLE. DUE TO POSSIBLE ENGINE DAMAGE AND METAL ON CHIP PLUG , AIRCRAFT WAS TRUCKED BACK TO BASE. (X) 1 G 7 1 3U 3 U H3WE E4CE 2000112000029 20001120 00029 SO 2000 11 20 CA001016003 1 20000914 G 2912 460635 HOUSING PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA THREADED AREA CRACKED W O OTHER K FLUID LOSS CL CLIMB 1 CA (CAN) UPON CLIMB OUT, PILOT SELECTED GEAR UP AT WHICH POINT THE GEAR WOULD NOT LOCK IN THE UP POSITION. PILOT THEN TRIE D TO CYCLE THE GEAR DOWN, BUT THE GEAR WOULD NOT RESPOND. THE PILOT MADE AN EMERGENCY LANDING GEAR EXTENSION SUCCESSFUL LY ACHIEVING THREE GREEN. A LANDING WAS MADE WITHOUT INCIDENT. UPON INSPECTION, MAINTENANCE FOUND A LARGE HYDRAULIC LE AK FROM THE RT ENGINE COWL CAUSED BY A CRACKED HYDRAULIC FILTER HOUSING LOCATED ON THE ENGINE FIREWALL. A NEW HOUSING W AS INSTALLED WITH NO FURTHER PROBLEMS. IT IS FELT THE HOUSING FAILED DUE TO OVERTORQUEING. (X) 1 L 7 2 3O 3 O A20SO E14EA 2001032000083 20010320 00083 NM 2001 3 20 CA001016005 1 20000915 G 2421 SHAFT 976J1198 BOEING 727 727171C 1384057 NM PWA JT8 JT8D7A 52053 NE GENERATOR FAILED W H DEACTIVATE SYST/CIRCUITS H ELECT. POWER LOSS-50 PC CR CRUISE 1 CA 1509 YL4921 (CAN) DURING CRUISE FLIGHT NR 3 ENGINE GENERATOR INDICATED UNDER EXCITATION FOLLOWED BY UNDER VOLTAGE THEN A FIELD TRIP. THE RESIDUAL VOLTAGE WAS BELOW MINIMUM AS SUCH THE CSD WAS DISCONNECTED AND THE ELECTRICAL BUSS LOADS WERE REDUCED. THE GENERATOR WAS FOUND TO HAVE A FAILED INPUT SHAFT. THE GENERATOR WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE. 2 L 7 3 4F 4 F A3WE E2EA 2000112000030 20001120 00030 CE 2000 11 20 CA001016006 1 20000902 G 5540 05310081 HORN CESSNA 053100681 CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA STOP BOLT CONTAC WORN W K NONE O OTHER IN INSP/MAINT 1 CA 10560 (CAN) RUDDER WAS ALLOWED TO MOVE BEYOND TRAVEL LIMITS DUE TO WORN HORN P/N 0531008-1. HORN WAS REPLACED WITH NEW FACTOR Y PART AND NEW RUDDER STOP NUT P/N MS21042L5 AND BOLT AN5-5A. RUDDER CHECKED FOR TRAVEL AND SAFETY. (X) 1 H 7 1 3O 3 O NT 3A12 E274 2001032000084 20010320 00084 NM 2001 3 20 CA001016007 1 20000921 G 2751 106079113 INDICATOR BOEING 737 737284 138448R NM PWA JT8 JT8D9A 52048 NE TE FLAPS SPLIT W O OTHER N FALSE WARNING AP APPROACH 1 CA 4490 156 (CAN) ON APPROACH FLIGHT CREW WERE UNABLE TO EXTEND THE FLAPS PAST 5 UNITS DUE TO AN ASYMMETRY INDICATION. AN UNEVENTFUL FLAPS 5 LANDING WAS CARRIED OUT. MAINTENANCE INSPECTED THE TRAILING EDGE FLAPS WITH NO FAULTS FOUND. THE PROBLEM WAS TR ACED TO THE INDICATOR, WHICH WAS REPLACED. THE SYSTEM THEN CHECKED SERVICEABLE AND THE AIRCRAFT RETURNED TO SERVICE. 2 L 7 2 4F 4 F A16WE E2EA 2000112700054 20001127 00054 EU 2000 11 27 CA001016010 1 20000920 G 2435 29282PML BRUSHES SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1B 6OO30 NE STARTER FAILED W O OTHER O OTHER IN INSP/MAINT 1 CA 22000 458 114 (CAN) PREMATURE WEAR OF STARTER BRUSHES AND ARMATURE. THERE APPEARS TO BE NO EXCESS CURRENT DRAW ON GENERATOR. NO OTHER ELECTRICAL ABNORMALITIES ON THIS AIRCRAFT. BRUSH WEAR WAS DETECTED ON 100 HOUR INSPECTION. STARTER GENERATOR WAS SENT TO CANADIAN AERO ACCESSORIES WITH A COPY OF THIS SDR. PLEASE FIND ATTACHED A COPY OF THE COMPONENT CARD. 1 G 7 1 3U 3 U H9EU E19EU 2001032000085 20010320 00085 NM 2001 3 20 CA001016011 1 20001001 G 5320 6937241 BOLT BOEING 737 7372M8 1384483 NM PWA JT8 JT8D15 52051 NE ELEVATOR PCU MISSING W C ABORTED TAKEOFF F J FLT CONT AFFECTED WARNING INDICATION TX TAXI/GRND HDL 1 CA (CAN) CREW REPORTED ON TAXI OUT WHEN THEY CHECKED THE FLIGHT CONTROLS THE ELEVATOR FELT VERY RESTRICTED IN DOWN TRAVEL M OTION. OPERATION FELT NORMAL WITH A SYSTEM HYDRAULIC DEPRESSURIZED. UPON INVESTIGATION FOUND A SYSTEM ELEVATOR PCU INPUT ROD TO ELEVATOR INPUT TORQUE TUBE ATTACH BOLT NOT INSTALLED. BOLT WAS REINSTALLED WITH NEW WASHER AND LOCKNUT. ELEVATOR SYSTEM FUNCTION CHECKED I.A.W. MAINTENANCE MANUAL 27-31-101. NOTE: BOLT WAS FOUND AT BOTTOM OF TAIL CONE. NO NUT OR WAS HER WAS PRESENT. 2 L 7 2 4F 4 F A16WE E2EA 2000112700055 20001127 00055 GL 2000 11 27 CA001017007 2 20000915 G 7530 6890550 COMPRESSOR BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL AFT DIFFUSER CRACKED W O OTHER O OTHER IN INSP/MAINT 1 CA 4517 460 CAC2458 (CAN) DURING 100-HOUR INSPECTION OF THE HELICOPTER, A BLACK LINE WAS OBSERVED ON ONE OF THE COMPRESSOR ASSEMBLY MOUNTING PAD ARMS WHICH FORMS THE REAR DIFFUSER OF THE COMPRESSOR. CLOSER VISUAL INSPECTION WITH MAGNIFYING GLASS CONFIRMED CRA CK. THE CRACKED MOUNTING ARM IS AT THE 4:00 POSITION WHEN LOOKING AT THE AFT SIDE OF THE COMPRESSOR. COMPRESSOR ASSEMBL Y FOR REPAIR. (X) 1 G 7 1 3U 3 U H2SW E4CE 2001033000005 20010330 00005 CE 2001 3 30 CA001017008 1 20000923 G 3246 16218000 WHEEL CLEVELAND 40289 BEECH 100 A100 1152915 CE PWA PT6 PT6A28 EA MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A ROUTINE INSPECTION MAINTENANCE NOTICED A CRACK IN THE PAINT IN THE BEAD AREA. AREA WAS CLEANED WITH A LI QUID DYE PEN INSPECTION FOUND A 2.5 INCH CRACK FOLLOWING THE CIRCUMFERENCE. WHEEL ASSEMBLY WAS REPLACED. 1 L 7 2 3T 4 T A14CE E4EA 2000112000032 20001120 00032 SO 2000 11 20 CA001017009 2 20000927 G 7414 BL5005561R MAGNETO CONT CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO LT MAGNETO FAILED W O OTHER R PARTIAL RPM/PWR LOSS CR CRUISE 1 CA 35 810084R (CAN) MAGNETO FAILED REPEATEDLY ON THAT AIRCRAFT AND ENGINE. THIS ONE LASTED 35.4 HOURS. UNIT REPLACED BY OVERHAULED ON E. (X) 1 H 7 1 3O 3 O A4CE E5CE 2001033000006 20010330 00006 CE 2001 3 30 CA001017010 1 20001004 G 5521 5061000090 BRACKET BEECH 90 C90A 1152911 CE PWA PT6 PT6A21 52043 EA ELEVATOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 4478 (CAN) DURING A ROUTINE MAINTENANCE, IT WAS OBSERVED THAT THERE WAS A CRACK ON THE ELEVATOR INBOARD RIB BRACKET, UPON DI SASSEMBLY OF THE PART FOR REPLACEMENT, IT WAS NOTICED THAT THE INBOARD RIB WAS ALSO CRACKED IN THE SAME AREA. THE CRACK ON THE RIB WAS FROM A RIVET HOLE. THIS PROBLEM HAS BEEN REPORTED BY US INITIALLY ON AIRCRAFT. 1 L 7 2 3T 4 T RT 3A20 E4EA 2000112000033 20001120 00033 WP 2000 11 20 CA001017011 2 20000724 G 7250 31081821 TURBINE WHEEL GARRTT 310355011 GARRTT TPE331 TPE33110U 01514 WP T/E OF BLADE BROKEN W O OTHER O OTHER IN INSP/MAINT 1 CA 3796 (CAN) ENGINE REMOVED FOR HIGH TAXI AND GROUND IDLE SNAG. DISASSEMBLY REVEALED NR 1 COMPRESSOR IMPELLER HAD A PIECE BROK EN OUT OF THE TRAILING EDGE OF 1 BLADE .085 INCH UP FROM THE PLATE .480 INCH FROM THE OUTER RIM OF THE PLATE. THE RESULT ING DAMAGE DOWN STREAM FROM THE NR 1 IMPELLER IS EXTENSIVE. IT CONSISTS OF 3101829 SHROUD, 3103496 DIFFUSER, 893482, NR 2 IMPELLER, 893384 DIFFUSER, 3102022 HOUSING, 3108164-2 NR 1 ROTOR, 3102106-10 NR 2 ROTOR, 3102655-2 NR 3 ROTOR, 310151 3-17 STATOR, 3101515-6 STATOR, 5 OF 3101846 NOZZLE SEGMENTS, 12 OF 3103128 SHROUD SEGMENTS. (X) 4 T E4WE 2000112000034 20001120 00034 CE 2000 11 20 CA001018003 1 20000915 G 5540 995241791 SPRING BEECH 100600012 BEECH 100 A100 1152915 CE PWA PT6 PT6A28 EA END OF SPRING BROKEN W O OTHER O OTHER IN INSP/MAINT 1 CA 2469 (CAN) DURING UNSCHEDULED MAINTENANCE, BOTH LT AND RT RUDDER RETURN SPRINGS WERE FOUND BROKEN. NO FLIGHT CONTROL PROBLEM S WERE REPORTED FROM THE FLIGHT CREW. THE SPRINGS WERE REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. THESE RETURN SPRI NGS ARE AN IMPROVED VERSION CHANGED AS A RESULT OF AN OPTIONAL SERVICE BULLETIN. THE IMPROVEMENT WAS A LONGER SERVICE LI FE. (X) 1 L 7 2 3T 4 T A14CE E4EA 2001033000008 20010330 00008 SW 2001 3 30 CA001018004 1 20000926 G 5551 22123 BRACKET BBAVIA 8 8GCBC 1220803 SW LYC O360 O360C2E 41514 EA STABILIZER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 7826 (CAN) ON 100 HOUR INSPECTION, LOWER STABILIZER ATTACHMENT BRACKET, WHICH SPANS BETWEEN TAIL POST AND STAB AFT SPAR FITTI NG, WAS FOUND CRACKED APPROXIMATELY 1 INCH UP FROM LOWER WELD AREA. CRACKS FOUND ON BOTH SIDE ANGLES. 1 H 7 1 3O 3 O A21CE E286 2000112000035 20001120 00035 2000 11 20 CA001018005 4 20000928 G 2562 BS2166 BATTERY NARCO ELT10C CESSNA 150 150G 2071816 CE CONT O200 O200A 17020 SO BATTERY WRONG PART W O OTHER O OTHER IN INSP/MAINT 1 CA 81688 (CAN) ELT WAS EQUIPPED WITH A NON-APPROVED BATTERY FOR THE ELT TYPE. REF: ANO B014 EDITION 4, NOVEMBER 20, 1998. (X) 1 H 7 1 3O 3 O 3A19 E252 2001033000009 20010330 00009 EA 2001 3 30 CA001018006 2 20000921 G 8550 LW13388 GASKET CESSNA 172 172N 2072434 CE LYC O320 O320H1AD 41508 EA MCAULY 1C160 1C160DTM GL OIL SYSTEM DETERIORATED W K NONE O OTHER IN INSP/MAINT 1 CA 240 (CAN) OIL FILTER ADAPTER REMOVED FOR INSPECTION OF GASKET IN RESPONSE TO EMERGENCY AD 2000-18-53 AND FOUND GASKET TO BE IN A MUSHY, SOFT, DETERIORATING CONDITION, RATHER THAN THE FIRM RUBBER IT IS SUPPOSED TO BE LIKE. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2001033000010 20010330 00010 EA 2001 3 30 CA001018007 2 20000921 G 8550 LW13388 GASKET PIPER PA44 PA44180 7104402 SO LYC O360 O360E1A6 41514 EA OIL SYSTEM DETERIORATED W K NONE O OTHER IN INSP/MAINT 1 CA 200 (CAN) OIL FILTER ADAPTER REMOVED FOR INSPECTION OF GASKET IN RESPONSE TO EMERGENCY AD 2000-18-53 AND FOUND GASKET TO BE IN A MUSHY, SOFT DETERIORATING CONDITION, RATHER THAN THE FIRM RUBBER IT IS SUPPOSED TO BE LIKE. 1 L 7 2 3O 3 O A19S0 E286 2001011105393 20010111 05393 CE 2001 1 11 CA001018011 1 20000926 G 6100 BEARING MCAULY C2A34C204 CESSNA 180 180K 2072624 CE CONT O470 O470U 17026 SO MCAULY 2A34C C2A34C204 GL PROPELLER FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 1694 317 765389 (CAN) PROPELLER PARTS CORRODED BEYOND REPAIR. BLADE BEARING RACES AND BALLS. BLADE SPLIT RETAINING RINGS. PISTON AND PISTON PINS. CYLINDER ACTUATING PINS. NOTE: THESE PARTS CORRODED AFTER 6 YEARS, NOW REGULATION IS 10 YEARS. (X) 1 H 7 1 3O 3 O 5A6 E273 5 C P3EA 2001033000016 20010330 00016 2001 3 30 CA001018016 4 20001003 G 3418 727422 CIRCUIT BREAKER BEECH 99 B99 1154004 CE PWA PT6 PT6A28 EA STALL WARNING TRIPPED W O OTHER N FALSE WARNING CL CLIMB 1 CA (CAN) PILOT DEPARTED AIRPORT, A GEAR UP SELECTION WAS MADE AND THE GEAR DID NOT RETRACT. THE CONTROL CB WAS POPPED. PILO T ELECTED TO RETURN TO BASE TO HAVE IT CHECKED OUT. AIRCRAFT WAS PUT ON JACKS AND GEAR SWINGS WERE CARRIED OUT AND NOTHI NGWAS FOUND. FURTHER INVESTIGATION SHOWED THE CONTROL CB WAS PULLED THE NIGHT BEFORE FOR MAINTENANCE REASONS. THE CB WAS NOT RESET AND NO ONE NOTICED UNTIL THE ARICRAFT WAS IN THE AIR AND THE GEAR WOULD NOT RETRACT. 1 L 7 2 3T 4 T A14CE E4EA 2001033000017 20010330 00017 EA 2001 3 30 CA001018017 1 20000928 G 3230 6A05533001 SPRING WIPLINEINC 8000 DHAV DHC3 DHC3 2800202 EA MLG BROKEN W O OTHER O OTHER AP APPROACH 1 CA (CAN) PILOT COMPLAINED OF NO GEAR DOWN AND LOCK INDICATION - RT MAIN GEAR. UPON INSPECTION FOUND LOCK SPRING BROKEN AND HALF MISSING, PLUS COVER TORN AWAY. LOCKING MECHANISM FOUND NON FUNCTIONAL DUE TO STRAIN OF BOLT BECOMING BENT WHEN FORW ARD LOCK CONTACTED GEAR TUNNEL TOP. SPRING AND BOLT WERE REPLACED. FUNCTION TESTED - OK. AIRCRAFT WAS RETURNED TO SERVIC E. IT SHOULD BE FURTHER NOTED THAT THE OTHER MAIN GEAR LOCK SPRING WAS FOUND CRACKED AND REPLACED AT THE SAME TIME. 1 H 7 1 3R A815 2000112000036 20001120 00036 SO 2000 11 20 CA001019003 2 20000920 G 8530 ST68ER CYLINDER CONT CESSNA 182 182Q 2072732 CE CONT O470 O470U 17026 SO MCAULY 2A34C C2A34C204 GL INTKE & EXH VALV FAILED W O OTHER O OTHER IN INSP/MAINT 1 CA 1702 286771R (CAN) DURING ROUTINE MAINTENANCE, A LOW DIFFERENTIAL COMPRESSION READING WAS NOTED ON THREE OF THE SIX CYLINDERS. IT WA S ALSO NOTED THE LEAKAGE WAS APPARENTLY COMING FROM THE EXHAUST VALVES ON TWO CYLINDERS AND FROM THE INTAKE VALVE ON ANO THER. THE REMAINING THREE CYLINDERS ALSO SHOWED A DECREASED READING COMPARED TO PREVIOUS CHECKS ON RECORD. ALL SIX CYLI NDERS WERE REMOVED AND FORWARDED TO AN ENGINE REPAIR FACILITY FOR EVALUATION. THE CYLINDERS WERE REPAIRED WITH NEW PART S AS NECESSARY. FIVE OF THE INTAKE VALVES ARE SHOWING THE FACE OF THE VALVE WORN BYEOND GRINDING LIMITS. ALL OF THE GU IDE AND STEM WEAR WAS DEEMED NORMAL CONSIDERING THE AMOUNT OF TIME ON THESE CYLINDERS. (X) 1 H 7 1 3O 3 O NT 3A13 E273 5 C P3EA 2000112000037 20001120 00037 EU 2000 11 20 CA001019005 1 20001002 G 3233 9603001111 ACTUATOR PILATS 5322012039 PILATS PC12 PC1245 EU NOSE SHAFT SEAL LEAKING W O OTHER K FLUID LOSS IN INSP/MAINT 1 CA 1423 (CAN) DURING AN ANNUAL INSPECTION, A LEAK WAS NOTED ON THE NOSE GEAR ACTUATOR. THE ACTUATOR WAS NOTED LEAKING IN THE SH AFT SEAL. THE ACTUATOR WAS REPLACED WITH A SERVICEABLE SPARE AND WILL BE MONITORED ON A REGULAR BASIS TO DETERMINE INTEG RITY. (X) 1 L 7 1 3T RT A78EU 2000112000038 20001120 00038 CE 2000 11 20 CA001019008 1 20000913 G 2730 05341221 ELEVATOR CESSNA 172 172S 2072439 CE BELLCRNK BRG HOL WORN W O OTHER O OTHER IN INSP/MAINT 1 CA 154 (CAN) ELEVATOR WORN. 1 H 7 1 3O NT 3A12 2001033000023 20010330 00023 EA 2001 3 30 CA001019009 2 20000911 G 8520 STUD CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA MCAULY 1C160 1C160DTM GL ROCKR CAM BROKEN W O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) THIS INCIDENT OCCURRED 30 MI EAST OF ATIKOKAN. CREW CONTINUED FLIGHT UNITL REACHING THE ATIKOKAN AIRPORT. FAILURE OF NR 2 CYLINDER EXHAUST ROCKER CAM STUD. THE CONDITION OF THE BROKEN STUD AND NUT WOULD INDICATE THAT THE NUT WAS INSTA LLED IN A CROSS THREADED POSITION; THEREFORE IF A TORQUE WAS USED, THERE WAS NOT SUFFICIENT TORQUE ON THE ROCKER CAM TO HOLD IT TIGHT. COMPLETE CYLINDER ASSEMBLY CHANGED WITH SERVICEABLE UNIT. ENGINE GROUND RUN WAS NORMAL. AIRCRAFT RETURNED TO SERVICE. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2001032000087 20010320 00087 NM 2001 3 20 CA001019010 1 20000921 G 5754 65173531 RIB BOEING 727 72725 1384006 NM PWA JT8 JT8D7B 52053 NE NR 8 SLAT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A ROUTINE A CHECK IT WAS NOTICED THAT THE NR 8 SLAT ACTUATOR MOUNT WAS CRACKED AT THE ROD END ATTACH POINT. SLAT WAS REMOVED AND MOUNT BRACKETS AND RIB FOUND TO BE BROKEN. SLAT WAS REPLACED AND AIRCRAFT RELEASED. REPLACEMENT PE R BOEING M.M. 27-81-11. 2 L 7 3 4F 4 F A3WE E2EA 2001033000024 20010330 00024 WP 2001 3 30 CA001019011 2 20000922 G 7200 NAS1303 BOLT GARRTT TFE7312 AMD FALC10 FALCON10 2730101 EU GARRTT TFE731 TFE7312 01518 WP ENGINE WRONG PART W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA P73211 (CAN) ENGINE AFTERBODY LT FOUND SEVERAL FASTENERS WERE NOT NAS 1303 PER FALCON 10 I.P.C. 54-22-05 PAGE 1-1 - INCORRECT H ARDWARE, REPLACED BY CORRECT HARDWARE PER FALCON 10 IPC 54-22-05 PAGE 1-1. 2 L 7 2 4F 4 F A33EU E6WE 2000103100107 20001031 00107 EA 2000 10 31 CA001019012 2 20000925 G 7414 M3100 IMPULSE COUPLING SLICK 4372 ZLIN 242 Z242L 9970204 EU LYC O360 AEIO360A1B6 41514 EA LATCHING PAWL BROKEN W O OTHER O OTHER IN INSP/MAINT 1 CA 2135 96100405 (CAN) A STUDENT PILOT REPORTED ENGINE WOULD NOT START. MAINT NOTICED IMPULSE COUPLING WAS NOT SNAPPING (THE LT MAGNETO HAS IMPULSE COUPLING ONLY). LT MAGNETO WAS REMOVED, FOUND ONE OF IMPULSE COUPLING PAWL RIVETS HAD SHEARED CAUSING PAWL TO FALL DOWN BEHIND REMAINING PAWL NOT ALLOWING IT TO ENGAGE ON MAGNETO STOP PIN. MAGNETO ROTOR SHAFT WAS ALSO DAMAGED BEYOND REPAIR BY UNATTACHED PAWL. SLICK 500 HR INSP REQUIRES AN INSP BE CARRIED OUT ON IMPULSE HUB ASSY PAWL AND THEIR RETAINING RIVETS - A MEASUREMENT IS GIVEN IN SLICK MAINT MANUAL FOR CLEARANCE BETWEEN PAWL BOSS AND PAWL PLATE. (X) 1 L 7 1 3O 3 O 0 A76EU 1E10 2001032000088 20010320 00088 NM 2001 3 20 CA001019013 1 20000926 G 2710 82700566S001 CONTROL CABLE DHAV DHC8 DHC8* NM PWA PW120 PW123 NE LT AILERON BROKEN W K NONE F FLT CONT AFFECTED IN INSP/MAINT 1 CA 6500 (CAN) PILOT REPORTED ON WALKAROUND, ITEM STICKING OUT OF FLAP WELL, MAINTENANCE CALLED IN, DISCOVERED BROKEN CABLE STRAN DS AT STATION YW 174 AT THE FAIR LEAD. ITEM WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE. 2 H 7 2 4T 4 T RT A13NM E20NE 2001033000025 20010330 00025 NE 2001 3 30 CA001019014 2 20000926 G 7532 310533701 GASKET DHAV DHC8 DHC8* NM PWA PW120 PW123 NE PORT ENGINE BLOWN W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 8927 (CAN) LIAT, OPERATOR MAINTENANCE CONTROL REPORT:AFTER TAKEOFF, PORT ENGINE TORQUE, STARTED TO FLUCTUATE UNCONTROLLABLY. POWER LEVER WAS RETARDED TO AVOID OVER-TORQUE CONDITION, FLUCTUATIONS CONTINUED, AND PORT CONDITION LEVER WAS MOVED TO S TART/FEATHER. AIRCRAFT RETURNED TO LAND UNEVENTFULLY. ENGINE REPORT:ON EXAMINATION HBOV GASKET WAS BLOWN, GASKET WAS REP LACED AND EGR CARRIED OUT SATISFACTORY. AIRCRAFT RETURN TO SERVICE. 2 H 7 2 4T 4 T RT A13NM E20NE 2001033000027 20010330 00027 CE 2001 3 30 CA001019017 1 20000814 G 3397 99131 WIRE AVTECH CESSNA 560 560XL 2076702 CE LT CONSOLE BURNED OUT W B H EMER. DESCENT DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS DE DESCENT 1 CA 96 600 (CAN) UPON DESCENT INTO MUSKOKA CAPTAIN NOTICED SMOKE BY HIS L/H KNEE, AT FIRST MINOR, THEN INTENSIFIED. CAPTAIN DECLARE D AN EMERGENCY AND INITIATED AN EMERGENCY DESCENT AND LANDING AT MUSKOKA. PASSENGERS AND CREW DEPARTED THE AIRCRAFT WITH NO INJURIES. MAINTENANCE PERSONEL DISASSEMBLED COCKPIT PILOTS SIDE FOR INVESTIGATION OF SMOKE IN THE COCKPIT. MAINTENAN CE PERSONEL FOUND SOME OVERHEATED/ BURNED WIRING AT THE PC038 CONNECTOR TO THE EMERGENCY LIGHTING BATTERY. THE BATTERY W AS SENT TO CESSNA FOR EVALUATION AND THEY REPORTED THAT ALTHOUGH THERE WERE SOME CHAFED WIRES INSIDE THE BATTERY PACK, T HEY WERE NOT THE SOURCE OF ANY SMOKE. 2 L 7 2 4F RT A22CE 2001032000095 20010320 00095 NM 2001 3 20 CA001019025 1 20000912 G 4920 49600011 APU BOEING 767 767233 NM PWA JT9 JT9D7R4D 52054 NE APU BAY FAILED W D RETURN TO BLOCK T J ENGINE CASE PENETRATION WARNING INDICATION TX TAXI/GRND HDL 1 CA (CAN) DURING PUSH BACK AND ENGINE START OF RIGHT HAND ENGINE, AUXILIARY POWER UNIT FAULT LIGHT AND SHUTDOWN. AUXILIARY P OWER UNIT HAD INTERNAL SEIZURE, CAUSING TURBINE TO BE DISCHARGED. METAL PIECE WAS EJECTED OUT OF EXHAUST PORT. AUXILIARY POWER UNIT CHANGED AND OPERATION CHECK CARRIED OUT. FURTHER INFORMATION WILL FOLLOW AFTER INVESTIGATION. 2 L 7 2 4F 4 F RT A1NM E3NE 2001032000096 20010320 00096 NM 2001 3 20 CA001019026 1 20000917 G 2520 86526002 SEAT BACK BOEING 767 767233 NM PWA JT9 JT9D7R4D 52054 NE ROW 22 COLLAPSED W A UNSCHED LANDING O OTHER CL CLIMB 1 CA (CAN) AFTER TAKEOFF, PASSENGER SEATS 22H & 22K BACKREST METAL FRAME COLLAPSED. BACKREST FELL ON THE PASSENGERS SEATED IN 23 H/K. NO REPORTED INJURY. SEAT ASSEMBLY REPLACED. 2 L 7 2 4F 4 F RT A1NM E3NE 2001011105419 20010111 05419 WP 2001 1 11 CA001019027 1 20000826 G 5610 9615059002 CONTROLLER DOUG DC932 DOUG DC9 DC932 3022066 WP PWA JT8 JT8D7 52053 NE APU FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 47198 (CAN) THE CAPTAIN RECEIVED A SUBSTANTIAL ELECTRICAL SHOCK WHILE AIRCRAFT WAS PARKED, FROM AROUND THE EDGE OF THE SLIDING WINDOW.WITH THE AIRCRAFT ON EXTERNAL POWER. THE CAPTAIN WAS SEATING IN THE FLIGHT DECK, IS HAND TOUCHED THE EXTERIOR SK IN OF THE AIRCRAFT THROUGH THE OPEN WINDOW. THE WINDOW WAS REPLACED. SECOND OCCURRENCE. WITH AIRCRAFT ON AUXILIARY POWE R UNIT, AND GROUND POWER DISCONNECTED NO SHOCK FELT.CLEANED EXTERNAL POWER RECEPTACLE, CHECKED FOR GROUND BETWEEN PIN "N " TO GROUND, CHECKED FOR GROUND BETWEEN SLIDING WINDOW FRAME TO GROUND. "0" VOLT. AIRCRAFT CONSIDERED SERVICEABLE. 2 L 7 2 4F 4 F A6WE E2EA 2001032000097 20010320 00097 WP 2001 3 20 CA001019029 1 20000903 G 3246 MS2000634 BOLT DOUG DC9 DC932 3022066 WP PWA JT8 JT8D7 52053 NE LT NLG WHEEL MISSING W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING WALK AROUND INSPECTION OF AIRCRAFT, LEFT HAND NOSE LANDING GEAR WHEEL ASSEMBLY, FOUND WITH ONE TIE BOLT MIS SING. (TIE BOLT ATTACHES HUB HALVES TOGETHER) SUSPECT TIE BOLT CRACKED AND SEPARATED FROM WHEEL HUB. TIRE ASSEMBLY REPLA CED AS PER MAINTENANCE MANUAL REF. 32-40-02. 2 L 7 2 4F 4 F A6WE E2EA 2001033000029 20010330 00029 SW 2001 3 30 CA001020004 1 20000928 G 2910 222040125001 SUPPORT BRACKET BELL 222 222 1182122 SW LYC LTS101 LTS101650C3 41560 NE HYD ACTUATOR DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 3541 (CAN) FOUND UNSATISFACTORY HYDRAULIC ACTUATOR SUPPORT REMOVED FOR DIMENSIONAL VERIFICATION, RESULTS SATISFACTORY; TRAN SMISSION UPPER & LOWER CASE ASSY INSP RESULTS SATISFACTORY; HYDRAULIC ACTUATOR SUPPORT REINST ON A/C WITH NEW HARDWAR E. 1 G 7 2 3U 3 U H9SW E5NE 2001033000030 20010330 00030 2001 3 30 CA001020005 4 20000817 G 3100 B19030FA MODULE UROCOP EC120 EC120B 8680987 EU TMECA ARRIUS ARRIU2F NE VEMD TOP SCREEN FAILED W H DEACTIVATE SYST/CIRCUITS H ELECT. POWER LOSS-50 PC TX TAXI/GRND HDL 1 CA 165 (CAN) VEMD. MODULE 1 WAS DISAPPEARING MOMENTARILY. 1 G 7 2 3U 3 U NC R0001RD E34NE 2001033000031 20010330 00031 NE 2001 3 30 CA001020008 2 20000907 G 7250 UL20025 SHAFT BOEING 757 757* NM RROYCE RB211 RB211535E4 54555 NE HP TURBINE CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 41808 (CAN) DURING A SCHEDULED ENGINE VISIT AT RRC, THE HP TURBINE STUB SHAFT WAS FOUND TO BE EXCESSIVELY CORRODED AROUND BOLT HOLES. RRC LAB REPORT CONFIRMED CORROSION AND THE STUB SHAFT WAS SCAPPED AND A NEW REPLACEMENT FITTED. 2 L 7 2 4F 4 F RT A2NM E12EU 2001033000032 20010330 00032 NE 2001 3 30 CA001020009 2 20000914 G 7230 UL16758 DRUM RROYCE RB211 RB211535E4 54555 NE COMPRESSOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 38465 7458 DN36651 (CAN) INTERMEDIATE PRESSURE COMPRESSOR ROTOR DRUM P/N UL16758 S/N 36651 EX ESN 30534 & MODULE 02 DM3560 WAS SNAGGED AT I NIT INSP DURING OVERHAUL OF THIS MODULE AT RRC DUE TO CRACKING FOUND IN D OVE TAIL OF BLADE SLOTS OF STAGE 6 & STAGE 3. CRACKS CAN BE DETECTED BY VISUAL INSP ALONE. STAGE 6 DOVE TAIL SLOTS FEATURE CRACKS IN PRESSURE FACE TO RUNOUT RADIUS OF DOVE TAIL SLOTS. WORST AFFECTED DOVE TAIL AT NR 7 POS WHICH FEATURES AN OPEN CRACK APROX 0.410 LONG & EXTENDS ONTO FWD FACE. ROTOR WILL BE SENT BACK TO ROLLS ROYCE, DERBY, UK FOR INVESTIGATIO N. NO RPTS FROM OPERATOR OF ANY ABNORMAL MODE O F OP.2000-11-06TC: FOLOW-UP DETAILS REQD 4 F E12EU 2001033000033 20010330 00033 CE 2001 3 30 CA001020010 1 20000906 G 3246 C1630030201 WHEEL CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA MCAULY 1C160 1C160DTM GL MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) FISSURE SUR LE REBOURD DE JANTE A PROXIMITE DES LEVRE POUR TENIR LES ENJOLIEURS DE ROUE. (WHEEL CRACKED) 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2001032000101 20010320 00101 NE 2001 3 20 CA001020011 2 20000809 G 7260 AS20625 NUT RROYCE RB211 RB211535E4 54555 NE FUEL PUMP GEAR LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) THIS ENGINE BELONGING TO CANADA 3000 WAS ROUTINELY INSPECTED AT TSN 34,557.3 & TSR 10.164.5 HOURS. FOUND 1 OFF NUT (AS20625) IN THE MCD CAVITY. THE ENGINE WAS REMOVED AND SENT TO RRC. UPON INVESTIGATION AT RRC IT WAS FOUND THAT THE NU T HAVE COME LOOSE FROM ONE OF THE STUDS ATTACHING THE HP FUEL PUMP IDLER GEAR OUTER RACE TO THE FRONT HOUSING OF THE GEA R. NO DAMAGE WAS FOUND ON THE GEARBOX. THE MODULE WAS OVERHAULED TO A LEVEL 4 WORK SCOPE AND RETURNED TO SERVICE. 4 F E12EU 2000103100108 20001031 00108 EA 2000 10 31 CA001020012 2 20000830 G 7414 SWITCH SLICK 6250 PIPER PA24 PA24250 7102404 SO LYC O540 O540A1D5 41532 EA RT MAGNETO BROKEN W O OTHER O OTHER IN INSP/MAINT 1 CA 3801 90120008 (CAN) PILOT PHONE A.M.E., SAYS HE HAS NO MAG DROP ON ONE MAG. ASKED IF HE DID A LIVE/DEAD MAGS CHECK AT LAST SHUTDOWN, HE SAID HE FORGOT EVEN AFTER HE WAS REMINDED TO DO SO ON PREVIOUS OCCASION. BROKEN WIRE AT TERMINAL ON MAGNETO RIGHT. REPLACED TERMINAL. (X) 1 L 7 1 3O 3 O 1A15 E295 2000103100109 20001031 00109 EA 2000 10 31 CA001020014 2 20000914 G 7300 LW10682 CONTROLLER LYC TIO540A2B PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2B 41532 EA LEFT LEAKING W O OTHER K FLUID LOSS IN INSP/MAINT 1 CA 1215 L161761 (CAN) OIL LEAK DETACHED DURING HOSE REPLACEMENT. UNSCHEDULED REMOVAL. INSTALLED OVERHAULED UNIT. (X) 1 L 7 2 3O 3 O A20SO E14EA 2000103100110 20001031 00110 SO 2000 10 31 CA001020015 1 20000921 G 3244 0613160 TIRE PARKERHANFIN 401402800 PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2B 41532 EA TIRE CUT W O OTHER O OTHER TX TAXI/GRND HDL 1 CA 1059 (CAN) DETECTED FIRST CUT AT REMOVAL OF TOW-BAR. DETECTED TWO MORE CUTS .50 INCH SPACED APPROX 10 INCHES FROM EACH OTHE R, WHEN INSPECTING TIRE AFTER REMOVAL. IT WAS REPORTED THAT AIRCRAFT WAS LANDED ONCE WITH PILOT APPLYING BRAKES BEFORE NOSE GEAR TOUCHED GROUND. INSPECTED, NO SIGNS OF HARD LANDING. HOWEVER, DAMAGE MAY HAVE BEEN DONE WHEN APPROACHING AIR CRAFT WITH TOW-BAR OR AT HANGAR ENTRANCE, DOOR SILL HAVING HUMPER-GUIDES. NOTE: HANGAR DOORS BEING MODIFIED AND TRAIN ING GIVEN TO PERSONNEL ON HOOKING TOW BAR. (X) 1 L 7 2 3O 3 O A20SO E14EA 2000103100111 20001031 00111 SO 2000 10 31 CA001020016 1 20000927 G 2822 481802 PUMP PIPER DWG54300 PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA RT WING ROOT FAILED W O OTHER O OTHER CR CRUISE 1 CA 3332 317405479 (CAN) THIS PUMP TURNS ON FROM ENGINE START UNTIL SHUT DOWN. AT THE END OF GING TO LEG, PILOT NOTICED FUEL PRESSURE HIT TING VARY MIN (25 PSI)A T IDLE 750 RPM, UNBURN RUNNING OK AT 1000 RPM. (CARGO FLIGHT ON RETURN LAG, TAKEOFF AND CLIMB OK. DURING CRUISE, RIGHT FUEL BOOST PUMP INOP LIGHT CAME ON FOR THE REST OF THE FLIGHT. PILOT PULLED CIRCUIT BREAKER OFF. AFTER LANDING, PUMP CHECKED AS DEAD, INOP, WITH EFFORT TO START WHEN TAPPED ON. REPLACED PUMP. NOTE: CHECKED AL L AIRCRAFT ASM, SBS, SLS/INSP PROG, NO TBO PRESCRIBED. (X) 1 L 7 2 3O 3 O A20SO E14EA 2000103100112 20001031 00112 EA 2000 10 31 CA001020017 2 20000928 G 7314 RG9080J4A PUMP PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA RT ENGINE FAILED W O OTHER O OTHER IN INSP/MAINT 1 CA 565 C9728 (CAN) RECURRING PROBLEM. AIRCRAFT HAS FLOWN 48.7 HOURS SINCE LAST OCCURRENCE AND REPAIRS. THIS TIME FOLLOWS REPLACEMEN T OF IN-LINE ELECTRIC FUEL BOOST PUMP 481-802, AFTER FAILURE. FUEL SERVO SCREEN CHECKED, NOZZLES REMOVED, FLUSHED LINES SERVO TO NOZZLES. INSTALLED NEW NOZZLE BODIES 2541946. REPLACED FUEL PUMP TOO. TEST FLIGHT. (X) 1 L 7 2 3O 3 O A20SO E14EA 2001032000102 20010320 00102 EU 2001 3 20 CA001020019 1 20000913 G 3411 PITOT TUBE BRAERO DH125 BAE125800A 1500285 EU PITOT/STATIC SYS CLOGGED W A UNSCHED LANDING J WARNING INDICATION TO TAKEOFF 1 CA (CAN) PILOTS REPORTED LOSS OF ALL PITOT-STATIC INSTRUMENTATION ON TAKEOFF - ALL ADC SUPPLIED INSTRUMENTATION FLAGGED & N O INFO FROM STANDBY EQUIP. A/C RETURNED TO AIRPORT. IDENT INHIBIT LIGHT WAS ON - UPON LDG. ALL INSTRUMENTATION RETURNE D TO NORMAL. - SUSPECT NR 2 PITOT WAS PLUGGED, WEATHER WAS CLEAR, UFR - BASED ON FAILURE NR 2 PITOT SYS DISASSEMBLED AND BLOWN CLEAR - REASSEMBLED & TESTED PE R ST0571 APPENDIX B STALL 3 SYS RESET & BOTH ADC TESTED, SWITCHING FROM 1-2 TESTE D SERVICEABLE, BOTH BACKUP BATTERY PACKS SERVICED & REINSTALLED - UNABLE TO DUPLICATE SNAG. A/C RELEASED ON CONDITION OF SATISFACTORY TEST FLT.- TEST FLT PERFORMED SERVICEABLE ALL EQUIP OP NORMALLY. A/C RT-SRV. 2 L 7 2 4F RT A3EU 2001032600417 20010326 00417 SO 2001 3 26 CA001020020 2 20000929 G 7414 36066 DRIVE GEAR DIAMON DA20 DA20C1 2990001 GL CONT O240 IO240B 17063 SO MAGNETO BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 855 (CAN) L/H MAGNETO (SLICK 4310 S/N 99042051) HAS BEEN REMOVED FOR 500 HR INSPECTION. FOUND ONE (1) TOOTH ON THE DRIVE GEA R WAS MISSING. REPLACED DRIVE GEAR (P/N 36066). REMOVED ENGINE OIL SUMP AND FOUND THE MISSING GEAR TOOTH. 1 L 7 1 3O 3 O NT TA4CH E7SO 2001031300040 20010313 00040 WP 2001 3 13 CA001020021 1 20000920 G 7810 90632323 TAILPIPE CVAC 440 440 2422902 WP ALLSN 501D 501D13D 03004 GL RT ENGINE BROKEN W E ENGINE SHUTDOWN J WARNING INDICATION CR CRUISE 1 CA (CAN) THE FLIGHT CREW OBSERVED A RT ENGINE ZONE 1 FIRE WARNING, THE ENGINE WAS SHUTDOWN AND THE FIRE WARNING WENT OUT PR IOR TO FIRING THE FIRE EXTINGUISHER. RECTIFICATION: THE RT ENGINE TAIL PIPE, UNIVERSAL JOINT P/N 906323-23 REPLACED, SYS TEM TESTED ON GROUND AIRCRAFT RELEASED FOR FLIGHT. 2 L 7 2 4R 4 T 6A6 E282 2001031300041 20010313 00041 EA 2001 3 13 CA001020022 1 20000923 G 3250 CONTROL UNIT DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA NLG STEERING MALFUNCTIONED W O OTHER O OTHER CR CRUISE 1 CA (CAN) PIC REPORTED TO YVP FSS (22:40 H LCL) THAT THE NOSE WHEEL STEERING TILLER WAS STUCK IN RT POSITION. THE AIRCRAFT L ANDED WITHOUT INCIDENT.NOSE WHEEL STEERING SYSTEM INSPECTED WITH AIRCRAFT ON JACKS; CABLE TENSION VERIFIED, HYDRAULIC SY STEM CHECKED, ACTUATOR TORQUE LINKS ETAL - TAXI CHECKED 90 - NO FAULT FOUND. LACK OF HYDRAULIC PRESSURE DUE TO CB NOT CL OSED CONSIDERED PROBABLE.NO SUBSEQUENT PROBLEM REPORTED BY FLIGHT CREWS. 1 H 7 2 3T 4 T RT A9EA E4EA 2001031300042 20010313 00042 NE 2001 3 13 CA001024002 2 20000822 G 7200 ENGINE CNDAIR CL601 CL6013A 8070802 EA GE CF34 CF343A 30015 NE RIGHT NOISY W E ENGINE SHUTDOWN E Y VIBRATION/BUFFET ENGINE STOPPAGE DE DESCENT 1 CA 4650 4650 (CAN) CREW REPORTED ZERO OIL PRESSURE ON RT ENGINE DURING FLIGHT FROM ARAPAHO, COLORADO TO WASHINGTON, DC, AS THEY PASSE D OVER ST. LOUIS AT FL370 WITH ALL OTHER PARAMETERS NORMAL (INCLUDING OIL TEMP). CORP WINGS MAINTENANCE CONTACTED VIA FL IGHT PHONE AND PILOTS DIRECTED TO DROP TO FL330 AND SEE IF ANY CHANGE. NONE REPORTED, SO PILOT CONTINUED FLIGHT. ON DESC ENT IN PREPARATION FOR APPROACH TO FL250, CREW HEARD 2 DISTINCT POPPING SOUNDS FROM THE RT ENGINE AND ELECTED TO SHUT TH E ENGINE DOWN WHILE OVER VIRGINIA. AIRCRAFT DIVERTED TO DULLAS IN THE NORMAL LANDING PATTERN, PERFORMED UNEVENTFUL SINGL E ENGINE LANDING AND TAXIED TO THEIR FBO. 2000-10-31TC: FOLLOW-UP REPORT EXPECTED FROM ORIGINATOR. 2 L 7 2 4F 4 F RT A21EA E15NE 2001031300043 20010313 00043 EA 2001 3 13 CA001024003 1 20001012 G 2434 2CM70D6A GENERATOR CNDAIR CL215 CL2151A10 EA GEN BAY FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 1770 109 (CAN) NORMAL TIME BETWEEN OVERHAULS FOR THIS UNIT IS 1300 HOURS; THIS GEN ONLY HAD 109 TSO. THE FOLLOWING PROBLEMS WERE FOUND: BRUSHES WERE WORN, FOUR SCREWS WHICH RETAIN A PLATE ON THE GEN WERE COMPLETELY WORN OUT EVEN IF THEY HAD ALWAYS BEEN HELD TOGETHER WITH LOCK WIRE. GEN CHANGED AND DEFECTIVE PIECE SENT FOR OVERHAUL. 2 H 7 2 4R A14EA 2001031300044 20010313 00044 2001 3 13 CA001024004 4 20000923 G 3418 WARNING SYSTEM CNDAIR CL600 CL6002B19 EA COCKPIT ACTIVATED W C ABORTED TAKEOFF N FALSE WARNING TO TAKEOFF 1 CA (CAN) THE CREW ABORTED TAKEOFF DUE TO A STALL FAIL CAUTION MESSAGE. AFTER REDUCING THE SPEED WHEN ABORTING THE TAKEOFF, THE STALL FAIL MESSAGE CLEARED ITSELF. BREAKERS RESETTED AND AIRCRAFT RETURNED TO SERVICE (EICAS 2000 INCORPORATED ON TH IS A/C). 2 L 7 2 4F RT A21EA 2001031300045 20010313 00045 2001 3 13 CA001024005 4 20000923 G 3418 COMPUTER CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE STALL WARNING MALFUNCTIONED W C ABORTED TAKEOFF N FALSE WARNING TO TAKEOFF 1 CA (CAN) A STALL FAIL CAUTION MESSAGE APPEARED ON TAKEOFF ROLL AT 70 KTS, FOLLOWED BY A CONFIG SPLRS WARNING MESSAGE (THE T AKEOFF WAS NOT ABORTED).THE STALL COMPUTER WAS RESET (EICAS 2000 INCORPORATED ON THIS A/C). 2 L 7 2 4F 4 F RT A21EA E15NE 2001031300046 20010313 00046 2001 3 13 CA001024006 4 20000923 G 3418 COMPUTER CNDAIR CL600 CL6002B19 EA STALL WARNING MALFUNCTIONED W C ABORTED TAKEOFF N FALSE WARNING TO TAKEOFF 1 CA (CAN) THE STALL FAIL CAUTION MESSAGE APPEARED ON TAKEOFF ROLL AT 70 KTS.THE STALL COMPUTER WAS RESET (EICAS 2000 INCORPO RATED ON THIS A/C). 2 L 7 2 4F RT A21EA 2001031300047 20010313 00047 2001 3 13 CA001024007 4 20000923 G 3418 COMPUTER CNDAIR CL600 CL6002B19 EA STALL WARNING MALFUNCTIONED W D RETURN TO BLOCK N FALSE WARNING TX TAXI/GRND HDL 1 CA (CAN) THE FLIGHT CREW REPORTED A STALL FAIL CAUTION MESSAGE BEFORE TAXI OUT.THE STALL COMPUTER WAS RESET (EICAS 2000 INC ORPORATED ON THIS A/C). 2 L 7 2 4F RT A21EA 2001031300048 20010313 00048 EA 2001 3 13 CA001024008 1 20000923 G 2761 4916405 CONTROL UNIT CNDAIR CL600 CL6002B19 EA SPOILERS FAILED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 1032 (CAN) AFTER TAKEOFF A FLIGHT SPOILERS FAULT STATUS MESSAGE APPEARED ON ED2. THE MAINTENANCE REPLACED THE SECU NR 2 AND T HE LEFT FLIGHT SPOILER OUTBOARD PCU (P/N: 27000-3, S/N: MAL.3438). 2 L 7 2 4F RT A21EA 2001031300049 20010313 00049 EA 2001 3 13 CA001024009 1 20000923 G 2752 853D10018 ACTUATOR CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE TE FLAPS FAILED W O OTHER F FLT CONT AFFECTED AP APPROACH 1 CA (CAN) CREW REPORTED FLAP FAIL MESSAGE AND FLAPS MOVEMENT STOPPED AFTER SELECTION FROM 0 TO 8 DEGREES DURING APPROACH. (N OTE: SB 601R-27-111 WAS CARRIED OUT 3 WEEKS AGO.) THE MAINTENANCE FOUND THE FLEXSHAFT BETWEEN NR 3 & NR 4 ACTUATORS TWIS TED/KINKED. CABLES REPLACED AND AIRCRAFT FERRIED TO SLC TO REPLACE THE ACTUATOR AS PER FAA AD 98-20-01. 2 L 7 2 4F 4 F RT A21EA E15NE 2001031300050 20010313 00050 2001 3 13 CA001024010 4 20000927 G 3418 COMPUTER CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE STALL WARNING MALFUNCTIONED W O OTHER J WARNING INDICATION CR CRUISE 1 CA (CAN) STALL FAIL MESSAGE POSTED ON THE EICAS IN FLIGHT AT 250 KTS.STALL COMPUTER RESET. AIRCRAFT RETURNED TO SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001031300051 20010313 00051 2001 3 13 CA001024011 4 20000927 G 3418 COMPUTER CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE STALL WARNING MALFUNCTIONED W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA (CAN) STALL FAIL CAUTION MESSAGE POSTED UPON TAKEOFF, ASSOCIATED WITH CONFIG SPOILERS WARNING.ABORTED TAKEOFF AT 80 KTS. RESET STALL COMPUTER. SYSTEM OPS CHECKED GOOD.AIRCRAFT BACK IN SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001031300052 20010313 00052 2001 3 13 CA001024012 4 20000927 G 3418 COMPUTER CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE STALL WARNING MALFUNCTIONED W C ABORTED TAKEOFF N FALSE WARNING TO TAKEOFF 1 CA (CAN) STALL FAIL CAUTION MESSAGE POSTED UPON TAKEOFF, ASSOCIATED WITH CONFIG SPOILERS WARNING.ABORTED TAKEOFF AT 80 KTS. RESET STALL COMPUTER. AIRCRAFT BACK IN SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001032600418 20010326 00418 NE 2001 3 26 CA001024013 2 20000929 G 7200 CARBON SEAL CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE LT ENGINE FAILED W E ENGINE SHUTDOWN K J FLUID LOSS WARNING INDICATION CL CLIMB 1 CA (CAN) DURING CLIMB FLIGHT CREW NOTICED LEFT ENGINE OIL PRESSURE FLUCTUATION. AIRCRAFT RETURNED TO DEPARTING AIRPORT. LT ENGINE CARBON SEAL REPLACED. AIRCRAFT BACK IN SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001031300053 20010313 00053 EA 2001 3 13 CA001024014 1 20000929 G 3260 VALVE CNDAIR CL600 CL6002B19 EA NLG FAILED W O OTHER J WARNING INDICATION AP APPROACH 1 CA (CAN) PILOT REPORTED A GEAR DISAGREE WARNING MESSAGE UPON SELECTION, AND THE NOSE LANDING GEAR DID NOT EXTEND.MAINTENANC E REPLACED THE MAIN AND NOSE LANDING GEAR PRIORITY VALVES. 2 L 7 2 4F RT A21EA 2001031300054 20010313 00054 EA 2001 3 13 CA001024015 1 20000930 G 5210 HANDLE CNDAIR CL600 CL6002B19 EA PAX DOOR LACK OF LUBE W O OTHER J WARNING INDICATION CR CRUISE 1 CA (CAN) DURING FLIGHT, PAX DOOR OUTER HANDLE MESSAGE POSTED ON EICAS, FOLLOWED QRH - RESTOWED SUCCESSFULLY. OUTER HANDLE C ONFIRMED STIFF DURING STOWING AND EJECTION. ADJUSTED OUTER HANDLE SUPPORT BOX, AIRCRAFT BACK IN SERVICE. 2 L 7 2 4F RT A21EA 2001031300055 20010313 00055 EA 2001 3 13 CA001024016 1 20000930 G 2750 855D1009 BPSU CNDAIR CL600 CL6002B19 EA RT WING TE FLAPS DEFECTIVE W O OTHER F FLT CONT AFFECTED CL CLIMB 1 CA 916 (CAN) UPON FLAP SELECTION FROM 20 TO 0 DEGREES, FLAP FAIL MESSAGE ON EICAS. RT BPSU REPLACED, AIRCRAFT BACK IN SERVICE. 2 L 7 2 4F RT A21EA 2001031300056 20010313 00056 EA 2001 3 13 CA001024017 1 20000930 G 2750 CONTROL UNIT CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE TE FLAPS FAILED W F ACTIVATE FIRE EXT. J WARNING INDICATION CR CRUISE 1 CA (CAN) FLAP FAIL MESSAGE APPEARED ON FLIGHT (CRUISE) WHEN FLAPS AT 0 DEGREES.RESET THE FLAP SYSTEM, AIRCRAFT BACK IN SERV ICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001031300057 20010313 00057 EA 2001 3 13 CA001024018 1 20000930 G 2742 ACTUATOR CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE HORIZONTAL STAB FAILED W O OTHER F FLT CONT AFFECTED CR CRUISE 1 CA (CAN) WHEN OPERATING THE PILOT/CO-PILOT STAB TRIM SWITCHES, THE STAB TRIM CHANNEL NR 1 INOP MESSAGE APPEARS.REPLACED THE HSTA AND MCU. SERIAL NUMBERS NOT AVAILABLE AT THIS TIME. AIRCRAFT RETURNED TO SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001031300058 20010313 00058 EA 2001 3 13 CA001024019 1 20001001 G 3242 BRAKE ASSY CNDAIR CL600 CL6002B19 EA RT MLG FAILED W O OTHER B SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 CA (CAN) AIRCRAFT WAS TAXIING TO POSITION WITH 34 PEOPLE ON BOARD, CREW REPORTED THAT THEY FELT THE RIGHT SIDE BRAKES DRAGG ING AND THEY ALSO REPORTED THAT ANOTHER AIRCRAFT HAD SEEN SMOKE COMING FROM RIGHT WHEELS. AIRCRAFT WAS STRANDED ON ACTIV E TAXI WAY. RIGHT HAND INBOARD TIRE HAD BLOWN AND THE RIGHT HAND INBOARD BRAKE HAD LOCKED UP. THE BRAKE AND WHEEL ASSEMB LY WERE REPLACED OPS CHECKED GOOD. 2 L 7 2 4F RT A21EA 2001031300059 20010313 00059 EA 2001 3 13 CA001024020 1 20001001 G 3230 4622 PRIORITY VALVE CNDAIR CL600 CL6002B19 EA NLG FAILED W O OTHER J WARNING INDICATION AP APPROACH 1 CA (CAN) NOSE GEAR INDICATOR SLOW TO SEQUENCE WHEN GEAR PLACED TO DOWN POSITION. GEAR DISAGREE & NOSE DOOR OPEN WARNING MES SAGES.MAINTENANCE REPLACED THE NOSE LANDING GEAR PRIORITY VALVE (P/N: 4622) AND ELECTICAL HYDRAULIC PUMP REPLACED (P/N: 848847). 2 L 7 2 4F RT A21EA 2001031300060 20010313 00060 2001 3 13 CA001024021 4 20001003 G 3418 COMPUTER CNDAIR CL600 CL6002B19 EA STALL WARNING MALFUNCTIONED W C ABORTED TAKEOFF N FALSE WARNING TO TAKEOFF 1 CA (CAN) THE FLIGHT CREW REPORTED THE STALL FAIL CAUTION MESSAGE AT THE BEGINNING OF THE TAKEOFF AT 80 KTS, TAKEOFF WAS ABO RTED. THIS IS AN AIRCRAFT WITH EICAS 2000 INCORPORATED. MAINTENANCE RESET THE STALL COMPUTER, AIRCRAFT RETURNED TO SERVI CE. 2 L 7 2 4F RT A21EA 2001031300061 20010313 00061 2001 3 13 CA001024022 4 20001003 G 3418 COMPUTER CNDAIR CL600 CL6002B19 EA STALL WARNING MALFUNCTIONED W C ABORTED TAKEOFF N FALSE WARNING TO TAKEOFF 1 CA (CAN) THE CREW REPORTED THE STALL FAIL CAUTION MESSAGE AT THE BEGINNING OF THE TAKEOFF AT 95 KTS, TAKEOFF WAS ABORTED.TH IS IS AN AIRCRAFT WITH EICAS 2000 INCORPORATED. MAINTENANCE RESET THE STALL COMPUTER, AIRCRAFT RETURNED TO SERVICE. 2 L 7 2 4F RT A21EA 2001031300062 20010313 00062 2001 3 13 CA001024023 4 20001003 G 3418 COMPUTER CNDAIR CL600 CL6002B19 EA STALL WARNING MALFUNCTIONED W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 CA (CAN) THE CREW REPORTED THE STALL FAIL CAUTION MESSAGE ON CLIMB OUT.THE EICAS 2000 STATUS ON THIS AIRCRAFT IS UNKNOWN.MA INTENANCE RESET THE STALL COMPUTER, AIRCRAFT RETURNED TO SERVICE. 2 L 7 2 4F RT A21EA 2001031300063 20010313 00063 2001 3 13 CA001024024 4 20001003 G 3418 COMPUTER CNDAIR CL600 CL6002B19 EA STALL WARNING FAILED W C ABORTED TAKEOFF N FALSE WARNING TO TAKEOFF 1 CA (CAN) THE CREW REPORTED THE STALL FAIL CAUTION MESSAGE AT THE BEGINNING OF THE TAKEOFF, TAKEOFF WAS ABORTED.THE EICAS 20 00 STATUS ON THIS AIRCRAFT IS UNKNOWN. MAINTENANCE RESET THE STALL COMPUTER, AIRCRAFT RETURNED TO SERVICE. 2 L 7 2 4F RT A21EA 2001031300064 20010313 00064 EA 2001 3 13 CA001024025 1 20001007 G 5610 NP1393215 WINDSHIELD CNDAIR CL600 CL6002B19 EA COCKPIT CRACKED W O OTHER O OTHER LD LANDING 1 CA (CAN) DURING LANDING, PILOTS WINDSHIELD CRACKED. LANDING UNEVENTFUL.AWAITING FOR PARTS TO REPLACE. 2 L 7 2 4F RT A21EA 2001031300065 20010313 00065 NE 2001 3 13 CA001024026 2 20001006 G 7250 ENGINE CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE NR 1 FAILED W E B A ENGINE SHUTDOWN EMER. DESCENT UNSCHED LANDING B Y SMOKE/FUMES/ODORS/SPARKS ENGINE STOPPAGE CL CLIMB 1 CA (CAN) DURING CLIMB, NR 1 ENGINE EXPERIENCED AN UN-COMMANDED SHUT DOWN. FLIGHT CREW DECLARED AN EMERGENCY LANDING (UNEVEN TFUL). THE AIRPORT FIRE DEPARTMENT FOAMED THE ENGINE AFTER LANDING BECAUSE OF VISIBLE SMOKE COMING OUT OF THE JET PIPE. THE ENGINE LPT HAD DAMAGE VISIBLE FROM THE EXHAUST. THE ENGINE WAS REPLACED.AIRCRAFT BACK IN SERVICE. 2000-10-31TC: FOLL OW-UP REPORT EXPECTED FROM ORIGINATOR. 2 L 7 2 4F 4 F RT A21EA E15NE 2001031300066 20010313 00066 NE 2001 3 13 CA001024027 2 20001006 G 7532 32895902 BLEED VALVE CNDAIR CL600 CL6002B19 EA GE CF34 CF341A NE LT ENGINE FAILED W O OTHER J WARNING INDICATION CR CRUISE 1 CA (CAN) CREW REPORTED A WING ANTI-ICE DUCT WARNING MESSAGE IN CRUISE. UNABLE TO DUPLICATE THE PROBLEM ON GROUND, HOWEVER, UPON CHECKING THE SYSTEM, MAINTENANCE NOTICED THE 14TH STAGE SOV LT WOULD ALWAYS REMAIN OPEN, REGARDLESS OF THE SELECTIO N IN THE COCKPIT. REPLACED THE LT 14TH STAGE SOV.AIRCRAFT BACK IN SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001031300067 20010313 00067 EA 2001 3 13 CA001024028 1 20001006 G 2740 70608 CONTROL UNIT CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE HORIZONTAL STAB FAILED W O OTHER J WARNING INDICATION CR CRUISE 1 CA (CAN) CREW REPORTED SEVERAL STAB AND MACH TRIM CAUTION MESSAGES INTERMITTENT IN CLIMB AND CRUISE. REPLACED THE HSTCU, AI RCRAFT BACK IN SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001032600489 20010326 00489 EA 2001 3 26 CA001024029 1 20001006 G 7830 TORQUE BOX CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE THRUST REVERSER DAMAGED W A UNSCHED LANDING E VIBRATION/BUFFET CR CRUISE 1 CA (CAN) DURING FLIGHT, AN UNUSUAL RUMBLING NOISE AND SOME VIBRATION WAS OBSERVED. ALL ENGINE PARAMETERS WERE NORMAL. CREW ELECTED TO DECLARE AN EMERGENCY LANDING AS A PRECAUTIONARY MEASURE. FOUND THE LT THRUST REVERSERS TORQUE BOX DAMAGED, AL ONG WITH THE UPPER STANG FAIRING.DAMAGED PARTS REPLACED, AIRCRAFT BACK IN SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001031300068 20010313 00068 EA 2001 3 13 CA001024030 1 20001006 G 2740 CONTROL UNIT CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE HORIZONTAL STAB MALFUNCTIONED W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA (CAN) CREW REPORTED A CONFIG STAB WARNING MESSAGE DURING TAKEOFF ROLL AND STAB NOSE UP BY ITSELF. ABORTED TAKEOFF AT 97 KNOTS.NO FAULTS ON HSTCU NOR ON THE MDC. PERFORMED FULL OPERATIONAL CHECK OF STAB. NO FAULTS FOUND. AIRCRAFT RETURNED TO SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001031300069 20010313 00069 NE 2001 3 13 CA001024031 2 20001006 G 7314 99D671 FILTER CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE FUEL PUMP FAILED W O OTHER J WARNING INDICATION DE DESCENT 1 CA (CAN) CREW REPORTED A RT FUEL TO PRESSURE CAUTION MESSAGE IN DESCENT. MESSAGE WENT AWAY WHEN THE THRUST LEVERS WERE PUSH ED FORWARD.MAINTENANCE REPLACEDTHE RT ENGINE FUEL FILTER ELEMENT AND RT ENGINE FUEL LO PRESS SWITCH. AIRCRAFT BACK IN SE RVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001031300070 20010313 00070 EA 2001 3 13 CA001024032 1 20001006 G 2750 860D10018 FCU CNDAIR CL600 CL6002B19 EA TE FLAPS FAILED W O OTHER J WARNING INDICATION CR CRUISE 1 CA (CAN) DURING CRUISE, ON A FERRY FLIGHT, PILOT REPORTED A FLAPS HALFSPEED MESSAGE, QUICKLY FOLLOWED BY A FLAPS FAIL. A 0 DEGREES FLAP LANDING WAS PERFORMED. REPLACED THE FECU. 2 L 7 2 4F RT A21EA 2001031300071 20010313 00071 EA 2001 3 13 CA001024033 1 20001006 G 2750 855D1009 BPSU CNDAIR CL600 CL6002B19 EA RIGHT FAILED W O OTHER J WARNING INDICATION DE DESCENT 1 CA (CAN) FLAPS FAIL UPON SELECTION, CREW REPORTED THAT THE FLAPS DID NOT MOVE. RT BPSU REPLACED, AIRCRAFT BACK IN SERVICE. 2 L 7 2 4F RT A21EA 2001031300072 20010313 00072 EA 2001 3 13 CA001024034 1 20001006 G 2421 IDG CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE LEFT LACK OF LUBE W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA (CAN) UPON TAKEOFF, NR 1 IDG DROPPED OFFLINE, ABORTED TAKEOFF. FOUND LEFT IDG OIL LEVEL LOW. SERVICED IDG PER AMM. AIRCR AFT BACK IN SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001031300073 20010313 00073 EA 2001 3 13 CA001024035 1 20001006 G 2740 CONTROL UNIT CNDAIR CL600 CL6002B19 EA HORIZONTAL STAB FAILED W O OTHER J WARNING INDICATION TX TAXI/GRND HDL 1 CA (CAN) DURING 2 STAB TRIM TESTS, CHANNEL 2 FAILED INDICATED ON HSTCU FROM PANEL. REPLACED HSTCU, SYSTEM OPS CHECKED GOOD ON GROUND.AIRCRAFT BACK IN SERVICE. 2 L 7 2 4F RT A21EA 2001031300074 20010313 00074 EA 2001 3 13 CA001024036 1 20001006 G 5230 HANDLE CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE CARGO DOOR FAILED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) CREW REPORTED A CARGO DOOR CAUTION MESSAGE DURING CLIMB. CREW RETURNED TO FIELD.LUBED CARGO DOOR HANDLE AND OPS CH ECK PER AMM.AIRCRAFT BACK IN SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001031300075 20010313 00075 EA 2001 3 13 CA001024037 1 20001006 G 5270 WARNING SYSTEM CNDAIR CL6002B19 CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE CARGO DOOR ACTIVATED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 7028 (CAN) CREW REPORTED A CARGO DOOR CAUTION MESSAGE AFTER TAKEOFF. CREW RETURNED TO FIELD. OPS CHECKED PER AMM. 2 L 7 2 4F 4 F RT A21EA E15NE 2001031300076 20010313 00076 2001 3 13 CA001024038 4 20001006 G 3417 607300001 TRANSDUCER CNDAIR CL600 CL6002B19 EA ADC FAILED W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 CA (CAN) CREW REPORTED A STALL FAIL CAUTION MESSAGE POSTED AFTER TAKEOFF. RETURNED TO BASE. (AIRCRAFT POST EICAS 2000).REMO VED AND REPLACED NR 1 MACH TRANSDUCER. SYSTEM CHECK GOOD. 2 L 7 2 4F RT A21EA 2001031300077 20010313 00077 2001 3 13 CA001024039 4 20001006 G 3418 COMPUTER CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE STALL WARNING FAILED W C ABORTED TAKEOFF N FALSE WARNING TO TAKEOFF 1 CA (CAN) STALL FAIL CAUTION MESSAGE POSTED FOLLOWED BY CONFIG SPOILERS MESSAGE AT APPROX. 80 KTS.ABORTED TAKEOFF, AND RETUR NED TO BLOCKS.SPC MEMORY RESET PER AMM. AIRCRAFT BACK IN SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001031300078 20010313 00078 EA 2001 3 13 CA001024040 1 20001017 G 2752 ACTUATOR CNDAIR CL600 CL6002B19 EA TE FLAPS FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) FLAPS FAILED AT 38 DEGREES. PERFORMED ACTUATOR TORQUE CHECKS PER AMM, FOOUND NR 1 ACTUATOR RT WITH SLIGHTLY HIGHER TORQUE THAN THE OTHER ONES. REPLACED NR1 ACTUATOR RT. 2 L 7 2 4F RT A21EA 2001031300079 20010313 00079 2001 3 13 CA001024041 4 20001007 G 3418 COMPUTER CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE STALL WARNING FAILED W C ABORTED TAKEOFF N FALSE WARNING TO TAKEOFF 1 CA (CAN) STALL FAIL CAUTION MESSAGE FOLLOWED BY CONFIG SPOILERS AT APPROX 80 KTS.ABORTED TAKEOFF.SPC RESET PER AMM, AIRCRAF T BACK IN SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001031300080 20010313 00080 NE 2001 3 13 CA001024042 2 20001007 G 7200 ENGINE CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE NR 1 OVERHEATED W E A ENGINE SHUTDOWN UNSCHED LANDING K M J FLUID LOSS OVER TEMP WARNING INDICATION CL CLIMB 1 CA (CAN) SHORTLY AFTER TAKEOFF, NR 1 ENGINE OIL TEMPERATURE PARAMETER WENT INTO RED FOLLOWED BY A LOW OIL PRESSURE WARNING. ENGINE SHUT DOWN, EMERGENCY DECLARED AND UNEVENTFULY LANDING. NR 1 ENGINE REPLACED AND AIRCRAFT RETURNED TO SERVICE. 20 00-10-31TC: FOLLOW-UP REPORT EXPECTED FROM ORIGINATOR 2 L 7 2 4F 4 F RT A21EA E15NE 2001031300081 20010313 00081 EA 2001 3 13 CA001024043 1 20001007 G 2742 ACTUATOR CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE HORIZONTAL STAB FAILED W C ABORTED TAKEOFF F J FLT CONT AFFECTED WARNING INDICATION TO TAKEOFF 1 CA (CAN) DURING TAKEOFF, STAB TRIM CAUTION MESSAGE ILLUMINATED. TAKEOFF ABORTED AT 100 KNOTS.RTO INSPECTION, HSTA AND MCU R EPLACEMENT CARRIED OUT ON AIRCRAFT BEFORE RETURNING INTO SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001031300082 20010313 00082 2001 3 13 CA001024044 4 20001007 G 3418 COMPUTER CNDAIR CL600 CL6002B19 EA STALL WARNING FAILED W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 CA (CAN) STALL FAIL CAUTION MESSAGE ILLUMINATED ON CLIMB JUST AFTER TAKEOFF. NO EMERGENCY DECLARED.SPC RESET AS PER AMM, AI RCRAFT BACK IN SERVICE. 2 L 7 2 4F RT A21EA 2001031300083 20010313 00083 2001 3 13 CA001024045 4 20001007 G 3444 ANTENNA CNDAIR CL600 CL6002B19 EA GROUND PROXIMITY FAILED W O OTHER N FALSE WARNING CL CLIMB 1 CA (CAN) IN CLIMB AT ABOUT 4500 FEET; FLIGHT CREW RECEIVED AURAL WARNING TERRAIN, TERRAIN, PULL UP, PULL UP & GPWS WARNING LIGHT.RADAR ALTIMETER ANTENNA AND COAX CABLES REPLACED, AIRCRAFT RETURNED TO SERVICE. 2 L 7 2 4F RT A21EA 2001031300084 20010313 00084 2001 3 13 CA001024046 4 20001007 G 3418 COMPUTER CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE STALL WARNING FAILED W C ABORTED TAKEOFF N FALSE WARNING TO TAKEOFF 1 CA (CAN) DURING TAKEOFF STALL FAIL CAUTION MESSAGE ILLUMINATED. TAKEOFF ABORTED.STALL PROTECTION COMPUTER RESET AS PER AMM, AIRCRAFT RETURNED TO SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001031300085 20010313 00085 2001 3 13 CA001024047 4 20001007 G 3418 COMPUTER CNDAIR CL600 CL6002B19 EA STALL WARNING FAILED W C ABORTED TAKEOFF N FALSE WARNING TO TAKEOFF 1 CA (CAN) DURING TAKEOFF, AT 80 KNOTS, STALL FAIL CAUTION MESSAGE ILLUMINATED.TAKEOFF ABORTED.STALL PROTECTION COMPUTER RESE T AS PER AMM, AIRCRAFT RETURNED TO SERVICE. 2 L 7 2 4F RT A21EA 2001031300086 20010313 00086 2001 3 13 CA001024048 4 20001007 G 3418 COMPUTER CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE STALL WARNING FAILED W O OTHER N FALSE WARNING CL CLIMB 1 CA (CAN) DURING CLIMB OUT, AT 160 KNOTS AND 1500 FEET, STALL FAIL CAUTION MESSAGE ILLUMINATED. STALL PROTECTION COMPUTER RE SET AS PER AMM, AIRCRAFT RETURNED TO SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001031300087 20010313 00087 EA 2001 3 13 CA001024049 1 20001007 G 3230 75000600 VALVE CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE NLG FAILED W O OTHER J WARNING INDICATION AP APPROACH 1 CA (CAN) ON APPROACH UNABLE TO EXTEND NOSE LANDING GEAR. MANUAL EXTENSION USED. NOSE WHEEL STEERING FAILED ON LANDING. NLG EXTEND AND STEERING VALVE REPLACED AS PER AMM. AIRCRAFT RETURNED TO SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001032600253 20010326 00253 EA 2001 3 26 CA001026012 1 20001004 G 3320 KCD4N RELAY DHAV DHC8 DHC8311 1386006 EA PWA PW120 PW123 NE CABIN LIGHTS FAILED W K NONE L NO TEST IN INSP/MAINT 1 CA (CAN) DURING MAINTENANCE IT WAS DISCOVERED THAT THE LT SIDEWALL LIGHTING WOULD NOT SHUT OFF WHEN SELECTED. THE LIGHTING RELAY 3325-K2 WAS REPLACED AND THE LIGHTING FUNCTION CHECKED SERVICEABLE. THE RELAY IS SUSPECTED TO BE ORIGINAL EQUIPMEN T. TTAF 22,015 HRS, 32,623 CYCLES. 2 H 7 2 4T 4 T RT A13NM E20NE 2000112100213 20001121 00213 CE 2000 11 21 CA001026014 1 20000930 G 2913 10138800519 MOTOR BEECH 300 300BEECH 1152930 CE ELECTRIC MOTOR SHORTED W O OTHER O OTHER CR CRUISE 1 CA 1957 221 (CAN) MOTOR WOULD RUN AS DESIGNED BUT BECAUSE OF ONE BAD COMUTATOR SEGMENT WOULD NOT TURN WHEN SELECTED IF BRUSH WAS ON BAD SEGMENT. DURING FLT AS HYD PRESS IS LOWERED (DUE TO TEMP) PUMP WILL COME ON FOR 1-2 SECONDS TO BUILD UP FROM 2,750 PSI TO 3,000 AND SHUT OFF. A SAFETY MACHINE IS BUILT IN IF AFTER POWER IS SELECTED TO 15 SECONDS - 02 AMP BREAKER WILL POP AND SHUT OFF SYS - NORMAL GEAR EXT OR RETRACTION IS 8 SECONDS. 1ST TIME AFTER ONE ONE- HALF HRS OF FLT - C/B TRIPPE D AND GEAR PUMPED DOWN BY HAND. ACFT PLACED ON JACK, NORMAL, PRESSURE SWITCH CHANGED AS IT WAS FELT TO BE INTERMITENT 2ND TIME IT HAPPENED - GEAR PUMPED DOWN AGAIN AND REMAINED FAILED. POWER PAK REPLACED. (X) 2 L 7 2 4T A24CE 2001032600254 20010326 00254 EA 2001 3 26 CA001026015 1 20001012 G 5755 FITTING DHAV DHC7 DHC7103 2802710 EA PWA PT6 PT6A50 52043 EA HAMSTD 24PF 24PF305 GL SPOILER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING INSPECTION THE LEFT HAND OUTBOARD GROUND SPOILER INBOARD FITTING WAS FOUND CRACKED. SPOILER REMOVED FROM AI RCRAFT AND WILL BE REPLACED. THE CRACK LENGTH IS 0.75. NOTE: THE P/N WAS TAKEN FROM THE DATA PLATE ON THE SPOILER. 2 H 7 4 4T 4 T A20EA E4EA 6 C P1NE 2001032600255 20010326 00255 EA 2001 3 26 CA001026016 1 20001012 G 5755 FITTING DHAV DHC7 DHC7103 2802710 EA PWA PT6 PT6A50 52043 EA HAMSTD 24PF 24PF305 GL SPOILER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING INSPECTION, THE LEFT HAND INBOARD GROUND SPOILER FITTING WAS FOUND TO BE CRACKED BETWEEN FASTENERS. (NOTE: P/N WAS TAKEN FROM DATA PLATE ON THE SPOILER. SPOILER WILL BE REPLACED PRIOR TO AIRCRAFT RETURNING TO SERVICE. THE CRACK ED FITTING IS LOCATED AT THE OUTBOARD POSITION. THE LENGTH OF THE CRACK IS APPROXIMATELY 1/2 INCH. 2 H 7 4 4T 4 T A20EA E4EA 6 C P1NE 2000112800299 20001128 00299 NE 2000 11 28 CA001026019 1 20001002 G 6220 SB7003102 BEARING SKRSKY 761030801004 SKRSKY S76 S76A 8143006 NE TMECA ARRIEL ARRIEL1S1 60030 NE AFT BASE END SEPARATED W K NONE O OTHER IN INSP/MAINT 1 CA B02700478 (CAN) UPON PURCHASE OF THIS HELICOPTER AND DISASSEMBLY FOR INSPECTION AND RE-FURBISHING, THE BLUE POSITION M/R SPINDLE, RETENTION BEARING AND THRUST BEARING WERE REMOVED AS A COMPLETE UNIT. THE AFT BASE END OF THE THRUST BEARING, APPROX .7 5 INCH, WAS FOUND SEPARATED FROM THE MAIN BODY OF THE BEARING. (X) 1 G 7 2 3U 3 U H1NE E19EU 2000112800237 20001128 00237 NE 2000 11 28 CA001026020 1 20001002 G 6220 7610308010049 HUB SKRSKY 763510950004 SKRSKY S76 S76A 8143006 NE TMECA ARRIEL ARRIEL1S1 60030 NE SPINDLE MOUNT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 10194 A08100110 (CAN) UPON PURCHASE OF THIS AIRCRAFT AND DISASSEMBLED FOR INSPECTION AND RE-FURBISHING, THE MAIN ROTOR HEAD ASSEMBLY WAS FOUND CRACKED AT THE FOLLOWING LOCATION THE LOWER ATTACHMENT EAR FOR THE MAIN ROTOR DAMPER (RED POSITION). (X) 1 G 7 2 3U 3 U H1NE E19EU 2001031300095 20010313 00095 NM 2001 3 13 CA001027004 1 20001011 G 2497 BMS1331 WIRE BOEING 737 737201 1384454 NM PWA JT8 JT8D9A 52048 NE APU SPLIT W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) 3 WIRES P/N BMS13-31 TYPE 1 CLASS 1 AWG4 AT CONNECTOR P/N FRF0E28-22S LOCATED FROM APU SHROUD THEN 3 FEET FORWARD TO SPLICES. FOUND TO HAVE MULTIPLE LONGITUDINAL SPLITS IN INSULATOR COATINGS. SPLITS FOUND TO BE 6 INCHES TO 12 INCHES I N LENGTH WITH BARE WIRE EXPOSURE UP TO 0.100 IN WIDTH. 2 L 7 2 4F 4 F A16WE E2EA 2001031300096 20010313 00096 NM 2001 3 13 CA001027005 1 20001018 G 5551 69702513 BOLT BOEING 737 737200 1384453 NM HORIZONTAL STAB WORN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ACCOMPLISHING D CHECK ON US REGISTERED B737 IT WAS NOTED THAT LEFT HAND AND RIGHT HAND AFT HORIZ STAB ATTACH POINT BOLTS FOUND ONLY HAND TIGHT. UPON FURTHER INVESTIGATION ALL THREE BOLTS AFT ON R/H HORIZ STAB AND ALL THREE BOLTS AFT L T HORIZ STAB HAVE WEAR/FRETTING, PITTING AND LIGHT CORROSION ON THE SHAFTS INDICATING IMPROPER TORQUE VALUE. 2 L 7 2 4F A16WE 2001032600258 20010326 00258 EU 2001 3 26 CA001027006 1 20000920 G 5753 137205B68 BRACKET BAG JETSTM JETSTM3101 1500215 EU ROTOL R333 R333482F12 GL SLAT/FLAPS CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 28332 SDJ4904 (CAN) DURING UNSCHEDULED RAMP INSPECTION, AIRWORTHINESS INSPECTOR NOTED 1 BRACKET TO BE CRACKED. BRACKET ATTACHES SLAT T O FLAP AND CLASSIFIED AS PRIMARY CLASS 2 STRUCTURE. AIRCRAFT FERRIED TO MAINTENANCE BASE, WHERE 1 ADDITIONAL BRACKET WA S FOUND TO BE CRACKED. 2 BRACKETS FABRICATED AND INSTALLED, BRACKET(S) APPEAR TO HAVE BEEN CRACKED FOR QUITE SOME TIME. IN ADDITION TO AGE AND CYCLES ON AIRCRAFT POSSIBLE CONTRIBUTING FACTOR COULD BE COMPONENT LOCATION IN PROXIMITY OF ENGI NE EXHAUST CAUSING CORROSION. 2 L 7 2 4T RT A21EU 6 C P61GL 2000112100214 20001121 00214 CE 2000 11 21 CA001027012 1 20000929 G 3246 C1660610301 WHEEL CESSNA 206 U206A 2073316 CE CONT O520 IO520F 17032 SO INNER WHEEL HALF CRACKED W K NONE O OTHER TX TAXI/GRND HDL 1 CA (CAN) FLANGE ON INNER WHEEL HALF CRACKED CAUSING BRAKE TO JAM. AIRCRAFT HAD DIFFICULTY TAXIING. (X) 1 H 7 1 3O 3 O A4CE E5CE 2000112800238 20001128 00238 WP 2000 11 28 CA001027014 1 20001004 G 6210 369D21100517 BLADE HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL M/R BLADE BROKEN W K NONE O OTHER HO HOVERING 1 CA 2634 009999JI48 (CAN) PILOT REPORTED A STRANGE VIBRATION IN THE HELICOPTER. UPON INVESTIGATION ENGINEERING FOUND THE UPPER LEADING EDGE LUG OF THE BLADE CRACKED AND BROKE LOOSE FROM THE BLADE AND ONE BLADE RETENTION PIN BENT. MAIN ROTOR BLADE AND BLADE RET ENTION PINS WERE REPLACED. AS A PRECAUTIONARY MEASURE MAIN ROTOR HUB LEAD LAG LINKS WERE REPLACED. REMAINING BLADES, L INKS AND PINS WERE CHECKED AND FOUND SERVICEABLE. (X) 1 G 7 1 3U 3 U H3WE E4CE 2000112100215 20001121 00215 CE 2000 11 21 CA001027016 1 20001019 G 8011 PM2401 STARTER CESSNA 172 172RG 2072438 CE LYC O360 O360F1A6 41514 EA MCAULY 2D34C B2D34C220 GL STARTER FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 897 80078307 (CAN) MULTIPLE PIECES OF A BURNED AND BROKEN BOLT FOUND IN ENGINE COWLS. BOLT DETERMINED TO BE FROM REAR OF STARTER HOU SING. UPON FURTHER INSPECTION, TWO OF THE REMAINING THREE CASE THROUGH-BOLTS WERE FOUND LOOSE. MISSING BOLT SHOWED SIG NS OF ELECTRICAL ARCING LEADING TO EVENTUAL CUTTING OF THE BOLT. (X) 1 H 7 1 3O 3 O 3A17 E286 5 C P7EA 2001032600466 20010326 00466 EA 2001 3 26 CA001027017 1 20001007 G 2730 C6TEM104229 ARM DHAV DHC6 DHC6 2802606 EA PWA PT6 PT6A20 52043 EA LT ELEVATOR FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) THE SIX ATTACH HOLES ARE COUNTERSUNK TOO DEEP FOR THE INTENDED FASTENERS (PLT110-6) IF INSTALLED THIS ITEM COULD C OME LOOSE RESULTING IN LOSS OF LT ELEVATOR CONTROL. CONCERNED ABOUT MOR IN SAME BATCH IN SERVICE. PLEASE SEE ATTACHED PH OTO COPY. 1 H 7 2 3T 3 T RT A9EA E4EA 2000112100216 20001121 00216 CE 2000 11 21 CA001027018 1 20001027 G 3240 LINE CESSNA 206 U206A 2073316 CE CONT O520 IO520F 17032 SO LT/RT BROKEN W D RETURN TO BLOCK K FLUID LOSS TX TAXI/GRND HDL 1 CA (CAN) AFTER LOADING PASSENGERS, AIRCRAFT STARTED TO TAXI. WHILE ON RUNWAY, PILOT HAD A FAILED BRAKE ON RT SIDE FOLLOWED BY A FAILURE ON THE LT SIDE. AIRCRAFT WAS PUSHED TO TAXIWAY. PASSENGERS HAD STEPPED ON BRAKELINES DURING BOARDING AND BROKEN THEM OFF. BRAKE LINES RE-FLARED AND AIRCRAFT RETURNED TO SERVICE. (X) 1 H 7 1 3O 3 O A4CE E5CE 2000112100217 20001121 00217 NE 2000 11 21 CA001030002 2 20000919 G 7230 COMPRESSOR PWA BEECH 200 B200 1152922 CE PWA PT6 PT6A42 52043 NE COMPR SHROUD FAILED W B EMER. DESCENT B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 CA 3953 681 PCE94208 (CAN) SHORTLY AFTER TAKEOFF, THE CABIN FILLED WITH FUMES AND LIGHT SMOKE. THE AIRCRAFT RETURNED TO THE POINT OF DEPARTUR E. ENGINE WAS SPLIT AT THE C-FLANGE. NO OBVIOUS DAMAGE OR ABNORMALITIES WERE FOUND. A NEW NR 2 BEARING COVER AND GA SKET WERE INSTALLED. ENGINE TEST RUN AND PROBLEM FOUND TO PERSIST. ENGINE REMOVED AND COMPRESSOR SECTION TORN DOWN AT STANDARD AERO. FOUND THE CENTRIFUGAL COMPRESSOR RUBBING ON THE COMPRESSOR SHROUD HOUSING. CLEARANCES RESTORED, ENGINE RE-ASSEMBLED, INSTALLED, TEST RUN AND AIRCRAFT TEST FLOWN. FUMES AND SMOKE NO LONGER PRESENT. (X) 1 L 7 2 4T 4 T A24CE E4EA 2001032600467 20010326 00467 EA 2001 3 26 CA001030003 1 20001004 G 5230 21526063960 SHAFT CNDAIR CL215 CL2151A10 EA CARGO DOOR CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 3390 (CAN) TOTAL SURFACE CORROSION ON INSIDE DIAMETER OF TORQUE SHAFTS AFFECTING 50 - 65 PERCENT OF TOTAL DIAMETER THE FULL L ENGTH OF ONE SHAFT AND APPROX. 60 PERCENT OF LENGTH OF THE OTHER SHAFT. BOTH SHAFTS HAVE SCATTERED PIN HEAD TO 0.250 DIA METER PITTS THROUGH OUT REMAINING AREA.- SHAFT NR 1 HAS MIN. WALL THICKNESS .240 TO AV. THICKNESS .260- SHAFT NR 2 HAS MIN. WALL THICKNESS .245 TO AV. THICKNESS ..255 THERE IS NO SURFACE CORROSION PROTECTION ON THE INSIDE DIAMETER OF THE SHAFTS.SPLINED ENDS OF SHAFTS (MACHINED AND WELDED SEPARATELY) ARE FREE OF ALL DEFECTS AS PER NDT. 2 H 7 2 4R A14EA 2001032600468 20010326 00468 CE 2001 3 26 CA001030004 1 20001004 G 5330 58130412 SKIN CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO MCAULY 3AF32C 3AF32C505 GL FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 10534 (CAN) SKIN CRACKED BY LEFT NOSE GEAR DRAG BRACE ATTACH POINT. SKIN REPLACED. TEE GUSSETT, DOUBLER AND BRACKET WERE ALSO REPLACED. RETRACTION TEST COMPLETED. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2000112800239 20001128 00239 SW 2000 11 28 CA001030005 1 20001017 G 2910 70061H00A180A LINE BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL UPPER DECK FAILED W K NONE O OTHER NR NOT REPORTED 1 CA (CAN) OIL LINE FAILED AT AREA WHERE IT IS CLAMPED TO THE UPPER DECK. (X) 1 G 7 1 3U 3 U H2SW E4CE 2001011105863 20010111 05863 EU 2001 1 11 CA001030008 1 20001019 G 7722 9717382108 PIN PILATS 975290201 PILATS PC12 PC1245 EU PWA PT6 PT6A67B 52043 NE CONNECTOR LOOSE W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 CA 170 (CAN) AIRCRAFT DEPARTED AND SHORTLY AFTER, THE ITT INDICATION STARTED FLUCTUATING BETWEEN 700 AND 300. ALL OTHER ENGINE PARAMETERS WERE WITHIN MANUFACTURER'S SPECIFICATIONS. AIRCRAFT RETURNED TO BASE FOR INSPECTION. PROBLEM WAS FOUND TO BE A LOOSE PIN CONNECTION AT THE BACK OF THE EIS PANEL. PIN WAS SECURED AND AIRCRAFT RETURNED TO SERVICE. (X) 1 L 7 1 3T 4 T RT A78EU E26NE 2001032600475 20010326 00475 EU 2001 3 26 CA001031003 1 20001016 G 7920 13X395MOM18182 LINE ZLIN 242 Z242L 9970204 EU LYC O360 AEIO360A1B6 41514 EA ENGINE OIL FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING SCHEDULED MAINTENANCE (HOSES REPLACEMENT 5 YEAR) ENGINE OIL HOSES (FROM ENGINE TO OIL COOLER) P/N 13X395 M OM 1818.2 WAS FOUND: RADIUS ON THE HOSE WAS BELOW MINIMUM RECOMMANDED RADIUS (10 X DIAMETER OF THE HOSE). MEASURED RADIU S WAS 5 INCH, NEW HOSE SAME P/N INSTALLED. RECOMMENDED ACTION TO THE OWNER IN CLOSED 100 HR INSPECTION PROVIDE NEW ENGIN E OIL HOSE (LONGER) AND RE-ROUTING ENGINE HOSE. 1 L 7 1 3O 3 O 0 A76EU 1E10 2001032600476 20010326 00476 EU 2001 3 26 CA001031004 1 20001017 G 7110 71100071 COWLING BRAERO DH125 HS125700A 4230170 EU GARRTT TFE731 TFE7313R1H 29001 WP ENGINE FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 8070 (CAN) UPON INSPECTION FOUND AN BOLTS IN AFT ENG COWLINGS FLANGE. REPLACED WITH NAS I.A.W. HAWKER RAYTHEON I.P.C. 2 L 7 2 4F 4 F A3EU E6WE 2001032600477 20010326 00477 NM 2001 3 26 CA001031005 1 20000218 G 2497 22AWG WIRE DHAV DHC8 DHC8202 2809007 NM PWA PW120 PW123 NE COCKPIT CHAFED W H DEACTIVATE SYST/CIRCUITS H N ELECT. POWER LOSS-50 PC FALSE WARNING CR CRUISE 1 CA (CAN) THE FOLLOWING WAS REPORTED TO US. NR 1AC GENERATOR FAILED IN FLIGHT, MTW ACTIONS REPLACED AC GENERATOR, CHECKED, FAULT REMAINED, TROUBLESHOT GCU REPLACED, CHECKED, FAULT REMAINED, ON INSPECTION FOUND CHAFED WIRES BEHIND CB PANEL - CB 2421-3, -5, -7 & -9. WIRES REPLACED. A/C CHECKED CARRIED OUT SATISFACTORY, A/C RETURNED TO SERVICE. 2 H 7 2 4T 4 T RT A13NM E20NE 2001032600478 20010326 00478 NM 2001 3 26 CA001031008 1 20000229 G 2731 82700562059 CONTROL CABLE DHAV DHC8 DHC8* NM PWA PW120 PW123 NE ELEVATOR LOOSE W O OTHER O OTHER DE DESCENT 1 CA (CAN) FLIGHT CREW REPORTED RECEIVING A MIS-TRIM MESSAGE ON THE ID-802. THE AUTO-PILOT WAS THEN DISENGAGED & FLT CREW ATT EMPTED TO MOVE TRIM MANUALLY TO A NOSE DOWN ATTITUDE. A RESTRICTION TO THIS MOVEMENT WAS FELT IN THE TRIM CONTROL. AN EX TENDED ROUTE WAS REQUESTED FROM ATC & THE AIRCRAFT LANDED WITHOUT INCIDENT. IT WAS NOTED THAT THE ELEVATOR MANUAL TRIM A PPEARED TO OPERATE NORMALLY AFT OF THE RESTRICTION. (DETAIL: INCIDENT OCCURRED DESCENDING THROUGH 150, VMC, +5C REF: ASR 44R/00/DH8ENGINEERS: COULD NOT REPRODUCE FAULT, BUT ON FURTHER INVESTIGATION TRIM CABLE TENSION DISCOVERED TO BE 0 LBS O NLY, CABLES THOROUGHLY INSPECTED, RE-TENSIONED. FUNCTIONALLY CHECKED & A/C RETURNED TO SERVICE. 2 H 7 2 4T 4 T RT A13NM E20NE 2001031500100 20010315 00100 EA 2001 3 15 CA001031010 2 20001007 G 7261 305306301 SLEEVE DHAV DHC8 DHC8* NM PWC 150 PW150A EA OIL VALVE LEAKING W D RETURN TO BLOCK B SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 CA (CAN) THE FOLLOWING REPORT TO US: FOLLOWING FLT OCCURRENCE REPORT FROM PILOT IN COMMAND OF FLT SK0765 (SAS COMMUTER): DU RING TAXI, 5 MIN AFTER ENGINE START, A/C HELD DUE TO GROUND WORKS, JUST AFTER A/C COME TO COMPETE STOP, SMOKE WARNING FR OM LAVATORY ACTIVATED. ??? AT CAI STATION OPENED COCKPIT DOOR&INFORMED ABOUT WARNING AS WELL. AT TIME SMELL OF SMOKE REC OGNIZED BY CABIN CREW. VISIBLE SMOKE OBSERVED WHEN THEY OPENED LAVATORY DOOR,A GROUND EMERG EVACUATION PERFORMED ACCORDI NG TO PROCS & FIRE BRIGADE ASSISTANCE REQUIRED VIA ATC. MAINT:ENGINE GROUND RUNS HAVE SINCE BEEN CARRIED OUT & IT HAS BE EN DETERMINED THAT LAVATORY SMOKE DETECTOR SET OFF BY OIL FUMES FROM RT ENGINE. 2 H 7 2 4T 4 T RT A13NM E00062EN 2001032600481 20010326 00481 NM 2001 3 26 CA001031011 1 20001009 G 2611 473082 SMOKE DETECTOR DHAV DHC8 DHC8* NM CARGO BAY FAILED W F A ACTIVATE FIRE EXT. UNSCHED LANDING N FALSE WARNING CL CLIMB 1 CA (CAN) THE FOLLOWING FLT OCCURRENCE RPT MADE BY PILOT IN COMMAND OF FLT SK0764 (SAS COMMUTER): JUST AFTER TAKEOFF DURING INIT CLIMB AT APPROX. 3,000 FT, CREW RECEIVED SMOKE FWD CARGO WARNING INTERMITTENTLY FOR APPROX. 3 SEC OR SO. AFTER ONL Y 10 SEC, IT CAME ON AGAIN, AT 1ST IT FLICKERED, THEN CAME ON PERSISTENTLY.I THEN DID MEMORY ITEM & DISCHARGED FWD-CARGO BAY FIRE BOTTLE, CALLED ITC, INFORMED CAI & HAD RADAR VECTOR TO RWY 24 ILS.A NORMAL LDG MAD E&AFTER LDG, TURNED TO LEFT ON TAXI-WAY B. AFTER APPROX. 50 METERS, PASSENGERS WERE EVACUATED THROUGH FWD LT EXIT. SMOKE IND. DISAPPEARED JUST AFTE R BOTTLE EXTINGUISHED. THE FIRE BRIGADE ON TAXI-WAY ON STANDBY, READY TO TAKE ACTION IF NECESSARY. 2 H 7 2 4T RT A13NM 2001032600482 20010326 00482 NM 2001 3 26 CA001031012 1 20001011 G 3411 PITOT TUBE DHAV DHC8 DHC8* NM PITOT STATIC SYS CONTAMINATED W A UNSCHED LANDING G J MULTIPLE FAILURE WARNING INDICATION DE DESCENT 1 CA (CAN) : (FLT NOSK1868 - DEPARTING STAVANGER AT 1225 TO COPENHAGEN). PILOTS RPT IN A/C TECH LOG (L528) STATES:AT FL160 IA S MISMATCH APPEARED. DISAGREEMENT BETWEEN ALL INSTRUMENTS & STANDBY INSTRUMENTS. LOT OF LIGHTS CAME ON CAUTION WARN PANE L. SOME OF THESE WERE PITCH TRIM, ELEV FEEL, SOME SPOILER LIGHTS, NR1 STALL SYS FAIL, & PUSHER SYS FAIL. AFTER APPROX. 8 MINS, MOST FAILURES CANCELED THEMSELVES EXCEPT FOR NR 1 STALL SYS FAIL & PUSHER SYS FAIL. DURING FAIL PERIOD, LT AIRSP EED & ALTIMETER FAILED COMPLETELY FOR APPROX 3-4 MINS. RUDDER CONTROL CAUTION LIGHT ALSO CAME ON DURING FAILURE PERIOD. LT AIRSPEED WENT TO 30, RT AIRSPEED 230 IAS, STANDBY160 IAS.MAINT: TROUBLESHOOTING FOUND WATER CONTA 2 H 7 2 4T RT A13NM 2001032600483 20010326 00483 NM 2001 3 26 CA001031014 1 20000921 G 3231 83232017103 LINK DHAV 83232017003 DHAV DHC8 DHC8* NM SEQUENCE VALVE BROKEN W O OTHER J WARNING INDICATION DE DESCENT 1 CA 838 (CAN) CREW SELECTED GEAR DOWN DURING DESCENT INTO AMAKUSA. LT MLG WOULD NOT EXTEND (DOORS FAILED TO OPEN). CREW PERFORM ED ALT EXT PER QRH & GEAR CAME DOWN & LOCKED INTO POS. A/C MADE UNEVENTFUL LDG AT AMAKUSA AIRPORT. CHIEF PILOT FLYING&NO TED LT MLG SLOW TO DISPLAY UP&LOCKED AFTER TAKEOFF&POPPING SOUND HEARD DURING RETRACTION. ELECTED TO EXTEND GEAR EARLIE R THAN NORMAL DURING DESCENT AND SUBSEQUENTLY DISCOVERED PROBLEM AND ACTED ACCORDINGLY. FSR WASNT NOTIFIED UNTIL NEXT MO RNING. AMX MAINT INVEST. FOUND LT MLG DOOR SEQUENCE LINK TO BE BROKEN IN 2 PIECES (HENCE MLG DOORS WOULD NOT OPEN HYDRAU LICALLY). 2 H 7 2 4T RT A13NM 2001031300098 20010313 00098 NM 2001 3 13 CA001031015 1 20000924 G 2720 7G772 PRESSURE SWITCH DHAV DHC8 DHC8301 NM RUDDER DAMPER FAILED W D RETURN TO BLOCK N FALSE WARNING TX TAXI/GRND HDL 1 CA 2161 (CAN) FROM BWIA MAINTENANCE REPORT: NR 2 RUDDER HYDRAULIC CAUTION LIGHT ILLUMINATED, SWITCHES SWAPPED FOR TROUBLESHOOTIN G. PROBLEM TRANSFEREE TO NR 1 SIDE. NR 1 PRESSURE SWITCH ON RUDDER DAMPER REPLACED (SWITCH WAS SWAPPED).AIRCRAFT FUNCTIO NALLY TESTED SATISFACTORY, RETURNED TO SERVICE. 2 H 7 2 4T RT A13NM 2001031300099 20010313 00099 NM 2001 3 13 CA001031016 1 20000926 G 2720 7G772 PRESSURE SWITCH DHAV DHC8 DHC8301 NM RUDDER DAMPER FAILED W D RETURN TO BLOCK N FALSE WARNING TX TAXI/GRND HDL 1 CA 12 (CAN) BWIA MCC REPORT FROM GEORGETOWN, BARBADOS: NR 2 RUDDER HYDRAULIC CAUTION LIGHT ILLUMINATED (SWITCHES SWAPPED FOR T ROUBLESHOOTING), PROBLEM TRANSFERRED TO NR 1 SIDE. NR 1 PRESSURE SWITCH ON RUDDER DAMPER REPLACED (SWITCH WAS SWAPPED).A IRCRAFT FUNCTIONALLY TESTED SATISFACTORY, RETURN TO SERVICE. 2 H 7 2 4T RT A13NM 2001031300100 20010313 00100 NM 2001 3 13 CA001031017 1 20000804 G 2910 NAS16124 O-RING DHAV DHC8 DHC8301 NM PRESS MANIFOLD DETERIORATED W O OTHER J K WARNING INDICATION FLUID LOSS CR CRUISE 1 CA (CAN) THE FOLLOWING REPORTED TO US (BRYMON MAINT CTL): DURING CRUISE AT 16,000 FT ON ROUTE TO GLASGOW SPARE CAUTION LIGH T ILLUMINATED (LIGHT ABOVE FUEL TANK LOW LEVEL) THEN EXTINGUISHED FOLLOWED BY HYDRAULIC CAUTION LIGHTS. HYDRAULIC CONTEN TS I INDICATED NR 2 SYS DEPLETED. EMERGENCY CHECKLIST CONSULTED & PAN DECLARED.GEAR EXTENDED ON FINAL AT GLASGOW TO PERM IT EMERGENCY CHECK LIST ACTION BEFORE UNEVENTFUL APPROACH & LDG. A/C CLEARED RWY&SHUTDOWN. LDG GEAR PINS INSERTED INTO G EAR & A/C TOWED TO STAND, PASSENGERS DISEMBARKED. MAINT: FOUND NR 2 HYDRAULIC PRESSURE MANIFOLD LEAKING AT BLANK (AN814- 4D).SEAL FOUND DETERIORATED. NEW SEAL FITTED & BLANK REPLACED. FOLLOWING ITEMS ALSO REPLACED, AS SYS RAN DRY. 1) ENGINE 2 H 7 2 4T RT A13NM 2001032600484 20010326 00484 NM 2001 3 26 CA001031018 1 20000813 G 2910 NAS16121 O-RING 8291000255 DHAV DHC8 DHC8* NM PWA PW120 PW123 NE SEQUENCE VALVE DEFORMED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A DAILY INSPECTION WHILE ON A MAINTENANCE INPUT; CREW FIXED OXYGEN BOTTLE & ASSOCIATED HOSES FOUND COVERED IN HYDRAULIC FLUID. ACTION: OXYGEN BOTTLE & HOSES REMOVED. HYDRAULIC POWER APPLIED TO THE NR 2 SYSTEM HYDRAULIC LEAK FO UND AT NOSE GEAR SOLENOID SELECTOR VALVE RESTRICTOR UNION O-RING. O-RING REPLACED AND CHECKED SATISFACTORY. AREA THOROUG HLY CLEANED AND OXYGEN EQUIPMENT REFITTED WITH NEW HOSES. 2 H 7 2 4T 4 T RT A13NM E20NE 2001032600485 20010326 00485 NM 2001 3 26 CA001031019 1 20001011 G 2910 AN81510D O-RING DHAV DHC8 DHC8* NM PWA PW120 PW123 NE HYD SYSTEM CRACKED W O OTHER K J FLUID LOSS WARNING INDICATION AP APPROACH 1 CA 4723 (CAN) ON APPROACH TO POS, WITH GEAR UP, GOT HIS NR 2 EDP HYDRAULIC CAUTION LIGHT AND NOTICED HIS NR 2 HYDRAULIC QUANTIT Y DROPPED TO ZERO. FOLLOWED PROCEDURES PER QRH. AIRCRAFT LANDED IN PORT OF SPAIN & TOWED TO GATE. MAINTENANCE: NR 2 EDP SUPPLY LINE TO THE PRESSURE MANIFOLD, UNION FOUND SHEARED OFF AT PRESSURE MANIFOLD SIDE. UNION STILL ATTACHED TO LINE. T HIS IS EXACT DEFECT REPORTED.MANIFOLD REPLACED & AIRCRAFT FUNCTION TESTED, LEAK CHECKED AND RETURNEED TO SERVICE. 2 H 7 2 4T 4 T RT A13NM E20NE 2001032600486 20010326 00486 NM 2001 3 26 CA001031021 1 20000828 G 2810 82820045104 TUBE DHAV DHC8 DHC8* NM PWA PW120 PW123 NE FUEL SYSTEM CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA 14059 (CAN) DURING SCHEDULED INSPECTION OF RT FUEL TANK, SERIOUS WEAR ON THE AFFECTED FUEL TUBE WAS DETECTED. THE INTERFERENC E WITH THE BONDING STRAP CREATED HEAVY WEAR & PENETRATION OF THE TUBE WALL. THE STRAP INSTALLATION MUST BE CORRECTED AND FORWARD INSTALLATION OF THE FUEL TUBE. ACTION: WORN TUBE REPLACED AND BONDING STRAP ROUTED CORRECTLY.QIR INVESTIGATION REPORT - DMAR-NDAR-00-00003 FILED BY BOMBARDIER, DEHAVILLAND. 2 H 7 2 4T 4 T RT A13NM E20NE 2001031300101 20010313 00101 NM 2001 3 13 CA001031022 1 20001009 G 5270 8520200015 WARNING SYSTEM DHAV DHC8300 DHAV DHC8 DHC8301 NM PWA PW120 PW123 NE SERVICE DOOR ACTIVATED W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA 422 (CAN) THE FOLLOWING WAS REPORTED TO US (FROM BRYMON SAFETY REPORT 213R/00/DH8): TAKEOFF ABORTED SHORTLY AFTER POWER APPL ICATION, DUE TO INTERMITTENT SERVICE DOOR WARNING LIGHT ILLUMINATION. PILOT LIAISON WITH CABIN ATTENDANT WHO ADVISED SER VICE DOOR HANDLE NOT ACCURATELY STOWED. RESET HANDLE, WARNING LIGHT CLEARED (EXTINGUISHED), AIRCRAFT RETURNED TO TAKEOF F, SATISFACTORY. 2 H 7 2 4T 4 T RT A13NM E20NE 2001032700004 20010327 00004 NM 2001 3 27 CA001031023 1 20000905 G 2910 DSC1896 CHECK VALVE DHAV DHC8 DHC8* NM PWA PW120 PW123 NE RT WING FRACTURED W D RETURN TO BLOCK K J FLUID LOSS WARNING INDICATION TX TAXI/GRND HDL 1 CA (CAN) DURING TAXI, DECREASE IN HYDRAULIC FLUID QUANTITY OBSERVED. AIRCRAFT RETURNED TO RAMP. HYDRAULIC FLUID NOTICED TO BE COMING FROM RIGHT WING/ARMPIT AREA. INSPECTION REVEALED A BROKEN AND SEVERED BODY OF THE PTU CHECK VALVE AND A DIST ORTED HYDRAULIC LINE (P.N. 82940010-159). BOTH ITEMS REPLACED. GROUND RUN CARRIED OUT, SYSTEMS FUNCTION CHECK AND LEAK C HECK CARRIED OUT S ATISFACTORY. AIRCRAFT RETURNED TO SERVICE.NOTE: OPERATOR FLEETWIDE CAMPAIGN IN EFFECT TO CHECK FOR DE FECTS IN ASSOCIATED PARTS. DEFECTIVE PART TO BE SENT TO MANUFACTURER FOR ANALYSIS. 2 H 7 2 4T 4 T RT A13NM E20NE 2001032600487 20010326 00487 NM 2001 3 26 CA001031025 1 20001009 G 3411 PH1001DH PITOT HEAD DHAV DHC8 DHC8* NM PWA PW120 PW123 NE PITOT STATIC SYS CONTAMINATED W C ABORTED TAKEOFF H J ELECT. POWER LOSS-50 PC WARNING INDICATION TO TAKEOFF 1 CA (CAN) NR 1 ASI FAILED TO REGISTER UP TO 70 KTS, REJECTED TAKEOFF COMPLETED. AFTER REJECTED TAKEOFF, AIRCRAFT RETURNED T O STAND FOR INVESTIGATION. ENGINEER CLEARED PITOT HEAD AND REPORTED, EXCESSIVE WATER APPARENT IN TUBE. AIRCRAFT WAS PARK ED OVERNIGHT IN HEAVY RAIN AND THIS WAS THE FIRST FLIGHT OF THE DAY. 2 H 7 2 4T 4 T RT A13NM E20NE 2001031300102 20010313 00102 EA 2001 3 13 CA001031026 1 20001009 G 2910 AN81510D CONNECTOR DHAV DHC8 DHC8311 1386006 EA PWA PW120 PW123 NE PRESS MANIFOLD SHEARED W O OTHER K J FLUID LOSS WARNING INDICATION AP APPROACH 1 CA 11837 (CAN) THE FOLLOWING WAS REPORTED TO US: INFO GATHERED FROM RETURNING ENGINEER (TODAY 10TH OCT) STATES THAT CAPTAIN REPOR TED ON APPROACH HE NOTICED THAT NR 2 ENGINE HYDRAULIC PUMP CAUTION LIGHT ILLUMINATED AND WITHIN 3 SECONDS OBSERVED TOTA L LOSS OF NR 2 HYDRAULIC FLUID IN THE SYSTEM.PER QRH, ALT EXT WAS CARRIED OUT AND AIRCRAFT LANDED UNEVENTFULLY. AIRCRAFT WAS REPORTED TO HAVE STOPPED AT 7,500 FEET FROM POINT OF TOUCH DOWN. CAPTAIN REQUESTED AIRCRAFT BE TOWED TO GATE.MAINT ENANCE:REPLACED MANIFOLD ASSEMBLY AND UNION, NR 2 HYDRAULIC SYSTEM FLUID REPLENISHED, SYSTEM BLED AND AIRCRAFT RELEASED AS SERVICEABLE. 2 H 7 2 4T 4 T RT A13NM E20NE 2001032600488 20010326 00488 NM 2001 3 26 CA001031027 1 20000306 G 2913 82970007001 PUMP DHAV DHC8 DHC8* NM PWA PW120 PW123 NE HYD SYSTEM FAILED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 688 (CAN) AFTER TAKEOFF ON GEAR RETRACTION, NR 2 EDP CAUTION LIGHT ILLUMINATED, LEFT DOOR, AND NOSE DOOR ADVISORY LIGHT ILLU MINATED ON AND NR 2 MAIN AND STANDBY HYDRAULIC PRESSURE FELL TO BELOW 1000 PSI. LANDING GEAR LOWERED USING PTU. AIRCRAFT LANDED NORMALLY. NR 2 EDP REPLACED, RETRACTION CHECK CARRIED OUT ON TEST FLIGHT, CHECKED OK. S/N ON: MX500840CD S/N OFF : MX614976D 2 H 7 2 4T 4 T RT A13NM E20NE 2001031300103 20010313 00103 EA 2001 3 13 CA001031028 1 20001020 G 6120 57B1901 LINK DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL PROPELLER CRACKED W O OTHER O OTHER NR NOT REPORTED 1 CA 17196 3566 (CAN) CRACK INDICATION ON THE LINK ARM FOUND DURING OVERHAUL INSPECTION. 1 H 7 2 3T 4 T RT A9EA E4EA 6 C P15EA 2001031300104 20010313 00104 EA 2001 3 13 CA001101003 1 20001010 G 5610 NP1393215 WINDSHIELD CNDAIR CL600 CL6002B19 EA COCKPIT FAILED W A UNSCHED LANDING O OTHER CR CRUISE 1 CA (CAN) THE LT WINDSHIELD SHATTERED. MAINTENANCE REPLACED THE WINDSHIELD P/N NP139321-5 (S/N ON:00119H6340). 2 L 7 2 4F RT A21EA 2001011106126 20010111 06126 EA 2001 1 11 CA001101006 1 20001010 G 5610 WINDOW CNDAIR CL6002B19 CNDAIR CL600 CL6002B19 EA COCKPIT FAILED W O OTHER O OTHER CR CRUISE 1 CA 2839 7343 (CAN) DURING CRUISE, A LOUD BANG WAS HEARD AND THE RT SIDE WINDOW WAS OBSERVED TO BE SHATTERED. AN EVENTFUL LANDING FOLL OWED.BOTH CORE AND OUTER LAYERS FOUND TO BE DAMAGED. WINDOW REPLACED AND A/C RETURNED TO SERVICE. 2 L 7 2 4F RT A21EA 2001032600116 20010326 00116 EA 2001 3 26 CA001101007 1 20001014 G 2612 47259701 CONTROL PANEL CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE COCKPIT FAILED W C ABORTED TAKEOFF N FALSE WARNING TO TAKEOFF 1 CA (CAN) DURING TAKEOFF, APU FIRE WARNING BELLS SOUNDED. CREW DISCHARGED FIRE EXTINGUISHER AND APU FIRE WARNING STOPPED. MU LTIPLE FIRE FAIL MESSAGES WEREALSO POSTED.MAINTENANCE CREW OBSERVED SPILLED BEVERAGE CONTAINER ON L/H SIDE CONSOLE AND F LUID EVIDENT IN FIRE AND OVERHEAT CONTROL UNIT. REPLACED FIRE AND OVERHEAT CONTROL UNIT.AIRCRAFTRETURNED TO SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001031300105 20010313 00105 EA 2001 3 13 CA001101008 1 20001014 G 2750 CONTROL UNIT CNDAIR CL600 CL6002B19 EA TE FLAPS FAILED W O OTHER F J FLT CONT AFFECTED WARNING INDICATION DE DESCENT 1 CA (CAN) DURING DESCENT, FLAPS FAIL AMBER MESSAGE ON EICAS, AS CREW SELECTED FLAPS TO 8 DEGREES. 0 DEGREES FLAPS LANDING PE RFORMED WITH NO FURTHER EVENTS. FURTHER DETAILS TO FOLLOW. 2 L 7 2 4F RT A21EA 2001032600127 20010326 00127 EA 2001 3 26 CA001101010 1 20001015 G 3260 864806 PSEU CNDAIR CL600 CL6002B19 EA GE CF34 CF341A NE MLG FAILED W O OTHER N FALSE WARNING AP APPROACH 1 CA (CAN) GEAR DISAGREE WARNING MESSAGE POSTED DURING APPROACH. NOSE GEAR SHOWED DOWN AND LOCKED WHILE MAIN GEAR SHOWED UP & LOCKED.ABORTED APPRAOCH, PERFORMED MANUAL GEAR EXTENSION AND PERFORMED UNEVENTFUL EMERGENCY LANDING. PSEU REPLACED, AIR CRAFT BACK IN SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001031300106 20010313 00106 SO 2001 3 13 CA001101016 1 20001003 G 3244 613160 TIRE CLEVELAND 40140 PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2B 41532 EA NOSE WHEEL FAILED W C ABORTED TAKEOFF O OTHER TO TAKEOFF 1 CA 29 (CAN) 1) AT REPLACEMENT: NEW BEARINGS & CUPS & AXLE CHECKED.2) NEXT FLIGHTS PILOT REPORTED SHIMMING.3) SHIMMY DAMPENER LOW IN FLUID, RESERVICED.4) FURTHER ON PILOT PRECISED - NOT SHIMMING BUT SAID THE NOSE WHEEL SKIPPING ON TAKEOFF AS SPEE D INCREASED. 5) AIRCRAFT ON JACKS: CALIPERED TIRE TO LD GEAR FORK, NOT ROUND.6) INSTALLED NEW TIRE. PILOT REPORTS NOW OK .7) RETURNED FAULTY TIRE TO API LTD ON WARRANTY. NOTE: NO FLAT SPOTS, NO BULGES ON DEFECTIVE TIRE. TIRE, MICHELIN-AVIAT OR 6.00X6PR TT 1 L 7 2 3O 3 O A20SO E14EA 2001031300107 20010313 00107 EA 2001 3 13 CA001101020 1 20001015 G 4990 APU CNDAIR CL600 CL6002B19 EA APU BAY FAILED W O OTHER J WARNING INDICATION CR CRUISE 1 CA (CAN) APU OIL TEMP CAUTION MESSAGE POSTED ON EICAS IN FLIGHT, WITH APU OPERATING BECAUSE IDG NR 1 WAS DEFERRED. CREW DEC LARED AN EMERGENCY LANDING AND MADE AN UNSCHEDULED LANDING.INSPECTED APU AND FOUND IT LOW ON OIL. SERVICED WITH ON QUART OF OIL. AIRCRAFT BACK IN SERVICE. 2 L 7 2 4F RT A21EA 2001031300108 20010313 00108 EA 2001 3 13 CA001101021 1 20001020 G 2710 AILERON CNDAIR CL600 CL6002B19 EA WING FAILED W O OTHER F FLT CONT AFFECTED CR CRUISE 1 CA (CAN) AP RWD MESSAGE. TRANSFERED TO MANUAL FLIGHT. ON FLIGHT CONTROL SYNOPTIC PAGE, ONLY THE LEFT AILERON WAS DEFLECTING . THERE WAS THE FEELING OF A BLOCKAGE. AFTER PILOT TOOK OVER, HEAVY JERK DURING A LEFT TURN AND NORMAL FLIGHT AFTER. AIL ERON MOVES AGAIN. 2 L 7 2 4F RT A21EA 2001031300109 20010313 00109 EA 2001 3 13 CA001101023 1 20001020 G 2710 CONTROL UNIT CNDAIR CL600 CL6002B19 EA AILERON FAULTY W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA (CAN) AT 80 KTS DURING TAKEOFF ROLL, THE AILERON WARNING MSG APPEARED.THE FLIGHT CREW ABORTED TAKEOFF AT 85 TO 90 KTS. (UNEVENTFUL). AIRCRAFT WAS ROUTED TO THE HANGAR FACILITY FOR HIGH SPEED TAKEOFF INSPECTION AND AILERON INVESTIGATION. NO DEFECT NOTED, AIRCRAFT RELEASED FOR SERVICE. 2 L 7 2 4F RT A21EA 2001031300110 20010313 00110 EA 2001 3 13 CA001101024 1 20001020 G 2750 FCU CNDAIR CL600 CL6002B19 EA GE CF34 CF343A 30015 NE TE FLAPS FAILED W A UNSCHED LANDING F FLT CONT AFFECTED CL CLIMB 1 CA (CAN) THE FLAPS FAIL CAUTION MSG APPEARED UPON FLAP SELECTION AFTER TAKEOFF. FLAPS INDICATED 8 DEGREES WITH FLAPS SELEC TED TO 0 DEGREE (APPROXIMATELY.). THE FLIGHT CREW RETURNED TO THE DEPARTING AIRPORT (ALLENTOWN --PA (ABE) & DECLARED AN EMERGENCY LANDING.MAINTENANCE ACTION: INSPECTED FLAP FOR CONDITION AND SECURITY (OK) (FIRST EVENT) RESET THE FLAP SYSTEM , OPERATION CHECK, SERVICEABLE (72 HOURS). 2 L 7 2 4F 4 F RT A21EA E15NE 2001031300111 20010313 00111 EA 2001 3 13 CA001101025 1 20001020 G 5610 WINDOW CNDAIR CL600 CL6002B19 EA COCKPIT FAILED W O OTHER O OTHER CL CLIMB 1 CA (CAN) CREW ADVISED THAT AFTER TAKEOFF CAPTAINS SIDE WINDOW OUTER PANE SHATTERED. AIRCRAFT RETURNED TO NASHVILLE. MAINTEN ANCE DISPATCHED FROM ATLANTA TO REPLACE WINDOW. 2 L 7 2 4F RT A21EA 2001011106135 20010111 06135 WP 2001 1 11 CA001102002 1 20001008 G 2460 CIRCUIT BREAKER LKHEED 1011 10113851 5265010 WP RROYCE RB211 RB21122B02 54555 NE GALLEY FAILED W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 CA (CAN) SPARKS WHERE SEEN COMING FROM LT MID GALLEY SERVICE OUTLET DURING TAKEOFF, CIRCUIT BREAKERS J19 & C13 PULLED AND C OLLARED. SYSTEM DE-ACTIVATED AND AIRCRAFT RELEASED UNDER MEL. 2 L 7 3 4F 4 F A23WE E12EU 2001031300112 20010313 00112 WP 2001 3 13 CA001102003 1 20001013 G 2720 CONNECTOR WHITTAKER 1496452 LKHEED 1011 1011385114 WP RROYCE RB211 RB21122B02 54555 NE SHUTOFF VALVE WRONG PART W K NONE O OTHER IN INSP/MAINT 1 CA 67M (CAN) DURING DEFECT TROUBLE SHOOTING OF THE YAW SAS 2 FAIL & RUDDER HYDRAULIC LIMITER FOUND WRONG PART INSTALLED, (UNION WITH OUT A RESTRICTOR), INSTALLED ON THE HYDRAULIC SHUTOFF VALVE REPLACED AIRCRAFT DISPATCHED.PART WAS FOUND NOT TO HAV E BEEN INSTALLED BY AIR TRANSIT (PART WAS NOT IN THE AIR TRANSIT SYSTEM), THE AIRCRAFT COULD HAVE BEEN IMPORTED IN THIS MANNER.WITHOUT DISASSEMBLY COULD NOT VISUALLY CONFIRM THAT THE PROPER UNION IS INSTALLED. 2 L 7 3 4F 4 F A23WE E12EU 2001031400001 20010314 00001 NE 2001 3 14 CA001102006 3 20001012 G 6111 6903A10S BLADE HAMSTD 43E60581 CNDAIR CL215 CL2151A10 EA HAMSTD 43E 43E60 NE PROPELLER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 3737 2329 206025 (CAN) CRACK FOUND ON LEADING EDGE IN SHOT PEENED AREA, LOCATED IN A OLD LOCAL REPAIR AT STATION 46 INCH. 2 H 7 2 4R A14EA 6 C P871 2001032600146 20010326 00146 CE 2001 3 26 CA001102007 1 20001002 G 3222 0542106 SPRING CESSNA 170 170B 2072306 CE LYC O360 O360A1A 41514 EA TAIL WHEEL BROKEN W O OTHER O OTHER LD LANDING 1 CA 4012 (CAN) DURING LANDING ON A GRAVEL STRIP THE TAIL WHEEL SPRING BROKE. PILOT KEPT CONTROL OF THE PLANE AND HAD NO OTHER DA MAGE. THE LOWER SPRING LEAF (P.N. O542106) HAS BEEN FOUND BROKEN AT TWO PLACES. ALL (4) SPRING LEAVES HAVE BEEN REPLACED WITH NEW UNITS. 1 H 7 1 3O 3 O A799 E286 2001032600147 20010326 00147 EA 2001 3 26 CA001102009 1 20000919 G 3242 2158750224 BRAKE ASSY CNDAIR CL215 CL2156B11415 EA LT BRAKE OVERHEATED W O OTHER M B OVER TEMP SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 CA 15 15 (CAN) WHEN THE AIRCRAFT STOPPED, THE GROUND CREW NOTICED SMOKE COMING FROM THE LEFT WHEEL. FANS WERE USED TO COOL OFF TH E BRAKES. THE FUSE PLUGS HAVE MELTED. AIRCRAFT BRAKE SYSTEM WAS INSPECTED AND FOUND TO BE IAW THE MAINTENANCE MANUAL. TH E LEFT BRAKE AND WHEEL ASSEMBLY WERE REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. THE BRAKE HAS BEEN SENT FOR EXPERTIS E DUE TO DISKS JAMMING. 2 H 7 2 4T RT A14EA 2001031400002 20010314 00002 EA 2001 3 14 CA001102010 1 20000829 G 5311 21531036252 FRAME CNDAIR CL215 CL2151A10 EA FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 2184 (CAN) DURING 50 HRS INSPAT 2184 HRS TAT, 1579 LAND LDGS & 9512 WATER DROPS, CRACK RPTED AT UPPER FASTENER OF LT REAR SPA R OUTBOARD WING TO FUSELAGE FRAME ANGLE LOCATED AT FS 434.5 & LBL 51. IN ORDER TO KEEP A/C IN SE RVICE, AMOC FOR AD CF-9 7-07R2 GRANTED BY TCA - ALLEVIATION NOAARDG 2000/A116. ALLEVIATION REQ VISUAL INSP OF CRACK PROPAGATION AT INTERVALS NOT TO EXCEED 10 HRS. DURING VISUAL INSP AT 2224 HRS TAT, 1596 LAND LA NDINGS & 9621 WATER DROPS, ANOTHER CRACK RPTED IN SA ME AREA ON ANGLE P/N 215-31036-68. ANGLE IS FASTENED ON FRAME ANGLE P/N 215-31036-252 AT WL218. ONCE THAT ANGLE -68 REMV D TO BE REPL, THEN 2ND CRACK FOUND ON FRAME ANGLE 215-31036-252. 2 H 7 2 4R A14EA 2001031400003 20010314 00003 NE 2001 3 14 CA001102011 2 20000922 G 8550 LINE CNDAIR CL215 CL2151A10 EA PWA R2800 R2800CA3 52026 NE OIL PRESSURE SHEARED W E A ENGINE SHUTDOWN UNSCHED LANDING Y ENGINE STOPPAGE CR CRUISE 1 CA 1354 (CAN) A MISSION HAS BEEN ABORTED DUE TO IMPORTANT OIL LEAK FROM THE ENGINE FRONT CASE ASSEMBLY. AFTER AN INVESTIGATION, IT WAS FOUND THAT THE UPPER OIL TRANSFER TUBE PORT THREADS ON THE FRONT CASE DAMAGED AND HAD ITS PLUG LOOSENED THAT CAU SED AN EXCESSIVE OIL LEAK. NOTE: SERVICE BULLETIN NO.1755, FRONT CASE OIL TRANSFER TUBE PORT THREAD REPAIR WAS NOT INCOR PORATED. 2 H 7 2 4R 4 R A14EA 5E8 2001031400004 20010314 00004 NM 2001 3 14 CA001102014 1 20000925 G 2782 6544851 ACTUATOR BOEING 737 7372Q9 138448M NM PWA JT8 JT8D9A 52048 NE GROUND SPOILER CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) ON LANDING DURING GROUND SPOILER DEPLOYMENT HYDRAULIC FLUID WAS OBSERVED LEAKING FROM THE NR 5 GROUND SPOILER NR 5 ACTUATOR. OBSERVATION REVEALED THAT UNDER PRESSURE A CRACK WOULD OPEN UP IN THE CASE. SPOILER ACTUATOR WAS REPLACED. CH ECKED SERVICEABLE. 2 L 7 2 4F 4 F A16WE E2EA 2001031400005 20010314 00005 NM 2001 3 14 CA001102015 1 20000929 G 3222 L507945 BEARING BENDIX 26010452 BOEING 737 737201 1384454 NM PWA JT8 JT8D9A 52048 NE NLG WHEEL FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 137 B5472 (CAN) ABNORMAL NOSE WHEEL VIBRATION OBSERVED DURING TAXI. MAINT JACKED A/C NOSE GEAR ASSY. REMOVED NR 1 & NR 2 NOSE WHEE L ASSY, OBSERVED NR 1 NOSE WHEEL ASSY OUTER BEARING HAD FAILED CAUSING DAMAGE TO AXLE ASSY (P/N 65-46215-2). A/C REMOVE D FROM SERVICE.AXLE / INNER CYLINDER ASSY REPLACED (P/N 65-46315-12). INVEST. IS ONGOING BY QA AS TO WHY BEARING FAILED . 2 L 7 2 4F 4 F A16WE E2EA 2001031400008 20010314 00008 2001 3 14 CA001103007 4 20001020 G 2310 5985999522043 ANTENNA BOEING 737 737230 NM TENSIONER FAILED W O OTHER D INFLIGHT SEPARATION CR CRUISE 1 CA (CAN) DURING TEST FLIGHT, THE NR 1 HF ANTENNA SEPARATED AT THE CABLE TENSIONER AFTER TENSIONER FAILURE. THE FREED CABLE WHIPPED AGAINST THE FUSELAGE, DAMAGING 4 CABIN WINDOWS AND DENTING THE FUSELAGE AT 2 PLACES (STA 685 AND 688). THE TURN BARREN SECTION OF THE TENSIONER FLAPPED AGAINST THE NR 4 SPOILER CAUSING DAMAGE TO THE SPOILER. 2 L 7 2 4F RT A16WE 2001032600242 20010326 00242 CE 2001 3 26 CA001103009 1 20001020 G 2434 1101912 GENERATOR CESSNA 182 182G 2072716 CE CONT O470 O470R 17026 SO MCAULY 2A34C 2A34C50 GL ELECTRICAL FAILED W K NONE H L ELECT. POWER LOSS-50 PC NO TEST IN INSP/MAINT 1 CA (CAN) 4 GENERATORS WERE TRIED ON THIS AIRCRAFT OVER A PERIOD OF 15 - 18 MONTHS, THE END RESULT WAS INSTALLING AN ALTERNA TOR KIT, AS THE COMPANY OVERHAULED THE GENERATOR WAS DOING SUBSTANDARD WORK. 1 H 7 1 3O 3 O NT 3A13 E273 5 C P3EA 2001031400010 20010314 00010 NM 2001 3 14 CA001103010 1 20000919 G 5410 654685015 FITTING BOEING 737 737230C 1384472 NM PWA JT8 JT8D15 52051 NE NR 1 ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CRACK DETECTED VISUALLY IN WEB OF RIGHT ARM OF THE NR 1 ENGINE FORWARD MOUNT FITTING. THE ENGINE WAS REMOVED TO FA CILITATE LAP JOINT MODIFICATION AND REMOVAL TASK CARD CALLS FOR INSPECTION OF ALL ENGINE MOUNTS. 2 L 7 2 4F 4 F A16WE E2EA 2001031400011 20010314 00011 EA 2001 3 14 CA001103011 2 20001025 G 7310 LW120980170 LINE PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA FUEL MANIFOLD DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA L640661A (CAN) AD 93-02-05 AND LYC SB 342C ADDR BENDING LIMITS FOR FUEL LINE ALONG WITH MEANS OF MINIMIZING HAZARDS OF FUEL LINE DAMAGE. 2 LIMITS LISTED ARE NO BENDS WITHIN 0.69 INCH FROM END AND MIN RADIUS OF 0.62 INCH (.6250 INCH) TO CENTER OF F UEL LINE. WHEN LINE IS BENT TO THESE LIMITS AND INST ON NR 2 CYL, IT COMES WITHIN 0.20 INCH OF COWL, OVERLAPS COWL HALF JOIN BY 0.40 INCH IN VERTICAL PLANE. WITH OVERLAP, TORQUE DEFLECTION OF ENG COULD ALLOW CONTACT OF FUEL LINE TO INNER COWL FLANGE. MINOR DEVIATION FROM SB INSTRUCTIONS WILL ELIMINATE HAZARD. IF BEND STARTS AT 0.69 INCH FROM END AND MIN RADIUS IS REDUCED TO 0.30 INCH, DISTANCE TO INNER COWL IS ACCEPTABLE AND NO DANGER OF CONTACT WITH COWL EXISTS. (X) 1 L 7 2 3O 3 O A20SO E14EA 2000112800151 20001128 00151 NE 2000 11 28 CA001103013 2 20001005 G 7321 430128307 FUEL CONTROL LYC BOLKMS 117 BK117B1 5626012 EU LYC LTS101 LTS101750B1 41560 NE ENGINE INOPERATIVE W O OTHER R PARTIAL RPM/PWR LOSS CR CRUISE 1 CA 2364 LE45704EFA (CAN) DURING TEST FLIGHT FOR NR 1 ENGINE AIRFLOW MODULATOR REPLACEMENT, IT WAS DISCOVERED THAT THE NR 2 ENGINE WAS N1 L IMITED CAUSING LOW POWER. (X) 1 G 7 2 3U 3 U H13EU E5NE10 2001031400013 20010314 00013 NM 2001 3 14 CA001103017 1 20001018 G 2751 2061141 INDICATOR BOEING 737 7372A3 138448A NM PWA JT8 JT8D9A 52048 NE TE FLAPS FAILED W O OTHER N FALSE WARNING AP APPROACH 1 CA 482 (CAN) ON APPROACH THE FLAPS FAILED TO EXTEND BEYOND 5 UNITS AND INDICATED AN ASYMMETRICAL CONDITION. THE AIRCRAFT LANDED WITHOUT INCIDENT. FLAP POSITION INDICATOR WAS REPLACED AND THE SYSTEM CHECK WITH NO FURTHER FAULT FOUND. THE AIRCRAFT W AS RETURNED TO SERVICE. 2 L 7 2 4F 4 F A16WE E2EA 2000112800154 20001128 00154 2000 11 28 CA001103018 4 20001026 G 2562 4000 TRANSPONDER SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1B 6OO30 NE CABIN FAILED W K O NONE OTHER O OTHER NR NOT REPORTED 1 CA 406184 (CAN) DURING ANNUAL INSPECTION, THE ELT FAILED BECAUSE OF NO OUTPUT POWER. THE ELT WAS RETURNED TO THE MANUFACTURER FOR REPAIR. THIS IS THE SECOND TIME THAT THIS ELT HAS FAILED ITS ANNUAL INSPECTION DUE TO LACK OF OUTPUT POWER. IT PREVIOU SLY FAILED JUNE 2, 1999. (X) 1 G 7 1 3U 3 U H9EU E19EU 2001031400014 20010314 00014 NM 2001 3 14 CA001103019 1 20001015 G 3242 STATOR BENDIX 26010425 BOEING 737 737204 1384458 NM PWA JT8 JT8D15 52051 NE BRAKE ASSY BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA B4429 (CAN) NR 2 BRAKE FOUND DAMAGED DURING MAIN WHEEL ASSEMBLY (WORN TO LIMITS) REPLACEMENT. BROKEN PIECE FELL OUT ONTO GROUN D. REF. ATTACHED PICTURE. NR 2 BRAKE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. 2 L 7 2 4F 4 F A16WE E2EA 2000122900116 20001229 00116 EU 2000 12 29 CA001103020 1 20000517 G 2435 BRUSHES 150SG122Q SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1B 6OO30 NE STARTER GEN WORN W K NONE O OTHER IN INSP/MAINT 1 CA 5674 393 6451 (CAN) ON A ROUTINE START-UP BRUSH INSPECTION, IT WAS NOTED THAT THE BRUSHES WERE WORN. STARTER/GENERATION WAS REPLACED. THE SUBJECT STARTER WAS FOR REPAIR. INSPECTION REPORT: PREVIOUS CONDITION (06/14/99) BRUSHES WERE RUN DOWN TO RIVETS CAUSING SEVERE COMMUTATOR WEAR. DUE TO THE COMMUTATOR WEAR, THE ARMATURE WAS ON THE LAST RUN. (X) 1 G 7 1 3U 3 U H9EU E19EU 2000112900325 20001129 00325 SW 2000 11 29 CA001103021 1 20000909 G 2821 A2802 SOLENOID VALVE BELL 212 212 1181420 SW PWA PT6T PT6T3 52045 EA FUEL SUMP LEAKING W O OTHER K FLUID LOSS TX TAXI/GRND HDL 1 CA (CAN) WHILE THE FUEL SUMPS WERE BEING DRAINED IN PREPARATION FOR FLIGHT, IT WAS NOTED THAT THE LEFT FUEL SUMP WAS LEAKIN G. THE SUMP SOLENOID WAS RECYCLED AND FUEL LEAK STOPPED. WITH SIMPLEX SPRAY SYS INST FUEL DRAIN SOLENOID IS INACCESSIB LE. TH E SOLENOID DRAIN VALVE P/N A280-2 REPL. DRAIN VALVE DISASSEMBLED TO TRY AND LOCATE CAUSE FOR FUEL LEAK. UPON EXA MINING DISASSEMBLED VALVE, IT FOUND TO CONTAIN 3 PIECES OF SAND IN VALVE. SUBMITTER SUSPECTED THAT PIECE OF SAND OR OTH ER FOREIGN MATTER PREVENTED SEALING SURFACES ON VALVE FROM SEALING PROPERLY. SHOULD BE ISOLATED INCID. AT THIS PARTICUL AR OPERATION. IF, UPON CONDUCTING SUMP DRAIN, FUEL CONTINUES TO LEAK, RECYCLE DRAIN SOLENOID. (X) 1 G 7 1 4U 4 U H4SW E22EA 2000120700197 20001207 00197 SW 2000 12 7 CA001106002 1 20001012 G 2420 LW13039 BRACKET BBAVIA 8 8GCBC 1220803 SW LYC O360 O360C2E 41514 EA MIDDLE FAILED W K NONE B H SMOKE/FUMES/ODORS/SPARKS ELECT. POWER LOSS-50 PC LD LANDING 1 CA 2431 (CAN) IN-FLIGHT FAILURE OF REAR HALF OF BRACKET CAUSING ALTERNATOR FORWARD MOUNT TO BREAK. PILOT NOTICED BURNING SMELL IN COCKPIT FROM ALTERNATOR BELT AND UPON LANDING, INVESTIGATED AND FOUND ALTERNATOR HANGING ONLY BY THE WIRES AND SUPPOR T OF 1 SCAT HOSE. (X) 1 H 7 1 3O 3 O A21CE E286 2001032600243 20010326 00243 CE 2001 3 26 CA001106003 1 20001023 G 5553 04310093 FITTING CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA MCAULY 1A103 1A103TCM GL VERTICAL STAB CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 21318 (CAN) CRACK FOUND IN BRACKET THAT ATTACHES VERTICAL FIN TO FUSELAGE, AT THE REAR ATTACH POINT. 1 H 7 1 3O 3 O NT 3A19 E223 5 N P50GL 2000120700198 20001207 00198 GL 2000 12 7 CA001106006 2 20001020 G 7250 6898782 BLADE ALLSN 250C 250C20B 03013 GL 2ND ST BLADE RT MISSING W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA 1644 HX119758 (CAN) N1 AND N2 SYSTEMS ABLE TO ROTATE PRIOR TO DISMANTLING, TURBINE FULLY DISMANTLED. NO EVIDENCE OF FOD UPSTREAM OF 2 ND STAGE TURBINE WHEEL. HEAVY D.O.D. DOWNSTREAM OF 2ND WHEEL. 2ND TURBINE WHEEL MISSING ONE TURBINE BLADE. QTY SIX BL ADES APPROX. 180 INCHES AWAY EXHIBIT DAMAGE ON THE TRAILING EDGES. THE NR 8 STATIONARY LAB SEAL IS BROKEN IN TWO PIECES , HOWEVER, BEARING LOCATION IS ONLY MINIMALLY EFFECTED. GP FORWARD ROTATING LAB SEAL BROKEN, PART OF SEAL HAS NOT BEEN LOCATED. 1ST AND 2ND BLADE PATHS EXHIBIT SUBSTANTIAL TIP RUB INDICATIONS. ALL OIL NOZZLES, SHAFTS, SUPPORTS AND BEARIN GS ARE IN NORMAL CONDITION. (X) 3 U E4CE 2000112900326 20001129 00326 SW 2000 11 29 CA001106007 1 20001020 G 6520 206030446001F MOUNT BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL T/R GEARBOX FAILED W K NONE P NO WARNING INDICATION NR NOT REPORTED 1 CA (CAN) CRACK RADIATING ACROSS REAR PORT SIDE ATTACHMENT HOLE FOR THE TAIL ROTOR GEARBOX STUDS. (X) 1 G 7 1 3U 3 U H2SW E4CE 2001032600245 20010326 00245 NM 2001 3 26 CA001106009 1 20000303 G 2910 82920010363 LINE DHAV DHC8 DHC8* NM PWA PW120 PW123 NE HYD PUMP FRACTURED W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CL CLIMB 1 CA 4532 (CAN) CLIMBING THOUGH FL80 FROM COPENHAGEN, 1ST OFFICER REPORTED LOSS OF NR 2 HYDRAULIC SYSTEM CONTENTS. AIRCRAFT RETU RNED TO COPENHAGEN, CARRYING OUT ACTION IAW EMERGENCY CHECKLIST NR 2 HYDRAULIC SYSTEM FLUID LOSS. AIRCRAFT STATICS: TOTA L HOURS 4532.10 TOTAL CYCLES 4601REF/ASR050/00/DH8 ENGINE INSPECTION FOUND HYDRAULIC PRESSURE LINE FRACTURED, PIPE ASSE MBLY REPLACED AND LEAK CHECK CARRIED OUT SATISFACTORY. DURING ENGINE RUN, HYDRAULIC NR 2 SYSTEM DEPLETED AND ILLUMINATIO N OF CAUTION LIGHTS & NR 2 SPU CCT BKR POPPED, MAINTENANCE FOUND LEAK FROM NR 2 SPU CASE DRAINCASE, SPU REPLACED & NR 2 CASE DRAIN FILTER REPLACED & NR 2 ENGINE DRIVEN PUMP REPLACED IAW DHC-8 AMM 5-50-33 DUE 2 H 7 2 4T 4 T RT A13NM E20NE 2001031400015 20010314 00015 NM 2001 3 14 CA001106010 1 20000312 G 5260 85210276101 BOLT DHAV 85210001001 DHAV DHC8 DHC8301 NM PWA PW120 PW123 NE AIRSTAIRS LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA 19202 (CAN) THE FOLLOWING WAS REPORTED TO US (FROM BRYMON MAINTENANCE CONTROL): AFTER LANDING IN ABERDEEN THE NR 1 CABIN ATTE NDANT WAS UNABLE TO OPEN PASSENGER AIRSTAIR DOOR. ENGINEERS WERE CALLED TO ASSIST WITH OPENING THE DOOR USING THE EXTERN AL MECHANISM.AIRCRAFT STATISTICS: TOTAL HOURS: 19202.35 TOTAL CYCLES: 20379 REF ASR - 057/00/DH8. UPON INSPECTION: BRY MON ENGINEERS FOUND A THREADED INSERT HAD WORKED LOOSE FROM THE BOLT AND INTERFERED WITH THE DOOR LINKAGE. THE BOLT AND THREADED INSERT WERE REPLACED WITH NEW ITEMS AND AIRCRAFT RETURNED TO SERVICE. 2 H 7 2 4T 4 T RT A13NM E20NE 2001031400017 20010314 00017 NM 2001 3 14 CA001106013 1 20001018 G 5610 8SC0043005 WINDSHIELD DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE COCKPIT FAILED W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA 4120 (CAN) WHILE IN CRUISE AT 18,000 FT PILOTS FORWARD WINDSHIELD SHATTERED. NO BIRD OR F.O.D. REPORTED. ABNORMAL PROCEDURES CARRIED OUT. AIRCRAFT DESCENT TO STAY CLEAR OF ICING. CABIN PRESSURIZATION 3.0 LBS MAX & 150 IAS AS PER CHECKLIST. NORMA L LANDING C/O NO FURTHER COMPLICATIONS. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001030600003 20010306 00003 EA 2001 3 6 CA001106015 1 20001025 G 2711 C2CF451ND ROD DHAV DHC2 DHC2MK1 2800102 EA PWA R985 R985AN14B 52008 NE LT AILERON WRONG PART W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) UPON INSPECTION, THE LT AILERON PUSH ROD WAS FOUND TO BE NOTICEABLY HEAVIER THAN THE OTHER. THE TUBE WAS CHECKED W ITH A MAGNET AND FOUND TO BE STEEL. NO RECORD CAN BE FOUND OF STEEL PUSH RODS BEING APPROVED FOR DHC-2 BEAVER AIRCRAFT - SUSPECT BOGUS PART. THE TUBE SECTION WAS REPLACED WITH AN APPROVED COMPONENT. 1 H 7 1 3R 3 R A806 5E1 2001032600004 20010326 00004 EA 2001 3 26 CA001106016 1 20001031 G 5341 C3FS145 BUSHING DHAV DHC3 DHAV DHC3 DHC3 2800202 EA PWA PT6 PT6A34 52043 EA TIE BAR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 172 (CAN) DURING AD CF-82-26R1, FOUND THAT TIE BAR BUSHINGS WERE NOT OF NORMAL TYPE PER PARTS MANUAL. TIE BAR BUSHINGS WERE REMVD&VISUAL&DYE CHECK INSP CARRIED OUT ON END FITTING. DURING NDT INSPE CTION, IND.S WERE THAT CRACK RADIATING FROM BU SHING HOLE ON TOP INBOARD EDGE. FOR PURPOSES, OF FURTHER INSP, SURFACE MATERIAL REMVD TO MIN THICKNESS OF TIE BAR LUG. F LUORESCENT PENETRANT INSPECTION CARRIED OUT AGAIN, & CRACK IND. 1 H 7 1 3R 4 T A815 E4EA 2001031400019 20010314 00019 EU 2001 3 14 CA001106018 1 20001027 G 3297 9717510230 WIRE 9603001102 PILATS PC12 PC1245 7090551 EU MLG ACTUATOR CORRODED W A UNSCHED LANDING N FALSE WARNING LD LANDING 1 CA 2792 0163 (CAN) UPON LOWRING OF LANDING GEAR FLT CREW RPTED THEY HAD NO R/H GREEN DOWN &LOCKED GEAR IND.. FLT CREW NOTIFIED ATC&UN EVENTFUL PRECAUTIONARY LDG CARRIED OUT. A/C TOWED OFF RWY & MAINT CREWS INVESTIGATED THE FALSE IND.. PLUG PG 057 REMVD FROM RT MLG ACTUATOR DOWN IND. SWITCH, (SW IS INTERNAL IN ACTUATOR)&JUMPER PLACED TO SIMULATE SW OPEARTION. PROVIDED GRE EN IND. TO COCKPIT SO ACTUATOR (MISTA KENLY) CONSIDERED AS HAVING FAULTY IND. MICRO SWITCH,&REPL. SEVERAL GEAR SWINGS WE RE CARRIED OUT WITH NORMAL IND.S&A/C RT-SRV. A/C DEPARTED TO ITS NEXT DESTINATION&AGAIN FAILED TO HAVE R/HGEAR DOWN&LOCK ED INDICTION UPON LOWERING OF 1 L 7 1 3T RT A78EU 2001032600011 20010326 00011 CE 2001 3 26 CA001106020 1 20001024 G 2820 AN9176D FITTING CESSNA 185 A185F 2072821 CE CONT O520 IO520D 17032 SO MCAULY 2A34C D2A34C58 GL FUEL LINE CRACKED W O OTHER B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 CA 1600 (CAN) THERE WAS A STRONG SMELL OF FUEL WHEN THE AIRCRAFT WAS PARKED AND DOOR OPENED.A CHECK OF THE COMPLETE FUEL SYSTEM, FOUND UNDER CABIN FLOOR. LEFT SIDE WHERE FRONT AND REARFUEL TANK LINES ARE CONNECTED, TEE FITTING WAS LEAKING. UPON REM OVAL ATHE TEE FITTING P/N AN917-6D IT WAS FOUND TO BE CRACKED. 1 H 7 1 3O 3 O 3A24 E5CE 5 C P3EA 2001031400024 20010314 00024 NM 2001 3 14 CA001107005 1 20001031 G 2620 453N260220 TUBE BOEING 757 75728A 1384976 NM RROYCE RB211 RB211535E437 54555 NE EXTINGUISHER WORN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING C-CHECK INSPECTION, FOUND CARGO FIRE EXTINGUISHING TUBE RUBBED THROUGH BY CONTACTING APU BLEED AIR DUCT. CA USE OF PROBLEM IS THE APU DUCT VIBRATION WITH CLOSE TOLERANCE. FIX IS INCORPORATION OF SB 57-26A0040. 2 L 7 2 4F 4 F RT A2NM E12EU 2001031400025 20010314 00025 EA 2001 3 14 CA001107006 1 20001013 G 7830 22850741115 SWITCH GE CF343A1 CNDAIR CL600 CL600* EA GE CF34 CF343A1 30015 NE THRUST REVERSER INTERMITTENT W E ENGINE SHUTDOWN H ELECT. POWER LOSS-50 PC CR CRUISE 1 CA 4066 (CAN) AIRCRAFT DEPARTED FARNBOROUGH EN ROUTE TO BEIRUT. CLIMBING THROUGH 45,000 FEET AT 220 KNOTS, THE RT AMBER REVERSE R UNLOCK CAPTION ILLUMINATED. CHECK LISTS FOLLOWED, EMERGENCY STOW WAS SELECTED. ENGINE WAS SHUT DOWN AND AIRCRAFT DIVER TED TO STANSTED AIRPORT. FURTHER TROUBLESHOOTING REVEALED THAT THE STOW SWITCH FROM THE RT THRUST REVERSER WAS FOUND INT ERMITTENT. 2 L 7 2 4F 4 F RT A21EA E15NE 2001031400026 20010314 00026 NE 2001 3 14 CA001107008 2 20001029 G 7321 6078T55P20 FUEL CONTROL CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE NR 2 ENGINE MALFUNCTIONED W A E UNSCHED LANDING ENGINE SHUTDOWN M OVER TEMP CR CRUISE 1 CA (CAN) DURING CRUISE, NR 2 ENGINE N2 NOTED DROPPING TOWARDS ZERO AND ITT RAPIDLY INCREASING INTO THE RED.FAULTY MFC CONFI RMED DURING GROUND RUN. MFC REPLACED AND A SUCCESSFUL GROUND RUN FOLLOWED. 2 L 7 2 4F 4 F RT A21EA E15NE 2001031400027 20010314 00027 NE 2001 3 14 CA001107009 2 20001029 G 7230 COMPRESSOR GE CF343A1 CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE ENGINE DAMAGED W A E UNSCHED LANDING ENGINE SHUTDOWN E VIBRATION/BUFFET CL CLIMB 1 CA 807499 (CAN) CREW REPORTED NR 1 ENGINE VIBRATION AFTER TAKEOFF FOLLOWED BY UNCOMMANDED ENGINE STOPPAGE.BOROSCOPE INSPECTION REV EALED EXTENSIVE COMPRESSOR DAMAGE. 2 L 7 2 4F 4 F RT A21EA E15NE 2000112900327 20001129 00327 EU 2000 11 29 CA001107011 1 20001026 G 6220 704A3363320851 MAIN ROTOR 350A31000001 SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1B 6OO30 NE STARFLEX END DELAMINATED W K NONE O OTHER NR NOT REPORTED 1 CA 718 M375 (CAN) DELAMINATION DETECTED WITH REFERENCE TO EUROCOPTER AS350 MAINTENANCE WORK CARD 62.20.00.601 PARAGRAPH 4.3 (ILLUSTR ATION FIGURE 5, DETAIL A, LOCATION ON PART AT DETAIL N). PENETRATION WITH A 010 INCH FEELER GAUGE TO A DEPTH OF APPROX IMATELY .75 INCH DETECTED BETWEEN ATTACHMENT BLOCK TO STARFLEX AND LAMINATED COMPONENT. TOLERANCE EXCEED PRESCRIBED LIM ITS. (P=.45 INCH APPROXIMATELY, L=1.0 INCH APPROXIMATELY). PART HAS A 6,400 HOUR SERVICE LIFE LIMIT. DEFECT OCCURRED AT 718 HOURS IN SERVICE. (X) 1 G 7 1 3U 3 U NC H9EU E19EU 2001031400028 20010314 00028 NE 2001 3 14 CA001107012 2 20001107 G 8530 404473 ROCKER CNDAIR CL215 CL2151A10 EA PWA R2800 CA3 52026 NE CAP BROKEN W O OTHER K E FLUID LOSS VIBRATION/BUFFET CR CRUISE 1 CA 951 (CAN) AIRCREW REPORTED LT ENGINE ROUGH RUNNING AND OIL LEAK UPON INVESTIGATION EXHAUST ROCKER CAP FOUND BROKEN. BOTH ROC KER ARM ADJUSTERS INTAKE AND EXHAUST WERE BACKED ALL WAY OUT. AT NUMBER 8 CYLINDER. 2 H 7 2 4R 4 R A14EA E231 2001031400029 20010314 00029 NM 2001 3 14 CA001107015 1 20001007 G 3411 PITOT LINE BOEING 737 737201 1384454 NM PWA JT8 JT8D9A 52048 NE AIRSPEED IND LOOSE W K NONE J WARNING INDICATION TO TAKEOFF 1 CA (CAN) LOSS OF CAPTAINS AIRSPEED INDICATOR DURING TAKEOFF. FOUND PITOT LINE LOOSE. PITOT LINE TIGHTENED. SYSTEM LEAK CHEC KED AND TESTED AS PER M.M. 34-11-0. 2 L 7 2 4F 4 F A16WE E2EA 2000120400200 20001204 00200 SO 2000 12 4 CA001107016 1 20001024 G 3250 AN3H10A BOLT PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA BOOT SHEARED W K NONE O OTHER TX TAXI/GRND HDL 1 CA (CAN) WHILE TAXIING ON THE GROUND, THE PILOT NOTICED THERE WAS NO CONTROL OF THE NOSE WHEEL. AFTER CHECKING THE 3 BOLTS , AN3H-10A WERE FOUND SHEARED OFF. THE BOLTS WERE REPLACED AND PROPERLY TORQUED AND LOCKED PER MAINTENANCE MANUAL. (X) 1 L 7 2 3O 3 O A20SO E14EA 2001032600014 20010326 00014 GL 2001 3 26 CA001107017 1 20001016 G 2701 83450712 SWITCH GC41511003 BOMBDR BD700 BD7001A10 1390006 GL CONTROL YOKE SHORTED W K NONE N FALSE WARNING IN INSP/MAINT 1 CA 0047 (CAN) INTERMITTENT TCS ADVISORY (AMBER) POSTED ON PILOTS FLIGHT DIRECTOR DURING PREFLIGHT INSPECTION. FOUND BOLT (P/N NA S6203-40, ATA 27-11-01) HAD PENETRATED WIRING HARNESS TO THE PILOTS BUTTON AND SWITCH CONTROLS IN THE STEERING YOKE. SPE CIFICALLY THE TCS BUTTON (TOUCH CONTROL STEEING, ATA 22-11-05). ON REMOVAL OF THE HARNESS FROM THE COLUMN, IT WAS FOUND THAT ONE ADDITIONAL WIRE HAD BEEN DAMAGED. IN BOTH CASES THE INSULATION HAD BEEN STRIPPED OFF ABOUT 1/4. 2 L 7 2 4F RT T00003NY 2000120400201 20001204 00201 SO 2000 12 4 CA001107018 2 20001019 G 7414 ROTOR SHAFT SLICK 4309 DIAMON DA20 DA20C1 2990001 GL CONT O240 IO240B 17063 SO MAGNET & SEAL SHEARED W D RETURN TO BLOCK O OTHER IN INSP/MAINT 1 CA 400 99040600 (CAN) PLANE HAD BEEN SNAGGED FOR A 200 RPM DROP ON RT MAGNETO. MAGNETO WAS PULLED FOR INSPECTION, FOUND THE ROTOR SHAFT TO BE SHEARED. A NEW MAGNETO HAS BEEN RE-INSTALLED. (X) 1 L 7 1 3O 3 O NT TA4CH E7SO 2000120400202 20001204 00202 SO 2000 12 4 CA001107019 1 20001018 G 3710 441CC7 COUPLING AIRBORNE RAPCD441CC7 PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2B 41532 EA RT ENGINE SHEARED W O OTHER O OTHER CR CRUISE 1 CA 678 81089 (CAN) AIRCRAFT ON FLIGHT FROM RIMOUSKI TO HALIFAX. AT ARRIVAL, PILOT ADVISED HIS AMO THAT RT VACUUM PUMP INDICATED 0 AT SHUT DOWN PROCEDURE. AMO ARRANGED FOR PUMP REPLACEMENT AT HALIFAX. NOTE: USUAL FAILURE: SHEARED DRIVE. (X) 1 L 7 2 3O 3 O A20SO E14EA 2000112900330 20001129 00330 EU 2000 11 29 CA001107020 1 20001020 G 5532 STABILIZER VECTOR 350A14002008 SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1B 6OO30 NE L/E LWR SECTION CRACKED W K NONE O OTHER NR NOT REPORTED 1 CA 3633 TB2968 (CAN) CRACK FOUND ON UPPER VERTICAL FIN LOWER SECTION OF LEADING EDGE BETWEEN TWO RIVETS, 2.6250 INCHES ABOVE STAMPED FI TTING, 2.50 INCHES, LENGTH OF CRACK. (X) 1 G 7 1 3U 3 U H9EU E19EU 2001031400030 20010314 00030 NM 2001 3 14 CA001107021 1 20001017 G 5610 65528038 CONTROLLER BOEING 737 737296 1384486 NM PWA JT8 JT8D9 52048 NE WINDOW HEAT FAILED W O OTHER B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 CA 17525 (CAN) CAPTAINS NR 2 SLIDING WINDOW - EXTERIOR PANE SHATTERED ON CLIMB OUT. WINDOW HEAT SHORTED RESULTING IN SPARKS AND S MOKE FROM ARCING.WINDOW AND CONTROLLER REPLACED. TEARDOWN REPORT CONFIRMED THE WINDOW HEAT CONTROL FAILED. 2 L 7 2 4F 4 F RT A16WE E2EA 2000120400203 20001204 00203 EA 2000 12 4 CA001108002 2 20001024 G 7414 1068255514 MAGNETO LYC CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA MCAULY 1C160 1C160DTM GL POINTS FAILED W O OTHER O OTHER CR CRUISE 1 CA 185 L75776 (CAN) ENGINE STARTED TO RUN ROUGH IN FLIGHT AND THEN QUIT. AIRCRAFT FORCED TO DO EMERG LANDING. PRIOR TO INCIDENT, 4.1 HRS EARLIER, RIGHT MAG ROUGH AND DROPPING BELOW LIMITS ON STATIC RUN. MAG REMOVED INTERNAL TIMING SET, REINSTALLED. PO INT GAP PRIOR TO RE-TIMING FOUND CLOSER THAN NORMAL. JUST ATTRIBUTED TO POINTS WEARING IN. AFTER FORCED LANDING, MAG RE MOVED, POINTS CHECKED, NO POINT GAP NOTED. POINTS WERE TIGHT, WERE NOT MOVABLE, HAD NOT MOVED SINCE INTERNAL TIMING HA D BEEN CARRIED OUT. POINTS REMOVED, APPEARED PLASTIC CAM FOLLOWER MELTED, CAM FOLLOWER WORN DOWN TO APPROX. 1/2 OF NEW SET. CAM FOLLOWER APPEARED TO HAVE GOTTEN HOT. CONDENSORS, MAG HAVE BEEN SENT FOR FURTHER INVESTIGATION. (X) 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2000120400204 20001204 00204 SO 2000 12 4 CA001108003 1 20001030 G 2730 40060 CHANNEL PIPER 5423224 PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA BETWEEN RIBS CRACKED W O OTHER O OTHER IN INSP/MAINT 1 CA 12856 31176 (CAN) CRACKS FOUND WHEN TEARING DOWN ELEVATOR TO PERFORM INSTALLATION OF KIT 766-642 PER SB 1008 - BUTT RIB REPLACEMENT . SB 998A RELACEMENT OF SPAR ALSO CARRIED OUT TO COMPLY WITH AD 99-12-05. NOTE: NEW CHANNEL COMES IN KIT 766-642. T HESE CRACKS COULD NOT HAVE BEEN DETECTED IN SB 998A AND SB 1008 INSPECTION PROCEDURE AS CHANNEL IS CLOSED IN. SUBMITTER STATED TO SEE THAT AREA, AN INSPECTION HOLE AND BLANKING PLUG WOULD BE REQUIRED SUCH AS IN SB 998A, BUT LOCATED SOMEWHE RE BETWEEN THE RIBS AS ABOVE AND REAR OF THE CHANNEL. (X) 1 L 7 2 3O 3 O A20SO E14EA 2000112900331 20001129 00331 NE 2000 11 29 CA001108008 1 20001022 G 6310 7636109103104 SHAFT SKRSKY SKRSKY S76 S76A 8143006 NE ALLSN 250C 250C30S 03013 GL OUTPUT SHAFT SHEARED W K NONE O P OTHER NO WARNING INDICATION NR NOT REPORTED 1 CA A06700640 (CAN) POWER OUTPUT SHAFT FOUND SHEARED AT THE THREADED END WHEN ENGINE WAS REMOVED FOR SCHEDULED MAINTENANCE. POSSIBLE CAUSE IS ENGINE DRIVESHAFT MISALIGNMENT - NEW SHAFT WAS INSTALLED ON ENGINE AND SHAFT ALIGNMENT CARRIED OUT ON REINSTALL ATION OF ENGINE. (X) 1 G 7 2 3U 3 U H1NE E1GL 2000112900332 20001129 00332 GL 2000 11 29 CA001108009 2 20001025 G 7314 6896810 PUMP SKRSKY S76 S76A 8143006 NE ALLSN 250C 250C30S 03013 GL FUEL PUMP WORN W O OTHER O OTHER CR CRUISE 1 CA 2549 CAE890189S (CAN) NR 2 ENGINE DECELLED IN-FLIGHT. INLET FUEL LINE TO FUEL PUMP (P/N 76307-02003-083) HAD WORN A GROOVE ON FUEL PUMP UNION (P/N AN919-19D). THIS ALLOWED AIR INTO THE FUEL SUPPLY SYSTEM. FUEL PUMP P/N 6896810 REPLACED. AN919-10D UNION REPLACED. ENGINE GROUND RUN AND FLIGHT TESTED, SERVICEABLE. AIRCRAFT RETURNED TO SERVICE. (X) 1 G 7 2 3U 3 U H1NE E1GL 2000112900333 20001129 00333 NE 2000 11 29 CA001108010 1 20001026 G 5320 7620202003126 POST SKRSKY SKRSKY S76 S76A 8143006 NE TMECA ARRIEL ARRIEL1S1 60030 NE STA 215 CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 10194 760015 (CAN) CHANNEL (POST) CRACKED AT BAGGAGE FLOOR LEVEL. STATION 215 AND BL ZERO REPAIR CENTERLINE POST IAW SRM 53-10-03 PA GE 219, 30 NOV. 1998 AVAILABLE FOR REPAIR. (X) 1 G 7 2 3U 3 U H1NE E19EU 2000112900334 20001129 00334 NE 2000 11 29 CA001108011 1 20001026 G 6230 7610408500041 BEARING SKRSKY S76 S76A 8143006 NE TMECA ARRIEL ARRIEL1S1 60030 NE SWASHPLATE CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA A2300027 (CAN) UPON PURCHASE AND DISASSEMBLY OF THIS HELICOPTER, THE SWASHPLATE BEARING SHOWED SIGNS OF CORROSION AND LACK OF GRE ASE. THE SWASHPLATE DRIVE LINK LUG ALSO SHOWED SIGNS OF CORROSION. (X) 1 G 7 2 3U 3 U H1NE E19EU 2001010900001 20010109 00001 EA 2001 1 9 CA001109004 1 20001026 G 2910 FITTING DHAV DHC7 DHC7102 2802708 EA PWA PT6 PT6A50 52043 EA HAMSTD 24PF 24PF305 GL HYD LINE BROKEN W O OTHER K J FLUID LOSS WARNING INDICATION CL CLIMB 1 CA 31593 (CAN) DURING CLIMB NR 2 HYDRAULIC PUMP CAUTION LIGHT ILLUMINTED, SYSTEM PRESSURE AND QUANTITY DROPPED TO ZERO. NR 1 HYDR AULIC PUMP THEN FAILED SHORTLY AFTER. MAINTENANCE DISCOVERED AN ALUMINUM HYDRAULIC LINE BROKEN AT THE FLARED FITTING. T HIS LINE IS LOCATED AFT OF THE ENGINE FIRE WALL IN THE NR 2 NACELLE. NR 1 & NR 2 HYDRAULIC PUMP & FILTERS REPLACED. THE SYSTEM BLED AND LEAK CHECKED AND THE AIRCRAFT RETURNED TO SERVICE. 2 H 7 4 4T 4 T A20EA E4EA 6 C P1NE 2001031400032 20010314 00032 NM 2001 3 14 CA001109008 1 20001101 G 3211 69186803 BOLT BOEING 727 727217 NM PWA JT8 JT8D17 52049 NE MLG FITTING CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 1393 (CAN) DURING DISASSEMBLY OF RT MAIN LANDING GEAR OLEO TO CARRY OUT OLEO SEAL REPLACEMENT DUE STRUT LEAKING, IT WAS FOUND THAT THE RT MAIN LANDING GEAR UPPER SIDE STRUT UNIVERSAL FITTING ATTACH BOLT HEAD WAS CRACKED. RT UPPER SIDE STRUT UNIV ERSAL FITTING ATTACH BOLT REPLACED WITH NEW BOLT, GEAR SWING CARRIED OUT CHECKS SERVICEABLE PER M/M 32-11-41. NOTE AFTER REVIEW OF THE BOLT IT WAS OBSERVED THAT THE BOLT IS CORRODED UNDER THE HEAD AS THE HEAD CAME OFF WHILE BEING REMOVED. U NSERVICEABLE BOLT IS NOW IN OUR QUARANTINE AWAITING DISPOSITION. 2 L 7 3 4F 4 F RT A3WE E2EA 2001032700009 20010327 00009 SO 2001 3 27 CA001110002 1 20001023 G 3710 442CW SPLINE ADAPTER PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA RT ENGINE SHEARED W O OTHER J WARNING INDICATION CR CRUISE 1 CA 808 (CAN) PNEUMATIC PUMP WARNING CAME ON IN CRUISE ON RETURN FLIGHT TO BASE (CARGO FLIGHT). REPLACED PUMP, USUAL DRY AIR PUMP FAILURE. 1 L 7 2 3O 3 O A20SO E14EA 2000120400205 20001204 00205 EA 2000 12 4 CA001110003 2 20001018 G 7314 02480010402 PUMP BEECH 90 C90 1152913 CE PWA PT6 PT6A20 52043 EA FUEL PUMP FAILED W O OTHER O OTHER IN INSP/MAINT 1 CA 3617 1689 (CAN) FUEL PUMP FAILED. (X) 1 L 7 2 3T 3 T 3A20 E4EA 2001032700010 20010327 00010 EA 2001 3 27 CA001110004 2 20001101 G 7414 1068291018 MAGNETO PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA ENGINE FAILED W O OTHER R Y PARTIAL RPM/PWR LOSS ENGINE STOPPAGE NR NOT REPORTED 1 CA 119 (CAN) PILOT REPORTED HE HAD MAG DROP AT END OF LEG. OK AT RESTART AND AGAIN BAD AT ARRIVAL. RETURN LEG SHOWED HI-EGT A ND HI-CHT. CHECKED MAGNETO TIMING FIRING AT TDC INSTEAD OF 20 DEGREES BDC. ATTEMPTED RE TIMING TO 20 DEGREES IN VAIN. CONCLUSION: INTERNAL WEAR AND SLIPPAGE. 1 L 7 2 3O 3 O A20SO E14EA 2001032700011 20010327 00011 NM 2001 3 27 CA001110007 1 20001023 G 5730 149T17500159 PANEL BOEING 767 767233 NM PWA JT9 JT9D7R4D 52054 NE FUSELAGE MISSING W O OTHER D INFLIGHT SEPARATION NR NOT REPORTED 1 CA (CAN) ON AIRCRAFT ARRIVAL FOUND PANEL MISSING ON LEFT HAND WING ROOT TO FUSELAGE. PANEL 195CL INSTALLED NEW ANCHOR NUTS AND PANEL. 2 L 7 2 4F 4 F RT A1NM E3NE 2001032700013 20010327 00013 NM 2001 3 27 CA001110009 1 20001023 G 2913 MPN6294502 MOTOR BOEING 767 767233 NM PWA JT9 JT9D7R4D 52054 NE HYD PUMP FAILED W O OTHER J WARNING INDICATION AP APPROACH 1 CA (CAN) ON APPROACH TO TORONTO, CENTRE HYDRAULIC LOSS. EXTENDED THE GEARS MANUALLY, AIRCRAFT LANDED WITHOUT FURTHER INCIDE NT. HYDRAULIC FILTERS, AC MOTOR HYDRAULIC PUMP DRIVE, AND AIR DRIVEN PUMP UNIT WERE CHANGED. OPERATION CHECK CARRIED OUT , NORMAL. 2 L 7 2 4F 4 F RT A1NM E3NE 2001032700014 20010327 00014 NM 2001 3 27 CA001110013 1 20001014 G 7722 285N002821 CARD BOEING 767 767233 NM PWA JT9 JT9D7R4D 52054 NE RT ENGINE FAULTY W E A ENGINE SHUTDOWN UNSCHED LANDING N FALSE WARNING NR NOT REPORTED 1 CA (CAN) RIGHT HAND ENGINE OVERHEAT ON ENGINE CREW ALERT SYSTEM, AND MASTER CAUTION CAME ON ON CLIMB OUT. ENGINE SHUT DOWN AND DIVERTED INTO WINNIPEG. FOUND RIGHT HAND ENGINE LOGIC CARD M10274 AT FAULT. REPLACED M10274 CARD. 2 L 7 2 4F 4 F RT A1NM E3NE 2001032700017 20010327 00017 WP 2001 3 27 CA001110016 1 20001009 G 5610 5613217519 WINDOW DOUG DC9 DC932 3022066 WP PWA JT8 JT8D7 52053 NE COCKPIT DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CREW REPORTED SMALL HOLE 1/4 - 1/2 INCH IN COCKPIT LEFT HAND SLIDING WINDOW.CHANGED LEFT HAND COCKPIT WINDOW. 2 L 7 2 4F 4 F A6WE E2EA 2001032700018 20010327 00018 NM 2001 3 27 CA001110018 1 20001010 G 3350 LIGHT BOEING 747 747433 NM PWA 4056 PW4056 NE CABIN FAILED W K NONE L NO TEST IN INSP/MAINT 1 CA (CAN) NUMEROUS EMERGENCY LIGHTS OUT ON AIRCRAFT FLOOR PATH LIGHTING. LIGHTS REPAIRED AT R1 DOOR, ISLES R3 AND UPPER DECK LIGHT SYSTEM CHECKED SERVICEABLE. 2 L 7 4 4F 4 F RT A20WE E24NE 2001031400041 20010314 00041 EA 2001 3 14 CA001110026 1 20001101 G 5610 NP1393215 WINDSHIELD CNDAIR CL600 CL6002B19 EA COCKPIT FAILED W O OTHER O OTHER NR NOT REPORTED 1 CA 420 (CAN) CREW REPORTED THAT AFTER LANDING THE PILOTS WINDSHIELD SHATTERED, AIRCRAFT TAXIED TO THE GATE. ASA DISPATCHED MAIN TENANCE PERSONNEL FROM ATL ALONG WITH A WINDSHIELD TO CARRY OUT REPAIRS.THE WINDSHIELD WAS REPLACED AND THE AIRCRAFT RET URNED INTO SERVICE. 2 L 7 2 4F RT A21EA 2001031400042 20010314 00042 EA 2001 3 14 CA001110028 1 20001101 G 2611 473052 SMOKE DETECTOR CNDAIR CL600 CL6002B19 EA CARGO BAY FAILED W A UNSCHED LANDING N FALSE WARNING CR CRUISE 1 CA (CAN) CARGO SMOKE WARNING CAME ON DURING CRUISE FLIGHT. CREW FOLLOWED QRH. BOTH EXTINGUISHER BOTTLES BLOWN. MESSAGE REMA INED. DECLARED AN EMERGENCY AND LANDED WITHOUT INCIDENT, RETURNING TO CVG. R&R THE CARGO SMOKE DETECTOR BOXES. 2 L 7 2 4F RT A21EA 2001031400043 20010314 00043 EA 2001 3 14 CA001110029 1 20001101 G 5610 NP1393225 WINDOW CNDAIR CL600 CL6002B19 EA COCKPIT FAILED W A UNSCHED LANDING O OTHER CL CLIMB 1 CA 1220 (CAN) AFTER TAKEOFF FROM DES MOINES, IOWA CREW REPORTED THAT THE PILOTS SIDE WINDOW SHATTERED, NO LOSS OF PRESSURIZATION . AIRCRAFT RETURNED TO DES MOINES, AND COMPLETED AN UNEVENTFUL LANDING. ASA DISPATCHED MAINTENANCE PERSONNEL TO REPLACE THE WINDOW. 2 L 7 2 4F RT A21EA 2001032700020 20010327 00020 EA 2001 3 27 CA001110031 1 20001102 G 7600 5071T98P03 AMPLIFIER CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE NR 1 ENGINE FAILED W O OTHER J WARNING INDICATION CL CLIMB 1 CA (CAN) FLT 4627, AFTER SETTING CLIMB THRUST THE LT ENGINE ACCELERATED TO OVER 101 PERCENT. THE POWER LEVER WAS RETARDED AND THE ENGINE (N1) THEN LATER DROPPED BY 6 PERCENT UNCOMMANDED. REMOVE AND REPLACE NR 1 ENGINE N1 CONTROL AMPLIFIER. PE RFORMED FUNCTIONAL CHECK IAW CRJ POWER PLANT GROUND RUN MANUAL 77-00-00. OPS CHECK GOOD. 2 L 7 2 4F 4 F RT A21EA E15NE 2001032700021 20010327 00021 EA 2001 3 27 CA001110032 1 20001102 G 2400 RELAY CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE WARNING SYSTEM FAILED W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA (CAN) APR INOP CAUTION MESSAGE ON TAKEOFF ROLL, ABORTED TAKEOFF. REMOVED AND REPLACED APR ARM RELAY (K1KL) IN JB-5. OPS CHECKED, SYSTEM NORMAL. 2 L 7 2 4F 4 F RT A21EA E15NE 2001031400044 20010314 00044 EA 2001 3 14 CA001110033 1 20001102 G 3234 601R510087 HANDLE CNDAIR CL600 CL6002B19 EA MLG BROKEN W O OTHER O OTHER AP APPROACH 1 CA (CAN) CREW REPORTED THAT DURING SELECTION OF THE LANDING GEAR TO THE DOWN POSITION, THE LANDING GEAR SELECTOR HANDLE BRO KE. THE LANDING GEAR DID EXTEND TO A DOWN AND LOCKED POSITION AND THE AIRCRAFT LANDED WITHOUT INCIDENT. REMOVED, REPLACE D AND TESTED THE LANDING GEAR HANDLE PANEL ASSY IAW AMM. AIRCRAFT BACK IN SERVICE. 2 L 7 2 4F RT A21EA 2001031400045 20010314 00045 NE 2001 3 14 CA001110034 2 20001102 G 7230 6078T27G01 COMPRESSOR CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE NR 1 ENGINE DAMAGED W A UNSCHED LANDING E X J VIBRATION/BUFFET ENGINE FLAMEOUT WARNING INDICATION CL CLIMB 1 CA 7243 7243 (CAN) CREW REPORTED NR 1 ENGINE VIBRATION AFTER TAKEOFF FOLLOWED BY AN UNCOMMANDED ENGINE STOPPAGE. MAINTENANCE REPORTED THAT A BORESCOPE INSPECTION REVEALED EXTENSIVE COMPRESSOR DAMAGE. 2000-11-14TC: 2 L 7 2 4F 4 F RT A21EA E15NE 2001031400046 20010314 00046 EA 2001 3 14 CA001110035 1 20001102 G 2130 21197646 CONTROL PANEL CNDAIR CL600 CL6002B19 EA COCKPIT DEFECTIVE W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) ON CLIMB OUT OF MEMPHIS THE CREW WERE UNABLE TO PRESSURIZE THE AIRCRAFT USING EITHER AUTO OR MANUAL MODES. MAINTEN ANCE FOUND THE OVERHEAD PRESSURIZATION CONTROL PANEL TO BE DEFECTIVE. A NEW PRESSURIZATION CONTROL PANEL WAS INSTALLED A ND THE AIRCRAFT RETURNED TO SERVICE. 2 L 7 2 4F RT A21EA 2001031400047 20010314 00047 EA 2001 3 14 CA001110036 1 20001102 G 2910 601R7528637 LINE CNDAIR CL600 CL6002B19 EA HYD SYSTEM CHAFED W A UNSCHED LANDING J K WARNING INDICATION FLUID LOSS CR CRUISE 1 CA (CAN) FIGHT CREW RECEIVED NR 1 HYDRAULIC LOW PRESSURE CAUTION MESSAGE, FOLLOWED QRH, DIVERTED TO BNA FOR REPAIR. MAINTEN ANCE FOUND 3/4 INCH HYDRAULIC PRESSURE LINE CHAFED, REPAIRED LINE WITH PERMASWAGE FITTINGS IAW AMM. REMOVED AND REPLACED NR 1 HYD EDP, AND FLEXIBLE LINE P/N 601R75147-19 DUE TO APPARENT FLUID SEEPAGE, OPS AND LEAK CHECKED GOOD. 2 L 7 2 4F RT A21EA 2001032700022 20010327 00022 EA 2001 3 27 CA001110038 1 20001104 G 2120 14243101 DUCT CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE AIR DISTRIBUTION CRACKED W O OTHER B SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 CA (CAN) AFTER FLIGHT 5401 FROM CVG TO TOL, WHILE PARKED AT THE GATE WITH APU RUNNING GOT A SMOKE TOILET WARNING MSG & LAV SMOKE DETECTOR WAS BEEPING. ALSO SMOKE IN THE CABIN. PERFORMED QRH, SMOKE DETECTOR STOPPED BEEPING & WARNING MSG CLEARED , AND CALLED FOR FIRE TRUCK. NO PAX WERE ON BOARD.FOUND DUCT P/N 14243-101 FROM RT PRSOV TO RT PACK HEAT EXCHANGER CRACK ED. 2 L 7 2 4F 4 F RT A21EA E15NE 2001031400048 20010314 00048 NE 2001 3 14 CA001110039 2 20001107 G 7230 BLADE GE CF343A1 CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE COMPRESSOR FAN DAMAGED W A UNSCHED LANDING B E SMOKE/FUMES/ODORS/SPARKS VIBRATION/BUFFET TO TAKEOFF 1 CA 807402 (CAN) AFTER TAKEOFF OUT OF MANCHESTER NH (MHT) GOT N1 VIB ICON. FOLLOWED BY SMOKE IN CABIN. CREW SHUT DOWN THE ENGINE AN D RETURNED TO BLOCKS. PRELIMINARY REPORT OF EXTENSIVE FAN BLADE DAMAGE. ROAD CREW BEING ARRANGED TO GO TO MHT FOR POSSIB LE ENGINE CHANGE. AVIONICS TECH DISPATCHED TO DO AN FDR DOWN LOAD. 2000-11-14TC: EXPECT FOLLOW-UP SDR FROM ORIGINATOR A S TO CAUSE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001031400049 20010314 00049 NE 2001 3 14 CA001110040 2 20001107 G 7200 ENGINE CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE NACELLE FAILED W A UNSCHED LANDING E X J VIBRATION/BUFFET ENGINE FLAMEOUT WARNING INDICATION AP APPROACH 1 CA 9000 (CAN) INBOUND FLIGHT FROM RALIEGH / DURHAM, NC (RDC). PILOT FELT SLIGHT VIBRATION IN SEAT. OIL PRESSURE WENT TO ZERO. EN GINE AUTO-SHUTDOWN. AIRCRAFT MADE AN UNEVENTFUL LANDING. CHIP DETECTOR HAS LARGE AMOUNT OF DEBRIS ON IT.ENGINE HAS APPRO XIMATELY 9000 HOURS ON IT AND WAS INSTALLED ON OCT 10/2000. PREVIOUS SHOP VISIT WAS FOR COMPRESSOR DAMAGE. AIRCRAFT CURR ENTLY IN HANGAR AT CINCINNATI. COWLINGS HAVE BEEN OPENED. NO OBVIOUS SIGN OF DAMAGE - NO OIL IN TAILPIPE.FDR READOUT BEI NG MADE. 2000-11-14TC: EXPECT FOLLOW-UP SDR FROM ORIGINATOR AS TO CAUSE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001032700023 20010327 00023 EA 2001 3 27 CA001110041 1 20001109 G 5510 BUSHING CNDAIR CL600 CL6002B19 EA HORIZONTAL STAB DAMAGED W A UNSCHED LANDING J F WARNING INDICATION FLT CONT AFFECTED CR CRUISE 1 CA (CAN) SHORTLY AFTER TAKEOFF, THREE MINUTES AFTER AUTOPILOT WAS ENGAGED PILOT RECEIVED AP PITCH TRIM MESSAGE. SECOND FAIL URE OF AUOPILOT OCCURRED 1 MINUTE AFTER RE-ENGAGEMENT MESSAGES POSTED ON EICAS DURING EVENT WERE AP TRIM IS ND AND NU. E LECTRIC STAB TRIM OPERATED APPROX 10 PERCENT OF THE TIME IN ONE DIRECTION. PILOT ADVISED ATC OF THE PORBLEM, CONTACTED F LIGHT CONTROL, HEADED BACK TO DFW, DECLARED AND EMERGENCY AND MADE AN UNEVENTFUL APPROACH AND LANDING. TROUBLESHOOTING W AS CARRIED OUT. HORIZONTAL STAB BUSHINGS FOUND STIFF. EXCESSIVE FORCE USED TO MOVE STAB UP OR DOWN MANUALLY WITH HSTA DI SCONNECTED. RJ SL-55-001 WILL BE APPLIED TO AIRCRAFT. 2 L 7 2 4F RT A21EA 2001032700024 20010327 00024 EA 2001 3 27 CA001110042 1 20001109 G 2740 CONTROL UNIT CNDAIR CL600 CL6002B19 EA HORIZONTAL STAB FAILED W A UNSCHED LANDING F FLT CONT AFFECTED CL CLIMB 1 CA (CAN) AFTER TAKEOFF CREW REPORTED THAT BOTH CHANNELS OF THE STAB TRIM DISCONNECTED. CREW REPORTED THAT THEY WERE UNABLE TO RESET EITHER CHANNEL. AFTER LANDING CREW REPORTED THAT THEY COULD RESET BOTH CHANNELS, OUTSTATION MAINTENANCE PERFORM ED A DOWN LOAD OF THE MDC. INDICATIONS SHOWED POSSIBLY POBLEM WITH PILOTS DISCONNECT SWITCH, MAINTENANCE WAS UNABLE TO DUPLICATE PROBLEM. MAINTENANCE DID A SYSTEM RESET AND FULL BITE TEST OF THE STAB HSTCU, NO FAULTS NOTED. MAINTENANCE PER FORMED FULL SYSTEM CHECK OF STAB NO DEFECTS NOTED, AIRCRAFT RETURNED TO SERVICE. 2 L 7 2 4F RT A21EA 2000112900335 20001129 00335 GL 2000 11 29 CA001110045 2 20001017 G 7323 LN93556X32 BOLT BOLKMS 105 BO105C 5626005 EU ALLSN 250C 250C20B 03013 GL COLLECTIVE FAILED W K NONE R PARTIAL RPM/PWR LOSS CR CRUISE 1 CA CAE834907 (CAN) DURING CRUISE FLIGHT, PILOT WAS ONLY ABLE TO ACHIEVE 98 PERCENT N2 ON NR 1 ENGINE. UPON LANDING AT THE MAINTENANC E FACILITY, AN INSPECTION FOUND THE NR 1 ENGINE GOVERNOR CABLE WHERE IT ATTACHES TO THE COLLECTIVE FORK HAD BECOME DISE NGAGED. REF: MBB PARTS BOOK FIG 621 ITEM NR 40 CONNECTION FIGURE 438 ITEMS, NR 440 BOLT, NR 60 FORK LEVER, AND NR 110 ANCHOR NUT. BOLT NR 440 HAD BACKED OUT OF THE ANCHOR NUT NR 110 AND ALLOWED THE CABLE TO COME FREE OF THE COLLECTIVE FO RK NR 60. THE BOLT AND N2 CABLE WERE RE-ASSEMBLED AND FUNCTIONAL CHECK COMPLETED ON THE GOVERNOR/RIGGING ALL SYSTEMS FO UND SERVICEABLE. THE AIRCRAFT WAS THEN RETURNED TO SERVICE. (X) 1 G 7 2 3U 3 U H3EU E4CE 2001032700025 20010327 00025 NE 2001 3 27 CA001122002 2 20001108 G 7510 69701561 CLAMP BOEING 737 737217 1384464 NM PWA JT8 JT8D17 52049 NE NR 1 ENGINE FAILED W E ENGINE SHUTDOWN J WARNING INDICATION CL CLIMB 1 CA (CAN) NR 1 ENGINE SHUT DOWN, APPROXIMATELY 12 MINUTES INTO FLT. DUE TO ENGINE OVERHEAT AND START VALVE OPEN LIGHT ON. F OUND THERMAL ANTI-ICE DUCT CLAMP FAILED. REPLACED CLAMP, RT 8TH STAGE BLEED DUCT, AND 13TH STAGE BLEED DUCT TO EXPANSION BELLOWS. ENGINE RUN CARRIED OUT ALL SYSTEMS CHECK NORMAL AND NO LEAKS FOUND. A/C RETURNED TO SERVICE. 2 L 7 2 4F 4 F A16WE E2EA 2001031400051 20010314 00051 NM 2001 3 14 CA001122003 1 20000920 G 2710 CONTROL UNIT BOEING 737 737296 1384486 NM PWA JT8 JT8D9A 52048 NE AILERONS FAILED W K NONE F FLT CONT AFFECTED CR CRUISE 1 CA (CAN) EN ROUTE CREW REPORTED AILERONS WERE STIFF, BEYOND 5 DEGREES INPUT WITH AUTOPILOT SELECTED OFF. AUTOPILOT ON AILER ONS WERE BETTER. AIRCRAFT TAKEN OUT OF SERVICE FOR TOURBLESHOOTING. AILERON POWER CONTROL UNIT RIGGING CARRIED OUT AS PE R WORK CARD 51143, ITEM 7. AILERON CABLES CHECKED LT AND RT SIDE AND LT AILERON LUBED. NO FAULTS FOUND. 2 L 7 2 4F 4 F RT A16WE E2EA 2001032700026 20010327 00026 EA 2001 3 27 CA001122006 1 20001101 G 5720 C2W1071 BUSHING DHAV C2W1104A DHAV DHC2 DHC2* 2800108 EA PWA R985 R985AN1 52008 NE LIFT STRUT WORN W K NONE O OTHER IN INSP/MAINT 1 CA 9010 A0026 (CAN) DURING ROUTINE INSPECTION THE RT TOP LIFT STRUT BUSHING WAS FOUND TO BE WORN. THIS CONDITION APPEARS TO BE A WEAK PART IN DESIGN AS WE ARE CONSTANTLY REPAIRING THE TOP END OF THE LIFT STRUTS. : THE ALUMINIUM LIFT STRUT ENDS ARE FIELD REPAIRABLE. 1 H 7 1 3R 3 R A806 5E1 2000112800042 20001128 00042 EA 2000 11 28 CA001122007 1 20001101 G 5522 S6129661170 FITTING S6109210101 CARSON S61 S61LSKRSKY EA GE CT58 CT581401 30011 NE ATTACH LUG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 1491 (CAN) ON POST-FLIGHT INSPECTION, UPPER LEFT HAND LUG OF TAIL PYLON HINGE FITTING WAS FOUND CRACKED. HINGE REPLACED WITH STEEL PART NR S6120-66117-041 IN ACCORDANCE WITH S61320-23. (X) 2 G 7 2 4U 4 U H8EA 1E3 2001031400053 20010314 00053 EU 2001 3 14 CA001122008 1 20001103 G 5210 350902001 WINDOW SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1B 6OO30 NE COPILOTS DOOR CRACKED W O OTHER D INFLIGHT SEPARATION CR CRUISE 1 CA (CAN) COPILOTS WINDOW DEPARTED IN-FLIGHT. SUBMITTER SUSPECTED THAT THE WINDOW HAD A NICK IN IT CAUSING IT TO CRACK AND DEPART OUT OF AIRCRAFT. WINDOW IS INSTALLED ON A RUBBER SEAL THAT ATTACHES TO THE DOOR WINDOW FRAME. THE WINDOW IS A L ITTLE LARGER THAN THE DOOR WINDOW OPENING. TWO WEEK PRIOR TO THIS INCIDENT THE WINDOW WAS REMOVED AND RE-INSTALLED. (X) 1 G 7 1 3U 3 U NC H9EU E19EU 2001032700027 20010327 00027 NE 2001 3 27 CA001122010 2 20001109 G 7261 D9798 RESTRICTOR VALVE BOEING 727 72725 1384006 NM PWA JT8 JT8D7B 52053 NE OIL PRESSURE FAILED W E ENGINE SHUTDOWN J WARNING INDICATION DE DESCENT 1 CA (CAN) ON DESCENT INTO YEG THE NR 1 ENGINE OIL PRESSURE BEGAN FLUCTUATING BETWEEN 0-35 PSI. IMMEDIATELY FOLLOWING THIS IN DICATION THE LOW OIL PRESSURE BYPASS LIGHT ILLUMINATED. ENGINE WAS SHUT DOWN. TROUBLE SHOOTING REVEALED RESTRICTOR GOING TO OIL PRESSURE INDICATION SYSTEM FAILED. ALSO REPLACE OIL PRESSURE RELIEF VALVE. THE ENGINE WAS GROUND RUN AT HIGH POW ER SETTING FOR 45 MINUTES WITH NO FURTHER INDICATIONS PROBLEMS. THE AIRCRAFT HAS OPERATED FROM YEG TO YWG TO YHM TO YWG WITHOUT ANY FUTHER PROBLEMS. THE COMPANY HAS CONSIDERED IT A DEFINITE FIX.. 2 L 7 3 4F 4 F A3WE E2EA 2000113000154 20001130 00154 GL 2000 11 30 CA001122011 2 20000601 G 7321 78315 SCREW BENDIX 252464429 BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL FUEL CONTROL SHEARED W O OTHER D X J INFLIGHT SEPARATION ENGINE FLAMEOUT WARNING INDICATION NR NOT REPORTED 1 CA 334377 (CAN) THE SCREW HEAD RETAINING THE FUEL CONTROL UNIT RATIO LEVER COVER (FUEL SIDE) SEPARATED IN-FLIGHT ALLOWING FUEL TO LEAK INTO THE ENGINE COMPARTMENT UNDER HIGH PRESSURE AND REDUCE THE FUEL FLOW TO THE ENGINE TO THE POINT WHERE CONTINUED FLIGHT WAS NOT POSSIBLE. THE HELICOPTER CRASHED AND BURNED WHILE ATTEMPTING AN AUTORATIONAL LANDING (TSB REPORT A00W010 5) RESULTING IN THE DEATH OF THE PILOT. EXAMINATION OF THE FRACTURED SCREW HEAD AT THE TSB LAB (PROJECT LP 72/00) DETER MINED THE FRACTURE WAS THE RESULT OF THE HEC. IT WAS ALSO DETERMINED THE SCREW MATERIAL AND MARKINGS DID NOT MEET THE M ANUFACTURER''S SPECIFICATIONS PLACING THE SCREW IN THE CATEGORY OF A SUSPECTED UNAPPROVED PART. (X) 1 G 7 1 3U 3 U H2SW E4CE 2000112800155 20001128 00155 SO 2000 11 28 CA001122012 2 20001108 G 8530 652956 EXHAUST VALVE CONT 654653A4 CESSNA 185 A185F 2072821 CE CONT O550 IO550D 17042 SO MCAULY D3A34 D3A34C401 GL SEAL SURFACE BURNED W O OTHER O OTHER IN INSP/MAINT 1 CA 518 (CAN) AFTER COMPLETING THE ENGINE CYLINDER DIFFERENTIAL COMPRESSION TEST ON A ROUTINE INSPECTION, DETERMINED NR 3 AND NR 4 CYLINDERS HAD EXCESSIVE LEAKAGE THROUGH THE EXHAUST VALVES. THE BAFFLES AT EACH END OF THE EXHAUST MUFFLER WERE FOUN D BROKEN AWAY FROM THE ORIGINAL LOCATION AND JAMMED NEAR THE OUTLET PORT. EXCESSIVE EXHAUST BACK PRESSURE COULD HAVE CA USED THE EXHAUST VALVES TO DETERIORATE PREMATURELY. (X) 1 H 7 1 3O 3 O 3A24 E3SO 5 C P47GL 2000112800156 20001128 00156 EU 2000 11 28 CA001122013 1 20001112 G 3242 9595601511 BRAKE PILATS PC12 PC1245 EU RT GEAR FROZEN W O OTHER O OTHER LD LANDING 1 CA 1110 (CAN) RIGHT BRAKE FROZEN, ON LANDING, RIGHT TIRE DID NOT ROTATE; THUS, TIRE WORE THROUGH AND WENT FLAT. AIRCRAFT WAS ST OPPED ON RUNWAY. MAINTENANCE CALLED. TIRE REMOVED, GEAR INSPECTED AND NEW WHEEL AND TIRE INSTALLED. (X) 1 L 7 1 3T RT A78EU 2001031400055 20010314 00055 NE 2001 3 14 CA001122016 2 20001108 G 7200 ENGINE BOEING 737 7372M8 1384483 NM PWA JT8 JT8D15 52051 NE NR 2 FAILED W E A ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) DURING CLIMB FROM VANCOUVER THE CREW NOTICED NR 2 ENGINE OIL QUANTITY DROP TO ZERO. THEY INITIATED A PRECAUTIONARY SHUT DOWN OF THE ENGINE AND RETURNED TO VANCOUVER. MAINTENANCE PERSONNEL IN VANCOUVER FOUND NORMAL OIL QUANTITY IN THE ENGINE. THEY CARRIED OUT AN ENGINE RUN TO CHECK OTHER PARAMETERS AND FOUND THEM TO BE NORMAL. NR 2 ENGINE OIL QUANTITY W AS DEFERRED ON MEL79-1 AND THE AIRCRAFT RELEASED TO SERVICE. 2 L 7 2 4F 4 F A16WE E2EA 2001031400056 20010314 00056 NM 2001 3 14 CA001122017 1 20000925 G 3244 0397692 TIRE BOEING 737 737217 1384464 NM PWA JT8 JT8D9A 52048 NE MLG FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 773 (CAN) DURING THE TAKEOFF ROLL NR 4 MAIN WHEEL TIRE TREAD SEPARATED. THERE WAS NOTHING UNUSUAL NOTED BY THE FLIGHT CREW A ND THE AIRCRAFT PROCEEDED TO SASKATOON. THE SEPARATED TIRE TREAD WAS DISCOVERED ON THE RUNWAY BY AIRPORT MAINTENANCE CRE WS AND REPORTED TO CALGARY MAINTENANCE. THE AIRCRAFT LANDED AT SASKATOON WITHOUT INCIDENT AND AN INSPECTION OF THE AIRCR AFT WAS ACCOMPLISHED AND TIRE CONDITION WAS CONFIRMED. A MAINTENANCE CREW WAS DISPATCHED FROM CALGARY AND ASSESSED THE D AMAGE AND REPLACED THE MAIN WHEEL ASSY. THE AIRCRAFT WAS FERRIED BACK TO CALGARY FOR REPAIR. 2 L 7 2 4F 4 F A16WE E2EA 2001031400057 20010314 00057 NM 2001 3 14 CA001122018 1 20001107 G 3242 STATOR BENDIX 26010425 BOEING 737 737284 138448R NM PWA JT8 JT8D9A 52048 NE BRAKE ASSY BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 405 B3962 (CAN) DURING THE SERVICE CHECK NR 3 BRAKE TENSION ADJUSTMENT PINS WERE FOUND LOOSE. WHEN CHECKED FURTHER ONE OF THE BRAK E STATORS HAD BROKEN AND THERE WERE MULTIPLE PIECES FOUND CONTAINED INSIDE THE WHEEL. NR 3 BRAKE WAS REPLACED AND NR 3 M AIN WHEEL ASSEMBLY DUE TO DAMAGE. AIRCRAFT RETURNED TO SERVICE. 2 L 7 2 4F 4 F A16WE E2EA 2001031400058 20010314 00058 NM 2001 3 14 CA001122019 1 20001103 G 3242 6544566 O-RING BENDIX 26010425 BOEING 737 7372A3 138448A NM PWA JT8 JT8D9A 52048 NE VALVE DAMAGED W O OTHER K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA 2274 4 BC0650 (CAN) CREW REPORTED A LOSS OF B SYSTEM HYDRAULIC FLUID EN ROUTE FROM ABBOTTSFORD TO CALGARY. UPON ARRIVAL IN CALGARY THE NR 1 BRAKE WAS FOUND TO BE LEAKING AT QUICK DISCONNECT FITTING AT THE BRAKE ASSY. WHEN THE FITTING WAS REMOVED THE BACK UP O-RING WAS FOUND DAMAGED. A BRAKE O-RING KIT WAS INSTALLED AND THE AIRCRAFT RETURNED TO SERVICE. 2 L 7 2 4F 4 F A16WE E2EA 2001032700029 20010327 00029 CE 2001 3 27 CA001122020 1 20000707 G 7603 C2995050101 THROTTLE CABLE CESSNA 206 U206F 2073333 CE CONT O520 IO520F 17032 SO ENGINE SEIZED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) A NEW THROTTLE CABLE RECEIVED FROM CESSNA WAS INSTALLED ON THE AIRCRAFT BUT SEIZED UP WHEN THE CABLE WAS FLEXED TO ALLOW HOOKUP TO THE THROTTLE CABLE. ANOTHER NEW CABLE FROM CESSNA WAS TRIED WITH THE SAME RESULT.A THROTTLE CABLE MADE BY MCFARLANE MCC299505-0101 WAS INSTALLED AND RIGGED PROPERLY WITHOUT FAULT. 1 H 7 1 3O 3 O A4CE E5CE 2000112800160 20001128 00160 CE 2000 11 28 CA001122022 1 20001002 G 8011 PS1432 CASTING PRESTOLITE MZ4222 CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA NEAR FRONT BRG CRACKED W O OTHER O OTHER IN INSP/MAINT 1 CA 356 A143350 (CAN) CASTING SUPPORTING THE DRIVE GEAR CRACKED. THE DRIVE GEAR STAYED ENGAGED AFTER ENGINE WAS STARTED. (X) 1 H 7 1 3O 3 O NT 3A12 E274 2001032700030 20010327 00030 EA 2001 3 27 CA001122023 2 20001027 G 7322 SCREW CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA FLOAT BOWL LOOSE W E A ENGINE SHUTDOWN UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA 2185 31 (CAN) ENGINE WAS RUNNING ROUGH, OVER TORQUING AND MIXTURE CONTROL WOULD NOT SHUT DOWN ENGINE. THE FLOAT BOWL SCREWS WERE FOUND LOOSE AND THE TWO HALVES OF THE CABLES WERE SEPARATED BY ABOUT .040 INCH. THE LOWER FLOAT BOWL NEEDED HELICOILS BECAUSE THE THREADS WERE DAMAGED / MISSING AND THEN THE SCREWS HEADS WERE LOCKWIRED TO EACH OTHER UPON REASSEMBLY. SEVER AL OTHER 172S HAVE HAD THE SAME PROBLEM WITH DIFERENT TSN ON THE CARBS. 1 H 7 1 3O 3 O NT 3A12 E274 2001011106119 20010111 06119 CE 2001 1 11 CA001122024 1 20001102 G 5510 07326015 FITTING CESSNA 123260026 CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO HORIZONTAL STAB SHEARED W K NONE O OTHER IN INSP/MAINT 1 CA 7436 (CAN) ON INSPECTION, NOTICED THAT THE HORIZONTAL STABILIZER WOULD MAKE A NOISE WHEN THE TIP WAS MOVED UP AND DOWN. THE T AIL WAS TAKEN APART AND THE 10 RIVETS HOLDING THE FRONT FITTING. THE TOP 3 RIVETS ON EACH FITTING WAS SHEARED. THE RIVET S WERE ALL REPLACED. (X) 1 H 7 1 3O 3 O A4CE E5CE 2001032700031 20010327 00031 CE 2001 3 27 CA001122025 1 20001107 G 3250 071230916 BELLCRANK CESSNA 185 A185F 2072821 CE CONT O520 IO520D 17032 SO MCAULY 2A34C D2A34C58 GL TAILWHEEL STEER WORN W K NONE O OTHER IN INSP/MAINT 1 CA 8910 (CAN) DURING INSPECTION OF TAIL WHEEL STEERING CABLES, WORN BELLCRANKS WERE DISCOVERED AT SPRING ATTACH POINT. 1 H 7 1 3O 3 O 3A24 E5CE 5 C P3EA 2001032700033 20010327 00033 CE 2001 3 27 CA001122027 1 20001102 G 2720 07135295 LINK CESSNA 185 A185F 2072821 CE CONT O520 IO520D 17032 SO MCAULY 2A34C D2A34C58 GL RUDDER TRIM STRIPPED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) PILOT REPORTED RUDDER TRIM HARD TO ADJUST. PARTS REMOVED AND FOUND THREADS ON WHEEL SCREW AND LINK ROD STRIPPED. A PORTION OF SCREW FOUND BROKEN INSIDE LINK ROD. 1 H 7 1 3O 3 O 3A24 E5CE 5 C P3EA 2001011106120 20010111 06120 EU 2001 1 11 CA001122028 1 20001102 G 5510 350A23002029 PLATE SNIAS SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1B 6OO30 NE HORIZONTAL STAB CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 8725 1232 (CAN) AT 8,724.9 AIRFRAME HOURS, WHILE CONDUCTING A 100-HOUR INSPECTION, A CRACK WAS DETECTED ON THE LT UPPER HORIZONTAL STABILIZER ATTACHMENT DOUBLER. THIS IS A KNOWN STRESS AREA AND REPLACEMENT PARTS ARE NOW UPGRADED. EUROCOPTER SERVICE LETTER 400-53-82 SHOWS THE UPGRADED PARTS. UPGRADED PARTS HAVE BEEN INSTALLED AND AIRCRAFT WAS RETURNED TO SERVICE. (X ) 1 G 7 1 3U 3 U H9EU E19EU 2001032700034 20010327 00034 NM 2001 3 27 CA001122029 1 20001114 G 2612 896767 FIRE LOOP BOEING 737 737281 138448P NM PWA JT8 JT8D17 52049 NE APU CHAFED W F ACTIVATE FIRE EXT. N FALSE WARNING CR CRUISE 1 CA (CAN) APU FIRE WARNING IN CRUISE, APU FIRE HANDLED & WARNING CEASED, BOTTLE DISCHARGED. AIRCRAFT CARRIED OUT A NORMAL L ANDING. MAINTENANCE INSPECTED APU & AREA AND FOUND NO INDICATIONS OF FIRE OR OVERHEAT. THE AIRCRAFT WAS RELEASED UNDER T HE PROVISIONS OF THE MEL. NEXT OVERNIGHT MAINTENANCE DISCOVERED DAMAGED WIRING AT THE TAIL PIPE FIRE LOOP. WIRING & LOO P WERE REPLACED ALONG WITH THE FIRE BOTTLE. THE SYSTEM TESTED SERVICEABLE AND THE AIRCRAFT RELEASED. 2 L 7 2 4F 4 F A16WE E2EA 2001040200118 20010402 00118 EU 2001 4 2 CA001122030 1 20000923 G 5753 137202B61 BRACKET BAG JETSTM JETSTM3101 1500215 EU ROTOL R333 R333482F12 GL LT & RT FLAP CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 27932 (CAN) LT FLAP BRACKET FOR FLAP TO SLAT ATTACHMENT 4TH FROM INBOARD END FOUND CRACKED. BRACKET REPLACED WITH MADE REPAIR PART. RT FLAP BRACKET FOR FLAP TO SLAT ATTACHMENT 7TH FROM INBOARD END FOUND CRACKED. BRACKET REPLACED WITH MADE REPAIR PART. 2 L 7 2 4T RT A21EU 6 C P61GL 2001040200119 20010402 00119 EU 2001 4 2 CA001122031 1 20000930 G 5753 137202B61 BRACKET BAG JETSTM JETSTM3101 1500215 EU ROTOL R333 R333482F12 GL LT FLAP CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 28385 (CAN) DURING SCHEDULED MAINTENANCE INSPECTION ATTACHMENT BRACKET FOR FLAP TO SLAT FOUND BROKEN. BRACKET POSITION LT OUTB OARD FLAP, SECOND INBOARD FROM OUTBOARD END. BRACKET REPLACED WITH MADE REPAIR PART. 2 L 7 2 4T RT A21EU 6 C P61GL 2001040200120 20010402 00120 EU 2001 4 2 CA001122032 1 20001003 G 5753 137202B61 BRACKET BAG JETSTM JETSTM3101 1500215 EU ROTOL R333 R333482F12 GL LT FLAP CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 27976 (CAN) LT OUTBOARD FLAP TO SLAT ATTACHMENT BRACKET FOUND CRACKED. BRACKET REPLACED WITH MADE REPAIR PART. 2 L 7 2 4T RT A21EU 6 C P61GL 2001031400059 20010314 00059 SW 2001 3 14 CA001122033 1 20000913 G 2913 66948 CLIP BELL 212076011001 BELL 205 205A1 1181414 SW LYC T53 T5313B 41549 NE HYD PUMP MISSING W O OTHER J F WARNING INDICATION FLT CONT AFFECTED IN INSP/MAINT 1 CA AV3001058E (CAN) CIRCLIP AT END OF PUMP, (SOME PARTS FOUND IN PUMP P/S CAVITY) WAS FOUND MISSING, AND ALLOWED THE DRIVE SHAFT TO DI SENGAGE FROM PUMP AND MOVE INTO THE TRANSMISSION DRIVE QUILL. THE PUMP WAS REMOVED AND SENT FOR TEST AND INSPECTION WHIC H CONFIRMED SUSPICION.REPORT OF PUMP TEST AND PILOTS INCIDENT REPORT ATTACHED. CIRCLIP AND EXTERNAL P/S REPLACED AS PER BHT TB-205-86-70. 1 G 7 1 4U 4 U H1SW E17EA 2001032700035 20010327 00035 SO 2001 3 27 CA001123002 1 20001026 G 2730 71056003 SPRING PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA ELEVATOR BUNGEE BROKEN W O OTHER O G OTHER MULTIPLE FAILURE TO TAKEOFF 1 CA 648 (CAN) ON TAKEOFF, PILOT FELT A SNAP ON THE CONTROL WHEEL, THINKING THAT THE TRIM HAD STUCK MOMENTARILY HE FLEW THE AIRCR AFT TO ITS NEXT DESTINATION WITHOUT ANY PROBLEMS BUT NOTICED NO DOWN PRESSURE ON THE CONTROLS ONCE HE LANDED. ON INVESTI GATION WE FOUND THE ELEVATOR DOWN SPRING HAD BROKEN AT THE REAR PORTION OF THE SPRING, ABOUT AN INCH FROM THE HOOK END. 1 L 7 2 3O 3 O A20SO E14EA 2001011106123 20010111 06123 CE 2001 1 11 CA001123003 1 20001108 G 5610 10138402521 WINDSHIELD BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA COCKPIT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING PRE-FLIGHT INSPECTION, THE FLIGHT CREW NOTICED A CRACK IN THE LT WINDSHIELD. MAINTENANCE ADVISED. AIRCRAF T REMOVED FROM SERVICE WINDSHIELD REPLACED. (X) 1 L 7 2 4T 4 T A24CE E4EA 2001032700038 20010327 00038 SO 2001 3 27 CA001123007 1 20001030 G 5320 4810100 SILL PIPER PA31T PA31T 7103124 SO PWA PT6 PT6A28 EA CABIN DOOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) MAINTENANCE INSPECTION REVEALED DOOR SILL AREA CRACKING UNDER THE FLOOR AND ADJACENT TO THE CABIN DOOR HINGE AREA. PARTS AFFECTED OR REPLACED INCLUDE P/N 48101-00 RIB (BULKHEAD) (CRACKING), 45648-00 DOOR SILL (CRACKING). AIRSTAIR HING E(S) 46396-00/46395-00 AND PIN 81761-70 REPLACED NEW AT THIS TIME. STRUCTURAL REPAIRS C/O AS REQUIRED. AIRCRAFT RETURNED TO SERVICE.A/C TTSN 17769.7 1 L 7 2 3T 4 T A8EA E4EA 2001032700039 20010327 00039 SO 2001 3 27 CA001123008 1 20001031 G 3230 4204202 ARM PIPER PA31T PA31T 7103124 SO PWA PT6 PT6A28 EA MLG CRACKED W A UNSCHED LANDING J WARNING INDICATION NR NOT REPORTED 1 CA (CAN) CREW REPORTED DIFFICULT EXTENDING AND RETRACTING LANDING GEAR. GEAR EXTENDED AND LOCKED ON 2ND ATTEMPT AND UNEVENT FUL LANDING C/O.MAINTENANCE DISCOVERED BROKEN MAIN LANDING GEAR RETRACTION ARM P/N 42042-02. LT PART REPLACED NEW. GEAR SWING C/O A/C RELEASED. 1 L 7 2 3T 4 T A8EA E4EA 2001032700040 20010327 00040 NM 2001 3 27 CA001123009 1 20001116 G 2130 1305026 SELECTOR KNOB BOEING 757 75728A 1384976 NM RROYCE RB211 RB211535E437 54555 NE CABIN PRESSURE FAILED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) THRU 10,000 FEET CABIN ALTITUDE EICAS WARNING. QRH ACTIONED. AIRCRAFT RETURNED TO YYZ WITHOUT INCIDENT. CABIN PRES SURE SELECTOR REPLACED. 2 L 7 2 4F 4 F RT A2NM E12EU 2001032700041 20010327 00041 SO 2001 3 27 CA001123010 1 20001120 G 5610 7955300 FITTING PIPER PA32 PA32300 7103212 SO LYC O540 TIO540S1AD 41532 EA HARTZL HCE2Y HCE2YR1BF GL WINDSCREEN CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 2611 (CAN) WHEN ENDEAVOURING TO REPLACED THE WINDSCREENS, THESE BRACKETS WERE FOUND HEAVILY CORRODED AND HAD TO BE REPLACED. 1 L 7 1 3O 3 O A3SO E14EA 5 C P9EA 2001032700042 20010327 00042 2001 3 27 CA001123011 4 20001120 G 6113 05503214 BULKHEAD CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA MCAULY 1C160 1C160DTM GL SPINNER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 8616 (CAN) DURING ENGINE AND PROP REMOVAL, THE SPINNER BULKHEAD WAS FOUND CRACKED AROUND THE BOLT HOLES. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2001040300035 20010403 00035 SW 2001 4 3 CA001123016 1 20001110 G 6420 206011724003 VENT BELL 206 206L 1181522 SW T/R PITCH CHANGE CLOGGED W K NONE O OTHER IN INSP/MAINT 1 CA 1031 (CAN) DURING REPLACEMENT OF BOOT ON TAIL ROTOR PITCH CHANGE MECHANISM, THE VENT HOLE IN TUBE ASSY P/N 206-011-724-003 WA S FOUND OBSTRUCTED. FUTHER INVESTIGATION REVEALED THAT DRIED GREASE WAS PLUGGING THE HOLE. THE VENT HOLE WAS CLEANED, AN D THE TUBE RE-ASSEMBLED. THE GREASE USED FOR LUBRICATION OF THE TRUNNION AND HOUSING BEARINGS IS AEROSHELL 22. AFTER LUB RICATION OF THOSE BEARINGS, THE MANUFACTURER RECOMMENDS WIPING THE AREA WITH A CLEAN CLOTH. THIS OPERATION VERY LIKELY P ACKED THE GREASE IN THE HOLE, ALLOWING IT TO DRY AND PREVENTING THE NECESSARY VENTING OF THE BOOT AREA. MAINTENANCE PERS ONNEL HAS BEEN ADVISE TO MAKE SURE THE VENT HOLE IS CLEARED AFTER EACH LUBRICATION. 1 G 7 1 3U H2SW 2001032700048 20010327 00048 NM 2001 3 27 CA001123018 1 20001017 G 2934 AERO983614 CONNECTOR DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE RESERVOIR CORRODED W O OTHER J WARNING INDICATION LD LANDING 1 CA (CAN) ON LANDING ROLL SPOILER INBOARD HYDRAULIC AND NR 1 ISO VALVE CAUTION LIGHTS ILLUMINATED -- INSPECTED AND FOUND SEV ERE CORROSION ON ISO VALVE SWITCH CANNON PLUG AND SOCKET. R&R SWITCH AND CANNON PLUG, OPS CHECK GOOD AT THIS TIME. DEFER RAL INSPECTED AIRCRAFT AND NR 1 RUDDER ISOLATION VALVE. FOUND EVIDENCE OF ARCING AT NR 1 ISOLATION VALVE CONNECTOR AT RE SERVOIR.RESERVOIR LEVEL SWITCH & CANNON PLUG REPLACED, OPS CHECK CARRIED OUT, AIRCRAFT RETURNED TO SERVICE. 2 H 7 2 4T 4 T RT A13NM E20NE 2001032700049 20010327 00049 2001 3 27 CA001123019 4 20001024 G 2565 82560034021 COVER DHAV DHC8 DHC8* NM PWA PW120 PW123 NE DITCHING DAM MISSING W O OTHER D INFLIGHT SEPARATION CR CRUISE 1 CA (CAN) DITCHING DAM COVER DETACHED, DAM SEPARATED INFLT. A/C JUST LEVELLED IN CRUISE, CABIN CREW RPTED LOAD BANGING NOISE , SPEED REDUCED, 1ST OFFICER INSP&CONFIRMED DAM COVER DETACHED, BUT DAM STILL ATTACHED. PAN DECLARED, INITY ELECTED TO D IVERT OT NEWQUAY TO AVOID DAMAGE TO PERSON/PROPERTY ON GROUND. HOWEVER DAM DETACHED INFLT SO DECISION MADE TO CONTINUE T O PLYMOUTH AS PER FLT SCHEDULE. BRYMON ENGINEERS CONFIRMED A/C PRE-MOD 8/1690 FITMENT OF NEOPRENE DIAPHRAGM REQD TO HELP PREVENT INADVERTANT DAM DEPLOYMENT BY CABIN PRESSURE: INSP DIAPHRAGM P/N 83510007-101 INST CABIN PRESSURE AIR INFLATED BAG SUFFICIENTLY TO DEPLOY DITCHING DAM.N2 BOTTLE HAS BEEN PREV REPL. NEW PARTS FITTED&A/C RETURN TO SERVICE. CARRY OU 2 H 7 2 4T 4 T RT A13NM E20NE 2001032700050 20010327 00050 NM 2001 3 27 CA001123020 1 20001025 G 5270 82420109033 PROXIMITY SWITCH DHAV DHC8 DHC8* NM EMERGENCY EXIT OUT OF ADJ W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 CA (CAN) DURING CLIMB OUT FROM ARLANDA, AT APP FL150 WE GOT A FUSELAGE DOOR WARNING. MFD SHOWED THE FWD EMERGENCY EXIT. I INFORMED THE PURSER ABOUT THE PROBLEM AND WE HAD 72 PAX ONBOARD SO NO RESEATING WAS POSSIBLE.DURING DESCENT THE WARNING DISAPPEARED. NORMAL UNEVENTFUL LANDING CARRIED OUT . TECHNICIANS LUBRICATED AND ADJUSTED THE PROXIMITY SWITCH TARGET M ECHANISM AND TESTED IT WITHOUT ANY REMARKS. A/C RETURNED TO SERVICE. 2 H 7 2 4T RT A13NM 2001032700051 20010327 00051 EA 2001 3 27 CA001123021 2 20001024 G 7261 305306301 REGULATOR VALVE DHAV DHC8 DHC8* NM PWC 150 PW150A EA ENGINE LEAKING W A UNSCHED LANDING B J SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CL CLIMB 1 CA (CAN) DEPARTED COPENHAGEN ON ATTEMPT TO CARRY OUT A POSITIONING FLIGHT (SK9100), COPY FROM PILOTS (FOR):- SHORTLY AFT ER TAKEOFF WE HEARD SMOKE WARNING FROM LAVATORY. INSPECTION REVEALED NO SMOKE OR FIRE.AND FLIGHT RETURNED TO COPENHAGEN FOR TECHNICAL INVESTIGATION.THE LAVATORY SMOKE DETECTOR IS SENSITIVE TO ENGINE FUMES AND BOTH ENGINES PRIOR TO THIS FLIG HT WERE PRE-MOD (S/B 35038). 2 H 7 2 4T 4 T RT A13NM E00062EN 2001032700052 20010327 00052 NM 2001 3 27 CA001123023 1 20001012 G 2611 473082 SMOKE DETECTOR DHAV DHC8 DHC8* NM CARGO BAY FAILED W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 CA (CAN) FLT 210 FLYING AT 240 KTS IAS, VMC APPROXIMATELY 10 MINS AFTER TAKEOFF. WE GOT A SMOKE WARNING, ON CAUTION / WARNI NG PANEL, MASTER WARNING FLASHING, TRIPLE CHIME & FWD FIRE BOTTLE ARM ;T ON, FWD BAGGAGE EXT SWITCH LT/PUSH BUTTON ON. ALL INTERMITENTLY ON SEVERAL TIMES FOR 4/5 MINS PERIOD. REQUESTED RETURN - STARTED DESCENT INFORMED CA, INFORMED PAX, OR H - CHECKLIST FOLLOWED, DUE TO INTERMITENT WARNING - NOT ABLE TO BOTTLE, SEVERAL MORE WARNINGS DURING APPROACH SVG. NORM AL LANDING, PASSENGERS DISEMBARKED AT STAND 40, THROUGH L1-PAX DOOR. NEVER ANY SMELL OF SMOKE OR VISUAL SIGN OF SMOKE/FI RE. 2 H 7 2 4T RT A13NM 2001032700053 20010327 00053 NM 2001 3 27 CA001123024 1 20001105 G 3320 BR9120WW LAMP DHAV DHC8 DHC8102 2809003 NM PWA PW121 PW121 52124 NE ROW 5 SHORTED W O OTHER B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA (CAN) MAINTENANCE NOTIFIED OF ELECTRICAL SMOKE FROM CABIN OVERHEAD LIGHT AT ROW 5 D/F, BULB WAS REMOVED, AND MEL ISSUED FOR OVERHEAD LIGHTING SYSTEM, A/C RETURN TO SERVICE. LAMP WAS REPLACED ON 7 NOV 2000, OPERATIONAL CHECK GOOD, MEL REMOVE D. 2 H 7 2 4T 4 T RT A13NM E20NE 2001032700054 20010327 00054 NM 2001 3 27 CA001123025 1 20001026 G 2611 473054 SMOKE DETECTOR DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120 NE CARGO BAY MALFUNCTIONED W O OTHER N FALSE WARNING DE DESCENT 1 CA 15347 4277 (CAN) DURING DESCENT INTO PHL, BAGGAGE COMPARTMENT SMOKE DETECTOR LIGHT ILLUMINATED. EMERGENCY DECLARED, FLIGHT LANDED W ITHOUT INCIDENT. NR 2 SMOKE DETECTOR REPLACED, NR 1 SMOKE DISCONNECTED IN ACCORDANCE WITH MEL 26-08, AIRCRAFT WAS RETURN ED TO SERVICE. NR 1 SMOKE DETECTOR REPLACED ON 27TH OCTOBER 2000. 2 H 7 2 4T 4 T RT A13NM E20NE 2001031400060 20010314 00060 NM 2001 3 14 CA001123027 1 20001025 G 3240 BRAKE ASSY DHAV DHC8 DHC8103 1386005 NM PWA PW121 PW121 52124 NE HAMSTD 14SF 14SF7 NE RT NACELLE OVERSERVICED W O OTHER O OTHER LD LANDING 1 CA (CAN) THE FOLLOWING WAS REPORTED TO US FROM ALLEGANY AIRLINES: FLIGHT 3968 UPON LANDING IN MHT, NEW HAMPSHIRE, NORMAL B RAKES LOST, FLUID LEAK OUT OF RIGHT NACELLE, CONTENTS LOW ON NR 1 SYSTEM (APPROXIMATELY 0.7 QTS). FOUND OVERSPILL CAN RI GHT WHEEL WELL FULL. ENGINEERS EMPTIED AND SERVICED NR 1 & 2 SYSTEMS, CLEANED WHEEL WELL, RAN AND TAXIED AIRCRAFT, NO LE AKS NOTED, BRAKES STOPPED NORMALLY. AIRCRAFT RETURNED TO SERVICE. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001031400061 20010314 00061 NM 2001 3 14 CA001123028 1 20001109 G 5270 WARNING SYSTEM DHAV DHC8402 DHAV DHC8 DHC8* NM SERVICE DOOR FALSE INDICATION W A UNSCHED LANDING N FALSE WARNING CR CRUISE 1 CA 4025 (CAN) PILOTS REPORT: SERVICE DOOR WARNING CAME ON WHEN REACHING FL230 INTERMITTENT BETWEEN FL180-060, STEADY ON BELOW FL060.MAINTENANCE ACTION: DOOR INSPECTION CARRIED OUT AND FOUND PULL FORCE LESS THAN 10 KG, ACTION TAKEN. PULL TEST CAR RIED OUT AGAIN, POST DOOR RE-RIGGED IAW AMM 52-22-00 AND PULL TEST PASSED, AIRCRAFT RETURNED TO SERVICE. 2 H 7 2 4T RT A13NM 2001031400062 20010314 00062 NM 2001 3 14 CA001123029 1 20001103 G 6100 PROPELLER DHAV DHC8 DHC8* NM LT AND RT FAILED W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA (CAN) PILOTS FLIGHT OCCURRENCE REPORT: DURING TAKEOFF ROLL, WE DIDN'T GET A/F ARMED, ABORTED TAKEOFF AND RETURNED TO THE GATE. MAINTENANCE REPORT: MAINTENANCE LOG ENTRY FOR RECTIFICATION OF DEFECT AS FOLLOWS: REF LOG SEQUENCE NO L072 PROPEL LERS; A/F NOT ARMED UPON DEPARTURE<